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Honeywell
CommercialFlightSystemsGroupBusinessand Commuter AviationSystemsDivisionHoneywellInc.BOX 29000Phoenix,Arizona85038
SPZ-8000 Digital Automatic FlightControl System
Gulfstream IV
SystemMaintenance Manual
Volume Ill— Fault Isolation, Interconnects, Schematics,and Maintenance Practices
22-14-00TITLE PAGE T-1
PRINTED IN U.S.A. PUB, NO. A15-114638REVISED 15 APR 1993
1 JUNE 1987
PROPRIETARY NOTICE
Thisreviseddocument and the informationdisclosedhereinare proprietarydata of Honeywell Inc.Neitherthisdocument nor the informationcontainedhereinshallbe used,reproduced,or disclosedto otherswithoutthe writtenauthorizationof Honeywell Inc.,except to the extent requiredforinstallationor maintenance of recipient’sequipment.
NOTICE - FREEDOM OF INFORMATION ACT (5 USC 552)ANDDISCLOSURE OF CONFIDENTIAL INFORMATION GENERALLY (18 USC 1905)
Thisreviseddocument isbeingfurnishedinconfidenceby HoneywellInc.The informationdisclosedhereinfallswithinexemption (b)(4)of5 USC 552 and the prohibitionsof 18 USC 1905.
S93
LASEREF and PRIMLJS are registered trademarks of Honeywell Inc.
COLORCAL, COLORADAR, and LASERTRAK are additional trademarks of Honeywell Inc.
22-14-00TITLE PAGE T-2
Copyright 1993 Honeywell IncAll Rtghts Reserved
REVISED 15 APR 19931JUNE 7987
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ManualTitle
II FIAfT I PAR[a- 1 FIGIIFIFI TA131F I I
N() I GltAPlfI N(J PflWl ELI IN(I. . . .
mI
. ..— .= ~- ... F - .-.---: —-— ——-. -A =... -. —— .7----- . =-Y - --L---=-=--——— -— ----A .-. . =: -—— A - .&— A-: _ - -.. ----
—— ——-
HotJFyWl II H}.IJIY
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RECORD OF REVISIONS - VOLUME III
Upon receipt of a revision, insert the latest revised pages and dispose ofsuperseded pages. Enter revision number and date, insertion date, and theincorporator’s initials on the Record of Revisions. The typed initials HI are usedwhen Honeywell Inc. is the incorporator.
Revision Revision InsertionNumber Date Date By
Revision Revision InsertionNumber Date Date By
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Feb 1/88
Mar 1/89
Ott 1/89
Mar 15/91
Auq 15/91
Apr 1/93
Mar 1/88
A~r 15/89
NOV 15/89
A~r 15/91
Nov 1/91
Jul 1/93
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Original .. 0 .. Jun 1/87Revision .. I .. Feb 1/88Revision .. 2 .. Mar 1/89Revision .. 3 .. Ott 1/89
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Record of RevisionsRR-1/RR-2
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MAINTENANCEMANUALGULFSTREAM IV
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Interconnects (cent)584585586587588589590591592593594595596597598598.1598.2598.3598.4598.5598.6598.7598.8598.9598.10598.11598.12598.13598.14598.15598.16598.17598.18598.19598.20598.21598.22598.23598.24598.25598.26598.27598.28598.29598.30598.31598.32598.33598.34598.35
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Interconnects (cent)598.72598.73598.74598.75598.76598.77598.78598.79598.80598.81598.82598.83598.84598.85598.86598.87598.88598.89598.90598.91598.92598.93598.94598.95598.96598.97598.98598.99598.100598.101598.102598.103598.104598.105598.106598.107598.108598.108.1598.108.2598.108.3598.108.4598.108.5598.108.6598.108.7598.108.8598.108.9598.108.10
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Interconnects (cent)598.160598.161598.162598.163598.164598.164 .1/598.164.2598.165598.166598.167598.168598.169598.170598.171598.172598.173598.174598.175598.176598.177598.178598.179598.180598.181598.182598.183598.184598.184.1/598.184.2598.185598.186598.186.1/598.186.2598.187598.188598.188.1/598.188.2598.189598.190598.190.1/598.190.2598.191598.192598.192.1/598.192,2598.193598.194598.195598.196598.197598.198598.199598.200598.201598.202598.203
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SECTION 5FAULT ISOLATION
1. General
This section provides faulty component isolation information as an aid introubleshooting the System should any failure occur during GROUND CHECK.
2. Procedure
The Ground Maintenance Test Procedure (Table 301) contains a troubleshootingprocedure as part of each test. The troubleshooting procedures list theerror messages and describe what action to take for each error message.Also, Table 301 contains a Ground Test Summary, paragraph 4.5.2.11. TheGround Test Summary is a review of all failures which occurred while runningthe ground maintenance test. This review allows the operator to run theentire test and then review the failures before troubleshooting the system.This feature allows rapid identificationof subsystem failures which causedmultiple failure annunciations throughout the ground maintenance test.
Mode flow diagrams, Section 3, and interconnect information, Section 6, canbe used as aids in isolating the faulty components.
Additional information to aid in troubleshooting each subsystem is containedin the following paragraphs:
Subsvstem paraqraDh
LASEREF@ 11 Inertial Reference System (IRS)AZ-81O Air Data SystemAA-300 Radio Altimeter SystemEDZ-884 Electronic Display System (EDS)DFZ-820 Flight Guidance SystemPRIMUS@ 870 Weather Radar SystemFMZ-800 Flight Management System (FMS)Engine Pressure Ratio Transmitter
3.04.0
u7.08.09.010.O
22-14-00Page 401
Aug-15/91Use or disclosure of mformatlon on this page IS subject 10 the restrictions on the Mle page of thm documenl
3. LASEREF@ II Inertial Reference System (IRSl
A. Self-Test
Pressing either the TEST pushbutton on the mode select unit (MSU) or theTEST pushbutton on the IRU itself will cause the IRS to output testvalues. Pressing the TEST pushbutton on the MSU causes all three IRUS toenter test. The test mode ARINC 429 output values are shown in Table401. The test mode ASCB output values are shown in Table 402. The testmode outputs for the MSU and the IRU are shown in Table 403. The ISDUdisplay of IRU test mode outputs is shown in Table 404. Table 405 showsthe abbreviations for test modes.
B. System Navigation Performance Determination and Removal Criteria
Figure 401 provides removal criteria for monitoring of IRS NAVperformance. To determine system navigation performance, accuratepresent position latitude/longitude and navigation time must be known.The latitude/longitude data used to determine navigation accuracy can beobtained several ways, such as known ramp coordinates or a known point onthe airfield. With the aircraft located at such a known position, anaccurate measurement of system radial position error or drift can beobtained. The IRS position data can be obtained from the FMS, ISDU orLASERTRAK’”. The known aircraft position can then be compared to IRSposition to compute the position error. The FMS will perform this errorcalculation automatically but it must be cautioned that the IRS positionis being compared to the FMS position. Since the FMS position isutilizing other sensors (including all the IRSS) its position issusceptible to the errors introduced by these sensors. This error may beeliminated as follows:
. When the IRS position is to be checked, the FMS position should bemanually updated to the accurately known position via the positionsensor page. After the position update, the IRS status page should beselected and total IRS miles from the FMS position should be checked.
c. Reject Criteria
(1) IF the IRU radial position error falls within the grayband area ofFigure 401 (the Reject-2 Consecutive Fits region), the IRU should bechecked again, after the next flight, for a second exceedance beforeremoving. By next flight it is meant that the IRU is powered downand restarted with a full alignment prior to NAV mode being entered.
(2) If the IRU radial position error falls above the grayband area ofFigure 401 (The Reject-1 Flt region), the IRU should be removed anddoes not need to be checked twice. However, caution should beexercised before removing an IRU after only one flight to ensurethat the system error is not resulting from accidental operatorerror, e.g., incorrect initial position entry.
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Honeywell
3. D. Techniques to Improve Navigation
The
(1)
(2)
(3)
(4)
(5)
MAINTENANCEMANUALGULFSTREAM IV
Performance
following items are a general summary of operational techniques thatbe used to improve system navigation performance.
Use exact aircraft position for initialization rather than local VORor airport coordinates.
Minimize aircraft motion during alignment (also downmode align).
Perform initial system alignment using OFF-to-NAV, and then (ifnecessary) initiate a downmode alignment just prior to taxi/takeoff.If the system has not accumulated any substantial groundspeed orpresent position errors, then the downmode alignment is not neededat this time.
If possible, perform system alignment procedures with aircraftheaded in the general direction of proposed flight.
Use the total time the system is in the navigation mode (NAV TIME)when calculating position error rather than only flight time. Forthe most accurate determination of system navigation performance,the navigation time should be used for this calculation.
22-14-00Page 403
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Honeywell !&!#~.cE
Signal
Time-to-NAV ready
Present positionlatitude (inertial)
Present positionlongitude (inertial)
Groundspeed
TK angle-true
Magnetic heading
Windspeed
Wind direction(true)
True heading
IRS discretes
Present positionlatitude
Present positionlongitude
Groundspeed
Track angle (true)
True heading
Windspeed
Wind direction(true)
Track angle(magnetic)
Magnetic heading
Drift angle
)ctal.abel
007
010
011
012
013
014
015
016
044
270
310
311
312
313
314
315
316
317
320
321
Phase1
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
Phase1 TestValue
9.0
22 30.0(N)
22 30.0(E)
200.0
90.0
30.0
100.0
30.0
30.0
*
22.5(N)
22.5(E)
200.0
90.0
30.0
100.0
30.0
90.0
30.0
-10.0
Phase2
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FW
FW
FW
FW
FW
FW
FW
FW
FW
FW
Phase2 TestValue
9.0
22 30.0(N)
22 30.0(E)
200.0
90.0
30.0
100.0
30.0
30.0
*
22.5(N)
22.5(E)
200.0
90.0
30.0
100.0
30.0
90.0
30.0
-10.0
Test Mode ARINC 429 Output ValuesTable 401
Phase3
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
Phase3 TestValue
9.0
Z2 30.0(N)
Z2 30.0[E)
200.0
90.0
30.0
100.0
30.0
30.0
*
22.5(N)
22.5(E)
200.0
90.0
30.0
100.0
30.0
90.0
30.0
-10.0
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. . .- MAINTENANCE
Signal
F1ightpath angle
Flightpath accel
Pitch angle
Roll angle
Body pitch rate
Body roll rate
Body yaw rate
Body long accel
Body lat accel
Body normal accel
Platform heading
Track angle rate
Inertial pitch rate
Inertial roll rate
IRS maintenance
Time-to-NAV RDY
Cycle counter
Potential verticalspeed
Inertial altitude
Along tk horiz accel
Cross track accel
Vertical accel
3ctalLabel
322
323
324
325
326
327
330
331
332
333
334
335
336
337
350
351
354
360
361
362
363
364
Phase1
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
(+)
FT
FT
FT
FT
FT
Phase1 TestValue
-5.0
0.02
15.0(up)
5.0(R)
10.0
10.0
10.0
0.02
0.1
0.1
22.5
4.0
10.0
10.0
*
9.0
*
-600
10000.0
0.02
0.02
0.1
Phase2
FW
FW
FW
FW
FW
FW
FW
FW
FW
FW
FW
FW
FW
FW
FT
FT
(+)
FW
FW
FW
FW
FW
Phase2 TestValue
-5.0
0.02
15.0(up)
5.0(R)
10.0
10.0
10.0
0.02
0.l
0.1
22.5
4.0
10.0
10.0
*
9.0
*
-600
,0000.0
0.02
0.02
0.1
Test Mode ARINC 429 OutDut ValuesTable 401 (cent)
Phase3
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
FT
(+)
FT
FT
FT
FT
FT
Phase3 TestValue
-5.0
0.02
15.0(up)
5.0(R)
10.0
10.0
10.0
0.02
0.1
0.1
22.5
4.0
10.0
10.0
*
9.0
*
-600
10000.0
0.02
0.02
0.1
22-14-00Paqe 405
Aug-15/91UseordisclosureofInformationonihlspageIS subjecttotherestr!ctlonsonthetlllepageofthisdocument
Signal
Inertial verticalspeed
N-S velocity
E-W velocity
Body normal accel
Equipment ID
OctalLabel
365
366
367
370
371
Phase1
FT
FT
FT
FT
FT
Phase1 TestValue
-600.0
200.0
200.0
0.1
*
Phase2
FW
FW
FW
FW
FT
Phase2 TestValue
-600.0
200.0
200.0
0.1
*
Phase3
FT
FT
FT
FT
FT
Phase3 TestValue
-600.0
200.0
200.0
0.1
*
* Current data. Not affected by test mode.
Test Mode ARINC 429 Output ValuesTable 401 (cent)
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WordLength Test Value
WSP* Signal (LSB = O)** (Phase 1, 2, and 3)
1 IRS Control 16 1000OOOO***
2 Sine Pitch Angle 16 0.25883 (15°)
3 Cosine Pitch Angle 16 0.966 (15°)
4 Sine Roll Angle 16 0.5 (30°)
5 Cosine Roll Angle 16 0.86608 (30°)
6 True Heading 16 30.0’(Flag) o
7 Inertial Altitude 16 10,000 ft
8 Pitch Angle 16 15°(Flag) o
9 Roll Angle 16 5.0”(Flag) o
10 Magnetic Heading 16 30”(Flag) o
11 Inertial Vert. Speed 16 -600 ft/min(Flag) o
12 Pitch Rate 16 10.0 deg/s(Flag) o
13 Roll Rate 16 10.0 deg/s(Flag) o
14 Yaw Rate 16 10.0 deg/s(Flag) o
15 Long. Acceleration 16 0.02 g(Flag) o
16 Lateral Acceleration 16 0.1 g(Flag) o
17 Normal Acceleration 16 0.1 g(Flag) o
18 Groundspeed 16 200 kt(Flag) o
Test Mode ASCB Output Values 22-14-00Table 402 Paqe 407
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MAINTENANCE
Honeywell FMWA..
WordLength Test Value
WSP* Signal (LSB = O)** (Phase 1, 2, and3)
19 Track Angle (True) 16 90°(Flag) o
20 Flightpath Angle 16 -5.0°(Flag) o
21# Vertical Accel 16 0.1 g(Flag) o
22# Along Track Accel 16 0.2 g(Flag) o
23# Cross Track Accel 16 0.02 g(Flag) o
24# Track Angle Rate 16 4.0 deg/s(Flag) o
25# Flightpath Accel 16 0.02 g(Flag) o
26# PPOS Lat 24 22.5N27# (Flag) o
27# PPOS Long 24 22.5E28# (Flag) o
29# E - W Velocity 16 200 kt(Flag) o
30# N - S Velocity 16 200 kt(Flag) o
# On extended data field only.* WSP = Word sequence position.** Validity bit (LSB or Flag) is set to O, or invalid, in test mode.*** Least significant 8 bits are variable data specifying the IRU address
where 02 = left, 03 = right, and 04 = center.
Test Mode ASCB Output ValuesTable 402 (cent)
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Phase 1 Phase 2 Phase 3(;;;;:d;s (Second 8S (;g:;:d;s
Annunciator Signal Period)
MSU Annunciators
ALIGN On Original state Original state
FAULT On Original state Original state
NAV RDY (Six-annunciator MSU On Original state Original stateonly)
NO AIR (Six-annunciator MSU On Original state Original stateonly)
ON BATT On Original state Original state
BATT FAIL On Original state Original state
IRU Annunciator
Fault ball Original state Original state Original state
Test Mode OutputsTable 403
Parameter Test Value (All Three Phases)
Track 90”
Groundspeed 200 kt
Latitude N 22° 30.0’
Longitude E 22° 30.0’
Wind direction 30”
Windspeed 100 kt
True heading 30°
Time-to-NAV Current data
ISDU Dis~lav of IRU Test Mode OutDuts.-Table 404 22-14-00
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Abbreviation Definition Abbreviation Definition
DS Do not send NCD No computed data
FL Light flashing o Original value
FR From OFF Light off
FT Functional test ON Light on
FW Failure warning T True
I Invalid TV Test value
L Lamp v Valid
M Magnetic z Null output
N Normal operation
Abbreviations for Test ModesTable 405
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40
35
30
25
RADIAL 20POSITIONERROR(nml) 15
10
5
00 1 2 3 4 5 6 7 8 9 10 11 12
NAV TIME (hours)
RejectCrfterfa:1)IftheIRUradialpositionerrorhlfswithinthe“Grayband” ~dlalPoaltfnError~: Distancebetweenaccurateknown aircraft positionandtheareaofthechart(the“Rejecf-2ConaewtiveFfts”region),theIRU dispfayadlRS”pftion as takenfromtheFMS,ISDUor’LASERTRAK’N.IttheFMS “IRSStatusshouldbechac+wfagainafterthenexlflightforasecond Page’isusedtoobtaintotalpositionerror,theFMS poehkrnshouldbemanually updatedtotheexc9edarrcebeforerernrwhg. accurateknownpositionprfortoreadingerror.2)tftheIRUradialpositionerrorfallsabovethe‘Grayband”areaof ~ ThetotitimethattheSystem hasbeeninthe navigate mode until the time when thethe dwl (the “Rejed-1 Ftf regbn), the IRU should be removed and systempositbn is taken to cxxnpute position error, This indudas grwnd time if in navigate mode.does not need tobec&&ad h%+%.However,cardionshouldbeexerdsedbeforeremovinganIRUafteronlyoneftighttoensurethatthesystemerrorisnotresultingfromacddentaloperatorerror.e.g.:Incorrectinitial position entry
IRU Performance Removal CriteriaFigure 401 22-14-00
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MAINTENANCE
Honeywell $%%..4, AZ-81O Air Data System
A. DADC Functions
(1) The DADC will output test values when the self-test select pin,JIA-52 is grounded. The DADC self-test expected output values(analog outputs) are shown in Table 406. The DADC ARINC 429self-test expected output values are shown in Table 407. The DADCASCB self-test expected output values are shown in Table 408.
(2) The DADC cabin pressure ratio output is shown in Figure 402.
(3) The FAA V~O function for the Gulfstream IV is shown in Figure 403.
(4) The CAA V~O function for the Gulfstream IV is shown in Figure 404.
(5) The low-speed static source error correction (SSEC) is shown inFigure 405 and the high-speed SSEC is shown in Figure 406.Technical Newsletter, Pub. No. 23-1980-04, Revision 7, contains theSSEC information to test the DADC for compliance with FAR 91.171 andFAR 43.
B. Altitude Preselect Operation
The desired altitude is selected in this mode by slewing via the APS knobon the guidance panel to the desired value. No further action isrequired. To arm altitude preselect, either IAS, V/S, MACH, or pitchhold is selected as a mode to fly to the selected altitude. When outsidethe altitude bracket trip point, the APS ARM annunciator is illuminatedalong with the selected vertical mode. When reaching the bracketaltitude, the system automatically switches to the APS CAP mode and theactive pitch mode is cancelled. At bracket, a command is generated toasymptotically capture the selected altitude. When the altitude isreached, the APS CAP is automatically cancelled and switched to the ALTHOLD mode. If the air data computer is not valid, the altitude preselectmode cannot be selected.
Figure 407 illustrates the operation of the altitude alerting system. Asthe aircraft approaches the selected altitude, a single momentary (0.5 to1.0 second) ground is provided at 1000 feet for an audio alerting device,and the amber alert light on the altimeter is illuminated. The alertlight remains illuminated until the aircraft is within 250 feet of theselected altitude where it is extinguished. No warning signals aregenerated within 250 feet of the selected altitude. If the aircraftshould subsequently deviate from the selected altitude, a singlemomentary ground is provided at 250 feet deviation and the alert light isilluminated. The light remains illuminated until a deviation of 1000feet is recorded, then it is extinguished.
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Parameter Self-Test Value
Altitude Switch Set
V~OWarning off
Air Data Valids Invalid when self-testinput is grounded
DADC Self-Test Analog OutputsTable 406
Parameter Self-Test Value Units
Pressure Alt 4000 feet
Baro Corr Alt 1000 feet
Alt Rate 5000 feet
CAS 350 knots
TAS 466 knots
Mach No. 0.790 Mach
TAT -16 “c
SAT -45 “c
vMo 300 knots
Baro Corr (rob) 1013.3 millibar
Baro Corr (inHg) 29.921 inHg
Total Pressure 1083.6 millibar
Overspeed Warning off ---
Normal AOA 0.5 ratio
Selected Altitude 12,000 feet
DADC Self-Test ARINC 429 OutputsTable 407
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Parameter Self-Test Value Units
Pressure Alt 4000 feet
Baro Corr Alt 1000 feet
Alt Rate 5000 feet per minute
CAS 350 knots
TAS 466 knots
Mach No. 0.790 Mach
SAT -45 “c
TAT -16 “c
vMo 300 knots
MMo 0.880 Mach
Impact Pressure 9 inHg
Total Pressure 32 inHg
Baro Set 1013.3 millibars
Baro Set 29.921 inHg
V~oWarning off ---
Altitude Alert Lamp off ---
Normal AOA 0.5 ratio
True AOA 5 degrees
Valids invalid ---
NOTE: In self-test, test bit in WSP1 is set.
DADC ASCB Self-Test OutputsTable 408
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.—
..-
—.
—.—
.,,.
_.
10 20 30 40
I
ID
ALTITUDE X 1000 FEET AD-10279
Cabin Pressure Ratio OutputFigure 402 22-14-00
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MAINTENANCE
Honeywell !!H!!!+A&.
60
5150
43.5
40
34
3027.86
20
10
0
J’-.004Mil\h
x
#
D——
m---
m— —-
DO FT.
MMO s 4.886 X 10-6 X SSECAE
-d J,I
I “e% /’‘p-= NJ /’=0”8’0y—
7
I
II1—~
I
I II
I1 .
200 240249 280 309320 340
.— 1 ——. —
~M = f(~SEC
360 400
+0.7139
LT, CAS)
COMPUTED AIFISPEED - KNOTS AD-16232
The M~o value for SSEC altitudes below 27,860 feet is a function of the SSEC.-altitude and 340 knots of CAS.
FAA VHO Function for the Gulfstream IVFigure 403 22-14-00
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60
50
4543.5
40
34
30
20
10
FOR ALT >51,000 FT. THE Mmo SLOPE
/
CONTINUES BASED ON ALTITUDE/MmoRELATIONSHIP ESTABLISHED BETWEEN 45,000 AND 51,000 FT
Mmo VARIES LINEARLY FROM
,-----IIII
I-1 I.. -—- ---— ----- -— -- —
II -4--–––-–—-—--–— --– —-:– —-–
I II I
II i 1
:I I
I ;I I
II
II
II I I
} I 1 II I I
I I I II I I II I II ; I II I 1I I I II
;I
I
1I
I I II
1 I II
I III
1I
1 I 1 1 1 1 1I180 I 2(JO I 2401 280 I
19;.3 2i2.1 24>.3 ioi.5
COMPUTED AIRSPEED - KNOTS
NOTE: THE Mmo VALUE FOR SSEC ALTITUDES BELOW 30,000 FEET ISA FUNCTION OF THE SSEC ALTITUDE AND 320 KNOTS OF CAS,
I
o
AD-18481
The M~O value for SSEC altitudes below 30,000 feet is a function of the SSECaltitude and 320 knots of CAS.
CAA VMO Function for the Gulfstream IVFigure 404 22-14-00
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Honeywell !/&!g~.cE
0.200.190.180.170.160.150.14
9 0.13r
G-IV STATIC SOURCE ERROR CORRECTION“LOW SPEED” RANGE (FUNCTION OF AOA)
~ (3,12.
~ o.11-~ o.lo-
G 0.09-~ 0.013-
0!! o.07-4 0.06-
0.05-0.04-0.03“
(.35
T /(.55,.155)
. (.50,.12!
I(.45,.0965)
“ (.40,.072)
)515)
(.25,.024)
I(.30,.037)
0.02i (.1901) I
0.01 — — (.20,.012)o.oo’!- [ I
(.60,.194)
o 0.2 0.4 0.6
AOA VoltageRatio(AOA PROBE) AD-16229
[1& A PSNOTE: True P~ = PSI PSI +QCI QCI
QCI = indicated QC
PSI = indicated P~
A PSQCI is calculated according to the graph above.
Ps~ is calculated according to the graph on Figure 406.
[Ps— = 1 when Mach <0.886PSI )
This correction curve is used at all Mach numbers.
SSEC (Low-Speed Range) for the Gulfstream IVFigure 405 22-14-00
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1.01
r1- -——
o.99-
0.98-
0.97-
0.96-0%/
o.95-
0.94-
0.93,0.85
31=1
&NOTE: True P~ = (PSI) PSI
PSI = indicated P~
QCI = indicated QC
o
1
OR MAC H C.886 (.9”
(.92,.93442)I
(.90,.9;
.95493)1
42)
7 0.89 0.91
lNDICATED MACH AD-16230
APS+ QCI QCI
&QCI is calculated accord
— is calculated accord”Q:;
This correction curve isthan or equal to 0.886.
ng to the graph on Figure 405.
ng to the graph above.
used when indicated Mach number is less
SSEC (High-Speed Range) for the Gulfstream IVFigure 406 22-14-00
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+ 1000 FT
+250 FT
O FT
-250 FT
-1000 FT
..
I ALERT LIGHT(S)F (+ 1020 FT:) -
I
-.—.——— --—-
DEPA
‘TUREALERT LIGHT(S) OFF
-------k< ----------------------\
— .—
AUDIO-.—— .—— —
‘TURE
ALERT LIGHT(S) OFF(- 230 FT.) \ SELEI—
ALERT.—— ——— —
/ALERT LIGHT(S)ON
-——— —-—— -——. —___ ____ _,
ON UNTIL /
RESET
Altitude Alerting SequenceFigure 407
DEPA
----
AD-1 1664-R2
22-14-00
----
TED ALTITUDE
——
iTURE
——
I
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4. C. Angle of Attack (AOA) Operation
The air data computer receives information in the form of discrete inputs(flaps position discretes), analog input (Teledyne angle of attackpotentiometer) and digital bus inputs (AOA indexer set and test modecommands from the display controller). The DADC performs calculationsand comparisons, and outputs information in the form of discrete out uts
Y(indexer switch discretes and test mode switch discretes) and digita busoutputs (true AOA on ASCB, normal AOA on ASCB and ARINC 429, and flapposition discretes on ASCB). These outputs are used by the symbolgenerator for display on the EFIS to drive indexer lamp indicators andannunciate AOA test modes to other system components. Figure 408 is ageneral block diagram ofDADC AOA 1/0.
. AOA Test Mode Operation
Two test modes are commanded by the display controller: (1) AOA sealevel test and (2) AOA 15,000 feet test. In the test mode, a discreteswitch called AOA test mode switch is set in combination with (1) AOAsea level test switch or (2) AOA 15,000 feet test switch to indicatetest mode status. In AOA sea level test, the pressure altitude outputis driven to 0.750 V dc which is the sea level altitude outputvoltage. In the AOA 15,000 feet test, the pressure altitude output isdriven to 3.750 V dc (sea level) altitude output voltage. In eitherAOA test the potentiometer and flap position inputs and relatedoutputs operate normally.
D. DADC Red X Failures
There are a number of items listed belowto red X on the primary flight display.
(1)
which will cause air data items
AOA Probe - The air data computer receives angle of attackinformation from the on-side AOA probe. The computer uses thisinformation to compute normalized angle of attack and to calculatestatic source error correction (SSEC). SSEC is applied tobare-corrected altitude, calibrated airspeed, Mach, and trueairspeed. If AOA information goes invalid, the following is eitherred X or amber dashed on the primary flight display or thenavigation display:
● Angle of Attack. Airspeed. Mach● Altitude● True Airspeed
The AOA information comes from one of the four potentiometers whichare mechanically connected to the AOA probe. The air data computermonitors this information to check that it is within a valid voltagerange. If the probe is rotated against either its up or down stops,or if the potentiometer has open spots (dead spots) at certainpositions, the air data computer will sense this and invalidatethe AOA information. Note that the vertical speed display does notred X.
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LAMPPOWERr 1
INDEXERI I
‘~ ‘$+
EFIS DISPLAYS
(=
vDISPLAY NORMAL AOA
INDEXER SET
FLAPPOSITION o
DISCRETES AI I I
J.——A2B1ODADC
I i - “’”RDISPLAY
CONTROLLER
TELEDYNEAOA
POTENTIOMETER
IAOA INDEXER SETAOA SL TEST COMMAND
AOA INDEXER SET
t :/
NORMAL AOAAOA 15 KFT TEST COMMAND
AOA SL TEST COMMAND TRUE AOAAOA 15 KFT TEST COMMANO FLAP POSITION
)’tASCB
AD-307m
INDEXER SET
-
DADC AOA Block DiagramFigure 408
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4. D. (2)
(3)
(4)
(5)
(6)
Flap Position - The air data computer receives flap position fromfour discretes which are tied to the flap handle switches in thepedestal. The computer uses the information to calculate normalizedangle of attack. If flap position information goes invalid, theangle of attack display on the primary flight display will red X.~~~t[~ap position information is monitored to check for valid input
If the computer sees no flap position (i.e., flap handlebetwee; selections) or more than one flap position at the same time,the air data computer will sense this and invalidate the flapposition information, thus invalid AOA.
Total Air Temperature Probe - The air data computer receives totalair temperature from the temperature probe. The computer uses theinformation to calculate total and static air temperature, and trueairspeed. If air temperature information goes invalid, the staticair temperature (SAT) and the true airspeed (TAS) on the navigationdisplay will indicate amber dashes. The air temperature probeinformation is monitored for reasonableness and if the temperatureexceeds 99 “C for 5 consecutive seconds, the air data computer willinvalidate the air temperature information. The autopilot needstrue airspeed for engagement.
Bare-Correction - The air data computer receives bare-correctionfrom the baro knob potentiometer of the display controller. If thebare-correction input goes invalid, the displayed altitude will redX and the baro set display will indicate amber dashes. Thebare-correction is monitored to check that it is between 28.00 to31.00 inHg. If the baro set goes outside of this range, the airdata computer will sense this and invalidate it. An invalid baroset will occur if the knob is rotated against either stop or if thedisplay controller is disconnected.
EPR - The air data computer provides CAS and total pressure tothe EPR transmitters. Loss of this data to the EPR transmitterwill result in the EICAS message EPR 1 USING DADC 2 or EPR 2 USINGDADC 1.
Internal Failures -The air data computer has a number of internal.. . .monitors which check to insure items internal to the LRU areoperating properly (e.g., pressure sensors, power supply, aircraftID input discretes, etc). If the computer senses one of these, itwill normally flag all the following outputs.
●
●
●
●
●
●
●
●
●
Angle of AttackAirspeedMachAltitudeTrue AirspeedVertical SpeedStatic Air TemperatureBarometric CorrectionCabin Pressure Ratio
EICAS will display DADC 1 (2) FAIL and EPR 1 USING DADC 2 or EPR 2USING DADC 1 as appropriate.
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5. AA-300 Radio Altimeter Svstem
A. Preflight Test
(1) Rotate SET knob on the DC-884 Display Controller, with RAD ALTselected on the FLT REF menu, to set bug to 50 feet.
CAUTION: UNDER NO CIRCUMSTANCES SHALL POWER BE TURNED ON WITHTHE TRANSMIT ANTENNA DISCONNECTED FROM THETRANSMITTER OR DAMAGE TO THE TRANSMITTER MAY RESULT.
(2) ~u~n50;e;;stem power. The RAD ALT display on the PFD shall indicate.
(3) Select the TEST menu on the DC-884 Display Controller. Press andhold the RAD ALT line select button. The RAD ALT display on the PFDshall indicate 100 t 10 feet, and the DH annunciator shall not belit.
(4) Release the line select button. The RADALT display on the PFDshall return to O t 5 feet, and the DH annunciator shall light.
B. In-Flight Test
NOTE: The self-test feature is inhibited with autopilot engagements,
(1)
(2)
(3)
(4)
(5)
so the autopilot must be temporarily disengaged before-performingin-flight tests.
Verify that no amber dashes are present in the RAD ALT display onthe PFD and the display blanks when the aircraft climbs above 2500feet absolute altitude.
~: RAD ALT display will blank below 2500 feet if the groundreturn signal is lost. The display may blank momentarilywhen the aircraft is in a bank in excess of 45 degrees (thisis normal).
Rotate SET knob on the DC-884 Display Controller with RADALTselected on the FLT REF menu to select a DH of 200 feet.
Press and hold the line select button labeled RAD ALT on the TESTmenu. The RAD ALT display shall indicate 100 t 10 feet, and the DHannunciator shall light.
Release the line select button. The RAD ALT display shall return tothe previous indication.
Rotate SET knob to desired position with RAD ALT selected on the FLTREF menu of the DC-884 Display Controller.
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6. EDZ-884 Electronic DisDlay System [EDS~
Il. Trend and Limit Monitoring
(1) Overview
The trend and limit monitoring portion of the FC-880 Fault WarningComputer (FWC) acts as a data acquisition and storage system forrecording aircraft, engine and APU data under various circumstancesand requirements. This function operates automatically usingpassive (no operator interface required) recording techniques. Anoption for an operator-initiated recording is also provided.
Engine trend data recording consists of a set of engine and aircraftparameters recorded during steady state flight (cruise) and duringtakeoff. APU data is recorded just prior to the first engine startof a flight. This type of recording is used to monitor thelong-term histories and relative health of the aircraft engines andAPUs.
An engine limit exceedance triggers the recording of sequential setsof engine and aircraft parameters. This sequential set ofparameters includes pre- and post-exceedance data points in order toproduce detailed time vs. parameter value plots of an engineexceedance. Likewise, an APU exceedance triggers the recording ofsequential sets of APU and aircraft parameters. Also, the operatorwill be able to manually trigger a recording of engine and aircraftdata of the same format as an exceedance.
Data extraction is the responsibility of the aircraft operator/manufacturer and is easily performed using a dedicated output fromthe FWC. This output directly interfaces to the DL-800/900 DataLoader using a standard RS-232 bus format. All data processing willbe done via a ground-based system chosen by the aircraft operator/manufacturer.
The memory to record trend and limit exceedance data is nonvolatileEEPROM requiring no hold-up power. 64K bytes of memory is allocatedfor trend and limit recording with provisions for an additional 64Kbytes of memory included for growth. The FWC maintenance testcontains a message indicating EEPROM memory usage.
The engine and aircraft parameters to be recorded in both trend andlimit exceedance monitoring, along with their associated acronyms,are listed in Table 409. APU parameters are listed in Table 410.The range and resolution of each parameter recorded is identical tothat transmitted by the DA-880 Data Acquisition Unit (DAU) and usedfor engine instrument and other displays.
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Acronym Parameter
TGT Turbine Gas TemperatureLP (Nl) Low Pressure Tacht&(N2) High Pressure Tach
Engine Pressure RatioFF Fuel FlowTVI Turbine Vibration Indication (LP, HP)EOT Engine Oil TemperatureEOP Engine Oil PressureFQ Fuel QuantityWAI Wing Anti-iceEAI Cowl Anti-iceSvo Start Valve Open/ClosedGMT Greenwich Mean TimeDATE Day, Month, YearMACH Mach NumberALT Pressure AltitudeCAS Calibrated AirspeedLATERAL MODE ~ Lateral Autopilot ModeVERTICAL MODE - Vertical Autopilot ModeAT MODE Autothrottle ModeAOA Angle of AttackSAT Static Air TemperatureBLC)P Bleed Air PressureSTARTS Number of Engine Starts
Enqine and Aircraft Trend and Limit Exceedance ParametersTable 409
Acronym Parameter
APU EGT - APU Exhaust Gas TemperatureAPU RPM - APU Rotor SpeedBLDP Bleed Air PressureGMT Greenwich Mean TimeDATE Day, Month, YearALT Pressure AltitudeSAT Static Air Temperature
APU Recording ParametersTable 410
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Unless otherwise specified, all data is retrieved from the selectedDAU channel, as indicated by the DA-884 Display Controller; NZ-9XX(l), if valid, otherwise NZ-9XX (2); DADC (l), if valid, otherwiseDADC (2); IRS (l), if valid, otherwise IRS (2); the priority FZ-820FGC; the priority PZ-800 (AT); and the priority PZ-800 (Perf). Ifan automatic switch to another source is not allowed, as with theDAU, FGC, Perf, and AT, and the device is invalid, zeroes will berecorded. This scheme also allows for data source mixing. Forexample, to determine steady state conditions, Mach may be takenfrom DADC (1) while altitude is taken from DADC (2).
6. A. (2) Trend Recording
Engine data from two different flight conditions are recorded fortrend analysis: cruise and takeoff. Cruise condition recordingsprovide a meaningful historical trend of engine performance.Takeoff data provides a basis for assessing engine margindeterioration.
Takeoff data is recorded when the aircraft reaches 100 knots duringthe takeoff roll for every flight. Takeoff data is recordedregardless of the steady-state criteria or weight-on-wheelsindication. The enabling logic for the 100 knots trend recording isvalid airspeed > 100 knots from both DADCS and valid groundspeed >50 knots from the NZ-9XX Navigation Computers (NZ). Default to NZ 1groundspeed if NZ 1 is valid and groundspeed is valid (WSP 8, bitO), otherwise use NZ 2 groundspeed if valid and groundspeed isvalid. If neither is valid, disable the 100-knot trend recording.
The aircraft and engine parameters which define cruise, theirorigin, and associated allowable deviations or tolerances about afixed value are listed in Table 411. Data sources for theseparameters are as previously discussed. Failure of all sources fora parameter used to determine steady state results in suspension ofthe trend recording function.
A flight’s first cruise trend recording is made at the firstinstance the steady-state flight conditions are satisfiedimmediately following the takeoff recording. Cruise trendrecordings are taken at approximately one and one-half (1-1/2) hourintervals following this initial recording. Steady-state flight, asdefined in Table 411, must be satisfied prior to a cruise trendrecording with weight-on-wheels used to inhibit any trend recordingduring nonideal conditions such as engine runs on the ground. Aground state on FWC J1A-1OO causes trend data to be recorded at5-minute intervals. The FWC enables a blue TREND RECORD messagewhenever trend data is recorded with J1A-1OO grounded.
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The specific method of recording engine and aircraft parametersrequires the use of two recording techniques: snapshot and picture.A snapshot is defined as a single frame, or value, of a specificparameter at a given point in time. The FWC records snapshot databy placing the current value of a parameter in nonvolatile memory.A picture is formed by computing the average of a parameter over al-second period. The number of values which make up the averagedepends on the density of that parameter on the ASCB. The FWCrecords picture data by placing the computed average value of aparameter in nonvolatile memory. Engine parameters are recorded aspictures and accounting or aircraft configuration parameters arestored as snapshots.
Table 412 lists the parameters recorded and which type of recordingis required. The particular data source for each parameter is aspreviously defined.
The FWC maintains an engine starts log. An engine start is definedas the transition of the left and right SVO discretes from O to 1.The engine start count is incremented each time both SVO discretestransition from O to 1. The source of the SVO discretes is theselected DAUS. Failure of either selected OAU channel results inloss of engine start data for the current flight. The engine startcount is reset to O when EEPROM is erased.
APU trend data is recorded just prior to the first engine start ofeach flight. The logic to enable an APU trend recording isweight-on-wheels active and the transition of either SVO discretefrom O to 1. As before, the SVO discretes are retrieved from theselected OAU. Failure of both selected OAUS results in loss of theAPU trend function. APU trend data is stored using both the pictureand snapshot techniques. Table 413 lists the APU parametersrecorded, which type of recording is required, and the data source.The FWC uses a quasi endless-loop technique to compute and retain acurrent picture of various APU parameters. The current APU pictureplus snapshot data is moved to nonvolatile memory at the time theAPU trend recording is enabled.
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I Allowable DeviationsParameter Data Source (Deltas) I
Vertical Acceleration IRS fo.lo”gMach Number DADC 10.05Pressure Altitude DADC t200 ftTotal Air Temperature DADC ~5.1)“cHP (L) DAU *2.0%IHP (R) DAU i2.o%
Steady State Flight Condition ParametersTable 411
PictureParameter (Average) Snapshot Data Source
RECORDING TYPE x FWCTGT (L,R) x DAUEPR (L,R) x DAULP (L,R) x DAUHP (L,R) x DAUFF (L,R) x DAUEOT (L,R) x DAUEOP (L,R) x DAUTVI, LP (L,R) x DAUTVI, HP (L,R) x DAUBLEED AIR PRESS (L,R) X DAUSVO (L,R) DAUWAI (L,R) i DAUEAI (L,R) x DAUFQ x DAUDATE x FMSGMT x FMSALT x DADCCAS DADC:WJ (NORM) : DADC
x DADCMACH x DADCLATERAL MODE x FGCVERTICAL MODE x FGCAT MODE x ATSTARTS FWCCHECKSUM : FWC
Engine Trend Data Recording ParametersTable 412
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Honeywell !ff!!~.c’
PictureParameter (Average) Snapshot Data Source
RECORDING TYPEAPU EGT xAPU RPM xBLEED AIR PRESS (L,R) XGMTDATEALTSATCHECKSUM
x FWCDAUDAUDAU
x FMSx FMSx DADCx DADCx FWC
APU Trend Recording ParametersTable 413
6. A. (3) Engine and APU Limit Exceedance Recording
Limit exceedance recording permits the aircraft and enginemanufacturers to accurately-determinethe health of engines after alimit exceedance. The aircraft operator is able to review a portionof the data associated with the last exceedance detected sincepower-up. This operator-accessibledata includes maximum value andtime duration of an exceedance and is available on the EXCEEDANCEsystem page of the crew alerting system display. This sameinformation is also included in the complete nonvolatile memory datapackage.
The limit exceedance recording includes a data package sufficient todetermine the events occurring prior to, at, and immediately afterthe exceedance. For accounting purposes the time (in GMT) and dateof the event are also included in the data package. To complete thedata package, the maximum values attained at any time during theexceedance and duration of each exceedance are also recorded. Asboth pre- and post-exceedance data points are recorded, this data issuitable for creating time vs. magnitude history plots of anexceedance.
Table 414 lists the specific conditions for exceedance eventrecognition. The source of data is as previously discussed.
An exceedance event commences with any one of the enablingconditions listed in Table 414. The exceedance continues until allparameters have satisfied their disabling conditions listed inTable 414 or until 5 minutes has elapsed, whichever occurs first.
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Type Parameter Data Source Limit (Enable Exceedance) Disable
Engine
Engine
Engine
Engine
Engine
Engine
Engine
Engine
Engine
LP
LP
HP
HP
HP
TGT
TGT
TGT
Engine Fire
DAU
DAU
DAU
DAU
DAU
DAU
DAU
DAU
DAU
LP > 95.5, 20 sec LP s 95.0
LP > 98.3, 500 ms LP s 95.0
HP > 97.5, 5 min HP g 97.0
HP > 99.7, 20 sec HP s 97.0
HP > 102.7, 500 ms HP g 97.0
TGT > 715, 5 min TGT s 710
TGT > 800, 20 sec TGT s 710
TGT > 820, 500 ms TGT g 710
ASCB bit = logic 1-and-
A/S > 60 kt(500 ms)
bit = logic O-or-
A/S s 60 kt
Engine OperatorRequest
FWC FWC JIA-81=open toground transition
(500 ms)
JIA-81=open
APU APU Fire DAU ASCB bit = logic 1-and-
A/S > 60 kt(500 ms)
bit = logic O-or-
A/S s 60 kt
Parameters Monitored for Exceedance Event RecordingTable 414
An operator-requested engine exceedance recording input is included.This input consists of a cockpit or avionics rack-mounted momentarypushbutton. The pushbutton provides a ground state on FWC JIA-81.The FWC enables an engine exceedance recording in response to anopen-to-ground transition on this input. The FWC monitors maximumvalues and time-in-exceedance for 25 seconds or until 5 minutes haselapsed, whichever is shorter. Recordings made in response to thisinput are so noted in the trigger source byte included in eachexceedance data package.
The FWC enables a timed 5-second blue ENGINE EXCEEDANCE message whenan engine exceedance is detected, and a timed 5-second blue APUEXCEEDANCE message when an APU exceedance is detected.
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Honeywell !!!!!5.”There are six types of recording techniques used to accumulate thelimit exceedance data package. They are:
. Snapshot recording
. Picture recording● Endless-loop recording● Time-in-exceedance recording● Maximum value recording. Short-term display recording (volatile memory only)
The principle technique used to form the limit exceedance datapackage is endless-loop recording. Endless-loop recording makes useof both picture and snapshot data to compile data points before andafter an exceedance to permit formation of time vs. parameter valuehistories. In particular, a record of parameter values for the past15 seconds is maintained in volatile memory. Upon detection of anexceedance, an additional 10 seconds of parameter values are storedin volatile memory. The entire 25-second history is transferred tononvolatile memory. The fifteenth record is the data point whichrepresents a picture of the parameter value at the time of theexceedance.
Accumulation of the 15-second past-history data is accomplished bycontinuously updating a series of 15 sequential pictures recorded atl-second intervals. Each picture shall be the average of theparameter values over a l-second period. Data recorded during the10 seconds following the detection of an exceedance is done in thesame manner.
The time-in-exceedance recording method is used to create a recordof the amount of time a parameter remains in its exceedance band.The FWC records the total amount of time a parameter is in itsexceedance band during any given exceedance event. The FWC makesonly one recording per parameter per exceedance event.
Maximum value recording requires the FWC to determine and store themaximum value a parameter attains during an exceedance event. TheFWC continuously monitors specific parameters during each exceedanceevent and stores in nonvolatile memory each maximum value achieved.
The short-term display recording consists of placing specificexceedance data in volatile memory for immediate recall and displayby the operator. The FWC retains the maximum value and time-in-exceedance data of the most recent exceedance experienced sincepower-up. In addition, the source of the exceedance trigger isincluded with this data. This data is recalled and transmitted viathe ASCB system page buffer in response to the display controllerselection of the exceedances system page. The time-in-exceedancedata is displayed as 1 second for times less than 1 second and isrounded to the nearest second for times greater than 1 second.Figure 409 shows the format of the EXCEEDANCE system page. The FWCenables a white NO EXCEEDANCES RECORDED message for display on theEXCEEDANCES page when no exceedances have been recorded.
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EXCEEDANCES
ENGINE EXCEEDANCEMAX-TIME
TGT: 0000 0:00 0000 0:00LP: 000.0 0:00 000.0 0:00HP: 000.0 0:00 000.0 0:00TRIGGERED BY: XXXXXXX
APU EXCEEDANCEMAX
EGT: 0000RPM: 000.0TRIGGERED BY: XXXXXXX
Exceedance System Page FormatFigure 409
To properly correlate the event, specific accounting parameters mustbe included in the exceedance data”package. Table ~15 lists theparameters to be recorded during an engine exceedance and the typeof recording to be used. Table 416 lists the parameters to berecorded during an APU exceedance and the type of recording to beused.
The FWC includes a trigger source byte in each exceedance datapackage. This byte indicates the parameter responsible fortriggering the exceedance recording (i.e., L TGT, R HP,operator, etc.).
Exceedance events are limited in the FWC to occur no more frequentlythan once every 25 seconds. This guarantees the FWC will gather the10-second post-exceedance data for the current event and the15-second pre-exceedance data for the next event.
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Honeywell !#!!!!&.cE
Type of RecordPre-Event/Post-Event Time in
Parameter Endless-Loop Snapshot Max Value Exceedance Data Source
RECORDING TYPE x FWC~~T(&~) x x x DAU
DAUHP (L,R) ; : 1 DAUEPR (L,R) x DAUFF (L,R) DAUEOT (L,R) ! DAUEOP (L,R) DAUTVI, LP (L,R) i DAUTVI, HP (L,R) DAUBleed Air Press (L,R) ~ DAUSVO (L,R) x DAUWAI (L,R) x DAUEAI (L,R) x DAUFQ x DAUDATE x FMSGMT x FMS
x PERF;;T DADCCAS i DADC~1$ (NORM) x DADC
x DADCMACH x DADCLATERAL MODE x FGCVERTICAL MODE x FGCAUTOTHROTTLE MODE x ATTRIGGER SOURCE FWCCHECKSUM i FWC
Engine Exceedance Recording ParametersTable 415
Type of RecordPre-Event/Post-Event
Parameter Endless-Loop Snapshot Max Value Data Source
RECORDING TYPE x FWCAPU EGT x x DAUAPU RPM x DAUBleed Air Press (L,R) ~ DAUGMT x FMSDATE FMSALT ; DADCSAT DADCCHECKSUM i FWC
APU Exceedance Recording ParametersTable 416 22-14-00
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6. A. (4) FC-880 Fault Warning Computer (FWC) Data Download Requirements
The contents of EEPROM are transmitted outside the FWC by means ofan RS-232 data link. The requirements to perform the download areas follows:
. Weight-on-wheels
. IAS < 50 knots on either valid DADC or both DADCS invalid
. Not in maintenance test
● JIA-86 = GND
. Debounced for 500 ms
● DL-800/900 Data Loader connected/powered on
. 3-1/2-inch floppy disk installed in DL-800/900 with write-protecttab in view
NOTE: Both FWCS may go invalid while the DL-800/900 formats thediskette. The FWC not being downloaded will become validwhen formatting is complete.
Upon completion of download, an internal flag is set that enablesthe memory to be erased. The requirements for memory erase are asfollows:
. Weight-on-wheels
● IAS < 50 knots on either valid DADC or both DADCS invalid
. Download complete
c JIA-68 = GND
. Debounced for 500 ms
Memory erasure is accomplished by storing zeroes in all memorylocations.
A DOWNLOAD IN PROGRESS 28V/OPEN discrete output is provided onJIB-94. The output is set to 28 V when a download is in progress,otherwise the output is set to OPEN.
An ERASE IN PROGRESS 28V/OPEN discrete output is provided on JIB-95.The output is set to 28 V when an EEPROM erase is in progress,otherwise the output is set to OPEN.
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The data loader/fault warning interface isInterconnects,Table 501.
shown in Figure D-2.4 of
Refer to paragraph 6.A.(5) for the FC-880 FWC trend and limitdownload procedure.
6. A. (5) FC-880 FWC Trend and Limit Download Procedure
~: Refer to paragraph 6.A.(4) for download requirements.
(a) Setup
~ Apply electrical power to A/C.
~ Power-up all display units.
a Perform FWC memory usage EEPROM bit test, as required.
~ Connect DL-800/900 Data Loader to connector on copilot’sconsole.
CAUTION: DO NOT USE FLOPPY DISK ON WHICH DATA DOWNLOADALREADY ACCOMPLISHED. DATA LOADER WILL ERASEALL PREVIOUS DATA.
~ Place a 3-1/2-inch floppy disk in data loader.
NOTE- Ensure that write protect tab on disk is closed (hole is‘“ covered) or that disk is not a write protect disk.
(j Ensure data loader ON and DATA lights are illuminated.Position of selector switch on data loader does not affectdata download.
(b) Procedure
~ Select FWC #1 or FWC #2 on R/H side monitor panel switch.
~ Select, as desired, FWC #1 or FWC #2 on sensor page ofeither DC-884 Display Controller.
~ On R/Hmonitor panel, press to test and verify DNLOAD INPROGRESS (blue) and ERASE IN PROGRESS (yellow) lightsilluminate.
~ Press and hold the DATA DNLOAD switch for approximately1 second. Ensure that CAS display has a red X and DNLOAD INPROGRESS light illuminates for duration of download (solidblue light).
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Honeywell #~~#$YENOTES: 10 If DNLOAD IN PROGRESS light is flashing after being
6. A. (5) (b) S
selected, remove disk. Either the write protecttab is not closed, or a bad disk is installed.Reset both FWC circuit breakers and any otherbreakers required due to erroneous messages.Assure that write protect tab is closed or thatproper disk is installed, and repeat steps ~ thru ~of procedure.
2. The FWC being downloaded will display a red Xduring download process. The off-side FWC willhave a red X only during formatting of data disk(approximately 3 minutes). Side being downloadedwill annunciate fail on CAS.
After DNLOAD IN PROGRESS blue light extinguishes, removedisk from data loader. Open write protect tab on data disk,if applicable. Label disk with A/C serial number, FWCposition, and date downloaded (e.g., 1163.#1.040891).
Press and hold the TREND ERASE switch (on the R/H monitorpanel) for approximately 1 second. Ensure ERASE IN PROGRESSlight (yellow) illuminates for duration of erase function(approximately 3 minutes).
Repeat all steps for opposite side FWC. Ensure a new floppydisk is inserted and appropriate FWC selected throughout theprocedure. Identify correctly the data disk as defined instep ~.
Ensure DATA DNLOAD and TREND ERASE switch guards arepositioned down.
Remove data loader and restore A/C to normal configuration.
Select_maintenance test FWC on the DC-884 DisplayController. Verify that both FWC’S engine exceedances areO% EEPROM.
B. Troubleshooting Display Unit Red “X’’ing
When the display unit (DU) displays a black display with a red X, thealternate SG should be selected which causes the DU to accept data fromits ALT1 bus (Reference Appendix A, SG/DU Interface Requirements, page598.110, Section 6, Interconnects). If the expected display appears,then the primary SG/DU bus interface should be verified for this DU. Ifthe red X remains, then the DU should be removed and installed in adifferent position. If the red X follows the DU, then the DU should bereplaced. If the expected display appears after moving the DU to a newlocation, the SG should be removed and installed in a different position.If the DUS driven by that SG have the expected display, then the SG/DUbus interface should be verified at the original locations. If a red Xis displayed after moving the SG to a new location, then the SG should bereplaced. 22-14-00
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Honeywell !!!!!$~f’When the DU intermittently displays a black display with a red X, the DUshould be swapped with a DU in another location. With the original DU inthe new location, if a red X appears, this DU should be replaced. If thered X remains in the original location, then the SG should be swappedwith another SG. If the DUS driven by the original SG in the newlocation red X, then the SG should be replaced. If the red X remains inthe original location, then the SG/DU interface should be verified.
7. DFZ-820 FlicthtGuidance Svstem
This paragraph contains troubleshooting flow charts and minimum wirerequirements to aid in diagnosing faults of the DFZ-820 Flight GuidanceSystem. The flow chart figures are listed in paragraph 7.A. and the tablesare listed in paragraph 7.B.
A. List of Flow Chart Figures
410 Diagnosing Symptoms
411 Both FZ-820S Failing Power-up (FGC 1 and2 FAIL Messages on EICAS)
412 Single FZ-820 Failing Power-up (FGC 1or 2 FAIL Annunciated)
413 Unintended Priority Transfers
414 AP, YD, or Trim Engagement Inhibited
415 AP, YD, and Trim Disengagement (AllEngaged Functions)
416 AP or Trim Disengagement (YD isEngageable)
417 Unintended Mode Disengagement
418 AP, YD, or Trim Control Problems(Oscillations, Kicks, Sluggishness, etc.)
B. List of Tables
Table &
417 Minimum Wiring/Power Requirement forFZ-820 to Run GMT
418 Minimum Servo Wiring Required forFZ-820 to Successfully Power-up
419 Normal Switch States
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i!
I YES
I
Uith weight on uheds end airspeedless thsn 80 kts, activate the ground
maintenance test snitch
t/ \ /’-----’
i iProceed throu9h the Perform the sctions indicated
ground nteintenence test on EICAS as to why theto the flight fault — growtd meintenece testsmsnsry in formetim can not be rm.
I
I
+YES
/ \
i,,/,,s , ~Mer-w YES ~., YES
<, problem occurred ? ,.
‘~<’ ‘“”wer-u:~re’” ‘
NOI
II Go to figure 412 !I
Diagnosing SymptomsFigure 410 (Sheet 1) 22-14-00
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Honeywell %!!!%5.”
/ \,’ was an FCC 1 or ,
<
)
2 FAIL massageYES
displayed on“\\ EICAS ?
---J.-2/
>
Can bath FZ-820Sbe manually se(ectad ‘0
‘\.
via the displaycontroller ?
I Go to figure 413I
-.-J--3Can the YD ard
UTrim be engaged ?Co to figura 414
1YES
Does the YD andHlrim remain engaged ? Co to figure 415
Open the weight on heelsWOW circuit breakers, and I
attanpt to engage the AP
~CantheAP&\) ‘0 +_<. . engaged ?
Go to figure 614\
1 YESr , .—
NO /Does the AP
\
Does the YD alsoremain engaged ?
>disengage ? Go to figure 415 il
,;
‘~ “————”
--LYEs
*
/’ Uerecontr.t \ YESperformance problems
\
Go to figure 418Ireported ?
/’
.---Q%\. /
iNO
It Record the details of the
I ‘rob%”%%”x” ~problem persists
(
Diagnosing SymptomsFigure 410 (Sheet 2) 22-14-00
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Dual FZ-820S~, failing pouer-up ‘)
/
/---+
\““Are all the circuit
NO Close 81( the OFZ-800 circuit breakers,.
‘ breakers for the FZ-820S “I (FZ-820 (1,2), Stab Aug (1,2), AP servo (1,2), I( (insiuding servos) GP-820 (1,2)) end attenpt another full
‘\pushed in ? on-grwd power-up via the nwster avionics
pouer switch.
I Activate the gromdmaintenance teat witch I
/’t
\
NO ,/
< ::~~-:::~$~$m---’!NO
Run the FZ-820, GP-820, aiteron,●levator, rudder, trim, fault warning,
and cockpit switches growd Iwintenancetests with both FZ-820S
It 1
Deactivate the maintenancetest switch and then tryanother full on-ground
powr-up via the masteravionics inter switch k-3yEs J ~:::~i;::;:;z;;r::e ~
+ ,Es‘ Did this pc+ter-tp
<
Try saveral more fullattenpt pass ? on-growd power -upe.
“’----”” 1
I
Swap the -r 1 and 2FZ-820S (1 goes into 2}s
rack; Z into 1‘s rack)
I
Both FZ-820S Failing Power-Up(FGC 1 and 2 FAIL Messages on EICAS)
Figure 411 (Sheet 1)
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Honeywell !$!.!.by’
Try another ful I on-groundgxwer-up via the master
avionics power switch1
I
1e> ‘Es<--.’> “sDO both FZ-8ZOS
\ /
1 No
rCheck that the FZ-820S
have the mininsan requi remsntsto potter-up (ace table 417)
tTry another ful ( on-gromd
pouer-~ via the materWiOIIics power switch
+
Pull the weight on wheels(~) Circuit breakers, andattempt an in-air power-up
T00 to prob(em so[vinghints caikd lSingle
FZ-fQO failing power-up’(Figure 412)
1 II
I NO
-._._k— ———————Replace OP-820 and
try another on-groadpower-up
I )
Ii
,“ \ r 1 1
‘---T--’ II II
i NOI 1 ,—
.Rep(ace one of the failing /Did this ~“er.up... YESFZ-820S and try another Contact a Honeyuet 1 ~
on-grourd pobter-up attenpt pass ? ,./, field ●ngineer 1’
I-~””
&Both FZ-820S Failing Power-Up
(FGC 1 and 2 FAIL Messages on EICAS)Figure 411 (Sheet 2)
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FZ-820 poner:
28 v to pilot’ s/copilot’s 1OJ1A-1,228 v to pilot’ s/copilot’s 1OJ1A-4,528 v to pilot’ s/copi lot’s IOJIA-6,728 v to pilot’ s/copilot’s 1OJ1A-8,928 v to pi lot*s/copi lot’s 1OJ2B-65
ASCB connections to:
pi[ot’s/copilot’s 1OJ1B-1 to ASCB HIpilot’ s/copilot’s 1OJ1B-2 to ASCB LOpilot’ s/copilot’s 1OJ2B-1 to ASCB HIpi[ot’s/copi lot’s 1OJ2B-2 to ASCB LO
Configuration discretes
Gnd to pitot’s/copilot’s 1OJ1B-79Gnd to pitot’s/copilot’s 1OJ1B-81Gnd to pilot’s IOJ1B-102Gnd to copilot’s 1OJ1B-103Gnd to pi lot’s/copi lot’s 1OJ2B-67
Miscellaneous:
AP QD to pi lot’s/copi lot’s 10J26-54, -66
Cross FZ-820 strapping:
1OJ2A-41 to c1OJ2A-421OJ2A-42 to c1OJ2A-411OJ2A-43 to c1OJ2A-441OJ2A-44 to c1OJ2A-431OJ2A-45 to c1OJ2A-461OJ2A-46 to c1OJ2A-451OJ2A-47 to c1OJ2A-481OJ2A-48 to c1OJ2A-471OJ2A-49 to c1OJ2A-5O1OJ2A-5O to c1OJ2A-49
Pi(ot Fz-820 to GP-820:
1OJ2A-65,66 to llJ1-12,131OJ2B-89 to llJ1-691OJ2B-96,97 to llJ1-5,61OJ2B-98,99 to llJ1-3,410J2B-1OO,1O1 to llJ1-7,81OJ2B-102,1O3 to llJ1-1,21OJ2B-106 to llJ1-38
Copi lot FZ-820 to 6P-820:
c1OJ2A-65,66 to 11J2-12,13c1OJ2B-89 to 11J2-69c1OJ2B-96,97 to 11J2-5,6c1OJ2B-98,99 to 11J2-3,4c1OJ2B-1OO,1O1 to 11J2-7,8c1OJ2B-102,1O3 to 11J2-1,2c1OJ2B-106 to 11J2-38
Minimum Wiring/Power Requirementfor FZ-820 to Run GMT
Table 417
Note:The full Miring required,it is documented insection 6, Interconnects,Table 501.The wiring listed hereshoutd al 10U entryinto the gromd maintenancetest, so that the f 1ightfau[t sunnary informationcan be used.
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Pilot~s Wiring
FZ-820 to rudder actuator:
1OJ1A-58 to 14J1-A1OJ1A-63,64 to 14JJ1-F, E1OJ1A-59,6O to 14J1-M, J1OJ1A-61,62 to 16J1-L, K14J1-B to GND
FZ-820 to ai leron servo
1OJ2A-57,58 to 12J1-1,21OJ2A-61 to 12J1-121OJ1B-7O,71 to 12J1-16,1712J1-14 to GND
FZ-820 to elevator servo
1OJ2A-55,56 to 13J1-1,21OJ2A-61 to 13J1-111OJ1B-68,69 to 13J1-17,1613J1-14 to GND
Copilot~s Wiring
FZ-820 to rudder actuator:
C1OJ1A-58 to 14J1-AC1OJ1A-63,64 to 14J1-H, Gc1OJ1A-59,6O to 14J1-s, Rc10J1A-61 ,62 to 14J1-T, u14J1-B to GNO
FZ-820 to ai leron servo
C1OJ2A-57,58 to 12J2-1,2c1OJ2A-61 to 12J1-12C1OJ1B-7O,71 to 12J2-17,1612J1-22 to GND
FZ-820 to elevator servo
C1OJ2A-55,56 to 13J2-1,2c1OJ2A-61 to 13J1-11C1OJ1B-69,68 to 13J2-16,1713J1-22 to GND
Minimum Servo Wiring Required forFZ-820 to Successfull.vPower-U~
Table 418- 22-14-00Page 445
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/
( Single FZ-820 “fai(ing pouer-up )
&\ Close ai 1 the DFZ-800 circuit breakers I
/’breakers for the FZ-820
NO (FZ-820 (1,2), stab M (1,2), AP servo (1,2),<“
(including servos) * and GP-820 (1,2)), and attenpt armther.. full on-grcimd power-up via the mesterpushed in ?
avionics power snitch.~
1
YES
1 1
Enter Grotmd Maintenance Testand record the f 1ight faultm.snmry information for the
fai led Fz-820
.-J---
( Ooea the fai ledFz-820 flight fault \ YES Perform the recommended act ions
suimssry contain anythingfor that flight fault sunnery
\\ but zeros ? //(see section 4)
1 NO
Run the FZ-820, GP-820, aileron,elevator, rudder, trim, fault warning
arud coskpi t switches gromdmaintenance tasts with the
fai led FZ-820
It
Oid the gromd Perform the act i oms suggest ad
K.
maintenance test detectYES
. for the particular fault in theany faults ? grot.e-d maintenance test msnusl
I no
It
I
Deactivate the maintenancetest auitch and then try
another ful t on-grow-dpower-up via the mester
avionics power suitch
~ Try severai more futl on- i‘~~, YES‘Oid this po.er-up
\
ground power-ups. 1f they I [ Cstl Honeywell field engineer iatteqm pass ? / al 1 pasa, record the detai 1s
Iif problsm persists
\ ,/ srul track the failure.
Single FZ-820 Failing Power-Up(FGC 1 or 2 FAIL Annunciated)
Figure 412 (Sheet 1) 22-14-00Page 446
Aug 15/91Use or dmclosure Of InformalIon Oft this page IS subject to the restrictions on the title page of thts document
Swap the nurber 1 and 2 FZ-820(1 goes into 2)s rack; 2 into
1’s rack)
*
Does problem fol lowNO
4
Turn off pouer to thethe ‘badi FZ-820 ? ‘good’ FZ-820
I
i’ YES
I Turn off the FZ-820 powerto the ‘good’ FZ-820. i
I4ttaqx another on-grou’!d
power-up uith onty the failedFZ-820.
-
/Did this power-W\ yES
‘-~
1Remove the previously vsil idFZ-820 frcen its rack.
1
Attenpc armther on-grotmdpower-up with only the fai Lad
FZ-820.
I
*
I
q.-
Did this pouer-~attempt pass ?
Check the uiring frcimthe cross-side FZ-820 for
interference (seetable 417). m
LI )1 I I
-::*”NO
Repl sce the GP-820 andthen try another fui I !
en-ground pwer-up via the Imsster avionics power switch
1
[1 The ‘good’ FZ-820 is 1 I
~
\ attempt pass?I
--J---- +Pull the ueight-on-uheels NO ‘“
circuit bresker, and ..Z’Did this power-up
attenpt an in-air power-up \ attem$lt pass ? /-\
‘\ ,/,
i YES
Single FZ-820 Failing Power-Up(FGC 1 or 2 FAIL Annunciated)
Figure 412 (Sheet 2) 22-14-00Page 447
Aug 15/91Use or disclosure of Information on this pssge IS subject 10 the restrictions on Ihe title page of thm document
1 1‘No \
Pul 1 the ueight-on-uheets Did this power-upcircuit breaker, and atterqx pasa ?
attenpt an in-air power-up
1
{ \ Check cent irwi ty betueenYES
Oid this power-upthe servos and FZ-820 per
attenpt pasa ?tabie 418 and be sure
that these pins are locked
~ “~
in their connectors
Replace the failingFZ-820 and return it to
Honeyuel 1.I II
Single FZ-820 Failing Power-Up(FGC 1 or 2 FAIL Annunciated)
Figure 412 (Sheet 3)
YES
——
22-14-00Page 448
Aug 15/91Use or disclosure of Information on this page IS subject 10 the restrictions on the Mle page ot this document
MAINTENANCE
Honeywell W#i..
( FZ-820 priori tylengage ‘status tranafer )
“.-1
/’
I
Guith ueight on wheels and airspeed
It
---1Enter Grand maintenance Test
and record the flight fault sumnaryinf ormation for both FZ-B20a
YES
fI/ ...’
Rut the FZ-820, aileron, NO z’ Does ●i ther ‘\etevator, rudder, and flight fault sunnery
trim ground maintenance contain anythingtests ‘\ but zeros ? I
1i
+‘.~
,/YES
Oeact ivate the ground nmintensncetest witch, and then turn power
off to the FZ-820~
that was tranaferrad into Perform the recommended actions
(high priori ty/engagacf)
__Jl
for that flight fault sum?ary(ace aecticm 4)
Isa FGClor2 Try an on-growdFAIL message di splayed power-~ with the
‘Y~ ~
failed FZ.820
_J_ ‘
I
,/’were anypower .,, YES‘ .-
\ a-:i;i:y’”/,--[nform the aircraft’s
field engineer II\w’ I
i t1
Returnpower to the once engaged 1(high priority) FZ-820 I
Unintended Priority TransfersFigure 413 (Sheet 1) 22-14-00
Page 449Aug 15/91
UseordwclosureofInformation on this page IS sub)ect to the restrlcllons on the title page of this document
—--J--- l------Engage the YD and Trim (at
least one IRs and DADCnustbe val id) and try several
manual transfers betueen theFZ-820S via the display
mccrttrol lerns LIR FZ-S20 selectioa
IDoes priori ty transfer
No auggest~ actions for
(and remain transferred)now. If problem persists,
between the two FZ-820S ?ca(l a Honeywell field
engineer.
1NO
Attsnpt a ful I on-gromdpowar-tp ui th both FZ-820S
via the nmster avionicspower snitch
/t
\/
(00 both FZ-820S NO
power-up successful ly(they can be menue(lv
‘\ seiected) ? “/
I YES
IPu(( the neight-on-uheeis (W)
circuit breakers, and then engagethe AP. Through the display
controller, menuetly tranaferpriori ty between the tuo FZ-820S(the FZ-820 meY fai 1 if transfers
are attqted faster than 2 secondsapart - this is a known system
limitation).
tI
Ooes priority transferNo suggested actions for
(and remain transferred)now. If the problem persists,
between the tuo FZ-820a ?call a Honeywell field
engineer.
Unintended Priority TransfersFigure 413 (Sheet 2) 22-14-00
Paqe 450Aug-15/91Useordisclosureof Information on this page IS subiect to the restrlchons on the Ittle page of this document
Honeywell !#!!!-?&yE
( AP, YD, or Trimengage inhibit )
Manual ly transfer FZ-820priority via the display
control [er
1YES
/
Are all the circuit breakerspushed in for the FZ-820, GP-820,
servos, IRS, DAOC,EFIS, endcockpit sui tches ?
IYES
Pul( the weight-cm-heels (UCU)circuit breskers, and then pressthe AP push-button on the 6P-820
1
Los 1Close al I the SPZ-8000 c i rcui t breakers,
(FZ-820 (1,2), Stab AU!J (1,2), Ap servo (1,2),GP-820 (1 2) EICAS EFIS (1 2) [Rs (1.2),
and DAOC(1,2)), and ettenpt to transfer
1
NONo suggested actions for
:4,
Oid the AP ‘ now. [f problem persists,
always engage ? z call a Honeyuell fieldengineer.
L,./1s a message( displayed on ), ‘0 ~
\EICAS ?
,,/ EiiiiidI I
1YES
AP, YD, or Trim Engagement InhibitedFigure 414 (Sheet 1) 22-14-00
Page 451Aug 15/91
UseordisclosureofInlormfsllononthmpageIS subject 10 the restrlcllonsontheIlllepagf)ofth!sdocumenl.
Honeywell !!#!!!{b.cE
,._-J-/ \ Push- in the W circuit breakers,
1s the following and then rm the cockpit sui tches
~ messsge displayed onpert of the growd maintenance test.
\ EICAS:Al SO check thst the cockpit sui tch
‘7’
i-t. are in the correct state (S=table 419 )
i/ \
/IS the follouing
\
message displayed on YES Run the IRS self test, andEICAS: ‘IRS Ii
FAIL1 7check both IRS’s mountings
\____-J_
/
:, ‘0’Ezs&5En/,,/’ IS the follouing
\
YESmessage disptaysd on
EICAS: @OAoc\ airspeed, etc.)?
-’ %---=”
I II 11
i
,’~s t; foi,owiEnter the ground meintenmxe
I
test.mssaag dispiaysd onProceed to the f I ight
foul t sunnery, and than PSrf onn the !
\\\EICAS:
*AP OFF1 ,/reccamsrxked actions for the date.
‘—------’ II IJ
1NO
Rm the Fz-820, aileron,elevator, rudder, trim,
GP-820, and cockpit auitchesground maintenance tests.
Then perform any recmnendsdact ioms.
I 1 1 I
AP, YD, or Trim Engagement InhibitedFigure 414 (Sheet 2) 22-14-00
Page 452Aug 15/91
UseordisclosureofInformation on thm page IS subject to Ihe restrictions on the title page of this document
Honeywell !I#!5.cE
Switch Function
Stall warningAP disconnect
Emergency disconnectYD disconnectGo-aroundTouch control steeringTurn knob active
LRU Input Pin
1OJ1A-281OJ2B-54, 1OJ2B-66,llJ1-77, 11J2-771OJ2B-651OJ2B-67llJ1-72, 11J2-54llJ1-74, 11J2-531OJ2B-59, 1OJ2B-61
State
OPENGND
28 VGNDOPENOPENOPEN
Normal Switch StatesTable 419
22-14-00Page 453Aug 15/91
Useordisclosureof reformation on this page E subject 10 the restrictions on the title page of thm document.
,--A11 engaged fmctions
disengagement
I
Can the FZ-820 Try an on-grourd power-upgromd maintenance ad then turn to poner-tp
\ ‘e:tr,;%;:;hSuggestions in this manual
(see figure 411)
IYES
Has pouer been Proceed to the flight faultturned off since sutmbsry prtion of the gromd
the di sengagemant? nmintanance test
I
YESI
Run the FZ-S20, aileron, NOelevator, rudder, trim
and GP-820 grotstdmaintenance tests e~~y-:~+~a;m
I
‘~/
YESDid the gromd Perform the actions suggested
maintenance test D for the particular fault in thedetect any fai lures ? ground maintenance test manual
I NO
Uere sny sensor snsmel ies/ RIM the ground maintenance
\
(IRS or DAOC) reported test for the suspectedon the f 1ight? sensor
< WIUere any pouer anomaliesNo suggested actions for now.
reportad in flight?If problem persists, calt I
\ /II NO
II aircraft!s field engineer. I
Engage YD/MTrim (at least one OAOCand IRS must be valid). Through thedisptaycontroller,msnually
transf●rprioritybackandforthbetueanthe tuo FZ-820S ( the FZ-820Smsy fai 1 if transfers are attanpted
faster than two secmds apart -this ia a knonn system limitation)
t
AP, YD, and Trim Disengagement(Al1 Engaged Functions)Figure 415 (Sheet 1) 22-14-00
Page 454Aug-15/91
Use or disclosure of information on this pege IS subject to the restnchons on the title page of this document
i/’
<.
Enter grcsnd maintenense testDid any fni lures and record the f I isht fault sursnsry
occur during manual inforsmtion. Perform thetransfers? recannerxkedactions for that sumssry
(see section 6)
Noi
Oe-activate the grcsmd emi ntenencetest switch, pult the ueight-on-uheels
(W) circuit breaker.Engage the AP and then rnanuai ly
transfer priori ty between the twoFZ-820S (Note, the FZ-620S nmy fait
i f the control colurm moves ●xcesaiva(yor f aa t transfers are at tespted - these
are known system 1imitat ions)
I
4Enter grcumdmsintanerrce test
Did any f.silures and record the f 1ight faultsumasry\.-t:;::r
info~tion.Performtherssomnmdedactionsforthatsunnery
\ (sssSactim4)NO
Record dstai Is of disengagementand track problem
I
Call Honeywell field engirw%eri f problem psrsists
AP, YD, and Trim Disengagement(All Engaged Functions)Figure 415 (Sheet 2) 22-14-00
Page 455Aug 15/91
UseordisclosureoflntOrrnatlononlhl~pngeIS sub@ 10IhereslrlcllonsOnthetlllepage01lh!~documenl
+ \Haa powerbean NO Enter Gromd Maintenance Test
turned off since D and record the flight fault
the di sengagamant? aumrary information
I
1YESi
Rtm the FZ-820, ai leron, NO
3
Perform the reccmnendad
●levator, rudder, trim, fau(t aunnary containactions for that flight
GP-820 and cockpit aui tchea anything but zeros 7fault sunnary
gromd nmintenance testa (ace section 4)
I
t
Did the ground
\
Perform the act ions auggeatadmaintenance teat for the particular fault in the
detect any fai turea ? gromd nmintansnce teat manual
i NO
Deactivate the grcindmaintenance teat switch.
Then, verify that the cockpitswitch inputs are
in the correct stata(see table 619 for datai 1s)
t
AP or Trim Disengagement(YD is Engageable)
Figure 416 (Sheet 1) 22-14-00Page 456
Aug 15/91Useordisclosureof Information on th!s page IS sub)ect to the restrlcllons on the title page of Ihm document
I
/ \Can the AP be engaged,/ (at least ma IRS nmst be
/’-
(’valid and the w circuit Run the IRS self teat ad
\ breaker must be pulled),check the both IRS’S ASC8
‘\ and then Uoes AP connections and mountings
\ rentsin engaged ?
I1 1
Uittr the AP, VO, ad rrjmengaged, IWtu.sl 1y trarrs fer
priority bstneen the two FZ-820Susing the display cmtroiler.(Note, the FZ+K?DS may fai 1 i f
the cof!tro 1 COILSWIomvaaexcess i vel y or fast t rsnsf ● rs
●re at tqtad - theaaare knoun system limitations)
I/ \Did any failures
occur during rsanua( inforemtim. ‘Perfonm thet rarrsf●ra? racomended actions for that stsrmry
(aae sactim 4)
No
Enter Urti maintenance testand record the f 1ieht fed t sumiaw 1
tI 1
I
Cal I frmayvel I field engineerif problem persists
AP or Trim Disengagement(YD is Engageable)
Figure 416 (Sheet 2) 22-14-00Page-457
Aug-15/91Use or disclosure of Information on thm page IS subject to the restrtctlons on the lttle pagn of Ihls document
( Un- intended mode disengagement
I
1
Are all the circuit, breakers pushed in for the
Close al 1 the SPZ-8000 circuit breakers,
\
FZ-820S, GP-820, servos,(FZ-800 (1,2), Stab Aug (1,2), AP servo (1,2),
IRSS, DAOCS, EICAS, EFIS,CP-820 (1,2), IRS (1,2), DADC (1,2), EFIS (1,2)
and cockpit sui tchea ?El CAS), artd then atte@ to re-engage the mode
A—— r
<
Uere myGo to the problem sotving
messagesdi sptayad Did the AP, YD, or Htrim hints called ‘AP, YO, snd
on EICAS ?alao disangage ? Wrim diseng.sgementj
(Figure 415)
I
‘TYES
e)=----”
[heck the selected sideEFIS, OAOC, FMS, snd the
rsdio information displayedon EFIS when the nude
disengaged
A YES
“L_._/NO
-J-----
\ / 11 !)
1 NO1
RLS!the IRS gromd nmintenancetest, ard check both IRS’S ASCB
cornactors.
( Is the follouing RLS!the DAOCgrowd
message displayed on YES meintensrce test, and
EICAS: ‘OAOC invalid OAOCdata ? - check tuth OAOCIS Di tot
INVALID’ ?\
--T---I No
i1 1
RtM the F2-820, GP-820, cockpitswitches, DADC, IRS, Fault warning,snd EFIS ground maintenance teats.
Contact the Honeywel 1 fieldengineer for additi~sl
assistance
‘-h-’”Ii
Rm the DAOCgrand maintenancetest, snd check both DAOC*S ASCB
connectors.
Unintended Mode DisengagementFigure 417
22-14-00Page 458
7
Aug-15/91useordisclosureoflnfOrrnMlOnon this page IS subject to the restrictions on Ihe title page of this dmumenl
Honeywell !/!#!jb.cE
t t
\ /’ II I I
I1,01
/ \ I 1
\ /’ 11 J/
I-L_Y-
\ / 11 I
Check the wiring to IS the pitch axisthe affected FZ-8201S ~
servothe probtam ?
~ I ‘1
& IYES
I/are anv mistrim Replace the affectedccaditions reported ? axis ! servo
YES
AP, YD, or Trim Control Problems(Oscillations, Kicks, Sluggishness, etc.)
Figure 418 22-14-00Page 459
Aug 15/91Useordisclosure01information on this page IS subject 10 the restnchons on the Me page of thm documenl
MAINTENANCE
Honeywell H!WL.8. PRIMUS@ 870 Weather Radar System
The navigation display will display an amber WX in the lower left corner ifno SCI data is present or when an RTA failure has occurred. This may be dueto an actual bus failure or if the RTA is not powered up. When the RTAserial bus is functioning normally, the navigation display will indicate thepresence of any failures detected by the RTA fault monitoring system and bydisplaying an amber fault code number in the tilt angle location of thedisplay when in test mode. (Refer to Table 420.)
. Memory Reset
The RTA fault memory may be cleared by grounding a test point accessiblethrough the connector board support prior to power-up.
ND Fault CodesNOTE 1 NOTE 2 Fault Description
None None No fault
01 21
+
Azimuth scanning incorrectly (> 2.5 degrees for > 2 seconcls)01 31 Antenna elevation error (> 2 degrees for > 2 seconds)
02 03 Analog to digital converter failure02 22 STAB reference (< 1/2 A/D scale for > 2 seconds)02 32 NAV computer high-speed ARINC 429 failure
03 13 +15 volts failure (> * 1.5 Volts)03 23 Automatic gain control failure (< -1 V or > 9.73 V for 8 seconds)03 33 -15 volts failure (> ~ 1.5 volts)
04 16 Magnetron voltage failure (< 1500 volts min or > 2700 volts max)04 24 Mixercurrentfailure
05 25 AFClockfailure05 35 AFCsweepfailure
06 26 Fanvoltageabnormal
07 04 Digitalairdatafailure07 07 Pulsepairprocessorfailure07 14 Parallelaltitudefailure07 17 EPROMtestfailure07 27 VLS1testfailure-lossofvideoreadyinterrupt07 34 OADC altitude failure07 36 Analog altitude failure - If input is > 60,000 feet07 37 RAM test failure07 30 Nonvolatile memory failure
NOTES. 1. Fault data for -413/414 WC-874 WX Controllers.‘“ 2. Fault data for -415/416 WC-874 WX Controllers.
Display FormatTable 420
22-14-00Page 460
Aug 15/91Use or disclosure of Information on thm page IS subpcl to the restrictions on the Ittle page of thts document.
9. FMZ-800 Fliaht Management Svstem (FMS1
The following items are answers to operational questions pilots have asked.They were extracted from Honeywell FMS Technical Newsletters. All arerelated to the Phase II G-IV aircraft using the navigation computer with 9001software and the performance computer with 9003 software.
A. Airborne Logic
Several FMS functions and messages become operational only when theaircraft is in flight. The FMS considers itself airborne when:
● Groundspeed is greater than 50 knots (typically occurs first)● Airspeed is greater than 80 knots● Weight-on-wheels switch indicates no weight on the wheels.
The opposite logic is used to determine when the aircraft lands. Thus,it is Dossible for a hiqh-s~eed refused takeoff to be both a takeoff andlanding, resetting init~ali>ation parameters and ~
B. Runway Alignment
The FMS provides for easy update of present positthreshold through the RW POS prompt on the activerequirements for the display of this prompt are:
light summary data,
on to the runwayflight plan page. The(1) a departure runway
has been activated, and (2)-the aircraft is on the-ground,-and no highe~priority prompt is being displayed. This feature can be used to updateboth the FMS and IRS positions to the runway threshold. Some have askedif performing this update is really necessary and, if so, under whatcondition. In addressing these questions, FMS updatingare discussed in the following paragraphs.
(1) FMS Update at Takeoff
There are two situations for which you should consupdate to the FMS at the runway threshold:
(a) If you plan on selecting the FMS for guidancefollowing takeoff, such as when flying a SID,
and IRS updating
der performing an
immediatelyYOU should
consider updating the FMS position. This will helD eliminate acommanded maneuver to compensate for an error in the FMSposition when coupling to the FMS. This error could be theresult of inaccurate position initialization and/or prolongedground operations in an IRS-equipped aircraft. If you do notplan on selecting the FMS until several minutes after takeoffthe FMS will have begun radio updating, and any error will beautomatically removed.
(b) You should also consider doing an update to the runwaythreshold when taking off and you do not expect to receiveradio updating. This is rarely the case, but there may beairports where radio updating is not available. Radio updatingrequires good VOR and DME information or DME information fromtwo diffe~ent stations. 22-14-00
Page 461Aug 15/91
Use or dwclosure of InformalIon on Ihls page IS subject to Ihe restrictions on the title page of this document
9. B. (2) IRS Runway Alignment
If the IRS mode select unit is placed in the ALIGN position prior todoing the FMS update, the IRS also receives the update. The IRSposition is adjusted to the runway threshold, and IRS velocities areset to zero during this quick alignment. This quick alignment takes30 seconds, during which the aircraft must not be moved. The modeselect unit must be returned to the NAV position prior to aircraftmovement. Extreme caution should be used when doing a quick runwayalignment of the IRS. Failure to follow the correct procedures mayresult in complete loss of alignment.
Under normal circumstances, runway alignment of the IRS is of littlebenefit. Remember that, internal to the FMS, a correction isapplied to the IRS position. Therefore, inaccuracies in the raw IRSposition are of little consequence to the FMS. If an IRS isdisplaying several knots of groundspeed while the aircraft isstopped, you may consider doing a runway alignment. Again, useextreme caution when performing this procedure to avoid loss ofalignment.
c. Estimated Time Enroute
This paragraph describes the method the NZ-9XX Navigation Computer usesto calculate estimated time enroute (ETE) for stored flight plans and theactive flight plan when the PZ-800 Performance Computer is notinitialized.
(1) Active Flight Plan - ETE is computed using, in order, based onvalidity and availability, one of the following speeds against thecurve path distance:
(a) If airborne, the current TAS corrected for current wind and legcourse.
(b) The average TAS of the previous five flights.
(c) The default TAS of 300 knots.
~: For the predicted average groundspeed for the leg, the PZ-800needs to be initialized.
(2) Stored Fliqht Plan - ETE is computed using, in order, based on. .validitystraight
(a) The
(b) The
aid availability, one of the foliowing speeds against aline distance, not curve path distance:
average TAS of the previous five flights.
default TAS of 300 knots.
22-14-00Page 462
Aug 15/91Use or disclosure of InformalIon on this page w subpcl to the reslnctlons on the title page of this document
9. c. (3) “..based on validity and availability...“ means that if the listedspeed is valid and greater than 10 knots, that speed is used,otherwise, the next speed in the list is used. For example, if thePZ-800 is initialized, it will provide the average groundspeed forthe leg and the leg ETE will be calculated using the provided speed.
II ...average TAS of the previous five flights...” has beenimplemented using the following algorithm:
(a) If the aircraft has just landed, the flight was longer than 15minutes, and TAS remained valid for the entire flight, theaverage groundspeed for the flight just completed is set equalto the average TAS for the flight (as displayed on the FlightSummary page, line 2R).
(b) If the average of this flight’s speed and the previousfive-flight average is more than 20 percent greater than theprevious five-flight average speed, the five-flight averagespeed is increased by 125 percent.
(c) If the average of this flight’s speed and the previousfive-flight average is more than 20 percent less than theprevious five-flight average speed, the five-flight averagespeed is decreased by 80 percent.
(d) If the average of this flight’s speed and the previousfive-flight average is within 20 percent of the previousfive-flight average speed, the five-flight average speed is setequal to the average of this flight’s speed and the previousfive-flight average.
D. Descent Time and Fuel Predictions
Gulfstream Flight Operations and several Phase II G-IV operators reportedinstances of incorrect aircraft performance predictions. The problemmanifests itself as erroneous estimated time enroute (ETE)/estimated timeof arrival (ETA) and fuel predictions at waypoints in descent. Theerrors can be obvious; ETAs on ACTIVE FLT PLAN can be based ongroundspeeds as low as 130 knots. And PERF PLAN fuel predictions can beless on descent waypoints than at the destination. All other predictionsappear normal.
The problem requires a predicted deceleration at top-of-descent and anonpath descent. Under these conditions, subsequent mission predictionsdo not update on the descent legs. Thus, the effects of changing thepreselector altitude, dialing a manual speed or winds different from theentered winds are ignored in descent. The problem clears withperformance initialization or flight plan changes.
22-14-00Page 463
Aug 15/91Use or disclosure of lflfOrmatlOfl on this page !s subjecl 10 the restrictions on the Iltle page of this document
Honeywell !!I{%r.c’Selection of a cruise speed schedule (LRC, MAX SPD and MAXobscure the Dredicted final cruise sDeed. However. a dece”
END) mayerat”on to the
Ainitial descent speed is unlikely with LRC or MAX END selected.top-of-descent deceleration prediction is likely with MAX SPD or a manualcruise Mach 0.80 and higher selected.
While speed schedule changes can eliminate any occurrence, most operatorswill find a path descent the most convenient way to avoid the problem.Line-selecting the elevation of the destination waypoint to the CDUscratchpad, and reselecting to the waypoint will enter an altitudeconstraint at the destination. This results in a path descent thatavoids the problem.
9. E. Stored Flight Plan Waypoints
Stored flight plan waypoints are not updated when updating the FMSnavigation database. There are two properties of waypoints that must beconsidered. They are the name and the position. Either one or both ofthese properties may change in a new cycle of the database or thewaypoint may even be removed from the database.
If a waypoint contained within a stored flight plan is changed duringdatabase updating, the FMS displays the message FPL CONTAINS INVALID WPTwhen attempting to activate the affected stored flight plan. At thispoint, the proper action is to SHOW the affected flight plan. Theinvalid waypoint will be displayed in inverse video. The invalidwaypoint may be deleted or if the adjacent line select key is pressed,the WAYPOINT DEFINITION page will be displayed where the waypoint may beredefined. The action is the same regardless if the name or position ofthe waypoint was changed (or removed) in the database update.
F. Takeoff Vspeeds
The FMS checks takeoff initialization parameters against sensedparameters. If they do not agree the Vspeeds are inhibited, or turnedoff, on the PFD speed tape. The flashing is caused by the parametersalternately agreeing and then disagreeing.
The parameters that are checked include aircraft configuration andatmospheric conditions. Temperature and pressure altitude entries arechecked to within 1 degree and 100 feet, respectively. These tolerancesare based on the amount of change that would cause a l-knot change in aVspeed. If a temperature entry is made, the l-degree comparison tosensed temperature could very well be turning on and off the Vspeeddisplay.
It is recommended that no entry be made for temperature, pressurealtitude, or baro set during normal takeoff initialization. Thissimplifies the initialization and allows takeoff data to be computed oncurrent conditions. The data is automatically updated if the sensedconditions change. Entries are allowed, primarily to look at takeoffsunder different conditions; for example, later in the day when it is hot,
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or for tomorrow’s flight. Because the sensed temperature is used by theautothrottle and enqine, the temperature probe on the G-IV is asDirated.Aspiration improves-the-accuracy-ofthe probe whileAspiration is automatic on the ground after a bleed(APU or engine). Once aspiration is available, theshould be quite accurate. Again, it is recommendedused for takeoff calculations.
9. G. V1 Selection
on the ground.source is selectedsensed temperaturethat sensed values be
A momentary power interruption can cause the takeoff V1 selection todefault back to Vlmax. This only applies when a V1 different from thenormal Vlmax was entered from the V1 SELECT page. V1 SELECT is accessedfrom the second page (Vspeeds) ofT.O. DATA by line-selecting V1. Theproblem can occur when switching power buses after initial review of thetakeoff computations.
H. Speed/Altitude Entries
Several cases of unusual speed and wind predictions were reported whenoperators began using the new features of the Phase II FMS. Care shouldbe taken to ensure speed and altitude entries are made correctly.
For example, a Mach 0.80 constraint at a waypoint may be entered as .8 or.80. If just 80 (no decimal) is entered, it is interpreted as 80 knots.If80 is entered, performance will properly limit the speed target to thecomputed minimum speed. This is certainly different from the expected0.80 Mach. The decimal point is essential for entry of Mach constraints.Unusually low speed targets limited (inverse video) by performance areclues that an improper entry may have been made.
Misconceptions of the Phase II FMS capabilities may also contribute tothese problems. Speed and altitude constraints are not required for theFMS to plan and control efficient climbs and descents. Often, theselected speed schedules and flight plans are sufficient to control allrequired speed and altitude changes. When this isn’t the case, speed oraltitude constraints can be entered as required. Speed and altitudeconstraints are automatically entered when selecting SIDS or STARS.
I. Wind/Temperature Model
The wind and temperature model of the PZ-800 offers the ability to enterforecast winds and temperatures for flight planning. Good windinformation is important to accurate planning of time and fuel. Enteringonly the average cruise wind and ISA temperature deviation on the PERFINIT pages is sufficient for normal flight planning purposes. In flight,actual winds and temperatures are automatically blended with the forecastinformation to update flight planning continuously.
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The wind and temperature model can also acceptwa.vDoints. These entries should be considered
entries at individualif winds or temperatures
ar~’significantly different at individual waypoints......
Since ea~h’waypointwind or temperature entry is associated with an altitude, the forecastmodels can also be tailored to account for jetstream winds or temperatureinversions.
As with speed/altitude entries, the correct format is important. Forexample, an altitude entry of 430 is interpreted as 430 feet, not FL430.With no other wind entries, a 20-knot wind entered at 430 feet becomes apredicted wind of 250 knots at FL430. Flight level 430 should be enteredas 43000 or FL430. Future software versions will require at least fourcharacters for an altitude entry.
Forecast wind and temperature entries on PERF INIT 4/5 affect time andfuel predictions over the entire flight, even when blending of currentconditions becomes active after the aircraft is airborne. Sensed windand temperature values do not replace the forecast entries. In otherwords, current sensed values are not assumed constant for the rest of theflight.
Sensed wind is applied fully to time and fuel predictions immediately infront of the aircraft only. Further along the flight plan, the effect ofthe sensed wind is gradually reduced. At 200 nautical miles (NM) ahead,the wind is an equal blend of sensed and forecast winds. At 400 NMahead, the sensed wind is weighted 20 percent and the forecast windweighted 80 percent in estimating the wind.
Sensed temperature is blended with forecast temperatures similarly,except the range of sensed temperature blending is greater. The 50/50blending point for temperature occurs 500 NM in front of the aircraft.
Both sensed winds and temperatures are also blended with altitude forclimb and descent. Beyond 10,000 feet above or below, the sensed valueshave no influence. This eliminates application of ground conditions tocruise predictions. Therefore, cruise predictions are not affected bysensed wind and temperature until the aircraft nears the top-of-climb(TOC).
No PERF INIT wind entry is the same as a zero-wind forecast. On shortflights, the average cruise wind may reasonably approximate the sensedwind. On longer flight plans, a zero-wind forecast dominates, reducingthe average cruise wind shown on PERF DATA 2/4. For example, on a 1,000”NM flight plan with no forecast wind entry, a sensed 100-knot headwind atTOC would result in a 25-knot average cruise wind. Good flight planningis dependent on accurate forecast entries.
The impact of off-forecast conditions can be examined via the WHAT-IFINIT pages without affecting the active flight plan. This can be usefulto project a current wind over the remaining flight plan. WHAT-Ifpredictions blend the current wind with the new forecast. The new
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Honeywell !#!!bTEforecast can also be entered on PERF INIT 4/5 to update the active flightplan. For more generalized flight planning, STORED FPL INIT uses aconstant average cruise wind and no current wind blending.
The WIND-TEMPERATURE page (accessed from the PERF PLAN pages) displaywaypoint blended wind and temperature, and permit entry of waypointforecasts. The dynamic displayed value may change after entry, dependingupon the sensed conditions, current altitude, and the distance to thewaypoint. This is useful in reviewing the actual winds applied to thetime and fuel predictions.
To summarize, wind and temperature forecasts are essential to accurateflight planning. PERF INIT average cruise wind and temperature entriesare sufficient for normal flight planning purposes. WaypointWIND/TEMPERATURE entries should be used if winds or temperatures aresignificantly different at individual waypoints.
9. J. Temperature Envelope
The autothrottle disengages and the automatic engine ratings blank whenOAT/ISA LIMIT EXCEEDED annunciates on the CDU. This usually occursbecause the outside air temperature (OAT) is less than the G-IV aircraftflight manual (AFM) minimum operating temperature. The AFM specifies aminimum temperature of -70 “C above 35,000 feet pressure altitude. TheFMS does not display engine ratings outside the AFM operating envelope.However, the autothrottle can be re-engaged down to -80 “C OAT aftermanually selecting an engine rating on the DC-884 Display Controller.
K. Autothrottle Disengages
A problem with the flap actuator on some G-IVS can cause the sensed flapposition to be slightly inaccurate. Both the FMS and the autothrottleconsider the flap position input invalid when the actual flap positiondoes not agree with the flap lever position. The autothrottledisengages, automatic speeds are not displayed, and FLAP INPUT INVALIDannunciates on the CDU when this occurs. This has been seen mostfrequently during approach flap extensions from flaps 20 to flaps 39.Air loads on the flaps are a factor, and the problem can be intermittent.
If the emergency flap switch is OFF, and the manual flap circuitclosed, the problem is likely the flap actuator or flap rigging.
L. Takeoff and Landing Weight
The takeoff and landing computations of the PZ-800 are largely
breaker
independent of the FMS mission calculations. However, mis;ion weightpredictions are transferred automatically to takeoff and landing, whereappropriate. A problem can arise when these weights exceed the takeoffand landing weight envelopes specified in the G-IV aircraft flightmanual.
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For instance, the maximum ramp weight of 73,600 pounds is a legitimatemission weight. However, 73,600 exceeds the maximum takeoff weight(MTOW) of 73,200 pounds. Gross weights exceeding MTOW are nottransferred automatically to takeoff initialization. The pilot can enterMTOW manually. This can be confusing to the pilot accustomed to theautomatic display of takeoff weight.
Both landing and takeoff minimum weights can be encountered withlightweight aircraft. As with the G-IV aircraft flight manual, thePZ-800 is not able to compute takeoff or landing predictions for grossweights less than 45,000 pounds. While uncommon for completed G-IVS, thelack of takeoff and/or landing information can be annoying whenattempting to fly very light-weight G-IVS. (Vref is computed anddisplayed for aircraft weights down to 40,000 pounds.)
9. M. Level Off at 10,000 Feet for Airspeed Control in G-IV Phase II Aircraft
It is very unusual to have a problem which is a result of complying withFAA rulings, but one came up on the G-IV Phase II program. You should beaware of it because it could lead to altitude violations. The problemarises when you are coupled to a VNAV path with the autothrottlesengaged. The FAA required that the system had to automatically slow theaircraft to 250 knots or less prior to descending through 10,000 feet.The problem arises when the throttles are back against their aft limitbut the airspeed is above 250 knots. What should the system do?Gulfstream and Honeywell stated that the aircraft should stay on path,because normally the path was established to meet an ATC crossingrestriction. The FAA said, “No, the system must not violate FAR 91.70.The system should level the aircraft to dissipate the speed beforedescending through 10,000 feet.” Gulfstream and Honeywell said thatdrastically decreases the chances of making the cross restriction. TheNorthwest Region FAA (lead region for avionics) made the final decision.They cited precedent, the FMCS on the Air Carrier aircraft level-off todissipate the speed. Thus, the G-IV system should operate the same way.
For G-IV operators to satisfy the FAA requirement, make sure you have thespeed below 250 knots before reaching 10,000 feet (use speed brakes, ifnecessary). If the speed is correct, you will stay on path and make thecrossing restriction. If you’re too fast and all the automatics areengaged, you’ll do a momentary level-off at 10,000 feet. If thismaneuver causes the crossing restriction to be missed, you’ll get anUNABLE NEXT ALT message.
N. CDU Blanking
It is possible (and normal) for the off-side CD-81O Control Display Unit(CDU) to blank momentarily when long stored flight plans are created,changed or deleted. This is caused by the large quantity of dataprocessed between the two navigation computers in DUAL or INITIATEDTRANSFER. Phase IA software would typically disengage lateral navigation(LNAV) when the CDU blanked. LNAV remains engaged with Phase IIsoftware.
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9. 0. Fuel Used
FUEL USED on the FLT SUMMARY page is updated every second by adding hecurrent fuel flow to the previous value of fuel used. When power to thenavigation computer is interrupted, the fuel used calculation issuspended. When calculation resumes, the current fuel flow is assumed tobe the average fuel flow during the power interruption. If the currentfuel flow is significantly different from the average, fuel used will beinaccurate. The error increases with the duration of the powerinterruption.
P. Flight Plan Collapse
If a flight plan has a waypoint common to an airway or procedure, theflight plan automatically joins at that waypoint when the procedure isactivated by name. This convenient feature can remove much of the flightplan when a standard instrument departure (SID) is selected into a flightplan with the same origin and destination. Operators commonly flyingcircular flight plans should delete the common waypoint from the flightplan first, then select the procedure and rejoin the discontinuity at thewaypoint.
Q. EPR Bugs on Approach
The green engine pressure ratio (EPR) target bugs displayed on the centerengine indicating display disappear when flaps or landing gear arelowered on approach. This is normal. Flaps and gear-down drag data isnot available to accurately predict thrust required, and hence, the EPRlevel needed to maintain the approach speed. This does not affect theautothrottle, which is controlling to the approach speed. The buqs aredisplayed on takeoff and climb-out with gear-these operations are based on a defined EPR -
R. Victor Airways
A key feature of the Phase II NZ-920 Naviqat”
and/or flaps extended sinceevel.
on Comr)uteris the auaddens;ty worldwide database. A problem ha; been dis~overed in ac~essingsome Victor and all Whiskey airways by airway identifier in the NZ-920.However, individual waypoints of the airways can be entered and flownwithout problem.
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9. s. Data Loader Fault Codes
When the CDU displays a message of CHECK DATA LOAD (XX) after anattempted disk operation, the numeric value in the XX position may beinterpreted using Table 421.
01 No response to OPEN corrmarrd02 No response to STATUS cmnrand03 Illegal database file header ●
04 No response to REAO cmtmnand05 Error getting 1st flight plan record06 Flight plan record too long07 No disk installed08 Status cornnand failed09 CRC is illegal ●
OA EE size in header is bad ●
OB File size in header is bad *OC Database size or serial number is O ●
00 Database size in header is odd ‘OE Serial number is locked out *OF CRC lockout *10 Bad BOWt11 Bad fuel weight t12 Bad cargo weight t13 Bad number of passengers t14 Bad initial cruise altitude t15 Bad cruise speed t16 Bad cruise winds t17 Bad cruise fuel flow t18 Bad waypoints count t19 Too many waypoints in flight plan t1A Bad alternate waypoint count t
232425262728292A2B2C2D2E2F303132333435363738393A3B
Error getting spot wind tError getting spot temperature tError getting weather data tError getting first debug monitor recordNC OM RECOROGT 80 CHARSRead file not openRead attempted at EOFCamnarrd in workUnknown Op codeDisk error during readDisk error during writeDisk is write protectedDisk is fullNo response to wRITE comnandNo response to CLOSE ccsnnandSTATUS cormnand illegalNo response from debug monitorOisk is not formattedNo response to FORMATconsnandDataloader requires update for attempted functionIllegal characters in read bufferRead buffer overflowToo many AFIS flight plansIllegal open RO fileIllegal directory size
lB Too many waypoints in alternate t * These codes are associated with the navigationlC Odd numbers of bytes in block * database disks. Contact local Honeywell support10 File header locked out * for assistance.lE Error getting identifier tlF Error getting latitude t t These codes are associated with errors in flight20 Error getting longitude t plan format requirements. Contact flight plan21 Error getting speed constraint t provider for assistance.22 Error getting flight level constraint t
Data Loader Fault CodesTable 421
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Honeywell ff!fl!c.c’10. Enqine Pressure Ratio Transmitter
● Recording Failures Using ARINC 429 Label 353
ARINC 429 label 353 contains the result of BITE. There are four bitsdefining the BITE test ID, eight bits defining the current fault, andeight defining the flight fault. The flight fault contains failureswhich occurred since the last aircraft ground to air transition. Thisdata will assist our repair shops in locating the cause of the failure.
Label 353 is defined as follows:
. T v
LABEL FAULT BITE LOGICDATA TEST o
IDENTIFIERSSM
AD-30794#
Definition
LabelCurrent FaultFlight FaultBite IdentifierLogic OSSMParity (odd)
Reference
N/ATable 422Table 422Table 422N/AN/AN/A
It is easier to record this data in HEX since there are less numbers torecord. Remember to record all bits in this word.
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Honeywell !’(!!!!~.c’
Faultlite Data‘est Bit Funct ion Cormnents
iRI NC o Total pressure on-side ADC On-side AOC(1) 1 Total pressure of f-s ide ADC Off-side ADC
2 CAS of f-s ids ADC On-side ADC3 CAS off-side ADC Off -s ide ADC4 429 wraparound test CCA Al5 ADC SDItest On- or off-side ADC6 Unused7 Unused
EPR o CPU test Processor A3(2) 1 Watchdog timer test Processor A3
2 8254 interval counter test CCA A23 Scheduled act ivity complet ion test Processor A34 Stack overflow Processor A35 Unused6 Unused7 Unused
klST o Overpressure test CCA A2(3) 1 EPR 1imit exceedance test CCA A2
2 TrimPlug test Trimplug setting or CCA Al3 Unused4 EPR SDI test EPR SDIpins or CCA Al5 Unused6 Unused7 Unused
MEM o RAM address i ng test Processor A3(4) 1 RAM read after write test Processor A3
2 NVM modeling coefficient sumcheck CCA A23 NVM cal i brat ion coefficient sumcheck CCA A24 ROM sumcheck Processor A35 NVM region coefficient sumcheck CCA A26 Unused7 Unused
DCR o Pressure time pulse raw data test CCA A2(5) 1 Normal ized pressure time pulse test CCA A2
2 Temperature time pulse raw data test CCA A23 Normal ized temperature time pulse test CCA A24 Unused5 Unused6 Unused7 Unused
Label 353 Fault Codes for AC03 and BC03Table 422
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SECTION 6INTERCONNECTS
This section provides interconnect information for the SPZ-8000 System (Table501) as an aid in troubleshooting the System should any failure occur duringGROUND CHECK.
NOTICE
Procedures in Table 501 are based onEngineering Bulletin EB701O494, Rev P.
Table 501 is not intended to be used forinitial installation of optional systems.Any installation information listed in theAppendices is for reference only.
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Table 501 - Table of Contents
Paraqra~h $ub.ject
1.0 Introduction
2.0 List of Figures Incorporated in this Table (501)
3.0 Electrical Installation Design
3.1 Power Requirements3.2 Grounding Requirements3.3 Avionics Standard Communication Bus (ASCB)
Installation3.4 Interconnect Format Definition3.5 Interconnect Requirements
4.0 Electrical Interconnect Definition
Pilot’s UnitConnector
Designation No.
9
10
11
12
13
14
20
29
29A
59
61
Unit Name
Digital Air Data Computer No. 1
Flight Guidance Computer No. 1
Guidance Panel
Autopilot Aileron Servo
Autopilot Elevator Servo
Bertea Rudder Actuator
Radio Altimeter No. 1
Trim Elevator Servo
Trim Elevator Servo Bracket
Weather Radar R/T
Weather Radar Controller No. 1
502
502
505
505511513
519520
521
522
528
540
546
548
550
551
552
554
555
559
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Pilot’s UnitConnector
Designation No. Unit Name ~
65
115
120
121
122
123
L128
R128
129
130
131
132
133
134
135
136
137
149
170
171
172
198
Symbol Generator No. 1 562
Display Controller No. 1 568
Control Display Unit No. 1 572
Navigation Computer No. 1 574
Performance Computer No. 1 581
Data Loader
Autothrottle Servo
Autothrottle Servo
Manual Controller
Display Unit No. 1
Display Unit No. 2
Display Unit No. 3
Display Unit No. 4
588
No. 1 589
No. 2 590
591
592
596
598.2
598.6
Fault Warning Computer No. 1
Display Brightness Panel
Data Acquisition Unit No. 1
Data Acquisition Unit No. 2
Global Positioning System SensorUnit No. 1 (Optional)
Inertial Reference Unit No. 1
Inertial System Display Unit (Optional)
Mode Select Unit
Navigation Display Unit (Optional)
598.10
598.19
598.20
598.29
598.38
598.38.1
598.38.6
598.38.9
598.38.12
Interconnect InformationTable 501 (cent) 22-14-00
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Copilot’s UnitConnector
Designation No.
C9
c 10
c 20
C 61
C 65
E 65
C115
C120
C121
C122
C130
C131
C134
C149
C170
E170
Ap~endices
Appendix A
Appendix B
Appendix C
Appendix D
Unit Name
Digital Air Data Computer No. 2
Flight Guidance Computer No. 2
Radio Altimeter No. 2
Weather Radar Controller No. 2
Symbol Generator No. 2
Symbol Generator No. 3
Display Controller No. 2
Control Display Unit No. 2
Navigation Computer No. 2
Performance Computer No. 2
Display Unit No. 6
Display Unit No. 5
Fault Warning Computer No. 2
Global Positioning System SensorUnit No. 2 (Optional)
Inertial Reference Unit No. 2
Inertial Reference Unit No. 3 orAttitude Heading Reference Unit
Subject
Symbol Generator/Display Unit InterfaceRequirements
Electronic Display System Reversionary Selection
Listing of all Discrete Inputs/Outputs to theSPZ-8000 System Components
AFGCS Schematics (See Para. 2.0 for listing)
—
Paqe
598.38
598.44
598.56
598.58
598.60
598.66
598.73
598.77
598.79
598.85
598.92
598.96
598.100
598.108.1
598.108.2
598.108.7
598.110
598.122
598.135
598.216
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I
AR~endices Sub.iect Paqe
Appendix E Environmental Tests 598.243
Appendix F LSZ-850 Lightning Sensor System Installation 598.250
Appendix G Spare Flight Management System Installation 598.264
Appendix H P-800 Weather Radar System Installation 598.296
Appendix I VLF/Omega System Installation 598.311
Appendix K Microwave Landing System (MLS) Installation 598.339
Appendix L Traffic Alert and Collision Avoidance System 598.367(TCAS) Installation
Appendix M TACAN Installation 598.406
Interconnect InformationTable 501 (cent)
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1. Introduction
This Table contains system com~onent interconnection information andlighting, power, inte;lock, and switching schematics.
2. List of Figures Incorporated in this Table.
Fiqure No.
3-1
3-2
3-3
3-4
3-5
3-6
3-7
3-8
Appendix A
A-1
A-2
A-3
A-4
A-5
A-6
Title
Automatic Flight Guidance Control SystemPower Distribution
Electronic Display System Power Distribution
Flight Management Computer System PowerDistribution
Miscellaneous Sensors Power Distribution
Inertial Reference System Power Distribution
Deleted
ASCB Bus Coupler
G-IV ASCB Interconnect
Symbol Generator No. 1 (Bus A/Display UnitInterconnect)
Symbol Generator No. 1 (Bus B/Display UnitInterconnect)
Symbol Generator No. 1 (WXR/Display UnitInterconnect)
Symbol Generator No. 2 (Bus A/Display UnitInterconnect)
Symbol Generator No. 2 (Bus B/Display UnitInterconnect)
Symbol Generator No. 2 (WXR/Display UnitInterconnect)
~
507
508
509
510
510.1
---
514
517
598.112
598.113
598.114
598.115
598.116
598.117
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Fiqure No.
A~~endix A
A-7
A-8
A-9
ARc)endix B
B-1
B-2
Armendix C
None
AD~endix D
D-1.l
D-1.2
D-1.3
D-1.4
D-1.5
D-1.6
D-1.7
D-1.8
D-1.9
D-1.1O
Title
Symbol Generator No. 3 (Bus A/Display UnitInterconnect)
Symbol Generator No. 3 (Bus B/Display UnitInterconnect)
Symbol Generator No. 3 (WXR/Display UnitInterconnect)
Electronic Display System’s External ReversionaryInterface Schematic for the G-IV
Reversionary Controller
Autopilot Quick Disconnect Schematic
Yaw Damper Engage/Disengage Switch andAnnunciator Schematic
Mach Trim Engage/Disengage Switch andAnnunciator Schematic
Take Off/Go Around Engage Switch Schematic
Touch Control Steering Engage Switch Schematic
Elevator Trim Switch Schematic
AFGCS Clutch Schematic
Autopilot Off Annunciator
Autopilot Off Horn
FGC Priority Status/Select Schematic
&
598.118
598.119
598.120
598.124
598.125
598.217
598.218
598.219
598.220
598.221
598.222
598.223
598.224
598.225
598.226
Interconnect InformationTable 501 (cent) 22-14-00
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Fiqure No.
Ar)pendix D
D-2.1
D-2.2
D-2.3
D-2.4
D-2.5
D-2.6
D-2.7
D-3.1
D-3.2
D-3.3
D-3.4
D-4.1
D-4.2
D-5.1
D-5.2
D-6.1
D-7.1
D.7.2
A~~endix E
None
Amendix F
F-1
Title
Caution/Warning Reset and Scroll Switch Schematic
Trend and Limit Memory Erase Switch Schematic
Data Down Load Initiate Switch Schematic
Comparison Monitor Reset Switch Schematic
ILS/MLS Switching Schematic
Joystick Schematic
Trend and Limit Manual Exceedance Recording
Autothrottle Off Horn
A/T Engage/Disengage Switch Schematic
A/T Disconnect Switch Schematic
Autothrottle Off Annunciator
P-870/EFIS Interface
SG/WX Range Discrete Interface
AOA Chevron Annunciator Schematic
Maintenance Test Enable Switch Schematic
AFIS Interconnect Schematic
Dimming and Test Panel Interconnect
Battery and Charger Interconnect
G-IV Lightning Sensor System Block Diagram
598.228
598.229
598.230
598.231
598.232
598.233
598.234
598.234.2
598.235
598.236
598.236.1
598.238
598.238.1
598.240
598.241
598.242.1
598.242.3
598.242.4
598.251
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Fiqure No.
A~Dendix G
G-1
G-2
G-3
G-4
G-5
G-6
G-7
G-8
G-9
AD~endix H
H-1
Appendix I
I-1I-2
Appendix K
K-1K-2K-3
Appendix L
L-1L-2
Appendix M
M-1
Title
Three FMS Installation Block Diagram
FWC Interface to Spare FMS
Data Loader Interface to Spare FMS
PMS Interface to Spare FMS
ASCB Interface to Spare FMS
Spare FMS Radio Switching
FMS Discrete Switching
Long Term Sensor Switching
Input Power Switching
WX Source Switching Schematic
Single VLF/Omega InstallationDual VLF/Omega Installation B“
MLS in G-IV Svstem Block Diaa
B1ockock D
am
Diagramagram
MLS System Schematic - Typic~l (Pilot’s Side)MLS System Schematic - Typical (Copilot’s Side)
G-IV TCAS SystemG-IV TCAS System Wiring Diagram (Typical)
TACAN System Schematic
Paqe
598.265
598.284
598.285
598.286
598.287
598.289
598.291
598.293
598.294
598.297
598.314598.315
598.343598.345598,347
598.371598.373
598.409
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3.0 ELECTRICAL INSTALLATION DESIGN
3.1 Power Requirements
3.1.1 AC Power - The aircraft ac power inverters must supply single phase 115volts (rein104, max 122) 400 Hz 120 Hz sine wave with a maximum totalharmonic distortion of 5% and 26 volts (rein23.5, max 27.5) 400 Hz *2OHz sine wave with a maximum total harmonic distortion of 5%. Under allload conditions, amplitude modulation of the power supply shall notexceed 2 percent at any frequency. (Percent modulation is defined asone-half of the peak to peak modulation envelope divided by the carrieramplitude and multiplied by 100.) With its load rating, the powersupply’s output impedance shall be less than .3 ohm for sinusoidal loadvariations at all frequencies below 10 Hz.
3.1.2 DC Power - The aircraft dc power supply must be 28 Vdc (nominal). Thenormal minimum and maximum allowable voltages are 22.0 and 29.5 Vdcrespectively (DO-160 CAT A).
3.1.3 Power Distribution - See Figures 3-1 thru 3-4 for independent subsystempower requirements.
3.1.4 Power Supplied to LRU’S - The voltage level of the power supplied to theLRU’S is important in this installation. The potential is thedifference between the power pins and power ground pins at the LRU.Excessive voltage drops in the power wire(s) and power ground wire(s)may cause one or more of the following conditions:
a. LRU to draw additional current from the aircraft supply system.
b. Since the LRU is drawing more current, they produce more heat, moreheat causes lower LRU MTBF’s.
c. LRU shutdowns, even though the aircraft supply system voltages arewithin normal minimum and maximum levels.
Therefore, the recommended maximum total combined voltage drop (voltagedrop of the power wire(s) plus voltage drop of the power ground wire(s))is 1.0 volt. Voltage drop is a function of current and resistance(Resistance in this case is a function of wire gauge and wire length).See Chart 3-1 for determining proper wire gauge for LRU power and powerground wires.
Interconnect InformationTable 501 (cent)
22-14-00Page 505Jun 1/87
Use or dmclosure of mformatron on thm page IS subject to the reslnct!ons on the t!tle page of this document
wm181614EL:T’c:’LE:ART6”4A’”
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200 350 25
160 200 20
I20 210 15
100 I 75 12
80 140 1079 I ?0 ‘)
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“THE GPSSU IS OPTIONAL EQUIPMENT . ONE OR TWO MAY BE INSTALLED.
THE ISDU AND NDU ARE OPTIONAL EOUIPMENT - AN lNSTALLATI~2NMAY HAVE ONE OR THE OTHER BUT NOT BOTH.AD-35176M
Inertial Reference SystemPower Distribution
Figure 3-5
Interconnect InformationTable 501 (cent) 22-14-00
Page 510.1/510.2Apr 15/93
Use or disclosure of information on this page is subject to the restrictions on the title page of this document.
3.2 Grwnd~ng Requirements
Good grounds are a key factor In a good ~nstallatlon. Each ground shouldbe run as a separate wire and terminated at one central point. Thefollowing special requirements shall be met.
a. Chassis ground shall be terminated td the frame of the aircraft withminimum wire length from the mating connector.
b. All shielded wires shall have the shields tied at one end only to theaircraft frame or central groun6 point except where noted. Either endof the shielded pair may be terminated to the airframe ground exceptwhere explicit shielding terminations are given.
c. Grounds should be grouped by function; that is: AC grounds on onegroup of terminal blocks, DC grounds on another group, and Signalgrounds on another group. The DC power ground is for high current DCreturns, AC ground is for high current AC returns, and signal groundis for DC and AC signal references. All terminal block grounds areattached to the airframe at one central location.
d. Servo Power Grounds 1OJ1A-5, C1OJ1A-5, 12J1-10, 12J2-10, 13J1-10 and13J2-10 snail be terminated at a common point which is also tied toaircraft ground.
e. Trim Servo Power Grounds 29J1-10, 29J2-10, 1OJ1A-2 and CIOJIA-2 shallbe terminated at a common point which is also tied to Aircraft Ground.
f. All AC grounds shall be tied together, all DC grounds shall be tiedtogether and all signal grounds shall be tied together. All AC, DCand signal grounds shall be tied together at a single point andconnected to the airframe.
Interconnect InformationTable 501 (cent) 22-14-00
Page-5ilJun 1/87
Use or dwclosure of mtormatlon on thm page IS subject to the restrlcttons on the I!tle page of thm documenl
3.2 Groundinq Requirements (cent)
It is very important that this grounding technique be adhered to. Do nottie the various ground wires to multiple aircraft frame points and dependon the aircraft structure itself to provide a low impedance path for theindividual grounds. ONLY chassis grounds and shield grounds are groundedat multiple points in the aircraft.
T
r .—‘1
I II CENTRAL
AIRCRAFT II GNDBLOCKS II IL —— –-l
\ v JTOVARIOUSAIRCRAFT LOCATIONS AD-464
D’1 Because signal grounds are low currents, multiple signal grounds can be
connected to remote aircraft terminal blocks other than the centralgrounding blocks as long as these remote terminalblocks are isolatedfromground. The various remote signalground blocks must all be grounded onlyat the aircraft central grounding point. For example, if ten signalgrounds are connected to a remote terminal block, a minimum of onegrounding wire must be run from this terminal block to the aircraftcentral ground point.
Interconnect InformationTable 501 (cent) 22-14-00
Page-5i2Mar 15/91
Use or disclosure of mformatlon on this page w subject to the r<.strlctlons on the title page of thm document,
3.3 Avionics Standard CommunicationBus (ASCB) InstallationFor The G-IV
The ASCB is the primary communicationpath between major subsystems of theSPZ-8000 Integrated Avionics System. Physically, it consists of twomulti-point serial synchronous digital communications networks, eachelectrically isolated from the other, and each capable of maintaining fullinter-systemcommunicationin the event of a failure on the other. The ASCBcomplies with RTCA Document DO-160A which requires that the followinginstallation requirementsbe met:
a. There are two independentASCB’S denoted “A” and “B”, each consistingof one wire pair.
b. TheASCB transmissionlines shall be Raychem2524EOl14 with a thermoradjacket or its equivalent.
c. Each ASCB transmission line pair shall have a characteristic impedanceof 125 ohms t 5 ohms. The characteristiccapacitance shall be 12 t 2picofarads/foot.
d. Each ASCB transmission line pair shall be terminated at its two endswith non-inductive 127 ohm resistors t 1%, 1/4 watt, metal film. Thecable length between the last stub and the termination resistor shallbe 24 inches.
e. The ASCB transmission lines shall have a maximum length betweenterminators of 150 feet.
f. Stub lengths at each user pickoff shall not exceed 36 inches. Stubconnections to the main bus shall be accomplished via bus couplersconfigured as illustrated in Figure 3-7.
9. The shield connections at each stub shall be accomplished via the buscoupler.
h. All bus couplers shall be electricallybonded to the aircraftstructure.
i. The ASCB transmission lines shall be connected in a daisy chainfashion between user subsystem.
Interconnect InformationTable 501 (cent) 22-14-00
Page-513Mar 15/91
Use or disclosure of information on thm page m subject to the restrictions on the title page of this document.
BU
(L (WHITE) OUTER RING
(H (TAN) CENTER PIN
ASCB Bus CouplerFigure 3-7
AD-6794-RI
Interconnect InformationTable 501 (cent) 22-14-00
Page 514Jun 1/87
Use or dmclosure of Information on thm page IS subject to the restrictions on the tllle page 01 Ihls document
3.3.1 Avionics Standard Communication Bus Interconnect Installation
See Figure 3-8 for ASCB Interconnect.
Interconnect InformationTable 501 (cent) 22-14-00
Page 515/516Jun 1/87
Use or disclosure of mformatlon on thm page m subject to the restnchons on the Mle page of thm document
rz
f-——— —--. -.— -— .—— ——— ——— ——— — ——— ——.
1I
—I
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1’OCNO1 v
0CN02
115J2-AM I,,55A11 I
I El ‘1I
LC)AD55A47 II
l-- ‘——— —.— ——— ——
T——— ——— ——— ——.
1
IIIIIIIIII
IIII~
I
IIIII
I
II
III
I
II
55A14 LEFTTEST PANEL
II I r]L(lA~55A49,
[’ ~55A9~
122J1A33’34PZ NO 1
122J10-415
,
I55A6NZNO1
121J18.2&31
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wlB.13/14
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II
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65Jlf+46’47
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IIIIIIIIILE~
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III
I
II
IIIII
IIIIIII
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u
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C65J 18-46147 1;:155A48
c65Jf A.1617
SG NO 2
C65Jl B-16/17~ 55A15
1!
I 55A46
BG NO 3
SG NCI 3
BC NO 3 n
E65Jl B.4&47 -
II IL’ ——— ——— ——— ——— ——— —————— ——.
IIII
I
II
I
IIIIIIII
IIII
II
II
III
III
.— JAO 16044
2.4 Interconnect Format Definition
Each connection is typically shown as indicated ~n the figure below.
AIOBA A3 AAADESCRIPTION FROM PIN AWG TO PIN(S) COMMENTS
P
[:] SERVO DRIVE H 2$IAJ1-1 (22)-------29J1-zL 29AJ1-2 (22)-------29J1-1
A DESCRIPTION OF SIGNAL FUNCTION
~ FROM CONNECTION
XX AJ1 -XX
UNIT-TDESIGNATORCONNECTOR JPIN
A WIRE GAUGE SIZE
A TO CONNECTION
XX J1 -XX
IFE=
~ MISC. COMMENTS
Interconnect InformationTable 501 (cent) 22-14-00
Page 519Jun 1/87
Use or disclosure of Information on thm page IS subje( t to the reslrlctlons on the Mle page of this document
3.5 interconnect Requirements
3.5.1 Interlocks - The SPZ-8000 Integrated Avionics System utilizeselectrical and mechanical engage interlocks.
. The electrical interlocks consist of program pins on the unit’smating connector that electrically determine how a unit shallfunction.
. The mechanical interlocks are mechanically keyed connectors thatprevent units from being incorrectly connected or from beinginstalled.
3.5.2 Maintenance Test - An external switch located in the avionics rack isrequired to enable the Maintenance Test by providing a ground on theappropriate pin of each LRU. Maintenance test will also be interlockedwith Weight-on-Mheels to ensure against activation during flight.
3.5.3 Inertial Reference System
mTO ASSURE THE IRS MISCOMPAREUIRING IS CORRECT. THIS WIRING SHOULD BE100% CONTINUITY CHECKED. THIS IS TO INSURE PROPER AUTOPILOT VOTING OFIRS DATA. THE WIRES THAT ARE CRITICAL: IRU #3 JIA-E6 MUST GO TO FGC #1AND #2 JIB-95. IRU#3 JIA-E7 MUST GO TO FGC #1 AND #2 JIB-96. THISWIRING IS ALSO NOTED IN THE INTERCONNECT SECTION OF THIS DOCUMENT.
3.5.4 Weather Radar System - Cable runs shall be limited to less than 50feet.
EFIS control and picture bus connections shall be made using twisted,shielded pair having a characteristic impedance of 70 ohms tlo%.
Chassis ground to aircraft ground connections shall be made using 20AWG stranded wire. Resistance between these two connections shall be<0.1 ohm.
Interconnect InformationTable 501 (cent) 22-14-00
Page 520Apr 15/93
Use or disclosureof information on this page issubject to the restrictions on the title page of this document
4.0 ELECTRICAL INTERCONNECT DEFINITION
This section provides the electrical interconnect definition for theSPZ-8000 Digital Integrated Flight Guidance System as it is installed inthe G-IV.
This interconnect is ordered per unit connector designation numbers.Reference Table 1-1 for these numbers.
m:
1 THIS PIN IS PROVIDED TO ALLOW THE USE OF A LOCAL GROUND FORPROGRAMMING PINS IN ORDER To REDUCE WIRE LENGTHS. THIS PIN SHOULDNOT 8E TIED TO ANY AIRCRAFT GROUND.
2 ASSIGN AIRCRAFT J-BOX TERMINAL FOR EACH WIRE TO BE USED FORINSERTING FLIGHT TEST SIGNALS VIA THE FTIU.
3 SEE PARA. 3.1.4 FOR DETERMINING PROPER WIRE GAUGE.
4 AN ASTERISK SYMBOL (*) AFTER A FUNCTION NAME MEANS THAT FUNCTIONIS ENABLED WITH A SIGNAL GROUND.
5 A DIODE IS NEEDED TO BE PLACED IN PARALLEL WITH THE RUDDERACTUATOR ENGAGE SOLENOID TO REDUCE BACK EMF FROM THAT SOLENOID.IF THAT DIODE IS NOT IN PLACE, THE BACK EMF FROM THE SOLENOID WILLTRIP THE FGC INTERNAL MONITORS, WHEN FGC’S ARE SWITCHED WITH THEYAW DAMPER ENGAGED.
6 OPTIONAL EQUIPMENT DENOTED BY (OPT).
Interconnect InformationTable 501 (cent) 22-14-00
Page 521Apr 15/93
Use or disclosure of information on this page is subject to the restrictions onthetitlepagc of this document
Digital Air Data Computer No. 1
IOBP Function Connector Pin Connects To
(P) 28 VDCHI 9J1A-1 (NOTE 3)---------------- A/C 28 V DC PWR(P) 28 VDCHI -2 (NOTE 3)---------------- A/C 28DC PWR(P) 28 VDC RETURN -3 (NOTE 3)---------------- A/C PWR GND(P) 28 V DC RETURN ~~ \]~;E 3)---------------- A/C PWR GND(P) SIGNAL GROUND -------------------- SIG GND(P) SIGNAL GROUND 4 (22)-------------------- SIG GND
[;] DC GROUND -7 (22)-------------------- A/C GNDDC GROUND -8 (22)-------------------- A/C GND
(P) CHASSIS GROUND -9 (22)-------------------- CHASSIS GND(P) CHP.SSISGROUND -10 (22)---D-- ------------ CHASSIS GNC(B) SYSASCB PRIMARY BUS (H)
[-11 (22)--~-7- ------------ SEE SECT 3.3
>(8) ~~;R;SCB PRIMARY BUS (L) +; (22)---s-- ------------
SPARE -14SPARE -15SPARE -16SPARE -17SPARE -18SPARE -19SPARE -20SPARE -21SPARE -22SPARE -23SPARE -24SPARE -25SPARE -26SPARE -27SPARE -28SPARE -29SPARE -30SPARE -31SPARE -32SPARE -33
(0) ALT VALID (28 V DC/OPEN) -34 (22)------------------- STALL WARNCOMPUTER #1,
I
REF APPX C(I) BARO POT (H) -35 (22)-------,+ -------- 115J2-L(1) BARO POT (w) -36 (22)---------- -------- 115J2-M(I) BARO POT(I) BARO DISA8LE*
(L) -37 (22)------J+ -------- 115J2-N-38 ------NC
}
REF APPX C(I) SSEC DISABLE* 9J1A-39 ------NC
Interconnect InformationTable 501 (cent) 22-14-00
Page 522Feb 1/88
Use or dE.CIOSUreof Intormahon on thm page IS subject to the restrtctlons on the title page of thm document
Digital Air Data Computer No. 1
106& Function Connector Pin Connects To
SPARE 9J1A-40SPARE -41SPARE -42SPARE -43SPARE -44SPARE -45SPARE -46SPARE -47SPARE -48SPARE -49SPARE -50SPARE -51
(I) AIR DATA SELF TEST* -52 ------NCSPARE -53SPARE -54
(1) FLAP POS #1 ((lDEG*) -55 (22)------------------ A/C WIRING(1} FLAP POS #2 (10 DEG*)
}
-56 (22)------------------ A/C WIRING A~PX(I) FLAP POS #3 (20 DEG*) -57 (22)------------------ A/C WIRING(1) [;;IJVEPOS#4 (39 DEG*) -58 (22)------------------ A/C WIRING
-59SPARE -60SPARE -61
(I) CABIN PRESS REF (H)
i
-62 (22)+- ----------- A/c WIRING(0) CABIN PRESS RATIO (W) -63 (22)---rl------------ A/CHIRING(I) ;;~~ PRESS REF (C) +: (22)---V- ----------- A/CWIRING
(0) CABIN PRESS RATIO VALID -66 (22)------------------ ~l&W/RING,(GND/OPEN)SPARE -67SPARE -68SPARE -69SPARE -70SPARE -71
(1) TEMPERATURE PROBE (H)+
-72 (22)----X- ---------- A/C WIRING(1) Wl;;RATURE PROBE (L) -73 (22)---!~-- ---------- A/C WIRING
-74SPARE -75SPARE -76
(0) ALTITUDE SWITCH -77 ------NC REFAPPX C(0) PRESSURE ALT SIG (H) 9J1A-78 (22)------------------ STALL WARN
COMPUTER #l
Interconnect InformationTable 501 (cent) 22-14-00
Page 523Mar 15/91
Use or d~sclosure of mformallon on thts page IS subject to the restncuons on the !Itle page of Ihls document.
Digital Air Data Computer No. 1
IOB& Function Connector Pin Connects To
SPARE 9J1A-79(0) ALT SWITCH COMMON -80 (22)------------------- A/CWIRING,
REF APPX C(I) AOA TEST MODE SW COMMON -81 (22)------------------- A/C SIGGND(I) AOA TEST SW COMMON (SL) -82 ------NC(I) ::~R:EST SW COMMON (15K) -83 ------NC
-84(0) OVERSPEED WARNING -85 (22)------------------- A/CWIRING,
(28 V DC/OPEN) REF APPX CSPARE -86SPARE -87SPARE -88SPARE -89SPARE -90SPARE -91
(0) AOA TEST MODE SELECT -92 (22)------------------- STALL WARN(GND/OPEN)
1
COMPUTER #1(I) ALERTER SELECT (OPEN/GND) -93 (22)------------------- C9J1A-93,
1OJ2B-88,C1OJ2B-88
(0) AOA INDEXER (RED) -94 (22)------------------- APPXD REF(GND/OPEN) APPX
(0) AOA INDEXER (GREEN) -95 (22)------------------- APPXD C(GND/OPEN)
(0) AOA INDEXER (YELLOW) -96 (22)------------------- APPXD(GND/OPEN)
J
(0) AOA TEST MODE (SL) SELECT -97 ------NC(GND/OPEN)
(0) AOA TEST MODE (15K) SELECT -98 ------NC(GND/OPEN)SPARE -99
(I) PILOT/COPILOT* -1oo ------NC(I) AIRCRAFT ID IDO
1
-101 (22)------------------ A/C GND(I) AIRCRAFT ID ID1 -102 ------NC REF(I) AIRCRAFT ID ID2 -103 ------NC APPX(1) AIRCRAFT ID ID3 -104 (22)------------------ A/CGND C(I) AIRCRAFT ID ID4 -105 ------NC(I) AIRCRAFT ID ID5 9J1A-106 (22)------------------ A/C GND
Interconnect InformationTable 501 (cent) 22-14-00
Page 524Mar 15/91
Use or disclosure of information on this page IS subject to the r%tnctlons on the Ittle page of this document.
Digital Air Data Computer No. 1
I(IEI~ Function
SPARESPARESPARESPARESPARESPARESPARESPARESPARESPARESPARESPARE
[6) SYS ASCB SECONDARY(8) ;~jR~SCB SECONDARY
SPARESPARESPARESPARESPARESPARESPARESPARESPARESPARE
~ Connects To
-12(H)
$-13 (22)---C--- ----------- SEE SECT3.3
(L) :;; (22)--~’--- --------.--
-16-17-18-19-20-21-22-23-24-25
(B) ARINC 429 OUTPUT #l (H) -26 (22)--+$
----------- 65J1A-39{B) ARINC 429 OUTPUT #l (L) -27 (22)--+ ------------ 65J1A-40
SHIELD GND------------
Interconnect Information
SPARE -28SPARE -29
(B) ARINC 429 OUTPUT #3 (H) -30 (22)--n-
$
----------- 170J1B”K4,II C170JIB-K4
(B) ARINC 429 OUTPUT #3 (L) -31 (22)-- -------------- 170J1B-K5,YSHIELD GND-----------
$
C170J18-K5(B) ARINC 429 OUTPUT #4 (H) -32 (22)--fl- ----------- A/C WIRING{B) ARINC 429 OUTPUT #4 (L) -33 (22)-- - - ------------ A/C WIRINGYSHIELD GND-----------
SPARE -34SPARE -35SPARE -36SPARE -37SPARE -38SPARE 9J1B-39
Table 501 (cent)22-14-00
I
Page 525Apr 15/93
Use Or disclosure of information on this page is subject to the restrictions on the title page of this document,
I:E!
(0)
(o(o1
(1)
(B)
(B)
Digital Air Data Computer No. 1
Function Connector Pin
SPARE 9J1B-40SPARE -41SPARE -42SPARE -43SPARE -44SPARE -45SPARE -46SPARE -47SPARE -48ALT ALERT HORN (28V/OPEN) 4; (22)-------------------SPARESPARE -51SPARE -52AOA REF (H
1
f
-53 (22)--fi- ------------~$~R~EF (L 1:$ (22)--ii-- ------------
SPARE -56 itSPARE -57SPARE -58
::
SPARE -59II
~~~R~IG (W) -60 (22)--~----.-------.----61
SPARE -62SPARE -63SPARE -64SPARE -65SPARE -66SPARE -67SPARE -68SPARE -69ARINC 429 OUTPUT #2 (H)
1
-70 (22)--,?- -------------
~1
ARINC 429 OUTPUT #2 (L)Jt *
-71 (22)-V----------------
SPARE -72SPARE -73SPARE -74ALT ALERT ANNUN (GND/OPEN) -75 (22)-------------------~~~R~LERT HORN (GND/OPEN) ~~: (22)-------------------
SPARE -78SPARE 9J1B-79
Connects To
A/C WIRINGAPPX C
TOAOA PROBETO AOA PROBE
TO AOA PROBE
E65J1A-39,C65J1A-39E17OJ1B-J1O,APPX LE65JIA-40,C65JIA-40E170J1B-J1l,APPX L
A/C WIRING REF)A/C WIRING APPX
rL
Interconnect InformationTable 501 (cent) 22-14-00
Page 526Apr 15/93
Use or disclosure of information on this page is subject to the re: trictions on the title page of this document.
IOB~ Function
RESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDSPARESPARESPARERESERVEDRESERVEDSPARESPARESPARERESERVEDRESERVEDRESERVEDRESERVED
(I) ALT SELECT TACH(I) $~R;ELECT TACH
SPARE
Digital Air Data Computer No. 1
Connector Pin Connects To
9J1B-80-81-82-83-84-85-86-87-88-89-90-91-92-93-94-95-96-97-98-99-1oo-101-102
(H)1
-103 (22)---’->------------ llJ1-30(L) -104 (22)--!Cj- ----------- llJ1-31
-1059J1B-106
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure Ot mformatlon on Ihls page IS sublet to the restrictions on the title page of Ihm document
(P)
(P)
(P)(P)
(P)
(P)(P)
(P)(P)
(I)
(o)(o)
(o)
(1)
Flight Guidance Computer No. 1
Function Connector Pin
28 VDC PWR 10JIA-1 (NOTE 3)----------------(STAB AUG SERVO PWR)28 V DC PWR RTN -2 (NOTE 3)----------------(STAB AUG SERVO P14RRTN)CHASSIS GND -3 (22)--------------------28 V DC (AUTO PILOT -4 (NOTE 3)----------------SERVO PWR)28 V DC (AUTO PILOT “5 (NOTE 3)----------------SERVO PWR RTN)28 V DC COMPUTER POWER -6 (t’’mTE3)----------------28 V DC COMPUTER POWER -7 (NOTE 3)----------------RTN28 V DC COMPUTER POWER -8 (NOTE 3)----------------28 V OC COMPUTER POWER -9 (NOTE 3)----------------RTNSPARE -10SPARE -11SPARE -12SPARE -13SPARE -14SPARE -15SPARE -16SPAREHDG SEL (H)HOG SEL (L)SPAREAP BRAKE (28V DC/OPEN):$:~EBRAKE (28 V DC/OPEN)
SPARERESERVEDSPARESPARESTICK SHAKER ACTIVE(28V/OPEN)SPARESPARESPARESPARE 103
-i7-18 (22)---19 (22)---20-21 (22}---22 (22)---23-24-25-26-27-28 (22)--
-29-30-31
1A-32
f\ I...----..-It------ ---\/
-- - - - - -- ., -------- ---
--------------
---------------
.------
Connects To
A/C 28 V DC PWR
A/C 28 V DC RTN
A/C CHASSIS GNDA/C 28 V DC PWR
A/C 28 V DC P14RRTNA/C 28 V DC PWRA/C 28 V DC PWRRTNA/C 28 V DC PWRA/C 28V DC PWRRTN
llJ1-26llJ1-27
12P2-21, 13P2-2129J2-21
A/C WIRING REFAPPENDIX C
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Flight Guidance Computer No. 1
IOB~ Function Connector Pin Connects To
(1) TRIM DN CMD 10J1A:4: (22)------------------- APPENDIX DSPARESPARE -35SPARE -36
(0) PRIORITY STATUS Ill -37 (22)------------------- llJ1-70,(28V/OPEN) l15J1-a,
Cl15J1-a, APPX CSPARE “38SPARE -39
(1) Y/D ENGAGE/DISENG -40 (22)------------------- APPENDIXD,(OPEN/GNO TOGGLE) REF APPENDIX C
(I) TRIM ENGAGE/DISENG -41 (22)------------------- APPENDIX O,(OPEN/GND TOGGLE) REF APPENDIX CSPARE -42SPARE -43SPARE -44SPARE -45SPARE -46
(I) :$;?EUP CMD -47 (22)------------------- APPENDIXD-48
SPARE -49SPARE -50SPARE -51SPARE -52SPARE -53SPARE -54SPARE -55SPARE -56SPARE -57
(0) YAW DAMP ENGAGE (28V/OPEN) -58 (22)------------------- I4P1-A,C1OJ1A-58134J1B-26,C134J1B-26,
1
APPENDIX D(o) RUDDER ACTUATOR EXEC (H) -59 (22)---+1- ---------- 14J1-M(o) RUDDER ACTUATOR EXEC (L) -60 (22)-----C>----------- 14J1-J
SHIELD GND-----J(I) RUD LVDT FEEDBACK (H) -61 (22)-----’-~-*---------- 14J1-L(I) RUD LVDT FEEDBACK (L) 1OJ1A-62 (22)----!~;------------ 14J1-K
SHIELD GND-----~
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Flight Guidance Computer No. 1
IOB_P_ Function Connector Pin Connects To
(o)1
RUD ACTUATOR DRIVE (H)1OJ1A-63 (20)-----;2,----------- 14J1-F(o) RUD ACTUATOR DRIVE (L) -64 (20)-----ci- ---------- 14J1-E
SHIELD GND-----
SPARE -65SPARE -66SPARE IOJIA-67
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Use or disclosure of mformatlon on this page IS subject 10 the reslrlctlons on the Mle page of Ihts document
Flight Guidance Computer No. 1
IOBP Function Connector Pin Connects To
(B) SYSASCB PRIMARY
‘ ‘i------------}REF,EcTIoN3*3
1OJ1B-1 (22)---=-BUS HI
(B) SYS ASCB PRIMARY -2 (22)--g- --------------BUS LOSPARE -3RESERVED -4RESERVED -5SPARE -6
(?) SPEED CMD (H)1
-7 (22)--:--- ------------- ilJ1-24(I) (L) -8 (22)--+ ------------- llJ1-25
SPARE QSPARE :io
(I) V/S CMD (H) -11 (22j--~-4
------------- llJ1-28(1) (L) -12 (22)-L+ ------------- llJ1-29
SPARE -13SPARE -14SPARE -15
(I) PITCH UP TRIM LIMIT -16 (22)------------------- 29AJ1-6SPARE -17SPARE -18
(1) PITCH DN TRIM LIMIT -19 (22)------------------- 29AJ1-5SPARE -20SPARE -21SPARE -22SPARE -23SPARE -24SPARE -25SPARE -26SPARE -27SPARE -28SPARE -29SPARE -30SPARE -31SPARE -32SPARE -33SPARE -34SPARE -35
(0) A - PROC DAC #3 -36 (22)-------------------(0) A - PROC DAC #4 A-37 (22)------------------- 2(0) A - PROC DAC #5 -38 (22)-------------------(0) A - PROC DAC #6 1OJ1B-39 (22)-------------------
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Icm~
(1]
(I)(o)(G)
(o)
(o)
(I)(I)
(I)(1)
(1)(2){1)
FunctioQ
SPARESPARESPARESPARE
Honeywell
Flight Guidance
(H)26 VAC REF
(L)5 - PROC DAC #3B - PROC OAC #4SPARESPARESPARESPAREB - PROC DAC #5SPARESPARESPARESPAREB - PRC)CDAC #6SPARESPARESPARESPARESPARESPARE
nector P~
MANUALGULFSTREAMIV
Computer No. 1
1OJ1B-4O-41-42-43
t-44 (22)----- -----------””
t-4s (22)----- ----”---------46 22)-------------------
[-47 22}--------------------48-49-50
ts TQ
29J1-3,26 V AC PURSIG GND
A2
-ii
A-52 (22)------------------- 2-s3-s4-s5-s6-s7 (22)--------------------58“s9-60-61-62-63
FLIGHT TEST INWT #1 (H) -64 (22)-------------------FLIGHT TEST INPUT #1 (L) 4: (22)-------------------SPARESPARE -67
tELEVATOR TACtiFEEDBACK (H) -68 (22)---F:- ------------ELEVATOR TACH FEEDBACK (L) -69 (22)---=>- ------------
iAILERON TACH FEEDBACK (H) -70 (22)-+;- ------------AILERON TACH FEEDBACK (L) -71 (22)---C;;;- ---------
ITRIM TACH FEEDBACK (H)1OJ1B-72 (22)----ir-i- ---------
A2
A2
13J1-1713J1-16
12J1-2712J1-1629W-16
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Flight Guidance Computer No. 1
IOB~ Function Connector Pin Connects To
(I)II +
TRIM TACH FEEDBACK (L)1OJ1B-73 (22)---U -------------- 29 1-17(I) FLIGHT TEST INPUT#2 (H) -74 (22)-------------------~:] FLIGHT TEST INPUT #2 &) ~~~ (22)------------------- A
(I) 102 -77~~] A/C IDENTIFICATION ID3 -78
1
REFID4 -79 (22)------------------- SIGGND APpX
(I) IDS -80 ‘ID6 -81 (22)------------------- SIG GND
SPARE -82SPARE -83SPARE -84
(I) CS TRIM DN CMD -85 (22)------------------- APPENDIXD(I) CS TRIM UPCMD -86 (22)------------------- APPENDIX D
RESERVED -87 ------NCSPARE -88SPARE -89SPARE -90SPARE -91SPARE -92SPARE -93SPARE -94
INSTALLATION CRITICAL - PINS 95 AND 96ARE CRITICAL. SEE PAGE 3-13.
(I) MISCOMPARE #1* -95 (22)------------------- C1OJ1B-95, ‘E170J1A-E6
(I) MISCOMPARE #2* -96 (22)------------------- C1OJ1B-96,E170J1A-E7
SPARE -97 REFSPARE -98 ~APPX
(I) RAD ALT FORMAT ID1 -99 ------NC c(I) RAD ALT FORMAT IDO -1oo -----NC
SPARE -101(1) PILOT/COPILOT I.D. #1 -102 (22)------------------ A/CGND(I) PILOT/COPILOT I.D. #2 -103 -----NC(I) END ITEM TEST -104 -----NC
SPARE -105(0) PROGRAM PIN GND 1 1OJ1B-106 1
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Flight Guidance Computer No. 1
IOB~ Function Connector Pin Connects To
SPARE 1OJ2A-1SPARE -2
(P) :;~M;L GND -3 (22)-------------------- A/CSIGNALGND-4
SPARE -5SPARE -6SPARESPARE iSPARE -9SPARE -loSPARE -11SPARE -12SPARE -13SPARE -14SPARE -15SPARE -16SPARE -17SPARE -18SPARE -19SPARE -20SPARE -21SPARE -22SPARE -23SPARE -24SPARE -25SPARE -26SPARE -27SPARE -28SPARE -29SPARE -30SPARE -31SPARE -32SPARE -33SPARE -34SPARE -35
(I) CROSS RADIO -36 (22)--~-j-
1
----------- C20J1-W,ALTITUDE (H) II C1OJ2B-26,
137J1A-50(I) CROSS RADIO 1OJ2A-37 (22)--&j- ----------- C20J1-N,
ALTITUDE (L) C1OJ28-27,137J1A-51,C20J1-E
{
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Flight Guidance Computer No. 1
IOB& Function Connector Pin Connects To
(I) CROSS RADIO 1OJ2A-38 (22)------------------ C20J1-Y,ALTITUDE VALID C10J2B-28,-
137J1B-19SPARE -39SPARE -40
(1) A/P CROSS PWR SENSE IN -41 (22)------------------- C1OJ2A-42(o) A/P CROSS PWR SENSE OUT -42 (22)------------------- CIOJ2A-41(I) STAB AUG PWR SENSE IN -43 (22)------------------- C1OJ2A-44(0) STAB AUG PWR SENSE OUT -44 (22)------------------- C1OJ2A-43(I) CROSS SERVO PWR SENSE IN -45 (22)------------------- C1OJ2A-46(0) CROSS SERVO PWR SENSE OUT -46 (22)------------------- C1OJ2A-45(I) CROSS SERVOS OFF IN -47 (22)------------------- C1OJ2A-48(0) CROSS SERVOS OFF OUT -48 (22)------------------- C1OJ2A-47(I) CROSS CHANNEL SYNC IN -49 (22)------------------- C1OJ2A-5O(o) CROSS CHANNEL SYNC OUT -50 (22)------------------- C1OJ2A-49(0) A-PROC DAC #1 -51 (22)-------------------(o) A-PROC DAC #2 A-52 (22)------------------- 2(o) B-PROC DAC #1 -53 (22)-------------------(o) B-PROC DAC #2 -54 (22)----- -------------(0) ELEVATOR SERVO DRIVE (H)
I-55 (20)-;-;- ------------- 13P1-1
(o) ELEVATOR SERVO DRIVE (L) -56 (20)--C-- ------------- 13P1-2SHIELDGND --d
(0) AILERON SERVO DRIVE (H)i
-57 (20)--:;- ------------- 12P1-1(0) AILERON SERVO DRIVE (L) -58 (20)--\-2-------------- 12P1-2
SHIELOGNO --d
(0) TRIM ORIVE UP -59 (20)------------------- 29J1-2(o) -60 (20)------------------- 29J1-1(0) AILERON AND EL~;ATOR -61 (22)------------------- APPENDIXD
CLUTCH DRIVESSPARE -62
(0) TRIM CLUTCH DRIVE -63 (22)------------------- APPENDIXOSPARE -64
(o) 5 V DC GP PWR#l -65 (22)------------------- llJ1-12(o) 5 V DC GP PWR RTN #1 -66 (22)------------------- lJ1-13(o) FDAC COMMON 1OJ2A-67 (22)-------------------
A
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IOB-y_
(B)
(B)
(I)
(I)
(I)
(r)
(I)
Function
SYS ASCB SECONDARYBUS HISYS ASCB SECONDARYBUS LOSPARERESERVEDRESERVEDSPARESPARESPARESPARESPARESPARESPARESPARESPARESPARESPARESPARESPARESPARESPARE ‘SPARESPARESPARESPARESPARERADIO ALTITUDE (H)
Flight Guidance Computer No. 1
RADIO ALTITUDE (L)
RADIO ALTITUDE VALID
B FLIGHT TEST (H)INPUT #1B FLIGHT TEST (L)INPUT #1
Connector Pin Connects ToI
1OJ2B-1 (22)---7~;-~---------]REFsEC TION33
-2 (22)---J& ------------
::-5-6
1-9-10-11-12-13-14-15-16-17-18-19-20-21-22-23-24-25-26 (22)--;-:-t------------ C1OJ2A-36,
I
1;
1
20J1-W, -136J1A-50
-27 (22)--!{;..------------ C1OJ2A-37,20J1-N,136J1A-51,20JI-E
-28 (22)------------------- 20J1-Y,C1OJ2A-38,136J1B-19”
-29 (22)-------------------
A 21OJ2B-3O (22)-------------------
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10/3& function
(I) BF~+Gl+; TEST
(1) fN~~~G~j TEST
SPARESPARESPARESPARESPARESPARESPARESPARESPARESPARESPARE
(1)(1) TRIM SERVO POS(I)
SPARESPARESPARESPARESPARESPARE
Flight Guidance Computer No. 1
Connector Pin Connects To
(H) 1OJ2B-31 (22)-------------------
A 2(L) -32 (22)-------------------
-33’34“35-36“37-38-39-40-41-42-43
(x)
1
-44 (22)---:~~ ------------ 29J1-18(Y) -45 (22)--i--( ------------ 29J]-19(z) -46 (22)---C-- --”--------- 29JI-20
-47-48-49-5a-51-52
{0] Y/D OISENGAGE ANNUN(28v/QPEN)
(I) AUTOPILOT DISCONNECT(OPEN/GND)
{1) TK POS REF(1) 7X REF GND(I) TK NEG REF{1) TK SIG (H}
(I) TK OUT OF DETENT
(1) CS TK SIG (H)
(I) :S& OUT OF DETENT
-53 (22)--------’----------
-54 (22)-------------------
-55 [22)--------------------56 (22)--------------------57 (22)--------------------58 {22)-------------------
-59 (22)-------------------
-60 (22)-------------------
-61 (22)-------------------1OJ2B-62
APPENDIX D,REF APPENDIX CAPPENDIX D,REF APPENDIX C129JI-3129JI-4129JI-3129J1-2,CIOJ2B-60129J1-8,C1OJ2B-61129J1-12,C1OJ2B-58129J1-17,CIOJ28-59
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Use or disclosure of mformatton on this page m sublect to the restrictions on Wm (Me pagt of this document
Flight Guidance Computer No. 1
IOB& Function Connector Pin Connects To
SPARE 1OJ2B-63SPARE -64
(I) EMERGENCY DISCONNECT -65 (22)------------------- 1OJ1A-6,\
(OPEN/28V) 1OJ1A-8(I) TRIM DISCONNECT (OPEN/GND)-66 (22)------------------- APPENDIX D(I) YAW DAMPER DISCONNECT -67 (22)------------------- SIGGND
(OPEN/GND)(I) TEST SIGNAL ENABLE* A-68 (22)------------------- 2(I) FTIU INSTALLED* ~;: (22)-------------------
SPARE REFSPARE -71 ‘APPX
(I) SPEED BRAKES DEPLOYED* -72 (22)------------------- A/CWIRING cSPARE -73
(I) WEIGHT ON WHEELS* -74 (22)------------------- A/CWIRINGSPARE -75SPARE -76SPARE -77
(I) GEAR DOWN* -78 (22)------------------- A/CWIRING(1) MAINTENANCE TEST ENABLE* -79 (22)------------------- APPENDIX D
SPARE -80(0) TRIM DISENGAGE ANNUN -81 (22)------------------- APPENDIXD,
(28V/OPEN)(I) PW%IR!PRESET GND INPUT A-82 (22)------------------- 2
-83SPARE -84SPARE -85SPARE -86SPARE -87
(0) PILOT/COPILOT* -88 (22)------------------- 9J1A-93,CPL SELECT OUT (OPEN/GND) C9J1A-93,
C1OJ2B-88,APPXC(0) ~~A~N VALID (28V/OPEN) -89 (22)------------------- llJ1-69
-90SPARE -91SPARE -92SPARE -93
(I) PITCH THUMB WHEEL (H) ’94 (22)---~T-
!
------------ C1OJ2B-104,129J1-18
(I) PITCH THUMB WHEEL (L) -95 (22)---’J- ------------ C1OJ2B-105,
$
129J1-19(0) PANEL STROBE (H) -96 (22)---~- ----------- llJ1-5(o) (L) 1OJ2B-97 (22)---1& ------------ llJ1-6
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of Information on thm page w sub)ect to the r +stnctlons on the title page of Ihts document.
Flight Guidance Computer No. 1
IOB~ Function Connector Pin Connects To
(0) PANEL CLOCK (H) 10J2B:;; [;$]--,:--+----------- ;\::-:(o) (L) --.--- -----------
(0) GP SERIAL DATA REC (H) -1oo (22)-R-*::::::::::: ;;:;-;(o) (L) -101 (22)--7-
(1) GP SERIAL DATA TRANS (H) -102 (22)--15~-$------------ llJ1-I
(I) GP SERIAL DATA TRANS (L) -103 (22)--G-- ------------ llJ1-2
(I) ~[~:~ PITCH THUMB (H) -104(22)---~r- 1------------
J
C1OJ2B-94,
/;- 129J1-21(I) ~~11:~PITCH THUMB (L) -105 (22)--
Y------------ C1OJ2B-95,
SHIELD GND------ 129J1-22(I) GP BUTTON ARM #1 1OJ2B-106 (22)------------------ ;llJ1-38
(GND/OPEN)
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Use or disclosure of information on this page m subysct 10 the reslrlctlons on the title page of this document,
Guidance Panel
IOB_p_ Function Connector Pin
*
Connects To
(I) SERIAL DATA REC #1 (H) llJ1-1 (22)------H- --------- 1OJ2B-102(I) SERIAL DATA REC #l (L) -2 (22)------
Y------------ 1OJ2B-103
SHIELDGND ------
(1) PANEL CLOCK #1 (H) J*-3 (22)-----(,- --------- 1OJ2B-98(I) (L) -4 (22)-----
Y------------- 1OJ2B-99
SHIELDGND ------
(I) PANEL STROBE #1 (H) -5 (22)------fi-$
--------- 1OJ2B-96(1) (L) -6 (22)----- -------------- 1OJ2B-97YSHIELD GND ------
fl$(0) SERIAL DATA TRANS #1 (H) -7 (22)----- - ---------- 10J2B-1OO(0) SERIAL DATA TRANS #1 (L) -8 (22)----- - - ---------- 1OJ2B-101YSHIELDGND ------
(P) CHASSIS GND -9 (22)-------------------- A/CGND(P) CHASSIS GND -10 (22)------------------- A/C GND(0) GS/EL ACTIVE GND #1 -11 (22)------------------- 11J2-11,
ILS/MLSRECEIVER,APPX C
(I) 5V DC A/P POWER #1 -12 (22)------------------- 1OJ2A-65(1) 5 V DC A/P POWER #1 RTN -13 (22)------------------- 1OJ2A-66(0) BC ACTIVE GND #1 -14 (22)------------------- 11J2-14, GPWS,
APPX C(P) 28 V DC ANNUN PWR #1 -15 (NOTE 3)--------------- A/C WIRING(P) :8VEDC ANNUN PWR #1 RTN -16 (NOTE 3)--------------- A/C WIRING
-17SPARE -18SPARE -19SPARE -20SPARE -21SPARE -22SPARE -23
(0) SPEED TACH #1 (H) -24 (22)-----R$
-------- 1OJ1B-7(o) (L) -25 (22)------ - --------- 1OJ1B-8
SHIELDGND ------Y
(0) HEADING TACH #1 (H) -26 (22)------fi-(0) $
-------- 1OJ1A-18(L) llJ1-27 (22)------- - --------- 1OJ1A-19
SHIELDGND ------r
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Guidance PanelIOBP Function Connector Pin Connects To
(0) V/S TACH#l [~]4
llJ1-28 (22)------=-- --------- 1OJ1B-11(o) -29 (22)-----~YJ---------- 1OJ1B-12
SHIELD GND ------
1(0) ALT PRESELECT TACH #1 (H) -30 (22)------=- --------- 9J1B-103(0) ALTPRESELECTTACH#l (L) -31 (22)-----+ ---------- 9J1B-104
SHIELD GND ------,
(0) CRSSELTACH#l (H) -32 (22)(o) i
--------- --------- 115J2-c,C115J2-C(L) -33 (22)-----+ --------- l15J2-d,Cl15J2-d
SHIEL!)GND ------
SPARE -34(1) SUBTEST SELECT* -35 (22)------------------- 115J1-V,C115J1-V
11J2-35, APPX C(0) CRS SYN#l (GND/OPEN) -36 (22)------------------- l15J2-e,Cl15J2-e
SPARE -37(0) BUTTON ARM#l (GND/OPEN) -38 (22)------------------- 1OJ2B-106
l:) !j;:i::l:ll[;l:l:-39 (22)------------------- APPX C&D-40
(0) M/T DISENGANNUNGND -41(0) A/P MISTRIMANNUNGND -42(0) HORNGND -43 ------NC(I) TRIM UP ENABLE -44 (22)------------------- APPX D
SPARE -45SPARE -46SPARE -47
(1) EDGE LIGHTING DIM (H) -48 (22)------------------- A/C WIRING~:] CONTROL (O-5 VDC) (L) -49 (22)-------------------
PUSHBUTTON ANNUN DIM (H) -50 (22)------------------- A/C WIRINGCONTROL (O-5 VDC)
(I) TRIM DN ENABLE -51 (22)------------------- APPX D(I) DIGITAL DISPLAY DIM (H) -52 (22)------------------- A/C WIRING
CONT (O-5 VDC)SPARE -53SPARE -54SPARE -55
(I) CS TRIM UP ENABLE -56 (22)------------------- APPX DSPARE -57
(I) MAINTENANCE TEST SEL* llJ1-58 (22)------------------- 134J1A-19,C134J1A-19,11J2-58,APPX C
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Use or disclosure of mformatlon on thm page IS subjec to the reslncl!ons on the Itlle pag? of this document
Gujdance Panel
IOBP Function Connector Pin Connects To
SPARE llJ1-59SPARE -60
(I) FGC LEFT PRIORITY SELECT* -61 (22)------------------- I15J1-HH(I) FGC RIGHT PRIORITY SEL* -62 (22)------------------- 115J1-z
SPARE -63(1) LAMP TEST #1* -64 (22)------------------- A/C WIRING,
APPX c
(1) CS TRIM DN ENABLE -65 (22)------------------- APF’XDSPARE -66SPARE -67SPARE -68
(I) ANNUNCIATOR VALID #1 -69 (22)------------------- 1OJ2B-89(28v/OpEN)
(I) PRIORITY STATUS #1 -70 (22)------------------- 1OJ1A-37,(28v/OPEN) l15J1-a,
Cl15J1-a,APPX C
(1) wow* -71 (22)------------------- A/C WIRING,APPX C
(1) TOGA #1 -72 (22)------------------- APPX D,APPX C
(I) S/B MANUAL TRIM SELECT -73(1) TCS #1* -74 (22)------------------- APPX D,
APPX CSPARE -75SPARE -76
(I) A/P DISCON #l (OPEN/GND) -77 (22)------------------- APPX 1),Appx C(I) Y/D ENG/DISENG #1 -78 (22)------------------- APPX D, APPX C(1) M/T ENG/DISENG #1 llJ1-79 (22)------------------- APPX D, APPX c
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Guidance Panel
(1)(1)
(1)(1)
(0)(o)
(P)(P)(o)
(1)(1)(o)
(P)(P)
(o)(o)
(o)(0)
Function Connector Pin
iSERIAL DATA REC#2 (H) 11J2-1 (22)------:~1-----------SERIAL DATAREC #2 (L) -2 (22)------~;-----------
SHIELDGND ------JPANEL CLOCK#2 (H)
t-3 (22)------;~,-----------
(L) -4 (22)------C,-----------SHIELDGND ------d
PANEL STR06E#2 (H)t
-5 (22)-----=Q- ----------(L) -6 (22)-----!C+- ----------
SHIELD GND ------
SERIAL DATA TRANS #2 (H)t
-7 (22)-----;;- ----------SERIAL DATA TRANS #2 (L) -8 (22)------C;-----------
StilELDGND ------J
CHASSIS GND -9 (22)--------------------CHASSIS GND -lo (22)-------------------GS/EL ACTIVE GND #2 -11 (22)-------------------
5 V DC A/P POklER#2 ~~: [;;]-------------------5 V DC A/P POWER #2 RTN .------------------BC ACTIVE GND #2 -14 (22)-------------------
28 V DC ANNUN PWR #2 -15 (NOTE 3)---------------28 V DC ANNUN PWR #2 RTN -16 (NOTE 3)---------------SPARE -17SPARE -18SPARE -19SPARE -20SPARE -21SPARE -22SPARE -23sPEEDTAcH#2 [ti] 4-24 (22)------~2----------
-25 (22)-----&’-----------SHIELD GND ------J
HEADING TACH#2 (H)\
-26 (22)-----f-~,----------(L) 11J2-27 (22)------{-- ---------
SHIELDGND ------~
Interconnect informationTable 501 (cent)
Use or disclosure of mtormatlon on thts page E, sublet: to the restrictions on the t!t(e pa!
Connects To
C1OJ2B-102C1OJ2B-103
C1OJ2B-98C1OJ2B-99
CIOJ2B-96C1OJ2B-97
C1OJ2B-1OOC1OJ2B-101
A/C GNDA/C GNDllJI-11, ILSRECEIVER, APPX CC1OJ2A-65C1OJ2A-66llJ1-14, GPllSAPPX CA/C WIRINGA/C MIRING
C1OJ1B-7C1OJ1B-8
C1OJ1A-18C1OJ1A-19
22-14-00Page 543Jun 1/87
g{ofthw document
Guidance Panel
IOBP
(0)(o)
(o)(0)
(0)
(Oj
(I)
(0)
(o)
(I)
(I)(1)
(1)(1)
(I)
(I)
Function Connector Pin
V/S TAC.H#2 (H)I
liJ2-28 (22)--------- ---------(L) -29 (22)-----++- ---------
SHIELD GND ------
tALT PRESELECT TACti#2 (H) -30 (22)-----Y2Y- ---------ACT PRESELECT TACH #2 (L) -31 (22)-----~Y~-----------
SHIELD GND ------
CRS SEL TACti#? (H) -32 (22) ‘ii{--------- ---------1,1
(L) -33 (22)-----~-J-----------‘f
SHIELD GND ------JSPARE -34SUBTEST SELECT* -35 (22)-------------------
CRS SYN #2 (GND1OPEN) -36 (22)-------------------
SPARE -37BUTTON ARM#2 (GND/OPEN) -38 (22)-------------------SPARE . -39SPARESPARESPARESPARETRIM UP ENABLESPARESPARESPARESPARESPARESPARETRIM ON ENABLESPARETCS #2*TOGA #2SPARECS TRIM UP ENABLESPAREMAINTENANCE TEST SEL*
-46-41-42-43-44 (22)--------------------45-46-47-48-49-50-51 (22)--------------------52-53 (22)--------------------54 (22)--------------------55-56 (22)--------------------57-58 (22)-------------------
SPARE 11J2-59
Connects To
C1OJ1B-11C1OJ1B-12
C9J1B-103C9JIB-104
l15J2-g,Cl15J2-gl15J2-h,Cl15J2-n
115J1-V,C115J1-VllJ1-35, APPX Cl15J2-j,Cl15J2-j
C1OJ2B-106
APPX D
APPx D
APPX D, APPX CAPPX D, APPX C
APPX D
134JIA-19,C134J1A-19,llJ1-58, APPX C
Interconnect InformationTable 501 (cent) 22-14-00
Page 544Feb 1/88
Use or dmclosure of mformatlon on thts page H subfecl to the , ?stnctlons on the Mle page of this jocument
Guidance Panel
10BP Function Connector Pin Connects To
SPARE 11J2-60(I) FGC LEFT PRIORITY SELECT* -61 (22)------------------- C115J1-HH(1) FGC RIGHT PRIORITY SELECT* -62 (22)------------------- C115J1-Z
SPARE -63(I) LAMP TEST #2* -64 (22)------------------- A/C WIRING,
APPX C(’J,,., CS TRIM DN ENABLE -65 (22)------------------- APPX D
SPARE -66SPARE -67SPARE -6&
(I) ANNUNCIATOR VALID #2 -69 (22)------------------- C1OJ2B-89(28v/opEN)
(I) PRIORITY STATUS #2 -70 (22)------------------- U~:;A;37,(28v/oPEN)
C115J1-:,APPX C
SPARE -71SPARE -72SPARE -73SPARE -74SPARE -75SPARE -76
(1) A/P DISCON #2 (OPEN/GND) -77 (22)------------------- APPX D REF(1) Y/D ENG/DISENG #2
}-78 (22)------------------- APPX D APPX
(1) M/T ENG/DISENG #2 11J2-79 (22)------------------- APPX D C
Interconnect InformationTable 501 (cent) 22-14-00
Page-545Feb l/88
Use or disclosure of reformation on this page IS subject to the restrictions on the title page of this document
Autopi1ot Ai1eron Servo
IOB_P_ Function Connector Pin Connects To
I(I) SERVO DRIVE (H) 12P1-1 (20)-------
i------------ 1OJ2A-57,
(I) SERVO DRIVE (L) -2 (20)------- ------------ 1OJ2A-58,(P) 26VAC SYNCHROREF (H) -3 ------NC
(P)
(P)
(I)
(I)
(P)(o)(o)(o)(o)
26 VAC SYNCHRO REF (L) ~~ ------NCSPARESPARE -6SPARE -7SPARE -8SPARE -9CHASSIS GROUND -10 (22)------------------- A/CCHASSISGNDSPARE -11+28 V DC CLUTCH -12 (22)------------------- APPENDIXDEXCITATIONSPARE -13-28 V DC CLUTCH -14 (22)------------------- A/CGNDEXCITATIONSHIELD GROUND -15 (22)-----,SERVO TACH (H)
1-17 (22)-----;~,- ---------- 1OJ1B-7O
(L) -16 (22)___-_Cj_ ---------- 1OJ1B-71SYNCHRO POSITION (X) -18 ------NC
(Y) -19 ------NC
SPARE -20(I) SERVO BRAKE (28 V DC) -21 (22)------------------- C1OJ1A-21(I) SERVO BRAKE (GND) 12P1-22 (22)------------------- A/CGND
Interconnect InformationTable 501 (cent) 22-14-00
Page 546Jun 1/87
Use or disclosure of mtormatlon on this page m subject to the restr)ctlons on the title page of thm jocument
(I)(I)(P)
(P)
(P)
(P)(o)(o)(o)(o)
(I)(I)
Autcpilot Aileron Servo
Function Connector Pin
SERVO DRIVE (H) 12P2-1 (20)--------?-----------(L) -2 (20)--------?-----------
26 V AC SYNCHRO REF (H) -3 ------NC
26VAC SYNCHRO REF (L) -4 ------NCSPARE -5SPARE -6SPARE -7SPARE -8SPARE -9CHASSIS GROUND -lo (22)-------------------SPARE -11SPARE -12SPARE -13SPARE -14SHIELD GROUND -15 (22)-----,SERVO TACH (H) -17 (22)-----’--~-
/----------
(L) -16 (22)----\-;- ----------SYNCHRO POSITION (X) -18 ------NC
(Y) -19 ------NCSPARE -20SERVO BRAKE (28V DC) -21 (22)-------------------SERVO BRAKE (GND) 12P2-22 (22)-------------------
Connects To
C1OJ2A-57C1OJ2A-58
A/C CHASSIS GND
C1OJ1B-7OC1OJ1B-71
1OJ1A-21A/C GND
Interconnect InformationTable 501 (cent) 22-14-00
Page 547Jun 1/87
Use or disclosure of InformalIon on Ihls page M sublecl 10 the restr!cl!ons on the t!tle page of lhls document
(I)(1)(P)
(P)
(P)(I)
(I)(P)(o}(o)(o)(o)
(I)(1)
Autopilot Elevator Servo
Function Connector Pin
SERVO DRIVE (H)!
13P1-1 (20)-------------------(L) -2 (20)-------------------
26 VAC SYNCHRO REF (H) -3 ------NC
26 V AC SYNCHRO REF (L) ------NCSPARE ::SPARE -6SPARE -7SPARE -8SPARE -9CHASSIS GROUND -lo (22)-------------------28 V DC CLUTCH EXC -11 (22)-------------------SPARE -12SPARE -13-28 V DC CLUTCH EXC -14 (22)-------------------SHIELD GROUND -15 (22)-----/\SERVO TACH (H)
1-16 (22)----7--1-----------
SYNCHRO poslT\LJ ’17 (22)-----<j- ----------(x) -18 ------NC(Y) -19 ------NC
SPARE -20SERVO BRAKE (28 V DC) -21 (22)-------------------SERVO BRAKE (GND) 13Pi-22 (22)-------------------
Connects To
1OJ2A-551OJ2A-56
A/C CHASSIS GNDAPPENDIX D
A/C GND
1OJ1B-691OJ1B-68
C1OJ1A-2IA/C GND
Interconnect InformationTable 501 (cent) 22-14-00
Page 548Jun 1/87
Use or disclosure of Information on thts page E subject to the rtstnctlons on the Mle page of this document
Autopilot Elevator Servo
IOB~ Function Connector Pin Connects To
(I) SERVO DRIVE (H) +13P2-1 (20)-------- ----------- C1OJ2A-55(I) (L) -2 (20)-------------------- C1OJ2A-56(P) 26 V AC SYNCHRO REF (HI -3 ------NC
(Pj 26 VAC SYNCHRO RZF (L) -4 ------NCSPARE -5SPARE -6SPAi?E -7SPARE -8SPARE -9
(P) CHASSIS GROUND -10 (22)------------------- A/c CHASSISMJ)SPARE -11SPARE -12SPARE -13SPARE -14
(P) SHIELD GROUND -15 (22)-----J,(o) SERVO TACH (H)
I-16 (22)-------- ---------- C1OJ1B-69
(o) SYNCHRO poslTIL~ -17 (22)----JC;- ---------- C1OJIB-68(o) (x) -18 ------NC(o) (Y) -19 ------NC
SPARE -20(I) SERVO BRAKE (28 V DC) -21 (22)------------------- lCIJIA-21(I) SERVO BRAKE (GND) 13P2-22 (22)------------------- A/CGND
Interconnect InformationTable 501 (cent) 22-14-00
Page 549Jun 1/87
Use or disclosure of mformat!on on Ihw page IS subject 10 the restrictions on the We page of this document
(1)
(I)
(I)(?)(I)(I)
(I)(1)
(o)
(o)
(o)(o)
(I)(I)
(o)
(o)
6ERTEA Rudder Actuator
Function Connector Pin
ACTIVATE SOLENOID (H) 14P1-A (22)-- --------
A
+
-------ENGAGE (28 V DC) 5
ACTIVATE SOLENOID (L) -B (22)----------- -------ENGAGESPARE -cSPARE#l DRIVE#1 DRIVE#2 DRIVE#2 DRIVE
- LEFT+ RUDDER- LEFT+ RUDDER
-D-E (20)-F (20)-G (20)-H (20)
------ .-------- ------- .-------- -
#1 RUDDER LVDT EXEC (L)t
-J (22)--;-;---------------#l RUDDER LVDT EXEC (H) -M (22)--<J- --------------
#1 RUDDER LVDT (L) -K (22)-:-2~
1
-----.--------FEEDBACK#1 RUDDER LVDT (H) -L (22)-!C;- --------------FEEDBACK
RUDDER LIMIT WARN (ARM) -N (22)--------------------RUDDER LIMIT WARN (NO) -P (22)--------------------
#2 RUDDER LVDT EXEC (L)I
-R (22)-{-;- --------------#2 RUDDER LVDT EXEC (H) -s (22)--~J- --------------
#2 RUDDER LVDT (H)
!
-T (22)--;>{ --------------FEEDBACK#2 RUDDER LVDT (L) 14P1-U (22)-!C;- --------------FEEDBACK
Connects To
1OJ1A-58,C1OJ1A-58,134J1B-26,C134J1B-26A/C GND
1OJ1A-641OJ1A-63C1OJ1A-64C1OJ1A-63
1OJ1A-6O1OJ1A-59
1OJ1A-62
1OJ1A-61
137J1B-54A/C 28 V DC
C1OJ1A-6OC1OJ1A-59
C1OJ1A-61
C1OJ1A-62
Interconnect InformationTable 501 (cent) 22-14-00
Page 550Jun 1/87
Use or disclosure of mtormatlon on thm page m subject to the rcstrlctlons on the tllle page of thm document
I
I
I
(I)(I)
(o)
(o)(P)(o)
(o)(o)
(I)(o)(o)(o)
(o)(o)
(P)(P)(P)(P)(o)
(I)
Radio Altimeter No. 1
Function Connector Pin
SPARE 20J1-ASPARE -BSPARE -cTEST INHIBIT* -D ------NCOUTPUT TEST -E (22)-------------------
TRACK INVALID -F ------NCSPARE -GSPARE -HSPARE -JSPARE -KTRIP NO. 4 (400 FT) ------NC+/- 15 V DC COMMON i ------NCOUTPUT COMMON
p
-N (22)------;--- --:-- -
II ~;ALT TRIP COMMON -P ------NC ,,TRIP NO. 3 (50 FT) ------NCSPARE :! II j;TEST* -T (22)--------- ,,--------TRIPNO. 1 (1200 FT) -u ------NC ‘1TRIP NO. 2 (250 FT) -v ------NC Ii ‘iALT OUTPUT (EH) -w (22)-----1’-----:--- -
?SHIELD GND-----------
AUX OUTPUT (H) -x (22)-------------------RAD. ALT. VALID (28V/OPEN) -Y (22)-------------------
+15 V DC -z ------NC-15 V DC -a ------NCPOWER GND -b (NOTE 3)---------------+27.5 V DC 20J1-c (NOTE 3)---------------TRANSMIT 20J2 **--------? -------- 21J1
- - -1- - -
RECEIVE 20J3 **--------9
-------- 22J1-----
Connects To
APPX C2OJ1-N,1OJ2B-27,C1OJB-37,136J1A-51,APPXC
2OJ1-E,1OJ2B-27,C1OJ2A-37,136J1A-51,APPX J, APPX L
134J1A-95,APPXc
1OJ2B-26,C1OJ2A-36,136J1A-50APPX L1OJ2B-28,C1OJ2A-38,136J1B-19,APPXCAPPX L
A/C PWR GNDA/C 28 V DC PWRCOAX TO TRANSMITANTENNACOAX TO RECEIVEANTENNA
**MATING CONNECTOR HONEYWELL PART NO. 4008064, GRFF4007-0002 (ST)HONEYWELL PART NO. 4008065, GRFF41OO-OOO1 (RT ANGLE)
NJ-rJ: FOR FURTHER INFORMATION ON THE RADIO ALTIMETER SYSTEM, PLEASE REF:AA-300, O & I MANUAL, PUB. NO. 15-3321-06.
Interconnect InformationTable 501 (cent) 22-14-00
Page 551Apr 15/93
Use or disclosure of information on this page is subject to the restrictions on the title page of this document
Trim Elevator Servo
IOB_P_ Function Connector Pin Connects To
(1) SERVO DRIVE (L) +29J1-1 (20)---- --------------- 1OJ2A-6O(I) (H) ~; [;~;----~-- ------------ 1OJ2A-59(P) 26 V AC SYNCHRO REF (H)
I
-----.- ------------ 1OJ1B-44,A/C 26VAC PWR
(P) 26 V AC SYNCHRO REF (L) -4 (22)-------Y------------ A/C PWRGNDSPARE -5SPARE -6SPARE -7SPARESPARE :;
(P) CHASSIS GROUND -10 (22)------------------- A/C CHASSIS GNDSPARE -11SPARE -12SPARE -13SPARE -14
(P) SHIELD GROUND -15 (22)-----,(0) SERVO TACti [~] -16 (22)-----~~-
1---------- 1OJ1B-72
(o) -17 (z2)-----!-;----------- 1OJ1B-73
(o) (x)
1
-18 (22)-~-~- ------------- 1OJ2B-44(0) SYNCHRO POS (Y) -19 (22)-!-!- ------------- 1OJ2B-45(o) (z) -20 (22)-{-;- ------------- 1OJ2B-46
SHIELDGND ---J
(I) ~~~V~ ~~KE (H) -21 (22)------------------- C1OJ1A-22
(I) ~~~~~ BRAKE (L) 29J1-22 (22)------------------- A/C GND
Interconnect InformationTable 501 (cent) 22-14-00
Page 552Jun 1/87
Use or dwclosure of mformalton on Ihls page ts subject 10 the I !strlctlons on the Mle page of this document
Trim Elevator Servo
IOB_P_ Function Connector Pin Connects To
(I) SERVO DRIVE (L) i29J2-1 (20)-- ----------------- C1OJ2A-6O(I) (H) -2 (20)--1-- -------------- C1OJ2A-59(P) 26 VAC SYNCHRO REF (H)
!-3 (22)----- -------------- C1OJ1B-44,
A/C 26V
iAC PWR
(P) 26VAC SYNCHRO REF (L) -4 (22)----- -------------- A/C PWfl GNjjSPARE -5SPARE -6SPARE -7SPARESPARE 1!
(P) CHASSIS GROUNDSPARE
-10 (22)------------------- A/CCHASsISGNll-11
(I) (28 V DC) -12 (22)------------------- APPENDIX IICLUTCH EXC
(I)SPARE
(GND) -13 (22)------------------- A/CGNt)-14
(P) SHIELD GROUND -15 (22)-----/\(o) SERVO TACH [~]
t-16 (22)------------------ C1OJ1B-72
(o) -17 (22)----{-;----------- C1OJIB-73
(o) (x) I-18 (22)------ ------------ C1OJ2B-44(o) SERVO POS (Y) -19 (22)---’-J------------- CloJ2B-45(o) (z) -20 (22)--~-~- ------------ C1OJ2B-46
SHIELDGND ---~’(I) SERVO BRAKE (28 V DC) -21 (22)------------------- 1OJ1A-22(I) SERVO BRAKE (GND) 29J2-22 (22)------------------- A/CGND
Interconnect InformationTable 501 (cent) 22-14-00
Page 553Jun 1/87
Use or dmclosure Of mformatlon on this page IS sublet’ lo the restrictions on the lltle page ot !hls document
Trim Elevator Servo Bracket
i06~ Function Connector Pin Connects To
(o) P.DN LIMIT (NC) 29 AJ1-1 ------NC(0) P.UP LIMIT (NC) ------NC(I) P.DN LIMIT (C) :: (22)-------------------- 28V DC NO.1 PWR
(1) P.UP LIMIT (C) -4 (22)-------------------- 28VDC NO.I PWR
(o) P.DN LIMIT (NO) -5 (22)-------------------- 1OJ1B-19(0) P.UP LIMIT (NO) -6 (22)-------------------- 1oJ1B-16(1) TRIM EYPASS ------NC(0) TRIM BYPASS 29AJl~i ------NC
(o) P.DN LIMIT (NC) 29AJ2-1 ------NC(o) P.UP LIMIT (NC) -2 ------NC(I) P.DN LIMIT (C) -3 (22)-------------------- 28 VDCN().2 PWR
(I) P.UP LIMIT (C) -4 (22) -------------------- 28 V DC NO.2 PWR
(o) P.DN LIMIT (NO) -5 (22) -------------------- C1OJ1B-19(o) P.UP LIMIT (NO) -6 (22)-------------------- C1OJ1B-I6(I) TRIM BYPASS -7 ------NC(0) TRIM BYPASS 29AJ2-8 ------NC
I
Interconnect InformationTable 501 (cent) 22-14-00
Page 554Jun 1/87
Use or disclosure of mformatlon on this page !s sub)ecl 10 the reslnctlons on the title page of this documenl
Weather Radar RTA
IOB& ~ Connector Pin Connects To
(P) 28 VDC POWER 59J1-A (20)--------------------- 28VDC, A/C PWR(P) 28 VDC POWER -B (20)--------------------- 28VDC, A/C PWR
RESERVED -C thru G(I) M&ELECT * -H (22)--------------------- A/CGND
-J
t(B) ATTITUDE (ARINC 429) (H) -K (22)----------- --; ----- c170J1B-F14(B) ATTITUDE (ARINC 429) (L) -L (22)----------- --U----- C170J1B-F15
RESERVED -M thru P(I) REACT COMPENSATION OVERRIDE*l! (22)--------------------- GND (SEE NOTE)
RESERVED(I) WOW -T ------NC(I) REMOTE ON * -u (22)--------------------- 61J1-N,C61J1-N
65J1B-20,C65J1B-20,E65J1B-20
RESERVED -v(P) 28 VDC POWER RETURN -W (20)--------------------- A/C PWR GND(P) 28 VDC POWER RETURN -X (20)--------------------- A/C PWR GND
RESERVED -YRESERVED -zSPARE -AA thru HH
$(B) ALTERNATE CONTROL BUS (H) -a (22)--------O- --------- C61J1-A(B) ALTERNATE CONTROL BUS (L) -b (22)----- +----------- C61J1-B
CONTROL BUS SHIELD(B) PRIMARY CONTROL BUS f-p (22)---- --
(H) -C (22)---- -------------- 61J1-A(B) PRIMARY CONTROL BUS (L) -d (22)-------
Y------------ 61J1-B
CONTROL BUS SHIELD(B) RT EFIS CONTROL BUS
-p (22)--------
i
(H) -e (22)-------8 ---------- ~:;j;j-;,
(B) RT EFIS CONTROL BUS (L) -f (22)-------J’------------ C65JlA~2,
YE65J1A-2
CONTROL BUS SHIELD
-$
-p (22)---- :>(B) LEFT EFIS PICTURE BUS (H) -g (22)--- ------------ 65J1B-37(B) LEFT EFIS PICTURE BUS (L) -h (22)-------1’------------ 65J1B-38
PICTURE BUS SHIELD Y59J1-q (22)--------
*W: An open on 59J1-R causes the radar to be in React Compensation modeanytime WX is selected. A ground allows React compensation to bemanually selected on the controller.
,Interconnect Information
Table 501 (cent) 22-14-00Page 555
Apr 15/93Use or disclosure of information on this page is subject to the restrictions on the title page of this document.
Weather Radar RTA
IOB~ M@i!m Connector Pin
i
connects To
‘B) ;fi~T~[)EFISpICTURE59J1-i (22)--------S-- --------- E65JlB-37
lJ(B) ;;~~&EFIS PICTURE
-j (22)--------”-- ---------
Y
E65J1B-38
PICTURE BUS SHIELD -q (22)----
$(8) RIGHT EFIS PICTURE 8US (H) -k (22)----- -&--------- C65J1B-37(B) RIGHT EFIS PICTURE BUS (L) -S (22)----- --Y------------ c65J18-38
PICTURE BUS SHIELD -q (22)--------
(B) LEFT EFIS CONTROL BUS(H)
$
-m (22)--------;-- --------- 65J1A-51,E65J1A-51
(B) LEFT EFIS CONTROL BUS (L) -n (22)------- ‘t------------ E65J1~ ~~
1
65J1A 52
CONTROL BUS SHIELD -p (22)--------
t](B) AIR DATA (ARINC 429) (L) -r {22)-----------------fl.- DADC 429(B) ~;~R~TA (ARINC 429) (H) -t (22)-------------- --&- OUTPUT
59J1-u thru z
Interconnect InformationTable 501 (cent) 22-14-00
Page 556Apr 15/93
Use or disclosure of information on this page IS subject to the rc stfictions on the title page of this I Iocument
Weather Radar R/T
10BP Function Connector Pin
/WX SERIAL DATA #1 (Ii)59J2-A (22)----1~7- -----------
Connects ToI
(o) 65LJ1A-51,E65J1A-5165J1A-52,E65J1A-52
I
I(L) Ilt-T (22)-------- -----------
T(0)
(1)(0)
SHIELD GND -h (22)-----J ~WX SERIAL DATA #2 (H) -v (22) -
Y--.----- .----------
IIC65J1A-1,E65J1A-1C65JIA-2,E65J1A-2
(L)iii-B (22)-----L-- -----------(c)
SHIELD GNDI+ (22)___
FAULT (NO. 1) (GND/OPEN) -c (22)--------------------(1)(o)
SPARE -DSPARE -ESPARE -FSPARE -GSPARE -HSPARE -JSPARE -KWX VIDEO #2 (H)
i-L (22)-------------C- ----
WX VIDEO #2 (L) -M (22)------------L+ ---(o)(o)
APPX DAPPX DTIE TO 59J2-g
SPARECONTROL PANEL GNDSIGNAL GND (NO. 1)SIGNAL GND (NO. 2)SERIAL CONTROL (H)SERIAL CONTROL (L)SPARESPARESPARESPARESPARESPARESPARESPARESPARE
L ------
-N-P (22)---------------------R (22)--------------------
(I)(I)(I)(I)(I)
C61J-CSIGNAL GNDSIGNAL GNDC61J1-AC61J1-B
-s (22j-------------------
1-u (22)--------------=- ---n (22)--------------~=~- ---w-x-Y-z-a-b
::-e
SPARE -fWX VIDEO NO. 1 (H)
I-i (22)---~- --------------
WX VIDEO NO. 1 (L) 59J2-j (22)--~1- --------------(0)(0)
APPX DAPPX D
Interconnect InformationTable 501 (cent) 22-14-00
Page 557Feb 1188
Use or dwclosure Of Informahon on this page M subject to the restrictions on the tllle pagt] of Ihm document
Weather Radar R/T
IOB_P_ Function Connector Pin Connects To
SPARE 59J2-k(0) TGT ALERT NO. 1 (GND/OPEN) -m (22)-------------------- APPXD REF
}(0) :;& (NO. 2) (GND/OPEN) -P (22) -------------------- APPXD APpxc
-Q
SPARE -rSPARE -sSPARE -tSPARE -uSPARE -vSPARE -wSPARE -xSPARE
(0) TGT ALERT (NO. 2)(GND/OPEN)SPARESPARESPARESPARESPARESPARESPARE
:: (22)-------------------- APPX D,REF APPX C
-AA-BB-cc-DD-EE-GG
59J2-HH
NOTE “ FOR FURTHER INFORMATION ON THE WEATHER RADAR SYSTEM, PLEASE REF:
‘“ P-800 SDI, PUB. NO. IB8023137.
Interconnect InformationTable 501 (cent) 22-14-00
Page 558Jun 1/87
Use or dw.closure of mformatlon on thm page m subject to the estrlctlons on the INle page of thm document
Weather Radar Controller No. 1
IOB~ Function Connector Pin Connects To
(0) SERIAL CONTROL (H)$
61J1-A (22)-------+- --------- 59J1-c(0) SERIAL CONTROL (L) -B (22)-------- -- --------- 59J1-d(I) SHIELDGND -M (22)--------Y
(P) CONTROL PANEL GND -c (20) --------------------- CHASSIS GIUI
(P) 28 VDC POWER -D (20)--------------------- 28VDC, A/C PWR
(P) 28VDC PWRRTN -E (20) --------------------- A/C PWRGND
SPARE -F
(P) 28V PANEL LIGHTING -G ------NC
(P) 5V PANEL LIGHTING -H (20)--------------------- A/C 5V
LIGHTING
(P) LIGHTING COMMON -J (20)--------------------- A/C LIGHTING
GND
(P) PUSHBUTTON 28V LIGHTING -K (22) --------------------- A/C 28V
LIGHTING
RESERVED -L
(0) R/T ON/OFF (GND/OPEN) -N (20)--------------------- 59J1-U,
C61J1-N,
65J1B-20,
C65J1B-20,
E65J1B-20
(I) FORCED STANDBY ● -P (22)--------------------- A/CWOWSWITCH
SPARE 61J1-R thru U
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of information on this page is subject $o the restriction son the title page of this document,
Weather Radar Controller No. 1
106~ Function Connector Pin Connects To
(0) RANGEA 61~2-A (22) -------------------- FIGURE D-4.2(0) RANGE B -B (22)-------------------- FIGURE D-4.2(0) RANGE C -C (22) -------------------- FIGURE D-4.2
(0) RANGE D -D (22)-------------------- FIGURE D-4.2(0) FPLN SELECTED (GND/OPEN) -E (22)------
t
------------ FIGURED-4.2(1) WX INT (H} -F (22)---~- ----------- 131JI-2(0) WX INT (W) -G (22)--+- ------------ 131J1-15(1) WX INT (L) -H (22)---U-- ------------ 131J1-3
(I) PROGRAM RANGE A -J (22)-------------------- A/C WIRING(I) PROGM RANGE B
1
-K (22)-------------------- A/C WIRING APPX(I) PROGRAM RANGE C -L (22)-------------------- A/CWIRING C(1) PROGRAM RANGE D -M (22)-------------------- A/C WIRING(I) PROGRAM RANGE COMMON -N {22)-------------------- A/C WIRING
RESERVED -P(0) ID PROG COMMON -R ------NC
(I) ~~A[~OG -s ------NC61J2-T thru U
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22-14-00Page 561
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I
1
I
I
(B)(B)(P)(P)(P)
(I)(I)(o)
(I)(I)(B)(B)
(I)
(B)(B)
(I)(I)
(I)(I)(I)(I)(I)(B)(B)(B)(B)(B)
(B)
Symbol Generator No. 1
E!!!Kuw Connector Pin Connects To
WX CNTRL (H) 65J1A-1 ------NCDATA #2 (L) ------NC28 V DC PWR ‘$ (NOTE 3)---------------- A/CDC pWRPWR GND -4 (NOTE 3)---------------- A/C DC pWR GNDSIGNAL GND ~~ (22) -------------------- SIGNAL GNO
RESERVED
RESERVED
RESERVED :;
RESERVED -9
SPARE -loSG I.D. A -11 (22)------------------- 65J1B-50
}
REF-12 ------NC APPX
BC VALID (~ND/OPEN) -13 (22)------------------- 134JIA-97, cC134J1A-97
TCAS INSTALLED* -14 (22) ------------------- APPX 1.
LX POWER ON* -15 (22) ----- ------------- APPX F, APPX C
SYS ASCB PRINARY BUS (H)*
-16 (22)--R- ------------- SEE SECTION 3.3
SYS ASCB PRINARY BUS (L) -17 (Z+-u- -------------1-18
RESERVED -19P870 INSTALLED* -20 (22)------------------- SIGNAL GNDSPARE -21
* 1APPX CSG/DU BUS A (H) -22 (22)--n
(L) ‘------------ SEE APPENDIX A-23 (22)-!~-- --.----------
RESERVED -24MACH TAPE DISABLE* -25 ------NCILS/MLS* #1 -26 (22)------------------- APPX D, APPX C
FPLN SEL* -27 (22) -------------------
RANGE SELECT A -28 (22) -------------------
RANGE SELECT B -29 (22) -------------------
RANGE SELECT C -30 (22)-------------------RANGE SELECT D -31 (22)----- -------------ADFNO. 1, (H)
$-32 (22)--fi---------------
ARINC 429 (L) -33 (22)_u- ------. --.--DNE NO. 1 ARINC 429 (H)
$-34 (22)---------n-- -----
DHE NO. 1 ARINC 429 (L) -35 (22)---------+- -----TA/RA NO. 1 ARINC 429 -36 (22)-------------------(H)TA\RA NO. 1 ARINC 429 65J1A-47 (22)-------------------
1APPENDIX DAPPENDIX D REFAPPENDIX D APPXAPPENDIX D CAPPENDIX DADF NO. 1,ARINC 429DNENO. 1,ARINC 429APPX L
APPX L
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of informationon this page issubject to the retrictionsonthe title page of this document.
IOB_P_
(B)(B)(B)(B)
(B)(B)(B)(B)(B)(B)(B)(B)(o)(B)
(B)
(B)(B)(B)(B)
(I)
(I)
Symbol Generator No. 1
U!Ktiu! Connector Pin Connects To
ARINC 429(H) 65J1A-37 ------NCARINC 429 (L) -38 ------NCDADC NO. 1 ARINC 429 (H)
%-39 (22)--7-
DADC NO. 1 ARINC 429 (L) -40 (22)-+- ==== ;!;g~%
VOR NO. 1 ARINC 429 (L)$
-41 (22)--p- ------------- VORNO. 1
VOR NO. 1 ARINC 4!;)(H) -42 (22)--J- -- ---------- ARINC 429MLS/ILS NO. 1
$-43 (22)-----/3- ---------- APPENDIXD
ARINC 429 (L) -44 (22)-----JJ- -- -------SG/DU WXR BUS (H)
!
-45 (22)------’+-~ ------- SEE APPENDIX A
W~D[oWXf BUS il.] -46 (22)--------- - -------%-48 (22)-------- -- ------- 170J1B-E5
~RoG P*N GND of+)ARINC 429 -49 (22)--------L’- ------- 170J1B-E6-50
P-870 MX (H)
$
-51 (22)--------fi- ------- 59J1-m,E65J1A-51
CNTL DATA #l (L) -52 (22)--------4- ------- 59J1-n,E65J1A-52
LX OR TACAN ARINC 429 (H) -53 (22)------------------- APPX F, APPX MLX OR TACAN ARINC 429 (L) -54 (22)----------- ------- APPX F, APPX MBC ASCB PRIMARY (H)
$]-55 (22)--------Q ------- SEE SECTION 3.3
~;A~;CB PRIMARY (L) -56 (22) ---------$ -------
-57
RESERVED -58
SG PWR DN* -59 (22) ------------------- Ill;l~I~;NG,
C65Jl~-66,E65J1A-60,134J1A-41,C134J1A-41,APPENDIX B &C
SG1 REV* 65J1A-60 (22)------------------- A/C WIRING,E65J1A-60,C65J1A-60,134J1A-41,C134J1A-41,65J1A-59,APPENDIX B & C
Interconnect InformationTable 501 (cent) 22-14-00
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Symbol Generator No. 1
10B& fJl!@dm connector Pin ~Q
{I) SG2 REV* 65J1A-61 (22)------------------- A/CWIRING,E65J1A-61,C65J3A-61,134J1A-42,C134JIA-42,C65J1A-59,APPENDIX B&C
(I) SG3 REV* -62 (22)------------------- A/’CWlRING,
E65J1A-62,
C65J1A-62,
134J1A-43,
C134JIA-43,
E65JIA-59,
APPENDIX B & C
(I) DU1 REV* -63 (22) ------------------- A/C WIRING,
E65JlA-63,
C65J1A-63,
134J1A-44,
C134J1A-44,
APPENDIX B&C
(I) lNJ3 REV* -64 (22) ------------------- A/C WIRING,
E65J1A-64,
C65J1A-64,
134JIA-46,
C134J1A-46,
132JI-22,
APPENDIX B &C
(1) DU4 REV* 65J1A-65 {22)------------------- A/CllIRING,
E65J1A-65,
C65J1A-65,
134J1A-47,
C134J1A-47,
133J1-22,
APPENDIX B &C
Interconnect InformationTable 501 (cent) 22-14-00
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Use or dmclcmure of mfofmakm on thm page !s sub}ect 10 the res!ncl!ons on the title page of !hm document,
IOBP Function
Symbol Generator No. 1
Connector Pin Connects To
(I) !IU6REV* 65J1A-66 (22)------------------- A/C WIRING,E65J1A-66,C65J1A-66,134J1A-49,C134J1A-49,
(1) LX INSTALLED*APPENDIx B & C
65JIA-67 (22)------------------- APPX F, APPX C
Interconnect InformationTable 501 (cent)
22-14-00Use or disclosure of mformatlon on tlus page (S sutqec[ to the
Page 565Feb 1/88
re!mct!ons on [he t(tle page of lhs document
I
I
I
IOB&
(I)
(I)
(P)(P)(P)(B)(B)
(I)(I)(B)(B)
(B)(B)
(I)
(B)(B)(I)(I)(I)(I)
(B)(B)(B)(B)(B)(B)
Symbol Generator No. 1
Function Connector Pin
BCTESTREQUEST N0.1*65J1B-1 (22)--------------------
BC TEST REQUEST NO. 2* -2 (22)--------------------
RESERVED -3RESERVED -4CHASSIS GND -5 (22)--------------------28V DC PWR (BC) (H) -6 (22)--------------------
(L) -7 (22)--------- ----------IRS #3 ARINC 429 (H)
$-8 (22)-----43-- ----------
(L) -9 (22)-----:-- ----------SPARE -10BC I.D. A -11 (22)-------------------
LASERTRAK!RINC 429 (H)LASERTRAKARINC 429 (L)SPARESYS ASCB (H)
:;~~~~~~Y BUS (L)
RESERVED
WX ON*
-12 j--j--NC-13 (22)----f3-
$----------
-14 (22)----+’- -----------15
*-16 (22)----4- ------------17 (22)---+ ------------18-19-20 (22)-------------------
Connects To
C65J1B-1,E65J113-1,134J1A-96C65J1B-2,E65J1B-2,C134J1A-96
CHASSIS GND
A/C 28 VDC PWRA/C PWR GNDE170J1B-E5E170J1B-E6
}
REF65J1B-50 APPX
198J1-24 (O;T)198J1-25 (OPT)
REF SEC. 3.3
59J1-U, 61J1-N,C61J1-N, APPX CC65J1B-20,E65J1B-20,
RESERVED -21SG/DU BUS B (H)
$----------]
-22 (22)----J3- SEE APPENDIX A
(L) -23 (22)----# -----------
-24
-25ILS/MLS* #2 -26 (22)------------------- APPENDIXD,SG IDC -27 ------NC REF. APPX CSPARE -28RESERVED -29RESERVED -30RESERVED -31ADF NO. 2 ARINC 429 (H)
i]
-32 (22)-----m ----------- ADF NO. 2
ADF NO. 2 ARINC 429 (L) -33 (22)-----!! ----------- ARINC 429
DME NO. 2 ARINC 429 (H) -34 (22)------ ----------- Df4ENfJ. 1
DME NO. 2 ARINC 429 (L) -35 (22)-----[~ ----------- ARINC42g
RESERVED 65J1B-36
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of information on this page is subject to the res rictions on the title page of this dc}cument,
,
I
I
I
Symbol Generator No. 1
IOB~ Function Connector Pin Connects To
(B) WX VIDEO DATA (H)@
65J1B-37 (22)-- - ------------- 59J1-g(B) (L) -38 (22)-- - --- -------- 59J1-h(B) DADC NO. 2 (H) -39 (22)--------Y
If------- E65J1B-39,
C9J1B-70(B) ARINC 429 (L) -40 (22)-------U’- -------- E65J1B-40,
$
C9J1B-71(B) VOR NO. 2 ARINC 429 (H) -41 (22)--fi- ------------- VORNO. 2
(B) VOR NO. 2 ARINC 429 (L) 1-42 (22)--U- ------------- ARINC 429
(B) MLS/ILS NO. 2 (H)$
-43 (22)--n- ------------- APPENDIXD(B) ARINC 429 (L) -44 (22)--U- ------------- 1
RESERVED -45(B) BC ASCB SECONDARY [H)
~$-46 (22)--( - ------------- SEE SECTION 3.3
(B) (L) -47 (22)-- - ----- -------
$
1(B) IRS NO. 2 (H) -48 (22)--------A- ------- C170J1B-E5(B) ARINC 429 (L) -49 (22)--------V ------- C170J1B-E6
(0) PROG PIN GND OUT +: (22)------------------- A1(0) SG VALID OUT (GND/OPEN) ------NC
(0) SG 0VERTE14P OUT (GND/OPEN) -52 (22) ------------------- 134J1A-51,
C134JIA-51,
SEE APPENDIX C(0) BELOW DH OUT (GND/OPEN) -53(1) UEIGHT ON WHEELS* -54 (22)------------------- A/C WIRING’(1) JOYSTICK FORE* -55 (22)------------------- APPENDIX D(I) JOYSTICK AFT* -56 (22)------------------- APPENDIX D(1) JOYSTICK LT* -57 (22) ------------------- APPENDIX D REF
(I) JOYSTICK RT* -58 (22)------------------- APPENDIX D APPX(I) JOYSTICK ENTER* -59 (22)------------------- APPENDIX D c(I) JOYSTICK CLEAR* -60 (22)------------------- APPENDIX D ‘
SPARE -61SPARE -62RESERVED -63RESERVED -64
(0) CS HDG SRC DISPLAYED -65 (22)------------------- A/C WIRING(GND/OPEN)
(I) MAINTENANCE TEST -66 (22)------------------- APPENDIX D=ENABLE GNDRESERVED 65J1B-67
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of information on this page is subject to the restrictions on the title page of this document
Display Controller No. 1
(P)(P)(P)(P)(P)(P)
(I)(I)(B)
(B)
(P)(P)(I)
(I)
(1)
(I)(I)(I)
Function Connector Pin Connects To
28 V DC POWER 115J1-A (NOTE 3)---------------- A/C28VDC28 V DC POWER RTN -B (NOTE 3)---------------- A/C 28 V DC RTN
$PANEL DIM141NGCONTR0L (H) -C (22)----- ------------- A/C 5VDC
PANEL DIMMING CONTROL (L) j: [j~]----- ------------- LIGHTING CNTLSIG GROUND -------------------- A/C SIGGNDCHASSIS GROUND ~[ (22)-------------------- CHASSISGNDSPARESPARESPARE :!SPARE -KSPARE -LRESERVED -MANNUNCIATOR DIMMING (L)
*-N (22)--- ---------------- A/C 5VDC
ANNUNCIATOR DIMMING (H) -P (22)--- -- ------------- ANNUN DIMMING
t
SYSASCB PRIMARY BUS (H) -R (22)--fl-- ------------] SEE SECTION 3.3
(L) ~; (22)--&- ------------RESERVED TEST
J
RESERVED TEST -uANNUNCIATOR PWR ~[] -V (22)-------------------- A/C 28 V DC
-W (22)-------------------- POWERGNDDAY/NIGHT (OPEN/28 V DC) -X (22)-------------------- DAY/NIGHTANNUN
DIMMINGDISCRETE,APPX C
RESERVED TEST -YSPARE -zFGC LEFT PRIORITY -a (22)-------------------- 1OJ1A-37,(28V/OPEN) llJ1-70,
Cl15J1-a,APPX C
FGC RIGHT PRIORITY -b (22)-------------------- ;~3:l~G37,(28V/OPEN)
cl15il-6,APPX C
ARINC ILS INSTALLED* -c (22)-------------------- A/C WIRING REFMLS INSTALLED* -d (22) -------------------- APPX K
}
APPX
SPARE l15J1-e (22)-------------------- c
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of information on this page is subject to the res!rictionson the title page of this document
I
I
I
Display Controller No. 1
IOB_P_ Function Connector Pin Connects To
(1) WINDSHEAR INSTALLED* l15J1-f------NC(I) PILOT/COPILOT* -g.-----NC
1
REF(I) IRS TRIPLEX/DUAL* -h------NC APPX(~] LTRK INSTALLED* -i (22)-------------------- A/C WIRING C
TCAS INSTALLED* -j (22)-------------------- APPX L(1) WOW* -k (22)-------------------- A/CWIRING
(I) TCAS RA -m (22)-------------------- APPX L(r) RESERVED SPARE(I) EMER CHECKLIST SELECT* :; (22)-------------------- Cl15J1-p,
1
134J1A-103, REFC134J1A-103 APX
(I) CHECKLIST ENABLE* -q (22)-------------------- Cl15J1-q, C134J1A-104,C134J1A-104
SPARE -rSPARE -sSPARE -tSPARE -u
(0) SUBTEST SELECT -V (22)-------------------- llJ1-35, REF(GNO/OPEN)
}
11J2-35, APPX
C115J1-V C
SPARE -w
SPARE -x
SPARE -Y(0) FGC RIGHT -Z (22) -------------------- llJ1-62
PRIORITY SELECT (GND/OPEN)
(I) fvIAINT. TEST ENABLE* -AA (22) ------------------- APPENDIXD
(I) CAL IB/TEST -BB ------NC REF APPENDIX CSPARE -cc
(Ij LAMP TEST* -DC)(22)------------------- A/CWIRING,REF APPENDIX C
SPARE -EE(o) ILS/MLS SELECT OUT -FF (22) ------------------- APPENDIXD,
(GND/OPEN) REF APPENIIIX C
(o) NAV RETUNE -GG (22) ------------------- W{ ~, REF
(0) FGC LEFT 115J1-HH (22)------------------- llJ1-61
PRIORITY SELECT (GND/OPEN)
Interconnect InformationTable 501 (cent) 22-14-00
Page 569Apr 15/93
Use or disclosure of information on this page is subject ta the restrictions on the title page of thk document,
Display Controller No. 1
IOB_P_ Function Connector Pin Connects To
(B) SYS ASCB (H)t
115J21~ ~::]---:-:- ------------ SEE SECTION 3.3(B) SECONDARY BUS (L) -----.- ------------)
SPARE -c\/
SPARESPARE +SPARE -FSPARESPARE :;SPARESPARE 1
(1) (H) i-L (22)----’-2------------- 9JIA-35(o) BARO SET (w)
{-M (22)---!--’------------- 9J1A-36
(I) (L) -N (22)---!Ci1------------- 9JIA-37SHIELD GND ---
SPARE -P(1) PHOTO SENSOR #1 (H) t-R (22)---;~l- ------------ 130J]-28,
(I) (L) i131J1-29
-s (22)---\-;- ------------ 130J1-41,
I
131J1-42(I) PHOTO SENSOR #2 (H) -T (22)----f~- ------------ 130J1-2!l,
(I)131J1-28
(L) -u (22)---+-- ------------ 130J1-42,
I131J1-41
(I) PHOTO SENSOR #3 (H) -V (22)---2121- ------------ 130J1-26,
C130J1-26,11 131 J1-26,
II C131J1-26,
II 132J1-26,
II 133J1-26,
IIC115J2-V, REMOTE
~jo:fN:~R (H)(I) PHOTO SENSOR #3 (L) -w (22)---J;-;-------------
C130Ji-2~,131J1-27,C131J1-27,132J1-27,133J1-27,C115J2-W, REMOTELT SENSOR (L)
SPARE 115J2-X
Interconnect InformationTable 501 (cent) 22-14-00
Page 570Jun 1/87
Use or disclosure of mformallon on thm page m subject to the rf strlctlons on the Mle page of this document
Display Controller No. 1
IOB~ Function Connector Pin
SPARE 115J2-YSPARE -zSPARESPARE $
(I) CRS SEL #l (H) -C (24)--{-~-
1
------------- llJ1-32,C115J2-C
(I) (L) -d (24)--:-;- ------------- llJ1-33,Cl15J2-d
(I) CRS SEL #l SYNC (GND/OPEN) -e (24)-------------------- llJ1-36,Cl15J2-e
SPARE -f(I) CRS SEL #2 (H) .g (24).--~.~-
1
------------- 11J2-32,Cl15J2-g
(I) (L) -h (24)----U;-------------- 11J2-33,Cl15J2-h
(I) CRS SEL #2 SYNC l15J2-j (24)-------------------- 11J2-36,(GND/OPEN) Cl15J2-j
I
Interconnect InformationTable 501 (cent) 22-14-00
Page 571Jun 1/87
Use or dmclosure of mformatlon on thm page E sublet 10 the restrictions on the Mle page of thm document
CDU No. 1
10BP Function Connector Pin Connects To
SPA2E
(P)
120J1-A
+28 V DC POWER -B ( NOTE 3)---------------- A/C 28 V DC PWR
(P) POWER RETURN -C ( NOTE 3)---------------- A/C POWER GND(I) PANEL LIGHTING RTN -D (22)-------------------- A/C POWER GND
SPARE -E
(P) 28 V ANNUN LIGHTING -F (20)-------------------- A/C 28 VDC F%IR(P) CHASSIS GN!I -G (20)-------------------- A/C CHASSIS GND(P) ANNUN LIGHTING RTN -H (22)-------------------- A/C LTNG GND(P) 5V KEY BOARO PANEL LTNG -J (22)-------------------- A/C LTNG CNTL
RESERVEDSPARE ::
(B) RS422 XMTR * (H)I
-N (22)-----% ----------- 121JIA-55
(B) (DATA) NAV COMP (L) -N (22)----~Y’- ----------- 121J1A-56SHIELD GND---
(B) RS422 XMTR - (H)i
-P (22)-----=- ----------- 121J1B-7(B) (CNTL) NAV COMP (L) -R (22)----:$- ----------- 121J1B-S
SHIELD GND---
(B) RS422 RCVR - (l-l)
I-S [22)----+ ----------- 121J1A-65
(B) (DATA) NAV COMP (L) -T (22)-------- ----------- 121J1A-66(B) RS422 RCVR - (H) -U (22)-----N-- ----------- 121J1B-32(B) (CNTL) NAV COt’4P (L) V (22)-----’u~- ----------- 121J1B-33
(B) RS422 RCVR - (H) -W (22)-----= ----------- 121J1B-35
(B) (CLK) NAV COMP (L) --~[::]----++ ----------- 121J18-36(B) RS422 XMTR - (H) ----------- 122J1A-103[B) (DATA) PERF COMP (L) -z (22):::+: ----------- 122J1A-104
SHIELD GND---(B) RS422 XMTR - (H)
i-a {22)-----S-- ----------- I22J1A-105
(B) (CNTL) PERF COMP (L) -b (22)----++- ----------- 122J1A-106SHIELD GND---
(B) RS422 RCVR - (H)
[
-C (22)----7~7- ----------- 122J1A-101(B) (OATA) PERF COMP (L) -d (22)-----X- ----------- 122J1A-102(B) RS422 RCVR - (H) -e (ZZ)----7-T- ----------- 122J1A-99[;] (CNTL) PERF COMP (L) -f (zz)-------- ----------- 122J1A-1OO
RS422 RCVR - (H)(B) (CLK) PERF COMP
-g (22)-------- ----------- 122J1A-97(L) -h (22)-----’~- ----------- 122J1A-98
(0) ct)uvALIO (GNO/OpEN) 120J1-i (22)-------------------- 121J1B-loo,134J1A-75,C134J1A-75
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Use or rkckmure of mtormatlon on this page M subject to the ecdrlctlons on the Iltle page of this ~ocument
CDU No. 1
IOBP Function Connector Pin Connects To.—
SPARE 120J1-jSPARE -k
(0) R PHOTO SENSOR OUT -m (22)-------------------- TEST ONLY
(0) L PHOTO SENSOR OUT -n (22)-------------------- TEST ONLY
SPARE -P(1) DIM CALIBRATION -q (22) -------------------- TEST ONLY
SPARE -r
(I) LAMP TEST* -s (22)-------------------- A/C LAMP TEST,REF APPX C
SPARE -t
SPARE
(I) ANNUN LIGHTING BRIGHT/DIM :1 (22) -------------------- A/C WIRING,
(OpEN/28V) REF APPX C(I) ANNUN LIGHTING DIM -w (22) -------------------- A/C WIRING
CONTROL (0-28V)
SPARE -x
SPARE -YSPARE -z
SPARE -AASPARE -BB
SPARE -cc
SPARE -DD(1) SELF TEST ENBL* -EE ------NC
SPARE -FFSPARE -GGSPARE 120J1-HH
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of mformatlon on thts page ts sublet’ 10 the reslrlctlons on the title page of this document
Navigation Computer No. 1
IOB~
(P)
(P)(P)(P)(P)(P)
(B)(B)
(I)
(B)(B)
(B)(B)(B)(B)
(B)(B)
(B)(B)
(B)
(B)
Function Connector Pin Connects To
AIRCRAFT BATT +28V 121J1A-1 (20)-------------------- A/C 28 VDC
SPARE
+28 V DC POWERPOWER RETURNCHASSIS GROUND
SIGNAL GROUND
AIRCRAFT BATT RETURN
RESERVED
RESERVED
SYS ASCB PRI BUS (H)SYS ASCB PRI BUS (L)
RESERVEDRESERVEDDISC CNTL INPUT -
NO CLOCK ASCB*
SPARE
ARINC 429 RCVR -
MLS/ILS PRIMARY
ARINC 429 RCVR -
DME PRIMARY
RS 422 RCVR -
DME PRIMARY
RESERVED
ARINC 429 RCVR -
LTS #2
RESERVED
ARINC 429 RCVR -
LTS#l
(H)(L)
(H)(L)(H)(L)
(H)(L)
(H)(L)
BATTERY DIRECT-2
-3 (NOTE 3)---------------- A/C 28VDC PWR
-4 (NOTE 3)---------------- A/CGND
-5 (20) -------------------- A/C CHASSISGND
-6 (20)-------------------- A/CSIGNALGND
-7 (20)-------------------- A/C POWERGND
-8
-9-lo (22)-~-
$------------- REF. SECT3.3
-11 (22)-3- --------------1-12-13-14 (22)------------------- SIGGND,
REF. APPX C
-15
-16 (22)-fl-
$
------------- APPXD
-17 (22)-#- ------------- APPXD
-18 (22)-fi-$
------------- DMENO. 1,
-19 (22)-~- 1--------------ARINC 429-20 ------NC-21 ------NC-22
#-23 (22)--H---------------- C149JI-24 (OPT)
-24 (22)--U- -------------- C149J1-25 (OPT)-25-26 (22)--~-
*------------- 149JI-38 (OPT)
-27 (22)-~~- ------------- 149J1-39 (OPT)
RS422 RCVR - (H)
DATA LOADER
-28 (22)-fi-ll
T
-------------- 123J1-T,C121J1A-28
II(DATA) (L) 121J1A-29 (22)--&* ------------- 123J1-S,
C121J1A-29
Interconnect InformationTable 501 (cent) 22-14-00
Page 574
Apr 15/93
Use or disclosure of information on this page issubject to the re:trictionson the title page of this document.
Navigation Computer No. 1
IOBJ& Function Connector Pin Connects To
(B) RS422 RCVR - (H) 121J1A-30 ------NC(B) NAV PRIMARY (L) -31 ------NC
(B) ARINC 429 RCVR - (H) -32 (22)---r+$ 1
----------- VORNO. 1,
(B) NAV PRIMARY (L) -33 (22)---U- ------------ ARINC 429
RESERVED -34(B) AFIS/ACRS (H) -35 (22)---pt
$-----------
1DMUJ1-18 APPX
(B) RX BUS (L) 4; (22)---~- ------------ DMUJ1-19 D
RESERVED
RESERVED -38
RESERVED -39
(B) RS422 XMTR - (H) -40 ------NC(B) GENERAL BUS #3 (L) -41 ------NC
RESERVED -42
(B) ARINC 429 REC - (H) -43 (22)---CJ$
)
----------- VORNO. 2,
(B) NAV SECONDARY (L) -44 (22) ---U-------------- ARINC 429.
(B) ARINC 429 XMTR (H) -45 (22)------
$
l? --------- C170J1B-C5,E170J1B-A8
(B) GEN BUS SECONDARY (L) -46 (22)------4----------C170J1B-C6,SHIELD GND--------------- E170J1B-A9
~: GEN BUS SECONDARY OUTPUT ALSO GOES TO THE FOLLOWING:ADF #2, COMM #2, DME #2, ILS #2, MLS #2, VOR #2, AND XPDR #2
(I) HIGH/LOW* SPEED BUS-LTS#l -47 -----NC APPX C(I) HIGH/LOW* SPEED BUS-LTS#2 -48 -----NC APPX C(I) HIGH/LOW* SPEED BUS-LTS#3 -49 -----NC
t
APPX C(B) ARINC429XMTR (H) -50 (22)-------H--------- 149J1-18 (opT)
~~ C149J1-26 (OPT)170J1B-A8
!,+
DMUJ1-20 (APPX D)(B) GEN BUS PRIMARY (L) 121 J1A-51 (22) -------~=L --------- 149J1-37 (OPT)
IC149J1-27’(OPT)170J1B-A9
DMUJ1-21 (APPX D)
SHIELD GND---------------
U: GEN BUS PRIMARY OUTPUT ALSO GOES TO THE FOLLOWING:
ADF #1, COMM #1, DME #1, ILS #1, MLS #1, VOR #1, AND XPDR#l
Interconnect InformationTable 501 (cent) 22-14-00
Page 575Apr 15/93
Use or disclosure of information on this page is subject to the restrictionson the title pag(’of this document,
Navigation Computer No. 1
IOB~ Function Connector Pin connects To
(B) RS 422 XMTR -
1
(H) 121J1A-52 (22)----------1=1----- 123J1-H,C121J1A-52
(B) DATA LOADER (L) -53 (22)----------4-J----- 123J1-G,
1’C121J1A-53
(DATA) SHIELD GND------------
SPARE -54(B) RS 422 RCVR - [~]
!-55 (22)---+q- ----------- 120J1-M
(B) (DATA) CDU -56 (22) ---4:J- ----------- 120J1-N
SPARE -57
RESERVED -58
RESERVED -59
RESERVED -60
RESERVED -61
RESERVED -62
RESERVED -63
RESERVED -64
(B) RS 422 XMTR - [~]I
-65 (22)----q~l- ---------- 121)J1-S
(B) (DATA) CDU -66 (22)----4-+----------- 120J1-TSHIELD GND----------------
RESERVED 121J1A-67
Interconnect InformationTable 501 (cent) 22-14-00
Page 576Mar 15/91
Use or dcs.closure of Information on this page ts subject 10 the rhstncttons on the title page of this document
Navigation Computer No. 1
IOB~ Function connector Piq co nnects TO
RESERVED 121 J1B-1
RESERVED -2
SPARE
RESERVED ::
RESERVED
SPARE ::
t(B) RS 422 CDU CNTL RCVR (H) -7 (22) ----~r- ------------ 120J1-P
(B) (L) -S (22)----U- ------------ 120J1-R
(0) TAG SYNC -9 (22)-------------------- C121J1B-34
(B) IKZ;; RCVR .10 (22)---F+.+------------ ;:: ;;: cll~[PORT C -11 (22)---c;-;------------
(B) RS 232 XMTR -12 (22)---~” ------------ FLT TEST ONLY
{5) ~SZ3; RCVR
!
-13 (22)----G- ----------- FLT TEST ONLY (2)PORT A -14 (22)----;1- ----------- FLT TEST ONLY (7)
(B) RS 232 XMTR -15 (22)----u- ----------- FLT TEST ONLY (3)(o) Cou SYNC -16 (22)------------------- C121J1B-48
(B) RS 232-RCVR -17 (22)
1
---+% ------------ FLIGHT TEST ONLY{1
RETURN PORT B -18 (22)---1-F ------------ FLIGHT TEST ONLY
(B) RS 232-XMTRII
-19 (22)---@------------ FLIGHT TEST ONLY
(B) RS 422 XMTR - DATA (H) -20 (22)----: ‘------------ 123JI-K,T C121J1B-20
(B) LOADER (CLK) (L) -21 (22)----1+----------- 123JI-J,SHIELD GOD------------- C121JIB-21
(B) ARINC 429 RCVR -#)
(H) -22 (22) ------- - --------- DME NO. 2,
(6) DME SECONOARY1?
[~] -:~ (22)------U- --------- ARINC 429(B) RS 422 RCVR- ------NC(B) DME SECONDARY (L) ~25 ------NC
RESERVED -26RESERVED -27
(B) SYS ASCB SEC BUS (H)
!
-28 (22)---?- ------------ REFSECT 3.3RESERVED -29RESERVED -30
[;~ SYS ASCB SEC BUS (L) ‘i.3] (22)--.&- ---X ------ REF sEcT 3.3RS 422 XMTR 4(H) 121J1B-32 (22)--~-------ii ------ 120J1-U
Interconnect InformationTable 501 (cent) 22-14-00
Page-5f7Mar 15/91
Use or dmclosure of mtormatlon on thm page )s subject to the restrictions on the Idle page of thm tlocurnent,
10BP
(B)
(1)
(B)(B)
(o)(o)
(0)
(o)(o)(0)[:]
[:]
(o)(1)
(o)
(o)(o)
(o)
(B)(B)(I)(1)(I)(1)(I)(.1)(1)
Navigation Computer No, 1
Function Connector Pin Connects ToI
CNTL-CDU Jt~(L) 121J1B-33 (22)--- --------------SHIELD GND------------Y
TAG SYNC -34 (22)-------------------
RS 422 XMTR CLK-CDU (H) -35 (22)------5-*
---------(L) -36 (22)-------~ ---------SHIELD GND---------~
TRUE/MAG SELECT (GND/OFIEN)-37 (22)-----------z-.-----ONSIDE TUNING CNTL -38 (22)-------------------[AUTOTUNt)(GND/ OPEN)REMOTE TUNING CONTROL .39 ------NC(GND/OPEN)LAT WPT ALERT (GND/OPEN) -40 (22)-------------------VERT ldPTALERT [GND/OPEN) -41 (22)-------------------DEAD RECKONING (GND/OPEN) -42 (22)-------------------OFF SET ALERT (GND/OPEN) -43 (22)-------------------APPR SENSITIVITY (GND/OPEN)-44 (22)-------------------INDEP OP (GND/OPEN) -45 (22)-------------------CDU MSG (GND/OPEN) -46 ------NC
DGRADE ACCURACY (GND/OPEN)-47 (22)-------------------CDU SYNC -48 (22)-------------------
NAv COMP VALID (GND/OpEN) -49 (22)-------------------SPARE -50SPARE -51RESERVED -52VERTICAL TRACK AURAL -53 ------NCALERT (GND/OPEN)CROSS SIDE TUNING CONTROL -54 (22)-------------------(AUTOTUNE) (GND/OPEN)RESERVED -55RESERVED -56ARINC 429 RCVR- (H) -57 ------NCLTs#3 (L) -58 ------NCLTS#l NUMBER BIT #1 -59 ------NCLTS#l NUMBER BIT#2 -60 ------NCLTS#2 NUMBER BIT #1 -61 ------NCLTS#2 NUMBER BIT#2 -62 ------NCLTS#3 NUMBER BIT #1 -63 ------NCLTS#3 NUMBER BIT#2 -64 ------NCSDI #3 121J1B-65 ------NC
120JI-V
C121J1B-9
120J1-w120J1-X
.
NAV CONT #1,CL21J1B-54
REF
APPX”
c
C121J1B-16
C121J1B-38,NAV CONT #2
Interconnect InformationTable 501 (cent) 22-14-00
Page 578Feb 1/88
Use or dmclosure of mformatlon on this page E subpct to the restrictions on the tttle page of this document
Navigation Computer No. 1
IOB~ Function connector Pin Connects To
(I) CROSSFILL ENABLE* 121J1B-66 ------NC
(I) VER B ASCB* -67 (22)------------------- SIG GND(I) FUEL FLOW CONFIG IDO -68 ------NC(1) FUEL FLOW CONFIG ID1 -69 ------NC(1) FUEL FLOW CONFIG ID2 -70 ------NC(I) OPERATIONAL MODE ID O -71 (22),---=---------------SIGGND(I) WOW* -72 (22)------------------- A/CWIRING(I) PERF COMP INSTALLED* -73 (22)------------------- SIG GND(I) LTS #1 CONFIG -74 ------NC(I) LTS #1 CONFIG -75 ------NC(I) LTS #1 CONFIG -76 ------NC(1) LTS #2 CONFIG -77 ------NC(1) LTS #2 CONFIG -78 ------NC(I) LTS #2 CONFIG -79 ------NC REF
RESERVED -80 APPXRESERVED -81 cRESERVED -82
(I) DL CONNECTED* -83 (22)------------------- 123J1-E(I) RADIO CONFIG IDO -84 (22)------------------- A/CGND(I) RADIO CONFIG ID1 -85 ------NC(I) RADIO CONFIG ID2 -86 ------NC(I) MAINT TEST ENABLE* -87 (22)------------------- APPX D(I) ILS*/MLS SELECT -88 (22)------------------- APPX D(I) LTS#3 CONFIG -89 (22)-------------------(I) LTS#3 CONFIG -90 (22)-------------------(I) LTS#3 CONFIG -91 (22)-------------------(I) OPERATIONAL MODE ID 1 -92 (22)------------------- SIGGND(1) INITIATED XMIT* -93 ------NC(1) INITIATED REC* -94 ------NC(I) DME SCAN TYP* -95 (22)------------------- A/CGND(1) RADIO BUS TYPE (OPEN/GND) ~~~ ------NC(1) SINGLE ASCB* ------NC(I) SDI#l=LEFT -98 (22)------------------- GND(1) sDI#2=RIGHT 121J1B-99 ------NC
Interconnect InformationTable 501 (cent) 22-14-00
Page 579Mar 15/91
Use or disclosure of mformatlon on Ihls page IS subpc$ 10 the restncllons on the Ittle pagu of thm document.
Navigation Computer No. 1
IOB~ Function Connector Pin Connects To
(I) CDU VALID* 121J1B-1OO (22)------------------ 120J1-i,134J1A-75,C134J1A-75
(I) TRUE REF SELECTED* -101 (22)------------------(I) AFIS INSTALLED* -102 (22)------------------(I) OVERSPEED PROTECTION -103 ------NC
DISABLE*(I) RS 422 OFFSIDE VOR -104 ------NC APX
CONNECTED* ‘c
(I) NAV/DME MANUAL* TUNE -105 (22) ------------------ SECNAV/DME
SEC AUTO TUNE
DISABLE SW
(I) NAV/DME MANUAL* 121J1B-106 (22) ------------------ PRI NAV/DME
TUNE PRI AUTO TUNE
DISABLE SW ,
Interconnect InformationTable 501 (cent) 22-14-00
Page 580Apr 15/93
Use or disclosure of information on this page is subject to the resrictions on the title page of this document,
Performance Computer No. 1
IOB~ Function Connector Pin Connects To
(P) CHASSIS GROUND 122J1A-1 (22)-------------------- A/C GND(P) SIGNAL GROUND -2 (22)-------------------- A/C SIGGND(P) SERVO POWER (H) -3 (NOTE 3)---------------- 28VDC(P) SERVO POWER (H) -4 (NOTE 3)---------------- 28VDC(P) CLUTCH POWER (H) -5 (NOTE 3)---------------- 28VDC(P) CLUTCH POWER (H) -6 (NOTE 3)---------------- 28VDC(P) CC)MPUTERPOWER (H) -7 (NOTE 3)---------------- 28VDC(P) COMPUTER POWER (H) -8 (NOTE 3)---------------- 28VDC(P) SERVO POWER (L) -9 (NOTE 3)---------------- A/C PWRGND(P) SERVO POWER (L) -10 (NOTE 3)--------------- A/C PWRGND(P) CLUTCH POWER (L) -11 (NOTE 3)--------------- A/C PWRGND(P) CLUTCH POWER (L) -12 (NOTE 3)--------------- A/C PWRGND(P) COMPUTER POWER (L) -13 (NOTE 3)--------------- A/C PWRGND(P) COMPUTER POWER (L) -14 (NOTE 3)- ------------- A/C PWRGND(0) SERVO NO. 1 DRIVE (H)
[
-15 (20)----- ------------- L128P1-B,C122J1A-15
(0) SERVO NO. 1 DRIVE (L) -16 (20)----- ------------- L128P1-C,
i
C122J1A-16(0) SERVO NO. 2 DRIVE (H) -17 (20)----- ------------- R128P1-C,
C122J1A-17(0) SERVO NO. 2 DRIVE (L) -18 (20)----- ------------- R128P1-B,
C122J1A-18RESERVED -19RESERVED “20RESERVED -21RESERVED -22
(0) SERVO CLUTCH DRIVE NO. 1 -23 (20)------------------- L128P1-E,C122J1A-23,134J1B-30,C134J1B-30
(0) SERVO CLUTCH DRIVE NO. 2 -24 (20)------------------- R128P1-E,C122J1A-24,134J1B-32,C134J1B-32
RESERVED -25RESERVED -26SPARE -27SPARE -28SPARE -29SPARE -30SPARE 122J1A-31
Interconnect InformationTable 501 (cent) 22-14-00
Page 581Mar 15/91
Use or disclosureofmformahononthmpage IS subpcttotherestrlcllonsonthetitlepage 01 thisdocument.
IOBP
(B)(B)
(B)(B)(B)
(B)(B)(B)(B)(B)(B)(I)(o)(I)
(I)
PerformanceComputer No. 1
Function $onnector Pin
SPARE 122J1A-32
ASCB (H) -33 (22)”-”fi-”j-------”----PRIMARY PORT (L) -34 (22)----- ------------SPARE -35RESERVED -36RESERVED -37SPARE -38RS 232 RCVR (1/0) %4-------------39 (22)---,-,RS 232 RTN (1/0) -40 (22)---~;-
$
. - --- --- -- - -
RS 232 XMTR (1/0) -41 (22)---~- . - - -- . - - .- --
RS 232 RCVR (A/T)
RS 232 RTN (A/T)
RS 232 XMTR (A/T)RS 232 RCVR (PERF)RS 232 RTN (PERF)RS 232 XMTR (PERF)CROSS-SIDE A/T ENGAGE*A/T ENGAGE (GND/OPEN)MAINT TEST ENABLE*RESERVEDRESERVEDRESERVEDGEAR DOWN*
-42-43-44-45-46-47-48-49-50-51-52-53-54
SPARERESERVEDRESERVED
-55-56
122J1A-57
i
(22)--+- .
(22)-+-- -(22)---U- -
1
(22)--p-- -(zZ)-_J.~-- _
(22)_Ju- .
(22)--------(22)--------(22)--------
(22)--------
- --- - - -- -- .- - -- - - ---- -- - -- . - --- . .- . . -- . ---- --- - -- - - - ----- - - - - - - ----------- ---------- ----- -- - - -- - - . -
-------- ---
Connects TQ
SEE SECT. 3.3
‘ FLT TEST ONLY
22J1A-4922J1A-48‘Px0,:FAPPX C
A/C GEAR DOWNDISCRETE,C122J1A-54,REF APPX C
Interconnect InformationTable 501 (cent) 22-14-00
Page-582Mar 15/91
Use or disclosure of mformallon on Ihls page IS subject tother+stnctlonsonthehtlepage ofthisdocument
PerformanceComputer No. 1
IOB_p_ ~ Connector Pin Connects To
SPARE 122 J1A-58
(I) LEFT/RIGHT* SELECT -59 ------NC
(I) ASCB VER A/B* -60 (22) ------------------- SIG GNDRESERVED -61 REF
(I) LEFT BLEED SRC ON* -62 (22)------------------- A/CWIRINGAP~X(I) RIGHT BLEED SRC ON* -63 (22)------------------- A/C WIRING
SPARE -64RESERVED -65 P
(I) ASCB SINGLE/DUAL* -66 (22)------------------- SIGGNDRESERVED -67RESERVED -68RESERVED -69RESERVED -70RESERVED -71 5.1 I@FLAPS IN MOTION -72 (22)-----~----- A/c ‘IRING
(I) LEFT AC PACK ON/OFF -73 (22)------------------- A/C WIRING(28V/OPEN)
(I) RIGHT AC PACK ON/OFF 122J1A-74 (22) ------------------- A/C WIRING J(28V/OPEN)
Interconnect InformationTable 501 (cent) 22-14-00
Page 583Mar 15/91
Use or dmclosure of mformallon on thm page IS subject 10 the restncllons on the title page of this document.
Honeywell &!#~~E
Performance Computer No. 1
IOBP Function Connector Pin Connects To
(I) WOW* 122J1A-75 (22)------------------- ~~~xW;RING,
RESERVED -76RESERVED -77RESERVED -78RESERVED -79RESERVED -80
(I) A/T ENGAGE/DISENGAGE -81 (22)------------------- APPX D/REF
{OPEN/GND TOGGLE) APPX C
(B)
(B)
(B)(B)
(B)(B)
(B)(B)
RESERVEDRESERVEDRS422 XMTRRS422 XMTR
RS422 XMTRRS422 XMTR
RS422 XMTRRS422 XNTR
RS422 RCVRRS422 RCVRRS422 RCVRRS422 RCVRSPARESPARESPARERS422 XMTRRS422 XMTR
RS422 XNTRRS422 XMTR
RS422 XMTRRS422 XMTR
RS422 RCVRRS422 RCVR
-82-83
t(FT1-CLK) (H) -84 (22)---C-- -----------:(FT1-CLK) (L) -85 (22)---’+- ------------
SHIELD GND-----------
I(FT1-CNTL) (H) -86 (22)---= ------------(FT1-CNTL) (L) -87 (22)---’-!-------------
SHIELD GND-----------~
I(FT1-DATA) (H) -88 (22)---G- ------------(FT1-DATA) (L) -89 (22)---’$- ------------
SHIELD GND-----------
1(FT1-DATA) (H) -90 (22)--T?- ------------(FT1-DATA) (L) -91 (22)---=-- ---
$
-------
(FT1-CNTL) (H) -92 (22)------;~j- -..----
(FT1-CNTL) (L) ~;; (22)---------- -------
-95-96
i(CDU-CLK) (H) -97 (22) ---lfi--- ----------
(CDU-CLK) (L) -98 (22) ---~7--- ----------
SHIELD GND-----------~fi
i(CDU-CNTL) (H) -99 (22)---7-T-- ----------(CDU-CNTL) (L) -100 (22)---- ------------
SHIELD GND------------ Y
t(CDU-DATA) (H) -101 (22)---1:-- ----------(CDU-DATA (L) -102 (22)---Y-- ----------
SHIELD GND------------
I
(CDU-DATA) (H) -1o3 (22)--77-- ----------(CDU-DATA) (L) -104 (22)------ ----------(CDU-CNTL) (H) -1o5 (22)-----------------
122J1A-106 (22)--+-- ----------) (1)
●
FLT TEST ONLY
120J1-g120J1-h
120J1-e120J1-f
120J1-c120J1-d
120J1-Y120J1-Z120J1-a120J1-b
(B) RS422 RCVR(B) RS422 RCVR
(CDU-CNTL, ,L,
Interconnect InformationTable 501 (cent) 22-14-00
Page”584Feb 1/88
Use or disclosure of mformalton on this page IS subjecl to the r xstnctlons on the otle page ot this document
Performance Computer No. 1
IOB_P_ Function
(P) CHASSIS GND(P) SIGNAL GND
SPARE
(B) r4SCB SECONDARY PORT
(B) ASCB SECONDARY PORTSPARERESERVEDRESERVEDSPARERESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVED
Connector Pin Connects To
122J1B1; [;;]-------------------- A/CGND
-------------------- A/C SIGGND
!(H) ~~ ~:j]--fj- -------------)SEE SECT 3.3(L) -6 ------ -------------\/
-7-8-9-10-11-12-13-14-15-16-17-18-19-20-21-22-23-24-25-26-27-28-29-30-31-32-33-34-35-36-37-38-39
122J1B-40
Interconnect InformationTable 501 (cent) 22-14-00
Page 585Jun 1/87
Useordisclosure01Irrformatlonon this page IS subject to the restrictions on the title page of this documanl
Performance Computer No. 1
IOB~ Function Connector Pin Connects To
RESERVED 122J1B-41
RESERVED -42
RESERVED -43
RESERVED -44
RESERVED -45
(1) PLA1 POS (C)J-46 (22)---t=F ---- ------ A/CWIRING
(I) PLA2 Pos (c)-34~ (22)--------F-F------ A/CWIRING
RESERVEDRESERVED -49RESERVED -50RESERVED -51RESERVED -52RESERVED -53RESERVED -54RESERVED -55RESERVED -56RESERVED -57
(I) SERVO NO. 1 TACH (L)
1
-58 (22)---;~~ ------------ L128pl-D,C122J1B-58
(I) SERVO W. 1 TACH (H) -59 (22)--+4 ------------ L128P1-A,
I
C122J1B-59(I) SERVO NO. 2 TACH (L) -60 (22)---~[ ------------ R128pl-A>
C122J1B-60(I) SERVO NO. 2 TACH (H) -61 (22)----~ ------------ R128PI-D,
C122J1B-61RESERVED -62RESERVED -63RESERVED -64RESERVED -65
(I) PLA 1 POS (L)1
-66 (22)---t-t ------------ A/CUIRING(I) PLA 1 POS (H) -67 (22)---~F ------------ A/CUIRING~;~ PLA 2 POS (L) -68 (22)--------t-t
J------- A/CWIRING
PLA 2 POS (H) +; (22)--------4=L ------- A/c wIRINGRESERVEDRESERVED -71RESERVED -72RESERVED -73RESERVED -74RESERVED -75RESERVED 122J1B-76
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of InformalIon on this page IS subject to the fvstncllons on the t!tle page of this document
Performance Computer No. 1
IOBAE!maM Connector P ui Son ects TOn
RESERVED 122J1B-77RESERVED -78RESERVED -79RESERVED -80RESERVED -81RESERVED -82RESERVED -83RESERVED -84RESERVED -85RESERVED -86INTERLOCK #1 -87 (22)-------------------INTERLOCK #2
I
-88 (22)------------------- AP~X
INTERLOCK #3 -89 (22)-------------------
INTERLOCK #4 -90 (22)-------------------
(1) A/T DISCONNECT (OPEN/GND) ~;~ (22) ------------------- APPX D, APPX C
RESERVED
RESERVED -93
RESERVED -94
RESERVED -95 I
(1) PLA REF (H) -96 (22)--$
--------------- 26 VAC400HZ
(1) PLA REF (L) -97 (22)--- --------------- 26 VAC400HZ
RESERVED -98
(0) A/T ENGAGED GND -99 (22)------------------- A/CUIRINGRESERVED -1oo ENGINE SYNCRESERVED -101 COMPUTERRESERVED -102RESERVED -103RESERVED -104RESERVED -105
(o) PERF COMP INSTALLED 122J1B-106 ------NC
Interconnect InformationTable 501 (cent) 22-14-00
Page-587Mar 15/91
Use or dwclosure of mformalton on Ihts page ts sub)ecl to the restrictions on the Iltle page of this document,
Data Loader
IOB~ ~ Connector Pin Connects To
SPARE 123J1-A(P) 28 V DC POWER RTN -B (20) -------------------- A/C 28 V DC,
POWER RETURN
(P) 28 V DC POWER -C (20)-------------------- A/C28VDC PMR
(0) LOADER CONNECTED RIGHT -D (22) -------------------- C121JlB-83
(GND/OPEN)
(0) LOADER CONNECTED LEFT -E (22) -------------------- 121 J1B-83
(GND/OPEN)
(0) LOADER CONNECTED AUX -F
(GND/OPEN)
(B) RS422 RCV (DATA) (L) -G (22) --4=1--
i
------------ 121J1A-53,
‘1 C121J1A-53(B) (H) -H (22)--JO-- ------------- 121J1A-52,
C121J1A-52
(B) RS422 RCV (CLK) (L) -J (22) --fl--
i
--”--------- 121J1B-21,
C121JlB-21
(B) (H) -K (22)------ ------------ 121J1B-20,
C121J1B-20
RESERVED -L
RESERVED
RESERVED 1
RESERVED
RESERVED 1
(B) RS422 TX (DATA) (L)
!
-S (22)--0--- ------------ 121J1A-29,
11 C121J1A-29(B) (H) -T (22)---!!--------------- 121JIA-28,
C121JIA-28
(B) RS232 RCV LINE SIG DET ------NC(B) RS232 SIGNAL GND :; (22) -------------------- SIG GND(B) RS232 DATA SET READY ------NC IAPPX(B) RS232 CLEAR TO SEND ------NC D(B) RS232 REQUEST TO SEND :;------NC(B) RS232 RCV DATA -z----------$-
i----------.-
(B) RS232 XMIT DATA --------- - -----------{P) CHASSIS GND :: (22)----W-------------- A/C CHASSIS GND
SPARE 123J1-c
Interconnect InformationTable 501 (cent) 22-14-00
Page 588Mar 15/91
Use or dmclosure of mforrnatton on thm page )S subject 10 the r !stnctlons on the htle page of this document
10BP
(o)
(o)
(I)
(I)
(1)
(P)
(P)
Autothrottle Servo No. 1
Function Connector Pin
SERVO TACH (H) L128P1-A (22)-----7~y-
i
-----.---
SERVO TACH (L) -D (22)-----d-~- -----.-.-
l’SHIELD GND------------SERVO DRIVE (H)
I
-B (20)---------- ---------
SERVODRIVE (L) -c (20)---------- ---------
CLUTCH (H) -E (20)--------------------
ym;s JL$ -F (20)--------------------L128P1-G (22)--------------------
Connects To
122J1B-59,C122J1B-59122J1B-58,C122J1B-58
122J1A-15,C122J1A-15122J1A-16,C122JIA-16122J1A-23,C122JIA-23,134J1B-30,C134J1B-30A/C PWR GNDA/C CHASSIS GND
Interconnect InformationTable 501 (cent) 22-14-00
Page 589Feb 1/88
Use or dlSCiOSufe of lnfOrmatlOn on this page IS sublet 10 the restrictions on the Iltle page 01 Ihm document
Autothrottle Servo No. 2
106P Function Connector Pin Connects To
(0) SERVO TACH (H)
[
R128P1-A (22)-----7~1-- --------- 122J1B-60,C122J1B-60
(0) SERYOTACH (1) -D (22)-----!-J-- ---------
Y
122JIB-61,C122J1B-61
SHIELD GN9-------------(1) SERVO !3RIVE (H)
1-B (20)---------- --------- 122J1A-18,
C122J1A-18(1) SERVO DRIVE (L) -C (20)----------t--------- 122J1A-17,
C122J1A-17(1} CLLITCH (H) -E (20)-------------------- 122J1A-24,
C122JIA-24,
134J1B-32,
C134J1B-32
(P) CLUTCH (L) -F (20)-------------------- A/C PWR GND
(P) CHASSIS GND R128P1-G (22)-------------------- A/C CHASSIS GND
Interconnect InformationTable 501 (cent) 22-14-00
Page 590Feb 1/88
Useordwclosure of mformatron on tths page IS sub~ect to the Mrictlonson the Ittle page of fhm document
Manual Controller
IOB_P_
(P)(o)
(P)(P)(P)(I)(o)(o)
(P)(P)
(P)(o)
(P)
(P)
(I)
(o)
(o)
(o)
(o)
(P)
(o)
(o)
Function Connector Pin Connects To
-15 VDC EXC SYS 1 129J1-1 (22) -------------------- 1OJ2B-57
TK SIGNAL SYS 1 -2 (22)-------------------- 1OJ2B-58,
+15 V DC EXC SYS 1TK RETURN SYS 1
CHASSIS GROUNDTK DETENT SYS 1 (COMMON)
TK DETENT SYS 1 (DETENT)
TK DETENT SYS 1
(DETENT NOT)
LIGHTING (5V) (H)
LIGHTING LO
C1OJ2B-6O-3 (22)-------------------- 1OJ2B-55-4 (22)-------------------- 1OJ2B-56-5 (22)-------------------- A/C CHASSISGND-6 (22)-------------------- A/C 28 VDCN0.1
------NC:: (22)----------------------10J2B-59,
C1OJ2B-6I-9 (22)-------------------- A/C 5V LIGHTING-10 (22)------------------- A/C LIGHTING GND
-15 VDC EXC SYS 2 -11 (22)-------------------TK SIGNAL SYS 2 -12 (22)-------------------
+15 V DC EXC SYS 2 -13 (22)-------------------TK RETURN SYS 2 -14 (22)-------------------
TK DETENT SYS 2 (COMMON) ‘-15 (22)-------------------
TK DETENT SYS 2 (DETENT) -16 ------NC
TK DETENT.SYS 2 -17 (22)-------------------(DETENT NOT)
(H) -18 (22)--:j- + . - - --- . - -- - - -
PITCH WHEEL SYS 1
(L) i-19 (22)-J<;- -------------
SHIELD GND-------J
LIGHTING (28V) (H) -20 (22)-------------------
PITCH WHEEL (H)f
-21 (22)-----f;- ---------
SYS 2 (L)11~
129J1-22 (22)------C-----------SHIELD GND-------
C1OJ2B-57C1OJ2B-58,1OJ2B-6OC1OJ2B-55C1OJ2B-56A/C 28 VDC NO. 2
1OJ2B-61,C1OJ2B-59IOJ2B-94,C1OJ2B-104IOJ2B-95,C1OJ2B-105A/C 28 VDC
LIGHTING PWR
IOJ2B-104,
C1OJ2B-94
IOJ2B-105,
C1OJ2B-95
Interconnect InformationTable 501 (cent) 22-14-00
Paae 591Jui 1/87
Use or dmclosure of Information on Ihm page IS sub]ec~ 10 the restrictions on the Iltle page of fh!s document.
Display Unit No. 1
IOB~ Function Connector Pin Connects To
(o)
I
(H) 130J1-1 (22)------?-- ---------- 135J1-1(I) BRIGHTNESS POT (W) -14 (22) ----!--- ---------- 135J1-2
(o) (L) -13 (22) ----U-- ---------- 135J1-3
SHIELD GND ------
(0) (H) -2 ------NC
(1) WX DIMMING (w) -15 -----NC
(o) (L) -3 ------NC
RESERVED
RESERVED ::
RESERVED -6
RESERVED -7
SPARE
RESERVED :;
RESERVED -lo
RESERVED -11RESERVED -12RESERVED -16RESERVED -17RESERVED -18
(B) BUS 3 (H) 9/-19 (22)---- - ----------- SEE APPENDIX A,
(B) (L) 1-20 (22)----L- ----------- FIG. A-4SPARE -21
(I) DU PWR DN* -22 (22)------------------- REV
CONTROLLER
P9-X,
t
APPENDIX B & C
(I) LIGHTING BUS (H) -23 (22) ------- ----------- 5V OR 28 V DC
(I) (L) -24 (22) ------- ----------- LIGHTING BUS FOR
INCLINOMETER
LIGHTING
1.5 WATTS
SPARE -25
(I) 4REMOTE LT SENSOR (H) 130J1-26 (22)----nr- ----------- 131J1-26,
132J1-26,
133J1-26,
115J2-V,
C115J2-V,
C131J1-26,
C130J1-26,
REMOTE
LT SENSOR HI
Interconnect InformationTable 501 (cent) 22-14-00
Page 592Mar 15/91
Use or disclosure of mformatton on this page m subject 10 the !~strlctlons on the title page of Ihm documenl
Display Unit No. 1
IOB& ~ Connector Pin Connects To
J(I) REMOTE LT SENSOR (L) 130J1-27 (22)---& ----------- 131J1-27,132J1-27,133J1-27,115J2-W,C115J2-W,C131J1-27,C130J1-27,REMOTE
i
LT SENSOR LO(0) DLS OUT (H) -28 (22)--& ------------- 131J1-29,115J2-R(o) (L) -41 (22)- - - ------------- 131J1-42,115J2-S
SHIELDGND -~(I) ALS (H)
t-29 (22)-----~1----------- 131J1-28,115J2-T
(I) (L) -42 (22)-----U-- --------- 131J1-41,115J2-URESERVED -30RESERVED -31RESERVED -32
(B) BUS 3 TERM (L) -33 -----NC
RESERVED -34
(B) BUS 2 ~llf) -35 (22) -----77--$--------)
SEE APPENDIX A(B) -36 (22)-----N-- --------- FIG. A-7(0) DU VALID (GND/OPEN) -37 ------NC(B) BUS 1 (H) -38 (22)------;--
#---------]SEE APPENDIX A
(B) (L) -39 (22)------------------ FIG. A-1
(0) REMOTE LT SENSOR GND -40 (22)----- ------------- A/C REMOTE(0) REMOTE LT SENSOR PWR (H) -53 (22)--1~-
i }------------- LT SENSOR
(o) (L~H1i:;#--y- -------------
RESERVED -43 ‘-RESERVED -44RESERVED -46RESERVED -47RESERVED -48
(B) BUS 2 TERM (L) -49 -----NCRESERVED -50RESERVED -51
(B) BUS 1 TERM (L) -52 -----NCRESERVED -55RESERVED -56RESERVED -57
(B) BUS4 (H) +130J1-58 (22)----:-- ---------- 130J1-85
Interconnect InformationTable 501 (cent) 22-14-00
Page 593Mar 15/91
Use or disclosure of mformatlon on thm page IS subpcl to the restrictions on the title page of thm document
Display Unit No. 1
IOBP
(B)
(B)
(B)
(B)(())
(o)
(o)
(B)(B)
(B)(B)
(B)(B)
(B)
(o)(o)(I)
(I)
Function Connector Pin
BUS 4 TRM [~jI Ii
130 J1-45 (22) -----C7- ----------
BUS 4 -59 -----NC
RESERVED -60
~;S:XB:E~ TERM (L) -61 -----NC
-62
RESERVED -63
WX BUS 1 TERM (L) -64 -----NC
DU OVERTEMP (GND/OPEN) -65 (22) -------------------
DU WRAPAROUND (H)(AF??NC429)DU WRAPAROUND (L)(ARINC 429)RESERVEDRESERVEDWX BUS 3 (H)WX BUS 3 (L)RESERVEDRESERVEDSPAREWX BUS 2 (H)WX BUS 2 (L)SPAREWX BUS 1 (H)
WX BUS 1 (L)
RESERVED
RESERVED
RESERVED
~~S~XB~Ej TERM (L)
BURST OUT (H)(L)
PORT SEL A
~
-66 (22)-----;;- ----------
-79 (22)----JC;- ----------
-67-68-69 -----NC-70 -----NC-71-72-73-74 -----NC-75 -----NC-76-77 -----NC-78 -----NC-80-81-82-83 -----NC-84
i-85 (22)-----~J- -----------86 (22)----JY;-Y-----------87 (22)-------------------
PORT SEL B -88 (22)-------------------
RESERVED 130J1-89
Connects To
130J1-86
134J1A-34,C134J1A-34134J1B-34,C134JIB-34134J1B-35,C134J1B-35
130J1-58130J1-45131J1-87,A/C WIRING,APPX B & C131J1-88,A/C WIRING,APPX B & C
Interconnect InformationTable 501 (cent) 22-14-00
Page 594Jun 1/87
UseordisclosureofInlormallon on this page IS subject to Ihe r, stnctlons on the title page of this document
Display Unit No. 1
IOBP Function Connector Pin Connects To
(I) I.D. #1 130J1-90 ------NC1
REF APPENDIX C
(I) I.D. #2 -91 ------NC
RESERVED -92
RESERVED -93
(P) CHASSIS GND -94 (22)------------------- A/C CHASSIS GNDRESERVED -95RESERVED -96
RESERVED -97RESERVED -98
(I) SOFTWARE ENABLE* -99 (22)------------------- FLT TEST ONLY
(I) SOFTWARE ENABLE* -100 (22)------------------ FLT TEST ONLY
(P) 28VDC -101 (NOTE 3)--------------(P) 28VDC
)-102 (NOTE 3)-------------- A/C 28 VDC PWR
(P) 28 V DC -103 (NOTE 3)--------------(P) 28 V DC RTN -104 (NOTE 3)-------------- A/C 28 V DC
(P) 28 V DC RTN)
-105 (NOTE 3)-------------- PUR RTN
(P) 28 V DCRTN 13OJ1-106 (NOTE 3)--------------
/
Interconnect InformationTable 501 (cent) 22-14-00
Page-595Jun 1/87
Use or disclosure of Information on this page w sublecf to the restnct!ons on Ihe htle page of ttus document.
Display Unit No. 2
IOB~ Function Connector Pin Connects To
(o)
i
(H) 131J1-1 (22)------,~-- --------- 135J1-4[~] BRIGHTNESS POT (W) -14 (22)-----I-F-- --------- 135J1-5
(L) -13 (22) ------ -- --------- 135J1-6
SHIELD GND -----Y
(0) (H)
i
5----------- 61J2-F-2 (22)-------(1) WX DIMMING (w) -15 (22)-----i -- --------- 61J2-G(o) (L) -3 (22)------4-- --------- 61J2-H
RESERVED -4RESERVEDRESERVED ::RESERVEDSPARE :;RESERVED -9RESERVED -loRESERVED -11RESERVED -12RESERVED -16RESERVED -17RESERVED -18
(B) BUS3 (H) fl~-19 (22)-----T - ---------- SEE APPENDIX A,(B) (L) 1+! (22)-----~- ---------- FIG. A-5
SPARE
(I) DU PWR DN* -22 (22)------------------- ~;VbCONTROLLER
APPEfiDIXB & C(I) LIGHTING BUS (H) -23 ------NC(1) (L) -24 ------NC
SPARE -25n+_____(I) REMOTE LT SENSOR (H) 131J1-26 (22)----1-1 130J1-26,
132J1-26,133JI-26,115J2-V,C115J2-V,C131J1-26,C130J1-26,REMOTELT SENSOR HI
Interconnect InformationTable 501 (cent) 22-14-00
Page 596Mar 15/91
Use or disclosure of Information on thts page E sublect to the rvstnct!ons on the htle page of Ihw document
Display Unit No. 2
IOB_P_ Function Connector Pin Connects To
(I)
(o)(o)
(I)(I)
(B)
(B)(B)(o)(B)(B)(o)(o)(o)
(B)
(B)
REMOTE LT SENSOR (L) 131 J1-27 (22)---u- L1 ~_____ 130J1-27,
132J1-27.
DLS OUT (H)(L)
ALS (H)
REsERv\~)
RESERVED
RESERVED
:~~E:v~~RM (L)
BUS 2 (H)
(L)
DU VALID (GND/OPEN)
BUS 1 (H)REMOTE L~L~ENsoR GND
REMOTE LT SENSOR PWR
RESERVEDRESERVEDRESERVEDRESERVEDRESERVEDBUS 2 TERM (L)RESERVEDRESERVED:::ESlv:;RM (L)
RESERVEDRESERVED
133J1-27;115J2-W,C115J2-W,C131J1-27,C130J1-27,REMOTE
~~; [;;]------------------ ;#:Yy&J----- ---.---...--- $
SHIELD GND ---
i-29 (22)------n-- -------- 130J1-28,115J2-R-42 (22)------!~---------- 130J1-41,115J2-S-30-31-32-33 ------NC-34-35 (22)-------fi-
*]------- SEE APPENDIX A
-36 (22)-------U- ------- FIG. A-8-37 ------NC-38 (22)-------fi-
$)------- SEE APPENDIX A
-39 (22)--------J- ------- FIG. A-2-40 ------NC
(H) -53 ------NC(L) -54 ------NC
-43-44-46-47-48-49 ------NC-50-51-52 ------NC-55-56
131J1-57
Interconnect InformationTable 501 (cent) 22-14-00
Page 597
Mar 15/91Use or disclosure of mformetlon on this page IS sub)ac to the reslnctlons on Ihe tttle page of this document
Display Unit No. 2
IOB_P_ Function Connector Pin
i
Connects To
(B) BUS 4 (H) 131J1-58 (22)-------~- -------- 131J1-85(B) :;; ~ TRM (L) -45 (22)---------- -------- 131J1-86(B) (L) -59 ------NC
RESERVED -60(B) WX BUS 2 TERM (L) -61 ------NC
RESERVED -62RESERVED -63
(B) WX BUS 1 TERM (L) -64 ------NC(0) DU OVERTEMP (GND/OPEN) -65 (22)------------------- 134J1A-35,
t
C134J1A-35(0) DU WRAPAROUND (H) -66 (22)------7?---------- 134J1B-39,
(ARINC 429) C134JIB-39(0) DU WRAPAROUND (L) -79 (22)------JJ---------- 134J1B-40,
(ARINC 429) C134J1B-40RESERVED -67RESERVED -68
(B) WX BUS 3 [[]i]
-69 (22)-------~- -------- SEE APPENDIX A
(B) -70 (22)---------- -------- FIG. A-9RESERVED -71RESERVED -72SPARE -73
(B) WX BUS 2 (H)i)
-74 (22) -------R-- -------- SEE APPENDIX A
(B) (L) -75 (22)------W-- -------- FIG. A-6SPARE -76
(B) WX BUS 1 [tl]i]
-77 (22)-------R-- -------- SEE APPENDIX A
(B) -78 (22)-------U-- -------- FIG. A-3RESERVED -80RESERVED -81RESERVED -82
(B) WX BUS 3 TERM (L) -83 ------NCRESERVED -84
(0) BURST OUT (H)i
-85 (22)------l~r- -------- 131J1-58(o) (L) -86 (22)-------G---------- 131J1-45(I) PORT SEL A -87 (22)------------------- 130J1-87,
A/C WIRING,APPENDIX B & C
(I) PORT SEL B -88 (22)------------------- 130J1-88,
A/C WIRING,
APPENDIX B & C
RESERVED 131J1-89
Interconnect InformationTable 501 (cent) 22-14-00
Page 598Mar 15/91
Use or disclosure of InformalIon on this page IS subject to the ~estrlcttons on the title page of !hls document.
IOB_P_
(I)(I)
(P}
(I)(I)(P)(P)(P)(P)(P)(P)
Function
I.D. #1I.D. #2RESERVED
RESERVED
CHASSIS GNDRESERVEDRESERVEDRESERVEDRESERVEDSOFTWARE ENABLE*SOFTWARE ENABLE*28 V DC28 V DC28 V DC28 V DC RTN
28 V DC RTN28 V DC RTN
Display Unit No. 2
Connector Pin Connects To
131J11:: (22)------------------- GND}
REF------NC APPENDIX C
-92-93-94 (22)------------------- A/C CHASSIS GND-95-96-97-98-99 (22)------------------- FLT TEST ONLY
-100 (22)------------------ FLT TEST ONLY
-101 (NOTE 3)--------------
)-102 (NOTE 3)-------------- A/C 28 V DC PWR
-103 (NOTE 3)--------------
-104 (NOTE 3)-------------- A/C28VDC
)
-105 (NOTE 3)-------------- PWRRTN
I31J1-106 (NOTE 3)--------------
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.1Jun 1/87
Use or disclosure of mformattonon thm page !s sublet.r to [he restrictions on Ihe title page of this dormment
Display Unit No. 3
IOB~ Function Connector Pin Connects To
(o) (H) 132J1-1 (22) ------~ --1--------- 135J1-7
(1) BRIGHTNESS POT (W)i
-14 (22) -----VI-- --------- 135J1-8
(o) (L) -13 (22)----- -- --------- 135J1-9
SHIELDGND ----- Y
(0) (H) -2 ------NC
(1) WX DIMMING (w) -15 ------NC
(o) (L) -3 ------NC
RESERVED -4
RESERVED
RESERVED :;
RESERVED -7
SPARE
RESERVED ::
RESERVED -lo
RESERVED -11RESERVED -12RESERVED -16RESERVED -17RESERVED -18
(B) BUS3 (H) -19 (22)-----7,-4 --------- SEE APPENDIX A,(B) (L) -20 (22)------U-S --------- FIG. A-2
SPARE -21(I) DU PWR DN* -22 (22)------------------- A/CWIRING,
65J1A-64,
C65J1A-64,
134J1A-46,
C134J1A-46,
E65J1A-64,
APPENDIX B & C
(I) LIGHTING BUS (H) -23 ------NC(I) (L) -24 ------NC
SPARE -25
i(I) REMOTE LT SENSOR (H) 132J1-26 (22)-----;- ---------- 130J1-26,
131J1-26,133J1-26,115J2-V,C115J2-V,C131J1-26,C130J1-26,REMOTELT SENSOR HI
Interconnect InformationTable 501 (cent) 22-14-00
Page 598:2Mar 15/91
Use or dwclosure of InformalIon on this page is subject to the rwxrlctlons on the title page of thw document.
Display Unit No. 3
IOB-P_ Function Connector Pin I Connects To
(I) J Lk______ ~30J1.27REMOTE LT SENSOR (L) 132J1-27 (22)---G
131J1-27;
133J1-27,
115J2-W,
C115J2-W,C131J1-27,C130J1-27,
REMOTE
(o)(o)
(1)(1)
(B)
(B)(B)(o)
(B)
(B)
(o)
(o)
(o)
(B)
(B)
DLS OUT (H)
(L)
ALS (H)
REsERv~~)
RESERVED
RESERVED
:;~Elv~~RM (L)
BUS 2 (H)
(L)
DU VALID (GND/OPEN)
REMOTE L;L\ENSoR ~ND
REMOTE LT SENSOR PWR
RESERVERESERVERESERVERESERVERESERVEBUS 2 1
RESERVE
RESERVE
BUS 1 1
RESERVE
RESERVE
RESERVE
1)))1ERM (L)))ERM (L)1))
i
LT SENSOR LO
-28 (22)-1:~ -------------- 133J1-29
-41 (22)-w -------------- 133J1-42
SHIELDGND ---
-29 (22)-~- + -------------- 133J1-28-42 (22).JU.S -------------- 133J1-41
-30
-31
-32
-33 ------NC
-34
#-35 (22)---R- ------------- SEE APPENDIX A
1-36 (22)---U- ------------- FIG. A-5-37 (22)------------------- 134J1A-29,
C134J1A-29,
i]
APPENDIX B& C
-38 (22)-------O- -------- SEE APPENDIX A
-39 (22)-------$ -------- FIG. A-8-40 ------NC
(H) -53 ------NC(L) 4; ------NC
-44-46-47-48-49 ------NC-50-51-52 ------NC-55-56
132J1-57
Interconnect InformationTable 501 (cent) 22-14-00
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Use or dmclosure of Information on this page is subject to the restrictions on the title page of thts document
Display Unit No. 3
106J_
(B)(B)(B)
(B)
(B)(o)
(o)
(o)
(B)(B)
(B)(B)
(B)(B)
(B)
(o)(o)(I)
(1)
Function Connector Pin
BUS 4 (H)1
132JI-58 (22)------r~r---------BUS 4 TERM (L) -45 (22)------}:L ---------;KES4EO(L) -59 ------NC
-60WX BUS 2 TERM (L) -61 ------NCRESERVED -62RESERVED -63WX BUS 1 TERM (L) -64 ------NCDUOVERTEMP (GND/OPEtIf) -65 (22)-------------------
PU WRAPAROUND (H)(ARINC 429)DU WRAPAROUND (L)(ARINC 429)RESERVEDRESERVED;; ;;; : (H)
(L)RESERVEDRESERVEDSPARE;; :1: ; (H)
(L)SPARE:; ;3: : (H)
(L)RESERVEDRESERVEDRESERVED~XBB;E; TERM (L)
BURST OUT (H)(1)
PORT SEL A
i
-66 (22)-----lq- ---------
-79 (22)-----;:/----------
-67-68-69 ------NC-70 ------NC-71-72-73-74 ------NC-75 ------NC-76-77 ---”--NC-78 ------NC-80-81-82-83 ------NC-84
!-85 (22)----t~i- -----------86 (22)---”4;4- -----------87 (22)-------------------
PORT SEL B -88 (22)-------------------
RESERVED 132J1-89
Connects To
132J1-85132J1-86
134J1A-36,C134J1A-36134J1B-41,C134JIB-41134J1B-42,C134J18-42
132J1-58132JI-45133JI-87,A/C WIRING,APPENDIX B & C
133J1-88,
A/C WIRING,
APPENDIX B & C
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.4Jun 1/87
Use or disclosure Of mformatlon on this page IS subject to the r ?slrlcttons on the title page of this document
Display Unit No. 3
OB~ Function Connector Pin Connects To
I) I.D. #1 132J1-90 ------NC
)
REF
I) I.D. #2 -91 (22)------------------- GND APPENDIX C
RESERVED -92
RESERVED -93
P) CHASSIS GND ~;: (22)------------------- A/C CHASSIS GND
RESERVED
RESERVED -96
RESERVED -97
RESERVED -98
I) SOFTWARE ENABLE* -99 (22)------------------- FLT TEST ONLY
1) SOFTWARE ENABLE* -100 (22)------------------ FLT TEST ONLY
P) 28 V DC -101 (NOTE 3)--------------
P) 28 V DC
)
-102 (NOTE 3)-------------- A/C 28 V DC PWR
P) 28 V DC -103 (NOTE 3)--------------
P) 28 V DC RTN -104 (NOTE 3)-------------- A/C 28 V DCP) 28 V DC RTN
)-105 (NOTE 3)-------------- PWR RTN
P) 28 V DC RTN 132J1-106 (NOTE 3)--------------
Interconnect InformationTable 501 (cent) 22-14-00
Page 598:5Jun 1/87
Use or dmclosure of information on Ihm page IS subjecl to Ihe restrlcttons on the title page of this document
Display Unit No. 4
105~ Function Connector Pin Connects To
(0)
i
(H) 133J1-1 (22)------,> ---------- 135J1-10[~] BRIGHTNESS POT (W) -14 (22)-----,-F- ---------- ~35J1-lJ
(L) -13 (22)------Y
---------- 135J1-12SHIELD GND -----
(0) (H) -2 ------NC
[~] ‘ix DIMMING
(w) -15 -----NC
(L) ------NC
RESERVED ::
RESERVED -5
RESERVED -6
RESERVED -7
SPARE -8
RESERVED -9
RESERVED -lo
RESERVED -11RESERVED -12RESERVED -16RESERVED -17RESERVED -18
(B) BUS3 (H)i
-19 (22)-----fi- ---------- SEE AppENDIx A,(B) (L) )~;; (22)-----v- ---------- FIG. A-1
SPARE(I) DU PWR ON* -22 (22)------------------- ;~~l~I~:NG,
C65Jl~-6~,
134J1A-47,
C134JIA-47,
E65J1A-65
APPENDIX B & C
(I) LIGHTING BUS (H)
(1) (L)
SPARE
-23 ------NC-24 ------NC
133J1-25
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.6Mar 15/91
Useordisclosureoflnform~tlononthispage(ssublecttotheestnctlonson the tttle page of lhts document
REMOTE
Display Unit No. 4
IOB~ Function Connector Pin Connects To
[
(I) REMOTE LT SENSOR (H) 133J1-26 (22) -------- --------- 130J1-26,
II131 J1-26,
1,132J1-26,115J2-V,
1, C115J2-V,;1 C131J1-26,
;;C130J1-26,REMOTE
,1 LT SENSOR HI(I) REMOTE LT SENSOR (L) -27 (22)-------- --------- ~:~;~-j~,
132J1127;115J2-W,C115J2-W,C131J1-27,C130J1-27,
I
+
LT SENSOR LO
(0) DLS OUT ~~j -28 (22)--9- ------------- 132J1-29(o) -41 (22)-~uL--------------- 132J1-42
SHIELDGND ---(1) ALS (H) -29 (22)--~-
i------------- 132J1-28
(I) REsERv~~) ~$ (22)--g- ------------- 132J1-41
RESERVED -31RESERVED -32
(B) BUS 3 TERM (L) -33 ------NC
RESERVED -34
(B) BUS 2 (H) -35 (22)---;-i 1------------- SEE APPENDIX A
(B) (L) -36 (22)---u- ------------- FIG. A-4(0) DU VALID (GND/OPEN) -37 (22)------------------- 134J1A-30,
C134J1A-30,
i]
APPX B & C(B) BUS 1 (H) -38 (22)--------P- -------- SEE APPENDIX A
(B) (L) -39 (22) ---------- -------- FIG. A-7
(0) REMOTE LT SENSOR GND -40 ------NC(0) REMOTE LT SENSOR PWR (H) -53 ------NC
(o) (L) ~;; ------NC
RESERVED
RESERVED -44
RESERVED -46
RESERVED 133J1-47
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.7Mar 15/91
Use or disclosure of mformahon on thm page IS subpcl to the restrictions on the title page of thts document
Display Unit No. 4
IOB~ Function Connector Piq Connects To
RESERVED 133J1-48
(B) BUS 2 TERM (L) -49 ------NCRESERVED -50RESERVED -51
(B) BUS 1 TERM (L) -52 ------NCRESERVED -55RESERVED -56RESERVED -57
(B) BUS 4 (H) t-58 (22)-----1~I- --------- 133JI-85(B) BUS 4 TERM (L) 4: (22)-----4:+-1--------- 133J1-86(B) BUS4 (L) ------NC
RESERVED -60(B) ~[S~l:E~ TERM (L) -61 ------NC
-62RESERVED -63
(B) UX BUS 1 TERM (L) -64 ------NC(0) DU OVERTEMP (GND/OPEN) -65 (22)------------------- 134J1A-37,
I
C134J1A-37(0) DU WRAPAROUND (H) -66 (22)-----,=1- --------- 134J1B-43,
(ARINC 429) C134J1B-43
(o) DU WRAPAROUND (L) -79 (22) ----- jLJ- --------- 134J1B-44,
(ARINC 429) C134J1B-44
RESERVED -67
RESERVED -68
(B) WX BUS 3 (H) -69 ------NC(B) WX BUS 3 (L) -70 ------NC
RESERVED -71RESERVED -72SPARE -73
(B) WX BUS 2 (H) -74 ------NC(B) WA:;S 2 (L) -75 ------NC
-76(B) WX BUS 1 (H) -77 ------NC(B) [;S~ljE~ (L) -78 ------NC
-80RESERVED -81RESERVED -82
(B) WX BUS 3 TERM (L) -83 ------NCRESERVED 133J1-84
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.8Jun 1/87
UseordisclosureOf mformat)on on this page IS subject to the reslnct(ons on the Wle page of this document
10I3_P_
(o)(o)(1)
(1)
(I)(I)
(P)
(1)(1)(P)(P)(P)
(P)(P)(P)
Function
BURST OUT (H)(L)
PORT SEL A
PORT SEL B
SPAREI.D. #lI.D. #2SPARESPARECHASSIS GNDRESERVEDRESERVEDRESERVEDRESERVEDSOFTWARE ENABLE*SOFTWARE ENABLE*28 V DC28VDC’28 V DC
28 V DC RTN28 V DC RTN28 V DC RTN
Display Unit No. 4
Connector Pin Connects To
133J1-85 (22)--q~l-1------------ 133J1-58
-86 (22)--4~+- ------------ 133J1-45-87 (22)------------------- 132JI-87,
A/C WIRING,
APPX B & C
-88 (22)------------------- 132J1-88,
A/C WIRING,
APPENDIX B & C
-89
-90 (22)------------------- GND}
REF-91 (22)------------------- GND APPX C-92-93-94 (22)------------------- A/C CHASSISGND-95-96-97-98-99 (22}------------------- FLT TEST ONLY-100 {22)------------------ FLT TEST ONLY-101 (NOTE 3)--------------
}
-102 (NOTE 3)-------------- A/C 28 V 13C PWR
-103 (NOTE 3)--------------
}
-104 (NOTE 3)-------------- A/C 28 V DC-105 (NOTE 3)-------------- PWR RTN
133J1-106 (NOTE 3)--------------
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.9Jun 1/87
Use or dmclosure of mformatlon on thm page IS sublect to the restrtcflons on Ihe title page of this document
I
I
IOB_P_
(P)(P)(P)
(P)(P)(P)
(P)
(P)
(P)
(1)
(I)
(1)
(1)
(1)
(o)
(o)
(r)
(1(I(I
(1
(I(1(I
—
Function
28 V DC POWER28 V DC POWER28 V DC POWERRESERVED28 V DC POWER GND28 V DC POWER GND28 V DC POWER GNDRESERVEDSIGNAL GNllSIGNAL GNDSIGNAL GND
KEYING PIN NO. 1KEYING PIN NO. 2KEYING PIN NO. 3KEYING PIN NO. 4KEYING PIN NO. 5RESERVEDRESERVED
Fault Warning Computer No. 1
Connector Pin Connects To
134J1A-1 (NOTE 3)”---------------
-2 (NOTE 3)----------------
}
A/C 28V DC PWR
-3 (NOTE 3)----------------
-5 (N;TE 3)--- --------------6 (NOTE 3)----------------
}A/C 28 V DC
-7 (NOTE 3)--- ------------- POWER GND-8-9 (22)--------------------
}-10 (22)------------------- A/C SIGNALGND-11 (22)--------------------12 (22)-------------------- GND-13 ------NC-14 (22)------------------- GND
-15 ------NC
-16 (22) ------------------- GND-17-18
FGCMAINT TEST (GND/OPEN) -19 (22)-------------------
SPARE -20
AP OFF ANNUN (GND/’OPEN) -21 (22)-------------------
RESERVED -22
WARN RESET* -23 (22)-------------------
CAUTION RESET* -24 (22) -------------------
VOICE RECORDER FAIL -25 (22)-------------------
(OPEN/GND)
STEER BY WIRE FAIL -26 (22) -------------------
(GND/OPEN)
AHRS COOL FAIL* -27 (22)---- ---------------
CAT 2 BENDIX ILS INTALLED* -28 (22)-------------------
DU 3 VALID* -29 (22)-------------------
DU 4 VALID* -30 (22)-------------------
RESERVED -31SPARE -32 -----NCSPARE -33 -----NCDU1 OVERTEMP* 134J1A-34 (22)-------------------
llJ1-58,11J2-58C134J1A-lS
APPENDIX C
APPX DAPPX DA/C WIRING
A/C WIRING
E170J1B-EIAPPX C132J1-37,C134J1A-29133JI-37,C134J1A-30
130J1-65,C134J1A-34
?EF~PPx
c
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.10Apr 15/93
Use or disclosure of information on this page is subject to the restrictions on the title page of this document
IOBL
(I)
(I)
(I)
(I)
(I)
(I)
Eu!Kw!n
DU2 OVERTEMP*
DU3 OVERTEMP*
DU4 OVERTEMP*
DU5 OVERTEMP*
DU6 OVERTEMP*
RESERVEDSG1 REV*
(1) SG2 REV*
(I) SG3 REV*
(I) DU1 REV*
(I) DU2 REV*
Fault Warning Computer No. 1
Con ector Pinn
134J1A-35 (22)-------------------
-36 (22)-------------------
-37 (22)-------------------
-38 (22)-------------------
-39 (22)-------------------
-40-41 (22)-------------------
-42 (22)-------------------
-43 (22)-------------------
-44 (22)-------------------
134J1A-45 (22)-------------------
m nnects TQ
131J1-65,C134J1A-35132J1-65,C134J1A-36133J1-65,C134J1A-37C131J1-65,C134J1A-38C130J1-65,C134J1A-39
C134J1A-41,A/C WIRING,
65J1A-60,
C65J1A-60,
E65J1A-60,
65J1A-59, APPX
BAND C
C134J1A-42,
A/C WIRING,
65J1A-61,
C65J1A-61,
E65J1A-61,
C65J1A-59, APPX
B AND CC134J1A-43,A/C WIRING,65J1A-62,C65J1A-62,E65J1A-62,E65J1A-59,APPX B AND CC134J1A-44,~~;l~I~jNG,
C65Jl~-6~,E65J1A-63,APPX B AND CC134J1A-45,131J1-22, APPXB AND C,A/C WIRING
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.11Mar 15/91
Use or dmclosure of mformat!on on thm page IS suble[ I to the restrictions on the title page of Ihw document.
Fault Warning Computer No. 1
108& EM@li2n &nn~ Connects TQ
(I) DU3 REV* 134J1A-46 (22) ------------------- C134J1A-46,
A/C WIR2NG,
65J1A-64,
C6SJ1A-64,
E65J1A-64,
132J1-22, APPX
BANDC
(I) DU4 REV* -47 (22)------------------- C134J1A-47,A/C WIRING,65JIA-65,C65J1A-65,E65JIA-65,133J1-22, APPXB AND C
(I) DL15REV* -48 (22)------------------- C134J1A-48,C131J1-22,A/C WIRING,APPX 8 AND C
(I) DU6 REV* -49 (22)------------------- C134J1A-49,:&I::NG,
C65Jli-6&E65J1A-66,APPX B AND C
(I) CAT 2 MLS INSTALLED* -50 (22)------------------- APPX C(1) SG1 OVERTEMP* -51 (22)------------------- C134JIA-51,
65J1B-52(I) SG2 OVERTEMP* -52 (22)------------------- C134J1A-52,
C65J3B-52{I) SG3 OVERTEMP* -53 (22)------------------- C134JIA-53,
E6541B-52RESERVED -54SPARE -55
{P) CHASSIS GND -56 (22)------------------- A/C CHASSIS GND(P) CHASSIS GNII -57 (22)------------------- A/C CHASSIS (iNll{P) CHASSIS GND -58 (22)------------------- A/C CHASSIS GND
RESERVED 134JIA-59
4
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.12Mar 15/91
Use or Mclosure ot mlormatton on thm page is subpcl to the restnc!}ons on the Wie page of thm document,
Fault Warning Computer No. 1
IOB& Function Connector Pin Connects To
RESERVED 134J1A-60
t(B) SYS ASCB PRIMARY BUS (H) -61 (22)--9-- -------------
%
(B) SYS ASCB PRIMARY BUS (L) -62 (zz)-!G_1------------- REF. SECT. 3.3
(I) WOW* ~~; (22) ------------------- A/C WOW
RESERVED
(I) FWC ID*1 -65 (22) ------------------- SIG GND
(I) FWC ID *2 -66 ------NC
(I) GEAR DOWN* -67 (22) ------------------- A/c GEAR
DOWN DISCRETE
(I) MEMORY ERASE BUTTON* -68 (22)------------------- APPX D
(I) WINDSHEAR AVAILABLE* -69 (22)------------------- APPX J(I) GND SPOILER NOT ARMED -70 (22)------------------- A/C WIRING(I) EMER BATT 1 FAIL (OPEN/GND)-71 (22)------------------- A/C WIRING(I) EMER BATT 2 FAIL (OPEN/GND)-72 (22)------------------- A/C WIRING(I) AOA HEAT 1 FAIL (OPEN/GND) -73 (22)------------------- A/C WIRING APPX(I) AOAHEAT 2 FAIL (OPEN/GND) -74 (22)------------------- A/CWIRING C F(I) CDU 1 VALID* -75 (22)------------------- 120J1-i,
121J1B-1OO,C134J1A-75
(I) CDU 2 VALID* -76 (22) ------------------- clzOJ1-i,
C121J1B-1OO,C134J1A-76
(I) SPARE CDU VALID* -77 (22)------------------- APPXG(I) SPARE FMS ACTIVE 2* -78 (22) ------------------- APFJX G
(I) SPARE FMS ACTIVE 1* -79 (22) ------------------- APPX G
(I) AP OFF RESET -80 (22)------------------- APPX D(I) MANUAL EXCEEDANCE RECORD* -81 (22)------------------- APPX D(I) CAT 2 NAV INSTALLED* -82 (22)------------------- APPX C(I) AUTOTHROTTLE DISCONNECT -83 (22)------------------- APPX D
(OPEN/GND)(I) BRAKE OVHT (BTMS)* -84 (22)------------------- APPXC
(GND/OPEN) C134J1A-84(I) MAINTENANCE TEST ENABLE* -85 (22)------------------- AppX D
(I) FWC DATA DOWNLOAD 134J1A-86 (22)------------------- AppXD *INITIATE*
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.13Apr 15/93
Use or disclosure of information on this page issubject:o the restrictions on thetitle pageof this document,
Fault Warning Computer No. 1
IOB_P_ Function Connector Pin Connects To
{I) SPARE NZ VALID* 134 JlA1;~ (22) ------------------- APPX &)
RESERVED
RESERVED -89
(I) SPARE FMS INSTALLED* -9o (22)------------------- APPXG(o) AUTOTHROTTLE OFF ANNUN -91 (22)------------------- APPXD
(GND/OPEN)(0) FWC VALID (GND/OPEN) -92 ------NC(0) SPARE -93 ------NC
(o) HEADING MISCOMPARE -94 (22)------------------- STANDBY RMI’S(GND/OPEN)
(0) RAD ALT TEST (GND/OPEN) -95 (22)------------------- 20J1-T(0) B.C. TEST REQUEST -96 (22)------------------- 65J18-1,
(GND/OPEN) C65J1B-1,E65J1B-1
(I) BUS CON VALID NO. 1* -97 (22)------------------- 65J1A-13,
C134J1A-97 REF
(I) BUS CON VALID NO. 2* -98 (22) ------------------- C65J1A-13,APPX
C134J1A-98 C
(1) BUS CON VALID NO. 3* -99 (22)------------------- E65J1B-13, ,C134J1A-99
(I) SYSTEM TEST 1 -100 (22)------------------ TBD(1) SYSTEM TEST 2 -101 (22)------------------ TBD(I) SYSTEM TEST 3 -102 (22)------------------ TBD{o) EMER CHECKLIST SEL -103 (22)------------------ l15J1-p,
(GND/OPEN) Cl15J1-p,C134J1A-103
(0) CHECKLIST INSTALLED -104 (22)------------------ l15J1-q,(GND/OPEN) Cl15J1-q,
C134J1A-104(I) SCROLL-UP* -105 (22)------------------ APPXD(1) SCROLL-DN* 134JIA-106 (22)------------------ APPXD 1
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.14Apr 15/93
Use or disclosure of informationon this page issubject to the restriction sonthe title page of this document.
Fault Warning Computer No. 1IOB&
(I)
(I)
(I)
(I)
(I)
(I)
(I)
(I)
(I)(1)
(I)
(I)
(I)
(I)(I)(I)(I)(I)(I)(I)(I)(I)(I)(1)
Function Connector Pin
L. FUEL VALVE OPEN 134J1B-1 (22)--------------------
(28V/OPEN)
R. FUEL VALVE OPEN -2 (22)--------------------
(28V/OPEN)
L. FUEL VALVE CLOSED -3 (22)--------------------
(28V/OPEN)
R. FUEL VALVE CLOSED -4 (22)--------------------
(28V/OPEN)
COMBINED HYD VALVE OPEN -5 (22) --------------------
(28V/OPEN)
FLT HYD VALVE OPEN -6 (22)--------------------(28V/OPEN)COMBINED HYD VALVE CLOSED -7 (22)--------------------(28V/OPEN)FLT HYD VALVE CLOSED -8 (22)--------------------(28V/OPEN)DC EXT POWER (28V/OPEN) -9 (22)--------------------ACFT CONFIGURATION -lo (22)-------------------(28V/OPEN)RESERVED -11L. OIL FILT. B PASS -12 (22)-------------------(OPEN/28V)R. OIL FILT. B PASS -13 (22)-------------------
(OPEN/28V)
FLIGHT RECORDER FAIL -14 (22) -------------------
(OPEN/28V)
RESERVED -15
INHIBIT SELECT (28V/OPEN) -16 (22) -------------------
LCOWL PRESS LOW (28V/OPEN)-17(22)-------------------R COWL PRESS LOW (28V/OPEN)-18(22)-------------------VHF COM 1 FAIL (OPEN/28V) -19 (22)-------------------VHF COM2 FAIL (OPEN/28V) -20 (22)-------------------VHF COM 3 FAIL (OPEN/28V) -21 (22)-------------------L WING TEMP LOW (OPEN/28V)-22 (22)-------------------R WING TEMP LOW (OPEN/28V) -23 (22)-------------------AUTOPILOT CLUTCH (28V/OPEN)-24(22)-------------------TRIM CLUTCH (28V/OPEN) -25 (22)-------------------RUDDER ACTUATOR (28V/OPEN)-26 (22)-------------------
RESERVED 134J1B-27
Connects
A/C WIRING
A/C WIRING
A/C WIRING
A/C WIRING
A/C WIRING
A/C WIRING
A/C WIRING
A/C WIRING
A/C WIRINGA/C WIRING
A/C WIRING
A/C WIRING
A/C MIRING
A/C WIRINGA/C WIRINGA/C WIRINGA/C WIRINGA/C WIRINGA/C WIRINGA/C WIRINGA/C WIRINGAPPENDIX DAPPENDIX D14P1-A,IOJ1C1OJ1A-58,C134J1B-26,APPENDIX D
REFAPPXc
-58,
Interconnect InformationTable 501 (cent)
22-14-00Page 598.15Mar 15/91
Use or disclosure of mformatton on thm page IS sublet! to the restrictions on the We page of th!s document.
Fault Warning Computer No. 1
IOB~ Function Connector Pin Connects To
(I) APU ALTERNATOR OFF 134J1B-28 (22) ------------------- A/c WIRING I
(28V/OPEN)
RESERVED -29
(I) AUTOTHROTTLE CLUTCH NO. 1 -30 (20) ------------------- lZZJIA-Z3,
(28V/OPEN) C122J1A-23,
L128PI-E,
C134J1B-30 ‘APXRESERVED -31 c
(I) AUTOTHROTTLE CLUTCH NO. 2 -32 (20)------------------- 122J1A-24,(28V/OPEN) C122J1A-24,
R128PI-E,C134J1B-32 ,
SPARE -33(B) DU 1 WRAPAROUND (H)
$
-34 (22)---:-- ----------- 130J]-66,C134J1B-34
(B) DU 1 WRAPAROUND (L) -35 (22)----$- ----------- 130J1-79,C134J1B-35
SPARE -36SPARE -37SPARE -38
(B) DU 2 WRAPAROUND (H)
1
-39 (22)---O-- ----------- 131J1-66,
C134J1B-39(B) DU 2 WRAPAROUND (L) -40 (22)---U-- ----------- 131J1-79,
1
C134J1B-40(B) DU 3 WRAPAROUND (H) -41 (22)---fi-- ----------- 132J1-66,
C134J1B-41(B) DU 3 WRAPAROUND (L) J-42 (22)---1 -- ----------- lSZJ1-T9,
t
C134J1B-42(B) DU 4 WRAPAROUND (H) -43 (22) ---R-- ----------- lSSJ1-GG,
C134J1B-43(B) DU 4 WRAPAROUND (L) -44 (22)---:-- ----------- 133J1-79,
C134J1B-44SPARE -45
SPARE -46
SPARE -47
(B) DU 5 WRAPAROUND (H)
1
-48 (22)---R-- ----------- ClslJ1-(jG,
C134J1B-48(B) DU 5 WRAPAROUND (L) -49 (22)---!!- ----------- C131J1-79,
t
C134JIB-49(B) IRS #2 HIGH SPEED (H) -50 (22)---~- ----------- C170J1B-H14
ARINC 429(B) IRS #2 HIGH SPEED (L)134J1B-51 (22)--&- ----------- C170J18-H15
ARINC 429
Interconnect InformationTable 501 (cent) 22-14-00
Page 598,16Apr 15/93
Use or disclosureof information on this page issubject to the res’rictionson the title page of this document
Fault Warning Computer No. 1
IOBD
(B)
(B)
(B)
(B)
(B)
(B)
(B)
Function Connector Pin Connects To
RESERVED 134J1B-52RESERVED -53RESERVED -54RESERVED -55RESERVED -56RESERVED -57SPARE -58SPARE -59SPARE -60SYS ASCB (H)
$
-61 (22) --n-- ------------ REF
SECONDARY BUS (L) 1-62 (22)--.!!-------------- SECT. 3.3SPARE -63SPARE -64SPARE -65SPARE -66SPARE -67RESERVED -68RESERVED -69RESERVED -70RESERVED -71RESERVED -72RESERVED -73RESERVED -74RESERVED -75RESERVED -76DU 6 WRAPAROUND (H)
i
-77 (22)--fl-- ------------ C130J1-66,C134J1B-77
DU 6 WRAPAROUND (L) -78 (22)----- ------------ C130J1-79,
$
C134J1B-78IRS #1 HIGH SPEED (H) -79 (22)--fi-- ------------ 170J1B-H14ARINC 429IRS #1 HIGH SPEED (L) -80 (22)--{~-- ------------ 170J1B-H15ARINC 429IRS #3 HIGH SPEED (H)
t
-81 (22)--fi-- ------------ E170J1B-H14ARINC 429IRS #3 HIGH SPEED (L) -82 (22)--s- ------------ E170J1B-H15ARINC 429RESERVED -83RESERVED -84RESERVED -85RESERVED 134J1B-86
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.17Apr 15/93
Use or disclosure of information on this page is subject to the restrictions on the title page of this document
Fault Warning Computer No. 1
10B~ Function Connector Pin ~
(0) RED AURAL (28V/OPEN) 134JIB-87 [22}------------------- A/C WIRING ‘(0) AMBER AURAL (28V/OPEN) -88 (22)------------------- A/C WIRING(0) BLUE AURAL (28V/OPEN) -89 (22)------------------- A/C WIRING(o) INHIBIT OUTPUT -90 (22)------------------- A/CWIRING
(28v/oPEN)(0) A/P DISC TEST -91 (22) ------------------- A/C WIRING
(28V/OPEN)
(0) GEAR HORN INHIBIT -92 (22) ------------------- A/C MIRING(28V/OPEN)
(0) EICAS FAIL (OPEN/28V) -93 (22)------------------- A/C WIRING(0) DOWNLOAD IN PROGRESS -94 (22)------------------- APPXD
(28V/OPEN)(0) ERASE IN PROGRESS -95 (22)------------------- APPXD REF
(28V/OPEN) APPX(0) AUTOTHROTTLE OFF HORN -96 (22)------------------- APPXD c
(28V/OPEN)
(0) AP OFF HORN (28V/OPEN) -97 (22)------------------- APPXD
(0) MASTER WARNING ANNUN -98 {22) ------------------- APPENDIX D
(28V/OPEN)
(0) MASTER CAUTION ANNUN -99 (22) ------------------- APPENDIX D J
(28V/OPEN)
(0) VALT ALERT HORN -100 (22)------------------ A/CWIRING,
+
C134JIB”1OO
(0) DATA ON LOAD RS232 TXD -101 (22)-----fi---------- APPXD(0) DATA DN LOAD RS232 RXD -102 (22)----v------------ APPX D(0) DATA DN LOAD RS232 RTS -103 ------NC(0) DATA DN LOAD RS232 CTS -104 ------NC(0) DAIA;EDNLOAD RS232 DTR -105 ------NC
134J1B-106
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.18Mar 15/91
Use or dmclosure of information on thm page w sublecf 10 the r~stnctlons on the title page of fhm doc~meot
IlisplayBrightness Panel
IOB& Function connector Pin @ nnects To
(I) OUI DIMMING (H) ------------- 130J1-1(o) (w) ------------- 130J1-14(1) (L) ------------- 130J1-13(I) DU2 DIMMING (H) ------------- 131J1-1(o) (w) ------------- 131J1-14(1) (L) ------------- 131J1-13(1) DU3 OIMMING (H) ------------- 132J1-1(o) (w) ------------- 132J1-14(1) (L) ------------- 132J1-13(I) DU4 DIMMING (H) ------------- 133J1-1(o) (M) ------------- 133J1-14(I) (L) ------------- 133J1-13(1) DU5 OIMMING (H) ------------- C131J1-1(o) (w) ------------- C131J1-14(I) (L) ------------- C131J1-13(I) DU6 DIMMING (H) ------------- C130J1-1(o) (M) ------------- C130J1-14(I) (L) ------------- C130J1-13(P) PANEL LIGHTING (5V) HI ------------ A/C 5V LIGHTING
(P) LIGHTING RTN ------------ A/~ LIGHTING RTN
(P) ~;;i;IS GND -21 (22)------------------- A/C CHASSIS GNDd 135J1-22
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.19Mar 15/91
Use or disclosure of mforrnafton on lhm page IS sublecl to the restrictions on the Me page of thm document
Data Acquisition Unit No. 1
(B)
(B)
(I)(I)
(I)
(I)(I)(I)
(1)(I)
(I)(I)
(I)(I)(I)(I)(I)(1)(I)(1)(I)(I)
(I)(1)
Function Connector Pin Connects To
RESERVED 136J1A-1SPARE -2SPARE -3SYSASCB PRIMARY BUS (H) i-4 (22) --P--- ------------ REF SECTION 3.3
SPARE -5
~~;R~SCB PRIMARY BUS (L) i-6 (22)------ ------------ REFLECTION 3.3
-7
~~;N~R;;; RATIO (H) -8 (22)--m--2
}
------------ A/C LEFT ENGINE(L) -9 (22)--$- ------------ PRESSURE RATIO
TRANSMITTERDAU IDENTAOO -lo ------NC REF APPENDIX CRESERVEDFUEL FLOW (IMPELLER)
‘~ [;;~,~~~~~~~~~~~~~~}~ {~~:~~~!+TER
-12 (22)--7--(COMMON)(DRUM)
RESERVED -15HIGH PRESS (H)
t-16 (22)--:-- ------------ A/CLEFTHIGH
COMPRESSOR TACH (L)}
-17 (22)------ ------------ pRESSURECoM-PRESSOR TACH
i
TRANSMITTERLOW PRESS (H) -18 (22)---O-- ------------ A/C LEFT LOW
COMPRESSOR TACH (L) -19 (22)--JJ--
}
------------ PRESSURECOM-
PRESSOR TACH
TRANSMITTER
AC VOLTS/FREQ (H) -20 ------NC
(L) -21 ------NC
ESS/AUX AC (H) -22 ------NC
VOLTS/FREQ (L) -23 ------NC
(A) -24 ------NC
AC % LOAD (B) -25 ------NC
(c) -26 ------NC
(N) -27 ------NC
COMB HYDRAULIC (H) -28 (22)-------~-$--------]
TO FLT HYD PRESSPRESS (L) -29 (22)------Q --------- TRANSMITTERSPARE -30SPARE -31~~;~;TY HYD (H) -32 (22)-------~-
$
}
-------- TO UTILITY HYD(L) 136J1A-33 (22)------J~ --------- PRESS
TRANSMITTER
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.20Mar 15/91
Use or dmclosure of Information on thm page IS subjecf to the restrictions on the title page of Ihts document.
Data Acquisition Unit No. 1
IOB~ Function Connector Pin Connects To
SPARE 136J1A-34
(I)(I)
(I)(I)
(1)(I)
(1)(I)
(I)(1)
(1)
(i)
(I)
(1)
(I)(I)(I)(I)(1)(I)
SPARE -35APPLIED BRAKE [~] -36 (22)_;i-
$------------ TO APPLIED BRAKE
PRESS 1-37 (22)---U -------------- PRESSTRANSMITTER
ENGINE OIL (H))
-38 (22)---f\:::::::::::::: j:E::GINE 011-PRESS (L) -39 (22)---~-
TRANSMITTERLP TURBINE (H) -40 (22) ---;{ $-----------) TO FORE TURBINE
VIBRATION INDICATION (L) -41 (22) ---=-------------- VIBRATION
INDICATION
t
TRANSMITTER
HP TURBINE (H) -42 (22)----;- ----------- TO AFT TURBINE1VIBRATION INDICATION (L) -43 (22)----U-------------- VIBRATION
INDICATION
t
TRANSMITTERFUEL QUANTITY (H) -44 (22)----C- ----------- TO LEFT FUEL
(L) 1-45 (22)----U ------------- QUANITY
1}
TRANSMITTERBLEED AIR PRESS (H) -46 (22)----i~- ----------- TO LEFT BLEED
AIR(L) -47 (22)----!:1-------------MANIFOLD PRESS
TRANSMITTERSPARE -48SPARE -49
(H)
t}
-50 (22)----i~------------- C1OJ2A-36,RADIO ALTIMETER 1OJ2B-26, 20J1-W
(L) -51 (22)----:’------------- C1OJ2A-37,1OJ2B-27,20J1-N, 20J1-E
BATTERY AMPS (H) -52 ------NC(L) -53 ------NC
BATTERY VOLTS (H) -54 ------NC(L) -55 ------NC
COMB HYD QTY (H) -56 (22)------,~-$---------)
TO FLT HYD QUAN-
(L) -57 (22)------U- --------- TITY TRANSMITTER
SPARE -58
SPARE 136J1A-59
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.21Apr 15/93
Use or disclosure of information on this page is subject .O the restrictions on the title page of this document
Data Acquisition Unit No. 1
IOB-P_
(I)(I)(I)(I)
(I)(I)(I)
(I)
(1)
(1)(I)
(I)(I)(I)(I)
(I)(I)
Function Connector Pin Connects To
~~~ f;ti~UST (H)+
136J1A-60 (22)----8-- ----------- TO APU GAS TEMP(L)
1
-61 (22)----K- ----------- TRANSMITTERAPU RPM (H)
$-62 (22)----r~- ----------- TO APU TURBINE
(L) -63 (22)----u- ----------- SPEED
$
TRANSMITTERENG FUEL TEMP (H) -64 (22)----;T- ----------- TO ENG FUEL TEMP
(L) -65 (22)----v- ----------- TRANSMITTER
FUEL TANK TEMP (H)
tl
-66 (22)----~r- ----------- TO FUEL TANK
TEMP
(L) -67 (22) ------ ----------- TRANSMITTER
SPARE -68
SPARE -69
SPARE -70
SPARE -71
SPARE -72
SPARE -73
RESERVED -74
RESERVED -75
DAU IDENTAO1 -76 (22) ------------------- SIG GND
i
REF APPENDIX CENG OIL TEMP (H) -77 (22)----fi- ----------- TO LEFT ENG
(L) )~;~ (22)----V- ----------- OILTEMPSPARESPARE -80SPARE -81SPARE -82DC VOLTS (H) -83 ------NC
(L) -84 ------NCESS DC VOLTS (H) -85 ------NC
(L) -86 ------NCSPARE -87SPARE -88SPARE -89SPARE -90DC % LOAD (H) -91 ------NC
(L) -92 ------NCSPARE -93SPARE -94RESERVED 136J1A-95
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.22Mar 15/91
Use or disclosure of mformatlon on this page m subject to the r?strlctlons on the title psge of this document.
Data Acquisition Unit No. 1
IOB~ Function Connector Pin Connects To
RESERVED 136J1A-96(P) ~l+;;~IS GND -97 (22)------------------- A/CCHASSISGND
-98
RESERVED -99
(I) SIGNAL GND -100 (22)------------------ A/CSIGNALGNDSPARE -101RESERVED -102
(P) PWR GND -103 (22) ------------------ A/C PWRGND
SPARE -104
RESERVED -105
(PO 28 V DC PWR 136J1A-106 (22)--------:--------- A/C 28VDC PWR
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.23Jun 1/87
Use or disclosure of Intormatton on thm page IS subje,:t to the reslnctlons on the Mle page of this document
Data Acquisition Unit No. 1
IOBP Function
(I)(1)
(B)
(B)
(I)
(I)
.(1)
(I)
(I)
(1)
(1)
(I)
(I)
(1)
(1)
(I)
(1)
(I)
Connector Pin Connects To
TURBINE GAS (ALUMEL) 136J1B-1 ( 22) -------------------- LEFT TURBINE GAS
TEMP (CHROMEL)}
-2 ( 22)-------------------- TEMP TRANSMITTER
AND ENG STBYINSTRUMENTS
SPARE4SYS A’jCB‘jECONDARY BUS (H) ~~ (22)--77-,--------------
)
REF SECTION 3.3SPARESYS r@SCBSECONDARY BUS (L) ~~ (22)--’V~----------------SPARE -7RESERVED -8L. REV UNLOCK (28V/OPEN) -9 (22)-------------------- ~[~F~~RUST REV
L. FUEL PRESS LOW -10 (22)------------------- A/C FUEL PRESS(28V/OPEN)L. FUEL LOW LEVEL
LOW DISCRETE-11 (22)------------------- A/C L. FUEL LOU
(28V/OpEN) LEVEL DISCRETEL. pYLON HOT (28v/OpEN) -12 (22)------------------- A/C L. PYLON HOT
DISCRETEL. ENGINE HOT (28V/OPEN) -13 (22)------------------- A/C L. ENGINE
HOT DISCRETEL. OIL PRESS LOW -14 (22)------------------- A/C L. OIL PRESS(28V/OPEN) LOW DISCRETECALL (28V/OPEN) -15 (22)------------------- A/C CALL
DISCRETE
L. IGNITION 1 (28v/OpEN) -16 (22)------------------- A/C L. IGNITIONDISCRETE
L. WING ANTI-ICE ON -17 (22)------------------- A/C L. WING WARM
(28v/oPEN) DISCRETE
L. COWL ANTI-ICE ON -18 (22)------------------- A/C L. ENG
(28 V/OPEN) A/I ON DISCRETE
RAD ALT 1 FAIL (oPEN/28v) -19 (22)------------------- 1oJ2B-28,
C1OJ2A-38,
20J1-Y
cABIN PRESS LOW (28v/OPEN) -20 (22)------------------- A/CCABIN PRESS
LOW DISCRETEL. IGNITION 2 (28v/OpEN) -21 (22)------------------- A/C L.IGNITION
2, DISCRETECOMBINED HYD HOT 136J1B-22 (22)------------------- A/C COMB HYD HOT
(28v/OPEN) DISCRETE
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.24Feb 1/88
Use or disclosure of mformatlon on Ihls page m subject to the rejtrlctlons on the title page of this document
I
Data Acquisition Unit No. 1
10B-P_ ~ Connector Pin Connects To
(I) COMBINED HYD SYS 136J1B-23 (22)------------------- A/C COMB HYD SYSFAIL (28V/OPEN) DISCRETE
(1) L. FUEL FILTER FAIL -24 (22)------------------- A/C L. FUEL(28V/OPEN) FILTER FAIL
DISCRETE(1) L. AIL HYD SHUTOFF -25 (22)------------------- A/ L. AILHYD
(28V/OPEN) SHUTOFF DISCRETE(I) L. BLEED HOT -26 (22)------------------- A/CL. BLEED HOT
(28V/OPEN) DISCRETE
(I) L. BLEED PRESS HIGH -27 (22)------------------- A/C L. BLEED
(28V/OPEN) PRESS HIGH
DISCRETE
(I) L. START VALVE OPEN -28 (22)------------------- A/C L. START
(28V/OPEN) VALVE OPENDISCRETE
(I) L. ALTERNATOR HOT -29 (22)------------------- A/C L. ALTHOT
(28V/OPEN) DISCRETE
(1) L. CONVERTER HOT -30 (22)------------------- A/C L. CONVHOT(28V/OPEN) DISCRETE
(I) SMOKE DETECT -31 (22)------------------- A/C SMC)KEDETECT
(28V/OPEN) DISCRETE(I) L. CONV FAN FAIL -32 (22) ------------------- A/C L. CONV FAN
(28V/OPEN) FAIL DISCRETE
(I) ELEV. COMB HYD OFF -33 (22)------------------- A/C ELEVCC)MB
(28V/OPEN) HYDOFF DISCRETE(I) APU ALTERNATOR HOT -34 (22)------------------- A/CAPIJALTHoT
(28V/OPEN) DISCRETE(1) L. COOL TURB HOT -35 (22)------------------- A/C L. C()()LTIJRB
(28V/OPEN) HOT DISCRETE
(I) L. AC PWR FAIL -36 (22)------------------- A/C L. AC PWR
(28V/OPEN) FAIL DISCRETE
(1) L. DC PWR FAIL -37 (22)------------------- A/C L. DC PWR
(28V/OPEN) FAIL DISCRETE
(I) L. STALL BARR FAIL -38 (22)------------------- A/C L. STALL
(OPEN/28V) BARR FAIL
DISCRETE
(1) L. EMER BATT DISCHG -39 (22)------------------- A/C L. EMERBATT
(28V/OPEN) DISCHG DISCRETE
(I) L. WING HOT 136J1B-40 (22)------------------- A/C L. WING HOT
(28V/OPEN) DISCRETE
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.25Jun 1/87
Use or disclosure of InformalIon on Ihts page IS subyw to the restncuons on the Mle page of thm document
Data Acquisition Unit No. 1
IOB~ Function Connector Pin Connects To
(I) L. MAIN FUEL FAIL 136J1B-41 (22)------------------- A/C L. MAIN FUEL
(28v/oPEN) FAIL DISCRETE
(I) L. ALT FUEL FAIL -42 (22)------------------- A/C L. ALTFUEL
(28V/OPEN) FAIL DISCRETE
RESERVED -43
(I) STALL BARR 1 -44 (22)------------------- A/C STALL BARR 1
(28V/OPEN) DISCRETE
(I) CABIN OXYGEN ON -45 (22)------------------- A/C CABIN OXYON
(28V/OPEN) DISCRETE
(I) AUX AC PWR FAIL -46 (22)------------------- A/CAUXAC PWR
(28V/OPEN) FAIL DISCRETE
(I) APU FIRE -47 (22)------------------- A/CAPU FIRE
(28V/OPEN) DISCRETE
(1) AFT EQUIP HOT -48 (22)------------------- A/CAFTEQUIP
(28V/OPEN) HOT DISCRETE
SPARE -49
(I) AUX HYD HOT -50 (22) ------------------- A/C AUX HYD HOT(28V/OPEN) DISCRETE
(1) ISOLATION VALVE -51 (22)------------------- A/C ISOLATION(28V/OPEN) VALVE DISCRETE
(I) EX BATT SW ON -52 (22)------------------- A/C EX BATT SW(28V/OPEN) ON DISCRETE
(I) RUDDER COMB HYD OFF -53 (22)------------------- A/C RUDD COMB(28V/OPEN) HYDOFF DISCRETE
(I) SINGLE RUDDER LIMIT -54 (22)------------------- A/C SINGLE RUDD(28V/OPEN) LIMIT DISCRETE
(I) STAB/FLAP -55 (22)------------------- A/C STAB/FLAP(28V/OPEN) DISCRETE
(I) EPMP BATT SW OFF -56 (22)------------------- A/C EPMPBATTSW
(28V/OPEN) OFF DISCRETE
(I) STALL BARRIER OFF -57 (22)------------------- A/C STALL
(28V/OPEN) BARRIER
OFF DISCRETE
(I) TRANSFORMER RECTIFIER -58 (22) ------------------- A/C TRU FAILFAIL (28V/OPEN) DISCRETE
(I) EPMP PS FAIL (28V/OPEN) -59 (22)------------------- A/C EPMP PS FAILDISCRETE
(I) UTILITY HYD OFF 136J1B-60 (22)------------------- A/CUTILITYHYD(28V/OPEN) OFF DISCRETE
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.26Mar 15/91
Use or disclosure of mlormallon on Ihm page IS sub)ect to the rf stnctlons on the title page of Ihls documant.
IOB&
(1)
(I)
(1)
(1)(s)
(1)
{1)
(I)
(1)
(1)
{1)
(I)
(I)
(I)(1)
(1)
(1)
(1)
Gata Acquisition Unit No. 1
~ Connector Pin Connects To
LP/HPSYNC SELECT 136J1B-61 (22)------------------- A/CLP/HPSYNCSELECT DISCRETE(OPEN/28V)
SPARESPAREL. COWL ANTI-ICE OVHT(28V/OPEN)
SPAREL. ENGINE FIRE*
DAU IDENT BOO‘FUELXFLOW OPEN*
ENG FIRE LOOP ALERT*
CABIN DFRN 1 ( >9.8)*(RED ANNUN)L. PITOT HT FAIL*
L. ALTERNATOR BEARINGFAIL*
BRAKE MAINT REQ’D(OPEN/GND)BRAKE FAIL(OPEN/GND)APU MASTER WARN*
STBY PITOT HT FAIL*
MAINT TEST ENABLE*DU FAN 1 FAIL (OPEN/GND)
DAU IDENT BO1
BATT CHARGER 1 FAIL/OPENIGND)
-62-63-64 (22)-------------------
-65-66 (22)-------------------
-67 ------NC-68 (22)-------------------
-69 (22)-------------------
-70 (22)-------------------
-71 (22)-------------------
-72 (22)-------------------
-73 (22)-------------------
-74 (22)-------------------
-75 (22)-------------------
-76 (22)-------------------
-77 (22)--------------------78 (22)-------------------
-79 (22)-------------------
-80 (22)-------------------
A/C L. COWLANTI-ICEOVHT DISCRETE
A/C L. ENGINEFIRE DISCRETEREF APPENDIX CA/C FUEL XFLOUOPEN DISCRETEA/C ENG FIREl-OOPALERTDISCRETEA/C CABIN DFRN 1DISCRETEA/C L. PITOT HTFAIL DISCRETEA/C L. ALTBEARING FAILDISCRETEA/C BRAKE SYSDISCRETEA/C BRAKE FAILDISCRETEA/C APU MASTERWARN DISCRETEA/C STBY PITOTHT FAIL DISCRETEAPPENDIX DDU FAN 1 FAILOISCRETESIG GNDREF APPENDIX CA/C BATT CHARGER1 DISCRETE
136J1B-81 (22)------------------- A/C-NUTCRACKERDISCRETE
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.27Jun 1/87
Use or disclosure of mformallon on Ihm page IS suble( t to the restrictions on lhe t!lle page of this document
Data Acquisition Unit No. 1
IOB& Function Connector Pin Connects To
RESERVED 136J1B-82SPARE -83SPARE -84SPARE -85SPARE -86SPARE -87SPARE -88SPARE -89SPARE -90SPARE -91SPARE -92SPARE -93RESERVED -94RESERVED -95RESERVED -96RESERVED , -97SPARE -98RESERVED -99
(I) ~~j[;L GND -1oo (22)------------------ A/C SIGNALGND-101
RESERVED -102(P) POWER GND -103 (22)------------------ A/C PWRGND
SPARE -104RESERVED -105
(P) 28 V DC PWR 136J1B-106 (22)------------------ A/C 28 V DC pWR
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.28Jun 1/87
Use or disclosure of Information on thts page IS subject 10 the r, stnctlons on the Mle page of this document
Data Acquisition Unit No. 2
IOBP
(B)
(B)
(I)(I)
(I)
(I)(I)(I)
(I)(I)
(I)(I)
(I)(I)(I)(I)(I)(I)(I)(I)(I)
(I)
Function Connector Pin Connects To
RESERVED 137J1A-1SPARESPARE ::SYS ASCB PRIMARY BUS (H) -4 (22)-----+’----------
I
REF SECTION 3.3SPARE -5SYS ASCB PRIMARY BUS (L)
[1-6 (22)-------- ---------- REF SECTION 3.3
SPARE -7;~;N;R;;; RATIO (H) ?$-8 (22)------,-- ---------- A/C RIGHT ENGINE
(L) )-9 (22)------G------------ PRESSURE RATIOTRANSMITTER
DAU IDENT AOO
RESERVEDFUEL FLOW (IMPELLER)
(COMMON)(DRUM)
RESERVEDHIGH PRESS (H)COMPRESSOR TACH (L)
LOW PRESS (H)COMPRESSOR TACH (L)
AC VOLTS/FREQ [~]
AUX AC (H)VOLTS/FREQ (L)
(A)AC % LOAD (B)
(c)(N)
FLT HYDRAULIC (H)
PRESS (L)SPARE
-10 (22)------------------- SIGGNDREF APPENDIX C
-11-12 (22)-----q-
+}
--------- A/C RIGHT FUEL-13 (22)-----’,-1- --------- FLOW TRANSMITTER-14 (22)-----U’------------15
t---------]-16 (22)-----19-- A/C RIGHT HIGH-17 (22)-----V- --------- PRESSURE COM-
PRESSOR TACH
t---------]
TRANSMITTER-18 (22)------’3-- A/C RIGHT LOW-19 (22)-----++- --------- PRESSURECOM-
PRESSOR TACHTRANSMITTER
-20 ------NC-21 ------NC-22 ------NC-23 ------NC-24 ------NC-25 ------NC-26 ------NC-27 ------NC
i}
-28 (22)-----2- ---------- TO COMBHYDPRESS
-29 (22)----#-- --------- TRANSMITTER-30
SPARE -31(I) AUX HYD PRESS (H) -32 (22)-----@--
$)--------- TO AUXHYD PRESS
(I) (L) 137J1A-33 (22)----j~------------- TRANSMITTER
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.29Mar 15/91
Use or disclosure Of Inforrnallon on this page IS subjet t to the restrictions on the title page of this document
Data Acquisition Unit No. 2
(I)(I)
(I)(1)
(I)
(I)
(I)(I)
(I)(I)
(I)(1)
(I)
(I)
(I)(I)(I)(I)(1)(I)
Function Connector Pin Connects To
SPARE 137J1A-34SPARE -35APPLIED BRAKE PRESS (H)
i-36 (22)----~r - ----------- TO APPLIED BRAKE
(L) -37 (22)----~- 1----------- PRESS
t
TRANSMITTERENGINE OIL (H) -38 (22)----R-- ----------- TO ENGINE OILPRESS (L) -39 (22)------- 1----------- PRESS
TRANSMITTER
LP TURBINE
t}
(H) -40 (22)----=- ----------- ;OF;[~II
VIBRATION INDICATION (L) -41 (22)---JU- ----------- VIBRATIONINDICATION
i
TRANSMITTERHP TURBINE (H) -42 (22)----~i- ----------- TO AFT TURBINE
1VIBRATION INDICATION (L) -43 (22)----u- ----------- vIBRATIONINDICATION
FUEL QUANTITY (H) -44 (22)(L) ---+’,+----------] ‘N;gi;T:[EL-45 (22)----G-- ----------- QUANITY
i
TRANSMITTERBLEED AIR PRESS (H) -46 (22)----fi- ----------- TO RIGHT BLEED
(L) -47 (22)----’+ 1----------- AIR MANIFOLDPRESSTRANSMITTER
SPARE -48SPARE -49
(H) -50 (22)-----fi-t----------- 1OJ2A-36,
1
C20J1-W,RADIO ALTIMETER
II1
C1OJ2B-26(L) -51 (22)----JJ------------- 1OJ2A-37,
C20J1-N,C20J1-E,C1OJ2B-27
BATTERY AMPS (H) -52 ------NC(L) -53 ------NC
BATTERY VOLTS (H) -54 ------NC(L) -55 ------NC
FLT HYD QTY (H) -56 (22)------5-\]--------- TO FLT HYD QUAN-
(L) -57 (22)------!J- --------- TITY TRANSMITTERSPARE -58SPARE 137J1A-59
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.30Apr 15/93
Use or disclosure of information on this page is subject to the rest ictions on the title page of this document.
Data Acquisition Unit No. 2
IOB~ Function Connector Pin Connects To
RESERVED 137J1A-60RESERVED -61RESERVED -62RESERVED -63
(1) ENG FUEL TEMP (H){]
-64 (22)------O- --------- TO ENG FUEL TEMP(I) (L) -65 (22)------U- --------- TRANSMITTER
SPARE -66SPARE -67SPARE -68SPARE -69
(I)
[
(A) -70 ------NC(I) (B) -71 ------NC(I) AUX AC % LOAD (c) -72 ------NC(1) (N) -73 ------NC
RESERVED -74RESERVED -75
(I) DAU IDENT AO1 -76 ------NC REF APPENDIX C(I) ENG OIL TEMP (H) ?~-77 (22)-------
1--------- TO RIGHTENG
(I) (L) -78 (22)-----+ --------- OILTEMPSPARE -79SPARE -80SPARE -81SPARE -82
(I) DC VOLTS (H) -83 ------NC(I) (L) -84 ------NC(I) AUX DC VOLTS (H) -85 ------NC(I) (L) -86 ------NC
SPARE -87SPARE -88SPARE -89SPARE -90
(I) DC % LOAD (H) -91 ------NC(I) (L) -92 ------NC(I) AUX DC % LOAD (H) -93 ------NC(I) (L) -94 ------NC
RESERVED -95RESERVED 137J1A-96
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.31Mar 15/91
Use or disclosure of mformatlon on th!s page IS subject to the restncttons on the title page of this document.
106& Function
(P) CHASSIS GNDSPARERESERVED
(]) SIGNAL GNDSPARERESERVED
(P) PWR GNDSPARERESERVED
(P) 28 V DC PWR
Data Acquisition lJnit No. 2
Connector Pin Connects=
137J1A14: (22)------------------- A/C CHASSISGND
-99-100 (22)------------------ A/CSIGNALGND-101-102-103 (22)------------------ A/C PWRGND-104-105
i37JlA-106 (22)------------------ A/C 28V DC PWR
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.32Jun 1/87
Use or disclosure of Information on this page IS sub)ect to the r ?strlctlons on the t!tle page of thm document
Data Acquisition Unit No. 2
IOBP-
(I)
(I)
(B)
(B)
(I)
(I)
(I)
(I)
(I)
(I)
(I)
(I)
(I)
(I)
(1)
(Ij
(I)
(I)
Function Connector Pin
TURBINE GAS (ALUMEL) 137J1B-1 (22)--------------------
TEMP (CHROMEL) -2 (22)--------------------
SPARESYS ASCB SECONDARY BUSSPARESYS ASCB SECONDARY BUSSPARERESERVEDR. THRUST REV UNLOCK(28V/OPEN)
I(H) ~~ (22)---;;- -
{L) -Ej(22)--!+ --1-8-9 (22)--------
- - -- - - - -- ---
----- ------ -
------- -----
R. FUEL PRESS LOW -lo (22)-------------------(28V/OPEN)
R. FUEL LOW LEVEL -11 (22)-------------------(28V/OPEN)R. PYLON HOT -12 922)-------------------(28V/OPEN)R. ENGINE HOT -13 (22)-------------------(28V/OPEN)R. OIL PRESS LOW -14 (22)-------------------(28V/OPEN)CALL (28V/OPEN) -15 (22)-------------------
R. IGNITION 1 -16 (22)-------------------(28V/OPEN)R. WING ANTI-ICEON -17 (22)-------------------(28V/OPEN)R. COWL ANTI-ICE ON -18 (22)-------------------(28V/OPEN)RAD ALT 2 FAIL -19 (22)-------------------(OPEN/28V)
MAIN CABIN DOORS UNLOCKED -20 (22)-------------------(28V/OPEN)R. IGNITION 2 -21 (22)-------------------(28V/OPEN)FLT HYD HOT 137J1B-22 (22)-------------------(28V/OPEN)
Connects To
RIGHT TURBINEGAS TEMPTRANSMITTERAND ENG STBYINSTRUMENTS
REF SECTION 3.3
REF SECTION 3.3
A/C R. THRUSTREV UNLOCKDISCRETEA/C R. FUELPRESSLOW DISCRETEA/C R. FUEL LOWLEVEL DISCRETEA/C R. PYLON HOTDISCRETEA/C R. ENGINEHOT DISCRETEA/C R. OIL PREssLOW DISCRETEA/C CALLDISCRETEA/C R.IGNITION 1DISCRETEA/C R. WINGA/IDISCRETEA/C R. COWLA/IDISCRETE1OJ2A-38,C1OJ2B-28,C20J1-YA/C MAIN CABINDOORS DISCRETEA/C R.IGNITION 2DISCRETEA/C FLT HYD HOTDISCRETE
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.33Jun 1/87
Use or disclosure of mformatlon on thm page IS sublet 10 the restrictions on the tnle page of lhls document
.- . . MAINTENANCE
IOB~
(1)
(1)
(1)
(1)
(1)
(1)
(1)
(1)
(1)
(1)
(1)
(1)
(1)
(1)
(1)
(1)
(1)
Honeywell g/$~$f~M;-
Data Acquisition Unit No. 2
!3!@m!n
FLT HYD SYS FAIL(28V/OPEN)R. FUEL FILTER FAIL(28V/OPEN)
R. AIL HYD SHUTOFF(28V/OPEN)R. BLEED HOT(28V/OPEN)R. BLEED PRESS HIGH(28V/OPEN)
R. START VALVE OPEN(28V/OPEN)
R. ALTERNATOR HOT(28V/OPEN)R. CONVERTER HOT(28V/OPEN)FLAME DETECT(28V/OPEN)R. CONV FAN FAIL(28V/OPEN)ELEV. FLTHYD OFF(28V/OPEN)RESERVEDR. COOL TURB HOT(28V/OPEN)R. AC PWR FAIL(28V/OPEN)R. DC PWRFAIL(28v/oPEN)R. STALL BARR FAIL(OPEN/28V)
R. EMER BATT DISCHG(28V/OPEN)R. WING HOT(28V/OPEN)
Connector Pin
137J1B-23 (22)-------------------
-24 (22)-------------------
-25 (22)-------------------
-26 (22)-------------------
-27 (22)-------------------
-28 (22)-------------------
-29 (22)-------------------
-30 (22)-------------------
-31 (22)-------------------
-32 (22)-------------------
-33 (22)-------------------
-34-35 (22)-------------------
-36 (22)-------------------
-37 (22)----------”--------
-38 (22)-------------------
-39 (22)-------------------
137J1B-40 (22)-------------------
Connects To
A/C FLT liYDSYSFAIL DISCRETEA/C R. FUELFILTER FAILDISCRETEA/R. AILHYDSHUTOFF DISCRETEA/C R. BLEED HOTDISCRETEA/C R. BLEEDPRESS HIGHDISCRETEA/C R. STARTVALVE OPENDISCRETEA/C R. ALT HOTDISCRETEA/C R. CONV HOTDISCRETEA/C FLAME DETECTDISCRETEA/C R. CONV FANFAIL DISCRETEA/C ELEV FLT HYDOFF DISCRETE
A/C R. COOL TURBHOT DISCRETEA/C R. AC P#lRFAIL DISCRETEA/C R. DC PWRFAIL DISCRETEA/t R. STALLBARR FAILDISCRETEA/c R; EMER BATTDISCHG DISCRETEA/C MIRING R.WING HOTDISCRETE
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.34Mar 15/91
Use or disclosure of mforrnatlon on thm page IS subject to the restrctlons on the title page of thts document.
Data Acquisition Unit No. 2
IOBP Function Connector Pin Connects To
(I) R. MAIN FUEL FAIL 137J1B-41 (22)------------------- A/C WIRING R.(28v/OPEN) MAIN FUEL FAIL
DISCRETE(I) R. ALT FUEL FAIL -42 (22)------------------- A/C R. Al? FUEL
(28V/OPEN) FAIL DISCRETERESERVED -43
(1) STALL BARR 2 -44 (22)------------------- A/C STALL BARR 2(28V/OPEN) DISCRETE
(1) CABIN PRESS MAN -45 (22)------------------- A/C CABIN PRESS(28v/OpEN) MAN DISCRETE
(1) AC EXT PWR -46 (22)------------------- A/C AC EXT PWR~~~~~oPEN) DISCRETE
-47(I) FWD RAD RACK HOT -48 (22)------------------- A/C FWD RAD RACK
(28v/OpEN) HOT DISCRETE(I) SPD BRAKE EXTENDED -49 (22)------------------- A/C SPD BRAKE
(28V/OPEN) EXTENDEDDISCRETE
(I) TRANSFORMER RECTIFIER -50 (22)------------------- A/C TRU DISCRETEUNIT HOT (28V/OPEN)
(I) ENGINE SYNC ON -51 (22)------------------- A/C ENG SYNC(28v/OpEN) DISCRETE
(I) ICE DET (28V/OPEN) -52 (22)------------------- A/C ICE DETDISCRETE
(1) RUDDER FLT HYD OFF -53 (22)------------------- A/C RUDD FLT HYD(28V/OPEN) OFF DISCRETE
(I) RUDDER LIMIT -54 (22)(28V/OPEN)
------------------- A/C RUDDER LIMITDISCRETE
(I) GND SPOILER FAIL -55 (22)------------------- A/C GND SPOILER(28v/OpEN) FAIL DISCRETESPARE -56
(1) TONE GEN FAIL -57 (22)------------------- A/C TONE GEN(oPEN/28v) FAIL DISCRETE
(I) BAGGAGE DOORS UNLOCKED -58 (22)------------------- A/C BAGGAGE(28v/OpEN) DOORS DISCRETE
(1) SERVICE DOORS OPEN -59 (22)------------------- A/C SERVICE(28V/OPEN) DOORS DISCRETESPARE 137J1B-60
Interconnect InformationTable 501 (cent) 22-14-00
Page 598,35Feb 1/88
Use or disclosure of mformahon on this page IS subject to the restncttons on the We page of Ihls document
Data Acquisition Unit No. 2
106P
(1)
(1)
(1)
(I)
(I)
(1)
(I)
(I)
(I)
(I)
(1)
(1)
(1)
(I)(I)
(1)(1)
(I)
Function Connector Pin
GND PROX VALID 137JIB-61 (22)-------------------(OPEN/28V)SPARE -62SPARE -63R, COWL ANTI-lCE OVRT -64 (22)-------------------(28V/OF’EN)
SPARE -65R. ENGINE FIRE* -66 (22)-------------------
DAU IDENT BOO -67 (22)-------------------
FUEL. INTK OPEN* -68 (22)-------------------
ENG FAULT LOOP ALERT* -69 (22)-------------------
CABIN DFRN 2 ( J9.6)* -70 (22)-------------------(AMBER ANNUN)R. PITOT HEAT FAIL* -71 (22)-------------------
R. ALTERNATOR BEARING -72 (22)-------------------FAIL*BRAKE PEDAL (OPEN/GND) -73 (22)-------------------
ANTI-SKID FAIL (OPEN/GND) -74 (22)-------------------
APU ALT BRG FAIL -75 (22)-------------------(OPEN/GND)TAT PROBE HT FAIL* -76 (22)-------------------
MAINT TEST ENABLE* -77 (22)-------------------DU FAN 2 FAIL (OPEN/GND) -78 (22)-------------------
DAU lDENT BO1 -79 ------NCBATT CHARGER 2 FAIL -80 [22)-------------------(OPEN/GND)NOW* 137J1B-81 (22)-------------------
Connects To
A/C GND PROXVALID DISCRETE
A/C R. COWLANTI-ICEDISCRETE
A/C l?.ENGINEFIRE DISCRETE
SIG GN!I
REF APPENDIX C
A/C FUEL INTK
OPEN DISCRETEA/C ENG FAULTLOOP ALERTDISCRETEA/C CABIN DFRN 2DISCRETEA/C R. PITOT HTFAIL DISCRETEA/C R. BEARINGFAIL DISCRETEA/C BRAKEPEDAL DISCRETEA/C ANTI-SKIDFAIL DISCRETEA/C APU ALT BRGFAIL DISCRETE
A/C TAT PROBE HTFAIL DISCRETEAPpENDIX DDU FAN 2 FAILDISCRETEREF APPENDIX CA/C BATT CHARGER2 DISCRETEA/C NUTCRACKERDISCRETE
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.36Feb 1/88
Use or disclosure of miormahon on Ih/s page !s sublecl to the r :str)cttons on the MI? page of Ihm document
Data Acquisition Unit No. 2
IOB_P_ Function Connector Pin Connects To
RESERVED 137J1B-82SPARE -83SPARE -84SPARE -85SPARE -86SPARE -87SPARE -88SPARE -89SPARE -90SPARE -91SPARE -92RESERVED -93RESERVED -94RESERVED -95RESERVED -96RESERVED -97SPARE -98RESERVED -99
(I) ~~~L GND -100 (22)------------------ A/CSIGNALGND
-101RESERVED -102
(P) POWER GND -103 (22)------------------ A/CPWRGNDSPARE -104RESERVED -105
(P) 28 V DC PWR 137J1B-106 (22)------------------ A/C 28 V DC pWR
*
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.37Jun 1/87
Use or dk?.closureof Information on th!s page IS subjec! to the reslrlchons on the t!tle pag(: of thm document
GLOBAL POSITIONING SYSTEM SENSOR UNIT No. 1 (OPTIONAL)
IOB~ Function Connector Pin Connects To
(0] GPSSU FAULT 149J1-1 {22)---- ---------x--- APPX C(B) DADCI 429 INPUT (H)
$-6 (22)-~- ------- -----
#
DADC #1(B) DADC1 429 INPUT (L) -7 (22)- - ---------’1--- DADC #1
SHIELD GND--------- Y --- SHIELD GND
(0) INPUT DISCRETE RETURN -8 -:~g(0) TIME MARK #2 (H)(o) TIME MARK #2 (L) ::2 ----NC
(B) DADC2 429 INPUT (H)*
-lo (22)43- ---------fi--- DAr.)c#2
(B) DADC2 429 INPIJT (L) -11 (22)J’-Y
--------.11--- DADC #2SHIELD GND-------- Y --- SHIELD GND
(0) TIME MARK #3 {H) -13 ----NC(0) TIME MARK #3 (L) -14 ----NC(8) IRS1/FMSl 429 INPUT (H)
$-18 (22)fl- ---------- --
__--;121J1A-50
(B) IRS1/FMSl 429 INPUT (L) -37 (22) -Y “1--- 121J1A-51SHIELD GND--------- --- SHIELD GND
(o) TIME MARK #l (H) -19 ----NC(0) TIME MARK #l (L) -20 ----NC(I) 429 OUTPUT HS/LS SELECT* -21 ----NC
*
APPX C(B) 429 OUTPUT #2 (H) -24 (22)fi- ------.-y_- C121JIA-23(B) 429 OUTPUT #2 (L) -25 (22)
Y---------
+--- C121J1A-24
SHIELD GN5--------- --- SHIELD GND
(B) IRS2/FtlS2429 INPUT (H) -26 (22)fi- ---.----$$ 4--- C121JIA-50
(B) IRS2/FMS2 429 INPUT (L) -27 (22)1- ----------- -k_.
C121J1A-51SHIELD GND--------- SHIELD GND
(B) 429 OUTPUT #3 (H) -29 (22)f+$
----..--- APPX G(B) 429 OUTPUT #3 (L) -30 (22) -
Y---------;::: APPX G
SHIELD GND---------- Y --- SHIELDGND
(P) CHASSIS GROUND -33 (22)------------------ A/C CHASSIS GND(P) +28V POWER RETURN -34 (22)------------------ A/C POWER GND(P) +28V DC POWER -35 (22)------------------ A/C +28V DC
(B) 429 OUTPUT #1 (H)(B) 429 OUTPUT #1 (L) ::! !;@::l::::g::: YT;-;;
SHIELD GND---------- --- SHIELD-GND(1) DADC 419/429 SELECT* 149J1-40 ----NC APPX C
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.38Apr 15/93
Use or disclosure of information on this page is subject to the r~strictions on the title page of this document
INERTIAL REFERENCE UNIT No. 1
IOB~ Function Connector Pin Connects To
(I) IDENT RES R1 170J1A-A1 ----NC
(I) sDI/4 -A7 ----NC
(I) IDENT RES R2 -B1 ----NC
(I) IDENT RES R3 -Cl -----NC(I) IDENT RES COM -C2 -----NC
(I) IDENT RES R4 -D1 ----NC
(B) GPS1 429 INPUT #1 (H) -E2 -----NC(B) GPS1 429 INPUT #1 (L) -E3 -----NC(B) GPS2 429 INPUT #2 (H) -E4 ----NC(B) GPS2 429 INPUT #2 (L) -E5 -----NC(o) CTVAL 1 -E6 ----NC(o) CTVAL 2 -E7 ----NC
(o) AC FAIL LOGIC OUT -E1O ----NC(I) AC TO BATT XFER -En ----NC
(I) ASCB FORMAT SEL -E13 (22)----------------- 170J1B-A1(I) 37 WORD FORMAT -E14 (22)----------------- 170J1B-A1
(I) GPS1 TIME MARK (lHz) #1 (H)-F4 ----NC(I) GPS1 TIME MARK (lHz) #1 (L)-F5 ----NC
(I) GPS2 TIME MARK (lHz) #2 (H)-G2 ----NC(1) GPS2 TIME MARK (]fiz)#2 (L)-G3 ----NC
(o) CHARGER INHIBIT 170J1A-G9 (22)------------------ IRU BATTERY(28V/0)
Interconnect InformationTable 501 (cent) 22-14-00
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Useor disclosure of information on this page is subject to the restrictions on the title pag~ of this document
INERTIAL REFERENCE UNIT No. 1
IOB_P_ Function Connector Pin Connects To
(B) SYS ASCB PRI (H)$
170J1A-H1 (22)---fl--(B} SYS ASCB PRI (L) -H2 (22)---U-- ~~~~~~~~~~ ‘EF ‘ECT 3“3
(B) RS 232 DATA XMTR -H3 (22)-----
!l
-----n --- TEST CONNECTOR(B) RS 232 DATA RCVR -H4 (22)---~!- -----;;--- TEST CONNECTOR(B) RS 232 CONNON -H7 (22)---!’-
X. 1’::: :;;:JO~[;cTOR-----
SHIELD GND-------------
(B) RS 232 DTR -H5 ----NC(B) RS 232 CTS -H6 ----NC
(1) MEM ACCESS WR ENA (GND/0) -H1O (22)----------------- FLT TEST 0NL%
(I) SDI/3 -J9 ----NC
(B) SYS ASCB SEC (H) -K1 (22)---$-$
---------- REF SECT3.3(B) SYS ASCB SEC (L) -K2 (22)---u-- ----------
(I) ~~~~,~~ITE INHIBIT 170J1A-K6 ----NC
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.38.2
Apr 15/93
Use or disclosure of information on this page is subject to the restrictions on the title page of this document,
INERTIAL REFERENCE UNIT No. 1
Function Connector Pin
LOGIC GROUND 170J1B-A1 (22)------------------IRU ORIENT/1 -A2 (22)------------------IRU ORIENT/2 -A3 (22)------------------
Connects To
172J1-U170J1B-A1170J1B-A1
(o)(I)(I)
sDI/2 -A7 (22)-----
$
------------FMS1 429 INPUT (H) -A8 (22)--A ------------GEN BUS PRIMARY (L) -A9 (22)--~- ___f_
SHIELD GND----------- ---
(1)(B)(B)
170J1B-A1121J1A-62121J1A-49SHIELD GND
(I)(B)
(B)
REMOTE TEST -A1O (22)-----
$
-----------ISDU/NDU 429 INPUT (H) -A13 (22)--: ------$--
ISDU/NDU 429 INPUT (L) -A14 (22)--”Y
b
r------ ---
172J1-W171J1-24 (OPT)198J1-24 (OPT)171J1-25 (OPT)198J1-25 (OPT)SHIELD GNDSHIELD GND-----------1 1---
(0) BATT FAIL ANNUN (GND/0) -A15 (22)----------------- DIM &TEST PANEL
FMS2 429 INPUT (H)*
-C5 (22)---q- ------9---GEN BUS SECONDARY (L)
k-C6 (22)--- - ------;---
SHIELD GND------------ ---
(B)(B)
C121J1B-3C121J1B-15SHIELD GND
(o)(o)
FAULT ANNUN (GND/0) .-D2 (22)------------------ATT ANNUN (GND/0) -D3 ----NC
DIM & TEST PANEL
(o)(o)(o)
NO AIR ANNUN (GND/0) -El ----NCON DC ANNUN (GND/0) -E2 ----NCNAV READY ANNUN (GND/0) -E3 ----NC
ARINC 429 OUT #2 (H)*
-E5 (22)--fi- --...--~---ARINC 429 OUT #2 (L) -E6 (22)-- - ------- ---
YSHIELD GND----------- Y ---
(B)(B)
65J1A-4865J1A-49SHIELD GND
(I)(I)(I)
MODE DISCRETE/1 (GND/0) -F1 (22)------------------MODE DISCRETE/2 (GND/0) -F2 (22)------------------ALIGN ANNUN (GND/0) -F3 (22)------------------
172J1-e172J1-fDIM & TEST PANEL
ARINC 429 OUT #4 (H) -F14 (22)--~$
------fl---ARINC 429 OUT #4 (L) 170J1B-F15 (22)--; -----------
SHIELD GND----------- ? ---
(B)(B)
E65J1A-4BE65J1A-49SHIELD GND
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.38.3Apr 15/93
Use or disclosure of information on this page is subject to the restrictions on the title page of this document
IOB~
(o)
(B)
(B)
(B)(B)
(B)
(B)
(I)
(I)(B)(B)
(o)
(B)(B)
(B)(B)
INERTIAL REFERENCE UNIT No. 1
Function Connector Pin
IRU VALID 170J1B-G1 ----NC
ARINC 429 OUT #1 (H)%
-G7 (22)---R- -----fi---
ARINC 429 OUT #1 (L) -G8 (22)---{ -*----- $---
SHIELD GND----------- 1 I---
ARINC 4290UT #5 (H)*
-G14 (22)--~- a----------ARINC 4290UT #5 (L) -G15 (22)-- -------1-1---
SHIELD GND----------- Y- K-
ARINC 429 OUT #6 (H) -H14 (22)--fl
ARINC 429 OUT #6 (L) -H15 (22)--V
SHIELD GND------------1 1---
DADC 429/575 SEL (GND/0) -J6 (22)------------------
SDI/1 (GND/0) -J9 ----NCDADC 429 INPUT (H) -J1O (22)---~
*------ .--
SECONDARY DATA BUS (L) -Jll (22)---?- ----------SHIELD GOD------------ ---
ON BATT ANNUN (GND/0) -J15 (22)-----------------
DADC 429 INPUT (H)$
-K4 (22)---~- ----- ---PRIMARY DATA BUSSHIE~~)GND -K5 (22)----- ---------
---------- -. ---
ARINC 429 OUT #3 (H)$
-K12 (22)---fi- -----n--ARINC 4290UT #3 (L) 170JIB-K13 (22)---u- ------!!---
Connects To
171J1-26 (OPT)198J1-26 (OPT)171J1-27 (OPT)198J1-27 (OPT)SHIELD GND
DDRMI #1DDRMI #1SHIELD GND
134J1B-79C134JIB-79134J1B-80C134J1B-80SHIELD GND
170J1B-A1
C9J1B-30C9J1B-31SHIELD GND
DIM &TEST PANEL
9J1B-309JIB-31SHIELD GND
C65J1A-48C65J1A-49
SHIELD GND-------------J I--- SHIELD GND
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.38.4Apr 15/93
Use or disclosure of information on this page is subject to the re: trictions on the title page of this document.
INERTIAL REFERENCE UNIT No. 1
IOB& Function Connector Pin Connects To
(P) 115VAC, 400Hz, PWR 170J1C-1 (20)------------------ A/C AC PWR(P) +24V DC BATTERY INPUT -2 (16)------------------ IRU BATT JIB-8
(P) +28V DC ESSENTIAL INPUT -4 (20)------------------ A/CDC PWR(P) 115V AC, 400Hz RETURN -5 (20)------------------ A/CAC RTN(P) +28V DC ISDU/NDU PWR -6 (20)------------------ 172J1-M
171J1-3 (OPT)198J1-3 (OPT)
(P) +28V DC INPUT -7 (16)------------------ A/C DC PWR(P) 28V DC/BATT RETURN -8 (16)------------------ A/C DC RTN(P) ANNUNCIATOR PWR OUT -9 (20)------------------ 172J1-L(P) ANNUNCIATOR PWR IN -10 (16)------------------ A/C DC PWR(I) CHASSIS GND 170J1C-11 (16)------------------ CHASSIS GND
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.38,5Apr 15/93
Use or disclosure of information on this page is subject to the restrictions on the title page of this document.
INERTIAL SYSTEM DISPLAY UNIT (OPTIONAL)
IOB& Function Connector Pin Connects To
(P) 5V PNL LIGHT (H) 171J1-1 (20)------------------- A/CWIRING
(P) 5V PNL LIGHT (L) -2 (20)------------------- A/CWIRING
(P) +28V DC ISDU PWR -3 (20)------------------- 172J1-M,170J1C-6
(P) +28V DC PWR RTN -4 (20)------------------- GNDATCB PANEL
(I) CLR/ENT DIMMING -7 (22)------------------- APPXC
(P) CHASSIS GND -8 (20)------------------- CHASSIS GND
(I) DATA DISPLAY TEST -11 (22)------------------- APPX C
(B) ISDU OUTPUT (H) -24 (22) ----~$
m------ --- 170J1B-A13(B) ARINC 429 (L) -25 (22)------ -------~1--- 170JlB-A14
SHIELD GND----------- --- SHIELD GND
(B) ARINC 429 INPUT (H)$
-26 (22)---fi- --------@--- 170J1B-G7(B) ARINC 429 INPUT (L) 171J1-27 (22)--- - ------------ 170J1B-G8
SHIELD GND----------- Y --- SHIELD GND
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.38.6
Apr 15/93
Use or disclosure of information on this page is subject to the res rictions on the title page of this document.
INERTIAL SYSTEM DISPLAY UNIT (OPTIONAL)
IOB_P_ Function Connector Pin Connects To
(P) 5V PNL LIGHT (H) 171J2-1 ----NC(P) 5V PNL LIGHT (L) -2 ----NC(P) +28V DC ISDU PWR -3 (20)------------------- 172J2-M,
E170J1C-6(P) +28V DC PWR RTN -4 (20)------------------- GNDAT CB PANEL
(1) CLR/ENT DIMMING ----NC(P) CHASSIS GND :: (20)------------------- CHASSIS GND
(I) DATA DISPLAY TEST -11 ----NC
(B) ISDU OUTPUT (H)*
-24 (22)---n- ------- E170J1B-A13(B) ARINC 429 (L) -25 (22)---”-Y
.__ft:: E170J1B-A14SHIELD GND----------- V --- SHIELD GND
(B) ARINC 429 INPUT (H)$
-26 (22)----~ ----------- E170J1B-G7(B) ARINC 429 INPUT (L) 171J2-27 (22)------ -------;--- E170J1B-G8
SHIELD GND----------- --- SHIELDGND
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.38;7Apr 15/93
Use or disclosure of information on this page is subject 10 the restrictions on the title page of this document,
INERTIAL SYSTEM DISPLAY UNIT (OPTIONAL)
IOB~ Function Connector Pin Connects To
(P) 5V PNL LIGHT (H) 171J3-1 ----NC(P) 5V PNL LIGHT (L) -2 ----NC(P) +28V DC ISDU PWR -3 (20)------------------- 172J3-M,
C170J1C-6(P) +28V DC PWR RTN -4 (20)------------------- GNDATCB PANEL
(1) CLR/ENT DIMMING -7 ----NC
(P) CHASSIS GND -8 (20)------------------- CHASSISGND
(I) DATA DISPLAY TEST -11 ----NC
(B) ISDU OUTPUT (H) -24 (22)----a$
------ --- C170J1B-A13(B) ARINC 429 (L) -25 (22)----~- ___+_-
YC170J1B-A14
SHIELD GND----------- --- SHIELDGND
(B) ARINC 429 INPUT (H) -26 (22)----~$
----------- C170J1B-G7(B) ARINC 429 INPUT (L) 171J3-27 (22)---J~------------- C170J1B-G8
SHIELD GND----------- ~--- SHIELD GND
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.38.8Apr 15/93
Use or disclosure of information on this page is subject to the re<’trictions on the title page of this document.
MODE SELECT UNIT
IOB~ Function Connector Pin Connects To
(I) CHASSIS GND 172JI-A (20)-------------------- CHASSIS GND
(P) ANNUNCIATOR PWR INPUT -L (20)-------------------- 170J1C-9(P) +28V DC PIJR -M (20)-------------------- 170J1C-6
171J1-3 (OPT)198J1-3 (OPT)
(o) IRU BLOWER CONTROL (28V/0)-N (20)-------------------- BLOWER CONTROLRELAY
(I) FAULT ANNUN (GND/0) -P (22)-------------------- DIM&TEST PANEL
(P) O-5 V PANEL LIGHTING (H) -S (20)-------------------- A/C WIRING(P) O-5V PANEL LIGHTING (L) -T (20)-------------------- A/CWIRING(I) LOGIC GNC) -u (22)-------------------- 170J1B-A1(1) 28V DC PWR RET -V (20)-------------------- 28VDC RTN(0) TEST SWITCH (GND/0) -w (22)-------------------- I7OJ1B-A1O
(I) BATT FAIL ANNUN (GND/0) -Z (22)-------------------- DIM & TEST PANEL(I) ALIGN ANNUN (GND/0) -a (22)-------------------- DIM & TEST PANEL
(0) MODE SELECT 1 (GND/0) -e (22)-------------------- 170J1B-F1(o) MODE SELECT 2 (GND/0) -f (22)-------------------- 170J1B-F2(1) ON BATT ANNUN (GND/0)(I) ANNUNCIATOR TEST
-g (22)-------------------- DIM&TEST PANEL172J1-h ----NC
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.38.9Apr 15/93
USe or disclosure of information on this page is subject to the restrictions on the title page of this document
IOB_P_
(I)
(P)(P)
(o)
(I)
(P)(P)(I)(I)(o)
(I)(I)
(o)(o)(I)(I)
MODE SELECT UNIT
Function Connector Pin Connects To
CHASSIS GND 172J2-A (20)-------------------- CHASSIS GND
ANNUNCIATOR PWR INPUT -L (20)-------------------- E170J1C-9+28V DC PWR -M (20)-------------------- E170J1C-6
171J2-3 (OPT)198J2-3 (OPT)
IRU BLOWER CONTROL (28V/0)-N (20)-------------------- BLOWER CONTROL
FAULT ANNUN (GND/0)
O-5 V PANEL LIGHTINGO-5 V PANEL LIGHTINGLOGIC GND28V DC PWR RETTEST SWITCH (GND/0)
., . .RELAY
-P (22)-------------------- DIM &TEST PANEL
(H) -S ----NC(L) ~j ~zijNC
-------------------- E170J1B-A1-V (20)-------------------- 28V DC RTN-w (22)-------------------- E17OJ1B-A1O
BATT FAIL ANNUN (GND/0) -Z (22)-------------------- DIM &TEST PANELALIGN ANNUN (GND/0) -a (22)-------------------- DIM & TEST PANEL
MODE SELECT 1 (GND/0) -e (22)-------------------- E170J1B-F1MODE SELECT 2 (GND/0) -f (22)-------------------- E170J1B-F2ON BATT ANNUN (GND/0) -g (22)-------------------- DIM & TEST PANELANNUNCIATOR TEST 172J2-h ----NC
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of information on this page is subject to the restrictionson the title page of this document.
MODE SELECT UNIT
IOB_P_ Function Connector Pin Connects To
(I) CHASSIS GND 172J3-A (20)-------------------- CHASSIS GND
(P) ANNUNCIATOR PWR INPUT -L (20)-- ------------------ C170J1C-9(P) +28V DC PWR -M (20)-------------------- C170J1C-6
171J3-3 (OPT)198J3-3 (OPT)
(o) IRU BLOWER CONTROL (28V/0)-N (20)-------------------- ~;:];R CONTROL
(I) FAULT ANNUN (GND/0) -P (22)-------------------- DIM&TEST PANEL
(P) O-5 V PANEL LIGHTING (H) -S ----NC(P) O-5V PANEL LIGHTING (L) ~j ~ziiNC(1) LOGIC GND -------------- C170J1B-A1(1) 28V DC PWR RET -v (20)=:::-------------- 28V DC RTN(0) TEST SWITCH (GND/0) -w (22)-- ------------------ C17OJ1B-A1O
(I) BATT FAIL ANNUN (GND/0) -z (22)-------------------- DIM & TEST PANEL(I) ALIGN ANNUN [GND/0) -a (22)-------------------- DIM & TEST PANEL
(o) MODE SELECT 1 (GNO/0) -e (22)-------------------- C170J1B-F1(0) MODE SELECT 2 (GND/0) -f (22)-------------------- C170JIB-F2(I) ON BATT ANNUN (GND/0)(I) ANNUNC IATO!?TEST
-g (22)-------------------- DIM& TEST PANEL172J3-h ----NC
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IOB&
(P)(P)(P)
(P)
(1}(P)
(1)
(5)
(B)
(B)(B)
NAVIGATIONAL DISPLAY UNIT (OPTIONAL)
Function Connector Pin
5V PNL LIGHT (H) 198J1-1 (20)-------------------5V PNL LIGHT (L) -2 (20)-------------------+28V DC NDU PWR -3 (20)-------------------
+28V DC PWR RTN -4 (20)-------------------
BRT/DIM -7 (22)-------------------CHASSIS GND -8 (20)-------------------
DATA DISPLAY TEST -11 (22)-------------------
NDU OUTPUT (H) -24 (22)--:-
f
4------- ---II
ARINC 429 (L) -25 (22)--’1- --------’ i---T T
SHIELD GND----------l 1---
ARINC 429 INPUT (H)*
-26 (22)--~- ------- -G---ARINC 429 INPUT (L) 198J1-27 (22)--J;- --------~#---
SHIELD GND---------- ---
Connects To
A/C WIRINGA/C WIRING172JI-M,170J1C-6GND AT CB PANEL
APPX CCHASSIS GND
APPX C
170J1B-A1365J1B-13170J1B-A1465J1B-14SHIELD GND
170JIB-G7170JIB-G8SHIELD GND
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Use or disclosure of information on this page is subject to the restrictions on the title page of this document.
NAVIGATIONAL DISPLAY UNIT (OPTIONAL)
IOB~ Function Connector Pin Connects To
(P) 5V PNL LIGHT (H) 198J2-1 ----NC(P) 5V PNL LIGHT (L) ----NC(P) +28V DC NDU PWR :$ (20)------------------- 172J2-M,
E170J1C-6(P) +28V DC PWR RTN -4 (20)------------------- GNDATCB PANEL
(1) BRT/OIM -7 ----NC(P) CHASSIS GND -8 (20)------------------- CHASSISGND
(I) DATA DISPLAY TEST -11 ----NC
(B) NDU OUTPUT (H)
i
-24 (22)---S- -------fi--- E170J1B-A13E65J1B-13
(B) ARINC 429 (L) -25 (22)---”- ------- it--- E170J1B-A14
T 1 SH,E,O-GNDE65J1B 14
SHIELD GND-----------
(B) ARINC 429 INPUT (H)*
-26 (22)---~- m---------- E170J1B-G7(B) ARINC 429 INPUT (L) 198J2-27 (22)---?- -------f--- E170J1B-G8
SHIELD GND------------ --- SHIELDGND
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of information on this page is subject to the restrictions on the title page of this document
NAVIGATIONAL DISPLAY UhflT (OPTIONAL)
IOB_P_ Function Connector Pin Connects To
(P) 5V PNL LIGHT (H) 198J3-1 ----NC(P) 5V PNL LIGHT (L) ----NC(P) +28V DC NDU PWR :: (20)------------------- 172J3-M,
C170JIC-6(P) +28V DC PWR RTN -4 (20)------------------- GNDAT CBPANEL
(I) BRT/DIM -7 ----NC(P) CHASSIS GND -8 (20)------------------- CHASSIS GND
(I) DATA DISPLAY TEST -11 ----NC
(B) NDU OUTPUT (H) -24 (22)---fl-
$
----.-11--- C170J1B-A13
C65J1B-13(B) ARINC 429 {L) -25 (22)---”- ----..s-il.---
Ti
C170J1B-A14C65J1B-14
SHIELD GND----------- --- SHIELDGND
(B) ARINC 429 INPUT (H) -26 (2z)---.f3.*
------ .--- C170J1B-G7(B) ARINC 429 INPUT (L) 198J3-27 (22)---;- -------8--
SHIELD GND---------- f- - :;;;:;B&;;
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Use or disclosure of information on this page is subjectto the restrictimson the title page of this document,
Digital Air Data Computer No. 2
IOBP Function Connector Pin Connects To
(P) 28 VDCHI C9J1A-1 (NOTE 3)---------------- A/C 28 V DC PWR
(P) 28 VDCHI -2 (NOTE 3)---------------- A/C 28 V DC PWR(P) 28 V DC RETURN -3 (NOTE 3)---------------- A/C PWR GND(P) 28 V DC RETURN -4 (NOTE 3)---------------- A/C PWR GND(P) SIGNAL GROUND -5 (22)-------------------- A/C SIG GND(P) SIGNAL GROUND -6 (22)-------------------- A/C SIG GND(P) DC GROUND -7 (~2)--.---.------------- A/C GND(P) DC GROUND -8 (22)-------------------- A/C GND(P) CHASSIS GROUND -9 (22)-------------------- CHASSIS GND(P) CHASSIS GROUND -10 (22)------------------ CHASSIS GND
1(9) SYS ASCB PRIMARY BUS (H) -11 (22)--’=--------------- SEE SECT 3.3
}(B) :;:R;SCB PRIMARY BUS (L) 4$ (22)-+ -------------
SPARE -14SPARE -15SPARE -16SPARE -17SPARE -18SPARE -19SPARE -20SPARE -21SPARE -22SPARE -23SPARE -24SPARE -25SPARE -26SPARE -27SPARE -28SPARE -29SPARE -30SPARE -31SPARE -32SPARE -33
(0) ALT VALID (28 V DC/OPEN) -34 (22)------------------- STALL WARN
COMPUTER #2,
{
REF APPX C
(I) BARO POT (Ii) -35 (22)------Q-- -------- C115J2-L(I) BARO POT (w) -36 (22)---------- -------- C115J2-M(1) BARO POT (L) -37 (22)------>1-- -------- C115J2-N(I) BARO DISABLE* -38 ------NC
}
REF APPX C(I) SSEC DISABLE* C9J1A-39 ------NC
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Use or disclosure of information on this page is subject to the restrictionson the title page of this document
Digital Air Data Computer No. 2
(I)
(I)(I)(I)(I)
(I)(o)(I)
(o)
(1)(1)
(o)(o)
Function Connector Pin
SPARE C9J1A-40SPARE -41SPARE -42SPARE -43SPARE -44SPARE -45SPARE -46SPARE -47SPARE -48SPARE -49SPARE -50SPARE -51AIR DATA SELF TEST* -52 ------NCSPARE -53SPARE -54FLAP POS #1 (O DEG*) -55 (22)-------------------FLAP POS #2 (10 DEG*) -56 (22)-------------------FLAP POS #3 (20 DEG*) -57 (22)-------------------FLAP POS #4 (39 DEG*) ~:: (22)-------------------SPARESPARE -60SPARE -61CABIN PRESS REF (H)
i
-62 (22)_~~.- ------.-----CABIN PRESS RATIO (W) -63 (22)---T-- ------------:;:;: PRESS REF (L) -64 (22)-Jo--- ---.--------
-65CABIN PRESS RATIO VALID -66 (22)-------------------(GND/OPEN)SPARE -67SPARE -68SPARE -69SPARE -70SPARE -71TEMPERATURE PROBE (H)
$-72 (22)--~i-- ------------
~;~;;RATURE PROBE (L) -73 (22)--O -- -------------74
SPARE -75SPARE -76ALTITUDE SWITCH -77 ------NCPRESSURE ALTSIG (H) C9J1A-78 (22)-------------------
Connects To
A/C WIRING
I
A/C WIRING APPXA/C WIRING CA/C WIRING
A/C WIRINGA/C WIRINGA/C WIRING
“A/C WIRINGAPPX C
A/C WIRINGA/C WIRING
REF APPX CSTALL WARNCOMPUTER #2
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of mtormatlon on Ihm page IS sub)ect to the restrictions on the I!tle pago of thts document,
Digital Air Data Computer No. 2
IOB~ Function Connector Pin Connects To
SPARE C9J1A-79(0) ALT SWITCH COMMON -80 (22)------------------- A/CWIRING,
REF APPX C(I) AOA TEST MODE SW COMMON -81 (22)------------------- A/C SIGGND(I) AOA TEST SW COMMON (SL) -82 ------NC(I) :$;R:EST SW COMMON (15K) -83 ------NC
-84(0) OVERSPEED WARNING -85 (22)------------------- A/C WIRING,
(28 V DC/OPEN) REF APPX CSPARE -86SPARE -87SPARE -88SPARE -89SPARE -90SPARE -91
(0) AOA TEST MODE SELECT -92 (22)------------------- STALL WARN x(GND/OPEN) COMPUTER #2
(I) ALERTER SELECT -93 (22)------------------- 9J1A-93,(OPEN/GND) 1OJ2B-88,
C1OJ2B-88(0) AOA INDEXER (RED) -94 (22)------------------- APPXD ~REF
(GND/OPEN) APPX(0) AOA INDEXER (GREEN) -95 (22)------------------- APPXD c
(GND/OPEN)(0) AOA INDEXER (YELLOW) -96 (22)------------------- APPX D 1
(GND/OPEN)(0) AOA TEST MODE (SL) SELECT -97 ------NC
(GND/OPEN)(0) AOA TEST MODE (15K) SELECT -98 ------NC
(GND/OPEN)SPARE -99
(I) PILOT/COPILOT* -100 (22)------------------ A/C SIG GND(I) AIRCRAFT ID IDO -101 (22)------------------ A/C GND(I) AIRCRAFT ID ID1 -102 ------NC
I
REF(I) AIRCRAFT ID ID2 -103 ------NC APPX(I) AIRCRAFT ID ID3 -104 (22)------------------ A/C GND C(I) AIRCRAFT ID ID4 -105 ------NC(I) AIRCRAFT ID ID5 C9J1A-106 (22)------------------ A/C GND
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of mformatlon on this page IS subject to the eslrlctlons on the Mle page of thwi document
Digital Air Data Computer No. 2
(B)(B)
(B)(B)
(B)
(B)
(B)(B)
Function Connector Pin Connects To
SPARE C9J1B-1SPARE -2SPARESPARE ::SPARESPARE ::SPARE -7SPARE -8SPARE -9SPARE -loSPARE -11
;;~RiSCB SECONDARY BUS (H) ~;; (22)---]----------] SEE SECT 3.3SYS ASCB SECONDARY BUS (L) ~;~ (22)---~- -----------SPARESPARE -16SPARE -17SPARE -18SPARE -19SPARE -20SPARE -21SPARE -22SPARE -23SPARE -24SPARE -25ARINC 429 OUTPUT #1 (H)
$-26 (22)---f)-------------- C65J1B-39
ARINC 429 OUTPUT #1 (L) -27 (22)---- - ------------ C65J1B-40SHIELD GND-----------Y
SPARE -28SPARE -29ARINC 429 OUTPUT #3 (H)
t
-30 (22)---fi- ------------ 17OJ1B-J1O,C17OJ1B-J1O
ARINC 4290UTPUT #3 (L) -31 (22)---”- ------------T 170JIB-J1l,C170J1B-J1l
SHIELD GND-----------ARINC 429 OUTPUT #4 (H)
$-32 (22)---&- ------------ A/CWIRING
ARINC 429 OUTPUT #4 (L) -33 (22)--!;- ------------ A/CWIRINGSHIELD GND-----------
SPARE -34SPARE -35SPARE -36SPARE -37SPARE C9J1B-38
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Useordisclosureofinformationonthispageissubjecttotherestrictionsonthetitlepageofthisdocument,
Digital Air Data Computer No. 2
(0)
(o)(o)
(o)
(B)
(B)
Function Connector Pin
SPARE C9J1B-39SPARE -40SPARE -41SPARE -42SPARE -43SPARE -44SPARE -45SPARE -46SPARE -47SPARE -48~;~R~LERTHORN (28 V/OPEN) ~;; (22)-------------------
SPARE -51SPARE -52AOA REF (H)
1
-53 (22)------ ----------M!R:EF (L) -54 (22)---;+- ----,.-----
“55SPARE -56
II
SPARE -57t$
SPARE -5811~1
SPARE -59AOOR:IG (W) -60 (22)---:-- -----------
-61SPARE -62SPARE -63SPARE -64SPARE -65SPARE -66SPARE -67SPARE -68SPARli -69ARINC 429 OUTPUT #2 (H)
t-70 (22)----R- -----------
;:
ARINC 4290UTPUT #2 (L) 1-71 (22)---“-- -----------
7SHIELD GND------------1
SPARE -72SPARE C9JIB-73
Connects To
A/C WIRING,APPX C
TO AOA PROBETOAOA PROBE
TO AOA PROBE
65J1B-39,E65J1B-39E170JIB-K4,APPX L65J1B-40,E65J1B-40,E170J1B-K5APPX L
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.42Apr 15/93
Use or disclosure of information on this page is subject to the re trictions on the title page of this document,
Digital Air Data Computer No. 2
IOB& Function Connector Pin Connects To
SPARE C9J1B-74(0) ALT ALERT ANNUN (GND/OPEN) -75 (22)------------------- A/C WIRING REF(0) ALT ALERT HORN (GND/OPEN) -76 (22)------------------- A/C WIRING APPX
cSPARE -77SPARE -78SPARE -79RESERVED -80RESERVED -81RESERVED -82RESERVED -83RESERVED -84RESERVED -85RESERVED -86RESERVED -87RESERVED -88RESERVED -89RESERVED -90SPARE -91SPARE -92SPARE -93RESERVED -94RESERVED -95SPARE -96SPARE -97SPARE -98RESERVED -99RESERVED -1ooRESERVED -101RESERVED -102
(I) ALT SELECT TACH (H) -103 (22)---~~-+(1)
----------- 11J2-30ALT SELECT TACH (L) -104 (22)--!C--Y----------- 11J2-31SPARE -105SPARE C9J1B-106
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of Information on this page IS sub)e(I to Ihe restrictions on the Mle pagt? of thw document
IOB_P_
(P)
(P)
(P)(P)
(P)
(P)(P)
(P)(P)
(I)
(o)(o)
Flight Guidance Computer No. 2
Function Connector Pin
28 V DC PWR C1OJ1A-1 (NOTE 3)----------------(STAB AUG SERVO PWR)28 V DC PWR RTN -2 (NOTE 3)----------------(STAB AUG SERVO PWR RTN)CHASSIS GND -3 (22)--------------------28 V DC (AUTO PILOT -4 (NOTE 3)----------------SERVO PWR)28 V DC (AUTO PILOT -5 (NOTE 3)----------------SERVO PWR RTN)28 V’DC COMPUTER POWER -6 (NOTE 3)----------------28 V DC COMPUTER POWER -7 (NOTE 3)----------------RTN28 V DC COMPUTER POWER -8 (NOTE 3)----------------28 V DC COMPUTER POWER -9 (NOTE 3)----------------RTNSPARE -loSPARE -11SPARE -12SPARE -13SPARE -14SPARE -15SPARE -16SPARE -17HDG SEL (H)
t-18 (22)--~-~- ------------
(L) -19 (22)--J~;- ------------SPARE -20AP BRAKE (28V DC/OPEN) -21 (22)-------------------MIEB~KE (28VDC/OPEN) ~;; (22)-------------------
Connects To
A/C 28 V DC PWR
A/C 28 V DC RTN
A/C CHASSIS GNDA/C 28 V DC PWR
A/C 28 V DC PWRRTNA/C 28 V DC PWRA/C 28 V DC PWRRTNA/C 28 V DC PWRA/C 28 V DC PWRRTN
11J2-2611J2-27
12P1-21, 13P1-2129J1-21
SPARE -24RESERVED -25SPARE -26SPARE -27
(I) STICK SHAKER ACTIVE -28 (22)------------------- A/C WIRING REF(28V/OPEN) APPENDIX CSPARE -29SPARE -30SPARE -31SPARE C1OJ1A-32
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Jun 1/87Use or disclosure 01 InformalIon on this page IS subject to the r?slnctlons on the title page of this document
Flight Guidance Computer No. 2
106_P_ Function Connector Pin Connects To
(I) TRIM DN CMD CIOJIA::j (22)------------------- APPENDIXDSPARESPARE -35SPARE -36
(o) PRIORITY STATUS #2 -37 (22)------------------- llJ2-70,115Jl-b,(28V/OPEN) Cl15J1-b, APPX CSPARE -38SPARE -39
(I) Y/G REMOTE ENGAGE/ -40 (22)------------------- APPENDIXD,DISENGAGE (OPEN/GNDTOGGLE) REF APPENDIX C
(I) TRIM REMOTE ENGAGE/ -41 (22)------------------- APPENDIXD,DISENGAGE (OPEN/GND TOGGLE) REF APPENDIX CSPARE -42SPARE -43SPARE -44SPARE -45SPARE -46
(I) :NH4EUP CMD -47 (22)------------------- APPENDIXD
-48
SPARE -49
SPARE -50
SPARE -51
SPARE -52
SPARE -53
SPARE -54
SPARE -55
SPARE -56
SPARE -57
(0) YAW DAMP ENGAGE (28V/OPEN) -58 (22) ------------------- 14 P1-A,1OJ1A-58
134J1B-26,
C134J1B-26,
!
APPENDIX D
(0) RUDDER ACTUATOR EXEC (H) -59 (22)----;~r ---------- 14J1-S(o) RUDDER ACTUATOR EXEC (L) -60 (22)-----C;- ---------- 14J1-R
SHIELD GND-----J
(I) RUD LVDT FEEDBACK (H) i-61 (22)----~-~- ---------- 14J1-T(I) RUD LVDT FEEDBACK (L) 1OJ1A-62 (22)----~Y’------------ 14J1-U
SHIELD GND -.---
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Use or dwclosure of information on this page IS sub]ec! 10 the res!r!ctlons on the Mle pag( of this document
Flight Guidance Computer No. 2
IOB& Function Connector Pin Connects To
(o) RUD ACTUATOR HI
1
C1OJ1A-63 (22)---{-;------------ 14J1-HDRIVE
(o) RUD ACTUATOR DRIVE LO -64 (22)---!;-;------------ 14J1-GSHIELD GND ----J
SPARE -65SPARE -66SPARE C1OJ1A-67
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Use or disclosure of mformatlon on thm page IS subject to the r,!strlcllons on the Mle page of this document
Flight Guidance Computer No. 2
(B)
(B)
(I)(1)
(I)(I)
(I)
(I)
Function
SYS ASCB PRIMARY~y~ A~cB pRl~;~yBUS
BUS (L)SPARERESERVEDRESERVEDSPARESPEED CMD [Ii;
SPARESPAREV/S CMD (H)
(L)SPARESPARESPAREPITCH UP TRIM LIMITSPARESPAREPITCH DN TRIM LIMITSPARESPARESPARESPARESPARESPARESPARESPARESPARESPARESPARESPARESPARESPARESPARESPARE
Connector Pin Connects To
1)
C1OJ1B-1 (22)---f~l- ------------RED SECTION 3.3
-2 (22)---[-;- ------------
-3-4-5-6
+-7 (22)------ ------------ 11J2-24-8 (22)---!~--------------- 11J2-25-9-lo
i-11 (22)----- ------------ 11J2-28-12 (22)--{-;- ------------ 11J2-29-13-14-15-16 (22)------------------- 29AJ2-6-17-18-19 (22)------------------- 29AJ2-5-20-21-22-23-24-25-26-27-28-29-30-31-32-33-34
C1OJ1B-35
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Flight Guidance Computer No. 2
IOB~ Function
[cl]
(o)(0)
(I)
(1}(o)(o)
(o)
(o)
(1)(1)
(1)(1)
Connector Pin
A-PROC DAC #3 C1OJ1B-36 (22)-------------------A-PROC DAC #4 -37 (22)-----”-------------A-PROC DAC #5 -38 (22)-------------------A-PROC DAC #6 ::: (22)-------------------SPARESPARE -41SPARE -42SPARE -43
{Ii)
1
-44 (22)-- ----------------26 V AC REF
(L) -45 (22)-- ------~---------B-PROC DAC #3 -46 (22)-------------------B-PROC DAC #4 -47 (22)-------------------SPARE -48SPARE -49SPARE -50SPARE -51B-PROC DAC #5 ~:: (22)-------------------SPARESPARE -54SPARE -55SPARE -56B-PROC DAC #6 -57 (22)-------------------SPARE -58SPARE -59SPARE -60SPARE -61SPARE -62SPARE -63FLIGHT TEST INPUT#l (H) -64 (22)-------------------FLIGHT TEST INPUT#l (L) ~~~ (22)-----’-------------SPARESPARE -67
iELEVATOR TACH FEEDBACK (H) -68 (22)--;?- -------------ELEVATOR TACtiFEEDBACK (L) -69 (22)--.-;--------------
Connects To
A2
29J2-3,26 VAC PWRPWR GNCI
A 2
A2
A2,
A2
13J2-171332-16
(1) AILERON TACliFEEDBACK (H) -70(1) AILERON TACH FEEDBACK (L) -71(1) TRIM TACH FEEDBACK (H) -72(I) TRIt4TACH FEEDBACK (L) -73(I) FLIGHT TEST INPUT #2 (H) -74(r) FLIGHT TEST INPUT#2 (L) -75
I(22)-:~j ------------- 12J2-17(22)--;<- ------------- lZJZ-16(22)--,--I------------- 29J2-16(22)--<7- ------------- 292-17(22)-------------------(22)------------------- A
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Use or dwclosure of Information on thts page IS sub)ect to the r ?strlctlons on the Me page of this document
I
I
Flight Guidance Computer No. 2
108& Function Connector Pin Connects To
(1) ID1 C1OJIB-76------NC(1) ID2 -77------NC(1) A/C ID3 -78------NC(1) IDENTIFICATION ID4 -79 (22)------------------- SIGGND
\
REF(1) 105 -80------NC APPX
106 -81 (22)------------------- SIG GND CSPARE -82SPARE -83SPARE -84
(I) CS TRIM DN CMD -85 (22)------------------- APPENIIIXD(1} CS TRIM UP CMD -86 {22)------------------- APPENOIXD
RESERVED -87------NC(I) RESERVED -88------NC(I) RESERVED -89------NC
SPARE -90SPARE -91SPARE -92SPARE -93SPARE -94
INSTALLATION CRITICAL PINS 95 AND 96 ARE CRITICAL, SEE PAGE 3-13.
(1) MISCOMPARE #1* -95 (22)------------------- 1OJ1B-95, ‘E170J1A-E6
(1) MISCOMPARE #2* -96 (22)------------------- IOJIB-96,E170J1A-E7
SPARE -97 REFSPARE -98 ● APPX
(1) RAD ALT FORMAT 101 -99 -----NC c(I) RAD ALT FORMAT IDO -100 ------NC
SPARE -101(I) PILOT/COPILOT I.D. #1 -102 ------NC{1) PILOT/COPILOT I.D. #2 -103 (22)------------------ A/CGND(I) END ITEM TEST -104------Nt
SPARE -105(o} PROGRAM PIN GND 1 CIOJ1!3-106 >
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Use or disclosure of information on this page is subject :0 the restrictions on the title page of this document
Flight Guidance Computer ho. 2
10B& Function Connector Pin Connects To
SPARE C1OJ2A-1SPARE -2
(P) ~:~[;L GND -3 (22)-------------------- A/C SIGNAL GND-4
SPARE -5SPARESPARE $SPARESPARE ::SPARE -loSPARE -11SPARE -12SPARE -13SPARE -14SPARE -15SPARE -16SPARE -17SPARE -18SPARE -19SPARE -20SPARE . -21SPARE -22SPARE -23SPARE -24SPARE -25SPARE -26SPARE -27SPARE -28SPARE -29SPARE -30SPARE -31SPARE -32SPARE -33SPARE -34SPARE -35
I
(I) CROSS RADIO ALTITUDE (H) -36 (22)---f~l------------ ZOJ1-W, 1OJZB-Z6,136J1A-50
(I) CROSS RADIO ALTITUDE (L) -37 (22)--!Cj- ----------- 20J1-N, ]OJ2B-27,136J1A-51, 20J1-E
(I) CROSS RADIO C1OJ2A-38 (22)------------------ 20J1-Y, 10J2~-28,ALTITUDE VALID 136J1B-19
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Flight Guidance Computer No. 2
IOB_P_ Function Connector Pin Connects To
SPARE C1OJ2A-39SPARE -40
(I) A/P CROSS PWR SENSE IN -41 (22)------------------- 1OJ2A-42(0) A/P CROSS PWR SENSE OUT -42 (22)------------------- 1OJ2A-41(I) STAB AUG CROSS PWR -43 (22)------------------- IOJ2A-44
SENSE IN(0) STAB AUG CROSS PWR -44 (22)------------------- 1OJ2A-43
SENSE OUT(I) CROSS SERVO PWR SENSE IN -45 (22)------------------- 1OJ2A-46(o) CROSS SERVO PWR SENSE OUT -46 (22)------------------- 1OJ2A-45(1) CROSS SERVO’S OFF IN -47 (22)------------------- 1OJ2A-48(0) CROSS SERVO’S OFF OUT -48 (22)------------------- 1OJ2A-47(I) CROSS CHANNEL SYNC IN -49 (22)------------------- 1OJ2A-5O(0) CROSS CHANNEL SYNC OUT -50 (22)------------------- 1OJ2A-49(o) A-PROC DAC #1 -51 (22)-------------------(o) A-PROC DAC #2 A-52 (22)------------------- 2(o) B-PROC DAC #1 -53 (22)-------------------(o) B-PROC DAC #2 -54 (22)----- -------------(0) ELEVATOR SERVO DRIVE (H) -55 (20)--’-~-
1------------- 13P2-1
(0) ELEVATOR SERVO DRIVE (L) -56 (20)-{-;- ------------- 13P2-2SHIELD GND --J
(0) AILERON SERVO DRIVE (H) -57 (20)..;>,-1------------- 12P2-1
(0) AILERON SERVO DRIVE (L) -58 (20)--C-- ------------- 12P2-2SHIELD GND --J
(0) TRIM DRIVE UPI
-59 (20)----- ------------- 29J2-2(0) (ELEV) DN -60 (20)--!C;-------------- 29J2-1
SHIELD GND --J
(0) AILERON AND ELEVATOR -61 (22)------------------- APPE.NDIXDCLUTCH DRIVESPARE -62
(0) TRIM CLUTCH DRIVE -63 (22)------------------- APPENDIXDSPARE -64
(0) 5 V DC GP PWR #2 -65 (22)------------------- 11J2-12(o) 5 V DC GP PWR RTN #2 -66 (22)-------------------A1J2-13(0) DAC COMMON C1OJ2A-67 (22)-------------------
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.51Jun 1/87
Use or dwclosure of mformatlon on this page IS sub!ecI 10 the restrlct)ons on the Wle page of Ihw document
Flight Guidance Computer No. 2
106_P_
(B)
(B)
(I)
(I)
(I)
(I)
(I)
Function Connector Pin Connects To
SYS ASCB SECONDARY
1}
C1OJ2B-1 (22)---f~( ------------BUS (H) REF SECTION 3.3SYS ASCB SECONDARY -2 (22)---!~;- ------------~:~RE (L)
-3RESERVED -4RESERVED -5SPARE -6SPARE -7SPARE -8SPARE -9SPARE -loSPARE -11SPARE -12SPARE -13SPARE -14SPARE -15SPARE -16SPARE -17SPARE -18SPARE -19SPARE -20SPARE -21SPARE -22SPARE -23SPARE -24SPARE -25RADIO ALTITUDE (H)
!
-26 (22)--;-~l------------- 1OJ2A-36,
II C20J1-W,137J1A-50
RADIO ALTITUDE (L) -27 (22)--++ ------------ 1OJ2A-37,C20J1-N,137J1A-51,C20J1-E
RADIO ALTITUDE VALID -28 (22)------------------- C20J1-Y,1OJ2A-38,137J1B-19
B FLIGHT TEST (H) -29 (22)-------------------INPUT #1 A 2B FLIGHT TEST (L) C1OJ2B-3O (22)-------------------INPUT #1
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.52Jun 1/87
Use or dwclosure of Information on thm page IS subject to the n stnctlons on the Me page of thm document
IOB_P_
(I)
(I)
(1)(I)(I)
(o)
(I)
(I)(I)(])(1)
(I)
(I)
(I)
Function
B FLIGHT TESTINPUT #2 .B FLIGHT TESTINPUT #2SPARESPARESPARESPARESPARESPARESPARESPARESPARESPARESPARE
TRIM SERVO POS
SPARESPARESPARESPARESPARE
Flight Guidance Computer No. 2
Connector Pin
(H) C1OJ2B-31 (22)-------------------
(L) -32 (22)-------------------
-33-34-35-36-37-38-39-40-41-42-43
(x) .44 (22)_{+- + -.----------(Y) -45 (22)------1------------(z) -46 (22)--++-----------
-47-48-49-50-51
SPARE -52Y/D DISENGAGE ANNUN -53 (22)-------------------(28V/OPEN)AUTOPILOT DISCONNECT -54 (22)-------------------(OPEN/GND)TK POS REF -55 (22)-------------------TK GND REF -56 (22)-------------------TK NEG REF -57 (22)-------------------TK SIG (H) -58 (22)-------------------
TK OUT OF DETENT -59 (22)-------------------
CS TKSIG (H) -60 (22)-------------------
CS TK OUT OF DETENT -61 (22)-------------------SPARE C1OJ2B-62
Connects To
A2-
29J2-1829J2-1929J2-20
APPENDIX D,REF APPENDIX CAPPENDIX D,REF APPENDIX C129J1-13129J1-14129J1-11129J1-12,IOJ2B-60129J1-17,1OJ2B-61129J1-2,1OJ2B-58129J1-8,1OJ2B-59
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.53Jun 1/87
Use or disclosure Of mtormatlon on Ihls page IS subjac 10 the restrictions on the Mle pag, of this document
Flight Guidance Computer No. 2
IOB
P Function Connector Pin Connects To
SPARE C1OJ2B-63
SPARE -64
(I) EMERGENCY DISCONNECT -65 (22) ------------------- C1OJ1A-6,7
(OPEN/28V) C1OJ1A-8,11J2-76
(I) TRIM DISCONNECT (OPEN/GND) -66 (22)------------------- APPENDIX D(I) YAW DAMPER DISCONNECT -67 (22)------------------- SIG GND
(OPEN/GND)(I) TEST SIGNAL ENABLE* A-68 (22)------------------- 2(1) FTIU INSTALLED* -69 (22)-------------------
SPARE -70 REFSPARE -71 APPX
(I) SPEED BRAKES DEPLOYED* -72 (22)------------------- A/C WIRING ~cSPARE -73
(1) WEIGHT ON WHEELS* -74 (22)------------------- A/C WIRINGSPARE -75SPARE -76SPARE -77
(I) GEAR DOWN* -78 (22)------------------- A/C WIRING(I) MAINTENANCE TEST ENABLE* -79 (22)------------------- APPENDIX D
SPARE -80(0) TRIM DISENGAGE ANNUN -81 (22)------------------- APPENDIX 0,
(28v/opEN)(I) PWR UP RESET GND INPUT A-82 (22)------------------- 2
SPARE -83SPARE -84SPARE -85SPARE -86SPARE -87
(o) PILOT/COPILOT*CPL -88 (22)------------------- 9J1A-93,SELECT OUT (OPEN/GND) C9J1A-93,
1OJ2B-88,APPX C
(0) ~~A:lN VALID (28V/OPEN) -89 (22)------------------- 11J2-69-90
SPARE -91SPARE C1OJ2B-92
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.54Feb 1/88
Use or disclosure of mformatlon on thts page IS sublect fo the restncllons on the title page of this document
Flight Guidance Computer No. 2
IOB~ Function Connector Pin Connects To
SPARE C1OJ2B-93(I) PITCH THUMB WHEEL (H)
t
-94 (22)----fi- ----------- ;;::~-;;4,
(I) PITCH THUMB WHEEL (L) -95 (22)----!;------------ :10J2B 105,
i
129J1-22(0) PANEL STROBE (H) -96 (22)----;- ----------- 11J2-5(o) (L) -97 (22)-----
x----------- 11J2-6
(0) PANEL CLOCK (H) -98 (22)-----t----------- 11J2-3
(o) (L) -99 (22)---JJ ----------- 11J2-4
(0) GP SERIAL DATA REC (H) -100 (22)--.~r+----------- ;~:;-~(o) (L) -101 (22)---U- ----------- -
(I) GP SERIAL DATA TRANS (H) -102 (22)----~$----------- 11J2-1
(I) GP SERIAL DATA TRANS (L) -103 (22)---~ ----------- 11J2-2
(I) ;fio): PITCH THUMB (H) -104(22)----fi
t
----------- 1OJ2B-94,129J1-18
(I) ;~~;~ PITCH THUMB (L) -105 (22)--J;- ----------- 1OJ2B-95,SHIELD GND----- 129J1-19
(I) GP BUTTON ARM C1OJ2B-106 (22)------------------ 11J2-38#2 (GND/OPEN)
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.55Mar 15/91
Use or dwclosure of mformatlon on this page IS subler to the restncllons on the title page of thw document
Radio Altimeter No. 2
IOB& Function Connector Pin Connects To
SPARE C20J1-ASPARE -BSPARE
(I) TEST INHIBIT* :: ------NC APPX C(I) OUTPUT TEST -E (22)-------------------- c20J1-N,
C1OJ2B-27,IOJ2A-37,137J1A-51APPX C
(o) TRACK INVALID -F ------NCSPARE -GSPARESPARE 1SPARE -K
(o) TRIP NO. 4 (400 FT) ------NC(P) +/- 15 V DC COMMON :; ------NC ~(0) OUTPUT COMMON
1’
-N (22)-------- --$-- --- C20J1-E,
~1 ~: C1OJ2B-27,1OJ2A-37,~1 ,1 137J1A-51,
(0) ALT TRIP COMMON -P ------Nc :! ,, APPX L(0) ~$j[ENO. 3 (50 FT) -R ------NC ,1 t~
-s 11(I) TEST* -T (22)-----;;- --41------- C134J1A.95,
14 APPX C(0) TRIP NO. 1 (1200 FT) -u .-----NC ~: II(0) TRIP NO. 2 (250 FT) ------NC ,1 ~{(0) ALT OUTPUT (EH) :: (22)-----y- --,{------- C1OJ2B-26,
SHIELD GND------------ 11 1OJ2A-36,II 137J1A-50
(0) AUX OUTPUT (H)II
-X (22)-----------ti------- APPX L(0) RAD ALT VALID (28V/OPEN) -Y (22)-------------------- ;;~;;B;;8,
137J1B-13,APPX C,APPX L
(P) +15 V DC -z ------NC(P) -15 V DC -a ------NC(P) POWER GND -b (NOTE 3)---------------- A/C PWRGND(P) +27.5 V DC C20J1-C (NOTE 3)---------------- A/C 28VDC PWR
~: FOR FURTHER INFORMATION ON THE RADIO ALTIMETER SYSTEM, PLEASE REF:AA-300, O& I MANUAL, PUB. No. 15-3321-06.
— ——. .—Interconnect information
Table 501 (cent) 22-14-00Page 598.56
Apr 15/93
Use or disclosure of information on this page is subject to the restrictions on the title page of this document.
Radio Altimeter No. 2
106_P_ Function Connector Pin Connects To
(o) TRANSMIT C20J2 * ---------
?
------- C21J1 COAX TO TRANSMIT
------ ANTENNA(1) RECEIVE C20J3 * ---------0------- C22J1 COAX TO RECEIVE
L----- ANTENNA
*MATING CONNECTOR SPERRY PART NO. 4008064, GRFF4007-OO02 (ST)SPERRY PART NO. 4008065, GRFF41OO-OOO1 (RT ANGLE)
Interconnect InformationTable 501 (cent) 22-14-00.—
Page 598.57Jun 1/87
Useor disclosure of mformatton on this page IS sublet to the reslnctlons on the title page of this document
IOB~
(o)(o)(I)(P)(P)
(P)
(P)(P)
(P)
(P)
(o)
(I)
Weather Radar Controller No. 2
Function Connector Pin
SERIAL CONTROL (H)$
C61J1-A (22)--------fi-- ------ ---
SERIAL CONTROL (L) -B (22)-------
SHIELD GND Y- ----------M (22)--------CONTROL PANEL GND -c (20)---------------------28 VDC POWER -D (20)---------------------
28 VDC PWR RTN ~; (20)---------------------SPARE28 V PANEL LIGHTING -G ------NC5 V PANEL LIGHTING -H (20)---------------------
LIGHTING COMMON -J (20)---------------------
PUSHBUTTON 28V LIGHTING -K (22)---------------------
RESERVED -LR/T ON/OFF (GND/OPEN) -N (20)---------------------
FORCED STANDBY * -P (22)---------------------
SPARE C61J1-R thru U
Connects To
59J1-a59J1-b
CHASSIS GND28VDC, A/CPWRA/C PWR GND
A/C 5VLIGHTINGA/C LIGHTINGGNDA/C 28VLIGHTING
59J1-U,C61J1-N,65J1B-20,C65J1B-20,E65J1B-20A/C WOWSWITCH
Interconnect InformationTable 501 (cent) 22-14-00
Page 598,58Apr 15/93
Use or disclosure of information on this page is subject to the res rictions on the title page of this document,
Weather Radar Controller No. 2
IOB_P_ Function Connector Pin Connects To
(0) RANGE A C61J2-A (22)-------------------- FIGURE D-4.2
(o) RA[;; : -B (22)-------------------- FIGURE D-4.2
(o) -C (22)-------------------- FIGURE D-4.2
(0) RANGE D -D (22)-------------------- FIGIJRE D-4.2
(0) FPLN SELECTED (GND/OPEN) -E (22) ------ ------------- FIGURE D-4.2(I) WX INT (H)
f
-F (22)---fl--------------- 131J1-2(0) WX INT (W) -G (22)------ ------------- 131J1-15(I) WX INT (L) -H (22)------ ------------- 131J1-3(I) PROGRAM RANGE A -J (22)-------------------- A/CWIRING(I) PROGRAM RANGE B
}
-K (22)-------------------- A/CWIRINGAPX(I) PROGRAM RANGE C -L (22)-------------------- A/CWIRING C(I) PROGRAM RANGE D -M (22)-------------------- A/CWIRING(I) PROGRAM RANGE COMMON -N (22)-------------------- A/CWIRING
RESERVED(o) ID PROG COMMON :[ (22)-------------------- C61J2-S(I) ID PROG -S (22)-------------------- C61J2-R
SPARE C61J2-T thru U
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.59Apr 15/93
Use or disclosure of information on this page issubject to the restrictions onthe title page of this document
Symbol Generator No. 2
IOB~ Function Connector Pin Connects To
(B) WX CNTL (H)$
C65J1A-1 (22)-----fi- ----------- 59J1-e,E65JlA-l(B) DATA #2 (L) -2 (22)-----U- ----------- 59J1-f,E65JlA-2(P) 28VDC PWR -3 (NOTE 3)---------------- A/CDC PWR(P) PURGND -4 (NOTE 3)---------------- A/CDC PWRGND(P) SIGNAL GND -5 (22)-------------------- SIGNAL GND
RESERVED -6RESERVED -7RESERVEDRESERVED ::SPARE -lo
(I) SG I.D. ; -11------NC(I) -12 (22)------------------- C65J1B-50 REF(0) BC VALID (GND/OPEN)
}-13 (22)------------------- 134J1A-98, APPX
C134J1A-98 C(1) TCAS INSTALLED* -14 (22)------------------- APPX L REF(I) LX POWER ON* 1-15 (22)------- ----------- APPX F APPXC
~(B) SYSASCB PRIMARY BUS (H) -16 (22)----fi ----------- SEE SECTION 3.3(B) SYSASCB PRINARY BUS (L) ~;~ ~~~~lN;-~- -----------(0) SPARE
)
RESERVED -19(I) P870 INSTALLED* -20 (22)------------------- SIGNAL GND,
APPX CSPARE -21
[;] SG/DU BUSA (H) -22 (22)----n $., SEE APPENDIX A(L) -23 (22)----U- ----------- FIG. 3B
RESERVED -24(I) NACHTAPE DISABLE* -25 ------NC(1) ILS/MLS* #1 SEL -26 (22)------------------- APPENDIX D(I) FPLN SEL*
1
-27 (22)------------------- APPENDIXD(I) RANGE SELECTA -28 (22)------------------- APPENDIX DREF(I) RANGE SELECT B ~;; ~;;]------------------- APPENDIX DAPPX(I) RANGE SELECT C ------------------- APPENDIXD C(I) RANGE SELECTD -31 (22)------- ----------- APPENDIX D(B) ADF NO. 1 (H)
$}
-32 (22)----~- -----------ARINC 429 ADF NO. 1
(B) ADF NO. 1 (L) -33 (22)----’:- ----------- ARINC 429ARINC 429
(6) DNE NO. 1 ARINC 429 (H) -34 (22)----n(B) DNE NO. 1 ARINC 429 (L) $-----------] ‘E ’001-35 (22)----U- ----------- ARINC 429
$(B) TA/RA NO. 2ARINC 429 (H) -36 (22)---------n- ------ APPX L(B) TA/RA NO. 2 C65J1A-47 (22)---------~- ------ Appx L
ARINC 429 (L)
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.60Apr 15/93
Use or disclosure of information on this page issubject to the resrictions on thetitle pageof this document.
Symbol Generator No. 2
IOB&
(B)(B)(B)
(B)
(B)(B)(B)(B)(B)(B)(B)(B)(o)(B)(B)(B)(B)(B)(B)
(I)
(I)
EuKtiu! Connector Pin Connects To
ARINC 429 (H) C65J1A-37 ------NCARINC 429 (L) -38 ------NCDADC NO. 1 ARINC 429 (L) -39 (22)-----R
i
---------- E65J1A-39,9J1B-70
DADC NO. 1 ARINC 429 (H) -40 (22)-----:- ---------- E65J1A-40,
[/
9J1B-71VOR NO. 1 ARINC 429 (L) -41 (22)-----R-- ---------- VORNO. 1VORNO. 1 ARINC4;;I(H) -42 (22)-------- ---------- ARINC 429MLS/ILS NO. 1 -43 (22)-----~- ---------- APPENDIXDARINC 429 (L) -44 (22)-----lJ- ----------SG/DU WXR BUS (H) -45 (22)----fi- ---------- SEE APPENDIX A;~{D[oWX; BUS (L) -46 (22)----J1-
X.----.----
(H) -48 (22)---- - ---------- 170J1B-K12ARINC ~29 (L) -49 (22)------- ---------- 170J1B-K13PROG PIN GND OUT -50P-870 WX (H) -51 ------NCCNTL DATA #1 (L) -52 ------NCLX OR TACANARINC 429 (H) -53 (22)------------------- APPX F, APPXMLX OR TACANARINC 429 (L) -54 (22)------------------- APPX F, APPXMBC ASCB PRIMARY (H) -55 (22)----fi-
$ 1---------- SEE SECTION 3.3
BC ASCB PRIMARY (L) -56 (22)----U- ----------SPARE -57RESERVED -58SG PWR DN* -59 (22)------------------- A/C WIRING,
C65J1A-61,E65J1A-61,65J1A-61,134J1A-42,C143J1A-42,APPENDIX B& C
SG1 REV* C65J1A-60 (22)------------------- A/CWIRING,E65J1A-60,65J1A-60,134J1A-41,C134J1A-41,65J1A-59,APPENDIX B &C
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.61Apr 15/93
Useordisclosure ofinformation on this page is subject ‘otherestrictions onthetitle page of this document.
Symbol Generator No. 2
IOB~ Function Connector Pin Connects To
(I) SG2 REV* C65J1A-61 (22)------------------- A/C WIRING,E65J1A-61,65J1A-61,134J1A-42,C134J1A-42,C65J1A-59,APPENDIX B & C
(I) SG3 REV* -62 (22)------------------- A/CIIIIRING,E65J1A-62,65J1A-62,134J1A-43,C134J1A-43,E65J1A-59,APPENDIX B & C
(I) DUI REV* -63 (22)------------------- A/CUIRING,E65J1A-63,65J1A-63,134J1A-44,C134J1A-44,APPENDIX B & C
(I) DU3 REV* -64 (22)------------------- A/cWIRING,E65J1A-64,65J1A-64,134J1A-46,C134J1A-46,132J1-22,APPENDIX B & C
(I) DU4 REV* C65J1A-65 (22)------------------- A/CWIRING,E65J1A-65,65J1A-65,134J1A-47,C134J1A-47,133J1-22,APPENDIX B &C
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.62Mar 15/91
Use or disclosure 01 mformatlon on this page IS sub)ecl to the restnctlons on the title page of ths document.
10BP Function
Symbol Generator No. 2
Connector Pin Connects To
(I) DU6 REV* C65J1A-66 (22)------------------- A/C WIRING,E65J1A-66,65J1A-66,134J1A-49,C134L?1A-49,APPENDIX E & C
(1) LX INSTALLEC* C65J1A-67 (22)------------------- APPX F, APPX C
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.63Feb 1/88
Use or dwclosure ot mformal!on on this page IS subpct to the restrictions on the title page of this document
Symbol Generator No. 2
IOB_P_ Function Connector Pin Connects To
(I) BC TEST REQUEST C65J1B-1 (22)-------------------- 65J1B-1,NO. I* E65J1B-1,
134J1A-96(I) BC TEST REQUEST NO. 2* -2 (22)-------------------- 65J1B-2,
E65J1B-2,C134J1A-96
RESERVED -3RESERVED -4
(P) CHASSIS GND -5 (22)-------------------- CHASSIS GND(P) 28 V DC PWR (BC) (H) -6 (22)-------------------- A/C 28VDC PWR
(L) -7 (22)------------ ------- A/C PWRGND(B) IRS #3 ARINC 429 [~]
8~~ [;;]--------fl-- ------- E170J1B-K12
(B) ---------- -u
------- E170J1B-K13SPARE -lo
(I) BC I.D. A -11 ------NC
}
REF(I) B -12 (22)------------------- C65J1B-50APPX
(B) LASERTRAK ARINC 429 (H) n*
-13 (22)”------ -- ------- 198J3-24 (O;T)(B) ~M;~TRAK ARINC 429 (L) -14 (22)-------;-- ------- 198J3-25 (OPT)
-15(B) SYS ASCB (H)
$]-16 (22)---------- ------- REF SEC. 3.3
(B) SECONDARY BUS (L) -17 (22)-------~- -------RESERVED -18RESERVED -19
(1) WX ON* -20 (22)------------------- :;;;y,N61J1-N,
C65J1B-;O,E65J1B-20,APPX C
RESERVED -21(B) SG/DU BUS B (H)
$]-22 (22)-------O-- ------- SEE APPENDIX A
(B) (L) -23 (22)-------U-- -------(1) COMPARATOR MONITOR RESET* -24 (22)------------------- APPENDIX D,
}(1) COMPARATOR MONITOR DISABLE*-25 (22)------------------- A/C WIRING REF(I) ILS/MLS* #2 -26 (22)------------------- APPENDIXD, APX(1) :;A~g c -27------NC c
-28RESERVED -29
(B) RESERVED C65J1B-30
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.64Apr 15/93
Use or disclosure of information on this page is subject to the restrictions on the title page of this document
I
I
IOBP
(B)(B)(B)
(B)(B)
(B)(B)(B)(B)(B)(B)(B)(B)
(B)(B)(B)(B)(o)(o)(o)
(o)(I)(I)(I)(I)(I)(I)(I)(I)(I)
(o)
(I)
Symbol Generator No. 2
Function Connector Pin Connects To
RESERVED C65J1B-31ADF NO. 2 (H)
t----------] ‘DF ‘O. 2-32 (22)----fi--
ARINC 429 (L) -33 (22)-----H-- ---------- ARINC 429
DME NO. 2 ARINC 429 (H)$----------] ‘E‘02
-34 (22)----fi--DME NO. 2 ARINC 429 (L) -35 (22)----{-- ---------- ARINC 429RESERVED -36MX VIDEO DATA (H)
\
-37 (22)----fl-- ---------- 59J1-k(L) -38 (22)---- -x ----------59J1-s
DADC NO. 2 (H) -39 (22)---- -- ---------- C9J1B-26ARINC 429 (L) -40 (22)----J’-
H----------- C9J1B-27
VOR NO. 2 ARINC 429 (H) -41 (22)----
1
---------- VORNO. 2VOR NO. 2 ARINC ~;; (L) -42 (22)----l’-
F
---------- ARINC 429t4LS/ILSNO. 2 -43 (22)---- - ---------- APPENDIX DARINC 429 (L) -44 (22)----J- ----------RESERVED -45BC ASCB SECONDARY (H) -46 (22)----fi-
i
1---------- SEE SECTION 3.3
(L) -47 (22)----~- ----------IRS NO. 2 (H) -48 (22)---- -
f? ---------- C170J1B-E5ARINC 429PROG PIN ~ND of;) -49 (22)----~- ---------- cl OJIB-E6A-50 (22)------------------- 1SG VALID OUT (GND/OPEN) -51 ------NCSG OVERTEMP OUT (GND/OPEN) -52 (22)------------------- 134J1A-52,
C134J1A-52,SEE APPENDIX C
BELOW DH OUT (GND/OPEN) -53UEIGHT ON WHEELS* -54 (22)------------------- A/C WIRING1JOYSTICK FORE* -55 (22)------------------- APPENDIx DJOYSTICK AFT* -56 (22)------------------- APpENDIx DJOYSTICK LT* -57 (22)------------------- APPENDIx D REFJOYSTICK RT* -58 (22)------------------- APPENDIx D APPXJOYSTICK ENTER* -59 (22)------------------- APPENDIx D cJOYSTICK CLEAR* -60 (22)------------------- APPENDIx D ~WX FAULT* -61 (22)------------------- APPENDIx DWX TARGET ALERT* -62 (22)------------------- APPENDIx DRESERVED -63RESERVED -64CS HDG SRC DISPLAYED -65 (22)------------------- A/c UIRING(GND/OPEN)MAINTENANCE TEST GND -66 (22)------------------- APPENDIx DRESERVED C65J1B-67 I
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.65Apr 15/93
Use or disclosure of information on this page is subject to the restrictions on the title page of this document.
I
I9
I
Symbol Generator No. 3
IOB_P_ Function Connector Pin Connects To
(B) WX$
(H) E65J1A-1 (22)----fi-- ----------- C65JlA-l,59Jl-e(B) CNTL DATA #2 (L) -2 (22)----U-- ----------- C65JlA-2,59Jl-f(P) 28 V DC PWR -3 (NOTE 3)---------------- A/CDC PWR(P) PWR GND -4 (NOTE 3)---------------- A/CDC PWRGND(P) SIGNAL GND -5 (22)-------------------- SIGNAL GND
RESERVED -6RESERVED -7RESERVED -8RESERVED -9SPARE -lo
(1) SG I.D. : -11 (22)------------------- E65J1B-50 REF(I)
1
-12 (22)------------------- E65J1B-50 APPX(0) BC VALID (GND/OPEN) -13 (22)------------------- 134J1A-99, c
C134J1A-99(I) TCAS INSTALLED* -14 (22)------------------- APPXL REF(I) LX POWER ON* )-15 (22)------- ----------- APPX F APPXC
$(B) SYS ASCB PRINARY BUS (H) -16 (22)----R-- ----------- SEE SECTION 3.3(B) SYS ASCB PRIMARY BUS (L) d: (22)----U-- -----------1(0) SPARE ------NC
RESERVED -19(I) P870 INSTALLED* -20 (22)--------,----------- APPXH, APPXC
SPARE -21(B) SG/DU BUS A (H) -22 (22)---:(B) (L)
--$::::::::::] SEE APPENDIXA-23 (22)---u--
RESERVED -24(I) MACH TAPE DISABLE* -25 ------NC(I) ILS/MLS* #l SEL -26 (22)------------------- APPENDIX D(I) FPLN SEL*
I
-27 (22)------------------- APPENDIX D(I) RANGE SELECT A -28 (22)------------------- APPENDIX D REF(I) RANGE SELECT B -29 (22)------------------- APPENDIX D APPX(I) RANGE SELECT C -30 (22)------------------- APPENDIX D C(I) RANGE SELECT D -31 (22)------- ----------- APPENDIX D(B) ADF NO. 1 (H)
!}
-32 (22)---fi-- ----------- ADF NO. 1ARINC 429 ARINC 429
(B) ADF NO. 1 (L) -33 (22)---:-- -----------ARINC 429
(B) DME NO. 1 ARINC 429 (H) -34 (22)---fi(B) ME NO. 1 ARINC 429 (L)
--$----.--] ~ENOo~-35 (22)---U-- ----------- ARINC 429
*(B) TA/RA NO. 1 ARINC 429 (H) -36 (22)----------n- ---- APPX L(B) TA/RA NO. 1 E65J1A-47 (22)---------+ ---- APPX L
ARINC 429 (L)
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of information on this page is subject to the restrictions on the title page of this document
106~
(B)(B)(B)
(B)
(B)(B)(B)(B)(B)(B)(B)(B)(o)(B)(B)
(B)(B)(B)(B)
(I)
(I)
Symbol Generator No. 3
Function Connector Pin Connects To
ARINC 429 (H) E65J1A-37 ------NCARINC 429 (L) -38 ------NCDADC NO. 1 ARINC 429 (H)
t
-39 (22)----C- ----------- C65J1A-39,9J1B-70
DADC NO. 1 ARINC 429 (L) -40 (22)----:- ----------- C65J1A-40,
~1
9J1B-71VOR NO. 1 ARINC 429 (H) -41 (22)----A- ----------- VOR NO. 1VORNO. 1 ARINC 4~;l(L) -42 (22)----11- ----------- ARINC 429MLS/ILS NO. 1 -43 (22)----fi- ----------- APPENDIXDARINC 429 (L) -44 (22)----!!- -----------SG/DU WXR BUS (H) -45 (22)----K- ----------- SEE APPENDIX A;;~DIJoWX~BUS (L) -46 (22)----!1- -----------
(H) -48 (22)----K ----------- 170J1B-F14ARINC 429 (L) -49 (22)----:-- ----------- 170J1B-F15PROG PIN GNDOUT -50Ux (H)
$-51 (22)---*-- ----------- 59J1-m,65JlA-51
CNTL DATA #l (L) -52 (22)------- ----------- 59J1-n,65JlA-52
LX OR TACAN ARINC 429 (H) -53 (22)------------------- APPX F, APPX MLX OR TACAN ARINC 429 (L) 4: ~;;]---h -------------- APPX F, APPX MBC ASCB PRINARY (H)
~----------- SEE SECTION 3.3
BC ASCB PRINARY (L) -56 (22)~~~{~- -----------1SPARE -57RESERVED -58SG PWR DN* -59 (22)------------------- A/C WIRING,
E65JIA-62,65J1A-62,C65J1A-62,134J1A-43,C134J1A-43,APPENDIX B & C
SG1 REV* E65J1A-60 (22)------------------- lll~l~I~;NG,
C65Jl~-6&,134J1A-41,C134J1A-41,65J1A-59,APPENDIX B & C
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of information on this page issubject to the restrictions onthe title page of this document,
Symbol Generator No. 3
IOB_P_ Function Connector Pin Connects To
(I) SG2 REV* E65J1A-61 (22)------------------- A/C WIRING,65J1A-61,C65J1A-61,134J1A-42,C134J1A-42,C65J1A-59,APPENDIX B & C
(I) SG3 REV* -62 (22)------------------- A/CWIRING,65J1A-62,C65J1A-62,134J1A-43,C134J1A-43,E65J1A-59,APPENDIX B & C
(I) DU1 REV* -63 (22)------------------- A/CWIRING,65J1A-63,C65J1A-63,134J1A-44,C134J1A-44,APPENDIX B & C
(I) DU3 REV* -64 (22)------------------- A/CWIRING,65J1A-64,C65J1A-64,134J1A-46,C134J1A-46,132J1-22,APPENDIX B & C
(I) DU4 REV* E65J1A-65 (22)------------------- A/cWIRING,65J1A-65,C65J1A-65,134J1A-47,C134J1A-47,133J1-22,APPENDIX B & C
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of mformatlon on this page IS sub]ect 10 the restrictions on the Mle page of thm document
IOBP Function
Symbol Generator No. 3
Connector Pin Connects To
(I) DU6 REV* E65J1A-66 (22)------------------- A/C WIRING,65J1A-66,C65J1A-66 ,134J1A-49,C134J1A-49,APPENDIX B & C
(I) LX INSTALLED* E65J1A-67 (22)------------------- APPX F, APPX C
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of mformatlon on Ihm page IS subject 10 the restrictions on the tnle page of this document.
I
I
IOB~
(I)
(I)
(P)(P)
(P)(B)(B)
(I)(I)
(B)(B)
(B)(B)
(I)
(B)(B)
(I)(I)(I)(1)
(B)(B)
Symbol Generator No. 3
Function Connector Pin Connects To
BC TEST REQUEST E65J1B-1 (22)-------------------- 65J1B-1,NO. 1*
BC TEST REQUEST NO. 2*
RESERVEDRESERVEDCHASSIS GND28V DC PWR (BC)
28V DC GND (BC)IRS #3 ARINC 429 (H)
(L)SPAREBC I.D. A
B
LASERTRAKARINC 429 (H)LASERTRAKARINC 429 (L)SPARESYS ASCB (H)SECONDARY BUS (L)RESERVEDRESERVEDWX ON*
RESERVEDSG/DU BUS B (H)
(L)
C65J1B-1,134J1A-96
-2 (22)-------------------- 65J1B-2,C65J1B-2,C134J1A-96,
-3
:: (22)-------------------- CHASSIS GND-6 (22)-------------------- A/C 28VDC PWR
-7 (22)------- ------------ A/C PWRGND
$-8 (22)----~- ------------ E170J1B-F14-9 (22)----U- ------------ E170J1B-F15-lo-11 (22)------------------- E65J1B-50REF-12 (22)------------------- E65J1B-50APPX
+-13 (22)---fi- ------------ 198J2-24 (O:T)-14 (22)---U- ------------ 198J2-25 (OPT)-15-16 (22)---A
*------------ REF SEC. 3.3
-17 (22)---: ------------1-18-19-20 (22)------------------- 59J1-U, 61J1-N,
C61J1-N,65JIB-20,C65J1B-20,APPX C
-21
$-22 (22)---O- ------------ SEE APPENDIX A-23 (22)---V- ------------1
COMPARATOR MONITOR RESET* -24 (22)------------------- APPENDIXDCOMPARATOR MONITOR ENABLE* -25 (22)------------------- A/C WIRINGILS/MLS* #2 -26 (22)------------------- APPENDIXDSG ID C -27 (22)------------------- E65JlB-50SPARE -28RESERVED -29RESERVED -30RESERVED E65J1B-31
REFAPPX
c
Interconnect InformationTable 501 (cent) 22-14-00
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Use of disclosure of information on this page is subject to the ret Irictions on the title page of this document,
I
I
106~
(8)
(B)
(B)(B)
(B)(B)(B)
(B)
(B)
(B)
(B)(B)
(B)(B)(B)(B)
(0)(o)(o)
(o)(1)(1)(I)(I)(1)(1)(1)(I)(1)
Symbol Generator No. 3
Function Connector Pin Connects ToI
ADF NO. 2 (H)
t}
E65J1B-32 (22)---;--- ----------ARINC 429 ADF NO. 2ADF NO. 2 (L) -33 (22)---:--- ---------- ARINC 429ARINC 429DME NO. 2 ARINC 429 (H) -34 (22)----RDME NO. 2 ARINC 429 (L)
--$,,,,,,,:,,] ;;:O,;-35 (22)------
RESERVEDWX VIDEO DATA (H)
(L)DADC NO. 2 (H)
ARINC 429 [L]
-36-37 (22)---fJ--
!
---------- 59JI-i-38 (22)---jt--- ---------- 59J1-j
A-39 (22)---,,--- ---------- 65JIB-39,C9J1B-70
-40 (22)---$- ---------- 65J1B-40,. .
i}
C9J1B-71’VOR NO. 2 ARINC 429 (H) -41 (22)---fi-- ---------- VOR
NO. 2 ARINC 429VORNO. 2ARINC 429 (L) -42 (22)---ti-- ---------e
1MLS/ILS NO. 2 (H)
*-43 (22)------ 1----------APPENDIX D
ARINC 429 (L) -44 (22)---:-- ----------RESERVED -45BC ASCB SECONDARY [~j
$
-46 (22)---fi--1
----------- SEE SECTION 3.3-47 (22)---~’--
%------------
IRS NO. 2 (H) -48 (22)--- ---------- C170J1B-F14ARINC 429 (L) -49 (22)---:-- ----------- cl OJIB-F15PROG PIN GND OUT A-::1(22)------------------- 1SG VALID OUT (GND/OPEN) ------NCSG OVERTEMP OUT (GND/OPEN) -52 (22)------------------- 134J1A-53,
C134J1A-53,SEE APPENDIX C
BELOW OH OUT (GND/OPEN) -53WEIGHT ON WHEELS* -54 (22)------------------- A/C WIRINGJOYSTICK FORE* -55 (22)------------------- APPENDIX OJOYSTICK AFT*
I
-56 (22)------------------- APPENDIX DJOYSTICK LT* -57 (22)------------------- APPENDIXD REFJOYSTICK RT* -58 (22)------------------- APPENDIX DAPPXJOYSTICK ENTER* -59 [22)------------------- APPENDIX D CJOYSTICK CLEAR* -60 (22)------------------- APPENDIX DWX FAULT* -61 (22)------------------- APPENDIXDWX TARGET ALERT* -62 (22)------------------- APPENDIXDRESERVED E65J1B-63
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of information on this page is subject :0 the restrictions on the title page of this document,
Symbol Generator No. 3
10BP Function Connector Pin Connects To
RESERVED E65JIB-64(0) CS HDG SRC DISPLAYED -65 (22)------------------- A/C WIRING
(GND/OpEN)(I) MAINTENANCE TEST GND -66 (22)------------------- APPENDIX D
RESERVED E65J1B-67
Interconnect InformationTable 501 (cent) 22-14-00
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Use or dwclosure of mformatlon on this page IS sublect 10 the r?strlctlons on Ihe Mle page of lhm document
Display Controller No. 2
(P)(P)
(P)(P)(P)(P)
(I)(I)(B)(B)
(P)(P)(I)
(I)
(I)
(I)(I)(I)
Function Connector Pin Connects
28 V DC POWER C115J1-A (NOTE 3)---------------- A/C 28VDC28 V DC POWER RTN -B (NOTE 3)---------------- A/C 28 VDCRTN
$PANEL DIMMING CONTROL (H) -C (22)------- ------------ A/c 5VDCPANEL DIMMING CONTROL (L) -D (22)------- ------------ LIGHTING CNTLSIG GROUND -E (22)-------------------- A/C SIGGNDCHASSIS GROUND -F (22)-------------------- CHASSIS GNDSPARE -GSPARE -HSPARE -JSPARE -KSPARE -LRESERVED -M I
!ANNUN DIMMING (L)
+-N (22)-- ---------------- A/C 5VDC
ANNuNDIMMING5V (H) -P (22)-- ---------- ------
$]
ANNUN DIMMING iSYSASCB PRIMARY BUS (H) -R (22)---------Q-- ------ SEE SECTION 3.3 ;
(L) -s (22)---------JJ-- ------RESERVED TEST -TRESERVED TEST -uANNUNCIATORPWR (H) -V (22)-------------------- A/C 28VDC
(L) -W (22) -------------------- POWERDAY/NIGHT (OPEN/28 V DC) -X (22)-------------------- DAY/NIGHT
ANNUN DIMMINGDISCRETEAPPENDIX C
RESERVED TEST -YSPAREFGC LEFT PRIORITY :: (22)-------------------- 1OJ1A-37,(28V/OPEN) llJ1-70,
l15J1-a,APPX C
FGC RIGHT PRIORITY -b (22)-------------------- UKJ;l;~37,(28V/OPEN)
l15J;-b;APPX C
ARINC ILS INSTALLED* -c (22)-------------------- A/C WIRING REFMLS INSTALLED* -d (22)-------------------- APPX K
}APPX
SPARE Cl15J1-e (22)-------------------- c
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of information on this page is subject to the restrictions on the title pag$ of this document,
I
I
I
IOB&
(I)
(1)(I)(1)(I)(r)(I)(I)(1)
(I)
(o)
(o)
(1)
(1)
(I)
(o)
(o)
(o)
Display Controller No. 2
Function Connector Pin Connects
SPARE Cl15J1-f ------NC 8
PILOT/COPILOT* -g (22)------------------- A/C SIG GN[IRS TRIPLEX/DUAL* -h ------NCLTRK INSTALLED* -i (22)------------------- A/C WIRINGTCAS INSTALLED* -j (22)------------------- APPX Lwow* -k (22)------------------- A/C WIRINGTCAS RA -m (22)------------------- APPX LRESERVEDEMER CHECKLIST SELECT* ~~ (22)------------------- l15J1-p,
CHECKLIST ENABLE*
SPARESPARESPARESPARESUBTEST SELECT(GND/OPEN)
SPARESPARESPAREFGC RIGHT PRIORITYSELECT (GND/OPEN)MAINT. TEST ENABLE*
CALIB/TESTSPARELAMP TEST*
SPARElLS/MLS SELECT OUT(GND/OPEN)NAV RETUNE
FGC LEFT PRIORITYSELECT (GND/OPEN)
134JIA-103,C134J1A-103
-q (22)------------------- l15J1-q,134J1A-104,C134J1A-104,
-r
::-u-v (22)-------------------
-w-x
:: (22)-------------------
-AA (22)------------------
-BB ------NC-cc-DD (22)------------------
-EE-FF (22)------------------
-GG (22)------------------
C115J1-HH (22)------ ------------
REFAPPXc
REFAPPX
c
}
IIJ1-35, REF11J2-35, APPX C115J1-v
11J2-62
APP D, REF APP C
REF APPENDIX C
A/C WIRING,REF APPENDIX C
APPENDIX D,REF APPENDIX CAPPX K,REF APPX C11J2-61
Interconnect InformationTable 501 (cent) 22-14-00
Page 598,74Apr 15/93
Lk+eorctisclosure of intormationon this page issubject to the restrictionson the title page of this document
IOB~
(B)(B)
(I)(o)(I)
(I)
(1)
(I)
(I)
(1)
(I)
Display Controller No. 2
Function Connector Pin ConnectS
SYS ASCBt
(H) C115J21~ [~:]---:>1-------------- )SEESECTION 3.3SECONDARY BUS (L) ------- ------------.,SPARESPARESPARESPARESPARESPARESPARESPARE
BARO SET(H)(w)(L)
SPAREPHOTO SENSOR #l
PHOTO SENSOR #2
PHOTO SENSOR #3
(H)
(L}
(H)
(L)
(H)
-c ‘--D-E-F
:!-J-K
1
-L (22)----:;- ------------ C9J1A-35-M (22)---1--,------------- C9J1A-36-N (22)----C-- ------------ C9J1A-37
SHIELD GND ---
-P
1
-R (22)----~~1-------------
-s (22)---J{;- ------------
I
-T (22)----:;- ------------
-u (22)---J<-- ---------”--
1
C130J1-28,C131J1-29C130J1-41.
C130J1-42,C131J1-41
T-V (22)---:2( ------------ 130J1-26,C130J1-26,
II
1131J1-26,”
(1C131J1-26,132J1-26,
II 133J1-26,II 115J2-V, REMOTE
~~o;fN~~R (H)PHOTO SENSOR#3 (L) C115J2-W (22)----!-;-------------
C130Ji-2;,131J1-27,C131J1-27,132J1-27,133J1-27,115J2-W, REMOTELT SENSOR (L)
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of Information on this page IS sub]ec[ to the restncttons on the title page of Ihm document
[OBy_
(I)(I)
(r)
(I)(I)(I)
Functioq
SPARESPARESPARESPARESPARECRS SEL #l (H)
(L)
CRS SEL #l SYNC(GND/OPEN)SPARECRS SEL #2 (H)
(L)CRS SEL #2 SYNC(GND/OPEN)
Display Controller No. 2
Connector Pin Connects
C115J2-X-Y-z-a-b
i-c (24)--1’-T-T------.-----. llJ1-32, 115J2-c-d (24)---C~- ------------- IIJ1-33, l15J2-d
-e (24)-------------------- IIJI-36, I15J2-e
-f I
-g (24)--f-~-i------------- 11J2-32, l15J2-g
-h (24)-.-C~-------------- 13J2-33, l15J2-hCl15J2-j (24)-------------------- 11J2-36, l15J2-j
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of mformahon on ihm page IS subject to the wslrlcllons on the Me page ot thts oocwnent
IOBy_
(P)[q
(P)(P){P)(P)
(B)(B)
(B)(B)
(B)(B)(B)(B)(B)(B)(B)(B)
(B)(B)
(B)(B)[:]
(B)(B)(o)
CDU NO. 2
Function Connector Pin Connects To
SPARE C120J1’A+28 V DC POWERPOWER RETURNPANEL LIGHTING RTNSPARE28 V ANNUN LIGHTINGCHASSIS GNDANNUN LIGHTING RTN5V KEYBOARD PANEL LTNGRESERVEDSPARERS422 XMTR - (H)(DATA) NAV COMP (L)
RS422 XMTR - (H)(CNTL) NAV COMP (L)
RS422 RCVR - (H)(DATA) NAV COMP (L)RS422 RCVR - (H)(CNTL) NAV COMP (L)RS422 RCVi?- {H)(CLK) NAV COMP (L)RS422 XMTR - (H)(DATA) PERF COMP (L)
RS422 XMTR - (H)(CNTL) PERF COMP (L)
RS422 RCVR - (H)(DATA) PERF COMP (L)RS422 RCVR - (H)(CNTL) PERF COMP [l.]RS422 RCVR -[CLK) PERF COMP (L)CDU VALID(GND/OPEN
-B (NOTE 3)-----------------c (NOTE 3)-----------------D (22)---------------------E-F (20)---------------------G (20)---------------------H(22)-----,----------------J (22)---------------------K
‘Ii(22) ----,=-,--------------N (22)-------- -----------
SHIELD GND---~
t‘P (22)----19:-------------R (22)-------- -----------
SHIELD GND---~
t‘S (22)----17j-------------T (22)-------- -----------
k-u (22)-----X-------------v (22)----!-J------------
t-w (22)-----W-- ------------x (22)----!~J------------
t-Y (22)-------- ------------z (22)----JYJ- -----------
SHIELD GND---
t-a (22)---------.----------b (22)_-\.;- -.---.--.--SHIEiD 6ND---~
i-c (22)--------------------d (22)----!-!------------
t-e (22)-----------.--.-----f (22)----!~-------------
t‘g (22)----i-~---------.---h (22)--------------------. .
C120J1-i (22)--------------------
A/C 28 V DC PWRA/C POWER GNDA/C POWER GND
A/C 28 V DC PWRA/C CHASSIS GNDA/C LTNG GNDA/C LTNG GND
C121J1A-55C121J1A-56
C121J1B-7C121J1B-8
C121J1A-65C121J1A-66C121J1B-32C121J1B-33C121J1B-35C121J1B-36C122J1A-103C122J1A-104
C122J1A-105C122J1A-106
C122J1A-101C122J1A-102C122J1A-99C12J1A-1OOC122J1A-97C122J1A-98C121J1B-1OO,134J1A-76,C134J1A-76
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of mformat!on on this page IS subpcl to the restrictions on the hlle page of thm document
CDU No. 2
10BP Function Connector Pin Connects To
SPARE C120J1-jSPARE -k
(0) R PHOTO SENSOR OUT -m (22)-------------------- TEST ONLYL PHOTO SENSOR OUT -n (22)-------------------- TEST ONLYSPARE -P
(I) DIM CALIBRATION -q (22)-------------------- TEST ONLYSPARE
(I) LAMP TEST*-r-s (22)-------------------- A/C LAMP TEST,
REF APPX CSPARE -tSPARE -u
(1) ANNUN LIGHTING BRIGHT/DIN -V (22)-------------------- A/C WIRING,(OPEN/28V) REF APPX C
(I) ANNUN LIGHTING DIM CONTROL ‘W (22)-------------------- A/C WIRING(0-28vDC)SPARE -xSPARE -YSPARE -zSPARE -AASPARE -BBSPARE -ccSPARE -DD
(I) SELF TEST ENBL* -EE ---”--NCSPARE -FFSPARE -GGSPARE C120J1-HH
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of mformatlon on thts page IS subject 10 the reslrlctlons on the Mle page of !h)s document
Navigation Computer No. 2
IOB~
(P)
(P)
(P)(P)(P)(P)
(B)(B)
(I)
(B)(B)(B)(B)(B)(B)
(B)(B)
(B)(B)(B)
(B)
(B)(B)(B)(B)
(B)(B)
Function Connector Pin Connects To
AIRCRAFT BATT+28V C121J1A-1 (20)-------------------- A/c 28VDCBATTERY DIRECT
SPARE+28 V DC POWER ~; (NOTE 3)---------------- A/C 28VDC PWR
POWER RETURNCHASSIS GROUNDSIGNAL GROUNDAIRCRAFT BATT RETURNRESERVEDRESERVEDSYSASCB PRI BUS (H)~;;R~SCB PRI BUS (L)
RESERVEDNO CLOCK ASCB*
-4 (NOTE 3)---------------- A/C PWRGND-5 (20)-------------------- CHASSISGND-6 (20)-------------------- SIGNAL GND-7 (20)-------------------- A/C POWER GND-8-9
*-lo (22)--fi-- ------------ REF. SECT3.3-11 (22)-4-- -------------12-13-14 (22)------------------- SIGGND,
REF. APPX CSPARE -15ARINC 429 RCVR - (H)
1
-16 (22)--n-- ------------ APPXDMLS/ILS PRIMARY (L) -17 (22)--1!-- ------------ APPXDARINC 429 RCVR - (H) -18 (22)--X-- ------------ DME NO. 2,DME PRIMARY (L) -19 (22)--u--- 1------------ ARINC 429RS422 RCVR - (H) -20 ------NCDME PRIMARY (L) -21 ------NCRESERVED -22ARINC 429 RCVR - (H)
*-23 (22)----- ------------ 149J1-24 (OPT)
LTS #2 (L) -24 (22)------ ------------ 149J1-25 (OPT)RESERVED -25ARINC 429 RCVR - (H) -26 (22)--fi-
$------------ C149J1-38 (OPT)
LTS #1 (L) ~;~ ~;;]--v-a-- --------- ;;fM~li39 (OPT)RS422 RCVR - (H)
!
----- -- ---------11 121Jl~-;8
DATA LOADER (DATA) (L) -29 (22)-----2-- --------- 123J1-S,
RS422 RCVR -NAV PRIMARYARINC 429 RCVR -NAV PRIMARYRESERVED;~I;~~CRS (H)
(L)
121J1A-29(H) -30 ------NC(Lj -31 ------NC
$](H) ~;; [;;~-------fi- -------- VOR NO. 2,(L) ------------- -----
u ARINC 429-34
*-35 (22)-------~- ------- DMUJ1-22 APPX
1C121J1A-36 (22)-------S-- -------- DMUJ1-23 D
Interconnect InformationTable 501 (cent) 22-14-00
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Navigation Computer No. 2
106~ ~ Connector Pin Connects To
RESERVED C121J1A-37RESERVED -38RESERVED -39
(B) RS422 XMTR - (H) -40 ------NC(B) GENERAL BUS #3 (L) -41 ------NC
RESERVED(B) ARINC 429 REC ~p](B) NAV SECONDARY :: ~:;],,fl,*,,,,,,,,,,,,] [:;J04J
(B) ARINC 429 XMTR (H)
t
-45 (22)------+-- -------- 170J1B-C5,E170JIB-C5
(B) GEN BUS SECONDARY (L) -46 (22)------“-- -------- 170J1B-C6,;SHIELD GND--------------- E170J1B-C6
~: GEN BUS SECONDARY OUTPUT ALSO GOES TO THE FOLLOWING:ADF #1, COMM #l, DME #1, ILS #l, MLS #l, VOR #1, AND XPDR#l
(I) HIGH/LOW* SPEED BUS-LTS#l -47 -----NC APPX C(I) HIGH/LOW* SPEED BUS-LTS#2 -48 -----NC APPX C(I) HIGH/LOW* SPEED BUS-LTS#3 -49 -----NC
1
APPX C(B) ARINC 429 XMTR (H) -50 (22)-------:--- ------ 149J1-26 (OPT)
C149J1-18 (OPT)Ittl C170J1B-A8It DNUJ1-24
(APPX D)(B) GEN BUS PRIMARY (L) 121J1A-51 (22)----------- ------ 149J1-27 (OPT)
IC149J1-37 (OPT)C170J1B-A9DMUJ1-25(APPX D)
SHIELD GND---------------
NOTE: GEN BUS PRIMARY OUTPUT ALSO GOES TO THE FOLLOWING:ADF #2, COMM#2, DME #2, ILS #2, MLS #2, VOR #2, AND XPDR #2
I
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.80Apr 15/93
Use or disclosure of information on this page is subject to the restrictions on the title page of this document
Navigation Computer No. 2
IOBLE!dmi!m lonnector pm
.ects To
(B) RS422 XNTR -
t
(H) C121J1A-52 (22)-------?- ------- W~iHg2
(B) DATA LOADER (DATA) (L) -53 (22)-------L!- ------- ;;;j;~&3
SHIELD GND -------------1’SPARE -54
(B) RS422 RCVR - (H)t
-55 (22)---fi------------- C120J1-M(B) ~tl~l~)CDU (L) +; (22)---V- ------------ C120J1-N
RESERVED -58RESERVED -59RESERVED -60RESERVED -61RESERVED -62RESERVED -63RESERVED -64
(B) RS422 XNTR - (H)t
-65 (22)------Q-- ------- C120J1-S(B) (DATA) CDU (L) -66 (22)------J-L--------- C120J1-T
SHIELD GND-------------YRESERVED C121J1A-67
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.81Mar 15/91
Useordisclosureof mformatlon on this page IS subject to the restrictions on the title page of thm document.
Navigation Computer No. 2
IOB-F_ huKm2a Connector Pin Connects To
RESERVED C121J1B-1RESERVEDSPARE ::RESERVEDRESERVED ::SPARE -6
(B) RS 422 CDU CNTL RCVR (H)$
-----.- ------------(L) ~; [;;]----- -------.---.-
C120J1-P(B) C120J1-R(0) TAG SYNC -9 (22)-------------------- 121J1B-34
(B) ~;T~;~ RCVR -10 (22)--@--
i
------------- FLT TEST ONLYPORT C -11 (22)-J-1- ------------- FLT TEST ONLY
(B) RS 232 XMTR -12 (22)--~- ------------- FLT TEST ONLY
(B) ~;Tfi;;RCVR -13 (22)------
J
------------ FLT TEST ONLY (2)PORT A -14 (22)------ ------------ FLT TEST ONLY (7)
(B) RS 232 XMTR -15 (22)--JJ- ------------ FLT TEST ONLY (3)(0) CDU SYNC -16 (22)------------------- 121JIB-48
(B) ~S23;-RCVR -17 (22)--~-
i
------------- FLIGHT TEST ONLYPORT B -18 (22)----- ------------- FLIGHT TEST ONLY
(B) RS 232-XMTR -19 (22)--u- ------------- FLIGHT TEST ONLY(B) RS 422 XMTR- DATA (H) -20 (22)--~-
1
------------ 123J1-K,121J1B-20
LOADER (CLK) (L) -21 (22)--’~- ------------- 123J1-J,121J1B-21
(B) ARINC 429 RCVR- (H) -22 (22)-------~- -------- DMENO. 1,(B) DME SECONDARY (L) J$ 1+;(22)-------! - -------- ARINC 429(B) RS 422 RCVR- (H) ------NC(B) DME SECONDARY (L) -25 ------NC
RESERVED -26RESERVED -27
(B) SYS ASCB SEC BUS (H) -28 (22)----f31-
t
---------- REF. SECT3.3RESERVED -29RESERVED -30 II
(B) SYS ASCB SEC BUS (L) -31 (22)----1-1--- -------- REF. SECT3.3[~] RS422 XMTR CNTL-CDU (H) -32 (22)-----’-~ -#-------- C120J1-U
SHIE[;)GND-33 (22)--------- -------- C120J1-V---------------
(I) TAG SYNC C121J1B-34 (22)------------------- 121J1B-9
I
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.82Mar 15/91
Use or disclosure of Information on fhm page IS subject to the r;strlctlons on the title page of this document
Navigation Computer No. 2
10BP
(B)(B)
(o)(o)
(o)
(o)(o)(o)(o)(o)(o)(o)
io)(I)
(o)
(o)
(o)
(B)(3)(1)(I)(I)(Ij(I)(I)(I)(I)[:]
(I)
Function Connector Pini
RS422 XMTR (H)I
C121J1B-35 (22)-------=- --------
CLK-CIIU (L) -36 (22)------J-’- --------YSHIELD GND----------
TRUE/MAG SELECT (GND/OPEN) -37 (22)-------------------ONSIDE TUNING CNTL -38 (22)-------------------(AUTOTUNE)(GND/OPEN)REMOTE TUNING CONTROL -39 ------NC(GND/OPEN)LAT WPT ALERT (GND/OPEN) -40 (22)-------------------VER7 WPT ALERT (GND/OPEN) -41 (22)-------------------DEAD RECKONING (GliO/OPEN) -42 (22)-------------------OFFSET ALERT (GND/OPEN) -43 (22)-------------------APPR SENSITIVITY (GND/OPEN)-44 (22)-------------------INDEP OP (GND/OPEN) -45 (22)-------------------COU MSG (GND/OPEN) -46 ------NC
Connects To
C120J1-UC120J1-X
1REF
APP%c
DGRADE ACCURACY (GND/OPEN) -47 (22)-------------------CDU SYNC -48 (22)------------------- 121J1B-16 INAV COMP VALID (GNO/OPEN) -49 (22)-------------------SkARE -50SPARE -51RESERVED -52VERTICAL TRACK AURAL -53 ------NCALERT (GND/OPEN)CROSSSIDE TUNING CONTROL -54 (22)------------------- 121J1B-38,(AUTOTUNE) (GND/OPEN) NAV CONT #1RESERVED -55RESERVED -56ARINC 429 (H) -57 ------NCRCVR LTS #3 (L) -58 ------NCLTS#l NUMBER !31T#1 -59 ------NCLTS#l NUMBER BIT #2 -60 ------NCLTS#2 NUMBER BIT #1 -61 ------NCLTS#2 NUMBER BIT #2 -62 ------NCLTS#3 NUHBER BIT #l -63 ------NCLTS#3 NUMBER BIT #2 -64 ------NCSDI #3 -65 ------NCCROSS FILL ENABLE* -66 ------NCVER B ASCB* -67 (22)-------------------- SIGGNDFUEL FLOW CONFIG IDO -68 -...---NCFUEL FLOW CONFIG ID1C121J1B-69 ------NC ..
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.83Feb 1/88
Use or dwclosure of Information on thm page IS subjec 10 the restrictions on the Mle page of thts document,
Navigation Computer No. 2IOB_P_
(I)(1)(I)(1)(1)(I)(1}(1)(1)(I)
{1)(1)(I)(1)(1)(I)(I)(1)[;]
(I)(I)(I)(I)(1)(I)(1)(I)
(I)(1)(I)
(I)
(1)
(I)
Function Connector Pin
FUEL FLOW CONFIG I02C121J1B-70 ------NCOPERATIONAL MODE IDO -71 (22)-------------------WOW -72 (22)-------------------PERF COMP INSTLD* -73 (22)-------------------LTS#l CONFIG -74 ------NCLTS#l CONFIG -75 ------NCLTS#l CONFIG -76 ------NCLTS#2 CONFIG -77 ------NCLTS#2 CONFIG -78 ------NCLTS#2 CONFIG -79 ------NCRESERVECI -80RESERVED -81RESERVED -82DL CONNECTED* -83 (22)-------------------RADIO CONFIG IDO +: (22)-------------------RADIO CONFIG ID1 ------NCRADIO CONFIG ID2 -86 ------NCMAINT TEST ENABLE* -87 (22)-------------------ILS*/MLS SELECT -88 (22)-------------------LTS#3 CONFIG -89 (22)-------------------LTS#3 CONFIG -90 (22)-------------------LTS#3 CONFIG -91 (22)-------------------OPERATIONAL MODE ID1 -92 (::~;:i~---------------INITIATED XMIT* -93 -INITIATED REC* -94 ------NCDME SCAN TYP* -95 (22)-------------------RADIO BUS TYPE (OPEN/GND) -96 ------NCSINGLE ASCB* -97 ------NCSDI#l=LEFT -98 ------NCsDI#2=RIGHT -99 (22)-------------------CDU VALID* -1oo (22)------------------
TRUE REF SELECTED* -101 (22)------------------AFIS INSTALLED* -102 (22)------------------OVERSPEED PROTECTION -103 ------NCDISABLE*RS 422 OFFSIDE VOR -104 -----_NCCONNECTED*NAV/DME MANUAL* TUNE SEC -105 (22)------------------
NAV/DME MANUAL* C121J1B-106 (22)------------------TUNE PRI
Connects To
SIG GNDA/C WIRINGSIG GND
123J1-DSIG GND
APPX DAPPX D
SIG GND
SIG GND
SIG GNDC120J1-i,134J1A-76,C134J1A-76
SEC NAV/DMAUTO TUNEDISABLE SWPRI NAV/DMAUTO TUNEDISABLE SW
REFAPPX‘c
Interconnect InformationTable 501 (cent)
22-14-00Page 598.84Apr 15/93
Use or disclosure of information on this page is subject to the re! trictions on the title page of this d~cument.
Performance Computer No. 2
10B& Function Connector Pin Connects To
(P) CHASSIS GROUND C122JlA1j ~;:]-------------------- A/CGND(P) SIGNAL GROUND -------------------- A/CSIGGND(P) SERVO POWER (H) -3 (NOTE 3)---------------- 28VDC(P) SERVO POWER (H) -4 (NOTE 3)---------------- 28VDC(P) CLUTCH POWER (H) -5 (NOTE 3)---------------- 28VDC(P) CLUTCH POWER (H) -6 (NOTE 3)---------------- 28VDC(P) COMPUTER POWER (H) -7 (NOTE 3)---------------- 28 V DC(P) COMPUTER POWER (H) -8 (NOTE 3)---------------- 28VDC(P) SERVO POWER (L) -9 (NOTE 3)---------------- A/C PWRGND(P) SERVO POWER (L) -10 (NOTE 3)--------------- A/C PWRGND(P) CLUTCH POWER (L) -11 (NOTE 3)--------------- A/C PWRGND(P) CLUTCH POWER (L) -12 (NOTE 3)--------------- A/C PWRGND(P) COMPUTER POWER (L) -13 (NOTE 3)--------------- A/C PWRGND(P) COMPUTER POWER (L) -14 (NOTE 3)- ------------- A/C PWRGND(0) SERVO NO. 1 DRIVE (H)
[
-15 (20)----- ------------- L128P1-B,122J1A-15
(0) SERVO NO. 1 DRIVE (L) -16 (20)----- ------------- L128P1-C,
i
122J1A-16(0) SERVO NO. 2 DRIVE (H) -17 (20)------------------ R128P1-C,
122J1A-17(0) SERVO NO. 2 DRIVE (L) -18 (20)---------- -------- R128P1-B,
122J1A-18RESERVED -19RESERVED -20RESERVED -21RESERVED -22
(0) SERVO CLUTCH DRIVE NO. 1 -23 (20)------------------- L128P1-E,122J1A-23,134J1B-30,C134J1B-30
(0) SERVO CLUTCH DRIVE NO. 2 -24 (20)------------------- R128P1-E,122J1A-24,134J1B-32,C134J1B-32
RESERVED -25RESERVED -26SPARE -27SPARE -28SPARE -29SPARE -30SPARE -31SPARE C122J1A-32
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.85Mar 15/91
Use or disclosure of mformalton on Ihm page IS subpw to the restrictions on the tttle pagr of thm document
Performance Computer No. 2
IOB_P_ Function Connector Pin Connects To
(B) AS;~R~RIMARY [~;t----------- SEE SECT 3.3
(B) C122J1A::: !::;:::j: ------------1SPARE -35RESERVED -36RESERVED -37SPARE -38
(B) RS 232 RCVR (1/0) -39 (22)---;>-
)
Y-----------(B) RS 232 RTN (1/0) -40 (22)---~$- -.-----.---(B) RS 232 XMTR (1/0) -41 (22)------ --..-------.
(6) RS 232 RCVR (A/T)
I
-42 (22)------ ------------(B) RS 232 RTN (A/T) -43 (22)--J-L- ------------● FLT TEST ONLY(B) RS 232 Xt4TR(A/T) -44 (22)---:;- ------------
(B) RS 232 RCVR (PERF)
i
-45 (22)---;- ------------(B) RS 232 RTN (PERF) -46 (22)---r~- .-------~---(B) RS 232 XMTR (PERF) .47 (*2)---G.- ------------
(I) CROSS-SIDE A/T ENGAGE* -48 (22)------------------- 122J1A-49
{O) A/T ENGAGE (GND/OPEN) -49 (22)------------------- 122J1A-48(1) MAINT TEST ENABLE* ~;~ (22)------------------- APPX 0,
RESERVED REF APPX CRESERVED -52RESERVED -53
(I) GEAR DOWN* -54 (22)------------------ A/C GEARDOWN
I
REFDISCRETE, APPX122J1A-54 C
SPARE -55RESERVED -56RESERVED C122J1A-57
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.86Mar 15/91
Use or dmctosure of mformatlon on thm page IS subject to the ‘estrtctions on the Mle page of this document
Performance Computer No. 2
IOB~ ~- Connector Pin Connects To
SPARE C122J1A-58(I) LEFT/RIGHT* SELECT -59 (22)------------------- SIGGND \
(I) ASCB VER A/B* -60 (22)------------------- SIGGNDRESERVED -61
(I) LEFT BLEED SRC ON* -62 (22)------------------- A/C WIRING(1) RIGHT BLEED SRC ON* -63 (22)------------------- A/CWIRING
SPARE -64RESERVED -65
(I) ASCB SINGLE/DUAL* 4; (22)------------------- SIGGNDRESERVED REFRESERVED -68 PAPPXRESERVED -69 cRESERVED -70RESERVED -71 5.1 m
(1) FLAPS IN MOTION -72 (22)-----NVV ------ AIC WIRING(1) LEFT AC PACK ON/OFF -73 (22)------------------- A/CWIRING
(28V/OPEN)(I) RIGHT AC PACK ON/OFF -74 (22)------------------- A/C WIRING
(28V/OPEN)(I) WOW* -75 (22)------------------- A/C WIRING ,
RESERVED -76RESERVED -77RESERVED -78RESERVED C122J1A-79
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.87Mar 15/91
UseordisclosureofIntonnatlononthispageIS subjecttothereslnc~lonson the Iltle pagt? of this document
Performance Computer No. 2
IOBJ_
(I)
(B)(B)
(B)(B)
(B)(B)
(B)(B)(B)(B)
(B)(B)
(B)(B)
(B)(B)
(B)(B)(B)(B)
Function Connector Pin Connects To
RESERVED C122J1A-80A/T ENGAGE/DISENGAGE -81 (22)------------------- APPXD/REF(OPEN/GNDTOGGLE) APPX CRESERVED -82RESERVED -83RS422 XMTR (FTI-CLK)
i
1
(H) -84 (22)---O- -------------RS422 XMTR (FT1-CLK) (L) -85 (22)--!+!H ------------
-----------‘HIELD(yD-~6 (Zz).-lnlj-------------RS422 XMTR (FT1-DTR)
RS422 XMTR (FT1-DTR) (L) -87 (22)----- -------------SHIELD GND-----------~
iRS422 XMTR (FT1-DATA) (H) -88 (22)--i~1 -------------RS422 XMTR (FT1-DATA) (L) -89 (22)----- ------------- FLT TEST ONLY
SHIELD GND-----------~ ,RS422 RCVR (FT1-DATA) (H) -90 (22)---7---------------
!
J
RS422 RCVR (FT1-DATA) (L) -91 (22)--!*!--------------RS422 RCVR (FT1-CTS)
$(H) -92 (22)--i-i -------------
RS422 RCVR (FT1-CTS) (L) ~;~ (22)---G---------------SPARESPARE -95SPARE -96RS422 XMTR (CDU-CLK)
i(H) -97 (22)---C- -------------
RS422 XMTR (CDU-CLK) (L) -98 (22)-+ -------------SHIELD GOD----------- ,
RS422 XMTR (CDU-DTR) (H)--99 (22)--i~l~-------------RS422 XMTR (CDU-DTR) (L) -100 (22)--%- -------------
SHIELD GND-----------
!RS422 XMTR (CDU-DATA) (H) -101 (22)-i~-l--------------RS422 XMTR (CDU-DATA (L) -102 (22)------------------
SHIELD GND-----------~
tRS422 RCVR (CDU-DATA) (H) -103 (22)--D-- ------------RS422 RCVR (CDU-DATA) (L) -104 (22)-!=!- ------------RS422 RCVR (CDU-CTS)
i(H) -105 (22)----- ------------
RS422 RCVR (L) C122J1A-106 (22)-!=!- ------------(CDU-CTS)
C120J1-gC120J1-h
C120J1-eC120J1-f
C120J1-CC120J1-d
C120J1-YC120J1-ZC120J1-aC120J1-b
Interconnect InformationTable 501 (cent)
22-14-00Page 598.88
Jun 1/87Use or disclosure Of mformatlon on Ih!s page IS subject to the eslrlctlons on the Mle page of thwi document
Performance Computer No. 2
IOB_P_ Function Connector Pin Connects To
(P) CHASSIS GND C122J1B-1 (22)-------------------- A/C GND(P) ~;~[;L GND -2 (22)-------------------- A/C SIG GND
(B) ASCB SECONDARY PORT i(H) ~~ (22)--;2,-~-------------)SEE SECT 3.3(B) ASCB SECONDARY PORT (L) -5 (22)---C;- -------------
SPARE -6RESERVED -7RESERVED -8SPARE -9RESERVED -10RESERVED -11RESERVED -12RESERVED -13RESERVED -14RESERVED -15RESERVED -16RESERVED -17RESERVED -18RESERVED -19RESERVED -20RESERVED -21RESERVED -22RESERVED -23RESERVED -24RESERVED -25RESERVED -26RESERVED -27RESERVED -28RESERVED -29RESERVED -30RESERVED -31RESERVED -32RESERVED -33RESERVED -34RESERVED -35RESERVED -36RESERVED -37RESERVED -38RESERVED -39RESERVED C122J1B-40
Interconnect InformationTable 501 (cent)
22-14-00Page 598.89jun 1/87
Use or disclosure of mformatlon on Ihm page IS subjec’ 10 the restnct(ons on the title page of this document
10B&
(I)(I)
(I)
(I)
(I)
(1)
(I)(I)(I){1)
Eu!Kmn
RESERVEDRESERVEDRESERVEDRESERVEDRESERVEDPLA1 POS (C)PLA2 Pos (c)RESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDSERVO NO. 1 TACH
SERVO NO. 1 TACH
SERVO NO. 2 TACH
SERVO NO. 2 TACH
RESERVEDRESERVEDRESERVEDRESERVEDPLA 1 POSPLA 1 POSPLA 2 POSPM 2 PosRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVED
Performance Computer No. 2
Connector Pin connects TQ
C122J1B-41-42-43-44-45
i-46 (22)--q=1- ----- r------ ;;: ~;j;g-47 (22)-------f-t--------
-48-49-50-51-52-53-54-55-56
(L)
(H)
(L)
(H)
-57-58 (22)--;9;-
~
------------
-59 (22)-+- ------------
-60 (22)--q+-
1
------------
-61 (22)-.& .-----------
L128P1-D,122J1B-58L128P1-A,122JIB-59R128P1-A,122J1B-60R128P1-D,122J1B-61
-62-63-64-65
(L) -66 (22)-.-F. - ----------- A/cwIRING(H) [1-67 (22)---& - ---- ------ A/CWIRING(L)
1-68 (22)--------q-+------- A/CWIRING
(ii) -69 (22)--------A=J- ------ A/C WIRING-70-71-72-73-74-75
C122J1B-76
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.90Mar 15/91
Use or dwclosure of Information on thm page IS sub]ect 10 the r ?strlctlons on the tttle page of this document.
Performance Computer No. Z
IOB~ m!w.m Connector Pin nnects TQ
RESERVED C122J1B-77RESERVED -78RESERVED -79RESERVED -80RESERVED -81RESERVED -82RESERVED -83RESERVED -84RESERVED -85RESERVED -86INTERLOCK #1 -87 (22)-------------------INTERLOCK #2
}
-88 (22)------------------- AP:XINTERLOCK #3 -89 (22)-------------------INTERLOCK #4 -90 (22)-------------------
(I) A/T DISCONNECT (OPEN/GND) +; (22)------------------- APPX D,APPX CRESERVEDRESERVED -93RESERVED -94RESERVED -95
(I) PLA REF (H)i
-96 (22)--- --------------- 26 V AC 400 HZ(I) PLA REF (L) -97 (22)--- --------------- 26 V AC 400 HZ
RESERVED -98(0) A/T ENGAGED GND +:.(22)------------------- A/C WIRING
RESERVED ENGINE SYNCRESERVED -101 COMPUTERRESERVED -102RESERVED -103RESERVED -104RESERVED -105
(0) PERF COMP INSTALLED C122J1B-106 ------NC
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.91Mar 15/91
Use or disclosure ot Information on thm page IS subfecl 10 the reslnctlons on the ttle page of Ihm document.
Display Unit No. 6
IOB~ Function Connector Pin Connects To
(o)
{
(H) C130J1-1 (22)------5-- ---------- 135J1-16~;~ BRIGHTNESS POT (W) -14 (22)----!-1------------ 135J1-17
(L) -13 (22)----!~- ---------- 135J1-18SHIELD GND ------
(0) (H) -2 ------NC~:j WX DIMMING (w) -15 -----NC
(L) -3 ------NCRESERVED -4RESERVED -5RESERVED -6RESERVEDSPARE ::RESERVED -9RESERVED -loRESERVED -11RESERVED -12RESERVED -16RESERVED -17RESERVED -18
(B) BUS3 (H)$
-19 (22)----R- ----------- SEE APPENDIX A,(B) (L) 1+:(22)----U- ----------- FIG. A-1
SPARE(I) DU PWR DN* -22 (22)------------------- REV
CONTROLLERPIO-j,
(1) LIGHTING BUS (H) -23 (22)(I) (L)
-.$.] g;p:[D;; ;::-24 (22)------- ----------- LIGHTING BUS FOR
INCLINOMETERLIGHTING1.5 WATTS
SPARE -25i(I) REMOTE LT SENSOR (H) C130J1-26 (22)---+~& ----------- 130J1-26,
131J1-26,132J1-26,115J2-V,C115J2-V,C133J1-26,C131JI-26,REMOTELT SENSOR HI
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.92Mar 15/91
Use or disclosure of mformatlon on this page IS subject to the ~estrlctlons on the title page of this document.
Display Unit No. 6
106~
(I)
(o)
(o)
(I)
(I)
(B)
(B)(B)(o)(B)(B)(o)(o)(o)
(B)
(B)
Function Connector Pin
1
Connects To
REMOTE LT SENSOR (L) C130J1-27 (22)----4$ ------------ 130J1-27,131J1-27,132J1-27,115J2-W,C115J2-W,133J1-27,C131J1-27,
REMOTE
(H)DLS OUT
(L)
(H)ALS
(L)
RESERVED
LT SENSOR LO-28 (22)----------------- C131J1-29,
iC115J2-R
-41 (22)--lci-- ------------ C131J1-42,
“T C115J2-S -SHIELDGND ---
i
-29 (22)--2-- ------------ C131J1-28,C115J2-T
-42 (22)--’~-- ------------ C131J1-41,C115J2-U
-30RESERVED -31RESERVED -32;::E3v~;RM (L) -33 ------NC
-34BUS2 [~]
i]-35 (22)-------O---------- SEE APPENDIX A-36 (22)------!~- -------- FIG. A-7
DU VALID (GND/OPEN) -37 ------NCBUS 1 ~~j
t]-38 (22)-------O-- -------- SEE APPENDIX A-39 (22)------!~-- -------- FIG. A-4
REMOTE LT SENSOR GND -40 ------NCREMOTE LT SENSOR PWR (H) -53 ------NC
(L) +: ------NCRESERVEDRESERVED -44RESERVED -46RESERVED -47RESERVED -48BUS 2 TERM (L) -49 ------NCRESERVED -50RESERVED -51BUS 1 TERM (L) -52 ------NCRESERVED C130J1-55
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.93Mar 15/91
Use or disclosure of Information on this page IS subjec, 10 the restrictions on the title pagt! of this document
Display Unit No. 6
IOBP Function
(B)(B)(B)
(B)
(B)(o)
(o)
(o)
(B)(B)
(B)(B)
(B)
(B)
(B)
(I)
Connector Pin
RESERVED C130J1-56
RESERVED -57
BUS 4 (H) -58 (22)------f-~-1-.-------
BUS 4 TERM (L) -45 (22)-----JO;- ---------BUS 4 (L) -59 ------NCRESERVED -60WX BUS 2 TERM (L) -61 ------NCRESERVED -62RESERVED -63WX BUS 1 TERM (L) -64 ------NCDU OVERTEMP (GND/OPEN) -65 (22)-------------------
DU WRAPAROUND .(H)(ARINC 429)DU WRAPAROUND (L)(ARINC 429)RESERVEDRESERVEDWX BUS 3 (H)WX BUS 3 (L)RESERVEDRESERVEDSPAREWX BUS 2 (H)WX BUS 2 (L)SPAREWX BUS 1 (H)WX BUS 1 (L)RESERVEDRESERVEDRESERVEDWX BUS 3 TERM (L)RESERVEDBURST OUT (H)
(L)PORT SEL A
I-66 (22)------;Jr ---------
-79 (22)-----JC;- ---------
-67-68-69 ------NC-70 ------NC-71-72-73-74 ------NC-75 ------NC-76-77 ------NC-78 ------NC-80-81-82-83 ------NC-84
t-85 (22)-----f-~- ----------86 (22)-----~-;------------87 (22)-------------------
PORT SEL B -88 (22)-------------------
RESERVED C130J1-89
Connects To
C130JI-85C130J1-86
134J1A-39,C134J1A-39134J1B-77,C134J1B-77134J1B-78,C134J1B-78
C130J1-58C130J1-45C131J1-87, A/CWIRING,APPX B & CC131J1-88,A/C WIRING,APPX B & C
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of Information on this page IS subject to the r,!strtct!ons on the title page of this document
(I)(I)
(P)
(I)(1)(P)(P)(P)
(P)(P)(P)
Function
I.D. #1I.D. #2RESERVEDRESERVEDCHASSIS GNDRESERVEDRESERVEDRESERVEDRESERVEDSOFTWARE ENABLE*SOFTWARE ENABLE*28 V DC28 V DC28 V DC
28 V DC RTN28 V DC RTN28 V DC RTN
Display Unit No. 6
Connector Pin Connects To
C130J1-90 ------NC)REF APPENDIX C
-91 ------NC-92-93-94 (22)------------------- A/C CHASSIS GND-95-96-97-98-99 (22)------------------- FLT TEST ONLY-100 (22)------------------ FLT TEST ONLY-101 (NOTE 3)--------------
}-102 (NOTE 3)-------------- A/C 28V DC PWR-103 (NOTE 3)--------------
-104 (NOTE 3)-------------- A/C 28VDC
)-105 (NOTE 3)-------------- PWRRTN
C13OJ1-106 (NOTE 3)--------------
Interconnect InformationTable 501 (cent) 22-14-00
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Use or dwclosure of NIformatlon on lhls page IS subpc to the restrictions on the title page of thts document.
Display Unit No. 5
IOB_P_ Function Connector Pin Connects To
(o)
t
(H) C131J1-1 (22)------fi ---------- 135J1-13(I) BRIGHTNESS POT ~~~ -14 (22)----,-T------------ 135J1-14(o) -13 (22)------ - ---------- 135J1-15
SHIELD GND -----f
(0) (H) -2 (22)----+ ‘______ C61J2-F(I) WX DIMMING (w) -15 (22)---,-r-
!----------- C61J2-G
(o) (L) -3 (22)------ - ----------- C61J2-HSHIELDGND -----Y
RESERVED -4RESERVEDRESERVED ::RESERVED -7SPARE -8RESERVED -9RESERVED -10RESERVED -11RESERVED -12RESERVED -16RESERVED -17RESERVED -18
(B) BUS3 (H)i
-19 (22)-----~1----------- SEE APPENDIX A,(B) (L) 1-20 (22) ------0 ----------- FIG. A-2
SPARE -21(I) DU PWR DN* -22 (22)------------------- A/C WIRING,
134J1A-48,C134J1A-48APPENDIX B & C
(I) LIGHTING BUS (H) -23 ------NC(I) (L) -24 ------NC
SPARE -25
t(I) REMOTE LT SENSOR (H) C131J1-26 (22)------91---------- 130J1-26,
131J1-26,132J1-26,115J2-V,C115J2-V,133J1-26,C130J1-26,REMOTELT SENSOR HI
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of mformahon on this page IS subject to the restrictions on the Otle page of this document
Display Unit No. 5
IOB_P_ Function Connector Pin
J
Connects To
(I) REMOTE LT SENSOR (L) C131J1-27 (22)----U-- ---------- 130J1-27,131J1-27,132J1-27,115J2-W,C115J2-W,133J1-27,C130J1-27,REMOTE
t
LT SENSOR LO(0) DLS OUT (H) -28 (22)--P-- ------------ C130J1-29,,1 C115J2-T(o) (L) -41 (22)-+ ------------ C130J1-42,
C115J2-USHIELDGND ---
(1) ALS (L)
t
-29 (22)----- ------------ C130J1-28,C115J2-R
(I) (L) -42 (22)-J~--------------- C130J1-41,C115J2-S
RESERVED -30RESERVED -31RESERVED -32
(B) BUS 3 TERM (L) -33 ------NCRESERVED -34
(B) BUS 2 (H)i]
-35 (22)-------O-- -------- SEE APPENDIX A(B) (L) -36 (22)-------1~--------- FIG. A-8(0) DU VALID (GND/OPEN) -37 ------NC(B) BUS 1 :!](B) t]
-38 (22)-------~- -------- SEE APPENDIX A-39 (22)-------!=!--------- FIG. A-5
(0) REMOTE LT SENSOR GND -40 ------NC(o) REMOTE LT SENSOR PWR [:] -53 ------NC(o) -54 ------NC
RESERVED -43RESERVED -44RESERVED -46RESERVED -47RESERVED -48
(B) BUS 2 TERM (L) -49 ------NCRESERVED -50RESERVED -51
(B) BUS 1 TERM (L) -52 ------NCRESERVED -55RESERVED C131J1-56
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of Information on this page IS subtect to the reslrlct!ons on the title page of this document
.- -- MAINTENANCE
Display Unit No. 5
10BP
::]
(B)
(B)
(B)(0)
(o)
(o)
(B)(B)
(B)(B)
(B)(B)
(B)
(o)(o)(1)
(I)
Function
RESERVEDBus 4 (H)BUS 4 TERM [:]BUS 4RESERVEDWX BUS 2 TERM (L)RESERVEDRESERVEDWX BUS 1 TERM (L)
Connector Pin Connects To
C131J1-57
i-58 (22)-----~r- ---------- C131J1-85-45 (22)-----J- ---------- C131J1-86-59 ------NC-60-61 ------NC-62-63-64 ------NC
DU OVERTEMP (GNDjOPEN) -65 (22)------------------- 134J1A-38,1 C134J1A-38
DU WRAPAROUND (H)(ARINC 429)DU WRAPAROUND (L)(ARINC 429)RESERVEDRESERVEDWx 3 (H)
(L)RESERVEDRESERVEDSPAREWx 2 (H)
(L)SPAREWx 1 (H)
(L)RESERVEDRESERVEDRESERVED~;s~XB;E;TERM (L)
BURST OUT (H)(L)
PORT SEL A
PORT SEL B
RESERVED
-66 (22)---”?;
1
---------- 134J1B-48,C134J1B-48
-79 (22)----JJ- ---------- 134J1B-49,C134J1B-49
-67-68-69 (22)-----~-
$ )---------- SEE APPENDIX A
-70 (22)-----U- ----------- FIG. A-9-71-72-73
i-74 (22)----1?- ----------- SEE APPENDIX A
1~;: (22)----V- ----------- FIG. A-6
#-77 (22)----f3- ----------- SEE APPENDIX A1-78 (22)----L’- ----------- FIG. A-3-80-81-82-83 ------NC-84
7$-85 (22)----i - ----------- C131J1-58-86 (22)----U- ----------- C131J1-45-87 (22)------------------- ;;;:;:-87, A/C
.APPi B’&c
-88 (22)------------------- C130J1-88,A/C WIRING,APPX B &C
C131J1-89
Interconnect InformationTable 501 (cent) 22-14-00
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Use or dmclosure of Information on this page IS subject 10 the I ?stnctlons on the Me page of this document
10B_P_
(I)(1)
(P)
(1)(I)(P)(P)(P)
(P)(P)(P)
Display Unit No. 5
Function
I.D. #1I.D. #2RESERVEDRESERVEDCHASSIS GNDRESERVEDRESERVEDRESERVEDRESERVEDSOFTWARE ENABLE*$OFT14AREENABLE*28V DC28 V DC28 V DC
28 V DC RTN28 V DC RTN28V DC RTN
Connector Pin Connects To
C131Jl:;~ (22)------------------- GND REF------NC ) APPENDIX C
-92-93.94 (22)------------------- A/c CHA.SSISGND-95-96-97-98-99 (22)------------------- FLT TEST ONLY-100 (22)------------------ FLT TEST ONLY-101 (NOTE 3)--------------
)-102 (NOTE 3)-------------- A/C 28 V DC PMR-103 (NOTE 3)--------------
-104 (NOTE 3)-------------- A/C 28VDC
)-105 (NOTE 3)-------------- PWRRTN
C131JI-106 (NOTE 3)--------------
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Use or ckiclosure ot mformahon on this page IS sublet’ 10 Ihe restrlcllons on the Ittle pagf of th!s document
Fault Warning Computer No. 2
IOB_P_ Function Connector Pin Connects To
(P) 28 V DC POWER C134J1A-I (NOTE 3)---------------- A/Cp;jE[DC(P) 28 V DC POWER -2 (NOTE 3)----------------(P) 28 V DC POWER -3 (NOTE 3)--- ------------- }
RESERVED -4(P) 28 V DC PWR GNO -5 (NOTE 3)---------------- A/C28VDC(P) 28 V DC PWR GND -6 (NOTE 3)----------------
}POWER GND
(P) 28 V DC PWR GND ~: (NOTE 3)----------------RESERVED
(P) SIGNAL GND -9 (22)--------------------(P) SIGNAL GND
}-10 (22)------------------- A/C SIGNAL GND
(P) SIGNAL GND -11 (22)-------------------(I) KEYING PIN NO. 1 -12 [2~~j:N~--------------- GND
\
(1) KEYING PIN NO. 2 -13 --(1) KEYING PIN NO. 3 -14 (22)------------------- GND(1) KEYING PIN NO. 4 -15 ------NC(1) KEYING PIN NO. 5 -16 (22)------------------- GND
RESERVED -17RESERVED -18
(o) FGCMAINT TEST (GND/OPEN) -19 (22)------------------- IIJ1-58,11J2-58,134J1A-19
SPARE -20(o) AP OFF ANNUN (GND//OPEN) -21 (22)------------------- APPENOIXD
RESERVED -22(1) WARN RESET* -23 (22)------------------- APPX D(1) CAUTION RESET* -24 (22)------------------- APPX D REF(1) VOICE RECORDER FAIL -25 (22)------------------- A/’CWIRING ‘AP[X
(OPEN/GND)(1) STEER BY WIRE FAIL* -26 (22)------------------- A/CWIl?ING(1) AHRS COOL FAIL* -27 (22)------------------- E170J1B-E1(1) CAT II BENDIX ILS INSTLLED*-28 (22)------------------- APPX C(I) DU3 VALID* -29 (22)------------------- 132JI-37,
134J1A-29(1) DU 4 VALID* -30 [22)------------------- 132JI-37,
134J1A-30RESERVED -31
(1) SPARE -32 ------NC(I) SPARE -33 ------NC(I) DU1 OVERTEMP* -34 (22)------------------- 130J1-65,
134J1A-34(I) DU2 OVERTEMP* C134J1A-35 (22)------------------- 131J1-65,
134J1A-35 ,
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of informationon this page is subject to the restrictions on thetitle pageof this document.
IOB~
(I)
(I)
(I)
(I)
(1)
(I)
(I)
(I)
(I)
Function
DU3 OVERTEMW
DU4 OVERTEMP*
DU5 OVERTEMP*
DU6 OVERTEMP*
RESERVEDSG1 REV*
SG2 REV*
SG3 REV*
DU1 REV*
DU2 REV*
Fault Warning Computer No. 2
Connector Pin
C134J1A-36 (22)-------------------
-37 (22)-------------------
-38 (22)-------------------
-39 (22)-------------------
-40-41 (22)-------------------
-42 (22)-------------------
-43 (22)-------------------
-44 (22)-------------------
C134J1A-45 (22)---------------”---
Connects To
132J1-65,134J1A-36133J1-65,134J1A-37C131J1-65,134J1A-38C130J1-65,134J1A-39
134J1A-41,A/C WIRING,65J1A-60,C65J1A-60,E65J1A-60,65J1A-59,APPX B AND C134J1A-42,A/C WIRING,65J1A-61,C65J1A-61,E65J1A-61,C65J1A-59,APPX B AND C134J1A-43,A/C WIRING,65J1A-62,C65J1A-62,E65J1A-62,E65J1A-59,APPX B AND C134J1A-44,A/C WIRING,65J1A-63,C65J1A-63,E65J1A-63,APPX BAND C134J1A-45.A/C WIRING,131J1-22,APPX BAND C
Interconnect InformationTable 501 (cent) 22-14-00
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Use or dwlosure of mformahon on this page IS subpcl 10 the restrictions on the tllle page 01 Ihm document
Fault Warning Computer No. 2
10B_P_ Function Connector Pin Connects To
(I) DU3 REV* C134J1A-46 (22)------------------- 134J1A-46,A/C WIRING,65J1A-64,C65J1A-64,E65J1A-64,132J1-22,APPX B AND C
(I) DU4 REV* -47 (22)------------------- 134J1A-47,A/C WIRING,65J1A-65,C65J1A-65,E65J1A-65,133J1-22,APPX B AND C
(I) DU5 REV* -48 (22)------------------- 134J1A-48,C131J1-22,A/C WIRINGAPPX B AND C
(I) DU6 REV* -49 (22)------------------- 134J1A-49, ‘A/C WIRING,65J1A-66,C65J1A-66,E65J1A-66,APPX B AND C
(I) CAT II MLS INSTALLED* -50 (22)------------------- APPX C(I) SG1 OVERTEMP* -51 (22)------------------- 134J1A-51,
65J1B-52(I) SG2 OVERTEMP* -52 (22)------------------- 134J1A-52,
C65J1B-52(I) SG3 OVERTEMP* -53 (22)------------------- 134J1A-53,
E65J1B-52RESERVED -54
SPARE -55(P) CHASSIS GND NO. 1 -56 (22)------------------- A/CCHASSISGND(P) CHASSIS GND NO. 2 -57 (22)------------------- A/C CHASSIS GND(P) CHASSIS GND NO. 3 C134J1A-58 (22)------------------- A/c CHASSIS GND
Interconnect InformationTable 501 (cent) 22-14-00
Page 598~102Mar 15/91
Use or disclosure of Information on thts page IS subject 10 the rxtnctlons on the title page of th!s document.
IOBP
(B)(B)(1)
(1)(1)(1)
(I)(1)(1)
(I)
(1)
[1)
(x)
(I)
(I)
(I)(I)(1)(I)(1)(I)(I)
Function
RESERVEDRESERVED
Fault Warning Computer No. 2
Connector Pin Connects To
C134J1A-59-60 I
SYSASCB PRIMARY BUS (H) -61 (22)--;----------------1REF. SECT. 3.3-qSYS ASCB PRIMARY BUS (L) -62 (22j--&}-~------------jwow* -63 (22)------------------- A/C HOWRESERVED -64FWC IDO -65 ------NCFWC 100 -66 (22)------------------- SIGGNOGEAR DOWN* -67 (22)------------------- A/CGEARDC
DISCRETEMEMORY ERASE BUTTON* -68 (22)------------------- APPXDWINOSHEAR AVAILABLE* -69 (22)------------------- APPXJGND SPOILER NOT ARMED -70 (22)------------------- A/CklIRING(GND/OPEN)EMER BATT 1 FAIL -71 (22)------------------- A/CWIRING(OPEN/GNO)EMER BATT 2 FAIL -72 (22)------------------- A/C WIRING(OPEN/GND)
AOAHEAT 1 FAIL -73 (22) ------------------- A/C WIRING(OPEN/GND)AOA HEAT 2 FAIL -74 (22)------------------- A/C WIRIN&(OPEN/GND)CDU 1 VALIO* -75 (22)------------------- 120J1-i,
134J1A-75,I21J1B”1OO
COU 2 VALID* -76 (22)------------------- C120J1-i,134J1A-75,C121JIB-1OO
SPARE CDU VALID* -77 (22)------------------- APPX GSPARE FMS ACTIVE 2* -78 (22)------------------- APPXGSPARE FMS ACTIVE 1* -79 (22)------------------- APPXGAP OFF RESET -80 (22)------------------- APPXD
MANUAL EXCEEDANCE RECORD* -81 (22) ------------------- APPX O
CAT II NAV INSTALLED* -82 (22)------------------- APPXCAUTOTHROTTLE C134J1A-83 (22)------------------- APPX DDISCONNECT (OPEN/GND)
Interconnect InformationTable 501 (cent) 22-14-00
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Use or dwclosure of mformatlon on thts page !s sublet ( 10 the restnctmns on the M(e page of lhm document
Fault Warning Computer No. 2
IOB& Function Connector Pin
(I) BRAKE OVHT (BTMS)* C134J1A-84 (22)-------------------(GND/OPEN)
(I) MAINTENANCE TEST -85 (22)-------------------ENABLE*
(1) FWC DATA -86 (22)-------------------DOWNLOAD INITIATE*
(1) SPARE NZ VALID* -87 (22)-------------------RESERVED -88RESERVED -89
(I) SPARE FMS INSTALLED*(o)
-90 (22)-------------------AUTOTHROTTLE OFF ANNUN -91 (22)-------------------(GND/OPEN)
(0) FWC VALID (GND/OPEN)(o)
-92 ------NCSPARE -93
(o)------NC
HEADING MISCOMPARE -94 (22)-------------------(GND/OPEN)
(o) RAD ALT TEST (GND/OPEN)(o)
-95 (22)-------------------B.C. TEST REQUEST -96 (22)-------------------(GND/OPEN)
(1) BUS CON VALID NO. 1* -97 (22)-------------------
(I) BUS CON VALID NO. 2* -98 (22)-------------------
(I) BUS CON VALID NO. 3* -99 (22)-------------------
(1) SYSTEM TEST 1 -1oo (22)------------------(r) SYSTEM TEST 2 -101 (22)------------------(1) SYSTEM TEST 3(0)
-102 (22)------------------EMER CHECKLIST SEL -103 (22)------------------(GND/OPEN)
(0) CHECKLIST INSTALLED(GND/OPEN)
-104 (22)------------------
(I) SCROLL UP*(I)
-105 (22)------------------SCROLL DN* C134J1A-106 (22)------------------
Connects To
APPX C134J1A-84APPX D
APPX D!
I
APPX G I
APPX GAPPX O
tSTANOBY RM ‘S
C20J1-T65J1B-2,C65JIB-2,E65JIB-265J1A-13,134JIA-97C65J1A-13,134J1A-98E65JIA-13,134J1A-99TBDTBDTBDl15J1-p,Cl15J1-p,134J1A-103l15J1-q,Cl15J1-q,134J1A-104APPX DAPPX O
REFAPPXc
Interconnect InformationTable 501 (cent)
22-14-00Page 598.104
Apr 15/93Use or disclosure of information on this page is subject to the restrictions on the title page of this d>cument
Fault Warning Computer No. 2
106_P_ Function Connector Pin Connects To
(I) L. FUEL VALVE OPEN C134J1B-1 (22)-------------------- A/C WIRING ‘(28V/OPEN)
(I) R. FUEL VALVE OPEN -2 (22)-------------------- A/CWIRING(28V/OPEN)
(I) L. FUEL VALVE CLOSED -3 (22)-------------------- A/CWIRING(28V/OPEN)
(I) R. FUEL VALVE CLOSED -4 (22)-------------------- A/CWIRING(28V/OPEN)
(I) COMBINED HYD. VALVE OPEN -5 (22)-------------------- A/C WIRING(28V/OPEN)
(1) FLT. HYD VALVE OPEN -6 (22)-------------------- A/C WIRING(28V/OPEN)
(1) COMBINED HYD. VALVE CLOSED-7 (22)-------------------- A/CWIRING(28V/OPEN)
(I) FLT. HYD. VALVE CLOSED -8 (22)-------------------- A/CWIRING(28v/oPEN)
(I) DC EXT PWR (28V/OPEN) -9 (22)-------------------- A/CWIRING REF(I) ACFT CONFIGURATION -10 [22)------------------- A/CWIRING ‘APPX
(28V/OPEN) cRESERVED -11
(I) L. OIL FILT B PASS -12 (22)------------------- A/C WIRING(OPEN/28V)
(I) R. OIL FILT B PASS -13 (22)------------------- A/C WIRING(OPEN/28V)
(I) FLIGHT RECORDER FAIL -14 (22)------------------- A/C WIRING(OPEN/28V)RESERVED -15
(1) INHIBIT SELECT (28V/OPEN) -16 (22)------------------- A/C WIRING(1) L COWL PRESS LOW (28V/OPEN)-17(22)------------------- A/C MIRING(1) R COWL PRESS LOW (28V/OPEN)-18(22)------------------- A/C WIRING(I) VHF COM 1 FAIL (OPEN/28V) -19 (22)------------------- A/C WIRING(1) VHF COM 2 FAIL (OPEN/28V) -20 (22)------------------- A/C WIRING(1) VHFCOM3 FAIL (OPEN/28V) -21 (22)------------------- A/CW]RING(1) L WING TEMP LOW (OPEN/28V) -22 (22)------------------- A/C WIRING(I) R WING TEMP LOW (OPEN/28V) -23 (22)------------------- A/C WIRING(1) AUTOPILOT CLUTCH (28V/OPEN)-24 (22)------------------- APPENDIX D(I) TRIM CLUTCH (28V/OPEN) -25 (22)------------------- APPENDIXD(1) RUDDER ACTUATOR (28V/OPEN) -26 (22)------------------- 14P1-A,1OJIA-58,
C1OJ1A-58,134J1B-26APPENDIX D
RESERVED C134J1B-27 I
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Use or dsclosure of InformalIon on thm page IS subject to the restnct(ons on the Wle page of thm document
Fault Warning Computer No. 2IOB
~ Function Connector Pin @nects To
(1) APU ALTERNATOR OFF C134J1B-28 (22)------------------- A/c WIRING ‘(28V/OPEN)RESERVED -29
(I) AUTOTHROTTLE CLUTCH NO. 1 -30 (20)------------------- 122J1A-23,(28V/OPEN) C122J1A-23,
L128P1-E,134J1B-30 b
RESERVED -31 APPX(1) AUTOTHROTTLE CLUTCH NO. 2 -32 (20)------------------- 122J1A-24, c
(28V/OPE?i) C122J1A-24,R128P1-E,C134J16-32 ,
SPARE -33(B) IN 1 WRAPAROUND (H) -34 (22)---fl--
Z
---------- 130J1-66,134J18-34
(B) DU 1 WRAPAROUND (L) -35 (22)---u-- ---------- 130JI-79,134J1B-35
SPARE -36SPARE -37SPARE -38
(B) DU 2 WRAPAROUND (H)
i
-39 (22)---fi-- ---------- 131J1-66,134J16-39
(B) DU 2 WRAPAROUND (L) -40 (22)---:-- ----------- 131J1-79,134JlB-40
(B) DU 3 WRAPAROUND (H) -41 (22)---fl-- ----------- 132J1-66,
u134J1B-41
(B) DU 3 WRAPAROUND (L) -42 (22)--- -- ----------- 132J1-79,134J1B-42
(B) DU 4 WRAPAROUND (H) -43 (22)---fi-- ----------- 133JI-66,134J1B-43
(6) DU 4 WRAPAROUND (L) -44 (22)---#-- ----------- 133J1-79,134J1B-44
SPARE -45SPARE -46SPARE -47
(B) DU 5 WRAPAROUND (H)
t
-48 (22)---fi-- ----------- C131J1-66,134J1B-48
(B) DU 5 WRAPAROUND (L) -49 (22)---:-- ----------- C131J1-79,
t
134J1B-49(8) IRS #2 HIGH SPEEt3 (H) -50 (22)---fl-- ----------- C170J1B-H14
ARINC 429(B) IRS #2 HIGH SPEED(L)C134J1B-51 (22)---O- ----------- C170J1B-H15
ARINC 429
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of information on this page is subject to the re: rictions on the title page of this document
(B)(B)
(B)
(B)
(B)
(B)
(B)
(B)
Function
RESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDSPARESPARE
Fault Warning Computer No. 2
Connector Pin Connects To
SPARESYS ASCB (H)
SECONDARY BUS (L)SPARESPARESPARESPARESPARERESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVED
C134J1B-52-53-54-55-56-57-58-59
RESERVED -76DU 6 WRAPAROUND (H) -77
DU 6 WRAPAROUND (L) -78
-60-61 (22)---+---------] REF. SECT 33~:: (22)--+- -----------
-64-65-66-67-68-69-70-71-72-73-74-75
IRS #1 HIGH SPEED (H) -79ARINC 429IRS #1 HIGH SPEED (L) -80ARINC 429IRS #3 HIGH SPEED (H) -81ARINC 429IRS #3 HIGH SPEED (L) -82ARINC 429RESERVED -83RESERVED -84RESERVED -85RESERVED C134J1B-86
(22)---O
(22)---:
(22)---fi
(22)---Q
(22)---:
(22)---:
3--------.-------------i----------------------$------------------------
C130J1-66,134J1B-77C130J1-79,134J1B-78170J1B-H14
170J1B-H15
E170J1B-H14
E170J1B-H15
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of information on this page is subject 10 the restrictions on the title page of this document.
IOB_P_
(o)
(o)(o)(o)(o)(o)
(o)
(o)
(o)
(o)
(o)(o)
(o)
(o)
(o)(o)(o)(o)(o)
Fault Warning Computer No. 2
Function connector Pin
RED AURAL C134J1B-87 (22)-------------------(28V/OPEN)AMBER AURAL (28V/OPEN) -88 (22)-------------------BLUE AURAL (28V/OPEN) -89 (22)-------------------INHIBIT OUTPUT (28V/OPEN) -90 (22)-------------------A/P DISC TEST (28V/OPEN) -91 (22)-------------------GEAR HORN INHIBIT -92 (22)-------------------(28V/OPEN)EICAS FAIL -93 (22)-------------------(OPEN/28V)DOWNLOAD IN PROGRESS -94 (22)-------------------(28V/OPEN)ERASE IN PROGRESS -95 (22)-------------------(28V/OPEN)AUTOTHROTTLE OFF HORN -96 (22)-------------------(28V/OPEN)APOFF HORN (28V/OPEN) -97 (22)-------------------MASTER WARNING -98 (22)-------------------ANNUN (28V/OPEN)MASTER CAUTION ANNUN -99 (22)-------------------(28V/OPEN)VALT ALERT HORN -1oo (22)------------------
DATA DN LOAD RS232 TXDi
-101 (22)--------- -------DATA DN LOAD RS232 RXD -102 (22)------:-- -------DATA DN LOAD RS232 RTS -103 ------NCDATA DN LOAD RS232 CTS -104 ------NCDATA DN LOAD RS232 DTR -105 ------NC
SPARE C134J1B-106
Connects To
A/C WIRING1
A/C WIRINGA/C WIRINGA/C WIRINGA/C WIRINGA/C WIRING
A/C WIRINGIAPPX D
t
REFAPPX
APPX II c
APPX DI
APPX DAPPX D
APPX D JA/C WIRING,134J1B-1OOAPPX DAPPX D
Interconnect InformationTable 501 (cent) 22-14-00
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Use or dmclosure of mformallon on this page IS subject to the r ?stncllons on the tllle page of thts ticument,
GLOBAL POSITIONING SYSTEM SENSOR UNIT No. 2 (OPTIONAL)
IOB~ Function Connector Pin Connects To
(o) GPSSU FAULT C149J1-1 (22)------------------- APPXC
(B) DADC1 429 INPUT (H) -6 (22)----a
%
------ a--- DADC #1
(B) DADC1 429 INPUT (L) -7 (22)----; ------J;--- DADC #1SHIELD GND----------- --- SHIELD GND
(o) INPUT DISCRETE RETURN -8 ----NC(0) TIME MARK #2 (H) -9 ----NC(0) TIME MARK #2 (L) -22 ----NC
(B) DADC2 429 INPUT (H)*
-lo (22)--f- -------n --- IIADC#2(B) DADC2 429 INPUT (L) -11 (22)--
1’- ‘------“~~~ ~~~~J2GNDSHIELD GND-------A--- Y
(0) TIME MARK #3 (H) -13 ----NC(0) TIME MARK #3 (L) -14 ----NC(B) IRS1/FMSl 429 INPUT (H) -18 (22)---?
$n------ ---- C121J1A-50
(B) IRS1/FMSl 429 INPUT (L)b
-37 (22)--- - ------~;--- C121J1A-51SHIELD GND--------—- --- SHIELDGND
(0) TIME MARK #1 (H) -19 ----NC(0) TIME MARK #1 (L) -20 ----NC(1) 429 OUTPUT HS/LS SELECT* -21 ----NC
$
APPX C(B) 429 OUTPUT #2 (H) -24 (22)---fi .----- --- 121J1A-23(B) 429 OUTPUT #2 (L) -25 (22)---? ------f--- 121J1A-24
SHIELD GND------------ 9 --- SHIELDGND
(B) IRS2/FMS2 429 INPUT (H)$
-26 (22)---n.- ---------- 121J1A-50(B) IRS2/FMS2 429 INPUT (L) -27 (22)---1~- ------J;--- 121J1A-51
SHIELD GND----------- --- SHIELD GND
(B) 429 OUTPUT #3 (H) -29 (22)---P*-------A
il--- APPX G(B) 429 OUTPUT #3 (L) -30 (22)--J’-
7----------
?APPX G
SHIELD GND------------ --- SHIELD GND
(P) CHASSIS GROUND -33 (22)------------------ A/C CHASSIS GND(P) +28V POWER RETURN -34 (22)------------------ A/C POWER GND(P) +28V DC POWER -35 (22)------------------ A/C+28VDC
$
POWER(B) 4290UTPUT #1 (H) -38 (22)---Q ------+--- C121J1A-26(B) 429 OUTPUT #1 (L) -39 (22)---”
Y----------
‘?C121J1A-27
SHIELD GND----------- --- SHIELDGND(I) DADC 419/429 SELECT* C149J1-40 ----NC APPX C
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INERTIAL REFERENCE UNIT NO. 2
IOB_P_ Function Connector Pin Connects To
(I) IDENT RES R1 C170JlA-Al ----NC
(I) SDI/4 -A7 ----NC
(r) IDENT RES R2 -B1 ----NC
(1) IDENT RES R3 “cl ----NC(I) IDENT RES COM -C2 ----NC
(1) IDENT RES R4 -~1 ----NC
(B) GPS2 429 INPUT #l (H) -E2 ----NC(B) GPS2 429 INPUT #l (L) -E3 ----NC(B) GPS1 429 INPUT #2 (H) -E4 ----NC(B) GPS1 429 INPUT #2 (L) -E5 ----NC(o) CTVAL 1 -E6 ----NC(o) CTVAL 2 -E7 ----MC
(o) AC FAIL LOGIC OUT -E1O ----NC(1) AC TO BATT XFER -En ----NC
(1) ASCB FORMAT SEL -E13 (22)----------------- C170J1B-A1(I) 37 WORD FORMAT -E14 (22)----------------- C170J1B-A1
(I) GPS2 TIME MARK (]Hz) #l (H}-F4 ----NC(1) GPS2 TIME MARK (]Hz) #1 {L)-F5 ----NC
(1) GPS1 TIME MARK (lHz) #2 (H)-G2 ----NC(1) GPSI TIME MARK (]Hz) #2 (L)-G3 ----NC
(o) CHARGER INHIBIT C170J1A-G9 (22)------------------ IRU BATTERY(28V/0)
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INERTIAL REFERENCE UNIT No. 2
IOB& ~ Connector Pin Connects To
(B) SYS ASCB PRI (H) C170J1A-H1 (22)--fl-$
----------- REF SECT3.3(B) SYS ASCB PRI (L) -H2 (22)--~- ------- ----
(B) RS 232 DATA XMTR -H3 (22)--fi-
t“
------ --- TEST CONNECTOR(B) RS 232 DATA RCVR -H4 (22)--ii- ------::--- TEST CONNECTOR(B) RS 232 COMMON -H7 (22)-- - ------- --- TEST CONNECTOR
SHIELD GND---------- Y Y --- SHIELDGND
(B) RS 232 DTR -H5 ----NC(B) RS 232 CTS -H6 ----NC
(I) MEM ACCESS MR ENA (GND/0) -H1O (22)----------------- FLT TEST ONLY
(I) SDI/3 -J9 ----NC
(B) SYS ASCB SEC (H) -K1 (22)--fl-*
----------- REFSECT 3.3(B) SYS ASCB SEC (L) -K2 (22)_\- ------- ----
(1) ~:~:,~~ITE INHIBIT C170J1A-K6 ----NC
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71
INERTIAL REFERENCE UNIT No. 2
Function C~nnector Pin
LOGIC GROUND C170J1B-AI mw~----------------IRU ORIENT/1 -AZIl?uoRIENT/2 -A3 (22)------------------
Connects To
172J3-U
C170JIB-A1
(o)(I)(I)
sDI/2 -A7 ----NCFMS2 429 INPUT (H) -A8 (22)----9-
$fl---..---.--
GEN BUS PRIMARY (L)i
-A9 (22)---- -- -----+---SHIELD GND------------ ---
(1)(B)(B)
C121J1A-62C121J1A-49SHIELD GND
REMOTE TEST -A1O (22)-------------:---ISDU/NDU 429 INPUT (H)
r
-A13 (22)---~- ----- ---
ISDU/NDU429 INPUT (L) -A14 (22)---+- __-;_-
172J3-W171J3-24 (OPT)198J3-24 (OPT)171J3-25 (OPT)198J3-25 (OPT)SHIELD GND
(1}(B)
(B)
SHIELD GOD------------ I 1---
BATT FAIL ANNUN (GND/0) -A15 (22)----------------- DIM & TEST PANEL(o)
FMS1 429 INPUT (H)$
-C5 (22)---fi-- ------ --GEN BUS SECONDARY {L) -C6 (22)---- -- ----1--
Y Y---SHIELD GND------------
121J1B-3121JIB-15SHIELD GND
(B)(B)
FAULT ANNUN (GND/0) -D2 (22)------------------ATT ANNUN (GND/0) -D3 ----NC
DIM & TEST PANEL(o)(o)
NO AIR ANNUN (GND/0) -El ----NCON DC ANNUN (GND/0) -E2 ----NCNAV READY ANNUN (GND/0) -E3 ----NC
ARINC 4290UT #2 (H) -E5 (22)---fl-$
n------.---ARINC 429 OUT #2 (L) -E6 (22)---- -- 11
Y Y-------------
SHIELD GND------------
(0)(0)(0)
65J1B-4865J1B-49SHIELD GND
(B)(B)
MODE DISCRETE/1 (GND/0) -F1 (22)------------------MODE DISCRETE/2 (GND/0) -F2 (22)------------------ALIGN ANNUN (GND/0) -F3 (22)------------------
172J3-e172J3-fDIM & TEST PANEL
{1)(I)(I)
ARINC 429 OUT #4 (H) -F14 (22)--fi-
$
.----~---
ARINC 429 OUT #4 (L)C170J1B-F15 (22)---!!- .-.--4---
E65J1B-4859J1-KE65JIB-4959J1-LSHIELD GND
(B)
(B)
SHIELD GND------------ 1 I---
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INERTIAL REFERENCE UNIT No. 2
IOB~ Function Connector Pin Connects To
(0) IRU VALID C170J1B-G1 ----NC
(B) ARINC 429 OUT #1 (H) -G7 (22)---~-
$
------II--- 171J3-26 (OPT)
198J3-26 (OPT)(B) ARINC 429 OUT #1 (L) -G8 (22)--”- -------:’--- 171J3-27 (opT)
Ii198J3-27 (OPT)
SHIELD GND----------- --- SHIELD GND
(B) ARINC 429 OUT #5 (H)$
-G14 (22)-43- ----------- DDRMI #2(B) ARINC 429 OUT #5 (L) -G15 (22)-;- -------ii--- DDRMI #2
SHIELD GND----------- Y --- SHIELDGND
(B) ARINC 429 OUT #6 (H)
t
-H14 (22)-:- -------fl--- 134J1B-50
(B) ARINC 429 OUT #6 (L) j -------f::: ~g;;-H15 (22)-’ -
SHIELD GOD----------
(1) DADC 429/575 SEL (GNO/0) -J6 (22)------------------ C170JlB-Al
(I) SDI/1 (GND/0) -J9 (22)------------------ c170J1B-A1(B) DADC 429 INPUT (H)
~-J1O (22)-~- --------m--- C9J1B-30
(B) SECONDARY DATA BUS (L) -Jll (22)-J -?
-------J-’--- C9J1B-31SHIELD GOD----------- Y --- SHIELD GND
(0) ON BATT ANNUN (GND/0) -J15 (22)----------------- DIM & TEST PANEL
(B) DADC 429 INPUT (H) -K4 (22)--~$
------ --- 9J1B-30(B) PRIMARY DATA BUS (L) -K5 (22)--} __l- 9J1B-31
SHIELD GND----------- Y --- SHIELDGND
(B) ARINC 429 OUT #3 (H)$
-K12 (22)-fi- ------ --- C65J1B-48(B) ARINC 429 OUT #3 (L)C170J1B-K13 (22)- C65J1B-49
‘?- ‘------?~~ SH~ELD GNDSHIELD GND-----------
Interconnect InformationTable 501 (cent) 22-14-00
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INERTIAL REFERENCE UNIT No. 2
IOB_P_ Function Connector Pin Connects To
(P) 115V AC, 400Hz,PWR C170J1C-1 (20)------------------ A/C AC PWR(P) +24V DC BATTERY INPUT -2 (16)------------------ IRU BATT JIB-8
(P) +28V DC ESSENTIAL INPUT -4 (20)------------------(P) 115V AC, 400Hz RETURN -5 (20)------------------(P) +28V DC ISDU/NDU PWR -6 (20)------------------
(P) +28V DC INPUT -7 (16)------------------(P) 28V DC/BATT RETURN -8 (16)------------------(P) ANNUNCIATOR PWR OUT -9 (20)------------------(P) ANNUNCIATOR PWR IN(I)
-10 (16)------------------CHASSIS GND C170J1C-11 (16)------------------
A/C DC PWRA/C AC RTN172J3-M171J3-3 (OPT)198J3-3 (OPT)A/C DC PWRA/C DC RTN172J3-LA/C DC PWRCHASSIS GND
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INERTIAL REFERENCE UNIT No. 3
ATTITUDE HEADI~[ REFERENCE UNIT
Function Connector Pin Connects To
E170J1B-A1
(I) IDENT RES RI E170J1A-AI ----NC
(I) sDI/4 -A7 (22)------------------
(1) IDENT RES R2 -B] ---- NC
(I) IDENT RES COM -C2 ---- Nc
(I) IDENT RES R4 -D] ----NC
(B)(B)(B)(B)(o)
GPS1 429 INPUT #3 (H) -E2 ----NCGPS1 429 INPUT #3 (L) -E3 ----NCGPS2 429 INPUT #3 (H) -E4 “---NCGPS2 429 INPUT #3 (L) -E5 ----NCCTVAL 1 -E6 (22)------------------ IOJIB-95
C1OJ1B-951OJ1B-96C1OJIB-96
(o} CTVAL 2 -E7 (22)------------------
(o)(I)
AC FAIL LOGIC OUT -E1O ----NCAC TO BATT XFER -En ----NC
(1)(1)
ASCB FORMAT SEL -E13 (22)-----------------37 WORD FORMAT -E14 (22)-----------------
E170J1B-AIE170J1B-A1
(I)(1)
GPSI TIIIEMARK (lHz) #3 (tl)-F4----NCGPS1 TIME MARK (lHz) #3 (L)-F5 ----NC
(1)(1)
GPS2 TIPIEMARK (]ttZ)#3 (H)-G2 ----NCGPS2 TIME MARK (lHz) #3 (L)-G3 ----NC
(o) CHARGER INHIBIT E170J1A-G9 ----NC(2av/o)
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L
(B)(B)
(B)(B)(B)
(B)(B)
(I)
(I)
(B)(B)
(I)
INERTIAL REFERENCE UNIT No. 3
ATTITUDE HEADI;( REFERENCE UNIT
E!4MmI! Connector Pin
SYS ASCB PRI (H)$
E170J1A-H1 (22)--n-- -----------SYSASCB PRI (L) -H2 (22)--{-- -----------
AS 232 DATA XMTR -H3 (22)--fl-
$
---.--p<--RS 232 DATA RCVR -H4 (22)--1-- -----------RS 232 COMNON
?-H7 (22)-- -
+I------ ---
SHIELD GND----------- ---
RS 232 DTR -H5 ----NCRS 232 CTS -H6 ----NC
MEM ACCESS WR ENA (GND/0) -H1O (22)-----------------
sDI/3 -J9 (22)------------------
SYS ASCB SEC (H) -K1 (22)--fl-*
-----------SYSASCB SEC (L) -K2 (22)+- -----------
BITE WRITE INHIBIT E170J1A-K6 ----NC(GND/0)
Connects To
REF SECT3.3
TEST CONNECTORTEST CONNECTORTEST CONNECTORSHIELD GND
FLT TEST ONLY
170J1B-A1
REF SECT3.3
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INERTIAL REFERENCE UNIT No. 3
ATTITUDE HEADIti’”REFERENCEUNIT
E!l!Etm Connector Pin Connects To
172J1-UE170J1B-A1E170J1B-A1
LOGIC GROUND E170J1B-A1 (22)------------------IRU ORIENT/1 -A2 (22)------------------IRU ORIENT/2 -A3 (22)------------------
(o)(1)(I)
(I)(B)(B)
SDI/2 -A7 (22)-----
$
---.--------FMS1 429 INPUT (H) -A8 (22)--~- -------n
GEN BUS SECONDARY (L) -A9 (22)--11-11---
Y---.-------
SHIELD GOD----------- ? ---
E170J1B-A1121J1B-3121J1B-15SHIELD GND
(I)(B)
(B)
REMOTE TEST -A1O (22)---- ------------ISDU/NDU 429 INPUT (H)
t
-A13 (22)-fl- A------- ---11
ISDU/NDU 429 INPUT (L) -A14 (22)-”- --------’’---7 7
172J2-W171J2-24 (OPT)198J2-24 (OPT)171J2-25 (OPT)198J2-25 (OPT)SHIELD GNDSHIELD GOD-----------1 1---
(0) BATT FAIL ANNUN (GND/0) -A15 (22)----------------- DIM&TEST PANEL
FMS2 429 INPUT (H) -C5 (22)--~*-.----- ---
GEN BUS PRIMARY SH1~~~GND-C6 (22)-~4- -------------------__.. ---
(B)(B)
C121J1B-3C121J1B-15SHIELD GND
(o)(o)
FAULT ANNUN (GND/0) -D2 (22)------------------ATT ANNUN (GND/0) -D3 ----NC
DIM&TEST PANEL
(o) NO AIR ANNUN (GND/0) -El (22)------------------ 134J1A-27,C134J1A-27
(o) ON DC ANNUN (GND/0) -E2 ----NC
ARINC 429 OUT #2 (H) -E5 (22)--m$
-------aARINC 429 OUT #2 (L) -E6 (22)--{-
~1--------------SHIELD GND----------- ‘?---
(B)(B)
65J1B-865J1B-9SHIELD GND
(I)(I)(1)
MODE DISCRETE/1 (GND/0) -F1 (22)------------------MODE DISCRETE/2 (GND/0) -F2 (22)------------------ALIGN ANNUN (GND/0) -F3 (22)------------------
172J2-e172J2-fDIM &TEST PANEL
ARINC 429 OUT #4 (H) -F14 (22)-fl-$
------$---ARINC 4290UT#4 (L)E170J1B-F15 (22)- - ------- ---YSHIELD GND----------- Y ---
(B)(B)
E65J1B-8E65J1B-9SHIELD GND
Interconnect InformationTable 501 (cent) 22-14-00
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INERTIAL REFERENCE UNIT No. 3
ATTITUDE HEADI~( REFERENCE UNIT
IOB~ Function Connector Pin Connects To
(0) IRUVALIfl E170J1B-GI ----NC
(B) ARINC4290UT#l (H)
i
-G7 (22)---R-- -----:--- 171J2-26 (OPT)198J2-26 (OPT)
(B) ARINC4290UT#l (L) -G8 (22)---”-
r
-----4--- 171J2-27 (OPT)198J2-27 (OPT)
SHIELD GND----------- ---- SHIELDGND
(B) ARINC4290UT#5 (H) -G14 (22)--fi-
2
-----n.- DDRMI #1DDRMI #2
(B) ARINC4290UT#5 (L) -G15 (22)--’t-il
r -----Y
--- DDRMI #1DDRMI #2
SHIELD GND------------ --- SHIELDGND
(B) ARINC4290UT#6 (H) -H14 (22)--fi-
$
.---. ---It 134J1B-81
C134J1B-81(B) ARINC4290UT#6 (L) -H15 (22)--i’-
I1~ + --- 134J1B-82C134J1B-82
SHIELD GND------------ --- SHIELD GND
(1) DADC429/575SEL (GND/0) -J6 (22)-------------------C170J1B-A1
(1) SDI/1 (GND/0) -J9 ----NC(B) DADC 429 INPUT (H)
$-J1O (22)--~- -------@--- 9J1B-70
(B) SECONDARY DATA BUS (L) -Jll (22)--Y- ------J 1--- 9J1B-71SHIELD GND----------- t-- SHIELDGND
(0) ON BATT ANNUN (GND/0) -J15 (22)----------------- DIM&TEST PANEL
(B) DADC 429 INPUT (H)*
-K4 (22)--a- ---------- C9J1B-70(B) PRIMARY DATA BUSSHIE[;)GND-K5 (22)--;- ------+--- C9J1B-71
.-------- -- --- SHIELDGND
(B) ARINC4290UT#3 (H)$
-K12 (22)--~- ------ --- C65J1B-8(B) ARINC4290UT#3 (L)E170J1B-K13 (22)+- ------$ -- C65J1B-9
SHIELD GND----------- --- SHIELDGND
Interconnect InformationTable 501 (cent)
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INERTIAL REFERENCE UNIT No. 3
ATTITUDE HEADI;: REFERENCE UNIT
IOB~ Function Connector Pin Connects To
(P) 115VAC, 400Hz, PWR E170J1C-1 (20)------------------ A/C AC PWR(P) +24V DC BATTERY INPUT -2 (16)------------------ IRU BATT JIB-8
(P) +28V DC ESSENTIAL INPUT -4 (20)------------------ A/C DC PWR(P) 115V AC, 400Hz RETURN -5 (20)------------------ A/C AC RTN(P) +28V DC ISDU/NDU PWR -6 (20)------------------ 172J2-M
171J2-3 (OPT)198J2-3 (OPT)
(P) +28V DC INPUT -7 (16)------------------ A/C DC PWR(P) 28V DC/BATT RETURN -8 (16)------------------ A/C DC RTN(P) ANNUNCIATOR PWR OUT -9 (20)------------------ 172J1-L[~] ANNUNCIATOR PWR IN -10 (16)------------------ A/C DC PWR
CHASSIS GND E170J1C-11 (16)------------------ CHASSIS GND
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APPENDIX ASYMBOL GENERATOR/DISPLAY UNIT
INTERFACE REQUIREMENTS
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APPENDIX ASYMBOL GENERATOR/DISPLAY UNIT INTERFACE REQUIREMENTS
1.0 SYMBOL GENERATOR/DISPLAY UNIT INTERFACE REQUIREMENTS
The following paragraphs define the electrical interface requirements forthe Symbol Generator/Display Unit interconnect.
a. The SG/DU transmission lines shall be Raychem 2524E0114 with athermorad jacket or its equivalent. (This same cable is used forASCB) . Each transmission line pair shall have a characteristicimpedance of 125 f 5 ohms. The characteristic capacitance shall be 12t 2 picofarads/foot.
b. DUS are to be connected to a bus as shown below. Only the DIJat theend of the cable shall be terminated..
c. One to six Display Units may be connected to a single 1 MHz SG busoutput .
d. Each DU has provisions for bus termination. The + input is alwaysused. The - input is used if the DU does not provide the bustermination. The TRM - input is used to terminate the bus within thedisplay unit.
Note that if a terminating DU is removed from the panel, all remainingDUS utilizing that particular bus may fail to operate or may operateintermittently. Therefore, optional termination resistors can beincorporated into the aircraft wiring should dispatch without a DU berequired. The termination resistors should be 120, 5??,1/2 W, carboncomposition.
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HIGH SPEED DIFFERENTIAL INPUT TERMINATION
%w.[TE:-:;~@ii
.— —-1*
L——— ——— —AD-9063-R1
e. The cable shield should be connected to airframe ground at one pointonly, preferably at the symbol generator as shown in paragraph l.O.b.The length of the wire connecting the shield to airframe ground shouldbe 18 in. maximum.
f. The maximum stub length is3 ft. The minimum distance between stubs is2 ft.
9“ The unshielded distance from the end of the shield to the rear of aconnector is 2 in. maximum.
h. The maximum cable length from a Symbol Generator to the DU at the endof a 1 MHz Bus is 200 ft.
1.1 Svmbol Generator No. l/Disr)layUnits
FiguresA-l, A-2, andA-3 illustratethe three Symbol Generator/DisplayUnitinterconnectsfor Symbol Generator No. 1.
Interconnect InformationTable 501 (cent) 22-14-00
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———‘D~LR~&l 1
IPILOTPFD
130J17
IPRI+ 38 !?
PRl- 39 !W!
IPRITRM- 52
L ——— —— d
r ———S=LR~65
7
ISYMBOL GENERATOR
65J1A
SG/DU BUS A (H) 22 y; ,q: ‘:: ~
I (L) 23II II
e u
I Y-SHIELD GND
L ——— —— dr ———
D=LR~331
I133.)1
EICASSYS/WARN
.q: :
:; j
IALT 2+ 19 :-:
ALT 2- 20 .! !:!
IALT 2 TRM - 33 -u -4: :-: :)
k ———— . -
r .——D=L=&O
1
I
C130J1COPILOT PFD - ~: ::::)
IALT 2+ 19 !; ;~;
ALT 2 TRM - 33 .. s.
I ALT 2- 20
k ——— —— d Ao-12zes-Rl
Symbol Generator No. 1 (Bus A/Display Unit Interconnect)Figure A-1
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r ——— 7D~LR~ti 131J1
IPILOTND
I
n
PRI+ 38 ,-1
PRI- 39 -
IPRITRM- 52
1- ———— —
r ——— 1
I
S+LR~=SYMBOL GENERATOR
65JIB
,p: ‘:” ~>
ISG/DU BUS B (H) 22 , ‘/-; II II
(L) 23 ~?’
4 .
L ———— — J r ———D=LR~=
1
I
132J1EICASENG/WARN
P
r
I
ALT2+ 19 -1 [11
ALT2- ~
IALT2 TRM- 33 G
L ———— —
Symbol Generator No. 1 (Bus B/Display Unit Interconnect)Figure A-2
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p——— ——-‘SGIILRU65
a
ISYMBOL GENERATOR 85J1A
ISG/DU WXRBUS (H) 45 ‘-!SG/DU WXRBUS (L) 46 .!!
I L SHIELD GND
L ——— —— J’ r ——— ——DU2/LRU131
1
I131J1
DISPLAYUNITNO.2P.ND
P
Wxl+ 77 ,-, J’
I IIWX1- 78 ~
I WX1TRM- 84 L
L ——— ——
r ——— —Du5/LRuct31
ti
—1
IC131J1
DISPLAYUNITNO.5CP.ND Wxl+ 77 - P
I WX 1TRM- 8411114W
I PWX 1- 78
1- .—— ——
Symbol Generator No. 1 (WXR/Display Unit Interconnect)Figure A-3
AO-12S91-RI
:)
I
‘)
)
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1.2 Svmbol Generator No. 21Dis~lav Units
Figures A-4, A-5, and A-6 illustrate the Symbol Generator/Display Unitinterconnectsfor Symbol Generator No. 2.
r ———D=LRm30
-1
I
130J1COPILOTPFD 7
I
PRI+ 36 ~=iPRl- 39 :-;
IPRITRM- 52
L ——— —— d
r .——s=LRTa5
7
ISYMBOL GENERATOR
C65J1A7
,q ‘:: :>
ISG/DUBUSA(H) 22 ‘/-; 7
II II(L) 23 d .
I t- SHIELDGND
L ———— — . r ———D=LR==
1
I133J1
ElC’sSYS/WARN :::)
I
ALT 1+ % :-:1111
ALT 1- 36 :-: 4
IALTITRM- 49 L : ::: )
J~
k ——— —— -
r ——— -1
ID=L=c130PILOTPFD
I
IL ——— —— AO-1Z2S2-R1
Symbol Generator No. 2 (Bus A/Display Unit Interconnect)Figure A-4
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r ———t)~LR;’ 1
I131 J1
COPILOT ND -
IPRI+ 38 ‘ !-!
PRl- 39 !-:
IPRITRM- 52
L .—— — — J
r ———szLRTm5 -1
ISYMBOL GENERATOR C65J1B
I
SG/DU BUS B (H) 22 , r! ,p:: ‘: ~
(L) 23 :! II IId .
I s- SHIELDGND
L ——. —— . r ———D~LR~32 -1
IEICASENG/WARN
132J1
I1111
ALT 1- 36
IALT 1TRM- 49
k ——— —— d
———‘D=LR~C131
T
IPILOT ND d:: ::;)
IALT 2+ 19 . ;-/ !4’
ALT2 TRM- 33 ,II
1
ALT 2- ~ - ‘“
L ———— — -Ao-~1
Symbol Generator No. 2 (Bus B/Display Unit Interconnect)Figure A-5
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r ———S=L==
-1
IC65J1A
SYMBOL GENERATOR 7
I
SG/DU WXRBUS (H) 45 ‘~;SG/DU WXRBUS (L) 46 .
I
L SHIELD GND
L ——— —. d + r ——— ——Du5/LRu131
7
I
131J1DISPLAY UNIT NO. 2
,q; :“ ‘-. .)
COPILOT ND
I
WX2+ 74 ,-!1111
wx2- 75 .
IWX2TRM- 61 “ L: :- :-. )
L ——— —— .
——. ——‘DlJ2/LRU C131
1
I
C131J1DISPLAY UNIT NO. 5
,r- ‘-’-, ,)
PILOT ND
IWX2+74 :-:
WX2TRM- 61 ~ ; !“!
I
wx2- 75 “
1- ——— —— dAo-lz2w-Rl
Symbol Generator No. 2 (WXR/Display Unit Interconnect)Figure 4-6
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L..J Svmbol Generator No. 3/DisDlav Unit Interconnect
Figures A-7, A-8, and A-9 illustrate the Symbolinterconnects for Symbol Generator No. 3.
P ——— .— -‘DU1/LRU130 8
I130J1
PILOTPFDt-_
I J+ALT1+ 35ALT1- ~
I ALTITRM- 49
L .—— .—
I I.&J~SHEILD GND
Generator/Disp” ay Un t
IEICASSYS/WARN
IPRI+
PRI-
IPRITRM-
L — — —— —,
r ——— .
ID=LR~~30COPILOTPPD
IALT 1+
ALTITRM-
1 ALTl-
k — —— — —<
52 I
%J
Symbol Generator No. 3 (Bus A/Display Unit Interconnect)Figure A-7
Use or disclosure of information
Interconnect InformationTable 501 (cent)
on this page is subject to the restrictions
22-14-00Page 598.118
Mar 15/91on the tile page of this document.
r ———D=i=~ 1
I131J1
PILOT ND
I
~
ALT I + 35 ,;
.ALTI - m -
IALT 1 TRM - 49
L ——— ——
r ———S=LR~E6S
7
ISYMBOL GENERATOR
SVDU BUS B (H) 22 ‘7,~: ‘:” ~~
I (L) 23 .II II Id .
I
L SHIELD GNC
L ———— — . r ———D=LR;32
Y
IEICASENG/WARN
.q:::)
I PRl- 39 .!-!!!
IPRITRM - 52 Gi *- :: :)
& ———— — &
r ———D=LR~~31
P
-1
I
C’131JlCOPILOT ND p:)
IALT 1+ 35 :1 ,*1
ALT 1TRM- 49
I
ALTI - ~ -
& ———— — AS7ZSRI
Symbol Generator No. 3 (Bus B/Display Unit Interconnect)Figure A-8
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rS=LR~E&’— —
—7
ISYMBOL GENERATOR
E65J1A
I
SGIDU WXR BUS(H) 45 !:; 7SG/DU WXRBUS (L) 46 ,
I
‘t SHIELD GND
L~ E65JIA
——— —— r ——— ——DU2/LRU 131
1
IDISPLAYUNITNO.2131J1
F: ‘- “-: .)
P. ND
IWX3 + 69 .;-; ;;
wx3- 70 4 )
I WX3TRM- 63 “L ‘-a ~: .-. )
L ——— ——
r ——— ——DU5LRU C131
1
IDISPLAYUNITNO.5 P: : ‘::.)
CF.ND
IWx3+ 69.~-:;;
WX3TRM- 63 ;-; :W:
Iwx3- 70
1- ——— .— dAD-12297-RI
Symbol Generator No. 3 (WXR/Display Unit Interconnect)Figure A-9
Interconnect InformationTable 501 (cent) 22-14-00
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APPENDIX BREVERSIONARY SELECT REQUIREMENTS
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APPENDIX BREVERSIONARY SELECT REQUIREMENTS
1.0 ELECTRONIC DISPLAY SYSTEM REVERSIONARYSELECTION
1.1 Introduction
The Rev Controller shall provide the flight crew with one controller withwhich to control all Rev modes of the Electronic Display System (EDS).This controller shall be designed to meet the following criteria:
1. The Rev Controller shall be functionally easy to understand and tooperate. This is of importance due to the flight crew’s need toutilize the Rev Controller in the event of an EDS failure.
2. The Rev Controller shall be extremely reliable. This shall beachieved through the utilization of mechanical switches and diodes toimplement the logic required to configure the EDS to the properreversionary states. No electronic logic devices shall be used.
The Rev Controller shall output logic commands that will be utilized bythe Symbol Generators (SGS) and Display Units (DUS) to configure to theproper reversionary state. The logic signals shall be self-latchingthereby requiring less input circuitry for the SGS and DUS. Theself-latching requirement shall be met through the utilization ofself-latchingmechanical switches.
The Rev Controller utilized on the G-IV is manufactured by GulfstreamAerospace Corporation. The internal schematic and output pins are shownin Figure B-2.
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1.2 Functional Descrit)tion
The Rev Controller shall provide control of all the Electronic DisplaySystem reversionary states. A complete tabulation of all reversionarystates and resulting system configurations is provided in Table B-2 (A) -(E). These tables can be reduced to provide the DU input port switchinglogic as presented in Table B-3.
1.2.1 SG ReversionarySelect
In the event of the absence of a signal from the SG, the DU shalldisplay a message to the flight crew that a SG failure has occurred(i.e. Red X). The flight crew will then select the proper SG Rev Selectto reconfigure the EDS to compensate for the particular SG failure.
The SGS shall utilize the SG Rev Select logic to shut down or toreconfigure their output formats due to one of the SGS being shut down.
The DUS shall utilize the SG Rev Select logic to reconfigure their inputports to match the configuration of the operable SGS.
1.2.2 DU Reversionary Select
In the event of a DU failure, the flight crew will utilize the RevController to reconfigure the EDS to the proper reversionary state.
The DUS shall utilize the DU Rev Select logic to shutdown if applicable.
The SGS shall utilize the DU Rev Select logic to reconfigure theiroutput ports to supply the proper formats to the reconfigured DUS.
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REVERSIONARYCONTROL
SWITCHING
A—SG1 FAIL ● ~LB–SG1 FAIL @ SGS FAILC–SG3 FAIL ● SG2 FAILD—SG3 FAIL . SG2 FAILE—SG2 FAIL ● ~
AO+770-R3
Electronic Display System’s ExternalReversionary Interface Schematic for the G-IV
Figure B-1
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——— .—— — —.—— ——REVERSIONARYCONTROL(PAGE1~
AL-r r
‘c-cQ—. i .SGNO.IFAIL
. 0 I - BGNO.1FAIL* SGNO.3 ~L- Du NO.1ANDNO.2 PORTSELA
v
~/
r’=
II SGNO.1FAIL● SGNO.3FAIL
N/c DUNO.1ANDNO.2PORTSELB z
~I
N/co IWCyc
{NM’MW SGCONTROL
PILOT
ALT
~&3GN0.3FAILE
I1I
)
;
i I
L-,=~:=sG~2,A,L*=No3FA,L-N/c , OUNO.SANDNO.6PORTSELB
I
SGN0.2FAlL. SGNO.3~N/Crl DUANO.5ANDN0.6BELA
I
(
SGWtilROL‘WW COPILOT
t%
WI-66
131J1-66
F65J1A-62,ES5J1A-SS,62.mum-a
G ce5JlA-6z,c134JlA-43
r 13UM6
133WS6
‘1F CSSJIA-66.SI,
C134.IIA-42
r 6sJlA-61,Es5JlA.61,lMJIA.4zSGNO.3WXSELREUY
ReversionaryControl1erFigure B-2 (Page 1 of 2)
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m=!?!”.
-
ReversionaryControllerFigure B-2 (Page 2 of 2)
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WI SG3 SG2. FA~8RE BUS1 BUS2 BUS1 BUS2
COMMENTBUS1 BUS2
NORMAL PFD – ND – – SYS – ENG PFD – ND –
DU1 DU2 DU4 DU3 DU6 DU5
DU1FAIL — — PFD – – SYS – ENG PFD – ND –
(PLT PFD) DU2 DU4 DU3 DU6 DU5
DU2 FAIL PFD – – – – SVs – ENG PFD – ND –
- }NO REV PROVISION
(PI.T ND) DUI DU4 DU3 DU6 DU5
DU3 FAIL PFD — ND – – COMP – – PFD – ND –
(ENQ) DU1 DU2 DU4 DU6 DU5
DU4FAIL PFD — ND – – — — COMP PFD – ND –
(SYWWARN) DU1 DU2 DU3 DU6 DU5
DU5FAIL PFD – ND – – SYS – ENG PFD – – –
}NO REV PROVISION
(CPLT ND) DU1 DU2 DU4 DU3 DU6
DU6 FAIL PFD — ND — — SYS – ENG – – PFD —
(CPLT PFD) DU1 DU2 DU4 DU3 DU5
DU1 AND DU2 – — – – – SYS – ENG PFD – ND –
FAIL DU4 DU3 DU6 DU5
I DU3 AND DU4 pFD – ND – – – – – PFD – ND –
1
NOREVPROVISIONSFAIL DU1 DU2 DU6 DU5
Dd5 AND DU6 PFD – ND – – SW3 – ENG – – – –
FAIL DU1 DU2 DU4 DU3
AD-6776-RI
wm<(Dz
DU SG1 SG3 SG2FAILURE Bus1 BUS 2 BUS 1 BUS 2 BUS 1
COMMENTBUS 2
NORMAL – – – – PFD SYS ND ENG PFD – ND –
DUI DU4 DU2 DU3 DU6 DU5
DUI FAIL – – — – – SYS PFD ENG PFD – ND –
(PLT PFD) DU4 DU2 DU3 DU6 DU5
DU2 FAIL – – – – PFD SYS – ENG PFD – ND –
}NO REV PROVISION
(PLT ND)— DU 1 DU4 DU3 DU6 DU5
DU3 FAIL – – – – PFD COMP ND – PFD – ND –(ENG) Du 1 DU4 DU2 DU6 DU5
DU4 FAIL – – – – PFD – ND COMP PFD – ND –
(SYS/WARN) DU 1 DU2 DU3 DU6 DU5
DU5 FAIL – – – – PFD SYS ND ENG PFD – – –
}NO REV PROVISION
(CPLT ND) DU 1 DU4 DU2 DU3 DU6.——DU6 FAIL - – – -- PFD SYS ND ENG – – PFD –
(CPLT PFD~ - IN 1 DU4 DU2 DU3 DU5_ .DU I AND DU2 – — — — — SYS – ENG PFD’ – ND –
FAIL DU4 DU3 DU6—. DU5
DU3 AND DU4 — . — — PFD – ND – PFD – ND —
1
NO REV PROVISIONSFAIL DU 1 DU2 DU6 DU5
DU5 AND DU6 – – – – PFD SYS ND ENG – – – –
FAIL DU 1 DU4 DU2 DU3AD-6777-61
NN
DU SG1 SG3 SG2FAILURE BUS 1 BUS 2 BUS 1 BUS 2 BUS 1 BUS2 COMMENT
NORMAL PFD – ND – PFD SYS ND ENG – – – –
DU1 DU2 DU6 DU4 DU5 DU3
DU1 FAIL – – PFD – PFD SYS ND ENG – – – –
(PLT PFD) DU2 DU6 DU4 DU5 DU3
DU2 FAIL PFD – – – PFD SYS ND
}
ENG – – – – No REV PROVISION
(PLT ND) DU1 DU6 DU4 DU5 DU3
DU3 FAIL PFD – ND – PFD COMP ND – – – – –
(ENG) DU1 DU2 DU6 DU4 DU5
DU4 FAIL PFD — ND — PFD — ND COMP – – – –
(SYSAVARN) DU1 DU2 DU6 DU5 DU3
DU5FAIL PFD – ND – PFD SYS – ENG – – – –
}NO REV PROVISION
(CPLT ND) DUI DU2 DU6 DU4 DU3
DU6 FAIL PFD – ND – – SYS PFD ENG – – – –
(CPLT PFD) DU1 DU2 DU4 DU5 DU3
DU1 AND DU2 – – – – PFD SYS ND ENG – – – –
FAIL DU6 DU4 DU5 DU3
DU3 ANDDU4” PFD - ND – PFD – ND – – – – –
~ 1 ._
NO REV PROVlS10t4SFAIL DU1 DU2 DU6 DU5
DU5 AND DU6 PFD – ND – – SYS - ENG – – – –
FAIL DU1 DU2 DU4 LNJjNH778-m
u
+-4.
NN
2B1
ND
DU5
ND—.DU5
ND
DU5
ND
DU5
ND
DU5
—
PFD
DU5
ND
DU5
ND
DU5
S2 !COMMENT
<
ENG
DU3
ENG
DU3
ENG
DU3
—
COMF
}NO REV PROVISION
DU SGI SG3 sFAILURE BUS t BUS 2 BUS t BUS 2 Bus 1
NORMAL PFD – ND – – – – – PFD SYS
DU 1 DU2— DU6 DU4
DU1 FAIL – – PFD – – – – – PFD SYS
(PLT PFD) DU2 DU6 DU4
DU2 FAIL PFD – – – – – – – PFD SYS
(PLT ND) DUI DU6 DU4
DU3 FAIL PFD — ND — — – – – PFD COMP
(ENG) DUI DU2 DU6 DU4
DU4 FAIL PFD — ND — — — — — PFD –
(SYS/WARN) DUI DU2 DU6 DU3
DU5 FAIL PFD – ND – – – – – PFD SYS ENG
–}NO REV PROVISION
(CPLT ND) DUI DU2 DU6 DU4 DU3—.DU6 FAIL PFD – ND – – – – – – SYS ENG
(CPLT PFD) DU1 DU2 DU4 DU3
DUI AND DU2 – – – – – – – – PFD SYS ENG
FAIL DU6 DU4 DU3
DU3 AND DU4 PFD – ND – – – – – PFD – —
- 1
NO REV PROVISIONSFAIL DU1 DU2 DU6
DU5 AND DU6 PFD – ND – – – – – – SYS I – I ENG
FAIL DUI DU2 DU4 DU3AD-6779-R1
SQ SG SGFAI?:RE BUS 1 BUS 2 BUS 1 BUS 2 BUS 1 BUS 2 COMMENT
NORMAL – – — — PFD SYS ND ENG – – – –
Dul/6 DU4 DU2f5 DU3
DU1 FAIL – – – – – SYS PFD ENG – – – –
(PLT PFD) DU4 DUW5 DU3
DU2 FAIL – – - – PFD SYS ND ENG – – – –
}NO REV PROVISION “
(PLT ND) Dul/6 DU4 DU5 DU3
DU3 FAIL – – – – PFD COMP ND – – — — —
(ENG) DU1/6 DU4 DUW5
DU4 FAIL – – – – PFD – ND COMP – – – –
(SYSA4ARN) Dul/6 DUW5 DU3
DU5 FAIL - - – – PFD SYS ND ENG — — – —
}NO REV PROVISION
(CPLT ND) Dul/6 DU4 DU2 DU3
I DU6FAIL – – – – PFD SYS ND ENG – – – – 1
t
1 I I I I##-D1 -r Drrh I . .,. ‘ -U4 DUW5 DU3
–– – – PFD SYS ND ENG – – – –)
FAIL DU6 DU4 DU5 DU3
,DU3 AND DU4 – – – – PFD – ND – – – – –
FAIL Dul/6 DUW5$1NO REV PROVISION
9U5 AND DU6 – – – – PFD SYS ND ENG – – – –
FAIL DUI DU4 DU2 0U3 )AD-6780-R1
Table B-3DU Input Port Switching Logic for the G-IV
DU INPUT PORT PORTSEL A PORTSEL B
PRIMARY OPEN OPEN1ST ALTERNATE GND OPEN2ND ALTERNATE OPEN GND3RD ALTERNATE GND GND
Dul&Du2
1ST ALTERNATE -----> SG1 FAIL “ SG3 FAIL2ND ALTERNATE -----> SG1 FAIL “ SG3 FAIL
Du3&Du4
1ST ALTERNATE -----> SG3 FAIL “ SG2 FAIL2ND ALTERNATE -----> SG3 FAIL “ SG2 FAIL
DU5&DU6
1ST ALTERNATE -----> SG2 FAIL “ SG3 FAIL2ND ALTERNATE -----> SG2 FAIL “ SG3 FAIL
Interconnect InformationTable 501 (cent) 22-14-00
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The SGS shall utilize the SG Rev Select logic to shut down or toreconfigure their output formats due to one of the SGS being shut down.
The DUS shall utilize the SG Rev Select logic to reconfigure their inputports to match the configurationof the operable SGS.
1.4.2 DU Reversionary Select
In the event of a DU failure, the flight crew will utilize the RevController to reconfigure the EDS to the proper reversionary state.
The DUS shall utilize the DU Rev Select logic to shutdown if applicable.
The SGS shall utilize the DU Rev Select logic to reconfigure theiroutput ports to supply the proper formats to the reconfiguredDUS.
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APPENDIX CDISCRETE INTERFACE SUMMARY
Interconnect InformationTable 501 (cent) 22-14-00
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APPENDIX CDISCRETE INTERFACE SUMMARY
1.0 INTRODUCTION
This appendix provides a complete listing of all the discrete inputs andoutputs to the SPZ-8000 system components. This listing is comprised ofthe information presented below.
● Name● LRU Pin Number. Type. Description
1.1 Discrete Name
The name of the discrete shall be that as utilized within the interconnect,reference Sec. 4.0.
1.2 LRU Pin Number
The LRU pin number shall be repeated here for the sake of being complete.
1.3 Discrete Tyoe
Discrete Inputs
All of the discrete inputs shall have one of the types as described below.
. Grid/OpenType A
GndVin s 1.5 VdcIsinkZ 4 uAdc
. 28 V de/Open Type A
28 V dcVin z18VdcIsource s 180 uAdc
OpenVin s 4.5 V dc
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Discrete Outputs
All of the discrete outputs shall have one of the types as described below:
. Grid/Open Type A
GndIsink s 200mAdc
. Grid/OpenType B
GndIsinkS 80 nwldc
. Grid/OpenType C
GndIsinkf 20 mAdc
● Grid/Open Type D
GndIsinks 50mAdc
. 28 V de/Open Type A
28 V dcIsource s 100 mAdc
. 28 V de/Open Type B
28 V dcIsource s 1.0 Adc
. 28 V de/Open Type C
28 V dcIsource s 1.5Adc
1.4 Discrete Descrir)tion
A brief description of each discrete shall be provided.
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3. DADC Discrete Summary
Discrete Inputs
Baro Disable 91C9J1A-38
Grid/OpenType A
Ground = Disables Barometric CorrectionOpen = Normal Operation
SSEC Disable 9/c9JlA-39
Grid/OpenType A
Ground = Disables Static Source Error CorrectionOpen = Normal Operation
DADC Self Test 9/C9JlA-52
Grid/OpenType A
Ground = Selects DADC Self TestOpen = Normal Operation
Flap Position No. 1,2,3,4 9/C9JlA-55, 56, 57, 58
Grid/OpenType A
Flaps 55 56 57 58
0 Gnd Open Open Open10 Open Gnd Open Open20 Open Open Gnd Open39 Open Open Open Gnd
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Alerter Select 9/c9JlA-93
Grid/OpenType A
Ground = Copilot DADC is MasterOpen = Pilot DADC is Master
Plt/Cplt Select 9/c9JA-loo
Grid/OpenType A
Ground = Copi1otOpen = Pilot
Aircraft ID 9/C9JlA-101,102,103,104,105,107
Grid/OpenType A
101 102 103 104 105 106
G-IV Application Gnd Open Open Gnd Open Gnd
CAA Application Gnd Gnd Gnd Gnd Open Gnd
Discrete Outputs
Altitude Valid 9/c9JlA-34
28 V de/Open Type A
28 V dc = Altitude Output is ValidOpen = Altitude Output is Invalid
Cabin Pressure Valid 9/CJIA-66
Grid/OpenType B
Ground = Cabin Pressure is ValidOpen = Cabin Pressure is Invalid
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Altitude Switch (no) 9/c9JlA-77Altitude Switch (c) 9/c9JlA-80
200 MA dc Inductive Load600 MA dc Resistive Load
Continuity between 9/C9JlA-77 and -80 when ascending through42,000 ft. Open when descending through 40,000 ft.
Overspeed Warning 9/C9JlA-85
28 V de/Open Type C
28Vdc= IndicatedAirspeed in excess of VmoOpen = Normal Operation
AOA Test 9/C9JlA-92AOA Test (SL) 9/c9JlA-97AOATest (15000) 9/C9JlA-98
Grid/OpenType A
Ground = AOA Test ActiveOpen = Normal Operation
AOA Indexer (Red) 9/c9JlA-94AOA Indexer (Green) 9/c9JlA-95AOA Indexer (Amber) 9/C9JlA-96
Grid/OpenType B
Ground = Respective Indexer is to be activeOpen = Indexer is to be off
Altitude Alert Horn 9/c9JlB-49
28 V de/Open Type A
28 V dc = Altitude AlertOpen = Annun Change Normal Operation
Provides a 2.0 second duration pulse to alert theflight crew to an Altitude Alert
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Altitude Alert Annun 9/c9JlB-75
Grid/OpenType A
Ground = Master Altitude Preselect Error is within thespecified limits
Open = Normal Operation
The specified Altitude Preselect error limits are:
o When capturing an altitude
250 ft < Alt Preselect Error < 1000 ft
o When departing an altitude
Alt Preselect Error > 250 ft.
Altitude Alert Horn 9/C9JlB-76
Grid/OpenType C
Ground = Altitude Alert Annun ChangeOpen = Normal Operation
Provides a 0.75 second duration pulse to alert the Flight Crewto an Altitude Alert.
Interconnect InformationTable 501 (cent) 22-14-00
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o. FGC Discrete Summary
Discrete Inputs
Stick Shaker Active 10/CIOJIA-28
28 V de/Open Type A
28 V dc = Stick Shaker Active (DisengageAutopilot)Gnd = Normal Operation
Yaw Damper Engage/ lo/cloJIA-40Disengage
Grid/OpenType A
Open to Gnd Transition = Engage/Disengage Toggle
Reference Appendix D
Trim Engage/Disengage lo/cloJIA-41
Grid/OpenType A
Open to Gnd Transition = Engage/DisengageToggle
Reference Appendix D
Aircraft ID 10/CIOJIB-76,77,78,79,80,81
Grid/OpenType A
76 77 78 79 80 81
G-IV Application Open Open Open Gnd Open Gnd
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Miscompare #1, #2 10/CIOJIB-95, 96
Grid/OpenType A
Ground = bliscompareOpen = No miscorrtpare
NOTE: These two pins are Installation Critical.Please see note on Page 3-13.
Rad Alt Format lo/cloJIB-99,100
Grid/OpenType A
99 100
Sperry Rad Alt Open OpenARINC 552 Open GndCollins ALT 50 Gnd OpenCollins ALT 55 Gnd Gnd
Pilot/Copilot I.D. 10/CIOJIB-102,103#1, #2
Ground/Open Type A
102 103
Pi1ot Gnd OpenCopi1ot Open Gnd
End Item Test lo/cloJIB-lo4
Grid/OpenType A
Ground = End Item Test EnableOpen = Normal Configuration
For Factory Use Only
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Autopilot Disconnect 10/C10J2B-54
Grid/OpenType A
Ground = Normal OperationOpen = Disconnects the Autopilot
Reference Appendix D
Emergency Disconnect 10/C10J2B-65
28 V de/Open Type A
28Vdc= Enables Normal AP/YD/MT EngagementOpen = Disconnects AP/YD/blT
This discrete is utilized to ensure that the AFGCS servos arecompletely disconnected when the FGC losses power.
Trim Disconnect 10/C10J2B-66
Grid/OpenType A
Ground = Normal OperationOpen = Disconnects the Trim
Yaw Damper Disconnect 10/C10J2B-67
Grid/OpenType A
Ground = Normal OperationOpen = Disconnects the Yaw Damper
Test Signal Enable 10/C10J2B-68
Grid/OpenType A
Ground = Enables Test SignalsOpen = Normal Operation
Flight Test Use Only
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FTIU Installed 10/C10L?2B-69
Grid/Open Type A
Ground = Enables FGC Interaction with the FTIUOpen = Normal Operation
Flight Test Use Only
Speed Brake 10/C10J2B-72
Grid/OpenType A
Ground = Speed Brakes DeployedOpen = Normal Operation
Weight On Wheels (WOW) 10/C10J2B-74
Grid/OpenType A
Ground = Aircraft on the GroundOpen = Aircraft is Airborne
Gear Down 10/C10J2B-78
Grid/Open Type A
Ground = Gear DownOpen = Gear Retracted
Maintenance Test Enable 10/C10J2B-79
Grid/Open Type A
Ground = Enables Maintenance TestOpen = Normal Operation
Maintenance Test is controlled via the Display Controller.
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Power Up Reset 10/C10J2B-82
Grid/OpenType A
Ground = FGC ResetOpen = Normal Operation
Discrete Outputs
Priority Status #l 1OJ1A-37
28 V de/Open Type A
28Vdc= FGC #1 has PriorityOpen = FGC #1 does not have Priority
Priority Status #2 C1OJ1A-37
28 V dc/OPen Type A-.
28 V dc = FGC #2 has PriorityOpen = FGC #2 does not have Priority
Yaw Damper Disengage 10/C10J2B-53Annun
28 V de/Open Type A
28Vdc= Yaw Damper DisengagedOpen = Yaw Damper Engaged
Reference Appendix D
Trim Disengage Annun 10/C10J2B-81
28 V de/Open Type A
28 V dc = Trim DisengagedOpen = Trim Engaged
Reference Appendix D
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CPL Select Out 10/C10J2B-88
Grid/Open Type D
Ground = Copilot CPL is ActiveOpen = Pilot CPL is Active
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11. Guidance Panel Discrete Summary
Discrete Inputs
Subtest Select ~lJ1/llJ2-35
Grid/OpenType A
Ground = Maintenance Test “Select” Button PushedOpen = Normal Operation
Maintenance Test Sel llJ1/llJ2-58
Grid/OpenType A
Ground = FGC Selected for Maintenance TestOpen = Normal Operation
Lamp Test No. 1 llJ1-64
Grid/OpenType A
Ground = All Annunciator Lamps on for 30 sec at CurrentDimming Control Level
Open = Normal Operation
Priority Status #1 llJ1-70
28 V de/Open Type A
28Vdc= FGC #l has PriorityOpen = FGC #1 does not have Priority
Weight On Wheels (WOW) llJ1-71
Grid/OpenType A
Ground = Aircraft on the GroundOpen = Aircraft is Airborne
Reference Appendix D
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Take Off/Go Around llJ1-72/llJ2-54(TOGA)
Grid/OpenType A
Vomentary ground to open transition togglesthe TOGA mode logic between engaged and disengaged.
The WOW discrete is utilized to determine whether a Take Off orGo Around is desired.
Reference Appendix D.
Touch Control Steering llJ1-74/llJ2-53(TCS)
Grid/OpenType A
Ground = Selects TCS OperationOpen = Normal Operation
Reference Appendix D
Autopilot Disconnect llJ1/J2-77
Grid/OpenType A
Ground = Normal OperationOpen = Disconnects the Autopilot
Reference Appendix D
Yaw Damper Engage/ llJ1/J2-78Disengage
Grid/OpenType A
Pomentary ground to open transition toggles the Yaw Damperbetween engaged and disengaged.
Reference Appendix D
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Trim Engage/Disengage llJ1/J2-79
Grid/OpenType A
Momentary ground to open transition toggles the trim systembetween engaged and disengaged.
Reference Appendix D
Lamp Test No. 2 11J2-64
Grid/OpenType A
Ground = All Annunciator Lamps on for 30 sec at CurrentDimming Control Level
Open = Normal Operation
Priority Status #2 11J2-70
28 V de/Open Type A
28Vdc= FGC #2 has PriorityOpen = FGC #2 does not have Priority
Discrete Outputs
GS/EL Active Gnd llJ1/J2-11
Grid/Open Type A
Ground = Approach CapturedOpen = Normal Operation
Backcourse Active Gnd llJ1/J2-14
Grid/OpenType A
Ground = Backcourse CapturedOpen = Normal Operation
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Autopilot Disengage 1131-39
Grid/Open Type A
Ground = AP Disengagement (1.0 Second)Open = Normal Operation
Yaw Damper Disengage llJ1-40Annun Gnd
Grid/OpenType A
Ground = AJtomatic YD DisengagementOpen = Normal Operation
Trim Disengage Annun lIJ1-41Gnd
Grid/OpenType A
Ground = Automatic Trim DisengagementOpen = Normal Operation
Autopilot Pistrim Annun 1131-42Gnd
Grid/OpenType A
Ground = Elevator FistrimOpen = Normal Operation
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~~. RacfAlt Iliscrete Summary
Discrete Inputs
Test Inhibit 20/c20Jl-D
Grid/Open Type A
Ground = Inhibit Rad’Alt TestOpen = Normal Operation
Test 20/c20Jl-T
Grid/Open Type A
Ground = Rad Alt TestOpen = Normal Operation
Discrete Outputs
Track Invalid 20/c20Jl-F
Grid/OpenType A
Ground = Rad Alt Unlock (no delay)Open = Normal Operation
Alt Trip (400 ft) 20/c20Jl-LAlt Trip (50 ft) 20/c20Jl-RAlt Trip (1200 ft) 20/C20Jl-UAltTrim (250 ft) 20/C20Jl-V
Grid/OpenType A
Ground = Altitude TripOpen = Normal Operation
Rad Alt Valid 20/C20Jl-Y
28 V de/Open Type A
28 V.dc = Rad Alt ValidOpen = Rad Alt Invalid
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59. Weather Radar R/T/A Discrete Summary
Discrete Inputs
WX ON 59J1-U
Grid/OpenType A
Ground = P870 WX System EnergizedOpen = P870 WX System Turned Off
REACT Compensation 59J1-R
Grid/Open Type A
Ground = REACT manually selectableon WC
Open = REACT mode on when WXselected
Discrete Outputs
The WX R/T/A does not provide any discrete outputs that are installationvariable.
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S1. WX Controller Discrete Surmnary
Discrete Inputs
Forced Standby 61/c61Jl-P
Grid/OpenType A
Ground = Forced StandbyOpen = Normal Operation
Program Range A 61/C61J2-JProgram Range B 61/C61J2-KProgram Range C 61/C61J2-LProgram Range D 61/C61J2-MProgram Range Comm 61/C61J2-N
Grid/OpenType A
Range (nmi) D c B A
0.5 Open Open Open Gnd1.0 Open Open Gnd Open2.5 Gnd Gnd Gnd Gnd5.0 Gnd Gnd Gnd Open
Gnd Gnd Open Gnd:: Gnd Gnd Open Open50 Gnd Open Gnd Gnd100 Gnd Open Open Open150 Open Open Gnd Gnd200 Gnd Open Open Gnd300 Gnd Open Gnd Open500 Open Gnd Open Open1000 Open Gnd Open Gnd2000 Open Gnd Gnd Open
NOTE: Program Range Pins must be grounded by using the Program— Range Conwn(61/C61J2-N). These pins must not be tied to
Aircraft Grid.
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ID Program Pin 61/C61J2-S
Grid/OpenType A
Short to C61J2-R for WXC #2Open = WXC #1
Discrete Outputs
Range A 51/C61J2-ARange B 61/C61J2-BRange C 61/C61J2-CRange D 61/C61J2-D
Gnc!/OpenType A
Provides encoded WX Range per the range select knob or per61/C61J2-J/K/L/Mwhen FPLN is selected.
FPLN 61/C61J2-E
Grid/OpenType A
Ground = Flight Plan Mode SelectedOpen = Normal Operation
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65. Symbol Generator (SG) Discrete Summary
Discrete Inputs
SG Identifiers ----- SG ID A 65/C65/E65JlA-11----- SG ID B 65/C65/E65JlA-12----- SG ID C 65/C65/E65JlB-27
Grid/Open Type A11 12 27 SG Position
G-IV Application Gnd Open Open SG1Open Gnd Open SG2Gnd Gnd Gnd SG3
TCAS Installed 65/C65/E65JlA-14
Grid/Open Type A
Ground = TCAS InstalledOpen = TCAS not Installed
LX Power On 65/C65/E65JlA-15
Grid/Open Type A
Ground = LX System EnergizedOpen = LX System Turned Off
P870 Installed 65/C65/E65JlA-20
Grid/Open Type A
Ground = P870 WX System InstalledOpen = P800 WX System Installed
Mach Tape Disable 65/C65/E65JlA-25
Grid/Open Type A
Ground = Disables Mach Tape on PFDOpen = Allows Airspeed Tape on PFD to transition
to a Mach Tape
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ILS/MLS* #1 SEL 65/C65/E65JlA-26
Grid/Open Type A
Ground = MLS #1 SelectedOpen = ILS #1 Selected
FPLN SEL 65/C65/E65JlA-27
Grid/Open Type A
Ground = Flight Plan Mode SelectedOpen = Normal Operation
Reference Appendix D
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Range Select A, B, C, D 65/C65/E65JlA-28, 29, 30, 31
Grid/OpenType A
RNGSEL D
Gnd
Gnd
RNGSEL C
Gnd
Gnd
RNGSEL B
Gnd
RNGSEL A
Open
Gnd
0.5
1.0 Open
2.5 Open Open Open Open
5 Open Open Open Gnd
10 Open Open Gnd Open
Gnd25 Open
Open
Open
Gnd
Gnd
Gnd
50
100
150
200
300
500
Open Open
Open
Gnd
Gnd Gnd
OpenGnd Open
Open Gnd Gnd
Open
Gnd
Gnd
Open
Gnd
Gnd
Open
Gnd
Gnd
Gnd
Gnd
Gnd
Open
1000
2000
UNDEF
UNDEF
Open Open
Open Open Gnd
Gnd
Open
Gnd Gnd
Gnd Open Open
Reference Appendix D ‘
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SG PWR DN
Grid/Open
Ground =Open =
SGI REV
Grid/Open
Ground =Open =
SG2 REV
Grid/Open
Ground =Open =
SG3 REV
Grid/Open
Ground =Open =
DU1 REV
Grid/Open
Ground =Open =
0U3 REV
Grid/Open
Ground =Open =
65/C65/E65JlA-59
Type A
SG Powered DownSG Power Up
65/C65/E65JlA-60
Type A
SG1 RevNormal Operation
65/C65/E65JlA-61
Type A
SG2 RevNormal Operation
65/C65/E65JlA-62
Type A
SG3 RevNormal Operation
65/C65/E65JlA-63
Type A
DU1 RevNormal Operation
65/C65/E65JlA-64
Type A
DU3 RevNormal Operation
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DU4 REV 65/C65/E65JlA-65
Grid/OpenType A
Ground = DU4 RevOpen = Normal Operation
DU6 REV 65/C65/E65JlA-66
Grid/Open Type A
Ground = DU6 RevOpen = Normal Operation
LX Installed 65/C65/E65JlA-67
Grid/OpenType A
Ground = LX System InstalledOpen = LX System Not Installed
BC I.D. A,B 65/C65/E65JlB-11,12
Grid/OpenType A11 12 Result
---------------------.--.---------------------G-IV Application Open Open Undefined
Gnd Open BC1Open Gnd BC2Gnd Gnd BC3
WX ON 65/C65/E65JlB-20
Grid/OpenType A
Ground = P870 WX System EnergizedOpen = P870 WX System Turned Off
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Comparator Ponitor Disabled 65/C65/E65JlB-25
Grid/OpenType A
Ground = Comparator I$onitor DisabledOpen = Comparator Yonitor Enabled
.
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ILS/MLS* #2 SEL 65/C65/E65JlB-26
Grid/Open Type A
Ground = MLS #2 SelectedOpen = ILS #2 Seiected
Weight on Wheels (WOW) 65/C65/E65JlB-54
Grid/OpenType A
Ground = Aircraft on GroundOpen = Aircraft Airborne
Joystick Fore 65/C65/E65JlB-55
Grid/OpenType A
Ground = Fore PositionOpen = Neutral Position
Joystick Aft 65/C65/E65JlB-56
Grid/Open Type A
Ground = Aft PositionOpen = Neutral Position
Joystick Lt 65/C65/E65JlB-57
Grid/Open Type A
Ground = Left PositionOpen = Neutral Position
Joystick Rt 65/C65/E65JlB-58
Grid/OpenType A
Ground = Right PositionOpen = Neutral Position
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Joystick Enter 65/C65/E65JlB-59
Grid/OpenType A
Ground = Enter InitiatedOpen = No Command
Joystick Clear 65/C65/E65JlB-60
Grid/OpenType A
Ground = Clear Joystick to Preset PositionOpen = No Command
WX Fault 65/C65/E65JlB-61
Grid/OpenType A
Ground = FaultOpen = Normal Operation
Reference Appendix D
WX Target Alert 65/C65/E65JlB-62
Grid/OpenType A
Ground = Target AlertOpen = Normal Operation
Reference Appendix D
Maintenance Test Enable 65/C65/E65JlB-66
Grid/OpenType A
Ground = MaintenanceTest EnabledOpen = Normal Operation
Reference Appendix D
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Discrete Outputs
BC Valid 65/C65/E65JlA-13
Grid/OpenType A
Ground = Bus Controller ValidOpen = Bus Controller Invalid
SG Valid 65/C65/E65JlB-51
Grid/OpenType A
Ground = SG ValidOpen = SG Invalid
SG Overtemp 65/C65/E65JlB-52
Grid/Open Type A
Ground = SG OvertempOpen = Normal Operation
Below Decision Height 65/C65/E65JlB-53(DH)
Grid/OpenType A
Ground = TrueOpen = Normal Operation
CSHDG SRC 65/C65/E65JlB-65
Grid/OpenType A
Ground = Cross-Side Heading Source Displayed on PFDOpen = Normal Operation
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115. Display Controller (DC) Discrete Summary
Discrete Inputs
Day/Night 115/Cl15Jl-X
28 V de/Open Type A
28 V dc = NightOpen = Day
FGC Left Priority 115/Cl15Jl-a
28 V de/Open Type A
28 V dc = Left FGC has PriorityOpen = Left FGC does not have Priority
FGC Right Priority 115/Cl15Jl-b
28 V de/Open Type A
28 V dc = Right FGC has PriorityOpen = Right FGC does not have Priority
ARINC ILS 115/Cl15Jl-c
Grid/Open Type A
Ground = ARINC ILS InstalledOpen = ARINC ILS not Installed
MLS Installed 115/Cl15Jl-d
Grid/Open Type A
Ground = MLS InstalledOpen = MLS not Installed
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Windshear Computer 115/Cl15Jl-fInstalled
Grid/Open Type A
Ground = Windshear Computer is Installed.
Open = Windshear Computer is not Installed.
Pilot/Copilot 115/Cl15Jl-g
Grid/Open Type A
Ground : ;:y:;otOpen “
IRS Triplex/Dual 115/Cl15Jl-h
Ground = DualOpen = Triplex
LTRK Installed 115/Cl15Jl-i
Ground = LTRK InstalledOpen = LTRK not Installed
TCAS Installed 115/Cl15Jl-j
Grid/Open Type A
Ground = TCAS InstalledOpen = TCAS not Installed
Weight on Wheels (WOW) 115/Cl15Jl-k
Grid/Open Type A
Ground = Aircraft on GroundOpen = Aircraft Airborne
TCAS RA 115/Cl15Jl-m
Grid/Open Type A
Ground = TCAS RA, select TCASsystem page
Open = Normal
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Emergency Checklist 115/CllJl-pSelect
Grid/Open Type A
Ground = Emer Checklist SelectedOpen = Normal
Checklist Installed 115/Cl15Jl-q
Grid/Open Type A
Ground = Checklist InstalledOpen = Checklist not Installed
Maint. Test Enable 115/cl15Jl-AA
Grid/Open Type A
Ground = Maintenance Test EnabledOpen = Normal Operation
Lamp Test 115/cl15Jl-DD
Grid/Open Type A
Ground = Initiate Test of all AnnunciatorsOpen = Normal Operation
Discrete Outputs
Subtest Select 115/Cl15Jl-v
Grid/Open Type A
Ground = Maintenance Test “Select” Button PushedOpen = Normal Operation
FGC Right Priority Select 115/Cl15Jl-z
Grid/Open Type A
Momentary Ground = Right FGC Priority SelectOpen = Normal
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ILS/MLS Select Out 115/cl15Jl-FF
Grid/Open Type A
Ground = MLS SelectedOpen = ILS Selected
NAV Retune 115/cl15Jl-GG
Grid/Open Type A
Momentary Ground (500 t 50 msec) =DME is retuned by theNAV control
Open = Normal
FGC Left Priority Select 115/Cl15Jl-HH
Grid/Open Type A
Momentary Ground = Left FGC Priority SelectOpen = Normal
J
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Z()● CDU Discrete Summary
Discrete Inputs
Lamp Test 120/C120Jl-s
Grid/OpenType A
Ground = Lamp TestOpen = Normal Operation
All annunciators test to level of dim control.
Annun Lighting Bright/Dim 120/C120Jl-v
28V de/Open Type A
28 Vdc = DimOpen = Bright
Test Enable 120/c120Jl-EE
Grid/OpenType A
Ground = Enables Maintenance TestOpen = Normal Operation
Discrete Outputs
The CDU does not provide any discrete outputs that are installationvariable.
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121. Nav Computer Discrete Summary
Discrete Inputs
Clockless ASCB 121/C121JlA-14
Grid/Open Type A
Ground = Clockless ASCBOpen = Clocked ASCB
ARINC 429 Bus Speed 121/C121JlA-47, 48, 49
Grid/Open Type A
Ground = Low SpeedOpen = High Speed
Long Term Sensor (LTS) 121/C121JlB-59, 60Port No. 1
Grid/Open Type A
LTS Type 59 60
Open OpenNo. 1 Open GndNo. 2 Gnd OpenNo. 3 Gnd Gnd
Long Term Sensor (LTS) 121/C121JlB-61, 62Port No. 2
Grid/Open Type A
LTS Type 61 62
Open OpenNo. 1 Open GndNo. 2 Gnd OpenNo. 3 Gnd Gnd
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Long Term Sensor (LTS) 121/C121JlB-63, 64Port No. 3
Grid/Open Type A
LTS Type 63 64
Open OpenNo. 1 Open GndNo. 2 Gnd OpenNo. 3 Gnd Gnd
Version B ASCB 121/C121JlB-67
Grid/Open Type A
Ground = Version B ASCBOpen = Version A ASCB
Operational Mode
Grid/Open Type
121/C121JlB-71, 92
A
IDO ID1(JIB-71) (JIB-92)
Initiated XFER/Dual Operation Open OpenSingle Operation Gnd OpenIndependent Operation Open GndCDU Mode Control Gnd Gnd
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Weight On Wheels (WOW) 121/C121JlB-72
Grid/Open Type A
Ground = Aircraft on the GroundOpen = Aircraft is Airborne
Perf Computer Installed 121/C121JlB-73
Grid/OpenType A
Ground = Perf Computer InstalledOpen = Perf Computer not Installed
Long Term Sensor (LTS) 121/C121JlB-74,75, 76No. 1 Configuration
Grid/OpenType A
LTS No. 1 Type 74 75 76
Port not used Open Open OpenIRU Open Open GndOmega Open Gnd OpenLoran C Open Gnd GndGPS Gnd Open Open
Long Term Sensor (LTS) 121/C121JlB-77,78, 79No. 2 Configuration
Grid/OpenType A
LTS No. 2 Type 77 78 79
Port not used Open Open OpenIRU Open Open GndOmega Open Gnd OpenLoran C Open Gnd GndGPS Gnd Open Open
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Data Loader Connected 121/C121JlB-83
Grid/OpenType A
Ground = Data Loader ConnectedOpen = Not Connected
Radio Config 121/C121JlB-84,85, 86
Grid/OpenType A \
Radio Type 84 85 86
King 429 Open Open OpenCollins 429 Gnd Open OpenSperry ASCB Open Gnd OpenCollins 422 Gnd Gnd Gnd
Maintenance Test 121/C121JlB-87
Grid/OpenType A
Ground = Maintenance Test EnabledOpen = Not Enabled
ILS/MLS Select 121/C121JlB-88
Grid/OpenType A
Ground = ILS DataOpen = MLS Data
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Long Term Sensor (LTS) 121/C121JlB-89,90, 91No. 3 Configuration
Grid/OpenType A
LTS No. 3 Type 89 90 91
Port not used Open Open OpenIRU Open ;l;n GndOmega Open OpenLoran C Open Gnd GndGPS Gnd Open Open
Initiated Transmit 121/C121JlB-93
Grid/OpenType A
Ground = Transmit DataOpen = Brickwall
Reference Appendix D
Initiated Receive 121/C121JlB-94
Grid/OpenType A
Ground = Receive DataOpen = Brickwall
Reference Appendix D
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DME Scanning Type 121/C121J12-95
Grid/OpenType A
Ground = DME; Scanning TypeOpen = DME; Single Mode
Radio Bus Type 121/C121JlB-96
Grid/OpenType A
Ground = RS-422Open = ARINC 429
Single ASCB 121/C121JlB-97
Grid/OpenType A
Ground = Single ASCBOpen = Dual ASCB
Source/i)estination ID 121/C121JlB-98, 99, 65
Grid/OpenType A
SDI #1 SDI #2 SDI #3NAV Computer Configuration 98 99 65
Reserved Open Open OpenCenter Open Open GndRight Open Gnd OpenReserved Open Gnd GndLeft Gnd Open OpenReserved Gnd Open GndReserved Gnd Gnd OpenReserved Gnd Gnd Gnd
CDU Valid 121/c121JlB-loo
Grid/OpenType A
Ground = Normal OperationOpen = CDU Failure
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Heading Reference Select 121/C121JlB-101
Grid/Open Type A
Ground = Heading Ref; True ReferenceOpen = Heading Ref; Magnetic Reference
AFIS Installed 121/c121JlB-lo2
Grid/Open Type A
Ground = AFIS EnabledOpen = Not Enabled
Overspeed Protection 121/C121JlB-103Disabled
Grid/Open Type A
Ground = Overspeed Protection DisabledOpen = Overspeed Protection Enabled
RS 422 Offside VOR 121/C121JlB-104Connected
Grid/Open Type A
Ground = Offside VOR ConnectedOpen = offside VOR not Connected
Secondary NAV/DME 121/C121JlB-105Manual Tune
Grid/Open Type A
Ground = Manual Tune OnlyOpen = FMS Tuning Enabled
Primary NAV/DME 121/C121JlB-106Manual Tune
Grid/Open Type A
Ground = Manual Tune OnlyOpen = FMS Tuning Enabled
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121/C121JlB-38
Discrete Outputs
True/Mag Select 121/C121JlB-37
Grid/OpenType A
Ground = TrueOpen = Mag
Onside Tune Control(Autotune)
Grid/Open Type A
Ground = Nav Tuning is auto controlledOpen = Nav Tuning is controlled by pilot
Remote Tuning Control 121/C121JlB-39
Grid/OpenType A
Ground = Nav Tuning is Remote ControlledOpen = Nav Tuning is NOT Remote Controlled
Lateral Waypoint 121/C121JlB-40
Grid/OpenType A
Ground = Lateral Waypoint AlertOpen = Normal Operation
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Vertical Waypoint 121/C121JlB-41
Grid/OpenType A
Ground = Vertical Waypoint AlertOpen = Normal Operation
Dead Reckoning 121/C121JlB-42
Grid/OpenType A
Ground = Dead Reckoning Mode EnabledOpen = Normal Navigation
Offset Alert 121/C121JlB-43
Grid/OpenType A
Ground = Offset AlertOpen = Normal Operation
Approach Sensitivity 121/C121JlB-44
Grid/OpenType A
Ground = Approach Sensitivity EnabledOpen = Normal Sensitivity
Independent Operation 121/C121JlB-45
Grid/OpenType A
Ground = IndependentOperationOpen = Normal Operation
CDU Message 121/C121JlB-46
Grid/OpenType A
Ground = CDU Message AlertOpen = No CDU Message
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Degrade Accuracy 121/C121JlB-47
Grid/OpenType A
Ground = The FMS is in a degrade mode of operation and cannotguarantee the required accuracy for the present phase offlight, with the available position sensors.
Open = Normal operation
Nav Computer Valid 121/C121JlB-49
Grid/OpenType A
Grcund = Nav Computer ValidOpen = Nav Computer Invalid
Vertical Track Aural 121/C121JlB-53
Grid/OpenType A
Ground = Alert (double pulsed ground)Open = Normal Operation
Cross side Tuning 121/C121JlB-54Control (Autotune)
Grid/OpenType A
Ground = Cross side Nav tuning is auto controlledOpen = Cross side Nav tuning is controlled by pilot
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122. Perf Computer Discrete Summary
Discrete Inputs
Maintenance Test Enable 122/C122JlA-50
Grid/Open Type A
Ground = Maintenance Test EnabledOpen = Normal Operation
Gear Down 122/C122JlA-54
Grid/OpenType A
Ground = Gear DownOpen = Gear Retracted
Left/Right Select 122/C122JlA-59
Grid/Open Type A
Ground = Right Performance/Autothrottle ComputerOpen = Left Performance/Autothrottle Computer
Version A/B 122/C122JlA-60
Grid/Open Type A
Ground = ASCB Version BOpen = ASCB Version A
Left Bleed Source On 122/C122JlA-62
Grid/OpenType A
Ground = Left Bleed Source OnOpen = Left Bleed Source Off
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Right Bleed Source On 122/C122JlA-63
Grid/OpenType A
Ground = Right Bleed Source OnOpen = Right B1eed Source Off
ASCB Single/Dual 122/C122JlA-66
Grid/OpenType A
Ground = DualOpen = Single
Flaps In Motion 122/C122JlA-72
28 V de/Open Type A
28Vdc= Flaps In MotionOpen = Flaps not In Motion
Left AC Pack On/Off 122/C122JlA-73
28 V de/Open Type A
28 V dc = Left AC Pack OnOpen = Left AC Pack Off
Right AC PackOn/Off 122/C122JlA-74
28 V de/Open Type A
28 V dc = Right AC Pack OnOpen = RightAC Pack Off
Weight On Wheels (WOW) 122/C122JlA-75
Grid/OpenType A
Ground = Aircraft on the GroundOpen = Aircraft is Airborne
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A/T Engage/Disengage 122/C122JlA-81
Grid/OpenType A
Momentary transition between open and ground toggles the A/Tbetween engaged and disengaged.
Reference Appendix D
PZ Interlock #1, 2, 3, 4 122/C122JlB-87,88, 89, 90
Grid/OpenType A
The table below identifies the strapping requirements for thevarious certification agencies along with the correspondingCDUidentifier.
Pin #1 Pin #2 Pin #3 Pin #4 Certification CDU(JIB-87) (JIB-88) (JIB-89) (JIB-90) Type Ident
Open Open Open Gnd FAA/Brunei A-Open Open Gnd Open DOT/DGAC B-Open Open Gnd Gnd CAAOpen Gnd Open Open Australia ::Open 6nd Open Gnd Generic JAR E-Open Gnd Gnd Open Special Mission F-
A/T Disengage 122/C122JlB-91
Grid/OpenType A
Ground = Normal OperationOpen = Disengage Autothrottle
Discrete Outputs
The Perf Computer contains no aircraft variable discrete outputs.
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23. Data Loader Discrete Summary Discrete Inputs
Discrete Inputs
The Data Loader does not provide any discrete inputs that areinstallationvariable.
Discrete Outputs
The Data Loader does not provide any discrete outputs that areinstallationvariable.
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130. Display Unit (DU) Discrete Summary
DU PWR DN 130/C130/131/C131/132/133Jl-22
Grid/OpenType A
Ground = DU Powered DownOpen = DU Power Up
Port Sel A/El 130/C130/131/C131/132/133Jl-87/88
Grid/OpenType A
Du Input Port Port Sel A Port Sel 2
Primary Port Open Open1st Alternate Gnd Open2nd Alternate Open Gnd3rd Alternate Gnd Gnd
DU Address Select 130/C130/131/C131/132/133Jl-90/91
The Display Units each have an address that defines itslocation within the cockpit. The SG transmits formatdata (i.e.: PFD, ND) to a specific DU address. Thisallows the SG to implement reversionaryformat switchingwith no switching intelligencerequired by the DU.
The DU address shall be defined by the ID discretes asillustrated in Table 8.3.3 below.
G-IV ID #1 10 #2J1-90 J1-91
DU 1/6 Open OpenDU 2/5 Gnd OpenDU 3 Open GndDU 4 Gnd Gnd
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Software Enable 130/C130/131/C131/132/133Jl-99 , 100
Grid/OpenType A
Ground = Software EnableOpen = Normal Operation
Flight Test Only
Discrete Outputs
The DU contains no aircraft variable discrete outputs.
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134. Fault Warning Computer (FWC) Discrete Summary
Discrete Inputs
Keying Pins 1 thru 5 134/C134JlA-12,13,14,15,16
Grid/OpenType A
12 13 14 15 16
G-IV Gnd Open Gnd Open Gnd
Warn Reset 134/C134JlA-23
Grid/OpenType A
Ground = Master Warn ResetOpen = Normal Operation
Caution Reset 134/C134JlA-24
Grid/OpenType A
Ground = Master Caution ResetOpen = Normal Operation
Voice Recorder Fail 134/C134JlA-25
Grid/OpenType A
Ground = Normal OperationOpen = Voice Recorder Fail
Steer by Wire Fail 134/C134JlA-26
Grid/OpenType A
Ground = Steer by Wire FailOpen = Normal Operation
NOTE: ‘AND’ with GEAR DOWN discrete (134/C134JlA-67) formessage enable.
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AHRS Cool Fai1 134/C134JlA-27
Grid/OpenType A
Ground = Cool FailOpen = Normal Operation
DU3 Valid 134/C134JlA-29
Grid/OpenType A
Ground = DU 3 ValidOpen =DU3 Fail
DU4 Valid 134/c134JlA-30
Grid/OpenType A
Ground = DU4 ValidOpen =DU4 Fail
I#indshearInstalled 134/C134JlA-32
Grid/OpenType A
Ground = Windshear InstalledOpen = klindshear not Installed
Windshear Valid 134/c134JlA-33
Grid/Open Type A
Ground = Windshear ValidOpen = Windshear Invalid
SG1 Rev Select 134/c134JlA-41
Grid/OpenType A
Ground = SG1 Rev SelectedOpen = Normal
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SG2 Rev Select 134/C134JlA-42
Grid/OpenType A
Ground = SG2 Rev SelectedOpen = Normal
SG3 Rev Select 134/c134JlA-43
Grid/Open Type A
Ground = SG3 Rev SelectedOpen = Normal
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DU1 Rev Select 134/c134JlA-44
Grid/Open Type A
Ground = DU1 Rev SelectedOpen = Normal
DU2 Rev Select 134/c134JlA-45
Grid/Open Type A
Ground = DU2 Rev SelectedOpen = Normal
DU3 Rev Select 134/C134JlA-46
Grid/OpenType A
Ground = DU3 Rev SelectedOpen = Normal
DU4 Rev Select 124/C124JlA-47
Grid/OpenType A
Ground = DU4 Rev SelectedOpen = Normal
DU5 Rev Select 134/C134JlA-48
Grid/OpenType A
Ground = DU5 Rev SelectedOpen = Normal
DU6 Rev Select 134/c134JlA-49
Grid/OpenType A
Ground = DU6 Rev SelectedOpen = Normal
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Weight on Wheels (WOW) 134/C134JlA-63
Grid/Open Type A
Ground = Aircraft on the GroundOpen = Aircraft in Air
FWC ID 134/C134JlA-65, 66
Grid/Open Type A
65 66
FWC1 Gnd (l):nFWC2 Open
Gear Down 134/C134JlA-67
Grid/OpenType A
Ground = Gear Down and LockedOpen = Gear Retracted
Memory Erase Button 134/C134JlA-68
Grid/Open Type A
Ground = Erase Non-VolatileMemoryOpen = Normal Operation
Windshear Available 134/C134JlA-69
Grid/Open Type A
Ground = Windshear AvailableOpen = Windshear not Available
Ground Spoi 1 er Not Armed 134/C 134JlA-70
Grid/Open Type A
Ground = Gnd Spoiler not ArmedOpen = Gnd Spoiler Armed
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Emergency Battery 1 Fail 134/C134JlA-71
Grid/OpenType A
Ground = Normal OperationOpen = Emergency Battery 1 Fail
Emergency Battery 2 Fail 134C134J1A-72
Grid/OpenType A
Ground = Normal OperationOpen = Emergency Battery 2 Fail
AOA Heater 1 Fail 134/c134JlA-73
Grid/OpenType A
Ground = Normal OperationOpen = AOA Heater 1 Fail
AOA Heater 2 Fail 134/c134JlA-74
Grid/OpenType A
Ground = Normal OperationOpen = AOA Heater 2 Fail
CDU 1 Valid 134/c134JlA-75
Grid/OpenType A
Ground = CDU ValidOpen = CDU Invalid
CDU 2 Valid 134/C134JlA-76
Grid/OpenType A
Ground = CDU ValidOpen = CDU Invalid
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Spare CDU Valid 134/c134JlA-77
Grid/Open Type A
Ground = CDU ValidOpen = CDU Invalid
Spare FMS Active 2 134/C134JlA-78
Grid/Open Type A
Ground = Spare FMS Replaces FMS 2Open = Normal Operation
Spare FMS Active 1 134/c134JlA-79
Grid/Open Type A
Ground = Spare FMS Replaces FMS 1Open = Normal Operation
Brake Temp Monitor 134/C134JlA-84Systems (BTMS)
Grid/Open Type A
Ground = Brake Overheat (BRAKE OVHT)Open = Normal Operation
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Autopilot Off Reset 134/C134JlA-80
Grid/OpenType A
Ground = Resets the “AUTOPILOTOFF” Ann on EICASOpen = Normal Operation
Reference Appendix D
Manual Exceedance Record 134/C134JlA-81
Grid/OpenType A
Ground = Manual RecordingOpen = Normal Auto Recording
Autothrottle Disconnect 134/C134JlA-83
Grid/Open Type A
Ground = Normal OperationOpen = Disengage Autothrottles
Maintenance Test 134/C134JlA-85
Grid/OpenType A
Ground = Maintenance Test EnabledOpen = Normal Operation
FWC Data Download 134/C134JlA-86
Grid/Open Type A
Ground = Initiate FWC Data DownloadOpen = Normal Operation
Spare NZ Valid 134/C134JlA-87
Grid/Open Type A
Ground = NZ ValidOpen = NZ Invalid
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Honeywell ~#!!%wcE
Spare FMS Instal1ed 134/c134JlA-90
Grid/OpenType A
Ground = Spare FMS Instal1edOpen = Two FMS Installation
BC Valid 134/C134JlA-97, 98, 99
Grid/OpenType A
Ground = Bus Controller ValidOpen = Bus Controller Invalid
Scroll Up 134/c134JlA-lo5
Grid/OpenType A
Ground = Scroll Caution/Advisoryt4essagesOpen = No Scroll
Scroll Down 134/C134JlA-106
Grid/OpenType A
Ground = Scroll Caution/AdvisoryMessages DownOpen = No Scroll
CateaorY 11 ProQram Pins
CAT 11 Bendix ILS Installed 134/C134JlA-28CAT 11 MLS Installed 134/c134JlA-50CAT II NAV Installed 134/C134JlA-82
Ground/Open, Type A
GND= CAT II Certified Receiver Type* InstalledOpen = Non-CAT II Aircraft
*NOTE : Current certificationonly has the NAV option availablebut FWC Logic is provisioned for future certifications.CAT 11 NAV Installed (JIA-82)must be grounded for theBendix ILS and MLS options to work.
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Left FuelOpen
28 V
28 VOpen
Right.Fue”Open
28 V
28 VOpen
Left FuelClosed
28 V
Shutoff Valve 134/C134JlB-l
de/Open Type A
dc = Left Fuel Shutoff Valve Open= Left Fuel Shutoff Valve is not Open
Shutoff Valve 134/C134JlB-2
de/Open Type A
dc = Right Fuel Shutoff Valve Open= Right Fuel Shutoff Valve is not Open
Shutoff Valve 134/c134JlB-3
de/Open Type A
28Vdc= Left Fuel Shutoff Valve ClosedOpen = Left Fuel Shutoff Valve is not Closed
Right Fuel Shutoff Valve 134/C134JlB-4Closed
28 V de/Open Type A
28Vdc= Right Fuel Shutoff Valve ClosedOpen = Right Fuel Shutoff Valve is not Closed
Combined Hydraulic 134/c134JlB-5Shutoff Valve Open
28 V de/Open Type A
28Vdc= Combined Hydraulic Shutoff Valve OpenOpen = Combined Hydraulic Shutoff Valve is not Open
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Flight Hydraulic 134/C134JlB-6Shutoff Valve Open
28 V de/Open Type A
28 Vdc= Flight Hydraulic Shutoff Valve OpenOpen = Flight Hydraulic Shutoff Valve is not Open
Combined Hydraulic 134/c134JlB-7Shutoff Valve Closed
28 V de/Open Type A
28Vdc= Combined Hydraulic Shutoff Valve ClosedOpen = Combined Hydraulic Shutoff Valve is not Closed
Flight Hydraulic 134/C134JlB-8Shutoff Valve Closed
28 V de/Open Type A
28Vdc= Flight Hydraulic Shutoff Valve ClosedOpen = Flight Hydraulic Shutoff Valve is not Closed
DC Ext Power 134/c134JlB-9
28 V de/Open Type A
28Vdc= DC External ConnectionOpen = No External Connection
ACFT Configuration 134/c134JlB-lo
28 V de/Open Type A
-28 Vdc = Aircraft not properly configured for T/O or landing. Open = Normal Operation
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Left Oil Filter 134/C134JlB-12Bypass
28 V de/Open Type A
28 V dc = Normal OperationOpen = Left Oil Filter Bypass
Right Oil Filter 134/c134JlB-13Bypass
28 V de/Open Type A
28Vdc= Normal OperationOpen = Right Oil Filter Bypass
Flight Recorder Fail 134/c134JlB-14
28 V de/Open Type A
28 V dc = Normal OperationOpen = Flight Recorder Inoperative
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Inhibit Select 134/C134JlB-16
28 V de/Open Type A
28Vdc= Activate Inhibit Function (Edge Triggered)Open = Normal Operation
For inhibit to be activated must have following condition:
(Valid Rad ALT) . ((< 400 Ft. RA) or (Gear Down))
Left Cowl Press Low 134/c134JlB-17
28 V de/Open Type A
28Vdc= Left Cowl Pressure LowOpen = Normal Operation
Right Cowl Press Low 134/C134JlB-18
28 V de/Open Type A
28 V dc = Right Cowl Pressure LowOpen = Normal Operation
VHF Corn1 Fail 134/c134JlB-19
28 V de/Open Type A
28 V dc = Normal OperationOpen = VHF ConnnunicationRadio Failure
VHF Corn2 Fail 134/C134JlB-20
28 V de/Open Type A
28 V dc = Normal OperationOpen = VHF CommunicationRadio Failure
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VHF Corn3 Fail 134/C134JlB-21
28 V de/Open Type A
28 V dc = Normal OperationOpen = VHF CommunicationRadio Failure
Wing Temp Low Left 134/C134JlB-22Right 134/C134JlB-23
28 V de/Open Type A
28 V dc = Normal OperationOpen = Wing Temp Low (Wing A/I message must also be active
for 2 2 rein)
Autopilot Clutch 134/C134JlB-24
28 V de/Open Type A
28 V dc = Clutch EngagedOpen = Clutch Disengaged
Trim Clutch 134/C134JlB-25
28 V de/Open Type A
28 V dc = Clutch EngagedOpen = Clutch Disengaged
Yaw Damper Clutch 134/C134JlB-26
28 V de/Open Type A
28 V dc = Clutch EngagedOpen = Clutch Disengaged
APU Alternator Off 134/C134JlB-28
28 V de/Open Type A
28 Vdc = APU Alternator OffOpen = Normal Operation
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Autothrottle Clutch No. 1 134/C134JlB-30
28 V dc/ Open Type A
28 V dc = A/T Clutch EngagedOpen = A/T Clutch Disengaged
Autothrottle Clutch No. 2 134/C134JlB-32
28 V de/Open Type A
28 V dc = A/T Clutch EngagedOpen = A/T Clutch Disengaged
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Discrete Outputs
FGC Maint Test 134/C134JlA-19
Grid/OpenType A
Ground = FGC Selected for MaintenanceTestOpen = Normal Operation
Autopilot Off Annun 134/C134JlA-21
Grid/OpenType A
Ground = Autopilot OffOpen = Autopilot On or Reset
Reference Appendix D
Windshear Test 134/c134JlA-93
Grid/OpenType A
Ground = Initiates Windshear Self-TestOpen = Normal Operation
Heading Miscompare 134/c134JlA-94
Grid/OpenType A
Ground = Heading Miscompare (>6”)Open = Normal Operation
Radio Altimeter Test 134/c134JlA-95
Grid/OpenType A
Ground = Initiates Self Test of Radio AltimeterOpen = Normal Operation
Bus Controller Power 134/C134JlA-96Up Test
Grid/OpenType A
Ground = Initiates Bus Controller Self Test Upon Power UpOpen = Normal Operation
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Emergency Checklist 134/c134JlA-lo3Selected
Grid/OpenType A
Ground = Emergency Checklist SelectedOpen = Normal Operation
Checklist Installed 134/C134JlA-104
Grid/OpenType A
Ground = Checklist is Installed in the FWCOpen = Checklist is not Installed in the FWC
Red Aural Output 134/C134JlB-87
28 V de/Open Type A
28Vdc= New Red MessageOpen = Normal Operation
Amber Aural Output 134/C134JlB-88
28 V de/Open Type A
28 V dc = New Amber MessageOpen = Normal Operation
Blue Aural Output 134/C134JlB-89
28 V de/Open Type A
28 V dc = New Blue MessageOpen = Normal Operation
Inhibit Output 134/c134JlB-90
28 V de/Open Type A
28Vdc= Inhibit Function ActiveOpen = Inhibit Function Disabled
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Autopilot Disconnect 134/c134JlB-91Test
28 Vdc/Open Type A
28 V dc = Autopilot Disconnect Test ActiveOpen = Normal Operation
Gear Horn Inhibit 134/C134JIB-92
28 V de/Open Type A
28Vdc = R4DALT> 1300 ft.Open = RADALT< 1200ft.
EICAS Fail 134/c134JlB-93
28 V de/Open Type A
28 V dc = Normal OperationOpen = Failure of any Active EICAS Unit
Download In Progress 134/c134JlB-94
28 V de/Open Type A
28 Vdc = EEPROM Data Being Transferred Out Of FWCOpen = Normal Operation
Erase In Progress 134/c134JlB-95
28 V de/Open Type A
28 V dc = EEPROM Being ErasedOpen = Normal Operation
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Autothrottle Off Horn 134/C134JlB-96
28 V de/Open Type A
28 V dc = Autothrottle DisengagementOpen = Normal Operation
AP Off Horn 134/c134JlB-97
28 V de/Open Type A
28 V dc =AP Disengagement (2.5 see)Open = Normal Operation
Master Warn Annun 134/C134JlB-98
28 V de/Open Type A
28 V dc = Annunciation OutputOpen = Normal Operation
Reference Appendix D
Master Caution Annun 134/c134JlB-99
28 V de/Open Type A
28 V dc = Annunciation OutputOpen = Normal Operation
Reference Appendix D
VALT Alert Horn 134/C134JlB-99
28 V de/Open Type A
28 V dc = VNAV ALT Alerter Horn OnOpen = VNAV ALT Alerter Horn Off
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36. Data Acquisition Unit (DAU) Discrete Summary
Discrete Inputs
DA;,~:;NT AOO/AOl/ 136JlA-10/76 (AOO/AOl)136JlB-67/79 (BOO/BOl)137JlA-10/76 (AOO/AOl)137JlB-67/79 (BOO/BOl)
Grid/OpenType A
ID AOO ID AO1 ID BOO ID BO1
DAU No. 1 Open Gnd Open GndDAU No. 2 Gnd Open Gnd Open
Rev Unlock 136J1B-9 (left)137J1B-9 (right)
28 V de/Open Type A
28 V dc = Thrust Reverser Fully or Partially DeployedOpen = Normal Operation
Fuel Pressure Low 136J1B-10 (left)137J1B-10 (right)
28 V de/Open Type A
28Vdc= Fuel Press. at Inlet to High Press. Pump <15 PSIor Both Boost Pumps on one side have been turnedoff with the Crossflow Valve Closed
Open = Normal Operation
Fuel Low Level 136J1B-11 (left)137J1B-11 (right)
28 V de/Open Type A
28V dc = Fuel Level is Below 700 lbs.Open = Level Above 700 lbs.
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Pylon Hot 136JlB-12 (left)137J1B-12 (right)
28 V de/Open Type A
28 V dc = Engine Pylon Temperature >325F (163C)Open = Normal Operation
Eng Hot 136J1B-13 (left)137JIB-13 (right)
28 V de/Open Type A
28 V dc = Engine Cooling AirTemp > 860F (460C)Gpen = Normal Operation
Oil Press Low 136J1B-14 (left)137J1B-14 (right)
28 V de/Open Type A
28Vdc= Engine Oil Pressure K 15 psiOpen = Normal Operation
Call “ 136J1B-15137J1B-15
28 V de/Open Type A
28 V dc = CallOpen = Normal Operation
Ignition 1 136J1B-16 (left)137J1B-16 (right)
28 V de/Open Type A
28Vdc= Engine Ignition OnOpen = Ignition Off
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Wing Anti-Ice On 136J1B-17 (left)137J1B-17 (right)
28 V de/Open Type A
28 V dc = Wing Anti-Ice OnOpen =Anti-Ice Off
Engine Cowl Anti-Ice On 136J1B-18 (left)137J1B-18 (right)
28 V de/Open Type A
28Vdc= Engine Anti-Ice OnOpen = Anti-Ice Off
RA 1,2 Fail 136J1B-19 (RA 1)137J1B-19 (RA 2)
28 V de/Open Type A
28 V dc = Normal OperationOpen = Radio Altimeter Failure
Cabin Press Low 136J1B-20
28 V de/Open Type A
28 V dc = Cabin Alt > 9,750:250 ft.Open = Normal Operation
Ignition 2 136J1B-21137J1B-21
28 V de/Open Type A
28Vdc= Ignition OnOpen = Ignition Off
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.
COMB HYD Hot 136J1B-22
28 V de/Open Type A
28 V dc = Combined Hydraulic System Fluid Temperature> 220F (104C)
Open = Normal Operation
COMB HYD Fail 136J1B-23
28 V de/Open Type A
28 V dc = Combined Hydraulic System FailedOpen = Normal Operation
Fuel Filter Fail 136J1B-24 (left)137J1B-24 (right)
28 V de/Open Type A
28 V dc = Fuel Filter CloggedOpen = Normal Operation
AIL HYDOff 136J1B-25 (left)137J1B-25 (right)
28 V de/Open Type A
28 V dc = Aileron Hydraulic ShutoffOpen = Normal Operation
Bleed Hot 136J1B-26 (left)137J1B-26 (right)
28 V de/Open Type A
28 V dc = Bleed AirTemp > 550F (288C)Open = Normal Operation
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{
Bleed Press High 136Jlf3-27(left)137J1B-27 (right)
28 V de/Open Type A
28vcic= Bleed Air Pressure z 90 PSIOpen = Normal Operation
SW 136J1B-28 (left)137J1B-28 (right)
28 V de/Open Type A
28Vdc= Engine Start Valve is OpenOpen = Valve Closed
Altntr Hot 136J1B-29 (left)137J1B-29 (right)
28 V de/Open Type A
28V dc =Alternator Temp Y 250F (121C)Open = Normal Operation
Conv Hot 136J1B-30 (left)137J1B-30 (right)
28 V de/Open Type A
28 V dc = Converter Temperature > 221F (105C)Open = Normal Operation
Smoke Detect 136J1B-31
28 V de/Open Type A
28Vdc= Smoke DetectedOpen = Normal Operation
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Conv Fan Fail 136JlB-32 (left)137J1B-32 (right)
28 V de/Open Type A
28Vdc= Converter Fan FailureOpen = Normal Operation
ELEV COMB HYD Off 136J1B-33
28 V de/Open Type A
28Vdc= Elevator Combined Hydraulic OffOpen = Normal Operation
APU Altntr Hot 136J1B-34
28 V de/Open Type A
28 V dc =APUAlternator Temp >300F (149C)Open “= Normal Operation
Cool Turb Hot 136J1B-35 (left)136J1B-35 (right)
28 V de/Open Type A
28 V dc = Engine Cooling Turbine Discharge Air Temperature> 400F (204C)
Open = Normal Operation
AC PWR Fail 136J1B-36 (left)137J1B-36 (right)
28 V de/Open Type A
28 V dc = AC Power FailureOpen = Normal Operation
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DC PWR Fail 136J1B-37 (left)137J1B-37 (right)
28 V de/Open Type A
28Vdc= DC Power FailureOpen = Normal Operation
Stall Barrier Fail 136J1B-38 (left)137J1B-38 (right)
28 V de/Open Type A
28Vdc= Normal OperationOpen = Stall Barrier Failure
Emer Batt Dischg 136JIB-39 (left)137J1B-39 (right)
28 V de/Open Type A
28Vdc= Emer Batt Being DischargedOpen = Normal Operation
Wing Hot 136J1B-40 (left)137J1B-40 (right)
28 V de/Open Type A
28 V dc =Wing Anti-Ice Exhaust Duct Temperature > 180F (83C)Open = Normal Operation
Main Fuel Fail 136J1B-41 (left)137J1B-41 (right)
28 V de/Open Type A
28 V dc = Main Boost Pump has FailedOpen = Normal Operation
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Alt Fuel Fail 136J1B-42 (left)137J1B-42 (right)
28 V de/Open Type A
28V dc = Alternate Boost Pump has FailedOpen = Normal Operation
Stall Barr 1,2 136J1B-44 (Stall Barr 1)137J1B-44 (Stall Barr 2)
28 V de/Open Type A
28 V dc = Stall Barrier System Giving Stall Angle IndicationOpen = Normal Operation
Cabin Oxy On 136J1B-45
28 V de/Open Type A
28Vdc= Cabin Altitude Exceeded 13,500 ft., Passenger Masksshould Deploy
Open = Normal Operation
AUX AC Power Fail 136J1B-46
28 V de/Open Type A
28Vdc= Auxiliary Power FailureOpen = Normal Operation
APU Fire 136J1B-47
28 V de/Open Type A
28V dc =APU FireOpen = Normal Operation
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Aft Equip Hot 136J1B-48
28 V de/Open Type A
28 V dc=Aft Equipment Area Temperature is above 200F (93C)Open = Normal Operation
Landing Gear Status 136J1B-49
28 V de/Open Type A
28Vdc= Gear Up, Either Throttle Below XX% N2 or GearUp and Flaps Greater Than 20% (L Main, R Main,Nose Wheel)
Open = Normal Operation
AUX HYD Hot 136J1B-50
28 V de/Open Type A
28Vdc= Auxiliary Hydraulic Pump Case Temperature> 300F (149C)
Open = Normal Operation
Isolation Valve 136J1B-51
28 V de/Open Type A
28Vdc= Bleed Isolation Valve OpenOpen = Normal Operation
EX Batt SwOn 136J1B-52
28 V de/Open Type A
28Vdc= External Battery Switch OnOpen = Switch Off
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Rudder COMB HYD Off 136J1B-53
28 V de/Open Type A
28 V dc = Rudder Combined Hydraulic OffOpen = Normal Operation
Single Rudder Limit 136J1B-54
28 V de/Open Type A
28 V dc = Input Pressure Load Limiter FailureOpen = Normal Operation
Stab-Flap Fail 136J1B-55
28 V de/Open Type A
28Vdc= Flaps Up, Stabilizer Not UpOpen = Normal Operation
EPMP BATT SW OFF 136J1B-56
28,V de/Open Type A
28 V dc = EPMP Battery Switch is OffOpen = Normal Operation
Stall Barr Off 136J1B-57
28 V de/Open Type A
28Vdc= Both Stall Barrier Systems OffOpen = Normal Operation
TRU Fail 136J1B-58
28 V de/Open Type A
28Vdc= Transformer Rectifi~r Unit has no Output
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EPMP PS Fait 136J1B-59
28 V de/Open Type A
28Vdc= Electrical Power Monitor Panel Power Supply FailureOpen = Normal Operation
UTY HYD Off 136J1B-60
28 V de/Open Type A
28Vdc= Utility Hydraulic Pump Switch OffOpen = Normal Operation
LP/HP Select 136J1B-61
28 V de/Open Type A
28Vdc= HP SelectedOpen = LP Selected
Cowl A/I OVHT 136J1B-64 (left)137J1B-64 (right)
28”V de/Open Type A
28Vdc= Engine Cowl Anti-Ice Exhaust Duct Temperature > TBDOpen = Normal Operation
En~ Fire 136J1B-66 (left)137J1B-66 (right)
Grid/OpenType A
Ground = Engine Fire Zone Temperature > 440F (227C)Open = Normal Operation
Fuel Xflow Open 136J1B-68
Grid/OpenType A
Ground = Fuel Crossflow Valve OpenOpen = Valve Closed
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Eng Fire Loop Alert 136J1B-69
Grid/OpenType A
Ground = Engine Fire DetectedOpen = Normal Operation
Cabin DFRN 136J1B-70(Red Annun)
Grid/OpenType A
Ground = Cabin DFRN > 9.8Open = Normal Operation
Pitot Heat Fail 136J1B-71 (left)137J1B-71 (right)
Grid/OpenType A
Ground = Pitot Tube Heater Elements not EnergizedOpen = Normal Operation
Altntr Brg Fail 136J1B-72 (left)137J1B-72 (right)
Grid/OpenType A
Ground = Alternator Bearing FailureOpen = Normal Operation
Brake Maint Req’d 136J1B-73
Grid/OpenType A
Ground = Normal OperationOpen = One Brake Channel Failure
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Brake Fail 136 J1B-74
Grid/OpenType A
Ground = Normal OperationOpen = Both Brake Channels Failed
APU Master Warn 136J1B-75
Grid/OpenType A
Ground = APU EGT/APU RPM/Oil Temp High/Oil Pressure Low/Control Current High/Alternator Bearing Failure
Open = Normal Operation
Stby Pitot Heat Fail 136J1B-76
Grid/OpenType A
Ground = Standby Pitot Tube Heater Elements not EnergizedOpen = Normal Operation
Maintenance Test Enable 136J1B-77137J1B-77
Grid/OpenType A
Ground = Maintenance Test EnabledOpen = Normal Operation
DU Fan 1, 2 Fail 136J1B-78 (Fan 1)137J1B-78 (Fan 2)
Grid/OpenType A
Ground = Normal OperationOpen = Du Fan Fail
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Batt 1,2 Chgr Fail 136J1B-80 (Batt 1)137J1B-80 (Batt 2)
Grid/OpenType A
Ground = Normal OperationOpen = Battery 1,2 Charger Failure
Weight On Wheels (WOW) 136J1B-81 (left)137J1B-81 (right)
Grid/OpenType A
Ground = Aircraft on the GroundOpen = Normal Operation
Main Cabin Doors 137J1B-20
28 V de/Open Type A
28Vdc= Main Doors not LockedOpen = Normal Operation
FLTHYD Hot 137J1B-22
28 V de/Open Type A
28Vdc= Flight Hydraulic System Fluid Temperature> 220F (104C)
Open = Normal Operation
FLT HYD SYS Fail 137J1B-23
28 V de/Open Type A
28Vdc= Flight Hydraulic System FailedOpen = Normal Operation
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F1ame Detect 137J1B-31
28 V de/Open Type A
28 V dc = Flame DetectedOpen = Normal Operation
ELEV FLT HYD Off 137J1B-33
28 V de/Open Type A
28 V dc = Elevator F1ight Hydraulic OffOpen = Normal Operation
Cabin Press Man 137J1B-45
28 V de/Open Type A
28Vdc= Cabin Pressure Controller Switched OffOpen = Normal Operation
AC Ext Pwr 137J1B-46
28 V de/Open Type A
28 V dc = AC External ConnectionOpen = No Connection
Fwd Rad Rack Hot 137J1B-48
28vdc/Open Type A
28 V dc = Fwd Radio Rack Area Temperature is above 200F (93C)Open = Normal Operation
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Spd Brake Extded 137J1B-49
28 V de/Open Type A
28Vdc= Speed Brake Handle not in Fully Retracted PositionOpen = Normal Operation
TRU Hot 137J1B-50
28 V de/Open Type A
28 V dc = Transformer Rectifier Unit Temperature > 200F (93C)
Open = Normal Operation
Engine Sync 137J1B-51
28 V de/Open Type A
28Vdc= Engine Sync is OnOpen = Sync Off
Ice Det 137J1B-52
28,V de/Open Type A
28Vdc= Icing is OccurringOpen = Normal Operation
Rudder FLT HYD Off 137J1B-53
28 V de/Open Type A
28V dc = Rudder Flight Hydraulic OffOpen = Normal Operation
Rudder Limit 137J1B-54
28 V de/Open Type A
28 V dc = Rudder Actuator Torque Limiter is in OperationOpen = Normal Operation
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Honeywell f#!!~wcE
Gnd Spoiler Fail 137J1B-55
28 V de/Open Type A
28Vdc= Gnd Spoiler Component Fail or Deployed Gnd SpoilerPanel
Open = Normal Operation
Tone Gen Fail 137J1B-57
28 V de/Open Type A
28 V dc = Normal OperationOpen = Aural Tone Generator has Failed
Baggage Doors 137J1B-58
28 V de/Open Type A
28Vdc= Baggage Door not LockedOpen = Door Locked
Service Doors 137J1B-59
28 V de/Open Type A
28Vdc= Aft Equipment Door OpenOpen = Door Closed
Gnd Prox Valid 137J1B-61
28 V de/Open Type A
28Vdc= Gnd Prox InvalidOpen = Gnd Prox Valid
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Fuel Intk Open 137J1B-68
Grid/OpenType A
Ground = Fuel Intertank Valve OpenOpen = Valve Closed
Eng Fault Loop Alert 137J1B-69
Grid/OpenType A
Ground = Engine Fault DetectedOpen = Normal Operation
Cabin DFRN (Amber 137J1B-70Annun)
Grid/OpenType A
Ground = Cabin DFRN > 9.6Open = Normal Operation
Brake Pedal 137J1B-73
Grid/OpenType A
Ground = Brake Pedal OnOpen = Brake Pedal Off
Anti-Skid Fail 137J1B-74
Grid/OpenType A
Ground = Normal OperationOpen = Failure in Anti-Skid System
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APU ALT BRG Fail 137J1B-75
Grid/OpenType A
Ground = Normal OperationOpen = APU Alternator Bearing Failure
TAT Probe Heater Fail 137J1B-76
Grid/OpenType A
Ground = TAT Probe Heater FailureOpen = Normal Operation
Discrete Outputs
The DAU contains no aircraft variable discrete outputs.
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149. Global Positioning System Sensor Unit (GPSSU) Discrete Summary
Discrete Inputs
429 Output HS/LS Select 149J1-21
Grid/Open Type A
Grid*= Low SpeedOpen = High Speed
DADC Input 419/429 Select 149J1-40
Grid/Open Type A
Grid*= 419 DataOpen = 429 Data
*When grounding pins 21 and/or 40, use only pin 149J1-8. Do not useany other ground and do not tie pin 8 to 28V DC GND.
Discrete Outputs
GPSSU Fault 149J1-1
Grid/Open, Gnd Isink s 280 mA DC
Gnd = FaultOpen = Normal Operation
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Hone~ellMAINTENANCEMANUALGULFSTREAMIV
171. Inertial System Display Unit (ISDU) Discrete Summary
Discrete Inputs
CLR/ENT Dimming 171J1-7
Grid/Open Type A
Gnd = DimOpen = Bright
Data Display Test 171J1-11
Grid/Open Type A
Gnd = IlluminatedOpen = Off
Discrete Outputs - None
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198. Navigation Display Unit (NDU) Discrete Summary
Discrete Inputs
BRT/DIM 198J1-7
Grid/Open Type A
Gnd = Keyboard Cue Lights are DimOpen = Keyboard Cue Lights are Bright
Test 198J1-11
Grid/Open Type A
Gnd = Test ModeOpen = Normal Mode
Discrete Outputs - None
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APPENDIX DSCHEMATICS
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APPENDIX DSCHEMATICS
1.0 AFGCS SCHEMATICS
The following figures depict AFGCS interconnect configurations that shouldbe utilized in the aircraft installation.
Figure D-1.l Autopilot Disconnect SwitchFigure D-1.2 Yaw Damper Engage/Disengage SwitchFigure D-1.3 Trim Engage/Disengage SwitchFigure D-1.4 Take Off/Go-Around SwitchFigure D-1.5 Touch Control Steering SwitchFigure D-1.6 Elevator Trim SwitchFigure D-1.7 AFGCS Clutch SchematicFigure D-1.8 Autopilot Off AnnunciatorFigure D-1.9 Autopilot Off HornFigure D-1.1O FGC Priority Status/Select Schematic
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F134JIA-80
1OJ2B-66
PILOT COPILOT1OJ2B-54
llJ1-77
C1OJ2B-54
11J2-77
C1OJ2B-66
I C134J1A-80
AD-9064-R1
Autopilot Quick Disconnect SchematicFigure D-1.l
Use or disclosure of information
Interconnect InformationTable 501 (cent)
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22-14-00Page 598*217
Mar 15/91on the title page of this document.
Honeywell #&~AHNcE
r~~PLT Y/DENG/DISENG SW
Ir
1OJ1A-4O
+
9 llJ1-78
+-U —“— 11J2-78
+1
L C1OJ1A-4O
I
I
Y/D
1 ‘~’ i—-
+~~~ ,j-l-28 VDC
ANNUN PWRI
&
1OJ2B-53
C1OJ2B-53
AD-9065-R2
Yaw Damper Engage/DisengageSwitchAnd Annunciator Schematic
Figure D-1.2
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rPLT M= ~ 1ENG/DISENG SW
II
10J1A41
+
*llJ1-79
+[
u~ 11J2-79
~ C1OJ1A-41
I I
1 ‘QG i..—..-+~ ,+ 28 VDC
~~ ANNUN PWRI
+
1OJ2B-81
C1OJ2B-81
AD-9oa6-R2
Mach Trim Engage/Disengage SwitchAnd Annunciator Schematic
Figure D-1.3
Interconnect InformationTable 501 (cent) 22-14-00
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PILOIWTOGA S%
T
COPIL
o
OT’STOGA WV
T
Take Off/Go Around Engage Switch SchematicFigure D-1.4
lIJ1-72
11J2-54
AD-9068-R1
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PILOT’STCS SW
r’—’’’’-”
COPILOT’STCS SW
r’— “’2-53AD-9069-R1
Touch Control Steering Engage Switch SchematicFigure D-1.5
Use or disclosure of
Interconnect InformationTable 501 (cent) 22-14=00
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r——FGC 1
III
II Cs
I (
I——
r ——FGC 2
I Cs
I {IIII
I——
AD-9067%3
Elevator Trim Switch SchematicFigure D-1.6
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r
——— —FGC NO. 1
—10J2A ,*p, AILF%&N~RVO
‘1
I AP CLUTCH DRIVE 61 w 12 CLUTCHI
ITRIM CLUTCH DRIVE 63 r
* — ——— JI 10J1A’
IYIDENGAGEDRIVE 58
L
—
——. — 13P1
r
——— —FGC NO. 2 C1OJ2A
IAP CLUTCH DRIVE 61 4I - ——.
ITRIM CLUTCH DRIVE 63 [ )
I
*— ———
C1OJ1A 2gp2 TRIMSERVO 1I YID ENGAGE DRIVE 58
1.1- ——— — — ——— J
r
——— —
FWC NO. 1 134J1B
I AP CLUTCH 24 i- ——.
I TRIM CLUTCH 25 ) r 1:14J1 YAWDAMPER SERVO
4~ A YIDENGAGE
IY/DCLUTCH 26 f 4 I
1-W -J——— ————
r
——— —
FWC NO. 2 C134J1 B
I AP CLUTCH 24
ITRIM CLUTCH 25
IYID CLUTCH 26
L ——— ~ AD-12as-Rl
AFGCS Clutch SchematicFigure D-1.7
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28 VDCANNUN 134J1 A-21POWER AP OFF
NOTE: THIS ANNUNCIATOR IS IN LIEU OF AUTOPILOTOFF ANNUNICATOR ON THE PFD.
AD-12299-RI
Autopilot Off AnnunciatorFigure D-1.8
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AP OFFHORN
AD-1Z300-R1
Autopi1ot Off HornFigure D-1.9
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~GC NO. 1——— ——— ——— ———
10J1A 115J1 DC-SS4NO.1 1“I (28VIOPEN) PRIORIWSTATUSNO.1
- 37 T * a I
IINTERNAL
PROCESSORS~ SELECTBLJITON I
I10J2B
‘STATUS
‘; ;“ ~J : : ‘~’r
+“ 2? I(H) 100
I
CHANGEREQUEST (L) ml
SERIAL OATAb I
LFROM GP-S20
——— ——. I
r.——. —.— IGP-S20 llJ1 PRIORl~
IHH SELECT NO. 1
(H) 7 PRIORITY I
PRIORIW (L) 8
I
z SELECT NO. 2SELECT NO. 1* IPARALLEL a
I SE]:ALPRIORllYSELECTNO.2“
@l
ICONVERTOR ~ 62 -
NO. 1 PRIORITYFGC 1 2
I STATUS NO. 1 I- 70 4
I
~——— ——— A
I PRIOR~ 11J2SELECT NO. 1●
- ——— —
4 61 cll~l D= ~24 1
IPhlORIW
fwtALLEL SELEOTNO.2* ~4 FGC 1
4 4)
“%
2 I
ISE~~AL PRIORITY
CONVERTOR STATUSNO.270 4 PRIORI?Y I
I NO. 2r \
SELECT NO. 1.U. . — HH 4
-1PRIORITY iem cm Nln ei~;;=A
J- ——— —— -:”oMGp-7zm A!——————~GC NO.2 C1OJ2B.—
JI CHANGE ~ ‘.’.”:1::1 }
I REQUEST
I INTERNAL C1OJ1A
I
PROCESSORS (2SV/OPEN)* S7
PRIORITY STATUS NO. 2
I
a
J
I
II[I1
L ——— ——— A L ——— ——— -JA&lzns
FGC Priority Status/SelectSchematicFigure D-1.1O
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2.0 EDS SCHEMATICS
The following figures depict EDS interconnect configurations that should beutilized in the aircraft installation.
Figure D-2.1 Caution/WarningReset and Scroll SwitchFigure D-2.2 Trend Memory Erase SwitchFigure D-2.3 Data Download Initiate SwitchFigure D-2.4 Data Loader/FaultWarning InterfaceFigure D-2.5 MLS/ILS InterfaceFigure D-2.6 Joystick SchematicFigure D-2.7 Trend and Limit Manual Exceedance Recording
Interconnect InformationTable 501 (cent) 22-14-00
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PLTSCROLLUPSW
~ ~’w’A-’05
r—.—PLT CAUTION ANNuNAND REWSW 1
I b I o 0
L
lW1 A-24
C124J1A-24
) t T IS4JIS-S3L——— -1 1} C134J1B-S9
CPLTSCROLLUPSw
l= “
CPLTSCROLLOovmw
1 l–––--lr
4) ‘=+——.
CPLTCAUTION -1MNUN ANDRSSErSW
I
I c
i6
Caution/WarningReset and Scroll Switch SchematicFigure D-2.1
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MEM ERASE
NOTETHIS SWITCH TO BE LOCATEDINTHE EQUIPMENT BAY.
Trend and Limit MemoryErase Switch Schematic
Figure D-2.2
A&9071
Use or disclosure of information
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DATADOWNLOADSw
-r
NOTETHIS SWITCH TO BE LOCATEDIN THE EQUIPMENT BAY A~10878
Data Down oad Initiate Switch SchematicFigure D-2.3
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Fwc 1134J1B “DOWNLOAD IN PROGRESS”
J95
i “ERASE IN PROGRESS”
Fwc 2 C134J1B
9495 ~
II
r+28vDc* FWC 2 DOWNLOAD
FWC 1 DOWNLOADAD-20984
Data Loader/FaultWarning InterfaceFigure D-2.4
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.0.s07.4,
ILS/MLS Switching SchematicFigure D-2.5
J
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SSJJ --1r
FORE
8;
LT UT
RFr
1
i
}
JOYSTICK1
I
-1
11111
S7 LT55 FORE
5s RT
s An
41
i59 ENTERI
-!+ENTERv -’j%
60CLEAR I
v I I51 VALlDw
-—. -
I
II,x, c5’sJlr3
F-- “’:57 LT5sFORE
1 ; L
i
$;
ISsRT I
JOYSTICK55 AH I
I
$
5sENTERENTER I
#
so CLEAR ICLEAR
.A&12Sjl
Joystick SchematicFigure D-2.6
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MANUAL EXCEEDANCE RECORDING
~ ~’w’A-8’
* .Lcl~lA+l
AD-20985
Trend and Limit Manual Exceedance RecordingFigure D-2.7
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3.0 FMCS SCHEMATICS
The following figures depict FMCS interconnect configurations that shouldbe utilized in the aircraft installation.
Figure D-3.1 Autothrottle Off HornFigure D-3.2 Autothrottle Engage/Disengage SwitchesFigure D-3.3 Autothrottle Disconnect SwitchesFigure D-3.4 Autothrottle Off Annunciator
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AT OFFHORN
134 1B-96
AD-1 6239 ~
Autothrottle Off HornFigure D-3.1
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Honeywell f$#~&wcE
AK ENGAGEIDISENGAGE SW
*
~1~I
i
122,1A-81
IA/T Engage/DisengageSwitch Schematic
Figure D-3.2
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DISCONNECT DISCONNECT
Sw Sw
122J1 B-91
I134J1A-83
I I
o 0 ClZ2J1 B-91I i
LOCATED ON LOCATED ON C134J1A-83
LEFT THROTTLE RIGHT THROITLE AD-1 0881 -f%?
A/l DisconnectSwitch SchematicFigure D-3.3
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28 VDCANNUN v 134J1A-91POWER AT OFF
C134J1A-91AD-1 6240
Autothrottle Off AnnunciatorFigure D-3.4
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4.0 WEATHER RADAR SCHEMATICS
The following figures depict WX interconnect configurations that should beutilized in the aircraft installation.
IFigure D-4.1 P-870/EFIS InterfaceFigure D-4.2 SG/WX Range Discrete Interface
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WC-474 SG 1
RANGE i,5
RANGE
* CONTROL 1
4* VIDEO
v
WU-S70 SG 3
CONTROL: - co~ROL 1
LEFl
o II
CONTROL2 YZsv
A
IT
SG1VALlD
SG 2
* VIDEOv
WC-474CONTFIOL2
)5RANGE * RANGEt
P-870/EFIS Interface ho.1s78Figure D-4.1
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AO-M879
SG/WX Range Discrete InterfaceFigure D-4.2
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5.0 MISCELLANEOUSSCHEMATICS
The following figures depict MISC interconnect configurationsthat shouldbe utilized in the aircraft installation.
Figure D-5.1 AOA Chevron Annunciator SchematicFigure D-5.2 Maintenance Test Enable Switch Schematic
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28 VDCNO. 1
28 VDCNO. 2
Il—A
‘Gil
9J1A-_98
C9J1A-95
C9J1A-96~~
AD-9(I72AOA Chevron Annunciator Schematic
Figure D-5.1
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MAINT TESTENABLE SW
ENABLED
~“”z’+ 65J1B-66
F E65J1B-66
C65J1 B-66
i=
115J1-AA
C115J1-AA
k121J1B-87
C121J1B-87
F122J1A-50
Cl 22J1A-50
E134J1A-85
C134J1A-85
136JIB-77
NOTE . 137J1 B-77
THIS SWITCH TO BEiLOCATEDINTHE:~QUWM-EN7 BAY AD-9075-R3
Maintenance Test Enable Switch SchematicFigure D-5.2
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6.0 AFIS INTERCONNECTSCHEMATICS
The following figures depict AFIS interconnectwiring that should be usedin the aircraft installation.
Figure D-6.1 AFIS InterconnectSchematic
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I AFISIACRS ~
{
(H)121J1A-35BUS (L)121J1A-36 -9:: :;::: }Tx J81
1
I1 I
I
L ———— — -1 I I~i=M72 ~GEiAY7 — 1
I
{
I(H)C121JIA-50
‘~;;;~ Tx
I
++(L)C121J1A-51g i ;
I{
(H)C121J1A-35 ‘, t !‘F’~;~Rs Rx -+~,
(L)C121J1A-36 ----—;=:— – -
L ——~— — d 1
DMU JI-24(H)1 Rx
DMU J1-25 (L) J
DMU J1-22 (H)
}
TxDMU J1-23 (L) }
I AFISIACRS ~
{
(H)E121J1A-35
Bus (L)E121J1A-36 W-:: :-: ;:} ‘x JIt .
AFIS InterconnectSchematicFigure D-6.1
FMS 2
FMs 3
—JAD-21m
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7.0 IRS INTERCONNECTSCHEMATICS
The following figures depict IRS interconnect wiring that should be used inthe aircraft installation.
Figure D-7.1 Dimming and Test Panel InterconnectFigure D-7.2 Battery and Charger Interconnect
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fIRU 1 DIM & TEST PANEL MSU
ALIGN ANNUN 170J1B-F3 J2B-57 J2B-84 172J1-a
ON BAIT ANNUN 170JIB-J15 J2B-56 J2B-98 172J1-g
BAIT FAILANNUN 170J1B-Al5 J2B-55 J2B-85 172JI-Z
FAILANNUN 170J1B-D2 J2B-54 J2B-99 172J1-P
IRU 2
ALIGN ANNUN Cl70J1B-F3 J2B-53 J2B-86 172J3-a
ON BAIT ANNUN Cl70J1B-J15 J2B-67 J2B-1OO ~ 172J3-g
BAIT FAILANNUN Cl70J1B-Al5 J2B-68 J2B-87 172J3-Z
FAILANNUN Cl 70J1B-D2 J2B-80 J2B-101 172J3-P
IRU 3 orAHRS
ALIGN ANNUN El70J1B-F3 J2B-94 J2B-69 172J2-a
ON BATT ANNUN El70J1B-J15 J2B-81 J2B-97 172J2-g
BAIT FAILANNUN El70J1B-Al5 J2B-82 J2B-83 172J2-Z
FAILANNUN El70J1B-D2 J2B-95 J2B-96 172J2-P
1
Dimming and Test Panel InterconnectFigure D-7.1
-— .
.
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IRU #1 BATTERY &CHARGER #1
CHARGERINHIBIT 170J1A-G9 JIA-1
BAIT IN 170J1C-2 J1 B-8
NZ-920 #1
BAIT IN 121J1A-1 JIA-11
BAIT RET 121J1A-7 J1B-7J
tI . JIB-6AIRCRAFT POWER GNDAIRCRAFT +28 V DC J1B-5
IRU #2 BATTERY &CHARGER #2
CHARGERINHIBIT C170J1A-G9 JIA-1
BAIT IN Cl 70J1C-2 J1B-8
NZ-920 #2
BAIT IN C121J1A-1 JIA-11
BAIT RET C121J1A-7 T J1B-7●
!1 J1B-6AIRCRA17 POWER GNDAIRCRAFT +28 V DC J1B-5
1
IRU #3 or AHRS
BATT IN El70J1C-2
Battery and Charger InterconnectFigure D-7.2
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APPENDIX EENVIRONMENTAL REQUIREMENTS
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APPENDIX EENVIRONMENTAL REQUIREMENTS
1.0 ENVIRONMENTAL TESTS
Unless otherwise specified the test procedures applicable to a determinationof equipment performance under environmental test conditions are set forthin the RTCA Document DO 160A, “Enviornmental Conditions and Test Proceduresfor Airborne Equipment”, January, 1980 and AS-8034 Minimum PerformanceStandards for Airborne Multipurpose Electronic Displays, December, 1982.
The P-870 Weather Radar System has been qualified to DO-160B. For a list ofspecific categories refer to table E-1.
The equipment not previously qualified shall be submitted to and shallsuccessfully pass the following applicable simulated environmentalconditions for the categories and levels specified or shall be qualified bysimilarity.
1.1 Temperature and Altitude
RTCA Document DO-160A contains several temperature and altitude testprocedures which are specified according to the category for which theequipment will be used.
1.1.1 Low Temperature Test
The equipment shall be subjected to the test conditions of RTCA/DO-160Apara. 4.4 and meet the requirements of the respective System SpecificationPerformance Test section.
REMOTE . COCKPIT.DO-160A PARA. 4.0 CAT.A2F2 CAT.AIF1.
OPERATING TEMPERATURE -55 Degrees. -30 Degrees,
1.1.2 High Temperature Test
The equipment shall be subjected to the test conditions of RTCA/DO-160Apara. 4.5 and meet the requirements of the respective System SpecificationPerformance Test section.
REMOTE . COCKPIT.
OPERATING TEMPERATURE +70 Degrees. +55 Degrees.
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1.2 Altitude Tests
1.2.1 Altitude
The equipment shall be subjected to the test conditions of RTC/DO-160Apara. 4.6.1 and meet the requirementsof the respective SystemSpecification PerformanceTest section.
1.2.2 Decompression Test
The equipment shall be subjected to the test conditions of RTC/DO-160Apara. 4.6.2 and meet the requirements of the respective SystemSpecification Performance Test section.
1.2.3 Overpressure Test
The equipment shall be subjected to the test conditions of RTC/DO-160Apara. 4.6.3 and meet the requirements of the respective SystemSpecification PerformanceTest section.
1.3 TemrieratureVariation Test
The equipment shall be subjected to the test conditions of RTC/DO-160Apara. 5.0 and meet the requirements of the respective System SpecificationPerformance Test section.
CAT.C
TEMPERATURE RATE .................... 2 Deg C/Min.
1.4 HumiciitvTest
The equipment shall be subjected to the test conditions of RTC/DO-160Apara. 6.0 and meet the requirements of the respective System SpecificationPerformance Test section.
CAT.A
HUMIDITY ........................... 95% for 48 hours.
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1.5 Shock Test
1.5.1 Operational Shocks
The equipment shall be subjected to the test conditions of RTC/DO-160Apara. 7.1 and meet the requirements of the respective SystemSpecification Performance Test section.
OPERATIONAL ...................... 6G
1.5.2 Crash Safety Shocks
The equipment shall be subjectedto the test conditions of RTC/DO-160Apara. 7.2.
CRASH SAFETY ..................... 15G
1.6 Vibration Test
CAT.0
The equipment shall be subjected to the test conditions of RTC/DO-160Apara. 8.0 and meet the requirementsof the respective System SpecificationPerformanceTest section.
1.7 Ex~losive Mixture Test
DO-160 PARA. 9.0
The equipment is not installed in an explosive mixture environment and istherefore not subject to this test.
1.8 WaterDroofnessTest
DO-160 PARA. 10.0
The equipment is not installed in an environment requiring these tests andthey will not be conducted.
1.9 Fluids Susceptibility
DO-160A PARA 11.0
The equipment is not installed in an environmentcontaining these fluidsand is therefore not subject to this test.
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1.10 Sand and Dust
DO-160A PARA. 12.0
The equipment is not installed in a sand laden moderate wind conditionenvironment and is therefore not subject to this test.
1.11 Funaus Growth Test
DO-160 PARA. 13.0
The equipment design uses components that do not contain organicmaterials so is therefore not subject to this test.
1.12 Salt Sm-av
DO-160 PARA. 14.0
The equipment is not installed in a salt laden moderate wind conditionenvironment and is therefore not subject to this test.
1.13 Macmetic Effect
The equipment shall be subjected to the test conditions ofRTC/DO-160Apara. 15.0 and meet the requirements of the respective SystemSpecification PerformanceTest section.
CATEGORY SELECTION BASEDON TEST RESULTS
1.14 Power SUDDIY InDut Tests
1.14.1 Normal Operating Conditions
The equipment shall be subjected to the test conditions of RTC/DO-160Apara. 16.3.1 and 16.3.2 and meet the requirements of the respectiveSystem Specification PerformanceTest section.
CAT.A
1.14.2 Abnormal Operating Conditions
The equipment shall be subjected to the test conditions of RTC/DO-160Apara. 16.3.3 and 16.3.4 and meet the requirements of the respectiveSystem Specification PerformanceTest section.
CAT.A
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1.15 Voltaqe Spike
DO-160 PARA. 17.0 CAT.A
The equipment shal1 be subjected to the test conditions of RTC/DO-160Apara. 17.3 and meet the requirementsof the respective SystemSpecification PerformanceTest section.
600 Volt, 10u Sec.Source Impedance 50 ohms.
1.16 Audio Frewency Conducted Susceptibility
The equipment shall be subjected to the test conditions of RTC/DO-160Apara. 18.0 and meet the requirementsof the respective SystemSpecification PerformanceTest section.
CAT.Z
MAXIMUM RIPPLE .................... 1.4 VOLTS.
1.17 Induced Sicmal Susce~tibilitv
The equipment shall be subjected to the test conditions of RTC/DO-160Apara. 19.0 and meet the requirementsof the respective SystemSpecification PerformanceTest section.
CAT.A
1.18 Radio FreauencY Susceptibility
The equipment shall be subjected to the test conditions ofRTC/DO-160Apara. 20.0 and meet the requirements of the respective SystemSpecification Performance Test section.
EQUIPMENT SHALL BE TESTED TO CAT Z REQUIREMENTSAND OFFENDING FREQUENCIESIDENTIFIED
1.19 Emission of Radio Frequencies
The equipment shall be subjected to the test conditions of RTC/DO-160Apara. 21.0 and meet the requirementsof the respective SystemSpecification PerformanceTest section.
CAT.A
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1.20 X-Rav Radiation [DisDlav Units Onlv)
The equipment shall meet the requirements of Document AS-8034 para. 5.20.
1.21 Ultraviolet Radiation [DisDlayUnits Onlv\
The equipment shall meet the requirements of Document AS-8034 para. 5.21.
1.22 Foaqinq {DisDlav Units on~v~
The equipment shall meet the requirements of Document AS-8034 para. 5.22.
1.23 Thermal Shock {Disc)lavUnits Onlv~
The equipment shall meet the requirements of Document AS-8034 para. 5.23.
1.24 Dielectric Test (DisDlav Units OnIv)
The equipment shall meet the requirements of Document AS-8034 para. 5.24after completion of all other qualification tests.
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Table E-1P-870 Environmental Qualifications
Cateqory Qualifications
WU-870 WC-874
Temperature Altitude F2 B1
Temperature Variation B c
Humidity A A
Shock - Operational 6g 6gCrash Safety 15g 15g
Vibration JLY KS
Explosion x x
Waterproofness x x
Fluid Susceptibility x x
Sand and Dust x x
Fungus Resistance x x
Salt Spray x x
Magnetic Effect A A
Power Input A A
Voltage Spike A A
AF Conducted Susceptibility A A
Induced Signal Susceptibility A A
RF Susceptibility A A
RF Emissions A A
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APPENDIX FLSZ-850 LIGHTNING SENSOR SYSTEM
INSTALLATION
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APPENDIX FLSZ-850 LIGHTNING SENSOR SYSTEM INSTALLATION
1.0 LSZ-850 LIGHTNING SENSOR SYSTEM INSTALLATION
1.1 Scope
This appendix provides installation information for the Lightning SensorSystem (LSS). Included is mechanical and electrical data for the LightningSystem as well as interconnect information necessary to tie this system intothe G-IV system. Wiring modifications required for the baseline C-IV unitsare also provided.
1.2 Functional Description
The LSS is a passive (non-radiating) system which is approved for use underFAA TSO C11O. It detects electromagnetic and electrostatic fielddisturbances present during thunderstorm activity. This lightning activityis analyzed and formatted for display on the EFIS as an aid in severeweather avoidance. The system consists of the LP-850 Processing Unit, theLU-860 Controller, and the AT-850 Antenna.
The LP-850 Processor Unit interfaces with the antenna, controller, and otheraircraft sensors, for analyzing input data, and formatting and transmittingdata to EFIS (Symbol Generator). Communication to EFIS is via an ARINC 429serial bus.
NOTE “ Lightning data is available for all 7008570-XXX Symbol Generators‘“ except the -913. Lightning is not displayed when using a
7008570-913.
The LU-860 Controller provides the LSS with pushbutton mode selections ofOFF, STANDBY, LX, and CLEAR/TEST.
The AT-850 antenna assembly is a low profile unit which mounts on anexterior surface of the aircraft. It receives and amplifies orthogonalmagnetic fields and the electrostatic field.
A test circuit is provided which exercises the antenna and antenna/processor unit link by having the processor unit provide a test stimulus tothe antenna. The resultant antenna inputs are analyzed and displayed in thenormal manner to allow the operator to verify the operation of the system.
Figure F-1 shows a block diagram of the system. An equipment list isprovided in Table F-1.
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Am EmQJw01—OmrmL
u0.5vm
r
r
——
LU-WO
Tl+dd,46.!7 F/G--’-: –
Con-mou.su ~%%?N%m
I GROLFND
1’ II M5J1B
I , PwRm 66
IL-— Y
11TAP II
msza II
Y14.5J1A
52
47
53
w.-
ld=d=d=rlS2r.
—-
FFiFzY--lxurl- 1
24
L.dtNHIWTRFTW
rIIIIIII
J
(3- (JIAdOTOJIA471IWLWIED 1P&Nrs4NAL5MwNrEom~
G-IV Lightning Sensor System B1ock DiagramFigure F-1
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Table F-1LSZ-850 Lightning Sensor System Equipment List
Outline &Connector Part Installation Mating MountingDesiccator llescri~tion Otv Number Dwq. No. Connector Hardware
145JIA, LP-850 1 7011822-903 7011823 DPX2MA-67S-67S- 1/4 ATR Short145J1B Processor Unit 33B-0011 Tray
(SPN 2500122-1) (SPN 7011839-901)
146JI LU-860 1 7012738-905/ 7012739 MS27473E-1OA35S Dzus MountController -906* (SPN 4011518-25)
147J1 AT-850 1 4057697-901 4057962 MS27473E12-35S 10-32 SocketAntenna (SPN 4011518-060) Screws (3)(Tear-drop)
147J1 AT-855 1 7014062-902 7014072 MS27473E12-35S #8 ScrewsAntenna (SPN 4011518-060) w/max Washer(Brick) Dia. of .350 inch
* ~: Bezel Color, Gray/Black
1.3 Installation Information
1.3.1 LP-850 Processor Unit
The processor unit is housed in a 1/4 ATR short rack and is designed tomount in the aircraft employing a standard 1/4 ATR tray using a singlethumb screw insertion/holdownnut. An extraction handle shall bemounted under the front rack overhang. Outline and installationinformation, includingmating connectors, is provided in Table F-1.
There are no external cooling requirementsfor the processor unit. Aminimum one inch clearance shall be provided between the top, back,sides, and front of the unit and any adjacent equipment for thermalisolation.
For optimum service life, the processor unit shall be installed in alocation where ambient temperature is between -20 and +40 degrees C.
1.3.2 LU-860 Controller
The LU-860 contains four pushbuttons for mode control of the LSS.Mounting is accomplishedusing Dzus fasteners located on either side ofthe front panel. Outline and installationinformation, includingmatingconnectors, is provided in Table F-1.
There are no power requirements,other than that necessary for panellighting.
There are no external cooling requirementsfor the controller.
1.3.3 AT-850 Antenna
The antenna is a low profile non-standardassembly which mounts on theaircraft exterior surface. The assembly is covered with a glassreinforced thermoplastic injectionmolded cover which is coated with ananti P-static material. The antenna is secured to the aircraft using asilicone gasket for sealing cabin pressure and 3 - 10/32 hex socketscrews. Outline and installationinformation, included matingconnectors, is provided in Table F-1.
The operation of the LSS is very dependent on proper placement of theantenna. The site for the antenna shall be determined by usingHoneywell test equipment, or equivalent,which is specificallydesignedto provide the necessary test signals to allow evaluation of thepossible aircraft mounting locations.
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1.4 Environmental Oualifications
1.4.1 LP-850 Processor Unit
The LP-850 Processor Unit is qualified to the following DO-160Bstandards: F2A/JLY/YxxxxxAAAzA.
1.4.2 LU-860 Controller
The LU-860 Controller is qualified to the following DO-160B standards:F2A/PKs/YxxxxxAAAzA ●
1.4.3 AT-850 Antenna
The AT-850 Antenna is qualified to the following DO-160B standards:F2A/JLY/YsFxxxAAAzA.
1.5 Power and Groundinq Requirements
The power and grounding requirementsare as described in Section 3 of thisdocument. Table F-2 specifies the type and amount of power needed by eachLSS unit.
1.6 Weiaht
See Table F-2 for weight information.
1.7 Other Mountina/WirinaRequirements
The cable run from the antenna to the processor unit shall not exceed 150feet.
Defeating of the LSS antenna inputs is required when those communicationsystems operating at or below 4 MHz are active. A circuit in the LP-850unit has been provided to allow this. This circuit requires that pins145J1B-24 and 145J1B-25 be connected together to accomplish the defeating.Connection of these pins through the aircraft frame is not recommended.
Shielding of signal wires connecting the processor and antenna unitsshould be grounded at the LP-850 Processor Unit only. Grounding of theshields at the AT-850 may cause excessive noise levels on the lines.Shields must be kept separate. If bulkhead connections are required,individual shields shall be carried through on separate pins.
IRS informationmay be replaced with any unit which provides true headingat a minimum .133 second update rate and present position at a minimum 5second update rate via an ARINC 429 bus.
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Pin 7 of the AT-850 unit is chassis ground. Connection of this pin tochassis ground is not recommended and should be used only in thoseapplicationswhich require each unit to be grounded to the chassis.
1.8 Interconnect Information
Interconnectdata for the entire LSZ-850 installationfollows. Completeinformation is provided for the processor, controller, and antenna, aswell as modifications required for the baseline G-IV components.
Table F-2Lightning Sensor System Power and Weight Parameters
POWERUNIT WEIGHT TYPE CONSUMPTION
LP-850 6.75 LBS 28Vdc 28 W
AT-850 2.5 LBS flov(jc* 0.75 w
LU-860 0.5 LBS 28Vdc 0.7 w
* Supplied by processor unit
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Processor Unit
IOBP
(I)(I)
(I)(I)(0)(0)(o)(o)(o)(o)(o)(0)(0)(o)(P)(o)(1)(1)(I)(1}(o)(o)(0)(o)(o)(o)(1)(I)(P)(1)(I)(r)(I)(I)(I)(r)(I)(o)(o)
Function Connector Pin Connects To
HREF (H) 145J1A-1 ------NCHREF (L) -2 ------NCSPARE -3SPARE -4SPARE -5VREF (H) ------NCVREF (L) :; ------NCRED VIDEO (H) -8 ------NCRED VIDEO (L) -9 ___~~
GREEN VIDEO (H) -lo ------NC.GREEN VIDEO (L) -11 __.-~~RED/GREEN VIDEO SHIELD -12 ------NCBLUE/VIDEO SEL SHIELD -13 ------NCBLUE VIDEO (i-l) -14 ------NCBLUE VIDEO (L) -15 ------NCVIDEO SEL (H) -16 ------NCVIDEO SEL (L) -17 ------NCDC RETURN -18 ------NCSTBY WX * -19 ------NCRANGE O -20 ------NCRANGE 1 -21 ------NCRANGE 2 -22 ------NCRANGE 3 -23 ------NCHS (H) -24 ------NCHREF (H) -25 ------NCHREF (L) -26 ------NCHREF/VREF SHIELD -27 ------NCVREF (H) -28 ------NCVREF (L) -29 ------NCRED VIDEO (H) “30 ------NCRED VIDEO (L) -31 ------NCDC RETURN -32 ------NCGREEN VIDEO (H) -33 ------NCGREEN VIDEO (L) -34 ------NCBLUE VIDEO (H) -35 ------NCBLUE VIDEO (L) -36 ------NCVIDEO SEL (H) -37 ------NCVIDEO SEL (L) -38 ------NCSEL CHK LIST * -39 ------NCSEL NAV FODE * -40 ------NCHS (L) -41 ------NCVS (H) 145J1A-42 ------NC
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IOBP
(1)(I)(I)(o)(I)
(I)(I)(1)(1)(1)(I)(I)(1)(I)(I)(1)
(1)(1)(I)(I)(I)(I)
(1)[~j
Function
TEST MODE 1 *TEST MODE 2 *TEST RETURNVS (L)CS COMMON
Cs 1Cs 2Cs 3Cs 4Cs 5CS 6Cs 7CS 8Cs 9Cs 10Cs 11
Cs 12Cs 13Cs 14Cs 15CS 16CS COMMON
RS-232 (H)RS-232 (H)RS-232 COM
Processor Unit
Connector Pin
145J1A-43 ------NC-44 ------NC-45 ------NC-46 ------NC-47 (22)--------------------
-48 ------NC-49 ------NC-50 ------NC-51 ------NC-52 (22)---------------------53 (22)---------------------54 ------NC-55 ------NC-56 ------NC-57 ------NC-58 (22)--------------------
-59 (22)---------------------60 ------NC-61 ------NC-62 ------NC-63 ------NC-64 (22)--------------------
-65 ------NC-66 ------NC
145J1A-67 ------NC
Connects 70
145J1A-52,145J1A-53
145J1A-47145J1A-47
145J1A-64(See Note 1)145J1A-64
145J1A-58,145J1A-59
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Processor Unit
IOB&
(I)(1)(P)(P)
(P)
(I)(I)(I)(I)(1)(1)(I)(o)(I)(I)(I)(I)(o)(o)(o)(1)(o)(o)(I)(I)(B)(B)(B)(B)
(o)(o)(I)(I)(I)(I)(I)(I)(I)(I)
Function
HDG VALIDwow *28 VDC POWER28 VDC POWER GND
CHASSIS GND
Hn (H)Hn (L)OUTER SHIELDTAS REF (L)Hw (H)Hw (L)’Hw SHIELD-10 VDCE (H)E (L)E SHIELDHn SHIELD+10 VDC10 VDC RETURN10 VDC SHIELDTEST SHIELDTEST LOOP (H)TEST LOOP (L)XMIT INHIBITXMIT INHIBIT RETURNARINC 429 (H)RECEIVER 1 (L)ARINC 429 (H)RECEIVER 2 (L)
LX VALID FLAGLX VALID FLAG RETURNTAS (H)TAS (L):1: ~;; (H)
IAS (L)IAS REF (H)A/PSPEEDREF (H)A/P SPEED REF (L)
Connector Pin
145J1B-1 (22)----------------------2 (22)----------------------3 (20)----------------------4 (20)---------------------
-5 (20)---------------------
$-6”(22)-- ----~---------=--7 (22)-- ----J4--------J-~--8 ::::::~;---tI-9
y!1,
1-lo (22)---~+-+-- ----+’11 (22)------T,--- ‘--------12 -------
J-13 (22)--- --‘ I n_--[_
i
T~-- ~-1
I
-----------:;: [;;~:::t Ii___ ---16 -------Y I !
------- it
::j [;;]--4-7-1----------$----<-+--------- -
-24 (22)---------------------25 (22)---------------------26 ------NC-27 ------NC ,
Z-28 (22)-------- -----------29 (22)-------- --~!-------
-30 ------NC-31 ------NC-32 ------NC-33 ------NC-34 ------NC-35 ------NC-36 ------NC-37 ------NC-38 ------NC
145JIB-39 ------NC
Connects To
A/C 28V DC PWRA/C WOW SWITCHA/C 28VDC PWRA/C 28VDCPWR GNDA/C CHASSISGND147J1-11147JI,-12
147JI-1147J1-14
147J1-151471JI-3147J1-4
147J1-8147JI-9
147J1-5147JI-6See Note 2See Note 2
IRS ARINC 429TRANSMITTER(See Note 3)
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Processor Un~t
IOBP
(I)(1)(1)(B)(B)(1)(I)(B)(B)(1)(B)(B)(1)(B)(B)(1)(1)(1)(1)(o)(0)
(o)(I)(I)(1)(1)(I)
Function
DADC HP (H)DADC HP (L)TRANSMITTER 3 SHIELDAf!INC429 (Ii)TRANSMITTER 4 (L)TRANSMITTER 4 SHIELDIAS REF (L)ARINC 429 (H)TRANSMITTER 1 (L)TRANSMITTER 1 SHIELDARINC 429 (H)TRANSMITTER 2 (L)TRANSMITTER 2 SHIELDARINC 429 (H)TRANSMITTER 3 (L)TRANSMITTER 3 SHIELDHDG (Y)liDG(Z)HDG (X)HDG SYNCHRO (H)HDG SYNCHRO (L)SPARECP RETURNHDG OFFLX-TLX-SLX MODEPMR ON
SPARE
Connector Pin
145J1B-40 ------NC-41 ------NC-42 ------------43 ------NC-44 ------NC-45-46-47-48-49-50-51-52-53-54-42
-----------
------NC
i(22)-.---.,?- ----------
(22} -------- -------.-
--------- -.!
~(22)------=- ‘----------(22)-----J,=+ --------------------
(22) i----------,$
---------(2+_+- ------------------- J
-55 ------NC-56 ------NC-57 ------NC-58 ------NC-59 ------NC-60-61 (22)---------------------62 ------NC.63 (22)---------------------64 [22)---------------------65 (22j---------------------66 (22)--------------------
145J1B-67
Connects To
65JIA-5365JIA-54
C65J1A-53C65JIA-54
E65J1A-53E65J1A-54
146J1-12
146J1-13146J1-9146J1-11146JI-7,65J1A-15,C65J1A-15,E65J1A-15
NOTES: 1. This connection is required if antenna is mounted on bottom ofaircraft.
2. 145J1B-24 and 145J1B-25 are to be connected when tiFcommunicationsare active.
3. IRS input may be replaced with any unit providing true heading ata 0.133 second update rate and present position at a 5 secondupdate rate via an ARINC 429 bus.
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10BP
(P)
(p)
(1)
(0)
(o)(1)(o)
Controller Unit
Function Connector Pin
SPARE 146J1-1+28 VDC PANEL DIMMING ------NCSPARE :;PANEL DIMMING (L) -4 (20)---------------------
SPARE+5 VIIC PANEL DIMMING :: (20)---------------------
CONTROL (H)
POWER ON -7 (22)---------------------
SPARELx-s :: (22)---------------------SPARE -loLX MODE -11 (22)--------------------CONT PNL RTN -12 (22)--------------------LX-T 146J1-13 (22)--------------------
Connects To
A/C 5VLIGHTINGCONTROL (L)
A/C 5VLIGHTINGCONTROL(ti)145J1B-66,65J1A-15,C65J1A-15,E65JIA-15
145J1B-64
145JIB-65145J1B-61145J1B-63
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105P
(o)
(0)(o)
(I)(1)
(o)
(I)
Function
tlw(H)SPAREE (H)E (L)
TEST LOOP (H)TEST LOOP (L)
SPARE+10 VDC10 VOC RETURNSPAREHn (H)Hn (L)
SPAREHw (L)
-10 WIG
SPARE
Antenna
Connector Pin1
mt147J~-1 (22)__-y-F- ------------2--]’
1-3 (22)----------=- “-------4 (22)--------+- -“-----
-5 (22)-a------------------6 (22)--!+---------------
-7
G (22)----------$=--------9 (22)..--.-----1{-+--------10
1-11 (22)-= -------:--------12 (@~. ---------------
-13-14 (22) 11~-------- -----------
U.j! I-15 (22)--------- ----------
147J1-16 THRU -22
Connects To
145J1B-10
145J1B-14145J1B-15
145J1B-22145J1B-23
145J1B-18145JIB-19
145J1B-6145J1B-7
145J1B-11
145J1B-13
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Symbol Generator No. 1
JOBP Function Connector Pin Connects To——
(1) LX PWR ON 65JIA-15 (22)-------------------- 145JI13-66,146J1-7,C65JIA-15,
iE65J1A-15
(B) LX (H) -53 (22)----9- ----””------ 145Jli3-47(B) ARINC 429 (L) -54 (22)---++----------- 145J1B-48
(I) LX INSTALLED 65JIA-67 (22)-------------------- A/CGND
Symbol Generator No. 2
10BP Function Connector Pin Connects To——
(1) LX PklRON C65J1A-15 (22)-------------------- 145J1B-66,14631-7,65J1A-15,
1
E65JIA-15[B) LX (H) -53 (22)---O-- ------u------ 145J1B-50[B) ARINC 429 [L) -54 (22).-++ ------------- 145J1B-51
(1) LX INSTALLED C65J1A-67 (22)-------------------- A/C GND
Symbol Generator No. 3
IOBP Function Connector Pin Connects To——
(1) LX PWR ON E65J1A-15 (22)-------------------- 145J1B-66,146J1-7,65JIA-15,
4
C65J1A-15(B) LX (H) -53 (22)---=’- ------------- 145J1B-53(B) ARINC 429 (L) -54 (22)--4~J ------------- 145J1B-54
(I) LX INSTALLED E65J1A-67 (22)-------------------- A/C GND
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APPENDIX GSPARE FLIGHT MANAGEMENT SYSTEM INSTALLATION
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APPENDIX GSPARE FLIGHT MANAGEMENT SYSTEM INSTALLATION
1.0 SPARE FLIGHT MANAGEMENT SYSTEM INSTALLATION
1.1 scoDe
This appendix provides information on the installation of a spare FlightManagement System (FMS) into the G-IV cockpit. Included is information onthe wiring of the spare as well as a description of the required changesto the baseline G-IV system. A brief operational description of thisarchitecture is also provided.
1.2 Operational Description
Operationally,the spare FMS can be considered to have two basic operatingmodes: warm spare and replacement. As a warm spare, it navigates usingdata supplied to it via the ARINC 429 radio and ASCB. It receives themajority of its data in the same manner as FMS #1, primary data from the#1 systems and secondary data from the #2 systems.
The spare is connected to ASCB A and B in the same manner as FMS #2 (i.e.primary is ASCB B and secondary is ASCBA). All ASCB transmissions fromthe spare are software inhibited.
Flight plans can only be loaded into the spare via the spare CDU. Thetransfer of flight plans from the spare to either #1 or #2 or vice versacannot be accomplished.
The spare FMS may be selected to replace either FMS #l or FMS #2. This isaccomplished using the FMS selector switch depicted in Figure G-1. Whenthe switch is thrown, the replaced unit is powered down, the spareundergoes a cold start, its active flight plan is replaced with the planactive in the remaining FMS, and it begins to function identically to thereplaced unit.
A block diagram of the signal switching required for the three FMSarchitecture is shown in Figure G.1. Details on the Switching of specificfunctions is provided in the fo710wing sections.
1.3 Mountinu Information
The spare FMS is composed of the same units as FblS’s#1 and #2, namely anNZ-800 Navigation Computer and a CD-81O Control Display Unit. The DL-800Data Loader, which is included in the baseline G-IV equipment, is alsoutilized in this architecture. A third PerformanceComputer is notincluded. Refer to Section 2.3 for mounting requirements.
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NIv
0d.
~.c _=_L @ 1
t-
1-“ . w NO. 1
2
+;W
WIT H
, All SW ICMESSUOW?tfm PUS t, ?c0NW31JllA1WN
s MIcWS DENOTED w @ NW ACIIVAIED WISN SfLECTOII9w11Cl+U ACEDIN 9.3POS111G+415PAREi3EFtUXS FM *I
3 SWICHES OWQTEO 8? @ bSE N31VA1ED V.WZNSELECIWIw Wn WED IN 1,3 m.wrm (WANE IIEI’LALWF&@21
4 AmwcWCM --’+ mm A Mm ❑
4
* 4I
5EIUN bnll W3mHs UnlwI mm
y *Nz No. I
M W IMIA (+WXONDUW NAVMTA
IWERMAMMWIEIES
Cd&9J
,
F’; ~ L_
‘*E OPAnc Nz esJwl Mm UacnErf WwuI mm
lNIEn+JAvmsmEIEs
PI!MAIWN4V (WA
5PPE . *W— W MIA
J
1 1 +- “ mr.—— 1
+ ‘%%J IL–. –--l
I8E—MUIMTA ! I
1I
J H ‘“’W ‘n --l %%”* 1 y,omcm
T ●“”
Honeywell #u#@&NcE
1.4 Fault Warninq Comouter Interface
The Fault Warning Computer (FWC) interfaceswith the spare through theSPARE CDU VALID and SPARE NZ VALID discretes. Three other discrete inputshave been added to the FWC. These are: SPARE FMS INSTALLED (indicating aspare is installed), SPARE FMS ACTIVE 2 (indicatingthe spare has replaced#2), and SPARE FMS ACTIVE 1 (indicatingthe spare has replaced #l). Thelast two signals are activated by the FMS selector switch. The interfaceis shown in Figure G-2.
1.5 Data Loader Interface
The data loader permits the loading of the spare FMS through its AUXposition and, as such, requires no switching. The data loaderinterconnect shown in Figure G-3.
1.6 Performance Management Comrmter Interface
Each Performance Management Computer (PMC) is paired operationallywithone FMS. Figure G-4 shows the switching required when the spare isactivated.
1.7 Interconnect Information
Providing the replacement capability requires that a large number of wiresbe switched. These can be grouped into the following general categories:
~: The warm spare is configured as FMS #2 for ASCB purposes. When itis selected to replace FMS #1 its ASCB inputs must be switched. Refer toFigure G-5 for ASCB switching.
Radios: The warm spare is configured to use left side radios as itsprimary inputs and the right side radios as its secondary inputs. Theseinputs must be switched when the spare replaces FMS #2. Radio tuningcontrol from the spare must be activatedwhen the spare replaces FMS #1 or#2. Refer to Figure G-6 for radio switching.
Int)ut/OutrmtDiscretes: Any input discrete which is side-dependentmustbe switched when the spare replaces either FMS #1 or FMS #2. The SDI andLTS configuration discretes are two such examples. Any LTS common to bothFMS #1 and FMS #2 may be similarly configured for the spare and does notrequire switching (e.g. if the same VLF/Omega is connected to FMS #1 andFMS #2, the spare should be configured for VLF/Omega and connected to thatsame source, with no switching required). Refer to Figure G-7 fordiscrete switching.
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LonciTerm Sensor In~uts: Any long term sensor input (i.e. IRS, VLF/Omega,etc.) which is side-dependentmust be switched when the spare replaceseither FMS #1 or FMS #2. Any sensor which is common to FMS #l and FMS #2may be wired directly to the spare and does not require switching. Referto Figure G-8 for long term sensor switching.
Power: Power is to be removed from either FMS #1 or FMS #2 after it hasbeen replaced. Refer to Figure G-9 for power switching.
Interconnectdata for the entire spare FMS installationfollows. Completeinformation is provided for the spare Navigation Computer and its CDU aswell as modifications required for the baseline G-IV components.
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106P
(P)(B)(B)
(B)(B)
(B)(B)(B)(B)(B)(B)
(P)(B)(6]
(B)(B)
p]
(B)(B)(B)(B)
CDU No. 1
Function Connector Pin
+28 VDC POWER 120J1-B (20)---------------------RS422 XMTR - (H)
t-Y (22)-----R- ------------
PELF COMP (DATA) (L) -z (22)-----y- ------------SHIELD GND---------
RS422 XMTR - (H)t
-a (22)----1?--------------PELF COMP (CNTL) (L) -b (22)-----Y-- ------------
SHIELD GND---------RS422 RCVR - (H) -c (22)-----Q--’------------PERF COMP (DATA) (L) It:-d (22)-------- ------------RS422 RCVR - (H) -e (22)----PERF COMP (CNTL) (L)
I
n-- -------------f (22)-----U-- ------------RS422 RCVR - (H) -g (22)---- -- ------------
7PERF COMP (CLK) (L) 120J1-h (22)----!----------------
CDU !40. 2
Function Connector Pin
+28 VDC POWER C120J1-B (20)---------------------RS422 XMTR - (H) -Y (22)-----fi
$------------
PERF COMP (DATA) (L) -z (22)----J+ ------------SHIELD GND---------
RS422 XMTR - (H) -a (22)------~i------------
PERF COMP (CNTL) (L) -b (22)----- - ------------SHIELD GND---------Y
llS422RCVR - (H)
i
-c (22)--------------------PELF COMP (DATA) (L) -d (22)-----U- ------------RS422 RCVR - (H) -e (22)-----= ------------PERF COMP (CNTL) \l.] -f (22)----J$- ------------RS422 RCVR - -g (22)----~$___PERF COMP (CLK) (L) C120J1-h (22)-----G- ------------
Connects To
Figure G-9Figure G-4Figure G-4
Figure G-4Figure G-4
Figure G-4Figure G-4Figure G-4Figure G-4Figure G-4Figure G-4
Connects To
Figure G-9Figure G-4Figure G-4
Figure G-4Figure G-4
Figure G-4Figure G-4Figure G-4Figure G-4Figure G-4Figure G-4
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Spare CDU
IOB_P_ Function Connector Pin Connects To
SPARE E120J1-A(P) +28VDC POWER -B (20)--------------------- A/C 28VDC PWR(P) POWER RETURN -C (20)--------------------- A/C 28VDC
RETURN(I) PANEL LIGHTING RETURN -D (22)--------------------- A/C LTG RETURN
SPARE -E(P) 28 VllCANNUNCIATOR LTG -F (20)--------------------- A/C28VDC LTG
PWR(P) CHASSIS GND -G (20)--------------------- A/CCHAssIs
GND(P) ANNUNCIATOR LTG RETURN -H (20)--------------------- A/C LTG RETURN(P) 5V KEYBOARD PANEL LTG :{ (22)--------------------- A/C 5V LTG pWR
RESERVEDSPARE -L
(B) RS422XMTR - (H)t
-~ (22)_-,7., -------------- E121J1A-55(B) NAVCCN4P (DATA) (L) -N (22)---- - -------------- E121J1A-56
------Y(B) RS42Z XMTR - (H]
‘HIELD:fi;;]---[$ :::::::::::::::: E121J1B8E121J1B-7
(B) NAVCOMP (CNTL) (L) ------SHIELD GND------Y
(B) RS422 RCVR - (H)$
-s (22)---=- -------------- E121J1A-65(B) NAVCOMP (DATA) (L) -T (22)--:+ -------------- E121J1A-66(B) RS422 RCVR - (H) ~~ @;j---f$-$-------------- E121J1B-32(B) NAVCOMP (CNTL) (L) ------ -------------- E121J1B-33(B) RS422 RCVR - (H) -W (22)---X- -------------- E121J1B-35(B) NAVCOMP (CLK) (L) i-x (22)---:- -------------- E121J1B-36(B) RS422 XMTR - (H)
*-.--.--+ - -------------- FIGURE G-4
(B) PERF COMP (DATA) (L) :! -------$- -------------- FIGURE G-4SHIELD GND------
(B) RS422 Xt4TR- (H) -------- -? t
-------------- FIGURE G-4(B) PERFCOMP (CNTL) (L) :: -------y-- -------------- FIGURE G-4
SHIELD GND------(B) RS422 RCVR - (H)
$~- -------------- FIGURE G-4------*-
(B) PERFCOMP (DATA) (L) :: ------J-l---------------- FIGURE G-4(B) RS422 RCVR - (H) s------ ---
$-------------- FIGURE G-4
(B) pERFCOMp(CNTL) ~I_j :; ------$- -------------- FIGURE G-4(B) RS422 RCVR - -9 ---”--*-
#-------------- FIGURE G-4
(B) PERFCOMP (CLK) (L) -h ------J-L- -------------- FIGLIREG-4{O) CDU VALID (GND/OPEN) -i ------------------------- E121JIB-1OO,
134J1A-77,C134J1A-77
SPARE .
SPARE E120Jl:i
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Spare CDU
IOB~ Function Connector Pin Connects To
(0) R PHOTO SENSOR OUT E120J1-m ------NC(0) L PHOTO SENSOR OUT -n ------NC
SPARE -P(1) DIM CALIBRATION -q ------NC
SPARE -r(1) LAMP TEST* -s (22)--------------------- A/C LAMP TEST
SPARE -tSPARE
(I) ANNUN LIGHTING BRIGHT/DIM ~; (22)--------------------- A/C WIRING(OPEN/28V)
(I) ANNUN LIGHTING DIM CONTROL -W (22)--------------------- A/C WIRING~c)i:;v)
-xSPARE -YSPARE -zSPARE -AASPARE -5%SPARE -ccSPARE -DD
(I) SELF TEST ENABLE * -EE ------NCSPARE -FFSPARE -GGSPARE E120J1-HH
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Navigation Computer No. I
IOB_P_
[P){B}(B)(B)(B)(B)(B)(B)(%)(B)
(B)
(B)(B)(B)(B}(B)(8)
(1)(1](1)(B)(B)
(B)
(B)
Function Connector Pin
+28YDC POWERARINC 429 RCVR -!4LS/ILSPRIARINC 429 RCVR -DME PRIARINC 429 RCVR -LTS #2ARINC 429 FWR -LTS #lRS422 RCVR -
OATA LOADER (DATA)
121J1A-3 (20)---------------------(H) -~~ (~*).-7--.$----.-.....-(L) -17 (22)--4----------------(H) ~;: [:;]--~---$ ------------(L) ----.----.-.”---(H) ~;j ~;;]::Q--*.---..------(L) ------------(H) -26 (22}~1-fi~II~------.-.---(L) -27 (22)------ ------------(H) -28 (22)--~~---f------------
II[L) i-29 (22)---!!-----.---------
ARINC 429 RCVR - (H)t
.32 (22)--7?-- ------------NAV PRIMARY {L) ------------ARINC 429 RCVR - (H) % l::{::pL::$-----.--..--NAY SECONDARY (L) -44 (22)---’c/-----.-6--..---ARINC 429 XMTR - (H) “45 (22)---~r--/------------GEN BUS SEC (L) -46 (22)---Y--- ------------
SHIELD GND------HIGH/LCWSPEEDBUS-LTS#l -47 (22)--------------------HKH/LoN*sPEEDBus-LTs#2 -48 [22}--------------------HIGH/LoN*spEEoBus-}j;#3 ~$ V]---:----------------ARINC 429 XMTR -
t----.-- -----.----.-
GEN BUS PRI (L) -51 (22)--~l--- ------------SHIELD GNO------J
RS422 XMTR - (H)
1
-52 (22)--fy - ------------
II
DATA LOADER (L) 121J1A-53 (22)--~-l-- ------------(DATA}
TSHIELD GtW------~
Connects To
FIGLIREG-9FIGURE G-6FIGURE G-6FIGURE G-6FIGURE G-6FIGURE G-8FIGURE G-8FIGURE G-8FIGURE G-8123J1-T,C121J1A-28,E121J1A-28123JI-S,C121J1A-29,E121J1A-29FIGURE G-6FIGURE G-6FIGURE G-6FIGURE G-6FIGURE G-6FIGURE G-6
AS REQUIREDAS REQUIREDAS REQUIREDFIGURE G-6FIGURE G-6
123J1-H,C121J1A-52,E121J1A-52123JI-G,C121J1A-53,E121J1A-53
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.271Mar 15/91
USe or disclosure Of information on this page is subject to the restrictions on the title page of this document.
Navigation Computer No. 1
IOBP
(o)(o)(B)
(B)
(B)(B)(I)(o)
(1)(o)
(B)(B)(1)(1)(I)(J)(I)(1)(I)(1)(I)(I)(1)(1)(1)(1)
(1)(1)[1)(I)(I)(1)
Furtction Connector Pin
TAG SYNC 121J1B-9 (22) ---------------------CDU SYNC -16 (22)------ -------------RS422 XMTR - (H)
t-20 (22)---fi- -------------
DATA LOADER (CLK) (L) :; &-21 (22)---4-- ------------
SHIELD GND-------JARINC 429 RCVR - (H)
$-22 (22)-----7~- -----------
DME SECONDARY (L) -23 (22)-----i--------------TAG SYNC -34 (22)--------------------ONSIDE TUNING CNTL -38 (22)--------------------(AUTOTUNE) (GND/OPEN)CDU SYNC -48 (22)--------------------CROSS-SIDE TUNING CONTROL -54 (22)--------------------(AUTOTUNE) (GND/OP~~]ARINC 429 RCVR - $
-57 (22)--:- --------------LTS #3 (L) -58 (22)--a-----------------LTS #1 NUMBER BIT #1 -59 (22)--------------------LTS #1 NUMBER BIT #2 -60 (22)--------------------LTS #2 NUMBER BIT #l -61 (22)--------------------LTS #2 NUMBER BIT #2 -62 (22)--------------------LTS #3 NUMBER BIT #l -63 (22)--------------------17S #3 NUMBER BIT #2 -64 (22)--------------------PERF COMP INSTALLED * -73 (22)--------------------LTS #1 CONFIGURATION -74 (22)--------------------LTS #1 CONFIGURATION -75 (22)--------------------LTS #1 CONFIGURATION -76 (22)--------------------LTS #2 CONFIGURATION -77 (22)--------------------LTS #2 CONFIGURATION -78 (22)--------------------LTS #2 CONFIGURATION -79 (22)--------”’----------MAINT TEST ENABLE * -87 (22)--------------------
ILS*/MLS SELECT -88 (22)--------------------LTS #3 CONFIGURATION -89 (22)--------------------LTS #3 CONFIGURATION -90 (22)---------------”----LTS #3 CONFIGURATION -91 (22)--------------------NAV/DME MANUAL * TUNE SEC -105 (22)-------------------NAV/DME MANUAL * 121J1B-106 (22)-------------------TUNE PRI
Connects To
FIGURE G-7FIGURE G-7123JI-K,C121JIB-20,E121J1B-20123JI-J,C121JIB-21,E121JlB-21
FIGURE G-6FIGURE G-6FIGURE G-7FIGURE G-6
FIGURE G-7FIGURE G-6
FIGURE G-8FIGURE G-8FIGURE G-7FIGURE G-7FIGURE G-7FIGURE G-7FIGURE G-7FIGURE G-7SIGNAL GNDFIGURE G-7FIGURE G-7FIGURE G-7FIGURE G-7FIGURE G-7FIGURE G-7E121JlB-87,APPX DFIGURE G-6FIGURE G-7FIGURE G-7FIGURE G-7FIGURE G-6FIGURE G-6
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.272Apr 15/93
Use or disclosure of information on this page is subject to the restrictions orI the title page of this document.
.- MAINTENANCE
NavigationComputer No. 2
IOB~
(P)~:]
(B)(B)(B){B)(B)(B)(B)
(B)
(B)(B)(B)(B)(B)(B)
(I)(1)(1){B)(%)
(B)
(B)
Function Connector Pin Connects To
FIGURE G-9FIGURE G-6FIGURE G-6FIGURE G-6FIGURE G-6FIGURE G-8FIGURE G-8FIGURE G-8FIGURE G-8123J1-T,121J1A-28,E121J1A-28123J1-S,121J1A-29,E121J1A-29
+28VDC POWERARINC 429 RCVR -MLS/ILS PRIARINC 429 RCVR -DME PRIARINC 429 RCVR -LTS #2ARINC 429 RCVR -LTS #1RS422 RCVR -
C121J1A-3 (20)---6-- --------------(H)
t-16 (22)-+3----------------
(L) -17 (22)-+ -- --------------(H)
$-18 (22)-+1-- --------------
(L) -19 (22)-%-- --------------(H) :;: [;:]-Q--J --------------(L) --------.--.--{H) ~$; [;;]:~:~--------------(L) --------------(H) -28 (22)~-----------------
II
(L) &-29 (22)-&i----------------DATA LOADER (DATA)
ARINC 429 RCVR - (H) +-32 (22)-1~r-y--NAV PRIMARY (L) -33 (22)-Y- --ARINC 429 RCVR - (H)
::? [;;]-Lr-#--NAV SECONDARY (L) ----ARINC 429 XMTR - (H) -45 (22):-~r-$--GEN BUS SEC (L) -46 (22)- --- --
YSHIELD GND-----liIGH/LOW*SPEED BUS-LTS #1 -47 (22)--------HIGH/LOW SPEED BUS-LTS #2 -48 (22)--------HIGH/LOW* SPEED BUS-LTS #3 -49 (22)--:-----ARINC 429XMTR - (H)
$-50 (22)--jj- --
GEN BUS PRI (L) -51 (22)-y- ;-StlIELDGND-----
RS422 XMTR - (H) -52 (22)-------
FIGURE G~6FIGURE G-6FIGURE G-6
------ --- ---------- -- ----------- - ---
FIGURE G-6FIGURE G-6FIGURE G-6
--------- ----------- - ---
AS REQUIREDAS REQUIREDAS REQUIREDFIGURE G-6FIGURE G-6
----------------- ------------------ -
------------
123J1-H,121J1A-52,E121JIA-52
---
II
DATA LOADER 1(L) C121J1A-53 (22)--1:- -------------(DATA)
T
123JI-G,121J1A-53,E121J1A-53
SHIELD GND------J
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.273Mar 15/91
Use or disclosure of information on this page is subject to the restrictions on the title page of this document.
Navigation Computer No. 2
106_P_
(o)(o)(B)
(B}
(B)(B)(I)(o)
(1)(o)
(B)(B)(1)(1)[1}(r)(1)(I)(I)(1)(1)(1)(1)(I)(1)(1}(1){1)(I)(1)(I)
Function Connector Pin Connects To
TAG SYNC C121J]B-9 (22) ---------------------CDU SYNC -16 (22)----- --------------RS422 XMTR - (H)
[
-20 {22} --~1- --------------
II
DATA LOADER (CLK) (L) -21 (22)--LJ-- --------”----r
SHIELD GND------~ARINC 429 RCVR - (H)
t-22 (22)-----,=~------------
fameSECCN’41ARY (L) -23 (22)-----J- -----------TAG SYNC -34 (22)--------------------ONSIDE TUNING CNTL -38 (22)--------------------(AUTOTUNE) (GND/OPEN)CDU SYNC -48 (22)--------------------CROSS-SIDE TUNING CONTROL -54 (22)------------------s-(AUTOTUNE) (GND/OPEN)ARINC 429 RCVR - (H)
t’57 (22)--I?-- ‘------------
LTS #3 (L) -58 (22)------ -------------LTS #1 NUMBER BIT#l -59 (22)--------------------LTS #1 NUMBER BIT #2 -60 (22)--------------------LTS #2 NUMBER BIT#l -61 (22)--------------------LTS #2 NUMEfERBIT #2 -62 (22)--------------------LTS #3 NUMBER BIT #1 -63 (22)--------------------LTS #3 NUMBER BIT#2 -64 (22)--------------------PERF COMP INSTALLED * -73 (22)--------------------LTS #1 CONFIGURATION -74 (22)--------------------LTS #1 CONFIGURATION -75 (22)--------------------LTS #1 CONFIGURATION -76 (22)--------------------LTS #2 CONFIGURATION -77 (22)--------------------LTS #2 CONFIGURATION -78 (22)--------------------LTS #2 CONFIGURATION -79 (22)--------------------ILS*/MLS SELECT. -88 (22)--”-----------------LTS #3 CONFIGURATION -89 (22)--------------------LTS #3 CONFIGWATION -90 (22)--------------------LTS #3 CONFIGURATION -91 (22)--------------------NAV/DME MANUAL * TUNE SEC -105 (22)-------------------NAV/DME MANUAL * C121JIB-106 (22)-------------------TUNE PRI
FIGURE G-7FIGURE G-7123J1-K,121J1B-20,E121J1B-20123J1-J,121J1B-21,E121JIB-21
FIGURE G-6FIGURE G-6FIGURE G-7FIGURE G-6
FIGURE G-7FIGURE $-6
FIGURE G-8FIGURE G-8FIGURE G-7FIGURE G-7FIGURE G-7FIGURE G-7FIGURE G-7FIGURE G-7SIGNAL GNDFIGURE G-7FIGURE G-7FIGURE G-7FIGURE G-7FIGURE G-7FIGURE G-7FIGURE G-6FIGURE G-7FIGURE G-7FIGURE G-7FIGURE G-6FIGURE G-6
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.274Apr 15/93
Use or disclosure of information on this page is subject to the restrictions on the title page of this document.
Spare Navigation Computer
IOB~ ~ Connector Pin Connects To
(P) AIRCRAFT BATT+28V E121J1A-1 (20)--------------------- A/C28VDCBAl?ERY DIRECT
SPARE -2(P) +28VDC POWER -3 (20)--------------------- A/C 28VDC PWR(P) POWER RETURN -4 (20)--------------------- &u;;VDC
(P) CHASSIS GROUND -5 (20)--------------------- $$ CHASSIS
(P) SIGNAL GROUND + (20)--------------------- A/c SIGNAL GND(P) A/C BATTERY RETURN -7 (20)--------------------- :4 BATTERY
RESERVEDRESERVED x
(B) SYS ASCB PRI BUS (H) ~;; [;;]-.fl$-------------- FIGURE G-5(B) SYS ASCB PRI BUS (L) ----- -------------- FIGURE G-5
RESERVED -12RESERVED -13
(I) ~O&OCK ASCB * -14 (22)-------------------- SIGNAL GND-15
(B) ARINC 429 RCVR - (H)i
-16 (22)--fi- -------------- FIGURE G-6(B) MLS/ILS PRI (L) -17 (22)--=- --”----------- FIGURE G-6(B) ARINC 429 RCVR - (H)
$-18 (22)--A- -------------- FIGURE G-6
(B) DME PRI (L) -19 (22)--& -------------- FIGURE G-6RESERVED -20RESERVED -21RESERVED -22
(B) ARINC 429 RCVR - (H)i
-23 (22)---G-- ------------- FIGURE G-8(B) LTS #2 (L) -24 (22)---!!- ------------- FIGURE G-8
RESERVED -25(B) ARINC 429 RCVR - (H)
!,
-26 (22)--1;-- ------------- FIGURE G-8(B) LTS #l (L) . -27 (22)---V-- ------------- FIGURE G-8(B) RS422 RCVR - (H) -28 (22)--P- ------------- 123J1-T,
121J1A-28,‘1 C121J1A-28
(B) ~;~~AOAOER (L) -29 (22)--&--------” ------- 123JI-S,121J1A-29,C121J1A-29
RESERVED -30RESERVED -31
(B) ARINC 429 RCVR - (H)i
-32 (22)---=-- ------------ FIGURE G-6(B) NAV PRIMARY (L) -33 (22)---!!-- ------------ FIGUREG-6
RESERVED - E121Jl~-34
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.275Mar 15/91
Use or dkclosure of information on this page is subject to the restrictions on the Mle page of thts document.
Spare Navigation Computer
IOB& ~ Connector Pin gonnects To
(B) RESERVED E121J1A:;: [;;]:::fi+------------ DNUJ1-26 APPX
(B) RESERVED 1“- ------------ DNUJI-27 IIRESERVED -37RESERYED -38RESERVED -39RESERVED -40RESERVED -41RESERVED -42
(B) ARINC 429 RCVR - (H) +-43 (22)--3-* -------------- FIGURE G-6(B) NAV SECONDARY (L) ----- -------------- FIGURE G-6(B) ARINC 429 XMTR - [~] ::: [:;].~Y*---------------
+
FIGURE G-6(B) GEN BUS SEC -46 (22)-- --------------- FIGURE G-6
SHIELD GND------(1) HIGH/LOhP SPEED BUS-LTS #1 -47 (22)-------------------- AS REQUIRED(1) HIGH/LOW SPEED BUS-LTS #2 -48 (22)-------------------- AS REQUIRED(I) HIGH/LOW SPEED BUS-LTS #3 -49 (22)----------T--------- AS REQUIRED(B) ARINC 429 XMTR - [~] -50 (22)-------~- -(B) GEN BUS PRI \\~ T-T--- [;:;[~:::-51 (22)---------- --:-+---
SHIELD GND------------Y“+ )DMUJ1-28 APPX
L ----- DMUJ1-29 D
(B) RS422 XMTR - (H) -52 (22)+ ‘--------------
1
123J1-H,
II121JlA-52,C121JIA-52
(B) DAT;AOADER (L} -53 (2@.!.-
Y
-------------- 123J1-6,121J1A-53,
SHIELD GND------ C121J1A-53SPARE
(B) RS422 RCVR - (H) :% (22)-l~i”$--”----------- E120J1-M(B) ~;~R~DATA) (L) :;; (22)--O- -------------- E120J1-N
(B) RS422 RCVR - (H) -58 ------NC(B) (L) -59 ------NC
RESERVED -60RESERVED -61
[~] RS422 XMTR - (H) -62 ------NC(L) -63 ------NC
RESERVED -64(B) RS422 XMTR - (H)
t-65 (22)-~j- --------------- E120J1-S
(B) CDU (DATA) (L) -66 (22)-- - --------------- E120J1-TSHIELD GND------Y
RESERVED E121JlA-67
Interconnect InformationTable 501 (cent) 22-14-00
Page 598;276Mar 15/91
Use or disclosure of information on this page is subject to the restrictions on the title page of this document.
Spare Navigation Computer
IOB_P_
(B)(B)(o)(B)(B)(B)(B)(B)(B)(o)(B)(B)(B)(B)
(B)
(B)(B)
(B)
(B)(B)(B)
(1)(B)(B)
Function Connector Pin
RESERVED E121J1B-1RESERVED -2SPARE -3RESERVED -4RESERVED -5SPARERS422 RCVR - (H)CDU (CNTL) (L)TAG SYNCRS232 RCVR (c)RETURN (C)RS232 XMTR (c)RS232 RCVR (A)RETURN [A)RS232 XMTR (A)CDU SYNCRS232 RCVR (B)RETURN (B)RS232 XMTR (B)RS422 XMTR - (H)
DATA LOADER (CLK) (L)
-6i-7 (22)------~- -----------
-8 (22)------’~- ------------9 (22)----------------------lo ------NC-11 ------NC-12 ------NC-13 ------NC-14 ------NC-15 ------NC-16 (22)---------------------17 ------NC-18 ------NC
~;; i;;i~i~~-f--------------
il1-21 (22)J-L----------------
1’SHIELD GND------J
ARINC 429 RCVR - (H)i
-22 (22)---fi- -------------DME SECONDARY (L) -23 (22)---U- -------------RESERVED -24RESERVED -25RESERVED -26RESERVED -27 tSYS ASCB SEC BUS (H)
I
-ii (22)---:- -------------RESERVED -29RESERVED -30 IISYS ASCB SEC BUS [~] -31 (22)---~- -------------RS422 XMTR - -32 (22)-1~:----------------CDU (CNTL) (L) -33 (22)-Y---- -------------
SHIELD GND------TAG SYNC -34 (22)---- ---------------RS422 XMTR - (H)
#-35 (22)-5- ---------------
CDU (CLK) (L) E121J1B-36 (22)~~- ---------------SHIELD GND------
~onnects To
E120J1-PE120J1-RFIGURE G-7
FIGURE G-7
123J1-K,121J1B-20,C121J1B-20123J1-J.121J1B-21,C121J1B-21
FIGURE G-6FIGURE G-6
FIGURE G-5
FIGURE G-5E120J1-UE120J1-V
FIGURE G-7E120J1-WE120J1-X
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.277Mar 15/91
Use or disclosure of information on this page is subject to the restrictions on the title page of this document.
Spare Navigation Computer
IOB& Function Connector Pin Connects To
(0) TRUE/MAG SELECT E121J1B-37 ------NC(GND/OPEN)
(0) ONSIDE TUNING CNTL -38 (22)-------------------- FIGURE G-6(AUTOTUNE) (GND/OPEN)
(o) REMOTE TUNING CNTL -39 ------NC(GND/OPEtt)
(o) LAT WPT ALERT (GND/OPEN) -40 ------NC(o) VERTWPT ALERT (GND/OPEN) -41 ------NC(o) DEAD RECKONING (GND/OPEN) -42 ------NC(o) OFFSET ALERT (GND/OPEN) -43 ------NC(o) APPR SENSITIVITY (GND/OPEN) -44 ------NC(0) INDEP OP (GND/OPEN) -45 ------NC(o) CDU MSG (GND/OPEN) -46 ------NC(o) DGRD ACCURACY (GNi)/OPEN) -47 ------NC(1) CDU SYNC -48 (22)-------------------- FIGURE G-7(0) NAV COMP VALID (GND/OPEN) -49 (22)-------------------- 134J1A-87,
C134J1A-87SPARE -50SPARE -51RESERVED -52
(o) VERTICAL TRACK AURAL -53 ------NCALERT (GND/OPEN)
(o) CROSS-SIDE TUNING CONTROL -54 (22)-------------------- FIGURE G-6(AUTOTUNE) (GND/OPEN)RESERVED -55RESERVED -56
(B) ARINC 429 RCVR - (H) ’57 (22)-i~--t-------------- FIGURE G-8
(El) LTS #3 (L) -58 (22)--G----------------- FIGuRE G-8(I) LTS #1 NUMBER BIT #1 -59 (22)-------------------- FIGURE G-7(I) LTS #1 NUMBER BIT #2 -60 (22)-------------------- FIGURE G-7(I) LTS #2 NUMBER BIT #1 -61 (22)-------------------- FIGURE G-7(I) LTS #2 NUMBER BIT #2 -62 (22)-------------------- FIGURE G-7(I) LTS #3 NUMBER.BIT #l -63 (22)-------------------- FIGURE G-7(1) LTS #3 NUMBER BIT #2 -64 (22)-------------------- FIGURE G-7(1) SDI #3 -65 (22)-------------------- FIGURE G-7(I) CROSSFILL ENABLE * -66 ------NC(1) VERSION BASCB * -67 (22)-------------------- SIGNAL GND
RESERVED -68RESERVED -69RESERVED -70
(1) OPERATIONAL MODE IDO -71 (22)-------------------- SIGNAL GND(1) wow * -72 (22)-------------------- A/C WOW SWITCH(I) PERFCOMP INSTALLED *E121J1B-73 (22)-------------------- SIGNALGND
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.278Apt-15/93
Use ordisclosure of irtformationon this page is subject to the restrictions onthe title page of this document.
Spare Navigation Computer
IOB_P_ Function Connector Pin Connects To
(I) LTS#l CONFIGURATION E121J1B-74 (22)-------------------- FIGURE G-7(I) LTS#l CONFIGURATION -75 (22)-------------------- FIGURE G-7(I) LTS#l CONFIGURATION -76 (22)-------------------- FIGURE G-7(I) LTS#2 CONFIGURATION -77 (22)-------------------- FIGURE G-7(1) LTS #2 CONFIGURATION -78 (22)-------------------- FIGURE G-7(I) LTS #2 CONFIGURATION :~; (22)-------------------- FIGURE G-7
RESERVEDRESERVED -81RESERVED -82
(I) DL CONNECTED * -83 (22)-------------------- 123J1-F
(I) RADIO CONFIG ID O -84 (22)-------------------- SIGNAL GND(I) RADIO CONFIG ID 1 -85 ------NC(I) RADIO CONFIG ID 2 -86 ------NC(I) MAINT TEST ENABLE * -87 (22)-------------------- 121J1B-87 ‘(I) ILS*/MLS SELECT -88 (22)-------------------- FIGURE G-6(I) LTS #3 CONFIGURATION -89 (22)-------------------- FIGURE G-7(I) LTS #3 CONFIGURATION -90 (22)-------------------- FIGURE G-7(I) LTS #3 CONFIGURATION -91 (22)-------------------- FIGURE G-7\~~ OPERATIONAL MODE ID 1 ~;g (22)-------------------- FIGURE G-7
INITIATEDXMIT * ------NC(I) INITIATED REC * -94 ------NC(I) DME SCAN TYPE * ~:~ (22)-------------------- SIGNAL GND(I) RADIO BUS TYPE (OPEN/GND) ------NC(I) SINGLE ASCB * -97 ------NC(I) SDI #l -98 (22)-------------------- FIGURE G-7(I) SDI #2 -99 (22)-------------------- FIGURE G-7(I) CDU VALID * -100 (22)------------------- E120J1-i(I) TRUE REF SELECTED * -101 ------NC(I) METRIC OPTION * -102 ------NC(I) OVERSPEED PROTECTION DIS * -103 ------NC(I) RS422 OFFSIDE VOR CONNECT * -104 ------NC(I) NAV/DME MANUAL * TUNE SEC -105 (22)------------------- FIGURE G-6(I) NAV/DME MANUAL * E121J1B-106 (22)------------------- FIGURE G-6
TUNE PRI
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.279Mar 15/91
Use or disclosure of information on this page IS subject to the restrictions on the title page of this document.
Performance Computer Flo.1
IOB& Function Connector Pin Connects To
(B) RS422 XMTR - ~~]i
122J1A-97 (22)-O--- -------------- FIGURE G-4(B) CDU (CLK) -98 (22)~Y~-- -------------- FIGURE G-4
SHIELD GND-----(B) RS422 XMTR - (H) -99 (22)--fi--
t-------------- FIGURE G-4
(B) CDU (CNTL) (L) -100 (22)-- - -------------- FIGURE G-4~SHIELD GND------
(B) RS422 XMTR - (H)t
-101 (Zz)-pr- -------------- FIGUREG-4(B) CDU (DATA) (L) -102 (22)-y- -------------- FIGURE G-4
SHIELD GND------(B) RS422 RCVR - (H) -103 (22)-n-
+-------------- FIGURE G-4
(B) CDU (DATA) (L) -104 (22)-lJ- -------------- FIGURE G-4(B) RS422 RCVR - (H)
$-105 (22)--- -------------- FIGURE G-4
(B) CDU (CNTL) (L) 122J1A-106 (22)-~~- -------------- FIGURE G-4
(0) PERF COMP INSTALLED 122J1B-106 (22)------------------- FIGURE G-4
Interconnect InformationTable 501 (cent) 22-14-00
Page 598~280Mar 15/91
Use or disclosure of information on this page is subject to the restrictions on the title page of this document.
Performance Computer No. 2
IOB_P_ Function - Connector Pin Connects To
C122J1A-97 (22)--~--98 (22)-J-’
SHIELD GND------f
+ ------ ------ --:+ -- - . -. -. - - --- .
(B)(B)
RS422XMTR - [~]CDU (CLK)
FIGURE G-4FIGURE G-4
(B)(B)
RS422 XMTR - (H)CDU (CNTL) (L)
-99-(22)--5-1oo (22)-9
ELI)GND-------101 (22)-7-102 (22)-\
ELD GND------
FIGURE G-4FIGURE G-4
SHI
SliI
+ ------- --..-.--i_____
(B)(B)
RS422 XPITR- (H)CDU (DATA) (L)
FIGURE G-4FIGURE G-4
(B)(B)(B)(B)
RS422 RCVR - [1+]CDU (DATA)RS422 RCVR - (H)CDU (CNTL) (L)
1-103 (22)-~- -------.-------104 (22)-g- ----------..--
X-105 (22)-~7- --------------
C122JIA-106 (22)-U- --------------
FIGURE G-4FIGURE G-4FIGURE G-4FIGURE G-4
(o) PERF COMP INSTALLED C122J1B-106 (22)------------------- FIGURE G-4
Interconnect InformationTable 501 (cent)
22-14-00Page 598.281
F4ar15/91lJseordkclosure of information on this page is subject to the restrictions on the title page of this document,
Data Loader
10BP Function Connector Pin Connects To
——
(0) LOADER CONNECTED AUX 123J1-F (22)--------------------- E121J1B-83
(B) RS422 RCVR - (L)
1
-G (22)--7=’T---------------
II
(B) NAV CONIP(DATA) (H) -H (22)--~=~- --------------
I
(B) RS422 RCVR - (L)
I
-J (22)--;=1- --------------
(B) NAV COMP (CLK) (Ii);:~
-K (22)---=-- --------------
(B) RS422 XMTR - (L) i-s (22)---i=i---------------
{i
I(B) NAV COMP (DATA) (H) 123J1-T (22)----- --------------
SHIELD GND-------
121J1A-53,C121J1A-53,E121J1A-53121J1A-52,C121J1A-52,E121J1A-52121JIB-21,C121JIB-21,E121J1B-21121J1B-20,C121J1B-20,E121J1B-20121J1A-29,C121J1A-29,E121JIA-29121JIA-28,E121t.?lA-28
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.282Feb 1/88
Use or disclosure of information on this page is subject 10 the restrictions on the title page of this document.
Fault Warning Computer No. 1
IOBP Function Connector Pin——
(1) SPARE CDU VALID 134J1A-77 (22)-------”------------
(I) SPARE FMS ACTIVE 2 -78 (22)--------------------(I) SPARE FMS ACTIVE 1 -79 (22)--------------------(I) SPARE NZ VALID -87 (22)--------------------
(I) SPARE FMS INSTALLED 134J1A-90 (22)--------------------
IOBP
(I)
(I)(I)(I)
(I)
Connects To
E120J1-i,E121J18-1OO,C134J1A-77FIGURE G.2FIGURE G.2E121J1B-49,C134J1A-87SIGNAL GND
Fault Warning Computer No. 2
Function Connector Pin Connects To
SPARE CDU VALID C134J1A-77 (22)-------------------- E120J1-i,E121J1B-1OO,134J1A-77
SPARE FMS ACTIVE 2 -78 (22)-------------------- FIGURE G.2SPARE FMS ACTIVE 1 -79 (22)-------------------- FIGURE G.2SPARE NZ VALID -87 (22)-------------------- E121J1B-49,
134J1A-87SPARE FMS INSTALLED C134J1A-90 (22)-------------------- SIGNALGND
Interconnect InformationTable 501 (cent) 22-14-00
Page‘598;283Feb 1/88
Use or disclosure of information on this page is subject to the restrictions on the title page of this document.
r —— ——SP=E ~U
7
CDU VALID i
III
I 79 SPARE FMS ACTIVE 1
II
I78 SPARE FMS ACTIVE 2
-1
IL ————
90SPAREFMS INSTLD Ir
——S=E=
-
E121J1B = b ——— — J
I C134J1A ~~& — —
I
-1i7sp/IRECDLJVALIDI
I NZ VALID 49 . 87 SPARE NZ VALID
I
( ) 79 SPARE FMS ACTIVE 1 I
I- 1D 78 SPARE FMS ACTIVE 2 I
I II
— 90 SPARE FMS INSTLD
I I I&J
= - ——— —J
L ——— .
23 CONFIGURATION
1,3 CONFIGURATIONAD-143CUJ-R1
FMS SELECTORSWITCH
.
r
?’31,2
=L
Is
FWC Interfaceto Spare FMSFigure G-2
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Use or disclosure of information on this page is subject to the restrictions on the title page of thts document.
IIIIIIIIIIIIIL ———
GRS-422 DATATO LOADER LO
53
1E“121J1A
RS422 DATATO LOADER HIH 52
7E121J1B
RS-422 CLK TO LOADER LOJ
SPARE NZ
KRS-422 CLK TO LOADER HI
20
E121J1Ar
RS~22 DATA TO FMs Los a 29
RS422 DATA TO FMS HIT 28
L
— — ——
‘1II
IIIIIIIIIII
–JAD-1633e
Data Loader Interfaceto Spare FMSFigure G-3
Interconnect InformationTable 501 (cent) 22-14-00
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Use or disclosure of information on this page is subject to the restrictions on the title page of this document.
Noms
I sWIWHESS+ICWNFOS w 1.2 CU#iGURA_
2 s8mcnEs osm’rso w @ AREACTIVATEDWWEN3SLECTm mm ~W 2 3 POSll~ @AaE FIEPI.ACSS FMS 1)
3 SWIT_S =KXEED SY 2 -E AC71VATSD _ SSLE_~ SW=H -D$?W1.3PC61T10N@WlTE ~FMS2’1
PMS Interfaceto Spare FMSFigure G-4
—1
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f-———
7T
SPARE NZ
I E121JIA TASCB B+ ,-,
ASCBB - ! !-I +
I
ASCB PRIMARY+ 10II
w
II
IIIiiIi
t4} T
I ASCB PRIMARY - 11 I v * 1 ASCB A + ,-,Q I
Iu + ASCB A - II
●, i1
I II II II I
E121J1B T
I ASCB SECONDARY+ 28 ‘ ‘F;
I
IIII 4II
IIIII
ASCB SECONDARY- 31II
I
1- ——— J
NOTES1.SWITCHES SHOWN FOR FMS 1,2 CONFIGURATION.2.ALL SWITCHES ACTIVATED WHEN SELECTOR PLACEDIN 2,3POSITION (SPARE REPLACES FMS 1). AD-14303-R1
ASCB Interface to Spare FMSFigure G-5
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Use or disclosure of information on this page is subject to the restrictions on the title page of this document.
———-
T“”” ,2,,,0
lbG SVNC Ml 9
I Cou S“* GW1 16
T*G S“wc IN 34 1
I cm S“NC ,94 *
( ,9 i [,1s .CONFIGU.A180NO! SCIWTE5
LT5 ECONFIG”RA140N01scnE1E5
LIS CCONFIGURATIONDISCFWTES
m 1 , 1 T?4 T,, I 1>6 I61
64 I
n 1
18
n I
m
64
m
m
91
LISN” ,I CoNPlc.”nAf#r?+
III
LIS NO 2COWIGURA11ON
I I--.33
;
w-... IGURA1K?+4I
3-o--
1————.
I TM SYNC 0“1
I CC4J Swc OU1
ITAOSYNCIN
CC4J SVNC IN
III
LISNO ICOWIGURA11ON I
NOTES
I SWITCHES DENOTED BY @ ARE AC1tVAIEO WHEN 5ELECTWSWOTCM PLACED bN 2 3 pOs, roON ISPAnf nfPMccs ws 1)
2 SWIICHES OENOTEO 0“ @ ARE AC IIUAIED WHEN SELECTOR
SWIICH PL.CCO IN 1 3 POSIIION (SPARE REPLACES FMS 21
@—
( ~75
76
[ ;
61
82
LIS NO 2C@4FlGURA1KlU 17
78
19
[ ~
w
64
LIS NO 3CONIIGLIRA11ON -
w
91
sol No I m
sol ?40 2 m .
=l=E=b-3-
I
n 1 I I I I
w 174 1 I I15 1
?6 1
et A
62
17L
70 }
II 11SNOI
CG+4F,0UFI.,KW4
I 1I LISNO Z
I COW lGUFIAT 13N
I
LIS DCOWW3W7ATIOND, SCRETES
LTS ECm61GURAT10NOI$CRETES
Lrs FCONFIGURATIONDtSCRE TES
——
—
————i
II ‘
19
63
I
64LISNO 3CONFIGUIIAW3N m—
I 11=1IL ——— —
Spare FMS Radio SwitchingFigure G-6
Interconnect Information
,. !*IS
Table 501 (cent) 22-14-00Page 598.289/598.290
Mar 15/91Use or disclosure 01 mlormahon on Ihm page IS subject 10 the reslncttons on the title page of Ihlg document
F=~––- ,2tJ$A
YNo. 1RADIOS
i ,L51MLS c’I LWE. PR, cI NWPR,
(:
I NAV-SEC(:
I
[
GEN BUS-SEC ;
I
GEN BuS PI+, ;
16
11 1
IS
89T
32 1
% ,I
,T
43 1
44,
45 146
%
5,
\ I I
II I1111
.11111 I
II OMcSEc
Ic’ON.51~AU101UNI
CSOSS.$ILW AUTOTUSI
I
MANUAL TUNE . SEC
*,wdAt; ufi* >fii
121310
S2 I I I I?3 Iw% Imw} —. L– _ -
{
DD_- D
D
L————. xl 1111111
rw=.~ — — - 1111111E121JIA
( ‘. -!-JM 10lLS/MLS
L 11@
(n w @
Ou&ml
L $9-b>
(M u f@NAV-?8,
L u ‘-b 1
(H 43+@
NAV-SECL 44 !
IIIIII1IIIIIIII
I 1NOIES
0 SWIICIIES 5H0wN FOR FWS I 2 CONFIGuRATION
2 SWITCHES DENOIEO 0“ @ ARE AC TtV41E0 WHEN SELECTOR
PLACEO IN 23 POSITION (SPARE REPLUES FMS ,,
3 SWIICHES OEt+OIED B, @ ARE .CT8VATE0 WHEN 5ELEC1OR
PLACEO IN I 3 PCISITION (SPARE REFIACES FMS 21
J@)__
.EN.s.c[H145~
—OWSlOf AU1OTUNE I w I I I I I 1 I
a“””s’””’”’-l”~
,
—
3.
—J II I I
1 1 I—1
I.
;(
>DME.SEC : :
ON.51WAU1OTUNEm
I CFIOSS.SIMAU1OT”NE
MANUAL TUNE . sEC ,~
~
1 MANuALnJNE-ml ,00 ,. I
FMS Discrete SwitchingFigure G-7
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22-14-00Page 598.291/598.292
Mar 15/91Use 01 disclosure of Information on thm page IS subpscl 10 the restncllons on the tllle page of thm document.
rN=O~ — 1
1, 121J1A
{ “- ‘~,
H 26
I
LTSNO,1L 27
SENSOR A
1
{ ;— – –- “?
H 23
ILTSNO.2 L 24 SENSOR B
I
121J1B
I { ]
M 57LTSNO.3 L ~ T SENSORC
L .— - -
rSPARE NZ 1,12,,1A—.-
1
( ‘+<
H 26
I
aLTSNO.1
L 27
I
:@
( ~
H 23
I+
LTSNO.2L 24
I
+~E121JlB
{ :
H 57
I+
LTS NO. 3L 58
L ———
rN=O= -1
I
C121J1A
I
LTSNO. 1{ ‘~ –
H 26L 27
SENSOR O
I
{ J
9H 23
I
LTS NO. 2 1 24 . SENSOR E
IC121J1B
{ J
H 57 A
I
11S NO. 3 ~ * SENSOR F
L ——— J NOTES:
1. SWITCHES DENOTED BY@ AREACTIVATEDWHEN SELECTOR SWITCHPLACED IN 1,3 POSITION (SPARE REPLACES FMS 2). 015s=4?1
Long Term Sensor SwitchingFigure G-8
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useordisclosureofInformationonthispegeissubjecttotherestricticmsOnthetitlepageofthtsdocument,
4
NZ NO. 1 NC 28 VDC121J1A
+28 VDC PWR 3
f
I I I
CDU NO. 1 120J1#c
+28 VDC PWR B
L
28 VDC
NZ NO. 2 C121J1ANC 28 VDC
+28 VDC PWR 3
tI I
I
CDU NO. 2 C120J1A/C 28 VDC
+28 VDC PWR B
L
NOTES:
1. SWITCHES DENOTED BY @ ARE ACTIVATED WHEN SELECTOR SWITCHPLACED IN 2, 3 POSITION (SPARE REPLACES FMS 1).
2. SWITCHES DENOTED BY @ ARE ACTIVATED WHEN SELECTOR SWITCHPLACED IN 1, 3 POSITION (SPARE REPLACES FMS 2). AD-16338
Input Power SwitchingFigure G-9
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Use or disclosure of information on this page is subject to the restrictions on the Mle page of this document.
APPENDIX HP-800 WEATHERRADAR SYSTEM INSTALLATIONI
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APPENDIX HP-800 WEATHER RADAR SYSTEM INSTALLATION
1.0 P-800 WEATHER RADAR SYSTEM INSTALLATION
1.1 EQuipment List
Outline &Connector Installation Mat ing Mount i ngDesignator Description Qty Part Number Owg. No. Connector Hardware
59J1 WR-800 1 M1585350-34 3715751[Jl) KPSE06F22-55S Tray SPN -
59J2 Weather \;:;:; l- J2] KPSE06F22-55SW M1585356Radar R/T
Manual,Pub. t!o.188023137)
60J1 WA-800 WXR 1 M1585354 1713860 KPSE06F20-395 Flange MountAntenna Peal.
---- FP-900 WXR 1 M1585377 3714499 ---- ----Flat PlateRadiator
61J1, 61J2 WC-81O WXR 2 7006921-311/-312 7006922 (Jl) KJ6F14A-18SN Dzus MountC61J1, C61J2 Control ler (J2] KJ6F14A-18SA
1.2 Eauipment Power and kfeiqht
UnitNo. Description Power Weight
59 WR-800 Weather 168 Watts/28 V dc 21.0 lbsRadar R/T 40 VA/115 V ac
60 WA-800 WXR ---- 15.25lbs withF1atP1 ate
61 WC-81O WXR 15 Watts/28 V dc 1.9 lbsController Panel Lighting - 4.6 W/5 V dc or
28 V dc
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1IIIIIIJ1IIIIII
I
I
I
J
1IIIIII1
WX Source Switching Schematic Ao-m❑,
Figure H-1
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1.3 Mechanical Installation Information
1.3.1 Weather Radar R/T (WXR R/T) Installation - This unit shall have anenvelope size of 1/2 ATR and shall be mounted on a mounting tray HoneywellP/N M1585356. If the WXR R/T is subject to vibration greater thanspecified by 00-160A Category O, it shall be mounted on vibrationisolators.
There are no external cooling requirements for the weather radar R/T; a 28V dc fan is mounted on the rear of the unit to ensure adequate heatdissipation. In addition, a minimum one inch clearance shall be providedbetween the top, back, sides and front of the unit and any adjacentequipment for thermal isolation.
For optimum service life the R/T should be installed in a location whereambient air temperature is between -20°C and +40”C. However, it should beas close as possible to the WXR antenna.
The weather radar R/T shall meet the environmental requirements as listedin Appendix E of this installation bulletin.
NOTE : For further information on the Primus 800 Coloradar System,please reference: Primus 800, System Description andInstallation Manual, Pub. No. IB8023137.
1.3.2 Weather Radar Antenna Installation - The antenna pedestal is designed forcantilever mounting on the aircraft bulkhead and provides line-of-sightstabilization. The antenna pedestal accommodates an 18 in. flat platephase array radiator.
There are no external cooling requirements for the antenna pedestal. Theantenna pedestal shall meet the environmental requirements as listed inAppendix E of this installation bulletin.
Maximum Permissible Exposure Level (MPEL) - Radiation effects ofweather radar can be hazardous to life. Personnel should remainat a distance greater than 8 feet from the radiating Antenna ofthe radar system in order to be outside the envelope in whichradiation exposure levels equal or exceed 10 milliwatts per squarecentimeter (the limit recommended in FAA Advisory Circular No.20-68A, dated April 11, 1975). The distance of8 feet, whichdefines the MPEL boundary is calculated on the basis of radiatordiameter, rated peak-power output, and duty cycle for the radarsystem. These are far-field distance calculations, based on therecommendations outlined in AC No. 20-68A. The near-field tofar-field intersection distances are less than the safe distancelisted here.
Interconnect InformationTable 501 (cent) 22-14-00
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1.3.3 Weather Radar Controller Panel - The WXR controller panels maximumallowable envelope shall be:
Width Heiaht Depth
5.75 in. 1.875 in. 6.5 in.
There are no external cooling requirements for the WXR controller panel.The WXR controller shall meet the environmental requirements as listed inAppendix E of this installation bulletin.
1.4 Power Distribution
MmmvclcMN N_~
nm“””
L-I==F–=== ‘J’I IsWins 0 ‘a VOcwm
C-5 WC
I 5wl-rsH ED3E~0WCWL
+ j
/’/’.
/+—1—
—
Interconnect InformationTable 501 (cent) 22-14-00
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Weather Radar R/l
(I)
(I)(P)(P)(P)(P)(P)(P)(B)(B)
(o)(o)(o)
(P)(P)(o)(o)
(o)(o)(o)(o)(I)(I)(1)
(o)(o)(I)(I)(I)(I)(I)(I)
Function Connector Pin
115 V400HZ REF (H) 59J1-A (zz)-----* -------------
115 V 400 HZ REF (L)28V DC POWER28V DC POWER28V DC POWER28 V DC POWER RETURN28 V DC POWER RETURN28 V DC POWER RETURNATT (ARINC 429) (L)~;~RIARINC 429) (H)
SPAREELEV MOTOR (H)ELEV MOTOR (L)
+-B (22)----- ---------------c (NOTE 3)-----------------D (NOTE 3)-----------------E (NOTE 3)-----------------F (NOTE 3)-----------------G (NOTE 3)-----------------H (NOTE 3)-----------------J (22)------n
8- --- -- . -- -
-cc (22)-----g- --------.--K-L
$-M (22)-------- -----------GG (22)------- -----------
CONTROL PANEL 6ND $ (22):-------------------SPARE28 V DC SWITCHED -R (22)--------------------ANTENNA GND -s (22)--------------------115VAC; 400HZ (L)
T-T (22)-------- -----------
ANT PWR (H) -v-u (22)-------- -----------SPARESPAREELEV RESOLVER S1 :! (22)------+- --------ELEV RESOLVER S3
hi-Y (22)------- - --------
ELEV RESOLVER S2 -z (22)------- - --------ELEV RESOLVER S4 -r (22)-------J!- --------SHIELD GND -----------YAZ CENTER RESOLVER (H) :: (22)--------------------~;A~~NTER RESOLVER (L) -q (22)--------------------
SPARE ::SPAREAZ DRIVE (P) BAZDRIVE (P) ASHIELD GND~:~~~;;)fl;::; ~j]
RT ON/OFF (GND/OPEN)SERIAL CONTROL (H)SERIAL CONTROL (L) 59J1
-e-f (22)-------BB (22)------DD (22)------g (22):------p (22)-------h (22)-------i (22)-------y (22)------
------.---
-------------------------
----
----------
Connects To
A/C 115 VAC;400 HZ PWRA/C PWR GND28 V DC, A/C PWR28 V DC, A/CPWR28 V DC, A/CPWRA/C PWR GNDA/C PWR GNDA/C PWR GND
1IRS HI SPEEDOUTPUT
60J1-X60J1-W61J1-C
60J1-K60J1-L60J1-M60J1-N
60J1-P60J1-R60J1-T60J1-U
60J1-D60J1-E
60J1-H60J1-A
60J1-Z60J1-Y61J1-N,C61J1-N61J1-A61J1-B
Interconnect InformationTable 501 (cent) 22-14-00
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Weather Radar R/T
IOB_P_ Function Connector Pin Connects To
SPARE 59J1-j(P) +28 V DC -k (20)-------------------- 60J1-n
SPARE -mSPARE -nSPARESPARE ::SPARE -uSPARE -vSPARE -wSPARE -xSPARE -zSPARE -AASPARE -EESPARE -FFSPARE 59J1-HH
Interconnect InformationTable 501 (cent) 22-14-00
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IOBP
(o)
(o)
(I)(o)
(o)
(I)(o)
(o)(o)
(1)(I)(I)(I)(1)
(o)(o)
Weather Radar R/T
Function Connector Pin Connects To
$WX SERIAL DATA#l (H) 59J2-A (22)-----fi ----------- 65J1A-51,E65J1A-51
-T (22)----”-7
----------- 65J1A-52,E65J1A-52
(L)
SHIELD GNDWX SERIAL DATA#2 (H)
SHIELD GNDFAULT (NO. 1
SPARESPARESPARESPARESPARESPARESPAREWX VIDEO #2ldXVIDEO #2
SPARE
(L)
(GND/OPEN)
(H)(L)
CONTROL PANEL GNDSIGNAL GND (NO. 1)SIGNAL GND (NO. 2)SERIAL CONTROL (H)~E&L CONTROL (L)
SPARESPARESPARESPARESPARESPARESPARESPARESPAREWX VIDEO NO. 1 (H)
-h (22)-----J-v (22)-----R
i
-----------
-B (22)-----!!- -----------
-g (22)-----1-c (22)--------------------
-D-E-F-G
:!-K
*-L (22)------------fi- -----M (22)-----------+ ----
1-------
-N-P (22)---------------------R (22)---------------------s (22)----------------- --
$-u (22)--------------A- ---n (22)--------------U ---w-x-Y-z-a-b-c-d-e
C65J1A-1,E65J1A-1C65J1A-2,E65J1A-2
PAGE H-2PAGE H-14
PAGE H-2PAGE H-2TIE TO 59J2-g
C61J-CSIGNAL GNDSIGNAL GNDC61J1-AC61J1-B
-f-i (22)--fi-
$------------- PAGE H-2
WX VIDEO NO. 1 ~Lj 59J2-j (22)--V- ------------- PAGEH-2
Interconnect InformationTable 501 (cent) 22-14-00
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Weather Radar R/7
10B-P_ Function Connector Pin Connects To
SPARE 59J2-k(0) TGT ALERT NO. 1 (GNl)/OPEN) -m (22) -------------------- PAGE H-2 REF
}{O) FAULT (NO. 2) {GND/OPEN) -p (22)-------------------- PAGE H-2 PAGE
H-14SPARE -qSPARE -rSPARE -sSPARE -tSPARE -uSPARE -vSPARE “wSPARE -xSPARE
(0) TGT ALERT (NO. 2)(GND/OPEN)SPARESPARESPARESPARESPARESPARESPARE
-Y-Z (22)-------------------- PAGE H-2
REF PAGE H-14-AA-66-cc-DD-EE-GG
59J2-Hl-l
NOTE: FOR FURTHER INFORMATION ON THE WEATHER RAOAR SYSTEM, PLEASE REF:P-800 SDI, PUB. NO. IB8023137.
Interconnect InformationTable 501 (cent) 22-14-00
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Weather Radar Antenna
IOB~
(I)
(o)
(o)(o)(I)(P)(I)(1)(I)(o)
(o)
(I)
(o)
(I)
(I)
Function Connector Pin Connects To
AZ DRIVE A (P) 60J1:; (22)-------------------- 59J1-gBSPARESPARE -cAZ CENTER RESOLVER R1
i-D (22)---------- --------- 59J1-b-E (22)---------- --------- 59J1-q
115 VAC 400 HZ REF ~;) -F ------NC115VAC 400HZ REF (L) -G ------NCAZDRIVE B (P) -H (22)-------------------- 59J1-f28 V DC SWITCHED -K (22)-------------------- 59J1-R
ELEVATION RESOLVER S1S3
SPAREELEVATION RESOLVER S2
S4SPAREELEVATION MOTOR (L)
(H)ELEVATION TACH (H)
(L)SPARESPARESPARESPARESPARESPARESHIELD GROUNDSPARESPARESPARESPARESPARE28 V DCSPARESPARE
ANTENNA GROUND -L (22)---------- --------- 59J1-S
i
115 VAC;400 HZ ANT PWR (L)-M (22)---------- --------- 59J1-T115 VAC;400 HZ ANT PWR (H)j~ ~~~]-----ti--- --------- 59J1-U
------ - --------- 59J1-X~~ (22)-----11------------- 59J1-Y
!$-T (22)-----ii--- --------- 59J1-Z-U (22)---- ---- --------- 59J1-r-v Y
1-w (22)----- -------------- 59J1-GG
h-x (22j----- -------------- 59J1-M-Y (22)----- --- --------- 59J1-p-z (22)---:4i--- --------- 59J1-g
:;-c-d-e-f-g (22)------h.
~;-k-m
SPARE 6oJ1-r
-n (20)---------------- 59J1-k-P-cl
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Weather Radar Controller No. 1
106~ Function Connector Pin Connects To
(o) SERIAL CONTROL (H)*
61J1-A (22)-----%- ----------- 59J1-i(0) SERIAL CONTROL (L) -B (22)-----V- ---------- 59J1-y(I) SHIELDGND -M (22)------(P) CONTROL PANEL GND -c (22)-------------------- 59J1-N(P) 28V DC POWER -D (NOTE 3)---------------- A/C PWR(P) ~~A[EDC PWR RTN -E (NOTE 3)---------------- A/C PWRRTN
-F(P) 28V PANEL LIGHTING ------NC(P) 5 V PANEL LIGHTING :; (22)-------------------- A/C LIGHTING(P) LIGHTING COMMON -J (22)-------------------- A/C LIGHTING GND(P) PUSHBUTTON 28V LIGHTING -K (22)-------------------- A/C LIGHTING
RESERVED -L(o) R/T ON/OFF (GND/OPEN) -N (22)-------------------- C61J1-N,59Jl-h(I) FORCED STANDBY* -P (22)-------------------- A/CWIRING,
REF PAGE H-15RESERVEDSPARE :!SPARE -TSPARE 61J1-U
Interconnect InformationTable 501 (cent) 22-14-00
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Weather Radar Controller No. 1
IOB~ Function Connector Pin Connects To
(0) RANGEA 61J2-A (22) -------------------- PAGE H-2(0) RANGE B -B (22) -------------------- PAGE ti-2(0) RANGE C
1
-C (22)-------------------- PAGE H-2 pAGE(0) RANGE I) -D (22) -------------------- pAGEti-2 I-I-16(0) FPLN SELECTED (GND/OPEN) -E (22)--------- ---------- PAGE H-2(1) WX INT (H) -F (22)-----n-
$
---------- 131J1-2(0) IdXINT (W) -G (22) ---------- ---------- 131 JI-15(1) WXINT (L) -H (22)-----U-- ---------- 131J1-3(1] PROGRAM RANGE A ~[ [~$----!--------------- A/C WIRING(I) PROGRAM RANGE B -------------------- A/CWIRING(I) PROGRAM RANGE C
I
-L (22)-------------------- A/C WIRING PAGE(I) PROGRAM RANGE D -M (22)-------------------- A/C WIRING H-15(1) PROGRAM RANGE COMM -N (22)-------------------- A/CWIRING
RESERVED -P(0) ID PROG COM -R ------NC(I) $IA;~OG ------NC
:;SPARE 61J2-U
~: FOR FURTHER INFORMATION ON THE WEATHER RADAR SYSTEM, PLEASE REF:P-800 SDI, PUB. NO. IB8023137.
Interconnect InformationTable 501 (cent) 22-14-00
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Useof disclosure of information on this page issubject to the restrictions onthe title page ofthisdr!cument.
Weather Radar Controller No. 2
IOB~ Function Connector Pin Connects To
(0) SERIAL CONTROL (H)$
C61JI-A (22)----fl- ------------ 59J2-U(0) SERIAL CONTROL (L) -B (22}---- - ------------ 59J2-n(1) SHIELDGNO Y-M (22)-----(P) CONTROL PANEL GND -C (22)-------------------- 59J2-P(P) 28VDC POWER -D (NOTE 3)---------------- A/C PWR
‘p) ;;A[EDC pWR RTN~; (NOTE 3)---------------- A/C PMRRTN
(P) 28V PANEL LIGHTING -G ------NC(P) 5 V PANEL LIGHTING -H (22)-------------------- A/C LIGHTING(P) LIGtlTINCICOMMON -J (22)-------------------- A/C LIGHTING Gt4D(P) PUSHBUTTON 28V LIGHTING -K (22)-------------------- A/C LIGHTING(1) RESERVED -L(0) R/T ON/OFF (GND/OPEN) -N (22)-------------------- 61J1-N,59Jl-h(1) FORCED STANDBY* -P (22)-------------------- A/C WIRING,
REF PAGE H-15RESERVED -RSPARE -sSPARESPARE c61Jl:i
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(o)(o)(o)(o)(o)
(I)(o)(1)
(1)(I)(I)(I)(o)
(o)(I)
Weather Radar Controller No. 2
Function Connector Pin
RANGE A C61J2-A (22)--------------------RANGE B -B (22) ---------------------RANGE C -c (22)--------------------RANGE D -D (22)--------------------FPLN SELECTED (GND/OPEN) -E (22)--------------------
WX INT (H)WX INT (W)WX INT (L) $-F (22)------------~- ----
-G (22)------------\~- -----H (22)------------V ----
PROGRAM RANGE A -J (22)--------------------PROGRAM RANGE B -K (22)--------------------PROGRAM RANGE C -L (22)--------------------PROGRAM RANGE D -M (22)--------------------PROGRAM RANGE COMM -N (22)--------------------RESERVED -PID PROGRAM -R (22)--------------------ID PROGRAM -s (22)--------------------SPARESPARE C61J2~~
Connects To
PAGE H-2PAGE H-2
I
PAGE H-2 PAGEPAGE H-2 H-16PAGE H-2A/C MIRINGC131J1-2C131J1-15C131J1-3
A/C WIRINGA/C WIRINGA/C WIRING
I
A/C WIRING PAGEA/CWIRING H-15
C61J2-SC61J2-R J
~: FOR FURTHER INFORMATION ON THE WEATHER RADAR SYSTEM, PLEASE REF:P-800 SDI, PUB. NO. IB8023137.
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59. Weather Radar R/T Discrete Summary
Discrete Inputs
The WX R/T does not provide any discrete inputs that are installationvariable.
Discrete Outputs
WX R/T Fault No. 1 59J2-C
Grid/Open Type A
Ground = Antenna FaultOpen = Normal Operation
Target Alert No. 1 59J2-m
Grid/Open Type A
Ground = Target AlertOpen = Normal Operation
WX R/T Fault No. 2 59J2-p
Grid/OpenType A
Ground = Antenna FaultOpen = Normal Operation
Target Alert No. 2 59J2-z
Grid/Open Type A
Ground = Target AlertOpen = Normal Operation
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61. WX Controller Discrete Summary
Discrete Inputs
Forced Standby 61/c61Jl-P
Grid/Open Type A
Ground = Forced StandbyOpen = Normal Operation
Program Range A 61/C61J2-JProgram Range B 61/C61J2-KProgram Range C 61/C61J2-LProgram Range D 61/C61J2-MProgram Range Comm 61/C61J2-N
Grid/Open Type A
Range (nmi) D c B A
0.51.02.55.0
;:5010015020030050010002000
Open Open Open GndOpen Open Gnd OpenGnd Gnd Gnd GndGnd Gnd Gnd OpenGnd Gnd Open GndGnd Gnd Open OpenGnd Open Gnd GndGnd Open Open OpenOpen Open Gnd GndGnd Open Open GndGnd Open Gnd OpenOpen Gnd Open OpenOpen Gnd Open GndOpen Gnd Gnd Open
NOTE : Program Range Pins must be grounded by using the ProgramRange Comm (61/C61J2-N). These pins must not be tied toAircraft Grid.
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ID Program Pin 61/C61J2-S
Grid/Open Type A
Short to C61J2-R for WXC #2Open = WXC #1
Discrete Outputs
Range A 61/C61J2-ARange B 61/C61J2-BRange C 61/C61J2-CRange D 61/C61J2-D
Grid/Open Type A
Provides encoded WX Range per the range select knob or per61/C61J2-J/K/L/M when FPLN is selected.
FPLN 61/C61J2-E
Grid/Open Type A
Ground = Flight Plan Mode SelectedOpen = Normal Operation
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APPENDIX IVLF/OMEGA SYSTEM INSTALLATION
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1,
APPENDIX IVLF/OMEGA SYSTEM INSTALLATION
1.0 VLF/OMEGA SYSTEM INSTALLATION
1.1 scoDe
This Appendix provides data for installationof a VLF/Omega system intothe G-IV aircraft. Both electrical and mechanical parameters areprovided. Interconnect information deals not only with the components ofthe VLF/Omega system itself, but also the wiring modifications required tointegrate it into the baseline G-IV system. Informationfor both singleand dual VLF installations is provided.
1.2 O~erational Description
The VLF/Omega system consists of the OZ-800 VLF/Omega Receiver/Processor
Unit (RPU) and one of the following:
. AT-800 H-Field, Tear Drop Antenna/Coupler Unit
. AT-801 H-Field, Brick Antenna/CouplerUnit
● AT-802 Antenna Coupler Amplifier
. AT-803 E-Field, Blade Antenna/CouplerUnit
The VLF/Omega system is approved for use under FAA TSO-C94a. It providesupdated position and velocity informationto and receives initializationdata from the two Navigation Computers (NZ-800). Communication to andfrom the VLF/Omega sensor is via ARINC 429. Each sensor contains twolow-speed ARINC 429 receivers and two high-speedArinc 429 transmitters.
The RPU is housed in a standard ARINC 1/4 ATR short box. It receives theamplified antenna signals and converts them into position information.The RPU contains the ARINC 429 interface for communication with the NavUnits. The RPU also supplies the antenna with its required *12 V dcpower.
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,!
The H-field antennas receive and amplify the magnetic field component ofthe Omega signals. The teardrop antenna is a small, lightweight loopantenna that is mounted with screws through the main body of the antenna.The brick antenna is electricallyequivalent to the tear drop antenna. Itis designed for mounting on aircraft which require internal mountingwithin tail cones and fin caps.
These antennas are susceptibleto magnetic field components produced byaircraft electrical equipment. Strong current impulses produced by switchclosures, relay contacts, transformer saturation effects, etc., cangenerate magnetic fields with frequency components extending into theOmega band. Unless previous experience or an equivalent installationhasbeen made, an electrical skin map of the aircraft will have to be made todetermine the optimum location for the antenna.
The antenna coupler amplifier is designed to accommodate the simultaneousoperation of a single VLF and ADF system using a common ADF-sense antenna.
A block diagram of a system employing a single VLF/Omega receiver is shownin Figure I-1. A dual VLF/Omega installation is shown in Figure I-2.
1.3 EnvironmentalQualifications
The VLF/Omega units have been qualified to the DO-160B standards calledout in Table I-2.
There are no external cooling requirements for the RPU. A minimum 2-inchclearance around the RPU is recommendedfor thermal isolation.
1.4 Power and Wei~ht Specifications
Power and weight specs for the units comprising the VLF/Omega system are
listed in Table I-3.
1.5 Other Mountin~/WirinQ Constraints
The cable run between the antenna/couplerunit and the VLF/Omega receiveris not to exceed 200 feet.
Shields should be terminated as shown. Connecting shields together in theantenna cable can cause signal to be excessively noisy or, in extremecases, actual loss of signal.
The VLF/Omega sensor(s)may be connected to any FMS Long Term Sensor (LTS)input port. All LTS inputs require proper identification. Tables I-4,I-5, and I-6 provide configurationinformationfor the FMS LTS inputports.
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,1
AT-80X
E
POWER
{
k
A/c wow+SWITCH
OZ-800
}
BITE
PRIMARYFMS INPUT {
)LOOP A
}LOOP B
SECONDARYFMS INPUT {
~ NC 28 VDC
~ WC GNDNZ NO. 1
: }
SENSORDATA
INZ NO. 2
#
AD-16798
Block Diagram - Single VLF/Omega Installation
Figure 1-1
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AZ-800NO. 1 c A/C28 VDC
AT-80XNO.1 -“
4 “ }
z JvCGNDBfTE NZ NO.1
PRIMARYFMS INPUT { :
: )
SENSOR
{ :
NO. 1 DATA
POWER
: }LOOP A
~ )
SENSOR
{ :
NO. 2 DATASECONDARY
: )
FMS INPUT
LOOP B~
Nc WOW4SWITCH
OZ-800NO.2
SECONDARYFMS INPUT ( :
AT-80XNO.2
= }BITE
NZ NO.2
POWER{ F : )
SENSORNO.2DATA
PRIMARYFMS INPUT( ~
: )LOOP A
: }SENSORNO.1DATA
~ )LOOP B b
e A/C28VDC
AK wow+SWITCH
+ NC GNDAO-167e9
B1ock Diagram - Dual VLF/Omega Instal1ationFigure I-2
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Table I-2EnvironmentalQualifications
CATEGORY QUALIFICATION
OZ-800 AT-80X
Temperature/Altitude F2
Temperature Variation B
Humidity B
Shock Operational: 6GCrash Safety: 15G
Vibration o
Explosion x
Waterproofness x
Fluid Susceptibility x
Sand and Dust x
Fungus Resistance x
Salt Spray x
Magnetic Effect z
Power Input A
Voltage Spike A
Audio Frequency z
ElectromagneticCompatibility z/z/z(Induced Signal Suscpetibility/
/RF Susceptibility/RF Emissions)
F2
x
c
Operational: 6GCrash Safety: 15G
J
x
x
x
x
x
x
x
x
x
x
x/x/x
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Table I-3Weight and Power Specifications
Unit Weight Power
OZ-800 6.5 lbs 28 V dc, 34 W
AT-800 2.2 lbs t 12Vdc, 0.18W
AT-801 2.2 lbs ~ 12 V dc, 0.18 W
AT-802 .74 lbs ~ 12 V dc, 0.18 W
AT-803 1.8 lbs ~ 12 V dc, 0.18 W
Note: AT-80X power is supplied by OZ-800.
.6 Interconnect Information - Sincile Svstem
Interconnect data for a single VLF/Omega system installation follows.Complete informationis provided for the RPU and antenna. Modificationstothe baseline G-IV system are also included. The RPU maybe connectedto anyof the three available LTS input ports of the Navigation Computer. TableI-4 provides VLF/Omega configurationdata for each of the FMS input ports.
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IOB_P_
(B)(B)(B)(B)(I)(I)(I)(B)(B)
(B)(B)(I)(I)(I)(I)(I)(I)(1)(I)(I)(1)(1)(I)(I)(I)(I)
NAVIGATION COMPUTER NO. 1(Single System)
Function - Connector Pin
ARINC 429 RCVR - (H)#
121 J1A-23 (22) ------P- ------LTS #2 (L) ------ARINC 429 RCVR - (H) % [;:] :fi:#=------LTS #1 (L) -27 (22) -.. ----------HIGH/LOW* SPEED BUS-LTS #1 -47 (22) ---------------HIGH/LOW* SPEED BUS-LTS #2 -48 (22) ---------------HIGH/LOW* SPEED BUS-LTS #3 -49 (22) ---------------ARINC 429 XMTR - (H)
#-50 (22) ----- ---------
GEN BUS PRIMARY S& G~~lJIA-51 (22) ---!!--------------------------
ARINC 429 RCVR - (H) 121J1B-57 (22LTS #3LTS #l ~uMBER BIT $;) -58 (22
-59 (22LTS #1 NUMBER BIT #2 -60 (22LTS #2 NUMBER BIT #1 -61 (22LTS #2 NUMBER BIT #2 -62 (22LTS #3 NUMBER BIT #1 -63 (22LTS #3 NUMBER BIT #2 -64 (22LTS #1 CONFIG -74 (22LTS #1 CONFIG -75 (22LTS #1 CONFIG -76 (22LTS #2 CONFIG -77 (22LTS #2 CONFIG -78 (22LTS #2 CONFIG -79 (22LTS #3 CONFIG -89 (22LTS #3 CONFIG -90 (22LTS #3 CONFIG 121J1B-91 (22
n+
------ -------II----- --.-----u
-----.-- -.-----
Connects To
TABLE I-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4141J1-27141J1-28
TABLE I-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4
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,,,
IOB~
(6)(B)(B)(B)(I)(I)(1)(B)(B)
NAVIGATION COMPUTER NO. 2(SingleSystem)
Function Connector Pin Connects To
ARINC 429 RCVR -i
(H) C121J1A-23 (22) -O ----------LTS #2 (L} -24 (22]
#
-------ARINC 429 RCVR - (H) -26 (22) --~-~~ -------LTS #1 (L) -27 (22) ----~+ -------HIGH/LOW* SPEED BUS-LTS #1 -47 (22) ---------------
HIGl+/LOW* SPEED BUS-LTS #2 -48 (22) ---------------
HIGH/LOW* SPEED BUS-LTS #3 --- - - - - - --- - --
ARINC 429 XMTR - (H) ::: [xi --l~r..$-------GEN BUS PRIMARY $~&C~&JIA-51 (22) ---Y- --------
- - - -- -- --- - - - - I
(B) ARINC 429 RCVR - (H)(B) LTS #3 (L)(I) LTS #l NUMBER BIT #1(I) LTS #1 NUMBER BIT #2(1) LTS #2 NUMBER BIT #1(I) LTS #2 NUMBER BIT #2(I) LTS #3 NUMBER BIT #1(1) LTS #3 NUMBER BIT #2(1) LTS #1 CONFIG(1) LTS #1 CONFIG(1) LTS #1 CONFIG(1) LTS #2 CONFIG(I) LTS #2 CONFIG(1) LTS #2 CONFIG(1) LTS #3 CONFIG(I) LTS #3 CONFIG(1) LTS #3 CONFIG
— —r
C121J1B-57-58-59-60-61-62-63-64-74-75-76-77-78-79-89-90
C121J1B-91
:22) -:22) -:22) -
3--t ‘--J- ‘-----
---------
--------m-
------
:22j -----.---------,22)---------------:22) ---.-.---------;22)-----.---.---..’221---..----.---G-’22j---------------:22)---------------:22)---------------:22)----------.----,22)---------------:22)---------------,22}---------------,22)---.-----------,22]---------.-----
TABLE I-4TABLE 1-4TABLE I-4TABLE 1-4TABLE I-4TABLE I-4TABLE I-4141J1-25141J1-26
TABLE 1-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4TABLE 1-4TABLE I-4TABLE I-4TABLE I-4TABLE I-4
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,,,
.
(o)
(o)
(I)
(I)(I)(I)
(I)
(I)(I)(I)(I)(I)(o)
(o)
(o)
(I)(I)(I)(I)(B)(B)(I)(1)(1)(I)(B)(B)(I)(B)(B)
RECEIVER PROCESSOR UNIT(Single System)
Function Connector Pin
BITE (L) 141J1-1 (22)
I
-{~>1-- ----
Ill!
BITE (H) -10 (22) -L-LJ-+-- -----1~~1
ACU TYPE -36 (22) -;-v-;- -----
BITE SHIELD -20 ------+.J 1DATA FROM CDU (L) -2 ------NCLOOP A (H) -3 (22) -J-:-;-- 4.----
LOOP A
LOOP A SHIELDDATA FROM CDULOOP BLOOP BLOOP B SHIELDPOWER COMMON
+12 VDC
-12 VDC
(L)1’11 J-4 (22) -1-f-j-- ----
-13 ------{-l I(H) -5(H)
------qcn i-6 (22) ---7 (22) --~-ij-’--#
-----(L) -i-- -----
-16 ------7~~ 1
1
-9 (22) --7-p,-7--- ----
-18 (22) -j-lJ-~--- ----,11
+/- 12 VDC PWR SHIELDOUTER SHIELDTAS (z)TAS (x)ARINC 429 XMTR - (H)PRIMARY DATA (L)SHIELD COMMONTAS (Y)TAS (SIGNAL)TAS VALIDARINC 429 XMTR - (H)SECONDARY DATA (L)SHIELD COMMONARINC 429 RCVR - (H)SECONDARY DATA (L)
-19 (22) -J- - J---+----
f
Ly-8 ----------31 -----------11 ------NC-12 ------NC-14 (22) --,~~-
t---------
-15 (22) --y-- ----------44 --------17 ------NC-21 ------NC-22 ------NC 1
z-23 (22) ---- ----------24 (22) ---- ----------44 --------25 (22) ---------------
141J1-26 (22) ---------------
Connects To
142/151Jl-3(142J1-F)(Note 2)142/151Jl-l(142J1-E)(Note 2)142/151Jl-2(Note 2)
142/151Jl-9(142J1-H)142/151Jl-10(142J1-A)
142/151Jl-12142/151Jl-13
142/151Jl(142J1-D)142/151Jl(142J1-B)142/151Jl(142J1-C)
-6
-7
-5
TABLE I-4TABLE I-4
TABLE I-4TABLE I-4
C121J1A-50C121J1A-51
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RECEIVER PROCESSOR UNIT(Single System)
IOB~ Function Connector Pin Connects To
(B) ARINC 429 RCVR - (H)I
141J1-27 (22) ------+5T- ---- 121J1A-50(B) PRIMARY DATA (L) -28 (22) ------#Gt- ---- 121J1A-51(I) SDI BITO -29 ------NC
(I) SDI BIT1 -30 ------NC(0) DATA TOCDU (L) -32 ------NC(0) DATA TOCDU (H) -33 ------NC(I) TAS REF -34 ------NC(0) FSK DATA (H) -35 ------NC(I) TAS400HZREF (H) -37 ------NC(I) TAS 400 HZ REF (L) -38 ------NC(I) COMPASS VALID -39 ------NC(I) SECONDARY ON/OFF CONTROL -40 (22) --------------- 141J1-49,
141J1-53(I) HDG 400 HZ REF (H) -41 ------NC(I) HDG400HZ REF (L) -42 ------NC(0) FSK DATA (L) -43 ------NC[;\ ;:: (z) -45 ------NC
(Y) -46 ------NC(I) HDG (x) -47 ------NC(I) RANGE/HYPERBOLICMODE(OPEN/GND)-48 ------NC(I) PRIMARY ON/OFF CONTRO -49 (22) --------------- ;::::-::,
(1) H-FIELD MOUNT -50 ------NC (Note 1)(I) WOW (GND/OPEN) . -51 (22) --------------- A/C WOW SWITCH(1) WOW (OPEN/GND) -52 ------NC(1) PROGRAM PIN COMMON -53 (22) --------------- 141J1-40,
141J1-49,(Note 1)
SPARE -54(P) +28VDC POWER RETURN -55 (20) --------------- iy&u~8v Dc
SPARE -56(P) +28V DC POWER 141J1-57 (20) --------------- A/C+28VDC
IOTES:,. Wiring shown is for top-mounted H-field antenna. 141J1-50 is to be
connected to 141J1-53 for bottom-mountedantenna configuration.
!.Wires terminating at pins 141J1-1, 141J1-10, and 141J1-36 are twistedtriple.
I.Antenna connections, LRU No. 142, shown in parenthesis refer toinstallationsusing the AT-803 only.
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,,,
(1)(o)(I)(I)(I)(1)(I)(I)(o)(o)(1)(0)(o)[1)(I)
106~
{o)[;]
(1)(1)(o)(o)
(o)
Function
BITEACU TYPEBITEBITE SHIELD-12 VDCPOWER COMMON+12 VDCPOWER SHIELDLOOP AMOP ALOOP A SHIELDLOOP BLOOP BLOOP B SHIELDOUTER SHIELD
EuQtiQn
LOOP A+12 VDC-12 VDCPOWER COMMONPOWER SHIELI)BITEBITESPARELOOP ASPARE
(H)
(L)
ANTENNA/COUPLER UNIT(AT-800 or AT-801)(Single System)
142J1
(H)(1.)
(H)(L)
142J1
I.-1 (22) -J_@ ------”--2 (22) -{;-+- --------:j (22) -j-y;- --------
--------
1
-5 (22) -+-f+- ---------6 (22) ------- ---------7 (22) +y’{- ---------8 ------1-/>,
I-9 (22) -q;--lq----------10 (22) ;-y;- ---------11 ------- -
t-12 (22) J-’’->J----------13 ~::u-;;+;- ---------14”
‘?-’-15 -------
ANTENNA/COUPLER UNIT(AT-803)
(Single System)
Connector Pin
(L)
I
142J1-A (22) ------+- ----B (22) --f:,------ ----c (22) ---------------D (22) -+------ ---
.--------(H)
i:; [:;; ---~~j------ ---
(L) ------------ ----G
</
(H) i-H (22) --------{;- ---142J1-K
Connects To
141J1-10141J1-36141J1-1
141JI-19141J1-9141J1-18
141JI-3141JI-4
141J1-614131-7
Connects To
141JI-4141J1-18S41JI-19141J1-9
141J1-iO141J1-1
141J1-3
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,,,
IOB&
(1)(o)(1)(I)(I)(I)(I)(I)(o)(o)(1)(o)(o)(1)(I)
Function
BITEACU-TYPEBITEBITE SHIELD-12 VDCPOWER COMMON+12 VDCPOWER SHIELDLOOP ALOOP ALOOP A SHIELDLOOP BLOOP BLOOP B SHIELDOUTER SHIELD
ANTENNA/COUPLERAMPLIFIER(AT-802)
(Single System)
Connector Pin ~-,
(H)
I
151J11; [;;; --;~-;{- --------------- -----.-
(L)II II
‘3 ~~~~-~~j~~-j- -------
1
l/\l”:: (22) ----------------6 (22) --+${;- --------7 (22) -------- -------Iyl-8 ---------
(H)1
-9 (22) --J-f~J- -------(L) -10 ~::~w:;;y~;- -------
-11(H)
1-12 (22) -J~~J- -------
(L) -13 (22) -+JY’+- --------14 -------< -/
151J1-15 --------~
Connects To
141J1-10141J1-36141J1-1
141J1-19141J1-9141J1-18
141J1-3141J1-4
141J1-6141J1-7
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1.7 Interconnect Information - Dual System
Interconnectdata for a dual VLF/Omega system installation follows.Complete information is provided for the RPU and antenna. Modificationsto the baseline G-IV system are also included. The RPU’S may be connectedto any of the three available LTS input ports of the Navigation Computer.Tables I-5 and I-6 provide VLF/Omega configuration information for each ofthe FMS LTS input ports.
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—— .- MAINTENANCE
IOB&
(B)(B)(B){B)(B)(B)
(I)(1)(I)(B)(B)
(B)(B)[{]
(I)(I)(1)(I)(1)(1](I)(1)(1)(I)~;]
(1)
NAVIGATION COMPUTER NO. 1(Dual System)
Function Connector Pin
ARINC 429 RCVR - (H)i
121J1A-23 (22) -------- ------LTS #2 (L) -24 (22) --- - -- ------ARINC 429 RCVR - (H)
9-26 (22) --- - -. -----.
LTS #1 (L) 1$-27 (22) ---% -- -..---
ARINC 429 XMTR - (H) -45 (22) ----~ -- ------
GEN BUS SECONDARY (L) +$-46 (22) --- - -- ------
SHIELD GND----------------
HIGH/LOW* SPEED BUS-LTS #1 -47 (22) ---------------HIGH/LOW* SPEED BUS-LTS #2 -48 (22) .--------------HIGH/LOW* SPEED BUS-LTS #3 -49 (22) ---------------ARINC 429 XMTR - (H)
$-50 (22) ----~r- -------
GEN BUS PRIMARY (L) 12L?1A-51 (22) ------- -------SHIELD GND-----------------
ARINC 429 RCVR - (H)LTS #l NUMBER BIT ;:)LTS #3
LTS #1 NUMBER BIT #2.TS#2 NUMBER BIT #l.TS#2 NUM8ER BIT #2.TS#3 NUMBER BIT#l.TS#3 NUMBER BIT #2.TS#1 CONFIG.TS#1 CONFIG.TS#1 CONFIG.TS#2 CONFIG.TS#2 CONFIG,TS#2 CONFIG.TS#3 CONFIG.TS#3 CONFIG.TS#3 CONFIG
I121JlB:;~ [;;] -n- ----------------
-59 (22) ---:-:------”---60 (22) ----------------61 (22) ----------------62 (22) ----------------63 (22) ----------------64 (22) ----------------74 (22) ----------------75 (22) ---------------:;; [;;] ---------------
----------------78 (22) ----------------79 (22) ----------------89 (22) ----------------90 (22) ---------------
121J1B-91 (22) ---------------
Connects To
TABLES I-5, 1-6TABLES I-5, I-6TABLES I-5, 1-6TA8LES I-5, I-6C141J1-25C141J1-26
TABLES I-5, I-6TABLES I-5, 1-6TABLES I-5, I-6141J1-27141J1-28
TABLES 1-5, 1-6TABLES 1-5, I-6TABLES I-5, I-6TABLES I-5, I-6TABLES I-5, I-6TABLES I-5, I-6TABLES I-5, I-6TABLES I-5, I-6TABLES I-5, I-6TABLES I-5, I-6TABLES I-5, I-6TABLES 1-5, 1-6TABLES 1-5, 1-6TABLES I-5, I-6TABLES 1-5, I-6TABLES I-5, I-6TABLES I-5, 1-6
Interconnect InformationTable 501 (cent) 22-14-00
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1’
IOBP
(B)(B)(B)(B)(B)[B)
(1)(1)(1)(B)(B)
(B)(B)(1)(I)(1)(1)(I)(I)(I)(1)(1)(1)(1)(1)(I)(1)(1)
NAVIGATION COMPUTER NO. 2(Dual System)
Function Connector Pin
ARINC 429 RCVR -
/
[~] C121J1A-23 (22) --~; --------LTS #2 -24 (22) ----.- --------ARINC 429 RCVR - (H) -25 (22) --:{- --------LTS #1 (L) -26 (22) ---~<- --------ARINC 429 XMTR - (H) ’45 (22) ‘-1-1- --------GEN BUS SECONDARY (L) -46 (22) ---Y- --------
SHIELD GND----------------
HIGH/LOW* SPEED BUS-LTS #1 -47 (22) ---------------HIGH/LOW*SPEED BUS-LTS #2 -48 {22) ---------------HIGH/LOW* SPEED BUS-LTS #3 -49 (22) ------ --------ARINC 429 XMTR - (H)
t-50 {22) ------ --------
GENIUS PRIMARY S~~~LD~~:lJIA-51 (22) --~Y(- --------------------.--.
ARINC 429 RCVR - (H)LTS #3 [L)LTS #1 NUMBER BIT #1LTS #1 NUMBER BIT #2LTS #2 NUMBER BIT #1LTs#2 NuMBERBIT#2LTS #3 NUMBER BIT#lLTS #3 NUMBER BIT #2LTS #1 CONFIGLTS #l CONFIGLTS #1 CONFIGus#Z CONFiGLTS #2 CONFIGLTS #2 CONFIGLTS #3 CONFIGLTS #3 CONFIGLTS #3 CONFIG
1C121J1B-57 (22) ----- ---------58 (22) --!C-- ---------59 (22) ----~-----------60 (22) ----------------61 (22) ----------------62 (22) ----------------63 (22) ----------------64 (22) ----------------74 (22) ----------------75 (22) ----------------76 (22) ----------------77 (22) ----------------78 (22) ----------------79 (22) ----------------89 (22) ----------------90 (22) ---------------
C121J1B-91 (22) ---------------
Connects To
TABLES 1-5, 1-6TABLES I-5, I-6TABLES I-5, 1-6TABLES I-5, 1-6141J1-25141J1-26
TABLES I-5, I-6TABLES I-5, I-6TABLES I-5, I-6C141J1-27C141J1-28
TABLES I-5, 1-6TABLES I-5, 1-6TABLES I-5, I-6TABLES 1-5, 1-6TA8LES I-5, I-6TABLES 1-5, 1-6TABLES I-5, I-6TABLES I-5, I-6TABLES 1-5, I-6TABLES I-5, I-6TABLES I-5, 1-6TABLES I-5, I-6TABLES I-5, 1-6TABLES 1-5, I-6TABLES I-5, I-6TABLES I-5, 1-6TABLES I-5, I-6
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,!,
(o)
(o)
(I)
(I)(I)(I)
(I)(I)(I)(1)(1)(o)
(o}
(0)
Function
BITE
BITE
ACU TYPE
BITE SHIELDDATA FROM CDULOOP A
LOOP A
LOOP A SHIELDDATA FROM CDULOOP BLOOP BLOOP B SHIELDPOWER COMMON
+12 VDC
-12 Vllc
RECEIVER PROCESSOR UNIT NO. 1(Dual System)
Connector P~nf\ I
(L) 141J1-1 (22) --J--q-+- ---
1i~ll.
(H) -10 (22) _~-~+.Lm_
,111
-36 ___~~l f\ [
-20---------b-yl
(L) ------NC , \(H)
f:: (22) -----p- - ---
~,,1{L) -4 (22) ---r-+ ’i-----
-13 --------$-J I(H) -5 ------NC [ II
Connects To
142/151Jl-3,(142J1-F),(Note 2)142/151Jl-1,~;:;;li;),
142/151Jl-9,(142J1-H)142/151Jl-10,(142J1-A)
(Hj -6 (22) ---i-----k$--- 142/151Jl-12(L) -7 (22) ---~-(-l--r---- 142/151Jl-13
-16 -------- t-~ \ I-9 (22) --------- -v--- 142/151 Jl-6,
Ill rl (142J1-D),Jl_l-18 (22) --- ~- --- 142/151 Jl-7,
f!! ~ 1(142J1-B)
-19 (22) ---7-L -- - --- 142/151 Jl-5,
sly(142J1-C)
(1) +/- 12 VDC PWR SHIELD -a ----------(I) OUTER SHIELD -31 ------------J(1) TAS (z) -li --”---NC(I) TAS (x) -12 ------NC(B) ARINC 429 XMTR - (H)
+-14 (22) ------f@T- ---- TABLE I-5
(B) PRIMARY DATA (L) -15 (22) ------- ------- TABLE 1-5(I) SHIELD COMMON -44 -----------f(1) TAS (Y)(1) TAS (SIGNAL)(I) TAS VALID(B) ARINC 429 XMTR - (H)(B) SECONDARY DATA (L)(I) SHIELD COMMON(B) ARINC 429 RCVR - (H)(B) SECONDARY DATA (L)(B) ARINC 429 RCVR - (H)
-17 ------NC-21 ------NC-22 ------NC
$-23 (22) ---------- ---- TABLE I-5-24 (22) ----.~-{-- ---- TABLE ]-5-44 ----”------Y
i-25 (22) ------0--- ---- C121J1A-45-26 (22) ------$- ----
t
C121J1A-46141J1-27 (22) -----i?--- ---- 121J1A-50
Interconnect InformationTable 501 [cent) 22-14-00
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Use or disclosure of information on this page is subject to the restrictions on the title page of thk document.
,1,
(B)(I)(I)(o)(o)(1)(o)(I)(I)(I)(1)
(I)(1)(o)(I)(I)(I)(1)(I)
(I)(I)(I)(I)
(P)
(P)
RECEIVER PROCESSOR UNIT NO. 1(Dual System)
Function Connector Pin Connects To
PRIMARY DATA (L) jl~141J1:;; (22) --------~-- -- 121J1A-51SDI BIT O ------NCSDI BIT 1 -30 ------NCDATA TO CDU (L) -32 ------NCDATATO CDU (H) -33 ------NCTAS REF -34 ------NCFSK DATA (H) -35 ------NCTAS 400HZ REF (H) -37 ------NCTAS 400HZ REF (L) -38 ------NCCOMPASS VALID -39 ------NCSECONDARY ON/OFF CONTROL -40 (22) --------------- SIG GND
HDG 400HZ REF (H) -41 ------NCHDG 400HZ REF (L) -42 ------NCFSK DATA (L) -43 ------NCHDG (z) -45 ------NCHDG (Y) -46 ------NCHDG (x) -47 ------NCRANGE/HYPERBOLICMODE(OPEN/GND)-48------NCPRIMARY ON/OFF CONTRO -49 (22) --------------- SIG GND
H-FIELD MOUNT -50 ------NC (Note 1)WOW (GND/OPEN) -51 (22) --------------- A/C WOW SWITCHWOW (OPEN/GND) -52 ------NCPROGRAM PIN COMMON -53 ------NC
SPARE -54+28 VDC POWER RETURN -55 (20)---------------- A&c+;8vDc
SPARE -56+28 VDC POWER 141J1-57 (20)---------------- A/C +28 V DC
NOTES:1. Wiring shown is for top-mountedH-field antenna. 141J1-50 is to be
connected to 141J1-53 for bottom-mountedantenna configuration.
2. Wires terminating at pins 141J1-1, 141J1-10, and 141J1-36 are twistedtriple.
3. Antenna connections, LRU No. 142, shown in parenthesis refer toinstallationsusing the AT-803 only.
Interconnect InformationTable 501 (cent) 22-14-00
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!!,
Function
RECEIVER PROCESSOR UNIT NO. 2(Dual System)
IOBD Connector Pin
({\
c141J1-2 (22j -- -fi----- ---
Connects To
{0) BITE (L)
(H)
C142/C151Jl-3,{C142J1-F) ,(Note 2)142/151Jl-1,(142J1-E) ,(Note 2)
!111i-10 (22) _l-J-L-l_ ---
T
II
-36 ------NQI
(0) BITE
(1) ACU TYPE
-20 --.-----!--J ~-2 ------NC\-3 (22) fil
t---l-,,-;-- ---
(1)(1)(1)
BITE SHIELDDATA FROM CDULOOP A
(L)(H)
(L)
C142/C151Jl-9,(C142J1-H}C142/C151Jl-10,(C142J1-A)
-4 (22) -- --+--;--+---,11(1) LOOP A
1]1-13 ----------------Nc[ ~
i:: (22) --w--y- ----7 (22) --q--y-l-- ----16 -----------9 (22)
I
--J.Q-l-- ---]\ll
-18 (22) --q-,-:-l-- ---
{1)(1)(1)(1)(1)[0)
LOOPA SHIELDDATA FROM CDULOOP BLOOP BLOOP BSHIELDPOWER COMMON
(H)(H)(L)
C142/C151Jl-12C142/C151Jl-13
C142/C151Jl-6,(C142J1-D)142/151Jl-7,(142J1-B)142/151Jl-5,(142J1-C)
(o) +12 VDC
Q1; &-19 (22) --- -- - -- ---(0) -12 VDC
(I)(1)(1)(1)(B)(B)(1)(I)(1)(I)(B)(B)(I)(B)(B)
+/- 12 VDC PWR SHIELD J% ------------ J
. .--- - - - . -- - -
OUTER SHIELDTAS (z) -11 ------NCTAS (x) -12 ------NCARINC429XMTR - {H)
i-14 (22) -----;r-- ----- TABLE I-6
PRIMARY DATA (L) ~;: (22) -----y -- ---- TABLE 1-6SHIELD COMMON ----------TAS (Y) -17 ------NCTAS (SIGNAL) -21 ------NCTAS VALID -22 ------NCARINC 429 XMTR - (H)
i~~j ~:~] ----ID-- ---- TABLE I-6
SECONDARY DATA (L) -------- ---..-Y
TABLE I-6SHIELO COMMON -44 -----------ARINC 429 RCVR - (H)
i-25 (22) -----@- ---- 121J1A-45
SECONDARY DATA (L) C141J1-26 {22) -----J;-- ---- 121J1A-46
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use Or disclosure Of information on this page is sub]ect to the restrictions on the title page of tf’us document.
,!,
IOBP
(B)(B)(I)(I)(o)(o)(I)(o)(I)(I)(I)(I)
[;]
(o)(1)(1)(I)(I)(I)
(I)(1)(I)(I)
(P)
(P)
RECEIVER PROCESSOR UNIT NO. 2(Dual System)
Function Connector Pin Connects To
ARINC 429 RCVR - (H)4
C141J1-27 (22) -------- ----- C121J1A-50PRIMARY DATA (L) -28 (22) ------c-- ----- C121J1A-51SDI BIT O -29 ------NCSDI BIT 1DATATO CDU (L)DATATO CDU (H)TAS REFFSK DATA (H)TAS 400HZ REF (H)TAS 400HZ REF (L)COMPASS VALIDSECONDARY ON/OFF CONTROL
-30 ------NC-32 ------NC-33 ------NC-34 ------NC-35 ------NC-37 ------NC-38 ------NC-39 ------NC-40 (22)---------------- SIGGND
HDG 400HZ REF (H) -41 ------NCHDG 400HZ REF (L) -42 ------NCFSK DATA (L) -43 ------NCHDG (z) -45 ------NCHDG (Y) -46 ------NCHDG (x) -47 ------NCRANGE/HYPERBOLIC MODE(OPEN/GND)-48 ------NCPRIMARY ON/OFF CONTROL -49 (22)---------------- SIGGND
H-FIELD MOUNT -50 ------NC (Note 1)WOW (GND/OPEN) -51 (22)---------------- A/C WOW SWITCHWOW (OPEN/GND) -52 ------NCPROGRAM PIN COMMON -53 ------NC
SPARE -54+28 VDC POWER RETURN -55 (20) ---------------- A/C +28 V DC
RETURNSPARE -56+28 VDC POWER C141J1-57 (20) ---------------- A/C+28VDC
NOTES:1. Wiring shown is for top-mounted H-field antenna. C141J1-50 is to be
connected to C141J1-53 for bottom-mountedantenna configuration.
2. Wires terminating at pins C141J1-1, C141J1-10, and C141J1-36 aretwisted triple.
3. Antenna connections, LRU No. C142, shown in parenthesis refer toinstallationsusing the AT-803 only.
Interconnect InformationTable 501 (cent) 22-14-00
Page 598.330Mar 15/91
Use or disclosure of information on this page is subject to the restrictions on the title page of this d xxment.
,,,
ANTENNA/COUPLERUNIT NO. 1(AT-800 or AT-801)(Dual System)
IOB& Function Connector Pin
(I) BITE (H)f)
t
142J11j (22) ---7-R--E-- --(0) ACU TYPE ------NC, ,, I(1) BITE (L) -3 (22) -----~~] ~~~Ev~~IELD -4 Iy-T-- ‘-----------
i-5 (22) --- ‘-5--L-- --
(I) POWER COMMON 111~-6 (22) --------- -- --(1) +12 VDC -7 (22) ---;-!~--t----(I) POWER SHIELD -8(0) LOOP A (H) ‘--------1-: ‘ 4-9 (22) --------- -- --(0) LOOP A (L) Illr+-lo (22) --------- -- --(1) LOOP A SHIELD -11 --------J-Y ~(0) LOOP B (H)
k-12 (22) ---~--~--!-- --
(0) LOOP B (L)i{
-13 (22) --- -J-’--’-- --(1) LOOP B SHIELD -14 --------- r(I) OUTER SHIELD 142J1-15 ------------
ION~ Function
(0) LOOPA(I) +12 VDC(I) -12 VDC(I) POWER COMMON(I) POWER SHIELD(0) BITE(0) BITE
SPARE(0) ~C))~EA
ANTENNA/COUPLER UNIT NO. 1(AT-803)
(Dual System)
(L)
(H)(L)
(H)
Connector PinI
142J1-A-B-c
::
::
::142J1-K
i
(22) --------,2P- --(22) ----~ --J-’-- --(22) ---;-;------ --(22) -------------------------
+(22) ----:------- --(22) ---JJ ----------
(22)II 4---------p+----b
Connects To
141J1-10
141J1-1
141J1-19141J1-9141J1-18
141J1-3141J1-4
141J1-6141J1-7
Connects To
141J1-4141J1-18141JI-19141J1-9
141J1-10141J1-1
141J1-3
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ANTENNA COUPLER AMPLIFIER NO. 1(AT-802)
(Dual System)IOB& Function Connector Pin Connects To
(I) BITE (H)
/
51J1-1 (22) -q;~;<- ------- 141J1-10(0) ACU TYPE -2 (22) --l+-++-------- 141J1-36(I) BITE (L) -3 (22) -44--I+-------- 141J1-1(I) ~;~EV;~IELD -4 -------+-Y-.1(I)
/
-5 (22) -Iq~lJ- ------- 141J1-19(I) POWER COMMON -6 (22) -I+-+J- ------- 141J1-9(I) +12 VDC -7 (22) -i~-+d- ------- 141J1-18(1) POWER SHIELD -8(0) LOOP A (H)
.___,m-9 (22) -q,’qJ-
I------- 141J1-3
(0) LOOP A (L) -10 (22) -Id-4~- ------- 141J1-4(1) LOOP A SHIELD -11 ------+-Y.I(0) LOOPB (H) -12 (22) -41q+-
I------- 141J1-6
(0) LOOP B (L) -13 (22) -+-J-44-------- 141J1-7(I) LOOP B SHIELD f-14 --------(1) OUTER SHIELD 151J1-15 ---------
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!!,
IOBJ_
(1)(o)(I)(I)(1)(1)(I)(I)(o)(o)(I)(o)(o)(I)(I)
Function
BITEACU TYPEBITEBITE SHIELD-12 VDCPOWER COMMON+12 VDCPOWER SHIELDLOOP ALOOP ALOOP A SHIELDLOOP BLOOP BLOOP B SHIELDOUTER SHIELD
IOB~ Function
(0) LOOPA(I) +12VDC(I) -12 VDC(1) POWER COMMON(I) POWER SHIELD(0) BITE(0) BITE
SPARE(0) ~C))~EA
ANTENNA/COUPLER UNIT NO. 2(AT-800 or AT-801)(Dual System)
Connector Pin
(H) f>
i
C142J1:: (22) ---1 --~--1-- ---------NC! :! ,
(L) -3 (22) ---+--~--,-- ----6 ----:----J-J i
(H)$
-9 (22)-----L-9-J-----(L) -10 ~::f::::;.!+{-- ---
-11(H)
i-12 (22) -----L~=J-- ---
(L) -13 (22) -----I J-’ J-- ---Wti
-14 ----------C142J1-15 ----------
ANTENNA/COUPLERUNIT NO. 2(AT-803)
(Dual System)
Connects To
C141J1-10
C141J1-I
C141J1-19C141J1-9C141J1-18
C141JI-3C141J1-4
C141J1-6C141J1-7
Connector Pin Connects ToI
(L) $C142J1-A (22)----------1~1- --- C]41J]-4-B (22) -----O ------- --- C141J1-18
i-C (22) ----J-! ------ --- C141J1-19-~ (22) -----!! ------ --- C141J1.9-J ---------~
(H)$
-~ (22)-----O------- --- C141J1-10(L) ~: (22) -----L! ------ --- C141J1-1
I(H) -H (22)----------l~----- C141J1-3
C142J1-K
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,!!
ANTENNA COUPLER AMPLIFIER NO. 2(AT-802)
(Dual System)IOB
~ Function Connector Pin Connects To
(I) BITE (H) C151J1-1 (22)---lf~~+-
1
------ C141J1-10(0) ACUTYPE -2 (22)---1-1-44- ------ C141J1-36(I) BITE (L) -3 (22)---1JY4:- ------ C141J1-1(I) 133:EVS:IELD -4
\
-------J-T,J- ------
(1) -5 (22)---(1) POWERCOMMON -6 (22)--- I;., J- ------ :;:;;;:;9(I) +12 VDC -7 ~~~~;11j4~i;- ------ C141J1-18(I) POWER SHIELD -8(0) LOOPA (H) -9 (22)---
IJ;’21L ----.- C141J1-3
(0) LOOPA (L) -10 (22)---JAJAJ- ------ C141J1-4(I) LOOPA SHIELD -11 -------J-Y [(0) LOOPB (H) -12 (22)
i----h=+ ~- ------ C141J1-6
(0) LOOPB (L) -13 (22)----!+4+- ------ C141J1-7(1) LOOPB SHIELD -14 --------\Y(1) ~ OUTERSHIELD C151J1-15 --------- J’
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Table I-4NZ Configurationfor Single VLF/Omega Sensor
RPU NZ-800CONNECTED INPUT LTS CONFIGURATION BUS LTS
To: PORT SPEED NUMBER:========== =========== ============*==============-----==== ================
.TSNO. 1 JIA-26(H) JIB-74 JIB-75 JIB-76 JIA-47 JIB-59 JIB-60JIA-27(L) OPEN GND OPEN OPEN OPEN OPEN
.TSNO. 2 JIA-23(H) JIB-77 JIB-78 JIB-79 JIA-48 JIB-61 JIB-62JIA-24(L) OPEN GND OPEN OPEN OPEN OPEN
.TS NO. 3 JIB-57(H) JIB-89 JIB-90 JIB-91 JIA-49 JIB-63 JIB-64JIB-58(L) OPEN GND OPEN OPEN OPEN OPEN
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,!
Table I-5NZ CONFIGURATIONFOR NO. 1 VLF/OMEGA SENSOR
(DUAL INSTALLATION)
RP~ NO. 1 NZ-800CONNECTED INPUT LTS CONFIGURATION BUS
TO:LTS
PORT SPEED NUMBER*a*n=aE=a=s =E=S===EE5====S =*as=uxn==s=9%==%xmR===Es= S========= ====S*====*=*=====
121J1A-26(H) JIB-74 JIB-75 JIB-76 JIA-47 JIB-59 JIB-60LTS NO. 1 121J1A-27(L) OPEN GND OPEN OPEN OPEN GND
C121J1A-26(H) JIB-74 JIB-75 JIB-76 JIA-47 JIB-59 J18-60C121J1A-27(L) OPEN GND OPEN OPEN GND OPEN
121J1A-23(H) JIB-77 JIB-78 JIB-79 JIA-48 JIB-61 JIB-62LTS NO. 2 121JIA-24(L) OPEN GND OPEN OPEN OPEN GND
C121J1A-23(H) JIB-77 JIB-78 JIB-79 JIA-48 JIB-61 JIB-62C121J1A-24(L) OPEN GND OPEN OPEN GND OPEN
121J1B-57(H) JIB-89 JIB-90 JIB-91 JIA-49 JIB-63 JIB-64LTS NO. 3 121JIB-58(L) OPEN GND OPEN OPEN ~ GND
~ JIB-89 JIB-90 JIB-91 JIA-49 JIB-63 JIB-64C121J1B-58(L) OPEN GND OPEN OPEN GND OPEN
o.0.-.CO~o6?ciiCJ,
-.67
(+
RPU NO. 2CONNECTED
TO:=aamaEnaa=a
LTS NO. 1
LTS NO. 2
LTSNO. 3
Table I-6
NZ CONFIGURATIONFOR NO. 2 VLF/OMEGA SENSOR(DUAL INSTALLATION)
NZ-800INPUT LTS CONFIGURATION BUS LTSPORT SPEED NUMBER
[E=========,=u====E==9======9====%E==EU==E%====E====5================I I I
JIB-74 JIB-75 JIB-76 JIA-47 JIB-59 J18-60OPEN GND OPEN OPEN GND OPENJIB-74 JIB-75 JIB-76 JIA-47 JIB-59 JIB-60
C121J1A-27(L) OPEN GND OPEN OPEN OPEN GND
121JIA-23(H) JIB-77 JIB-78 JIB-79 JIA-48 JIB-61 JIB-62121JIA-24(LI OPEN GND OPEN OPEN GND OPENC121J1A-23(H) JIB-77 JIB-78 JIB-79 JIA-48 JIB-61 JIB-62C121J1A-24(L) OPEN GND OPEN OPEN OPEN GND
121J1B”(H) I JIB-89 I JIB-90 I JIB-91 i JIA-49 I JIB-63 I JIB-64121JIB-(L) OPEN GND OPEN OPEN GND OPENC121J1B-57(H) JIB-89 JIB-90 JIB-91 JIA-49 JIB-63 JIB-64C121J1B-58(L) OPEN GND OPEN OPEN OPEN GND
APPENDIX KMICROWAVE LANDING SYSTEM (MLS) INSTALLATION
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APPENDIX KMICROWAVE LANDING SYSTEM (MLS) INSTALLATION
1.0 MLS INSTALLATION
1.1 Sco~e
This appendix provides data for the installation of the Honeywell MLSreceivers, control units, and paired DME into the G-IV aircraft. Includedare MLS system mechanical mounting requirements and the electricalinterconnections required to tie this system to existing G-IV avionics.
1.2 Functional Description
The ML-850 Microwave Landing System Receiver is designed for use with theC-band Time Referenced Scanning Beam (TRSB) Microwave Landing Systemsconforming to revised ICAO standards of FAA 14 CFR Part 171 Subpart J datedSep 18, 1986 or FAA-STD-022C. It is currently not compatible with Europeanground stations conforming to older ICAO standards which did not employprovisions for magnetic heading selection of runway centerline.
The MLS system operates on one of 200 channels between 5031.0 and 5090.7 MHz.The signal format is time multiplexed, that is, each function (azimuth,elevation, basic data, auxiliary data, and back azimuth) is transmittedsequentially on a single carrier frequency. Each function is identified by adigitally encoded preamble. The preamble is followed by TO and FRO scanningbeam signals or more digital data depending on the function.
The ML-850 receiver system provides guidance to the azimuth/back azimuth andglide path flight angles selected on the control unit or automaticallytransmitted from the ground station. The G-IV system will be configured forfront azimuth approaches only. Guidance is output from the receiver in theform of analog and/or digital deviation signals intended to driveconventional course deviation indicator displays. ILS look-alike ARINC 429labels are provided on the digital bus allowing integration to the G-IVautopilot and display on the EFIS. The MLS receiver scales and biases theseARINC 429 labels to the corresponding ILS mV per dots of deviation.
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1.2 Functional Description (continued)
Approach azimuth angles may be selected from the runway centerline out to thelimits of the proportional coverage area of the ground station. This angleis entered as the approach magnetic heading. Glidepath angles may beselected from the minimum safe angle for the desired runway heading (astransmitted from the ground station) up to the maximum allowable glidepathangle of 4“ for the G-IV.
Deviation from the selected angle is computed and scaled in the receiver.
Actual aircraft position angles relative to the centerline of the groundtransmitter are computed by timing the occurrence of the swept scanningbeams. The time interval between the centers of the TO and FRO scanningbeams is proportional to the aircraft position angle.
The receiver computes the centers of the received TO and FRO scans,calculates the aircraft position angle for each scan, and subtracts theselected angle to derive deviations. Each scan is validated according toRTCA DO-177 criteria and confidence counters are maintained to drive flagwarnings.
The scanning beam envelope is filtered using a 26 kHz low pass filter. Theangle data is filtered with a 10 radian/second low pass filter prior tocalculating the deviations. The deviations are scaled prior to output.Azimuth deviations are scaled as a function of runway length, Glidepathdeviations are scaled as a function of the selected glidepath angle.
The receiver uses basic data from the ground to determine runway length forazimuth scaling, proportional coverage limits, minimum glidepath, runwayheading and station identification.
The receiver also processes and outputs auxiliary data which pertains to theground station for use by other systems such as EFIS, AFCS, FMS, or RNAVequipment.
All digital data is received from the ground station in the form ofdifferential phase shift keyed (DPSK) microwave signals. These areconverted, reformatted and output. from the receiver on ARINC 429 andHoneywell RCB digital buses along with the derived angles and deviations.
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A Morse code station identifier is decoded by the receiver and output as anaudio signal, a discrete signal and digitally on both buses.
The MLS receiver transmits ARINC 429 labels for the purpose of flightguidance, crew display, and internal monitoring. Once these labels aretransmitted by the MLS receiver, they are switched into the SG by the displaycontroller (DC) through an external relay. The DC energizes this relay basedon flight crew selection of MLS as the active or preview nav source.
The MLS system in the G-IV is configured as a dual receiver and dual controlhead system. Each MLS receiver tunes a DME. MLS receiver 1 tunes DME 1, MLSreceiver 2 tunes DME 2. This DME information is then sent to the symbolgenerators with the paired MLS receiver as selected by the displaycontroller. See Figure 1.
Refer to Collins system description and installation manual 523-0774155 forcomplete information on the Collins DME 442.
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rtA.
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MLS System Schematic - Typical (Pilot Side)Figure K-2
h43 4344 44
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c7aA3 Cli?lt FMS 2E
—
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MLS System Schematic - Typical (Copilot Side)Figure 3
L
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1.3 Mechanical Installation Information
MLS Receiver
The MLS receiver is mounted in an MT-853 mounting tray, P/N 7510664-901.Forced air cooling is ~ required for the MLS receiver.
The MLS receiver may be located outside the pressure vessel, although thisinstallation places the MLS receivers in the avionics rack lclcated in thepressure vessel.
Refer to MLS System Description and Installation Manual, HoneywellPublication A15-3800-02, for detailed installation information.
Antennas
Antennas are located in the Gulfstream III standard antenna locations forMLS. These locations show acceptable performance on the Gulfstream IV. Theyare at station 46.75, 12 inches either side of centerline on the top of theaircraft for the two front antennas, and centered about station 595.0, oncenterline, 12 inches apart for the two aft antennas. The antennas shall beplaced no closer than 5 inches to each other. The aircraft skin in contactwith the antennas shall be free of insulating materials (paint) and shall betreated with an electrically conductive corrosion protection.
RF Cables
Rear antenna shading and insufficient coverage by ground transmitters maycause difficulty in complete MLS coverage at t60° from center azimuth(required certification coverage). The most dramatic improvement in MLSsystem performance can be obtained by insuring the RF path between the MLSreceiver and the antennas is of the lowest loss possible. An improvement ofonly 3 dBm of rf path loss doubles signal power at the receiver. Althoughthe MLS receiver allows up to 11 dBm of rf path loss, flight tests on theG-IV have shown these values to be unacceptable for rear antenna coverage.Therefore, the following rf cables are recommended:
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I. Electronic Cable Specialists cable P/N 310801: the RF loss on this cableis 9.3 dBm/100 ft at 5 GHz of cable run. Bend radius is 2“. Weight is15 lbs\100ft. The mating connector is a crimp on type and is P/N CTS022.The crimping tool is P/N 225020/5-1 with a die number Y-149. Thesecables may be supplied with the connectors attached and complete loss andVSWR documentation is provided with each cable. In this instance, testcables should be installed to determine correct cable length. Althoughthis presents a more challenging installation problem, the end result isa superior MLS system.
2. PIC Wire and Cable:
P/N S22089: The RF loss on this cable is 9.5 dBm/100 ft of cable run at5 GHz. Bend radius is 2.5”. Weight is 20 lbs/100 ft. Mating connectorsare TBD.
Alternate for front antenna cables:
P/N 7556124: The RF loss on this cable is 12.8 dBm/100 ft of cable runat 5 Ghz. Bend radius is 2.0”. Weight is 15 lbs/100 ft. Matingconnector is P/N 1-225554-1 TNC right angle, P/N 1-225550-3 TNC straight.
If possible, bulkhead connectors should be avoided - especially those in anenvironment exposed to water, salt, fuels, hydraulic and deicing fluids,etc.. These agents cause rf connections to deteriorate with time andexposure level.
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1.4 Environmental Qualifications
The MLS receiver has been tested to the following DO-160B environmentalqualifications.
DO-160BSection Environment MLS Receiver.
4 Temperature and Altitude CAT A2/El
5 Temperature Variation CAT A
6 Humidity CAT A
7 Shock (Operate and YESSustained)
8 Vibration CATJ, M, L, Y
9 Explosion Proofness CAT El
10 Waterproofness CAT X
11 Fluid Susceptibility CAT X
12 Sand and Dust CAT X
13 Fungus CAT X
14 Salt Spray CAT X
15 Magnetic Effect CAT Z
16 Power Input CAT B, Z
17 Conducted Voltage CAT ATransient
18 Audio Frequency Conducted CAT ZSusceptibility
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DO-160BSect ion Environment MLS Receiver
19 Induced Signal CAT ZSusceptibility
20 Radio Frequency CAT ZSusceptibility(Radiated and Conducted)
21 Spurious Radio Frequency CAT ZEmission
22 Lightning
Signal and Power Cables CAT L
Antenna Cables CAT L
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The MLS control head has been tested to the following DO-160B environmentalqualifications.
DO-160BSection Environment MLS Receiver
4 Temperature and Altitude CAT A2/Cl
5 Temperature Variation CAT A
6 Humidity CAT A
7 Shock (Operate and YESSustained)
8 Vibration CAT K, P, and S
9 Explosion Proofness CAT El
10 Waterproofness CAT X
11 Fluid Susceptibility CAT X
12 Sand and Dust CAT X
13 Fungus CAT X
14 Salt Spray CAT X
15 Magnetic Effect CAT Z
16 Power Input CAT B, Z
17 Conducted Voltage CAT ATransient
18 Audio Frequency Conducted CAT ZSusceptibility
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DO-160BSection Environment MLS Receiver
19 Induced Signal CAT ZSusceptibility
20 Radio Frequency CAT ZSusceptibility(Radiated and Conducted)
21 Spurious Radio Frequency CAT ZEmission
22 Lightning
Signal and Power Cables CAT L
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MLS
MLS
Receiver
.“1 : “
—.. ...—.- —
, .,
... ’:,,.
1
1
Table K-1Equipment
,.. . .* m
. .. . . — — — . ..——
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. ,,. .,*, .:. . .,
Interconnect InformationTable 501 (cent)
m,
m●
. . .
22-14-00Page 598;355
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MLS Contro”
.. ..’
Head
. 1’
,, ,
Table K-1 (continued)MLS Equipment List
. ‘, . . .
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m
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. .,, #
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m
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.“
Interconnect InformationTable 501 (cent)
22-14-00Page 598.356
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Table K-1 (continuedMLS Equipment List
MLS Front Antenna
. .m.
... .
.. “1 ‘. ...“
I ,. ‘: . . .. ... . . . .
,,mmm
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. . . ..
,, .
. ..
Interconnect InformationTable 501 (cent)
.
.m.
.,
.. ,
,,
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MLS
Table K-1 (continued)MLS Equipment List
Rear Antenna
1 i“ .’ n
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., , ,. ..“ .* m“
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.
.. . . . .. .. .
“-.
,.
.m
,....
,. “
,,
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1.5 Power and Weiqht Specification
Power for the MLS receiver and control head is taken from the aircraft 28Vdc power bus. A single circuit breaker switches power to the MLS receiver.The MLS receiver uses 15.5 VA maximum of power. The MLS control head uses4.0 VA maximum of power.
The maximum weight of the MLS receiver is 2.22 kg (4.9 pounds). The maximum
weight of the MLS control head is 567 g (1.25 pounds).
1.6 Additional Interface Requirements
New part number display controllers, symbol generators, and fault warningcomputers must be installed when the aircraft is updated to operate withMLS . The required part numbers are:
UnitNumber Unit Part Number
65/C65/E65 SG-884 Symbol Generator 7008570-904
115/cl15 DC-884 Display Controller 7007540-941/-942
134/c134 FC-880 Fault Warning Computer 7007484-905
All mounting requirements specified in previous sections of this documentremain the same. This appendix defines the additional requirements for theaddition of the MLS function.
1.7 Interconnect Information
Interconnect information for the MLS receiver follows. Completeinterconnect information is provided for the MLS receiver as well asmodifications required to baseline and other retrofit equipment.
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MLS Receiver 1 (MLZ-850)
10B_P_ Function Connector Pin Connectss
(P) 28 VDC P~R 116J1-5 (22) ----------------- 28VDC PWR (H),117J1-E
(P) 28 VDC PWR RET -4 (22)----------------- 28VDC PWR (L),117J1-J
(0) RCB OUT (P) -42 (22)--;-------------- l17J1-g(0) RCB OUT (N) -40 (22)----------------- 117J1-R
SHIELD GND -37 (22)--Y(I) RCB IN (P) -67 (22)----------------- l17J1-h(1) RCB IN (N) -39 (22)--!-1--------------117J1-S
SHIELDGND 117J1-s (22)--Y(0) AUDIO (HI) 116J1-9 (22)--9-------------- 117J1-B(0) AUDIO (LO) -21 (22)-d~-------------- l17J1-t
(0) MORSE BIT -44 ----NC(I) MLS OFF (NO) -7 (22)----------------- 117J1-A(0) STRAP COMMON -36 (22)----------------- 116J1-49,
116J1-61,116J1-51,116J1-65, 116J1-26
(1) MSAO (NO) 0.1”
I-64 ----NC
(I) MSA1 (NO) 0.2” -38 ----NC(I) MSA2 (NO) 0.4” -50 ----NC(1) MSA3 (NO) 0.8° NOTE -49 (22)----------------- 116J1-36(i) MSA4 (NO) 1.6° 1 -58 ----NC(!) MSA5 (NO) 3.2° -61 (22)----------------- 116J1-36(1) MSA6 (NO) 6.4° -59 ----NC(1) MSA7 (NO) 12.8° 116J1-45 ----NC
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IOBP
(I)(I)(I)(I)(1)(I)(o)
(o)(o)
(o)
(o)(o)
(o)(o)(o)
(o)
(o)
(o)
(o)
(o)
(I)
[c)]
(B)
(o)(o)(I)(1)
Function
MSA PARITYAFT PA (NO)FORE PA (NO)SIDE IDO (NO)~~yEE~~~ (NO)
AZ DEV (HI LVL)(+RIGHT)
AZ DEV COMMONAZ DEV (LO LVL)
(+RIGHT)GPDEV (HI LVL)
(+DOWN)GP DEV COMMONGPDEV (LO LVL)
(+DOWN)SHIELD GNDSHIELD GNDAZ VAL (HI LVL)
(Po)AZ VAL (LO LVL)
{PO)GP(~;; (HI LVL)
GPVAL (LO LVL)(Po)
AZ/CHAN CHANGE(Po)
GP CHANGE (PO)
MLS Receiver 1 (MLZ-850) (cent)
Connector Pin
116J1::; wwN;---------------
-16 ----NC-65 (22)------------------26 @~ii----------------31-20 ----NC
-3 ----NC-10 ----NC
-11 ----NC
-22 ----NC-1 ----NC
-62 ----NC-63 ----NC-24 ----NC
-23 ----NC
-14 ----NC
-12 ----NC
-25 ----NC
-17 ----NC
CHANGE INHIBIT -57 ---------------------(NO)
BAZ ENABLED -6 ----NCMLS 429 OUTPUT (A) -33 (22)-a -------------MLS 429 OUTPUT (B)
d-2 (22)--I --------------
SHIELD GND -35 (22)--1SEL GP > 4“ (NO) -54 ----NCBAZ AVAILABLE (NO) -57 ----NCMLS RF IN (FORE) l16J2---~2.---------~2--------MLS RF IN (AFT) 116J3------~---fj ------------
Connects To
116J1-36
116J1-36116J1-36
llJ1-11
TO PILOTMLS/DME SELECTRELAY
118J1 See 1.3119J1 See 1.3
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MLS Receiver 2 (MLZ-850)
IOB~ Function Connector Pin Connect:~
(P) 28 VDC PWR C116J1-5 (22)----------------- 28 VDC PWR (H),C117J1-E
(P) 28 VDC PWR RET -4 (22)----------------- 28 VDC PWR (L),Cl17J1-j
(0) RCB OUT (P) -42 (22)--9-------------- Cl17J1-g(0) RCB OUT (N) -40 (22)-J-L------------- C117J1-R
SHIELD GND -37 (22)--7
(I) RCB IN (P) -67 (22) --?-------------- Cl17J1-h(I) RCB IN (N) -39 (22)--’-L ------------- C117J1-S
SHIELDGND -s (22)--Y
(0) AUDIO(HI) -9 (22)--9-------------- C117J1-B(0) AUDIO(LO) -21 (22) ----------------- Cl17J1-t
(0) MORSEBIT -44 ----NC(I) MLS OFF (NO) -7 (22)----------------- C117J1-A(0) STRAP COMMON -36 (22) ----------------- C116J1-49, C116J1-61,
C116J1-51, C116JI-65,C116J1-26
(I) MSAO (NO) O;1°
I-64 ----NC
(1) MSA1 (NO) 0.2” -38 ----NC(I) MSA2 (NO) 0.4” -50 ----NC(I) MSA3 (NO) 0.8° NOTE -49 (22)----------------- C116J1-36(I) MSA4 (NO) 1.6” 1 -58 ----NC(I) MSA5 (NO) 3.2° -61 (22)----------------- C116J1-36(I) MSA6 (NOO 6.4° -59 ----NC(1) MSA7 (NO) 12.8” C116J1-45 ----NC
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IOB~
(I)(1)(I)(I)(1)(I)(o)
(o)(o)
(o)
(o)(o)
(o)(o)(o)
(o)
(o)
(o)
(o)
(o)
Function
MSA PARITYAFT PA (NO)FORE PA (NO)SIDE IDO (NO)SIDE ID1 (NO)BAZ ENBLAZ DEV (HI LVL)
(+RIGHT)AZ DEV COMMONAZ DEV (LO LVL)
(+RIGHT)GP(~;DW~fI LVL)
GP DEV COMMONGP(~~~U~\O LVL)
SHIELD GNDSHIELD GNDAZ(~V} (HI LVL)
AZ{~V~ (LO LVL)
GP(JVj (HI LVL)
GP(~;j (LO LVL)
AZ/CHAN CHANGE(Po)
GP CHANGE (PO)
MLS Receiver 2 (MLZ-850) (cent)
Connector Pin Connects To
C116J11:j ~-------------------- C116J1-36
-16 ----NC-65 (22)----------------- C116J1-36-26 ~~~~~;--------------- C116J1-36-31-20 ----NC
-3 ----NC-lo ----NC
-11 ----NC
-22 ----NC-1 ----NC
-62 ----NC-63 ----NC-24 ----NC
-23 ----NC
-14 ----NC
-12 ----NC
-25 ----NC
-17 ----NC
(I) CHANGEINHIBIT (NO) -57 --------------------- llJ1-11(0) BAZ ENABLED -6 ----NC(B) MLS 429 OUTPUT (A) -33 (22)---------------- TO COPILOT p(B) MLS 429 OUTPUT (B) -2 (22)-J’-------------- t4~4~~E SELECT
SHIELD GND 1-35 (22)--(0) SEL GP >4° (NO) -54 ----NC(0) BAZ AVAILABLE (NO) -57 ----NC(I) MLS RF IN (FORE) Cl16J2----~>------------~>----- C118J1 See 1.3(I) MLS RF IN (AFT) Cl16J3--------~>--------------- C119J1 See 1.3
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MLS Control Head 1 (CM-850)
IOB& Function Connector Pin Connects To
(P) 28 VDC PWR 117J1-E (22)----------------- 28VDC PWR (H),116J1-5
(P) 28 VDC PWR RET -j (22)----------------- ~~6~lC4PWR (L),
(I) 5 VAC/DC DIMMING -D (22)----------------- ;l~MVP~~EL LIGHTS
(I) 28 VDC DIMMING -a ----NC
(I) DIMMING COMMON -Z (22)----------------- 5V PANEL LIGHTSDIMMING
(0) AUDIO (HI) -B (22)--:1------------- 116J1-9(0) AUDIO (LO) -t (22)---------------- 116J1-21
(I) RCB OUT (P)(I) RCB OUT (N)
-g (22)--fi------------- 116J1-42
d-R (22)-J- ------------- 116J1-40
SHIELD GND 116J1-37 (22)--
(0) RCB IN (P) l17J1-h (22)- -n
------------- 116J1-67(0) RCB IN (N) -S (22)- - ------------- 116J1-39
SHIELD GND -S (22)--Y
(0) MLS OFF -A (22)----------------- 116J1-7(0) MLS AUDIO (HI) -b (22)--fi-------- ----- MLS NO 1 AUDIO(0) MLS AUDIO (LO) -c (22)--- ------------- J-BOX
SHIELD GND -k (22)--Y
(I) FMS TUNING (P) -F ----NC(I) FMS TUNING (N) -G ----NC(I) NAV CTL (P) -f ----NC(I) NAV CTL (N) -P ----NC
RESERVED -r ----NC(I) TEST INHIBIT -Y ----NC
RESERVED -P ----NC(I) VOR/DME PAIRED -X (22)----------------- l17J1-n
RESERVED -d ----NC(I) SIDE SELECT (NO) -n (22)----------------- l17J1-q, 117J1-X(0) STRAP COMMON l17J1-q (22)----------------- l17J1-n
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IOBP
(P)
(P)
(I)
(I)
(I)
(o)(o)
(I)(I)
Function
28 VDC PWR
28 VDC PWR RET
5 VAC/DC DIMMING
28 VDC DIMMING
DIMMING COMMON
AUDIO (HI)AUDIO (LO)
RCB OUT (P)RCB OUT (N)
MLS Control Head 2 (CM-850)
Connector Pin
C117J1-E (22)-----------------
-j (22)-----------------
-D (22)-----------------
-a ----NC
-z (22)-----------------
-B (22)--O--------------t (22)--w------------d
:: v:;--fJ------------ ------ ----. .
- “SHIELD GND 116J1-37 (22)--J
(o)(o)
(o)(o)(o)
(I)(I)(I)(I)
(I)
(I)
(I)(o)
Connects To
28 VDC PWR (H),Cl16J1-528VDC PWR (L),C116J1-45 V PANEL LIGHTSDIMMING
5 V PANEL LIGHTSDIMMING
C116J1-9C116J1-21
C116J1-42C116J1-40
RCB IN (P) l17J1-h (22)--?------------- C116J1-67RCB IN (N) -s (22)-J- ------------- C116J1-39
SHIELD GND -S (22)--Y
MLS OFF -A (22)----------------- C116J1-7MLS AUDIO (HI) -b (22)-f+------------ :L;o~O 2 AUDIOMLS AUDIO (LO) -c (22)-y ------------- .
SHIELD GND -k (22)--
FMS TUNING (P)FMS TUNING (N)NAV CTL (P)NAV CTL (N)RESERVEDTEST INHIBITRESERVEDVOR/DME PAIREDRESERVEDSIDE SELECT (NO)SIDE SELECT COMMON
-F ----NC-G ----NC-f ----NC-P ----NC-r ----NC-Y ----NC-P ----NC-X (22)----------------- Cl17J1-q-d ----NC
----NCCl17Jl~; (22)----------------- C117J1-X
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Display Controller 1
IOB_P_ Function Connector Pin Connects 70
(I) t4LS INSTALLED l15J1-d (22}----------------- SEE NOTE 2(0) 500 ms NAV RETUNE 115JI-GG (22)----------------- 78A3-32
(SEE NOTE 3)
5isplay Controller 2
IOB& Function Connector Pin Connects T~
(I) MLS INSTALLED l15J1-d (22)----------------- SEE NOTE 2(0) 500 ms NAV RETUNE 115J1-GG (22)----------------- 78A3-32
(SEE NOTE 3)
NOTES: 1. G-IV strapped for 4 degrees - Max Allowable Descent by Auto Pilot.
2. Connected to Power Ground.
3. This discrete is used to force the Gables control head to tune theDME in a continuous label stream rather than in a burst tune mode.This will allow the DME to be retuned when switching from NAV tuningsource, to MLS tuning source, and then back to NAV. If thisdiscrete is not momentarily grounded the DME will not be retuned bythe NAV and an “F” will be displayed on the NAV control head.
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I APPENDIX LTRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM (TCAS) INSTALLATION
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APPENDIX LTRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM (TCAS) INSTALLATION
1.0 TCAS INSTALLATION
1.1 Sco~e
This appendix provides data for the installation of the Honeywell TCAScomputer into the G-IV aircraft. Included are TCAS mechanical mountingrequirements and the electrical interconnections required to tie this systemto existing G-IV avionics and diversity Mode S transponders.
1.2 Functional Description
The TCAS system determines the range, altitude, and bearing of otheraircraft equipped with mode S/ATCRBS transponders with respect to thelocation of own aircraft. The system monitors the trajectory of thesetarget aircraft for the purpose of determining if any of them constitute apotential collision hazard. TCAS target aircraft are displayed on the TCASsystem page and on the pilot and copilot’s navigation display. These targetdisplays are crew selectable though the display controllers. Also, the TCASsystem page will pop-up automatically when the TCAS computer computes atarget as a resolution advisory class target if not already called up fordisplay. The system is responsible for estimating the separation at closestapproach and determining if a potential conflict exists. If so, the systemdisplays a resolution advisory to the pilot on the Primary Flight Displayson the vertical speed tape. In addition to the visual resolution advisoryannunciations, aural annunciations broadcast through the crew audio paneland a dedicated speaker, reinforce avoidance commands to the flight crew.An aural advisory annunciation cancel button, canceling the currentannunciation, is available to the flight crew. The correctness of theavoidance maneuver is ensured by coordination of mutual intentions withother TCAS equipped aircraft through the Mode S transponders.
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The TCAS system is composed of several LRU’S, sensors, and antennas. The
TCAS computer is the focus of the TCAS system. It communicates,hi-directionally, with the two Mode S transponders, though four ARINC 429buses. Air data information, from the AZ-81O digital air data computers, ispassed through the Mode S transponders to the TCAS computer on these buses.
The TCAS computer also communicates traffic and resolution advisories, inARINC 429 format, with the three symbol generators on two high speed buses.The flight data recorder data acquisition unit is also tied to one of thesebuses to record all resolution advisories issued to the flight crew.
The TCAS computer receives absolute altitude data directly from the twoRT-300 radio altimeters. This altitude information is communicated to theTCAS computer on two ARINC 552 analog buses. A “radio altitude valid”discrete also communicates each RT-300’s validity to the TCAS computer.
In addition to the two radio altitude antennas, the TCAS system relies onsix other antennas for operation. Two of these antennas are driven by thereceiver/transmitter located in the TCAS computer. These are the aircrafttop-mounted directional antenna and the bottom mounted omni-directionalantenna. Both of these antennas operate in the L-band. (The (-902) TCAScomputer is certified for a dual (top and bottom) directional antennainstallation.)
Each Mode S transponder also communicates through two dedicatedomni-directional transmit/receive L-band antennas. Two of the antennas aremounted on the top of the aircraft and the other two are mounted on thebottom of the aircraft.
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Pilot interface with the TCAS system is made through the dual Gablestransponder control heads and the TCAS adapter panel located on the centerconsole. The TCAS adapter panel is not tied directly to the TCAS computer,rather is situated in series between the Mode S transponders and the Mode Scontrol heads. The TCAS computer is located downstream from the Mode Stransponders. All control data is passed to the TCAS computer through thefour ARINC 429 buses linking the transponders to the TCAS computer.
The TCAS computer also receives discrete data from the landing gear up/downand weight-on-wheels switches. Gear up/down logic is used in the correctionof the lower antenna beam pattern. Weight-on-wheels logic is used to movethe TCAS system into a “standby” mode while on the ground if the system hasbeen so pin-programmed.
TCAS failure information is displayed on the CAS as “TCAS Fail”. Thisinformation is passed to the FWC over ASCB from the SG words. (TCAStransmits failure data to the SG’S on ARINC 429.)
To run TCAS self-test, transponders should be in STBY and the TCAS adapterpanel should be in TA or TA/RA mode. While weight is on the wheels, pressingthe test switch on the transponder control panel will execute the TCAS self-test. Depression of the test switch for greater than 8 seconds causes theextended maintenance mode/failure page to be displayed in place of the TAdisplay on the System Page.
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-u
RadtoAllimeler I
tl--tl:0:DADC I
SCI SC3 SC2I I
QEIllllllnolllIIIIMNI10P lCASDireclionol Anlenno
Q
lll!llllnill
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OMlnllll OIOMOII
11
, 7E 000000000000 0
I ‘i!! oI;ii
I I I 1 WA Okeluj en (m I I-.
~“:, I I RAflACi@cj b (42S) I I[ 1 ICAS bmldkd I “n” I Twsmldw.– I I
Pilol/Copilo{Audio ConlrolPonels
—::::
Cc.aHm@emdW@! On-s CAsclelu ~ @MOhmAuSoSpltmf+,ot,~ ~--l-.. P..-l.-,,m. o--~l-a’- ~-”1-. P--l-oller
~--e” Rodiotlimeler 2
,qx”y Lvrn,r”ller, Swlem PO* AA. OscJOyCkdc
-“p.!”, = Ulapl!l, !.!ri!wu .Sy$lmlP.3JeAdoCMw Oilmrc
ma o J5#-~ ,0 .-1(X h$tdw
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~ ‘ii_~:5:;->m- IJ
-0lx Sul (42s) -L9 0
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enno
I
vi Mode S 2
wMode S 1
II *II 1
I@o
I
7$ ‘~+zijiq ,, . ,I ..-.-,.. -,...- .. . . .... . .. . ---- - --- . .
~ ‘“’’’’””’”’””””’4Hi
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I Callm% CaAtdIn●dvullllc.mw , I I SKOnaolv(CIMS-*]m$
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~pl Jg31 ‘“des‘O”’’O’’”sJ?@e !)@?
G-IV TCAS Syslem
Figure L-1
l-MsmNsx Pt10$ lCAS
Lfrc 10P flue W+ ANIINW
;3
i
43a
tCAS lCA$wn urrou PUIG Sollou ANIINM
m
-V Ol$PIAV
lCASmm muc
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I
tII SW2
s9
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81 AulrJAl sumcssAoN11 CMAs% OaI SlcNu cm
—
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iiidl
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+ wCmoICA$ N$l
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I
1111 Il’-
Sc moov am 1NIIIUNSC Sooo PcmronuAnct
lrulr Sraus5 :%@ COAA4NI$c CIAO-WA US ~OSA
m.. -----------1[ 1A~V SMIU$ I1@c mAaSrlAv SVAIUS tlx 1A OISJWV SIAIIJS Z sat SC J
lJ WADSFIAV SVAW$ t JIA JIA
n ~
uAt/k&–ti-mEAAAl I
u uld--l3-
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‘.. llc~$sl I
Pmo@MrmuSU ?ScUclIM 42$s4
WrM ]50~-=- 11,,, ..-.
I
I 1- -u ----tin.-,,,. -Allmtlnum1e M 41 II I
‘~- ‘“=’“-” - ‘-......-----.---
Ilop 8NICII$M
-L-J “uI
SA
EN
I AnNcmN Mx v V*ID (W)
sol I OAoc I*U1
num- > Ilm . .I ------- —— lRw$PcslM n lRMsPotaR II I
S.Q[ 2 O,oc W*U1 I
G-IV TCAS SYSTEM WIRING DIAGRAM (TYPICAL) - ONLY SIDE 1 TRANSPONDER SHOWN
Figure L-2
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1.3 Mechanical Installation Information
TCAS Computer
The TCAS computer is mounted in an ARINC 600 6 MCU tray. Forced air coolingis required for the TCAS computer. The ARINC 600 tray is available with anintegral cooling fan. The fan can be located in various positions aroundthe tray (P/N dependent) to accommodate aircraft spacing requirements.
The TCAS computer must be located inside the pressure vessel.
Refer to TCAS System Description and Installation Manual, HoneywellPublication 15-3841-05, for detailed installation information. See Table L-1.
Antennas
Placement of the upper directional antenna on the G-IV was established byGulfstream to be on the aircraft centerline at approximately STA 180.Refer to TCAS System Description and Installation Manual, HoneywellPublication 15-3841-05 for additional requirements. See Table L-1.
Lower directional antenna placement is approximately at STA 140.5.
1.4 Environmental Qualifications
The TCAS computer has been tested to the following DO-160B environmentalqualifications. These qualifications meet or exceed the requirements ofARINC 735, attachment 13.
DO-160BSection Environment TCAS Com~uter
4 Temperature and Altitude CAT A2
5 Temperature Variation CAT B
6 Humidity CAT A
7 Shock (Operate and Sustained) YES
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DO-160BSection Environment TCAS ComDuter
8 Vibration CAT O
10 Waterproofness CAT X
11 Fluid Susceptibility CAT X
12 Sand and Dust CAT X
13 Fungus CAT X
14 Salt Spray CAT X
15 Magnetic Effect CAT Z
16 Power Input CAT A
17 Conducted Voltage Transient CAT A
18 Audio Frequency Conducted CAT Z
Susceptibility
19 Induced Signal Susceptibility CAT Z
20 Radio Frequency Susceptibility CAT Z(Radiated and Conducted)
21 Spurious Radio Frequency Emission CAT Z
22 Lightning
Signal and Power Cables CAT K
Antenna Cables CAT M
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TCAS
TCAS Computer
:’
,.m
mm.6
,1
..’
Table L-1Equipment List
,.
... .,.
., . m,I . . .
.,>”,
“,m:, -.:l,i ,.... - 1. i.. il . I IJ :::-1.- i.:. *I:; .!..::~i ..,i ! .: ~.l.ill..:,:
:,!, I.1.. ,’ 1:.:,: .:,s .
:. :. :.......,:. .::1
,. :-.:.
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Directions”
.1!!11‘:.. l,!
.:. -,-.-11-
.. ... -
. .
.. .
. .
.
=. . .,, ;..:.,:
I .1..i
!,:.-:.,:;
ma .
Table L-1 (continued,TCAS Equipment List
...~
. . ..-i1.
,. 1.’: !il...l
. . .. .
> .,I 11’1,1 .,, ,, ..* :: !
m.
... . . ,
. .m,
. .
,,
.,!
. .
,.
. ,, . .. . . 1 . . .
.q. . .
. . .
.’.
. . . . .. .. .
. . ... .. .
..-.
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Table L-1 (continued)TCAS Equipment List
Omni-directional Antenna (Single Directional Installation only)
,m.,11,.- ,: [L,.~i . Il.. i,,,I ~,, ...il I(!l:-:,,r. .---- .:.. :.
:>.:.!I .~:., :1:...I ,’1: ~.1,..1 i: ....l’~~i; I .“,:,..:. :
. ...,.. —. -, —-. ,-— .,. —- .— ,& ,-- !-— ,.. — —, —.,., —-
..— .—... — .—. — —-— —.— —— ..—
~, ,. m,. .
,. . . . .
,.,’; . :. i. I.:m .; .ml.I ‘.. ‘.-
. . . ‘..\, : . ,. . . I :: ‘1:. ,: ., . . I ,’.’,.! .:.,.
. . I ‘ : :: ‘u.- ..: .. ..
Omni-directional Antenna with Directional Fit and Form (Single DirectionalInstallation Provisioned for Dual Directional Antennas)
I& :11.,1: I ,. :11I:!: .. .:.-‘1.. .!.”
:,
,!i,:r .(I,
.-. ..-..-
1:.~.l.. .
1’ :11 .! I “ I ‘ : I ‘ 1 ‘ ‘. . . . . :“ .
.- , ,....,: - !r..: !-.1.-, ..:.:...1 ,,rl.1,..I i.,t..i,.!ll:~lll
..- -.. .
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1.5 Power and Weiqht Specification
Power for the TCAS computer is taken from the aircraft 115 VAC 400 Hz powerbus. A single circuit breaker switches power to the TCAS computer. TheTCAS computer uses 80 Watts maximum of power.
The maximum weight of the TCAS computer is 15.0 kg (33 pounds).
1.6 Additional Interface Requirements
New part number display controllers, symbol generators, and fault warningcomputers must be installed when the aircraft is updated to operate withTCAS . The required part numbers are as follows:
UnitNumber ~ Part Number
65/C65/E65 SG-884 Symbol Generator 7008570-904
115/cl15 DC-884 Display Controller 7007540-941/-942
134/c134 FC-880 Fault Warning Computer 7007484-905
All mounting requirements specified in previous sections of this documentremain the same. This appendix defines the additional requirements for theaddition of the TCAS function.
1.7 Interconnect Information
Interconnect information for the TCAS computer follows. Completeinterconnect information is provided for the TCAS computer as well asmodifications required to baseline and other retrofit equipment.
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TCAS COMPUTER
IOB
~ Function Connector Pin Connects To
LEFT TOP INSERT
(I) TOP ANTENNA - 0 193LTP-1 (NOTE l)------------- 194J1-1
(I) TOP ANTENNA - 90 -2 (NOTE l)------------- 194J1-2(I) TOP ANTENNA - 180 -3 [NOTE l)------------- 194JI-3(1) TOP ANTENNA - 270 193LTP-4 (NOTE l)------------- 194J1-4
LT MIDDLE INSERT
(I) BOTTOM ANT O)OMNI 193 LMP1j (NOTE l)------------- 195JI-1(I) BOTTOM ANT - 90 (NOTE 4)------------- 195JI-2(I) BOTTOM ANT - 180 -3 (NOTE 4)------------- 195J1-3
(I) BOTTOM ANT - 270 193LMP-4 (NOTE 4)------------- 195J1-4
LT BOTTOM INSERT
(P) 1~:05V~CPRIMARY 193LBP-1 (20)----------------- A/C 115 VAC POWER
FUTURE SPARE -2 ----NCRESERVED (28 VDC RETURN) -3 ----NCFUTURE SPARE ----NC
(0) 115 VAC (H) :: (20)----------------- TRAY INTEGRAL FANOUTPUT TO FANFUTURE SPARE -6 ----NC
(P) 115 VAC PRIMARY -7 (12)----------------- A/C 115 VAC(COLD) POWER GROUND
(I) SIGNAL GROUND -8 (12)----------------- A/C SIGNAL GND(0) 115 VAC (C) -9 (16)----------------- TRAY INTEGRAL FAN
OUTPUT TO FANRESERVED {28 VDC -lo ----NCPRIMARY POWER)
(I) CHASSIS GROUND -11 (16)----------------- A/CCHASSIS GND(I) SUPPRESSION PULSE -12 (NOTE 2)------------- XPDR#2 (PIN BP-12)(0) SUPPRESSION PULSE 193LBP-13 ----NC
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TCAS COMPUTER (cent)
106& Function Connector Pin Connects To
RIGHT TOP INSERT
THIS INSERT IS BLANK
RT MIDDLE INSERT
RESERVED 193RMP-lA ----NC
RESERVED -lB ----NCRESERVED -lC ----NCRESERVED -lD ----NC
(0) TA DISPLAY ENBL * -lE ----NC(0) AURAL ADVISORY DISCRETE -lF ----NC
(CORRECTIVE) *SPARE -lG ----NCSPARE -lH ----NC
(I) CLIMB INHIBIT -lJ ----NCDISCRETE 1 *
(0) AURAL ADVISORY DISCRETE -lK ----NC(PREVENTIVE) *
(0) AURAL ADVISORY DISCRETE -2A ----NC(TFFK ALERT) *
SPARE -2B ----NCSPARE -2C ----NC
(I) ADVISORY/ANNOUNCE COMMON -ZD ----NC
SPARE -2E ----NC
(0) SYNTHESIZED VOICE -2F ----NC
80HM (H)
(0) SYNTHESIZED VOICE 193RMP-2G ----NC
(0) 8 OHM (L)
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TCAS COMPUTER (cent)
IOB& Function Connector Pin Connects To
RT MIDDLE INSERT
(I) RADIO ALTIMETER 1
J
193RMP-2H (22)--~i- ----------- 20J1-XARINC 552 SIGNAL (H)
(I) RADIO ALTIMETER 1 -2J (22)--L!- ----------- 20J1-NARINC 552 SIGNAL (L)
(1) RAD ALT 1 VALID -2K (22)----------------- 20J1-Y(28 V/OPEN)
(0) VISUAL ANNUNCIATOR -3A (22)------- --------- l15J1-m,(CORRECTIVE) *
I
Cl15J1-m(0) VISUAL ANNUNCIATOR -3B (22)-------
(PREVENTIVE) *(0) VISUAL ANNUNCIATOR -3C (22)-------
(TFFK ALERT) *(I) ADVISORY/ANNUN CANCEL * -3D ----NC
FUTURE SPARE -3E ----NC(0) SYNTHESIZED VOICE
$}
-3F (22)---I;------------600 OHM (H) A/C AUDIO SYSTEM
(0) SYNTHESIZED VOICE -3G (22)--12-- ----------
600 OHM (L)
SHIELD GND -------JFUTURE SPARE. -3H ----NCFUTURE SPARE -3J ----NCFUTURE SPARE -3K ----NC
(I) RESERVED - PITCH ATTITUDE -4A ----NCSYNCHRO (X)
(I) RESERVED - PITCH ATTITUDE -4B ----NC
SYNCHRO (Y)
(I) RESERVED - PITCH ATTITUDE -4C ----NCSYNCHRO (Z)RESERVED - ATTITUDE 193RMP-4D ----NCSHIELD GROUND
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TCAS COMPUTER (cent)
IOB~ Function Connector Pin Connects TQ
RT MIDDLE INSERT
(1) RESERVED - ROLL 193RMP-4E ----NCATTITUDE SYNCHRO (X)
(I) RESERVED - ROLL -4F ----NC
ATTITUDE SYNCHRO (Y)
(I) RESERVED - ROLL -4G ----NC
ATTITUDE SYNCHRO (Z)
(I) RESERVED - ATTITUDE REF -4H - ---NC
26 VAC (H)(I) RESERVED - ATTITUDE REF -4J ----NC
26VAC (L)(I) RESERVED - ATTITUDE VALID -4K ----NC(I) RESERVED - MAG HEADING -5A ----NC
SYNCHRO (X)
(I) RESERVED - MAG HEADING -5B ----NC
SYNCHRO (Y)
(I) RESERVED - MAG HEADING -5C ----NCSYNCHRO (Z)
FUTURE SPARE -5D ----NCFUTURE SPARE -5E ----NCFUTURE SPARE -5F ----NCFUTURE SPARE -5G ----NC
(0) RESERVED - MAG HEADING -5H ----NC26 VAC REF (H)
(0) RESERVED - 193RMP-5J ----NC
MAG HEADING 26 VAC REF (L)
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TCAS COMPUTER (cent)
IOB~ Function Connector Pin Connects To
RT MIDDLE INSERT
(I) WOW* 193RMP-5K (22)----------------- I!~~!~flCKER
(I) RESERVED - PERF LIMIT -6A ----NCARINC 429 (H)
(I) RESERVED - PERF LIMIT -6B ----NCARINC 429 (L)
(I) MAG HEADING VALID -6C ----NC
DISC (28 V/OPEN)(I) PERFORMANCE LIMIT DISCRETE -6D ----NC(I) A/C ALT LIMIT - 2000 FEET * -6E (22)----------------- 193RMP-6K(I) A/C ALT LIMIT - 4000 FEET * -6F (22)----------------- 193RMP-6K(I) A/C ALT LIMIT - 8000 FEET * -6G (22)----------------- 193RMP-6K(I) A/C ALT LIMIT - -6H ----NC
16000 FEET *(I) A/C ALT LIMIT - -6J (22)----------------- 193RMP-6K
32000 FEET *(0) PROGRAM COMMON -6K (22)----------------- 193RMP-6E,
193RMP-6F,
193RMP-6G,
193RMP-6J,
193RMP-7E,
193RMP-7J,
193RMP-12C,
193RMP-13E,
193RMP-14C
(I) RESERVED - MAG HEAD/ATT -7A ----NC
ARINC 429 (H)
(I) RESERVED - 193RMP-7B ----NC
MAG HEAD/ATTARINC 429 (L)
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(B)
(B)
(1)
(B)
(B)
(1)
(o)(o)
TCAS COMPUTER (cent}
Function Connector Pin
RT MIDDLE INSERT
TA~RA DISPLAY #l
$
193 RMP-7C (22)--fi- -------- ---
ARINC 429 HI SPEED (H)TA/RA DISPLAY #l -7D (22) --~J - -----------
ARINC 429 HI
SPEED (L) SHIELD GND ------rTA DISPLAY #l STATUS ;;: ~~:!~----------------
FUTURE SPARETA/RA DISPLAY #Z
t
-7G (22) -fi-- -----------
ARINC 429 HI SPEED (H) !1II
TA/RA DISPLAY #2 -7H (22)-~\-*
‘1
-----------ARINC 429 HISPEED (L) SHIELD GND ------
TA DISPLAY #2 STATUS -7J (22) -----------------
FUTURE SPARE -7K ----NC
DATA LOADER XMIT A -8A ----NC
DATA LOADER XMIT B -8% ----NC
DATA LOADER SPARE -8C ----NC
DATA LOADER SPARE -80 ----NC
DATA LOADER SPARE -8E ----NC
DATA LOADER SPARE -8F ----NC
DATA LOADER SPARE -8G ----NC
DATA LOAOER SPARE -8H ----NC
DATA LOADER SPARE 193RMP-8~ ----NC
Connects To
65/E65JlA-36
65/E65JlA-47
193RMP-6K
C65J1A-36,FLIGHT DATARECORDER DAUC65J1A-47,FLIGHT DATARECORDER DAU193RMP-6K
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TCAS COMPUTER (cent)
IOB~ Function Connector Pin ~nects To
RT MIDDLE INSERT
DATA LOADER SPARE 193RMP-8K ----NC(I) DATA LOADER RECEIVE A -9A ----NC(I) DATA LOADER RECEIVE B -9B ----NC
DATA LOADER SPARE -9C ----NCDATA LOADER SPARE -9D ----NCDATA LOADER SPARE -9E ----NCDATA LOADER SPARE -9F ----NCDATA LOADER SPARE -9G ----NCDATA LOADER SPARE -9H ----NCDATA LOADER SPARE -9J ----NCDATA LOADER SPARE -9K ----NC
(I) WEATHER RADAR -1OA ----NCASPECT RATIO *
(I) WEATHER RADAR -1OB ----NCINTERFACE ENABLE *
(I) WEATHER RADAR -1OC ----NCRNG SEL 8 (TTL)
(I) WEATHER RADAR -1OD ----NCRNG SEL 4 (TTL)
(I) WEATHER RADAR -1OE ----NCRNG SEL 2 (TTL)
(I) WEATHER RADAR 193RMP-1OF ----NCRNG SEL 1 (TTL)
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TCAS COMPUTER (cent)
IOB& Function Connector Pin Connects ?0
RT MIDDLE INSERT
(I) RED VIDEO (P) TTL 193RMP-1OG ----NC(I) RED VIDEO (N) TTL -1OH ----NC(I) GRN VIDEO (P) TTL -1OJ ----NC(I) GRN VIDEO (N) TTL -1OK ----NC(I) BLUE VID (P) TTL -11A ----NC(I) BLUE VID (N) TTL -llB ----NC(I) VIDEO ENABLE (POS) TTL -llC ----NC(I) VIDEO ENABLE (NEG) TTL -llD ----NC
SHIELD -llE ----NC(I) HORIZONTAL REF (POS) TTL -llF ----NC(I) HORIZONTAL REF (NEG) TTL -llG ----NC(I) VERTICAL REF (POS) TTL -llH ----NC(I) VERTICAL REF (NEG) TTL -llJ ----NC(I) DC RETURN -llK ----NC(1) WEATHER RADAR STBY DISC * -12A ----NC(I) RADALT 552/COLLINS * -12B ----NC(I) TA/RA BLOCK -12C (22)------------------ 193RMP-6K
TRANSFER PROG *(I) A/C TYPE - 1 * -12D ----NC(I) A/C TYPE - 0 * -12E ----NC(I) VOLUME - 1 * -12F ----NC(I) VOLUME - 0 * -12G ----NC
USER DEFINED -12H ----NCUSER DEFINED -12J ----NCUSER DEFINED -12K ----NC
(0) RA DISPLAY #1 193RMP-13A ----NC
ARINC 429 LO SPEEII - (HI)
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TCAS COMPUTER (cent)
10B_P_ Function Connector Pin Connects To
RT MIDDLE INSERT
(0) RA DISPLAY #1 193RMP-13B ----NCARINC 429 LOSPEED - (LO)
(0) RA DISPLAY #2 -13C ----NCARINC 429 LO
SPEEIl - (HI)(0) RA DISPLAY #2 -13D ----NC
ARINC 429 LOSPEED - (LO)
(I) RAT;Aj~L~Y #2 -13E (22)----------------- 193wp-6K
(I) LANDING GEAR DOWN * -13F (22)----------------- GEAR HANDLE SWITCH(1) CLIM8 INHIBIT -13G ----NC
DISCRETE 2 *(1) RADIO ALTIMETER #1 -13H ----NC
ARINC 429 (HI)(I) RADIO ALTIMETER #1 -13J ----NC
ARINC 429 (LO)(1) TCAS SYSTEM STATUS DISC * -13K ----NC(0) TX COORO #2
$
-14A (22)--i~-- ---------- goTp-5EARINC 429 Hi SPEED (HI)
(0) TX COORD #2 -14B (22)----- ----------- 90Tp-5F
ARINC 429 HI SPEED (LO)(I) RA DISPLAY #1 STATUS -14c (22)----------------- 193fU4P-6K(I) RESERVED 193RMP-140 ----NC
ARINt 429 (HI)
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TCAS COMPUTER (cent)
IOB& Function Connector Pin Connects To
RT MIDDLE INSERT
(I) R:~;R~;~)ARINC 193RMP-14E ----NC
(I) XT COORD #1
J
-14F (22)--~1-- ---------- 89TP-5GARINC 429 HI SPEED (HI)
(1) XT COORD #1 -14G (22)---!!------------ 89TP-5HARINC 429 HI SPEED (LO)
(I) XT COORD #2
t
-14H (22)--i~l------------ 90Tp-5GARINC 429 HI SPEED (HI)
(I) XT COORD #2 -14J (22)------ ---------- 90TP-5HARINC 429 HI SPEED (LO)FUTURE SPARE -14K ----NCFUTURE SPARE -15A ----NCFUTURE SPARE -15B ----NCFUTURE SPARE -15C ----NCFUTURE SPARE -15D ----NCFUTURE SPARE -15E ----NCFUTURE SPARE -15F ----NCFUTURE SPARE -15G ----NCFUTURE SPARE -15H ----NC
(0) TX COORD #1
$
-15J (22)--~i- ----------- 89TP-5E
ARINC 429 Hi SPEED (HI)(0) TX COORD #1 193RMP-15K (22)--’-!-
1
----------- 89TP-5FARINC 429 HI SPEED (LO)
SHIELD GND ----- -
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TCAS COMPUTER (cent)
IOB~ Function Connector Pin ~nects To
RT BOTTOM INSERT
FUTURE SPARE 193RBP-lA ----NCFUTURE SPARE -lB ----NCFUTURE SPARE -lC ----NCFUTURE SPARE -lD ----NCFUTURE SPARE -lE ----NCFUTURE SPARE -lF ----NCFUTURE SPARE -lG ----NC
(0) RA GUIDANCE -lH ----NCLBL 270 BIT 18SERIES/SHUNT
(0) RA GUIDANCE -lJ ----NCLBL 270 BIT 19SERIES/SHUNT
(0) RA GUIDANCE -lK ----NC
LBL 270 BIT 20
SERIES/SHUNT
FUTURE SPARE -2A - ---NCFUTURE SPARE -2B ----NCFUTURE SPARE -2C ----NC
FUTURE SPARE -2D ----NCFUTURE SPARE -2E ----NC
FUTURE SPARE -2F ----NCFUTURE SPARE -2G ----NC
(0) RA GUIDANCE -2H ----NCLBL 270 BIT 21SERIES/SHUNT
(0) RA GUIDANCE -2J ----NCLBL 270 BIT 22SERIES/SHUNT
(0) RA GUIDANCE 193RBP-2K ----NCLBL 270 BIT 22SERIES/SHUNT
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TCAS COMPUTER (cent)
IOB_P_ Function Connector Pin Connects To
RT BOTTOM INSERT
(1) RADIO ALTIMETER 2
!
193RBP-3A (22)---~i- ---------- C20J1-xARINC 552 SIGNAL (H)
(I) RADIOALTIMETER 2 -3B (22)---L~- ---------- C20J1-NARINC 552 SIGNAL (L)
(I) RAD ALT 2 VALID -3C (22)----------------- C20J1-Y(28 V/OPEN)
(I) RADIO ALTIMETER -3D ----NC#2 ARINC 429 (H)
(I) RADIO ALTIMETER -3E ----NC#2 ARINC 429 (L)FUTURE SPARE -3F ----NCFUTURE SPARE -3G ----NC
(0) RA GUIDANCE LBL 270 -3H ----NCBIT 24 SERIES/SHUNT
(0) RA GUIDANCE LBL 270 -3J ----NCBIT 25 SERIES/SHUNT
(0) RA GUIDANCE LBL 270 -3K ----NCBIT 26 SERIES/SHUNT
(I) RESERVED DISCRETE -4A ----NC(I) RESERVED DISCRETE -4B ----NC(I) RESERVED DISCRETE -4C ----NC(I) RESERVED DISCRETE 193RBP-4D ----NC
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IOBP
(I)(I)(o)
(o)
(o)
(I)(I)(1)(I)
(I)(I)(I)(I)(1)(I)
TCAS COMPUTER (cent)
Function Connector Pin Con~ects To
RT BOTTOM INSERT
RESERVED DISCRETE 193RBP-4E ----NCRESERVED DISCRETE -4F ----NCRA GUIDANCELBL 270 -4H ----NC
BIT 27 SERIES/SHUNTRA GUIDANCE LBL 270 -4J ----NC
BIT 28 SERIES/SHUNT
RA GUIDANCELBL 270 -4K ----NCBIT 29 SERIES/SHUNT
ADVIS INHIBIT DISCRETE 1 * -5A ----NC
ADVIS INHIBIT DISCRETE 2 * -5B ----NC
ADVIS INHIBIT DISCRETE 3 * -5C ----NC
ADVIS INHIBIT DISCRETE 4 * -5D (22)----------------- 148J1A-096,
GROUND PROXINCR CLIMB INHIBIT 1 * -5E ----NCINCR CLIMB INHIBIT 2 * -5F ----NCINCR CLIMB INHIBIT 3 * -5G ----NCINCR CLIMB INHIBIT 4 * -5H ----NCCLIMB INHIBIT DISCRETE 3 * -5J ----NCCLIMB INHIBIT 193RBP-5K ----NCDISCRETE 4 *
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IOB~
(I)
(I)(I)(I)(o)(o)(1)(I)
(I)(I)(I)(I)(I)
(I)(I)(I)(I)
TCAS COMPUTER (cent)
Function Connector Pin
RT BOTTOM INSERT
DATA LOADER 193RBP-6A ----NCDISCRETE 1
DATA LOADER DISCRETE 2 -6B ----NCRESERVED DISCRETE -6C ----NC
RESERVED DISCRETE -6D ----NCCFDS ARINC 429 (HI) -6E ----NCCFDS ARINC 429 (LO) -6F ----NCCFDSARINC 429 (HI) -6G ----NCCFDSARINC 429 (LO) -6H ----NCFUTURE SPARE -6J ----NCFUTURE SPARE .6K - ---NCAUDIO VOLUME PROGRAM PIN -7A ----NC NOTE 5
AUDIO VOLUME PROGRAM PIN -7B ----NC NOTE 5AUDIO VOLUME PROGRAM PIN -7C ----NC NOTE 5AUDIO TONE ENABLE * -7D ----NCGROUND DISPLAY -7E (22)-----------
MODE PROGRAM *
DISPLAY ALL TRAFFIC * -7F ----NCCABLE DELAY SGN * -7G - ---NC NOTE 1CABLE DELAY MSB * -7H ----NC NOTE 1
CABLE DELAY LSB * 193RBP-7J ----NC NOTE 1
Connects To
-- 193RBP-7K
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TCAS COMPUTER (cent)
10B.P_ Function Connector Pin ~lects To
RT BOTTOM INSERT
(0) PROGRAM COMMON 193RBP-7K (22)----------------- 193RBP-7E, l15J1-j,Cl15J1-j, 65J1A-14,C65J1A-14, E65J1A-14
(I) RESERVED PROGRAM PIN -8A ----NC(I) RESERVED PROGRAM PIN -8B ----NC(I) RESERVED PROGRAM PIN -8C ----NC(I) RESERVED PROGRAM PIN -8D ----NC(I) RESERVED PROGRAM PIN -8E ----NC(1) TA/RA DISPLAY -8F ----NC
SYMBOL MAX 16 *(I) TA/RA DISPLAY -8G ----NC
SYMBOL MAX 8 *(I) TA/RA DISPLAY -8H ----NC
1
NOTE 3
SYMBOL MAX 4 *(1) TA/RA DISPLAY -8J ----NC
SYMBOL MAX 2 *(1) TA/RA DISPLAY -8K ----NC
SYMBOL MAX 1 *RESERVED FOR - 9A ----NC
BENCH TEST
193RBP-7A ----NC
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TCAS TOP ANTENNA
IOB~ Function Connector Pin Connects IQ
(I) ANTENNA 0° 194J1-1 (NOTE l)------------- 193LTP-1
(I) ANTENNA 90° -2 (NOTE l)------------- 193LTP-2
(I) ANTENNA 180° -3 (NOTE l)------------- 193LTP-3
(1) ANTENNA 270° 194J1-4 (NOTE l)------------- 193LTP-4
TCAS BOTTOM ANTENNA
IOB
_P_ Function Connector Pin Connects 10
(I) ANTENNA OO/OMNI 195J1-1 (NOTE l)------------- 193LMP-1(I) ANTENNA 90° -2 (NOTE 4)------------- 193LMP-2(I) ANTENNA 180° -3 (NOTE 4)------------- 193LMP-3(I) ANTENNA 270° 195J1-4 (NOTE 4)------------- 193LMP-4
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DISPLAY CONTROLLER NO. 1
IOB& Function Connector Pin Connects To
(1) TCAS INSTALLEO l15J1-j (22)----------------- 193RBP-7K
‘1) ‘~&:;STEM PAGEl15J1-m (22)----------------- 193RBP-3A,
193RMP-3B,193RMP-3C
DISPLAY CONTROLLER NO. 2
IOB~ Function Connector Pin Connects To
(I] TCAS INSTALLED Cl15J1-j (22)----------------- 193RBP-7K(I) T;;ME~;STEM PAGE Cl15J1-m (22)----------------- 193RBP-3A,
193RMP-3B,193RMP-3C
SYMBOL GENERATOR NO. 1
IOB& Function Connector Pin Connects To
(I) TCAS INSTALLED 65J1A-14 (22)------ ---------- 193RBP-7K(B) TA/RA DISPLAY #l -36 (22)--~-
:
---------- 193RMP-7CARINC 429 HI SPEED (Ii) It
(B) TA/RA DISPLAY #1 65J1A-47 (22)--$ ---------- 193RMP-7DARINC 429 HI SPEED (L)
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SYMBOL GENERATOR NO. 2
IOB~ MLdiQn ~ Connects To
(I) TCAS INSTALLED C6SJ1A-14 (22) ----- ----------- 193 RBP-7K
(B} TA/RA DISPLAY #2
t
-36 (22)--fi- ---------- 193 RMP-7G
ARINC 429 HI SPEED {H)(B) TA/RA DISPLAY #2 C65J1A-47 (22)--:- ----------- 193RMP-7H
ARINC 429 HI SPEED (L)
SYMBOL GENERATOR NO. 3
IOB~ Function Connector Pin Connects To
{1) TCAS INSTALLED E65J1A-14 (22)----- ----------- 193RBP-7K(B) TA/RA llISPLAY #1
!
-36 (22)--fi- ---------- 193 RMP-7C
ARINC 429 HI SPEED (H)(B) TA/RA DISPLAY #1 E65JlA-47 (22)--~’- ----------- 193RMP-7D
ARINC 429 HI SPEED (L)
RADIO ALTIMETER NO. I
IOB~ Function Connector Pin Connects To
$(0) RAD ALT #1 OUTPUT (L) 20J1-N (22)--fi- ----------- 193RMP-2J(0) RAO ALT #1 OUTPUT (H) -X (22)--w- ----------- 193RMP-2H(0) RAD ALT #1 VALID 20J1-Y (22)----------------- 193RMP-2K
RADIO ALTIMETER NO. 2
IOB& Function $onnector Pin Connects To
$(t)) RAD ALT #2 OUTPUT (L) C20J1-N (22)---fi- ---------- 193RBP-3B(0) RAD ALT #2 OUTPUT (H) -x (22)--= --”------- 193RBP-3A(0) RAD ALT #2 VALID C20J1-Y (22)----------------- 193RBP-3C
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DIGITAL AIR DATA NO. 1
IOB~ Function Connector Pin Connects To
(B) AIR DATA OUTPUT #2
1
9J1B-70 (22)--fi- ----------- C65J1A-39,ARINC 429 LO SPEED (ii) ~i E65J1A-39,
It148J1A-57,
II XPDR 1 TP-7H,XPDR 2 MP-5A
(B) AIR DATA OUTPUT #2 9J1B-71 (22)-’1-- -----------
T
C65J1A-40,ARINC 429 LO SPEEII (L) E65J1A-40,
SHIELD GND ------ 148J1A-58,XPDR 1 TP-7J,XPDR 2 MP-5B
DIGITAL AIR DATA NO. 2
IOB~ Function Connector Pin Connects To
(B) AIR DATA OUTPUT #2 C9J1B-70 (22)-a-ll
1
----------- C65J1B-39,ARINC 429 LO SPEED (H) E65J1B-39,
148J1B-57,II XPDR 1 MP-5A,11 XPDR 2 TP-7H
(B) AIR DATA OUTPUT #2 C9J1B-71 (22)-JJ-
Y
----------- C65J1B-40,ARINC 429 LO SPEED (L) E65J1B-40,
SHIELD GND ------ 148J1B-58,XPDR 1 MP-5B,XPDR 2 TP-7J
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NOTES
1. The following coaxial cable types meet TCAS directional and
omni -directional antennas’ interface requirements:
Outside Attenuation
Cable type/ Diameter Weight at 1 MHz Time Delay
Manufacturer @l&lE&l ~ m m
RG142/Various 0.206 0.047 0.0130 1.44
RG142B/Various 0.195 0.050 0.0130 1.44
RG393/Various 0.195 0.050 0.0075 1.44
311201/ECS 0.320 0.086 0.0059 1.31
AA5886/Times 0.390 0.150 0.0049 1.27
AA5887/Times 0.270 0.075 0.0072 1.27
AA5888/Times 0.230 0.055 0.0083 1.27
The following two cables are specifically designed for TCAS/Mode S antenna
installations:
Electronic Cable Specialists cable P/N 310801: the RF loss on this cable is9.3 dBm/100 ft at 5 GHz of cable run. Bend radius is 2“. Weight is 15lbs/100ft. The mating connector is a crimp on type and is P/N CTS022. The
crimping tool is P/N 225020/5-1 with a die number Y-149. These cables maybe supplied with the connectors attached and complete loss and VSWRdocumentation is provided with each cable. In this instance, test cablesshould be installed to determine correct cable length. Although thispresents a more challenging installation problem, the end result is asuperior TCAS system.
PIC Wire and Cable P/N S22089: The RF loss on this cable is 9.5 dBm/100 ftof cable run at 5 GHz. Bend radius is 2.5”. Weight is 20 lbs/100 ft.Mating connectors are TBD.
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NOTES (continued~
If possible, bulkhead connectors should be avoided - especially those in anenvironment exposed to water, salt, fuels, hydraulic and deicing fluids,etc.. These agents cause rf connections to deteriorate with time andexposure level.
The TCAS computer provides compensation for differences in propagationdelay between the top and bottom antennas. Propagation delay is a functionof cable characteristic delay and cable length. If the difference inpropagation delay between the upper and lower antennas exceed 50 nS, cabledelay must be set on 193RBP-7G, 193RBP-7H, and 193RBP-7J.
Nominally, 40 feet difference in cable length would be needed to requiresetting the cable delay programming pins to other than OPEN’S. Since mostG-IV installations upper and lower TCAS antenna cable runs should be under
40 feet, setting these pins should not be required. For those installerswith unusual cable run requirements, refer to section K.9, Cable Delay forthe programming of these pins.
2 The TCAS computer is provided with an internal “T” to connect to thesuppression pulse bus. The TCAS computer is tied to the end of the
suppression pulse bus. The TDR-94D’s are provided with a single mutualsuppression bus input. See diagram below.
TCAS Mode S Mode S2 1
L-Band SuppressionPulse Bus
NC
3 These pins are not used in this installation as the maximum symbol limitwill be set within symbol generator software.
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NOTES (continued)
4 If a directional antenna is used for the lower antenna installation, the90°, 180°, and 270” coaxial line must be connected. The aircraft, however,
may be provisioned for a lower directional antenna. The 3 additionalcoaxial wires may be run and capped and stowed. They should @ beterminated if they are not used, as the TCAS computer interprets aterminated line as being connected to a directional antenna. -(902) TCAScomputers are certified to operate with either a bottom directional antenna(dual directional mode) or bottom omni-directional antenna (singledirectional). An omni-directional antenna with the same form and fit asthe directional antenna is available from Sensor Systems, Inc.. Thisallows the aircraft to be provisioned for the dual-directional installationand still function in a single directional (omni on the bottom)configuration.
5 Pins RBP-7A, RBP-7B, and RBP-7C program the power output level of the 8 0and 600 0 audio outputs. The table below shows the program setting and theresulting power level at each output for that setting.
Program Pins 600 0 Audio 8 Q Audio
7A 7B 7C dBm mW dBW W
11 16 40 6 4.011 : 13 20 3 2.0101 10 10 0 1.0100 75 -3 0.5011 4 2.5 -6 0.25010 1 1.25 -9 0.12001 -2 0.63 -12 0.06000 19 80 9 8.0
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1.8 Pin-Programmed Options
The following pin-programming options are available on the TCAS computer.
Refer to ARINC Characteristic 735, attachment 3B for a complete description
of all interwiring options:
Aircraft Altitude Limit
These pins select the “can’t climb” altitude in 2000 foot increments, up to62,000 feet. Pins RMP-6E through RMP-6J are jumpered to program common(RMP-6K) to set the limit. The limit set by the pins represents worst case.
Audio Tone Enable
When RBP-7D is tied to program common (RMP-7K), an audio tone is output onthe synthesized voice outputs just prior to the transmission of an auralresolution advisory.
Ground Display Mode
Connection of RBP-7E to program common (RBP-7K) indicates that the TCAScomputer unit should place itself in the “standby” mode while on the ground.With this pin in an “open” configuration, only traffic will be displayed tothe flight crew.
Display All Traffic
This discrete is used to set bit 27 (all traffic or TA/RA only bit) of label001 on the TA/RA display bus. The EFIS software is programmed to displayall traffic (OT/PT/TA/RA) regardless of the setting on this bit, and hencethis discrete.
Cable Delay
RBP-7G through RBP-7J convey to the TCAS computer the amount of differentialdelay between the top and bottom TCAS antenna cables. Tie RBP-7G to programcommon to add delay time to the bottom antenna; leave open to add delay timeto top antenna. Program RBP-7H and RBP-7J as follows to add time to TCAS:
RBP-7H/7J = OPEN/OPEN 0-50 nS; RBP-7H/J = OPEN/GND 51-150 nSRBP-7H/7J = GND/OPEN 151-250 nS; RBP-7H/J = GND/GND 251-350 nS
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1.8 Pin-Programmed Options (continued)
RA/TA Display Maximum
Pins RBP-8F through RPB-8K are used to encode the maximum number clf intruder
symbols to be presented on certain TA displays. In this installation,maximum number of intruder symbols will be set within the symbol generators.
ARINC/BCA 429 Display Format Select
This pin selects the label stream format to be output from the TCAS computerto the symbol generators. A “ground”onRMP-12C selects the BCA format.
ARINC 552/Collins BCA Radio Altitude Format Select
This pin selects the analog format to be received by the TCAS computer. An“open” on RMP-12B selects ARINC 552 format.
1.9 Discrete InDuts
The TCAS computer allows discrete inputs to account for varying aircraft
performance conditions and to inhibit various TCAS computer operationsduring hazardous conditions.
Performance Limit
Pin RMP-6D has been assigned to provide the TCAS computer with an input froma flight management computer (FMC). The FMC would determine when theaircraft can no longer attain a 1500 fpm rate of climb and cause an “open”
condition on this pin. If performance is not limited, the pin should bepulled to ground. When the input is an “open”, the climb is limited whilethe altitude of the aircraft is above the value set in the aircraft altitudelimit program pins.
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Increase Climb Inhibit
Four discretes; RBP-5E through RBP-5H, are provided to indicate that theaircraft’s climb performance is limited below 2500 fpm.
Advisory Inhibit
Four discretes; RBP-5A through RBP-5D, are provided to inhibit normaloperation during hazardous conditions. Grounding RBP-5A or RBP-5D causesthe TCAS computer to go to the “standby” mode. A ground at RBP-5C causes
the TCAS computer to go into a TA only mode. Grounding RBP-5D will inhibitvoice and aural outputs. In this installation, RBP-5D will be tied togrid/open outputs on the windshear and ground proximity warning computers.
Advisory Annunciation Cancel
A discrete is provided to allow the pilot to cancel the currentannunciation. Placing a ground on RMP-3D will cause the TCAS computer tocancel the current annunciation.
Climb Inhibit
Four discretes; RMP-lJ, RMP-13G, RBP-5J, and RBP-5K, are provided toindicate that the aircraft’s climb performance is limited below 1500 fpm.
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APPENDIX MTACAN INSTALLATION
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APPENDIX M
TACAN INSTALLATION
1.0 TACAN INSTALLATION
1.1 Scope
This appendix provides data for the installation of the Collins TCN-500
Advanced Digital TACAN System and its interface with the existing SPZ-8000
system in the G-IV. Included are a functional description, equipment list,mechanical installation information, system schematic, and electricalinterconnect information.
1.2 Functional Descri~tion
The SPZ-8000 system is modified to interface with a single TCN-500 Advanced
Digital TACAN System. The TCN-500 System consists of a 374E-1Receiver/Transmitter, a 377J-I TACAN control unit, and two TACAN antennas.TACAN provides digital bearing, distance, range rate, and time-to-stationinformation on an ARINC 429 bus. In this installation, only digital bearing
and distance information is used.
Modifications to the SPZ-8000 Electronic Display System were required to
accommodate interface to the TACAN system. These modifications are software
only and have been made to the Display Controller (DC-884) and SymbolGenerator (SG-884). TACAN frequency and mode selections are done throughthe TACAN control unit. Tuning via the FMS is not available.
TACAN will send digital distance and bearing information to each SG in ARINC
429 format. This is sent to the SG via ARINC 429 Port 14. This port was
previously used to receive data from the Lightning Sensor System. Thus,with TACAN installed lightning data is not available for display.
Selection or preview of TACAN receiver information will be via the NAVselect menu on either the pilot or copilot DC. Also, bearing pointerselection will be via the MAP or COMP function key through selection of TCNor AUTO. TACAN NAV source, bearing, course, and distance can be displayedon both the Primary Flight and Navigation Displays.
When TACAN is selected as the active navigation source, TACAN lateralnavigation mode shall be operational. Similar to VOR mode, TACAN will
couple to the Flight Guidance Computer and provide automatic intercept,
capture, and tracking of a selected TACAN radial.
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1.3 Eauipment List
New part number Symbol Generators and Display Controllers must be installedwhen the aircraft is upgraded to operate with TACAN. The required partnumbers are:
ConnectorDesignator ~ w Part Number
65/C65/E65 SG-884 3 7008570-913
115/cl15 DC-884 2 7007540-951 (GRAY)952 (BLACK)
The TCN-500 system equipment to be supplied by Collins is listed below:
~ m Part Number
374E-1 Receiver/Transmitter 1 622-8149-004
377J-1 Control 1 622-2510-003
L-Band Antenna 2 522-2632-001
1.4 Mechanical Installation Information
Installation of the SG-884 and DC-884 are specified in Section 2.2 of thisdocument. For TACAN installation information refer to Collins TCN-500Advanced Digital TACAN Installation, Document No. 523-0774762.
1.5 Svstem Schematic
See Figure M-1.
1.6 Electrical Interconnect Information
For TACAN receiver/transmitter, control, and antenna electrical interconnectinformation refer to Collins TCN-500 Advanced Digital TACAN Installation(523-0774762) . The only Honeywell SPZ-8000 interconnect addition is theTACAN R/T to each of the three Symbol Generators on the ARINC 429 bus. Noadditional wiring is required for the Display Controller.
Interconnect InformationTable 501 (cent) 22-14-00
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-.
374 E-1 RCVR/XMTR
ANTENNA #1 J1
ANTENNA #2 J2
SUPPRESSION IN J5
IDENT OUTIDENT COMMONIDENT SHIELDTERNARY CONTROL A
TERNARY CONTROL BTERNARY SHIELD26 V AC DIST EXC13 V AC HIGH13 V AC LOWPOWER GROUNDRT STATUS FLAGCONTROL TRANSFERTURN-ON COMMAND
28 V DC IN (HI)28 V DC IN (HI)28 V DC IN (LO)28 V DC IN (LO)CHASSIS GROUNDCHASSIS GROUND
PROGRAM PIN 4SIGNAL GROUND
TERNARY A OUTPUTTERNARY B OUTPUTTERNARY OUT SHIELD
J3
131412686970865
11923693
1234
4997
2217
798081
n L-BAND ANTENNA It
n- L-BAND SUPPRESSION
EQUIPMENT
I 1~377J-1 CONTROL I
.-, + B
—
4 A/c5vDc— MEc
——
}
A/C— 28 V DC
+
IDENT INIDENT COMMON
TERNARY ATERNARY B
PANEL LIGHTS13 V ACGROUND
RT NO 1 FLAGCONTROL XFERON/OFF
● ✎A/C AUDIO . N1~
IDENT OUTPUTSYSTEM AC GROUND
~
I SYMBOL GENEWTOR#1 I
I-I65J1A Ir’
53 ARINC 429 (HI)!I
[# 54 ARINC 429 (LO)~-
LSYMBOL GENERATOR#2
C 5JIA
J*t 1d I
*. 53 ARINC 429 (HI).- 54 ARINC 429 (LO)
II SYMBOL GENERATOR#3 I
~5JlA
t-. + f-,h I 53 ARINC 429 (HI)
2; ~ 54 ARINC 429 (LO)
TACAN System SchematicFigure M-1
Interconnect InformationTable 501 (cent) 22-14-00
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SYMBOL GENERATOR NO. 1
IOB& Function Connector Pin Connects To
(B) ARINC 429 (HI)*
65J1A-53 (22)---fl-- --------- TACANJ3-79
(B) ARINC 429 (LO) 65J1A-54 (22)------- --------- TACANJ3-80
SYMBOL GENERATOR NO. 2
IOB& Function Connector Pin Connects To
(B) ARINC 429 (HI)$
C65J1A-53 (22)---fl-- --------- TACANJ3-79(B) ARINC 429 (LO) C65J1A-54 (22)---~- --------- TACANJ3-80
SYMBOL GENERATOR NO. 3
IOB& Function Connector Pin Connects To
(B) ARINC 429 (Hi) E65J1A-53 (22)---fl-$
-------- TACAN J3-79(B) ARINC 429 (LO) E65J1A-54 (22)---U-- --------- TACAN J3-80
Interconnect InformationTable 501 (cent) 22-14-00
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SECTION 7SYSTEM SCHEMATICS
Information normally contained in overall system schematics has been incorporated
in the mode flow diagrams (Section 3) and the interconnects (Section 6);therefore, this section has been omitted.
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SECTION 8REMOVAL/REINSTALLATION AND ADJUSTMENT
1. General
2
I
This section provides instructions for removing and reinstalling, andadjusting each unit of the SPZ-8000 Automatic Flight Control System that hasbeen previously installed in the System. Should any INSTALLATION CRITICALcases arise with the reinstallation of any unit, be sure to comply 100percent with the instructions.
CAUTION: TO PREVENT COMPONENT DAMAGE, TURN AIRCRAFT POWER OFF WHEN REMOVINGOR INSTALLING COMPONENTS.
NOTE s No adjustment is required unless stated otherwise.—.
After reinstallation of any unit, check unit operation in accordance with
applicable GROUND CHECK procedure.
Eaui~ment and Materials
A. Equipment
No special equipmen+ or materials other than those commonly used in shopare required for reinstalling units in existing trays and clamps andadjusting the System.
B. Materials
WARNING: BEFORE YOU USE A MATERIAL, YOU MUST KNOW THE HAZARD CODE AND
NOTE:
Adhes
GET THE NECESSARY PROTECTION. A HAZARD CODE IDENTIFIES THREE
EFFECTS OF A MATERIAL ON A PERSON: HEALTH, FIRE, ANDREACTIVITY. THE HIGHER THE NUMBER, THE MORE DANGEROUS THEHAZARD . BE CAREFUL WITH ANY MATERIAL THAT HAS A HAZARD CODE
WITHA2, 3, 0R4. REFER TO ATTACHMENT H FOR AN EXPLANATION OFTHE HAZARD CODE.
You can use equivalent alternatives for the materials in thislist.
ve-sealant, general purpose, RTV, silicone (MIL-A-46106, Type 1 -soft spreadable thixotropic paste, group 1) - SILASTIC RTV 732 (black orwhite), Dow Corning Corp, Midland, MI (HAZARD CODE 11OD)
Sealing compound, temperature-resistant, high-adhesion, two component,polysulfide synthetic rubber (MIL-S-8802, Type 1 - bichromate curedsealing materials, Class B1/2 - spreadable) - PR-1422 (base andaccelerator), Products Research and Chemical Corp, Coating and SealantsDiv, Glendale, CA (HAZARD CODE 311C)
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3. Procedure for DU-880 Dis~lay Unit
r!. Remove Disp”
(1) Loosen
(2) slowlytray cl
ay Unit
screw on panel at the bottom center of unit.
Dull forward on to~ and bottom of bezel to seDarate unit andnnector, and s-
6. Reinstall Display Unit
(1) ~~;:j ;~it into mount.
ide’unit out of tray.
ng tray ensuring that unit guide pins are
(2) Carefully apply firm pressure until unit connector is mated withtray connector.
(3) Tighten screw on panel.
c. PFD Inclinometer Level Adjustment
(1) Loosen two screws on inclinometer.
(2) Adjust inclinometer until level and tighten screws.
D. CRT Filter Cleaning
(1) Inspect outside surface for foreign material and variations “optical properties.
(2) Particles of grit, dirt, or sand are to be removed carefullyhigh-pressure dry air or a soft camel-hair brush.
(3) Alcohol Cleaning
n
with
(a) Dampen a clean portion of a blue (or cotton) wipe with alcohol.
(b) Carefully rub unclean portion of filter with damp wipe.
(c) Repeat step 3.D.(3)(b) until filter is clean.
[d) Alcohol sometimes leaves a licthtfilm residue on the filter: if.,this is found,
(4) Ammoniated Cleaner
(a) h~);gra clean.
clean with a lightly ammoniated cleaner. ‘
portion of blue (or cotton) wipe with ammoniated
(b) Carefully rub filmy portion of filter with damp wipe.
(c) Wipe off residue with clean dry portion of blue (or cotton)wipe.
(d) Repeat steps 3.D. (4)(b) and (c) until clean.
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4. Procedure for WC-810\874 Weather Radar Controller, GP-820 Fllqht GuidanceController. PC-880 Turn Pitch Controller. DC-884 Display Controller. CD-81O
I
Control DisRlay Unit, DL-800/900 Data Loader, DP-884 Dimmer Panel, LU-850Liqhtninq Sensor Controller, Mode Select Unit, Navigation Dis~lay Unit, or
Inertial System DisrIlaYUnit
I A. Remove Controllers, Display or Select Unit, Data Loader, or Dimmer Panel
(1) Loosen unit screw (DZUS) fasteners.
(2) Slide unit out of panel and disconnect cable connector.
I B. Reinstall Controllers, Display or Select Unit, Data Loader, or DimmerPanel
(1) Mate unit connector with cable connector and slide unit into panel.
I (2) Tighten unit screw (DZUS) fasteners.
5. Procedure for AZ-81O Diqital Air Data Computer, FZ-820 Fliqht GuidanceI Comi)uter, NZ-920 Navigation Comr)uter, SG-884 Symbol Generator. FC-880 Fault
Warninq Com~uter, DA-884 Data Acciuisition Unit. or PZ-800 Performance
IComputer, LP-850 Liqhtinq Sensor Processor, ML-850 MLS Receiver, OZ-800receiver Processor Unit, Inertial Reference Unit, or RT-91O TCAS Computer
A. Remove Computers, Symbol Generator, or Data Acquisition Unit
(1) For air data computers, disconnect pitot and static lines.
(2) Loosen unit holddown knob.
(3) Slowly pull forward on unit handle to separate unit and trayconnectors and slide unit out of tray.
B. Reinstall Computers, Symbol Generators, or Data Acquisition Unit
(1) Slide unit into mounting tray.
CAUTION: DO NOT FORCE FIT. IF MATING IS DIFFICULT, REMOVE THEUNIT AND CHECK FOR CONNECTOR PINS THAT MAY BE BENT OROUT OF ALIGNMENT. ALSO CHECK THE ALIGNMENT OF THERECEPTACLE IN THE MOUNTING TRAY.
(2) Carefully apply firm pressure until unit connectors are mated withconnector receptacles on mounting tray.
(3) Tighten unit holddown knob, ensuring proper engagement is made.
(4) For air data computers, connect pitot and static lines and performpitot/static leak check.
(5) For LP-850 Lightning Sensor Processors, adjust switches S1 throughS4 on front of unit to settings specified on the correction factorlabel located on the rack or near the LP-850.
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6. Procedure for RT-300 Radio Altimeter Receiver Transmitter
A. Remove Radio Altimeter Receiver Transmitter
(1) Disconnect cable and antenna connectors.
(2) Loosen unit holddown knobs and remove unit.
B. Reinstall Radio Altimeter Receiver Transmitter
(1) Slide unit into mounting tray and secure with unit holddownassembly.
(2) Mate unit connectors with applicable antenna and cable connectors.
c. Radio Altimeter Display Zero Ground Adjustment
The zero height adjustment is accomplished with the unit operating andall electrical connections (including antennas) made. Perform thefollowing
CAUTION:
steps:
UNDER NO CIRCUMSTANCES SHALL POWER BE TURNED ONUNLESS ANTENNA OR SUITABLE LOAD [50-OHMTERMINATION) IS CONNECTED TO TRA~SMIT CONNECTOR.BOTH THE TRANSMIT AND RECEIVE ANTENNAS MUST BECONNECTED TO CONDUCT THE ZERO HEIGHT ADJUSTMENT.
(1) Apply system power.
(2) The RAD ALT display on the PFD will show a value near zero.
(3) After a 2-minute stabilization period, the zero height adjust maythen be used to zero the RAD ALT display for this installation.
7. Procedure for AT-222 Radio Altimeter Antennas
CAUTION: DO NOT PAINT THE FIBERGLASS RADOME (ANTENNA FRONT FACE).
A. Clean the mounting surfaces well with emery cloth to provide a goodground between the aircraft and the antennas. A conductive coatingshould be used for corrosion prevention. A suitable commercial productis Alodine 1201 which can be brush applied.
B. The antennas must be mounted on a conductive surface for properoperation. The surface area should be smooth and free fromdiscontinuities between the transmit and receive antennas.
c. Connectors of antennas should be oriented as shown in Figure 701.
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TRANSMIT ANTENNA
RECEIVE ANTENNA
t
7’CONNECTORS(AT-200 SERIESANTENNAS)
L
1NOTES:
-J 1. THE DASHED LINE REPRESENTSA LINE CONNECTING THE CENTERSOF THE TWO ANTENNAS.
2. ONE OR BOTH ANTENNAS MAY BEROTATED 180 DEGREES.
3.DO NOT POSITION THE ANTENNASO THE CONNECTOR IS POINTINGFORE OR AFT.
AD-30732#
Correct Orientation of AT-222 AntennasFigure 701
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8. Procedure for WR-800 Weather Radar Receiver Transmitter
A. Remove Receiver Transmitter
(1) Release RT quick-disconnect, then remove waveguide-run flange fromRT waveguide.
(2) Disconnect aircraft mating connector P201 and P202 if used.
(3) Place protective covers over RT and aircraft waveguide flanges.
(4) Remove safety wire, loosen hold-down clamps, and pull RT out ofmounting tray.
B. Reinstall Receiver Transmitter
CAUTION: BEFORE INSTALLING RT, CHECK THAT STC SWITCH ON FRONT PANEL ISSET AT 24 TO CORRESPOND WITH THE SIZE OF ANTENNA RADIATORINSTALLED.
(1) Slide RT into mounting tray until it is hooked under curved hold-down end of tray. Position, hand-tighten, and safety-wire hold-downclamps in front.
(2) Remove protective cover from RT waveguide flange. Check flange fordents or foreign matter. Connect waveguide run by means of quick-disconnect clamp (M1585214). Connect aircraft interconnectionwiring to RT connector J201 and J202 if used.
9. Procedure for WA-800 Weather Radar Antenna and FP-900 24-Inch Radiator Plate
A. Remove Antenna
(1)
(2)
(3)
(4)
(5)
(6)
Release antenna quick-disconnect; then remove waveguide-run flangefrom antenna waveguide. Carefully remove pressure or O-ring seal ifwaveguide is pressurized.
Disconnect aircraft connector P301 from antenna.
Place protective covers over antenna and aircraft mating waveguideflanges.
Remove and retain four socket-head cap screws and associated washersholding flat-plate phased-array radiator to antenna (supportradiator while these screws are being removed), then removeradiator.
Place protective covers over antenna and radiator waveguide matingflanges.
Support antenna pedestal, and remove and retain hardware holdingpedestal to aircraft bulkhead. Remove antenna pedestal.
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9. B. Reinstall Antenna
I
(1)
(2)
(3)
(4)
(5)
Align antenna mounting holes with four holes in aircraft bulkhead,then fasten antenna in place with appropriate hardware.
Remove protective covers from antenna and aircraft mating waveguideflanges. Check flanges for dents or foreign matter. Connectwaveguide to antenna by means of quick-disconnect clamp (ifwaveguide is pressurized, install pressure window and RF gasketbetween waveguide and antenna). Connect aircraft interconnectionwiring to antenna connector J301.
Remove protective cover from radiator waveguide flange. Checkflange for dents or foreign matter.
Position flat-plate radiator so mounting holes are aligned withholes in antenna waveguide flange and legend on radiator readsright-side up (logo should be below legend), then fasten radiator toantenna using four socket-head cap screws and associated flat andlockwashers furnished.
Set SCAN ON/OFF switch to ON.
c. Antenna Stabilization Checks
This procedure provides a method for adjusting the sensitivity of theradar stabilization amplifiers (in the receiver transmitter) tocorrespond to the sensitivity of the vertical reference in the individualaircraft. This procedure should be accomplished for each newinstallation, whenever stabilization problems are suspected, or after thestabilization system has been serviced.
~: As received from the factory, the antenna synchros and resolversare correctly aligned. For other than new installations, it isnecessary for correct alignment of these items to be verified inaccordance with applicable maintenance manual procedures.
(1) Preliminary Checks
(a) Verify that mounting surface of antenna is aligned with rolland pitch axes of aircraft tl/4 degree.
(b) Before applying power to radar system, make sure that MODswitch on RT front panel is slid to the right (OFF) so as todisable modulator and prevent transmitter from transmitting.
(c) Verify that SCAN switch on antenna pedestal is in OFF position.Turn system on and press SB/T pushbutton. After the 50-secondtime delay, verify noise band is broken up to indicate thattransmitter is not transmitting.
(d) Press WX pushbutton, and verify that MOD switch is off by theWAIT staying on the display all the time. Ensure that STABswitch on RT front panel is slid to right (OFF) to deactivatestabilization circuit. Press SB/T pushbutton and test patternwill be displayed.
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9. c. (1) (e) By reference to mounting surface of aircraft verticalreference, determine and record pitch angle of aircraft as itrests on ramp.
(2) Antenna Elevation
(a)
(b)
(c)
(d)
(e)
(f)
(9)
(h)
I
Manually position flat-plate phased-array radiator in dead-ahead position as indicated by antenna azimuth scale.
Loosen, or remove, as necessary, mounting hardware of aircraftvertical reference. Lift it from mountjng surface and levelit.
In test mode, set TILT control on indicatorshown on indicator display).
With spirit level, check that antenna pitchrecorded in step 9.C. (l)(e) tl.O degree.
Excessive error observed in step 9.C. (2)(d)defective:
at O degree (as
equals that
may result from
● Aircraft vertical reference; output should be O volt.
● Indicator: Degree tilt calibration of TILT control can beconfigured at antenna elevation synchro B304: ac voltagemeasured between S2 and S3 should equal voltage between S2and S1.
. Antenna: Elevation synchro B304 may require alignment.
● Receiver transmitter stabilization circuitry.
● Antenna installation at bulkhead.
Alternately turn TILT control to both 15 degrees up and 15degrees down positions, and verify, by observing spirit level,that flat-plate radiator responds in same direction in anamount equal to aircraft pitch as determined by preceding step9.C. (2)(d) 15 f 1.0 degrees.
With flat-plate radiator facing dead-ahead, adjust TILT controluntil spirit level is centered (O degree elevation). DisregardTILT control setting and aircraft pitch angle. Slide STABswitch on RT front panel to the left (ON).
Press SB/T pushbutton (STBY mode) and alternately displaceaircraft vertical reference in pitch axis 20 degrees up and 20degrees down. Verify that flat-plate radiator elevates 10.3 t0.5 degrees in opposite direction.
Press SB/T pushbutton (test mode) and verify that antennaslowly oscillates between 10.3 degrees and 20 degrees; e.g., ifpitch reference is 20 degrees up, the antenna would move from10.3 degrees down to 20 degrees down.
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9. C. (3) Roll Compensation
(a) In test mode, 1 evel aircraft vertical reference as described instep 9.C.(2)(b).
(b) Refer to antenna azimuth scale and manually position flat-plateradiator facing dead-ahead. Slide STAB switch on the front of
RTto the right (OFF).
(c) Adjust TILT control until flat-plate radiator is perpendicularto earth as measured with spirit level. Disregard TILT controlsetting when making this adjustment. Slide STAB switch on RTfront panel to the left (ON). Press SB/T pushbutton to getSTBY mode.
(d) Position aircraft vertical reference in roll axis 20 degreesleft bank keeping it at O degree on pitch axis, and verify thatantenna moves up. If it moves down instead, press SB/T
pushbutton twice and then verify antenna moves up 17.5 t 1.0degrees.
NOTE: Each time the system is switched from TEST to STBY theantenna is electrically changing from 60 degrees left to60 degrees right, but the first time it is turned toSTBY the side is not known. That is the reason it mayhave to be switched from STBY to TEST to STBY again. -
(e) Press SB/T pushbutton twice (STBY mode), and then verifyantenna moves down 17.5 t 1 degrees.
(f) Press SB/T pushbutton (test mode) and verify antenna slowlyoscillates between 17.5 degrees up and 17.5 degrees down.
(g) Turn antenna SCAN switch ON (on antenna) and verify antennamoves up 17.5 degrees on the left side and down 17.5 degreesthe right side.
on
(h) Turn system OFF; verify SCAN switch on antenna pedestal in ONposition; and slide MOD switch on RTto the left (ON) toactivate modulator.
(i) Restore vertical reference installation.
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9. D. Pressurization Checks
For those installations in which the waveguide is to be pressurized,conduct the following pressurization test after connecting the waveguidebetween the RT and the antenna.
If a flow meter is not available for testing, the change in pressure withrespect to time may be used for the same purpose.
(1) Apply 10 lb/in2 (O, 7 kg/cm2) through waveguide bleeder.
(2) Arrest air flow from pressure source into waveguide.
(3) Observe time in seconds required for pressurization in waveguide todrop to 5 lb/in2 (O, 35 kg/cm2).
The time it will take for the pressure to drop to 5 lb/in2 (O, 35 kg/cm2)varies linearly with time versus waveguide length. For each foot (30, 5cm) of waveguide, the minimum allowable time is 5 seconds. Thus, forexample, for 3 feet (91 cm) of waveguide, the minimum allowable time is15 seconds.
10. Procedure for WU-870 Antenna and Receiver Transmitter Unit
A. Remove Unit
WARNINGS: 1.
2.
3.
POSITION AIRCRAFT RADAR SYSTEM TO FACE AWAY FROMBUILDINGS, LARGE METAL STRUCTURES, OR OTHER AIRCRAFT INCLOSE PROXIMITY BEFORE YOU TURN ITON. THEY ARE LIKELYTO RETURN LARGE AMOUNTS OF REFLECTED ENERGY AND CAUSEDAMAGE TO THE SYSTEM.
DO NOT OPERATE RADAR WITHIN 50 FEET OF OTHER AIRCRAFT OROBJECTS, OR CLOSER THAN 100 FEET TO REFUELING OPERATIONS.
NEVER LOOK DIRECTLY INTO THE ANTENNA (WHILE IT ISOPERATING) FOR PROLONGED PERIODS OF TIMEATA CLOSE
RANGE. SERIOUS EYE TISSUE DAMAGE CAN RESULT DUE TO THEHEATING EFFECT OF RADAR ENERGY.
(1) Remove electrical power from aircraft.
(2) Gain access to nose avionics rack (under radome).
(3) Remove electrical connector.
(4) Remove radar unit.
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10. B. Install Unit
(1) Install unit.
(2) Connect electrical connector.
(3) Make sure SCAN and MOD switches are turned on.
(4) Inspect area for foreign objects.
(5) Close radome.
(6) Perform PRIMUS@ 870 Weather Radar System antenna stabilization andoperational checkout.
c. Antenna Stabilization Checks
NOTE: Pitch and roll gain adjustments only affect the analog
stabilization function. ARINC 429 digital stabilization is
preset and cannot be adjusted. However, it can be checked foraccuracy.
(1) Preliminary Checks
(a)
(b)
(c)
(d)
(e)
Install waveguide extension and dummy load on the unit.
Using inclinometer, verify that fan mounting surfaces arealigned to the pitch and roll axis of the aircraft within 51/4degree. Record aircraft level points.
Make sure that SCAN and XMTR switches on the unit housing arein the OFF position. Adjust antenna azimuth to OO. Make sureautotilt is off.
Select map mode on both pilot and copilot display controllers.Make sure that copilot WX controller is OFF and that pilotcontroller is selected to STANDBY and the GAIN to preset(DEPRESS). On power-up, verify a flashing WAIT (amber)mnemonic is displayed on both NAV displays for approximately45 seconds, then change to mnemonic STBY (green)-.”
Using inclinometer, adjust tilt control for O“ antenna p“on pilot controller. Make sure that 0° on controllercorresponds to O t 1/4° antenna pitch measured on wavegu-upper surface.
~: Repeat steps 10.C.(l)(d) and (e) for copilot’scontroller.
CAUTION: DO NOT OPERATE IRS WITHOUT COOLING FOR LONG PERIODSTIME (1 HOUR MAX).
tch
de
OF
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Honeywell t$~!frwc’10. C. (1) (f) Select IRS No. 2 on IRS breakout box and tilt table.
(g) select pilot’s controller to STBY and copilot’s controller to.
(2) Antenna Elevation
(a) Tilt IRS NO. 2 to 25° noseup and O“ roll.
(b) Make sure antenna tilts down 25 t 1°.
(3) Antenna Roll
(a)
(b)
(c)
(d)
(4) Roll
Select VARIABLE GAIN (PULL).
Tilt IRS No. 2 to 0“ pitch and 25° right wing down.
Make sure antenna tilts up 25 ~ 1°.
Conduct roll offset adjustment if step 1O.C.(3)(C) is out oftolerance.
Offset Adjustment
NOTE: This is an in-flight adjustment. If two controllers areinstalled, one must be off.
(a)
(b)
(c)
(d)
(e)
(f)
At an altitude of 10,000 feet above ground level or greater,
and in the 100 NM range, adjust antenna tilt down until a
fairly solid band of ground clutter is visible.
Select variable gain, WX, REACT OFF. Observe VAR on display.
Select REACT ON-OFF-ON-OFF within 3 seconds. VAR should not
be displayed. This puts the unit in roll compensation mode.Press REACT pushbutton once more and verify VAR is notdisplayed. If it is, repeat this step.
Adjust manual GAIN control on controller until the groundclutter display is symmetrical.
Do not touch manual GAIN control once display is adjustedproperly.
Select REACT ON-OFF-ON-OFF within four seconds to exit theroll compensation mode. When VAR is displayed again, the rollcompensation mode has been exited. Set variable or presetGAIN as desired.
Note that this compensation is now stored in nonvolatilememory in the RT and will not be erased if power is removedfrom the system.
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11. Procedure for SM-600 Dual Servo, TM-260 Dual Trim Servo and Brackets, andSM-81O Servo
For removal and reinstallation of the servos and bracket, refer toinstructions in the Gulfstream IV Aircraft Maintenance Manual.
12. Procedure for CM-850 MLS Control/DisPlav Unit
A. Remove Control/Display Unit
(1) Using a 3/32 Allen Wrench, loosen unit mounting clamps.
(2) Slide unit out of panel and disconnect aircraft cable connector.
B. Reinstall Control/Display Unit
(1) Mate unit connector with aircraft cable connector and slide unitinto panel.
(2) Using a 3/32 Allen Wrench, tighten unit mounting clamps.
13. Procedure for Global Positioning System Sensor Unit (GPSSU)
A. Remove GPSSU
(1) Disconnect aircraft cable and antenna connectors.
(2) Remove four screws and washers securing GPSSU to airframe.
B. Reinstall GPSSU
(1) Secure the GPSSU to the airframe using four 10-32 screws,lockwashers, and flat washers.
(2) Mate unit connectors with applicable antenna and cable connectors.
14. Procedure for AT-91O TCAS Directional Antenna
~: There is at least one AT-91O required for TCAS, mounted on top of thefuselage. A second (optional) RT-91O may be mounted on the bottom ofthe fuselage. These procedures apply to both antennas.
A. Remove TCAS Directional Antenna
(1) Remove and save eight non-torx drive screws securing antenna toaircraft.
(2) Verify that the four coaxial cables have the appropriate colorcoding rings in place. If they have been damaged or removed, tagthe cables as appropriate.
(3) Remove antenna.
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Honeywell
14. B. Disassemble Antenna and Mounting
MAINTENANCEMANUALGULFSTREAMIV
PIate
(1) Remove and save attaching hardware and separate antenna dish andadapter plate.
(2) Clean antenna dish and adapter plate to remove any sealant and
foreign material.
c. Assemble Antenna and Mounting Plate
(1) Mate antenna dish with adapter plate, making sure that all holes
are aligned.
(2) Using a grease pencil, make an alignment mark on antenna dish and
adapter plate.
(3) Separate antenna dish and adapter plate.
(4) Apply a continuous bead of sealing
in adapter plate.
(5) Place adapter plate over antenna d
earlier in paragraph (b) above.
(6) Press adapter plate onto antenna d
compound PR1422 to outer recess
sh to match alignment marks made
sh.
(7) Attach adapter plate to antenna dish, using supp”hardware. Leave airframe mounting holes empty.
D. Reinstall TCAS Directional Antenna
(1) Place new O-ring, Honeywell Part No. 4000017,of antenna assembly.
(2) Position antenna assembly to its location onmounting holes (note the nonsymmetrical hole
ied attaching
-240, in O-rng groove
fuselage and alignpattern).
(3) Note orientation of antenna with respect to airframe. Doattach antenna to airframe at this time.
not
(4) Carefully inspect all mating connectors for the presence of foreignmatter.
(5) Connectand matto J4.
Clean as necessary.
four coaxial cables to antenna. Note color bands on cablesng connectors: yellow to Jl, black to J2, blue to J3, red
(6) Align antenna mounting holes with holes in aircraft (note thenonsymmetrical hole pattern). Install washer on non~torx drivescrew, apply sealant to threads, and install through antennamounting holes into airframe. Tighten to 18 inch-pounds maximumtorque.
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Use or disclosure of information on this pagei.ssubject to the restrictions on the title page of this d acument.
15. Procedure for AT-800/803 Antenna Coupler Unit (ACU)
A. Remove Antenna Coupler Unit
(1) Remove and save screws securing antenna to aircraft.
(2) Break seal between ACU/gasket seam or antenna/shim seam and remove
ACU .
(3) Disconnect cable connector.
B. Reinstall Antenna Coupler Unit
(1)
(2)
(3)
(4)
(5)
Install new gasket, if applicable.
Connect cable connector.
Position ACU over gasket.
Apply sealing compound PR1422 or equivalent to ACU/gasket seam. Ifgasket is not used, position ACU and apply Silastic, RTV732, around
the circumference of the ACU and the mating surface seam.
Install nonmagnetic mounting screws through antenna, shim, andthrough the aircraft skin into captive nutplates. Tighten thescrews to a maximum of 10 inch-pounds torque or 5 inch-pounds aboveplatenut breakaway torque.
16. Procedure for AT-850 Antenna
A. Remove AT-850 Antenna
(1) Remove and save three screws securing antenna to aircraft.
(2) Break seal between antenna/gasket seam and remove antenna.
(3) Disconnect cable connector.
B. Reinstall AT-850 Antenna
(1) Connect cable connector.
(2) Install and align antenna and secure with three No. 10 nonmagneticstainless screws removed in Step 16.A.(1).
(3) Tighten screws to a maximum of 10 inch-pounds torque or 5inch-pounds above platenut breakaway torque.
(4) Apply sealing compound PR1422 between antenna and gasket seam.
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17. Procedure for AT-855 Antenna and AT-801 Antenna Coupler Unit
A. Remove antenna
(1) Remove and save screws securing antenna to aircraft.
(2) Disconnect cable connector and remove antenna.
B. Reinstall antenna
(1) Connect cable connector.
(2) Install antenna and secure with No. 10 nonmagnetic stainless screwsremoved in Step 17.A.(1).
18. Procedure for Updatinq the Navigation Database
Updating the NAV database is accomplished using the DL-800/900 Data Loader.First if the DL-800/900 is not installed in the aircraft, connect theportable data loader umbilical cable to the aircraft connector. Apply powerto the data loader using the appropriate aircraft circuit breaker and pressthe data loader power switch. The power LED will illuminate and after thepower-up BITE sequence has been completed, the data LED will illuminate.Select LEFT or RIGHT to load the respective FMS. Insert the database diskto be loaded into the slot on the loader. All other steps are accomplishedon the CDU.
The DATA LOAD page is accessed through the second page of the NAV index(NAV key) or from the IDENT and MAINTENANCE pages. Once on this page(Figure 702), press the NAV DB line select key. This will change thedisplay to Figure 703, where the prompt to transfer from the loader islocated.
NOTE “ The data loader must have power applied and the selector switch must‘“ be in the appropriate position for the FR LOADER prompt to appear on
the CDU.
Pressing the FR LOADER line select key will change the display toFigure 704. Press the key next to the YES PROMPT TO BEGIN LOADING. The CDUwill indicate the progress of the transfer as shown in Figure 705. When thecounter reaches 100%, the FMS will verify the successful transfer byvalidating the CRC (cyclic redundancy check) as shown in Figure 706. Whenthe CRC is validated, the screen will blank momentarily while the FMSexecutes its BITE sequence using the new database. When this is completed,the CDU will return to the NAV IDENT page and the message DB TRANSFERCOMPLETE will be in the scratchpad line.
In dual installation, this procedure must be performed on each side.
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Apr 15/93Useor disclosure of information onthispage issubject to the restrictions on the title page ofthiadccurnent.
/ \lc = DATA LOAO 1/1 ( >
mDATA TO BE LOADED
H
H4CIJSTOM DB
B
B4NAV DB BOTH>
B
H
MAINTENANCE
H
Data to be LoadedFigure 702
AD-20865 @
Display
11DATA LOAD
aTRANSFER OF
NAV DB
IH<TO COPILOT
~
a 4FR COPILOT FR LOADER>
F
la
n
4CLEAR MAINTENANCE>H
\ /AD-20865 @
Transfer of NAV Database Display
Figure 703
I22-14-00
Page 717Apr 15/93
Use or disclosure of information on this page is subject to the restrictions on the title page of this document.
ii
IJ3El
DATA LOAD 1/1CONFIRM TRANSFER OF
NAV DB
FROM DATA LOADER
-4laH
<NO IFHI‘Es’ H
AD-20865 @
Confirm Transfer of NAV Database Display
Figure 704
DATA LOADTRANSFER OF
+
(!3 FROM DATA LOADER
HIS 07% COMPLETE
oat<ABORT
Percent Complete of Transfer DisplayFigure 705
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Apr 15/93Use or disclosure of information on this page issubject to the restrictions on the title page of this dr}cument.
+
DATA LOAD 1/1
eTRANSFER OF
It H
FROM OATA LOADERIS COMPLETE
CRC CHECK IN PROGRESS4ABORT
l+-E31
B
\ /
AD-20865 @
Completion of Transfer DisplayFigure 706
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MAINTENANCE
Honeywell !!iit’%k~~
SECTION 9SHIPPING, HANDLING. AND STORAGE
Refer to Manual, Sperry Pub. No. 09-1100-01, for detailed Procedures for
preparing all system components for storage or shipment.
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