Avionic Emb 145-2

Business and Commuter Aviation SystemsHoneywell Inc.Box 29000Phoenix, Arizona 85038

PRIMUS® 1000 IntegratedAvionics System

Embraer EMB-145

SystemMaintenance Manual

Volume II ── System Interconnects,Maintenance Practices, Shipping,Handling and Storage, andHoneywell Support

22-05-14TITLE PAGE T-1

PRINTED IN U.S.A. PUB. NO. A15-1146-065 1 NOVEMBER 1996

SYSTEMMAINTENANCEMANUALEMBRAER 145

PROPRIETARY NOTICE

This document and the information disclosed herein are proprietary data of Honeywell Inc.Neither this document nor the information contained herein shall be used, reproduced, ordisclosed to others without the written authorization of Honeywell Inc., except to the extentrequired for installation or maintenance of recipient’s equipment.

NOTICE - FREEDOM OF INFORMATION ACT (5 USC 552) ANDDISCLOSURE OF CONFIDENTIAL INFORMATION GENERALLY (18 USC 1905)

This document is being furnished in confidence by Honeywell Inc. The information disclosedherein falls within exemption (b) (4) of 5 USC 552 and the prohibitions of 18 USC 1905.

S96

22-05-14TITLE PAGE T-2

Copyright 1996 Honeywell Inc.All Rights Reserved 1 NOVEMBER 1996


RECORD OF REVISIONS - VOLUME II

Upon receipt of a revision, insert the latest revised pages and dispose of superseded pages. Enterrevision number and date, insertion date, and the incorporator’s initials on the Record of Revisions. Thetyped initials HI are used when Honeywell Inc. is the incorporator.

RevisionNumber

RevisionDate

InsertionDate By

RevisionNumber

RevisionDate

InsertionDate By

Page RR-122-05-14 Nov 1/1996Use or disclosure of information on this page is subject to the restrictions on the title page of this document.


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Page RR-222-05-14 Nov 1/1996Use or disclosure of information on this page is subject to the restrictions on the title page of this document.


LIST OF EFFECTIVE PAGES - VOLUME II

Original . . 0 . . Nov 1/1996

SUBHEADING AND PAGE REVISION SUBHEADING AND PAGE REVISION

TitleT-1 0T-2 0

Record of RevisionsRR-1 0RR-2 0

List of Effective PagesLEP-1 0LEP-2 0LEP-3 0LEP-4 0LEP-5 0LEP-6 0

Section 3System Interconnects

3-1 03-2 03-3 03-4 03-5 03-6 03-7 03-8 03-9 03-10 03-11 03-12 03-13 03-14 03-15 03-16 03-17 03-18 03-19 03-20 03-21 03-22 03-23 0

3-24 03-25 03-26 03-27 03-28 03-29 03-30 03-31 03-32 03-33 03-34 03-35 03-36 03-37 03-38 03-39 03-40 03-41 03-42 03-43 03-44 03-45 03-46 03-47 03-48 03-49 03-50 03-51 03-52 03-53 03-54 03-55 03-56 03-57 03-58 03-59 03-60 03-61 03-62 03-63 03-64 0

F indicates right foldout page with blank back.

Page LEP-122-05-14 Nov 1/1996Use or disclosure of information on this page is subject to the restrictions on the title page of this document.



Section 3 (cont)System Interconnects

3-65 03-66 03-67 03-68 03-69 03-70 03-71 03-72 03-73 03-74 03-75 03-76 03-77 03-78 03-79 03-80 03-81 03-82 03-83 03-84 03-85 03-86 03-87 03-88 03-89 03-90 03-91 03-92 03-93 03-94 03-95 03-96 03-97 03-98 03-99 03-100 03-101 03-102 03-103 03-104 03-105 03-106 03-107 03-108 03-109 03-110 03-111 03-112 0

3-113 03-114 03-115 03-116 03-117 03-118 03-119 03-120 03-121 03-122 03-123 03-124 03-125 03-126 03-127 03-128 03-129 03-130 03-131 03-132 03-133 03-134 03-135 03-136 03-137 03-138 03-139 03-140 03-141 03-142 03-143 03-144 03-145 03-146 03-147 03-148 03-149 03-150 03-151 03-152 03-153 03-154 03-155 03-156 03-157 03-158 03-159 03-160 03-161 03-162 0





3-163 03-164 03-165 03-166 03-167 03-168 03-169 03-170 03-171 03-172 03-173 03-174 03-175 03-176 03-177 03-178 03-179 03-180 03-181 03-182 03-183 03-184 03-185 03-186 03-187 03-188 03-189 03-190 03-191 03-192 03-193 03-194 03-195 03-196 03-197 03-198 03-199 03-200 03-201 03-202 0

F 3-203/204 0F 3-205/206 0

3-207 03-208 03-209 03-210 03-211 03-212 0

3-213 03-214 0

F 3-215/216 03-217 03-218 0

F 3-219/220 03-221 03-222 03-223 03-224 03-225 03-226 03-227 03-228 03-229 03-230 03-231 03-232 03-233 03-234 03-235 03-236 03-237 03-238 03-239 03-240 03-241 03-242 03-243 03-244 03-245 03-246 03-247 03-248 03-249 03-250 03-251 03-252 03-253 03-254 03-255 03-256 03-257 03-258 03-259 03-260 03-261 03-262 03-263 03-264 0





3-265 03-266 03-267 03-268 03-269 03-270 03-271 03-272 03-273 03-274 0

Table of Contents - Section 4TC4-1 0TC4-2 0

Section 4Maintenance Practices

4-1 04-2 04-3 04-4 04-5 04-6 04-7 04-8 04-9 04-10 04-11 04-12 04-13 04-14 04-15 04-16 04-17 04-18 04-19 04-20 04-21 04-22 04-23 04-24 04-25 04-26 04-27 04-28 04-29 04-30 0

4-31 04-32 04-33 04-34 04-35 04-36 04-37 04-38 04-39 04-40 04-41 04-42 04-43 04-44 04-45 04-46 04-47 04-48 04-49 04-50 04-51 04-52 04-53 04-54 04-55 04-56 04-57 04-58 04-59 04-60 04-61 04-62 04-63 04-64 04-65 04-66 04-67 04-68 04-69 04-70 04-71 04-72 04-73 04-74 0

Section 5Shipping, Handling and Storage

5-1 05-2 0




Table of Contents - Section 6TC6-1 0TC6-2 0

Section 6Honeywell Support

6-1 06-2 06-3 06-4 06-5 06-6 0



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SECTION 3SYSTEM INTERCONNECTS

This section provides interconnect information as an aid in troubleshooting the PRIMUS® 1000Integrated Avionics System. The interconnect information in Table 3-1 is based on HoneywellEngineering Bulletin EB7021523, Revision A. For specific avionics wiring information, refer to thewiring diagrams in the Embraer 145 aircraft maintenance manual.

Page 3-122-05-14 Nov 1/1996Use or disclosure of information on this page is subject to the restrictions on the title page of this document.


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Table 3-1. Interconnect Information

TABLE OF CONTENTS

Para Title Page

1.0 (Deleted) 3-6

2.0 (Deleted) 3-6

3.0 (Deleted) 3-6

4.0 ELECTRICAL INSTALLATION DESIGN 3-7

5.0 ELECTRICAL INTERCONNECT DEFINITION 3-38

6.0 SUPPLEMENTARY WIRING INFORMATION (FIGURES) 3-202

APPENDIX A ARINC 429 INTERFACES 3-244

APPENDIX B OPTIONAL FMS 3-248

APPENDIX C PRIMUS 870/660/880 OPTIONS 3-261

APPENDIX D DUAL RAD ALT OPTION 3-269

APPENDIX E GPS OPTION 3-272


Table 3-1. Interconnect Information (cont)


LIST OF FIGURES

Figure Title Page

4-1 Voltage Drop as a Function of Cable Length 3-84-2A Single Point Shield Grounding W/O Bulkhead Conn 3-124-2B Single Point Shield Grounding W/O Bulkhead Conn 3-124-2C Multi Point Shield Grounding W/O Bulkhead Conn 3-134-2D Multi Point Shield Grounding W/O Bulkhead Conn 3-134-2E Single Point Shield Grounding with Bulkhead Conn 3-144-2F Single Point Shield Grounding with Bulkhead Conn 3-144-2G Multi Point Shield Grounding with Bulkhead Conn 3-154-2H Multi Point Shield Grounding with Bulkhead Conn 3-154-2I Shield Grounding Example for Rack Mount Connectors 3-174-2J Shield Grounding Example for Panel/Pedestal Mounted Units 3-204-2K Shield Grounding Example for Bulkhead Connectors and

for Non-Panel Mounted/Non-Rack Mounted Units 3-224-3 Aircraft Grounding 3-244-4 Installation Diagram of an ICB Bus Configuration 3-264-5 High Speed Differential Input Termination 3-284-6 DU/IC Bus Interface (Terminated DU) 3-294-7 DU/IC Bus Interface (Unterminated DU) 3-294-8 High Speed Differential Input Termination 3-304-9 DU/WX Bus Interface (Terminated DU) 3-314-10 DU/WX Bus Interface (Unterminated DU) 3-314-11 RSB Bus Construction 3-344-12 Digital Audio Bus Construction 3-364-13 Lamp Driver Current Draw Requirements 3-376-1A 28 V dc Power 3-2036-1B 28 V dc Power 3-2056-2 Weight On Wheels 3-2076-3 Functional Test 3-2086-4 AHRS Remote Switches 3-2096-5 Left WX/DU Picture Bus 3-2106-6 Right WX/DU Picture Bus 3-2116-7 Edge Lighting 3-2126-8 Lamp Test 3-213




LIST OF FIGURES (cont)

Figure Title Page

6-9 Display/SG Reversionary 3-2156-10 AHRS Reversion Switching 3-2176-11 MADC Reversion 3-2196-12 DAU Reversion 3-2216-13 Display Wrap Around 3-2226-14 RMU Engine Backup Display Interface 3-2236-15 AP/YD Off Warn 3-2246-16 AP Disconnect Interface 3-2256-17 Touch Control Steering (TCS) 3-2266-18 Go-Around Interface 3-2276-19 Elevator Trim Interface 3-2286-20 Surface Position Sensors 3-2296-21 RSB Interface 3-2306-22 COM/NAV Strapping 3-2316-23 Digital Audio Bus 3-2326-24 Pilot’s Primary MIC/Phone 3-2336-25 Copilot’s Primary MIC/Phone 3-2346-26 Observer’s Primary MIC/Phone 3-2356-27 No. 1 VHF COM/MIC PTT 3-2366-28 No. 2 VHF COM/MIC PTT 3-2376-29 Emergency NAV/COM Audio 3-2386-30 Passenger Address Interface 3-2396-31 DME/XPDR Mutual Suppression 3-2406-32 HF Considerations 3-2416-33 Master Caution/Warning 3-2426-34 Maintenance Panel Connections 3-243

LIST OF TABLES

Table Title Page4-1 Auxiliary Chassis Wire Grounding 3-104-2 Circuit Breaker Selections 3-16




1.0 (Deleted)

2.0 (Deleted)

3.0 (Deleted)




4.0 ELECTRICAL INSTALLATION DESIGN

4.1 Power Requirements

4.1.1 DC Power - The aircraft dc power supply must be 27.5 V dc (nominal). Thenormal minimum and maximum allowable voltages are 22.0 and 29.5 V dcrespectively (DO-160 CAT A).

NOTE: For further information about aircraft power supply, refer to RTCA(Radio Technical Commission for Aeronautics) Specification DO-160C.

4.1.2 (Deleted)

4.1.3 Power Supplied to LRUs - The voltage level of the power supplied to theLRUs is important in this installation. The potential is the differencebetween the power pins and power ground pins at the LRU. Excessivevoltage drops in the power wire(s) and power ground wire(s) may cause oneor more of the following conditions:

• The LRU will draw additional current from the aircraft supply system.

• Since the LRU is drawing more current, they produce more heat, loweringLRU MTBFs.

• LRU shutdowns may occur, even though the aircraft supply systemvoltages are within 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 0.5 volt. Voltage drop is a function of current and resistance(Resistance in this case is a function of wire gauge and wire length).See Figure 4-1 for determining proper wire gauge for LRU power and powerground wires.

4.2 Grounding Requirements

Proper grounding is a key factor in ensuring proper system operation undernormal conditions and under HIRF and lightning environments. This sectionmust be complied with to satisfy these requirements.

4.2.1 Chassis Grounding - All units specified in this section must be properlygrounded to the airframe ground. The grounding techniques to accomplishthis are specified for (1) Panel/Pedestal Mount Units and for (2) RackMount/Remote Mount Units.




CIRCUITVOLTAGE

20 18 16 14 12 10 8 6 4 2 1 1/0 2/0 3/0 4/0

400

300

200

175

150

12510

0

8090

607050

40

30

20

15

10

986

75432

1.51

EXAMPLE DESCRIBED INSECTION 246 C & D

20 18 16 14 12 10 8 6 4 2 1 1/0 2/0 3/0 4/0

CABLE SIZE

100

CURVE 1

CURVE 2

CURVE 3

ELECTRIC CABLE CHART

20028

10014200

800115

100

15075600

10050400 7009045360 6308040320 5607035280 490

6030240 4205025200 350

4020160 280

3015120 210

2512100 175

2010140189

80120

16872

112147

6498

126

56

84

105

48

7094

4063

832 56728 496324 42

5220 35

36

CA

BL

E L

EN

GT

H I

N F

EE

T P

ER

VO

LT

DR

OP

AD-39740-R1@

CURVES:1.

2.

3.

CONTINUOUS RATING - AMPERESCABLES IN CONDUIT AND BUNDLESCONTINUOUS RATING - AMPERESSINGLE CABLE IN FREE - AIRINTERMITTENT RATING - AMPERESMAXIMUM IN 2 MINUTES

Voltage Drop as a Function of Cable LengthFigure 4-1




4.2.1.1 Panel/Pedestal Mount Unit Grounding

Panel/Pedestal Mount units (see Paragraph 4.2.2.3B) cannot be reliablygrounded to the airframe via the panel mounting screws or DZUSfasteners. Grounding of these units is accomplished by using the shieldgrounding braid as detailed in Paragraph 4.2.2.3B and Figure 4-2J.

4.2.1.2 Rack Mount/Remote Mount Unit Grounding

All Rack Mount/Remote Mount units shall be electrically bonded to theairframe. This is accomplished by ensuring that the mating surfacesbetween the LRU mounting tray (or LRU mounting feet if a tray is notused) provides a low impedance (< 0.1 ohm) electrical path.

The mating surfaces must be free of all paint and other non-conductiveelements and should be burnished to ensure a good bond. If the aircraftmating surface is not conductive, a bonding strap of at least 1/4 inchwide (preferably 1/2 inch wide) tin coated copper braid can be usedbetween the LRU mounting tray (or LRU itself if a tray is not used) andthe nearest airframe grounding point.

4.2.1.3 Auxiliary Chassis Grounding

Auxiliary Chassis Grounding using a defined LRU connector pin isrequired for all the units specified in Table 4-2. This table lists allthe Primus 1000 units that require an auxiliary chassis grounding wire.The auxiliary chassis grounding is accomplished by using a specifiedmaximum length of 22 AWG insulated wire. The grounding points andmaximum length of the wires is defined in Table 4-1.




Table 4-1Auxiliary Chassis Wire Grounding

Unit Chassis Gnd Max GroundNo. Description Conn Pin Wire Length Wire Grounding Point────────────────────────────────────────────────────────────────────────────────1 AH-800 J1C-11 6 in. See Note 1

11 GC-550 J1-79 8 in. See Note 1

12 SM-200A(AIL) J1-C 12 in. See Note 213 SM-200A(EL) J1-C 12 in. See Note 214 SM-200A(RUD) J1-C 12 in. See Note 2

61 WC-650 J1-F 8 in. See Note 1

115 DC-550 J1-45 8 in. See Note 1

129 PC-400 J1-j 8 in. See Note 1

136 DA-800 J1A-101 6 in. See Note 1J2A-101 6 in. See Note 1

137 DA-800 J1A-101 6 in. See Note 1J2A-101 6 in. See Note 1

143 RCZ-851 J1-67 6 in. See Note 3

144 RM-855 J1-L 8 in. See Note 1J1-U 8 in. See Note 1

160 AV-850A J1-N 8 in. See Note 1J2_D 8 in. See Note 1

193 RT-910 LBP-11 6 in See Note 1────────────────────────────────────────────────────────────────────────────────NOTES: 1. Ground this wire to the end of the shield grounding braid (see Figure

4-2J).

2. Ground this wire to the nearest airframe ground point. Do not groundthis wire to the servo/actuator itself because the wire is used as abackup ground path in case of poor or intermittent servo/actuator toairframe bonding.

3. Ground this wire to the mounting rack grounding lug adjacent to therack mating connectors.

4. Ground this wire by attaching a mounting bolt to the rear of themounting tray and using this bolt to secure the wire via a lug.

────────────────────────────────────────────────────────────────────────────────




4.2.2 Shield Grounds

4.2.2.1 Single Point Versus Multi Point Shield Grounding

The majority of the shielded wires in the PRIMUS® 1000 system have theshields grounded at both ends. This is called multi point grounding andis specified to minimize the adverse effects of HIRF and lightning.

Due to technical considerations, multi point grounding cannot be usedfor all shielded wires. In these special cases only one end of eachcontinuous shielded cable segment is grounded. This is called singlepoint grounding. Deciding which cable segment end to ground on a singlepoint ground cable should be based on the ease of locating a good shieldground in the particular installation (i.e., the end which provides theeasiest grounding method should be grounded). If either end can begrounded easily, then the transmitter end should be grounded. The onlyshielded cables that are single point grounded are the following:

• All low-level analog audio signals

• DU-870 potentiometer dimming control (shield grounded at DU-870 only)

• ADF Antenna triaxial cable

The interconnect portion of this document (paragraph 5) specifies if oneor both ends of a shielded cable requires grounding. Shields must notbe connected to any LRU or bulkhead connector pin.

Examples of both single and multi point shield grounding methods withoutbulkhead connectors are shown in Figures 4-2A through 4-2D. Bulkheadconnector shield handling is detailed in Paragraph 4.2.2.2.




(H)

(L)

J1

1

2

9

10

(H)

(L)

J1

AD-30764@NC

AUDIOOUTPUT

AUDIOINPUT

Example #1Single Point Shield Grounding W/O Bulkhead Conn

Figure 4-2A

(H)

(L)

J1

1

2

5

6

(H)

(L)

J1

AD-30099@

(L)

(H)

J1

5

6

NC

NC

AUDIOINPUT

AUDIOOUTPUT

AUDIOINPUT

Example #2Single Point Shield Grounding W/O Bulkhead Conn

Figure 4-2B




(H)

(L)

J1

1

2

9

10

(H)

(L)

J1

AD-30765@

ARINC429

OUTPUT

ARINC429

INPUT

Example #3Multi Point Shield Grounding W/O Bulkhead Conn

Figure 4-2C

(H)

(L)

J1

1

2

5

6

(H)

(L)

J1

AD-30102@

(L)

(H)

J1

5

6

ARINC429

OUTPUT

ARINC429

INPUT

ARINC429

INPUT

Example #4Multi Point Shield Grounding W/O Bulkhead Conn

Figure 4-2D




4.2.2.2 Bulkhead Connector Shield Handling

The treatment of shields at bulkhead connectors is dependent on whetherthe shielded cable segment requires single or multi point shieldgrounding (see Paragraph 4.2.2.1). Shielded cables that require multipoint shield grounding require that the shields be grounded at bothsides of the bulkhead connectors. Shielded cables that require singlepoint shield grounding are usually floating on both sides of thebulkhead connector. This is done because it is usually easier to grounda single point shield at the cable ends opposite the bulkheadconnectors.

Examples of bulkhead connector shield handling with both single andmulti point shield grounding methods is shown in Figures 4-2E through4-2H.

4.2.2.3 Shield Grounding Methods

This section details the preferred method of shield grounding at allLRUs and bulkhead connectors. This grounding method represents just onemethod. Other methods may also be used but they must provide equivalentshield grounding effectiveness.

4.2.2.3A Shield Grounding Method for Rack Mount Units

This subsection describes the preferred shield grounding method for thefollowing rack mount units:

AH-800 AHRU ComputerDU-870 Display UnitDA-800 Data Acquisition UnitRCZ-850/851B Com UnitRNZ-850/850C Nav UnitIC-600 Integrated Avionics Computer

The shield grounding method for rack mount units is detailed in Figure4-2I.




(H)

(L)

J1

1

2

NC

A

B

9

10

(H)

(L)

J1

NC

A

B

AD-30098@

BULKHEADCONNECTOR

AUDIOINPUT

AUDIOOUTPUT

Example #1Single Point Shield Grounding with Bulkhead Conn

Figure 4-2E

AUDIOOUTPUT

(H)

(L)

J1

1

2

5

6

AUDIOINPUT

(H)

(L)

J1

AD-30100-R2@

AUDIOINPUT

(L)

(H)

J1

5

6

NC

C

D

C

D

BULKHEADCONNECTOR

NCNC

Example #2Single Point Shield Grounding with Bulkhead Conn

Figure 4-2F




(H)

(L)

J1

1

2

A

B

9

10

(H)

(L)

J1

A

B

AD-30101@

ARINC429

OUTPUT

ARINC429

INPUT

BULKHEADCONNECTOR

Example #3Multi Point Shield Grounding with Bulkhead Conn

Figure 4-2G

(H)

(L)

J1

1

2

5

6

(H)

(L)

J1

AD-30103@

(L)

(H)

J1

5

6

C

D

C

D

BULKHEADCONNECTOR

ARINC429

INPUT

ARINC429

OUTPUT

ARINC429

INPUT

Example #4Multi Point Shield Grounding with Bulkhead Conn

Figure 4-2H




SOLDER RING SLEEVE

4" MAX 22 AWG INSULATEDPIGTAIL WIRE

SHIELDED CABLE

2" MAX 22 AWG INSULATEDJUMPER WIRE

4" MAXUNSHIELDED

AD-30766@

1/4" WIDE TIN PLATED COPPER FLAT BRAID

STEEL CLAMP TO SECURE BRAID(S) TO CONNECTOR BACKSHELL

CONNECTOR BACKSHELL

TRAY CONNECTOR

TRAY BACKPLANE

Shield Grounding Example for Rack Mount ConnectorsFigure 4-2I




NOTES FOR FIGURE 4-2I

1. The shield grounding example shows 2 shielded cable shields grounded at aconnector backshell using a length of flat braid.

2. Each pigtail wire provides a ground for a maximum of 2 shielded cables (donot use any more than one jumper wire per pigtail wire).

3. The pigtail wires are attached to the end of the braid by crimp or solder.

4. Each braid shall have a maximum of 6 pigtail wires connected to it. Becauseof the jumper wire, each braid can ground up to 12 shielded cables.

5. If more than 12 shielded cables require grounding at a connector, useadditional braids as required.

6. Cover the exposed braid between the backshell and the pigtail wires withinsulating tubing.

7. The use of backshells is not mandatory. If backshells are not used the 1/4inch wide shield ground braid should be grounded at the rear of the mountingtray using a lug terminal.

8. If backshells are used, verify proper electrical bonding (< 0.1 ohm) betweenthe backshell and the mounting tray.




4.2.2.3B Shield Grounding Method for Panel/Pedestal Mounted Units

This subsection describes the preferred shield grounding method for thefollowing panel/pedestal mounted units:

GC-550 Guidance ControllerPC-400 Turn/Pitch ControllerWC-650 WX ControllerDC-550 Display ControllerCD-810 Control Display UnitRM-855 Radio Management UnitAV-850A Audio Control UnitCD-850 Clearance Delivery Head

The shield grounding method for panel/pedestal mounted units isdetailed in Figure 4.2J.

4.2.2.3C Shield Grounding Method for Bulkhead Connectors and for Non-PanelMounted/Non-Rack Mounted Units

This subsection describes the preferred shield grounding method for thefollowing units and for bulkhead connectors:

AZ-850 Air Data ComputerSM-200 Ail, Rud, Elev ServosRT-300 Radio Altimeter R/TWU-650 WX RT

The shield grounding method for non-panel mounted/non-rack mountedunits and bulkhead connectors is detailed in Figure 4-2K.

NOTE: The AZ-850 is included in this classification because itsmounting tray does not have an integral mating connector.




AIRCRAFT MATINGCONNECTOR

BACKSHELL

STEEL CLAMP TO SECURE BRAIDTO CONNECTOR BACKSHELL

SOLDER RING SLEEVE


SHIELDED CABLE


22 AWG INSULATED CHASSISGND WIRE (REF TABLE 4.2)

1/4" WIDE TIN PLATED COPPER FLATBRAID (ONE CONTINUOUS LENGTH)

FOLD BRAIDIN HALF

GROUNDING LUG (CONNECTTO AIRFRAME GROUND)

4" MAXUNSHIELDED

AD-30767@

Shield Grounding Example for Panel/Pedestal Mounted UnitsFigure 4-2J




NOTES FOR FIGURE 4-2J

1. The shield grounding example shows 2 shielded cable shields grounded at aconnector backshell and to aircraft ground using a length of flat braid.

2. Braid length from connector backshell to grounding lug shall be 18 inchesmax.



5. Each braid shall have a maximum of 6 pigtail wires connected to it (7 wiresif chassis gnd wire is connected). Because of the jumper wire, each braidcan ground up to 12 shielded cables (one braid is sufficient for eachpanel/pedestal mounted unit).

6. Cover the exposed braid between the backshell and the pigtail wires plusbetween the grounding lug and the backshell with insulating tubing.

7. Connector strain reliefs can be used in lieu of backshells. Tie braid tostrain relief using a mounting lug crimped or soldered to the braid (NOTE:Backshells are preferable over strain reliefs).

8. The use of connector strain reliefs or backshells is not mandatory. Ifneither is used, the 1/4 inch wide shield ground braid is run directly fromthe wire harness to aircraft ground with a maximum length of 18 inches.

9. If backshells or strain reliefs are used, verify proper electrical bonding(< 0.1 ohm) between the backshell/strain relief and the connector.




SOLDER RING SLEEVE


SHIELDED CABLE


4" MAXUNSHIELDED

AD-30768@

1/4" WIDE TIN PLATED COPPER FLAT BRAID

BACKSHELL

CONNECTOR

STEEL CLAMP TO SECURE BRAID(S)TO CONNECTOR BACKSHELL

Shield Grounding Example for Bulkhead Connectorsand for Non-Panel Mounted/Non-Rack Mounted Units

Figure 4-2K




NOTES FOR FIGURE 4-2K

1. The shield grounding example shows 2 shielded cable shields grounded at aconnector backshell using a length of flat braid.



4. Each braid shall have a maximum of 6 pigtail wires connected to it. Becauseof the jumper wire, each braid can ground up to 12 shielded cables.

5. If more than 12 shielded cables require grounding at a connector, useadditional braids as required.

6. Cover the exposed braid between the backshell and the pigtail wires withinsulating tubing.

7. Connector strain reliefs can be used in lieu of backshells. Tie braid tostrain relief using a mounting lug crimped or soldered to braid end (NOTE:Backshells are preferable over strain reliefs).

8. Bulkhead connector shield grounding assumes that the bulkhead connectors areproperly bonded to the bulkhead itself and that the bulkhead material isconductive and electrically bonded to the airframe.

9. The use of connector strain reliefs or backshells is not mandatory. Ifneither is used, the 1/4 inch wide shield ground braid should be grounded toairframe ground with as short as run as possible, but no longer than 12inches from the harness break-out point.




4.2.2.3D Units Without Shield Grounding Requirements

The following unit does not have shield wires that can be grounded atthe unit connector:

FX-600 Flux Valve

4.2.3 Power/Signal Grounds - All DC power grounds shall be tied together, allsignal grounds shall be tied together, and all lighting grounds shall betied together. DC power, signal, and lighting ground groups are then tiedtogether at a single point and connected to the airframe. The aircraftgrounding diagram (figure 4-3) illustrates this grounding method.

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.

Aircraft GroundingFigure 4-3




NOTE: Because signal grounds are low currents, multiple signal grounds can beconnected to remote aircraft terminal blocks other than the centralgrounding blocks as long as these remote terminal blocks are isolated fromground. The various remote signal ground 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 grounding point.

4.3 Interconnect Requirements

The PRIMUS® 1000 Integrated Avionics System utilizes electrical andmechanical engage interlocks.

• The electrical interlocks consist of program pins on the unit’s matingconnector that electrically determine how a unit shall function.

• The mechanical interlocks are mechanically keyed connectors that preventunits from being incorrectly connected or installed.

4.3.1 Polarities - Installing the system in accordance with the interconnectinformation defined in this document will result in the following servophasing:

Roll Right - CCW drum rotation viewed from drum end

Pitch Up - CW drum rotation viewed from drum end

TO ASSURE THE FGC/SERVO WIRING IS CORRECT, THIS WIRING SHOULD BE 100%CONTINUITY CHECKED. THIS IS TO INSURE THE PROPER SERVO IS INSTALLED ANDTHE PHASING BETWEEN THE AUTOPILOT SENSORS AND AIRCRAFT CONTROLS IS CORRECTAS REFERENCED WITH THE ABOVE PHASING INFORMATION.




4.4 ICB Requirements

Maintaining proper bus cabling and stub connections within the aircraft isextremely important. The following installation guidelines have beenoptimized through actual tests to ensure reliable bus operation. Theseinstallation techniques reduce signal reflections and susceptance toradiated and conducted energy and radiated emissions. Alternate methods ofinstallation must maintain the shielding integrity and minimize unshieldedconductor lengths as illustrated in Figure 4-4 below.

Installation Diagram of an ICB Bus ConfigurationFigure 4-4




To minimize bus driver power to a practical limit, twisted-pair shieldedcable with a 125 ohm characteristic impedance shall be used. The airframemanufacturer can use Raychem 2524E0114 or Filotex 69654 or equivalent.

Bus wires are not required to be terminated at both ends.

The terminating resistors may be located inside the LRU’s.

The stub length outside the box, excluding the connector pin, shall be lessthan 4.3 inches. Butt splices with solder rings will be utilized for allstub interconnections.

The shield connections at each stub shall be accomplished with a butt splicewhich will provide a maximum shield to shield connection of 0.3 inches.

A minimum cable length of 23 inches is required between any two users. Thisis necessary to minimize reflections.

All stub wiring shall comprise twisted-pair unshielded wiring of suitablewire gauge (the use of thick insulation to minimize inter-wiring capacitanceand 24-gauge is recommended).

Because of the high levels of the HIRF and Lightning threats, it isrecommended that the shield for the IC bus should be grounded at both endsusing a 1-inch (maximum) length of 22 gauge wire.

4.5 IC/Display Unit Bus Interface

The IC/DU buses provide PFD, MFD, and EICAS data from the ICs to the DUs.The IC/DU bus layout is shown in Paragraph 6, Figure 6-9. The followingparagraphs define the electrical interface requirements for the IC/DisplayUnit interconnect.

• The IC/DU transmission lines shall have a characteristic impedance of 125± 10 ohms. The characteristic capacitance shall be 12 ± 2picofarads/foot. Raychem 2524E0114 (with thermorad jacket) cable,Filotex Part No. 69654 cable, or equivalent can be used. (This is ASCBtype cable.)

• Each DU has provisions for bus termination. The + and - inputs arealways used. The - input is tied to the TERM input to terminate the buswithin the display unit (see Figure 4-5).




High Speed Differential Input TerminationFigure 4-5

• DUs are to be connected to a bus as shown in Figure 4-6 (Terminated DU)or Figure 4-7 (Unterminated DU).

• The maximum cable length from an IC-600 to a DU is 200 feet.

• There shall be a minimum of 23 inches of cable between adjacent stubs(see Figure 4-7).

• The preferred method of constructing a DU stub connection is the same asfor the ASCB stub (see Figure 4-2). Using this method the unshieldedstub length can be up to 6 inches.

• Butt splices with solder rings will be utilized for all stubinterconnections (see Figure 4-2).

• The bus shield connections at each stub shall be accomplished with a buttsplice which will provide a maximum shield to shield connection of 0.3inches (see Figure 4-2). If a stub shield is used, connect the stubshield to the bus shield as shown in Figure 4-7 with a butt splice orminimum length (less than 2 inches) 20 AWG wire. All exposed wires atthe splice and wires used to connect shields at the splice shall becovered with an overbraid material. The overbraid material shall then betied to the shield or airframe ground.

• The Bus shields shall be grounded to the airframe ground at each LRUconnector as specified in Paragraph 5 with a minimum length 20 AWG wire.Refer to Paragraph 4.2.2 for proper shield grounding points and overbraidor backshell protection.

• It is very important that the DU/IC buses in a redundant system beinstalled with consideration for damage failure modes. Therefore, thebuses should be bundled separately wherever possible, should not passthrough common connectors or feedthroughs, and should not be installed inhigh risk areas such as wing leading edges, engine shrapnel path, etc.




200' MAX

23'' MIN 23'' MIN 23'' MIN

AD-21678-R3@

10''MAX

SG 1 MHZBUS

NOTES:1.

(NOTE 1)

TERM

UNTERMINATEDDU

UNTERMINATEDDU

TERMINATEDDU

THE STUB SHIELDING CAN BE ELIMINATED BY CONSTRUCTING THESTUB AS SHOWN IN FIG. 4-2, AND DISCUSSED IN PARAGRAPH 4.5

+

-

+ - + -

DU/IC Bus Interface (Terminated DU)Figure 4-6

NOTE: If a terminating DU is removed from the panel, all remaining DUsutilizing 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 noninductive 127 ohm,±1%, 1/4 watt, metal film. The cable length between the last stuband the termination resistor shall be a minimum of 23 inches. Thisoptional termination method is shown in Figure 4-4. Provideoverbraid protection for exposed wires and resistor at thetermination point.

200' MAX

23'' MIN 23'' MIN 23'' MIN

AD-21675-R3@

10''MAX

23'' MIN

SG 1MHZBUS

NOTES:1.

(NOTE 1)

UNTERMINATEDDU

UNTERMINATEDDU

UNTERMINATEDDU

THE STUB SHIELDING CAN BE ELIMINATED BY CONSTRUCTING THESTUB AS SHOWN IN FIG. 4-2, AND DISCUSSED IN PARAGRAPH 4.5CABLE: ASCB CABLE OR ELECTRICAL EQUIVALENT

+ - + - + -

127

DU/IC Bus Interface (Unterminated DU)Figure 4-7




4.6 WX/Display Unit Bus Interface

The WX/DU buses provide Weather Radar data from the WX unit to the DUs. TheWX/DU bus layout is shown in Paragraph 6, Figures 6-5 and 6-6. Thefollowing paragraphs define the electrical interface requirements for theWX/Display Unit interconnect.

• The WX/DU transmission lines shall have a characteristic impedance of 70± 10% ohms. The characteristic capacitance shall be 30 picofarads/footmax. Honeywell Part No. 3718911-1 cable or equivalent, such asESC 422402, shall be used. (NOTE: ASCB type cable cannot be used).

• Each DU has provisions for bus termination. The + and - inputs arealways used. The - input is tied to the TERM input to terminate the buswithin the display unit.

High Speed Differential Input TerminationFigure 4-8

• DUs are to be connected to a bus as shown in Figure 4-9. Only the DU atthe end of the cable shall be terminated.

• The maximum cable length from the WX to a DU is 50 feet.


• The preferred method of constructing a DU stub connection is the same asfor the ASCB stub (see Figure 4-2). Using this method the unshieldedstub length can be up to 6 inches.





DU/WX Bus Interface (Terminated DU)

50' MAX

23'' MIN 23'' MIN 23'' MIN

WX 1MHZPICTURE

BUS

AD-30105-R1@

10''MAX

(NOTE 1)

TERM

TERMINATEDDU

UNTERMINATEDDU

UNTERMINATEDDU

NOTES:

1.

+ - + -

+

-

THE STUB SHIELDING CAN BE ELIMINATED BY CONSTRUCTING THESTUB AS SHOWN IN FIG.4-2 AND DISCUSSED IN PARAGRAPH 4.6

Figure 4-9

NOTE: If a terminating DU is removed from the panel, all remaining DUsutilizing 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 noninductive 100 ohm,±1%, 1/4 watt, metal film. The cable length between the last stuband the termination resistor shall be a minimum of 23 inches. Thisoptional termination method is shown in Figure 4-10. Provideoverbraid protection for exposed wires and resistor at thetermination point.

DU/WX Bus Interface (Unterminated DU)

90' MAX

23'' MIN 23'' MIN 23'' MIN

AD-39744@

10''MAX

23'' MIN

100WX 1 MHzPICTUREBUS

(NOTE 1)

+ - + - + -

UNTERMINATEDDU

UNTERMINATEDDU

UNTERMINATEDDU

W

Figure 4-10




• The bus shield connections at each stub shall be accomplished with a buttsplice which will provide a maximum shield to shield connection of 0.3inches (see Figure 4-2). If a stub shield is used, connect the stubshield to the bus shield as shown in Figure 4-10 with a butt splice orminimum length (less than 2 inches) 20 AWG wire. All exposed wires atthe splice and wires used to connect shields at the splice shall becovered with an overbraid material. The overbraid material shall then betied to the shield or airframe ground.

• The DU and WX Bus shields shall be grounded to the airframe ground ateach LRU connector as specified in Paragraph 5 with a minimum length 20AWG wire. Refer to Paragraph 4.2.2 for proper shield grounding pointsand overbraid or backshell protection.

4.7 Radio System Bus (RSB) Interface

The RSB is the primary communication path between major subsystems of thePRIMUS® II Integrated Radio System. The RSB consists of multi-point serialsynchronous digital communications networks - one primary bus and twoon-side (backup) buses. Each bus is electrically isolated from the otherbuses. The RSB bus layout is shown in Paragraph 6, Figure 6-21. The RSBcomplies with RTCA Document DO-160C which requires that the followinginstallation requirements be met:

• There are three independent RSBs denoted "PRIMARY," "L SECONDARY," and "RSECONDARY" each consisting of one shielded wire pair.

• The RSB transmission lines shall have a characteristic impedance of125 ± 5 ohms. The characteristic capacitance shall be 12 ± 2picofarads/foot. Raychem 2524E0114 (with thermorad jacket) cable,Filotex Part No. 69654 cable, or equivalent can be used.

• Each RSB transmission line pair shall be terminated at its two ends withnoninductive 120 ohm resistors ±5%, 1/4 watt, metal film. 127 ohm ±1%resistors may also be used. The cable length between the last stub andthe termination resistor shall be 23 inches. Provide overbraidprotection for exposed wires and resistor at termination point.

• The RSB transmission lines shall have a maximum length betweenterminators of 150 feet.


• The preferred method of constructing an RSB stub connection is the sameas for the ASCB (see Figure 4-2). Using this method the unshielded stublength can be up to 6 inches.




• Butt splices with solder rings will be utilized for all stubinterconnections (Ref. Figure 4-2).

• The RSB bus shield connections at each stub shall be accomplished with abutt splice which will provide a maximum shield to shield connection of0.3 inches (see Figure 4-2). If a stub shield is used, connect the stubshield to the RSB bus shield as shown in Figure 4-11 with a butt spliceor minimum length (less than 2 inches) 20 AWG wire. All exposed wires atthe splice and wires used to connect shields at the splice shall becovered with an overbraid material. The overbraid material shall then betied to the shield or airframe ground.

• The RSB shield shall be grounded to the airframe ground at each LRUconnector as specified in Paragraph 5 with a minimum length 20 AWG wire(see Figure 4-11). Refer to Paragraph 4.2.2 for proper shield groundingpoints and overbraid or backshell protection.

• It is very important that the three RSB buses in a redundant system beinstalled with consideration for damage failure modes. Therefore, thebuses should be bundled separately wherever possible, should not passthrough common connectors or feedthroughs, and should not be installed inhigh risk areas such as wing leading edges, engine shrapnel path, etc.

4.8 Digital Audio Bus Interface Requirements

The Digital Audio bus is the primary audio communication path between majorsubsystems of the PRIMUS® II Integrated Radio System and the Audio Panels.The Digital Audio bus consists of multi-point serial synchronous digitalcommunications networks - two primary buses. Each bus is electricallyisolated from the other bus. The Digital Audio bus layout is shown inParagraph 6, Figure 6-23. The Digital Audio bus complies with RTCA DocumentDO-160C which requires that the following installation requirements be met:

• There are two independent Digital Audio buses denoted "Digital Audio 1"and "Digital Audio 2" each consisting of one shielded wire pair.

• The Digital Audio bus transmission lines shall have a characteristicimpedance of 125 ± 5 ohms. The characteristic capacitance shall be 12 ±2 picofarads/foot. Raychem 2524E0114 (with thermorad jacket) cable,Filotex Part No. 69654 cable, or equivalent can be used.




150' MAX

23'' MIN 23'' MIN 23'' MIN

AD-21676-R3@

10''MAX

120 W120 W

CABLE: RAYCHEM 2524E0114 OR FILOTEX 69654.125 W , THERMORAD JACKET

NOTES:THE STUB SHIELDING CAN BE ELIMINATED BY CONSTRUCTING THESTUB AS SHOWN IN FIG. 4-2 AND DISCUSSED IN PARAGRAPH 4.7

1.

(NOTE 1)

SUBSYSTEMN

SUBSYSTEM2

SUBSYSTEM1

RSB Bus ConstructionFigure 4-11




• Each Digital Audio bus transmission line pair shall be terminated at itstwo ends with noninductive 120 ohm resistors ±5%, 1/4 watt, metal film.127 ohm ±1% resistors may also be used. The cable length between thelast stub and the termination resistor shall be 23 inches.

• The Digital Audio bus transmission lines shall have a maximum lengthbetween terminators of 150 feet.



• The Digital Audio bus shield connections at each stub shall beaccomplished with a butt splice which will provide a maximum shield toshield connection of 0.3 inches (see Figure 4-2). If a stub shield isused, connect the stub shield to the Digital Audio bus shield as shown inFigure 4-12 with a butt splice or minimum length (less than 2 inches) 20AWG wire. All exposed wires at the splice and wires used to connectshields at the splice shall be covered with an overbraid material. Theoverbraid material shall then be tied to the shield or airframe ground.

• The Digital Audio bus shield shall be grounded to the airframe ground ateach LRU connector as specified in Paragraph 5 with a minimum length 20AWG wire (see Figure 4-12). Refer to Paragraph 4.2.2 for proper shieldgrounding points and overbraid or backshell protection.

• It is very important that the two Digital Audio buses in a redundantsystem be installed with consideration for damage failure modes.Therefore, the buses should be bundled separately wherever possible,should not pass through common connectors or feedthroughs, and should notbe installed in high risk areas such as wing leading edges, engineshrapnel path, etc.




150' MAX

23'' MIN 23'' MIN 23'' MIN

AD-39745@

10''MAX

120 W120 W

(NOTE 1)

SUBSYSTEMN

SUBSYSTEM2

SUBSYSTEM1

Digital Audio Bus ConstructionFigure 4-12




4.9 Special Considerations for Master Caution and Master Warning Lamp Drivers

In order to supply sufficient current to the master caution and masterwarning lamps, current draw restrictions on other lamp driver outputs arerequired. Each ’bank’ of lamp driver outputs shall be limited to less than500 milliamps of current draw as shown in Figure 4-13 below.

Lamp Driver Current Draw RequirementsFigure 4-13




5.0 ELECTRICAL INTERCONNECT DEFINITION

This paragraph provides the electrical interconnect definition for thePRIMUS® 1000 Digital Integrated Avionics System.

The interconnect information is ordered per unit connector designationnumbers.

5.1 Interconnect Format Definition

Each connection is typically shown as indicated below.

1 2 3 4 5 6IO DESCRIPTION FROM PIN AWG TO PIN(S) COMMENTSBP

(O) SERVO DRIVE (H) 29AJ1-1 (22)-T-S----- 29J1-2(O) SERVO DRIVE (L) 29AJ1-2 (22)-T-S----- 29J1-1

1 I = INPUTO = OUTPUTB = BI-DIRECTIONAL BUSP = POWERI/O = INPUT/OUTPUT

2 DESCRIPTION OF SIGNAL FUNCTION

3 FROM CONNECTION

UNIT DESIGNATION 29ACONNECTOR J1PIN -1

4 MINIMUM WIRE GAUGE SIZE

S = Shield IS = Inner ShieldT = Twisted OS = Outer Shield

5 TO CONNECTION

UNIT DESIGNATION 29CONNECTOR J1PIN -2




6 MISC. COMMENTS

NOTES: 1. A letter "C" before a Unit No. indicates copilot’s side(2nd) LRU. A letter "E" before a Unit No. indicates 3rdLRU.

2. All discrete output signals include the logic type inparenthesis after the function name. The first statewithin the parenthesis enables the function name.

Example: DU VALID (GND/OPEN)

This means the DU is valid with a ground.

5.2 Notes

The following notes are referenced throughout the interconnect interfacedata.

NOTES: 1. Recommended wire gauge for power input pins should only be usedif total voltage drop from power source to LRU does not exceed 1volt. Refer to paragraph 4.1.3 for determining proper wiregauge if the length of the wire is such that the voltage dropexceeds 1 volt for the recommended wire gauge.

2. Use Raychem 2524E0114 (with thermorad jacket) cable, FilotexPart No. 69654, or equivalent. This same cable is used forASCB, RSB, and SG/DU bus.




ATTITUDE AND HEADING REFERENCE UNIT NO. 1AH-800

IOBP Function Connector Pin Connects To

(B) ASCB ONSIDE DATA (H) 1J1A-C10(B) ASCB ONSIDE DATA (L) -C13

(I) SHOP MAINTENANCE -E1(I) RESERVED -E2(I) RESERVED -E3

(B) ASCB XSIDE DATA (H) -F10(B) ASCB XSIDE DATA (L) -F13

(B) MEM ACCESS DATA (TX) -H3 (24)-T-S----------S--(B) MEM ACCESS DATA (RX) -H4 (24)-T-S----------S-- FIG. 6-34(B) MEM ACCESS COM -H7 (24)-T-S----------S--(B) MEM ACCESS MODE SEL -H10 (24)-T-S----------S--

SHIELD GND ───────────┘ └─── SHIELD GND(B) ASCB BU DATA (H) -K3(B) ASCB BU DATA (L) 1J1A-K5




ATTITUDE AND HEADING REFERENCE UNIT NO. 1 (cont)AH-800


(O) PROGRAM PIN COMMON 1J1B-A1

(I) LAMP TEST (RESERVED) -A7(I) RESERVED -A8(I) RESERVED -A9(I) TEST COMMAND (RESERVED) -A10 (24)----------------- TEST SWITCH,

FIG. 6-3

(O) SERIAL DATA OUT (H) -B6(O) SERIAL DATA OUT (L) -B7

(I) SERIAL DATA IN (H) -B10(I) SERIAL DATA IN (L) -B11

(O) AHRS FAIL ANNUNCIATOR-D2

(O) BASIC MODE ANNUNCIATOR(RSVD) -D3

(O) DISCRETE COMMON (RSVD) -D7(O) OVERTEMP WARN ANNUNCIATOR

(RSVD) -E1(O) SLAVING FAIL ANNUNCIATOR

(RSVD) -E2(O) DG MODE ANNUNCIATOR (RSVD) -E3

(O) ARINC 429 OUT #2 (H) -E5 (24)-T-S----------S-- FIG.(O) ARINC 429 OUT #2 (L) -E6 (24)-T-S----------S-- 6-10

SHIELD GND ─────────────┘ └── SHIELD GND

(O) MAG HDG SYNCHRO (X) (RSVD) -E10(O) MAG HDG SYNCHRO (Y) (RSVD) -E11(O) MAG HDG SYNCHRO (Z) (RSVD) -E12

(O) ALIGN ANNUNCIATOR(RSVD) -F3

(I) MEMORY MODULE INHIBIT -F6 (24)----------------- MEM MODULE (ORN)(I) MEMORY MODULE POWER -F7 (24)----------------- MEM MODULE (RED)(I) MEMORY MODULE RETURN -F8 (24)----------------- MEM MODULE (BLK)(I) MEMORY MODULE CLOCK -F9 (24)----------------- MEM MODULE (YEL)(I) MEMORY MODULE DATA 1J1B-F11 (24)----------------- MEM MODULE (BRN)






(I) MAG HDG 26 V 400 HZ REF(RSVD) 1J1B-F13

(O) ARINC 429 OUT 4 (H) -F14(O) ARINC 429 OUT 4 (L) -F15

(O) AHRS VALID (RSVD) -G1(O) MAG HDG VALID (RSVD) -G2

(O) ARINC 429 OUT 1 (H) -G7 (24)-T-S----------S-- FIG.(O) ARINC 429 OUT 1 (L) -G8 (24)-T-S----------S-- 6-10

SHIELD GND ───────────┘ └── SHIELD GND

(I) 26 V 400 HZ RET (RSVD) -G13

(I) HEADING SLEW COM -H1 (24)----────ô-------- (I) HEADING SLEW 0 -H2 (24)--------│-------- FIG. 6-4(I) HEADING SLEW 1 -H3 (24)--------│-------- (I) HEADING SLEW 2 -H4 ────────────┘(I) HEADING SLEW 3 -H5(I) DG MODE SELECT -H6 (24)----------------- INSTRUMENT PANEL

FIG. 6-4

(I) FLUX VALVE INPUT A -H8 (22)-T-S----------S-- 4J1-A(I) FLUX VALVE INPUT B -H9 (22)-T-S----------S-- 4J1-B(I) FLUX VALVE INPUT C -H10 (22)-T-S----------S-- 4J1-C(I) FLUX VALVE COMMON F -H11 (22)-T-S----------S-- 4J1-F

SHIELD GND ─────────┘ └── NC

(O) FLUX VALVE EXCITATION D -H12 (22)-T-S----------S-- 4J1-D(O) FLUX VALVE EXCITATION E -H13 (22)-T-S----------S-- 4J1-E

SHIELD GND ───────────┘ └── NC

(O) ARINC 429 IN #2 (H) -J10 (24)(O) ARINC 429 IN #2 (L) -J11 (24)

(O) AUX POWER ANNUNCIATOR(RSVD) 1J1B-J15






(I) ARINC 429 #1 IN (H) 1J1B-K4 (24)-T-S---------S-- FIG.(I) ARINC 429 #1 IN (L) -K5 (24)-T-S---------S-- 6-11


(0) ARINC 429 #3 OUT (H) -K12 (24)-T-S---------S-- FIG.(0) ARINC 429 #3 OUT (L) -K13 (24)-T-S---------S-- 6-10


(I) WOW 1J1B-K15 (24)---------------- FIG. 6-2






(I) 28 V DC AUXILIARY 1J1C-2 (22)------------------ FIG. 6-1

(O) CONTROLLER 28 V DC PWR -6

(I) 28 V DC PRIMARY -7 (22)------------------ FIG. 6-1

(O) 28 V DC RETURN -8 (22)------------------ DC PWR GND

(I) CHASSIS GND 1J1C-11




FLUX VALVE NO. 1FX-600


(O) STATOR A 4J1-A (22)-T-S-----------S-- 1J1B-H8(O) STATOR B -B (22)-T-S-----------S-- 1J1B-H9(O) STATOR C -C (22)-T-S-----------S-- 1J1B-H10(O) STATOR COMMON F 4J1-F (22)-T-S-----------S-- 1J1B-H11

NC ────────┘ └── SHIELD GND

(I) EXCITATION D -D (22)-T-S-----------S-- 1J1B-H12(I) EXCITATION E -E (22)-T-S-----------S-- 1J1B-H13





PILOT’S MADCAZ-850


(I) UNIT ID 1 9J1-1(I) UNIT ID 2 -2(I) UNIT ID 3 -3 (24)------------------ SIGNAL GROUND(I) UNIT ID 4 -4 -(I) UNIT ID 5 -5 (24)------------------ SIGNAL GROUND(I) UNIT ID 6 -6(I) UNIT ID 7 -7(I) SDI 1 -8 (24)------------------ SIGNAL GROUND(I) SDI 2 -9(I) SDI 3 -10

SPARE -11(I) WEIGHT-ON-WHEELS -12 (24)------------------ FIG. 6-2(I) SIGNAL GROUND -13 (24)------------------ SIGNAL GROUND

SPARE -14(I) TAT PROBE HEAT DISCRETE -15 (24)------------------ TAT PROBE

HEAT SIGNAL(I) BARO SELECT (IN/HPA) -16 (24)------------------ 190J2B-82(I) SPARE IN #3 GND -17(I) SPARE IN #4 GND -18(I) SPARE IN #1 +28 V -19 ---------------------- RESERVED FOR

ALT. VMO SIGNAL(I) SPARE IN #2 +28 V -20(O) DISCRETE OUT #1(170 KTS) -21 (24)------------------ RUDDER TRIM

SYSTEM(O) DISCRETE OUT #2(205 KTS) -22 (24)------------------ SPOILER COMMAND(O) DISCRETE OUT #3(24,500 FT) -23 (24)------------------ SYSTEM(O) DISCRETE OUT #4(TBD KTS) -24(O) ALTITUDE TRIP POINT(TBD FT) -25(P) +28 V DC HI -26 (22)------------------ FIG. 6-1(P) +28 V DC LO -27 (22)------------------ DC GROUND(O) OVERSPEED WARNING DISC -28 (24)------------------ CREW ALERTING

SYSTEM(O) MADC VALID DISC -29(B) ASCB ON SIDE PRIMARY HI -30(I) TEMP PROBE HI -31 (24)-T-S-----------S-- 500 OHM TEMP PROBE(I) TEMP PROBE LO -32 (24)-T-S-----------S-- 500 OHM TEMP PROBE

SHIELD GND ────────────┘ └── SHIELD GNDSPARE -33

(B) ASCB ON SIDE PRIMARY LO -34(I) AOA HI -35 -(I) AOA ARM -36 -(I) AOA LO -37 -(I) CALIBRATION ENABLE 9J1-38 --------------------- SHOP USE ONLY




PILOT’S MADC (cont)AZ-850


SPARE 9J1-39SPARE -40SPARE -41

(I) ATC ENABLE DISC -42(O) ATC A1 -43(O) ATC A2 -44(O) ATC A4 -45(O) ATC B1 -46(O) ATC B2 -47(O) ATC B4 -48(O) ATC C1 -49(O) ATC C2 -50(O) ATC C4 -51(O) ATC D4 -52

SPARE -53SPARE -54

(B) RS-232 RX IN HI -55 (24)-T-S----------S--(B) RS-232 LO -56 (24)-T-S----------S-- FIG. 6-34(B) RS-232 TX OUT HI -57 (24)-T-S----------S--

SHIELD GND ────────────┘ └─── SHIELD GND

(I) VMO SELECT -58(B) ASCB ON SIDE BACKUP HI -59(B) ARINC 429 BUS 1 HI -60 (24)-T-S----------S-- FIG.(B) ARINC 429 BUS 1 LO -61 (24)-T-S----------S-- 6-11

SHIELD GND ────────────┘ └── SHIELD GND

(B) ASCB ON SIDE BACKUP LO -62(B) ARINC 429 BUS 2 HI -63 (24)-T-S----------S-- FIG.(B) ARINC 429 BUS 2 LO -64 (24)-T-S----------S-- 6-11


(B) ASCB X-SIDE PRI (H) -65(B) ARINC 429 BUS 3 HI -66 (24)-T-S----------S-- FIG.(B) ARINC 429 BUS 3 LO 9J1-67 (24)-T-S----------S-- 6-11





PILOT’S MADC (cont)AZ-850


(B) ARINC 429 BUS 4 HI 9J1-68 (24)-T-S----------S-- FIG.(B) ARINC 429 BUS 4 LO 9J1-69 (24)-T-S----------S-- 6-11


(I) FUNCTIONAL TEST DISC -70 (24)----------------- FIG. 6-3(I) BARO SELECT DISC (STD) -71 (24)----------------- 130J1-46(I) SSEC DISABLE(GND=DISABLE) -72(I) SPARE -73 --------------------- SHOP USE ONLY

(I) BARO-CORRECTION A (H) -74 (24)-T-S----------S-- 130J1-21(I) BARO-CORRECTION B (L) -75 (24)-T-S----------S-- 130J1-25


SPARE -76(B) ASCB CROSS SIDE PRIMARY LO -77

SPARE -78SPARE 9J1-79




FLIGHT GUIDANCE CONTROLLERGC-550


(I) PILOT MODE GND 11J1-1 (22)------------------ SIGNAL GND(I) COPILOT MODE GND -2(P) PANEL LGHTG 5 V (H) -3 (22)------------------ FIG. 6-7(P) LGHTG COMMON -4 (22)------------------ DC GND

ANNUNCIATOR LIGHTING -5 (22)------------------ DAY/NIGHT SWITCHSPARE -6

(O) #1 PUSHBUTTON (FD1) -7 (24)------------------ 190J1B-48(O) #2 PUSHBUTTON (AP ENG) -8 (22)------------------ 190J2B-85(O) #3 PUSHBUTTON (YD ENG) -9 (22)------------------ 190J2B-83(O) #4 PUSHBUTTON (CPL) -10 (24)------------------ 190J2B-55,

C190J2B-55(O) #5 PUSHBUTTON (HDG) -11 (24)------------------ 190J1B-22,

C190J1B-22(O) #6 PUSHBUTTON (BNK) -12 (24)------------------ 190J2B-56,

C190J2B-56(O) #7 PUSHBUTTON (NAV) -13 (24)------------------ 190J1B-24,

C190J1B-24(O) #8 PUSHBUTTON (APR) -14 (24)------------------ 190J1B-25,

C190J1B-25(O) #9 PUSHBUTTON (ALT) -15 (24)------------------ 190J1B-26,

C190J1B-26(O) #10 PUSHBUTTON (SPD) -16 (24)------------------ 190J1B-27,

C190J1B-27(O) #11 PUSHBUTTON (FLC) -17 (24)------------------ 190J1B-28,

C190J1B-28(O) #12 PUSHBUTTON (RESERVED) -18 -----NC

(O) #13 PUSHBUTTON (VS) -19 (24)------------------ 190J1B-30,C190J1B-30

(O) #14 PUSHBUTTON (FD2) -20 (24)------------------ C190J1B-48(P) +15 V MODE POWER -21 (24)------------------ 190J2B-59,

129J1-C(I) #1 LAMP (FD2) -22 (24)------------------ C190J1B-36(I) #2 LAMP (AP ENG) -23 (22)------------------ 190J2B-86(I) #3 LAMP (YD ENG) -24 (22)------------------ 190J2B-84(I) #4 LAMP (CPL L) -25 (24)------------------ 190J2A-99(I) #5 LAMP (HDG) -26 (24)------------------ 190J2A-106,

C190J2A-106(I) #6 LAMP (BNK) -27 (24)------------------ 190J2A-98,

C190J2A-98(I) #7 LAMP (NAV) -28 (24)------------------ 190J2A-105,

C190J2A-105(I) #8 LAMP (APR) -29 (24)------------------ 190J2A-104,

C190J2A-104(I) #9 LAMP (ALT) 11J1-30 (24)------------------ 190J2A-103,

C190J2A-103




FLIGHT GUIDANCE CONTROLLER (cont)GC-550


(I) #10 LAMP (SPD) 11J1-31 (24)------------------ 190J2A-102,C190J2A-102

(I) #11 LAMP (FLC) -32 (24)------------------ 190J1B-37,C190J1B-37

(I) #12 LAMP (FD1) -33 (24)------------------ 190J1B-36

(I) #13 LAMP (VS) -34 (24)------------------ 190J2A-101,C190J2A-101

SPARE -35(I) #15 LAMP (CPL R) -36 (24)------------------ C190J2A-99

SPARE -37SPARE -38SPARE -39SPARE -40

SPARE -41SPARE -42SPARE -43

(O) #1 SET KNOB 1 -44 (24)-T-S-----------S-- 115J1-9(O) #1 SET KNOB 2 CRS 1 -45 (24)-T-S-----------S-- 115J1-10(O) #1 SET KNOB COMMON -46 (24)-T-S-----------S-- 115J1-11

SHIELD GND ─────────┘ └── SHIELD GND

(O) #2 SET KNOB 1 -47 (24)-T-S-----------S-- 115J1-12, │ │ C115J1-12

(O) #2 SET KNOB 2 HDG -48 (24)-T-S-----------S-- 115J1-13, │ │ C115J1-13

(O) #2 SET KNOB COMMON -49 (24)-T-S-----------S-- 115J1-14,│ │ C115J1-14


(O) #3 SET KNOB 1 -50 (24)-T-S-----------S-- 115J1-15, │ │ C115J1-15

(O) #3 SET KNOB 2 ALT -51 (24)-T-S-----------S-- 115J1-16, │ │ C115J1-16

(O) #3 SET KNOB COMMON -52 (24)-T-S-----------S-- 115J1-17,│ │ C115J1-17


(O) #4 SET KNOB 1 -53 (24)-T-S-----------S-- 115J1-18, │ │ C115J1-18

(O) #4 SET KNOB 2 SPD -54 (24)-T-S-----------S-- 115J1-19, │ │ C115J1-19

(O) #4 SET KNOB COMMON 11J1-55 (24)-T-S-----------S-- 115J1-20,│ │ C115J1-20





FLIGHT GUIDANCE CONTROLLER (cont)GC-550


(O) #5 SET KNOB 1 11J1-56 (24)-T-S-----------S-- C115J1-9(O) #5 SET KNOB 2 CRS 2 -57 (24)-T-S-----------S-- C115J1-10(O) #5 SET KNOB COMMON -58 (24)-T-S-----------S-- C115J1-11


SPARE -59SPARE -60SPARE -61

(O) CRS 1 PUSH TO SYNC -62 (24)------------------ 115J1-70(O) HDG PUSH TO SYNC -63 (24)------------------ 115J1-71,

C115J1-71RESERVED -64

(O) SPD (IAS/MACH SEL) -65 (24)------------------ 115J1-68,C115J1-68

(O) CRS 2 PUSH TO SYNC -66 (24)------------------ C115J1-70 -67 -68 -69 -70 -71 -72

SPARE -73 -74 -75 -76 -77 -78

SPARE 11J1-79




AILERON SERVOSM-200


(I) MOTOR INPUT + 12J1-A (18)-T-S------------S-- 190J2B-101(I) (CCW DRUM ROTATION) - -B (18)-T-S------------S-- 190J2B-102

SHIELD GND ────────┘ └─── SHIELD GND

(P) SERVO POWER GND -C

(O) POSITION SYNCHRO EXC H -D(O) 26 VAC, 400 HZ C -E

-F (22)------------------- 190J2B-88,115J1-27(I) CLUTCH EXCITATION -G

-H-J (22)───┐

GNDTACH SHIELD -K

(O) TACHOMETER OUTPUT + -L (24)-T-S------------S-- 190J2B-99(O) (CCW DRUM ROTATION) - -N (24)-T-S------------S-- 190J2B-100


X -P(O) POSITION SYNCHRO OUTPUT Y -R

Z -S

-MSPARES -T

-U 12J1-V




ELEVATOR SERVOSM-200






-F (22)------------------- 190J2B-89,HSCU(I) CLUTCH EXCITATION -G

-H-J (22)───┐

GNDTACH SHIELD -K

(O) TACHOMETER OUTPUT + -L (24)-T-S------------S-- 190J2B-103(O) (CCW DRUM ROTATION) - -N (24)-T-S------------S-- 190J2B-104



Z -S

-MSPARES -T

-U13J1-V




RUDDER SERVOSM-200






-F (22)------------------- 190J2B-87(I) CLUTCH EXCITATION -G

-H-J (22)───┐

GND(O) TACH SHIELD -K(O) TACHOMETER OUTPUT + -L (24)-T-S------------S-- 190J2B-96

(CCW DRUM ROTATION) - -N (24)-T-S------------S-- 190J2B-95SHIELD GND ────────┘ └─── SHIELD GND


Z -S

-MSPARES -T

-U 14J1-V




RADIO ALTIMETER NO. 1RT-300


SPARE 20J1-ASPARE -BSPARE -C

(I) TEST INHIBIT -D(O) OUTPUT TEST -E──┐

TRACK INVALID -F │SPARE -G │SPARE -H │SPARE -J │SPARE -K │

(O) TRIP NO. 4 (200 FT) -L │ (24)-------------- STALL PROTECTION│ COMPUTER

(P) +/- 15 V DC COMMON -M │(O) OUTPUT COMMON -N └(24)---T-S-------S-- 190J2A-50,

│ │ C190J2A-50,│ │ 193RMP-2J,│ │ 93RBP-3B

(I) ALT TRIP COMMON -P (24)-------│-------│-- DC GND(O) TRIP NO. 3 (50 FT) -R │ │

SPARE -S │ │(I) TEST* -T (24)-------│-------│-- FIG. 6-3(O) TRIP NO. 1 (1200 FT) -U │ │(O) TRIP NO. 2 (1500 FT) -V (24)-------│-------│-- AURAL WARNING

│ │ SYSTEM(O) ALT OUTPUT (EH) -W (24)-----T-S-------S-- 190J2A-51,

│ │ C190J2A-51│ │

SHIELD GND ──────────┘ └── SHIELD GND

(O) AUX OUTPUT (H) -X (24)----T-S--------S-- 193RMP-2H,193RBP-3A

(O) RAD. ALT VALID (28 V/OPEN) -Y (24)------------------ 190J2A-49,C190J2A-49,193RMP-2K193RBP-3C

+15 V DC -Z-15 V DC -a

(P) POWER GND -b (22)------------------ DC GND(P) +28 V DC 20J1-c (22)------------------ FIG. 6-1(O) TRANSMIT 20J2 * ------ô--------- 21J1 COAX TO TRANSMIT

------┘ ANTENNA(I) RECEIVE 20J3 * ------ô--------- 22J1 COAX TO TRANSMIT

------┘ ANTENNA




ANTENNA AND RECEIVER/TRANSMITTER UNITWU-650


(P) 28 V DC POWER 59J1-A (20)------------------- FIG. 6-1-B (20)------------------- FIG. 6-1

(P) POWER GROUND -X (20)------------------- DC GND-W (20)------------------- DC GND

(I) #2 CONTROL BUS H -aL -b

(I) #1 CONTROL BUS H -c (24)-T-S------------S-- 61J1-AL -d (24)-T-S------------S-- 61J1-B

SHIELD GND ────────┘ └── 61J1-M

CONTROL BUS SHIELD -p (24)(I) REMOTE ON -U (24)------------------- 61J1-R(I) GND FOR 429 STABILIZATION -T (24)------------------- SIG GND, 59J1-R

TRANSMIT ON -C-V

(I) STABILIZATION INPUT H -K (24)-T-S------------S-- 1J1B-K12(I) (ARINC 429) L -L (24)-T-S------------S-- 1J1B-K13

│ │ (FIG. 6-10)SHIELD GND ────────┘ └── SHIELD GND

-E(I) GND FOR INVERTED MOUNT -S(I) REACT COMPENSATION OVERRIDE -R (24)------------------- SIG GND, 59J1-T(I) GND FOR 200 MV/DEG -P

-J-F-Y-M-N

10V -H(I) STABILIZATION 400 HZ 26V -Z(I) REF INPUT 115V -D

COM -G(B) LEFT EFIS CONTROL BUS H -m (24)-T-S------------S-- 190J2A-17(B) L -n (24)-T-S------------S-- 190J2A-18

SHIELD GND ────────┘ └── SHIELD GND

(B) CENTER CONTROL BUS H -t(B) L -r(B) RIGHT EFIS CONTROL BUS H -e (24)-T-S------------S-- C190J2A-17(B) L -f (24)-T-S------------S-- C190J2A-18


59J1-q (24)




ANTENNA AND RECEIVER/TRANSMITTER UNIT (cont)WU-650


(B) H 59J1-g (24)-T-S-------------S-- 130J1-77, LEFT EFIS PICTURE │ │ 131J1-77 FIG.

(B) L -h (24)-T-S-------------S-- 130J1-64, 786-5│ │ 131J1-78

SHIELD GND ───────┘ └── SHIELD GND

(B) CENTER PICTURE BUS H -i(B) L -j(B) H -k (24)-T-S------------S-- C130J1-77,

RIGHT EFIS PICTURE BUS │ │ C131J1-77 FIG.(B) L 59J1-s (24)-T-S------------S-- C130J1-64, 78 6-6

│ │ C131J1-78 SHIELD GND ───────┘ └── SHIELD GND




PILOT’S WEATHER RADAR CONTROLLERWC-650


(B) SERIAL CONTROL (HI) 61J1-A (24)----T-S--------S-- 59J1-c(B) SERIAL CONTROL (LO) -B (24)----T-S--------S-- 59J1-d

│ └── SHIELD GNDSPARE -C │

(P) 28 V DC INPUT -D (22)------│----------- FIG. 6-1(P) 28 V DC GND -E (22)------│----------- DC PWR GND(I) CHASSIS GND -F (22)------│----------- CHASSIS GND

EDGE LIGHTING 28 V DC (+) -G │(P) EDGE LIGHTING 5 V AC/DC (+) -H (24)------│----------- FIG. 6-7(P) EDGE LIGHTING RETURN -J (24)------│----------- LIGHTING GND(I) ANNUNCIATOR DIMMING -K (24)------│----------- DAY NIGHT LOGIC

SPARE -L │CONTROL BUS SHIELD GND -M (24)-----─┘SPARE -N

(I) FSB1 -P (24)------------------ FIG. 6-2(O) REMOTE ON -R (24)------------------ 59J1-U

FSB2 -SOFF IN -TOFF OUT 61J1-U




DISPLAY CONTROLLER NO. 1DC-550


(I) SIGNAL GND 115J1-1 (22)------------------ SIGNAL GND(P) LGHTG 28 V (H) -2(P) LGHTG 5 V (H) -3 (22)------------------ FIG. 6-7(P) LGHTG COM -4 (22)------------------ DC GND(P) +28 V DC POWER -5 (22)------------------ FIG. 6-1(P) DC POWER GND -6 (22)------------------ DC PWR GND(I) #8 PUSH BUTN (DU 2 BZ PB1) -7 (24)------------------ 131J1-46(I) #9 PUSH BUTN (DU 2 BZ PB2) -8 (24)------------------ 131J1-47(I) #1 SET KNOB 1 -9 (24)--T-S----------S-- 11J1-44(I) #1 SET KNOB 2 CRS 1 -10 (24)-T-S----------S-- 11J1-45(I) #1 SET KNOB COM -11 (24)-T-S----------S-- 11J1-46


(I) #2 SET KNOB 1 -12 (24)-T-S----------S-- 11J1-47,C115J1-12(I) #2 SET KNOB 2 HDG -13 (24)-T-S----------S-- 11J1-48,C115J1-13(I) #2 SET KNOB COM -14 (24)-T-S----------S-- 11J1-49,C115J1-14


(I) #3 SET KNOB 1 -15 (24)-T-S----------S-- 11J1-50,C115J1-15(I) #3 SET KNOB 2 ALT -16 (24)-T-S----------S-- 11J1-51,C115J1-16(I) #3 SET KNOB COM -17 (24)-T-S----------S-- 11J1-52,C115J1-17


(I) #4 SET KNOB 1 -18 (24)-T-S----------S-- 11J1-53,C115J1-18(I) #4 SET KNOB 2 SPD -19 (24)-T-S----------S-- 11J1-54,C115J1-19(I) #4 SET KNOB COM -20 (24)-T-S----------S-- 11J1-55,C115J1-20


(I) #5 SET KNOB 1 -21 (24)-T-S----------S-- 131J1-21(I) #5 SET KNOB 2 MFD -22 (24)-T-S----------S-- 131J1-25(I) #5 SET KNOB COM -23 (24)-T-S----------S-- 131J1-63


(I) #6 SET KNOB 1 -24 (24)-T-S----------S-- 132J1-21,C115J1-24(I) #6 SET KNOB 2 EICAS -25 (24)-T-S----------S-- 132J1-25,C115J1-25(I) #6 SET KNOB COM -26 (24)-T-S----------S-- 132J1-63,C115J1-26


(I) 28V AUTOPILOT CLUTCH -27 (22)----------------- 190J2B-88, 12J1-FSPARE 115J1-28




DISPLAY CONTROLLER NO. 1 (cont)DC-550


(O) AUTOPILOT OFF LIGHT 115J1-29 (22)----------------- FIG. 6-15(O) AUTOPILOT OFF HORN -30 (22)----------------- FIG. 6-15

SPARE -31(I) TCS -32 (24)----------------- FIG. 6-17(I) 28V AUTOPILOT DISCONNECT -33 (24)----------------- FIG. 6-16(B) DC/SG BUS (H) -34 (24)-T-S----------S-- 190J2A-15(B) DC/SG BUS (L) -35 (24)-T-S----------S-- 190J2A-16

SHIELD GND ─────────┘ └── SHIELD GND(B) DC/MG BUS (H) -36(B) DC/MG BUS (L) -37

PFD DIM (H) -38PFD DIM (L) -39

MFD DIM (H) -40MFD DIM (L) -41

(I) LIGHT + HORN DISABLE -42 (22)----------------- 190J2B-79,115J1-43(I) MOMENTARY LIGHT DISABLE -43 (22)----------------- 190J2B-79,115J1-42(I) MOMENTARY HORN DISABLE -44 (22)----------------- 190J2B-77(I) CHASSIS GND -45 (22)----------------- CHASSIS GND(I) LAMP TEST GND -46(I) #10 PUSH BUTTN (DU 2 BZ PB3)-47 (24)----------------- 131J1-50(I) #11 PUSH BUTTN (DU 2 BZ PB4)-48 (24)----------------- 131J1-51(I) #12 PUSH BUTTN (DU 2 BZ PB5)-49 (24)----------------- 131J1-60

PFD DIM (H) -50PFD DIM (W) -51PFD DIM (L) -52

(O) DH SET (H) -53 (24)-T-S----------S-- 190J2A-12(O) DH SET (W) -54 (24)-T-S----------S-- 190J2A-13(O) DH SET (L) -55 (24)-T-S----------S-- 190J2A-10

SHIELD GND ─────────┘ └── SHIELD GND(I) #13 PUSH BUTTN (DU 2 BZ PB6)-56 (24)----------------- 131J1-62

#14 PUSH BUTTN -57#15 PUSH BUTTN -58ADI ON GND -59

(I) MASTER CAUTION RESET BUTTON -60 (24)----------------- FIG. 6-33(I) MASTER WARNING RESET BUTTON -61 (24)----------------- FIG. 6-33(I) #18 PUSH BUTTN -62(I) HSI ON GND -63(I) #19 PUSH BUTTN -64(I) #20 PUSH BUTTN -65(I) #21 PUSH BUTTN (IN/HPA) -66 (24)----------------- 130J1-47(I) WX ON GND 115J1-67




DISPLAY CONTROLLER NO. 1 (cont)DC-550


(I) #22 PUSH BUTTN (SPD 115J1-68 (24)----------------- 11J1-65,IAS/MACH SEL) C115J1-68

(I) #23 PUSH BUTTN (RESERVED) -69

(I) #24 PUSH BUTTN -70 (24)----------------- 11J1-62(PUSH SYNC CRS 1)

(I) #25 PUSH BUTTN -71 (24)----------------- 11J1-63,C115J1-71(PUSH SYNC HDG)

(I) #1 SWITCH (DU #4 PFD SELECT)-72 (24)----------------- FIG. 6-9(I) #2 SWITCH (AHRS REVERSION) -73 (24)----------------- FIG. 6-10(I) #3 SWITCH (MADC REVERSION) -74 (24)----------------- FIG. 6-11

(I) #4 SWITCH (DAU CH A -75 (24)-----------------REVERSION) FIG. 6-12

(I) #5 SWITCH (DAU CH B -76 (24)-----------------REVERSION)

(I) #6 SWITCH (DU #2 PFD SELECT)-77 (24)-----------------(I) #7 SWITCH (DU #2 EICAS -78 (24)----------------- FIG. 6-9

SELECT) (I) #8 SWITCH (DU #4 115J11-79 (24)-----------------

EICAS SEL)




TURN KNOB/PITCH WHEEL CONTROLLERPC-400


(I) TURN KNOB -15V INPUT 129J1-A (24)-T-S-----------S-- 190J2B-60(O) TURN KNOB SIGNAL -B (24)-T-S-----------S-- 190J2B-73(I) TURN KNOB +15V INPUT -C (24)-T-S-----------S-- 190J2B-59, 11J1-21


(I) TURN KNOB SIGNAL GND -D (22)------------------ SIGNAL GNDSPARE -E

(I) TURN KNOB SWITCH (COM) -F (24)------------------ +28 VOLT SERVO POWER(O) TURN KNOB IN DETENT -G(O) TURN KNOB NOT IN DETENT -H (24)------------------ 190J2B-75,

C190J2B-75(P) 0 - 28 V EDGE LIGHTING -J(P) ANNUNC POWER GND -K(O) RESERVED -L(O) RESERVED -M(P) 0 - 28 V ANN DIM INPUT GND -N(I) RESERVED -P(I) RESERVED -R(I) RESERVED -S(I) RESERVED -T(O) PITCH WHEEL (+) -U (24)-T-S-----------S-- 190J2B-68(O) PITCH WHEEL (-) -V (24)-T-S-----------S-- 190J2B-69


(I) RESERVED -W(O) RESERVED -X

SPARE -Y(O) RESERVED -Z

SPARE -aSPARE -bSPARE -cSPARE -dSPARE -e

(I) RESERVED -f(P) 0 - 5 V EDGE LIGHTING -g (24)------------------ FIG 6-7(I) RESERVED -h(I) RESERVED -i(P) CHASSIS GND -j (24)------------------ CHASSIS GND(I) RESERVED -k(P) 0 - 28 V ANN DIMMING INPUT -m(P) EDGE LIGHTING LOW -n (24)------------------ LIGHTING GND

SPARE -pRESERVED -qRESERVED -rSPARE -sSPARE 129J1-t




PILOT’S PFDDISPLAY UNIT NO. 1

DU-870


(I) (H)130J1-1 (24)-T-S-----------S-- AIRCRAFTBRIGHTNESS POT (W) -14 (24)-T-S-----------S-- DIMMING

(I) (L) -13 (24)-T-S-----------S-- CONTROLNC ─────────┘ └─── SHIELD GND

(H) -2WX DIMMING (W) -15

(L) -3RESERVED -4RESERVED -5RESERVED -6RESERVED -7SPARE -8RESERVED -9RESERVED -10RESERVED -11RESERVED -12RESERVED -16RESERVED -17RESERVED -18

BUS 3 (H) -19(L) -20

(O) SET KNOB (BARO) (A) -21 (24)------------------ 9J1-74(I) DU PWR DN* -22 (24)------------------ FIG. 6-9(P) 5 V LIGHTING (H) -23 (22)------------------ FIG. 6-7(P) LIGHTING COMMON -24 (22)------------------ LIGHTING COMMON(O) SET KNOB (BARO) (B) -25 (24)------------------ 9J1-75

REMOTE LT SENSOR (H) -26REMOTE LT SENSOR (L) -27

(O) DLS OUT (H) -28 (24)-T-S-----------S-- 131J1-29(O) (L) -41 (24)-T-S-----------S-- 131J1-42


(I) ALS (H) -29 (24)-T-S-----------S-- 131J1-28(I) (L) -42 (24)-T-S-----------S-- 131J1-41


RESERVED -30(B) HDLC OUT + -31(B) HDLC OUT - 130J1-32




PILOT’S PFDDISPLAY UNIT NO. 1 (cont)

DU-870


BUS 3 TERM (L) 130J1-33RESERVED -34

(I) BUS 2 (H) -35 (24)-T-S-----------S-- FIG.(B) (L) -36 (24)-T-S-----------S-- 6-13


(O) DU VALID (GND/OPEN) -37(B) BUS 1 (H) -38 (24)-T-S----------S-- FIG.(B) (L) -39 (24)-T-S----------S-- 6-13


REMOTE LT SENSOR GND -40

REMOTE LT SENSOR PWR (H) -53(L) -54

RESERVED -43RESERVED -44BUS 4 TRM (L) -45

(O) PB (STD) -46 (24)----------------- 9J1-71PB (IN/HPA) -47 (24)----------------- 115J1-66RESERVED -48BUS 2 TERM (L) -49PB -50PB -51BUS 1 TERM (L) -52RESERVED -55RESERVED -56RESERVED -57BUS 4 (H) -58BUS 4 (L) -59

(O) PB -60WX BUS 2 TERM (L) -61DH (H) -62DH (COM) -63 (24)----------------- SIGNAL GND

(B) WX BUS 1 TERM (L) -64 (24)-T-S----------S-- FIG.(B) WX BUS 1 (H) -77 (24)-T-S----------S-- 6-5


DU OVERTEMP (GND/OPEN) -65(B) DU WRAPAROUND (H) -66 (24)-T-S----------S--

(ARINC 429) │ │ FIG. 6-13(B) DU WRAPAROUND (L) 130J1-79 (24)-T-S----------S--

(ARINC 429) │ │SHIELD GND ────────┘ └── SHIELD GND




PILOT’S PFDDISPLAY UNIT NO. 1 (cont)

DU-870


DH (L) 130J1-67RESERVED -68WX BUS 3 (H) -69WX BUS 3 (L) -70RESERVED -71SPARE -72SPARE -73WX BUS 2 (H) -74WX BUS 2 (L) -75SPARE -76WX BUS 1 (L) -78 (24)----------------- FIG. 6-5

(I) SIGNAL GROUND -80 (24)----------------- SIGNAL GNDRESERVED -81RESERVED -82WX BUS 3 TERM (L) -83RESERVED -84SPARE -85SPARE -86

(I) PORT SEL 3 -87 (24)----------------- FIG.6-9PORT SEL 2 -88PORT SEL 1 -89I.D. #3 -90I.D. #2 -91I.D. #1 -92RESERVED -93CHASSIS GND -94RESERVED -95RESERVED -96RESERVED -97RESERVED -98SOFTWARE ENABLE* -99SOFTWARE ENABLE* -100

(P) 28 V DC -101 (22)-----------------(P) 28 V DC -102 (22)----------------- FIG. 6-1(P) 28 V DC -103 (22)-----------------(P) 28 V DC RTN -104 (22)----------------- A/C 28 V DC(P) 28 V DC RTN -105 (22)----------------- PWR RETURN(P) 28 V DC RTN 130J1-106 (22)-----------------

* FLIGHT TEST ONLY




PILOT’S MFDDISPLAY UNIT NO. 2

DU-870


(I) (H) 131J1-1 (24)-T-S-----------S-- AIRCRAFTBRIGHTNESS POT (W) -14 (24)-T-S-----------S DIMMING

(I) (L) -13 (24)-T-S-----------S-- CONTROLNC ─────────┘ └─── SHIELD GND



BUS 3 (H) -19(L) -20

(O) SET KNOB #5(MFD) (H) -21 (24)----------------- 115J1-21DU PWR DN* -22

(P) 5 V LIGHTING (H) -23 (22)----------------- FIG. 6-7(P) LIGHTING COMMON -24 (22)----------------- LIGHTING COMMON(O) SET KNOB #5 (MFD) (L) -25 (24)----------------- 115J1-22

REMOTE LT SENSOR (H) -26

REMOTE LT SENSOR (L) -27(O) DLS OUT (H) -28 (24)-T-S-----------S-- 130J1-29(O) (L) -41 (24)-T-S-----------S-- 130J1-42


(I) ALS (H) -29 (24)-T-S-----------S-- 130J1-28(I) (L) -42 (24)-T-S-----------S-- 130J1-41


RESERVED -30(B) HDLC OUT + -31 (24)--T-S---------S-- FIG.(B) HDLC OUT - 131J1-32 (24)--T-S---------S-- 6-13





PILOT’S MFDDISPLAY UNIT NO. 2 (cont)

DU-870



(B) BUS 2 (H) -35 (24)-T-S----------S-- FIG.(B) BUS 2 (L) -36 (24)-T-S----------S-- 6-13


DU VALID (GND/OPEN) -37

(B) BUS 1 (H) -38 (24)-T-S---------S-- FIG.(B) BUS 1 (L) -39 (24)-T-S---------S-- 6-13


REMOTE LT SENSOR GND -40REMOTE LT SENSOR PWR (H) -53

(L) -54RESERVED -43RESERVED -44BUS 4 TRM (L) -45

(O) PB (BEZEL BUTTON 1) -46 (24)---------------- 115J1-7(O) PB (BEZEL BUTTON 2) -47 (24)---------------- 115J1-8

RESERVED -48BUS 2 TERM (L) -49

(O) PB (BEZEL BUTTON 3) -50 (24)---------------- 115J1-47(O) PB (BEZEL BUTTON 4) -51 (24)---------------- 115J1-48

BUS 1 TERM (L) -52RESERVED -55RESERVED -56RESERVED -57BUS 4 (H) -58BUS 4 (L) -59

(O) PB (BEZEL BUTTON 5) -60 (24)---------------- 115J1-49WX BUS 2 TERM (L) -61PB -62 (24)---------------- 115J1-56

(O) MFD BEZEL/SET KNOB #5 COMMON-63 (24)---------------- 115J1-23WX BUS 1 TERM (L) -64DU OVERTEMP (GND/OPEN) -65DU WRAPAROUND (H) -66(ARINC 429)DU WRAPAROUND (L) -79(ARINC 429)RESERVED -67RESERVED -68WX BUS 3 (H) 131J1-69




PILOT’S MFDDISPLAY UNIT NO. 2 (cont)

DU-870


WX BUS 3 (L) 131J1-70RESERVED -71SPARE -72SPARE -73WX BUS 2 (H) -74WX BUS 2 (L) -75SPARE -76

(B) WX BUS LEFT (H) -77 (24)-T-S-----------S-- FIG.(B) WX BUS LEFT (L) -78 (24)-T-S-----------S-- 6-5


(I) SIGNAL GROUND -80 (24)------------------ SIGNAL GNDRESERVED -81RESERVED -82WX BUS 3 TERM (L) -83

(O) PB (BEZEL BUTTON 6) -84SPARE -85SPARE -86

(I) PORT SEL 3 -87 (24)------------------ FIG. 6-9PORT SEL 2 -88PORT SEL 1 -89

(I) I.D. #3 -90 (24)------------------ FIG. 6-9I.D. #2 -91I.D. #1 -92RESERVED -93CHASSIS GND -94RESERVED -95RESERVED -96RESERVED -97RESERVED -98SOFTWARE ENABLE* -99SOFTWARE ENABLE* -100

(P) 28 V DC -101 (22)----------------(P) 28 V DC -102 (22)---------------- FIG. 6-1(P) 28 V DC -103 (22)----------------(P) 28 V DC RTN -104 (22)---------------- A/C 28 V DC(P) 28 V DC RTN -105 (22)---------------- PWR RETURN(P) 28 V DC RTN 131J1-106 (22)----------------

*FLIGHT TEST ONLY




EICASDISPLAY UNIT NO. 3

DU-870


(I) (H) 132J1-1 (22)-T-S-----------S-- AIRCRAFTBRIGHTNESS POT (W) -14 (22)-T-S-----------S-- DIMMING

(I) (L) -13 (22)-T-S-----------S-- CONTROLNC ────────┘ └─── SHIELD GND



BUS 3 (H) -19(L) -20

(O) SET KNOB (CAS) (H) -21 (24)-T-S-----------S-- 115J1-24,C115J1-24(O) SET KNOB (CAS) (L) -25 (24)-T-S-----------S-- 115J1-25,C115J1-25(O) BEZEL COMMON -63 (24)-T-S-----------S-- 115J1-26,C115J1-26


(I) DU PWR DN* -22 (24)------------------ FIG. 6-9(P) 5 V LIGHTING (H) -23 (22)------------------ FIG. 6-7(P) 5 V LIGHTING COMMON -24 (22)------------------ LIGHTING COMMON

SET KNOB (CAS) (L) -25REMOTE LT SENSOR (H) -26REMOTE LT SENSOR (L) -27

DLS OUT (H) -28(L) -41

ALS (H) -29(L) -42

RESERVED -30(B) HDLC OUT + -31 (24)-T-S-----------S-- FIG.(B) HDLC OUT - 132J1-32 (24)-T-S-----------S-- 6-13





EICASDISPLAY UNIT NO. 3 (cont)

DU-870



(B) BUS 2 (H) -35 (24)-T-S-----------S-- FIG.(B) (L) -36 (24)-T-S-----------S-- 6-13


DU VALID (GND/OPEN) -37(B) BUS 1 (H) -38 (24)-T-S-----------S-- FIG.(B) (L) -39 (24)-T-S-----------S-- 6-13



(L) -54RESERVED -43RESERVED -44BUS 4 TRM (L) -45PB 1 -46PB 2 -47RESERVED -48BUS 2 TERM (L) -49PB 3 -50PB 4 -51BUS 1 TERM (L) -52RESERVED -55RESERVED -56RESERVED -57BUS 4 (H) -58BUS 4 (L) -59PB 5 -60WX BUS 2 TERM (L) -61PB (MENU) -62BEZEL COMMON -63WX BUS 1 TERM (L) -64DU OVERTEMP (GND/OPEN) -65DU WRAPAROUND (H) -66(ARINC 429)DU WRAPAROUND (L) 132J1-79




EICASDISPLAY UNIT NO. 3 (cont)

DU-870


RESERVED 132J1-67RESERVED -68WX BUS 3 (H) -69WX BUS 3 (L) -70RESERVED -71SPARE -72SPARE -73WX BUS 2 (H) -74WX BUS 2 (L) -75SPARE -76WX BUS 1 (H) -77WX BUS 1 (L) -78

(I) SIGNAL GROUND -80 (24)----------------- SIGNAL GROUNDRESERVED -81RESERVED -82WX BUS 3 TERM (L) -83PB 6 -84SPARE -85SPARE -86

(I) PORT SEL 3 -87 (24)----------------- FIG. 6-9PORT SEL 2 -88PORT SEL 1 -89I.D. #3 -90

(I) I.D. #2 -91 (24)----------------- FIG. 6-9I.D. #1 -92RESERVED -93CHASSIS GND -94RESERVED -95RESERVED -96RESERVED -97RESERVED -98SOFTWARE ENABLE* -99SOFTWARE ENABLE* -100

(P) 28 V DC -101 (22)-----------------(P) 28 V DC -102 (22)----------------- FIG. 6-1(P) 28 V DC -103 (22)-----------------

(P) 28 V DC RTN -104 (22)----------------- A/C 28 V DC(P) 28 V DC RTN -105 (22)----------------- PWR RETURN(P) 28 V DC RTN 132J1-106 (22)-----------------

*FLIGHT TEST ONLY




DATA AQUISITION UNIT NO. 1DA-800

Function Connector Pin Connects To

PACK VALVE 1 POS DIN 136J1A-1 (24)---------------- PACK VLV POS SW 1OUTBD BRAKE INOP DIN -2 (24)---------------- BRAKE CONTROL UNITINBD BRAKE INOP DIN -3 (24)---------------- BRAKE CONTROL UNITFUEL XFEED SW DIN -4 (24)---------------- FUEL CNTRL PANELBATT CNTOR 1 DIN -5 (24)---------------- BATTERY CONTACTOR 1ESS BUS CNTOR 1 DIN -6 (24)---------------- ESS BUS CONTACTOR 1GEN LINE CNTOR 1 DIN -7 (24)---------------- GEN LINE CONTACTOR 1GEN LINE CNTOR 3 DIN -8 (24)---------------- GEN LINE CONTACTOR 3APU LINE CNTOR DIN -9 (24)---------------- APU LINE CONTACTORAPU STARTER CNTOR DIN -10 (24)--------------- APU STARTER CNTORENG 1 A/ICE SW DIN -11 (24)--------------- A/ICE CNTRL PANELENG1 FIRE DET FAIL DIN -12 (24)--------------- ENG 1 FIRE CNTRL MODAPU FIRE DET FAIL DIN -13 (24)--------------- APU FIRE CNTRL MODFLAP FAIL 1 DIN -14 (24)--------------- FLAP ELEC CNTRL UNITGND SPOILER CMD DIN -15 (24)--------------- SPOILER CNTRL RELAYSGND SPLR ENG INPT DIN -16 (24)--------------- SPOILER CNTRL RELAYSFUEL LO LEVEL 1 DIN -17 (24)--------------- SIGNAL COND UNIT2C POWER CNTOR ON DIN -18 (24)--------------- FUEL CONTROL PANEL1C POWER CNTOR ON DIN -19 (24)--------------- FUEL CONTROL PANELPITOT 1 INOP DIN -20 (24)--------------- PITOT 1 CURRENT SNSRPITOT 3 INOP DIN -21 (24)--------------- PITOT 3 CURRENT SNSRSPLR WHEELS A/G DIN -22 (24)--------------- SPOILER CNTRL RELAYSTAT 1 INOP DIN -23 (24)--------------- TAT 1 CURRENT SNSRW/S 1 OVERHEAT DIN -24 (24)--------------- W/S TEMP CONTROLLERW/S 1 INOP DIN -25 (24)--------------- W/S TEMP CONTROLLERL UPLOCK SNSR A DIN -26 (24)--------------- LG ELECTRONICS UNITL UPLOCK SNSR B DIN -27 (24)--------------- LG ELECTRONICS UNITL DOWNLOCK SNSR A DIN -28 (24)--------------- LG ELECTRONICS UNITL DOWNLOCK SNSR B DIN -29 (24)--------------- LG ELECTRONICS UNITAUTOPRESN CONTROL DIN -30 (24)--------------- DIGITAL PRESS CNTRLRSPS 1 OFF DIN -31 (24)--------------- SWS CONTROL PANELSTEERING FAIL DIN -32 (24)--------------- STRG ELEC CNTRL UNITDUCT OVERTEMP 1 DIN -33 (24)--------------- DUCT OVTP SW 1PACK OVERTEMP 1 DIN -34 (24)--------------- PACK OVTP SW 1PACK OVERPRESS 1 DIN -35 (24)--------------- PACK 1 OVR PRESS SWL FLIGHT IDLE LCK DIN -36 (24)--------------- FLT IDLE LOCK SOLENAURAL WARN FAIL DIN -37 (24)--------------- AURAL WARN COMPUTERGEAR LEVER DOWN DIN -38 (24)--------------- LG CONTROL LEVERSPBK LEVER POS DIN -39 (24)--------------- SPBK LEVER SWGEAR DOWN LOCKED DIN -40 (24)--------------- LG ELECTRONIC UNITVHF COM 1 PTT DIN -41 (24)--------------- FIG. 6-27EMERG EXIT 1 SW DIN 136J1A-42 (24)--------------- EMERG EXIT DOOR 1 SW




DATA AQUISITION UNIT NO. 1 (cont)DA-800


SPOILER LEFT OB DIN 136J1A-43 (24)-------------- SPLR PROX SW LEFT OBENG 1 A/I LO PRESS DIN -44 (24)-------------- ENG 1 LOW PRESS SWWING 1 A/I LO PRESS DIN -45 (24)-------------- WING 1 LOW PRESS SWWING 1 A/I OVRPRESS DIN -46 (24)-------------- WING 1 OVERPRESS SWREV/WOWS/DISAGREE DIN -47 (24)-------------- COCKPIT RELAYSPARE GND/OPN DIN -48SPARE GND/OPN DIN -49PACK VALVE 1 CMD DIN -50 (24)--------------- PACK VALVE RELAY 1DC BUS 1 OFF DIN -51 (24)--------------- RELAY BOX DC BUS 1ESS DC BUS 1 OFF DIN -52 (24)--------------- RELAY BOX ESS BUS 1SHED DC BUS 1 OFF DIN -53 (24)--------------- RELAY BOX SHED BUS 1ENG 1 FIRE DIN -54 (24)--------------- ENG 1 FIRE CNTRL MODEXTG BTL A PWR 1 DIN -55 (24)--------------- FIRE HANDLEEXTG BTL A PWR 2 DIN -56 (24)--------------- FIRE HANDLEEXTG BTL APU PWR DIN -57 (24)--------------- FIRE SWITCH APU1A POWER CNTOR ON DIN -58 (24)--------------- FUEL SYS CONTACTORHS VALVE 1 CMD DIN -59 (24)--------------- HS VALVE 1 CMD SWLDG GEAR MONITOR DIN -60 (24)--------------- LG ELECTRONIC UNITHYD 1 PUMP SELECT DIN -61 (24)--------------- HYD PUMP 1 SWHYD 2 PUMP SELECT DIN -62 (24)--------------- HYD PUMP 2 SWSPARE 28V/OPN DIN -63SPARE 28V/OPN DIN -64AUTOPRESN TEST DIN -65 (24)--------------- DIGITAL PRESS CNTRLRHF COM PTT DIN -66 (24)--------------- HF COM XCVR PTTIDENT #1 CH. A -67 -------------------} NCIDENT #2 CH. A -68 -------------------} NCIDENT #3 CH. A -69 (24)---------------} GNDBRK 1 PRESSURE { (H) -70 (24)-T-S-------S--- BRAKE CONTROL

{ (L) -71 (24)-T-S-------S--- UNITSHIELD GND ───────────┘ └─── SHIELD GND

-72-73-74

115 VAC BUS OFF { (H) -75 (24)-T-S-------S--- 115 VAC{ (L) 136J1A-76 (24)-T-S-------S--- BUS

SHIELD GND ───────────┘ └─── SHIELD GND






RESERVED 136J1A-77-78

RESERVED -79BRAKE 1 TEMP { (H) -80 (24)-T-S----------S---- BRAKE TEMP

{ (L) -81 (24)-T-S----------S---- XMITTER NO. 1SHIELD GND ───────────┘ └─── SHIELD GND

-82BRAKE 2 TEMP { (H) -83 (24)-T-S----------S---- BRAKE TEMP






-91OXYGEN PRESS { (H) -92 (24)-T-S----------S---- OXYGEN PRESSURE

{ (L) -93 (24)-T-S----------S---- TRANSDUCERSHIELD GND ───────────┘ └─── SHIELD GND

RESERVED -94-95

RESERVED -96-97-98

SIGNAL GROUND #1 CH. A -99 (24)--------------- SIGNAL GROUNDSIGNAL GROUND #2 CH. A -100 (24)-------------- SIGNAL GROUNDCHASSIS GROUND CH. A -101 (24)-------------- CHASSIS GROUND

-102+28 VDC #1 CH. A -103 (22)--------------}+28 VDC #2 CH. A -104 (22)--------------} FIG.+28 VDC RTN #1 CH. A -105 (22)--------------} 6-1A+28 VDC RTN #2 CH. A 136J1A-106 (22)--------------}






RESERVED 136J1B-1RESERVED -2

{ (H) -3 (24)-T-S-----------S---- ROLLROLL TRIM POS { (W) -4 (24)-T-S-----------S---- TRIM

{ (L) -5 (24)-T-S-----------S---- ACTUATOR POTSHIELD GND ──────────┘ └──── SHIELD GND

{ SIG (H) -6 (24)-T-S-----------S---- ENGINE NO. 1{ SIG (L) -7 (24)-T-S-----------S---- OIL{ SHIELD GND ──────────┘ └──── SHIELD GND

ENG 1 OIL TEMP A {{ EXC (H) -8 (24)-T-S-----------S---- TEMPERATURE{ EXC (L) -9 (24)-T-S-----------S---- A SENSOR

SHIELD GND ──────────┘ └──── SHIELD GND

{ (H) -10 (24)-T-S----------S---- CONTROL COLUMNCTL COL POS 1 { (W) -11 (24)-T-S----------S---- POSITION SENSOR

{ (L) -12 (24)-T-S----------S---- NO. 1SHIELD GND ───────────┘ └──── SHIELD GND

{ (H) -13 (24)-T-S----------S---- CONTROL WHEELCTL WHEEL POS 1 { (W) -14 (24)-T-S----------S---- POSITION SENSOR


{ (H) -16 (24)-T-S----------S---- CONTROL WHEELCTL WHEEL POS 2 { (W) -17 (24)-T-S----------S---- POSITION SENSOR


{ SIG (H) -19 (24)-T-S----------S---- ENGINE NO. 1{ SIG (L) -20 (24)-T-S----------S---- FUEL{ SHIELD GND ───────────┘ └──── SHIELD GND

ENG 1 FUEL TEMP {{ EXC (H) -21 (24)-T-S----------S---- TEMPERATURE{ EXC (L) -22 (24)-T-S----------S---- SENSOR

SHIELD GND ───────────┘ └──── SHIELD GND

-23CKPT TEMP SENSOR { (H) -24 (24)-T-S----------S---- COCKPIT

{ (L) 136J1B-25 (24)-T-S----------S---- TEMP SENSORSHIELD GND ───────────┘ └──── SHIELD GND






{ SIG (H) 136J1B-26 (24)-T-S----------S---- COOLER NO. 1{ SIG (L) -27 (24)-T-S----------S---- ANTI-ICE{ SHIELD GND ───────────┘ └──── SHIELD GND

COOLER 1 INLT TMP {{ EXC (H) -28 (24)-T-S----------S---- INLET TEMP{ EXC (L) -29 (24)-T-S----------S---- SENSOR


{ SIG (H) -30 (24)-T-S----------S---- COOLER NO. 1{ SIG (L) -31 (24)-T-S----------S---- ANTI-ICE{ SHIELD GND ───────────┘ └──── SHIELD GND

COOLER 1 OTLT TMP {{ EXC (H) -32 (24)-T-S----------S---- OUTLET TEMP{ EXC (L) -33 (24)-T-S----------S---- SENSOR


-34-35-36-37

APU RPM OUTPUT { (H) -38 (24)-T-S----------S---- APU ELEC{ (L) -39 (24)-T-S----------S---- SIGNAL UNIT


ARINC 429 OUT #1 A (H) -40 (24)-T-S----------S---- FIG.ARINC 429 OUT #1 A (L) -41 (24)-T-S----------S---- 6-14(To RMU 1 & 2) SHIELD GND ───────────┘ └──── SHIELD GND

ARINC 429 IN #1 (H) -42 (24)-T-S----------S---- FIG.ARINC 429 IN #1 (L) -43 (24)-T-S----------S---- 6-12(From IC 1) SHIELD GND ───────────┘ └──── SHIELD GND

ARINC 429 IN #2 (H) -44 (24)-T-S----------S---- SHIP’S CLOCK (H)ARINC 429 IN #2 (L) 136J1B-45 (24)-T-S----------S---- SHIP’S CLOCK (L)







ARINC 429 IN #3 (H) 136J1B-46 (24)-T-S----------S---- FADEC NO. 1ARINC 429 IN #3 (L) -47 (24)-T-S----------S---- CH. A


ARINC 429 IN #4 (H) -48 (24)-T-S----------S---- FUEL COMPUTERARINC 429 IN #4 (L) -49 (24)-T-S----------S---- CH. A


ARINC 429 OUT #2 A (H) -50 (24)-T-S----------S---- FIG.ARINC 429 OUT #2 A (L) -51 (24)-T-S----------S---- 6-12(To IC 1 & 2) SHIELD GND ───────────┘ └──── SHIELD GND

{ SIG (H) -52 (24)-T-S----------S---- ENGINE NO. 1{ SIG (L) -53 (24)-T-S----------S---- OIL{ SHIELD GND ───────────┘ └──── SHIELD GND

ENG 1 OIL PRESS {{ 10V EXC (H) -54 (24)-T-S----------S---- PRESSURE{ 10V EXC (L) -55 (24)-T-S----------S---- SENSOR


RESERVED FOR TEST -56RESERVED FOR TEST -57RESERVED FOR TEST -58RESERVED FOR TEST -59RESERVED FOR TEST -60RESERVED FOR TEST -61RESERVED FOR TEST -62RESERVED FOR TEST -63RESERVED FOR TEST -64RESERVED FOR TEST -65RESERVED FOR TEST -66RESERVED FOR TEST -67A717 FDR OUT { (H) -68 (24)-T-S----------S---- FDR A717 IN (H)

{ (L) -69 (24)-T-S----------S---- FDR A717 IN (L)SHIELD GND ───────────┘ └──── SHIELD GND

RESERVED FOR TEST -70{ (H) -71 (24)-T-S----------S---- ENGINE NO. 1

ENG 1 OIL LEVEL { (W) -72 (24)-T-S----------S---- OIL LEVEL{ (L) -73 (24)-T-S----------S---- SENSOR


-74BATT 1 TEMP SNS 1 { (H) -75 (24)-T-S----------S---- BATT NO. 1

{ (L) 136J1B-76 (24)-T-S----------S---- TEMP SENSORSHIELD GND ───────────┘ └──── SHIELD GND






{ IMPELLOR 136J1B-77 (24)-T-S----------S---- ENGINE NO. 1ENG 1 FUEL FLOW { COMMON -78 (24)-T-S----------S---- FUEL FLOW

{ DRUM -79 (24)-T-S----------S---- METERSHIELD GND ───────────┘ └──── SHIELD GND

FLAP POSITION 1 { (H) -80 (24)-T-S----------S---- FLAP ELEC.{ (L) -81 (24)-T-S----------S---- CNTRL UNIT


USED ON DAU 2 -82USED ON DAU 2 -83

USED ON DAU 2 -84USED ON DAU 2 -85

NORMAL ACCEL FDR { (H) -86 (24)-T-S----------S---- NORMAL{ (L) -87 (24)-T-S----------S---- ACCEL SENSOR


APU GEN VOLTAGE { (H) -88 (24)------------------- APU GENERATOR{ (L) -89 (24)------------------- LINE

BATT 1 VOLTAGE { (H) -90 (24)-------------------- HOT BATT{ (L) -91 (24)-------------------- BUS NO. 1

GEN 1 CURRENT { (H) -92 (24)-T-S----------S---- GENERATOR NO. 1{ (L) -93 (24)-T-S----------S---- SHUNT


RESERVED -94-95

RESERVED -96-97

RS-422 XMT CH. A (H) -98 (24)-T-S----------S---- 137J1B-100 (H)RS-422 XMT CH. A (L) -99 (24)-T-S----------S---- 137J1B-101 (L)


RS-422 RCV CH. A (H) -100 (24)-T-S---------S---- 137J1B-98 (H)RS-422 RCV CH. A (L) 136J1B-101 (24)-T-S---------S---- 137J1B-99 (L)







GEN 3 CURRENT { (H) 136J1B-102 (24)-T-S---------S---- GENERATOR NO. 3{ (L) -103 (24)-T-S---------S---- SHUNT


RS-232 XMT CH. A -104 (24)------------------}RS-232 RCV CH. A -105 (24)------------------}FIG. 6-34RS-232 COM CH. A 136J1B-106 (24)------------------}






ELEC BAY OVTEMP DIN 136J2A-1 (24)---------------- ELEC BAY OVTP SWEMRG LTS NOT ARMD DIN -2 (24)---------------- EMERG LTS PANEL SWMAIN DOOR SW DIN -3 (24)---------------- MAIN DOOR SW MONITORELEC BAY DOOR SW DIN -4 (24)---------------- ELEC BAY DOOR SWACCESS DOOR 1 SW DIN -5 (24)---------------- CKPT ACCESS DOOR SWGPU CNTOR DIN -6 (24)---------------- GPU AUX RELAY CNTCTESS BUS CNTOR 2 DIN -7 (24)---------------- ESS BUS CONTACTOR 1GEN LINE CNTOR 2 DIN -8 (24)---------------- GEN LINE CNTOR 2GEN LINE CNTOR 4 DIN -9 (24)---------------- GEN LINE CNTOR 4BKUP RELAY ENERG DIN -10 (24)--------------- BACKUP RELAY CONTACTBATT CNTOR 2 DIN -11 (24)--------------- BAT CONTACTOR 2ENG2 FIRE DET FAIL DIN -12 (24)--------------- ENG 1 FIRE CNTRL MODSPBK LEVER CMD DIN -13 (24)--------------- SPBRK LEVER SWITCHFUEL LO LEVEL 2 DIN -14 (24)--------------- SIGNAL COND UNITACCESS DOOR 2 SW DIN -15 (24)--------------- TAIL ACCESS DOOR SWENGLISH/METRIC DIN -16 (24)--------------- DAU STRAP (OPN=ENG)PITOT 2 INOP DIN -17 (24)--------------- PITOT 2 CURRENT SNSRSPBK DRIVE RELAYS DIN -18 (24)--------------- SPOILER CNTRL RELAYSW/S 2 OVERHEAT DIN -19 (24)--------------- W/S TEMP CONTROLLERW/S 2 INOP DIN -20 (24)--------------- W/S TEMP CONTROLLERICE DETECTOR FAIL DIN -21 (24)--------------- ICE DETECT SENSORICE CONDITION DIN -22 (24)--------------- ICE DETECT SENSORN UPLOCK SNSR A DIN -23 (24)--------------- LG ELECTRONIC UNITR UPLOCK SNSR A DIN -24 (24)--------------- LG ELECTRONIC UNITN UPLOCK SNSR B DIN -25 (24)--------------- LG ELECTRONIC UNITR UPLOCK SNSR B DIN -26 (24)--------------- LG ELECTRONIC UNITN DOWNLOCK SNSR A DIN -27 (24)--------------- LG ELECTRONIC UNITR DOWNLOCK SNSR A DIN -28 (24)--------------- LG ELECTRONIC UNITN DOWNLOCK SNSR B DIN -29 (24)--------------- LG ELECTRONIC UNITR DOWNLOCK SNSR B DIN -30 (24)--------------- LG ELECTRONIC UNITR FLIGHT IDLE LCK DIN -31 (24)--------------- FLT IDLE LOCK SOLENSPS 2 OFF DIN -32 (24)--------------- SPS 2 CNTRL PANELPACK VALVE 2 POS DIN -33 (24)--------------- PACK VLV POS SW 2DUCT OVERTEMP 2 DIN -34 (24)--------------- DUCT OVERTEMP SW 2PACK OVERTEMP 2 DIN -35 (24)--------------- PACK OVERTEMP SW 2PACK OVERPRESS 2 DIN -36 (24)--------------- PACK OVPRESS SW 2VHF COM 2 PTT DIN -37 (24)--------------- FIG. 6-28OUTB BRK DEGRADED DIN -38 (24)--------------- BRAKE CONTROL UNITINBD BRK DEGRADED DIN -39 (24)--------------- BRAKE CONTROL UNITEMERG EXIT 2 SW DIN -40 (24)--------------- EMERG EXIT DOOR 2 SWSPOILER RIGHT OB DIN -41 (24)--------------- SPLR PROX SW RT OBAPU FUEL SOV COMM DIN -42 (24)--------------- APU RELAY/SWITCHREV/WOW 2 DISAGREE DIN -43 (24)--------------- COCKPIT RELAYA/ICE SYSTEM TEST DIN 136J2A-44 (24)--------------- A/I TEST SW






RESERVED - END ITEM TEST 136J2A-45SPARE GND/OPN DIN -46SPARE GND/OPN DIN -47SPARE GND/OPN DIN -48SPARE GND/OPN DIN -49PACK VALVE 2 CMD DIN -50 (24)--------------- PACK VALVE RELAY 2DC BUS 2 OFF DIN -51 (24)--------------- DC BUS 2 RELAY BOXESS DC BUS 2 OFF DIN -52 (24)--------------- ESS BUS 2 RELAY BOXSHED DC BUS 2 OFF DIN -53 (24)--------------- SHED BUS 2 RELAY BOXEXTG BTL B PWR 1 DIN -54 (24)--------------- FIRE HANDLEEXTG BTL B PWR 2 DIN -55 (24)--------------- FIRE HANDLEOUTBD CARD ENERG DIN -56 (24)--------------- BRAKE CONTROL UNITINBD CARD ENERG DIN -57 (24)--------------- BRAKE CONTROL UNITCENTRAL BUS OFF DIN -58 (24)--------------- DC BUS RELAY BOX1B POWER CNTOR ON DIN -59 (24)--------------- FUEL CONTROL PANELAGCU ALC CONTROL DIN -60 (24)--------------- APU GCU (Pin H)AGCU ASC POWER DIN -61 (24)--------------- APU GCU (Pin Z)HS VALVE 2 CMD DIN -62 (24)--------------- HS VALVE 2 CMD SWSPARE 28V/OPN DIN -63SPARE 28V/OPN DIN -64SPARE 28V/OPN DIN -65SPARE 28V/OPN DIN -66IDENT #1 CH. B -67 -------------------} NCIDENT #2 CH. B -68 -------------------} NCIDENT #3 CH. B -69 -------------------} GND

{ (H) -70 (24)-T-S----------S---- RUDDER PEDALRUDDER PEDAL POS { (W) -71 (24)-T-S----------S---- POSITION

{ (L) -72 (24)-T-S----------S---- SENSORSHIELD GND ───────────┘ └──── SHIELD GND

{ SIG (H) -73 (24)-T-S----------S---- FUEL{ SIG (L) -74 (24)-T-S----------S---- TANK{ SHIELD GND ───────────┘ └──── SHIELD GND

FUEL TANK TEMP {{ EXC (H) -75 (24)-T-S----------S---- TEMPERATURE{ EXC (L) -76 (24)-T-S----------S---- PROBE


RESERVED -77-78

RESERVED -79AIR/GROUND 1 DIN -80 (24)--------------- LANDING GEAR SYSUSED ON DAU 2 -81USED ON DAU 2 136J2A-82






136J2A-83-84-85-86-87-88-89-90-91-92-93

RESERVED -94-95

RESERVED -96-97-98

SIGNAL GROUND #1 CH. B -99 (24)-------------- SIGNAL GROUNDSIGNAL GROUND #2 CH. B -100 (24)------------- SIGNAL GROUNDCHASSIS GROUND CH. B -101 (24)------------- CHASSIS GROUND

-102+28 VDC #1 CH. B -103 (22)-------------}+28 VDC #2 CH. B -104 (22)-------------} FIG.+28 VDC RTN #1 CH. B -105 (22)-------------} 6-1A+28 VDC RTN #2 CH. B 136J2A-106 (22)-------------}







-3-4-5-6-7-8

{ SIG (H) -9 (24)-T-S-----------S---- ENGINE NO. 1{ SIG (L) -10 (24)T-S-----------S---- OIL{ SHIELD GND ───────────┘ └──── SHIELD GND

ENG 1 OIL TEMP B {{ EXC (H) -11 (24)T-S----------S---- TEMPERATURE{ EXC (L) -12 (24)T-S----------S---- B SENSOR


-13-14-15-16-17-18-19-20-21-22-23-24-25-26-27-28-29

BATT 2 TEMP SNS 1 { (H) -30 (24)-T-S----------S---- BATT NO. 2{ (L) -31 (24)-T-S----------S---- TEMP SENSOR 1


-32-33

GEN 3 VOLTAGE { (H) -34 (24)------------------- GENERATOR NO. 3{ (L) 136J2B-35 (24)------------------- LINE






GEN 1 VOLTAGE { (H) 136J2B-36 (24)------------------- GENERATOR NO. 1{ (L) -37 (24)------------------- LINE

USED ON DAU 2 -38USED ON DAU 2 -39ARINC 429 OUT #1 B (H) -40 (24)-T-S----------S---- MAINTENANCEARINC 429 OUT #1 B (L) -41 (24)-T-S----------S---- COMPUTER


ARINC 429 IN #5 (H) -42 (24)-T-S----------S---- STALL WARN CH. AARINC 429 IN #5 (L) -43 (24)-T-S----------S---- STALL WARN CH. A


ARINC 429 IN #6 (H) -44 (24)-T-S----------S---- FADEC 1ARINC 429 IN #6 (L) -45 (24)-T-S----------S---- CH. B


-46-47-48-49

ARINC 429 OUT #2 B (H) -50 (24)-T-S----------S---- FIG.ARINC 429 OUT #2 B (L) -51 (24)-T-S----------S---- 6-12(To IC 1 & 2) SHIELD GND ───────────┘ └──── SHIELD GND

-52-53-54-55

RESERVED FOR TEST -56RESERVED FOR TEST -57RESERVED FOR TEST -58RESERVED FOR TEST -59RESERVED FOR TEST -60RESERVED FOR TEST -61RESERVED FOR TEST -62RESERVED FOR TEST -63RESERVED FOR TEST -64RESERVED FOR TEST -65RESERVED FOR TEST -66RESERVED FOR TEST -67

-68-69

RESERVED FOR TEST 136J2B-70






136J2B-71-72-73-74-75-76-77-78-79-80-81-82-83-84-85-86-87-88-89-90-91-92-93

RESERVED -94-95

RESERVED -96-97

RS-422 XMT CH. B (H) -98RS-422 XMT CH. B (L) -99

RS-422 RCV CH. B (H) -100 -----NCRS-422 RCV CH. B (L) -101 -----NC

-102-103

RS-232 XMT CH. B -104 (24)------------------}RS-232 RCV CH. B -105 (24)------------------} FIG. 6-34RS-232 COM CH. B 136J2B-106 (24)------------------}




DATA AQUISITION UNIT NO. 2DA-800


AIL SYS1 PRESS SW DIN 137J1A-1 (24)--------------- AIL HYD PRESS SW 1ENG 1 BLEED POS DIN -2 (24)--------------- EBV POS MICRO SW 1XBLEED VLV POS DIN -3 (24)--------------- CBV POS MICRO SWR/AIR ACTR 1 POS DIN -4 (24)--------------- ACT POS MICRO SW 1SPARE GND/OPN DIN -5BLEED DUCT LEAK 1 DIN -6 (24)--------------- BLD DUCT LEAK SWS 1L AIR STARTER VLV DIN -7 (24)--------------- ATS VALVE LACCUM LOW PRESS DIN -8 (24)--------------- ACCUM PRESSURE SWBAGGAGE DOOR SW DIN -9 (24)--------------- BAGGAGE DOOR SW MONITSERVICE DOOR SW DIN -10 (24)-------------- SERVICE DOOR SW MONITFUELING DOOR SW DIN -11 (24)-------------- FUELING DOOR SWEXTG BTL A CRTG 1 DIN -12 (24)-------------- EXTINGUISHER BTL AEXTG BTL A CRTG 2 DIN -13 (24)-------------- EXTINGUISHER BTL AEXTG BTL A PRESS DIN -14 (24)-------------- EXTINGUISHER BTL AFUEL PRESS SW 1 DIN -15 (24)-------------- FUEL 1 PRESS SWHYD 1 THERMAL SW DIN -16 (24)-------------- HYD 1 THERMAL SWHYD 1 ENG PUMP SW DIN -17 (24)-------------- ENG PUMP PRESS SW 1HYD 1 ELEC PUMP SW DIN -18 (24)-------------- ELEC PUMP PRESS SW 1E1 A/ICE POS VLV DIN -19 (24)-------------- ENG 1 A/ICE VALVEWING1 A/I VLV POS DIN -20 (24)-------------- WING 1 A/ICE VALVESTAB A/I VLV POS DIN -21 (24)-------------- STAB A/ICE VALVEWING1 A/ICE LEAK DIN -22 (24)-------------- WING 1 DUCT LEAK SWSSTAB A/ICE LEAK DIN -23 (24)-------------- TAIL DUCT LEAK SWSENG1 OIL LO PRESS DIN -24 (24)-------------- ENG 1 OIL LO PRESS SWENG1 OIL LO LEVEL DIN -25 (24)-------------- ENG 1 OIL LO LEVEL SWENG1 FUEL FILTER DIN -26 (24)-------------- ENG 1 FLTR BYPASS SWRUD 1 PRESS SW DIN -27 (24)-------------- RUD PRESSURE SW 1CARGO SMOKE DET DIN -28 (24)-------------- CARGO SMOKE DETECTORHS VALVE 1 POS DIN -29 (24)-------------- HS VALVE 1 POS SWSPOILER LEFT IB DIN -30 (24)-------------- SPLR PROX SW LEFT IBTR 1 INHIBIT DIN -31 (24)-------------- ICU INHIBIT SWITCHTR 1 UP DEPLOY DIN -32 (24)-------------- TR 1 UP DEPLOY SWTR1 3RY UNLOCK DIN -33 (24)-------------- UP/LOW 3RY UNLCK SWSTR1 UP NOT STOW DIN -34 (24)-------------- INB/OUT 1 STOW SWSTR1 LOW NOT STOW DIN -35 (24)-------------- INB/OUT STOW SWSTR 1 PRESS ISOL DIN -36 (24)-------------- ICU ISOLATION SWMAIN PTRIM INOP DIN -37 (24)-------------- STAB CNTRL UNIT MAINBACKUP PTRIM INOP DIN -38 (24)-------------- STAB CNTRL UNIT BKUPTR 1 LOW DEPLOY DIN -39 (24)-------------- TR 1 LOW DEPLOY SWTR 1 TRANSIT DIN -40 (24)-------------- UP/LOW TRANSIT SWSTAB A/I LO PRESS DIN -41 (24)-------------- STAB LOW PRESS SWENG 1 A/I OVRPRESS DIN 137J1A-42 (24)-------------- ENG 1 OVERPRESS SW






STAB A/I OVRPRESS DIN 137J1A-43 (24)-------------- STAB OVERPRESS SWBEARING 1 FAIL DIN -44 (24)-------------- GEN 1BEARING 2 FAIL DIN -45 (24)-------------- GEN 2SPARE GND/OPN DIN -46SPARE GND/OPN DIN -47SPARE GND/OPN DIN -48TAT 2 INOP DIN -49 (24)-------------- TAT 2 CURRENT SENSORENG 1 BLEED CMD DIN -50 (24)-------------- EBV RELAY 1FUEL XFD VLV OPEN DIN -51 (24)-------------- CROSSFEED VLV POS (O)FUEL XFD VLV CLSD DIN -52 (24)-------------- CROSSFEED VLV POS (C)FUEL SOV 1 OPEN DIN -53 (24)-------------- ENG1 FUEL SOV POS (O)FUEL SOV 1 CLOSED DIN -54 (24)-------------- ENG1 FUEL SOV POS (C)HYD SOV 1 OPEN DIN -55 (24)-------------- ENG1 HYD SOV POS (O)HYD SOV 1 CLOSED DIN -56 (24)-------------- ENG1 HYD SOV POS (C)TOILET SMOKE DET DIN -57 (24)-------------- TOILET SMOKE DETECTAPU BLEED CMD DIN -58 (24)-------------- APU BLD DUMP RELAYXBLEED VLV CMD DIN -59 (24)-------------- XBLEED BYPASS RELAYAPU FIRE DIN -60 (24)-------------- APU FIRE CNTRL MODAPU MALFUNCTION DIN -61 (24)-------------- APUSPARE 28V/OPN DIN -62SPARE 28V/OPN DIN -63SPARE 28V/OPN DIN -64SPARE 28V/GND DIN -65DFDR STATUS DIN -66 (24)--------------- FLT DATA RECORDERIDENT #1 CH. A -67 -------------------} NCIDENT #2 CH. A -68 (24)---------------} GNDIDENT #3 CH. A -69 -------------------} NCBRK 3 PRESSURE { (H) -70 (24)-T-S----------S---- BRAKE CONTROL

{ (L) -71 (24)-T-S----------S---- UNITSHIELD GND ───────────┘ └──── SHIELD GND

-72-73-74

USED ON DAU 1 -75USED ON DAU 1 137J1A-76






RESERVED 137J1A-77-78

RESERVED -79USED ON DAU 1 -80USED ON DAU 1 -81

-82LATERAL ACCEL FDR { (H) -83 (24)-T-S----------S---- LATERAL

{ (L) -84 (24)-T-S----------S---- ACCEL SENSORSHIELD GND ───────────┘ └──── SHIELD GND

-85LONG ACCEL FDR { (H) -86 (24)-T-S----------S---- LONGITUDINAL

{ (L) -87 (24)-T-S----------S---- ACCEL SENSORSHIELD GND ───────────┘ └──── SHIELD GND

-88ENG 1 LP VIB { (H) -89 (24)-T-S----------S---- ENGINE NO. 1

{ (L) -90 (24)-T-S----------S---- LP VIB SENSORSHIELD GND ───────────┘ └──── SHIELD GND

-91ENG 1 HP VIB { (H) -92 (24)-T-S----------S---- ENGINE NO. 1

{ (L) -93 (24)-T-S----------S---- HP VIB SENSORSHIELD GND ───────────┘ └──── SHIELD GND

RESERVED -94-95

RESERVED -96-97-98

SIGNAL GROUND #1 CH. A -99 (24)--------------- SIGNAL GROUNDSIGNAL GROUND #2 CH. A -100 (24)-------------- SIGNAL GROUNDCHASSIS GROUND CH. A -101 (24)-------------- CHASSIS GROUND

-102+28 VDC #1 CH. A -103 (22)--------------}+28 VDC #2 CH. A -104 (22)--------------} FIG.+28 VDC RTN #1 CH. A -105 (22)--------------} 6-1B+28 VDC RTN #2 CH. A 137J1A-106 (22)--------------}







{ (H) -3 (24)-T-S-----------S---- YAWYAW TRIM POS { (W) -4 (24)-T-S-----------S---- TRIM

{ (L) -5 (24)-T-S-----------S---- ACTUATOR POTSHIELD GND ───────────┘ └──── SHIELD GND

{ SIG (H) -6 (24)-T-S-----------S---- ENGINE NO. 2{ SIG (L) -7 (24)-T-S-----------S---- OIL{ SHIELD GND ───────────┘ └──── SHIELD GND

ENG 2 OIL TEMP A {{ EXC (H) -8 (24)-T-S-----------S---- TEMPERATURE{ EXC (L) -9 (24)-T-S-----------S---- A SENSOR


{ (H) -10 (24)-T-S----------S---- CONTROL COLUMNCTL COL POS 2 { (W) -11 (24)-T-S----------S---- POSITION SENSOR

{ (L) -12 (24)-T-S----------S---- NO. 2SHIELD GND ────────────┘ └──── SHIELD GND

{ (H) -13 (24)-T-S----------S---- HYDRAULICHYD 1 FLUID QTY { (W) -14 (24)-T-S----------S---- QTY POT


{ (H) -16 (24)-T-S----------S---- HYDRAULICHYD 2 FLUID QTY { (W) -17 (24)-T-S----------S---- QTY POT


{ SIG (H) -19 (24)-T-S----------S---- ENGINE NO. 2{ SIG (L) -20 (24)-T-S----------S---- FUEL{ SHIELD GND ────────────┘ └──── SHIELD GND

ENG 2 FUEL TEMP {{ EXC (H) -21 (24)-T-S----------S---- TEMPERATURE{ EXC (L) -22 (24)-T-S----------S---- SENSOR

SHIELD GND ────────────┘ └──── SHIELD GND

-23PAX TEMP SENSOR { (H) -24 (24)-T-S----------S---- PASSENGER

{ (L) 137J1B-25 (24)-T-S----------S---- TEMP SENSORSHIELD GND ────────────┘ └──── SHIELD GND






{ SIG (H) 137J1B-26 (24)-T-S----------S---- COOLER NO. 2{ SIG (L) -27 (24)-T-S----------S---- ANTI-ICE{ SHIELD GND ────────────┘ └──── SHIELD GND

COOLER 2 INLT TMP {{ EXC (H) -28 (24)-T-S----------S---- INLET TEMP{ EXC (L) -29 (24)-T-S----------S---- SENSOR


{ SIG (H) -30 (24)-T-S----------S---- COOLER NO. 2{ SIG (L) -31 (24)-T-S----------S---- ANTI-ICE{ SHIELD GND ────────────┘ └──── SHIELD GND

COOLER 2 OTLT TMP {{ EXC (H) -32 (24)-T-S----------S---- OUTLET TEMP{ EXC (L) -33 (24)-T-S----------S---- SENSOR

-34-35-36-37

APU EGT OUTPUT { (H) -38 (24)-T-S----------S---- APU ELEC{ (L) -39 (24)-T-S----------S---- SIGNAL UNIT


ARINC 429 OUT #1 A (H) -40 (24)-T-S----------S---- FIG.ARINC 429 OUT #1 A (L) -41 (24)-T-S----------S---- 6-14(To RMU 1 & 2) SHIELD GND ────────────┘ └──── SHIELD GND

ARINC 429 IN #1 (H) -42 (24)-T-S----------S---- FIG.ARINC 429 IN #1 (L) -43 (24)-T-S----------S---- 6-10(From AH 1) SHIELD GND ────────────┘ └──── SHIELD GND

ARINC 429 IN #2 (H) -44 (24)-T-S----------S---- CABIN PRESSUREARINC 429 IN #2 (L) 137J1B-45 (24)-T-S----------S---- SENSOR UNIT







ARINC 429 IN #3 (H) 137J1B-46 (24)-T-S----------S---- FADEC NO. 2ARINC 429 IN #3 (L) -47 (24)-T-S----------S---- CH. A


ARINC 429 IN #4 (H) -48 (24)-T-S----------S---- FUEL COMPUTERARINC 429 IN #4 (L) -49 (24)-T-S----------S---- CH. B


ARINC 429 OUT #2 A (H) -50 (24)-T-S----------S---- FIG.ARINC 429 OUT #2 A (L) -51 (24)-T-S----------S---- 6-12(To IC 1 & 2) SHIELD GND ────────────┘ └──── SHIELD GND

{ SIG (H) -52 (24)-T-S----------S---- ENGINE NO. 2{ SIG (L) -53 (24)-T-S----------S---- OIL{ SHIELD GND ────────────┘ └──── SHIELD GND

ENG 2 OIL PRESS {{ 10V EXC (H) -54 (24)-T-S----------S---- PRESSURE{ 10V EXC (L) -55 (24)-T-S----------S---- SENSOR


RESERVED FOR TEST -56RESERVED FOR TEST -57RESERVED FOR TEST -58RESERVED FOR TEST -59RESERVED FOR TEST -60RESERVED FOR TEST -61RESERVED FOR TEST -62RESERVED FOR TEST -63RESERVED FOR TEST -64RESERVED FOR TEST -65RESERVED FOR TEST -66RESERVED FOR TEST -67USED ON DAU 1 -68USED ON DAU 1 -69RESERVED FOR TEST -70

{ (H) -71 (24)-T-S----------S---- ENGINE NO. 2ENG 2 OIL LEVEL { (W) -72 (24)-T-S----------S---- OIL LEVEL

{ (L) -73 (24)-T-S----------S---- SENSORSHIELD GND ────────────┘ └──── SHIELD GND

-74BATT 2 TEMP SNS 2 { (H) -75 (24)-T-S----------S---- BATT NO. 2

{ (L) 137J1B-76 (24)-T-S----------S---- TEMP SENSORSHIELD GND ────────────┘ └──── SHIELD GND






{ IMPELLOR 137J1B-77 (24)-T-S----------S---- ENGINE NO. 2ENG 2 FUEL FLOW { COMMON -78 (24)-T-S----------S---- FUEL FLOW

{ DRUM -79 (24)-T-S----------S---- METERSHIELD GND ────────────┘ └──── SHIELD GND

FLAP POSITION 2 { (H) -80 (24)-T-S----------S---- FLAP ELEC.{ (L) -81 (24)-T-S----------S---- CNTRL UNIT


HYD 1 PRESSURE { (H) -82 (24)-T-S----------S---- HYD PRESS{ (L) -83 (24)-T-S----------S---- XDUCER NO. 1


HYD 2 PRESSURE { (H) -84 (24)-T-S----------S---- HYD PRESS{ (L) -85 (24)-T-S----------S---- XDUCER NO. 2


ENG 2 LP VIB { (H) -86 (24)-T-S----------S---- ENGINE NO. 2{ (L) -87 (24)-T-S----------S---- LP VIB SENSOR


GEN 2 VOLTAGE { (H) -88 (24)------------------- GENERATOR NO. 2{ (L) -89 (24)------------------- LINE

GEN 4 VOLTAGE { (H) -90 (24)------------------- GENERATOR NO. 4{ (L) -91 (24)------------------- LINE

GEN 2 CURRENT { (H) -92 (24)-T-S----------S---- GENERATOR NO. 2{ (L) -93 (24)-T-S----------S---- SHUNT


RESERVED -94-95

RESERVED -96-97

RS-422 XMT CH. A (H) -98 (24)-T-S----------S---- 136J1B-100 (H)RS-422 XMT CH. A (L) -99 (24)-T-S----------S---- 136J1B-101 (L)


RS-422 RCV CH. A (H) -100 (24)-T-S---------S---- 136J1B-98 (H)RS-422 RCV CH. A (L) 137J1B-101 (24)-T-S---------S---- 136J1B-99 (L)

SHIELD GND ─────────────┘ └──── SHIELD GND






GEN 4 CURRENT { (H) 137J1B-102 (24)-T-S---------S---- GENERATOR NO. 4{ (L) -103 (24)-T-S---------S---- SHUNT


RS-232 XMT CH. A -104 (24)------------------}RS-232 RCV CH. A -105 (24)------------------} FIG. 6-34RS-232 COM CH. A 137J1B-106 (24)------------------}






AIL SYS2 PRESS SW DIN 137J2A-1 (24)--------------- AIL HYD PRESS SW 2ENG 2 BLEED POS DIN -2 (24)--------------- EBV POS MICRO SW 2APU BLEED POS DIN -3 (24)--------------- APU BLEED VALVER/AIR ACTR 2 POS DIN -4 (24)--------------- ACT POS MICRO SW 2SPARE GND/OPN DIN -5BLEED DUCT LEAK 2 DIN -6 (24)--------------- BLD DUCT LEAK SWS 2APU DUCT LEAK DIN -7 (24)--------------- APU DUCT LEAK SWSR AIR STARTER VLV DIN -8 (24)--------------- ATS VALVE RAPU LOW OIL PRESS DIN -9 (24)--------------- APU LOW OIL PRESS SWAPU HI OIL TEMP DIN -10 (24)-------------- APU OIL TEMP SWITCHEXTG BTL B CTRG 1 DIN -11 (24)-------------- EXTINGUISHER BTL BEXTG BTL B CRTG 2 DIN -12 (24)-------------- EXTINGUISHER BTL BEXTG BTL APU CRTG DIN -13 (24--------------- APU EXTINGUISHER BTLEXTG BTL B PRESS DIN -14 (24)-------------- EXTINGUISHER BTL BEXTG APU PRESS DIN -15 (24)-------------- APU EXTINGUISHER BTLENGLISH/METRIC DIN -16 (24)-------------- DAU STRAP (OPN=ENG)FLAP FAIL 2 DIN -17 (24)-------------- FLAP ELEC CNTRL UNITFUEL PRESS SW 2 DIN -18 (24)-------------- FUEL 2 PRESS SWAPU FUEL PRESS SW DIN -19 (24)-------------- APU FUEL PRESS SWHYD 2 THERMAL SW DIN -20 (24)-------------- HYD 2 THERMAL SWHYD 2 ENG PUMP SW DIN -21 (24)-------------- ENG PUMP PRESS SW 2HYD 2 ELEC PUMP SW DIN -22 (24)-------------- ELEC PUMP PRESS SW 2E2 A/ICE POS VLV DIN -23 (24)-------------- ENG 2 A/I VALVEWING2 A/I VLV POS DIN -24 (24)-------------- WING 2 A/ICE VALVEWING2 A/ICE LEAK DIN -25 (24)-------------- WING 2 DUCT LEAK SWSENG2 OIL LO PRESS DIN -26 (24)-------------- ENG 2 OIL LO PRESS SWENG 2 A/ICE SW DIN -27 (24)-------------- A/ICE CNTRL PANELENG2 OIL LO LEVEL DIN -28 (24)-------------- ENG 2 OIL LO LEVEL SWENG2 FUEL FILTER DIN -29 (24)-------------- ENG 2 FLTR BYPASS SWRUD 2 PRESS SW DIN -30 (24)-------------- RUD PRESSURE SW 2HS VALVE 2 POS DIN -31 (24)-------------- HS VALVE 2 POS SWSPOILER RIGHT IB DIN -32 (24)-------------- SPLR PROX SW RIGHT IBTR 2 INHIBIT DIN -33 (24)-------------- HCU INHIBIT SWITCHTR 2 UP DEPLOY DIN -34 (24)-------------- TR 2 UP DEPLOY SWTR2 3RY UNLOCK DIN -35 (24)-------------- UP/LOW 3RY UNLCK SWSTR2 UP NOT STOW DIN -36 (24)-------------- INB/OUT 2 STOW SWSTR2 LOW NOT STOW DIN -37 (24)-------------- INB/OUT STOW SWSTR 2 PRESS ISOL DIN -38 (24)-------------- HCU ISOLATION SWTR 2 LOW DEPLOY DIN -39 (24)-------------- TR 2 LOW DEPLOY SWTR 2 TRANSIT DIN -40 (24)-------------- UP/LOW TRANSIT SWENG 2 A/I LO PRESS DIN -41 (24)-------------- ENG 2 LOW PRESS SWWING 2 A/I LO PRESS DIN 137J2A-42 (24)-------------- WING 2 LOW PRESS SW






ENG 2 A/I OVRPRESS DIN 137J2A-43 (24)-------------- ENG 2 OVERPRESS SWWING 2 A/I OVRPRESS DIN -44 (24)-------------- WING 2 OVERPRESS SWRESERVED - END ITEM TEST -45SPARE GND/OPN DIN -46BEARING 3 FAIL DIN -47 (24)-------------- GEN 3BEARING 4 FAIL DIN -48 (24)-------------- GEN 4SPARE GND/OPN DIN -49FUEL SOV 2 OPEN DIN -50 (24)-------------- ENG2 FUEL SOV POS (O)FUEL SOV 2 CLOSED DIN -51 (24)-------------- ENG2 FUEL SOV POS (C)APU FUEL SOV CLSD DIN -52 (24)-------------- APU FUEL SOV POS (C)APU FUEL SOV OPEN DIN -53 (24)-------------- APU FUEL SOV POS (O)HYD SOV 2 OPEN DIN -54 (24)-------------- ENG 2 HYD SOV POS (O)HYD SOV 2 CLOSED DIN -55 (24)-------------- ENG 2 HYD SOV POS (C)ENG 2 BLEED CMD DIN -56 (24)-------------- EBV RELAY 2APU MASTER SW ON DIN -57 (24)-------------- APU CNTRL PANELENG 2 FIRE DIN -58 (24)-------------- ENG 2 FIRE CNTRL MODWING A/ICE SWITCH DIN -59 (24)-------------- ANTI-ICE CNTRL PANELSTAB A/ICE SWITCH DIN -60 (24)-------------- ANTI-ICE CNTRL PANEL2A POWER CNTOR ON DIN -61 (24)-------------- FUEL CONTROL PANEL2B POWER CNTOR ON DIN -62 (24)-------------- FUEL CONTROL PANELSPARE 28V/OPN DIN -63SPARE 28V/OPN DIN -64SPARE 28V/OPN DIN -65SPARE 28V/OPN DIN -66IDENT #1 CH. B -67 ------------------} NCIDENT #2 CH. B -68 ------------------} SIGNAL GROUNDIDENT #3 CH. B -69 ------------------} NC

-70-71-72

USED ON DAU 1 -73 -----NCUSED ON DAU 1 -74 -----NCUSED ON DAU 1 -75 -----NCUSED ON DAU 1 -76 -----NCRESERVED -77

-78RESERVED -79AIR/GROUND 2 DIN -80 (24)-------------- LANDING GEAR SYS

ENG 2 HP VIB { (H) -81 (24)-T-S----------S---- ENGINE NO. 2{ (L) 137J2A-82 (24)-T-S----------S---- HP VIB SENSOR







137J2A-83-84-85-86-87-88-89-90-91-92-93

RESERVED -94-95

RESERVED -96-97-98

SIGNAL GROUND #1 CH. B -99 (24)-------------- SIGNAL GROUNDSIGNAL GROUND #2 CH. B -100 (24)------------- SIGNAL GROUNDCHASSIS GROUND CH. B -101 (24)------------- CHASSIS GROUND

-102+28 VDC #1 CH. B -103 (22)-------------}+28 VDC #2 CH. B -104 (22)-------------} FIG.+28 VDC RTN #1 CH. B -105 (22)-------------} 6-1B+28 VDC RTN #2 CH. B 137J2A-106 (22)-------------}







-3-4-5-6-7-8

{ SIG (H) -9 (24)-T-S-----------S---- ENGINE NO. 2{ SIG (L) -10 (24)T-S-----------S---- OIL{ SHIELD GND ───────────┘ └──── SHIELD GND

ENG 2 OIL TEMP B {{ EXC (H) -11 (24)T-S-----------S---- TEMPERATURE{ EXC (L) -12 (24)T-S-----------S---- B SENSOR


-13-14-15-16-17-18-19-20-21-22-23-24-25-26-27-28-29

BATT 1 TEMP SNS 2 { (H) -30 (24)-T-S----------S---- BATT NO. 1{ (L) -31 (24)-T-S----------S---- TEMP SENSOR 2


-32-33

GPU VOLTAGE { (H) -34 (24)------------------- BATTERY RELAY BOX{ (L) 137J2B-35 (24)------------------- LINE CONNECTOR






BATT 2 VOLTAGE { (H) 137J2B-36 (24)------------------- HOT BATT{ (L) -37 (24)------------------- BUS NO. 2

APU GEN CURRENT { (H) -38 (24)-T-S----------S---- APU GENERATOR{ (L) -39 (24)-T-S----------S---- SHUNT


ARINC 429 OUT #1 B (H) -40 (24)-T-S----------S---- MAINTENANCEARINC 429 OUT #1 B (L) -41 (24)-T-S----------S---- COMPUTER


ARINC 429 IN #5 (H) -42 (24)-T-S----------S---- STALL WARN CH. BARINC 429 IN #5 (L) -43 (24)-T-S----------S---- STALL WARN CH. B


ARINC 429 IN #6 (H) -44 (24)-T-S----------S---- FADEC NO. 2ARINC 429 IN #6 (L) -45 (24)-T-S----------S---- CH. B


-46-47-48-49

ARINC 429 OUT #2 B (H) -50 (24)-T-S----------S---- FIG.ARINC 429 OUT #2 B (L) -51 (24)-T-S----------S---- 6-12(To IC 1 & 2) SHIELD GND ───────────┘ └──── SHIELD GND

-52-53-54-55

RESERVED FOR TEST -56RESERVED FOR TEST -57RESERVED FOR TEST -58RESERVED FOR TEST -59RESERVED FOR TEST -60RESERVED FOR TEST -61RESERVED FOR TEST -62RESERVED FOR TEST -63RESERVED FOR TEST -64RESERVED FOR TEST -65RESERVED FOR TEST -66RESERVED FOR TEST -67

-68-69

RESERVED FOR TEST 137J2B-70






137J2B-71-72-73-74-75-76-77-78-79-80-81-82-83-84-85-86-87-88-89-90-91-92-93

RESERVED -94-95

RESERVED -96-97

RS-422 XMT CH. B (H) -98 -----NCRS-422 XMT CH. B (L) -99 -----NC

RS-422 XMT CH. B (H) -100 -----NCRS-422 XMT CH. B (L) -101 -----NC

-102-103

RS-232 XMT CH. B -104 (24)------------------}RS-232 RCV CH. B -105 (24)------------------} FIG. 6-34RS-232 COM CH. B 137J2B-106 (24)------------------}




PILOT’SCOMMUNICATIONS UNIT

RCZ-851E


RESERVED 143J1-1(O) +28 V DC FAN POWER -2 (24)------------------ COOLING FAN - RED(P) +28 V DC COMM POWER -4 (22)------------------(P) +28 V DC COMM POWER -5 (22)------------------ FIG. 6-1(P) +28 V DC COMM POWER -6 (22)------------------

(P) +28 V DC XPDR POWER RETURN -7 (22)------------------ DC POWER GND

(P) +28 V DC XPDR POWER -8 (22)------------------ FIG. 6-1(P) +28 V DC XPDR POWER -9 (22)------------------(B) RSB PRIMARY (H) -10 -T-S---------------S-- FIG. 6-21(B) RSB PRIMARY (L) -11 -T-S---------------S--

SHIELD GROUND ───────┘ └─── SHIELD GND

(B) SELCAL/ACARS (L) -12(B) SELCAL/ACARS (H) -22

RESERVED -13

(O) COM +28 V ACH PWR -14

(B) RCB RCVR (#1) (L) -15(B) RCB RCVR (#1) (H) -28

(O) COMM STRAP +5 V DC -16 (24)------------------ FIG. 6-22

(P) +28 V DC COMM POWER RETURN -17 (22)------------------(P) +28 V DC COMM POWER RETURN -18 (22)------------------ DC POWER GND(P) +28 V DC COMM POWER RETURN -19 (22)------------------(P) +28 V DC XPDR POWER RETURN -20 (22)------------------

(I) VHF 1 PTT (GND/OPEN) -21 (24)------------------ FIG. 6-27

(I/O) SIMULCOM RET -24 (24)-T-S-----------S-- C143J1-24(I/O) SIMULCOM -35 (24)-T-S-----------S-- C143J1-35

SHIELD GROUND ───────────┘ └── SHIELD GND

(B) COM ACH DATA (L) -25(B) COM ACH DATA (H) -33

RESERVED -26RESERVED 143J1-27




PILOT’SCOMMUNICATIONS UNIT (cont)

RCZ-851E


(O) EMER COM AUDIO (L) 143J1-29 (24)-T-S-----------S-- FIG. 6-29(O) EMER COM AUDIO (H) -31 (24)-T-S-----------S--

SHIELD GROUND ───────────┘ └─── SHIELD GND

(O) REC PHONE AUDIO (H) -30

(I) AUX AUD 4 (L) -34(I) AUX AUD 4 (H) -62

(I) AUDIO STATUS 3 (GND/OPEN) -36

(I) COM 3 XMIT (GND/OPEN) -37 (24)------------------ COM 3 PTT

(I) AUX AUD 2 (H) -38(I) AUX AUD 2 (L) -49

(I) HF COM DISABLE (GND/OPEN) -39(I) GND (AUDIO SHIELDS) -40(I) COM +28V ACH RTN -41(I) AUDIO BUS SHIELD (GND) -42(O) COM STRAP +5 V DC RETURN -43 (24)------------------ COMM 1 STRAP CAA

FIG. 6-22(I) GND -44 (24)------------------ (I) GND -45 (24)------------------ BOBBIN(I) GND -46 (24)------------------


(I) COM 3 AUD (L) -50 (24)-T-S-----------S-- COM 3(I) COM 3 AUD (H) -66 (24)-T-S-----------S-- AUDIO


(I) AUX AUD 3 (L) -51(I) AUX AUD 3 (H) -52(B) RCB RCVR (#2) (L) -53(B) RCB RCVR (#2) (H) -68(O) +28 V DC FAN POWER RETURN -54 (24)------------------ COOLING FAN - BLUE(B) XPDR TO TCAS 429A -55 (24)-T-S-----------S-- 193RMP-14F(B) XPDR TO TCAS 429B 143J1-87 (24)-T-S-----------S-- 193RMP-14G






RCZ-851E


(B) AUDIO BUS #1 (H) 143J1-56 -T-S---------------S-- FIG. 6-23(B) AUDIO BUS #1 (L) -70 -T-S---------------S--SHIELD GROUND ───────┘ └─── SHIELD GND

(O) SIDETONE PHONE AUDIO (H) -57(I) GND -58 (24)------------------ BOBBIN(O) AGC ANALOG TP -59(I) GND -60 (24)------------------ BOBBIN

(B) LEFT SEC RSB (L) -61 -T-S---------------S-- FIG. 6-21(B) LEFT SEC RSB (H) -74 -T-S---------------S--SHIELD GROUND ───────┘ └─── SHIELD GND

(I) CHASSIS GND -67 (24)------------------ BOBBINRESERVED -71RESERVED -72

(I) AUDIO STATUS 1 (GND/OPEN) -76(I) ALT SRC SEL 2 (NO) -80 (24)------------------ FIG. 6-11(B) RCB XMTR (#1) (H) -81(B) RCB XMTR (#1) (L) -95(B) RCB XMTR (#2) (H) -82(B) RCB XMTR (#2) (L) -96

WOW -83 (24)------------------ FIG. 6-2RESERVED -84RESERVED -85

(O) COM STRAP CLK -88 (24)------------------ COMM 1 STRAP CCA(O) COM STRAP SIDE A0 -89 (24)------------------ FIG. 6-22

(B) TCAS TO XPDR 429A -90 (24)-T-S-----------S-- 193RMP-15J(B) TCAS TO XPDR 429B -104 (24)-T-S-----------S-- 193RMP-15K

SHIELD GROUND ────────────┘ └─── SHIELD GND

(O) XPDR ACTIVE (NO) -91 (24)------------------ TO AIRCRAFTANT. RELAY

(I) VHF 1 MIC (H) -92 (24)-T-S----------S-- FIG. 6-27(I) VHF 1 MIC (L) -106 (24)-T-S----------S--

SHIELD GROUND ────────────┘ └─── SHIELD GND

(I) COMM OFF (GND/OPEN) -93XPDR MUT SUP (P) 143J1-94 (24)-T-S-----------S-- FIG. 6-31






RCZ-851E


(I) RESERVED 143J1-97(I) RESERVED -98(B) ADC 1 TO XPDR 429A -99 (24)-T-S-----------S-- 9J1-66, FIG.6-11(B) ADC 1 TO XPDR 429B -86 (24)-T-S-----------S-- 9J1-67


(B) ADC 2 TO XPDR 429A -100 (24)-T-S----------S-- C9J1-66, C1J1B-K4,FIG. 6-11

(B) ADC 2 TO XPDR 429A -69 (24)-T-S----------S-- C9J1-67, C1J1B-K5SHIELD GROUND ────────────┘ └─── SHIELD GND

(I) COM STRAP DATA -101 (24)-----------------(O) COM STRAP LOAD -102 (24)----------------- FIG. 6-22(O) COM STRAP SIDE A1 -103 (24)-----------------

RESERVED -104(I) RESERVED 143J1-105





RCZ-851E


TRANSPONDER ANTENNA 143J2-1 ---(RG-214/U)-S-------- BOTTOM(BOTTOM) │ XPDR ANTENNA

143J2-2 ───────────────┘

COM ANTENNA 143J3-1 ---(RG-142/U)-S-------- COM ANT #1143J3-2 ───────────────┘

TRANSPONDER ANTENNA 143J6-1 ---(RG-214/U)-S-------- TOP(TOP) │ XPDR ANTENNA

143J6-2 ───────────────┘




PILOT’SRADIO MANAGEMENT UNIT

RM-855


(P) 28 V DC LIGHTING 144J1-A(P) 28 V DC LIGHTING RET -B(P) +28 V DC POWER -C (22)------------------ FIG. 6-1(P) +28 V DC POWER RETURN -D (22)------------------ DC GND(B) NAV BACKUP BUS (+) -E (24)-T-S-----------S-- 164J1B-102(B) NAV BACKUP BUS (-) -F (24)-T-S-----------S-- 164J1A-84


(P) 5 V DC LIGHTING -G (24)-T-S-----------S-- FIG. 6-7(P) 5 V DC LIGHTING RETURN -H (24)-T-S-----------S-- LIGHTING GND


(P) 0-5 V AC LIGHTING -J(P) 0-5 V AC LIGHTING RET -K

(I) CHASSIS GROUND -L (24)------------------ CHASSIS GND

(B) LEFT SEC RSB (H) -M -T-S---------------S-- FIG. 6-21(B) LEFT SEC RSB (L) -N -T-S---------------S--SHIELD GROUND───────┘ └── SHIELD GND

(I) WOW (GND/OPEN) -P (24)------------------ FIG. 6-2(I) WOW POLARITY (GND/OPEN) -R (24)------------------ SIGNAL GROUND

(GND FOR WOW=GND)(I) ATC IDENT (GND/OPEN) -S (24)------------------ TO ID SWITCHES,

C144J1-S(I) DISCRETE 1 INPUT 4 -T

(I) CHASSIS GROUND -U (24)------------------ CHASSIS GROUND

(B) PRIMARY RSB (H) -V -T-S---------------S-- FIG. 6-21(B) PRIMARY RSB (L) -W -T-S---------------S--SHIELD GROUND───────┘ └── SHIELD GND

(I) DISCRETE 1 INPUT 3 -X(I) ON/OFF PAGE DISABLE -Y (24)------------------ SIGNAL GND

(GND/OPEN)(I) DISCRETE 1 INPUT 1 -Z(I) DISCRETE 1 INPUT 0 -a(I) SIDE SEL B0 (GND/OPEN) -b (24)------------------ SIG. GND(I) SIDE SEL B1 (GND/OPEN) -c (24)------------------ SIG. GND(I) SIDE SEL EV PARITY -d (24)------------------ SIG. GND

(GND/OPEN)(I) TEST ENABLE (GND/OPEN) -e(I) COM FREQ XF (GND/OPEN) -f(I) COM MEM SEL 144J1-g

(GND/OPEN)




PILOT’SRADIO MANAGEMENT UNIT (cont)

RM-855


(I) MKR SENSE LEFT 144J1-h (24)------------------ 160J2-L, C144J1-h(I) MKR SENSE RIGHT -i (24)------------------ C160J2-L, C144J1-i(O) COM POWER OFF (GND/OPEN) -j(O) ATC POWER OFF (GND/OPEN) -k(O) VOR POWER OFF (GND/OPEN) -m(O) DME POWER OFF (GND/OPEN) -n(O) ADF POWER OFF (GND/OPEN) -p(O) MLS POWER OFF (GND/OPEN) -q(O) DISCRETE OUTPUT 1 -r(O) DISCRETE OUTPUT 0 -s(I) FMS BUS (-) -t (24)------------------ 121J1B-30,C144J1-t(I) ENG BACKUP FUNCTION ENABLE -u(I) NAV BACKUP FUNCTION ENABLE -v(I) ENG DISPLAY ENABLE #1 -w (24)------------------ 190J1B-34(I) ENG DISPLAY ENABLE #2 -x (24)------------------ C190J1B-34(I) ENG DISPLAY ENABLE #3 -y(I) DAU CONFIGURATION (2 DAUS) -z(I) FMS BUS (+) -AA (24)------------------ 121J1B-31,C144J1-AA(I) IAC CONFIGURATION 2 -BB

(B) DAU #1 (+) -CC (24)-T-S-----------S-- FIG. 6-14(B) DAU #1 (-) -DD (24)-T-S-----------S-- FIG. 6-14


(I) SPARE -EE

(B) DAU #2 (+) -FF (24)-T-S-----------S-- FIG. 6-14(B) DAU #2 (-) -GG (24)-T-S-----------S-- FIG. 6-14


(I) SPARE -HH(B) ARINC DAU 3 (H) -JJ(B) ARINC DAU 3 (L) -KK(P) +28 V DC PRIMARY POWER -LL (22)------------------ FIG. 6-1(P) +28 V DC PRIMARY POWER RTN -MM (22)------------------ DC GND(I) SPARE -NN(I) SPARE 144J1-PP

NOTE: THE REMOTE ON/OFF FUNCTION MUST NOT BE CONNECTED ON THE EMERGENCYRADIO SIDE.




ADF ANTENNA


(I) ADF MOD SHLD 158J1-A

(I) ADF COS MOD -B (24)-T-S---------------- 164J1A-91(I) ADF SIN MOD -H (24)-T-S---------------- 164J1A-104

└─────┐(I) ADF ANT TEST -C (24)---------│---------- 164J1A-77

│(I) ADF OUTER SHLD -D │(O) ADF INNER SHLD -E ──────────┐ ├────────── SEE NOTE BELOW(O) ADF RF INPUT -F -(TRIAX)-IS-OS---------- 164J2-1

(P) ADF +15 VDC -G (24)-------------------- 164J1B-1(P) ADF +15 VDC RETURN -J (24)-------------------- 164J1B-27

(I) ADF LOOP EN 158J1-K (24)-------------------- 164J1A-101

NOTE: RECOMMENDED ADF ANTENNA TRIAXIAL CABLE IS TROMPETER PN TRC-50-2 OREQUIVALENT. THE TRIAXIAL CABLE OUTER SHIELD IS GROUNDED AT THE ADFANTENNA END ONLY, TO THE AIRFRAME AND TO THE ADF MODULATION SHIELD. THEGROUND WIRE SHALL BE 20 AWG OR LARGER AND THE LENGTH SHALL NOT EXCEED 10INCHES.




PILOT’SAUDIO PANELAV-850A


(I) HAND MIC PTT 160J1-A (24)------------------ FIG. 6-24(GND/OPEN)

(O) EMERGENCY COM PTT -B (24)------------------ FIG. 6-27(GND/OPEN)

(O) VHF 2 PTT (GND/OPEN) -C (24)------------------(O) VHF 2 MIC (H) -D (24)---S-----------S-- FIG. 6-28(O) VHF 2 MIC (L) -W (24)---S-----------S--


(O) VHF 1 MIC (L) -E (24)---S-----------S--(O) VHF 1 MIC (H) -R (24)---S-----------S-- FIG. 6-27

SHIELD GND ──────────┘ └── SHIELD GND(O) VHF 1 PTT (GND/OPEN) -F (24)------------------

(I) EMER COM AUDIO (H) -G (24)-T-S-----------S-- FIG. 6-29(I) EMER COM/NAV AUDIO (L) ┌ -m (24)-T-S-----------S--SHIELD GND │ ──────────┘ └── SHIELD GND

│(I) EMER NAV AUDIO (H) │ -f (24)-T-S-----------S-- FIG. 6-29(I) EMER COM/NAV AUDIO (L) └ -m (24)-T-S-----------S--


(O) EMER COM MIC (L) -H (24)-T-S-----------S-- FIG. 6-27(O) EMER COM MIC (H) -P (24)-T-S-----------S--SHIELD GND ────────┘ └── SHIELD GND

(I) HAND MIC/MASK-BOOM MIC (L) -J (24)---S-----------S-- FIG. 6-24(I) HAND MIC (H) -K (24)---S-----------S--SHIELD GND ──────────┘ └── SHIELD GND

(O) CABIN/COCKPIT SPKR (L) ┌ -L (22)-T-S-----------S-- NO. 1 COCKPIT(O) COCKPIT SPKR (H) │ -Y (22)-T-S-----------S-- SPEAKER

SHIELD GND │ ──────────┘ └── SHIELD GND│

(O) CABIN/COCKPIT SPKR (L) └ -L (22)-T-S-----------S-- CABIN(O) CABIN SPKR (H) -e (22)-T-S-----------S-- SPEAKER


(P) +28 V DC POWER RETURN -M (22)------------------ DC GND

(I) COMMON GND -N(I) RESERVED HF MIC (L) -S (24)-T-S-----------S-- HF(I) RESERVED HF MIC (H) 160J1-T (24)-T-S-----------S-- MIC

└─── SHIELD GND




PILOT’SAUDIO PANEL (cont)

AV-850A


(P) +28 V DC POWER 160J1-U (22)------------------ FIG. 6-1(P) +28 V DC POWER -V (22)------------------ FIG. 6-1(I) HF PTT -X (24)------------------ HF PTT SWITCH(I) COM 3 MIC (L) -Z (24)-T-S-----------S-- COM 3(I) COM 3 MIC (H) -a (24)-T-S-----------S-- MIC


(O) HF 1 PTT (GND/OPEN) -b(B) DIG AUDIO BUS 2 (+) -c (24)-T-S-----------S-- FIG. 6-23(B) DIG AUDIO BUS 2 (-) -n (24)-T-S-----------S--


(B) DIG AUDIO BUS 1 (+) -d (24)-T-S-----------S-- FIG. 6-23(B) DIG AUDIO BUS 1 (-) -p (24)-T-S-----------S--SHIELD GND ───────┘ └── SHIELD GND

(I) 5 V LIGHTING GND -g (24)-T-S-----------S-- LIGHTING GND(P) 5 V LIGHTING -q (24)-T-S-----------S-- FIG. 6-7

SHIELD GND ──────┘ └── SHIELD GND

(I) MASK/BOOM PTT -h (24)------------------ FIG. 6-24(GND/OPEN)

(I) MASK/BOOM MIC (H) -i

(I/O) INTERPHONE AUDIO (L) -j (24)-T-S-----------S-- E160J1-j, C160J1-j(I/O) INTERPHONE AUDIO (H) -s (24)-T-S-----------S-- E160J1-s, C160J1-s


(O) PHONE AUDIO (L) -k (24)---S-----------S-- FIG. 6-24(O) PHONE AUDIO (H) -t (24)---S-----------S--SHIELD GND ───────┘ └── SHIELD GND

(P) +28 V DC DIMMING 160J1-r





AV-850A


(I) WARNING 5 AUDIO (H) 160J2-A(I) WARNING 5 AUDIO (L) -a

(I) WARNING 1 AUDIO (L) -B (24)-T-S------------S-- AURAL WARNING(I) WARNING 1 AUDIO (H) -W (24)-T-S------------S-- UNIT


(I) MASK MIC (H) -E (24)------------------- FIG. 6-24(I) MASK/BOOM MIC (L) -C

(I) COMMON GND -D (24)------------------- FIG. 6-24

(I) WARNING 2 AUDIO (L) -G(I) WARNING 2 AUDIO (H) -X

(I) CABIN DISABLE (GND/OPEN) -H(I) WARNING 3 AUDIO (L) -J(I) WARNING 3 AUDIO (H) -m

RESERVED -K

(O) MARKER BEAC 1 HI/LO SENS -L (24)------------------- 144J1-h, C144J1-h(O) STERO MUTE (GND/OPEN) -M

SPARE -N

(O) MAINT PHONE AUDIO (L) -P (24)-T-S------------S-- PA SYSTEM,(O) MAINT PHONE AUDIO (H) -f (24)-T-S------------S-- FIG. 6-30


(I) MAINT 2 MIC PTT -R

(I) AUXILIARY PTT -S(I) AUXILIARY MIC LO -T(I) AUXILIARY MIC HI 160J2-s





AV-850A


(I) PA MIC LO 160J2-U (24)-T-S-----------S-- PA SYSTEM,(I) PA MIC HI -i (24)-T-S-----------S-- FIG. 6-30


(O) VOICE RECORDER HI -V (24)-T-S-----------S-- COCKPIT VOICE(O) VOICE RECORDER LO -r (24)-T-S-----------S-- RECORDER


(I) BOOM MIC HI -Y (24)------------------ FIG. 6-24

(I) SPARE GND -C

(I) WARNING 4 AUDIO LO -Z(I) WARNING 4 AUDIO HI -t

(I) MASK INTERCOM ENABLE -b

(O) INT XMIT -c (24)------------------ E160J1-c, C160J2-cSPARE -d

(I) MAINT 1 MIC (LO) -e (24)-T-S-----------S-- PA SYSTEM,(I) MAINT 1 MIC (HI) -q (24)-T-S-----------S-- FIG. 6-30


(I) MAINT 2 MIC H -g(I) MAINT 2 MIC L -n

RESERVED -h

(I) PA PTT -j (24)------------------ PA SYSTEM,FIG. 6-30

(I) MAINT 1 MIC PTT -k (24)------------------ PA SYSTEM,FIG. 6-30

(I) INTERPHONE PTT 160J2-p (24)------------------ FIG. 6-24




OBSERVER’SAUDIO PANELAV-850A


(I) HAND MIC PTT E160J1-A (24)------------------ FIG. 6-26(GND/OPEN)

(O) EMERGENCY COM PTT -B(GND/OPEN)




SHIELD GND ──────────┘ └── SHIELD GND(O) VHF 1 PTT (GND/OPEN) -F (24)------------------

(I) EMER COM AUDIO (H) -G(I) EMER COM/NAV AUDIO (L) ┌ -m

│(I) EMER NAV AUDIO (H) │ -f(I) EMER COM/NAV AUDIO (L) └ -m

(O) EMER COM MIC (L) -H(O) EMER COM MIC (H) -P

(I) HAND MIC/MASK-BOOM MIC (L) -J (24)---S-----------S-- FIG. 6-26(I) HAND MIC (H) -K (24)---S-----------S--SHIELD GND ──────────┘ └── SHIELD GND

(O) CABIN/COCKPIT SPKR (L) ┌ -L (22)-T-S-----------S-- NO. 3 COCKPIT(O) COCKPIT SPKR (H) │ -Y (22)-T-S-----------S-- SPEAKER

SHIELD GND │ ──────────┘ └── SHIELD GND│

(O) CABIN/COCKPIT SPKR (L) └ -L (22)-T-S-----------S-- CABIN(O) CABIN SPKR (H) -e (22)-T-S-----------S-- SPEAKER


(P) +28 V DC POWER RETURN -M (22)------------------ DC GND(I) COMMON GND -N(I) HF MIC (L) -S (24)-T-S-----------S-- HF(I) HF MIC (H) -T (24)-T-S-----------S-- MIC

└─── SHIELD GND(P) +28 V DC POWER -U (22)------------------ FIG. 6-1(P) +28 V DC POWER -V (22)------------------ FIG. 6-1(I) HF PTT E160J1-X (24)------------------ HF PTT




OBSERVER’SAUDIO PANEL (cont)

AV-850A


(I) COM 3 MIC (L) E160J1-Z (24)-T-S-----------S-- COM 3(I) COM 3 MIC (H) -a (24)-T-S-----------S-- MIC


(I) COM 3 PTT (GND/OPEN) -b (24)------------------ COM 3 PTT SW(B) DIG AUDIO BUS 2 (+) -c (24)-T-S-----------S-- FIG. 6-23(B) DIG AUDIO BUS 2 (-) -n (24)-T-S-----------S--


(B) DIG AUDIO BUS 1 (+) -d (24)-T-S-----------S-- FIG. 6-23(B) DIG AUDIO BUS 1 (-) -p (24)-T-S-----------S--SHIELD GND ───────┘ └── SHIELD GND





(I/O) INTERPHONE AUDIO (L) -j (24)-T-S-----------S-- 160J1-j, C160J1-j(I/O) INTERPHONE AUDIO (H) -s (24)-T-S-----------S-- 160J1-s, C160J1-s


(O) PHONE AUDIO (L) -k (24)---S-----------S-- FIG. 6-26(O) PHONE AUDIO (H) -t (24)---S-----------S--SHIELD GND ───────┘ └── SHIELD GND

(P) +28 V DC DIMMING E160J1-r





AV-850A


(I) WARNING 5 AUDIO (H) E160J2-A(I) WARNING 5 AUDIO (L) -a

(I) WARNING 1 AUDIO (L) -B (24)-T-S------------S-- AURAL WARNING(I) WARNING 1 AUDIO (H) -W (24)-T-S------------S-- UNIT


(I) MASK MIC (H) -E (24)------------------- FIG. 6-26(I) MASK/BOOM MIC (L) -C

(I) COMMON GND -D (24)------------------- FIG. 6-26


(I) CABIN DISABLE (GND/OPEN) -H

(I) WARNING 3 AUDIO (L) -J(I) WARNING 3 AUDIO (H) -m

RESERVED -K

(O) MARKER BEAC 1 HI/LO SENS -L(O) STERO MUTE (GND/OPEN) -M

SPARE -N

(O) MAINT PHONE AUDIO (L) -P(O) MAINT PHONE AUDIO (H) -f

(I) MAINT 2 MIC PTT -R (24)------------------- FIG. 6-30

(I) AUXILIARY PTT -S(I) AUXILIARY MIC LO E160J2-T





AV-850A


(I) PA MIC LO E160J2-U (24)-T-S-----------S-- PA SYSTEM,(I) PA MIC HI -i (24)-T-S-----------S-- FIG. 6-30


(O) VOICE RECORDER HI -V (24)-T-S-----------S-- COCKPIT VOICE(O) VOICE RECORDER LO -r (24)-T-S-----------S-- RECORDER


(I) BOOM MIC HI -Y (24)------------------ FIG. 6-26

(I) SPARE GND -C



(O) INT XMIT -c (24)------------------ 160J2-c, C160J1-cSPARE -d

(I) MAINT 1 MIC (LO) -e(I) MAINT 1 MIC (HI) -q

(I) MAINT 2 MIC H -g (24)-T-S-----------S-- PA SYSTEM,(I) MAINT 2 MIC L -n (24)-T-S-----------S-- FIG. 6-30


RESERVED -h

(I) PA PTT -j (24)------------------ PA SYSTEM,FIG. 6-30

(I) MAINT 1 MIC PTT -k(I) INTERPHONE PTT E160J2-p (24)------------------ FIG. 6-26




PILOT’SNAVIGATION UNIT

RNZ-851


(O) DME HOLD NOT 164J1A-2(GND/OPEN)

(O) DME HOLD (GND/OPEN) -3

(O) DME 568 DATA (H) -5(O) DME 568 DATA (L) -15

(I) ADF RS 422 DATA SHIELD -7(O) AUX1 RCB TX1 -8(O) AUX1 RCB TX2 -9(P) ADF 26 V AC RETURN -10(P) ADF 26 V AC RETURN -11(O) ADF SYNCHRO Y OUT -12

(I) VOR/ILS ON/OFF (GND/OPEN) -14

(O) DME RS-422 SD2 (L) -16(O) DME RS-422 SD2 (H) -54

(O) DME 568 CLK (L) -17(O) DME 568 CLK (H) -19

(O) DME CH 1 AUDIO -18(I) MLS RCB SHLD -20

(O) MLS 1 RCB XMTR (H) -21 (24)-T-S-----------S-- 164J1A-25(O) MLS 1 RCB XMTR (L) -34 (24)-T-S-----------S-- 164J1A-38

(PROVISION) SHIELD GND ────────┘ └── SHIELD GND

(O) ADF SYNCHRO X OUT -22(P) ADF 26 V AC 400 HZ -23(I) CHANGE INHIBIT (GND/OPEN) -24

(I) MLS 1 RCB RCVR (H) -25 (24)-T-S-----------S-- 164J1A-21(I) MLS 1 RCB RCVR (L) -38 (24)-T-S-----------S-- 164J1A-34


(O) DME 568 SYNC (H) -26(O) DME 568 SYNC (L) -45

(O) DME MUT SUP RTN -28(O) ADF SYNCHRO Z OUT (GND) -33(I) ADF AUDIO OUT SHIELD -39

(I) DME ON/OFF 164J1A-40(OPEN/GND)




PILOT’SNAVIGATION UNIT (cont)

RNZ-851


(I) AUX 1 AUDIO (H) 164J1A-41(I) AUX 1 AUDIO (L) -55

(I/O) DME MUT SUP -42 (24)---S-----------S-- FIG. 6-31SHIELD GROUND ───────────┘ └── SHIELD GND

(O) DME RS-422 SD1 (L) -44 (24)-T-S-----------S-- RESERVED FOR(O) DME RS-422 SD1 (H) -57 (24)-T-S-----------S-- OPTIONAL FMS

SHIELD GROUND ───────────┘ └── SHIELD GND(O) DME VALID (28 V/OPEN) -46(O) ADF DC COS OUT -47(O) ADF AUDIO HI OUT -50(O) ADF AUDIO LO OUT -52

(I) NAV AUX DATA (L) -58(I) NAV AUX DATA (H) -70

(O) VOR/ILS RS-422 SD1 (L) -59 (24)-T-S-----------S-- RESERVED FOR(O) VOR/ILS MKR LAMP (M) -60 OPTIONAL FMS

(28 V/OPEN) (SEE J1B-89)(O) ADF DC SIN/SIN(NOT) OUT -61(O) AUX2 RCB TX1 -64(O) AUX2 RCB TX2 -65

(I) ADF HF KEY -66 (24)------------------ FIG. 6-32(I) AUX 2 AUDIO (H) -67(I) AUX 2 AUDIO (L) -68

(O) NAV AUX CLK (H) -69(O) NAV AUX CLK (L) -72

(O) DME 40 MV/MI -71(O) VOR/ILS MKR LAMP (I) -73

(28 V/OPEN)(O) RESERVED -74(I) AUX1 RCB RX1 -75(O) ADF ANTENNA TEST -77 (24)------------------ 158J1-C(I) AUX1 RCB RX2 -78(I) ADF MOD SHIELD -79(I) GND PS IN -80(I) AUX GND -81

(P) DME 28 V DC RETURN 164J1A-83 (22)------------------ DC POWER GND





RNZ-851


(O) VOR/ILS RS-422 SD 2B 164J1A-84 (24)----------------- 144J1-F

(P) VOR/ILS +28 V DC POWER -85 (22)-----------------(P) DME +28 V DC POWER -86 (22)----------------- FIG. 6-1(P) ADF +28 V DC POWER -87 (22)-----------------

(B) LEFT SEC RSB (H) -88 (24)-T-S----------S-- FIG. 6-21(B) LEFT SEC RSB (L) -102 (24)-T-S----------S--SHIELD GROUND────────────┘ └── SHIELD GND

(O) ADF COS MOD -91 (24)-T-S----------S-- 158J1-B(O) ADF SIN MOD -104 (24)-T-S----------S-- 158J1-H

SHIELD GROUND────────────┘ └── SHIELD GND

(I) AUX2 RCB RX1 -92(I) AUX2 RCB RX2 -93

(P) ADF 28 V DC RETURN -94 (22)----------------- DC POWER GND(P) DME 28 V DC RETURN -95 (22)----------------- DC POWER GND

(I) CLU SHLD GND -96(O) DME CH 2 AUDIO (H) -97

(P) VOR/ILS +28 V DC POWER -98 (22)-----------------(P) DME +28 V DC POWER -99 (22)----------------- FIG. 6-1(P) ADF +28 V DC POWER -100 (22)-----------------

(O) ADF LOOP EN -101 (24)----------------- 158J1-K

(I) CLUSTER GND -103 (22)----------------- DC POWER GND

(I) ADF MOD SHIELD 164J1A-105





RNZ-851


(O) ADF +15 V DC 164J1B-1 (24)------------------ 158J1-G

(O) 28 V DC FAN POWER -2 (24)------------------ COOLING FAN (RED)(I) SPARE STAT IN (DIG AUD) -5(I) SPARE STAT IN (DIG AUD) -6(I) RESERVED -7(I) AUX +28 V DC -8(O) RESERVED -9(O) RESERVED -10(O) RESERVED -11(O) RESERVED -12(I) MLS MORSE ID RETURN -13(P) RESERVED -20

(O) VOR/ILS RNAV VIDEO (H) -21(O) VOR/ILS RNAV VIDEO (L) -22(P) RESERVED -23

(P) ADF 28 V DC RETURN -25 (22)------------------ DC POWER GND

(O) NAV STRAP GND -26 (24)------------------ FIG. 6-22(O) ADF +15 V DC RETURN -27 (24)------------------ 158J1-J

(B) DIG AUDIO BUS 1 (L) -29 -T-S---------------S-- FIG. 6-23(B) DIG AUDIO BUS 1 (H) -42 -T-S---------------S--SHIELD GROUND───────┘ └── SHIELD GND

(I) SPARE STAT IN (DIG AUD) -30(I) AUD AUX SQUELCH -31(I) MLS MORSE ID (H) -32(I) RESERVED -33(I) RESERVED -34(I) RESERVED -35

(O) VOR/ILS EMER AUDIO (H) -36 (24)-T-S-----------S-- FIG. 6-29(O) VOR/ILS EMER AUDIO (L) -51 (24)-T-S-----------S--SHIELD GROUND ───────────┘ └── SHIELD GND

(O) RESERVED -37(P) VOR/ILS POWER RETURN -38 (22)------------------ DC POWER GND(P) VOR/ILS +28 V DC 164J1B-39 (22)------------------ FIG. 6-1

POWER





RNZ-851IOBP Function Connector Pin Connects To

(O) NAV STRAP +5 V DC 164J1B-40 (24)----------------- FIG. 6-22

(O) FAN 28 V DC POWER RETURN -44 (24)----------------- COOLING FAN (BLUE)

(I) AUDIO AUX XMT -45(I) RESERVED -47(I) RESERVED -48(O) RESERVED -49

(P) VOR/ILS POWER RETURN -50 (22)----------------- DC POWER GND(P) VOR/ILS +28 V DC POWER -52 (22)----------------- FIG. 6-1

(I) EFIS/MLS RIGHT -56

(I) NAV STRAP SIDE SPARE -57 (24)-----------------(I) NAV STRAP DATA -58 (24)----------------- FIG. 6-22(O) NAV STRAP CLK -59 (24)-----------------(O) NAV STRAP WD LOAD -84 (24)-----------------

(O) RESERVED -60(O) RESERVED -61(I) RESERVED -62(O) RESERVED -63(O) ILS MODE -64(O) RESERVED -65(O) RESERVED -66(I) DIG AUDIO BUS SHLD -67(P) ADF 26 V AC 400 HZ -68

(B) RSB PRIMARY (H) -71 -T-S--------------S-- FIG. 6-21(B) RSB PRIMARY (L) -81 -T-S--------------S--SHIELD GROUND────────┘ └── SHIELD GND

(O) ADF SYNTH CLOCK -72

(O) ADF RS 422 TXD B -73(O) ADF RS 422 TXD A -100

(O) VOR/ILS MKR LAMP (O) -74(28 V/OPEN)

(O) RESERVED -75(O) RESERVED -76(O) RESERVED -78(O) RESERVED -79(I) NAV STRAP SIDE SELECT -80 (24)----------------- FIG. 6-22(I) SEC RSB BUS SHIELD 164J1B-85





RNZ-851


(I) ADF ON/OFF 164J1B-87(O) NAV AUX SHIFT LD (L) -88(O) NAV AUX SHIFT LD (H) -90

(O) VOR RS-422 SD 1 (H) -89 (24)-T-S----------S-- RESERVED FOR(O) RESERVED -91 OPTIONAL FMS(O) RESERVED -92 (SEE J1A-59)(O) RESERVED -93(I) PRIMARY RSB BUS SHIELD -95(I) EFIS/MLS LEFT -96

(I) CLU GND -98 (22)------------------ DC POWER GND

(O) ADF LOCK -99(O) VOR/ILS RS-422 SD 2B -102 (24)------------------ 144J1-E(O) RESERVED -103(O) RESERVED -104(O) RESERVED 164J1B-106





RNZ-851IOBP Function Connector Pin Connects To

┌───── 158J1-E(I) ADF RF INPUT 1 164J2-1 -(TRIAX)-IS-OS--IS-OS- 158J1-F(I) ADF RF INPUT 2 164J2-2 ─────────┘ │ └── SHIELD GND

NC ────────────┘

(I) VOR/LOC ANT 164J3-1 ----S--------------S-- VOR/LOC 1 ANT(I) 164J3-2 ────┘ └── SHIELD GND

(I) GS ANT 164J4-1 ----S--------------S-- GS 1 ANT(I) 164J4-2 ────┘ └── SHIELD GND

(I) MKR BEAC ANT 164J5-1 ----S--------------S-- MKR BEAC 1 ANT(I) 164J5-2 ────┘ └── SHIELD GND

(I) DME ANT 164J6-1 ----S--------------S-- DME 1 ANT(I) 164J6-2 ────┘ └── SHIELD GND




CLEARANCE DELIVERY UNITCD-850


ON/OFF OUTPUT 165J1-AAUDIO INPUT HIGH -B

(I) WEIGHT ON WHEELS SENSE -C (24)------------------ 165J1-L, 165J1-q(GND WHEN WOW=GND)

(P) 5 V AC/DC LIGHTING INPUT -D (24)-T-S-----------S-- FIG. 6-7(P) LIGHTING COMMON -Z (24)-T-S-----------S-- DC GND


(P) 28 V DC POWER INPUT -E (22)------------------ FIG. 6-1(B) NAV AUX SHIFT/LOAD -F (24)-T-S-----------S-- C164J1B-90

INPUT BUS (+) │ │(B) NAV AUX SHIFT/LOAD -G (24)-T-S-----------S-- C164J1B-88

INPUT BUS (-) │ │SHIELD GND ──────┘ └─── SHIELD GND

SPARE -I(B) COM AUX OUTPUT BUS (+) -H (24)-T-S-----------S-- C143J1-33(B) COM AUX OUTPUT BUS (-) -J (24)-T-S-----------S-- C143J1-25

SHIELD GND ──────┘ └─── SHIELD GND

COM AUX OUTPUT BUS -pSHIELD GND

(B) PRIMARY RSB BUS (-) -R (24)-T-S-----------S--- FIG. 6-21(B) PRIMARY RSB BUS (+) -g (24)-T-S-----------S---SHIELD GND ──────┘ └─── SHIELD GND

RSB SHLD GND -K(I) WIDE BAND SELECT INPUT -L (24)------------------- 165J1-q, 165J1-C(B) NAV AUX OUTPUT BUS (+) -M (24)-T-S-----------S-- C164J1A-70(B) NAV AUX OUTPUT BUS (-) -N (24)-T-S-----------S-- C164J1A-58


NAV AUX OUTPUT BUS -dSHIELD GND

(B) NAV AUX CLOCK INPUT BUS (-)-P (24)-T-S------------S-- C164J1A-72(B) NAV AUX CLOCK INPUT BUS (+)-f (24)-T-S------------S-- C164J1A-69


NAV AUX CLOCK BUS 165J1-rSHLD GND




CLEARANCE DELIVERY UNIT (cont)CD-850


SPARE 165J1-QNAV AUDIO INPUT LOW -SROTOR MOD FILTER INPUT -T

(I) 0/300 DEG. ELECT INPUT -U(I) VSMA 7.9 V/11.8 V MAX INPUT-V

POST FAIL ANNUN OUTPUT -WCD/COM/NAV SELECT (+) -X

(I) WEIGHT ON WHEELS 165J1-Y (24)------------------- FIG. 6-2




CLEARANCE DELIVERY UNIT (cont)CD-850


28 V DC LIGHTING 165J1-aINPUTAUDIO OUTPUT HIGH -b

AUDIO OUTPUT LOW -cSYNCHRO/RSB COMPASS INPUT -e

NAV AUDIO INPUT HIGH -hRMI REL/MAG BEARING INPUT -i

(P) POWER GROUND -j (22)------------------ DC GNDAUDIO SHLD GND -kSPARE -lCD/COM/NAV SELECT -m

(I) SIDE SELECT -nSPARE -o

(O) JUMPER GND -q (24)------------------ 165J1-C,165J1-LNAV AUDIO SHLD GND -sAUDIO INPUT LOW -tSPARE -uSPARE -vSPARE -wSPARE -xSPARE -ySPARE 165J1-z




INTEGRATED AVIONICS COMPUTERIC-600


ADI VIDEO + 190J1A-1 ADI VIDEO - -2 │SPARE -3 │ADI COLOR 0 + -4 │ADI COLOR 0 - -5 │SPARE -6 │ADI COLOR 1 + -7 │ADI COLOR 1 - -8 │SPARE -9 │ADI COLOR 2 + -10 │ADI COLOR 2 - -11 │SPARE -12 │ADI COLOR 3 + -13 │ADI COLOR 3 - -14 │SPARE -15 │ADI FLYBACK + -16 │ADI FLYBACK - -17 │SPARE -18 │ADI PRIMARY TUBE VALID -19 RESERVEDADI RASTER/STROKE + -20 │ADI RASTER/STROKE - -21 │SPARE -22 │ADI PRIMARY STROKE READY + -23 │ADI PRIMARY STROKE READY - -24 │ADI SEC STROKE READY + -25 │ADI SEC STROKE READY - -26 │ADI SEC TUBE VALID -27 │HSI VIDEO + -28 │HSI VIDEO - -29 │SPARE -30 │HSI COLOR 0 + -31 │HSI COLOR 0 - -32 │SPARE -33 │HSI COLOR 1 + -34 │HSI COLOR 1 - -35 │SPARE -36 │HSI COLOR 2 + -37 │HSI COLOR 2 - -38 │SPARE 190J1A-39




INTEGRATED AVIONICS COMPUTER (cont)IC-600


HSI COLOR 3 + 190J1A-40 HSI COLOR 3 - -41 │SPARE -42 │HSI FLYBACK + -43 │HSI FLYBACK - -44 │SPARE -45 │HSI PRIMARY TUBE VALID -46 │HSI RASTER/STROKE + -47 │HSI RASTER/STROKE - -48 │SPARE -49 │HSI PRIMARY STROKE READY + -50 │HSI PRIMARY STROKE READY - -51 │

│HSI SEC STROKE READY + -52 │HSI SEC STROKE READY - -53 RESERVEDHSI SEC TUBE VALID -54 │

│ADI X DEFLECTION + -55 │ADI X DEFLECTION - -56 │SPARE -57 │ADI Y DEFLECTION + -58 │ADI Y DEFLECTION - -59 │SPARE -60 │HSI X DEFLECTION + -61 │HSI X DEFLECTION - -62 │SPARE -63 │HSI Y DEFLECTION + -64 │HSI Y DEFLECTION - -65 SPARE -66SPARE -67SPARE -68SPARE -69SPARE -70SPARE -71SPARE -72SPARE -73SPARE -74SPARE 190J1A-75






(I) MANUAL TRIM DN 190J1A-76 (22)---------------- PLT ACFT TRIM SW,(I) MANUAL TRIM UP -77 (22)---------------- FIG. 6-19

MANUAL TRIM ENABLE -78SPARE DIS IN 28/OPEN P3 -79RESERVED -80RESERVED -81

(I) AILERON POSITION POT 1(H) -82 (22)-T-S--------S--AILERON POSN SENSOR(I) AILERON POSITION POT 1(W) -83 (22)-T-S--------S--FIG. 6-20(I) AILERON POSITION REF -84 (22)---│--------│--


(I) ELEVATOR POSITION POT 1(H) -85(I) ELEVATOR POSITION POT 1(W) -86(I) ELEVATOR POSITION REF -87

RESERVED -88RESERVED -89RESERVED -90

RESERVED -91RESERVED -92RESERVED -93RESERVED -94

RESERVED FOR PRI ADF BRG -95SIM COMRESERVED FOR PRI ADF BRG SIN -96RESERVED FOR PRI ADF BRG X -97RESERVED FOR PRI ADF BRG Y -98RESERVED FOR PRI ADF BRG COS -99RESERVED FOR PRI ADF BRG Z -100RESERVED FOR PRI ADF BRG -101COS COM

-102RESERVED -103

-104 -105

RESERVED 190J1A-106






RESERVED FOR PRI DME 190J1B-1DME CLK +RESERVED FOR PRIMARY -2DME DATA +RESERVED FOR PRIMARY -3DME COMMONRESERVED FOR PRIMARY -4DME ENABLERESERVED FOR PRIMARY DME HOLD -5RESERVED FOR SEC DME CLK + -6RESERVED FOR SEC DME DATA + -7RESERVED FOR SEC DME COMMON -8RESERVED FOR SEC DME ENABLE -9RESERVED FOR SEC DME HOLD -10RESERVED FOR PS + IN -11RESERVED FOR PS = IN -12RESERVED ANALOG IN -13

(I) +28 VDC INPUT N2 OVERRIDE -14 (24)---------------- MAINT SWITCHRESERVED -15RESERVED -16RESERVED -17RESERVED -18RESERVED -19RESERVED -20

(I) LAMP TEST IN -21 (24)---------------- FIG. 6-8(I) HDG PB IN -22 (24)---------------- 11J1-11,

C190J1B-22-23

(I) NAV PB IN -24 (24)---------------- 11J1-13,C190J1B-24

(I) APPROACH PB IN -25 (24)---------------- 11J1-14,C190J1B-25

(I) ALT PB IN -26 (24)---------------- 11J1-15,C190J1B-26

(I) SPD PB IN -27 (24)---------------- 11J1-16,C190J1B-27

(I) FLC PB IN -28 (24)---------------- 11J1-17,C190J1B-28

(I) GA IN -29 (24)---------------- FIG. 6-18

(I) VS PB IN -30 (24)---------------- 11J1-19,C190J1B-30

SPARE -31RESERVED FOR BARO SET 190J1B-32INPUT (WIPER)






SPARE 190J1B-33(O) EICAS DISPLAYED ON RMU -34 (24)---------------- 144J1-w(O) MASTER CAUTION LAMP OUTPUT -35 (24)---------------- FIG. 6-33(O) LMP DRVR OUT 3 FD1 ON -36 (24)---------------- 11J1-33(O) LMP DRVR OUT 4 FLC -37 (24)---------------- 11J1-32,

C190J1B-37RESERVED -38RESERVED -39RESERVED SPARE DIS G/0 -40SPARE DIS IN 28/0 P7 -41SPARE AN DC -42SPARE AN DC -43

(I) MASTER WARNING INPUT FROM AWC -44 (24)---------------- AURAL WARNINGCOMP, (FIG. 6-33)

(I) SPARE DIS IN 28/0 P6 -45 (RESERVED FOR JOYSTICK INPUT - RIGHT)RESERVED FOR SEC SRN LATERAL -46DEV +RESERVED FOR SEC SRN LATERAL -47DEV -

(I) FD 1 ON PB -48 (24)---------------- 11J1-7RESERVED FOR SPARE DIS IN -4928/0 P9RESERVED FOR SEC GS DEV + -50RESERVED FOR SEC GS DEV - -51RESERVED FOR ROT/YAW RATE -525 V VALIDRESERVED FOR ROT/YAW RATE + -53RESERVED FOR ROT/YAW RATE - -54RESERVED FOR COMPASS SYNC + -55RESERVED FOR COMPASS SYNC - -56RESERVED FOR INNER MARKER -57BEC +RESERVED FOR INNER MARKER -58BEC -RESERVED FOR MIDDLE MARKER + -59RESERVED FOR MIDDLE MARKER - -60RESERVED FOR OUTER MARKER + -61RESERVED FOR OUTER MARKER - -62RESERVED -63RESERVED -64TRIM POSN SENSOR 1 (H) -65 (24)-T-S---------S-- HSCU LEFTTRIM POSN SENSOR 1 (L) -66 (24)-T-S---------S-- SURFACE POSN

SHIELD GND ──────┘ └── SHIELD GNDTRIM POSN SENSOR 2 (H) -67 (24)-T-S---------S-- HSCU RIGHTTRIM POSN SENSOR 2 (L) -68 (24)-T-S---------S-- SURFACE POSN

SHIELD GND ──────┘ └── SHIELD GNDRESERVED -69RESERVED 190J1B-70






RESERVED 190J1B-71RESERVED -72RESERVED -73RESERVED -74RESERVED -75

(I) SPARE DIS IN 28/O P11 -76 (RESERVED FOR JOYSTICK INPUT - UP)(I) SPARE DIS IN 28/O P1 -77 (RESERVED FOR JOYSTICK INPUT - DOWN)(I) STALL WARNING 28 VDC DISCRETE -78 (24)---------------- STALL PROTECTION

COMPUTER(I) SPARE DIS IN 28/0 P5 -79 (RESERVED FOR JOYSTICK INPUT - LEFT)

RESERVED FOR SEC AC REF + -80RESERVED FOR SEC AC REF - -81

RESERVED FOR SEC PITCH X -82RESERVED FOR SEC PITCH Y -83RESERVED FOR SEC PITCH Z -84

RESERVED FOR SEC ROLL X -85RESERVED FOR SEC ROLL Y -86RESERVED FOR SEC ROLL Z -87

RESERVED FOR SEC HDG X -88RESERVED FOR SEC HDG Y -89RESERVED FOR SEC HDG Z -90

RESERVED -91RESERVED -92RESERVED -93SPARE -94

RESERVED FOR SEC ADF BRG -95SIN COMRESERVED FOR SEC ADF BRG SIN -96RESERVED FOR SEC ADF BRG X -97RESERVED FOR SEC ADF BRG Y -98RESERVED FOR SEC ADF BRG COS -99RESERVED FOR SEC ADF BRG Z -100RESERVED FOR SEC ADF BRG -101COS COMRESERVED -102RESERVED -103RESERVED -104RESERVED -105RESERVED 190J1B-106






(P) DGC +28 V DC POWER 190J2A-1 (20)----------------- FIG. 6-1(P) DGC +28 V DC POWER -2 (20)----------------- FIG. 6-1(P) DGC +28 V DC POWER -3 (20)----------------- FIG. 6-1(P) DGC DC POWER GND -4 (20)----------------- DC PWR GND(P) DGC DC POWER GND -5 (20)----------------- DC PWR GND(P) DGC DC POWER GND -6 (20)----------------- DC PWR GND(P) PRI CPU LAMP RETURN -7 (20)----------------- DC PWR GND(I) DGC SIGNAL GND -8 (22)----------------- SIGNAL GND(I) DGC SIGNAL GND -9 (22)----------------- SIGNAL GND

-10 V REF OUT -11(O) 10 V RTN (DH REFERENCE) -10 (24)-T-S---------S-- 115J1-55(O) +10 V REF OUT (DH REFERENCE) -12 (24)-T-S---------S-- 115J1-53(I) DECISION HEIGHT INPUT WIPER -13 (24)-T-S---------S-- 115J1-54


SPARE -14(B) PRIMARY DC-550 + -15 (24)-T-S---------S-- 115J1-34(B) PRIMARY DC-550 - -16 (24)-T-S---------S-- 115J1-35


(B) WX CONTROL BUS (H) -17 (24)-T-S---------S-- 59J1-m(B) WX CONTROL BUS (L) -18 (24)-T-S---------S-- 59J1-n


(B) PRIMARY RSB (H) -19 (24)-T-S---------S-- FIG. 6-21(B) PRIMARY RSB (L) -20 (24)-T-S---------S-- FIG. 6-21


(B) ARINC 429 CH 0 IN (H) LRNA -21 (24)-T-S---------S-- FMS (H),│ │ C190J2A-21

(B) ARINC 429 CH 0 IN (L) LRNA -22 (24)-T-S---------S-- FMS (L),│ │ C190J2A-22


(B) ARINC 429 CH 2 IN (H) -23 (24)-T-S---------S-- MAINTENANCE(B) ARINC 429 CH 2 IN (L) -24 (24)-T-S---------S-- COMPUTER


RESERVED -25(B) ARINC 429 CH 12 IN (L) -26 (24)-T-S---------S-- RESERVED

│ │ (TS WITH 190J2A-40)SHIELD GND ───────────┘ └── SHIELD GND

RESERVED -27RESERVED 190J2A-28






(B) ARINC 429 CH 4 IN (H) 190J2A-29 (24)-T-S---------S-- 1J1B-G7, FIG.(PRI AHRS) │ │ 6-10

(B) ARINC 429 CH 4 IN (L) -30 (24)-T-S---------S-- 1J1B-G8 (PRI AHRS) SHIELD GND ───────────┘ └── SHIELD GND

(B) ARINC 429 CH 6 IN (H) -31 (24)-T-S---------S-- FIG.(B) ARINC 429 CH 6 IN (L) -32 (24)-T-S---------S-- 6-12

(DAU 2 CH B) SHIELD GND ───────────┘ └── SHIELD GND

(B) AP ARINC 429 CH 0 IN (H) (AHRS)-33 (24)-T-S---------S-- FIG. 6-10(B) AP ARINC 429 CH 0 IN (L) (AHRS)-34 (24)-T-S---------S-- SHIELD GND ───────────┘ └── SHIELD GND

(B) AP ARINC 429 CH 1 IN (H) (MADC)-35 (24)-T-S---------S-- FIG. 6-11(B) AP ARINC 429 CH 1 IN (L) (MADC)-36 (24)-T-S---------S-- SHIELD GND ───────────┘ └── SHIELD GND

(B) ARINC 429 OUTPUT TO DAU (H) -37 (24)-T-S---------S-- FIG. 6-12(B) ARINC 429 OUTPUT TO DAU (L) -38 (24)-T-S---------S-- SHIELD GND ───────────┘ └── SHIELD GND

(B) 429 LRN OUT (HI) -39 (24)-T-S------------ FMS ARINC IN 1(H) TS W\ 52

(B) ARINC 429 CH 12 IN (H) -40 (24)-T-S---------S-- PROVISION (TSWITH 190J2A-26)


(DAU 2 CH A) SHIELD GND ───────────┘ └── SHIELD GND

(B) ARINC 429 CH 10 IN (H) -43 (24)-T-S---------S-- (SEC MADC) │ │ FIG. 6-11

(B) ARINC 429 CH 10 IN (L) -44 (24)-T-S---------S-- (SEC MADC) SHIELD GND ───────────┘ └── SHIELD GND

(B) DU HDLC INPUT2 BUS (H) -45 (24)-T-S---------S-- FIG.(B) DU HDLC INPUT2 BUS (L) -46 (24)-T-S---------S-- 6-13

DU HDLC INPUT2 BUS (T) -47 │ │SHIELD GND ───────────┘ └── SHIELD GND

RESERVED -48(I) RADAR ALT 28 V VALID 190J2A-49 (24)---------------- 20J1-Y,193RMP-2K,

193RBP-3C,C190J2A-49






(I) RADAR ALT + 190J2A-51 (24)-T-S---------S-- 20J1-W, C190J2A-51(I) RADAR ALT - -50 (24)-T-S---------S-- 20J1-N, 193RMP-2J,

│ │ 193RBP-3B,│ │ C190J2A-50


(B) 429 LRN OUT (LO) -52 (24)-T-S---------S-- FMS ARINC IN 1│ │ (L) TS W\ 39

SHIELD GND ───────────┘ └── SHIELD GNDRESERVED -53

(I) LEFT SIDE SELECT -54 (24)---------------- SIGNAL GND(O) AP XMIT (H) -55 -(O) AP XMIT (L) -56 -(B) DGC-DGC/FTSU BUS (H) -57 (24)-T-S---------S-- TEST CONNECTOR,

│ │ C190J2A-57(B) DGC-DGC/FTSU BUS (L) -58 (24)-T-S---------S-- TEST CONNECTOR,

│ │ C190J2A-58,│ │ (FIG. 6-34)


SPARE DISC IN PB P3 -59SPARE FLAP SELECTION -60LANDING GEAR CMD DISCRETE -61 (24)---------------- LANDING GEAR LOGICSPEED BRAKES DEPLOYED -62 (24)---------------- SPEED BRAKECROSS-SIDE SG REV -63 (24)---------------- FIG. 6-9

(I) WEIGHT ON WHEELS (WOW) -64 (24)---------------- FIG. 6-2RESERVED -65

(I) SYS CONFIG IDENT 1 -66 (24)---------------- GND FOR DISPLAYIN METRIC UNITS

(I) SYS CONFIG IDENT 2 -67(I) SYS CONFIG IDENT 3 -68 (24)---------------- GND IF FMS

INSTALLED(I) SYS CONFIG IDENT 4 -69 (24)---------------- GND IF DUAL ADF

INSTALLED(I) SYS CONFIG IDENT 5 -70 (24)---------------- GND FOR CROSS-

POINTER FD CMD(I) SYS CONFIG IDENT 6 -71 (24)--------------- GND TO ENABLE

CATII LOGIC(I) A/C TYPE IDENT 1 -72 (24)--------------- SIGNAL GND

A/C TYPE IDENT 2 -73(I) A/C TYPE IDENT 3 -74 (24)--------------- SIGNAL GND

A/C TYPE IDENT 4 -75A/C TYPE IDENT 5 -76BENCH TEST IDENT 1 -77BENCH TEST IDENT 2 190J2A-78






BENCH TEST IDENT 3 190J2A-79BENCH TEST IDENT 4 -80




(SEC AHRS) SHIELD GND ───────────┘ └── SHIELD GNDRESERVED -85RESERVED -86RESERVED -87RESERVED -88RESERVED -89DIN GROUND OUTPUT -90

(B) RS232 SERIAL DATA OUT -91 (24)----------------(B) RS232 SERIAL DATA IN -92 (24)---------------- FIG. 6-34(B) RS232 SERIAL DATA GND -93 (24)----------------(O) ALT ALERT HORN OUT -94 (24)---------------- AUDIO WARNING SYS(O) DECISION HEIGHT WARN OUT -95 (24)---------------- AUDIO WARNING SYS(O) MASTER COMP MON OUT (RESERVED)-96(O) TEST OUT (RAD ALT) -97 (24)---------------- 20J1-T,C190J2A-97(O) BANK ANNUNC OUT -98 (24)---------------- 11J1-27,

C190J2A-98(O) COUPLE ANNUNC OUT -99 (24)---------------- 11J1-25

RESERVED ANNUNC OUT -100(O) VS MODE ANNUNC OUT -101 (24)--------------- 11J1-34,

C190J2A-101(O) IAS MODE ANNUNC OUT -102 (24)--------------- 11J1-31,

C190J2A-102(O) ALT MODE ANNUNC OUT -103 (24)--------------- 11J1-30,

C190J2A-103(O) APR MODE ANNUNC OUT -104 (24)--------------- 11J1-29,

C190J2A-104(O) NAV MODE ANNUNC OUT -105 (24)--------------- 11J1-28,

C190J2A-105(O) HDG MODE ANNUNC OUT 190J2A-106 (24)--------------- 11J1-26,

C190J2A-106






(P) SERVO + 28 V POWER 190J2B-1 (20)-----------------(P) SERVO + 28 V POWER -2 (20)----------------- FIG. 6-1(P) SERVO + 28 V POWER -3 (20)-----------------(P) SERVO + 28 V POWER -4 (20)-----------------

RESERVED -5(P) SERVO DC POWER GND -6 (20)----------------- DC PWR GND(P) SERVO DC POWER GND -7 (20)----------------- DC PWR GND(P) SERVO DC POWER GND -8 (20)----------------- DC PWR GND(P) SERVO DC POWER GND -9 (20)----------------- DC PWR GND

(B) HDLC OUT + (DU) -10 (24)-T-S---------S-- FIG.- -11 (24)-T-S---------S-- 6-13


RESERVED ARINC 429 OUTPUT (H) -12(B) ARINC 429 CH 13 IN (H) -13 (24)-T-S---------S-- WINDSHEAR COM-

(WINDSHEAR) PUTER, C190J2B-13(TS WITH190J2B-26)

(B) HDLC IN #1 (H) -14 (24)-T-S---------S-- FIG.(B) HDLC IN #1 (L) -15 (24)-T-S---------S-- 6-13




(O) MASTER CAUTION TO AWC -18 (24)---------------- AURAL WARNINGCOMP, FIG. 6-33

(O) MASTER WARNING TO AWC -19 (24)---------------- AURAL WARNINGCOMP, FIG. 6-33

(O) MASTER WARNING LAMP -20 (24)---------------- FIG. 6-33RESERVED -21RESERVED -22

(B) ARINC 429 CH 3 IN (H) -23 (24)-T-S---------S-- 9J1-60, FIG.(PRI MADC) │ │ 6-11

(B) ARINC 429 CH 3 IN (L) -24 (24)-T-S---------S-- 9J1-61, (PRI MADC) SHIELD GND ───────────┘ └── SHIELD GND

RESERVED ARINC 429 OUTPUT (L) -25(B) ARINC 429 CH 13 IN (L) 190J2B-26 (24)-T-S---------S-- WINDSHEAR COM-

(WINDSHEAR) │ │ PUTER, C190J2B-26│ │ (TS WITH│ │ 190J2B-13)







(B) ARINC 429 CH 15 IN (H) 190J2B-27 (24)-T-S---------S-- (PFD) │ │ FIG. 6-13

(B) ARINC 429 CH 15 IN (L) (PFD) -28 (24)-T-S---------S-- SHIELD GND ───────────┘ └── SHIELD GND

(B) ARINC 429 CH 5 IN (H) (TCAS) -29 (24)-T-S---------S-- 193RMP-7C(B) ARINC 429 CH 5 IN (L) (TCAS) -30 (24)-T-S---------S-- 193RMP-7D,




RESERVED ARINC 429 OUT (H) -33RESERVED ARINC 429 OUT (L) -34

ALT ALERT ANNUNC OUT -35(I) PRIMARY AC REF + -36(I) PRIMARY AC REF - -37

RESERVED -38RESERVED -39RESERVED -40RESERVED -41RESERVED -42RESERVED -43RESERVED -44

SECONDARY TRIM UP -45 (24)---------------- SECONDARY TRIMUP SWITCH

-46-47

(I) SG 1 REVERSION -48 (24)---------------- FIG. 6-9SECONDARY TRIM DN -49 (24)---------------- SECONDARY TRIM

DOWN SWITCHRESERVED -50

(I) AP LAMP RETURN 190J2B-51 (22)---------------- DC PWR GND






RESERVED 190J2B-52(B) SECONDARY RSB (H) -53 (24)-T-S---------S-- FIG. 6-21(B) SECONDARY RSB (L) -54 (24)-T-S---------S-- FIG. 6-21


(I) COUPLE PB INPUT -55 (24)---------------- 11J1-10,C190J2B-55

(I) BANK PB INPUT -56 (24)---------------- 11J1-12,C190J2B-56

SPARE DISC IN PB P1 -57SPARE DISC IN PB P2 -58

(O) +15 V EXTERNAL OUT -59 (24)--------------- 129J1-C, 11J1-21,FIG. 6-20

(O) -15 V EXTERNAL OUT -60 (24)--------------- 129J1-A, FIG. 6-2015 V RETURN -61 (24)--------------- FIG. 6-20RESERVED FOR LAT ACCEL INPUT -62RESERVED FOR LAT ACCEL TEST -63OUTRESERVED FOR NORMAL ACCEL -64INPUTRESERVED FOR LONGT ACCEL INPUT-65

(I) MAN TRIM UP -66 (24)---------------- CPLT ACFT TRIM SW,(I) MAN TRIM DN -67 (24)---------------- FIG. 6-19(I) PITCH WHEEL IN + -68 (24)-T-S---------S-- 129J1-U(I) PITCH WHEEL IN - -69 (24)-T-S---------S-- 129J1-V


(I) TCS 28 V INPUT -70 (24)---------------- FIG. 6-17RESERVED -71SPARE -72

(I) TURN KNOB INPUT -73 (24)---------------- 129J1-BSPARE -74

(I) TURN KNOB OUT OF DETENT -75 (24)---------------- 129J1-H,C190J2B-75

(I) AP DISCONNECT 28 V IN -76 (22)---------------- FIG. 6-16(O) MOMENTARY HORN DISABLE -77 (22)---------------- 115J1-44(O) YD OFF ANNUNC OUT -78 (22)---------------- FIG. 6-15(O) LIGHT AND HORN DISABLE -79 (22)---------------- 115J1-42,

115J1-43TRIM WARN ANNUNC OUT -80 ------NCTRIM UP ANNUNC OUT -81IN/HPA OUT -82 (22)---------------- 9J1-16

(I) YD ENGAGE SELECT PB IN -83 (22)---------------- 11J1-9(O) YD ENGAGE ANNUNC OUT -84 (22)---------------- 11J1-24(I) AP ENGAGE SEL PB IN -85 (22)---------------- 11J1-8(O) AP ENGAGE ANNUNC OUT -86 (22)---------------- 11J1-23(O) 28 V YD CLUTCH 190J2B-87 (22)---------------- 14J1-F






(O) 28 V AP CLUTCH 190J2B-88 (22)---------------- 12J1-F115J1-27,

(O) 28 V AP CLUTCH -89 (22)---------------- 13J1-F, HSCU

(I) AP DISCONNECT 28 VIN -90 (20)---------------- FIG. 6-16(I) MASTER CAUTION INPUT FROM AWC -91 (24)---------------- AURAL WARNING

COMP, FIG. 6-33

(O) PITCH TRIM OUT + -92 (22)-T-S---------S-- HSCU RETRACT(O) PITCH TRIM OUT - -93 (22)-T-S---------S-- HSCU EXTEND

SHIELD GND ──────┘ └── SHIELD GND(I) RIGHT SIDE SELECT IN -94(I) RUDDER SERVO TACH FB IN + -95 (24)-T-S---------S-- 14J1-N(I) RUDDER SERVO TACH FB IN - -96 (24)-T-S---------S-- 14J1-L


(O) RUDDER SERVO OUT (H) -97 (18)-T-S---------S-- 14J1-B(O) RUDDER SERVO OUT (L) -98 (18)-T-S---------S-- 14J1-A


(I) AILERON SERVO TACH FB IN + -99 (24)-T-S--------S-- 12J1-L(I) AILERON SERVO TACH FB IN - -100 (24)-T-S--------S-- 12J1-N


(O) AILERON SERVO OUT (H) -101 (18)-T-S--------S-- 12J1-A(O) AILERON SERVO OUT (L) -102 (18)-T-S--------S-- 12J1-B


(I) ELEVATOR SERVO TACH FB IN + -103 (24)-T-S--------S-- 13J1-L(I) ELEVATOR SERVO TACH FB IN - -104 (24)-T-S--------S-- 13J1-N


(O) ELEVATOR SERVO OUT (H) -105 (18)-T-S--------S-- 13J1-A(O) ELEVATOR SERVO OUT (L) 190J2B-106 (18)-T-S--------S-- 13J1-B





TCAS COMPUTERRT-910


SPARE 193RMP-1ASPARE -1BSPARE -1CSPARE -1DTA ENABLE -1E

(O) CORRECT AURAL ADVISE -1F (24)---------------- TO AUDIO SYSSPARE -1GSPARE -1HCLIMB INHIB 1 -1J

(O) PREVENT AURAL ADVISE 193RMP-1K (24)---------------- TO AUDIO SYS

(O) TRAFFIC AURAL ADVISE 193RMP-2A (24)---------------- TO AUDIO SYSSPARE -2BSPARE -2CADVISORY COMMON -2DSPARE -2E

(O) 8 OHM AUDIO H -2F (24)----------------- TO TCAS(O) L -2G (24)----------------- SPEAKER(I) ANALOG RAD ALT 1 H -2H (24)--T-S---------S-- 20J1-X, 193RBP-3A(I) L -2J (24)--T-S---------S-- 20J1-N, 193RBP-3B,

│ │ 190J2A-50,│ │ C190J2A-50

SHIELD GND ────┘ └── SHIELD GND

(I) ANALOG RAD ALT 1 VALID 193RMP-2K (24)----------------- 20J1-Y, 193RBP-3C,190J2A-49,C190J2A-49

CORRECT VISUAL ADVISE 193RMP-3APREVENT VISUAL ADVISE -3BTRAFFIC VISUAL ADVISE -3CADVISORY ANN CANCEL -3DSPARE -3E600 OHM AUDIO H -3F (24)--T-S---------S-- AURAL WARNING

L -3G (24)--T-S---------S-- UNITSHIELD GND ────┘ └── SHIELD GND

SPARE -3HSPARE -3JSPARE 193RMP-3K

PITCH ATTITUDE X 193RMP-4AY -4BZ -4C

ATTUTUDE SHIELDS -4DROLL ATTITUDE X -4E

Y 193RMP-4F




TCAS COMPUTER (CONT)RT-910


Z 193RMP-4G26 VAC ATT REF H -4H

L -4JATTITUDE VALID 193RMP-4K

MAG HDG X 193RMP-5AY -5BZ -5C

SPARE -5DSPARE -5ESPARE -5FSPARE -5G26 VAC VAC REF H -5H

L -5J(I) AIR GROUND 193RMP-5K (24)------------------ TO WOW SWITCH,

FIG. 6-2

(B) FMS 429 BUS A 193RMP-6A(B) (LO SPD) B -6B

MAG HDG VALID -6CFMS PERFORM LIMIT -6DMAX ALT LIM PRG #1 -6E

#2 -6F#3 -6G#4 -6H#5 -6J

PRG COMMON 193RMP-6K

PITCH ATT 429 BUS A 193RMP-7AB -7B

(B) TA/RA DISP 1 429 A -7C (24)-T-S-----------S-- 190J2B-29,B -7D (24)-T-S-----------S-- 190J2B-30,SHIELD GND ───────┘ └── SHIELD GND

(I) TA DISP 1 STATUS -7E (24)------------------ SIGNAL GNDSPARE -7FTA/RA DISP 2 429 A -7G (24)-T-S-----------S-- C190J2B-29

B -7H (24)-T-S-----------S-- C190J2B-30SHIELD GND ──────┘ └── SHIELD GND

(I) TA DISP 2 STATUS -7J (24)------------------ SIGNAL GNDSPARE 193RMP-7K






DATA LOADXMIT 429 BUS A 193RMP-8A

B -8BSPARE 429 IN BUS A -8C

B -8DSPARE 429 IN BUS A -8E

B -8FSPARE 429 IN BUS A -8G

B -8HSPARE 429 IN BUS A -8J

B 193RMP-8K

DATA LOADRCVR 429 BUS A 193RMP-9A

B -9BSPARE 429 OUT BUS A -9C

B -9DSPARE 429 OUT BUS A -9E

B -9FSPARE 429 OUT BUS A -9G

B -9HSPARE 429 OUT BUS A -9J

B 193RMP-9KSPARE 193RMP-10ASPARE -10BSPARE -10CSPARE -10DSPARE -10ESPARE -10FSPARE -10GSPARE -10HSPARE -10JSPARE 193RMP-10K

SPARE 193RMP-11ASPARE -11BSPARE -11CSPARE -11DSPARE -11ESPARE -11FSPARE 193RMP-11G






SPARE 193RMP-11HSPARE -11JSPARE 193RMP-11K

SPARE 193RMP-12AANALOG RAD ALT SELECT -12BTA/RA BLK XFER PRG -12C (24)----------------- SIGNAL GNDSPARE -12DSPARE -12ESPARE -12FSPARE -12GSPARE -12HSPARE -12JSPARE 193RMP-12K

RA DISP 1429 OUT BUS A 193RMP-13A

B -13BRA DISP 2429 OUT BUS A -13C

B -13D(I) RA DISP 2 STATUS -13E (24)----------------- SIGNAL GND(I) LAND GEAR UP/DN -13F (24)----------------- LANDING GEAR SYS

(GND=GEAR DN)CLIMB INHIB 2 -13GRAD ALT 1 429 BUS A -13H

B -13J(O) TCAS VAILD -13K

(B) TX COORD 2 429 BUS A 193RMP-14A (24)-T-S----------S-- C143J1-90(B) B -14B (24)-T-S----------S-- C143J1-104


(I) RA DISP 1 STATUS -14C (24)----------------- SIGNAL GNDSPARE 429 IN BUS A -14D

B -14E(B) XT COORD 1 429 BUS A -14F (24)-T-S----------S-- 143J1-55(B) B -14G (24)-T-S----------S-- 143J1-87


(B) XT COORD 2 429 BUS A -14H (24)-T-S----------S-- C143J1-55(B) B -14J (24)-T-S----------S-- C143J1-87


SPARE 193RMP-14K






SPARE 193RMP-15ASPARE -15BSPARE -15CSPARE -15DSPARE -15ESPARE -15FSPARE -15GSPARE -15H

(B) TX COORD 1 429 BUS A -15J (24)-T-S----------S-- 143J1-90(B) B 193RMP-15K (24)-T-S----------S-- 143J1-104


SPARE 193RBP-1ASPARE -1BSPARE -1CSPARE -1DSPARE -1ESPARE -1FSPARE -1G

(O) FLIGHT RECORDER #1 BIT 18 -1H(O) #2 BIT 19 -1J(O) #3 BIT 20 193RBP-1J

SPARE 193RBP-2ASPARE -2BSPARE -2CSPARE -2DSPARE -2ESPARE -2FSPARE -2G


(I) ANALOG RAD ALT 2 H 193RBP-3A (24)-T-S----------S-- 20J1-X, 193RMP-2H(I) L -3B (24)-T-S----------S-- 20J1-N, 193RMP-2J,

│ │ 190J2A-50,│ │ C190J2A-50


(I) ANALOG RAD ALT 2 VALID 193RBP-3C (24)----------------- 20J1-Y, 193RMP-2K,190J2A-49,C190J2A-49






RADIO ALTIMETER#2 429 H 193RBP-3D

L -3ESPARE -3FSPARE -3G


SPARE 193RBP-4ASPARE -4BSPARE -4CSPARE -4DSPARE -4ESPARE -4FRA SELF TEST INH -4G (24)----------------- SIGNAL GND

(O) FLIGHT RECORDER #10 BIT 24 -4H(O) #11 BIT 25 -4J(O) #12 BIT 26 193RBP-4K

ADVISORY INH #1 193RBP-5A#2 -5B#3 -5C#4 -5D

INCREASE CLIMB INH #1 -5E#2 -5F#3 -5G#4 -5H

CLIMB INHIB 3 -5JCLIMB INHIB 4 193RBP-5K

DATA LOADER LINK A-B 193RBP-6ALATA LOADER #2 -6BSPARE -6CDATA LOADER #4 -6DCMC/CFDIU 429 OUT A -6E

B -6FCMC/CFDIU 429 IN A -6G

B -6HSPARE -6JSPARE 193RBP-6K






AUDIO OUTPUT LEVEL #1 193RBP-7A TBD BY EMBRAER#2 -7B DURING INSTALLATION#3 -7C DESIGN

AUDIO TONE ENABLE -7DGND DISPLAY PROG -7EDISPLAY ALL TRAFFIC -7FANTENNA CABLE DELAY #1 -7G

#2 -7H#3 -7J

PROGRAM COMMON 193RBP-7K

SPARE 193RBP-8ASPARE -8BSPARE -8CSPARE -8DFUNC TEST INH -8ETA/RASYM LIM PROG #1 -8F

#2 -8G#3 -8H#4 -8J#5 193RBP-8K

FACTORY TEST 193RBP-9AFACTORY TEST -9BFACTORY TEST -9CFACTORY TEST -9DFACTORY TEST -9EFACTORY TEST -9FFACTORY TEST -9GFACTORY TEST -9HFACTORY TEST -9JALS FLT TEST DATA 193RBP-9KRECRD

ALS FLT TEST DATA 193RBP-10ARECRDALS FLT TEST DATA RECRD -10BALS FLT TEST DATA RECRD -10CALS FLT TEST DATA RECRD -10DALS FLT TEST DATA RECRD -10EALS FLT TEST DATA RECRD -10FALS FLT TEST DATA RECRD -10GALS FLT TEST DATA RECRD -10HALS FLT TEST DATA RECRD -10JFACTORY TEST 193RBP-10K






(I) TOP ANTENNA 0 DEG 193LTP- 1 (COAX)--------------- 194J1(I) TOP ANTENNA 270 DEG - 2 (COAX)--------------- 194J2(I) TOP ANTENNA 180 DEG - 3 (COAX)--------------- 194J3(I) TOP ANTENNA 90 DEG93LTP - 4 (COAX)--------------- 194J4

(I) BOT ANTENNA 0 DEG 193LMP- 1 (COAX)--------------- 195J1(I) BOT ANTENNA 90 DEG - 2 (COAX)--------------- 195J2(I) BOT ANTENNA 180 DEG - 3 (COAX)--------------- 195J3(I) BOT ANTENNA 270 DEG193LMP - 4 (COAX)--------------- 195J4

(I) 115 VAC 400 HZ PWR H 193LBP- 1 (20)----------------- 115 VAC PWRL - 7 (12)----------------- 115 VAC PWR

SPARE - 228 VDC H -10

L - 3SPARE - 4

(O) FAN POWER OUTPUT H - 5 (22)----------------- TO COOLING FAN(O) (115 VAC) L - 9 (22)----------------- TO COOLING FAN

SPARE - 6(O) SIGNAL GND - 8 (12)----------------- SIGNAL GND(O) CHASSIS GND -11 (22)----------------- CHASSIS GND(I) MUTUAL SUPP PULSE IN -12 (24)----------------- FIG. 6-31

MUTUAL SUPP PULSE OUT 193LBP-13




ATTITUDE AND HEADING REFERENCE UNIT NO. 2AH-800


(B) ASCB ONSIDE DATA (H) C1J1A-C10(B) ASCB ONSIDE DATA (L) -C13

(I) SHOP MAINTENANCE -E1(I) RESERVED -E2(I) RESERVED -E3

(B) ASCB SIDE DATA (H) -F10(B) ASCB SIDE DATA (L) -F13

(B) MEM ACCESS DATA (TX) -H3 ---------------------(B) MEM ACCESS DATA (RX) -H4 --------------------- FIG. 6-34(B) MEM ACCESS COM -H7 ---------------------(B) MEM ACCESS MODE SEL -H10 (24)-----------------

(B) ASCB BU DATA (H) -K3(B) ASCB BU DATA (L) C1J1A-K5




ATTITUDE AND HEADING REFERENCE UNIT NO. 2AH-800 (cont)


(O) PROGRAM PIN COMMON C1J1B-A1

(I) LAMP TEST (RESERVED) -A7(I) RESERVED -A8(I) RESERVED -A9(I) TEST COMMAND (RESERVED) -A10 (24)------------------- TEST SWITCH,

FIG. 6-3(O) SERIAL DATA OUT (H) -B6(O) SERIAL DATA OUT (L) -B7

(I) SERIAL DATA IN (H) -B10(I) SERIAL DATA IN (L) -B11

(O) AHRS FAIL ANNUNCIATOR-D2

(O) BASIC MODE ANNUNCIATOR(RSVD) -D3

(O) DISCRETE COMMON -D7 -

(O) OVERTEMP WARN ANNUNCIATOR(RSVD) -E1

(O) SLAVING FAIL ANNUNCIATOR(RSVD) -E2

(O) DG MODE ANNUNCIATOR (RSVD) -E3

(O) ARINC 429 OUT #2 (H) -E5 (24)-T-S------------S-- FIG.(O) ARINC 429 OUT #2 (L) -E6 (24)-T-S------------S-- 6-10


(O) MAG HDG SYNCHRO (X) (RSVD) -E10(O) MAG HDG SYNCHRO (Y) (RSVD) -E11(O) MAG HDG SYNCHRO (Z) (RSVD) -E12

(O) ALIGN ANNUNCIATOR(RSVD) -F3

(I) MEMORY MODULE INHIBIT -F6 (24)------------------ MEM MODULE (ORN)(I) MEMORY MODULE POWER -F7 (24)------------------ MEM MODULE (RED)(I) MEMORY MODULE RETURN -F8 (24)------------------ MEM MODULE (BLK)(I) MEMORY MODULE CLOCK C1J1B-F9 (24)------------------ MEM MODULE (YEL)






(I) MEMORY MODULE DATA C1J1B-F11 (24)------------------ MEM MODULE (BRN)(I) MAG HDG 26 V 400 HZ REF

(RSVD) -F13

(O) ARINC 429 OUT 4 (H) -F14(O) ARINC 429 OUT 4 (L) -F15

(O) AHRS VALID (RSVD) -G1(O) MAG HDG VALID (RSVD) -G2

(O) ARINC 429 OUT 1 (H) -G7 (24)-T-S-----------S-- FIG.(O) ARINC 429 OUT 1 (L) -G8 (24)-T-S-----------S-- 6-10


(I) 26 V 400 HZ RET (RSVD) -G13

(I) HEADING SLEW COM -H1 (24)-----------------(I) HEADING SLEW 0 -H2 (24)----------------- FIG. 6-4(I) HEADING SLEW 1 -H3 (24)-----------------(I) HEADING SLEW 2 -H4(I) HEADING SLEW 3 -H5

(I) DG MODE SELECT -H6 (24)----------------- INSTRUMENT PANEL,FIG. 6-4

(I) FLUX VALVE INPUT A -H8 (22)-T-S----------S-- C4J1-A(I) FLUX VALVE INPUT B -H9 (22)-T-S----------S-- C4J1-B(I) FLUX VALVE INPUT C -H10 (22)-T-S----------S-- C4J1-C(I) FLUX VALVE COMMON F -H11 (22)-T-S----------S-- C4J1-F

SHIELD GND ───────────┘ └── NC

(O) FLUX VALVE EXCITATION D -H12 (22)-T-S-----------S-- C4J1-D(O) FLUX VALVE EXCITATION E -H13 (22)-T-S-----------S-- C4J1-E

SHIELD GND ───────────┘ └── NC

(O) ARINC 429 IN #2 (H) -J10(O) ARINC 429 IN #2 (L) -J11(O) AUX POWER ANNUNCIATOR

(RSVD) C1J1B-J15






(I) ARINC 429 #1 IN (H) C1J1B-K4 (24)-T-S----------S-- FIG.(I) ARINC 429 #1 IN (L) -K5 (24)-T-S----------S-- 6-11


(0) ARINC 429 #3 OUT (H) -K12 (24)-T-S----------S-- FIG.(0) ARINC 429 #3 OUT (L) -K13 (24)-T-S----------S-- 6-10


(I) WOW C1J1B-K15 (24)-----------------FIG. 6-2






(I) 28 V DC AUXILIARY C1J1C-2 (22)------------------ FIG. 6-1

(O) CONTROLLER 28 V DC PWR -6

(I) 28 V DC PRIMARY -7 (22)------------------ FIG. 6-1

(O) 28 V DC RETURN -8 (22)------------------ DC PWR GND

(I) CHASSIS GND C1J1C-11




FLUX VALVE NO. 2FX-600


(O) STATOR A C4J1-A (22)-T-S-----------S-- C1J1B-H8(O) STATOR B -B (22)-T-S-----------S-- C1J1B-H9(O) STATOR C -C (22)-T-S-----------S-- C1J1B-H10(O) STATOR COMMON F -F (22)-T-S-----------S-- C1J1B-H11

NC ──────────┘ └── SHIELD GND

(I) EXCITATION D -D (22)-T-S-----------S-- C1J1B-H12(I) EXCITATION E -E (22)-T-S-----------S-- C1J1B-H13

NC ──────────┘ └── SHIELD GND




COPILOT’S MADCAZ-850


UNIT ID 1 C9J1-1UNIT ID 2 -2

(I) UNIT ID 3 -3 (24)------------------ SIGNAL GROUNDUNIT ID 4 -4

(I) UNIT ID 5 -5 (24)------------------ SIGNAL GROUNDUNIT ID 6 -6UNIT ID 7 -7SDI 1 -8

(I) SDI 2 -9 (24)------------------ SIGNAL GROUNDSDI 3 -10SPARE -11

(I) WEIGHT-ON-WHEELS -12 (24)------------------ FIG. 6-2(I) SIGNAL GROUND -13 (24)------------------ SIGNAL GROUND

SPARE -14(I) TAT PROBE HEAT DISCRETE -15 (24)------------------ TAT PROBE HEAT

SIGNAL(I) BARO SET DISCRETE (IN/HPA) -16 (24)------------------ C190J2B-82

SPARE IN #3 GND -17SPARE IN #4 GND -18

(I) SPARE IN #1 +28 V -19 ---------------------- RESERVED FORALT. VMO SIGNAL

SPARE IN #2 +28 V -20(O) DISCRETE OUT #1(170 KTS) -21 (24)------------------ RUDDER TRIM

SYSTEM(O) DISCRETE OUT #2(205 KTS) -22 (24)------------------ SPOILER COMMAND(O) DISCRETE OUT #3(24,500 FT) -23 (24)------------------ SYSTEM(O) DISCRETE OUT #4(TBD KTS) -24(O) ALTITUDE TRIP POINT(TBD FT)-25(P) +28 V DC HI -26 (22)------------------ FIG. 6-1(P) +28 V DC LO -27 (22)------------------ DC GROUND

OVERSPEED WARNING DISC -28 (24)------------------ CREW ALERTING SYSTEMMADC VALID DISC -29

ASCB ON SIDE PRIMARY HI -30

(I) TEMP PROBE HI -31 (24)-T-S-----------S-- 500 OHM TEMP PROBE(I) TEMP PROBE LO -32 (24)-T-S-----------S-- 500 OHM TEMP PROBE


SPARE -33ASCB ON SIDE PRIMARY C9J1-34LO




COPILOT’S MADC (cont)AZ-850


AOA HI C9J1-35AOA ARM -36AOA LO -37CALIBRATION ENABLE -38 ---------------------- SHOP USE ONLYSPARE -39SPARE -40SPARE -41

(I) ATC ENABLE DISC -42(O) ATC A1 -43(O) ATC A2 -44(O) ATC A4 -45(O) ATC B1 -46(O) ATC B2 -47(O) ATC B4 -48(O) ATC C1 -49(O) ATC C2 -50(O) ATC C4 -51(O) ATC D4 -52

SPARE -53SPARE -54

(B) RS-232 RX IN HI -55 (24)-T-S-----------S--(B) RS-232 LO -56 (24)-T-S-----------S-- FIG. 6-34(B) RS-232 TX OUT HI -57 (24)-T-S-----------S--


VMO SELECT -58ASCB ON SIDE BACKUP HI -59

(B) ARINC 429 BUS 1 HI -60 (24)-T-S-----------S-- FIG.(B) ARINC 429 BUS 1 LO -61 (24)-T-S-----------S-- 6-11

SHIELD GND ──────────┘ └─ SHIELD GND

(B) ARINC 429 BUS 2 HI -63 (24)-T-S-----------S- FIG.(B) ARINC 429 BUS 2 LO C9J1-64 (24)-T-S-----------S- 6-11





COPILOT’S MADC (cont)AZ-850


ASCB CROSS SIDE C9J1-65 -PRIMARY HI

(B) ARINC 429 BUS 3 HI -66 (24)-T-S----------S-- FIG.(B) ARINC 429 BUS 3 LO -67 (24)-T-S----------S-- 6-11


(B) ARINC 429 BUS 4 HI -68 (24)-T-S----------S-- FIG.(B) ARINC 429 BUS 4 LO -69 (24)-T-S----------S-- 6-11


(I) FUNCTIONAL TEST DISC -70 (24)----------------- FIG. 6-3(I) BARO SELECT DISC (STD) -71 (24)----------------- C130J1-46

SSEC DISABLE(GND=DISABLE) -72SPARE -73 --------------------- SHOP USE ONLY

(I) BARO-CORRECTION A (H) -74 (24)----------------- C130J1-21(I) BARO-CORRECTION B (L) -75 (24)----------------- C130J1-25

SPARE -76ASCB CROSS SIDE PRIMARY LO -77

SPARE -78SPARE C9J1-79




COPILOT’S DISPLAY CONTROLLERDC-550


(I) SIGNAL GND C115J1-1 (22)------------------- SIGNAL GNDLGHTG 28 V (H) -2

(P) LGHTG 5 V (H) -3 (22)------------------- FIG. 6-7(P) LGNTG COM -4 (22)------------------- LIGHTING GND(P) +28 V DC POWER -5 (22)------------------- FIG. 6-1(P) DC POWER GND -6 (22)------------------- DC PWR GND(I) #8 PUSH BUTN (DU4 BZ PB1) -7 (24)------------------- C131J1-46(I) #9 PUSH BUTN (DU4 BZ PB2) -8 (24)------------------- C131J1-47(I) #1 SET KNOB 1 -9 (24)--T-S-----------S-- 11J1-56(I) #1 SET KNOB 2 CRS2 -10 (24)-T-S-----------S-- 11J1-57(I) #1 SET KNOB COM -11 (24)-T-S-----------S-- 11J1-58


(I) #2 SET KNOB 1 -12 (24)-T-S-----------S-- 11J1-47,115J1-12(I) #2 SET KNOB 2 HDG -13 (24)-T-S-----------S-- 11J1-48,115J1-13(I) #2 SET KNOB COM -14 (24)-T-S-----------S-- 11J1-49,115J1-14


(I) #3 SET KNOB 1 -15 (24)-T-S-----------S-- 11J1-50,115J1-15(I) #3 SET KNOB 2 ALT -16 (24)-T-S-----------S-- 11J1-51,115J1-16(I) #3 SET KNOB COM -17 (24)-T-S-----------S-- 11J1-52,115J1-17


(I) #4 SET KNOB 1 -18 -----T-S-----------S-- 11J1-53,115J1-18(I) #4 SET KNOB 2 SPD -19 -----T-S-----------S-- 11J1-54,115J1-19(I) #4 SET KNOB 2 COM -20 -----T-S-----------S-- 11J1-55,115J1-20


(I) #5 SET KNOB 1 -21 -----T-S-----------S-- C131J1-21(I) #5 SET KNOB 2 MFD -22 -----T-S-----------S-- C131J1-25(I) #5 SET KNOB COM -23 -----T-S-----------S-- C131J1-63


(I) #6 SET KNOB 1 -24 -----T-S-----------S-- 115J1-24, 132J1-21(I) #6 SET KNOB 2 EICAS -25 -----T-S-----------S-- 115J1-25, 132J1-25(I) #6 SET KNOB COM -26 -----T-S-----------S-- 115J1-26, 132J1-63


RESERVED -27SPARE C115J1-28




COPILOT’S DISPLAY CONTROLLER (cont)DC-550


AUTOPILOT OFF LIGHT C115J1-29AUTOPILOT OFF HORN -30SPARE -31

(I) TCS -32 ---------------------- FIG. 6-17(I) 28V AUTOPILOT DISCONNECT -33 ---------------------- FIG. 6-16(B) DC/SG BUS (H) -34 (24)-T-S-----------S-- C190J2A-15(B) DC/SG BUS (L) -35 (24)-T-S-----------S-- C190J2A-16


DC/MG BUS (H) -36DC/MG BUS (L) -37PFD #2 DIM (H) -38PFD #2 DIM (L) -39

MFD #2 DIM (H) -40MFD #2 DIM (L) -41

(I) LIGHT + HORN DISABLE -42 (22)------------------ C115J1-43,C190J2B-79

(I) MOMENTARY LIGHT DISABLE -43 (22)------------------ C115J1-42,C190J2B-79

(I) MOMENTARY HORN DISABLE -44 (22)------------------ C190J2B-77(I) CHASSIS GND -45 (22)------------------ CHASSIS GND(I) LAMP TEST GND -46(I) #10 PUSH BUTTN (DU4 BZ PB3) -47 (24)------------------ C131J1-50(I) #11 PUSH BUTTN (DU4 BZ PB4) -48 (24)------------------ C131J1-51(I) #12 PUSH BUTTN (DU4 BZ PB5) -49 (24)------------------ C131J1-60

PFD DIM (H) -50PFD DIM (W) -51PFD DIM (L) -52

(I) DH SET (H) -53 (24)-T-S-----------S-- C190J2A-12(O) DH SET (W) -54 (24)-T-S-----------S-- C190J2A-13(I) DH SET (L) -55 (24)-T-S-----------S-- C190J2A-10

SHIELD GND ──────┘ └── SHIELD GND(I) #13 PUSH BUTTN (DU4 BZ PB6) -56 (24)------------------ C131J1-62

#14 PUSH BUTTN -57#15 PUSH BUTTN -58ADI ON GND -59

(I) MASTER CAUTION PUSH BUTTON -60 (24)------------------ FIG. 6-33(I) MASTER WARNING PUSH BUTTON -61 (24)------------------ FIG. 6-33

#18 PUSH BUTTN -62HSI ON GND C115J1-63




COPILOT DISPLAY CONTROLLER (cont)DC-550


#19 PUSH BUTTN C115J1-64#20 PUSH BUTTN -65#21 PUSH BUTTN (IN/HPA) -66 (24)------------------ C130J1-47WX ON GND -67

(I) #22 PUSH BUTTN (SPD IAS -68 (24)------------------ 11J1-65, 115J1-68MACH SEL)

#23 PUSH BUTTN (RESERVED) -69(I) #24 PUSH BUTTN (PUSH SYNC -70 (24)------------------ 11J1-66

CRS 2)(I) #25 PUSH BUTTN (PUSH SYNC -71 (24)------------------ 11J1-63, 115J1-71

HDG)(I) #1 SWITCH (DU # 2 MFD -72 (24)------------------ FIG. 6-9

SELECT)(I) #2 SWITCH (AHRS REVERSION) -73 (24)------------------ FIG. 6-10(I) #3 SWITCH (MADC REVERSION) -74 (24)------------------ FIG. 6-11(I) #4 SWITCH (DAU CH A -75 (24)------------------

(REVERSION) FIG. 6-12(I) #5 SWITCH (DAU CH B -76 (24)------------------

(REVERSION)(I) #6 SWITCH (DU #4 PFD SELECT)-77 (24)------------------(I) #7 SWITCH (DU #4 EICAS -78 (24)------------------FIG. 6-9

SELECT) (I) #8 SWITCH (DU #2 C115J1-79 (24)------------------

EICAS SEL)




COPILOT’S PFDDISPLAY UNIT NO. 5

DU-870


(I) (H) C130J1-1 (22)-T-S-----------S-- AIRCRAFTBRIGHTNESS POT (W) -14 (22)-T-S-----------S-- DIMMING

(I) (L) -13 (22)-T-S-----------S-- CONTROLNC ─────────┘ └── SHIELD GND



BUS 3 (H) -19(L) -20

(O) SET KNOB (BARO) (A) -21 (24)------------------ C9J1-74(I) DU PWR DN* -22 (24)------------------ FIG. 6-9(P) 5 V LIGHTING (H) -23 (22)------------------ FIG. 6-7(P) 5 V LIGHTING COMMON -24 (22)------------------ LIGHTING COMMON(O) SET KNOB (BARO) (B) -25 (24)------------------ C9J1-75

REMOTE LT SENSOR (H) -26REMOTE LT SENSOR (L) -27

(O) DLS OUT (H) -28 (24)-T-S-----------S-- C131J1-29(O) (L) -41 (24)-T-S-----------S-- C131J1-42


(I) ALS (H) -29 (24)-T-S-----------S-- C131J1-28(I) (L) -42 (24)-T-S-----------S-- C131J1-41


RESERVED -30HDLC OUT + -31HDLC OUT - C130J1-32




COPILOT’S PFDDISPLAY UNIT NO. 5 (cont)

DU-870


BUS 3 TERM (L) C130J1-33RESERVED -34

(B) BUS 2 (H) -35 (24)-T-S-----------S-- FIG.(B) BUS 2 (L) -36 (24)-T-S-----------S-- 6-13


DU VALID (GND/OPEN) -37(B) BUS 1 (H) -38 (24)-T-S-----------S-- FIG.(B) BUS 1 (L) -39 (24)-T-S-----------S-- 6-13




(O) PB STANDARD DISCRETE -46 (24)------------------ C9J1-71PB IN/HPA -47 (24)------------------ C115J1-66RESERVED -48BUS 2 TERM (L) -49PB -50PB -51BUS 1 TERM (L) -52RESERVED -55RESERVED C130J1-56





DU-870


RESERVED C130J1-57BUS 4 (H) -58BUS 4 (L) -59

(O) PB -60WX BUS 2 TERM (L) -61DH (H) -62DH (COM) -63 (22)------------------ SIGNAL GND

(B) WX BUS 1 TERM (L) -64 (24)-T-S-----------S-- FIG.(B) WX BUS 1 (H) -77 (24)-T-S-----------S-- 6-6


DU OVERTEMP (GND/OPEN) -65(B) DU WRAPAROUND (H) -66 (24)-T-S-----------S--

(ARINC 429) │ │ FIG. 6-13(B) DU WRAPAROUND (L) -79 (24)-T-S-----------S--

(ARINC 429) │ │SHIELD GND ──────────┘ └── SHIELD GND

DH (L) -67RESERVED -68WX BUS 3 (H) -69WX BUS 3 (L) -70RESERVED -71SPARE -72SPARE -73WX BUS 2 (H) -74WX BUS 2 (L) -75SPARE -76WX BUS 1 (L) -78 (24)------------------ FIG. 6-6

(I) SIGNAL GROUND -80 (24)------------------ SIGNAL GNDRESERVED -81RESERVED -82WX BUS 3 TERM (L) -83RESERVED -84SPARE -85SPARE -86

(I) PORT SEL 3 C130J1-87 (24)------------------ FIG. 6-9





DU-870


PORT SEL 2 C130J1-88PORT SEL 1 -89

(I) I.D. #3 -90 (24)------------------ FIG. 6-9I.D. #2 -91

(I) I.D. #1 -92 (24)------------------ FIG. 6-9RESERVED -93CHASSIS GND -94RESERVED -95RESERVED -96RESERVED -97RESERVED -98SOFTWARE ENABLE* -99SOFTWARE ENABLE* -100


(P) 28 V DC RTN -104 (22)----------------- A/C 28 V DC(P) 28 V DC RTN -105 (22)----------------- PWR RETURN(P) 28 V DC RTN C130J1-106 (22)-----------------

* FLIGHT TEST ONLY




COPILOT’S MFDDISPLAY UNIT NO. 4

DU-870


(I) (H) C131J1-1 (22)-T-S-----------S-- AIRCRAFTBRIGHTNESS POT (W) -14 (22)-T-S-----------S-- DIMMING

(I) (L) -13 (22)-T-S-----------S-- CONTROLNC ─────────┘ └── SHIELD GND



BUS 3 (H) -19(L) -20

(O) SET KNOB #5 (MFD) (H) -21 (24)----------------- C115J1-21DU PWR DN*

(P) 28 V LIGHTING (H) -23 (22)----------------- FIG. 6-8(P) 28 V LIGHTING COMMON -24 (22)----------------- LIGHTING COMMON(O) SET KNOB #5 (MFD) (L) -25 (24)----------------- C115J1-22

REMOTE LT SENSOR (H) -26

REMOTE LT SENSOR (L) -27(O) DLS OUT (H) -28 (24)-T-S-----------S-- C130J1-29(O) (L) -41 (24)-T-S-----------S-- C130J1-42


(I) ALS (H) -29 (24)-T-S-----------S-- C130J1-28(I) (L) C131J1 -42 (24)-T-S-----------S-- C130J1-41





COPILOT’S MFDDISPLAY UNIT NO. 4 (cont)

DU-870


RESERVED C131J1-30(B) HDLC OUT + -31 (24)-T-S-----------S-- FIG.(B) HDLC OUT - -32 (24)-T-S-----------S-- 6-13


BUS 3 TERM (L) -33RESERVED -34



DU VALID (GND/OPEN) -37





(O) PB -46 (24)------------------ C115J1-7(O) PB -47 (24)------------------ C115J1-8

RESERVED C131J1-48





DU-870


BUS 2 TERM (L) C131J1-49(O) PB -50 (24)------------------ C115J1-47(O) PB 2 -51 (24)------------------ C115J1-48

BUS 1 TERM (L) -52RESERVED -55RESERVED -56RESERVED -57BUS 4 (H) -58BUS 4 (L) -59

(O) PB -60 (24)------------------ C115J1-49WX BUS 2 TERM (L) -61PB -62 (24)------------------ C115J1-56

(O) MFD BEZEL/SET KNOB #5 COMMON-63 (24)------------------ C115J1-23WX BUS 1 TERM (L) -64DU OVERTEMP (GND/OPEN) -65DU WRAPAROUND (H) -66(ARINC 429)DU WRAPAROUND (L) -79(ARINC 429)

RESERVED -67RESERVED -68WX BUS 3 (H) -69WX BUS 3 (L) -70RESERVED -71SPARE -72SPARE -73WX BUS 2 (H) -74WX BUS 2 (L) -75SPARE -76

(B) WX BUS RIGHT (H) -77 (24)-T-S-----------S-- FIG.(B) WX BUS RIGHT (L) -78 (24)-T-S-----------S-- 6-6


(I) SIGNAL GROUND -80 (24)------------------ SIGNAL GNDRESERVED -81RESERVED -82WX BUS 3 TERM (L) -83

(O) PB6 -84





DU-870


SPARE C131J1-85SPARE -86

(I) PORT SEL 3 -87 (24)------------------ FIG. 6-9PORT SEL 2 -88PORT SEL 1 -89

(I) I.D. #3 -90 (24)------------------ FIG. 6-9I.D. #2 -91

(I) I.D. #1 -92 (24)------------------ FIG. 6-9RESERVED -93CHASSIS GND -94RESERVED -95RESERVED -96RESERVED -97RESERVED -98SOFTWARE ENABLE* -99SOFTWARE ENABLE* -100


(P) 28 V DC RTN -104 (22)-----------------A/C 28 V DC(P) 28 V DC RTN -105 (22)-----------------PWR RETURN(P) 28 V DC RTN C131J1-106 (22)-----------------

*FLIGHT TEST ONLY




COPILOT’S COMMUNICATIONS UNIT NO. 2RCZ-851G/851E


RESERVED C143J1-1

(GND/OPEN)(O) +28 V DC FAN POWER -2 (24)------------------ COOLING FAN - RED

(P) +28 V DC COMM 2 POWER -4 (22)------------------(P) +28 V DC COMM 2 POWER -5 (22)------------------FIG. 6-1(P) +28 V DC COMM 2 POWER -6 (22)------------------

(P) +28 V XPDR 2 POWER RETURN -7 (22)------------------ DC POWER GND

(P) +28 V DC XPDR 2 POWER -8 (22)------------------FIG. 6-1(P) +28 V DC XPDR 2 POWER -9 (22)------------------

(B) RSB PRIMARY (H) -10 -T-S---------------S--FIG. 6-21(B) RSB PRIMARY (L) -11 -T-S---------------S--SHIELD GND ──────┘ └── SHIELD GND

(B) SELCAL/ACARS (L) -12(B) SELCAL/ACARS (H) -22

RESERVED -13

(O) COM +28V ACH PWR -14

(B) RCB RCVR (#1) (L) -15(B) RCB RCVR (#1) (H) -28

(O) COMM STRAP +5 V DC -16 (24)------------------ FIG. 6-22

(P) +28 V DC COMM POWER RETURN -17 (22)------------------(P) +28 V DC COMM POWER RETURN -18 (22)------------------DC POWER GND(P) +28 V DC COMM POWER RETURN -19 (22)------------------(P) +28 V DC XPDR POWER RETURN -20 (22)------------------

(I) VHF 2 PTT (GND/OPEN) -21 (24)------------------ FIG. 6-28

(I/O) SIMULCOM RET -24 (24)-T-S-----------S-- 143J1-24(I/O) SIMULCOM C143J1-35 (24)-T-S-----------S-- 143J1-35





COPILOT’S COMMUNICATIONS UNIT NO. 2 (cont)RCZ-851G/851E


(B) COM ACH DATA (L) C143J1-25 (24)-T-S-----------S-- 165J1-J(B) COM ACH DATA (H) -33 (24)-T-S-----------S-- 165J1-H


RESERVED -26RESERVED -27

(O) EMER AUDIO (L) -29 (24)-T-S-----------S-- FIG.(O) EMER AUDIO (H) -31 (24)-T-S-----------S-- 6-29


(O) REC PHONE AUDIO (H) -30

(I) AUX AUD 4 (L) -34(I) AUX AUD 4 (H) -62


(I) HF COM XMIT (GND/OPEN) -37 (24)------------------ HF PTT

(I) AUX AUD 2 (H) -38(I) AUX AUD 2 (L) -49

(I) HF COM DISABLE (GND/OPEN) -39(I) GND (AUDIO SHIELDS) -40(I) COM +28V ACH RTN -41(I) AUDIO BUS SHIELD (GND) -42

(O) COM STRAP +5 V DC RETURN -43 (24)------------------ COMM 2 STRAP CAAFIG. 6-22

(I) GND -44 (24)------------------(I) GND -45 (24)------------------ BOBBIN(I) GND -46 (24)------------------


(I) HF1 COM AUD (L) -50 (24)-T-S-----------S-- HF(I) HF1 COM AUD (H) -66 (24)-T-S-----------S-- AUDIO


(I) AUX AUD 3 (L) -51(I) AUX AUD 3 (H) C143J1-52




COPILOT’S COMMUNICATIONS UNIT NO. 2 (cont)RCZ-851G/851E


(B) RCB RCVR (#2) (L) C143J1-53(B) RCB RCVR (#2) (H) -68

(O) +28 V DC FAN POWER RETURN -54 (24)------------------ COOLING FAN-BLUE(B) XPDR TO TCAS 429A -55 (24)-T-S-----------S-- 193RMP-14H(B) XPDR TO TCAS 429B -87 (24)-T-S-----------S-- 193RMP-14J


(B) AUDIO BUS #2 (H) -56 -T-S---------------S-- FIG. 6-23(B) AUDIO BUS #2 (L) -70 -T-S---------------S--SHIELD GND ──────┘ └── SHIELD GND

(O) SIDETONE PHONE AUDIO (H) -57

(I) GND -58 (24)------------------ BOBBIN(O) AGC ANALOG TP -59(I) GND -60 (24)------------------ BOBBIN

(B) LEFT SEC RSB (L) -61 -T-S---------------S-- FIG. 6-21(B) LEFT SEC RSB (H) -74 -T-S---------------S--SHIELD GND ──────┘ └── SHIELD GND

(I) CHASSIS GND -67 (24)------------------ BOBBIN


(I) AUDIO STATUS 1 (GND/OPEN) -76(I) ALT SRC SEL 2 (NO) -80 (24)------------------ FIG. 6-11

(B) RCB XMTR (#1) (H) -81(B) RCB XMTR (#1) (L) -95

(B) RCB XMTR (#2) (H) -82(B) RCB XMTR (#2) (L) -96

(I) WOW (GND/OPEN) C143J1-83 (24)------------------ FIG. 6-2




COPILOT’S COMMUNICATIONS UNIT NO. 2 (cont)RCZ-850/851E


RESERVED C143J1-84RESERVED -85

(O) COM STRAP CLK -88 (24)------------------ COMM 2 STRAP CCA(O) COM STRAP SIDE A0 -89 (24)------------------ FIG. 6-22

(B) TCAS TO XPDR 429A -90 (24)-T-S----------S-- 193RMP-14A(B) TCAS TO XPDR 429B -104 (24)-T-S----------S-- 193RMP-14B


(O) XPDR ACTIVE (NO) -91 (24)------------------ TO AIRCFT ANT.RELAY

(I) VHF 2 MIC (H) -92 (24)-T-S----------S-- FIG. 6-28(I) VHF 2 MIC (L) -106 (24)-T-S----------S--SHIELD GND ───────────┘ └── SHIELD GND

(I) COMM OFF (GND/OPEN) -93

(I/O) MUT SUP -94 (24)---S----------S-- FIG. 6-31SHIELD GND ───────────┘ └── SHIELD GND


(B) ADC 1 TO XPDR 429A -99 (24)-T-S-----------S-- FIG.(B) ADC 2 TO XPDR 429B -86 (24)-T-S-----------S-- 6-11


(B) ADC 2 TO XPDR 429A -100 (24)-T-S----------S-- FIG.(B) ADC 2 TO XPDR 429B -69 (24)-T-S----------S-- 6-11


(I) COM STRAP DATA -101 (24)----------------- COMM 2 STRAP CCA(O) COM STRAP LOAD -102 (24)----------------- FIG. 6-22(O) COM STRAP SIDE A1 -103 (24)-----------------

RESERVED -104RESERVED C143J1-105




COPILOT’S COMMUNICATIONS UNITRCZ-851G/851E


(I) TRANSPONDER ANTENNA C143J2-1 ---(RG-214/U)-S-------- BOTTOM XPDR ANT(BOTTOM) C143J2-2 ─────────────┘ (SEE NOTE BELOW)

(I) COM ANTENNA C143J3-1 ---(RG-142B/U)-S------- COM ANT #2C143J3-2 ─────────────┘

(I) TRANSPONDER ANTENNA C143J6-1 ---(RG-214/U)-S-------- TOP XPDR ANT(TOP) C143J6-2 ─────────────┘ (SEE NOTE BELOW)




COPILOT’SRADIO MANAGEMENT UNIT

RM-855


(P) 28 V DC LIGHTING C144J1-A(P) 28 V DC LIGHTING RET -B(P) +28 V DC POWER -C (22)------------------ FIG. 6-1(P) +28 V DC POWER RETURN -D (22)------------------ DC GND(B) NAV BACKUP BUS (+) -E (24)-T-S-----------S-- C164J1B-102(B) NAV BACKUP BUS (-) -F (24)-T-S-----------S-- C164J1A-84


(P) 5 V DC LIGHTING -G (24)-T-S-----------S-- FIG. 6-7(P) 5 V DC LIGHTING RETURN -H (24)-T-S-----------S-- LIGHTING GND


(P) 0-5 V AC LIGHTING -J(P) 0-5 V AC LIGHTING RET -K(I) CHASSIS GROUND -L (24)------------------ CHASSIS GND(B) RIGHT SEC RSB (H) -M -T-S---------------S-- FIG. 6-21(B) RIGHT SEC RSB (L) -N -T-S---------------S--


(I) WOW (GND/OPEN) -P (24)------------------ FIG. 6-2(I) WOW POLARITY (GND/OPEN) -R (24)------------------ SIG. GND

(GND FORWOW=GND)

(I) ATC IDENT (GND/OPEN) -S (24)------------------ TO ID SWITCHES,144J1-S

(I) DISCRETE 1 INPUT 4 -T

(I) CHASSIS GROUND -U (24)------------------ CHASSIS GND

(B) PRIMARY RSB (H) -V -T-S---------------S-- FIG. 6-21(B) PRIMARY RSB (L) -W -T-S---------------S--SHIELD GND ───────┘ └── SHIELD GND

(I) DISCRETE 1 INPUT 3 -X(I) ON/OFF PAGE DISABLE -Y (24)------------------ SIG. GND

(GND/OPEN)(I) DISCRETE 1 INPUT 1 -Z(I) DISCRETE 1 INPUT 0 -a

(I) SIDE SEL B0 (GND/OPEN) -b(I) SIDE SEL B1 (GND/OPEN) -c (24)------------------ SIG. GND(I) SIDE SEL EV PARITY C144J1-d

(GND/OPEN)




COPILOT’SRADIO MANAGEMENT UNIT (cont)

RM-855


(I) TEST ENABLE C144J1-e(GND/OPEN)

(I) COM FREQ XF (GND/OPEN) -f(I) COM MEM SEL (GND/OPEN) -g(I) MKR SENSE LEFT -h (24)------------------ 160J2-L, 144J1-h(I) MKR SENSE RIGHT -i (24)------------------ C160J2-L, 144J1-i(O) COM POWER OFF (GND/OPEN) -j(O) ATC POWER OFF (GND/OPEN) -k(O) VOR POWER OFF (GND/OPEN) -m(O) DME POWER OFF (GND/OPEN) -n(O) ADF POWER OFF (GND/OPEN) -p(O) MLS POWER OFF (GND/OPEN) -q(O) DISCRETE OUTPUT 1 -r(O) DISCRETE OUTPUT 0 -s(I) FMS BUS (-) -t (24)------------------ 121J1B-30, 144J1-t(I) ENG BACKUP FUNCTION ENABLE -u(I) NAV BACKUP FUNCTION ENABLE -v(I) ENG DISPLAY ENABLE #1 -w(I) ENG DISPLAY ENABLE #2 -x (24)------------------ SIGNAL GND

(I) ENG DISPLAY ENABLE #3 -y(I) DAU CONFIGURATION (2 DAU’S) -z(I) FMS BUS (+) -AA (24)----------------- 121J1B-31,144J1-AA(I) IAC CONFIGURATION 2 -BB

(B) ONSIDE DAU #1 (+) -CC (24)-T-S-----------S-- FIG.(B) ONSIDE DAU #1 (-) -DD (24)-T-S-----------S-- 6-14


(I) CHASSIS GROUND C144J1-EE





COPILOT’SRADIO MANAGEMENT UNIT (cont)

RM-855


(B) DAU #2 (+) C144J1-FF (24)-T-S-----------S-- FIG.(B) DAU #2 (-) -GG (24)-T-S-----------S-- 6-14


(I) SPARE -HH(B) ARINC DAU 3 (H) -JJ(B) ARINC DAU 3 (L) -KK(P) +28 V DC PRIMARY POWER -LL (22)------------------ FIG. 6-1(P) +28 V DC PRIMARY POWER RTN -MM (22)------------------ DC GND(I) SPARE -NN(I) SPARE C144J1-PP





#2 ADF ANTENNA (OPTION)


(I) ADF MOD SHLD C158J1-A

(I) ADF COS MOD -B (24)-T-S---------------- C164J1A-91(I) ADF SIN MOD -H (24)-T-S---------------- C164J1A-104

└─────┐(I) ADF ANT TEST -C (24)---------│---------- C164J1A-77

│(I) ADF OUTER SHLD -D │(O) ADF INNER SHLD -E ──────────┐ ├────────── SEE NOTE BELOW(O) ADF RF INPUT -F -(TRIAX)-IS-OS---------- C164J2-1

(P) ADF +15 VDC -G (24)-------------------- C164J1B-1(P) ADF +15 VDC RETURN -J (24)-------------------- C164J1B-27

(I) ADF LOOP EN C158J1-K (24)-------------------- C164J1A-101

NOTE: RECOMMENDED ADF ANTENNA TRIAXIAL CABLE IS TROMPETER PN TRC-50-2 OREQUIVALENT. THE TRIAXIAL CABLE OUTER SHIELD IS GROUNDED AT THE ADFANTENNA END ONLY, TO THE AIRFRAME AND TO THE ADF MODULATION SHIELD. THEGROUND WIRE SHALL BE 20 AWG OR LARGER AND THE LENGTH SHALL NOT EXCEED 10INCHES.




COPILOT’SAUDIO PANELAV-850A


(I) HAND MIC PTT C160J1-A (24)------------------ FIG. 6-25(GND/OPEN)

(O) EMERGENCY COM PTT -B (24)------------------ FIG. 6-28(GND/OPEN)




SHIELD GROUND ───────────┘ └──│ SHIELD GND(O) VHF 1 PTT (GND/OPEN) -F (24)------------------

(I) EMER COM AUDIO (H) -G (24)-T-S-----------S-- FIG. 6-29(I) EMER COM/NAV AUDIO (L) ┌─-m (24)-T-S-----------S--SHIELD GROUND│ ──────────┘ └── SHIELD GND

│(I) EMER NAV AUDIO (H) │ -f (24)-T-S-----------S-- FIG. 6-29(I) EMER COM/NAV AUDIO (L) └─-m (24)-T-S-----------S--


(O) EMER COM MIC (L) -H (24)-T-S-----------S-- FIG. 6-28(O) EMER COM MIC (H) -P (24)-T-S-----------S--SHIELD GROUND ───────────┘ └── SHIELD GND

(I) HAND MIC/MASK-BOOM MIC (L) -J (24)-T-S-----------S-- FIG. 6-25(I) HAND MIC (H) -K (24)-T-S-----------S--SHIELD GROUND ──────────┘ └── SHIELD GND

(O) CABIN/COCKPIT SPKR (L) ┌-L (22)-T-S-----------S-- NO. 2 COCKPIT(O) COCKPIT SPKR (H) │-Y (22)-T-S-----------S-- SPEAKER

SHIELD GROUND │ ─────────┘ └── SHIELD GND│

(O) CABIN/COCKPIT SPKR (L) └-L (22)-T-S-----------S-- CABIN(O) CABIN SPKR (H) -e (22)-T-S-----------S-- SPEAKER


(P) +28 V DC PWR RTN C160J1-M (22)------------------ DC GND




COPILOT’SAUDIO PANEL

AV-850A (cont)


(I) COMMON GND C160J1-N

(I) HF MIC (L) -S (24)-T-S-----------S-- HF(I) HF MIC (H) -T (24)-T-S-----------S-- MIC


(P) +28 V DC POWER -U (22)------------------ FIG. 6-1(P) +28 V DC POWER -V (22)------------------

(I) HF PTT -X (24)------------------ HF PTT

(I) COM 3 MIC (L) -Z (24)-T-S-----------S-- COM 3(I) COM 3 MIC (H) -a (24)-T-S-----------S-- MIC


(I) COM 3 PTT (GND/OPEN) -b (24)------------------ COM 3 PTT

(B) DIG AUDIO BUS 2 (+) -c (24)-T-S-----------S-- FIG. 6-23(B) DIG AUDIO BUS 2 (-) -n (24)-T-S-----------S--SHIELD GND ────────┘ └─── SHIELD GND

(B) DIG AUDIO BUS 1 (+) -d (24)-T-S-----------S-- FIG. 6-23(B) DIG AUDIO BUS 1 (-) -p (24)-T-S-----------S--SHIELD GND ────────┘ └─── SHIELD GND





(I/O) INTERPHONE AUDIO (L) -j (24)-T-S-----------S-- 160J1-j, E160J1-j(I/O) INTERPHONE AUDIO (H) -s (24)-T-S-----------S-- 160J1-s, E160J1-s


(O) PHONE AUDIO (L) -k (24)-T-S-----------S-- FIG. 6-25(O) PHONE AUDIO (H) -t (24)-T-S-----------S--SHIELD GND ─────────┘ └─── SHIELD GND

(P) +28 V DC DIMMING C160J1-r





AV-850A (cont)


(I) WARNING 5 AUDIO (H) C160J2-A(I) WARNING 5 AUDIO (L) -a

(I) WARNING 1 AUDIO (L) -B (24)-T-S-----------S-- AURAL WARNING(I) WARNING 1 AUDIO (H) -W (24)-T-S-----------S-- UNIT


(I) MASK MIC (H) -E (24)------------------ FIG. 6-25(I) MASK/BOOM MIC (L) -C

(I) COMMON GND -D (24)------------------ FIG. 6-25


(I) CABIN DISABLE (GND/OPEN) -H

(I) WARNING 3 AUDIO (L) -J(I) WARNING 3 AUDIO (H) -m

(I) SPARE -NRESERVED -K

(O) MARKER BEAC 1 HI/LO SENS -L (24)------------------ 144J1-i, C144J1-i(O) STERO MUTE (GND/OPEN) -M

SPARE -N

(O) MAINT PHONE AUDIO (L) -P(O) MAINT PHONE AUDIO (H) -f

(I) MAINT MIC 2 PTT -R

(I) AUXILIARY PTT -S(I) AUXILIARY MIC LO -T(I) AUXILIARY MIC HI C160J2-s





AV-850A (cont)


(I) PA MIC LO C160J2-U (24)-T-S-------------S-- PA SYSTEM,(I) PA MIC HI -i (24)-T-S-------------S-- FIG. 6-30


(O) VOICE RECORDER HI -V (24)-T-S-------------S-- COCKPIT VOICE(O) VOICE RECORDER LO -r (24)-T-S-------------S-- RECORDER


(I) BOOM MIC HI -Y (24)-------------------- FIG. 6-25(I) SPARE GND -C



(O) INT XMIT -c (24)-------------------- 160J2-c, E160J2-cSPARE -d

(I) MAINT 1 MIC (LO) -e(I) MAINT 1 MIC (HI) -q

(I) MAINT 2 MIC H -g(I) MAINT 2 MIC L -n

RESERVED -h

(I) PA PTT -j (24)-------------------- PA SYSTEM,FIG. 6-30

(I) MAINT 1 MIC PTT -k

(I) INTERPHONE PTT C160J2-p (24)-------------------- FIG. 6-25




COPILOT’S NAVIGATION UNITRNZ-851C


(O) DME HOLD NOT C164J1A-2(GND/OPEN)

(O) DME HOLD (GND/OPEN) -3(O) DME 568 DATA (H) -5(O) DME 568 DATA (L) -15(I) RESERVED -7(O) AUX1 RCB TX1 -8(O) AUX1 RCB TX2 -9(P) RESERVED -10(P) RESERVED -11(O) RESERVED -12

(I) VOR/ILS ON/OFF (GND/OPEN) -14

(O) DME RS-422 SD2 (L) -16(O) DME RS-422 SD2 (H) -54

(O) DME 568 CLK (L) -17(O) DME 568 CLK (H) -19

(O) DME CH 1 AUDIO -18(I) MLS RCB SHLD -20

(O) MLS 1 RCB XMTR (H) -21 (24)-T-S-----------S-- C164J1A-25(O) MLS 1 RCB XMTR (L) -34 (24)-T-S-----------S-- C164J1A-38


(O) RESERVED -22(P) RESERVED -23(I) CHANGE INHIBIT (GND/OPEN) -24

(I) MLS 1 RCB RCVR (H) -25 (24)-T-S-----------S-- C164J1A-21(I) MLS 1 RCB RCVR (L) -38 (24)-T-S-----------S-- C164J1A-34


(O) DME 568 SYNC (H) -26(O) DME 568 SYNC (L) -45

(O) DME MUT SUP RTN -28(O) RESERVED -33(I) RESERVED -39(I) DME ON/OFF C164J1A-40

(OPEN/GND)




COPILOT’S NAVIGATION UNITRNZ-851C (cont)


(I) AUX 1 AUDIO (H) C164J1A-41(I) AUX 1 AUDIO (L) -55

(I/O) DME MUT SUP -42 (24)---S----------S-- FIG. 6-31SHIELD GND ───────────┘ └── SHIELD GND

(O) DME RS-422 SD1 (L) -44 (24)-T-S----------S-- RESERVED FOR(O) DME RS-422 SD1 (H) -57 (24)-T-S----------S-- OPTIONAL FMS


(O) DME VALID (28 V/OPEN) -46(O) RESERVED -47(O) RESERVED -50(O) RESERVED -52

(I) NAV AUX DATA (L) -58 (24)-T-S----------S-- 165J1-N(I) NAV AUX DATA (H) -70 (24)-T-S----------S-- 165J1-M


(O) VOR/ILS RS-422 SD1 (L) -59 (24)-T-S----------S-- RESERVED FOR(O) VOR/ILS MKR LAMP (M) -60 OPTIONAL FMS

(28 V/OPEN) (SEE J1B-89)(O) RESERVED -61(O) AUX2 RCB TX1 -64(O) AUX2 RCB TX2 -65

(I) RESERVED -66(I) AUX 2 AUDIO (H) -67(I) AUX 2 AUDIO (L) -68

(O) NAV AUX CLK (H) -69 (24)-T-S----------S-- 165J1-f(O) NAV AUX CLK (L) -72 (24)-T-S----------S-- 165J1-P


(O) DME 40 MV/MI -71(O) VOR/ILS MKR LAMP (I) -73

(28 V/OPEN)(O) RESERVED -74(I) AUX1 RCB RX1 -75(O) ADF ANTENNA TEST -77 (24)------------------ C158J1-C (IF

(RNZ-851) 2ND ADF ISINSTALLED)

(I) AUX1 RCB RX2 -78(I) RESERVED C164J1A-79






(I) GND PS IN C164J1A-80(I) AUX GND -81

(P) DME 28 V DC RETURN -83 (22)---------------- DC PWR GND

RS-422 SD2 -84 (24)---------------- C144J1-F

(P) VOR/ILS +28 V DC POWER -85 (22)---------------- FIG. 6-1(P) DME +28 V DC POWER -86 (22)----------------(P) ADF +28 V DC POWER -87 (22)---------------- IF 2ND ADF IS

(RNZ-851) INSTALLED

(B) RIGHT SEC RSB (H) -88 (24)-T-S---------S-- FIG. 6-21(B) RIGHT SEC RSB (L) -102 (24)-T-S---------S--SHIELD GND ────────────┘ └─── SHIELD GND

(O) ADF COS MOD -91 (24)-T-S---------S-- C158J1-B(O) ADF SIN MOD -104 (24)-T-S---------S-- C158J1-H

(RNZ-851) │ │ (IF 2ND ADF│ │ IS INSTALLED)


(I) AUX2 RCB RX1 -92(I) AUX2 RCB RX2 -93

(P) ADF 28 V DC RETURN -94 (22)---------------- DC POWER GND(P) DME 28 V DC RETURN -95 (22)---------------- DC POWER GND

(I) CLU SHLD GND -96(O) DME CH 2 AUDIO (H) -97

(P) VOR/ILS +28 V DC POWER -98 (22)---------------- FIG.(P) DME +28 V DC POWER -99 (22)---------------- 6-1(P) ADF +28 V DC POWER -100 (22)---------------- IF 2ND ADF

(RNZ-851) IS INSTALLED

(O) ADF LOOP EN -101 (24)---------------- C158J1-K (IF 2ND(RNZ-851) ADF IS INSTALLED)

(I) CLUSTER GND -103 (22)---------------- DC POWER GND

(I) RESERVED C164J1A-105






(O) ADF +15 V DC C164J1B-1 (24)----------------- C158J1-G (IF 2ND(RNZ-851) ADF IS INSTALLED)

(O) 28 V DC FAN POWER -2 (24)----------------- COOLING FAN(RED)

(I) SPARE STAT IN (DIG AUD) -5(I) SPARE STAT IN (DIG AUD) -6(I) RESERVED -7(I) AUX +28 V DC -8(O) RESERVED -9(O) RESERVED -10(O) RESERVED -11(O) RESERVED -12(I) MLS MORSE ID RETURN -13(P) RESERVED -20

(O) VOR/ILS RNAV VIDEO (H) -21(O) VOR/ILS RNAV VIDEO (L) -22

(P) RESERVED -23

(O) CT -24(O) VOR/LOC AUDIO HI -36(O) LO -51

(P) ADF 28 V DC RETURN -25 (22)----------------- DC POWER GND(RNZ-851) (IF 2ND ADF

IS INSTALLED)

(O) NAV STRAP GND -26 (24)----------------- FIG. 6-22

(O) ADF +15 V DC RETURN -27 (24)----------------- C158J1-J (IF 2ND(RNZ-851) ADF IS INSTALLED)

(B) DIG AUDIO BUS 1 (L) -29 -T-S--------------S-- FIG. 6-23(B) DIG AUDIO BUS 1 (H) -42 -T-S--------------S-- SHIELD GND ───────┘ └─── SHIELD GND

(I) SPARE STAT IN (DIG AUD) -30(I) AUD AUX SQUELCH -31(I) MLS MORSE ID (H) -32(I) RESERVED -33(I) RESERVED -34(I) RESERVED C164J1B-35






(O) VOR/ILS EMER AUDIO (H)C164J1B-36 (24)-T-S-----------S-- FIG.(O) VOR/ILS EMER AUDIO (L) -51 (24)-T-S-----------S-- 6-29


(O) RESERVED -37

(P) VOR/ILS POWER RETURN -38 (22)----------------- DC POWER GND(P) VOR/ILS +28 V DC POWER -39 (22)----------------- FIG. 6-1

(O) NAV STRAP +5 V DC -40 (24)---------------- FIG. 6-22(O) FAN 28 V DC POWER RETURN -44 (24)---------------- COOLING FAN

(BLUE)

(I) AUDIO AUX XMT -45(I) RESERVED -47(I) RESERVED -48(O) RESERVED -49(P) VOR/ILS POWER RETURN -50 (22)---------------- DC POWER GND(P) VOR/ILS +28 V DC POWER -52 (22)---------------- FIG. 6-1(I) EFIS/MLS RIGHT -56(I) NAV STRAP SIDE SPARE -57 (24)----------------(I) NAV STRAP DATA -58 (24)---------------- FIG. 6-22(O) NAV STRAP CLK -59 (24)----------------(O) NAV STRAP WD LOAD -84 (24)----------------(O) RESERVED -60(O) RESERVED -61(I) RESERVED -62(O) RESERVED -63(O) ILS MODE -64(O) RESERVED -65(O) RESERVED -66(I) DIG AUDIO BUS SHLD -67(P) RESERVED -68(B) RSB PRIMARY (H) -71 -T-S-------------S-- FIG. 6-21(B) RSB PRIMARY (L) C164J1B-81 -T-S-------------S--







(O) RESERVED C164J1B-72

(O) RESERVED -73(O) RESERVED -100

(O) VOR/ILS MKR LAMP (O) -74(28 V/OPEN)

(O) RESERVED -75(O) RESERVED -76(O) RESERVED -77(O) RESERVED -78(O) RESERVED -79

(I) NAV STRAP SIDE SELECT -80 (24)---------------- FIG. 6-22

(I) SEC RSB BUS SHIELD -85

(I) RESERVED -87

(O) NAV AUX SHIFT LD (L) -88 (24)-T-S---------S-- 165J1-G(O) NAV AUX SHIFT LD (H) -90 (24)-T-S---------S-- 165J1-F

SHIELD GND ────────────┘ └─── SHIELD GND

(O) VOR RS-422 SD 1 (H) -89 (24)-T-S---------S-- RESERVED FOR(O) RESERVED -91 OPTIONAL FMS(O) RESERVED -92 (SEE J1A-59)(O) RESERVED -93(I) PRIMARY RSB BUS SHIELD -95(I) EFIS/MLS LEFT -96

(I) CLU GND -98 (22)---------------- DC POWER GND

(O) RESERVED -99(O) VOR/ILS RS-422 SD 2 (H) -102 (24)---------------- C144J1-E(O) RESERVED -103(O) RESERVED -104(O) RESERVED C164J1B-106




COPILOT’S NAVIGATION UNIT (cont)RNZ-851C


┌────── C158J1-E(I) ADF RF INPUT 1 C164J2-1 -(TRIAX)-IS-OS--IS-OS-- C158J1-F(I) ADF RF INPUT 2 C164J2-2 ──────────┘ └─── SHIELD GND

(IF 2ND ADF IS INSTALLED - RNZ-851)

(I) VOR/LOC ANT C164J3-1 ----S------------S----- VOR/LOC 2 ANTC164J3-2 ────┘ └───── SHIELD GND

(I) GS ANT C164J4-1 ----S------------S----- GS 2 ANTC164J4-2 ────┘ └───── SHIELD GND

(I) MKR BEAC ANT C164J5-1 ----S------------S----- MKR BEAC 2 ANTC164J5-2 ────┘ └───── SHIELD GND

(I) DME ANT C164J6-1 ----S------------S----- DME 2 ANT(RNZ-851) C164J6-2 ────┘ └───── SHIELD GND




COPILOT’S INTEGRATED AVIONICS COMPUTERIC-600


ADI VIDEO + C190J1A-1 ADI VIDEO - -2 SPARE -3 ADI COLOR 0 + -4 ADI COLOR 0 - -5 SPARE -6 ADI COLOR 1 + -7 ADI COLOR 1 - -8 SPARE -9 ADI COLOR 2 + -10 ADI COLOR 2 - -11 SPARE -12 ADI COLOR 3 + -13 ADI COLOR 3 - -14 SPARE -15 ADI FLYBACK + -16 ADI FLYBACK - -17 SPARE -18 RESERVEDADI PRIMARY TUBE VALID -19 ADI RASTER/STROKE + -20 ADI RASTER/STROKE - -21 SPARE -22 ADI PRIMARY STROKE READY + -23 ADI PRIMARY STROKE READY - -24 ADI SEC STROKE READY + -25 ADI SEC STROKE READY - -26 ADI SEC TUBE VALID -27 HSI VIDEO + -28 HSI VIDEO - -29 SPARE -30 HSI COLOR 0 + -31 HSI COLOR 0 - -32 SPARE -33 HSI COLOR 1 + -34 HSI COLOR 1 - -35 SPARE -36 HSI COLOR 2 + -37 HSI COLOR 2 - -38 SPARE C190J1A-39




COPILOT’S INTEGRATED AVIONICS COMPUTER (cont)IC-600


HSI COLOR 3 + C190J1A-40 HSI COLOR 3 - -41 SPARE -42 HSI FLYBACK + -43 HSI FLYBACK - -44 SPARE -45 HSI PRIMARY TUBE VALID -46 HSI RASTER/STROKE + -47 HSI RASTER/STROKE - -48 SPARE -49 HSI PRIMARY STROKE READY + -50 HSI PRIMARY STROKE READY - -51

HSI SEC STROKE READY + -52 RESERVEDHSI SEC STROKE READY - -53 HSI SEC TUBE VALID -54

ADI X DEFLECTION + -55 ADI X DEFLECTION - -56 SPARE -57 ADI Y DEFLECTION + -58 ADI Y DEFLECTION - -59 SPARE -60 HSI X DEFLECTION + -61 HSI X DEFLECTION - -62 SPARE -63 HSI Y DEFLECTION + -64 HSI Y DEFLECTION - -65 SPARE -66SPARE -67SPARE -68SPARE -69SPARE -70SPARE -71SPARE -72SPARE -73SPARE -74SPARE C190J1A-75






(I) MANUAL TRIM DN C190J1A-76(I) MANUAL TRIM UP -77

MANUAL TRIM ENABLE -78SPARE DIS 2810 P -79RESERVED -80RESERVED -81RESERVED FOR PRIMARY PITCH X -82RESERVED FOR PRIMARY PITCH Y -83RESERVED FOR PRIMARY PITCH Z -84RESERVED FOR PRIMARY ROLL X -85RESERVED FOR PRIMARY ROLL Y -86RESERVED FOR PRIMARY ROLL Z -87RESERVED FOR PRIMARY HDG X -88RESERVED FOR PRIMARY HDG Y -89RESERVED FOR PRIMARY HDG Z -90

RESERVED -91RESERVED -92RESERVED -93RESERVED -94

RESERVED FOR PRI ADF BRG SIN -95COMRESERVED FOR PRI ADF BRG SIN -96RESERVED FOR PRI ADF BRG X -97RESERVED FOR PRI ADF BRG Y -98RESERVED FOR PRI ADF BRG COS -99RESERVED FOR PRI ADF BRG Z -100RESERVED FOR PRI ADF BRG COS -101COM

-102RESERVED -103

-104 -105

RESERVED C190J1A-106






RESERVED FOR PRI DME C190J1B-1CLK +RESERVED FOR PRI DME DATA + -2RESERVED FOR PRI DME COMMON -3RESERVED FOR PRI DME ENABLE -4RESERVED FOR PRI DME HOLD -5RESERVED FOR SEC DME CLK + -6RESERVED FOR SEC DME DATA + -7RESERVED FOR SEC DME COMMON -8RESERVED FOR SEC DME ENABLE -9RESERVED FOR SEC DME HOLD -10RESERVED FOR PS + IN -11RESERVED FOR PS = IN -12AIRSPEED PRESSURE IN -13

(I) 28 VDC DISCRETE N2 OVERRIDE -14 (24)---------------- MAINT SWITCHRESERVED -15RESERVED -16RESERVED -17RESERVED -18RESERVED -19RESERVED -20

(I) LAMP TEST IN -21 (24)---------------- FIG. 6-8(I) HDG PB IN -22 (24)---------------- 11J1-11,

190J1B-22RESERVED PB IN -23

(I) NAV PB IN -24 (24)---------------- 11J1-13,190J1B-24

(I) APR PB IN -25 (24)---------------- 11J1-14,190J1B-25

(I) ALT PB IN -26 (24)---------------- 11J1-15,190J1B-26

(I) SPD PB IN -27 (24)---------------- 11J1-16,190J1B-27

(I) FLC PB IN -28 (24)---------------- 11J1-17,190J1B-28

(I) GA IN -29 (24)---------------- FIG. 6-18

(I) VS PB IN -30 (24)---------------- 11J1-19,190J1B-30

SPARE C190J1B-31






RESERVED BARO SET IN C190J1B-32(WIPER)SPARE -33

(O) EICAS DISPLAYED ON RMU -34 (24)---------------- 144J1-x(O) MASTER CAUTION LAMP OUTPUT -35 (24)---------------- FIG. 6-33(O) LAMP DRIVER FD2 ON -36 (24)---------------- 11J1-22(O) LAMP DRIVER FLC -37 (24)---------------- 11J1-32,

190J1B-37RESERVED -38RESERVED -39RESERVED -40RESERVED FAST/SLOW 28 V VALID -41RESERVED FAST/SLOW DCVAR -42INPUT +RESERVED FAST/SLOW DCVAR -43INPUT -

(I) MASTER WARNING INPUT FROM AWC -44 (24)---------------- AURAL WARNINGCOMP (FIG. 6-33)

(I) RESERVED SEC NAV 28 V VALID -45 (RESERVED FOR JOYSTICK INPUT - RIGHT)RESERVED SEC SRN LATERAL DEV +-46RESERVED SEC SRN LATERAL DEV --47

(I) FD 2 ON -48 (24)---------------- 11J1-20RESERVED SEC GS 28 V VALID -49RESERVED SEC GS DEV + -50RESERVED SEC GS DEV - -51RESERVED ROT/YAW RATE 5 V -52VALIDRESERVED ROT/YAW RATE + -53RESERVED ROT/YAW RATE - -54RESERVED COMPASS SYNC + -55RESERVED COMPASS SYNC - -56RESERVED INNER MARKER BEC + -57RESERVED INNER MARKER BEC - -58RESERVED MIDDLE MARKER + -59RESERVED MIDDLE MARKER - -60RESERVED OUTER MARKER + -61RESERVED OUTER MARKER - -62RESERVED -63RESERVED -64TRIM POSN SENSOR 2 (H) -65 (24)-T-S----------S-- HSCU RIGHTTRIM POSN SENSOR 2 (L) -66 (24)-T-S----------S-- SURFACE POSN

SHIELD GND ────────────┘ └─── SHIELD GNDTRIM POSN SENSOR 1 (H) -67 (24)-T-S----------S-- HSCU LEFTTRIM POSN SENSOR 1 (L) -68 (24)-T-S----------S-- SURFACE POSN

SHIELD GND ────────────┘ └─── SHIELD GNDRESERVED -69RESERVED C190J1B-70






RESERVED C190J1B-71RESERVED -72RESERVED -73RESERVED -74RESERVED -75

(I) RESERVED SEC ATT 28 V VLD -76 (RESERVED FOR JOYSTICK INPUT - UP)(I) RESERVED SEC HDG 28 V VLD -77 (RESERVED FOR JOYSTICK INPUT - DOWN)(I) STALL WARNING 28 VDC DISCRETE -78 (24)----------------- STALL PROTECTION

COMPUTER(I) SPARE DIS 28/0 GP -79 (RESERVED FOR JOYSTICK INPUT - LEFT)

RESERVED FOR SEC AC REF + -80RESERVED FOR SEC AC REF - -81

RESERVED FOR SEC PITCH X -82RESERVED FOR SEC PITCH Y -83RESERVED FOR SEC PITCH Z -84

RESERVED FOR SEC ROLL X -85RESERVED FOR SEC ROLL Y -86RESERVED FOR SEC ROLL Z -87

RESERVED FOR SEC HDG X -88RESERVED FOR SEC HDG Y -89RESERVED FOR SEC HDG Z -90

RESERVED -91RESERVED -92RESERVED -93SPARE -94

RESERVED FOR SEC ADF BRG SIN -95COMRESERVED FOR SEC ADF BRG SIN -96RESERVED FOR SEC ADF BRG X -97RESERVED FOR SEC ADF BRG Y -98RESERVED FOR SEC ADF BRG COS -99RESERVED FOR SEC ADF BRG Z -100RESERVED FOR SEC ADF BRG COS -101COMRESERVED -102RESERVED -103RESERVED -104RESERVED -105RESERVED C190J1B-106






(P) DGC +28 V DC POWER C190J2A-1 (20)----------------- FIG. 6-1(P) DGC +28 V DC POWER -2 (20)----------------- FIG. 6-1(P) DGC +28 V DC POWER -3 (20)----------------- FIG. 6-1(P) DGC DC POWER GND -4 (20)----------------- DC PWR GND(P) DGC DC POWER GND -5 (20)----------------- DC PWR GND(P) DGC DC POWER GND -6 (20)----------------- DC PWR GND(P) PRI CPU LAMP RETURN -7 (20)----------------- DC PWR GND(I) DGC SIGNAL GND -8 (22)----------------- SIGNAL GND(I) DGC SIGNAL GND -9 (22)----------------- SIGNAL GND

(O) DH SET (L) -10 (24)-T-S---------S-- C115J1-55(O) DH SET (H) -12 (24)-T-S---------S-- C115J1-53(I) DH SET (W) -13 (24)-T-S---------S-- C115J1-54

SHIELD GND ───────┘ └── SHIELD GND-10V REF OUT -11SPARE -14

(B) PRIMARY DC-550 + -15 (24)-T-S---------S-- C115J1-34(B) PRIMARY DC-550 - -16 (24)-T-S---------S-- C115J1-35


(B) WX CONTROL -17 (24)-T-S---------S-- 59J1-e(B) WX CONTROL -18 (24)-T-S---------S-- 59J1-f


(B) PRIMARY RSB (H) -19 (24)-T-S---------S-- FIG. 6-21(B) PRIMARY RSB (L) -20 (24)-T-S---------S-- FIG. 6-21


(B) ARINC 429 CH 0 IN (H) LRNA -21 (24)-T-S---------S-- FMS (H),│ │ 190J2A-21

(B) ARINC 429 CH 0 IN (L) LRNA -22 (24)-T-S---------S-- FMS (L),│ │ 190J2A-22

SHIELD GND ───────┘ └── SHIELD GNDRESERVED -23RESERVED -24RESERVED -25

(B) ARINC 429 CH 12 IN (L) -26 (24)-T-S---------S-- RESERVED (TS WITH│ │ C190J2A-40)



(B) ARINC 429 CH 4 IN (H) -29 (24)-T-S---------S-- C1J1B-G7, FIG.(PRI AHRS) │ │ 6-10

(B) ARINC 429 CH 4 IN (L) C190J2A-30 (24)-T-S---------S-- C1J1B-G8 (PRI AHRS) SHIELD GND ───────────┘ └── SHIELD GND






(B) ARINC 429 CH 6 IN (H) C190J2A-31 (24)-T-S---------S-- FIG.(B) ARINC 429 CH 6 IN (L) -32 (24)-T-S---------S-- 6-12


AP ARINC 429 CH 0 (H) -33AP ARINC 429 CH 0 (L) -34AP ARINC 429 CH 1 (H) -35AP ARINC 429 CH 1 (L) -36

(B) ARINC 429 OUTPUT TO DAU (H) -37 (24)-T-S---------S-- FIG.(B) ARINC 429 OUTPUT TO DAU (L) -38 (24)-T-S---------S-- 6-12


(B) 429 LRN OUT (HI) -39 (24)-T-S---------S-- FMS ARINC IN 2(H) TS W\ 52

(B) ARINC 429 CH 12 IN (H) -40 (24)-T-S---------S-- RESERVED (TS WITH)C190J2A-26)



(B) ARINC 429 CH 10 IN (H) -43 (24)-T-S----------S-- 9J1-60, 190J2B-23(SEC MADC) │ │ FIG. 6-11

(B) ARINC 429 CH 10 IN (L) -44 (24)-T-S----------S-- 9J1-61, 190J2B-24 FIG. 6-11

(SEC MADC) SHIELD GND ───────────┘ └── SHIELD GND

(B) HDLC IN #2 (H) -45 (24)-T-S----------S-- FIG.(B) HDLC IN #2 (L) -46 (24)-T-S----------S-- 6-13


HDLC IN #2 (T) -47RESERVED -48

(I) RADAR ALT 28 V VALID -49 (24)----------------- 20J1-Y,193RMP-2K,193RBP-3C,190J2A-49

(I) RADAR ALT + -51 (24)-T-S----------S-- 20J1-W,190J2A-51(I) RADAR ALT - -50 (24)-T-S----------S-- 20J1-N,190J2A-50,

│ │ 193RMP-2J,│ │ 193RBP-3B

SIGNAL GND ────────┘ └── SHIELD GND

(B) 429 LRN OUT (LO) C190J2A-52 (24)-T-S----------S-- FMS ARINC IN 2│ │ (L) TS W\ 39







RESERVED C190J2A-53LEFT SIDE SELECT -54

(O) RESERVED -55(O) RESERVED -56(B) DGC-DGC/FTSU BUS (H) -57 (24)-T-S---------S-- TEST CONNECTOR,(B) DGC-DGC/FTSU BUS (L) -58 (24)-T-S---------S-- FIG. 6-34

SIGNAL GND ────────┘ └── SHIELD GND

RESERVED -59RESERVED FOR FLAP INPUT -60LANDING GEAR CMD DISCRETE -61 (24)---------------- LANDING GEAR LOGICSPEED BRAKES DEPLOYED -62 (24)---------------- SPEED BRAKERESERVED FOR FLAP INPUT -63

(I) WEIGHT ON WHEELS (WOW) -64 (24)---------------- FIG. 6-2RESERVED -65

(I) SYS CONFIG IDENT 1 -66 (24)---------------- GND FOR DISPLAYIN METRIC UNITS

(I) SYS CONFIG IDENT 2 -67(I) SYS CONFIG IDENT 3 -68 (24)---------------- GROUND IF FMS

INSTALLED(I) SYS CONFIG IDENT 4 -69 (24)---------------- GROUND IF DUAL

ADF INSTALLED(I) SYS CONFIG IDENT 5 -70 (24)---------------- GROUND FOR CROSS

POINTER FD CMD(I) SYS CONFIG IDENT 6 -71 (24)---------------- GROUND TO ENABLE

CAT II LOGIC

(I) A/C TYPE IDENT 1 -72 (24)---------------- SIGNAL GNDA/C TYPE IDENT 2 -73

(I) A/C TYPE IDENT 3 -74 (24)---------------- SIGNAL GNDA/C TYPE IDENT 4 -75A/C TYPE IDENT 5 -76TEST IDENT 1 -77TEST IDENT 2 -78TEST IDENT 3 -79TEST IDENT 4 -80

(B) ARINC 429 CH 9 IN (H) -81 (24)-T-S---------S-- FIG.(B) ARINC 429 CH 9 IN (L) C190J2A-82 (24)-T-S---------S-- 6-12







(B) ARINC 429 CH 11 IN (H) C190J2A-83 (24)-T-S---------S-- FIG.(B) ARINC 429 CH 11 IN (L) -84 (24)-T-S---------S-- 6-10

(SEC AHRS) SHIELD GND ───────────┘ └── SHIELD GND

RESERVED -85RESERVED -86RESERVED -87RESERVED -88RESERVED -89DIN GROUND -90

(B) RS232 SERIAL DATA OUT -91 (24)----------------(B) RS232 SERIAL DATA IN -92 (24)---------------- FIG. 6-34(B) RS232 SERIAL DATA GND -93 (24)----------------(O) ALT ALERT HORN OUT -94 (24)---------------- AUDIO WARNING SYS(O) DECISION HEIGHT WARN OUT -95 (24)---------------- AUDIO WARNING SYS

MASTER COMP MON OUT -96

(O) RAD ALT TEST OUT -97 (24)---------------- 20J1-T, 190J2A,97(O) BANK ANNUNC OUT -98 (24)---------------- 11J1-27, 190J2A-98(O) COUPLE ANNUNC OUT -99 (24)---------------- 11J1-36

RESERVED ANNUNC OUT -100

(O) VS MODE ANNUNC OUT -101 (24)--------------- 11J1-34, 190J2A-101(O) IAS MODE ANNUNC OUT -102 (24)--------------- 11J1-31, 190J2A-102(O) ALT MODE ANNUNC OUT -103 (24)--------------- 11J1-30, 190J2A-103(O) APR MODE ANNUNC OUT -104 (24)--------------- 11J1-29, 190J2A-104(O) NAV MODE ANNUNC OUT -105 (24)--------------- 11J1-28, 190J2A-105(O) HDG MODE ANNUNC OUT C190J2A-106 (24)--------------- 11J1-26, 190J2A-106






SERVO + 28 V POWER C190J2B-1SERVO + 28 V POWER -2SERVO + 28 V POWER -3SERVO + 28 V POWER -4RESERVED -5

SERVO DC POWER GND -6SERVO DC POWER GND -7SERVO DC POWER GND -8SERVO DC POWER GND -9

(B) HDLC OUT + (DU) -10 (24)-T-S---------S-- FIG.(B) HDLC OUT - (DU) -11 (24)-T-S---------S-- 6-13


RESERVED ARINC 429 OUTPUT (H) -12(B) ARINC 429 CH 13 IN (H) -13 (24)-T-S---------S-- WINDSHEAR SYS,

190J2B-13(TS W/C190J2B-26)





(O) MASTER CAUTION TO AWC -18 (24)---------------- AURAL WARNINGCOMP, FIG. 6-33

(O) MASTER WARNING TO AWC -19 (24)---------------- AURAL WARNINGCOMP, FIG. 6-33

(O) MASTER WARNING LAMP OUTPUT -20 (24)---------------- FIG. 6-33RESERVED -21RESERVED -22

(B) ARINC 429 CH 3 IN (H) -23 (24)-T-S---------S-- C9J1-60, FIG.(PRI MADC) │ │ 6-11

(B) ARINC 429 CH 3 IN (L) C190J2B-24 (24)-T-S---------S-- C9J1-61, SHIELD GND ───────────┘ └── SHIELD GND






RESERVED ARINC 429 OUT C190J2B-25(L)

(B) ARINC 429 CH 13 IN (L) -26 (24)-T-S---------S-- WINDSHEAR SYS,190J2B-26(TS W/C190J2B-13)

(B) ARINC 429 CH 15 IN (H) (PFD) -27 (24)-T-S---------S-- FIG.(B) ARINC 429 CH 15 IN (L) (PFD) -28 (24)-T-S---------S-- 6-13


(B) ARINC 429 CH 5 IN (H) (TCAS) -29 (24)-T-S---------S-- 193 RMP-7G(B) ARINC 429 CH 5 IN (L) -30 (24)-T-S---------S-- 193 RMP-7H,




RESERVED ARINC 429 OUTPUT (H) -33RESERVED ARINC 429 OUTPUT (L) -34RESERVED ALT ALERT ANNUNC OUT -35RESERVED PRIMARY AC REF + -36RESERVED PRIMARY AC REF - -37RESERVED -38RESERVED -39RESERVED -40RESERVED -41RESERVED -42RESERVED -43RESERVED -44RESERVED -45RESERVED -46RESERVED -47

(I) SG 2 REVERSION -48 (24)---------------- FIG. 6-9

RESERVED -49RESERVED C190J2B-50






(I) AP LAMP RETURN C190J2B-51 (22)--------------- DC PWR GNDRESERVED -52

(B) SECONDARY RSB (H) -53 (24)-T-S-------S--- FIG. 6-21(B) SECONDARY RSB (L) -54 (24)-T-S-------S--- FIG. 6-21

SHIELD GND ───────────┘ └───── SHIELD GND

(I) COUPLE PB INPUT -55 (24)--------------- 11J1-10,190J2B-55

(I) BANK PB INPUT -56 (24)--------------- 11J1-12,190J2B-56

RESERVED -57RESERVED -58+15 V EXTERNAL OUT -59-15 V EXTERNAL OUT -6015 V RETURN -61RESERVED LATERAL ACCEL INPUT -62RESERVED LAT ACCEL TEST OUTPUT-63RESERVED NORMAL ACCEL INPUT -64RESERVED LONGT ACCEL INPUT -65

(I) MAN TRIM IN (UP) -66(I) MAN TRIM IN (DN) -67

RESERVED PITCH WHEEL IN + -68RESERVED PITCH WHEEL IN - -69

(I) TCS 28 V INPUT -70 (24)--------------- FIG. 6-17RESERVED -71SPARE -72TURN KNOB INPUT -73SPARE -74

(I) TURN KNOB OUT OF DETNT -75 (24)--------------- 129J1-H,190J2B-75

(I) AP DISCONNECT 28 V IN -76 (24)--------------- FIG. 6-16

(O) MOMENTARY HORN DISABLE -77 (22)--------------- C115J1-44RESERVED YD OFF ANNUNC OUT -78

(O) LIGHT AND HORN DISABLE -79 (22)--------------- C115J1-42,C115J1-43

RESERVED TRIM WARN ANNUNC OUT -80RESERVED TRIM UP ANNUNC OUT -81IN/HPA -82 (22)--------------- C9J1-76RESERVED YD ENG SELECT PB IN -83RESERVED YD ENG ANNUNC C190J2B-84OUT






AP ENGAGE SEL PB IN C190J2B-85AP ENGAGE ANNUNC OUT -86RESERVED -8728 V AP CLUTCH -8828 V AP CLUTCH -89

(I) AP DISCONNECT 28 VIN -90 (20)---------------- FIG. 6-16(I) MASTER CAUTION INPUT FROM AWC -91 (24)---------------- AURAL WARNING

COMP, FIG. 6-33(O) PITCH TRIM OUT + -92(O) PITCH TRIM OUT - -93(I) RIGHT SIDE SELECT IN -94 (24)---------------- SIGNAL GND






RESERVED -105RESERVED C190J2B-106




6.0 SUPPLEMENTARY WIRING INFORMATION (FIGURES)


Table

3-1.Interconnect

Information

(con

t)

SY

ST

EM

MA

INT

EN

AN

CE

MA

NU

AL

EM

BR

AE

R1

45

28Vdc

Power

TC

AS

GP

WS

DC

BU

S 1

AVIONICSMASTERRELAY

AM

DC

BU

S 1

A

7.5 FCS 1

10 PFD 1

10 MFD 2

5 DME 1

130J1-101, -102, -103

164J1A-86, -99

131J1-101, -102, -103

AM

DC

BU

S 1

B

7.5 VHF 3

7.5 WX

5 TDR 1

5 FMS

59J1-A, B61J1-D

143J1-8, 9143J5-8, 9

SBC1

SH

ED

DC

BU

S 1

DC

BU

S 1

DAU 1B

CMC

5136J2A-103,136J2A-104

BC 1 ELT EBC1

CENTRAL DC BUS

ES

S D

C B

US

1

ES

S D

C B

US

1

PLT AUDIO 1

5 RMU 1 144J1-C

SWS - SHAKER 1

SWS - CHANNEL 1

AWS 1

FDR

5 DAU 1A

EICAS DU

5 AHRS 1 1J1C-7

10 VHF 1

PITCH TRIM 1

RAD ALT 1 20J1-c5

AVIONICSMASTERRELAY

AM

ES

S D

C B

US

1 5 ADC 1 9J1-26

VOR/ILS/MB 1

ADF 1 164J1A-87, -100

1641A-85, -98164J1B-39, -525

5

160J1-U, 160J1-V

136J1A-103136J1A-104

132J1-101, -102, -103

143J1-4, -5, -6

TO FIG6-1B

EIC

5

AD-50089@

BT

C1

121J1B-10, -11, -12, -52

5 FMS CDU

5 FMS DL

120J1-B, F, v

123J1-C

10

10 ICI 190J2A-1, -2, -3

INV

ER

TE

R

5 DISPLAY CONTROL 1 115J1-5

HOT BUS

BACKUP ESS DC BUS 1

5 AHRS 1 AUX 1J1C02

10 EICAS DU

10

DAU 1/25

IC 1

132J1-101, -102, -103

BACKUP HOT BUS

BACKUPBATT

BACKUP DC BUS 2

MFD 1

10 PFD 2

10

AHRS 2 AUX5

IC 2

BACKUP DC BUS 1

MFD 2

10 PFD 1

10

Figure6-1A

Pa

ge

3-2

03

/20

422-05-14

No

v1

/19

96

Use

or

disclo

sure

of

info

rma

tion

on

this

pa

ge

issu

bje

ctto

the

restrictio

ns

on

the

titlep

ag

eo

fth

isd

ocu

me

nt.

Table

3-1.Interconnect

Information

(con

t)

SY

ST

EM

MA

INT

EN

AN

CE

MA

NU

AL

EM

BR

AE

R1

45

28Vdc

Power

DC

BU

S 2

ES

S D

C B

US

2

EBC2

ES

S D

C B

US

2

BATT 2

TO FIG6-1A

BC 2

BT

C2

CENTER DC BUS

ES

S D

C B

US

2

CPLT AUDIO 2

RMU 2 C144J1-C

PITCH TRIM 2

STBY ATT

5

5

5

DAU 2A 137J1A-103,137J1A-104

C160J1-U, C160J1-V

5

SWS - CHANNEL 2

SWS - PUSHER

SWS - SHAKER 2

DAU 2B

AHRS 2 C1J1C-75

137J2A-103,137J2A-104

10 IC 2

OBSERVER AUDIO E160J1-U,V5

C190J2A-1, -2, -3

AWS 2

STBY ALT

CVR

DC

BU

S 2

AVIONICSMASTERRELAY

AM

DC

BU

S 2

B

5

5

5

5

HF

VOR/ILS/MB 2

TDR 2

ADF 2 C164J1A-87, -100

OMEGA

GPS 149J1-34

C164J1A-85, -98C164J1B-39, -52

C143J1-8, -9C143J5-8, -9

AM

DC

BU

S 2

A

5

5

5

10

MFD 1

DME 2 C164J1A-86, -99

CDH 165J1-E

RAD ALT 2 C20J1-c

ADC 2 C9J1-26

VHF 2 C143J1-4, -5, -6

5

10 131J1-101,-102, -103

PFD 210 C131J1-101,-102, -103

SBC2

SH

ED

DC

BU

S 2

AD-50090@

DISPLAY CONTROL 2 C115J1-55

Figure6-1B

Pa

ge

3-2

05

/20

622-05-14

No

v1

/19

96

Use

or

disclo

sure

of

info

rma

tion

on

this

pa

ge

issu

bje

ctto

the

restrictio

ns

on

the

titlep

ag

eo

fth

isd

ocu

me

nt.



IN AIR

WOWSWITCH

1J1B-K15

9J1-12

136J2A-80

190J2A-64

137J2A-80

C1J1B-K15

C9J1-12

C190J2A-64

61J1-P

C143J1-83

144J1-P

C144J1-P

165J1-Y

143J1-83

AD-50091@

193RMP-5K

Weight On WheelsFigure 6-2




TEST

MASTERTEST

SWITCHC9J1-70

1J1B-A10

C1J1B-A10

9J1-70

20J1-T

AD-39924@

190J2A-97

C190J2A-97

Functional TestFigure 6-3




+ 360°/MIN

- 360°/MIN

1J1B-H1

1J1B-H2

1J1B-H3

PILOT'S

+ 360°/MIN

- 360°/MIN

C1J1B-H1

C1J1B-H2

C1J1B-H3

HEADING SLEW

1J1B-HI 1J1B-H6

DG MODESELECT

C1J1B-HI C1J1B-H6

DG MODESELECT

COPILOT'S

DG MODE AD-39925@

1J1B-H4 C1J1B-H4

AHRS Remote SwitchesFigure 6-4




131J1

77

78

H

L

130J1

77

78

H

L

H

L

g

h

DU 2

DU 1

59J1

1

23" MIN

WXPORT 1

WXPORT 1

AD-50092@

LEFTPICTURE

BUS

WU-650/870

64 TERM

10" MAX STUB1

NOTES:USE HPN 3718911-1 CABLE (70 ± 10%).TOTAL LENGTH MUST BE < 50 FT (REF. SECTION 4.6)FOR THE WU-660/WU-880, PICTURE BUSPINS ARE J1-1 (H) AND J1-2(L)

Left WX/DU Picture BusFigure 6-5




Right WX/DU Picture Bus

C131J1

77

78

H

L

C130J1

77

78

H

L

H

L

k

s

DU 4

DU 5

59J1

1

23" MIN

WXPORT 1

WXPORT 1

AD-50093@

RIGHTPICTURE

BUS

WU-650/870

64 TERM

10" MAX STUB1

NOTES:USE HPN 3718911-1 CABLE (70 ± 10%).TOTAL LENGTH MUST BE < 50 FT (REF. PARAGRAPH 4.6)FOR THE WU-660/WU-880, PICTURE BUSPINS ARE J1-5 (H) AND J1-6(L)

Figure 6-6




0 -5 V DCEDGE LIGHTING

11J1-3

61J1-H

115J1-3

C115J1-3

130J1-23

132J1-23

C130J1-23

C131J1-23

165J1-D

160J1-q

C160J1-q

144J1-G

C144J1-G

AD-39927@

GC-550

WC-650

P DC-550

C PDC-550

DU#1

DU#3

DU#5

DU#4

P CD-850

P AV-850A

CP AV-850A

P RM-855

CP RM-855

129J1-g PC-400

131J1-23 DU#2

E160J1-q OB AV-850A

Edge LightingFigure 6-7




Lamp Test

LAMP TESTGND

C190J1B-21

190J1B-21AD-39928@

Figure 6-8



(Blank Page)




Display/SG Reversionary

16

DU NO. 1 - PFD 1

22

130J1

878889

909192

DU POWER DN

PORT SEL 3PORT SEL 2PORT SEL 1

ID NO. 3ID NO. 2ID NO. 1

IC-600 NO. 2C190J2B

48 SG REV

DC-550 NO. 2 C115J1

777872

CS MFD=EICAS

COPILOTS IC-600REVERSIONSWITCH

PILOTS IC-600REVERSIONSWITCH ANNUNCIATOR

POWER

LIGHTINGGND

LIGHTINGGND

79CS MFD=PFD

OS MFD=EICASOS MFD=PFD

IC-600 NO. 1190J2B

48 SG REV

DC-550 NO. 1 115J1

777872

CS MFD=EICAS 79CS MFD=PFD

OS MFD=EICASOS MFD=PFD

PFD

NRM

EICAS

MFD1REVSW

DU NO. 2 - MFD 1

22

131J1

878889

909192

DU POWER DN



DU NO. 3 - EICAS

22

132J1

878889

909192

DU POWER DN



DU NO. 4 - MFD 2

22

C131J1

878889

909192

DU POWER DN



PFDNRM

EICAS

MFD2REVSW

DU NO. 5 - PFD 2

22

C130J1

878889

909192

DU POWER DN



AD-39748-R2@

28 V DCBUS 2

28 V DCBUS 1

K3

K1

K2

15

35

34 DC/ICBUS OUT

DC/ICBUS IN

15

3534

190J2A

H

L

H

L

115J1

C115J1

DC/ICBUS OUT

H

L

H

LDC/IC

BUS IN

C190J2A

63

LATCHINGSWITCHES

16

CROSS-SIDE SG REV

Figure 6-9

Page 3-215/21622-05-14 Nov 1/1996Use or disclosure of information on this page is subject to the restrictions on the title page of this document.



429 CH 4 IN2930

BUS SELECTSWITCHING

LOGIC 1516

429 CH 11 IN8384

PILOT'S IC-600

429 CH 4 IN2930

BUS SELECTSWITCHING

LOGIC1516

429 CH 11 IN8384

COPILOT'S IC-600C190J2A190J2A

3334

AUTOPILOT

429 CH 0 IN

190J2A

G8G7

E5E6

COPILOT'S AH-800

429 OUT 1

429 OUT 2

C1J1B

G8G7

E5E6

PILOT'S AH-800

429 OUT 1

429 OUT 2

1J1B

73

3435

COPILOT'S DC-550

AHRS 1 SEL

IC SERIAL BUS

C115J1

73

3435

PILOT'S DC-550

AHRS 2 SEL

IC SERIAL BUS

115J1

AD-50095@

K12K13

F14F15

429 OUT 3

429 OUT 4

K12K13

F14F15

429 OUT 3

429 OUT 4 SPS,GPWSFMS

SPS,GPWSFMS

59J1-K59J1-L

WEATHERRADAR

4342

DAU2 DA-800

429 IN 2

137J1B

AHRSREVERSION

SWITCH

AHRS Reversion SwitchingFigure 6-10



(Blank Page)




MADC Reversion

PILOT'S DC-550MADC REV

115J1

74 NORMREV

PILOT'SMADC REVSWITCH

PILOT'S MADCAZ-850 PILOT'S IC-600

429 CH 10 IN

190J2A

4323 4424

429 CH 3 IN

190J2B

COPILOT'S IC-600

429 CH 3 IN

C190J2B

23

4324

44429 CH 10 IN

C190J2A

429 BUS OUT

9J1

6061

PILOT'S AH-800

K4K5

429 CH 1 IN

1J1B

COPILOT'S AH-800

429 CH 1 IN

C1J1B

K4K5

OPTIONAL P-870WX RADAR

59J1

PILOT'S RCZ-851E

429 CH 2 IN

143J1

10080

6999

143J1

429 CH 1 IN86

429 BUS OUT

9J1

6667

COPILOT'SRCZ-851E

429 CH 2 IN

C143J1

100

8069

99

C143J1

429 CH 1 IN86

TO HORIZONTALSTABILIZER

CONTROL UNIT 9J1

6364

TO FADEC 1A

TO FADEC 1A

RESERVED

TO FADEC 2A

TO FADEC 2A

429 BUS OUT

TO PRESSUREDIGITAL

CONTROLLER 9J1

6869

TO STALLPROTECTION

COMPUTER

TO GROUND PROXWARNING SYSTEM

429 BUS OUT

COPILOT'S DC-550MADC REV

C115J1

74

COPILOT'S MADCAZ-850

429 BUS OUT

C9J1

6061

429 BUS OUT

C9J1

6667

TO HORIZONTALSTABILIZERCONTROL UNITC9J1

6364

TO FADEC 1B

TO FADEC 1B

RESERVED

TO FADEC 2B

TO FADEC 2B

429 BUS OUT

TO PRESSUREDIGITALCONTROLLERC9J1

6869

TO STALLPROTECTION CH3COMPUTER

TO WINDSHEARCOMPUTER

TO OPTIONALFMS

429 BUS OUT

AD-50096@

TO OPTIONALFMS/GPS

TO OPTIONALGPS

tr

3536

AP429 CH 1 IN

COPILOT'SMADC REV

SWITCH

Figure 6-11

Page 3-219/22022-05-14 Nov 1/1996Use or disclosure of information on this page is subject to the restrictions on the title page of this document.



DAU Reversion

429 CH 9 IN8182

BUS SELECTSWITCHING

LOGIC

429 CH 8 IN4142

PILOT'S IC-600 J2A

5150

PILOT'S DAU CH A

429 CH2 OUT

J1B

76

75

PILOT'S DC-550

DAU B SEL

J1

PILOTSDAU

REVERSIONSWITCH

AD-50097@

DAU A SEL3534

429 CH 7 IN3132

429 CH 6 IN3132

J2B1615

J2A

J1

5150

PILOT'S DAU CH B

429 CH2 OUT

J2B

429 CH 9 IN8182

BUS SELECTSWITCHING

LOGIC

429 CH 8 IN4142

COPILOT'S IC-600J2A

5150

COPILOT'S DAU CH A

429 INPUT

429 CH2 OUT

J1B

76

75

COPILOT'S DC-550

DAU B SEL

J1

DAU A SEL 3534

429 CH 7 IN3132

429 CH 6 IN3132

J2B

1615

J2A

J1

5150

COPILOT'S DAU CH B

429 CH2 OUT

J2B

J2A3738 429 OUTPUT

4342

4041

429 CH1 IN

429 CH2 OUT

J1B

FIG 6-14

136

136

190

115 C115

C190

J2A

4041

J1B

FIG 6-14

137

137

429 CH1 OUT

NORMREV

COPILOTSDAU

REVERSIONSWITCH

J2A

Figure 6-12




Display Wrap Around

DU NO. 1 - PFD 1130J1

353649

3839

HDLC #2 IN

HDLC #2 TERM

HDLC #1 IN

IC-600 NO. 1 190J2B

1011

14

DU HDLC OUT +-

AD-39750@

+-

+-

6679

ARINC 429 OUT+-

DU NO. 2 - MFD 1131J1

3536

3839

HDLC #2 IN

HDLC #1 IN+-

+-

3132

HDLC OUT+-

DU NO. 3 - EICAS132J1

3536

3839

HDLC #2 IN

HDLC #1 IN+-

+-

3132

HDLC OUT+-

DU NO. 4 - MFD 2C131J1

3536

3839

HDLC #2 IN

HDLC #1 IN+-

+-

3132

HDLC OUT+-

DU NO. 5 - PFD 2C130J1

353649

3839

HDLC #2 IN

HDLC #2 TERM

HDLC #1 IN+-

+-

6679

ARINC 429 OUT+-

DU HDLC #1 IN(TERMINATED)

+-

DU HDLC #2 IN +-

DU HDLC #3 IN(UNTERMINATED)

+-

ARINC 429 CH 15 IN +-

OPT HDLC #2 TERM

190J2A

15

1617

2728

4546

47

IC-600 NO. 2 C190J2B

1011

14

DU HDLC OUT +-

DU HDLC #1 IN(TERMINATED)

+-

DU HDLC #2 IN +-

DU HDLC #3 IN(UNTERMINATED)

+-

ARINC 429 CH 15 IN +-

OPT HDLC #2 TERM

C190J2A

15

1617

2728

4546

47

23" MIN

10" MAX STUB

10" MAX STUB

10" MAX STUB

10" MAX STUB

23" MIN

10" MAX STUB

23" MIN

10" MAX STUB

10" MAX STUB

10" MAX STUB

23" MIN

10" MAX STUB

10" MAX STUB

23" MIN

23" MIN

10" MAX STUB

10" MAX STUB

23" MIN

23" MIN

10" MAX STUB

127

127

W

W

Figure 6-13




RMU Engine Backup Display Interface

CCDD

FFGG

144J1

+-

+-

INPUT BUS #1

INPUT BUS #2

PILOT'S RMU

4140

136J1B

+-

OUTPUT BUS #1

PILOT'S DAU

CHANNEL A

C144J1

+-

+-

INPUT BUS #1

INPUT BUS #2

COPILOT'S RMU

4140

137J1B

+-

OUTPUT BUS #1

COPILOT'S DAU

CHANNEL A

AD-50098@

FF

DDCC

GG

Figure 6-14




R MAINAVIONICSBUS

AP OFFLAMP(PROVISION)

YD OFFLAMP(PROVISION)

AP OFFAUDIOWARNING

AP OFFLAMP OUT

AP OFFHORN OUT

29

30

PILOT'S DC-550

YD OFFLAMP OUT

78

PILOT'S IC-600

AD-39751@

115J1

190J2B

AP/YD Off WarnFigure 6-15




PLT SERVOPOWER

FIGURE6-1A

PILOT'SWHEEL

MASTER SW

COPILOT'SWHEEL

MASTER SW

7690

190J2B

APDISCONNECT

PILOT'S IC-600

33

115J1

AP DISCONNECT

PILOT'S DC-550

7690

C190J2B

APDISCONNECT

COPILOT'S IC-600

33

C115J1

AP DISCONNECT

COPILOT'S DC-550

FIGURE6-1A

AD-36375-R2@

AP Disconnect InterfaceFigure 6-16




70

C190J2B COPILOT'S IC-600

32

C115J1 COPILOT'S DC-550

AD-39931-R1@

70

190J2B PILOT'S IC-600AUTOPILOT

SERVOPOWER

32

115J1 PILOT'S DC-550

COPILOT'STCS

PILOT'STCS

TCS INPUT

TCS INPUT

TCS INPUT

TCS INPUT

Touch Control Steering (TCS)Figure 6-17




SIGNALGND

PILOT'S

71

190J2B

GO AROUND

PILOT'S IC-600

SIGNALGND

COPILOT'S

71

C190J2B

GO AROUND

COPILOT'S IC-600

AD-36378-R1@

Go-Around InterfaceFigure 6-18




Elevator Trim Interface

SERVO POWER

DN

UP

PILOT'S ELEC.TRIM SWITCH

77

76

MAN TRIM UP

MAN TRIM DN

PILOT'S IC-600

AD-50099@

190J1A

SERVO POWER

DN

UP

COPILOT'S ELEC.TRIM SWITCH

66

67

MAN TRIM UP

MAN TRIM DN

190J2B

45

49 SEC TRIM DN

SEC TRIM UPSECONDARY PITCH

TRIM SWITCHES

Figure 6-19




Surface Position Sensors

PILOT'S IC-600

AILERON POSITION POT 1 (W)

+15V OUT

-15V OUT

15V RTN

190

J1A

82

83

85

86

J2B

59

60

61

AILERONPOSITIONSENSOR

AD-50100@

84

87

AILERON POSITION POT 1 (H)

AILERON POSITION POT 1 (L)

Figure 6-20




RSB Interface

RMU NO. 1

120

IC-600 NO. 1

COM NO. 1

NAV NO. 1

CL DEL UNIT

120

RMU NO. 2

120 120

IC-600 NO. 2

COM NO. 2

NAV NO. 2

120

NOTE 2

NOTE 2

NOTE 2

144J1

MN

144J1

VW

190J2A

1920190J2B

5354

143J1

7461

143J1

1011

HL

HL

HL

HL

HL

HL

HL

HL

HL

164J1A

164J1B

7181

88102

165J1

gR

C144J1

VW

MN

5354

1920

1011

7181

88102

7461

C144J1

C190J2A

C190J2B

C143J1

C143J1

C164J1B

C164J1A

PRI RSB

PRI RSB

PRI RSB

PRI RSB

RIGHT SEC RSB

RIGHT SEC RSB

RIGHT SEC RSB

RIGHT SEC RSB

LEFT SEC RSB

PRI RSB

LEFT SEC RSB

PRI RSB

LEFT SEC RSB

PRI RSB

LEFT SEC RSB

PRI RSB

PRI RSB

AD-39934@

LE

FT

SE

C B

US

PR

I B

US

RIG

HT

SE

C B

US

HL

HL

HL

HL

HL

HL

HL

HL

120

TEST CONN NO. 1(FIG 6-34)

RSB WIRING REQUIREMENTS ARE DEFINED IN PARAGRAPH 4.7THE MAX LENGTH OF THE STUB WIRING TO THE AIRCRAFTTEST CONNECTORS IS 18 INCHESFOR SIMPLICITY THIS DIAGRAM DOES NOT SHOW THE SHIELDGROUNDING POINTS. ALL RSB SHIELDS SHALL BE MULTIPOINT GROUNDED AS DEFINED IN PARAGRAPH 4.2.2

NOTE: 1.2.

3.



W W W W

W

W

Figure 6-21




COM/NAV Strapping

143J1

103

164J1B

COM NO. 1

NAV NO. 1

AD-30340-R4@

SPARE E8

E2

102

101

89

88

43

16

E2

E7

E1

E6

E4

E3

84

80

59

58

57

26

40

E8

E6

E7

E1

E4

E3

(H)

(L)

WD LOAD

DATA

SPARE

CLK

5 V DCOUTPUT

SPARE

(H)

(L)

WD LOAD

DATA

CLK

5 V DCOUTPUT

SPARE

COM NO. 1STRAPPING

CIRCUITCARD

NAV NO. 1STRAPPING

CIRCUITCARD

NOTE: 1. ALL WIRE IS 24 AWG.

(RED)

(BLK)

(BLU)

(GRN)

(WHT)

(ORG)

(YEL)

(RED)

(BLK)

(GRN)

(WHT)

(BLU)

(YEL)

(ORG)

3A

4A

5A

1A

6A

2A

1B

300P17

300J17

4B

5B

2B

1C

6B

2C

3B

300P17

300J17

Figure 6-22




COM NO. 1

NAV NO. 1

AUDIO PNL NO. 1

120 120

143J1

5670

164J1B

4229

160J1

dp

cn

160J1

HL

HL

HL

HL

DIGITALAUDIO NO. 1

DIGITALAUDIO NO. 1

DIGITALAUDIO NO. 1

DIGITALAUDIO NO. 2

NOTE: USE ASCB CABLE AND INSTALL AS DEFINEDIN PARAGRAPH 4.8

COM NO. 2

NAV NO. 2

AUDIO PNL NO. 2

120 120

HL

HL

HL

HL

C160J1

C160J1

C164J1B

C143J1

5670

4229

cn

dp

AD-39935@

DIGITALAUDIO NO. 2

DIGITALAUDIO NO. 1

DIGITALAUDIO NO. 2

DIGITALAUDIO NO. 2

AUDIO PNL NO. 3

160AJ1

dp

cn

160AJ1HL

HL

DIGITALAUDIO NO. 1

DIGITALAUDIO NO. 2

W W W W

Digital Audio BusFigure 6-23




AD-39752-R1@

AUDIO PANEL NO. 1

HAND/MASK/BOOM MIC LOHAND MIC HI

HAND MIC PTT

PHONE AUDIO LOPHONE AUDIO HI

MASK/BOOM PTT

INTERPHONE PTTCOMMON GND

MASK MIC HI

BOOM MIC HI

160J2

PD

E

Y

h

AKJ

tk

NC

XMIT

OFFYOKESWITCH

MASK MIC

BOOM MIC

PHONE

HAND MIC

160J1

OPTIONALINTERPHONE PTT

Pilot’s Primary MIC/PhoneFigure 6-24




AD-39753-R2@

AUDIO PANEL NO. 2


HAND MIC PTT


MASK/BOOM PTT


MASK MIC HI

BOOM MIC HI

C160J2

PD

E

Y

h

AKJ

tk

NC

XMIT

OFFYOKESWITCH

MASK MIC

BOOM MIC

PHONE

HAND MIC

C160J1


Copilot’s Primary MIC/PhoneFigure 6-25




AD-39754-R1@

AUDIO PANEL NO. 3


HAND MIC PTT


MASK/BOOM PTT


MASK MIC HI

BOOM MIC HI

E160J2

PD

E

Y

h

AKJ

tk

NC

XMIT

OFFYOKESWITCH

MASK MIC

BOOM MIC

PHONE

HAND MIC

E160J1


Observer’s Primary MIC/PhoneFigure 6-26




AUDIO PNL NO. 1

EMER COMMIC OUTPUT

(H)

(L)

VHF 1MIC OUTPUT

(H)

(L)

EMER COM PTT

VHF 1 COM PTT

NC

P

H

R

E

B

F

160J1

AUDIO PNL NO. 2

VHF 1MIC OUTPUT

(H)

(L)

F

R

E

C160J1

VHF 1 COM PTT

AUDIO PNL NO. 3

VHF 1MIC OUTPUT

(H)

(L)

F

R

E

C160AJ1

VHF 1 COM PTT

COM NO. 1

MIC INPUT(H)

(L)

92

106

21

143J1

PTT INPUT

AD-39755-R2@NOTE: ALL WIRES ARE 24 AWG.

NC

PILOTS DAU

PLT RADIOXMIT KEYING

41

136J1A

No. 1 VHF COM/MIC PTTFigure 6-27




(H)

(L)

160J1

D

W

C160J1

AUDIO PNL NO. 1

AUDIO PNL NO. 2

VHF 2MIC OUTPUT

VHF 2 COM PTT C

W

D

VHF 2 COM PTT

(L)

(H)

VHF 2MIC OUTPUT

VHF COM NO. 2

(H)

(L)

NC

MIC INPUT

PTT INPUT

92

106

21

C

C143J1NC

E160J1AUDIO PNL NO. 3

AD-50101@

W

D

VHF 2 COM PTT

(L)

(H)

VHF 2MIC OUTPUT

NC

NOTES: ALL WIRES ARE 24 AWG.

C

P

H

EMER COM PTT

(L)

(H)

EMER COMMIC OUTPUT

NCB

PILOTS DAU

COPILOT RADIOXMTR KEYING37

136J2A

No. 2 VHF COM/MIC PTTFigure 6-28




AUDIO PANELNO. 1

(H) EMER NAVAUDIO f

m

160J1

NC

(L) EMER NAV/COM AUDIO

G(H) EMER COMAUDIO

NOTES:

NAV UNIT NO. 2

EMER NAVAUDIOOUTPUT

(H)

(L)

36

51

C164J1B

AUDIO PANELNO. 2

(H) EMER NAVAUDIOf

m

C160J1

NC

(L) EMER NAV/COM AUDIO

G (H) EMER COMAUDIO

COM UNIT NO. 2

EMER COMAUDIOOUTPUT

(H)

(L)

31

29

C143J1B

AD-50102@

(NOTE 2)2.2K1/4W

(NOTE 2)2.2K1/4W

ALL WIRE IS TWISTED SHIELDED PAIR 24 AWG.2.2K RESISTOR IS USED TO REDUCE EMERGENCYAUDIO LEVEL THIS IS A TYPICAL VALUE. ANY VALUEBETWEEN ZERO AND 10K MAY BE USED OR A 10KPOT MAY BE INSTALLD.

1.2.

Emergency NAV/COM AudioFigure 6-29




AUDIO PANEL NO. 1

MAINT PHONE AUDIO(H)

(L)

160J2

f

P

MAINT MIC 1(H)

(L)

q

e

kMAINT MIC 1 PTTMSTEREO MUTE

PA MIC(H)

(L)

i

U

jPA PTT

WARNING NO. 3(H)

(L)

m

J

AUDIO PANEL NO. 2 C160J2

m

J

MSTEREO MUTE

PA MIC(H)

(L)

i

U

WARNING NO. 3(H)

(L)

jPA PTT

AUDIO PANEL NO. 3 E160J2

m

J

MSTEREO MUTE

PA MIC(H)

(L)

i

U

WARNING NO. 3(H)

(L)

jPA PTT

nMAINT MIC 2

(H)

(L)

RMAINT MIC 2 PTT

g

PASSENGERADDRESSSYSTEM

AD-39757@

Passenger Address InterfaceFigure 6-30




COM NO. 2

94

C143J1

MUT SUPPINPUT/OUTPUT

NAV NO. 2

MUT SUPPINPUT/OUTPUT42

NOTES:1. USE 24 AWG SINGLE SHIELDED WIRE2. GROUND SHIELD ENDS AT NAV AND COM UNIT

BOBBINS. AD-50103@

COM NO. 1

94

143J1


NAV NO. 1

MUT SUPPINPUT/OUTPUT42

C164J1A

164J1A

TCAS COMPUTER

12

193LBP


DME/XPDR Mutual SuppressionFigure 6-31




HF SYSTEM

HF PTT

AUDIO PNL NO. 1

HF 1 PTT b

160J1

AUDIO PNL NO. 2

HF 1 PTT b

C160J1

AUDIO PNL NO. 3

HF 1 PTT b

E160J1

NOTES: 1. ALL WIRE IS 24 AWG.

VHF COM NO. 1

HF COM XMIT(GND/OPEN)

37

143J1

NAV NO. 1

HF KEY (ADF)66

164J1A

NAV NO. 2

HF KEY (ADF)66

C164J1

AD-39938@

HF ConsiderationsFigure 6-32




35

C190J1B

MASTER CAUTIONLAMP OUTPUT

COPILOT'S IC-600

COPILOT'S MASTERCAUTION ANNUNC/SWITCH

35

190J1B

MASTER CAUTIONLAMP OUTPUT

PILOT'S IC-600

PILOT'S MASTERCAUTION ANNUNC/SWITCH

COPILOT'S MASTERWARNING ANNUNC/SWITCH

PILOT'S MASTERWARNING ANNUNC/SWITCH

44MASTER WARNINGINPUT FROM AWC

44MASTER WARNINGINPUT FROM AWC

18

C190J2B

MASTER CAUTIONOUTPUT TO AWC

18

190J2B

MASTER CAUTIONOUTPUT TO AWC

19MASTER WARNINGOUTPUT TO AWC

19MASTER WARNING

OUTPUT TO AWC

20MASTER WARNINGLAMP OUTPUT

20MASTER WARNING

LAMP OUTPUT

91MASTER CAUTIONINPUT FROM AWC

91MASTER CAUTIONINPUT FROM AWC

60

C115J1

MASTER CAUTIONGND = ACTIVE

COPILOT'S DC-550

60

115J1

MASTER CAUTIONGND = ACTIVE

PILOT'S DC-550

AD-39939-R1@

61MASTER WARNINGGND = ACTIVE

61MASTER WARNING

GND = ACTIVE

+28 VDC

+28 VDC

+28 VDC

+28 VDC

AURALWARNING

COMPUTER

AURALWARNING

COMPUTER

Master Caution/WarningFigure 6-33




50 -

PIN

D -

CO

NN

EC

TO

R (

M24308/4

-5F

)

9

10

11

18

27

28

29

36

47

48

49

30

31

32

2

1

3

4

5

21

22

23

24

33

41

MODE SEL

AHRU 1 RS-232

TX

RX

COM

MODE SEL

AHRU 2 RS-232

TX

RX

COM

IC-600 1 RS-232

TX

RX

COM

IC-600 2 RS-232

TX

RX

COM

IC-600 ICB

AZ-850 1 RS-232

TX

RX

COM

AZ-850 2 RS-232

TX

RX

COM

NZ-2000 RS-232

TX

RX

COM

37 -

PIN

D -

CO

NN

EC

TO

R (

M24308/4

-4F

)

12

13

14

15

16

17

18

19

20

21

22

23

DAU 1A RS-232

TX

RX

COM

DAU 1B RS-232

TX

RX

COM

DAU 2A RS-232

TX

RX

COM

DAU 2B RS-232

TX

RX

COM

AD-50104@

Maintenance Panel ConnectionsFigure 6-34




APPENDIX AARINC 429 INTERFACES




IC-600IC-600 ARINCARINC 429429 PORTPORT ALLOCATIONSALLOCATIONS

IC-600INPUT PORT PINS DESCRIPTION

0 J2A-21,22 LRN1 RESERVED RESERVED2 J2A-23,24 MAINTENANCE COMPUTER (PLT ONLY)3 J2B-23,24 PRI MADC4 J2A-29,30 PRI AHRS5 J2B-29,30 TCAS6 J2A-31,32 SEC R DAU7 J2B-31,32 SEC L DAU8 J2A-41,42 PRI R DAU9 J2A-81,82 PRI L DAU10 J2A-43,44 SEC MADC11 J2A-83,84 SEC AHRS12 J2A-40,26 RESERVED13 J2B-13,26 WINDSHEAR14 J2A-27,28 RESERVED15 J2B-27,28 OS PFD

AP 0 J2A-33,34 AHRSAP 1 J2A-35,36 AHRS

IC-600OUTPUT PORT PINS DESCRIPTION

0 J2A-39,52 LRN1 J2A-37,38 DAU (IC-600 NO. 1 TO DAU NO. 1)




AH-800AH-800 ARINCARINC 429429 PORTPORT ALLOCATIONSALLOCATIONS

AH-800INPUT PORT PINS DESCRIPTION

1 J1B-K4,K5 SEC MADC2 J1B-J10,J11 PRI MADC

AH-800OUTPUT PORT PINS DESCRIPTION

1 J1B-G7,G8 PRI IC-6002 J1B-E5,E6 SEC IC-600,

AP IC-6003 J1B-K12,K13 WEATHER RADAR4 J1B-F14,F15 OPTIONAL LRN, DAU NO. 2

AZ-850AZ-850 ARINCARINC 429429 PORTPORT ALLOCATIONSALLOCATIONS

AZ-850OUTPUT PORT PINS DESCRIPTION

1 J1-60,61 PRI IC-600, SEC IC-6002 J1-63,64 OS FADEC, CS FADEC, HSCU3 J1-66,67 PRI COM, SEC COM, AHRS, WXR4 J1-68,69 STALL PROTECTION SYSTEM, ECS,

GPWS




DA-800DA-800 ARINCARINC 429429 PORTPORT ALLOCATIONSALLOCATIONS (for(for eacheach channel)channel)

DA-800INPUT PORT PINS DESCRIPTION

1 J1B-42,43 OS IC-600 (TO NO. 1 DAU),AHRU (TO NO. 2 DAU)

2 J1B-44,45 SHIP’S CLOCK (TO NO. 1 DAU)CABIN PRESSURE (TO NO. 2 DAU)

3 J1B-46,47 OS FADEC CH. A4 J1B-48,49 FUEL COMPUTER5 J2B-42,43 STALL WARNING SYSTEM6 J2B-44,45 OS FADEC CH. B

DA-800OUTPUT PORT PINS DESCRIPTION

1A J1B-40,41 RMU1B J2B-40,41 CMC

2A J1B-50,51 IC-6002B J2B-50,51 IC-600




APPENDIX BOPTIONAL FMS




FMS NAVIGATION COMPUTERNZ-2000


( ) RESERVED FOR GROWTH 121J1A-1( ) RESERVED FOR GROWTH -2

(B) ASCB PORT A ONSIDE (H) -4(B) ASCB PORT A ONSIDE (L) -30

( ) IT BATTERY CURRENT SENSE -5(I) TAG SYNC IN -6(I) CDU SYNC IN -7( ) BUFFERED POWER VALID (TEST) -8

( ) TESTIN2 -10 (24)----------------- TEST CONNECTOR( ) TESTIN1 -11 (24)----------------- TEST CONNECTOR(O) VERT TRACK AURAL ALRT (G/O) -12( ) RESERVED FOR GROWTH -13( ) RESERVED FOR GROWTH -14( ) RESERVED FOR GROWTH -15( ) RESERVED FOR GROWTH -16

(B) RS-232 FMS CPU DM REC -17 (24)----------------- TEST CONNECTOR(B) RS-232 FMS CPU DM XMT -3 (24)----------------- TEST CONNECTOR

( ) ADC VMO CONTROL OUT -18

(B) ASCB PORT B OFFSIDE (H) -20(B) ASCB PORT B OFFSIDE (L) -9

(I) TESTIN4 -21 (24)----------------- TEST CONNECTOR(I) SPARE DISC IN #17 -22(I) SPARE DISC IN #23 -23(I) SPARE FMS DISC IN #3 -24(O) SPARE FMS DISC OUT #3 -25( ) RESERVED FOR GROWTH -26( ) RESERVED FOR GROWTH -27(I) CDU VALID IN -28 (22)----------------- 120J1-i(O) INDEPENDENT OPERATION OUT -29(O) SPARE DISC OUT #15 121J1A-31




NAVIGATION COMPUTERNZ-2000 (cont)


(B) A-429 RCVR #20 (H) 121J1A-32(B) A-429 RCVR #20 (L) -19

(I) FLASH PROGRAM ENABLE IN -33 (24)----------------- TEST CONNECTOR

(B) RS-232 IOP CPU DM XMT -34 (24)----------------- TEST CONNECTOR(SEE J1B-69 FOR RCV PIN)

(I) TESTIN5 -35 (24)----------------- TEST CONNECTOR(I) TESTIN3 -37 (24)----------------- TEST CONNECTOR(O) SPARE FMS DISC OUT #4 -38(O) ONSIDE AUTO TUNING OUT -39( ) POWER SUPPLY TEST SIGNAL -40(I) INITIATED XFER-RECEIVE IN -41(I) SPARE DISC IN #15 -42( ) RESERVED FOR GROWTH -43( ) RESERVED FOR GROWTH -44

(B) ASCB PortA ONSIDE Ver B (H) -46(B) ASCB PortA ONSIDE Ver B (L) -58

(I) SDI #1 IN (IDENT3) -47 (24)----------------- SIGNAL GROUND

(B) ASCB PortB OFFSIDE Ver B (H)-48(B) ASCB PortB OFFSIDE Ver B (L)-36

(O) TAG SYNC OUT -50(O) CDU SYNC OUT -51(O) SPARE DISC OUT #16 -53(O) CDU MESSAGE OUT -54

(I) Analog In #1 (H) -56(I) Analog In #1 (L) -55

(I) TRUE REFERENCE SELECTED IN -57

(B) A-429 RCVR #19 (H) -59(B) A-429 RCVR #19 (L) 121J1A-45







(B) RS-232 CONFIG MOD RCVR -61 (24)----------------- 199J1-3(B) ARINC-429 GB#1 XMT (H) -62 (24)-T-S-----------S- 149J1-18(B) ARINC-429 GB#1 XMT (L) -49 (24)-T-S-----------S- 149J1-37

SHIELD GND ─────────────┘ └─── SHIELD GND

(B) A-429 RCVR #16 (H) -63(B) A-429 RCVR #16 (L) -77

(I) SPARE FMS DISC IN #5 -64(I) SPARE FMS DISC IN #6 -65

(B) A-429 XMTR #6 (H) -66(B) A-429 XMTR #6 (L) -79

(I) SPARE DISC IN #18 -67(I) SPARE DISC IN #24 -68(O) DEGRADED ACCURACY OUT -69(I) SPARE DISC IN #19 -70


(B) A-429 RCVR #18 (H) -73 (24)-T-S-----------S- C190J2A-39(B) A-429 RCVR #18 (L) -72 (24)-T-S-----------S- C190J2A-52


(O) REMOTE TUNING OUT -78(I) SPARE DISC IN #13 -80


(I) ILS*/MLS SELECT IN -82(I) SPARE DISC IN #16 -83

(I) SPARE DISC IN #12 -85(I) SPARE DISC IN #21 121J1A-86







(B) A-429 RCVR #17 (H) -89 (24)-T-S-----------S- 190J2A-39(B) A-429 RCVR #17 (L) -75 (24)-T-S-----------S- 190J2A-52


(B) A-429 RCVR #13 (H) -90 (24)-T-S-----------S- C9J1-68 MADC(B) A-429 RCVR #13 (L) -76 (24)-T-S-----------S- C9J1-69 #2


(B) RS422 CDU CNTL REC (H) -92 (22)-T-S-----------S- 120J1-P(B) RS422 CDU CNTL REC (L) -52 (22)-T-S-----------S- 120J1-R


(I) SPARE FMS DISC IN #4 -93(I) SPARE DISC IN #14 -95(O) APPROACH SENSITIVITY OUT -96(I) SPARE DISC IN #22 -97(O) NAV COMPUTER VALID OUT -98(I) SPARE DISC IN #20 -99(O) OFFSIDE AUTO TUNING OUT -100

(B) ASCB PortA ONSIDE Clock (H) -102(B) ASCB PortA ONSIDE Clock (L) -87

(B) RS422 CDU CNTL XMT (H) -103 (22)-T-S-----------S- 120J1-U(B) RS422 CDU CNTL XMT (L) -104 (22)-T-S-----------S- 120J1-V


(B) A-429 RCVR #15 (H) -105 (24)-T-S-----------S- RESERVED(B) A-429 RCVR #15 (L) -91 (24)-T-S-----------S- FOR AFIS


(B) RS-232 SPARE XMT IOP 121J1A-106






(B) RS422 CDU DAT REC (H) 121J1B-1 (22)-T-S-----------S-- 120J1-M(B) RS422 CDU DATA REC (L) -14 (22)-T-S-----------S-- 120J1-N


(I) SPARE FMS DISC IN #7 -2

(B) ARINC-429 GB#2 XMT (H) -3 (24)-T-S-----------S-- 193RMP-6A(B) ARINC-429 GB#2 XMT (L) -15 (24)-T-S-----------S-- 193RMP-6B


(B) A-429 XMTR #3 (H) -4 (24)-T-S-----------S-- RESERVED(B) A-429 XMTR #3 (L) -16 (24)-T-S-----------S-- FOR AFIS


(O) OFFSET ALERT OUT -5(O) SPARE DISC OUT #12 -6(O) SPARE DISC OUT #14 -7(P) CONFIG MODULE POWER +5V -8 (22)----------------- 199J1-1( ) TEST SIGNAL +14V -9

(P) Power +28V -10 (22)----------------- (P) Power +28v -11 (22)----------------- 5A CKT BRKR

(P) Power +28V -12 (22)----------------- 121J1B-52

(B) RS422 CDU DATA XMT (H) -13 (24)-T-S-----------S- 120J1-S(B) RS422 CDU DATA XMT (L) -26 (24)-T-S-----------S- 120J1-T


(B) A-429 RCVR #1 (H) -17 (24)-T-S-----------S- 149J1-38(B) A-429 RCVR #1 (L) -18 (24)-T-S-----------S- 149J1-39


(B) A-429 RCVR #2 (H) -19 (24)-T-S-----------S- OMEGA(B) A-429 RCVR #2 (L) -20 (24)-T-S-----------S- SENSOR


( ) TEST SIGNAL -14V -22

(P) Power Return -23 (22)----------------- (P) Power Return -24 (22)----------------- DC GROUND(P) Power Return 121J1B-25 (22)-----------------






(B) A-429 RCVR #14 (H) 121J1B-27(B) A-429 RCVR #14 (L) -54

(B) RS422 DATA LDR CLK XMT (H) -29 (22)-T-S-----------S- 123J1-K(B) RS422 DATA LDR CLK XMT (L) -28 (22)-T-S-----------S- 123J1-J


(B) RS422 GENERAL BUS XMT (H) -31 (24)-T-S-----------S- 144J1-AA, C144J1-AA(B) RS422 GENERAL BUS XMT (L) -30 (24)-T-S-----------S- 144J1-t, C144J1-t


(B) A-429 RCVR #7 (H) -33(B) A-429 RCVR #7 (L) -47

(B) A-429 RCVR #3 (H) -34(B) A-429 RCVR #3 (L) -21

(I) SEC RADIO MANUAL TUNE IN -35

( ) TEST SIGNAL +5V -36(P) Chassis Ground -37 (22)----------------- CHASSIS GROUND(P) Chassis Ground -38 (22)----------------- CHASSIS GROUND(P) Signal Ground -39 (22)----------------- SIGNAL GROUND(I) SDI #3 IN (IDENT1) -40(B) RS-232 SPARE REC IOP -41(I) SPARE FMS DISC IN #8 -42

(B) A-429 RCVR #5 (H) -44 (24)-T-S-----------S- C1J1B-K12 AHRS(B) A-429 RCVR #5 (L) -43 (24)-T-S-----------S- C1J1B-K13 #2


(B) RS422 DATA LDR DATA XMT (H) -45 (22)-T-S-----------S- 123J1-H(B) RS422 DATA LDR DATA XMT (L) -58 (22)-T-S-----------S- 123J1-G


(B) RS422 XMTR #2 (H) -46(B) RS422 XMTR #2 (L) -32

( ) SIGNAL GND FOR C.M. 121J1B-48 (22)----------------- 199J1-2,TEST CONNECTOR






(B) A-429 RCVR #4 (H) 121J1B-49 (24)-T-S-----------S- 1J1B-K12 AHRS(B) A-429 RCVR #4 (L) -50 (24)-T-S-----------S- 1J1B-K13 #1


( ) TEST SIGNAL VS -51

( ) Aircraft Battery +28V -52 (22)----------------- TO 28 VDC FMS MAINPOWER, 121J1B-10,-11,-12

(B) RS-232 CFG MOD XMT (RSRVD) -53

(I) IDENT4 (PRIVATE MODE) -55

(B) RS422 CDU CLOCK XMT (H) -57 (22)-T-S-----------S- 120J1-W(B) RS422 CDU CLOCK XMT (L) -56 (22)-T-S-----------S- 120J1-X


(B) A-429 RCVR #6 (H) -59(B) A-429 RCVR #6 (L) -60

(I) PERF COMPUTER INSTALLED -61

(B) A-429 RCVR #8 (H) -62(B) A-429 RCVR #8 (L) -75


(I) DATA LOADER CONNECTED IN -65 (24)----------------- 123J1-E, 149J1-12(I) MAINTENANCE TEST ENABLE IN -66

(B) A-429 RCVR #12 (H) -67 (24)-T-S-----------S- 9J1-68 MADC(B) A-429 RCVR #12 (L) -68 (24)-T-S-----------S- 9J1-69 #1


(B) RS-232 IOP CPU DM REC -69 (24)----------------- TEST CONNECTOR(SEE J1A-34 FOR XMT PIN)

(B) RS422 RCVR #5A (H) -71(B) RS422 RCVR #5A (L) 121J1B-70






(B) RS422 DME SEC RCV (H) 121J1B-73 (24)-T-S-----------S- C164J1A-57(B) RS422 DME SEC RCV (L) -74 (24)-T-S-----------S- C164J1A-44


(O) LATERAL WAYPOINT ALERT OUT -76(I) WEIGHT ON WHEELS (WOW) IN -77 (24)----------------- GND = WOW

(B) RS422 RCVR #5B (H) -79(B) RS422 RCVR #5B (L) -78

(B) RS422 DME PRI RCVR (H) -80 (24)-T-S-----------S- 164J1A-57(B) RS422 DME PRI RCVR (L) -81 (24)-T-S-----------S- 164J1A-44


(I) SDI #2 IN (IDENT2) -84

(B) RS422 DATA LDR DATA REC (H) -86 (22)-T-S-----------S- 123J1-T(B) RS422 DATA LDR DATA REC (L) -72 (22)-T-S-----------S- 123J1-S


(B) A-429 RCVR #10 (H) -87(B) A-429 RCVR #10 (L) -101

( ) TEST SIGNAL +5 -88(O) TRUE/MAGNETIC SELECTED OUT -89

(I) INITIATED XFER-TRANSMIT IN -91( ) RESERVED FOR GROWTH -92(O) DEAD RECKONING OUT -93

(B) RS422 VOR SEC RCVR (H) -94 (24)-T-S-----------S- C164J1B-89(B) RS422 VOR SEC RCVR (L) -95 (24)-T-S-----------S- C164J1A-59


(B) RS422 VOR PRI RCVR (H) -96 (24)-T-S-----------S- 164J1B-89(B) RS422 VOR PRI RCVR (L) -82 (24)-T-S-----------S- 164J1A-59


(B) RS422 XMTR #3 (H) -97(B) RS422 XMTR #3 (L) 121J1B-83






(B) A-429 XMTR #5 (H) 121J1B-98(B) A-429 XMTR #5 (L) -85

(B) A-429 XMTR #4 (H) -99 (24)-T-S-----------S- 190J2A-21, GPWS│ │ C190J2A-21

(B) A-429 XMTR #4 (L) -100 (24)-T-S-----------S- 190J2A-22, GPWS│ │ C190J2A-22


(I) PRI RADIO MANUAL TUNE IN -102

(B) A-429 RCVR #9 (H) -103(B) A-429 RCVR #9 (L) -90

(O) VERT WAYPOINT ALERT OUT -104(I) SPARE DISC IN #13 -105( ) RESERVED FOR GROWTH 121J1B-106




FMS CDUCD-810


(P) +28 VDC POWER 120J1-B (20)--------------------- FIG. 6-1A(P) POWER RETURN -C (20)--------------------- POWER GND(P) PANEL LIGHTING RETURN -D (22)--------------------- LIGHTING GND(P) 28V ANNUNC LIGHTING -F (20)--------------------- FIG. 6-1A(P) CHASSIS GND -G (20)--------------------- CHASSIS GND(P) ANNUNC LIGHTING RETURN -H (22)--------------------- LIGHTING GND(P) 5V KEYBOAD PANEL LIGHTING -J (22)--------------------- ACFT 5V

LIGHTING

(B) RS422 XMTR (H) -M (22)---T-S-----------S--- 121J1B-1(B) NAV CMPTR - DATA (L) -N (22)---T-S-----------S--- 121J1B-14


(B) RS422 XMTR (H) -P (22)---T-S-----------S--- 121J1A-92(B) NAV CMPTR - CNTL (L) -R (22)---T-S-----------S--- 121J1A-52


(B) RS422 RCVR (H) -S (22)---T-S-----------S--- 121J1B-13(B) NAV CMPTR - DATA (L) -T (22)---T-S-----------S--- 121J1B-26


(B) RS422 RCVR (H) -U (22)---T-S-----------S--- 121J1A-103(B) NAV CMPTR - CNTL (L) -V (22)---T-S-----------S--- 121J1A-104


(B) RS422 RCVR (H) -W (22)---T-S-----------S--- 121J1B-57(B) NAV CMPTR - CLK (L) -X (22)---T-S-----------S--- 121J1B-56


(O) CDU VALID (GND/OPEN) -i (22)--------------------- 121J1A-28(O) R PHOTO SENSOR OUT -m(O) L PHOTO SENSOR OUT -n(I) DIM CALIBRATION -q(I) LAMP TEST -s

(I) ANNUNC LIGHTING BRT/DIM -v (22)--------------------- FIG. 6-1A(OPEN/28V)

(I) ANNUNC LIGHTING DIM 120J1-w (22)--------------------- ACFT ANNUNCCONTROL (0 - 28 V) DIM CONTROL




FMS DATA LOADERDL-900


(P) +28 VDC POWER RETURN 123J1-B (20)--------------------- POWER GND(P) +28 VDC POWER -C (20)--------------------- FIG. 6-1A(O) LOADER CONNECTED LEFT -E (22)--------------------- 121J1B-65,

149J1-12

(B) RS422 RCVR (L) -G (22)---T-S-----------S--- 121J1B-58(B) DATA (H) -H (22)---T-S-----------S--- 121J1B-45


(B) RS422 RCVR (L) -J (22)---T-S-----------S--- 121J1B-28(B) CLOCK (H) -K (22)---T-S-----------S--- 121J1B-29


(B) RS422 TXMITR (L) -S (22)---T-S-----------S--- 121J1B-72(B) DATA (H) -T (22)---T-S-----------S--- 121J1B-86


(B) RS232 RCV LINE SIG DET -U (22)-------------------- MAINT(B) RS232 SIGNAL GND -V (22)--------------------(B) RS232 DATA SET READY -W (22)-------------------- TEST(B) RS232 CLEAR TO SEND -X (22)--------------------(B) RS232 REQUEST TO SEND -Y (22)-------------------- CONN

(B) RS232 RCV DATA -Z (22)---T-S-----------S--- 149J1-2(B) RS232 XMIT DATA -a (22)---T-S-----------S--- 149J1-3


(P) CHASSIS GND 123J1-b (22)--------------------- CHASSIS GND




FMS CONFIGURATION MODULEIM-803


(P) +5 VDC POWER 199J1-1 (22)-------------------- 121J1B-8(P) DC POWER RETURN -2 (22)-------------------- 121J1B-48,

TEST CONNECTOR(O) DATA XMIT -3 (24)-------------------- 121J1A-61




APPENDIX CPRIMUS 870/660/880 OPTIONS




ANTENNA AND RECEIVER/TRANSMITTER UNITWU-870


28 V DC POWER 59J1-A (20)------------------- 28 VDC Ckt Brkr,-B (20)------------------- 7.5 Amp, 61J1-D

POWER GROUND -X (20)------------------- DC GND-W (20)------------------- DC GND

#2 CONTROL BUS H -aL -b

#1 CONTROL BUS H -c (24)-T-S------------S-- 61J1-AL -d (24)-T-S------------S-- 61J1-B

SHIELD GND ────────┘ └── 61J1-M

CONTROL BUS SHIELD -p (24)------NCREMOTE ON -U (24)------------------- 61J1-RWEIGHT ON WHEELS -T (24)------------------- ACFT WOW SWITCHTRANSMIT ON -C

-V RESERVED-F FOR-Y ANALOG-E AIRSPEED-S INPUT

ARINC 429 ADC INPUT INSTALLED -H (24)------------------- SIG GND

STABILIZATION INPUT H -K (24)-T-S------------S-- 1J1B-K12(ARINC 429) L -L (24)-T-S------------S-- 1J1B-K13

│ │ (FIG 6-10)SHIELD GND ────────┘ └── SHIELD GND

REACT COMPENSATION OVERRIDE -R (24)------------------- SIG GND, 59J1-TGND FOR 200 MV/DEG -P

-J-M-N

STABILIZATION 400 HZ 26V -ZREF INPUT 115V -D

COM -G

LEFT EFIS CONTROL BUS H -m (24)-T-S------------S-- 190J2A-17L 59J1-n (24)-T-S------------S-- 190J2A-18SHIELD GND ────────┘ └── SHIELD GND




ANTENNA AND RECEIVER/TRANSMITTER UNIT (cont)WU-870


ARINC 429 AIR DATA INPUT H 59J1-t (24)-T-S------------S-- MADCL -r (24)-T-S------------S-- MADC

RIGHT EFIS CONTROL BUS H -e (24)-T-S------------S-- C190J2A-17L -f (24)-T-S------------S-- C190J2A-18


-q (24)------NC

LEFT EFIS PICTURE BUS H -g (24)-T-S-------------S-- 130J1-77,│ │ 131J1-77 FIG.6-5

L -h (24)-T-S-------------S-- 130J1-64,│ │ 131J1-78


CENTER PICTURE BUS H -iL -j

RIGHT EFIS PICTURE BUS H -k (24)-T-S------------S-- C130J1-77,│ │ C131J1-77 FIG.

L 59J1-s (24)-T-S------------S-- C130J1-64, 6-6│ │ C131J1-78





PILOT’S WEATHER RADAR CONTROLLERWC-870


SERIAL CONTROL (HI) 61J1-A (24)----T-S--------S-- 59J1-cSERIAL CONTROL (LO) -B (24)----T-S--------S-- 59J1-d

│ └── SHIELD GNDSPARE -C ------NC │28 V DC INPUT -D (22)------│----------- +28 VDC PWR, 7.5

│ Amps, 59J1-B28 V DC GND -E (22)------│----------- DC PWR GNDCHASSIS GND -F (22)------│----------- CHASSIS GNDEDGE LIGHTING 28 V DC (+) -G ------NC │EDGE LIGHTING 5 V AC/DC (+) -H (24)------│----------- 5V PNL LIGHTINGEDGE LIGHTING RETURN -J (24)------│----------- LIGHTING GNDANNUNCIATOR DIMMING -K (24)------│----------- DAY NIGHT LOGICSPARE -L ------NC │CONTROL BUS SHIELD GND -M (24)-----─┘SPARE -N ------NCFSB1 -P (24)------------------ FIG 6-2REMOTE ON -R (24)------------------ 59J1-U

FSB2 -S ------NCOFF IN -T ------NCOFF OUT 61J1-U ------NC




WEATHER RADAR RECEIVER/TRANSMITTERWU-660/880

IOPB Function Connector Pin Connects To

(O) LEFT WXPD BUS (P) 59J1-1 (24)-T-S-----------S-- FIG. 6-5(O) LEFT WXPD BUS (N) -2 (24)-T-S-----------S-- FIG. 6-5

SHIELD──────────────┘ └── SHIELD

RESERVED -3 -----NCRESERVED -4 -----NC

(O) RIGHT WXPD BUS (P) -5 (24)-T-S-----------S-- FIG. 6-6(O) RIGHT WXPD BUS (N) -6 (24)-T-S-----------S-- FIG. 6-6

SHIELD──────────────┘ └── SHIELD

RESERVED -7 -----NCRESERVED -8 -----NCRESERVED -9 -----NCRESERVED -10 -----NC

(I) REMOTE ON -11 (22)------------------ 61J1-R

RESERVED -12 -----NC

(P) +27.5 V DC PRI POWER -13 (22)------------------ FIG. 6-1(P) +27.5 V DC PRI POWER -14 (22)------------------ FIG. 6-1(P) POWER GROUND -15 (22)------------------ DC GND(P) POWER GROUND -16 (22)------------------ DC GND

RESERVED -17 -----NCRESERVED -18 -----NCRESERVED -19 -----NCRESERVED -20 -----NCRESERVED -21 -----NC

(I) ARINC 429 AHRS (P) -22 (24)-T-S-----------S-- FIG. 6-10(I) ARINC 429 AHRS (N) -23 (24)-T-S-----------S-- FIG. 6-10

SHIELD──────────────┘ └── SHIELDRESERVED -24 -----NCRESERVED -25 -----NCRESERVED -26 -----NCRESERVED -27 -----NCRESERVED 59J1-28 -----NC




WEATHER RADAR RECEIVER/TRANSMITTER (cont)WU-660/880


RESERVED 59J1-29 -----NCLEFT EFIS CONTROL BUS (H) -30 (24)-T-S-----------S-- 190J2A-17LEFT EFIS CONTROL BUS (L) -31 (24)-T-S-----------S-- 190J2A-18

SHIELD──────────────┘ └── SHIELD

RIGHT EFIS CONTROL BUS (H) -32 (24)-T-S-----------S-- C190J2A-17RIGHT EFIS CONTROL BUS (L) -33 (24)-T-S-----------S-- C190J2A-18

SHIELD──────────────┘ └── SHIELD

RESERVED -34 -----NCRESERVED -35 -----NCRESERVED -36 -----NCRESERVED -37 -----NCRESERVED -38 -----NCRESERVED -39 -----NCRESERVED -40 -----NCRESERVED -41 -----NCRESERVED -42 -----NC

(I) ARINC 429 AIR DATA (P) -43 (24)-T-S-----------S-- FIG. 6-11(I) ARINC 429 AIR DATA (N) -44 (24)-T-S-----------S-- FIG. 6-11

SHIELD──────────────┘ └── SHIELD

RESERVED -45 -----NCRESERVED -46 -----NCRESERVED -47 -----NCRESERVED -48 -----NCRESERVED -49 -----NCRESERVED -50 -----NCRESERVED -51 -----NCRESERVED -52 -----NCRESERVED -53 -----NCRESERVED -54 -----NCRESERVED -55 -----NCRESERVED -56 -----NCRESERVED -57 -----NCRESERVED -58 -----NCRESERVED -59 -----NCRESERVED -60 -----NCRESERVED -61 -----NCRESERVED -62 -----NCRESERVED -63 -----NCRESERVED -64 -----NCRESERVED -65 -----NCRESERVED -66 -----NCRESERVED 59J1-67 -----NC




WEATHER RADAR RECEIVER/TRANSMITTER (cont)WU-660/880


RESERVED 59J1-68 -----NCRESERVED -69 -----NCRESERVED -70 -----NC

(B) LEFT SCI BUS (P) -71 (24)-T-S-----------S-- 61J1-A(B) LEFT SCI BUS (N) -72 (24)-T-S-----------S-- 61J1-B

SHIELD──────────────┘ └── 61J1-M

RESERVED -73 -----NCRESERVED -74 -----NCRESERVED -75 -----NCRESERVED -76 -----NCRESERVED -77 -----NCRESERVED -78 -----NCRESERVED -79 -----NCRESERVED -80 -----NCRESERVED -81 -----NCRESERVED -82 -----NCRESERVED -83 -----NCRESERVED -84 -----NC

(I) ALT/AIR/STAB CONFIG 0 -85 ---------------------- SIG GND(I) ALT/AIR/STAB CONFIG 1 -86 -----NC(I) ALT/AIR/STAB CONFIG 1 -87 -----NC(I) ALT/AIR/STAB CONFIG 1 -88 -----NC

RESERVED -89 -----NC(I) WEIGHT ON WHEELS -90 ---------------------- A/C WOW INPUT

(P-880 ONLY)RESERVED -91 -----NCRESERVED -92 -----NCRESERVED -93 -----NCRESERVED -94 -----NC

(I) TEXT FAULTS -95 (22)------------------ SIG GND

RESERVED -96 -----NCRESERVED -97 -----NCRESERVED -98 -----NCRESERVED -99 -----NCRESERVED -100 -----NCRESERVED -101 -----NCRESERVED -102 -----NCRESERVED -103 -----NCRESERVED 59J1-104 -----NC




PILOT’S WEATHER RADAR CONTROLLERWC-650/880


SERIAL CONTROL (HI) 61J1-A (24)----T-S--------S-- 59J1-71SERIAL CONTROL (LO) -B (24)----T-S--------S-- 59J1-72

│ └── SHIELD GNDSPARE -C ------NC │28 V DC INPUT -D (22)------│----------- +28 VDC PWR28 V DC GND -E (22)------│----------- DC PWR GNDCHASSIS GND -F (22)------│----------- CHASSIS GNDEDGE LIGHTING 28 V DC (+) -G ------NC │EDGE LIGHTING 5 V AC/DC (+) -H (24)------│----------- 5V PNL LIGHTINGEDGE LIGHTING RETURN -J (24)------│----------- LIGHTING GNDANNUNCIATOR DIMMING -K (24)------│----------- DAY NIGHT LOGICSPARE -L ------NC │CONTROL BUS SHIELD GND -M (24)-----─┘SPARE -N ------NCFSB1 -P (24)------------------ FIG 6-2REMOTE ON -R (24)------------------ 59J1-11

FSB2 -S ------NCOFF IN -T ------NCOFF OUT 61J1-U ------NC




APPENDIX DDUAL RAD ALT OPTION






SPARE 20J1-ASPARE -BSPARE -CTEST INHIBIT -DOUTPUT TEST -E ┐TRACK INVALID -F │ ------NCSPARE -G │SPARE -H │SPARE -J │SPARE -K │TRIP NO. 4 (200 FT) -L │ (24)---------------- STALL PROTECTION

│ COMPUTER+/- 15 V DC COMMON -M │ ------NCOUTPUT COMMON -N └(24)-T-S-----------S-- 190J2A-50,

│ │ 193RMP-2JALT TRIP COMMON -P (24)---│-----------│-- DC GNDTRIP NO. 3 (50 FT) -R ------NC│ │SPARE -S │ │TEST* -T (24)----│-----------│-- 190J2A-97TRIP NO. 1 (1200 FT) -U ------NC│ │TRIP NO. 2 (1500 FT) -V (24)----│-----------│-- AURAL WARNING

│ │ SYSTEMALT OUTPUT (EH) -W (24)--T-S-----------S-- 190J2A-51

│ │SHIELD GND ──────────┤ ├── SHIELD GND

AUX OUTPUT (H) -X (24)--T-S-----------S-- 193RMP-2HRAD. ALT VALID (28 V/OPEN) -Y (24)------------------- 190J2A-49

193RMP-2K

+15 V DC -Z ------NC-15 V DC -a ------NCPOWER GND -b (22)------------------- DC GND+28 V DC 20J1-c (22)------------------- 1.5 AMP CIRCUIT

BREAKERTRANSMIT 20J2 * ------ô---------- 21J1 COAX TO TRANSMIT

------┘ ANTENNARECEIVE 20J3 * ------ô---------- 22J1 COAX TO TRANSMIT

------┘ ANTENNA






SPARE C20J1-ASPARE -BSPARE -CTEST INHIBIT -DOUTPUT TEST -E ┐TRACK INVALID -F │ ------NCSPARE -G │SPARE -H │SPARE -J │SPARE -K │TRIP NO. 4 (200 FT) -L │(24)------------------ STALL PROTECTION

│ COMPUTER+/- 15 V DC COMMON -M │ ------NCOUTPUT COMMON -N └(24)-T-S-----------S-- C190J2A-50

│ │ 193RBP-3BALT TRIP COMMON -P (24)---│-----------│-- DC GNDTRIP NO. 3 (50 FT) -R ------NC│ │SPARE -S │ │TEST* -T (24)----│-----------│-- C190J2A-97TRIP NO. 1 (1200 FT) -U ------NC│ │TRIP NO. 2 (1500 FT) -V (24)----│-----------│-- AURAL WARNING

│ │ SYSTEMALT OUTPUT (EH) -W (24)--T-S-----------S-- C190J2A-51

│ │SHIELD GND ──────────┤ ├── SHIELD GND

AUX OUTPUT (H) -X (24)--T-S-----------S-- 193RBP-3ARAD. ALT VALID (28 V/OPEN) -Y (24)------------------- C190J2A-49

193RBP-3C

+15 V DC -Z ------NC-15 V DC -a ------NCPOWER GND -b (22)------------------- DC GND+28 V DC C20J1-c (22)------------------- 1.5 AMP CIRCUIT

BREAKERTRANSMIT C20J2 * ------ô---------- C21J1 COAX TO TRANSMIT

------┘ ANTENNARECEIVE C20J3 * ------ô---------- C22J1 COAX TO TRANSMIT

------┘ ANTENNA




APPENDIX EGPS OPTION




APPENDIX EGNSSU


GNSSU FAULT 149J1-1RS-232 TRANSMIT -2 (24) -T-S-----------S--- 123J1-ZRS-232 RECEIVE -3 (24) -T-S-----------S--- 123J1-a


429 IN DATA LOADER (H) -4 ------NC SEE NOTE 1429 IN DATA LOADER (L) -15 ------NC

AIR DATA REF INPUT #1 (H) -6 (24) -T-S-----------S--- 9J1-68 FIG.AIR DATA REF INPUT #1 (L) -7 (24) -T-S-----------S--- 9J1-69 6-11


INPUT DISCRETE RETURN -8 (24)-------------------- 149J1-21

TIME MARK #2 (H) -9TIME MARK #2 (L) -22

AIR DATA REF INPUT #2 (H) -10 (24) -T-S----------S--- C9J1-68 FIG.AIR DATA REF INPUT #2 (L) -11 (24) -T-S----------S--- C9J1-69 6-11

SHIELD GND ───────┘ └─── SHIELD GND

DATA LOAD MODE DISCRETE -12 (24)------------------- 123J1-E,121J1B-65


GEN PURPOSE/DIFF 429 #2 (H) -16GEN PURPOSE/DIFF 429 #2 (L) -17

429 IN IRS/FMS #1 (H) -18 (24)-T-S-----------S--- 121J1A-62429 IN IRS/FMS #1 (L) -37 (24)-T-S-----------S--- 121J1A-49



429 HS/LS SELECT -21 (24)------------------- 149J1-8GEN PURPOSE/DIFF 429 #1 (H) -23GEN PURPOSE/DIFF 429 #1 (L) 149J1-41

NOTE 1: THE DL-900 DATA LOADER CONNECTS TO THE RS-232 PORT, PINS 2 & 3.




GNSSU (cont)


429 OUT #2 (H) 149J1-24429 OUT #2 (L) -25

429 IN IRS/FMS #2 (H) -26429 IN IRS/FMS #2 (L) -27

AIR/GROUND -28 (24)------------------- WOW SWITCH(GND = WOW)

429 OUT #3 (H) -29429 OUT #3 (H) -30

429 IN #3 (H) -31429 IN #3 (H) -32

CHASSIS GND -33 (24)------------------- CHASSIS GND

+28 V DC RETURN -34 (20)------------------- DC POWER GND+28 V DC POWER -35 (20)------------------- ACFT +28 VDC

(3 AMP BREAKER)

SDI PIN #1 -36 (24)------------------- SIGNAL GNDSDI PIN #2 -5

429 OUT #1 (H) -38 (24)-T-S-----------S--- 121J1B-17429 OUT #1 (H) -39 (24)-T-S-----------S--- 121J1B-18


AIR DATA 419/429 SELECT 149J1-40


TABLE OF CONTENTS - SECTION 4

SECTION/PARAGRAPH/TITLE PAGE


4 MAINTENANCE PRACTICES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1

1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1

2. Equipment and Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-3

3. Procedure for the AH-800 Attitude Heading Reference Unit (AHRU) . . . . . . . . 4-4

4. Procedure for the AHRU Mounting Tray Fan Filter . . . . . . . . . . . . . . . . . . . . . 4-5

5. Procedure for the AHRU Mounting Tray Fan . . . . . . . . . . . . . . . . . . . . . . . . . . 4-6

6. Procedure for the AHRU Mounting Tray . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-8

7. Procedure for the AT-860 ADF Antenna . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-9

8. Procedure for the AT-910 TCAS Directional Antenna . . . . . . . . . . . . . . . . . . 4-10

9. Procedure for the AV-850A Audio Control Unit . . . . . . . . . . . . . . . . . . . . . . . 4-12

10. Procedure for the AZ-850 Micro Air Data Computer (MADC) . . . . . . . . . . . . . 4-19

11. Procedure for the BL-870/871 Bezel Assembly . . . . . . . . . . . . . . . . . . . . . . . 4-20

12. Procedure for the CD-810 Control Display Unit . . . . . . . . . . . . . . . . . . . . . . 4-21

13. Procedure for the CD-850 Clearance Delivery Control Head (CDH) . . . . . . . . 4-21

14. Procedure for the DA-800 Data Acquisition Unit (DAU) . . . . . . . . . . . . . . . . . 4-23

15. Procedure for the DC-550 Display Controller . . . . . . . . . . . . . . . . . . . . . . . . 4-24

16. Procedure for the DL-900 Data Loader . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-25

17. Procedure for the DU-870 Display Units . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-26

18. Procedure for the FX-600 Thin Flux Valve . . . . . . . . . . . . . . . . . . . . . . . . . . 4-28

19. Procedure for the GC-550 Guidance Control Unit . . . . . . . . . . . . . . . . . . . . . 4-43

20. Procedure for the Global Navigation System Sensor Unit (GNSSU) . . . . . . . 4-44

21. Procedure for the IC-600 Integrated Avionics Computer (IAC) . . . . . . . . . . . 4-45

22. Procedure for the IM-803 Installation Module . . . . . . . . . . . . . . . . . . . . . . . . 4-47

23. Procedure for the MM-260 AHRS Memory Module . . . . . . . . . . . . . . . . . . . . . 4-49

24. Procedure for the NZ-2000 FMS Navigation Computer . . . . . . . . . . . . . . . . . 4-50

25. Procedure for the PC-400 Autopilot Controller . . . . . . . . . . . . . . . . . . . . . . . 4-54

26. Procedure for the RCZ-851(X) Integrated Communications Unit . . . . . . . . . . 4-55

27. Procedure for the RM-855 Radio Management Unit (RMU) . . . . . . . . . . . . . . 4-56

28. Procedure for the RNZ-851(X) Integrated Navigation Unit . . . . . . . . . . . . . . . 4-58

29. Procedure for the RNZ-851/RCZ-851 Strap Board Assembly . . . . . . . . . . . . . 4-62

30. Procedure for the RT-300 Radio Altimeter Receiver Transmitter . . . . . . . . . . 4-63

31. Procedure for the RT-910 TCAS Computer Unit . . . . . . . . . . . . . . . . . . . . . . 4-65

32. Procedure for the SM-200 Servo Drive and SB-201 Drum and Bracket

Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-66

33. Procedure for the WC-6X0/8X0 Weather Radar Controller . . . . . . . . . . . . . . . 4-68

34. Procedure for the WU-6X0/8X0 Antenna and Receiver Transmitter Unit

(RTA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-69

Page TC4-122-05-14 Nov 1/1996Use or disclosure of information on this page is subject to the restrictions on the title page of this document.

TABLE OF CONTENTS - SECTION 4 (Cont)

List of Illustrations

FIGURE/TITLE PAGE


Figure 4-1. Fan Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-7

Figure 4-2. AV-850A Audio Control Unit Adjustment Locations . . . . . . . . . . . . . . . . . . . . . 4-18

Figure 4-3. Nomograph . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-32

Figure 4-4. Checklist Loading Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-46

Figure 4-5. COM Unit Adjustment Locations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-56

Figure 4-6. NAV Unit Adjustment Locations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-59

Figure 4-7. RT-300 Zero Adjustment Cable . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-64

Figure 4-8. Typical PRIMUS® 660/880 Stabilization Trim Mode Entry Page . . . . . . . . . . . . 4-73

Figure 4-9. Typical PRIMUS® 660/880 Stabilization Trim Adjustment Page . . . . . . . . . . . . 4-74

List of Tables

TABLE/TITLE PAGE

Table 4-1. AV-850A Audio Control Unit Adjustments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-17

Table 4-2. Aircraft Alignment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-31

Table 4-3. Aircraft Alignment Example 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-33





SECTION 4MAINTENANCE PRACTICES

1. General

This section provides instructions for removing, reinstalling, and adjusting each line replaceableunit (LRU) of the PRIMUS® 1000 Integrated Avionics System that has been previously installedby the aircraft manufacturer or completion center. Where applicable, instructions for replacinglamps, knobs and setscrews are included. Adjustment information is called out as required.

CAUTIONS: 1. SHOULD ANY INSTALLATION CRITICAL CASES ARISE WITH THEREINSTALLATION OF ANY UNIT, YOU MUST COMPLY 100 PERCENTWITH THE INSTRUCTION.

2. TO PREVENT DAMAGE TO EQUIPMENT, TURN AIRCRAFT POWER OFFWHEN REMOVING OR INSTALLING LRUs.

The following paragraphs describe general information when removing or installing antennas:

NOTE: For all antennas not supplied by Honeywell, removal and installation should be inaccordance with manufacturer’s installation instructions.

A. Antenna Weather Protection

(1) Some antennas require gaskets, and others have O-rings. When reinstallingantennas, new gaskets or O-rings should be used.

(2) A weather sealant should be applied around the periphery of the antenna base toprevent seepage of water and condensation and preclude corrosion. If a sealant oraerodynamic smoother is used around the periphery of the antenna base, it shouldbe applied after the antenna has been bolted down. The sealant used should benon-adhering to allow the antenna to be removed at a later time, if necessary.Chromatic tape is recommended.

NOTE: When mounting antennas on a pressurized fuselage, aleveling and sealing compound such as Product Research No.870B-1/2 aerodynamic smoother should be used between theentire mounting surface of the antenna and the fuselage. Useof this compound, in addition to the installation gasket, willcompensate for surface irregularities and voids between theantenna and the fuselage. A mold releasing agent may beused on the fuselage prior to installation to prevent theleveling compound from adhering to the fuselage.

(3) To prevent water seepage on top mounted antennas, it may be necessary to applySilastic sealant (RTV-3145 or equivalent) to the mounting screw heads.



B. Antenna Hardware

(1) Clean the airframe at the antenna mounting area to remove any foreign material.

(2) Because of the insulation qualities of gaskets and leveling compounds, the mountingscrews are required to provide the electrical bonding between the antennas and theaircraft (typically 15 milliohms or less is required). Therefore, the technician doingthe reinstallation must be sure that any hardware being reused is clean and free ofcorrosion. If in doubt, use new hardware.

(3) Gaskets and O-rings deform during initial installation. While it is possible to reusegaskets and O-rings, it is highly recommended that new gaskets or O-rings be used.

C. General Antenna Removal Instructions

NOTE: These procedures apply to all antennas. To prevent damage to theantennas, do not apply pressure to or pry on plastic housings.

(1) Pull the appropriate circuit breakers.

(2) After removing and saving the hardware, cut the bond line of any installer-appliedsealant between the antenna and the aircraft skin.

(3) Pull the antenna away from the aircraft skin far enough to disconnect the cableconnector(s).



2. Equipment and Materials

Augat, Part No. T-114-1, IC puller is used as a switch pushbutton puller when replacing lampson the GC-550 Guidance Control Unit.

• HMN 97D0878, HAZARD CODE 210DRetaining compound - Loctite Assure No. 425 surface curing threadlocker, Loctite Corp,Newington, CT (Used on controller knob setscrews)

Refer to the applicable leading particulars table in SECTION 2 of this manual for replacementgaskets, lamps, knobs, and setscrew part numbers.

Uploading/Downloading of the checklist files requires the following:

• IBM compatible laptop personal computer (PC)

• IAC to PC adapter harness, Honeywell Part No, T-336238-2.

Reinstallation of the mounting tray for the AH-800 AHRU requires the use of the leveling device,Honeywell Part No. UG5046, and Embraer-fabricated yaw-axis alignment tool.

The AHRS flux valve calibration procedure and mounting tray leveling procedure requires thefollowing:

• 50-pin maintenance connector to PC adapter cable, Honeywell Part No. T-336238. Refer tothe Embraer 145 Aircraft Maintenance Manual for details

• IBM compatible laptop PC

• AHZ-800 AHRS Installation Software, Part No. 26011402-102 (version 1.7 or later)

• Four sets of shim washers 0.250 in. (6.35 mm) to 0.375 in. (9.52 mm) I.D. and 0.750 in.(19.05 mm) to 0.875 in. (22.22 mm) O.D. containing the following:

– Qty 2 at 0.100 in. (2.54 mm) thick

– Qty 2 at 0.050 in. (1.27 mm) thick

– Qty 4 at 0.015 in. (0.381 mm) thick

– Qty 4 at 0.006 in. (0.152 mm) thick

No additional special equipment or materials other than those commonly used in the shop arerequired for reinstalling units in existing trays and clamps and adjusting the system. Do notover tighten mounting screws. Where torque values are not given, finger tightening of themounting screws is acceptable.



3. Procedure for the AH-800 Attitude Heading Reference Unit (AHRU)

A. Removal and Reinstallation Procedures

(1) Remove the AHRU.

(a) Loosen the two thumbwheel clamps until they disconnect from the supporthooks.

(b) Slide the unit out of the mounting tray.

(2) Reinstall the AHRU.

CAUTION: WHEN PLACING THE UNIT ON THE MOUNTING TRAY, DO NOTFORCE FIT. IF MATING IS DIFFICULT, REMOVE THE UNIT ANDCHECK FOR CONNECTOR PINS THAT MAY BE BENT OR OUT OFALIGNMENT. ALSO, VISUALLY CHECK THE ALIGNMENT OF THERECEPTACLE ON THE MOUNTING TRAY.

(a) Place the unit on the mounting tray. Slide it onto the three guide pins. Slidethe unit backwards until its connectors are fully engaged with the matingconnectors of the mounting tray.

(b) Secure the unit in place by tightening the two thumbwheel clamps over thesupport hooks.

CAUTION: IF THE MOUNTING TRAY IS MOVED IN ANY DIRECTION, ACOMPLETE TRAY ALIGNMENT MUST BE DONE. REFER TOTHIS PROCEDURE IN PARAGRAPH 6.

B. Adjustment Procedures

Not applicable.

C. Repair Procedures

Not applicable.

D. Return to Service Procedures

Refer to the test procedures in the Aircraft Maintenance Manual.



4. Procedure for the AHRU Mounting Tray Fan Filter

NOTE: In a new installation, the filter should be cleaned or replaced after approximately 100hours of operation and then approximately every 300 to 500 hours depending on theenvironmental conditions.


(1) Remove the filter.

Pull up on the removal tab to separate the filter from the fan.

(2) Reinstall the filter.

Align the cutout area on the bottom of the filter with the wires on the fan and pressdown on the filter until it snaps into place.


Not applicable.

C. Cleaning Procedures

NOTE: Visually inspect the filter for signs of damage or deterioration. Replace filterif any damage or deterioration is found.

(1) Vacuum the filter using a standard commercial vacuum cleaner or clean the filterusing compressed air at a pressure not to exceed 30 PSI.

(2) Wash the filter in a mild detergent solution and rinse with water. Temperature of thedetergent solution or the water must not exceed 140 °F. Do not use chlorinesolutions.

(3) Allow the filter to air dry.

(4) Install the filter on the fan assembly.


Apply 28 V dc power to the AHRU and verify proper operation of the fan.



5. Procedure for the AHRU Mounting Tray Fan

See Figure 4-1.


(1) Remove the fan.

(a) Remove the fan filter as previously instructed in paragraph 4.A.(1).

(b) There are two wires (one red, one black) coming out of the fan housing.Disconnect these wires at their source.

(c) Turn the rim clamps until the flat edge of each clamp is facing toward the fan.

(d) Separate the fan from the fan mounting plate.

(2) Reinstall the fan.

(a) Place the fan in position on mounting tray, making sure that the AIRFLOWarrow on the fan points down.

(b) Attach the fan to the base of the tray with three rim clamps. Make sure thatthe flat edge of the rim clamp faces away from the fan.

(c) Connect the red wire to the 28 V dc source.

(d) Connect the black wire to the ground source.


Not applicable.


Not applicable.


Apply 28 V dc power to the AHRU and verify proper operation of the fan.



NOTE: FAN FILTER (NOT SHOWN)SNAPS ON TOP.A

IRF

LO

W

AD-51243@

PILOT'SFAN

MOUNTING

FANHOUSING

MACHINE SCREWAND RIM CLAMP (4 PL)

MOUNTINGTRAY

CO-PILOT'SFANMOUNTING

Figure 4-1. Fan Replacement



6. Procedure for the AHRU Mounting Tray

CAUTION: THE PHYSICAL/MECHANICAL INSTALLATION OF THE MOUNTING TRAY FORTHE AHRU HAS A VERY LARGE EFFECT ON THE ACCURACY OF ATTITUDEAND HEADING DATA. DO NOT REMOVE THE TRAY UNLESS IT HAS BEENDAMAGED OR DEFORMED.


(1) Remove the mounting tray.

(a) Remove the unit, fan, and filter as instructed in paragraphs 3, 4, and 5.

(b) Remove and set aside the four nuts, four washers, and four screws that attachthe ARINC 600 connector to the rear of the mounting tray.

(c) Detach the ARINC 600 connector.

(d) Remove and set aside the four screws and four washers that attach themounting tray to the airframe.

(2) Reinstall the mounting tray.

NOTE: The accuracy of attitude angle indication is directly dependentupon the accuracy with which the AHRU is aligned with theaircraft axes. The mounting tray must be installed with arelative alignment accuracy of ±0.2 degree in the pitch, rolland yaw axes.

(a) Using the mounting hardware previously removed and set aside, attach themounting tray to the airframe. Screws should be tight enough to preventmovement of the tray.

(b) Using the connector hardware previously removed and set aside, installthe ARINC 600 connector, making sure to leave a maintenance loop inthe harness of sufficient length so as not to apply any pressure on themounting tray.

(c) Level the tray in accordance with procedures in paragraph 6.B.


Refer to AHRU mounting tray alignment procedures in the Embraer Aircraft MaintenanceManual.


Not applicable.





7. Procedure for the AT-860 ADF Antenna

NOTES: 1. The AT-860 ADF Antenna, is a totally self-contained low profile antenna thatrequires no adjustment during operation. It combines both the loops and thesense antennas in one package, and therefore, does not require a separatelong wire sense antenna.

2. It is very important that the metal base of the antenna be electrically bonded(less than 2.5 milliohms) to the metal skin of the airframe to provide a groundplane for the antenna elements. When a mounting gasket is used, themounting bolts must provide electrical contact with the metal spacers that formthe mounting holes in the antenna through the mounting nuts to the airframe.


NOTE: Refer to the general instruction in paragraph 1.A.

(1) Remove the antenna.

(a) Loosen, remove and set aside four No. 10 sockethead cap screws.

(b) Unseal and remove the antenna.

(c) Disconnect the cable connectors.

(2) Reinstall the antenna.

(a) Place the new gasket, Honeywell Part No. 7020801-947, on the antenna.

(b) Connect the cable connectors.

(c) Mount the antenna and apply the appropriate sealant.

(d) Install the four No. 10 corrosion resistant steel socket-head cap screws thatwere removed and previously set aside.


Not applicable.


Not applicable.





8. Procedure for the AT-910 TCAS Directional Antenna

NOTES: 1. There is at least one AT-910 required for TCAS, mounted on top of thefuselage. A second (optional) AT-910 may be mounted on the bottom of thefuselage. These procedures apply to both antennas.

2. Refer to the general instructions in paragraph 1.A.


(1) Remove the antenna.

(a) Loosen, remove and set aside eight non-torx drive screws and washerssecuring the antenna to the aircraft.

(b) Unseal and remove the antenna.

(c) Verify that the four coaxial cables have the appropriate color coding rings inplace. If they have been damaged or removed, tag the cables.

(d) Disconnect the four cable connectors.

(2) Disassemble the antenna and mounting plate.

(a) Remove and set aside the attaching hardware and separate antenna dish andadapter plate.

(b) Clean the antenna dish and adapter plate to remove any sealant and foreignmaterial.

(3) Assemble the antenna and mounting plate.

(a) Mate the antenna dish with the adapter plate, making sure that all holes arealigned.

(b) Using a grease pencil, make an alignment mark on the antenna dish andadapter plate.

(c) Separate the antenna dish and adapter plate.

(d) Apply a continuous bead of sealant (polysulfide type 1, class B-1/2) to theouter recess in the adapter plate.

(e) Place the adapter plate over the antenna dish to match alignment marks madeearlier in paragraph 8.A.(3)(b).

(f) Press the adapter plate onto the antenna dish.

(g) Attach the adapter plate to the antenna dish using the attaching hardwareremoved in paragraph 8.A.(2)(a).



(4) Reinstall the antenna.

(a) Place the new O-ring, Honeywell Part No. 4000171-240, in the O-ring grooveof the antenna assembly.

(b) Position the antenna assembly to its location on the fuselage and align themounting holes (note the non-symmetrical hole pattern).

(c) Note the orientation of the antenna with respect to the airframe. Do not attachthe antenna to the airframe at this time.

(d) Carefully inspect all mating connectors for the presence of foreign matter.Clean as necessary.

(e) Connect the four coaxial cables to the antenna. Note the color bands on thecables and mating connectors: yellow to J1, black to J2, blue to J3, and red toJ4.

(f) Align the antenna mounting holes with the holes in the aircraft (note thenon-symmetrical hole pattern).

(g) Secure the antenna with eight non-torx drive screws and washers that wereremoved and previously set aside.

(h) Tighten the screws to 18 inch-pounds maximum torque.


Not applicable.


Not applicable.





9. Procedure for the AV-850A Audio Control Unit


(1) Remove the AV-850A Audio Control Unit.

(a) Disengage the Dzus fasteners on the unit.

(b) Slide the unit out of the aircraft mounting location and disconnect the cableconnector(s).

(2) Reinstall the AV-850A Audio Control Unit.

(a) Mate the unit connector(s) with the aircraft cable connector(s) and slide theunit into the mounting location.

(b) Engage the Dzus fasteners on the unit.


(1) Adjust the AV-850A Audio Control Unit.

NOTE: All adjustments for the AV-850A Audio Control Unit are set atthe factory for typical operating conditions. Most installationsshould not require adjustment of the audio control unit. If anadjustment is necessary, perform that adjustment inaccordance with the following procedures. Table 4-1 containsa list of audio control unit adjustable functions and theapplicable potentiometer associated with that function. Figure4-3 provides adjustment locations for the AV-850A AudioControl Units.

(a) Warning Adjustments

The warning inputs are factory set for a nominal input signal of 10 milliwattsinto 600 ohms. Should adjustment become necessary, proceed as follows.

1 Warning 1 Level Adjust

Apply an input signal to the WARNING 1 AUDIO input. While listening tothe cockpit speaker or phones, adjust the WARNING 1 LEVEL ADJUSTpotentiometer (A1R40) for the desired output level.











(b) Maintenance System Adjustments

The Maintenance System is adjusted for typical microphones and headphonesand will not normally need adjusting. Should adjustment become necessary,proceed as follows:

1 Maintenance Mic 1 Level

Adjust the Audio Control Unit INPH and PHONE controls for a comfortableheadphone listening level while listening to interphone audio transmittedfrom the cross-side Audio Control Unit. Connect a microphone to theMAINT 1 MIC input of the Audio Control Unit. Ground the MAINT 1ENABLE input of the Audio Control Unit. Adjust the MNT 1 MICpotentiometer (A3R11) for the desired level using the cross-side AudioControl Unit as a reference. Perform Maintenance Phone Level adjustmentas described in paragraph 11.B.(1)(b)3.

2 Maintenance 2 Mic Level

Adjust the Audio Control Unit INPH and PHONE controls for a comfortableheadphone listening level while listening to interphone audio transmittedfrom the cross-side Audio Control Unit. Connect a microphone to theMAINT 2 MIC input of the Audio Control Unit. Ground the MAINT 2ENABLE input of the Audio Control Unit. Adjust the MNT 2 MICpotentiometer (A3R60) for the desired level using the cross-side AudioControl Unit as a reference. Perform Maintenance Phone Level adjustmentas described in paragraph 11.B.(1)(b)3.

3 Maintenance Phone Level

Connect headphones to the MAINT PHONE output of the Audio ControlUnit. Adjust the MNT PH potentiometer (A3R19) to obtain the desiredMaintenance Phone level while listening to interphone audio.



(c) Passenger Address (PA) System Adjustments

The PA output is factory adjusted to generate 10 mW into 600 ohms. Shouldadjustment become necessary, proceed as follows:

• Depress the PA microphone select button

• While the Push to Talk (PTT) button is engaged, adjust the PA LVLpotentiometer (A2R40) for the desired level in the cabin.

(d) Miscellaneous Adjustments

1 Cockpit Mic Level

The Cockpit Mic Level potentiometer (A1R17) is adjusted for typicalmicrophones and will not normally need adjusting.

NOTE: This adjustment is for signals internal to theAudio Control Unit only. Changing thisadjustment will not change the modulationcharacteristics of a COM radio.

2 Comm/Mkr Minimum Gain

The purpose of this adjustment is to set the minimum level that an"autoselected" COM receiver (a receiver that was selected automaticallybecause the COM transmitter was selected) may have. It also sets theminimum gain that a selected Marker Beacon receiver may have. Turningoff the audio of an autoselected COM or the Marker Beacon require thedevices to be deselected manually.

Depress the COM 1 microphone select switch. While listening to COM 1,adjust the volume controls for a comfortable listening level. Rotate theCOM 1 receiver volume control fully counterclockwise, then deselect theCOM (button recessed). Adjust the MIN GAIN potentiometer (A1R54) forthe desired level.

3 Mkr Mute Level

The Marker Beacon Mute Level is factory adjusted to work properly withthe RNZ-851 NAV Unit and normally will not need to be adjusted.

NOTE: The Marker Beacon mute algorithm in theAudio Control Unit relies on both timing andMarker Beacon audio level to determine whento un-mute the Marker Beacon audio. Thetiming parameters are not adjustable. Thisprocedure adjusts the audio level threshold.

Apply a signal modulated with one of the marker tones (Inner, Middle, orOuter) to the Marker Beacon receiver. Adjust the signal strength so thatthe selected Marker indicator is just illuminated.



Turn the MKR MUTE potentiometer (A1R53) fully clockwise. Momentarilydepress the Marker mute button to mute the Marker signal. Beginadjusting the MKR MUTE potentiometer counterclockwise in smallincrements and wait at least 5 seconds after each increment. If the signaldoes not reappear within 5 seconds, continue to turn the potentiometer insmall increments until the signal does reappear. (Wait 5 seconds aftereach increment). This will establish the correct Marker mute level.

4 Phone Squelch

Depress the PA microphone select button. Latch in all switch/pots exceptfor INPH and MUTE.

Adjust the SQUELCH potentiometer (A1R68) while listening to theheadphone output and transmitting on the Interphone.

5 Voice Recorder Output Level

The voice recorder output potentiometer (A3R35) is factory adjusted for 10mW into 600 ohms. Interfacing the output to a voice recorder with inputlevels other than this will require adjustment of the Audio Control Unit.Refer to applicable voice recorder instructions on how to set input level.

6 Minimum Speaker Gain

Depress the COM 1 microphone select switch. While listening to COM 1,adjust the COM 1 and SPEAKER volume controls for a comfortablelistening level. Rotate the SPEAKER volume control fullycounterclockwise. Latch out the MIC/MASK selector. Adjust the MINSPKR potentiometer (A3R48) for the desired level.

(e) Sidetone Adjustments

1 Headphone Sidetone Level

NOTE: The differential level between the COMreceiver level and the COM sidetone levelwhen listening in the headphone is set by theselected COM receiver.

While listening to a COM transmission such as ATIS, adjust the COM andHEADPHONE volume control for a comfortable listening level. Whiletransmitting on an unused frequency, adjust the COM sidetone level for acomfortable listening level. See Figure 4-6 for the location of the COMsidetone level for an RCZ-851.



2 Speaker Sidetone Level

While listening to the cockpit speaker and transmitting on a COMtransceiver, adjust SPEAKER SIDETONE for the desired speakersidetone level.

3 Internal Sidetone Level

While listening to the cockpit speaker and transmitting on the CABINaddress system, adjust the INT ST potentiometer (A3R46) for the desiredspeaker sidetone level. This will normally be adjusted to the samesidetone level as the COMs.


Replacement of the control knobs.

NOTE: Only the large SPEAKER and HEADPHONE knobs are field replaceable.The small knobs require removal of the front panel, and should only beserviced in an approved shop.

(1) Use a 0.060-inch O.D., 6 flute, Bristol wrench to loosen the setscrews.

(2) Slide the knob off the shaft.

(3) Turn the shaft fully counterclockwise.

(4) On new knobs, make sure that the setscrews are out far enough to allow the knob toslide onto the shaft.

(5) Slide the knob onto the shaft with the pointer at the 8 o’clock position.

(6) Tighten the setscrews.

(7) Check to make sure that the knob is not rubbing against the front panel, and that thepointer is at the 8 o’clock position when rotated fully counterclockwise.





Table 4-1. AV-850A Audio Control Unit Adjustments

FUNCTION LABEL AV-850AADJUSTMENTS

Cabin PA Level PA LVL A2R40

Cockpit Mic Level MIC LVL A1R17

Comm/Mkr Minimum Gain MIN GAIN A1R54

Internal Sidetone INT ST A3R46

Maintenance 1 Mic Level MNT 1 MIC A3R11

Maintenance 2 Mic Level MNT 2 MIC A3R60

Maintenance Phone Level MNT PH A3R19

Marker Mute Level MKR MUTE A1R53

Minimum Speaker Gain MIN SPKR A3R48

Phone Squelch SQUELCH A1R68

Voice Recorder Output Level CVR A3R35

Warning 1 Level WRNG 1 A1R40





ST A2R38*

NOTE: * A2R38 is software disabled when ST control is on front panel



FRONT

FRONT

WRNG 4 (A1R43)WRNG 5 (A1R44)

MKR MUTE (A1R53)MIN GAIN (A1R54)

WRNG 2 (A1R41)WRNG 1 (A1R40)

MIC LVL (A1R17)SQUELCH (A1R68)

WRNG 3 (A1R42)

MNT PH (A3R19) A3TP1/MNT 2 MIC (A3R60) MNT 1 MIC (A3R11)

ST (A2R38)* PA LVL (A2R40)

CVR (A3R35)MIN SPKR (A3R48)INT ST (A3R46)

LEFT SIDE

RIGHT SIDE AD-34524@

*NOT FUNCTIONAL IN UNITS WITH FRONT PANEL ST CONTROL.

Figure 4-2. AV-850A Audio Control Unit Adjustment Locations



10. Procedure for the AZ-850 Micro Air Data Computer (MADC)


(1) Remove the MADC.

(a) Disconnect the pitot and static lines. Cap or cover the hose end connectors tokeep debris out of the system.

(b) Disconnect the cable connector.

(c) Using a 3/16-inch Allen wrench, loosen the jackscrew until the hold-down hookreleases the MADC.

(d) Slide the MADC out of the tray.

(2) Reinstall the MADC.

(a) Slide the MADC into the mounting tray.

(b) Make sure that the rear boss engages the mounting tray slot.

(c) Make sure that the hold-down hook engages the boss on the MADC and usinga 3/16-inch Allen wrench, tighten the jackscrew.

(d) Mate the cable connector and the unit connector.

(e) Connect the pitot and static lines and perform the appropriate pitot/static leakcheck as instructed in the Aircraft Maintenance Manual.

(3) Procedure for Non-Honeywell Components

Non-Honeywell parts of the Air Data System, such as the temperature probes are notcovered here. For specific information on these components, consult the AircraftMaintenance Manual.


Not applicable.


Not applicable.


Refer to the test procedures for the Air Data System in the Aircraft Maintenance Manual.



11. Procedure for the BL-870/871 Bezel Assembly


(1) Remove the bezel assembly.

(a) Loosen the two captive holding screws at the ends of the bezel assembly.

(b) Gently pull the bezel assembly straight away from the display unit separatingthe bezel and the display unit connectors.

(2) Reinstall the bezel assembly.

(a) Align the bezel assembly on the display unit so the bezel and display unitconnectors mate.

(b) Tighten the captive screws.

B. PFD Bezel Assembly Inclinometer Level Adjustment Procedures

(1) Loosen the two screws on the inclinometer.

(2) Adjust the inclinometer until level and tighten the screws.


Replacement of BL-870/871 Bezel Assembly set knobs.

(1) Loosen both the setscrews in the knob with a 1/16-inch Allen wrench.


(3) On new knobs, make sure that the setscrews are out far enough to allow the knob toslide onto the shaft. Apply retaining compound to the setscrews.

(4) Slide the knob onto the shaft.

(5) Make sure that the space between the knob and the bezel is approximately 0.030 in.(0.8 mm).

(6) Tighten both No. 6-32 setscrews with the Allen wrench.

(7) Visually check the spacing between the knob and the bezel to make sure that theknob has not slipped during installation.





12. Procedure for the CD-810 Control Display Unit


(1) Remove the CD-810 Control Display Unit.



(2) Reinstall the CD-810 Control Display Unit.

(a) Mate the cable connector(s) with the unit connector(s) and slide the unit intothe aircraft mounting location.



Not applicable.


Not applicable.



13. Procedure for the CD-850 Clearance Delivery Control Head (CDH)


(1) Remove the CD-850 CDH.

(a) Using an 3/32-inch Allen wrench, loosen the unit mounting clamp screwsaccessible through holes at the sides of the front panel.

(b) Slide the CDH out of the panel and disconnect the cable connector.

(2) Reinstall the CD-850 CDH.

(a) Mate the cable connector with the unit connector and slide the display into thepanel.

(b) Using a 3/32-inch Allen wrench, tighten the unit mounting clamp screws.


Not applicable.





NOTE: Each control knob is held in place by two No. 4-40 X 3/32-inch hexsetscrews. The setscrews in the small tuning knob are reached throughaccess holes in the large tuning knob.

(1) Rotate the large tuning knob as necessary to reach the setscrews in the smalltuning knob.

(2) Using the appropriately sized Allen wrench, loosen both No. 4-40 setscrews in theknob.


(4) On new knobs, make sure that the setscrews are out far enough to allow the knob toslide onto the shaft. Apply retaining compound to the setscrews.

(5) Slide the large tuning knob onto the shaft.

(6) Make sure that the space between the knob and the bezel is approximately0.030 inch (0.8 mm).


(8) Recheck spacing between the knob and the bezel to make sure that knob has notslipped during installation.

(9) Slide the small tuning knob onto the shaft, making sure that the small tuning knobdoes not rub against the large tuning knob.

(10) Align the access holes in the large tuning knob with the setscrews in the small tuningknob.


(12) Recheck to make sure that the small tuning knob has not slipped during installation,and is not rubbing against the large tuning knob.





14. Procedure for the DA-800 Data Acquisition Unit (DAU)


(1) Remove the DA-800 DAU.

(a) Press up on the inside at the top of the front handle to release the lockinglever. Move the locking lever out and down to release the locking cam.

(b) Slowly pull forward on the handle to separate the unit and tray connectors andslide the unit out of the tray.

(c) Stow the locking lever by pressing it up and into the slot in the handle until thelatching button clicks into place.

(2) Reinstall the DA-800 DAU.

(a) Press up on the inside at the top of the front handle to release the lockinglever. Move the locking lever out and down to release the locking cam.

CAUTION: WHEN PLACING THE UNIT ON THE MOUNTING TRAY, DO NOTFORCE FIT. IF MATING IS DIFFICULT, REMOVE THE UNITAND CHECK FOR CONNECTOR PINS THAT MAY BE BENT OROUT OF ALIGNMENT. ALSO, VISUALLY CHECK THEALIGNMENT OF THE RECEPTACLE ON THE MOUNTING TRAY.

(b) Place the unit on the mounting tray. Slide the unit backwards until itsconnectors are fully engaged with the mating connectors of the mounting tray.To make sure proper connector engagement, place a gauge 0.220 inch(5.58 mm) thick (a No. 2 drill bit is 0.221 inch) between back of unit and centerof tray. If gauge fits between unit and tray, the unit is improperly engaged.Remove and reinstall as required until proper connector engagement is made.

(c) Making sure that the locking cam mates properly with the cam receptacle,move the locking lever up and into the slot in the handle until the lockingbutton clicks into place.


Not applicable.


Not applicable





15. Procedure for the DC-550 Display Controller


(1) Remove the DC-550 Display Controller.



(2) Reinstall the DC-550 Display Controller.




Not applicable.


Not applicable.





16. Procedure for the DL-900 Data Loader


(1) Remove the DL-900 Data Loader.



(2) Reinstall the DL-900 Data Loader.




Not applicable.


Not applicable.





17. Procedure for the DU-870 Display Units


(1) Remove the DU-870 Display Unit.

(a) Loosen the two captive holding screws at the ends of the bezel assembly.

(b) Gently pull the bezel assembly straight away from the display unit separatingthe bezel and the display unit connector. Set the bezel assembly aside.

(c) Using a 3/16-inch Allen wrench, loosen the jackscrew and separate the unitand tray connector(s).

(d) Gently lift the front of the display unit until the jackscrew latch clears the slot inthe mounting tray.

(e) Slide the display unit out of the tray.

(2) Reinstall the DU-870 Display Unit.


(a) Slide the display unit into the panel tray, lifting the front of the display unit asnecessary to make sure that the jackscrew latch engages the slot in themounting tray.

(b) Slide the display unit backwards until its connectors are fully engaged with themating connectors of the mounting tray.

(c) Tighten the jackscrew with a 3/16-inch Allen wrench.

(d) Reinstall the bezel assembly.

1 Align the bezel assembly on the display unit.

2 Tighten the captive screws.


Not applicable.




Cleaning of the display unit faceplate filter.

NOTE: The display unit faceplate is protected by a filter which reduces reflections. Itis sturdy, but it is not indestructible.

(1) Inspect the outside surface for foreign material and variations in optical quality.

(2) Particles of grit, dirt, or sand are to be removed with pressurized dry air or a softcamel-hair brush.

(3) Dampen a clean piece of lint-free cloth with isopropyl alcohol or ammoniated cleaner.Do not use household paper towels.

(4) Carefully rub the unclean portion of the filter with the damp cloth.

(5) Repeat paragraphs 17.C.(3) and (4) as necessary until the filter is clean.





18. Procedure for the FX-600 Thin Flux Valve

NOTE: Whenever a flux valve is removed and reinstalled or replaced, a compass swingmust be performed to maintain desired long-term heading accuracy. Any errors in theoutput of the flux valve in excess of ± 1 degree, which are caused by extraneousmagnetic fields, will be corrected by performing the flux valve calibration procedurein paragraph 18.B.


(1) Remove the FX-600 Thin Flux Valve.

(a) Remove and set aside the three non-magnetic screws securing flux valve tomounting bracket. DO NOT lose non-magnetic screws. Put as little strain aspossible on lead connections when withdrawing flux valve.

(b) One at a time, loosen the captive screws, Honeywell Part No. 873076-62,which hold the six terminal lugs to the terminal board on the flux valve. Slidethe lugs out from under the screw heads and tighten the screws in the terminalboard. Label the leads to the flux valve terminal board to make sure properreconnection.

(2) Reinstall the FX-600 Thin Flux Valve.

(a) One at a time, loosen the screws in the terminal board. Connect and securethe flux valve leads to the terminal board. Be certain to make properconnections.

(b) Install the flux valve in the mounting bracket and secure with three No. 6-40 X3/8-inch, roundhead, non-magnetic machine screws, Honeywell Part No.1712115, that were removed and previously set aside. DO NOT tighten thescrews.

NOTE: DO NOT use the magnetic type screws to mount theflux valve.

(c) Align centerline on the flux valve mounting flange alignment scale with thelongitudinal axis of the aircraft. Tighten the mounting screws.

B. FX-600 Thin Flux Valve Calibration Procedures

Whenever a FX-600 Thin Flux Valve or MM-260 Memory Module is installed or removedand replaced, the system must be calibrated in order for it to provide the desired magneticheading accuracy. If the flux valve calibration has never been performed, as in a newinstallation, the MAG mode will not be valid. This procedure will provide for computationand correction for index error, single cycle error and two cycle error. Any errors in theoutput of the flux valve in excess of ± 1 degree, which are caused by extraneous magneticfields, will be corrected by performing the flux valve calibration as follows:



(1) Compass Swing Site

Move the aircraft to a level site that is free of buried metal objects and is at least500 feet from the nearest metal structure. A Compass Rose that has beenmagnetically surveyed within the past two years is desirable if the results of theCompass Swing are to satisfy an accuracy of ± 1.0 degree.

(2) Aircraft Alignment

This section of the procedure defines the method to determine the alignment of theaircraft to a reference line of the Compass Rose. This alignment procedure willallow for the aircraft to be placed close to, but not have to be exactly on thereference line and will provide the accuracy of the initial reference heading to bewithin ± 0.2 degrees.

NOTES: 1. The AHZ-800 compass system will provide an accuracyof ± 1.0 degree or less if the procedure outlined in thisparagraph is utilized. If an alternate procedure todetermine the initial reference heading to be entered isused, the initial reference heading may not be within therequired ± 0.5 degrees and the results of the compassswing may not provide a system accuracy of ± 1.0degree. An example of an alternate method that maynot provide an initial reference heading accuracy of ±0.5 degrees is the use of a land compass or sightcompass. Use of this alternate method may onlyprovide a compass system accuracy of approximately ±1.5 to 2.5 degrees after the compass swing iscompleted.

2. The aircraft may positioned to any known heading tobegin the compass swing and that known heading wouldbe used to enter as the initial reference heading inparagraph 18.B.(3)(m). Care should be exercised tomake sure that this heading is accurate to within ± 0.5degrees. Generally, most Compass Roses will bemarked with a minimum of the cardinal and intercardinal headings and frequently will have headingsmarked at 30 degree increments. A Compass Rose willseldom have the inter cardinal headings marked. Thebest and most efficient results will be achieved byfollowing the procedure outlined in this paragraph.

(a) Position the aircraft to a known cardinal or inter cardinal heading. In thisprocedure, it will be assumed that the reference line used is the MAGNETICN-S line of the Compass Rose and the aircraft will be pointing North.

(b) Position the aircraft such that it is aligned close to the N-S line.

(c) Drop a plumb line from the aircraft centerline at or near the nose and at ornear the tail. Mark the points where the plumb bob comes to rest.



(d) Measure the distance between the nose and tail plumb bob marks. Recordthis distance on line 1 of Table 4-2.

(e) Measure the lateral displacement distance of each plumb bob mark from theN-S line. Record these distances on line 2 and line 3 of Table 4-2.

NOTE: If this displacement is to the left of the reference(N-S) line, while facing in the same direction as theaircraft, it shall have a negative (-) value. If thisdisplacement is to the right of the reference (N-S)line, while facing in the same direction as the aircraft,it shall have a positive (+) value.

(f) Algebraically subtract the lateral displacement at the tail (line 3) from thelateral displacement at the nose (line 2). [The equation would be: (line 2) -(line 3)]. Record the result on line 4 of Table 4-2.

(g) Determine the aircraft misalignment using the Nomograph (Figure 4-4).Record this value on line 5 of Table 4-2. The polarity of line 5 will be thesame as line 4.

(h) Convert the value of line 5 in Table 4-2 from minutes to degrees. Enter thenumber of degrees in line 6 of Table 4-2. The polarity of line 6 will be thesame as line 4 and line 5.

As an aid, the following conversions are provided:

• 0.1 deg = 6 minutes









• 1.0 deg = 60 minutes.



(i) Algebraically add the heading of the reference line and the value of line 6.Record this value on line 7 of Table 4-2. This will be the actual aircraftheading and will be used in paragraph 18.B.(3)(l) as the initial referenceheading.

As an aid, three examples are shown in Tables 4-3, 4-4, and 4-5.

Table 4-2. Aircraft Alignment

PLUMB BOB SEPARATION ALONG AIRCRAFT_______________Line 1

DISPLACEMENT OF NOSE PLUMB BOB FROM N-S LINE____________Line 2

DISPLACEMENT OF TAIL PLUMB BOB FROM N-S LINE_______________Line 3

PLUMB BOB DISPLACEMENT = (Line 2) - (Line 3)_______________Line 4

AIRCRAFT ALIGNMENT WITH N-S LINE FROM NOMOGRAPH_______________Line 5

VALUE OF LINE 5 CONVERTED TO DEGREES _______________Line 6

ACTUAL AIRCRAFT HEADING = ( 0.0 deg ) + (Line 6)_______________Line 7



99

87

60

48

36

30

24

21

18

15

12

9

6

3

2

3530

20

15

10

5

4

3

2

1

0.70

0.50

0.40

0.30

0.25

0.20

0.15

0.1

0.05

100

90

80

70

60

50

40

30

25

20

15

10

AIRCRAFTMISALIGNMENT

(MINUTES)

PLUMB BOBDISPLACEMENT

(INCHES)

PLUMB BOBSEPARATION

(FEET)

AD-46791@

USING A STRAIGHT EDGE, CONNECT LINE BETWEENPLUMB BOB SEPARATION AND DISPLACEMENT VALUESTO DETERMINE AIRCRAFT MISALIGNMENT.

NOTE:

Figure 4-3. Nomograph



Example 1:

Aircraft positioned pointing north and nose and tail both to the east (right) ofthe magnetic N-S line. Nose plumb bob displacement = 8 inches; tail plumbbob displacement = 6 inches; plumb bob separation = 22 feet. Line 4 =(Line 2) - (Line 3) = (+8) - (+6) = +2.

Table 4-3. Aircraft Alignment Example 1

PLUMB BOB SEPARATION ALONG AIRCRAFT 22 feet Line 1

DISPLACEMENT OF NOSE PLUMB BOB FROM N-S LINE + 8 inches Line 2

DISPLACEMENT OF TAIL PLUMB BOB FROM N-S LINE + 6 inches Line 3

PLUMB BOB DISPLACEMENT = (Line 2) - (Line 3) + 2 inches Line 4

AIRCRAFT ALIGNMENT WITH N-S LINE FROM NOMOGRAPH + 30 minutes Line 5

VALUE OF LINE 5 CONVERTED TO DEGREES + 0.5 deg Line 6

ACTUAL AIRCRAFT HEADING = ( 0.0 deg ) + (Line 6) 000.5 deg Line 7

Example 2:

Aircraft positioned pointing north and nose and tail both to the west (left) ofthe magnetic N-S line. Nose plumb bob displacement = -4 inches; tail plumbbob displacement = -7 inches; plumb bob separation = 20 feet. Line 4 =(Line 2) - (Line 3) = (-4) - (-7) = -4 +7 = +3.



DISPLACEMENT OF NOSE PLUMB BOB FROM N-S LINE - 4 inches Line 2

DISPLACEMENT OF TAIL PLUMB BOB FROM N-S LINE - 7 inches Line 3

PLUMB BOB DISPLACEMENT = (Line 2) - (Line 3) + 3 inches Line 4

AIRCRAFT ALIGNMENT WITH N-S LINE FROM NOMOGRAPH + 48 minutes Line 5

VALUE OF LINE 5 CONVERTED TO DEGREES + 0.8 deg Line 6




Example 3:

Aircraft positioned pointing north with nose to the west (left) and tail to theeast (right) of the magnetic N-S line. Nose plumb bob displacement = -3inches; tail plumb bob displacement = + 1.5 inches; plumb bob separation =25 feet. Line 4 = (Line 2) - (Line 3) = (-3) - (+1.5) = -3 -1.5 = -4.5.



DISPLACEMENT OF NOSE PLUMB BOB FROM N-S LINE - 3 inches Line 2

DISPLACEMENT OF TAIL PLUMB BOB FROM N-S LINE + 2 inches Line 3

PLUMB BOB DISPLACEMENT = (Line 2) - (Line 3) - 4.5 inches Line 4

AIRCRAFT ALIGNMENT WITH N-S LINE FROM NOMOGRAPH - 60 minutes Line 5

VALUE OF LINE 5 CONVERTED TO DEGREES - 1.0 deg Line 6


(3) Flux Valve Calibration Procedure

NOTES: 1. The accuracy of the flux valve calibration will be optimizedif the calibration procedure is performed while the aircraft’sengines are running and all normal electrical and avionicssystems are operating. The magnetic characteristics of theengines are different if they are running or if they are notrunning and the electrical and avionics systems and theirassociated wiring can contribute magnetic noise in theaircraft. The flux valve should be calibrated under magneticconditions that closely approximate the conditionsencountered in flight.

2. It is recommended that the Compass Swing not beperformed if the wind is greater than 15 knots.

3. If more than one AHRS is to be calibrated, the flux valvecalibration procedure can be performed on multiple unitssimultaneously. To do this, the RS-232 port of each AHRSto be calibrated can either be connected to a separateserial port on the PC, connected to separate PCs ormultiplexed into a single port via an external switch.

4. If a dual swing is to be done, the best results will beachieved by using two PCs, by multiplexing the two AHRSinto one COM port of a PC or by using one PC with twoCOM Ports and performing both Compass Swings at thesame time. This will save time and reduce the possibility ofcompass splits.



(a) Before connecting the Honeywell adapter cable (T-236238) to the 50-pinaircraft maintenance connector and the PC, make sure the System power isoff.

(b) Connect P1 of the adapter cable to the 50-pin maintenance connector locatedon the maintenance panel behind the pilot’s seat.

(c) Connect P3 of the adapter cable to the PC’s 9-pin access connector.

(d) Apply aircraft ground to J1 AHRS PROGRAM GROUND.

(e) Set S1 to AHRS 1 ENABLE or S2 to AHRS 2 ENABLE, if a single flux valvecalibration is being performed. Set S1 to AHRS 1 ENABLE and S2 to AHRS 2ENABLE, if a multiple flux valve calibration is being performed.

(f) Turn on power to the AHRS and wait 4 minutes for the system to stabilize.

(g) Turn on the PC.

(h) Run the AHZ-800 Attitude Heading Reference System PC Installation/MemoryAccess Software program, Honeywell Part No. 26011402-102, on the PC bytyping "MA" at the DOS prompt. The following title screen will appear:

AHZ-800

Attitude Heading Reference System

PC Installation / Memory Access Software

Part Number: 26011402-102

Version: 1.7 Compiled: 10-12-94

Copyright 1993, 1994, Honeywell Inc.

All rights reserved

Press any key to go to the main menu

(i) Press any key to continue to see the following Main Menu screen:

ConfigurationCalibration

Single Flux Valve Calibration

Multiple Flux Valve Calibration

Display Flux Valve Calibration

Single Tray Heading Alignment



(j) Verify that the PROGRAMMING AHRS CONFIGURATION procedure has beenperformed before continuing the Flux Valve Calibration Procedure. SelectCONFIGURATION from the Main Menu. The following is an example of theREAD CONFIGURATION page of the AHZ-800 Installation software:

AHRU Orientation: Handle Left

SDI: AHRS #1

ASCB ConfigurationHigh Priority:

ASCB Version:

ARINC ConfigurationARINC DADC 1 Speed: Low Speed

ARINC DADC 2 Speed: Low Speed

Controller ConfigurationController Configuration: Discretes

Tray Heading MisalignmentMisalignment coefficient = 0.0082

Misalignment coefficient: Preserve

Enter=Edit Field; ESC=Quit; F1=Write Config to Memory Module

(k) From the Main Menu, select "Calibration" and then select "Multiple Flux ValveCalibration". The following example shows AHRS 1 and AHRS 2 will beconnected to COM 1. This selection would apply if the PC has only one COMport and AHRS 1 and AHRS 2 will be multiplexed into COM 1 port. If the PChas two COM ports, AHRS 1 can be connected to COM 1 port and AHRS 2can be connected to COM 2 port. To edit the port definitions, follow theinstruction at the bottom of the screen.

Multiple Flux Valve Calibration will calibrate up to four AHRUs at once. AnAHRU may be connected to either serial port 1 (COM1) or serial port 2(COM2), if available. Four AHRUs are listed below, indicate which serialport (if any) the unit is connected to.

AHRS #1: COM1

AHRS #2: COM1

AHRS #3: NOT USED

AHRS #4: NOT USED

Press RET to edit; Press ESC to save and begin calibration



(l) On the installation program s main menu, select the STATUS PAGE. If amultiple swing is to be done, both AHRS should be checked. The following isan example of that page:

System Status

Miscellaneous Data Discretes

Mode = DG Basic Shop Maintenance = Disabled

Elapsed Time = 6919.52 sec Memory Access = Enabled

Internal Temp = 64.23 °C Auxiliary Power = Available

SDI = AHRS #2 On Primary Power

Memory Access Password = Enabled Weight-on-Wheels = On-Ground

# of Flight Faults in NVM = 1 Functional Test = Not In Progress

DG Mode = Selected

HS1,HS2,HS3,HS4 = 1,1,0,0

The AHRU is currently not exhibiting any faults, Press any key to Exit

(m) If the flux valve has previously been calibrated, verify that:

• The AHRU is currently not exhibiting any faults

• Memory Access = Enabled and Weight-On-Wheels = On-Ground.

If the memory module has never had flux valve coefficients written to it, suchas in a new installation, expect to see a memory module fault for the flux valvecoefficient sumcheck test. If there are any other flux valve faults, the fluxvalve and wiring should be checked.



(n) On the installation program’s Main Menu, select the "Memory Access Tests"option. Then select the "Interface Test" option. This will verify that thecommunication between the PC or laptop and the AHRU is established. Thefollowing is an example of the Interface Test screen:

Interface Test

Memory Access Read Test: Passed

Memory Access Input Discrete Test

Ground/Air Flag: On Ground

Memory Access Discrete: EnabledWeight On Wheels Discrete: On Wheels

Memory Access Write Test: Passed

Interface Test Passed

Press Any Key to Return to the Main Menu

(o) Verify the following:

• Interface Test Passed

• Ground/Air Flag: On Ground

• Weight-On-Wheels Discrete: On Wheels messages appear.

(p) Select the DG mode from the DG/SLVD switch in the cockpit.



(q) On the installation program’s Main Menu, select the "Calibration" option. Nextselect the "Single Flux Valve Calibration" or "Multiple Flux Valve Calibration"option. The following or similar screen will be displayed:

Steer the aircraft to a known heading, accurate to within ± 0.5°

Enter Reference Heading (Degrees): _______

(r) Enter the initial reference heading (actual aircraft heading from Line 7,Table 4-2) as a value, in degrees, in the range of 000.0 to 359.9 degrees andselect "ENTER" on the PC. This heading can be any cardinal or inter cardinalheading. Verify that the compass card display in the cockpit reads the valueentered as the initial reference heading.

If the PC indicates that it was unsuccessful in its attempt to transmit theentered initial reference heading to the AHRS, perform the steps in paragraph18.B.(3)(o).

CAUTION: THE COMPASS SWING PROCEDURE SHOULD BECOMPLETED WITHIN 60 MINUTES, OR AS QUICKLY ASPOSSIBLE, FROM THE TIME THE INITIAL REFERENCEHEADING WAS "ENTERED". THE BASIS OF THE 60 MINUTETIME LIMIT IS THE MAXIMUM SPECIFIED ALLOWABLE FREEDRIFT OF THE HEADING AXIS GYRO, WHICH IS ± 5.0DEGREES PER HOUR. (TYPICALLY, THE FREE DRIFT WILLBE SIGNIFICANTLY LESS THAN ± 5.0 DEGREES PER HOUR)WHEN THE INITIAL REFERENCE HEADING IS "ENTERED", THEHEADING AXIS GYRO IS ALSO SUBJECT TO EARTH RATE.THE PROCEDURE WILL MEASURE THE TOTAL DRIFT OF THEHEADING AXIS GYRO FROM THE TIME THE INITIALREFERENCE HEADING IS "ENTERED" TO WHEN THE FINALHEADING IS "ENTERED". IF THE TOTAL DRIFT OF THEHEADING AXIS GYRO HAS EXCEEDED ± 5.0 DEGREES THESOFTWARE WILL NOT ALLOW FOR A SUCCESSFULCOMPLETION OF THE COMPASS SWING PROCEDURE.THEREFORE, AS LATITUDE INCREASES, THE MAXIMUMALLOWABLE TIME DECREASES.



NOTE: The total drift of the heading axis gyro is the sum ofthe free drift and earth rate. Earth rate is a functionof the latitude of the compass swing location. Earthrate is negative (-) in the Northern hemisphere andpositive (+) in the Southern hemisphere.

The formula for earth rate (ER) is: ER = ± 15 sin (latitude)

As an aid, the following earth rates and worst case total drift rates and timelimits are provided for reference:

LATITUDE EARTH RATE MAX TOTAL DRIFT MAX TIME

0 deg 0 deg/hr 5.0 deg/hr 60 minutes

10 deg 2.6 deg/hr 7.6 deg/hr 39 minutes






(s) If the PC indicates that it was unable to place the AHRS into the Flux ValveCalibration Mode, perform the following steps:

1 Turn off power to the AHRS.

2 Check the RS-232 connections between the AHRS and the PC.

3 Turn on power to the AHRS.

4 Verify that the configuration has been programmed, by selecting the "ReadConfiguration" option from the program’s Configuration Menu.

5 Wait several minutes for the system to stabilize.

6 Repeat paragraph 18.B.(3)(n).

7 If the PC cannot place the AHRS in the "Calibration Mode" on the secondattempt, take the proper steps to make sure that the AHRS MemoryModule, AHRU, Flux Valve or wiring is repaired.



(t) On the PC’s screen will be a list of cardinal and inter cardinal headings. Toverify that the Calibration Mode has been entered, check the cockpit forindications that the displayed heading is in the DG mode and the displayedheading is the value entered as the initial reference heading. Using the EFISor PFD compass card as a reference, taxi or tow the aircraft to the nextheading displayed on the PC. Position the aircraft to within ± 5.0 degrees ofthe heading which is listed by the PC.

The following is an example of the display on the PC.

Flux Valve Calibration being performed on: AHRS #1 connected to COM1

Perform a 360 degree compass swing,stopping at the cardinal and inter-cardinalheadings (within ±5.0°). The final headingsample must be the same as the initialreference heading (within ±5.0°).

Select the corresponding swing heading atright and press enter.

-----------45 Degrees90 Degrees135 Degrees180 Degrees225 Degrees270 Degrees315 DegreesExit-----------

NOTE: The aircraft may now be taxied to the next headinglisted, or, if for some reason it is desirable, theaircraft can be taxied to any of the listed headings inany order. If the headings are selected in any order,move the cursor to the appropriate heading on the listand select “ENTER”. Continue this process until allof the listed headings have been selected Also, theinitial aircraft heading can be any of the cardinal orinter cardinal headings.

(u) After the aircraft has been positioned to the heading displayed by the cursoron the PC, let the flux valve stabilize for 15 to 20 seconds and then select"ENTER". Repeat for all the headings listed. After all of the headings listedhave been entered, the calibration software will display a new screen. Thisscreen will prompt the operator to return to the initial heading within ± 5degrees and press "ENTER". The final heading sample will be the startingheading. When the PC indicates that the flux valve calibration has beencompleted successfully, press any key on the PC’s keyboard.

(v) If during the swing, the PC indicates that the position of the aircraft needs tobe adjusted, adjust the aircraft by the amount indicated on the PC.



(w) If the PC indicates that a flux valve failure has occurred, terminate the fluxvalve calibration and take the proper steps to make sure that the AHRU, fluxvalve or wiring is repaired.

(x) If the PC displays an instruction to position the aircraft to another heading,return to paragraph 18.B.(3)(p).

(y) If the PC indicates that a second compass swing is required, press any key onthe PC’s keyboard and return to paragraph 18.B.(3)(p).

(z) If the PC indicates that the flux valve calibration has failed, perform the stepsin paragraph 18.B.(3)(o).

(aa) If the PC indicates that the AHRS was unable to write the results of the fluxvalve calibration to the memory module, take the proper steps to make surethat the AHRU, memory module or wiring is repaired.

(ab) Remove power and disconnect the AHRS Test Box from the aircraftconnectors and the PC.

(ac) The next time the AHRS is powered up, it will then use the results of thecompleted compass swing procedure. The MAG mode will now be valid if thisis the first time flux valve coefficients were stored by the memory module. Thestored flux valve coefficients can then be read on the Display Flux ValveCoefficients screen of the PC.

(ad) After this flux valve calibration (compass swing) procedure has beenperformed, the compass system will provide an accuracy of ± 1.0 degreeunder normal operating conditions. If dual AHZ-800 systems are installed, themaximum split between the two systems should be ± 2.0 degrees.

NOTE: There may appear to be compass system errors orsplits if the compass system is observed while on ataxi way, ramp area or near a hangar, due to metalreinforcement in the ramp or taxi way or due tomagnetic disturbances if near a hangar.


Not applicable.





19. Procedure for the GC-550 Guidance Control Unit


(1) Remove the GC-550 Guidance Control Unit.


(b) Slide the unit out of the panel.

(c) Disconnect the cable connectors.

(2) Reinstall the GC-550 Guidance Control Unit.

(a) Mate the cable connectors with the unit connectors and slide the unit into thepanel.



Not applicable.


Replacement of the pushbutton switch lamps.

NOTE: Access to these lamps does not require removing the control unit from theinstrument panel.

CAUTION: BE CAREFUL TO AVOID CRACKING THE PLASTIC SWITCH PUSHBUTTONWHEN PERFORMING PARAGRAPH 19.C.(1).

(1) Use an IC puller and insert the tips into the notch at the top and bottom or on eachside of the switch pushbutton. Gently pull straight out until the pushbutton assemblymoves out from the switch housing.

(2) Grasp the pushbutton assembly and slide it out until it reaches its stop and then letthe pushbutton assembly hinge down.

(3) Remove and replace the defective lamp.

(4) Hinge the pushbutton assembly up and slide the assembly back into the housinguntil it locks into position.





20. Procedure for the Global Navigation System Sensor Unit (GNSSU)


(1) Remove the GNSSU.

(a) Disconnect the aircraft cable and antenna connectors.

(b) Remove and set aside the four screws and washers securing GNSSU to theairframe.

(2) Reinstall the GNSSU.

(a) Secure the GNSSU to the airframe using the four 10-32 screws, lockwashers,and flat washers that were removed and set aside.

(b) Mate the unit connectors with the appropriate antenna and cable connectors.


Not applicable.


Not applicable.





21. Procedure for the IC-600 Integrated Avionics Computer (IAC)


(1) Remove the IC-600 IAC.

(a) Loosen the mounting tray hold-down knob.

(b) Slowly pull forward on the unit handle to separate the unit and tray connectorsand slide the unit out of the tray.

(2) Reinstall the IC-600 IAC.

NOTE: Make sure that the correct part number IAC is being installed.Pilot’s side (IAC No. 1) uses Part No. 7017000-824XX andcopilot’s side (IAC No. 2) uses Part No. 7017000-834XX.

(a) Slide the unit into the mounting tray.


(b) Slide the unit backwards until its connectors are fully engaged with the matingconnectors of the mounting tray.

(c) If necessary, gently lift the front of the unit to make sure that the hold-downassembly mates properly with the tray hold-down hooks.

(d) Tighten the hold-down knob.

B. Checklist Loading Procedures

(1) IAC Checklist Upload Procedure

The MFD checklist is stored in each IC-600 Integrated Avionics Computer.

(a) The aircraft must be on the ground (WOW) and powered up in standby.

(b) Locate the 50-pin maintenance connector located behind the pilot’s seat.Connect a personal computer (PC) using a RS-232 interconnect cableHoneywell Part No. T-336238-2 to the 50 pin maintenance connector.Connect IC-1 or IC-2 for the appropriate IAC and connect to the PC.



NOTES: 1. The PC must have the checklist programmingsoftware and the desired checklist available foruse. Refer to the ECP-800 ProgrammableChecklist Manual for details.

2. If the PC has Windows 3.1 or 95, do notaccess the ECP-800 software from theWindows prompt. Instead, use the DOSprompt to start the checklist software.

(c) Apply power to the avionics. Observe that the RA SET area on the PFD isvalid.

(d) Using the on-side DC-550 Display Controller, use the RA (DH) knob to set 890RA (DH) on the PFD.

(e) Push and hold the display controller TEST pushbutton for a minimum of 10seconds and while holding the TEST pushbutton momentarily push the displaycontroller ET pushbutton. The following display (Figure 4-4) appears on theonside PFD:

C H E C K L I S T L O A D I N G

P R O G R A M M A B L E C H E C K L I S T

E Q U I P M E N T I S R E Q U I R E D

S C R E E N W I L L B L A N K

C Y C L E I C - 6 0 0 C I R C U I T

B R E A K E R T O R E C O V E R

D C 5 5 0 P U S H B U T T O N S

N A V E N T E R C K L S T AD-51524@

890 RA

Figure 4-4. Checklist Loading Page

(f) Momentarily push the NAV pushbutton on the onside DC-550 DisplayController. The PFD momentarily blanks and a large red X is displayed. Thered X remains until paragraph 24.B.(3)(i).



(g) Use the electronic programmable checklist software on the PC to output thechecklist and upload it to the onside IAC.

NOTE: If a checklist is already in the IAC, error code 5100 isdisplayed on the PC. Follow the instructions on thePC.

(h) When the upload is complete, follow the instructions on the PC to finish.

(i) Pull the appropriate IAC circuit breaker to power down the IAC.

(j) Remove the RS-232 cable from the maintenance connector.

(k) Push in the appropriate IAC circuit breaker to power up the IAC.

(l) When the IAC is powered up, verify that the checklist can be selected bypushing either the NORM or EMER buttons which are selectable on the onsideMFD bezel menu.

(m) Review the checklist for accuracy.

(n) The procedure is complete.


Not applicable.



22. Procedure for the IM-803 Installation Module

NOTE: The IM-803 defines the configuration of the aircraft in which an optional NZ-2000FMS is installed, and is located near the NZ-2000 mounting tray.


(1) Remove the IM-803 Installation Module.

(a) Loosen the two captive screws that attach the module to the enclosure.

(b) Grasp the handle and slide the module out of the enclosure.



(2) Reinstall the IM-803 Installation Module.

CAUTION: IF THE IM-803 IS REMOVED FROM THE AIRCRAFT AND REPLACEDWITH AN IM-803 FROM CUSTOMER-OWNED SHELF STOCK OR WASOBTAINED FROM EMBRAER OR HONEYWELL, THECONFIGURATION STRAPS WILL HAVE TO BE CUT IN ACCORDANCEWITH THE LIST IN SECTION 3 AND THE PROCEDURE INPARAGRAPH 22.B. OF THIS MANUAL.

(a) Carefully slide the module into the enclosure.

(b) Tighten the two captive screws.


Cutting the configuration straps.

CAUTIONS: 1. BE VERY CAREFUL WHEN CUTTING CONFIGURATION STRAPS SOAS NOT TO DAMAGE THE CIRCUIT CARD ASSEMBLY.

2. PERFORM STRAP CUTTING IN AN ELECTROSTATIC-SAFEENVIRONMENT TO PREVENT DAMAGE TO THE CIRCUIT CARDASSEMBLY.

3. ALWAYS TRANSPORT THE CIRCUIT CARD ASSEMBLY IN ITSENCLOSURE OR IN AN ANTISTATIC BAG.

(1) Loosen the two captive screws that attach the module to the enclosure.

(2) Grasp the handle and slide the module containing the circuit card assembly out ofthe enclosure.

(3) Using a pair of diagonal cutters, cut the straps (jumper wires) in two places andremove the wire fragment.

(4) After cutting all the required jumpers, install the module in its enclosure and securewith the two captive screws.


Not applicable.





23. Procedure for the MM-260 AHRS Memory Module


NOTE: Removal of the Memory Module requires that the AHRU be out of the rack.

(1) Remove the MM-260 AHRS Memory Module.

NOTE: The MM-260 is "hard wired" to the AHRU mounting trayconnector. Extract the five pins from connector 1J1B-F6, F7,F8, F9 and F11.

(a) Remove and set aside the three screws which can be seen to the left of theconnectors when looking into the rack.

(b) Lift the memory module out of the mounting tray.

(2) Reinstall the MM-260 AHRS Memory Module.

(a) Insert the leads from the memory module into the ARINC 600 connector perthe following color code:

• Orange - F6

• Red - F7

• Black - F8

• Yellow - F9

• Brown - F11.

(b) Align the memory module with the mounting holes on the back of themounting tray.

(c) Reinstall and tighten the mounting screws that were previously removed andset aside.

(d) Perform adjustment procedures in paragraph 23.B.


Perform AHRS leveling procedure and flux valve calibration procedure.


Not applicable.





24. Procedure for the NZ-2000 FMS Navigation Computer

CAUTION: IF AN NZ-2000 IS REMOVED FROM THE AIRCRAFT AND REPLACED WITH ANNZ-2000 FROM CUSTOMER OWNED SHELF STOCK, OR WAS OBTAINED FROMEMBRAER OR HONEYWELL, IT MAY BE NECESSARY TO DOWNLOAD THECUSTOM AND NAVIGATION DATABASE AND CHECKLIST FILES FROM THEMEMORY TO A 3.5-INCH DISKETTE. BOTH THE NAVIGATION AND CUSTOMDATABASE AND THE CHECKLIST WILL NEED TO BE UPLOADED TO THEREPLACEMENT NZ-2000. REFER TO THE PROCEDURES IN PARAGRAPH 24.B.

NOTES: 1. The custom database is made up of flight plans and pilot defined waypoints.This database can be loaded from a disk if available. Please refer to yourcompany’s flight operations department for availability of custom databaseinformation on disk.

2. Through the use of the DL-900 Data Loader, you have the option to transferthe custom database to 3.5-inch floppy diskettes. Also, you have the option totransfer the custom or navigation database from disk to the NZ-2000.


(1) Remove the NZ-2000 FMS Navigation Computer.

(a) Loosen the mounting tray hold-down knob.


(2) Reinstall the NZ-2000 FMS Navigation Computer.

(a) Slide the unit into the mounting tray.


(b) Slide the unit backwards until its connectors are fully engaged with the matingconnectors of the mounting tray.

(c) If necessary, gently lift the front of the unit to make sure that the hold-downassembly mates properly with the tray hold-down hooks.

(d) Tighten the hold-down knob.



B. Dataload and Data Transfer Procedures

(1) Loading the Navigation Database from the DL-900 Data Loader.

NOTE: Every 28 days, the FMS navigation database in the NZ-2000must be updated. The loading of the new navigation databasecan only be accomplished while the aircraft is on the ground.

(a) Apply power to the data loader using the appropriate aircraft circuit breaker.

(b) Push the POWER switch on the data loader. The POWER LED shall light andafter the powerup BITE sequence is completed, the DATA LED shall light.

(c) On the data loader, select LEFT or RIGHT.

(d) Insert the navigation database disk in the data loader.

(e) On the CD-810 Control Display Unit (CDU), select the DATA LOAD page fromthe NAV INDEX, page 2.

(f) On the DATA TO BE LOADED page, select NAV DB.

(g) On the TRANSFER OF NAV DB page, select FR LOADER.

(h) On the CONFIRM TRANSFER OF NAV DB page, confirm selection byselecting YES or NO.

(i) Monitor % of loading progress. In the case of the worldwide database, theFMS prompts for insertion of more than one disk. The FMS automaticallybegins reading the next disk. When complete, the message DB TRANSFERCOMPLETE is displayed and the FMS does a restart.

NOTE: If power is interrupted, ABORT selected, or otherproblems stop the loading, the data load processmust be repeated from the beginning.

(j) Remove the disk and turn off the data loader. Remove from the aircraft if notpermanently installed.

(2) Transferring the Custom Database To or From the DL-900 Data Loader.

The custom database can be transferred to or from the data loader. When loadingthe custom database from the data loader, the custom database is completelyreplaced by the contents of the disk including stored flight plans and pilot definedwaypoints. When transferring the custom database to a disk, both the pilot definedwaypoints and flight plans are transferred. This option keeps a permanent record ofthe custom database for loading in case of NZ-2000 replacement or other losses ofthe custom database. Refer to the following steps to transfer the custom database:



(a) If the DL-900 Data Loader is not installed in the aircraft, connect the dataloader cable to the aircraft connector.

(b) Apply power to the data loader using the appropriate aircraft circuit breaker.

(c) Push the POWER switch on the data loader. The POWER LED shall light andafter the powerup BITE sequence is completed, the DATA LED shall light.

(d) On the data loader, select LEFT or RIGHT.

(e) If transferring from the data loader to the NZ-2000, insert the custom databasedisk in the data loader. If transferring from the NZ-2000 to the data loader,insert a formatted disk. If a disk needs formatting, use the MAINTENANCEpage option.

(f) On the CD-810 Control Display Unit (CDU), select the DATA LOAD page fromthe NAV INDEX, page 2.

(g) On the DATA TO BE LOADED page, select CUSTOM DB.

(h) On the TRANSFER OF CUSTOM DB page, select TO LOADER or FRLOADER depending on whether you are transferring data from or to the dataloader.

(i) On the CONFIRM TRANSFER OF CUSTOM DB page, confirm selection byselecting YES or NO.

(j) Monitor % of loading progress. When complete, the message DB TRANSFERCOMPLETE is displayed. The FMS does a restart in the case where thecustom database was loaded from the data loader.

NOTE: If power is interrupted, ABORT selected, or otherproblems stop the loading, the data load processmust be repeated from the beginning.

(k) Remove the disk and turn off the data loader. Remove from the aircraft if notpermanently installed.


The NZ-2000 battery pack can be replaced by the customer. The battery pack is stockedunder Honeywell Part No. 7020116-1 and consists of two AA lithium thionyl chloridebatteries shrink-wrapped together and connected to a lead set. A No. 1 Phillipsscrewdriver is required to access the battery pack during removal and replacement. Allbattery packs have a manufacturer’s date code in WW/YY (week/year) format. Batterypacks with date codes exceeding 3 years of age should not be used for replacement.



(1) Battery Pack Removal

CAUTION: IF AN NZ-2000 BATTERY IS GOING TO BE REMOVED, THE CUSTOMAND NAVIGATION DATABASE WILL BE LOST. THE CUSTOMDATABASE MUST BE DOWNLOADED FROM THE MEMORY TO A3.5-INCH DISKETTE. THE CUSTOM DATABASE WILL NEED TO BEUPLOADED TO THE NZ-2000 ALONG WITH THE CURRENTNAVIGATIONAL DATABASE SUPPLIED BY HONEYWELL AFTER THEBATTERY IS REPLACED. REFER TO THE PROCEDURES INPARAGRAPH 24.B.(1) AND 24.B.(2).

(a) Download the custom database in accordance with paragraph 24.B.(2).

(b) Remove power from the NZ-2000.

(c) Remove the NZ-2000 in accordance with paragraph 24.A.

(d) Remove the four screws which secure the fan/battery access door. Thescrews are on the left and right side of the chassis near the fan housinglocated at the rear of the unit.

(e) Open the fan/battery access door to gain access to the battery pack. Thedoor is hinged at the bottom.

(f) The battery pack is secured to the door with a bracket and two screws.Remove the two screws and the retaining bracket.

(g) Disconnect the battery pack lead set from the header on the fan/filter card andremove the battery pack from the unit.

(2) Battery Pack Installation

(a) Position the battery pack into the fan/battery access door so the lead set exitsclosest to the mating header on the fan/filter card.

(b) Place the retaining bracket over the battery pack and install the two screws tosecure the battery pack.

(c) Connect the battery pack lead set to the mating connector on the fan/filtercard. The lead set connector is keyed to ensure the correct polarity (the keyin the lead set connector must be positioned over the missing pin on themating header). Push down on the connector until it seats fully against theheader.

(d) Close the fan/battery access door and install the four screws to secure thedoor.

(e) Install the NZ-2000 in accordance with paragraph 24.A.



(f) Apply power to the NZ-2000 and enter the date and time on the CDU. Thisstep is necessary to place the ICM7170 Clock/Calender chip in low powermode. If the ICM7170 is not initialized, the battery life will be greatly reduced.

(g) Refer to procedures in paragraph 24.B.(1) and 24.B.(2) for loading thenavigational and custom database.



25. Procedure for the PC-400 Autopilot Controller


(1) Remove the PC-400 Autopilot Controller.


(b) Slide the unit out of the aircraft mounting location and disconnect the cableconnector.

(2) Reinstall the PC-400 Autopilot Controller.

(a) Mate the cable connector with the unit connector and slide the unit into theaircraft mounting location.



Not applicable.


Not applicable.





26. Procedure for the RCZ-851(X) Integrated Communications Unit


(1) Remove the RCZ-851(X) Integrated Communications Unit.

(a) Cut the safety wire and loosen the thumbnuts.


(2) Reinstall the RCZ-851(X) Integrated Communications Unit.


(a) Place the unit on the mounting tray. Slide the unit backward until itsconnectors are fully engaged with the mating connectors of the mounting tray.

(b) Tighten the thumbnuts and attach the safety wire.

NOTE: Instructions for the removal and reinstallation of aCOM module are contained with the replacementmodule.

B. Adjustment Procedure

NOTE: All adjustments on the COM Unit are set at the factory for typical operatingconditions. Most COM Unit installations should not require any adjustments.If an adjustment is necessary, perform the adjustment in accordance with thefollowing procedures. See Figure 4-5 for the adjustment locations.

(1) Microphone Level Adjustment

Because of differences in microphone characteristics, it may be necessary to resetthe MIC Level Adjustment to obtain the desired modulation level.

(2) Sidetone Level Adjustment

The sidetone level on the COM Unit is preset at the factory. If a change in sidetonelevel is desired, the adjustment should first be attempted on the Audio Control Unit.Refer to paragraph 9.B. of this section. If the desired level cannot be obtained byAudio Control Unit adjustments, adjust the Sidetone Level on the COM unit to obtaindesired sidetone level.

(3) Master Audio Adjustment

The Master Audio Adjustment controls sidetone and receiver audio. This adjustmentshould not be changed, as any adjustment will adversely affect audio input levels inthe AV-850A Audio Control Unit.




Not applicable.



MIC LEVELADJUST

MASTERAUDIO

ADJUST

SIDETONE LEVELADJUST

AD-17752@

Figure 4-5. COM Unit Adjustment Locations

27. Procedure for the RM-855 Radio Management Unit (RMU)


(1) Remove the RM-855 RMU.

(a) Loosen the clamp screws on the panel at each top corner of the unit.

(b) Without turning the screws, push them straight into the panel. This willrelease the clamp.

(c) Slide the RMU out of the panel and disconnect the cable connector.



(2) Reinstall the RM-855 RMU.

(a) Mate the cable connector with the RMU connector.

(b) Slide the RMU into the panel.


Not applicable.


Replacement of the tuning knobs.

(1) Use a 0.060-inch O.D., 6 flute, Bristol wrench to loosen the setscrews.

(2) Remove the defective knob.

(3) On new knobs, make sure that the setscrews are out far enough to allow the knob toslide onto the shaft. Apply retaining compound to setscrews.

(4) Slide the large tuning knob onto the shaft.

(5) Make sure that the space between the knob and the bezel is approximately0.025 inch (0.6 mm).

(6) Tighten both No. 4-40 setscrews with the Bristol wrench.

(7) Recheck spacing between the knob and the bezel to make sure that knob has notslipped during installation.

(8) Slide the small tuning knob onto the shaft, making sure that the small tuning knobdoes not rub against the large tuning knob.

(9) Align the access holes in the large tuning knob with the setscrews in the small tuningknob.

(10) Tighten both No. 4-40 setscrews with the Bristol wrench.

(11) Recheck to make sure that the small tuning knob has not slipped during installation,and is not rubbing against the large tuning knob.





28. Procedure for the RNZ-851(X) Integrated Navigation Unit


(1) Remove the RNZ-851(X) Integrated Navigation Unit.

(a) Cut the safety wire and loosen the thumbnuts.


(2) Reinstall the RNZ-851(X) Integrated Navigation Unit.


(a) Place the unit on the mounting tray. Slide the unit backward until itsconnectors are fully engaged with the mating connectors of the mounting tray.

(b) Tighten the thumbnuts and attach the safety wire.

NOTE: Instructions for the removal and reinstallation of aNAV module are contained with the replacementmodule.


All adjustments on the NAV Unit are set at the factory for typical operating conditions.Most NAV Unit installations should not require any adjustments. If an adjustment isnecessary, perform the adjustment in accordance with the following procedures. NAV unitshave holes in the top cover and the holes are labeled. See Figure 4-6 for NAV Unitadjustment locations.

Some procedures below refer to digital and analog audio signals. The digital audio is the"normal" audio from the AV-850A Audio Control Unit. The analog audio signals are thetraditional audio signals used in aircraft. VOR/LOC analog audio is used for theemergency backup audio system.

(1) LOC Audio Level Adjustment

The LOC Audio adjustment controls the VOR/LOC receiver emergency audio levelout of the AV-850A. This adjustment will not affect the digital audio level from theAV-850A. Emergency audio for the VOR/LOC is a backup system for the digitalaudio and is connected on the side of the aircraft that has the CD-850 ClearanceDelivery Control Head (CDH) installed.

Before making any adjustments of the LOC audio level, perform the followingprocedure to determine if adjustment is needed.



AD-51154@

LOC AUDIOMKR AUDIO(NOT USED) ADF AUDIO MKR SENS LOW MKR SENS HIGH

DME ACT 2AUDIO

DME ACT 1AUDIO

Figure 4-6. NAV Unit Adjustment Locations



(a) Set the HEADPHONE volume control on the AV-850A Audio Control Unit to itstypical operating position and push in the EMER button on the AV-850A.

(b) Push the NAV AUDIO button on the CD-850 CDH and verify NAV AUDIO isshown on the CDH display.

(c) Tune the CDH to a VOR station, either in flight or on the ground and verify aflag-out-of-view condition on an indicator.

(d) Listen to the VOR emergency audio with a set of headphones.

(e) Adjust the audio level as follows:

• Find the LOC AUDIO adjustment on top of the NAV unit and increase ordecrease audio level as desired

• For an increase of audio level, turn the adjustment clockwise

• For a decrease of audio level, turn the adjustment counterclockwise.

(2) MKR Audio Level Adjustment

(3) MKR High and Low Sensitivity Threshold Adjustments

The MKR High and Low Sensitivity Adjustments control how long the marker lampswill be ON and how long the marker audio will be heard when crossing a markerground station. These adjustments will not affect the marker digital or analog audiooutput levels, only the duration of the marker audio and display.

The High sensitivity mode is typically used for "enroute" flying, i.e., high altitudes andthe Low sensitivity mode is typically used during approach, i.e., low altitudes,typically when flying an ILS.

To determine if either High or Low sensitivity needs adjustment, perform thefollowing flight test procedure:

(a) Electromagnetic Compatibility

With all aircraft avionics systems operating in flight, verify by observation, thatno adverse effects are present.

(b) Marker Beacon Performance Checks

1 In low sensitivity mode, the marker beacon annunciator light should beilluminated for a distance of 2,000 to 3,000 feet when flying at an altitudeof 1,000 feet AGL on the localizer centerline in all flap and gearconfigurations.



NOTE: To determine distances of 2,000 to 3,000 feettime the marker beacon light duration,determine ground speed and then use theformulas listed below:

Upper limit = 1775

Seconds Ground Speed in Knots

Lower limit = 1183

Seconds Ground Speed in Knots

2 In high sensitivity mode, the marker beacon annunciator light and audio willremain on longer than when in low sensitivity.

3 The audio signal should be of adequate strength and sufficiently free frominterference to provide positive identification.

4 As an alternate procedure, cross the outer marker at normal ILS approachaltitudes and determine adequate marker aural and visual indication.

NOTE: When adjusting Marker High and Lowsensitivity thresholds, the High sensitivityadjustment must always be set to the desiredthreshold before Low sensitivity adjustment isperformed.

5 Find the adjustments on top of the NAV Unit. To cause the Marker lampsand audio to stay ON for a shorter length of time, turn the MKR SENSHIGH or MKR SENS LOW adjustment clockwise.

(4) ADF Audio Level Adjustment

The ADF AUDIO adjustment controls the ADF receiver analog audio level. Thisadjustment will not affect the digital audio output level from the Honeywell AV-850AAudio Control Unit.

(a) For an increase of audio level, turn the adjustment clockwise.

(b) For a decrease of audio level, turn the adjustment counterclockwise.

(5) DME Audio Level Adjustment

The DME audio adjustments control the DME analog audio levels. Theseadjustments will not affect the digital output level from the Honeywell AV-850A AudioControl Unit.

(a) For an increase of audio level, turn the adjustment clockwise.

(b) For a decrease of audio level, turn the adjustment counterclockwise.




Not applicable.



29. Procedure for the RNZ-851/RCZ-851 Strap Board Assembly

CAUTION: THE STRAP BOARD ASSEMBLY CAN BE DAMAGED BY ELECTROSTATICDISCHARGE (ESD). GROUND YOURSELF BEFORE HANDLING THE ASSEMBLY,AND ALWAYS HANDLE IT BY THE EDGES.

NOTE: The Integrated Radio System contains a total of four strap board assemblies; oneCOM and one NAV assembly contained in each remotely mounted strappingassembly.


(1) Remove the RNZ-851/RCZ-851 Strap Board Assembly.

(a) Remove the two screws and cover from the strapping assembly.

(b) Remove and set aside the three roundhead screws and lockwashers securingthe COM or NAV strap board assembly.

(c) Gently pull out on the assembly and disconnect the flat connector from theassembly.

(2) Reinstall the RNZ-851/RCZ-851 Strap Board Assembly.

CAUTION: BE VERY CAREFUL WHEN CUTTING CONFIGURATION STRAPS SOAS NOT TO DAMAGE THE STRAP BOARD ASSEMBLY.

NOTE: If the strap board assembly is removed from the aircraft andreplaced with an assembly from customer owned shelf stockor was obtained from Honeywell, the configuration straps willhave to be cut in accordance with the list in Section 3 of thismanual.

(a) Handle the strap board assembly by its edges and attach the flat connector tothe assembly.

(b) Secure the assembly using the three roundhead screws and lockwashers thatwere removed and previously set aside.

(c) Check that the harness grommet is positioned at the bottom of slot in chassis.




Not applicable.


Not applicable.



30. Procedure for the RT-300 Radio Altimeter Receiver Transmitter

A. Removal and Reinstallation Procedure

(1) Remove the RT-300 Radio Altimeter Receiver Transmitter.

(a) Disconnect the aircraft cable and antenna connectors.

(b) Remove and set aside the mounting hardware on the front of the unit andloosen the mounting hardware on the rear of the unit and remove the unit.

(2) Reinstall the RT-300 Radio Altimeter Receiver Transmitter.

(a) Slide the unit into the mounting tray and secure with the applicable hardware.

(b) Mate the aircraft cable and antenna connectors.


Adjust the radio altimeter display zero ground.

NOTE: There are two ways that the zero ground adjustment can be accomplished.The preferred and most accurate way is described in paragraph 30.B.(1). If acable (Figure 4-7) is not available to perform this procedure, then thealternate procedure in paragraph 30.B.(2) can be used.

(1) Preferred RT-300 Zero Ground Adjustment.

(a) Connect the cable (Figure 4-7) in-line with the aircraft cable and the RT-300.

(b) Check that the RT-300 transmit and receive ports (J2 and J3) are connectedto the antennas.

(c) Connect a digital voltmeter (DVM) to the cable meter leads.

(d) Apply power to the RT-300.

(e) Adjust the potentiometer, that is accessible through hole in front panel ofRT-300, for 0 ± 2 mV indication on DVM.



(f) Remove power and disconnect the adjustment cable.

(g) Connect the aircraft cable to the RT-300.

(2) Alternate RT-300 Zero Ground Adjustment.

(a) Apply power to the RT-300.

(b) Adjust the potentiometer, that is accessible through hole in front panel ofRT-300, until a positive radio altitude is displayed on one of the PFDs.

(c) Adjust the potentiometer for zero foot display indication on the PFD.

TO RT-300

TOAIRCRAFT

CABLE

A

B

C

D

E

F

G

H

J

K

L

M

N

P

R

S

T

U

V

W

X

Y

Z

a

b

c

A

B

C

D

E

F

G

H

J

K

L

M

N

P

R

S

T

U

V

W

X

Y

Z

a

b

c

MS3126F16-26S MS3121F16-26P

NOTE 2

NOTE4

(+) (-)

NOTES: 1. ALL WIRING 22 AWG, EXCEPT AS NOTED.

2. WIRING FOR PINS b AND c IS 20 AWG.

3. LENGTH OF CABLE IS SIX INCHES.

4. LENGTH OF DVM LEADS ARE AS REQUIRED.CONNECT PLUG TO LEADS AS REQUIRED TOCONNECT TO DVM. AD-31291@

Figure 4-7. RT-300 Zero Adjustment Cable




Not applicable.



31. Procedure for the RT-910 TCAS Computer Unit


(1) Remove the RT-910 TCAS Computer Unit.

(a) Turn the fluted knob of the Boxmount hold-downs counterclockwise (CCW).

NOTE: DO NOT disengage the white locking lever at thistime. Continue to turn fluted knob until hold-downsare fully disengaged.

(b) Disengage the white locking lever by turning it CCW.

(c) Slowly pull forward on the unit handle to separate the unit and the trayconnectors and slide the unit out of the tray.

(2) Reinstall the RT-910 TCAS Computer Unit.

(a) Slide the unit into the mounting tray and push it completely to the rear,partially engaging the unit connectors.

(b) Raise the hold-down extractor so that the front lip of the extractor rests justbehind the lower panel of the unit. Turn the white locking lever clockwise(CW) as far as it can go, making sure that the cup engages the hook.

(c) Turn the fluted knob of the hold-down extractor CW until the red indicatordisappears.


Not applicable.


Not applicable.





32. Procedure for the SM-200 Servo Drive and SB-201 Drum and BracketAssembly


(1) Remove the SM-200 Servo Drive.

(a) Disconnect the cable connector from the servo drive.

(b) Cut the safety wire and remove the four screws and lock washers securing theservo drive to the drum and bracket assembly.

(c) Slide the servo drive out of the drum and bracket assembly.

(2) Reinstall the SM-200 Servo Drive.

(a) Slide the servo drive into the rear of the drum and bracket assembly andsecure with four screws, Honeywell Part No. 4011086, and lock washers.Safety wire all four screws with Low Mu Monel wire, 0.020-inch diameter.

(b) Mate the servo drive connector with the cable connector.

(3) Remove the SB-201 Drum and Bracket Assembly.

(a) Remove the servo drive in accordance with paragraph 32.A.(1).

(b) Release the bridle cable tension.

(c) Cut the safety wire on the four screws securing the retaining plate. Removeand set aside the screws and the retaining plate.

(d) Remove and set aside the four cable keepers, Honeywell Part No. 2518330.

(e) Cut the safety wire. Remove and set aside two screws securing the swagedcable terminals to the drum.

(f) Unwrap the bridle cables from the drum.

(g) Remove and set aside four nuts, bolts, and washers securing the drum andthe bracket assembly to the airframe.

(h) Lift the drum and bracket assembly away from the airframe.



(4) Reinstall the SB-201 Drum and Bracket Assembly.

(a) Mount the drum and bracket assembly rigidly to the airframe with four 1/4-inchdiameter bolts of sufficient length, and four suitable lockwashers and nuts.

INSTALLATION CRITICAL

TO MAKE SURE CABLE TERMINAL CAPTURE, USE ONLY 0.138-32-NC-2ASTAINLESS STEEL DRILLED SCREWS, HONEYWELL PART NO. 2554911-1.STANDARD FILLISTER-HEAD SCREWS MAY NOT PROPERLY RETAIN THECABLE TERMINAL.

(b) Wrap the bridle cables around the servo bracket drum. Secure the swagedcable terminals to the servo bracket drum with the screws removed inparagraph 32.A.(3)(e), or if a new servo, use the screws supplied with the newservo. Safety wire the screws through adjacent holes in the drum with Low MuMonel wire, 0.020-inch diameter and 4 inches long.

(c) Adjust the control system and the bridle cables to the proper tension asinstructed in the aircraft maintenance manual.

INSTALLATION CRITICAL

TO MAKE SURE THAT THE CABLE CANNOT JAM BETWEEN THE DRUM ANDKEEPERS, THE DISTANCE BETWEEN THE KEEPERS AND DRUM IS MEASUREDAFTER THE KEEPERS AND RETAINING PLATE ARE INSTALLED. THE DISTANCEBETWEEN THE DRUM AND KEEPERS MUST NOT EXCEED 0.040 INCH ANDMUST NOT BE LESS THAN 0.005 INCH. THE 3/32-INCH CABLE DIAMETER ISVERIFIED. THESE ARE CRITICAL INSTALLATION REQUIREMENTS.

(d) Install two of the four cable keepers removed in paragraph 32.A.(3)(d), on theservo bracket at the points of cable tangency to the drum. The other twokeepers must be located at 90 degrees from the first two.

(e) Install the retaining plate, Honeywell Part No. 2518332, on the slotted end ofthe cable keepers using the four 5/16-inch long, No. 8-32, drilled fillister-headscrews removed in paragraph 32.A.(3)(c). Safety wire these four screws withLow Mu Monel wire, 0.032-inch in diameter and 4 inches long.

(f) Reinstall the servo drive in accordance with paragraph 32.A.(2).


Not applicable.


Not applicable.





33. Procedure for the WC-6X0/8X0 Weather Radar Controller


(1) Remove the Weather Radar Controller.


(b) Slide the unit out of the aircraft mounting location and disconnect the cableconnectors.

(2) Reinstall the Weather Radar Controller.

(a) Mate the cable connector with the unit connector and slide the unit into theaircraft mounting location.



Not applicable.



NOTE: It is recommended that this procedure be performed in a clean workbenchenvironment. Each knob has two No. 2-56 setscrews. Use a 0.048-inchO.D., 6 flute, Bristol wrench.

(1) Loosen the setscrews.


(3) On new knobs, make sure that the setscrews are out far enough to allow the knob toslide onto the shaft. Apply retaining compound to setscrews.

(4) Slide the knob onto the shaft.

(5) Make sure that the space between the knob and the front panel is approximately0.030 inch (0.8 mm).

(6) Tighten the setscrews.

(7) Visually check the spacing between the knob and the front panel to make sure thatthe knob has not slipped during installation.





34. Procedure for the WU-6X0/8X0 Antenna and Receiver Transmitter Unit(RTA)


(1) Remove the RTA.

(a) Disconnect the cable connector from the unit.

(b) Remove and set aside the hardware used to attach the unit to the airframe.

(2) Reinstall the RTA.

(a) Attach the unit to the airframe with the applicable hardware.

(b) Mate the aircraft cable connector with the unit connector.


(1) Adjust the Antenna and Receiver Transmitter Unit on the ground.

NOTE: This procedure must be done by two persons. One in thecockpit and one at the RTA unit.

WARNINGS: 1. POSITION THE AIRCRAFT RADAR SYSTEM TO FACE AWAYFROM BUILDINGS, LARGE METAL STRUCTURES, OR OTHERAIRCRAFT IN CLOSE PROXIMITY BEFORE YOU TURN IT ON.THEY ARE LIKELY TO RETURN LARGE AMOUNTS OFREFLECTED ENERGY AND CAUSE DAMAGE TO THE SYSTEM.

2. DO NOT OPERATE RADAR WITHIN 50 FEET OF OTHERAIRCRAFT OR OBJECTS, OR CLOSER THAN 100 FEET TOREFUELING OPERATIONS.

3. NEVER LOOK DIRECTLY INTO THE ANTENNA (WHILE IT ISOPERATING) FOR PROLONGED PERIODS OF TIME AT ACLOSE RANGE. SERIOUS EYE TISSUE DAMAGE CAN RESULTDUE TO THE HEATING EFFECT OF RADAR ENERGY. THEMAXIMUM PERMISSIBLE EXPOSURE LEVEL (MPEL)BOUNDARY IS A RADIUS OF 9 FT (3.66 M) FOR WU-650/870UNITS AND 25.7 FT (7.8 M) FOR WU-660/880 UNITS.REFERENCE SECTION 2, CHAPTER 5 FOR DETAILS.

(a) Before applying power to the radar, set the SCAN and XMTR toggle switches,on the RTA housing, to OFF (toward antenna).

(b) Level the pitch and roll axes of the aircraft relative to the earth’s surface.

(c) Verify that the mounting surface of the RTA is aligned to the pitch and rollreference axes of the aircraft within ± 1/4 degree.

(d) Apply aircraft power as necessary.



(e) On the WC-XXX Radar Controller, make the following selections:

• RADAR = SBY

• TILT = 0°

• GAIN = Push knob in for preset gain.

(f) Verify, in the SBY mode, that the flat plate antenna is at 0 within ± 1/2 degree.If not, adjust the elevation feedback potentiometer R1 (WU-650/870 only) for 0±1/4 degrees.

(g) Push and hold the AHRS TEST switch located on the maintenance panel.This simulates 15 degrees of nose up pitch and 5 degrees of right roll.

(h) Verify that the antenna tilts down 15 ± 2 degrees.

(i) Release the AHRS TEST switch.

(j) Pull out the GAIN knob to select variable gain. This places the RTA in the rollcalibration mode.

(k) Press and hold the AHRS TEST switch.

(l) Verify that the antenna tilts up 5 ± 1 degrees.

(m) Release the AHRS TEST switch.

(n) Remove power from the radar.

(o) Set the SCAN and XMTR toggle switches, on the RTA housing, to ON (awayfrom antenna).

(p) Apply aircraft power as necessary.

(q) Verify, in the SBY mode, that the antenna is tilted up 15 ± 2 degrees.

(2) Adjust WU-650/870 Roll Offset Compensation.

NOTE: This procedure is for WU-650/870 installations only andshould be done while airborne. The roll offset is preset at thefactory so the procedure is necessary only if a roll offset erroris detected.

(a) At an altitude of 10,000 feet (3,048 meters) or greater above the ground,establish a wings-level cruise attitude.

(b) On the WC-650/870 Radar Controller, select WX Mode, 100 NM range,variable GAIN, and RCT OFF. Observe that the VAR is displayed in the WXmode box on the MFD.

(c) Adjust the antenna tilt down until a fairly solid band of ground clutter is visible.



(d) Push the RCT button once and then three more times within 4 seconds. VARshould not be displayed. This puts the radar in the roll compensation mode.

(e) Push the RCT button once more and make sure that VAR is not displayed. Ifit is, repeat this step.

(f) Adjust the GAIN control on the WC-650/870 Radar Controller until the groundclutter display is symmetrical.

(g) Do not touch the manual GAIN control once the display is adjusted properly.

(h) Push the RCT button once and then three more times within 4 seconds. Thiscauses the WU-650/870 to exit the roll compensation mode. When VAR isdisplayed again, the roll compensation mode has been exited.

(i) Set the variable or preset GAIN as desired.

(j) This compensation data is now stored in nonvolatile memory in theWU-650/870 and will not be erased when power is removed from the system.

(3) Adjust WU-660/880 Roll Offset Compensation.

There are two stabilization trim modes available for WU-660/880 installations. If theSTAB TRIM ENABLE strap (59J1-61) is open, only adjustment of roll offset isavailable. If the STAB TRIM ENABLE strap is grounded, roll offset, pitch offset, rollgain, and pitch gain are available for adjustment.

WU-660/880 radar installations on Embraer 145 aircraft are configured with theSTAB TRIM ENABLE strap open which means only roll offset is adjustable.

NOTE: This procedure is for WU-660/880 installations only and mustbe done while airborne. The roll offset is preset at the factoryso the procedure is necessary only if a roll offset error isdetected.

(a) At an altitude of 10,000 feet (3,048 meters) or greater above ground level,establish a wings level cruise attitude.

(b) Select WX mode and 25 NM range on the radar controller. Adjust the antennatilt down until a fairly solid band of ground clutter is visible. Adjust the tilt untilthe green region of the ground returns start at about 20 NM.

(c) Enter the stabilization trim mode by pushing the STAB button, on the radarcontroller, four times within 3 seconds. A display with text instructions shouldbe displayed on the MFD. See Figure 4-8 for a typical display. The displaywill have text overlays on the radar data so that ground returns can be seen tomake the adjustments.



(d) To make a roll offset change, pull out the GAIN knob on the radar controller.See Figure 4-9 for a typical display. The offset range is from -2.0 to +2.0degrees and is adjusted by the GAIN knob. Polarity is such that clockwiseknob rotation causes the antenna to move down when scanning on the rightside.

(e) While flying straight and level, adjust the GAIN knob until the ground clutterdisplay is symmetrical.

(f) Push in the GAIN knob. When it is pushed in, the display will return to theprevious message.

(g) Set the mode switch on the radar controller to any other position to exit themode and save the offset value in non-volatile memory.


Not applicable.





NOTE: THE DISPLAY SHOWN MAY NOT REPRESENT ACTUAL FLIGHT CONDITIONS.

BEZEL MENU DISPLAY AREA

360

N

3

6

33

30

5050

-10

WX

WX

STAB KEY NEXTPULL OUT GAIN KNOB TO ADJUST

ROLL OFFSET:

25

+15

300

SATTATTAS

FMSKDVT12.512

NMMIN

31547.0

SYSTEM PAGEDISPLAY AREA

AD-51677@

+25

Figure 4-8. Typical PRIMUS® 660/880 Stabilization Trim Mode Entry Page



NOTE: THE DISPLAY SHOWN MAY NOT REPRESENT ACTUAL FLIGHT CONDITIONS.

BEZEL MENU DISPLAY AREA

360

N

3

6

33

30

5050

-10

1F1BB:STRAPS

STA

B UNCAL

VARWX

WX

ROLL OFFSET: -0.2°

WX

+5.0°PULL OUT GAIN KNOB WHEN DONE

AIR

CRAFT ROLL:

25

+15

300

SATTATTAS

FMSKDVT12.512

NMMIN

31547.0

SYSTEM PAGEDISPLAY AREA

AD-51678@

+25

Figure 4-9. Typical PRIMUS® 660/880 Stabilization Trim Adjustment Page



SECTION 5SHIPPING, HANDLING AND STORAGE

Refer to manual, Pub. No. 09-1100-01, for detailed procedures for preparing all System componentsfor storage or shipment.



(Blank Page)


TABLE OF CONTENTS - SECTION 6

SECTION/PARAGRAPH/TITLE PAGE


6 HONEYWELL SUPPORT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-1

1. Worldwide Exchange/Rental Program for Regional Airlines . . . . . . . . . . . . . . 6-1

2. Contracted Maintenance Agreements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-1

3. Test Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-1

4. Customer Service Order Desk (End Item LRUs) . . . . . . . . . . . . . . . . . . . . . . . 6-2

5. Customer Support - Material (Repair Piece Part Spares Services) . . . . . . . . . 6-2

6. Warranty . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-3

7. Customer Engineering . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-3

8. Training . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-3

9. Honeywell Facilities . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-4

10. Regional Airline Customer Engineering Locations . . . . . . . . . . . . . . . . . . . . . 6-6



(Blank Page)



SECTION 6HONEYWELL SUPPORT

1. Worldwide Exchange/Rental Program for Regional Airlines

Honeywell’s Worldwide Exchange/Rental Program for Regional Airlines provides an extensiveservice for LRU End Item products, complementing our worldwide support center network.This service is intended to supplement a sound spares program, not to serve as a primarysource of spares.

For routine exchange or rental service, or for further information regarding Exchange or Rentalunits, contact any of the facilities listed in Honeywell Facilities, paragraph 9 of this section.

2. Contracted Maintenance Agreements

Regional airlines have a number of options from which to choose to support their Honeywellavionics in day-to-day operations. These choices involve trade-offs between start-upexpenditures for test equipment, shop facilities, personnel training, etc., versus costs associatedwith having repairs accomplished by an outside agency.

Airlines can also consider different levels of in-house repair (Level 2 - repair by SRU or moduleexchange, or Level 3 - repair by piece part replacement).

A variety of contracted maintenance agreements for repairs accomplished by a HoneywellSupport Center are available: time and material repair, flat rate repair, cost per flight hourpricing, or other individually customized support concepts covering all Honeywell LRUs installedon regional aircraft. These agreements represent cost effective means for an airline to achievefinancial maintenance goals, while minimizing start-up costs.

For full details on Honeywell maintenance agreements, or consultation on other customizedsupport options, contact Honeywell Product Support Marketing in Phoenix, Arizona at602-436-3150.

3. Test Equipment

Specialized test equipment is not required for normal flight line maintenance of Honeywellavionics. Certain standard, commercially available avionics aids such as ramp (signal)checkers, oscilloscopes, meters, etc., may be useful for more detailed troubleshooting. Abreakout box can also be helpful for certain equipment, and availability of this item can bediscussed with a Honeywell Customer Engineer.

Full details of appropriate Honeywell manufactured test equipment required for shop level repairof specific Honeywell equipment are available through Customer Engineering, or from ProductSupport Marketing.

To request a quote, or to place an order for Honeywell manufactured test equipment, contactHoneywell’s Customer Service order desk in Phoenix, Arizona at 602-436-4512.



4. Customer Service Order Desk (End Item LRUs)

Honeywell’s Customer Service order desk in Phoenix, Arizona is available to receive orders orprocess inquiries for new, end item LRU spares and/or retrofit avionics products for Honeywell’sregional airline customers.

To place normal orders, determine order status, upgrade an existing order, or request price anddelivery information, please contact the Customer Service Representative at:

• Telephone Number . . . . . . . . . . . . . . . . . . . . 602-436-8925

• FAX Number . . . . . . . . . . . . . . . . . . . . . . . . 602-436-7100.

5. Customer Support - Material (Repair Piece Part Spares Services)

A. Routine Repair Piece Part Spares Orders

Regional airlines desiring to place routine repair piece part spares orders, determine orderstatus, upgrade an existing order, or request price and delivery for spares should contactthe Customer Service Representative in Phoenix, Arizona at:

• Telephone Number . . . . . . . . . . . . . . . . 602-436-6105

• FAX Number . . . . . . . . . . . . . . . . . . . . . 602-436-1500.

B. AOG Repair Piece Part Service

AOG repair piece part spares service for regional airlines is available 24 hours a day,every day. After normal hours call:

• Inside USA . . . . . . . . . . . . . . . . . . . . 1-800-872-7739

• Outside USA . . . . . . . . . . . . . . . . . . . . . 214-402-4300

• Australia . . . . . . . . . . . . . . . . . . . . . . . 61-3-330-1411

• Canada . . . . . . . . . . . . . . . . . . . . . . 1-800-267-9947

• France . . . . . . . . . . . . . . . . . . . . . . . . 33-61-71-9662

• Singapore . . . . . . . . . . . . . . . . . . . . . . . . 65-542-1313

• United Kingdom . . . . . . . . . . . . . . . . 44-1-256-722200.

To expedite the AOG process, please be prepared to give the operator the airlinename, telephone number, type of aircraft, tail number, and part number causing theAOG situation.



6. Warranty

Honeywell avionics equipment installed on regional airline aircraft are warranted either throughthe aircraft manufacturer, typically beginning on the date the aircraft is delivered, or for itemspurchased direct from Honeywell, beginning on the date the items were shipped from Honeywell.

During the warranty period, Honeywell will at its option, either repair or replace at no charge,each item that is returned to a Honeywell Support Center.

Honeywell also provides a full range of appropriate warranties to cover repair services atHoneywell Support Centers, exchange units and piece part spares. In addition, we will supportin-house warranty repair agreements with airlines which possess the necessary technicalcapability.

For additional details regarding the Honeywell Warranty, or response to a specific question,please contact Warranty Administration at:


• FAX Number . . . . . . . . . . . . . . . . . . . . . . . . 602-436-3165.

7. Customer Engineering

A key element in Honeywell’s regional airline support is our worldwide Customer Engineeringorganization. The members of this group are strategically located around the world at airtransport hubs and manufacturing locations. These individuals have earned an excellentreputation within the avionics industry as the result of their high level of education, experience,dedication and responsiveness.

Customer Engineering is ready to provide regional airlines with on-site technical assistance,provisioning consultation, training and regulatory agency coordination. In addition, customerengineers will provide engineering interface assistance for other inter-related equipment on theaircraft, and will support your maintenance engineers and technicians. Continuing assistance isprovided through telephone consultation, or at the airlines facilities, as requirements dictate.

Refer to the list at the end of this section for Regional Airline Customer Engineering locations,telephone and fax numbers.

8. Training

Honeywell’s dedicated Customer training staff is available to assist airlines in acquiring thetechnical skills and knowledge needed to operate and maintain Honeywell products.

Customer Training conducts formal courses on regional airline systems/products at Honeywell’sCustomer Training Center in Phoenix, Arizona, and at selected locations worldwide. Coursesare scheduled annually based on customer interest and new aircraft delivery projections. Aregularly updated Honeywell Customer Training Schedule brochure gives full details of alltraining courses offered.



Honeywell offers the following level of training courses:

• Operational (Pilot) Training

• Flight Line Maintenance Training

• Component Level Maintenance Training.

For full details, and information on Honeywell training courses, or a copy of the HoneywellCustomer Training Schedule, contact the Customer Training Department in Phoenix, Arizona at:


• FAX Number . . . . . . . . . . . . . . . . . . . . . . . . 602-436-4100.

9. Honeywell Facilities

A. North and South America

Central Support Center

Honeywell Inc.1830 Industrial Ave.Wichita, KS 67216

Tel: 316-522-8172Fax: 316-522-2693

Northwest Support Center

Honeywell Inc.4150 Lind Ave. SouthwestRenton, WA 98055

Tel: 206-251-9511Fax: 206-251-9368

Dallas Support Center

Honeywell Inc.7825 Ridgepoint Drive

Irving, TX 75063

Tel: 214-402-4300Fax: 214-402-4999

Ohio Support Center

Honeywell Inc.8370 Dow CircleStrongsville, OH 44136

Tel: 216-243-8877Fax: 216-243-1954

Canada Support Center

Honeywell Ltd.Aerospace Division

3 Hamilton Ave.Ottawa, Ontario K1y 4J4

Canada

Tel: 613-728-4681Fax: 613-728-7084



B. Europe and Africa

France Support Center

Honeywell Aerospace1 rue Marcel Doret - BP14

31701 Blagnac Cedex, France

Tel: 33-56212-1500Fax: 33-56130-0258

United Kingdom Support Center

Honeywell Avionics Systems Ltd.Edison RoadBasingstoke, HampshireRG21 2QDEngland

Tel: 44-1-256-722200Fax: 44-1-256-722201

Authorized Support Center

Apparatebau Gauting GmbHAmmerseestr, 45-39

89317-0 Gauting, Germany

Tel: 49-89-85601-0Fax: 49-89-85601-183

C. Asia and Pacific

Australia Support Center

Honeywell Ltd.Sperry Drive

Trade ParkTullamarine, 3043Victoria, Australia

Tel: 61-3-330-1411Fax: 61-3-330-3042

Singapore Support Center

Honeywell Aerospace Pte. Ltd.2 Loyang CrescentSingapore 1750

Tel: 65-542-1313Fax: 65-542-1212



10. Regional Airline Customer Engineering Locations

A. North and South America

Phoenix, ArizonaTel: 602-436-4400

Fax: 602-436-4100

Seattle, WashingtonTel: 206-656-2705Fax: 206-251-9368

Dallas, TexasTel: 214-402-4332

Fax: 214-402-4399

Wichita, KansasTel: 316-522-8172Fax: 316-522-2693

Reston, VirginiaTel: 703-620-4918

Fax: 703-860-8985

Wheeling, IllinoisTel: 708-577-1753Fax: 708-459-8023

Seattle, WashingtonTel: 206-656-2705

Fax: 206-251-9368

Altanta, GeorgiaTel: 404-952-4445Fax: 404-984-8631

Downsview, Ontario, CanadaTel: 416-375-3819Fax: 416-375-4531

B. Europe and Africa

Basingstoke, EnglandTel: 44-1-256-722200

Fax: 44-1-256-722201

Munich, GermanyTel: 49-89-404072Fax: 49-89-401838

Toulouse, FranceTel: 33-6212-1500

Fax: 33-6130-0258

Paris, FranceTel: 33-1-4473-8785Fax: 33-1-4474-9446

Rome, ItalyTel: 39-6-5037-294Fax: 39-6-5034-406

C. Asia and Pacific

SingaporeTel: 65-542-1313Fax: 65-542-1212

Hong KongTel: 852-832-5681Fax: 852-838-3280

Melbourne, AustraliaTel: 61-3-330-1411Fax: 61-3-330-3042


Documents

Avionic Emb 145-2