Avionic Gulfstream IV-2

HoneywellCommercial Flight Systems Group Business and Commuter Aviation Systems Division Honeywell Inc.BOX 29000

Phoenix, Arizona 85038

SPZ-8000

Digital Automatic Control SystemGulfstream IV

Flight

System Maintenance ManualVolume II Ground Check

22-14-00TITLEPRINTED IN U.S.A PUB. NO. Al 5-1146-38

PAGE

T-1

REVISED 15 APR 1993 1 JUNE 1987

PROPRIETARY NOTICEThis revised document and the information disclosed herein are proprietary data of Honeywell Inc. Neither this document nor the information contained herein shall be used, reproduced, or disclosed to others without the written authorization of Honeywell Inc., except to the extent required for installation or maintenance of recipients equipment. NOTICE - FREEDOM OF INFORMATION ACT (5 USC 552) AND DISCLOSURE OF CONFIDENTIAL INFORMATION GENERALLY (18 USC 1905) This revised document is being furnished in confidence by Honeywell Inc. The information herein falls within exemption (b) (4) of 5 USC 552 and the prohibitions of 18 USC 1905. disclosed

S93

USEREF and PRIMLJS are registered trademarks of Honeywell Inc. COLORCAL, COLORADAR, and LASERTRAK are additional trademarks

of Honeywell

Inc.

22-14-00TITLECopyright 1993 Honeywell Inc. AN Rights Reserved

PAGE

T-2

REVISED 15 APR 1993 1 JUNE 1987

Date Received

READER COMMENTS(Mail or FAX this form to [602] 436-4100) comments and recommendations to improve future editions Your Name Address State Telephone No. Honeywell Pub. No. Manual Title Country FAX ATA No. Date Zip Company/Airline

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RECORD OF REVISIONS- VOLUME 11 Upon receipt of a revision, insert the latest revised pages and dispose of superseded pages. Enter revision number and date, insertion date, and the incorporators initials on the Record of Revisions. The typed initials HI are used when Honeywell Inc. is the incorporator. Revision Number 01 02 03 04 05 06 Revision Date Feb 1/88 Mar 1/89 Ott 1/89 Mar 15/91 Auq 15/91 A~r 15/93 Insertion Date Mar 1/88 [email protected]!ov

By

Revision Number

Revision Date

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By

15/89

A~r 15/91 Nov 1/91 Jul 1/93

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Page RR-1/RR-2 Aug 15/91

Honeywell

GULFSTREAMIV

MAINTENANCE MANUAL

LIST OF EFFECTIVEPAGES- VOLUME II Original Revision Revision Revision .. .. .. .. 0 1 2 3 .. .. .. .. Jun Feb Mar Ott 1/87 1/88 1/89 1/89 Revision Revision Revision . . 4 . . Mar 15/91 . . 5 . . Aug 15/91 . . 6 . . .Apr 15/93

SUBHEADING ANDPAGE Title T-1 T-2 Record of Revisions RR-1/RR-2 List of Effective LEP-1 LEP-2 LEP-3 LEP-4 LEP-5/LEP-6 Pagess s s

REVISION 6 6 6 6 6 6 6 6 6 4 4 4 4 4 6 6 : 6 6 6 6 4 6 6 4 6 4 4 4 44

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HoneywellSUBHEADING ANDPAGE Ground Check (cent) 365 366 367 368 369 370 371 372 373 374 375 376 377 378 379 380 381 382 383 384 385 386 387 388 389 390 391 392 393 394 395 396 397 398 398.1 398.2 398.3 398.4 398.5 398.6 398.7 398.8 398.9 398.10 398.11 398.12 398.13 398.14 398.15 398.16 REVISION 4 4 4 6 4 4 4 4 4 4 4 4 4 6 6 6 6 4 4 4 ; 4 4 4 4 6 6 6 4 6 4 6 4 4 4 6 6 6 4 6 4 4 4 6 4 4 6 4 6

GULFSTREAMIV

MAINTENANCE MANUAL

SUBHEADING ANDPAGE 398.17 398.18 398.19 398.20 398.21 398.22 398.23 398.24 398.25 398.26 398.27 398.28 398.29 398.30 398.31 398.32 398.33 398.34 398.35 398.36 398.37 398.38 398.39 398.40 398.41 398.42 398.43 398.44 398.45 398.46 398.47 398.48 398.49 398.50 398.51 398.52 398.53 398.54 398.55 398.56 398.57 398.58 398.59 398.60 398.61 398.62 398.63 398.64 398.65 398.66 398.67

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HoneywellSUBHEADING ANDPAGE Ground Check (cent) 398.68 398.69 398.70 398.71 398.72 398.73 398.74 398.75 398.76 398.77 398.78 398.79 398.80 398.81 398.82 398.83 398.84 398.85 398.86 398.87 398.88 398.89 398.90 398.91 398.92 398.93 398.94 398.95 398.96 398.97 398.98 398.99 398.100 398.101 398.102 398.103 398.104 398.105 398.106 398.107 398.108 398.109 398.110 398.111 398.112 398.113 398.114 398.115 398.116 398.117 REVISION 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 6 6 4 4 4 6 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 6 4 4 4 4 4 4 4 4 4 4 4

GULFSTRE4MIV

MANUAL

SUBHEADING ANDPAGE 398.118 398.119 398.120 398.121 398.122 398.123 398.124 398.125 398.126 398.127 398.128 398.129 398.130 398.131 398.132 398.133 398.134 398.135 398.136 398.137 398.138 398.138.1/398.138.2 398.139 398.140 398.140.1 398.140.2 398.141 398.142 398.142.1 398.142.2 398.143 398.144 398.145 398.146 398.147 398.148 398.149 398.150 398.151 398.152 398.152.1 398.152.2 398.152.3/398.152.4 398.153 398.154 398.155 398.156 398.157 398.158 398.159 398.160

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HoneywellSUBHEADING ANDPAGE Ground Check (cent) 398.161 398.162 398.163 398.164 398.165 398.166 398.167 398.168 398.169 398.170 398.171 398.172 398.173 398.174 398.175 398.176 398.177 398.178 398.179 398.180 398.181 398.182 398.183 398.184 398.185 398.186 398.187 398.188 398.189 398.190 398.191 398.192 398.193 398.194 398.195 398.196 398.197 398.198 398.199 398.200 398.201 398.202 398.203 398.204 398.205 398.206 398.207 398.208 398.209 398.210 REVISION 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4 4

GULFSTREAMIV

MAINTENANCE MANUAL

SUBHEADING ANDPAGE 398.211 398.212 398.213 398.214 398.215 398.216 398.217 398.218 398.219 398.220 398.221 398.222 398.223 398.224 398.225 398.226 398.227 398.228 398.228 .1/398.228.2 398.229 398.230 398.231 398.232 398.233 398.234 398.235 398.236 398.237 398.238 398.239 398.240 398.241 398.242 398.243 398.244 398.245 398.246 398.247 398.248 398.249 398.250 398.251 398.252 398.253 398.254 398.255 398.256 398.257 398.258 398.259 398.260

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SUBHEADING ANDPAGE Ground Check (cent) 398.261 398.262 398.263 398.264 398.265 398.266 398.267 398.268 398.269 398.270 398.271 398.272 398.273 398.274 398.274.1 398.274.2 398.275 398.276 398.277 398.278 398.279 398.280 398.281 398.282 398.283 398.284 398.284.1 398.284.2 398.284.3 398.284.4 398.284.5 398.284.6 398.284.7 398.284.8 398.285 398.286 398.287 398.288 398.289 398.290 398.291 398.292 398.293 398.294 398.295 398.296 398.297 398.298 398.299/398.300

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LEP-5/LEP-6 Apr 15/93document.

SECTION4 GROUND CHECK 1. General This section provides a ground maintenance test procedure (Table 301) for checking the SPZ-8000 System for correct installation and proper operation Table 302 provides a ground check procedure all components in the system. for the flight management system. NOTICE of

I

Procedures in Table 301 are based on Honeywell Engineering Bulletin EB7015661, Revision B. Procedures in Table 302 are based on Honeywell Engineering Bulletin EB7018760, Revision -. Should any failures ISOLATION, Section 2. arise 5. while performing the following test, refer to FAULT

Eaui~ment and Materials Equipment and materials are listed in Table 301.

3.

Procedure Instructions for performing the test are listed in Table 301.

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TABLEOF CONTENTS ~ 1.0 2.0 3.0 SCOPE ABBREVIATIONS SPECIFIC REQUIREMENTS 3.1 3.2 3.3 4.0 Overview Maintenance Test Configuration/Initiation Basic Display Formats and Operations Title ~ 304 305 314 314 314 317 319 319 323 382 398.6 398.62 398.103 398.107 398.111 398.112 398.198 398.248 398.276

MAINTENANCE TEST OPERATIONS 4.1 4.2 4.3 4.4 4.5 4.6 System Check Electronic Display Systems (EDS) Sensor Test FMS/PMSTest Automatic Flight Guidance Control Summary Test

System (AFGCS)

APPENDIX A APPENDIX B APPENDIX C APPENDIX D APPENDIXE APPENDIX F

LIST OF TESTS AVAILABLE FORMAINTENANCE TEST DELETED FLIGHTFAULTSUMMARY DESCRIPTION RECOMMENDED ACTIONSFOR FLIGHT FAULTSUMMARY SERVOSWITCHING MONITOR USEDWITHFLIGHT FAULT SUMMARY SERVOSWITCHING MONITOR LOGICTABLE

Ground Maintenance Test Procedure Table 301

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Page 303 Mar 15/91

1.0

SCOPE This document defines the requirements and instructions for the ground maintenance test for the SPZ-8000 system installed on the Gulfstream G-IV aircraft.

Ground Maintenance Test Procedure Table 301 (cent)

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2.0

ABBREVIATIONS Abbreviations Abbreviation AC A/C ACARS ACCEL ADC Addr ADF AD I A/D AFCS AFGCS AFIS AGC AHRS AHRU AI I AIL ALRT ALT AMPS ANN, ANNUN ANT AOA AOSS AP, A/P APE APP, APRPP, APR APS APU ARINC ARM AS ASCB AT, A/T ATC ATR ATT AUX AZ B/A BARO BATT used in this document are defined as follows:

Equivalent Alternating Current Aircraft ARINCCommunications Addressing and Reporting Accelerometer, Acceleration Air Data Computer Address Automatic Direction Finder Attitude Director Indicator Analog to Digital Automatic Flight Control System Automatic Flight Guidance Control System Airborne Flight Information System Automatic Gain Control Attitude and Heading Reference System Attitude and Heading Reference Unit Anti-Ice Ai 1eron Alert Altitude Amperes Annunciator Antenna Angle of Attack After Over Station Sensor Autopilot Autopilot Engage Approach Altitude Preselect Auxiliary Power Unit Aeronautical Radio, Inc. Armed Airspeed Avionics Standard Communications Bus Autothrottles Air Traffic Control Air Transport Requirement Attitude Auxiliary Azimuth Bank Angle Barometric Battery Ground Maintenance Test Procedure Table 301 (cent)

System

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Abbreviation BC BCD BIT BITE BNR BOO BOW BRG BRK % CAS CB Ccw CDI CDU CDS CDU CE CH CHG CKSUM CKT CLB CLK CLR CMD CMPTR CNTL COM COMB COMP CONFIG CONT CORR Cos CP CPL CPU CRC CRS CRT CRZ Cs CT CTRL

Equivalent Back Course or Bus Controller Binary-Coded-Decimal Built In Test Built In Test Equipment Binary Bottom of Descent Basic Operating Weight B6&ng Civil Aviation Authority (British) Capture Crew Alerting System or Calibrated Airspeed Circuit Breaker Counterclockwise Course Deviation Indicator Control Display Unit Differential Resolver Control Display Unit Course Error Channel Change Check Sum Circuit Climb Clock Clear Command Computer Control Common Combined Compensation, Compass, or Compacted Configuration Controller Correction Cosine Cross Pointers, Copilot Couple Central Processor Unit Cyclic Redundancy Check Course Cathode Ray Tube Cruise Cross Side Control Transformer Control Ground Maintenance Test Procedure Table 301 (cent)

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Abbreviation Cw DA D/A DADC DAU DB DC DCT DDM DEFL DEG DEMOD DES DET DEV, DEVN DG RFF DISC DISENG DISP DISPL DIST DL DMA DME EC DSR DTG DTRK DU DUP E EEPROM,E2PROM EFIS EGT EDS EICAS EL, ELEV EMI ENG EO E OFF EPR EPROM

Equivalent Clockwise Drift Angle Digital to Analog Digital Air Data Computer Data Acquisition Unit Data Base Display Controller Direct Difference in Depth of Modulation Deflection Degree Demodulator Descent Detector, Detent Deviation Directional Gyro Decision Height Differential, Difference Disconnect Disengage Display Displacement Distance Data Loader Direct Memory Access Distance Measuring Equipment Down Dual Remote Compensator Des i red Distance To Go Desired Track Display Unit Duplicate East Electronically Erasable Programmable Read Only Memory Electronic Flight Instrument System Exhaust Gas Temperature Electronic Display System Engine Instrument and Crew Alerting System Elevator, Elevation Electromagnetic Interference Engage, Engine Easy-On Easy-Off Engine Pressure Ratio Erasable PROM Ground Maintenance Test Procedure Table 301 (cent)

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Abbreviation ESS ET ETA ETE EVM EX LOC EXT FAA FAR FD, F/D FDBK FF FFS FGC FL FLCH FLT FMS FPL, FPLtl FPM FR, FRM FREQ FV FWC GA, G/A GCR GMAP GMT GP GPS GRD GS, G/S GSPD GW HB HBM HDG HDLC HF HORIZ HP HR HSI HYD H/W IAS

Equivalent Essential Elapsed Time Estimated Time of Arrival Estimated Time In Route Engine Vibration Monitor Expanded Localizer Extend, External Federal Aviation Authority Federal Aviation Requirement Flight Director Feedback Fuel Flow Flight Fault Summary Flight Guidance Computer Flight Lever Flight Level Changer F1ight Flight Management System Flight Plan Feet Per Minute From Frequency Flux Valve Fault Warning Computer Go Around Ground Clutter Reduction Ground Map Greenwich Mean Time Guidance Panel Global Positioning System Ground Glideslope, Groundspeed Groundspeed Gross Weight Heart Beat Heart Beat Monitor Heading High Level Data Link Control High Frequency Horizontal High Pressure Hour Horizontal Situation Indicator Hydraulic Hardware Indicated Airspeed Ground Maintenance Test Procedure Table 301 (cent)

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Abbreviation ICAO ID, IDENT IF IGN ILS INC-DEC IND INIT INS INTFC INTGL INTLK INV 1/0 IRC IRS IRU 1s0 Ivv KBPS kHz KN, KT L LAT LBS L/C LH LIM LNAV LOC LON LORAN LP LPV LRN LRU LSB LTG LTS LVC LVDT MAG MAGVAR MFD MHz MIN

Eaui val ent International Civil Aviation Organization Identi fi cation Intermediate Frequency Ignition Instrument Landing System Increase-Decrease Indicator Initialization Inertial Navigation System Interface Integral Interlock Invert Input/Output Instrument Remote Controller Inertial Navigation System Inertial Navigation Unit Isolation Instantaneous Vertical Velocity Kilo Bits Per Second Kilohertz Knots Left Latitude Lateral Beam Sensor Inductive/Capacitive Left Hand Limit Lateral Navigation/Lateral Guidance Localizer Longitude Position Sensor Type Low Pressure Latched Power Valid Long Range Navigation Line Replaceable Unit Least Significant Bit Lighting Long Term Sensor Line Voltage Compensation Linear Variable Differential Transformer Magnetic Magnetic Variation Multifunction Display Megahertz Minutes Ground Maintenance Test Procedure Table 301 (cent)

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Abbreviation MLS MM MMo MOM MON MSB MSG MSL M/T, M/TRIM MUX N NAV fl:D ND NDB NM NO NOC NORM NOTAM NW NVR !):s o/c OM Osc 0ss P PAll PB Pc PERF PFD PISO PIT PITCH SYNC PLA PLN PMs Pos PPH PPOS PRESS PRI, PRIM

Equivalent Microwave Landing System ~iddle Marker ~aximum Allowable Mach Number ~omentary !on i tor ~ost Significant Bit Yessage ~ean Sea Level ~ach Trim multiplexer Uorth Navigation No Connection, Normally Closed, MOComputer Data Navigation Display Non-Directional Beacon Yautical Mile Uormally Open NAVon Course Uormal Notice To Airman Non-Return To Zero Uon-Volatile RAM Navigation Computer Jnni Bearing Selector 3n Course )uter Marker )scillator )ver Station Sensor Pressure Pitch Attitude Pushbutton Performance Computer Performance Primary Flight Display Parallel In Serial Out Pitch Pitch Synchronization power Lever Angle P1an performance Management System Position Pounds Per Hour Present Position Pressure %irnary Ground Maintenance Test Procedure Table 301 (cent)

or NAVComputer

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Abbreviation PROC PROF PROG PROM P/s PSI Pv PM PWM PWR : ~TY RA, R/A, RADALT RAM RCT RCVR . REF REL RET RETR REV ;; RMI RN, RNAV RNAPP !!: ROM RPM RT, R/T RUD s SAT SBY, STBY SCI SCR Scs SDI SEC SEL ~!D SIG

Equivalent Processor Profi 1e Programmer, Programming Programmable Read Only Memory Pitot Switch Pounds Per Square Inch Power Valid Pitch Wheel or Pulse Iiidth Pulse Width Modulated Power Performance Computer Quality Factor Quantity Right Radio Altimeter Random Access Memory Rain Echo Attenuation Receiver Reference Release Return Retract Reverse Source (Same as Back Course) Rate Gyro Right-Hand Radio Magnetic Indicator Area NAV RNAV Approach Range Rol 1 Read Only Memory Revolutions Per Minute Receiver/Transmitter, Rate of Turn Rudder South Static Air Temperature Standby Serial Control Interface Source Single Channel Select Source/Destination Identification Seconds, Secondary Select Symbol Generator Standard Instrument Departure Signal Ground Maintenance Test Procedure Table 301 (cent)

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Abbreviation SIN SING SIPO SPD SRAM SRN SSEC SSM STAEL STAR STBY STC STCS STP STR, STRG Svo Sw, s~kl SYNC SYS T TAS TAT TBD TCS TEMP TGT TK TKE TKOD TLA TLE TOC TOD TOGA TP TRK % TSO TTG llL UART UTIL, UTY V1

Ea uivalent Sine Single Serial In Parallel Out Speed System Random Access Memory Short Range Navigation Static Source Error Correction Sign Status Matrix Station Elevation Standard Terminal Arrival Route Standby Sensitivity Time Control Single Trim Channel Select Steep Steering Start Valve Open Software Synchronization System Temperature True Airspeed True Air Temperature To Be Determined Touch Control Steering Temperature Target, Turbine Gas Temperature Turn Knob, Track Track Error Turn Knob Out of Detent Torque Limit Aileron Torque Limit Elevator Top Of Climb Top Of Descent Take Off-Go Around Test Point Track Thrust Reference Set True Technical Standard Order Time-To-Go Tuned to Localizer Universal Asynchronous Receiver Transmitter Utility Takeoff Decision Speed


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Abbreviation V2 VA VAL VANG VAPP, VAPR VAR VBS Vco VEL VERT VFLC Vfs VG VHF VLD VLF Vmo VNAV VOR VORTAC VPTH Vr VRAM Vref VRT, VERT Vs, v/s Vse VTA ;L, W/L NO wow WPT WR, WX WSP XFER XMTR X-SIDE XTRK YD, Y/D

Equivalent Takeoff Safety Speed (Speed to be attained at 35 feet AGC, assuming recognition of an engine failure after VI) Volt Ampere Valid Vertical Angle VORApproach Variable Vertical Beam Sensor Voltage Controlled Oscillator Velocity Vertical Vertical Flight Level Change Final Takeoff Climb Speed (Airspeed for single-engine climb in a clean configuration below 1500 feet AGC) Vertical Gyro or Vertical Generator Very High Frequency Valid Very Low Frequency MaximumAllowable Airspeed Vertical Navigation VHFOmni Range Colocated VORand Tacan Stations Vertical Path Takeoff Rotation Speed Video Random Access Memory Reference Speed (Landing) Vertical Vertical Speed Enroute Climb Speed (~irspeed for single-engine climb in a clean configuration above 1500 feet AGC) Vertical Track Alert West Wings Level Washed Out Weight on Wheels Waypoint Weather Radar Word Sequence Position Transfer Transmitter Cross-Side Cross TRACK Yaw Damper


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3.0 3.1

SPECIFIC REQUIREMENTS Overview Ground Maintenance Test is an operator activated set of diagnostics consisting of five maJor tests> 1) System Check, 2) Electronic Display System (EDS), 3) Flight Management System (FW~S), 4) Automatic Flight Guidance Control System (AFGCS), and 5) Sensors. Each major test is described in detail in separate sections within this manual. The Maintenance Test isolates faults Additional information (LRU) level. down to the Line Replaceable Unit is also provided in most cases.

3.2

Maintenance

Test Configuration/Initiation Test the operator must satisfy

To configure the system for Maintenance the following conditions: Airspeed less than 50 knots

weight on Wheels (WOW) TEST switch on Display Controller (DC) depressed in either the Left or Right Avionics the DC

-

Maintenance Bay.

Test Switch activated

When all the conditions mentioned above have been satisfied, Cathode Ray Tube (CRT) appears as shown in Figure 3-1.

[1===EFIS RADALT [1------

EICAS ===[1 A/P DISC ======[] ALT ===[1 [1=== S/L A/T DISC [1-----======[1 MAINT===[1 [1=== Test Menu Figure 3-1


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Note that follows:

the Engine Instrument

Display

now displays

test

value as

TGT 1000 Red LP/HP 100.0 Red Oil Pressure 10 Red Oil Temperature 100 White EVMHP/LP 1.00 White Hyd Pressure (all) 1000 White Fuel Temperature 100 Amber Fuel Quantity Total 2000 White Fuel Quantity L-R 1000 White EPR 0.98 White Additionally, Blue MAINTSWITCH ON and FGC SYSTEM TESTn messages are displayed on the Crew Alerting System (CAS) display. The PFD on the side from which Ground Maintenance Test is being run will display an amber VSPDor the airspeed tape. To initiate Maintenance labeled MAINTlocated produces the System Test 3-2. The Crew Alerting 3-3. Test, the operator presses the line select key in the bottom right corner of the DC. This Menu to appear on the DC CRT, shown in Figure System (CAS) display appears as shown in Figure

I

\

CA(3 (3

EDS SYSTEM AFGCS CHECK FMS/PMS SUMMARY

AD-22803 #

System Test Menu Figure 3-2 Ground Maintenance Test Procedure Table 301 (cent)

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MAINTENANCE TEST

CASDisplay,

Maintenance Figure 3-3

Test Start

Each of the tests available to the operator from the System Test Menu are described in detail in separate sections within this document. All the interfacing is through the DC, CAS display, the Guidance Panel, the Manual Controller, and aircraft switches. The following section explains the basic display formats and operations procedures associated with the DC, and the CAS display.


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3.3

Basic Dis~lav

Formats and O~erations

The operator selects, initiates, and provides feedback for most tests with the Guidance Panel (GP), through the DC. The operator interacts Manual Controller, and aircraft switches, to perfom portions of the Automatic Flight Guidance Control System (AFGCS) Test. 3.3.1 - Throughout the operation of Maintenance Test, the Display Controller DC CRT assumes 4 different modes> the Test Menu, the System Test Menu, the Subsystem Test Menu, and the LRUTest Menu. The Test Menu, shown in Figure 3-4, is required to initiate the If all the conditions described in Maintenance Test Maintenance Test. Configuration/Initiation Section 3.2, the Test Menu will be displayed. The System Test Menu, shown in Figure 3-5, select the various major tests. allows the operator to

I

The Subsystem Test Menu, example shown in Figure 3-6, operator to select various subsystem tests associated The LRUTest Menu, example shown in Figure 3-7, manipulate the major or subsystem tests. 3.3.2 Crew Alerting two sections, allows

allows the with major tests. the operator is divided into to

System (CAS) Display - The CAS display the right side and the left side.

The left side of the display indicates the status or error message associated with the system or LRUas a result of the test. All the messages associated with each test are explained in their respective sections. The right side of the display indicates that the Maintenance Test by displaying the Maintenance by the annunciation of the test currently being any instructions and/or options available to the displayed. system is in Test header followed executed. In addition, operator are



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onthe

r 1=== EFIS EICAS ===[1 A/P DISC ======[1 RADALT [1=;;=== === s/L OA-----> ALT ===[1 rl ====== ======[1 MAINT ===[1 [1===

1

Test Menu Figure 3-4

AFGCS [1=;;=== === ,SENSORS

[1=:+=== === SYSTEM CHECK

~

E,,

===[1======[1

FMS/PMS===[1 SUMMARY ======[1 RETURN ===[1

System Test Menu Figure 3-5

[1=== []=y== ===DC SG [1=;;=== ===

n

EDS

DAU1

F~! DAU2 ======[1 RETURN 1===[1

===[1 ~ -;=[1

Subsystem Test Menu, EDS Example Figure 3-6

I

[1=== [l=~;=== === PASS FAIL [1=;;=== ---

n

DAU1

===[1 ======[1 SELE& ===[1 DOWN ======[1 RETURN ,===[1

LRUTest Menu, DAU1 Example Figure 3-7 Ground Maintenance Test Procedure Table 301 (cent)

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4.0 4.1

MAINTENANCE TEST OPERATIONS Svstem Check The System Test determines the present system configuration.

4.1.1

General Operation - The operator selects, initiates, and provides feedback for the System Test through the Display Controller (DC). When the System Test Menu is displayed on the DC Cathode Ray Tube (CRT) as shown in Figure 4-1, the operator initiates the System Check Test by pressing the line select key labeled SYSTEM CHECK.

System Test Menu Figure 4-1 Status and error messages appear on the Crew Alerting System (CAS) display. The following is a list of messages that may appear as a result of executing the System Check Test. With all the LRUS installed and the system functioning normally, the message SYSTEM CHECK PASS will appear on the left side of the CAS display. BC BC 1 2 3 TEST FAIL BC 1 2 3 INVALID NO BC ON BUSA NO BC ON BUS B Bus Controller Status


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ASCB LRUSNOTON ASCB FWC1 FWC2 ~#J1l;$A lB 2B AFCS 1 2 NZ12 DC12 ;::C1122

ASCBStatus

I

PZ12 VALID LRUSINVALID FWC1 FWC2 ::U1l; ;A lB 2B fijc~ ; 2 DC12 y):c1122 PZ12 4.1.2 Recommended Maintenance The following is a list and recommended action. MESSAGE BC 1 2 3 TEST FAIL Action of messages associated ACTION See next para ra h for detailed description. Verify aircra ![t atteries are properly charged if seen during battery start. Replace SG/FWC. Verify BCTest Request Wiring and BC Valid Wiring. Check ASCBinterconnects. Identifies which boxes are not received on ASCB by the fault warning computer. Check ASCB interconnects for listed boxes. Make sure units are in and selected on, CBS in. Identifies invalid. which boxes are on ASCBand are Replace SG. with maintenance test LRUSTransmitting Valid Data

NO BC ON BUSA B LRUSNOTON ASCB

LRUS INVALID BC 1 2 3 INVALID

See next paragraph.


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The following is a detailed description FAIL and BUXCTLR 1-2-3 FL. A Bus Controller test is performed the test, the following conditions 1. 2. 3. 4. 5.

for the messages, master

BC 1-2-3 TEST FWC. To initiate

by the default must be met:

FWCpower up sequence complete Weight on wheels active (ground) Airspeed valid and indicating less than 60 kts. Activity on both Bus A and Bus B All three Bus Controllers valid (discretes)

FWCNo. 1 is designated the default master for initiation of the Bus Once the above enable logic has been satisfied, FWC1 Controller Test. checks FWC2 to ensure a test is not in progress nor has been previously If a test is not complete nor in progress by FWC2, FWC1 performed. initiates the test by transmitting a ground on the BC Test Request line. The FWC1 looks at the Bus Controller Frame Control Transmission for a FWC1 then ensures each Bus Controller assumes control Test Frame Flag. of the bus by looking at the Controller ID. After each frame cycles through each controller, FWC1 checks the Bus Controller Valids. If an open condition is detected, then BC X TEST FAIL message is enabled. FWC 1 then transmits the results via WSP66. For FWC2 a one second wait is inserted at the end of the enabling logic to allow time for the master Following the wait, WSP66 of FWC1 is (FWC 1) to initiate the test. If FWC1 test is complete, FWC2 sets checked to determine the status. WSP66 to reflect the same status. If FWC1 test is in progress, FWC2 waits one second and checks again. Once the Bus Controller Test is complete, the Bus Controller Monitors become active and should the Bus Controller become invalid, a BC X FAIL message is enabled. BC TEST REQUEST NO. 1 * 134J1A-96 (22) ----------W;Bli C65J1B-1, C65J1B-2,

BC TEST REQUEST NO. 2 * C134J1A-96 (22) ----------;~~&2;*~ND

ENABLE


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Page 321 Mar15/91 document.

For convenience, below: BYTEo

the Bus Controller BIT FUNCTION HDLCFLAG ADDRESS TEST FRAME FLAG CONTROLLER ID

Frame Control

Transmission FORMAT

is listed

BIT

: 2 2 2 ; 2 ; 3,4 5

6~5

4 2:0

;[&T-UP

FRAME

7E HEX 81 HEX LOGIC 1 =TEST OO=CONTROLLER O O1=CONTROLLER 1 10=CONTROLLER 2 ll=CONTROLLER 3 LOGIC I=START-UP ALWAYS O 0-7 HEX CRC 7E HEX below: BIT FORMAT

RESERVED FRAME NUMBER ERROR CHECK HDLCFLAG WSP66 of the FWCis listed BIT FUNCTION BUS CONTROLLER TEST STATUS TEST COMPLETE TEST IN PROGRESS TEST RESULTS BC 1 STATUS BC 2 STATUS BC 3 STATUS SPARE

For convenience, WSP BIT

15 14 13 12 11 1o-o

LOGIC 1 = COMPLETE LOGIC 1 = IN PROGRESS LOGIC 1 = TEST PASSED LOGIC 1 = TEST PASSED LOGIC 1 = TEST PASSED

If Test Complete Bit 15 = O, the blue BUS CTLR X FL messages are enabled using the discrete input valids. This message can be enabled independent from the Weight on Wheels discrete. The Bus Controller Valids into the FWCare as follows: C134J1A-97 C134J1A-98 C134J1A-99

BUS CONVALIDNO. 1 *

65J1A-13 (22)-----13497,-97,

BUS CONVALIDNO. 2 * C65J1A-13 (22)-----13498,-98, BUS CONVALIDNO. 3 * E65J1A-13 (22)-----13499,-99, * GND=VALID/OPEN-INVALID


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If Test Complete Bit 15 = Logic 1, message logic 1. 2. 3. If BC Status If BC Status enabled. Bit = 1 (PASS) and BC is valid,

is as follows: there will be no message.

Bit = O, (FAIL), the blue BC X TEST FAIL message is the blue BUS CTLR

If BC Status Bit = X (DONTCARE) and BC is invalid X FL message is enabled.

NOTE: Any message enabled as a result of 2 above is disabled following either the loss of weight on wheels or airspeed greater than 60 kts, the messages will not return. To proceed with the Maintenance This completes the System Check Test. Test, the operator presses the line select key labeled SYSTEM CHECK, to This produces the System Test Menu to be displayed on deselect the test. the DC CRT. 4.2 Electronic DisDlav Svstems (EDS~

When the System Test Menu is displayed on the DC CRT as shown in Figure 4-2, the operator initiates the Electronic Display System (EDS) Test by pressing the line select key labeled EDS. This produces the EDS Subsystem Menu to appear on the DC CRT as shown in Figure 4-3. The CAS display will be as shown in Figure 4-3.1.

~ e

a

EDS e SYSTEM flFGCS e CHECK FMS/PMS SUMMARY a a

e

e

~

AD-22803#

System Test Menu Figure 4-2


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on the title page nf this


EDS - Subsystem Test Menu Figure 4-3

EDS PLEFHE MFIKE SELECTIONAD-22805#

EDS - CAS Display Figure 4-3.1 The operator selects one of the subsystem tests or returns to the System Test Menu by pressing the appropriate line select key. Each of the subsystem tests are described in the following sections.


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Mar-15/91 the restrictions on the title page of this document.

!.2.1 !.2.1.1

Display General

Controller Operation

(DC)

The operator selects, through the DC.

initiates,

and provides

feedback

for the DC Test

When the EDS Subsystem Test Main is displayed on the DC CRT, the operator initiates the DC Test by pressing the line select key labeled DC. This produces the LRUTest Menu to appear on the DC CRT as shown in Figure 4-4.

UP PPtss FAIL t( SELECT DOWN

DC LRUTest Menu Figure 4-4 The CAS Display will be as shown in Figure 4-4.1.


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Mfl INTENRNCE TEST DcIl.

DC 1 STftTUS TEST] 2. DC 2 STllTUS TEST 3. CONF16URfITION TEST 4. SOFTllllRE MOD LEVEL TESTA A AD-22807-R1 #

A

CAS Display Figure 4-4.1 There are three tests associated with the DC test. The Status Test will show the LRUSnot received on ASCBby the Display Controller as well as the Built-In-Test (BITE) results. The Configuration Test will show the current strapping of the configuration pins on the The Software Mod Level Test will show the Display Controller. internal software level of the Display Controller. There is no correlation between the Software Mod Status in Maintenance Test and the Mod Status shown externally on the LRU. The Software Mod Levels are used for reporting purposes. The operator presses the line select key labeled SELECT to initiate the DC Status Test, the option highlighted on the CAS display. Status or error messages appear on the CASdisplay. A typical CAS Display for the DC Status Test is shown in Figure 4-4.2.


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f

\

MRINTENflNCETESTDC 1 ONRSCB DC 1 VflLID DC 1 flSCB PflSS flLL LRUSRECEIVED

DC

DC 1 BITE PINS USE PRSS/FilIL TO CONTINUEA A h AD-22aoe-Rl#

CAS Display

for the DC Status Figure 4-4.2

Test

NOTE: DC 2 Status Test CAS Display is the same as shown in Figure 4-4.2 except Number 1 is shown as 2. The following is a list of all messages that may appear on the CAS display as a result of executing the DC Status Test. BUS DC 1 ON ASCB DC 2 ON ASCB VALID DC 1 VALID DC 2 VALID DCS Transmitting Valid Data Active DCS on ASCB


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ASCB DC 1 ASCBFAIL DC 2 ASCBFAIL LRUSNOTRECEIVED DC 2 DC 1 PZ12 DC 1 ASCBPASS DC 2 ASCBPASS ALL LRUSRECEIVED BITE

ASCBStatus

with Respect

to the DCS

Built

In Test Results

DC 1 BITE FAIL DC 2 BITE FAIL TACHINPUTSTUCK VRAM TEST FAIL SRAM TEST FAIL ROM CHECK SUMFAIL PASS - DC 2 BITE PASS A/D FAIL To proceed with DC Test, the operator presses the PASS or FAIL line select key based on the outcome of the test. This advances the test to the DC Configuration Test, the option highlighted on the CAS To initiate the test the operator display, as shown in Figure 4-4.3. presses the line select key labeled SELECT. The resulting status or error messages appear on the CAS display. A typical CAS Display for the DC Configuration Test is shown in Figure 4-4.4.


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m

DC 1. STFITUSTEST[2. CONFIGURFITION TEST] 3. SOFTW13RE MODLEVEL TEST

AD-22809#

DC Configuration

Test - CAS Option Highlighted Figure 4-4.3


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F

Y

DC 1 2 ID PflSS DC 1 CONFIGURFITION IRS TRIPLEXPZ INSTRLLED ILS INSTRl_l-ED FGC 1 (2) SELECTED CRS 1 2 SYNC DC2 CONFIGURFITION IRS TRIPLEX PZ INSTflLLED II-S INSTF!LLED FGC 1 (2) SELECTED CRS 1 2 SYNCA

DC

USE PfISS/FflIL TO CONTINUEA A AD-2281 0#

CAS Display

for the DC Configuration Figure 4-4.4

Test

The following is a list of all messages that may appear as a result of The operator is responsible for executing the DC Configuration Test. verifying that the configuration is correct. ID DC 1 ID PASS DC 2 ID PASS Verifies Correct Identification


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Paqe 330 Mar-15/91

cONFIGURATION DC CONFIGURATION IRS TRIPLEX IRS DUAL PZ INSTALLED TWOMLS INSTALLED ONEMLS INSTALLED I LS INSTALLED FGC 1 2 SELECTED FGC 1 SELECTED FGC 2 SELECTED CRS 1 2 SYNC CHECKLIST ENABLED

Aircraft

Configuration

Information

To proceed with DC Test, the operator presses the PASSUor FAIL line select key based on the outcome of the test. This advances the test to the DC Software Mod Level Test, the option highlighted on the To initiate the test the CAS display, as shown in Figure 4-4.5. operator presses the line select key labeled SELECT. A typical CAS Display for the DC Software Mod Level Test is shown in Figure 4-4.6.

I

DC

1. STFITUSTEST 2. CONFIGURATION TEST !3. SOFTHRREMODLEVEL TEST] h AA

DC Software Mod Level Test Figure 4-4.5 Ground Maintenance Test Procedure Table 301 (cent)

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DC 1 S/ii = REV113 DC 2 S/ii = REV 113A A

DCA

.

AD-2281 2#

CAS Display

for the DC Software Figure 4-4.6

Mod Level Test

The resulting status or error messages appear on the CAS display. The following is a list of all messages that may appear as a result of executing the DC Software Mod Level Test. MODLEVEL DC 1 S/W = XXXX DC 2 S/W = XXXX NOTE : There is no correlation between Software Mod Status Maintenance Test and the Mod Status shown externally LRU . in on the Software Revision Information


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Pacie 332 Mar-15/91 document.

4.2.1.2

Recommended Maintenance The following is a list and recommended action. Status Test:

Action of messa9es associated with maintenance test

MESSAGE DC(X) NOTIN TEST NOTONASCB DC 1 ASCBFAIL DC 2 ASCBFAIL DC 1 BITE FAIL DC 2-BITE FAIL AID FAIL

ACTION VerifyA/Cwiring Replace DC. J1-A, B, R, S.

List boxes not rcvd by DC1 via ASCB. Check ASCBinterconnects. List boxes not rcvd by DC2 via ASCB. Check ASCBinterconnects. Replace display Replace display controller. controller.

The DC can fail intermittently on power-up. When this occurs, entering Maintenance Test will reveal a DC X BITE FAIL and A/D FAIL. If cycling the DC circuit breaker does not clear this failure then replace the DC. 1. 2. Check CRS#l and CRS#2 interconnect from guidance panel. Replace display controller. controller. controller. controller.

TACHINPUT STUCK

VRAM TEST FAIL SRAM TEST FAIL ROM CHECK SUMFAIL Configuration Messacae CRS 1 2 SYNC Test:

Replace display Replace display Replace display

Action Course sync button depressed or Wiring from GP-820, llJ1-36 or 11J2-36.


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To proceed with DC Test, the operator presses the PASS or FAIL line select key based on the outcome of the test. This advances the test to the DC-Status Test, the option highlighted on the CAS display. The CAS Display will be as shown in Figure 4-4.7.

DC il. STRTUS TEST]flLL TEST COMPLETE 2. CONFIGURATION TEST 3. SOFTkitlRE MOD LEVEL TESTA A

A

.

.

.

AD-2281 3#

Figure

4-4.7

To return to the EDS Subsystem Menu. the operator presses the line select key labeled RETURN. The message on the CAS display prompts the operator to make a selection. 4.2.1.3 Instructions This section may be required if the operator is executing the DC Test in any manner other than what has been described in the above section. If following the general operation section, proceed to Section 4.2.2. The operator selects, through the DC. initiates, and provides feedback for each test

Based on the information presented on the CAS display, the operator determines if the equipment passed or failed the test, and presses the appropriate line select key on the DC. This step is required before the Maintenance Test will proceed. In addition, the operator may be required to select an option associated with a test or return to the line previous menu. To do this, the operator presses the appropriate select key on the DC.


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Page 334 Mar 15/91

The following is a list of how to use the LRIJTest Menu displayed the DC CRT for Maintenance Test (refer to Figure 4-4). llPASS~l The operator presses current test. FAIL The operator presses current test. UP The operator presses this test selections presented SELECT The operator presses this line select is highlighted on the CAS display. DOWN The operator presses selections presented RETURN this line select key to step through on the CAS display. the test key to initiate the task that line select key to back-step through the on the Crew Alerting System (CAS) display. this line select key if the equipment fails this line select key if the equipment passes

on

the

the

The operator presses this line select key to return to the menu that had been previously displayed on the DC. This is not used to select the options presented on the CAS display. 4.2.1.4 DC Maintenance ~~ 4 :3 42 Test ASCBData Bit Function MAINTTest Enable WOW/GND MAINTTest Select Format Logic 1 = Enabled Logic 1 = WOW Logic 1 = Select


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onthetitle

4.2.2 4.2.2.1

Symbol Generator General

(SG)

Operation feedback for the Symbol

initiates, and provides The operator selects, Generator (SG) Test through the DC.

When the EDS Subsystem Test Menu is displayed on the DC CRT, as shown in Figure 4-4.8, the operator initiates the SG Test by pressing the line select key labeled SG. This causes the LRUTest Menu to appear on the DC CRT, as shown in Figure 4-4.9. The CAS Display will be as There are five tests associated with the SG shown in Figure 4-4.10. The Status Test will show the active Symbol Generators on ASCB Test. as well as the SGS transmitting valid data. The Software Mod Level Test will show the internal software level of each Symbol Generator. There is no correlation between Software Mod Status in Maintenance Test and the Mod Status shown externally on the LRU. The Software Mod Levels are used for reporting purposes. The three SG ASCBTests will show the LRUSnot received on ASCBby each Symbol Generator as well as the Built-In-Test (BITE) results.

~ e

DU e DC SG e FWC Df+U2 ~ a

e

e

e

AD-22814#

EDS Subsystem Test Menu Figure 4-4.8


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mUP Pfiss FAIL SELECT DOWN RETURN

LRUTest Menu Figure 4-4.9

MFHNTENFINCE TEST S6Il. STFITUS TEST] 2, SOFTNRRE HOD LEVEL TEST 3. S6 1 RSCB TEST 4. SG 2 fiSCB TEST 5. SG 3 flSCB TEST.

AD-22816#

CAS Display Figure 4-4.10 The operator presses the line select key labeled SELECT to initiate the S& Status Test, the option highlighted on the CAS display. Status or error messages appear on the CAS display. A typical CAS display for the SG Status Test is shown in Figure 4-4.11.


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SG 1 2 3 ON FISCB S6 1 2 3 VFILID SG 1 BITE PflSS SG 2 BITE PRSS SG 3 BITE PflSS SG1231DPflSS~ A.

S6

~ USE PRSS/Ffl IL TO CONTINUEA A

.

.

AD-Z?817#

CAS Display for the SG Status Figure 4-4.11

Test on the CAS

The following is ; list of all messages that may appear display as a resu t of executing the SG Status Test. BUS SG 1 2 3 ON ASCB VALID SG 1 2 3 VALID SGS Transmitting Valid Data Active SGS on ASCB


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Page 338 Mar 15/91

BITE SG 1 BITE FAIL SG 2 BITE FAIL SG3 BITE FAIL ASCBFAILURE POWER SUPPLYFAIL DISCRETEFAILURE ARINC FAILURE E2 PROM FAILURE INTERLOCK FAILURE SG 1 BITE PASS SG 2 BITE PASS SG 3 BITE PASS ID SG 1 2 3 PASS

Built

In Test Results

Verifies

Correct

Identification

To proceed with SG Test, the operator presses the PASS or FAIL line select key based on the outcome of the test. This advances the test to the SG Software Mod Level Test, the option highlighted on the CAS display, as shown in Figure 4-4.12. To initiate the test the operator presses the line select key labeled SELECT. The resulting status or error messages appear on the CAS display. A typical CAS Display for the SG Software Mod Level Test is shown in Figure 4-4.13.

S61. STflTUS TEST 12. SOFTMFIRE MOD LEVEL TEST] 3. S6 1 flSCB TEST 40 S6 2 FISCB TEST 5. S6 3 flSCB TESTA A A

.

AD-2281 8#

SG Software

Mod Level Test Option Figure 4-4.12


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Page 339 Mar-15/91

MFHNTENFINCE TESTS6 1 S/h CPU I+= 0119 CPU B = 0119 flSCB = 0116 SG 2 SIM CPU R = 0119 CPU B = 0119 flSCB = 0116 SG 3 S/ii CPU R = 0119 CPU B = 0119 FISCB = 0116,

S6

USE PfISS/FflIL TO CONTINUE.

AD-22819#

CAS Display

for the SG Software Figure 4-4.13

Mod Level Test may appear as a result of

The following is a list of all messages that executing the SG Software Mod Level Test. MODLEVEL SG 1 S/W: SG 2 S/W: SG 3 S/W: CPU A = XXXX CPU B = XXXX ASCB= XXXX Software Revision

Information

NOTE: There is no correlation between Software Mod Level in Maintenance Test and the Mod Status shown externally on the LRU .


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Page 340 Mar 15/91

To proceed with SG Test, the operator presses the PASS or FAIL line select key based on the outcome of the test. This advances the test to the SG-l ASCBTest, the option highlighted on the CASdisplay, the test the operator presses as shown in Figure 4-4.14. To initiate the line select key labeled SELECT. The resulting status or error messaqes appear on the CAS display. A typical CAS Display for the SG1 ASCB~est is shown in Figure 4:4.15. f

Y

S6

1. STflTUS TEST2. [3. 4. 5. SOFTMRRE MOD LEVEL TEST S6 1 flSCB TEST] S6 2 FISCB TEST S6 3 f3SCB TESTA AD-22820#

SG 1 ASCBTest Option Figure 4-4.14

F

\

S6 1 FISCB PflSS fiLLLRUS RECEIVEDA

S6USE Pf3SS/Ff31L TO CONTINUEA Av

.

.

AD-22821#

CAS Display

for the SG 1 ASCBTest Figure 4-4.15


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Page 341 Mar 15/91 document,

The following is a list of all messages of executing the SG 1 ASCBTest. ASCB SG 1 ASCBPASS ALL LRUSRECEIVED SG 1 ASCBFAIL LRUSNOTRECEIVED DC12 FWC1 2 NZ12 DAU1A lB 2A 2B AFCS 1 2 DADC1 2 PZ12 A/T 1 2 SG23 NOTE: SG 1 ASCBTest gives 1 2. ASCBStatus

that

may appear

as a result

with Respect

to SGS

SG 1 ASCBFAIL

LRUSNOTRECEIVED AFCS

To proceed with SG Test, the operator presses the PASSn or FAIL line select key based on the outcome of the test. This advances the test to the SG 2 ASCBTest, the option highlighted on the CAS display, as shown in Figure 4-4.16. To initiate the test the operator presses the line select key labeled SELECT. The resulting status or error messages appear on the CAS display. A typical CAS Display for the SG 2ASCB Test is shown in Figure 4-4.17.


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/

\

S610 STRTUS TEST2. 3. [4. 5.A

SOFTWRRE MOD LEVEL TEST S6 1 f3SCB TEST S6 2 flSCB TESTI SG 3 FISCB TESTA AD-22822#


4

\

MfHNTENflNCE TESTSG 2 fISCBPRSS

S6USE PfISS/FllIL TO CONTINUEA A AD-22a23(Rl)#

RL1LRUSAv

RECEIVED

.

CAS Display



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Paqe 343 Mar-15/91 document,

The following is a list of all messages that of executing the SG 2 ASCBTest. ASCB SG 2 ASCBPASS ALL LRUSRECEIVED SG 2 ASCBFAIL LRUSNOTRECEIVED DC12 FMC1 2 NZ12 DAU1A lB 2A2B AFCS 1 2 DADC1 2 PZ12 A4T1132 NOTE: SG 2 ASCBTest gives 1 2. ASCBStatus

may appear

as a result

with Respect

to SGS

SG 2 ASCBFAIL LRUSNOTRECEIVED AFCS

To proceed with SG Test, the operator presses the PASSWor FAILW line select key based on the outcome of the test. This advances the test to the SG 3 ASCBTest, the option highlighted on the CAS display, as shown in Figure 4-4.18. To initiate the test the operator presses the line select key labeled SELECT. The resulting status or error messages appear on the CAS display. A typical CM Display for the SG3ASCB Test is shown in Figure 4-4.19.

Ground MaintenanceTable 301

Test Procedure(cent)

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disclosure

of information


totherestrictions

/

F

T

SG1. STRTUS TEST2. 3. 4s [5,A A

SOFTKRRE MOD LEVEL TEST S6 1 flSCB TEST S6 2 f3SCB TEST S6 3 flSCB TEST]A AD-22824#


f

\

S6 3 flSCB PRSS flLL LRUS RECEIVED A

SGUSE PflSS/FflIL TO CONTINUEA A

1

AD-22825#

CAS Display



22-14-00 Pacie 345Mar-15/91


The following is a 1ist of all messages that of executing the SG 3 ASCBTest. ASCB SG 3 ASCBPASS ALL LRUSRECEIVED SG 3 ASCBFAIL LRUSNOTRECEIVED DC12 FWC1 2 NZ12 DAU1A lB 2A 2B AFCS 1 2 DAOC12 PZ12 A/T 1 2 SG12 NOTE: SG 3 ASCBTest gives 1 2. 4.2.2.2 Recommended Maintenance The following is a list and recommended action. Status ~ SG(X) NOT IN TEST Test: ACTION ASCBStatus

may appear

as a result

with Respect

to SGS

SG 3 ASCBFAIL LRUSNOTRECEIVED AFCS

Action of messages associated with maintenance test

NOTE: This message is followed by a secondary which indicates why it is not in test. NOTON ASCB 1. $ INVALID ;:

message 4, 11, 16, 17

VerifyA/CwiringJlA-3, JIB-11, 50, 66. Check ASCBinterconnects. Replace symbol generator. VerifyA/CwiringJIA-11, Replace symbol generator.

16, 17.


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346

Apr 15/93Use or disclosure of informationon this page is subject to the restrictions onthe

MESSAGE A/S ABOVE 50 KNOTS TEST SWITCH OFF

ACTION A/S must be below 50 knots for maintenance test. 1. 2. Verify maintenance test switch JIB-66. Replace symbol generator. Verify WOW input JIB-54. Replace symbol generator. input

WEIGHT ONWHEELS OFF SG(X) BITE FAIL ASCBFAILURE POWER SUPPLYFAIL DISCRETEFAILURE ARINCFAILURE E2 PROM FAILURE INTERLOCK FAIL ASCBTest: MESSAGE SG 1 ASCBFAIL

1. 2.

Replace symbol generator. Replace symbol generator. Replace symbol generator. Replace symbol generator. Replace symbol generator. Replace symbol generator. Replace symbol generator.

ACTION List boxes not rcvd by SG1 via ASCB (Message is normal in Phase II because of a problem in the symbol generator software, which will be fixed in the next symbol generator software update.) List boxes not rcvd by SG2 via ASCB (Message is normal in Phase II because of a problem in the symbol generator software, which will be fixed in the next symbol generator software update.)

SG 2 ASCBFAIL


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onthetitle

MESSAGE SG 3 ASCBFAIL

ACTION List boxes not rcvd by SG3 via ASCB (Message is normal in Phase II because of a problem in the symbol generator software, which will be fixed in the next symbol generator software update.)

To proceed with SG Test, the operator presses the PASSn or FAIL line select key based on the outcome of the test. This advances the test to the SG Status Test, the option highlighted on the CAS display, as shown in Figure 4-4.20. To return to the EDS Subsystem Menu, the operator presses the line select key labeled RETURN. The message on the CAS display prompts the operator to make a selection.

S6FILLTEST COMPLETE [1. STflTUS TESTI 2. SOFTHRRE MOD LEVEL TEST 3. SG 1 flSCB TEST 4. SG 2 RSCB TEST 5. SG 3 flSCB TESTA.

A1

A.

AD-22826#

SG Status Test Option Figure-4-4.20 Ground Maintenance Test Procedure Table 301 (cent)

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issu~ect

totheresttictions


4.2.2.3

Instructions This section may be required if the operator is executing the SG Test in any manner other than what has been described in the above section. If following the general operation section, proceed to Section 4.2.3. The operator selects, through the DC. initiates, and provides feedback for each test

Based on the information presented on the CAS display, the operator determines if the equipment passed or failed the test, and presses the appropriate line select key on the DC. This step is required before In addition, the operator may be the Maintenance Test will proceed. required to select an option associated with a test or return to the line previous menu. To do this, the operator presses the appropriate select key on the DC. The following is a list of how to use the LRUTest Menu displayed the DC CRT for Maintenance Test (refer to Figure 4-4). PASS The operator presses current test. IIFAILI, The operator presses current test.llp!l

on

this

line

select

key if the equipment

passes

the

this

line

select


fails

the

The operator presses this test selections presented SELECT

line select key to back-step through the on the Crew Alerting System (CAS) display.

The operator presses this line highlighted on the CAS display. ,,D~MN1l The operator presses selections presented

select

key to initiate

the task

that

is

this line select key to step on the CAS display.

through

the test


22-14-00



RETURN The operator presses this line select key to return to the menu that had been previously displayed on the DC. This is not used to select the options presented on the CASdisplay. 4.2.2.4 SG Maintenance ~ 27 27 27 27 4.2.3 4.2.3.1 ~ 15-4 3-1 0 Test ASCBData Bit Function Displayed Vertical Speed Spare F1ag (Or Maintenance Test) Twos Compliment Logic 1 = Valid

Data Acquisition General

Unit 1 (DAU1)

Operation feedback for the Data

initiates, and provides The operator selects, Acquisition Unit (DAU) Test through the DC.

When the EDS Subsystem Test Main is displayed on the DC CRT, as shown in Figure 4-4.21, the operator initiates the DAUTest by pressing the line select key labeled DAU1. This produces the LRUTest Menu to appear on the DC CRT, as shown in Figure 4-4.22. The Status/Software Test associated with each DAUwill show the active DAUSon ASCB, the DAUStransmitting valid data, verifies the correct identification pins, and shows the internal software level of each DAU. There is no correlation between Software Mod Status in Maintenance Test and the Mod Status shown externally on the LRU. The Software Mod Levels are used for reporting purposes.



Page 350 Apr 15/93

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of informationon


onthe

eB

eDU ~ DC SG eAD-22827#

e e e

FWC Df)U2

EDS Subsystem Test Main Figure 4-4.21

~ e

~

UP e PASS FAIL e SELECT DOWN ~ e

a

e

e

AD-22828#

LRUTest Menu Figure 4-4.22 The operator presses the DAUStatus/Software display, as shown in on the CAS display. Status/Software Test the line select key labeled SELECT to initiate Test, the option highlighted on the CAS Figure 4-4.23. Status or error messages appear Atypical CAS Display for the DAU1 is shown in Figure 4-4.24.


22-14-00


Paqe 351 Mar-15/91

P

>

DRU 1Il. STfITUS/SOFTWfIRETESTI

AD-22829#

DAUStatus/Software Test Option Figure 4-4.23 F >

OR(J IlllB ON flSCB Df+U lfl lB VFILID DRU lR lB ID PflSS SOFTWFIRE MOD LEVEL CPU R = (?106 RSCB fl= 0104 CPU B = 0106 RSCB B = 0104A

DRU 1

USE Pf3SS/FfIIL TO CONTINUEA Av

.

.

AD-22830#

DAU1 Status/Software Figure 4-4.24

Test


22-14-00

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Use or disclosure Ot information on this page is subject to the restrictions on the title page of this document.

The following is a list of all messages that may appear display as a result of executing the DAUStatus/Software BUS DAU1A ONASCB DAUlB ON ASCB VALID DAUlAVALID DAUlB VALID ID DAU1A ID PASS DAUlB ID PASS MOD LEVEL SOFTWARE MODLEVEL CPU = Xxxx ASCBA = XXXX SOFTWARE MODLEVEL CPU = Xxxx ASCBB = XXXX ~: Software Revision Information Verifies Correct Identification DAUSTransmitting Valid Data Active DAUSon ASCB

on the CAS Test.

There is no correlation between Software Mod Level in Maintenance Test and the Mod Status shown externally on the LRU.


22-14-00Page

353


Mar-15/91

4.2.3.2

Recommended Maintenance The following is a list and recommended action. Status/Software MESSAGE DAU(X) NOT IN TEST ~: Test:

Action of messages associated with maintenance test

ACTION

This message is followed by a secondary which indicates why it is not in test. 1. 2. 3.

message 5, 103, 106,

NOTON ASCB

VerifyA/Cwiring JIA-4, JIB-79. Check ASCBinterconnects. Replace DAU. VerifyA/Cwiring Replace DAU. JIA-4,

INVALID

1. 2.

5, JIB-79.

To proceed with DAUTest, the operator presses the PASS or FAIL line select key based on the outcome of the test, which results in the CAS Display shown in Figure 4-4.25. To return to the EDS Subsystem Menu, the operator presses the line select key labeled RETURN. The message on the CAS display prompts the operator to make a selection.

f-

MFIINTENflNCE TEST DflU 1FILL TEST COMPLETE[1. STflTUS/SOFTMflRETESTI

AD-22a31#

CAS Display Figure 4-4.25


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Page 354 Mar-15/91 dccument

4.2.3.3

Instructions This section may be required if the operator is executing the DAU1 Test in any manner other than what has been described in the above If following the general operation section, proceed to section. Section 4.2.4. The operator selects, through the DC. initiates, and provides feedback for each test

Based on the information presented on the CAS display, the operator determines if the equipment passed or failed the test, and presses the appropriate line select key on the DC. This step is required before In addition, the operator may be the Maintenance Test will proceed. required to select an option associated with a test or return to the line previous menu. To do this, the operator presses the appropriate select key on the DC. The following is a list of how to use the LRUTest Menu displayed the DC CRT for Maintenance Test (refer to Figure 4-4). PASS The operator presses current test. FAIL The operator presses current test.ltupll

on

this

line

select


passes

the

this

line

select


fails

the



The operator presses this line highlighted on the CAS display. 11~()~1, The operator presses selections presented

select

key to initiate

the task

that

is

this line select key to step through on the CAS display.

the test


22-14-00


Paae 355 Mar-15/91

RETURN The operator presses this line select key to return to the menu that had been previously displayed on the DC. This is not used to select the options presented on the CASdisplay. 4.2.4 4.2.4.1 Data Acquisition Unit 2 (DAU2) Test - The DAU2Test operates identical Refer to Section 4.2.3 for the required procedures. to the DAU1. DAUMaintenance ~ 19 4.2.5 4.2.5.1 Fault ~ 3 Test ASCBData BIT FUNCTION Maintenance Test Enable FORMAT Logic 1 = Enabled

Warning Computer (FWC) Operation for the Fault

General

The operator selects, initiates, and provides feedback Warning Computer Test (FWC) Test through theDC.

tihen the EDS Subsystem Test Menu is displayed on the DC CRT, as shown in Figure 4-4.26, the operator initiates the FWCTest by pressing the line select key labeled FWC. This produces the LRUTest Menu on The Status Test will show the the DC CRT as shown in Figure 4-4.27. active FWCSon ASCB, the FWCStransmitting valid data, verify correct identification pins, show the aircraft configuration information, and give the Built-In-Test (BITE) Results. The Software Mod Level Test will show internal software levels for each FWC. There is no correlation between Software Mod Status in Maintenance Test and the Mod Status shown externally on the LRU. The Software Mod Levels are The Checklist Test will show whether or used for reporting purposes. not a checklist installed and give the checksum of the installed The Cross-Side ASCBTest will show theASCB status with checklist. respect to the cross-side FWC(the one not selected on the sensor menu). The EEPROM BIT Test will show the percentage of memory used for Trend and Limit data as well as allowing the operator a means to test the EEPROM memory. ~: Executing this test will shorten the life of the EEPROM memory. This test may take over 5 minutes to execute.


22-14=00

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of information

on this page is sublect to the restrictions


~

Qe e ~ DC SG

DU FWC DA(.J2 ~ a

a

a

AD-22E32#

EDS Subsystem Test Menu Figure 4-4.26

e e

~

UP e PRSS FAIL ~ SELECT DOWN a a

e

~

AD-22833#

LRUTest Menu Figure 4-4.27 The operator presses the line select key labeled SELECT to initiate the FWCStatus Test, the option highlighted on the CAS display, as shown in Figure 4-4.28. Status or error messages appear on the CAS display. A typical CAS Display for the FWCStatus Test is shown in Figure 4-4.29.


22-14-00Page 357Apr 15/93of

on the title page Use or disclosureof informationon this page is subjectto the restrictions

this document.

F

)

FMCIl. STflTUS TESTI2. 3, 4. 5. SOFTMI?RE MOD LEVEL TEST CHECKLIST CROSS-SIDE flSCB TEST EEPROM BIT TEST

AD-22834#

FWCStatus Test Option Figure 4-4.28 f \

FWC 1 2 ON RSCB

FllC

FUC1 2 VflLID FWC1 BITE PflSS FMC2 BITE PflSS FHC1 2 ID Pf3SS fl/C ID PINS FWC 1 PFISS PINS = 10IUlFMC 2 PFISS

PINS = 10101A

USE PflSS/Ff31LTO CONTINUEA A

.

AD-22835#

CAS Display

for the FWCStatus Figure 4-4.29

Test


22-14-00



The following is a list of all messages that may appear display as a result of executing the FWCStatus Test. BUS FWC1 2 ONASCB VALID FWC1 2 VALID ID FWC1 ID PASS FWC2 ID PASS PINS A/C ID PINS: FWCPASS FWCFAIL PINS = 10101 Keying Pins 1 thru 5 134/C134JlA-12,13,14,15,16 Aircraft Configuration Verifies Correct Identification FWCSTransmitting Valid Data Active FWCSon ASCB

on the CAS

Information

Grid/Open Type A 12 G-IV O = Open BITE FWC1 BITE FAIL FWC2 BITE FAIL INTERLOCK FAILURE POWER SUPPLYFAIL DISCRETEFAILURE ARINCFAILURE CPU RAMFAILURE FWC1 BITE PASS FWC2 BITE PASS Gnd 1 = Gnd Built In Test Results 13 Open 14 Gnd 15 Open 16 Gnd


22-14-00

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Page 359 Mar-15/91

To proceed with FWCTest, the operator presses the PASS or FAIL line select key based on the outcome of the test. This advances the test to the FWCSoftware Mod Level Test, the option highlighted on the CAS display, as shown in Figure 4-4.30. To initiate the test the operator presses the line select key labeled SELECT. The resulting status or error messages appear on the CAS display. A typical CAS Display for the FWCSoftware Mod Level Test is shown in Figure 4-4.31.f >

FifC1. STRTUS TEST[2. SOFTWRRE MOD LEVEL TEST]

30 CHECKLIST 4. CROSS-SIDE flSCB TEST5, EEPROM BIT TEST

AD-22636#

FWCSoftware Mod Level Test Option Figure 4-4.30 f \

FWC1 S/W:CPU = 0113FISCB = 0110

FliC

FWC 2 S/W: CPU= 0113 RSCB 0110u

USE PflSS/Ff31LTO CONTINUEA A

A

.

AD-22837#

CAS Display

for the FWCSoftware Figure 4-4.31

Mod Level Test


22-14-00


Page 360 Mar 15/91

The following is a list of all messages that executing the FWCSoftware Mod Level Test. MODLEVEL FWC1 S/W: FWC2 S/W: CPU = Xxxx ASCB= XXXX ~: Software Revision

may appear Information

as a result

of

There is no correlation between Software Mod Level Test and the Mod Status shown externally on the LRU.

To proceed with FWCTest, the operator presses the PASS or FAIL line select key based on the outcome of the test. This advances the test to the FWCChecklist, the option highlighted on the CAS display, To initiate the test the operator presses as shown in Figure 4-4.32. the line select key labeled SELECT. The resulting status or error Atypical CAS display for the FWC messages appear on the CAS display. Checklist Test (without checklist installed) is shown in Figure 4-4.33.

FliC1. STFITUS TEST2. 131 4. 5..

SOFTHRRE MOD LEVEL TEST CHECKLIST] CROSS-SIDE f+SCB TEST EEPROM BIT TEST1

vFWCChecklist Option Figure 4-4.32

AD-22a3a#


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Page 361 Mar 15/91

e

-

CHECKLIST FMC 1 UNFIVRILRBLE FMC 2 UNt3VRILRBLEA

FIICUSE PflSS/F(+IL TO CONTINUEA A AD-22839#

CAS Display

for the FWCChecklist

Test may appear as a result of

Figure The following is a list of all executing the FWCChecklist. CKL CHECKLIST FWCINSTALLED FWCUNAVAILABLE CKSUM = XXXX

4-4.33 messages that

Checklist

Status

To proceed with FWCTest, the operator presses the PASS or FAIL line select key based on the outcome of the test. This advances the test to the FWCCross-Side ASCBTest, the option highlighted on the CAS display, as shown in Figure 4-4.34. To initiate the test the operator presses the line select key labeled SELECT. The resulting status or error messages appear on the CAS display. A typical CAS display for the FWCCross-Side ASCBTest is shown in Figure 4-4.35.


22-14-00

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to

the restrictions on the title page of fhis document.

Paae 362 Mar-15/91

F

T

FMC 1. STRTUS2. 3. [4. 5. TEST SOFTIIRRE MOD LEVEL TEST CHECKLIST CROSS-SIDE flSCB TESTI EEPROM BIT TEST

AD-22840#

FWCCross-Side I Figure

ASCBTest Option 4-4.34

e

\

FHC 2 RSCB PtlSS RLL LRUS RECEIVEDA A

FWCUSE PRSS/FflIL TO CONTINUEA AD-22a41(Rl)#

.

CAS Display

for the FWCCross-Side Figure 4-4.35

ASCBTest


22-14-00


Paae 363 Mar15/91

The following is a list of all messages executing the FWCCross-Side ASCBTest. ASCB FWC2 ASCBPASS FWC1 ASCBPASS FWC2 ASCBFAIL FWC1 ASCBFAIL ALL LRUSRECEIVED LRUSNOTRECEIVED DAU1A lB 2A 2B SG123 AFCS 1 2 NZ12 DC12 IRS 1 2 DADC1 2 PZ12 ASCBStatus

that

may appear

as a result

of

with Respect to FWC

I

I

To proceed with FWCTest, the operator presses the PASS or FAIL This advances the line select key based on the outcome of the test. test to the FW~EEPROM BIT Test, the option highlighted on the CAS display, as shown in Figure 4-4.36. TO initiate the test the operator presses the line select key labeled SELECT. The resulting status or error messages appear on the CAS display. A typical CAS Display for the FWCE~PROMBIT Test is shown in Figure 4-4.37.

FlfC1. STFITUS TEST2. 3. 4. 15. SOFTMRRE MOD LEVEL TEST CHECKLIST CROSS-SIDE IISCB TEST EEPROM BIT TESTI

AD-22842#

FWCEEPROM BIT Test Option Figure 4-4.36 Ground Maintenance Test Procedure Table 301 (cent)

22-14-00Pagetitle page of this document.

364

Apr 15/93Use or disclosure of informationon this page is subject to the restrictions onthe

IFHC 1 EEPROM Z FULL FliC 2 EEPROM Z FULL

MfHNTENRNCE TEST FiiC

IIFIRNING EXECUTING THIS TEST MILLSHORTEN THE LIFE OF THE EEPROM MEMORY NOTE THIS TEST TflKES OVER 5 MINUTES TO EXECUTE PRESS SELECT TO CONTINUE OR PFISS/ FFIIL TO RETURN TO MRIN MENUI

.

.

.

AD-22a43#

FWCEEPROM BIT Test Figure 4-4.37 4.2.5.2 Recommended Maintenance The following is a list and recommended action. Status Test: Action Action of messages associated with maintenance test

!kwuEFWCNOT IN TEST

NOTE : This message is followed by a secondary indicates why it is not in test. NOTON ASCB 1. 2.

message which

VerifyA/Cwiring JIA-5, 6, 7, 63, 65, 66, 85. Replace fault warning computer.


22-14-00

Use or disclosure Of information on this page is subjecf to the restrictions on the title page uf this


Status-

Test

(cent): Action 1. 2. Verify Maintenance Test Switch input JIA-85. Replace fault warning computer. Verify WOW input JIA-63.

TEST SWITCHOFF

WEIGHT ON WHEELS OFF FWC(X) BITE FAIL INTERLOCK FAILURE POWER SUPPLYFAIL DISCRETEFAILURE ARINC FAILURE CPU RAMFAILURE FWC(X) FAIL Checklist FWCUNAVAILABLE ASCBTest: FWC1 ASCBFAIL FWC2 ASCBFAIL Test:

1.

Replace Replace Replace Replace Replace Replace

Fault Fault Fault Fault Fault Fault

Warning Computer. Warning Computer. Warning Computer. Warning Computer. Warning Computer. Warning Computer. JIA-16.

CheckA/C

ID Pins JIA-12 thru

Action None, Checklist not installed. (Message Normal Without ASC 178).

Action List boxes not rcvd by FWC1 via ASCB. Check ASCB interconnects. List boxes not rcvd by FWC2 via ASCB. Check ASCB interconnects.


22-14-00


Paqe 366 Mar-15/91

To proceed with FWCTest, the operator presses the PASS or FAIL line select key based on the outcome of the test. This advances the test to the FWCStatus Test, the option highlighted on the CAS display, as shown in Figure 4-4.38. To return to the EDS Subsystem Menu, the operator presses the line select key labeled RETURN. The message on the CAS display prompts the operator to make a selection.

FMCil. STRTUS TEST~FILL TEST COMPLETE 2. 3. 4. 5.A

SOFTliFIRE MOD LEVEL TEST CHECKLIST CROSS-SIDE FISCB TEST EEPROM BIT TESTAT

A

.

.

AD-22844#

FWCStatus Test Option Figure 4-4.38 4.2.5.3 Instructions This section may be required if the operator is executing the FWCTest in any manner other than what has been described in the above section. If following the general operation section, proceed to Section 4.2.6. The operator selects, through the DC. initiates, and provides feedback for each test

Based on the information presented on the CAS display, the operator determines if the equipment passed or failed the test, and presses the appropriate line select key on the DC. This step is required before the Maintenance Test will proceed. In addition, the operator may be required to select an option associated with a test or return to the previous menu. To do this, the operator presses the appropriate line select key on the DC.


22-14-00

Paqe 367

Mar15/91 Use or disclosure of information on this page is subject to the restrictions on the title page of this document.

The following is a list of how to use the LRUTest Menu displayed the DC CRT for Maintenance Test (refer to Figure 4-4). PASS The operator presses current test. FAIL The operator presses current test.IllJpll

on

this

line

select

key if the equipment passes

the

this

line

select


fails

the



The operator presses this line select is highlighted on the CAS display. DOWN The operator presses selections presented RETURN

key to initiate

the task that

this line select key to step through on the CAS display.

the test

The operator presses this line select key to return to the menu that had been previously displayed on the DC. This is not used to select the options presented on the CAS display. 4.2.5.4 FWCMaintenance ~ 63 64 ~ 15-0 15-0 Test ASCBData BIT FUNCTION MAINTENANCE TEST MAINTENANCE TEST FORMAT



Page 368 Apr 15/93

Use or disclosure

of informationon


onthe

4.2.6 4.2.6.1

Display

Unit (DU) Operation and provides feedback for the Dis~laY .-

General

The operator selects, initiates, Unit (DU) Test through the DC.

When the EDS Subsystem Test Main is displayed on the DC CRT, as shown in Figure 4-4.39, the operator init. ates the DU Test by pressing the line select key labeled DU. This produces the LRUTest Menu on the DC CRT, as shown in Figure 4-4.40. There are four tests associated with the Display Unit. The Status - est will show the Reversionary and Overheat status of each DU. The Pi ot DUSTest uses the ARINC429 wraparound data from DU1 and DU2 to show the Error and Status Data associated with either DU1 or DU2. The EICAS DUSTest uses the ARINC 429 wrar)around data from DU3 and DU~ to show the Error and Status Data associated with either DU3 or DU4. The Copilot DUSTest uses the ARINC429 wraparound data from DU5 or DU6 to show the Error and Status Data associated with either DU5 or DU6.

o-l(3AD-22845#

EDS Subsystem Test Main Figure 4-4.39


22-14-00

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Page 369 Mar 15/91

/

~

ml=--i

UP

l-oElAD-22646#

EF

Pf+ssFAIL

SELECT DO14N

RETURN

LRUTest Menu Figure 4-4.40 The operator presses the line select key labeled the DU Status Test, the option highlighted on the Status or error messages shown in Figure 4-4.41. A typical CAS Display display. . . for the DU Status Figure-4-4.42; SELECT to initiate CAS display, as appear on the CAS Test is shown in

.

AD-22647#

DU Status Test Option Figure 4-4.41


22-14-00

Use or disclosure of information on this page is subject to the restrictions on the title page of this dccument.

Paae 370 Mar-15/91

/

MflINTENFINCE TESTNO DU IN REVERSION NO DU OVERHEFITED.

DU

I

USE PRSS/FRIL TO CONTINUE. .AD-22848#

Status

or Error Messages on CAS Display Figure 4-4.42

The following is a list of all messages that may appear on the CAS display as a result of executing the DU Status Test. REV DU REVERSION: DU 123456 NO DU IN REVERSION OVERHEAT DU OVERHEAT: DU 123456 NO DUOVERHEATED To proceed with DUTest, the operator presses the PASS or FAIL line select key based on the outcome of the test. This advances the test to the Pilot DUSTest, the option highlighted on the CAS display, as shown in Figure 4-4.43. To initiate the test the operator presses the line select key labeled SELECT. The resulting status or error messages appear on the CAS display. A typical CAS Display for the Pilot DUSTest is shown in Figure 4-4.44. Indicates Overheat Status Indicates Reversionary Status


22-14-00


Page 371 Mar 15/91

AD-22849#

Pilot DUSTest Figure 4-4.43

DU 1 VflLIDflRINCDU 2 VBLID flRINCA

DUUSE PRSS/FRIL TO CONTINUEA A AD-22850#

CAS Display

for the Pilot Figure 4-4.44

DUSTest


22-14-00 Page 372Mar 15/91

L& or

disclosure of information on thk page is subject to the restrictions on the title page of this document.

The following is a list of all ~xecuting the Pilot DUSTest. ARINC

messages that Error Pilot

may appear

as a result

of with

Status DUS

and Data Associated

DU 1 ARINC FAILURE DU 2 ARINC FAILURE LABEL350 ERROR LABEL351 ERROR LABEL352 ERROR LABEL353 ERROR DATA= XXXXX LABEL356 ERROR LABEL357 ERROR DATA- XXXXX DU 1 VALIDARINC DU 2 VALIDARINC NOTRECEIVINGDU 1 ARINC NOTRECEIVINGDU 2ARINC To proceed with DUTest, the operator presses the PASS or FAIL line select key based on the outcome of the test. This advances the test to the EICAS DUSTest option, highlighted on the CAS display, as To initiate the test the opc~ator presses the shown in Figure 4-4.45. line select key labeled SELECT. The resulting status or error messages appear on the CAS display. A typical CAS Display for the EICAS DUSTest is shown in Figure 4-4.46.

7

MflINTENflNCE TEST DU1. STfiTUS TEST2. PILOT DUS 13. EICFIS DUSI

4. COPILOT DUSAD-22851 #

EICAS DUSTest Option Figure 4-4.45


22-14-00


Page 373 Mar 15/91

DU 3 VflLIDFIRINC DU 4 VflLIDflRINC bA

DUUSE PRSS/FRIL TO CONTINUEA A AD-22852#

CAS Display

for the EICAS DUSTest Figure 4-4.46 that may appear as a result with

The following is a list of all messages of executing the EICAS DUSTest. ARINC Error Status EICAS DUS DU 3 ARINC FAILURE DU 4ARINC FAILURE LABEL350 ERROR LABEL351 ERROR LABEL352 ERROR LABEL353 ERROR DATA= XXXXX LABEL356 ERROR LABEL357 ERROR DATA- XXXXX DU 3 VALIDARINC DU 4 VALIDARINC NOTRECEIVINGDU 3 ARINC NOTRECEIVINGDU 4 ARINC

and Data Associated


22-14-00

Use or disclosure of information on this page is subject to the restrictions on the titl

Avionic Gulfstream IV-2

postal regulations prohibit

insure gust lock

inspect dpx connector

feel rough spots

cathode ray tube

touch control steering

software mod levels

crew alerting system

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