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Page 1: Avionic Gulfstream IV-2

Honeywell

Commercial Flight Systems GroupBusiness and Commuter AviationSystems DivisionHoneywell Inc.BOX 29000Phoenix, Arizona 85038

SPZ-8000 Digital Automatic FlightControl System

Gulfstream IV

SystemMaintenance Manual

Volume II — Ground Check

22-14-00TITLE PAGE T-1

PRINTED IN U.S.A PUB. NO. Al 5-1146-38REVISED 15 APR 1993

1 JUNE 1987

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PROPRIETARYNOTICE

This 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 disclosedto others without the written authorization of Honeywell Inc., except to the extent required forinstallation or maintenance of recipient’s equipment.

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

This revised 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.

S93

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

22-14-00TITLE PAGE T-2

Copyright 1993 Honeywell Inc.AN Rights Reserved

REVISED 15 APR 19931 JUNE 1987

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Date Received

READER COMMENTS(Mail or FAX this form to [602] 436-4100)

comments and recommendations to improve future editions

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Date Received

REPORT OF POSSIBLE DATA ERROR(Mail or FAX this form to [602] 436-4100)

Your Name Company/Airline

Address

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Honeywell Pub. No. ATA No.

Manual Ttile

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NC). LiFiAPHFlrlllHr

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RECORDOF REVISIONS- VOLUME11

Upon receipt of a revision, insert the latest revised pages and dispose ofsuperseded pages. Enter revision number and date, insertion date, and theincorporator’s initials on the Record of Revisions. The typed initials HI are usedwhen Honeywell Inc. is the incorporator.

Revision Revision InsertionNumber Date Date By

Revision Revision InsertionNumber Date Date By

Feb 1/88

Mar 1/89

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HoneywellMAINTENANCEMANUALGULFSTREAMIV

LIST OF EFFECTIVEPAGES- VOLUMEII

Original . . 0 . . Jun 1/87Revision . . 1 . . Feb 1/88Revision . . 2 . . Mar 1/89Revision . . 3 . . Ott 1/89

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Ground Check (cent)365 -366367368369370371372373374375376377378379380381382383384385386387388389390391392393394395396397398398.1398.2398.3398.4398.5398.6398.7398.8398.9398.10398.11398.12398.13398.14398.15398.16

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Ground Check (cent)398.68398.69398.70398.71398.72398.73398.74398.75398.76398.77398.78398.79398.80398.81398.82398.83398.84398.85398.86398.87398.88398.89398.90398.91398.92398.93398.94398.95398.96398.97398.98398.99398.100398.101398.102398.103398.104398.105398.106398.107398.108398.109398.110398.111398.112398.113398.114398.115398.116398.117

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SUBHEADINGANDPAGE

Honeywell

Ground Check (cent)398.161398.162398.163398.164398.165398.166398.167398.168398.169398.170398.171398.172398.173398.174398.175398.176398.177398.178398.179398.180398.181398.182398.183398.184398.185398.186398.187398.188398.189398.190398.191398.192398.193398.194398.195398.196398.197398.198398.199398.200398.201398.202398.203398.204398.205398.206398.207398.208398.209398.210

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SUBHEADINGANDPAGE

Ground Check (cent)398.261398.262398.263398.264398.265398.266398.267398.268398.269398.270398.271398.272398.273398.274398.274.1398.274.2398.275398.276398.277398.278398.279398.280398.281398.282398.283398.284398.284.1398.284.2398.284.3398.284.4398.284.5398.284.6398.284.7398.284.8398.285398.286398.287398.288398.289398.290398.291398.292398.293398.294398.295398.296398.297398.298398.299/398.300

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SECTION4GROUNDCHECK

1. General

This section provides a ground maintenance test procedure (Table 301) forchecking the SPZ-8000 System for correct installation and proper operation ofall components in the system. Table 302 provides a ground check procedurefor the flight management system.

NOTICE

Procedures in Table 301 are based on HoneywellEngineering Bulletin EB7015661, Revision B.

Procedures in Table 302 are based on HoneywellEngineering Bulletin EB7018760, Revision -.

Should any failures arise while performing the following test, refer to FAULTISOLATION, Section 5.

2. 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

~ Title ~

1.0 SCOPE 304

2.0 ABBREVIATIONS 305

3.0 SPECIFIC REQUIREMENTS 314

3.1 Overview 3143.2 Maintenance Test Configuration/Initiation 3143.3 Basic Display Formats and Operations 317

4.0 MAINTENANCETEST OPERATIONS 319

4.1 System Check 3194.2 Electronic Display Systems (EDS) 3234.3 Sensor Test 3824.4 FMS/PMSTest 398.64.5 Automatic Flight Guidance Control System (AFGCS) 398.624.6 Summary Test 398.103

APPENDIXA LIST OF TESTS AVAILABLEFORMAINTENANCETEST 398.107

APPENDIXB DELETED 398.111

APPENDIXC FLIGHTFAULTSUMMARYDESCRIPTION 398.112

APPENDIXD RECOMMENDEDACTIONSFOR FLIGHTFAULTSUMMARY 398.198

APPENDIXE SERVOSWITCHINGMONITORUSEDWITHFLIGHT FAULT 398.248SUMMARY

APPENDIXF SERVOSWITCHINGMONITORLOGICTABLE 398.276

Ground Maintenance Test ProcedureTable 301

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1.0 SCOPE

This document defines the requirements and instructions for the groundmaintenance test for the SPZ-8000 system installed on the Gulfstream G-IVaircraft.

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

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2.0 ABBREVIATIONS

Abbreviations used in this document are defined as follows:

Abbreviation Equivalent

AC Alternating CurrentA/C AircraftACARS ARINCCommunications Addressing and Reporting SystemACCEL Accelerometer, AccelerationADC Air Data ComputerAddr AddressADF Automatic Direction FinderADI Attitude Director IndicatorA/D Analog to DigitalAFCS Automatic Flight Control SystemAFGCS Automatic Flight Guidance Control SystemAFIS Airborne Flight Information SystemAGC Automatic Gain ControlAHRS Attitude and Heading Reference SystemAHRU Attitude and Heading Reference UnitAII Anti-IceAIL Ai 1eronALRT AlertALT AltitudeAMPS AmperesANN, ANNUN AnnunciatorANT AntennaAOA Angle of AttackAOSS After Over Station SensorAP, A/P AutopilotAPE Autopilot EngageAPP, APRPP, APR ApproachAPS Altitude PreselectAPU Auxiliary Power UnitARINC Aeronautical Radio, Inc.ARM ArmedAS AirspeedASCB Avionics Standard Communications BusAT, A/T AutothrottlesATC Air Traffic ControlATR Air Transport RequirementATT AttitudeAUX AuxiliaryAZ AzimuthB/A Bank AngleBARO BarometricBATT Battery

Ground Maintenance Test ProcedureTable 301 (cent)

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Abbreviation

BCBCDBITBITEBNRBOOBOWBRGBRK

%’CASCBCcwCDICDUCDSCDUCECHCHGCKSUMCKTCLBCLKCLRCMDCMPTRCNTLCOMCOMBCOMPCONFIG ‘CONTCORRCosCPCPLCPUCRCCRSCRTCRZCsCTCTRL

Equivalent

Back Course or Bus ControllerBinary-Coded-DecimalBuilt In TestBuilt In Test EquipmentBinaryBottom of DescentBasic Operating WeightB6&ng

Civil Aviation Authority (British)CaptureCrew Alerting System or Calibrated AirspeedCircuit BreakerCounterclockwiseCourse Deviation IndicatorControl Display UnitDifferential ResolverControl Display UnitCourse ErrorChannelChangeCheck SumCircuitClimbClockClearCommandComputerControlCommonCombinedCompensation, Compass, or CompactedConfigurationControllerCorrectionCosineCross Pointers, CopilotCoupleCentral Processor UnitCyclic Redundancy CheckCourseCathode Ray TubeCruiseCross SideControl TransformerControl

Ground Maintenance Test ProcedureTable 301 (cent)

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Abbreviation Equivalent

Cw ClockwiseDA Drift AngleD/A Digital to AnalogDADC Digital Air Data ComputerDAU Data Acquisition UnitDB Data BaseDC Display ControllerDCT DirectDDM Difference in Depth of ModulationDEFL DeflectionDEG DegreeDEMOD DemodulatorDES DescentDET Detector, DetentDEV, DEVN DeviationDG Directional Gyro

Decision HeightRFF Differential, DifferenceDISC DisconnectDISENG DisengageDISP DisplayDISPL DisplacementDIST DistanceDL Data LoaderDMA Direct Memory AccessDME Distance Measuring Equipment

DownEC Dual Remote CompensatorDSR Desi redDTG Distance To GoDTRK Desired TrackDU Display UnitDUP DuplicateE EastEEPROM,E2PROM Electronically Erasable Programmable Read Only MemoryEFIS Electronic Flight Instrument SystemEGT Exhaust Gas TemperatureEDS Electronic Display SystemEICAS Engine Instrument and Crew Alerting SystemEL, ELEV Elevator, ElevationEMI Electromagnetic InterferenceENG Engage, EngineEO Easy-OnE OFF Easy-OffEPR Engine Pressure RatioEPROM Erasable PROM

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Abbreviation Equivalent

ESS EssentialET Elapsed TimeETA Estimated Time of ArrivalETE Estimated Time In RouteEVM Engine Vibration MonitorEX LOC Expanded LocalizerEXT Extend, ExternalFAA Federal Aviation AuthorityFAR Federal Aviation RequirementFD, F/D Flight DirectorFDBK FeedbackFF Fuel FlowFFS Flight Fault SummaryFGC Flight Guidance ComputerFL Flight LeverFLCH Flight Level ChangerFLT F1ightFMS Flight Management SystemFPL, FPLtl Flight PlanFPM Feet Per MinuteFR, FRM FromFREQ FrequencyFV Flux ValveFWC Fault Warning ComputerGA, G/A Go AroundGCR Ground Clutter ReductionGMAP Ground MapGMT Greenwich Mean TimeGP Guidance PanelGPS Global Positioning SystemGRD GroundGS, G/S Glideslope, GroundspeedGSPD GroundspeedGW Gross WeightHB Heart BeatHBM Heart Beat MonitorHDG HeadingHDLC High Level Data Link ControlHF High FrequencyHORIZ HorizontalHP High PressureHR HourHSI Horizontal Situation IndicatorHYD HydraulicH/W HardwareIAS Indicated Airspeed

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Abbreviation Eaui val ent

ICAO International Civil Aviation OrganizationID, IDENT Identi fi cationIF Intermediate FrequencyIGN IgnitionILS Instrument Landing SystemINC-DEC Increase-DecreaseIND IndicatorINIT InitializationINS Inertial Navigation SystemINTFC InterfaceINTGL IntegralINTLK InterlockINV Invert1/0 Input/OutputIRC Instrument Remote ControllerIRS Inertial Navigation SystemIRU Inertial Navigation Unit1s0 IsolationIvv ‘ Instantaneous Vertical VelocityKBPS Kilo Bits Per SecondkHz KilohertzKN, KT KnotsL LeftLAT LatitudeLBS Lateral Beam SensorL/C Inductive/CapacitiveLH Left HandLIM LimitLNAV Lateral Navigation/Lateral GuidanceLOC LocalizerLON LongitudeLORAN Position Sensor TypeLP Low PressureLPV Latched Power ValidLRN Long Range NavigationLRU Line Replaceable UnitLSB Least Significant BitLTG LightingLTS Long Term SensorLVC Line Voltage CompensationLVDT Linear Variable Differential TransformerMAG MagneticMAGVAR Magnetic VariationMFD Multifunction DisplayMHz MegahertzMIN Minutes

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Abbreviation

MLSMMMMoMOMMONMSBMSGMSLM/T, M/TRIMMUXNNAV

fl:DNDNDBNMNONOCNORMNOTAMNWNVR

!):so/cOMOsc0ssPPAllPBPcPERFPFDPISOPITPITCH SYNCPLAPLNPMsPosPPHPPOSPRESSPRI, PRIM

Equivalent

Microwave Landing System~iddle Marker~aximum Allowable Mach Number~omentary!on i tor~ost Significant BitYessage~ean Sea Level~ach Trim‘multiplexerUorthNavigationNo Connection, Normally Closed, or NAVComputerMOComputer DataNavigation DisplayNon-Directional BeaconYautical MileUormally OpenNAVon CourseUormalNotice To AirmanNon-Return To ZeroUon-Volatile RAMNavigation ComputerJnni Bearing Selector3n Course)uter Marker)scillator)ver Station SensorPressurePitch AttitudePushbuttonPerformance ComputerPerformancePrimary Flight DisplayParallel In Serial OutPitchPitch Synchronizationpower Lever AngleP1anperformance Management SystemPositionPounds Per HourPresent PositionPressure%irnary

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Abbreviation Equivalent

PROC ProcessorPROF Profi 1ePROG Programmer, ProgrammingPROM Programmable Read Only MemoryP/s Pitot SwitchPSI Pounds Per Square InchPv Power ValidPM Pitch Wheel or Pulse IiidthPWM Pulse Width ModulatedPWR Power

Performance Computer: Quality Factor~TY Quantity

RightRA, R/A, RADALT Radio AltimeterRAM Random Access MemoryRCT Rain Echo AttenuationRCVR . ReceiverREF ReferenceREL ReleaseRET ReturnRETR RetractREV Reverse Source (Same as Back Course)

Rate Gyro;; Right-HandRMI Radio Magnetic IndicatorRN, RNAV Area NAVRNAPP RNAVApproach

Range!!: Rol1ROM Read Only MemoryRPM Revolutions Per MinuteRT, R/T Receiver/Transmitter, Rate of TurnRUD Rudders SouthSAT Static Air TemperatureSBY, STBY StandbySCI Serial Control InterfaceSCR SourceScs Single Channel SelectSDI Source/Destination IdentificationSEC Seconds, SecondarySEL Select

Symbol Generator~!D Standard Instrument DepartureSIG Signal

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Abbreviation Eauivalent

SIN SineSING SingleSIPO Serial In Parallel OutSPD SpeedSRAM System Random Access MemorySRN Short Range NavigationSSEC Static Source Error CorrectionSSM Sign Status MatrixSTAEL Station ElevationSTAR Standard Terminal Arrival RouteSTBY StandbySTC Sensitivity Time ControlSTCS Single Trim Channel SelectSTP SteepSTR, STRG SteeringSvo Start Valve OpenSw, s~kl SoftwareSYNC - SynchronizationSYS SystemT TemperatureTAS True AirspeedTAT True Air TemperatureTBD To Be DeterminedTCS Touch Control SteeringTEMP TemperatureTGT Target, Turbine Gas TemperatureTK Turn Knob, TrackTKE Track ErrorTKOD Turn Knob Out of DetentTLA Torque Limit AileronTLE Torque Limit ElevatorTOC Top Of ClimbTOD Top Of DescentTOGA Take Off-Go AroundTP Test PointTRK Track

Thrust Reference Set% TrueTSO Technical Standard OrderTTG Time-To-GollL Tuned to LocalizerUART Universal Asynchronous Receiver TransmitterUTIL, UTY UtilityV1 Takeoff Decision Speed

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Abbreviation Equivalent

V2 Takeoff Safety Speed (Speed to be attained at35 feet AGC, assuming recognition of an enginefailure after VI)

VA Volt AmpereVAL ValidVANG Vertical AngleVAPP, VAPR VORApproachVAR VariableVBS Vertical Beam SensorVco Voltage Controlled OscillatorVEL VelocityVERT VerticalVFLC Vertical Flight Level ChangeVfs Final Takeoff Climb Speed (Airspeed for single-engine

climb in a clean configuration below 1500 feet AGC)VG Vertical Gyro or Vertical GeneratorVHF Very High FrequencyVLD ValidVLF “ Very Low FrequencyVmo MaximumAllowable AirspeedVNAV Vertical NavigationVOR VHFOmni RangeVORTAC Colocated VORand Tacan StationsVPTH Vertical PathVr Takeoff Rotation SpeedVRAM Video Random Access MemoryVref Reference Speed (Landing)VRT, VERT VerticalVs, v/s Vertical SpeedVse Enroute Climb Speed (~irspeed for single-engine climb

in a clean configuration above 1500 feet AGC)VTA Vertical Track Alert

West;L, W/L Wings LevelNO Washed Outwow Weight on WheelsWPT WaypointWR, WX Weather RadarWSP Word Sequence PositionXFER TransferXMTR TransmitterX-SIDE Cross-SideXTRK Cross TRACKYD, Y/D Yaw Damper

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3.0 SPECIFIC REQUIREMENTS

3.1 Overview

Ground Maintenance Test is an operator activated set of diagnosticsconsisting of five maJor tests> 1) System Check, 2) Electronic DisplaySystem (EDS), 3) Flight Management System (FW~S), 4) Automatic FlightGuidance Control System (AFGCS), and 5) Sensors. Each major test isdescribed in detail in separate sections within this manual.

The Maintenance Test isolates faults down to the Line Replaceable Unit(LRU) level. Additional information is also provided in most cases.

3.2 Maintenance Test Configuration/Initiation

To configure the system for Maintenance Test the operator must satisfythe following conditions:

- Airspeed less than 50 knots

- weight on Wheels (WOW)

“TEST” switch on Display Controller (DC) depressed

- Maintenance Test Switch activated in either the Left or Right AvionicsBay.

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

[1

[1

[1===------------

[1===------

[1===

EFIS EICAS ===[1RADALT A/P DISC ======[]S/L <-----ALA-----> ALT ===[1A/T DISC ======[1

MAINT===[1

Test MenuFigure 3-1

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Note that the Engine Instrument Display now displays test value asfollows:

TGT 1000 RedLP/HP 100.0 RedOil Pressure 10 RedOil Temperature 100 WhiteEVMHP/LP 1.00 WhiteHyd Pressure (all) 1000 WhiteFuel Temperature 100 AmberFuel Quantity Total 2000 WhiteFuel Quantity L-R 1000 WhiteEPR 0.98 White

Additionally, Blue “MAINTSWITCHON” and “FGC SYSTEMTESTn messages aredisplayed on the Crew Alerting System (CAS) display. The PFD on the sidefrom which Ground Maintenance Test is being run will display an amberVSPDor the airspeed tape.

To initiate Maintenance Test, the operator presses the line select keylabeled ‘MAINT”located in the bottom right corner of the DC. Thisproduces the System Test Menu to appear on the DC CRT, shown in Figure3-2. The Crew Alerting System (CAS) display appears as shown in Figure3-3.

CA(3(3

\

EDS

SYSTEM CHECK FMS/PMS

AFGCS SUMMARY

System Test MenuFigure 3-2

AD-22803 #

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MAINTENANCETEST

CASDisplay, Maintenance Test StartFigure 3-3

Each of the tests available to the operator from the System Test Menu aredescribed 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 sectionexplains the basic display formats and operations procedures associatedwith the DC, and the CAS display.

Ground Maintenance Test ProcedureTable 301 (cent)

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3.3 Basic Dis~lav Formats and O~erations

The operator selects, initiates, and provides feedback for most teststhrough the DC. The operator interacts with the Guidance Panel (GP),Manual Controller, and aircraft switches, to perfom portions of theAutomatic Flight Guidance Control System (AFGCS)Test.

3.3.1 Display Controller - Throughout the operation of Maintenance Test, theDC 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 theMaintenance Test. If all the conditions described in Maintenance TestConfiguration/Initiation Section 3.2, the Test Menu will be displayed.

The System Test Menu, shown in Figure 3-5, allows the operator toselect the various major tests.

The Subsystem Test Menu, example shown in Figure 3-6, allows theoperator to select various subsystem tests associated with major tests.

The LRUTest Menu, example shown in Figure 3-7, allows the operator tomanipulate the major or subsystem tests.

3.3.2 Crew Alerting System (CAS) Display - The CASdisplay is divided intotwo sections, the right side and the left side.

The left side of the display indicates the status or error messageassociated with the system or LRUas a result of the test. All themessages associated with each test are explained in their respectivesections.

The right side of the display indicates that the system is inMaintenance Test by displaying the “Maintenance Test” header followedby the annunciation of the test currently being executed. In addition,any instructions and/or options available to the operator aredisplayed.

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I

r 1===

[1=;;======rl ======

‘1[1===

[1=:+======[1=;;======

[1===[]=y=====[1=;;======

EFIS EICASRADALT A/P DISCs/L <.---->OA-----> ALT

MAINT

Test MenuFigure 3-4

~ E,,

SYSTEMCHECK FMS/PMSAFGCS SUMMARY,SENSORS RETURN

System Test MenuFigure 3-5

nEDS

DC F~!SG DAU2DAU1 RETURN

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

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

===[1~-;=[1

‘======[11===[1

Subsystem Test Menu, EDS ExampleFigure 3-6

[1===[l=~;===

===[1=;;===------

nDAU1

PASS SELE&FAIL DOWN

RETURN

LRUTest Menu, DAU1 ExampleFigure 3-7

===[1======[1===[1======[1,===[1

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4.0 MAINTENANCETEST OPERATIONS

4.1 Svstem Check

The System Test determines the present system configuration.

4.1.1 General Operation - The operator selects, initiates, and providesfeedback 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 bypressing the line select key labeled “SYSTEMCHECK”.

System Test MenuFigure 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 aresult of executing the System Check Test. With all the LRUS installedand the system functioning normally, the message “SYSTEM CHECK PASS”will appear on the left side of the CASdisplay.

BC Bus Controller StatusBC 1 2 3 TEST FAILBC 1 2 3 INVALIDNO BC ON BUSANO BC ON BUS B

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I

LRUSTransmitting Valid Data

ASCB ASCBStatus

LRUSNOTONASCBFWC1FWC2~#J1l;$A lB 2B

AFCS 1 2NZ12DC12;::C1122

PZ12

VALID

LRUSINVALIDFWC1FWC2::U1l; ;A lB 2B

fijc~ ; 2

DC12y):c1122

PZ12

4.1.2 Recommended Maintenance Action

The following is a list of messages associated with maintenance testand recommended action.

MESSAGE ACTION

BC 1 2 3 TEST FAIL 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 ValidWiring.

NO BC ON BUSA B Check ASCBinterconnects.

LRUSNOTONASCB Identifies which boxes are not received on ASCBby the fault warning computer. Check ASCBinterconnects for listed boxes. Make sure unitsare in and selected on, CBS in.

LRUS INVALID Identifies which boxes are on ASCBand areinvalid.

BC 1 2 3 INVALID See next paragraph. Replace SG.

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The following is a detailed description for the messages, “BC 1-2-3 TESTFAIL” and “BUXCTLR1-2-3 FL”.

A Bus Controller test is performed by the default master FWC. To initiatethe test, the following conditions must be met:

1. FWCpower up sequence complete2. Weight on wheels active (ground)3. Airspeed valid and indicating less than 60 kts.4. Activity on both Bus A and Bus B5. All three Bus Controllers valid (discretes)

FWCNo. 1 is designated the default master for initiation of the BusController Test. Once the above enable logic has been satisfied, FWC1checks FWC2 to ensure a test is not in progress nor has been previouslyperformed. If a test is not complete nor in progress by FWC2, FWC1initiates the test by transmitting a ground on the BC Test Request line.The FWC1 looks at the Bus Controller Frame Control Transmission for aTest Frame Flag. FWC1 then ensures each Bus Controller assumes controlof the bus by looking at the Controller ID. After each frame cyclesthrough each controller, FWC1 checks the Bus Controller Valids. If anopen condition is detected, then “BC X TEST FAIL” message is enabled. FWC1 then transmits the results via WSP66. For FWC2 a one second wait isinserted at the end of the enabling logic to allow time for the master(FWC1) to initiate the test. Following the wait, WSP66 of FWC1 ischecked to determine the status. If FWC1 test is complete, FWC2 setsWSP66 to reflect the same status. If FWC1 test is in progress, FWC2waits one second and checks again. Once the Bus Controller Test iscomplete, the Bus Controller Monitors become active and should the BusController become invalid, a “BC X FAIL” message is enabled.

BC TEST REQUESTNO. 1 * 134J1A-96 (22) ----------W;Bli C65J1B-1,

BC TEST REQUESTNO. 2 * C134J1A-96 (22) ----------;~~&2; C65J1B-2,

* ~ND ENABLE

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For convenience, the Bus Controller Frame Control Transmission is listedbelow:

BYTE BIT BIT FUNCTION FORMAT

o HDLCFLAGADDRESS

: TEST FRAMEFLAG2 6~5 CONTROLLERID22

; 4 ;[&T-UP FRAME2

RESERVED; 2:0 FRAMENUMBER3,4 ERRORCHECK5 HDLCFLAG

7E HEX81 HEXLOGIC 1 =TESTOO=CONTROLLEROO1=CONTROLLER110=CONTROLLER2ll=CONTROLLER3LOGIC I=START-UP

ALWAYSO0-7 HEXCRC7E HEX

For convenience, WSP66 of the FWCis listed below:

WSP BIT BIT FUNCTION BIT FORMAT

BUS CONTROLLERTEST STATUS

15 TEST COMPLETE LOGIC 1 = COMPLETE14 TEST IN PROGRESS LOGIC 1 = IN PROGRESS

TEST RESULTS13 BC 1 STATUS LOGIC 1 = TEST PASSED12 BC 2 STATUS LOGIC 1 = TEST PASSED11 BC 3 STATUS LOGIC 1 = TEST PASSED

1o-o SPARE

If Test Complete Bit 15 = O, the blue “BUS CTLRX FL” messages are enabledusing the discrete input valids. This message can be enabled independentfrom the Weight on Wheels discrete.

The Bus Controller Valids into the FWCare as follows:

BUSCONVALIDNO. 1 * 65J1A-13 (22)-----13497,-97, C134J1A-97

BUSCONVALIDNO. 2 * C65J1A-13 (22)-----13498,-98, C134J1A-98

BUS CONVALIDNO. 3 * E65J1A-13 (22)-----13499,-99, C134J1A-99

* GND=VALID/OPEN-INVALID

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If Test Complete Bit 15 = Logic 1, message logic is as follows:

1. If BC Status Bit = 1 (PASS) and BC is valid, there will be no message.

2. If BC Status Bit = O, (FAIL), the blue “BC X TEST FAIL” message isenabled.

3. If BC Status Bit = X (DON’TCARE) and BC is invalid the blue “BUS CTLRX FL” message is enabled.

NOTE: Any message enabled as a result of 2 above is disabledfollowing either the loss of weight on wheels or airspeedgreater than 60 kts, the messages will not return.

This completes the System Check Test. To proceed with the MaintenanceTest, the operator presses the line select key labeled “SYSTEMCHECK”, todeselect the test. This produces the System Test Menu to be displayed onthe DC CRT.

4.2 Electronic DisDlav Svstems (EDS~

When the System Test Menu is displayed on the DC CRT as shown in Figure4-2, the operator initiates the Electronic Display System (EDS) Test bypressing the line select key labeled “EDS”. This produces the EDSSubsystem Menu to appear on the DC CRT as shown in Figure 4-3. The CASdisplay will be as shown in Figure 4-3.1.

~ a

e EDS e

e SYSTEM CHECK FMS/PMS a

e flFGCS SUMMARY ~

e a

AD-22803#

System Test MenuFigure 4-2

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EDS - Subsystem Test MenuFigure 4-3

EDS

PLEFHE MFIKESELECTION

AD-22805#

EDS - CAS DisplayFigure 4-3.1

The operator selects one of the subsystem tests or returns to the SystemTest Menu by pressing the appropriate line select key. Each of thesubsystem tests are described in the following sections.

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!.2.1 Display Controller (DC)

!.2.1.1 General Operation

The operator selects, initiates, and provides feedback for the DC Testthrough the DC.

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

UP

PPtss SELECT

FAIL DOWN

t(

DC LRUTest MenuFigure 4-4

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

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MflINTENRNCE TEST

DcIl. DC 1 STftTUS TEST]2. DC 2 STllTUS TEST3. CONF16URfITION TEST4. SOFTllllRE MOD LEVEL TEST

A A A

AD-22807-R1 #

CASDisplayFigure 4-4.1

There are three tests associated with the DC test. The Status Testwill show the LRUSnot received on ASCBby the Display Controller aswell as the Built-In-Test (BITE) results. The Configuration Testwill show the current strapping of the configuration pins on theDisplay Controller. The Software Mod Level Test will show theinternal software level of the Display Controller. There is nocorrelation between the Software Mod Status in Maintenance Test andthe Mod Status shown externally on the LRU. The Software Mod Levelsare used for reporting purposes.

The operator presses the line select key labeled “SELECT” to initiatethe DC Status Test, the option highlighted on the CAS display.Status or error messages appear on the CASdisplay. A typical CASDisplay for the DC Status Test is shown in Figure 4-4.2.

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f \

MRINTENflNCETEST

DC 1 ONRSCB DC

DC 1 VflLID

DC 1 flSCB PflSSflLL LRUSRECEIVED

DC 1 BITE PINSUSE PRSS/FilIL TO CONTINUE

A A h

AD-22aoe-Rl#

CAS Display for the DC Status TestFigure 4-4.2

NOTE: DC 2 Status Test CASDisplay is the same as shown inFigure 4-4.2 except Number 1 is shown as 2.

The following is a list of all messages that may appear on the CASdisplay as a result of executing the DC Status Test.

BUS Active DCSon ASCB

DC 1 ONASCBDC 2 ON ASCB

VALID DCS Transmitting Valid Data

DC 1 VALIDDC 2 VALID

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ASCB ASCBStatus with Respect to the DCS

DC 1 ASCBFAILDC 2 ASCBFAILLRUSNOTRECEIVEDDC 2DC 1PZ12DC 1 ASCBPASSDC 2 ASCBPASSALL LRUSRECEIVED

BITE Built In Test Results

DC 1 BITE FAILDC 2 BITE FAILTACHINPUTSTUCKVRAMTEST FAILSRAMTEST FAILROMCHECKSUMFAIL PASS

- DC 2 BITE PASSA/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 thetest to the DC Configuration Test, the option highlighted on the CASdisplay, as shown in Figure 4-4.3. To initiate the test the operatorpresses the line select key labeled “SELECT”. The resulting statusor error messages appear on the CASdisplay. A typical CASDisplayfor the DC Configuration Test is shown in Figure 4-4.4.

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DC1.STFITUSTEST[2. CONFIGURFITIONTEST]3. SOFTW13REMODLEVEL TEST

AD-22809#

DC Configuration Test - CASOption HighlightedFigure 4-4.3

m

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F Y

DC 1 2 ID PflSS DC

DC 1 CONFIGURFITIONIRS TRIPLEX

PZ INSTRLLEDILS INSTRl_l-ED

FGC 1 (2) SELECTEDCRS 1 2 SYNC

DC2 CONFIGURFITIONIRS TRIPLEX

PZ INSTflLLEDII-S INSTF!LLED

FGC 1 (2) SELECTEDCRS 1 2 SYNC USE PfISS/FflIL TO CONTINUE

A A A

AD-2281 0#

CAS Display for the DC Configuration TestFigure 4-4.4

The following is a list of all messages that may appear as a result ofexecuting the DC Configuration Test. The operator is responsible forverifying that the configuration is correct.

ID Verifies Correct Identification

DC 1 ID PASSDC 2 ID PASS

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cONFIGURATION Aircraft Configuration Information

DC CONFIGURATIONIRS TRIPLEXIRS DUALPZ INSTALLEDTWOMLS INSTALLEDONEMLSINSTALLEDI LS INSTALLEDFGC 1 2 SELECTEDFGC 1 SELECTEDFGC 2 SELECTEDCRS 1 2 SYNCCHECKLISTENABLED

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

I

DC

1. STFITUSTEST2. CONFIGURATIONTEST

!3. SOFTHRREMODLEVEL TEST]

h A A

DC Software Mod Level TestFigure 4-4.5

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DC 1 S/ii = REV113 DC

DC 2 S/ii = REV 113

A A A.

AD-2281 2#

CASDisplay for the DC Software Mod Level TestFigure 4-4.6

The resulting status or error messages appear on the CAS display. Thefollowing is a list of all messages that may appear as a result ofexecuting the DC Software Mod Level Test.

MODLEVEL Software Revision Information

NOTE:

DC 1 S/W = XXXXDC 2 S/W = XXXX

There is no correlation between Software Mod Status inMaintenance Test and the Mod Status shown externally on theLRU.

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4.2.1.2 Recommended Maintenance Action

The following is a list of messa9es associated with maintenance testand recommended action.

Status Test:

MESSAGE ACTION

DC(X) NOTIN TEST VerifyA/Cwiring J1-A, B, R, S.NOTONASCB Replace DC.

DC 1 ASCBFAIL List boxes not rcvd by DC1 via ASCB.Check ASCBinterconnects.

DC 2 ASCBFAIL List boxes not rcvd by DC2 via ASCB.Check ASCBinterconnects.

DC 1 BITE FAIL Replace display controller.

DC 2-BITE FAIL Replace display controller.

AID FAIL The DC can fail intermittently on power-up.When this occurs, entering Maintenance Testwill reveal a “DC X BITE FAIL” and “A/DFAIL”. If cycling the DC circuit breakerdoes not clear this failure then replace theDC.

TACHINPUTSTUCK 1. Check CRS#l and CRS#2 interconnectfrom guidance panel.

2. Replace display controller.

VRAMTEST FAIL Replace display controller.

SRAMTEST FAIL Replace display controller.

ROMCHECKSUMFAIL Replace display controller.

Configuration Test:

Messacae Action

CRS 1 2 SYNC Course sync button depressedor Wiring from GP-820, llJ1-36or 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 thetest to the DC-Status Test, the option highlighted on the CASdisplay.The CAS Display will be as shown in Figure 4-4.7.

DCil.STRTUS TEST]

flLLTEST COMPLETE 2. CONFIGURATION TEST3. SOFTkitlREMOD LEVEL TEST

A A A. . .

AD-2281 3#

Figure 4-4.7

To return to the EDS Subsystem Menu. the operator presses the lineselect key labeled “RETURN”. The message on the CAS display promptsthe operator to make a selection.

4.2.1.3 Instructions

This section may be required if the operator is executing the DC Testin 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, initiates, and provides feedback for each testthrough the DC.

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

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The following is a list of how to use the LRIJTest Menu displayed onthe DC CRT for Maintenance Test (refer to Figure 4-4).

llPASS~l

The operator presses this line select key if the equipment passes thecurrent test.

‘FAIL”

The operator presses this line select key if the equipment fails thecurrent test.

‘UP”

The operator presses this line select key to back-step through thetest selections presented on the Crew Alerting System (CAS) display.

“SELECT”

The operator presses this line select key to initiate the task thatis highlighted on the CAS display.

“DOWN”

The operator presses this line select key to step through the testselections presented on the CASdisplay.

“RETURN”

The operator presses this line select key to return to the menu thathad been previously displayed on the DC. This is not used to selectthe options presented on the CASdisplay.

4.2.1.4 DC Maintenance Test ASCBData

~~ Bit Function Format

4 MAINTTest Enable Logic 1 = Enabled:3 WOW/GND Logic 1 = WOW42 MAINTTest Select Logic 1 = Select

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4.2.2 Symbol Generator (SG)

4.2.2.1 General Operation

The operator selects, initiates, and provides feedback for the SymbolGenerator (SG) Test through the DC.

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

~

e DU e

e DC FWC a

e SG Df+U2 e

e ~

AD-22814#

EDS Subsystem Test MenuFigure 4-4.8

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mUP

Pfiss SELECT

FAIL DOWN

RETURN

LRUTest MenuFigure 4-4.9

MFHNTENFINCE TEST

S6Il. STFITUSTEST]2, SOFTNRRE HOD LEVEL TEST3. S6 1 RSCB TEST4. SG 2 fiSCBTEST5. SG 3 flSCBTEST

.AD-22816#

CAS DisplayFigure 4-4.10

The operator presses the line select key labeled “SELECT” to initiatethe S& Status Test, the option highlighted on the CAS display. Statusor error messages appear on the CAS display. A typical CAS displayfor the SG Status Test is shown in Figure 4-4.11.

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SG 1 2 3 ON FISCB S6

S6 1 2 3 VFILID

SG 1 BITE PflSS

SG 2 BITE PRSS

SG 3 BITE PflSS ~

SG1231DPflSS~ USE PRSS/FflIL TO CONTINUE

A A A. . .

AD-Z?817#

CAS Display for the SG Status Test‘Figure 4-4.11

The following is ;display as a resu”

BUS

SG 1 2 3 ON

VALID

SG 1 2 3 VALID

list of all messages that may appear on the CASt of executing the SG Status Test.

Active SGS on ASCB

ASCB

SGS Transmitting Valid Data

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BITE Built In Test Results

SG 1 BITE FAILSG 2 BITE FAILSG3 BITE FAILASCBFAILUREPOWERSUPPLYFAILDISCRETEFAILUREARINCFAILURE

E2 PROMFAILUREINTERLOCKFAILURESG 1 BITE PASSSG 2 BITE PASSSG 3 BITE PASS

ID Verifies Correct Identification

SG 1 2 3 PASS

To proceed with SG Test, the operator presses the “PASS” or “FAIL”line select key based on the outcome of the test. This advances thetest to the SG Software Mod Level Test, the option highlighted on theCASdisplay, as shown in Figure 4-4.12. To initiate the test theoperator presses the line select key labeled “SELECT”. The resultingstatus or error messages appear on the CASdisplay. A typical CASDisplay for the SG Software Mod Level Test is shown in Figure 4-4.13.

S6

1. STflTUS TEST12. SOFTMFIRE MOD LEVEL TEST]3. S6 1 flSCBTEST40 S6 2 FISCBTEST5. S6 3 flSCBTEST

A A A.

AD-2281 8#

SG Software Mod Level Test OptionFigure 4-4.12

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S6 1 S/h’

CPU I+= 0119CPU B = 0119flSCB= 0116

SG 2 SIM

CPU R = 0119CPU B = 0119flSCB= 0116

SG 3 S/ii

CPU R = 0119CPU B = 0119FISCB= 0116

MFHNTENFINCE TEST

S6

USE PfISS/FflILTO CONTINUE

, .AD-22819#

CAS Display for the SG Software Mod Level TestFigure 4-4.13

The following is a list of all messages that may appear as a result ofexecuting the SG Software Mod Level Test.

MODLEVEL Software Revision Information

SG 1 S/W:SG 2 S/W:SG 3 S/W:CPU A = XXXXCPU B = XXXXASCB= XXXX

NOTE: There is no correlation between Software Mod Level inMaintenance Test and the Mod Status shown externally on theLRU.

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To proceed with SG Test, the operator presses the “PASS” or “FAIL”line select key based on the outcome of the test. This advances thetest to the SG-l ASCBTest, the option highlighted on the CASdisplay,as shown in Figure 4-4.14. To initiate the test the operator pressesthe line select key labeled “SELECT”. The resulting status or errormessaqes appear on the CASdisplay. A typical CASDisplay for the SG1ASCB~est is shown in Figure 4:4.15. ‘-

f Y

S6

1. STflTUSTEST2. SOFTMRRE MOD LEVEL TEST[3. S6 1 flSCBTEST]4. S6 2 FISCBTEST5. S6 3 f3SCBTEST

A

AD-22820#

SG 1 ASCBTest OptionFigure 4-4.14

F \

S6 1 FISCBPflSS S6

fiLLLRUS RECEIVED USE Pf3SS/Ff31LTO CONTINUE

A A A. . v

AD-22821#

CAS Display for the SG 1 ASCBTestFigure 4-4.15

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The following is a list of all messages that may appear as a resultof executing the SG 1 ASCBTest.

ASCB ASCBStatus with Respect to SGS

SG 1 ASCBPASSALL LRUSRECEIVEDSG 1 ASCBFAILLRUSNOTRECEIVEDDC12FWC1 2NZ12DAU1A lB 2A 2BAFCS 1 2DADC1 2PZ12A/T 1 2SG23

NOTE: SG 1 ASCBTest gives “SG 1 ASCBFAIL” “LRUSNOTRECEIVEDAFCS1 2.”

To proceed with SG Test, the operator presses the ‘PASSn or “FAIL”line select key based on the outcome of the test. This advances thetest to the SG 2 ASCBTest, the option highlighted on the CASdisplay, as shown in Figure 4-4.16. To initiate the test theoperator presses the line select key labeled ‘SELECT”. The resultingstatus or error messages appear on the CASdisplay. A typical CASDisplay for the SG 2ASCB Test is shown in Figure 4-4.17.

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/ \

S6

10 STRTUS TEST2. SOFTWRRE MOD LEVEL TEST3. S6 1 f3SCBTEST[4. S6 2 flSCBTESTI5. SG 3 FISCBTEST

A A

AD-22822#

4 \

MfHNTENflNCE TEST

SG 2 fISCBPRSS S6

RL1LRUS RECEIVED USE PfISS/FllILTO CONTINUE

A A Av

SG 2 ASCBTest OptionFigure 4-4.16

.

CAS Display for the SG 2 ASCBTestFigure 4-4.17

“AD-22a23(Rl)#

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The following is a list of all messages that may appear as a resultof executing the SG 2 ASCBTest.

ASCB ASCBStatus with Respect to SGS

SG 2 ASCBPASSALL LRUSRECEIVEDSG 2 ASCBFAILLRUSNOTRECEIVEDDC12FMC1 2NZ12DAU1A lB 2A2BAFCS 1 2DADC1 2PZ12A4T1132

NOTE: SG 2 ASCBTest gives “SG 2 ASCBFAIL” “LRUSNOTRECEIVEDAFCS1 2“.

To proceed with SG Test, the operator presses the ‘PASSWor “FAILWline select key based on the outcome of the test. This advances thetest to the SG 3 ASCBTest, the option highlighted on the CASdisplay, as shown in Figure 4-4.18. To initiate the test the operatorpresses the line select key labeled ‘SELECT”. The resulting statusor error messages appear on the CASdisplay. A typical CM Displayfor the SG3ASCB Test is shown in Figure 4-4.19.

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F T

SG1. STRTUS TEST2. SOFTKRRE MOD LEVEL TEST3. S6 1 flSCBTEST4s S6 2 f3SCBTEST[5, S6 3 flSCBTEST]

A A A

AD-22824#

f\

S6 3 flSCBPRSS SG

flLLLRUS RECEIVED USE PflSS/FflILTO CONTINUEA A A

SG 3 ASCBTest OptionFigure 4-4.18

/

1AD-22825#

CAS Display for the SG 3 ASCBTestFigure 4-4.19

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4.2.2.2

The following is a 1ist of all messages that may appear as a resultof executing the SG 3 ASCBTest.

ASCB ASCBStatus with Respect to SGS

SG 3 ASCBPASSALL LRUSRECEIVEDSG 3 ASCBFAILLRUSNOTRECEIVEDDC12FWC1 2NZ12DAU1A lB 2A 2BAFCS 1 2DAOC12PZ12A/T 1 2SG12

NOTE: SG 3 ASCBTest gives “SG 3 ASCBFAIL” “LRUSNOTRECEIVEDAFCS1 2“.

Recommended Maintenance Action

The following is a list of messages associated with maintenance testand recommended action.

Status Test:

~ ACTION

SG(X) NOT IN TEST

NOTE: This message is followed by a secondary messagewhich indicates why

NOTONASCB 1.

$

INVALID;:

it is not in test.

VerifyA/CwiringJlA-3, 4, 11, 16, 17JIB-11, 50, 66.Check ASCBinterconnects.Replace symbol generator.

VerifyA/CwiringJIA-11, 16, 17.Replace symbol generator.

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MESSAGE ACTION

A/S ABOVE50 KNOTS A/S must be below 50 knots formaintenance test.

TEST SWITCHOFF 1. Verify maintenance test switch inputJIB-66.

2. Replace symbol generator.

WEIGHTONWHEELSOFF 1. Verify WOWinput JIB-54.2. Replace symbol generator.

SG(X) BITE FAIL Replace symbol generator.

ASCBFAILURE Replace symbol generator.

POWERSUPPLYFAIL Replace symbol generator.

DISCRETEFAILURE Replace symbol generator.

ARINCFAILURE Replace symbol generator.

E2 PROMFAILURE Replace symbol generator.

INTERLOCKFAIL Replace symbol generator.

ASCBTest:

MESSAGE ACTION

SG 1 ASCBFAIL List boxes not rcvd by SG1 via ASCB (Messageis normal in Phase II because of a problem inthe symbol generator software, which will befixed in the next symbol generator softwareupdate.)

SG 2 ASCBFAIL List boxes not rcvd by SG2 via ASCB (Messageis normal in Phase II because of a problem inthe symbol generator software, which will befixed in the next symbol generator softwareupdate.)

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MESSAGE ACTION

SG 3 ASCBFAIL List boxes not rcvd by SG3 via ASCB (Messageis normal in Phase II because of a problem inthe symbol generator software, which will befixed in the next symbol generator softwareupdate.)

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

S6

[1. STflTUS TESTIFILLTEST COMPLETE 2. SOFTHRRE MOD LEVEL TEST

3. SG 1 flSCBTEST4. SG 2 RSCB TEST5. SG 3 flSCBTEST

A A A1 . .

AD-22826#

SG Status Test OptionFigure-4-4.20

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4.2.2.3 Instructions

This section may be required if the operator is executing the SG Testin 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, initiates, and provides feedback for each testthrough the DC.

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

The following is a list of how to use the LRUTest Menu displayed onthe DC CRT for Maintenance Test (refer to Figure 4-4).

“PASS“

The operator presses this line select key if the equipment passes thecurrent test.

IIFAILI,

The operator presses this line select key if the equipment fails thecurrent test.

ll”p!l

The operator presses this line select key to back-step through thetest selections presented on the Crew Alerting System (CAS) display.

“SELECT”

The operator presses this line select key to initiate the task that ishighlighted on the CAS display.

,,D~MN1l

The operator presses this line select key to step through the testselections presented on the CAS display.

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‘RETURN”

The operator presses this line select key to return to the menu thathad been previously displayed on the DC. This is not used to selectthe options presented on the CASdisplay.

4.2.2.4 SG Maintenance Test ASCBData

~ ~ Bit Function -

27 15-4 Displayed Vertical Speed Two’s Compliment27 3-1 Spare27 0 F1ag Logic 1 = Valid27 (Or Maintenance Test)

4.2.3 Data Acquisition Unit 1 (DAU1)

4.2.3.1 General Operation

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

When the EDS Subsystem Test Main is displayed on the DC CRT, as shownin Figure 4-4.21, the operator initiates the DAUTest by pressing theline select key labeled “DAU1“. This produces the LRUTest Menu toappear on the DC CRT, as shown in Figure 4-4.22. The Status/SoftwareTest associated with each DAUwill show the active DAUSon ASCB, theDAUStransmitting valid data, verifies the correct identificationpins, and shows the internal software level of each DAU. There is nocorrelation between Software Mod Status in Maintenance Test and theMod Status shown externally on the LRU. The Software Mod Levels areused for reporting purposes.

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ee DU e

~ DC FWC e

B SG Df)U2 e

e

AD-22827#

EDS Subsystem Test MainFigure 4-4.21

~ ~

e UP a

e PASS SELECT e

e FAIL DOWN e

e ~

AD-22828#

LRUTest MenuFigure 4-4.22

The operator presses the line select key labeled “SELECT” to initiatethe DAUStatus/Software Test, the option highlighted on the CASdisplay, as shown in Figure 4-4.23. Status or error messages appearon the CAS display. Atypical CAS Display for the DAU1

Status/Software Test is shown in Figure 4-4.24.

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P >

DRU 1

Il. STfITUS/SOFTWfIRETESTI

AD-22829#

DAUStatus/Software Test OptionFigure 4-4.23

F >

OR(J IlllB ON flSCB DRU 1

Df+U lfllB VFILIDDRU lR lB ID PflSS

SOFTWFIRE MOD LEVELCPU R = (?106RSCB fl= 0104CPU B = 0106RSCB B = 0104 USE Pf3SS/FfIILTO CONTINUE

A A A. . v

AD-22830#

DAU1 Status/Software TestFigure 4-4.24

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DAUSTransmitting Valid Data

Verifies Correct Identification

The following is a list of all messages that may appear on the CASdisplay as a result of executing the DAUStatus/Software Test.

BUS Active DAUSon ASCB

DAU1A ONASCBDAUlB ON ASCB

VALID

DAUlAVALIDDAUlB VALID

ID

DAU1A ID PASSDAUlB ID PASS

MODLEVEL Software Revision Information

SOFTWAREMODLEVELCPU = XxxxASCBA = XXXX

SOFTWAREMODLEVELCPU = XxxxASCBB = XXXX

~: There is no correlation between Software Mod Level inMaintenance Test and the Mod Status shown externally onthe LRU.

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4.2.3.2 Recommended Maintenance Action

The following is a list of messages associated with maintenance testand recommended action.

Status/Software Test:

MESSAGE ACTION

DAU(X)NOTIN TEST

~: This message is followed by a secondary messagewhich indicates why it is not in test.

NOTONASCB 1. VerifyA/Cwiring JIA-4, 5, 103, 106,JIB-79.

2. Check ASCBinterconnects.3. Replace DAU.

INVALID 1. VerifyA/Cwiring JIA-4, 5, JIB-79.2. Replace DAU.

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

f- MFIINTENflNCETEST

DflU1FILL TEST COMPLETE [1. STflTUS/SOFTMflRETESTI

AD-22a31#

CAS DisplayFigure 4-4.25

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4.2.3.3 Instructions

This section may be required if the operator is executing the DAU1Test in any manner other than what has been described in the abovesection. If following the general operation section, proceed toSection 4.2.4.

The operator selects, initiates, and provides feedback for each testthrough the DC.

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

The following is a list of how to use the LRUTest Menu displayed onthe DC CRT for Maintenance Test (refer to Figure 4-4).

“PASS”

The operator presses this line select key if the equipment passes thecurrent test.

“FAIL”

The operator presses this line select key if the equipment fails thecurrent test.

ltupll

The operator presses this line select key to back-step through thetest selections presented on the Crew Alerting System (CAS) display.

“SELECT”

The operator presses this line select key to initiate the task that ishighlighted on the CAS display.

11~()”~1,

The operator presses this line select key to step through the testselections presented on the CAS display.

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“RETURN”

The operator presses this line select key to return to the menu thathad been previously displayed on the DC. This is not used to selectthe options presented on the CASdisplay.

4.2.4 Data Acquisition Unit 2 (DAU2) Test - The DAU2Test operates identicalto the DAU1. Refer to Section 4.2.3 for the required procedures.

4.2.4.1 DAUMaintenance Test ASCBData

~ ~ BIT FUNCTION FORMAT

19 3 Maintenance Test Enable Logic 1 = Enabled

4.2.5 Fault Warning Computer (FWC)

4.2.5.1 General Operation

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

tihen the EDS Subsystem Test Menu is displayed on the DC CRT, as shownin Figure 4-4.26, the operator initiates the FWCTest by pressing theline select key labeled ‘FWC”. This produces the LRUTest Menu onthe DC CRT as shown in Figure 4-4.27. The Status Test will show theactive FWCSon ASCB, the FWCStransmitting valid data, verify correctidentification pins, show the aircraft configuration information, andgive the Built-In-Test (BITE) Results. The Software Mod Level Testwill show internal software levels for each FWC. There is nocorrelation between Software Mod Status in Maintenance Test and theMod Status shown externally on the LRU. The Software Mod Levels areused for reporting purposes. The Checklist Test will show whether ornot a checklist installed and give the checksum of the installedchecklist. The Cross-Side ASCBTest will show theASCB status withrespect to the cross-side FWC(the one not selected on the sensormenu). The EEPROMBIT Test will show the percentage of memory usedfor Trend and Limit data as well as allowing the operator a means totest the EEPROMmemory.

~: Executing this test will shorten the life of the EEPROMmemory. This test may take over 5 minutes to execute.

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~

Q DU a

e DC FWC a

e SG DA(.J2 a

~ ~

AD-22E32#

EDS Subsystem Test MenuFigure 4-4.26

e ~

e UP e

e PRSS SELECT a

~ FAIL DOWN

~ a

AD-22833#

LRUTest MenuFigure 4-4.27

The operator presses the line select key labeled “SELECT” to initiatethe FWCStatus Test, the option highlighted on the CAS display, asshown in Figure 4-4.28. Status or error messages appear on the CASdisplay. A typical CASDisplay for the FWCStatus Test is shown inFigure 4-4.29.

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F )

FMC

Il. STflTUS TESTI2. SOFTMI?RE MOD LEVEL TEST3, CHECKLIST4. CROSS-SIDE flSCBTEST5. EEPROM BIT TEST

AD-22834#

FWCStatus Test OptionFigure 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 PINSFWC 1 PFISS

PINS = 10IUlFMC 2 PFISS

PINS = 10101 USE PflSS/Ff31LTOCONTINUEA A A

.AD-22835#

CAS Display for the FWCStatus TestFigure 4-4.29

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The following is a list of all messages that may appear on the CASdisplay as a result of executing the FWCStatus Test.

BUS Active FWCSon ASCB

FWC1 2 ONASCB

VALID FWCSTransmitting Valid Data

FWC1 2 VALID

ID Verifies Correct Identification

FWC1 ID PASSFWC2 ID PASS

PINS Aircraft Configuration Information

A/C ID PINS:FWCPASSFWCFAILPINS = 10101

Keying Pins 1 thru 5 134/C134JlA-12,13,14,15,16

Grid/Open Type A

12 13 14 15 16

G-IV Gnd Open Gnd Open Gnd

O = Open 1 = Gnd

BITE Built In Test Results

FWC1 BITE FAILFWC2 BITE FAILINTERLOCKFAILUREPOWERSUPPLYFAILDISCRETEFAILUREARINCFAILURECPU RAMFAILUREFWC1 BITE PASSFWC2 BITE PASS

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

f>

FifC

1. STRTUS TEST[2. SOFTWRRE MOD LEVEL TEST]30 CHECKLIST4. CROSS-SIDE flSCBTEST5, EEPROM BIT TEST

AD-22636#

FWCSoftware Mod Level Test OptionFigure 4-4.30

f \

FWC1 S/W: FliCCPU = 0113FISCB= 0110

FWC2 S/W:CPU= 0113

RSCB❑ 0110 USE PflSS/Ff31LTO CONTINUE

A A A.

AD-22837#

CAS Display for the FWCSoftware Mod Level TestFigure 4-4.31

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The following is a list of all messages that may appear as a result ofexecuting the FWCSoftware Mod Level Test.

MODLEVEL Software Revision Information

FWC1 S/W:FWC2 S/W:CPU = XxxxASCB= XXXX

~: There is no correlation between Software Mod Level Test andthe 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 thetest to the FWCChecklist, the option highlighted on the CAS display,as shown in Figure 4-4.32. To initiate the test the operator pressesthe line select key labeled “SELECT”. The resulting status or errormessages appear on the CAS display. Atypical CAS display for the FWCChecklist Test (without checklist installed) is shown in Figure 4-4.33.

FliC1. STFITUSTEST2. SOFTHRRE MOD LEVEL TEST131 CHECKLIST]4. CROSS-SIDE f+SCBTEST5. EEPROM BIT TEST

. v 1AD-22a3a#

FWCChecklist OptionFigure 4-4.32

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e -

CHECKLIST FIICFMC 1 UNFIVRILRBLE

FMC 2 UNt3VRILRBLE USE PflSS/F(+ILTO CONTINUE

A A A

AD-22839#

CAS Display for the FWCChecklist TestFigure 4-4.33

The following is a list of all messages that may appear as a result ofexecuting the FWCChecklist.

CKL Checklist Status

CHECKLISTFWCINSTALLEDFWCUNAVAILABLECKSUM= XXXX

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

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F T

FMC

1.STRTUS TEST2. SOFTIIRRE MOD LEVEL TEST3. CHECKLIST[4. CROSS-SIDE flSCBTESTI5. EEPROM BIT TEST

AD-22840#

I

e \

FHC 2 RSCB PtlSS FWCRLL LRUS RECEIVED

USE PRSS/FflIL TO CONTINUE

A A A

FWCCross-Side ASCBTest OptionFigure 4-4.34

.

CAS Display for the FWCCross-Side ASCBTestFigure 4-4.35

‘AD-22a41(Rl)#

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I

I

The following is a list of all messages that may appear as a result ofexecuting the FWCCross-Side ASCBTest.

ASCB ASCBStatus with Respect to FWC

FWC2 ASCBPASSFWC1 ASCBPASSFWC2 ASCBFAILFWC1 ASCBFAILALL LRUSRECEIVEDLRUSNOTRECEIVEDDAU1A lB 2A 2BSG123AFCS 1 2NZ12DC12IRS 1 2DADC1 2PZ12

To proceed with FWCTest, the operator presses theline select key based on the outcome of the test.

“PASS” or “FAIL”

This advances thetest to the FW~EEPROMBIT Test, the option highlighted on the CASdisplay, as shown in Figure 4-4.36. TO initiate the test theoperator presses the line select key labeled “SELECT”. The resultingstatus or error messages appear on the CAS display. A typical CASDisplay for the FWCE~PROM-BIT Test is shown in Figure 4-4.37.

FlfC

1. STFITUS TEST2. SOFTMRRE MOD LEVEL TEST3. CHECKLIST4. CROSS-SIDE IISCBTEST15. EEPROM BIT TESTI

AD-22842#

FWCEEPROMBIT Test OptionFigure 4-4.36

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I MfHNTENRNCE TEST ‘

FHC 1 EEPROM FiiCZ FULL

FliC2 EEPROM IIFIRNINGEXECUTING THIS TEST MILLZ FULL SHORTEN THE LIFE OF THE

EEPROM MEMORY

NOTE THIS TEST TflKES OVER5 MINUTES TO EXECUTE

PRESS SELECT TO CONTINUE OR PFISS/FFIILTO RETURN TO MRIN MENU

I

. . .AD-22a43#

FWCEEPROMBIT TestFigure 4-4.37

4.2.5.2 Recommended Maintenance Action

The following is a list of messages associated with maintenance testand recommended action.

Status Test:

!kwuE Action

FWCNOT IN TEST

NOTE: This message is followed by a secondary message whichindicates why it is not in test.

NOTONASCB 1. VerifyA/Cwiring JIA-5, 6, 7,63, 65, 66, 85.

2. Replace fault warning computer.

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Status Test (cent):

-Action

TEST SWITCHOFF 1. Verify Maintenance Test Switchinput JIA-85.

2. Replace fault warning computer.

WEIGHTONWHEELSOFF 1. Verify WOWinput JIA-63.

FWC(X) BITE FAIL Replace Fault Warning Computer.

INTERLOCKFAILURE Replace Fault Warning Computer.

POWERSUPPLYFAIL Replace Fault Warning Computer.

DISCRETEFAILURE Replace Fault Warning Computer.

ARINC FAILURE Replace Fault Warning Computer.

CPU RAMFAILURE Replace Fault Warning Computer.

FWC(X) FAIL CheckA/C ID Pins JIA-12 thru JIA-16.

Checklist Test:

- Action

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

ASCBTest:

- Action

FWC1 ASCBFAIL List boxes not rcvd by FWC1 via ASCB.Check ASCB interconnects.

FWC2 ASCBFAIL List boxes not rcvd by FWC2 via ASCB.Check ASCBinterconnects.

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To proceed with FWCTest, the operator presses the “PASS” or “FAIL”line select key based on the outcome of the test. This advances thetest to the FWCStatus Test, the option highlighted on the CASdisplay, as shown in Figure 4-4.38. To return to the EDS SubsystemMenu, the operator presses the line select key labeled “RETURN”. Themessage on the CASdisplay prompts the operator to make a selection.

FMC

il. STRTUS TEST~FILLTEST COMPLETE 2. SOFTliFIREMOD LEVEL TEST

3. CHECKLIST4. CROSS-SIDE FISCBTEST5. EEPROM BIT TEST

A A A. . T

AD-22844#

FWCStatus Test OptionFigure 4-4.38

4.2.5.3 Instructions

This section may be required if the operator is executing the FWCTestin 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, initiates, and provides feedback for each testthrough the DC.

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

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The following is a list of how to use the LRUTest Menu displayed onthe DC CRT for Maintenance Test (refer to Figure 4-4).

“PASS”

The operator presses this line select key if the equipment passes thecurrent test.

“FAIL”

The operator presses this line select key if the equipment fails thecurrent test.

IllJpll

The operator presses this line select key to back-step through thetest selections presented on the Crew Alerting System (CAS) display.

“SELECT”

The operator presses this line select key to initiate the task thatis highlighted on the CAS display.

“DOWN”

The operator presses this line select key to step through the testselections presented on the CAS display.

“RETURN”

The operator presses this line select key to return to the menu thathad been previously displayed on the DC. This is not used to selectthe options presented on the CAS display.

4.2.5.4 FWCMaintenance Test ASCBData

~ ~ BIT FUNCTION FORMAT

63 15-0 MAINTENANCETEST64 15-0 MAINTENANCETEST

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4.2.6 Display Unit (DU)

4.2.6.1 General Operation

The operator selects, initiates, and provides feedback for the Dis~laYUnit (DU) Test through the DC.

When the EDS Subsystem Test Main isin Figure 4-4.39, the operator init.line select key labeled “DU”. ThisDC CRT, as shown in Figure 4-4.40.with the Display Unit. The Status -Overheat status of each DU. The Pi”wraparound data from DU1 and DU2 toassociated with either DU1 or DU2.429 wrar)around data from DU3 and DU~associated with’ either DU3 or DU4.

.-

displayed on the DC CRT, as shownates the DUTest by pressing theproduces the LRUTest Menu on theThere are four tests associatedest will show the Reversionary andot DUSTest uses the ARINC429show the Error and Status DataThe EICAS DUSTest uses the ARINC

to show the Error and Status DataThe Copilot DUSTest uses the

ARINC429 wraparound data from DU5 or DU6 to show the Error and StatusData associated with either DU5 or DU6.

o-l(3

EDS Subsystem Test MainFigure 4-4.39

AD-22845#

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=--i

EF

/ ~

mlUP

Pf+ss SELECT

FAIL DO14N

RETURN

l-oEl

AD-22646#

LRUTest MenuFigure 4-4.40

Thethe

operator presses the line select key labeled “SELECT” to initiateDU Status Test, the option highlighted on the CAS display, as

shown in Figure 4-4.41. Status or error messages appear on the CASdisplay. A typical CAS Display for the DU Status Test is shown inFigure-4-4.42;”

. .

.AD-22647#

DUStatus Test OptionFigure 4-4.41

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/MflINTENFINCETEST

NO DU IN REVERSION DU

NO DU OVERHEFITED I USE PRSS/FRIL TO CONTINUE

. . .AD-22848#

Status or Error Messages on CAS DisplayFigure 4-4.42

The following is a list of all messages that may appear on the CASdisplay as a result of executing the DU Status Test.

REV Indicates Reversionary Status

DU REVERSION:DU 123456NO DU IN REVERSION

OVERHEAT Indicates Overheat Status

DUOVERHEAT:DU 123456NO DUOVERHEATED

To proceed with DUTest, the operator presses the “PASS” or “FAIL”line select key based on the outcome of the test. This advances thetest to the Pilot DUSTest, the option highlighted on the CAS display,as shown in Figure 4-4.43. To initiate the test the operator pressesthe line select key labeled “SELECT”. The resulting status or errormessages appear on the CAS display. A typical CAS Display for thePilot DUSTest is shown in Figure 4-4.44.

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AD-22849#

Pilot DUSTestFigure 4-4.43

DU 1 VflLIDflRINC DU

DU 2 VBLID flRINC USE PRSS/FRIL TO CONTINUE

A A A

AD-22850#

CAS Display for the Pilot DUSTestFigure 4-4.44

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The following is a list of all messages that may appear as a result of~xecuting the Pilot DUSTest.

ARINC Error Status and Data Associated withPilot DUS

DU 1 ARINCFAILUREDU 2 ARINCFAILURELABEL350 ERRORLABEL351 ERRORLABEL352 ERRORLABEL353 ERRORDATA= XXXXXLABEL356 ERRORLABEL357 ERRORDATA- XXXXXDU 1 VALIDARINCDU 2 VALIDARINCNOTRECEIVINGDU 1 ARINCNOTRECEIVINGDU 2ARINC

To proceed with DUTest, the operator presses the “PASS” or “FAIL”line select key based on the outcome of the test. This advances thetest to the EICAS DUSTest option, highlighted on the CAS display, asshown in Figure 4-4.45. To initiate the test the opc~ator presses theline select key labeled “SELECT”. The resulting status or errormessages appear on the CASdisplay. A typical CAS Display for theEICAS DUSTest is shown in Figure 4-4.46.

7MflINTENflNCETEST

DU

1. STfiTUSTEST2. PILOT DUS13. EICFISDUSI4. COPILOTDUS

AD-22851 #

EICAS DUSTest OptionFigure 4-4.45

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DU 3 VflLIDFIRINC DU

DU 4 VflLIDflRINC USE PRSS/FRILTOCONTINUE

b A A A

AD-22852#

CAS Display for the EICAS DUSTestFigure 4-4.46

The following is a list of all messages that may appear as a resultof executing the EICAS DUSTest.

ARINC Error Status and Data Associated withEICAS DUS

DU 3 ARINCFAILUREDU 4ARINC FAILURELABEL350 ERRORLABEL351 ERRORLABEL352 ERRORLABEL353 ERRORDATA= XXXXXLABEL356 ERRORLABEL357 ERRORDATA- XXXXXDU 3 VALIDARINCDU 4 VALIDARINCNOTRECEIVINGDU3 ARINCNOTRECEIVINGDU 4 ARINC

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To proceed with DUTest, the operator presses the “PASS” or “FAIL”line select key based on the outcome of the test. This advances thetest to the Copilot DUSTest, the option highlighted on the CASdisplay, as shown in Figure 4-4.47. To initiate the test the operatorpresses the line select key labeled “SELECT”. The resulting status orerror messaaes smear on the CAS display. A typical CAS Display forthe Copilot”DUs Test is shown in Figure 4-4.48.

.-

V>

AD-2285W

Copilot DUSTest OptionFigure 4-4.47

/ T

DU5 VRLIDflRINC DU

DU 6 VFILIDFIRINC USE PRSS/FRIL TO CONTINUE

A A A. . .

AD-22854#

CAS Display for the Copilot DUSTestFigure 4-4.48

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The following is a list of all messages that may appear as a resultof executing the Copilots OUSTEST.

ARINC

DU 5 ARINCFAILUREDU 6 ARINCFAILURELABEL350 ERRORLABEL351 ERRORLABEL352 ERRORLABEL353 ERRORDATA= XXXXXLABEL356 ERRORLABEL357 ERRORDATA- XxxxxDU 5 VALIDARINCDU 6 VALIDARINCNOTRECEIVINGDU5NOTRECEIVINGDU6

To proceed with DUTest,line select key based on

Error Status and Data Associated withCopilot DUS

ARINCARINC

the operator presses the “PASS” or “FAIL”the outcome of the test. This advances the

test to the DU-Status Test, the option highlighted on the CAS display,as shown in Figure 4-4.49. To return to the EDS Subsystem Menu, theoperator presses the line select key labeled “RETURN”. The operatorpresses the return key a second time to return to the System TestMenu.

DU

[1. STFITUS TESTIRLL TEST COMPLETE 2. PILOT DUS

3, EICflS DUS4. COPILOTDUS

AD-22855#

DUStatus Test OptionFigure 4-4.49

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4.2.6.2 Recommended Maintenance Action

The following is a list of messages associated with maintenance testand recommended action.

Status Test:

- Action

DUOVERHEAT Insure DU Fan C.B.’S are in.;: Insure DU fans are operative.3. Check DU filter.4. CheckA/C wiring fromDU J1-65 to FWC

JIA-34.5. Replace DU.6. Replace FWC.

DU(X) IN REVERSION 1. Verify reversionary switch wiring.Correct J1-37, 22, 87, 88.

2. Replace DU.

Pilot DUTest:

- Action

NOTRECEIVINGDU 1(2) Check DUwraparound.ARINC ;: VerifyA/CwiringJl-94, 66, 79, 101,

102, 103, 104, 105, 106, 38, 39 andJ1-35, 36, 19, 33 if in reversionarymode.

3. Replace DU.

EICAS DUTest:

- Action

NOTRECEIVING 1. Check DUwraparound.DU3(4) ARINC 2. Verify A/C wiring from Rev Control

panel P9-G, f, H, j, or DUwiringJ1-66, 79, 94, 101 thru 106.

3. Replace DU.

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Copilot DUTest:

Messacie Action

NOTRECEIVING 1. Check DUwraparound.DU 5(6) ARINC 2. Verify A/C wiring from Rev Control

panel A, P1O-K, f, h, j, P9-j, orDUwiring J1-66, 79, 94, 101 thru 106.

3. Replace DU.

Pilot/EICAS/Copilot DUTests:

Messacae Action

DU(X) ARINCFAILURE Check DUwraparound J1-66 & 79 to faultwarning computers. Move DUto anotherposition. If message follows DU, replacethe DU. If message does not follow, thendecode the 429 wraparound data.

NOTE: This message is followed by label error messages.

LABEL350 ERROR Activity Counter

LABEL351 ERROR Internal DU Failure

LABEL352 ERROR Internal DU Failure

LABEL353 ERROR Internal DU FailureDATA= XXXXX

LABEL356 ERROR CGS Fatal Error Code (For Data 50100Verify A/C wiring J1-38, 39, 58).Replace DU.

LABEL357 ERROR BIT Fatal Error Code/Replace DU.DATA= XXXXX

DU(X) IN REVERSION Check DU Reversionary Miring.

4.2.6.3 Instructions

This section may be required if the operator is executing the DUTestin any manner other than what has been described in the abovesection. If following the general operation section, proceed toSection 4.3.

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The operator selects, initiates, and provides feedback for each testthrough the DC.

Based on the information presented on the CASdisplay, the operatordetermines if the equipment passed or failed the test, and pressesthe appropriate line select key on the DC. This step is requiredbefore the Maintenance Test will proceed. In addition, the operatormay be required to select an option associated with a test or returnto the previous menu. To do this, the operator presses theappropriate line select key on the DC.

The following is a list of how to use the LRUTest Menu displayed onthe DC CRT for Maintenance Test (refer to Figure 4-4).

“PASS”

The operator presses this line select key if the equipment passes thecurrent test.

“FAIL”

The operator presses this line select key if the equipment fails thecurrent test.

“up,,

The operator presses this line select key to back-step through thetest selections presented on the Crew Alerting System (CAS) display.

“SELECT”

The operator presses this line select key to initiate the task thatis highlighted on the CASdisplay.

‘DOWNn

The operator presses this line select key to step through the testselections presented on the CASdisplay.

“RETURNn

The operator presses this line select key to return to the menu thathad been previously displayed on the DC. This is not used to selectthe options presented on the CASdisplay.

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4.2.6.4 DUARINC429 Wraparound Data

LABELBIT BIT FUNCTION NOTE----- I l----------------------------------------------l---------351 “ “BFAILO351 15 PERSONALITYPROMCRCFAILURE351 14 CHARACTERPROMCRC FAILURE351 13 NORMALPROMCRC FAILURE351 12 SYSTEMPROMCRC FAILURE

,351 11 DEFLECTIONAMPLIFIERTEMPERATUREFAILURE351 10 HIGHVOLTAGEPWERSUPPLYFAILURE351 9 429 SERIAL OUTPUTBUSTRANSMISSIONFAILURE351 8 POT EXCITATIONFAILURE351 7 DISPLAYLIGHTSENSORFAILURE351 6 VECTORGENERATORFAILURE351 5 VECTORGENERATORTIMERFAILURE351 4 INPUT DISCRETELATCH351 3 A/D CONVERTERFAILURE351 2 HSB CIRCUIT351 1 SCC CHIP351 0 BIT FAILUREMATRIXSUMMARYBIT351----- I l----------------------------------------------l---------352 BFAIL1352 15-14 SPARE352 13 SP TRANSITIONRAMLOCATIONFAILURE352 12 SP TRANSITIONRAMADDRESSFAILURE352 11 RASTERTRANSITIONRAMLOCATIONFAILURE352 10 RASTERTRANSITION-RAMADDRESSFAILURE352 9 SP PROGRAMRAMLOCATIONFAILURE352 8 SP PROGRAMRAMADDRESSFAILURE352 7 RASTERPROGRAMRAMLOCATIONFAILURE352 6 RASTERPROGRAMRAMADDRESSFAILURE352 5 CORERAMLOCATIONFAILURE352 4 CORERAMADDRESSFAILURE352 3 VG RAMLOCATIONFAILURE352 2 VG RAMADDRESSFAILURE352 1 DMARAMLOCATIONFAILURE352 0 DMARAMADDRESSFAILURE

I l----------------------------------------------l----------------353 BFAIL2353 15-6 SPARE353 5 FLIGHT/DEBUGMODEPARITYFAILURE353 4 DUADDRESSFAILURE353 3 FOCUSEND-AROUNDFAILURE353 2 PHOSPHORPROTECTFAILURE353 1 CRT FILAMENTCURRENTLOW353 0 CRT FILAMENTCURRENTHIGH

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LABELBIT BIT FUNCTION NOTE----- I l----------------------------------------------l-------350 BFAIL3350 15-4 SPARE350 3 REMOTELIGHTSENSORFAILURE350 2 ALTERNATELIGHTSENSORFAILURE350 1 BALANCEPOT FAILURE350 0 BRIGHTNESSPOT FAILURE----- I l~~+-;~+~~-~~~~;-------------------------------l-----357357 15-3 SPARE357 2-o ERRORCODE = DUADDRESSFAILURE357 ; = VECTORGENERATORFAILURE357 3 = DU PROGRAMPROMFAILURE357 4 = DU RAMFAILURE----- I l~;;-~~~~~-~~;~~-------------------------------l-------356356 CODESDEFINEDIN CGS PROGRAMMERSMANUAL-CONTACTHONEYWELL----- I l----------------------------------------------l-----

Subject: ARINCWrap-around Label 356

Label 356 will only be transmitted in the event a fatal error is detected bythe Core Graphics System. The label is transmitted just prior to the DUresetting, indicated by the display of the red “X”. The following is adescription of the information contained in the bits associated with label356.

32 28 24 20 16 12 09- - -- - - - - ---- - -------- -- - -- --- - -- - -- ----- - -- - ---- - ---- - - -- ------ ---- -- --

IXxxx Xxxx Xxxxx xxx Xxxx Xxxx

don’t care CGSerror code BCD object number BCDExample:

0110 0101 0000 0010 0000 0011

don’t care 5 0 2 0 3

i.e., timeout of object number 3

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4.3 Sensor Test

When the System Test Menu is displayed on the Display Controller (DC)Cathode Ray Tube (CRT) as shown in Figure 4-5, the operator initiates theSensor Test by pressing the line select key labeled “SENSORS”. Thisproduces the Sensor Subsystem Menu to appear on the DC CRT as shown inFigure 4-6. The CAS Display will be as shown in Figure 4-6.1.

--i

IM131NTENANCE TEST{

EDS

SYSTEM CHECK

AFGCS

SENSORS

FMS/PMS

SUMMARY

RETURN

System Test MenuFigure 4-5

WEATHER RADAR DADC

RADIO ALT RADIOS t

AD-22856#

Sensor Subsystem MenuFigure 4-6

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AD-22859#

CAS DisplayFigure 4-6.1

The operator selects one of the subsystem tests or returns to theSystem Test Menu by pressing the appropriate line select key.Presently, only the IRS and the DADCtests exist. Each of the testsare described in the following sections.

4.3.1 Inertial Reference System (IRS)

4.3.1.1 General Operation

The operator selects, initiates, and provides feedback for theInertial Reference System (IRS) Test through the DC.

When the Sensor Subsystem Menu is displayed on the DC CRT, theoperator initiates the IRS Test by pressing the line select keylabeled “IRS”. This produces the Line Replaceable Unit (LRU) TestMenu to appear on the DC CRT as shown in Figure 4-7. There are twotests associated with the Inertial Reference Unit. The Status Testwill show the active IRSS on ASCB, the IRSS transmitting valid data,and the current mode of the IRSS. The Fault Summary will show theBuilt-In-Test results from the IRSS.

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d(3

wQ Q

Thethe

mlUP

PASS SELECT

FAIL DOWN

RETURN

\

AD-228S8#

LRUTest MenuFigure 4-7

oDerator messes the line select key labeled “SELECT” to initiateIRS Statu; Test, the option highlighted on the CAS display

shown in Figure 4-7.1. The resulting status or error messagesdisplayed on the Crew Alerting System (CAS) Display. Atypica-Display for the IRS Status Test is shown in Figure 4-7.2.

asare

CAS

Ao-22880#

IRS Status Test OptionFigure 4-7.1

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MflINTENflNCETEST

IRS 1 2 ON RSCB IRS

IRS 1 2 VfiLID

IRS MODES:IRS 1 N(3VIRS 2 NflV USEPfISS/FfIILTO CONTINUE

. .AD-2z861#

CAS Display for the IRS Status TestFigure 4-7.2

The following is an explanation of all messages that may appear on theCASdisplay as a result of executing the IRS Status Test.

BUS Active IRSS on ASCB

IRS 1 2 ONASCBIRS 1 2 NOTIN TESTNOTONASCB

VALID IRSS Transmitting Valid Data

IRS 1 2 VALID

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MODE Indicates IRS Operational Mode

IRS MODESIRS 1 ALIGNIRS 1 ATTITUDEIRS 1 NAVIRS 1 UNKNOWNIRS 2ALIGNIRS 2 ATTITUDEIRS 2 NAVIRS 2 UNKNOWN

To proceed with the IRS Test, the operator presses the “PASS” or“FAIL” line select key based on the outcome of the test. Thisadvances the test to the IRS Fault Sunnnary, the option highlighted onthe CAS display, as shown in Figure 4-7.3. To initiate the test, theoperator presses the line select key labeled “SELECT”. The resultingstatus and error messages are displayed on the CAS display. A typicalCAS Display for the IRS Fault Summary is shown in Figure 4-7.4.

AD-22862#

IRS Fault Summary OptionFigure 4-7.3

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NO IRS 1 FRULTS IRS

NO IRS 2 FRULTS USE PflSS/FflIL TO CONTINUEA A A

.AD-22863#

CAS Display for the IRS Fault SummaryFigure 4-7.4

The followinq is a list of all messages that may appear as a result ofexecuting th; IRS Fault Summary.

FAULT Built

IRS 1 FAULTS:IRS 2 FAULTS:POWERSUPPLYSENSORLSICMEMORYACCELRESIDUALTEMPSENSORWATCHDOGDISCRECPUA/D ORNO IRSNO IRS

E 1/0

MUX1 FAULTS2 FAULTS

In Test Results

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4.3.1.2 Recommended Maintenance Action

The following is a list of messages associated with maintenance testand recommended action.

Status Test:

- Action

IRS(X) NOT IN TEST VerifyA/Cwiring JIB-H1, H2, Kl, K2,NOTONASCB JIC-1, 5, 4, 10, 7, 8.

IRS(X) UNKNOWN Replace IRS.

Fault Test:

IRS 1 2 FAULTS:

POWERSUPPLY Replace IRS.

SENSORYLSIC Replace IRS.

MEMORY Replace IRS.

ACCELRESIDUAL Replace IRS.

TEMPSENSOR Replace IRS.

WATCHDOG Replace IRS.

DISCRETE1/0 Replace IRS.

CPU Replace IRS.

A/D ORMUX Replace IRS.

To proceed with the IRS Test, the operator presses the “PASS” or“FAIL” line select key based on the outcome of the test. Thisadvances the test to the IRS Status Test, the option highlighted onthe CAS display, as shown in Figure 4-7.5. To return to the SensorSubsystem Menu, the operator presses the line select key labeled“RETURN”. The message on the CASdisplay prompts the operator to makea selection, as shown in Figure 4-7.6.

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IRS

[1.STFITUSTEST]FILLTEST COMPLETE 2. FFIULTSUMMRRY

AD-22884#

IRS Status Test OptionFigure 4-7.5

AD-2288s#

CAS Display PromptFigure 4-7.6

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4.3.2 Digital Air Data Computer (DADC)

4.3.2.1 General Operation

The operator selects, initiates, and provides feedback for the DigitalAir Data Computer (DADC)Test through the DC.

When the Sensor Subsystem Menu is displayed on the DC CRT, as shown inFigure 4-7.7, the operator initiates the DADCTest by pressing theline select key labeled “DADC”. This produces the LRUTest Menu toappear on the DC CRT, as shown in Figure 4-7.8. There are five testsassociated with the Digital Air Data Computer. The Status Test willshow the active DADCSon ASCB, the DADCStransmitting valid data, theASCBstatus with respect to DADCS,and the configuration pininformation. The Configuration Test will show the DADCConfigurationinformation and the software revision information. There is nocorrelation between Software Mod Status in Maintenance Test and theMod Status shown externally on the LRU. The Software Mod Levels areused for reporting purposes. The Fault Summary Test will show theBuilt-In-Test (BITE) results of each DADC. The DADCOutput Tests, onefor each DADC,will check the following outputs: AOAIndex - Top,Middle, and Bottom, Altitude Alert annunciator and horn, and the VMOWarning horn.

d(3

~ ..-22866,

Sensor Subsystem MenuFigure 4-7.7

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d(3 mUP

PASS SELECT

FAIL DOWN

RETURN PEl

LRUTest MenuFigure 4-7.8

The operator presses the line select key labeled “SELECT”to initiatethe DADCStatus Test, the option highlighted on the CAS display, asshown in Figure 4-7.9. The resulting status or error messages aredisplayed on the CASdisplay. A typical CASDisplay for DADCStatusTest is shown in Figure 4-7.10.

MfHNTENflNCE TEST

DflDC -

Il. STFITUSTESTI2. CONFIGURATION TEST30 FflULTSUMMRRY4. DRDC1 OUTPUTTEST5. DRDC2 OUTPUTTEST

.AD-22868#

DADCStatus Test OptionFigure 4-7.9

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DFIDC1 2 ON FISCB DflDC

DRDC1 2 VfILID

DFIDC1 13SCBPRSSDFIDC2 IISCBPfiSS

H/C ID PINS:DRDC 1 PRSS

PINS = 010110

DflDC2 PFISSPINS = 010110 USE PflSS/FflIL TOCONTINUE

A A A

AD-22869#

CAS Display for DADCStatus TestFigure 4-7.10

The following is a list of all the possible messages that may appearon the CASdisplay as a result of executing the DADCStatus Test.

BUS Active DADCSon ASCB

DADC1 2 ONASCBDADC1 2 NOTIN TESTNOTONASCBDADC1 2 NOTIN TESTINVALID

VALID DAOCSTransmitting Valid Data

DAOC1 2 VALID

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ASCB ASCBStatus with Respect to DADCS

DADC1 ASCBFAILDADC2 ASCBFAILDADC2 NOTRCVDDADC1 NOTRCVDDC NOTRECEIVEDFWCNOTRECEIVEDDADC1 ASCBPASSDADC2 ASCBPASS

ID Aircraft Configuration Information

A/C ID PINSDADC1 PASSDADC2 PASSDADC1 FAILDADC2 FAILPINS = 010110

Aircraft ID 9/C9JlA-101,102,103,104,105,107

Grid/Open Type A

101 102 103 104 105 106

G-IV Application Gnd Open Open Gnd Open Gnd

CAAApplication Gnd Gnd Gnd Gnd Open Gnd

NOTE: For CAAAircraft with -864 DADCPINS = 010000.

To proceed with the DADCTest, the operator presses the “PASS” or‘FAILn line select key based on the outcome of the test. Thisadvances the test to the DADCConfiguration Test, the optionhighlighted on the CAS display, as shown in Figure 4-7.11. Toinitiate the test, the operator presses the line select key labeled“SELECT”. The resulting status and error messages are displayed onthe CASdisplay. A typical CAS Display for the DADCConfigurationTest is shown in Figure 4-7.12.

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● Y

DRDC

1. STFITUS TEST12. CONFIGURfiTION TEST]3. FRULT SUMMflRY4. DFIDC1 OUTPUTTEST5. DRDC 2 OUTPUT TEST

AD-22870#

DADCConfiguration Test OptionFigure 4-7.11

Y

DFIDC1 CONFIG DFIDCPILOT/MflSTER

DflDC2 CONFIGCOPILOT/SLflVE

MODSTRTUSDflDC1 = BBDflDC2 = BB USE PRSS/FRILTOCONTINUE

A A AT

AD-22871#

CAS Display for the DADCConfiguration TestFigure 4-7.12

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The following is a list of all messages that may appear as a resultof executing the DADCConfiguration Test. The operator isresponsible for verifying that the configuration is correct.

CONFIGURATION DADCConfiguration Information

DADC1 CONFIG:DADC2 CONFIG:PILOT SLAVEPILOT MASTERCOPILOTSLAVECOPILOTMASTERSSEC DISABLEDBARODISABLEDSELF TEST ENABLEDMISMATCHDETECTED

MODLEVEL Software Revision Information

MODSTATUS: NOTE: There is no correlation betweenDADC1 Software Mod Level Test and theDADC2 Mod Status shown externally on the

LRU.

To proceed with the DADCTest, the operator presses the “PASS” or“FAILn line select key based on the outcome of the test. Thisadvances the test to the DADCFault Sunmnary, the option highlightedon the CASdisplay, as shown in Figure 4-7.13. To initiate the test,the operator presses the line select key labeled “SELECT”. Theresulting status and error messages are displayed on the CAS display.A typical CAS Display for the DADCFault Summary Test is shown inFigure 4-7.14.

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7MfHNTENRNCE TEST

DRDC

1. STFITUS TEST2. CONFIGURFITION TEST[3. FRULT SUMMRRYI4. DRDC 1 OUTPUT TEST5. DRDC 2 OUTPUT TEST

AD-22872#

DADCFault Summary OptionFigure 4-7.13

7MfHNTENflNCE TEST

DflDC1 BITE FflIL DRDCflLTSELECT

DRDC 2 BITE FRILRLT SELECT USE PRSS/FRIL TO CONTINUE

1A A II

AD-22873#

CAS Display for the DADCFault Summary TestFigure 4-7.14

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The following is a list of all messages that may appear as a resultof executing the DADCFault Summary.

BITE Built In Test Results

DADC1 BITE FAILDADC2 BITE FAILPILOT-STATICD/A-F/D CONVERTERD/A CONVERTERF/D CONVERTER5VDCMONITORROMCHECKSUMCABINPRESS RATIOALT SELECTBAROCONVERSIONTEMPPROBEAOAPOTFLAPSDADC1 BITE PASSDADC2 BITE PASS

~: “DADC1 BITE FAIL” and “DADC2 BITE FAIL” will be annunciateduntil the Altitude Preselect knob is rotated.

To proceed with the DADCTest, the operator presses the “PASS” or“FAIL” line select key based on the outcome of the test. Thisadvances the test to the DADC1 Output Test, the option highlightedon the CASdisplay, as shown in Figure 4-7.15. To initiate the test,the operator presses the line select key labeled “SELECT”. The CASdisplay will be as shown in Figure 4-8. The operator is prompted totest various discrete outputs associated with the DADC. The operatorpresses the line select key labeled “SELECT”to activate the outputand enters pass or fail for each output to advance. When the lastoutput is tested, the test advances to the return to main menuoption. The operator presses the line select key labeled “SELECT”toadvance the test to the DADC2 Output Test.

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/ Y

AD-22874#

DADC1 Output Test OptionFigure 4-7.15

e >

DRDC 1 OUTPUT TEST DflDC

11.flOFIINDEXTOPI2. FIOIIINDEX MIDDLE30 FIORINDEX BOTTOM4. FILTITUDE RLERT flNN5. RLTITUDE FILERTHORN6. VMO tiflRNINGHORN7. RETURN TO MflINMENU

A A A. .

CAS DisplayFigure 4-8

,AD-22875#

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To proceed with the DADCTest, the operator presses the line selectkey labeled “SELECT” to initiate the DADC2 Output Test, the optionhighlighted on the CAS display. The CASdisplay will be similar tothat shown in Figure 4-8, only “DADC2 OUTPUTTEST” will beannunciated on the left. The operator is prompted to test variousdiscrete outputs associated with the DAOC. The operator presses theline select key labeled “SELECT”to activate the output and enterspass or fail for each output to advance. When the last output istested, the test advances to the return to main menu option. Theoperator presses the line select key labeled “SELECT” to return thetest to the DADCStatus Test, as shown in Figure 4-8.1. To return tothe Sensor Subsystem Menu, the operator presses the line select keylabeled “RETURN”. The operator presses the return key a second timeto return to the System Test Menu.

DRDC[It STFITUSTESTI

FILLTEST COMPLETE 2. CONFIGURATION TEST3, FllULTSUMMRRY4. DFIDC 1 OUTPUT TEST5. DRDC 2 OUTPUT TEST

A A A

AD-22876#

DADCStatus TestFigure 4-8.1

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4.3.2.2 Recommended Maintenance Action

The following is a list of messages associated with maintenance testand recommended action.

Status Test:

Messaqe Action

DADC(X)NOTIN TEST 1. VerifyA/CwiringJIA-l, 2, 3, 4,NOTON ASCB 11, 12.

2. Replace DADC.

NOTE“ To test DADC#1 when performing GMTfrom DC #2, DADC#2 must be—.valid. To test DADC#2 when performing GMTfrom DC #1, DADC#1must be valid.

DADC1 ASCBFAIL List of boxes not rcvd by DADC1 via ASCB.Check ASCB.

DADC2 ASCBFAIL List of boxes not rcvd by DADC2 via ASCB.Check ASCB.

NOTE“ The “DADCASCBFAIL” message will be followed by one or more of—.the following three messages.

DADC1(2) NOTRCVD 1. VerifyA/CwiringJIA-l, 2, 3, 4, 11, 12,2. Check ASCBinterconnects.3. Replace DADC.

DC NOTRECEIVED 1. Check on-side display controller breakers.2. Check ASCBinterconnects.3. Verify power to DC JIA, B, V, W.4. Replace DADC/DC.

FWCNOTRECEIVED 1. Check on-side fault warning computerbrkrs (Verify wiring JIA-11, 12).Check ASCB.

;: Replace DADC/FWC.

DADC(X)NOT IN TEST 1. Verify power to display controller,J1-A, B, V, W.

2. Check ASCBinterconnects.

DADC1 FAIL Check A/C ID pins J1A-101 thru J1A-106.

DADC2 FAIL CheckA/C ID pins J1A-101 thru J1A-106.

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Configuration Test:

!!!SSWE

SSEC DISABLED

BARODISABLED

SELF TEST ENABLED

MISMATCHDETECTED

Fault Summary Test:

Messaae

DADC1 BITE FAILDADC2 BITE FAILPITOT-STATICD/A CONVERTERF/D CONVERTER5VDCMONITORROMCHECKSUM

CABINPRESS RATIO

DADC(X)BITE FAILALT SELECT

Action

1. Check SSEC disable pin JIA-39.2. Check for stuck button on front of

unit/replace DADC.

Check baro disable pin JIA-38/replace DADC.

Check air data self test pin JIA-52/replaceDADC.

Ensure correct part number DADCSareinstalled. Message logged when softwarelevels are different between DADC1 and DADC2. (e.g., Mod BL installed on one side and adifferent Mod level on the other side.)

Action

Replace DADC.Replace DADC.Replace DADC.Replace DADC.Replace DADC.Replace DADC.Replace DADC.

Check for the following from the cabinpress system:JIA-62 Cabin Press (Ref)JIA-63 Cabin Press Ratio(Wiper) Check for shorts on this output.JIA-64 Cabin Press LoJIA-66 Cabin Press RatioValid (VALID=GND)

1. Rotate Alt Select Knob.2. Check for the following

from the guidance panel:J1B-103 Altitude Preselect Tach-HIJ1B-104 Altitude Preselect Tach-LO

3. Check for the following from the flightguidance computer: JIA-93 Alerter Selectdisc.

4. Check DADCwiring J1A-101, 106.

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Fault Summary Test (cent):

Mssi!9e Action

DADC(X)BIT FAIL Check for the following from the displayBAROCONVERSION controller.

JIA-35 baro pot excitation (-10 V)JIA-36 baro pot wiper.JIA-37 baro pot common

DADC(X)BIT FAIL Check for the following from the tempTEMPPROBE probe:

JIA-72 Temperature Probe-HIJIA-73 Temperature Probe-LO

DADC(X)BITE FAIL Check for the following from theAOA Probe:AOAPOT JIB-53 AOARef (+10 Vdc)

JIB-54 AOARef CommonJIB-60 AOASig (Wiper)

DADC(X)BITE FAIL Check for the following inputs from theFLAPS flap handle switch:

Gnd on JIA-55 for O deg FlapsGnd on JIA-56 for 10 deg FlapsGnd on JIA-57 for 20 deg FlapsGnd on JIA-58 for 39 deg Flaps

4.3.2.3 Instructions

This section may be required if the operator is executing either theIRS or the DADCTests in any manner other than what has beendescribed in the above sections. If following the general operationsection, proceed to Section 4.4.

The operator selects, initiates, and provides feedback for each testthrough the DC.

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

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The following is a list of how to use the LRUTest Menu displayed onthe DC CRT for Maintenance Test (refer to Figure 4-4).

“PASSn

The operator presses this line select key if the equipment passes thecurrent test.

“FAILn

The operator presses this line select key if the equipment fails thecurrent test.

The operator presses this line select key to back-step through thetest selections presented on the Crew Alerting System (CAS) display.

“SELECTn

The operator presses this line select key to initiate the task thatis highlighted on the CAS display.

“DOWN”

The operator presses this line select key to step through the testselections presented on the CASdisplay.

“RETURN”

The operator presses this line select key to return to the menu thathad been previously displayed on the DC. This is not used to selectthe options presented on the CAS display.

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4.3.2.4 IRS Maintenance Test ASCBData

WSPBIT BIT FUNCTION NOTEFORMATI l-------------------------l----l------------------------

35 MAINTENANCETEST35 15 SPARE35 14 SPARE35 13 A/D OR MUXFAULT LOGIC 1 = FAULT35 12 CPU FAULT LOGIC 1 = FAULT35 11 DISCRETE1/0 FAULT LOGIC 1 = FAULT35 10 WDTFAULT LOGIC 1 = FAULT35 9 SYSTEMTESTS LOGIC 1 = FAULT35 8 TEMPSENSORFAULT LOGIC 1 = FAULT35 7 GYROFREQANDBIAS FAULT LOGIC 1 = FAULT35 6 GYROFAULT LOGIC 1 = FAULT35 5 ACCELRESIDUALFAULT LOGIC 1 = FAULT35 4 SPARE35 3 MEMORYFAULT LOGIC 1 = FAULT35 2 SENSORLSIC FAULT LOGIC 1 = FAULT35 1 SPARE35 0 POWERSUPPLYFAULT LOGIC 1 = FAULT

4.4 FMS/PMSTest

When the System Test Menu is displayed on the Display Controller (DC)Cathode Ray Tube (CRT) as shown in Figure 4-9, the operator initiates theFMSTest by pressing the line select key labeled “FMS/PMS”. This produce:the Flight Management System/ Performance Management System (FMS/PMS)Subsystem Menu to appear on the DC CRT as shown in Figure 4-10.

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System Test MenuFigure 4-9

FMS/PMSSubsystem MenuFigure 4-10

The operator selects one of the subsystem tests or returns to the SystemTest Menu by pressing the appropriate line select key. The tests aredescribed in the following sections.

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4.4.1 Flight Management System (FMS)

4.4.1.1 General Operation

The operator selects, initiates, and provides feedback for the FlightManagement System (FMS) Test through the DC. There are five testsassociated with the Flight Management System. The FMSStatus Test,one for each FMS, will show the active FMSSon ASCB, the FMSStransmitting valid data, the sensors used by the FMSS, and theBuilt-In-Test (BITE) results. The FMSConfiguration Test, one foreach FMS, will show the configuration pin status. The FMSSoftwareMod Level Test will show the internal software levels of each FMSandCDU. There is no correlation between Software Mod Status inMaintenance Test and the Mod Status shown externally on the LRU, TheSoftware Mod Levels are used for reporting purposes.

When the FMS/PMSSubsystem Menu is displayed on the DC CRT, theoperator initiates the FMSTest by pressing the line select keylabeled “FMS”. This produces the Line Replaceable Unit (LRU) TestMenu to appear on the DC CRT as shown in Figure 4-11. Verify the Ft4SCDU1 and 2 are displaying the TEST pattern on the CDUCRT as shown inFigure 4-12. Verify CDUMessage lights are sequencing in order, onboth CDU’S. Depress ~ switches on both CDU’S and verify inversevideo is displayed on appropriate annunciator when selected.

Pflss

FAIL

mUP

SELECT

DO14N

RETURN

LRUTest MenuFigure 4-11

laEl

l--=t-=

t--=

AD-22879#

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GR RE OR ~]>

s

e LS3L MNOPQR 789 LS3R e

e) LS4L STUVIAJ .0 LS4R c

XYZDC ‘/ KB CK e

PRF NV PRV NX FP PRG DIR

AD-22880#

CDUTest DisplayFigure 4-12

The operator presses the line select key labeled “SELECT” to initiatethe FMS1 Status Test, the option highlighted on the Crew AlertingSystem (CAS) display, as shown in Figure 4-12.1. The resulting statusor error messaqes are displayed on the CAS display. A typical CASDisplay for th; FMS1 Status-Test is shown in Figure 4-12.2.

MRINTENRNCE TEST

FMSI

Il. FMS 1 STRTUS TESTI2. FMS 2 STRTUS TEST30 FMS 1 CONFIGURFITION4. FMS 2 CONFIGURATION5. SOFTMRRE MOD LEVEL TEST

. . .AD-22881 #

FMS1 Status Test OptionFigure 4-12.1

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TMfHNTENflNCE TEST

FMS 1 STRTUS TEST: FMSNZ 1 ON 9SCBNZ 1 VFILID

flCTIVE SENSORS:RFCS 1 2DRDC 1 2IRS 1 2PERF 1 2SG 123

NZ 2 DISPLRY USE PRSS/FFIIL TO CONTINUENZ 2 BRSICNFIV-PRI-SECDME-PRI-SECNZ BITE PRSSCDU BITE PRSS

CPU B BITE PRSSCPU C BITE PFISS

CASDisplay for the FMS 1 Status TestFigure 4-12.2

.AD-22882#

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I

Ground Maintenance Test Procedure

The following is a list of all messages that may appear on the CASdisplay as a result of executing the FMS1 Status Test.

BUS NZ 1 Active on ASCB

NZ 1 ONASCB

VALID NZ 2 Transmitting Valid Data

NZ 1 VALID

SENSORS Indicates Sensors used by FMS1

ACTIVESENSORS:AFCS 1 2DADC1 2LNAV1 2IRS 1 2 3PZ 1 2 (See note)SG123NZ 2 DISPLAYNZ 2 BASICX-SIDE NZACARSMLSNAV- PR1 SECDME- PR1 SECLRN123

BITE Built In Test Results

NZ BITE PASSNZ BITE FAILCDUBITE PASSCDUBITE FAILCPU B BITE PASSCPUB BITE FAILCPU C BITE PASSCPUC BITE FAIL

NOTE: Not logged as Active Sensor when using -976 and -978 NZwithout mod AK.

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To proceed with the FMSTest, the operator presses the “PASS” or“FAIL” line select key based on the outcome of the test. Thisadvances the test to the FMS2 Status Test, the option highlighted onthe CAS display, as shown in Figure 4-12.3. To initiate the test, theoperator presses the line select key labeled “SELECT”. The resultingstatus and error messages are displayed on the CAS display. A typicalCAS Display for the FMS2 Status Test is shown in Figure 4-12.4.

FMS

1. FMS 1 STFITUSTEST[2. FMS 2 STfiTUS TEST]3. FHS 1 CONFIGURFITION4. FMS 2 CONFIGURFITION5. SOFTHRRE MOD LEVEL TEST

. .AD-22883#

FMS2 Status Test OptionFigure 4-12.3

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F \

F14S2 STFITUSTEST: FMSNZ 2 ON FISCBNZ 2 VflLID

RCTIVE SENSORS:RFCS 1 2DRDC 1 2IRS 1 2PERF 1 2SG123

NZ 1 DISPLFIY USE PRSS/FRIL TO CONTINUENZ 1 BRSICNFIV-PRI-SECDME-PRI-SECNZ BITE PRSSCDU BITE PFISS

CPU B BITE PFISSCPU C BITE PRSS

A A A. .

AD-228B4#

CASDisplay for the FMS2 Status TestFigure 4-12.4

The following is a list of all messages that may appear as aexecuting the FMS2 Status Test.

BUS NZ

NZ 2 ONASCB

VALID

NZ 2 VALID

2 Active onASCB

NZ 2 Transmitting Valid Data

result of

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I

I

Ground Maintenance Test Procedure

SENSORS

ACTIVESENSORS:AFCS 1 2DADC1 2LNAV1 2IRS 123PZ 1 2 (See note)SG 123NZ 1 DISPLAYNZ 1 BASICX-SIDE NZACARSMLSNAV- PR1 SECDME- PR1 SECLRN123

BITE

NZ BITE PASSNZ BITE FAILCDUBITE PASSCDUBITE FAILCPU B BITE PASSCPU B BITE FAILCPU C BITE PASSCPUC BITE FAIL

Indicates Sensors used by FMS2

Built In Test Results

To proceed with the FMSTest, the operator presses the “PASS” or“FAIL” line select key based on the outcome of the test. Thisadvances the test to the FMS1 Configuration Test, the optionhighlighted on the CASdisplay, as shown in Figure 4-12.5. Toinitiate the test, the operator presses the line select key labeled“SELECT”. The resulting status and error messages are displayed onthe CAS display. A typical CAS Display for a Phase II FMS1Configuration Test is shown in Figure 4-12.6.

~: Not logged as Active Sensor when using -976 and -978NZwithout mod AK.

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FMS

10 FMS 1 STRTUS TEST2. FMS 2 STFITUS TEST[3. FMS 1 CONFIGURATION]4. FMS 2 CONFIGURATION5. SOFTIIRRE MOD LEVEL TEST

AD-22885#

FMS1 Configuration Test OptionFigure 4-12.5

FMS 1 CONFIGURATION FMSNZ 1 ID PF!SS

RFIDIO = COLLINS 429DME = SCflNNING

LRN 1 =LRN 2 =LRN 3 =

MODE = CDU CONTROLFLIGHT RULES = FfIf3ENGLISH MERSUREPERF INSTflLLED USE PRSS/FRIL TO CONTINUE

A A A

AD-22886#

CAS Display for a Phase II FMS1 Configuration TestFigure 4-12.6

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The following is a list of all messages that may appear as a resultof executing the FMS1 Configuration Test. The operator isresponsible for verifying that the configuration is correct.

CONFIGURATION NAVComputer 1 Configuration

FMS1 CONFIG:NZ ID PASSNZ ID FAILRADIO= KING429RADIO= COLLINS429RADIO= SPERRYASCBRADIO= COLLINS422DME= SCANNINGDME= SINGLELRN1

}

= SEE BELOWLRN2 = SEE BELOW NOTE: This portion of the test isLRN3 = SEE BELOW unavailable for Phase II aircraft.MODE= INIT XFERMODE= INDEPENDENTMODE= SINGLEMODE= CDUCONTROL

AA)FLIGHTRULES= CAA NOTE: -905 FWCcorrectly labels thisFLIGHTRULES= F as “OVRSPDPROTECTON/OFF”METRICMEASUREENGLISHMEASUREPZ INSTALLEDCROSSFILL ENABLEDL CONNECTED

(LRN sources)IRS#3 IRS#4 IRS#5 IRSOMEGA#1 OMEGA#2 OMEGA#3 OMEGALORAN#1 LORAN#2 LORAN#3 LORANGPS#1 GPS#2 GPS#3 GPS

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To proceed with the FMSTest, the operator presses the “PASS” or“FAIL” line select key based on the outcome of the test. Thisadvances the test to the FMS2 Configuration Test, the optionhighlighted on the CASdisplay, as shown in Figure 4-12.7. Toinitiate the test, the operator presses the line select key labeled“SELECT”. The resulting status and error messages are displayed onthe CAS display. A typical CAS Display for the FMS2 ConfigurationTest is shown~n Figu;e 4-12.8. - -

f- +

FMS

1. FMS 1 ST13TUSTEST2. FMS 2 ST13TUS TEST3. FMS 1 CONFIGURFITION[4. FMS 2 CONFIGURRTIONI5. SOFTilllREMOD LEVEL TEST

A A A. . w

AD-22887#

FMS2 Configuration Test OptionFigure 4-12.7

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FMS2 CONFIGURFITIONNZ 2 ID PHSS

RflDIO= COLLINS429DME = SCRNNING

LRN 1 =LRN 2 =LRN 3 =

MODE = CDU CONTROLFLIGHT RULES = FRRENGLISH MERSUREPERF INSTRLLED

MfHNTENflNCE TEST

FMS

USE PFISS/FFIILTO CONTINUE

CAS Display for the FMS2 Configuration TestFigure 4-12.8

AD-22888#

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The following is a list of all messages that may appear as a resultof executing the FMS2 Configuration Test. The operator isresponsible for verifying that the configuration is correct.

CONFIGURATION

FMS2 CONFIG:NZ ID PASSNZ ID FAILRADIO= KING429RADIO= COLLINS429RADIO= SPERRYASCBRADIO= COLLINS422DME= SCANNINGDME= SINGLELRN1

}

= SEE BELOWLRN2 = SEE BELOW NOTE: This portion of the test isLRN3 =SEE BELOW unavailable for Phase 11 aircraft.MODE= INIT XFERMODE= INDEPENDENTMODE= SINGLEMODE= CDUCONTROL

AFLIGHTRULES= CAA NOTE: -905 FWCcorrectly labels thisFLIGHTRULES= F as “OVRSPDPROTECTON/OFF”METRICMEASUREENGLISHMEASUREPZ INSTALLEDCROSSFILL ENABLEDL CONNECTED

(LRN sources)IRS#3 IRS#4 IRS#5 IRSOMEGA#1 OMEGA#2 OMEGA#3 OMEGALORAN#1 LORAN#2 LORAN#3 LORANGPS#1 GPS#2 GPS#3 GPS

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To proceed with the FMSTest, the operator presses the “PASS” or“FAIL” line select key based on the outcome of the test. Thisadvances the test to the Software Mod Level Test, the optionhighlighted on the CAS display, as shown in Figure 4-12.9. Toinitiate the test, the operator presses the line select key labeled“SELECT”. The resulting status and error messages are displayed onthe CAS display. A typical CAS Display for the FMSSoftware Mod LevelTest is shown in Figure 4-12.10.

FMS

1.FMS 1 STRTUS TEST2. FMS 2 STfITUSTEST3. FMS 1 CONFIGURATION4. FMS 2 CONFIGURFITION15. SOFTllflREMOD LEVEL TESTj

.AD-228a9#

Software Mod Level Test OptionFigure 4-12.9

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F \

NZ 1 S/Ii FMSCPU R = DEL llKCPU B = BDEL llCCPU C = CDEL 11P

NZ 2 S/1:CPU R = DEL llKCPU B = BDEL llCCPU C = CDEL 11P

CDU 1 S/Ii = 06

CDU 2 S/Ii= 06 USE PfISS/FRIL TO CONTINUE

A A A

AD-22890#

CAS Display for the FMSSoftware Mod Level TestFigure 4-12.10

The following isof executing the

MODLEVEL

NZ S/W:

a list of all messages that may appear as a resultSoftware Mod Level Test.

CPUA = XxxxxxCPU B = XXXXXXCPU c = Xxxxxx

NOTE: There is no correlation between Software Mod Level inMaintenance Test and the Mod Status shown externally on theLRU. Ensure identical dash numbers installed. Different Modlevels may produce a “MISMATCHDETECTED”message.

CDUMODLEVEL

CDUS/W = XX

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4.4.1.2 Recommended Maintenance Action

The following is a list of messages associated with maintenance testand recommended action.

Status Test:

~ Action

NZ BITE FAIL With all avionics powered up, pull both air(NO OTHERFMS data computers circuit breakers. Also pullFAILURES) the breaker to the nut cracker switch

(Weight On Wheels). The NZ will now operatein airborne mode. Maintain these conditionsfor three minutes. Now close the breaker tothe nut cracker switch. Repeat GMT. Iffailure remains, replace the NAVcomputer.If failure is gone, proceed to the next test.

NZ BITE FAIL ALONG Same action as for NZ bite failWITHCDUBITE FAIL (See above action).(NO OTHERFMSFAILURES)

CDUBITE FAIL Same action as for NZ bite fail but(NO OTHERFMS Replacing CDUinstead of NZ if failFAILURES) report remains (See above action).

CPU B BITE FAIL Replace NAVComputer.

CPU C BITE FAIL If this message is displayed for more thanfive minutes following NZ power up, replacethe NAVcomputer. If failure is removed,proceed to the next test.

NOTE: This message will appear for up to five minutes on power up.If this message occurs after the five minute power-up period,it indicates a failure.

An ASCBFailure may also cause this message.

FMS(X) NOT IN TEST 1. VerifyA/CwiringJIA-10, 11, 14NOTONASCB on NAVComputer.

2. Replace NAVComputer.

NZ ID FAIL 1. Check following pins: JIB-98 SDI #1,JIB-99 SDI #2, JIB-65 SDI #3

2. Replace NZ.

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To proceed with the FMSTest, the operator presses the “PASS” or“FAIL” line select key based on the outcome of the test. Thisadvances the test to the FMS1 Status Test, the option highlighted onthe CAS display, as shown in Figure 4-12.11. This indicates that allsegments of the FMSTest have been completed. To return to theFMS/PMSSubsystem Menu, as shown in Figure 4-12.12, the operatorpresses the line select key labeled “RETURN”. The operator pressesthe RETURNkey a second time to return to the System Test Menu.

FMS

[1. FMS 1 STflTUS TEST)f)LLTEST COMPLETE 2. FMS 2 STfiTUS TEST

3. FMS 1 CONFIGURflTION4. FMS 2 CONFIGURFITION5. SOFTMflRE MOD LEVEL TEST

A A A

AD-22891 #

FMS1 Status Test OptionFigure 4-12.11

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FMS/PMSSubsystem MenuFigure 4-12.12

After performing the FMSTest, the NZS may be in Single Operation TheConfiguration Problems Pages will show “DUALINOP” and “SLAVE”messages. The NZ’S will require the [ircuit breakers to be recyc”ed

or independent mode.on both NZ’S to recover back to a dua

AD-22892#

4.4.2 Performance Management System (PMS)

4.4.2.1 General Operation

The operator selects, initiates, and provides feedback for thePerformance Management System (PMS) Test through the DC.

When the FMS/PMSSubsystem Menu is displayed on the DC CRT, theoperator initiates the PMSTest by pressing the line select keylabeled “pMS”. This produces the Line Replaceable Unit (LRU) TestMenu to appear on the DC CRT as shown in Figure 4-12.13. There areten tests associated with the Performance Management System.

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The Perf Status Test, one for each PMS, will show the PMSSactive onASCB, the PMSStransmitting valid data, the LRUSreceived on ASCB, andthe status of the internal battery. The Autothrottle Status Test, onefor each A/T system, will show the A/Ts active on ASCB, theA/Tstransmitting on ASCB, the LRUSreceived on ASCB, and the prioritystatus. The Perf Configuration Test will show the status of alldiscrete inputs and the identification pin status. The A/TConfiguration Test will also show the status of all discrete inputsand the identification pin status. The PLA Position Test will showthe PLA position data for each autothrottle system. The A/T SwitchesTest will allow the operator to verify each A/T is receiving andrecognizing each quick disconnect and each engage/disengage switch.The A/T Servo Test, one for each A/T system, will determine systemfriction by monitoring servo currents and rate feedbacks, as well asshow the status of clutch voltages, servo tach, and servo current.

~

e UP e

e Pllss SELECT e

~ FAIL DO14N Q

~ ~

AD-22893 #

LRUTest MenuFigure 4-12.13

The operator presses the line select key labeled “SELECT” to initiatethe Perf 1 Status Test, the option highlighted on the Crew AlertingSystem (CAS) display, as shown in Figure 4-12.14. The resultingstatus or error messages are displayed on the CAS display. A typicalCAS Display for the Perf 1 Status Test is shown in Figure 4-12.15.

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F \

PMS

[1. PERF 1 STRTUS TESTI2. PERF 2 STRTUS TEST3, FIT1 STflTUS TEST4. FIT2 STfITUSTEST50 PERF CONFIGURATION TEST6. RT CONFIGURflTION TEST7. PLfIPOSITION8. fIT SMITCHES9. RT 1 SERVO TEST10. flT2 SERVO TEST

AD-22894#

Perf 1 Status Test OptionFigure 4-12.14

f \

MfHNTEN(lNCE TESTPERF 1 ON RSCB PMS

PERF 1 VfiLIDPERF 1 fISCBPRSS

FILLLRU’S RECEIVED

BflTTERY OK USE PflSS/Ff31LTO CONTINUE

A A A. v

AD-22895#

CASDisplay for the Perf 1 Status TestFigure 4-12.15

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The following is a list of all messages that may appear on the CASdisplay as a result of executing the Perf 1 Status Test.

BUS PZ 1 Active on ASCB

PERF 1 ON ASCB

VALID PZ 1 Transmitting Valid Data

PERF 1 VALID

ASCB ASCBStatus with Respect to PZS

PERF 1 ASCBPASSALL LRUSRECEIVEDPERF 1 ASCBFAILLRUSNOTRECEIVEDPERF 2NZ 1DADC1 2FGC 1 2DC12DAU1A lB 2A 2BFWC1 2AT12SG123

BATTERY Internal Battery Status

BATTERYO.K.BATTERYLOWBATTERYDEAD

To proceed with PMSTest, the operator presses the “PASS” or “FAIL”line select key based on the outcome of the test. This advances thetest to the Perf 2 Status Test, the option highlighted on the CASdisplay, as shown in Figure 4-12.16. The operator presses the lineselect key labeled “SELECT”to initiate the Perf 2 Status Test. Theresulting status or error messages are displayed on the CAS display.A typical CAS Display for the Perf 2 Status Test is shown in Figure4-12.17.

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f Y

PMS

1. PERF 1 STFITUS TEST12. PERF 2 STF!TUSTEST]3. FIT1 STfiTUS TEST4. RT 2 STRTUS TEST5. PERF CONFIGURATION TEST6. RT CONFIGURfiTION TEST7, PLflPOSITION8. (+TSMITCHES9. RT 1 SERVOTEST10. FIT2 SERVOTEST

A A A

AD-22B96#

Perf 2 Status Test OptionFigure 4-12.16

t >

PERF 2 ON RSCB PMS

PERF 2 VFILIDPERF 2 FISCBPFISS

FILLLRU’S RECEIVED

BRTTERY OK USE PFISS/FflILTOCONTINUE

A A A.

AD-22897#

CAS Display for the Perf 2 Status TestFigure 4-12.17

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Page 138: Avionic Gulfstream IV-2

The following is a list of all messages that may appear on the CASdisplay as a result of executing the Perf 2 Status Test.

BUS PZ 2 Active on ASCB

PERF 2 ONASCB

VALID PZ 2 Transmitting Valid Data

PERF 2 VALID

ASCB ASCBStatus with Respect to PZS

PERF 2 ASCBPASSALL LRUSRECEIVEDPERF 2ASCB FAILLRUSNOTRECEIVEDPERF 1NZ 2DADC1 2FGC 1 2DC12DAU1A lB 2A 2BFWC1 2AT12SG123

BATTERY Internal Battery Status

BATTERYO.K.BATTERYLOWBATTERYDEAD

To proceed with PMSTest, the operator presses the “PASS” or “FAIL”line select key based on the outcome of the test. This advances thetest to the AT 1 Status Test, the option highlighted on the CASdisplay, as shown in Figure 4-12.18. The operator presses the lineselect key labeled “SELECT”to initiate the AT 1 Status Test. Theresulting status or error messages are displayed on the CAS display.A typical CASDisplay for the AT 1 Status Test is shown in Figure4-12.19.

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e Y

PMS

1. PERF 1 STRTUS TEST2. PERF 2 STFITUSTEST13. RT 1 STflTUS TEST]4. FIT2 STFITUS TEST5. PERF CONFIGURATION TEST6. RT CONFIGURATION TEST7. PLFIPOSITION80 RT SHITCHES9. (3T1 SERVO TEST10. RT 2 SERVO TEST

AD-22898#

AT 1 Status Test OptionFigure 4-12.18

F \

RT 1 ON RSCB PMS

flT 1 VllLIDFIT1 RSCBPRSS

FILLLRU’S RECEIVED

FIT1 (2) MFISTER USE PflSS/FflIL TOCONTINUE

A A A. . J

AD-22898#

CAS Display for the AT 1 Status TestFigure 4-12.19

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The following is a list of all messages that may appear on the CASdisplay as a result of executing the AT 1 Status Test.

BUS AT 1 Active on ASCB

AT 1 ON ASCB

VALID AT 1 Transmitting Valid Data

AT 1 VALID

ASCB ASCBStatus with Respect to ATs

AT 1 ASCBPASSALL LRUSRECEIVEDAT 1 ASCBFAILLRUSNOTRECEIVEDDADC1 2NZ12FGC 1 2IRS 1 2DC12DAU1A lB 2A2BPERF 1 2

PRIORITY Master AT

AT 1 MASTER

To proceed with PMSTest, the operator presses the “PASS” or “FAIL”line select key based on the outcome of the test. This advances thetest to the AT 2 Status Test, the option highlighted on the CASdisplay, as shown in Figure 4-12.20. The operator presses the lineselect key labeled “SELECT” to initiate the AT 2 Status Test. Theresulting status or error messages are displayed on the CAS display.A typical CAS Display for the AT 2 Status Test is shown in Figure4-12.21.

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e

PMS

1. PERF 1 STFITUSTEST2. PERF 2 STfiTUS TEST3. FIT1 STRTUS TEST[4. RT 2 STflTUSTEST]5. PERF CONFIGURATION TEST6s RT CONFIGURATION TEST7. PLFIPOSITION8. FITSWITCHES91 RT 1 SERVO TEST10. RT 2 SERVO TEST

AD-22900#

AT 2 Status Test OptionFigure 4-12.20

● \

FIT 2 ON HSCB PMS

flT2 VRLIDRT 2 RSCB PRSS

RLL LRU’S RECEIVED

FIT1 (2) MfiSTER USE PFISS/FflILTO CONTINUE

A A A

b,

b

. . .AD-22901#

AT 2 Status TestFigure 4-12.21

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The following is a list of all messages that may appear on the CASdisplay as a result of executing the AT 2 Status Test.

BUS AT 2 Active on ASCB

AT 2 ON ASCB

VALID AT 2 Transmitting Valid Data

AT 2 VALID

ASCB ASCBStatus with Respect to ATs

AT 2 ASCBPASSALL LRUSRECEIVEDAT 2 ASCBFAILLRUSNOTRECEIVEDDADC1 2NZ12FGC 1 2IRS 1 2DC12DAU 1A lB 2A 2BPERF 1 2

PRIORITY Master AT

AT 2 MASTER

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To proceed with PMS Test, the operator presses the “PASS” or “FAIL”line select key based on the outcome of the test. This advances thetest to the Perf Configuration Test, the option highlighted on the CASdisplay, as shown in F~gure 4-12.22. -

MflINTENflNCETEST

PMS

1. PERF 1 STfiTUS TEST2. PERF 2 STflTUS TEST3. fiT1 STFITUS TEST4. flT2 STflTUSTEST

15. PERF CONFIGURATION TESTI6. FITCONFIGURATION TEST7. PLfl POSITION8. 17TSWITCHES9. RT 1 SERVO TEST10. RT 2 SERVO TEST

. 1

Perf Configuration Test OptionFigure 4-12.22

vAD-22902#

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The operator presses the line select key labeled “SELECT” to initiatethe Perf Configuration lest. The resulting status or error messagesare displayed on the CAS display. A typical CAS Display for the PerfConfiguration Test is shown in Figure 4-12.23.

f Y

MfHNTENflNCETESTPERF 1 PMS

GEM? OOiiNL BLEED OFFRBLEED OFFL flCPt3CKOFFR RC PRCK OFFLEFT SELECT

VERSIONB flSCBDURL

61V

PERF 26EfIRDOHNL BLEEDOFFR BLEEDOFFL RC PINK OFFR flCPflCKOFFR16HT SELECTVERSIONB f!SCB

DURL61V USE Pf)SS/FllILTO CONTINUE

h A A

CAS Display for the Perf Configuration Test-AD-2290%Rl#

Figure 4-12.23

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Page 145: Avionic Gulfstream IV-2

The following is a list of all messages that may appear on the CASdisplay as a result of executing the Perf Configuration Test.

DISCRETES Indicates Configuration Pins Status

GEAR DOWNGEAR UPL BLEED ONL BLEED OFFR BLEED ONR BLEED OFFLAC PACKONLAC PACK OFFR AC PACK ONRAC PACK OFFLEFT SELECTRIGHT SELECT

ID Indicates Status of ID Pins

VERSION AASCBVERSION BASCBDUALSINGLEG-IV (See note)UNKNOWN

To proceed with PMS Test, the operator presses the “PASS” or “FAIL”line select key based on the outcome of the test. This advances thetest to the AT Configuration Test, the option highlighted on the CASdisplay, as shown in Figure 4-12.24. The operator presses the lineselect key labeled ‘SELECT” to initiate the AT Configuration Test.The resulting status or error messages are displayed on the CASdisplay. A typical CAS Display for the AT Configuration Test isshown in Figure 4-12.25.

NOTE: FWC -905 and -914 will display the following for the variousPZ configurations:

Certification Type I.D. DisDlav

FAA/Brunei Configuration ADOT/DGAC Configuration BCM Configuration CAustralia Configuration DGeneric JAR Configuration ESpecial Mission Configuration F

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MRINTENf)NCE TEST

PMS

1. PERF 1 STRTUS TEST2. PERF 2 STflTUS TEST3. FIT1 STRTUS TEST4. RT 2 STE!TUS TEST5. PERF CONFIGURATION TEST160 FITCONFIGURIITION TESTI7. PLfl POSITION8. RT SHITCHES9, FIT1 SERVO TEST10. FIT2 SERVO TEST

. ,AD-22904#

AT Configuration Test OptionFigure 4-12.24

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P 5

MfHNTENflNCETESTf3T1 PMS

6EflRDOtiNL BLEED OFFR BLEEDOFFL RC PRCK OFFR RC Pf!CKOFFLEFT SELECT

VERSIONB llSCBDURLGIV

FIT2GERR DOUNL BLEED OFFR BLEED OFFL fICP(ICKOFFR RC PRCK OFFRIGHTSELECTVERSIONB flSCBDUfiL(SINGLE)

GIV USE PflSS/FflILTO CONTINUEA A A

.“ AD-22905-R1 #

CAS Display for the AT Configuration TestFigure 4-12.25

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The following is a list of all messages that may appear on the CAS ‘--display as a result of executing the AT Configuration Test.

DISCRETES Indicates Configuration Pins Status

GEAR DOWNGEAR UPL BLEED ONL BLEED OFFR BLEED ONR BLEED OFFL AC PACK ONLAC PACK OFFRAC PACK ONRAC PACK OFFLEFT SELECTRIGHT SELECT

ID Indicates Status of ID Pins

VERSION AASCBVERSION BASCBDUALSINGLEG-IV (See note)UNKNOWN

To proceed with PMS Test, the operator presses the “PASS” or “FAIL”line select key based on the outcome of the test. This advances thetest to the PLA Position Test, the option highlighted on the CASdisplay, as shown in Figure 4-12.26. The operator presses the lineselect key labeled “SELECT” to initiate the PLA Position Test.

~: WC -905 and -914 wi11 display the following for the variousPZ configurations:

Certification T!me I.D. DisDlav

FAA/Brunei Configuration ADOT/DGAC Configuration BCAA Configuration CAustralia Configuration DGeneric JAR Configuration ESpecial Mission Configuration F

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Mf31NTENf7NCETEST

PMS

10 PERF 1 ST9TUS TEST2. PERF 2 STRTUS TEST3. fIT1 STRTUS TEST4s FIT2 STRTUS TEST54 PERF CONFIGURATION TEST6. FITCONFIGURATION TEST[7. PLll POSITION]8. fIT SMITCHES9. FIT1 SERVO TEST10. FIT2 SERVO TEST

. 1 T

AD-2290S#

PLA Position Test OptionFigure 4-12.26

Upon selection of the PLA Position test with at least one AT inmaintenance test, the FWC will enable the advisory message “PLEASEENERGIZETHE PLA SYSTEM PRESS SELECT WHEN COMPLETE.” This message isasking the operator to make sure there is power to the PLA system-byclosing the circuit breakers for 26 V ac.

When the PLA system is energized, the operator then pressesselect key labeled “SELECT” on the DC. The position data w“displayed as shown in Figure 4-12.27. The resulting statusmessages are displayed on the CAS display.

the line11 beor error

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Page 150: Avionic Gulfstream IV-2

flT 1PLFI1 = XX.X DEGPLf32 = XX.X DEG

flT 2PLfl 1 = XX.X DEGPLFI2 = XX.X DEG

MFHNTENRNCE TEST

PMS

USEPFISS/FfIILTOCONTINUE

1 . 1AD-22907#

Position Data DisplayFigure 4-12.27

PI-Achecks should be performed as follows:

1. Verify that PLA is 0.0 t 3.0 degrees with the throttles at theidle stops.

2. Verify that PLA is 39.5 t 3.0 degrees with the throttles at theforward stop.

NOTE: If the PLA measurement does not pass the above tests, itshould be checked with the throttles pinned at idle andpinned at the forward stops. Uith the throttles pinned,the requirement is O.Ot l.O degrees at idle and39.5+ 1.0/-0.0 degrees at the forward stop.

3. Verify that PLA is somewhere between 0.0 and 39.5 degrees withthe throttles in an intermediate position.

The following is a list of all messages that may appear on the CASdisplay as a result of executing the PLA Position Test.

PLA Failures

REFERENCE FAILPLA INPUT FAIL

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To proceed with PMS Test, the operator presses the “PASS” or “FAIL”line select key based on the outcome of the test. This advances thetest to the AT-Switches Test, the option highlighted on the CASdisplay, as shown in Figure 4-12.28. The operator presses the lineselect key labeled “SELECT” to initiate the AT Switches Test.

I MfHNTENflNCE TEST

PMS

1. PERF 1 STflTUS TEST2. PERF 2 STflTUSTEST3. FIT1 STRTUS TEST4. FIT2 STflTUSTEST5. PERF CONFIGURATION TEST6. RT CONFIGURIITION TEST7. PLR POSITION18. FITSMITCHESI9, 9T 1 SERVO TEST

I 10. FIT2 SERVO TEST

.AD-22903#

AT Switches Test OptionFigure 4-12.28

The initial menu Presented to the oDerator each time the test isaccessed is as shown in Figure 4-12”.29. Note that each type of switchis listed twice for A/T 1 and A/T 2; these correspond to switches onleft and right throttle handles. Each switch listing on the left ofthe display is followed by a question mark denoting that its operationhas not been verified. The question mark will be removed followingsuccessful recognition of switch depression by the autothrottle, asshown in Figure 4-12.30.

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I MflINTENflNCETESTfiT1: PMS

fl/TDISC?R/T DISC?

ENGliGE/DISENGRGE?ENGFIGE/DISENGfIGE?

FIT2:F1/TDISC?R/T DISC?

ENGflGE/DISENGRGE?ENG8GE/DISENGflGE?

DEPRESS LEFT R/T DISC

. , wAD-22909#

Initial MenuFigure 4-12.29

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I MRINTENRNCE TEST13T1: PMS

R/T DISCfl/T DISC

ENGfIGE/DISENGFIGEENGRGE/DISENGRGE

RT 2:13/T DISCfl/T DISC

ENGfIGE/DISENGfIGEENGRGE/DISENGRGE USE PfISS/FRIL TO CONTINUE

. . 1

AD-22910#

Successful Recognition of Switch Depression Removes Question MarkFigure 4-12.30

The operator will be prompted with instructions on the CAS display asto which switch to press. Be ready. The FWC will automaticallyadvance the menu selection if an A/T response is not received within10 seconds from initial display of the operator prompt. When thisoccurs, the switch is assumed to have failed and the question mark isnot removed from the switch listing. The “auto” advance feature doesnot apply to the pass/fail prompt.

~: Each switch must be pressed for 0.5 to 1.0 seconds to ensurethat it will be recognized. This is due to transmission timesand update rates while in Ground Maintenance Test only. Innormal operation the autothrottle will recognize a much shorterduration switch closure.

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The following is a list of all messages that may appear on the CASdisplay as a result of executing the AT Switches Test.

SWITCHES Quick Disc and Engage/Disengage Switch

AT DISC SWITCH FAILEDAT ENG/DIS SWITCH FAILED

To proceed with PMS Test, the operator presses the “PASS” or “FAIL”line select key based on the outcome of the test. This advances thetest to the AT 1 Servo Test, the option highlighted on the CASdisplay, as shown in Figure 4-12.31. The operator presses the lineselect key labeled “SELECT” to initiate the AT 1 Servo Test. Thiswill produce the CAS display shown in Figure 4-12.32.

hlfHNTENRNCE TEST

PMS

10 PERF 1 STRTUS TEST2. PERF 2 STFITUS TEST3. RT 1 STRTUS TEST40 13T2 ST8TUS TEST5. PERF CONFIGURFITION TEST60 RT CONFIGURfiTION TEST7. PLR POSITION8. RT SNITCHES19. FIT1 SERVO TEST\10. FIT2 SERVO TEST

AD-22911#

AT 1 Servo Test OptionFigure 4-12.31

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Page 155: Avionic Gulfstream IV-2

I MfHNTENflNCE TEST

PMS

DEPRESS flNDRELEFISEEITHERR/T ENGflGE/DISENGRGE SWITCH

CRUTION- THROTTLES WILLHOVE DURING THIS TEST

DEPRESS RND HOLD SELECTTO INITIRTE TEST

.AD-2291 2#

CAS Display for the AT 1 Servo TestFigure 4-12.32

The or)eratormust respond to the messages by first pressing andreleaking) one of the’engage/disengage switches and then pressing andholding the select button on the DC. The CAS display will be as shownin Fiqure 4-12.33. Once these steps have been taken, the throttlesshould begin to move.

CAUTION: INSURE GUST LOCK IS DISENGAGED PRIOR TO PERFORMING THEAUTOTHROTTLE SERVO TEST.

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I MflINTENflNCETESTI PMS

VERIFY:FITOFF HORNFITOFF LIGHTS

THROTTLE RCTIVITYMESSRGES

I USE PF!SS/FRIL TO CONTINUE

.AD-22913#

CASDisplayFigure 4-12.33

The servo test consists of the autothrottle moving both throttles fromthe current position, through maximum and minimum PLA, approximatelyback to the position at which the test was initiated. The throttleswill move at a normal rate with monitors and servo control/feedbackloops active. During this activity the autothrottle will monitorservo currents and rate feedbacks to determine system friction. Theautothrottle will indicate “EXCESSIVE FRICTION” on the CAS display, ifdetected. The threshold for excessive friction has been set at alevel which would seriously degrade autothrottle performance. Theautothrottle also determines and reports the clutch voltage, servotach, and servo current status. Failures will be displayed asmessages on the CAS (e.g., “CLUTCH FAIL’” “TACH FEEDBACK FAIL,” or“SERVO CURRENT FAIL”).

~: Grabbing the throttles to increase friction is not a valid testof system performance.

The following is a list of all messages that may appear on the CASdisplay as a result of executing the AT 1 Servo Test.

SERVO TEST

AT1:EXCESSIVE FRICTIONCLUTCH FAILTACH FEEDBACK FAILSERVO CURRENT FAIL

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Page 157: Avionic Gulfstream IV-2

test to the AT-2 Servo Test, the option highlighted on the CASdisplay, as shown in Figure 4-12.34. The Operator presses the lineselect key labeled “SELECT” to initiate the AT 2 Servo Test. Thiswill produce the CAS display shown in Figure 4-12.35.

MRINTENflNCE TEST

.

To proceed with PMS Test, the operator presses the “PASS” or “FAIL”line select key based on the outcome of the test. This advances the

b

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PMS

1. PERF 1 STRTUS TEST2. PERF 2 STRTUS TEST3. FIT1 STflTUS TEST4. FIT2 STflTUS TEST50 PERF CONFIGURATION TEST6. fITCONFIGURATION TEST7. PLflPOSITION8. FITSliITCHES9. RT 1 SERVO TEST[10. RT 2 SERVO TEST]

v w vAO-22914#

AT 2 Servo Test OptionFigure 4-12.34

Page 158: Avionic Gulfstream IV-2

I MflINTENRNCE TESTI

flT 2 PMS

DEPRESS 13NDRELEFISEEITHERfl/T ENGRGE/DISENGflGESWITCH

CflUTION-THROTTLESWILLMOVEDURINGTHIS TEST

IDEPRESS 13NDHOLDSELECT

TO INITIFITETEST

. . .AD-2291 5#

CAS Display for the AT 2 Servo TestFigure 4-12.35

The operator must respond to the messages by first pressing (andreleasing) one of the engage/disengage-switches and”then p~essing andholding the select button on the DC. The CAS Display will be as shownin Figure 4-12.36. Once these steps have been taken, the throttlesshould begin to move.

CAUTION: INSURE GUST LOCK IS DISENGAGED PRIOR TO PERFORMING THEAUTOTHROTTLE SERVO TEST.

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MRINTENfINCE TEST

flT2 PMS

VERIFY: RT OFF HORN9T OFF LIGHTS

THROTTLE FICTIVITYMESSflGES

I USE PflSS/FRIL TO CONTINUE

v . rAD-2291 6#

CAS DisplayFigure 4-12.36

The servo test consists of the autothrottle moving both throttles fromthe current position, through maximum and minimum PLA, approximatelyback to the position at which the test was initiated. The throttleswill move at a normal rate with monitors and servo control/feedbackloops active. During this activity the autothrottle will monitor servocurrents and rate feedbacks to determine system friction. Theautothrottle will indicate “EXCESSIVE FRICTION” on the CAS display, ifdetected. The threshold for excessive friction has been set at alevel which would seriously degrade autothrottle performance. Theautothrottle also determines and reports the clutch voltage, servotach, and servo current status. Failures will be displayed asmessages on the CAS (e.g., “CLUTCH FAIL,” “TACH FEEDBACK FAIL,” or“SERVO CURRENT FAIL”).

NOTE. Grabbing the throttles to increase friction is not a valid test—.of system performance.

The following is a list of all messages that may appear on the CASdisplay as a result of executing the AT 2 Servo Test.

SERVO TEST

AT2:EXCESSIVE FRICTIONCLUTCH FAILTACH FEEDBACK FAILSERVO CURRENT FAIL

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To proceed with the PMS Test, the operator presses the “PASS” or“FAIL” line select key based on the outcome of the test. Thisadvances the test to the Perf 1 Status Test, the option highlighted onthe CAS display, as shown in Figure 4-12.37. This indicates that allsegments of the FMS Test have been completed. To return to theFMS/PMS Subs.vstemmenu, the operator Dresses the line select kevlabeled “RETURN”. The-operator presses the RETURN key a second-timeto return to the System Test Menu.

F\

PMS[1.PERF 1 STflTUSTESTI

flLLTEST COMPLETE 2. PERF 2 STRTUS TEST3. FIT1 STfiTUS TEST4. RT 2 STflTUS TEST5. PERF CONFIGURIITION TEST6. flTCONFIGURATION TEST7, PLFlPOSITION8. FITSWITCHES9. FIT1 SERVO TEST10. FIT2 SERVO TEST

A A A. v

AD-2291 7#

Figure 4-12.37

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Page 161: Avionic Gulfstream IV-2

HoneywellMAINTENANCEMANUALGULFSTREAMIV

4.4.2.2 Recommended Maintenance Action

The following is a list of messages associated with maintenance testand recommended action.

Status Test:

Problem/’’MESSAGE” Possible Causes

“AT 1 (2) NOTON No power to PZ-800.ASCB ;: PZ-800 box not

seated properly.3. Primary ASCB bus

interface wiring(or coupler) fault.

4. PZ-800 1/0 fault.

‘AT 1 (2) INVALID” 1. Fault in wiringbetween PZ-800 boxand servos (power,servo drive, clutchdrive, or tachfeedback).

2. Fault in SM-81Oservo unit.

3. PZ-800 failure.

Action

1.

2.

3.

4.

5.

6.

7.

1.

2.

3.

Cycle and close PZ-800circuit breaker.Reseat PZ-800 box (removebox and inspect DPXconnector on the PZ-800 andthe aircraft rack fordamage).Run the AT Status Test forthe other AT.If only one AT shows theproblem, swap L/R PZ-800boxes. If the problemfollows the box, thenreplace the faulty PZ-800.If the problem does notfollow the box, or if itapplies to both ATs, it isprobably not a PZ-800failure; continue with thefollowing steps.Check for 28V to PZ-800power pins. If there is nopower, check associatedwiring.Check-out ASCB businterface wiring (andcoupler).

Cycle and close PZ-800circuit breaker.Perform steps 3,4,5 above(i.e., swap boxes, etc.)Complete all remainingautothrottle groundmaintenance tests and takecorrective actions.

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Status Test (cent):

Problem/’’MESSAGE” Possible Causes Action

“LRUS NOTRECEIVED” 1. LRUbox not seated 1. Cycle and close breaker for“DADC1 (2)” properly. LRU.“NZ 1 (2)” 2. LRU not receiving 2. Reseat LRU box (remove boxetc. power. and inspect DPX connectoretc. 3. LRU failed. on the LRU and the aircraft

4. Secondary ASCB bus rack for damage).interface wiring 3. Run ground maintenance test(or coupler) fault. for LRU.

5. PZ-800 failure. 4. If no LRUS are receivedfrom the opposite side,then check-out secondarybus interface wiring (andcoupler).

5. Perform steps 3,4,5 above(i.e., swap boxes, etc.).

“AT 1 (2) MASTER” Display Controller Toggle between AT 1,2 on thefault. DC. IfAT selected on the DC

does not agree with that shownon the ground maintenance testdisplay, check-out the DisplayController.

“AT 1 (2) NOT IN 1. “TEST SWITCH OFF.” 1. Note that groundTEST” “A/S ABOVE 50 KTS.” maintenance test cannot be

$ “WEIGHT ON WHEELS run in flight.OFF.“ 2. Ensure that maintenance

test switch is on (locatedin the avionics bay).

3. Check “weight on wheels”input to the PZ-800 (andassociated aircraftwiring).

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configurationTest:

~roblem/’’MESSAGE”

“GEAR UP”

“L BLEED ON (OFF)”“R BLEED ON (OFF)”“L AC PACK ON(OFF)““R AC PACK ON(OFF)”

“LEFT (RIGHT)SELECT”

Possible Causes

Aircraft wiringproblem.

If the indicatedconfiguration isdifferent from theactual, an aircraftwiring problem could becausing discreteinput(s) to PZ-800 tobe in error.

If the indicated PZ-800position is differentfrom actual, an air-craft wiring problemcould be causing anincorrect staticdiscrete input to thePZ-800 regarding leftor right position ofthe box.

Action

Check “Gear down” discreteinput to the PZ-800 (andassociated aircraft wiring).

NOTE: Honeywell SpecificationNo. EB701O494, ‘Instal-lation EngineeringBulletin for the GIV,”can be used to identifyall pin numbers into orout of the PZ-800.

Check discrete inputs to PZ-800(and associated wiring).

Check static discrete input tothe PZ-800 (and associatedwiring).

.

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Configuration Test (cent):

Problem/”MESSAGE” Possible Causes Actions

PLA position not 1. Red dots not 1. Insert the rigging pin withequal to 39.5 * aligned on the body the throttles at the3.0 degree at the’ of the PLA forward stop. If theforward stop. transducer. rigging pin cannot be

2. Problem with the inserted, recheck enginebasic mechanical rigging per GAC Report No.engine rigging. 1159C-PP-461.

3. Fault in PLA 2. Verify that the two redtransducer or dots on the body of the PLAwiring. transducer are

4. PZ-800 failure. approximately aligned whenthe throttles are at idlestops. If not, turn thePLA transducer until theyare approximately lined up.

3. Recheck calibration of thePLAs with the throttlespinned at the idle stops.

4. Repeat steps 3 and 4 above(i.e., swap boxes, etc.).

5. Repeat step 5 above(check-out PLA, etc.).

“REFERENCE FAILn 1. No 26 V ac power to 1. Check circuit breaker forPZ-800. 26V ac.

2. PZ-800 failure. 2. Check-out wiring for 26 Vac power to the PZ-800.

3. If only one AT shows theproblem, swap L/R PZ-800boxes. If the problemfollows the box, thenreplace the faulty PZ-800.

4. If the problem does notfollow the box, or if itapplies to both ATs, it isprobably not a PZ-800failure.

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Configuration Test (cent):

“PLA INPUT FAIL” 1. Fault in wiring 1. If only one AT shows thefrom PZ-800 to PLA problem, swap L/R PZ-800transducers (PLA boxes. If the problemRef). follows the box, then

2. Fault in wiring replace the faulty PZ-800.from PLA 2. If the problem does nottransducers to follow the box, or if itPZ-800. applies to both ATs, it is

3. PLA transducer probably not a PZ-800failure. failure; continue with the

4. PZ-800 failure. following steps.3. Check-out wiring from

PZ-800 to PLA transducers(PLA Ref).

4. Check-out wiring from PLAsto PZ-800.

5. Check-out PLAtransducer(s). Also,remove the PLAtransducer(s) and spin theshaft. If the shaft doesnot spin freely (or if youfeel “rough spots”), thePLA transducer should bereplaced.

Displayed PLA value 1. Red dots are 180 1. Align (approximately) redmoves in the wrong degrees out of dots on PLA transducer withdirection as the alignment on the the throttles at idlethrottles are body of the PLA stops.moved. transducer (i.e., 2. Check PLA wiring.

PLA transducer isoperating in thewrong quadrant).

2. PLA input to thePZ-800 is miswired.

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Configuration Test (cent):

“VERSION A ASCB” Aircraft wiring problem Check static discrete input tocausing static discrete the PZ-800 (and associatedinput to PZ-800 to wiring).indicate version A ASCBinstead of version B.

“SINGLE” Aircraft wiring problem Check static discrete input tocausing static discrete the PZ-800 (and associatedinput to PZ-800 to wiring).indicate single ASCBinstead of dual.

“UNKNOWN” Aircraft wiring problem Check static discrete input tocausing static discrete the PZ-800 (and associatedinput to the PZ-800 to wiring).indicate an aircrafttype other than GIV.

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PLA Position Test:

Problem/”MESSAGE” Possible Causes Actions

PLA position not 1. PLA not properly Insert rigging pin.equal to 0.0 t 3.0 calibrated. ~1 Calibrate PLAs (set to 0.0degrees at idle 2. Fault in PLA t 1.0 degree at idle stop>stop. transducer or check for 39.5 + 1.0/-0.0

wiring. degrees at forward stop).3. PZ-800 failure. 3. If only one AT shows the

problem, swap L/R PZ-800boxes. If the problemfollows the box, thenreplace the faulty PZ-800.

4. If the problem does notfollow the box, or if itapplies to both ATs, it isprobably not a PZ-800failure; continue with thefollowing steps.

5. Check-out the PLAtransducer(s) and wiring.Also, remove the PLAtransducer and spin theshaft. If it does not spinfreely (or if you can feel“rough spots”), the PLAtransducer should bereplaced.

PLA positions are 1. PLA transducer not 1. Check that PLA mountingnot consistent mounted properly screws are properlyover time. (slipping). tightened.

2. PLA transducer 2. Check-out PLA transducer.failure. Also, remove transducer and

spin the shaft. If it doesnot spin freely (or youfeel “rough spots”), thetransducer should bereplaced.

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Page 168: Avionic Gulfstream IV-2

AT Switches Test:

Problem/’’MESSAGE” Possible Causes Actions

“AT DISC SWITCH 1. Improper test 1. Repeat test and hold switchFAILED” execution (need to for 1 second. Also, be

press disconnect ready. The test willbutton for 0.5 to prompt for various switches1.0 seconds). to be pressed. The

2. Fault in disconnect operator has 10 seconds toswitch or switch respond before that switchwiring. is considered failed and

3. PZ-800 failure. the test automaticallymoves on to the next step.

2. If only one AT shows theproblem, swap L/R PZ-800boxes. If the problemfollows the box, thenreplace the faulty PZ-800.

3. If the problem does notfollow the box, or if itapplied to both ATs, thenit is probably not a PZ-800failure; continue with thefollowing steps.

4. Check-out disconnectswitches and wiring.

“AT ENG/DIS SWITCH 1. Improper test 1. Repeat test as describedFAILED” execution. above for disconnect

2. Fault in switch.engage/disengage 2. Repeat steps 2 and 3“aboveswitch or switch (i.e., swap boxes, etc.).wiring. 3. Check-out engage disengage

3. PZ-800 failure. switches and wiring.

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AT Servo Test:

“EXCESSIVE 1. Excessive friction 1. Re-check throttle systemFRICTION” in the aircraft friction force (without AT

throttle system. servos engaged).2. Excessive friction Procedures are outlined in

due to AT servo section 1.0.installation. 2. Check-out AT servo

installation (check againstGAC drawing No.1159F40900). Check cabletension by verifying springgap as called out on theGAC drawing.

“TACH FEEDBACK 1. Fault in wiring 1. If only one AT shows theFAIL” (also, one or between the problem, swap L/R PZ-800both throttles may servo/tach and boxes. If the problemmove faster than PZ-800. follows the box, thennormal). 2. Tach failure. replace the faulty PZ-800.

3. PZ-800 failure. 2. If the problem does notfollow the box, or if itapplies to both ATs, thenit is probably not a PZ-800failure; continue with thefollowing steps.

3. Check-out wiring betweenthe tach and PZ-800.

4. Check-out servo drivewiring and clutch wires.

5. Check-out servo/tach.Replace servo, if required.

“SERVO CURRENT 1. Fault in servo 1. Repeat steps 1 and 2 aboveFAIL” (also, one or drive wiring (i.e., swap boxes, etc.).both throttles may between PZ-800 and 2. Check-out servo drivenot move). servos. wiring.

2. Fault in clutch 3. Check-out clutch power andpower wiring. drive wiring.

3. PZ-800 failure. 4. Check tach feedback wiring.5. Check-out servo. Replace

if required.

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AT Servo Test (cent):

Probleml’’MESSAGE” Possible Causes Actions

No throttle 1. Improper test 1. Carefully repeat test.movement, no execution (need to 2. Check clutch drive wiring.messages. press and release

engage switch thenhold select buttonon the DisplayController).

2. Fault in clutchdrive wiring.

Erratic throttle 1. Fault in tach 1. Check tach feedback wiring.movement. feedback wiring 2. Check servo drive wiring.

(intermittent). 3. Check clutch drive/power2. Fault in servo wiring.

drive wiringg (intermittent). .. Fault in clutch

drive/power wiring(intermittent).

No “AT off” tone. 1. Problem with 1. Check FWC output to toneaircraft tone generator.generator or wiring 2. Check AT clutch input tofrom Fault Warning FWC.Computer (FWC) to 3. Check aircraft tonetone generator. generator and wiring.

2. FWC not properlysending signal togenerate tone.

No AT off lights. 1. Burned out light 1. Check light bulbs.bulbs. 2. Check FWC output to AT off

2. FWC not properly lights.sending signal to 3. Check AT clutch input toturn on lights. FWC.

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4.5 Automatic Fliqht Guidance Control Svstem (AFGCS)

The Automatic Flight Guidance Control System (AFGCS) Test is divided intotwo segments, the Status Test and the System Test. The Status Testperforms a quick configuration test on the system. The System testexercises complete system operation and aids fault isolation to the linereplaceable unit (LRU) level.

Each Flight Guidance Computer (FGC) checks the configuration at thebeginning of the test. When in dual configuration, the main FGC performsits tests first, then the FGC switches priority and the tests arerepeated. In either case, the FGC not currently performing the test isin standby mode.

4.5.1 Status Test - The Status Test checks the configuration of the systemwith respect to the FGC.

4.5.2 System Test - The System Test is comprised of a series of LRU specifictests. The individual tests available to the operator are explained inthe following sections.

4.5.2.1

4.5.2.2

4.5.2.3

05 FGC Test

The FGC test displays the preflight power-up built in test (BIT)results on the Crew Alerting System (CAS) display. The test alsoverifies the engage logic circuitry for the Auto Pilot (A/P), YawDamper (Y/D) and elevator trim. The final part of the test consistsof a flight director circuitry and outputs test.

10 Guidance Panel Test

The GP-820 test verifies the correct operation of the lights,pushbuttons and knobs on the GP-820 Guidance Panel (GP). Inaddition, the test verifies the pushbuttons and annunciatorsassociated with the Autopilot (A/P) on the wheel, kickpanel, and thethrottle handle.

15 Manual Controller Test

The Manual Controller Test verifies the correct operation of thepitch thumbwheel and the turn knob located on the PC-800 ManualController.

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4.5.2.4 20 Elevator Servo Test

The Elevator Servo test verifies the presence of the elevator servomotor interface and the absence of crossfeeds between the elevatorand the other three servos (Aileron, Rudder, and Trim).

4.5.2.5 25 Aileron Servo Test

The Aileron Servo Test verifies the presence of the aileron servomotor interface and the absence of crossfeeds between the aileron andthe other three servos (Elevator, Rudder, and Trim).

4.5.2.6 30 Rudder Servo Test

The Rudder Servo Test verifies the presence of the rudder linearactuator interface and the absence of crossfeeds between the actuatorand the other three servos (Elevator, Aileron, and Trim).

4.5.2.7 35 Pitch Trim Servo Test

The Pitch Trim Servo Test verifies the presence of the pitch trimservo motor interface and the absence of crossfeeds between the trimservo and the other three servos (Elevator,Aileron, and Rudder).

4.5.2.8 40 Cockpit Switches Test

The Cockpit Switches Test verifies the correct operation of thepushbuttons associated with the trim, Yaw Damper (Y/D) and theA/Pannunciators.

4.5.2.9 45 Subsystem Status Test

The Subsystem Status Test checks for the presence of sensor inputs,specifically, the Digital Air Data Computer (DADC) and the InertialReference System (IRS).

4.5.2.10 50 Flight Fault Summary

The Flight Fault Summary stores the fault data that occurred duringflight with respect to the automatic disconnect (A/P or Y/D) or FGCfailures. The information is retained only if power remains on thebox following the flight for a -905 or -906 FGC. A -907 FGC hasadditional Non-Volatile RAM to store failures with power removed.Only the fault data from the last failure is stored for a -905 or-906 FGC. A -907 FGC has the capability to store up to eightprevious failures. The summary may be accessed only when the FGC isin the Maintenance Test Mode.

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4.5.2.11 55 Ground Test Summary

The Ground Test Summary stores all the failures detected since thesystem entered the AFGCS Maintenance Test. The messages arepresented to the operator one at a time.

4.5.3 General Operations - The operator selects, initiates, and providesfeedback for the AFGCS test through the Display Controller (DC). Inaddition, for the AFGCS test, feedback is also provided by the operatorthrough the GP-820 Guidance Panel (GP),PC-800 Manual Controller (PC),and the cockpit switches. When the AFGCS test is being executed the CASdisplays the “MAINTENANCE TEST” and the “AFGCS” header and the optionsavailable to the operator on the right side. The message that indicateswhich FGC is in test is displayed on the left side.

When the System Test Menu is displayed on the DC Cathode Ray Tube (CRT)as shown in Figure 4-13, the operator initiates the AFGCS test bypressing the line select key labeled “AFGCS”. This produces the LRUTest Menu on the DC CRT and the CAS display appears as shown in Figure4-14.

{[

e EDS

~ SYSTEM CHECK FMS/PMS

e AFGCS SUMMARY

~

\\

bEl

~ AD-22918*

System Test MenuFigure 4-13

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LRU Test MenuFigure 4-14

~

e UP a

~ PASS SELECT a

e FAIL DO14N

~ a

AD-22919#

4.5.3.1 Status Test

The operator presses the line select key labeled “SELECT” to initiatethe Status Test, the option highlighted on the CAS display, as shownin Figure 4-14.1. A typical CAS display for the AFGCS Status Test isshown in Figure 4-14.2.

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/ w

AO-22920#

Status Test OptionFigure 4-14.1

F h

FGC1 2 ONFISCB flFGCS

FGC 1 2 VFILIO

FGC1 (2) MFISTER* USE PfISS/FflIL TOCONTINUEA A A

*WILL DISPLAY FGC SELECTED AT TEST INITIATION

splay for the AFGCS Status TestFigure 4-14.2

vAD-22921 #

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The following is an explanation of the messages associated with theStatus Test that appear on the CAS display.

ASCB Active FGCS on ASCB

FGC 1 2 ONASCBFGC NOT IN TESTNOT ON ASCBFGC NOT IN TESTINVALID

VALID FGCS Transmitting Valid Data

FGC 1 2 VALID

MASTER Indicates Master FGC

FGC 1 (2) MASTER

BITE Built In Test Results

AFCS BIT MEMORY FAILAFCS BIT RAM FAILAFCS BIT SERVO INTFC FAILAFCS BIT I/OFAILAFCS BITH/WMON FAIL

4.5.3.1.1 Recommended Maintenance Action

The following is a list of messages associated with maintenance testand recommended action.

!ksa9!2 Action

FGC NOT IN TEST 1. Verify jumpers between J1B-106and 79, 81.

NOT ONASCB 2. Verify computer power and gridsatJIA-6, 7, 8, 9.

3. VerifyA/Cwiring JIB-1, 2, 102,JIA-65, 66, J2B-1OO, 101, 65, 96,74, 98.

4. Replace FGC.

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Page 177: Avionic Gulfstream IV-2

!!ksw!2 Action

FGC NOT IN TEST VerifyA/Cwiring J2B-74, 98.A/S ABOVE 50 KNOTS

AFCS BIT MEMORY FAIL Replace Flight Guidance Computer.

AFCS BIT RAM FAIL Replace Flight Guidance Computer.

AFCS BIT SERVO VerifyA/Cwiring J2A-41 thru 50.INTFC FAIL ;: Replace FGC.

FGC NOT IN TEST VerifyA/Cwiring J2B-2, 101.INVALID

AFCS BIT 1/0 FAIL Replace FGC.

AFCS BIT H/Wt40N FAIL Replace FGC.

NOTE: When executing the FGC test, the combination of messages canindicate failures.

Based on this information, the operator determines if the system~:s~:~ :; failed the test, and pushes the appropriate line select key

The operator presses the pass or fail line select key toterminate”the Status Test and advance to the System Test, as shown inFigure 4-14.3.

AD-22922#

Terminate Status Test and Advance to System TestFigure 4-14.3

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4.5.3.2 System Test

To initiate the System Test, the option highlighted on the CASdisplay, as shown in Figure 4-14.3, the operator presses the lineselect key labeled “SELECT”. The operator may choose the testsuggested on the CAS display by pressing the line select key labeled“SELECT” or browse through the test options by pressing the lineselect key labeled “UP” or “DOWN” accordingly. The down line selectkey allows the operator to step through the test options and the upline select key allows the operator to backstep through the list oftest options.

4.5.3.2.1 05 FGCTest

With the CAS Display as shown in Figure 4-14.4, the operatorinitiates the FGC test by pressing the line select key labeled“SELECT”. The resulting messages associated with this test aredisplayed on the CAS display. as shown in Figure 4-14.5. Theoperator presses the line select key labeled “SELECT” to stepthrough the messages or to continue with the FGC Test, as shown inFigure 4-14.6.

AD-22923#

Initiate the FGC TestFigure 4-14.4

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4 \

FGC 1 IN TEST RFGCS

05 FGCTEST1 PREFLIGHT TEST PIISS

PRESS SELECT TO CONTINUE

A A A

AD-22924#

CAS DisplayFigure 4-14.5

e

FGC 1 IN TEST flFGCS

05 FGC TEST

IN PROCESS (1 PflSS*)

PRESS SELECT TO CONTINUEA A A

.AD-22925#

* A17ER TEST IS COMPLETE “IN PROCESS” BECOMES ‘“l PASS”

“SELECT” for FGC TestFigure 4-14.6

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Recall, when the test advances, it switches control to the remainingFGC if installed, and the FGC test is repeated. When both FGCS havebeen tested, the AFGCS test advances to the guidance panel segment.The following is a list of messages that may appear as a result ofthe FGC Test.

BITE Built In Test Results

PREFLIGHT TEST PASSAFCS SERVO PWROFFAFCS CONFIG PIN FAILA/B PROCESSOR INTFC FAIL

SERVO Servo Interface Status

AP SERVO POWER FAILAP SERVO INTFC FAILYD SERVO POWER FAILYD SERVO INTFC FAILTRIM SERVO INTFC FAIL1/2 FGC INTFC FAIL2/1 FGC INTFC FAIL

4.5.3.2.2 10 Guidance Panel Test

When the last message associated with the FGC Test is displayed, theoperator presses the line select key labeled “SELECT” an additionaltime to advance to the Guidance Panel Test. To initiate the test,the operator presses the line select key labeled “SELECTn when the“1O GUIDANCE PANEL TEST?” message is displayed on the CAS display,as shown in Figure 4-14.7.

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FGC1 IN TEST RFGCS

10 GUIDRNCE PflNEL TEST?

A A A A

AO-2292W

Guidance Panel TestFigure 4-14.7

The first segment of the test verifies that all the pushbutton (PB)annunciators illuminate, as shown in Figure 4-14.8. The operatorobserves the GP and presses the line select key labeled “FAIL” ifthe PB are not lighting individually in order. If the GP isfunctioning properly, the operator presses the line select keylabeled “PASS” and the test advances.

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/ \

MfHNTENflNCE TEST

FGC 1 IN TEST flFGCS

10 GUIDFINCE PRNEL TEST

FILLGP-820 PB LIGHTINDIVIDUFILLYIN ORDER?

NO= FflIL YES= Pf3SS

.

Verification

If the GP failsis displayed onselect key labe-the test.

. vAD-22927#

of Pushbutton Annunciator IlluminationFigure 4-14.8

the test, the “GP-820 PB ANNUNCIATOR FAIL” messagethe CAS display. The operator presses the lineed “SELECT” to acknowledge the failure and advance

The next segment of the test verifies that the displays illuminate,as shown in-Figure 4-14.9. The operator observes the-GP and pressesthe line select key labeled “FAIL” if the displays are not lightingindividually in order. If the GP is functioning properly, theoperator presses the line select key labeled “PASS” and the testadvances.

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FGC 1 IN TEST flFGCS

10 GUIDRNCE PRNEL TEST

9LL GP-820 DISPLRYS LIGHTINDIVIDUFILLY IN ORDER?

NO = FfiIL YES = Pflss

A A A

AD-22928#

Displays IlluminateFigure 4-14.9

If the GP fails the test, the “GP-820 DISPLAY FAIL” message isdisplayed on the CAS display. The operator presses the line selectkey labeled “SELECT” to acknowledge the failure and advance thetest.

The next segment of the test verifies the operation of each GPpushbutton one at a time, in sequence. When the test is initiated,the operator actuates the Autothrottle (A/T) Arm. If the pushbuttonis functioning properly, the test advances to verify the nextpushbutton. If the operator does not actuate the pushbutton within10 seconds from the time the message to do so is displayed, or theGP is not functioning properly, a message is displayed on the CASdisplay that asks if the A/TArm has been actuated. If it has not,the operator presses the line select key labeled “FAIL”. Thiscauses the test to be revisited and gives the operator anotheropportunity to actuate the pushbutton. If the pushbutton has beenactuated, the operator presses the line select key labeled “PASS”.This produces the “A/T ARM FAIL” message to be displayed on the CASdisplay. The operator presses the line select key labeled “SELECT”to acknowledge the failure and to continue with the test.

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The operator is prompted to actuate the following pushbuttons: theSPD, the IAS/MACH, the LVAV, the VNAV, the FL CH, the HDG SEL SYNC,the HDG SEL, the BANK, the BC, theAPR, the V/S, theA/P, the PFD-CMD, the ALT HLD. The procedure discussed above for testing the A/TArm holds true for all other pushbuttons. Uhen this portion of thetest is completed, the GP-820 Test advances to the next segment.

The test advances to verify the items associated with the A/Plocated on the wheel and the throttle. The operator actuates thepilot A/P disconnect switch located on the outboard side of thewheel. If the switch is functioning properly, the test advances toverify the next switch. If the operator does not actuate the switchwithin 10 seconds from the time the message to do so is displayed onthe CAS display, or the switch is not functioning properly, amessage is displayed that asks if the A/P disconnect switch has beenactuated. If it has not, the operator presses the line select keylabeled “FAIL”. This causes the test to be revisited and gives theoperator another opportunity to actuate the switch. If the switchhas been actuated, the operator presses the line select key labeled“PASS”. This produces the “PILOTA/P DISC FAIL” message on the CASdisplay. The operator presses the line select key labeled “SELECT”to acknowledge the failure and continue the test.

The operator is prompted to actuate the following switches, or whereindicated, knobs: the pilot go around, the pilot touch controlsteering, the copilot A/P disconnect, the copilot go around, thecopilot touch control steering, the lamp test, the manual trim, thepilot trim up, the pilot trim down, the copilot trim up, copilottrim down, the vertical speed knob, the heading knob, and the speedknob. The procedure discussed above for testing the pilot A/Pdisconnect switch holds true for all other switches and knobs.

Several messages may appear on the CAS display as a result of theGP-820 Test. The following is a list of messages that may appear.The operator presses the line select key labeled “SELECT” to stepthrough the various messages or continue with the test.

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Cockpit Switches through GPFailures

GUIDANCE PANEL TEST Guidance Panel PushbuttonFailures

A/T ARM PB FAILSPD PB FAILIAS/MACH PB FAILLNAV PB FAILVNAV PB FAILFLCH PB FAILHDG SYNC PB FAILHDG SEL PB FAILBANK PB FAILBC PB FAILAPR PB FAILV/S PB FAILAP PB FAILPFD-CMD PB FAILALT HLD PB FAILPA/PDISC FAILP GO AROUND FAILPTCS FAILCPA/PDISC FAILCP GO AROUND FAILCPTCS FAILLAMP TEST FAILM/TRIM ENG FAILPTRIMUP FAILPTRIMDN FAILCP TRIM UP FAILCP TRIMDN FAIL

GP820 PB ANNUNCIATOR FAIL GP Annunciator/Display FailuresGP820 DISPLAY FAILANNUN VALID FAIL

SPEED KNOB FAIL GP Knob FailuresHDG KNOB FAILV/S KNOB FAIL

Recall, when the test advances, it switches control to the other FGCif installed, and the GP-820 Test is repeated. When both FGCS havebeen tested, the AFGCS Test advances to the manual controllersegment.

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4.5.3.2.3 15 Manual Controller Test

To initiate the Manual Controller Test the operator presses the lineselect key labeled “SELECT” when the “15 MANUAL CONTROLLER TEST?”message is displayed on the CAS display, as shown in Figure 4-14.10.

FGC1 IN TEST f3FGCS

15 Mf3NUflLCONTROLLER TEST?

A A A

AO-22929#

Manual Controller TestFigure 4-14.10

When the test is initiated, the operator moves the thumbwheel. Ifthe thumbwheel is functioning properly, the test advances to verifythe turn knob. If the thumbwheel is not moved within 10 secondsfrom the time the message to do so is displayed, or the thumbwheelis not functioning properly, a message is displayed on the CASdisplay that asks if the thumbwheel has been moved. If it was not,the operator presses the line select key labeled “FAIL”. Thiscauses the test to be revisited and gives the operator anotheropportunity to move the thumbwheel. If the thumbwheel has beenmoved, the operator presses the line select key labeled “PASS”.This produces the “PITCHTHUMBWHEEL #X FAIL” message on the CASdisplay. The operator presses the line select key labeled “SELECT”to acknowledge the failure and continue the test.

The operator is prompted to perform the following tasks to test theturn knob: set the turn knob right, set the turn knob left, centerthe turn knob. The procedure discussed above for testing thethumbwheel holds true for the turn knob.

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Several messages may appear on the CAS display as a result of theManual Controller Test. The following is a list of messages thatmay appear. The operator presses the line select key labeled“SELECT” to step through the various messages or to continue on withthe test. Recall, the test advances to the remaining FGC ifinstalled, and the Manual Controller Test is repeated. When bothFGCS have been tested, the AFGCS Test advances to the elevator servosegment.

MANUAL CONTROLLER TEST Manual Controller Failures

PITCH THUMBWHEEL #1 FAILPITCH THUMBWHEEL #2 FAILTURN KNOB RIGHT#l FAILTURN KNOB RIGHT #2 FAILTURN KNOB LEFT #1 FAILTURN KNOB LEFT #2 FAILTKOUTOF DETENT #1 FAILTKOUTOF DETENT #2 FAILTK CENTER #1 FAILTKCENTER#2 FAIL

4.5.2.3.4 20 Elevator Servo Test

NOTE: Execution of this test will move A/C surfaces.

The Elevator Servo Test verifies the elevator servo motor interface.When the “20 ELEV SERVO TEST?” message is presented on the CASdisplay, as shown in Figure 4-14.11, the operator presses the lineselect key labeled “SELECT” to initiate the test. The operator isinstructed to center the column and depress the A/P button. Theoperator must continue to depress the button until the test iscompleted. If the operator does not, the test aborts.

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{

FGC 1 IN TEST RFGCS

20 ELEV SERVO TEST?

A A AAD-22930#

Elevator Servo TestFigure 4-14.11

Several messages may appear on the CAS display as a result of theElevator Servo Test. The following is a list of messages that mayappear. The operator presses the line select key labeled “SELECT”to step through the various messages or to continue with the test.Recall, when the test advances, it switches control to the remainingFGC if installed, and the Elevator Servo Test is repeated. Whenboth FGCS have been tested, the AFGCS Test advances to the aileronservo segment.

ELEVATOR SERVO TEST Elevator Servo Failures

ELEV CWCMD FAILELEV STOP CMD FAILELEV CCW CMD FAILELEV/AIL X- FEED FAILELEV/RUD X-FEED FAILELEV/TRIM X-FEED FAILTEST ABORTED

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:::W:JANCE

GULFSTRE4M IV

4.5.2.3.5 25 Aileron Servo Test

NOTE: Execution of this test will move A/C surfaces.

The Aileron Servo Test verifies the aileron servo motor interface.When the ‘25AIL SERVO TEST?” message is presented on the CASdisplay, as shown in Figure 4-14.12, the operator presses the lineselect key labeled “SELECT” to initiate the test. The operator isinstructed to center the wheel and depress the A/P button. Theoperator must continue to depress the button until the test iscompleted. If the operator does not, the test aborts.

FGC1 IN TEST IIFGCS

25 FIILSERVO TEST?

A A A, v v

AD-22931#

Aileron Servo TestFigure 4-14.12

Several messages may appear on the CAS display as a result of theAileron Servo Test. The following is a list of messages that mayappear. The operator presses the-line select key labiled “SELECT” tostep through the various messages or to continue with the test.Recall, when the test advances, it switches control to the remainingFGC if installed and the Aileron Servo Test is repeated. When bothFGCS have been tested, the AFGCS test advances to the rudder servosegment.

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AILERON SERVO TEST Aileron Servo Failures

AIL CWCMD FAILAIL STOPCMD FAILAIL CCWCMD FAILAIL/ELEV X-FEED FAILAIL/RUDX-FEED FAILAIL/TRIMX-FEED FAILTEST ABORTED

4.5.2.3.6 30 Rudder Servo Test

~: Execution of this test will move A/C surfaces.

The Rudder Servo Test verifies the rudder linear actuator interface.When the “30 RUD SERVO TEST?” message is presented on the CASdisplay, as shown in Figure 4-14.13, the operator presses the lineselect key labeled “SELECTnto initiate the test. The operator isinstructed to apply flight hydraulics then press the line select keylabeled “SELECT”. The operator is next instructed to center thepedals and depresses the Y/D button. The operator must continue todepress the button until the test is completed. If the operatordoes not, the test aborts.

FGC 1 IN TEST flFGCS

30 RUD SERVO TEST?

A A A. . .

AD-22932#

Rudder Servo TestFigure 4-14.13

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Several messages may appear on the CAS display as a result of theRudder Servo Test. The following is a list of messages that mayappear. The operator presses the line select key labeled “SELECT”to step through the various messages or to continue with the test.Recall, when the test advances, it switches control to the remainingFGC and the Rudder Servo Test is repeated. Nhen both FGCS have beentested, the AFGCS Test advances to the pitch trim servo segment.

RUDDER TEST Rudder Actuator Failures

(X)RUD POSCMD FAILRUD STOP CMD FAIL(X)RUDNEGCMD FAILRUD/ELEV X-FEED FAILRUD/AIL X-FEED FAILRUD/TRIM X-FEED FAILTEST ABORTED

4.5.2.3.7 35 Pitch Trim Servo Test

NOTE: Execution of this test will move A/C surfaces.

The Pitch Trim Servo Test verifies the pitch trim servo motorinterface. When the “35 PITCH TRIM SERVO TEST?” message ispresented on the CAS display, as shown in Figure 4-14.14, theoperator presses the line select key labeled “SELECT” to initiatethe test. The operator is instructed to set trim to zero anddepress the A/P button. The operator must continue to depress thebutton until the test is completed. If the operator does not, thetest aborts.

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FGC 1 IN TEST flFGCS

35 PITCHTRIM SERVO TEST?

A A A

AD-22934#

Pitch Trim Servo TestFigure 4-14.14

Several messages may appear on the CAS display as a result of thePitch Trim Servo Test. The following is a list of messages that mayappear. The operator presses the line select key labeled “SELECT” tostep through the various messages or to continue with the test.Recall, the test advances to the remaining FGC if installed, and thePitch Trim Servo Test is repeated. When both FGCS have been tested,the AFGCS Test advances to the cockpit switches segment.

PITCH TRIM SERVO TEST Pitch Trim Servo Failures

(X)TRIM DNCMD FAILTRIM STOP CMD FAIL(X)TRIM UPCMD FAILTRIM UP LIMIT FAILTRIMDN LIMIT FAILTEST ABORTED

4.5.3.2.8 40 Cockpit Switches Test

To initiate the Cockpit Switches Test the operator presses the lineselect key labeled “SELECT”, when the “40 COCKPIT SHITCHES TEST?”message is displayed on the CAS display, as shown in Figure 4-14.15.

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FGC 1 IN TEST flFGCS

40 COCKPIT SW TEST?

A A A 4.

AD-z2933#

Cockpit Switches TestFigure 4-14.15

The Cockpit Switches Test verifies the switches wired to the FGC.The operator actuates the pilot A/P disconnect switch located on theoutboard side of the wheel. If the switch is functioning properly,the test advances to verify the next switch. If the operator doesnot actuate the switch within 10 seconds from the time the message todo so is displayed on the CAS display, or the switch is notfunctioning properly, a message is displayed that asks iftheA/Pdisconnect switch has”been actuated. If it has not, the operatorpresses the line select key labeled ‘FAIL”. This causes the test tobe revisited and gives the operator another opportunity to actuatethe switch. If the switch has been actuated, the operator pressesthe line select key labeled “PASS”. This produces the “PILOT A/PDISC FAIL” message on the CAS display. The operator presses the lineselect key labeled ‘SELECT” to acknowledge the failure and continuethe test.

The operator is prompted to actuate the following switches: the Y/Dengage, the Trim engage, the pilot trim up, the pilot trim down, thecopilot A/P disconnect, the copilot trim up, and the copilot trimdown. The procedure discussed above for testing the pilotA/Pdisconnect switch holds true for all other switches. When thisportion of the test is completed, the Cockpit Switches Test advancesto verify various annunciators.

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This segment asks the operator several questions concerning theoperation of the A/P, Y/D and M/Trim annunciators.

The operator verifies that the A/P off annunciator is flashing. Ifit is flashing, the operator presses the line select key labeled“PASSN and the test advances. If it is not, the operator pressesthe line select key labeled “FAIL”. This produces a fail message.The operator presses the line select key labeled “SELECT” toacknowledge the failure and to continue with the test. The operatorverifies the A/P off horn in the same fashion.

Next the operator is instructed to watch the Y/D disengageannunciator to determine if it cycles off and then on. If theannunciator cycles, the operator presses the line select key labeled‘pASS” and the test advances. If it does not, the operator pressesthe line select key labeled “FAIL”. This produces a fail message.The operator presses the line select key labeled “SELECT” toacknowledge the failure and to continue with the test. The operatorverifies the M/Trim annunciator in the same fashion.

Status or error messages are displayed on the CAS display as aresult of the Cockpit Switches Test. The following is a listmessages that may appear. The operator presses the line select keylabeled “SELECT” to step through the various messages or to continueon with the test. Recall, the test advances to the remaining FGC ifinstalled, and the Cockpit Switches Test is repeated. When bothFGCS have been tested, the AFGCS Test advances to the subsystemstatus segment.

COCKPIT SWITCHES TEST Cockpit Switches Failures

PA/PDISC FAILP Y/D ENG FAILM/TRIM ENG FAILPTRIM UP FAILPTRIM DN FAILCPA/P DISC FAILCP TRIM UP FAILCPTRIMDN FAILA/P OFF ANNUN FAILA/POFF HORN FAILY/D DISENGAGE ANNUN FAILM/TRIM DISENG ANNUN FAIL

Annunciator Failures

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4.5.3.2.9 45 Subsystem Status Test

When the last message associated with the Cockpit Switches Test isdisplayed, the operator presses the line select key labeled “SELECTan additional time to advance to the Subsystem Status Test. Toinitiate the test the operator presses the line select key labeled“$ELECT” when the “45 SUBSYSTEM STATUS TEST?” message is displayedon the CAS display, as shown in Figure 4-14.16. The operatorpresses the line select key labeled “SELECT” to step through themessages or continue with the test. Typical CAS displays for theAFGCS Subsystem Status Test are shown in Figure 4-14.17 and Figure4-14.18.

FGC 1 IN TEST flFGCS

45 SUBSYSTEM STRTUS TEST?

A A A

AD-22935#

Subsystem Status TestFigure 4-14.16

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* >

FGC 1 IN TEST FIFGCS

45 SUBSYSTEM STfiTUSTEST

1 PREFLIGHT TEST PRSS

PRESS SELECT TO CONTINUEA A A

AD-22936#

Typical CAS Display for the AFGCS Subsystem Status Test(Preflight Test Pass)

Figure 4-14.17

*

FGC 1 IN TEST RFGCS

45 SUBSYSTEM STFITUSTEST

1 Pllss

PRESS SELECT TO CONTINUEA A A

.AD-22937#

Typical CAS Display for the AFGCS Subsystem Status Test(Pass)

Figure 4-14.18

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The following is a list of messages that may appear as a result ofexecuting the Subsystem Status Test.

SUBSYSTEM STATUS TEST Sensor Validation Failures

IRS/ FGC INTFC FAILDADC/ FGC INTFC FAILL EFIS X) FGC INTFC FAIL

[R EFIS X) FGC INTFC FAIL

4.5.3.2.10 50 Flight Fault Summary

When the last message associated with the Subsystem Status Test isdisplayed, the operator presses the line select key labeled “SELECT”an additional time to advance the test to the Flight Fault Summary,as shown in Figure 4-14.19. To display the Flight Fault Sunwnaryonthe CAS display, the operator presses the line select key labeled‘SELECTW when the “50 Flight Fault Sununary?”message is displayed.The operator should record the alpha-numeric codes. A typical CASdisplay of Flight Fault Summary data for a -905 or -906 FGC is shownin Figure 4-14.20. Refer to Appendix C for a description of thealpha-numerical codes. Refer to Appendix G for a description of thedisplay of Flight Fault Summary Non-Volatile RAM (NVR) data availablefrom a -907 Flight Guidance Computer. In the event the NVR data isunavailable, the data will default to alpha-numeric codes of the lastfailure, as shown in Figure 4-14.20. The operator presses the lineselect key labeled ‘SELECTn to display the Flight Fault Sunuoarydataon the CAS display for the remaining FGC. The operator presses theline select key labeled “SELECT” to advance to the ground summarysegment.

AF6CS

F6C1IIITUT 54 F11611TFAIILTSIJiOIARY?

bmmw

Flight Fault SummaryFigure 4-14.19

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MAINTENANCETEST

AF6C5

FGC1 IN TUT 50 FL1611TFAULTSIJHIURY0000 0000 0000 00000000 00000000 00000000

000000000000000000000000

Typical CAS Display of Flight Fault Summary DataFigure 4-14.20

4.5.3.2.11 55 Ground Test Summary

The Ground Test Summary allows the operator to review all the failmessages that resulted from the AFGCS Maintenance Test. To displaythe Ground Test Summary messages on the CAS display, the operatorpresses the line select key labeled “SELECT” when the “55 GROUNDTEST SUMMARY?” message is displayed, as shown in Figure 4-14.21.The operator presses the line select key labeled “SELECT” to stepthrough the messages. The messages are explained in theirrespective sections. When all the messages have been displayed,the AFGCS Test advances to the FGC Test. To return to the SystemTest Menu, the operator presses the line select key labeled“RETURN”.

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FGC 1 IN TEST flFGCS

55 GROUND TEST SUMMFIRY?

AD-22940#

Ground Test SummaryFigure 4-14.21

4.5.3.2.12 Recommended Maintenance Action

The following is a list of messages associated with maintenancetest and recommended action.

05 FGC Test:

Messaue Action

(X) AFCSSERVOPWR OFF 1. Verify Stab Aug Servo Power/Grid(X) YD SERVO POWER FAIL 31A-1, 2.(X) YDSERVOINTFC FAIL 2. Replace FGC.(X) TRIM SERVO INTFC FAIL1/2 (2/1) FGC INTFC FAIL

(X) AFCS SERVO POWER OFF 1. Verify AP Servo Power/GridJIA-4, 5.(X) AP SERVO POWER FAIL 2. Replace FGC.(X) AP SERVO INTFC FAIL

(X) AFCS SERVO POWER OFF 1. Verify AP Servo Power/GridJIA-4, 5.(X) AP SERVO INTFC FAIL 2. Verify Stab Aug Servo Power/Grid(X) YD SERVO POWER FAIL JIA-1, 2.(X) YD SERVO INTFC FAIL 3. Verify primary ASCB Bus Input(X) TRIM SERVO INTFC FAIL JIB-1, 2.(X) A/B PROCESSOR INTFC 4. Replace FGC.

FAIL

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05 FGC Test (cent):

!&!SALE Action

(X) AP SERVO INTFC FAIL If the AP Disconnect is OK, thenperform the aileron and elevator servotests to isolate possible servo wiringinterface problems. If wiring OK,replace FGC.

(X) TRIM SERVO INTFC FAIL 1. ~f~ifiT~~ServoTach Input

2. Verify’trim servo drive outputJ2A-59, 60.

3. Verify trim disconnect inputJ2B-66.

4. Replace FGC.

(X) AP SERVO INTFC FAIL Check to see if the left or rightA/P(X) TRIM SERVO INTFC FAIL disconnect switch is stuck open or the

ground to the switch is missing. Ifwiring and power OK, then replace theFGC.

(X) AP SERVO INTFC FAIL Verify emergency disconnect J2B-65.(X) YD SERVO INTFC FAIL(X) TRIM SERVO INTFC FAIL(X) A/B PROCESSOR INTFC FAIL

1/2 FGC INTFC FAIL 1. Verify secondary ASCB Bus J2B-1, 2.2/1 FGC INTFC FAIL 2. Verify priority status J1B-102,(X) A/B PROCESSOR 103, 106, JIA-58.INTFC FAIL 3. Verify wiring J2A-43 thru 48, 63

J2B-1, 2, 96 thru 101.

(X) YD SERVOINTFC FAIL Verify wiring J2B-67.

ACFT CONFIGPIN Check the following aircraft pins:1OJ1B-76, 77, 78, 79, 80, 81.If wiring OK, replace the FGC.

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05 FGC Test (cent):

- Action

1/2 FGC INTFC FAIL Verify the wiring interface between2/1 FGC INTFC FAIL Both FGCS for:A/B PROCESSOR JIA-58 YAW DAMP ENGAGE (28 V/OPEN)INTFC FAIL J2A-41 AP CROSS PWR SENSE IN

J2A-42 AP CROSS PWR SENSE OUTJ2A-43 STABAUG PWR SENSE INJ2A-44 STABAUG PWR SENSE OUTJ2A-45 CROSS SERVO PWR SENSE INJ2A-46 CROSS SERVO PWR SENSE OUTJ2A-47 CROSS SERVOS OFF INJ2A-48 CROSS SERVOS OFF OUTJ2A-61 AILERON AND ELEVATOR CLUTCH

DRIVESJ2A-63 TRIM CLUTCH DRIVEVerify secondary ASCB bus inputJ2B-1,2.Verify priority status J1B-102, 103,106, JIA-58.VerifyA/Cwiring J2B-96 thru 101.If wiring OK, then replace FGC.

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10 Guidance Panel Test:

Messaqe Action

~: If digits flash erratic on GP, no switches will input to theFGC. VerifyA/C wiring 10/C10J2B-106.

A/T ARM PB FAIL Replace Guidance Panel.SPD PB FAIL Replace Guidance Panel.IAS/MACH PB FAIL Replace Guidance Panel.LNAV PB FAIL Replace Guidance Panel.VNAV PB FAIL Replace Guidance Panel.FLCH PB FAIL Replace Guidance Panel.HDG SYNC PB FAIL Replace Guidance Panel.HDG SEL PB FAIL Replace Guidance Panel.BANK PB FAIL Replace Guidance Panel.BC PB FAIL Replace Guidance Panel.APR PB FAIL Replace Guidance Panel.V/S PB FAIL Replace Guidance Panel.AP PB FAIL Replace Guidance Panel.PFD-CMD PB FAIL Replace Guidance Panel.ALT HLD PB FAIL Replace Guidance Panel.

A/P DISC FAIL Pushing the A/P disconnect switchesopens ground logic to the guidance panelJ1-77, J2-77, to the #1 and #2 FlightGuidance Computers J2B-54, 66 and to the#1 and #2 Fault Warning ComputersJIA-80. If the message appears withoutprompting to push the switch, the logicis already open. Verify the A/C wiring.If the message appears after the test(pushing the switch) check the switches.

P(CP) GA DISCONNECT Check the pilot’s (copilot’s) TO/GAswitch and the appropriate wiring.Pushing the switch provides ground logicto the Guidance Panel llJ1-72 (11J2-54).If switch and wiring are OK, thenreplace the Guidance Panel.

P(CP) TCS DISCONNECT Check the pilot’s (copilot’s) TCS switchand the appropriate wiring. Pushing theswitch provides ground logic to theGuidance Panel llJ1-74 (11J2-53). Ifswitch and wiring are OK, then replacethe Guidance Panel.

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10 Guidance Panel Test (cent):

!kssiME Action

LAMP TEST FAIL Check the 1amp test switch and theappropriate wiring. Pushing the switchprovides ground logic to the GuidancePanel llJ1-64, 11J2-64. If switch andwiring are OK, then replace the GuidancePanel.

Y/D ENG FAIL

M/TRIMENGFAIL

Check the yaw damper engage switch andthe appropriate wiring. Pushing theswitch opens ground logic to theGuidance Panel llJ1-78, 11J2-78 and tothe Flight Guidance Computers 1OJ1A-4O,C1OJ1A-4O. If switch and wiring are OK,then the problem could be with eitherthe Guidance Panel or the FlightGuidance Computer.

Check the trim engage switch and theappropriate wiring. Pushing the switchopens ground logic to the Guidance PanelllJ1-79, 11J2-79 and to the FlightGuidance Computers 1OJ1A-41, C1OJ1A-41.If switch and wiring are OK, then theproblem could be with either theGuidance Panel or the Flight GuidanceComputer.

PTRIMUP (DN) FAIL Check the respective trim up/down switchCP TRIM UP (DN) FAIL and the appropriate wiring. Pushing the

switch provides ground logic to theFlight Guidance Panel (J1-44, 51, 56,65, J2-44, 51, 56, 65) and the FlightGuidance Computers (JIA-33, 47, JIB-85,86). Refer to Figure D.1.6 in AppendixD, of the Interconnect (Section 6)portion of the Maintenance Manual. Ifthis test does not indicate any failure,but the trim servo does not move, go totest #35 pitch trim servo test.

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10 Guidance Panel Test (cent):

- Action

GP820 PB Check wire from the Guidance PanelANNUNCIATOR FAIL llJ1-38 to the #1 FGC 1OJ2B-106 and from

the Guidance Panel llJ2-38to the #2 FGCC1OJ2B-106. VerifyA/Cwiring J2B-102,103. If wiring is OK, problem could bewith either the Guidance Panel or theFlight Guidance Computer.

GP820 DISPLAY FAIL VerifyA/C wiring J2B-102, 103. Replacethe Guidance Panel.

ANNUN VALID FAIL Check wire from the Guidance PanelllJ1-69 to the #1 FGC 1OJ2B-89 and fromthe Guidance Panel 11J2-69 to the #2 FGCC1OJ2B-89. VerifyA/C wiring J2B-102,103. If wiring is OK, problem could bewith either the Guidance Panel or theFlight Guidance Computer.

SPEED KNOB FAIL

HDG KNOB FAIL

V/S KNOB FAIL

Check wires from the Guidance PanelllJ1-24, 25 to the #1 FGC 1OJ1B-7, 8 andfrom the Guidance Panel 11J2-24, 25 tothe #2 FGC C1OJ1B-7, 8. If wiring isOK, problem could be with either theGuidance Panel or the Flight GuidanceComputer.

Check wires from the Guidance PanelllJ1-26, 27 to the #1 FGC 1OJ1A-18, 19and from the Guidance Panel 11J2-26, 27to the #2 FGC C1OJ1A-18, 19. If wiringis OK, problem could be with either theGuidance Panel or the Flight GuidanceComputer.

Check wires from the Guidance PanelllJ1-28, 29 to the #1 FGC 1OJ1B-11, 12and from the Guidance Panel 11J2-28, 29to the #2 FGCC1OJ1A-11, 12. If wiringis OK, problem could be with either theGuidance Panel or the Flight GuidanceComputer.

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15 Manual Controller Test:

Messaae Action

PITCH THUMBWHEEL Check wires from the manual controller#1 FAIL (J1-18, 19, 21, 22) to both FGCPITCH THUMBWHEEL (10/C10J2B-94, 95, 104, 105).#2 FAIL If wiring is OK, problem could be with

either the manual controller or eitherFlight Guidance Computer.

TURN KNOB RIGHT Check wires from the manual controller#1 FAIL (J1-1 thru 4, 11 thru 14) to both FGCSTURN KNOBRIGHT (10/C10J2B-55 thru 58, 60). If wiring#2 FAIL is OK, problem could be with either the

manual controller or either FlightGuidance Computer.

TURN KNOB LEFT #1 Same as turn knob right fail.FAILTURN KNOB LEFT #2FAIL

TK OUT OF DETENT Check the turn control detent switch#1 FAIL interface between the manual controllerTK OUT OF DETENT (J1-6, 8, 15, 17) and the FGC#2 FAIL (10/C10J2B-59, 61). If wiring is OK,TK CENTER #1 FAIL then replace the appropriate FGC.TK CENTER #2 FAIL

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ELEV STOP CMDFAIL

ELEV/AIL X-FEEDFAILELEV/RUD X-FEEDFAILELEV/TRIM X-FEEDFAIL

20 Elevator Servo Test:

Messaue Action

ELEV CWCMD FAIL OPTION 1: If both messages occur, theELEV CCWCMD FAIL servo drive wiring or the servo tach

wiring could be reversed; the servocould be disconnected or the surfacecontrols have excessive friction.

●VerifyA/CwiringJlB-68, 69, J2A-55,56. The FGC will reveal moreinformation and recommendations.

OPTION 2: If only one of these messagesoccurred, it is possible that a servotach wire is missing or there isexcessive friction in one direction.Repeat the test to ensure that thecontrol column wasn’t bumped during thetest.

OPTION 3: Replace the FGC or Servo.

Check to see that there is no noise onthe elevator servo tach input to theFGC. Verify servo free to move. If noexcessive noise is present, replace theappropriate FGC.

These three messages indicate thatduring the elevator servo test, the FGCsaw movement from these other servos.For aileron and rudder X-feed. Repeatthe elevator servo test, chances arethat the column or surfaces could havebeen bumped. If the failure(s) persist,then check the wiring interface from theFGC to the servos. If the wiring is OK,then replace the appropriate FGC. Fortrim X-feed, replace the FGC.

AP Eng Switch was not depressed untilend of test.

TEST ABORTED

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25 Aileron Servo Test:

AIL CWCMD FAILAIL CCWCMD FAIL

AIL STOP CMD FAIL

AIL/ELEVX-FEEDFAILAIL/RUD X-FEEDFAILAIL/TRIM X-FEEDFAIL

TEST ABORTED

Action

See AFCS ELE CW CMD Fail, but verifyA/Cwiring JIB-70, 71, J2A-57, 58.

See AFCS Elev Stop CMD Fail.

These three messages indicate thatduring the aileron servo test, the FGCsaw movement from these other servos.For rudder and elevator X-feed repeatthe aileron servo test. Chances arethat the column or surfaces could havebeen bumped. If the failure(s) persistthen check the wiring interface from theFGC to the servos. If the wiring is OK,then replace the appropriate FGC.

AP Eng switch was not depressed untilend of test.

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Honeywell ###!&wcE

30 Rudder Servo Test:

Messaae

RUD POS CMO FAILRUD NEG CMD FAIL

RUD STOP CMD FAIL

RUD/ELEV X-FEEDFAILRUD/AIL X-FEEDFAILRUD/TRIM X-FEEDFAIL

TEST ABORTED

Action

Verify that the rudder actuator isconnected. Then check the wiringinterface between the FGC (10/CIOJIA-59thru 64) and the rudder actuator. Ifwiring is OK, replace the appropriateFGC or rudder actuator.

NOTE: These message are sometimesdisplayed with good systems dueto actuator tolerances.

See AFCS Elev Stop CMD Fail. Verifyactuator is free to move.

These three messages indicate thatduring the rudder servo test, the FGCsaw movement from these other servos.For aileron and elevator X-feed repeatthe rudder servo test. Chances are thatthe column or surfaces could have beenbumped. If the failure(s) persist, thencheck the wiring interface from the FGCto the servos. If the wiring is OK,then replace the appropriate FGC. Fortrim X-feed, replace appropriate FGC.

YD Eng switch was not depressed untilend of test.

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35 Pitch Trim Servo Test:

Messaqe Action

TRIM UP(DN) CMD If the trim servo moved in the oppositeFAIL direction as indicated by the advisory

display, then check the polarity of thepitch trim wiring between the FGC andthe trim servo. If the FGC testindicated no failures, but the trimservo did not move, then 1) verify thatthe servo is connected, 2) check to seeif the trim servo is beyond its limitswitches, or 3) verify that all wiringis in place (10/CIOJIB-44, 72, 73,J2A-59, 60, J2B-44, 45, 46, JIA-22).

TRIM STOP CMD FAIL Verify servo is free to move.;: Replace appropriate FGC.

TRIM UP(DN) LIMIT 1. Verify that the trim servo bracketis connected.

2. Verify that all wiring is in placebetween trim servo bracket and FGC.

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40 Cockpit Switches Test:

Messaue Action

A/P DISC FAIL Check the pilot’s AP disconnect switch,and appropriate wiring.

P Y/D ENG FAIL 1. Verify wire interface to FGC.M/TRIM ENG FAIL 2. Replace FGC.

P TRIM UP(DN) FAIL 1. Check the pilot’s trim switch andassociated wiring.

2. Replace the appropriate FGC.

CPA/P DISC FAIL Check the copilot disconnect switch, andappropriate wiring.

CP TRIM UP(DN) 1. Check the copilot’s trim fail switchand associated wiring.

2. Replace the appropriate FGC.

A/POFFANNUN FAIL Check light bulb.

A/POFF HORN FAIL Verify wiring to annunciator (horn).

Y/D DISENG ANNUN Check light bulb.FAIL

M/TRIM DISENG ANNUN Check light bulb.FAIL

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45 Subsystem Status Test:

!!kssxE Action

IRS/FGC INTFC The IRS interface is checked via theFAIL ASCB. The FGC checks for a valid

transmission from the IRS and checks forvalid IRS data. If the failure occurs,first check the appropriate IRScomputer. If the problem still exists,then check the ASCB wiring, if other LRUinterface failure messages haveoccurred, chances are the FGC is notcommunicating on the ASCB or the ASCBwiring at the FGC has failed.

See IRS/FGC Intfc Fail Message, butreference DADC in place of IRS.

DADC/FGCINTFC FAIL

L EFIS/(X)FGCINTFC FAILR EFIS/(X)FGCINTFC FAIL

1. Check power to SG 1 (2).2. Check SG reversionary panel status

gridsfrom overhead panel.3. Check ASCB interconnects.

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4.6 Summarv Test

When the System Test Menu is displayed on the Display Controller (DC)Cathode Ray Tube (CRT) as shown in Figure 4-15, the operator initiates theSummary Test by pressing the line select key labeled “SUMMARY”. ThisDroduces the Summary Line Re~laceable Unit (LRU) Menu to smear on the DC. .CRT as shown in Fig~re 4-16.”

EDS

SYSTEM CHECK FMS/PMS

AFGCS SUMMARY

[1===[I=;j======[l=~;======

System Test MenuFigure 4-15

mMENU SELE;!

DOWNRETURN

LRU Test MenuFigure 4-16

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

AD-22803 #

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4.6.1 General Operation

The operator selects, initiates, and provides feedback for the SummaryTest through the DC.

When the LRU Test Menu is displayed on the DC CRT, the operatorinitiates the Automatic Flight Guidance Control System (AFGCS) StatusSummary, the option highlighted on the Crew Alerting System (CAS)display (Figure 4-17), by pressing the line select key labeled “SELECT”.The resulting status or error messages appear on the CAS display.

To proceed with the Summary Test, the operator presses line select keylabeled “MENU”. This advances the test to the Sensors Summary, theoption highlighted on the CAS display. To initiate the test, theoperator presses the line select key labeled “SELECT”. To review themessages associated with the Inertial Reference System (IRS), theoperator presses the line select key labeled “SELECT”. The messagesindicate the outcome of the tests. If the operator did not execute aparticular test or did not enter whether the test passed or failed, themessage consists of the title of the test followed by a question mark.

To continue with the test the operator presses the line select keylabeled “MENU”. This advances the menu to the Digital Air Data Computer(DADC) Summary. To review the messages associated with the DADC, theoperator presses the line select key labeled “SELECT”. The messagesindicate the outcome of the tests. If the operator did not execute aparticular test or did not enter whether the test passed or failed, themessage consists of the title of the test followed by a question mark.

1) AFGCS STATUS SUMMARY

2) SENSORS SUMMARY3) EDS SUMMARY4) FMS/PMS SUMMARY

CAS DisplayFigure 4-17

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To proceed with the Summary Test, the operator presses line select keylabeled “MENU” twice. This advances the test to the Electronic DisplaySystem (EDS) Summary, the option highlighted on the CAS display. Toinitiate the test, the operator presses the line select key labeled“SELECT”. To review the messages associated with the DC, the operatorpresses the line select key labeled “SELECT”. The messages indicate theoutcome of the tests. If the operator did not execute a particular testor did not enter whether the test passed or failed, the message consistsof the title of the test followed by a question mark.

To continue with the test the operator presses the line select keylabeled “MENU”. This advances the test to the Symbol Generator (SG).To review the messages associated with the SG, the operator presses theline select key labeled “SELECT”. The messages indicate the outcome ofthe tests. If the operator did not execute a particular test or did notenter whether the test passed or failed, the message consists of thetitle of the test followed by a question mark.

To continue with the test the operator presses the line select keylabeled “MENU”. This advances the test to the Data Acquisition Unit(DAU). To review the messages associated with the DAU, the operatorpresses the line select key labeled “SELECT”. The messages indicate theoutcome of the tests. If the operator did not execute a particular testor did not enter whether the test passed or failed, the message consistsof the title of the test followed by a question mark.

To continue with the test the operator presses the line select keylabeled “MENU”. This advances the test to the Fault Warning Computer(FWC). To review the messages associated with the FWC, the operatorpresses the line select key labeled ‘SELECT”. The messages indicate theoutcome of the tests. If the operator did not execute a particular testor did not enter whether the test passed or failed, the message consistsof the title of the test followed by a question mark.

To continue with the test the operator presses the line select keylabeled ‘MENU”. This advances the test to the Display Unit (DU). Toreview the messages associated with the DU, the operator presses theline select key labeled ‘SELECT”. The messages indicate the outcome ofthe tests. If the operator did not execute a particular test or did notenter whether the test passed or failed, the message consists of thetitle of the test followed by a question mark.

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To proceed with the Summary Test, the operator presses the line selectkey labeled “MENU” twice. This advances the test to the F1ightManagement System/perfo~ance Management System (FMS/PMS) Summary, theoption highlighted on the CAS display. To initiate the test, theoperator presses the line select key labeled “SELECT”.To review themessages associated with the FMS> the operator presses the line selectkey labeled “SELECT”. The messages indicate the outcome of the tests.If the operator did not execute a particular test or did not enterwhether the test passed or failed} the message consists of the title ofthe test followed by a question mark.

To continue with the test the operator presses the line select keylabeled ‘MENU”. This advances the test to the PMS.

To proceed with the SunnnaryTest, the operator presses the line selectkey labeled “MENU” twice. This advances the test to the AFGCS StatusSummary, the option highlighted on the CAS display. To return to the$::~w~est Menu, the operator presses the line select key labeled

.

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APPENDIX ALIST OF TESTS AVAILABLE FOR MAINTENANCE TEST

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APPENDIX ALIST OF TESTS AVAILABLE FOR MAINTENANCE TEST

The following is a list of the tests available forMaintenance Test.

I. System Check

II. Electronic Display System (EDS)

A. Display Controller (DC)

~: %~~u%~on Test3. Software Mod Level Test

B. Symbol Generator (SG)

1. Status Test2. Software Mod Level Test3. SG 1 ASCB Test4. SG 2 ASCB Test5. SG 3 ASCB Test

c. Data Acquisition Unit 1 (DAU1)

1. Status/Software Test

D. Data Acquisition Unit 2 (DAU2)

1. Status/Software Test

E. Fault Warning Computer (FWC)

1. Status Test2. Software Mod Level Test3. Checklist4. Cross-Side ASCB Test5. EEPROM Bit Test

F. Display Unit (DU)

Status Test;: Pilot DUS Test3. EICAS DUS Test4. Copilot DUS Test

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III. Sensor

A. Inertial Reference System (IRS) Test

Status Test;: Fault Summary Test

B. Digital Air Data Computer (DADC) Test

. Status Test;. Configuration Test3. Fault Summary Test4. DADC 1 Output Test5. DADC 2 Output Test

IV. Flight Management System/Performance Management System(FMS/PMS)

A. Flight Management System (FMS)

FMS 1 Status Test;: FMS 2 Status Test3. FMS 1 Configuration Test4. FMS 2 Configuration Test5. Software Mod Level Test

B. Performance Management System (PMS)

1. Perf 1 Status Test2. Perf 2 Status Test3. AT 1 Status Test4. AT 2 Status Test5. Perf Configuration Test6. AT Configuration Test7. PLA Position8. AT Switches9. AT 1 Servo Test

10. AT 2 Servo Test

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v. Automatic Flight Guidance Control System (AFGCS)

A. Status Test

B. System Test

Flight Guidance Computer (FGC) 05:: Guidance Panel (GP) Test 103. Manual Controller Test 154. Elevator Servo Test 205. Aileron Servo Test6. Rudder Servo Test ;;7. Pitch Trim Test 358. Cockpit Switches Test 409. Subsystem Status Test 4510. Flight Fault Summary Test 5011. Ground Test Summary Test 55

VI. Summary Test

B. Sensor Summary

:: I%c

c. EDS

;: !;3. DAU4. FWC5. DU

D. FMS/PMS

1. FMS2. PMS

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APPENDIX CFLIGHT FAULT SUMMARY DESCRIPTION

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APPENDIX CFLIGHT FAULT SUMMARY DESCRIPTION

FGC FLIGHT FAULT SUMMARY (TEST 50)

The FLIGHT FAULT SUMMARY (FFS) is a collection of fault data words that arestored in RAM in the FGC. These data words (16 Bit Words) are displayed inhexadecimal format on the CAS Display. These fault data words will store powerup failures, monitor trips, engage state conditions for automatic disconnects,and hardware failures.

NOTE: The FFS can be accessed only through Maintenance Test.

Fault Data Word Descric)tion

The flight fault summary words are briefly described here.

1. MONFLAGA, MONFLAGB, AUTODISC, TRIPDSNG

These words store which autopilot, yaw damper, or math trim monitor wastripped. MONFLAGA represents “A” processor monitors and MONFLAGB,TRIPDSNG, and AUTODISC represent “B” processor monitors. MONFLAGA containsPerformance Monitor Flags. MONFLAGB contains Servo and FZ Monitor Flags.AUTODISC/TRIPDSNG contain the Trim Monitor Flags.

2. HWFAIL

This word stores which hardware monitor was tripped.

3. FENGTSTA, FENFGSTB

These words represent a “snapshot” of all the engage state conditions thatexisted when the AP, YD, or M-Trim automatically disengaged. (These arekey words when investigating the Servo Switching Monitor.)

4. MAINIA, MAIN2A, MAIN3A, MAINIB, MAIN2B, MAIN3B

When the FGC goes through an “on - ground” power up it does a series oftests. Should any of these tests fail, the type of failure is stored inthese words.

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FGC FLIGHT FAULT SUMMARY APPENDIX C

Hexadecimal Format

Shown is the hexadecimal characters and their binary equivalent.

Hex Value Binarv Value Hex Value Binarv Value

o

:34567

0000

0001001000110100010101100111

8 10009 1001A 1010B 1o11c 1100D 1101E 1110F 1111

Examr)les

MONFLAGA = 0802 = 0000 1000 0000 0010\

bit 15) bit O

Bits 11 and 1 were set. Look at the table for MONFLAGA to determine whichmonitors were tripped.

HWFAIL = 4217 = 0100 0010 0001 0111\

bit 15Z bit O

Bits 14, 9, 4, 2, 1, and O were set. Look at the table for HWFAIL to determinewhich hardware failures occurred.

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FGC FLIGHT FAULT SUMMARY APPENDIX C

CAS DISPLAY

LINE 1: 50 FLIGHT FAULT SUMMARY

LINE 2: 0000 0000 0000 0000

LINE 3: 0000 00000000 00000000

LINE 4: 000000000000 000000000000

MNEMONIC FORMAT

LINE 2: MONFLAGA HWFAIL FENGTSTA (2 words)

LINE 3: MONFLAGB AUTODISC/TRIPDSNG (2 words) FENGTSTB (2 words)

LINE 4: MAIN1A-MAIN2A-MAIN3A MAIN1B-MAIN2B-MAIN3B

WORD/BIT FORMAT

LINE 2: 0000 0000 0000 0000(bits15-0) (bits 15-0) (bits 31-0)

LINE 3: 0000 00000000 00000000(bits 15-0) (bits 31-0) (bits 31-0)

LINE 4: 0000-0000-0000 0000-0000-0000(15-0,15-0,15-0) (15-0,15-0,15-0)

Fault Data Tables

Following are the Fault Data Tables which list each bit of all the displayedhexadecimal data on the Flight Fault Summary. The recommended actionsreferenced can be found in Appendix D “Recommended Actions for Flight FaultSummary”.

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FGC FLIGHT FAULT SUMMARY APPENDIX C

MONFLAGA (LINE 2, WORD 1)

BIT NO. PERFORMANCE MONITOR (MNEMONIC) RECOMMENDED ACTION

15 SPARE14 SPARE13 SPARE12 SPARE11 MFRUDMO-RUDSERVOMOTIONFAIL10 MFELVMOT-ELEVSERVO MOTION FAIL9 MFAILMOT-AILSERVOMOTION FAIL8 MFYDCLO-Y/D CLOSURE FAIL7 MFROLCLO-ROLL CLOSURE FAIL6 MFPITCLO-PITCH CLOSURE FAIL5 MFVALYD-YD VALIDITY FAIL4 MFSFBAI-AIL SERVO FB FAIL3 MFSFBEL-ELEV SERVO FB FAIL2 MFAZLMM-NORMACCEL LIMITS FAIL

SPARE: MTRSAMP-TRIM SERVO AMP FAIL

HW FAIL (LINE 2, WORD 2)

BIT NO. MONITOR/VALID (MNEMONIC)

15 SPARESPARE

i: SPARE12 TKTFAILA-TICKET FAILURE DISENGAGE/FAIL FLAG A.1511 EXHBRSTB-B-PROCHEART BEAT FAIL A.1510 ISOERR - +5V 1S0 FAIL A.14

ADOFFERR-A/D OFFSET FAIL A.14: GNDERR-A/D GND INPUT FAIL A.147 NEG15ERR-A/D -15V INPUT FAIL A.146 REFIOERR-A/D 10V REF INPUT FAIL A.145 SIOERR-SERIAL 1/0 FAIL A.13

SWTCHMO-SERVO SWITCHING MONITOR N/A: STUCKPB-STUCK P/B DETECTED A.122 SPARE1 SRVOPWR-SERVO POWER VALID Logic 1 = Valid N/Ao FGCVAL-FGC VALID Logic 1 = Valid N/A

~: Referenced recommended actions are found in Appendix D.

AllA.1OA.9A.8A.7A.6A.5A.4A.3A.2

A.1

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FGC FLIGHT FAULT SUMMARY APPENDIX C

MONFLAGB (LINE 3, WORD1)

BIT NO. FLAG/VALID RECOMMENDEDACTION

15 TRUNAWA-ELEV TRIM RUNAWAYMONITOR B.1214 TKTFAILB- TICKET FAILUREDISENGAGEFAIL FLAG B.613 MFELV- ELEVATORMONITOR B.1112 TRMINHT- TRIM INHIBIT MONITOR B.1O11 MFAIL - AILERON MONITOR B.910 SRVOPWR - SERVO POWER VALID Logic l=Valid N/A9 FGCVAL- FLT GUIDANCECOMPUTERVALIDLogic l=Valid N/A8 SWTCHMO- SERVOSWITCHINGMONITOR B.87 ADCONV- A/D CONVERSIONERROR B.76 EXHBRSTA- EXCESSIVEHB RESETS IN A-PROC B.6

RTLPERR8- REAL-TIMELOOPERROR8MS B.5: RTLPERR- REAL-TIMELOOPERROR B.53 SIOERR - SERIAL 1/0 ERROR B.42 STUCKPB- STUCKP/B FLAG B.31 MFYDPOS- YD SERVOCONTROLFLAG B.2o MTRMFAIL- MANUALTRIM FAIL FLAG B.1

AUTODISC(LINE 3, WORD2)

BIT NO. FLAG/VALID RECOMMENDEDACTION

15 MTRMFAIL- TRIM FAIL FLAG B.114 SPARE13 MTINOP- MANUALTRIM INOP B.1812 SPARE11 MTMONOP- MACHTRIM MONITORFLAG B.1710 SPARE9 MTRUNAW- MANUALTRIM RUNAWAYFLAG B.68 SPARE7 MFSBTR- MANUALTRIM FEEDBACKFLAG B.156 SPARE5 TRMSWFLG- LIMIT SWITCHESFLAG B.13

SPARE: LIMSWFLG- LIMIT SWITCHESFLAG B.142 SPARE1 XTRMSWFL- CROSSTRIM SWITCHESFLAG B.13o SPARE

NOTE: Referenced recommended actions are found in Appendix D.

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FGC FLIGHT FAULT SUMMARY APPENDIX C

TRIPDSNG (LINE 3, WORD 3)

BIT NO.

151413121110

;765

:2

:

FLAG/VALID RECOMMENDED ACTION

AP TRIM RUNAWAY B.12AP POWER FEEDBACK N/AELEVATOR SERVO B.11TRIM INHIBIT MONITOR B.1OAILERON SERVO B.9RESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDYD COMMAND RESPONSETRIMINOP - ELEV TRIM INOPERATIVE

B.2B.19

NOTE: Referenced recommended actions are found in Appendix D.

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FGC FLIGHT FAULT SUMMARY APPENDIX C

FENGTSTA - LATCHED VERSION OF ENGTSTA STATUS TEST WORD (LINE 2, WORDS 3 & 4)

BIT NO. FLAG/VALID

31 ENGPWRV - SERVO ENGAGE POWER VALID30 QSRVPOFB - SERVO CLUTCH POWER OFF FB29 QSRVOFFB - SERVOS OFF FB28 XSTATUSV - CROSS CHANNEL STATUS VALID27 QYDBRKFB - YD SERVO BRAKE FB26 QYDRELAY - YD BRAKE RELAY “ON” FB25 QAPCLTCH - AP SERVO CLUTCH FB24 QARELAY - AP CLUTCH RELAY “ON” FB23 QTRCLTCH - ELEV TRIM CLUTCH FB22 QELTRELA - ELEV TRIM RELAY “ON” FB21 YDSELENG - YD SELECT/ENGAGE STATUS20 APSELENG - AP SELECT/ENGAGE STATUS19 YDSELSTB - YD SELECT/STANDBY STATUS

APSELSTB - AP SELECT/STANDBY STATUS;; YDOFFSTB - YD OFF/STANDBY STATUS16 APOFFSTB - AP OFF/STANDBY STATUS15 YDOFFINV - YDOFF/INVALID STATUS14 APOFFINV - APOFF/INVALID STATUS13 HIGHPRI - PRIORITY CHANNEL STATUS12 YDDISC - YD QUICK DISCONNECT P/B11 APDISC - AP QUICK DISCONNECT P/B10 TCS - TOUCH CONTROL STEERING P/B9 APPERFBY - AP PERFORMANCE MONITORS BYPASS8 YDPERFBY - YD PERFORMANCE MONITORS BYPASS

TRPERFBY - TRIM PERFORMANCE MONITORS BYPASS; VAHRS - VOTED IRS DATA VALID5 VDADCV - VOTED DADC DATA VALID4 APPT - APPROACH TRACK MODE3 STALWARN - STALL WARNING FLAG2 SPARE1 MTSELECT - MACH TRIM SELECT STATUSo SPARE

NOTE: See Appendix E “Servo Switching Monitor Used With Flight Fault Summary”to determine appropriate action.

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Page 229: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

FENGTSTB - LATCHED VERSION OF ENGTSTB STATUS TEST WORD (LINE 3, WORDS 4 & 5)

BIT NO. FLAG/VALID

31 ENGPWRV - SERVO ENGAGE POWER VALID30 QSRVPOFB - SERVO CLUTCH POWER OFF FB29 QSRVOFFB - SERVOS OFF FB28 XSTATUSV - CROSS CHANNEL STATUS VALID27 QYDBRKFB - YD SERVO BRAKE FB26 QYDRELAY - YD BRAKE RELAY “ON FB”25 QAPCLTCH - AP SERVO CLUTCH FB24 QARELAY - AP CLUTCH RELAY “ON FB”23 QELTLTCH - ELEV TRIM CLUTCH FB22 QELTRELA - ELEV TRIM RELAY “ON FB”21 YDSELECT - YD SELECT STATUS20 APSELECT - AP SELECT STATUS19 TCS - TOUCH CONTROL STEERING P/B18 ACTIVCHN - ACTIVE CHANNEL STATUS17 YDDISC - YD QUICK DISCONNECT P/B16 APDISC - AP QUICK DISCONNECT P/B15 ELVTINOP - ELEVATOR TRIM INOPERATIVE FLAG14 APSERMO - AP SERVO MONITORS FLAG13 ELTMONBY - AUTO TRIM MONITORS BYPASS FLAG12 APMONBY - AP SERVO MONITORS BYPASS FLAG11 YDMONBY - YD SERVO MONITORS BYPASS FLAG10 STALWARN - STALL WARNING FLAG

VAHRS - VOTED IRS DATA VALID; VDADCV - VOTED DADC DATA VALID7 APPT - APPROACH TRACK MODE6 MTMOBY - MANUAL TRIM MONITORS BYPASS FLAG5 MTSELSTB - MANUAL TRIM SELECT/STANDBY STATUS4 MTSELENG - MANUAL TRIM SELECT/ENGAGE STATUS3 MTOFFSTB - MANUAL TRIM OFF/STANDBY STATUS2 MTOFFINV - MANUAL TRIMOFF/INVALID STATUS1 MFYDPOS - YD POS MONITORo SPARE

NOTE: See Appendix E “Servo Switching Monitor Used With Flight Fault Summary”to determine appropriate action.

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

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Page 230: Avionic Gulfstream IV-2

n 0000 0000 0000 0000 0000 0000

2 v!?jg If my b! ta are set In this word, psrform

&n their correspxrdlng recannmdsdactlwrs first~o

3v$m If my bits ore set in this word, do their+wa correspondingreccmwwki octIms second

~rtg-$Wn~cu= If bite ere eet in this wrd, da their

050correspondingreccinnendedset ierrs th I rd

&*c.

x% If bits me set in this word, do theircorrespendlngremmrmded octione fourth;=

7*~u If bits sre eet in this uord, do their0 correapmdi~ recwmmded actions fiftha

If bits ore set In this uord, do theircorrespondingrecunnendedact lam Icrst 3.

Page 231: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

BIT NO.

151413121110

:

;

:32

i

MAINIA (LINE 4, WORD 1)

ELEVATOR TRIM SERVO AMP FAILRESERVEDRESERVEDAP OR YD SERVO POWER RELAY FAILURESPAREELEV TRIM ENGAGE TEST FAILURESPAREELEV TRIM PRE-DRIVE TEST CONDITIONSFAILURESERVOSOFF ‘AND’ GATEFAILUREELEVTRIM PRE-ENGAGECONDITIONSFAILURESERVOPOWEROFF ‘OR’ GATEFAILURESPAREELEVTRIM BRAKEFAILELEVTRIM SERVOENGAGERELAYFAILSPAREELEVTRIM PULL-UPRESISTORFAILURE

MAIN2A(LINE4. WORD2L

D/AWRAPAROUNDFAILURELATCHEDPOWERVALIDFAILUREMEMORYCHECKSUMFAILURERAMFAILURESPAREPOWERSUPPLYMONITORRESETFAILUREAIRCRAFTCONFIGURATIONPIN FAILURESERIAL WRAPAROUND FAILURERESERVEDSERVO POWER INHIBIT FAILUREF/DANNUNCIATORVALID FAILUREA/D CALIBRATIONFAILRESERVEDRESERVEDSPAREELEVTRIM CLUTCHISOLATIONDIODEFAIL

NOTE: Referenced recommended actions are found in Appendix D.

RECOMMENDED ACTION

C.1

C.2

C.3

C.3C.4C.3C.5

C.11C.3

REPLACEFZ

REPLACEFZREPLACEFZREPLACEFZREPLACEFZ

REPLACEFZC.6C.7

REPLACEFZC*7

REPLACEFZ

C.8

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Page 232: Avionic Gulfstream IV-2

I

I

FGC FLIGHT FAULT SUMMARY APPENDIX C

BIT NO. MAIN3A [LINE 4, WORD 3) RECOMMENDED ACTION

200MS POWER DOWN TIMER FAILURE REPLACE FZ;: POWER INTERRUPT INTERLOCKS TEST FAIL REPLACE FZ13 HBM FAILURE (TIMER TOO SHORT) REPLACE FZ12 HBM FAILURE (TIMER TOO LONG) REPLACE FZ

HBM RESET INTERLOCKSTEST FAILURE REPLACEFZiii POWERINTERRUPTPRE-TESTCONDITIONSFAIL N/A

HBMRESETPRE-TESTCONDITIONSFAIL N/A: SPARE

PREFLIGHT TEST TICKET FAILURE REPLACE FZ: RESERVED

RESERVED: RESERVED3 RESERVED2 RESERVED

SPARE; SPARE

BIT NO. MAINIB (LINE4. WORD4~

SERVO POWER PRE-ENGAGE CONDITIONSFAILURE:: YD ENGAGE TEST FAILURE :::

AP ENGAGE TEST FAILURE C.lo:; RESERVED11 AP BRAKEFAIL C*1210 YD PRE-ENGAGECONDITIONSFAIL C.9

AP PRE-ENGAGECONDITIONSFAIL C*1O: RESERVED

SERVOSOFF ‘AND’ GATE FAILURE C.4; SERVO POWER OFF ‘OR’ GATE FAILURE C.55 YD SERVO POWER RELAY FAIL C.24 AP SERVOPOWERRELAY FAIL C.23 YD SERVO ENGAGE RELAY FAIL2 AP SERVO ENGAGE RELAY FAIL ::;0

YD PULL-UP RESISTOR FAILURE REPLACE FZi AP PULL-UP RESISTOR FAILURE REPLACE FZ

NOTE: Referenced recommended actions are found in Appendix D.

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Page 233: Avionic Gulfstream IV-2

FGCFLIGHTFAULTSUMMARY APPENDIXC

BIT NO. ~ RECOMMENDEDACTION

15 D/A WRAPAROUNDFAILURE REPLACEFZ14 LATCHEDPOWERVALIDFAILURE REPLACEFZ13 MEMORYCHECKSUMFAILURE REPLACEFZ12 RAMFAILURE REPLACEFZ11 RESERVED10 5 VOLT UNDERVOLTAGE MONITOR TEST FAIL REPLACE FZ

5 VOLT OVERVOLTAGE TEST FAIL REPLACE FZ: SERIAL WRAPAROUND FAILURE REPLACE FZ7 STATUS TRANSFER RAM FAILURE REPLACE FZ6 SERVO POWER INHIBIT FAILURE REPLACE FZ5 PROCESSOR VALID FAILURE REPLACE FZ

A/D CALIBRATION FAIL REPLACE FZ! RESERVED2 AIRCRAFT CONFIGURATION PIN FAILURE C.6

YD ISOLATIONDIODEFAIL C.8: AP ISOLATIONDIODEFAIL C.8

BIT NO. MAIN3B(LINE4. WOR06L

200MS POWERDOWNTIMERFAILURE REPLACE FZ;: POWER INTERRUPT INTERLOCKS TEST FAIL REPLACE FZ

HBM FAILURE (TIMER TOO SHORT) REPLACE FZ:; HBM FAILURE (TIMER TOOLONG) REPLACEFZ

HBMRESET INTERLOCKSTEST FAILURE REPLACEFZ# FD/ANNUNCIATORVALIDFAILURE C*7

POWERINTERRUPTPRE-TEST CONDITIONSFAIL N/A: HBMRESETPRE-TEST CONDITIONSFAIL N/A7 PREFLIGHTTEST TICKET FAILURE REPLACEFZ6 RESERVED

RESERVED: RESERVED3 RESERVED2 YD SERVOAMPFAIL C.13

ELEVSERVOAMPFAIL C.1: AIL SERVOAMPFAIL C*1

NOTE: Referenced recommended actions are found in Appendix D.

Ground Maintenance Test ProcedureTable 301 (cent)

22-14-00Page 398.124

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Page 234: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

Fault Data Bit DescriI)tion

Following are descriptions of the Bits from the Data Words contained in theFlight Fault Summary.

MONFLAGA [LINE 2. WORD 1)

Bit 15 - SDare

Bit 14 - SDare

Bit 13 - Sr)are

Bit 12 - SDare

Bit 11 - Rudder Servo Motion Monitor

Data Used: Yaw Damper Position CommandVoted Dynamic Pressure

Function: A) Prevention of Yaw Damper induced rudder moments in excess of 4.4degrees-yaw/see/see.

B) Detection of Yaw Damper or Rudder Servo position commandmalfunctions which result in rudder servo motion in excess ofcomputed limits.

C) Detection of D/A feedback measurement failures.

Reversion: Monitor trip will cause AP (if engaged) and YD to disengage.

See Figure C-1.

Bit 10 - Elevator Servo Motion Monitor

Data Used: Elevator Servo RateTrim CommandVoted True AirspeedVoted Dynamic Pressure

Function: A) Prevention ofAP induced pitching moments in excess of3.75degrees-pitch/sec/sec.

B) Detection of Autopilot induced malfunctions which result inelevator motion in excess of computed limits.

Reversion: Monitor trip will cause the AP/YD to disengage.

See Figure C-2.

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

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Page 235: Avionic Gulfstream IV-2

\ 4

TO ANALOG vOTED

‘SERVO AMPLIFIER — DYNAMICPREssuRE

——— ——— ,——.

- ‘T————.— ————

‘B’PROCESSOR SOFIWARE.—— ——

‘APROCESSOR SO-AREFIxED YAW

1ACCEL LIMIT

1~(4’%EC>)

+ D/A AIDCONVERT -

ICONVERT G

i

YDI ABSOLUTE OVER

+ THnESHOLDENGAGE1 ZERO

I

VALUE

I

DETECT

( I1 I

YAW DAMPER

I~.l”ERROR LIMITS

CONTROL LAWNOTE

SERIES ACTUATOR 1 RUOOER

POSITION CMO OVER LIMIT- DEBOUNCE ON

MOTIONERROR MONITOR

(

1+

DETECT O 1 SEC FLAG

NOTE RESET OESOUNCESI

KD =7.1TO INITIALIZE

[(

G= q 57.%KRIG ●CH5R= .IX12745

Ko ]S6R=36.

57.3+KRIG S8R & CHm q C6R = 3.5SCndR = .lCrJ AD.20233

Rudder Servo (Series) Motion MonitorFigure C-1

ELEVATOR SERVOTACH (POSITIVE VOTED VOTEDNOSE DOWN) TAS DYNAMICPRESSURE

TRIMSERVO OVERTACH

ASSOLUTE ELEVATORVALUE THRESHOLD +MOTIONMONITOR

O=ECT F!AG

FIXEOPITCHACCELERATIONLIMIT (3”/SEC2) AO+?U234

Elevator Servo Motion MonitorFigure C-2

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Page 236: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

MONFLAGA (LINE 2. WORD 11-

Bit 9 - Aileron Servo Motion Monitor

Data Used: Aileron Servo RateVoted Dynamic PressureVoted True Airspeed

Function: A) Prevention of Autopilot induced rolling moments in excess of 8degrees-roll/see/see.

B) Detection of Autopilot induced malfunctions which result inaileron servo motion in excess of computed limits.

C) Autopilot malfunctions result from:1) Servo Amplifier Faults2) Faults in Aileron Servo Control

Reversion: Monitor trip will cause the AP/YD to disengage.

See Figure C-3.

Bit 8 - Yaw C)amDerClosure Monitor

Data Used: Yaw Body RateVoted RollVoted PitchRudder Position

Function: A) Detection of adverse or oscillatory rudder activityB) Detection of adverse Yaw rates greater than fl degree-yaw/see.C) Prevention of Yaw Damper malfunctions from causing excessive tail

loads, especially at high airspeeds.

Reversion: If both AP and YD are engaged at time of failure, AP/YD aredisengaged. If YD is engaged, YD is disengaged.

See Figure C-4.

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

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Page 237: Avionic Gulfstream IV-2

;ERVO-OVER-

FILTER + FILTER - &&%a THRESHOLD AIL MOTION

3ATE DETECT ~ MONITOR FIAG

A

%8 VOTEDDYNAMIC THRESHOLD

PRESSURE /

‘A’ PROCESSORSO~AREFIXED ROLLACCEL LIMIT(8”/sEc’)

AD-20231

Aileron Servo Motion MonitorFigure C-3

lalNocoseWSITIVE RIGHTSANK)

VARIASLEUm~PllCHNDSE-UP)

‘AWRATE~ERIGHTIURw ZEROUMIT

N ~R SOFIWARE + m*O* UMITS ‘TAS

l“ESECTHRESHOLD!

a OVER-TNRESHOLD

0.2 SEC

4- D=CTOESOUNCE __

“ON’ONLY

5“ HOGWCTHRESHOLD

~ OPPOSITEPolARrTY +

WRIESACTUATORPOSITION DEIECTRIGHT RUDDERPOSITIV@

ovER-THRESHOLD YD CLOSURE

D~ - FLAGAO-20232

Yaw Damper Closure MonitorFigure C-4

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Page 238: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

MONFLAGA (LINE 2, WORD 1~

Bit 7 - Roll Closure and Limits Monitor

Data Used: Voted Radio AltitudeComputed Roll CommandVoted RollRoll Body RateAileron Servo Motor VoltageApproach Track Logic

Function: A) Detection of Limit failures which cause open loop conditions.B) Prevention of Autopilot malfunctions causing excessive rolling

moments.

Reversion: Monitor trip will cause the AP/YD to disengage.

See Figure C-5.

Bit 6 - Pitch Closure Monitor

Data Used: Computed Turn Compensation CommandPitch Prediction TermPitch Rate PredictionVoted Pitch Body RatePitch CommandVoted PitchVoted RollElevator Servo Voltage

Function: A) Detection of open loop conditions in the pitch axis.B) Prevention of Autopilot malfunctions from causing significant

pitch movements, especially at low airspeeds.

Reversion: Monitor trip will cause the AP/YD to disengage.

See Figure C-6.

Ground Maintenance Test ProcedureTable 301 (cent)

22-14-00Page 398.129‘Mar 15/91

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Page 239: Avionic Gulfstream IV-2

NN

START

66’ 30 48”

+J+

vOTED RADIOALTITUDE ILIMIT

VOTEDROLL

A PROCESSORCOMPUTEO ROLL COMMANO

ROLL EFIRO!J

I

THRESHOLD

flESET

DEBOUNCE

03 SECONODEBOUNCE

YES

NOTE1: AT INITIAL12ATION,SET RATE LIMITER TO4s”.

NOTEZ RESET OE60UNCE5TO INITIALIZE

‘A’PROCESSOR(100mSEC LOOP)

*1 SETMONITOR A

FLAG1

EXIT

%$%a--HFD“’’”SUB AD13170.Rt

Page 240: Avionic Gulfstream IV-2

w

A.

c-t

VOTEO PITCHEOOYRATE 1

%

+A PROCESSOR COMPUTED COMPUTEO TURN

36

LIMIT - PITCHPITCH COMMANO COMPENSATION RATE

+PITCH o 5“/SEC

SELECT 0“/S +25”/SERROR SMALLER PITCH RATE

— 573 VALVELIMITER

322 FTASEC PREDICTIONVTS

VOTED PITCH ANGLE THRESHOLO* 1.5X3

START RESETDEBOUNCES + CONTINUE

bRESETDE130UNCES

1 J, , l~sp

NOTE: RESET DEBOUNCES ToINITIALIZE

r I 1

‘OTEi&‘“TE’E=P‘A’PROCESSOR SOFTWARE

(100mSECLOOP) I J AD.13171

Page 241: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

MONFLAGA (LINE 2, WORD 1~

Bit 5 - Yaw OamDer Position Validation Monitor

Data Used: Yaw Damper Position

Function: A) Validation of Yaw Damper position used in other monitors.B) Minimize exposures to invalid Yaw Damper position data being used

in the monitors.

Reversion: Monitor trip after 2 error over threshold (0.15 deg) detectionswithin 1 second will result in the AP/YD disengaging. If both AP/YDare engaged at the time of failure, AP/YD are disengaged. If theYD is engaged, YD is disengaged.

See Figure C-7.

Bits 4 and 3 - Servo Feedback Monitors (Aileron and Elevator)

Data Used: Servo Motor VoltageServo Motor CurrentServo Motor Rate

Function: A) Verification of the measured motor data sent to the A processormonitors.

B) Detection of servo feedback errors which may result in latentinoperative A processor monitors.

C) Prevention of servo feedback faults from remaining undetected(latent), thereby disabling performance monitors in the Aprocessor. (Only the B processor servo feedback monitors areintended for rapid detect protection from active malfunctions andtherefore will trip before the A processor monitors if invalidfeedback data is received by both processors).

Reversion: Monitor will trip approximately 400 msec after initial failuredetection. Monitor trip will result in the AP/YD disengaging.

See Figure C-8.

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

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Page 242: Avionic Gulfstream IV-2

Honeywell ##ii~NcE

I

II

NOTE 1 RES~ DEBOUNCE TO INITIALIZE

I

1 NOTE 1v- MMPER

IPosmoN

WmES140L9

It

FauFM

f

}

1 0.19 THREsnoLo 2 ERUORSYAW CAMPERPOSITION CO;?ERT

AuOWEOPER SEC

I

IYw

I

OAMPE~PoslnoN

%’ PROCESSOR SO-ARE I ‘h’ PROCESSOR SOFWARE

(2smSECWOATE) (la mSEC MAX UPOATE IN-AA) Ab131m

Validation Process for Yaw Damper Position(Data Used in Monitors)

Figure C-7

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

Paae 398.133“Mar 15/91

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Page 243: Avionic Gulfstream IV-2

m<

“KPROCESSOR SOFTWAnE

“’””’s ~1 7

MOTOR CURRENTI

AOSOLUTE b1

a(Almq + VNJJE O** I - EFWlOR

NOTEI

MOT(M nAIE 2B?(x m nw)

y&ow&N.

NoI

PURECONTINUE OELAYOU

104 SEC)

1sETAPSERVOFEED9-nAQ

4 TOI.ERA?KE

- 1: To WlwJzri SET FLnm CUTFIJT -0\

NOTEZ

NOTEZ TO INITIMUE sET FLTER UJTWT = I UT OFFSST OFFSET J(1 voiT) AO-I.W4

Page 244: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

MONFLAGA (LINE 2. WORD 1)

Bit 2 - Normal Acceleration Limits Monitor

Data Used: Voted Normal AccelerationElevator Servo Motor VoltageVoted RollCosine Roll Angle

Function: A) Prevention of Autopilot induced normal acceleration greater thantO.5g delta.

B) Detection of B processor pitch control law errors that inducepitch rates above TAS programmed limits.

NOTE: Higher g rate inputs will be detected by the Elevator Servo MotionMonitor.

Reversion: Monitor trip will cause the AP/YD to disengage.

See Figure C-9.

Bit 1 - S~are

Bit O - Elevator Trim Servo Amolifier Monitor

Data Used: Elevator Trim Pulse Width CommandElevator Trim Motor Volts

Function: A) Detection of inoperative trim driversB) Detection of servo motor shorts or opens, which cause the servo to

be inoperative.

Reversion: The monitor will trip if the trim failure persists for 200msec. Ifthe cross-side FGC is active, the engaged side will disengage. Ifonly one side is valid, trim will disengage and the autopilot willdisengage if previously engaged.

See Figure C-10.

Ground Maintenance Test ProcedureTable 301 (cent)

22-14-00Paqe 398.135‘Mar 15/91

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Page 245: Avionic Gulfstream IV-2

eto-s

ns” m

AhI

NOTE 1● T

r-l RATELIMIT F

VOTED tNORMAL ACCEL

,ERo~==_/ ‘–f_~:

(NOSEUP POSITIVE1 II

rELEVATOR

:OPPOSITE

MOTOR VOLTSi

* POLARITY(NOSE-DN POSITIVE) OETECT

i,x25EC

&[

.

1 OPPOSITE

NOTE 1: TO INITIALIZE. SETOUTPUT xO

NOTE 2 TO INITIALIZE. RESETOEBOUNCE

h--xx-i I&lNOTE 2

03SEC*

I iiEiECl ~udiOUNCE “ON

L

t

!

‘RESET OEBOUNCE IF POLARITY

i4v CHANGE OR IF BELOWTtiRESNOLO

“A’PROCESSOR SOF?WA~E Ao-f31n2s mSEC LOOP

Page 246: Avionic Gulfstream IV-2

NN

TRIM PULSEWIDTH OMD

0“ /+%ASSOLUTE \ ERROR

[ilanb) VALVE

m

(D NO<al*o7 EI.EWTOR TRIM-1 MOTOR VOL~

~~

@mc%%< > DEBOUNCE

ELEVATOR

mo DESOUNCE zoo msEc “ON’ - TRIM SERVCAMPLIFIER

~%FLAG

-u0.

d.+’)A.m7 OONTINUE THRESHOLD = 14V

AD-U*

Page 247: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

MONFLAGB (LINE 3, WORD 1)

Bit 15 - Elevator Trim Runawav Monitor

Data Used: Elevator Servo CurrentTrim Rate Feedback

Function: A) Detection of Autopilot Trim Runaway conditions.B) Detection of oscillatory condition in the trim servo.

Reversion: Monitor trip will cause Ap disengagement via the AP clutches.

See Figure C-n.

Bit 14 - Ticket Failure Disen~aae Fail Flaq

This bit will be set if a software error or hardware problem prevents anymonitor from functioning properly.

Bit 13 - Elevator Monitor

This bit will be set if the Servo Amplifier Monitor or the Servo FeedbackMonitor detect a fault.

Servo Amplifier Monitor:

Data Used: Pulse Width CommandServo Motor Voltage

Function: A) Detection of servo amplifier faults which result in invalid servooperation.

B) Detection of servo motor shorts, which cause the servo to beinoperative.

Reversion: Monitor trip will cause AP disengagennnentvia the AP clutches.

See Figure C-11.l

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Page 248: Avionic Gulfstream IV-2

Servo Feedback Monitor:

Data Used: Servo Motor VoltageServo Motor CurrentServo Motor Rate

Function: A) Detection of open motor conditions which result in faulty motoractivity.

B) Detection of servo feedback errors which result in invalid databeing used in the servo control laws.

C) Verification of the motor feedback data used in other monitors.

Reversion: Monitor trip will cause Ap disengagement via the AP clutches.

See Figure C-11.2

Bit 12 - Autotrim Inhibit Monitor

Data Used: Elevator RateElevator Trim RateElevator Servo Current

Function: Detection of jammed elevator servo causing trim to be commanded.

Reversion: Monitor trip will cause AP/YD to disengage.

See Figure C-12.

Bit 11 - Aileron Monitor

See Bit 13 - Elevator Monitor

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Page 249: Avionic Gulfstream IV-2

D-0

I MOTE1

ELEwTOfl Moss-up lRIM~ _ENT — 0.s50.1 O+WANOOETECT

b

“ *

AP TRW~v

0.33 mSECLOOP FLAO

-1

NOTE 1

—.— —.— NOSE.00WN TRIM

B PFIOCWR::FIWARE OEMAND DETECT

OVER T~ESNOLOe NOSE DOWN

TRIM#lATEDETECT

THRESNOLO *“MCb O.rmsc

III

-——— ———

,1ELEVAT~ J-.

OVERTNRESHOLO

TRIMT-~ 02#*t I NOSEUPTRIMRATEDETECT

(2EmSECLOOPI ITWIESMOLO I*ISEC

J IXO ?/SEC.——— ——— I

NOTE 1:flESETDEBOUNCESTOINITIALIZE w A@ i3n8

Page 250: Avionic Gulfstream IV-2

PULSE-WIDTH YES

- RESETCMD DEBOUNCE *CONTINUE(%)

TNO

T IBPROcESSORSOFTWARE

SECOND PAST-VALUE CMD

ABSOLUTEVALUE - ERROR

NnTF.S<

MOTOR ~VOLTS

RESET NOCONTINUE ~ DEBOUNCE

~ DISENGAGE

NOTE 1-------f. RESET DEBOUNCE TO INITIALIZEWHEI

CLEAR DEBOUNCE WHEN SIGN-ON ER2. CLEAR PAST VALUES WHEN NOT ENGAGED.3. EL~VTCOCE;ERVO AMP OEBOUNCE:

AILEtiON-S#lVO AMP DEBOUNCE175 mSEC

ENNOT ENGAGED,?RORSIGNAL CHANGES. T

THRESHOLD= 14V

AD 13167R3

Page 251: Avionic Gulfstream IV-2

&l I

MOTOR VOLTS

~ MOTOR CURRENTm (AMPS)3<0

mm MOTOR RATEmn.

(X lWRPM)

wm SM-M)OTACH:

lV/100 RPMz

<

I ‘E PROCESSOR SOFTWARE

+ 25 +—

NOTE1 TO INITIALIZE SET FILTER OUTPUT

4ABSOLUTE

-1

VALUE 0.25s + 1+ ERROR

+

NOTE 1

CONTINUE

+0.25 ABSOLUTE 1

VALUE 0.25s , 1““rl

TOLEFIANCE+

=0 NOTE 2

SET SERVOFEEDBACKFLAG

u

NoTE2: TO INITIALIZE SET FILTER OUTPUT=l VOLT OFFSET OFFSET ~AD.13163

Page 252: Avionic Gulfstream IV-2

ELEVATORTRIMTACH

ITHRE6H0LD

ELEVATOR OVERDWW*OLDTACH

ALJTOTRIM(BAMEPOLARIW) tNHIBIT

FLAG

THREBHOLD‘“’’’”p~ I

t 1

~ATOR ABBoLuTE - THREBHOLDSERVOCURRENT VALLfE D~CT DEBOUNCE

“ON’ONLY d2 SEc

Ib J

Autotrim Inhibit MonitorFigure C-12

A9mw

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

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Page 253: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

MONFLAGB [LINE 3. WORD 1)

Bit 10 - Servo Enaaae Power Valid

The servo engage power valid is derived (in both A and B processors) from thecross-channel switching discrete inputs and the servo clutch power feedbackdiscretes. The servo engage power valid is required for enabling of servoclutches and servo drivers in order to prevent engagement if the cross-sidechannel is already engaged.

See Figure C-13.

Bit 8 - Servo Switchina Monitor

This monitor validates the states of the servo switching discrete inputs withrespect to the engage statuses. Both processors monitor servo switching.Each processor validates the servo switching states based on internallygenerated statuses.

Bit 1 - Yaw Damper Servo Control Flaq

Data Used: Yaw Damper CommandYaw Damper PositionYaw Damper Motor VoltageYaw Damper Servo Motor Rate

Function: A) Detection of analog servo loop hardware faults which result inthe yaw damper servo motion not corresponding to the commands.

B) Detection of yaw damper servo being inoperative and not correctlyresponding to the yaw damper commands.

Reversion: Monitor trip will cause disengagement of AP/YD via the yaw damperrelay.

See Figure C-13.l.

Bit O - Manual Trim Fail Flaq

See Figure C-13.2.

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

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Page 254: Avionic Gulfstream IV-2

● SE- ENOAOEPowsu VALIO

SEKVOCLUTCNPWROFF

ZSIOE SET:

CNANNEL . SE~ ENGAGEPOWER VMIO

WHIM SEFWO PWll@s msEc)

--

(60th Processors)Servo Engage Power Valid Logic

Figure C-13

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

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Page 255: Avionic Gulfstream IV-2

-ONQo0

<mSI

ITATE1~11 a I0.1 ~SIT~ LIMIT

c_“ +FYJStTl@lEflnon

LVDTPOSITIONFEEDBACK

TW$

:p K = 29.3?RAO/SEC

I c-l’s RATS LIMIT = t5.33vS 61 ● 00ZSSECS+GoWnJs POSITION LIMIT = 1.5”. *A. c.1..~~lwqg

--5SET MONITOR FIA(l

me-!Gn B-PROCESSORz EXM 25mSECLOOP-J

tEXIT M Iswsl

Page 256: Avionic Gulfstream IV-2

““’Tsw’TcHEsFLA”~ TRIMMONITORS FLAG MANAG13vU3W(BPROCESSOR, 100 mSEC UPDATE, PARTITIONED)

‘;=~+ CROSS-CHSTATUSVALID9

-VImom~ -3*G*I-VI(JJO● OZJIv ZZE=P-’””L~~maOm TRIMIN-LIMITSFLAG-3 CROSSTRIMIN-LIMITSFLAG(ASCB)

~a

CROSS-CHSTATUSVALID m DEBOUNCE TRIMREVERSIONt+ 1SEC

CROSSAFCSDATAVALID ‘c FLAG

‘PSELECTEDAPSERVOPOWER I AD-31656@

Page 257: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

AUTODISC (LINE 3, WORD 2)

Bit 15 - Autotrim Inoperative Monitor

Data Used: Elevator Servo CurrentTrim RateTrim In-Limits Inputs

Function: A) Detection of inoperative trim drivers.B) Detection of trim driver feedback errors, preventing latent

inoperative Pitch Trim Runaway Monitor.

Reversion: The monitor will trip if the trim failure persists for 3 or moreseconds. If the cross-side FGC is active, the engaged side willdisengage trim. If only one side is valid, no disengage will occur,“AP TRIM FAIL” will be annunciated, and the pilot must then manuallydisengage the AP and retrim the aircraft.

See Figure C-14.

Bit 13 - Manual Trim Ino~erative Monitor

Data Used: Manual Trim Switch InputsElevator Trim RateTrim In-Limit Inputs

Function: A) Detection of inoperative trim drivers.B) Detection of trim feedback errors.

Reversion: Monitor trip will cause disengagement of trim.

See Figure C-15.

Bit 11 - Mach Trim Inoperative Monitor

Data Used: Trim Rate FeedbackMach Trim Stab Error

Function: A) Detection of inoperative trim drivers.B) Detection of trim feedback errors preventing latent inoperative

Mach Trim Runaway Monitor.

Reversion: Monitor trip will cause the Mach Trim to disengage. After a trimfailure, the Mach Trim and AP may not be re-engaged.

See Figure C-16.

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Page 258: Avionic Gulfstream IV-2

——. ——. —

IELEVATOR ABSOLUTE _

OVER

TRIM T&x IVALUE

TNRESNOLOOETECT

-1ZSnSSCLOOP——— ———

TNRESN(H.Ot I

!l-=-@@INOTE

——— — ——1( , MSAMPNOSE-

> UPTRIM

~1OEM~O OE?ECT

rELEVATOR 1SEFWOCURRENT ml

Ii’ ‘ NOTE

S.33mSEC LOOPx&wTN#E.

-1* OESOUNCE

OEMAMI OETECT (3SEC)——— ———

n PROCESSOR SOFTWARE- ‘lDOmSEC

IN-LIMITsNOSEUPJI

IN-LIMITSNOSE00WN ~

mm RESETomolmcssTO lNITIAUZE

AP TFllMFAILFLAa

Page 259: Avionic Gulfstream IV-2

UAMLJALTRIMINm FM

Manual Trim InoperativeMon$torFigure C-15

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Page 260: Avionic Gulfstream IV-2

4A f

MCHTPOSA A

YMACH TRIM

&MA1’ b ERROR(57?)

T

II

TRMTAB 4ZERO i

n I(*72) MACH TRIM

ENGAG~ AD-13174

—. .——

ELEVATORTRIM TACH

I

ITRIM RA~

-&

OVER THRESHOLDNOSE DN

I

D~CT

(25 mSEC LOOP)-1——— d.15=/SEC NOSEON

TRIM RATE

- OVER THRESHOLDNosmosmP

IN LIMITSNOSE UP

MACH TRIMERROR —

& PROCESSOR SOFTWARE100mSEC

X.5” NOSE-DOWN DEMAND ,1,

IDESOtJNCE

0.3 SEC I

MACH TRIMMONfTOR

NOTE 1: ~lE5E’f’l?WESAMms

Mach Trim Inoperative MonitorFigure C-16

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Page 261: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

AUTODISC [LINE 3. WORD 2)

Bit 9 - Manual Trim Runawav Monitor

Data Used: Manual Trim Switch InputsElevator Trim Rate

Function: A) Detection of manual trim runaway conditions.B) Detection of oscillatory condition in the trim servo.

Reversion: Monitor trip will cause disengagement of trim.

See Figure C-17.

Bit 7 - Trim Feedback Monitor

Data Used: Trim Position Inputs (SIN and COS)Elevator Trim Rate

Function: Detection of trim feedback faults with trim tach or X,Y, and Z legsof trim synchro position.

Reversion: Monitor trip will cause disengagement of trim.

See Figure C-18.

Bit 5 - Trim Switch Monitor

Data Used: Manual Trim Switch Inputs

Function: Detection of miswired or inop manual trim switches.

Reversion: Monitor trip will cause disengagement of trim.

See Figure C-19.

Ground Maintenance Test ProcedureTable 301 (cent)

22-14-00Page 398.147

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Page 262: Avionic Gulfstream IV-2

MAINTENANCE

Honeywell M$!Rh.

Ground Maintenance Test ProcedureTable 301 (cent)

22-14-00Page 398.148

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Page 263: Avionic Gulfstream IV-2

2w

m

td!?jon-(D

NN

31

Im 540’

.* - Iw

ANY 2 J=

mom

(slwb~

%&o cos4e lANOSNT

———— ———.7

ELEVATORmu T* TRMTAO

1SSMSSCLOOFi———— ———— J

1 I o W’)SSC

Page 264: Avionic Gulfstream IV-2

PILOTTRIMUP CMD

.PILOTTRIMUPENABLE

PILDTTRIM SWITCH~CAUTION PUG

PILOT TRIMON CMD

PILOT TRIM ON ENA6LE

c TRIM SWITCH PUG

COPILOTTRIMUPOMD

COPILOTTRIMUPENABLE

COPILOTTRIMSWITCH~CAUTION PUG

COPILOTTRIMONOMD

OOPILOTTRIM ON ENABLEmum

Trim Switch MonitorFigure C-19

Ground Maintenance Test ProcedureTable 301 (cent)

22-14-00Page 398.150‘Mar 15/91

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Page 265: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

AUTODISC (LINE 3. WORD 21

Bit 3 - Trim In - Limits Monitor

Data Used: Nose-Up Limit SwitchNose-Down Limit Switch

Function: Detection of both trim limit switches being set.

Reversion: If the Limit Switches Flag is set for 1 second or more the trimsystem will disengage.

See Figure C-20.

Bit 1 - Cross Trim Switches Flact

See Figure C-13.2.

TRIPDSNG [LINE 3. WORD3)

Bit 15 - AP Trim Runawav

Data Used: Elevator Servo CurrentTrim Rate Feedback

Function: Detection of runaway trim after activation of AP or Trim ServoBrake.

Reversion: Monitor trip will cause disengagement ofAP and Trim.

Bit 14 - AP Power Feedback

This bit will be set when AP has power.

Bit 13 - Elevator Servo

See MONFLAGB, Bit 13.

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Page 266: Avionic Gulfstream IV-2

Bit 12 - Trim Inhibit Monitor

Data Used: Elevator RateElevator Trim RateElevator Servo Current

Function: Detection of jammed elevator servo causing continuouscommanded.

Reversion: Monitor trip will cause disengagement ofAP and Trim.

trim to be

See Figure C-20.1

Bit 11 - Aileron Servo

See MONFLAGB, Bit 11.

Bit 1 - Yaw Damper Command ResDonse

Data Used: Servo VoltageServo CurrentServo Rate

Function: A) Detection of open conditions which result in faulty activity.B) Detection of servo feedback errors which result in invalid data

being used in the servo control laws.C) Verification of the feedback data used in other monitors.

See Figure C-11.l

Bit O - Elevator Trim Inoperative

Data Used: Elevator Servo CurrentTrim Rate Feedback

Function: A) Detection of inoperative trim drivers.B) Detection of A processor trim control law failures which result

in invalid trim servo operation.C) Detection of trim driver feedback errors which prevent latent

inoperative pitch trim runaway monitor.

Reversion: Monitor trip will cause disengagement of AP and Trim.

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Page 267: Avionic Gulfstream IV-2

FENGTSTA (LINE 2. WORDS 3 & 4)

Bit 31 - Servo Enaaqe Power Valid (ENGPWRV]

The Servo Engage Power Valid is deri~ed (in ~oth A and B processors) from thecross - channel switching feedback discrete inputs and the servo clutch powerfeedback discretes. Servo engage power is required valid for enabling ofservo clutches and servo drivers in order to prevent engagement if the cross-side channel is already engaged. If this bit is set, the FGC is engaged ormay be engaged at any time. Reference Appendix E, paragraph 6.1. See FigureC-13.

Bit30 - Servo Power Off Feedback (SRVPWROFF)

The Servo Power Relay is in its off or open position. Reference Appendix E,paragraph 2.0.

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

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Page 268: Avionic Gulfstream IV-2

IN-LIMIT NOSE UPIN-LIMIT NOSE DN

TRIM IN-LIMKANNUNCIATION

TRIMENGAGED

MACHMACH TRIM

o ANNUNCIATIONII

A/P ENGAGED

Trim In-Limits MonitorFigure C-20

mum

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

I Page 398.152.2Apr 15/93

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Page 269: Avionic Gulfstream IV-2

ELEVATORTRIM TACH

THRESHOLD

ELEVATOR 1 IOVER THRESHOLD

+ DETECT AUTOTRIMTACH 0.5s+1 [ (SAME POLARITY) INHIBIT

FLAG

THRESHOLD0.75 AMp~

+ IELEVATOR 1 Ic ABSOLUTE - THRESHOLDSERVO CURRENT 0.5s+1 I VALUE DETECT DEBOUNCE

a ‘ON’ONLY2 SEC

TRIM INLIMITS

TRIM OFFLOAD(A/PENGAGED) Ao-131ao-Rl

Autotrim Inhibit MonitorFigure C-20.1

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Page 270: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

FENGTSTA [LINE 2. WORDS 3 & 4~

Bit 29- Servos Off (SERVOFF)

See Figures C-21, C-22, and C-23. Reference Appendix E, paragraph 2.0.No servos are engaged by this FGC.

Bit 28 - Cross Channel Status Valid (XSTATUSVL

The Cross - Channel Status Valid is derived (in both A and B processors) fromthe cross-channel input switching discretes. A valid status indicates that thecross-channel is either in a valid active state or a standby engage state andthe cross-FGC is capable of engaging the system. See Figure C-24. ReferenceAppendix E, paragraph 6.1.

Bit 27 - Yaw Damper Brake (YDBRAKEI

The Yaw Damper servo brake is active. Reference Appendix E, paragraph 2.0.

Bit 26 - Yaw DamRer Brake Relav “On” Feedback (YDRELAY)

This FGC’S YD brake relay is on or engaged. Reference Appendix E, paragraph2.0.

Bit 25 - AutoDilot Servo Clutch (APCLTCH)

See Figure C-21. Elevator and aileron servo clutches are active or engaged.Reference Appendix E, paragraph 2.0.

Bit 24 - AutoDilot Clutch Relav “On” Feedback (APRELAY)

See Figure C-21. This FGC’S AP clutch relay is on or engaged.Reference Appendix E, paragraph 2.0.

Bit 23 - Elevator Trim Clutch Feedback (ELTCLTCH)

See Figure C-23. The Elevator Trim servo clutch is active or engaged,Reference Appendix E, paragraph 2.0.

Bit 22 - Elevator Trim Relav “On” Feedback [ELTRELAY)

See Figure C-23. This FGC’S Elevator Trim clutch relay is on or engaged.Reference Appendix E, paragraph 2.0.

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

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Page 271: Avionic Gulfstream IV-2

At/sl-s

‘———————— ‘— ———FQ~NO~ ~GcG.r ——— ——— ——— ——— -

I AP SEFNO PW

AP SERVO PWR 1’- OOTH

W SEFNDPWRFBBOTH *

A?SEWO FWT4FEJ* Born

BOTH 0 4

!!!!!!.=

— A HE3MVALID

—B HBM VALIO

LATCHED PWR VALID

:f==rAdm-li’’’:Jc.28vJ:y~-g ‘~SERVO WR ENABLE h ~

SERVO FWR ENABLE B ~

BOTHW REL&Y C - BOTH

, Lwwrw.v.w, ) ( 1-

I . ..... ....... . .. I I,oRE,AYoFF~ I I I “mGnnr’‘N’’n’’uNN”-’lb

GUI ,U” l-n” U., ! I 1 1 * , , * . . . . . . . . . . .-1 , -. .. . . . . . .. . . .BOTH

BOTHCLUTCH FWR OFF FB I I 1 I

I

I 1--H-R~ ‘“’’”-’ L

L +28V *-!ICOMPUTER PWRI

11 II

AIL

\ELEV

-. -- -. -— SESVO SERVO

BOTH ::’”,CLU ltiH MELAY UN FU I

eon{ 4R+ SERVO CLUTCH FB

BAP CLUTCH ENGAOE CMD I ~ CLUTCV r

- &vOstOFF

+V(PULL-UP)—

~ I I

I

TRIM SERVO OFFIw sERVO OFF

80TH -SERVOS OFF FB

BoTH mSERVOS OFF 1 I

———— ———— ———— —— J v

I I ~YDRELAVOFF II r, ,Sro”mn”cc GIl

- ElOTHI I I L,” , L“ m“ “,,

+ BOTH

,

0 I

r*

I

lr ? ~

+28V

(COMPUTER FWRI

-’Hr-dTRltA SEFIVO OFF

YD SERVO OFF

SERVOS OFF

1 sERvOS OFF FB

———— ———— ——— ———— .

AmlmIz

Page 272: Avionic Gulfstream IV-2

——— ——. .—— ——— —__1FQCNO.1 F=~--–––––––––––

IBOTH *

YWTRIM SERVO PWIT

YD/lRIM SERVG PWR— BOTH

VD/TRIM SEWD Will FB

BOTH *YO/TfllM SERVD PWR FE

I

D BOTH

)

A HOM VA1lD—

I

STAB AUG STAB AUGNO 1 I

~A HBM VALID

6 HEM VALIO— NO 2EREAKER BREAKER

—0 HOM VALl0

LATCHED PWR VALID— LATCHED PWR VALID

~ SERVO PWR ENABLE A I I SERVOPWREMA8LE A ~

~ sERvO PwR ENA8LE 0IT

1

SERVO FWR ENABLE B s

YD RELAY OFF F8 I +28 VDCBOTH N + WI IIELAY OFF FE

(ESSENTIALI VO RELAY OFF - BOTH

AP FIELAVOFF I I AP RELAY OFF

TRIM RELAY OFF AIRCRAFT INTERCONNECT

BOTH -CLUTCH PWR OFF

TRIM I!ELAY OFF

00TH 4CLUTCH FWR OFF FB

CLUTCH PWR OFF

J , CLUTCH FWfl OFF FB* 90TH

* BOTH

I IDISENGAGE ANNUN STUBS>

A ANO 0PROCESSORS I I

A AND BP$tOCESSOn5

~ YOSERVO DRIvE EN

w J&I I

I

* I

+ANALOG

POSN LOOP———— +

/

RUDDERHYDRAULICACTUATOR

IWD + ~ +~ POSITION CMD I

l+.+

1+

YDCLUTCHI?ELAYONFS IM ‘I

I

IBOTH * ACTUA1OR YD CLUTCH RELAY ON F8 B0,,4

BOTH eVD SEFWOCLUTCH FB

ISOLENOID

IYD SERVO CLUTCH FEI

WI CLUTCH ENGAGE CMDs

YO CLUTCH ENGAGE CMD ~

+V WI OUICI(.DISCONNECT

AP SERVOS OFF AP SERVOS OFF

ltllM SERVO Oft TR’MS[fWOOfF

BOTH 4SERVOS OFF FB

BOTH

-——— ———— ———— ——— 1 1- ——— ——— ——— ——— ——-

Page 273: Avionic Gulfstream IV-2

‘———————— ‘— ———FO~NO~ r ——————————————-FGC NO. 2

@==d-* mlI ..- ..-C

dTIAL)‘~eorn ... .. . .. .. II w RELAY OFF

ICONNECTI

w RELAY OFFW* I I I I 1

111

CLUTCH PwR OFF

I(.,” , tin w“ OFF FB

OOTIE

BOT14CLUTCH PwR OFF FB -

1 1 I* BOTH

A AND 0PIIOCESSO

BC

B<

r-bsEN’AGEANNAANOBPROCESSORS

TRIMSERVODRIVEEN

( *

i Iof

I1’

#

+ ITRIM AMPL (WD I

I

I I I0 L—–—d

* ~ TRIM4

I SERVO

I[w“ITRIM CLUTCH nELAY ON FO TRIM CLUTCH RELAY ON FB

TRIM SEFIVO CLUTCH FB I I“

TRIM SERVO ENGAGE CMD

@~i XkoOFF ,

%,

IW SEiWOS OFF

WI S.5W0 OFF ISOTH

SESVOS OFF FB ~i

8071 I‘“ “---”--——————t

———— .—— — ———— —— -1

-( TRIM OUl&T~j:CONNECT > 1 I 1 +V‘(wLL. upI

1

II SESVOSOFFBOTH

SERVOS OFF FSSOTH

I I1- ——— ——— ——— ——— ——.

.0 W,*

Page 274: Avionic Gulfstream IV-2

SERVO CLUTCHPOWER OFFSERVOS OFFSENSOR VALIDATION TCOMPLETE (ASCB)

,● SETCROSS-CHANNELSTATUSVALID

● R’S= DEBOUNCE.

YD/lWIM SERVO POWER ,

ACTIVECHANNEL q 2-FRAMECROSS CHANNEL STATUSVALID DEEOUNCE

El● RESETCROSS-CHANNELSTATUSVALID

● RESET DEBOUNCE

(25mSEC)

ADw126W

(Both Processors)Cross-Channel Status Valid Logic Diagrams

Figure C-24

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

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Page 275: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

FENGTSTA (LINE 2, WORDS 3 & 4)

Bit 21 - Yaw Dam~er Select/Enqaqe Status (YDSELENGI

If this Bit is set, the Yaw Damper is selected and engaged by this FGC. Manualengagements of the Yaw Damper are monitored in the A processor per Figure C-25.A valid engagement will result in setting the selected/engaged status bit andannunciating the engagement by activating the appropriate YD annunciator. If avalid YD push-button is detected, but servo engagement does not occur due to aninvalid sensor and/or pre-engage condition as determined by the B processor, itis flagged by the B processor. If the YD engages without a valid push-buttonbeing detected, the selected/engage status will not be set resulting in adisengage via the servo switching monitor. If the A processor detects anengagement of the YD servo from its side when in YD selected/standby state itwill change it status to YD selected/engaged and activate the YD engageannunciator (see Figure C-26). Reference Appendix E, paragraph 6.3.

Bit 20 - Autooilot Select/Enqaqe Status (APSELENG\

Similar to FENGTSTA Bit 21. If this Bit is set, the AP is selected and engagedby this FGC. Reference Appendix E, paragraph 6.3.

Bit 19 - Yaw DamllerSelect/Standby Status [YDSELSTBI

The YD selected/standby status is slaved to the priority channel via the ASCBas shown in Figure C-27. If this Bit is set, the YD is selected, but notengaged by this FGC (this FGC is low priority). Reference Appendix E,paragraph 6.3.

Bit 18 - AutoDilot Select/Standby Status (APSELSTB)

Similar to FENGTSTA Bit 19. If this Bit is set, the AP is selected, but notengaged by this FGC (this FGC is low priority). Reference Appendix E,paragraph 6.3.

Bit 17 - Yaw DamDer Off/Standbv Status (YDOFFSTB)

See Figures C-28 and C-29. If this Bit is set the YD is not selected and thisFGC is not high priority. Reference Appendix E, paragraph 6.3.

Bit 16 - AutollilotOff/Standby Status (APOFFSTBl

See Figures C-28, C-29, and C-30. If this bit is set, the AP is not selectedand this FGC is not high priority. Reference Appendix E, paragraph 6.3.

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Page 276: Avionic Gulfstream IV-2

I

A-ProcessorAP/YO Automatic Servo Switching Status/Annunciation

Logic DiagramFigure C-25

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Page 277: Avionic Gulfstream IV-2

VALID STATE● SET YD

YD ENGAGE SELECT/ENGAGESWITCHING STATE

o STATUS● CLEAR YD

SELECT/STBYSTATUS

YD SELECTED/ENGAGED

PRIORITY CHANNEL

● SET AP/YDSELECT/ENGAGE

t ) STATUS

o ● CLEAR AP/YDSELECT/STBY—STATUS

● CLEAR ‘AP DISENG’

AP ENGAGE VALID STATESWITCHING STATE ‘ ( b

AP SELECTED/ENGAGED4

RESET TCS

TCS P/B ENGAGE FLAG

TCS ENGAGEc

I(100 mSEC)

AD-20271

(A-Processor)AP/YD Engage Status and Annunciation Logic

Figure C-26

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Page 278: Avionic Gulfstream IV-2

APOFF/STANDSY .APSELECIED/ENGAGED(ASCB}

Ib

● s= AP100 mSEC sELEcTKrANoEw

DEBOUNCE STATUS● RESET AP

CROSS AFCS MTA VALID T OFF~ANDSYSTATUS

YDSELEff~ANDBY—

YDOFF&TANDt3YYDSELECTED/ENGAGEDfASCB) 100mSEC ● SETYO. DESOUNCE S=Ew~/STANDBY

● REsEr YoOFF/STANDBYSTATUS

● S= APOFF/=ANDBY

. STATUS

PRIORllY CHANNEL A

YD SELECTEWENGAGED ~

(100 mSEC)

L

RES= AP/YDSELECTIENGAGE

SAWSES

(A-Processor)AP/YD Selected/StandbyStatus Logic Diagram

Figure C-27

Ground Maintenance Test ProcedureTable 301 (cont.) 22-14-00

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Page 279: Avionic Gulfstream IV-2

‘DpwRF”G~:=’’’ENGAI 9- 1

APPT● SET SENSOR

DISENGAGE FLAGVOTED DADC VALID ● RESET ‘“ AND “

( SELECT/ENGAGEVOTED IRS VALID STATUS

I I

‘“ PIB

YD QUICK-DISCONNECT PjB ● RESET AP AND ‘D

Y“ CLUTCH RELAY ON P/BSELECTED/ENGAGESTATUSES

Y“ SELECTEDIENGAGED~

14-1 I

SENSOR FLAG‘“ ‘“R FLAG

● RESET AP AND ‘DSELECTEDRTANDBY

CROSS CHANNEL STATUS VALID—STATUSES

● SET “ AND ‘“CROSS AFCS DATA VALID DEBOUNCE ~ OFF/STANDBY

YD SELECT/STANDBY ‘ON’ 2 SEC STATUSES

CROSS YD SELECT/ENGAGED (100 mSEC)

Y“ SELECTEDISTANDBY 1

T

RUDDER SERVO CONTROL FLAG (B-’ROC)‘“ “RF MONITOR BYPASS FLAG SET

SAW “RF MONITOR BYPASS FL4G● MONITOR DISENGAGE

FLAG

‘P SELECT ENGAGEAD-20272

(A-Processor)Yl)Disengage Status Change Logic Diagram

Figure C-28

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Page 280: Avionic Gulfstream IV-2

‘A’PROCESSORCROSS-CHANNEL STATUS VALID 100 mSEC LOOP

SERVO POWER VALIDIL

YD SELECT/STANDBY● SET

100 mSECT - AP OFF/STANDBY

YD SELECT/ENGAGE DEBOUNCEa - YD OFF/STANDBY

YD OFF/STANDBY c RESET:

PRIORITY CHANNEL ~- AP OFF/STANDBY

YD OFF - YD OFF/STANDBYSWITCHINGSTATE VALID STATE

AO-20273

(A-Processor)AP and YD Off/Standby Status Logic Diagram

Figure C-29

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Page 281: Avionic Gulfstream IV-2

AP SE1.EC7EWENGAGED RESET AP● AP DISENGAGE 4 SEAEVM3AWD

AP WICK-DISCONNECT p181 ,

==’’”=% , IMANIJALTRIM DEMAND ● RES~ APGO AROUND WS AP SELECTEDSTANDSY

sELEcTED/sr~

AP PmSinus

● mAP

slALLwARNfuGDFFmmJwYSAmJs

I—?

Rsslm● M DtSENGAGE - ● AP SELEC1’EDiEN~w

APSELECTED/ENGAGEDmmus

(A-Processor)AP Disengage Status Change Logic Diagram

Figure C-30

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Page 282: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

FENGTSTA [LINE 2, WORDS 3 & 4~

Bit 15 - Yaw DamDer Off/Invalid Status (YDOFFINV)

See Figure C-31. If this Bit is set, the YD is not selected and this FGC isinvalid. Reference Appendix E, paragraph 6.3.

Bit 14 - AutolIilotOff/Invalid Status (APOFFINVI.

See Figure C-31. If this Bit is set, theAP is not selected and this FGC isinvalid. Reference Appendix E, paragraph 6.3.

Bit 13 - Priority Channel Status (HIGHPRI)

The A processor high-priority channel is slaved to the B processor’s activechannel status as shown in Figure C-32, provided that the Servo Power Valid isset. If the Servo Power Valid is not set, high-priority status is synchronizedto the cross-channel ASCB priority status. This FGC will be the first toengage servos (AFGC MASTER). Reference Appendix E, paragraph 6.1. See FiguresC-32 and C-33.

Bit 12 - Yaw Damper Quick Disconnect (YDDISC)

YD quick disconnect is not being pushed (inactive) if this Bit is set.Reference Appendix E, paragraph 3.0.

Bit 11 - AutoRilot t)uick Disconnect (APDISC)

AP quick disconnect is not being pushed (inactive) if this Bit is set.Reference Appendix E, paragraph 3.0.

Bit 10 - Touch Control Steerina [TCSI

Touch Control Steering is active if this Bit is set. Reference Appendix E,paragraph 3.0.

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Page 283: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

FENGTSTA (LINE 2. WORDS3 & 4)

Bit 9 - Autot)ilotPerformance Monitors BYt)ass[APPERFBYI

Pitch and roll performance monitors are not being executed (typically becausethis FGC is not engaged). Reference Appendix E, paragraph 5.0.

Bit8 - Yaw DamDer Performance Monitors Bmass [YDPERFBY~

Yaw performance monitors are not being executed (typically because this FGC isnot engaged). Reference Appendix E, paragraph 5.0.

Bit 7 - Trim Performance Monitors BYDass {MTMONBY\

Trim performance monitors are not being executed (typically because this FGC isnot engaged). Reference Appendix E, paragraph 5.0.

Bit 6 - IRS Sensor Valid

The data from the IRS sensors are being properly received by this FGC, if thisBit is set. Reference Appendix E, paragraph 4.0.

Bit 5 - DADC Sensor Valid

The data from the DADC sensor is being properly received by this FGC, if thisBit is set. Reference Appendix E, paragraph 4.0.

Bit 4 - Armroach Track Mode (APPT\

This FGC is in its final phase of an approach mode if this Bit is set.Reference Appendix E, paragraph 4.0.

Bit 3 - Stall Warninq Flaci(STALWARN)

A stall warning flag is set if either the right or left stick shaker input isactivated as shown in Figure C-34. Reference Appendix E, paragraph 3.0.

Bit 2 - SDare

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Page 284: Avionic Gulfstream IV-2

Honeywell f#$~~NcE●

AP SELECTEWENGAGED sm.● AP~D MONITORS

DISENGAGEFLAG

SERVO M VALID

R)ES=● SERVO PVVRENABLE A● SERVO PWR VALIDc APAND YD SELECTED/ENGAGEDSTATUSES

● AP AND YD 0FFXTANDB%STATUSES

● AP AND YD SELECTEDISTANDSYSTATUSES

sm.● AP AND YD OFF/lNVALIDSTAWSES

(A-Processor)Servo Power Inhibit Logic

Figure C-31

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Page 285: Avionic Gulfstream IV-2

LEfi SIDE

ACTIVECHANNEL(-B --)

FGCVAUD

PwDRm CnANNEL

(A-Processor)High-Priority Channel Status Logic Diagram

Figure C-32

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Page 286: Avionic Gulfstream IV-2

CROSS-CHANNEL STATUS VALID

SERVO ENGAGE POWER VALID !● RESCT PRIORITYCHANNEL STATUS

ACTIVECHANNEL1

(FROM B PROCESSOR) t25 mSEC

1° DEBOUNCE II

FGC VALID

1’1

Il— i

I . R’s= DEBOUNCEI

(25mSEC)

PRIOR17YCHANNEL d i AD-1Z690i

(A-Processor)Low-Priority Channel Status Logic Diagram

Figure C-33

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Page 287: Avionic Gulfstream IV-2

LSTICK SHAKERR STICKSHAKER

WARN FIAG

_ R’s= =AuSTAU WARN FUG DEBOUNCE L-N FLAG&

(100 ntSEC)

(A-Processor)Stick Shaker Input Processing/Debounce

Figure C-34

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Page 288: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

FENGTSTA (LINE 2, WORDS 3 & 4)

Bit 1 - Mach Trim Select Status

Manual/Mach Trim is selected to be engaged. Reference Appendix E, paragraph6.3.

Bit O - Sttare

FENGTSTB (LINE 3, WORDS 4 & 5)

Bit 31 - Servo Enqaqe Power Valid [ENGPWRV)

Similar to FENGTSTA Bit 31. This FGC is engaged or may be engaged at any time,if this bit is set. Reference Appendix E, paragraph 6.2.

Bit 30 - Servo Power Off Feedback [SRVPWROFF~

See Figure C-21. If this Bit is set, the Servo Power Relay is in its off oropen position. Reference Appendix E, paragraph 2.0.

Bit 29 - Servos Off (SERVOFFI

See Figures C-21, C-22, and C-23. No Servos are engaged by this FGC.Reference Appendix E, paragraph 2.0.

Bit 28 - Cross Channel Status Valid [XSTATUSV)

See Figure C-24. The Cross-FGC is capable of engaging the system. ReferenceAppendix E, paragraph 6.2.

Bit 27 - Yaw Damper Brake (YDBRAKE)

Yaw Damper Servo Brake is active. See Figure C-22. Reference Appendix E,paragraph 2.0.

Bit 26 - Yaw DamDer Brake Relav “On” Feedback (YDRELAY~

The FGC YD Brake Relay is on or engaged. See Figure C-27. Reference AppendixE, paragraph 2.0.

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\

FGC FLIGHT FAULT SUMMARY APPENDIX C

FENGTSTB (LINE 2, WORDS 3 & 4)

Bit 25 - AutoDilot Servo Clutch (APCLTCH)

See Figure C-21. Elevator and aileron servo clutches are active or engaged.Reference Appendix E, paragraph 2.0.

Bit 24 - AutoDilot Clutch Relay “On” Feedback (APRELAY)

See Figure C-23. The FGC’S AP Clutch Relay is on or engaged. ReferenceAppendix E, paragraph 2.0.

Bit 23 - Elevator Trim Clutch Feedback [ELTCLTCH)

See Figure C-23. The Elevator trim servo clutch is active or engaged.Reference Appendix E, paragraph 2.0.

Bit 22 - Elevator Trim Relay “on’”Feedback (ELTRELAYl

See Figure C-23. The FGC’S Elev trim clutch relay is on or engaged. ReferenceAppendix E, paragraph 2.0.

Bit 21 - Yaw DamDer Select Status (YDSELECTI

See Figure C-35. The YD has been selected to be engaged. Reference AppendixE, paragraph 6.3.2.

Bit 20 - Autol)ilot Select Status (APSELECT)

See Figure C-35. The AP has been selected to be engaged. Reference AppendixE, paragraph 6.3.2.

Bit 19 - Touch Control Steerinq (TCS)

Touch Control Steering is active. Reference Appendix E, paragraph 3.0.

Bit 18 - Active Channel Status [ACTIVCHN)

The active channel status is derived from the logic as shown in Figure C-36.Note that the active channel status is synchronized to the cross-channellow-priority status that is transmitted via the ASCB. After a cold start theleft side has priority if both FGC’S start simultaneously. Basically, thisflag is the same as high priority status, but for the B-Processor. ReferenceAppendix E, paragraph 6.2.

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Page 290: Avionic Gulfstream IV-2

YDS~S~:CT VALID STATE

YD PUSHBUTTON(AIRCRAFT PANEL)

YD S:L?CTEDSTATUS

YD SELECTED m

YD SELECTED/ENGAGED(ASCB)YD SERVO CLUTCH FB 125 mSEC

CROSS AFCS DATA VALID IDEBOUNCE

.w

ACTIVE CHANNEL

AP SERVO CLUTCH FB 125 mSEC

AP SELECTED/ENGAGED(ASCB) DEBOUNCE

AP SELECTEDw d

~c

AP PUSHBUTTON J’SET

AP SELECTEDAP SERVO MONITOR FLAG c STATUSGROUND ENGAGE INHIBIT FLAG

a (25 mSEC)

AP SELECT VALID STATESTATE

AD-20274

B-ProcessorManual Select/Mode Synchronization

Figure C-35

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Page 291: Avionic Gulfstream IV-2

PRIORITY STATUS (ASCB)

CROSS AFCS DATA VALID

(ASCB DATA)c RESET

DEBOUNCE

CROSS-CHANNEL STATUS VALID

SERVO ENGAGE POWER VALID

PRIORITY CHANGE 125 mSECDEBOUNCE

\

SERVOS tOFF FB

RESETDEBOUNCE

COLD START

LEFT SIDESERVOS OFF

CROSS-SIDE AFCS DATAVALIDo

SERVO POWER VALID SET

ACTIVE CHANNELACTIVE CHANNEL

STATUS

(25 mSEC)AO-202?5

(B-Processor)Active Channel Status Logic Diagram

Figure C-36

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FGC FLIGHT FAULT SUMMARY APPENDIX C

FENGTSTB (LINE 3. WORDS 4 & 51

Bit 17 - Yaw DamRer Ouick Disconnect

YD quick disconnect is not being pushed (inactive) if this Bit is set.Reference Appendix E, paragraph 3.0.

Bit 16 - Autor)ilot(luickDisconnect

AP quick disconnect is not being pushed (inactive) if this Bit is set.Reference Appendix E, paragraph 3.0.

Bit 15 - AutoDilot Trim Inorferative(TRIMINOP)

A fault in the Elevator Trim system was detected by the Trim Inoperative

Monitors. Reference Appendix E, paragraph 5.0.

Bit 14 - AutoDilot Servo Monitors (APSRVMON)

The AP Servo Monitor Flag is set whenever one of the associated AP servo

monitors indicates an invalid state as defined in Figure C-37. This flag isused to disable servo power if the cross-channel is valid. If not, this statusis used to disengage the AP servos and inhibit AP servo engagement. If thisBit is set a fault affecting either the aileron or elevator servos has beendetected. Reference Appendix E, paragraph 5.0.

Bit 13 - Auto Trim Monitors BYr)ass(ELTMONBY)

All Elev Trim monitors are being bypassed, indicating that AP trim is notengaged. Reference Appendix E, paragraph 5.0.

Bit 12 - Autos)ilotServo Monitors BYDass (APPERFBY)

All AP monitors are being bypassed, indicating that AP is not engaged.Reference Appendix E, paragraph 5.0.

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FGC FLIGHT FAULT SUMMARY APPENDIX C

FENGTSTB (LINE 3. WORDS 4 & 51

Bit 11 - Yaw Damper Servo Monitors BvDass (YDPERFBY~

All YD monitors are being bypassed, indicating that YD is not engaged.Reference Page Appendix E, paragraph 5.0.

Bit 10 - Stall Warning .~..

If a stall warning condition is detected from the stick shaker inputs asspecified in Figure C-38 a stall warning flag is set that will in turn cause AP

disengagement. Reference Appendix E, paragraph 3.0. If this bit is set, thestick shaker inputs to this FGC is active.

Bit 9 - IRS Sensor Valid

The data from the IRS sensors are being properly received by this FGC.Reference Appendix E, paragraph 4.0.

Bit 8 - DADC Sensor Valid

The data from the DADC sensors are being properly received by this FGC.Reference Appendix E, paragraph 4.0.

Bit 7 - Armroach Track Mode (APPT~

This FGC is in the final phase of an approach mode. Reference Appendix E,paragraph 4.0.

Bit 6 - Manual Trim Monitors B!mass Flaq (MTMONBY)

All Manual/Mach Trim monitors are being bypassed, indicating that Manual/Machtrim is not engaged. Reference Appendix E, paragraph 5.0.

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Page 294: Avionic Gulfstream IV-2

APSERVOPWR

CROSS-CHANNEL STATUSVALID.$H.● APTRIM FAIL

● AP TRIM FAILANNIJN FM

AP TRIM INOPERATIVE

AP TRIM FAIL

AP SELECTED

. S= AP SERW

AP SERVO MONITORS FLAGMONITORS FuG

● QES~ AP TRIM

TRIM PERFOFiMAN~ MONITORS BYRASSFtAG

AP PERFORMANCE MONITORS SYW FLAG(2s MSEC)

AILERON SERVO AMPLIFIER

AILERObISERVOFEEOSACK=TOR SERW AUPLJFIERELEVATOR ~ FEEDSAOK mlm

(B-Processor)

AP Servo Monitor Invalid Status Logic

Figure C-37

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Page 295: Avionic Gulfstream IV-2

LSTICK SHAKERR STICKSHAKER

DEBOUNCE WARN FUG

RES~ -AUSTAU WARN FLAG WARN FIAG

(50 m SEC) AD.aul

(B-Processor)Stick Shaker Input Processing/Debounce

Figure C-38

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Page 296: Avionic Gulfstream IV-2

TRIM OFFm~

TRIM SELECTED ~ED (-=) —

CROSSOH AFCS -TA VALID ItXI mSEC ● TRIM SELE~ANDBY

DEBOUNCEPRIORIIY CHANNEL(FROM ‘A PROCESSOR) ~

-1] ● ~lM OFF/STANDSY I

I

-i

RES~:● TRIM SELECTEWENGAGED

=ATUS

I

IRESET:

● TRIMSEl,mSAND6Y ~ATUSTRIM SEIECTED/STAND8Y

YOPWRFIAG● TRIM 0FW5TANDS% =A~S

4&lmo

Trim(B-Processor)

Selected/Standby Status LogicFigure C-39

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Page 297: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

FENGTSTB (LINE 3, WORDS 4 & 5~

Bit 5 - Manual Trim Select/Standby Status (MTSELSTB)

Trim Selected/Standby status is slaved to the priority channel via the ASCB asshown in Figure C-39. Manual/Mach Trim is selected, but not engaged by thisFGC. Reference Appendix E, paragraph 6.3.

Bit 4 - Manual Trim Selected/EnQaQed Status (MTSELENG)

Manual engagement of trim is monitored in the B processor. The trim push-button transition is validated against the servo switching logic. A validengagement results in the Trim Selected/Engaged Status being set as per Figure

C-40. Manual/Mach Trim is selected and engaged by this FGC if this Bit is set.Reference Appendix E, paragraph 6.3.

Bit 3 - Manual Trim Off/Standby Status (MTOFFSTB)

The Trim Off/Standby Status is computed as shown in Figure C-41. Manual/MachTrim is not selected and this FGC is not high priority if this Bit is set.Reference Appendix E, paragraph 6.3.

Bit 2 - Manual Trim Off/Invalid Status (MTOFFINV~

The TrimOff/Invalid Status is set per Figure C-42. Manual/Mach Trim is notselected and this FGC is invalid if this Bit is set. Reference Appendix E,paragraph 6.3.

Bit 1 - Yaw DamDer Position Monitor (MFYDPOS~

A fault in the YD position feedback has been has been detected. ReferenceAppendix E, paragraph 5.0.

Bit O - Soare

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Page 298: Avionic Gulfstream IV-2

TRIM ENGAGE VALID STATESWITCHING STATE

PRIORITY CHANNEL

SET. TRIM SELECTED/ENGAGED

TRIM PUSHBUTTON DEBOUNCE STATUS2~ mSEC 4 RESET

● TRIM OFF/STANDBY STATUS

TRIM SELECTED/ENGAGED

TRIM CLUTCH RELAY ON FB \

AP CLUTCH RELAY ON FBMANUAL TRIM ENGAGED FLAG

MANUAL TRIM DEMAND 0 DEBOUNCE FLAGS FOR

VOTED DADC VALID 1 SEC z MACH TRIM ENGAGED FLAG } USE IN TRIMMONITORS

DADC MISCOMPARE c

AP TRIM ENGAGED FLAG1

(100 mSEC)

AO.20276

(B-Processor)

Trim Engage Status LogicFigure C-40

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Page 299: Avionic Gulfstream IV-2

CROSS-CH STATUS VALIDSERVO POWER VALID

TRIM SELECTED/STANDBY SET:100 mSEC

TRIM SELECTED/ENGAGED DEBOUNCE. . TRIM OFF/STANDBY

c STATUS

TRIM OFF/STANDBY f )

PRIORITY CHANNEL i )

RESET.

TRIM OFF● TRIM OFF/STANDBY

VALID STATE STATUSSWITCHING

STATEL

(100 mSEC)

AW3J277

(A-Processor)AP and YD Off/Standby Status Logic Diagram

Figure C-41

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Page 300: Avionic Gulfstream IV-2

AP SERVO MONITORS ~

7

CROSS-CHANNEL STATUS VALID

‘DM”N”ORsMG~r

RES~● SERVO POWERENABIE a

● SERVO POWERVALID

● TRIM SELEC7/E?GAGE=ATLIS

● TRIM SELECT/SYANDEYSTAWS

● TRIM OFF~ANDBySTATUS

s=● TRIM OFF/lNVAUD

STATUS

(B-Processor)Servo Power Inhibit Logic

Figure C-42

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Page 301: Avionic Gulfstream IV-2

FGC FLIGHTFAULTSUMMARY APPENDIXC -

MAINIA(LINE 4. WORD1) - Contains Engage Logic Failure Flags

Bit 15 - 200MS Power Down Timer Failure

The elevator trim servo amplifier and interface circuitry are verified forgross failures. With the elevator trim clutch engaged, a maximum positivecommand is input to the amplifier. The elevator trim servo motor voltagefeedback is verified to exceed ten volts within a 200 msec timeout.

Bit 14 - Reserved

Bit 13 - Reserved

Bit 12- Servo Power Relay Failure (AP or YD)

Prior to engaging the servo power relays, the following pre-test conditions areverified:

● Presence of AP servo power● Presence of YD servo power● AP servo power relay verified to be open. YD servo power relay verified to be open. All servo clutch relays are open

If the above conditions are valid, the relay is exercised and verified forproper operation. This flag will be set if the relays fail to engage.

Bit 11- Reserved

Bit 10- Elev Trim Enqaqe Test Failure

The elevator trim clutch relay and interface circuitry are verified for properoperation. The elevator trim clutch relay is commanded to close. Engagementmust occur within a 175 msec timeout.

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I

IFGC FLIGHT FAULT SUMMARY APPENDIX C

MAINIA (LINE 4, WORD 1)

IBit 9 - Soare

I Bit 8 - Elev Trim Pre-Drive Test Conditions Failure

Prior to verifying that the Elev Trim servo drive relays are not stuck closed,the X-FGC engage status is examined. The following pretest conditions areverified:

. Elev trim clutch relay not closed● AP servo power relay not open. AP quick disconnect switch not pushed● No X-FGC servos are engaged

IBit 7 - Servos Off ‘AND’ Gate Failure

The circuits which functionally generate the servos off FB discrete areverified. With all servo clutch relays open, the discrete is verified to beset. With the Elev Trim clutch relay engaged, the servos off FB discrete isverified to be cleared.

Bit 6 - Elev Trim Pre-EnciaqedConditions Failure

Prior to engaging the elevator trim clutch relay, the following pre-testconditions are verified:

● Elev trim clutch relay not closed● AP servo power relay not open. AP quick disconnect switch not pushed. No X-FGC servos are engaged

IBit 5 - Servo Power Off ‘OR ‘ Gate Failure

The circuits which functionally generate the servo power off FB discrete areverified. With any servo power relay open, the discrete is verified to be set.With all servo power relays engaged, the servo power off FB discrete isverified to be cleared.

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Page 303: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

MAINIA (LINE 4. WORD 11

Bit 4 - St)are

Bit 3 - Elev Trim Brake Fail

With the elevator trim clutch engaged, the elevator trim brake relay isverified to be engaged.

Bit 2 - Elev Trim Servo Enqaqe Relav Fail

With the servo power relay engaged and the elevator trim clutch relaydisengaged, a positive command is input to the elevator trim servo amplifier.Any voltage output is indicative of stuck-closed relay contacts.

Bit 1 - Spare

Bit O - Elev Trim Pull-UD Resistor Failure

With the servo power relay open, the elevator trim clutch relay is commanded toengage. If the relay closes, power is being applied to the relay, possiblethrough a shorted pull-up resistor.

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Page 304: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

MAIN2A (LINE 4, WORD 2~ - FGC Hardware and 1/0 Failure Flags

Bit 15 - D/A Wraparound Failure

The D/A and A/D converters are verified for offset, and scale (7 bits) errors.

Range Tested: -9.0 to +9.0 voltsConversion Error: ~156 mv

Bit 14 - Latched Power Valid Failure

This flag is set if the latched power valid cannot be cleared.

NOTE: A failure in this latch will inhibit all real-time activity.

Bit 13 - Memory Checksum Failure

All pages of memory are checksummed.

Bit 12 - RAM Failure

All of scratch RAM is exercised by writing known data to each word of RAM andverifying that the same data can be read from RAM. The integrity of the RAMaddress and data bus lines is also verified.

Bit 11 - SDare

Bit 10 - Power SUDDIY Monitor Reset Failure

The B processor simulates an over- and under-voltage condition in order toverify operation of the power supply monitors. A trip in either monitor willcause both processors to be reset. This flag indicates that an A processorreset did not occur.

Bit 9 - Aircraft Configuration Pin Failure

One or more of the six aircraft configuration or strapping pins do not agreewith this given software.

Bit 8 - Serial WraL)aroundFailure

The integrity of the controller and serial data interface between the FGC andthe controller is verified.

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.

FGC FLIGHT FAULT SUMMARY APPENDIX C

MAIN2A (LINE 4. WORD 21

Bit 7 - Reserved

Bit 6 - Servo Power Inhibit Failure

The A processor servo power enable command is verified for proper operation(part of the hardware interlocks test).

Bit 5 - FD/Annunciator Valid Failure

The Flight Director annunciator valid is verified for proper operation (part ofthe hardware interlocks test).

Bit 4 - A/D Calibration Fail

Known specific analog (positive, ground, and negative) references are convertedand verified to be within the proper tolerances.

Conversion tolerances: 10 volts t100mV, +5 volts t500mV, GND t100mV, -15 volts~1 volt,

Bit 3-1 - Reserved

Bit O - Elev Trim CLutch Isolation Diode Fail

The elevator trim clutch isolation diode is verified against opens and shorts(~: The shorted diode test is performed only with another FGC installed).

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Page 306: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

MAIN3A (LINE 4, WORD3) - Heartbeat and Power Interrupt Test Failure Flags

Bit 15 - ZOOMS Power Down Timer Failure

Hardware timer which measures the duration of a power interrupt is examined forproper operation.

Bit 14 - Power InterrutltInterlocks Test Fail

The operation of the hardware interlocks is verified after a power interruptoccurs.

Bit 13 - HBM Failure [timer too short)

This failure flag indicates that the Heartbeat Monitor timeout period is lessthan its specified tolerance (<40 mS).

Bit 12 - HBM Failure [timer too lon~)

This failure flag indicates the Heartbeat Monitor timeout period is greaterthan its specified tolerance (>100 mS).

Bit 11 - HBM Reset Interlocks Test Failure

The operation of the hardware interlocks is verified after a heartbeat monitorreset occurs.

Bit 10 - Power Interrupt Pre-test Conditions Fail

Prior to testing the hardware interlocks during a power interrupt, thefollowing pre-test conditions are verified:

● FD Annunciator verified as valid● AP Servo power present● YD Servo power present● Emergency disconnect switch not pushed. AP servo power relay not open● YD servo power relay not open

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Page 307: Avionic Gulfstream IV-2

Honeywell ~&!!#’NcE

FGC FLIGHT FAULT SUMMARY APPENDIX C

MAIN3A (LINE 4. WORD 3)

Bit 9 - HBM Reset Pre-test Conditions Fail

Prior to testing the hardware interlocks during a heartbeat monitor reset, thefollowing pre-test conditions are verified:

. FD Annunciator verified as valid

. AP Servo power present● YD Servo power present

. Emergency disconnect switch not pushed● AP servo power relay not open. YD servo power relay not open

Bit 8 - St)are

Bit 7 - PreflicahtTest Ticket Failure

The following tests are required to be performed (and verified not to have beenby-passed) after all cold starts:

. Aircraft configuration (strapping logic) test● Storage memory (RAM) test● Program memory (ROM) test● Heartbeat monitor test

Bit 6-O - Reserved

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Page 308: Avionic Gulfstream IV-2

Honeywell ##i!!~NcE

FGC FLIGHT FAULT SUMMARY APPENDIX C

MAINIB (LINE 4, WORD4) - Contains Engage Logic Failure Flags

Bit 15 - Servo Power Pre-Enable Conditions Failure

Prior to engaging the servo power relays, the following pre-test conditions areverified:

. Presence of AP servo power● Presence of YD servo power. AP servo power relay verified to be open● YD servo power relay verified to be open● All servo clutch relays are open

Bit 14 - YD Enqaqe Test Failure

The YD clutch relay and interface circuitry are verified for proper operation.The YD clutch relay is commanded to engage. Engagement must occur within a 175msec timeout.

Bit 13 - AP Enqaqe Test Failure

The AP clutch relay interface circuitry are verified for proper operation. TheAP clutch relay is commanded to engage. Engagement must occur with a 175 msectimeout.

Bit 12 - Reserved

Bit 11 - AP Brake Fail

With the AP clutch engaged, the AP brake relay is verified to be engaged.

Bit 10 - YD Pre-Enqaqe Conditions Fail

Prior to engaging the YD clutch relays, the following pretest conditions areverified:

● YD clutch relay not closed● YD servo power relay not open. YD quick disconnect switch not pushed. YD clutch not engaged. No X-FGC servos are engaged

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Page 309: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

MAINIB (LINE 4, WORD4~

Bit 9 - AP Pre-Enaaue Conditions Fail

. AP clutch relay not closed

. AP servo power relay not open

. AP quick disconnect switch not pushed

. AP clutch not engaged

. No X-FGC servos are engaged

Bit 8 - Reserved

Bit 7 - Servos Off ‘AND’ Gate Failure

The circuits which functionally generate the servos off FB discrete areverified. With all servo clutch relays open, the discrete is verified to be

set. With AP clutch relay engaged, the servos off FB discrete is verified to

be clear.

Bit 6 - Servo Power Off ‘OR’ Gate Failure

The circuits which functionally generate the servo power off FB discrete areverified. With any servo power relay open, the discrete is verified to be set.With all servo power relays engaged, the servo power off FB discrete is

verified to be clear.

Bit 5 - YD Servo Power Relay Fail

The YD servo power relay is exercised and verified to be operational.

Bit 4 - AP Servo Power Relav Fail

The AP servo power relay is exercised and verified to be operational.

Bit 3 -YD Servo Enqaqe Relay Fail

With the servo power and the YD clutch relays open, a positive command is inputto the YD servo amplifier. Any voltage output is indicative of stuck-closedrelay contacts.

Bit 2 - AP Servo EnqacieRelay Fail

With the servo power and the AP clutch relays open, a positive command is inputto the AP servo amplifier. Any voltage output is indicative of stuck-closedrelay contacts.

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Page 310: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

MAINIB (LINE 4. WORD4)

Bit 1 - YD PuI1-uD Resistor Failure

With the YD servo power relay open, the YD clutch relay is commanded to engage.If the relay closes, power is being applied to the relay, possibly through ashorted pull-up resistor.

Bit O - AP Pull-uD Resistor Failure

With the AP servo power relay open, the AP clutch relay is commanded to engage.If the relay closes, power is being applied to the relay, possibly through ashorted pull-up.

MAIN2B (LINE 4. WORD 5) - FGC Hardware and 1/0 Failure Flags

Bit 15 - D/A Wraparound Failure

The D/A and A/D converters are verified for monotonicity, offset, and scale (7bits).

Range tested: -9.0 to +9.0 voltsConversion error: *156 mv

Bit 14 - Latched Power Valid Failure

This flag is set if the latched power valid cannot be cleared.

NOTE: A failure in this latch will inhibit all real-time activity.

Bit 13 - Memory Checksum Failure

All pages of memory are checksummed.

Bit 12 - RAM Failure

All of scratch RAM is exercised by writing known data to each word of RAM andverifying that the same data can be read from RAM. The integrity of the RAMaddress and data bus lines is also verified.

Bit 11 - Reserved

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Page 311: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

MAIN2B (LINE 4. WORD 5~

Bit 10 - 5 Volt Undervoltaqe Monitor Test Fail

An undervoltage condition is simulated within the power supply in order to testthe power supply monitors. This flag indicates that the undervoltage monitorhas failed.

NOTE: A processor reset must occur within 400uS after the undervoltagecondition is simulated.

Bit 9 - 5 Volt Overvoltage Monitor Test Fail

An overvoltage condition is simulated within the power supply in order to testthe power supply monitors. This flag indicates that the overvoltage monitorhas failed.

NOTE: A processor reset must occur within 400uS after the overvoltagecondition is simulated.

Bit 8 - Serial Wraparound Failure

The integrity of the serial data input and output RAMs is verified.

Bit 7 - Status Transfer RAM Failure

The status transfer RAM is exercised by writing known data to each word of RAM,transferring the data to the A-processor, then back to the B-processor, andverifying that the same data can be read from RAM. The integrity of the RAMaddress and data bus lines is also verified in this same manner.

NOTE: Upon completion of this test, all words of the status transfer RAM areinitialized and verified to be zero.

Bit 6 - Servo Power Inhibit Failure

The B-processor servo power enable command is verified for proper operation(part of the hardware interlocks test).

Bit 5 - Processor Valid Failure

The Processor valid discrete FB is verified for proper operation (part of thehardware interlocks test).

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Page 312: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

MAIN2B (LINE 4, WORD 5)

Bit 4 - A/D Calibration Fail

Known specific analog (positive, ground and negative) references are convertedand verified to be within the proper tolerances.

Conversion tolerances: 10 volts t100mV, gnd t100mV, -15 volts ~1 volt

Bit 3 - Reserved

Bit 2 - Aircraft Conficwration Pin Failure

One or more or the six aircraft configuration or strapping pins do not agree

with this given software.

Bit 1 - YD Isolation Diode Fail

The YD clutch isolation diode is verified against opens and shorts (NOTE: Theshorted diode test is performed only with another FGC installed).

Bit O - AP Isolation Diode Fail

The AP clutch isolation diode is verified against opens and shorts (u: Theshorted diode test is performed only with another FGC installed).

MAIN3B (LINE 4, WORD 61 - Heartbeat and Power Interrupt,and Servo Amp FailureF1ags

Bit 15 - 200 MS Power Down Timer Failure

The Hardware timer which measures the duration of a power interrupt is examinedfor proper operation.

Bit 14 - Power Interrut)tInterlocks Test Fail

The operation of the hardware interlocks is verified after a power interruptoccurs.

Bit 13 - HBM Failure [timer too short)

This failure flag indicates that the Heartbeat Monitor timeout period isgreater than its specified tolerance (<40 mS).

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Page 313: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

MAIN3B [LINE 4, WORD 61

Bit 12 - HBM Failure (timer too lona)

This failure flag indicates that the Heartbeat Monitor timeout period is

greater that its specified tolerance (>100mS).

Bit 11 - HBM Reset Interlocks Test Failure

The operation of the hardware interlocks is verified after a heartbeat monitorreset occurs.

Bit 10 - FD/Annunciator Valid Failure

The Flight Director annunciator valid is verified for proper operation (part ofthe hardware interlocks test).

Bit 9 - Power lnterruDt Pre-test Conditions Fail

Prior to testing the hardware interlocks during a power interrupt, thefollowing pre-test conditions are verified:

. FD Annunciator verified as valid

. Processors valid

. AP Servo power present

. YD Servo power present

. Emergency disconnect switch not pushed

. AP servo power relay not open

. YD servo power relay not open

Bit 8 - HBM Reset Pre-test Conditions Fail

Prior to testing the hardware interlocks during a heartbeat monitor reset, the

following pre-test conditions are verified:

c FD Annunciator verified as valid

. Processor valid

. AP Servo power present

. YD Servo power present

. Emergency disconnect switch not pushed

. AP servo power relay not open

. YD servo power relay not open

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Page 314: Avionic Gulfstream IV-2

FGC FLIGHT FAULT SUMMARY APPENDIX C

MAIN3B (LINE 4. WORD 61

Bit 7 - Prefliaht Test Ticket Failure

The following tests are required to be performed (and verified not to have beenbypassed) after all cold starts:

. Aircraft configuration (strapping logic) test● Storage memory (RAM) test● Program memory (ROM) test. Power supply monitor test. Heartbeat monitor test

Bit 6-3 - Reserved

Bit 2 - YD Servo AmD Fail

The YD servo amplifier and interface circuitry are verified (approx. 1.0 deg)for gross failures. A positive position command (0.75 deg) is output to theactuator and the YD servo motor voltage feedback is verified to exceed t6 voltsor ~4mA of current feedback within a 125 msec timeout. If the motor voltagedoes not exceed the threshold, the actuator position is verified to approximatethe command.

Bit 1 - Elev Servo AmD Fail

The elevator servo amplifier and interface circuitry are verified for grossfailures. With the AP clutch engaged, a maximum positive command is input tothe amplifier. The elevator servo motor voltage feedback is verified to exceedten volts within a 50 msec timeout.

Bit O - Ail Servo AmD Fail

The aileron servo amplifier and interface circuitry are verified for grossfailures. With the AP clutch engaged, a maximum positive command is input tothe amplifier. The aileron servo motor voltage feedback is verified to exceedten volts within a 50 msec timeout.

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Page 315: Avionic Gulfstream IV-2

APPENDIX DRECOMMENDED ACTIONS FOR FLIGHT FAULT SUMMARY

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

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Page 316: Avionic Gulfstream IV-2

Honeywell ~~~!~vc’Recommended Action #A.1

Trim Servo Amplifier Monitor

Trim Servo Anpi lifier Monitor

t

Did the ground Perform the actions suggestedmaintenance test detect for the particular fault in the

any fai lures? ground maintenance test manual

Check the Trim motor driveuiring to the servo:

1OJ2A-59 to 29J1-21OJ2A-6O to 29J1-1

Be sure that these pins arelocked in their connectors.

Fix the aircraft wiring.

&Ground Maintenance Test Procedure

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Page 317: Avionic Gulfstream IV-2

NORMAL ACCELERATION LIMITSMONITOR

MAKE NOTE OF THE CONDITION OFENCOUNTERED, OR WAS THE AIRCRAIT THE FAILURE AND REPORT A PERF-

IN A MISTRIM SITUATION WHEN THE ORMANCE LIMITATION PROBLEM TOHONEYWELL

WAS A FAILURE OF EITHER SERVO PERFORM THE RECOMMENDED ACTIONAMP MONITOR ALSO INOICATED? FOR SERVO AMP FAILURES

CHECK AIRBRAKE CONTROL BOX00 THE FLAPS AND AIRBRAKES AND FZ-820 CONTINUITY FROM:

INPUTS TO THE FZ-820 STILLWORK? (RUN GMT #40)

10J2B-72 TO SPEED BRAKE SWITCHBE SURE THE PINS ARE LOCKED IN

THEIR CONNECTORS.

NOYES

IS THE MOUNTING OF THE IRSS

YES

[1

CORRECT THE MOUNTINGOF THE IRSS

1

&

Normal Acceleration LimitsRecommended Action #A.2

U4nCORRECT THE WIRINGTO THE FZ-820

AO-22941#

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Page 318: Avionic Gulfstream IV-2

[

~ ELEVATOR SERVO FEEDBACK MONITOR ~

( DID THE B’s ELEVATOR SERVOMONITOR TRIP ALSO? REPLACE THE FZ-820

(LINE 3 WORD 1 BIT 13)

EEi==nFOLLOW THE RECOMMENDED ACTION

AD-22942#

Elevator Servo Feedback Monitor

IRecommended Action #A.3

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Test Procedure(cent)

22-14-00Page 398.201

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Page 319: Avionic Gulfstream IV-2

AILERON SERVO FEEDBACK MONITOR

v

DID THE B’s AILERON SERVOMONITOR TRIP ALSO? REPLACE THE FZ-820

IIFOLLOW THE RECOMMENDED ACTIONFOR A B AILERON SERVO MONITORTRIP, RA #B.9 II

Ai 1 eron Servo FeedbackRecommended Action

AD-22943#

Monitor#A.4

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Page 320: Avionic Gulfstream IV-2

b

I

Yaw Damper PositionRecommended Action #A.5

YD POSITION MONITOR

E&icllAD-22944W

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Page 321: Avionic Gulfstream IV-2

Recommended Action #A.6Pitch Closure Monitor

+

Are elevator servocable tenaicma uithin

Correct the cable tenai ons onthe etevator servo.

1YES

uaa the aircraft mistrirmredin turbelance or a windshear at

the time of the fai lure?

1

Uere the flaps or airbrakes in transition

at the time of the

INO

-P====7the f al lure and track thls problem

I f the problem persists,replace the FZ-820.

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Page 322: Avionic Gulfstream IV-2

RoLLoLoau?EMoNrrcm

JNo FAILUREOCCURREOMORE

TNAN3TIMES PER FUGNTORCWCEIN TWO CONSECUTIVEFLJGHTS.

CHEOKTHE CABLETENSIONS OFTNE AILERONSEWO @BLE.

J

AREAILERONSEWOCAMETUWONSWTNIN CORRECfTNE CASLE TENSNMS

0+4 THE AILERON SSRUO.

WASTHE AIRCRA17MLSTRIMEDIN TURSULANCEOR A WINDSHEARWHEN TNE FAJLUREOCCURRED?

RUN AILERONSSWO (10)GROUNOMAINTENANCETE.Sl.

J

WERE ANY PROSLEMSDt7t’ECTED?

MAKENOTS OF TNE CONDITIONSYES OF TNE FAILURISINFORM?HE HI

R~ATIVE TO TRACKTNEREF’IACESEWO MOTORAND PRoaLEMWITNnils Fz.szo.

RUNAILERONSERVO(10)GROUNDhWNTENANOETSST

AGAIN. 1

IF THE PROSLEMPERSISIS.REPIACE THE FZ.S2D.

v

REPIAOE TNE FZ420 .

No

REllJRN SEWO TO 1+FORANALYE3S.

~17 ~

Roll Closure MonitorRecommended Action #A.7

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Page 323: Avionic Gulfstream IV-2

Recommended Action #A.8Yaw Damper Closure Monitor

Yaw Danper closure monitor

Did either of the foltouing oscur:

YEs - Uhite in the air and in a turnone of the pi lots stapped on tha

- Uhile on the gromd and in a turnone of the pilots stepped on the

Note the condi t i ona and track Replace the FZ-8Z0.

the problem uith this FZ-820. 11

r *

If the problem persists,rapLace the FZ-8Z0.

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Page 324: Avionic Gulfstream IV-2

AILERON SERVO MOTION

ENCOUNTERING HEAVY TURBLENCEWHEN THE FAILURE OCCURRED ?

WAS THE CONTROL COLUMNNO GRABBED OR BUMPED, WHILEt

THE AP WAS ENGAGED, WHEN THEFAILUREOCCURRED ?

v v

CONTACT THE HONEYWELL FIELD NOTE THE CONDITIONS OF THEREPRESENTATIVE FOR AN FZ-BOO FAILURE AND REPORT A NUISANCE

FAILURE AND REPIACE THE PROBLEM TO THE HONEYWELLFAILED FZ-800. FIELD REPRESENTATIVE.

AO-29416 @

Aileron Servo Motion MonitorRecommended Action #A.9

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Page 325: Avionic Gulfstream IV-2

Recommended Action #Al OElevator Servo Motion Monitor

t

IJas the aircraft encounteringheavy turbulence when the

NO

i

NO Was the control COIUM

grabbed or tnmped, while

the AP brasengaged, when the

& r-Note the corrdit ions of the fai lureand track the problem with this

FZ-820.

If the problem persists,replace the FZ-820.

I J

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Page 326: Avionic Gulfstream IV-2

Honeywell ~&!!&~E

Recommended Action #Al 1Rudder Servo Motion Monitor

t

Was the a i reraf t anmmteri wheavy turbknce uhm the

fai lure occurred?

no

NO Were the rudder pedalsstepped on, uhi le the YO

use engaged, whm the

EiE&!zn +Note the condi time of the fai lure

and track the protdem ni th this FZ-820.

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Page 327: Avionic Gulfstream IV-2

1

I

Recommended Action #Al 2Stuck Pushbutton

Are any of the buttons

MO

+

NO Did both sides failGMT #lO?

YES

tClose the GP-820circuit breaker

I

I Swap the FZ-8ZOS: IPi totts -> copilotls

Copilot’s -> Pilot’s

I Rertn GMTMO II I

I

Next PeWS

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Page 328: Avionic Gulfstream IV-2

Stuck Pushbutton(fxwe 2 of 2)

Did the failure follow

“&Is the side that is failing

NO

T

Check continuity between:

GP-820 FZ-820 Signa(

J2-69 J2B-89 FD VALIDJ2-12 J2A-65 5V POUERJ2-13 J2A-66 5V POUER RETJ2-I J2B-102 SERIAL OLfT-HJ2-2 J2B-103 SERIAL WT-LJ2-3 J2B-98 CLK-HJ2-4 J2B-99 CLK-LJ2-5 J2B-96 STROBE-HJ2-6 J2B-97 STROBE-LJ2-7 J2B-1OO SERIAL IN-HJ2-8 J2B-101 SERIAL IN-L

Be sure the pins are locked intheir connectors.

I

1

Check continuity between:

GP-820 FZ-820 Signe 1

J1-69 J2B-89 FD VALIDJ1-12 J2A-65 5V POWERJ1-13 J2A-66 5V POWERRETJ1-1 J2B-102 SERIAL WT-HJ1-2 J2B-103 SERIAL CUT-LJ1-3 J2B-98 CLK-HJ1-4 J2B-99 CLK-LJ1-5 J2B-96 STROBE-HJI-6 J2B-97 STROBE-LJ1-7 J2B-1OO SERIAL IN-HJ1-8 J2B-101 SERIAL IN-L

Be sure the pins are lockedin their connectors.

I

IYES

I

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Page 329: Avionic Gulfstream IV-2

f Seria[I/O Failures ~

Recommended Action #Al 3Serial 1/0 Failure”

f

1s the 28v GP-820 circuit RepLace or repair thebreakar installed? circuit breaker

YES

t

Suap the cross FZ-820with this one.

t

Does this FZ-820 also fail?NO _[

11Replace the first FZ-820.

I

1YES

<

Does this FZ-820 fail withanother GP-820 installed?

Replace the GP-820

I YES

t

Is the failed FZ-820 onthe pilot’s (Nol) side?

NO

Check continuity betueen:

Copi lot isGP-820 FZ-820 Signal

J2-69J2-12J2-13J2-1J2-2J2-3J2-4J2-5J2-6J2-7J2-8

J2B-89 FD VALIDJ2A-65 5V POUERJ2A-66 5V POWERRETJ2B-102 SERIAL UJT-HJ2B-103 SERIAL MIT-LJ2B-98 CLK-HJ2B-99 CLK-LJ2B-96 STROBE-HJ2B-97 STROBE-LJ2B-100 SERIAL IN-HJ2B-101 SERIAL IN-L

Be sure the pins are locked intheir comectors.

t

Check continuity between:

PilottsGP-820 FZ-820 Signal

J1-69J1-12J1-13J1-1J1-2J1-3J1-4J1-5J1-6J1-7J1-8

J2B-89 FO VALIDJ2A-65 5V PDUERJ2A-66 5V POUER RETJ2B-102 SERIAL OUT-HJ2B-103 SERIAL OUT-LJ2B-98 CLK-HJ2B-99 CLK-LJ2B-96 STROBE-HJ2B-97 STROBE-LJ2B-1OO SERIAL IN-HJ2B-101 SERIAL IN-L

Be sure the pins are lockedin their connectors.

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Page 330: Avionic Gulfstream IV-2

Recommended Action #A.14FZ–820 Hardware Problem

TFz-820 hardware

problem

+I 4

Replace the FZ-820.

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Page 331: Avionic Gulfstream IV-2

Honeywell #&##’flwcE

Recommended Action #A.15FZ–820 Processing Problem

Replace the FZ-620.

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Page 332: Avionic Gulfstream IV-2

I

( TRIM FAILURE )

CHECK LINE 3, WORDS 2 AND 3AND FOLLOW THE RECOMMENDEDACTIONS FOR THE BITS THAT ARE SET

AD-22945#

Trim FailureRecommended Action #B.1

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Page 333: Avionic Gulfstream IV-2

4

CHECK THE POSITION COMMAND,LVDT EXCITATION ANDFEEDBACK TO THE COPILOT’SRUDDER ACTUATOR:C1OJ1A-63, 64 TO C14JI-H,GC1OJ1A-61, 62 TO C14J1-T,UCIOJIA-59, 60T0 C14J1-S,RBE SURE THAT THESE PINSARE LOCKED IN THEIRCONNECTORS.

(YAW DAMPER POSITION MONITOR J

1

PERFORM THE ACTIONS SUGGESTEDMAINTENANCE TEST DETECT FOR THE PARTICULAR FAULTIN

THE GROUND MAINTENANCE TESTMANUAL

NO

ICHECK THE POSITION COMMAND,LVDT EXCITATION ANDFEEDBACK TO THE PILOT’SRUDDER ACTUATOR:1OJ1A-63, 64T0 14J1-F, EIOJIA-61, 62T0 14J1-L, K1OJ1A-59,6OTO 14JI-M, JBE SURE THAT THESE PINSARE LOCKED IN THEIRCONNECTORS

9

t. .

( ANY WIRINGPROBLEMS FIX THE AIRCRAFT WIRING.

FOUND?

I REPLACE THE FZ-820I

IF PROBLEM PERSISTS, CONTACTNO HAS THE FAILURE

HAPPENED SINCE THE REPLACE THE RUDDERA HONEYWELL FIELD ENGINEER FZ-820 WAS REPLACED? ACTUATOR, IF PROBLEM PERSISTS

b\ #

AD-22946#

Page 334: Avionic Gulfstream IV-2

Recommended Action # B.3Stuck Pushbutton

TExamine the pushbuttons on

the GP-820 .I 1

*

Are any of the buttons

YES

1r

Try pressing the button toTrack the problem ~ith

force i t to release.this GP-820.

t

NO YES

Replace the GP-820. Track the problem Hi ththis GP-820.

I 1

&

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Page 335: Avionic Gulfstream IV-2

Recommended Action # B.4Serial 1/0 Failure

Serial 1/0 Fai lures

t

Is the 28v GP-820 circuit Replace or repair thebreaker installed? circuit breaker

YES

Swap the cross FZ-820uith this one.

t,~

Doss this FZ-820 also fail? .!?——-[ RepLace the first FZ-820.

~“

IYES

$

Doss this FZ-820 fail with NOanother GP-820 installed? Replace the GP-820

1

IYES

t

Is the failed FZ-820 on YES

\ ‘he‘i’ot’s‘No”‘i” ~

INO

Check continuity between:

GP-820 FZ-820 Signal. . . . . . ..- ------- ------- . . . . . .

J2-69J2-12J2-13J2-1J2-2J2-3J2-4J2-5J2-6J2-7J2-8

J2B-89 FD VALJ2A-65 5V PWERJ2A-65 5V POUER RETJ2B-102 SERIAL WT-HJ2B-103 SERIAL OUT-LJ2B-98 CLK-HJ2B-99 CLK-LJ2B-% STROBE-HJ2B-97 STROBE-LJ2B-1OO SERIAL IN-HJ2B-101 SERIAL IN-L

Be sure the pina are locked intheir comsctors.

Check contirwi ty batuean:

GP-820 FZ-820 Signal. . . . . . . . . . . . . . . . . . . . . . . . . ..-

J1 -69 J2B-89 FD VALIDJ1-12 J2A-65 5V POWERJ1-13 J2A-65 5V POUER RETJ1-1 J2B-102 SERIAL CUT-HJ1-2 J2B-103 SERIAL OUT-LJ1-3 J2B-98 CLK-HJ1-4 J2B-99 CLK-LJ1-5 J2B-96 STROBE-HJ1-6 J2B-97 STROBE-LJ1-7 J2B-1OO SERIAL IN-HJ1-8 J2B-101 SERIAL IN-L

Be sure the pins are lockedin their connectors.

Ground Maintenance Test ProcedureTable 301 (cent)

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

22-14-00Page ‘398;2i8

Mar 15/91title page of this document.

Page 336: Avionic Gulfstream IV-2

RECOMMENDED ACTION NO. B.5

REAL-TIME LOOP ERRER

f \REAL-TIME LOOP ERROR

I

DID THE FAILUREOCCUR REPLACE THE FZ-820 IFDURING TURBULENCE ? PROBLEM PERSISTS

.

IS MOD DN INSTALLEDOR -906/907 FGC ? hYEs

INO

IIRETURN THE FZ-820 TO A

HONEYWELL FIELD SHOP TOHAVE MOD DN INSTALLED OR

CONVERT TO -906/907 I AD-3485#

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

Page 398.219Apr 15/93

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Page 337: Avionic Gulfstream IV-2

RECOMMENDED ACTION NO. B.6

FZ-820 PROCESSING PROBLEM

FZ-820 PROCESSING PROBLEM

I

t

DID THE FAILURE OCCUR REPLACETHE FZ-820 IFDURING TURBULENCE ? PROBLEM PERSISTS

IS MOD ON INSTALLED

1NO

msn AD-34853

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

Page 398.220Apr 15/93

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

Page 338: Avionic Gulfstream IV-2

I

( AID CONVERSION ERROR )

D+3cnAD-22947#

A/D Conversion ErrorRecommended Action #B.7

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

Page 398;221Mar 15/91

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Page 339: Avionic Gulfstream IV-2

SERVO SWITCHING MONITOR

WERE ANY FAILURESDETECTED BY THE A PROCESSOR PERFORM THE RECOMMENDED ACTIONS

SUGGESTED FOR THE A PROCESSOROTHER THAN THE SERVO FAILURE

SWITCHING MONITOR?

WERE ANY POWER-UP PERFORM THE RECOMMENDED ACTIONS(ANY LINE 4 WORDS NOT SUGGESTED FOR THE POWER-UP

FAILURE●

GO TO SECTION 4(DIAGNOSING SERVO SWITCHINGMONITOR FAILURES) AD-22948#

B Processor Servo Switching MonitorRecommended Act ion #B. 8

Ground Maintenance Test ProcedureTable 301 (cent)

22-14-00Page 398.222‘Mar 15/91

Use or disclosureOf informationon this page is subject to the restrictions on the tile page of this document,

Page 340: Avionic Gulfstream IV-2

( AILERON SERVO MONITOR )

tDOES LINE 2, WORD 1

FOLLOW THE RECOMMENDED

IN THE FLIGHT FAULT ACTIONS FOR THE APPROPRIATE

SUMMARY SHOW ANY LINE 2, WORD 1 PERFORMANCEMONITOR +

+NO

PERFORM THE ACTIONS SUGGESTED

MAINTENANCE TEST DETECT FOR THE PARTICULAR FAULT INTHE GROUND MAINTENANCE TESTMANUAL

CHECK THE TACH FEEDBACK AND NO CHECK THE TACH FEEDBACK ANDMOTOR DRIVE WIRING TO THE MOTOR DRIVE WIRING TO THEAILERON SERVO AILERON SERVOC1OJ1 B-70, 71 TO 12J2-16,17 lWIB-70, 71 TO 12J1-16, 17Cl W2A-57, 5B TO 12J2-2, 1 1W2A-57, 58 TO 12J1-2, 1BE SURE THAT THESE PINS BE SURE THAT THESE PINSARE LOCKED IN THEIR ARE LOCKED IN THEIRCONNECTORS CONNECTORS

( ANY WIRINGPROBLEMS

IFIX THE AIRCRA~ WIRING,

FOUND?

IREPLACE THE FZ-820 I

t

IIF PROBLEM PERSISTS, CONTACT ‘0 HAS THE FAILURE

A HONEYWEU FIELD ENGINEER HAPPENED SINCE THE REPLACE THE AILERON SERVO,FZ-820 WAS REPLACED? IF PROBLEMS PERSISTS

\ tAD-22949#

Aileron Servo MonitorRecommended Action #B.9

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

Page 398.223Mar 15/91

Use or dkclosure of informationon thk page is subject to the restrictions on the tile page ot thk document.

Page 341: Avionic Gulfstream IV-2

TRIM INHIBIT MONITOR

tRUN THE FZ-S20 (05) AND PITCHTRIM (35) GROUND MAINTENANCETESTS FOR BOTH FZ-820

tPERFORM THE ACTIONS SUGGESTED

MAINTENANCE TEST DETECT FOR THE PARTICUfAR FAULT INTHE GROUND MAINTENANCE TESTMANUAL

CHECK THE TRIM BRAKE NO CHECK THE TRIM BRAKEFROM THE CROSS SIDE FROM THE CROSS SIDEFZ-S20 FZ-S20:1W 1A-22 TO 29J2-21 C1OJ1A-22 TO 29J1 -21AIC GND TO 29J2-22 NC GND TO 29J2-22

BE SURE THAT THESE PINS BE SURE THAT THESE PINSARE LOCKED IN THEIRCONNECTORS

ARE LOCKED IN THEIRCONNECTORS

I It

FIX THE AIRCRAIT WIRING.

REPLACE THE FZ-820

t

IF PROBLEM PERSISTS, CONTACTA HONEYWELL FIELD ENGINEER HAPPENED SINCE THE REPIACE THE TRIM ACTUATOR.

FZ-820 WAS REPLACED? IF THE PROBLEM PERSISTS

AD-22950#

Trim Inhibit MonitorRecommended Action #B.10

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

Page 398.224‘Mar 15/91

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Page 342: Avionic Gulfstream IV-2

ELEVATOR SERVO MONITOR

+DOES LINE2. WORD 1

(PERFORMANCE MONITORS) FOLLOW THE RECOMMENDED

IN THE FLIGHT FAULT ACTIONS FOR THE APPROPRIATE

SUMMARY SHOW ANY LINE2, WORD 1 PERFORMANCEMONITOR

RUN THE FZ-820(06) ANDELEVATOR (20) GROUNDMAINTENANCE TESTS

tPERFORM THE ACTIONS SUGGESTED

MAINTENANCE TEST DETECTFOR THE PARTICULAR FAULT INTHE GROUND MAINTENANCE TESTMANUAL

CHECK THETACH FEEDBACK ANDMOTOR DRIVE WIRING TO THE

CHECK THETACH FEEDBACK AND

SERVOMOTOR ORIVEWIRING TO THE

C1OJ1B-66, 69 TO 13J2-17, 16NO SERVO

1OJ1B-66, 69T0 13J1-17, 16C1OJ2A-55, 56 TO 1SJ2-1. 2BE SURE THAT THESE PINS

1OJ2A-55, 56 TO 13J1-1, 2

ARE LOCKED IN THEIRBE SURE THAT THESE PINS

CONNECTORSARE LOCKED IN THEIRCONNECTORS

t

FIX THE AIRCRA~ WIRING

I REPIACETHEFZ-620 I

tIF PROBLEM PERSISTS, NOCONTACT A HONEYWELL

REPLACE THE ELEVATORHAPPENED SINCE THE

FIELD ENGINEERSERVO IF PROBLEM

FZ-820 WAS REPLACED? PERSISTS

AD-2m51 #

Elevator Servo MonitorRecommended Action #B.11

Ground Maintenance Test ProcedureTable 301 (cent)

22-14-00Page 398.225

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Page 343: Avionic Gulfstream IV-2

( AP TRIM RUNAWAY MONITOR )

PERFORM THE ACTIONSSUGGESTEO FOR THATFAULT IN THE GROUNDMAINTENANCE TEST MANUAL

NO

CHECK THE TACH F.B.SYNCHROPOS., SYNCHROREFERENCE AND SERVO DRIVEWIRINGTO THE SERVOC1OJ1B-72, 73T0 29J2-16, 17 NO

DID THE PILOT’S SIDEC1OJ2B-44, 45, 46 TO 29J2-18, 19, 20C1OJ1B-44,45TO 29J2-3, 4C1OJ2A-6O, 59T0 29J2-1, 2BE SURE THAT THESE PINSARE LOCKED IN THEIRCONNECTORS

I

CHECK THETACH F.B.SYNCHRO POS., SYNCHROREFERENCE AND SERVO DRIVEWIRING TO THE SERVOlDJIB-72, 7310 2SJ1-16, 171OJ2B-44, 45, 46 TO 2SJ1-18, 19, 201OJ1B-44, 45T0 2SJI-3, 41W2A-60, 59 TO 29J1-1, 2BE SURE THAT THESE PINSARE LOCKED IN THEIRCONNECTORS

I

t

FIX THE AIRCRAFt’ WIRING

I REPLACE FZ-620 Ir

IF PROBLEM PERSISTS, NOCONTACTA HONEYWELL HAPPENED SINCE THE

FIELD ENGINEERREPLACE THE TRIM SERVO

J

AD-22852#

AP Trim Runaway MonitorRecommended Action #B.12

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

?aqe 398.226‘Mar 15/91

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Page 344: Avionic Gulfstream IV-2

( CROSS TRIM SWITCH FLAGAND TRIM SWITCH FIAG )

CHECK FOR OTHER BITSIN LINE 3 WORD 2 S=

RUN THE COCKPIT SWITCHES (40)GROUND MAINTENANCE TEST

WITH BOTH FZ-S20SI I

+PERFORM THE ACTIONSSUGGESTED FOR THATFAULT IN THE GROUNDMAINTENANCE TEST MANUAL

I NO

CHECK THE UP/DN ENABLES ANDCMDS WIRING FROM THE TRIMSWITCHES ON THE PILOT ANDCOPILOT CONTROL COLUMNS .mi!%zl11J2-44, 51 TO CPLT UP, DN NO11J2-56, 65 TO PLT UP, DNCIWIA-47, 33 TO CPLT UP, DNC1OJ1 S-88. 85 TO PLT UP. DN

DID THE PILOT’S SIDEFZ-620 FAIL?

I EE-&URE THAT THESE PINS I \ / IGk-GL%&?<~l”+H&GI Aiii LOCKED IN THEIR - I

)-+YES 11J2-44, 51 TO CPLT UP, DN11J2-56, 66 TO PLT UP, ONCIWIA-47, 33 TO CPLT UP, DNC1OJ1S-86 85 TO PIT UP, I)N

. ..--E PINSI =_iOiiKEO IN THEIR

JECTORS AND THE SWITCHES

I.3ECTLY

I

ICONNECTORS AND THE SWITCHESARE OPERATING CORRECTLY I I

coin------- .._ARE OPERATING CORI

t

FIX THE AIRCRA~ WIRING

IREPLACE THE FZ-820

II

+

I

IF PROBLEM PERSISTS, NO

CONTACT A HONEYWELL HAPPENED SINCE THE

FIELD ENGINEERREPLACE THE TRIM SERVO

AD-22953#

Cross Trim Switch Flag and Trim Switch FlagRecommended Action #B.13

Ground Maintenance Test ProcedureTable 301 (cent)

22-14-00Page 398.227

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Page 345: Avionic Gulfstream IV-2

Recommended Action # B.13 (cent)Cross Trim Switch Flag

Trim Switch F1ag

Cross Trim Switch FlsgTrim Switch Flag

(Ps9s 2 of 2)

I

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

Pacie398.228‘Mar 15/91

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Page 346: Avionic Gulfstream IV-2

CHECK THE TRIM SERVOBRACKET OUTPUTS AT

BOTH LIMITS ANOOUTSIDE THE LIMIT

29AJ1-6 (UP LIM)29AJ2-6 (UP LIM)28AJ1-5 (DN LIM)29AJ2-5 (DN LIM)

I

TRIM LIMIT SWITCH FIAG

I

[1(

REPLACE TRIM SERVOBRACKET

CHECK LIMIT SW. WIRING NOC1OJ1B-16 TO 29AJ2-6

YES CHECK LIMIT SW. WIRING1OJ1B-16 TO 29AJ1-6

C1OJ1B-19 TO 29AJ2-5 1OJ1B-19 TO 29AJ1-5

FIX THE AIRCRA17’WIRING

REPLACE THEFAlLED FZ-820

Trim Limit Switch FlagRecommended Action #B. 14

AD-29634#

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

Page 398.228.1/39%.228.2Mar 15/91

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Page 347: Avionic Gulfstream IV-2

Recommended action # B.15Trim F.B. flag

Chesk the tech F.S.,synchm position snd*ro mferensewiring to tha servo

CIOJIB-~,73 to 29J2-16,1?c1W2S-46,45,46 to 29J2-18,19,20

C1OJ1B-44,45 to 29J2-3,4C1OJ2A-6O,59to 29J2-1 ,2

Be swe that these pim●m lecked in their

mmssrors.I

Trim F.S. flag-)

+

Oid the grcudPerform the set i ms suggested

far the particular fault inmintmmce testdetest tha grms’xl mintsnmsc tsxtsw failures? -i

I

m

t

no

Check the tssh F.E.,synchropoeitim mds-m referensemiring to the servo

10JIB-~,73 to 29J1-16,17IOJ2S-44,45,46 to 29J1-18,19,20

1OJ1B-44,45 to 29J1-3,61OJ2A-6O,59 to 29J1-1 ,2

Be sure that thess pins●re losked in their

csmectors.

/4( &ny uiring

prsblan Fix the sircrsft wiring.fared?

INO

t

Has the f ai lureIf prcbtm persists, cmtsct heppenxdsinse thes llmew$ll field engineer F2-S20 use

replscsd? ‘)Y’s “~

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

Page 398.229Mar 15/91

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Page 348: Avionic Gulfstream IV-2

Recommended action # B.16Manual Trim Runaway

( hrusl lrirn Rmeusy Hmitor )

I Rm the FZ-820 (OS) endtrim servo (35) 9-

m{ ntsrlence tests

\ / Ll [[I

I I I

Check the tsch F.B..

L

m Check the tech F. S.,pm psitim, ~re positfmr

symhm referenm end $*ro rsference Mdeerw driveuiring servo drivs uirim

COtha serve to the servo

Se - that these pine Ss sure thet these pim●re hsked in their ●re lecked in their

Samectors. —tore .

I I I

1 I

Im

I Replsse the failed F2-SZO

I

+

Has the f ●i lure[f -Len pweists, comsct happened sime thes lbneynsll field engineer FZ-S20 me ~, if ~t- pwsists

repl cud?

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

Page 398.230Mar 15/91

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Page 349: Avionic Gulfstream IV-2

Recommended action # B.17Mach Trim Monitor

MschTrim Monitor

I

RIM the FZ-S20(0S) adtri- serm (35) ~

mi menuus tssts

i

Perform the ect i ens suggeetsd

-i m-e tat *tectfor the particular fsult inthe ward mintensnm test

-1

Checkthe tsch F. B., so Check the tsch F-B.,synchm pesiticm, eynchropesitim,

synchroreference snd synchrorefe~e endservo drise uiring ? servmdrive wiring

to the servm to the serwo

C10J18-~,~ to 29J2-16,17so

C10J2S-44,45,46 to ZW2-18,19,2010J1B-7Z,73 to 29J1-16,17

1OJ2S-46,45,U to 29J1-18,19,20C1OJ1B44,4S to29J2-3,4 IOJIB-46,45 to 29JI-3,4C1W2A-60,59 to 29J2-1 ,2 10J2A-60,59 to 29J1-1,2

Se sure that these pine Be ewe that these pins●re locked in tl!ei r ●re lacked in their

—tom . C-’mrs .

1 1

1

Fix the ●ircraft wiring.1

Rephce the f=iled FZ-S201

I

If problem persists, crntect Replsce the trim● HO!WV#ll field engineer servo, if PrOblcm psrsists

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

Page 3981231Mar 15/91

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Page 350: Avionic Gulfstream IV-2

Recommended action # B.18Manual Trim Inoperative

( 14awel Trim lmqer8tive Hmnitor )

tI 1

RIM the FZ-S20 (05),trim serw (35) end

C=kpft Suf tches (40)grmud mimtenuice tests

\Perform the uc i mm suggested

for the percicular fault inmei nt-e test detect

the Srmncl nmintemme wst-1

so

Chemkthe tncf! F.S.,synchrmpmsitim,

mm refaremm h fnrvm drive wfring

to the seem so

CIOJIB-~, i3 to 29J2-16,17CIOJ2S-66,45,46 to29J2-18,19,20

C1OJ1B-44.45 to 29J2-3.4C10J2A-60;59 to29J2. 1;2

Chuk the I@& elmbles and- niring fra the trinswimheem the pi lot endmmpilot cmmtmlcml~

11J2-44,51 to WLT w,ti11J2-56,65 tO PLTw,*

C1OJ1A-47,33to CPLIw,tiC1OJ1B-S6,S5toPLT w,*

S@awe thet these pirm●- bcked in their

—tors and the switchee●remperatirrg cmrrectly.

Cheek the ted! F. B.,8-M positim,

synchro reference and8erv0 drive wiring

to the sarw

10J18-~,~ to 29JI-16,1710J2S-44,45,46 to29J1-18,19,20

1OJ1B-44,45 to 29J1-3,41OJ2A-6O,59 to 29J1-1,2

Omck the t@/rh tnables adb wiring frm the trimsuitches m the pi tot amd

empi lot cmntmt cotw

11J2-44,51 to WLT w,*11J2-56,65 to PIT ~,rh

C10J1A-47,33 to CPLT UP,*C10J18-S6,35 to PLT WI,ch

se sure thet these pinswe locked in their

c-tort and the sui tche$●re mperatins correct Ly.

IL

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

Page 398.232Mar 15/91

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Page 351: Avionic Gulfstream IV-2

Recommended Action # B.18 (cent)Manual Trim Inoperative

I+

[Replace the failed FZ-220

1

I

If problem persists, sontact NOa HonayweLl field engineer

MW51 Trim lnoparati~@e9e 2 of 2)

RSPISCe the trimservo, if problem persists n

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

Page 398.233Mar 15/91

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

Page 352: Avionic Gulfstream IV-2

Recommended action # B.19AP lkim Inoperative

( AP Trfrn Incfwativa rianitor )

Checktln tad F. B.,mm po8itlan,

qndlre mfcrcme &smwdrim miring

to dm s8wo

C10J18-m,73 to29J2-16,1?cfOJ2S-U,45,46 to 29J2-18,19,20

CIWIB-44,45 to29J2-3,4CIOJ26-60,59 to 29J2-1.2

Rtn the F2-SZO (05)md trim w-m <35)

srauxl rnintenence tests

Perfor9 ttm ectim Su2msted

mineonmm test *cectfer th. particular fsult intfioeramdminwnaw test

~1

Iso IChock thetedr F.B.,

*re pooitfon,8@W0 refuence d

nrve drive niringto the servo

lWIE-~,~ to 2941-16,171OJ2S-64,45,46 to 29J1-18,19,20

10JIB-~,45 tO 29J1-3,b10J2A-60,59 tO 29J1-1,2

J I I

+

Anymiringprabme f-

fix the sircreft wiring.n

I Replace the faikd FZ-S20 I

r

If prabla xrsist8, Cmtact RepLecethe trim● ~11 ffeld mimer ~, if -- preiece

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

Page 398.234Mar 15/91

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Page 353: Avionic Gulfstream IV-2

Recommended Action #ClServo Amplifier Failures

I‘0Did both FZ-820S fai 1 this same test?

Does this FZ-820 continue to fai 1?NO

—. ,.. ,, ..,- 11 Replace the cross FZ-820

t

Does this FZ-820 pass? Replace the first FZ-8201

NO

tI 1

Disconnect the servo associated with this fai lure andrecycle power cm this FZ-820; trim servo for elev trim

fai lures; Aileron for Ai 1 ~ fai lures; Elevator servofor Elev snp failures

t

Does this FZ-820 pass? Replace this servo INO

t

Check the harness for shorts:10J2A-59/10J2A-60 (elev trim)10J2A-57/10J2A-58 (Aileron)10J2A-55/10J2A-56 (Elevator)

Be sure the pins are locked intheir comectors.

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

Page 398.235Mar 15/91

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Page 354: Avionic Gulfstream IV-2

Recommended Action #C.2Servo Power Relay Fai.Iures

Servo power Relay Fei lures

Suap FZ-820S. Does the YESfeult follow the mit? II

Replace this FZ-8201

1-tt I

Measure the servo power voltege into this FZ-820;AP: 10JlA-4/10JlA-5m: 10JIA-1/10JIA-2

#

Does servo power =28v nominal? NO

YES

Ueasure the EMERGENCYDISCONNECTvoltege: 10J2B-65\10J2A-3 I

T YES

lnatell 100 ohm, 10 uatt (0.28eIq drau)resistor across 10JIA-4/10JIA-5 and measure.

Install across 10JIA-1/10JIA-2 and measure.

~

Voltage drop across resistor should notexceed 10% less than the 28v ncsniml.

Check aircraft harnessand circuit breakers.

L.. Jrm. “k. : - ,1 P I Ii, ,.1:

In :-*.:. . ~m.:r. . ,1m

Ground Maintenance Test ProcedureTable 301 (cent)

Use or disclosure of information on this page is subjecf to the restrititons on the

22-14-00Page 398;236

Mar 15/91title page of this document.

Page 355: Avionic Gulfstream IV-2

Recommended Action #C.3Elev Trim Engage Test Failures

( Elev Trim Engage Test Failures )

t

N Did both FZ-820S fai 1 this same test?

Remove the cross FZ-820 andrecycla power on this FZ-820

1

I t

Does this FZ-820 continue to fai 1?

I I YES

NO I—.- Replace the cross FZ-820

t

Does this FZ-820 pass? Replace the first FZ-820

NO

Measure trim quick disconnectinput resistance; 10J2B-66/10J2A-3

I Be sure the pins are locked intheir connectors. I

tCheck aircraft harness and both

pilot’s and copilot’s columdiscormect suitches

NO

II Check the AP sarvo power using the procedreoust ined mder SERVO POUER RELAY FAILURES II

I 1 & I

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

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Page 356: Avionic Gulfstream IV-2

( SERVOS OFF ‘AND’ GATE FAIL 1

I COMPARE LINE 4 WORD 1 BIT 7WITH LINE 4 WORD 4 BIT 7 I

ARE THESE TWO BITS REPIJ4CE THIS FZ-820

INSTALL THE CROSS Fz-820IN THIS SLOT. DOES THIS REPLACE THE FIRST FZ-820FZ-820 FAIL THIS TEST?

MEASURE THE CROSS SERVOS OFFRESISTANCE; 10J2A-4WIOJ2A+IT SHOULD BE GREATER THAN 10K OHMSIF NOT, CHECK THE AIRCRA~ HARNESS.BE SURE THE PINS ARE LOCKED INTHEIR CONNECTORS

Servos Off ‘AND’ Gate Fai1ureI Recommended Action #C.4

AD-22954#

Ground Maintenance Test ProcedureTable 301 (cent)

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

22-14-00Page 398.238

Mar 15/91title page of this document.

Page 357: Avionic Gulfstream IV-2

( SERVOS OFF “OR’ GATE FAIL )

It

I COMPARE LINE 4 WORD 1 BIT 5WITH LINE 4 WORD 4 BIT 6

ARE THESE TWO BITSREPIACE THIS FZ-620

INSTALL THE CROSS FZ-620IN THIS SLOT. DOES THIS REPLACE THE FIRST FZ-620FZ-600 FAIL THIS TEST?

+ YES

MEASURE THE CROSS SERVOS OFFRESISTANCE; 10J2A-46/l 0J2A-3IT SHOULD BE GREATER THAN 10K OHMSIF NOT, CHECK THE AIRCRAFT HARNESS.BE SURE THE PINS ARE LOCKED INTHEIR CONNECTORS

IServos Off ‘OR’ Gate Fai1ure

Recommended Action #C.5

AD-22955#

Ground Maintenance Test ProcedureTable 301 (cent) 22-14-00

Page 398.239Mar 15/91

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Page 358: Avionic Gulfstream IV-2

AIRCRAFT ID FAILURE

ICHECK LINE 4 WORD 5 BIT 2

I

iNO

MEASURE THE RESISTANCE BETWEEN THEFOLLOWING PINS AND SIGNAL GND (1OJ2A-3):

MEASURED RESISTANCEPIN SHOULD BE10J1B-76 OPEN1W 1B-77 OPEN1W 1B-78 OPEN1OJ1B-79 <5 OHMS10J1B-60 OPEN1OJ1B-81 <5 OHMSBE SURE THAT ALL PINS ARELOCKED IN THEIR CONNECTORS

YES

IREPLACE THIS FZ-620

Aircraft ID Fai1ureRecommended Act ion #C. 6

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IS THE 28 V CONTROLLER REPLACE OR REPAIR THECIRCUIT BREAKER INSTALLED? CIRCUIT BREAKER

INSTALL THE X-FZ IN THIS SLOT

DOES THIS UNIT FAIL? REPfACE THE FIRST FZ

DOES THIS UNIT FAIL WITHANOTHER CONTROLLER INSTALLED? REPfACE THE CONTROLLER

YES

CHECK CONTINUITY~N~EEN: CHECK CONTINUITY BETWEEN:CNTRLR FZ CNTRLR FZJ2-69 J2B-89 FD VALID

SIGNALJ1-69 J2B-89 FD VALID

J2-12 J2A-65 5 V PANEL POWER J1-12 J2A-65 5 V PANEL POWERJ2-11 J2A-66 5 V PANEL POWER RET J1-11 J2&66 5 V PANEL POWER RHJ2-1 J2B-102 SERIAL DATA OUT-H J1-1 J2B-102 SERIAL DATA OUT-HJ2-2 J2B-103 SERIAL DATA OUT-L J1-2 J2B-I 03 SERIAL DATA OUT-LJ2-3 J2B-98 CLOCK-H J1-3 J2B-98 CLOCK-HJ2-I J2B-99 CLOCK-L J1-4 J2B-99 CLOCK-LJ2-5 J2B-96 STROBE-H J1-5 J2B-96 STROBE-HJ2-6 J2B-97 STROBE-L J1-6 J2B-97 STROBE-LJ2-7 J2B-1OO SERIAL DATA IN-H J1-7 J2B-100 SERIAL DATA IN-HJ2-8 J2B-101 SERIAL DATA IN-L J1-6 J2B-101 SERIAL DATA IN-L

AD-22957#

Serial 1/0 Fai1ureRecommended Action #C.7

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Page 360: Avionic Gulfstream IV-2

Recommended Action #C.8Clutch Diode Failures

NO

IOid both FZ-820S f ai 1 this same test?

I YES

Remove the cross FZ-820 andrecycle power on this FZ-820

Does this FZ-820 continue to fail?NO ,_

Replace the cross FZ-820

/

lnsta~ 1 the cross FZ-820 inthis slot, and cycle pouer

+

Does this FZ-820 pass? {I Replace the first FZ-820

NO

Discomect the servo associated Hi th this f ai lure andrecycle power on this FZ-820; trim servo for elev trim

fai lures; Aileron, then elevator servos for AP fai lures

IDoes this FZ-820 pass? Replace this servo

Check the harness for shorts:1OJ2A-63 (elev trim)1OJ2A-61 (Aileron/elevator)

Be sure all pins are locked intheir connectors.

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Page 361: Avionic Gulfstream IV-2

Recommended Action #C.9YD Engage Test Failures

( YD Engage Test Fai lures )

Did both FZ-820S fail this same test?

I YES

4Removethe cross FZ-820 andrecycle pouer on this FZ-820

t

Ooes this FZ-820 continue to fai 1?NO + Replace the cross FZ-820

YESD

v, ,

I[natal 1 the cross FZ-820 inthis slot, and cycle pcwer I

i

Does this Fz-820 pass?YES

{1Replaca the first FZ-820

NO

Measure YD quick disconnectinptt resistance; 10J2B-67/10J2A-3 I

tCheck aircraft harness and both

pilot’s and copitot’s columdisconnect suitches

NO

tCheck the YD servo poner using the procedure

outlined under SERVO POUER RELAY FAILURES

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Page 362: Avionic Gulfstream IV-2

Recommended Action #C.10AP Engage Test Failures

NODid both FZ-820S fai 1 this same test?

I YES

Does this FZ-820 continue to fai 1?

I YES

NO JI,,.I RepLace the cross FZ-820 I

t

Instal 1 the cross FZ-820 inthis slot, and cycle power

I J

i

Does this FZ-820 pass?YES

IIReplace the first FZ-820

NO

1‘

Heasure AP quick di scornect inputresistance; 10J28-54/10J2A-3

Be sure the pins are locked intheir connectors.

t J-Check aircraft harness and both

pilot’s and copilot’s columdisconnect sui tches

A

I

Check the AP servo pouer using the procedureout t ined under SERVO POUER RELAY FAILURES

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Page 363: Avionic Gulfstream IV-2

Recommended Action #Cl 1Elevator Trim Brake Failures

Elevator Trim 8rake Fai lures)

RWI the FZ-SZO (0S) and pitchtrim (351 gmwd mintenmce

teets for both FZ-SZO

It/ \

<

Did the gradmint— test Perform the sctian suegested

detected m for the pertitular fault in the

failures ? grti mintmmce test -l> .

‘-F’Check the tr in brake

I L ICheck the trim brake

fra the crmssside fra the cross si~Fz-azo : FZ-SZO: I

Be sure that these pifu Se sure that these pinsare locked in their we lacked in their

Carnctore . —tom .

#/ \

m

m4

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Page 364: Avionic Gulfstream IV-2

Recommended Action #C.12AP Brake Relay Failures

t

NODid bath FZ-820S fai 1 this same test?

I YES

Does this FZ-820 continue to fail?NO II..—. –1 Replace the cross FZ-820

1

Does this FZ-820 pass?YES

Replace the first FZ-820

NO

Disconnect the aileron servo andrecycle Power on this FZ-820

iCheck the interconnect ui ri ng

Does this FZ-820 pass? to the aileron servo. If nomiswi res found, replace the servo.

NO

Discormect the elevator servo andrecycle pouer on this Fz-820

iCheck the interconnect wiring

Does this FZ-820 pass? to the elevator servo. If nomiwires fomd, replace the servo.

NO

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Page 365: Avionic Gulfstream IV-2

Recommended Action #Cl 3YD Servo Amplifier Failures

+

No Did both FZ-820S fai L this s- teat?

IYES

t

Does this FZ-820 cmtinue to fait?

Instal t the cross FZ-820 in

this stot, and cycle pwar.

I

NO.— - - II RapLace the cross FZ-820

t

Dote this FZ-820 peas? Ra@aca the firat FZ-820n

Ooee the fault folbx YES {1Raphsethe failed

the linear actuetor? ~inear acwstor I

so

Check the harness for rniauires:1OJ1A-58 - YD ENOAOE1OJ1A-59 - EXCITATION III1OJ1A-6O - EXCITATION LO1OJ1A-61 - LVDT HI1OJ1A-62 - LWT LO1OJ1A-63 - DRIVE1OJ1A-64 - ORIVS

Se sure the pine are locked intheir mrmeetora.

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Honeywell ~###!’!’vcE

APPENDIX ESERVO SWITCHING MONITOR USED WITH

FLIGHT FAULT SUMMARY

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APPENDIX ESERVO SWITCHING MONITOR USED WITH FLIGHT FAULT SUMMARY

1.0 SERVO $hlITCHING MONITOR

The servo switching monitor is designed to verify the engaged status ofthe servos. The monitor uses hardware (discrete) and software (status)data to validate the performance of both single and dual Flight GuidanceComputer (FGC) configurations. The servo switching monitor can besubdivided into the following five major groups:

. Hardware monitor

. Pushbutton monitor

. Sensor monitor● Performance monitors monitorc Engage status monitor

2.0 HARDWARE MONITOR

The hardware portion of the servo switching monitor verifies theperformance of the servo relays. These relays are illustrated in FigureE-1. There are two levels or paths of servo control. The first level isthe normal servo engage/disengage path. The second is the abnormaldisconnect path. All disengagements using the abnormal disconnect pathwill result in a failed autopilot.

The relays used in the normal engage/disengage path are called the servoengage relays. These provide the following discrete information:

Proc/ Ref~ @ Mnemonic W Active Sicmal Description (=11

A26,B26 1 YDRELAY YD BRAKE RELAY This FGC YD brake relay is engaged

A27,B27 2 YDBRAKE YD BRAKE YD brake is active

A25,B25 3 APCLTCH AP CLUTCH Elevator and Aileron clutch isactive

A24,B24 4 APRELAY AP CLUTCH RELAY This FGC AP clutch relay isengaged

A23,B23 5 ELTCLTCH ELEV TRIM CLUTCH Elevator trim clutch is active

A22,B22 6 ELTRELAY ELEV TRIM RELAY This FGC elevator trim relay isengaged

A29,B29 7 SERVOFF SERVOS OFF All servo engage relays in thisFGC are off, thus this FGC is notcontrolling any servos

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Page 368: Avionic Gulfstream IV-2

YD

1av

10UM:; TO IJNSAR

I I @ACTUATOR

YOREIAY @ iYOSRAKE~ I

I

II

-WI

YD SNams I

IISWOPWROFF

I @I

II

II

Yo SERVO I

iI

Yu REIAY ISsRvO POWER(+2s v) I

I

II

II

I 1 I

I&vo POWER REMY(+ZSV) .

I ssRvoFF

I

ELsv TRIM I

oLulcN IRSLAY I

II

I

ELsv TRIM II

APolsc 4 ~

i- ,

COMMAND I@w 10K (A-PROC) I

2SVI TO NLSRON

I @I AND SLEVATOt?

SsRVosAPRSIAY @

&rcN APCLTCN-REIAY

A? SNGAGEAO-ZSS35*

FZ-800 Servo Clutch InterfaceFigure E-1

Each servo engage relay is controlled by only one processor; however,relay performance is monitored by both. The A-processor controlsengagement/disengagement of the elevator trim relay, while the B-processorcontrols both the AP clutch and the YD brake relays.

Only one relay is used in the abnormal disconnect path. This relay,called the servo power relay, switches power to all the servo engagerelays. When this relay opens, all servo engage relays are deprived ofpower and are consequently deactivated. The servo power relay is theprimary disconnect path used whenever any failures are detected.

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SERVO SWITCHING MONITOR APPENDIX E

A simultaneous command is required from each processor to engage the servopower relay. This inherently provides each processor with two importantfunctions:

NOTE: The servo ower relay enable command from each processor isilabelled S VOPWRV; reference designation 9 (Processors A & B

Bits 31) in Figure E-1.

. A secondary disengage ath andY. A means to independent y disengage all servos.

For example? suppose the B-processor commands the aileron and elevatorservos to disengage vla the normal engage/disengage relays. Next, su poseone of these falls and remains stuck closed. EUsin the secondary pat andcommanding the servo power rela to open (SRVOPWRV~ the B-processor can

{remove power from the clutch re ays and thus power from the servos.

Monitoring of the servo engaged status by the cross-processor allow~o;hecross-processor to disengage the system if a failure is detected.example, suppose a YD servo disengagement is requested, but due to afailure, the B-processor does not see this request and continues tocontrol the rudder. The A-processor, by commanding the servo power relayto open (SRVOPWRV), can disengage the system.

Only one discrete feedback is available to monitor the state of the servopower relay. This signal is described as follows:

Ref~ Mnemonic Name Active Siqnal Description (=1)

8 SRVPWROFF Servo The servo power relaPower i!

is open, thus removingpower from all clutc es, and power to the

Off FB servos is switched off. (Processors A & BBits 30)

The above hardware signals provide a concise description of the engagedstatus of the system. The following are a few examples of a steady statesystem:

Table E-1 shows the ex ected state of the relays when onl the YD isen aged in this FGC.7

Bnly the YD relay is on iwhile the P and Elev trimre ays are off. Since this FGC is engaged, tfieServos Off signal is low,as is the Servo Power Off feedback.

Table E-1

YDRELAY. . . 1YDBRAKE. . . 1APCLTCH. . . 0APRELAY. . . 0ELTCLTCH . . 0ELTRELAY . . 0SERVOFF. OSRVPWROFF: : 0

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SERVO SWITCHING MONITOR APPENDIX E

Table E-2 shows the state of the relays when both the AP and YD areengaged by this FGC. All relays and their corresponding brake/clutchfeedbacks are set. Since this FGC is controlling the servos, both theServos Off and Servo Power Off signals are low.

Table E-2

YDRELAY.YDBRAKE.APCLTCH.APRELAY.ELTCLTCHELTRELAYSERVOFF.SRVPWROFF

.* 1

. . 1

. . 1

. . 1

. . 1

.*

. . :

. . 0

In Table E-3 the YD and Man./Mach Trim are engaged, but in the cross-FGC.This is why the YD and Trim relays are off, but the servo feedbacks (Trimclutch, YD brake) are high. Note also that since this FGC is not engaged,~~~eServos Off signal is high, indicating that all servos are off on this.

Because the Servo Power Off feedback is not high, this FGC has notfail;d.

Table E-3

YDRELAY. . . 0YDBRAKE. . . 1APCLTCH. . . 0APRELAY. . . 0ELTCLTCH . . 1ELTRELAY . . 0SERVOFF. . . 1SRVPWROFF. . 0

Table E-4 represents a system where nothing is engaged. Again, since theServo Power Off feedback is low, this FGC is still valid.

Table E-4

YDRELAY.YDBRAKE.APCLTCH.APRELAY.ELTCLTCHELTRELAYSERVOFF.

. . 0

. . 0

. . 0

. . 0

. . 0● . o. . 1

SRVPWROFF. . 0

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Honeywell #&!!-~NcESERVO SWITCHING MONITOR APPENDIX E

Table E-5 shows the effect of a failure on the system. Here, the AP andYD are engaged by the cross-FGC, however, this FGC has failed. We knowthat this FGC has failed because the Servo Power Off signal is high.

Table E-5

YDRELAY. . . 0YDBRAKE. . . 1APCLTCH. . . 1APRELAY. . . 0ELTCLTCH . . 1ELTRELAY . . 0SERVOFF. . . 1SRVPWROFF. . 1

Tables E-2 through E-5 are representative samples of the hardware portionof the engaged states of a dual channel system. These states are what theservo switching monitor has been designed to verify. If this monitor doesnot match a pre-programmed valid state, a failure has been detected. Somefailure examples are shown below:

In Table E-6, the YD in this FGCwas commanded to engage, but did notcompletely do so. The YD Relay engaged, but the YD Brake signal did notgo high. This could be due to an isolation diode failing open. SRVPWROFFwill be set high once the servo switching monitor trips.

Table E-6

YDRELAY. . . 1YDBRAKE. . . 0APCLTCH. . . 0APRELAY. . . 0ELTCLTCH . . 0ELTRELAY . . 0SERVOFF. . . 0SRVPWROFF. . 0

In Table E-7, both the YD and MT are engaged. Both relays have closed,and their corresponding Brake/Clutch lines have gone high. A failure hasoccurred in the Servos Off signal. It remained high. There couldpossibly be a failure in this circuit. SRVPWROFF will be set high oncethe servo switching monitor trips.

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SERVO SWITCHING MONITOR APPENDIX E

Table E-7

YDRELAY. . . 1YDBRAKE. . . 1APCLTCH. . . 0APRELAY. . . 0ELTCLTCH . . 1ELTRELAY . . 1SERVOFF. . . 1SRVPWROFF. . 0

In Table E-8, the failure conditions show that the AP and Trim areengaged. What is missing is the YD. It should also be engaged. Thefailure could be caused by the YD relay itself, or with the engage commanddrivers to the relay. SRVPWROFF will be set high once the servo switchingmonitor trips.

Table E-8

YDRELAY. . . 0YDBRAKE. . . 0APCLTCH. . . 1APRELAY. . . 1ELTCLTCH . . 1ELTRELAY . . 1SERVOFF. . . 0SRVPWROFF. . 0

3.0 PUSHBUTTON MONITOR

The following pushbutton inputs are monitored and recorded by the engagelogic:

Proc/&J Mnemonic Active Siqnal Description (=1)

A1O,B19 TCS Touch control steering activeA12,B17 YDDISC YD quick disconnect NOT pushedA11,B16 APDISC AP quick disconnect NOT pushedA3,B1O STALWARN Stall warning active

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Page 373: Avionic Gulfstream IV-2

When the TCS pushbutton is pressed, and theAP is engaged, control of theaileron, elevator and trim are disengaged until the pushbutton isreleased. The state of the servo clutch engage relays is verified againstthis condition as shown in the following table:

Table E-9 shows the AP, YD and Trim are engaged. This FGC’S TCS is notactive. This is a normal engaged state.

Table E-9

YDRELAY. .YDBRAKE. .APCLTCH. .APRELAY. .ELTCLTCH .ELTRELAY .SERVOFF. .SRVPWROFF.TCS. . . .

.

.;

.1

.1

.1

.

.;

.0

. 0

Table E-10 shows TCS is active. As soon as the FGC sees this pushbutton,it disengages the AP and Elev trim clutches. This leaves only the YDengaged. Since the Elev trim clutch relay is not engaged(ELTCLTCH=ELTRELAY=O)Man./Mach trim cannot be selected. See thefollowing example.

Table E-10

YDRELAY. . . 1YDBRAKE. . . 1APCLTCH. . . 0APRELAY. . . 0ELTCLTCH . . 0ELTRELAY . . 0SERVOFF. . . 0SRVPWROFF. . 0TCS. . ...1

Table E-n shows that TCS is active. However, both the YD brake and elevtrim relays are active. This shows the state where YD and Man./Mach trimremain engaged during a TCS maneuver.

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Honeywell #jf#~f~NcESERVO SWITCHING MONITOR APPENDIX E

Table E-n

YORELAY. . . 1YDBRAKE. . . 1APCLTCH. . . 0APRELAY. . . 0ELTCLTCH . . 1ELTRELAY . . 1SERVOFF. . . 0SRVPWROFF. . 0TCS. . ...1

3.2 APDISC/YDDISC

The AP and YD quick disconnect pushbuttons are used by the operator todisengage the corresponding servos. Each input, when the pushbutton isnot pushed, will appear as a ground to the FGC. To the FGC, this is it’snormal state, and thus is assigned a “l”. In other words, the FGC assumesthe logic:

If APDISC=l, the AP quick disconnect is @pushed.

The same is true for YDDISC. The following tables show the normal stateof the relays relative to the active states of the quick disconnectpushbuttons.

NOTE: While an option for a YD quick disconnect pushbutton is provided bythe FGC, the pushbutton does not exist on the aircraft. This inputis hard-wired to signal ground at the rear connector of the FGC.Therefore, this input should always appear set to ‘l’. An inputstatus of ‘O’ implies a loose connection (or even miswire) in theharness assembly.

In Table E-12, the AP, YD and Trim relays are all engaged. The quickdisconnects are not pushed (=1).

Table E-12

YDRELAY. . . 1YDBRAKE. . . 1APCLTCH. . . 1APRELAY. . . 1ELTCLTCH . . 1ELTRELAY . . 1SERVOFF. . . 0SRVPWROFF. . 0APDISC . . . 1YDDISC . . . 1

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SERVO SWITCHING MONITOR APPENDIX E

In Table E-13, the AP quick disconnect pushbutton is being pushed causingthe AP relays to open. Since YD and Mach trim are selected, these relaysremain engaged. Since the AP quick disconnect is being pushed, APDISC =0(or active) and the AP relay is disengaged.

Table E-13

YDRELAY. . . 1YDBRAKE. . . 1APCLTCH. . . 0APRELAY. . . 0ELTCLTCH . . 1ELTRELAY . . 1SERVOFF. . . 0SRVPWROFF. . 0APDISC . . . 0YDDISC . . . 1

3.3 STALWARN

The two stall warning input discretes are filtered and voted by the engagelogic. If either input appears active, the FGC will disengage the AP.The servo switching monitor examines these discrete inputs only during APengagement. If the AP remains engaged while either stall warning isactive, an abnormal disconnect is performed.

4.0 SENSOR MONITOR

The servo switching monitor makes sure that the FGC properly disengages ifthe IRS valid (VAHRS) and/or the DADC valid (VDADC) goes invalid. Ifthese sensor voted valids (l=valid or not failed) go invalid, this monitorverifies the engaged status of the FGC. The following engaged status isallowed for each given sensor failure:

● IRS fai1 (VAHRS=O) - Man./Mach trim only (Proc A, Bit 6 and Proc B,Bit 9)

● DADC fail (VDADC=O) - Nothing unless in APPT, where AP, YD or Man./Machtrim are allowed. (Proc A, Bit 5 and Proc B, Bit 8)

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SERVO SWITCHING MONITOR APPENDIX E

The following tables show the valid relationship of the monitored states:

Table E-14 shows that the YD is engaged in this FGC. Both sensors arevalid. No other servos are engaged. This FGC is not in an approach mode.

Table E-14

YDRELAY. . . 1YDBRAKE. . . 1APCLTCH. . . 0APRELAY. . . 0ELTCLTCH . . 0ELTRELAY . . 0SERVOFF. . . 0SRVPWROFF. . 0VAHRS. . . . 1VDADC. . . . 1APPT . . . . O (Proc A, Bit 4 and Proc B,

Bit 7)

Table E-15 shows that the YD is engaged in this FGC. All other servos aredisengaged. The AHRS sensor is valid, however, the DADC is invalid. ThisFGC is in an active approach mode.

Table E-15

YDRELAY. . . 1YDBRAKE. . . 1APCLTCH. . . 0APRELAY. . . 0ELTCLTCH . . 0ELTRELAY . . 0SERVOFF. . . 0SRVPWROFF. . 0VAHRS. . . . 1VDADC. . . . 0APPT . ...1

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Honeywell ##!!~NcE

SERVO SWITCHING MONITOR APPENDIX E

5.0 PERFORMANCE MONITORS

Each processor employs a ‘handshake’ between the real-time performancemonitors and the servo switching monitor. This internal status flagverifies that the monitors are operating when required and are bypassedwhen expected. The flags monitored are defined below:

Proc/~

A9,B12

A8,B11

B6

A7B13

B15

B14

B1

Mnemonic

APPERFBY

YDPERFBY

MTMONBY

TRPERFBYELTMONBY

TRIMINOP

APSRVMON

MFYDPOS

Name

AP MonitorsBypass

YD MonitorsBypass

Man./Mach TrimMonitors Bypass

Elev TrimMonitors Bypass

TrimInoperative

AP FailureDetected

YD FailureDetected

Active Simal Description (=11

When this flag is set, it indicates thatthe AP performance monitors are beingbypassed (A&B processors).

When this flag is set, it indicates thatthe YD performance monitors are beingbypassed (A&B processors).

When this flag is set, it indicates thatthe M-Trim performance monitors are beingbypassed (B-processor only).

When these flags are set, they indicatethe elevator trim performance monitors arebeing bypassed (TRPERFBY in A-processorand ELTMONBY in B-processor).

The AP trim monitors detected aninoperative condition with the trimservos.

A failure affecting either the elevator oraileron servos has been detected.

A failure affecting the YD positionfeedback has been detected.”

All the above performance monitor bypass flags are set whenever this FGCis not engaged. For example, engaging the AP and YDwill cause APPERFBY,YDPERFBY. TRPERFBY and ELTMONBY flaas to reset to zero. MTMONBY willremain set. Disengaging the AP onl~, with the YD remaining engaged, willcause both APPERFBY and ELTMONBY flags to both be set. Engaging theM-Trim without the AP will cause the MTMONBY flag to be cleared.

The status of the two servo monitors, TRIMINOP, APSRVMON and MFYDPOS tellsthe servo switching monitor that this FGC is only partially operational.For example, if the fault flag APSRVMON is set, it indicates that afailure was detected by either the aileron or elevator servo monitors.This will cause loss of all AP functions but will not affect YD. Thislimited operation is verified by the servo switching monitor.

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SERVOSWITCHINGMONITOR APPENDIXE

6.0 ENGAGESTATUSMONITOR

The engage status portion of the servo switching monitor verifies that allinternal status flags are set to their proper states. These flags may begrouped into two major parts, channel status and engaged status flags.

6.1 A-Processor Channel Status Flaas

Proc/~ Mnemonic Name Active Sicmal Description [=11

A13 HIGHPRI ~{~~u:riority This FGC will be the first to try to engagethe servos when the system is commanded todo SO.

A28 XSTATUSV Cross-Status The cross-FGC is capable of engaging theValid system.

A31 ENGPWRV Engage Valid This FGC is engaged or may be engaged atany time.

6.2 B-Processor Channel Status Flaqs

Proc/~ Mnemonic Name Active Sicmal Descric)tion[=11

B31 ENGPWRV Engage Valid This FGC is engaged or may be engaged atany time.

B28 XSTATUSV Cross-Status The cross-FGC is capable of engaging theValid system.

B18 ACTIVCHN Active Channel Essentially the B-processor High PriorityStatus status.

6.2.1 HIGHPRI - In a dual channel installation, only one FGC will assume HighPriority. This FGC will be the box that controls the servos, allaircraft modes, and all message annunciations.

6.2.2 ENGPWRV - This flag implies the potential for engagement of this FGC.When this flag is set, this FGC either: (1 has the capability of

!engaging at any time, or (2) this FGC is a ready engaged.

6.2.3 XSTATUSV - This flag represents the status of the cross-FGC. If it isset, the cross-FGC is valid and is capable of controlling the servos.

6.2.4 ACTIVCHN - Active channel status is the priority flag used by theB-processor. It indicates that this FGC is valid, and this FGC willcontrol the servos when commanded.

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The relationship between each one of these four flags is shown below:

Table E-16 shows that both FGCS are valid. This FGC is High priority,and will engage (if not already engaged) when commanded.

Table E-16

HIGHPRI . . 1ENGPWRV . . 1XSTATUSV. . 1ACTIVCHN. . 1

Table E-17 shows that both FGCS are valid and neither FGC is engaged(ENGPWRV=l). This FGC is not High priority, and will not assume sountil the cross-FGC relinquishes it.

Table E-17

HIGHPRI . . 0ENGPWRV . . 1XSTATUSV. . 1ACTIVCHN. . 0

Table E-18 does not show very definitive information. Two states arepossible: (1) either the cross-FGC is valid and is either engaged andthis FGC is valid, or (2) the cross-FGC is not engaged, and this FGC isfailed. The other servo switching monitor data will nail-down thisactual cause.

Table E-18

HIGHPRI . . 0ENGPWRV . . 0XSTATUSV. . 1ACTIVCHN. . 0

Table E-19 shows that this FGC is High priority, but is capable of onlyFD functions (ENGPWRV=O). The cross-FGC is invalid, either because ithas failed or is not installed.

Table E-19

HIGHPRI . . 1ENGPURV . . 0XSTATUSV. . 0ACTIVCHN. . 0

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Table E-20 shows that this FGC is either en a ed, or capable of being?!engaged, while the cross-FGC has either fai e , or is not installed.

Table E-20

HIGHPRI. . . 1ENGPWRV. . . 1XSTATUSV . . 0ACTIVCHN . . 1

6.3 Enaaae Status Flaas

The following fla s rovide the engaged status of the FGC: These flags?!may be divided in o wo groups, those that denote the desired status of

the system, and those that provide the actual status of this FGC.

6.3.1 A-Processor Desired Status Flags

Proc/~ Mnemonic Name Active Sianal Description (=1)

Al MTSELECT Man./Mach Trim The Man./Mach trim is selected to beSelected engaged (if possible).

~;~:-EC: - Control of Man./Mach trim is selected. When conditions are

IfAP not engaged), Man./Mach trim will be engaged by the High

priori y“ GC.

6.3.2 B-Processor Desired Status Flags

Proc/~ Mnemonic Name Active Sianal Description (=1)

B21 YDSELECT YD Selected The YD has been selected to be engaged.

~: If this FGC has active channelstatus set, it will try to engagethe YD.

B20 APSELECT AP Selected The AP has been selected to be engaged.

~: If this FGC has active channelstatus set, it will try to engagethe AP.

6.3.2.1 YDSELECT

The YD is requested and should be or is en a ed by one of the FGCS.If this FGC cannot be engaged, YDSELECT wilf ~e cleared.

6.3.2.2 APSELECT

The AP is requested and should be or is en a ed by one of the FGCS.If this FGC cannot be engaged, APSELECT wil ?% e cleared.

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6.3.3 Ac;:a~G;tatus Flags - These flags reflect the actual engaged status ofThese flags will not change until the FGC transitions to its

desired ~tate. For example, this FGC will not set YDSELENG status untilafter this side engages the YD.

A-Processor Present Status Flags:

Proc/~ Mnemonic Name Active Siqnal Description (=1)

A21 YDSELENG YD SELECTED - YD is selected and engaged by this FGC.ENGAGED

A20 APSELENG AP SELECTED - AP is selected and engaged by this FGC.ENGAGED

A19 YDSELSTB YD SELECTED - YD is selected but not engaged by thisSTANDBY FGC (this FGC is low priority).

A18 APSELSTB AP SELECTED - AP is selected but not engaged by thisSTANDBY FGC (this FGC is low priority).

A17 YDOFFSTB YD OFF-STANDBY YD is not selected and this FGC is nothigh priority.

A16 APOFFSTB AP OFF-STANDBY AP is not selected and this FGC is nothigh priority.

A15 YDOFFINV YD OFF-INVALID YD is not selected and is invalid (cannotbe engaged by this FGC).

A14 APOFFINV AP OFF-INVALID AP is not selected and is invalid (cannotbe engaged by this FGC).

B-Processor Present Status Flags:

Proc/~ Mnemonic Name Active Sicmal Descrirltion(=1)

B4 MTSELENG Man./Mach Trim Man./Mach trim is selected and engaged bySELECTED-ENGAGED this FGC.

B5 MTSELSTB Man./Mach Trim Man./Mach trim is selected and engaged bySELECTED-STANDBY the cross-FGC.

B3 MTOFFSTB Man./Mach Trim Man./Mach trim is not selected and thisOFF-STANDBY FGC is not high priority.

B2 MTOFFINV Man./Mach Trim Man./Mach trim is not selected and isOFF-INVALID invalid (cannot be engaged by this FGC).

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6.3.3.1 SELENG Status

Selected/engaged (SELENG) status becomes active when theAP, YDorMThas been selected and when this FGC has actually engaged.

6.3.3.2 SELSTB Status

Selected/standby (SELSTB) status becomes active when the appropriatefunction has been selected, and the cross-FGC is actually engaged.This FGC can pick-up engagement when required.

6.3.3.3 OFFSTB Status

Off/standby (OFFSTB) status becomes active when the appropriatefunction is not selected and this FGC is not High Priority (HIGHPRI).

6.3.3.4 OFFINV Status

Off/invalid (OFFINV) status becomes active after a fault is detectedby this FGC making it incapable of controlling the servos.

6.4 Hardware Versus Enqa~ed Status Flaus

This section relates these engaged status flags to their correspondinghardware configurations.

ExamDle 1

System configuration:

. Dual

. FGC1YD/Man./Mach Trim engaged

. FGC2 is valid.

FGC1’S hardware configuration is shown in E-21. Both the YD relay andbrake are high, as well as the elev trim relay and clutch.

Table E-21

YDRELAY. . . 1YDBRAKE. . . 1APCLTCH. . . 0APRELAY. . . 0ELTCLTCH . . 1ELTRELAY . . 1SERVOFF. . . 0SRVPWROFF. . 0

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FGC2’S hardware configuration is shown in Table E-22. Since no relays areengaged by this side, only the brake and clutch lines are high. Theservos off signal is also high for the same reason.

Table E-22

YDRELAY. . . 0YDBRAKE. . . 1APCLTCH. . . 0APRELAY. . . 0ELTCLTCH . . 1ELTRELAY . . 0SERVOFF. . . 1SRVPWROFF. . 0

FGC1’S engage and channel status flags are shown in Table E-23. Here, wecan see that FGC1 is both high priority and active channel, making it thecontrolling FGC.

This table also shows that FGC2 is valid (XSTATUSV=l) thus, we can assumethat, if FGC1should fail, FGC2 will assume priority and keep the systemengaged.

Because FGC1has verified that it is engaged, the YDSELENG and MTSELENGflags are set. Because FGC1is high priority, none of its standby flagsare set. Since it has not failed, none of the invalid flags are set.

Table E-23

HIGHPRI . . 1ENGPWRV . . 1XSTATUSV. . 1ACTIVCHN. . 1YDSELENG. . 1APSELENG. . 0YDSELSTB. . 0APSELSTB. . 0YDOFFSTB. . 0APOFFSTB. . 0YDOFFINV. . 0APOFFINV. . 0MTSELENG. . 1MTSELSTB. . 0MTOFFSTB. . 0MTOFFINV. . 0

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FGC2’S engage and channel status flags are shown in Table E-24. Here, wecan see that FGC2 is not in control because neither its high priority oractive channel status flags are set. Because FGC2 cannot engage itsservos until FGC1 disengages, ENGPWRV is zero.

FGC2’S engage/status flags show that both YD and Man./Mach Trim areselected. Since this side is low priority, or standby, this side willreengage YD and Man./Mach Trim should FGC1disengage unexpectedly.Because the AP is not engaged, the APOFFSTB flag is set.

Table E-24

HIGHPRI . . 0ENGPWRV . . 0XSTATUSV. . 1ACTIVCHN. . 0YDSELENG. . 0APSELENG. . 0YDSELSTB. . 1APSELSTB. . 0YDOFFSTB. . 0APOFFSTB. . 1YDOFFINV. . 0APOFFINV. . 0MTSELENG. . 0MTSELSTB. . 1MTOFFSTB. . 0MTOFFINV. . 0

Example 2

System configuration:

● Dual● FGC1failed● FGC2 has re-engaged AP, YD and Man./Mach Trim

The hardware configuration of the servo switching monitor for the failedbox, FGC1, is shown in Table E-25. This data shows that FGC1has failed(SRVPWROFF=l) and disengaged (SERVOFF=l).

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Because the YDBRAKE, APCLTCH, and ELTCLTCH are all high, we can tell thatthe system is still engaged.

Table E-25

YDRELAY. . . 0- YDBRAKE. . . 1

APCLTCH. . . 1APRELAY. . . 0ELTCLTCH . . 1ELTRELAY . . 0SERVOFF. . . 1SRVPWROFF. . 1

Table E-26 shows the hardware flags associated with FGC2.

FGC2 has re-engaged the system. All its relays are engaged andoperational.

Table E-26

YDRELAY. . . 1YDBRAKE. . . 1APCLTCH. . . 1APRELAY. . . 1ELTCLTCH . . 1ELTRELAY . . 1SERVOFF. . . 0SRVPWROFF. . 0

The status flags stored by FGC1 are shown in Table E-27. Even though FGC1is low priority, it cannot set any of its standby flags (AP, YD or MTSELSTB) because it has failed. Because of its failed condition, AP, YDand Man./Mach Trim are all off-invalid. Because it can no longer engagethe system, ENGPWRV=O.

NOTE: FGC1 can still properly latch the valid status of FGC2(XSTATUSV=l).

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Table E-27

HIGHPRI .ENGPWRV .XSTATUSV.ACTIVCHN.YDSELENG.APSELENG.YDSELSTB.APSELSTB.YDOFFSTB.APOFFSTB.YDOFFINV.APOFFINV.MTSELENG.MTSELSTB.MTOFFSTB.MTOFFINV.

. 0

. 0

.

. Ii. 0

. 0

. 0

. 00

:0. 1.. :. 0. 0. 1

Table E-28 contains the status flags latched by FGC2. Here, we see thatFGC2 has assumed high priority (HIGHPRI=ACTIVCHN=l). Since FGC2 has re-engaged the system (all relays closed, see Table E-28) it has set each ofits selected-engaged status flags. In addition, FGC2 has latched FGC1’Sinvalid condition (XSTATUSV=O).

Table E-28

HIGHPRI .ENGPWRV .XSTATUSV.ACTIVCHN.YDSELENG.APSELENG.YDSELSTB.APSELSTB.YDOFFSTB.APOFFSTB.YDOFFINV.APOFFINV.MTSELENG.MTSELSTB.MTOFFSTB.MTOFFINV.

. 1

.

. :

. 1

. 1

.

. i!

. 00

:0. 0. 0.. :. 0. 0

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7.0 PUTTING IT ALL TOGETHER

Thus far, we’ve covered the meaning of each flag examined by the servoswitching monitor. Before we can review the procedure for interpretingthis data, you must be aware of its limitations.

7.1 Servo SwitchinQ Monitor Architecture

Because of its architecture, there are inherent limitations within theservo switching monitor. These limitations become apparent after a briefreview of the execution sequence.

● Execution and Sequencing

The signals described in Table E-29 are updated every 25 ms in theA-processor and every 50 ms in the B-processor. These updated signalsare then compared, at the corresponding rate, against entries in aconstants table. These entries (see Appendix F) define everycombination of permissible engaged states within the system.

If a match is found, the system has been verified to be in a validstate, and the servo switching monitor is satisfied.

If no matches are found after every entry is compared, the system isassumed to be in a transient state. The servo switching monitor willcontinue to update and compare the engaged status of the system,without tripping, until a match is found, but for only a limited time-out period. For example, with the system disengaged, assume the AP isselected (APSELECT=l). The system must first command YD engagement,then wait for the YD to actually engage (YDRELAY=YDBRAKE=l) beforecommanding AP engagement. After AP engagement is verified(APRELAY=APCLTCH=l), elev trim is commanded to engage. The monitorwill not be satisfied until the elev trim relay actually closes(ELTRELAY=ELTCLTCH=l). This process can take up to 500 ms.

If no matches are found within specific time-out periods (800 ms in theA-processor, 1 sec in the B-processor) this monitor will trip, and failthe FGC.

Just prior to failing the FGC, the processor will (1) store the lastset of updated signals into the Flight Fault Summary (FFS), then (2)open the servo power relay (reference designator 8 in Figure E-l).

These last two steps lead to shortcomings with the data reported by themonitor. Since only the last set of updated signals is stored, onlyone piece of a larger puzzle is available for evaluation. Since thisfault has been ongoing for the entire time-out period, the dynamicnature of the error is unknown.

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7.2 Data Analysis

We have not examined the actual bit sequence associated with displayedFlight Fault Summary data. This data is contained in four 16 bit words,forcing you to analyze up to 64 different flags. (See Appendix C,FENGTSTA and FENGTSTB).

The first step in analyzing this data is to reduce it to a moremanageable level.

Since this monitor runs independently in each processor, one processorwill typically trip before the other. The processor whose monitortripped first will latch the data that most accurately describes thefailure.

To determine which processor tripped first, look at the status of theServo Power Off signal (SRVPWROFF). This flag, bit 30 of FENGTSTA, andbit 30 of FENGTSTB, will equal zero in the processor that first failed.

Once you’ve isolated the processor, use this processor’s data todetermine the state of the system when the fault occurred (e.g. was theAP/YD engaged?, was only the YD/Man./Mach trim engaged?). The easiestway to determine this state is to examine the relays (APRELAY, YDRELAY)relative to their select/engage status flags (APSELECT=l? MTSELECT=l?).

Next, examine the status of the TCS and manual trim select pushbuttons todetermine if a synchronization mode was chosen.

Finally, check the priority status and the status of the cross-FGC(XSTATUSV) to determine the single/dual configuration.

After you’ve compiled this data and re-created the state of the system,compare the actual bit sequence with its corresponding progressiondefined in Appendix F. Any differences will highlight the miscomparedflags, and hopefully direct you to the cause of the fault.

E)(amDle1

A flight fault summary reads:

line 2 0000 0013 7E8C 1A63line 3 0700 00004000 1AB33B60line 4 000000000000 000000000000

Both the A and B-processors indicate failures of their servo switchingmonitors (line 2, word 2, bit 4 and line 3, word 1, bit 8).

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The first step is to decode the servo switching monitor’s data into 1’sand 0’s. This will give us the following information:

line 2 word 3 line 2 word 47E8C 1A63= 0111 1101 1000 1100 0001 10100110 0011

line 3 word 4 line 3 word 51AB3 3B60= 0001 1010 1011 Ooll 0011 1011 01100000

Step 1: Which processor tripped first?A-processor: SRVPWROFF = bit 30 FENGTSTA= 1B-processor: SRVPWROFF = bit 30 FENGTSTB= O

Therefore, the B-processor tripped first.

Step 2: What was the state of the system when the fault occurred?

Concentrating on the B-pr;;e;;s;s data (s~~ce it tripped first):

YD Brake Relay =0AP Clutch =1AP Clutch Relay =0Elev Trim Clutch =1Elev Trim Relay =0

this tells us that all servos were engaged, but not by this FGC.

This correlates with the AP and YD Select status flags (both =1). Inaddition, we can see that Man./Mach Trim was also selected (MTrimSelect-Standby =1).

Examining the pushbuttons:

YD Quick Disconnect = 1AP Quick Disconnect = 1TCS = O

shows that none are active.

Finally, checking the priority status flags shows that this FZ isstandby, or not high priority (Active Channel =0) and that the cross-FGCis valid (Cross-status valid =1).

In summary, the state of this FZ, when the fault occurred:. The B-processor failed first. when the AP and YD were both selected and engaged. by a valid cross-FGC. while this FZ was the standby channel. with no synchronization modes selected

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Step 3: Nail the cause.

We can identify the flag(s) that caused this monitor to fail by comparingthis fault code with its allowed state(s) found in Appendix F.

Look at the B-processor data (line 3, words 4 and 5) under STANDBY -AP/YD/MSEL. This represents the only allowable state for this condition.Compare this with the fault code. The flags that fall-out represent thesignals that have failed.

0011 XOXOxO1l XOXX0011 lXX1 x11O 000x - allowed state0001 1010 1011 0011 0011 1011 0110 0000 - failed statetMismatch

The failed signal: SERVOS OFF.

Since this signal is strictly internal to the FGC, replace this unit.

ExamDle 2

A flight fault sunnnaryreads:

line 2 0000 0013 5809 1B73line 3 0700 00004000 9FE713D0line 4 000000000000 000000000000

Both the A and B-processors indicate failures of their servo switchingmonitors (line 2, word 2, bit 4 and line 3, word 1, bit 8).

The first step is to decode the servo switching monitor’s data into 1’sand 0’s. This will give us the following information:

line 2 word 3 line 2 word 45809 1B73 = 0101 10000000 1001 0001 loll 0111 0011

line3” word 4 line 3 word 59FE7 13DO= 1001 1111 11100111 0001 0011 1101 0000

Step 1: Which processor tripped first?

A-processor: SRVPWROFF= bit 30 FENGTSTA = 1B-processor: SRVPWROFF= bit 30 FENGTSTB = O

Therefore, the B-processor tripped first.

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Step 2: What is the state of the system when the fault occurred?

Concentrating on the B-pr;~~;~[~s data (since it tripped first):=1

YD Brake Relay =1AP ClutchAP Clutch Relay ::Elev Trim Clutch =1Elev Trim Relay =1

This tells us that all servos were engaged by this FGC when the monitortripped.

Since all servos were engaged, we would expect both the AP and the YD tobe selected. However, a mismatch can be seen with the select statusflags. Only YDSELECT=l while APSELECT=O. Looking further shows yetanother mismatch. This time with the monitor bypass flags. The YDmonitor bypass is cleared indicating that these monitors are operational,but the AP monitor bypass is set, indicating that the AP performancemonitors are not executing. Both bypasses should have been cleared.

Man./Mach trim was also selected (MTrim Select-Engage =1). Since theAPis engaged, the Man./Mach trim monitor bypass is set. This is expected.

Examining the pushbuttons:YD Quick Disconnect =1AP Quick Disconnect =1TCS =0

shows that none were active when the fault data was latched.

Finally, the priority status flags show that this FZ is high priority(Active Channel =1) and that the cross-FGC is valid (Cross-status valid=1).

Note also that the aircraft was in its final phase of approach (APPT=l).

In summary, the state of this FZ, when the fault occurred:

. The B-processor failed first● when the AP and YD were both engaged by this FGC. with a valid cross-FGC. during an approach● with no synchronizationmodes selected. and failed because the AP was engaged but not selected to be engaged.

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Step 3: Nail the cause.

We can identify the flag(s) that caused this monitor to fail by comparingthis fault code with its allowed state(s) found in Appendix F.

Look at the B-processor data (line 3, words 4 and 5) underAP/YD/MSEL-DUAL. This represents the only allowable state for thiscondition. Compare this with the fault code. The flags that fall-outrepresent the signals that have failed.

lOOx 1111 1111 0111 0000 0011 x101 000x - allowed state1001 1111 1110 0111 0001 0011 1101 0000 - failed state

t t

Mismatch Mismatch

The mismatched signals: APSELECT and AP Monitor Bypass

With this data alone, we cannot conclusively derive the cause of thefault. Something caused the software to think that the AP should bedisengaged, but a disengagement did not occur.

Inputs to the FGC that affect disengagements include AP quick disconnect,stall warning and TCS. The primary suspect is the AP quick disconnect.

Recommended actions would be to verify these interfaces via groundmaintenance test and, if no faults are detected, to check the impedance ofeach AP quick disconnect to the FGC. If nominal values are measured, donot replace any FGCS. Instead, monitor this aircraft for additionalfaults.

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Servo Switching Monitor Worksheet

Separate the servo switching monitor’s hex fault words into binary:

A-m”ocessor B-Drocessor

31 Engage Valid 31 Engage Valid30 — Servo Power Off FB 30 — Servo Powwer Off FB29 — Servos Off 29 — Servos Off28 ~ Cross-status Valid 28 ~ Cross-status Valid

27 YD Brake 27 YD Brake26 — YD Brake Relay 26 — YD Brake Relay25 — AP Clutch 25 — AP Clutch24 ~ AP Clutch Relay 24 ~ AP Clutch Relay

23 Elev Trim Clutch 23 Elev Trim Clutch22 — Elev Trim Relay 22 — Elev Trim Relay21 — YD Selected-Engage 21 — YD Select20 — ‘AP Selected-Engage 20 — AP Select

19 YD Selected-Standby 19 TCS18 — AP Selected-Standby 18 — Active Channel17 — YD Off-Standby 17 — YD Quick Disconnect16 ~ AP Off-Standby 16 ~ AP Quick Disconnect

15 YD Off-Invalid 15 AP Trim Inoperative14 — AP Off-Invalid 14 — AP Servo ?40nitor13 — High Priority 13 — ETrim Monitor Bypass12 ~ YD Quick Disconnect 12 : AP Monitors Bypass

11 AP Quick Disconnect 11 YD Monitors Bypass10 — TCS 10 ~ Stall Iiarning

AP Monitors Bypass AHRS Valid:: YD Monitors Bypass := DADC Valid

Spare 7 Approach Track Mode;= AHRS (IRS) Valid 6= MTrim Monitor Bypass

DADC Valid MTrim Select-Standby:— Approach Track Mode := PITrimSelect-Engaged

3 Stall Warning 3 MTrim Off-Standby2— Spare 2= MTrim Off-Invalid

Mach Trim Selected YD Position Monitor:x Spare := Spare

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1. Which processor’s monitor tripped first?

A-processor: Servo power off FB (SRVPWROFF) =B-processor: Servo power off FB (SRVPWROFF) =—

2. What is the state of the system as latched by this processor?

1. YD Brake Relay2. YD Brake3. AP Clutch4. AP Clutch Relay

Elev Trim Clutch:: Elev Trim Relay7. Servos Off

3. Do the STATUS FLAGS agreeWhich do not?

ProcessorAB

High Priority/Active——ChannelCross-Status Valid——Engage Valid——

with this configuration?

A-Processor

YD Selected-Engage YD Off-StandbyAP Selected-Engage AP Off-StandbyYD Selected-Standby YD Off-InvalidAP Selected-Standby AP Off-Invalid

AP Monitors BypassYD Monitors BypassMach Trim Selected

B-Processor

ETrim Monitor Bypass MTrim Select-StandbyAP Monitors Bypass MTrim Select-EngagedYD Monitors Bypass MTrim Off-StandbyMTrim Monitor Bypass MTrim Off-InvalidYD Select AP SelectAP Servo Monitor YD Position Monitor

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Servo Switching Monitor Worksheet (cent)

4. Are any pushbuttons active?

A-Processor B-Processor

YD Quick Disconnect YD Quick Disconnect— AP Quick Disconnect AP Quick Disconnect

TCS TCS

Stall Warning Stall Warning

5. Sensor Status, are all OK?

A-Processor B-Processor

AHRS Valid AHRS Valid— DADC Valid DADC Valid— Approach Track Mode

6. Summarize the fault:

7. Nail the cause using the state tables found in Appendix F of the ServoSwitching Manual.

Al1owedState:__ _________ - ------------ ___ _____FailedState:~l_ _

2i i7--2i ~3--2i i9--16 i5--li ii--ii ?--~ :--;

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.,.

APPENDIX FSERVO SWITCHING MONITOR LOGICTABLE

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APPENDIX FSERVO SWITCHING LOGICTABLE

TCSFENGTSTA t

AP DISCAP/YD A~{:~/ENGAGED EN~!GEO M[!L M::L AP/YD

LINE 2, WORD3 t t ~ ~ t *Engage Valid 1 11Servo Power Off FB :::: : :Servos Off 0000 0 : :;0Cross-Status Valid Xxxx x x xxx

YD Brake 1111 1 1 111YD Brake Relay 11AP Clutch 11:; : i! :::AP Clutch Relay 1100 0 0 000

Elev Trim Clutch 1100 001Elev Trim Relay 100 i : 00YD Selected-Engage !1 11 iAP Selected-Engage 11;; : : 111

YD Selected-Standby 0000 0 000AP Selected-Standby 0000 : 0 000YD Off-Standby 0000 0 0 000AP Off-Standby 0000 0 0 000

LINE 2, WORD 4YD Off-Invalid 0000 0 0 000AP Off-Invalid 0000 0 0 000High Priority 1111 1 1 111YD Quick Disconnect 1111 1 1 111

AP Quick Disconnect xx x 11TCS ::XX x ; :11AP Monitors Bypass 00YD Monitors Bypass 00 :: : i! :: :

Trim Monitors Bypass 0011 0 1 110IRS Valid 11 1 1 1DADC Valid 1X* i i iApproach Track Mode Xllx i i lx ;

Stall Warning xx x x 00Spare !!XX x x xx ;Mach Trim Selected xx oSpare !!XX x : ! ! !

X = Don’t Care

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SERVO SWITCHING LOGICTABLE APPENDIX F

SINGLE STANDBYt t

FENGTSTA AP DISCYD/ YD/ AP/YD AP/YD/

EN;~GED MSEL MSEL ENGAGED TCS YD M%ELINE 2, WORD3 t ~ ~ t ~Engage Valid 1 100 + +-Servo Power Off FB l!: o 000 00 :Servos Off 00 0 011 11Cross-Status Valid 00 0 011 11 ;

YD Brake 1 1 lxx XxoYD Brake Relay ;1 00 000AP Clutch : :Xx XxoAP Clutch Relay :: 0 000 000

Elev Trim Clutch 00 1 xx XxoElev Trim Relay 00 1 :00 000YD Selected-Engage 00 000AP Selected-Engage ;: : :00 000

YD Selected-Standby 00 0 011 110AP Selected-Standby 00 0 1 00YD Off-Standby 00 : 0;0 :00AP Off-Standby 00 0 000 010

LINE 2. WORD 4YD Off-Invalid 000 000AP Off-Invalid !: ! Xoo 000High Priority 11 1 100 00YD Quick Disconnect 11 1 011 lx ;

AP Quick Disconnect xx x lxxTCS xx i x: ; xxAP Monitors Bypass ;1YD Monitors Bypass ;: : : i I 11 :

Trim Monitors Bypass 11 0 111 11IRS Valid 1 lxx xx ;DADC Valid ii 1 11X xxxApproach Track Mode lx x xxx xxx

Stall Warning xx x Xoo xxSpare xx x x x !XxMach Trim Selected 00 1 !0 XxoSpare xx ; xxx xxx

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SERVO SWITCHING LOGICTABLE APPENDIX F

STANDBY SINGLEFENGTSTA t t

AP DISC NOMSEL MSEL MODE MSEL MSEL [~DE

LINE 2. WORD3 ~ ~ ~ ~Engage Valid 1 + + 1Servo Power Off FB o : 0 0 0 ;Servos Off 1 1 1 0 1Cross-Status Valid ! x 1 1 0 0

YD Brake o 0 x x o 0YD Brake Relay o 0 0 0AP Clutch ; o ! x o 0AP Clutch Relay o 0 0 0 0 0

Elev Trim Clutch 1 0 x x 1Elev Trim Relay o 0 0 1 :YD Selected-Engage ; o 0 0 0 0AP Selected-Engage o 0 0 0 0 0

YDSelected-Standby o 0 0 0 0 0AP Selected-Standby o 0 0 0 0 0YD Off-Standby o 0 x o 0AP Off-Standby o 0 x i o 0

LINE 2. WORD4YDOff-Invalid o 0 x o 0AP Off-Invalid o 0 x o ; xHigh Priority oYD Quick Disconnect ; ; ! x ; ;

AP Quick Disconnect x x x x xTCS x x x x i xAP Monitors Bypass 1 1 1 1 1 1YD Monitors Bypass 1 1 1 1 1Trim Monitors Bypass 1 ;IRS Valid ; x ; x ; ;DADCValid x x xApproach Track Mode : ; x x ; x

Stall Warning x x x x x xSpare x x x x x xMach Trim Selected 1 1 1 1 0Spare x x : x x x

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SERVO SWITCHING LOGICTABLE APPENDIX F

FENGTSTB APIYD AP DISCTRIM YD/ YD/

MSEL INOP AP/YD ENGAGED MSEL EN[~GED MSELLINE 3. WORD 4 tt t ~ t ~Engage’Valid 11Servo Power Off FB ; : : ::: : iServos Off 00 0000 H oCross-Status Valid !? Olloox xx x

YOBrake 1111111 11 1YD Brake Relay 1 11111AP Clutch 1 ;11110 :: :AP Clutch Relay 1111110 00 0

Elev Trim Clutch 1111111 00 0Elev Trim Relay 1 11111 00 0YDSelect 1 111111AP Select 1111110 :: :

TCS Oooooox xx xActive Channel 111111 11 1YDQuick Disconnect 111111 ;AP Quick Disconnect 111111X H :

LINE 3, WORD 5AP Trim Inoperative o Ooxxx xx xAP Servo Monitor : 00000 00 0ETrim Monitor Bypass :0 00001 11 1AP Monitors Bypass 000 0001 11 1

YD Monitors Bypass 0000000 00 0Stall Warning 00 Oooox xx xIRS Valid 11 1111 11 1DADC Valid 11 11X11 xl 1

Approach Track Mode Xxlxlxx lx xMTrim Monitor Bypass 11111 1MTrim Select-Standby :0 000 : :0 :MTrim Select-engaged 11 : 0001 00 1

MTrim Off-Standby 00 00000 00 0MTrim Off-Invalid 0000000 00 0Rudder Position Mon.Spare ! ; ! !!; ! !! !

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.- -m MAINTENANCE

SERVO SWITCHING LOGICTABLE APPENDIX F

SINGLE TCSFENGTSTB t t

AP DISCAP/YD/ YD/ YD/ ~~{[D/MSEL MSEL EN~8GED MSEL AP/YD

LINE 3, WORD 4 ~ ~ t ~ * tEngage Valid 1 1Servo Power Off FB o 0 :; : : : :: :Servos Off o 0 000 0000Cross-Status Valid o 0000 !0011

YD Brake 1 1111 11111YD Brake Relay 1 1 11AP Clutch 1 : : : : 0 :00 :AP Clutch Relay 1 0000 00000

Elev Trim Clutch 1 1 000 10000Elev Trim Relay 1 1 000 10000YD Select 1 1 11111AP Select 1 : ::0 11111

TCS o Xxxx 11111Active Channel 1 1111 1111YD Quick Disconnect 1 1 1 1111 iAP Quick Disconnect 1 x ;;0 11111

LINE 3, WORD5AP Trim Inoperative x Xxxx OxxooAP Servo Monitor o x xxx 00000ETrim Monitor Bypass o 1111 11111AP Monitors Bypass o 1111 11111

YD Monitors Bypass o 0000 00000Stall Warning o x xxx 00000IRS Valid 1 1111 11111DADCValid 1 1X11 1X11X

Approach Track Mode x Xlxx XlxxMTrim Monitor Bypass 1 0111 0 11 iMTrim Select-Standby o 0000 0 :000MTrim Select-Engaged 1 1001 10000

MTrim Off-Standby o 0 000 00000MTrim Off-Invalid o 0 Xxo 00000Rudder Position Mon. 000 00 0Spare ! !lXxx xx !;X

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SERVO SWITCHING LOGICTABLE APPENDIX F

STANDBYFENGTSTB t

AP/YD/ YD/ MSEL NOAP/YD MSEL MSEL YD ONLY MODE

LINE 3, WORD4 ~Engage Valid + + + o + -+-Servo Power Off FB o 0 0 0 0 0Servos Off 1 1 1 1Cross-Status Valid i 1 i 1 1 1

YD Brake x x x x x xYD Brake Relay o 0 0 0 0 0AP Clutch x x x x x xAP Clutch Relay o 0 0 0 0 0

Elev Trim Clutch x x x x x xElev Trim Relay o 0 0 0 0 0Y(ISelect 1 1 1 0 0AP Select 1 1 ; o 0 0

TCS x x x x x xActive Channel o 0 0 0 0 0YD Quick Disconnect x x x x x xAP Quick Disconnect x x x x x x

LINE 3, WORD5AP Trim Inoperative o 0 x x x xAP Servo Monitor o 0 0 0 x xETrim Monitor Bypass 1 1 1 1 1 1AP Monitors Bypass 1 1 1 1 1 1

YDMonitors Bypass 1Stall Warning i : i x ; ;IRS Valid x x x x xDADC Valid x 1 x i 1 x

Approach Track Mode x x x x x xMTrim Monitor Bypass 1 1 1 1 1MTrim Select-Standby : 1 0 1 0MTrim Select-Engaged o : 0 0 0 0

MTrim Off-Standby 1 0 0 1 0 xMTrim Off-Invalid o 0 0 0 xRudder Position Mon. o 0 0 ! xSpare ! x x x x x

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SERVO SWITCHING LOGIC TABLE APPENDIX F

SINGLEFENGTSTB t

AP DISC NO Tcs/AP/ NOMSEL MSEL MODE YD/MSEL MSEL MODE

LINE 3, WORD 4 _t_ ~ ~ t _t_ J_Engage Valid 1 1 1Servo Power Off FB : : 0 : 0 0Servos Off o 1 0 0 1Cross-Status Valid x x ; o 0 0

YD Brake o 0 0 1 0YD Brake Relay o 0 0 1 : 0AP Clutch o 0 0 0 0 0AP Clutch Relay o 0 0 0 0 0

Elev Trim Clutch o 0 1 0Elev Trim Relay ; o 0 : 0YD Select o 0 1 i oAP Select o 0 : 1 0 0

TCS x x x x x xActive Channel 1 xYD Quick Disconnect ; i ! 1 ; xAP Quick Disconnect x o x 1 x x

LINE 3, WORD 4AP Trim Inoperative x x x 1 x xAP Servo Monitor x o 0 0 x xETrim Monitor Bypass 1 1 1 1 1 1AP Monitors Bypass 1 1 1 1 1 1

YD Monitors Bypass oStall Warning ; ; ; o ; ;IRS Valid x x x 1 x xDADC Valid 1 x x 1 1 x

Approach Track Mode x x x x x xMTrim Monitor Bypass o 1 1 0 0MTrim Select-Standby o 0 0 0 c1 :MTrim Select-Engaged 1 1 0 1 1 0

MTrim Off-Standby o 0 0 0 0 0MTrim Off-Invalid o x o 0 xMan or Emerg Trim x ! x o x xSpare x x x x x x

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APPENDIX GNON-VOLATILE RAM (NVR)

DISPLAY OF FLIGHT FAULT SUMMARY

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IAPPENDIX G

NON-VOLATILE RAM (NVR)DISPLAY OF FLIGHT FAULT SUMMARY

II 1.0 INTRODUCTIONI

The object of this document is to describe the procedure to display datafrom failures detected by the Flight Guidance Computer (FGC) software andstored in Non Volatile RAM (NVR). This data will be accessed through theFlight Fault Summary (FFS) entry of the GMT menu. Entry into the flightfault summary portion of ground maintenance test did not change and iscontained in Appendix C.

Currently, the FFS only displays the last recorded failure since the mostrecent power-up. This data is lost when FGC power is turned OFF. With theincorporation of NVR the FGC is capable of saving up to a maximum of eightfailures. For each failure, it stores twenty different states of twentydifferent and previously specified data words per processor (A & Bprocessors). The SELECT option on the display controller is used to scrollthrough the FGC failures. In addition, this data is not lost or destroyedif FGC power is removed. However, the operator has the option of clearingthe NVR data before exiting the FFS in response to FGC prompts.

INOTE: Subsequent to clearing FFS, exit Ground Maintenance Test prior to

removing power from the FGC. Failure to comply may result in the FGCreverting back to the single failure hexadecimal FFS format.

I 2.0 DISPLAY FORMAT

Besides displaying NVR data, the new FFS format is more user friendly.Unnecessary or redundant data is not displayed and English languagedescriptions of the failures replace the hexadecimal code. Also, additionalinformation such as flight conditions is included to facilitatetroubleshooting of problems in the field. Figure G-1 shows the FFS displayformat.

2.1 Field 1

This field indicates that the Flight Fault Summary has been selected. Itwill always display “50 L (or R) FFS”. It also displays the NVR buffernumber where the failure was stored, which is one digit from zero to eight.The last recorded failure will appear first and the oldest one, last. Whenall eight buffers are full, it will wrap around and start recording againfrom the first buffer.

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2.2 Fields 2 and 3

These two fields display the lateral and vertical active modes or TouchControl Steering (TCS) at the time of the failure. Refer to table G-1 for alisting of lateral and vertical mode messages.

2.3 Fields 4, 5 and 6

These three fields on line 2 contain information about the flight conditionwhen the failure occurred.

Field 4 indicates the current altitude, field 5 the current speed (IAS ORMach), and field 6 the current vertical speed for each failure.

F1 F2 F312 CHAR. 6 CHAR. 6 CHAR.

F49 CHAR. 8 [;AR. 9 ;liAR.

F819 C~~RACTERS 4 CHAR.

F9 F1O19 CHARACTERS 4 CHAR.

—. -- - -- - -- - - - - --- - - - - - --- - --

50 L FFS #8 VOR13 ALT1l----------------------------30000FT 300KTS +5500FPM

----------------------------1.AIL SERVO MOTION PM

L----------------------------2.AIL SERVO FB

JMORE

--------------------------

Flight Fault Summary FormatFigure G-1

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Table G-1Lateral and Vertical Mode Messages

VERTICAL MODE MESSAGES

MESSAGE CORRESPONDING MODE

Xxxoo NO VERTICAL MODESBYO1 PITCH FLIGHT DIR STANDBYPIT05 PITCH HOLDGA 07 PITCH GO-AROUNDVs 09 VERTICAL SPEED HOLDFLC29 FLC IASFLC2B FLC MACHALTOC ALT SEL ARMALTOD ALT SEL CAPTALT1l ALT HOLDVNV2C FMS VNAV ARMVNV2D VNAV VERTICAL SPEED HOLDVNV2F VNV FLC IAS HOLDVNV31 VNV FLC MACH HOLDVNV33 VNV ALT SEL CAPTVNV35 VNV ALT HLDGS 1A GLIDESLOPE ARMGS lB GS CAPTUREGS lD GS TRACKGS OF DUAL APP GLIDE SLOPE TRK

LATERAL MODE MESSAGES

MESSAGE CORRESPONDING MODE

Xxxoo NO LATERAL MODESBYO1 ROLL FLIGHT DIR STANDBYROL05 HEADING HOLDROL07 WINGSLEVELROL09 BANK HOLDTK 7D BANK SELECTHDGOB HEADING SELECTVOROC VOR NAV ARMVOROD VOR NAV CAPT 1VOROF VOR NAV CAPT 2VOR1l VOR NAV TRACK 1VOR13 NAV OVERSTATIONVOR43 VOR NAV AFTER OVERSTATION 1VOR45 VOR NAV AFTER OVERSTATION 2VOR14 VOR APP ARM

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Table G-1 (cent)Lateral and Vertical Mode Messages

LATERAL MODE MESSAGES (cent)

MESSAGE CORRESPONDING MODE

VOR15 VOR APP CAPT 1VOR17 VOR APP CAPT 2VOR19 VOR APP TRACK 1VORIB APP OVERSTATIONVOR4D VOR APP AFTER OVERSTATION 1VOR4F VORAPP AFTER OVERSTATION 2LOCIC NAV LOC ARMLOCID NAV LOC CAPT 1LOC 1 F NAV LOC CAPT 2LOC65 APP-NAV LOC CAPT 2LOC21 NAV LOC TRACK 1LOC47 NAV LOC TRACK 2LOC67 APP-NAV LOC TRACK 2LOC22 LOCALIZERAPP ARMLOC23 LOCALIZERAPP CAPT 1LOC25 LOCALIZER APP CAPT 2LOC69 NAV-APP LOC CAPT 2LOC27 LOCALIZERAPP TRACK 1LOC51 APP LOC TRACK 2LOC6B NAV-APP LOC TRACK 2LOC53 DUAL APP LOC TRACKBC 34 B/C LOC ARMBC 35 B/C LOC CAPT 1BC 37 B/C LOC CAPT 2BC 75 BCAPP-BC LOC CAPT 2BC 39 B/C LOC TRACK 1BC 49 BC LOC TRACK 2BC 77 BC APP-BC LOC TRACK 2LNV40 LNAV ARM MODELNV41 LNAV TRACK MODEBC 3A B/C APP LOC ARMBC 3B B/C APP LOC CAPT 1BC 3D B/C APP LOC CAPT 2BC 79 BC LOC-BC APP CAPT 2BC 3F B/C APP LOC TRACK 1BC 55 BC LOC APP TRACK 2BC 57 DUAL BC APP LOC TRACK

~: This is a generic list and not all modes apply to G-IV.

1

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2.4 Fields 7 and 8

Field 7 displays the actual failure. Refer to paragraph 3.0 for a list offield 7 failure message descriptions. Field 8 displays the category offailures as specified below.

Pu = Power-up FailureHM = Hardware FailurePM = Performance Monitor Failure$3 = Servo Switching Monitor Failure

2.5 Fields 9 and 10

Field 9 is reserved for additional messages within the same failure. Ifmore than two monitors of the same type tripped or as in the case of theServo Switching Monitor, more than two messages were required, field 10 willdisplay “MORE” and the operator will be able to scroll in more messages onlines 3 and 4 by depressing the SELECT push button on the DisplayController. As long as more messages are still available, the word “MORE”will continue to appear on field 10. If field 10 is empty, depressingSELECT will cause the FGC to start displaying the next failure.

3.0 FAILURE HIERARCHY

Upon entry into the Flight Fault Summary, the most recent fault will bedisplayed first and the operator will be able to scroll, using the SELECToption on the display controller, to the other faults in descending order ofoccurrence. If no failures of any kind are found, a message indicating “NOFAILURES” will be displayed. All referenced recommended actions arecontained in appendix D. Appendices C, E, and F should be used for decodingservo switching monitor failures.

3.1 Power-ur) Failures

A list of the power-up failure messages follows:

NVR FAILURE RECOMMENDED ACTION

ROM CHECKSUM FAIL Replace FGCRAM FAIL Replace FGCSERVO INTFC FAIL C.1-C.5, C.8-C.131/0 INTFC FAIL C.7H/WMONITOR FAIL Replace FGCSERVO PWR OFF FAIL Replace FGCACFT STRAPPING FAIL C.6A/B PROC SYNC FAIL Replace FGC

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3.2 Hardware Failures

The following messages indicate a hardware failure:

NVR FAILURE RECOMMENDED ACTION

GP POWER FAIL Check GP-820 power inputsFGC HW FAIL B.5, B.6SERIAL 1/0 ERROR A.13STUCK PUSHBUTTON A.12, B.3

3.3 Performance Monitor Failures

The following messages can be generated:

NVR FAILURE RECOMMENDED ACTION

RUD SERVO MOTIONEL SERVO MOTIONAIL SERVO MOTIONYD CLOSUREROLL CLOSUREPITCH CLOSUREYD POS VALIDATIONAIL SERVO FBEL SERVO FBNORM ACCEL LIMTRIM SERVO AMPEL TRIM RUNAWAYEL MONITORTRIM INHIBITAIL MONITORRUD CMD/RESPONSEMAN TRIM FAILMAN TRIM INOPMACH TRIM FAILMAN TRIM RUNAWAYMAN TRIM FBTRIM SW FAILTRIM LIMIT SWX-TRIM SW FAILTRIM INOP

AllA.1OA.9A.8A.7A.6A.5A.4A.3A.2A.1B.12B.11B.1OB.9B.2B.1B.18B.17B.6B.15B.13B.14B.13B.19

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3.4 Servo Switchinq Monitor Failure

If a Servo Switching Monitor failure is detected, field 8 will display“SS” and the long words ENGTSTA and ENGTSTB will be displayed in hex onfields 7 and 9.

----------------------------50 L FFS #8 VOR13 ALT1l----------------------------30000FT 300KTS +0500FPM

----------------------------ENGTSTA= 0611 030A SS

----------------------------ENGTSTB= 0604 1030 MORE

----------------------------

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Additional processing of ENGTSTA and ENGTSTB is performed and messageswill be posted on fields 7 and 9 to assist the operator to take correctiveaction. The messages are shown in Table G-2 below.

Table G-2Servo Switching Monitor Messages

ENGTSTA ENGTSTB MESSAGE

Bit 30 =0 Bit 30 =1 A-PROC FAIL FIRSTBit 30 =1 Bit 30 =0 B-PROC FAIL FIRST

Bit 10 =1 Bit 19 =1 TCS ACTIVEBit 10 =0 Bit 19 =1 TCS MISMATCHBit 10 =1 Bit 19 =0 TCS MISMATCH

Bit 3 =1 Bit 10 =1 STALL WARN ACTIVEBit 3 =0 Bit 10 =1 STALL WARN MISMATCHBit 3 =1 Bit 10 =0 STALL WARN MISMATCH

Bit 11=0 Bit 16 =0 AP DIS ACTIVEBit 11=1 Bit 16 =0 AP DIS MISMATCHBit 11=0 Bit 16 =1 AP DIS MISMATCH

Bit 12=0 Bit 17 =0 YD DIS ACTIVEBit 12=1 Bit 17 =0 YD DIS MISMATCHBit 12=0 Bit 17 =1 YD DIS MISMATCH

Bit 6=1 Bit 9 =1 IRS VALIDBit 6=0 Bit 9 =1 IRS VALID MISMATCHBit 6=1 Bit 9 =0 IRS VALID MISMATCH

Bit 5=1 Bit 8 =1 DADC VALIDBit 5=0 Bit 8=1 DADC VALID MISMATCHBit 5=1 Bit 8=0 DADC VALID MISMATCH

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Honeywell !.%@fl.cE

Para

1.0

2.0

3.0

4.0

5.0

6.0

7.0

TABLE OF CONTENTS

Title

SCOPE

EQUIPMENT AND MATERIALS FOR TESTS

FMS FAULT ISOLATION

CONFIGURATIONS

RADIOCONFIGURATION

FLIGHTCONFIGURATION

FMS SYSTEM TESTS

&

1

1

1

2

4

9

11

Flight Management SystemGround Check Procedure

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1.0 SCOPE

The format of these tests is to identify the required response withoutelaboration. These tests assume that the technicians performing thesetests are familiar with the FMZ-800 system operation. For additionalinformation on system operation, consult Pilot’s Operating Handbook(Pub. No. 28-1146-43-XX) - Section II.

All values stated in these tests should have a 10% tolerance.

2.0 EQUIP14ENTAND MATERIALS FOR TESTS

None required.

3.0 FMS FAULT ISOLATION

If the FMS appears to have failed (no CDU display on power-up) thefailure may be isolated to either the CDU, NZ, or PZ by the followingmethod. Press the NAV function key on the CDU. If there is no dtsplay

on the CDU, press the PERF function key. If there is a display on theCDU, then the NZ has failed. If no display is present, pressing any ofthe letter or number keys will result in an entry to the scratchpad. Ifno CDU display can be generated from the keypad, the CDU has failed.

Flight Management SystemGround Check Procedure

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MAINTENANCE

Honeywell H!!#i5i5.

.0 CONFIGURATIONS

There are four configuration states that the FMS may exist in: Dual,Initiated Transfer, Independent and Single.

. Single is the configuration that a single FMS system is configuredfor or a default mode when two systems in a duplex installation arenot communicating with the offside FMS.

. Independent Mode exists only in duplex installations. In this modeonly offside tuning information is transferred between systems.

. Initiated Transfer mode is applicable to duplex installations. Inthis mode offside radio tuning commands and pilot defined data baseentries are transferred automatically. Active flight plan andperformance initialization data are transferred only on commandeither through an aircraft mounted switch or via a line select keyprompt on the last page of the active flight plan.

. Dual mode is similar to initiated transfer mode except that allactive flight plan entries and performance initialization data aretransferred to the offside system without the need for a separatepilot action.

The FMS will operate in Dual or Initiated Transfer modes only when thefollowing criteria are met.

. Both systems must have the same software version {SW PROGRAM).

. Both systems must have the same navigation data base region andeffective dates (NAV DB and DB CYCLE).

. Both systems must have the same programming pin configurations(CONFIG PIN).

. Both custom data bases must be identical (CUSTOM DB).

. Both FMS’S must have the same present positions with a 10 NMtolerance (PPOS OIFF).

. Both FMS’S must be in agreement as to the master-slave relationship(SLAVE).

The information in parenthesis will be displayed on the CONFIG PROBLEMSpage if the system is not operating in the mode for which it has beenconfigured. See Figure 1.

Flight Management SystemGround Check Procedure

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CONFIG PROBLEMS 1/1t >

H SW PROGRAM PPOS DIFF H

HCONFIG PIN DB CYCLE

CUSTOM DB SLAVE H

HNAV DB

m

H

4DATA LOAD MAINTENANCE>

Figure 1

The aircraft is wired to permit the operator to change the FMSconfiguration from the CDU. Since the aircraft has been wired for thisoption, on the Maintenance Page there will be a CHANGE CONFIGprompt.Pressing the line select key next to the prompt will yield the displayshown in Figure 2. From this page you may select the desiredconfiguration offered by the prompts.

NOTE: If initiated transfer is selected, flight plan transfers areaccomplished from the last page of the ACTIVE FLT PLAN page.

( 3

a SELECTED C’ONFIG

DUAL E

BCHANGE CONFIG TO

<DUAL INITIATED XFER> ❑

Hi <SINGLE INDEPENDENT> a

IBlMaintenance

B

AD-2of36s@

Figure 2

Flight Management SystemGround Check Procedure

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c●

L

j.O RADIOCCJNFIGURATION

The following information is provided for use in configuring the TUNINGpage to reflect the radio complement installed in the aircraft.

It is possible to modify the radio list as seen on the TUNING pages. TheFMS is configured at the factory for two ADFs, two VHF COM radios, twoNAV receivers, two HFs, and two transponders. If it becomes necessary tochange these pages, the following procedure may be used.

. Press the NAV function key.

. Press the NEXT function key. You should now see the second page ofthe NAV INDEX.

. Select the MAINTENANCE option.

● Press the NEXT function key. You should now have the MAINTENANCEFAILED SENSORS page.

. Enter RC in the scratchpad using the keyboard. (Figure 3.)

/( MAINTENANCE 2/2

IFAlLED SENSORS

SENSOR HISTORY>

HEIJb

Figure 3

. Press the bottom left line select key. This results in the displayshown in Figure 4.

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Page 418: Avionic Gulfstream IV-2

RADIO CON FIG 1/1 )&,<RECORD

lRADIO TuNE 1/31

k

H

<TYPE l= ADF 21I COM 1 COM 2 I H

<NO . I NAV 1 NAV 2 I

I I H

4MAINT DE-SEL PRV FRQ>H

AD-30959-SM

Figure 4

The cursor is now 1 ocated on the upper 1 eft position of the RADIOTUNE page (ADF 1 in Figure 4). To move the cursor, use the NEXT andPREV function keys. This will also access pages 2 and 3.(Figures 5, 6 and 7.)

A

AD-309S0-SM

Figure 5

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Page 419: Avionic Gulfstream IV-2

Honeywell !!$!!!!H.CE

RADIO CONFIG 1/1

<RECORD

lRADIO TUNE 2/31

F

H

<TYPE !- HF 21 ~I I

4N0 . iXPDR 1 XPDR 2i

I I E la<MAINT DE-SEL PRV FRQ>

J@ E

AD-30961-SM

Figure 6

t ~

IE3 4RECORD

lRADIO TuNE 3/3! B1

H<TYPE 1-

III H

H<NO. I I

1 I B

HDE-SEL PRV FRQ>

AD-309s2-SM

Figure 7

To change the number suffix of the radio,NO. prompt (Figure 8). The choices are 1

press the key2, 3, and no

next to thesuffix.

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Page 420: Avionic Gulfstream IV-2

RADIO CON FIG 1/1

<RECORD

i COM 1

INAv 1

COM 2 I<NO. NAV 2 i

I i+MAINT SEL PRV FRQ>

AD-309S3-SM

Figure 8

If recall of the previous frequency is desired on radios other thanthe NAV receivers, pressing the lower right line select key willtoggle the display from SEL PREV FREQ to DE-SEL PREV FREQ (Figure 9).

SEL PREV FREQ - will cause the previously entered frequency to bedisplayed on the RADIO TUNE page in small script. (Allows togglingbetween 2 frequencies.)

DE-SEL PREV FREQ - will cause only the last entry to be displayed onthe RADIO TUNE page.

RADIO CONFIG 1/1<RECORD

IRADIO TuNE 1/31

<TYPE Imm ADF 2!

ICOM 1

INAV I

COM 21NAV 21<NO .

I I<MAINT DE-SEL PRV FRQE

AD-309S4-SM

Figure 9

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Page 421: Avionic Gulfstream IV-2

Honeywell !!f!!!!!b.c’

c When all the radios have been configured in the desired manner, theconfiguration is recorded in non-volatile memory by pressing theupper left line select key addacent to the RECORll prompt.

To change the radio type at the cursor position, press the lineselect key adjacent to the TYPE prompt. The available choices are:ADF, COM, HF, and XPDR. (Figures 10 and 11. )

1 ) 2

m<RECORD

IRADIO TUNE l/31(s

a<TYPE 1- ADF 21

ICOM 1 COM 2! H

H<NO . lNAV 1 NAV 21

I I H

DE-SEL PRV FRQ>H

AD-30965-SM

Figure 10

>

H <RECORD

lRADIO TuNE 1/31H

H<TYPE Il!lml ADF 21

jCOM 1 COM 21 B

H<NO . lNAV 1 NAV 21

I I H

DE-SEL PRV FRQ>H

AD-30966-SM

Figure 11

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Page 422: Avionic Gulfstream IV-2

6.0 FLIGHT CONFIGURATION

The FMS bank angles used during lateral track changes may be adjusted byaccessing the Flight Configuration Page. This page is accessed byentering “FC” at bottom left line select key on Maintenance Page 2. Thisresults in the display shown in Figure 12.

FLIGHT CONFIGSANK FACTO17

-- (0-15)

<MAINT

1/1

!4IH

1-aIHl

AD-30605

Figure 12

The bank factor can be adjusted between O and 15. It can only bechanged while on the ground, and only from the master FMS. The bankfactor represents the maximum bank angle to be used by the FMS,unless a higher bank is required to maintain protected airspace.

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Page 423: Avionic Gulfstream IV-2

. The FMS does not use the selected bank factor during operation within10 miles of the origin and 25 miles of the destination. During thesetimes, the FMS assumes the bank factor is 15.

. The selected bank factor is defaulted to 7. Changes made areremembered between flights. if a new computer is placed on theaircraft, the bank factor should be adjusted to desired value ifdifferent than 7.

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Page 424: Avionic Gulfstream IV-2

7.0 FMS SYSTEM TESTS

TESTTITLE NO. STEPS RESPONSE

Power Check 1.0

i!. Remove all LRUS Power All voltages shallup the aircraft and be within 10%. Allcheck all plugs for grounds shall bevoltages and grounds < .25 ohms.on correct pins.

B. Power down the aircraft CDUS should showand install all LRUS. Initialization page.Power up the aircraftand proceed to nextstep.

Data Loader 2.0

A. Obtain current NAV database disk and load database in left side FMS.

B. Load data base in rightside FMS.

c. Load data base incenter (AUX) FPIS.This step for triplexFMS installations.

D. Enter the date and timeon the NAV IDENT pageof the CDU.

NAV data base shallload in leftNZ.

NAV data base shallload in right NZ.

NAV data base shallload in third NZ.

CDU displays currentdate and time.

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Page 425: Avionic Gulfstream IV-2

Honeywell !!f!!!!!.c’

TESTTITLE NO. STEPS RESPONSE

Data Loader 2.0(cent)

E. Remove power fromaircraft for 5 min.Reapply power toaircraft.

FMS 3.0Configurations

A. Set up FMS configura-tion for DUAL orINITIATED TRANSFER.See paragraph 4.0 fordetails.

B. Using RADIOCONFIGURA-TION page, configurethe FMS to aircraftconfiguration. Performto both left and right(center if applicable)FMS systems. Seeparagraph 5.0 fordetails.

I

Verify data base dateand time are retained.

DUAL or INITIATEDTRANSFER annunciatedon CONFIGpage.

Set-up RADIOCONFIGto aircraftconfiguration.

Interface Tests 4.0

A. Set IRS Sensors to alignmode if available.

B. Enter present position Check reception ofon the POSITION INIT this position by thepage and load. sensor (IRS or Omega)

by selecting the POSSENSORS page andverify the position ofthe appropriatesensor.

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Page 426: Avionic Gulfstream IV-2

TESTTITLE NO. STEPS RESPONSE

Interface Tests 4.0(cent)

c. If an Omega is present,select the VLF/OMEGAstatus prompt and goto page two of theVLF/OMEGA DATA page.

D. Place the FMS Auto/Manual Tuning switchto AUTO position.(This switch may becontained in radiocontrol head.)

E. Enter a valid NAVfrequency on thePROGRESS page at theNAV 1 or NAV 2 prompt.

F. Select the DELETE keyon the CDU then lineselect it to theNAV prompt of thepreviously tunedradio.

G. Select the FPL keyon the CDU and entera flight plan on theACTIVE FLT PLAN pages.

H. Select FMS and theMAP mode on the NavDisplay.

Verify the date andtime with the date andtime entered. Verifyposition.

Verify that thefrequency is acceptedand the letter Rannunciated in frontof the stations ident.Verify the radio hasbeen tuned to theentered frequency.

Verify that the Rannunciator changesto an A annunciation.

Verify the display ofthis map informationon the Nav Display.

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Page 427: Avionic Gulfstream IV-2

MAINTENANCE

Honeywell WtNRh.

TESTTITLE NO. STEPS RESPONSE

Interface Tests 4.0(cent)

I. Select the PERF key Verify that grosson the CDU and enter weight and the PERFnumber of passengers DATA prompt areand cargo weight on displayed.page 5 of the PerfInit section.

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