Cirrus Garmin GFC 700 Скачать руководство пользователя страница 8

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HAPTER

22-10: GFC 700 A

UTOMATED

LIGHT

ONTROL

YSTEM

CIRRUS A

IRPLANE

AINTENANCE

ANUAL

ROUBLESHOOTING

MODELS SR22

AND

SR22T

“PFT” (white text on red background)
annunciation is displayed on PFD.

Pre-flight test has failed.

Ensure Pers Avionics system
is in proper working order. Check for
proper operation of GIA Integrated
Avionics Unit, GSU ADAHRS, and all
GSA servos.

Verify no red X’s are displayed on
MFD and PFDs.

Verify no related alert messages are
displayed on PFD (press [ALERTS]).

Check AUX – SYSTEM STATUS page
on MFD to verify all LRUs are online
(green check).

Isolate fault to an LRU. Replace this
LRU and confirm resolution of
annunciation.

No aural alert is heard after successful
pre-flight test.

Audio operation fault has occurred.

Repeat autopilot engagement,
followed by disengagement to
confirm audio operation fault.

Verify connections for GIA 1/GMA 1
and GIA 2/GMA 2 audio interface.

Autopilot clutches cannot be
overpowered.

Servo clutch torque settings are
incorrect.

Check the servo clutch torque
settings.

Perform Adjustment/Test - GSM 86
Servo Clutch Test.

(Refer to 22-10)

Trim hesitates during trim switch
operation.

Excessive friction on aircraft pitch
trim system.

Press trim switch on yoke in one
direction until it reaches the stop.
Using stop watch, time trim speed
from one end of travel to opposite
stop. Verify elapsed time measures
20±3 seconds for each direction.

Trouble - GFC 700 Autopilot System

Probable Cause

Remedy

23 Dec 2016

Содержание Garmin GFC 700

Страница 1: ...nd is used to stabilize aircraft pitch roll and yaw optional axes Pitch autotrim provides trim commands to the pitch trim servo to relieve any long term effort required by the pitch servo The system c...

Страница 2: ...vos and provides Autopilot engagement and annunciation Autopilot command and control Auto trim operation Manual electric trim Two axis airplane control pitch and roll including approaches Level LVL mo...

Страница 3: ...apter interfaces with the dual GIA 63W Integrated Avionics computers through serial communication on separate RS 485 ports Trim commands from the yoke switches are routed through the GTA 82 when autop...

Страница 4: ...nd controls engagement of the drive clutch solenoid The servo mount contains a capstan and slip clutch The capstan transfers the output torque of the servo actuator to the mechanical flight control su...

Страница 5: ...is positioned in front of the MFD and PFD For maintenance practices pertinent to the GCU 479 FMS keyboard see Flight Management Computing section of Navigation And Pitot Static Systems Refer to 34 60...

Страница 6: ...MC 707 AFCS MODE CONTROLLER PITCH TRIM CARTRIDGE GIA 63W INTEGRATED AVIONICS COMPUTER 2 GIA 63W INTEGRATED AVIONICS COMPUTER 1 MFD PFD GTA 82 PITCH TRIM ADAPTER GSA 80 GSM 86 YAW SERVO optional GSA 81...

Страница 7: ...Perspective Avionics system is in proper working order Check for proper operation of GIA Integrated Avionics Unit GSU ADAHRS and all GSA servos Verify no red X s are displayed on MFD and PFD Verify n...

Страница 8: ...solution of annunciation No aural alert is heard after successful pre flight test Audio operation fault has occurred Repeat autopilot engagement followed by disengagement to confirm audio operation fa...

Страница 9: ...C 707 Check GMC 707 wiring and connector Perform Operational Test GFC 700 Autopilot Refer to 22 10 Replace GMC 707 Refer to 22 10 MANIFEST GMC software mismatch Communication halted annunciation is di...

Страница 10: ...nunciation is displayed on PFD The elevator is mis trimming down Check AUX SYSTEM STATUS page on MFD to verify pitch servo is online green check Verify pitch servo is receiving power Check pitch servo...

Страница 11: ...ational Test GFC 700 Autopilot Refer to 22 10 Replace roll servo Refer to 22 10 AIL black text on yellow background annunciation is displayed on PFD The aileron is mis trimming to right Check for poss...

Страница 12: ...onfiguration Probable Cause Remedy YAW white text on red background annunciation is displayed on PFD Yaw axis failure has occurred Check AUX SYSTEM STATUS page on MFD to verify yaw servo is online gre...

Страница 13: ...in lb 1 69 Nm of torque during disengage ment e Turn fasteners counter clockwise to loosen locking cams f Disconnect electrical connector from back of mode controller Remove mode controller 2 Install...

Страница 14: ...se to tighten locking cams Torque fasteners 20 2 in lb 2 26 0 22 Nm f Reset KEYPADS AP CTRL circuit breaker g If GMC 707 has been replaced with a new or different unit or original unit has been repair...

Страница 15: ...L CHAPTER 22 10 GFC 700 AUTOMATED FLIGHT CONTROL SYSTEM MODELS SR22 AND SR22T MAINTENANCE PRACTICES 15 Figure 22 10 2 GMC 707 AFCS Mode Controller 1 RADIO MODULE BRACKET REF LEGEND 1 GMC 707 Mode Cont...

Страница 16: ...assembly GTA 82 Pitch Trim Adapter a Remove screws and washers securing pitch trim adapter to mounting plate 3 Assembly GTA 82 Pitch Trim Adapter a Position mounting plate to pitch trim adapter and se...

Страница 17: ...YSTEM MODELS SR22 AND SR22T MAINTENANCE PRACTICES 17 Figure 22 10 3 GTA 82 Pitch Trim Adapter RH AFT LONGERON REF LEGEND 1 Mounting Plate 2 Pitch Trim Adapter 3 Screw 4 Washer 5 Bolt 6 Spacer 7 Nut TI...

Страница 18: ...ION The servo actuator and servo mount must fit flush together withnogapsbeforetighteningmountingbolts Donotunder any circumstances try to close gap by tightening mounting bolts or the servo mount wil...

Страница 19: ...to servo output gear e Install GSA 80 servo actuator Refer to 22 10 D GSA 81 Servo Actuator See Figure 22 10 4 See Figure 22 10 5 1 Removal GSA 81 Servo Actuator a Set BAT 1 BAT 2 and AVIONICS switch...

Страница 20: ...lb 3 95 0 56 Nm Refer to 20 60 e Connect servo actuator connector to aircraft harness NOTE Ensure that harness is properly secured to the airframe f Reset AP SERVOS circuit breaker g If GSA 81 has be...

Страница 21: ...AT 1 BAT 2 and AVIONICS switches to OFF positions b Pull AP SERVOS circuit breaker c Remove access panel CF5 Refer to 6 00 d Serials w Air Conditioning Remove condenser Refer to 21 50 e Disconnect pit...

Страница 22: ...tan and wrap short end of bridle cable approximately 480 clockwise such that cable exits bottom of capstan NOTE Align cable keeper so arm extends through mounting bracket hole but does not contact pul...

Страница 23: ...tension If elevator control cable tension falls outside specified tolerance perform Adjustment Test Elevator System Rigging Refer to 27 30 e On servo capstan position bridle cable stop ball at 9 o clo...

Страница 24: ...cable clamps is set 25 0 2 0 0 0 lb 11 3 0 9 0 0 kg If bridle cable tension falls outside speci fied tolerance loosen aft clamp assembly and adjust bridle cable as required to obtain 25 0 2 0 0 0 lb 1...

Страница 25: ...astellated Nut 7 Pulley 8 Bridle Cable 9 Bolt 10 Star Washer 5 21 22 4 9 3 10 16 15 1 5 14 6 9 2 ELEVATOR CABLES REF BRACKET REF NOTE 4 4 13 9 9 4 4 4 9 4 9 4 9 4 12 7 17 BULKHEAD FS186 REF 11 Retaini...

Страница 26: ...22T 26 Figure 22 10 4 Pitch Servo 2 of 2 19 19 19 19 19 19 19 6 ELEVATOR CABLES REF NOTE BULKHEAD FS186 REF LEGEND 3 Screw 4 Washer 6 Nut 8 Bridle Cable 9 Bolt 19 Clamp 20 Bridle Cable End Fitting 21...

Страница 27: ...roll servo to mounting bracket and remove roll servo from airplane 2 Disassembly GSM 86 Roll Servo Mount a Remove screws and washers securing stiffener ring to capstan cable guards b Remove cable gua...

Страница 28: ...lb 1 13 0 23 Nm Refer to 20 60 4 Installation GSM 86 Roll Servo Mount a Position roll servo to mounting bracket and secure with bolts and washers b Torque bolts 35 0 5 0 in lb 3 95 0 56 Nm Refer to 20...

Страница 29: ...re with bolts and nuts Torque nuts 50 5 in lb 5 6 0 6 Nm Refer to 20 60 j Position LH end of bridle cable and clamp assembly to LH aileron cable and loosely secure with bolts and nuts k While pushing...

Страница 30: ...N REF BRACKET REF 2 8 9 3 11 12 1 3 8 14 LEGEND 1 Plug 2 Screw 3 Washer 4 Capstan 5 Nut 6 Clamp 7 Bridle Cable 8 Bolt 9 Star Washer 10 GSM 86 Roll Servo Mount 11 Stiffener Ring 12 Cable Guard 13 Retai...

Страница 31: ...ts and washers securing yaw servo to mounting bracket and remove yaw servo from airplane 2 Disassembly GSM 86 Yaw Servo Mount a Remove screws and washers securing stiffener ring to capstan cable guard...

Страница 32: ...rque bolt 35 0 5 0 in lb 3 95 0 56 Nm Refer to 20 60 d Install cable guards e Position stiffener ring to capstan cable guards and secure with screws and washers Torque screws 10 0 2 0 in lb 1 13 0 23...

Страница 33: ...ecess h Ensure three wraps of bridle cable exist around capstan and that stop ball is in center of cable wrap when cable is at center of travel i Ensure that stop ball can not become disengaged from c...

Страница 34: ...0 0 0 lb 11 3 0 9 0 0 kg o Using scale verify 20 1 rudder deflection angle p Remove rigging lockout pin from rudder actuation pulley in empennage q Ensure flight control systems operate through full r...

Страница 35: ...lug 2 Screw 3 Washer 4 Capstan 5 Slip Clutch Cartridge 6 Clamp 7 Bridle Cable 8 Bolt RUDDER CABLE REF 7 11 9 3 8 3 8 1 13 8 3 6 15 NOTE Ensure bridle cable does not rub on cable guards 9 Star Washer 1...

Страница 36: ...2 of 2 7 PULLEY REF 8 6 3 3 6 16 17 RUDDER CABLE REF 7 8 3 6 6 3 17 16 7 14 BRACKET REF BULKHEAD 222 REF BATTERY 2 SHELF REF ELT SHELF REF LEGEND 3 Washer 6 Clamp 7 Bridle Cable 8 Bolt 14 GSA 80 Serv...

Страница 37: ...t completion the PFT annunciation will clear e To verify trim switches are operating correctly perform the following trim switch checks 1 On pilot s yoke momentarily actuate trim roll switch to the le...

Страница 38: ...on power lever Verify TO is annunciated on PFD for both pitch and roll modes and command bars indicate a wings level pitch up attitude 11 Press FD on GMC 707 to deactivate Go Around mode and reset Fli...

Страница 39: ...center 12 Press AP on GMC 707 to engage autopilot 13 Rotate pitch command wheel on GMC 707 down to command full NOSE DN 14 Hold yoke firmly and verify mis trim annunciation is displayed on PFD 15 Whil...

Страница 40: ...nge of motion prior to initiating test If test must be stopped press AP DISC on yoke to disconnect autopilot See Figure 27 10 2 NOTE Flight control surfaces may need to be lockout pinned for automated...

Страница 41: ...to zero NOTE Afterdataiscollectedandprocessed minimum and maximum torque readings from initial direction of test are displayed on PFD The servo immediately reverses direction and performs test in oppo...

Страница 42: ...CHAPTER 22 10 GFC 700 AUTOMATED FLIGHT CONTROL SYSTEM CIRRUS AIRPLANE MAINTENANCE MANUAL MAINTENANCE PRACTICES MODELS SR22 AND SR22T 42 23 Dec 2016 Intentionally Left Blank...

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