Removal of the Integrated Drive Generator -IDG 1(2),(4000XU) Installation of the Integrated Drive Generator -IDG 1(2),(4000XU) Removal of the GCU-1(2) (1XU1, 1XU2) Installation of the GCU-1(2) (1XU1, 1XU2) Operational Check of GAPCU via CFDS Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power EIS Start Procedure EIS Stop Procedure Engine Automatic Start Engine Shutdown
R NOTE : As the GEN 2 was set to OFF because of a true failure, the fault
____ R confirmation is not necessary.
R 4. Fault Isolation
_______________
R CAUTION : BEFORE YOU START THE CHECK OF IDG WIRING THAT INCLUDES CONNECTORS,
_______ R EXAMINE EACH CONNECTOR TO MAKE SURE THAT THERE IS NO OIL IN IT. R IF YOU FIND OIL, CLEAN THE CONNECTOR AND CONNECT IT AGAIN. R IF THE FAILURE CONTINUES, DO THE TROUBLE SHOOTING PROCEDURE AS R GIVEN BELOW.
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R A. If the fault symptom is identified by the CFDS message IDG2 (E2-4000XU)
R SERVO VLV RTN/ GCU2 (1XU2) and the upper ECAM-DU warning GEN 2 FAULT:
R - do an electrical resistance test of the IDG 2 servo valve (Ref. ASM 24-
R 21/01) between:
R . pins B/1 and B/2 (75 ohms plus or minus 6 ohms)
R . pins B/2 and IDG case (do a check for a short circuit of the
R servo-valve return wiring to the IDG case).
R (1) If the resistance values are out of the specified limits:
R - replace the engine 2 IDG (4000XU) (Ref. AMM TASK 24-21-51-000-040)
R and (Ref. AMM TASK 24-21-51-400-040).
R (2) If the resistance values are in the specified limits:
R - do a check of the servo- valve return wiring (Ref. ASM 24-21/01)
R for a short to ground or a short to shield between:
R . pin B/2 of the IDG 2 and pin B/11H of the GCU 2
R . pin B/11H and pin B/10H of the GCU 2.
R (a) If the wiring is not correct:
R - repair or replace as necessary.
R (b) If the wiring is correct:
R - replace the GCU-2 (1XU2) (Ref. AMM TASK 24-22-34-000-001) and
R (Ref. AMM TASK 24-22-34-400-001).
R 1 If the fault continues:_
R - replace the engine 2 IDG (4000XU) (Ref. AMM TASK 24-21-51-
R 000-040) and (Ref. AMM TASK 24-21-51-400-040).
R B. Do this operational test to make sure that the system operates correctly.
R (1) Aircraft Maintenance Configuration
R (a) Energize the aircraft electrical circuits
R (Ref. AMM TASK 24-41-00-861-002).
R (b) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only)
R (Ref. AMM TASK 31-60-00-860-001).
R (2) On the ELEC panel 35VU:
R - push, release and push again the GEN 2 pushbutton switch (3XU2).
R (3) Do the operational test of the GAPCU (Ref. AMM TASK 24-41-00-740-
R 002).
R (4) Start the engine 2 (Ref. AMM TASK 71-00-00-710-003).
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : 401-499, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page B291
Aug 01/05 CES
R (5) Do this test:
R -------------------------------------------------------------------------------
R ACTION RESULT
R -------------------------------------------------------------------------------
R On the ECAM control panel: On the lower ECAM DU:
R - get the ELEC page. - the correct electrical parameters of
R the GEN 2 are shown and the AC2
R busbar is supplied by the GEN 2.
R 5. Close-up________
R A. Put the aircraft back to its initial configuration.
R (1) Stop the engine 2 (Ref. AMM TASK 71-00-00-710-028).
R (2) Do the EIS stop procedure
R (Ref. AMM TASK 31-60-00-860-002).
R (3) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY
R potentiometers to OFF.
R (4) De-energize the aircraft electrical circuits
R (Ref. AMM TASK 24-41-00-862-002).
R TASK 24-20-00-810-918
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本文链接地址：A320 Trouble Shooting Manual 排故手册 电源 2(61)
