________
 A. Put the aircraft back to its initial configuration.
 (1) Stop the engine 1 (Ref. AMM TASK 71-00-00-710-028).

 (2) Do the EIS stop procedure
 (Ref. AMM TASK 31-60-00-860-002).

 (3) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.

 (4) De-energize the aircraft electrical circuits
 (Ref. AMM TASK 24-41-00-862-002).

 TASK 24-20-00-810-962

 Failure of the IDG 2 Servo-Valve Wiring to the GCU 2
 1. Possible Causes
_______________
 - GCU-2 (1XU2)

 - IDG (4000XU)

 - wiring

 2. Job Set-up Information
______________________
 A. Referenced Information
 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 24-21-51-000-040 Removal of the Integrated Drive Generator -IDG 1(2),(4000XU) AMM 24-21-51-400-040 Installation of the Integrated Drive Generator -IDG
 1(2),(4000XU)
 AMM 24-22-34-000-001 Removal of the GCU-1(2) (1XU1, 1XU2)
 AMM 24-22-34-400-001 Installation of the GCU-1(2) (1XU1, 1XU2)
 AMM 24-41-00-740-002 Operational Check of GAPCU via CFDS
 AMM 24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

 External Power AMM 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
 from the External Power
 AMM 31-60-00-860-001 EIS Start Procedure
 AMM 31-60-00-860-002 EIS Stop Procedure
 AMM 71-00-00-710-003 Engine Automatic Start
 AMM 71-00-00-710-028 Engine Shutdown
 ASM 24-21/01

 3. Fault Confirmation
__________________
 A. Test
 Not applicable.

 NOTE : As the GEN 2 was set to OFF because of a true failure, the fault
____
 confirmation is not necessary.

 4. Fault Isolation
_______________
 CAUTION : BEFORE YOU START THE CHECK OF IDG WIRING THAT INCLUDES CONNECTORS,
_______ EXAMINE EACH CONNECTOR TO MAKE SURE THAT THERE IS NO OIL IN IT. IF YOU FIND OIL, CLEAN THE CONNECTOR AND CONNECT IT AGAIN. IF THE FAILURE CONTINUES, DO THE TROUBLE SHOOTING PROCEDURE AS GIVEN BELOW.
 「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 : 106-149, 229-299, 303-399, 401-499, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page C293
 Aug 01/05 CES

 A. If the fault symptom is identified by the CFDS message GCU2 (1XU2)/ IDG2 (E2-4000XU) and the upper ECAM-DU warning GEN 2 FAULT:
 - replace the GCU-2 (1XU2) (Ref. AMM TASK 24-22-34-000-001) and (Ref. AMM TASK 24-22-34-400-001).
 (1) If the fault continues:

 - do a check of the servo valve wiring (Ref. ASM 24-21/01) for an open circuit, a short to ground, a short circuit or a short to shield between: . pin B/1 of the IDG 2 and pin B/11J of the GCU 2 . pin B/2 of the IDG 2 and pin B/11H of the GCU 2 . pins B/11J and B/10H of the GCU 2 . pins B/11H and B/10H of the GCU 2.

 (2) If the wiring is not correct:

 - repair or replace as necessary.

 (3) If the wiring is correct:

 - replace the engine 2 IDG (4000XU) (Ref. AMM TASK 24-21-51-000-040) and (Ref. AMM TASK 24-21-51-400-040).
 B. Test
 (1) Aircraft Maintenance Configuration

 (a) Energize the aircraft electrical circuits
 (Ref. AMM TASK 24-41-00-861-002).

 (b) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001).

 (2) On the ELEC panel 35VU:

 - push, release and push again the GEN 2 pushbutton switch (3XU2).

 (3) Do the operational test of the GAPCU (Ref. AMM TASK 24-41-00-740-002).

 (4) Start the engine 2 (Ref. AMM TASK 71-00-00-710-003).

 (5) Do this test:

 -------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
On the ECAM control panel:  On the lower ECAM DU:
 - get the ELEC page.  - the correct electrical parameters of the GEN 2 are shown and the AC2 busbar is supplied by the GEN 2.
 「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 : 106-149, 229-299, 303-399, 401-499, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page C294
 Aug 01/05 CES

 5. Close-up
________
　
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 電源 2(97)