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R  . pins B/11H and B/10H of the GCU 1. 
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-1 (1XU1) (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 1 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 1 pushbutton switch (3XU1). 
R  (3) Do the operational test of the GAPCU (Ref. AMM TASK 24-41-00-740-
R  002). 
R  (4) Start the engine 1 (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 B282
 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 1 are shown and the AC1 
R  busbar is supplied by the GEN 1. 
R  5. Close-up________ 
R  A. Put the aircraft back to its initial configuration. 
R  (1) Stop the engine 1 (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 24-20-00-810-915

R Failure of the IDG 2 Servo Valve or its Wiring R 1. Possible Causes
_______________
R - IDG (4000XU) R - GCU-2 (1XU2) R - wiring
R 2. Job Set-up Information
______________________
R A. Referenced Information
R -------------------------------------------------------------------------------R REFERENCE DESIGNATION R -------------------------------------------------------------------------------
R AMM 24-21-51-000-040 R R AMM 24-21-51-400-040 R R AMM 24-22-34-000-001 R AMM 24-22-34-400-001 R AMM 24-41-00-740-002 R AMM 24-41-00-861-002 R R AMM 24-41-00-862-002 R R AMM 31-60-00-860-001 R AMM 31-60-00-860-002 R AMM 71-00-00-710-003 R AMM 71-00-00-710-028 R ASM 24-21/01
R 3. Fault Confirmation
__________________
R A. Test
R Not applicable.

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.
 「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 B284
 Aug 01/05 CES

R  A. If the fault symptom is identified by the CFDS message IDG2 (E2-4000XU) 
R  SERVO VLV/ 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) 
　
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