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R  . pins C and G (6.725 ohms plus or minus 2.075 ohms). 
R  (a) If the resistance values are out of the specified limits: 
R  - replace the CT-AC, 2 (41XU2) (Ref. AMM TASK 24-22-17-000-001) 
R  and (Ref. AMM TASK 24-22-17-400-001). 
R  (b) If the resistance values are in the specified limits: 
R  - do a check of the wiring (Ref. ASM 24-22/01) for a short 
R  circuit between: 
R  . pins A, B and C of the CTA and pin A/15B of the GCU 2 
R  . pin G of the CTA and pin A/14B of the GCU 2. 
R  1 If the wiring is not correct:_ 
R  - repair or replace as necessary. 
R  2 If the wiring is correct:_ 
R  - replace the GCU-2 (1XU2) (Ref. AMM TASK 24-22-34-000-001) 
R  and (Ref. AMM TASK 24-22-34-400-001). 
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 C213
 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 24-20-00-810-926

R Failure of the Feeders Between the IDG 1 and the GLC 1 R 1. Possible Causes
_______________
R - IDG (4000XU) R - GCU-1 (1XU1) R - feeders
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 24-22/01
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 1 was set to OFF because of a true failure, the fault
____ R confirmation is not necessary.
R 4. Fault Isolation
_______________
R A. If the fault symptom is identified by the CFDS message WRG: GEN1 FEEDER
R and the upper ECAM-DU warning GEN 1 FAULT:
R - Do a check of the feeders (Ref. ASM 24-22/01) for an open circuit or a
R short to airframe between:

R . Terminal T1 of the IDG 1 and pin 1 of the generator 1 contactor R module (30XN1)
 「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 C215
　
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