R 4. Fault Isolation
_______________

R  A. If the fault symptom is identified by the CFDS message CTA (51XU2)/ IDG2 
R  (E2-4000XU)/ GCU2 (1XU2) and the upper ECAM-DU warning GEN 2 FAULT: 
R  - read the EPGS GROUND REPORT or POST FLIGHT REPORT to see if there is 
R  one or two of the CFDS messages that follow: 
R  . IDG2 (E2-4000XU) LOW OIL PRESSURE 
R  . IDG2 (E2-4000XU) OIL OUT TEMP SENSE / GCU2 (1XU2) 
R  (1) If one or two of the CFDS messages are given: 
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 these CFDS messages are not given: 
R  - do a check of the resistance of the Current Transformer (CT) 
R  (51XU2) (Ref. ASM 24-22/01) between: 
R  . pins 1 and 4 (10.15 ohms plus or minus 3.45 ohms) 
R  . pins 2 and 4 (10.15 ohms plus or minus 3.45 ohms) 
R  . pins 3 and 4 (10.15 ohms plus or minus 3.45 ohms). 
R  (a) If the resistance values are out of the specified limits: 
R  - replace the CT (51XU2) (Ref. AMM TASK 24-22-17-000-001) and 
R  (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 to 
R  ground, a short circuit or an open circuit between: 
R  . pin 1 of the CT and pin A/12B of the GCU 2 
R  . pin 2 of the CT and pin A/12A of the GCU 2 
R  . pin 3 of the CT and pin A/11A of the GCU 2 
R  . pin 4 of the CT and pin A/11B 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).

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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). 
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 24-22-00-810-821

R  Failure of the Generator Control Unit 1 
R  1. Possible Causes_______________ 
R  - GCU-1 (1XU1) 
R  2. Job Set-up Information______________________ 
R  A. Referenced Information 
R  -------------------------------------------------------------------------------
R  REFERENCE  DESIGNATION 
R  -------------------------------------------------------------------------------
R  AMM  24-22-34-000-001  Removal of the GCU-1(2) (1XU1, 1XU2) 
　
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