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 Engine 1(2) 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 PMG/ GCU2 (1XU2) and the upper ECAM-DU warning GEN 2 FAULT:
R - replace the engine 2 IDG (4000XU) (Ref. AMM TASK 24-21-51-000-040) and
R (Ref. AMM TASK 24-21-51-400-040).
R (1) If the fault continues:
R - do a check of the wiring of the IDG 2 PMG stator (Ref. ASM 24-R 22/01) for a short circuit, an open circuit, a short to ground or a
R short to shield between:
R . pin B/12 of the IDG 2 and pin C/10 of the GCU 2
R . pin B/13 of the IDG 2 and pin C/11 of the GCU 2
R . pin B/14 of the IDG 2 and pin C/9 of the GCU 2
R . pins C/10, C/11, C/9 and pin C/7 of the GCU 2 (short to shield of R the PMG wiring).
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 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).
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.
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Aug 01/05 CES
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 24-20-00-810-910 R Failure of the IDG 1 PMG Stator or its Wiring to the GCU 1 R 1. Possible Causes
_______________
R - IDG (4000XU) R - GCU-1 (1XU1) R - wiring
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