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).
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).
 「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 C240
 Aug 01/05 CESR TASK 24-20-00-810-939 R Failure of the POR neutral wiring of the GCU 2 R 1. Possible Causes

_______________
R - GCU-2 (1XU2) R - wiring R 2. Job Set-up Information
______________________
R A. Referenced Information
R -------------------------------------------------------------------------------R REFERENCE DESIGNATION 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 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 A. If the fault symptom is identified by the CFDS message WRG: POR NEUTRAL/
R GCU2 (1XU2) and the upper ECAM-DU warning GEN 2 FAULT:
R - do a check of the Point-Of-Regulation neutral wiring for an open
R circuit between pin A/14H of the GCU 2 and neutral aircraft connection
R (Ref. ASM 24-22/01).

R (1) If there is no continuity:
R - repair or replace as necessary.

R (2) If there is continuity:
R - replace the GCU-2 (1XU2) (Ref. AMM TASK 24-22-34-000-001) and (Ref.
R AMM TASK 24-22-34-400-001).

 「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 C241
 Aug 01/05 CESR 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.

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).
　
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