(4) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002).
TASK 24-20-00-810-964
Failure of the POR Sense Wiring or the Feeders of the IDG 2
1. Possible Causes
_______________
- GCU-2 (1XU2)
- wiring
- feeders
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 24-22-34-000-001 Removal of the GCU-1(2) (1XU1, 1XU2)
AMM 24-22-34-400-001 Installation of the GCU-1(2) (1XU1, 1XU2)
AMM 24-41-00-740-002 Operational Check of GAPCU via CFDS
AMM 24-41-00-861-002 Energize the Aircraft Electrical Circuits from the
External Power AMM 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
AMM 31-60-00-860-001 EIS Start Procedure
AMM 31-60-00-860-002 EIS Stop Procedure
AMM 71-00-00-710-003 Engine Automatic Start
AMM 71-00-00-710-028 Engine Shutdown
ASM 24-22/01
3. Fault Confirmation
__________________
A. Test
Not applicable.
NOTE : As the GEN 2 was set to OFF because of a true failure, the fault
____
confirmation is not necessary.
4. Fault Isolation
_______________
A. If the fault symptom is identified by the CFDS message WRG: POR/ GCU2 (1XU2)/ WRG: FEEDER and the upper ECAM-DU warning GEN 2 FAULT:
- do a check of the Point-Of-Regulation (POR) sense wiring (Ref. ASM 24-22/01) for a short to ground, a short circuit or an open circuit between: . terminal D of the GLC 2 and pin A/14G of the GCU 2 (phase A) . terminal E of the GLC 2 and pin A/15H of the GCU 2 (phase B) . terminal F of the GLC 2 and pin A/15G of the GCU 2 (phase C) . pin A/14H of the GCU 2 and ground.
「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 : 106-149, 229-299, 303-399, 401-499, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page C299
Aug 01/05 CES
(1) If the wiring is not correct:
- repair or replace as necessary.
(2) If the wiring is correct:
- replace the GCU-2 (1XU2) (Ref. AMM TASK 24-22-34-000-001) and (Ref. AMM TASK 24-22-34-400-001).
(3) If the fault continues:
- do a check and repair the feeders (Ref. ASM 24-22/01) for an open circuit or a high resistance between: . terminal T1 of the IDG 2 and terminal D of the GLC 2 . terminal T2 of the IDG 2 and terminal E of the GLC 2 . terminal T3 of the IDG 2 and terminal F of the GLC 2 . terminal N of the IDG 2 and airframe ground.
B. Test
(1) Aircraft Maintenance Configuration
(a) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(b) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001).
(2) On the ELEC panel 35VU:
- push, release and push again the GEN 2 pushbutton switch (3XU2).
(3) Do the operational test of the GAPCU (Ref. AMM TASK 24-41-00-740-002).
(4) Start the engine 2 (Ref. AMM TASK 71-00-00-710-003).
(5) Do this test:
-------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
On the ECAM control panel: On the lower ECAM DU:
- get the ELEC page. - the correct electrical parameters of the GEN 2 are shown and the AC2 busbar is supplied by the GEN 2.
5. Close-up
________
A. Put the aircraft back to its initial configuration.
(1) Stop the engine 2 (Ref. AMM TASK 71-00-00-710-028).
(2) Do the EIS stop procedure
(Ref. AMM TASK 31-60-00-860-002).
「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 : 106-149, 229-299, 303-399, 401-499, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page D200
Aug 01/05 CES
(3) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
(4) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002).
INTEGRATED DRIVE GENERATOR SYSTEM (IDG, GCU) - FAULT ISOLATION PROCEDURES
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