(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 1 pushbutton switch (3XU1).
(3) Do the operational test of the GAPCU (Ref. AMM TASK 24-41-00-740-002).
(4) Start the engine 1 (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 1 are shown and the AC1 busbar is supplied by the GEN 1.
「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 C283
Aug 01/05 CES
5. Close-up
________
A. Put the aircraft back to its initial configuration.
(1) Stop the engine 1 (Ref. AMM TASK 71-00-00-710-028).
(2) Do the EIS stop procedure
(Ref. AMM TASK 31-60-00-860-002).
(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).
TASK 24-20-00-810-958
Failure of the Phase C of the IDG 2
1. Possible Causes
_______________
- IDG (4000XU)
- GCU-2 (1XU2)
- feeder
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 24-21-51-000-040 Removal of the Integrated Drive Generator -IDG 1(2),(4000XU) AMM 24-21-51-400-040 Installation of the Integrated Drive Generator -IDG
1(2),(4000XU)
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: GEN2 FEEDER PHASE C/ IDG2 (E2-4000XU) and the upper ECAM-DU warning GEN 2 FAULT:
- do a check of the resistance of the main stator windings of the IDG 2 (Ref. ASM 24-22/01) between terminals T3 and N (7 milliohms plus or minus 1 milliohm).
「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 C285
Aug 01/05 CES
(1) If the resistance values are out of the specified limits:
- replace the engine 2 IDG (4000XU) (Ref. AMM TASK 24-21-51-000-040) and (Ref. AMM TASK 24-21-51-400-040).
(2) If the resistance values are in the specified limits:
- do a check of the feeder (Ref. ASM 24-22/01) for an open circuit condition or a high resistance between terminal T3 of the IDG 2 and terminal F of the GLC 2.
(a) If the feeder is not correct:
- repair or replace the feeder as necessary.
(b) If the feeder is correct:
- replace the GCU-2 (1XU2) (Ref. AMM TASK 24-22-34-000-001) and (Ref. AMM TASK 24-22-34-400-001).
1 If the fault continues:
_
- replace the engine 2 IDG (4000XU) (Ref. AMM TASK 24-21-51-000-040) and (Ref. AMM TASK 24-21-51-400-040).
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 電源 2(94)
