(4) Start the engine 1 (Ref. AMM TASK 71-00-00-710-003).
C. Do this test:
-------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
On the ECAM control panel: On the lower ECAM display unit:
- get the ELEC page. - the correct electrical parameters of GEN 1 are shown and AC 1 busbar is supplied by GEN 1.
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : 001-049, 051-099, 101-149, 151-199, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page 202
201-299, 301-399, 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) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : 001-049, 051-099, 101-149, 151-199, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page 203
201-299, 301-399, Aug 01/05 CES
TASK 24-20-00-810-803
Loss of the GEN 1 (Failure of the Electrical Wiring between the IDG 1, GLC 1 and GCU 1)
1. Possible Causes
_______________
- GCU-1 (1XU1)
- IDG (4000XU)
- wiring
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 24-21-51-000-040
AMM 24-21-51-400-040
AMM 24-22-34-000-001
AMM 24-22-34-400-001
AMM 24-41-00-740-002
AMM 24-41-00-861-002
AMM 24-41-00-862-002
AMM 31-60-00-860-001
AMM 71-00-00-710-003
AMM 71-00-00-710-028
ASM 24-22/01
3. Fault Confirmation
__________________
A. Test Not applicable.
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 Test of the Ground power Control Unit (GPCU)Energize the Aircraft Electrical Circuits from Engine 1(2)De-energize the Aircraft Electrical Circuits Supplied from the External PowerEIS Start ProcedureEngine Automatic StartEngine Shutdown
NOTE : As the GEN 1 was set to OFF because of a true failure, the fault
____
confirmation is not necessary.
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : 001-049, 051-099, 101-149, 151-199, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page 204
201-299, 301-399, Aug 01/05 CES
4. Fault Isolation
_______________
**ON A/C 001-049, 051-062, 101-105, 151-152, 201-205,
A. If the fault symptom is identified by the CFDS message CHECK IDG 1 PHASE SEQ and the upper ECAM DU warning GEN 1 FAULT:
- do a check of the wiring for phase inversion on the feeders between respectively the IDG 1 pins A/T1, B/T2, C/T3 and the GLC 1 pins D, E, F and between respectively the GLC 1 pins D, E, F and the GCU 1 pins B/1A, B/2B, C/3A (Ref. ASM 24-22/01).
(1) If the wiring is not correct:
- repair it.
(2) If the wiring is correct:
- replace the GCU-1 (1XU1) (Ref. AMM TASK 24-22-34-000-001) and (Ref. AMM TASK 24-22-34-400-001).
(a) If the fault continues:
- replace the IDG (4000XU) (Ref. AMM TASK 24-21-51-000-040) and (Ref. AMM TASK 24-21-51-400-040).
**ON A/C 063-099, 106-149, 153-199, 206-299, 301-399,
A. If the fault symptom is identified by the CFDS message CHECK IDG 1 PHASE SEQ and the upper ECAM DU warning GEN 1 FAULT:
- do a check of the wiring for phase inversion on the feeders between respectively the IDG 1 pins A/T1, B/T2, C/T3 and the module 30XN1 pins 1, 2, 3 and between respectively the module 30XN1 pins 1, 2, 3 and the GCU 1 pins B/1A, B/2B, C/3A (Ref. ASM 24-22/01).
(1) If the wiring is not correct:
- repair it.
(2) If the wiring is correct:
- replace the GCU-1 (1XU1) (Ref. AMM TASK 24-22-34-000-001) and (Ref. AMM TASK 24-22-34-400-001).
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本文链接地址：A320 Trouble Shooting Manual 排故手册 电源 1(97)
