(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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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 電源 1(97)