- wiring

 2. Job Set-up Information
______________________
 A. Referenced Information
 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM  24-22-34-000-001 
AMM  24-22-34-400-001 
AMM  24-22-55-000-001 
AMM  24-22-55-400-002 
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  31-60-00-860-002 
AMM  71-00-00-710-003 
AMM  71-00-00-710-028 
ASM  24-22/02

 3. Fault Confirmation
__________________
 A. Test Not applicable.
Removal of the GCU-1(2) (1XU1, 1XU2)Installation of the GCU-1(2) (1XU1, 1XU2)Removal of the Contactors (9XU1, 9XU2, 11XU1, 11XU2)Installation of the Contactors (9XU1, 9XU2, 11XU1, 11XU2)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 ProcedureEIS Stop ProcedureEngine Automatic StartEngine Shutdown
 NOTE : As the GEN1 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 262
 201-299, 301-399, Aug 01/05 CES

 4. Fault Isolation
_______________

 A. If the fault symptom is identified by the CFDS message BTC1 OR/AND GLC1 and the warnings GEN1 FAULT and AC BUS1 FAULT on the upper ECAM DU:
 - replace the GLC-1 (9XU1) (Ref. AMM TASK 24-22-55-000-001) and (Ref. AMM TASK 24-22-55-400-002).
 (1) If the fault continues:
 - 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:
 - do a check and repair the wiring: . from the pin B/2D of the GCU1 (1XU1) to the pin B/25 of the GLC1 (9XU1) and to the pin B/10 of the BTC1 (11XU1) . from the pin B/23 of the GLC1 (9XU1) and from the pin B/12 of the BTC1 (11XU1) to the pin B/3 of the GLC1 (9XU1), through the relay (4XU1) . from the pin B/5 of the GLC1 (9XU1) to the ground . from the pin B/12C of the GCU1 (1XU1) to the pin X1 of the relay (4XU1), through the relay (20XU) . from the pin X2 of the relay (4XU1) to the ground (Ref. ASM 24-22/02).
 B. Do this operational test to make sure that the system operates correctly.
 (1) Aircraft Maintenance Configuration

 (a) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002).

 (b) Do the EIS start procedure (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 GPCU (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 display unit:
 - push the ELEC key to get the ELEC  - the correct electrical parameters of page. GEN 1 come into view
 - the AC 1 busbar is supplied by the GEN 1.
 「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : 001-049, 051-099, 101-149, 151-199, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page 263
 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 264
 201-299, 301-399, Aug 01/05 CES

 TASK 24-20-00-810-825

 Loss of the GEN 2 (Failure of the IDG 2 Feeder or GCU 2 POR Wiring)
 1. Possible Causes
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