4. Fault Isolation
_______________

 A. If the fault symptom is identified by the CFDS message BTC2 OR/AND GLC2 and the warnings GEN2 FAULT and AC BUS2 FAULT on the upper ECAM DU:
 - replace the GLC-2 (9XU2) (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-2 (1XU2) (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 GCU2 (1XU2) to the pin B/25 of the GLC2 (9XU2) and to the pin B/10 of the BTC2 (11XU2) . from the pin B/23 of the GLC2 (9XU2) and from the pin B/12 of the BTC2 (11XU2) to the pin B/3 of the GLC2 (9XU2), through the relay (4XU2) . from the pin B/5 of the GLC2 (9XU2) to the ground . from the pin B/12C of the GCU2 (1XU2) to the pin A/X1 of the relay (4XU2) . from the pin A/X2 of the relay (4XU2) to the ground (Ref. ASM 24-22/03).
 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 2 pushbutton switch (3XU2).

 (3) Do the operational test of the GPCU (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 display unit:
 - push the ELEC key to get the ELEC  - the correct electrical parameters of page. GEN 2 come into view
 - the AC 2 busbar is supplied by the GEN 2.
 「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : 001-049, 051-099, 101-149, 151-199, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page 286
 201-299, 301-399, Aug 01/05 CES

 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).

 (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 287
 201-299, 301-399, Aug 01/05 CES

 TASK 24-20-00-810-835

 Failure of the APU Generator Control Unit
 1. Possible Causes
_______________
 - GCU-APU (1XS)
 2. Job Set-up Information
______________________
 A. Referenced Information
 -------------------------------------------------------------------------------REFERENCE DESIGNATION
 -------------------------------------------------------------------------------
AMM 24-23-34-000-001 Removal of the GCU-APU (1XS)
 AMM 24-23-34-400-001 Installation of the GCU-APU (1XS)
 AMM 24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

 APU AMM 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied from the APU
 3. Fault Confirmation
__________________
 A. Test
 Not applicable.

 NOTE : As the APU GEN 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 GCU APU and the upper ECAM DU warning APU GEN FAULT:
 - replace the GCU-APU (1XS) (Ref. AMM TASK 24-23-34-000-001) and (Ref. AMM TASK 24-23-34-400-001).
 B. Make sure that the aircraft electrical circuits operate correctly in APU configuration.
 (1) Energize the aircraft electrical circuits from the APU (Ref. AMM TASK 24-41-00-861-002).

 (2) De-energize the aircraft electrical circuits from the APU (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 288
 201-299, 301-399, Aug 01/05 CES
　
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