NOTE : As the GEN 2 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 222
 201-299, 301-399, Aug 01/05 CES

 4. Fault Isolation
_______________

 A. If the fault symptom is identified by the CFDS message GCU 2 and the upper ECAM DU warning GEN 2 FAULT:
 - 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:
R  - do a pin retention check (Ref. ESPM 204823) of the sockets of the 400VC1 (Ref. AWM 24-22-01). Use a dynamometer, the CANNON value is
 1.2 daN (2.7 lbf) minimum and the SOURIAU value is 2.8 daN (6.3 lbf) minimum, in relation to pin/socket type used.
 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 (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 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).

 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 2 are shown and AC 2 busbar is supplied by GEN 2.
 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) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.

 (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 223
 201-299, 301-399, Aug 01/05 CES

 TASK 24-20-00-810-811

 Loss of the GEN 2 (Failure of the Electrical Wiring between the IDG 2, GLC 2 and GCU 2)
 1. Possible Causes
_______________
 - GCU-2 (1XU2)

 - 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 2 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 224
 201-299, 301-399, Aug 01/05 CES

 4. Fault Isolation
_______________

 **ON A/C 001-049, 051-062, 101-105, 151-152, 201-205,
　
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