- do a check of the CFDS for messages related to the ECU engine-speed sense-function. Do the trouble shooting for CFDS messages related to the ECU.

 (3) If there is no message or no disconnection:

 - do a check of the resistance of the IDG 2 PMG stator (Ref. ASM 24-22/01) between: . pins B/12 and B/13 (1 ohm plus or minus 0.05 ohm) . pins B/12 and B/14 (1 ohm plus or minus 0.05 ohm) . pins B/13 and B/14 (1 ohm plus or minus 0.05 ohm).
 (a) If the resistance values are out of the specified limits:

 - replace the engine 2 IDG (4000XU) (Ref. AMM TASK 24-21-51-000-040) and (Ref. AMM TASK 24-21-51-400-040).

 (b) If the resistance values are in the specified limits:

 - do a check of the wiring of the IDG 2 PMG stator (Ref. ASM 24-22/01) for a short circuit, an open circuit, a short to ground or a short to shield between: . pin B/12 of the IDG 2 and pin C/10 of the GCU 2 . pin B/13 of the IDG 2 and pin C/11 of the GCU 2 . pin B/14 of the IDG 2 and pin C/9 of the GCU 2 . pins C/10, C/11, C/9 and pin C/7 of the GCU 2 (short to shield of the PMG wiring).
 1 If the wiring is not correct:
_ - repair or replace as necessary.
 2 If the wiring is correct:
_
 - 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:
_
 - replace the engine 1 IDG (4000XU) (Ref. AMM TASK 24-21-51-000-040) and (Ref. AMM TASK 24-21-51-400-040).

 B. Test

 (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 GAPCU (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 DU:
 - get the ELEC page.  - the correct electrical parameters of the GEN 2 are shown and the AC2 busbar is supplied by the 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) Do the EIS stop procedure
 (Ref. AMM TASK 31-60-00-860-002).

 (3) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.

 (4) De-energize the aircraft electrical circuits
 (Ref. AMM TASK 24-41-00-862-002).

 TASK 24-20-00-810-951

 Failure of the Feeders or the POR Sense Wiring of the IDG 1
 1. Possible Causes
_______________
 - GCU-1 (1XU1)

 - feeders

 - wiring

 2. Job Set-up Information
______________________
 A. Referenced Information
 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM  24-22-34-000-001 
AMM  24-22-34-400-001 
AMM  24-41-00-740-002 
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  24-22/01

 3. Fault Confirmation
__________________
 A. Test Not applicable.
Removal of the GCU-1(2) (1XU1, 1XU2)Installation of the GCU-1(2) (1XU1, 1XU2)Operational Check of GAPCU via CFDSEnergize the Aircraft Electrical Circuits from the External PowerDe-energize the Aircraft Electrical Circuits Supplied from the External PowerEIS Start ProcedureEIS Stop ProcedureEngine Automatic StartEngine Shutdown
 NOTE : As the GEN 1 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 WRG: FEEDER/WRG: POR/ GCU1 (1XU1) and the upper ECAM-DU warning GEN 1 FAULT:
 - do a check of the feeders (Ref. ASM 24-22/01) for an open circuit or a high resistance between: . terminal T1 of the IDG 1 and terminal D of the GLC 1 . terminal T2 of the IDG 1 and terminal E of the GLC 1 . terminal T3 of the IDG 1 and terminal F of the GLC 1 . terminal N of the IDG 1 and the airframe ground.
　
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