R . If the oil pressure is correct: R - stop the trouble shooting.
R (3) If the fault continues:
R - do the BITE test of the GAPCU (Ref. AMM TASK 24-41-00-740-002).

R (a) If the BITE test gives the message TEST FAILED:
R - push the line key adjacent to the TEST FAILED message.

R 1_ If the maintenance message GCU1 (1XU1) comes into view:
R - replace the GCU-1 (1XU1) (Ref. AMM TASK 24-22-34-000-001)
R and (Ref. AMM TASK 24-22-34-400-001).

 「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : 401-499, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page B258
 Aug 01/05 CES

R (b) If the BITE test gives the message TEST PASSED:
R - do a check and repair the wiring of the IDG 1 disconnect
R circuit (Ref. ASM 24-21/01) for a short to 28VDC between:

R . pin B1 of the ELEC/IDG1 pushbutton switch (5XT) and pin B3 of R the relay (7XT)

R . pin B2 of the relay (7XT) and pin X1 of the IDG 1 DISC CTL R relay (3XT)

R . pin B1 of the IDG 1 DISC CTL relay and pin A/2J of the GCU 1. R - do a check and repair the contact of the P/BSW-ELEC/IDG 1 (5XT) R for correct operation between pin B1 and pin B3 (normally open) R (Ref. ASM 24-21/01).

R B. Do this operational test to make sure that the system operates correctly.

R (1) Aircraft Maintenance Configuration

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

R (b) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only)
R (Ref. AMM TASK 31-60-00-860-001).

R (2) On the ELEC panel 35VU:
R - push, release and push again the GEN 1 pushbutton switch (3XU1).

R (3) Do the operational test of the GAPCU (Ref. AMM TASK 24-41-00-740-R 002).

R (4) Start the engine 1 (Ref. AMM TASK 71-00-00-710-003).

R (5) Do this test:

R -------------------------------------------------------------------------------R ACTION RESULT
R -------------------------------------------------------------------------------
R R R R  On the ECAM control panel: - get the ELEC page.  On the lower ECAM DU: - the correct electrical parameters of the GEN 1 are shown and the AC1 busbar is supplied by the GEN 1. 
R  5. Close-up________ 

R A. Put the aircraft back to its initial configuration.
R (1) Stop the engine 1 (Ref. AMM TASK 71-00-00-710-028).
R (2) Do the EIS stop procedure

R (Ref. AMM TASK 31-60-00-860-002).
R (3) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY
R potentiometers to OFF.

 「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : 401-499, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page B259
 Aug 01/05 CESR (4) De-energize the aircraft electrical circuits R (Ref. AMM TASK 24-41-00-862-002).

R TASK 24-20-00-810-907 R IDG 2 Manual Disconnect R 1. Possible Causes
_______________
R - IDG (4000XU)
R - GCU-2 (1XU2)
R - P/BSW-ELEC/IDG 2 (6XT)
R - wiring

R 2. Job Set-up Information

______________________
R A. Referenced Information
R -------------------------------------------------------------------------------R REFERENCE DESIGNATION R -------------------------------------------------------------------------------
R AMM 12-13-24-612-041 R R AMM 24-21-00-210-046 R R AMM 24-21-00-210-047 R R AMM 24-21-00-720-041 R R AMM 24-21-51-000-040 R R AMM 24-21-51-400-040 R R AMM 24-22-34-000-001 R AMM 24-22-34-400-001 R AMM 24-41-00-740-002 R AMM 24-41-00-861-002 R R AMM 24-41-00-862-002 R R AMM 31-60-00-860-001 R AMM 31-60-00-860-002 R AMM 71-00-00-710-003 R AMM 71-00-00-710-028 R ASM 24-21/01
R 3. Fault Confirmation
__________________
R A. Test
R Not applicable.

IDG Servicing - Filling of the IDG with Oil or Addition of Oil after a Level Check Check of the Oil Level and Oil-Filter Differential-Pressure Indicator (DPI) Visual Inspection of the IDG for Oil Leaks and Check of the Electrical Circuits Operational Test of the IDG Disconnect and Reconnect (Reset) Function - Engine in Operation 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 Check of GAPCU via CFDS Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power EIS Start Procedure EIS Stop Procedure Engine Automatic Start Engine Shutdown
R NOTE : As the GEN 2 was set to off because of a true fault, the fault
____ R confirmation is not necessary.
　
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