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 On the ECAM control panel: On the lower ECAM DU:
R - get the ELEC page. - the correct electrical parameters of
R the GEN 1 are shown and the AC1
R 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. R (4) De-energize the aircraft electrical circuits
R (Ref. AMM TASK 24-41-00-862-002).
 「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : 401-499, ∞∞24-00-00∞∞∞∞∞∞∞∞∞∞Page 227
 Aug 01/05 CESR TASK 24-00-00-810-817 R IDG 2 Thermal Disconnection R 1. Possible Causes

_______________ R - IDG (4000XU) R 2. Job Set-up Information
______________________
R A. Referenced Information
R -------------------------------------------------------------------------------R REFERENCE DESIGNATION R -------------------------------------------------------------------------------
R AMM 24-21-00-612-043 R AMM 24-21-51-000-040 R R AMM 24-21-51-400-040 R 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 3. Fault Confirmation
__________________
R A. Test
R Not applicable.

R 4. Fault Isolation

_______________ Servicing of the IDG after Oil Chemical Contamination Removal of the Integrated Drive Generator -IDG 1(2),(4000XU) Installation of the Integrated Drive Generator -IDG 1(2),(4000XU) 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 A. If the fault symptom is identified by the CFDS message: R - IDG2 (E2-4000XU) THERMAL DISCONNECT and the upper ECAM-DU warnings IDG R 2 OIL OVHT and GEN 1 FAULT or R - IDG2 (E2-4000XU) THERMAL DISC FAILED and the upper ECAM-DU warning IDG R 2 OIL OVHT:
R NOTE : Do the trouble shooting procedure for all CFDS messages that come
____ R into view with the CFDS messages IDG2 (E2-4000XU) THERMAL R DISCONNECT or IDG2 (E2-4000XU) THERMAL DISC FAILED.
R - replace the engine 2 IDG (4000XU) (Ref. AMM TASK 24-21-51-000-040) and
R (Ref. AMM TASK 24-21-51-400-040)
R - do the servicing of the IDG 2 external oil-circuit with new oil after
R oil chemical contamination (Ref. AMM TASK 24-21-00-612-043).

 「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, ∞∞24-00-00∞∞∞∞∞∞∞∞∞∞Page 228
 Aug 01/05 CESR 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 2 pushbutton switch (3XU2).

R (3) Do the operational test of the GAPCU (Ref. AMM TASK 24-41-00-740-R 002).
R (4) Start the engine 2 (Ref. AMM TASK 71-00-00-710-003).
R (5) Do this test:
R -------------------------------------------------------------------------------
R ACTION RESULT

R -------------------------------------------------------------------------------R On the ECAM control panel: On the lower ECAM DU:
R - get the ELEC page. - the correct electrical parameters of
R the GEN 2 are shown and the AC2
R busbar is supplied by the GEN 2.

R 5. Close-up

________ R A. Put the aircraft back to its initial configuration. R (1) Stop the engine 2 (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. R (4) De-energize the aircraft electrical circuits
　
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