R  A. If the fault symptom is identified by the CFDS message IDG2 (E2-4000XU) 
R  GEN CT/ GCU2 (1XU2) and the upper ECAM-DU warning GEN 2 FAULT: 
R  - do an electrical resistance test of the IDG 1 current transformer (Ref. 
R  ASM 24-22/01) between: 
R  . pins A/6 and A/1 (12 ohms plus or minus 2 ohms) 
R  . pins A/7 and A/1 (12 ohms plus or minus 2 ohms) 
R  . pins A/8 and A/1 (12 ohms plus or minus 2 ohms). 
R  (1) If the resistance values are out of the specified limits: 
R  - replace the engine 2 IDG (4000XU) (Ref. AMM TASK 24-21-51-000-040) 
R  and (Ref. AMM TASK 24-21-51-400-040). 
R  (2) If the resistance values are in the specified limits: 
R  - do a check of the wiring of the IDG 2 current transformer (Ref. ASM 
R  24-22/01) for an open circuit, a short to ground or a short circuit 
R  between: 
R  . pin A/1 of the IDG 2 and pin A/14E of the GCU 2 
R  . pin A/6 of the IDG 2 and pin A/14D of the GCU 2 
R  . pin A/7 of the IDG 2 and pin A/15E of the GCU 2 
R  . pin A/8 of the IDG 2 and pin A/15D of the GCU 2. 
R  (a) If the wiring is not correct: 
R  - repair or replace as necessary. 
R  (b) If the wiring is correct: 
R  - replace the GCU-2 (1XU2) (Ref. AMM TASK 24-22-34-000-001) and 
R  (Ref. AMM TASK 24-22-34-400-001). 
R  1 If the fault continues:_ 
R  - replace the engine 2 IDG (4000XU) (Ref. AMM TASK 24-21-51-
R  000-040) and (Ref. AMM TASK 24-21-51-400-040). 
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 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).

 「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 B247
 Aug 01/05 CES

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 
R  (Ref. AMM TASK 24-41-00-862-002).

R TASK 24-20-00-810-904 R Low Oil Pressure of the Integrated Drive Generator 1 R 1. Possible Causes
_______________
R - IDG (4000XU) R - GCU-1 (1XU1) 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
　
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