R 4. Fault Isolation
_______________

R A. If the fault symptom is identified by the maintenance message IDG2 R (E2-4000XU) MANUAL DISCONNECT and by the upper ECAM-DU warnings IDG 2 OIL R LO PR or IDG 2 OIL OVHT:
R NOTE : You can find this message with other CFDS fault messages. First,
____ R do the trouble shooting for all the other CFDS fault messages.
R (1) Read the flight log book and the maintenance log book to identify the
R cause of the IDG disconnect.

R (2) If there is no cause or if the cause is unknown:
R - do a check of the Differential Pressure Indicator (DPI) of the IDG
R 2 (Ref. AMM TASK 24-21-00-210-046),
R - do a check of the scavenge filter and charge filter (if installed).

R (a) If the DPI is extended:
R - replace the engine 2 IDG (4000XU) (Ref. AMM TASK 24-21-51-000-R 040) and (Ref. AMM TASK 24-21-51-400-040).

R (b) If the DPI is not extended:
R - do a visual check of the IDG 2 oil level (Ref. AMM TASK 24-21-R 00-210-046).

R  1_  If the oil level is not correct:
R  - do a visual inspection of the IDG 2 for oil leaks (Ref. AMM 
R  TASK 24-21-00-210-047). 

R a_ If you find leaks:
R - repair or replace the components as necessary to remove
R the oil leaks.

R b_ If you find no leaks:
R - add oil (Ref. AMM TASK 12-13-24-612-041)
R - connect the IDG 2 (if disconnected)
R - do a dynamic disconnect test of the IDG 2 (Ref. AMM TASK
R 24-21-00-720-041).

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 GCU2 (1XU2) comes into view:
R - replace the GCU-2 (1XU2) (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 B262
 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 2 disconnect
R circuit (Ref. ASM 24-21/01) for a short to 28VDC between:

R . pin B1 of the ELEC/IDG2 pushbutton switch (6XT) and pin B3 of
R the relay (8XT)

R . pin B2 of the relay (8XT) and pin X1 of the IDG 2 disconnect
R control relay (4XT)

R . pin B1 of the IDG 2 disconnect control relay and pin A/2J of
R the GCU 2.
R - do a check and repair the contact of the P/BSW-ELEC/IDG 2 (6XT)
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 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 R R R  On the ECAM control panel: - get the ELEC page.  On the lower ECAM DU: - the correct electrical parameters of the GEN 2 are shown and the AC2 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).

 「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 B263
 Aug 01/05 CESR (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).
　
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