Failure of the Integrated Drive Generator 2

TASK 24-21-00-810-823-A
Failure of the Integrated Drive Generator 2

1. Possible Causes

IDG [4000XU]
IDG-ENG 2 [4000XU2]

2. Job Set-up Information
A. Referenced Information

REFERENCE	DESIGNATION
TSM TASK 24-00-00-810-809-A	Failure of the IDG 2 Oil-Out Temperature Bulb or its Wiring
TSM TASK 24-20-00-810-905-A	Low Oil Pressure of the Integrated Drive Generator 2
AMM 24-21-51-000-040	Removal of the Integrated Drive Generator - IDG 1(2)
AMM 24-21-51-000-803	Removal of the Integrated Drive Generator - IDG 1(2)
AMM 24-21-51-400-040	Installation of the Integrated Drive Generator - IDG 1(2)
AMM 24-21-51-400-803	Installation of the Integrated Drive Generator - IDG 1(2)
AMM 24-41-00-740-002	Operational Check of the GAPCU via the CFDS
AMM 24-41-00-861-002	Energize the Aircraft Electrical Circuits from the External Power
AMM 24-41-00-862-002	De-energize the Aircraft Electrical Circuits Supplied from the External Power
AMM 31-60-00-860-001	EIS Start Procedure
AMM 31-60-00-860-002	EIS Stop Procedure
AMM 71-00-00-710-003	Engine Automatic Start
AMM 71-00-00-710-028	Engine Shutdown
AMM 71-00-00-860-814	Shutdown of the Engine
AMM 71-00-00-860-823	Start the Engine (Normal Automatic Start)

3. Fault Confirmation
Subtask 24-21-00-869-051-A ** ON A/C NOT FOR ALL

A. Test
Not applicable.

NOTE: As the GEN 2 was set to OFF because of a true failure, the fault confirmation is not necessary.

4. Fault Isolation
Subtask 24-21-00-810-082-B ** ON A/C NOT FOR ALL

A. If the fault symptom is identified by the CFDS message IDG2 (E2-4000XU) and the upper ECAM-DU warning GEN 2 FAULT:
(1) If one of these CFDS messages:
- IDG2 (E2-4000XU) OIL OUT TEMP/ GCU2 (1XU2)
- IDG2 (E2-4000XU) LOW OIL PRESSURE
comes into view with IDG2 (E2-4000XU), do the trouble shooting for these messages first:
(a) Do the procedure for an overtemperature (Ref. TSM TASK 24-00-00-810-809).
(b) Do the procedure for a low oil pressure (Ref. TSM TASK 24-20-00-810-905).
(2) If the CFDS messages given in step (1) do not come into view:

replace the engine 2 IDG [4000XU] AMM 24-21-51-000-040 and AMM 24-21-51-400-040.

Subtask 24-21-00-710-082-G ** ON A/C NOT FOR ALL

B. Do this operational test to make sure that the system operates correctly.
(1) Aircraft Maintenance Configuration
(a) Energize the aircraft electrical circuits
AMM 24-41-00-861-002.
(b) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only)
AMM 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 AMM 24-41-00-740-002.
(4) Start the engine 2 AMM 71-00-00-710-003.
(5) Do this test:

ACTION	RESULT
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.

Subtask 24-21-00-810-082-F ** ON A/C NOT FOR ALL

C. If the fault symptom is identified by the CFDS message IDG2 (E2-4000XU) and the upper ECAM-DU warning GEN 2 FAULT:
(1) If one of these CFDS messages:
- IDG2 (E2-4000XU) OIL OUT TEMP/ GCU2 (1XU2)
- IDG2 (E2-4000XU) LOW OIL PRESSURE
comes into view with IDG2 (E2-4000XU), do the trouble shooting for these messages first:
(a) Do the procedure for an overtemperature (Ref. TSM TASK 24-00-00-810-809).
(b) Do the procedure for a low oil pressure (Ref. TSM TASK 24-20-00-810-905).
(2) If the CFDS messages given in step (1) do not come into view:

Replace IDG-ENG 2 [4000XU2] AMM 24-21-51-000-803 and AMM 24-21-51-400-803.

Subtask 24-21-00-710-082-D ** ON A/C NOT FOR ALL

D. Do this operational test to make sure that the system operates correctly.
(1) Aircraft Maintenance Configuration
(a) Energize the aircraft electrical circuits
AMM 24-41-00-861-002.
(b) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only)
AMM 31-60-00-860-001.
(2) In the cockpit, on the ELEC panel 35VU:

Push, release and push again the GEN 2 pushbutton switch (3XU2).

(3) Do the operational check of the GAPCU via the CFDS AMM 24-41-00-740-002.
(4) Start engine 2 AMM 71-00-00-860-823.
(5) Do this test:

ACTION	RESULT
On the ECAM control panel: Push the ELEC key to get the ELEC page.	On the lower ECAM DU: The correct electrical parameters of GEN 2 are shown and GEN 2 supplies the AC2 busbar.

5. Close-up
Subtask 24-21-00-860-061-D ** ON A/C NOT FOR ALL

A. Put the aircraft back to its initial configuration.
(1) Stop engine 2 AMM 71-00-00-860-814.
(2) Do the EIS stop procedure
AMM 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
AMM 24-41-00-862-002.

Subtask 24-21-00-860-061-G ** ON A/C NOT FOR ALL

A. Put the aircraft back to its initial configuration.
(1) Stop the engine 2 AMM 71-00-00-710-028.
(2) Do the EIS stop procedure
AMM 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
AMM 24-41-00-862-002.

[Rev.8 from Aug 2018] 2026.04.04 04:26:32 UTC