Failure of the IDG2 Cooler

TASK 24-20-00-810-856-A
Failure of the IDG2 Cooler

1. Possible Causes

IDG2 oil cooler
IDG2 oil cooling tubing

2. Job Set-up Information
A. Referenced Information

REFERENCE	DESIGNATION
AMM 24-21-49-000-040	Removal of the Tubings - IDG Cooling Oil
AMM 24-21-49-400-040	Installation of the Tubings - IDG Cooling Oil
AMM 24-41-00-740-004	Operational Check of the GPCU 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 71-00-00-710-003	Engine Automatic Start
AMM 71-00-00-710-028	Engine Shutdown
AMM 73-11-60-000-001	Removal of the Integrated Drive Generator (IDG) Oil Cooler Assembly
AMM 73-11-60-400-001	Installation of the Integrated Drive Generator (IDG) Oil Cooler Assembly

3. Fault Confirmation
Subtask 24-20-00-700-113-A ** ON A/C NOT FOR ALL

A. Test
Not applicable.

NOTE: As the GEN2 was set to OFF because of a true failure, the fault confirmation is not necessary.

4. Fault Isolation
Subtask 24-20-00-810-103-A ** ON A/C NOT FOR ALL

A. If the fault symptom is identified by the CFDS message IDG COOLER 2 and the warning IDG2 OIL OVHT on the upper ECAM DU:

replace the IDG2 oil cooler AMM 73-11-60-000-001 and AMM 73-11-60-400-001.

(1) If the fault continues:

do a check for cooler tubing blockage and replace the IDG2 oil cooling tubing which is blocked AMM 24-21-49-000-040 and AMM 24-21-49-400-040.

Subtask 24-20-00-860-116-A ** 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 GEN2 pushbutton switch (3XU2).

(3) Do the operational check of the GPCU with the CFDS AMM 24-41-00-740-004.
(4) Start the engine 2 AMM 71-00-00-710-003.

Subtask 24-20-00-710-091-A ** ON A/C NOT FOR ALL

C. Do this test:

ACTION	RESULT
1.On the ECAM control panel: get the ELEC page.	On the lower ECAM display unit: the correct electrical parameters of GEN2 are shown and AC2 busbar is supplied by GEN2.

5. Close-up
Subtask 24-20-00-860-117-A ** 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) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
(3) De-energize the aircraft electrical circuits
AMM 24-41-00-862-002.

[Rev.8 from Aug 2018] 2026.04.04 04:26:15 UTC