Overtemperature of the IDG 2

TASK 24-20-00-810-850-A
Overtemperature of the IDG 2

1. Possible Causes

IDG [4000XU]
Integrated Drive Generator (IDG) Oil Cooler Assembly

2. Job Set-up Information
A. Referenced Information

REFERENCE	DESIGNATION
AMM 24-21-51-000-040	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 24-41-00-740-004	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 24-20-00-700-099-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 24-20-00-810-088-B ** ON A/C NOT FOR ALL

CAUTION: AFTER AN IDG OIL LOW PRESSURE (LO PR) OR OVERHEAT (OVHT) CONDITION:

DO NOT CONNECT THE DISCONNECTED IDG1(2) AGAIN, AND
REPLACE IDG1(2).

IF YOU DO NOT OBEY THESE INSTRUCTIONS, YOU WILL INCREASE THE DAMAGE TO IDG1(2) AT THE NEXT ENGINE START.

A. If the fault symptom is identified by the CFDS message IDG 2 (OVERTEMP) and the upper ECAM DU warning IDG 2 OIL OVHT:

Replace the IDG [4000XU] AMM 24-21-51-000-040 and AMM 24-21-51-400-040
Flush the external circuit with new oil.

(1) If the fault continues:

Replace the Integrated Drive Generator (IDG) Oil Cooler Assembly AMM 73-11-60-000-001 and AMM 73-11-60-400-001.

Subtask 24-20-00-860-104-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 GEN 2 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 24-20-00-710-077-A ** ON A/C NOT FOR ALL

C. Do this test:

ACTION	RESULT
On the ECAM control panel: get the ELEC page.	On the lower ECAM display unit: the correct electrical parameters of GEN 2 are shown and AC 2 busbar is supplied by GEN 2.

5. Close-up
Subtask 24-20-00-860-105-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 04:26:14 UTC