IDG 2 Thermal Disconnection

TASK 24-00-00-810-817-A
IDG 2 Thermal Disconnection

1. Possible Causes

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

2. Job Set-up Information
A. Referenced Information

REFERENCE	DESIGNATION
AMM 24-21-00-612-043	Servicing of the IDG after Oil Chemical Contamination
AMM 24-21-00-612-804	Servicing of the IDG after Oil Chemical Contamination
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 24-00-00-869-054-A ** ON A/C NOT FOR ALL

A. Test
Not applicable.

4. Fault Isolation
Subtask 24-00-00-810-067-D ** ON A/C NOT FOR ALL

A. If the fault symptom is identified by the CFDS message:
- IDG2 (E2-4000XU) THERMAL DISCONNECT and the upper ECAM-DU warnings IDG 2 OIL OVHT and GEN 1 FAULT or
- IDG2 (E2-4000XU) THERMAL DISC FAILED and the upper ECAM-DU warning IDG 2 OIL OVHT:

NOTE: Do the trouble shooting procedure for all CFDS messages that come into view with the CFDS messages IDG2 (E2-4000XU) THERMAL DISCONNECT or IDG2 (E2-4000XU) THERMAL DISC FAILED.

Replace IDG-ENG 2 [4000XU2] AMM 24-21-51-000-803 and AMM 24-21-51-400-803
Do the servicing of the IDG 2 external oil-circuit with new oil after oil chemical contamination AMM 24-21-00-612-804.

Subtask 24-00-00-710-057-C ** 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) In the cockpit, on the ELEC panel 35VU:

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

(3) Do the BITE test of the GAPCU 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.

Subtask 24-00-00-810-067-G ** ON A/C NOT FOR ALL

C. If the fault symptom is identified by the CFDS message:
- IDG2 (E2-4000XU) THERMAL DISCONNECT and the upper ECAM-DU warnings IDG 2 OIL OVHT and GEN 1 FAULT or
- IDG2 (E2-4000XU) THERMAL DISC FAILED and the upper ECAM-DU warning IDG 2 OIL OVHT:

NOTE: Do the trouble shooting procedure for all CFDS messages that come into view with the CFDS messages IDG2 (E2-4000XU) THERMAL DISCONNECT or IDG2 (E2-4000XU) THERMAL DISC FAILED.

replace the engine 2 IDG [4000XU] AMM 24-21-51-000-040 and AMM 24-21-51-400-040
do the servicing of the IDG 2 external oil-circuit with new oil after oil chemical contamination AMM 24-21-00-612-043.

Subtask 24-00-00-710-057-F ** 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) 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.

5. Close-up
Subtask 24-00-00-860-054-C ** 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 24-00-00-860-054-F ** 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 04:26:08 UTC