Failure of the IDG 1

TASK 24-20-00-810-822-A
Failure of the IDG 1

1. Possible Causes

Generator 1 contactor-module 30XN1
Terminal block 1999VT
Terminal block 400VT1
Terminal blocks T1, T2, T3 and N of IDG 1
Receptacle 400VC1
[4000XU1]

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

3. Fault Confirmation
Subtask 24-20-00-700-066-A ** ON A/C NOT FOR ALL

A. Test
Not applicable.

NOTE: As the GEN 1 was set to OFF because of a true failure, the fault confirmation is not necessary.

4. Fault Isolation

CAUTION: BEFORE YOU START THE CHECK OF IDG WIRING THAT INCLUDES CONNECTORS, EXAMINE EACH CONNECTOR TO MAKE SURE THAT THERE IS NO CONTAMINATION IN IT. IF YOU FIND CONTAMINATION, CLEAN THE CONNECTOR AND CONNECT IT AGAIN. IF THE FAILURE CONTINUES, DO THE TROUBLE SHOOTING PROCEDURE AS GIVEN BELOW.

Subtask 24-20-00-810-066-B ** ON A/C NOT FOR ALL

A. If the fault symptom is identified by the CFDS message IDG 1 (GEN DIODE) and the upper ECAM DU warning GEN 1 FAULT:
(1) Do a visual inspection and repair or replace as necessary:

Generator 1 contactor-module 30XN1
Terminal block 1999VT
Terminal block 400VT1
Terminal blocks T1, T2, T3 and N of IDG 1
Receptacle 400VC1 .

(2) Replace [4000XU1] AMM 24-21-51-000-040 and AMM 24-21-51-400-040.

Subtask 24-20-00-860-082-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 1 pushbutton switch (3XU1).

(3) Do the operational check of the GPCU with the CFDS AMM 24-41-00-740-004.
(4) Start the engine 1 AMM 71-00-00-710-003.

Subtask 24-20-00-710-066-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 1 are shown and AC 1 busbar is supplied by GEN 1.

5. Close-up
Subtask 24-20-00-860-083-A ** ON A/C NOT FOR ALL

A. Put the aircraft back to its initial configuration.
(1) Stop the engine 1 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 04:26:12 UTC