Operational Test of the IDG Disconnect and Reconnect Function - Engine Static

TASK 24-21-00-710-040-A
Operational Test of the IDG Disconnect and Reconnect Function - Engine Static

WARNING: BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER THE ENGINE SHUTDOWN. USE APPLICABLE THERMAL GLOVES. THE ENGINE PARTS CAN STAY HOT FOR ONE HOUR AFTER SHUTDOWN AND CAN BURN YOU.

ZONE: 438
ZONE: 448

1. Reason for the Job
Refer to the MPD TASK: 242100-04
OPERATIONAL CHECK OF INTEGRATED DRIVE GENERATOR (IDG) DISCONNECT AND RECONNECT FUNCTION.

To do a check of the IDG disconnect system and reset system.

NOTE: This procedure is only applicable for an engine replacement.

NOTE: There is an alternative method that is specially applicable for an IDG replacement, refer to (Ref. TASK 24-21-00-720-041).

2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	Torque wrench: range to between 22 and 20 lbf.in (0.25 and 0.23 m.daN )

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
438	FAN COWL
448	FAN COWL
FOR [1000EM1] (ENGINE-1)
438AR
FOR [1000EM2] (ENGINE-2)
448AR

C. Referenced Information

REFERENCE	DESIGNATION
TASK 24-41-00-861-002-A	Energize the Aircraft Electrical Circuits from the External Power
TASK 24-41-00-861-002-A-01	Energize the Aircraft Electrical Circuits from the APU
TASK 24-41-00-861-002-A-02	Energize the Aircraft Electrical Circuits from Engine 1(2)
TASK 24-41-00-862-002-A	De-energize the Aircraft Electrical Circuits Supplied from the External Power
TASK 24-41-00-862-002-A-01	De-energize the Aircraft Electrical Circuits Supplied from the APU
TASK 24-41-00-862-002-A-02	De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)
TASK 31-60-00-860-001-A	EIS Start Procedure
TASK 31-60-00-860-002-A	EIS Stop Procedure
TASK 71-13-00-010-040-A	Opening of the Fan Cowl Doors
TASK 71-13-00-010-040-B	Opening of the Fan Cowl Doors
TASK 71-13-00-410-040-A	Closing of the Fan Cowl Doors
TASK 71-13-00-410-040-B	Closing of the Fan Cowl Doors
IDG - Reset Ring ** ON A/C NOT FOR ALL

3. Job Set-up
Subtask 24-21-00-861-050-A ** ON A/C NOT FOR ALL

A. Aircraft Maintenance Configuration
(1) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(2) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only)
(Ref. AMM TASK 31-60-00-860-001).
(3) On the ECAM control panel, push the ELEC key to get the ELEC page.

Subtask 24-21-00-010-050-A ** ON A/C NOT FOR ALL

B. Open the right fan cowl door (Ref. AMM TASK 71-13-00-010-040):
(1) FOR [1000EM1] (ENGINE-1)
438AR
(2) FOR [1000EM2] (ENGINE-2)
448AR

Subtask 24-21-00-865-050-A ** ON A/C NOT FOR ALL

C. Make sure that this(these) circuit breaker(s) is(are) closed:

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
122VU	ELEC/IDG2/DISC	2XT	T25
122VU	ELEC/IDG1/DISC	1XT	T24

Subtask 24-21-00-865-051-A ** ON A/C NOT FOR ALL

D. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
122VU	ELEC/GCU/2	2XU2	T27
122VU	ELEC/GCU/1	2XU1	T26

4. Procedure

CAUTION: ENGAGE THE IDG DISCONNECT MECHANISM WITH THE DISCONNECT RESET RING BEFORE YOU START THE ENGINE. IF NOT YOU WILL CAUSE DAMAGE TO THE DOG TEETH, AT ENGINE START.

CAUTION: DO NOT PUSH THE IDG DISCONNECT PUSHBUTTON SWITCH FOR MORE THAN 3 SECONDS. THERE MUST BE AT LEAST 60 SECONDS BETWEEN TWO OPERATIONS OF THE SWITCH. THIS IS TO PREVENT DAMAGE TO THE DISCONNECT SOLENOID WHICH WILL BECOME TOO HOT.

Subtask 24-21-00-710-050-A ** ON A/C NOT FOR ALL

A. Operational Test of the IDG Disconnect and Reconnect Function

NOTE: This test is for the system 1. For the other system(s), use the indications between the parentheses.

ACTION	RESULT
1.On the ELEC control panel 35VU: Lift the guard and push the IDG1(2) pushbutton switch.
2.On the IDG 1(2): Slowly pull out the disconnect reset ring to the full limit of travel. Monitor the hand force that is necessary: this force must not be too high. The disconnect mechanism must move freely without hard points. Let the disconnect reset ring go slowly back to the initial position.	On the related IDG: If you hear a click while you hold the disconnect reset ring, this shows that the disconnect function operates correctly.
CAUTION: MAKE SURE THAT THERE IS CORRECT RESET OF THE IDG DISCONNECT MECHANISM. IF THE RESET IS NOT CORRECT, YOU MUST REMOVE AND REPLACE THE IDG BEFORE THE NEXT FLIGHT. 3.On the IDG 1(2): Again, slowly pull out the disconnect reset ring to the full limit of travel.	On the related IDG: The force is much less than in step 2. There is no click.
4.On the panel 35VU: Lower the safety guard. NOTE: When you do the first engine start, make sure that the related engine electrical-generation system operates correctly.

Subtask 24-21-00-710-050-B ** ON A/C NOT FOR ALL

A. Operational Test of the IDG Disconnect and Reconnect (Reset) Function - Engine Static

IDG - Reset Ring ** ON A/C NOT FOR ALL

NOTE: This test is for the system 1. For the other system(s), use the indications between the parentheses.

ACTION	RESULT
1.On the ELEC control panel 35VU: Lift the guard and push the IDG1(2) pushbutton switch.
2.On the IDG 1(2): Remove the screw (3) and desengage the loop clamp (2). Slowly pull out the disconnect reset ring (1) to the full limit of travel. Monitor the hand force that is necessary: this force must not be too high. The disconnect mechanism must move freely without hard points. Let the disconnect reset ring (1) go slowly back to the initial position.	On the IDG 1(2): If you feel a click while you hold the disconnect reset ring, this shows that the disconnect function operates correctly.
CAUTION: MAKE SURE THAT THERE IS CORRECT RESET OF THE IDG DISCONNECT MECHANISM. IF THE RESET IS NOT CORRECT, YOU MUST REMOVE AND REPLACE THE IDG BEFORE THE NEXT FLIGHT. 3.On the IDG 1(2): Again, slowly pull out the disconnect reset ring (1) to the full limit of travel. Let the disconnect reset ring (1) go slowly back to the initial position. Install the loop clamp (2) on the disconnect reset ring (1) and attach the loop clamp with the screw (3). TORQUE the screw to between 22 and 20 lbf.in (0.25 and 0.23 m.daN ) .	On the IDG 1(2): The force is much less than in step 2. There is no click.
4.On the panel 35VU: Lower the safety guard. NOTE: When you do the first engine start, make sure that the related engine electrical-generation system operates correctly.

5. Close-up
Subtask 24-21-00-410-050-A ** ON A/C NOT FOR ALL

A. Close the right fan cowl door (Ref. AMM TASK 71-13-00-410-040):
(1) FOR [1000EM1] (ENGINE-1)
438AR
(2) FOR [1000EM2] (ENGINE-2)
448AR

Subtask 24-21-00-865-052-A ** ON A/C NOT FOR ALL

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
122VU	ELEC/GCU/2	2XU2	T27
122VU	ELEC/GCU/1	2XU1	T26

Subtask 24-21-00-862-050-A ** ON A/C NOT FOR ALL

C. Put the aircraft back to its initial configuration.
(1) Do the EIS stop procedure
(Ref. AMM TASK 31-60-00-860-002).
(2) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).

[Rev.10 from 2021] 2026.04.01 08:26:23 UTC