Loss of the GEN 2 (Failure of the Electrical Wiring between the GLC 2 and GCU 2)

TASK 24-20-00-810-812-A
Loss of the GEN 2 (Failure of the Electrical Wiring between the GLC 2 and GCU 2)

1. Possible Causes

wiring
EGIU-2 [22XU2]
GCU-2 [1XU2]

2. Job Set-up Information
A. Referenced Information

REFERENCE	DESIGNATION
ASM 242202
AMM 24-22-33-000-001	Removal of the EGIU-1(2)
AMM 24-22-33-400-002	Installation of the EGIU-1(2)
AMM 24-22-34-000-001	Removal of the GCU-1(2)
AMM 24-22-34-400-001	Installation of the GCU-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 71-00-00-710-028	Engine Shutdown
AMM 71-00-00-710-043	Normal Engine Automatic Start Procedure

3. Fault Confirmation
Subtask 24-20-00-700-059-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 24-20-00-810-059-A ** ON A/C NOT FOR ALL

A. If the fault symptom is identified by the CFDS message CHECK GLC 2 GCU 2 PIN B2D WIRING and the upper ECAM DU warning GEN 2 FAULT:

reset the circuit breaker on the front of the GCU 2.

(1) If the circuit breaker trips:

Do a check of the wiring for short to ground between:
. the GCU 2 pin B/2D and successively the GLC 2 pin B/3, GCU 2 pin A/5B, EGIU 2 pin A/12D and EGIU 2 pin A/12A
. the GCU 2 pin A/12C and the GLC 2 AUX RELAY pin X1
. the GCU 2 A/12D and the EGIU 2 pin A/13A ASM 242202.

(a) If the wiring is not correct:

repair it.

(b) If the wiring is correct:

do a check for short to ground of the internal wiring of the EGIU 2 between the pin A/12A and the pin A/13A.

1 If the wiring is shorted:

replace the EGIU-2 [22XU2] AMM 24-22-33-000-001 and AMM 24-22-33-400-002.

2 If the wiring is not shorted:

replace the GCU-2 [1XU2] AMM 24-22-34-000-001 and AMM 24-22-34-400-001.

Subtask 24-20-00-860-068-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 71-00-00-710-043.

Subtask 24-20-00-710-059-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 24-20-00-860-069-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 04:39:01 UTC