Failure of the ENG2 FIRE Pushbutton Switch or its Wiring to the GCU2

TASK 24-20-00-810-827-A
Failure of the ENG2 FIRE Pushbutton Switch or its Wiring to the GCU2

1. Possible Causes

wiring

2. Job Set-up Information
A. Referenced Information

REFERENCE	DESIGNATION
ASM 242203
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 24-20-00-700-107-A ** ON A/C NOT FOR ALL

A. Test
Not applicable.

NOTE: As the GEN2 was set to OFF because of a true failure, the test configuration is not necessary.

4. Fault Isolation
Subtask 24-20-00-810-096-A ** ON A/C NOT FOR ALL

A. If the fault symptom is identified by the CFDS message CHECK FIRE HANDLE 2 RESET GEN2 and the upper ECAM DU warning GEN2 FAULT:

do a check of the status of the ENG2 FIRE pushbutton switch on the FIRE panel (1WD).

(1) If the pushbutton switch has not been pushed:

do a check for intermittent +28VDC and repair the wiring between respectively:
. the pin A/3A of the GCU2 and the pin C/V of the ENG/APU FIRE PNL (1WD)
. the pin A/3A of the GCU2 and the pin A/B3 of the SENSOR-TDC AC2 ASM 242203.

(2) If the pushbutton switch has been pushed:

do the necessary maintenance procedure and then reset the generator 2.

Subtask 24-20-00-710-083-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 panel 35VU:

push, release and push again the GEN2 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.
(5) 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 GEN2 are shown and AC2 busbar is supplied by GEN2.

5. Close-up
Subtask 24-20-00-860-111-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 04:26:12 UTC