Operational Test of the Pneumatic Starter Valve and FMU with the CFDS [IAE]

TASK 80-13-51-710-040-B
Operational Test of the Pneumatic Starter Valve and FMU with the CFDS

ZONE: 400

1. Reason for the Job
Self explanatory
2. Job Set-up Information
A. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
400	POWER PLANT, NACELLES AND PYLONS

B. 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 31-32-00-860-012-A	Procedure to Get Access to the SYSTEM REPORT/TEST/ENG Page
TASK 31-60-00-860-001-A	EIS Start Procedure
TASK 31-60-00-860-002-A	EIS Stop Procedure
Starter Valve / FMU Test Indications
FMU Interchangeability Table

3. Job Set-up
Subtask 80-13-51-861-054-A ** ON A/C NOT FOR ALL

A. Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).

Subtask 80-13-51-865-054-A ** ON A/C NOT FOR ALL

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
FOR FIN: 1000EM1 (ENGINE1)
49VU	ENGINE/1/FADEC A/AND EIU 1	2KS1	A04
49VU	ENGINE/1/HP FUEL SOV	1KC1	A01
121VU	ENGINE/ENG1/FADEC B/AND EIU 1	4KS1	R41
FOR FIN: 1000EM2 (ENGINE2)
49VU	ENGINE/2/FADEC A/AND EIU 2	2KS2	A05
49VU	ENGINE/2/HP FUEL SOV	1KC2	A02
121VU	ENGINE/ENG2/FADEC B	4KS2	Q40

Subtask 80-13-51-860-058-A ** ON A/C NOT FOR ALL

C. Aircraft configuration
(1) On the maintenance panel 50VU:
(a) Release the FADEC GND PWR 1(2) pushbutton switch:

On the pushbutton switch, the ON legend comes on.

(2) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only)
(Ref. AMM TASK 31-60-00-860-001).
(3) Supply the aircraft pneumatic system from a HP ground power unit or the APU. On the lower ECAM display unit, make sure that the available air pressure is between 30 psi (2.07 bar) and 40 psi (2.75 bar).
(4) On the center pedestal, on the ENG panel 115VU:

WARNING: PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR:

THE FLIGHT CONTROLS
THE FLIGHT CONTROL SURFACES
THE LANDING GEAR AND THE RELATED DOORS
COMPONENTS THAT MOVE.

MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS AND/OR CAN CAUSE DAMAGE TO THE EQUIPMENT.

CAUTION: MAKE SURE THAT THE ENG/MASTER 1(2) CONTROL SWITCH (ON THE PANEL 115VU) IS SET TO OFF BEFORE YOU START THE FUEL PUMPS.

(a) Make sure that the ENG/MASTER 1(2) control switch is set to OFF.

CAUTION: DO NOT RUN THE ENGINE IF THE FUEL INLET PRESSURE IS NOT POSITIVE (THE FUEL IS NECESSARY TO LUBRICATE THE ENGINE FUEL PUMP AND THE FMU AND THUS PREVENT DAMAGE).

(5) Start the aircraft fuel pumps

ACTION	RESULT
1.On the HYD/FUEL panel 40VU:
Push all the FUEL/PUMPS pushbutton switches.	The OFF legends of these pushbutton switches go off.
2.On the overhead circuit breaker panel 49VU:
Open the circuit breaker 1KC1(2) to open the LP valve.	After a not many seconds: On the upper ECAM display unit: * the ENG 1(2) LP valve OPEN message comes into view * the single chime sounds * the MASTER CAUT light comes on.

(6) On the Air cond panel 30VU, make sure that:

the PACK 1 and the PACK 2 pushbutton switches are in the off position (the OFF legends are on).

4. Procedure
Subtask 80-13-51-710-055-A ** ON A/C NOT FOR ALL

A. Do this test:
(1) On the left or right MCDU get the SYSTEM REPORT/TEST ENG page (Ref. AMM TASK 31-32-00-860-012).
(2) Push the line key adjacent to the NEXT PAGE indication.
(3) Do this test:

ACTION	RESULT
1.On the MCDU, push the line key adjacent to the ENG 1(2) indication.	The ENG 1(2) menu comes into view.
2.Push the line key adjacent to the FADEC 1A(2A) indication.	The FADEC 1A(2A) menu comes into view.
3.Push the line key adjacent to the SYSTEM TEST indication.	The FADEC SYSTEM TEST menu comes into view.
4.Push the line key adjacent to the STARTER VALVE TEST indication.	The STARTER VALVE TEST menu comes into view. Starter Valve / FMU Test Indications ** ON A/C NOT FOR ALL
5.Push the line key adjacent to the ENABLE TEST CAUTION indication.	CAUTION/TURN ON STARTER indication comes into view. Starter Valve / FMU Test Indications ** ON A/C NOT FOR ALL
6.Push the line key adjacent to the CAUTION/TURN ON STARTER indication.	TURN OFF STARTER and TEST IN PROGRESS indications come into view. After not many seconds, STARTER ON/NO FAULT indication replaces TEST IN PROGRESS indication. Starter Valve / FMU Test Indications ** ON A/C NOT FOR ALL Monitor oil pressure during the test. Do not continue to motor the engine if you do not see positive oil pressure.
7.Push the line key adjacent to the TURN OFF STARTER indication.	TEST IN PROGRESS indication comes into view . After not many seconds ENABLE TEST CAUTION and RETURN NO FAULT (or RETURN FAULT DETECTED) indications come into view. Starter Valve / FMU Test Indications ON A/C NOT FOR ALL If the CHECK FMU PART NUMBER or FAULT DETECTED indication comes into view, make sure that the FMU P/N is applicable to your aircraft. To do this, refer to the FMU Interchangeability Table. FMU Interchangeability Table ON A/C NOT FOR ALL NOTE: If the message CHECK FMU PART NUMBER is systematically displayed, check for it's P/N. However, this message should not be considered as a detected fault as the EEC does not have the capability to readout the FMU P/N.
8.Push the line key adjacent to the RETURN indication.	The SYSTEM TEST menu comes into view. Starter Valve / FMU Test Indications ** ON A/C NOT FOR ALL NOTE: If you must do again the test on the same or alternate channel, you must: -go back to the ENG SYSTEM REPORT/TEST menu and -wait 30 seconds before you try again the test. NOTE: If failures are found during the test, you must use the GROUND SCANNING function, read the fault message on the screen and do the related troubleshooting.
9.On the MCDU, push the line select key adjacent to the RETURN indication until the CFDS menu page comes into view.	The CFDS menu comes into view.
10.Push the MCDU MENU key.	The MCDU menu comes into view.

5. Close-up
Subtask 80-13-51-860-059-A ** ON A/C NOT FOR ALL

A. Put the aircraft back to its initial configuration.
(1) On the HYD/FUEL panel 40VU:
(a) Release all the FUEL/PUMPS pushbutton switches.
(b) The OFF legend of these pushbutton switches comes on.
(2) On the maintenance panel 50VU:
(a) Push the FADEC GND PWR 1(2) pushbutton switch.
(b) On the pushbutton switch, the ON legend goes off.
(3) Stop the pneumatic supply to the aircraft:

disconnect the HP ground power unit or stop the APU.

(4) Do the EIS stop procedure
(Ref. AMM TASK 31-60-00-860-002).

Subtask 80-13-51-865-055-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
49VU	ENGINE/2/HP FUEL SOV	1KC2	A02
49VU	ENGINE/1/HP FUEL SOV	1KC1	A01

Subtask 80-13-51-862-054-A ** ON A/C NOT FOR ALL

C. De-energize the aircraft electrical circuits. (Ref. AMM TASK 24-41-00-862-002)

[Rev.10 from 2021] 2026.04.01 03:44:56 UTC