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 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 31-10-00-700-001 Test Program after Removal/Installation of a VU panel AMM 71-00-00-710-003 Engine Automatic Start AMM 73-21-10-000-002 Removal of the Hydromechanical Unit (HMU) AMM 73-21-10-400-002 Installation of the Hydromechanical Unit (HMU) ASM 76-12/01
R AWM 76-12-01
 3. Fault Confirmation
__________________
 A. Test
 (1) Not applicable, the fault is evident.
 4. Fault Isolation
_______________
 A. Table of the circuit breakers used in this procedure:
 -------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU ENGINE/2/HP FUEL SOV 1KC2 A02
 B. If the fault symptom is identified by the CFDS message MASTER LEVER, HMU:
 NOTE : The fault is generated if there is a demand / position disagree on
____ the HMU HP fuel shut-off valve. While the A/C is electrically powered and the engine master lever is set to OFF.
 - disconnect the connector 4000KC-A from the HMU and make sure that, when the ENG/MASTER control switch on the 115VU is in the OFF position, there is 28VDC at pin AA/1 of the connector 4000KC-A (Ref. ASM 76-12/01) and (Ref. AWM 76-12-01).
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 (1) If there is 28VDC:

 - replace the HMU (Ref. AMM TASK 73-21-10-000-002) and (Ref. AMM TASK 73-21-10-400-002).
 (2) If there is no 28VDC:
 - remove the panel 115VU.

 - do a check of the aircraft wiring between the connector 4000KC-A and the ENG/MASTER control switch (2KC) pin AA/1 to pin 1G.

 - do a check of the aircraft wiring between the ENG/MASTER control switch (2KC) pin 3G and the circuit breaker (1KC2) (Ref. ASM 76-12/01).

 (a) If the wiring is not correct:

 - repair the above defective wirings.

 (b) If the wiring is correct:

 - replace the CTL SW-ENG/MASTER 2 (2KC) on the panel 115VU. (Ref. R AWM 76-12-01)
 - install the panel 115VU and do a test program after removal/installation of a VU panel. (Ref. AMM TASK 31-10-00-700-001)
 C. Test
 (1) Start the engine 2 by the engine automatic start procedure (Ref. AMM TASK 71-00-00-710-003).

 (2) Make sure that there is no ECAM and CFDS fault message shown.

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 TASK 76-12-00-810-816
 Failure of the Control of the Fuel Shut-off Valve on Engine 1
 1. Possible Causes
_______________
 - aircraft wiring

 - RELAY-ENG/MASTER 1 (11QG)

 - ACTUATOR-LP FUEL VALVE, ENG 1 (9QG)

 - VALVE-LP FUEL, ENG 1 (12QM)

 - CTL SW-ENG/MASTER 1 (3KC)

 - ECU (4000KS)

 2. Job Set-up Information
______________________
 A. Referenced Information
 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 28-24-00-710-002 Operational Test of the ENG 1(2) LP Fuel Valve 12QM
 (13QM) R AMM 28-24-41-000-001 Removal of the LP Fuel Valve 12QM(13QM) R AMM 28-24-41-400-001 Installation of the LP Fuel Valve 12QM(13QM)
 AMM 28-24-51-000-001 Removal of the LP Fuel Valve Actuator AMM 28-24-51-400-001 Installation of the LP Fuel Valve Actuator AMM 71-00-00-710-003 Engine Automatic Start AMM 73-21-60-000-001 Removal of the Electronic Control Unit (ECU)(4000KS) AMM 73-21-60-400-001 Installation of the Electronic Control Unit
 (ECU)(4000KS)
 ASM 28-24/01
 ASM 76-12/01

 3. Fault Confirmation
__________________
 A. Test
 (1) Not applicable, the fault is evident.
 4. Fault Isolation
_______________
 A. Table of the circuit breakers used in this procedure:
 -------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU FUEL/LP VALVE/MOT1/ENG1 1QG A08 121VU FUEL/LP VALVE/MOT2/ENG1 3QG M25
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