(c) If the fault continues:
- replace the VALVE-LP FUEL, ENG 2 (13QM) (Ref. AMM TASK 28-24-41-000-001) and (Ref. AMM TASK 28-24-41-400-001).
(d) If the fault continues:
- replace the CTL SW-ENG/MASTER 2 (2KC) on the panel 115VU.
(2) If the valve is open:
- replace the fuel pump and filter assembly (Ref. AMM TASK 73-11-10-000-003) and (Ref. AMM TASK 73-11-10-400-003).
(3) If the fault continues, replace the HMU (Ref. AMM TASK 73-21-10-000-002) and (Ref. AMM TASK 73-21-10-400-002).
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.
F 『 EEFF : ALL E ∞∞76-12-00∞∞∞∞∞∞∞∞∞∞Page 212
E E Feb 01/98 E E ECES
E
F 『
E C F M E
E E
E 56 E
E E
TASK 76-12-00-810-814
Failure of the Control of the Fuel Shut-off Valve on Engine 1
1. Possible Causes
_______________
- HMU
- aircraft wiring
- CTL SW-ENG/MASTER 1 (3KC)
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------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/1/HP FUEL SOV 1KC1 A01
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).
F 『 EEFF : ALL E ∞∞76-12-00∞∞∞∞∞∞∞∞∞∞Page 213
E E Aug 01/05 E E ECES
E
F 『
E C F M E
E E
E 56 E
E E
(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 (3KC) pin AA/1 to pin 1G.
- do a check of the aircraft wiring between the ENG/MASTER control switch (3KC) pin 3G and the circuit breaker (1KC1) (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 1 (3KC) 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 1 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.
F 『 EEFF : ALL E ∞∞76-12-00∞∞∞∞∞∞∞∞∞∞Page 214
E E Aug 01/05 E E ECES
E
F 『
E C F M E
E E
E 56 E
E E
TASK 76-12-00-810-815
Failure of the Control of the Fuel Shut-off Valve on Engine 2
1. Possible Causes
_______________
- HMU
- aircraft wiring
- CTL SW-ENG/MASTER 2 (2KC)
2. Job Set-up Information
______________________
A. Referenced Information
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：A320 Trouble Shooting Manual 排故手册 发动机控制(23)
