DOC AIRBUS | TSM A320FTroubleshoot the Engine after a Hung Start event
TASK 71-00-00-810-885-A
Troubleshoot the Engine after a Hung Start event
1. Possible Causes
A. Referenced Information
3. Fault Confirmation
Subtask 71-00-00-710-145-A ** ON A/C NOT FOR ALL
Subtask 71-00-00-860-099-A ** ON A/C NOT FOR ALL
[Rev.8 from Aug 2018]
2026.04.04 04:40:54 UTC
Troubleshoot the Engine after a Hung Start event
1. Possible Causes
- INTEGRATED FUEL PUMP AND CONTROL [4360KS]
A. Referenced Information
| REFERENCE | DESIGNATION |
|---|---|
| TSM TASK 71-00-00-810-854-A | Troubleshoot the Engine after a Surge - Forward Thrust event |
| TSM TASK 73-11-00-810-808-A | Integrated Fuel Pump and Control/FMV-Track Check Channel A |
| TSM TASK 73-11-00-810-813-A | Integrated Fuel Pump and Control/FMV-Track Check Channel B |
| TSM TASK 73-21-00-810-873-A | T2 Engine Sensor Signal Disagreement |
| AMM 36-11-00-710-802 | Operational Test of the Bleed Air System |
| AMM 72-00-00-210-812 | General visual Inspection (GVI) of the Engine Exhaust Area |
| AMM 72-00-00-210-813 | General Visual Inspection (GVI) of the Engine Inlet Area |
| AMM 72-35-00-290-801 | Borescope Inspection of the High Pressure Compressor (HPC) Assembly |
| AMM 73-11-01-000-801 | Removal of the Integrated Fuel Pump and Control (IFPC) |
| AMM 73-11-01-400-801 | Installation of the Integrated Fuel Pump and Control (IFPC) |
| AMM 73-21-00-200-806 | Electronic Engine Control (EEC) Sensing System Check |
| AMM 73-21-00-710-806 | Test No.7 - EEC Operation Test (Self Test) |
| AMM 73-21-00-710-807 | Test No.6 - EEC Operation Test (Idle Test) |
| AMM 80-11-00-210-801 | General Visual Inspection (GVI) of the Engine Starting System |
Subtask 71-00-00-710-145-A ** ON A/C NOT FOR ALL
A. Investigate the Engine after a Hung Start event
(1) Using the Multipurpose Control and Display Unit (MCDU) test the FADEC system for any recorded faults AMM 73-21-00-710-806.
(2) Any EEC monitored faults are transmitted to the aircraft Centralized Fault Display Interface Unit (CFDIU). The MCDU allows interactive dialog with the EEC. Use the MCDU to review the previous flight leg fault information, scheduled maintenance fault information and ground fault information. If there are any faults reported troubleshoot them first.
4. Fault Isolation(1) Using the Multipurpose Control and Display Unit (MCDU) test the FADEC system for any recorded faults AMM 73-21-00-710-806.
(2) Any EEC monitored faults are transmitted to the aircraft Centralized Fault Display Interface Unit (CFDIU). The MCDU allows interactive dialog with the EEC. Use the MCDU to review the previous flight leg fault information, scheduled maintenance fault information and ground fault information. If there are any faults reported troubleshoot them first.
WARNING:
BE CAREFUL WHEN YOU DO WORK ON THE ENGINE AFTER SHUTDOWN. THE ENGINE CAN STAY HOT FOR A LONG TIME. IF YOU DO NOT OBEY THIS WARNING, INJURY CAN OCCUR.
Subtask 71-00-00-810-152-A ** ON A/C NOT FOR ALL A. Do the steps that follow:
(1) If the crew alert warning messages related to the engine stall appear, refer to troubleshoot the engine after a surge-forward thrust event (Ref. TSM TASK 71-00-00-810-854).
(2) If the maintenance messages related to the Fuel Metering Valve (FMV) track check on channel A appear with the ECAM warning for engine FADEC status maintenancee and/or the ECAM warning for engine fuel control fault and engine fuel valve fault, refer to integrated fuel pump and control/FMV-track check channel A (Ref. TSM TASK 73-11-00-810-808).
(3) If the maintenance messages related to the FMV track check on channel B appear with the ECAM warning for engine FADEC status maintenancee and/or the ECAM warning for engine fuel control fault and engine fuel valve fault, refer to integrated fuel pump and control/FMV-track check channel B (Ref. TSM TASK 73-11-00-810-813).
(4) If the maintenance messages related to the High Pressure Compressor (HPC) Stator Vane Actuator (SVA) primary failure appear with the ECAM warning for engine compressor vane thrust limited, refer to HPC SVA master actuator / mechanical failure resulting in inability to position actuator (Ref. TSM TASK 75-31-00-810-819).
(5) If the maintenance messages related to the T2 engine sensor disagree appear with the ECAM warning for engine FADEC status maintenance, refer to T2 engine sensor signal disagreement (Ref. TSM TASK 73-21-00-810-873).
(6) If there are no EEC monitored faults or messages recorded, check the burner pressure and PS14 sensing lines AMM 73-21-00-200-806.
(7) If no problems are found, inspect the starter air supply ducts AMM 80-11-00-210-801.
(8) If you do not find any problems, visually inspect the engine inlet area AMM 72-00-00-210-813.
(9) If you find evidence of foreign object damage (FOD), borescope inspect the HPC AMM 72-35-00-290-801.
(10) If you do not find any problems, visually inspect the engine exhaust area AMM 72-00-00-210-812.
(11) If there are no fault messages associated with this problem, make sure that the aircraft pneumatic system is operating properly AMM 36-11-00-710-802.
(12) If you do not find any problems:
(a) Replace INTEGRATED FUEL PUMP AND CONTROL [4360KS] AMM 73-11-01-000-801 and AMM 73-11-01-400-801.
(13) To confirm the repair of this fault, do a FADEC system idle test AMM 73-21-00-710-807.
5. Close-up(1) If the crew alert warning messages related to the engine stall appear, refer to troubleshoot the engine after a surge-forward thrust event (Ref. TSM TASK 71-00-00-810-854).
(2) If the maintenance messages related to the Fuel Metering Valve (FMV) track check on channel A appear with the ECAM warning for engine FADEC status maintenancee and/or the ECAM warning for engine fuel control fault and engine fuel valve fault, refer to integrated fuel pump and control/FMV-track check channel A (Ref. TSM TASK 73-11-00-810-808).
(3) If the maintenance messages related to the FMV track check on channel B appear with the ECAM warning for engine FADEC status maintenancee and/or the ECAM warning for engine fuel control fault and engine fuel valve fault, refer to integrated fuel pump and control/FMV-track check channel B (Ref. TSM TASK 73-11-00-810-813).
(4) If the maintenance messages related to the High Pressure Compressor (HPC) Stator Vane Actuator (SVA) primary failure appear with the ECAM warning for engine compressor vane thrust limited, refer to HPC SVA master actuator / mechanical failure resulting in inability to position actuator (Ref. TSM TASK 75-31-00-810-819).
(5) If the maintenance messages related to the T2 engine sensor disagree appear with the ECAM warning for engine FADEC status maintenance, refer to T2 engine sensor signal disagreement (Ref. TSM TASK 73-21-00-810-873).
(6) If there are no EEC monitored faults or messages recorded, check the burner pressure and PS14 sensing lines AMM 73-21-00-200-806.
(7) If no problems are found, inspect the starter air supply ducts AMM 80-11-00-210-801.
(8) If you do not find any problems, visually inspect the engine inlet area AMM 72-00-00-210-813.
(9) If you find evidence of foreign object damage (FOD), borescope inspect the HPC AMM 72-35-00-290-801.
(10) If you do not find any problems, visually inspect the engine exhaust area AMM 72-00-00-210-812.
(11) If there are no fault messages associated with this problem, make sure that the aircraft pneumatic system is operating properly AMM 36-11-00-710-802.
(12) If you do not find any problems:
(a) Replace INTEGRATED FUEL PUMP AND CONTROL [4360KS] AMM 73-11-01-000-801 and AMM 73-11-01-400-801.
(13) To confirm the repair of this fault, do a FADEC system idle test AMM 73-21-00-710-807.
Subtask 71-00-00-860-099-A ** ON A/C NOT FOR ALL
A. Put the aircraft back to its initial configuration.
(1) Make sure that the work area is clean and clear of tools and other items.
(1) Make sure that the work area is clean and clear of tools and other items.