DOC AIRBUS | TSM A320FTroubleshoot the Engine after a Surge - Forward Thrust event
TASK 71-00-00-810-854-A
Troubleshoot the Engine after a Surge - Forward Thrust event
1. Possible Causes
2. Job Set-up Information
A. Referenced Information
3. Fault Confirmation
Subtask 71-00-00-710-111-A ** ON A/C NOT FOR ALL
Subtask 71-00-00-860-066-A ** ON A/C NOT FOR ALL
[Rev.8 from Aug 2018]
2026.04.04 04:35:04 UTC
Troubleshoot the Engine after a Surge - Forward Thrust event
1. Possible Causes
2. Job Set-up Information
A. Referenced Information
| REFERENCE | DESIGNATION |
|---|---|
| AMM 36-11-41-200-802 | Removal of Intermediate Pressure Bleed Check Valve for Detailed Inspection |
| AMM 71-00-00-710-805 | Test No. 4 - Power Acceleration/Deceleration Test |
| 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 72-31-00-290-802 | Borescope Inspection of the Low Pressure Compressor (LPC) Assembly |
| AMM 72-35-00-290-801 | Borescope Inspection of the High Pressure Compressor (HPC) Assembly |
| 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 75-31-00-200-802 | Mechanical Check of the High Pressure Compressor (HPC) Stator Vane Control System |
| AMM 75-31-00-200-803 | Mechanical Check of the Low Pressure Compressor (LPC) Stator Vane Control System |
| AMM 75-32-01-200-801 | Mechanical Check of the Low Pressure Compressor (LPC) (2.5) Bleed Air System |
Subtask 71-00-00-710-111-A ** ON A/C NOT FOR ALL
A. Investigate the Engine After a Surge - Forward Thrust event
(1) Look at the AIDS report to confirm the engine surge.
(2) Corrective action is not necessary if the only indication of the surge is that the stall detection flag was set and there were no reports from the flight crew or by ground observations.
(3) If as a result of a reported surge crew action was required to maintain satisfactory engine operational limits remove the engine from service.
(5) If the reported surge occurred at takeoff/initial climb power and the cause cannot be found and corrected, remove the engine from service.
(6) Use the Multipurpose Control and Display Unit (MCDU) and test the FADEC system for any recorded faults AMM 73-21-00-710-806.
4. Fault Isolation(1) Look at the AIDS report to confirm the engine surge.
(2) Corrective action is not necessary if the only indication of the surge is that the stall detection flag was set and there were no reports from the flight crew or by ground observations.
(3) If as a result of a reported surge crew action was required to maintain satisfactory engine operational limits remove the engine from service.
NOTE: If the surge resulted in the EEC Foreign Object Damage (FOD) logic being enabled it could result in the requiring the pilot to pull back on the throttle to keep the Exhaust Gas Temperature (EGT) from exceeding limits. Once the FOD logic has reset, the engine will return to normal operation. If it can be determined that the FOD logic was enabled continue troubleshooting the engine without removing the engine from service.
(4) If as a result of a reported surge the engine went below normal idle speed, remove the engine from service. (5) If the reported surge occurred at takeoff/initial climb power and the cause cannot be found and corrected, remove the engine from service.
(6) Use the Multipurpose Control and Display Unit (MCDU) and test the FADEC system for any recorded faults AMM 73-21-00-710-806.
NOTE: 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 exceedance report information, previous flight leg fault information, scheduled maintenance fault information, ground fault information and ground scanning report. 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 71-00-00-810-119-A ** ON A/C NOT FOR ALL A. Do the steps that follow:
(1) Visually inspect the engine inlet area. Refer to do a General Visual Inspection (GVI) of the engine inlet area AMM 72-00-00-210-813.
(2) If damage is found beyond acceptable limits remove the engine from service.
(3) If you do not find any problems:
(a) Visually inspect the engine exhaust area. Refer to do a General Visual Inspection (GVI) of the engine exhaust area AMM 72-00-00-210-812.
(4) If you do not find any problems and the engine gaspath is considered suspect:
(a) Inspect the High Pressure Compressor (HPC) AMM 72-35-00-290-801.
(5) If you do not find any problems:
(a) Inspect the Low Pressure Compressor (LPC) AMM 72-31-00-290-802.
(6) If you do not find any problems and the engine gaspath is considered acceptable:
(a) Do a check of the HPC stator vane hardware AMM 75-31-00-200-802.
(7) If you do not find any problems:
(a) Do a check of the LPC stator vane hardware AMM 75-31-00-200-803.
(8) If you do not find any problems:
(a) Do a check of the LPC bleed AMM 75-32-01-200-801.
(9) If you do not find any problems:
(a) Do a check of the burner pressure sense line AMM 73-21-00-200-806.
(10) If you do not find any problems, inspect the Intermediate Pressure Check Valve (IPCV) AMM 36-11-41-200-802.
(a) If a problem is found, remove and replace the IPCV AMM 36-11-41-200-802.
(11) If no problems are found and the engine gaspath and systems are considered acceptable, do a power acceleration/deceleration test AMM 71-00-00-710-805.
(a) If a surge is encountered remove the engine from service.
5. Close-up(1) Visually inspect the engine inlet area. Refer to do a General Visual Inspection (GVI) of the engine inlet area AMM 72-00-00-210-813.
(2) If damage is found beyond acceptable limits remove the engine from service.
(3) If you do not find any problems:
(a) Visually inspect the engine exhaust area. Refer to do a General Visual Inspection (GVI) of the engine exhaust area AMM 72-00-00-210-812.
(4) If you do not find any problems and the engine gaspath is considered suspect:
(a) Inspect the High Pressure Compressor (HPC) AMM 72-35-00-290-801.
(5) If you do not find any problems:
(a) Inspect the Low Pressure Compressor (LPC) AMM 72-31-00-290-802.
(6) If you do not find any problems and the engine gaspath is considered acceptable:
(a) Do a check of the HPC stator vane hardware AMM 75-31-00-200-802.
(7) If you do not find any problems:
(a) Do a check of the LPC stator vane hardware AMM 75-31-00-200-803.
(8) If you do not find any problems:
(a) Do a check of the LPC bleed AMM 75-32-01-200-801.
(9) If you do not find any problems:
(a) Do a check of the burner pressure sense line AMM 73-21-00-200-806.
(10) If you do not find any problems, inspect the Intermediate Pressure Check Valve (IPCV) AMM 36-11-41-200-802.
(a) If a problem is found, remove and replace the IPCV AMM 36-11-41-200-802.
(11) If no problems are found and the engine gaspath and systems are considered acceptable, do a power acceleration/deceleration test AMM 71-00-00-710-805.
(a) If a surge is encountered remove the engine from service.
Subtask 71-00-00-860-066-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.