DOC AIRBUS | TSM A320FTroubleshoot the Engine after an Auto Acceleration event
TASK 71-00-00-810-852-A
Troubleshoot the Engine after an Auto Acceleration event
1. Possible Causes
2. Job Set-up Information
A. Referenced Information
3. Fault Confirmation
Subtask 71-00-00-710-109-A ** ON A/C NOT FOR ALL
Subtask 71-00-00-860-064-A ** ON A/C NOT FOR ALL
[Rev.8 from Aug 2018]
2026.04.04 04:35:04 UTC
Troubleshoot the Engine after an Auto Acceleration event
1. Possible Causes
2. Job Set-up Information
A. Referenced Information
| REFERENCE | DESIGNATION |
|---|---|
| TSM TASK 73-11-00-810-845-A | Fuel Flow not at Shutoff During Start - Failure on Both Channels |
| TSM TASK 75-31-00-810-812-A | LPC SVA Position Error - Track Check Channel A |
| TSM TASK 75-31-00-810-813-A | HPC SVA Master/Slave Actuator Position Error - Track Check Channel A |
| TSM TASK 75-31-00-810-821-A | LPC SVA Position Error - Track Check Channel B |
| TSM TASK 75-31-00-810-822-A | HPC SVA Master/Slave Actuator Position Error - Track Check Channel B |
| TSM TASK 75-32-00-810-833-A | LPC (2.5) Bleed Valve Actuator Mechanically Stuck Closed - Track Check |
| TSM TASK 76-11-00-810-824-A | Autothrust Instinctive Disconnect Hardwired Discrete Signal Failure Channel A |
| TSM TASK 76-11-00-810-825-A | TRA Signal Failure Channel A |
| TSM TASK 76-11-00-810-826-A | TRA Signal Failure Channel B |
| TSM TASK 76-11-00-810-827-A | Autothrust Instinctive Disconnect Hardwired Discrete Signal Failure Channel B |
| TSM TASK 76-11-00-810-829-A | Autothrust Engage Hardwired Discrete Signal Failure Channel A |
| TSM TASK 76-11-00-810-830-A | Autothrust Engage Hardwired Discrete Signal Failure Channel B |
| AMM 22-96-00-710-001 | Operational Test of the AFS |
| AMM 36-11-00-740-802 | BITE Test of the Engine Bleed Air System (EBAS) (System Test) |
| 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 73-21-00-710-806 | Test No.7 - EEC Operation Test (Self Test) |
| AMM 73-21-01-000-801 | Removal of the Electronic Engine Control (EEC) |
| AMM 73-21-01-400-801 | Installation of the Electronic Engine Control (EEC) |
| AMM 77-11-23-000-801 | Remove the N2 Speed Transducer |
Subtask 71-00-00-710-109-A ** ON A/C NOT FOR ALL
A. Investigate The Engine After an Auto Acceleration event
(1) Use this troubleshooting procedure to investigate the engine after an increase in engine parameters (N1, N2, EGT, and fuel flow) without thrust lever movement.
(2) Using the Multipurpose Control and Display Unit (MCDU) test the FADEC system for any recorded faults AMM 73-21-00-710-806.
(3) 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) Use this troubleshooting procedure to investigate the engine after an increase in engine parameters (N1, N2, EGT, and fuel flow) without thrust lever movement.
(2) Using the Multipurpose Control and Display Unit (MCDU) test the FADEC system for any recorded faults AMM 73-21-00-710-806.
(3) 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 71-00-00-810-117-A ** ON A/C NOT FOR ALL A. Do the steps that follow:
(1) If the maintenance messages related to the Throttle Resolver Angle (TRA) signal failure on channel A appear with the ECAM warning for engine one Throttle Lever Angle (TLA) fault and/or engine thrust lever fault and engine thrust and reserver, refer to TRA signal failure (Ref. TSM TASK 76-11-00-810-825).
(2) If the maintenance messages related to the TRA signal failure on channel B appear with the ECAM warning for engine one TLA fault and/or engine thrust lever fault and engine thrust and reserver, refer to TRA signal failure (Ref. TSM TASK 76-11-00-810-826).
(3) If the maintenance messages related to the Integrated Fuel Pump and Control (IFPC) mechanical failure on Fuel Metering Unit (FMU) appear with the ECAM warning for engine FADEC status maintenance and/or engine fuel control fault and engine fuel valve fault, refer to Integrated Fuel Pump and Control (IFPC) / mechanical failure - unable to control metering valve position (Ref. TSM TASK 73-11-00-810-845).
(4) If the maintenance message related to the FMV not closed on channel A appear with the ECAM warning for engine FADEC status or the ECAM warning for engine fuel valve fault, refer to fuel flow not at shutoff during start (Ref. TSM TASK 73-11-00-810-845).
(5) If the maintenance message related to the FMV not closed on channel B appear with the ECAM warning for engine FADEC status or the ECAM warning for engine fuel valve fault, refer to fuel flow not at shutoff during start (Ref. TSM TASK 73-11-00-810-845).
(6) If the maintenance message related to the autothrust engage harwired discrete signal failure on channel A appear with the ECAM warning for ATHR INOP, refer to autothrust engage - discrete failure (Ref. TSM TASK 76-11-00-810-829).
(7) If the maintenance message related to the autothrust engage harwired discrete signal failure on channel B appear with the ECAM warning for ATHR INOP, refer to autothrust engage - discrete failure (Ref. TSM TASK 76-11-00-810-830).
(8) If the maintenance message related to the autothrust instinctive disconnected hardwired discrete signal failure on channel A appear with the ECAM warning for engine FADEC status maintenance, refer to autothrust instinctive disconnect hardwired discrete - signal failure (Ref. TSM TASK 76-11-00-810-824).
(9) If the maintenance message related to the autothrust instinctive disconnected hardwired discrete signal failure on channel B appear with the ECAM warning for engine FADEC status maintenance, refer to autothrust instinctive disconnect hardwired discrete - signal failure (Ref. TSM TASK 76-11-00-810-827).
(10) If the maintenance message related to the High Pressure Compressor (HPC) Stator Vane Actuator (SVA) primary failure on channel A appear with the ECAM warning for engine FADEC status maintenance or the ECAM warning for engine compressor vane thrust limited, refer to HPC SVA mechanical failure (Ref. TSM TASK 75-31-00-810-813).
(11) If the maintenance message related to the HPC SVA primary failure on channel B appear with the ECAM warning for engine FADEC status maintenance or the ECAM warning for engine compressor vane thrust limited, refer to HPC SVA mechanical failure (Ref. TSM TASK 75-31-00-810-822).
(12) If the maintenance message related to the Low Pressure Compressor (LPC) SVA mechanicaly failure on channel A appear with the ECAM warning for engine FADEC status maintenance or the ECAM warning for engine compressor vane thrust limited, refer to LPC SVA mechanical failure (Ref. TSM TASK 75-31-00-810-812).
(13) If the maintenance message related to the LPC SVA mechanicaly failure on channel B appear with the ECAM warning for engine FADEC status maintenance or the ECAM warning for engine compressor vane thrust limited, refer to LPC SVA mechanical failure (Ref. TSM TASK 75-31-00-810-821).
(14) If the maintenance message related to the LPC (2.5) bleed valve mechanicaly stuck closed appear with the ECAM warning for engine compressor vane, refer to LPC 2.5 Bleed Mechanical Failure (Ref. TSM TASK 75-32-00-810-833).
(15) If there are no EEC monitored faults recorded, check the aircraft Automatic Flight System (AFS) for any recorded faults AMM 22-96-00-710-001.
(16) If you do not find any problems, check the Bleed Monitoring Computer (BMC) for any recorded faults AMM 36-11-00-740-802.
(17) If you do not find any problems or this problem continues:
(a) Replace TRANSDUCER-N2 [4065KS] AMM 77-11-23-000-801 and AMM 77-11-23-000-801.
(b) Do the test given in Para. 3.
(18) If the problem continues:
(a) Replace INTEGRATED FUEL PUMP AND CONTROL [4360KS] AMM 73-11-01-000-801 and AMM 73-11-01-400-801.
(b) Do the test given in Para. 3.
(19) If the problem continues:
(a) Replace
(b) Do the test given in Para. 3.
5. Close-up(1) If the maintenance messages related to the Throttle Resolver Angle (TRA) signal failure on channel A appear with the ECAM warning for engine one Throttle Lever Angle (TLA) fault and/or engine thrust lever fault and engine thrust and reserver, refer to TRA signal failure (Ref. TSM TASK 76-11-00-810-825).
(2) If the maintenance messages related to the TRA signal failure on channel B appear with the ECAM warning for engine one TLA fault and/or engine thrust lever fault and engine thrust and reserver, refer to TRA signal failure (Ref. TSM TASK 76-11-00-810-826).
(3) If the maintenance messages related to the Integrated Fuel Pump and Control (IFPC) mechanical failure on Fuel Metering Unit (FMU) appear with the ECAM warning for engine FADEC status maintenance and/or engine fuel control fault and engine fuel valve fault, refer to Integrated Fuel Pump and Control (IFPC) / mechanical failure - unable to control metering valve position (Ref. TSM TASK 73-11-00-810-845).
(4) If the maintenance message related to the FMV not closed on channel A appear with the ECAM warning for engine FADEC status or the ECAM warning for engine fuel valve fault, refer to fuel flow not at shutoff during start (Ref. TSM TASK 73-11-00-810-845).
(5) If the maintenance message related to the FMV not closed on channel B appear with the ECAM warning for engine FADEC status or the ECAM warning for engine fuel valve fault, refer to fuel flow not at shutoff during start (Ref. TSM TASK 73-11-00-810-845).
(6) If the maintenance message related to the autothrust engage harwired discrete signal failure on channel A appear with the ECAM warning for ATHR INOP, refer to autothrust engage - discrete failure (Ref. TSM TASK 76-11-00-810-829).
(7) If the maintenance message related to the autothrust engage harwired discrete signal failure on channel B appear with the ECAM warning for ATHR INOP, refer to autothrust engage - discrete failure (Ref. TSM TASK 76-11-00-810-830).
(8) If the maintenance message related to the autothrust instinctive disconnected hardwired discrete signal failure on channel A appear with the ECAM warning for engine FADEC status maintenance, refer to autothrust instinctive disconnect hardwired discrete - signal failure (Ref. TSM TASK 76-11-00-810-824).
(9) If the maintenance message related to the autothrust instinctive disconnected hardwired discrete signal failure on channel B appear with the ECAM warning for engine FADEC status maintenance, refer to autothrust instinctive disconnect hardwired discrete - signal failure (Ref. TSM TASK 76-11-00-810-827).
(10) If the maintenance message related to the High Pressure Compressor (HPC) Stator Vane Actuator (SVA) primary failure on channel A appear with the ECAM warning for engine FADEC status maintenance or the ECAM warning for engine compressor vane thrust limited, refer to HPC SVA mechanical failure (Ref. TSM TASK 75-31-00-810-813).
(11) If the maintenance message related to the HPC SVA primary failure on channel B appear with the ECAM warning for engine FADEC status maintenance or the ECAM warning for engine compressor vane thrust limited, refer to HPC SVA mechanical failure (Ref. TSM TASK 75-31-00-810-822).
(12) If the maintenance message related to the Low Pressure Compressor (LPC) SVA mechanicaly failure on channel A appear with the ECAM warning for engine FADEC status maintenance or the ECAM warning for engine compressor vane thrust limited, refer to LPC SVA mechanical failure (Ref. TSM TASK 75-31-00-810-812).
(13) If the maintenance message related to the LPC SVA mechanicaly failure on channel B appear with the ECAM warning for engine FADEC status maintenance or the ECAM warning for engine compressor vane thrust limited, refer to LPC SVA mechanical failure (Ref. TSM TASK 75-31-00-810-821).
(14) If the maintenance message related to the LPC (2.5) bleed valve mechanicaly stuck closed appear with the ECAM warning for engine compressor vane, refer to LPC 2.5 Bleed Mechanical Failure (Ref. TSM TASK 75-32-00-810-833).
(15) If there are no EEC monitored faults recorded, check the aircraft Automatic Flight System (AFS) for any recorded faults AMM 22-96-00-710-001.
(16) If you do not find any problems, check the Bleed Monitoring Computer (BMC) for any recorded faults AMM 36-11-00-740-802.
(17) If you do not find any problems or this problem continues:
(a) Replace TRANSDUCER-N2 [4065KS] AMM 77-11-23-000-801 and AMM 77-11-23-000-801.
(b) Do the test given in Para. 3.
(18) If the problem continues:
(a) Replace INTEGRATED FUEL PUMP AND CONTROL [4360KS] AMM 73-11-01-000-801 and AMM 73-11-01-400-801.
(b) Do the test given in Para. 3.
(19) If the problem continues:
(a) Replace
(b) Do the test given in Para. 3.
Subtask 71-00-00-860-064-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.