DOC AIRBUS | TSM A320FTroubleshoot the Engine after a Hot Start/Impending Hot Start event
TASK 71-00-00-810-861-A
Troubleshoot the Engine after a Hot Start/Impending Hot Start event
1. Possible Causes
2. Job Set-up Information
A. Referenced Information
3. Fault Confirmation
Subtask 71-00-00-710-119-A ** ON A/C NOT FOR ALL
Subtask 71-00-00-860-074-A ** ON A/C NOT FOR ALL
[Rev.8 from Aug 2018]
2026.04.04 04:40:54 UTC
Troubleshoot the Engine after a Hot Start/Impending Hot Start event
1. Possible Causes
2. Job Set-up Information
A. Referenced Information
| REFERENCE | DESIGNATION |
|---|---|
| TSM TASK 71-00-00-810-869-A | Troubleshoot the Engine after an Engine Performance Decreased 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 73-21-00-810-871-A | T2 Engine Sensor Signal Failure Channel A |
| TSM TASK 73-21-00-810-872-A | T2 Engine Sensor Signal Failure Channel B |
| TSM TASK 75-32-00-810-832-A | LPC (2.5) Bleed Valve Actuator Mechanically Stuck Open - Track Check |
| TSM TASK 75-32-00-810-838-A | HPC Bleed Valve Failed Closed during Engine Starting |
| TSM TASK 75-32-00-810-841-A | HPC Bleed Valve Failed Open (not during starting) |
| TSM TASK 75-32-00-810-844-A | Active HPC Bleed Valve Failed Open (not during Start) |
| TSM TASK 75-32-00-810-845-A | Active HPC Bleed Valve Failed Closed (during Start) |
| TSM TASK 77-21-00-810-808-A | EGT Sensor Electrical Failure Channel A |
| TSM TASK 77-21-00-810-809-A | EGT Sensor Electrical Failure Channel B |
| AMM 36-11-00-710-802 | Operational Test of the Bleed Air System |
| AMM 71-00-00-910-804 | General Warnings and Cautions and Related Safety Data |
| AMM 72-00-00-210-809 | Visual Examination (after an Exhaust Gas Temperature (EGT) Overtemperature) |
| 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 73-21-00-710-807 | Test No.6 - EEC Operation Test (Idle 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 75-00-00-210-802 | Visual Examination of the Engine Air Systems |
Subtask 71-00-00-710-119-A ** ON A/C NOT FOR ALL
A. Investigate the Engine after a Hot Start/Impending Hot 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.
(3) Check to ensure that the ambient conditions such as tailwinds (10 Knots max.) or crosswinds (20 Knots max.) did not contribute to the hot start AMM 71-00-00-910-804.
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.
(3) Check to ensure that the ambient conditions such as tailwinds (10 Knots max.) or crosswinds (20 Knots max.) did not contribute to the hot start AMM 71-00-00-910-804.
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 71-00-00-810-127-A ** ON A/C NOT FOR ALL A. Do the steps that follow:
(1) If the maitenance messages related to the T3 sensor failure on channel A appear with the ECAM warning for engine minor fault and/or engine sensor fault and amber crosses on Exaust Gas Temperature (EGT) indication, refer to EGT sensor electrical failure (Ref. TSM TASK 77-21-00-810-808).
(2) If the maintenances messages related to the EGT sensor failure on channel B appear with the ECAM warning for engine minor fault and/or engine sensor fault and amber crosses on EGT indication, refer to EGT sensor electrical failure (Ref. TSM TASK 77-21-00-810-809).
(3) If you do not find any problems or if the messages related to the EGT sensor failure do not appear, the indicated EGT is assumed to be correct.
(a) Determine the maximum temperature and duration attained and perform the necessary maintenance.
(b) Refer to do an inspection of EGT overtemperature AMM 72-00-00-210-809.
(c) If the engine is determined to be serviceable, go to the Para. 4.A.(4).
(4) 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 maintenance 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).
(5) If the maintenance messages related to the FMV track check on channel B appear with the ECAM warning for engine FADEC status maintenance 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).
(6) If the maintenance messages related to the 2.5 bleed valve actuator failure appear with the ECAM warning for the engine compressor vane fuel comsumption increased thrust limited, refer to LPC (2.5) bleed valve actuator mechanically stuck open - track check (Ref. TSM TASK 75-32-00-810-832).
(7) If the maintenance messages related to the High Pressure Compressor (HPC) Stator Vane Actuator (SVA) primary failure appear with ECAM warning engine compresor 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).
(8) If the maintenance messages related to the T2 engine sensor signal failure on channel A appear with the ECAM warning for engine FADEC status maintenance and/or the ECAM warning for engine sensor fault, refer to T2 engine sensor signal failure channel A (Ref. TSM TASK 73-21-00-810-871).
(9) If the maintenance messages related to the T2 engine sensor signal failure on channel B appear with the ECAM warning for engine FADEC status maintenance and/or the ECAM warning for engine sensor fault, refer to T2 engine sensor signal failure channel B (Ref. TSM TASK 73-21-00-810-872).
(10) If the maintenance messages related to the HPC bleed valve fail closed appear with the ECAM warning for engine air system fault, refer to HPC bleed valve failed closed during engine starting (Ref. TSM TASK 75-32-00-810-838).
(11) If the maintenance messages related to the HPC bleed valve fail open appear with the ECAM warning for engine system fault, refer to HPC bleed valve failed open (not during starting) (Ref. TSM TASK 75-32-00-810-841).
(12) If the maintenance messages related to the active HPC bleed valve fail closed appear with the ECAM warning for engine air system fault, refer to active HPC bleed valve failed closed (during starting) (Ref. TSM TASK 75-32-00-810-845).
(13) If the maintenance messages related to the active HPC bleed valve fail open appear with the ECAM warning for engine system fault, refer to Active HPC bleed valve failed open (not during Starting) (Ref. TSM TASK 75-32-00-810-844).
(14) 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.
(15) If you do not find any problems, do a visual inspection of the engine air systems for indications of hot gas leakage. Look carefully at the Environmental Control System (ECS) ducts, the Anti-ice ducts and the Turbine Cooling Air (TCA) tubes AMM 75-00-00-210-802.
(16) If not previously accomplished, run the engine at idle AMM 73-21-00-710-807.
(17) 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.
(18) If there is another impending hot start with no associated maintenance messages the engine gaspath is suspect. Refer to troubleshoot the engine after an engine performance decreased event (Ref. TSM TASK 71-00-00-810-869).
(19) If the gaspath condition is acceptable:
(a) Replace
5. Close-up(1) If the maitenance messages related to the T3 sensor failure on channel A appear with the ECAM warning for engine minor fault and/or engine sensor fault and amber crosses on Exaust Gas Temperature (EGT) indication, refer to EGT sensor electrical failure (Ref. TSM TASK 77-21-00-810-808).
(2) If the maintenances messages related to the EGT sensor failure on channel B appear with the ECAM warning for engine minor fault and/or engine sensor fault and amber crosses on EGT indication, refer to EGT sensor electrical failure (Ref. TSM TASK 77-21-00-810-809).
(3) If you do not find any problems or if the messages related to the EGT sensor failure do not appear, the indicated EGT is assumed to be correct.
(a) Determine the maximum temperature and duration attained and perform the necessary maintenance.
(b) Refer to do an inspection of EGT overtemperature AMM 72-00-00-210-809.
(c) If the engine is determined to be serviceable, go to the Para. 4.A.(4).
(4) 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 maintenance 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).
(5) If the maintenance messages related to the FMV track check on channel B appear with the ECAM warning for engine FADEC status maintenance 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).
(6) If the maintenance messages related to the 2.5 bleed valve actuator failure appear with the ECAM warning for the engine compressor vane fuel comsumption increased thrust limited, refer to LPC (2.5) bleed valve actuator mechanically stuck open - track check (Ref. TSM TASK 75-32-00-810-832).
(7) If the maintenance messages related to the High Pressure Compressor (HPC) Stator Vane Actuator (SVA) primary failure appear with ECAM warning engine compresor 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).
(8) If the maintenance messages related to the T2 engine sensor signal failure on channel A appear with the ECAM warning for engine FADEC status maintenance and/or the ECAM warning for engine sensor fault, refer to T2 engine sensor signal failure channel A (Ref. TSM TASK 73-21-00-810-871).
(9) If the maintenance messages related to the T2 engine sensor signal failure on channel B appear with the ECAM warning for engine FADEC status maintenance and/or the ECAM warning for engine sensor fault, refer to T2 engine sensor signal failure channel B (Ref. TSM TASK 73-21-00-810-872).
(10) If the maintenance messages related to the HPC bleed valve fail closed appear with the ECAM warning for engine air system fault, refer to HPC bleed valve failed closed during engine starting (Ref. TSM TASK 75-32-00-810-838).
(11) If the maintenance messages related to the HPC bleed valve fail open appear with the ECAM warning for engine system fault, refer to HPC bleed valve failed open (not during starting) (Ref. TSM TASK 75-32-00-810-841).
(12) If the maintenance messages related to the active HPC bleed valve fail closed appear with the ECAM warning for engine air system fault, refer to active HPC bleed valve failed closed (during starting) (Ref. TSM TASK 75-32-00-810-845).
(13) If the maintenance messages related to the active HPC bleed valve fail open appear with the ECAM warning for engine system fault, refer to Active HPC bleed valve failed open (not during Starting) (Ref. TSM TASK 75-32-00-810-844).
(14) 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.
(15) If you do not find any problems, do a visual inspection of the engine air systems for indications of hot gas leakage. Look carefully at the Environmental Control System (ECS) ducts, the Anti-ice ducts and the Turbine Cooling Air (TCA) tubes AMM 75-00-00-210-802.
(16) If not previously accomplished, run the engine at idle AMM 73-21-00-710-807.
(17) 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.
(18) If there is another impending hot start with no associated maintenance messages the engine gaspath is suspect. Refer to troubleshoot the engine after an engine performance decreased event (Ref. TSM TASK 71-00-00-810-869).
(19) If the gaspath condition is acceptable:
(a) Replace
Subtask 71-00-00-860-074-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.