DOC AIRBUS | TSM A320FTroubleshoot the Engine after an EGT Exceeded Operating Limits event
TASK 71-00-00-810-855-A
Troubleshoot the Engine after an EGT Exceeded Operating Limits event
1. Possible Causes
2. Job Set-up Information
A. Referenced Information
3. Fault Confirmation
Subtask 71-00-00-710-112-A ** ON A/C NOT FOR ALL
Subtask 71-00-00-860-067-A ** ON A/C NOT FOR ALL
[Rev.8 from Aug 2018]
2026.04.04 04:40:53 UTC
Troubleshoot the Engine after an EGT Exceeded Operating Limits event
1. Possible Causes
2. Job Set-up Information
A. Referenced Information
| REFERENCE | DESIGNATION |
|---|---|
| TSM TASK 73-21-00-810-894-A | P2 Synthesized in Disagreement with ADIRUx |
| TSM TASK 73-21-00-810-897-A | T2 in Disagreement with ADIRUx or T2 in Range Failed |
| TSM TASK 75-32-00-810-832-A | LPC (2.5) Bleed Valve Actuator Mechanically Stuck Open - Track Check |
| 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 71-00-00-710-806 | Power Assurance Test |
| AMM 71-00-00-720-811 | Test No. 3 - Idle Power Test |
| AMM 72-00-00-100-802 | Cleaning of the Engine Gaspath |
| AMM 72-00-00-210-809 | Visual Examination (after an Exhaust Gas Temperature (EGT) Overtemperature) |
| AMM 72-41-00-290-802 | Borescope Inspection of the Combustion Chamber and HPT Nozzle Guide Vanes |
| AMM 73-11-00-210-805 | General Visual Inspection of the Fuel Distribution System for Contamination |
| AMM 73-21-00-710-806 | Test No.7 - EEC Operation Test (Self Test) |
| AMM 75-00-00-210-802 | Visual Examination of the Engine Air Systems |
| AMM 75-32-01-200-801 | Mechanical Check of the Low Pressure Compressor (LPC) (2.5) Bleed Air System |
| AMM 75-32-01-400-801 | Installation of the Low Pressure Compressor (LPC) (2.5) Bleed Valve Actuator |
| AMM 77-21-00-210-801 | General Visual Inspection (GVI) of the Temperature Indicating System |
Subtask 71-00-00-710-112-A ** ON A/C NOT FOR ALL
A. Investigate the Engine After an EGT Exceeded Operating Limits event
(1) Use this troubleshooting procedure to investigate the engine after an EGT Exceeded Operating Limits event.
4. Fault Isolation(1) Use this troubleshooting procedure to investigate the engine after an EGT Exceeded Operating Limits event.
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 71-00-00-810-120-A ** ON A/C NOT FOR ALL A. Do the steps that follow:
(1) Look at the AIDS engine report - gas path advisory for information relating to the fault. Refer to Do the EEC system interactive test AMM 71-00-00-710-806.
(2) Make sure that the engine is serviceable AMM 72-00-00-210-809.
(3) Using the Multipurpose Control and Display Unit (MCDU) test the FADEC system for any recorded faults.
(a) If the engine is serviceable, find the reason for the high EGT indication in the steps below.
(b) If the engine is not serviceable, replace the engine.
(4) Review the Engine Performance Data.
(a) If the engine performance has degraded slowly over time, clean the engine gaspath AMM 72-00-00-100-802, or remove the engine for overhaul.
(b) If there was a step increase in EGT continue with the procedure below.
(5) Use the Multipurpose Control and Display Unit (MCDU) to test the FADEC system for any recorded faults AMM 73-21-00-710-806.
(7) If the maintenace messages related to the EGT sensor electrical failure on channel B appear with the ECAM warning for engine minor fault and/or engine sensor fault along with amber crosses on EGT indication, refer to EGT sensor electrical failure channel B (Ref. TSM TASK 77-21-00-810-809).
(8) If you do not find any problems or if the EGT sensor electrical failure message does NOT appear, the indicated EGT is assumed to be correct.
(9) If the maintenance messages related to the 2.5 bleed valve actuator failure open appear with the ECAM warning for engine compressor vane fuel consumption increased thrust limited, refer to LPC (2.5) bleed valve actuator mechanically stuck open - track (Ref. TSM TASK 75-32-00-810-832).
(10) 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 75-31-00-810-817).
(11) If the maintenance messages related to the T2 sensor disagree with ADIRU sensor appear, refer to T2 in disagreement with ADIRUx or T2 in range failed (Ref. TSM TASK 73-21-00-810-897).
(12) If the maintenance messages related to the Pamb sensor disagree with ADIRU sensor appear, refer to PAMB in range failed (Ref. TSM TASK 73-21-00-810-902).
(13) If the maintenance messages related to the P2 calculated disagree with ADIRU sensor appear, refer to P2 synthesized in disagreement with ADIRUx (Ref. TSM TASK 73-21-00-810-894).
(14) Make sure that the EGT indication system operates correctly AMM 77-21-00-210-801.
(15) If you do not find any problems, do a visual inspection the LPC 2.5 bleed system AMM 75-32-01-200-801. Look carefully for evidence of binding in the actuation system or torn/missing 2.5 bleed seals.
(16) If you do not find any problems, check to make sure that the LPC (2.5) bleed linkage is secure AMM 75-32-01-400-801.
(17) If you do not find any problems, do a visual inspection of the engine air systems for indications of hot gas leakage AMM 75-00-00-210-802. Look carefully at the Environmental Control System (ECS) ducts the anti-ice ducts and the turbine cooling air tubes.
(18) If you do not find any problems, borescope inspect the combustion chamber area AMM 72-41-00-290-802. Look carefully at the fuel nozzles for clogging.
(19) If you do not find any problems, check the fuel nozzles for clogging/coking AMM 73-11-00-210-805.
(20) Do a power assurance test AMM 71-00-00-720-811.
5. Close-up(1) Look at the AIDS engine report - gas path advisory for information relating to the fault. Refer to Do the EEC system interactive test AMM 71-00-00-710-806.
(2) Make sure that the engine is serviceable AMM 72-00-00-210-809.
(3) Using the Multipurpose Control and Display Unit (MCDU) test the FADEC system for any recorded faults.
(a) If the engine is serviceable, find the reason for the high EGT indication in the steps below.
(b) If the engine is not serviceable, replace the engine.
(4) Review the Engine Performance Data.
(a) If the engine performance has degraded slowly over time, clean the engine gaspath AMM 72-00-00-100-802, or remove the engine for overhaul.
(b) If there was a step increase in EGT continue with the procedure below.
(5) Use the Multipurpose Control and Display Unit (MCDU) to test the FADEC system for any recorded faults AMM 73-21-00-710-806.
NOTE: 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.
NOTE: If the EEC senses a surge inside of the takeoff envelope Foreign Object Damage (FOD) is assumed to have occurred and the Low Pressure Compressor (LPC) bleed is held partially open. If there is no other damage this will result in normal engine parameters except for an elevated EGT typically 212 deg.F (100.00 deg.C) . The LPC bleed open FOD command is removed when the thrust lever is reduced to idle and then reset to the desired power level. This action restores normal LPC bleed operation and restores EGT to normal.
(6) If the maintenace messages related to the EGT sensor electrical failure on channel A appear with the ECAM warning for engine minor fault and/or engine sensor fault along with amber crosses on EGT indication, refer to EGT sensor electrical failure channel A (Ref. TSM TASK 77-21-00-810-808). (7) If the maintenace messages related to the EGT sensor electrical failure on channel B appear with the ECAM warning for engine minor fault and/or engine sensor fault along with amber crosses on EGT indication, refer to EGT sensor electrical failure channel B (Ref. TSM TASK 77-21-00-810-809).
(8) If you do not find any problems or if the EGT sensor electrical failure message does NOT appear, the indicated EGT is assumed to be correct.
(9) If the maintenance messages related to the 2.5 bleed valve actuator failure open appear with the ECAM warning for engine compressor vane fuel consumption increased thrust limited, refer to LPC (2.5) bleed valve actuator mechanically stuck open - track (Ref. TSM TASK 75-32-00-810-832).
(10) 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 75-31-00-810-817).
(11) If the maintenance messages related to the T2 sensor disagree with ADIRU sensor appear, refer to T2 in disagreement with ADIRUx or T2 in range failed (Ref. TSM TASK 73-21-00-810-897).
(12) If the maintenance messages related to the Pamb sensor disagree with ADIRU sensor appear, refer to PAMB in range failed (Ref. TSM TASK 73-21-00-810-902).
(13) If the maintenance messages related to the P2 calculated disagree with ADIRU sensor appear, refer to P2 synthesized in disagreement with ADIRUx (Ref. TSM TASK 73-21-00-810-894).
(14) Make sure that the EGT indication system operates correctly AMM 77-21-00-210-801.
(15) If you do not find any problems, do a visual inspection the LPC 2.5 bleed system AMM 75-32-01-200-801. Look carefully for evidence of binding in the actuation system or torn/missing 2.5 bleed seals.
(16) If you do not find any problems, check to make sure that the LPC (2.5) bleed linkage is secure AMM 75-32-01-400-801.
(17) If you do not find any problems, do a visual inspection of the engine air systems for indications of hot gas leakage AMM 75-00-00-210-802. Look carefully at the Environmental Control System (ECS) ducts the anti-ice ducts and the turbine cooling air tubes.
(18) If you do not find any problems, borescope inspect the combustion chamber area AMM 72-41-00-290-802. Look carefully at the fuel nozzles for clogging.
(19) If you do not find any problems, check the fuel nozzles for clogging/coking AMM 73-11-00-210-805.
(20) Do a power assurance test AMM 71-00-00-720-811.
Subtask 71-00-00-860-067-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.