DOC AIRBUS | TSM A320FTroubleshoot the Engine after a No Light with Correct Fuel Flow event
TASK 71-00-00-810-851-A
Troubleshoot the Engine after a No Light with Correct Fuel Flow event
1. Possible Causes
A. Referenced Information
3. Fault Confirmation
Subtask 71-00-00-710-108-A ** ON A/C NOT FOR ALL
Subtask 71-00-00-860-063-A ** ON A/C NOT FOR ALL
[Rev.8 from Aug 2018]
2026.04.04 04:35:04 UTC
Troubleshoot the Engine after a No Light with Correct Fuel Flow event
1. Possible Causes
- FUEL FLOW DIVIDER [4090KS]
- fuel recovery tank
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 73-21-00-810-870-A | EEC Internal Failure Level B |
| TSM TASK 73-21-00-810-878-A | EEC Internal Failure Level A NO GO |
| TSM TASK 73-21-00-810-912-A | Aircraft 28 VDC Bus Fail Channel A |
| TSM TASK 73-21-00-810-913-A | Aircraft 28 VDC Bus Fail Channel B |
| TSM TASK 74-00-00-810-830-A | Ignition Failure/Engine Failed to Light during Start |
| TSM TASK 74-00-00-810-831-A | Ignition/Exciter #1 Failure |
| TSM TASK 74-00-00-810-832-A | Ignition/Exciter #2 Failure |
| AMM 36-11-00-740-802 | BITE Test of the Engine Bleed Air System (EBAS) (System Test) |
| 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 72-41-00-290-802 | Borescope Inspection of the Combustion Chamber and HPT Nozzle Guide Vanes |
| AMM 72-41-01-920-803 | Replacement of the Diffuser Case Insert and Spacer |
| AMM 72-51-00-290-802 | Borescope Inspection of the High Pressure Turbine (HPT) |
| AMM 73-11-00-210-805 | General Visual Inspection of the Fuel Distribution System for Contamination |
| AMM 73-11-03-000-801 | Removal of the Fuel Flow Divider |
| AMM 73-11-03-400-801 | Installation of the Fuel Flow Divider |
| AMM 73-13-01-000-801 | Removal of the Fuel Recovery Tank |
| AMM 73-13-01-400-801 | Installation of the Fuel Recovery Tank |
| 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 74-00-00-710-802 | Operational Test of the Ignition System with the CFDS |
Subtask 71-00-00-710-108-A ** ON A/C NOT FOR ALL
A. Investigate the Engine after a No Light with Correct Fuel Flow 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 71-00-00-810-116-A ** ON A/C NOT FOR ALL A. Do the steps that follow:
(1) If the maintenance messages related to the ignition system A failure appear with the ECAM warning for engine ignition system A fault and engine ignition system A, refer to ignition/exciter #1 failure (Ref. TSM TASK 74-00-00-810-831).
(2) If the maintenance messages related to the ignition system B failure appear with the ECAM warning for engine ignition system B fault and engine ignition system B, refer to ignition/exciter #2 failure (Ref. TSM TASK 74-00-00-810-832).
(3) If the maintenance messages related to the ignition failure during engine start appear with the ECAM warning for engine start - engine ignition fault, refer to ignition failure/engine failed to light during start (Ref. TSM TASK 74-00-00-810-830).
(4) If the maintenance messages related to the Fuel Metering Valve (FMV) not closed on channel A appear with the ECAM warning for engine FADEC status maintenance or the crew alert warning message for engine fuel valve fault, refer to fuel flow not at shutoff during start channel A (Ref. TSM TASK 73-11-00-810-845).
(5) If the maintenance messages related to the FMV not closed on channel B appear with the ECAM warning for engine FADEC status maintenance or the crew alert warning message for engine fuel valve fault, refer to fuel flow not at shutoff during start channel B (Ref. TSM TASK 73-11-00-810-845).
(6) If the maintenance messages related to the EEC internal fail no go on both channels appear with the ECAM warning for engine FADEC system fault, refer to EEC internal fail no go on both channels (Ref. TSM TASK 73-21-00-810-878).
(7) If the maintenance messages related to the EEC internal fail short time dispatch on both channels appear with the ECAM warning for engine minor fault, refer to EEC internal fail short time dispatch on both channels (Ref. TSM TASK 73-21-00-810-870).
(8) If the maintenance messages related to the aircraft 28 VDC Bus failed on channel A appear with the ECAM warning for engine FADEC status maintenance or with crew alert warning message for engine aircraft FADEC supply and/or ECAM warning engine start, refer to aircraft 28 VDC Bus failed (Ref. TSM TASK 73-21-00-810-912).
(9) If the maintenance messages related to the aircraft 28 VDC Bus failed on channel B appear with the ECAM warning for engine FADEC status maintenance or with crew alert warning message for engine aircraft FADEC supply and/or ECAM warning engine start, refer to aircraft 28 VDC Bus failed (Ref. TSM TASK 73-21-00-810-913).
(10) If there are no EEC monitored faults or messages recorded, check the operation of the ignition system AMM 74-00-00-710-802.
(11) If you do not find any problems, the engine gaspath is suspect. Inspect the engine inlet area AMM 72-00-00-210-813.
(12) If you find evidence of Foreign Object Damage (FOD), borescope inspect the High Pressure Compressor (HPC) AMM 72-35-00-290-801.
(13) If you do not find any problems, borescope inspect the combustion chamber area AMM 72-41-00-290-802.
(14) If you do not find any problems, borescope inspect the High Pressure Turbine (HPT) AMM 72-51-00-290-802.
(15) If you do not find any problems, check the fuel nozzles for clogging/coking AMM 73-11-00-210-805.
(16) If you do not find any problems, check the igniters for correct immersion depth AMM 72-41-01-920-803.
(17) If you do not find any problems or the fault continues:
(a) Replace FUEL FLOW DIVIDER [4090KS] AMM 73-11-03-000-801 and AMM 73-11-03-400-801.
(18) If the fault continues:
(a) Replace fuel recovery tank AMM 73-13-01-000-801 and AMM 73-13-01-400-801.
(19) If you do not find any problems, run the engine at idle AMM 73-21-00-710-807.
(20) If the fault continues, it may indicate an aircraft system interface problem, such as, the Environmental Control System (ECS). Check the aircraft ECS for any recorded faults AMM 36-11-00-740-802.
5. Close-up(1) If the maintenance messages related to the ignition system A failure appear with the ECAM warning for engine ignition system A fault and engine ignition system A, refer to ignition/exciter #1 failure (Ref. TSM TASK 74-00-00-810-831).
(2) If the maintenance messages related to the ignition system B failure appear with the ECAM warning for engine ignition system B fault and engine ignition system B, refer to ignition/exciter #2 failure (Ref. TSM TASK 74-00-00-810-832).
(3) If the maintenance messages related to the ignition failure during engine start appear with the ECAM warning for engine start - engine ignition fault, refer to ignition failure/engine failed to light during start (Ref. TSM TASK 74-00-00-810-830).
(4) If the maintenance messages related to the Fuel Metering Valve (FMV) not closed on channel A appear with the ECAM warning for engine FADEC status maintenance or the crew alert warning message for engine fuel valve fault, refer to fuel flow not at shutoff during start channel A (Ref. TSM TASK 73-11-00-810-845).
(5) If the maintenance messages related to the FMV not closed on channel B appear with the ECAM warning for engine FADEC status maintenance or the crew alert warning message for engine fuel valve fault, refer to fuel flow not at shutoff during start channel B (Ref. TSM TASK 73-11-00-810-845).
(6) If the maintenance messages related to the EEC internal fail no go on both channels appear with the ECAM warning for engine FADEC system fault, refer to EEC internal fail no go on both channels (Ref. TSM TASK 73-21-00-810-878).
(7) If the maintenance messages related to the EEC internal fail short time dispatch on both channels appear with the ECAM warning for engine minor fault, refer to EEC internal fail short time dispatch on both channels (Ref. TSM TASK 73-21-00-810-870).
(8) If the maintenance messages related to the aircraft 28 VDC Bus failed on channel A appear with the ECAM warning for engine FADEC status maintenance or with crew alert warning message for engine aircraft FADEC supply and/or ECAM warning engine start, refer to aircraft 28 VDC Bus failed (Ref. TSM TASK 73-21-00-810-912).
(9) If the maintenance messages related to the aircraft 28 VDC Bus failed on channel B appear with the ECAM warning for engine FADEC status maintenance or with crew alert warning message for engine aircraft FADEC supply and/or ECAM warning engine start, refer to aircraft 28 VDC Bus failed (Ref. TSM TASK 73-21-00-810-913).
(10) If there are no EEC monitored faults or messages recorded, check the operation of the ignition system AMM 74-00-00-710-802.
(11) If you do not find any problems, the engine gaspath is suspect. Inspect the engine inlet area AMM 72-00-00-210-813.
(12) If you find evidence of Foreign Object Damage (FOD), borescope inspect the High Pressure Compressor (HPC) AMM 72-35-00-290-801.
(13) If you do not find any problems, borescope inspect the combustion chamber area AMM 72-41-00-290-802.
(14) If you do not find any problems, borescope inspect the High Pressure Turbine (HPT) AMM 72-51-00-290-802.
(15) If you do not find any problems, check the fuel nozzles for clogging/coking AMM 73-11-00-210-805.
(16) If you do not find any problems, check the igniters for correct immersion depth AMM 72-41-01-920-803.
(17) If you do not find any problems or the fault continues:
(a) Replace FUEL FLOW DIVIDER [4090KS] AMM 73-11-03-000-801 and AMM 73-11-03-400-801.
(18) If the fault continues:
(a) Replace fuel recovery tank AMM 73-13-01-000-801 and AMM 73-13-01-400-801.
(19) If you do not find any problems, run the engine at idle AMM 73-21-00-710-807.
(20) If the fault continues, it may indicate an aircraft system interface problem, such as, the Environmental Control System (ECS). Check the aircraft ECS for any recorded faults AMM 36-11-00-740-802.
Subtask 71-00-00-860-063-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.