Failure of Engine 2
1. Possible Causes
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- VALVE-AIR RELEASE, R WING TK (87QM)
- engine
- low-pressure fuel shut-off valve
- PS3 Sense line
- IP bleed check valve
- Hydromechanical Unit (HMU)
2. Job Set-up Information
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A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 28-24-00-720-001 AMM 36-11-41-200-001 AMM 71-00-00-710-006 AMM 72-00-00-200-026 AMM 72-21-00-290-003
AMM 72-31-00-290-002
AMM 72-32-00-210-002
R AMM 72-41-00-290-001
R
AMM 72-51-00-290-004
R AMM 72-54-00-210-005
R AMM 72-54-00-290-005
R AMM 72-54-00-290-006
R AMM 72-54-00-290-007
R AMM 72-54-00-290-008
AMM 72-63-00-000-003
AMM 72-63-00-400-003
AMM 73-11-10-000-003
AMM 73-11-10-400-003
AMM 73-21-10-000-002
AMM 73-21-10-400-002
R AMM 73-29-00-710-040
R
R AMM 73-29-00-710-040
R
AMM 79-00-00-281-002
F EEFF : ALL E E ECES Functional Test of the LP Fuel Shut Off ValvesInspection/Check of the IP Bleed Check ValveMinimum Idle CheckInspection/Check of the PS3 LineBorescope Inspection of the Booster Rotor Blades, Stages 2,3,4 and 5 through the Booster Inlet and Borescope Ports SO3 and SO5Inspection of the High Pressure Compressor Rotor AssemblyInspection/Check of the HPC Front Stator Assembly Borescope Inspection of the Combustion Chamber Liners, Dome Areas,HPT Nozzle Vanes and ShroudsBorescope Inspection of High-Pressure Turbine Nozzle Assembly Inspection of the Turbine Case Inspection of the Stage 1-3 Blades Inspection of the Stage 4 Blades Inspection of the Stage 2-4 Nozzle Segments Inspection of the Stage 1-4 Stationary Air SealsRemoval of the Accessory Gearbox AssemblyInstallation of the Accessory Gearbox AssemblyRemoval of the Fuel Pump and Filter AssemblyInstallation of the Fuel Pump and Filter AssemblyRemoval of the Hydromechanical Unit (HMU)Installation of the Hydromechanical Unit (HMU) Operational Test of the FADEC on the Ground (with Engine Motoring) Operational Test of the FADEC on the Ground (with Engine Non motoring)Check of the Electrical Master Chip Detector for Particles
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3. Fault Confirmation
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R A. Test
R CAUTION : IF THE ENGINE WAS NOT RESTARTED AFTER THE EVENT OR WITHIN 24
_______ R HRS, DO THE ENGINE DRY OUT PROCEDURE, OR FURTHER DAMAGE TO R ENGINE MAY OCCUR.
R CAUTION : WHEN THE "ENG/MASTER" LEVER IS IN THE "ON" POSITION, BE VERY
_______ R CAREFUL NOT TO SET THE "ENG/MODE" SELECTOR SWITCH TO "CRANK" OR R "IGN/START". R IF YOU DO SET THE SELECTOR SWITCH TO ONE OF THESE POSITIONS, R THE ENGINE WILL START. THERE IS THUS A RISK OF INJURY TO R PERSONS AND OF DAMAGE TO EQUIPMENT.
R NOTE : The ENG1(2) FAIL ECAM warning is shown if the engine rolls back
____ R sub idle below 50% N2 and the Master Lever is still set to ON.
R (1) If the engine was successfully restarted after the event:
R - do the operational test of the FADEC 2A and 2B (with the engine
R motoring) (Ref. AMM TASK 73-29-00-710-040).
R (2) If the engine could not restart after the event or no start attempt
R was done:
R - do the operational test of the FADEC 2A and 2B (with the engine non
R motoring) (Ref. AMM TASK 73-29-00-710-040).
4. Fault Isolation
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A. Do the trouble shooting related to the failure message(s):
(1) Triggered (if any) during the fault confirmation test referred in Para. 3.A.
(2) Available (if any) in the Post Flight Report (PFR), the FADEC Last Leg Report and SMR/Class 3 Report for ECU, HMU, FMV, VSV, PS3 failure messages.
(3) If no failure message and the fault (ECAM WARNING) occurred just after the engine start sequence or during taxi out or at first engine acceleration with no other symptom than the engine spooling down sub idle:
- do a check for correct operation of the low-pressure fuel shut-off valve (Ref. AMM TASK 28-24-00-720-001), 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：A320 Trouble Shooting Manual 排故手册 发动机 ENGINE(8)
