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 1A and 1B (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),
- check that the drive mechanism of the valve is not broken.
(4) If no failure message is found and if the fault occurred during engine operation in gravity feeding (boost pump off):
- inspect the VALVE-AIR RELEASE, L WING TK (86QM) and fuel supply tubes in the wing fuel tank for condition,
- repair or replace as necessary.
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(5) If no failure message is found, and if at the time of the event, the Crew reported symptoms such as Stall, high EGT, sudden power loss, high vibration ,do the following:
- make sure the fan rotates freely and smoothly,
- do a visual inspection of the LPT stage 4 rotor blades,
- do a check of the Master Magnetic Chip Detector for particles (Ref. AMM TASK 79-00-00-281-002),
- examine the fuel filter cartridge, do a contamination check of the fuel filter (Ref. AMM TASK 73-11-10-000-003) and (Ref. AMM TASK 73-11-10-400-003),
- visually examine the VSV actuation system hardware for abnormal condition (Ref. AMM TASK 72-32-00-210-002).
(a) If nothing is found:
- do an inspection check of the PS3 Sense line (Ref. AMM TASK 72-00-00-200-026).
(b) If nothing is found:
- do an inspection of the IP bleed check valve for free operation and condition of the flappers (Ref. AMM TASK 36-11-41-200-001).
(c) If nothing is found:
- visually examine the alternator stator and rotor for evidence of contact.
1 if evidence of contact is found:
_
- do a check for correct installation of the rotor and the stator,
- repair as required.
2 If any play is noticed in the drive shaft assembly:
_
- replace the AGB (Ref. AMM TASK 72-63-00-000-003) and (Ref. AMM TASK 72-63-00-400-003).
B. If nothing is found:
(1) do the following inspection as necessary:
(a) do a borescope inspection of the high-pressure compressor-rotor assembly (Ref. AMM TASK 72-31-00-290-002),
(b) do a borescope inspection of the high-pressure turbine blades/nozzles (Ref. AMM TASK 72-51-00-290-004),
R (c) do a borescope inspection of the low pressure turbine (Ref. AMM R TASK 72-54-00-290-005) and (Ref. AMM TASK 72-54-00-290-006) and R (Ref. AMM TASK 72-54-00-290-007) and (Ref. AMM TASK 72-54-00-290-R 008) and (Ref. AMM TASK 72-54-00-210-005),
R (d) do a borescope inspection of the combustor chamber (Ref. AMM TASK R 72-41-00-290-001),
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(e) do a borescope inspection of the low pressure compressor (Ref. AMM TASK 72-21-00-290-003).
(f) If nothing is found:
- replace the Hydromechanical Unit (HMU) (Ref. AMM TASK 73-21-10-000-002) and (Ref. AMM TASK 73-21-10-400-002).
C. Do a minimum idle check (Ref. AMM TASK 71-00-00-710-006).
(1) No additional maintenance action is required if the fault is not confirmed.
(2) Repeat the fault isolation procedure if the fault continues.
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本文链接地址：A320 Trouble Shooting Manual 排故手册 发动机 ENGINE(7)
