(a) If nothing is found:
1 do the following inspection as necessary:
_
- do a borescope inspection of the high-pressure compressor-rotor assembly (Ref. AMM TASK 72-31-00-290-002),
- do a borescope inspection of the high-pressure turbine blades/nozzles (Ref. AMM TASK 72-51-00-290-004),
- do a borescope inspection of the low pressure turbine (Ref. R AMM TASK 72-54-00-290-005) and (Ref. AMM TASK 72-54-00-290-R 006) and (Ref. AMM TASK 72-54-00-290-007) and (Ref. AMM TASK R 72-54-00-290-008) and (Ref. AMM TASK 72-54-00-210-005),
- do a borescope inspection of the combustion chamber (Ref. R AMM TASK 72-41-00-290-001),
- do a borescope inspection of the low pressure compressor (Ref. AMM TASK 72-21-00-290-003).
2 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).
a 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).
(4) If no failure message was found and if at the time of the event, the crew did not report symptoms such as stall, high EGT, sudden power loss, high vibrations:
- 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) ,
R - do a check of the Master Magnetic Chip Detector for particles (Ref. R AMM TASK 79-00-00-281-002).
(a) If nothing is found:
- do a detailed visual inspection of the PS3 sense line (Ref. AMM TASK 72-00-00-200-026).
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1 If nothing is found:
_
- remove and check the IP bleed check valve for correct condition (Ref. AMM TASK 36-11-41-200-001).
a 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) and the fuel pump (Ref. AMM TASK 73-11-10-000-003) and (Ref. AMM TASK 73-11-10-400-003).
(b) If the fault occurred during engine operation in gravity feeding (boost pump off):
- inspect the VALVE-AIR RELEASE, R WING TK (87QM) and fuel supply tubes in the wing fuel tank for condition,
- repair or replace if necessary.
(5) Do the operational test of the FADEC 2A and 2B (with the engine R motoring) (Ref. AMM TASK 73-29-00-710-040).
B. 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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TASK 72-00-00-810-805
Failure of the Two Engines
1. Possible Causes
_______________
- snow ingestion
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
72-00-00-810-806 Failure of Engine 1
72-00-00-810-807 Failure of Engine 2
3. Fault Confirmation
__________________
A. Test
(1) Not applicable, the confirmation can cause damage to the engine.
4. Fault Isolation
_______________
A. There is no known engine related problem that would cause the ECAM warning ENG DUAL FAILURE to come into view.
NOTE : Do the trouble shooting of individual engine per TSM procedure for
____
ENG 1(2) FAIL ECAM warning:
- for engine 1 (Ref. TASK 72-00-00-810-806),
- for engine 2 (Ref. TASK 72-00-00-810-807).
(1) No trouble shooting is required if the fault has occured on snow covered runway:
(a) During use of the thrust reverser at low speed. The engine failure was most likely caused by snow ingestion.
- Make sure that the air intake and fan blades are free of ice or snow accumulation before the next flight.
(b) During taxi. The reversion of the radio-altitude to NCD (non-computed data) can be occur and cause the removal of the inhibition of the 中國(guó)航空網(wǎng) m.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：A320 Trouble Shooting Manual 排故手冊(cè) 發(fā)動(dòng)機(jī) ENGINE(5)
