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REFERENCE DESIGNATION
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78-36-00-410-040 Closing of the Thrust Reverser Doors
3. Job Set-up
__________
Subtask 72-00-00-941-067
A. Safety Precautions
(1) On the center pedestal, on the ENG panel 115VU:
(a) Put a warning notice to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
(3) On the overhead maintenance panel 50VU:
(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put a warning notice to tell persons not to energize the FADEC 1(2).
Subtask 72-00-00-010-074
B. Open the fan cowl doors (Ref. TASK 71-13-00-010-040):
FOR 1000EM1
437AL, 438AR
FOR 1000EM2
447AL, 448AR
Subtask 72-00-00-040-059
C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041).
Subtask 72-00-00-010-079
D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040):
FOR 1000EM1
451AL, 452AR
FOR 1000EM2
461AL, 462AR
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E E Feb 01/98 E E ECES E 4. Procedure
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_________ Subtask 72-00-00-210-062
A. Visual Inspection
NOTE : Visual inspection must be done without part removal.
____
(1) Possible damage to the spinner front and rear cones (Ref. TASK 72-21-00-210-005).
(2) General condition of the fan rotor blades (Ref. TASK 72-21-00-210-009).
(3) Wear of abradable material in fan inlet case (Ref. TASK 72-23-00-210-004).
(4) Condition of acoustical panels that may have been damaged as a result of interference with blade tip (Ref. TASK 72-23-00-210-004).
(5) Condition of splitter fairing and booster inlet guide vanes (IGV) (Ref. TASK 72-23-00-210-004) and (Ref. TASK 72-21-00-210-005).
(6) Condition of fan outlet guide vanes (OGV) and seals of fan OGV inner shroud (Ref. TASK 72-23-00-210-004).
(7) Damage to T12 sensor probe (Ref. TASK 73-21-40-210-002).
(8) Condition of exhaust and stage 4 LP turbine blades (Ref. TASK 72-54-00-290-006).
Subtask 72-00-00-280-057
B. Gaspath Inspection
(1) FOD associated with normal engine parameters.
(a) Do the step that follows if one or more of these conditions apply:
- FOD event has resulted in fan blade missing material/fan blade damage beyond serviceable limits.
- FOD event struck fan blades radially inward of mid span shroud.
- Evidence of debris has entered the booster inlet, ie: damage or debris on spinner front and rear cones, stage 1 booster vane or splitter fairing.
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1 Do a borescope inspection of the HPC stages 1, 3 and 8
_ (Ref. TASK 72-31-00-290-002).
NOTE : The borescope inspection may be delayed 25 hours or 10
____ cycles (whichever comes first) provided FOD did not result in missing material to the fan blades. Service extension is only permitted on one engine in the event of a dual engine FOD.
2 If damage is found inspect the other stages (Ref. TASK 72-31-
_
00-290-002).
R 3_ Do a borescope of the combustion chamber dome assembly after aR bird strike/ingestion event (Ref. TASK 72-42-00-290-005).
4 If the engine is referenced in the CFM SB 72-0391, do a
_ borescope inspection (use a flexible borescope) of the booster blades stage 5 and booster vane abradable stage 5 (Refer to CFM SB 72-0391).
NOTE : The borescope inspection may be delayed 25 hours or 10
____ cycles (whichever comes first).
(2) FOD associated with abnormal engine parameters.
(a) If FOD event was associated with surge, stall or flameout, do the steps which follow:
- Do a borescope inspection of the booster (Ref. TASK 72-21-00-290-003).
- Do a borescope inspection of the HPC stages 1, 3 and 8 (Ref. TASK 72-31-00-290-002).
- If damage is found inspect the other stages (Ref. TASK 72-31-00-290-002). 中國航空網(wǎng) www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：A320飛機維護(hù)手冊 AMM ENGINE 發(fā)動機 1(34)
