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(b) Engine operation with oil between 140 deg.C (284 deg.F) and 155 deg.C (311 deg.F) is allowed for 15 minutes.
(c) Above 155 deg.C (311 deg.F) the oil system must be drained (Ref. TASK 12-13-79-610-003) and (Ref. TASK 12-13-79-610-004) and serviced (Ref. TASK 12-13-79-610-002) and (Ref. TASK 12-13-79-610-002). Troubleshoot.
(d) After abnormally high oil temperature, check that the supply filter, common scavenge filter and chip detectors of lube unit are free of metal particles. If metal particles are present, remove and disassemble the engine for inspection.
(3) Oil Consumption
(a) Normal oil consumption is not expected to exceed 0.57 l.hr (approximately 0.6 quart.hr) (0.15 USgal.hr).
(b) As soon as one of the following cases occur, Troubleshooting (Ref. TSM TASK 79-00-00-810-818) or (Ref. TSM TASK 79-00-00-810-818) must be performed:
- Oil consumption exceeds 0.85 l.hr (approximately 0.9 quart.hr)
(0.22 USgal.hr).
- Oil consumption substantially exceeds that of the other operating engines.
- Oil consumption indicates a gradual increasing trend.
- Oil consumption indicates sudden step increase.
(c) The maximum serviceable oil consumption rate is limited to 1.5 l.hr (approximately 1.5 quart.hr) (0.40 USgal.hr). Consumption monitoring.
- Troubleshooting (Ref. TSM TASK 79-00-00-810-818) or (Ref. TSM TASK 79-00-00-810-818) must be performed as soon as the oil consumption rate overshoots the limit.
- If the result of the troubleshooting is not conclusive and no action can be taken to reduce the oil consumption rate, the engine has to be replaced.
Subtask 72-00-00-210-104
E. IFSD time limitation
(1) Dry-out the engine if you can not restart within 24 hours and after each ferry flight.
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F. Checks Required after Rough Landing Limits are Exceeded
(1) General
(a) The following procedure is to be used following a rough landing.
(2) Visual Inspection/Checks. Inspect the following:
(a) Wear of abradable material in fan inlet case at the 6 and 12 o'clock positions (Ref. TASK 72-23-00-210-003).
(b) Engine mounting pads forward and aft (Ref. TASK 72-23-00-210-004) and (Ref. TASK 72-56-00-210-002).
(c) Accessory and hardware attachments for metal fractures or excessive distortion.
(d) Piping connections for leaks.
(e) Lines, tubing for possible interferences.
(f) Turbine frame aft flange (Ref. TASK 72-56-00-210-002).
(3) Borescope Inspection/Checks. Inspect the following:
(a) Stages 1, 3, and 8 HPC blades (borescope ports S2, S4, and S9). (Ref. TASK 72-31-00-290-002).
Subtask 72-00-00-210-066
G. Inspection after Stall
(1) General
(a) If a stall or suspected stall has occurred, the following inspection and troubleshooting must be done (Ref. TSM 77 PB 101).
(2) Visual Inspection/Checks. Inspect the following:
(a) Fan rotor and abradable material (Ref. TASK 72-21-00-210-005) and (Ref. TASK 72-23-00-210-003).
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(3) Borescope Inspection/Checks. Inspect the following:
(a) For engine stalls in the start region, or for off-idle stalls which result in engine rollback into sub-idle N2 range:
1 If the start region EGT limit of 725 deg.C was exceeded,
_ borescope inspect HPT blades and stage 1 LPT blades (borescope ports S16 and S17) (Ref. TASK 72-52-00-290-004) and (Ref. TASK 72-54-00-290-005). (Ref. Fig. 601/TASK 72-00-00-991-305)
2 If the cause of the stall is not known, borescope inspect
_ stages 1, 3 and 8 HPC blades (borescope ports S2, S4 and S9) (Ref. TASK 72-31-00-290-002).
(b) For engine stalls at or above idle which do not result in engine rollback into sub-idle N2:
1 Borescope inspect HPT blades and stage 1 LPT blades (borescope
_ ports S16 and S17) (Ref. TASK 72-52-00-290-004) and (Ref. TASK 72-54-00-290-005). (Ref. Fig. 602/TASK 72-00-00-991-306)
2 If the cause of the stall is not known, borescope inspect
_ stage 5 of booster rotor blades (borescope port S05 at 3:30 o'clock location and at the rear end of booster) (Ref. TASK 72-21-00-290-003) and stages 1, 3 and 8 HPC blades (borescope ports S2, S4 and S9) (Ref. TASK 72-31-00-290-002).
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