C. Referenced Information
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AMM 71-11-00-210-001 Visual Inspection of the Air Intake Cowl AMM 71-50-00-210-001 Visual Inspection of the Power Plant Wire Harness AMM 72-31-00-290-002 Inspection of the High Pressure Compressor Rotor
Assembly AMM 72-52-00-290-001 Borescope Inspection of the High-Pressure Turbine
Blades (from the rear) AMM 73-21-50-210-002 Visual Inspection of the Wiring Harnesses AMM 77-31-30-000-002 Removal of the Turbine Rear Frame Vibration Sensor AMM 77-31-30-400-002 Installation of the Turbine Rear Frame Vibration
Sensor
AMM 77-32-34-710-040 Operational Check of EVMU through CFDS
AMM 77-32-34-860-041 Change the configuration of the Accelerometer
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AMM 79-00-00-281-002 Check of the Electrical Master Chip Detector for
Particles AMM 79-00-00-281-003 Check of FWD, AFT Sump, AGB, and TGB scavenge screens AMM 79-35-00-040-042 Replacement of the Main Oil Supply Filter and Check
of the Electrical Chip Detector Visual Indicator (pop-out) ASM 77-32/02
3. Fault Confirmation
__________________
A. Test
(1) Not applicable.
4. Fault Isolation
_______________
A. If momentary vibration on ECAM is between 3.2 and 4.1 units but in order of less than 1 minute and provided indication did not repeat during the flight or following flights:
- no maintenance action is required.
NOTE : Trouble shooting is to be carried out within 50 cycles.
____
NOTE : If the engine core vibration level has been reported just after
____
the engine installation:
- dispatch the aircraft. Vibration level must be monitored closely and reported to CFMI on a regular basis.
NOTE : Trouble shooting is recommended at next maintenance opportunity
____
not interfering with Revenue Service operation.
(1) If the fault symptom is identified on the lower ECAM display unit by the crew observation ENG1/2 - CORE VIB higher than 3.2 and lower than
4.1 units for less than one minute, but intermittently repeated:
(a) Do a check of the wiring, connectors and receptacles (Ref. ASM 77-32/02) between:
- the No. 1 bearing vibration sensor (4002EV) and the EVMU (2EV),
- the TRF vibration sensor (4003EV) and the EVMU (2EV).
(b) Disconnect the harnesses from the No. 1 bearing and the TRF sensors.
- do a check for damaged pins or connector oxidation (Ref. AMM TASK 71-50-00-210-001).
1 If damage is found:
_ - repair or replace as required.
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2 If no damage is found:
_
- do a cleaning of the connectors using a bristle brush with stoddard solvent (Material No. CP2011) (Ref. AMM TASK 73-21-50-210-002).
(c) Do an electrical test of the No. 1 bearing vibration sensor and the TRF vibration sensor:
- disconnect the aircraft harness from the vibration sensor connectors. If necessary, use soft nose pliers.
- measure the insulation resistance with a megohmeter 0-100 megohms, V=45VDC between: . pins 1 and 2 . pins 1 and 3 . pin 2 and connector body . pin 3 and connector body, the insulation resistance is expected to be greater than 20 megohms.
1 If one of these measurements is less than 20 megohms:
_ - the sensor is not serviceable.
2 If one of the two vibration sensors is found not serviceable:
_
- configure the MCDU to read the other vibration sensor output (Ref. AMM TASK 77-32-34-860-041).
NOTE : If the TRF vibration sensor is not serviceable, it
____ should be replaced (Ref. AMM TASK 77-31-30-000-002) and (Ref. AMM TASK 77-31-30-400-002).
NOTE : The No. 1 bearing vibration sensor cannot be replaced
____
on-wing.
(d) If nothing is found: 中國航空網 www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 發動機指示(108)
