TASK 77-00-00-810-866
Core Vibrations Higher than or Equal to 5.5 Units (2.2 Ips) on Engine 1 or 2
1. Possible Causes
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- wiring, connectors and receptacles
- No. 1 bearing vibration sensor (4002EV)
- TRF vibration sensor (4003EV)
- EVMU (2EV)
2. Job Set-up Information
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A. Fixtures, Tools, Test and Support Equipment
-------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
No specific bristle brush
No specific megohmeter
No specific soft nose pliers
B. Consumable Materials
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Material No. CP2011 *
stoddard solvent (Ref. 70-30-00)
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 AMM 79-00-00-281-002 Check of the Electrical Master Chip Detector for
Particles
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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
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A. Test
(1) Read the advisory report <07> PRE EVENT and POST EVENT to confirm the interval of time.
NOTE : Trouble shooting is required before next flight.
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4. Fault Isolation
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A. If momentary vibration on ECAM is greater than 5.5 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.
(1) If the fault symptom is identified on the lower ECAM display unit by the crew observation ENG1/2 - CORE VIB higher than or equal to 5.5 units with core vibration indication flashing green and greater than
5.5 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.
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).
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(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. 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：A320 Trouble Shooting Manual 排故手册 发动机指示(92)
