F 『
E C F M E
E E
E 56 E
E E
AMM 72-54-00-290-006 Inspection of the Stage 4 Blades 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 77-32-34-710-040 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 AMM 79-00-00-281-003 Check of FWD, AFT Sump, AGB, and TGB scavenge screens ASM 77-32/02
3. Fault Confirmation
__________________
A. Test
(1) Not applicable, the fault is evident.
NOTE : Vibration level is reported through a pilot report or
____ mechanical report <07> or EVMU unbalance report.
4. Fault Isolation
_______________
A. If the fault symptom is identified on the lower ECAM display unit by the crew observation: ENG 1(2)-FAN VIBRATION higher than 6 units:
(1) Do the following checks if no aircraft structure vibration/rumble was also reported by the crew.
NOTE : If momentary vibration on ECAM is greater than 6 units but in
____ order of less than 1 minute, no maintenance action is required provided indication is not associated with aircraft vibration felt by the crew and the indication did not repeat during the flight or following flights.
NOTE : Trouble Shooting is recommended at next maintenance
____ opportunity not interfering with Revenue Service operation.
(a) Do a check of the wiring, connectors and receptacles between (Ref. ASM 77-32/02):
- the No. 1 vibration sensor (4002EV) to the EVMU (2EV)
- the TRF vibration sensor (4003EV) to the EVMU (2EV).
(b) Check for damaged pins or connector oxidation:
1 If damage is found, repair or replace as necessary.
_
2 Do a cleaning of the connectors using a bristle brush with
_ Stoddard solvent (Material No. CP2011) (Ref. AMM TASK 73-21-50-210-002).
F 『 EEFF : ALL E ∞∞77-00-00∞∞∞∞∞∞∞∞∞∞Page 254
E E Aug 01/05 ERE ECES
F 『
E C F M E
E E
E 56 E
E E
(c) Do an electrical test of the No. 1 bearing vibration sensor and the TRF vibration sensor:
1 Disconnect the aircraft harness from the vibration sensor
_ connectors. If necessary, use soft nose pliers.
2 Measure the insulation resistance with a Megohmeter 0-100
_
Megohms, U= 45 VDC between:
. pins 1 and 2
. pins 1 and 3
. pin 2 and connector body
. pin 3 and connector body
3 The insulation resistance is expected to be greater than 20
_ Megohms. If anyone of these measurement is less than 20 Megohms, the sensor is not serviceable.
a 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)
- if the TRF vibration sensor is not serviceable, it must be replaced (Ref. AMM TASK 77-31-30-000-002) at the next opportunity.
NOTE : The No. 1 bearing vibration sensor cannot be
____ replaced on-wing.
(d) If the check (a), (b) and (c) are correct:
- do the operational test of the Engine Vibration Monitoring Unit EVMU throught the Centralized Fault Display System (CFDS) (Ref. AMM TASK 77-32-34-710-040)>.
(e) If the check (a), (b), (c) and (d) are correct:
- configure the MCDU to read the other vibration sensor output (Ref. AMM TASK 77-32-34-860-041)
中國航空網(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 發(fā)動機(jī)指示(88)
