(4) If the vibration continues with engine N1 vib less than 2 units, cold trim balance the engine using the vectorial method with the 51% N1 speed only, using current vib mamual input option, according to EVMU flight data print.
NOTE : In SCREWS TO CHANGE menu, push the line key adjacent to the
____ UPDATE indication to memorize the EVMU calculation.
F 『 EEFF : ALL E ∞∞77-00-00∞∞∞∞∞∞∞∞∞∞Page A221
E E Aug 01/05 E E ECES
E F 『 EEFF : 051-051, E ∞∞77-00-00∞∞∞∞∞∞∞∞∞∞Page A222
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R **ON A/C 051-051,
R A. Balance the engine with the CFM Trim Balance Software, using the actual
R flight data prints :
R (1) Cold trim balance the engine using One Shot method (2 sensors, 5
R speeds) (Ref. AMM TASK 71-00-00-750-001)
R - Dispatch the aircraft.
R (2) If the vibration continue, Cold trim balance the engine using
R Vectorial method (Ref. AMM TASK 71-00-00-750-001)
R - Dispatch the aircraft.
R (3) If the vibration continue with engine N1 vib higher than 2 units, go
R to step(2)
R (4) If the vibration continue with engine N1 vib less than 2 units, Cold
R trim balance the engine using Vectorial method with the 51 % N1 speed
R only : input only 51% N1 data into the software.
R - Dispatch the aircraft.
E E May 01/05 E E ECES
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POWER - FAULT ISOLATION PROCEDURES
__________________________________
R **ON A/C 001-049, 051-099, 101-105, 151-154, 201-207,
TASK 77-10-00-810-809
Loss of the ECU Cross Channel on Engine 1
1. Possible Causes
_______________
- harness J9
- ECU (4000KS)
- control alternator
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 73-21-30-000-001 Removal of the Control Alternator AMM 73-21-30-400-001 Installation of the Control Alternator AMM 73-21-50-000-042 Removal of the HJ9 Harness AMM 73-21-50-400-042 Installation of the HJ9 Harness AMM 73-21-60-000-001 Removal of the Electronic Control Unit (ECU)(4000KS) AMM 73-21-60-400-001 Installation of the Electronic Control Unit
(ECU)(4000KS)
ASM 73-25/18
3. Fault Confirmation
__________________
A. Not apllicable
4. Fault Isolation
_______________
A. If the fault symptom is identified by the maintenance message ALT, ECU, J9: NOTE 1 : In the usual operating condition, a fault of the harness J9 is detected with the test of the channel A. NOTE 2 : When a cross channel fault occurs, the harness fault is detected during the test on the opposite channel.
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 發動機指示(114)
