Material No. 08-028
SCOTCH TAPE PRIMER (Ref. 20-31-00)
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Material No. 08-032 USA MIL-I-19166
INSULATING ADHESIVE TAPE (Ref. 20-31-00) Material No. 08-053 D DAN 328-H
GLASS FIBER TAPE (Ref. 20-31-00)
C. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
71-13-00-010-040 Opening of the Fan Cowl Doors 71-13-00-410-040 Closing of the Fan Cowl Doors 77-31-10-991-300 Fig. 501
3. Job Set-up
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Subtask 77-31-10-941-051
A. Safety Precautions
(1) On the center pedestal, on the ENG panel 115VU:
(a) Put a warning notice to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
(3) On the overhead maintenance panel 50VU:
(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put a warning notice to tell persons not to energize the FADEC 1(2).
Subtask 77-31-10-010-051
B. Open the fan cowl doors: (Ref. TASK 71-13-00-010-040)
FOR 1000EM1
437AL, 438AR
FOR 1000EM2
447AL, 448AR
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4. Procedure
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(Ref. Fig. 501/TASK 77-31-10-991-300)
Subtask 77-31-10-720-051
A. Electrical Test of the No.1 Bearing Vibration Sensor.
(1) Disconnect the aircraft harness from the No.1 bearing vibration sensor connector. Use soft-nose connector pliers only if necessary.
(2) Measure the insulation resistance (on the connector) with a Megohmmeter 0-100 Meghoms between:
(a) Pins 1 and 2
(b) Pins 1 and 3
(c) Pin 2 and connector body
(d) Pin 3 and connector body
R (e) The insulation resistance must be more than 20 Meghoms. If any R one of these measurements is less than 20 Megohms, the sensor is R not serviceable.
(3) Make sure that the connector and the receptacle are clean and clear of unwanted material.
(4) Connect the aircraft harness to the No.1 bearing vibration sensor connector. Fully tighten by hand.
Subtask 77-31-10-040-050
B. Deactivation of the N.1 bearing sensor NOTE : If the sensor is not serviceable, deactivate the N.1 bearing
____ sensor to prevent automatic printing of frequency analysis reports.
(1) On the applicable engine, disconnect harness 4002EV-A from the N.1 bearing vibration sensor.
(2) Install a protective cover on harness 4002EV-A. We recommend that you R use plug cover 660-021M08 (Glenair) MIL-C-83723 or equivalent.
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No. 1 Bearing Vibration Sensor
Figure 501/TASK 77-31-10-991-300
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(3) Isolate the connector area. To do this, install SPECIAL MATERIALS (Material No. 05-044) or SPECIAL MATERIALS (Material No. 05-065) or BONDING AND ADHESIVE COMPOUNDS (Material No. 08-005) or BONDING AND ADHESIVE COMPOUNDS (Material No. 08-028) or BONDING AND ADHESIVE COMPOUNDS (Material No. 08-032) or BONDING AND ADHESIVE COMPOUNDS (Material No. 08-053).
R (4) Install a protective cover on sensor 4002EV. We recommend that you R use plug cover 660-022M08 (Glenair) MIL-C-83723 or equivalent. Attach R the plastic cover with a tie-rap.
(5) Attach and safety the electical harness 4002EV-A to the harness 4002KS (assembly 642W9821-501) with 2 tie-raps (or hoops) to prevent chafing of one harness against the other.
5. Close-up
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Subtask 77-31-10-410-051
A. Close Access
(1) Make sure that the work area is clean and clear of tool(s) and other items.
(2) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040) FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR 中國航空網 www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：A320飛機維護手冊 AMM ENGINE INDICATING 發動機指示(50)
