79-34-01
 ALL  ú ú N03 Page 404 ú Feb 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
E. Procedure
 S 644-028-N00
 (1)
Lubricate the packing for the thermocouple probe with engine oil.

 S 434-008-N00

 (2)  
Install the packing to the thermocouple probe.

 S 424-020-N00

 (3)  
Install the thermocouple probe with the steps that follow:

 (a)  
Lubricate the threads of the bolts with engine oil.

 (b)  
Install the thermocouple probe with the bolts.

 (c)  
Tighten the bolts to 85-95 pound-inches (10.7-11.3 newton-meters).

 (d)  
Install the lockwire or safety cable and safety cable ferrule to the bolts.

 (e)  
Attach the lugs for the EEC wire harness to the terminal studs for the thermocouple probe with the washers and nuts.

 (f)  
Tighten the alumel lug (larger nut) to 18-22 pound-inches (2.0-2.5 newton-meters).

 (g)  
Tighten the chromel lug (smaller nut) to 15-18 pound-inches (1.7-2.0 newton-meters).

 F.
Put the Airplane Back to Its Usual Condition.

 S 414-034-N00
 WARNING: OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU CLOSE THE
_______ THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
 (1)  
Close the right thrust reverser (AMM 78-31-00/201).

 S 414-029-N00

 (2)  
Close the right core cowl panel (AMM 71-11-06/201).

 S 414-030-N00

 (3)  
Close the right fan cowl panel (AMM 71-11-04/201).

 S 444-031-N00

 (4)  
Do the activation procedure for the thrust reverser
 (AMM 78-31-00/201).

 S 864-022-N00

 (5)  
For the applicable engine, remove the DO-NOT-CLOSE tag and close these circuit breakers as follows:

 (a)  P6 Main Power Distribution Panel
 1) 6G15 SCU ALT PWR ENG 1
 2) 6G23 ENG SCU 1

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 79-34-01
 ALL  ú ú N03 Page 405 ú Feb 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
3) 6G16 SCU ALT PWR ENG 2
 4) 6G24 ENG SCU 2
 5) 6G17 SCU ALT PWR ENG 3
 6) 6G25 ENG SCU 3
 7) 6G18 SCU ALT PWR ENG 4
 8) 6G26 ENG SCU 4

 S 714-014-N00
 (6)  Do the operational test for the indicating system of the oil temperature (AMM 79-34-00/501).
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 79-34-01
 ALL  ú ú N02 Page 406 ú Feb 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
OIL FILTER BYPASS WARNING SYSTEM - DESCRIPTION AND OPERATION
____________________________________________________________
 1.  General
_______
 A.  The oil filter bypass warning system uses a differential pressure switch, with advisory and status messages in the flight compartment, to show when the engine main oil filter gets to a bypass condition.
 2.  Oil Filter Differential Pressure Switch (Fig. 1)
_______________________________________
 A.  The differential pressure switch for the main oil filter is installed at approximately the 9 o'clock position just forward of the main oil filter housing on the HPC case. The differential pressure switch is a hydraulically actuated and electrically operated snap-action switch.
 B.  The differential pressure switch senses the oil pressure differential across the main oil filter.
 3.  Oil Filter Bypass Warning Indication
____________________________________
 A.  An EICAS advisory message ENG (1, 2, 3, or 4) OIL FILT will show on the main EICAS display when the differential pressure of the main oil filter gets to the bypass value. (An EICAS status message ENG (1, 2, 3, or 4) OIL FILT will also show on the auxiliary EICAS display if the STAT key is pushed.)
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機維護手冊 滑油 OIL(129)