(5)
IPC 79-32-01 Fig. 1
(6)
WDM 79-33-11
(7)
SSM 79-33-01
C.
Access
(1)
Location Zone
412 Engine 1 - Fwd HPC Case 10:00 o'clock
422 Engine 2 - Fwd HPC Case 10:00 o'clock
432 Engine 3 - Fwd HPC Case 10:00 o'clock
442 Engine 4 - Fwd HPC Case 10:00 o'clock
(2)
Access Panel
415 Left Thrust Reverser Half - Engine 1
425 Left Thrust Reverser Half - Engine 2
435 Left Thrust Reverser Half - Engine 3
445 Left Thrust Reverser Half - Engine 4
D.
Procedure
(1)
Remove the protection caps.
S 424-011-N00
(2)
Put the warning switch to the bracket with the electrical connector in the direction shown in Fig. 401.
S 644-021-N00
(3)
Lubricate the threads of the bolts, which attach the warning switch, with engine oil.
S 434-012-N00
(4)
Attach the warning switch to the bracket with the bolts.
S 434-010-N00
(a) Tighten the bolts.
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79-33-01
ALL ú ú N01 Page 405 ú Jun 18/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
S 434-013-N00
(5)
Connect the oil pressure tube to the warning switch.
(a)
Tighten the tube nut.
S 434-014-N00
(6)
Connect the vent tube to the warning switch.
(a)
Tighten the tube nut.
S 434-015-N00
(7)
Connect the electrical connector (DS1584) to the warning switch.
E.
Put the Airplane Back to Its Usual Condition.
S 414-027-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 left thrust reverser (AMM 78-31-00/201).
S 414-022-N00
(2)
Close the left core cowl panel (AMM 71-11-06/201).
S 414-023-N00
(3)
Close the left fan cowl panel (AMM 71-11-04/201).
S 444-024-N00
(4)
Do the activation procedure for the thrust reverser
(AMM 78-31-00/201).
S 424-029-N00
(5)
Remove the DO-NOT-CLOSE tags and close these circuit breakers that follow:
(a)
P7 Overhead Circuit Breaker Panel
1) 7F9 EIU L
2) 7F10 EIU C
3) 7F15 EIU R
(6)
Do the operational test for the warning switch (AMM 79-33-00/501).
S 794-018-N00
(7)
Examine the tube connections of the warning switch for oil leakage after the engine shutdown.
S 714-017-N00
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
OIL TEMPERATURE INDICATING SYSTEM - DESCRIPTION AND OPERATION
_____________________________________________________________
1. General
_______
A. The oil temperature indicating system measures the temperature of engine oil at the main gearbox and at the No. 3 bearing scavenge oil tube. These temperatures are sent through the electronic engine control (EEC) to the EFIS/EICAS interface units (EIU's).
B. The oil temperature of the main gearbox is shown on the auxiliary EICAS display in the flight compartment. The oil temperature of the No. 3 bearing is compared to the oil temperature of the main gearbox to get a differential oil temperature, which is shown on the electronic propulsion control system (EPCS) maintenance page adjacent to the title of DOT.
2. EEC Oil Temperature Thermocouple Probe (Fig. 1)
______________________________________
A. The thermocouple probe for the EEC oil temperature includes two thermocouples and is installed on the forward face of the main gearbox at approximately the 7 o'clock position.
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