(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.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

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 ALL  ú ú N01 Page 406 ú Jun 18/99
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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