747-400 AMM 飞机维护手册 气动系统 PNEUMATIC SYSTEM(174)

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 ~............................................................ | E/59/352/10 (Engine 1) | E/59/353/10 (Engine 1) | .............................................................. | E/59/352/01 (Engine 2) | E/59/353/01 (Engine 2) | .............................................................. | E/59/352/11 (Engine 3) | E/59/353/11 (Engine 3) | .............................................................. | E/59/352/00 (Engine 4) | E/59/353/00 (Engine 4) | 2..............................….............................1
 S 215-043
 (8)  
Make sure that the applicable labels and bits are set as follows: label 352, bit 23 is set to 0, label 352, bit 24 is set to 1, label 353, bit 11 is set to 0, label 353, bit 12 is set to 1,

 (9)  
Put the ENGINE BLEED switches to the desired position.

 (10)
 Remove electrical power if it is not necessary (AMM 24-22-00/201).

 S 845-032
 S 865-014
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 BLEED AIR TEMPERATURE SENSOR - REMOVAL/INSTALLATION
___________________________________________________
 1.  General_______
 A.  This procedure contains two tasks. The first task removes the bleed air temperature sensor. The second task installs the bleed air temperature sensor. The second task also does a test for the installation of the sensor.
 B.  The bleed air temperature sensor is installed on the right side of the lower forward strut. It is necessary to remove the access door for the mid-lower forward strut to get access to the sensor.
 C.  The installation of the sensor is the same for each strut.
 TASK 36-22-02-004-001
 2.  Remove the Bleed Air Temperature Sensor (Fig. 401)_______________________________________
 A.  References
 (1)  
AMM 24-22-00/201, Manual Control

 (2)  
AMM 36-00-00/201, Pneumatic System

 (3)  
AMM 54-62-00/201, Nacelle Strut Access Panels

 (4)  
IPC 36-12-02 Fig. 2

 B.  
Access

 (1)  
Location Zone
 452 Nacelle Strut 1 - Torque Box
 462 Nacelle Strut 2 - Torque Box
 472 Nacelle Strut 3 - Torque Box
 482 Nacelle Strut 4 - Torque Box

 (2)  
Access Panel 452DR Access Door, Midlower Strut (Forward) - Nacelle Strut 1 462DR Access Door, Midlower Strut (Forward) - Nacelle Strut 2 472DR Access Door, Midlower Strut (Forward) - Nacelle Strut 3 482DR Access Door, Midlower Strut (Forward) - Nacelle Strut 4

 C.  
Prepare to Remove the Sensor

 (1)  
Supply electrical power (AMM 24-22-00/201).

 (2)
Release the pressure in the pneumatic system (AMM 36-00-00/201).

 S 864-004

 (3)  
Open this circuit breaker for the applicable engine and attach a DO-NOT-CLOSE tag.

 (a)  
On the main power distribution panel, P6: 1) 6H32, AIR SUPPLY CONT 1 PWR 2) 6H33, AIR SUPPLY CONT 2 PWR 3) 6H34, AIR SUPPLY CONT 3 PWR

 S 864-002
 S 864-003
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

OUTBOARD

Bleed Air Temperature Sensor Installation
Figure 401 (Sheet 1)

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 36-22-02
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

Bleed Air Temperature Sensor Installation
Figure 401 (Sheet 2)

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