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时间:2011-04-13 08:10来源:蓝天飞行翻译 作者:航空
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SENSING TUBE
DRAIN HOLESELECTRICAL CONNECTOR WING RIB
BLEED AIR FWD
OVERPRESSURE
SWITCH

ENGINE 4 BLEED AIR PRESSURE SENSOR
(ENGINE 1 BLEED AIR PRESSURE SENSOR IS OPPOSITE)

B
Bleed Air Pressure Sensor Installation
Figure 401

L98691
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 36-21-02
 ALL  ú ú 04 Page 402 ú Jun 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 S 864-055
 (5)  
Open the applicable circuit breaker and attach a DO-NOT-CLOSE tag:

 (a)  
P6 Main Power Distribution Panel
 1) 6H32, ENG 1 AIR SUPPLY CONT
 2) 6H33, ENG 2 AIR SUPPLY CONT
 3) 6H34, ENG 3 AIR SUPPLY CONT
 4) 6H35, ENG 4 AIR SUPPLY CONT


 D.
Remove the Sensor


 S 034-006
 (1)  
Disconnect the electrical connector from the sensor:

 (a)  
Engine 1 - DX846 BLEED PRESSURE SENSOR

 (b)  
Engine 2 - DX847 BLEED PRESSURE SENSOR

 (c)  
Engine 3 - DX994 BLEED PRESSURE SENSOR

 (d)  
Engine 4 - DX995 BLEED PRESSURE SENSOR


 S 034-007
 (2)  
Disconnect the pressure sensing tube from the sensor.

 S 034-021

 (3)  
Remove the four screws and washers that attach the transmitter to the support bracket.

 S 024-022

 (4)  
Remove the pressure sensor.

 S 214-061

 (5)
Inspect the pressure sensing tube drain hole for obstructions.

 S 034-009

 (6)  
Put a cover on the open pressure sensing tube to keep out unwanted objects.


 TASK 36-21-02-404-010
 3.  Install the Bleed Air Pressure Sensor (Fig. 401)_____________________________________
 A. Consumable Materials
 (1)  
G00095 Detector - Leak, Leak-Tek (160X)

 B.
References

 (1)  
AMM 24-22-00/201, Manual Control

 (2)  
AMM 27-81-00/201, Leading Edge Flap System


 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 36-21-02
 ALL  ú ú 15 Page 403 ú Feb 18/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

 (3)  
AMM 36-00-00/201, Pneumatic System

 (4)  
AMM 71-00-00/201, Power Plant

 (5)  
AIPC 36-21-02, Fig. 1


 C. Access
 (1)  
Location Zone
 452 Engine 1 - Right Upper Half Strut
 462 Engine 2 - Right Upper Half Strut
 472 Engine 3 - Left Upper Half Strut
 482 Engine 4 - Left Upper Half Strut


 (2)  
Access Panel
 521AB Left Access Panel, Lower Inboard Nacelle
 521AB Left Access Panel, Lower Skin Leading Edge
 621AB Right Access Panel, Lower Inboard Nacelle
 631AB Right Access Panel, Lower Skin Leading Edge

 

 D. Install the Sensor
 S 434-011
 (1)  
Remove the cover from the pressure sensing tube.

 S 424-012

 (2)  
Put the sensor in the support bracket.

 (a)  
Use the four screws and washers to attach the support bracket.


 NOTE: The screws go in the nutplates.
____
 S 434-013
 (3)  
Connect the pressure sensing tube.

 (a)  
Tighten the tube nut.


 S 434-014
 (4)  
Connect the electrical connector to the transmitter:

 (a)  
Engine 1 - DX846 BLEED PRESSURE SENSOR

 (b)  
Engine 2 - DX847 BLEED PRESSURE SENSOR

 (c)  
Engine 3 - DX994 BLEED PRESSURE SENSOR

 (d)  
Engine 4 - DX995 BLEED PRESSURE SENSOR


 S 864-056
 (5)  
Remove the DO-NOT-CLOSE tag and close the applicable circuit breaker.

 (a)  
P6 Main Power Distribution Panel
 1) 6H32, ENG 1 AIR SUPPLY CONT
 
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本文链接地址:747-400 AMM 飞机维护手册 气动系统 PNEUMATIC SYSTEM(162)