(a)
If there is leakage, it must be repaired.
S 714-021
(11)
Look at the EICAS MAINT PAGE for the 21 ECS.
(a)
Make sure the left and the right DUCT PRESSURE indications are approximately equal.
E.
Put the Airplane to Its Usual Condition
S 864-022
(1)
Release the pressure in the pneumatic system (AMM 36-00-00/201).
S 414-023
(2)
Close the access door (AMM 06-09-03/201).
(3)
Remove electrical power if it is not necessary (AMM 24-22-00/201).
S 864-024
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
36-21-01
ALL ú ú 01 Page 405 ú Feb 10/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
BLEED AIR PRESSURE SENSOR - REMOVAL/INSTALLATION
________________________________________________
1. General________
A. This procedure contains two tasks. The first task removes the bleed air pressure sensor. The second task installs the bleed air pressure sensor.
B. There is a bleed air pressure sensor installed on the wing rib on the forward inboard side of each strut/wing interface. It is necessary to extend the leading edge flaps to get access to the sensor.
TASK 36-21-02-004-001
2. Remove the Bleed Air Pressure Sensor (Fig. 401)____________________________________
A. References
(1)
AMM 24-22-00/201, Manual Control
(2)
AMM 27-81-00/201, Leading Edge Flap System
(3)
AMM 36-00-00/201, Pneumatic System
(4)
AIPC 36-21-02, Fig. 1
B.
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
C.
Prepare to Remove the Sensor
S 864-002
(1)
Supply electrical power (AMM 24-22-00/201).
(2)
Do this task: Leading Edge Flap Extension (AMM 27-81-00/201).
S 864-057
S 014-003
WARNING: YOU MUST CAREFULLY DO THE STEPS IN THE TASK BELOW TO INSTALL
_______ THE LE FLAP SAFETY LOCKS. THE LE FLAPS CAN MOVE QUICKLY IF YOU DO NOT INSTALL THE SAFETY LOCKS CORRECTLY. THIS CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
(3)
Do this task: Extended Leading Edge Flap Deactivation and Safety Lock Installation (AMM 27-81-00/201).
(4)
Release the pressure in the pneumatic system (AMM 36-00-00/201).
S 864-004
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
36-21-02
ALL ú ú 01 Page 401 ú Oct 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
BLEED AIR
BLEED AIR
OVERPRESSURE
PRESSURE
SWITCH
SENSOR
ENGINE 3 WING RIBBLEED AIR
PRESSURE
SENSOR
DRAIN HOLES ENGINE 4
SEE A
BLEED AIR
PRESSURE
SENSOR
SEE B
ELECTRICAL PRESSURE
CONNECTOR SENSING TUBE
SCREW
SUPPORT WASHER
FWD (4 LOCATIONS) BRACKET
ENGINE 3 BLEED AIR PRESSURE SENSOR (ENGINE 2 BLEED AIR PRESSURE SENSOR IS OPPOSITE)
A
BLEED AIR SCREW PRESSURE WASHER SENSOR (4 LOCATIONS) PRESSURE
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本文鏈接地址：747-400 AMM 飛機維護手冊 氣動系統(tǒng) PNEUMATIC SYSTEM(161)
