(6)
Apply the leak detector to the tube connection.
S 794-016
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
36-21-02
ALL ú ú 11 Page 404 ú Oct 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
S 794-062
(7)
Do method 1 or method 2 to apply pressurized air to the pressure sensor.
(a)
METHOD 1; Dry motor the applicable engine (AMM 71-00-00/201).
(b)
METHOD 2; Pressurize the pneumatic system upstream of the PRSOV (AMM 36-00-00/201).
S 794-066
(8)
Examine the pressure sensor installation for leakage.
S 864-064
(9)
Release the pressure in the pneumatic system (AMM 36-00-00/201).
S 364-065
(10)
If there is leakage, repair the cause of the leakage.
E.
Put the Airplane to Its Usual Condition
S 414-023
WARNING: YOU MUST CAREFULLY DO THE STEPS IN THE TASK BELOW TO REMOVE THE
_______ LE FLAP SAFETY LOCKS. THE LE FLAPS CAN MOVE QUICKLY IF YOU DO NOT DO THE STEPS CORRECTLY. THIS CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
(1)
Do this task: "Safety Lock Removal and Leading Edge Flap
Activation" (AMM 27-81-00/201).
(2)
Do this task: "Leading Edge Flap Retraction: (AMM 27-81-00/201).
S 864-020
(3)
Remove the electrical power if it is not necessary
(AMM 24-22-00/201).
S 864-058
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
36-21-02
ALL ú ú 01 Page 405 ú Oct 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
BLEED AIR OVERPRESSURE SWITCH - REMOVAL/INSTALLATION
____________________________________________________
1. General_______
A. This procedure contains two tasks. The first task removes the bleed air overpressure switch. The second task installs the bleed air overpressure switch.
B. The switch is installed on the wing rib at the forward inboard side of each strut-wing interface. It is necessary to extend the leading edge flaps to get access to the switch.
TASK 36-21-03-004-001
2. Remove the Bleed Air Overpressure Switch (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 36-21-03, Fig. 1
B.
Access
(1)
Location Zones
452 System 1 - Right Upper Half Strut
462 System 2 - Right Upper Half Strut
472 System 3 - Left Upper Half Strut
482 System 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 Switch
S 864-002
(1) Supply electrical power (AMM 24-22-00/201).
S 014-003
WARNING: MAKE SURE THE SAFETY LOCKS FOR THE LEADING EDGE FLAPS ARE
_______ INSTALLED BEFORE YOU DO WORK ADJACENT TO THE LEADING EDGE FLAPS. OPERATION OF THE LEADING EDGE FLAPS CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
MAKE SURE THERE ARE NO PERSONS OR EQUIPMENT NEAR THE LE AND TE FLAPS AND THE FLAP DRIVE MECHANISMS BEFORE YOU MOVE THE FLAP CONTROL LEVER. WHEN YOU MOVE THE CONTROL LEVER WITH THE HYDRAULIC POWER REMOVED, THE ELECTRICAL POWER CAN MOVE THE FLAPS AND CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
(2) Extend and lock the leading edge flaps (AMM 27-81-00/201).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機維護手冊 氣動系統 PNEUMATIC SYSTEM(163)
