2......…........…...................................…...........….....…........1
B. References
(1)
AMM 27-81-00/201, Leading Edge Flaps
(2)
AMM 30-11-00/501, Wing Thermal Anti-Ice System
(3)
SSM 30-11-01
(4)
WDM 30-11-11
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
C. Access
(1) Location Zone 531 Leading Edge to Front Spar, Left Wing at Outboard Engine 631 Leading Edge to Front Spar, Right Wing at Outboard Engine
D. Procedure
S 424-009
(1) Install the wing anti-ice valve:
(a)
Install 2 new seals (6) and make sure that they stay in position.
(b)
Move the valve (3) into its position.
(c)
Support the valve (3) and install the V-band coupling (5) over the duct flanges.
(d)
Install the nuts (4) on the V-band coupling T-bolt.
(e)
Tighten the nuts (4).
(f)
Connect the electrical connector DV152 (left) or DV153 (right) (1) to the valve (3).
(g)
Connect the bonding jumpers (2) to the valve (3).
NOTE: Some valves have only one bonding jumper.
____
S 864-017
(2) Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) P6, Main Power Distribution Panel
1) 6C8, WING TAI VLV
2) 6C9, WING TAI CONT
S 714-012
(3)
Do this task: "Operational Test - Wing Thermal Anti-Ice System" (AMM 30-11-00/501).
(4)
Remove the leading edge flap safety locks (AMM 27-81-00/201).
(5)
Retract the leading edge flaps (AMM 27-81-00/201).
(6)
Remove electrical power (AMM 24-22-00/201).
S 094-018
S 864-015
S 864-016
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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2.
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747-400 MAINTENANCE MANUAL
ENGINE INLET THERMAL ANTI-ICE SYSTEM - DESCRIPTION AND OPERATION
________________________________________________________________
General (Fig. 1)
_______
A. The engine inlet thermal anti-ice (TAI) system prevents ice formation on the four engine inlet cowls. Heated air supplied by the engine bleed air system is sprayed against the inner flow surface of the inlet cowl. The flow of heated air is regulated by a control valve in the engine strut.
B. A duct running forward through the engine strut connects the control valve to a D-ring spray manifold in the inlet cowl leading edge. Hot bleed air flows from spray holes in the manifold and is discharged overboard through an exhaust port at the bottom rear of the inlet cowl.
C. The engine inlet anti-ice system for each engine consists of a control switch, system relays, an anti-ice control valve, pneumatic ducting, an nose cowl pressure switch, and an engine cowl overheat switch. The system is powered by 28 volts dc from the APU battery bus through circuit breakers on the P6 panel.
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本文鏈接地址：747-400 AMM 飛機維護手冊 防冰和排雨 ICE AND RAIN PROTECTION(12)
