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 DO-NOT-CLOSE tag:
 (a) P6, Main Power Distribution Panel
 1) 6J10, NACELLE ANTI-ICE 1
 2) 6J11, NACELLE ANTI-ICE 2
 3) 6J12, NACELLE ANTI-ICE 3
 4) 6J13, NACELLE ANTI-ICE 4
 S 864-004
 (3)  Make sure that there is no pressure in the pneumatic system
 (AMM 36-00-00/201).
 S 014-005
 (4)  AIRPLANES WITH ACCESS DOOR ON THE FORWARD FAIRING;
 Open the access door on the No. 3 forward fairing of the engine
 strut.
 S 044-026
 (5)  AIRPLANES WITHOUT ACCESS DOOR ON THE FORWARD FAIRING;
 Remove No. 2 and No. 3 forward fairings of the engine strut
 (AMM 54-62-04/401).
 S 034-007
 (6)  Remove the electrical connector (3) from the applicable anti-ice
 valve (2):
 ~.....................
 | Engine 1 | DV88 |
 .......................
 | Engine 2 | DV159 |
 .......................
 | Engine 3 | DV160 |
 .......................
 | Engine 4 | DV161 |
 2............…........1
 S 024-009
 (7)  Remove the valve:
 (a) Disconnect the bonding jumper.
 (b) Disconnect the pressure sense tube (4) at the union (6).
 (c) Remove the union (5) from the valve (2).
 (d) Discard the packing (7) on the union (6).
 (e) Remove the couplings (1) which attach the valve (2) to the
 duct.
 (f) Remove the valve (2) and the seals (5).

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

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 ALL  ú ú 01 Page 403 ú Jun 18/01
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A
747-400
MAINTENANCE MANUAL

 TASK 30-21-03-404-010
 3. Engine Inlet Anti-Ice Valve Installation (Fig. 401)
________________________________________
 A. Parts ~.............................................................................. | AMM | | AIPC | ................. ............................ | FIG | ITEM | NOMENCLATURE | SUBJECT | FIG | ITEM | ................................................................................ | 401 | 1 | Coupling | 30-21-03 | 01 | 5 | | | 2 | Valve | | | 15 | | | 5 | Seal | | | 10 | | | 6 | Union | | | 50 | | | 7 | Packing | | | 60 | 2......…........…...................................…...........….....…........1
 B. References
 (1)  
AMM 24-22-00/201, Manual Control

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

 (3)  
AMM 36-11-04/201, Engine Bleed Air Pressure Regulating and Shutoff Valve

 (4)  
AMM 54-62-04/401, Forward Fairing - Removal/Installation

 (5)  
SSM 30-21-01

 (6)  
WDM 30-21-11

 C. Access
 (1)  
AIRPLANES WITH ACCESS DOOR ON THE FORWARD FAIRING;

 Location Zone 451 Engine 1 - Strut Forward Fairing, No. 3 Fairing 461 Engine 2 - Strut Forward Fairing, No. 3 Fairing 471 Engine 3 - Strut Forward Fairing, No. 3 Fairing 481 Engine 4 - Strut Forward Fairing, No. 3 Fairing

 (2)  
AIRPLANES WITHOUT ACCESS DOOR ON THE FORWARD FAIRING; Location Zone 451 Engine 1 - Strut Forward Fairing, No. 2 and No. 3 Fairings 461 Engine 2 - Strut Forward Fairing, No. 2 and No. 3 Fairings 471 Engine 3 - Strut Forward Fairing, No. 2 and No. 3 Fairings

 481 Engine 4 - Strut Forward Fairing, No. 2 and No. 3 Fairings
 D. Valve Installation
 S 424-011
 (1)  Install the valve:
 (a)  Set the anti-ice valve (2) in the duct and install the couplings (1) with the seals (5).
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 30-21-03
 ALL  ú ú 01 Page 404 ú Oct 18/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

 CAUTION: MAKE SURE THAT THE VALVE IS INSTALLED AS SPECIFIED IN THE
_______ STEP THAT FOLLOWS. IF THE VALVE IS NOT INSTALLED CORRECTLY, THE ELECTRICAL CONNECTOR CAN TOUCH THE HYDRAULIC LINE AND CASUE DAMAGE TO IT.
 (b)  
Turn the valve so that center of the electrical connector on the valve is 4.20 to 4.50 inches from the flange surface of the upper spar fitting assembly (Fig. 401). 1) Tighten the couplings to 95-110 pound-inches torque.
　
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