(c)  
Install packing (7) on each end of the union (6).

 (d)  
Install the union (6) on the valve (2).

 (e)  
Connect the pressure sense tube (4) to the union (6).

 (f)  
Connect the bonding jumper.

 S 434-012
 (2)  Install the electrical connector (3).
 E. Valve Operation and Air Leak Test
 S 864-014
 (1)  Remove the DO-NOT-CLOSE tag and close this circuit breaker for the applicable engine:
 (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 864-015
 (2)  Supply electrical power (AMM 24-22-00/201).
 S 864-024
 CAUTION: IF THE PNEUMATIC AIR IS HOT (APPROXIMATELY 350°F), DO NOT OPEN
_______ THE ENGINE INLET ANTI-ICE VALVE FOR MORE THAN 30 SECONDS. AFTER THE VALVE CLOSES, LET THE INLET COWL BECOME COOL. TOO MUCH HEAT CAN CAUSE DAMAGE TO THE INLET COWL.
 (3)  
Supply pneumatic power (AMM 36-00-00/201).

 (4)  
Manually open the PRSOV (AMM 36-11-04/201).

 S 864-018

 (5)  
Push the applicable NACELLE ANTI-ICE switch on the anti-ice/rain removal module to ON.

 S 984-017
 (a)  Make sure that the position indicator on the valve moves from CLOSED to OPEN.
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 ALL  ú ú 01 Page 405 ú Jun 18/01
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A
747-400 MAINTENANCE MANUAL
 (6)  S 794-019Make sure that there is not too much air leakage from the valve. (a) Diffuse leakage is permitted. (b) Jet blast leakage is not permitted.
 (7)  S 414-020AIRPLANES WITH ACCESS DOOR ON THE FORWARD FAIRING; Close the access door on the fairing.
 (8)  S 404-027AIRPLANES WITHOUT ACCESS DOOR ON THE FORWARD FAIRING; Install No. 2 and No. 3 forward fairings of the engine strut (AMM 54-62-04/401).
 (9)  S 864-022Remove pneumatic power (AMM 36-00-00/201).
 S 864-023

 (10) Remove electrical power (AMM 24-22-00/201).

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 ENGINE INLET ANTI-ICE NOSE COWL PRESSURE SWITCH - REMOVAL/INSTALLATION
______________________________________________________________________
 1.  General_______
 A.  There are two tasks in this subject. There is one task for removal and there is one task for installation of the engine inlet thermal anti-ice (TAI) nose cowl pressure switch.
 B.  The procedure is the same for each engine.
 TASK 30-21-04-004-001
 2.  Remove the Nose Cowl Pressure Switch (Fig. 401)____________________________________
 A.  References
 (1)  
AMM 36-00-00/201, Pneumatic System

 (2)  
AMM 54-62-04/401, Forward Fairing - Removal/Installation

 (3)  
SSM 30-21-01, SSM 30-21-02, SSM 30-21-03, SSM 30-21-04

 (4)  
WDM 30-21-11, WDM 30-21-21, WDM 30-21-31, WDM 30-21-41

 B.  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
 C.  Procedure
 S 844-002
 (1)  
Make sure that there is no pressure in the pneumatic system (AMM 36-00-00/201).

 S 864-026
　
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