D. Install the Check Valve
 S 434-012
 (1)  
Remove the covers from the ducts.

 S 424-025

 (2)  
AIRPLANES WITH 9036-5-2 CHECK VALVES;
 Do the steps that follow:

 NOTE:____The 9036-5-2 check valve does not have a flange. The flange is a separate part. See flagnote 1 (Figure 401) for the 9036-5-2 check valve.
 (a)  
Open the access panel 191ML (AMM 06-09-03/201).

 (b)  
Loosen the nuts.

 NOTE: This prevents flange warpage.
____
 (c)  
Install the O-ring in the flange.

 (d)  
Install the check valve in the flange.

 (e)  
Use the check valve wrench to tighten the check valve to 650-750 inch-pounds.

 (f)  
Tighten the nuts using hand tools only to 65-75 inch-pounds.

 (g)  
Install a lockwire from the check valve housing to a bolt on the flange.

 NOTE: This flange bolt should be installed with the head
____ below the flange. All other flange bolts should be installed with their heads above the flange.
 S 424-026
 (3)  
AIRPLANES WITHOUT 9036-5-2 CHECK VALVES;
 Do the steps that follow:

 (a)  
Install a new gasket above where the check valve will be installed.

 (b)  
Put the check valve in position.

 (c)  
Put the washers and nuts on the bolts.

 (d)  
Tighten the nuts using hand tools only to 65-75 inch-pounds.

 (4)  
Supply pressure to the pneumatic system (Ref 36-00-00/201).

 S 864-018

 (5)  
Put the switches that follow to the OPEN position:

 (a)  
The APU bleed air switch

 (b)  
The two wing ISLN switches.

 S 864-017
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747-400 MAINTENANCE MANUAL
 S 794-019
 (6)  
Examine the check valve flange for leakage:

 (a)  
A small quantity of leakage is permitted.

 (b)  
If jet blast leakage occurs, you must repair the cause of the leakage.

 E.
Put the Airplane to Its Usual Condition

 S 864-020
 (1)  
Release the pressure in the pneumatic system if it is not necessary (AMM 36-00-00/201).

 S 864-021

 (2)
Remove electrical power if it is not necessary (Ref 24-22-00/201).

 S 414-022

 (3)  
Close the access door 191ML (AMM 06-09-03/201).

 (4)  
Close the access door 193AL (Ref 06-09-03/201).

 S 414-024
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747-400
MAINTENANCE MANUAL

 ENGINE BLEED AIR PRESSURE COMPENSATOR DUCT - REMOVAL/INSTALLATION
_________________________________________________________________
 1.  General
_______
 A.  This procedure contains two tasks. The first task removes the engine bleed air pressure compensator duct. The second task installs the engine bleed air pressure compensator duct.
 B.  It is necessary to open the applicable right and left trailing edge fairing doors to get access for these tasks.
 TASK 36-11-16-004-001
 2.  Remove the Engine Bleed Air Pressure Compensator Duct (Fig. 401)
_____________________________________________________
 A.  References
 (1)  
24-22-00/201, Manual Control

 (2)  
36-00-00/201, Pneumatic System

 (3)  
36-11-04/201, Pressure Regulating and Shutoff Valve

 (4)  
AMM 54-62-00/201, Nacelle Strut Access Panels

 (5)  
AMM 54-62-02/501, Nacelle Strut Access Doors

 B.  
Access

 (1)  
Location Zone
　
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