S 415-076-N00
 (2)  
If removed, install the supply and return tubes with the steps that follow:

 (a)  
Lubricate the threads of the tube nut on the return tube with engine oil.

 (b)  
Install the return tube between the tee on the return manifold and the adapter on the 2.5 bleed valve actuator. 1) Tighten the tube nuts on the return tube to 270-300

 pound-inches (30.5-33.9 newton-meters). 2) Safety the tube nuts with lockwire or safety cable and safety cable ferrule.

 (c)  
Lubricate the threads of the tube nuts on the supply tube with antigalling compound.

 (d)  
Install the supply tube between the tee on the supply manifold and the adapter on the 2.5 bleed valve actuator. 1) Tighten the tube nut at the supply manifold to 340-375

 pound-inches (38.4-42.4 newton-meters).
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2)  Tighten the tube nut at the 2.5 bleed valve actuator to 225-250 pound-inches (25.4-28.2 newton-meters).
 3)  Safety the tube nuts with lockwire or safety cable and safety cable ferrule.
 (e)  
Lubricate the threads of the bolt, which attaches the supply and return tubes together, with engine oil.

 (f)  
Install the clamp, bolt, and nut to attach the supply and return tubes. 1) Tighten the bolt to 36-40 pound-inches (4.1-4.5

 newton-meters).
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2.9 BLEED VALVE - REMOVAL/INSTALLATION
______________________________________
 1.  General
_______
 A.  This procedure gives the instructions to remove and install the right and left 2.9 bleed valves. The differences in the removal and installation instructions between the two 2.9 bleed valves are written in the procedure.
 B.  The two 2.9 bleed valves are installed on the aft case of the high pressure compressor (HPC) at the 1:00 o'clock and 10:00 o'clock positions.
 C.  You can get access to the 2.9 bleed valve through the applicable thrust reverser.
 TASK 75-32-03-004-001-N00
 2.  Remove the 2.9 Bleed Valve (Fig. 401)
__________________________
 A.  Special Tools and Equipment
 (1)  
PWA 85436 - Torque Adapter, Pratt and Whitney,
 Commercial Products Division, 400
 Main Street, East Hartford, CT
 06108

 B.  
References

 (1)
AMM 71-11-04/201, Fan Cowl Panels

 (2)
AMM 71-11-06/201, Core Cowl Panels

 (3)
AMM 78-31-00/201, Thrust Reverser System

 C.  
Access

 (1)  
Location Zone
 412 Engine 1 - HPC Aft Case 1 or 10 o'clock
 422 Engine 2 - HPC Aft Case 1 or 10 o'clock
 432 Engine 3 - HPC Aft Case 1 or 10 o'clock
 442 Engine 4 - HPC Aft Case 1 or 10 o'clock

 (2)  
Access Panel
 415 Left Thrust Reverser Half - Engine 1
 416 Right Thrust Reverser Half - Engine 1
 425 Left Thrust Reverser Half - Engine 2
 426 Right Thrust Reverser Half - Engine 2
 435 Left Thrust Reverser Half - Engine 3
 436 Right Thrust Reverser Half - Engine 3
 445 Left Thrust Reverser Half - Engine 4
 446 Right Thrust Reverser Half - Engine 4

 D.  
Prepare to Remove the 2.9 Bleed Valve

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
　
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