adjuster assembly to the lever arm on the LPT valve. 2) Align the hole in the lever arm with the rigging pin hole in the LPT valve.
 NOTE: Permit no distance between the lever arm and idler
____ arm on the HPT valve while you adjust the system.
 3)  Install the rigging pin through the lever arm and into the rigging pin hole in the LPT valve.
 4)  Remove the lockwire and loosen the two jamnuts from the rod ends of the adjuster assembly.
 5)  Turn the adjuster and align the bolt holes of the rod end of the adjuster assembly and the lever arm.
 NOTE: Make sure you can see the threads of both rod ends
____ through the inspection holes in the adjuster.
 6)  Lubricate the bolt with engine oil.
 7)  Attach the rod end of the adjuster assembly to the lever arm on the LPT valve with the bolt and the nut.
 NOTE: Install the bolt from the inner side of the lever
____
 arm.

 a) Tighten the nut to 36-40 pound-inches (4.1-4.5 newton-meters). 8) Tighten the jamnuts to 14-16 pound-inches (1.6-1.8 newton-meters). 9) Safety the jamnuts with lockwire.
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 75-24-00
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
CAUTION: MAKE SURE THE THREE RIGGING PINS AND THE POSITIONING BOLT
_______ ARE REMOVED FROM THE ENGINE. IF THE RIGGING PINS OR THE POSITIONING BOLT ARE NOT REMOVED, DAMAGE TO THE ENGINE CAN OCCUR.
 (f)  Remove the three rigging pins and the positioning bolt from the engine.
 H. Return the Aircraft to Its Usual Condition
 S 415-025-N00
 WARNING: OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU CLOSE THE
_______ THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
 (1)  
Close the right thrust reverser (AMM 78-31-00/201).

 S 415-022-N00

 (2)  
Close the right core cowl panel (AMM 71-11-06/201).

 S 415-023-N00

 (3)  
Close the right fan cowl panel (AMM 71-11-04/201).

 S 445-024-N00

 (4)  
Do the activation prcoedure for the thrust reverser
 (AMM 78-31-00/201).

 S 715-050-N00

 (5)  
Do the test of the TCC control cable that is shown in the Power Plant Test Reference Table (AMM 71-00-00/501).

 TASK 75-24-00-835-035-N00
 3. Turbine Case Cooling System Adjustment (Complete Rig Procedure) (Fig. 501)
_______________________________________________________________
 A. Special Tools and Equipment
 (1)  PWA 85465 - Rig Pin (3 required), Pratt & Whitney, Commercial Products Division, 400 Main Street, East Hartford, CT 06108
 NOTE: The rigging pin is contained in the PWA 85675 Rigging
____
 Pin Kit.

 B. Standard Tools and Equipment
 (1)  
Bolt - Positioning, Standard Hex Head Bolt No. 8-32, 1.5 inch (38 mm) minimum thread length.

 C.
Consumable Materials

 (1)  
D00390 Oil - Engine

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
(2)  
G02334 Lockwire - AS3214-02

 D.
References

 (1)  
AMM 71-00-00/501, Power Plant

 (2)  
AMM 71-11-04/201, Fan Cowl Panels

 (3)  
AMM 71-11-06/201, Core Cowl Panels

 (4)  
AMM 78-31-00/201, Thrust Reverser System

 (5)  
IPC 75-24-03 Fig. 10

 (6)  
IPC 75-24-11 Fig. 1

 E.
Access

 (1)  
Location Zone 412 Engine 1 - HPC Fwd Case to LPT Case at 2 o'clock 422 Engine 2 - HPC Fwd Case to LPT Case at 2 o'clock 432 Engine 3 - HPC Fwd Case to LPT Case at 2 o'clock 442 Engine 4 - HPC Fwd Case to LPT Case at 2 o'clock

 (2)  
Access Panel
 416 Right Thrust Reverser Half - Engine 1
　
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