S 328-008-N00

 (4)  
Do the steps that follow to install the inserts in the boss thread.

 (a)  
Install the insert in the inserting tool.

 NOTE: Use this Insert: 1191-9TN-0500, Heli-Coil Products
____
 Division/Mite Corporation.

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
(b)  
Put the end of the inserting tool in the boss threads.

 (c)  
Turn the handle of the inserting tool clockwise until the top of the insert is 3/4 to 1-1/2 pitch below the face of the boss.

 NOTE: You can remove the insert with the extracting tool.
____
 (d)  
Use long nose pliers to break off the insert tang.

 G.  
Put the Airplane Back to Its Usual Condition

 S 418-009-N00 WARNING: OBEY THE INSTRUCTIONS IN THE PROCEDURE TO CLOSE THE THRUST
_______ REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.
 (1)  
Close the thrust reverser (AMM 78-31-00/201).
 S 418-010-N00

 (2)  
Close the core cowl panel (AMM 71-11-06/201).
 S 418-011-N00

 (3)  
Close the fan cowl panel (AMM 71-11-04/201).
 S 448-012-N00

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

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
TURBINE SECTION - DESCRIPTION AND OPERATION
___________________________________________
 1.  General
_______
 A.  The turbine section consists of the turbine nozzle, high pressure turbine (HPT), low pressure turbine (LPT), and turbine exhaust case. Reaction to the combustion gases passing through the turbines, causes the turbines to rotate and drive their respective compressors.
 2.  Turbine Nozzle (Fig. 1)
______________
 A.  The turbine nozzle is located in the rear internal portion of the diffuser case and contains the inner combustion chamber, the vane cluster of the 1st-stage HPT, and the cooling duct of the 1st-stage HPT (blade).
 B.  The inner combustion chamber (liner) is fabricated from rolled ring sections of nickel alloy welded together to form the inner diameter portion of the combustion chamber. The forward section (lip) fits into the inner (bulkhead) section of the outer combustion chamber (liner), which forms the complete burner or combustion chamber. A slip joint seal provides the forward fit of the inner liner to the outer liner. The inner liner is a short double pass flow type liner for efficient and even airflow and film cooling. The inner surfaces, which are exposed to combustion gases, are coated with a magnesium zirconate material as a thermal barrier protection.
 C.  The vane clusters of the 1st-stage HPC are assembled to form a ring of vanes positioned at the rear of the combustion chamber between the inner and outer combustion liners. The cluster assembly consists of 17 clustered vanes with two vanes per cluster for a total of 34 vanes. The nickel cobalt alloy vanes are hollow with internal baffles and cooling holes which allow boundary air, from the diffuser case, to be directly distributed through the vane and over the exterior of the airfoil to reduce metal temperature. Sheet metal seals between adjacent vane cluster platforms reduce gaspath leakage and ensure adequate cooling airflow.
 D.  The cooling duct of the 1st-stage HPT (blade) consists of a cast case and cooling air nozzle with honeycomb nozzle seals. The cast case is attached to the rear of the inner combustion chamber and the inner diameter wall of the diffuser case. The cooling duct is the main structural support for the ring of 1st-stage vane clusters and inner combustion chamber (liner) which are retained by a flange on the rear outer diameter of the duct case. The cooling air nozzles are sealed by two honeycomb seal lands that align with knife-edge seals on the 1st-stage HPT rotor.
　
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