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 A.  The No. 3 bearing is a roller type bearing with a one piece inner and one piece outer race. The individual rollers are positioned to the inner race by a retainer device.
 B.  The No. 3 bearing compartment consists of the carbon seal assembly (spring loaded) on the forward side, the bearing housing, and the carbon seal assembly (spring loaded) on the aft side. The forward and aft carbon seal assemblies are bolted to the bearing housing which is attached to the inner rear flange of the diffuser case.
 C.  The carbon seal assemblies form the compartment oil sump. The nozzle which supplies oil to the bearing and seals is attached to the forward seal assembly.
 D.  The bearing compartment is provided with a heat shield duct which is supplied with precooled air from the 12th-stage HPC. For more information on cooling of the No. 3 bearing compartment, refer to Engine Bearing Cooling System - Description and Operation (AMM 75-22-00/001).
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 72-40-00
 ALL  ú ú N01 Page 3 ú Jun 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
DIFFUSER CASE ASSEMBLY - APPROVED REPAIRS
_________________________________________
 1.  General
_______
 A.  This procedure gives instructions when you repair the thread bosses on the diffuser case.
 B.  Three boss threads are repaired in this procedure. They are the AP8 borescope access port, the AP9 borescope access port, and the immersion thermocouple port.
 TASK 72-41-02-308-013-N00
 2.  Diffuser Case Assembly - Approved Repairs
_________________________________________
 A.  General
 (1)  
Do this repair after you repair the boss threads with a tap if this condition does not occur:

 (a)  
There are a minimum of four full threads which are not less than 0.350 inch (8.890 mm) from the surface A (Fig. 801).

 (2)  
It is not necessary to machine the inner counterbore when you do this repair.

 (3)  
When the engine is disassembled sufficiently to give acces to the inner surface of the diffuser case, then you must machine the counterbore.

 B.  
Equipment

 (1)  
Insert Installation Tool - 535-9, Heli-Coil
 Products Division/Mite Corporation: Danbury
 Connecticut 06810.

 (2)  
Insert Extracting Tool - 1227-16, Heli-Coil
 Products Division/Mite Corporation

 (3)  
Thread Plug Gage - 1694-9, Heli-Coil
 Products Division/Mite Corporation

 (4)  
Tap - 38193-9, Heli-Coil Products

 (5)  
Bottoming Tap - 43193-9, Heli-Coil Products
 Division/Mite Corporation.

 (6)  
Tap Guide, PWA 81439

 (7)  
Reamer Guide, PWA 81441

 (8)  
Special Reamer, PWA 81442

 (9)  
Special Reamer, PWA 81443

 C.  
References

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

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

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

 D.  
Access

 (1)  
Location Zone
 412 Engine 1 - LPC Intermediate Case
 422 Engine 2 - LPC Intermediate Case
 432 Engine 3 - LPC Intermediate Case
 442 Engine 4 - LPC Intermediate Case

 

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 72-41-02
 ALL  ú ú N01 Page 801 ú Feb 10/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
(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
　
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