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 D.  There are four sensing probes installed between the exhaust case struts. Two probes measure the gaspath total temperature (TT4.95) and the other two measure gaspath total temperature (TT4.95) and gaspath total pressure (PT4.95). For additional information on the engine pressure ratio (PT4.95) probes and the exhaust gas temperature (TT4.95) thermocouple probes, refer to 77-11-00/001 and 77-21-00/001 respectively.
 E.  The inner cone portion of the case provides support for the No. 4 bearing, with load forces transmitted from the bearing, through the struts, to the outer case structure. The oil pressure and scavenge tubes of the No. 4 bearing are routed within case struts at the 1:30 and 2:30 o'clock locations respectively.
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 ALL  ú ú N01 Page 10 ú Feb 10/93
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
6TH-STAGE LPT BLADE - INSPECTION/CHECK
______________________________________
 1.  General
_______
 A.  This procedure gives instructions for the inspection of the 6th-stage LPT blades.
 B.  The 6th-stage LPT blades are the last stage of blades of the low pressure turbine.
 C.  You can look forward through the turbine exhaust area to see the
 6th-stage LPT blades.

 TASK 72-53-01-206-001-N00
 2.  6th-Stage LPT Blade Inspection (Fig. 601)
______________________________
 A.  Standard Tools and Equipment
 (1)  
Light - White, Fluorescent

 B.  
References

 (1)  
IPC 72-53-01 Fig. 1

 C.  
Access

 (1)  
Location Zone
 412 Engine 1 - LPT
 422 Engine 2 - LPT
 432 Engine 3 - LPT
 442 Engine 4 - LPT

 D.  
Procedure

 S 226-002-N00
 (1)  
With a fluorescent light, look forward through the turbine exhaust area to examine the 6th-stage LPT blades for damage.

 (a)  
Area A 1) No damage or cracks are permitted.

 (b)  
Area B 1) You can permit nicks that are not blend repaired, if they are no more than 0.015 inch (0.381 mm) in depth. 2) You can permit high metal, which is caused by nicks, if it

 is lifted no more than 0.030 inch (0.762 mm). 3) You cannot permit cracks.

 (c)  
Area C 1) You cannot permit damage or cracks.

 (d)  
Area D 1) You can permit nicks and dents that are not blend repaired,

 if they are no more than 0.020 inch (0.508 mm) in depth. 2) You cannot permit cracks.
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 ALL  ú ú N01 Page 601 ú Feb 10/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////

6th-Stage LPT Blade Inspection Figure 601
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 72-53-01
 ALL  ú ú N01 Page 602 ú Jun 10/88
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
6TH-STAGE LPT VANE - INSPECTION/CHECK
_____________________________________
 1.  General
_______
 A.  This procedure gives instructions for the inspection of the 6th-stage LPT vanes.
 B.  The 6th-stage LPT vanes are the last stage of vanes of the low pressure turbine.
 C.  You can look forward through the turbine exhaust area and between 6th-stage LPT blades to see the 6th-stage LPT vanes.
 TASK 72-53-02-206-001-N00
 2.  6th-Stage LPT Vane Inspection (Fig. 601)
_____________________________
 A.  Standard Tools and Equipment
 (1)  
Light - White, Fluorescent

 B.  
References

 (1)  
IPC 72-53-01 Fig. 1

 C.  
Access

 (1)  
　
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