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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
TURBINE EXHAUST CASE - INSPECTION/CHECK
_______________________________________
 1.  General_______
 A.  This procedure gives tasks to examine the external surface (par. 2) and the gaspath area (par. 3) of the turbine exhaust case. These tasks include the continue-in-service limits.
 B.  The turbine exhaust case is attached to the external rear flange of the low pressure turbine (LPT) case.
 C.  You can remove the turbine sleeve and plug to get access to the external surface of the turbine exhaust case and the gaspath area.
 TASK 72-54-01-206-001-N00
 2.  Turbine Exhaust Case External Inspection (Fig. 601)________________________________________
 A.  References
 (1)  
AMM 71-11-06/201, Core Cowl Panels

 (2)  
AMM 78-11-02/401, Turbine Exhaust Plug

 B.  
Access

 (1)  
Location Zone
 412 Engine 1 - Turbine Exhaust Case
 422 Engine 2 - Turbine Exhaust Case
 432 Engine 3 - Turbine Exhaust Case
 442 Engine 4 - Turbine Exhaust Case

 (2)  
Access Panel
 417 and 418 Core Cowl Panels - Engine 1
 427 and 428 Core Cowl Panels - Engine 2
 437 and 438 Core Cowl Panels - Engine 3
 447 and 448 Core Cowl Panels - Engine 4

 C.  
Procedure

 S 016-002-N00
 (1)  
Open the core cowl panels (AMM 71-11-06/201).

 S 016-003-N00

 (2)  
Remove the turbine exhaust plug (AMM 78-11-02/401).

 S 216-004-N00

 (3)  
Use the conditions in table 601 when you examine these areas of the turbine exhaust case for damage and cracks:

 NOTE: Get the regular time inspection that is referred to in the
____ table from the Maintenance Planning Document. The decreased time inspection is set at half of that value. These times can be adjusted if data collected by persons recommends it and the local regulatory agency permits it.
 (a)  The rail flanges R and S
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////
SEE B FLANGE T1 (EXHAUST PLUG REMOVED)
SEE CSEEA E
12 O-CLOCK SLOT (RACE TRACK) SEE D
RADIAL CRACK TO THE FLANGE O.D.
FLANGE PCRACK FROM A HOLE THAT GOES THROUGH THE FLANGE FLANGE R
FLANGE S (EXHAUST FLANGE T
FWD SLEEVE
REMOVED)
CIRCUMFERENTIAL
A
CRACK
ENGINE MOUNT 
HOLE AND BUSHING  RADIAL 
RAIL 
CRACK 
FILLET  BUSHING 
RADIUS  SEE  C  FILLET  HOLE 
RADIUS 

CIRCUMFERENTIAL CRACK IN THE FILLET RADIUS
ATTACHMENT AREA FOR THE ENGINE MOUNT RAIL SECTION
B
(EXAMPLE - FLANGES R AND S) ATTACHMENT BUSHING
C FOR GROUND HANDLING
D
Turbine Exhaust Case Exterior Inspection Figure 601 (Sheet 1)
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
FWD
A
SEE F
A
E

FILLET
RADIUS

FLANGE T
A-A

FILLET RADIUS FLANGE P
FILLET
RADIUS
RADIAL CRACK
FROM BOLT

FILLET RADIUS
RADIAL CRACK
FROM FLANGE O.D.

FLANGE T SECTION
F L-A0615
Turbine Exhaust Case Exterior Inspection
Figure 601 (Sheet 2)

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