S 416-006-N00
(6)
Close the core cowl panels (AMM 71-11-06/201).
TASK 72-54-01-206-007-N00
3. Turbine Exhaust Case Gaspath Area Inspection (Fig. 602)
____________________________________________
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
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
72-54-01
ALL ú ú N02 Page 606 ú Oct 18/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
SEE BSEE A
EXHAUST PLUG
O.D. DUCT AREA OF THE TURBINE EXHAUST CASE
A
A
EXHAUST BLADES OF THE
SLEEVE 6TH STAGE LPT
A
STRUT CRACKS STRUT
STRUT CRACKS
THROUGH THE LEADINGFILLETSTRUT OF THE TURBINE EDGERADIUSEXHAUST CASE
I.D. DUCT AREA OF THE
INNER FLANGE OF THE TURBINE EXHAUST CASE
TURBINE EXHAUST CASE
(EXHAUST PLUG REMOVED) B
AXIAL CRACK THROUGH AIRFOIL TO THE LEADING EDGE
FILLET RADIUS OF THE
STRUT I.D. AREA TO THE
WELD LINE
FLANGE T1 (REF)
RADIAL
CRACK I.D. OR O.D.
(25.4 MM) 1.0 INCH SEE C TRAILING STRUT AND TRAILING STRUT AIRFOIL EDGE CRACKS TO DUCT AREA DUCT AREA
STRUT EDGE TWO CRACKS THAT FILLET RADIUS OF
LEADING AIRFOIL TOUCH ARE A THE I.D. OR O.D
EDGE CRACKS SINGLE CRACK AREA CORD
C
RADIAL CRACK
OF THE LEADING CRACK
EDGE
FILLET RADIUS OF THE AXIAL CRACK ALONG
STRUT O.D. AREA TO THE WELD LINE
THE WELD LINE A-A
Turbine Exhaust Case Gaspath Inspection Figure 602
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
72-54-01
ALL ú ú N01 Page 607 ú Oct 10/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
C. Procedure
S 016-008-N00
(1)
Open the core cowl panels (AMM 71-11-06/201).
S 016-009-N00
(2)
Remove the turbine exhaust plug (AMM 78-11-02/401).
S 226-010-N00
(3)
Examine the struts and duct area of the turbine exhaust case for damage.
(a)
General damage - Nicks, Dents, and Cracks.
NOTE: Holes, tears, and angular dents that are a thin straight
____ line are the same as cracks. The length of a hole, tear, or a thin dent is to be added to the length of the crack. This total length is to be compared with the continue-in-service limits.
Cracks that are permitted in vanes can let hot exhaust gases flow through the vanes into the adjacent cowl area. Inspecttion of this area is recommended as part of the full inspection for continued operation.
1) The struts and duct areas of the turbine exhaust case, with some types of damage (skin bulges or depression, bulking, and distorted leading or trailing edges), can continue-in-service if these conditions occur: a) The leading and trailing edges' contours are smooth and
the crack limits are not more than those in Table 602. b) There is no skin separation from the strut stiffeners.
(b) The crack limits for the struts and duct area (of the turbine exhaust case) for regular or decreased time inspections are defined in Table 602.
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.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：747-400 AMM 飞机维护手册 发动机 ENGINE 2(112)
