b.
If the crack does not get longer after stop
_ drilling, repair the crack immediately.
_ drilling, repair the crack at the next "C" check.
2) Examine for nicks, scratches, or gouges. a) Nicks, scratches, or gouges up to 2.0 inches (50.8 mm) in length or diameter are permitted after cleanup.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
b) Remove the damage as shown in Figure 605. 3) Examine for dents and wrinkles. a) Dents, skin wrinkles, heat depressions, and skin waviness are permitted as shown in Figure 606. b) Dents are not permitted closer than 2.0 inches
(50.8 mm) to a panel edge. c) Dents with cracks, sharp creases, or holes are not permitted.
4) Examine for holes or punctures. a) Repair all holes with a weld repair (CMM 78-11-13).
(e) Examine the plug assembly engine attach ring (5, Fig. 607).
1) Examine for cracks. a) Remove edge cracks as shown in Figure 604. b) Other cracks are not permitted.
2) Examine for nicks, scratches and gouges. a) Nicks, scratches, or gouges up to .50 inch (12.7 mm) in length or diameter are permitted after cleanup. b) Remove nicks, scratches, or gouges as shown in Figure 605. 3) Examine for dents and wrinkles. a) Dents and wrinkles are not permitted. 4) Examine for holes and punctures. a) Holes and punctures are not permitted.
S 446-006-C00
(4) Put back the turbine exhaust system back to its usual configuration.
(a)
Make sure you repair any damage to the primary sleeve assembly and the turbine exhaust plug assembly (SRM 54-40-02).
(b)
Install the turbine exhaust plug (AMM 78-11-02/401). 1) Make sure that all fasteners are present and tight.
(c)
Install the primary sleeve assembly (AMM 78-11-01/401). 1) Make sure that all fasteners are present and tight.
S 446-007-C00
(5) Do the activation procedure for the thrust reverser for ground maintenance (AMM 78-31-00/201).
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PRIMARY SLEEVE ASSEMBLY - REMOVAL/INSTALLATION
______________________________________________
1. General
_______
A. This procedure has two tasks. The first task is for the removal of the Primary Sleeve Assembly. The second task is for the installation of the Primary Sleeve Assembly.
TASK 78-11-01-004-017-C00
2. Remove the Primary Sleeve Assembly
__________________________________
A. Equipment
(1)
C78009-1 - Primary Exhaust Nozzle and Plug - Remove and Install Tool
B.
References
(1)
AMM 71-11-02/201, Fan Cowl Panels
(2)
AMM 78-31-00/201, Thrust Reverser System
C.
Access
(1)
Location Zones
506 Left Engine - Turbine Exhaust Area
606 Right Engine - Turbine Exhaust Area
D.
Procedure (Fig. 401)
S 044-003-C00
WARNING: DO THE DEACTIVATION PROCEDURE TO PREVENT THE OPERATION OF THE
_______ THRUST REVERSERS. THE ACCIDENTAL OPERATION OF THE THRUST REVERSER CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
(1)
Do the deactivation procedure for the thrust reverser for ground maintenance (AMM 78-31-00/201).
S 014-002-C00
(2)
Open the fan cowl panels (AMM 71-11-02/201).
S 014-004-C00
WARNING: OBEY THE INSTRUCTIONS IN THE PROCEDURE TO OPEN THE THRUST
_______ REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.
(3) Open the thrust reverser (AMM 78-31-00/201).
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