78-11-00
ALL ú ú C01 Page 610 ú Mar 15/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
S 226-004-C00
(3) Examine the turbine exhaust plug.
(a)
Remove the turbine exhaust plug (AMM 78-11-02/401).
(b)
Examine the plug stiffener (1, Fig. 607). 1) Examine for cracks. a) See SRM 54-40-02. 2) Examine for nicks, scratches, and gouges. a) Nicks, scratches, or gouges up to .50 inches (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) See SRM 54-40-02. 4) Examine for holes and punctures. a) Repair all holes with a weld repair (CMM 78-11-13). 5) Examine for missing fasteners. a) A total of four fasteners can be missing if the missing fasteners are separated by at least 60 degrees.
b) Fasteners that are found to be missing must be replaced no later than the next C-Check.
NOTE: The fastener holes must be examined for
____ fatique cracking prior to the fasteners being replaced.
(c) Examine tail ring and aft cone (2,3, Fig. 607).
1) Examine for cracks. a) Remove edge cracks as shown in Figure 604. b) Circumferential cracks that are 0.50 inches (12.7 mm)
long or less and longitudinal cracks that are 2.5 inches (63.5 mm) long or less are permitted if you use the following restrictions.
1. Make sure the cracks are more than
_
1.0 inches (25.4 mm) from the aft edge of the tail ring.
a. Remove edge cracks as shown in Figure 604.
_
2. Make sure the cracks are more than
_
3.0 inches (76.2 mm) from all other edges.
a. Remove edge cracks as shown in Figure 604.
_
3.
Make sure that the distance between two cracks or a
_ crack and other damage is 3.0 inches (76.2 mm) or more.
4.
The crack must be stop drilled with a
_
0.190 inch (5 mm) diameter drill bit.
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78-11-00
ALL ú ú C01 Page 611 ú Nov 15/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
5.
A maximum of four cracks are permitted.
_
6.
Cracks must be examined at 500 flight hour
_ intervals until the tail ring or aft cone is replaced or repaired.
a. If the crack becomes longer after stop
_ drilling but is still less than 2.5 inches in length, stop drill the crack again.
b. If the crack becomes larger than 2.5 inches,
_ repair or replace the exhuast plug in 24 hours or less.
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. 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).
(d) Examine the forward cone (4, Fig. 607).
1) Examine for cracks.
a) Examine the weldments.
1. No cracks are permitted.
_ b) Remove edge cracks as shown in Figure 604. c) Cracks that are 0.50 inch (12.7 mm) or less are
permitted if you use the following restrictions.
1. Make sure the cracks are more than
_
3.0 inches (76.2 mm) from any edge.
2.
Make sure that the distance between two cracks or a
_ crack and other damage is 3.0 inches (76.2 mm) or more.
3.
The crack must be stop drilled with a
_
0.190 inch (5 mm) diameter drill bit.
4.
Only four cracks are permitted.
_
5.
Cracks must be examined at 125 flight hour
_ intervals until the forward cone is replaced or repaired.
a.
If the crack becomes longer after stop
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