(Continued)
Condition Maximum Serviceable Limit
Nicks and scratches Permitted if less than 0.025 inch (0.64 mm) in depth, if the
high metal has been removed. Refer to the
Continue-In-Operation Limits.
Cracks from the bolt holes in the mounting flanges The cracks must be radially outward, radially inward cracks
are not permitted. Four bolt holes with cracks are permitted.
Cracked bolt holes must be separated by at least five bolt
holes that are not cracked. Refer to the
Continue-In-Operation Limits.
(b) Examine the vane airfoil on the 2nd-stage HPT nozzle for the conditions that follow
(Figure 615):
Condition Maximum Serviceable Limit
Axial cracks Permitted lengths:
in the 0.09 inch (2.29 mm) - all
trailing edge 0.50 inch (12.7 mm) - two on each vane
that are more than 0.40 inch 0.75 inch (19.05 mm) - one on each vane
(10.16 mm) from the inner and the outer platforms All the cracks must be 0.25 inch (6.35 mm) apart.
Cracks in the trailing edge that are less than 0.40 inch
(10.16 mm) from the inner and the outer platforms
These cracks are permitted if the do not extend more than
1.0 inch (25.4 mm) in front of the aft edge. Refer to the
Continue-In-Operation Limits.
Axial cracks in the leading edge Cracks that do not break the surface layer are permitted.
Two cracks in each segment are permitted, if less then 0.20
inch (5.1 mm) long. One crack that is less then 0.30 inch
(7.62 mm) long is permitted in each segment. Refer to the
Continue-In-Operation Limits.
Cracks in the concave surfaces Two cracks less than 1.50 inch (38.1 mm) in length are
permitted. Refer to the Continue-In-Operation Limits.
Cracks in the convex surfaces Two cracks less than 1.00 inch (25.4 mm) in length are
permitted. Refer to the Continue-In-Operation Limits.
Dents, nicks, scores, and scratches All of this type of damage is permitted if it is less than 0.25
inch (6.4 mm) in length. Refer to the Continue-In- Operation
Limits.
Bowing of the trailing edge This type of damage is permitted, if the bowing is less than
0.060 inch (1.52 mm) from the initial edge. Refer to the
Continue-In-Operation Limits.
Burns on the convex and the concave sides This damage is permitted if the area is less then 1.0 square
inch (6.45 square cm). The burn must not make a hole fully
through the metal. Refer to the Continue-In-Operation Limits.
Burns and spalls on the leading edge This damage is permitted if it is less than 1.0 inch (25 mm) in
radial length, and 0.25 inch (6.4 mm) in width. The damage
must not be fully through the airfoil. Refer to the
Continue-In-Operation Limits.
Material that is gone from the trailing edge Permitted, if the total missing area on each airfoil is not more
than 0.25 inch by 0.25 inch (6.3 mm by 6.3 mm).
767
AIRCRAFT MAINTENANCE MANUAL
CF6-80A SERIES ENGINES
72-00-00
NoC
Page 698
D633T1B7 Aug 22/2017
ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details
EFFECTIVITY
ABX 001-007, 011, 012, 016-019, 021, 022, 025, 101,
109, 114, 115, 314-999
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