(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 in the trailing edge that are
more than 0.40 inch
(10.16 mm) from the inner and the outer
platforms
Permitted lengths: 0.09 inch (2.29 mm) - all 0.50 inch (12.7 mm) - two on each
vane
0.75 inch (19.05 mm) - one on each vane
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).
(c) Examine the inner and outer platforms on the 2nd-stage HPT turbine nozzle for the
conditions that follow:
Condition Maximum Serviceable Limit
Cracks in the platform area between
the vanes
Cracks 0.150 inch (3.81 mm) in length are permitted with no quantity limit. Two
cracks 0.60 inch (15.24 mm) in length are permitted on each platform segment if
the cracks are at least 0.30 inch (7.62 mm) apart. Refer to the
Continue-In-Operation Limits.
767
AIRCRAFT MAINTENANCE MANUAL
CF6-80A SERIES ENGINES
72-00-00
NoC
Page 618
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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