(Continued)
CONDITION CONTINUE-IN-OPERATION LIMIT
Stage 1 HPT Vane inner and outer platform has material that is gone (from
cracks) or burns that go all the way through. The total damage area is less
than 0.2 sq inch (129 sq mm) on each airfoil. The total damage area on
each assembly is less than 1.0 sq inch (645 sq mm).
25 flight cycles
Stage 1 HPT Vane inner and outer platform has bulges and bowing that are
less than 20% more than the limits.
25 flight cycles
Other damage on the HPT stage 1 and stage 2 shroud (less than 20% more
damage than the maximum serviceable limit)
25 flight cycles
(b) Stage 2 HPT Nozzle
CONDITION CONTINUE-IN-OPERATION LIMIT
All HPT stage 2 nozzle damage that is less than 20% more than the
Maximum Serviceable Limits
25 flight cycles
(c) HPT Rotor Blades Concave and Convex Surfaces, Area A
CONDITION CONTINUE-IN-OPERATION LIMITS
Stage 1 blade axial cracks in area A. The crack length is less than 1/2 the
distance between adjacent rows of cooling holes
10 flight cycles
Stage 1 blade holes from a hit in the convex surface of area A. One hole
with a diameter less than the distance between three trailing edge holes
(0.10 in. [2.54 mm]). Cracks from a hole are no longer than the distance
between four trailing edge holes (0.140 inch [3.56 mm]). One hole in each
blade, five blades in each set.
10 flight cycles
Stage 1 blade radial cracks out of the film holes in area A. The cracks have
connected with the next hole but have not turned axial.
10 flight cycles
Material from both tip walls up to five stage 1 or five stage 2 blades. Less
than 0.050 inch (1.27 mm) of the tip cap can be seen. There is no material
missing from below the tip cap
Permitted, if the blades are reinspected
within 200 flight cycles.
Material from six or more stage 1 blades six or more stage 2 blades. Less
than 0.050 inch (1.27 mm) of the tip cap can be seen. There is no material
missing from below the tip cap.
10 flight cycles
Leading edge cracks or missing material, in area A, on one blade 10 flight cycles
Stage 2 HPT Rotor Blade cracks in the pressure side of the platform (no
bowing)
10 flight cycles
Stage 2 blade tip area for radial cracks more than 0.750 inch (19.05 mm) 10 flight cycles
Stage 2 blade tip area for axial cracks more than 0.500 inch (12.70 mm) 10 flight cycles
SUBTASK 72-00-00-866-091-G00
(4) The Continue-In-Operation Limits for the LPT module follow:
NOTE: Make sure that you refer to the Maximum Serviceable Limits before the
Continue-In-Operation Limits.
(a) LPT Forward Case
767
AIRCRAFT MAINTENANCE MANUAL
CF6-80A SERIES ENGINES
72-00-00
NoC
Page 657
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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