CONDITION CONTINUE-IN-OPERATION LIMIT
Lever arms bent more than 4 degrees and less than 7 degrees or not
correctly assembled by the same amount of degrees)
10 flight cycles
NOTE: It is recommended that you do the
borescope inspection of the compressor for
blade damage and cracks.
The vane trunnion metal touches the case bore metal 200 flight cycles or 500 flight hours after 50%
of the vanes in a stage have this damage.
(d) Compressor Rear Frame
CONDITION CONTINUE-IN-OPERATION LIMIT
Front flange cracks into the skin, less than 0.200 inch (5.08 mm) in length. 50 flight cycles
Front flange cracks into the skin, more than 0.200 inch (5.08 mm) and less
than 4.00 inch (10.16 mm) in length
10 flight cycles
(e) Inner and Outer Liner Panels of the Combustor
CONDITION CONTINUE-IN-OPERATION LIMIT
Circumferential cracks. Three cracked dilution lands are adjacent to three
dilution lands that have no cracks.
25 flight cycles
Axial cracks, 12 cracks in each liner. Each crack is less than two and a half
panels in length.
25 flight cycles
Connected cracks 25 flight cycles
(f) Dome Assembly
CONDITION CONTINUE-IN-OPERATION LIMIT
Axial and circumferential cracks 5 flight cycles
Other damage (if it is less than 20% more than the limits) 25 flight cycles
SUBTASK 72-00-00-866-090-G00
(3) The Continue-In-Operation Limits for the high pressure turbine (HPT) follow:
NOTE: Make sure that you refer to the Maximum Serviceable Limits before the
Continue-In-Operation Limits.
(a) Stage 1 HPT Nozzle
CONDITION CONTINUE-IN-OPERATION LIMIT
Stage 1 HPT Vane leading edge has material that is gone, or burns that go
all the way through. The total burn area is less than 0.4 sq inch (258 sq mm)
on each airfoil. A maximum of four vanes in a 90 degree arc.
25 flight cycles
Stage 1 HPT Vane concave and convex surface of vane airfoil has material
that is gone or burns that go all the way through. The total damage area is
less than 0.5 sq inch (323 sq mm) on each airfoil.
25 flight cycles
Stage 1 HPT Vane trailing edge of vane airfoil has material that is gone
(from cracks) or burns that go all the way through. The total damage area is
less than 2.5 sq inch (1613 sq mm) on each airfoil. The total damage area
on each assembly is less than 10 sq inch (6452 sq mm).
25 flight cycles
767
AIRCRAFT MAINTENANCE MANUAL
CF6-80A SERIES ENGINES
72-00-00
NoC
Page 656
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ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details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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