(Continued)
Condition Maximum Serviceable Limit
Dents in the airfoil or the mid-span
shroud trailing edge fillet in the area of
the mid- span shrouds.
Permitted, if the dents are in the area AFT of the mid-span shroud, and there is
no other unserviceable damage. Dents are not permitted to show through to the
other side of the blade. Dents that are directly (approximately 0.25 inch (6.4
mm)) above or below the mid-span shrouds are not permitted.
NOTE: This type of damage is caused by contact with the mid-span shroud of
adjacent blade.
Mid-span shroud tip damage. Permitted.
NOTE: This type of damage is caused by contact with the mid-span shroud of
adjacent blade.
Signs of wear on the carboloy pads Permitted.
Signs of wear in the parent metal of the
mid-span shroud
Not permitted.
A piece of the carboloy pad is gone. No
more than 0.100 inch (2.54 mm) axial
length of the pad is gone.
Permitted.
ABX 001-007, 011, 012, 016-019, 021, 022, 025, 101, 109, 114, 115, 314
A piece of the carboloy pad is gone.
More than
0.100 inch (2.54 mm) axial length of the
pad is gone.
Permitted if:
1) There are no signs of wear in the mid- span shroud parent metal.
2) You must do an inspection before 25 flight cycles. There must be no sign of
wear in the parent metal.
3) You must do subsequent inspections each 200 flight cycles (maximum).
There must be no signs of wear in the parent metal of the mid-span shroud.
ABX 001-007, 011, 012, 016-019, 021, 022, 025, 101, 109, 114, 115, 314-999
SUBTASK 72-00-00-296-005-G00
(7) Use the borescope to visually examine the rotor spools and the disks for the condition that
follows:
Condition Maximum Serviceable Limit
Rub coat that is not there Permitted.
NOTE: This condition is permitted, but can effect the performance of the engine by a
small amount.
SUBTASK 72-00-00-296-006-G00
(8) Use the borescope to examine the 1st and 2nd-stage blade retainers for the conditions that
follow:
Condition Maximum Serviceable Limit
Cracks Not permitted.
Tabs that are gone Not permitted.
SUBTASK 72-00-00-296-007-G00
(9) Use the borescope at port B1-0 to examine the compressor rotor for oil leakage as follows:
NOTE: Refer to the Nondestructive Test Manual for the use of the fiber light probe and the
high intensity light.
767
AIRCRAFT MAINTENANCE MANUAL
CF6-80A SERIES ENGINES
72-00-00
NoC
Page 606
D633T1B7 Dec 22/2016
ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details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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