SUBTASK 72-33-01-216-005-G00
(3) Visually examine the 1st, 2nd, and 3rd stage vanes for the conditions that follow:
Condition Maximum Serviceable Limits
Tears in the airfoil Permitted, if less than 0.124 inch (3.18 mm).
Cracks Not permitted.
Nicks and scratches 0.50 inch (12.7 mm) from
the root radius
Permitted, if less than 0.03 inch (0.76 mm) in depth, and at least 0.25
inch (6.4 mm) apart.
Dents in the airfoil Permitted, if they are smooth and less than 0.06 inch (1.52 mm) in depth.
Vane leading or trailing edge damage Permitted, if less than 0.06 inch (1.52 mm) in depth, and all the edges are
smooth.
Nicks and scratches on the airfoil (less than
0.5 inch from the leading and trailing edges).
Permitted, if less than 0.015 inch (0.38 mm) in depth, and separated by at
least 0.10 inch (2.54 mm).
SUBTASK 72-33-01-216-006-G00
(4) Visually examine the fan stator fairings for the conditions that follow:
Condition Maximum Serviceable Limits
Cracks Four cracks are permitted on each fairing if they start at the screw hole and
go to the aft edge. No other cracks are permitted.
Nicks and scratches Permitted, if they are less than 0.06 inch (1.5 mm) in depth on the leading
edge, and 0.03 inch (0.8 mm) in depth on the remaining areas. There must
be a minimum separation of at least 0.25 inch (6.4 mm) between each nick
and scratch.
Dents Permitted, if they are less than 0.12 inch (3mm) in depth, and have a
smooth surface.
SUBTASK 72-33-01-216-007-G00
(5) Visually examine the teflon shrouds for the condition that follows:
Condition Maximum Serviceable Limits
Material that is damaged or not there Permitted
E. Put the Airplane to its Usual Condition
SUBTASK 72-33-01-416-008-G00
WARNING
OBEY THE INSTRUCTIONS IN THE PROCEDURE TO CLOSE THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO
PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.
(1) Close the thrust reversers (PAGEBLOCK 78-31-00/201).
SUBTASK 72-33-01-416-009-G00
(2) Close the core cowl panels (PAGEBLOCK 71-11-06/201).
SUBTASK 72-33-01-446-010-G00
(3) Do the activation procedure for the thrust reverser (PAGEBLOCK 78-31-00/201).
SUBTASK 72-33-01-416-011-G00
(4) Close the fan cowl panel (PAGEBLOCK 71-11-04/201).
END OF TASK
767
AIRCRAFT MAINTENANCE MANUAL
CF6-80A SERIES ENGINES
72-33-01
NoC
Page 602
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ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details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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