CONDITION MAXIMUM SERVICEABLE LIMIT
Cracks in the welds or in the parent metal Two in each case are permitted, if they are not in the flange. The cracks must
be less than 3.0 inches (76.0 mm) in length, and have a separation of two
times the length of the crack. See the Continue-In-Operation Limits (Ref
72-00-00/601).
Cracks in the boss pads Five cracks that are less than 1.0 inch (25.0 mm) in length are permitted in
each case. One crack that is between 1.0 inch (25.0 mm) and 4.0 inches
(102 mm) is permitted in each case. See the Continue-In-Operation Limits.
SUBTASK 72-51-01-216-003-G00
(2) Examine the 7th-stage air manifolds for the conditions that follow:
CONDITION MAXIMUM SERVICEABLE LIMIT
Radial cracks in the manifold feeder tubes
and the air pads
No cracks are permitted. Replace the manifold or the air pad
(PAGEBLOCK 75-26-01/401).
Radial cracks in the end of an elbow or
feeder tube Tees
Not permitted, replace the elbow or the feeder tube.
E. Put the Airplane to its Usual Condition
SUBTASK 72-51-01-416-020-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 72-51-01-416-017-G00
(2) Close the core cowl panels (PAGEBLOCK 71-11-06/201).
SUBTASK 72-51-01-416-018-G00
(3) Close the fan cowl panels (PAGEBLOCK 71-11-04/201).
SUBTASK 72-51-01-446-019-G00
(4) Do the activation procedure for the thrust reverser (PAGEBLOCK 78-31-00/201).
END OF TASK
767
AIRCRAFT MAINTENANCE MANUAL
CF6-80A SERIES ENGINES
72-51-01
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ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details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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