F. Prepare for the Inspection
SUBTASK 72-33-05-046-002-G00
WARNING
DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT
THE OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL
OPERATION OF THE THRUST REVERSER CAN CAUSE INJURIES TO
PERSONS OR DAMAGE TO EQUIPMENT.
(1) Do this procedure: Thrust Reverser Dactivation for Ground Maintenance
(PAGEBLOCK 78-31-00/201).
SUBTASK 72-33-05-016-003-G00
(2) Open the fan cowl panels (PAGEBLOCK 71-11-04/201).
SUBTASK 72-33-05-016-004-G00
(3) Open the core cowl panels (PAGEBLOCK 71-11-06/201).
SUBTASK 72-33-05-016-005-G00
WARNING
OBEY THE INSTRUCTIONS IN THE PROCEDURE TO OPEN THE THRUST
REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO
PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.
(4) Open the thrust reversers (PAGEBLOCK 78-31-00/201).
SUBTASK 72-33-05-946-006-G00
(5) If you will work in the engine inlet area, put a protective mat, STD-6378 on the lower half of the
inlet cowl.
G. Inspection of the Acoustical Liner Segments
SUBTASK 72-33-05-216-007-G00
(1) Visually examine the acoustical liners (except the wire mesh) on the forward fan case, aft fan
stator case, and the fan frame for the conditions that follow:
Condition Maximum Serviceable Limit
Cracks Not permitted, repair or replace the panel.
Damaged acoustical panels aft of the fan
blades
Not permitted, repair or replace the panel. See the Continue-In-Operation
Limits (PAGEBLOCK 72-00-00/601).
Nicks and scratches Permitted, if the glass laminate does not show broken fibers.
Delamination Not permitted, replace the panel.
Pieces that are gone Not permitted, repair or replace the panel.
Bushings are loose or gone Not permitted, replace the panel.
Tears and cuts in the surface coat Three in each panel are permitted, if they are in a forward to aft direction. The
total length of the damage must be less than 3.0 inches (762 mm). Damage
that is circumferential is not permitted. Repair or replace the panel.
Tears and cuts on the leading edge
surface coat
Not permitted, repair or replace panel. See the Continue-In-Operation Limits
(PAGEBLOCK 72-00-00/601).
SUBTASK 72-33-05-216-008-G00
(2) Visually examine the wire mesh for the conditions that follow:
767
AIRCRAFT MAINTENANCE MANUAL
CF6-80A SERIES ENGINES
72-33-05
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ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details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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