SUBTASK 72-35-00-016-036-G00
(2) Open the fan cowl panels (PAGEBLOCK 71-11-04/201).
SUBTASK 72-35-00-016-051-G00
(3) Open the core cowl panels (PAGEBLOCK 71-11-06/201).
SUBTASK 72-35-00-016-037-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).
F. Procedure
SUBTASK 72-35-00-216-038-G00
(1) Use the inspection tools (VSV sight gage, SPL-6403, VSV sight gage, SPL-6404, and VSV
sight gage, SPL-6716) to examine the VSV (Figure 607):
Condition Maximum Serviceable Limits
Look for a lever arm bent 2 degrees or less Permitted.
Look for a lever arm bent more than 2
degrees but not more than 4 degrees
Replace the lever arm (PAGEBLOCK 72-35-00/801).
Look for a lever
*[1]
arm bent more than 4
degrees but not more than 7 degrees
Not Permitted. Replace the engine (PAGEBLOCK 71-00-02/401). See
Over-Serviceable-Limit Extensions.
Look for a lever arm bent more than 7
degrees or the lever arm is broken
Not permitted. Replace the engine (PAGEBLOCK 71-00-02/401).
Look for a lever arm that is assembled
incorrectly
Measure the off-schedule angle before you replace the lever arm. If the
angle more than 4°, the VSV cannot be repaired. Replace the engine
(PAGEBLOCK 71-00-02/401). See the Continue-In-Operation Limits.
Look for an actuation ring or a connector link
that is broken
Not serviceable. Replace the engine (PAGEBLOCK 71-00-02/401).
*[1] It is recommended that you do a borescope inspection of the VSV for cracks or other damage to blades before you
operate the engine.
G. Continue-In-Operation Limits
NOTE: During this inspection procedure it is possible that a defect will be found that cannot be
corrected at the given location. The continue-in-operation limits are given to permit the
engine to be sent to a maintenance facility where the defect can be corrected. The
necessary maintenance must be scheduled in the specified period. The limit are one-time
only and the repairs must be made at or before the end of the limit period.
SUBTASK 72-35-00-866-039-G00
(1) The continue-in-operation limits shown below are given for the compressor stator casing.
Condition Continue-in-Operation Limits
Cracks in the casing The maximum limit is 25 cycles for skin cracks less than 0.17 inch
skin (4.3 mm in length, forward of the 10th-stage.
Cracks between the bolt hole and the casing skin 50 cycles for the forward flange.
8th-stage manifold end cap cracks 5 cycles or 30 hours
767
AIRCRAFT MAINTENANCE MANUAL
CF6-80A SERIES ENGINES
72-35-00
NoC
Page 615
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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