SUBTASK 72-00-00-216-068-G00
(5) Do the VSV feedback cable inspection procedure (TASK 75-31-03-206-009-G00).
SUBTASK 72-00-00-716-069-G00
(6) Do the VSV feedback cable adjustment/test (TASK 75-31-03-705-001-G00).
SUBTASK 72-00-00-016-164-G00
(7) If the stall was at low speed or in Reverse, do a check that the installation of the Intermediate
Pressure Check Valve is correct.
SUBTASK 72-00-00-716-070-G00
(8) Do a pressure check of the CIT Sensor (TASK 73-21-02-206-001-G00).
SUBTASK 72-00-00-296-065-G00
(9) Do the borescope inspection for the compressor rotor 1st-stage and the 12th-stage blades.
SUBTASK 72-00-00-296-066-G00
(10) Do the borescope inspection for the high pressure turbine rotor.
SUBTASK 72-00-00-116-073-G00
(11) If it is possible, clean the engine (TASK 72-00-00-117-006-G00).
L. Fan Blade Shingling Inspection
SUBTASK 72-00-00-216-076-G00
(1) Possible causes of fan blade shingling (overlapping of the fan blade shrouds) are: engine stall,
bird strike, foreign object damage, and engine overspeed. If one of these events has occurred,
you must do the steps that follow:
WARNING
BEFORE PERFORMING ANY MAINTENANCE TASK ASSOCIATED WITH
BIRD STRIKES, REFER TO THE SAFETY REQUIREMENTS LISTED IN
GPM 13-17.
(a) Examine the fan blades for shingling as follows:
1) Examine both the upper and lower surfaces of the mid span shrouds for signs of
chafing or scoring in the areas adjacent to the interlock surfaces.
2) All blades that are overlapped or show indications of overlapping must be removed
and inspected as follows (TASK 72-31-02-226-007-G00):
a) Use a strong light source to do a visual inspection of the midspan shrouds for
cracks and shingling (overlapping).
b) No cracks are permitted.
CAUTION
YOU MUST REPLACE BLADES THAT ARE NOT ALIGNED IN LESS
THAN 50 HOURS. DAMAGE THAT IS MORE THAN THE PERMITTED
LIMITS CAN OCCUR.
3) All blades that have misaligned midspan shrouds and are in the serviceable limits
must be replaced in less than 50 flight hours.
a) Send the removed blade to the engine shop for inspection and repair (GE
Engine Manual).
(b) Examine the abradable shroud in the forward fan case (TASK 72-33-04-206-001-G00).
767
AIRCRAFT MAINTENANCE MANUAL
CF6-80A SERIES ENGINES
72-00-00
NoC
Page 661
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ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details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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