(Continued)
CONDITION CONTINUE-IN-OPERATION LIMIT
Condition A: No cracks can extend into the radius area of the T-rib (aft of the
OGV stiffening rib)
5 flight cycles
Condition B: No cracks can be adjacent to the nut plate for the OGV mount 5 flight cycles
Material that is gone from one fan frame strut 10 flight cycles, if the leading and trailing
edges are not damaged. Put a temporary
cover on the damaged area.
*[1] ENGINES WITH GE SB 73-051 AND THE AFT FAN CASE IS NOT CRACKED; You do not need to do this inspection.
*[2] ENGINES WITH GE SB 73-051, GE SB 72-400, GE SB 72-428, AND THE AFT FAN CASE IS CRACKED; You do not
need to do this inspection.
SUBTASK 72-00-00-866-089-G00
(2) The Continue-In-Operation Limits for the Engine Core follow:
NOTE: Make sure that you refer to the Maximum Serviceable Limits before the
Continue-In-Operation Limits.
(a) Compressor Rotor
CONDITION CONTINUE-IN-OPERATION LIMIT
Radial tip crack in the 12th and 14th-stages 10 flight cycles
If damage to the stage 1-14 blades 10 flight cycles if you obey these steps.
that is more than the maximum serviceable limits: Damage is within repairable limits for
borescope blending of HPC stage 1-14 rotor
blades (AMM 72-35-00/828).
A maximum of one engine per aircraft has
damage exceeding serviceable limits.
A borescope inspection of all stages has
been performed and all blade damage is
within blend repairable limit.
(b) Compressor Stator Case
CONDITION CONTINUE-IN-OPERATION LIMIT
Skin cracks forward of stage 10, less than 0.17 inch (4.3 mm) in length 25 flight cycles
Forward circumferential flange cracks from the bolt hole to the skin 50 flight cycles
Stage 8 manifold end with cap cracks 5 flight cycles or 30 flight hours
Aft circumferential flange cracks that are radially inward from the bolt hole 25 flight cycles
CAUTION
DO NOT USE THE ENGINE FOR MORE THAN THE RECOMMENDED
LIMIT. IF TOO MUCH LOAD IS APPLIED TO THE VSV ACTUATION
SYSTEM, DAMAGE TO THE STATOR CASE BORES CAN OCCUR.
(c) Variable Stator Vane (VSV) System (Air System)
767
AIRCRAFT MAINTENANCE MANUAL
CF6-80A SERIES ENGINES
72-00-00
NoC
Page 655
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ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details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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