(Continued)
Condition Maximum Serviceable Limit
Connected cracks Permitted, if the cracks are in the limits for the axial and circumferential cracks.
More than two connected cracks are not permitted. Refer to the
Continue-In-Operation Limits.
Burns and metal that is missing No burn through areas allowed. Refer to the Continue-in-Operation Limits.
Metal that is gone from the overhang Up to fourteen damaged areas, 0.50 inch (12.7 mm) circumferential length by 0.10
inch (2.5mm) axial length permitted per combustor assembly. Three adjacent
damaged panels are not permitted. Refer to the Continue-In-Operation Limits.
Distortion Permitted, if the distortion is less than 0.50 inch (12.7 mm) from the initial contour.
Refer to the Continue-In-Operation Limits.
Decrease in the inner and outer
combustor liner overhang gap
Permitted, a closed or decreasing combustor liner overhang gap shortens the life
of the combustor, leading to distortion, bulging, or burn through.
Bulges 0.05 inch (1.3 mm) within any 2.0 inch x 1.0 inch (51 x 25 mm) area.
NOTE: Bulges in the inner and outer combustor liner panels are caused by a
cumulative closing of the inner and outer combustor liner overhang gap.
SUBTASK 72-00-00-296-021-G00
(8) Use the borescope to examine the fuel nozzle for the condition that follows (Figure 610):
Condition Maximum Serviceable Limit
Carbon on the fuel nozzle Permitted.
SUBTASK 72-00-00-296-159-G00
(9) Use the borescope to examine the combustor cowl for the conditions that follow:
Condition Maximum Serviceable Limit
Burns Not permitted. If there are burns, inspect fuel nozzle (PAGEBLOCK 73-11-05/601)
Cracks All cracks are permitted, if they are less than 0.25 inch (6.4mm) in length.
SUBTASK 72-00-00-296-022-G00
(10) Use the borescope to examine the 1-st stage high pressure turbine nozzle for the condition
that follows:
Condition Maximum Serviceable Limit
Leading edge burns or erosion Permitted , if the maximum span loss of material or burns (that are fully through
the metal) are not more than 0.2 square inch (129 square mm) for each vane. A
maximum of four vanes in a 90 degree arc can have this damage.
SUBTASK 72-00-00-416-023-G00
(11) Do the steps that follow to install the borescope plugs B2-1 through B2-6 (Figure 601):
NOTE: If you will do the borescope inspection of the high pressure turbine (that follows) at this
time, do not install the borescope plugs. The same borescope plugs will be used.
CAUTION
MAKE SURE THAT THE BORESCOPE PLUGS ARE INSTALLED IN THE
CORRECT PORT LOCATIONS. ENGINE DAMAGE CAN OCCUR IF A
BORESCOPE PLUG IS NOT INSTALLED IN THE CORRECT LOCATION.
(a) Apply a light layer of the anti-seize compound on the threads and the pressure faces of
the plugs.
767
AIRCRAFT MAINTENANCE MANUAL
CF6-80A SERIES ENGINES
72-00-00
NoC
Page 610
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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