3) lubricant, D60130 [V10-041]
SUBTASK 72-00-00-296-212-G00
(6) Use the borescope to examine the dome assembly, for the conditions that follow (Figure 607,
Figure 608):
Condition Maximum Serviceable Limit
Distortion of the splash plates or the dome sleeve. Permitted.
Missing splash plate Not permitted.
Burns, erosion and material that is gone from the splash
plate
Permitted, if each damaged accumulative area is less than
0.20 x 2.0 inch (5 x 50 mm).
Axial and radial cooling hole cracks in the dome plate Permitted, if they are not connected.
Circumferential cracks in the dome plate Permitted, less than 0.50 inch (12.7 mm) in length. Five
cracks are permitted, that are less than 1.0 inch (25 mm) in
length if there is 2.0 inch (51 mm) between each crack.
Overhang metal that is gone from the dome (Figure 607) Five damaged areas are permitted on each dome, if they
are less than 0.5 x 1.0 inch (13 x 25 mm).
Burn-through holes (Figure 607) Three on each dome are permitted, if they are less than 1.0
inch x 1.0 inch (25 x 25 mm).
PRE GE SB 72-523: Cracks in the igniter tube (Figure 608) Permitted.
POST GE SB 72-523: Cracks in the de-coupled igniter tube Not permitted. See the Continue-In- Operation Limits.
Metal that is gone from the ignitor tube (Figure 608) Five damaged areas are permitted on each ignitor tube. The
total damged area on each tube must be less than 0.50 x
0.50 inch (12.7 x 12.7 mm) Refer to the
Continue-In-Operation Limits.
Burns in the igniter ferrule Permitted.
Axial dome plate cracks Permitted, if they do not extend into the strut area.
Smile slot and circumferential cracks that connect to smile
slots (Figure 607)
Permitted, if three smile slots in a row do not connect.
Strut cracks (Figure 607) Not permitted. Refer to the Contune-In-Operation Limits.
Splash Plate Cracking Figure 608 0.300 inch (7.62 mm) length radial crack permitted. No
interconnecting cracks. No circumferential cracks. If limits
are exceeded, refer to the Continue-In- Operation Limits.
SUBTASK 72-00-00-296-213-G00
(7) Use the borescope to examine the inner and outer liner panels of the combustor for the
conditions that follow (Figure 609):
Condition Maximum Serviceable Limit
Axial cracks 0.7 inch (18 mm) or less in length Permitted.
Axial cracks more than 0.7 inch (18 mm) in length Ten full panel cracks are permitted in each liner. A crack
must not extend into an adjacent panel. The maximum
extension is 25 cycles.
Circumfer- ential cracks on panels with dilution holes Permitted, if a cracked area between two dilution holes is
next to at least three adjacent areas (between dilution
holes) that have no cracks. Maximum service extension is
25 cycles.
767
AIRCRAFT MAINTENANCE MANUAL
CF6-80A SERIES ENGINES
72-00-00
NoC
Page 687
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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