SUBTASK 72-00-00-296-019-G00
(6) Use the borescope to examine the dome assembly, for the conditions that follow
(Figure 607and 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 damaged
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 72-00-00-296-147-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 609
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
To Next Page
Loading...
