0.25 INCH (6.4
mm)
1.10
INCHES
(27.9
mm)
B
SEE
ROTOR BLADE
WITH
AXIAL HOLES
1
1
CF8-6995-00-A
AXIAL HOLES
ROW
OF 10
ROW
OF
9
ROW
OF 16
ROW
OF 10
FILM
HOLES
TRAILING
EDGE
HOLES
FROM
BLADE
PLATFORM
OR
8TH
CONCAVE
GILL HOLE
TIP
BLADE
FLAT
TIP CAP
A
A
EDGE
TRAILING
A
TIP CAP
CONVEX
SIDE (CV)
AREA
B
BLADE SHANK
AREA
DAMPER
BOSS
SERRATIONS
DOVETAIL
BLADE
PLATFORM
(BOTH
SIDES)
SEAL
LIP
A-A
TRAILING
EDGE
EDGE
LEADING
LIP
SURFACE
TIP CAP
SIDE (CC)
CONCAVE
(BACK
TO
GILL
HOLES)
LEADING
EDGE
CONCAVE
GILL
HOLES
(14)
HOLES
LEADING
EDGE
AREA
A
LEADING
EDGE
TIP
HOLES
C
TIP
NOTCH)
(SEE
FOR
TIP
SEE
A
ROW
OF
9
ROW
OF 16
(FROM
ONE
HOLE
SPACE
BLADE
TIP
AREA
ABOVE
THE TOP
GRILL HOLE)
26100 S00061422721_V1
1st-Stage High Pressure Turbine Rotor Blade Inspection
Figure 613/72-00-00-990-821-G00 (Sheet 1 of 2)
767
AIRCRAFT MAINTENANCE MANUAL
CF6-80A SERIES ENGINES
72-00-00
NoC
Page 641
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ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details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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