BALANCE
COMPARISON
DIFFERENCE
(II-IV)
TOTAL
MOMENT WEIGHT
OF
QUADRANT
IV
TOTAL
MOMENT WEIGHT
OF
QUADRANT
II
DEFFERENCE
(I-III)
TOTAL
MOMENT WEIGHT
OF
QUADRANT
III
TOTAL
MOMENT WEIGHT
OF
QUADRANT
I
__________________
__________________
__________________
__________________
__________________
__________________
WEIGHT
DIFF.
CHANGED
LARGE
(761).
YOU CAN
CHANGE BLADES
(180
˚
APART)
BETWEEN
OPPOSITE
QUADRANTS
TO
IN
THIS
EXAMPLE
THE
QUADRANT
I
TO
QUADRANT
III
MOMENT WEIGHT
DIFFERENCE
IS
TOO
QUADRANT
I
(TO GET
MORE
WEIGHT
IN
QUADRANT
I).
USE THE
MOMENT WEIGHT
TABLE
TO
MAKE
A
SELECTION
OF
WHICH
BLADES
TO
CHANGE.
THE
NEW
QUADRANT
WEIGHT
DIFFERENCE
( )
SHOULD
BE AS
CLOSE
TO
THE
INITIAL
AS
POSSIBLE.
_______EXAMPLE
MAKE
THE
SMALLER.
BLADES
FROM
QUADRANT
III CAN
BE
CHANGED
WITH
BLADES
FROM
DO
THE
STEPS
THAT
FOLLOW
TO
ESTIMATE
WHICH
BLADES
TO
CHANGE:
QUADRANT
I
III
II
IV
1243903
1243924
21
1092364
1092133
231
1 &
20
2 &
21
3 &
22
370
201
19
&
38
CHANGED
BLADES
NEW
TOTAL
WEIGHT
IF
THE
REPLACEMENT
BLADE
IS
LARGER
THAN
THE
INITIAL
,
CHANGE BLADES
THAT
HAVE
A
MOMENT WEIGHT
DIFFERENCE
THAT
IS
1/2
OF
THE
REPLACEMENT
BLADE/ORIGINAL
BLADE
WEIGHT
DIFFERENCE.
IF
THE
REPLACEMENT
BLADE
IS
LESS THAN
THE
INITIAL
,
CHANGE BLADES
THAT HAVE
IN
THIS
EXAMPLE
THE
TOTAL
MOMENT WEIGHT
DIFFERENCE
BETWEEN
BLADES
1 &
20,
2 &
21,
AND
3 &
22 IS
370.
TO
CALCULATE
THE NEW
:
SUBTRACT
370
FROM
THE
TOTAL
MOMENT WEIGHT
OF
QUADRANT
III
AND ADD 370
TO
THE
TOTAL
MOMENT WEIGHT
OF
QUADRANT
I.
THE NEW
IS 21
(THIS
IS
PERMITTED).
THE
SAME
STEPS
ARE
USED
FOR
QUADRANTS
II
AND IV.
A
WEIGHT
DIFFERENCE
THAT
2
TIMES
THE
REPLACEMENT
BLADE/ORIGINAL
BLADE
WEIGHT
DIFFERENCE.
REPLACEMENT
BLADES
__________________
__________________
__________________
__________________
__________________
__________________
1,243,533
1,244,294
761
1,092,163
1,092,334
171
1,260,027
1,260,027
0
1,115,963
1,115,686
277
INITIAL
BLADES
21627 S00061422919_V1
Balance Comparison Form
Figure 805/72-31-02-990-810-G00 (Sheet 2 of 2)
767
AIRCRAFT MAINTENANCE MANUAL
CF6-80A SERIES ENGINES
72-31-02
NoC
Page 814
D633T1B7 Dec 22/2016
ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details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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