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11. Divide the ramp moment index by the ramp
weight and multiply by 100 (1,000) to determine
the ramp weight center of gravity.
12. Check the ramp weight by locating the
weight and center of gravity on the
Example Center of Gravity Limits
Envelope Graph (see Figures 19-19 and
19-22).
NOTE
Approved points are located below
the maximum ramp weight line.
13. Enter the taxi fuel weight and moment
index on line 6 LESS FUEL FOR TAXIING
of the Weight and Balance
Computation Form. A standard 85-pound
(38.56-kilogram) burn-off is assumed.
The moment index for taxi is the difference
between the moment index of the
fuel loaded and the moment index of the
fuel remaining on-board after taxi.
14. Enter the differences between the values
on lines 5 and 6 onto line 7 TAKEOFF
WEIGHT of the Weight and Balance
Computation Form.
15. Divide the takeoff moment index by the
Takeoff Weight and multiply by 100
(1,000) to determine the takeoff center of
gravity. Enter the takeoff center of gravity
on line 7 of the Weight and Balance
Computation Form.
16. Check the takeoff weight by locating the
weight and center of gravity on the
Example Center-of-Gravity Limits
Envelope Graph (see Figures 19-19 and
19-22).
NOTE
Approved points are located inside
the envelope below the maximum
takeoff weight line.
17. Determine the estimated weight of the
fuel to be used in flight. The moment
index of the fuel used in flight is the difference
between the moment index of
the fuel remaining after taxi and the moment
index of the fuel remaining after
reaching the destination.
18. Enter the weight and moment index of the
fuel used in flight on line 8 LESS FUEL
TO DESTINATION of the Weight and
Balance Computation Form.
19. Enter the differences between the values
on lines 7 and 8 onto line 9 LANDING
WEIGHT of the Weight and Balance
Computation Form.
20. Divide the landing moment index by the
landing weight and multiply by 100
(1,000) to determine the landing centerof-
gravity. Enter the landing center-ofgravity
on line 9 of the Weight and
Balance Computation Form.
21. Check the landing weight by locating the
weight and center of gravity on the
Example Center of Gravity Limits
Envelope Graph (see Figures 19-19 and
19-22).
NOTE
Approved points are located inside
the envelope below the Maximum
Landing Weight line.
19-22 510OM-00
CITATION MUSTANG OPERATING MANUAL
510OM-00 19-23
CITATION MUSTANG OPERATING MANUAL
Figure 19-17. Example Aircraft Weighing Form—U.S. Units
19-24 510OM-00
CITATION MUSTANG OPERATING MANUAL
Figure 19-18. Example Weight-and-Balance Computation Form—U.S. Units
510OM-00 19-25
CITATION MUSTANG OPERATING MANUAL
Figure 19-19. Example Center-of-Gravity Limits Envelope Graph—U.S. Units
19-26 510OM-00
CITATION MUSTANG OPERATING MANUAL
Figure 19-20. Example Aircraft Weighing Form—Metric Units
510OM-00 19-27
CITATION MUSTANG OPERATING MANUAL
Figure 19-21. Example Weight-and-Balance Computation Form—Metric Units
19-28 510OM-00
CITATION MUSTANG OPERATING MANUAL
Figure 19-22. Example Center-of-Gravity Limits Envelope Graph—Metric Units
CITATION MUSTANG OPERATING MANUAL
Flight Planning and Performance
MODEL 510
510-0001 AND ON
MEMBER OF GAMA
19 JANUARY 2007 COPYRIGHT © 2006
CESSNA AIRCRAFT COMPANY
WICHITA, KANSAS, USA
510OM-00 ORIGINAL
CITATION MUSTANG OPERATING MANUAL
ii 510OM-00
TABLE OF CONTENTS
PAGE
DEFINITIONS………………………………………………………………………. 1
CLIMB……………………………………………………………………………….. 3
CRUISE……………………………………………………………………………... 9
MULTI-ENGINE…..………………………………………………….……………… 10
SINGLE-ENGINE…………………………………………………………...……….. 38
　
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