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EXAMPLES....................................................................................................................... 19-21
General........................................................................................................................ 19-21
Sample Loading Problem ............................................................................................ 19-21
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ILLUSTRATIONS
Figure Title Page
19-1 Baggage Door Opening Dimensions ..................................................................... 19-5
19-2 Baggage Compartment Limits ............................................................................... 19-5
19-3 Aircraft Weighing Form—U.S. Units .................................................................... 19-7
19-4 Weight-and-Balance Record—U.S. Units ............................................................. 19-8
19-5 Weight-and-Balance Computation Form—U.S. Units .......................................... 19-9
19-6 Standard Seating Configuration—U.S. Units...................................................... 19-10
19-7 Baggage and Cabinet Compartments Standard
Weight-and-Moment Tables—U.S. Units............................................................ 19-11
19-8 Fuel Loading Table—U.S. Units ......................................................................... 19-12
19-9 Center-of-Gravity Limits Envelope Graph—U.S. Units ..................................... 19-13
19-10 Aircraft Weighing Form—Metric Units .............................................................. 19-14
19-11 Weight-and-Balance Record—Metric Units........................................................ 19-15
19-12 Weight-and-Balance Computation Form—Metric Units..................................... 19-16
19-13 Standard Seating Configuration—Metric Units .................................................. 19-17
19-14 Baggage and Cabinet Compartments Standard
Weight-and-Moment Tables—Metric Units ........................................................ 19-18
19-15 Fuel Loading Table—Metric Units...................................................................... 19-19
19-16 Center-of-Gravity Limits Envelope Graph—Metric Units.................................. 19-20
19-17 Example Aircraft Weighing Form—U.S. Units................................................... 19-23
19-18 Example Weight-and-Balance Computation Form—U.S. Units......................... 19-24
19-19 Example Center-of-Gravity Limits Envelope Graph—U.S. Units ...................... 19-25
19-20 Example Aircraft Weighing Form—Metric Units ............................................... 19-26
19-21 Example Weight-and-Balance Computation Form—Metric Units ..................... 19-27
19-22 Example Center-of-Gravity Limits Envelope Graph—Metric Units .................. 19-28
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GENERAL
WEIGHT
Aircraft maximum weights are predicated on
structural strength and performance requirements.
It is necessary to ensure that the aircraft
is loaded within the various weight restrictions
to maintain structural integrity and to ensure
that performance is acceptable.
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CHAPTER 19
WEIGHT AND BALANCE
INTRODUCTION
This chapter provides procedures for establishing the basic empty weight and moment
of the Mustang aircraft. It also provides procedures for determining the weight and balance for
flight. This section also describes items on the Weight and Balance Data Sheet, which is provided
with the aircraft as delivered from Cessna Aircraft Company.
It is the responsibility of the pilot to make sure the aircraft is loaded properly. The aircraft
must be loaded so as to remain within the weight and balance limits prescribed
in the Aircraft Flight Manual (AFM) throughout the flight from takeoff to landing.
This manual presents data in both U.S. and metric units. Make sure that you use the
appropriate data in the weight-and-balance computations for your airplane.
CAUTION
WARNING
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BALANCE
Balance, or the location of the center of gravity
(CG), deals with aircraft stability. The horizontal
stabilizer must be capable of providing
an equalizing moment to that which is produced
by the wing and the aircraft overall.
Since the amount of force produced by the
horizontal stabilizer through elevator movement
　
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