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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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CITATION MUSTANG OPERATING MANUAL
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CITATION MUSTANG OPERATING MANUAL
INTENTIONALLY LEFT BLANK
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
CITATION MUSTANG OPERATING MANUAL
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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
is limited, the range of movement of the
CG is restricted so proper aircraft stability
and control is maintained.
Stability increases as the CG moves forward.
However, if the CG is located out of limits too
far forward, the aircraft may become so nose
heavy that it cannot be rotated at the proper
speed or flared for landing.
Locating the CG aft of limits is considerably
worse because the stability decreases.
Eventually the airplane becomes unstable.
BASIC FORMULA
Weight x Arm = Moment
This is the basic formula upon which all weight
and balance calculations are based. Remember
that the arm or CG location can be found by
adapting the formula as follows:
Arm = Moment
Weight
WEIGHT SHIFT FORMULA
Weight Shifted = Distance CG is shifted (x)
Total weight Distance weight is shifted
The above formula can be utilized to shift
weight if the CG is found to be out of limits.
Use of this formula avoids working the entire
problem over again.
WEIGHT ADDITION OR
REMOVAL
If weight is to be added or removed after a
weight and balance has been computed, a
simple formula can be used to determine the
shift in the center of gravity.
Weight added Distance the
(or removed) = CG is shifted
New total weight Distance between
the weight arm and
the old CG arm
If it is desired to find the weight change needed
to accomplish a particular CG change, the
formula can be adapted as follows:
Weight to be added Distance the
(or removed) = CG is shifted
Old total weight Distance between
the weight arm and
the new CG arm
DEFINITIONS
General
Basic Empty Weight—Standard empty weight
plus installed optional equipment. This is the
weight reflected on the Weight and Balance
Data Form supplied with the airplane.
MAC—Mean Aerodynamic Chord is an engineering
term that represents an airfoil’s chord
in aircraft design. As such, it is a constant
length, which is also used in the calculation
of center-of-gravity location in terms of percent
MAC.
Operational Landing Weight—This is the
weight at the start of touchdown. It is subject
to airport, operational, and related restrictions.
　
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