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Maximum ramp weight ................................................................. 8,730 pounds (3,960 kilograms)
Maximum takeoff weight* ........................................................... 8,645 pounds (3,921 kilograms)
Maximum landing weight*........................................................... 8,000 pounds (3,629 kilograms)
Maximum zero fuel weight........................................................... 6,750 pounds (3,062 kilograms)
Maximum nose baggage weight ......................................................... 320 pounds (145 kilograms)
Maximum tail cone baggage weight .................................................. 300 pounds (136 kilograms)
*Refer to the FAA-approved Aircraft Flight Manual for additional restrictions that may apply
due to runway, pressure, altitude, and temperature.
MAXIMUM DESIGN CENTER-OF-GRAVITY LIMITS
(U.S. UNITS)
Forward limit ......................................................... 285.59 inches aft of the datum (19.00% MAC)
at 5,550 pounds to 6,927 pounds
and/or................................................................ 287.04 inches aft of the datum (21.32% MAC)
at 8,730 pounds with straight line variation
between these points
Aft limit .................................................................. 292.46 inches aft of the datum (30.00% MAC)
at 5,314 pounds to 8,730 pounds
MAXIMUM DESIGN CENTER-OF-GRAVITY LIMITS (METRIC UNITS)
Forward limit .................................................. 7,254 millimeters aft of the datum (19.00% MAC)
at 2,517 kilograms to 3,142 kilograms
and/or ......................................................... 7,291 millimeters aft of the datum (21.32% MAC)
at 3,960 kilograms with straight line variation
between these points
Aft limit ........................................................... 7,428 millimeters aft of the datum (30.00% MAC)
at 2,410 kilograms to 3,960 kilograms
BALANCE LIMITS FOR
NORMAL GROUND
OPERATIONS
Removal of any large components forward of the
wing may require temporary ballast in the nose.
There are no balance limits for fuel loading operations.
For example, one wing fuel tank can
be completely filled prior to adding fuel to the
opposite wing fuel tank.
As with any aircraft, use caution when loading.
Always load aircraft from the nose to the
aft. Low fuel, unlevel terrain, wind, and snow
aft of the main landing gear can magnify the
potential for tipping the aircraft on its tail.
Zero Reference Datum Line
The zero reference datum line of the Model 510
is located 143.70 inches (3,650 millimeters) in
front of the jig point (nose jack pad location).
Horizontal distance from zero datum line to the
leading edge of the MAC is 273.71 inches (6952
millimeters). The addition of any weight in any
location therefore, results in a positive moment
change.
510OM-00 19-5
CITATION MUSTANG OPERATING MANUAL
Figure 19-1. Baggage Door Opening Dimensions
Figure 19-2. Baggage Compartment Limits
19-6 510OM-00
CITATION MUSTANG OPERATING MANUAL
FORMS
The Weight-and-Balance forms are discussed
below, and examples of the forms are included
in Figures 19-3 through 19-16. If the aircraft
has a different seating configuration from the
one depicted in the example, the form appropriate
to that configuration is in the AFM.
AIRCRAFT WEIGHING FORM
The aircraft weight, CG arm, and moment (divided
by 100) are all listed at the bottom of this
form as the aircraft is delivered from the factory
(Figures 19-3 and 19-10). Ensure that the
basic empty weight figures listed are current
and have not been amended.
WEIGHT-AND-BALANCE
RECORD
The Weight-and-Balance Record amends the
Aircraft Weighing Form (Figures 19-4 and
19-11). After delivery, if a service bulletin is
applied to the aircraft or if equipment is removed
or added that would affect the CG or
basic empty weight, it must be recorded on this
form in the AFM. The crew must always have
access to the current aircraft basic weight and
moment in order to be able to perform weight
and balance computations.
The tables already have computed moments/
100 for weights in various seating locations in
the aircraft (Figure 19-5).
WEIGHT-AND-BALANCE
COMPUTATION
A step-by-step process is outlined for determining
weight and CG limits. The payload
computations are made in the left column,
while the rest of the computations are shown
in the right column.
STANDARD SEATING
CONFIGURATION
The tables already have computed moments/
100 for weights in various seating locations
　
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