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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
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Figure 19-1. Baggage Door Opening Dimensions
Figure 19-2. Baggage Compartment Limits
19-6 510OM-00
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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
in the aircraft (Figures 19-6 and 19-13).
BAGGAGE/CABINET WEIGHTAND-
MOMENT TABLE
Notice in the baggage compartment contents
table the last weight that a moment/100 is
listed for under the last weight for which a moment/
100 listed under the column corresponds
to the placard limit in that compartment
(Figures 19-7 and 19-14). Remember that this
limit is structural in nature. It is based on the
maximum weight the flooring in that area can
support. This same point applies to the aft extension
and cabinet contents, as well.
FUEL LOADING WEIGHT-ANDMOMENT
TABLE
All of the tables have arms listed for the various
locations except the fuel table (Figures
19-8 and 19-15). Notice that the arm varies depending
on the quantity of usable fuel.
CENTER-OF-GRAVITY LIMITS
ENVELOPE GRAPH
After summing all the weights and moments,
it is necessary to determine whether the CG is
within allowable limits.
This graph represents the allowable CG envelope
(Figures 19-9 and 19-16).
The way to plot the location of the CG on the
graph is to determine the CG location in
inches aft of datum, then plot it against the
weight. To determine the CG arm, the total
moment (moment x 100) is divided by the
total aircraft weight.
510OM-00 19-7
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Figure 19-3. Aircraft Weighing Form—U.S. Units
19-8 510OM-00
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Figure 19-4. Weight-and-Balance Record—U.S. Units
510OM-00 19-9
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Figure 19-5. Weight-and-Balance Computation Form—U.S. Units
19-10 510OM-00
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Figure 19-6. Standard Seating Configuration—U.S. Units
510OM-00 19-11
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Figure 19-7. Baggage and Cabinet Compartments Standard Weight-and-
Moment Tables—U.S. Units
19-12 510OM-00
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Figure 19-8. Fuel Loading Table—U.S. Units
510OM-00 19-13
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Figure 19-9. Center-of-Gravity Limits Envelope Graph—U.S. Units
19-14 510OM-00
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Figure 19-10. Aircraft Weighing Form—Metric Units
　
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