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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.
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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
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Figure 19-5. Weight-and-Balance Computation Form—U.S. Units
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Figure 19-6. Standard Seating Configuration—U.S. Units
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Figure 19-7. Baggage and Cabinet Compartments Standard Weight-and-
Moment Tables—U.S. Units
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Figure 19-8. Fuel Loading Table—U.S. Units
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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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Figure 19-11. Weight-and-Balance Record—Metric Units
19-16 510OM-00
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Figure 19-12. Weight-and-Balance Computation Form—Metric Units
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Figure 19-13. Standard Seating Configuration—Metric Units
19-18 510OM-00
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Figure 19-14. Baggage and Cabinet Compartments Standard Weight-and-
Moment Tables—Metric Units
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Figure 19-15. Fuel Loading Table—Metric Units
19-20 510OM-00
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Figure 19-16. Center-of-Gravity Limits Envelope Graph—Metric Units
EXAMPLES
GENERAL
The contribution that any loading item makes
to a shift in the aircraft center of gravity depends
upon its distance from the aircraft Basic Empty
Weight center of gravity. Any weight placed in
the aft baggage compartment will shift the center
of gravity aft since it is aft of the typical
Basic Empty Weight center of gravity.
Adding fuel or passengers will shift the center
of gravity forward since they are forward
of the typical Basic Empty Weight center of
gravity. The magnitude of the shift for any
given weight is proportional to the length of
the moment arm from the center of gravity.
SAMPLE LOADING PROBLEM
The following step-by-step procedure illustrates
a logical manner in which to determine
the takeoff weight and center of gravity.
Loading tables can be found in this manual and
in the Weight and Balance Data Sheets.
The Example Center-of-Gravity Limits
Envelope Graph (Figures 19-19 and 19-22) is
an example plot of the fuel burn calculated
from the Example Weight and Balance
Computation Form (Figures 19-18 and 19-21).
NOTE
For the purposes of this sample problem,
weights are rounded to the nearest
whole pound and moment index
to two (2) decimal places for entry
on the Example Weight and Balance
Computation Form.
1. Enter the Basic Empty Weight, moment
index (moment/100 for U.S. Units or moment/
1,000 for Metric Units) and center
of gravity as weighed from the Airplane
Weighing Form (Figure 19-17) on line 1
BASIC EMPTY WEIGHT of the Example
Weight and Balance Computation Form
　
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