MODEL 510 SECTION VI - WEIGHT AND BALANCE DATA
CONTROL - EXAMPLES
FAA APPROVED
U.S.
EXAMPLES
General
The contribution that any loading item makes to a shift in the airplane's center-of-gravity depends
upon its distance from the airplane's 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 take-off
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 30 - 31) is an example plot of the
fuel burn calculated from the Example Weight and Balance Computation Form (Figures 28 - 29).
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/1000
for Metric Units) and center-of-gravity as weighed from the Airplane Weighing Form on line
1 BASIC EMPTY WEIGHT of the Example Weight and Balance Computation Form (See
Figures 28 - 29).
2. Determine the moment index for each passenger using the Crew and Passenger Weight
and Moment Tables (See Figures 10 - 11). Enter the weight and moment index for each
passenger on the PAYLOAD COMPUTATIONS side of the Weight and Balance
Computation Form.
3. Determine the moment index for any cabinet contents using the Baggage and Cabinet
Compartments Standard Weight and Moment Tables (See Figures 17 - 18). Enter the
weight and moment index on the PAYLOAD COMPUTATIONS side of the Weight and
Balance Computation Form.
4. Determine the moment index for baggage loading in the nose, toilet seat and tailcone
compartments using the Baggage and Cabinet Compartments Standard Weight and
Moment Tables (Figures 17 - 18). Enter the weight and moment index on the PAYLOAD
COMPUTATIONS side of the Weight and Balance Computation Form.
5. Total the weights and moment indices of the payload items at the bottom of the PAYLOAD
COMPUTATIONS side of the Weight and Balance Computation Form and enter these
values on line 2 PAYLOAD of the Weight and Balance Computation Form.
6. Enter the sums of the values on lines 1 and 2 onto line 3 ZERO FUEL WEIGHT of the
Weight and Balance Computation Form.
(Continued Next Page)
510WB-00 6-51
SECTION VI - WEIGHT AND BALANCE DATA MODEL 510
CONTROL - EXAMPLES
FAA APPROVED
U.S.
Sample Loading Problem (Continued)
7. Divide the zero fuel moment index by the zero fuel weight and multiply by 100 (1000) to
determine the zero fuel weight center-of-gravity.
8. Check the zero fuel weight and center-of-gravity by locating the weight and center-of-gravity
on the Example Center-of-Gravity Limits Envelope Graph (See Figures 30 - 31).
NOTE
Approved points are located below the maximum zero fuel weight line.
9. Look up the weight of fuel to be used for the flight and the corresponding moment index in
the Fuel Loading Table (See Figures 3 - 4). Enter the weight and moment index on line 4
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