Specifications

SECTION VII
MODEL 560 FLIGHT PLANNING AND PERFORMANCE
SAMPLE LOADING PROBLEM
Standard Airplane
Basic Empty Weight - 10,176 pounds.* 100 pounds of baggage at station 74 in nose.
Crew of 170 and 170 pounds in Seats 1 and 2. 300 pounds of baggage at station 434 in
One 170-pound Passenger in Seat 3. tailcone baggage compartment.
One 170-pound Passenger in Seat 4. 5424 pounds of fuel.
One 170-pound Passenger in Seat 5. 2000-pound fuel burnoff during trip.
One 170-pound Passenger in Seat 6. 200-pound fuel burnoff during taxi.
One 170-pound Passenger in Seat 7.
One 170-pound Passenger in Seat 8.
*Includes all undrainable fluids and a full service of oil.
Determine the operational takeoff weight and center-of-gravity. Loading tables are found in this
manual and in the Weight and Balance Data Sheets. The following step-by-step procedure illustrates a
logical manner in which to approach the loading problem.
NOTE
During computation of the following sample problem, weights are rounded to nearest
whole number (pound) for entry on the Weight and Balance Computation Form.
1. Use the Crew and Passenger Loading Table obtained from Weight and Balance Data
Sheets to determine the moment for each load station. Enter the figures for each load
station in the Weight and Balance Computation Form.
2. Use the Cabinet Loading Table obtained from Weight and Balance Data Sheet to determine
the moment for any cabinet contents and enter the figures in the Weight and Balance
Computation Form.
3. Use the Cargo Loading Table obtained from Weight and Balance Data Sheet to determine
the moment for cargo loading in the nose, aft cabin and tailcone compartments. Enter the
weight and moments for each load station in the Weight and Balance Computation Form.
4. Total the payload items and enter the totals on the Weight and Balance Computation Form
(two places).
5. Enter the Airplane Basic Empty Weight and Moment from the Airplane Weighing Form on
the Weight and Balance Computation Form.
6. Total the Basic Empty Weight and Payload and check the zero fuel weight.
NOTE
To check approved limits, locate the weight on the Center-of-Gravity Limits Envelope
Graph (refer to Figure 7-5). Approved points are points located below the Zero Fuel
Weight Line.
7. Determine the zero fuel weight center-of-gravity on the Weight and Balance Computation
Form; divide moment by weight and multiply by 100.
8. Use the Fuel Loading Table (refer to Figure 7-4) to determine the moment for the amount of
fuel being loaded for the flight. Enter the weight and moment of the fuel in the Weight and
Balance Computation Form.
9. Total zero fuel weight and fuel loading to obtain ramp weight.
NOTE
To check approved limits, locate the weight on the Center-of-Gravity Limits Envelope
Graph (refer to Figure 7-5). Approved points are points located below the Maximum
Ramp Weight line.
I 56OMB-01 Configuration AA 7-5