Wam - Example - THRUSH S2R-H80 Flight Manual

5.3.

WAM - EXAMPLE

Balance of an aircraft is a simple formula, it can be remembered simply as WAM, or:
Weight X Arm = Moment. Weight is in pounds, Arm is the location where the
weight is taken, in inches, when measured from the Datum which in this case is
the leading edge of the wing. Moment is the number derived from multiplying
weight X Arm. Once the total Weight and the Total Arm is known, the aircraft's CG
is determined by simply dividing the total Moment by the total Weight.
Single and Dual Cockpit
Baggage Compartment Arm:
-14.0 inches and max load is 100 lbs.
Smoker Tank Arm:
-9.1 inches & holds four gallons of oil weighing 26 lbs.
Hopper Rinse Tank Arm:
-30.0 inches & has a capacity of 24 gallons of water weighing 200 lbs.
The Hopper Arm:
29.9 inches and has a maximum capacity of 4,000 lbs.
Pilots Seat:
89.0 inches
Fuel Tank:
38.50 inches and have a total useable fuel capacity of 228 gals. Jet A weighs 6.7
lbs per gal.
Rear Cockpit Only:
Cargo:
Passenger:
The following calculations are representative only, and may or
may not represent your aircraft.
AFM H8001 SINGLE & DUAL COCKPIT Revision A
FAA APPROVAL DATE: 8/05/2014
S2R-H80 Single & Dual Cockpit
114.0 inches weighing 200 lbs. maximum.
127.0 inches at 170 lbs nominal.
NOTE:
AIRPLANE FLIGHT MANUAL
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