Cozy III
Pilot’s Operating Handbook Page 37
WEIGHT AND BALANCE
Every aircraft has an acceptable c.g. (center of gravity) range
which is determined by the designer and confirmed by flight
testing, within which the aircraft has positive stability, predictable
performance, and can be operated safely. It is a basic
requirement for obtaining a pilot's license that the pilot be familiar
with c.g. calculations and be able to perform them correctly. It is
the responsibility of every pilot to load his aircraft in such a way
that the c.g. is in the acceptable range, using ballast if
necessary. Empty weight and empty c.g. location are
determined before the first flight by weighing. It must be up-
dated and revised whenever new, permanent equipment is
added; i.e., wheel pants, spinner, different propeller, instruments,
upholstery, etc.
Loading data and sample calculations are shown below. Be sure
you use empty weight and moment data for your aircraft
determined by actual weighing. There can be considerable
builder differences, depending upon workmanship and
equipment. You can use the simple loading graphs provided for
routine service use, but to develop an accurate c.g. location, use
the mathematical formula and your pocket calculator with the
weight vs fuselage station chart. Add up the weight and moment
totals for your load as shown in the sample problems. Then
divide the total moment by the total weight, to get the loaded c.g.
position fuselage station (inches aft of the datum, F.S. 0.0).
FORMULA
weightloadedtotal
momentsalloftotal
positiongc
.. =
Empty moment is determined by weighing aircraft.
Pilot moment ................................................... (pilot weight x 59)
Front passenger moment .....................(passenger weight x 59)
Nose ballast moment .................................... (ballast weight x 8)
Rear passenger(s) moment ............... (passenger weight x 103)
Fuel moment ........................................ (fuel gallons x 6 x 104.5)
Oil moment ................................................ (oil quarts x 1 x 142)
Total loaded weight = empty weight + pilot + passengers +
nose ballast + fuel + oil
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