Computer Testing Supplement for IA.indb - Aviation Supplies ...

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DATUM
D
C.G.
L
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NOSE WHEEL TYPE AIRCRAFT
DATUM LOCATED FORWARD OF THE
MAIN WHEELS
C.G. = D
F x L ( W )
C.G.
L
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D
EXHIBIT 11
Empty weight center-of-gravity formulas.
DATUM
NOSE WHEEL TYPE AIRCRAFT
DATUM LOCATED FORWARD OF THE
MAIN WHEELS
C.G. = _ (D +
F x L
W )
DATUM
D
FIGURE 13.4.—Empty weight center-of-gravity formulas.
TAIL WHEEL TYPE AIRCRAFT
DATUM LOCATED FORWARD OF THE
MAIN WHEELS
C.G. = D +
R x L ( W )
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D
C.G.
C.G.
L
DATUM
TAIL WHEEL TYPE AIRCRAFT
DATUM LOCATED FORWARD OF THE
MAIN WHEELS
C.G. = _ D + R x L ( W )
CG = Distance from datum to center of gravity of the aircraft.
W = The weight of the aircraft at the time of weighing.
D = The horizontal distance measured from the datum to the main wheel weighing point.
L = The horizontal distance measured from the main wheel weighing point to the nose or
tail weighing point.
F = The weight at the nose weighing point.
R = The weight at the tail weighing point.
L
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