AlrcraR Publicalions
Piper Comanche
250
(Early Model)
Section
-
6
Weight and Balance
CENTER
OF GRAVITY
DATA
Basic Empty Measurement:
Center of Gravity
(Af?
of Datum)
.............................................................................
in
Moment
.......................
....
..
.....
....................................................................
in lb
.........................
Moment Increase With Landing Gear Retracted
......................
....
1266.0 in lb
Normal Category
Weight
Arm
Forward Limit
Arm
Rearward Limit
Pounds Inches
Aft
of Datum Inches
Aft
of Datum
2,800 87.7
2,400 82.5
1,900 or Less 80.5
**
NOTE
**
Straight line variation exists between the points given.
Datum is located 79 inches ahead of wing leading edge at station 65.5 (point of intersection of
straight and tapered sections).
STATIONS
(Arm
Aft
of Datum)
.........................................................................................
Engine Oil
.........................
..
28.0
in
Front Seat Passengers
.......................................................................................................
84.8 in
.................................................................
Basic Fuel
-
Internal Tanks
........................
..
90.0
in
................................................................................................
Rear Seat Passengers
11 8.5 in
.................................................................................................
Baggage Compartment 142.0 in
WEIGHT
AND
BALANCE DETERMINATION
FOR
FLIGHT
1.)
Add the weight of all items to be loaded to the airplane's basic empty weight.
2.)
Multiply the weight of each item by the stations
arm
to determine the moment of all items.
3.)
Add the moment of all items to be loaded to the basic empty weight moment.
4.)
Divide the total moment by the total weight to determine the C.G. location with landing gear
extended.
5.)
Add the moment increase with landing gear retracted
6.)
Divide the new total moment by the total weight to determine the C.G. location with landing
gear retracted.
7.)
Determine that total weight and C.G. meet weight and balance requirements
Copyright:
1993
Page
6-5
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