Piper WARRIOR III PA-28-161 Pilot Operating Handbook page 19

PIPER AIRCRAFT CORPORATION
PA-28-161, WARRIOR III
Moment
Center of Gravity
(C.G.)
C.G. Arm
C.G. Limits
Usable Fuel
Unusable Fuel
Standard Empty
Weight
Basic Empty
Weight
Payload
Useful Load
Maximum Ramp
Weight
ISSUED: JULY 1, 1994
The product of the weight of an item
multiplied by its arm. (Moment divided by
a constant is used to simplify balance
calculations by reducing the number of
digits.)
The point at which an airplane would
balance if suspended. Its distance from the
reference datum is found by dividing the
total moment by the total weight of the
airplane.
The arm obtained by adding the airplane's
individual moments and dividing the sum
by the total weight.
The extreme center of gravity locations
within which the airplane must be operated
at a given weight.
Fuel available for flight planning.
Fuel remaining after a runout test has been
completed in accordance with govern-
mental regulations.
Weight of a standard airplane including
unusable fuel, full operating fluids and full
oil.
Standard empty weight plus optional
equipment.
Weight of occupants, cargo and baggage.
Difference between takeoff weight, or ramp
weight if applicable, and basic empty
weight.
Maximum weight approved for ground
maneuver. (It includes weight of start, taxi
and run up fuel.)
SECTION 1
GENERAL
REPORT: VB-1565
1-9