PIPER
AIRCRAFT CORPORATION
PA-28-161, WARRIOR
II
SECTION
1
GENERAL
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: AUGUST 13,
1982
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.)
REPORT:
VB-1180
1-9
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