Weight And Balance Loading Form - Piper SENECA III Pilot's Information Manual

SECTION 6
PIPER AIRCRAFT
CORPORATION
WEIGHT
AND BALANCE
PA-34-220T,
SENECA
IH
Arm Aft
Weight Datum Moment
Lbs.) Inches) In-Lbs)
Basic Empt
Weight
Pilot
and
Eront Passenger
85 5
(Forward
Eacing)
Passengers (Center Seats)
I 119 I
(Aft Facing) (Optional)
Passengers
(Rear
Seats:
I 15
Passenger
(Jump Seat) (Optional)
i
is i
Baggage {Forward)
(100
Lbs. Max
22 5
Baggage iAft) (100 Lbs Max.)
178.7
Zero Fuel Weight (4470 Lbs. Max
Std) (See equipment list.)
Fuel (93
Gal. Max.)
-
Std.
93 6
(123 Gal, Max.)
-
Opt.
Ramp
Weight (4773
Lbs. Max.)
Fuel Allowance
for Start. Taxi.
-23
950
-2185
Runup
Takeoff
Weight
(4750
lbs. Max.)
The center
of gravity(C.G.)
for the takeoff weight
ofthe
actual
load[ng proMem is at
inches
aft
of the datum line. Locate
this
point (
) on
the
CG
range and
weight graph
\f
this point falls
within the weight
-
C.G. enselope. this loading meets the
weight and
bahnce
requirements
Takeoff
Weight (4750 1 bs. Max.)
Minus Estimated
Fuel Burnoff
95 0
@
Approximately
90 lbs. per hr
Landing
Weight (4513 l.bs. Max.)
Locate the
center
of gravity
for
the landing weight on the C G.
range
and weight graph. If
this
point
fans
within
the weight
C.G.
envelope.
the loading
may
be
assumed acceptable for
landing.
IT IS THE RESPONSIBILITY
OF THE PILOT AND AIRCRAFT OWNER TO INSURE
THAT THE AIRPLANE IS LOAD£D
PROPERLY.
WEIGHT
AND BALANCE LOADlNG FORM
Figure 6-11
REPORT: VB-1110
ISSUED: JANUARY 8, 1981
6-12
REVISED:
AUGUST 9,
1982