Piper SENECA III - Sample Loading Problem

PIPER
AIRCRAFT
CORPORATION
SECTION
6
PA-34-220T.
SENECA
Ill
WEIGHT
AND BALANCE
Arm
Alt
Weight
Datum Moment
(Lbs.) (Inches)
(ln-Lbs)
Basic Empty
Waght
3212
88.5 284262
Pilot and
Front
Passenger
340
85.5 29070
Passengers
(Ce
mer
Scats)
| 18.1
(Forward
Fac.ng)
Passengers
(Cemer
beats)
236 I 19.!
(Aft
FacingHOpdanal)
Passengers
i
Rear
Seas)
340
1516 53585
Passenger
(Jump
Sea
(Optional)
I18 i
Baggage
(Forward) HOG
Lbs.
Max
100
22,5 2250
Baggage
(Aft)
(100
I
.
Max]
178 7
Zero
Fuel
Weight
(41
0
Lbs
Max
4228
94
0 397275
Std)
(See
equipment
listJ
Fuel
(93
GaL
Max
i
-
Std.
545 936 51012
(123
Gal.
Max
)
-
Opt.
Ramp
Weight
(4"^3
Lbs.
Max
4773
939 448287
Fuel
Allowance
for
Sort. Tax
-23
95.0
-2l85
Runup
Takeoff
Weight
14250
lbs.
Max)
4750 93.9
446102
The
center
of gran)
(C.G.)
of
this
sample
loading
problem
is
at
939
inches
aft
of
the
datum hoe.
Locate
tha
point
(93.9)
on
the
C.G
range
and weight
graph. Since
this
point
falls
with.in
the
weight
-
C.G.
envelope,
this
loading
meets
the
weight and
balance
requirements.
Takeoff Weight
is?50
Lhs.
Maxl
4750 93.9
6102
Minus Estimated
Fue
Burnoff
-450
95.0
42750
@
Approxtmately
90 lbs.
per
br.
Landing
Weight
14513
Lbs,
Max.)
4300 93.8
403352
Locate
the
center
of
gravity for
the
landing
weight
on
the
C.G.
range
and weight
graph.
If
this
point
fals
within the
weight
C.G
envelope,
the
loading
may
be assumed acceptable
for
landing.
IT IS
THE
RESPONSIBILITY
OF
THE
PlLOT AND
AIRCRAFT
OWNER
TO
INSURE
THAT
THE
AIRPLANE
IS
LOADED
PROPERLY.
SAMPLE
LOADING
PROBLEM
Figure
6-9
ISSUED:
JANUARY 8,
1981
REPORT: VB-1110
REVISED:
AUGUST 9,
1982
6-11