Piper PA-28-236 DAKOTA, Pilot Operating Handbook

Page: 144 / 367

PIPER AIRCRAFT CORPORATION SECTION 6
PA-28-236, DAKOTA WEIGHT AND BALANCE
ISSUED: JUNE 1, 1978 REPORT: VB-910
6-9
REVISED: AUGUST 5, 1983
6.7 WEIGHT AND BALANCE DETERMINATION FOR FLIGHT
(a) Add the weight of all items to be loaded to the basic empty weight.
(b) Use the Loading Graph (Figure 6-13) to determine the moment of all
items to be carried in the airplane.
(c) Add the moment of all items to be loaded to the basic empty weight
moment.
(d) Divide the total moment by the total weight to determine the C.G.
location.
(e) By using the figures of item (a) and item (d) (above), locate a point
on the C.G. range and weight graph (Figure 6-15). If the point falls
within the C.G. envelope, the loading meets the weight and balance
requirements.
Arm Aft
Weight Datum Moment
(Lbs) (Inches) (In-Lbs)
Basic Empty Weight 1780 83.7 148986
Pilot and Front Passenger 340 80.5 27370
Passengers (Rear Seats) 340 118.1 40154
Fuel (72 Gallons Maximum) 432 95.0 41040
Baggage (200 Lbs. Maximum) 119 142.8 16993
Ramp Weight (3011 Lbs. Maximum) 3011 91.2 274543
Fuel allowance for engine start, taxi,
and run-up -11 95.0 -1045
Takeoff Weight
(3000 Lbs. Maximum) 3000 91.2 273498
The center of gravity (C.G.) of this sample loading problem is at 91.2
inches aft of the datum line. Locate this point (91.2) on the C.G. range and
weight graph. Since this point falls within the weight - C.G. envelope, this
loading meets the weight and balance requirements.
IT IS THE RESPONSIBILITY OF THE PILOT AND AIRCRAFT OWNER
TO INSURE THAT THE AIRPLANE IS LOADED PROPERLY.
SAMPLE LOADING PROBLEM (NORMAL CATEGORY)
Figure 6-9