Weight And Balance Determination For Flight - Piper PA-28-161 Pilot Operating Handbook

PIPER AIRCRAFT CORPORATION
PA-28-161, WARRIOR II
SECTION 6
WEIGHT AND BALANCE
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)
(ln-Lbs)
Basic Empty Weight 1500
85.9 128850
Pilot and Front Passenger 340.0
80.5
27370
Passengers (Rear Seats)* 340.0
118.1
40154
Fuel (48 Gallon Maximum) 267
95.0
25365
Baggage* (200 Lbs. Maximum) 142.8
Ramp Weight (2447 Lbs. Normal,
2027 Lbs. Utility Maximum) 2447 90.6
221739
Fuel Allowance
For Engine Start, Taxi and Run Up -7
95.0 -665
Takeoff Weight (2440 Lbs. Normal,
2020 Lbs. Utility Maximum) 2440 90.6
221074
The center of gravity (C. G.) of this sample loading problem is at 90.6 inches
aft of the datum line. Locate this point (90.6) 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.
*Utility Category Operation - No baggage or aft passengers allowed.
SAMPLE LOADING PROBLEM (NORMAL CATEGORY)
Figure 6-9
ISSUED: AUGUST 13, 1982
REVISED: JULY 15, 1983
REPORT: VB-1180
6-11