SECTION 6
PA-28-181, ARCHER III WEIGHT AND BALANCE
SECTION 6
PA-28-181, ARCHER III WEIGHT AND BALANCE
ISSUED: JULY 12, 1995 REPORT: VB-1611
6-9
ISSUED: JULY 12, 1995 REPORT: VB-1611
6-9
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.
The center of gravity (C.G.) of this sample loading problem is at 91.5 inches
aft of the datum line. Locate this point (91.5) 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 ENSURE THAT THE AIRPLANE IS LOADED PROPERLY.
*Utility Category Operation - No baggage or rear passengers allowed.
Arm Aft
Weight Datum Moment
(Lbs) (Inches) (In-Lbs)
Basic Empty Weight 1590.0 87.5 139125
Pilot and Front Passenger 340.0 80.5 27370
Passengers (Rear Seats)* 340.0 118.1 40154
Fuel (48 Gallon Maximum) 288.0 95.0 27360
Baggage (200 Lbs. Maximum)* 142.8
Ramp Weight (2558 Lbs. Normal,
2138 Lbs. Utility Maximum) 2558 91.5 234009
Fuel Allowance
For Engine Start, Taxi and Run Up -8 95.0 -760
Takeoff Weight (2550 Lbs. Normal,
2130 Lbs. Utility Maximum) 2550.0 91.5 233249
SAMPLE LOADING PROBLEM (NORMAL CATEGORY)
Figure 6-9
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.
The center of gravity (C.G.) of this sample loading problem is at 91.5 inches
aft of the datum line. Locate this point (91.5) 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 ENSURE THAT THE AIRPLANE IS LOADED PROPERLY.
*Utility Category Operation - No baggage or rear passengers allowed.
Arm Aft
Weight Datum Moment
(Lbs) (Inches) (In-Lbs)
Basic Empty Weight 1590.0 87.5 139125
Pilot and Front Passenger 340.0 80.5 27370
Passengers (Rear Seats)* 340.0 118.1 40154
Fuel (48 Gallon Maximum) 288.0 95.0 27360
Baggage (200 Lbs. Maximum)* 142.8
Ramp Weight (2558 Lbs. Normal,
2138 Lbs. Utility Maximum) 2558 91.5 234009
Fuel Allowance
For Engine Start, Taxi and Run Up -8 95.0 -760
Takeoff Weight (2550 Lbs. Normal,
2130 Lbs. Utility Maximum) 2550.0 91.5 233249
SAMPLE LOADING PROBLEM (NORMAL CATEGORY)
Figure 6-9
To Next Page
Loading...
