ALPHA Electro
www.pipistrel-aircraft.com
REV. 0
POH-167-00-40-150
Introduction
This section describes the procedure for establishing the basic empty weight and moment of the air-
plane. Sample calculations are provided for reference. Specific information regarding the weight and
arm for this airplane as delivered from the factory can be found in the aircraft documentation folder,
look for Weight and Balance Report.
WARNING! It is the responsibility of the pilot to make sure the airplane is loaded properly.
Operation outside of the prescribed weight and balance limitations could result in an accident
and serious or fatal injury.
Weighing procedure - (see also in WBR document)
Make sure all listed aircraft parts and appliances are installed and in position.
Remove all other objects (e.g. tools, rags, tie downs and other items ...). Install batteries. Retract flaps
and leave control surfaces centered.
Level the aircraft inside a closed spaced using a digital level. Calibrate it so that it reads 0
o
when placed
on the levelling surface (i.e the surface the aircraft is on). Then use it to make the tail cone’s center line
parallel to the levelling surface. Do this by placing the level on the upper surface of the tail cone just
fore of the vertical stabilizer and measuring the angle. Do the same on the tail cone’s lower surface.
The aircraft (tailcone centerline) is level once these two readings are the same (or use the tail leveling
tool/template).
Once levelled, read the scale readings and subtract eventual tare weight.
Now record all readings and fill out the bottom table.
The datum is the wing's leading edge at the fuselage root. Calculate the lever arm of CG using
this formula:
Weighing form (EAW and empty CG determination)
Scale reading Tare Net
Right main wheel (GR)
Left main wheel (GL)
G1 = GR + GL
Nose wheel (G2)
Total EAW (GEAW = GR + GL +G2)
Empty CG location (CGmm):
CGmm =
b x G1 - a x G2
(G1 + G2)
Weight and balance
6-2
To Next Page
Loading...
