ALPHA Trainer-POH.pdf - Pipistrel

4-2 ALPHA Trainer
REV. 0 Weight and balance
Introduction
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This section describes the procedure for estabilishing the basic empty weight and moment of the
airplane. 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 prescribed weight and balance limitations could resuld in an accident and
serious or fatal injuty.
Weighing procedure
Make sure all listed aircraft parts and appliances are installed and in position.
Remove all other objects (e.g. tools, rugs, tie downs and other items ...).
Empty fuel tanks except for the unusable fuel, inflate tires to recommended operating pressures.
Fill up engine oil to the top marking.
Retract flaps and leave control surfaces centred.
Level the aircraft inside a closed space - use the provided airfoil template at lower side of the wing
close to the wing root and make sure its straight edge is level (horizontal).
Once leveled, read the scale readings and subtract eventual tare weight.
Now record all readings and fill out the bottom table.
Datum is wing’s leading edge at wing root. Calculate the lever arm of CG using this formula:
Lever arm of CG (X) = ((G 1
/ G) x c) - a
Weighing form
Weighing point and symbol Scale reading Tare Nett
right main wheel (GR)
left main wheel (GL)
G1 = GR + GL
nose wheel (G2)
total (G = GR + GL +G2)