Weight and balance
Introduction
This chapter provides information on aircraft’s weight and balance, which is essential for safe ying
activity.
Weighing procedure
How to weigh the aircraft and later determine the CG correctly:
Make sure all listed aircraft parts and appliances are installed and in position.
Remove all other objects (e.g. tools, mops ...).
Empty fuel tanks except for the unusable fuel.
Fill up engine oil to the top marking.
Retract aps and spoilers, leave control surfaces centred.
Level the aircraft inside a closed space.
To do this, 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 measure and record all readings and ll out the bottom schematic.
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 (GD)
left main wheel (GL)
nose wheel (G2)
total (G = GD + GL +G2)
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