XtremeAIR XA42, Flight Manual

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Airplane Flight Manual XA42
AFM-XA42-0040-002-A.01
Page 2 Page date:
Chapter 06 EASA approved 24.01.2011
6.2.1 OWNERS WEIGHT AND BALANCE RECORD
Enter all weight change data from aircraft log book in the table below.
XA42 S/N:
Date
Description of
modification
Weight change
Added (+), Removed (-)
Operational empty
weight
Weight
kg
Arm
m
Moment
kg / m
Weight
Kg
Moment
kg * m
Empty weight as
delivered
─── ─── ───
6.3 CENTER OF GRAVITY CALCULATION (SAMPLE)
6.3.1 Sample
Left main wheel: M
lmw
= 294.0 kg
Right main wheel: M
rmw
= 305.4 kg
Tail wheel: M
tw
= 53.7 kg
Empty weight: M
E
= M
lmw
+ M
rmw
+ M
tw
= 653.1 kg
Main wheels – vertical reference plane: A = 118 mm
Tail wheel - vertical reference plane: B = 4488 mm
Center of gravity, Empty aircraft X
E
= 477 mm