XtremeAIR XA41, Maintenance Manual

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Maintenance Manual XA41/XA42
AMM-XA42-0040-001 C.00
Page 4 Page date:
Chapter 08 25.09.2018
WARNING
08-20-02 Center of Gravity
To calculate the center of gravity, refer to the figure below:
Figure 08-2: Center of Gravity calculation
The moment arms A and B are constant values:
XA42: A = 112 (mm)
B = 4475 (mm)
XA41: A = 120 (mm)
B = 4225 (mm)
For mass M
1,2,3
and the weighing procedure, refer to chapter 08-20-01.
Calculate the center of gravity X
S
of the empty aircraft as follows:
X
S
= (A * M
1
+ A * M
2
+ B * M
3
) / M
Only operate the aircraft in the permitted range of mass and center of gravity limits. This will
give good flight performance, good handling qualities and is also necessary for flight safety.