6-4
PAGE
ALPHA Trainer LSA
Pilot Operating Handbook
POH-162-00-40-001
PAGE REV. 0
SECTION 6
WEIGHT AND BALANCE
6.2 C.G. SAMPLE CALCULATION
The calculation below is an example of how to calculate the aircraft’s takeo
weight and C.G.. Except for the arm values in italic font, the values do not
apply to any particular aircraft and are for illustration purposes only. The arm
values in italic font are accurate and shall be used for any preflight calcu-
lations. The calculation results (i.e. Total weight and C.G.) shall be entered
into the weight and balance chart in section 6.3, to determine whether the
aircraft is within the flight limits prescribed in section 2.6.
NOTE: Calculate the moment for each item by multiplying its weight by its
arm. Add up the moments to get the total moment and then divide by the
total weight to get the C.G..
WEIGHT ARM MOMENT
[lbs] ([kg]) [inches]([mm])
[lbs*inches]
([kgmm])
Aircraft empty weight 647.6 (293.6)* 10 (254)*
6476
74574.4
Pilot 154 70 14.5 (370)
2233
25900
Co-pilot 176 80 14.5 (370)
2552
29600
Fuel 79 36 44.5 (1130)
3515.5
40680
Baggage compartment 22 10 36.6 (930)
805.2
9300
Total weight / moment 1078.6 489.6 -
15581.7
180054.4
C.G. - 14.4 (367.8)
* These values are to be obtained from the applicable aircraft’s weight and
balance report.
NOTE: CG
%MAC
= 100 x (CG
mm
- 40) / 900.
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