Pipistrel 1001 AT 912 LSA, Pilot Operating Handbook

Page: 126 / 182

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 takeoff
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.