“AERO” Sp. z o.o.
SECTION 6
AT-3 R100
WEIGHT AND BALANCE
JULY, 2010
Page 6-7
AEROPLANE FLIGHT MANUAL
Calculation Method
From the table 6.3: “Weight and Balance Schedule” the actual weight
and moment of the empty aeroplane should be read off. If on the rear
wall of the cockpit is installed the collapsible tow bar to the weight of
empty aer1,5 kg should be added and 2,6 kgm should
be increased.
Values of the moments should be calculated on the basis of the following
formula, multiplying the weight by the appropriate arm:
Moment of the pilot and passenger:
M
crew
[kgm]
= 0.60
(arm)
x Q
crew
Moment of the luggage:
M
lugg
[kgm]
= 1.125
(arm)
x Q
lugg
Moment of the fuel
M
fuel
[kgm]
= -0.257
(arm)
x Q
fuel
where: Q = weight [kg]
When calculating the Centre of Gravity, the changes in the weight of oil
and cooling liquid can be ignored since the difference of 0.5l (0.45kg)
between their max and minimum levels is insignificant.
Weights and moments should be calculated according to the following
table:
Aircraft Loading Example
Your Aircraft Loading
Moment [kgm] Weight
[kg]
Arm
[m]
Moment [kgm]
Weight
[kg]
Arm
[m]
(+)
(-)
(+)
(-)
Empty aircraft
358
91.3
Fuel 0.72 kg/l)
kg/l)
43.2
-0.257
-11.1
-0.257
Pilot +Passenger
142
0.6
85.2
0.6
Luggage
14
1.125
15.8
1.125
Subtotals
557.2
192.3
-11.1
Total weight,
arm & moment
557.2 0.325*
181.2
* total moment divided by total weight = total arm (see below)
9
