OPERATION MANUAL
SILA 450 c
AERO EAST EUROPE
Date 01.09.2015.
Revision 00
Page | 13
LIMITATIONS
2.6 WEIGHT LIMITS
Maximum take – off weight
472,5 kg
Maximum landing weight
472,5 kg
Maximum empty weight
297,5 kg
Maximum weight in baggage compartment 20kg
Figure 2-4
2.7 CENTER OF GRAVITY LIMITS
Center of Gravity range has two different categories for empty airplane and for different
load cases. Center of Gravity range for empty airplane is calculated for the worst possible
combination of loads from occupants, baggage(if any) and fuel, and considered the worst
combination of weights during flight.
Forward limit C.G. (empty airplane)
23,0% of MAC or 292 mm from leading edge
Aft limit C.G. (empty airplane)
27,0% of MAC or 340 mm from leading edge
Forward limit C.G. (MTOW)
29% of MAC or 368 mm from leading edge
Aft limit C.G. (MTOW)
34% of MAC or 432 mm from leading edge
Figure 2-5
Warning
Aircraft commander is obligate to take care about center of gravity positions by weighing the aircraft
and take care about approved weights for aircraft loadings (if any baggage, crew and fuel)
Picture 2 showing weighing plan of the SILA 450 C, and figure 2-6 showing calculation for determining
Center of Gravity position
Picture 2 – Weighing plan
Figure 2-6: Calculation of Center of Gravity positions
Weighing point
Scale reading R
i
[kg]
TareT
i
[kg]
Net WeightNW
i
= R
i
– T
i
[kg]
Nosewheel
R
N
=
[kg]
T
N
=
[kg]
NW
N
=
[kg]
Left wheel
R
L
=
[kg]
T
L
=
[kg]
NW
L
=
[kg]
Right wheel
R
R
=
[kg]
T
R
=
[kg]
NW
R
=
[kg]
Total weight [lbs] or [kg]
TW = NW
N
+ NW
L
+ NW
R
+ +
TW = [kg]
C.G. position from Datum (Leading edge) [mm]
C.G.=
(𝑅
𝐿
+𝑅
𝑅
)𝑏−𝑅
𝑁∙
𝑎
𝑇𝑊
=
( + )633− 790
𝑇𝑊
= [𝑚𝑚]
C.G. = [mm]
C.G. position [% MAC]
𝐶. 𝐺
̅̅̅̅̅ =
𝐶.𝐺.
𝑀𝐴𝐶
𝑥100 =
1270
∙ 100 = [%]
𝑪. 𝑮
̅̅̅̅̅ = [%]
