ATEC Atec Wheelchair ATEC 212 SOLO ROTAX 912 UL User Manual
35
9.5.
Centre of gravity determination
The aircraft has to be weighed at flight position including pilot and fuel.
Weight on main wheels
G
1
(kg)
Weight
on
tail
wheel
G
2
(kg)
Total
weight
G
=
G
1
+ G
2
(kg)
Wheel base
x
MW-TW
= 3,7
(m)
Distance from main wheel centre to leading edge
of wing in root point
of wing in root point
x
MW-LE
= 0,19
(m)
CG distance from main wheel centre
x
MW-CG
= G
2
* 3,7 / G
(m)
Length
of
MAC
b
MAC
= 1,032
(m)
Length of wing chord in the root area
b = 1,19
(m)
Back-swept
MAC
displacement
s
y
= 0,088
(m)
CG distance from leading edge of wing
in
in
root
point
x
LE-CG
= x
MW-LE
+ x
MW-CG
=
=
0,19
+
3,7
*
G
2
/ G
(m)
Distance from CG to leading edge of MAC
x
CG-MAC
= x
LE-CG
– s
y
=
= 0,102 + 3,7 * G
2
/ G
(m)
x
CG-MAC%
= x
CG-MAC
* 100 / 1,032 =
=9,884
+
358,5
*
G
2
/ G
(%)
9.6.
Useful weight, weight table
Useful weight is a difference between maximum take-off weight and the weight of empty
aircraft.
The useful weight by empty weight ………………………. kg is ………………………. kg.
The weight table
aircraft.
The useful weight by empty weight ………………………. kg is ………………………. kg.
The weight table
Fuel tank 50 l
1 l = 0,775 kg
Pilot weight kg
incl. 5 kg luggage
CG % MAC
Total weight
of aircraft kg
¼ ………. 12,5 l
½ ………. 25,0 l
¾ ………. 37,5 l
1 ……….. 50,0 l