Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS
ATEC v.o.s., Libice nad Cidlinou, Czech Republic
Page 46 of 59
8.5.
Weight Envelope
A = crew 70 kg, fuel 100 L
B = crew 70 kg, fuel 0 L
C = crew 200 kg, fuel 100 L
D = crew 70 kg, fuel 0 L
A
’
= crew 70 kg, fuel 100 L, luggage 20 kg
B
’
= crew 70 kg, fuel 0 L, luggage 20 kg
C
’
= crew 185 kg, fuel 100 L, luggage 20 kg
C
’’
= crew 200 kg, fuel 80 L, luggage 20 kg
D
’
= crew 200 kg, fuel 15 L, luggage 20 kg
D
’’
= crew 200 kg, fuel 0 L, luggage 17 kg
8.6.
Centre of gravity determination
The aircraft has to be balanced in
“
flight position
”
including crew and fuel.
Weight on main wheels
G
1
(kg)
Weight on nose wheel
G
2
(kg)
Total weight G
1
+ G
2
G = G
1
+ G
2
(kg)
Distance from main wheel axis to nose wheel axis
x
MW-FW
= 1,43
(m)
Distance from main wheel axis to wing leading
edge in the root area
x
MW-LE
= 0,75
(m)
Distance of the CG from main wheel axis
x
1
= G
2
* x
MW-FW
/ G
(m)
Length of MAC
b
MAC
= 1,112
(m)
Length of wing chord in the root area
b = 1,300
(m)
Back-swept MAC displacement
s
y
= 0,19
(m)
Distance from CG to leading edge
x
2
= x
MW-LE
–
X
1
(m)
Distance from CG to leading edge of MAC
x
3
= X
2
–
s
y
(m)
Distance from leading edge in % b MAC
x
CG-MAC%
= X
3
* 100 / 1,112
(%)
Front CG
Rear CG
% MAC
