A
A
I
I
R
R
P
P
L
L
A
A
N
N
E
E
T
T
E
E
C
C
H
H
N
N
I
I
C
C
A
A
L
L
D
D
E
E
S
S
C
C
R
R
I
I
P
P
T
T
I
I
O
O
N
N
,
,
O
O
P
P
E
E
R
R
A
A
T
T
I
I
N
N
G
G
,
,
M
M
A
A
I
I
N
N
T
T
E
E
N
N
A
A
N
N
C
C
E
E
A
A
N
N
D
D
R
R
E
E
P
P
A
A
I
I
R
R
M
M
A
A
N
N
U
U
A
A
L
L
3-23
Document No.:
EV97SLNOEN
Date of Issue:
02/2008
Revision:
-
3.6.2 Operating C.G. Range calculation
On the basis of knowledge of arms, weights of items, airplane empty weight and the C.G. position
it is possible to calculate weight and C.G. position according to below given formula:
Item
Arm to the Datum
(Leading edge)
C.G.
i
Weight
W
i
Moment
M
i
[in]
[mm]
[lbs]
or
[kg]
[lbs.in]
or
[kg.mm]
Empty airplane
Crew
19.69
500
Fuel
(
6 lbs/ USGAL
)
(0.72 kg/ltr.)
36.22
920
Baggage
50.00
1270
Total Weight
TW=
W
i
[lbs]
or
[kg]
Total Moment
TM=
M
i
[lbs.in]
or [kg.mm]
C.G. position from Datum (Leading edge):
]
[
]
........[
..........
....
..........
..........
.
.
mm
or
in
Weight
Total
Moment
Total
G
C
C.G.position in % MAC
(MAC ...Mean Aerodynamic Chord =
49.2 in
i.e.1250 mm):
C G
C G
MAC
. .
. .
...................
100
100 =................... [% MAC]
C.G.range limits
Empty weight C.G. range (standard equipment) ........................ 18
±2
% MAC
Operating C.G. range................................................................ 20
÷34
% MAC