Aircraft Operating Instructions (AOI)
Type:
CT
Series:
CTLS
LSA
Page: 6-7
AU 010 11000
Revision No. 6
Date: 05 Feb 2009
375
575
550
525
500
475
450
425
400
600
[kg]
350
325
300
1
00
120
140
160
180
200
2
20
240
260
2
80
300
[k
g*m]
80
Fli
g
ht
M
a
ss M
oment
Flig
ht Mass
0.2
82
m
11
.1
in
P
e
rm
is
s
ible
Mom
e
nt Ra
nge
0.
47
8
m
18
.8
in
0.3
00
m
11
.8
in
0.3
50
m
13
.8
in
0.4
00
m
15
.7
in
0.4
50
m
17
.7
in
80
0
1.20
0
1.15
0
1.10
0
1.05
0
1.00
0
95
0
90
0
85
0
1.35
0
[lb]
75
0
70
0
66
0
1.30
0
1.25
0
8.000
10.0
00
1
2.00
0
14.0
00
1
6.00
0
18
.000
20.00
0
22.0
00
2
4.00
0
26
.000
[i
n
*lb]
625
fo
rw
ard
li
mi
t
re
ar
li
m
it
max.
permitted
flight mas
s
600 kg
(1320
lb)
375
575
550
525
500
475
450
425
400
600
[kg]
350
325
300
1
00
120
140
160
180
200
2
20
240
260
2
80
300
[k
g*m]
80
1
00
120
140
160
180
200
2
20
240
260
2
80
300
[k
g*m]
80
Fli
g
ht
M
a
ss M
oment
Flig
ht Mass
0.2
82
m
11
.1
in
P
e
rm
is
s
ible
Mom
e
nt Ra
nge
0.
47
8
m
18
.8
in
0.3
00
m
11
.8
in
0.3
50
m
13
.8
in
0.4
00
m
15
.7
in
0.4
50
m
17
.7
in
80
0
1.20
0
1.15
0
1.10
0
1.05
0
1.00
0
95
0
90
0
85
0
1.35
0
[lb]
75
0
70
0
66
0
1.30
0
1.25
0
8.000
10.0
00
1
2.00
0
14.0
00
1
6.00
0
18
.000
20.00
0
22.0
00
2
4.00
0
26
.000
[i
n
*lb]
8.000
10.0
00
1
2.00
0
14.0
00
1
6.00
0
18
.000
20.00
0
22.0
00
2
4.00
0
26
.000
[i
n
*lb]
625
fo
rw
ard
li
mi
t
re
ar
li
m
it
max.
permitted
flight mas
s
600 kg
(1320
lb)
The example shown in this diagram represents the verification of the mass and mass
moment values achieved as by the example shown in the analysis table. The aircraft
with no fuel is represented by the values 415 kg (
916 lb
) and 165 kg*m (
14.338 in*lb
).
The aircraft takeoff fuel is represented by the values 458 kg (1.011
lb
) and 174 kg*m
(
15.127 in*lb
). Both values are within the allowed range. The two center of gravity
positions can be determined as 0,380 m (
15,0 in
) and 0,400 m (
15,7 in
)
Example 1:
mass moment with
empt
y f
u
el t
a
nks
Example 2:
mass moment with
ful
l fue
l ta
nk
s
