Serial Number 1646
Date of Issue: 23 June 2017
Revision - Original
34
[lbs]
[lbs]
[lbs]
X
X
T
T
[
[
i
i
n
n
c
c
h
h
]
]
X
X
T
T
[
[
%
%
]
]
C
C
r
r
e
e
w
w
/
/
F
F
u
u
e
e
l
l
/
/
B
B
a
a
g
g
g
g
a
a
g
g
e
e
180.8
585.3
765.9
14.45
30.8
C
C
r
r
e
e
w
w
/
/
F
F
u
u
e
e
l
l
/
/
B
B
a
a
g
g
g
g
a
a
g
g
e
e
213.6
754.2
967.8
14.33
32.9
C
C
r
r
e
e
w
w
/
/
F
F
u
u
e
e
l
l
/
/
B
B
a
a
g
g
g
g
a
a
g
g
e
e
272.5
1039.8
1312.4
16.38
34.7
C
C
a
a
l
l
c
c
u
u
l
l
a
a
t
t
e
e
d
d
p
p
o
o
s
s
i
i
t
t
i
i
o
o
n
n
o
o
f
f
C
C
.
.
G
G
.
.
i
i
s
s
w
w
i
i
t
t
h
h
i
i
n
n
a
a
p
p
e
e
r
r
m
m
i
i
t
t
t
t
e
e
d
d
r
r
a
a
n
n
g
g
e
e
o
o
f
f
2
2
1
1
,
,
6
6
-
-
3
3
5
5
,
,
6
6
%
%
b
b
S
S
A
A
T
T
.
.
To calculate weight and balance for an actual flight, follow the process shown in the Sample Loading Problem
shown below.
Loading Provisions and Calculations
Figure 1 shows the distance or “ARM” from the datum point, (set at the leading edge of the aircraft) for the
Pilot/Passenger seats, the Fuel Tank and the Aft Baggage Compartment. (NOTE: Items stored in the armrest will be
added to the Pilot/Passenger weight.
Weight
(lbs)
Arm
(inches)
Moment (weight x
Arm)
(Inch-lbs)
Maximum
Allowable
(inch-lbs)
Pilot and Passenger
(to include center console
and door pockets)
20.0
Baggage
50.5
1667
Fuel
13.2
2614
Aircraft Typical
Empty Weight
(includes oil and
unusable fuel)
766
14.45
11069
Total
Calculation of C.G. Position
C.G.(inches) = MOMENT
TOTAL WEIGHT
Calculation of Percent of Mean Aerodynamic Chord
%MAC =
C.G.
47.244 (inches)
Maximum Gross Weight
1320 lbs
Minimum %MAC (Forward C.G.)
21.6 %
Maximum %MAC (Aft C.G.)
35.6 %
%MAC – (Percent Mean Aerodynamic Chord)
