SC-POH-1-1-17
SECTION 6
WEIGHT & BALANCE
Revision: -
Date of issue: 2011-09-01
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6-5
6.5.2 Aircraft C.G. determination
After any changes in equipment or if the aircraft weight is affected by any
alternation or repair, a new weighing and C.G. determination perform as
follows:
Aircraft empty weight C.G. determination
1. Aircraft weighing according to 6.2.
2. Record weight and arm values to the aircraft empty weight C.G. table,
nose wheel arm is negative (-).
3. Calculate and record moment for each of the main and nose wheels using
the following formula:
MOMENT (lb in) = WEIGHT (lb) x ARM (in)
Nose wheel moment is negative (-).
4. Calculate and record total weight and moment.
5. Determine and record empty weight C.G. using the following formula:
M
TE
100
AIRCRAFT EMPTY WEIGHT C.G. = ------- (in) x -------- (%) of MAC
W
TE
MAC
Aircraft empty weight C.G. determination table
NOTE:
Empty weight is including oil, coolant, hydraulic fluid and unusable fuel.
NOTE
Actual Weight and Balance record this aircraft is shown in Section 9,
Supplement No. 02.
AIRCRAFT
EMPTY
C.G.
ITEM
WEIGHT
lb
ARM
in
MOMENT
lb in
RIGHT MAIN
WHEEL
W
R
=
L
R
=
LEFT MAIN
WHEEL
W
L
=
L
L
=
NOSE WHEEL
W
N
=
L
N
=
-
negative arm
-
TOTAL
Empty weight:
W
TE
=
C.G.
= in
% MAC
Aircraft moment:
M
TE
=
4-5
Date of Issue: 12/2007
Revision: 2.0
WEIGHT & BALANCE REPORT
Empty Weight CG Check
Empty weight CG range :
28 to 32 % of MAC
Max. take-off weight :
1 320 [lb]
Maximum useful weight :
W
Max Useful
= W
Max Take-Off
)
W
E
W
Max Useful
=
1320 [lb]
)
842.3 [lb]
= 477.7
[lb]
This useful weight must be never exceeded!
M
E
100
Aircraft Empty CG
= -------- [ in ] x --------- [ % ]
W
E
MAC
ITEM
WEIGHT
[lb]
ARM
[in]
MOMENT
(WEIGHT x ARM)
A
IR
C
R
A
FT
E
MP
TY
CG
RIGHT MAIN
WHEEL
W
R
= 325.2
L
R
= 31.3
10 178.8
LEFT MAIN
WHEEL
W
L
= 318.2
L
L
= 31.3
9 959.7
NOSE WHEEL
W
N
= 198.9
L
N
=
-
28.6
negative arm
-
5 688.5
COMPUTED CG
EMPTY
Empty weight:
W
E
=
842.3
[lb]
CG=
17.2
[in]
29.1
% MAC
Aircraft moment:
M
E
=
14 450.0
4-7
Date of Issue: 12/2007
Revision: 2.0
WEIGHT & BALANCE REPORT
Rear CG Check
WEIGHT
[lb]
ARM
[in]
MOMENT
(WEIGHT x ARM)
EMPTY AIRCRAFT
842.3
--------
14 450.0
PILOT
190.0
27.6
5 244.0
PASSENGER
190.0
27.6
5 244.0
BAGGAGE
COMPARTMENT - A
33.0
51.6
1 702.8
BAGGAGE
COMPARTMENT - B
7.0
70.9
496.3
WING LOCKERS
27.0
23.6
637.2
FUEL TANKS
11.0
7.1
78.1
TOTAL
W
T
=
1 300.3
[lb]
M
T
=
27 852.4
TAKE-OFF WEIGHT 1 300.3
[lb]
CG
=
21.4
[in]
36.2
% MAC
Max. take-off weight :
1 320 [lb]
Max. weight in baggage compartment A+B :
40 [lb]
Max. weight in wing lockers together :
88 [lb]
Operating CG range :
27 to 38 % of MAC
M
T
100
Aircraft CG
= -------- [ in ] x --------- [ % ]
W
T
MAC
Serial No.:
08SC142
Date:
2008-04-23
By:
Otakar Hrabinec
