ORLI
Č
AN M-8 EAGLE
PILOT'S OPERATING
REVISION NO. 05
DATE OF ISSUE: MAY 02,
WEIGHT AND BALANCE
PAGE
OF
65
67
4.
DETERMINATION OF PRE-FLIGHT CG
To calculate weight and balance for an actual flight, follow the process shown in the Sample Loading
Problem shown below.
The included table 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 Baggage Compartment.
Calculation of C.G. position
Percent calculation of Mean Aerodynamic Chord
WEIG
HT
[LB
S]
ARM
[INCHE
S]
MOMENT
(WEIGHT X
ARM) [INCH-
LBS]
MAXIMU
M
ALLOWA
B
L
E
[ I N C H -
LBS]
PILOT AND PASSENGER
(INCLUDES DOOR
POCKETS)
397,8
20,09
7 991,8
9 745,7
BAGGAGE
33,0
46,61
1 538,1
1 538,1
FUEL
90,0
14,86
1 337,4
2 360,0
AIRCRAFT TYPICAL EMPTY
WEIGHT (INCLUDES OIL AND
UNUSABLE FUEL)
802,2
15,65
12 554,4
12 554,1
TOTAL
1 323,0
17,70
23 421,7
MOMENT
C.G. [inches] =
TOTAL
WEIGHT
C.G.
% MAC =
%MAC – (Percent Mean Aerodynamic
Chord)
47.36
[inches]
MTOW
1320 lbs
MINIMUM %MAC (FORWARD C.G.)
23 %
MAXIMUM %MAC (AFT C.G.)
37 %
WARNING!
MAKE SURE THAT THE BAGGAGE IS PLACED FIXED INSIDE THE BAGGAGE
AREA. MOVEMENTS OF BAGGAGE IN-FLIGHT WILL CAUSE SHIFTS OF
CENTER OF GRAVITY!
Summary of Contents for M-8 EAGLE 2022
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