Evector EV-97 EUROSTAR SL MICROLIGHT - Operating Centre of Gravity range calculation

EV-97 Eurostar SL Microlight Maintenance Manual GEN/EUR/04 Issue 4 41
18.2 Operating Centre of Gravity range calculation
On the basis of moment arms, weights of items, aircraft empty weight and its C of G position it is
possible to calculate the weight and C of G location according to the formula given below:
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 aircraft
Crew
19.69
500
Fuel (0.72 kg/ltr.) 36.22 920
Baggage 50.00 1270
Total Weight
TW=
Σ
W
I
[lbs] or [kg]
Total Moment
TM=
Σ
M
i
[lbs.in] or [kg.mm]
C.G. position from Datum (Leading edge):
C.G.position in % MAC
(MAC ...Mean Aerodynamic Chord = 49.2 in i.e.1250 mm):
C.G.range limits
Empty weight C.G. range (standard equipment) 18±2% MAC or 200 – 250 mm AOD
Loaded aircraft C.G. range 27±7% MAC or 250 – 410 mm AOD
][ ]........[..........
..............
..........
.
. mmorin
WeightTotal
MomentTotal
GC
===
C G
C G
MAC
. .
. .
...................
= ⋅ = ⋅100 100 =................... [% MAC]