Atec ATEC 212 SOLO ROTAX 912 UL Centre of gravity determination, Useful weight, weight table

9.5.Centre of gravity determination

The aircraft has to be weighed at flight position including pilot and fuel.

Weight on main wheels Weight on tail wheel Total weight

Wheel base

Distance from main wheel centre to leading edge of wing in root point

CG distance from main wheel centre Length of MAC

Length of wing chord in the root area Back-swept MAC displacement

CG distance from leading edge of wing in root point

Distance from CG to leading edge of MAC

G1	(kg)
G2	(kg)
G = G1 + G2	(kg)
xMW-TW= 3,7	(m)
xMW-LE= 0,19	(m)
xMW-CG= G2 * 3,7 / G	(m)
bMAC = 1,032	(m)
b = 1,19	(m)
sy = 0,088	(m)
xLE-CG = xMW-LE + xMW-CG =
= 0,19 + 3,7 * G2 / G	(m)
xCG-MAC = xLE-CG – sy =
= 0,102 + 3,7 * G2 / G	(m)
xCG-MAC%= xCG-MAC* 100 / 1,032 =
=9,884 + 358,5 * G2 / G	(%)

9.6.Useful weight, weight table

Useful weight is a difference between maximum take-off weight and the weight of empty aircraft.

The useful weight by empty weight ………………………. kg is ………………………. kg.

The weight table

Fuel tank 50 l	Pilot weight kg	CG % MAC	Total weight
1 l = 0,775 kg	incl. 5 kg luggage		of aircraft kg
¼ ………. 12,5 l
½ ………. 25,0 l
¾ ………. 37,5 l
1 ……….. 50,0 l

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