Aerospool WT9 Dynamic LSA / Club, Pilot Operating Handbook

Page: 118 / 204

Page 6-8 EASA Approved Initial issue
6.4 Weight and Balance Determination for Flight
This part describes the procedure for calculating the weight and moment for various phases of a planned flight
and ensuring the center of gravity is within approved limits. To calculate the weight and moment of a loaded aircraft
use a Weight and Balance Loading Form (Chapter 6.4.2).
Aircraft Weight and CG Limits
The charts on Fig. 6-2 (Metric Units) and Fig. 6-3 (U. S. Standard Units) depict the aircraft ’s operational CG envelope in
the terms of CG arm aft of reference datum and as a percentage of the MAC. The relationship between CG arm and
percentage of the MAC is detailed in the Chapter 6.2.3.
Metric Units U. S. Standard Units
Empty weight Max. 410.8 kg Max. 906 lb
Empty CG range
12.5 to 13.5 %MAC
2.637 to 2.648 m (aft of Datum)
12.5 to 13.5 %MAC
103.80 to 104.26 in (aft of Datum)
Basic empty CG
range
12.4 to 13.4 %MAC
2.636 to 2.647 m (aft of Datum)
12.4 to 13.4 %MAC
103.77 to 104.22 in (aft of Datum)
Forward CG
(operating limit)
2.704 m (18.3 %MAC) at 542.5 kg
with straight line taper to
2.748 m (22.0 %MAC) at 600.0 kg
106.48 in (18.3 %MAC) at 1196 lb
with straight line taper to
108.18 in (22.0 %MAC) at 1323 lb
Rearward CG
(operating limit)
2.824 m (28.5 %MAC) at 600.0 kg 111.18 in (28.5 %MAC) at 1323 lb