Sinus 912 LSA Glider 550 MTOW
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REV. 3
Weights
Sinus 912 LSA weights
WEIGHT
912 LSA 80 HP
standard empty weight
643 lbs (292 kg)
max. takeoff weight (MTOM)
1210 lbs (550 kg)
fuel capacity (full)
2 x7.25/13 US gal
fuel capacity (usable)
14.5/24.5 US gal (55/93 L)
max. fuel weight allowable
101/167 lbs (46/76 kg)
maximum useful load
568 lbs (258 kg)
minimum combined cockpit crew weight
119 lbs (54 kg)
maximum combined cockpit crew weight
519 lbs (236 kg)
luggage weight
typically 55 lbs (25
kg), see page p.51
for exact values.
Allowance depends on
configuration, see weight
and balance.
WARNING!
Should one of the above-listed values be exceeded, the other MUST be reduced
in order to keep MTOM below 1210 lbs (550 kg). Pay special attention to luggage weight as this
is the only applicable mass on the airframe that has an influence on centre of gravity. Exceeding
baggage weight limits can shift aircraft’s balance to the point when the flight becomes uncon-
trollable! More information on baggage allowance can be found in chapter “Weight and Balance”.
Luggage access if via the optional side access door, for larger items the seat folds and the luggage
compartment becomes reachable.
Centre of gravity range
•
Aircraft's safe centre of gravity position ranges between 20% and 39% of mean aero-
dynamic chord.
•
Centre of gravity point ranges between 243 mm (9.5'') and 408 mm (16.0'') backwards
of datum. Datum is wing's leading edge at the fuselage root.
G-load factors
max. positive wing load:
+ 4 G
max. negative wing load:
– 2 G
These values correspond to ASTM standards for LSA’s. All parts have been tested to a safety factor of
a minimum 1.875, meaning they were subjected to at least a load of 7.5 G
1-6
General
