TYPE: Four-seat lightplane.

PROGRAMME: Resumption announced in 2003 as a development of earlier two-seat Utva-75 trainer used by air forces and flying clubs of the former Yugoslavia, at which time two prototypes were under construction.

DESIGN FEATURES: Compared to earlier Utva-75, has strengthened fuselage to meet FAR Pt23 requirements and redesigned engine cowling.

FLYING CONTROLS: Conventional and manual. Fluted skin on ailerons, flaps, fin, rudder and elevators; rudder and elevators horn-balanced; ground-adjustable tab on rudder; Flettner trim tab on each aileron; Teleflex actuator for elevator control tab.

STRUCTURE: All-metal semi-monocoque.

LANDING GEAR: Non-retractable tricycle type, with single wheel on each unit, and small tail bumper; oleo-pneumatic shock-absorbers. Tyres, size 7.00-8 on mainwheels; size 6.00-6 on nosewheel; hydraulic brakes.

POWER PLANT: One 224 kW (300 hp) Textron Lycoming IO-540-L1A5D flat-six. Total fuel 153 litres (40.4 US gallons; 33.7 Imp gallons) in integral wing tanks.

ACCOMMODATION: Pilot and three passengers in two pairs of seats; single-piece front windscreen and larger side windows. Separate baggage compartment.

AVIONICS: Integrated system to meet IFR requirements.