Classy Aircraft Sova

General information

SOVA is an upgraded four passengers version of the basic UTVA 75 two-seater, intended for initial training (and selection), sport flying (in aircraft sport clubs, agriculture and tourism. It can optionally be used for reconnaissance, patrolling, photo-shooting and other operations. One special advantage of this aircraft version equipped with advanced digital displays is that it can be used for initial training of several trainees, reducing considerably the cost of the training. Basic aircraft versions are certified according to the Federal Aviation Regulations (F.A.R. – Part 23: Airworthiness Standards). This version (SOVA) will be additionally certified according to CS-23 (Certification Specifications for Normal, Utility, Aerobatic, and Commuter Category Airplanes).

The following characteristics and the advanced avionics built in the aircraft; full training of pilots related to the aircraft purpose can be conducted, namely:

  • Basic flying
  • Aerobatic flying
  • Navigation flying
  • Basic elements of night flying
  • Instrument landing, category II

Technical information

The aircraft is equipped with modern electronic equipment meeting all the current international standards, and having the following main functions:

  • Two-way radio communication air-to-ground and air-to-air, UHF band, with simultaneous reception of all audio signals by the instructor and trainees. Quadruple connection enables mutual communication
  • Satellite and radio navigation enabled by the use of satellite navigation receivers and the ground beacon, VOR, DME, ILS and marker receiver.
  • Landing in adverse weather conditions, category II, day and night, using the existing ILS and GPS equipment.
  • Radar identification of aircraft using transponders (S mode operation).

SOVA is a single engine, low-wing, all-metal aircraft, with a “side by side” configuration of seats and fixed landing gear.

Power plant
Motor Lycoming IO-390- A1 B6
  • Four cylinder
  • Boxer
  • Air-cooled, direct injection
  • Maximum constant power . . 210 HP, (154.4 KW)
  • Cruise power 75%, . . . . . . . . . . . 157.5 HP (115.8 kW)
  • Economy power 65%, . . . . . . . . . 136.5 HP (110.4 kW)
  • Two-blade, all-metal, constant speed
  • Maximum RPM . . . . . . . . . . . 2700 rpm
  • Diameter . . . . . . . 1.96 m
Fuel installation
  • Integrated fuel tanks, wing, 175 l
  • Electric standby pump
  • Three-position valve for balance fuel distribution
  • Fuel cutoff valve
The hardness of the airframe with minimized weight has been verified through crushing strength tests
  • All-metal fuselage, skin type, with integrated center wing and attachments for the engine carrier, wings and tail surfaces
  • All-metal wings with integrated fuel tanks
  • All-metal horizontal and vertical tail, flaps and control surfaces
  • Engine and wing tips reinforced with glass-fiber composite.
    The landing gear is fixed, tricycle type. The main legs are rocker arm type, with oleo-nitrogen shock absorbers and disc brakes on main wheels. The nose leg is telescopic and self-centering, main wheels allow differential braking.

Service support

We are able to provide service support through maintenance program with our partner FAA approved aircraft shop in few locations in US.

Exploitation characteristics
  • Service life – 8.000 flight hours or 25 years
  • Optimum annual flying hours – 300 h.
  • General repair of airframe and engine after 2000 flying hours.
  • System mean time between failures (MTBF) is over 300 hours, and MTBF of the aircraft as a whole is over 50 hours.
Maintenance time:
  • Pre-flight inspection and fuel filling, up to 20 minutes.
  • Post-flight inspection, up to 30 minutes.

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