Додатне слике

Додатне слике

“SOVA“ Selective trainer and utility aircraft

U75 A41M "SOVA" is an upgraded version of the basic Utva 75 airplane, intended for initial training (and selection), sport flying and tourism. Optionally the airplane can be used for reconnaissance, aero-photo shooting, and other operations. It can also carry weapons if furnished with appropriate equipment. "SOVA" is a single engine, low wing airplane, full metallic "semimonocoque" type structure, with engine cowling and wing tips made of composite materials. The airplane is a four-seater in "side by side" configuration, with fixed landing gear. The configuration of the landing gear allows landing on concrete and prepared grass runways. The airplane is equipped with single four cylinder, air cooled engine ''LYCOMING IO-390-А3 А6", and with a constant speed propeller "HARTZELL HC-C2YR-1BFP/F 7894".
U75 A41M "SOVA" is designed and manufactured by Utva Aircraft Industry which holds the NCAO Part 21 G Production Organization Approval, and is in process of obtaining the NCAO Part 21 J Design Organization Approval. The airplane is in certification process under EASA CS-23 normal (with mtow = 1250kg), and utility (with mtow = 1050 kg) category.

Weight and dimensions:

  • Maximum takeoff weight 1250 kg / 2755.8 lb
  • Weight of empty aircraft, equipped 750 kg / 1653.5 lb
  • Wing surface area 15.1 m² / 6.4 ft
  • Wing span 9.804 m / 32.2ft
  • Aircraft length (overall) 7.110 m / 23.3 ft
  • Height 3.149 m / 10.3 ft
  • Wheel base 1.945 m /6.4 ft
  • Wheel track 2.584[m]/ 8.5[ft]

Flight performance:

  • Maximum horizontal speed at s/l 230 km/h / 118 knts
  • Stalling speed "flaps up", idle 105 km/h / 54 knts
  • Stalling speed "flaps down", idle 95 km/h / 49 knts
  • Best climb 150 km/h / 77 knts
  • Maximum rate of climb at s/l 3.6 m/s (708 ft/min)
  • Service ceiling 3200 m / 10.500 ft
  • Take-off distance over 15 m (50ft) 690 m / 2260 ft
  • Landing distance from 15 m (50ft) 610 m / 2000 ft
  • Endurance (economy speed) 4.2 hours
  • Flying range 670 km / 362nm

Power plant
Motor Lycoming IO-390- A3 A6

  • Four cylinder
  • Boxer configuration
  • Air cooled, direct injection
  • Maximum constant power, 210 HP (154.4 KW)
  • Cruise power 75%
  • Economy power 65%


  • Two-blade, all-metal, constant speed Hartzell HC-C2YR-1BFP/F7894
  • Maximum RPM (RPM)2700 rpm
  • Diameter 1.98 m

Fuel installation

  • Integral wing fuel tanks 175 lit/46 gal
  • Electric standby pump
  • Three-position valve as a fuel-cutoff valve and for fuel balancing


  • All-metal monocoque type fuselage, with integral center-wing and attachments for the engine mount, wings and tail surfaces
  • All-metal wings, flaps and ailerons, integral fuel tanks are in the wing leading edge, and between spars is the reinforced structure to accommodate pylons for external fuel tanks / armament
  • All-metal horizontal and vertical tail, flaps and control surfaces
  • Engine cowling and wing tips are made of glass-fiber composite.
  • The strength of the airframe with minimized weight has been verified through experimental crushing strength tests.

Landing gear

  • 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.
  • Main wheel tires are 6.00-6-6 ply rating bar while nose wheel tires are 5.00-5-6 ply rating bar
  • Landing gear with low pressure tires enables takeoff and landing at concrete runways or prepared grass runways

Control surfaces and controls

  • The primary controls are doubled. The primary controls are powered mechanically, the rudder and the elevator by control cables, and the flaps are powered by control tubes.
  • The flaps are actuated by way of electric actuators with mechanical synchronous deflection and with the position indicator.
  • All primary control surfaces are equipped with trimmers. Flatteners are installed on the ailerons and on the rudder and trimmers are located on the ailerons, the elevator and rudder.
  • The trimmers are actuated by way of electric actuators, controlled by means of the switches on the control stick and instrument panel with the position indicators in the cockpit.

Other mechanical controls:

  • Engine controls
  • Fuel controls
  • Door lock controls
  • Cockpit heating/cooling controls and windshield anti-fog controls
  • Parking brake control


The cockpit provides:

  • Ergonomic accommodation for 90% of pilots
  • Safe accommodation for 99% of pilots (up to 1000 mm /39" of seat height)
  • Approach vision reserve over 2°
  • Inclined instrument panel
  • Adjustable pedal positions, from the seat
  • Adjustable front seats
  • Front seats designed for accommodation of backpack parachutes in the course of semi-aerobatic training
  • Easy access to the luggage compartment behind the passenger seats, capacity up to 40 kg/88 lb
  • Part of the pilots' windows and the windows in the passenger part of the cockpit are dimmed, with UV protection
  • Large cockpit door, on both sides, opened upwards, enable comfortable entrance both in the pilot and the passenger compartment of the aircraft
  • Modern interior design, standard (training) or luxury version
  • Very wide cockpit (1250 mm/49")
  • Electric air conditioning unit, as an option

Hydraulic system
The hydraulic system is designed only for the disc brakes and the parking brake. Taxi control by way of differential braking.
Electric equipment

  • Electric installation 28V DC
  • Main source: Alternator 2 kW, optional: Alternator 3.5 kW, for the air-conditioner power supply
  • Auxiliary source: 16Ah battery
  • Engine starting by external generator or by battery

External LED lights:

  • Position lights
  • Reflector/taxi lights
  • Anti-collision lights

Interior lights

  • Interior LED lights for the cockpit, instruments and control boxes

Electronic equipment
The aircraft is equipped with modern electronic equipment which meets all the current international standards and provides the following main functions (even in the instrumental flying conditions – IFR):

  • Display of flight parameters on the pilot's and copilot's instrument panels.
  • Two-way radio communication air-to-ground and air-to-air, in VHF band.
  • Intercom communication between the pilot, copilot and two passengers.
  • Satellite navigation by means of GPS receiver.
  • Radio navigation by means of VOR/ILS receiver, marker receiver and DME unit
  • Landing in adverse weather conditions, cat. II, day and night, by the use of existing ILS and GPS equipment.
  • Identification and tracking of aircraft on flight control displays using transponders in S mode.
  • Engine and fuel parameters display and monitoring on one pilot's and co-pilot's display.
  • Display of flight altitude, speed and position of the aircraft on a backup device with autonomous power supply used by the pilot and co-pilot.
  • Emission of signals on emergency frequencies for SAR of the crew in case of an emergency landing.

The mentioned functions are provided using:

  • Intercom-marker PMA 7000 B
  • Two G500 systems, each comprising GDU 620 display (PFD and MFD),
  • Air data computer GDC74A with a temperature probe,
  • Inertial platform GRS77
  • Magnetic detector GMU44
  • Two GPS/NAV/COM systems GTN650
  • Air data computer GDC77
  • DME KN63 system
  • The transponder unit GTX33
  • Engine and fuel parameters display and monitoring unit MVP-50P
  • Electric standby instrument SAI 340
  • Emergency Locator Transmitter (ELT) ME 406

Other equipment

  • GT-50 clock/timer/G-meter
  • Carbon-monoxide detector in the cockpit

The aircraft is designed for training in shooting, rocketing and bombing, upon equipping with the collimator sight and with ordnance suspended on two underwing hardpoints, namely:

  • Machineguns in 7.62 mm cal.
  • Rockets in 7x57 mm cal. and
  • Aircraft bombs weighing up to 50 kg

Safety characteristics:

  • Designed and manufactured in accordance with the highest certification standards EASA CS-23.
  • Equipped for IFR flying, dual pilotage-navigation systems, with two pitot tubes and automatic electronic backup instrument.
  • Wide landing gear tricycle type with overhead protection roll bar against overturning.
  • Aircraft interior and exterior are designed to achieve high efficiency, comfort and safety. Comfortable pilot and instructor seats filled with memory foam enable them to fly for a long period of time without fatigue, and the door opening upwards enable easy wing access and the visibility over 270 ° for observation and surveillance of air traffic.
  • Good stall characteristics with "flaps up" and "flaps down".

With these specifications and integrated modern avionics, the aircraft provides a full pilot training, including:

  • Basic flying,
  • Aerobatic flying (only with the pilot or both the pilot and co-pilot in the front seats),
  • Navigation flying,
  • Basic elements of night flying,
  • Instrument landing, cat. II,
  • Basic elements of shooting, rocketing and bombing

Easy maintenance

  • "SOVA" aircraft design enables easy maintenance and easy access to all main aircraft systems.
  • The mechanic performs a routine 100-hour inspection in about 10 hours, in comparison to the standard 25 hours.
  • Minor defects are easily repaired.

Resource & Reliability

  • Service life is 8.000 flying hours or 25 years,
  • Optimum annual flying hours - 300 h.
  • Overhaul of the airframe and the engine after 2000 flying hours.
  • MTBF of the systems is around 300 hours, and MTBF of the aircraft is around 50 hours.

Maintenance time:

  • Pre-flight inspection and fuel filling, around 20 minutes.
  • Post-flight inspection, around 30 minutes.