“UTVA 75“


Time-tested utility and initial training all-metal classic

UTVA 75 is all metal, low-winged, propeller-driven, single-engined utility airplane with two side-by-side seats in a spacious cabin with excellent visibility. It has non-retractable landing gear and is equipped with control-navigational equipment. The airplane meets the requirements of FAR Part 23 (utility category) with +6g/-3g limit loads.

It is designed to comply specially with the criteria of simplicity, safety, maneuverability and economy, in partnership with Belgrade Institute for Mechanical Engineering, Aeronautics Institute “Žarkovo” and “Prva Petoletka” from Trstenik.

Thanks to the incomparable qualities built into UTVA 75: low fuel consumption, short take-off and landing, easy maintenance and servicing, strength and safety, UTVA 75 is intended for elementary training of pilots and acrobatics, tow of gliders, instrumental and visual flight by night, as well as for training.

First prototype took off on 19th May, 1976. and the second one in March 1977. The manufacturing in series has begun in September 1978.

Due to the incredible performances of the airplane, it won the prize at Precision Flying Championship in Sweden, in 1982. UTVA’s experts and designers team won the FAI prize.

From 1978 UTVA 75 founds its use in almost all Yugoslav Aircraft Association Organizations.

Power plant:
  • one 134 kw (180 Hp), 2700-1 AVCO LYCOMING IO-360B 1F flat-four, direct drive, horizontally opposed, air cooled engine equipped with a BENDIX RSA 5AD1 fuel injector.
  • two-blade metal variable-pitch propeller HARTZELL HC-C2YK-1 BF/F 7666 A with Woodward B 210681 propeller governor.
Airplane structure

UTVA 75 is strong, the all-metal construction and completely corrosion-proofed.

The wings:

cantilever, rectangular, with main and aux. wing spar and the integral fuel cells located between them.

dihedral: 6°, NACA 652 415 wing section.

Ailerons and flaps:

the trailing-edges carry ailerons and flaps which are interchangeable because of the same construction. There is one underwing hardpoint on each wing for drop tanks carriage or additional weapon stores. Balancing tab on each aileron.

The fuselage:

conventional all metal semi monocoque structure, 11 frames, 1 partial bulkhead and several stringers.

The tail:

cantilever, all metal structure with swept back vertical surfaces. Fluted skin on fin and rudder. Elevator horn-balanced.

The landing gear:

non-retractable tricycle type with oleo-pneumatic shock-absorbers that will smooth out the roughest landing, even on small unprepared fields.

Electrical system :

Main  electrical  system  is  14 DC  negative  ground-return  type  and  consist  of :  wires , fuses , switches , ground  supply  relay , started  relay , battery ,  battery  relay ,  voltage  regulator , over-voltage  relay ,  position  lights ,  anti-collision  light ,  taxiing  light ,  landing  reflector

Electronic equipment:

Standard : Air  speed  indicator, gyro horizon, altimeter, turn & slip indicator, directional gyro, ADF  indicator, vertical speed indicator, tachometer, manifold pressure & fuel  flow indicator, triple  engine gauge indicator, EGT indicator, fuel quantity indicator, ammeter, stall warning horn, magnetic  compass 

Optional (upon customer request on additional right instrument board): Air speed indicator, gyro horizon, altimeter, turn & slip indicator, directional gyro, vertical speed indicator


Standard: ADF receiver KING KR-85, VHF COMM transceiver KING KY-195 BF, antennas, dual  headset


Various light weapon loads hanged on two under-wing  pylons – two  machine  gun  pods  MAC-AA-52

– two unguided  missiles  launch : L 57-016MD, L 128-02, – bombs 2 x 100  kg

Fire managing by collimator optical sight (over instrument panel in front of pilot) and  switches (on control stick and inside central hood beam over pilot head)

Technical data:

Dimensions and areas:

wing span: 9,73 m
length overall: 7,11 m
height: 3,149 m
wheel track: 2,584 m
wings area: 14,63 m2


max T-O weight: 960 kg
weight empty, equipped: 685 kg
crew (2 persons): 2x 85 kg
luggage: 40 kg

Fuel capacity:

standard: 150 l
with drop-tanks: 2x 100 l


max level speed: 215 km/h
cruising speed: 185 km/h
stalling speed: 82 km/h
rate of climb: 4,6 m/s
service ceiling: 4000 m
T-O run: 126 m
T-O to 15 m: 250 m
landing from 15 m: 340 m
landing run 100 m:
range: with standard fuel 800 km
               with drop-tanks 2000 km