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.
- 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.
UTVA 75 is strong, the all-metal construction and completely corrosion-proofed.
cantilever, rectangular, with main and aux. wing spar and the integral fuel cells located between them.
dihedral: 6°, NACA 652 415 wing section.
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.
conventional all metal semi monocoque structure, 11 frames, 1 partial bulkhead and several stringers.
cantilever, all metal structure with swept back vertical surfaces. Fluted skin on fin and rudder. Elevator horn-balanced.
non-retractable tricycle type with oleo-pneumatic shock-absorbers that will smooth out the roughest landing, even on small unprepared fields.
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
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)
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
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