UTVA 75
| UTVA 75 | |
|---|---|
| |
| Serbian Air Force Utva 75 | |
| Role | Military trainer/general aviation |
| National origin |  Yugoslavia
|
| Manufacturer | UTVA |
| First flight | 19 May 1976[1] |
| Introduction | 1978 |
| Status | active |
| Primary user | Yugoslav Air Force |
| Produced | 1978-1985 |
| Number built | 136[1] |
The UTVA 75 is a compact, low-wing monoplane, piston-engine aircraft manufactured by UTVA. It was mainly used as a military basic trainer and sporting aircraft.[2]
Design and development
Designed in 1975 to replace the UTVA Aero 3 as the primary basic trainer in the Yugoslav Air Force. It features upward opening gull-wingtype access doors to the two-seat side-by-side cockpit. Another characteristic is a row of air scoops, presumably for cockpit ventilation, in the central front frame of the cockpit. The Utva 75 made its maiden flight in 1976.[1] Between 1978 and 1985, a total of 136 Utva 75s were produced for the former Yugoslav Air Force.[1] Following the breakup of Yugoslavia, many were passed on to successor states.
Variants
- UTVA 75A11
- Single-seat agricultural aircraft, largely using the Utva 75 airframe.[3]
- UTVA-75A21
- Two-seater with dual controls and provisions for blind instrument flying.[3]
- UTVA-75A41
- Four-seater with advanced avionics, first flown in 1986.[3]
- SAFAT 03
- A development of the UTVA 75 from the SAFAT Aviation Complex at Khartoum, Sudan, with a modified fuselage and tail fin. To confuse matters the Sudanese Government marked up a standard UTVA 75 as a SAFAT 03. One example known, which was displayed at the Dubai Air Show in 2011.
Operators
- Slovenian Air Force[5]
- Letalski center Maribor Civil operator (1989-today)
Former operators
Specifications (UTVA 75A21)
Data from Jane's All the World's Aircraft 1988-89[3]
General characteristics
- Crew: 2
- Capacity: 210 kg (460 lb) max
- Length: 7.11 m (23 ft 4 in)
- Wingspan: 9.73 m (31 ft 11 in)
- Height: 3.15 m (10 ft 4 in)
- Wing area: 14.63 m2 (157.5 sq ft)
- Aspect ratio: 6.5
- Empty weight: 685 kg (1,510 lb) equipped
- Max takeoff weight: 960 kg (2,116 lb)
- Fuel capacity: standard:160 L (42 US gal; 35 imp gal): with drop tanks 360 L (95 US gal; 79 imp gal)
- Powerplant: 1 × Lycoming IO-360-B1F 4-cyl. air-cooled horizontally-opposed piston engine, 134 kW (180 hp)
- Propellers: 2-bladed Hartzell HC-C2YK-1BF/F7666A variable-pitch metal propeller
Performance
- Maximum speed: 215 km/h (134 mph, 116 kn)
- Cruise speed: 165 km/h (103 mph, 89 kn)
- Stall speed: 95 km/h (59 mph, 51 kn) flaps up at idle
- 82 km/h (51 mph; 44 kn) 25° flap at idle
- Never exceed speed: 270 km/h (168 mph, 146 kn)
- Range: 800 km (500 mi, 430 nmi)
- Ferry range: 2,000 km (1,200 mi, 1,100 nmi)
- Service ceiling: 4,000 m (13,000 ft)
- g limits: +4.4 -2.2
- Rate of climb: 4.5 m/s (890 ft/min)
Armament
- Hardpoints: 2 with a capacity of 150 kg (330 lb) each, with provisions to carry combinations of:
- Rockets: 2x RL 128-02 128 mm (HVAR-5) or 2x rocket launcher with 12 rockets 57 mm
- Bombs: 2x 120 kg bombs or 4x 50 kg bombs
- Other: 2x MAC-AA-52 container with 7,62 mm or 2x cargo container 100 kg capacity or 2x drop tanks
Avionics
optional King KY 195B radio with standard radio compass
See also
Aircraft of comparable role, configuration, and era
References
- ^ a b c d "Školski avion UTVA-75". Vojska Srbije. Retrieved 10 July 2013.
- ^ Dusan. "Утва 75". www.vazduhoplovnetradicijesrbije.rs (in Serbian). Belgrade. Retrieved 26 February 2015.
- ^ a b c d John W.R. Taylor, ed. (1988). Jane's All the World's Aircraft 1988-89. London: Jane's Information Group. pp. 499–500. ISBN 0-7106-0867-5.
- ^ "World Air Forces 1997 pg. 71". flightglobal.com. Retrieved 3 May 2019.
- ^ "World Air Forces 1997 pg. 621". flightglobal.com. Retrieved 3 May 2019.
- ^ "Eurofighter: Dubai Air Show 2011". Eurofighter. 17 November 2011. Archived from the original on 15 May 2013. Retrieved 10 July 2013.
