UTVA 75
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]
UTVA 75 | |
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Serbian Air Force Utva 75 | |
Role | Military trainer/general aviation |
National origin | ![]() |
Manufacturer | UTVA |
First flight | 19 May 1976[1] |
Introduction | 1978 |
Status | active |
Primary user | Yugoslav Air Force |
Produced | 1978-1985 |
Number built | 136[1] |
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
![](../I/SAFAT_03.jpg.webp)
- 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
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Wikimedia Commons has media related to UTVA-75. |
Aircraft of comparable role, configuration, and era
References
- "Školski avion UTVA-75". Vojska Srbije. Retrieved 10 July 2013.
- Dusan. "Утва 75". www.vazduhoplovnetradicijesrbije.rs (in Serbian). Belgrade. Retrieved 26 February 2015.
- 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.