The UTVA-66 is a STOL light utility and liaison aircraft produced in the former Yugoslavia. A development of the UTVA-56, it first flew in 1966 and was intended largely for use by the Yugoslav military.
Description
The UTVA-66 was derived from the UTVA-56, featuring fixed leading-edge slats and a larger tail.[2]
The aircraft was designed to operate from unprepared fields. Its STOL characteristics include fixed leading-edge slats, flaps and drooping ailerons.[3] The cockpit is equipped with dual flight controls.[1] In the ambulance version, the front right seat and rear seats could be removed to accommodate two stretchers.[1] The 66H (“Hidro“) variant replaced the fixed landing gear with pontoon floats for operation from bodies of water;[2] these could also be exchanged for skis or wheels.[1]
Operational usage
About 130 UTVA-66 aircraft were manufactured.[1]
During the Yugoslav Wars, some aircraft fell into Slovenian and Croatian hands.[2] The last examples were withdrawn from military service in 1999.[1]
A number of aircraft were exported or later appeared in civilian use outside the former Yugoslavia, including in Canada and the United States.[4]
Variants
- 66AM – Air ambulance version.[2]
- 66H – Floatplane version.[2]
- 66V – Armed variant with provisions for underwing armament.[2]
Former military operators
- Republika Srpska Air Force[5]
- 92nd Light Multi-role Squadron[5]
Aircraft on display
- Serbia
- Museum of Aviation (Belgrade) in Belgrade – a number of UTVA-66 aircraft, including the UTVA-66H, are on display.[6]
Specifications (UTVA-66)
Data from Jane’s All the World’s Aircraft 1971–72.[3]
General characteristics
- Crew: 1
- Capacity:
- 3 passengers or
- 2 stretchers
- Length: 8.38 m (27 ft 6 in)
- Wingspan: 11.4 m (37 ft 5 in)
- Height: 3.20 m (10 ft 6 in)
- Wing area: 18.08 m2 (194.6 sq ft)
- Airfoil: NACA 4412 (modified)
- Empty weight: 1,250 kg (2,756 lb)
- Max takeoff weight: 1,814 kg (3,999 lb)
- Fuel capacity: 250 L (55 imp gal; 66 US gal)
- Powerplant: 1 × Lycoming GSO-480-B1J6 air-cooled flat-six engine, 200 kW (270 hp) [7]
Performance
- Maximum speed: 250 km/h (160 mph, 130 kn) at optimum height
- Cruise speed: 230 km/h (140 mph, 120 kn) max cruise
- Stall speed: 80 km/h (50 mph, 43 kn)
- Never exceed speed: 320 km/h (200 mph, 170 kn)
- Range: 750 km (470 mi, 400 nmi)
- Service ceiling: 6,700 m (22,000 ft)
- Rate of climb: 4.50 m/s (885 ft/min)
- Takeoff run to 15 m (50 ft): 352 m (1,155 ft)
- Landing run from 15 m (50 ft): 181 m (594 ft)
See also
Aircraft of comparable role, configuration, and era
References
- ^ a b c d e f “About us”. UTVA AVIO D.O.O. Retrieved 1 June 2026.
- ^ a b c d e f g h i Rendall 1996, p. 215.
- ^ a b Taylor 1971, pp. 472–473
- ^ a b “UTVA-66 Short takeoff and landing aircraft”. RedStar.gr. Retrieved 1 June 2026.
- ^ a b c Ripley 2013, p. 81.
- ^ “Muzej Ratnog Vazduhoplovstva”. AviationMuseum.eu. Retrieved 1 June 2026.
- ^ Fulton 1973, p. 104
Bibliography
- Fulton, Ken (19 July 1973). “Piston Engine Survey”. Flight International. Vol. 104, no. 3358. pp. 98–106.
- Rendall, David Alexander, ed. (1996). Jane’s Aircraft Recognition Guide. Glasgow: HarperCollins. ISBN 978-0-00-470980-2.
- Ripley, Tim (2013). Conflict in the Balkans 1991–2000 (PDF e-book ed.). Oxford, United Kingdom: Bloomsbury Publishing. ISBN 978-1-84603-748-1 – via Google Books.
- Taylor, John W. R., ed. (1971). Jane’s All The World’s Aircraft 1971–72. London: Sampson Low. ISBN 0-354-00094-2.