UTVA-60
| UTVA-60 |
| Role |
Light utility/training aircraft |
| National origin |
Yugoslavia |
| Manufacturer |
UTVA |
| First flight |
1959 (UTVA-56) |
| Variants |
UTVA 65
UTVA 66
|
The UTVA-60 is a Yugoslavian light aircraft of the 1950s-60s. First flying in 1959, it was built by UTVA for both the Yugoslavian armed forces and for civilian use.
Development and design
In 1959, the Yugoslav aircraft company UTVA designed and built a single-engined, high-winged light utility aircraft, the UTVA 56, a prototype first flying on 22 April 1959.[1] Testing was successful,[2] but the aircraft was redesigned for production, with a more powerful Lycoming O-480 engine, and designated the UTVA-60.[1]
The UTVA-60 is an all-metal monoplane fitted with a fixed conventional undercarriage. Trailing edge flaps are linked to the ailerons, drooping the ailerons when the flaps are lowered to reduce landing speed,[3] while the agricultural version's wing was fitted with slots.[1]
The UTVA-60 was used as the basis for the UTVA-65, a specialised agricultural aircraft, which used the wings, undercarriage and tail of the UTVA-60, but with a low-mounted wing. The UTVA-60 was replaced in production by the UTVA-66, a further improved version.[4]
Operational history
As well as civil use, the UTVA-60 was used by the Yugoslav Air Force, who received about 35, using them until 1982,[5] while Cambodia received four aircraft.[6][7]
Variants
- UTVA-56
- Prototype, powered by 194 kW (260 hp) Lycoming GO-435 engine.[1][3]
- UTVA-60-AT1
- Basic four seat utility version.[1]
- UTVA-60-AT2
- Dual control version.[1]
- UTVA-60-AG
- Agricultural version.[1]
- UTVA-60-AM
- Ambulance version.[1]
- UTVA-60H
- Floatplane, powered by 221 kW (296 kW) Lycoming GO-480-G1H6 engine.[1]
Operators
- Cambodia
- Yugoslavia
Specifications (UTVA-60-AT1)
Data from Jane's All The World's Aircraft 1965-66 [8]
General characteristics
- Crew: 1
- Capacity:
- 3 passengers or
- 2 stretchers and attendant
- Length: 8.22 m (27 ft 0 in)
- Wingspan: 11.40 m (37 ft 5 in)
- Height: 2.72 m (8 ft 11 in)
- Wing area: 18.08 m2 (194.6 sq ft)
- Aspect ratio: 7.19
- Airfoil: NACA 4412 (modified)
- Empty weight: 952 kg (2,099 lb)
- Gross weight: 1,448 kg (3,192 lb)
- Max takeoff weight: 1,620 kg (3,571 lb)
- Powerplant: 1 × Lycoming O-480-G1H6 air-cooled flat-six, 200 kW (270 hp)
- Propellers: 2-bladed Hartzell HC-A2X20-1B/10133-3 constant speed metal propeller
Performance
- Maximum speed: 252 km/h (157 mph; 136 kn) at sea level
- Cruising speed: 230 km/h (140 mph; 120 kn)
- Stall speed: 73 km/h (45 mph; 39 kn)
- Never exceed speed: 300 km/h (190 mph; 160 kn)
- Range: 780 km (485 mi; 421 nmi)
- Service ceiling: 5,200 m (17,060 ft)
- Rate of climb: 6.4 m/s (1,260 ft/min)
See also
- Related development
Notes
References
- Donald, David (ed.) The Encyclopedia of World Aircraft. Leicester, UK: Blitz Editions, 1997. ISBN 1-85605-375-X.
- Grandolini, Albert. "L'Aviation Royale Khmere: The first 15 years of Cambodian military aviation". Air Enthusiast, Thirty-seven, September-December 1988. Bromley, UK:Fine Scroll. issn 0143-5450. pp. 39–47 .
- "Sport and Business". Flight, 25 September 1959, p.305.
- Taylor, John W. R. Jane's All The World's Aircraft 1965-66. London: Samson Low, Marston, 1965.
External links
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