UTVA-60

UTVA-60

National origin: Yugoslavia
Manufacturer: UTVA
First flight: 1959 (UTVA-56)
Variants: UTVA 65 UTVA 66

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. Testing was successful, but the aircraft was redesigned for production, with a more powerful Lycoming O-480 engine, and designated the UTVA-60.

The UTVA-60 is an all-metal monoplane fitted with a fixed tricycle undercarriage. Trailing edge flaps are linked to the ailerons, drooping the ailerons when the flaps are lowered to reduce landing speed, while the agricultural version's wing was fitted with slots.

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.

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, while Cambodia received four aircraft.

Variants

UTVA-56
Prototype, powered by 194 kW (260 hp) Lycoming GO-435 engine.
UTVA-60-AT1
Basic four seat utility version.
UTVA-60-AT2
Dual control version.
UTVA-60-AG
Agricultural version.
UTVA-60-AM
Ambulance version.
UTVA-60H
Floatplane, powered by 221 kW (296 kW) Lycoming GO-480-G1H6 engine.

Operators

Cambodia

Royal Cambodian Air Force

Yugoslavia

Yugoslav Air Force

Specifications (UTVA-60-AT1)

Data from Jane's All The World's Aircraft 1965-66

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 m (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 x— 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)

Related development

UTVA 65
UTVA 66

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.

UTVA-60 Pictures

More aircraft.

Source: WikiPedia