UTVA-60
From Wikipedia, the free encyclopedia
The UTVA-60 is a Yugoslavian light aircraft of the 1960s. First flying in 1959, it was built by UTVA for both the Yugoslavian armed forces and for civilian use.
| UTVA-60 | |
|---|---|
| General information | |
| Type | Light utility/training aircraft |
| National origin | Yugoslavia |
| Manufacturer | UTVA |
| History | |
| Introduction date | 1960 |
| First flight | 22 April 1959 (UTVA-56) |
| Variants | UTVA 65 UTVA 66 |
Development and design
In 1959 the Yugoslav aircraft company UTVA designed and built a single-engined, high-winged light utility aircraft, the UTVA 56, with a prototype making the first flight 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, four-place, strut-braced high-wing monoplane. It is fitted with a fixed conventional undercarriage which uses cantilevered steel tube struts. Trailing-edge wing 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
Variants
- UTVA-56
- Prototype, powered by a 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 a 221 kW (296 kW) Lycoming GO-480-G1H6 engine.[1]
Operators
- Republika Srpska Air Force
- 92nd Light Multi role Aircraft Squadron
- Yugoslav Air Force
- 122nd Hydroplane Liaison Squadron (1964–1968)
- Letalski center Maribor (civil operator) YU-CBA, accident 20.06.1982
Specifications (UTVA-60-AT1)
Data from [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)
- 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
- Cruise 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 (480 mi, 420 nmi)
- Service ceiling: 5,200 m (17,100 ft)
- Rate of climb: 6.4 m/s (1,260 ft/min)
