Jump to content

SIAI-Marchetti S.210

From Wikipedia, the free encyclopedia
(Redirected from SIAI Marchetti S.210)
S.210
The prototype S.210M exhibited at the 1971 Paris Air Show at Le Bourget Airport in June 1971
Role Twin-engined cabin monoplane
Manufacturer SIAI-Marchetti
First flight 19 February 1970
Number built 12
Developed from SIAI-Marchetti S.205

The SIAI-Marchetti S.210 was a 1970s Italian twin-engined cabin-monoplane designed and built by SIAI-Marchetti as a development of the single-engined SIAI-Marchetti S.205.

Development

[edit]

The S.210 was developed from the single-engined S.205 and was an all-metal low-wing cantilever monoplane with a retractable tricycle landing gear. It was powered by two 200 hp (149 kW) Avco Lycoming TIO-360-A1B engines, one mounted on the leading edge of each wing. It had three pairs of side-by-side seats for one pilot and five passengers.

The prototype S.210M first flew on 18 February 1970 and was exhibited at the 1971 Paris Air Show wearing a military style colour scheme and markings. This aircraft was followed by an improved second prototype with increased baggage capacity and enlarged rear windows. A production batch of ten aircraft were built based on the second prototype.

Specifications (S.210)

[edit]

Data from Jane's All The World's Aircraft 1971-72 [1]

General characteristics

  • Crew: 1
  • Capacity: 5 passengers
  • Length: 8.83 m (29 ft 0 in)
  • Wingspan: 11.63 m (38 ft 2 in)
  • Height: 3.33 m (10 ft 11 in)
  • Wing area: 17.23 m2 (185.5 sq ft)
  • Empty weight: 1,030 kg (2,271 lb)
  • Gross weight: 1,850 kg (4,079 lb)
  • Fuel capacity: 360 L (95 US gal; 79 imp gal)
  • Powerplant: 2 × Avco Lycoming TIO-360-A1B flat-four piston engine , 150 kW (200 hp) each
  • Propellers: 2-bladed Hartzell HC-C2YK-1B/8468-10R constant-speed propellers, 1.88 m (6 ft 2 in) diameter

Performance

  • Maximum speed: 357 km/h (222 mph, 193 kn) at sea level
  • Cruise speed: 314 km/h (195 mph, 170 kn) at 2,400 m (8,000 ft) (econ cruise)
  • Range: 1,900 km (1,200 mi, 1,000 nmi) with maximum payload
  • Service ceiling: 8,100 m (26,600 ft)
  • Rate of climb: 10.1 m/s (1,980 ft/min)
  • Take-off distance to 15 m (50 ft): 400 m (1,310 ft)
  • Landing distance from 15 m (50 ft): 550 m (1,800 ft)

See also

[edit]

Related development

References

[edit]
  1. ^ Taylor 1971, p.131.
  • Taylor, John W. R. (1971). Jane's All The World's Aircraft 1971-72. London: Jane's Yearbooks. ISBN 0-354-00094-2.
  • Taylor, Michael J. H. (1989). Jane's Encyclopedia of Aviation. London: Studio Editions. p. 206.
  • The Illustrated Encyclopedia of Aircraft (Part Work 1982-1985). Orbis Publishing. p. 2854.