Scintex Rubis

Scintex Rubis
Scintex Rubis at Guyancourt airfield, Paris, in 1965
Role	General aviation aircraft
National origin	France
Manufacturer	Scintex-Aviation
First flight	3 June 1962
Introduction	1964
Primary user	Private owners
Number built	8
Developed from	ML 145

The Scintex ML 250 Rubis was a French civil utility aircraft of the 1960s.

Design and development

Scintex Aviation had manufactured the two-seat Emeraude from the late 1950s. In 1960 the firm designed the ML 145 four-seat low-wing cabin monoplane, powered by a 145 h.p. Continental O-300-B engine, the single example of which first flew on 25 May 1961.^[1]

Scintex Rubis at Toussus-le-noble airfield in 1967

Scintex developed the ML 250 with a larger five-seat cabin and fitted with a 250 hp (186 kW) Lycoming O-540 engine. This first flew on 3 June 1962.^[2] The aircraft was of a graceful design, using an all-wood construction, having a semi-monocoque plywood-covered fuselage and cantilever tapered low wing. The tail fin was swept and the aircraft, unusually, was fitted with a fully retractable tailwheel undercarriage.

Production and service

Eight production examples of the ML 250 Rubis were completed by Scintex during 1964-1965. Whilst the type had an advanced specification, it suffered from competition from contemporary all-metal aircraft types such as the Piper Comanche. The Rubis has remained in service with French private pilots and four were airworthy in 2005.^[3]

Specifications

Data from Jane's All The World's Aircraft 1965–66^[4]

General characteristics

• Crew: one
• Capacity: four
• Length: 7.75 m (25 ft 5 in)
• Wingspan: 10.25 m (33 ft 8 in)
• Height: 1.90 m (6 ft 3 in)
• Wing area: 159.1 sq ft (14.78 m²)
• Airfoil: root: NACA 23015 tip: NACA 23009^[5]
• Empty weight: 800 kg (1,764 lb)
• Loaded weight: 1,475 kg (3,252 lb)
• Useful load: 675 kg (1,488 lb)
• Powerplant: 1 × Lycoming O-540-A1D5 air-cooled flat-six engine, 250 hp (186 kW)

Performance

• Maximum speed: 315 km/h (170 knots, 196 mph)
• Cruise speed: 300 km/h (162 knots, 186 mph)
• Stall speed: 98 km/h (53 knots, 61 kmp)
• Range: 1,550 km (837 nmi, 963 mi) at 270 km/h (146 kn; 168 mph)
• Service ceiling: 6,500 m (21,325 ft)
• Rate of climb: 6.3 m/s (1,275 ft/min)

References

Notes

1. Green 1965, p. 63
2. Simpson 2001, pp. 489–490
3. Simpson 2001, p. 489
4. Taylor 1965, p. 55.
5. Lednicer, David (October 2007). "The Incomplete Guide to Airfoil Usage". Retrieved 2009-02-28.

Bibliography

• Green, William (1965). The Aircraft of the World. Macdonald & Co. (Publishers) Ltd.
• Simpson, Rod (2001). Airlife's World Aircraft. Airlife Publishing Ltd. ISBN 1-84037-115-3.
• Taylor, John W. R. (1965). Jane's All The World's Aircraft 1965–66. London: Sampson Low, Marson & Co., Ltd.