Boisavia Anjou

B.260 Anjou
General information
TypeCivil utility aircraft
ManufacturerBoisavia, SIPA
Number built1
History
First flight2 June 1956

The Boisavia B.260 Anjou (later developed by SIPA as the Sipavia Anjou) was a four-seat twin-engine light aircraft developed in France in the 1950s. It was a low-wing cantilever monoplane of conventional configuration with retractable tricycle undercarriage. Intended by Boisavia as a touring aircraft, it did not find a market and only the single prototype was constructed. At this point, the firm sold the design to SIPA, which modified the design and re-engined it with Lycoming O-360 engines, but found that they could not sell it either. At a time when the twin-engine light plane market was already dominated by all-metal American aircraft, the Anjou's fabric-over-tube construction was something of an anachronism, and all development was soon ceased. Plans to develop a stretched version with three extra seats and Potez 4D engines were also abandoned.

Variants

  • B.260 - Boisavia prototype with Regnier 4L engines (1 built)
  • S.261 - SIPA conversion with Lycoming O-360 engines (1 converted)
  • S.262 - Planned seven-seat version (not built)

Specifications (B.260)

Data from Jane's All the World's Aircraft 1958-59 [1]

General characteristics

  • Crew: 1
  • Capacity: 3 pax
  • Length: 7.2 m (23 ft 7 in)
  • Wingspan: 13 m (42 ft 8 in)
  • Height: 3 m (9 ft 10 in)
  • Wing area: 21.5 m2 (231 sq ft)
  • Aspect ratio: 7.6
  • Empty weight: 1,300 kg (2,866 lb)
  • Gross weight: 2,000 kg (4,409 lb)
  • Fuel capacity: 450 L (118.9 US gal; 99.0 imp gal) in two wing tanks + 2x 100 L (26.4 US gal; 22.0 imp gal) optional wing-tip tanks
  • Powerplant: 2 × SNECMA Régnier 4L-02 4-cylinder air-cooled inverted in-line piston engines, 130 kW (170 hp) each
(SNECMA licence-built )
  • Propellers: 2-bladed fixed-pitch propellers

Performance

  • Maximum speed: 300 km/h (190 mph, 160 kn)
  • Cruise speed: 240 km/h (150 mph, 130 kn) (economical)
  • Stall speed: 90 km/h (56 mph, 49 kn)
  • Range: 1,500 km (930 mi, 810 nmi)
  • Service ceiling: 6,800 m (22,300 ft)
  • Rate of climb: 6 m/s (1,200 ft/min)
0.833 m/s (3 ft/s) on one engine at 1,500 m (4,900 ft)
  • Take-off run: 160 m (520 ft)
  • Landing run: 150 m (490 ft)

References

  1. ^ Bridgman, Leonard, ed. (1957). Jane's All the World's Aircraft 1958-59. London: Jane's All the World's Aircraft Publishing Co. Ltd. p. 143.

Further reading

  • Taylor, Michael J. H. (1989). Jane's Encyclopedia of Aviation. London: Studio Editions. p. 192.
  • World Aircraft Information Files. London: Bright Star Publishing. pp. File 890 Sheet 73.
  • Simpson, R. W. (1995). Airlife's General Aviation. Shrewsbury: Airlife Publishing. pp. 370, 408–09.