Boisavia Mercurey

B.60 Mercurey

Role  | Civil utility aircraft
National origin | France
Manufacturer  | Boisavia
First flight  | 3 April 1949
Number built | 46

The Boisavia B.60 Mercurey was a series of four-seat light aircraft developed in France shortly after World War II.

## Contents

* 1 Design and operations
* 2 Variants
* 3 Specifications (B.60)
* 4 References
* 5 Further reading

## Design and operations

Boisavia B.601L Mercurey of Omniair at Dijon's Val Suzon airfield in 1965

The Mercurey was a conventional high-wing braced monoplane with fixed tailwheel undercarriage. It was built in small numbers and found use in the normal general aviation roles of tourer, trainer, agricultural aircraft, and glider tug.

## Variants

B.60 Mercurey
3 prototypes powered by 100 kW (140 hp) Renault 4Pei engine
B.601 Mercurey
Powered by a 140 kW (190 hp) Avco Lycoming O-435-1 engine;three built.
B.601L Mercurey
Main production version, equipped with an 130 kW (180 hp) Avco Lycoming O-360-A engine;twenty-seven built.
B.602 Mercurey
Powered by a 123 kW (165 hp) Continental E165-4 engine;two built.
B.602A
1x 159 kW (213 hp) Continental O-470-11
B.603 Mercurey Special
Glider tug version, powered by a 180 kW (240 hp) Salmson 8 As engine (Argus As 10);five built.
B.604 Mercurey II
Dedicated glider tug with lengthened fuselage, powered by a 170 kW (230 hp) Salmson 9ABc radial piston engine;one built).
B.605 Mercurey
Similar to the B.60, powered by a 130 kW (170 hp) Régnier 4LO2 (SNECMA 4L-02) engine;four built.
B.606 Mercurey
130 kW (170 hp) Régnier 4LO20 (SNECMA 4L-00) engine;one built.

## Specifications (B.60)

Data from Jane's All The World's Aircraft 1958–59[1]

General characteristics

* Crew: 1
* Capacity: 3 passengers
* Length: 7.20 m (23 ft 7 in)
* Wingspan: 11.38 m (37 ft 4 in)
* Height: 2.20 m (7 ft 3 in)
* Wing area: 18 m2 (190 sq ft)
* Airfoil: NACA 23.012
* Empty weight: 710 kg (1,565 lb)
* Gross weight: 1,277 kg (2,815 lb)
* Fuel capacity: 220 L (58.1 US gal; 48.4 imp gal)
* Powerplant: 1 × Lycoming O-320 4-cylinder air-cooled horizontally-opposed piston engine, 100 kW (140 hp)

(or 170 hp (127 kW) Lycoming O-340)

* Propellers: 2-bladed Ratier fixed-pitch propeller

Performance

* Maximum speed: 235 km/h (146 mph, 127 kn)
* Cruise speed: 200 km/h (120 mph, 110 kn)
* Stall speed: 70 km/h (43 mph, 38 kn)
* Range: 1,200 km (750 mi, 650 nmi)
* Service ceiling: 5,500 m (18,000 ft)
* Rate of climb: 4 m/s (790 ft/min)

* Take-off run: 210 m (689 ft)
* Landing run: 150 m (492 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.. pp. 142–143.

## Further reading

* Bridgman, Leonard (1953). Jane's All The World's Aircraft 1953–54. London: Jane's All The World's Aircraft Publishing Company.
* Gaillard, Pierre (June 2000). "Boisavia: Les petites vendanges de Lucien Tielès" (in fr). Le Fana de l'Aviation (367): 32–41.
* Simpson, R. W. (1995). Airlife's General Aviation. Shrewsbury: Airlife Publishing. pp. 408–09.
* 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.

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