PROFILBARU.COM

SAN Jodel D.140 Mousquetaire
	D.140C
Role	Five-seat light touring monoplane
National origin	France
Manufacturer	Société Aéronautique Normande (SAN)
First flight	4 July 1958
Introduction	1958
Status	Plans available (2012)
Primary user	French Air Force
Number built	243 (factory built)

The SAN Jodel D.140 Mousquetaire (Musketeer) is a French five-seat light touring monoplane based on the earlier Jodel D.117 and built by Société Aéronautique Normande (SAN) at Bernay.^[1]

Development

SAN had been producing the earlier Jodel D.117 under licence from which it then developed the larger 4 to 5-seat D.140.^[1] The prototype D.140 registration F-BIZE first flew on 4 July 1958.^[1] Early versions had a low triangular-shaped fin and rudder.

The final version was a glider tug variant the D.140R Abeille.^[1] Both the D.140E and D.140R were ordered by the French Air Force.^[1] As well as 243 factory-built aircraft more than 20 have been homebuilt from plans. The type was flown by aero clubs and private owners and remains in use in 2014.

Plans remained available in 2015.^[2]^[3]

Variants

D.140 Mousquetaire: Prototype powered by a 180hp Lycoming O-360 engine, one built.^[1]
D.140A Mousquetaire: Production variant with cabin ventilation, 45 built.^[1]
D.140B Mousquetaire II: Improved variant with better brakes, new engine cowling and better ventilation, 56 built.^[1]
D.140C Mousquetaire III: A D.140B with an enlarged swept tail, 70 built.^[1]
D.140E Mousquetaire IV: A D.140C with a further enlarged tail, modified ailerons and an all flying elevator/tailplane, 43 built.^[1]
D.140R Abeille: Glider towing variant with cut-down rear fuselage, new high vision canopy, 28 built first flown in 1965.^[1]

Operators

France

French Air and Space Force

Specifications (D.140)

Data from Jane's All the World's Aircraft 1962–63^[4]

General characteristics

Crew: 1
Capacity: 3 passengers
Length: 7.90 m (25 ft 11 in)
Wingspan: 10.22 m (33 ft 6 in)
Height: 2.15 m (7 ft 1 in)
Wing area: 17.9 m² (193 sq ft)
Airfoil: NACA 23015
Empty weight: 660 kg (1,455 lb)
Max takeoff weight: 1,200 kg (2,646 lb)
Powerplant: 1 × Lycoming O-360-A1A air-cooled flat-four piston engine, 130 kW (180 hp)

Performance

Maximum speed: 250 km/h (160 mph, 130 kn)
Cruise speed: 220 km/h (140 mph, 120 kn) (econ cruise)
Stall speed: 55 km/h (34 mph, 30 kn)
Range: 1,200 km (750 mi, 650 nmi)
Service ceiling: 4,500 m (14,800 ft)
Rate of climb: 5.00 m/s (985 ft/min)

References

Notes

^ ^a ^b ^c ^d ^e ^f ^g ^h ⁱ ^j ^k Simpson 1991, pp.283-284
^ Bayerl, Robby; Martin Berkemeier; et al: World Directory of Leisure Aviation 2011-12, page 94. WDLA UK, Lancaster UK, 2011. ISSN 1368-485X
^ Tacke, Willi; Marino Boric; et al: World Directory of Light Aviation 2015-16, page 99. Flying Pages Europe SARL, 2015. ISSN 1368-485X
^ Taylor 1962, p. 53

Bibliography

Simpson, R.W. (1991). Airlife's General Aviation. England: Airlife Publishing. ISBN 1-85310-194-X.
Taylor, John W. R. (1962). Jane's All the World's Aircraft 1962–63. London: Sampson Low, Marston & Co. Ltd.