Nord 3400

Nord 3400 Norbarbe
Role	Two-seat army liaison
National origin	France
Manufacturer	Nord Aviation
First flight	1958
Introduction	1959
Primary user	French Army Light Aviation
Produced	1959-1961
Number built	152

The Nord 3400 Norbarbe was a French two-seat observation and casualty-evacuation aircraft built by Nord Aviation for the French Army Light Aviation.^[1]

Design and development[edit]

The Nord 3400 was designed to meet a French Army requirement for a two-seat observation aircraft, with a secondary casualty-evacuation role. The 3400 was a braced high-wing monoplane with a fixed tailwheel landing gear and an enclosed cabin with tandem seating for a pilot and observer. The prototype F-MBTD first flew on 20 January 1958, powered by a 179 kW (240 hp) Potez 4D-30 engine. A second prototype with an increased wing area followed, being powered by a 194 kW (260 hp) Potez 4D-34 engine. A production batch of 150 was ordered by the French Army in the same configuration as the second prototype.

Variants[edit]

Nord 3400-01: First prototype, powered by a 179 kW (240 hp) Potez 4D-30 engine, with, 12.7 m (42 ft) span/19.5 m² (210 sq ft) area, wings.^[2]
Nord 3400: Production aircraft (and 2nd prototype), with a more powerful 194 kW (260 hp) Potez 4D-34 engine and increased span/area wings.^[3]

Operators[edit]

France

Specifications (Nord 3400)[edit]

Data from Jane's All the World's Aircraft 1962-63^[3]

General characteristics

Crew: 2
Length: 8.42 m (27 ft 7 in)
Wingspan: 13.11 m (43 ft 0 in)
Height: 3.1 m (10 ft 2 in)
Wing area: 20.82 m² (224.1 sq ft)
Aspect ratio: 8.2
Airfoil: NACA 23015^[4]
Empty weight: 920 kg (2,028 lb) equipped
Max takeoff weight: 1,350 kg (2,976 lb)
Fuel capacity: 220 L (58.1 US gal; 48.4 imp gal) in two self-sealing rubber tanks (160 kg (353 lb))
Powerplant: 1 × Potez 4D-30 4-cylinder air-cooled inverted in-line piston engine, 180 kW (240 hp)
Propellers: 2-bladed Ratier Type 24-56 adjustable-pitch propeller, 2.25 m (7 ft 5 in) diameter adjustable-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: 1,000 km (620 mi, 540 nmi)
Rate of climb: 7 m/s (1,400 ft/min)
Wing loading: 65 kg/m² (13 lb/sq ft)
Power/mass: 0.192 kW/kg (0.117 hp/lb)
Take-off run: <100 m (328 ft)
Landing run: <100 m (328 ft)

References[edit]

^ Flying Magazine: 50. August 1961. {{cite journal}}: Missing or empty |title= (help)
^ 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. 161.
^ ^a ^b Taylor, John W.R., ed. (1962). Jane's All the World's Aircraft 1962-63. London: Sampson Low, Marston & Co. p. 49.
^ Lednicer, David. "The Incomplete Guide to Airfoil Usage". m-selig.ae.illinois.edu. Retrieved 16 April 2019.

External links[edit]

Photos at airliners.net

[Flying-1] Flying Magazine: 50. August 1961. {{cite journal}}: Missing or empty |title= (help)

[JAWA58-59-2] 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. 161.

[JAWA62-63-3] Taylor, John W.R., ed. (1962). Jane's All the World's Aircraft 1962-63. London: Sampson Low, Marston & Co. p. 49.

[Selig-4] Lednicer, David. "The Incomplete Guide to Airfoil Usage". m-selig.ae.illinois.edu. Retrieved 16 April 2019.

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