Max Holste Super Broussard
| Max Holste MH260 Super Broussard / Nord 260 | |
|---|---|
|
|
| Type: | Short haul and feeder aircraft |
| Design country: |
France |
| Manufacturer: | |
| First flight: |
May 20, 1959 (MH.250) |
| Commissioning: |
Mid-1961 |
| Production time: |
1959 - |
| Number of pieces: |
10 (1 × MH.250, |
The Max Holste MH260 Super Broussard was a passenger and cargo aircraft produced by the French manufacturer Société des Avions Max Holste in the late 1950s.
history
After the single-engine Broussard , Max Holste developed the twin-engine Super Broussard. The first prototype , which on 20 May 1959 to the first flight started, carried the designation MH250, was with two nine-cylinder radial engines Pratt & Whitney R-1340 equipped and did not have a pressurized cabin . For the standard version MH260, however, two Turbomeca Bastan turboprops were provided as a drive. Compared to the MH250, the fuselage was also lengthened by 0.65 m and the angular windows replaced by round ones.
After the company was taken over by Nord Aviation , the model was produced as the Nord 260 in a small series of eight.
Before the takeover by the French Air Force (Center d'essais en vol, CEV), some aircraft were loaned to airlines, including Air Inter and the Norwegian Widerøe's Flyveselskap .
The MH.262 variant, which was still developed by Max Holste, received a pressure-ventilated hull with a circular cross-section. The pressurized cabin was designed to maintain a pressure corresponding to an altitude of 2500 m up to an altitude of 5000 m. This variant was mass-produced by Nord as Nord 262 .
The MH.280 version with two Lycoming T53 propeller turbines was also planned, but this did not get beyond the project stage.
construction
The Super Broussard was a twin-engine, cantilevered shoulder-wing aircraft with a three-part all-metal wing. The all-metal box body had an almost rectangular (MH250 and 260) or round cross-section (MH262). With the nose wheel landing gear, the nose wheel was complete, but the main landing gear could only be retracted by two thirds in the streamlined body on both sides of the fuselage. Landings on unpaved areas should also be possible. The machine did not have a pressurized cabin.
Technical specifications
| Parameter | Data MH260 |
|---|---|
| crew | 2 |
| Passengers | 17, 20 or 26, toilet and luggage space in the stern for 17 and 20 passengers, a buffet could be installed. |
| length | 18.04 m |
| span | 21.85 m |
| height | 7.11 m |
| Wing area | 54.5 m² |
| Empty mass | 5600 kg |
| Max. Takeoff mass | 9800 kg |
| Cruising speed | 390 km / h |
| Service ceiling | 8600 m |
| Range | 1000 km with 45 min reserve |
| Engines | 2 × Turbomeca Bastan IV turboprop engines, each with 1000 WPS three-bladed adjustable propellers, Ratier 1800 l fuel in six wing tanks |
See also
literature
- Karlheinz Kens: Airplane types - type book of international aviation. 4th edition, Carl Lange Verlag, Duisburg 1963.
Web links
- Photo and data of the North 260 flugzeuginfo.net (English)
- Three-sided drawing of the MH 260 (English)
- Description of the Nord 260 on Aviationsmilitaires.net (French)
- Description of the Nord 262 on Aviationsmilitaires.net (French)
Individual evidence
- ↑ Air-Britain Aviation World (English), September 2017, p. 131.