Fuji/Rockwell Commander 700
From Wikipedia, the free encyclopedia
| Commander 700 | |
|---|---|
| Type | Light transport |
| Manufacturer | Fuji / Rockwell |
| Maiden flight | 1975 |
The Fuji/Rockwell Commander 700 was a joint Japanese-American development between Fuji Heavy Industries and Rockwell International. When Rockwell sold off the general aviation division the agreement was terminated.
[edit] Development
Design of the Commander 700 started in Japan in 1971 with the designation FA-300, in 1974 Fuji signed a collaboration with Rockwell International to design and develop the aircraft as a joint venture. The aircraft was designated the Commander 700 for the North American market. The Commander 700 is a low-wing cantilever monoplane with a conventional tail unit and a retractablke tricycle landing gear. The aircraft was powered by two wing mounted Avco Lycoming turbocharged piston engines. The fuselage was designed to be pressurised with accommodation for two crew and four passengers. The prototype first flew in Japan on 13 November 1975 and the second Rockwell assembled aircraft on 25 February 1976. A parallel development was the Commander 710 with more powerful engines which first flew on 22 December 1976. In 1979 Rockwell International sold its General Aviation Division to Gulfstream American and the agreement with Fuji was terminated. Fuji then acquired the worldwide manufacturing and marketing rights for the aircraft.
[edit] Variants
- Commander 700
- Powered by two 340hp (254kW) Avco Lycoming engines.
- Commander 710
- Powered by two 450hp (335kW) Avco Lycoming engines.
[edit] Specifications (700)
Data from The Illustrated Encyclopedia of Aircraft (Part Work 1982-1985), 1985, Orbis Publishing, Page 1920
General characteristics
- Crew: 2
- Capacity: 4 passengers
- Length: 39 ft 5¾ in (12.03 m)
- Wingspan: 42 ft 5½ in (12.94 m)
- Height: 13 ft 3½ in (4.05 m)
- Wing area: 200.2 ft² (18.60 m²)
- Empty weight: 4704 lb (2134 kg)
- Gross weight: 6947 lb (3151 kg)
- Powerplant: 2 × Avco Lycoming TIO-549-R2AD flat-six piston engine, 350 hp (254 kW) each
Performance
- Maximum speed: 254 mph (409 km/h)
- Range: 1384 miles (2227 km)
- Service ceiling: 27,400 ft (8350 m)
[edit] References
- The Illustrated Encyclopedia of Aircraft (Part Work 1982-1985), 1985, Orbis Publishing, Page 1920
|
|||||
|
||||||||||||||
