|This article needs additional citations for verification. (May 2009)|
|Role||Light passenger/cargo aircraft|
|Primary user||Business flyers|
|Developed from||Cessna 310|
|Variants||Cessna 401, Cessna 402, Cessna 421|
The Cessna Model 411 is a 1960s American twin-engined, propeller driven light aircraft built by Cessna Aircraft. It was that company's largest business aircraft when it first flew in 1962, other than a four-engined airliner developed during the 1950s, which was not put into development.
Design and development
The 411 is an eight-seat low-wing twin-engined cabin monoplane retractable landing gear and an airstair entrance door. It has two 340 hp (254 kW) Continental GTSIO-520-C engines with three-bladed propellers. It has a retractable tricycle landing gear and an airstair door. The prototype first flew on 18 July 1962. During 1965 Cessna developed two generally similar and lower-cost versions, the Model 401 and Model 402. Production of the 411 finished in 1968. A pressurised version of the 411 was developed as the Cessna 421.
The Cessna 411 was mainly sold to business users in the United States. Other examples were exported to many overseas countries including Argentina, Australia, France, Germany, Japan, Spain, Switzerland and the United Kingdom. The type remains in operational service in several countries in 2014.
- Cessna 411
- Production variant, obtained type certificate awarded in 1964, 252-built.
- Cessna 411A
- A 411 with larger nose baggage capacity but the same overall length fuselage and optional tanks in engine nacelles, type certificate awarded in 1967, 50 built.
- French Air Force - Six 411s were delivered between 1966 and 1969 as communications aircraft, the four surviving aircraft were transferred to the CEV in 1973 and 1974.
Data from Jane's All The World's Aircraft 1965-66 
- Crew: two
- Capacity: four to six passengers
- Length: 33 ft 5½ in (10.20 m)
- Wingspan: 39 ft 10¼ in (12.15 m)
- Height: 11 ft 6½ in (3.52 m)
- Wing area: 200 ft² (18.58 m²)
- Empty weight: 3,820 lb (1,733 kg)
- Max. takeoff weight: 6,500 lb (2,948 kg)
- Powerplant: 2 × Continental GTSIO-520 flat-six turbocharged piston, 340 hp (254 kW) each
- Maximum speed: 268 mph (233 knots, 431 km/h) at 16,000 ft (4,875 m)
- Cruise speed: 224 mph (195 knots, 360 km/h) at 10,000 ft (3,050 m) (75% power)
- Stall speed: 84 mph (73 knots, 135 km/h) (flaps down)
- Range: 1,300 mi (1,130 nmi, 2,090 km)
- Service ceiling: 26,000 ft (7,925 m)
- Rate of climb: 1,600 ft/min (8.2 m/s)
- Related development
- Simpson 1991, p. 109
- Federal Aviation Authority Type Certificate Data Sheet A7CE
- Rod Simpson: The General Aviation Handbook, Hinckley 2005, p. 89
- Jackson 1979, p. 118
- Taylor 1965, p.210.
- The Illustrated Encyclopedia of Aircraft (Part Work 1982-1985). Orbis Publishing.
- Jackson, Paul A, (1979). French Military Aviation. Leicester, England: Midland Counties Publications. ISBN 0 904597 18 0.
- Simpson, R.W. (1991). Airlife's General Aviation. Shrewsbury, England: Airlife Publishing. ISBN 1-85310-194-X.
- Taylor, John W. R. (1965). Jane's All The World's Aircraft 1965-66. London: Samson Low, Marston.
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