The Cessna Model 411 is an American twin-engined, propeller-driven, non-pressurized light aircraft built by Cessna Aircraft. It was that company's largest business aircraft to enter production when it first flew in 1962.
| Cessna 411 | |
|---|---|
 Cessna 411A | |
| General information | |
| Type | Light passenger/cargo aircraft |
| National origin | United States |
| Manufacturer | Cessna |
| Number built | 302 |
| History | |
| Manufactured | 1962-1968 |
| First flight | July 18, 1962 |
| Developed from | Cessna 310 |
| Variants | Cessna 401/402 Cessna 421 |
Design and development
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The 411 is an eight-seat low-wing twin-engined cabin-class monoplane with retractable landing gear, pressurized cabin, and an airstair entrance door, which first flown on 18 July 1962.[1] It has two 340 hp (254 kW) Continental GTSIO-520-C engines with three-bladed propellers.[2] During 1965 Cessna developed two generally similar and lower-cost versions, the Model 401 and Model 402.[3] Production of the 411 finished in 1968 whilst a pressurized version of the 411 was developed as the Cessna 421.[4]
Variants
editOperators
editMilitary operators
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France- French Air and Space 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.[5] Two were used by Groupe de Liaisons Aériennes Ministérielles for VIP transport duties.[6]
Specifications
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Data from Jane's All The World's Aircraft 1965-66 [7]
General characteristics
- Crew: two
- Capacity: four to six passengers
- Length: 33 ft 5 1⁄2 in (10.20 m)
- Wingspan: 39 ft 10 1⁄4 in (12.15 m)
- Height: 11 ft 6 1⁄2 in (3.52 m)
- Wing area: 200 sq ft (19 m2)
- Empty weight: 3,820 lb (1,733 kg)
- Max takeoff weight: 6,500 lb (2,948 kg)
- Fuel capacity: 170 US gal (140 imp gal; 640 L) standard, 196 US gal (163 imp gal; 740 L) with auxiliary tanks
- Powerplant: 2 × Continental GTSIO-520 air-cooled geared, turbocharged flat-six engines, 340 hp (250 kW) each
- Propellers: 3-bladed constant-speed, 7 ft 4 in (2.24 m) diameter
Performance
- Maximum speed: 268 mph (431 km/h, 233 kn) at 16,000 ft (4,900 m)
- Cruise speed: 216 mph (348 km/h, 188 kn) at 25,000 ft (7,600 m) (econ cruise)
- Stall speed: 84 mph (135 km/h, 73 kn) (flaps down)
- Range: 1,300 mi (2,100 km, 1,100 nmi) at 216 mph (188 kn; 348 km/h) and 25,000 ft (7,600 m), normal fuel
- Service ceiling: 26,000 ft (7,900 m)
- Rate of climb: 1,600 ft/min (8.1 m/s)
- Takeoff distance to 50 ft (15m): 1,890 ft (580 m)
- Landing distance from 50 ft (15 m): 1,815 ft (553 m)
See also
editRelated development
References
edit- Notes
- ^ a b c Simpson 1991, p. 109
- ^ a b c Federal Aviation Authority Type Certificate Data Sheet A7CE
- ^ Simpson 1991, p. 108
- ^ Rod Simpson: The General Aviation Handbook, Hinckley 2005, p. 89
- ^ Jackson 1979, p. 118
- ^ (in French)http://www.avionslegendaires.net/2017/07/actu/le-glam-au-debut-des-annees-1970/
- ^ Taylor 1965, p.210.
- Bibliography
- 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.
External links
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