Cessna 411

The Cessna Model 411 is an American twin-engined, propeller-driven 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
Role Light passenger/cargo aircraft
National origin United States
Manufacturer Cessna
First flight July 18, 1962
Produced 1962-1968
Number built 302
Developed from Cessna 310
Variants Cessna 401/402
Cessna 421

Design and development
Early Cessna 411 from Switzerland fitted with the shorter nose

The 411 is an eight-seat low-wing twin-engined cabin monoplane retractable landing gear and an airstair entrance door.[1] It has two 340 hp (254 kW) Continental GTSIO-520-C engines with three-bladed propellers.[2] It has a retractable tricycle landing gear and an airstair door. The prototype first flew on 18 July 1962.[1] 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. A pressurized version of the 411 was developed as the Cessna 421.[4]

Variants
Cessna 411
Production variant, obtained type certificate awarded in 1964, 252-built.[1][2]
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.[1][2]

Operators

Military operators
 France
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.[5] Two were used by Groupe de Liaisons Aériennes Ministérielles for VIP transport duties.[6]

Specifications

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

Related development

References
Notes
  1. Simpson 1991, p. 109
  2. Federal Aviation Authority Type Certificate Data Sheet A7CE
  3. Simpson 1991, p. 108
  4. Rod Simpson: The General Aviation Handbook, Hinckley 2005, p. 89
  5. Jackson 1979, p. 118
  6. (in French)http://www.avionslegendaires.net/2017/07/actu/le-glam-au-debut-des-annees-1970/
  7. 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.
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