Cessna_411

Cessna 411

Cessna 411

American light twin-engine aircraft

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.

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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 with 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 and 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 whilst 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 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

3-view line drawing of the Cessna 411A

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