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Taylorcraft F22

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F22
A UK-registered F22A in 2019
Role Light utility aircraft
National origin USA
Manufacturer Taylorcraft
First flight August 1, 1988[1]
Introduction 1989[2]
Number built 17[1]
Developed from Taylorcraft F-21[1][3]

The Taylorcraft F22 is a two-seat American light aircraft produced in small numbers by Taylorcraft in the late 1980s and early 1990s.[1][3] It is a further development of the Taylorcraft F-19 via the F-21 design.[1][3] Manufacturing and marketing of the F22 was halted by the financial difficulties of Taylorcraft,[1][3] although plans to restart production existed in 2007.[1]

Design and development

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The F22 is a high-wing, strut-braced monoplane of conventional design.[1][4] Two of the four variants produced had fixed, tailwheel undercarriage, but the F22A and F22C had fixed, tricycle undercarriage instead.[1][3] The pilot and a single passenger sit side-by-side in an enclosed cabin.[1] Power is supplied by a piston engine mounted tractor-fashion in the nose, driving a propeller.[1] The airframe is of welded steel tube, covered in fabric.[5]

The prototype, registered N180GT,[1][3] first flew on August 1, 1989,[1] and production started at Taylorcraft's Lock Haven factory by the end of the year.[2] In 1992, after only 17 F22s were built, Taylorcraft was bankrupt and ceased business.[1]


Variants

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F22 Classic
Developed from the F-21B. Lycoming O-235 engine. Prototype N180GT had tricycle undercarriage, but production examples had tailwheels.[3] (4 built, including prototype[1])
F22A Tracker
Also marketed as the Tri-Classic.[3] Lycoming O-235-powered version with tricycle undercarriage.[1][3] (11 built[1])
F22B Ranger
Also marketed as the STOL-180.[3] Tailwheel version with Lycoming O-360 engine.[1][3] (1 built[1])
F22C Trooper
Also marketed as the TriSTOL.[3] Tricycle undercarriage version with Lycoming O-360 engine.[1][3] (1 built[1])


Specifications (F22A)

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Data from Jackson 2007, p.906

General characteristics

  • Crew: 1 pilot
  • Capacity: 1 passenger
  • Length: 22 ft 3 in (6.78 m)
  • Wingspan: 36 ft 0 in (10.97 m)
  • Height: 7 ft 7 in (2.31 m)
  • Wing area: 183.7 sq ft (17.07 m2)
  • Empty weight: 1,140 lb (517 kg)
  • Max takeoff weight: 1,750 lb (794 kg)
  • Powerplant: 1 × Lycoming O-235-L2C four-cylinder, horizontally-opposed, air-cooled piston engine, 118 hp (88 kW)

Performance

  • Maximum speed: 96 kn (110 mph, 178 km/h)
  • Cruise speed: 87 kn (100 mph, 161 km/h) at 75% power
  • Range: 530 nmi (610 mi, 980 km) at 75% power, 30 minute reserve
  • Service ceiling: 18,000 ft (5,500 m)
  • Rate of climb: 750 ft/min (3.8 m/s) maximum, at sea level
  • Wing loading: 9.53 lb/sq ft (46.5 kg/m2)

References

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Notes

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  1. ^ a b c d e f g h i j k l m n o p q r s t u Jackson 2007, p.905
  2. ^ a b Simpson 1995, p.383
  3. ^ a b c d e f g h i j k l m Simpson 1995, p.384
  4. ^ Taylor 1993, p.961
  5. ^ Jackson 2007, p.906

Bibliography

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  • Jackson, Paul, ed. (2007). Jane's All the World's Aircraft 2007-08 (98th ed.). London: Jane's Publishing Group. ISBN 978-0-7106-2792-6.
  • Simpson, R. W. (1995). Airlife's General Aviation. Shrewsbury: Airlife Publishing.
  • Taylor, Michael J. H. (1993). Jane's Encyclopedia of Aviation. London: Studio Editions.
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