Engineering:Piper PA-31T Cheyenne

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Short description: Turboprop-powered series of the PA-31 light transport aircraft
PA-31T Cheyenne
Piper PA-31T1 Cheyenne I Ursella, LUX Luxembourg (Findel), Luxembourg PP1267311070.jpg
PA-31T1 Cheyenne in landing configuration
Role Turboprop
Manufacturer Piper Aircraft
First flight 29 August 1969
Produced 1974–1985[citation needed]
Number built 823
Developed from Piper PA-31 Navajo
Variants Piper PA-42 Cheyenne

The Piper PA-31T Cheyenne is a turboprop development of the earlier PA-31P Pressurized Navajo.

Development

Originally, the aircraft was an upgraded version of the Pressurized Navajo equipped with two Pratt & Whitney Canada PT6A-28 turboprop engines. Later, the aircraft was further refined and developed, including aerodynamic improvements and fuselage extensions. The PA-31T led to the development of the PA-42 Cheyenne III and IV.

Operators

Military operators

 Mauritania
  • Mauritanian Air Force[1]
 United States
  • United States Department of Defense.[2]

Variants

PA-31T Cheyenne
Initial production version, powered by two 620-shp (462-kW) Pratt & Whitney Canada PT6A-28 turboprop engines.
Piper PA-31T Cheyenne
PA-31T-1
Original designation of the PT-31T Cheyenne I. Powered by 500-shp (373-kW) Pratt & Whitney Canada PT6A-II turboprop engines.
PA-31T Cheyenne II
Improved version, renamed version of original powered by two 620-shp (462-kW) Pratt & Whitney Canada PT6A-28 turboprop engines.
PA-31T2 Cheyenne IIXL
Stretched version, powered by two 750-shp (559-kW) Pratt & Whitney Canada PT6A-135 turboprop engines.

Specifications

Data from Jane's All the World's Aircraft 1976–77 [3]

General characteristics

  • Crew: 2
  • Capacity: 4–6 passengers
  • Length: 34 ft 8 in (10.57 m)
  • Wingspan: 42 ft 8 1⁄4 in (13.011 m) (over tip tanks)
  • Height: 12 ft 9 in (3.89 m)
  • Wing area: 229 sq ft (21.3 m2)
  • Airfoil: NACA 632-415 at root, 63A212 at tip
  • Empty weight: 4,870 lb (2,209 kg)
  • Max takeoff weight: 9,000 lb (4,082 kg)
  • Fuel capacity: 382 US gal (318 imp gal; 1,450 L) usable fuel
  • Powerplant: 2 × Pratt & Whitney Canada PT6A-28 turboprops, 620 shp (460 kW) each
  • Propellers: 3-bladed Hartzell HC-BTN-3B constant-speed propellers, 7 ft 9 in (2.36 m) diameter

Performance

  • Maximum speed: 326 mph (525 km/h, 283 kn) at 11,000 ft (3,400 m)
  • Cruise speed: 244 mph (393 km/h, 212 kn) at 25,000 ft (7,600 m) (econ. cruise)
  • Stall speed: 88 mph (142 km/h, 76 kn) (flaps down)
  • Range: 1,702 mi (2,739 km, 1,479 nmi) (econ. cruise, 45 min reserves)
  • Service ceiling: 29,000 ft (8,800 m)
  • Rate of climb: 2,800 ft/min (14 m/s)
  • Takeoff run to 50 ft (15 m): 1,980 ft (600 m)
  • Landing run from 50 ft (15 m): 1,860 ft (570 m)

See also

Related development

Aircraft of comparable role, configuration and era

References

  1. ↑ "World Air Forces 1987 pg. 72". flightglobal.com. https://www.flightglobal.com/pdfarchive/view/1987/1987%20-%202522.html. Retrieved 3 April 2019. 
  2. ↑ Tom, Kaminsky (2000). The United States military aviation directory. Airtime Publishing Inc.. ISBN 978-1-880588-29-1. 
  3. ↑ Taylor, John W.R. (1976), Jane's All The World's Aircraft 1976–77, London: Jane's Yearbooks, pp. 358–359, ISBN 0-354-00538-3 

External links



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