AIDC T-CH-1

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T-CH-1
Aidc-t-ch-1.jpg
T-CH-1 at the RoC Air Force Museum in Ganshan
Role Trainer
National origin Taiwan (Republic of China)
Manufacturer Aerospace Industrial Development Corporation
First flight 23 November 1973
Primary user Republic of China Air Force
Number built 52
Developed from North American T-28 Trojan

The AIDC T-CH-1 Chung Hsing was a turboprop-powered military trainer aircraft produced in Taiwan (Republic of China).

Development[edit]

Derived from the North American T-28 Trojan trainer, the first T-CH-1 prototype flew on 23 November 1973. A second prototype flew the following year. The T-CH-1 was a conventional, low-wing monoplane with tricycle undercarriage that accommodated the student and instructor in tandem.

Production of fifty aircraft for the Republic of China Air Force was spread out between March 1976 and 1981.


Variants[edit]

  • T-CH-1 Chung Hsing : Two-seat basic trainer, light attack aircraft for the Republic of China Air Force.
  • A-CH-1 : Two-seat weapons training aircraft for the Republic of China Air Force.
  • R-CH-1 : Two-seat reconnaissance aircraft for the Republic of China Air Force.

Operators[edit]

 Taiwan (Republic of China)

Specifications[edit]

Data from Jane's All The World's Aircraft 1980–81[1]

General characteristics

  • Crew: 2
  • Length: 10.26 m (33 ft 8 in)
  • Wingspan: 12.19 m (40 ft 0 in)
  • Height: 3.66 m (12 ft 0 in)
  • Wing area: 25.18 m2 (271.0 sq ft)
  • Aspect ratio: 6:1
  • Airfoil: NACA 64-2A215
  • Empty weight: 2,608 kg (5,750 lb)
  • Gross weight: 3,402 kg (7,500 lb)
  • Max takeoff weight: 5,057 kg (11,149 lb)
  • Fuel capacity: 963 L (212 imp gal; 254 US gal)
  • Powerplant: 1 × Avco Lycoming T53-L-701 turboprop, 1,082 kW (1,451 hp)

Performance

  • Maximum speed: 593 km/h; 368 mph (320 kn) at 15,000 ft (4,600 m)
  • Cruise speed: 315 km/h; 196 mph (170 kn) at 15,000 ft (4,600 m) (econ cruise)
  • Stall speed: 93 km/h; 58 mph (50 kn)
  • Never exceed speed: 685 km/h; 426 mph (370 kn)
  • Range: 2,010 km (1,249 mi; 1,085 nmi) (with maximum fuel)
  • Service ceiling: 9,754 m (32,000 ft)
  • Rate of climb: 17 m/s (3,400 ft/min)

See also[edit]

Related development
Aircraft of comparable role, configuration and era

References[edit]

  1. ^ Taylor 1980, pp. 176–177.
  • Taylor, John W.R. (ed.) (1980). Jane's All The World's Aircraft 1980-81. London: Jane's Publishing. ISBN 0-7106-0705-9. 
  • Taylor, Michael J. H. (1989). Jane's Encyclopedia of Aviation. London: Studio Editions. p. 44. 

External links[edit]