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Fuji LM-1 Nikko

From Wikipedia, the free encyclopedia

LM-1 Nikko
Fuji LM-1 JASDF Lakeland FL 22.04.09R.jpg
Airworthy Fuji LM-1 Nikko of 1955 in JGSDF markings at Lakeland, Florida, in April 2009
Role military communications aircraft
National origin Japan
Manufacturer Fuji Heavy Industries
First flight 6 June 1955
Introduction 1955
Status Active as Warbirds
Primary user Japanese Air Self-Defense Force
Number built 27
Developed from Beech T-34 Mentor
Variants Fuji KM-2
RTAF-2

The Fuji LM-1 Nikko is a Japanese light communications aircraft of the 1950s.

Development

Fuji Heavy Industries built 176 Beech T-34 Mentor two-seat training aircraft under licence in the early 1950s. Fuji then redesigned the basic Mentor as a four-seat communications aircraft under the designation LM-1. A new lengthened centre fuselage was added to the Mentor's wing, undercarriage and tail assembly. 27 LM-1s were produced during 1955-1956.[1]

Operational history

The LM-1s were delivered to the Japanese Air Self-Defense Force (JASDF) and were used for communications and general duties.[1] After withdrawal from operation, several LM-1s were sold on the U.S. civil market and are flown by civil pilots as "warbirds".[2]

Variants

LM-1
four-seat communications aircraft with 225 h.p. (168 kW) Continental engine (27 built)
LM-2
higher-powered version with 340 h.p. (254 kW) Lycoming engine (2 built)
RTAF-2
a variant developed in Thailand by Thai Aviation Industry.[3]
LM-11 Supernikko
A proposed more powerful version of the LM-1 powered by a 240 hp (180 kW) Lycoming GSO-480-B1A6 engine;[4] became the LM-2.[citation needed]

Specifications (LM-1)

Data from Green, 1956, p. 86

General characteristics

  • Crew: 1
  • Capacity: 3 passengers
  • Length: 25 ft 11 in (7.90 m)
  • Wingspan: 32 ft 9 in (9.98 m)
  • Height: 9 ft 7 in (3.63 m)
  • Wing area: 177.6 sq ft (16.50 m2)
  • Empty weight: 2,234 lb (1,013 kg)
  • Gross weight: 3,375 lb (1,531 kg)
  • Powerplant: 1 × Continental O-470 6-cylinder horizontally opposed air-cooled , 225 hp (168 kW)

Performance

  • Maximum speed: 185 mph (298 km/h, 161 kn)
  • Cruise speed: 157 mph (253 km/h, 136 kn)
  • Service ceiling: 17,388 ft (5,300 m)

References

Notes
  1. ^ a b Green 1956, p. 86
  2. ^ Simpson 2001, p. 246
  3. ^ Forsgren, John. "Aircraft Production in Thailand". Aeroflight.co.uk. 20 November 2004. Retrieved 3 January 2015.
  4. ^ Bridgman 1958, p. 201
Bibliography
  • Bridgman, Leonard (1958). Jane's All the World's Aircraft 1958–59. London: Sampson Low, Marston & Company, Ltd.
  • Green, William (1956). The Aircraft of the World. Macdonald & Co (Publishers) Ltd.
  • Simpson, Rod (2001). Airlife's World Aircraft. Airlife Publishing Ltd. ISBN 1-84037-115-3.


This page was last edited on 18 August 2021, at 14:44
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