Fuji LM-1 Nikko

LM-1 Nikko
Airworthy Fuji LM-1 Nikko of 1955 in JGSDF markings at Lakeland, Florida, in April 2009
General information
Type	military communications aircraft
National origin	Japan
Manufacturer	Fuji Heavy Industries
Status	Retired
Primary user	Japanese Air Self-Defense Force
Number built	27
History
Introduction date	1955
First flight	6 June 1955
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. 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.