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Bell 47J Ranger

Type of aircraft From Wikipedia, the free encyclopedia

Bell 47J Ranger
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The Bell 47J Ranger is an American single-engine single-rotor light helicopter manufactured by Bell Helicopter. It was an executive variant of the highly successful Bell 47 and was the first helicopter to carry a United States president.

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Design and development

The 47J was a four-seat variant of the earlier three-seat Bell 47H. The 47H was a deluxe variant of the 47G with a fully clad fuselage and an enclosed cabin. The 47H proved to be too small, so Bell developed the 47J. The 47J was a single pilot aircraft with the pilot seat and controls centered in the front of the cabin, and positioned close to the 180° view unobstructed Lexan "bubble" windscreen. A single bench seat at the rear of the cabin spanned its entire width and allowed for a passenger capacity limited by weight to typically 3 or 4 adults.

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Operational history

In March 1957 two Bell 47Js were bought by the United States Air Force as presidential transport and designated H-13J.[1] On 13 July 1957 a H-13J was the first helicopter used by a United States president when it carried Dwight D. Eisenhower from the White House.[1] In March 1962 the two helicopters were moved from presidential duties but were used as VIP transports for the next five years until retired in July 1967.[1]

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Variants

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Agusta-Bell 47J Ranger at the Hellenic Air Force Museum at Dekelia (Tatoi), Athens, Greece
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A Bell 47J-2 Ranger, with floats. (California, 1978)
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Agusta-Bell AB.47J3 Ranger in Italian Carabinieri markings at Pratica di Mare AFB, Italy in 2006
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Bell UH-13J Sioux at the National Museum of the United States Air Force
47J Ranger
Production variant powered by a 220hp Lycoming VO-435-A1B engine.,[2] 135 built.
47J-1 Ranger
Military VIP variant as the H-13J, two built.[3]
47J-2 Ranger
Production variant with a 240hp Lycoming VO-540-B1B engine, powered controls and metal blades.,[2] 104 built.
47J-2A Ranger
Production variant with a 260hp Lycoming VO-540-B1B3 engine and a collective boost system, 75 built.
47J-3
Italian built variant by Agusta-Bell.
47J-3B1
High-altitude variant of the 47J-3
47K
Training variant for the United States Navy, see HTL-7.[4]
HUL-1
United States Navy variant with a 260hp VO-435-B1B, 28 built became UH-13P in 1962.[4]
HUL-1G
Two HUL-1s used by the United States Coast Guard, became UH-13Q in 1962.[4]
HUL-1M
Variant of the HUL-1 with a 250shp YT-62-A-3 turboshaft engine, two built became UH-13R in 1962.[4]
HUL-2
Proposed turboshaft-powered variant, not built.[4]
HTL-7
Model 47K training version of the HUL-1 with a modified two-seat cockpit and a 240hp Lycoming O-435-6 engine, 18 built, later designated TH-13N in 1962.
UH-13J
Two Bell 47J-1 Ranger aircraft utilizing the 179 kW Lycoming VO-435-21 engine acquired for VIP transport of the U.S. President by the U.S. Air Force. Originally designated as H-13J until 1962.[2]
UH-13P
United States Navy variant for use aboard ice-breaking ships, Originally designated as the Navy HUL-1.
TH-13N
The HTL-7 re-designated in 1962.[4]
HH-13Q
The HUL-1G re-designated in 1962.[4]
UH-13R
The HUL-1M re-designated in 1962.[4]
HU-3
Brazilian Navy designation of the 47J.[5]

Operators

 Argentina
 Chile
 Colombia
 Cuba
 Greece
 Iceland
 Indonesia
 Italy
 Mexico
 Spain
 United States
 Venezuela
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Aircraft on display

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The helicopter at its present site on Dandenong-Frankston Road.
Brazil
Canada

Slovenia

United States
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Specifications (Bell 47J-2A)

Data from Jane's All The World's Aircraft 1965–66[22]

General characteristics

  • Crew: 1
  • Capacity: 3 passengers
  • Length: 32 ft 5 in (9.87 m)
  • Height: 9 ft 3 in (2.83 m)
  • Empty weight: 1,833 lb (831 kg)
  • Max takeoff weight: 2,950 lb (1,338 kg)
  • Fuel capacity: 48 US gal (40 imp gal; 180 L)
  • Powerplant: 1 × Lycoming VO-540-B1B vertically mounted air-cooled flat-six, 260 hp (190 kW)
  • Main rotor diameter: 37 ft 2 in (11.33 m)
  • Main rotor area: 1,085 sq ft (100.8 m2)

Performance

  • Maximum speed: 105 mph (169 km/h, 91 kn) at sea level
  • Cruise speed: 91 mph (146 km/h, 79 kn)
  • Range: 258 mi (415 km, 224 nmi) (no reserves)
  • Service ceiling: 11,000 ft (3,400 m)
  • Rate of climb: 870 ft/min (4.4 m/s)
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See also

Related development

Aircraft of comparable role, configuration, and era

Related lists

References

Bibliography

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