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Bell 214

By Wikipedia,
the free encyclopedia,

Bell 214
A Bell 214B
Role medium-lift helicopter
Manufacturer Bell Helicopter
First flight 1970
Introduced 1972
Primary user Islamic Republic of Iran Army
Developed from Bell 204/205
Variants Bell 214ST

The Bell 214 is a medium-lift helicopter derived from Bell Helicopter's ubiquitous UH-1 Huey series. The Bell 214ST shares the same model number, but is a larger, much-modified twin-engined derivative.

Design and development

The original development of the Model 214 was announced by Bell in 1970 under the name "Huey Plus". The first prototype was based on a Bell 205 airframe equipped with a Lycoming TS3 engine of 1,900 shp.

The first 214A demonstration prototype followed and was evaluated in Iran during field exercises with the Iranian Armed Forces. The trial was judged successful and an order for 287 214A helicopters followed. The intention was that these aircraft would be constructed by Bell in their Dallas-Fort Worth facility and that a further 50 214As and 350 Bell 214ST helicopters would then be built in Iran. In the event 296 214A models and 39 214C models were delivered, before the Iranian Revolution ended the plans for Iranian production.

Similar in size and appearance to the Bell 205 and Bell 212, the Bell 214 uses a single much larger, 2930shp (2185 kW) engine (Lycoming LTC4B-8) and upgraded rotor system giving it a high lifting capacity and good performance at high temperatures and high altitudes.It can be identified by the single large exhaust duct and wide chord rotor blades without stabilizer bars.

Bell offered the Bell 214B "BigLifter" for civil use. It received certification in 1976. A total of 104 214Bs were produced until 1981. Powered by a 2,930 shp (2,183 kW) Lycoming T5508D turboshaft, it has the same rotor drive and transmission system as the 214A. The transmission is rated at 2,050 shp (1,528 kW) for take-off, with a maximum continuous power rating of 1,850 shp (1,379 kW). The BigLifter features advanced rotor hub with elastomeric bearings; an automatic flight control system with stability augmentation; and commercial avionics.


  • Bell 214 Huey Plus - The prototype 214 flew in 1970. Powered by one Lycoming T53-L-702 turboshaft (1900 shp/1415 kW).
  • Bell 214A/C Isfahan - The 299 Bell 214As for the Imperial Iranian Army Aviation were built beginning in 1972, followed by 39 Bell 214Cs with a hoist and other search and rescue equipment for the Imperial Iranian Air Force.
  • Bell 214B BigLifter - Civil version of the 214A. 104 built.
  • Bell 214B-1 - This version of the Bell Model 214B is limited to a maximum 12,500-lb (5670-kg) maximum weight. The external load is the same as the 214B. This was done for certification purposes in some countries where the limit for "heavy" aircraft was/is at 5700 kg. The only difference between the 214B and 214B-1 is the dataplate and the flight manual.

Operational history

An estimated 170 Bell 214A/Cs remain in Iranian service. The overhaul facility set up at the time of delivery, the Iran Helicopter Support & Renewal Company, is now able to do major rebuilds that could be considered manufacture of new machines.

Approximately 27 214Bs are still flying in commercial service where the hook lifting capacity of 8000 lb suits them for fire fighting, logging, and similar crane work. User countries are Australia (3), Canada (8), France (1), Korea (8), Norway (2), Singapore (3) United States (?).

Per the Type Certificate Data Sheet, Note 10., "Except for a difference in maximum weight, the Model 214B and 214B-1 are identical to each other.


Military operators

Civil operators


  • McDerrmott Aviation - 3


  • Transwest Helicopters - 2


  • Helitrans AS - 2

Specifications (214A)

Data from The International Directiory of Civil Aircraft

General characteristics

  • Crew: 2
  • Capacity: 3,880 lb including 14 troops, or 6 stretchers, or equivalent cargo
  • Length: 48 ft 0 in (14.63 m))
  • Rotor diameter: 50 ft 0 in (15.24 m)
  • Height: 12 ft 10 in (3.90 m)
  • Empty weight: 7,588 lb (3,442 kg)
  • Loaded weight: 13,800 lb (6,260kg)
  • Max takeoff weight: 15,000 lb with slung load (6,805 kg)
  • Powerplant:Lycoming LTC4B-8D turboshaft, 2,930 shp (2,185 kW)


See also

Related development

Comparable aircraft

External links

Text from Wikipedia is available under the Creative Commons Attribution/Share-Alike License; additional terms may apply.

Published in July 2009.

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