User:BillCJ/Sandbox/Bell 214
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- This is a sandbox for the updated Bell 214 article.
| Bell 214 | |
|---|---|
 A Bell 214B |
|
| Type | medium-lift helicopter |
| Manufacturer | Bell Helicopter Textron |
| Maiden flight | 1970 |
| Introduced | 1972 |
| Primary user | Islamic Republic of Iran Army |
| Developed from | Bell 204/205 |
| Variants | Bell 214ST |
The Bell 214 medium-lift helicopter is derived from the ubiquitous UH-1 Huey series.
Contents |
[edit] Variants
[edit] Bell 214
Similar in size and apearance to the Bell 205 and Bell 212, the Bell 214 uses a single much larger, 2930shp (2185kW) engine (Lycoming LTC4B-8) and upgraded rotor system giving it a high lifting capacity and good performance at high temperatures and high altitudes. [1] It can be identified by the single large exhaust duct and wide chord rotor blades without stabilizer bars.
- Bell 214 Huey Plus - The prototype 214 flew in 1970. Powered by one Lycoming T53-L-702 turboshaft (1900shp/1415kW). [1]
- 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. [1]
- Bell 214B BigLifter - Bell offered the Bell 214B "BigLifter" for civil use.[1] Receiving certification in 1976, it was built until 1981 with total production of 104.
- Bell 214B-1 - This version of the Bell Model 214B is able to carry up to 12,500-lb (5670-kg) of internal loads. 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 5700kgs. The only difference between the 214B and 214B-1 is the dataplate and the flight manual.
[edit] Bell 214ST
A later derivative, the Bell 214ST (originally "stretched twin", later Super Transporter) was larger and of quite different appearance, with a 17 passenger capacity and two GE CT7-2A engines. This was also intended for sale to Iran, but after the fall of the Shah in 1979, Bell built a total of 100 for other customers. The largest batch of 45 went to Iraq in 1988.[2]
[edit] Text 1
The 214A & C were developed for Iran from the 214 Huey Plus (an improved version of the 205), powered by a massive 2185kW (2930shp) Lycoming LTC4B-8D (with more than twice the power of the 205's T53). Iran's Army took delivery of 287 214A Isfahan troop carrier and supply transport helicopters during the 1970s, while another 39 were delivered as 214C SAR helicopters. A commercial derivative, the 214B BigLifter, powered by a 1185kW (2930shp) Lycoming T5508D turboshaft, was built in smaller numbers for civil customers through to 1981. Its main use is as an aerial crane.
Frawley Civil[2]
[edit] Text 2
The company developed a Model 214A utility helicopter of which a total of 293 was delivered for service with Iranian Army Aviation, which gave them the name Isfahan. Subsequently, 39 generally similar aircraft, but with specific equipment for SAR operations, were delivered to the Iranian Air Force under the designation Bell Model 214C. Testing of these military helicopters convinced Bell that there should be a significant market for a civil variant, for it would have a lifting capability better than any contemporary helicopter within the medium category range. Accordingly, the company announced in early 1974 its intention to develop such an aircraft under the designation Bell Model 214B BigLifter. Generally similar in configuration to the military helicopter, retaining the same airframe, rotor/transmission systems, and powerplant, the BigLifter differs by having emergency escape windows in the cargo doors, an engine fire extinguishing system; and avionics suited to civil rather than military operation.
Two versions were available, and the standard Model 214B was intended for a variety of purposes. They included operation as a 14-passenger transport with a crew of two; as a cargo lifter, with an external cargo hook certificated to carry a maximum load of 3629kg; in an agricultural role, carrying a very similar chemical load; or as a firefighter able to drop a total 2725 litres of fire retardant, carried in cabin and under-fuselage tanks. The alternative Model 214B-1 was certificated to different standards that allowed for operation at a lower gross weight with an internal load. The Model 214B was available to commercial operators from the receipt of certification on 27 January 1976 until production ceased in 1981.
D.Donald "The Complete Encyclopedia of World Aircraft", 19
[edit] Text 3
This development of the UH-1, known as the Model 214 Huey Plus, was first announced in 1970. The prototype was a scaled-up, strengthened and improved Model 205, powered by a 1,415kW Lycoming engine, and this was followed by a 214A demonstration aircraft, which was shipped to Iran for evaluation. This resulted in an order for 287 aircraft, announced by Bell on 22 December 1972. The first 214A flew on 13 March 1974 and deliveries began on 26 April 1975. A further 50 214As and 350 twin-engined 214ST’s were to be built in Iran, but the fall of the Shah put an end to these plans.
VERSIONS
214A: Powered by a 2,185kW (2,930 shp) Lycoming LTC4B-8D turboshaft engine, an improved version of the T55-L-7C fitted to the original Model 214A demonstrator when it went to Iran. It has the 1,528kW (2,050 shp) transmission and rotor drive system developed for the KingCobra experimental gunship helicopter and embodies Bell's NodaMatic nodalised beam concept to minimise vibration. 296 delivered to the Iranian Imperial forces.
214B BigLifter: Commercial version of the 214A, announced on 4 January 1974, providing better lift capability than any commercial helicopter then in production. Powered by a 2,183kW (2,930 shp) Lycoming T5508D turboshaft, it has the same rotor drive and transmission system as the 214A. The engine is flat-rated at a maximum 1,677kW (2,250 shp) and the transmission at 1,528kW (2,050 shp) for take-off, with a maximum continuous power output of 1,379kW (1,850 shp). Advanced rotor hub with elastomeric bearings on the flapping axis; raked tips to main and tail rotors. Other features include an automatic flight control system with stability augmentation and attitude retention; nodalised suspension; separate dual-hydraulic systems; a large engine deck which serves as a maintenance platform; addition of an engine fire extinguishing system; push-out escape windows in the cargo doors, and commercial avionics.
214B-1: As 214B, but with restricted internal gross weight of 5,669kg (12,500 lb).
214C: Search and rescue variant of 214A. Total of 39 delivered to Iran.
214ST: Stretched twin-engined military version originally developed for production and service in Iran; but later transformed into commercial transport (described separately).
POWER PLANT: One 2,183kW Lycoming T5508D turboshaft engine. Standard fuel capacity 772 litres; maximum with auxiliary tank is 1,434 litres.
ACCOMMODATION: One or two pilots and 14 to 15 passengers.
Jane's Helicopter Markets and Systems
[edit] 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 24 214Bs are still flying in commercial service where the hook lifting capacity of 8000 lbs suits them for fire fighting, logging, and similar crane work. User countries are Australia (3), Canada (8), France (1), Korea (8), Norway (2), United States (?).
[edit] Operators
[edit] Military operators
[edit] Specifications (214A)
Data from The International Directiory of Military Aircraft[1]
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 (3,442 kg)
- Max takeoff weight: 15,000 lb with slung load (6,805 kg)
- Powerplant: 1× Lycoming LTC4B-8D turboshaft, 2,930 shp (2,185 kW)
Performance
- Cruise speed: 140 knots (260 km/h)
- Range: 255 mi (475 km)
- Service ceiling 16,400 ft (Dependent on environmental factors such as weight, outside temp., etc) ()
[edit] References
- ^ a b c d e Frawley, Gerard: The International Directory of Military Aircraft, page 34. Aerospace Publications Pty Ltd, 2002. ISBN 1-875671-55-2
- ^ a b Frawley, Gerard: The International Directory of Civil Aircraft, 2003-2004, page 44. Aerospace Publications Pty Ltd, 2003. ISBN 1-875671-58-7
[edit] External links
[edit] See also
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Related development
Comparable aircraft
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Category:U.S. civil utility aircraft 1970-1979 Category:Helicopters
