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Bell 214 for sale

Bell 214 for sale

Bell 214ST Super Transport – multi-purpose helicopter developed by the American company Bell Helicopter Textron Bell 214ST helicopter is a helicopter Bell 214A, which began in military-transport version in 1972 year for Iran’s army, requesting the helicopter 283, optimized for mountainous terrain and high temperatures. You can find Bell 214 for sale offers below. Bell 214 prices you can get by contacting our specialists. Average Bell 214 price $3,000,000

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Bell 214 specifications:

ModificationBell 214ST
Main rotor diameter, m15.85
Tail rotor diameter, m2.95
Length, m18.95
Height, m4.84
Mass, kg
blank4284
Max takeoff7938
Internal fuel, l1647 + optional 659
Engine type2 TBG General Electric CT7 file-2A
Power, kW2 x 1212
Cruising speed, km/h259
Range, km1020
Combat range, km858
Rate of climb, m/min543
Service ceiling, m1950
Static ceiling, m1460
Crew, pers1-2
Payload:18 passengers or 3493 kg of cargo

More information about Bell 214

Bell 214 for sale

First flight

The first flight of the prototype helicopter Bell 214ST was held in February 1977 year. Production of the three pre-production helicopters began in 1978, and in 1979 started the production of the first batch of 107 214ST helicopters, which began in 1982 and was completed in the year 1989 year.

In the year 1982 214ST helicopter was certified in the United States in a civil transport version with possibility of use as a multi-purpose. The helicopter also has passed certification of transport category in Canada, Japan, England, the United States, where it is used to service drilling platforms at sea. Additionally, in military-transport version ordered 45 helicopters for Iraq, 11 for Peru, 9 to 4 for Venezuela and Thailand.

Bell 214ST helicopter continues to guide the development of helicopters, Bell 205, 212 and 214, it can be seen as a new next-generation helicopter shop by tonnage approaching multipurpose and transport helicopters Sikorsky S-70. The possibility of using četyrehlopastnogo on a helicopter rotor with sleeve “type 600”.

Helicopter Bell 214ST is developed on the own funds of the firm “Bell”, izrashodovavšej on its development and certification of more than 100 million. dollars. Price of serial helicopters Bell 214ST in 1988 totaled 6.5 million dollars.

Design.

The helicopter is made in single-rotor diagram steering screw two GTD and ski gear.

All-metal fuselage of semi-monocoque type reinforced; on both sides of the fuselage are large cargo doors, sliding on guides, and doors for the crew. In the cockpit, with the maximum length of 4.13 m, width 2.41 m, and the volume of 8.95 M3, in the passenger version of the 15 seats in three rows and two additional seats at the base of the main rotor shaft, a cargo variant of the seat. Luggage compartment volume of 1.84 M3 is located behind the cargo cabin. A standard system of heating and ventilation.

Horizontal stabilizer, managed, rectangular in plan, 2.85 m span, size 2.22 m 2. End beam made in the form of Kiel, has a height of 1.5 m and 1.65 square m2.

Rotor bilobed, rectangular in plan, blades, improved design with application of KM; spar and Stringer along the trailing edge of the blade are made of glass fibre with unidirectional arrangement of fibres, edging made of fiberglass with the direction of the fibers at an angle of + 45 ° , compartments between the tie and the Stringer along back edges have a cellular structure with material “Nomex” as a placeholder. Toe blades closed protective tape from titanium, the ending-stainless steel blades, detachable blade chord 0.84 m. Bush with General horizontal hinge is elastomeric bearings applied on a helicopter developed by Bell System “Noda-Matic” suspension rotor pylon, which provides reduced vibration levels and incorporating elastomeric dampers, do not require lubrication during operation 1500č. Brake rotor standard.

Tail rotor diameter 2.95 m, bilobed, interchangeable blades. Spar has the shape of a sock, blades made of stainless steel, the middle part of the blade is made of an aluminium alloy with cellular structures, Stringer along the trailing edge of the blade made of fiberglass. The chord of the airfoil 0.36 m.

Contractor ski chassis. Wheel track 2.64 m. Variant with removed tricycle-equipped landing gear with standard gauge 2.83 m.

The powerplant.

The powerplant. Two General Electric engine mated ST7-2A with a free turbine placed in the fairing behind the main rotor shaft. Take-off engine power 1210kVt. In case of failure of one engine, the second is able to provide work in emergency mode, developing the power 1270kVt. Dimensions: length of 1,151 m, diameter 0.635 m. Engines equipped with a de-icing system.

Fuel system includes seven interrelated capacity tanks 1674l. Accommodate two additional fuel tanks with a capacity of 2 x 329l at the rear of the cab and auxiliary tank 95l under the passenger seat.

The transmission consists of a main gearbox, gear reducer combination intermediate, tail rotor gearbox, connecting shafts. Rotor drive transmission is designed for maximum power transfer 1730kVt, 1420kVt at maximum continuous mode and 1270 kW with one engine. Combined gearboxes, intermediate and tail rotor can operate without lubricant within one hour.

Control system of bearing and steering booster hydraulic screws, duplicated. There is a stability enhancement system for pitch, roll, yaw. Hydraulic system ensures the functioning of the control systems and brake gear; oil cooling system in transmission and combined gearbox. Pressure in the hydraulic system IPA consists of two pumps 13.2 with a drive from the main gearbox. Hydraulic fluid consumption 25.4 l/min and 19 l/min (hydraulic system).

Electrical system dubbed, includes two generators driven by the main gearbox.

A helicopter mounted systems improve stability and controllability (SCAS), adjust the position and height of the helicopter (AARS), automatic (using computers) fly-by stabilizer.

Electronic equipment includes a standard navigation system and dual redundant communication, radionavigacionnuû equipment, direction finder, radiootvetčik, distance measuring equipment, air data calculator. Setting low frequency radar navigation system. On demand of the customer installs non icing system, emergency floating chassis, suspension nodes for external cargo winch, two inflatable life rafts for 10-12 people.

Bell 214 prices about 3 000 000 USD.

Bell 214 specs.

ModificationBell 214ST
Main rotor diameter, m15.85
Tail rotor diameter, m2.95
Length, m18.95
Height, m4.84
Mass, kg
blank4284
Max takeoff7938
Internal fuel, l1647 + optional 659
Engine type2 TBG General Electric CT7 file-2A
Power, kW2 x 1212
Cruising speed, km/h259
Range, km1020
Combat range, km858
Rate of climb, m/min543
Service ceiling, m1950
Static ceiling, m1460
Crew, pers1-2
Payload:18 passengers or 3493 kg of cargo

Bell 214 BigLifter -multi-purpose helicopter developed by the American company Bell Helicopter Textron Bell helicopter-based Model 214 Huey Plus helicopter created as a hybrid variant of the UH-1 h Huey and Bell Model 309 KingCobra (used his transmission and main rotor) helicopter is optimized for use in the Middle East. The first prototype flew in December 1972 years. Series production helicopter began in April 1975 year. the Iranian AIR FORCE Helicopter Dubai, Oman, Thailand, Philippines and Ecuador.

 Bell 214A the first serial modification.
 Isfahan Bell 214A built by request of the Iranian air force.
AB-214Amodifying Bell 214A built by the Italian company Agusta c GTD LTC4B-8 d (2214 kW). The helicopter was AIR FORCE of Uganda.
 Bell 214V GTD with Avro Lycoming T5508D.
 Bell 214C Search and rescue version for the Iranian air force.
ModificationBell 214V
Main rotor diameter, m15.24
Tail rotor diameter, m2.95
Length, m18.52
Height, m4.57
Maximum takeoff weight, kg7257
Internal fuel, kg
Engine typeTBG 1 Textron Lycoming T5508D
Power, kW1 x 2185 (1528 during takeoff)
Cruising speed, km/h259
Range, km1100
Combat range, km420
Service ceiling, m4500
Static ceiling, m2500
Crew, pers2
Payload:18 passengers or 3175 kg of cargo

 

Bell 214 development.

Bell 214 is an American multi-purpose medium-duty helicopter from 1970 year aviation company “Bell Helicopter”.

Start of design work on the creation of a multipurpose helicopter Bell 214 was initiated in the year 1968, while the helicopter initially assumed his multi-objective assignment and on calculations of American aircraft manufacturers had to be exploited not only civil but also military aviation.

In the year 1970 the aircraft undertook its first flight, however, has not satisfied all requirements, was intended to further optimize its design and technical characteristics. In fact, the helicopter Bell model 214 was introduced in 1972, and originally entered the military service in the armed forces of Iran, where operated and as transport aircraft and as a combat aircraft capable of combating armed detachments of the enemy and soft-skinned vehicles.

The Bell 214 helicopter was able to prove myself very well, bringing his issue continued during the 11 years from 1970 to 1981 year, and currently, the helicopter continues to be used for both military and civilian.

Bell 214 history.

Bell 214ST Super Transport – the multi-purpose helicopter developed by the American firm Bell Helicopter Textron. The Bell 214ST helicopter is development of the Bell 214A helicopter which began to be developed in military transport option in 1972 for the army of Iran which ordered 283 helicopters optimized for operation in the conditions of the hilly terrain and high temperatures.

The first flight of the skilled Bell 214ST helicopter took place in February, 1977. Production of three pre-series helicopters began in 1978, and in 1979 production of the first serial party from 107 helicopters 214ST which deliveries began in 1982 began and came to the end in 1989.

The helicopter 214ST in 1982 was certified in the USA in civil transport option with a possibility of use as multi-purpose. The helicopter underwent also certification on transport category in Canada, Japan, England, the USA where it is used for service of drilling platforms at the sea. In addition in military transport option 45 helicopters for Iraq, 11 for Peru, 9 for Thailand and 4 for Venezuela are ordered.

The Bell 214ST helicopter continues the direction of development of the Bell 205, 212 and 214 helicopters, it can be considered as the new helicopter of the next generation which according to characteristics of loading capacity approaches the multi-purpose and transport Sikorsky S-70 helicopters. The possibility of use by helicopter of the four-blade bearing screw with the “type 600” plug was considered.

The Bell 214ST helicopter is developed on own means of Bell which spent more than 100 million dollars for its development and certification. The price of the serial Bell 214ST helicopter in 1988 made 6.5 million dollars.

Design. The helicopter is executed according to the single-screw scheme with the steering screw, two GTD and the ski chassis.

The fuselage an all-metal semi-monocoque of type of the strengthened design; on both sides of the fuselage the big cargo doors shifted on guides, and a door for crew are located. In passenger option of 15 seats located in three ranks and in addition two seats at the basis of a shaft of the bearing screw in cargo option of a seat clean up the cabin having the maximum length 4.13m, width 2.41m and volume 8.95m3. The luggage compartment volume 1.84m3 is behind a cargo cabin. There is a standard heating system and ventilation.

The stabilizer is operated, squared in the plan, scope 2.85m, the area 2.22m2. The trailer beam executed in the form of Kiel has height 1.5m and the area 1.65m2.

The bearing screw two-bladed, with squared blades in the plan, an advanced design with application of KM; the longeron and a stringer along a back edge of the blade are made of fiber glass with the unidirectional arrangement of fibers, a covering are made of fiber glass with the direction of fibers at an angle +45, compartments between a longeron and a stringer along a back edge have a cellular design with the material “Nomex” as filler. The sock of the blade is closed by a protective tape from the titan, a blade ends – from stainless steel, removable, a blade 0.84m chord. The plug with the general horizontal hinge has elastomeric bearings. By helicopter the Noda-Matik system of a suspension bracket of a pole of the bearing screw developed by Bell, providing decrease in level of vibrations and which is turning on the elastomeric shock-absorbers which are not demanding lubricant during 1500 h work is applied. A brake of the bearing screw standard.

Steering screw diameter 2.95m, two-bladed, blades interchangeable. The longeron has the blade sock form, a middle part of the blade from aluminum alloy with filler of a cellular design, the stringer along a back edge of the blade from fiber glass is made of stainless steel. Blade 0.36m chord.

The chassis not cleaning up ski. Chassis 2.64m track. The option with the standard three-basic chassis with a track 2.83m is possible.

Power plant. Two coupled CT7-2A General Electric engines with the free turbine are placed in a fairing behind shaft of the bearing screw. Take-off engine capacity is 1210 kW. In case of refusal one engine of the second it is capable to ensure functioning in the extraordinary mode, developing the power of 1270 kW. Engine sizes: length 1.168m, diameter 0.635m. Engines are supplied with anti-icing system.

The fuel system includes seven interconnected tanks with a capacity of 1674 l. Installation of two additional tanks with a capacity of 2 x 329 l in a back part of a cabin and an auxiliary tank with a capacity of 95 l under a passenger seat is provided.

Transmission consists of the main reducer, an intermediate reducer, the combined reducer, a reducer of the steering screw, connecting shaft. Transmission of the drive of the bearing screw is calculated on transfer of the maximum power of 1730 kW, 1420 kW on the maximum long mode and 1270 kW during the operation of one engine. Reducers combined, intermediate and the steering screw can work without lubricant within an hour.

Control system bearing and steering screws hydraulic, busterny, duplicated. There is a system of increase in stability on pitch, a list, roving. The hydraulic system provides functioning of a control system and the drive of brakes; there is an oil cooling system in transmission and the combined reducer. Pressure in a hydraulic system 21.3mpa is provided with two pumps with the drive from the main reducer. A consumption of working liquid in a hydraulic system 25.4l/mines and 19л/мин/¼¿¡ to a hydraulic system of general purpose).

The electric system duplicated turns on two generators with the drive from the main reducer.

By helicopter systems of increase in stability and controllability (SCAS), adjustment of situation and height of the helicopter (AARS), automatic (with use of the COMPUTER) an electroremote control system of the stabilizer are installed.

The electronic equipment includes standard system of navigation and connection with double reservation, the radio navigational equipment, a radio compass, the radio defendant, the ranging equipment, the calculator of air signals. Installation of radar station, the low-frequency navigation system is provided. Upon the demand of the customer the anti-icing system, the emergency float-operated chassis, suspension bracket knots for external freights, the winch, two inflatable liferafts of people is installed on 10-12.

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