Bell 222

$600,000 executive and utility helicopter certified for single-pilot operations

Overview

Bell United States ICAO: B222 1975–1991 Active $600,000 (2019)

The Bell 222 a twin-engine light helicopter manufactured by Bell Helicopters. Introduced in 1979, it was the first rotorcraft to be certified for single-pilot operations without the use of autopilot.

Live Fleet Activity (B222)

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Specifications

Units
Engine
2 × Lycoming LTS101-650C-3
Engine type
Turboshaft
Power
2 × 620 shp · 462 kW
Avionics
—
Wing tips
No winglets
Seats
9
Crew
—
Cabin width
4 ft 9 in  ·  1.46 m
Cabin height
4 ft 9 in  ·  1.46 m
Cabin length
6 ft 11 in  ·  2.10 m
Exterior length
49 ft 6 in  ·  15.10 m
Tail height
11 ft 6 in  ·  3.50 m
Fuselage diameter
5 ft 3 in  ·  1.60 m
Wing span
39 ft 8 in  ·  12.10 m
Baggage volume
—
Gross weight
—
Empty weight
—
Max takeoff weight
8,100 lb  ·  3,650 kg
Max landing weight
8,100 lb  ·  3,650 kg
Max payload
2,450 lb  ·  1,100 kg
Fuel capacity
240 gal · 900 L · 700 kg (Jet A)
Max cruise speed
139 kt  ·  160 mph  ·  257 km/h
Maximum speed
—
Cruise speed
—
Approach speed
—
Range
326 nm  ·  380 mi  ·  600 km
Fuel burn
—
Ceiling
20,000 ft  ·  6,100 m
Rate of climb
1,600 ft/min  ·  8 m/s
Takeoff distance
—
Landing distance
—
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Bell 222 approaching

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Operational Context

The manufacturing company Bell Helicopters started to develop a twin-turbine engine light helicopter in the late 1960s later designated as the new Bell 222. In January 1974, a model version was exhibited at a helicopter convention.

The Bell 222 was the first light commercial helicopter with twin engines constructed in the United States. In 1975, the manufacturing of 222 started. On August 13, 1976, the helicopter took its maiden flight. On August 16, 1979, it was awarded the Federal Aviation Administration (FAA) type certification, then on December 20, 1979, it was authorized for Visual Flight Rules (VFR) operation. On January 16, 1980, deliveries of 222 started. On May 15, 1980, the helicopter received its approval from the Federal Aviation Administration for single-pilot instrument flight rules (IFR) use.

The helicopter features numerous updated features such as dual hydraulic and electric systems, IFR avionics, sponsons lodging the retractable undercarriage, as well as introducing the use of Noda Matic vibration reduction system that the company had developed for the Bell 214ST.

The Bell 222 is fitted with two Lycoming/Honeywell LTS101-650 engines which produce a maximum of 592 shaft horsepower each. It is a turboshaft engine with a 1-stage low-pressure axial compressor and a 1-stage high-pressure centrifugal compressor, annular combustors, and 1-stage high-pressure turbine and 1-stage low-pressure turbine.

The helicopter’s engine exhaust stacks are situated at the back of the engines. The rotor system of the helicopter incorporates a two-bladed, slightly rigid high-kinetic energy main rotor and underslung rotor design to prevent the need for lead/lag hinges.

The rotor head is equipped with elastomeric bearings that consist of rubber and metal plates and is designed to meet the required stiffness for rotor hub bearing. The 222 is also designed with a pusher-type tail rotor with two blades attached on the left part of the tail boom.

The Bell 222 has a maximum speed of 139 knots and a travel range of 326 nautical miles. It can fly up to 20,000 feet and has a maximum takeoff weight of 3,670 kg.