- Aircraft History, Specification and Information -
Bell 212
Bell 212 C-GWWL Ascent Helicopters Ltd
1975 Bell 212
C-GWWL (sn 30702)
Ascent Helicopters Ltd
Photo taken Sep. 2009
Penticton Airport, BC Canada
Photo © AirplaneMart.com
Bell 212 - Alpine Helicopters - C-GAHV - Helicopter Hovering While Picking Up Water Bucket For Forest Fire Fighting
Bell 212
C-GAHV (sn 30699)
Alpine Helicopters
Picture taken July 02, 2004
Lillooet Airport, BC Canada (AR3 / CAR3)
Photo © AirplaneMart.com
Bell 212 Twin Huey - Alpine Helicopters Kelowna Canada - C-GIRZ - Fire Fighting Helicopter Pilot At Work
Bell 212
C-GIRZ (sn 30622)
Alpine Helicopters
Pilot visual lookout during water bucket pick up for fire fighting operations.
Photo taken July 01, 2004
Lillooet Airport, BC Canada (AR3 / CAR3)
Photo © AirplaneMart.com

The Bell 212 Twin Huey (also known as the Twin Two-Twelve) is a two-bladed, twin-engined, medium helicopter that first flew in 1968. Originally manufactured by Bell Helicopter in Mirabel, Quebec, Canada, the 212 is marketed to civilian operators and has a fifteen-seat configuration, with one pilot and fourteen passengers. In cargo configuration the 212 has an internal capacity of 6.23 m³ (220 ft3). An external load of up to 5,000 lb (2,268 kg) can be carried.


Based on the stretched fuselage Bell 205, the Bell 212 was originally developed for the Canadian Forces as the CUH-1N and later redesignated as the CH-135. The Canadian Forces took delivery of 50 starting in May, 1971. At the same time the United States military services ordered 294 Bell 212s under the designation UH-1N.

By 1971 the 212 had been developed for commercial applications. Among the earliest uses of the 212 in civil aviation was by Helicopter Service AS of Norway to be used in support of offshore oil rigs. Today the 212 can be found used in logging operations, maritime rescue and resupply in the Arctic on the Distant Early Warning Line or North Warning System.

The 212's main rotor is powered by a Pratt & Whitney Canada PT6T-3 Twin-Pac made up of two coupled PT6 power turbines driving a common gearbox. They are capable of producing up to 1,342 kW (1,800 shp). Should one engine fail the remaining engine can deliver 671 kW (900 shp) for 30 minutes, or 571 kW (765 shp) continuously, enabling the 212 to maintain cruise performance at maximum weight.

Early 212s configured with an Instrument Flight Rules (IFR) instrument package were required to have a large and very obvious fin attached to the roof of the aircraft, above and slightly behind the cockpit. This fin was initially determined necessary to alter the turning performance of the aircraft during complex instrument flight maneuvers, but now not required due to revised stipulations of the type certificate. Many aircraft still fly with the modification.
In 1979, with the purchase of eight by the Civil Air Authority, the 212 became the first U.S. helicopter sold in PRC.

The ICAO designator for this aircraft as used in a flight plan is B212.

The Bell 412 is a further development of the Bell 212, the major difference being the composite four-blade main rotor.


Bell Model 212 - Bell Helicopters company designation for the UH-1N.
Twin Two-Twelve - Civil utility transport version. It can carry up to 14-passenger.
Agusta-Bell AB 212 - Civil or military utility transport version. Built under license in Italy by Agusta.
Bell Model 412 - Bell 212 with a four-bladed semi-rigid rotor system. See Bell 412 for further information.


Civil operators
Brazil - Lider Taxi Aereo
Canada - Alpine Helicopters, CHC Helicopter
Faroe Islands - Atlantic Airways
Greenland - Air Greenland
Philippines - GMA News, Philippine Air Cargo Delivery

Government operators
Canada - Canadian Coast Guard
Germany - Federal Ministry of the Interior
Croatia - Police
Japan - Japan Coast Guard
Macedonia - Police
Mexico - various police forces
Philippines - Philippine National Police
Serbia - Police
United States - San Diego Fire Department

Specifications (Bell 212)

General characteristics
- Crew: 1 (two for IFR operation)
- Capacity: 14
- Length: 57 ft 1.68 in (17.43 m)
- Rotor diameter: 48 ft (14.64 m)
- Height: 12 ft 6.83 in (3.83 m)
- Disc area: 1,809.5 ft² (168.3 m²)
- Empty weight: 6529.4 lb (2961.7 kg)
- Max takeoff weight: 11,200 lb (5,080 kg)
- Powerplant: 1× Pratt & Whitney Canada PT6T-3 or -3B turboshaft, 1,800 shp (1,342 kW)

- Never exceed speed: 120 knots (138 mph, 223 km/h)
- Maximum speed: 120 knots (138 mph, 223 km/h)
- Cruise speed: 100 knots (115 mph, 186 km/h)
- Range: 237 nm (439 km)
- Service ceiling: 17,400 ft (5,305 m)
- Rate of climb: 1,745 ft/min (532 m/min)
- Disc loading: 6.19 lb/ft² (300.5 kg/m²)

Last updated December 23, 2009
This article is licensed under the GNU Free Documentation License. It uses material from the Wikipedia article "Bell 212".
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