Canada - 1999
Bombardier's Canadair Regional Jet pioneered the new 50 seat jet class, and has
since become a runaway sales success.
The Canadair Regional Jet - or CRJ - is designed to offer the high speed
advantages of much larger jets, with similar standards of service while at the
same time offering operating economics, particularly over longer stage lengths,
close to that of comparable size turboprops.
The concept of a stretched airliner derivative of the Challenger is not new,
Canadair (now part of Bombardier Aerospace) originally studied a 24 seat
stretched development of the CL-600 up to 1981. Design studies for a stretched
airliner based on the 601 however were first undertaken in 1987, leading
Canadair to launch the Regional Jet program on March 31 1989. The first of three
development aircraft took to the skies for the first time on May 10 1991.
Transport Canada certification was awarded on July 31 1992, allowing the first
customer delivery to Lufthansa that October.
Major changes over the Challenger apart from the stretched fuselage include a
new advanced wing optimised for airline operations, higher design weights, EFIS
flightdeck with Collins Pro-Line 4 avionics suite, new undercarriage, additional
fuel capacity and slightly more powerful CF-34 engines.
The original CRJ-100 series - the 100, 100ER and 100LR - was augmented by the 200 series (with more efficient engines) in 1995. The Series 200 is available in standard 200, long range 200LR with optional greater fuel capacity, and the extended range Series 200LR (all three are offered in B form with CF34-3B1s for improved hot and high performance). Corporate shuttle configurations are also available as the Corporate Jetliner and the SE (Special Edition).
The two-pilot flight deck is fitted with a Rockwell Collins Pro Line 4 electronic flight and information system (EFIS) and an engine indication and crew alerting system (EICAS). The instrument displays include dual primary flight displays and dual multifunction displays.
The system has an integrated dual automatic flight control system, dual attitude heading reference system (AHRS) and a dual air data system. The aircraft has Cat II operational capability. The addition of an optional Flight Dynamics Inc HGS 2100 HUD head up guidance system gives the aircraft Cat IIIa capability.
The aircraft also has a terrain collision avoidance system (TCAS) and a Rockwell Collins digital weather radar. The flight data recorder is supplied by Lockheed Martin Fairchild.
The communications system is a dual VHF navigation and communications radio. HF and VHF radios and selective calling are optional communications.
The windscreen and cockpit side windows are fitted with electric de-icing systems.
The design of the CRJ200, which evolved from the Challenger 604 business jet, is for regional airline operations. The aircraft is equipped with high efficiency engines giving a range up to 3,050km. The wings are transonic and are fitted with winglets for efficient high-speed flight.
The fuselage is of semi monocoque design. The main cabin is nearly 15m in length with a centre-line width of 2.57m and can seat between 15 and 52 passengers.
The rear baggage compartment provides a baggage space of 9m³. The cabins and baggage compartment are pressurised and air-conditioned.
Two General Electric high efficiency CF34-8C1 turbofan engines provide 56.4kN thrust at take-off and 61.3kN thrust with auto power reserve. The engines are equipped with pneumatically operated thrust reversers. The engine nacelles mounted on the sides of the rear section of the fuselage are developed and supplied by Thales Shorts.
Engine bleed air feeds the wing leading edge and engine intake cowling anti-icing systems.
There are two integral wing fuel tanks with a fuel capacity of 5,300 litres and an optional centre wing tank increases the fuel capacity by 2,780 litres. There are three gravity-refuelling points and one pressure-refuelling point on the wings.
A Honeywell GTCP 36-150 auxiliary power unit is installed in the rear fuselage section. Electrical power is provided by two 30kVA engine driven generators.
The aircraft is fitted with Dowty retractable tricycle type landing gear. The landing gear is equipped with Aircraft Braking System wheels and multiple disc steel brakes, Goodyear tyres and Hydro Aire Mark III anti-skid units. The main landing gear retracts inward and the nose unit retracts forward.
|Passengers||up to 52 seats|
|External fuselage diameter||2.69m|
|Baggage compartment volume||9.0m³|
|Cabin length, excluding cockpit||14.76m|
|Maximum cabin width||2.57m|
|Floor level cabin width||2.18m|
|Floor area, excluding cockpit||32.1m²|
|Maximum ramp weight||21,636kg|
|Maximum take-off weight||21,523kg|
|Maximum landing weight||20,275kg|
|Maximum zero fuel weight||17,917kg|
|Operating empty weight||13,730kg|
|Payload with full fuel||3,651kg|
|Turboprop engines||2 General Electric CF34-3B 1|
|Power||38.8kN at take-off|
|Power||41.0kN with auto power reserve|
|Maximum range, long range cruise||1,787km|
|Maximum cruise speed||621km/h|
|Maximum operating altitude||12,496m|
|FAR take-off airfield length (SL, ISA at max. take-off weight)||1,527m|
|FAR landing airfield length (SL at max. landing weight)||1,425m|
|Noise level, take-off, FAR 36||89 EPNdB|
|Noise level, sideline, FAR 36||98 EPNdB|
|Noise level, approach, FAR 36||94 EPNdB|