Bombardier Challenger 600
The Bombardier Challenger 600 is a twin-engine, fanjet aircraft with a retractable gear. The Challenger 600 is a low-wing airplane produced by Bombardier between the years 1981 and 1983, Serial Numbers 1023 through 10857. It seats up to 9 passengers and 2 pilots.
Wing span: 61 ft 10 in
Length: 68 ft 5 in
Height: 20 ft 9 in
Cabin Height: 6 ft 1 In
Cabin Width: 8 ft 2 In
Cabin Length: 28 ft 4 In
Cabin Volume: 1,035 cu ft
Door Height: 5 ft 8 In
Door Width: 3 ft
Internal Baggage: 115 cu ft
Max TO weight 41,100 LBS
Empty Weight: 31,000 LBS
Maximum Payload: 6850 LBS
Fuel capacity: 14,640 LBS
Manufacturer: Lycoming (now Honeywell)
Model: ALF 502L-2C
Horsepower: 7,500 LBS
Overhaul (HT): 4000hr TBO
Dual Collins / Sperry avionics
Terrain Awareness System
Dual WAAS GPS
Performance specifications on Bombardier Challenger 600
|Thrust: 7500.00 x 2||Gross Weight: 41,100 lbs|
|Top Speed: 477 kts||Empty Weight: 31,000 lbs|
|Cruise Speed: 458 kts||Fuel Capacity: 14,640 lbs|
|Stall Speed (dirty):||Range: 2,800 nmi|
|Rate of Climb: 3,400 fpm||Rate of Climb (One Engine): 743 fpm|
|Service Ceiling: 41,000||Ceiling (One Engine):|
|Ground Roll: 6,200||Ground Roll 4,150|
|Takeoff Roll Over 50 ft:||Landing Roll Over 50 ft:|
The Bombardier Challenger 600 series is a family of business jets. It was first produced by Canadair (as an independent company), and then produced from 1986 by Canadair as a division of Bombardier Aerospace. As of December 2017, close to 1,100 Challenger 600 Series have been delivered. Including the Challenger 300 and Challenger 850, the 1,600 Bombardier Challengers in-service had logged 7.3 million hours and over 4.3 million flights by early 2017.
Circa 1974, American aviation inventor Bill Lear conceptualized the LearStar 600, a low-range long-distance business jet which was powered by a pair of Garrett TFE731-1 geared turbofan engines and equipped with a supercritical wing. The name LearStar was not original to this concept, Lear had previously used the name for his conversion of Lockheed Lodestars into business transports. However, Lear lacked the capabilities to launch such an aircraft, and thus sought out other agencies to collaborate with to both produce and sell it, including the Canadian aerospace manufacturer Canadair. According to authors Ron Picklet and Larry Milberry, Canadair's top management were of the opinion that Lear's concept was sketchy at best. Lear did not have an expert grasp of aeronautical engineering; so far, he had only been able to pay a California aeronautical consultant to undertake very preliminary design explorations.
Following a study, contrasting the proposed Learstar against rivals such as the Lockheed Jetstar, Dassault Falcon 50, and Grumman Gulfstream II, Canadair decided to give its backing to the idea near the end of 1975. According to aerospace industry publication Flight International, the program was viewed by many Canadians as a step towards developing a privately driven high-technology aviation industry that would compete at a global level. Perhaps more importantly, the Canadian government had issued a demand that Canadair become self-sufficient, thus the company wanted to depend less upon subcontracting arrangements with other firms, such as France's Dassault Aviation and America's Boeing, or providing support packages for existing aircraft that they had already ended production of, such as the CF-5 fighter. Canadair felt a need to prove its ability to independently develop original high-tech projects at this time.
Canadair planned to use Lear's name and skills at self-promotion to secure extensive financial guarantees for a business jet project from the Canadian Federal government. This proved an effective choice: future Prime Minister Jean Chrétien specifically refers to the effect of personal contact with Lear on his decision to direct financial support to Canadair's program. At the time of these events, Chrétien was successively President of the Treasury Board, Minister of Industry, Trade and Commerce, and Minister of Finance, in the Canadian Federal government. Due to the use of letters of comfort, the extent of the Ministry's financial commitments for Canadair could be kept from parliament and the public for several years. These financial guarantees were later used as an academic example of insufficient monitoring and lax controls in government support of industry.
In April 1976, Canadair acquired the LearStar 600 concept. By this point, it was a 63 by 53.3 ft (19.2 by 16.2 m) long and wide aircraft capable of a maximum speed of Mach 0.85 and a range of 3,910 nmi; as an executive jet it had sufficient capacity for 14 passengers, in a freighter configuration it had a 7,500 lbs payload capacity, loaded and unloaded via a forward door, or as commuter airliner it could seat up to 30 passengers in a 2–1 seating configuration. Canadair developed the design into a large airframe furnished with a new supercritical wing design, new avionics and engines, as well as for compliance with new FAR part 25 standards. The configuration was frozen in August and a 1/25 model was tested in the National Aeronautical Establishment transonic wind tunnel. Reportedly, in excess of 1,800 hours of wind tunnel testing was performed upon the supercritical wing alone.
Backed by the Federal Government, the program was launched on 29 October 1976 with firm orders and deposits for 53 aircraft. Within the next two years, roughly 2,500 employees would be involved in designing the aircraft. Various changes to the original Learstar configuration had been made on the run up to launch, such as the conventional tailplane being substituted for a T-tail counterpart after the former was found to be in the path of the engine's exhaust flow, the relocation of fuel storage to the wings, and multiple increases of the aircraft's gross weight. Following disagreements over the direction of the program, Bill Lear was phased out of involvement; accordingly, in March 1977, the aircraft was renamed the Challenger 600. Reportedly, following his disassociation with the venture, Lear referred to Canadair's revised design as Fat Albert. Following Lear's death in May 1978, Canadair paid an estimated $25 million to his estate for his contribution to the program.
Due to the expansion of the design, the original powerplant configuration became untenable; thus engine manufacturer Lycoming proposed developing a new model, the Lycoming ALF 502L, which Canadair's design team accepted for the enlarged Challenger and drew up its general arrangement around. The type's wide cargo door had been designed in response to the needs of FedEx, the type's original launch customer, having placed an order for 25 aircraft. Additionally, FedEx had experienced problems with the General Electric CF34 engines, and favored the Lycoming ALF 502D instead; those later had delivery troubles and lacked performance. Reportedly, FedEx converted most of its orders into the Challenger's stretched version, intending to carry up to 12,500 lb of freight at a time using them. However, FedEx ultimately opted to cancel its orders due to the US Airline Deregulation Act, and the specific aircraft that were already in production were sold to other customers instead.
By the spring of 1977, Canadair had received over 70 firm orders and had begun constructing three prototypes. Furthermore, a $70 million loan was borrowed from European sources to help finance the program, which lessened the financial burden on the Canadian government. A full-scale fuselage mockup was displayed at the 1977 Paris Air Show before a European and North American tour and 106 had been sold by 1977 end. During late 1977, in the face of criticism that the project would not be capable of producing an aircraft fulfilling the performance guarantees made, Canadair officials had commented that they expected the first flight to occur during the following year and that initial deliveries had been scheduled to commence during September 1979. Flight International noted that even prior to the prototype's first flight, the type had already made a noticeable impact upon the competition, including the launch of the Cessna Citation III and Grumman Gulfstream III.
Airframe structural testing began in February 1979 and operational test cycling started in December 1979, simulating 72,638 flight hours by February 1985 while predicted lifetime was 30,000 hours. By early March 1978, the first prototype was almost finished and the assembly of the two other had debuted; destined to control handling qualities and test flight performance, it was formally rolled out on 25 May 1978, while 116 orders had been confirmed 19 months after go-ahead. By this point, production jigs allowing for a production rate of up to seven Challengers per month had been established, ready for quantity production to proceed.
Flight test phase
On 8 November 1978, the prototype aircraft took off for its maiden flight from Montreal, Quebec. The flight test and certification program would be conducted at Mojave Kern County Airport instead of Canada due to better conditions. The second and third prototypes first flew during 1979. A test flight on 3 April 1980 in the Mojave Desert resulted in disaster, the aircraft crashing due to the failure of the release mechanism to detach the recovery chute after a deep stall, killing one of the test pilots (the other test pilot and the flight test engineer parachuted to safety).
Despite the crash, both Transport Canada and the Federal Aviation Administration (FAA) in the United States issued the aircraft's type certification later that same year, albeit with restrictions to pilots including a limited maximum takeoff weight. In response, a modification program aimed at reducing the aircraft's weight was implemented, which had the benefit of improving the aircraft's range.
During 1980, the first production model of the Challenger series, the CL-600, entered service with end-customers. Early marketing of the type by Canadair typically contrasted the more spacious cabin offered by the Challenger against its competitors, which typically had more narrow fuselages and therefore cramped conditions, as well as the type's fuel economy. By 1982, while only 10 aircraft had entered service, the company had begun publicizing a new model of the aircraft, the CL-601, which was to be powered by a pair of General Electric CF34 turbofan engines in place of the original models’ Lycoming units. On 10 April 1982, the CL-601 performed its maiden flight. According to Flight International, the decision to adopt the CF34 engine for the new model was responsible for generating a substantial boom in Challenger sales.
According to Flight International, the slow initial sales of the Challenger heavily contributed to the near-bankruptcy of Canadair, which was only avoided via the purchasing of the company by Bombardier in 1986. Bombardier elected not only to continue production of the type but to finance the development of new models and derivatives. This choice was aided by Canadair's design decision to enable the Challenger to be readily stretched from the onset. As of October 2018, the best-selling variant of the Challenger series has been the CL-604, which was launched in 1995. The 500th aircraft was rolled out in May 2000. The 1000th, a 650, was delivered to NetJets in December 2015.
By October 2018, the global Challenger fleet amounted to 997: of these, 611 were based in North America, 151 in Europe, 93 in Latin America, 78 in Asia-Pacific, 37 in Africa and 23 in Middle East. According to Flight International, the Challenger 600 has been a foothold in the market for Bombardier, allowing them to more easily develop further business jets, such as the Bombardier Global Express; another direct derivative of the Challenger series has been the Bombardier CRJ100 series, a larger regional airliner. The publication also commented that the Challenger family “appears to have a solid future”, observing a production rate of two aircraft per month throughout 2018.
The Challenger is a twin-engined business jet, described by Flight International as being ‘’miniaturized twinjet airliner in every respect’’. While the Challenger is generally similar in configuration to previous aircraft of its type, some of its features stand out; for example, the use of a widened fuselage that allows a “walk-about cabin”. The Challenger was also one of the first business jets to be designed with a supercritical wing. The wing was referred by Canadair as being one of the aircraft's most advanced features. It is also capable of performing short takeoffs while maintaining the speed and comfort levels normally associated with larger jetliners. Challengers can be identified visually from their peers by their distinctive double slotted hinged flap arrangement, where the fairings can be seen below the wings, a configuration that was much more common on commercial airliners.
The Challenger's wing has been referred to as being a modified NACA symmetrical aerofoil. Akin to other supercritical wings, it features a rounded leading edge, an inverted camber, a blunt trailing edge and scalloping of the underside. The twin-spar wing box structure spans the entire length of the wing and is compartmentalized to form five internal fuel tanks; these tanks can accommodate up to 14,661 lb of fuel, nearly half the aircraft's empty weight. The skins of the wings are produced via large milling machines, which in 1978 were claimed to be in excess of anything else in North America. Many elements, such as the flaps, ailerons and leading edge feature conventional construction; however, several parts, including the wing/fuselage fairing, flap shrouds and wingtips are molded out of Kevlar, as are other elements of the aircraft.
The original CL-600 Challenger was powered by a pair of Lycoming ALF 502L turbojet engines, which was developed specifically for the Challenger. Subsequent models would adopt other powerplants, including the General Electric CF34 engine. The engines are mounted on the rear fuselage close to the aircraft's tail, providing smooth airflow to the engines even when flown at high angles of attack, although this was in a lower position than the original Learstar concept had placed them to mitigate against unfavorable pitch control characteristics. The engines are fitted with thrust reversers to decrease landing distances. An auxiliary power unit is also present for starting the engines and providing air conditioning within the cabin while on the ground.
The fuselage comprises three sections – the nose, centre, and tail – which are manufactured separately in their own jigs and joined late on in the production process. It has been designed to be pressurized at a maximum differential of 9.3 lb per square inch. Various cutouts are present across the fuselage to accommodate various features, such as a large main door on the port side of the aircraft forward of the wing, multiple regulation-compliant emergency exits, a baggage hatch on the port side aft of the wing, and numerous windows. The fuselage's diameter was designed to accommodate an unobstructed cabin floor, a cabin height of 6 ft 1inch in the centre section, as well as space for the wing box, underfloor integral fuel tanks, air ducts, and various control cabling. It was also designed to easily accommodate Canadair's early plans to stretch the fuselage, for which equal-length plugs are installed fore and after of the centre section to vastly increase the Challenger's capacity.
Various avionics are present upon the Challenger. As standard, the CL-600 is furnished with a dual-channel Sperry SPZ-600 automatic flight control system, incorporating a flight director and air data computers; more typical to larger commercial aircraft, this system is certifiable for conducting category 3A automatic landings. The flight control system features significant redundancy, including three individual hydraulic systems; even with complete failure and the loss of one actuator, a viable level of assisted control over the key flight surfaces remains present. Weather radar and Marconi-built solid-state instrument displays are supplied as standard, as well as a Collins-built radio set; optional long range radio-based equipment, such as a HF radio set and VHF navigational aids can be installed.
In a standard executive aircraft configuration, the cabin is divided between the forward galley, and two seating sections, which are typically fitted with a four-chair club section followed by either a conference grouping area or divans, along with a lavatory at the aft end. The chairs are fully reclining and can swivel, while the divans can serve as sleeping accommodation. Early examples feature luxuries such as telephones, lighting controls, and stereo systems; foldaway tables attached to the cabin walls were also installed, along with a pair of wardrobes, one fore and one aft, for storing hand luggage and other small items.