|A Bombardier CL-604|
|First flight||8 November 1978|
|Number built||1,066 (October 2018)|
|Developed into||Bombardier CRJ100/200|
Bombardier Global Express
The Bombardier Challenger 600 series is a family of business jets developed by Canadair after a Bill Lear concept, and then produced from 1986 by its new owner, Bombardier Aerospace. At the end of 1975, Canadair began funding the development of LearStar 600, and then bought the design for a wide-cabin business jet in April 1976. On 29 October, the programme was launched, backed by the Canadian federal government, and designed to comply with new FAR part 25 standards.
In March 1977, it was renamed the Challenger 600 after Bill Lear was phased out, and the original conventional tail was changed for a T-tail among other developments. The first prototype was rolled out on 25 May 1978, and performed its maiden flight on 8 November. The flight test program saw a deadly crash on 3 April 1980, but Transport Canada approved the CL-600 type certification on 10 August 1980.
In 1986, Canadair was close to bankruptcy and was bought by Bombardier. The jet was later stretched into the Bombardier CRJ regional airliner, introduced on 19 October 1992, and the longer range Global Express, introduced in July 1999. The 500th Challenger was rolled out in May 2000, and the 1000th was delivered to NetJets in December 2015. By October 2018, 1,066 aircraft had been built.
The Challenger is a low-wing jet powered by two turbofans mounted in aft fuselage pods, with a supercritical wing and a stand-up cabin with two seating sections. The original Lycoming ALF 502 turbofans were replaced by a pair of General Electric CF34s on the CL-601, which also gained winglets, and first flew on 10 April 1982. Subsequent variants have updated systems, avionics, and higher weights.
Around 1974, American aviation inventor Bill Lear conceptualised the LearStar 600, a low-wing, long-distance business jet, which was powered by a pair of Garrett TFE731-1 geared turbofan engines and equipped with a supercritical wing. Lear lacked the capabilities to launch such an aircraft, 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 an American 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 programme 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 for which they had already ended production, 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 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 then it was a 63 ft (19 m) long by 53.3 ft (16.2 m) wide aircraft capable of a maximum speed of Mach 0.85 and a range of 7,240 km (3,910 nmi); as an executive jet, it had sufficient capacity for 14 passengers; in a freighter configuration, it had a 3,400 kg (7,500 lb) payload capacity, loaded and unloaded through 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 were performed upon the supercritical wing alone.
Backed by the federal government, the programme 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 programme, 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 programme.
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 around which drew up its general arrangement. 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 favoured 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 programme, 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 in 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.
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. Airframe structural testing began in February 1979. and operational test cycling started in December 1979, simulating 72,638 flight hours by February 1985, while its predicted lifetime was 30,000 hours.
On 8 November 1978, the prototype aircraft took off for its maiden flight from Montreal, Quebec. The flight test and certification program were conducted at Mojave Kern County Airport instead of Canada due to better weather. 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 crashed 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.
The CL-600-1A11 type certification was approved by Transport Canada on 10 August 1980, and by the US Federal Aviation Administration on 7 November.
The program cost was C$1.5 billion (US$1.1 billion at the time).
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 publicising 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 by the purchase of the company by Bombardier in 1986. Bombardier elected not only to continue production of the type, but also 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.
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 a "miniaturised 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, a widened fuselage 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 to 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.
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 compartmentalised 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 using large milling machines, which in 1978 were claimed to be superior to anything else in North America. Many elements, such as the flaps, ailerons, and leading edge, feature conventional construction, but several parts, including the wing/fuselage fairing, flap shrouds, and wingtips, are moulded out of Kevlar, as are other elements of the aircraft.
The original CL-600 Challenger was powered by two Lycoming ALF 502L turbofan engines, which were developed specifically for the Challenger. Subsequent models adopted 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 unfavourable 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 pressurised at a maximum differential of 9.3 lb/sq in. 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 diameter was designed to accommodate an unobstructed cabin floor, a cabin height of 6 ft 1 in in the centre section, and 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 aft of the centre section to greatly increase the Challenger's capacity.
Various avionics are present in 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.
Built from 1996 through 2006, over 360 were delivered; early ones were selling for $4.0–$4.5 million and late models for less than $8 million in 2016. With 27,000 to 27,100 lb (12,200 to 12,300 kg) operating empty weights, it carries six or seven passengers and full fuel with the increased MTOW, is able to cruise 7.5–8.0 hr at Mach 0.80 and to fly five passengers 4,000 nm at Mach 0.74 up to FL 410. Thrust lapse as altitude increases, hefty power, and wing loadings affects hot-and-high performance; it takes off in 3,500 to 4,000 ft (1,100 to 1,200 m) for under 800 nmi (1,500 km; 920 mi) missions, in 5,684 ft (1,732 m) at MTOW and sea level, but in 9,123 ft (2,781 m) at ISA+20C and 5,000 ft (1,500 m) altitudes, TOW is reduced to 47,535 lb (21,562 kg) to meet climb requirements.
Pro Line 4 avionics include six 7.25 in (18.4 cm) cathode ray tubes and dual Flight management systems. It burns 3,800 lb (1,700 kg) in the first hour, 3,200 lb (1,500 kg) in the second hour, 2,800 lb (1,300 kg) in the third hour then 2,000 lb (910 kg)/hr. Scheduled maintenance is done every 200 h or six months, and major inspections are made every 96 months, and includes $110,000 landing-gear overhauls, the 8,729 lbf (38.83 kN) CF34-3B turbofans cost $375 per engine per hour.
The 605 and 650 improve the avionics and cabin, but their performance figures are similar to the 604.
The 500th unit was rolled out in May 2000. The 1000th, a 650, was delivered to NetJets in December 2015. 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. As of December 2017, close to 1,100 Challenger 600 Series have been delivered. 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.
By May 2019, the Challenger fleet suffered 17 hull loss accidents causing 39 fatalities.
|2000-10-10||US, Kansas, Wichita Airport||3||0||Test flight, impact with terrain during initial climb and post impact fire|
|2004-11-28||US, Colorado, Montrose Airport||3||3||Crashed during an attempted takeoff|
|2005-02-05||US, New Jersey, Teterboro Airport||0||14||Too far forward wing loading, failed takeoff attempt|
|2014-01-05||US, Colorado, Aspen Airport||1||2||Pilot error crash after tailwind landing in low-level windshear and gust conditions after a go-around.|
|2017-01-07||Oman, above Muscat||0||9||9,000 ft altitude loss after passing through the wake turbulence from an Airbus A380, written off due to damage after emergency landing|
|2018-03-11||Iran, Zagros Mountains||11||0||Crashed after a partial instrument failure, leading to a loss of control|
|2019-05-05||Mexico, Coahuila||13||0||Crashed on its return from Las Vegas, Nevada|
|2021-07-26||US, California, Truckee Tahoe||6||0||Crashed on approach. |
Data from Bombardier.