CC-144) has a
swept wing, a
T-tail and two aft-mounted
turbofans 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. 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 later 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 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. ==Variants==