History

The Learjet 35 and 36 are stretched, turbofan-powered developments of the initial Learjet models, the 23, 24 and 25. The availability of the Garrett AiResearch TFE731 turbofan in the late 1960s led to a development of the Learjet 25 that was initially known as the 25B-GF (Garrett Fan). A testbed Learjet 25 with a TFE731 on its left side flew in May 1971, while the definitive Learjet 35 prototype first flew on August 22 1973. Aside from turbofans, the 35 and longer range 36 differ from the earlier Learjet 25 in having a 0.33m (1ft 1in) fuselage stretch and five windows (instead of four) on the right side of the fuselage.

Performance

35A/36A - Max speed 872km/h (470kt), max cruising speed 852km/h (460kt), economical cruising speed 774km/h (418kt). Service ceiling 41,000ft. Range with four passengers, max fuel and reserves 4070km (2195nm) for 35A, 4673km (2522nm) for 36A. 31A - Max cruising speed 891km/h (481kt), typical cruising speed at 45,000ft 832km/h (450kt). Max certificated altitude 51,000ft. Range with two crew, four passengers and IFR reserves 2344km (1266nm), or 2752km (1486nm) for 31A/ER.

Weights

35A/36A - Empty equipped 4590kg (10,120lb), max takeoff 8300kg (18,300lb). 31A - Empty 4651kg (10,253lb), operating empty 5035kg (11,100lb), max takeoff 7030kg (15,500lb), or optionally 7711kg (17,000lb). 31A/ER - Max takeoff 7711kg (17,000lb).

Dimensions

35/36 - Wing span (over tip tanks) 12.04m (39ft 6in), length 14.83m (48ft 8in), height 3.73m (12ft 3in). Wing area 23.5m2 (253.3sq ft). 31A - Same except for wing span 13.35m (43ft 10in). Wing area 24.6m2 (264.4sq ft).

History

The new Bombardier Learjet 45 is Learjet's latest entry into the medium size corporate jet market. Bombardier owned Learjet announced it was developing the Model 45 at the US National Business Aircraft Association's annual convention in Dallas in September 1992. First flight was on October 7 1995 (the 32nd anniversary of the original Lear 23), and, after some delays, US FAA certification was granted on September 22 1997. The first customer aircraft was delivered in January 1998 The 45 is of classic Learjet design and layout. However, a number of key design changes were made early into the 45's design life including a larger fin and rudder, extended engine pylons, smaller delta fins, full span elevators, and single piece flaps. Larger than the Learjet31 and smaller than the 60, Learjet states that the 45's 1.50m (4.9ft) high and 1.55m (5.1ft) wide cabin will provide more head and shoulder room than any other aircraft in its class. The cabin is designed to accommodate double club seating, a galley and a full-width aft restroom, while eight windows line each side of the cabin.

Performance

High cruising speed 857km/h (463kt), normal cruising speed 817km/h (441kt), long range cruising speed 804km/h (434kt). Max certificated altitude 51,000ft. Max range with four passengers and IFR reserves 3704km (2000nm).

Weights

Empty 5466kg (12,050lb), basic operating empty 5783kg (12,750lb), max takeoff 9162kg (20,200lb).

Dimensions

Wing span 14.57m (47ft 10in), length 17.68m (58ft 0in), height 4.30m (14ft 1in). Wing area 29.0m2 (311.6sq ft)

History

The Learjet 55 and its followon successor, the Learjet 60, are the largest members of the Learjet family, and date back to development work undertaken in the late 1970s. In designing the 55, Learjet (or Gates Learjet as the company was then known as) took the wing of the earlier Longhorn 28/29 series and married it to an all new larger 10 seat fuselage. The original Model 55 Longhorn prototype first flew on November 15 1979. The first production aircraft meanwhile flew on August 11 1980, with the first delivered in late April 1981 (after FAA certification was granted in March that year). Development of the 55 led to a number of sub variants, including the 55B which introduced a digital flightdeck, modified wings, improved interior, and most importantly, the previous optional higher takeoff weights becoming standard. The 55C introduced `Delta Fins' which gave a number of performance and handling advantages, the 55C/ER is an extended range version with additional fuel in the tail cone (the additional tank can be retrofitted to earlier aircraft), while the 55C/LR introduced more fuel capacity. The improved Learjet 60 first flew in its basic definitive form in June 1991 (the modified Learjet 55 prototype earlier served as a proof of concept aircraft for the 60 with Garrett engines). It differs from the 55 in having a 1.09m (43in) fuselage stretch and new Pratt & Whitney Canada PW305 turbofans. Certification of the 60 was awarded in January 1993, with first deliveries following shortly afterwards. International Directory of Civil Aircraft

Performance

Max speed 884km/h (477kt), max cruising speed 843km/h (455kt), economical cruising speed 778km/h (420kt). Service ceiling 51,000ft. Range with two crew, four passengers and reserves 4442km (2397nm) for 55C/LR. 60 - High cruising speed 839km/h (453kt), normal cruising speed 828km/h (447kt), long range cruising speed 778km/h (420kt). Max certificated altitude 51,000ft. Range with two crew, four passengers and IFR reserves 4461km (2409nm).

Weights

Empty 5832kg (12,858lb), operating empty 6013kg (13,258lb), max takeoff 9525-9752kg (21,000-21,500lb). 60 - Empty 6282kg (13,850lb), basic operating empty 6641kg (14,640lb), max takeoff 10,659kg (23,500lb).

Dimensions

Wing span 13.34m (43ft 9in), length 16.79m (55ft 1in), height 4.47m (14ft 8in). Wing area 24.6m2 (264.5sq ft).

History

The Gulfstream G150 mid-size corporate jet is built by Israel Aircraft Industries and was originally marketed and supported by subsidiary Galaxy Aerospace Inc, which was acquired by Gulfstream in May 2001. Design work on the IAI-1126 Galaxy (initially called the Astra Galaxy and later renamed G150 on Gulfstream's take-over) began in the early 1990s and formal program launch was announced in September 1993. In 1995 a co-production arrangement was terminated that would have seen Yakovlev in Russia responsible for the design and manufacture of the Galaxy's fuselage, while IAI would be the main contractor responsible for final assembly, integration and marketing. Subsequently, SOGERMA of France was selected to manufacture production Galaxy fuselages and tails.

Performance

Typical cruising speed 871km/h (470kt). Max operating altitude 45,000ft. Max range with four passengers and reserves 6708km (3620nm), max range with eight passengers and reserves 6226km (3360nm). Range with 18 passengers in corporate shuttle configuration with reserves 5022km (2710nm)

Weights

Basic operating 8709kg (19,200lb), max takeoff 15,808kg (34,850lb).

Dimensions

Wing span 17.71m (58ft 1in), length 18.97m (62ft 3in), height 6.53m (21ft 5in). Wing area 34.3m2 (369.0sq ft)

History

The Challenger 601 addressed the original CL-600 Challenger's weight problems and replaced the troubled ALF-502 turbofans, creating a highly successful full size corporate jet. Troubles with the Avco Lycoming powered Challenger 600 led Canadair (now a division of Bombardier) to develop a vastly improved variant in the form of the General Electric CF-34 powered Challenger 601. Another important change was the addition of winglets, which are also offered as a retrofit to earlier aircraft. The 601 first flew on April 10 1982 and for a time was offered alongside the 600. The 600 was dropped from the model line in 1983. Subsequent development of the Challenger led to the 601-3A. First flying in 1987, this variant introduced an EFIS glass flightdeck and upgraded engines. Available from 1989, the 601-3R was an extended range model with higher weights (the range increase modifications can also be retrofitted to earlier 601-3As). Further improvements to the basic design led to the Challenger 604. Improvements include an advanced Collins ProLine IV EFIS avionics system with colour displays, higher weights, CF-34-3B turbofans and increased fuel tankage. Many other minor changes were incorporated based on Bombardier's experience with the Canadair Regional Jet. First flight with CF-34-3A engines was in September 1994, first flight with the CF-34-3B engines was on March 17 1995, with Transport Canada certification granted that September. First delivery was in January 1996.

Performance

Max cruising speed 851km/h (460kt), typical cruising speed 819km/h (442kt), long range cruising speed 786km/h (424kt). Max operating altitude 45,000ft. Range with max fuel and reserves 6208km (3352nm). 601-3A - Normal cruising speed 851km/h (460kt). Service ceiling 41,000ft. Range with max fuel, five pax and reserves 6236km (3365nm). 604 - Max cruising speed 882km/h (476kt), normal cruising speed 851km/h (459kt), long range cruising speed 787km/h (425kt). Certificated ceiling 41,000ft. Range with max fuel, five pax and reserves 7550km (4077nm) at long range cruising speed, 6980km (3769nm) at normal cruising speed.

Weights

Empty 9049kg (19,950lb), operating empty 11,605kg (25,585lb), max takeoff 19,550kg (43,100lb). 601-3R - Empty 9292kg (20,485lb), operating empty 11,566kg (25,500lb), max takeoff 19,550kg (43,100lb) or optionally 20,457kg (45,100lb). 604 - Empty 9806kg (21,620lb), operating empty 12,079kg (26,630lb), max takeoff 21,591kg (47,600lb), or optionally 21,863kg (48,200lb).

Dimensions

Wing span 19.61m (64ft 4in), length 20.85m (68ft 5in), height 6.30m (20ft 8in). Wing area 48.3m2 (520.0sq ft).

History

The highly successful CitationJet was developed as a replacement for the Citation and Citation I. Improved and stretched developments, the CJ1 and CJ2 respectively, are under development. Cessna launched the new Model 525 CitationJet at the annual US National Business Aircraft Association convention in 1989. First flight occurred on April 29 1991, FAA certification was awarded on October 16 1992 and the first delivery was on March 30 1993. The CitationJet is effectively an all new aircraft. The same basic Citation forward fuselage is mounted to a new T-tail configured tailplane and a new supercritical laminar flow wing, and it features Williams Rolls FJ44 turbofans (with paddle thrust reversers) and trailing link main undercarriage. The CitationJet's fuselage is 27cm (11in) shorter than the Citation/Citation I's, while cabin height is increased courtesy of a lowered centre aisle. It features EFIS avionics and is certificated for single pilot operation. At the 1998 NBAA convention Cessna revealed it was developing the improved CJ1 and stretched CJ2. The CJ1 will replace the CitationJet and will introduce a Collins Pro Line 21 EFIS avionics suite and a moderate increase in maximum takeoff weight. The CJ1 will be delivered from the first quarter of 2000. The CJ2 meanwhile is a stretched, faster and more powerful development. Due to fly in the second quarter of 1999 and be certificated 12 months later, the CJ2 will feature a 89cm (35in) cabin and 43cm (17in) tailcone stretch allowing standard seating for six in the main cabin. Like the CJ1 it will feature Collins Pro Line 21 EFIS avionics, plus uprated FJ44-2C engines, increased span wings, larger area tail, six cabin windows per side and greater range. It will be certificated for single pilot operation.

Performance

Max cruising speed at 3990kg (8800lb) AUW 704km/h (380kt). Initial rate of climb 3311ft/min. Certificated ceiling 41,000ft. Range with max fuel and reserves 2750km (1485nm). CJ1 - Range with pilot, three passengers and IFR reserves 2315km (1250nm). CJ2 - Max cruising speed at 33,000ft 741km/h (400kt). Service ceiling 45,000ft. Range with pilot, three passengers and IFR reserves 2687km (1450nm).

Weights

Empty 2794kg (6160lb), max takeoff 4717kg (10,400lb). CJ1 - Max takeoff 4812kg (10,600lb). CJ2 - Max takeoff 5585kg (12,300lb).

Dimensions

Wing span 14.26m (46ft 10in), length 12.98m (42ft 7in), height 4.18m (13ft 8in). Wing area 22.3m2 (240.0sq ft). CJ2 - Wing span 15.18m (49ft 10in), length 14.30m (46ft 11in).

History

One of the latest members of Cessna's extensive line of Citation business jets, the Citation Excel combines the cabin width and standup headroom comfort of the Citation X in a new small/medium size package. The new Excel resulted from customer consultation over what they wanted in a light corporate jet plus advances in engine and airframe technology. The basis of the Excel is a shortened Citation X fuselage (the same fuselage cross section as was used in the Citation III, VI and VII), combined with a modified unswept supercritical wing based on the Citation V Ultra's, the V's cruciform tail configuration and new Pratt & Whitney Canada PW-545A series turbofans. Other design features include trailing link main undercarriage units and a standard Honeywell Primus 1000 three 20 x 18cm (8 x 7in) screen EFIS avionics package (two Primary Flight Displays, one for each pilot, and a multifunction display). Cessna claims the Citation Excel's cabin is the largest of any light business jet. It features standup headroom and a dropped aisle that runs the length of the main cabin. Seated head and elbow room is greater than that in the Citation II and V, while the cabin length is similar to the Citation I, II, VI and VII. The Excel was one of the first applications for the new generation PW-500 series engines. The Excel's 16.9kN (3804lb) PW-545As (derated from 19.9kN/4450lb, with a TBO of 5000 hours) are fitted with Nordam thrust reversers as standard and the engines allow it to cruise at 801km/h (432kt). Cessna announced it was developing the Excel at the NBAA convention in October 1994. Prototype construction began in February 1995 and it flew for the first time on February 29 1996. The first production Excel rolled out in November 1997 and the type was certificated in April 1998, with first deliveries beginning mid that year at which stage over 200 were on order. Cesna delivered the 100th Excel in August 2000, at which time the company was building one every three days. Cessna says this is the fastest ramp-up of production of any Citation jet yet.

History

Max cruising speed at 35,000ft 795km/h (429kt). Initial rate of climb 3790ft/min. Max certificated altitude 45,000ft. Range at economical cruising speed with two crew, four passengers and reserves 3852km (2080nm).

History

Standard empty 5402kg (11,910lb), max takeoff 9071kg (20,000lb).

History

Wing span 16.98m (55ft 10in), length 15.79m (51ft 10in), height 5.24m (17ft 3in). Wing area 34.5m2 (369.7sq ft).