Cessna CitationJet/M2
Light business jet From Wikipedia, the free encyclopedia
Light business jet From Wikipedia, the free encyclopedia
The Cessna CitationJet/CJ/M2 (also known as the Model 525) are a series of light business jets built by Cessna, and are part of the Citation family. Launched in October 1989, the first flight of the Model 525 was on April 29, 1991. Federal Aviation Administration (FAA) certification was awarded on October 16, 1992, and the first aircraft was delivered on March 30, 1993. The CJ series are powered by two Williams FJ44 engines; the design uses the Citation II's forward fuselage with a new carry-through section wing and a T-tail. The original CitationJet model has been updated into the CJ1/CJ1+/M2 variants; additionally, the CJ1 was stretched into the CJ2/CJ2+ which was built between 2000 and 2016. The design was then further developed into the CJ3/CJ3+, built from December 2004 to present, and finally into the CJ4 which has been built since 2010. By June 2017, 2,000 of all variants had been delivered.[3]
| CitationJet/CJ/M2 series | |
|---|---|
| A 525A CJ2, gear and flaps extended | |
| General information | |
| Type | Business jet |
| National origin | United States |
| Manufacturer | Cessna |
| Status | Active, in production |
| Number built | 2000 as of June 8, 2017[1] |
| History | |
| Manufactured | 1991-present |
| First flight | 29 April 1991[2] |
| Developed from | Cessna Citation II |
| Developed into | Cessna 526 CitationJet |
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Development of the CitationJet was prompted by the 1985 discontinuation of the Citation I, a reaction to the increasing price of its Pratt & Whitney JT15D-1 engines, which rendered it uncompetitive with its larger straight wing Citation stablemates. Cessna believed that a substantial market still existed for a light 4-5 passenger jet with low operating costs, docile flying qualities, and the ability to operate from short runways usable by twin piston-engined light aircraft, a formula that had made the Citation I successful. However, that aircraft had been stigmatized for its slower cruise speed than its competitors, which had progressively been addressed in the Citation S/II and Bravo and the Citation V, Ultra and Encore, but at the cost of operating economy. To offer increased speed with reduced purchase and operating costs, Cessna engineers realized that a new, lighter airframe design would be needed, using less expensive and lower-thrust engines. To better compete with newer jets, Cessna also wanted to eliminate the step in the center aisle of the earlier Citations, created by the spar passing through the cabin.[4]
Cessna launched the $2.4 million (equivalent to $5.9 million in 2023) model 525 CitationJet at the October 1989 NBAA convention in Atlanta, estimating a demand for 1,000 aircraft over ten years.[5] Its first flight was on April 29, 1991, a Federal Aviation Administration (FAA) type certificate was awarded on October 16, 1992, and first delivery happened on March 30, 1993.[2] The aircraft met its initial design goal: its normal cruise speed was 29 kn (33 mph; 54 km/h) faster than that of the Citation I, and the newer CitationJet outperformed the older Citation I in all other significant metrics except maximum payload and approach noise, despite having 600 lbf (2.7 kN) less total engine thrust.[6]
Twenty years after its first flight, 1,450 CJs had been produced.[7] As of June 2017, 2,000 of all variants had been delivered, with five million hours flown.[1]
The six-seat CitationJet is a monoplane with a cantilever wing, a retractable tricycle landing gear and a pressurized cabin.
The jet uses the Citation II's forward fuselage, a new carry-through section, a new laminar flow, supercritical wing developed with NASA and Boeing, and a T-tail. Powered by two 1,900 lbf (8.5 kN) Williams FJ44s, the 10,000 lb (4,500 kg) aircraft has a trailing link undercarriage for smooth landings, and can be flown by a single pilot. Range is 1,500 nmi (2,800 km) with four passengers and it can cruise at 437 kn (503 mph; 809 km/h).[5]
The CitationJet retains the 58 in (147 cm) inside diameter, circular fuselage cross-section of the Citation I and II, a semi-monocoque construction of conventional aluminum alloys assembled with rivets, fasteners and adhesive bonding. To reduce interference drag, a large fairing encases the low wing center section, and the engines are mounted high on the tail. Composite materials save weight in non-load-bearing components including fairings and the nose radome.[8] The cockpit features EFIS avionics; fuselage length is reduced 11 inches (27 cm) compared to the Citation I, and cabin length is reduced by 1 ft 6 in (46 cm), but with a lowered center aisle for increased cabin height.[2][5] The cockpit side windows are slightly smaller than those on earlier Citations to lessen interior temperature differences between the cockpit and the main cabin.[9]
Wing structure is a conventional ladder with chord-wise ribs over front and rear spars, and an aft sub spar to support the landing gear. The NASA high-speed 0213 airfoil sustains natural laminar flow over 30% of the upper surface for 10-15% better lift-to-drag ratio than the larger NACA 23000-series wing of the Citation I.[8] To maintain the wing's laminar-flow qualities and reduce weight, icing protection is provided by ducted bleed air rather than the deicing boots or fluid deicing systems used on earlier Citations.[10]
Its FJ44 engine has a 16:1 overall pressure ratio and a 2.58:1 bypass ratio.[8][11] Early CitationJet models have a novel design feature to reduce weight: rather than conventional thrust reversers, the aircraft are equipped with thrust attenuator paddles that pivot from the rear fuselage, similar to those used on the Cessna T-37 Tweet military trainer.[12]
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The ICAO aircraft type designator for the CJ2 models is C25A.
The ICAO aircraft type designator for the CJ3 models is C25B.
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The ICAO aircraft type designator for the CJ4 models is C25C.
| Model | M2 (CJ1)[42] | CJ2+[43] | CJ3+[44] | CJ4[45] |
|---|---|---|---|---|
| Crew | 1 or 2 | |||
| Max. passengers | 7 | 9 | 9 | 10 |
| Length | 42 ft 7 in (12.98 m) | 47 ft 8 in (14.53 m) | 51 ft 2 in (15.59 m) | 53 ft 4 in (16.26 m) |
| Height | 13 ft 11 in (4.24 m) | 14 ft (4.27 m) | 15 ft 2 in (4.62 m) | 15 ft 5 in (4.69 m) |
| Wingspan | 47 ft 3 in (14.40 m) | 49 ft 10 in (15.19 m) | 53 ft 4 in (16.26 m) | 50 ft 10 in (15.49 m) |
| Wing area | 240 ft2 (22.3 m2) | 264 ft2 (25 m2) | 294 ft2 (27.32 m2) | 330 ft2 (30.66 m2) |
| Wing sweep | 0 degrees | 12.5 degrees | ||
| Cabin section | 57 in (1.45 m) height, 58 in (1.47 m) width | |||
| Cabin length | 11 ft (3.35 m) | 13 ft 7 in (4.14 m) | 15 ft 8 in (4.78 m) | 17 ft 4 in (5.28 m) |
| MTOW | 10,700 lb (4,853 kg) | 12,500 lb (5,670 kg) | 13,870 lb (6,291 kg) | 17,110 lb (7,761 kg) |
| Fuel capacity | 3,296 lb (1,495 kg) | 3,930 lb (1,783 kg) | 4,710 lb (2,136 kg) | 5,828 lb (2,644 kg) |
| Fuel volume | 492 gal (1,862 L) | 587 gal (2,221 L) | 703 gal (2,661 L) | 870 gal (3,293 L) |
| Basic OEW | 6,990 lb (3,171 kg) | 8,030 lb (3,642 kg) | 8,540 lb (3,874 kg) | 10,280 lb (4,663 kg) |
| Max. payload | 1,410 lb (640 kg) | 1,670 lb (757 kg) | 1,970 lb (894 kg) | 2,220 lb (1,007 kg) |
| Turbofan × 2 | FJ44-1AP-21 | FJ44-3A-24 | FJ44-3A | FJ44-4A |
| Thrust (each) | 1,965 lb (8.74 kN) | 2,490 lb (11.08 kN) | 2,820 lb (12.54 kN) | 3,621 lb (16.11 kN) |
| Max. cruise | 404 kn (748 km/h) | 418 kn (774 km/h) | 416 kn (770 km/h) | 451 kn (835 km/h) |
| Max. range | 1,550 nmi (2,871 km) | 1,781 nmi (3,298 km) | 2,040 nmi (3,778 km) | 2,165 nmi (4,010 km) |
| Takeoff | 3,210 ft (978 m) | 3,360 ft (1,024 m) | 3,180 ft (969 m) | 3,410 ft (1,039 m) |
| Landing | 2,590 ft (789 m) | 2,980 ft (908 m) | 2,770 ft (844 m) | 2,940 ft (896 m) |
| Ceiling | 41,000 ft (12,497 m) | 45,000 ft (13,716 m) | ||
| Max. climb rate | 3,698 fpm (18.8 m/s) | 4,120 fpm (20.9 m/s) | 4,478 fpm (22.75 m/s) | 3,854 fpm (19.6 m/s) |
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