TYPE: Business jet
PROGRAMME: Announced at NBAA Convention in New Orleans in October 1990; engine flew on Citation VII testbed (N650) 21 August 1992; first flight (N750CX) 21 December 1993; two preproduction aircraft to aid integration of production systems; first of these (N751CX) flown 27 September 1994, second (N752CX) flown 11 January 1995; FAA FAR Pt 25, Amendment 74 certification 31 May 1996 after flight test programme totalling more than 3,000 hours; JAA certification achieved 26 May 1998. First customer delivery July 1996. Citation X design team awarded the National Aeronautic Association's Robert J. Collier Trophy in February 1997. Cessna delivered its 3,000th Citation, a Citation X, on 19 Noveraber 1999. In October 2000, Cessna announced improvements to the Citation X aimed at boosting range/payload performance and enabling the aircraft to operate from shorter runways. Improvements, to be incorporated on all aircraft delivered after 1 January 2002, beginning with c/n 0173 include uprated 30.01 kN (6,764 lb st) Rolls-Royce AE 3007C-1 turbofans; 181kg (400 lb) increase in maximum take-off weight to 16,374 kg (36,100 lb), enabling a typically equipped aircraft to carry seven passengers with maximum fuel; and take-off balanced field length at MTOW of 1,567 m (5,140 ft). Several optional items of avionics became standard, including Honeywell TCAS II and EGPWS, CVR, satcom, VHF/AFIS, provisions for an FDR, and second HF transceiver, plus Teledyne angle of attack indicator/indexer, tail floodlights, red strobe light, pulse lights, Litton ELT, and 2,154 litre (76 cu ft) oxygen bottle. First delivery of an upgraded citation X took place on 5 February 2002 to golfer Arnold Palmer (c/n0176/N1AP).
CUSTOMERS: First delivery (0003/N1AP) to Arnold Palmer July 1996; 100th Citation X delivered 23 December 1999 to Townsend Engineering of Des Moines, Iowa and 200th delivered 14 October 2002 to NetJets Inc; total 203 by 31 December 2002, comprising seven, 28, 30, 36 in 1996-99, 37 in 2000. 34 in 2001, 31 in 2002, and 12 in the first nine months of 2003; most to US operators, but others exported to Canada, Finland, Germany, Mexico, South Africa and UK. Executive Jet Aviation (EJA) ordered 31 for delivery beginning in 1997 and extending beyond 2000, for its NetJets fractional ownership operation. Other early recipients included General Motors (five), Honeywell (two) and Williams Companies (three). Recent customers include former World Motor Racing Champions Nigel Mansell, who took delivery of one in February 2002, and Nelson Piquet, who ordered one at the NBAA Convention at Orlando, Florida, in September 2002, and the Air Traffic Management Bureau of the Civil Aviation Authority of China, which ordered one on 1 October 2001. By August 2003 more than 213 Citation Xs had been delivered, and had accumulated 414,352 flight hours.
COSTS: US$19,394 million, typically equipped. Direct operating cost, based on 1,000 n mile (1,852 km; 1,151 mile) stage length, US$1,294.92 per hour (both 2003).
DESIGN FEATURES: Optimised for high maximum operating Mach number; US transcontinental and transatlantic range. Design generally as for Citation VII, but with greater angles of sweepback on all flying surfaces and of increased size and weight. Wing sweepback at quarter-chord 37°; dihedral 2°.
FLYING CONTROLS: Dual hydraulically powered controls with manual reversion. One-piece all-moving tailplane; twopiece rudder, lower portion hydraulically powered, upper portion electrically powered; speed brakes/spoilers with manual back-up. Five spoiler panels per wing, operating in combination as aileron augmentors, airbrakes and lift dumpers.
STRUCTURE: Alloy fuselage. Thick wing skins, milled from solid; all control surfaces, spoilers, speedbrakes, wing fairings and flaps are of composites construction.
LANDING GEAR: Trailing-link main units, each with twin wheels; powered anti-skid carbon brakes; hydraulically steerable nose unit with twin wheels. Main tyres 26x6.6R14 (14 ply) tubeless; nose tyres 16x4.4D (6 or 10 ply) tubeless.
POWER PLANT: TWO Rolls-Royce AE 3007C-1 turbofans, each rated at 30.01 kN (6,764 lb st) for take-off, pod-mounted on sides of rear fuselage; FADEC. Hydraulically operated target-type thrust reversers standard. Fuel contained in flnree separate tanks, one in each outer wing and one in centre-section/forward fairing, combined usable capacity 1,306 litres (1,930 US gallons; 1,607 Imp gallons). Two independent fuel supply systems; fuel is fed from centre tank to wing tanks; single point and over-wing refuelling.
ACCOMMODATION: Crew of two on separate flight deck, and up to 12 passengers; interior custom designed; cabin is pressurised, heated and air conditioned; heated and pressurised baggage compartment in rear fuselage with external door. Windscreen electrically heated and demisted.
SYSTEMS: Pressurisation system, maximum pressure differential 0.64 bar (9.3 Ib/sq in), maintains 2,440 m (8,000 ft) cabin altitude at 15,545 m (51,000 ft). Dual isolated hydraulic systems, pressure 207 bar (3,000 lb/ sq in), maintained by pressure-compensated pumps. Splitbus electrical system is powered by two engine-driven 400 A DC generators, plus an APU-driven 400 A DC generator usable to FL310, with two 24 V 44 Ah Ni/Cd batteries; wiring designed to minimise susceptibility of critical systems to HIRF interference. Wing and tail leading-edges and engine inlets heated by engine bleed air for ice protection; wing cuffs, pitot/static system, AoA system and windscreen electiically heated. Oxygen system, capacity 2.15 m3 (76 cu ft), with pressure demand masks for crew and dropout mask for each passenger.
AVIONICS: Honeywell Primus 2000 dual digital autopilot/ flight director/ElCAS as core system.
Comms: Dual Honeywell RCZ-833 communication units with 25 kHz and 8.33 kHz channel spacing; dual RM-855 radio management units; dual AV-850 audio control panels; single Honeywell KHF-950 HF with provision for second; dual Mode S transponders; Coltech CSD-714 Selcal; Honeywell airborne traffic information system (APIS); L-3 Communications FA2100 CVR; threefrequency ELT.
Radar: Honeywell Primus 880 colour weather radar.
Flight: Dual Honeywell FMSes; dual Honeywell navigation systems including VOR/LOC/GS/MKR and DME; dual Laseref IV IRS; single ADF; Honeywell AA-300 radio altimeter. Air data is provided by dual AZ-840 micro air data computers.
Instrumentation: Five-tube EFIS with 178 x 203 mm (7 x 8 in) screens for pilot's and co-pilot's primary flight displays (PFD) and multifunction displays (MFD), with central EICAS display.
| DIMENSIONS, EXTERNAL: | |
| Wing span | 19.38 m (63 ft 7 in) |
| Wing aspect ratio | 7.8 |
| Length overall | 22.05 m (72 ft 4 in) |
| Height overall | 5.87 m (19 ft 3 in) |
| Tailplane span | 7.95 m (26 ft 1 in) |
| Wheel track | 3.23 m (10 ft 7 in) |
| Wheelbase | 8.74 m (28 ft 8 in) |
| DIMENSIONS, INTERNAL: | |
| Cabin (front to mid-pressure bulkhead): | |
| - Length: between pressure bulkheads | 8.64 m (28 ft 4 in) |
| - excl flight deck | 7.16 m (23 ft 6 in) |
| Max width | 1.70 m (5 ft 7 in) |
| Max height | 1.73 m (5 ft 8 in) |
| Baggage compartment volume (aft, including ski compartment) | 2.03 m3 (72 cu ft) |
| AREAS: | |
| Wings, gross | 48.96 m2 (527.0 sq ft) |
| Vertical tail surfaces (total) | 10.31 m2 (111.0 sq ft) |
| Horizontal tail surfaces (total) | 11.15 m2 (120.0 sq ft) |
| WEIGHTS AND LOADINGS: | |
| Weight empty, typically equipped | 9,809 kg (21,625 lb) |
| Max fuel weight | 5,897 kg (13,000 lb) |
| Max T-O weight | 16,374 kg (36,100 lb) |
| Max ramp weight | 16,511 kg (36.400 lb) |
| Max landing weight | 14,424 kg (31,800 lb) |
| Max zero-fuel weight | 11,068 kg (24,400 lb) |
| Max wing loading | 334.5 kg/m2 (68.50 lb/sq ft) |
| Max power loading | 272 kg/kN (2.67 lb/lb st) |
| PERFORMANCE: | |
| Max operating Mach No. (MMO) | 0.92 |
| Max operating speed (VMO): | |
| S/L to FL800 | 270 kt (500 km/h; 310 mph) |
| FL800 to FL306 | 350 kt (648 km/h; 403 mph) |
| above FL306 | M0.92 |
| Max cruising speed, mid-cruise weight at FL370 | M0.91 |
| Max cruising speed at FL350 | 525 kt (972 km/h; 604 mph) |
| Max rate of climb at S/L | 1,113m (3,650 ft)/min |
| Max certified altitude | 15,545 m (51,000 ft) |
| T-O balanced field length (FAR Pt 25) | 1,585 m (5,200 ft) |
| FAR Pt 25 landing field length | 1,039 m (3,410 ft) |
| VFR range with two crew, M0.82 at FL490, 100 n mile (185 km; 115 mile alternate and 45 min reserves) |
3.390 n miles (6,278 km; 3,901 mfles) |
| NBAA IFR range | 3.070 n miles (5,686 km; 3.533 miles) |
| OPERATIONAL NOISE LEVELS (FAR Pt 36 Amendment 20): | |
| T-O | 73.2 EPNdB |
| Approach | 90.3 EPNdB |
| Sideline | 83.8 EPNdB |
