TYPE: Business jet.

PROGRAMME: Announced at National Business Aircraft Association Convention in New Orleans, October 1994; derivation of Model 560 Citation V/Ultra Construction of prototype (N560XL) began February 1995; first flight 29 February 1996; public debut at NBAA convention at Orlando, Florida, November 1996, by which time prototype and preproduction aircraft (N561XL, c/n 560- 5001) had completed 350 hours of flight testing in 400 sorties; first production aircraft rolled out 21 November 1997; FAA certification achieved 22 April 1998; first delivery 2 July 1998 to Swift Transportation Inc of Phoenix, Arizona. First export, September 1998, to Automobilvertriebs AG, Austria; 100th production Excel rolled out 17 April 2000 and delivered in August 2000. Cessna delivered its 4,000th Citation, an Excel, on 7 October 2003.

CURRENT VERSION: Citation Excel: As described.
Citation XLS: Upgraded version, announced at NBAA Convention in Orlando 7 October 2003, where development aircraft (N562XL, c/n 560-5313) was displayed statically. Features 17.75 kN (3,991 lb st) Pratt & Whitney Canada PW545B turbofans providing 4.9 per cent more take-off thrust; and revised flight deck and cabin interior featuring Goodrich Aerospace crew seats, BE Aerospace passenger seats, LED lightning and restyled and upgraded furnishings. Empty weight 5,520 kg (12,170 lb); max zero-fuel weight 6,849 kg (15,100 lb); max T-O weight 9,163 kg (20,200 lb); max ramp weight 9,253 kg (20,400 lb); cruising speed at FL450 428 kt (793 km/h; 492 mph); max rate of climb at S/L 1,064 m (3,490 ft)/ min; time to climb to FL450 25 min; IFR range, with two crew and five passengers, 1,945 n miles (3,602 km/h; 2,238 miles); VFR range with max fuel 2,100 n miles (3,889 km; 2,417 miles). FAA certification scheduled for first quarter 2004, with deliveries beginning mid-2004, replacing Excel from c/n 560-5501. Unit cost $9,895 million (2003).

CUSTOMERS: Total market expected to exceed 1,000. Total of 15 delivered in 1998, 39 in 1999, 79 in 2000, 85 in 2001, 81 in 2002, and 42 in the first nine months of 2003. Recent customers include Avemex SA of Toluca, Mexico (three). Taxi Aereo Marilia (TAM) of Brazil (one) and the Swiss Federal Office for Civil Aviation, which took delivery of one on 28 August 2002. By August 2003 some 340 Excels were in service and had flown a total of 311,151 hours.

COSTS: US$9,451 million (2002).

DESIGN FEATURES: Combines systems and wing and tail surfaces of Citation Ultra (Encore) with shortened version of Citation X's fuselage, providing eight-seat cabin with stand-up headroom; dual ventral strakes.

FLYING CONTROLS: AS Citation Encore.

LANDING GEAR: Hydraulically retractable tticycle type with single wheel on each unit; trailing-link suspension on main legs. Mainwheel tyre size 23.5 x 8.0-10 (12 ply) tubeless, pressure 14.48 bar (210 lb/sq in); mechanically steerable nosewheel (±20°) with chined tyre, size 18x4.4DD (10 ply) tubeless, pressure 8.96 bar (130 lb/sq in). Hydraulic multiple disc carbon brakes with anti-skid and pneumatic emergency system.

POWER PLANT: Two 16.92 kN (3,800 lb st) Pratt & Whitney Canada PW545A turbofans. Nordam clamshell-type thrust reversers standard. Integral fuel tank in each wing, usable capacity 3,808 litres (1,006 US gallons; 838 Imp gallons) single-point pressure refuelling.

ACCOMMODATION: Choice of four standard seating configurations for up to 10 passengers in various layouts; seals recline, swivel and track forward and aft and laterally; forward refreshment centre and cupboard; aft lavatory and centreline cupboard. Airstair door on port side aft of flight deck. Baggage compartment in rear fuselage, capacity 317.5 kg (700 lb), with external access door incorporating integral step.

SYSTEMS: Honeywell RE-100(XL) APU optional from c/n 5021 (mid-1999) onwards, and retrofittable to earlier aircraft. Pressurisation system maximum differential 0.64 bar (9.3 lb/sq in), maintaining a sea level cabin altitude to 7,690 m (25,230 ft) or a 2,070 m (6,800 ft) cabin altitude to 13,715 m (45,000 ft). Hydraulic system, pressure 103.5 bar (1,500 lb/sq in), with two enginedriven pumps to operate landing gear, flaps, horizontal stabiliser, speed brakes and thrust reversers; separate hydraulic system for wheel brakes and anti-skid. Electrical system suppliedby two 28 V 300 A DC starter/generators, with 24 V 44 Ah Ni/Cd battery. Vapour cycle air conditioning system standard; APU optional. Oxygen system, capacity 2.15 m³ (76 cu ft) with pressure demand masks for crew and dropout constant-flow masks for passengers. Engine inlets and wing leading-edges supplied by engine bleed air for anti-icing; tailplane has de-icer boots; fin unprotected; electrically heated windscreen and cockpit side windows with PPG SurfaceSeal coating for rain dispersal, with electric blower assistance.

AVIONICS: Standard Honeywell Primus 1000 integrated digital avionics suite with lC-600 avionics computer as core system. Rockwell Collins system optional.
Comms: Dual Honeywell SRZ-850 transceivers, dual XS-852B Mode S transponders, Artex 110-4 ELT, L3 communications FA2100 CVR, airborne telephone system.
Radar: Honeywell Primus 880 colour weather radar.
Flight: Dual Honeywell NV-850, dual DM-850 DME, single DF-850 ADF, long-range navigation management system incorporating GPS, and Honeywell AA-300 radio altimeter.
Instrumentation: Three-tube EFIS with 178 x 203 mm ( 7 x 8 in) CRT screens composing dual primary flight displays (PFDs) showmg attitude/heading and all air data information, and single multifunction display (MFD) for map/plan, weather and checklist data.

Wing span 17.16 m (56 ft 33/4 in)
Wing aspect ratio 8.4
Length: overall 15.79 m (51 ft 91/2 in)
Height overall 5.30 m (17 ft 41/2 in)
Tailplane span 6.55 m (21 ft 6 in)
Wheelbase 6.67 m (21 ft 103/4 in)
Wheel track 4.54 m (14 ft 103/4 in)
Cabin:- Length:  
-between pressure bulkheads 7.39 m (24 ft 3 in)
-excl cockpit 5.69 m (18 ft 8 in)
-Max width 1.70 m (5 ft 7 in)
-Max height 1.73 m (5 ft 8 in)
Baggage capacity (aft) 2.26 m3 (80 cu ft)
Wings, gross 34.35 m2 (369.7 sq ft)
Vertical tail surfaces (total, incl tab) 4.73 m2 (50.9 sq ft)
Horizontal tail surfaces (total, incl tab) 7.88 m2 (84.8 sq ft)
Weight empty, typically equipped 5,579 kg (12,300 lb)
Max fuel weight (usable) 3,057 kg (6,740 lb)
Max TO weight 9,071 kg (20,000 lb)
Max ramp weight 9,163 kg (20,200 lb)
Max landing weight 8,482 kg (18,700 lb)
Max zero-fuel weight 6,804 kg (15,000 lb)
Max wing loading 264.1 kg/m2 (54.10 lb/sq ft)
Max power loading 269 kg/kN (2.64 lb/lb st)
Max operating speed (VMO):  
S/L to FL80 260 kt (481 km/h; 299 mph)
FL80 to FL265 305 kt (564 km/h; 351 mph) CAS
above FL265 M0.75
Max cruising speed at FL350 429 kt (795 km/h; 494 mph)
Stalling speed in landing configuration, at max landing weight 90 kt (167 km/h; 104 mph)
Max rate of climb at S/L 1,155 m (3,790 ft)/min
Rate of climb at S/L, OEI 259 m (850 ft)/min
Max certified altitude 13,715 m (45,000 ft)
Service ceiling, OEI 8,717 m (28,600 ft)
T-O balanced field length 1.095 m (3,590 ft)
Landing field length at max weight 969 m (3,180 ft)
NBAA IFR range 1,847 n miles (3.421 km; 2,157 miles)
VFR range with max fuel 2,080 n miles (3,852 km; 2,394 miles)
T-O 72.4 EPNdB
Approach 93.1 EPNdB
Sideline 85.3 EPNdB