Cessna 525A Citation CJ2

TYPE: Light business jet.

COUNTRY OF ORIGIN: United States of America

PROGRAMME: Design began 1 May 1998; construction of prototype started August 1998; announced at NBAA Convention at Las Vegas, Nevada, 18 October 1998; first flight of prototype (N2CJ, a rebuilt CitationJet) 27 April 1999, followed by first preproduction aircraft (N525AZ) on 15 October and second (N765CT) in mid-December 1999; total of 1,008 flight test hours accumulated by three aircraft by 9 April 2000; first production aircraft c/n 525A-0003/(N132CJ) rolled out 14 January 2000; FAA FAR Pt 23 certification achieved 21 June 2000; public debut at EAA AirVenture Oshkosh in July 2000; first customer delivery, 30 November 2000, was N200KP to King Pharmaceuticals of Tennessee (second production aircraft). By August 2003 the 176 CJ2s then in service had logged a total of 54,849 flight hours.

CUSTOMERS: Total of 76 firm orders held at time of launch; by December 2000 order backlog accounted for planned production until first quarter of 2004. Recent customers include WD40 Something LLC (second preproduction aircraft, re-registered N400WD), Avemex SA of Toluca, Mexico (one): Taxi Aereo Marilia (TAM) of Brazil (five); and Atlas Air Service GmbH of Germany (three). First delivery to overseas customer was D-IBBB, which arrived at Bremen for Atlas on 21 June 2001. 100th production CJ2 (N170TM) delivered to TitleMax Aviation Inc of Savannah, Georgia, on 27 August 2002. Total of 86 delivered in 2002, and 42 in the first nine months of 2003.

COSTS: US$5.214 million, typically equipped (2003).

DESIGN FEATURES: Development of Citation Jet CJ1 with fuselage stretched by 1.30 m (4 ft 3 in) in cabin and tailcone areas (extra two cabin windows), wing span increased by 0.84 m (2 ft 9 in), swept tailplane of greater span, Williams FJ44-2C turbofans and Rockwell Collins Pro Line 21 avionics. Design goals included improvements in cabin room and comfort, speed and range over CitationJet Common type rating with CJ1. Description for the Citation CJ1 applies also to the Citation CJ2, except as follows:

FLYING CONTROLS: Spoilers, 60° flap deflection and engine nacelle thrust attenuators provide lift dump function during landing roll.

STRUCTURE: Primarily metal, with composites in non-critical areas such as fairings, wing and tailplane tips and exhaust nozzles. Three-spar wing.

POWER PLANT: Two pod-mounted Williams FJ44-2C turbofans, each flat rated at 10.68 kN (2,400 lb st) at 22°C 72°F), with thrust attenuators. Integral fuel tank in each wing, total capacity 2,245 litres (593 US gallons; 494 Imp gallons), of which 2,222 litres (587 US gallons; 489 Imp gallons) are usable; overwing gravity refuelling.

ACCOMMODATION: One or two crew on flight deck; six passengers in standard centre club layout with refreshment centre on starboard side; customised interiors to customer's choice. Flight accessible baggage area at rear of cabin; other baggage compartments in nose and tailcone. Cabin is pressurised, heated and air conditioned. Six cabin windows per side. Main door on port side forward of wing; emergency exit starboard aft.

SYSTEMS: Pressurisation system, maximum pressure differential 0.61 bar (8.9 Ib/sq in). Open-centre 103.4 bar (1,500 Ib/sq in) hydraulic system for operation of landing gear, flaps, speedbrakes and thrast attenuators. Vapour cycle air conditioning system. Electrical system supplied by battery and two engine-driven starter/generators. Oxygen system, capacity 623 litres (22.0 cu ft) standard, 1,417 litres (50.0 cu ft) optional.

AVIONICS: Rockwell Collins Pro Line 21 suite as core system.
Comms: Honeywell CNI-5000 panel-mounted radios.
Radar: Rockwell Collins RTA-800 solid-state colour weather radar.
Flight: Honeywell KLN 900 GPS FMS, VOR, DME, ADF, Rockwell Collins digital autopilot, digital air data computer and AHRS standard.
Instrumentation: Two-tube EFIS with 203 x 254 mm (8 X 10 in) PFD and MFD active matrix LCDs; co-pilot's PFD optional.

DIMENSIONS, EXTERNAL:
Wing span 15.19 m (49 ft 10 in)
Wing aspect ratio 9.4
Length overall 14.53 m (47 ft 8 in)
Height overall 4.24 m (13 ft 103/4 in)
Tailplane span 6.34 m (20 ft 91/2 in)
Wheel track 4.88 m (16 ft 0 in)
Wheelbase 5.59 m (18 ft 4 in)
Passenger door: Height 1.29 m (4 ft 23/4 in)
Width 0.60 m (1 ft 111/2 in)
DIMENSIONS, INTERNAL:
Cabin: Length: overall 5.74 m (18 ft 10 in)
- excl cockpit 4.19 m (13 ft 9 in)
Max width 1.47 m (4 ft 10 in)
Max height 1.45 m (4 ft 9 in)
Baggage volume: nose 0.58 m3 (20.4 cu ft)
cabin 0.11 m3 (4.0 cu ft)
tailcone 1.42 m3 (50.0 cu ft)
total 2.11 m3 (74.4 cu ft)
AREAS:
Wings, gross 24.53 m2 (264.0 sq ft)
Vertical tail surfaces 4.35 m2 (46.8 sq ft)
Horizontal tail surfaces 6.57 m2 (70.7 sq ft)
WEIGHTS AND LOADINGS:
Weight empty, typically equipped 3,465 kg (7,640 lb)
Max fuel 1,783 kg (3,930 lb)
Payload with max fuel 363 kg (800 lb)
Baggage capacity: - nose 181 kg (400 lb)
- cabin 45 kg (100 lb)
- tailcone 272 kg (600 lb)
- total 499 kg (1,100 lb)
Max T-O weight 5,613 kg (12,375 lb)
Max landing weight 5,216 kg (11,500 lb)
Max ramp weight 5,670 kg (12,500 lb)
Max zero-fuel weight 4,218 kg (9,300 lb)
Max wing loading 228.9 kg/m2 (46.88 Ib/sq ft)
Max power loading 263 kg/kN (2.58 lb/lb st)
PERFORMANCE (estimated):
Max operating Mach No. (MMO) 0.72
Max operating speed (VMG):
S/L to FL80 260 kt (481 km/h; 299 mph)
FL80 to FL293 275 kt (509 km/h; 316 mph)
above FL293 M0.72
Max cruising speed at FL330 410 kt (759 km/h; 472 mph)
Econ cruising speed at FL410 332 kt (615 km/h; 382 mph)
Stalling speed in landing configuration at MLW 86 kt (160 km/h; 99 mph)
Max rate of climb at S/L 1,180 m (3,870 ft)/min
Rate of climb at S/L, OEI 342 m (1.123 ft)/min
Time to: FL370 17 min
FL430 36 min
Max certified altitude 13,715 m (45,000 ft)
FAR Pt 25 T-O balanced field length 1,042 m (3,420 ft)
Landing field length at max landing weight 908 m (2,980 ft)
Range: NBAA IFR reserves 1,550 n miles (2,870 km; 1,783 miles)
VFR reserves 1,738 n miles (3,218 km; 2,000 miles)
OPERATIONAL NOISE LEVELS:
T-O 74.5 EPNdB
Approach 91.4 EPNdB
Sideline 88.8 EPNdB
 

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