TYPE: Light business jet.
PROGRAMME: Announced on eve of NBAA Convention Orlando, Florida, 9 September 2002; fuselage mockup shown following day. First flight (N3CJ, c/n 711) 17 April 2003, followed by first production aircraft (N753CJ, c/n 525B-001) 11 August 2003; public debut (N753CJ) at NBAA Convention, Orlando, Florida 7 October 2003; second production aircraft (N763CJ, c/n 525B-002) flew 6 November 2003; total of 340 hours in 200 sorties completed by all three aircraft by 20 November 2003; certification to FAR Pt 23, including single pilot operation, second quarter of 2004; deliveries from third quarter of 2004.
DESIGN FEATURES: Further development of CJ1/CJ2 femily. Fuselage sfretched by 1.00 m (3 ft 31/2 in) (seven windows each side), giving 0.61 m (2 ft 0 in) extra in cabin, and wing span extended by 1.03 m (3 ft 41/4 in). Uprated engines with 14 per cent more T-O thrust and 12 per cent more in cruise. Improved range and passenger comfort.
CUSTOMERS: Orders for more than 160 held by mid-September 2003.
COSTS: US$5,995,000 typically equipped (2003).
DESIGN FEATURES: Wing dihedral 5°0'; sweepback 0° at 31 per cent chord; taper ratio 0.30. Tailplane sweepback 20° 0' at 25 per cent chord; no dihedral; taper ratio 0.43. Fin sweepback 49°0' at 25 per cent chord; taper ratio 0.56.
FLYING CONTROLS: Flaps fitted (deflection 55° on ground).
POWER PLANT: Two 12.37 kN (2,780 lb st) Williams FJ44-3A turbofans with FADEC.
ACCOMMODATION: As CJ2, but chemical lavatory starboard, rear, opposite baggage area.
SYSTEMS: Hydraulic system with two engine-driven pumps, pressure 103.5 bar (1,500 Ib/sq in). Secondary hydraulic system for mainwheel brakes. Cabin pressurisation as CJ2. Emergency oxygen system reservoir 1,134 litres (40.0 cu ft). Electrical system 28 V DC includes two engine-driven generators and one 44 Ah Ni/Cd battery. Engine bleed air for anti-icing of wing leading-edges engine air intakes and windscreen, and inflation of de-icing boots on horizontal leading-deges. Backup windscreen alcohol de-icing.
AVIONICS: Rockwell Collins Pro Line 21 suite as core system.
Comms: Dual VHF-4000 transceivers. Dual TDR-94 Mode S transponders. Optional CVR. Artex C-406-2 ELT.
Radar: As CJ2.
Flight: Collins NAV-4000/NAV-4500 dual VOR, LOC, glideslope and MKR; single (optional second) ADF. DME-4000 DME. AHC-3000 AHRS, ADC-3000 ADC. FMS-3000 FMS, GPS-4000A GPS, ALT-4000 radio altimeter, Goodrich Skywatch TCAS, Goodrich TAWS 8000 Landmark terrain-avoidance. Maintenance diagnostic system.
Instrumentation: Three-tube EFIS with 203 x 254 mm (8x10 in) PFD and MFD active matrix LCDs. Goodrich GH-3000 standby instruments; Smiths standby EHSl.
|Wing span||16.13 m (52 ft 11 in)|
|Wing mean chord||1.90 m (6 ft 23/4 in)|
|Wing aspect ratio||9.5|
|Length: - overall||15.60 m (51 ft 2 in)|
|- fuselage||13.79 m (45 ft 23/4 in)|
|Height overall||4.60 m (15 ft 1 1/4 in)|
|Tailplane span||6.32 m (20 ft 9 in)|
|Tailplane mean chord||1.09 m (3 ft 7 in)|
|Wheel track||4.88 m (16 ft 0 in)|
|Wheelbase||6.10 m (20 ft 0 1/4 in)|
|- Height||1.29 m (4 ft 3 in)|
|- Max width||0.60 m (1 ft 11 1/2 in)|
|Emergency exit width||0.51 m (1ft 8 in)|
|Cabin: Length overall||6.35 m (20 ft 10 in)|
|- Max width||1.45 m (4 ft 91/4 in)|
|- Max height||1.45 m (4 ft 9 in)|
|Baggage volume||as CJ2|
|Wings, gross||27.32 m2 (294.1sq ft)|
|Vertical tail surfaces (total)||5.23 m2 (56.30 sq ft)|
|Horizontal tail surfaces (total)||6.57m2 (70.68 sq ft)|
|WEIGHTS AND LOADINGS:|
|Weight empty, typically equipped||3,747 kg (8,260 lb)|
|Max fuel||2,136 kg (4,710 lb)|
|Baggage capacity||as CJ2|
|Max ramp weight||6,382 kg (14,070 lb)|
|Max T-O weight||6,291 kg (13,870 lb)|
|Max landing weight||5,783 kg (12,750 lb)|
|Max zero-fuel weight||4,767 kg (10,510 lb)|
|Max wing loading||230.3 kg/m2 (47.16 Ib/sq ft)|
|Max power loading||254 kg/kN (2.49 lb/lb st)|
|Max operating speed (VMO): S/L to FL80||260 kt (482 km/h; 299 mph) CAS|
|FL80 to FL293||275 kt (509 km/h; 316 mph) CAS|
|above FL 293||M0.72|
|Max cruising speed, at mid-cruise weight: at FL350||414 kt (767 km/h; 476 mph)|
|atFL390||408 kt (756 km/h; 496 mph)|
|Stalling speed, landing configuration at MLW||86 kt (159 km/h; 99 mph) CAS|
|Time to: FL410||22 min|
|Max certified altitude||13,715 m (45,000 ft)|
|T-O balanced field length||1,052 m (3,450 ft)|
|Landing runway length||936 m (3,070 ft)|
|Range: - with max fuel, VFR reserves||1,900 n miles (3,518 km; 2,186 miles)|
|- with four passengers, NBAA IFR reserves||1,771 n miles (3,280 km; 2,038 miles)|