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 3½ 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 4¼ in). Uprated engines with 14 per cent more T-O thrust and 12 per cent more in cruise. Improved range and passenger comfort. 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.
Description for Citation CJ1/CJ2 applies to CJ3, except as follows:
CUSTOMERS: Orders for more than 160 held by mid-September 2003.
COSTS: US$5,995,000 typically equipped (2003).
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.
| DIMENSIONS, EXTERNAL: | |
| 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) |
| Door: | |
| - 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) |
| DIMENSIONS, INTERNAL: | |
| 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 |
| AREAS: | |
| 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) |
| PERFORMANCE (estimated): | |
| 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 |
| FL430 | 26 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) |
