Cessna 525B Citation CJ3

TYPE: Light business jet.

COUNTRY OF ORIGIN: United States of America

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.

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).

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.

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)
 

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