TYPE: Business jet; utility twin-jet.

PROGRAMME: Project launched, but not then announced, June 2004; static testing completed between November 2004 and February 2005; public launch and debut, until then still unannounced, at Paris Air Show 13 June 2005, when prototype and cabin mockup displayed. ExecuJet Aviation Group of Switzerland announced as sales, service and support partner at time of launch. First flight (D-ISPN) 20 July 2005. Following early testing, re-registered D-CSPN on 10 August 2005 for flights above 5,700 kg (12,566 lb). Demonstrated grass strip landing in July 2006. Second prototype (D-CGSP) flew 29 September 2006, but was destroyed in an accident on 29 November 2006. Third prototype scheduled to fly in early 2007. EASA certification in CS 23 commuter category for single-pilot operation scheduled for third quarter 2007, followed by FAA FAR Pt 23 approval for day/night. IFR and known icing operations in fourth quarter 2007.

CUSTOMERS: Total of 65 orders held by October 2006.

COSTS: USD7.15 million (2006).

DESIGN FEATURES: Conventional low-wing configuration with unswept wing featuring small outward-canted winglets; swept fin and mildly swept tailplanes in cruciform configuration; dual downward-canted afterbody strakes. Pylon-mounted engines aft of cabin. Seven cabin windows on each side. Door on port side, immediately aft of cockpit. Wing sweepback 16° 50' at 25 per cent chord on inboard section, 9° 59' at 25 per cent chord on outboard section to wingtip. Dihedral 4°. Tailplane sweepback 20° 50' at 25 per cent chord. Fin sweepback 40° 10' at 25 per cent chord.

FLYING CONTROLS: Conventional and manual via pushrods and bellcranks. Elevators feature a bob weight and downspring system to modulate stick-free stability and control forces. Pitch trim is via two mechanically interconnected trim tabs with one electrical actuator each for redundancy; yaw and roll trim provided by electrically driven trim tabs on rudder and ailerons. Fowler flaps actuated by central electric motor via screw jacks and flexible drives. Hydraulically actuated spoiler on upper surface of wings.

STRUCTURE: Mostly carbon fibre composites with titanium wing attachment points. Minimum certified airframe service life 28.000 flight hours.

LANDING GEAR: Hydraulically retractable tricycle type with single wheel on each unit. Main units retract inwards. Reinforced legs and oversize wheels/tyres on all units to permit operation from unpaved surfaces.

POWER PLANT: Two Williams FJ44-3A turbofans, with FADEC, each rated at 12.54 kN (2.820 lb st). Fuel in integral wing tanks with independent venting, combined capacity 2,593 litres (685 US gallons; 570 Imp gallons). Honeywell RE100 APU flight operable to 9.140 m (30.000 ft). Gravity refuelling port in each wing; single-point pressure refuelling optional.

ACCOMMODATION: Cabin interior designed by Porsche Design Studio of Austria. Standard accommodation for eight passengers in double club configuration with centre aisle. ‘Plug and play’ modular interior has two movable bulkheads and seats and cabinetry mounted on tracks to facilitate quick change to alternative passenger seating arrangements, mixed passenger/cargo, all-cargo or air ambulance configurations, last-mentioned accommodating two stretchers and up to four seats for medical attendants. Standard self-contained lavatory, with basin, at forward end of cabin on starboard side is also removable. Standard cabin features four foldout tables (two for each double club pair); four 110 V power outlets in the cabin, plus one each in cockpit and lavatory; eight passenger-activated LED reading lights, and up/down indirect wash lights. Large plug-type door on starboard side forward of wing, with steps that lower automatically on door opening. Emergency exit each side, adjacent to wing leading-edge. Optional cargo net attaches to seat floor tracks and cabin headliner. Main baggage compartment is separate, located on port side aft of wing and accesses via a door below engine; additional baggage compartment in nose, with access via door in starboard side.

SYSTEMS: Cabin pressurisation system maintains 2,440 m (8,000 ft) cabin environment at maximum operating altitude of FL410. Hydraulic system, pressure 206 bar (3.006 lb/sq in), operates landing gear, spoilers, braking system and nosewheel steering. Electrical system supplied by one 24 V 40 Ah and one 24 V 18 Ah lead-acid batteries and two Honeywell 28 V 400 A starter/generators. 28 V DC external power socket optional, and can be used for charging aircraft main battery. Oxygen system of 0.91 m³ (32.0 cu ft) capacity includes quick-donning demand/flow masks with detachable goggles for crew and drop-down masks above every cabin seat and in lavatory for passengers. Bleed air anti-icing for wing leading-edges and engine inlets; electric heating for cockpit windscreen on captain's side, pitot/static probes. TAT and ice detection sensors and AoA probe.

AVIONICS: Honeywell APEX integrated avionics system as standard, comprising two 381 cm (15 in) PFDs and two 254 cm (10 in) across the diagonal, centrally mounted MFDs, dual ADAHRS, multimode VHF/COM/NAV/VOR/ILS digital radios, DME, radar altimeter, Mode S transponder, TCAS II with Change 7, EGPWS/TAWS Class A, tri-frequency ELT, and 76 mm (3 in) LCD standby instrument display.

DIMENSIONS, EXTERNAL:

• Wing span over winglets: 14.86 m (48 ft 9 in)
• Wing aspect ratio: 8.8
• Length: overall: 14.81 m (48 ft 7 in)
• fuselage: 14.18 m (46 ft 6¼ in)
• Height overall: 5.13 m (16 ft 10 in)
• Tailplane span: 6.48 m (21 ft 3 in)
• Wheel track: 3.08 m (10 ft 1¼ in)
• Wheelbase: 5.60 m (18 ft 4½ in)
• Passenger door: Height: 1.37 m (4 ft 6 in)
• Width: 0.84 m (2 ft 9 in)
• Rear baggage door: Height: 0.465 m (1 ft 6¼ in)
• Width: 0.725 m (2 ft 4½ in)

DIMENSIONS, INTERNAL:

• Cabin: Length: 5.10 m (16 ft 8¾ in)
• Max width: 1.52 m (5 ft 0 in)
• Max height: 1.64 m (5 ft 4½ in)
• Volume: 11.47 m³ (405 cu ft)
• Baggage compartment volume:
• rear: 0.99 m³ (35 cu ft)
• nose: 0.06 m³ (2.1 cu ft)

AREAS:

• Wings. gross: 24.99 m² (269.0 sq ft)
• Tailplane: 7.10 m² (76.42 sq ft)
• Fin: 5.00 m² (53.82 sq ft)

WEIGHTS AND LOADINGS:

• Weight empty: 3,510 kg (7,738 lb)
• Basic operating weight (single pilot): 3,601 kg (7,939 lb)
• Max baggage weight: 150 kg (331 lb)
• Payload: max (single pilot): 1,130 kg (2,491 lb)
• with max fuel: 674 kg (1,486 lb)
• Max fuel weight: 2,075 kg (4,575 lb)
• Max T-O weight: 6,300 kg (13,889 lb)
• Max ramp weight: 6,350 kg (13,999 lb)
• Max landing weight: 6,100 kg (13,448 lb)
• Max zero-fuel weight: 4,731 kg (10,430 lb)
• Max wing loading: 252.1 kg/m² (51.63 lb/sq ft)
• Max power loading: 251 kg/kN (2.46 lb/lb st)

PERFORMANCE (estimated):

• Max operating Mach No.: 0.70
• Max operating speed: S/L to FL80: 260 kt (481 km/h; 299 mph) CAS
• FL80 to FL298: 272 kt (504 km/h; 313 mph) CAS
• Max cruising speed: at FL330: 407 kt (754 km/h; 468 mph)
• at FL410: 402 kt (744 km/h; 463 mph)
• Approach speed, landing configuration: 100 kt (185 km/h; 115 mph) CAS
• Stalling speed, landing configuration: 77 kt (143 km/h; 87 mph)
• Max rate of climb at S/L: 1.329 m (4,360 ft)/min
• Rate of climb at S/L, OEI: 414 m (1,358 ft)/min
• Time to: FL330: 13 min
• FL390: 18 min
• FL410: 20 min
• Max operating altitude: 12,495 m (41,000 ft)
• T-O balanced field length at S/L: 914 m (3,000 ft)
• Landing from 15 m (50 ft): 814 m (2,670 ft)
• Range, with NBAA IFR reserves, 100 n mile (185 km; 115 mile) alternate:
• with max fuel: 1,950 n miles (3,611 km; 2,244 miles)
• pilot and six passengers: 1,800 n miles (3,333 km; 2,071 miles)
• g limits (design load factor): +3.1/-1.24

The article appears in the following publication:
Jane's All the World's Aircraft 2007-2008. Jane's Information Group Ltd. 2007. ISBN: 0-7106-2792-0