TYPE: Business prop.

PROGRAMME: Announced February 1993; designed in collaboration with Delft University; first flight (D-EBEW) 4 April 1996; initial LBA certification to FAR Pt 23 received 23 April 1997. Second prototype (D-EGBU) flew April 1998, featuring downturned wingtips and ventral stake, both of which had been added to first aircraft before its retirement in 1997. This aircraft lost on delivery to first customer, 21 April 1998. FAA certification 15 April 1998.

CURRENT VERSIONS: Extra EA-400: As described.
Extra EA-500: Turboprop. Described separately.

CUSTOMERS: Two prototypes and 61 production aircraft completed by October 2003, when a further six were in production. Combined rate of one per month for EA-400/500 anticipated by December 2004, rising to 18 to 24 per year.

COSTS: Typically equipped, US$895,000 (2003).

DESIGN FEATURES: Cantilever high-wing NLF aerofoil section, T tail layout; spacious cabin; optimised for low internal and external noise.

FLYING CONTROLS: Conventional and manual. Frise ailerons, maximum deflections +27/-19°; two-section Fowler flaps approximately two-thirds of span, deflection 0, 15 and 30° horn-balanced elevators, maximum deflection +33/-18°; trim tab in starboard elevator, maximum deflection +30/-20°; rudder maximum deflection ±25°; ground-adjustable tab on rudder. Interconnected aileron and rudder controls, with override.

STRUCTURE: Composites throughout. Airframe consists of skin with integral longerons and frames. Wing built on double front spar and rear spar, interconnected by ribs; tailplane has front and rear spar. Skins generally of carbon fibre fairings and honeycomb; longerons, frames, spars and ribs carbon fibre with foam core; wing leading-edge of glass fibre with honeycomb and glass fibre ribs. Service life 25 years/20,000 hours/30,000 cycles/22,500 pressurisation cycles.

LANDING GEAR: Hydraulically retractable tricycle type; designed and manufactured by Gomolzig; single wheels throughout; main units retract forward into fuselage sides; nosewheel retracts rearwards. Mainwheels size 15x6.0-6, nosewheel size 5.00-5. Minimum turning radius 20.4 m (67 ft). Independent hydraulic brakes on mainwheels. Nosewheel steerable ±30°.

POWER PLANT: One 261 kW (350 hp Teledyne Continental Voyager TSIOL-550-C six-cylinder liquid-cooled engine, driving an MT-Propeller MTV-14-D/195-30a four-blade, constant-speed (hydraulic) propeller; three-blade propeller optional. Fuel in two integral wing tanks, combined capacity 468 litres (123.6 US gallons; 102.9 Imp gallons), of which 404 litres (107 US gallons; 88.9 Imp gallons) are usable. Oil capacity 12.3 litres (3.2 US gallons; 2.7 Imp gallons).

ACCOMMODATION: Pilot and five passengers in pressurised cabin; rear seats in club configuration; single door on port side is horizontally split, with airstair in bottom half; top half hinges upwards. Emergency exit starboard side, opposite door.

SYSTEMS: Electrical system 24 V, with direct-driven 100 A alternator, belt-driven 85 A alternator and 24 V battery in tailcone. External power receptacle in tailcone. Pressurisation system, maximum differential 0.38 bar (5.5 lb/sq in). Wing and empennage leading-edges de-iced by Teflon inflatable boots.

AVIONICS: Standard Garmin avionics suite, comprising GNS 530 and GNS 430 GPS/nav/coms, each with colour LCD MFD; GI-106A nav indicator with glideslope; GMA 340 audio panel with marker beacon receiver and six-place intercom; GTX 327 transponder; Honeywell EO461 EADI EFIS; Honeywell EFIS attitude indicator; Litef LCR-92/CCU EA-85511 laser gyro platform; S-Tec 55X autopilot, and Bose pilot's and co-pilot's headsets. Second GTX 327, GTX 330 Mode S transponder, Bendix/King KN 62 DME, Skywatch TCAS, Honeywell RDR-200 colour weather radar in wingtip pod, and Garmin GDL 49 weather uplink system, all optional.