TYPE: Four-seat lightplane.

PROGRAMME: Announced 1996 as LC-40; aerodynamic prototype flown July 1996; first flight of certification prototype (N140LC), early 1997. Second prototype (N141LC) first flew 14 April 1997; public debut at Oshkosh August 1997; modified for FAA testing to confirm spin-resistance. Certification completed 18 September 1998; RLD certification completed March 2001.
First production aircraft (N424CH) delivered 24 February 2000.

CURRENT VERSIONS: Columbia 300: As described. Engineering designation LC40-550FG. Version discontinued in July 2003 following certification of Columbia 350.
Trainer: Lower-powered version with 116 kW (155 hp) engine, planned for flight training market, rivalling Cessna 172 and Cirrus SR20; since abandoned.
Columbia IV: Proposed version with pressurisation and retractable landing gear; since abandoned.
Columbia 350: Engineering designation LC42-550FG. Announced and publicly displayed at Sun 'n' Fun 2002; prototype (N70090) first flown early 2002 with deliveries due to start late 2002; however, certification delayed until May 2003 and deliveries started in late October 2003. All-electric systems replacing Columbia 300's vacuum pumps. Powered by 231 kW (310 hp) Teledyne Continental IO-550-N driving Hartzell three-blade propeller. Empty weight 1,043 kg (2,300 lb); performance data generally similar to Columbia 300.
Columbia 400: Engineering designation LC41-550FG. Turbocharged Columbia 300 with 224 kW (310 hp) Continental TSIO-550-C and (when available) FADEC. Announced 9 April 2000; prototype (N143LC converted from Columbia 300) first flew June 2000; first production aircraft (N166PD) registered September 2001; certification had been due in 2002 but was delayed; March 2004 was estimated; N166PD lost in accident 27 August 2003. Max T-O weight 1,633 kg (3,600 lb), provisional empty weight 1,066 kg (2,350 lb), normal cruising speed 220 kt (407 km/h; 253 mph), max rate of climb 366 m (1,200 ft)/min and service ceiling 7,620 m (25,000 ft). Other data as Columbia 300. Cockpit will eventually include electronic primary flight display projection system; prototype equipped with Highways in the Sky (HITS) instrumentation at one point.

CUSTOMERS: Deposits for 295 aircraft taken by end 1998; firm orders stood at 170 by late 2002. May be offered in fractional ownership schemes. Total 18 built (and nine registered in US) during 2000; 27 in 2001; and 12 in 2002; by September 2003, 79 had been registered and 72 delivered; 100th aircraft delivered December 2003. One example delivered to NASA at Langley 10 January 2001 for use as testbed for general aviation-based AGATE and SATS programmes; designated Columbia 300X.

COSTS: Columbia 350 US$369,900 fully IFR-equipped (2003); Columbia 400 US$436,900 (2003).

DESIGN FEATURES: Low-wing monoplane of typical Lancair appearance and design. Integral roll-over cage to protect cockpit area. Proprietary wing section, dihedral, and twist for spin resistant features. Airframe life 12,000 hours with provisions from FAA certification up to unlimited.

FLYING CONTROLS: Conventional and manual. Fowler flaps droop to 40° maximum. Aileron travel limits 22° up and 18° down; elevator travel up 13°, down 12°; rudder travel ±17°. Optional Precise Flight speedbrake.

STRUCTURE: All composites construction, including flight surfaces. One-piece dual-spar wing made of a combination of carbon fibre and glass fibre. Fuselage of composites construction with carbon fibre roll-over cage to protect cockpit area. Flight control surfaces constructed of carbon fibre materials.

LANDING GEAR: Fixed tubular steel tricycle type. Mainwheels 6.00-6, nosewheel 5.00-5. Cleveland brakes. Speed fairings on all wheels. Retractable version planned. Minimum ground turning radius 4.72 m (15 ft 6 in); nosewheel steerable ±60°.

POWER PLANT: Columbia 300 and 350: One 231 kW (310 hp) Teledyne Continental IO-550-N2B flat-six engine, driving three-blade constant-speed Hartzell PHC-J3YF-1RF/F7691D-1 propeller. FADEC. Total fuel capacity 402 litres (106 US gallons; 88.3 Imp gallons) in two integral wing tanks; usable fuel 371 litres (98.0 US gallons; 81.6 Imp gallons). Oil capacity 7.6 litres (2.0 US gallons; 1.7 Imp gallons).
Columbia 400: One 231 KW (310 hp) Teledyne Continental TSIO-550-C flat-six engine with two turbochargers and two intercoolers. Fuel and oil capacities as per Columbia 300 and 350.

ACCOMMODATION: Pilot and three passengers in two pairs of seats in enclosed cabin. Seating certified to 26 g. Double gull-wing doors hinge upwards. Emergency exit through large baggage door behind rear passenger seats with outside access by emergency hinge release pin mechanism on pilot's door.

SYSTEMS: Single 12 V battery; 14 V 60 A alternator; Seamech air conditioning optional. North Coast Industries Therma Wing de-icing on wing and tailplane leading edges optional from January 2004.

AVIONICS: Comms: Garmin G430 GPS/nav/com, G330 Mode-S transponder.
Flight: Garmin nav indicator, S-Tec 55X autopilot, Garmin 430 GPS, Goodrich Stormscope WX-500 lightning sensor. Avidyne Flight Max colour 267 mm (10½ in) flat panel moving map display.
Instrumentation: Options include Avidyne Entegra Primary Flight Display with flight director and other EFIS output display optional.

EQUIPMENT: Fire extinguisher standard.