TYPE: Four-seat lightplane.

PROGRAMME: Formally launched 23 April 1997 at the Aero 97 show at Friedrichshafen, Germany when mockup gisplayed; initially retained name of Katana; proof-of-concept prototype DA 40-V1 (OE-VPC) first flew on 5 November 1997, powered by a Rotax 914 engine; a Teledyne Continental IO-240-engined DA 40-V2 (OE-VPE) followed shortly thereafter; neither event was publicised; a third prototype, DA 40-V3, with Textron Lycoming IO-360 engine, flew in late 1998; fourth, near production standard, prototype (OE-VPM) joined the test programme in mid-1999 followed by three more prototypes comprising DA 40-P5 (c/n 40005/OE-VPQ), -P6 (40006/OE-VPB), -P7 (40007/OE-VPW), these having enlarged ventral strake and cutaway rudder.
First production aircraft (40008/OE-KPN) registered June 2000; second exhibited at Farnborough in following month. Lycoming-powered variant was initial production version, for which JAR 23 certification was achieved 25 October 2000; FAA certification, 9 April 2001, followed by JAA IFR certification on 27 April 2001, and FAA IFR certification on 23 August 2001. First deliveries to US customers (seven aircraft) took place during EAA AirVenture 2001 at Oshkosh in July 2001.
Austrian production temporarily halted in early 2002 upon transfer of Lycoming-engined variant to Canada, Thielert-engined version now sole European-built DA 40.

CURRENT VERSIONS: DA 40-180: Original version with Lycoming IO-360 engine; now produced by Diamond Canada.
DA 40-TDI: Powered by Thielert Centurion 1.7 turbo-diesel; converted prototype (OE-XPP) first flew 22 November 2001; JAR 23 certification achieved 22 November 2001. Development aircraft OE-VTA (80th Austrian-built). Initial batch will comprise 75 aircraft. As described.

CUSTOMERS: More than 280 orders and options for DA 40 series by September 2000. At least 83 from Austrian production had been registered by early 2002 to customers in Austria, Germany, Netherlands, Sweden, Switzerland, UK, USA and elsewhere. Total of 60 DA 40 TDIs ordered by end of 2002, including 35 for Lufthansa's pilot training school. Embry-Riddle Aeronautical University of Florida has indicated that it may convert an order for 10 DA 40-180s to DA 40-TDIs.

COSTS: DA 40-TDI €191,400 basically (N-VFR) equipped; full standard avionics (IFR) €38,500 extra; all excluding tax (2002).

DESIGN FEATURES: Four-seat development of DA 20; to be certified to FAR/JAR 23 or equivalents in Europe, North America, Russian Federation, South Africa and Turkey. DA 20 wings attach to new, wider centre-section to increase span; downturned tips to horizontal tail; single strake/tail bumper. Enlarged cabin increases fuselage length by 0.67 m (2 ft 2¼ in).
Wing section is Diamond-modified Wortmann FX 63-137/20; washout 1°.

FLYING CONTROLS: Conventional and manual. Ailerons and elevators operated by pushrods with low-friction bearings, rudder by cables; manual pitch trim standard, electric pitch trim optional via control stick-mounted switch; ground-adjustable trim tab on rudder; electrically actuated slotted flaps.

STRUCTURE: Fuselage, with integral vertical fin, is mostly of GFRP construction with local CFRP reinforcement in high-stress areas, comprising two half-shells bonded together. Two-spar wings with GFRP/PVC foam/GFRP sandwich skins; horizontal tail and rudder surfaces similarly covered.

LANDING GEAR: Fixed tricycle type, with cantilever spring steel leg on each main unit and elastomeric suspension on nose leg. Mainwheel size 6.00-6; nosewheel 5.00-5. Steering is provided by differential braking of mainwheel and friction-damped castoring nosewheel. Speed fairings on all three wheels.

POWER PLANT: One 99 kW (133 hp) Thielert Centurion 1.7 turbo-diesel, driving an MTV-12-B/180-17 three-blade constant-speed propeller. Fuel in two wing tanks, standard capacity 110 litres (29.0 US gallons; 24.2 Imp gallons); 155 litres (40.9 US gallons; 34.1 Imp gallons) optional.

ACCOMMODATION: Four persons in two side-by-side pairs. Single-piece canopy lifts up and forwards for access to front seats; rear occupants board through an upward-opening door to port. Cabin has 26 g composites self-adapting seats with three-point automatic safety harnesses and roll-over bar. Baggage compartment behind rear seats includes tubular extension into rear fuselage for extra-long items. Rigid baggage compartment extension for long objects such as skis, optional.

SYSTEMS: 14 V electrical system includes 90 A alternator; 12 V 35 Ah battery.

AVIONICS: Comms: Baseline N-VFR suite includes Garmin GNS 430 com/nav/GPS, GTX 327 transponder and intercom. IFR suite adds second GNS 430 and GMA 340 audio selector panel with marker beacon receiver. GNS 530 com/nav/GPS (exchange for GNS 430) and Ack E or Artex 406 MHz ELT optional.
Flight: N-VFR: Garmin GI 106A CDI. IFR: Second GI 106A CDI, IFR: Second GI 106A, Bendix/King KAP 140 dual-axis autopilot with optional altitude preselect and Sigma Tek DG with heading bug, standard. Further options include Bendix/King KCS 55A slaved compass system, KR 87 ADF, KN 62A DME and Goodrich WX-500 Stormscope.
Instrumentation: N-VFR fit includes TAE engine indication system, compass, ASI, altimeter (second optional), VSI, artificial horizon, turn co-ordinator, DG, OAT gauge, chronometer and alternate static port.

EQUIPMENT: Landing light, taxying light, position lights, instrument lighting system, overhead cabin light, power socket for hand-held GPS and heated pitot/static system, all standard. Options include Operational Package comprising gust lock, towbar, tools and pitot cover; fire extinguisher, and first aid kit.