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The Diamond DA-40 Diamond Star

Country of origin  
Austria

Photos  

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Photo © Michael Fritz

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Photo © Steven Pellegrino
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Powerplants  
DA-40-180 - One 134kW (180hp) Textron Lycoming IO-360-M1A flat four piston engine driving a three blade MTV-12-B/180-7 constant speed propeller.
DA-40D - One 100kW (135hp) Thielert Centurion 1.7 jet fuel burning turbo diesel flat four.

Performance  
DA-40-180 - Max level speed 287km/h (155kt), cruising speed at 75% power 272km/h (147kt), economical cruising speed 222km/h (120kt). Initial rate of climb 1070ft/min. Max certified altitude 16,400ft. Range with standard fuel and reserves 1100km (594nm), with optional fuel and reserves 1480km (799nm).
DA-40D - Max speed 285km/h (154kt), cruising speed at 80% power at 12,000ft 278km/h (150kt), cruising speed at 60% at 12,000ft 250km/h (135kt). Initial rate of climb 730ft/min. Range with standard fuel and reserves 1400km (750nm), with optional fuel and reserves 2030km (1100nm).

Weights  
DA-40-180 - Empty 700kg (1543lb), max takeoff 1150kg (2535lb).
DA-40D - Empty 750kg (1653lb), max takeoff same.

Dimensions  
Wing span 11.94m (39ft 5in), length 8.01m (26ft 3in), height 2.00m (6ft 7in). Wing area 13.5m2 (145.3sq ft).

Capacity  
Standard seating for four.

Production  
Over 425 built by end 2004, including 7 prototypes, over 300 DA-40-180 and over 125 DA-40D.

Type  
Four seat light aircraft

History  

The DA-40 Diamond Star is a composite construction four place light single now offered in avgas and jet fuel burning forms.

Diamond Aircraft was formed in 1981 as Hoffmann Flugzeugbau, and following bankruptcy reformed as Hoffmann Aircraft in 1984. The company was renamed HOAC Austria Flugzeugwerk in 1990 and Diamond Aircraft in 1996. The DA-40 is its first FAR/JAR Pt23 certificated aircraft, its earlier products include the H-36 Dimona, HK-36 Super Dimona (Katana Xtreme) and the Rotax 912 and Continental IO-240 powered DV-20/DA-20 Katana two seater. The DA-20 is built in Canada.

Diamond formally launched the DA-40 on April 23 1997 at the Aero 97 airshow in Friedrichshafen, Germany. The Rotax 914 powered proof of concept DA-40V-1 first flew on November 5 1997, the second prototype DA-40V-2 with a IO-240 followed shortly after. The third prototype, with a Textron Lycoming IO-360, the production powerplant, flew in 1998. Four further prototypes followed, with JAA JAR 23 certification awarded on October 25 2000. FAA and JAR certification was awarded in April 2001.

The DA-40-180 is based loosely on the DA-20 but features a larger fuselage with seating for four and a slightly longer span wing. The airframe is made from glassfibre reinforced plastics with carbonfibre reinforcement in some areas. Power is from a Lycoming IO-360 with Lasar electronic fuel injection. Standard fuel capacity is 155 litres, optional fuel capacity is 200 litres.

The turbo diesel Thielert Centurion 1.7 powered DA-40D TDI flew on November 28 2001. Despite "only" producing 100kW (135hp) the Centurion 1.7 gives the DA-40D TDI cruise performance comparable to the DA-40-180 and even better range, while burning just 17 litres of fuel (either jet fuel or diesel) an hour. Deliveries of this version started in early 2003.

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The backbone of this section is from the The International Directory of Civil Aircraft by Gerard Frawley and used with permission. To get your own copy of the book click here.