Skip to main content

DA40 Series
Technical Specifications

Power Plant

 DA40 NG

DA40 XLT

Engine

Austro Engine AE 300 turbocharged common-rail injected 2.0 liter diesel engine with 168 hp and EECU single lever control system

180 hp Lycoming IO360M1A AVGAS Piston Engine

Propeller

MT propeller MTV-6-R-/190-69 3-blade constant speed propeller

Hartzell 2 blade metal constant speed propeller. Optional Hartzell 2 blade composite constant speed propeller. Optional MT 3 blade constant speed propeller

Fuel grades

Jet A-1, Jet A, TS-1 (Russia, Ukraine), RT (Russia, Ukraine), No. 3 Jet Fuel (China), JP-8

AVGAS

Performance (max. mass)

 DA40 NG 

DA40 XLT

 

Max. speed (14,000 ft, MCP)

285 km/h TAS1154 kts TAS1263 km/h TAS

142 kts TAS

Cruise speed at 60 % (14,000 ft)

231 km/h TAS1125 kts TAS1

Cruise speed at 75 % (6,000 ft)

  

Stall speed, landing con guration

107 km/h CAS58 kts CAS169 km/h CAS

91 kts CAS

Rate of climb (ISA SL)

3.5 m/s1690 ft/min14.6 m/s

910 ft/min

Range at 60 % (incl. auxiliary tank)

1,741 km1940 nm1

Range at 45 % (incl. auxiliary tank)

1,537 km

830 nm

Consumption at 60 %

19.7 l/h5.2 US gal/h19.7 l/h

5.2 US gal/h

Take-off ground roll (ISA SL)

370 m1

1,214 ft1305 m

1,000 ft

Landing ground roll (ISA SL)

270 m886 ft305 m

1,000 ft

Max. operating altitude

5,000 m16,400 ft5,000 m

16,400 ft

Max. demonstrated crosswind

46 km/h

25 kts

37 km/h

20 kts

Dimensions

Mass and Loading

 DA40 NG DA40 XLT 

Seats

4444

Empty weight

900 kg11,984 lbs1792 kg2

1,746 lbs2

Useful load

410 kg1904 lbs1408 kg2

900 lbs2

Max. take off mass

1,310 kg2,888 lbs1,200 kg

2,646 lbs

Fuel capacity total
main tank
auxiliary tank

147 l / 118 kg
106 l / 84 kg
41 l / 33 kg
39 US gal / 261 lbs
28 US gal / 188 lbs
11 US gal / 74 lbs
189 l / 136 kg

50 US gal / 301 lbs

Specifications apply to standard equipped aircraft, if not otherwise stated. The above data are approximately specifications and may change without notice.
1. Specification may vary on the DA40 Tundra Star version.
2. Weight and Loads shown are for standard con guration. Selection of optional features may affect these weights. S/N specific Production variances can occur.