Technical data
First-class performance - the technical data of the Do228 in an overview.
Versatile and reliable - The Do228 NXT
Overview of the Do228 technical data
Dimensions
| Height: | 15 ft 11 in (4.86 m) |
| Length: | 54 ft 4 in (16.56 m) |
Wings
| Span: | 55 ft 8 in (16.97 m) |
| Area: | 344.3 ft2 (32 m2) |
Passenger Compartment
| Overall length: | 23 ft 3 in (7.08 m) |
| Maximum width: | 4 ft 4 in (1.32 m) |
| Maximum height: | 5 ft 1 in (1.55 m) |
Doors (height x width)
| Cockpit door | 2 ft 9 in x 2 ft 2 in (0.84 m x 0.65 m) |
| Passenger airstair door: | 4 ft 5 in x 2 ft 1 in (1.34 m x 0.64 m) |
| Passenger/cargo door (both door panels are open): | 4 ft 5 in x 4 ft 2 in (1.34 m x 1.28 m) |
| Baggage door (front): | 3 ft 11 in x 1 ft 8 in (1.2 m x 0.5 m) |
| Baggage door (rear): | 2 ft 11 in x 1 ft 9 in (0.89 m x 0.53 m) |
| Emergency exits (3): | 2 ft 2 in x 1 ft 7 in (0.67 m x 0.48 m) |
Weights
| Max. take-off weight (MTOW)I: | 14,110 lb (6,400 kg) |
| Max. landing weight (MLW)II: | 13,448 lb (6,100 kg) |
| Max. zero fuel weight (MZFM): | 13,095 lb (5,940 kg) |
| Typical basic weight (cargo layout): | 8,157 lb (3,700 kg) |
| Typical basic weight (passenger layout): | 8,631 lb (3,915 kg) |
| Typical basic weight (mission layout): | 9,204 lb (4,175 kg) |
| Max. usable fuelIII: | 4,156 lb (1,885 kg) |
Engines
| Engine manufacturer: | Honeywell |
| Model: | 2x TPE331-10 engine |
| Propeller: | MTV-27 propellers |
| (Flat) rated power: | 579 kW (776 SHP) each |
| Takeoff noise level: | 76,7 db (A) |
| Engine start temperature limits: | -40 °C to 55 °C (-40 °F to +131 °F) |
| Engine operation temperature limits: | -54 °C to 55 °C (-65,2 °F to +131 °F) |
Best in class performance
Takeoff distance to 35 ft IV
| 2,606 ft (794 m) at ISA, SL |
| 3,134 ft (961 m) at ISA + 10°C, 2.000 ft elevation |
| 3,970 ft (1,219 m) at ISA + 20°C, 4.000 ft elevation |
Accelerate stop distanceV
| 2,562 ft (781 m) at ISA, SL |
| 3,027 ft (923 m) at ISA + 10°C at 2,000 ft elevation |
| 3,684 ft (1,123 m) at ISA + 20°C at 4,000 ft elevation |
Landing distance from 50 ftVI
| 1,473 ft (449 m) at ISA at SL |
| 1,595 ft (486 m) at ISA + 10°C at 2,000 ft elevation |
| 1,729 ft (527 m) at ISA + 20°C at 4,000 ft elevation |
Maximum rangeVII
| 1,340 NM (2,482 km) at 0 kg payload |
| 1,323 NM (2,450 km) at 645 kg payload |
| 160 NM (296 km) at max. payload |
Speed
| Max. cruise speed: 445 km/h TAS (240 KTAS) |
| Min. control speed: 137 km/h IAS (74 KIAS) |
Climb rate
| Climb rate - two enginesVIII: 1,637 ft / min (8,3 m/s) |
| Climb rate - single engineIX: 410 ft / min (2,1 m/s) |
STOL takeoff to 50 ftX
| 1,460 ft (445 m) at ISA, SL |
| 1,640 ft (550 m) at ISA + 10°C, 2.000 ft |
| 2,021 ft (616 m) at ISA + 20°C, 4.000 ft |
Max. altitude
| 25,000 ft (7,620 m) |
STOL landing from 30 ftXI
| 1,189 ft (362 m) at ISA, SL |
| 1,227 ft (374 m) at ISA + 10°C, 2.000 ft |
| 1,319 ft (402 m) at ISA + 20°C, 4.000 ft |
I Optional MTOW increase to 6,575 kg (civil) / 6,600 (military) possible
II Optional MLW increase to 6,400 kg
III Optional wet wing increases max. usable fuel to 2,252 kg
IV MTOW (14,110 lb), paved dry runway, 0 kts wind, 0% slope, flaps 1, engine failure at V1
V MTOW (14,110 lb), paved dry runway, 0 kts wind, 0% slope, flaps 1, engine failure at V1
VI MLW (13,448 lb), paved dry runway, 0 kts wind, 0% slope, flaps DN, unfactorized data
VII MTOW (14,110 lb), cargo layout incl. 2 pilots each 187 lb, ISA, FL100, 0 kts wind, best range speed, NBAA IFR reserves (100 NM alternate)
VIII ISA, sea level, MTOW (14,110 lb), flaps 1, VY
IX ISA, sea level, MTOW (14,110 lb), flaps UP, VYSE
X MTOW STOL (12,570 lb), paved dry runway, 0 kts wind, 0% slope, flaps 2, unfactorized data
XI MLW STOL (12,570 lb), paved dry runway, 0 kts wind, 0% slope, Flaps DN, unfactorized data