FORCETALLY
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At a glance
Measured figures
Falcon 900B · Length
Single source20.21 m (66 ft 4 in)[source]
L-410 UVP-E20 · Length
Single sourceConfiguration
| Specification | Dassault Falcon 900 | Let L-410 Turbolet |
|---|---|---|
| Type | Business jet[source] | Regional airliner , cargo aircraft[source] |
| National origin | France[source] | — |
| Manufacturer | Dassault Aviation[source] | Let Kunovice[source] |
| Status | Active service, in production[source] | In service[source] |
14.42 m (47 ft 4 in)[source]
L-410 UVP-E20 · Height
Single source5.97 m (19 ft 7 in)[source]
Empty; Falcon 900B · Empty weight
Single sourceMaximum take-off; Falcon 900B · Max takeoff weight
Single source10,255 kg (22,608 lb)[source]
20,640 kg (45,503 lb)[source]
Empty; L-410 UVP-E20 · Empty weight
Single sourceMaximum take-off; L-410 UVP-E20 · Max takeoff weight
Single sourceL-410 UVP-E20 · 2 × General Electric H80-200 turboprop engines each
Single source2 × General Electric H80-200 turboprop engines, 597 kW (801 hp) each[source]
Falcon 900B · 3 × Honeywell TFE731 -5BR-1C turbofans thrust each
Single source3 × Honeywell TFE731 -5BR-1C turbofans , 21.13 kN (4,750 lbf) thrust each[source]
L-410 UVP-E20 · 1,670 ft/min
Single source8.5 m/s (1,670 ft/min)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Primary users |
|---|
French Air and Space Force Japan Coast Guard Nigerian Air Force Royal Malaysian Air Force[source] |
Russian Air Force Slovak Air Force Searca Aeroflot (historical)[source] |
| Number built | >500[source] | 1,200[source] |
|---|
| Manufactured | 1984–present[source] | 1971–present[source] |
|---|
| First flight | 21 September 1984 ( 1984-09-21 )[source] | 16 April 1969[source] |
|---|
| Developed from | Dassault Falcon 50[source] | — |
|---|
| Developed into | Dassault Falcon 2000 Dassault Falcon 7X[source] | Let L-610[source] |
|---|
| Capacity | 19 passengers[source] | 19 passengers / 1,800 kg (3,968 lb) payload[source] |
|---|
| Fuel capacity | 8,690 kg (19,160 lb)[source] | 1,300 kg (2,866 lb)[source] |
|---|
| Aspect ratio | 7.63:1[source] | 11.45[source] |
|---|
| Stall speed | 158 km/h (98 mph, 85 kn) (wheels and flaps down)[source] | — |
|---|
| Introduction date | — | 1970[source] |
|---|
| Variant | — | Aircraft Industries L 410 NG[source] |
|---|
| Endurance | — | Five hours and six minutes[source] |
|---|
| Airfoil | — | root: NACA 63A418 ; tip: NACA 63A412[source] |
|---|
| Propellers | — | 5-bladed Avia AV 725, 2.3 m (7 ft 7 in) diameter[source] |
|---|
| Fuel consumption | — | 240 kg/h (529 lb/h)[source] |
|---|
| Take-off run | — | 510 m (1,670 ft) (ISA, SL, MTOW)[source] |
|---|
| Landing run | — | 500 m (1,600 ft) (ISA, SL, MTOW)[source] |
|---|
| Alternative designation | — | L-410 Turbolet[source] |
|---|
| Country of origin | — | Czechoslovakia[source] |
|---|