Credit
Adrian Pingstone ( Arpingstone ) · Public domain · Resized · Public domain · Source ↗ · Modified
FORCETALLY
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At a glance
Measured figures
Jetstream 41 · Length
Single source63 ft 2 in (19.25 m)[source]
Falcon 20F · Length
Configuration
| Specification | British Aerospace Jetstream 41 | Dassault Falcon 20 |
|---|---|---|
| Type | Regional airliner /Feederliner[source] | Business jet[source] |
| National origin | United Kingdom[source] | France[source] |
| Manufacturer | British Aerospace[source] | Dassault Aviation[source] |
| Status | In service[source] | Out of production, in active service |
17.15 m (56 ft 3 in)[source]
Empty; Jetstream 41 · Empty weight
Single sourceMaximum take-off; Jetstream 41 · Max takeoff weight
Single source14,272 lb (6,474 kg)[source]
24,000 lb (10,886 kg)[source]
Empty; Falcon 20F · Empty weight
Single sourceMaximum take-off; Falcon 20F · Max takeoff weight
Single sourceCruise; Jetstream 41 · max at 20,000 ft (6,100 m)
Single sourceMaximum; Jetstream 41 · at 20,000 ft (6,100 m)
Single source295 kn (339 mph, 546 km/h) at 20,000 ft (6,100 m)[source]
295 kn (339 mph, 546 km/h) max at 20,000 ft (6,100 m)[source]
Cruise; Falcon 20F · at 12,200 m (40,000 ft) (econ. cruise)
Single sourceMaximum; Falcon 20F · at 7,620 m (25,000 ft) (max cruise)
Single sourceJetstream 41 · 2 × Allied Signal TPE331-14GR/HR turboprop engines, 1,650 shp ( ) each (handed GR / HR
Single source2 × Allied Signal TPE331-14GR/HR turboprop engines, 1,650 shp (1,230 kW) each (handed GR / HR)[source]
Falcon 20F · 2 × General Electric CF700 -2D-2 turbofans thrust each
Single source2 × General Electric CF700 -2D-2 turbofans , 20 kN (4,500 lbf) thrust each[source]
Jetstream 41 · 2,200 ft/min (
Single source2,200 ft/min (11 m/s)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Primary users | Guna Airlines Proflight Zambia[source] | Federal Express (formerly) French Navy United States Coast Guard[source] |
|---|
| Number built | 100[source] | 512[source] |
|---|
| Manufactured | 1992–1997[source] | 1965–1991[source] |
|---|
| Introduction date | 25 November 1992[source] | 3 June 1965[source] |
|---|
| First flight | 25 September 1991[source] | 4 May 1963[source] |
|---|
| Developed from | British Aerospace Jetstream 31[source] | — |
|---|
| Capacity | 29 passengers[source] | 8–14 passengers[source] |
|---|
| Airfoil | root: NACA 63A418 ; tip: NACA 63A412[source] | — |
|---|
| Maximum zero-fuel weight | 21,400 lb (9,707 kg)[source] | — |
|---|
| Maximum ramp weight | 24,100 lb (10,932 kg)[source] | — |
|---|
| Maximum landing weight | 23,300 lb (10,569 kg)[source] | — |
|---|
| Fuel capacity | 727 imp gal (873 US gal; 3,305 L) / 5,960 lb (2,703 kg) maximum[source] | 5,200 L (1,100 imp gal; 1,400 US gal)[source] |
|---|
| Propellers | 5-bladed McCauley , 9 ft 6 in (2.9 m) diameter (handed GR / HR) constant-speed feathering metal propellers[source] | — |
|---|
| Never exceed speed | 315 kn (362 mph, 583 km/h) CAS sea level to 17,400 ft (5,300 m)[source] | — |
|---|
| Service ceiling on one engine | 15,000 ft (4,600 m)[source] | — |
|---|
| Wing loading | 68.42 lb/sq ft (334.1 kg/m 2 )[source] | — |
|---|
| Power/mass | 0.1375 shp/lb (0.2260 kW/kg)[source] | — |
|---|
| Take-off run | 5,000 ft (1,500 m)[source] | — |
|---|
| Landing run | 4,200 ft (1,300 m)[source] | — |
|---|
| Developed into | — | Dassault Falcon 10 Dassault Falcon 50[source] |
|---|
| Aspect ratio | — | 6.4:1[source] |
|---|
| Stall speed | — | 152 km/h (94 mph, 82 kn)[source] |
|---|