FORCETALLY
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At a glance
Measured figures
Falcon 900B · Length
Single source20.21 m (66 ft 4 in)[source]
Super 748 · Length
Single sourceConfiguration
| Specification | Dassault Falcon 900 | Hawker Siddeley HS 748 |
|---|---|---|
| Type | Business jet[source] | Airliner[source] |
| National origin | France[source] | United Kingdom[source] |
| Manufacturer | Dassault Aviation[source] | Avro Hawker Siddeley Hindustan Aeronautics[source] |
| Status | Active service, in production[source] | In limited service with the Indian Air Force |
67 ft 0 in (20.42 m)[source]
Super 748 · Height
Single source24 ft 10 in (7.57 m)[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; Super 748 · Empty weight
Single sourceMaximum take-off; Super 748 · Max takeoff weight
Single sourceSuper 748 · 2 × Rolls-Royce RDa.7 Dart Mk 536-2 turboprop engines, 2,280 shp ( ) each equivalent
Single source2 × Rolls-Royce RDa.7 Dart Mk 536-2 turboprop engines, 2,280 shp (1,700 kW) each equivalent[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]
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] | British Airways Air Creebec Dan-Air Air North Varig[source] |
|---|
| Number built | >500[source] | 380[source] |
|---|
| Manufactured | 1984–present[source] | 1961–1988[source] |
|---|
| First flight | 21 September 1984 ( 1984-09-21 )[source] | 24 June 1960[source] |
|---|
| Developed from | Dassault Falcon 50[source] | — |
|---|
| Developed into | Dassault Falcon 2000 Dassault Falcon 7X[source] | Hawker Siddeley Andover BAe ATP[source] |
|---|
| Capacity | 19 passengers[source] | 40–58 passengers / 11,323 lb (5,136 kg) payload[source] |
|---|
| Fuel capacity | 8,690 kg (19,160 lb)[source] | 1,440 imp gal (1,730 US gal; 6,500 L) in two wing integral tanks[source] |
|---|
| Aspect ratio | 7.63:1[source] | 11.967[source] |
|---|
| Stall speed | 158 km/h (98 mph, 85 kn) (wheels and flaps down)[source] | — |
|---|
| Airfoil | — | root: NACA 23018 ; tip: NACA 4412[source] |
|---|
| Propellers | — | 4-bladed Dowty Rotol constant-speed fully-feathering propellers, 12 ft 0 in (3.66 m) diameter[source] |
|---|
| Wing loading | — | 56.1 lb/sq ft (274 kg/m 2 )[source] |
|---|
| Power/mass | — | 0.0981 hp/lb (0.1613 kW/kg)[source] |
|---|
| Take-off distance to 50 ft (15 m) | — | 3,800 ft (1,200 m)[source] |
|---|
| Landing distance from 50 ft (15 m) | — | 2,034 ft (620 m)[source] |
|---|
| Take-off distance | — | 2,624 ft (800 m)[source] |
|---|
| Landing distance | — | 1,968 ft (600 m)[source] |
|---|