FORCETALLY
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At a glance
Measured figures
Falcon 900B · Length
Single source20.21 m (66 ft 4 in)[source]
PC-12NG · Length
Single sourceConfiguration
| Specification | Dassault Falcon 900 | Pilatus PC-12 |
|---|---|---|
| Type | Business jet[source] | Passenger and cargo aircraft[source] |
| National origin | France[source] | Switzerland[source] |
| Manufacturer | Dassault Aviation[source] | Pilatus Aircraft[source] |
| Status | Active service, in production[source] | In production |
14.4 m (47 ft 3 in)[source]
PC-12NG · Height
Single source4.26 m (14 ft 0 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; PC-12NG · Empty weight
Single sourceMaximum take-off; PC-12NG · Max takeoff weight
Single sourcePC-12NG · 1 × Pratt & Whitney Canada PT6A-67P turboprop engine 1,200 shp
Single source1 × Pratt & Whitney Canada PT6A-67P turboprop engine, 890 kW (1,200 shp)[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]
PC-12NG · 1,919 ft/min
Single source9.75 m/s (1,919 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] | PlaneSense Royal Flying Doctor Service Tradewind Aviation United States Air Force[source] |
|---|
| Number built | >500[source] | 2,000 (as of May 2023 )[source] |
|---|
| Manufactured | 1984–present[source] | 1991–present[source] |
|---|
| First flight | 21 September 1984 ( 1984-09-21 )[source] | 31 May 1991[source] |
|---|
| Developed from | Dassault Falcon 50[source] | — |
|---|
| Developed into | Dassault Falcon 2000 Dassault Falcon 7X[source] | — |
|---|
| Capacity | 19 passengers[source] | 6 to 9 passengers seats[source] |
|---|
| Fuel capacity | 8,690 kg (19,160 lb)[source] | 1,226 kg (2,703 lb) / 1,521 L (402 US gal; 335 imp gal)[source] |
|---|
| Aspect ratio | 7.63:1[source] | — |
|---|
| Stall speed | 158 km/h (98 mph, 85 kn) (wheels and flaps down)[source] | 124 km/h (77 mph, 67 kn)[source] |
|---|
| Introduction date | — | 1994[source] |
|---|
| Variant | — | Pilatus U-28 Draco[source] |
|---|
| Airfoil | — | root : NASA LS(1)-0417MOD; tip : NASA LS(1)-0313[source] |
|---|
| Maximum landing weight | — | 4,500 kg (9,921 lb)[source] |
|---|
| Maximum zero fuel weight | — | 4,100 kg (9,039 lb)[source] |
|---|
| Cabin | — | 5.16 metres (16.9 ft) long, 1.47 metres (4.8 ft) high, up to 1.52 metres (5.0 ft) wide[source] |
|---|
| Propellers | — | 4-bladed Hartzell Propeller composite, 2.67 m (8 ft 9 in) diameter composite constant-speed fully-feathering reversible propeller[source] |
|---|
| Take-off distance over 50 ft (15 m) | — | 793 m (2,602 ft)[source] |
|---|
| Landing distance over 50 ft (15 m) | — | 661 m (2,169 ft)[source] |
|---|
| Fuel consumption | — | 250 L/h (66 gal/h; 55 imp gal/h) (915 km (569 mi; 494 nmi) trip, including climb, cruise and descent, 491 km/h (305 mph; 265 kn) average block speed)[source] |
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