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Name Falcon 7X
Manufacturer DASSAULT
Body Narrow
Wing Fixed Wing
WTC Medium
Type code L3J
Engine Jet
Engine count Multi
Mass group 4

Manufacturered as:





The Dassault Falcon 7X is a three-engine long-range corporate jet aircraft produced by the French manufacturer Dassault Aviation.

Technical Data

Wing span 26.21 m85.991 ft <br />
Length 23.19 m76.083 ft <br />
Height 7.80 m25.591 ft <br />
Powerplant 3 x Pratt & Whitney Canada PW307A, 28,5 kN each.
Engine model Pratt & Whitney Canada PW300

Performance Data

Take-Off Initial Climb
(to 5000 ft)
Initial Climb
(to FL150)
Initial Climb
(to FL240)
MACH Climb Cruise Initial Descent
(to FL240)
(to FL100)
Descent (FL100
& below)
V2 (IAS) kts IAS kts IAS kts IAS kts MACH TAS 487 kts MACH IAS kts IAS kts Vapp (IAS) kts
Distance 1590 m ROC ft/min ROC ft/min ROC ft/min ROC ft/min MACH 0.85 ROD ft/min ROD ft/min MCS kts Distance m
MTOW 2890028,900 kg <br />28.9 tonnes <br /> kg Ceiling FL510 ROD ft/min APC B
WTC M Range 57005,700 nm <br />10,556,400 m <br />10,556.4 km <br />34,633,858.293 ft <br /> NM

Accidents & Serious Incidents involving FA7X

  • FA7X, London City UK, 2016 (On 24 November 2016, a Dassault Falcon 7X being marshalled into an unmarked parking position after arriving at London City Airport was inadvertently directed into a collision with another crewed but stationary aircraft which sustained significant damage. The Investigation found that the apron involved had been congested and that the aircraft was being marshalled in accordance with airport procedures with wing walker assistance but a sharp corrective turn which created a 'wing growth' effect created a collision risk that was signalled at the last minute and incorrectly so by the wing walker involved and was also not seen by the marshaller.)
  • FA7X, en-route, north east of Kuala Lumpur Malaysia, 2011 (On 24 May 2011, a sudden uncommanded maximum upward deflection of the trimmable horizontal stabiliser occurred to a descending Dassault Falcon 7X. Automatic opposite elevator movement did not resolve the situation and an upset lasting just over 2½ minutes followed with a 9,500 feet climb at up to 41° pitch and a speed drop to 125KCAS. Only autonomous return of normal pitch response ended the control difficulty. The remainder of the flight was without further event. A single suddenly defective component with no effective crew response available and not anticipated during type certification was found to have caused the runaway.)