Abstract: The invention relates to a turbojet suspension pylon for an aircraft, the pylon being provided with a rigid structure (10) comprising a longitudinal central box (22). According to the invention, the rigid structure also comprises two lateral boxes (24a, 24b) fixed to a forward part of said central box (22), the pylon also comprising a first (6a) and a second (6b) engine forward suspension designed to resist forces applied along the longitudinal direction (X) of the pylon, these first and second suspensions being arranged on the two lateral boxes respectively.
Type:
Application
Filed:
May 22, 2006
Publication date:
August 14, 2008
Applicant:
Arbus France
Inventors:
Lionel Diochon, Michael Sarrato, David Chartier, Isabelle Petrissans