Patent ID: 6308915
Filing Date: 2001-10-30
Classification: B64D,B64F,F02C,F02K,F05D,Y02T

Abstract:
An aircraft tailcone assembly comprising:a longitudinal support member having forward and aft axial ends;a gas turbine engine mounted within said tailcone to said support member, said engine having an inlet and an exhaust;a firewall extending from said support member forward of said engine;at least one curved rotatable casing hingeably connected to said support member and rotatable from a closed position to an open position thereby exposing said engine;an inlet duct extending from an aperture in one of said rotatable casings to said engine inlet;interface means for making necessary electrical, mechanical, pneumatic, and hydraulic accessory connections between said tailcone assembly and said aircraft body; anda flange at said forward axial end of said support member adapted for quickly and rigidly attaching the entire tailcone assembly to said aircraft body.