The present disclosure relates to a rear assembly of a turbojet engine nacelle that includes a thrust reverser fixed structure having at least one half-cowl mounted on a beam pivotally hinged by at least one hinge, a suspension mast on which the fixed structure is movably mounted, a hatch for access to the hinge of the half-cowl, and a fireproof sealing device which includes a sealing gasket adapted to provide sealing between a median section of the nacelle and the beam area. The sealing gasket includes a tubular gasket type lower portion which extends at least partially over a seal bearing edge of the half-cowl that is adapted to cooperate with a seal bearing wall of the mast and an upper portion including an elastically deformable sealing sheet extending from the seal bearing wall of the mast to the rear face of the hatch for access to the hinge.
ENSEMBLE ARRIERE DE NACELLE DE TURBOREACTEUR COMPORTANT UN DISPOSITIF D'ETANCHEITE ANTI-FEU
2018-08-31
Patent
Electronic Resource
French
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
ENSEMBLE ARRIÈRE DE NACELLE DE TURBORÉACTEUR COMPORTANT UN DISPOSITIF D'ÉTANCHÉITÉ ANTI-FEU
European Patent Office | 2018
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