Patent ID: 8627644

Claim:
A thrust reverser for an airplane nacelle comprising: a front frame mounted downstream of a fan casing of a bypass turbojet engine housed in said nacelle, the front frame connecting the turbojet engine to a pylon; a reverser of the cascade type, these cascades being mounted on said front frame; a cowl mounted such that the cowl moves between a closed position in which the cowl covers said front frame, an open position in which the cowl uncovers said front frame and an intermediate maintenance position in which the cowl is situated downstream of said front frame; means for moving said cowl between said closed and open positions; and an internal structure able to move between an operating position in which the internal structure is partially covered by said front frame and is able to cover part of said turbojet engine and to define an annular cold air flowpath with said cowl, and the intermediate maintenance position situated downstream of said front frame, wherein said cowl comprises two half-cowls, and said internal structure comprises two internal half-structures, these half-cowls and these internal half-structures being able to open outward when said cowl and said internal structure are in the intermediate maintenance position.