| abstract |
The invention provides a locking system on a cascade thrust reverser for a bypass turbojet, the reverser ( 20 ) comprising guide means ( 60 ) for the movable parts ( 50 ), and the guide means ( 60 ) comprising rails ( 64 ) attached to the movable parts ( 50 ) and tracks ( 62 ) attached to the longitudinal members ( 36 ). n According to the invention, the locking system ( 80 ) comprises locks ( 82 ) located at the end ( 62 a ) of each track ( 62 ) in the opening direction ( 52 ), each lock comprising a bolt ( 110 ) capable of preventing the rail ( 64 ) moving in the opening direction ( 52 ). |