Patent ID: 8740147

Claim:
Pressure relief latch ( 30 , 130 , 230 ) for assembling in a removable way an aircraft panel ( 51 ) with an aircraft structure ( 53 ), said latch including: a console ( 31 , 131 , 231 ) able to be connected to the panel ( 51 ); a lever ( 34 , 134 , 234 ) mounted on the console so as to rotate about a first axis ( 35 , 135 , 235 ), an opening effort (E) exerted on a fulcrum ( 46 , 146 , 246 ) of the lever causing an angular displacement (D) of said fulcrum relative to the first axis, between a closing position and an opening position, a roller ( 37 , 137 , 237 ) arranged along a second axis ( 39 ) substantially parallel to the first axis, able to roll against a profile ( 36 , 136 , 236 ) of the lever when said lever moves between said positions, said roller being connected to a first end ( 41 ) of at least one elastic return device ( 42 , 142 , 242 ), one second end ( 43 ) of said device being connected to the console, the latch being characterized in that it is provided with means ( 47 , 48 , 136 , 260 ) able to vary the angular displacement (D) of the fulcrum of the lever according to the opening effort so that: between a minimal opening effort E 0 and an intermediate opening effort E 1 , the function D=f(E) has a slope higher than a value (X), between the intermediate effort E 1 and a maximum opening effort E 2 , the function D=f(E) has a slope lower than said value (X), said maximum effort E 2 corresponding to a maximum pressure between the panel and the structure, beyond which the opening position is reached, said means ( 47 , 48 , 136 , 260 ) being supported by the elastic return device and/or the profile of the lever and/or the fulcrum of the lever.