Patent ID: 7527220

Claim:
A mount for an aircraft engine configured to be attached firstly by a mounting beam to an aircraft, and secondly by lateral load transmission elements and a median load transmission element to the aircraft engine, wherein said lateral and median load transmission elements transmit loads from the engine to the aircraft during normal operation of said mount, the mount comprising: said mounting beam; said lateral load transmission element; and an integrated load transmission and failsafe assembly including said median load transmission element, said integrated load transmission and failsafe assembly being configured to ensure continuity of load transmission for said loads transmitted from the engine to the aircraft in the event of failure of one of said lateral and median load transmission elements, wherein the load transmission and failsafe assembly comprises a female clevis with two wings and a projecting failsafe element passing with clearance through the two wings of said female clevis, one of said female clevis and said projecting failsafe element being integral with the aircraft engine or with an intermediate case of said aircraft engine and the other of said female clevis and said projecting failsafe element being integral with the mounting beam, wherein said clearance between said projecting failsafe element and said two wings of said female clevis extends around an entire circumference of said projecting failsafe element.