Patent ID: 8864066

Claim:
An aircraft engine assembly comprising: a turbine engine and a pylon to mount the turbine engine, wherein the engine assembly is configured to be added on laterally to a structure of the aircraft, wherein the pylon includes a rigid structure including at least one box and offset radially relative to a lengthways axis of the turbine engine in a line of separation, wherein the pylon further includes first fasteners mounting the turbine engine on the rigid structure, and second fasteners attached firstly to the rigid structure and configured to be attached to the structure of the aircraft, wherein the second fasteners include a first attachment and a second attachment allowing a moment exerted in a lengthways direction of the turbine engine to be transmitted jointly, wherein each of the first and second attachments of the second fasteners includes a cylindrical part to transmit loads, and the cylindrical part is aligned in the lengthways direction of the turbine engine and traverses one or more orifices having an axis in the lengthways direction of the turbine engine, so that the first and second attachments are directly attached to the rigid structure and to the structure of the aircraft and do not transmit loads in the lengthways direction of the turbine engine between the rigid structure and the structure of the aircraft, wherein the rigid structure further includes a box rib extension protruding from the at least one box, in a first direction of the line of separation extending from the turbine engine to the rigid structure, and wherein the rib extension supports the first attachment in a position separating the first attachment from the second attachment, in the line of separation.