Structure for transferring a lateral load of an engine pylon to an aircraft wing

A structure for transferring a lateral load of an engine pylon to a wing of an aircraft, wherein the aircraft defines a longitudinal direction and a lateral direction perpendicular to the longitudinal direction, comprising:

• a first component having a first base portion and a first flange extending outward from the first base portion;
• a second component having a second base portion, a first raised portion extending outward from the second base portion to a first height, a second raised portion extending outward from the second base portion to a second height and being laterally spaced apart from the first raised portion, and a wall portion extending outward from the second base portion between the first and second raised portions to a third height that is less than either of the first and second heights with the wall portion terminating at a wall portion end;
• and a bushing having a base plate with laterally opposed first and second base plate ends, a first arm extending from the first base plate end, and a second arm extending from the second base plate end;
• wherein the first component, the second component and the bushing are configured to be assembled in an assembled state in which:
• the first flange is oriented generally longitudinally;
• the bushing is mounted to the second component in a manner such that the base plate of the bushing is in contact with the wall portion end of the second component, and the first and second arms of the bushing are positioned between the first and second raised portions of the second component;
• and at least part of the first flange of the first component is disposed between the first and second arms of the bushing, such that the first and second components are substantially restrained against lateral movement with respect to each other.

A structure for transferring a lateral load of an engine pylon to a wing of an aircraft, wherein the aircraft defines a longitudinal direction and a lateral direction perpendicular to the longitudinal direction, comprising:

• a first component having a first base portion and a first flange oriented generally longitudinally and extending outward from the first base portion, and a second flange extending outward from the first base portion and running generally parallel with the first flange, thereby defining an interflange gap between the first and second flanges, wherein the first base portion is attached to or made integral with one of the wing and the engine pylon;
• a second component having a second base portion and a raised portion extending outward from the second base portion toward the first base portion with the raised portion terminating at a raised portion end, wherein the second base portion is attached to or made integral with the other of the wing and the engine pylon;
• and
• one or more bushings each having a respective base plate with respective opposed first and second base plate ends and a respective first arm extending from the respective first base plate end;
• wherein each of the one or more bushings is disposed with its respective base plate in contact with the raised portion end and with its respective first arm extending toward the second base portion between the raised portion and the first or second flange;
• and
• wherein at least part of the raised portion and at least part of the one or more bushings are disposed within the interflange gap, such that the engine pylon is substantially restrained against lateral movement with respect to the wing.