Patent ID: 7997527
Filing Date: 2011-08-16
Classification: B64D

Abstract:
1. An assembly for an aircraft comprising: a wing element having a forward spar oriented parallel to a leading edge of the wing element along a wing spar direction; a suspension pylon for an engine under the wing element, wherein said wing spar direction is oriented in an X-Y plane and inclined in X and Y directions, wherein the X direction is the longitudinal direction of the suspension pylon and is parallel to a longitudinal axis of the engine and the Y direction is transverse to the suspension pylon and to the longitudinal axis of the engine, a Z direction being a vertical direction, and the X, Y and Z directions being orthogonal to each other; an attachment structure for attaching a rigid structure of the pylon onto the wing element, said attachment structure including two forward half-attachments, wherein each of said two forward half-attachments includes a shackle and is configured to resist forces applied along the vertical direction of the suspension pylon, wherein each shackle is mounted firstly articulated through a first pin onto a first fitting fixed to the forward spar, wherein the shackles have axes parallel to each other and parallel to the wing spar direction of the wing element, wherein each shackle is secondly mounted articulated through a second pin onto a second fitting fixed to the rigid structure, and wherein a same plane contains the axes of the two shackles of the forward half-attachments and said same plane does not intersect the wing spar direction.