Gas turbine engine mounting assembly

A mounting assembly for attaching a ducted fan gas turbine engine to an aircraft is provided. The engine has an intake 111, a propulsive fan, a fan case 125 surrounding the fan, and a core engine 126. The air intake is attached to the front of the fan case such that loads acting on the air intake are primarily transmitted to the fan case. The mounting assembly includes a support structure 133 extending in an axial direction of the engine and having a rearward region 134 which is adapted to attach to the aircraft. The mounting assembly further includes load distribution ring 135 which is coaxial with and rearward of the fan case, the load distribution ring being adapted to join to the fan case, and being joined to a forward region of the support structure. The support structure and the load distribution ring are adapted such that the primary load path for the loads transmitted to the fan case by the air intake is through the load distribution ring and the support structure, and thence to the aircraft.