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 (111) is attached to the front of the fan case such that loads acting on the air intake (111) are primarily transmitted to the fan case (125). The mounting assembly includes a support structure (133) extending in an axial direction of the engine and having a rearward region 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 (125), the load distribution ring (135) being adapted to join to the fan case (125), and being joined to a forward region of the support structure (133). The support structure (133) and the load distribution ring (135) are adapted such that the primary load path for the loads transmitted to the fan case (125) by the air intake (111) is through the load distribution ring (135) and the support structure (133), and thence to the aircraft.