Abstract: The rear hanging structure by which a turbojet engine is suspended from a mast under the wing of an aircraft includes a brace which is fixed to the mast and to which the engine is attached by at least three suspension links, the brace includes two parts which are fitted one within the other and are dimensioned in such a way as to ensure that each is able to take all of the suspension stresses independently of the other, the pins by which the brace is connected to the mast and to the suspension links passing through both parts of the brace. The redundancy thus achieved increases considerably the reliability of the suspension.

Abstract: The present invention provides an air tapping device for tapping a portion of the air passing through the bypass duct of a fan-type turbojet engine. The device is incorporated into the engine mount and is provided with an anti-vibration mounting to minimize the transmission of engine vibrations to the air tapping device. The device is preferably incorporated into the rear engine mount which attaches the engine to the aircraft structure.

Abstract: An engine mounting structure for a turbojet engine is disclosed which incorporates a safety rod in addition to the normal support rods used to attach a turbojet engine to a mounting structure. Under normal conditions, the safety rod is unstressed and supports none of the engine's weight. Upon rupture of one of the support rods, a tensile or compressive force exerted on the safety rod will move it into an active position so as to assume support of the engine's weight. A locking structure is also disclosed which will securely lock the rod in its active position such that it assumes the portion of the engine weight normally undertaken by the ruptured support rod.

Abstract: A dolly for use in the installation of a jet engine in an aircraft compartment. The dolly has longitudinal guide rails placed in the compartment and a device including two lateral guide rails and a lower, median guide rail; a foldable and removable front cradle carrying two runners and capable of being attached to the front of the engine, the runners cooperating with the lateral guide rails; a rear cradle that is removable and equipped with a runner cooperating with the lower median guide rail; a frame to which the lateral guide rails are adjustably attached; means for the vertical displacement and the longitudinal displacement of the frame.

Abstract: The apparatus for suspending a jet engine is composed of three assemblies: an assembly 1 of parts placed permanently on the engine, an assembly 3 of parts placed permanently on the cell, and a liaison assembly 5 for connection of the preceding parts. Assembly 3 placed on the cell is disposed at the bottom of a recess and the parts forming the liaison assembly are put into place across the recess and the assembly on the cell using tooling consisting of a guide tube and two spanners, the ends of which cooperate with the ends of the pieces of the liaison assembly. The invention also concerns a process and tooling for using the apparatus.