Abstract: A front attachment device for attaching an aircraft engine to an aircraft pylon includes an upper brace fitted with elements rigidly fastened to the pylon and first and a second connecting rods, each connected to the engine, via a first ball joint connection at one end portion and to the upper brace via a second ball joint connection on the other end portion. The device further includes in each connecting rod a third stand-by link. The first and second connecting rods are interchangeable with each other.

Abstract: A suspension of the turbo fan engine to an aircraft pylon, includes a fitting arranged to be attached to a pylon, a lever fastened in its central portion to the fitting via a linking device with a pivot pin. Two thrust rods are each connected by an end to the lever and including at the other end of the fastening device to the engine. The linking device is composed on the central portion of the lever, of two parallel branches apart from one another, and on the fitting, of a central fastening tab, whereas the fastening tab and both branches are held together by dint of the pivot pin.

Abstract: The present invention relates to an attachment device, in particular a front attachment device, for attaching a turbo engine (1) to an aircraft pylon including an upper brace (12, 12′) fitted with rigid fastening means to the pylon, a first (16) and a second (18) connecting rods, each connected to the engine, via a first ball joint connection (161, 181; 161′, 181′), on the one hand, and to the upper brace (12, 12′) via a second ball joint connection (165, 185; 165′, 185′), on the other hand. The device is characterised in that each connecting rod (16, 18) includes a third stand-by link (167, 187; 176′, 187′).

Abstract: The present invention relates to a suspension of the turbo fan engine to an aircraft pylon, including a fitting (12) arranged to be attached to a pylon, a lever (15) fastened in its central portion (150) to the fitting via a linking means with a pivot pin (150P), and two thrust rods (20, 22) each connected by an end to the lever and including at the other end of the fastening means to the engine. It is characterised in that said linking means is composed on said central portion (150) of the lever, of two parallel branches (151, 152) apart from one another, and on the fitting, of a central fastening tab (133), whereas the fastening tab and both branches are held together by dint of said pivot pin (150P).

Abstract: The present invention relates to a rear attachment suspension or device of a turbo engine (1) to an aircraft pylon including an upper brace (12) fitted with pylon fastening means, whereon are hinged by second ball joint connections (163, 183), three rocker bars transversal to the longitudinal axis of the engine, a first (16) and a second (18) rocker bars on both sides of the axis of the engine and a third rocker bar (17) between both of them, the rocker bars being themselves linked with the engine by first ball joint connections (161, 181). The suspension is characterised in that the first (16) and second (18) rocker bars each include a third (167, 187) stand-by link and in that the upper brace (12) is formed of a beam (120) fixed rigidly to the pylon.

Abstract: A jet engine suspension comprises a master component for attachment, fixed to an aircraft pylon. If it breaks and if the situation arises where the fixing screws are no longer able to transmit force, a peg takes over: the master component collapses until an upper shoulder rests on the pylon and supports this component. The peg is free of dynamic stress in normal service and there is absolutely no risk of it cracking in fatigue.