| 摘要 |
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.
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