| 摘要 |
A mount (20) for mounting an aircraft engine (10) to an aircraft includes a mounting frame (46) having first and second flanges (48, 50) spaced apart a predetermined distance. Each of the first and second flanges (48, 50) has a bolt hole (70) formed therein. A single thrust link (56) is connected at one end to th e mounting frame (46) and at another end to the engine (10) and serves as the primary axial loadpath for the engine (10). A lug (68) formed on the engine casing (38) is disposed between the first and second flanges (48, 50) and has a thickness that is le ss than the distance between the first and second flanges (48, 50). The lug (68) also ha s a bolt hole (70) formed therein. A bolt (72) extends through the bolt holes (70) in the first and second flanges (48, 50) and the lug (68) to connect the lug (68) to the first and second flanges (48, 50). The bolt hole (70) in the lug (68) is larger in diameter than the bolt (72) to allow the lug (68) to slide axially along the bolt (72). Th e first and second flanges (48, 50), the lug (68) and the bolt (72) provide a waiting failsafe arrangement (66) for reacting axial loads upon failure of the single thrust link (56).
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