Patent ID: 9399520
Filing Date: 2016-07-26
CPC Classification: B64D,F16B,F16C,Y10T

Claim Text:
1. An aircraft engine mounting assembly carrying an aircraft engine comprising: a clevis with a first arm and a second arm, a first sleeve and a second sleeve, an articulation spindle mounted in the first sleeve inserted into the first arm of the clevis and in the second sleeve inserted into the second arm of said clevis, said first sleeve comprising an inner shoulder projecting into said first sleeve and acting as a stop for a first end of said articulation spindle, a blocking device acting as a stop for a second end of said articulation spindle, a nut screwed onto a threaded portion of an extension of the second sleeve, the nut comprising an inner shoulder acting as a stop for the second end of the articulation spindle, at least two locking washers, each locking washer comprising an orifice having shapes complementary with those of the nut allowing the locking washer to move in translation on the nut and preventing a relative rotational movement between the locking washer and the nut, a tab washer comprising an orifice such that said tab washer is arranged about the extension of the second sleeve, the tab washer further comprising an element immobilizing it in rotation with respect to the second arm of the clevis, for each locking washer, a blocking element configured to adopt a first locked state, in which the blocking element limits the rotational movement of the locking washer with respect to the tab washer, and a second unlocked state, in which the blocking element does not impede the rotational movement of the locking washer with respect to the tab washer.