Abstract: A turbine engine mount to a pylon of an aircraft includes a bracket arranged to be attached to the pylon, and a lever attached in its central part to the bracket via a first connection and two thrust links each joined aft to the lever by a second connection. The lever includes a central part with two arms, and the bracket includes an integral attachment lug placed between the two arms and connected to the arms via a pivot pin to form the first connection. The lever is laterally connected to the bracket via pivot pins passing through the lever and mounted with a clearance to form connections on standby.

Abstract: The present invention pertains to turbine engine mounting onto an aircraft pylon, comprising a bracket (12) arranged to be attached to the pylon, a lever (15;15?) attached in its central part (150;150?) to the bracket by first connection means (150-130) with a pivot pin (136;136?) and two thrust links (20,22; 20?,22?) each joined aft to the lever by second connection means (200-155, 220-157; 200?-155?; 220?-157?) and including engine attachment means at the forward end, characterized in that the first connection means (150-130) consists of two parallel arms (151,153) spaced apart on central part (150) of the lever, cooperating with an attachment lug (130) integral with the bracket via a pivot pin, and lever (15,15?) comprises two third side connection means on standby (155-135, 157-137; 155?-135?; 157?-137?) with bracket (12,12?). The invention provides for simplified mounting with improved safety.