Abstract: A locking mechanism situated in an inner zone and comprising at least one component that is adjustable in a longitudinal direction and that is linked to a support by a link having a rod secured to the adjustable component. The link includes a guideway link, linking the rod and the support, and an adjustment system. The adjustment system comprises a pivoting control pivoting on itself and having a first end accessible from an outer zone, an intermediate piece configured to pivot on itself, an angle transmission converting a pivoting movement of the pivoting control into a pivoting movement of the intermediate piece, and a helical link converting a pivoting movement of the intermediate piece into a translational movement of the rod. The locking mechanism allows for adjustment from the outer zone. An aircraft comprising at least one such locking mechanism is also provided.

Abstract: A seal is interposed between two surfaces of an aircraft propulsion assembly. The seal includes at least two layers each comprising a plurality of strands made of a heat-resistant material, the strands of a first layer being oriented in a first orientation and the strands of a second layer being oriented in a second orientation different than the first orientation.