Abstract: A propulsive assembly including a turbine engine configured to be fastened to an aircraft by means of a suspension, having certain casing portions suitable for being decoupled so as to attenuate certain bending modes of the turbine engine in the event of an incident, the propulsive assembly comprising at least first and second casing portions (33a, 22) extending axially one after another, one of said casing portions being cantilevered out relative to said suspension, wherein a first casing portion (33a) possesses a first fastener portion (41) connected rigidly to the body (43) of the first casing portion (33a) and a second fastener portion (42) connected more flexibly to the body (43) of the first casing portion (33a), and wherein the second casing portion (22) is fastened to the second fastener portion (42) of the first casing portion (33a) in a manner that is permanent, and to the first fastener portion (41) of the first casing portion (33a) in a manner that is releasable.

Abstract: A propulsive assembly including a turbine engine configured to be fastened to an aircraft by means of a suspension, having certain casing portions suitable for being decoupled so as to attenuate certain bending modes of the turbine engine in the event of an incident, the propulsive assembly comprising at least first and second casing portions (33a, 22) extending axially one after another, one of said casing portions being cantilevered out relative to said suspension, wherein a first casing portion (33a) possesses a first fastener portion (41) connected rigidly to the body (43) of the first casing portion (33a) and a second fastener portion (42) connected more flexibly to the body (43) of the first casing portion (33a), and wherein the second casing portion (22) is fastened to the second fastener portion (42) of the first casing portion (33a) in a manner that is permanent, and to the first fastener portion (41) of the first casing portion (33a) in a manner that is releasable.