An aircraft fuselage has at least one reinforcement frame (13), at least one crossbar (14) and at least one energy-absorbing structural element (2) that includes a compression beam (21) having a longitudinal axis Z and oriented substantially in the direction of compression forces to be absorbed upon an impact, the compression beam being attached at a first end (213) thereof to the crossbar (14) and at a second end (214) thereof to the reinforcement frame (13). The compression beam (21) is attached at least one of its ends (213, 214) via a shoulder bracket (22), wherein the shoulder bracket further has the function of cutting the compression beam (21) in case of an impact.
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