A suspension arrangement for the casing shroud segments of the high-pressure turbine of a jet engine with inclination or graduation of the rotor blade tips (4) includes spaced apart attaching hooks (11) formed onto the casing shroud segments (2) which engage an axial retaining groove (13) on the turbine casing (1) on the upstream side and which are axially retained in the downstream direction by a retaining ring (14) arranged in a retaining ring groove (15) formed onto the turbine casing. In the retaining ring groove (15), assembly pockets (19) are provided on the downstream side, with the assembly pockets (19) agreeing with the distance and dimensioning of the attaching hooks (11), so that—with the rotor installed—axial travel (s2) of the casing shroud segments (2) is reduced and handling clearance is increased, when the casing shroud segments (2) are installed.