32 on a lug 26 of the turbine engine disc 10 the clip 32 is positioned on the disc 10 so that the radial lugs 42 44 extend along a rib 12 and towards the upstream side of the disc 10 the clip 32 is then translated downstream so that the u shaped 41 folds of the lateral tabs 36 38 fit on the longitudinal stops 30 of the radial lug 26 of the disc 10 the transverse wall 34 of the clip 32 coming to be applied against the upstream radial face of the radial lug 26 a fixing screw 46 is then inserted from the downstream side in the aligned orifices of the clip 32 the lug 26 and the annular flange 48 of the low pressure compressor rotor a fixing nut 50 is tightened on the upstream face of the clip 32 fig5 insertion of the clip 32 causes no change in the dimensions of the fixing screws 46 given the very small thickness of the transverse wall 34 which is around a few tenths of a millimeter it is desirable to size a clip 32 so that the radial tabs 42 44 are mounted with a radial clearance j with respect to a rib 12 on the disc 10 in order to compensate for the tolerances in the radial positioning of an orifice 28 on a radial lug 26 and thus guarantee in all circumstances an alignment of the orifice 40.