Abstract: Equipment for treating an annular component of an aircraft turbomachine includes a support of elongate shape along an axis. The support includes, at one of its ends, a mount configured to receive the component, which is intended to extend about the axis. A cover is configured to be mounted on the component and to cover an upstream end of this component. The cover includes an orifice oriented along the axis (X). A clamping member passes through the orifice and is configured to cooperate with the support and to fix the cover to the support. An annular masking gasket extends about the axis and is configured to be interposed between the mount and a downstream end of the component. The gasket has an annular groove configured to be a counter-form of the downstream end.