A method for manufacturing an aircraft turbomachine casing, this casing comprising: - an annular envelope extending around an axis A and made of a composite material comprising fibres which are woven and embedded in a resin, - an annular layer of abradable material extending inside the envelope, and - support panels extending around the axis A and interposed between the envelope and the abradable layer, characterised in that it comprises the steps comprising: a) preparing a paste by mixing at least two components, b) depositing the paste on an internal annular surface of the panels, c) spreading the paste by means of at least one roll extending substantially parallel to the axis A and intended to roll on guide annulus arranged on either side of the panels or of the envelope, coaxially thereto, so as to form an angular sector of the abradable layer which extends over a predetermined angle about the axis A, d) forming a chamfer at a circumferential end of the sector thus formed, e) and repeating the steps a) to d) until a plurality of consecutive angular sectors of the abradable layer are formed and cover the entire internal surface of the panels, the sectors formed in the step e) each comprising a circumferential end covering the chamfered circumferential end of the previously deposited sector. - an annular envelope extending around an axis A and made of a composite material comprising fibres which are woven and embedded in a resin, - an annular layer of abradable material extending inside the envelope, and - support panels extending around the axis A and interposed between the envelope and the abradable layer, characterised in that it comprises the steps comprising: a) preparing a paste by mixing at least two components, b) depositing the paste on an internal annular surface of the panels, c) spreading the paste by means of at least one roll extending substantially parallel to the axis A and intended to roll on guide annulus arranged on either side of the panels or of the envelope, coaxially thereto, so as to form an angular sector of the abradable layer which extends over a predetermined angle about the axis A, d) forming a chamfer at a circumferential end of the sector thus formed, e) and repeating the steps a) to d) until a plurality of consecutive angular sectors of the abradable layer are formed and cover the entire internal surface of the panels, the sectors formed in the step e) each comprising a circumferential end covering the chamfered circumferential end of the previously deposited sector. a) preparing a paste by mixing at least two components, b) depositing the paste on an internal annular surface of the panels, c) spreading the paste by means of at least one roll extending substantially parallel to the axis A and intended to roll on guide annulus arranged on either side of the panels or of the envelope, coaxially thereto, so as to form an angular sector of the abradable layer which extends over a predetermined angle about the axis A, d) forming a chamfer at a circumferential end of the sector thus formed, e) and repeating the steps a) to d) until a plurality of consecutive angular sectors of the abradable layer are formed and cover the entire internal surface of the panels, the sectors formed in the step e) each comprising a circumferential end covering the chamfered circumferential end of the previously deposited sector.