Unducted fan for an aircraft turbine engine

An unducted fan for an aircraft turbine engine, comprising:

• a propeller comprising a hub and an annular array of blades extending substantially radially outwards from said hub, the hub comprising an annular array of cowls, each of the cowls being mounted between radially inner ends of adjacent blades and suitable for being fixed to an upstream collar and to a downstream collar of the hub,
• wherein at least one cowl comprises, at a circumferential end, at least one joint edge which is contiguous with a complementary joint edge of an adjacent cowl,
• wherein said at least one cowl and at least one of said upstream and downstream collars are configured so that the at least one cowl can be mounted and dismounted by a movement including pivoting about an initial pivot axis which is circumferentially offset from said at least one joint edge towards a center of the at least one cowl, and so that, during said pivoting, said at least one joint edge moves radially inward from said complementary joint edge, and
• wherein said initial pivot axis passes substantially through at least one pivot region of contact between the at least one cowl and at least one of the upstream collar and the downstream collar of the hub.