Abstract: A process and apparatus for producing perforated composite structures, such as acoustic skins suitable for aircraft engine nacelle components. The process includes placing at least one mat member, a non-impregnated fabric member, and a pad member on a tool surface so that pins disposed on the mat member project through the fabric member to define holes therein, the fabric member is between the mat and pad members, and the mat, fabric and pad members yield a non-impregnated stack that conforms to the tool surface. The fabric member is then infused with a resin to yield a resin-impregnated fabric and the resin within the resin-impregnated fabric is partially cured, after which the partially-cured resin-impregnated fabric is removed from the tool surface and from between the mat and pad members. A post cure of the partially-cured resin-impregnated fabric can then be performed to yield the composite structure with the holes.