Abstract: Methods and systems for fastening components, including composite aircraft components, are disclosed. A method in accordance with one embodiment includes inserting an elongated member through at least one component (e.g., a first hole in a first component and a second hole in a second component). A collar is then swaged onto a helical groove of the elongated member, with the first and second components positioned between the collar and a head of the elongated member, and with the collar positioned between the second component and a removable portion of the elongated member. The removable portion is removed, for example, as an axial tensile force is applied to the elongated member during the swaging process.