Abstract: The present invention provides a method for controlling the thickness of composite laminates cured on closed angel tools. The invention utilizes a peel ply rather than a breather during the preparation for cure of laminate parts having a substantially uniform initial thickness. This method allows composite parts to be formed with greater uniformity and without the need for extra hardware. The composite part formed by the above method may find use in a wide variety of applications, including, for example, automotive and aerospace applications. Thus, for example, a composite part formed in accordance with the present invention is ideally suited for use as a shear tie in a commercial aircraft, which are used to secure the inner framework of the aircraft to the airplane skin.