<div class="htmlview paragraph">In multi-brake aircraft landing gear systems, it is common for brake rod bending to participate in brake squeal vibration modes. Experiments have proven that damping the bending mode of the rod can reduce brake vibration. A patented method of doing so with a simple, lightweight, split-tube insert for tubular brake rods is described. Equations for sizing the insert for a given interference pressure are presented, results of bench tests are summarized, and further development is discussed.</div>