<div class="htmlview paragraph">A general method for analyzing static, longitudinal, stick-free, and stick-fixed stability is presented. The method allows for analysis of several configurations and effects of power on the stability of the airplane. A single matrix equation is used in which the total airplane lift, drag, pitching moment, and downwash are used to obtain the airplane stability.</div> <div class="htmlview paragraph">The equations include the effects of auxiliary control devices generally used on general aviation aircraft such as downspring, bobweight, geared tab, and nonlinearities of control surface gearing.</div>