For control system design purposes, desirable locations of short period and phugoid poles with their respective damping factors and natural frequencies are specified for fixed-wing aircraft in U.S. Department of Defense military specifications (MIL-SPEC) documents [1,2] and for heliocopters in aeronautical design standard (ADS)/MIL-SPEC documents [3-5]. In both cases, the control system designers can verify and demonstrate the validity of their design, in part by analytically verifying that the closed-loop system, when linearized about different trim conditions, possesses damping factors and natural frequencies that satisfy these requirements.