The purpose of the paper is to outline a method for determining in a single analysis the aircraft flight-path stability, the dynamic tail loads, and the flutter response of the system. This method treats the airplane itself as a servomechanism and is called the Transfer Function-Fourier (TFF) method. The T F F method is first explained in general, followed by simple examples to demonstrate the concept of the Transfer Function and the use of the Fourier technique in obtaining the transient response. Also included is a brief summary of the history leading to the development of the T F F method in the field of automatic control. Examples are then given to show the conventional application of this method to the dynamic stability analysis of simple feedback servomechanisms and automatic control systems. The paper then points out that, through extension of these fundamental concepts, an aeroelastic aircraft may be analyzed dynamically by treating it as a multiple loop servomechanism with aerodynamic and aeroelastic feedbacks. This allows many of the methods and tools that were developed years ago by the electrical-servomechanism engineers in their study of the dynamic stability of communication networks, feedback amplifiers, servomechanisms, and automatic control systems to be applied directly by the T F F method to the dynamic analysis of aeroelastic aircraft. The paper also points out that many of the analysis techniques recently developed in the study of the dynamics of aeroelastic aircraft by conventional methods, especially the matrix techniques developed in the field of flutter, may be applied to the dynamic analysis of systems for automatic control. Practical examples are then given to demonstrate the extension of the T F F method to the dynamic analysis of rigid-body and aeroelastic aircraft. These examples include: (a) A rigid-body longitudinal dynamic analysis of an airplane to determine the transient maneuvering tail loads developed by elevator displacements. (b) A longitudinal dynamic stability and performance analysis (and a limited flutter analysis) of an airplane equipped with a mechanical gust load alleviation system that is actuated by elastic wing deflection. (c) A longitudinal dynamic analysis of an airplane to determine by a single analysis: (1) the stability of the aircraft flight path, (2) the dynamic tail loads, and (3) the flutter response of the control system and the multielastic structure, where these responses result from arbitrary gust disturbances or control force inputs. (This more complete analysis includes the degrees of