Abstract : This report presents a generic first-principles helicopter trim analysis for use on a personal work station. Working from the helicopter's physical properties, it calculates the main rotor blade's collective, longitudinal cyclic, body pitch, and stabilator pitch angles to maintain a trimmed flight condition over a complete forward-speed range. The computer program automatically sweeps through a forward-speed range, varying the collective, longitudinal cyclic, and stabilator pitch angles to satisfy the trimmed condition. It is an improvement over earlier work where the analyst had to vary these parameters at the keyboard. It presents an example of the usage with an AH-64A helicopter, and the program's source code is included.