This paper presents an overview of the STABLE microgravity isolation system developed and successfully flight-tested in October 1995. A description of the hardware design and operational principles is given. Samples of measured flight data are presented, including an evaluation of attenuation performance provided by the actively controlled electromagnetic isolation system. Preliminary analyses show that the acceleration environment aboard STABLE's isolated platform was attenuated by a factor of more than 25 between 0.1 and 100 Hz. STABLE was developed under a cooperative agreement between National Aeronautic and Space Administration, Marshall Space Flight Center, and McDonnell Douglas Aerospace. The flight hardware was designed, fabricated, integrated, tested, and delivered for launch during a five month period.