Abstract: An automated system is disclosed for rapidly inspecting a complete aircraft and detecting cracks in the airframe. For inspecting the aircraft fuselage, the system incorporates a framework disposed over the fuselage and extending along a major portion of the length of the fuselage. Beams having suction devices and acoustic sensors are movably attached to the framework and are moved into a position adjacent to the outer surface of the fuselage when the aircraft has been located within the framework. The suction devices attach the beams to the fuselage surface along fuselage panel joints or other areas to be inspected. Several acoustic sensors, located on each beam, are connected to a device for analyzing and recording or visually displaying the signals generated by the sensors upon the detection of noise generated by the formation or propagation of cracks.