Resonance inspection system and method for using same

A method for identifying a presence or an absence of a structural mode of a component for an aircraft propulsion system with a resonance inspection system, the method comprising:

• inserting a probe assembly of the resonance inspection system into the aircraft propulsion system to position a probe of the probe assembly contacting the component at a single point-of-contact, the probe includes at least one piezoelectric transducer including a sense piezo and a drive piezo;
• controlling the drive piezo, with a control assembly of the resonance inspection system, to apply a vibration to the component;
• measuring a vibratory response signature of the component with the sense piezo;
• generating, with the control assembly, a plurality of different resonance spectra waveforms for a portion of a frequency range of the vibratory response signature, the plurality of different resonance spectra waveforms including a first resonance spectra waveform and a second resonance spectra waveform, and the first resonance spectra waveform is different than the second resonance spectra waveform;
• detrending, with the control assembly, the first resonance spectra waveform and the second resonance spectra waveform;
• and
• identifying a presence or an absence of a structural mode of the component using the first resonance spectra waveform and the second resonance spectra waveform, the presence of the structural mode is identified by determining the first resonance spectra waveform includes a maximum slope point at a first frequency of the portion of the frequency range, the second resonance spectra waveform includes a second peak at a second frequency of the portion of the frequency range, and the first frequency and the second frequency are within a predetermined frequency range threshold.