A method for non-destructive evaluation of an aerospace component that is formed using direct metal laser sintering, DMLS, comprising: forming the aerospace component using a DMLS manufacturing process; stress relieving the aerospace component after forming the aerospace component using the DMLS manufacturing process; aluminide encapsulating the aerospace component after stress relieving the aerospace component; hot isostatic pressing the aerospace component after aluminide encapsulating the aerospace component, wherein hot isostatic pressing the aerospace component eliminates porosity in the aerospace component; after hot isostatic pressing the aerospace component, identifying a region of interest on the aerospace component; after identifying the region of interest, positioning a plurality of acoustic sensors (111, 112, 113) in the region of interest; after positioning the plurality of acoustic sensors, inducing a vibration in the region of interest using the plurality of sensors and receiving a resonance frequency spectra using the plurality of sensors; comparing the received resonance frequency spectra against a reference spectra to determine whether the hot isostatic pressing has successfully eliminated porosity in the aerospace component, wherein the step of comparing comprises identifying a frequency of a peak in the received resonance frequency spectra; if the step of comparing indicates that hot isostatic pressing has not successfully eliminated porosity in the aerospace component, then rejecting the aerospace component; if the step of comparing indicates that hot isostatic pressing has successfully eliminated porosity in the aerospace component, then: solutioning the aerospace component and ageing the aerospace component. forming the aerospace component using a DMLS manufacturing process; stress relieving the aerospace component after forming the aerospace component using the DMLS manufacturing process; aluminide encapsulating the aerospace component after stress relieving the aerospace component; hot isostatic pressing the aerospace component after aluminide encapsulating the aerospace component, wherein hot isostatic pressing the aerospace component eliminates porosity in the aerospace component; after hot isostatic pressing the aerospace component, identifying a region of interest on the aerospace component; after identifying the region of interest, positioning a plurality of acoustic sensors (111, 112, 113) in the region of interest; after positioning the plurality of acoustic sensors, inducing a vibration in the region of interest using the plurality of sensors and receiving a resonance frequency spectra using the plurality of sensors; comparing the received resonance frequency spectra against a reference spectra to determine whether the hot isostatic pressing has successfully eliminated porosity in the aerospace component, wherein the step of comparing comprises identifying a frequency of a peak in the received resonance frequency spectra; if the step of comparing indicates that hot isostatic pressing has not successfully eliminated porosity in the aerospace component, then rejecting the aerospace component; if the step of comparing indicates that hot isostatic pressing has successfully eliminated porosity in the aerospace component, then: solutioning the aerospace component and ageing the aerospace component.