One of the major challenges in the development of avionics is the requirement to assure their reliable functionality while subjected to the actual operating conditions which are static and dynamic in nature. Of particular interest to the developments presented in this paper are the dynamic loading conditions. Because the avionics have certain mass and elasticity, they respond to the loads encountered during operation with a specific vibration behavior. Therefore, development of reliable avionics packages depends upon our ability to determine the dynamic characteristics which define and control their vibration behavior, particularly as it relates to the dynamic environment within an aircraft which is a major contributor to the failure of airborne avionic systems. In this paper, computational and experimental hybrid methodolgy is used to quantitatively study the vibration characteristics of avionics. The computational methodology is based on the finite element method. The experimental methodology is based on the electro-optic holography method, which allows direct electro- optic recording, processing, and display of the laser holograms at the rate of 30 holograms per second, making it capable of producing quantitative data in nearly real-time. Using the electro- optic holography method, displacement magnitudes in the submicron range are measured noninvasively over the full field of view, as a function of the resonance frequencies. Although some of the experimentally observed mode shapes were not predicted using the computational model employed in this study, the correlation between the results obtained using the finite element and the electro-optic holography methods was otherwise good and the agreement between the corresponding resonance frequencies was within 2%.