Abstract: Techniques for testing a component for compatibility with a depressurization profile associated with a launch vehicle payload fairing during ascent are disclosed. A pressure of air or other gas within a pressure vessel containing the component is raised to a first value substantially higher than one atmosphere absolute pressure. The air/gas pressure within the pressure vessel is lowered, by venting into the ambient atmosphere, at a rate simulating or demonstrating margin with respect to the launch vehicle payload fairing depressurization profile. The component is inspected for damage. The component may be a panel including a honeycomb core sandwiched between two faceskins, the panel having a planar area in excess of twenty five square feet.