Hydrogen propulsion is an optimal choice for aerospace propulsion applications due to its exceptional properties of high power density and zero carbon emissions. In aerospace applications, hydrogen fuel is stored in a low-temperature liquid form and then heated to gaseous hydrogen through a heat transfer process before entering the combustion chamber to participate in combustion. Given the low temperature and high specific heat capacity of liquid hydrogen, the heat transfer process will involve a significant amount of heat consumption. This presents an opportunity to fully utilize the engine’s thermal cycle process to provide heat for liquid hydrogen. Based on the design concept of the liquid hydrogen heat exchanger for aviation hydrogen turbine engines, this study proposes an airworthiness-compliant design for the liquid hydrogen heat exchanger under the current airworthiness regulations. The findings of this study not only presented theoretical support for the airworthiness design of aviation hydrogen turbine engines with liquid hydrogen heat exchangers but also provided a valuable reference for the formulation of a special airworthiness certification condition policy for aviation hydrogen turbine engines.