Control and health management of modern aircraft turbine engines depends on sensing a wide variety of parameters throughout the engine, including temperatures, pressures, and vibration with different redundancy, reliability, and accuracy requirements. These parameters may be used as inputs to the various control systems as well as for monitoring the health performance status of various engine components. The different functions impose different requirements for the sensors. Control sensors demand proven extended reliability, accuracy, and response time that make them very expensive for turbine engine applications. On the other hand, engine health management sensors do not have such high reliability requirements and are often not redundant. This paper focuses on T48 EGT sensor design challenges towards its sizing driven by Conduction error elimination which poses geometrical limitations to sensor cross section ultimately effecting the creep characteristics when exposed to harsh engine operating environment. This paper discussed about the various creep mechanisms which are dependent on exhaust gas temperature and material’s microstructural properties. This paper also iterates probable way of overcoming these challenges with best suited existing solution.