Evaluation of no growth limit is crucial in damage tolerance assessment of aircraft composite structures. The fatigue tests and analyses for determining the no growth limit must demonstrate adherence to the “no-damage growth” concept, ensuring no initiation of new damage or growth of existing damage occurs. Factors such as the material composition, geometry, and method of adhesion/joining significantly influence the no growth limit of composite structures. The traditional approach used in determining the no growth limit is through stress life (SN) approach, which is time consuming and resource intensive. The current work aims to assess the no growth limit of carbon-fiber reinforced polymer (CFRP) composite specimens using infrared thermography (IRT), a rapid fatigue characterization methodology requiring fewer samples in comparison with traditional SN approach. Variations in geometry, including the introduction of notches and holes in the specimen, have been examined by quantifying their impact on the no growth limit. Furthermore, the study aims to assess the change in no growth limit when specimens are subjected to barely visible impact damage (BVID) prior to testing. The effectiveness of the IRT methodology in evaluating the no growth limit across different geometric configurations, including mechanically fastened specimens, is discussed.