Aging aircraft structures are inevitably exposed to environment for a long time facing many potential problems, including corrosion and wide spread fatigue damage, which in turn cause the degradation of flight safety. In this study, the environmental surface damages on aging aircraft structures induced during service were quantitatively analyzed. Additionally, S-N fatigue tests were performed with center hole specimens extracted from aging aircraft structures. From the results of quantitative analyses of the surface damages and fatigue tests, it is concluded that corrosion pits initiated during service reduce the fatigue life significantly. Finally, using the fracture mechanics and the EIFS (equivalent initial flaw size) concepts, the remaining fatigue life was predicted based on actual fatigue test results.

1. 서 론
 2. 실험 방법
 3. 결과 및 고찰
 4. 결 론
 Acknowledgement
 References

• 이은경(한국항공우주산업 기체해석팀) | Eungyeong Lee
• 정유인(한국항공우주산업 기체설) | Yooin Jeong
• 김상식(경상대학교 금속재료공학과) | Sangshik Kim Corresponding author