13th International Conference on Fracture June 16–21, 2013, Beijing, China -8- of life deregulation for the fatigue critical component is analysed with the calendar parking time prolonging. ⑵ According to the test results, the change rule that the shape parameter changed with the parking time is calculated by the dynamic S-N curve; the calculating model for deregulation rule of the fatigue life has been established for the fatigue critical component. The error between the predicted calendar life and the actual value is about 7.32%. ⑶ The rule that the DFR changes with the parking time is gained and the error between the theoretical calendar life and the actual value is about 4.04%. References [1] Liu Wenting, Li Yuhai. Aircraft Component Calendar Life Evolution Technology. Beijing: Aeronautic Industry Press, 2004 (in Chinese). [2] Zhang Dong. Accelerated Corrosive Test of the Aircraft Component Under Equivalent Environment Spectrum and the Computing Method for the Calendar Life[J]. ACTA AERONAUTICA ET ASTRONAUTICA SINCA, 2000，21(3): 196-201 (in Chinese). [3] Yang Xiaohua, Yao Weixing, Chen Yueliang. Research calendar life of aircraft component considering the effects of calendar environment[J]. Chinese Journal of Applied Mechanics, 2002,19（3）：157-159 (in Chinese). [4] Wang Bintuan, Yang Qingxiong. S-N Curves for LC4CS Aluminum Alloy and 30CrMnSiNi2A Steel Pre-corroded in Atmospheric Environment[J]. Journal of Mechanical Strength, 2000, 22 (3): 222-227 (in Chinese). [5] Cui Changjing, Chen Qunzhi, Wang Yuya. Corrosive Behavior of LY12CZ Aluminum Alloy in a Laboratory Simulated Atmospheric Environment of One Airport[J]. Corrosive Science and Projection Technology, 2009, 21（3）: 291-294 (in Chinese). [6] M.R.Sriaman, R.M.Pidapati. Life Prediction of Aircraft Aluminum Subjected to Pitting Corrosive under Fatigue Condition[J]. Journal of Aircraft，2009，46(4)：1253-1259. [7] S.Ishihara, S.Saka, Z.Y.Nan et al. Prediction of corrosive fatigue lives of aluminium alloy on the basis of corrosive pit growth law[J]. Fatigue Fracture Engineering Materials Component，2006， 29：472-480. [8] Frederic Menan, Gilbert Henaff. Synergistic Action of Fatigue and Corrosive during Crack Growth in the 2024 Aluminium Alloy[J]. Procedia Engineering, 2010,2: 1441-1450. [9] He Xiaofan, Liu Wenting, Jiang Dongbin. Method for Fatigue Test of Aircraft Components Considering Corrosive Influence. Journal of Beijing University of Aeronautics and Astronautics, 2003,1(29): 20-22 (in Chinese). [10] Yang Xiao-hua, Yao Wei-xing, Chen Yue-liang. Research on Mechanical Properties of LY12CZ Aluminum Alloy under Calendar Corrosive Environment[J]. Journal of Mechanical Strength， 2003，25（2）：227-228 (in Chinese). [11] Wu Xueren. Handbook of aircraft structural metal material mechanics performance. Beijing: Aeronautic Industry Press, 1996.
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