Abstract
Fatigue failures in operational aircraft thirty-six years ago motivated the United States Air Force to establish the USAF Aircraft Structural Integrity Program (ASIP). Since that time there have been many technical challenges encountered in the course of acquiring new aircraft that have changed ASIP from its original formulation, but not its original purpose of maintaining structural integrity. It is the purpose of this paper to discuss the basic concept of the USAF Aircraft Structural Integrity Program and some of the challenges it has faced while maintaining aircraft safety and minimizing the cost of structural maintenance of in-service aircraft.
Access this chapter
Tax calculation will be finalised at checkout
Purchases are for personal use only
Preview
Unable to display preview. Download preview PDF.
Similar content being viewed by others
References
Negaard, Gordon R., “The History of the Aircraft Structural Integrity Program,” Aerospace Structures Information and Analysis Center (ASIAC), Report No. 680. IB, 1980.
Lincoln, J.W., Damage Tolerance - USAF Experience, Proceeding of the 13th Symposium of the International Committee on Aeronautical Fatigue,” Pisa, Italy, 1985.
Pinckert, R.E., “Damage Tolerance Assessment of F-4 Aircraft,” AIAA Paper 76–904, Presented at the AIAA Aircraft Systems and Technology Conference, Dallas, Texas, 1976
Melliere, R. and Resnicky, J., “Dynamic Fatigue Testing of F-15 Vertical Tail to Simulate Buffet Environment,” WRDC-TR-90-4051, Proceedings of the 1989 USAF Structural Integrity Program Conference, San Antonio, Texas, 1990.
Colvin, J., “Stiffness Enhancement Using Bonded Skin Doublers Solved F-15 Vertical Tail Buffet Problem,” WL-TR-93-4080, Proceedings of the 1992 USAF Structural Integrity Program Conference, San Antonio, Texas, 1993.
Lincoln, J.W., Reassessment of the C-141 Structural Life, Proceedings of the 16th Symposium of the International Committee on Aeronautical Fatigue,” Tokyo, Japan, 1991.
Department of the Air Force, “Aircraft Structural Integrity Program, Airplane Requirements,” Military Standard MIL-STD-1530A, 1975.
Alford, R.E., Bell, R.P., Cochran, J.B. and Hammond, D.O., “C-141 WS 405 Risk Assessment,” WL-TR-92-4045, Proceedings of the 1991 USAF Structural Integrity Program Conference, San Antonio, Texas, 1992.
Lincoln, J.W., “Risk Assessments-USAF Experience,” Proceedings of the International Workshop on Structural Integrity of Aging Airplanes, Atlanta, GA, March 31 - 2 April 1992.
Elliott, W.R., Lincoln, J.W., and Register, D.C., Assessment and Terminating Action for Widespread Fatigue Damage in C-141 Wing Fuel Transfer Holes,Proceedings of the 18th Symposium of the International Committee on Aeronautical Fatigue, Melbourne, Australia, 1995.
Lincoln, J.W., Reassessment of the C-141 Structural Life, Proceedings of the 16th Symposium of the International Committee on Aeronautical Fatigue, Tokyo, Japan, 1991.
Coniog, D.O. and Lincoln, J.W., “Risk Assessment of the F-16 Wing,” WRDC-TR-894071, Proceedings of the 1988 USAF Structural Integrity Program Conference, San Antonio, Texas, 1989.
Babish, C.A., “F-16 Structural Integrity Program”, WL-TR-92-4045, Proceedings of the 1991 USAF Structural Integrity Program Conference, San Antonio, Texas, 1992.
Lincoln, J.W., Structural Technology Transition to New Aircraft, Proceedings of the 14th Symposium of the International Committee on Aeronautical Fatigue,” Ottawa, Ontario, Canada, 1987.
Author information
Authors and Affiliations
Editor information
Editors and Affiliations
Rights and permissions
Copyright information
© 1995 Springer-Verlag Berlin Heidelberg
About this paper
Cite this paper
Lincoln, J.W. (1995). Case Studies in Aircraft Structural Integrity. In: Batra, R.C. (eds) Contemporary Research in Engineering Science. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-80001-6_17
Download citation
DOI: https://doi.org/10.1007/978-3-642-80001-6_17
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-642-80003-0
Online ISBN: 978-3-642-80001-6
eBook Packages: Springer Book Archive