This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Considerations in the Service Life Extension Program for the C-141 Aircraft
Annotation ability available
Sector:
Language:
English
Abstract
The C-141 aircraft have had a long and useful life in the inventory of the United States Air Force. The issues associated with the extension of the life of this aircraft is typical of the problems faced in the extension of the life of any aircraft. One of the main issues is the corrosion damage in the aircraft. Another of the main issues is widespread fatigue damage. The presence of either of these problems could be life limiting or, at least, incur a significant economic impact to correct the problem. It is the purpose of this paper to examine the life extension issues related to structural integrity for the C-141 aircraft.
Authors
Citation
Lincoln, J., "Considerations in the Service Life Extension Program for the C-141 Aircraft," SAE Technical Paper 941232, 1994, https://doi.org/10.4271/941232.Also In
References
- Negaard, Gordon R. “The History of the Aircraft Structural Integrity Program,” Aerospace Structures Information and Analysis Center (ASIAC), Report No. 680.1B 1980
- Department of the Air Force “Aircraft Structural Integrity Program, Airplane Requirements” Military Standard MIL-STD-1530A 1975
- Lincoln, J.W. “Damage Tolerance - USAF Experience,” Proceeding of the 13th Symposium of the International Committee on Aeronautical Fatigue” Pisa, Italy 1985
- Department of the Air Force “Airplane Damage Tolerance Requirements,” Military Specification MIL-A-83444 2 July 1974
- Lincoln, J. W. “Risk Assessments-USAF Experience,” Proceeding of the International Workshop on Structural Integrity of Aging Airplanes Atlanta, GA March 31 2 April 1992
- Lincoln, J.W. “Reassessment of the C-141 Structural Life,” Proceeding of the 16th Symposium of the International Committee on Aeronautical Fatigue Tokyo, Japan 1991