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Fatigue Analyses of Riveted Lap-Splice Joints in a Narrow-Body Aircraft

  • J. C. NewmanJr.
  • R. Ramakrishnan
Conference paper

Abstract

The U.S. Federal Aviation Administration and Delta Air Lines had teamed to conduct a destructive evaluation of a retired narrow-body passenger aircraft that had nearly 60,000 flights. Some of the program objectives were to characterize the state of damage at riveted lap-joint fastener holes in the fuselage of an aircraft at the design service goal; and to develop or verify analysis methods that can correlate and predict the state of cracking at any point in time.

The crack-growth model, FASTRAN, was used to evaluate Elber’s effective stress-intensity-factor range in terms of crack-tip cyclic hysteresis energies and was found to correctly partition energies associated with crack-tip damage. The model was used to correlate constant-amplitude fatigue-crack-growth-rate data over a wide range in rates and stress ratios (minimum to maximum applied stress) from threshold to near fracture conditions. The model was then used to calculate fatigue lives using small-crack theory and/or crack growth in open-hole laboratory specimens, fastener-loaded holes in curved test panels cut from the aircraft fuselage, and fastener-loaded holes in acutal fuselage lap joints from the retired aircraft made of thin-sheet 2024-T3 aluminum alloy. Equivalent-initial-flaw sizes (EIFS) were established for the laboratory specimens and for the fuselage lap joints that had been subjected to actual service loads and environments. Calculated fatigue lives for the laboratory specimens agree well with test data; and the calculated crack length against flight pressure cycles for the narrow-body aircraft fuselage were quite similar to the results found from fractographic examinations.

In this paper, the terms fatigue life and crack-growth life are used synonymously since all fatigue-life calculations were performed using the FASTRAN crack-growth methodology with the EIFS concept and formulations based on small-crack theory.

Keywords

Federal Aviation Administration Corner Crack Fastener Hole Aircraft Fuselage Rivet Hole 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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References

  1. 1.
    Steadman, D., Bakuckas Jr., J. G.: DOT/FAA/AR-07/22, V1 (2007)Google Scholar
  2. 2.
    Ramakrishnan, R., Jury, D.: DOT/FAA/AR-07/22, V2 (2007)Google Scholar
  3. 3.
    Mosinyi, B., Bakuckas Jr., J. G., Steadman, D.: DOT/FAA/AR-07/22, V4 (2007)Google Scholar
  4. 4.
    Ramakrishnan, R., Steadman, D., Carter, A.: In: Proc. Int. Fatigue Congress, Atlanta, GA (2006)Google Scholar
  5. 5.
    Jury, D., Ramakrishnan, R., Carter, A.: In: Proc. Int. Fatigue Congress, Atlanta, GA (2006)Google Scholar
  6. 6.
    Ramakrishnan, R., Steadman, D.: In: Proc. Int. Fatigue Congress, Atlanta, GA (2006)Google Scholar
  7. 7.
    Bakuckas Jr., J. G.: DOT/FAA/AR-01/46 (2002)Google Scholar
  8. 8.
    Newman Jr., J. C.: NASA TM 104159 (1992)Google Scholar
  9. 9.
    Newman Jr., J. C.: In: AGARD CP 328, pp. 6.1–6.26 (1983)Google Scholar
  10. 10.
    Elber, W.: ASTM STP 486, pp. 230–242 (1971)Google Scholar
  11. 11.
    Harter, J.: AFGROW Users Guide, Version 4.0005.12.10. Wright-Patterson Air Force Base, OH (2002) Google Scholar
  12. 12.
    Newman Jr., J.C., Raju, I.S.: In: Atluri, S.N. (ed.) Computational Methods in the Mechanics of Fracture, vol. 2, pp. 311–334 (1986)Google Scholar
  13. 13.
    Newman Jr., J.C., Harris, C.E., James, M.A., Shivakumar, K.N.: Fatigue in New and Aging Aircraft. In: Cook, R., Poole, P. (eds.) Proceedings of the 19st ICAF Symposium, vol. I, pp. 523–539. EMAS Publishing, UK (1997)Google Scholar
  14. 14.
    Newman Jr., J. C., Steadman, D., Ramakrishnan, R.: submitted to Int. J. Fatigue (2010)Google Scholar
  15. 15.
    Hartman, A., Schijve, J.: NLR TR 69116 U, National Aerospace Laboratory (1969)Google Scholar
  16. 16.
    Paris, P.C., Gomez, M.P., Anderson, W.E.: Trend Engng. 13(1), 9–14 (1961)Google Scholar
  17. 17.
    Tomkins, B.: Phil. Magazine 18, 1041–1066 (1968)CrossRefGoogle Scholar
  18. 18.
    Bilby, B.A., Cottrell, A.H., Swinden, K.H.: Proc. Royal Society,  272(A), 304 (1963)Google Scholar
  19. 19.
    Dugdale, D.S.: J. Mech. Phys. Solids 8, 100–104 (1960)CrossRefGoogle Scholar
  20. 20.
    Schijve, J., Jacobs, F.A., Tromp, P.J.: NLR-TR 68117 U, National Aerospace Laboratory (1968)Google Scholar
  21. 21.
    Newman Jr., J.C.: Int. J. Fract. 24, 131–135 (1984)CrossRefGoogle Scholar
  22. 22.
    Newman Jr., J. C.: In: Fatigue of Aircraft Materials, Delft University Press, pp. 83-109 (1992)Google Scholar
  23. 23.
    Newman Jr., J., Edwards, P.: (eds.), Short-Crack Growth Behaviour in an Aluminum Alloy. AGARD R-732 (1988)Google Scholar
  24. 24.
    Landers, C.B., Hardrath, H.F.: NACA TN 3631 (1956)Google Scholar
  25. 25.
    Laz, P.J., Hillberry, B.M.: In: Lutjering, G., Nowack, H. (eds.) Fatigue Berlin, Germany, vol. 96, pp. 1293–1298 (1996)Google Scholar
  26. 26.
    Mosinyi, B., Bakuckas, J., Steadman, D., Awerbuch, J., Lau, A., Tan, T.: In: Ninth Joint FAA/DoD/NASA Aging Aircraft Conf., Atlanta, GA (2006)Google Scholar
  27. 27.
    de Rijck, J.J.M., Fawaz, S.: In: Fourth Joint DoD/FAA/NASA Aging Aircraft Conf., St. Louis, MO (2000)Google Scholar
  28. 28.
    Fawaz, S.A.: AFRL-VA-WP-TR-2000-3024 (2000)Google Scholar
  29. 29.
    Aircraft Accident Report—Aloha Airlines, Flight 243, Boeing 737-200, National Transportation Safety Board, NTSB/AAR-89/03 (1989)Google Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2011

Authors and Affiliations

  • J. C. NewmanJr.
    • 1
  • R. Ramakrishnan
    • 2
  1. 1.Mississippi State UniversityUSA
  2. 2.Delta Air Lines Inc.AtlantaUSA

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