Damage Tolerance Analysis on Repaired Fuselage Skin

Dibyo Legowo; I Wayan Susena; Sharudin Tambunan

doi:10.4028/www.scientific.net/KEM.306-308.265

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Model of Behavior of Materials with Delaminations under Hydrogen Embrittlement Conditions
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Damage Tolerance Analysis on Repaired Fuselage Skin
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HomeKey Engineering MaterialsKey Engineering Materials Vols. 306-308Damage Tolerance Analysis on Repaired Fuselage...

Damage Tolerance Analysis on Repaired Fuselage Skin

Abstract:

This paper discussed about the method used by operator to perform damage tolerance analysis for repaired fuselage skin. Skin damage may be caused by accidental damage or fatigue crack. Some element needed for damage tolerance analysis and the method to develop load spectrum will be discussed briefly. Therefore, this paper will describe a case study of damage tolerance analysis on repaired fuselage skin of narrow body jet aircraft.

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Periodical:

Key Engineering Materials (Volumes 306-308)

Pages:

265-270

DOI:

https://doi.org/10.4028/www.scientific.net/KEM.306-308.265

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Online since:

March 2006

Authors:

Dibyo Legowo, I Wayan Susena, Sharudin Tambunan

Keywords:

Damage Tolerance, Fuselage Skin, Repair

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References

[1] T. Swift, Repairs to Damage Tolerant Aircraft, International Symposium on Structural Integrity of Aging Airplanes, Atlanta, Georgia, (1990).

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[2] Repair Assessment Procedure and Integrated Design, Analysis Methods Document May 1998, www. tc. faa. gov/its/worldpac/techrpt/rapid. pdf.

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[3] D.P. Rooke and D.J. Cartwright: Compendium of Stress Intensity Factors (Her Majesty's Stationary Office, London, 1976).

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[2] [4] [6] [8] [10] [12] [14] [16] [18] [20] 0 20000 40000 60000 80000 100000 120000 140000 Flight number (N, cycle) crack length (inch) a critical = 15. 5 inch Ncritical=127096 a detectable = 13. 5 inch Ndetactable= 126482.

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10000 20000 30000 40000 50000 0 5 10 15 20 25 30 35 crack length (inch) residual strength (psi)yield stress = 45000 psi limit stress = 17867 psi.

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