Titlebook: Structural Integrity of Aging Airplanes; S. N. Atluri (J. C. Hunsaker Visiting Professor),S Conference proceedings 1991 Springer-Verlag Be

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An Evaluation of the Pressure Proof Test Concept for 2024-T3 Aluminium Alloy Sheet,ack length that is slightly less than the critical value at the maximum proof stress, the minimum assured life or proof test interval must be no more than 550 pressure cycles for a 1.33 proof factor and 1530 pressure cycles for a 1.5 proof factor to prevent in-flight failures.

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NASA Airframe Structural Integrity Program,etect disbonds at riveted lap splice joints has been conducted. All long-term program elements have been initiated and the plans for the methodology verification program are being coordinated with the airframe manufacturers.

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Conference proceedings 1991ars or so. A large number of these jet airplanes is currently operating at or beyond their designed fatigue lives. Thus, the structural integrity of these aging airplanes has become an issue of major concern to all nations of the world. To bring the needed technical and research focus on the issues

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The Civil Damage Tolerance Requirements in Theory and Practice,developed and ageing aircraft. Some improvements to the DTR are suggested. In principle, fracture control of aircraft is ensured by non-destructive inspection, although destructive inspection has been suggested for certain ageing aircraft, as will be discussed briefly as well.

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The Effect of Exfoliation Corrosion on the Fatigue Behavior of Structural Aluminium Alloys, rate in both as received and prior corroded material is measured in both wet and dry environments. The exfoliation corrosion is shown to enhance the fatigue crack growth rate in the 7178-T6 material whereas the same effect was not observed in 2024-T351.