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  • AIRCRAFT DESIGN, TESTING AND PERFORMANCE  (2)
  • AIR TRANSPORTATION AND SAFETY  (1)
  • 1
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    Recent fracture mechanics results from NASA research related to the aging commercial transport fleet (1991)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: NASA is conducting the Airframe Structural Integrity Program in support of the aging commercial transport fleet. This interdisciplinary program is being worked in cooperation with the U.S. airframe manufacturers, airline operators, and the FAA. Advanced analysis methods are under development to predict the fatigue crack growth in complex built-up shell structures. Innovative nondestructive examination technologies are also under development to provide large area inspection capability to detect corrosion, disbonds, and fatigue cracks. Recent fracture mechanics results applicable to predicting the growth of cracks initiating at the rivets of fuselage splice joints are reviewed.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AGARD, Fatigue Management; 6 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Evaluation of the concept of pressure proof testing fuselage structures (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The FAA and NASA have recently completed independent technical evaluations of the concept of pressure proof testing the fuselage of commercial transport airplanes. The results of these evaluations are summarized. The objectives of the evaluations were to establish the potential benefit of the pressure proof test, to quantify the most desirable proof test pressure, and to quantify the required proof test interval. The focus of the evaluations was on multiple-site cracks extending from adjacent rivet holes of a typical fuselage longitudinal lap splice joint. The FAA and NASA do not support pressure proof testing the fuselage of aging commercial transport aircraft. The argument against proof testing is as follows: (1) a single proof test does not insure an indefinite life; therefore, the proof test must be repeated at regular intervals; (2) for a proof factor of 1.33, the required proof test interval must be below 300 flights to account for uncertainties in the evaluation; (3) conducting the proof test at a proof factor of 1.5 would considerably exceed the fuselage design limit load; therefore, it is not consistent with accepted safe practices; and (4) better safety can be assured by implementing enhanced nondestructive inspection requirements, and adequate reliability can be achieved by an inspection interval several times longer than the proof test interval.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: DOT/FAA/CT-TN91/31
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    FAA/NASA International Symposium on Advanced Structural Integrity Methods for Airframe Durability and Damage Tolerance, part 2 (1994)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The international technical experts in the areas of durability and damage tolerance of metallic airframe structures were assembled to present and discuss recent research findings and the development of advanced design and analysis methods, structural concepts, and advanced materials. The principal focus of the symposium was on the dissemination of new knowledge and the peer-review of progress on the development of advanced methodologies. Papers were presented on the following topics: structural concepts for enhanced durability, damage tolerance, and maintainability; new metallic alloys and processing technology; fatigue crack initiation and small crack effects; fatigue crack growth models; fracture mechanics failure criteria for ductile materials; structural mechanics methodology for residual strength and life prediction; development of flight load spectra for design and testing; and corrosion resistance.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA-CP-3274-PT-2 , L-17432-PT-2 , NAS 1.55:3274-PT-2 , May 04, 1994 - May 06, 1994; Hampton, VA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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