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Evaluation of the concept of pressure proof testing fuselage structuresThe 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.
Document ID
19910017841
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Harris, Charles E. (NASA Langley Research Center Hampton, VA, United States)
Orringer, Oscar (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1991
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
DOT/FAA/CT-TN91/31
Accession Number
91N27155
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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