H.-J. Schmidt, B. Brandecker

Modern commercial transport aircraft with MTOW greater than 7.5to have to be certified with respect to the damage tolerance requirements as specified by FAR 25 Amendment 45 and JAR 25.571. Details of fatigue and damage tolerance requirements and their interpretation as well as methods of substantiation for development and certification are presented. The essential aspects of major full scale fatigue and damage tolerance tests for metallic structure are described using the AIRBUS A320 example. Especially details about test philosophy, test load program, test execution.and supporting coupon testing are given, which comprises more than 15 years experience of fatigue and damage tolerance testing for metallic structure of AIRBUS INDUSTRIE aircraft and the results of numerous discussions with European and other airworthiness authorities. Specific aspects of regional aircraft full scale testing are discussed with respect to definition of test specimen, test speed, simplification of test spectrum and justification of repairs.

European Forum: The Evolution of Regional Aircraft Technologies and Certification

Conference Paper

englisch

21,0 x 29,7 cm, 9 Seiten

DGLR-Bericht, 1989, 1989-02, European Forum: The Evolution of Regional Aircraft Technologies and Certification; S.147-155; 1989; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

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Bestellbar

1989