Abstract

This paper describes the Fatigue & Damage Tolerance Phase for the S19.1 Full Component Test of the A350 XWB Aircraft.   The aim of this test was to demonstrate that the fatigue phenomena does not occurs, as well as no crack growing on composite materials. A350XWB S19.1 Full Scale test is the first test developed on a S19.1 aircraft section, therefore, the process to carry out the test constitute an important step for the development of experimental models which allow for the better understanding of this kind of aircraft component. The process carried out to obtain relevant data for the CFRP F&DT test is described in this paper: Checking point of the structure selection. Specimen instrumentation. Spectra generation. Whiffletrees selection for structure load application. Load optimization for interfaces correlation.   The FCT results shown that the fatigue and damage tolerance Certification requirements are fulfilled.