Federal Aviation Administration Advisory Circular 33.70-2 Calibration Test Using DARWIN Part II

Abstract

<p>The Federal Aviation Administration (FAA) Advisory Circular (AC) 33.70-2 provides a calibration test case as a means for the FAA to assess a contractor's capability to perform analyticallifing procedures. The calibration test was conducted using the probabilistic risk analysis program Design Assessment of Reliability With INspection (DARWIN). An overview of DARWIN is presented. The required maximum stress field condition was determined by Jace Carter using the ABAQUS finite element code in part-one of this presentation. The circular states that the probability of failure (PDF) of the bolt hole feature of a rotating titanium ring is governed by the single most life limiting crack location. A sensitivity analysis was conducted using DARWIN to determine this crack location. The maximum fracture toughness and crack area at failure were also determined. The probability of failure was calculated for both with and without component inspection. In both cases the results were found to be within the acceptable ranges as defined in the AC. The loading profile specified in the AC is a simplistic singular zero to maximum load cycle representing a single main mission cycle. In addition, more realistic loading profiles contain a series of sub-and main-cycles, i.e., TURBISTAN is a loading sequence standard for fighter aircraft that was derived from the rotation per minute sequences of fighter engines. The TURBISTAN navigation mission type, which are characterized by long cruises are representative of the loading of a typical passenger planes which must meet FAA standards. The AC calibration test case was analyzed using the TURBISTAN navigation loading profiles and the results are discussed.</p><p>This presentation occurred at the Wright State University Campus-Wide Celebration of Research, Scholarship and Creative Activities on April 16, 2010</p>