DAMAGE TOLERANCE ANALYSIS FOR MULTIPLE SITE DAMAGE LAP JOINT FUSELAGE CN 235 WITH PROBABILISTIC METHOD

• Main Author: EDY PRASETYO (NIM : 23607025); Pembimbing 1 : Prof. Dr. Ichsan Setya Putra; Pembimbing 2 : Dr, EKO
• Format: Theses
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/15513
• Institution: Institut Teknologi Bandung

The background of this research are Federation Aviation <br /> <br /> <br /> <br /> Administration (FAA) regulations and Pengoperasian Pesawat Udara (DKU-PPU) about aircraft aging that must to follow in aircraft aging program for continuing airworthiness certificate. Aging Aircraft program cover program to enhancement all aircraft equipment like avionic equipment and other modern equipment and also to recalculate damage tolerance for aging aircraft especially for Multiple <br /> <br /> <br /> <br /> Site Damage (MSD) cases. MSD is crack that spread because of interaction of neighboring cracks. These cases will affect the quickly catastrophic failure and crack growth of MSD must be known. <br /> <br /> <br /> <br /> In this research, damage tolerance analysis for MSD cases with probabilistic method used to nine inline neighboring rivet holes with several possible crack initiations scenario. Several possible crack initiations scenario can be caused by stress distribution on each hole, hole quality, material quality around the hole and hole and geometry of the hole. This research will provide four cases initiation crack configuration, from two holes initiation to four holes initiation in the center of structure and spread to edge. <br /> <br /> <br /> <br /> Probabilistic with montecarlo used in this research. This method use random value with normal distribution to influence material properties of the structure. The next step, result of the calculation will be iterated a thousand times and the average of all iteration calculation will be the final result of all calculation. It also conducted a random process of load to calculate &#916;Keff value as one of input to find residual strength and crack growth value. <br /> <br /> <br /> <br /> All of process will result critical age from a structure base of rapid crack growth and residual strength analysis. For four configuration that have planned before, minimum average age is 855,000 cycle and maximum average age 2,760,000 cycle. <br /> <br /> <br /> <br /> These research result are expected to be used to predict crack growth of lap joint structure of CN 235 so it can be used to make aging aircraft program. Other than that the result of this research can be complement and be used as a comparison in the calculation of damage tolerance calculation with other method.