Analisis Pengujian Metode Liquid Penetran Testing Bedasarkan Acceptance Criteria Penetrant Testing Pada Komponen Cessna 152

Abstract

The Cessna 152 is a light, single-engine aircraft that is widely used for flight training. The structure of the aircraft must be able to withstand various stresses that occur due to forces when the aircraft is flying. One area that has the potential to experience a decrease in strength is the landing gear and propeller hub. This decrease in strength can cause cracks to occur in that part. Therefore, detecting defects in aircraft structures is very crucial. Liquid penetrant testing is a method for finding cracks utilizing capillarity on the test surface so that cracks can be seen. The criteria limits for defects that arise can be determined using the ASME acceptance criteria penetrant testing. The aim of this research is to determine the indications and criteria limits for defects that arise in the landing gear axle and propeller hub using liquid penetrant testing referring to ASME standards. The method used is quantitative with a test design, namely the test results present quantitative data from liquid penetrant testing on the component being tested. It is known that the research results show that the main landing gear axle component has 2 linear defects (cracks) whose size is outside the existing limits according to the rejected criteria and the propeller hub has 2 linear defects (cracks) and a rounded defect (pin hole) whose size is outside the existing limits so it is stated also rejected. In accordance with ASME standards, defects obtained are rejected, but are relevant but must be carried out maintenance.