ANALISIS KEKUATAN STRUKTUR EXTERNAL SKIN REPAIR AT STRINGER BETWEEN S-16L - S-18L FUSELAGE STATION 440 BOEING 737-400 MENGGUNAKAN SOFTWARE CATIA V5R20

PURNOMO AJI, ARI (2018) ANALISIS KEKUATAN STRUKTUR EXTERNAL SKIN REPAIR AT STRINGER BETWEEN S-16L - S-18L FUSELAGE STATION 440 BOEING 737-400 MENGGUNAKAN SOFTWARE CATIA V5R20. Skripsi thesis, Institut Teknologi Dirgantara Adisutjipto.

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Abstract

Fuselage is a structure on an aircraft as a place for passengers, goods, wings, vertical and horizontal tails, and powerplant. The effect of loads on the fuselage design can be generated from flight maneuvers, landing, take-off or ground handling conditions. One of the most influential loads on the fuselage is cabin pressure. In continuous aircraft operation, cabin pressure can cause damage in the form of cracks in the fuselage. To handle cases of cracks, a repair process must be carried out. In the repair process, the maximum stress value and margin of safety on the repaired structure will be analyzed. In this study, the modeling was taken from the SRM (Structural Repair Manual) on Repair 35 with a crack model using Detail IV. Modeling and analysis of the repair structure using the help of CATIA V5R20 software. The model is given internal pressure and tension load in the Z and Y directions. The maximum stress that occurs in the repair structure 35 detail IV which is subject to internal pressure and tension load is 16655.6 Psi which is located on the frame structure, with a margin of safety value of 2.902. The lowest margin of safety obtained from the analysis was 1.139 for the BACR15BB6AD fastener.

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