Abstract
The concept of SC-17M aircraft design was initiated to address the shortfalls on the DO-228 and Hawker Beechcraft King Air 350i aircraft. Until recently by using a standard specification, an SC-17M landing gear design has been carried out. Detailed study of sub-part C of the certification standard aided the application and determination of the necessary loads on the landing gear. The comprehensive design employed 300M steel as the best structural material to be used in the fabrication of the landing gear. The maximum bending moment in the shock absorber and wheel axle were calculated and validated with the use of Strand7 software in the model stress analysis. The reserve of strength calculated shows that the landing gear was able to withstand the applied loads without experiencing any failure.
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