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The marman interface is widely used in space applications to fit the spacecrafts to the launch vehicle and it is the same interface that allows the integration, test and transport of the satellites (AIT). It is usually designed for launch loads with related flight design safety factors and margins, but this is not always compatible with the handling and transport environment. In particular some criticalities are evidenced during the transport of satellites, where they are mounted in the container in horizontal position therefore subjected to bending loads due to gravity and transport dynamic loads. The study deals with a finite element analysis approach in the calculation and verification of marman clamp bands used for spacecraft AIT operations. The paper describes the details of modeling of the clamp band parts, the involved spacecraft launch vehicle interface ring and the MGSE interface.