A comprehensive Finite Element Model (FEM) of the F-16 Fighting Falcon is developed, emphasizing the inclusion of the fuselage and empennage in response to Ground Vibration Test (GVT) data. The GVT, which provides the first in-depth insight into an aircraft's dynamic behavior, is instrumental in validating and refining the FEM created during the development phase. Post-GVT, the model’s eigenfrequencies and mode shapes are analyzed, and the FE model is iteratively updated to ensure it accurately represents the dynamic characteristics of the test aircraft. Unlike previous studies that primarily focused on the aircraft's wings, this work extends the FEM to encompass the entire structure, utilizing data from all accelerometers positioned during the physical test.