The paper emphasizes the relevance of the problem of resonance in aircraft airframe structural elements, and relying on the operating experience shows the consequences of this phenomenon in terms of fatigue cracks occurring in the details of the aircraft airframe during vibration load. The types and consequences of failures in aviation equipment airframe structural elements arising from vibration load are analyzed. On the example of the slat, the forms of natural oscillations of high-lift devices are investigated, their relationship with the rotational frequencies of the high and low pressure rotors of the lift-propulsion system is shown. The study introduces the method of frequency offset of the structural pattern of the object under consideration, and implements the algorithm for modal analysis of a metal structure on the basis of modern applied packages of three-dimensional modeling and engineering analysis. The place of analytical calculations in the structure of the entire product life cycle is noted.