MIL-A-8870C

Abstract

This specification contains the general and detail design requirements and criteria in the design and construction of airplanes to: <br>a. Prevent flutter, divergence, and other dynamic and static aeroelastic instabilities. <br>b. Control structural vibrations. <br>c. Prevent fatigue failure of the airframe structure or structural components induced by vibrations, aeroacoustic and other oscillatory loads for the service life of the airplane. <br>d. Prescribe structural dynamic analyses, laboratory and ground tests, and structural dynamic flight tests required to demonstrate compliance with design requirements. <br>e. Apply to airplanes acquired by the Navy for all conditions of flight and surface operations for which the airplanes are required to operate. <strong>Beneficial comments (recommendations, additions, deletions) and any pertinent data which may be of use in improving this document should be addressed to: Commanding Officer, Naval Air Warfare Center Aircraft Divison Lakehurst, Code SR3, Lakehurst, NJ 08733-5100, by using the self-addressed Standardization Document Improvement Proposal (DD Form 1426) appearing at the end of this document or by letter.</strong> <b><u>Intended Use:</u></b> The requirements of this specification are intended for use in the design, construction and substantiation of airplanes with regard to the specified aeroelastic stability, vibration control and prevention of vibration and sonic fatigue failures of structure and structural components. The requirements may be modified for specific models of airplanes by type or detail specifications, by flight test or demonstration requirements, and by other contractual documents. <br>