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1.1 This practice covers simplified methods for satisfying structural requirements of very light aeroplanes. The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Level 1 Normal Category aeroplanes which have a single engine, a maximum take-off mass of not more than 750 kg (1654 lbm), a stalling speed in the landing configuration of not more than 83 km/h (45 knots) Calibrated Airspeed (CAS), an unpressurized fuselage, and are non-aerobatic. The content may be more broadly applicable; it is the responsibility of the applicant to substantiate broader applicability as a specific means of compliance. The topics covered within this practice are: Parts of Structure Critical to Safety, Material Strength Properties and Design Values, Design Properties, and Special Factors.

1.2 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable Civil Aviation Authorities (CAAs)) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this practice (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to the ASTM Committee F44 web page (www.astm.org/COMMITTEE/F44.htm).

1.3 Units—The values stated in SI units are to be regarded as standard. The values given in parentheses after SI units are provided for information only and are not considered standard.

1.4 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.

1.5 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.

4.1 The purpose of this practice is to establish simplified methods that can be used to satisfy the materials, processes, and methods of fabrication requirements of Specification F3114 and the fatigue strength evaluation requirements of Specification F3115 for very light aeroplanes as defined in 1.1.

4.2 EASA CM-S-006 provides additional guidance regarding the relevant requirements for aeroplanes defined in 1.1.