1.1 本规范涵盖旋翼机的制造。本规范包括轻型运动旋翼飞机的设计和性能要求。 1.2 本规范适用于以飞行证书、飞行许可证或其他类似文件的形式寻求民航当局批准的轻型旋翼飞机。 1.3 本规范中的旋翼机定义为仅用于日间VFR的旋翼飞机，旋翼叶片在飞行中不是由发动机驱动的，在飞行中由空气对单个旋翼的反作用力支撑，当飞机水平飞行时，该旋翼在基本垂直轴上自由旋转。 1.4 这些要求适用于正统设计的轻型旋翼机。具有以下基本特征的飞机将被视为: 1.4.1 固定总距或总距控制的旋翼在飞行中不可调， 1.4.2 带固定或地面可调螺距螺旋桨的单引擎， 1.4.3 不超过两个乘员座椅，以及 1.4.4 最大总重（MGW）为725 kg（1600 lb）或以下。 1.5 如果可以证明某个特征在所有重要方面都与历史上证明符合本规范的特征相似，并且在操作方面可以被视为单独的实体，则该特征应被视为适用且符合本规范。 1.6 如果这些要求不适用于特定的设计和结构特征，则有必要向ASTM轻型运动飞机委员会F37提交本规范的适当修正案，供其考虑和批准。 1.7 以国际单位表示的数值视为标准值。括号中给出的值仅供参考。 1.8 本标准并不旨在解决与其使用相关的所有安全问题（如有）。 本标准的使用者有责任在使用前制定适当的安全、健康和环境实践，并确定监管限制的适用性。 1.9 目录: 部分 范围 1. 目录 1.9 参考文件 2. 术语 3. 定义 3.1 缩略语 3.2 航班 4. 全体的 4.1 表演 4.2 可控性和机动性 4.3 纵向横向和方向控制 4.4 稳定性 4.5 地面处理特性 4.6 其他飞行要求 4.7 结构 5. 全体的 5.1 飞行载荷 5.2 发动机扭矩 5.3 控制系统负载 5.4 稳定和控制表面 5.5 地面载荷 5.6 主要部件要求 5.7 紧急着陆条件 5.8 其他载荷 5.9 设计和施工 6. 全体的 6.1 材料 6.2 制造方法 6.3 连接的锁定 6.4 结构保护 6.5 视察 6.6 索具和起重规定 6.7 材料强度特性和设计值 6.8 疲劳强度 6.9 特殊安全因素 6.10 承载系数 6.10.2 拟合系数 6.10.3 电缆系数 6.10.4 转子部件系数 6.10.5 颤振预防和结构刚度 6.11 控制表面和转子 6.12 控制面安装（转子叶片除外） 6.13 控制面铰链（转子叶片除外） 6.14 转子质量平衡 6.15 转子叶片间隙 6.16 转子头轴承 6.17 控制系统 6.18 驾驶舱设计 6.19 发电厂 7. 全体的 7.1 发动机 7.2 发动机和螺旋桨兼容性 7.3 转子旋转和制动系统 7.4 发电厂和转子系统兼容性 7.5 螺旋桨间隙 7.6 燃油系统 7.7 机油系统 7.8 冷却 7.9 进气系统 7.10 排气系统 7.11 发电厂控制装置和附件 7.12 整流罩和风舱 7.13 设备 8. 全体的 8.1 仪表安装 8.2 电气系统和设备 8.3 各种各样的设备 8.4 操作限制和信息 9 全体的 9.1 空速限制 9.2 重量和平衡 9.3 动力装置和螺旋桨限制 9.4 试点操作手册，POH 9.5 维护手册 9.6 标记和标牌 9.7 螺旋桨 10 设计和施工 10.1 关键词 12 1.10 本国际标准是根据世界贸易组织技术性贸易壁垒（TBT）委员会发布的《关于制定国际标准、指南和建议的原则的决定》中确立的国际公认标准化原则制定的。

1.1 This specification covers the manufacture of gyroplanes. This specification includes design and performance requirements for light sport gyroplane aircraft. 1.2 This specification applies to light gyroplane aircraft seeking civil aviation authority approval in the form of flight certificates, flight permits, or other like documentation. 1.3 A gyroplane for the purposes of this specification is defined as a rotorcraft to be used for day VFR only, with rotor blades that are not engine-driven in flight and are supported in flight by the reaction of the air on a single rotor that rotates freely on a substantially vertical axis when the aircraft is in horizontal flight. 1.4 These requirements apply to light gyroplanes of orthodox design. Aircraft having the following basic features will be so regarded: 1.4.1 Rotors of either fixed collective pitch or collective pitch control that are not adjustable in flight, 1.4.2 Single engine with fixed or ground adjustable pitch propeller, 1.4.3 No more than two occupant seats, and 1.4.4 A maximum gross weight (MGW) of 725 kg (1600 lb) or less. 1.5 Where it can be shown that a particular feature is similar in all significant respects to a feature that has historically demonstrated compliance with this specification and can be considered a separate entity in terms of its operation, that feature shall be deemed to be applicable and in compliance with this specification. 1.6 Where these requirements are inappropriate to particular design and construction features, it will be necessary to submit an appropriate amendment of this specification to ASTM Committee F37 on Light Sport Aircraft for consideration and approval. 1.7 The values stated in SI units are to be regarded as standard. The values given in parentheses are for information only. 1.8 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. 1.9 Table of Contents: Section Scope 1 Table of Contents 1.9 Referenced Documents 2 Terminology 3 Definitions 3.1 Acronyms 3.2 Flight 4 General 4.1 Performance 4.2 Controllability and Maneuverability 4.3 Longitudinal Lateral and Directional Control 4.4 Stability 4.5 Ground-Handling Characteristics 4.6 Miscellaneous Flight Requirements 4.7 Structure 5 General 5.1 Flight Loads 5.2 Engine Torque 5.3 Control System Loads 5.4 Stabilizing and Control Surfaces 5.5 Ground Loads 5.6 Main Component Requirements 5.7 Emergency Landing Conditions 5.8 Other Loads 5.9 Design and Construction 6 General 6.1 Materials 6.2 Fabrication Methods 6.3 Locking of Connections 6.4 Protection of Structure 6.5 Inspection 6.6 Provisions for Rigging and Derigging 6.7 Material Strength Properties and Design Values 6.8 Fatigue Strength 6.9 Special Factors of Safety 6.10 Bearing Factors 6.10.2 Fitting Factors 6.10.3 Cable Factor 6.10.4 Rotor Components Factor 6.10.5 Flutter Prevention and Structural Stiffness 6.11 Control Surfaces and Rotors 6.12 Control Surface Installations (Other Than Rotor Blades) 6.13 Control Surface Hinges (Other Than Rotor Blades) 6.14 Rotor Mass Balance 6.15 Rotor Blade Clearance 6.16 Rotor Head Bearings 6.17 Control Systems 6.18 Cockpit Design 6.19 Powerplant 7 General 7.1 Engine 7.2 Engine and Propeller Compatibility 7.3 Rotor Spin-Up and Brake Systems 7.4 Powerplant and Rotor System Compatibility 7.5 Propeller Clearance 7.6 Fuel System 7.7 Oil System 7.8 Cooling 7.9 Induction System 7.10 Exhaust System 7.11 Powerplant Controls and Accessories 7.12 Cowling and Nacelle 7.13 Equipment 8 General 8.1 Instruments—Installation 8.2 Electrical Systems and Equipment 8.3 Miscellaneous Equipment 8.4 Operating Limitations and Information 9 General 9.1 Airspeed Limitations 9.2 Weight and Balance 9.3 Powerplant and Propeller Limitations 9.4 Pilot Operating Handbook, POH 9.5 Maintenance Manual 9.6 Markings and Placards 9.7 Propellers 10 Design and Construction 10.1 Keywords 12 1.10 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.