F37 - Light Sport Aircraft

ABSTRACT
This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an “airplane.” In order to comply with flight requirements, the following shall be evaluated: load distribution limit, propeller speed and pitch limit, stalling speed, takeoff, climb, landing, balked landing, controllability and maneuverability, vibrations, and ground control and stability. For compliance of structure requirements, the following shall be considered: flight loads; control surface and system loads; horizontal stabilizing and balancing surfaces (balancing loads, maneuvering loads, and gust loads); vertical stabilizing surfaces (maneuvering loads, gust loads, and outboard fins or winglets); supplementary conditions for stabilizing surfaces; ailerons, wing flaps, and special devices; ground load conditions; water load conditions; emergency landing conditions; and other loads. The aircraft shall be designed with the following minimum instrumentation and equipment: flight and navigation instruments such as airspeed indicator, and altimeter; powerplant instruments such as fuel quantity indicator, tachometer (RPM), engine “kill” switch, and engine instruments; miscellaneous equipment such as master switch, and overload protection device; and safety belts and harnesses. Each airplane shall include a Pilot Operating Handbook (POH).
SCOPE
1.1 This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an “airplane.”  
1.2 This specification is applicable to the design of a light sport aircraft/airplane as defined by regulations and limited to VFR flight.  
1.3 Units—The values given in this standard are in SI units and are to be regarded as standard. The values given in parentheses are mathematical conversions to inch-pound (or other) units that are provided for information only and are not considered standard. The values stated in each system may not be exact equivalents. Where it may not be clear, some equations provide the units of the result directly following the equation.  
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 requirements 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.

SIGNIFICANCE AND USE
3.1 This specification provides designers and manufacturers of electric propulsion for light sport aircraft design references and criteria to use in designing and manufacturing EPUs.  
3.2 Declaration of compliance is based on testing and documentation during the design, ground testing and flight testing of the EPU by the manufacturer or under the manufacturers’ guidance.  
3.3 Manufacturers of the EPUs are encouraged to review and incorporate appropriate standards and lessons learned from ground based systems as documented in SAE J2344 and EASA CRI F-58 (see Appendix X2).  
3.4 Electric aircraft may contain potentially hazardous level of electrical voltage or current. It is important to protect persons from exposure to this hazard. Under normal operating conditions, adequate electrical isolation is achieved through physical separation means such as the use of insulated wire, enclosures, or other barriers to direct contact. There are conditions or events that can occur outside normal operation that can cause this protection to be degraded. Some means should be provided to detect degraded isolation or ground fault. In addition, processes or hardware, or both, should be provided to allow for controlled access to the high voltage system for maintenance or repair. A number of alternative means may be used to achieve these electrical safety goals including automatic hazardous voltage disconnects, manual disconnects, interlock systems, special tools and grounding. The intention of all these means is either to prevent inadvertent contact with hazardous voltages or to prevent damage or injury from the uncontrolled release of electric energy. Lightning strikes are not addressed in this Standard Practice because LSA aircraft are limited to VMC flight only.
SCOPE
1.1 This practice covers minimum requirements for the design and manufacture of Electric Propulsion Units (EPU) for light sport aircraft, VFR use. The EPU shall as a minimum consist of the electric motor, associated controllers, disconnects and wiring, an Energy Storage Device (ESD) such as a battery or capacitor, or both, and EPU monitoring gauges and meters. Optional onboard charging devices, in-flight charging devices or other technology may be included.  
1.2 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.  
1.3 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.

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1.1 The following requirements apply to the documentation of Light Sport Airplanes. This specification covers the Pilot’s Operating Handbook (POH), Flight Training Supplement (FTS), Maintenance Manual, Aircraft Kit Assembly Instructions (KAI), Component Original Equipment Manufacturer (OEM) manuals, Aircraft OEM’s Statement of Compliance, Registration, and Airframe Records information required for aircraft designed and manufactured in accordance with the ASTM Standards.  
1.1.1 This specification covers the minimum requirements for information that shall be provided by the airplane OEM or seller of a new light sport airplane, light sport airplane kit, engines, propellers, or accessories (that is, radio, transponder, instruments, GPS, etc.) as a part of the initial sale or transfer to the first end-user.  
1.1.2 This specification does not apply to the sale or transfer of used light sport airplane, engines, propellers, or accessories.  
1.2 This specification applies to airplanes seeking civil aviation authority approval, in the form of airworthiness certificates or other like documentation.  
1.3 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.  
1.4 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.

SCOPE
1.1 This specification provides the minimum requirements for a Pilot’s Operating Handbook (POH) for an aircraft designed, manufactured, and operated as a light sport aircraft.  
1.2 This specification defines the POH information that shall be provided by the aircraft manufacturer of a new airplane or airplane kit as a part of the initial sale or transfer to the first-end user.
Note 1: The POH may also be referred to as an Aircraft Operating Instruction (AOI). However, POH is considered the approved nomenclature.  
1.3 This specification applies to an airplane seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other like documentation as a light sport aircraft.  
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.

SCOPE
1.1 This specification addresses the aeroelasticity requirements of the airplane and is applicable to the design of a light sport aircraft/airplane as defined by regulations.  
1.2 This specification shall apply to airplanes with VH greater than 62 m/s (120 KCAS) and with VNE less than or equal to 129 m/s (250 KCAS). The content of this specification may be more broadly applicable. It is the responsibility of the applicant to substantiate broader applicability as a specific means of compliance.  
1.3 Units—The values given in this standard are in SI units and are to be regarded as standard. The values given in parentheses are mathematical conversions to inch-pound (or other) units that are provided for information only and are not considered standard. The values stated in each system may not be exact equivalents. Where it may not be clear, some equations provide the units of the result directly following the equation. It is also noted that the internationally accepted units for altitude and airspeed are feet and knots, respectively. This is the only exception to standard SI units.  
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.

ABSTRACT
This specification covers the establishment of the minimum requirements for the design, testing, and quality assurance of fixed-pitch or ground adjustable propellers for light sport aircraft. The propeller may not have design features that have been shown to be hazardous or unreliable unless the suitability of each questionable design detail or part can be established by tests. Strength testing; stress measurement, fatigue strength, and fatigue analysis, endurance testing, and teardown inspection shall be performed to meet the requirements prescribed.
SCOPE
1.1 This specification covers the establishment of the minimum requirements for the design, testing, and quality assurance of fixed-pitch or ground adjustable propellers for light sport aircraft. These propellers are used on light aircraft, and could be used with engines conforming to Practice F2339.  
1.1.1 When applying the additions provided in Appendix X1, this specification also covers the establishment of the minimum requirements for the design, testing and quality assurance of in-flight adjustable propellers for light-sport aircraft.  
1.2 This specification is intended for use by manufacturers of propellers for light sport aircraft.  
1.3 This specification does not address the airframe installation requirements for propellers.  
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 to 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.

ABSTRACT
This specification covers airworthiness requirements for the design of a powered or non-powered fixed wing light sport aircraft, a “glider.” Stability shall be shown by a tendency for the glider to return toward steady flight after: (1) a “push” from steady flight that results in a speed increase, followed by a non-abrupt release of the pitch control; and (2) a “pull” from steady flight that results in a speed decrease, followed by a non-abrupt release of the pitch control. Strength requirements are specified in terms of limit loads (the maximum loads to be expected in service) and ultimate loads (limit loads multiplied by prescribed factors of safety). The suitability of each structural design detail and part having an important bearing on safety shall be established by test. Each combination of engine, exhaust, cooling and fuel system on a powered glider must be compatible with the glider, and function in a safe and satisfactory manner within the operational limits of the glider and powerplant. Each aircraft shall include Aircraft Operating Instructions (AOI).
SCOPE
1.1 This specification covers airworthiness requirements for the design of a powered or non-powered fixed wing light sport aircraft, a “glider.”  
1.2 This specification is applicable to the design of a light sport aircraft glider as defined by regulations and limited to day VFR flight.  
1.3 A glider for the purposes of this specification is defined as a heavier than air aircraft that remains airborne through the dynamic reaction of the air with a fixed wing and in which the ability to remain aloft in free flight does not depend on the propulsion from a power plant. A powered glider is defined for the purposes of this specification as a glider equipped with a power plant in which the flight characteristics are those of a glider when the power plant is not in operation.  
1.4 The values stated in SI units are to be regarded as standard. The values given in parenthesis are for information only.  
1.5 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 requirements prior to use.  
1.6 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.

ABSTRACT
This specification covers design and performance requirements that apply for the manufacture of lighter-than-air light sport aircraft. Performance requirements for balloons, airships and thermal airships are: proof of compliance; general performance; flight performance; climb; controllability and maneuverability; descent; landing; and stability and control. Structure requirements for airships, thermal airships, balloons and vectored thrust balloons are presented in details. The power plant installation shall be easily accessible for inspection and maintenance. The equipments for airships and free balloons are presented in details. The operating limitations and other information necessary for safe operation shall be established and documented in a flight manual, which will be made available to the pilot upon aircraft delivery.
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1.1 This specification covers design and performance requirements that apply for the manufacture of lighter-than-air light sport aircraft.  
1.2 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 requirements prior to use.  
1.3 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.

ABSTRACT
This specification covers the manufacture of gyroplanes and includes design and performance requirements for light sport gyroplane aircraft. A gyroplane is a rotorcraft to be used for day visual flight rules (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. Aircraft having the following basic features will be so regarded: rotors of either fixed collective pitch or collective pitch control that are not adjustable in flight, single engine with fixed or ground adjustable pitch propeller, no more than two occupant seats, and a maximum gross weight of some value. For compliance, the following flight requirements should be met: load distribution limit, weight limit, empty weight, removable ballast, and rotor speed limit. In order to comply in terms of performance, the requirements for the following shall be evaluated: takeoff, climb, glide, never exceed airspeed, minimum controllable airspeed for level flight, best rate of climb airspeed, landing distance, maximum operating altitude, and height/velocity envelope. The gyroplane must be safely controllable and maneuverable with sufficient margin of control movement and blade freedom to correct for atmospheric turbulence and permit control of the attitude of the gyroplane at all power settings at the critical weight and balance at sea level and at the maximum operating altitude. The evaluation of the gyroplane's longitudinal lateral and directional control and stability shall be discussed. In terms of structure requirements, the following should be taken into consideration: flight loads, engine torque, control system loads, stabilizing and control surfaces, ground loads, main component requirements, emergency landing conditions, and other loads.
SCOPE
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 an...

ABSTRACT
This specification covers design and performance requirements for powered parachute aircraft. It also applies to powered parachute aircraft seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other like documentation. Each of the performance requirements shall be met at the maximum takeoff weight and most critical center of gravity (CG) position. To the extent that CG adjustment devices may be adjusted for flight, these components will be evaluated in the least favorable recommended position as it affects either performance or structural strength. All performance requirements apply in and shall be corrected to International Civil Aviation Organization (ICAO) defined standard atmosphere in still air conditions at sea level. Speeds shall be given in indicated (IAS) and calibrated (CAS) airspeeds in miles per hour (MPH). The wing performance, climb performance, controllability and maneuverability, and reference parameters shall be carefully determined and evaluated. Stability requirements of the aircraft such as longitudinal stability, lateral stability, and directional stability shall be discussed as well. In terms of structural requirements, the load and proof of structure of the aircraft shall be considered.
SCOPE
1.1 The following requirements apply for the manufacture of powered parachute aircraft. This specification includes design and performance requirements for powered parachute aircraft.  
1.2 This specification applies to powered parachute aircraft seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other like documentation.  
1.3 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 requirements prior to use.  
1.4 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.

SIGNIFICANCE AND USE
4.1 The purpose of this practice is to provide the minimum requirements necessary for the establishment of a production acceptance program for a manufacturer of light sport aircraft.  
4.2 The purpose of this specification is to provide the minimum requirements for the establishment of a ground and flight test program for verifying the initial production aircraft meets certain operational performance requirements that have been set forth by the manufacturer in its Pilot’s Operating Handbook (POH).  
4.3 In addition, this specification provides minimum requirements to verify that each subsequent production airplane has no obvious defects that would prevent the safe operation of the airplane.  
4.4 All requirements given in this specification are to be performed in accordance with the manufacturer’s Specification F2972-compliant quality assurance system requirements.  
4.5 The following criteria should not be construed as requirements for specific features to be included on a LSA. When a requirement specifies a feature that does not exist on a LSA, the requirement does not apply.
SCOPE
1.1 The following requirements apply for the manufacture of fixed wing aircraft, including gliders. This practice includes the production acceptance test requirements.  
1.2 This practice applies to aircraft seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other like documentation.  
1.3 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.  
1.4 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.

ABSTRACT
This specification covers minimum requirements for the design, manufacture, and installation of airframe emergency parachutes for light sport aircraft. Materials used for parts and assemblies, shall meet the conditions specified for (1) suitability and durability, (2) strength and other properties assumed in the design data, and (3) effects of environmental conditions, such as temperature and humidity, expected in service. Parachute model designations shall include the following: (1) parachute system parts list, (2) new parachutes model designations, (3) design changes, and (4) installation design changes. The strength requirements shall be specified in terms of limit loads and ultimate loads. The following minimum performance standards for the basic parachute system design shall be met: (1) parachute strength test to determine the ultimate load factor, (2) rate of descent, (3) component strength test, (4) staged deployment, and (5) environmental conditions. The installation design requirements are specified for the following: (1) coordination, (2) weight and balance, (3) system mounting, (4) extraction performance, (5) parachute attachment to the airframe, (6) activating housing routing, and (7) occupant restraint. Other requirements such as system function and operations and product marking are also detailed.
SCOPE
1.1 This specification covers minimum requirements for the design, manufacture, and installation of parachutes for airframes. Airframe emergency parachutes addressed in this specification refer to parachute systems designed, manufactured, and installed to recover the airframe and its occupants at a survivable rate of descent. This specification is not applicable to deep-stall parachutes, spin recovery parachutes, drogue parachutes, or other airframe emergency aerodynamic decelerators not specifically intended for safely lowering the airframe and occupants to the ground. The specification is applicable to these types of parachutes if they are an integral part of an airframe emergency parachute system designed to recover the airframe and occupants at a survivable rate of descent.  
1.2 The values stated in SI units are to be regarded as standard. There may be values given in parentheses that are mathematical conversions to inch-pound units. Values in parentheses are provided for information only and are not considered standard.  
1.2.1 Note that within the aviation community mixed units are appropriate in accordance with International Civil Aviation Organization (ICAO) agreements. While the values stated in SI units are regarded as standard, certain values such as airspeeds in knots and altitude in feet are also accepted as standard.  
1.3 Airframe emergency parachute recovery systems have become an acceptable means of greatly reducing the likelihood of serious injury or death in an in-flight emergency. Even though they have saved hundreds of lives in many different types of conditions, inherent danger of failure, even if properly designed, manufactured and installed, remains due to the countless permutations of random variables (attitude, altitude, accelerations, airspeed, weight, geographic location, etc.) that may exist at time of usage. The combination of these variables may negatively influence the life saving function of these airframe emergency parachute systems. They are designed to be a supplemental safety device and to be used at the discretion of the pilot when deemed to provide the best chance of survivability.  
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 requirements prior to use.  
1.5 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles fo...

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1.1 This practice provides an acceptable, and simplified, means of determining certain design loads criteria and conditions for fixed wing aircraft. In particular, the practice provides overall aircraft flight loads and flight conditions as well as control surface loads, wing loads, gust load factors, and gust loads on stabilizing surfaces.  
1.2 This practice is intended to be referenced by other standards that define requirements for comprehensive aircraft loads. This practice does not provide all aircraft loads required for structural compliance. In addition, each load or condition determined through this practice has limitations on its use within the relevant section to which it must adhere.  
1.3 Units—The values given in this standard are in SI units and are to be regarded as standard. Any values given in parentheses are mathematical conversions to inch-pound (or other) units that are provided for information only and are not considered standard. The values stated in each system may not be exact equivalents. Where it may not be clear, some equations provide the units of the result directly following the equation.  
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.

SIGNIFICANCE AND USE
3.1 This practice provides designers and manufacturers of engines for light sport aircraft design references and criteria to use in designing and manufacturing engines.  
3.2 Declaration of compliance is based on testing and documentation during the design and testing or flight testing of the engine type by the manufacturer or under the manufacturers' guidance.
SCOPE
1.1 This practice covers minimum requirements for the design and manufacture of reciprocating spark ignition engines for light sport aircraft, VFR use.  
1.2 The values stated in inch-pound units are to be regarded as standard. No other units of measurement are included in this standard.  
1.3 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.  
1.4 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.

SIGNIFICANCE AND USE
3.1 This practice provides designers and manufacturers of engines for light sport aircraft design references and criteria to use in designing and manufacturing engines.  
3.2 Declaration of compliance is based on testing and documentation during the design and testing or flight-testing of the engine type by the manufacturer or under the manufacturer's guidance.
SCOPE
1.1 This practice covers minimum requirements for the design and manufacture of reciprocating compression ignition engines for light sport aircraft, Visual Flight Rules (VFR) use.  
1.2 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.  
1.3 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.

ABSTRACT
This specification covers the minimum requirements for production acceptance testing of a powered parachute aircraft. The test includes ground and flight testing. In ground testing, the aircraft shall undergo inspection verification and engine break-in. In flight testing, on the other hand, the aircraft shall be inspected for performance while on a specified flight time, including takeoff and landing, and shall undergo instrument verification. In addition, this specification also provides for post flight acceptance testing, which shall include a review of all flight critical attachments and structures.
SCOPE
1.1 The following requirements apply for the manufacture powered parachute aircraft. This specification includes the production acceptance test requirements for powered parachute aircraft.  
1.2 This specification applies to powered parachute aircraft seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other like documentation.  
1.3 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 requirements prior to use.  
1.4 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.

ABSTRACT
This specification covers production acceptance test requirements for the manufacture of lighter-than-air light sport aircraft. This provides the minimum requirements for the establishment of a ground and flight test program for verifying the initial (first run) production aircraft meets certain operational performance requirement that have been set forth by the manufacturer in its Aircraft Operating Instructions. The minimum requirements to verify that each subsequent production aircraft has no obvious defects that would prevent the safe operation of the aircraft are described. Every production aircraft shall be flight tested to the minimums such as lighter-than-air airships, hot-air balloons and gas/hybrid balloons.
SCOPE
1.1 This specification covers production acceptance test requirements for the manufacture of lighter-than-air light sport aircraft.  
1.2 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.  
1.3 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.

ABSTRACT
This specification covers the manufacture of lighter-than-air light sport aircraft. This specification covers the minimum requirements for information that shall be provided by the manufacturer or seller of new lighter-than-air aircraft as a part of the initial sale or transfer to the first end user. This information shall include, but not be limited to, the information plate attached to the aircraft, the placard notice, Aircraft Operating Instructions, the maintenance manual, and the manufacturers statement of compliance. The placard notice shall be posted in the aircraft passenger area so that it is visible to both the pilot and passenger upon entry or while seated in the aircraft. The purpose of this specification is to require provision of the minimum information necessary for the proper identification, maintenance, and operation of light sport aircraft.
SCOPE
1.1 This specification covers the manufacture of lighter-than-air light sport aircraft.  
1.1.1 This specification covers the minimum requirements for information that shall be provided by the manufacturer or seller of new lighter-than-air aircraft as a part of the initial sale or transfer to the first end user.  
1.2 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 to determine the applicability of regulatory limitations prior to use.  
1.3 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.

ABSTRACT
This specification covers the requirements that apply for the manufacture of powered parachute aircraft; it includes pilot operating handbook requirements for powered parachute aircraft. This applies to powered parachute aircraft seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other similar documentation. Each light sport aircraft must include an aircraft operating instructions which includes: operating limitations, operating data, format, supplements, and data location and contact information. Each aircraft shall have a maintenance manual provided for the aircraft that covers the minimum of the requirements as defined by the aircraft manufacturer.
SCOPE
1.1 The following requirements apply for the manufacture of powered parachute aircraft. This specification includes pilot operating handbook requirements for powered parachute aircraft that were designed and manufactured in accordance with ASTM standards.  
1.1.1 This specification covers the minimum requirements for information that shall be provided by the manufacturer or seller of new light sport aircraft, engines, or propellers as a part of the initial sale or transfer to the first end user.  
1.1.2 This specification does not apply to the sale or transfer of used light sport aircraft, engines, or propellers.  
1.2 This specification applies to powered parachute aircraft seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other like documentation.  
1.3 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 requirements prior to use.  
1.4 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.

ABSTRACT
This guide covers the manufacture of powered parachute aircraft and their qualification for certification. This guide applies to powered parachute aircraft seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other like documentation. Interface documentation is the data necessary for the aircraft manufacturer to complete overall certification to ASTM powered parachute standards. The data represents a guide to recommended type, detail, and general format for data transfer from a major subcontractor to the aircraft manufacturer.
SCOPE
1.1 This guide covers the manufacture of powered parachute aircraft and their qualification for certification.  
1.2 This guide applies to powered parachute aircraft seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other like documentation.  
1.3 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 to determine the applicability of regulatory limitations prior to use.  
1.4 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.

SIGNIFICANCE AND USE
4.1 The purpose of this practice is to provide guidance to owners, mechanics, airports, regulatory officials, and aircraft and component manufacturers who may accomplish maintenance, repairs, and alterations on a light sport aircraft. In addition, this practice covers the format and content of maintenance manuals and instructions for the maintenance, repair, and alteration of an LSA.
SCOPE
1.1 This practice provides guidelines for the qualifications to accomplish the various levels of maintenance on U.S.-certificated experimental and special light sport aircraft. In addition, it provides the content and structure of maintenance manuals for aircraft and their components that are operated as light sport aircraft.  
1.2 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.  
1.3 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.

ABSTRACT
This specification establishes the minimum requirements for a Continued Operational Safety (COS) program for manufacturers of light sport aircraft (LSA) and LSA kits. It establishes a method for reporting, evaluating, and correcting unsafe conditions and service difficulty issues for the purpose of COS of a LSA. The elements of the COS program described in this specification include the following: Communication and Owner Information, Determination of Corrective Action, Notice of Corrective Action, and Continuation of Airworthiness.
This specification applies to aircraft seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other like documentation.
SCOPE
1.1 This specification establishes the minimum requirements for a Continued Operational Safety (COS) program for manufacturer’s of light sport aircraft and light sport aircraft kits.  
1.2 This specification applies to aircraft seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other like documentation.  
1.3 Units—The values stated in SI units are to be regarded as standard. No other units of measurement are included in this 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.

ABSTRACT
The following requirements apply for the manufacture of weight-shift-control aircraft. This specification includes Aircraft Operating Instructions (AOI) and Flight Training Supplement (FTS) requirements for aircraft that were designed and manufactured in accordance with requirements. This specification covers the minimum requirements for information that shall be provided by the manufacturer or seller of new light sport aircraft, engines, or propellers as a part of the initial sale or transfer to the first-end user. The information given shall be included where applicable on the information plate. Each aircraft must include a set of aircraft operating instructions. Each aircraft shall have an MIP document provided for the aircraft that complies with an accepted standard. Each aircraft shall have an FTS that describes features, performance, and procedures unique to that aircraft model.
SCOPE
1.1 The following requirements apply for the manufacture of weight-shift-control aircraft. This specification includes Aircraft Operating Instructions (AOI) and Flight Training Supplement (FTS) requirements for aircraft that were designed and manufactured in accordance with ASTM Standards.  
1.1.1 This specification covers the minimum requirements for information that shall be provided by the manufacturer or seller of new light sport aircraft, engines, or propellers as a part of the initial sale or transfer to the first-end user.  
1.1.2 This specification does not apply to the sale or transfer of used light sport aircraft, engines, or propellers.  
1.2 This specification applies to aircraft seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other like documentation.  
1.3 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.  
1.4 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.

ABSTRACT
This specification covers continued airworthiness requirements for the manufacture of weight-shift-control aircraft and their qualification for possible certification. A safety directive shall be distributed to all registered owners and appropriate CAAwhen a condition is found to exist that may also exist in other aircraft in the fleet and which would cause a deviation from original design or unsafe condition for flight, rendering the aircraft unairworthy. Service bulletins should be distributed to all registered owners by the manufacturer when no unsafe condition exists that could lead to an unairworthy condition, but a service problem has become repetitive for which the manufacturer has developed a design change, or service procedure change that will contribute to the improvement or convenience of operation or maintenance of the aircraft. The manufacturer should issue service letters on any subject that is considered helpful to the owners.
SCOPE
1.1 The following continued airworthiness requirements apply for the manufacture of weight-shift-control aircraft and their qualification for possible certification.  
1.2 This specification applies to aircraft seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other like documentation.  
1.3 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 requirements prior to use.  
1.4 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.

SIGNIFICANCE AND USE
2.1 The purpose of this practice is to establish that each production aircraft has been assembled properly and operates normally throughout its entire allowable flight envelope.  
2.2 If final assembly is completed outside of the main production facility, the manufacturer shall specify the required procedures and what persons are authorized to perform them.
SCOPE
1.1 The following requirements apply for the manufacture of weight-shift-control aircraft. This practice includes the production acceptance test requirements for weight-shift-control aircraft.  
1.2 This practice applies to aircraft seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other like documentation.  
1.3 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 requirements prior to use.  
1.4 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.

SIGNIFICANCE AND USE
4.1 This practice establishes the minimum set of requirements for an independent audit program for aircraft manufacturers. The intended use is to provide minimum requirements for an initial assessment of manufacturers bringing a new aircraft model to market, or for periodic review of an existing manufacturer’s operations.  
4.2 Compliance to this practice would ensure that the audit program and those who execute it meet the consensus set of minimum requirements and qualifications.  
4.3 This practice does not mandate manufacturer independent audits.  
4.4 Independent audits are to be conducted only at the request of the manufacturer or relevant CAA.
SCOPE
1.1 This practice establishes a minimum set of requirements for a Manufacturer Independent Audit Program in compliance with Practice F2839.  
1.2 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.  
1.3 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.

SCOPE
1.1 This guide covers the manufacture of Weight Shift aircraft and their qualification for certification.  
1.2 This guide applies to Weight Shift Control aircraft seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other like documentation.  
1.3 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 and health practices and determine the applicability of regulatory limitations prior to use.

ABSTRACT
This specification covers the minimum requirement for designing, testing, and labeling of weight-shift-control aircraft. This specification covers only weight-shift-control aircraft in which flight control systems do not use hinged surfaces controlled by the pilot. Flight requirements are specified for: (1) proof of compliance including hang point and trimming setting; (2) general performance such as (a) stall speed in the landing configuration, (b) stall speed free of control limits, (c) minimum climb performance, (d) flutter, buffeting, and vibration, (e) turning flight and stalls, and (f) maximum sustainable speed in straight and level flight; (3) controllability and maneuverability such as general, longitudinal, and lateral control; and (4) longitudinal stability and pitch testing. Structural requirements specified include: (1) strength requirements, (2) fulfillment of design requirements, (3) safety factors, (4) design airspeeds, (5) flight loads, (6) pilot control loads, (7) ground loads including landing gear shock absorption, and (8) emergency landing loads. Design and construction requirements are specified for: (1) materials, (2) fabrication methods, (3) self-locking nuts, (4) protection of structure, (5) accessibility, (6) setup and breakdown, (7) control system evaluated by operation test, (8) mast (pylon) safety device, (9) cockpit design, and (10) markings and placards. Powerplant requirements including installation, fuel system, oil system, induction system, and fire prevention, as well as equipment requirements such as powerplant instruments, miscellaneous equipment, and lap belts and harnesses, are detailed. Operating limitations such as load distribution limits are also specified.
SCOPE
1.1 This specification covers the minimum airworthiness standards a manufacturer shall meet in the designing, testing, and labeling of weight-shift-control aircraft.  
1.2 This specification covers only weight-shift-control aircraft in which flight control systems do not use hinged surfaces controlled by the pilot.
Note 1: This section is intended to preclude hinged surfaces such as typically found on conventional airplanes such as rudders and elevators. Flexible sail surfaces typically found on weight-shift aircraft are not considered hinged surfaces for the purposes of this specification.  
1.3 Weight-shift-control aircraft means a powered aircraft with a framed pivoting wing and a fuselage (trike carriage) controllable only in pitch and roll by the pilot's ability to change the aircraft's center of gravity with respect to the wing. Flight control of the aircraft depends on the wing's ability to flexibly deform rather than the use of control surfaces.  
1.4 This specification is organized and numbered in accordance with the bylaws established for Committee F37. The main sections are:    
Scope  
1  
Referenced Documents  
2  
Terminology  
3  
Flight Requirements  
4  
Structural Requirements  
5  
Design and Construction Requirements  
6  
Powerplant Requirements  
7  
Equipment Requirements  
8  
Operating Limitations  
9  
Keywords  
10  
Annex  
Annex A1  
Appendix  
Appendix X1  
1.5 The values stated in either SI units or inch-pound units are to be regarded separately as standard. The values stated in each system may not be exact equivalents; therefore, each system shall be used independently of the other. Combining values from the two systems may result in non-conformance with the standard.  
1.6 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 and health practices and determine the applicability of regulatory requirements prior to use.

SIGNIFICANCE AND USE
3.1 The purpose of this standard practice is to provide the minimum requirements for the conduct of compliance audits.  
3.2 The intended use of standard is to provide a basis for an internal or external entity to develop an audit program. An audit program defines specific requirements for the execution of audits for a particular objective. An example of an audit program would be an external (third party) audit of LSA manufacturer’s quality assurance system.  
3.3 Compliance to this standard would insure that audit programs and those who develop and execute them are following a consensus set of minimum requirements.  
3.4 This standard does not mandate either internal or external audits.  
3.5 An auditing entity cannot request or approve an audit.  
3.6 Other Audit Criteria—Other audit criteria may be included in the audit scope if specified in the audit plan. Examples include safety, technical, operational, and management requirements. Items that are outside the scope of auditable criteria may be submitted as observations for possible resolution. However these are not binding and are not mandatory.  
3.7 Additional Services—Additional services are outside the scope of an audit objective. Examples of such services are consultation to resolve negative or open findings or any other service where the auditing entity conducts an activity other than an audit for the audited entity.  
3.8 Compliance Assurance—An audit is only an indicator of the compliance health of the facility and/or organization during only the period under review and therefore has limited compliance assurance and is not assumed to be exhaustive.  
3.9 Level of Review is Variable—The audit scope may vary to meet different audit objectives. For example, the audit scope may include only selected audit criteria, selected period under review, or selected portions of a facility or organization.
SCOPE
1.1 This standard practice establishes the minimum set of requirements for auditing programs, methods, and systems, the responsibilities for all parties involved, and qualifications for entities conducting audits against ASTM standards on Light Sport Aircraft.  
1.2 This standard provides requirements to enable consistent and structured examination of objective evidence for compliance that is beneficial for the LSA industry and its consumers. It is the intent of this standard to provide the necessary minimum requirements for organizations to develop audit programs and procedures.  
1.3 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 and health practices and determine the applicability of regulatory limitations prior to use.

ABSTRACT
This practice covers the instructions a kit producer must provide to a consumer in order to assemble and safely flight-test a recreational aircraft to ensure compliance with applicable ASTM standards. The instructions prescribe the necessary mechanical skills or training, or both, required for successful completion of the kit, as well as necessary tooling, fixtures, inspections, measurements, and other pertinent items required for successful completion of the kit. The kit assembly instructions (KAI) shall include at least the following information: (1) Revisions; (2) Introduction and instructions for using the KAI; (3) Table of Contents; (4) Safety Summary; (5) Applicable standards and specifications; (6) Terminology; (7) Required consumer abilities and responsibilities; (8) Required equipment and environmental conditions; (9) Parts list; (10) Assembly operations; (11) Final assembly Inspections; (12) Flight-test procedures; and (13) Additional requirements.
SCOPE
1.1 This practice covers the instructions a kit producer must provide to a consumer in order to assemble and safely flight-test a recreational aircraft to ensure compliance with applicable ASTM standards.  
1.2 The instructions prescribe the necessary mechanical skills or training, or both, required for successful completion of the kit, as well as necessary tooling, fixtures, inspections, measurements, and other pertinent items required for successful completion of the kit. Proof of compliance with these instructions may be vital for obtaining flight authorizations from the applicable CAA.  
1.3 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 and health practices and determine the applicability of regulatory limitations prior to use.

SIGNIFICANCE AND USE
4.1 This guide provides some major themes and examples for consideration related to compliance which are not necessarily captured in any single standard pertinent to light sport aircraft. The outline of this document is intended to loosely reflect the process that an organization would go through in order to reach and maintain production of a light sport aircraft that is demonstrably compliant with the applicable ASTM standards.  
4.2 These considerations are applicable to manufacturers which are responsible for conformity to processes and procedures required in ASTM standards for light sport aircraft. Manufacturers are encouraged to think through the contents of this guide, reference the ASTM light sport aircraft standards, establish, document and follow their own procedures.  
4.3 Manufacturers are responsible for determining which standards and revisions thereof are part of the regulatory package of any given CAA, along with any other requirements applicable within the agency’s jurisdiction.  
4.4 Following this guide does not ensure compliance of a particular light sport aircraft; however, following the explanations provided herein should assist manufacturers in avoiding common pitfalls of declaring compliance prematurely, determining shortcomings in current declarations of compliance, and maintaining a body of documentation sufficient to support a declaration of compliance.
SCOPE
1.1 This document provides guidance to assist manufacturers in understanding and meeting ASTM standards for light sport aircraft. This guidance material presents philosophies, practices and considerations recommended by industry consensus, but does not present technical or business requirements that must be met.  
1.2 It is the intent of this guide to provide processes to be considered by organizations looking to develop or improve objective evidence of compliance for light sport aircraft. It does not attempt to identify all of the standards, regulations or other requirements that may be applicable to a given aircraft, production or testing process.  
1.3 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.  
1.4 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.

ABSTRACT
This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an “airplane.” In order to comply with flight requirements, the following shall be evaluated: load distribution limit, propeller speed and pitch limit, stalling speed, takeoff, climb, landing, balked landing, controllability and maneuverability, vibrations, and ground control and stability. For compliance of structure requirements, the following shall be considered: flight loads; control surface and system loads; horizontal stabilizing and balancing surfaces (balancing loads, maneuvering loads, and gust loads); vertical stabilizing surfaces (maneuvering loads, gust loads, and outboard fins or winglets); supplementary conditions for stabilizing surfaces; ailerons, wing flaps, and special devices; ground load conditions; water load conditions; emergency landing conditions; and other loads. The aircraft shall be designed with the following minimum instrumentation and equipment: flight and navigation instruments such as airspeed indicator, and altimeter; powerplant instruments such as fuel quantity indicator, tachometer (RPM), engine “kill” switch, and engine instruments; miscellaneous equipment such as master switch, and overload protection device; and safety belts and harnesses. Each airplane shall include a Pilot Operating Handbook (POH).
SCOPE
1.1 This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an “airplane.”  
1.2 This specification is applicable to the design of a light sport aircraft/airplane as defined by regulations and limited to VFR flight.  
1.3 Units—The values given in this standard are in SI units and are to be regarded as standard. The values given in parentheses are mathematical conversions to inch-pound (or other) units that are provided for information only and are not considered standard. The values stated in each system may not be exact equivalents. Where it may not be clear, some equations provide the units of the result directly following the equation.  
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 requirements 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.

SCOPE
1.1 This practice provides an acceptable, and simplified, means of determining certain design loads criteria and conditions for fixed wing aircraft. In particular, the practice provides overall aircraft flight loads and flight conditions as well as control surface loads, wing loads, gust load factors, and gust loads on stabilizing surfaces.  
1.2 This practice is intended to be referenced by other standards that define requirements for comprehensive aircraft loads. This practice does not provide all aircraft loads required for structural compliance. In addition, each load or condition determined through this practice has limitations on its use within the relevant section to which it must adhere.  
1.3 Units—The values given in this standard are in SI units and are to be regarded as standard. Any values given in parentheses are mathematical conversions to inch-pound (or other) units that are provided for information only and are not considered standard. The values stated in each system may not be exact equivalents. Where it may not be clear, some equations provide the units of the result directly following the equation.  
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.

SIGNIFICANCE AND USE
3.1 This practice provides designers and manufacturers of engines for light sport aircraft design references and criteria to use in designing and manufacturing engines.  
3.2 Declaration of compliance is based on testing and documentation during the design and testing or flight testing of the engine type by the manufacturer or under the manufacturers' guidance.
SCOPE
1.1 This practice covers minimum requirements for the design and manufacture of reciprocating spark ignition engines for light sport aircraft, VFR use.  
1.2 The values stated in inch-pound units are to be regarded as standard. No other units of measurement are included in this standard.  
1.3 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.  
1.4 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.

ABSTRACT
This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an “airplane.” In order to comply with flight requirements, the following shall be evaluated: load distribution limit, propeller speed and pitch limit, stalling speed, takeoff, climb, landing, balked landing, controllability and maneuverability, vibrations, and ground control and stability. For compliance of structure requirements, the following shall be considered: flight loads; control surface and system loads; horizontal stabilizing and balancing surfaces (balancing loads, maneuvering loads, and gust loads); vertical stabilizing surfaces (maneuvering loads, gust loads, and outboard fins or winglets); supplementary conditions for stabilizing surfaces; ailerons, wing flaps, and special devices; ground load conditions; water load conditions; emergency landing conditions; and other loads. The aircraft shall be designed with the following minimum instrumentation and equipment: flight and navigation instruments such as airspeed indicator, and altimeter; powerplant instruments such as fuel quantity indicator, tachometer (RPM), engine “kill” switch, and engine instruments; miscellaneous equipment such as master switch, and overload protection device; and safety belts and harnesses. Each airplane shall include a Pilot Operating Handbook (POH).
SCOPE
1.1 This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an “airplane.”  
1.2 This specification is applicable to the design of a light sport aircraft/airplane as defined by regulations and limited to VFR flight.  
1.3 Units—The values given in this standard are in SI units and are to be regarded as standard. The values given in parentheses are mathematical conversions to inch-pound (or other) units that are provided for information only and are not considered standard. The values stated in each system may not be exact equivalents. Where it may not be clear, some equations provide the units of the result directly following the equation.  
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 requirements 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.

SIGNIFICANCE AND USE
4.1 The purpose of this practice is to provide guidance to owners, mechanics, airports, regulatory officials, and aircraft and component manufacturers who may accomplish maintenance, repairs, and alterations on a light sport aircraft. In addition, this practice covers the format and content of maintenance manuals and instructions for the maintenance, repair, and alteration of an LSA.
SCOPE
1.1 This practice provides guidelines for the qualifications to accomplish the various levels of maintenance on U.S.-certificated experimental and special light sport aircraft. In addition, it provides the content and structure of maintenance manuals for aircraft and their components that are operated as light sport aircraft.  
1.2 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.  
1.3 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.

SIGNIFICANCE AND USE
2.1 This practice provides designers and manufacturers of engines for light sport aircraft design references and criteria to use in designing and manufacturing engines.  
2.2 Declaration of compliance is based on testing and documentation during the design and testing or flight testing of the engine type by the manufacturer or under the manufacturers' guidance.
SCOPE
1.1 This practice covers minimum requirements for the design and manufacture of reciprocating spark ignition engines for light sport aircraft, VFR use.  
1.2 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.  
1.3 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.

ABSTRACT
This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an “airplane.” In order to comply with flight requirements, the following shall be evaluated: load distribution limit, propeller speed and pitch limit, stalling speed, takeoff, climb, landing, balked landing, controllability and maneuverability, vibrations, and ground control and stability. For compliance of structure requirements, the following shall be considered: flight loads; control surface and system loads; horizontal stabilizing and balancing surfaces (balancing loads, maneuvering loads, and gust loads); vertical stabilizing surfaces (maneuvering loads, gust loads, and outboard fins or winglets); supplementary conditions for stabilizing surfaces; ailerons, wing flaps, and special devices; ground load conditions; water load conditions; emergency landing conditions; and other loads. The aircraft shall be designed with the following minimum instrumentation and equipment: flight and navigation instruments such as airspeed indicator, and altimeter; powerplant instruments such as fuel quantity indicator, tachometer (RPM), engine “kill” switch, and engine instruments; miscellaneous equipment such as master switch, and overload protection device; and safety belts and harnesses. Each airplane shall include a Pilot Operating Handbook (POH).
SCOPE
1.1 This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an “airplane.”  
1.2 This specification is applicable to the design of a light sport aircraft/airplane as defined by regulations and limited to VFR flight.  
1.3 Units—The values given in this standard are in SI units and are to be regarded as standard. The values given in parentheses are mathematical conversions to inch-pound (or other) units that are provided for information only and are not considered standard. The values stated in each system may not be exact equivalents. Where it may not be clear, some equations provide the units of the result directly following the equation.  
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 and health practices and determine the applicability of regulatory requirements prior to use.

ABSTRACT
This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an “airplane.” In order to comply with flight requirements, the following shall be evaluated: load distribution limit, propeller speed and pitch limit, stalling speed, takeoff, climb, landing, balked landing, controllability and maneuverability, vibrations, and ground control and stability. For compliance of structure requirements, the following shall be considered: flight loads; control surface and system loads; horizontal stabilizing and balancing surfaces (balancing loads, maneuvering loads, and gust loads); vertical stabilizing surfaces (maneuvering loads, gust loads, and outboard fins or winglets); supplementary conditions for stabilizing surfaces; ailerons, wing flaps, and special devices; ground load conditions; water load conditions; emergency landing conditions; and other loads. The aircraft shall be designed with the following minimum instrumentation and equipment: flight and navigation instruments such as airspeed indicator, and altimeter; powerplant instruments such as fuel quantity indicator, tachometer (RPM), engine “kill” switch, and engine instruments; miscellaneous equipment such as master switch, and overload protection device; and safety belts and harnesses. Each airplane shall include a Pilot Operating Handbook (POH).
SCOPE
1.1 This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an “airplane.”  
1.2 This specification is applicable to the design of a light sport aircraft/airplane as defined by regulations and limited to VFR flight.  
1.3 Units—The values given in this standard are in SI units and are to be regarded as standard. The values given in parentheses are mathematical conversions to inch-pound (or other) units that are provided for information only and are not considered standard. The values stated in each system may not be exact equivalents. Where it may not be clear, some equations provide the units of the result directly following the equation.  
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 and health practices and determine the applicability of regulatory requirements prior to use.

SIGNIFICANCE AND USE
4.1 This practice establishes the minimum set of requirements for an independent factory assessment audit program for aircraft manufacturers. The intended use is to provide minimum requirements for an initial assessment of manufacturers bringing a new aircraft model to market, or for periodic review of an existing manufacturer’s operations if required by relevant Civil Aviation Authority (CAA).  
4.2 Compliance to this practice would ensure that the audit program and those who execute it meet the consensus set of minimum requirements and qualifications.  
4.3 This practice does not mandate independent factory assessment audits.  
4.4 Independent audits are to be conducted only at the request of the manufacturer or relevant CAA.
SCOPE
1.1 This practice establishes a minimum set of requirements for a Manufacturer Assessment Independent Audit Program in compliance with Practice F2839.  
1.2 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 and health practices and determine the applicability of regulatory limitations prior to use.

ABSTRACT
This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an “airplane.” In order to comply with flight requirements, the following shall be evaluated: load distribution limit, propeller speed and pitch limit, stalling speed, takeoff, climb, landing, balked landing, controllability and maneuverability, vibrations, and ground control and stability. For compliance of structure requirements, the following shall be considered: flight loads; control surface and system loads; horizontal stabilizing and balancing surfaces (balancing loads, maneuvering loads, and gust loads); vertical stabilizing surfaces (maneuvering loads, gust loads, and outboard fins or winglets); supplementary conditions for stabilizing surfaces; ailerons, wing flaps, and special devices; ground load conditions; water load conditions; emergency landing conditions; and other loads. The aircraft shall be designed with the following minimum instrumentation and equipment: flight and navigation instruments such as airspeed indicator, and altimeter; powerplant instruments such as fuel quantity indicator, tachometer (RPM), engine “kill” switch, and engine instruments; miscellaneous equipment such as master switch, and overload protection device; and safety belts and harnesses. Each airplane shall include a Pilot Operating Handbook (POH).
SCOPE
1.1 This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an “airplane.”  
1.2 This specification is applicable to the design of a light sport aircraft/airplane as defined by regulations and limited to VFR flight.  
1.3 Units—The values given in this standard are in SI units and are to be regarded as standard. The values given in parentheses are mathematical conversions to inch-pound (or other) units that are provided for information only and are not considered standard. The values stated in each system may not be exact equivalents. Where it may not be clear, some equations provide the units of the result directly following the equation.  
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 and health practices and determine the applicability of regulatory requirements prior to use.

SIGNIFICANCE AND USE
4.1 This guide provides some major themes and examples for consideration related to compliance which are not necessarily captured in any single standard pertinent to light sport aircraft. The outline of this document is intended to loosely reflect the process that an organization would go through in order to reach and maintain production of a light sport aircraft that is demonstrably compliant with the applicable ASTM standards.  
4.2 These considerations are applicable to manufacturers which are responsible for conformity to processes and procedures required in ASTM standards for light sport aircraft. Manufacturers are encouraged to think through the contents of this guide, reference the ASTM light sport aircraft standards, establish, document and follow their own procedures.  
4.3 Manufacturers are responsible for determining which standards and revisions thereof are part of the regulatory package of any given CAA, along with any other requirements applicable within the agency’s jurisdiction.  
4.4 Following this guide does not ensure compliance of a particular light sport aircraft; however, following the explanations provided herein should assist manufacturers in avoiding common pitfalls of declaring compliance prematurely, determining shortcomings in current declarations of compliance, and maintaining a body of documentation sufficient to support a declaration of compliance.
SCOPE
1.1 This document provides guidance to assist manufacturers in understanding and meeting ASTM standards for light sport aircraft. This guidance material presents philosophies, practices and considerations recommended by industry consensus, but does not present technical or business requirements that must be met.  
1.2 It is the intent of this guide to provide processes to be considered by organizations looking to develop or improve objective evidence of compliance for light sport aircraft. It does not attempt to identify all of the standards, regulations or other requirements that may be applicable to a given aircraft, production or testing process.  
1.3 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 and health practices and determine the applicability of regulatory limitations prior to use.

SCOPE
1.1 This guide covers the manufacture of Weight Shift aircraft and their qualification for certification.  
1.2 This guide applies to Weight Shift Control aircraft seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other like documentation.  
1.3 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 and health practices and determine the applicability of regulatory limitations prior to use.

ABSTRACT
This specification covers the minimum requirement for designing, testing, and labeling of weight-shift-control aircraft. This specification covers only weight-shift-control aircraft in which flight control systems do not use hinged surfaces controlled by the pilot. Flight requirements are specified for: (1) proof of compliance including hang point and trimming setting; (2) general performance such as (a) stall speed in the landing configuration, (b) stall speed free of control limits, (c) minimum climb performance, (d) flutter, buffeting, and vibration, (e) turning flight and stalls, and (f) maximum sustainable speed in straight and level flight; (3) controllability and maneuverability such as general, longitudinal, and lateral control; and (4) longitudinal stability and pitch testing. Structural requirements specified include: (1) strength requirements, (2) fulfillment of design requirements, (3) safety factors, (4) design airspeeds, (5) flight loads, (6) pilot control loads, (7) ground loads including landing gear shock absorption, and (8) emergency landing loads. Design and construction requirements are specified for: (1) materials, (2) fabrication methods, (3) self-locking nuts, (4) protection of structure, (5) accessibility, (6) setup and breakdown, (7) control system evaluated by operation test, (8) mast (pylon) safety device, (9) cockpit design, and (10) markings and placards. Powerplant requirements including installation, fuel system, oil system, induction system, and fire prevention, as well as equipment requirements such as powerplant instruments, miscellaneous equipment, and lap belts and harnesses, are detailed. Operating limitations such as load distribution limits are also specified.
SCOPE
1.1 This specification covers the minimum airworthiness standards a manufacturer shall meet in the designing, testing, and labeling of weight-shift-control aircraft.  
1.2 This specification covers only weight-shift-control aircraft in which flight control systems do not use hinged surfaces controlled by the pilot.
Note 1: This section is intended to preclude hinged surfaces such as typically found on conventional airplanes such as rudders and elevators. Flexible sail surfaces typically found on weight-shift aircraft are not considered hinged surfaces for the purposes of this specification.  
1.3 Weight-shift-control aircraft means a powered aircraft with a framed pivoting wing and a fuselage (trike carriage) controllable only in pitch and roll by the pilot's ability to change the aircraft's center of gravity with respect to the wing. Flight control of the aircraft depends on the wing's ability to flexibly deform rather than the use of control surfaces.  
1.4 This specification is organized and numbered in accordance with the bylaws established for Committee F37. The main sections are:    
Scope  
1  
Referenced Documents  
2  
Terminology  
3  
Flight Requirements  
4  
Structural Requirements  
5  
Design and Construction Requirements  
6  
Powerplant Requirements  
7  
Equipment Requirements  
8  
Operating Limitations  
9  
Keywords  
10  
Annex  
Annex A1  
Appendix  
Appendix X1  
1.5 The values stated in either SI units or inch-pound units are to be regarded separately as standard. The values stated in each system may not be exact equivalents; therefore, each system shall be used independently of the other. Combining values from the two systems may result in non-conformance with the standard.  
1.6 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 and health practices and determine the applicability of regulatory requirements prior to use.

ABSTRACT
This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an “airplane.” In order to comply with flight requirements, the following shall be evaluated: load distribution limit, propeller speed and pitch limit, stalling speed, takeoff, climb, landing, balked landing, controllability and maneuverability, vibrations, and ground control and stability. For compliance of structure requirements, the following shall be considered: flight loads; control surface and system loads; horizontal stabilizing and balancing surfaces (balancing loads, maneuvering loads, and gust loads); vertical stabilizing surfaces (maneuvering loads, gust loads, and outboard fins or winglets); supplementary conditions for stabilizing surfaces; ailerons, wing flaps, and special devices; ground load conditions; water load conditions; emergency landing conditions; and other loads. The aircraft shall be designed with the following minimum instrumentation and equipment: flight and navigation instruments such as airspeed indicator, and altimeter; powerplant instruments such as fuel quantity indicator, tachometer (RPM), engine “kill” switch, and engine instruments; miscellaneous equipment such as master switch, and overload protection device; and safety belts and harnesses. Each airplane shall include a Pilot Operating Handbook (POH).
SCOPE
1.1 This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an “airplane.”  
1.2 This specification is applicable to the design of a light sport aircraft/airplane as defined by regulations and limited to VFR flight.  
1.3 Units—The values given in this standard are in SI units and are to be regarded as standard. The values given in parentheses are mathematical conversions to inch-pound (or other) units that are provided for information only and are not considered standard. The values stated in each system may not be exact equivalents. Where it may not be clear, some equations provide the units of the result directly following the equation.  
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 and health practices and determine the applicability of regulatory requirements prior to use.

SCOPE
1.1 The following requirements apply to the documentation of Light Sport Airplanes. This specification covers the Pilot's Operating Handbook (POH), Flight Training Supplement (FTS), Maintenance Manual, Aircraft Kit Assembly Instructions (KAI), Component Original Equipment Manufacturer (OEM) manuals, Aircraft OEM's Statement of Compliance, Registration, and Airframe Records information required for aircraft designed and manufactured in accordance with the ASTM Standards.  
1.1.1 This specification covers the minimum requirements for information that shall be provided by the airplane OEM or seller of a new light sport airplane, light sport airplane kit, engines, propellers, or accessories (that is, radio, transponder, instruments, GPS, etc.) as a part of the initial sale or transfer to the first end-user.  
1.1.2 This specification does not apply to the sale or transfer of used light sport airplane, engines, propellers, or accessories.  
1.2 This specification applies to airplanes seeking civil aviation authority approval, in the form of airworthiness certificates or other like documentation.  
1.3 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 and health practices and determine the applicability of regulatory limitations prior to use.

ABSTRACT
This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an “airplane.” In order to comply with flight requirements, the following shall be evaluated: load distribution limit, propeller speed and pitch limit, stalling speed, takeoff, climb, landing, balked landing, controllability and maneuverability, vibrations, and ground control and stability. For compliance of structure requirements, the following shall be considered: flight loads; control surface and system loads; horizontal stabilizing and balancing surfaces (balancing loads, maneuvering loads, and gust loads); vertical stabilizing surfaces (maneuvering loads, gust loads, and outboard fins or winglets); supplementary conditions for stabilizing surfaces; ailerons, wing flaps, and special devices; ground load conditions; water load conditions; emergency landing conditions; and other loads. The aircraft shall be designed with the following minimum instrumentation and equipment: flight and navigation instruments such as airspeed indicator, and altimeter; powerplant instruments such as fuel quantity indicator, tachometer (RPM), engine “kill” switch, and engine instruments; miscellaneous equipment such as master switch, and overload protection device; and safety belts and harnesses. Each airplane shall include a Pilot Operating Handbook (POH).
SCOPE
1.1 This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an “airplane.”  
1.2 This specification is applicable to the design of a light sport aircraft/airplane as defined by regulations and limited to VFR flight.  
1.3 Units—The values given in this standard are in SI units and are to be regarded as standard. The values given in parentheses are mathematical conversions to inch-pound (or other) units that are provided for information only and are not considered standard. The values stated in each system may not be exact equivalents. Where it may not be clear, some equations provide the units of the result directly following the equation.  
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 and health practices and determine the applicability of regulatory requirements prior to use.

SIGNIFICANCE AND USE
4.1 This guide provides some major themes and examples for consideration related to compliance which are not necessarily captured in any single standard pertinent to light sport aircraft. The outline of this document is intended to loosely reflect the process that an organization would go through in order to reach and maintain production of a light sport aircraft that is demonstrably compliant with the applicable ASTM standards.  
4.2 These considerations are applicable to manufacturers which are responsible for conformity to processes and procedures required in ASTM standards for light sport aircraft. Manufacturers are encouraged to think through the contents of this guide, reference the ASTM light sport aircraft standards, establish, document and follow their own procedures.  
4.3 Manufacturers are responsible for determining which standards and revisions thereof are part of the regulatory package of any given CAA, along with any other requirements applicable within the agency’s jurisdiction.  
4.4 Following this guide does not ensure compliance of a particular light sport aircraft; however, following the explanations provided herein should assist manufacturers in avoiding common pitfalls of declaring compliance prematurely, determining shortcomings in current declarations of compliance, and maintaining a body of documentation sufficient to support a declaration of compliance.
SCOPE
1.1 This document provides guidance to assist manufacturers in understanding and meeting ASTM standards for light sport aircraft. This guidance material presents philosophies, practices and considerations recommended by industry consensus, but does not present technical or business requirements that must be met.  
1.2 It is the intent of this guide to provide processes to be considered by organizations looking to develop or improve objective evidence of compliance for light sport aircraft. It does not attempt to identify all of the standards, regulations or other requirements that may be applicable to a given aircraft, production or testing process.  
1.3 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 and health practices and determine the applicability of regulatory limitations prior to use.

SCOPE
1.1 This specification establishes the minimum requirements for a quality assurance system for manufacturers of Light Sport Aircraft or Light Sport Aircraft kits, or both.  
1.2 This standard applies to aircraft seeking civil aviation authority approval in the form of flight certificates, flight permits, or other like documentation.  
1.3 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 and health practices and determine the applicability of regulatory limitations prior to use.

ABSTRACT
This specification covers design and performance requirements for powered parachute aircraft. It also applies to powered parachute aircraft seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other like documentation. Each of the performance requirements shall be met at the maximum takeoff weight and most critical center of gravity (CG) position. To the extent that CG adjustment devices may be adjusted for flight, these components will be evaluated in the least favorable recommended position as it affects either performance or structural strength. All performance requirements apply in and shall be corrected to International Civil Aviation Organization (ICAO) defined standard atmosphere in still air conditions at sea level. Speeds shall be given in indicated (IAS) and calibrated (CAS) airspeeds in miles per hour (MPH). The wing performance, climb performance, controllability and maneuverability, and reference parameters shall be carefully determined and evaluated. Stability requirements of the aircraft such as longitudinal stability, lateral stability, and directional stability shall be discussed as well. In terms of structural requirements, the load and proof of structure of the aircraft shall be considered.
SCOPE
1.1 The following requirements apply for the manufacture of powered parachute aircraft. This specification includes design and performance requirements for powered parachute aircraft.  
1.2 This specification applies to powered parachute aircraft seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other like documentation.  
1.3 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 and health practices and determine the applicability of regulatory requirements prior to use.