F44.20 - Flight

ABSTRACT
This specification covers airworthiness design standards associated with aeroplane flight. The applicant for a design approval shall seek the individual guidance of their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
SCOPE
1.1 This specification establishes the airworthiness design standards associated with aeroplane weight and center of gravity.  
1.2 The term “aeroplane” is utilized in this specification as it was originally conceived for normal category fixed wing aircraft with a maximum certificated weight of 19 000 lb or less and a passenger seating configuration up to 19 as defined in the Rules. However, these standards may be more broadly applicable and their usage should not be unnecessarily limited.  
1.3 The applicant for a design approval shall seek the individual guidance of their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan. For information on which CAA regulatory bodies have accepted this specification (in whole or in part) as a means of compliance to their small aircraft airworthiness regulations (hereinafter referred to as “the Rules”), refer to ASTM Committee F44 webpage (www.astm.org/COMMITTEE/F44.htm), which includes CAA website links.  
1.4 Units—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.  
1.5 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 limitations 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 provides airworthiness design requirements for general aeroplane performance, and is applicable to small aeroplanes as defined in Terminology F3060. The applicant for a design approval shall seek the individual guidance to their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
SCOPE
1.1 This specification covers the airworthiness design standards associated with general aeroplane performance. The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Normal Category aeroplanes. The content may be more broadly applicable; it is the responsibility of the Applicant to substantiate broader applicability as a specific means of compliance. The topics covered within this specification are: Stalling, Takeoff and Landing Speeds; Takeoff Performance, Distances and Path; Climb; Landing Performance and Distances; Balked Landing.  
1.2 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable civil aviation authorities (CAAs)) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this standard (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to ASTM Committee F44 webpage (www.astm.org/COMMITTEE/F44.htm).  
1.3 Units—This specification may present information in either SI units, English Engineering units, or both. The values stated in each system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used independently of the other, and values from the two systems shall not be combined.  
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 airworthiness design criteria for aeroplane handling characteristics in flight and on ground and water. The applicant for a design approval shall seek the individual guidance of their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
SCOPE
1.1 This specification addresses the airworthiness requirements for aeroplane handling characteristics in flight and on ground and water.  
1.2 The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Normal Category aeroplanes; however, the content may be more broadly applicable, and should not be unduly limited. The topics covered within this specification are: Flight Characteristics, Controllability, Trim, Stability, Ground and Water Handling Characteristics, and Vibration, Buffet, and High-speed Characteristics.  
1.3 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this specification (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to the ASTM Committee F44 web page (www.astm.org/COMMITTEE/F44.htm). Annex A1 maps the Means of Compliance of the ASTM standards to EASA CS-23, amendment 5, or later, and FAA 14 CFR Part 23, amendment 64, or later, rules.  
1.4 Units—This specification may present information in either SI units, English Engineering units, or both; the values stated in each system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used independently of the other, and values from the two systems shall not be combined.  
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 limitations 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 prescribes airworthiness design requirements for the establishment of operating limitations and information for the operation of aeroplanes. It addresses the general limitations and information to be contained in the aeroplane flight manual. The applicant for a design approval shall seek the individual guidance of their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
The requirements described in this specification cover: airspeed limitations, operating maneuvering speed, flap extended speed, minimum control speed, weight and center of gravity, auxiliary power unit limitations, minimum flight crew, maximum passenger seating configuration, kinds of operation, and maximum operating altitude.
SCOPE
1.1 This specification covers airworthiness requirements for establishing general limitations and information to be contained in the aeroplane flight manual. This specification specifies what information shall be provided and does not state how such information shall be presented unless this is necessary for the clarity of the purpose of the specification. Refer to Specification F3117/F3117M for means and methods of presentation. The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Level 1, 2, 3, and 4 Normal Category aeroplanes. The content may be more broadly applicable; it is the responsibility of the applicant to substantiate broader applicability as a specific means of compliance. The topics covered within this specification are: Limitations for Airspeed, Weight and Center of Gravity, Auxiliary Power Units, Minimum Flight Crew, Maximum Passenger Seating Configuration, Kinds of Operation, and Maximum Operating Altitude.  
1.2 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this specification (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to the ASTM Committee F44 web page (www.astm.org/COMMITTEE/F44.htm). Annex A1 maps the Means of Compliance described in this specification to EASA CS-23, amendment 5, or later, and FAA 14 CFR Part 23, amendment 64, or later.  
1.3 Units—This specification may present information in either SI units, English Engineering units, or both; the values stated in each system may not be exact equivalents. Each system shall be used independently of the other; combining values from the two systems may result in nonconformance with the 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
This specification establishes the airworthiness design requirements for low-speed aeroplane flight characteristics. The applicant for a design approval shall seek the individual guidance to their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
This specification is applicable to small aeroplanes and covers departure characteristics, spinning, and stall warning.
SCOPE
1.1 This specification covers the low-speed flight characteristics of fixed-wing aircraft and provides standards for departure characteristics, spinning, and stall warning. The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Normal Category aeroplanes. The content may be more broadly applicable; it is the responsibility of the Applicant to substantiate broader applicability as a specific means of compliance. The topics covered within this specification are: (4.1) Low-Speed Flight Characteristics Score, (4.2) Stall Characteristics, (4.3) Stall Warning, (4.4) Departure Characteristics: Single Engine, (4.5) Departure Characteristics: Multiengine, (4.6) Spinning, and (4.7) Safety-Enhancing Features.  
1.2 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this standard (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to the ASTM Committee F44 webpage (www.astm.org/COMMITTEE/F44.htm).  
1.3 Units—This standard may present information in either SI units, English Engineering units, or both; the values stated in each system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used independently of the other, and values from the two systems shall not be combined.  
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 airworthiness design standards associated with aeroplane flight. The applicant for a design approval shall seek the individual guidance of their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
Included in this specification are general requirements for proof of compliance, load distribution limits, weight limits (minimum and maximum weight), empty weight and corresponding center of gravity, and removable ballast.
SCOPE
1.1 This specification establishes the airworthiness design standards associated with aeroplane weight and center of gravity.  
1.2 The term “aeroplane” is utilized in this specification as it was originally conceived for normal category fixed wing aircraft with a maximum certificated weight of 19 000 lb or less and a passenger seating configuration up to 19 as defined in the Rules. However, these standards may be more broadly applicable and their usage should not be unnecessarily limited.  
1.3 The applicant for a design approval shall seek the individual guidance of their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan. For information on which CAA regulatory bodies have accepted this specification (in whole or in part) as a means of compliance to their small aircraft airworthiness regulations (hereinafter referred to as “the Rules”), refer to ASTM Committee F44 webpage (www.astm.org/COMMITTEE/F44.htm), which includes CAA website links.  
1.4 Units—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.  
1.5 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 limitations 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.

SCOPE
1.1 This specification establishes the airworthiness design standards associated with aeroplane weight and center of gravity.  
1.2 The term “aeroplane” is utilized in this specification as it was originally conceived for normal category fixed wing aircraft with a maximum certificated weight of 19 000 lb or less and a passenger seating configuration up to 19 as defined in the Rules. However, these standards may be more broadly applicable and their usage should not be unnecessarily limited.  
1.3 The applicant for a design approval shall seek the individual guidance of their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan. For information on which CAA regulatory bodies have accepted this specification (in whole or in part) as a means of compliance to their small aircraft airworthiness regulations (hereinafter referred to as “the Rules”), refer to ASTM Committee F44 webpage (www.astm.org/COMMITTEE/F44.htm), which includes CAA website links.  
1.4 Units—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.  
1.5 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 limitations 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.

SCOPE
1.1 This specification covers the airworthiness design standards associated with general aeroplane performance. The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Normal Category aeroplanes. The content may be more broadly applicable; it is the responsibility of the Applicant to substantiate broader applicability as a specific means of compliance. The topics covered within this specification are: Stalling, Takeoff and Landing Speeds; Takeoff Performance, Distances and Path; Climb; Landing Performance and Distances; Balked Landing.  
1.2 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable civil aviation authorities (CAAs)) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this standard (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to ASTM Committee F44 webpage (www.astm.org/COMMITTEE/F44.htm).  
1.3 Units—This specification may present information in either SI units, English Engineering units, or both. The values stated in each system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used independently of the other, and values from the two systems shall not be combined.  
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 provides airworthiness design requirements for general aeroplane performance, and is applicable to small aeroplanes as defined in Terminology F3060. The applicant for a design approval shall seek the individual guidance to their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
Performance requirements cover: stalling and takeoff speeds, takeoff performance, accelerate-stop distance, takeoff path, takeoff distance and takeoff run, takeoff flight path, climb, en route climb/descent, glide, reference landing approach speed, landing distance, and balked landing.
SCOPE
1.1 This specification covers the airworthiness design standards associated with general aeroplane performance. The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Normal Category aeroplanes. The content may be more broadly applicable; it is the responsibility of the Applicant to substantiate broader applicability as a specific means of compliance. The topics covered within this specification are: Stalling, Takeoff and Landing Speeds; Takeoff Performance, Distances and Path; Climb; Landing Performance and Distances; Balked Landing.  
1.2 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable civil aviation authorities (CAAs)) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this standard (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to ASTM Committee F44 webpage (www.astm.org/COMMITTEE/F44.htm).  
1.3 Units—This specification may present information in either SI units, English Engineering units, or both. The values stated in each system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used independently of the other, and values from the two systems shall not be combined.  
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 airworthiness design criteria for aeroplane handling characteristics in flight and on ground and water. The applicant for a design approval shall seek the individual guidance of their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
General requirements address general control forces such as takeoff, climb, level flight and descent; longitudinal control; directional and lateral control; minimum control speed; aerobatic maneuvers; control during landings; elevator control force in maneuvers; trim and stability requirements; ground and water handling characteristics; high speed characteristics; and vibration and buffeting.
SCOPE
1.1 This specification addresses the airworthiness requirements for aeroplane handling characteristics in flight and on ground and water.  
1.2 The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Normal Category aeroplanes; however, the content may be more broadly applicable, and should not be unduly limited. The topics covered within this specification are: Flight Characteristics, Trim Requirements, Stability Requirements, Ground and Water Handling Characteristics, Vibration and Buffet, and High Speed Characteristics.  
1.3 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this specification (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to the ASTM Committee F44 web page (www.astm.org/COMMITTEE/F44.htm). Annex A1 maps the Means of Compliance of the ASTM standards to EASA CS-23, amendment 5, or later, and FAA 14 CFR Part 23, amendment 64, or later, rules.  
1.4 Units—This specification may present information in either SI units, English Engineering units, or both; the values stated in each system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used independently of the other, and values from the two systems shall not be combined.  
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 limitations 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.

SCOPE
1.1 This specification addresses the airworthiness requirements for aeroplane handling characteristics in flight and on ground and water.  
1.2 The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Normal Category aeroplanes; however, the content may be more broadly applicable, and should not be unduly limited. The topics covered within this specification are: Flight Characteristics, Trim Requirements, Stability Requirements, Ground and Water Handling Characteristics, Vibration and Buffet, and High Speed Characteristics.  
1.3 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this specification (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to the ASTM Committee F44 web page (www.astm.org/COMMITTEE/F44.htm).  
1.4 Units—This specification may present information in either SI units, English Engineering units, or both; the values stated in each system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used independently of the other, and values from the two systems shall not be combined.  
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 limitations 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.

SCOPE
1.1 This specification covers the airworthiness design standards associated with general aeroplane performance. The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Normal Category aeroplanes. The content may be more broadly applicable; it is the responsibility of the Applicant to substantiate broader applicability as a specific means of compliance. The topics covered within this specification are: Stalling, Takeoff and Landing Speeds; Takeoff Performance, Distances and Path; Climb; Landing Performance and Distances; Balked Landing.  
1.2 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this standard (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to ASTM Committee F44 webpage (www.astm.org/COMMITTEE/F44.htm).  
1.3 Units—This specification may present information in either SI units, English Engineering units, or both. The values stated in each system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used independently of the other, and values from the two systems shall not be combined.  
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 covers airworthiness requirements for establishing general limitations and information to be contained in the aeroplane flight manual. This specification specifies what information shall be provided and does not state how such information shall be presented unless this is necessary for the clarity of the purpose of the specification. Refer to Specification F3117/F3117M for means and methods of presentation. The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Level 1, 2, 3, and 4 Normal Category aeroplanes. The content may be more broadly applicable; it is the responsibility of the applicant to substantiate broader applicability as a specific means of compliance. The topics covered within this specification are: Limitations for Airspeed, Weight and Center of Gravity, Auxiliary Power Units, Minimum Flight Crew, Maximum Passenger Seating Configuration, Kinds of Operation, and Maximum Operating Altitude.  
1.2 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this specification (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to the ASTM Committee F44 web page (www.astm.org/COMMITTEE/F44.htm).  
1.3 Units—This specification may present information in either SI units, English Engineering units, or both; the values stated in each system may not be exact equivalents. Each system shall be used independently of the other; combining values from the two systems may result in nonconformance with the 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.

SCOPE
1.1 This specification covers the low-speed flight characteristics of fixed-wing aircraft and provides standards for departure characteristics, spinning, and stall warning. The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Normal Category aeroplanes. The content may be more broadly applicable; it is the responsibility of the Applicant to substantiate broader applicability as a specific means of compliance. The topics covered within this specification are: (4.1) Low-Speed Flight Characteristics Score, (4.2) Stall Characteristics, (4.3) Stall Warning, (4.4) Departure Characteristics: Single Engine, (4.5) Departure Characteristics: Multiengine, (4.6) Spinning, and (4.7) Safety-Enhancing Features.  
1.2 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this standard (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to the ASTM Committee F44 webpage (www.astm.org/COMMITTEE/F44.htm).  
1.3 Units—This standard may present information in either SI units, English Engineering units, or both; the values stated in each system may not be exact equivalents. Each system shall be used independently of the other; combining values from the two systems may result in nonconformance with the 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.

SCOPE
1.1 This specification addresses the airworthiness requirements for aeroplane handling characteristics in flight and on ground and water.  
1.2 The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Normal Category aeroplanes; however, the content may be more broadly applicable, and should not be unduly limited. The topics covered within this specification are: Flight Characteristics, Trim Requirements, Stability Requirements, Ground and Water Handling Characteristics, Vibration and Buffet, and High Speed Characteristics.  
1.3 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this specification (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to the ASTM Committee F44 web page (www.astm.org/COMMITTEE/F44.htm).  
1.4 Units—This specification may present information in either SI units, English Engineering units, or both; the values stated in each system may not be exact equivalents. Each system shall be used independently of the other; combining values from the two systems may result in nonconformance with the standard.  
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 limitations 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.

SCOPE
1.1 This specification covers the low-speed flight characteristics of fixed-wing aircraft and provides standards for departure characteristics, spinning, and stall warning. The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Normal Category aeroplanes. The content may be more broadly applicable; it is the responsibility of the Applicant to substantiate broader applicability as a specific means of compliance. The topics covered within this specification are: (4.1) Low-Speed Flight Characteristics Score, (4.2) Stall Characteristics, (4.3) Stall Warning, (4.4) Departure Characteristics: Single Engine, (4.5) Departure Characteristics: Multiengine, (4.6) Spinning, and (4.7) Safety-Enhancing Features.  
1.2 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this standard (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to the ASTM Committee F44 webpage (www.astm.org/COMMITTEE/F44.htm).  
1.3 Units—This standard may present information in either SI units, English Engineering units, or both; the values stated in each system may not be exact equivalents. Each system shall be used independently of the other; combining values from the two systems may result in nonconformance with the 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.

SCOPE
1.1 This specification covers the airworthiness design standards associated with general aeroplane performance. The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Normal Category aeroplanes. The content may be more broadly applicable; it is the responsibility of the Applicant to substantiate broader applicability as a specific means of compliance. The topics covered within this specification are: Stalling, Takeoff and Landing Speeds; Takeoff Performance, Distances and Path; Climb; Landing Performance and Distances; Balked Landing.  
1.2 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this standard (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to ASTM Committee F44 webpage (www.astm.org/COMMITTEE/F44.htm).  
1.3 Units—This specification may present information in either SI units, English Engineering units, or both. The values stated in each system may not be exact equivalents. Each system shall be used independently of the other; combining values from the two systems may result in nonconformance with the 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.

SCOPE
1.1 This specification covers airworthiness requirements for establishing general limitations and information to be contained in the aeroplane flight manual. This specification specifies what information shall be provided and does not state how such information shall be presented unless this is necessary for the clarity of the purpose of the specification. Refer to Specification F3117 for means and methods of presentation. The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Level 1, 2, 3, and 4 Normal Category aeroplanes. The content may be more broadly applicable; it is the responsibility of the applicant to substantiate broader applicability as a specific means of compliance. The topics covered within this specification are: Limitations for Airspeed, Weight and Center of Gravity, Auxiliary Power Units, Minimum Flight Crew, Maximum Passenger Seating Configuration, Kinds of Operation, and Maximum Operating Altitude.  
1.2 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this specification (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to the ASTM Committee F44 web page (www.astm.org/COMMITTEE/F44.htm).  
1.3 Units—This specification may present information in either SI units, English Engineering units, or both; the values stated in each system may not be exact equivalents. Each system shall be used independently of the other; combining values from the two systems may result in nonconformance with the 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.

SCOPE
1.1 This specification establishes the airworthiness design standards associated with aeroplane weight and center of gravity.  
1.2 The term “aeroplane” is utilized in this specification as it was originally conceived for normal category fixed wing aircraft with a maximum certificated weight of 19 000 lb or less and a passenger seating configuration up to 19 as defined in the Rules. However, these standards may be more broadly applicable and their usage should not be unnecessarily limited.  
1.3 The applicant for a design approval shall seek the individual guidance of their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan. For information on which CAA regulatory bodies have accepted this specification (in whole or in part) as a means of compliance to their small aircraft airworthiness regulations (hereinafter referred to as “the Rules”), refer to ASTM Committee F44 webpage (www.astm.org/COMMITTEE/F44.htm), which includes CAA website links.  
1.4 Units—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.  
1.5 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 limitations 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.

SCOPE
1.1 This specification will cover the flight characteristics of fixed-wing aircraft with a certified maximum take-off weight of 8618 kg [19 000 lb] or less and a passenger-seating configuration of up to 19 at low speed and provide standards for departure characteristics, spinning, and stall warning.  
1.2 The term “aeroplane” is utilized in this specification as it was originally conceived for normal category fixed wing aircraft with a maximum certificated weight of 8618 kg [19 000 lb] or less and a passenger seating configuration up to 19 as defined in the Rules. However, these standards may be more broadly applicable and their usage should not be unnecessarily limited.  
1.3 The applicant for a design approval shall seek the individual guidance to their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan. For information on which CAA regulatory bodies have accepted this specification (in whole or in part) as a means of compliance to their Airworthiness Rules (hereinafter referred to as “the Rules”), refer to ASTM Committee F44 webpage (www.astm.org/COMMITTEE/F44.htm), which includes CAA website links.  
1.4 It is the responsibility of the applicant to validate any applicability beyond that identified in this specification and request acceptance from the applicable CAA.  
1.5 Units—Normally, the values stated are SI units followed by U.S. Customary Units in square brackets. 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 nonconformance with the standard. In some cases other units may be used exclusively (such as knots) and no other unit will be identified. This technique should be used sparingly and rationale for its use shall be clear and included in 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, health, and environmental practices and determine the applicability of regulatory limitations prior to use.  
1.7 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 airworthiness requirements for aeroplane handling characteristics in flight and on ground and water.  
1.2 The term “aeroplane” is utilized in this specification as it was originally conceived for normal category fixed wing aircraft with a certified maximum take-off weight of 19 000 lb or less and a passenger seating configuration up to 19 as defined in the Rules. However, this standard may be more broadly applicable.  
1.3 The applicant for a design approval must seek individual guidance from their respective CAA body concerning the use of this specification as part of a certification plan. For information on which CAA regulatory bodies have accepted this specification (in whole or in part) as a means of compliance to their Airworthiness Rules (hereinafter referred to as “the Rules”), refer to the ASTM Committee F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links. It will be the responsibility of the applicant to validate any applicability beyond that identified in this specification and request acceptance from the applicable CAA.  
1.4 Units—Normally, the values stated are SI units followed by US customary units in square brackets. 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 nonconformance with the standard.  
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 limitations 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 provides airworthiness design requirements for general aeroplane performance, and is applicable to small aeroplanes as defined in Terminology F3060. The applicant for a design approval shall seek the individual guidance to their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
Performance requirements cover: stalling and takeoff speeds, takeoff performance, accelerate-stop distance, takeoff path, takeoff distance and takeoff run, takeoff flight path, climb, en route climb/descent, glide, reference landing approach speed, landing distance, and balked landing.
SCOPE
1.1 This specification establishes the airworthiness design standards associated with general aeroplane performance.  
1.2 This specification is applicable to small aeroplanes as defined in Terminology F3060.  
1.3 The applicant for a design approval shall seek the individual guidance to their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan. For information on which CAA regulatory bodies have accepted this specification (in whole or in part) as a means of compliance to their small aircraft airworthiness regulations (hereinafter referred to as “the Rules”), refer to the ASTM Committee F44 webpage (www.astm.org/COMMITTEE/F44.htm) which includes CAA website links.  
1.4 Units—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 nonconformance with the standard.  
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 and health practices and determine the applicability of regulatory limitations prior to use.

ABSTRACT
This specification establishes the airworthiness design requirements for low-speed aeroplane flight characteristics. The applicant for a design approval shall seek the individual guidance to their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
This specification is applicable to small aeroplanes and covers departure characteristics, spinning, and stall warning.
SCOPE
1.1 This specification will cover the flight characteristics of aeroplanes at low speed and provide standards for departure characteristics, spinning, and stall warning.  
1.2 This specification establishes the airworthiness design requirements associated with low-speed aeroplane flight characteristics.  
1.3 The applicant for a design approval shall seek the individual guidance to their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan. For information on which CAA regulatory bodies have accepted this specification (in whole or in part) as a means of compliance to their small aircraft airworthiness regulations (hereinafter referred to as “the Rules”), refer to ASTM Committee F44 webpage (www.astm.org/COMMITTEE/F44.htm), which includes CAA website links.  
1.4 This specification is applicable to small aeroplanes.  
1.5 Units—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 nonconformance 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 limitations prior to use.

ABSTRACT
This specification covers airworthiness design standards associated with aeroplane flight. The applicant for a design approval shall seek the individual guidance of their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
Included in this specification are general requirements for proof of compliance, load distribution limits, weight limits (minimum and maximum weight), empty weight and corresponding center of gravity, and removable ballast.
SCOPE
1.1 This specification establishes the airworthiness design standards associated with aeroplane flight.  
1.2 The applicant for a design approval shall seek the individual guidance of their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan. For information on which CAA regulatory bodies have accepted this specification (in whole or in part) as a means of compliance to their small aircraft airworthiness regulations (hereinafter referred to as “the Rules”), refer to ASTM Committee F44 webpage (www.astm.org/COMMITTEE/F44.htm), which includes CAA website links.  
1.3 Units—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.  
1.4 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 limitations prior to use.

ABSTRACT
This specification prescribes airworthiness design requirements for the establishment of operating limitations and information for the operation of aeroplanes. It addresses the general limitations and information to be contained in the aeroplane flight manual. The applicant for a design approval shall seek the individual guidance of their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
The requirements described in this specification cover: airspeed limitations, operating maneuvering speed, flap extended speed, minimum control speed, weight and center of gravity, auxiliary power unit limitations, minimum flight crew, maximum passenger seating configuration, kinds of operation, and maximum operating altitude.
SCOPE
1.1 This specification establishes the airworthiness design requirements associated with the establishment of operating limitations and information for the operation of aeroplanes. It covers the need for establishing general limitations and information to be contained in the aeroplane flight manual. This specification specifies what information shall be provided and does not state how such information shall be presented unless this is necessary for the clarity of the purpose of the specification. Refer to Specification F3117 for means and methods of presentation.  
1.2 The applicant for a design approval shall seek the individual guidance of their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan. For information on which CAA regulatory bodies have accepted this specification (in whole or in part) as a means of compliance to their small aeroplane airworthiness regulations (hereinafter referred to as “the Rules”), refer to ASTM Committee F44 webpage (www.ASTM.org/COMITTEE/F44.htm), which includes CAA website links.  
1.3 This specification is applicable to small aeroplanes.  
1.4 Units—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.  
1.5 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 and health practices and determine the applicability of regulatory limitations prior to use.

ABSTRACT
This specification covers airworthiness design criteria for aeroplane handling characteristics in flight and on ground and water. The applicant for a design approval shall seek the individual guidance of their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
General requirements address general control forces such as takeoff, climb, level flight and descent; longitudinal control; directional and lateral control; minimum control speed; aerobatic maneuvers; control during landings; elevator control force in maneuvers; trim and stability requirements; ground and water handling characteristics; high speed characteristics; and vibration and buffeting.
SCOPE
1.1 This specification establishes the airworthiness design standards associated with general airplane-handling characteristics in flight and on ground and water.  
1.2 This specification is applicable to aeroplanes.  
1.3 The applicant for a design approval shall seek the individual guidance of their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan. For information on which CAA regulatory bodies have accepted this specification (in whole or in part) as a means of compliance to their small aircraft airworthiness regulations (hereinafter referred to as “the Rules”), refer to the ASTM Committee F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.4 Units—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 nonconformance with the standard.  
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 and health practices and determine the applicability of regulatory requirements prior to use.