F44.40 - Powerplant

ABSTRACT
This specification provides minimum requirements for the control, indication, and operational characteristics of propulsion systems. It was developed based on propulsion system installed on aeroplanes, but may be applicable to other applications. The applicant for a design approval must 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 minimum requirements for the control, indication, and operational characteristics of propulsion systems. It was developed based on propulsion system installed on aeroplanes, but may be applicable to other applications as well.  
1.2 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Aeroplane Airworthiness regulations (Hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links. 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—The values stated are SI units followed by imperial units in brackets. 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 minimum requirements for hazard mitigation in propulsion systems installed on small aeroplanes. The applicant for a design approval must 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 minimum requirements for hazard mitigation in propulsion systems installed on small aeroplanes.  
1.2 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (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 F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.3 Units—The values stated are SI units followed by imperial units in 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 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, 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 airworthiness requirements for the design and installation of electric propulsion systems for aeroplanes. Hybrid-electric propulsion systems are addressed implicitly unless explicitly stated otherwise. This specification was written with the focus on electric propulsion systems with conventional system layout, propulsion characteristics, and operation. The content may be more broadly applicable; it is the responsibility of the applicant to substantiate broader applicability as a specific means of compliance.  
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 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 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 prescribes minimum requirements for the design and integration of Fuel/Energy Storage and Delivery system installations for aeroplanes and is applicable to aeroplanes as defined in the F44 terminology standard. The applicant for a design approval must seek the individual guidance to their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
The requirements provided in this specification cover fuel system, fuel tanks, fuel pumps, fuel flow, pressure fueling systems, and fuel jettisoning system.
SCOPE
1.1 This specification covers minimum requirements for the design and integration of Fuel Storage and Delivery system installations for aeroplanes.  
1.2 This specification is applicable to aeroplanes as defined in the F44 terminology standard.  
1.3 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Aeroplane Airworthiness regulations (Hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMITTEE/F44.htm), which includes CAA website links. 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.  
1.4 Units—The values stated are SI units followed by imperial units in brackets. 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 covers airworthiness requirements for the installation and integration of propeller systems, and is applicable to aeroplanes as defined in F44 terminology standard. The applicant for a design approval must seek the individual guidance to their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
The requirements prescribed in this specification cover: propeller installation aspects (general propeller, feathering propellers, variable-pitch propellers, pusher propeller installation, propeller clearance), structural aspects (propeller vibration and fatigue), propeller control limitations (propeller speed and pitch limits, propeller reversing systems), and associated propeller systems (oil system-propeller feathering systems, turbopropeller-drag limiting systems).
SCOPE
1.1 This specification addresses the airworthiness requirements for the installation and integration of propeller systems.  
1.2 This specification is applicable to aeroplanes as defined in F44 terminology standard.  
1.3 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (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 F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links. 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.  
1.4 Units—The values stated are SI units followed by Imperial units in square brackets. 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.

SIGNIFICANCE AND USE
4.1 This specification provides designers of general aviation aeroplanes a process for evaluating and testing a fuel system under hot weather conditions to ensure safety during flight. The specification is applicable to kerosene-type turbine engine fuels and fuel systems for traditional general aviation aeroplanes.
SCOPE
1.1 This standard practice provides requirements for performing hot weather testing as a means of compliance to Subsection 7.7 of Specification F3063/F3063M for kerosene-type turbine fuels such as Jet A and Jet A-1 (Specification D1655). The appendix provides supplemental information and considerations for turbine fuel system hot weather operation. The material was developed through open consensus of international experts in general aviation.  
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 the ASTM Committee F44 web page (www.astm.org/COMMITTEE/F44.htm).  
1.3 The values stated in either SI units or inch-pound units are to be regarded separately as standard. 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. A specific warning is given in Section 6 on Test Setup.  
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 This practice provides designers of general aviation aeroplanes with a list of previously accepted required powerplant instruments, and a method for the powerplant information to be provided to the crew based on the type of powerplant installation. Criteria for mitigating the need for rate of change, direction of change, and proximity to limits information for some required powerplant instruments is also provided. This practice applies to reciprocating and turbine engine powerplant requirements. This practice provides a method of compliance to Section 6 of Specification F3064/F3064M.
SCOPE
1.1 This standard practice provides the minimum required powerplant instruments, along with information on how that information is provided to the flight crew or pilot of Normal Category Level 1, 2, 3, or 4 aeroplanes. The material was developed through open consensus of international experts in general aviation. This practice does not consider remotely piloted aeroplanes, nor does it consider electric, hydrogen, or hybrid 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.  
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 web page (www.astm.org/COMMITTEE/F44.htm).  
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 provides minimum requirements for the installation and integration of powerplant system units and is applicable to small aeroplanes as defined in the F44 terminology standard. The applicant for a design approval must 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 covers: air induction system for each engine and auxiliary power unit and their accessories, powerplant exhaust system, forced air induction and bleed air systems, oil system, liquid cooling, turbojet and turbofan reversing systems, and powerplant accessories and components. Also specified are tank tests for pressure, vibration, and tank sloshing.
SCOPE
1.1 This specification covers minimum requirements for the installation and integration of powerplant system units.  
1.2 This specification is applicable to small aeroplanes as defined in the F44 terminology standard. Use of the term airplane is used throughout this specification and will mean “small airplane.”  
1.3 The applicant for a design approval shall seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (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 F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.4 References within this standard normally refer to documents in United States legal system. Appendix X1 cross references documents in the legal system of other countries of corresponding content.  
1.5 Units—The values stated are SI units followed by imperial units in brackets. 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.  
1.6 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 airworthiness requirements for the design and installation of electric propulsion systems for aeroplanes. Hybrid-electric propulsion systems are addressed implicitly unless explicitly stated otherwise. This specification was written with the focus on electric propulsion systems with conventional system layout, propulsion characteristics, and operation. The content may be more broadly applicable; it is the responsibility of the applicant to substantiate broader applicability as a specific means of compliance.  
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 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 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 provides minimum requirements for the control, indication, and operational characteristics of propulsion systems. It was developed based on propulsion system installed on aeroplanes, but may be applicable to other applications. The applicant for a design approval must seek the individual guidance to their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
The requirements prescribed in this specification cover engine controls, powerplant operational characteristics and installation, and installation of powerplant instruments, indicators and sensors.
SCOPE
1.1 This specification covers minimum requirements for the control, indication, and operational characteristics of propulsion systems. It was developed based on propulsion system installed on aeroplanes, but may be applicable to other applications as well.  
1.2 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Aeroplane Airworthiness regulations (Hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links. 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—The values stated are SI units followed by imperial units in brackets. 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 addresses the airworthiness requirements for the installation and integration of propeller systems.  
1.2 This specification is applicable to aeroplanes as defined in F44 terminology standard.  
1.3 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (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 F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.4 Units—The values stated are SI units followed by Imperial units in square brackets. 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 minimum requirements for the control, indication, and operational characteristics of propulsion systems. It was developed based on propulsion system installed on aeroplanes, but may be applicable to other applications as well.  
1.2 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Aeroplane Airworthiness regulations (Hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.3 Units—The values stated are SI units followed by imperial units in brackets. 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.

SIGNIFICANCE AND USE
4.1 This practice provides designers of general aviation aeroplanes with a list of previously accepted required powerplant instruments, and a method for the powerplant information to be provided to the crew based on the type of powerplant installation. Criteria for mitigating the need for rate of change, direction of change, and proximity to limits information for some required powerplant instruments is also provided. This practice applies to reciprocating and turbine engine powerplant requirements. This practice provides a method of compliance to Section 6 of Specification F3064/F3064M.
SCOPE
1.1 This standard practice provides the minimum required powerplant instruments along with information on how that information is provided to the flight crew or pilot of Normal Category Level 1, 2, 3, or 4 aeroplanes. The material was developed through open consensus of international experts in general aviation. This practice does not consider remotely piloted aeroplanes, nor does it consider electric or hybrid-electric 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.  
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 web page (www.astm.org/COMMITTEE/F44.htm).  
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 covers minimum requirements for the design and integration of Fuel Storage and Delivery system installations for aeroplanes.  
1.2 This specification is applicable to aeroplanes as defined in the F44 terminology standard.  
1.3 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Aeroplane Airworthiness regulations (Hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.4 Units—The values stated are SI units followed by imperial units in brackets. 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 minimum requirements for the control, indication, and operational characteristics of propulsion systems. It was developed based on propulsion system installed on aeroplanes, but may be applicable to other applications as well.  
1.2 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Aeroplane Airworthiness regulations (Hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.3 Units—The values stated are SI units followed by imperial units in brackets. 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 addresses the airworthiness requirements for the installation and integration of propeller systems.  
1.2 This specification is applicable to aeroplanes as defined in F44 terminology standard.  
1.3 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (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 F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.4 Units—The values stated are SI units followed by Imperial 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 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 minimum requirements for the control, indication, and operational characteristics of propulsion systems. It was developed based on propulsion system installed on aeroplanes, but may be applicable to other applications as well.  
1.2 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Aeroplane Airworthiness regulations (Hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.3 Units—The values stated are SI units followed by imperial units in brackets. 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 addresses airworthiness requirements for the design and installation of electric propulsion systems for aeroplanes. Hybrid-electric propulsion systems are addressed implicitly unless explicitly stated otherwise. This specification was written with the focus on electric propulsion systems with conventional system layout, propulsion characteristics, and operation. The content may be more broadly applicable; it is the responsibility of the applicant to substantiate broader applicability as a specific means of compliance.  
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 web page (www.astm.org/COMMITTEE/F44.htm).  
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 covers minimum requirements for the installation and integration of powerplant system units.  
1.2 This specification is applicable to small aeroplanes as defined in the F44 terminology standard. Use of the term airplane is used throughout this specification and will mean “small airplane.”  
1.3 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (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 F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.4 References within this standard normally refer to documents in United States legal system. Appendix X1 cross references documents in the legal system of other countries of corresponding content.  
1.5 Units—The values stated are SI units followed by imperial units in 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 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, 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 airworthiness requirements for the design and installation of electric propulsion systems for aeroplanes. Hybrid-electric propulsion systems are addressed implicitly unless explicitly stated otherwise. This specification was written with the focus on electric propulsion systems with conventional system layout, propulsion characteristics, and operation. The content may be more broadly applicable; it is the responsibility of the applicant to substantiate broader applicability as a specific means of compliance.  
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 web page (www.astm.org/COMMITTEE/F44.htm).  
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 covers minimum requirements for the design and integration of Fuel/Energy Storage and Delivery system installations for aeroplanes.  
1.2 This specification is applicable to aeroplanes as defined in the F44 terminology standard.  
1.3 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Aeroplane Airworthiness regulations (Hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.4 Units—The values stated are SI units followed by imperial units in 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 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 covers minimum requirements for hazard mitigation in propulsion systems installed on small aeroplanes. The applicant for a design approval must seek the individual guidance to their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
The requirements prescribed in this specification cover: engines (turbine engine installations, engine isolation), powerplant ice protection (induction system icing protection, turbine engines, engine rain hail ice and bird ingestion, etc.), designated fire zones (for reciprocating engine, for turbine engines), fire protection (combustion heater, shutoff means), firewalls, fire detection, fire extinguishing, and flammable fluid fire protection.
SCOPE
1.1 This specification covers minimum requirements for hazard mitigation in propulsion systems installed on small aeroplanes.  
1.2 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (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 F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.3 Units—The values stated are SI units followed by imperial units in 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 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, 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 minimum requirements for the control, indication, and operational characteristics of propulsion systems. It was developed based on propulsion system installed on aeroplanes, but may be applicable to other applications as well.  
1.2 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Aeroplane Airworthiness regulations (Hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.3 Units—The values stated are SI units followed by imperial units in 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 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, 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 minimum requirements for the design and integration of Fuel/Energy Storage and Delivery system installations for aeroplanes.  
1.2 This specification is applicable to aeroplanes as defined in the F44 terminology standard.  
1.3 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Aeroplane Airworthiness regulations (Hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.4 Units—The values stated are SI units followed by imperial units in 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 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 minimum requirements for the control, indication, and operational characteristics of propulsion systems. It was developed based on propulsion system installed on aeroplanes, but may be applicable to other applications as well.  
1.2 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Aeroplane Airworthiness regulations (Hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.3 Units—The values stated are SI units followed by imperial units in 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 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, 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 the installation and integration of propeller systems.  
1.2 This specification is applicable to aeroplanes as defined in F44 terminology standard.  
1.3 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (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 F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.4 Units—The values stated are SI units followed by Imperial 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 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 minimum requirements for the installation and integration of powerplant system units.  
1.2 This specification is applicable to small aeroplanes as defined in the F44 terminology standard. Use of the term airplane is used throughout this specification and will mean “small airplane.”  
1.3 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (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 F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.4 References within this standard normally refer to documents in United States legal system. Appendix X1 cross references documents in the legal system of other countries of corresponding content.  
1.5 Units—The values stated are SI units followed by imperial units in 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 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, 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 covers minimum requirements for hazard mitigation in propulsion systems installed on small aeroplanes.  
1.2 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (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 F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.3 Units—The values stated are SI units followed by imperial units in 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 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, 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 prescribes minimum requirements for the design and integration of Fuel/Energy Storage and Delivery system installations for aeroplanes and is applicable to aeroplanes as defined in the F44 terminology standard. The applicant for a design approval must seek the individual guidance to their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
The requirements provided in this specification cover fuel system, fuel tanks, fuel pumps, fuel flow, pressure fueling systems, and fuel jettisoning system.
SCOPE
1.1 This specification covers minimum requirements for the design and integration of Fuel/Energy Storage and Delivery system installations for aeroplanes.  
1.2 This specification is applicable to aeroplanes as defined in the F44 terminology standard.  
1.3 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Aeroplane Airworthiness regulations (Hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.4 Units—The values stated are SI units followed by imperial units in 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 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 provides minimum requirements for the installation and integration of powerplant system units and is applicable to small aeroplanes as defined in the F44 terminology standard. The applicant for a design approval must 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 covers: air induction system for each engine and auxiliary power unit and their accessories, powerplant exhaust system, forced air induction and bleed air systems, oil system, liquid cooling, turbojet and turbofan reversing systems, and powerplant accessories and components. Also specified are tank tests for pressure, vibration, and tank sloshing.
SCOPE
1.1 This specification covers minimum requirements for the installation and integration of powerplant system units.  
1.2 This specification is applicable to small aeroplanes as defined in the F44 terminology standard. Use of the term airplane is used throughout this specification and will mean “small airplane.”  
1.3 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (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 F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.4 References within this standard normally refer to documents in United States legal system. Appendix X1 cross references documents in the legal system of other countries of corresponding content.  
1.5 Units—The values stated are SI units followed by imperial units in 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 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 limitations prior to use.

SCOPE
1.1 This specification covers minimum requirements for the design and integration of Fuel/Energy Storage and Delivery system installations for aeroplanes.  
1.2 This specification is applicable to aeroplanes as defined in the F44 terminology standard.  
1.3 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Aeroplane Airworthiness regulations (Hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.4 Units—The values stated are SI units followed by imperial units in 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 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.

SCOPE
1.1 This specification covers minimum requirements for the design and integration of Fuel/Energy Storage and Delivery system installations for aeroplanes.  
1.2 This specification is applicable to aeroplanes as defined in the F44 terminology standard.  
1.3 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Aeroplane Airworthiness regulations (Hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.4 Units—The values stated are SI units followed by imperial units in 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 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.

SCOPE
1.1 This specification covers minimum requirements for the installation and integration of powerplant system units.  
1.2 This specification is applicable to small aeroplanes as defined in the F44 terminology standard. Use of the term airplane is used throughout this specification and will mean “small airplane”.  
1.3 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (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 F44 webpage (http://www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.4 References within this standard normally refer to documents in United States legal system. Appendix X1 cross references documents in the legal system of other countries of corresponding content.  
1.5 Units—The values stated are SI units followed by imperial units in 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 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 limitations prior to use.

ABSTRACT
This specification provides minimum requirements for the control, indication, and operational characteristics of propulsion systems. It was developed based on propulsion system installed on aeroplanes, but may be applicable to other applications. The applicant for a design approval must seek the individual guidance to their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
The requirements prescribed in this specification cover engine controls, powerplant operational characteristics and installation, and installation of powerplant instruments, indicators and sensors.
SCOPE
1.1 This specification covers minimum requirements for the control, indication, and operational characteristics of propulsion systems. It was developed based on propulsion system installed on aeroplanes, but may be applicable to other applications as well.  
1.2 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Aeroplane Airworthiness regulations (Hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.3 Units—The values stated are SI units followed by imperial units in 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 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 covers airworthiness requirements for the installation and integration of propeller systems, and is applicable to aeroplanes as defined in F44 terminology standard. The applicant for a design approval must seek the individual guidance to their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
The requirements prescribed in this specification cover: propeller installation aspects (general propeller, feathering propellers, variable-pitch propellers, pusher propeller installation, propeller clearance), structural aspects (propeller vibration and fatigue), propeller control limitations (propeller speed and pitch limits, propeller reversing systems), and associated propeller systems (oil system-propeller feathering systems, turbopropeller-drag limiting systems).
SCOPE
1.1 This specification addresses the airworthiness requirements for the installation and integration of propeller systems.  
1.2 This specification is applicable to aeroplanes as defined in F44 terminology standard.  
1.3 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (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 F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.4 Units—The values stated are SI units followed by Imperial 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 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 minimum requirements for hazard mitigation in propulsion systems installed on small aeroplanes. The applicant for a design approval must seek the individual guidance to their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
The requirements prescribed in this specification cover: engines (turbine engine installations, engine isolation), powerplant ice protection (induction system icing protection, turbine engines, engine rain hail ice and bird ingestion, etc.), designated fire zones (for reciprocating engine, for turbine engines), fire protection (combustion heater, shutoff means), firewalls, fire detection, fire extinguishing, and flammable fluid fire protection.
SCOPE
1.1 This specification covers minimum requirements for hazard mitigation in propulsion systems installed on small aeroplanes.  
1.2 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (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 F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.3 Units—The values stated are SI units followed by imperial units in 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 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.