49.050 - Aerospace engines and propulsion systems

Standard Guide for Aerospace/Aviation Powerplant Personnel Certification

ASTM F3599-23(Guide)

SIGNIFICANCE AND USE
4.1 The guide is intended to be used to assess competencies of qualified individuals who wish to become certified as a Powerplant Technician through any certified program.
4.2 The guide is intended to be used in concert with a certification provider’s structure and materials for management, exam delivery, and candidate preparation.
4.3 Each section is categorized into theory, inspection, maintenance/service, troubleshooting, repair, and overhaul with each of these categories having a relevant competency level assigned (reference Table 1).
SCOPE
1.1 The purpose of this guide is to address the basic fundamental subject knowledge, task performance, and task knowledge activities and functions for power plants professionals.
1.2 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.
1.3 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.

Guide
9 pages
English language
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31-Aug-2023
49.020
49.050
F46

ASTM F3066/F3066M-23(Specification)

Standard Specification for Aircraft Powerplant Installation Hazard Mitigation

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.

Technical specification
7 pages
English language
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Technical specification
7 pages
English language
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31-May-2023
49.050
F44

ASTM F2840-14(2023)(Practice)

Standard Practice for Design and Manufacture of Electric Propulsion Units for Light Sport Aircraft

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

Standard
6 pages
English language
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31-Dec-2022
49.050
F37

ASTM F3005-22(Specification)

Standard Specification for Batteries for Use in Small Unmanned Aircraft Systems (sUAS)

ABSTRACT
This standard specifies the requirements for batteries used in small Unmanned Aircraft Systems (sUAS). It covers the standard terminology for sUAS as well as the requirements with respect to cells, mechanical design and assembly, electrical design, and maintenance of the pack and the recording of maintenance data.
SCOPE
1.1 This standard defines the requirements for batteries used in small Unmanned Aircraft Systems (sUAS).
1.2 This standard does not define requirements for the systems in which sUAS battery packs may be utilized.
1.3 This standard is subordinate to Specification F2910.
1.4 If allowed by a nation’s GAA, certain sUAS may be exempt from this standard and may use commercial off-the-shelf (COTS) batteries in non-safety-critical payloads (lithium chemistries may not be exempted). Air transport regulations still shall be adhered to when air transport is used for COTS cells or batteries in bulk.
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.

Technical specification
5 pages
English language
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Technical specification
5 pages
English language
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30-Sep-2022
49.050
F38

ASTM F2506-22(Specification)

Standard Specification for Design and Testing of Light Sport Aircraft Propellers

ABSTRACT
This specification covers the establishment of the minimum requirements for the design, testing, and quality assurance of fixed-pitch or ground adjustable propellers for light sport aircraft. The propeller may not have design features that have been shown to be hazardous or unreliable unless the suitability of each questionable design detail or part can be established by tests. Strength testing; stress measurement, fatigue strength, and fatigue analysis, endurance testing, and teardown inspection shall be performed to meet the requirements prescribed.
SCOPE
1.1 This specification covers the establishment of the minimum requirements for the design, testing, and quality assurance of fixed-pitch or ground adjustable propellers for light sport aircraft. These propellers are used on light aircraft, and could be used with engines conforming to Practice F2339.
1.1.1 When applying the additions provided in Appendix X1, this specification also covers the establishment of the minimum requirements for the design, testing and quality assurance of in-flight adjustable propellers for light-sport aircraft.
1.2 This specification is intended for use by manufacturers of propellers for light sport aircraft.
1.3 This specification does not address the airframe installation requirements for propellers.
1.4 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and to determine the applicability of regulatory limitations prior to use.
1.5 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.

Technical specification
5 pages
English language
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30-Sep-2022
49.050
F37

ASTM F3239-22a(Specification)

Standard Specification for Aircraft Electric Propulsion Systems

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.

Technical specification
9 pages
English language
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Technical specification
9 pages
English language
sale 15% off

31-Aug-2022
49.050
49.060
F44

Standard Practice for Radiographic Examination of Advanced Aero and Turbine Materials and Components

ASTM E2104-22(Practice)

SIGNIFICANCE AND USE
4.1 The requirements for radiographic examination in this practice are applicable to all types of metallic and nonmetallic material used in designated applications such as gas turbines and flight structures.
4.2 This practice establishes the basic parameters for the application and control of the radiographic process. This practice may be specified on an engineering drawing, specification, or contract; however, it is not a detailed radiographic technique and must be supplemented. Section 7 and Practices E1030/E1030M and E1032 contain information to help develop detailed radiographic techniques.
SCOPE
1.1 This practice establishes the minimum requirements for radiographic examination of metallic and nonmetallic materials and components used in designated applications such as gas turbine engines and flight structures.
1.2 The requirements in this practice are intended to control the radiographic process to ensure the quality of radiographic images produced for use in designated applications such as gas turbine engines and flight structures; this practice is not intended to establish acceptance criteria for material or components. When examination is performed in accordance with this practice, engineering drawings, specifications, or other applicable documents shall indicate the acceptance criteria.
1.3 All areas of this practice may be open to agreement between the cognizant engineering organization and the supplier, or specific direction from the cognizant engineering organization.
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.

Standard
11 pages
English language
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Standard
11 pages
English language
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31-May-2022
49.050
E07

ASTM D7685-11(2022)(Practice)

Standard Practice for In-Line, Full Flow, Inductive Sensor for Ferromagnetic and Non-ferromagnetic Wear Debris Determination and Diagnostics for Aero-Derivative and Aircraft Gas Turbine Engine Bearings

SIGNIFICANCE AND USE
4.1 This practice is intended for the application of in-line, full-flow inductive wear debris sensors. According to (1), passing the entire lubrication oil flow for aircraft and aero-derivative gas turbines through a debris-monitoring device is a preferred approach to ensure sufficient detection efficiency.
4.2 Periodic sampling and analysis of lubricants have long been used as a means to determine overall machinery health (2). The implementation of smaller oil filter pore sizes for machinery operating at higher rotational speeds and energies has reduced the effectiveness of sampled oil analysis for determining abnormal wear prior to severe damage. In addition, sampled oil analysis for equipment that is remote or otherwise difficult to monitor or access is not practical. For these machinery systems, in-line wear debris sensors can be very useful to provide real-time and near-real-time condition monitoring data.
4.3 In-line full-flow inductive debris sensors have demonstrated the capability to detect and quantify both ferromagnetic and non-ferromagnetic metallic wear debris. These sensors record metallic wear debris according to size, count, and type (ferromagnetic or non-ferromagnetic). Sensors are available for a variety of oil pipe sizes. The sensors are designed specifically for the protection of rolling element bearings and gears in critical machine applications. Bearings are key elements in machines since their failure often leads to significant secondary damage that can adversely affect safety, operational availability, or operational/maintenance costs, or a combination thereof.
4.4 The main advantage of the sensor is the ability to detect early bearing damage and to quantify the severity of damage and rate of progression of failure towards some predefined bearing surface fatigue damage limiting wear scar. Sensor capabilities are summarized as follows:
4.4.1 In-line full flow non-intrusive inductive metal detector with no moving parts.
4.4.2 Det...
SCOPE
1.1 This practice covers the minimum requirements for an in-line, non-intrusive, through-flow oil debris monitoring system that monitors ferromagnetic and non-ferromagnetic metallic wear debris from both industrial aero-derivative and aircraft gas turbine engine bearings. Gas turbine engines are rotating machines fitted with high-speed ball and roller bearings that can be the cause of failure modes with high secondary damage potential.  (1)2
1.2 Metallic wear debris considered in this practice range in size from 120 μm (micron) and greater. Metallic wear debris over 1000 μm are sized as over 1000 μm.
1.3 This practice is suitable for use with the following lubricants: polyol esters, phosphate esters, petroleum industrial gear oils and petroleum crankcase oils.
1.4 This practice is for metallic wear debris detection, not cleanliness.
1.5 The values stated in SI units are to be regarded as standard. The values given in parentheses are provided for information only.
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.

Standard
16 pages
English language
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31-Mar-2022
49.050
D02

ASTM F3063/F3063M-21(Specification)

Standard Specification for Aircraft Fuel Storage and Delivery

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.

Technical specification
14 pages
English language
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Technical specification
14 pages
English language
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31-Aug-2021
49.050
F44

ASTM F3338-21(Specification)

Standard Specification for Design of Electric Engines for General Aviation Aircraft

SCOPE
1.1 This specification covers minimum requirements for the design of electric engines.
1.2 Distributed propulsion is not excluded; however, additional requirements will be needed to address the additional issues that distributed propulsion can create. Some of those issues may include: use of a common motor controller/inverter, segregated electric harnesses, cooling systems, electric power supplies, and others.
1.3 This specification does not address all of the requirements that may be necessary for possible hybrid configurations where an electric engine and a combustion engine drive a common thruster. This specification may be used for the electric engine aspects with supplemental requirements for the thruster and the combustion engine.
1.4 Although this specification does not include specific requirements for electric engines that include gearboxes, thrusters, or any energy storage systems, it also does not preclude such capabilities. This specification may be used for the base electric engine aspects of the design, with supplemental requirements for any additional features prepared by the manufacturer and submitted to the Civil Airworthiness Authority for acceptance. This version of this ASTM specification also does not address all of the requirements necessary for configurations of motor driven ducted-fans. It is anticipated that the fan would be subject to parts of 14 CFR 33 or CS-E and/or 14 CFR 35 or CS-P, or equivalent, in particular blade-off and bird strike. These would be conducted on the fan as a unit (including motor) rather than on motor or fan alone.
1.5 The applicant for a design approval should 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 general aviation aircraft airworthiness regulations (hereinafter referred to as “the Rules”), refer to ASTM Committee F39 webpage (www.ASTM.org/COMITTEE/F39.htm), which includes CAA website links.
1.6 When applicable, this specification may be used for electric engines with a fixed-pitch propeller or fan. These configurations may be type-certificated as an electric engine including a thruster. There may be additional requirements not currently included in this specification for this type configuration. In addition, 5.25 is included as a test requirement for the electric engine. That section recognizes that when the electric engine does not have an integral thruster it will need to be tested with a representative load on the drive shaft to ensure the engine’s ability to operate properly with static and dynamic loads.
1.7 The values stated in inch-pound units are to be regarded as standard. The values given in parentheses are mathematical conversions to SI units that are provided for information only and are not considered standard.
1.8 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.
1.9 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.

Technical specification
13 pages
English language
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Technical specification
13 pages
English language
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31-Jul-2021
49.050
F39

ASTM F3065/F3065M-21a(Specification)

Standard Specification for Aircraft Propeller System Installation

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.

Technical specification
7 pages
English language
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Technical specification
7 pages
English language
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30-Apr-2021
49.050
F44

Standard Practice for Powerplant Instruments

ASTM F3432-20a(Practice)

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.

Standard
7 pages
English language
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Standard
7 pages
English language
sale 15% off

31-Oct-2020
49.050
F44

ASTM F3062/F3062M-20(Specification)

Standard Specification for Aircraft Powerplant Installation

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.

Technical specification
11 pages
English language
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Technical specification
11 pages
English language
sale 15% off

31-May-2020
49.050
F44

ASTM F3316/F3316M-19(Specification)

Standard Specification for Electrical Systems for Aircraft with Electric or Hybrid-Electric Propulsion

ABSTRACT
This specification applies to the electrical systems, electrical equipment, and electrical power distribution aspects of airworthiness and design for aircraft with electric or hybrid-electric propulsion. Developed through open consensus of international experts in general aviation, this material focused on Normal Category Airplanes. The content may be more broadly applicable; it is the responsibility of the applicant to substantiate broader applicability as a specific means of compliance.
This specification establishes the Aircraft Type Code (ATC) compliance matrix based on certification level, number of engines, type of engine(s), stall speed, cruise speed, meteorological conditions, altitude, and maneuvers. An ATC is defined by taking into account both the technical considerations regarding the design of the aircraft and the airworthiness level established based upon risk-based criteria. Requirements for electrical systems for electric propulsion cover power source capacity and distribution, electrical systems and equipment, circuit protective devices, master switch arrangement, switches, electrical cables and equipment, electrical system fire protection, electronic equipment, and storage battery design and installation.
SCOPE
1.1 This specification covers the electrical systems, electrical equipment, and electrical power distribution aspects of airworthiness and design for aircraft with Electric or Hybrid-Electric Propulsion. This specification was written with the focus on electric propulsion systems with conventional system layout, characteristics, and operation. This specification does not address all of the requirements that may be necessary for possible hybrid-electric configurations where an EPU and a combustion engine are used in combination to provide propulsion. The use of this specification combined with the applicable portions of Specification F3231/F3231M may be necessary for hybrid-electric configurations. This material was developed through open consensus of international experts in general aviation. This material 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.
1.2 An applicant intending to propose this information as a means of compliance for design approval shall 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 a Means of Compliance to their regulatory requirements (Hereinafter referred to as “the Rules”), refer to ASTM 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.

Technical specification
7 pages
English language
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Technical specification
7 pages
English language
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31-Oct-2019
49.050
49.060
F44

ASTM F2538-07a(2019)(Practice)

Standard Practice for Design and Manufacture of Reciprocating Compression Ignition Engines for Light Sport Aircraft

SIGNIFICANCE AND USE
3.1 This practice provides designers and manufacturers of engines for light sport aircraft design references and criteria to use in designing and manufacturing engines.
3.2 Declaration of compliance is based on testing and documentation during the design and testing or flight-testing of the engine type by the manufacturer or under the manufacturer's guidance.
SCOPE
1.1 This practice covers minimum requirements for the design and manufacture of reciprocating compression ignition engines for light sport aircraft, Visual Flight Rules (VFR) use.
1.2 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.
1.3 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.

Standard
4 pages
English language
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31-Dec-2018
49.050
F37

Specification for hose couplings for petrol, oil and lubricants - High pressure couplings

CEN/TS 16650:2014(Main)

SIST-TS CEN/TS 16650:2014

This Technical Specification specifies requirements for couplings of 2 in (50,8 mm), 2½ in (63,5 mm), 3 in (76,2 mm) and 4 in (101,6 mm) nominal sizes with ribbed tails and hexagons for use at pressures not exceeding 1 550 kN/m2 (225 lbf/in2). For assembly of coupling, see Figure 1.
This document is applicable to couplings which have been designed primarily for aircraft refuelling purposes, but they may also be used for other general purposes.

Technical specification
9 pages
English language
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1 day

Aerospace series - Cable outlet accessories for circular and rectangular electrical and optical connectors - Part 025: Cable outlet, style A, straight, unsealed, with cable tie strain relief for EN 3646 - Product standard

EN 3660-025:2013(Main)

SIST EN 3660-025:2014

This European Standard defines a range of cable outlets, straight, style A, for use under the following conditions:
Associated electrical connector(s)   :   EN 3660-002
Temperature range,   Class A   :   - 65 °C to 200 °C
   Class N   :   - 65 °C to 200 °C
   Class W   :   - 65 °C to 175 °C

Standard
11 pages
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1 day

08-Jan-2013
30-Jul-2013
49.050
49.060
ASD-STAN

Aerospace series - Identification marking methods for engine items - Engineering requirements

EN 4301:2009(Main)

SIST EN 4301:2009

This standard describes the coding system for marks, the processes used to produce these marks, as well as the general marking requirements for the identification of aerospace engine items.
This document is applicable to items whose engineering drawing or design folder refers to EN 4301 for all issues that are not in contradiction with specific indications appearing on the engineering drawing or in the design folder.
This document is not applicable to items requiring an identification plate.

Standard
21 pages
English language
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10-Mar-2009
29-Sep-2009
49.050
ASD-STAN

SIST

SIST EN 4301:2009(Main)

Aerospace series - Identification marking methods for engine items - Engineering requirements

EN 4301:2009

Standard
21 pages
English language
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02-Apr-2009
49.050
I13

Aerospace series - Identification marking of engine items - Design standard

EN 4300:2008(Main)

SIST EN 4300:2008

This standard:
-   describes the location and the layout of the marks of the item;
-   describes the marking processes to be used according to the environment and the function of the items;
-   determines the selection conditions of the marks;
-   determines the compatibility conditions of the marking processes with the constitution, the production and the use of the items.
This document applies to aerospace engine items and shall be used in conjunction with EN 4301.

Standard
18 pages
English language
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1 day

15-Apr-2008
30-Oct-2008
49.050
ASD-STAN

SIST

SIST EN 4300:2008(Main)

Aerospace series - Identification marking of engine items - Design standard

EN 4300:2008

Standard
18 pages
English language
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1 day

25-May-2008
49.050
I13

Aircraft - Pressure refuelling connections

ISO 45:1990(Main)

Specifies the basic dimensions and access clearance. The basic dimensions shall be as specified in figure 1. The clearance allowed around the connector shall be in accordance with figure 2.

Standard
4 pages
English language
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Standard
4 pages
French language
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Standard Practice for Design and Manufacture of Reciprocating Spark Ignition Engines for Unmanned Aircraft Systems (Withdrawn 2014)

ASTM F2689-08(Practice)

SIGNIFICANCE AND USE
This practice provides designers and manufacturers of engines for unmanned aircraft systems design requirements and criteria to use in designing and manufacturing engines.
Declaration of compliance is based on testing and documentation during the design and testing or flight testing of the engine type by the manufacturer or under the manufacturers' guidance.
Compliance with this specification is intended to demonstrate an adequate level of reliability in accordance with the UAS safety objectives.
SCOPE
1.1 This practice covers minimum requirements for the design and manufacture of reciprocating spark ignition engines for unmanned aircraft systems.
1.2 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatory limitations prior to use.
WITHDRAWN RATIONALE
This practice covers minimum requirements for the design and manufacture of reciprocating spark ignition engines for unmanned aircraft systems.
Formerly under the jurisdiction of Committee F38 on Unmanned Aircraft Systems, this practice was withdrawn without replacement in May 2014 due to its being too general for practical application.

Standard
3 pages
English language
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31-Jul-2008
10-Jun-2014
49.050
F38

Standard Practice for Design and Manufacture of Reciprocating Compression Ignition Engines for Unmanned Aircraft Systems (Withdrawn 2014)

ASTM F2667-07(Practice)

SCOPE
1.1 This practice covers minimum requirements for the design and manufacture of reciprocating compression ignition engines for unmanned aircraft systems use.
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.
WITHDRAWN RATIONALE
This practice covers minimum requirements for the design and manufacture of reciprocating compression ignition engines for unmanned aircraft systems use.
Formerly under the jurisdiction of Committee F38 on Unmanned Aircraft Systems, this practice was withdrawn without replacement in May 2014 due to its being too general for practical application.

Standard
3 pages
English language
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30-Jun-2007
09-Jun-2014
49.050
F38

Standard Practice for Design and Manufacture of Turbine Engines for Unmanned Aircraft System (Withdrawn 2014)

ASTM F2612-07(Practice)

SCOPE
1.1 This practice covers minimum requirements for the design and manufacture of turbine engines for unmanned aircraft systems.
1.2 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatory limitations prior to use.
WITHDRAWN RATIONALE
This practice covers minimum requirements for the design and manufacture of turbine engines for unmanned aircraft systems.
Formerly under the jurisdiction of Committee F38 on Unmanned Aircraft Systems, this practice was withdrawn without replacement in May 2014 due to its limited practicality.

Standard
3 pages
English language
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31-Mar-2007
15-May-2014
49.050
F38

Aircraft - Pressure fuel dispensing system - Test procedure and limit value for shut-off surge pressure

ISO 4153:1981(Main)

Includes a standard method for testing. The method specified and the limit value apply to all ground systems, fixed and mobile. Also, because these both are standardized, necessary knowledge is provided for aiding proper design of the aircraft fill control valve shut-off characteristics.

Standard
4 pages
English language
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Standard
4 pages
French language
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31-Oct-1981
49.050
49.100
ISO/TC 20

Aircraft - Pressure refuelling connections

ISO 45:1980(Main)

Standard
4 pages
English language
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Standard
4 pages
French language
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30-Apr-1980
30-Apr-1980
49.050
49.100
ISO/TC 20/SC 10