This specification establishes the airworthiness design requirements for low-speed aeroplane flight characteristics. The applicant for a design approval shall seek the individual guidance to their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.This specification is applicable to small aeroplanes and covers departure characteristics, spinning, and stall warning.1.1 This specification covers the low-speed flight characteristics of fixed-wing aircraft and provides standards for departure characteristics, spinning, and stall warning. The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Normal Category aeroplanes. The content may be more broadly applicable; it is the responsibility of the Applicant to substantiate broader applicability as a specific means of compliance. The topics covered within this specification are: (4.1) Low-Speed Flight Characteristics Score, (4.2) Stall Characteristics, (4.3) Stall Warning, (4.4) Departure Characteristics: Single Engine, (4.5) Departure Characteristics: Multiengine, (4.6) Spinning, and (4.7) Safety-Enhancing Features.1.2 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this standard (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to the ASTM Committee F44 webpage (www.astm.org/COMMITTEE/F44.htm).1.3 Units—This standard may present information in either SI units, English Engineering units, or both; the values stated in each system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used independently of the other, and values from the two systems shall not be combined.1.4 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.1.5 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.

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1.1 This specification provides the minimum requirements for an Unmanned Aircraft Flight Manual (UFM) for an unmanned aircraft system (UAS) designed, manufactured, and operated in the light UAS category as defined by a Civil Aviation Authority (CAA). Depending on the size and complexity of the UAS, an UFM may also contain the instruction for maintenance and continuing airworthiness for owner / operator authorized maintenance. This document has been purposefully designed within the broader context of the Committee F38 library. Although the original source materials for the content presented here were intended to function as standalone documents, the committee has consciously removed any redundant information in favor of adopting a referential "single-source-of-truth" approach. Consequently, when applying this standard, it is essential to consider and integrate all relevant Committee F38 standards to ensure its comprehensive and accurate implementation.1.2 When intending to utilize the information provided in this document as a Means of Compliance for operational or design approval, or both, it is crucial to consult with the respective oversight authority (for example, CAA) regarding its acceptable use and application. To find out 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"), please refer to the Committee F38 webpage (www.ASTM.org/COMMITTEE/F38.htm).1.3 This specification defines the UFM information that shall be provided by the manufacturer of a UAS as part of the initial sale or transfer to an end user.1.4 This specification applies to a UAS seeking a CAA approval, in the form of airworthiness certificates, type certificates, flight permits, or other like documentation as a UAS, in the configuration specified in the UFM delivered with the system.1.5 Any modifications that invalidate or otherwise affect the accuracy of UFM operating instructions shall be approved by the manufacturer and communicated to the regulatory authority in the certificate / permit application.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.

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Safe operation of the unmanned aircraft is of the primary importance to the unmanned aircraft industry and for successful integration of unmanned aircraft with manned aircraft in civil airspace. Operators and pilots-in-command of unmanned aircraft systems shall comply with applicable Federal Aviation Regulations (14 CFR Part 43, 14 CFR Part 71, 14 CFR Part 73, 14 CFR Part 91, 14 CFR Part 93, and 14 CFR Part 99). This standard includes the minimum additional methods that should be followed by unmanned aircraft system operators, including pilots-in-command, on every visual range flight to ensure the safe operation of the aircraft and safety of people and property in the air and on the ground. This visual range flight operation standard shall be used in conjunction with appropriate unmanned aircraft system airworthiness and pilot qualification standards.1.1 This practice prescribes guidelines that govern the visual flight operation of unmanned aircraft systems in civil airspace in order to provide for the safe integration of unmanned aircraft flight operations with manned aircraft flight operations.1.2 This practice applies to those operations conducted for civil purposes other than sport or recreation that remain within the visual range of the pilot in command (see Terminology F 2395 for a definition of "visual range").1.3 This practice complies with the known rules, regulations, and public law available at the time of its publication. Should any conflict with a rule, regulation, or public law arise, the user must comply with rule and should notify ASTM of the conflict.This practice only prescribes accepted methods for visual range flight operation of unmanned aircraft systems.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.

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4.1 The guide is intended to be used to assess competencies of qualified individuals who wish to become certified as an FHSS technician through a certification 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.1.1 The purpose of this guide is to address the basic fundamental subject knowledge activities and functions for avionics professionals to be titled Flight Hazard and Surveillance Systems (FHSS) Technicians.1.2 This guide does not cover weather detection and avoidance systems. These systems will be addressed in a future Aircraft Electronics Technician (AET) endorsement standard.1.3 This guide is the basis for the FHSS certification, an endorsement to the AET certification. Candidates must be a certified AET to take the certification exam associated with this guide.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.

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4.1 Demonstration plans developed in accordance with this practice will include all necessary content and key considerations to support an effective flight demonstration program aimed at approval or certification of UAS by the FAA through D&R demonstration.4.2 This practice does not address planning requirements for UAS development testing. It is assumed that a manufacturer has completed all UAS design and development and is preparing demonstration programs to support compliance demonstration on a stable and controlled system configuration. Manufacturers who wish to prepare a detailed design and development program should review Specification F3298 for programmatic examples.4.3 This practice is intended to be used on low-risk UAS that meet the following design criteria and operating limitations.4.3.1 The UAS has a command and control link that enables the pilot-in-command to take contingency action.4.3.2 The unmanned aircraft (UA) has a kinetic energy of ≤25 000 ft-lb calculated in accordance with methods specified within the MOC.4.3.3 The UA is operated ≤400 ft above ground level (AGL).4.3.4 No operations over open-air assemblies (operations over people are acceptable).4.3.5 No flight into known icing.4.3.6 Maximum of 20:1 aircraft to pilot ratio.4.3.7 The UA is electrically powered (excludes internal combustion engines and fuel cells).1.1 This standard practice is intended for low-risk UAS seeking type certification by the Federal Aviation Administration (FAA) under 14 CFR Part 21.17(b) in accordance with the FAA durability and reliability (D&R) means of compliance (MOC). The definition of “low-risk UAS” does not necessarily align with other definitions found within corresponding ASTM standards (F3442/F3442M) or other UAS-related standards. For the purposes of this practice, “low-risk” is defined as a UAS operated in accordance with the concept of operations (CONOPs), eligibility criteria, and kinetic energy threshold specified in the G-1 Issue Paper (which will be provided to the applicant by the FAA). See 4.3 for design criteria and operating limitations for low-risk UAS.1.2 This standard practice establishes a common methodology and key considerations for the development of minimum flight plans for low-risk UAS that demonstrate aircraft reliability as part of a D&R MOC.1.3 The scope of this standard practice encompasses D&R planning, data collection, and reporting.1.4 The values stated in SI units are to be regarded as standard. This is not intended to limit the systems of units used for design, development testing, or demonstration testing. However, the units of measurement used on pilot-facing placards and markings and manuals must be the same as those used on the corresponding equipment with recognition that international aviation utilizes feet for altitude and knots for airspeed as operational parameters.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.

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1.1 This specification covers international standards for the flight recording aspects of airworthiness and design for “small” aircraft.1.2 The applicant for a design approval must seek the individual guidance of their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan. For information on which CAA regulatory bodies have accepted this specification (in whole or in part) as a means of compliance to their Small Aircraft Airworthiness regulations (hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMMITTEE/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 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.

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This specification applies to the flight control aspects of airworthiness and design for "small" aircraft. It establishes the Aircraft Type Code (ATC) compliance matrix based on airworthiness 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. The requirements established by this specification for manual flight control cover control surface installation, operation and arrangement, control system stops, trim systems, control system locks, limit load static tests, operation tests, control system details, spring devices, cable systems, wing flap controls, wing flap position, and flap interconnection. Requirements for automatic flight control cover automatic pilot systems, stability augmentation, and artificial stall barrier system.1.1 This specification covers international standards for the flight control aspects of airworthiness and design for “small” aircraft.1.2 The applicant for a design approval must seek the individual guidance of their respective CAA body concerning the use of this specification as part of a certification plan. For information on which CAA regulatory bodies have accepted this specification (in whole or in part) as a means of compliance to their Small Aircraft Airworthiness regulations (hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMMITTEE/F44.htm) which includes CAA website links. Annex A1 maps the Means of Compliance described in this Standard to EASA CS 23, amendment 5, or later, and FAA 14 CFR 23, amendment 64, or later.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.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.

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