1、Designation: F2908 14F2908 16Standard Specification forAircraft Flight Manual (AFM) for a Small Unmanned AircraftSystem (sUAS)1This standard is issued under the fixed designation F2908; the number immediately following the designation indicates the year oforiginal adoption or, in the case of revisio
2、n, the year of last revision. A number in parentheses indicates the year of last reapproval. Asuperscript epsilon () indicates an editorial change since the last revision or reapproval.1. Scope1.1 This specification provides the minimum requirements for an Aircraft Flight Manual (AFM) for an unmanne
3、d aircraftsystem (UAS) designed, manufactured, and operated in the small UAS (sUAS) category as defined by a nations Governing CivilAviation Authority (GAA).(CAA). Depending on the size and complexity of the sUAS, an AFM may also contain the instructionfor maintenance and continuing airworthiness fo
4、r owner / operator authorized maintenance.1.2 This specification defines the AFM information that shall be provided by the manufacturer of a sUAS as part of the initialsale or transfer to an end user.1.3 This specification applies to a sUAS seeking a nations GAA CAA approval, in the form of flight c
5、ertificates, airworthinesscertificates, type certificates, flight permits, or other like documentation as a sUAS, in the configuration specified in the AFMdelivered with the system.1.4 Any modifications that invalidate or otherwise affect the accuracy of AFM operating instructions shall be approved
6、by themanufacturer and communicated to the regulatory authority in the certificate / permit application.2. Referenced Documents2.1 ASTM Standards:2F2909 Practice for Maintenance and Continued Airworthiness of Small Unmanned Aircraft Systems (sUAS)F2910 Specification for Design, Construction, and Tes
7、t of a Small Unmanned Aircraft System (sUAS)F2911 Practice for Production Acceptance of a Small Unmanned Aircraft System (sUAS)F3002 Specification for Design of the Command and Control System for Small Unmanned Aircraft Systems (sUAS)F3003 Specification for Quality Assurance of a Small Unmanned Airc
8、raft System (sUAS)F3005 Specification for Batteries for Use in Small Unmanned Aircraft Systems (sUAS)3. Terminology3.1 Definitions:3.1.1 basic empty weight (BEW), nbasic empty weight includes the standard empty weight plus operationaloptional andspecial equipment that has been installed in the unman
9、ned aircraft.3.1.2 field maintenance, ninspections and repairs made by owners/operators at a remote operating location away from theirnormal maintenance facility/provider.3.1.3 flight training supplement (FTS), nadditional information provided by the sUAS manufacturer to provide instruction inthe pr
10、oper operation of the system.3.1.4 landing area, nthe total area defined by the manufacturer needed to recover and bring the sUAS to a complete stop froma height of 3550 feet above the surface.3.1.5 manufacturer, nentity responsible for assembly and integration of components and subsystems to create
11、 a safe operatingsUAS.1 This test method is under the jurisdiction ofASTM Committee F38 on UnmannedAircraft Systems and is the direct responsibility of Subcommittee F38.03 on PersonnelTraining, Qualification and Certification.Current edition approved Jan. 15, 2014Feb. 15, 2016. Published February 20
12、14March 2016. Originally approved in 2014. Last previous edition approved in 2014 asF2908 14. DOI: 10.1520/F2908-14.10.1520/F2908-16.2 For referencedASTM standards, visit theASTM website, www.astm.org, or contactASTM Customer Service at serviceastm.org. For Annual Book of ASTM Standardsvolume inform
13、ation, refer to the standards Document Summary page on the ASTM website.This document is not an ASTM standard and is intended only to provide the user of an ASTM standard an indication of what changes have been made to the previous version. Becauseit may not be technically possible to adequately dep
14、ict all changes accurately, ASTM recommends that users consult prior editions as appropriate. In all cases only the current versionof the standard as published by ASTM is to be considered the official document.Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19
15、428-2959. United States13.1.6 maximum takeoff weight, nthe maximum allowable weight for takeoff (including payload).3.1.7 minimum operating crew (MOC), nthe minimum operating crew includes the pilot in command, a visual observer (ifone is required) and any other required crew member in order to safe
16、ly operate a specific UAS which includes the make, model,and control station specific to that unmanned aircraft.3.1.8 model number, na manufacturer-issued unique identifying number or code assigned to each manufactured type ofaircraft having the same structural design, components, and standard confi
17、guration.3.1.9 pre-flight planning, nan activity conducted by the pilot and his/her flight crew prior to takeoff to ensure that the flightwill be conducted safely and in accordance with all applicable standards and regulations. The activity includes, but is not limitedto, such things as checking wea
18、ther, route of flight, airspace, equipment configuration, support personnel, terrain, andcommunications requirements.3.1.10 shall vs. should vs. may, vuse of the word “shall” implies that a procedure or statement is mandatory and must befollowed to comply with this standard, “should” implies recomme
19、nded, and “may” implies optional at the discretion of thesupplier, manufacturer, or operator. Since “shall” statements are requirements, they include sufficient detail needed to definecompliance (for example, threshold values, test methods, oversight, reference to other standards). “Should” statemen
20、ts are providedas guidance towards the overall goal of improving safety, and could include only subjective statements. “Should” statements alsorepresent parameters that could be used in safety evaluations, and could lead to development of future requirements. “May”statements are provided to clarify
21、acceptability of a specific item or practice, and offer options for satisfying requirements.3.1.11 small unmanned aircraft system (sUAS), ncomposed of the small unmanned aircraft (sUA) and all required on-boardsubsystems, payload, control station, other required off-board subsystems, any required la
22、unch and recovery equipment, andcommand and control (C2) links between the sUAand the control station. For purposes of this standard sUAS is synonymous withthe term small Remotely Piloted Aircraft System (sRPAS) and sUA is synonymous with the term small Remotely Piloted Aircraft(sRPA).3.1.12 takeoff
23、 area, nthe total area defined by the manufacturer needed to launch the sUAS to a point where the aircraft is35 feet above the takeoff surface.3.2 Acronyms:3.2.1 AFMaircraft flight manual3.2.2 AGLabove ground level3.2.3 BEWbasic empty weight3.2.4 IASindicated airspeed3.2.5 MOCminimum operating crew3
24、.2.6 MSLmean sea level4. Applicability4.1 The purpose of theAFM is to provide guidance to owners, operators, mechanics, pilots, crew members, airports, regulatoryofficials, and aircraft and component manufacturers who perform or provide oversight of sUAS flight operations.4.2 For sUAS of a certain s
25、ize and simplicity, theAFM may also cover instruction for maintenance and continued airworthinessfor the minor maintenance, repair, and alteration of sUAS as provided for in section 7.10 of this standard.4.3 During the design and flight testing of a sUAS the manufacturer shall identify and record th
26、ose items that are required tobe included in the AFM as prescribed in this standard.4.4 Sections 6 and 7 of this standard serve as templates for manufacturers to structure their AFM.4.5 This standard is written for all sUAS that are permitted to operate over a defined area and in airspace authorized
27、 by anations GAA. CAA. It is assumed that a pilot, operator, or visual observer(s) will provide for the sense and avoid requirementto avoid collisions with other aircraft and that the maximum range and altitude at which the sUAS can be flown at will be specifiedby the nations GAA. CAA. Unless otherw
28、ise specified by a nations GAA CAA this standard applies only to UA that have amaximum take off gross weight of 55 lb/25 kg or less.5. General Requirements5.1 The AFM shall provide information in the following areas for a specific model of sUAS:5.1.1 System description.5.1.2 Operating characteristic
29、s.5.1.3 Performance and limitations.5.1.4 Normal, abnormal, and emergency operating procedures.5.1.5 Installed controls, indicators, equipment, and accessories. This information shall be included through one of the followingmethods:F2908 1625.1.5.1 Instructions for maintenance and continuing airwort
30、hiness.5.1.5.2 Referencing separate component manufacturer provided instructions or manuals.5.1.5.3 Any combination of 5.1.5.1 and 5.1.5.2.5.2 TheAFM technical content shall be consistent with the data developed in accordance with Practice F2909 and SpecificationsF2910, F3005, and F3002.5.3 The AFM
31、shall be structured in accordance with Section 6 of this standard.5.4 The AFM content shall be in accordance with Section 7 of this standard.5.5 All revisions, omissions, errors, changes, or updates to the AFM shall be tracked and distributed to all sUAS owners ofrecord in accordance with the qualit
32、y assurance requirements of Specification F3003.5.6 The AFM shall present a style, format, and appearance in accordance with accepted government or industry best practicesfor human readable technical manuals (for example, MIL-STD-3001 “Preparation of Digital Technical Information forMulti-Output Pre
33、sentation of Technical Manuals”). Additionally, if the AFM is provided in electronic format, it shall conform tocommon industry or government best practices for readability, indexing, navigation, scrolling and printing.5.7 All measurements shall be consistent with the equipment and instrumentation i
34、nstalled in the sUAS.5.8 Flight altitudes shall be barometric altitudes referenced either to MSL or AGL (barometric AGL is barometric altitudemeasured at the ground location of operation subtracted from the barometric altitude in flight).5.9 Due to the wide variety in size, weight, and system comple
35、xity of sUAS, not all items will apply to all systems. Optionalitems are marked by (O). Components required for the safe operation of the sUAS may not be identified as optional (O) in theAFM. All other items are considered mandatory for inclusion. However, if a manufacturer wishes to exclude a manda
36、tory item,a statement of justification shall be included in the AFM.6. Structure6.1 Title.6.2 Record of manual revisions (tabular format).6.3 (O) Table of contents.6.4 (O) Introduction.6.5 No. 1 General information and system description.6.6 No. 2 Performance and limitations.6.7 No. 3 Normal and abn
37、ormal procedures.6.8 No. 4 Emergency procedures.6.9 No. 5 Weight and balance, and equipment list.6.10 No. 6 Instructions for handling, servicing, field or preventative maintenance, and instructions for continuedairworthiness.6.11 No. 7 Supplements.7. Content7.1 Title PageShall be the TheAFM cover an
38、dshall provide the following information (decorative covers are allowed as longas this information is provided on the cover):7.1.1 Publication number,7.1.2 The words Aircraft Flight Manual,7.1.3 System name,7.1.4 Model number, and7.1.5 Date (show the date of issue).7.2 Record of Manual RevisionsThis
39、 section shall provide a form on which the owner can note all updates and changes to theAFM.7.3 (O) Table of ContentsThis optional section should provide the major headings, paragraphs, and page numbers to assist theowner in finding information in the AFM.7.4 (O) IntroductionThis optional section sh
40、ould provide the following information:7.4.1 A list of the standards used for the design and construction, and reference compliance with this standard,7.4.2 The name and contact information of the manufacturer of the sUAS, andF2908 1637.4.3 Data, location, and contact information for recovery of fly
41、ing permits and other documentation, should the manufacturerlose its ability to support the make and model.7.5 No. 1 General Information and System Description:7.5.1 Introduction to the sUAS.Introduction.7.5.2 Aircraft:7.5.2.1 Airframe,(1) (O) 3-view drawing,7.5.2.2 Flight control surfaces,7.5.2.3 E
42、ngine / propulsion, propellers, and rotors,7.5.2.4 Avionics,(1) Guidance, Navigation and Control (GNC) (i.e., (that is, flight computer),(2) Communications equipment, and(3) (O) Other avionics to include transponder, recording device, video processing, antenna, etc.7.5.3 Control station:7.5.3.1 Info
43、rmation displays (aircraft health and status, navigation, payload, etc.),7.5.3.2 User interfaces (for example, keyboards, trackballs, joysticks, etc.), and7.5.3.3 (O) Interoperability between control station and multiple aircraft types.7.5.4 Command and control (C2) link:7.5.4.1 Frequencies (Optiona
44、l if sensitive or classified), and7.5.4.2 Power / range (Optional if sensitive or classified).7.5.5 Launch and/or recovery equipment if applicable.7.5.6 Ground operational area set up:7.5.6.1 Area plan and diagram for on or off airport areas, and7.5.6.2 Security of cockpit (GCS type, closed or open
45、air) and/oror flight crew positions (visual observers, launch and recoverycrew) crew), or both, for personnel responsible for direct support of flight operations.7.6 No. 2 Performance and LimitationsThe following detailed information shall be provided to the operator. Those itemsmarked with an (O) a
46、re considered optional if not required for safety of flight by the manufacturer.7.6.1 Empty weight, maximum gross weight, and maximum takeoff weight,7.6.2 Top speed at sea level and cruise / loiter speed at a stated power setting and altitude,7.6.3 Endurance,7.6.4 (O) Stall speed,7.6.5 Total fuel ca
47、pacity / battery power, total usable fuel / battery, and approved types of fuels / batteries,7.6.6 (O) Takeoff area required at a normal launch site using normal takeoff/launch procedures as defined in 7.7.5,7.6.7 (O) Landing area required at a normal recovery site using normal landing/recovery proc
48、edures as defined in 7.7.8,7.6.8 Cruise speeds,7.6.9 Power setting and consumption appropriate to the type of propulsion (for example, fuel, battery, etc.),7.6.10 Prohibited maneuvers,7.6.11 (O) Center of Gravity gravity limitations and instructions for calculating/verifying CG locations as well as
49、removing oradding ballast (for those systems where the owner/operator is capable of adjusting/influencing),7.6.12 (O) Maximum operating altitude,7.6.13 (O) Rate of climb/descent,7.6.14 (O) Airspeed Indicator speed range markings,7.6.15 (O) Stalling speeds at maximum takeoff weight (VS and VS0),7.6.16 (O) Flap extended speed range (VS0 to VFE),7.6.17 (O) Maneuvering speed (VA) at gross weight and minimum weight,7.6.18 Never exceed speed (VNE),7.6.19 (O) Load factors,7.6.20 (O) Maximum propulsion output,7.6.21 (O) Applicable environm
