ASTM F2908-2014 Standard Specification for Aircraft Flight Manual &40 AFM&41 for a Small Unmanned Aircraft System &40 sUAS&41 《小型无人航空器系统40 sUAS41用航空器飞行手册40 AFM41的标准规范》.pdf

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1、Designation: F2908 14Standard 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 revision, the y

2、ear 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 requirementsfor an Aircraft Flight Manual (AFM) for an unmanned aircraf

3、tsystem (UAS) designed, manufactured, and operated in thesmall UAS (sUAS) category as defined by a nations Govern-ing Aviation Authority (GAA). Depending on the size andcomplexity of the sUAS, an AFM may also contain theinstruction for maintenance and continuing airworthiness forowner / operator aut

4、horized maintenance.1.2 This specification defines the AFM information thatshall be provided by the manufacturer of a sUAS as part of theinitial sale or transfer to an end user.1.3 This specification applies to a sUAS seeking a nationsGAA approval, in the form of flight certificates, airworthinessce

5、rtificates, type certificates, flight permits, or other likedocumentation as a sUAS, in the configuration specified in theAFM delivered with the system.1.4 Any modifications that invalidate or otherwise affect theaccuracy of AFM operating instructions shall be approved bythe manufacturer and communi

6、cated to the regulatory authorityin the certificate / permit application.2. Referenced Documents2.1 ASTM Standards:2F2909 Practice for Maintenance and Continued Airworthi-ness of Small Unmanned Aircraft Systems (sUAS)F2910 Specification for Design, Construction, and Test of aSmall Unmanned Aircraft

7、System (sUAS)F2911 Practice for Production Acceptance of a Small Un-manned Aircraft System (sUAS)F3002 Specification for Design of the Command and Con-trol System for Small UnmannedAircraft Systems (sUAS)F3003 Specification for Quality Assurance of a Small Un-manned Aircraft System (sUAS)F3005 Speci

8、fication for Batteries for Use in Small Un-manned Aircraft Systems (sUAS)3. Terminology3.1 Definitions:3.1.1 basic empty weight (BEW), nbasic empty weightincludes the standard empty weight plus operational andspecial equipment that has been installed in the unmannedaircraft.3.1.2 field maintenance,

9、ninspections and repairs made byowners/operators at a remote operating location away fromtheir normal maintenance facility/provider.3.1.3 flight training supplement (FTS), nadditional infor-mation provided by the sUAS manufacturer to provide instruc-tion in the proper operation of the system.3.1.4 l

10、anding area, nthe total area defined by the manu-facturer needed to recover and bring the sUAS to a completestop from a height of 35 feet above the surface.3.1.5 manufacturer, nentity responsible for assembly andintegration of components and subsystems to create a safeoperating sUAS.3.1.6 maximum ta

11、keoff weight, nthe maximum allowableweight for takeoff (including payload).3.1.7 minimum operating crew (MOC), nthe minimumoperating crew includes the pilot in command, a visualobserver (if one is required) and any other required crewmember in order to safely operate a specific UAS whichincludes the

12、 make, model and control station specific to thatunmanned aircraft.3.1.8 model number, na manufacturer-issued unique iden-tifying number or code assigned to each manufactured type ofaircraft having the same structural design, components, andstandard configuration.3.1.9 pre-flight planning, nan activ

13、ity conducted by thepilot and his/her flight crew prior to takeoff to ensure that theflight will be conducted safely and in accordance with allapplicable standards and regulations. The activity includes, butis not limited to, such things as checking weather, route of1This test method is under the ju

14、risdiction of ASTM Committee F38 onUnmannedAircraft Systems and is the direct responsibility of Subcommittee F38.03on Personnel Training, Qualification and Certification.Current edition approved Jan. 15, 2014. Published February 2014. DOI:10.1520/F2908-14.2For referenced ASTM standards, visit the AS

15、TM website, www.astm.org, orcontact ASTM Customer Service at serviceastm.org. For Annual Book of ASTMStandards volume information, refer to the standards Document Summary page onthe ASTM website.Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. Unite

16、d States1flight, airspace, equipment configuration, support personnel,terrain and communications 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” impliesrecommended, and

17、 “may” implies optional at the discretion ofthe supplier, manufacturer, or operator. Since “shall” state-ments are requirements, they include sufficient detail needed todefine compliance (for example, threshold values, testmethods, oversight, reference to other standards). “Should”statements are pro

18、vided as guidance towards the overall goal ofimproving safety, and could include only subjective statements.“Should” statements also represent parameters that could beused in safety evaluations, and could lead to development offuture requirements. “May” statements are provided to clarifyacceptabilit

19、y of a specific item or practice, and offer options forsatisfying requirements.3.1.11 small unmanned aircraft system (sUAS),ncomposed of the small unmanned aircraft (sUA) and allrequired on-board subsystems, payload, control station, otherrequired off-board subsystems, any required launch and recov-

20、ery equipment, and command and control (C2) links betweenthe sUA and the control station. For purposes of this standardsUAS is synonymous with the term small Remotely PilotedAircraft System (sRPAS) and sUA is synonymous with theterm small Remotely Piloted Aircraft (sRPA).3.1.12 takeoff area, nthe to

21、tal area defined by the manu-facturer needed to launch the sUAS to a point where theaircraft is 35 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 crew3.2.6 MSLmean

22、sea level4. Applicability4.1 The purpose of the AFM is to provide guidance toowners, mechanics, pilots, crew members, airports, regulatoryofficials, and aircraft and component manufacturers who per-form or provide oversight of sUAS flight operations.4.2 For sUAS of a certain size and simplicity, the

23、 AFM mayalso cover instruction for maintenance and continued airwor-thiness for the minor maintenance, repair, and alteration ofsUAS as provided for in section 7.10 of this standard.4.3 During the design and flight testing of a sUAS themanufacturer shall identify and record those items that arerequi

24、red to be included in the AFM as prescribed in thisstandard.4.4 Sections 6 and 7 of this standard serve as templates formanufacturers to structure their AFM.4.5 This standard is written for all sUAS that are permittedto operate over a defined area and in airspace authorized by anations GAA. It is as

25、sumed that a visual observer(s) willprovide for the sense and avoid requirement to avoid collisionswith other aircraft and that the maximum range and altitude atwhich the sUAS can be flown at will be specified by thenations GAA. Unless otherwise specified by a nations GAAthis standard applies only t

26、o UA that have a maximum take offgross weight of 55 lb/25 kg or less.5. General Requirements5.1 The AFM shall provide information in the followingareas for a specific model of sUAS:5.1.1 System description.5.1.2 Operating characteristics.5.1.3 Performance and limitations.5.1.4 Normal, abnormal, and

27、emergency operating proce-dures.5.1.5 Installed controls, indicators, equipment, and accesso-ries. This information shall be included through one of thefollowing methods:5.1.5.1 Instructions for maintenance and continuing airwor-thiness.5.1.5.2 Referencing separate component manufacturer pro-vided i

28、nstructions or manuals.5.1.5.3 Any combination of 5.1.5.1 and 5.1.5.2.5.2 The AFM technical content shall be consistent with thedata developed in accordance with Practice F2909 and Speci-fications F2910, F3005, and F3002.5.3 The AFM shall be structured in accordance with Section6 of this standard.5.

29、4 The AFM content shall be in accordance with Section 7of this standard.5.5 All revisions, omissions, errors, changes, or updates tothe AFM shall be tracked and distributed to all sUAS ownersof record in accordance with the quality assurance require-ments of Specification F3003.5.6 The AFM shall pre

30、sent a style, format, and appearancein accordance with accepted government or industry bestpractices for human readable technical manuals (for example,MIL-STD-3001 “Preparation of Digital Technical Informationfor Multi-Output Presentation of Technical Manuals”).Additionally, if the AFM is provided i

31、n electronic format, itshall conform to common industry or government best prac-tices for readability, indexing, navigation, scrolling and print-ing.5.7 All measurements shall be consistent with the equip-ment and instrumentation installed in the sUAS.5.8 Flight altitudes shall be barometric altitud

32、es referencedeither to MSL or AGL (barometric AGL is barometric altitudemeasured at the ground location of operation subtracted fromthe barometric altitude in flight).5.9 Due to the wide variety in size, weight and systemcomplexity of sUAS, not all items will apply to all systems.Optional items are

33、marked by (O). Components required forthe safe operation of the sUAS may not be identified asoptional (O) in the AFM. All other items are consideredF2908 142mandatory for inclusion. However, if a manufacturer wishes toexclude a mandatory item, a statement of justification shall beincluded in the AFM

34、.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 abnormal procedures.6.8 No. 4 Emergency procedures.6.9 No. 5 Weight an

35、d balance, and equipment list.6.10 No. 6 Instructions for handling, servicing, field orpreventative maintenance, and instructions for continued air-worthiness.6.11 No. 7 Supplements.7. Content7.1 Title PageShall be the AFM cover and provide thefollowing information (decorative covers are allowed as

36、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 section shall providea form on which the owner can note all updates and ch

37、anges tothe AFM.7.3 (O) Table of ContentsThis optional section shouldprovide the major headings, paragraphs, and page numbers toassist the owner in finding information in the AFM.7.4 (O) IntroductionThis optional section should providethe following information:7.4.1 A list of the standards used for

38、the design andconstruction, and reference compliance with this standard,7.4.2 The name and contact information of the manufacturerof the sUAS, and7.4.3 Data, location and contact information for recovery offlying permits and other documentation, should the manufac-turer lose its ability to support t

39、he make and model.7.5 No. 1 General Information and System Description:7.5.1 Introduction to the sUAS.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 Engine / propulsion,7.5.2.4 Avionics,(1) Guidance, Navigation and Control (GNC) (i.e., flightcomputer),

40、(2) Communications equipment, and(3) (O) Other avionics to include transponder, recordingdevice, video processing, antenna, etc.7.5.3 Control station:7.5.3.1 Information displays (aircraft health and status,navigation, payload, etc.),7.5.3.2 User interfaces (for example, keyboards, trackballs,joysti

41、cks, etc.), and7.5.3.3 (O) Interoperability between control station andmultiple aircraft types.7.5.4 Command and control (C2) link:7.5.4.1 Frequencies (Optional if sensitive or classified), and7.5.4.2 Power / range (Optional if sensitive or classified).7.5.5 Launch and/or recovery equipment if appli

42、cable.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 air)and/or flight crew positions (visual observers, launch andrecovery crew) for personnel responsible for direct support offlight operations.

43、7.6 No. 2 Performance and LimitationsThe followingdetailed information shall be provided to the operator. Thoseitems marked with an (O) are considered optional if notrequired for safety of flight by the manufacturer.7.6.1 Empty weight, maximum gross weight, and maximumtakeoff weight,7.6.2 Top speed

44、at sea level and cruise / loiter speed at astated power setting and altitude,7.6.3 Endurance,7.6.4 (O) Stall speed,7.6.5 Total fuel capacity / battery power, total usable fuel /battery, and approved types of fuels / batteries,7.6.6 (O) Takeoff area required at a normal launch site usingnormal takeof

45、f/launch procedures as defined in 7.7.5,7.6.7 (O) Landing area required at a normal recovery siteusing normal landing/recovery procedures as defined in 7.7.8,7.6.8 Cruise speeds,7.6.9 Power setting and consumption appropriate to the typeof propulsion (for example, fuel, battery, etc.),7.6.10 Prohibi

46、ted maneuvers,7.6.11 (O) Center of Gravity (for those systems where theowner/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 (V

47、Sand VS0),7.6.16 (O) Flap extended speed range (VS0to VFE),7.6.17 (O) Maneuvering speed (VA) at gross weight andminimum 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 environmental limitations,7.6.22 (O) Applicable VFR night

48、or IFR use limitations,7.6.23 Maximum wind limitations,7.6.24 (O) Other relevant parameters for rotary wing and/ormulti rotor systems, andF2908 1437.6.25 (O) Takeoff and landing data (TOLD) performanceplanning card or worksheet (this is a planning tool used todocument all the V speeds necessary for

49、safe flight fromtakeoff/launch to landing/recovery).7.7 No. 3 Normal ProceduresThe following detailedinformation shall be provided to the owner. Those itemsmarked with an (O) are considered optional at the discretion ofthe manufacturer.7.7.1 Preflight planning to include site selection for launchand recovery:7.7.1.1 Airspace environment,7.7.1.2 Radio Frequency (RF) environment,7.7.1.3 Use of launch and recovery equipment (for example,rails, nets, arresting gear), and7.7.1.4 Distance to control station.7.7.2 System assembly and pre-f