ASTM F2909-2014 Standard Practice for Maintenance and Continued Airworthiness of Small Unmanned Aircraft Systems &40 sUAS&41 《小型无人航空系统40 sUAS41维护和持续适航的标准实施规程》.pdf

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1、Designation: F2909 14Standard Practice forMaintenance and Continued Airworthiness of SmallUnmanned Aircraft Systems (sUAS)1This standard is issued under the fixed designation F2909; the number immediately following the designation indicates the year oforiginal adoption or, in the case of revision, t

2、he 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 establishes the standard practice forthe maintenance and continued airworthiness of sUAS

3、.1.2 This standard does not purport to address all of thesafety concerns, if any, associated with its use. It is theresponsibility of the user of this standard to establish appro-priate safety and health practices and determine the applica-bility of regulatory limitations prior to use.2. Referenced

4、Documents2.1 ASTM Standards:2F2908 Specification for Aircraft Flight Manual (AFM) for aSmall Unmanned Aircraft System (sUAS)F3005 Specification for Batteries for Use in Small Un-manned Aircraft Systems (sUAS)3. Terminology3.1 Definitions of Terms Specific to This Standard:3.1.1 command and control (

5、C2) link(s), nsafety-criticalradio-frequency (RF) link(s) between ground control station(GCS) and the small unmanned aircraft (sUA).3.1.2 flight control system, FCS, ncomposed of systemcomponents intended to take GCS commands via a C2 link andcontrol flight control surfaces and propulsion systems.3.

6、1.3 ground control station, GCS, na land- or sea-basedcontrol center that provides the facilities for human control ofsUA.3.1.4 manufacturer, nentity responsible for assembly andintegration of components and subsystems to create a safeoperating sUAS.3.1.5 propulsion system, nconsists of one or more

7、powerplants (for example, a combustion engine or an electric motorand, if used, a propeller or rotor) together with the associatedinstallation of fuel system, control and electrical power supply(for example, batteries, electronic speed controls, fuel cells, orother energy supply).3.1.6 shall versus

8、should versus may, vuse of the word“shall” implies that a procedure or statement is mandatory andmust be followed to comply with this standard, “should”implies recommended, and “may” implies optional at thediscretion of the supplier, manufacturer, or operator. Since“shall” statements are requirement

9、s, they include sufficientdetail needed to define compliance (for example, thresholdvalues, test methods, oversight, reference to other standards).“Should” statements are provided as guidance towards theoverall goal of improving safety, and could include onlysubjective statements. “Should” statement

10、s also represent pa-rameters that could be used in safety evaluations, and couldlead to development of future requirements. “May” statementsare provided to clarify acceptability of a specific item orpractice, and offer options for satisfying requirements.3.1.7 small unmanned aircraft system, sUAS, n

11、composedof the small unmanned aircraft (sUA) and all required on-boardsubsystems, payload, control station, other required off-boardsubsystems, any required launch and recovery equipment, andC2 links between the sUAand the control station. For purposesof this standard UAS is synonymous with the ICAO

12、 definitionof a Remotely Piloted Aircraft System (RPAS) and UA issynonymous with the ICAO definition of a Remotely PilotedAircraft (RPA).3.1.8 supplier, nany entity engaged in the design andproduction of components (other than payload if it is notrequired for safe operation of the sUAS) used on an s

13、UAS.3.1.8.1 DiscussionWhere the supplier is not themanufacturer, the supplier can only ensure that the componentscomply with accepted consensus standards.3.1.9 support equipment, nall associated equipment,whether ground based or airborne, used to enable safe opera-tion of the sUA. This includes all

14、elements of the controlstation, C2 links, telemetry, navigation, communicationsequipment, as well as equipment that may be used to launchand recover the aircraft.3.2 Acronyms:1This practice is under the jurisdiction of ASTM Committee F38 on UnmannedAircraft Systems and is the direct responsibility o

15、f Subcommittee F38.02 on FlightOperations.Current edition approved Jan. 15, 2014. Published January 2014. DOI: 10.1520/F2909-14.2For referenced ASTM standards, visit the ASTM website, www.astm.org, orcontact ASTM Customer Service at serviceastm.org. For Annual Book of ASTMStandards volume informatio

16、n, 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. United States13.2.1 AFMAircraft Flight Manual3.2.2 ATCAir Traffic Control3.2.3 C2Command and Control3.2.4 CGCenter of Gravity3.2.5 FC

17、SFlight Control System3.2.6 FTSFlight Termination System3.2.7 GAAGoverning Aviation Authority3.2.8 GCSGround Control Station3.2.9 GPSGlobal Positioning System3.2.10 INSInertial Navigation System3.2.11 PICPilot in Command3.2.12 RFRadio Frequency3.2.13 sUASmall Unmanned Aircraft3.2.14 sUASSmall Unmann

18、ed Aircraft System4. Applicability4.1 This standard is written for all sUAS that are permittedto operate over a defined area and in airspace authorized by anations governing aviation authority (GAA). It is assumed thata visual observer(s) will provide for the sense and avoidrequirement to avoid coll

19、isions with other aircraft and that themaximum range and altitude at which the sUAS can be flownwill be specified by the nations GAA. Unless otherwisespecified by a nations GAA this standard applies only to UAthat have a maximum take off gross weight of 25 kg (55 lb) orless.5. Requirements5.1 Contin

20、ued Airworthiness:5.1.1 The sUAS shall be maintained for continued airwor-thiness to meet sUAS limitations and performance capabilitiesrequired by the nations GAA.5.2 Small Unmanned Aircraft System (sUAS) Inspections:5.2.1 Scheduled Maintenance:5.2.1.1 The manufacturer shall establish the required i

21、nter-vals for scheduled inspections and publish this schedule in theAircraft Flight Manual (AFM) conforming to SpecificationF2908.5.2.1.2 As a minimum, the sUAS shall not be operated inthe GAAs airspace system unless it has undergone a scheduledinspection within the preceding 12 calendar months and

22、hasbeen approved for return to service by a person authorized bythe manufacturer or GAA.5.2.1.3 The manufacturer shall designate the maximumnumber of hours to be flown between scheduled inspections.5.2.1.4 The manufacturer shall specify preflight inspectionprocedures necessary to ensure safe operati

23、on of the sUAS.5.2.1.5 Inspections should address the requirements speci-fied in 5.2.2, as well as any additional items deemed necessaryby the manufacturer for safe flight.5.2.2 Inspection Requirements:5.2.2.1 Preflight Inspections:(1) Airframe shall be visually inspected in order to detectdefects r

24、esulting from any collision with foreign objects on theground and in the air.(2) All critical components as defined by the manufacturershall be visually inspected for corrosion, degradation, or anyanomalies.(3) The airframe shall be visually inspected to detectpotential loose parts or missing fasten

25、ers at critical joints andinterfaces.(4) All critical flight controls shall be visually inspected todetect potential loose parts or missing fasteners at critical jointsand interfaces.(5) All critical flight controls shall be inspected to ensureintegrity and proper control travel (inclusive of deflec

26、tion anddirection).(6) If equipped with an internal combustion engine, the fuelshall be verified for correct grade and checked for contamina-tion and degradation. The fuel quantity shall be verified to beadequate for the planned mission.(7) If equipped with an electric motor, the installed batterysh

27、all be of the correct type, properly secured, and adequatecharge verified for the flight.NOTE 1For certain types of battery chemistry, proper current,temperature, and voltage monitoring may also be required to avoid fire,explosion, or overheating. The inspections shall be performed in accor-dance wi

28、th manufacturers requirements and Specification F3005.(8) The propeller/rotor components shall be inspected fordegradation beyond allowable manufacturer limitations/specifications. Clearance of blades from adjacent structureand/or components as it rotates through its full motion shall beensured.(9)

29、The engine control unit(s) shall be inspected and/ortested to ensure functionality without system degradationbeyond allowable manufacturer limitations/specifications.(10) The powerplant components shall be visually in-spected for degradation of a material beyond allowable manu-facturer limitations/s

30、pecifications.(11) The powerplant system areas shall be inspected forextraneous materials and debris.(12) Each critical electrical sub-system should be checkedfor component degradation using built in test procedures thatwill identify component mal-function, if the sUAS has thiscapability.(13) The Fl

31、ight Control System (FCS) computer should betested on the ground by exercising key functions and visuallyverifying proper execution of the FCS as per manufacturersinstructions.(14) The navigation system including, but not limited to,the GPS and INS shall be checked to verify that all systems areprov

32、iding accurate information.NOTE 2This check may be combined with the FCS built-in-test.(15) If applicable, the hydraulic system shall be visuallyinspected to detect any fluid leaks, contamination, and properquantity.(16) The cooling system shall be visually inspected todetect blockage of any air int

33、ake used for cooling criticalelectronics. Avionics equipment should be checked for propercooling.(17) Other critical systems, including Flight TerminationSystems (FTS), shall be checked for proper operation.F2909 142(18) Latency between command from the GCS and feed-back from the airplane shall be m

34、easured and within acceptablerange per manufacturers instructions.(19) GCS software should be tested per manufacturersinstructions.(20) The commanded inputs shall be verified to be receivedby the intended aircraft only without any “cross control”. Thefrequency usage shall be per the approved frequen

35、cy spectrumrequirements.NOTE 3Cross control means signals meant for one test air vehicle, butreceived by another sUA in-flight. It may be due to accidental takeover orinterference via frequency.(21) Link between sUA and GCS should be tested permanufacturers instructions.(22) Control input devices at

36、 GCS should be tested forcorrect operation.(23) The GCS shall be verified for proper display opera-tion.(24) If automatic landing system exists, critical sub-systems needed for auto-land shall be tested prior to take-offper manufacturers instructions.(25) Autopilot test procedure shall be executed p

37、rior toeach flight in accordance with manufacturers instructions.(26) The GCS configuration shall be verified prior to flight.(27) The software loads for GCS and sUA, includingfirmware for system radios, shall be verified for properconfiguration.(28) All sensors, if related to safe aircraft operatio

38、ns, shallbe free from any type of blockage and shall be visuallyinspected for any potential damage or degradation. Someexamples may include: blocked pitot-tube, obstructed EO/IRcamera, etc.(29) Launch and recovery systems including landing gear,catapult, etc. shall be visually inspected for potentia

39、l damage ordegradation.(30) All system antennas shall be visually inspected forpotential damage or degradation.(31) Proper communication between the sUA pilot, safetypilot/trained observer, ATC, and other flight critical decisionelements which would reduce and/or eliminate the pilotsability to contr

40、ol the sUAS shall be verified. Verify properradio communications between the following:(a) ATC to Pilot-in-Command (PIC), if applicable.(b) PIC to ATC, if applicable.(c) Observer (OBS) to pilot (ground or aerial based, asapplicable).(d) Pilot to OBS (ground or aerial based, as applicable).(32) Each

41、basic control function shall be exercised witheach sUA prior to launch.(33) All onboard batteries shall be checked to determinebattery state. All batteries should have been recharged andbalanced per manufacturers instructions to ensure maximumcapacity.(34) Landing gear, wheels, and tires, if install

42、ed, shall bevisually inspected for potential damage or degradation.(35) The aircraft brake system, if installed, shall be in-spected for proper operation. Pneumatic brake systems shouldbe serviced per manufacturers instructions.5.2.2.2 Periodic InspectionsThe following inspections (ifapplicable) sha

43、ll be performed at the interval established by themanufacturer:(1) If installed, the fuel quantity indicator(s) shall give anaccurate indication of fuel quantity when the aircraft is in alevel flight position.(2) The sUAS fluid system(s) shall be maintained inaccordance with the manufacturers instru

44、ctions so that theoriginal performance characteristics of the fluid system(s) arenot degraded and the reliability of the system(s) is ensured.(3) The engine fuel, ignition, and intake system shall beinspected and operationally checked to ensure proper operationof each system.(4) Engine fuel lines sh

45、all be inspected for integrity andcorrect installation. Fuel leaks shall be corrected in accordancewith the manufacturers recommended procedures.(5) Fuel system filters shall be cleaned, or replaced, at theintervals specified by the manufacturer.(6) Engine integrity shall be monitored through the us

46、e ofcompression checks, oil analysis, and visual inspections as permanufacturers instructions.(7) Battery system indicators shall give an accurate indica-tion of stored electrical capacity.(8) The engine installation shall be visually inspected foradequate clearance of the engine from the strut/pylo

47、n or mountfixtures and/or hardware.(9) The propeller/rotor components shall be visually in-spected for degradation of material beyond allowable manu-facturer limitations/specifications. Separation of blades fromadjacent structure and/or components as it rotates through itsfull motion shall be verifi

48、ed.(10) Perform inspection of, and/or system test of, enginecontrol unit to ensure functionality without system degradationbeyond allowable manufacturer limitations/specifications.(11) The engine case shall be visually inspected for signs ofcase rupture or burn through.(12) Powerplant components sha

49、ll be visually inspected forcondition and security.(13) Powerplant system areas shall be visually inspectedfor extraneous materials and debris.(14) The FCS computer shall be tested on the ground byexercising key functions and visually verifying proper execu-tion of the FCS as per manufacturers instructions.(15) The electrical wiring shall be visually inspected andtested to avoid degradation due to insulation loss, shorting, etc.(16) The GCS shall be visually inspected for structuralintegrity and degradation.(17) The sUAS health monitoring