ASTM F3235-2017a Standard Specification for Aircraft Storage Batteries《飞机蓄电池的标准规格》.pdf

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1、Designation: F3235 171F3235 17aStandard Specification forElectricalAircraft Storage Batteries in Small Aircraft1This standard is issued under the fixed designation F3235; the number immediately following the designation indicates the year oforiginal adoption or, in the case of revision, the year of

2、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 NOTEEditorially corrected 4.1.2.3 in July 2017.1. Scope1.1 This specification covers international standards for the electrical

3、storage battery 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 ofthis specification as part of a certification plan. For information on which CAA regulatory bodies have

4、accepted this specification(in whole or in part) as a means of compliance to their Small Aircraft Airworthiness regulations (hereinafter referred to as “theRules”), refer to ASTM F44 webpage (www.ASTM.org/COMMITTEE/F44.htm) which includes CAA website links.1.3 This standard does not purport to addre

5、ss all of the safety concerns, if any, associated with its use. It is the responsibilityof the user of this standard to establish appropriate safety safety, health, and healthenvironmental practices and determine theapplicability of regulatory limitations prior to use.1.4 This international standard

6、 was developed in accordance with internationally recognized principles on standardizationestablished in the Decision on Principles for the Development of International Standards, Guides and Recommendations issuedby the World Trade Organization Technical Barriers to Trade (TBT) Committee.2. Referenc

7、ed Documents2.1 Following is a list of external standards referenced throughout this specification; the earliest revision acceptable for use isindicated. In all cases, later document revisions are acceptable if shown to be equivalent to the listed revision, or if otherwiseformally accepted by the go

8、verning civil aviation authority; earlier revisions are not acceptable.2.2 ASTM Standards:2F3060 Terminology for AircraftF3061/F3061M Specification for Systems and Equipment in Small Aircraft2.3 Other Standards:RTCA/DO-311 Minimum Operational Performance Standards for Rechargeable Lithium Battery Sy

9、stems3RTCA/DO-347 Certification Test Guidance for Small and Medium Sized Rechargeable Lithium Batteries and Battery Systems33. Terminology3.1 Terminology specific to this specification is provided below. For general terminology, refer to Terminology F3060.3.2 Definitions of Terms Specific to This St

10、andard:3.2.1 aircraft type code, nan Aircraft Type Code (ATC) is defined by considering both the technical considerations regardingthe design of the aircraft and the airworthiness level established based upon risk-based criteria; the method of defining an ATCapplicable to this specification is defin

11、ed in Specification F3061/F3061M.4. Electrical Storage BatteriesNOTE 1Table 1 provides correlation between variousAircraft Type Codes and the individual requirements contained within this section; refer to 3.2.1.For each subsection, an indicator can be found under each ATC character field; three ind

12、icators are used:1 This specification is under the jurisdiction of ASTM Committee F44 on General Aviation Aircraft and is the direct responsibility of Subcommittee F44.50 on Systemsand Equipment.Current edition approved Feb. 15, 2017Sept. 1, 2017. Published March 2017October 2017. Originally approve

13、d in 2017. Last previous edition approved in 2017 asF3235 171. DOI: 10.1520/F3235-17E01.10.1520/F3235-17A.2 For referencedASTM standards, visit theASTM website, www.astm.org, or contactASTM Customer Service at serviceastm.org. For Annual Book of ASTM Standardsvolume information, refer to the standar

14、ds Document Summary page on the ASTM website.3 Available from Radio Technical Commission for Aeronautics (RTCA), 1150 18th NW, Suite 910, Washington, DC 20036, https:/www.rtca.org.This document is not an ASTM standard and is intended only to provide the user of an ASTM standard an indication of what

15、 changes have been made to the previous version. Becauseit may not be technically possible to adequately depict 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

16、official document.Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States1An empty cell ( ) in all applicable ATC character field columns indicates that an aircraft must meet the requirements of that subsection.Awhite circle () in multiple co

17、lumns indicates that the requirements of that subsection are not applicable to an aircraft only if all suchATC characterfields are applicable.A mark-out () in any of the applicable ATC character field columns indicates that the requirements of that subsection are not applicable to an aircraftif that

18、 ATC character field is applicable.ExampleAn aircraft with an ATC of 1SRLLDLN is being considered. Since all applicable columns are indicated for 4.1.1, that subsection isapplicable to the aircraft.TABLE 1 ATC Compliance Matrix, Section 4SectionAirworthiness Level Number ofEnginesType ofEngine(s)Sta

19、ll Speed Cruise Speed MeteorologicalConditionsAltitude Maneuvers1 2 3 4 S M R T L M H L H D N I L H N A44.14.1.14.1.24.1.2.14.1.2.24.1.2.34.24.2.14.2.24.2.34.2.44.2.54.2.64.2.74.2.84.2.94.2.104.2.114.2.124.2.134.2.14F3235 17a24.1 Nickel Cadmium Batteries:4.1.1 Each nickel cadmium battery installatio

20、n capable of being used to start an engine or auxiliary power unit must haveprovisions to prevent any hazardous effect on structure or essential systems that may be caused by the maximum amount of heatthe battery can generate during a short circuit of the battery or of its individual cells.4.1.2 Nic

21、kel cadmium battery installations capable of being used to start an engine or auxiliary power unit must meet therequirements of either 4.1.2.1, 4.1.2.2, or 4.1.2.3.4.1.2.1 If the requirements of either 4.1.2.2 or 4.1.2.3 are not met, nickel cadmium battery installations capable of being usedto start

22、 an engine or auxiliary power unit must have a system to control the charging rate of the battery automatically so as toprevent battery overheating.4.1.2.2 If the requirements of either 4.1.2.1 or 4.1.2.3 are not met, nickel cadmium battery installations capable of being usedto start an engine or au

23、xiliary power unit must have a battery temperature sensing and over-temperature warning system with ameans for disconnecting the battery from its charging source in the event of an over-temperature condition.4.1.2.3 If the requirements of either 4.1.2.1 or 4.1.2.2 are not met, nickel cadmium battery

24、 installations capable of being usedto start an engine or auxiliary power unit must have a battery failure sensing and warning system with a means for disconnectingthe battery from its charging source in the event of battery failure.4.2 Large Rechargeable Lithium Ion Batteries:4.2.1 The provisions o

25、f 4.2.2 4.2.14 apply only to single-cell lithium ion batteries with a capacity greater than or equal to 60watt-hours and multi-cell lithium ion batteries with a capacity greater than or equal to 300 watt-hours.4.2.2 Safe cell temperatures and pressures must be maintained during any foreseeable charg

26、ing or discharging condition.4.2.3 Safe cell temperatures and pressures must be maintained during any failure of the charging or battery monitoring systemnot shown to be extremely remote.4.2.4 The rechargeable lithium battery installation must preclude explosion in the event of any failure of the ch

27、arging or batterymonitoring system not shown to be extremely remote.4.2.5 Design of the rechargeable lithium batteries must preclude the occurrence of self-sustaining, uncontrolled increases intemperature or pressure.4.2.6 No explosive or toxic gases emitted by any rechargeable lithium battery in no

28、rmal operation may accumulate within theaircraft in such quantities as would cause risk of fire/explosion or be harmful to the aircraft occupants, or both.4.2.7 No explosive or toxic gases emitted by any rechargeable lithium battery as the result of any failure, not shown to beextremely remote, of t

29、he battery charging system, battery monitoring system, or battery installation may accumulate within theaircraft in such quantities as would cause risk of fire/explosion or be harmful to the aircraft occupants, or both.4.2.8 No corrosive fluids or gases that may escape from any rechargeable lithium

30、battery may damage surrounding structure orany adjacent systems, equipment, or electrical wiring of the airplane in such a way as to cause a major or more severe failurecondition.4.2.9 Each rechargeable lithium battery installation must have provisions to prevent any hazardous effect on structure or

31、essential systems caused by the maximum amount of heat the battery can generate during a short circuit of the battery or of itsindividual cells.4.2.10 The lithium battery system must have a capability to control the charging rate of the battery automatically, so as toprevent battery overheating or o

32、vercharging, and the requirements of either 4.2.10.1 or 4.2.10.2 must be met.4.2.10.1 A battery temperature sensing and over-temperature warning system with a means for automatically disconnecting thebattery from its charging source in the event of an over-temperature condition must be provided.4.2.

33、10.2 A battery failure sensing and warning system with a means for automatically disconnecting the battery from itscharging source in the event of battery failure may be provided.4.2.11 Any rechargeable lithium battery installation, the function of which is required for safe operation of the aircraf

34、t, mustincorporate a monitoring and warning feature that will provide an indication to the appropriate flight crewmembers whenever thestate-of-charge of the batteries has fallen below levels considered acceptable for dispatch of the aircraft.4.2.12 Internal and external materials of the rechargeable

35、 lithium battery and battery system shall meet the applicablecertification flammability requirements of the installation.4.2.13 Installations of rechargeable lithium batteries must meet the applicable Flammable Fluid Fire Protection requirements ofSpecification F3061/F3061M.4.2.14 RTCA/DO-311 and RT

36、CA/DO-347 provide a method for demonstrating compliance to 4.2.2 4.2.11.5. Keywords5.1 batteries; battery; cadmium; nicad; nickelF3235 17a3APPENDIX(Nonmandatory Information)X1. SUPPORTING INFORMATION FOR REVISIONSX1.1 Revisions to Title of Specification F3235X1.1.1 Revision 17a:X1.1.1.1 DiscussionTh

37、is proposed change is to reword the title of the standard to remove the term “small aircraft” since thereis not a clear definition of what constitutes small aircraft.X1.1.1.2 ProposalWAS: Standard Specification for Electrical Storage Batteries in SmallAircraft. IS: Standard Specification forAircraft

38、 Storage Batteries.X1.1.1.3 Rationale for Change(s)The title identifies the specification as being applicable to “Small Aircraft” but there is nodefinition of what Small Aircraft includes in Terminology F3060 and there is no plan at this time to add such a definition as thereis not universal agreeme

39、nt on what Small Aircraft includes. The 14 CFR 1 definition of Small Aircraft is any aircraft with amaximum weight of 12 500 lb. Other FAA documents have indicated small airplanes can be airplanes with a maximum weightof up to 30 000+ lb. If we use the 14 CFR 1 definition, then that eliminates Level

40、 4 airplanes.X1.2 Revisions to Section 2.3X1.2.1 Revision 17a:X1.2.1.1 ProposalModify 2.3 to add references to RTCA/DO-311 and RTCA/DO-347.X1.3 Revisions to Section 4.2X1.3.1 Revision 17a:X1.3.1.1 DiscussionAs part of the effort to introduce rechargeable lithium-ion battery requirements to the syste

41、ms andequipment standard, content of AC20-184 is being incorporated into Specification F3235. This is only partial coverage for largerechargeable Li-Ion, other types of Li-ion batteries will be addressed in future revisions. This material has previously passedF44.50 sub-committee ballot 16-03.X1.3.1

42、.2 ProposalAdd the Lithium Battery requirements as defined below. Update Table 1 (ATC Compliance Matrix, Section4) to align with the proposed changes.X1.3.1.3 Rationale for Change(s)The proposal is to add content which is currently included in Special Conditions which areapplied to each aircraft wit

43、h a rechargeable lithium-ion battery installation.ASTM International takes no position respecting the validity of any patent rights asserted in connection with any item mentionedin this standard. Users of this standard are expressly advised that determination of the validity of any such patent right

44、s, and the riskof infringement of such rights, are entirely their own responsibility.This standard is subject to revision at any time by the responsible technical committee and must be reviewed every five years andif not revised, either reapproved or withdrawn.Your comments are invited either for re

45、vision of this standard or for additional standardsand should be addressed to ASTM International Headquarters. Your comments will receive careful consideration at a meeting of theresponsible technical committee, which you may attend. If you feel that your comments have not received a fair hearing yo

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