ASTM F2316-2008 Standard Specification for Airframe Emergency Parachutes for Light Sport Aircraft《轻型娱乐飞行器机身紧急情况降落伞的标准规范》.pdf

《ASTM F2316-2008 Standard Specification for Airframe Emergency Parachutes for Light Sport Aircraft《轻型娱乐飞行器机身紧急情况降落伞的标准规范》.pdf》由会员分享，可在线阅读，更多相关《ASTM F2316-2008 Standard Specification for Airframe Emergency Parachutes for Light Sport Aircraft《轻型娱乐飞行器机身紧急情况降落伞的标准规范》.pdf（7页珍藏版）》请在麦多课文档分享上搜索。

1、Designation: F 2316 08Standard Specification forAirframe Emergency Parachutes for Light Sport Aircraft1This standard is issued under the fixed designation F 2316; the number immediately following the designation indicates the year oforiginal adoption or, in the case of revision, the year of last rev

2、ision. 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 covers minimum requirements for thedesign, manufacture, and installation of parachutes for lightsport aircr

3、aft.1.2 The values stated in SI units are to be regarded asstandard. There may be values given in parentheses that aremathematical conversions to inch-pound units. Values in pa-rentheses are provided for information only and are notconsidered standard.1.2.1 Note that within the aviation community mi

4、xed unitsare appropriate in accordance with International Civil AviationOrganization (ICAO) agreements. While the values stated in SIunits are regarded as standard, certain values such as airspeedsin knots and altitude in feet are also accepted as standard.1.3 This standard does not purport to addre

5、ss 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 requirements prior to use.2. Referenced Documents2.1 FAA Document:2FAA Special Cond

6、itions 23-ACE-76 (Docket No. 118C),Ballistic Recovery Systems, Modified for Small GeneralAviation Aircraft3. Terminology3.1 Definitions of Terms Specific to This Standard:3.1.1 armed or arming, vthe next action activates thesystem.3.1.1.1 DiscussionArmed or arming is not simply remov-ing a safety pi

7、n.4. Materials and Manufacture4.1 MaterialsMaterials used for parts and assemblies, thefailure of which could adversely affect safety, must meet thefollowing conditions:4.1.1 The suitability and durability must be established byexperience or tests.4.1.2 The strength and other properties assumed in t

8、hedesign data must meet approved specifications.4.1.3 The effects of environmental conditions, such astemperature and humidity, expected in service must be takeninto account.5. Parachute Model Designations5.1 Parachute System Parts ListAparts list is required foreach parachute system for each airfra

9、me model in accordancewith this specification.5.2 New Parachute Model DesignationsEach new para-chute system model must be qualified in accordance with thisspecification.5.3 Design ChangesDesign or configuration changes thatimpact the parachute installation, performance, or operabilityrequire a new

10、parachute model designation. Each designchange of a part or component of a parachute system qualifiedby this specification must be evaluated relative to the require-ments of this specification.5.4 Installation Design ChangesAny airframe manufac-turer, builder, or owner changing the design of their a

11、ircraftunder this specification shall, as soon as possible, inform theparachute manufacturer about changes that may affect themounting, attaching, deployment, egress, or specifications ofthe parachute system.6. Parachute System Design Requirements6.1 Strength Requirements:6.1.1 Strength requirements

12、 are specified in terms of limitloads (the maximum loads to be expected in service) andultimate loads (loads that are experienced while performingparachute strength tests according to 6.2.1 to gain a safetyfactor (ultimate load factor) of 1.5). Compliance with strengthrequirements for components oth

13、er than the parachute assem-bly may be demonstrated by analysis or testing.6.1.2 System evaluation by analysis must use an acceptedcomputational method that has been verified through testing. Inother cases, load testing must be conducted.6.1.3 System evaluation by testing must be supported withinstr

14、ument calibration verified by an applicable weights andmeasures regulatory body, for example, state and federalgovernments.1This specification is under the jurisdiction of ASTM Committee F37 on LightSport Aircraft and is the direct responsibility of Subcommittee F37.70 on CrossCutting.Current editio

15、n approved Oct. 1, 2008. Published October 2008. Originallyapproved in 2003. Last previous edition approved in 2006 as F 2316 06.2Available from Ballistic Recovery Systems, Inc., 380 Airport Rd., South St.Paul, MN 55075.1Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshoho

16、cken, PA 19428-2959, United States.6.2 System DesignThe following minimum performancestandards for the basic parachute system shall be met.6.2.1 Parachute Strength TestA minimum of three suc-cessful drop tests of the parachute assembly shall be conductedunder ultimate load conditions to demonstrate

17、the parachutesstrength. A new parachute assembly may be used for each test.Data acquisition shall include recordings of inflation loads as afunction of time. A test under ultimate load condition is meantto achieve a safety factor (ultimate load factor) of 1.5 byapplying the Energy Method represented

18、 by E =12 mv2. Basedon the assumption that the parachute opening force correlatesto the kinetic energy present, the ultimate load factor of 1.5 isachieved by: (1) increasing the limit load test mass by 1.25 and(2) increasing the limit load test speed by 1.1. Therefore, theUltimate Load Factor = (1.2

19、5) 3 (1.1)2= 1.5 and a parachutestrength test under ultimate load conditions shall be conductedas follows:Min. Test weight = 1.25 3 Aircraft Gross Takeoff WeightMin. Test Speed = 1.1 3 Aircrafts Maximum Intended ParachuteDeployment Speed6.2.2 Rate of DescentRate of descent data shall be re-corded fo

20、r all tests in 6.2.1. This data may be corrected for theincrease in test vehicle weight to determine the rate of descentat the gross weight of the specific aircraft. Descent rate datafrom parachute canopies shall be corrected to 1500-m (5000-ft)density altitude and standard temperature.6.2.3 Compone

21、nt Strength TestAll critical components(such as bridles, lanyards, harnesses, activation cables, and soforth) shall be designed to meet the ultimate load factor definedin 6.1.6.2.4 Staged DeploymentThe parachute assembly shall bedesigned to stage the deployment sequence in an orderlymanner to reduce

22、 the chances of entanglements or similarmalfunctions.6.2.5 Environmental ConditionsThe system must beevaluated for operations in temperature conditions of 40 to48.9C (40 to 120F).6.3 Installation DesignEach manufacturer of an emer-gency parachute system shall provide a specific ParachuteInstallation

23、 Manual (PIM) for the installation into each per-taining aircraft with the documentation described in S2. ThePIM shall be used for all installations with parties referenced in6.3.1.6.3.1 CoordinationAirframe and parachute manufacturersmust coordinate and agree to ensure proper installation. Air-fram

24、e manufacturers of light sport aircraftspecial (fully built)must not alter the installation without consulting the parachutesystem manufacturer. For light sport aircraftexperimental (kitbuilt), the parachute manufacturer shall work with a neworiginal equipment manufacturer, the aircraft builder, or

25、theaircraft owner to create a proper installation design.6.3.2 Weight and BalanceThe installation of the para-chute system must not adversely affect the center of gravity ofthe subject aircraft.6.3.3 System MountingThe hardware used to install theparachute system shall not become loosened or detache

26、d as aresult of normal wear and tear.6.3.4 Extraction PerformanceIt must be shown that theextraction device will cleanly penetrate any covering or re-move the parachute systems cover, if any, and extract theparachute assembly to full line stretch without inhibiting ordamaging the parachute upon egre

27、ss. Airframe and parachutemanufacturers must coordinate to ensure that the extractiondevice and those components extracted by it have an unob-structed trajectory away from the aircraft. While it is recog-nized that the aircraft configuration is unpredictable in anemergency situation (for example, br

28、oken parts creating de-bris), all due care must be taken to provide a path of leastresistance assuming an extremely rapid rate of departure.6.3.5 Parachute Attachment to the AirframeThe para-chute assembly must be attached to the primary structure of theaircraft with an airframe attachment harness t

29、hat may becomposed of a single harness section or a series of harnesssections. The airframe and parachute manufacturers mustcoordinate and agree to ensure that the parachute attachment tothe subject airframe complies with the following conditions:6.3.5.1 Parachute deployments induce unique load dist

30、ribu-tions to the airframe, largely due to geometric locations of theharness attachment points. The airframe attachment points andairframe attachment harness for each individual aircraft typemust comply with the ultimate loads determined in the para-chute strength test described in 6.2.1.6.3.5.2 The

31、 harness system and attach points must beconfigured in a manner that presents the aircraft in a descentand landing attitude that maximizes the ability of the aircraftstructure to absorb the anticipated landing loads and minimizesthe probability of injury to the occupants.6.3.5.3 The airframe attachm

32、ent harness must be routedfrom the installed parachute to the airframe attachment pointsand secured in a manner that will prevent it from impactingnormal operations. It must also be shown that the harness willbe satisfactorily stripped free upon extraction and inflation ofthe parachute.6.3.5.4 The a

33、irframe attachment harness design must mini-mize the potential for conflict with the propeller. If conflictwith the propeller is unavoidable by installation design oroperator instructions such as shutting down the engine, theaircraft attachment harness must be manufactured from mate-rials that yield

34、 a reasonable likelihood of surviving a conflictwith the propeller.6.3.6 Activating Housing RoutingThe parachute systemmust be designed for activation without difficulty. The airframeand parachute manufacturers must coordinate and agree toinsure that the installation of the activation system in thes

35、ubject airframe complies with the following conditions:6.3.6.1 The routing of the activation system shall not createfriction points or other interruptions that may reduce theoccupants ability to activate the system.6.3.6.2 The activating system shall be secured along its pathsuch that it will not ch

36、ange during the normal operating life ofthe parachute system.6.3.6.3 If dual activating handles are used, they must be ofa design that allows activation with one handle, even if theother handle is inoperable. An airframe manufacturer electingto offer dual handle activation must coordinate installati

37、on withthe manufacturer of the ballistic parachute system.F23160826.3.6.4 It must be shown that arming and activating thesystem can only be accomplished in a sequence that makesinadvertent deployment extremely improbable. The systemmust not be armed before the initiation of activation proce-dures.6.

38、3.6.5 Some means to secure the activation system must beimplemented when the aircraft is not in service.6.3.7 Occupant RestraintEach seat in an airplane modi-fied or fitted with the emergency parachute system must beequipped with a restraint system consisting of a seat belt andshoulder harness that

39、will protect the occupants from head andupper torso injuries during parachute deployment and groundimpact at the critical load conditions.7. Workmanship, Finish and Appearance7.1 Workmanship must be of a high standard and performedin accordance with QA standards as established by industryconsensus (

40、possibly stand-alone standards established withinthe ASTM structure, see S3.1).8. System Function and Operations8.1 The installation design and location of the extractiondevice must consider fire hazards associated with the activationof the parachute system and reduce this potential as much aspossib

41、le without compromising function of the extractiondevice.8.2 The parachute system must be labeled to show itsidentification, function, and operation limitations.8.3 All components of the parachute system must be pro-tected against deterioration or loss of strength in service as aresult of normal wea

42、r, weathering, corrosion, and abrasion.9. Inspection and Maintenance9.1 Owners of parachute system must follow the parachutesystem manufacturers maintenance schedule.9.2 Instructions for continued airworthiness must be pre-pared for the parachute system and shall state the service cyclesfor relevant

43、 components of the system, including but notlimited to:9.2.1 Parachute canopy inspection and repacking.9.2.2 Extraction device inspection and refueling or replace-ment.9.3 If the maintenance schedule is not followed, the para-chute must be marked “Inoperative.”9.4 Adequate means must be provided to

44、permit annualexamination of the parachute container and other systemcomponents to ensure proper functioning, egress alignment,and security of harness bridles and activating housing.9.5 Specific climates may require modification to the para-chute systems inspection procedures.10. Operating Limitation

45、s10.1 Operating limitations must be prescribed to ensureproper operation of the parachute system.11. Product Marking11.1 Key components of the parachute system must bemarked on the container with the following information:11.1.1 Manufacturers identification,11.1.2 Part number and revision,11.1.3 Ser

46、ial number,11.1.4 Date of manufacture, and11.1.5 Service interval date.11.2 The parachute manufacturer or airframe manufacturermust supply placards or labels for placement in unobstructedview of the occupants or anyone near the egress point(exterior). Refer to 10.1 for operating limitations.11.3 The

47、 owner/operator must display placards or labels forthe cockpit or exterior such that these placards or labels can beseen by first responders at accident or incident sites.11.3.1 ScopeThese placards or labels are to provide avisual warning to rescue or other personnel at the scene of anaccident or in

48、cident in the event that the aircraft involved isequipped with a ballistically-deployed emergency parachutesystem. A ballistic device may include rocket motor, mortar,explosive projectile, spring, or other stored energy device.11.3.2 SourceThe manufacturer of parachute system orairframe shall supply

49、 the required warning placards or labelswith the product in accordance with this specification.11.3.3 Installation and Size of Placard or LabelTheairframe manufacturer or builder shall permanently install thewarning placards or labels in a manner specified by thisspecification.11.3.3.1 Danger PlacardA 7.62-cm (3-in.) minimum tri-angular placard or label with the word “Danger” (see proposedplacard in Appendix X1) must be placed adjacent to theparachute egress point for enclosed aircraft where the para-chute system may not be visible from the exteri