1、Designation: F2316 08 (Reapproved 2010)Standard Specification forAirframe Emergency Parachutes for Light Sport Aircraft1This standard is issued under the fixed designation F2316; the number immediately following the designation indicates the year oforiginal adoption or, in the case of revision, the
2、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 covers minimum requirements for thedesign, manufacture, and installation of parachutes for
3、lightsport aircraft.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 aviat
4、ion community mixed 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
5、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 requirements prior to use.2. Referenced Documents2.1 FAA Document:2
6、FAA Special Conditions 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
7、-ing a safety pin.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 propert
8、ies assumed in thedesign 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
9、 for each airframe 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 operabili
10、tyrequire a new 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 d
11、esign of their aircraftunder 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 Stren
12、gth requirements 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 fo
13、r components other 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 sup
14、ported withinstrument 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 CrossCuttin
15、g.Current edition approved Dec. 1, 2010. Published March 2011. Originallyapproved in 2003. Last previous edition approved in 2008 as F2316 08. DOI:10.1520/F2316-08R10.2Available from Ballistic Recovery Systems, Inc., 380 Airport Rd., South St.Paul, MN 55075.1Copyright ASTM International, 100 Barr Ha
16、rbor Drive, PO Box C700, West Conshohocken, 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 ul
17、timate load conditions to demonstrate 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 by
18、applying the Energy Method represented 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. The
19、refore, theUltimate Load Factor = (1.25) 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
20、 of descent data shall be re-corded for 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
21、and standard temperature.6.2.3 Component 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
22、sequence in an orderlymanner to reduce 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 pr
23、ovide a specific ParachuteInstallation 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 t
24、o ensure proper installation. Air-frame 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 m
25、anufacturer, the aircraft builder, or 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 syste
26、m shall not become loosened or detached 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 inhibit
27、ing ordamaging the parachute upon egress. 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
28、anemergency situation (for example, broken 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
29、 with an airframe attachment harness that 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 Parachu
30、te deployments induce unique load distribu-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 streng
31、th test described in 6.2.1.6.3.5.2 The 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
32、occupants.6.3.5.3 The airframe attachment 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 i
33、nflation ofthe parachute.6.3.5.4 The airframe 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 m
34、anufactured from mate-rials that yield 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 install
35、ation of the activation system in thesubject 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
36、along its pathsuch that it will not change 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
37、 activation must coordinate installation withthe manufacturer of the ballistic parachute system.F2316 08 (2010)26.3.6.4 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 befo
38、re the initiation of activation proce-dures.6.3.6.5 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 consi
39、sting of a seat belt andshoulder harness that 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 s
40、tandards as established by industryconsensus (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 sys
41、tem and reduce this potential as much aspossible 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 o
42、f strength in service as aresult of normal wear, 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
43、and shall state the service cyclesfor relevant 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 “Inoper
44、ative.”9.4 Adequate means must be provided to 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
45、inspection procedures.10. Operating Limitations10.1 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 identificat
46、ion,11.1.2 Part number and revision,11.1.3 Serial 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). Re
47、fer to 10.1 for operating limitations.11.3 The 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 ot
48、her personnel at the scene of anaccident or incident 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 manufactur
49、er of parachute system orairframe shall supply 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-
