1、Designation: F 2316 06Standard 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 (e) 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 airc
3、raft.1.2 The values stated in inch-pound units are to be regardedas the standard. The values in parentheses are for informationonly.1.3 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 establ
4、ish 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 Conditions 23-ACE-76 (Docket No. 118C),Ballistic Recovery Systems, Modified for Small GeneralAviation Aircraft3. Terminology3.1 D
5、efinitions 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 pin.4. Materials and Manufacture4.1 MaterialsMaterials used for parts and assemblies, thefailure of which could adversely affec
6、t 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 thedesign data must meet approved specifications.4.1.3 The effects of environmental conditions, such astemperature and humidit
7、y, expected in service must be takeninto account.5. Parachute Model Designations5.1 Parachute System Parts ListAparts list is required foreach parachute system for each airframe model in accordancewith this specification.5.2 New Parachute Model DesignationsEach new para-chute system model must be qu
8、alified in accordance with thisspecification.5.3 Design ChangesDesign or configuration changes thatimpact the parachute installation, performance, or operabilityrequire a new parachute model designation. Each designchange of a part or component of a parachute system qualifiedby this specification mu
9、st 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 aircraftunder this specification shall, as soon as possible, inform theparachute manufacturer about changes that may affect th
10、emounting, attaching, deployment, egress, or specifications ofthe parachute system.6. Parachute System Design Requirements6.1 Strength Requirements:6.1.1 Strength requirements are specified in terms of limitsloads (the maximum loads to be expected in service) andultimate loads (limit loads multiplie
11、d by prescribed factors ofsafety). The minimum factor of safety, or ultimate load factor,shall be 1.5. Compliance with strength requirements forcomponents other than the parachute assembly may be dem-onstrated by analysis or testing.6.1.2 System evaluation by analysis must use an acceptedcomputation
12、al method that has been verified through testing. Inother cases, load testing must be conducted.6.1.3 System evaluation by testing must be supported withinstrument calibration verified by an applicable weights andmeasures regulatory body, for example, state and federalgovernments.6.2 System DesignTh
13、e following minimum performancestandards for the basic parachute system shall be met.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 edition approved Oct. 1, 2006. Published Oct
14、ober 2006. Originallyapproved in 2003. Last previous edition approved in 2003 as F 2316 03.2Available from Ballistic Recovery Systems, Inc., 300 Airport Rd., South St.Paul, MN 55075.1Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.6.2
15、.1 Parachute Strength TestA minimum of three suc-cessful drop tests of the parachute assembly shall be conductedto demonstrate the ultimate load factor defined below. A newparachute assembly may be used for each test. Data acquisitionshall include recordings of inflation loads as a function of time.
16、The ultimate load factor shall be achieved by using thefollowing test parameters:Test Weight = (Maximum Operating Weight Limit) 3 (1.25)Test Speed = (Maximum Operating Speed Limit) 3 (1.1)The aircrafts gross takeoff weight must be used as themaximum operating weight. However, the parachutes ultimate
17、load factor may be used to determine the maximum speed.6.2.2 Rate of DescentRate 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 dat
18、afrom parachute canopies shall be corrected to 5000-ft (1500-m)density altitude 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 S
19、taged DeploymentThe parachute assembly shall bedesigned to stage the deployment 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 to+120F (40 to 48.9C).6.
20、3 Installation DesignEach manufacturer of an emer-gency parachute system shall provide a general ParachuteInstallation Manual (PIM) with the documentation described inS2. The PIM shall be used for all installations with partiesreferenced in 6.3.1.6.3.1 CoordinationAirframe and parachute manufacturer
21、smust coordinate to ensure proper installation. Airframe manu-facturers of light sport aircraftspecial (fully built) must notalter the installation without consulting the parachute systemmanufacturer. For light sport aircraftexperimental (kit built),the parachute manufacturer shall work with a new o
22、riginalequipment manufacturer, the aircraft builder, or the aircraftowner 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
23、theparachute system 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 stret
24、ch without inhibiting 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
25、 unpredictable in 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 struct
26、ure of theaircraft with an airframe attachment harness that may becomposed of a single harness section or a series of harnesssections. The airframe and parachute manufacturers mustcoordinate to ensure that the parachute attachment to thesubject airframe complies with the following conditions:6.3.5.1
27、 Parachute deployments induce unique load distribu-tions to the airframe. The airframe attachment points andairframe attachment harness must be shown to comply with theultimate loads determined in the parachute strength test de-scribed in 6.2.1. Limit load factors at each attachment pointmust be det
28、ermined for each specific aircraft design andaircraft attachment harness geometry at critical flight condi-tions.6.3.5.2 The harness system and attach points must beconfigured in a manner that presents the aircraft in a descentand landing altitude that maximizes the ability of the aircraftstructure
29、to absorb the anticipated landing loads and minimizesthe probability of injury to the 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 al
30、so be shown that the harness willbe satisfactorily stripped free upon extraction and inflation 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 i
31、nstructions such as shutting down the engine, theaircraft attachment harness must be manufactured 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 a
32、irframeand parachute manufacturers must coordinate to insure that theinstallation of the activation system in the subject airframecomplies 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 ab
33、ility to activate the system.6.3.6.2 The activating system shall be secured 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
34、 handle is inoperable. An airframe manufacturer electingto offer dual handle activation must coordinate installation withthe manufacturer of the ballistic parachute system.6.3.6.4 It must be shown that arming and activating thesystem can only be accomplished in a sequence that makesinadvertent deplo
35、yment extremely improbable. The systemmust not be armed before 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.F23160626.3.7 Occupant RestraintEach seat in an airplane modi-fied or fitted with the emer
36、gency parachute system must beequipped with a restraint system consisting 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 Workman
37、ship must be of a high standard and performedin accordance with QA standards 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 cons
38、ider fire hazards associated with the activationof the parachute system 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
39、 parachute system must be pro-tected against deterioration or loss of 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
40、 continued airworthiness must be pre-pared for the parachute system 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 mainten
41、ance schedule is not followed, the para-chute must be marked “Inoperative.”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 S
42、pecific climates may require modification to the para-chute systems 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 conta
43、iner with the following information:11.1.1 Manufacturers identification,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 unobstructe
44、dview of the occupants or anyone near the egress point(exterior). Refer 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 ScopeThe
45、se placards or labels are to provide avisual warning to rescue or other 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 projectil
46、e, spring, or other stored energy device.11.3.2 SourceThe manufacturer 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 p
47、ermanently install thewarning placards or labels in a manner specified by thisspecification.11.3.3.1 Danger PlacardA 3-in. (7.62-cm) 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 airc
48、raft where the para-chute system may not be visible from the exterior.NOTE 1Not all ballistically-deployed emergency parachutes egressthe upper surface of an aircraft. Some systems egress the underside of theaircraft. Therefore, an aircraft turned upside down in an accident orincident should display
49、 a label on the underside (Appendix X1 contains anexample of such labeling).(1) Danger Placard Text ExplanationAn explanatorybox shall be printed next to the “Danger” placard or label (seeproposed placard in Appendix X1).(2) The danger explanatory box shall describe the type ofballistic deployment device and provide contact informationfor rescue personnel to seek help from the manufacturer of theballistic device (see proposed placard in Appendix X1).11.3.3.2 Danger PlacardA 2-in. (5.08 cm) minimumtriangular placard or label (see proposed placard i
