ASTM F2339-2006 Standard Practice for Design and Manufacture of Reciprocating Spark Ignition Engines for Light Sport Aircraft《轻型运动飞行器用往复式火花点火式发动机的设计和制造的标准实施规程》.pdf
《ASTM F2339-2006 Standard Practice for Design and Manufacture of Reciprocating Spark Ignition Engines for Light Sport Aircraft《轻型运动飞行器用往复式火花点火式发动机的设计和制造的标准实施规程》.pdf》由会员分享,可在线阅读,更多相关《ASTM F2339-2006 Standard Practice for Design and Manufacture of Reciprocating Spark Ignition Engines for Light Sport Aircraft《轻型运动飞行器用往复式火花点火式发动机的设计和制造的标准实施规程》.pdf(4页珍藏版)》请在麦多课文档分享上搜索。
1、Designation: F 2339 06Standard Practice forDesign and Manufacture of Reciprocating Spark IgnitionEngines for Light Sport Aircraft1This standard is issued under the fixed designation F 2339; the number immediately following the designation indicates the year oforiginal adoption or, in the case of rev
2、ision, the year of last revision. 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 practice covers minimum requirements for thedesign and manufacture of reciprocating spark ign
3、ition enginesfor light sport aircraft, VFR use.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 regu
4、latory limitations prior to use.2. Significance and Use2.1 This practice provides designers and manufacturers ofengines for light sport aircraft design references and criteria touse in designing and manufacturing engines.2.2 Declaration of compliance is based on testing anddocumentation during the d
5、esign and testing or flight testing ofthe engine type by the manufacturer or under the manufactur-ers guidance.3. Engine Model Designation3.1 Engine Parts ListA parts list is required for eachengine model qualified in accordance with this specification.3.2 New Engine Model Designations:3.2.1 Each ne
6、w engine model must be qualified in accor-dance with this practice.3.2.2 Design or configuration changes that impact the in-stallation interface, performance, or operability of the enginerequire a new engine model designation.3.3 Design Changes of PartsEach design change of a partor component of an
7、engine model qualified to this specificationshould be evaluated relative to the requirements of thisspecification.4. Data Requirements4.1 Retained DataThe following data and informationshould be retained on file at the manufacturers facility for at aminimum of 18 years after production is discontinu
8、ed.4.1.1 Drawings that define the engine configuration.4.1.2 Material and process specifications referenced in theparts drawings.4.1.3 Engineering analyses and test data prepared for quali-fication with this specification.4.2 Delivered DataThe following data should be deliv-ered to the airplane manu
9、facturer to support design andoperation of the applicable airplane.4.2.1 An engine performance specification that defines theengine performance under all anticipated operating environ-ments.4.2.2 An installation manual that defines all functional andphysical interface requirements of the engine. Thi
10、s shouldinclude an engine outline/installation drawing.4.2.3 An operating manual that defines normal and abnor-mal operating procedures and any applicable operating limita-tions.4.2.4 A maintenance manual that defines periodic installedmaintenance, major inspection, overhaul intervals, and anyother
11、maintenance limitations.4.2.5 An overhaul manual that provides instruction fordisassembling the engine to replace or repair, or both, parts asrequired to return the engine to airworthy condition that is safefor operation until the next major overhaul.5. Design Criteria5.1 MaterialsThe materials used
12、 in the engine must beadequate for the intended design conditions of the engine.5.2 Fire PreventionThe design and construction of theengine and the materials used must minimize the probability ofthe occurrence and spread of fire by:5.2.1 Using fire-resistant lines, fittings, and other compo-nents th
13、at contain a flammable liquid when supplied with theengine; and5.2.2 Shielding or locating components to safeguard againstthe ignition of leaking flammable fluid.5.3 Engine CoolingThe engine design must include pro-visions for cooling; the installation manual must specify engineand component tempera
14、ture limitations.1This practice is under the jurisdiction of ASTM Committee F37 on Light SportAircraft and is the direct responsibility of Subcommittee F37.70 on Cross Cutting.Current edition approved June 1, 2006. Published June 2006. Originallyapproved in 2004. Last previous edition approved in 20
15、05 as F 2339 05.1Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.5.4 Engine MountingAttach points on the engine musthave data for the correct design of mounting structures to theairframe. The maximum allowable limit and ultimate loads
16、 forthe engine mounting attachments and related structure must bespecified.5.5 Ignition SystemsEach spark ignition engine must havea dual-ignition system with at least two spark plugs for eachcylinder and two separate electric circuits with separate sourcesof electrical energy, or have an ignition s
17、ystem of equivalentin-flight reliability. System maintenance must be specifiedunder the maintenance manual supplied by the manufacturer.5.5.1 Engines used in aircraft where the engine is notrequired for flight, for example, gliders, can be single ignition.5.5.2 Engines for use in only single seat ai
18、rcraft may usesingle ignition.5.6 Electronic Engine Controllers (EEC):5.6.1 Essentially Single Fault ToleranceThe EEC shouldbe designed to accommodate single failures of the electricalcircuit. Loss of any single EEC should not cause significantpower reduction or engine stoppage.5.6.2 The functioning
19、 of EECs must not be adverselyaffected by the declared environmental conditions of operationby the manufacturer, including temperature and moisture. Thelimits to which the system has been qualified shall be docu-mented in the installation manual. For protection againstradiated EMI/HIRF, the harnesse
20、s or cables should be shieldedfrom each sensor to each end point and electrically bonded tothe engine. Filter pin connectors should be located at thecontroller housing interface and shunted to ground on the case.Filter pin connectors should have 40 dB attenuation, minimum.For EMI emissions, powerlin
21、e filters suppress emissions fromthe controller on outgoing signals.5.7 Fuel and Induction System:5.7.1 Induction System IcingThe fuel and air intake pas-sages must be designed to minimize the accretion of ice.5.7.2 FilteringThe type and degree of fuel and air filter-ing necessary to prevent obstruc
22、tion of air or fuel flow must bespecified.5.7.3 Liquid LockEach passage in the induction systemthat conducts a mixture of fuel and air must be self-draining ordemonstrated to not cause damage from hydraulic lock onstarting.5.8 Lubrication System:5.8.1 The lubrication system of the engine must be des
23、ignedand constructed so that it will function properly in all flightattitudes and atmospheric conditions in which the engine isexpected to operate. In wet sump engines, this requirementmust be met when only one-half of the maximum lubricantsupply is in the engine.5.8.2 The lubrication system of the
24、engine must be designedand constructed to allow installing a means of cooling thelubricant if required.5.8.3 The crankcase on four-stroke engines must be ventedto the atmosphere to preclude leakage of oil from excessivepressure in the crankcase. This venting must have a means toprevent the blockage
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