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
25、of the vent by ice.5.9 Vibration GeneralThe engine must be designed andconstructed to function throughout its normal operating rangeof crankshaft rotational speeds and engine powers withoutinducing excessive stress in any of the engine parts.5.9.1 The engine must have a crankshaft vibration survey t
26、odetermine torsional and bending characteristics from idle speedup to maximum desired takeoff speed. This survey should bedone with a representative propeller and no hazardous condi-tions would be allowed.6. Qualification Tests6.1 Calibration TestEach engine design shall be testedand the characteris
27、tics of engine rated power, speeds, and fuelconsumption shall be determined.6.2 Detonation TestEach engine shall be tested to confirmthat the engine will not detonate throughout its range ofintended conditions of operation using the fuel which thedesigner/manufacturer has specified for the engine.6.
28、3 Durability TestingEach engine model must be sub-jected to an engine test that will verify durability by one of thefollowing methods.6.3.1 Accelerated Overhaul TestThis test simulates anengine overhaul interval. A protocol for this test shall incorpo-rate, as a minimum, the following elements:6.3.1
29、.1 At least 100 % of the time at maximum power thatwould occur over the overhaul interval.NOTE 1For calculation, each hour of normal flight would have 5 minof full power.6.3.1.2 At least 10 % of the time at cruise power that wouldoccur over the overhaul interval.6.3.1.3 At least one cycle per hour o
30、f test from maximumpower to cruise power and back.6.3.1.4 At least one engine start for each5hoftesting.6.3.1.5 During operation at maximum power, one cylindermust be maintained within 10F of the limiting cylinder headtemperature; the other cylinders must be operated at a tempera-ture not lower than
31、 50F below the limiting temperature, andthe oil inlet temperature must be maintained within 10F of thelimiting temperature.6.3.1.6 The engine must be fitted with a propeller thatthrust-loads the engine to the maximum thrust that the engineis designed to resist at each applicable operating conditions
32、pecified in this section.6.3.1.7 Each accessory drive and mounting attachment mustbe loaded. During operation at maximum power, the loadimposed by each accessory used only for an aircraft servicemust be the limit load specified by the applicant for the enginedrive or attachment point.6.3.1.8 After c
33、ompleting the accelerated overhaul test, eachengine must be completely disassembled and each componentmust conform to the new or overhaul limits established by thedesigner/manufacturer.6.3.2 Endurance Testing by Fleet LeaderIn place of theaccelerated overhaul test in 6.3.1, the engine may completeen
34、durance flight testing.6.3.2.1 The Fleet Leader Test Method is the operation of themake and model of the engine being developed on a flyingaircraft under the control of the engine manufacturer.F23390626.3.2.2 All engine maintenance must be documented on theengine, and no components may be replaced o
35、n the engineduring the test. If components are changed, the test must restartas0h.6.3.2.3 Periodic inspection must be performed. The flighttests shall subject the engine to all atmospheric conditions forwhich the manufacture states the engine may operate under inthe operating manual required in 4.2.
36、3.NOTE 2Atmospheric conditions in 6.3.2.3 are intended to coveroutside air temperatures, density altitudes, and humidity.6.3.2.4 There must be at least one engine start for each 5 hof operation.6.3.2.5 The engine must be fitted with a propeller thatthrust-loads the engine to the maximum thrust that
37、the engineis designed to resist at full power.6.3.2.6 Each accessory drive and mounting attachment mustbe loaded. The load imposed by each accessory used only foran aircraft service must be the limit load specified by theapplicant for the engine drive of attachment point.6.3.2.7 After completing the
38、 Endurance Test, each enginemust be completely disassembled and each component mustconform to the new or overhaul limits established by thedesigner/manufacturer.6.4 Engine Overhaul IntervalThe engine overhaul inter-val shall be reported in the operations manual (see 4.2.3)aseither the overhaul time
39、used to complete the acceleratedoverhaul test in 6.3.1 or 80 % of the time accumulated on theengine model fleet leader method from 6.3.2.7. Manufacturing Requirements7.1 The engine manufacturer shall establish inspections andtests necessary to ensure that each article produced conforms tothe design
40、and is in a condition for safe operation, including asapplicable:7.1.1 Inspections for raw materials, purchased items, andparts and assemblies produced by suppliers, including methodsused to ensure acceptable quality of parts and assemblies thatcannot be completely inspected for conformity and quali
41、tywhen delivered to the engine manufacturers facility.7.1.2 Production inspection of individual parts and com-plete assemblies, including the identification of any specialmanufacturing processes involved, the means used to controlthe processes, and the final test procedure for the completedengine.7.
42、1.3 A nonconforming materials review system that in-cludes documentation of parts disposition decisions, and asystem to dispose of rejected parts.7.1.4 A system for informing company inspectors of currentchanges in engineering drawings, specifications, and qualitycontrol procedures.8. Keywords8.1 li
43、ght sport aircraft; reciprocating spark ignition engineANNEXA1. RECIPROCATION OF SPARK IGNITION ENGINESA1.1 Electronic Engine Control SystemsA1.1.1 Software and Programmable Logic DevicesAnysystem, component, or sub-assembly which utilizes software orfirmware shall demonstrate that the software or f
44、irmware hasbeen developed in accordance with best industry practices, andthe software development and verification activities have beenperformed in accordance with DO-178, Software Consider-ations in Airborne Systems and Equipment Certification, meth-odologies, or an equivalent methodology generally
45、 accepted bythe aviation industry. Further, the verification levels shall bespecified in the installation instructions as required, to ensurecompatibility with safety objectives.A1.1.2 The documentation and verification results shall beavailable for review by the relevant CAA as required.A1.1.3 Comp
46、lex Electronic HardwareAny system, com-ponent, or sub-assembly which utilizes complex electronichardware shall demonstrate that the hardware has been devel-oped in accordance with the best industry practices, and thehardware design and verification activities have been per-formed in accordance with
47、DO-254, Design Assurance Guid-ance for Airborne Electronic Hardware, methodologies, or anequivalent methodology generally accepted by the aviationindustry. Further, the verification levels shall be specified in theinstallation instructions as required, to ensure compatibilitywith the safety objectiv
48、es. The documentation and verificationresults shall be available for review by the relevant CAA asrequired.A1.2 Study DocumentsA1.2.1 FAA AC 33.282Guidance Material for 14 CFR33.28 Reciprocation Engines, Electrical and Electronic ControlSystemsF2339063ASTM International takes no position respecting
49、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 rights, 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 revision of this standard or for additional standardsand sh
