1、Designation: F3232/F3232M 17Standard Specification forFlight Controls in Small Aircraft1This standard is issued under the fixed designation F3232/F3232M; the number immediately following the designation indicates the yearof original adoption or, in the case of revision, the year of last revision. A
2、number in parentheses indicates the year of last reapproval.A superscript epsilon () indicates an editorial change since the last revision or reapproval.1. Scope1.1 This specification covers international standards for theflight control aspects of airworthiness and design for “small”aircraft.1.2 The
3、 applicant for a design approval must seek theindividual guidance of their respective CAA body concerningthe use of this specification as part of a certification plan. Forinformation on which CAA regulatory bodies have acceptedthis specification (in whole or in part) as a means of compli-ance to the
4、ir Small Aircraft Airworthiness regulations (herein-after referred to as “the Rules”), refer to ASTM F44 webpage(www.ASTM.org/COMMITTEE/F44.htm) which includesCAA website links.1.3 The values stated in either SI units or inch-pound unitsare to be regarded separately as standard. The values stated in
5、each system may not be exact equivalents; therefore, eachsystem shall be used independently of the other. Combiningvalues from the two systems may result in non-conformancewith the standard.1.4 This standard does not purport to address all of thesafety concerns, if any, associated with its use. It i
6、s theresponsibility of the user of this standard to establish appro-priate safety and health practices and determine the applica-bility of regulatory limitations prior to use.2. Referenced Documents2.1 Following is a list of external standards referencedthroughout this specification; the earliest re
7、vision acceptablefor use is indicated. In all cases later document revisions areacceptable if shown to be equivalent to the listed revision, or ifotherwise formally accepted by the governing civil aviationauthority; earlier revisions are not acceptable.2.2 ASTM Standards:2F3060 Terminology for Aircr
8、aftF3061/F3061M Specification for Systems and Equipment inSmall AircraftF3082/F3082M Specification for Flight for GeneralAviationAeroplanesF3116/F3116M Specification for Design Loads and Condi-tionsF3117 Specification for Crew Interface in AircraftF3230 Practice for Safety Assessments of Systems and
9、Equipment in Small Aircraft2.3 Other Standards:RTCA/DO-335 Guidance for Installation of AutomaticFlight Guidance and Control Systems (AFGCS) for Part23 Airplanes33. Terminology3.1 Terminology specific to this specification is providedbelow. For general terminology, refer to Terminology F3060.3.2 Def
10、initions of Terms Specific to This Standard:3.2.1 aircraft type code, nan Aircraft Type Code (ATC) isdefined by considering both the technical considerations re-garding the design of the aircraft and the airworthiness levelestablished based upon risk-based criteria; the method ofdefining an ATC appl
11、icable to this specification is defined inSpecification F3061/F3061M.3.2.2 continued safe flight and landing, ncontinued safeflight and landing as applicable to this specification is definedin Specification F3061/F3061M.3.2.3 single failure, na single failure as applicable to thisspecification is de
12、fined in Practice F3230.4. Manual Flight ControlsNOTE 1Table 1 provides correlation between various Aircraft TypeCodes and the individual requirements contained within this section; referto 3.2.1. For each subsection, an indicator can be found under each ATCcharacter field; three indicators are used
13、:An empty cell ( ) in all applicable ATC character field columnsindicates that an aircraft must meet the requirements of that subsection.A white circle () in multiple columns indicates that the requirementsof that subsection are not applicable to an aircraft only if all such ATCcharacter fields are
14、applicable.A mark-out () in any of the applicable ATC character field columnsindicates that the requirements of that subsection are not applicable to an1This specification is under the jurisdiction ofASTM Committee F44 on GeneralAviation Aircraft and is the direct responsibility of Subcommittee F44.
15、50 onSystems and Equipment.Current edition approved Feb. 15, 2017. Published March 2017. DOI: 10.1520/F3232_F3232M-17.2For referenced ASTM standards, visit the ASTM website, www.astm.org, orcontact ASTM Customer Service at serviceastm.org. For Annual Book of ASTMStandards volume information, refer t
16、o the standards Document Summary page onthe ASTM website.3Available from RTCA, Inc., 1150 18th St., NW, Suite 910, Washington, DC20036, http:/www.rtca.org.Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United StatesThis international standard was
17、developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for theDevelopment of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.1aircraft if th
18、at ATC character field is applicable.ExamplesAn aircraft with an ATC of 1SRLLDLN is being consid-ered. Since all applicable columns are empty for 4.1.2, that subsection isapplicable to the aircraft. However, since the “S” number-of-enginesTABLE 1 ATC Compliance Matrix, Section 4SectionAirworthiness
19、Level Number ofEnginesType ofEngine(s)Stall Speed Cruise Speed MeteorologicalConditionsAltitude Maneuvers1234SMRTLMHLHDN I LHNA44.14.1.14.1.24.1.34.1.3.14.1.44.1.4.14.1.4.24.24.2.14.2.24.34.3.14.3.24.3.34.44.4.14.4.24.4.34.4.44.4.54.4.6 4.4.7 4.4.84.54.5.14.5.2 4.5.34.64.6.14.6.1.14.6.24.74.7.14.7.2
20、4.7.34.84.8.14.8.24.8.34.8.44.94.104.10.14.10.24.10.2.14.10.34.10.44.10.54.10.64.10.74.10.84.10.94.10.104.114.11.14.11.24.11.34.124.12.14.12.24.134.13.14.13.24.13.3 4.13.4 CCF3232/F3232M 172column for 4.4.7 contains an , then that subsection is not applicable.4.1 Control Surface Installation:4.1.1 M
21、ovable surfaces must be installed so that there is nointerference between any surfaces, their bracing, or adjacentfixed structure, when one surface is held in its most criticalclearance positions and the others are operated through theirfull movement.4.1.2 If an adjustable stabilizer is used, it mus
22、t have stopsthat will limit its range of travel to that allowing safe flight andlanding.4.1.3 Control surface hinges, except ball and roller bearinghinges, must have a factor of safety of not less than 6.67 withrespect to the ultimate bearings strength of the softest materialused as a bearing.4.1.3.
23、1 For ball or roller bearing hinges, the approved ratingof the bearing may not be exceeded.4.1.4 Control system joints (in push-pull systems) that aresubject to angular motion, except those in ball and rollerbearing systems, must have a special factor of safety of not lessthan 3.33 with respect to u
24、ltimate bearing strength of thesoftest material used as a bearing.4.1.4.1 The factor specified in 4.1.4 may be reduced to 2.0for joints in cable control systems.4.1.4.2 For ball or roller bearings, the approved rating of thebearing may not be exceeded.4.2 Operation and Arrangement:4.2.1 Each control
25、 must operate easily, smoothly, and posi-tively enough to allow proper performance of its functions.4.2.2 Controls must be arranged and identified to providefor convenience in operation and so as to not cause confusionand subsequent inadvertent operation; refer to SpecificationF3117.4.3 Control Syst
26、em Stops:4.3.1 Each control system must have stops that positivelylimit the range of motion of each movable aerodynamic surfacecontrolled by the system.4.3.2 Each stop must be located so that wear, slackness, ortakeup adjustments will not adversely affect the control char-acteristics of the aircraft
27、 because of a change in the range ofsurface travel.4.3.3 Each stop must be able to withstand any loadscorresponding to the design conditions for the control system.4.4 Trim Systems:4.4.1 Proper precautions must be taken to preventinadvertent, improper, or abrupt trim tab operation.4.4.2 There must b
28、e means near the trim control to indicateto the pilot the direction of trim control movement relative toaircraft motion.4.4.3 There must be means to indicate to the pilot theposition of the trim device with respect to both the range ofadjustment and, in the case of lateral and directional trim, then
29、eutral position.4.4.4 The means provided to satisfy the requirements of4.4.2 and 4.4.3 must be visible to the pilot and must be locatedand designed so as to not cause confusion.4.4.5 The pitch trim indicator must be clearly marked witha position or range within which it has been demonstrated thattak
30、e-off is safe for all center of gravity positions and each flapposition approved for takeoff.4.4.6 Trimming devices must be designed so that, when anyone connecting or transmitting element in the primary flightcontrol system fails, adequate control for safe flight andlanding is available with the lo
31、ngitudinal trimming devices.4.4.7 Trimming devices must be designed so that, when anyone connecting or transmitting element in the primary flightcontrol system fails, adequate control for safe flight andlanding is available with the longitudinal and directionaltrimming devices.4.4.8 Tab controls mus
32、t be irreversible unless the tab isproperly balanced and has no unsafe flutter characteristics.Irreversible tab systems must have adequate rigidity andreliability in the portion of the system from the tab to theattachment of the irreversible unit to the aircraft structure.4.5 Control System Locks:4.
33、5.1 If there is a device to lock the control system on theground or water, there must be a means to give unmistakablewarning to the pilot when lock is engaged, or to automaticallydisengage the device when the pilot operates the primary flightcontrols in a normal manner.4.5.2 If there is a device to
34、lock the control system on theground or water, the device must be installed to limit theoperation of the aircraft so that, when the device is engaged,the pilot receives unmistakable warning at the start of thetakeoff.4.5.3 If there is a device to lock the control system on theground or water, the de
35、vice must have a means to preclude thepossibility of it becoming inadvertently engaged in flight.4.6 Limit Load Static Tests:4.6.1 Compliance with established limit load requirementsmust be shown by limit load tests in which the direction of thetest loads produces the most severe loading in the cont
36、rolsystem.4.6.1.1 In meeting the requirements of 4.6.1, each fitting,pulley, and bracket used in attaching the system to the mainstructure must be included.4.6.2 Compliance must be shown by analysis or by indi-vidual load tests with the special factor requirements forcontrol system joints subject to
37、 angular motion.4.7 Operation Tests:4.7.1 It must be shown by operation tests that, when thecontrols are operated from the pilot compartment with thesystem loaded as prescribed in 4.7.2 and 4.7.3, the system isfree from jamming, excessive friction, excessive deflection, orany combination thereof.4.7
38、.2 For the entire system, the prescribed test loads arethose corresponding to the limit airloads on the appropriatesurface, or the limit pilot forces in Specification F3116/F3116M, whichever are less.4.7.3 For secondary controls, the prescribed test loads mustbe not less than those corresponding to
39、the maximum piloteffort established under Specification F3116/F3116M.4.8 Control System Details:F3232/F3232M 1734.8.1 Each detail of each control system must be designedand installed to prevent jamming, chafing, and interferencefrom cargo, passengers, loose objects, or the freezing ofmoisture.4.8.2
40、There must be means in the cockpit to prevent theentry of foreign objects into places where they would jam thesystem.4.8.3 There must be means to prevent the slapping of cablesor tubes against other parts.4.8.4 Each element of the flight control system must havedesign features, or must be distinctiv
41、ely and permanentlymarked, to minimize the possibility of incorrect assembly thatcould result in malfunction or reverse operation of the controlsystem.4.9 Spring DevicesThe reliability of any spring deviceused in the control system must be established by testssimulating service conditions unless fai
42、lure of the spring willnot cause flutter or unsafe light characteristics.4.10 Cable Systems:4.10.1 Each cable, cable fitting, turnbuckle, splice, andpulley used must meet specifications that are acceptable to thegoverning civil aviation authority.4.10.2 No cable smaller than 3.2 mm 0.125 in. diamete
43、rmay be used in primary control systems.4.10.2.1 Tab control cables are not part of the primarycontrol system and may be less than 3.2 mm 0.125 in.diameter in aircraft that are safely controllable with the tabs inthe most adverse positions.4.10.3 Each cable system must be designed so that there will
44、be no hazardous change in cable tension throughout the rangeof travel under operating conditions and temperature varia-tions.4.10.4 There must be means for visual inspection at eachfairlead, pulley, terminal, and turnbuckle.4.10.5 Each kind and size of pulley must correspond to thecable with which i
45、t is used.4.10.6 Each pulley must have closely fitted guards toprevent the cables from being misplaced or fouled, even whenslack.4.10.7 Each pulley must lie in the plane passing through thecable so that the cable does not rub against the pulley flange.4.10.8 Fairleads must be installed so that they
46、do not causea change in cable direction of more than 3.4.10.9 Clevis pins subject to load or motion and retainedonly by cotter pins may not be used in the control system.4.10.10 Turnbuckles must be attached to parts having angu-lar motion in a manner that will positively prevent bindingthroughout th
47、e range of travel.4.11 Wing Flap Controls:4.11.1 Each wing flap control must be designed so that,when the flap has been placed in any position upon whichcompliance with the performance requirements of the rules ofgoverning civil aviation authority is based, the flap will notmove from that position u
48、nless the control is adjusted or ismoved by the automatic operation of a flap load limitingdevice.4.11.2 The rate of movement of the flaps in response to theoperation of the pilots control or automatic device must givesatisfactory flight and performance characteristics under steadyor changing condit
49、ions of airspeed, engine power, and attitude;refer to Specification F3082/F3082M.4.11.3 If compliance with Specification F3082/F3082M ne-cessitates wing flap retraction to positions that are not fullyretracted, the wing flap control lever settings corresponding tothose positions must be positively located such that a definitechange of direction of movement of the lever is necessary toselect settings beyond those settings.4.12 Wing Flap Position Information:4.12.1 There must be a means to provide wing flap positioninformation for flap installations with only the
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