1、Designation: F3233/F3233M 17Standard Specification forInstrumentation in Small Aircraft1This standard is issued under the fixed designation F3233/F3233M; 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 theinstrumentation aspects of airworthiness and design for “small”aircraft.1.2 Th
3、e 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 th
4、eir 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 i
5、neach 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
6、is 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 referencethroughout 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 AircraftF3120/F3120M Specification for Ice Protection for Ge
9、neralAviation AircraftF3229/F3229M Practice for Static Pressure System Tests inSmall AircraftF3230 Practice for Safety Assessments of Systems andEquipment in Small Aircraft3. Terminology3.1 Terminology specific to this specification is providedbelow. For general terminology, refer to Terminology F30
10、60.3.2 Definitions: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 applicable to this specificat
11、ion 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 high speed, nan aircrafts performance level isconsidered high speed if VNEor VNOis greater than 463
12、 km/h250 knots, or MMOis greater than M0.6.3.2.4 instrument, nthe term instrument includes devicesthat are physically contained in one unit or component, anddevices that are composed of two or more physically separateunits or components connected together (such as a remoteindicating gyroscopic direc
13、tion indicator that includes a mag-netic sensing element, a gyroscopic unit, an amplifier, and anindicator connected together).3.2.5 low speed, nan aircrafts performance level is con-sidered low speed if VNEor VNOis less than or equal to 463km/h 250 knots, or MMOis less than or equal to M0.6.3.2.6 p
14、rimary display, nprimary display refers to thedisplay of a parameter that is located such that the pilot looksat it first when wanting to view that parameter.1This specification is under the jurisdiction ofASTM Committee F44 on GeneralAviation Aircraft and is the direct responsibility of Subcommitte
15、e F44.50 onSystems and Equipment.Current edition approved Feb. 15, 2017. Published March 2017. DOI: 10.1520/F3233_F3233M-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, r
16、efer to the standards Document Summary page onthe ASTM website.Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United StatesThis international standard was developed in accordance with internationally recognized principles on standardization establ
17、ished 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.14. InstrumentationNOTE 1Table 1 provides correlation between various Aircraft TypeCodes and the individual
18、 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:An empty cell ( ) in all applicable ATC character field columnsindicates that an aircraft must meet the requirements of that subsection.
19、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 applicable.A mark-out () in any of the applicable ATC character field columnsindicates that the requirements of that subsection are not a
20、pplicable to anaircraft if that ATC character field is applicable.ExampleAn aircraft with anATC of 1SRLLDLN is being considered.Since all applicable columns are empty for 4.1.3, that subsection isapplicable to the aircraft. Since both the “R” engine type column and the“L” cruise speed column for 4.1
21、.4 contain white circles, then thatsubsection is not applicable; however, for an aircraft with an ATC of1SRLHDLN, 4.1.4 would be applicable since the “H” cruise speedcolumn does not contain a white circle. 4.1.5 would not be applicable toeither aircraft, since it contains an in the “R” engine type c
22、olumn.4.1 Flight and Navigation Instruments:4.1.1 A means to determine airspeed must be provided.4.1.2 A means to determine altitude must be provided.4.1.3 A means to determine aircraft heading or direction offlight must be provided.NOTE 2The choice of technology to meet this requirement may bemanda
23、ted by some governing aviation authorities due to external require-ments; for example, a magnetic direction indicator.4.1.4 A means to determine free air temperature must beprovided.4.1.5 A speed warning device must be provided for turbine-engine-powered aircraft.4.1.6 A speed warning device must be
24、 provided for aircraftfor which VMO/MMOand VD/MDare established under Speci-fication F3116/F3116M and Specification F3082/F3082M ifVMO/MMOis greater than 0.8 VD/MD.4.1.7 Any speed warning device required by 4.1.5 or 4.1.6must give effective aural warning (differing distinctively fromaural warnings u
25、sed for other purposes) to the pilots wheneverthe speed exceeds VMOplus 11.11 km/h 6 knots or MMO+0.01.4.1.8 The upper limit of the production tolerance for anyspeed warning device required by 4.1.5 or 4.1.6 may notexceed the prescribed warning speed.4.1.9 The lower limit of any speed warning device
26、 requiredby 4.1.5 or 4.1.6 must be set to minimize nuisance warnings.4.1.10 If an attitude display is installed, the instrumentdesign must not provide any means, accessible to the flightcrew, of adjusting the relative positions of the attitude refer-ence symbol and the horizon line beyond that neces
27、sary forparallax correction.4.1.11 If airspeed limitations vary with altitude, the airspeedindicator must have a maximum allowable airspeed indicatorshowing the variation of VMOwith altitude.4.1.12 The altimeter must be a sensitive type.4.1.13 A third attitude instrument must be provided thatmeets t
28、he requirements of 4.1.13.1 4.1.13.6.4.1.13.1 In showing compliance with 4.1.13, the instrumentmust be powered from a source independent of the electricalgenerating system.4.1.13.2 In showing compliance with 4.1.13, the instrumentmust continue reliable operation for a minimum of 30 min aftertotal fa
29、ilure of the electrical generating system.4.1.13.3 In showing compliance with 4.1.13, the instrumentmust operate independently of any other attitude indicatingsystem.4.1.13.4 In showing compliance with 4.1.13, the instrumentmust be operative without selection after total failure of theelectrical gen
30、erating system.4.1.13.5 In showing compliance with 4.1.13, the instrumentmust be located in a position acceptable to the governing civilaviation authority that will make it plainly visible to and usableby any pilot at the pilots station.4.1.13.6 In showing compliance with 4.1.13, the instrumentmust
31、be appropriately lighted during all phases of operation.4.1.14 Instrument panel vibration may not damage, orimpair the accuracy of, any instrument.4.1.15 The instrument lights must have enough distance orinsulating material between current-carrying parts and thehousing so that vibration in flight wi
32、ll not cause shorting.4.2 Electronic Display Instrument Systems:4.2.1 Electronic display indicators must meet the arrange-ment and visibility requirements of Specification F3117.4.2.2 Electronic display indicators must not inhibit theprimary display of attitude, airspeed, altitude, or powerplantpara
33、meters needed by any pilot to set power within establishedlimitations, in any normal mode of operation.4.2.3 Electronic display indicators must not inhibit theprimary display of powerplant parameters needed by any pilotto properly set or monitor powerplant limitations during theengine starting mode
34、of operation.4.2.4 Electronic display indicators must have an indepen-dent magnetic direction indicator and either an independentsecondary mechanical altimeter, airspeed indicator, and atti-tude instrument or electronic display of parameters for altitude,airspeed, and attitude that are independent f
35、rom the aircraftsprimary electrical power system.4.2.5 If secondary instruments are installed to comply with4.2.4, they may be installed in panel positions that aredisplaced from the primary positions specified by SpecificationF3117, but must be located where they meet the pilotsvisibility requireme
36、nts of Specification F3117.4.2.6 Electronic display indicators must provide, whereappropriate, direction and rate of change of the parameterbeing displayed to the pilot.4.2.7 The electronic display indicators, including their sys-tems and installations, and considering other aircraft systems,must be
37、 designed so that one display of information essentialfor continued safe flight and landing will be available within 1s to the crew by a single pilot action or by automatic means forcontinued safe operation, after any single failure or probablecombination of failures (refer to Practice F3230).4.3 Ai
38、rspeed Indicating System:4.3.1 Each airspeed indicating instrument must be cali-brated to indicate true airspeed (at sea level with a standardatmosphere) with a minimum practicable instrument calibra-tion error when the corresponding pitot and static pressures areapplied.F3233/F3233M 172TABLE 1 ATC
39、Compliance Matrix, Section 4SectionAirworthiness Level Number ofEnginesType ofEngine(s)Stall Speed Cruise Speed MeteorologicalConditionsAltitude Maneuvers1234SMRTLMHLHDNILHNA44.14.1.14.1.24.1.34.1.4 CC4.1.5 4.1.64.1.74.1.84.1.94.1.104.1.11 4.1.12 4.1.13 4.1.13.1 4.1.13.2 4.1.13.3 4.1.13.4 4.1.13.5 4
40、.1.13.6 4.1.144.1.154.24.2.14.2.24.2.34.2.4 4.2.5 4.2.64.2.7 CC4.34.3.14.3.24.3.34.3.44.3.54.3.6 4.3.6.1 4.3.6.2 4.3.7 4.3.8 4.44.4.14.4.24.4.34.4.44.4.5 4.4.64.4.74.4.84.4.8.14.4.8.24.4.94.4.10 4.54.5.14.5.1.14.5.1.2 4.5.1.3 CC4.5.1.44.5.1.54.64.6.14.6.1.14.6.1.24.6.1.34.6.2 CC4.6.34.6.4 4.6.4.1 4.
41、6.4.2 F3233/F3233M 1734.3.2 Each airspeed system must be calibrated in flight todetermine the system error.4.3.3 The system error, including position error, but exclud-ing the airspeed indicator instrument calibration error, may notexceed 3 % of the calibrated airspeed or 9.3 km/h 5 knots,whichever
42、is greater, throughout the following speed ranges:1.3 VS1to VMO/MMOor VNE, whichever is appropriate withflaps retracted; and, 1.3 VS1to VFEwith flaps extended.4.3.4 The design and installation of each airspeed indicatingsystem must provide positive drainage of moisture from thepitot static plumbing.
43、4.3.5 If certification for instrument flight rules or flight inicing conditions is requested, each airspeed system must havea heated pitot tube or an equivalent means of preventingmalfunction due to icing; refer to Specification F3120/F3120M.4.3.6 Each system must be calibrated to determine thesyste
44、m error during the accelerate-takeoff ground run.4.3.6.1 In showing compliance with 4.3.6, the ground runcalibration must be determined from 0.8 of the minimum valueof V1to the maximum value of V2, considering the approvedranges of altitude and weight.4.3.6.2 In showing compliance with 4.3.6, the gr
45、ound runcalibration must be determined assuming an engine failure atthe minimum value of V1.4.3.7 Aircraft with high speed performance levels (refer to3.2.3) must meet the requirements of 4.3.6, 4.3.6.1, and 4.3.6.2regardless of seating capacity.4.3.8 Where duplicate airspeed indicators are required
46、, theirrespective pitot tubes must be far enough apart to avoiddamage to both tubes in a collision with a bird.4.4 Static Pressure System:4.4.1 Each instrument provided with static pressure caseconnections must be so vented that the influence of aircraftspeed, the opening and closing of windows, air
47、flow variations,moisture, or other foreign matter will least affect the accuracyof the instruments except as noted in Specification F3120/F3120M.4.4.2 The design and installation of a static pressure systemmust be such that positive drainage of moisture is provided.4.4.3 The design and installation
48、of a static pressure systemmust be such that chafing of the tubing, and excessivedistortion or restriction at bends in the tubing, is avoided.4.4.4 The design and installation of a static pressure systemmust be such that the materials used are durable, suitable forthe purpose intended, and protected
49、 against corrosion.4.4.5 To demonstrate the integrity of the static pressuresystem, a proof test must be conducted for unpressurizedaircraft in accordance with Practice F3229/F3229M.4.4.6 To demonstrate the integrity of the static pressuresystem, a proof test must be conducted for pressurized aircraftin accordance with Practice F3229/F3229M.4.4.7 If certification for instrument flight rules or flight inicing conditions is requested and a static pressure system isnecessary for the
