ASTM F3229 F3229M-2017 Standard Practice for Static Pressure System Tests in Small Aircraft《小型飞机静压系统试验的标准实施规程》.pdf

1、Designation: F3229/F3229M 17Standard Practice forStatic Pressure System Tests in Small Aircraft1This standard is issued under the fixed designation F3229/F3229M; the number immediately following the designation indicates the yearof original adoption or, in the case of revision, the year of last revi

2、sion. A 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 practice covers internationally accepted methodsfor the conducting static pressure system tests 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 practice as part of a certification plan. Forinformation on which CAA regulatory bodies have acceptedthis practice (in whole or in part) as a means of compliance totheir Small Ai

4、rcraft Airworthiness regulations (hereinafterreferred 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 ineach system m

5、ay 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 is theresponsi

6、bility 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 practice; the earliest revision acceptable

7、for useis indicated. In all cases later document revisions are accept-able 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 AircraftF3061/F3061M

8、Specification for Systems and Equipment inSmall Aircraft3. Terminology3.1 Terminology specific to this practice is provided below.For general terminology, refer to Terminology F3060.3.2 Definitions of Terms Specific to This Standard:3.2.1 aircraft type code, nan Aircraft Type Code (ATC) isdefined by

9、 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 practice is defined inSpecification F3061/F3061M.4. Static Pressure System TestsNOTE 1Table 1 pr

10、ovides 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:An empty cell ( ) in all applicable ATC character field columnsi

11、ndicates 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 applicable.A mark-out () in any of the applicable ATC character f

12、ield columnsindicates that the requirements of that subsection are not applicable 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 4.2.1, that subsection isapplicable to the aircraft. 4.1.

13、1 would not be applicable, since it containsan in the “D” meteorological condition column.4.1 Proof Test for Unpressurized Aircraft:4.1.1 To demonstrate the integrity of the static pressuresystem, a proof test must be conducted for unpressurizedaircraft by evacuating the static pressure system to a

14、pressuredifferential of approximately 3.4 kPa 0.5 psi or to a readingon the altimeter of 305 m 1000 ft above the aircraft elevationat the time of the test. Without additional pumping for a periodof 60 s, the loss of indicated altitude must not exceed 30 m100 ft on the altimeter.4.2 Proof Test for Pr

15、essurized Aircraft:4.2.1 To demonstrate the integrity of the static pressuresystem, a proof test must be conducted for pressurized aircraftby evacuating the static pressure system until a pressuredifferential equivalent to the maximum cabin pressure differ-ential for which the aircraft is type certi

16、ficated is achieved.1This practice is under the jurisdiction of ASTM Committee F44 on GeneralAviation Aircraft and is the direct responsibility of Subcommittee F44.50 onSystems and Equipment.Current edition approved Feb. 15, 2017. Published March 2017. DOI: 10.1520/F3229_F3229M-17.2For referenced AS

17、TM standards, visit the ASTM website, www.astm.org, orcontact ASTM Customer Service at serviceastm.org. For Annual Book of ASTMStandards volume information, refer to the standards Document Summary page onthe ASTM website.Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshoho

18、cken, PA 19428-2959. United StatesThis international standard was 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 Organi

19、zation Technical Barriers to Trade (TBT) Committee.1Without additional pumping for a period of 60 s, the loss ofindicated altitude must not exceed 2 % of the equivalentaltitude of the maximum cabin differential pressure or 30 m100 ft, whichever is greater.4.3 Calibration Test:4.3.1 Each static press

20、ure system must be calibrated in flightto determine the system error. The system error, in indicatedpressure altitude, at sea-level, with a standard atmosphere,excluding instrument calibration error, may not exceed 69m630 ft per 185 kmh 100 knots speed for the appropriateconfiguration in the speed r

21、ange between 1.3 VS0with flapsextended, and 1.8 VS1with flaps retracted. However, the errorneed not be less than 69m630 ft.5. Keywords5.1 calibration test; pitot; pressurization; proof test; staticASTM International takes no position respecting the validity of any patent rights asserted in connectio

22、n 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

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24、eration at a meeting of theresponsible technical committee, which you may attend. If you feel that your comments have not received a fair hearing you shouldmake your views known to the ASTM Committee on Standards, at the address shown below.This standard is copyrighted by ASTM International, 100 Bar

25、r Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959,United States. Individual reprints (single or multiple copies) of this standard may be obtained by contacting ASTM at the aboveaddress or at 610-832-9585 (phone), 610-832-9555 (fax), or serviceastm.org (e-mail); or through the ASTM websit

26、e(www.astm.org). Permission rights to photocopy the standard may also be secured from the Copyright Clearance Center, 222Rosewood Drive, Danvers, MA 01923, Tel: (978) 646-2600; http:/ 1 ATC Compliance Matrix, Section 4SectionAirworthiness LevelNumber ofEnginesType ofEngine(s)Stall SpeedCruiseSpeedMeteorologicalConditionsAltitude Maneuvers1234SMRTLMHLHDNILHNA44.14.1.1 4.24.2.14.34.3.1 F3229/F3229M 172