ASTM F3227 F3227M-2017 Standard Specification for Environmental Systems in Small Aircraft《小型飞机环境系统的标准规格》.pdf

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1、Designation: F3227/F3227M 17Standard Specification forEnvironmental Systems in Small Aircraft1This standard is issued under the fixed designation F3227/F3227M; the number immediately following the designation indicates the yearof original adoption or, in the case of revision, the year of last revisi

2、on. 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 specification covers international standards for theenvironmental system aspects of airworthiness and design for“small” airc

3、raft.1.2 The 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

4、-ance to their Small Aircraft Airworthiness regulations (herein-after referred to as “the Rules”), refer to the ASTM F44webpage (www.ASTM.org/COMMITTEE/F44.htm) which in-cludes CAA website links.1.3 The values stated in either SI units or inch-pound unitsare to be regarded separately as standard. Th

5、e values stated ineach 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

6、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 regulatory limitations prior to use.2. Referenced Documents2.1 Following is a list of external standards referencedthroughout this specificatio

7、n; the earliest revision 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 Ter

8、minology for AircraftF3061/F3061M Specification for Systems and Equipment inSmall AircraftF3083/F3083M Specification for Emergency Conditions,Occupant Safety and AccommodationsF3230 Practice for Safety Assessments of Systems andEquipment in Small AircraftF3233/F3233M Specification for Instrumentatio

9、n in SmallAircraft2.3 SAE Standards:3SAE AIR825/4, Rev A Chemical Oxygen Systems3. Terminology3.1 Terminology specific to this specification is providedbelow. For general terminology, refer to Terminology F3060.3.2 Definitions of Terms Specific to This Standard:3.2.1 aircraft type code, nan aircraft

10、 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 specification is defined inSpecification F3061/F3061M.3.2.2 BTPS, n

11、BTPS stands for “Body Temperature andPressure, Saturated;” this is defined to be a temperature of37C and a pressure equal to the ambient pressure to which thebody is exposed minus 6.27 kPa 47 mmHg; this is thetracheal pressure displaced by water vapor pressure when thebreathed air becomes saturated

12、with water vapor at 37C.3.2.3 chemical oxygen generator, na chemical oxygengenerator is defined as a device which produces oxygen bychemical reaction; for more detailed information, refer to SAEAIR825/4.3.2.4 continued safe flight and landing, ncontinued safeflight and landing as applicable to this

13、specification is definedin Specification F3061/F3061M.3.2.5 probable, adjprobable means that the event is an-ticipated to occur one or more times during the entire opera-tional life of each aircraft.1This specification is under the jurisdiction ofASTM Committee F44 on GeneralAviation Aircraft and is

14、 the direct responsibility of Subcommittee F44.50 onSystems and Equipment.Current edition approved Feb. 15, 2017. Published March 2017. DOI: 10.1520/F3227_F3227M-17.2For referenced ASTM standards, visit the ASTM website, www.astm.org, orcontact ASTM Customer Service at serviceastm.org. For Annual Bo

15、ok of ASTMStandards volume information, refer to the standards Document Summary page onthe ASTM website.3Available from SAE International (SAE), 400 Commonwealth Dr., Warrendale,PA 15096, http:/www.sae.org.Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-

16、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 Organization Technica

17、l Barriers to Trade (TBT) Committee.13.2.6 STPD, nSTPD stands for “Standard Temperatureand Pressure, Dry.” This is defined to be a temperature of 0 Cand a pressure equal to 101.33 kPa (760 mmHg) with no watervapor.4. VentilationNOTE 1Table 1 provides correlation between various Aircraft TypeCodes an

18、d 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 columnsindicates that an aircraft must meet the requirements of

19、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 field columnsindicates that the requirements of that subs

20、ection 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 4.1.1, that subsection isapplicable to the aircraft. However, since the “L” altitude column for 4.1.2contains an

21、, then that subsection is not applicable.4.1 Ventilation:4.1.1 Each passenger and crew compartment must be suit-ably ventilated. Carbon monoxide concentration must notexceed one part in 20 000 parts of air.4.1.2 The ventilating air in the flightcrew and passengercompartments must be free of harmful

22、or hazardous concen-trations of gases and vapors in normal operations and in theevent of reasonably probable failures or malfunctioning of theventilating, heating, pressurization, or other systems and equip-ment.4.1.3 If accumulation of hazardous quantities of smoke inthe cockpit area is reasonably

23、probable, smoke evacuationmust be readily accomplished starting with full pressurizationand without depressurizing beyond safe limits.4.1.4 For aircraft that operate at altitudes above 12 497 m41 000 ft, under normal operating conditions and in the eventof any probable failure conditions (refer to P

24、ractice F3230)ofany system which would adversely affect the ventilating air, theventilation system must provide reasonable passenger comfort.4.1.5 For aircraft that operate at altitudes above 12 497 m41 000 ft, under normal operating conditions and in the eventof any probable failure conditions (ref

25、er to Practice F3230)ofany system which would adversely affect the ventilating air, theventilation system must provide a sufficient amount of uncon-taminated air to enable the flight crew members to performtheir duties without undue discomfort or fatigue.4.1.6 For aircraft that operate at altitudes

26、above 12 497 m41 000 ft, under normal operating conditions, the ventilationsystem must be designed to provide each occupant with at least0.25 kg 0.55 lbm of fresh air per minute.4.1.6.1 In showing compliance with 4.1.6, in the event ofthe loss of one source of fresh air, the supply of fresh airflowm

27、ay not be less than 0.18 kg per minute 0.40 lbm for anyperiod exceeding 5 min.4.1.7 For aircraft that operate at altitudes above 12 497 m41 000 ft, other probable and improbable EnvironmentalControl System failure conditions (refer to Practice F3230) thatadversely affect the passenger and flight cre

28、w compartmentenvironmental conditions may not affect flight crew perfor-mance so as to interfere with the reliable performance ofpublished and trained duties to an extent that would interferewith continued safe flight and landing.4.1.8 For aircraft that operate at altitudes above 12 497 m41 000 ft,

29、other probable and improbable EnvironmentalControl System failure conditions (refer to Practice F3230) thatadversely affect the passenger and flight crew compartmentenvironmental conditions may not affect occupants so as tocause permanent physiological harm.5. PressurizationNOTE 2Table 2 provides co

30、rrelation 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()inal applicable ATC character field columnsindicates that

31、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 field columnsin

32、dicates 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 5.1.3, that subsection isapplicable to the aircraft. However, since the

33、 “L” altitude column for 5.1.1contains an , then that subsection is not applicable.5.1 Pressurized Cabins:5.1.1 The aircraft must be able to maintain a cabin pressurealtitude of not more than 4572 m 15 000 ft in the event of anyTABLE 1 ATC Compliance Matrix, Section 4SectionAirworthiness LevelNumber

34、 ofEnginesType ofEngine(s)Stall SpeedCruiseSpeedMeteorologicalConditionsAltitude Maneuvers1234SMRTLMHLHDNILHNA44.14.1.14.1.2 4.1.3 4.1.4 4.1.5 4.1.6 4.1.6.1 4.1.7 4.1.8 F3227/F3227M 172probable failure condition (refer to Practice F3230)inthepressurization system.5.1.1.1 In showing compliance with 5

35、.1.1 duringdecompression, the cabin altitude may not exceed 4572 m15 000 ft for more than 10 s and 7620 m 25 000 ft for anyduration.5.1.2 Pressurized cabins must have at least two pressurerelief valves to automatically limit the positive pressure differ-ential to a predetermined value at the maximum

36、 rate of flowdelivered by the pressure source.5.1.2.1 The combined capacity of the relief valves requiredby 5.1.2 must be large enough so that the failure of any onevalve would not cause an appreciable rise in the pressuredifferential. The pressure differential is positive when theinternal pressure

37、is greater than the external.5.1.3 Pressurized cabins must have at least two reversepressure differential relief valves (or their equivalent) toautomatically prevent a negative pressure differential thatwould damage the structure. However, one valve is enough ifit is of a design that reasonably prec

38、ludes its malfunctioning.5.1.4 Pressurized cabins must have a means by which thepressure differential can be rapidly equalized.5.1.5 Pressurized cabins must have an automatic or manualregulator for controlling the intake or exhaust airflow, or both,for maintaining the required internal pressures and

39、 airflowrates.5.1.6 Pressurized cabins must have instruments to indicateto the pilot the pressure differential, the cabin pressure altitude,and the rate of change of cabin pressure altitude (refer toSpecification F3233/F3233M).5.1.7 Pressurized cabins must have a warning indication atthe pilot stati

40、on to indicate when the safe or preset pressuredifferential is exceeded and when a cabin pressure altitude of3048 m 10 000 ft is exceeded.5.1.8 The 3048 m 10 000 ft cabin altitude warning re-quired by 5.1.7 may be increased up to 4572 m 15 000 ft foroperations from high altitude airfields (3048 to 4

41、572 m 10 000to 15 000 ft) provided the requirements of 5.1.8.1 5.1.8.4 aremet5.1.8.1 For compliance with 5.1.8, the landing or the takeoff modes (normal or high altitude) must be clearly indicated tothe flight crew.5.1.8.2 For compliance with 5.1.8, selection of normal orhigh altitude airfield mode

42、must require no more than one flightcrew action and go to normal airfield mode at engine stop.TABLE 2 ATC Compliance Matrix, Section 5SectionAirworthiness LevelNumber ofEnginesType ofEngine(s)Stall SpeedCruiseSpeedMeteorologicalConditionsAltitude Maneuvers1234SMRTLMHLHDNILHNA55.15.1.1 5.1.1.1 5.1.25

43、.1.2.15.1.35.1.45.1.55.1.65.1.75.1.85.1.8.15.1.8.25.1.8.35.1.8.45.1.95.1.105.1.11 5.1.11.1 5.1.11.2 5.1.12 5.1.12.1 5.1.12.2 5.1.13 5.1.14 5.1.15 5.1.15.1 5.1.15.2 5.1.16 5.1.17 5.1.18 5.25.2.15.2.25.2.35.2.4F3227/F3227M 1735.1.8.3 For compliance with 5.1.8, the pressurization systemmust be designed

44、 to ensure cabin altitude does not exceed3048 m 10 000 ft when in flight above flight level (FL) 250.5.1.8.4 For compliance with 5.1.8, the pressurization systemand cabin altitude warning system must be designed to ensurecabin altitude warning at 3048 m 10 000 ft when in flightabove flight level (FL

45、) 250.5.1.9 Pressurized cabins must have a warning placard forthe pilot if the structure is not designed for pressure differen-tials up to the maximum relief valve setting in combinationwith landing loads.5.1.10 Pressurized cabins must have a means to stop rota-tion of the compressor or to divert ai

46、rflow from the cabin ifcontinued rotation of an engine-driven cabin compressor orcontinued flow of any compressor bleed air will create a hazardif a malfunction occurs.5.1.11 If certification for operation above 12 497 m41 000 ft and not more than 13 716 m 45 000 ft isrequested, then after decompres

47、sion from any probable pres-surization system failure in conjunction with any undetected,latent pressurization system failure condition (refer to PracticeF3230) the aircraft must prevent cabin pressure altitude fromexceeding the requirements of 5.1.11.1 and 5.1.11.2.5.1.11.1 In showing compliance wi

48、th 5.1.11, if depressur-ization analysis shows that the cabin altitude does not exceed7620 m 25 000 ft, the pressurization system must prevent thecabin altitude from exceeding the cabin altitude-time historyshown in Fig. 1; note that time starts at the moment cabinaltitude exceeds 3048 m 10 000 ft d

49、uring decompression.5.1.11.2 In showing compliance with 5.1.11, maximumcabin altitude is limited to 9144 m 30 000 ft. If cabin altitudeexceeds 7620 m 25 000 ft, the maximum time the cabinaltitude may exceed 7620 m 25 000 ft is 2 min; note that timestarts at the moment cabin altitude exceeds 7620 m 25 000 ftand ends when it returns to 7620 m 25 000 ft.5.1.12 If certification for operation above 12 497 m41 000 ft and not more than 13 716 m 45 000 ft isrequested, then after decompressi