BS N 6-1998 Specification for aeromedical portable oxygen concentrator systems - General requirements《航空医疗用便携式氧浓缩器系统规范 一般要求》.pdf

1、BRITISH STANDARD AEROSPACE SERIES BSN6:1998 Specification for aeromedical portable oxygen concentrator systems Generalrequirements ICS 49.090BSN6:1998 This British Standard, having been prepared under the directionof the Engineering SectorBoard, was published underthe authority of the Standards Boar

2、d and comes intoeffect on 15 July 1998 BSI 05-1999 The following BSI references relate to the work on this standard: Committee reference ACE/38 Draft for comment 96/706246 DC ISBN 0 580 29543 5 Committees responsible for this British Standard The preparation of this British Standard was entrusted to

3、 Technical Committee ACE/38, Aircraft oxygen equipment, upon which the following bodies were represented: British Airways British Compressed Gases Association Civil Aviation Authority Health and Safety Executive Ministry of Defence Society of British Aerospace Companies Limited South Bank University

4、 Amendments issued since publication Amd. No. Date CommentsBSN6:1998 BSI 05-1999 i Contents Page Committees responsible Inside front cover Foreword ii 1 Scope 1 2 Normative references 1 3 Definitions 1 4 General 1 5 Design and performance 2 6 Construction 2 7 Information to be supplied in the indivi

5、dual equipment specification 3 List of references Inside back coverBSN6:1998 ii BSI 05-1999 Foreword This British Standard has been prepared under the direction of Technical Committee ACE/38 and specifies requirements for the construction and performance of aeromedical portable oxygen concentrators.

6、 The aircraft may not be specifically adapted for the oxygen concentrator, but the oxygen concentrator may require an electrical power source. The location of the oxygen concentrator in the aircraft is compatible with normal usage and impact conditions. The oxygen supplied from the concentrators is

7、intended for aeromedical purposes to enable disabled or incapacitated persons to travel on passenger aircraft without the need for recourse to heavy, and bulky, supplies of bottled oxygen. A British Standard does not purport to include all the necessary provisions of a contract. Users of British Sta

8、ndards are responsible for their correct application. Compliance with a British Standard does not of itself confer immunity from legal obligations. Summary of pages This document comprises a front cover, an inside front cover, pages i and ii, pages1 to4, an inside back cover and a back cover. This s

9、tandard has been updated (see copyright date) and may have had amendments incorporated. This will be indicated in the amendment table on theinside front cover.BSN6:1998 BSI 05-1999 1 1 Scope This British Standard specifies requirements for the construction and performance of aeromedical oxygen conce

10、ntrators and defines the characteristics of the gas to be delivered at the system outlet for aeromedical purposes in support of planned requirements of passengers. It also specifies elements to be contained in the individual equipment specification by the manufacturer. 2 Normative references This Br

11、itish Standard incorporates, by dated or undated reference, provisions from other publications. These normative references are made at the appropriate places in the text and the cited publications are listed on the inside back cover. For dated references, only the edition cited applies; any subseque

12、nt amendments to or revisions of the cited publication apply to this British Standard only when incorporated in the reference by amendment or revision. For undated references, the latest edition of the cited publication applies, together with any amendments. 3 Definitions For the purposes of this Br

13、itish Standard the following definitions apply: 3.1 oxygen concentrator system that uses air as a source from which oxygen for breathing purposes may be concentrated 3.2 portable able to be carried on board an aircraft not specifically adapted for the system 3.3 individual equipment specification de

14、claration of performance and usage prepared by the manufacturer 3.4 hazard consequence of use that may endanger the integrity of the aircraft and its operation or cause discomfort or injury to passengers and crew NOTEDiscomfort may include heat, noise, airflow, odour etc. 4 General 4.1 Oxygen flow T

15、he system shall provide a continuous flow of breathing oxygen by concentration from a supply of air drawn from the cabin. The flow of oxygen shall be defined in, and shall meet the requirements of, the individual equipment specification for each application. 4.2 Orientation The system shall be opera

16、ted only in the orientations specified in the individual equipment specification. 4.3 Electrical 4.3.1 When the system derives electrical power from the aircraft it shall be compatible with the aircraft power source. NOTEAn airworthy back-up power source may be incorporated. 4.3.2 The electromagneti

17、c characteristics shall conform to the relevant part of BSG100 or BSG229, and shall not interfere with aircraft avionics. 4.4 Air supply to system The system design shall be such that the cabin air inlet can not become occluded. Warning notices shall be displayed to warn users and other persons that

18、 the system air inlet must not be restricted. 4.5 Filtration Filtration shall be provided to the air supply in order that solid particulate material and/or water/water vapour cannot adversely affect the system. 4.6 Rapid decompression The effects of rapid decompression shall not cause disruption or

19、damage to the system, which could cause damage to the aircraft or otherwise harm the user and other persons. NOTEFunctioning during rapid decompression and/or rate of recovery after may be specified in the individual equipment specification see clause 7k). 4.7 Noise The noise generated by the system

20、, excluding audible alarms, when in use shall not exceed65dB(A) measured at a distance of1m. 4.8 Guidance The instructions for the operation of the system shall include guidance in the choice of the delivery system of the product gas to the user.BSN6:1998 2 BSI 05-1999 4.9 Hazards 4.9.1 The exhaust

21、gases shall not cause a hazard (see3.4) to the aircraft, user or other passengers and crew. Instructions shall be displayed to warn users that the exhaust must not be occluded or restricted. The system shall have a warning to prohibit smoking near the system. 4.9.2 The system shall be designed to be

22、 fail-safe. 4.10 Portability The system shall be portable. 5 Design and performance 5.1 Functional characteristics 5.1.1 The system shall reach minimum product gas purity (see5.2) within10min of being switched on, at normal cabin conditions. 5.1.2 The system shall have a failure indicator/alarm. 5.1

23、.3 The system shall be designed to prevent inadvertent operation of the controls at any time. 5.1.4 The system shall have clear and concise operating instructions and controls. 5.2 Oxygen purity 5.2.1 General The oxygen delivered from the system outlet tube shall be free from nauseous or objectionab

24、le odour and smoke, and shall not contain moisture, impurities or particles in excess of the values specified in5.2.2 to5.2.5. The oxygen delivered shall have a minimum purity of90%. 5.2.2 Solids Total solids shall not exceed0.1g/m 3of oxygen. Solid particles shall not exceed 54m in any dimension an

25、d shall not be toxic. 5.2.3 Carbon monoxide Carbon monoxide content of the delivered gas, as defined by volume, shall not exceed the CO content of the cabin air. 5.2.4 Carbon dioxide Carbon dioxide content of the delivered gas, as defined by volume, shall not exceed the CO 2content of the cabin air.

26、 5.2.5 Impurities Total impurities, excluding moisture, shall not exceed0.5% by volume. NOTE 1For these purposes nitrogen and argon are not considered to be impurities. NOTE 2This volume may contain traces of gases other than those listed above, provided that their presence does not constitute a phy

27、siological hazard. 5.3 Gas temperature The temperature of the product gas delivered at the outlet of the system shall be declared in the individual equipment specification and shall be equal to normal ambient cabin temperature 5 C. 5.4 System pressure The maximum design pressure within the system an

28、d the range of delivery pressure at the outlet shall be declared in and shall meet the requirements of the individual equipment specification. A pressure relief device shall be included (see6.5). 5.5 System housing temperature The maximum temperature of the systems external surface achieved during o

29、peration shall be declared in and shall meet the requirements of the individual equipment specification. NOTEThe maximum housing temperature should not exceed20 C above normal cabin ambient temperatures. 5.6 Reliability Statistical sampling schemes shall be employed to demonstrate the reliability le

30、vel stated in the individual equipment specification within the declared life of the system. 5.7 Environmental conditions The system shall operate without premature actuation or degradation of performance during or after exposure to the required atmospheric and mechanical environmental conditions st

31、ated in the relevant part of BSG100 or as specified in BSG229. NOTEBS G 229 is the implementation of EUROCAE/ED-14C and RTCA/DO-160C. 6 Construction NOTE 1The system should conform to current air worthiness standards for flammability, smoke and toxicity. NOTE 2The systems protective case should prov

32、ide impact protection and containment. 6.1 The system assembly shall be designed to ensure that leakage, failure or malfunction will not create a hazard (see3.4) to the aircraft or user. 6.2 The system assembly shall be designed such that passenger access to moving parts within the system is minimiz

33、ed. 6.3 Spillages of beverages and liquids shall not adversely affect the operation of the system. 6.4 In addition to the general requirements of this standard, the system material selection shall conform to the relevant clauses of BSN100 in respect of those materials in contact with oxygen. 6.5 A r

34、upture disc, relief valve or electrical auto shut down device shall be fitted to the system to prevent over-pressurisation due to any malfunction which could create excessive pressure.BSN6:1998 BSI 05-1999 3 6.6 The system shall withstand acceleration forces of 9 g when tested in accordance with2.1

35、and2.3 of BS4G229:1996 in each major axis as installed in the aircraft without damage or malfunction. 6.7 The system shall continue to function after being dropped onto a hard surface from its normal carrying position as defined in the individual equipment specification. 6.8 The system shall have no

36、 sharp edges. 6.9 The system shall be fitted with an electrical rating label. 7 Information to be supplied in the individual equipment specification The individual equipment specification shall contain the following information. a) The product gas flow rate and endurance requirements (see5.1). b) Th

37、e temperature of the product gas at the outlet of the system (see5.3). c) The maximum allowable operating pressure and delivery pressure (see5.4). d) The maximum temperature of the systems external surface (see5.5). e) The maximum noise level generated by the system operating at all altitudes betwee

38、n sea level and normal maximum cabin altitude. f) The maximum permissible size, shape and weight. The preferred location and method/s of restraint shall also be quoted. g) The electrical power requirements and connections, if applicable. h) The ability of the system to cope with transient or tempora

39、ry loss of power. i) How the system shall indicate to the user if there is a loss of power or product gas quality. j) The requirements and standards of the delivery system to ensure that the user receives the product gas without inappropriate dilution or restriction. k) The effects of rapid decompre

40、ssion. l) Whether the system may be used in combination with a gas humidifier and if so, which equipment is suitable. m) The frequency and requirements of scheduled servicing. n) The system reliability and life.4 blankBSN6:1998 BSI 05-1999 List of references (see clause 2) Normative references BSI p

41、ublications BRITISH STANDARDS INSTITUTION, London BS G 100, Specification for general requirements for electrical equipment and indicating instruments for aircraft. BS 4G 229:1996, Schedule for environmental conditions and test procedures for airborne equipment. BS 3N 100:1985, Specification for gen

42、eral design requirements for oxygen systems and equipment. Other references 1) EUROCAE/ED-14C/RTCA/DO-160C, Environmental conditions and test procedures for airborne equipment. 1) These publications can be obtained from the following addresses: EUROCAE (European Organisation for Civil Aviation Elect

43、ronics), 11 rue Hamelin, 75783 Paris Cedex 16, France RTCA (RadioTechnical Commission for Aeronautics), 1140 Connecticut Avenue, N.W., Suite 1020, Washington, DC 20036, USABS N 6:1998 BSI 389 Chiswick High Road London W4 4AL BSIBritishStandardsInstitution BSI is the independent national body respons

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