《ISO-3174-1994.pdf》由会员分享，可在线阅读，更多相关《ISO-3174-1994.pdf（12页珍藏版）》请在三一文库上搜索。
1、INTERNATIONAL STANDARD IS0 3174 Second edition 1994-l 2-01 Aircraft - Connections for checking hydraulic systems by ground appliances - Threaded type ABronefs - Raccords pour la vkification des circuits hydrauliques par des appareils au sol - Type filet6 Reference number IS0 3174 1994(E) Copyright I
2、nternational Organization for Standardization Provided by IHS under license with ISO Licensee=NASA Technical Standards 1/9972545001 Not for Resale, 04/23/2007 21:10:30 MDTNo reproduction or networking permitted without license from IHS -,-,- IS0 3174:1994(E) Foreword IS0 (the International Organizat
3、ion for Standardization) is a worldwide federation of national standards bodies (IS0 member bodies). The work of preparing International Standards is normally carried out through IS0 technical committees. Each member body interested in a subject for which a technical committee has been established h
4、as the right to be represented on that committee. International organizations, governmental and non-governmental, in liaison with ISO, also take part in the work. IS0 collaborates closely with the International Electrotechnical Commission (IEC) on all matters of electrotechnical standardization. Dra
5、ft International Standards adopted by the technical committees are circulated to the member bodies for voting. Publication as an International Standard requires approval by at least 75 % of the member bodies casting a vote. International Standard IS0 3174 was prepared by Technical Committee lSO/TC 2
6、0, Aircraft and space vehicles, Subcommittee SC 10, Aerospace fluid systems and components. This second edition cancels and replaces the first edition (IS0 3174:1981), of which it constitutes a technical revision. Annex A of this International Standard is for information only. 0 IS0 1994 All rights
7、reserved Unless otherwise specified, no part of this publication may be reproduced or utilized in any form or by any means, electronic or mechanical, including photocopying and microfilm, without permission in writing from the publisher. International Organization for Standardization Case Postale 56
8、 ? CH-1211 Geneve 20 ? Switzerland Printed in Switzerland ii Copyright International Organization for Standardization Provided by IHS under license with ISO Licensee=NASA Technical Standards 1/9972545001 Not for Resale, 04/23/2007 21:10:30 MDTNo reproduction or networking permitted without license f
9、rom IHS -,-,- INTERNATIONAL STANDARD 0 IS0 IS0 3174:1994(E) Aircraft - Connections for checking hydraulic systems by ground appliances - Threaded type 1 Scope This International Standard specifies the requirements for connections installed in aircraft hydraulic system pressure and suction lines, int
10、ended for checking the systems by means of ground appliances. 2 Normative references The following standards contain provisions which, through reference in this text, constitute provisions of this International Standard. At the time of publi- cation, the editions indicated were valid. All standards
11、are subject to revision, and parties to agreements based on this International Standard are encouraged to investigate the possibility of applying the most re- cent editions of the standards indicated below. Members of IEC and IS0 maintain registers of cur- rently valid International Standards. IS0 3
12、323:1987, Aircraft - Hydraulic components - Marking to indicate fluid for which component is ap- proved. MI L-STD-810, Environmental Test Methods and En- gineering Guidelines. 3 Basic connection elements The basic elements and dimensions of the con- nections shall be in accordance with figure I and
13、table 1. 4 Connecting thread 4.1 The profile, basic elements and dimensions of the three-start thread shall be in accordance with fig- ure 2 and table 1. 4.2 The end of the thread shall be relieved in order to ensure ease of engagement. 4.3 The thread shall be easily coupled or uncoupled from any po
14、sition of engagement. 5 Installation of the connection The clearance envelope for the connection on the air- craft shall be in accordance with figure3. Copyright International Organization for Standardization Provided by IHS under license with ISO Licensee=NASA Technical Standards 1/9972545001 Not f
15、or Resale, 04/23/2007 21:10:30 MDTNo reproduction or networking permitted without license from IHS -,-,- IS0 3174:1994(E) 0 IS0 Dimensions in millimetres P 0,9*O,lx45”orR0,9+0.1 1 0 0 1 I I + - n teeth equally spaced 45 *5” typ./C- M I I) See figure 2. Figure 1 - Basic dimensions of the aircraft con
16、nection R 0.25 0,25 R 0.13 or 0.13 x 45” *5” u 15 *0 30 typ. 7 NOTE - The thread dimensions conform to IS0 2901, IS0 2902, IS0 2903 and IS0 2904 except for the modified radii. Figure 2 - Three-start thread dimensions Copyright International Organization for Standardization Provided by IHS under lice
17、nse with ISO Licensee=NASA Technical Standards 1/9972545001 Not for Resale, 04/23/2007 21:10:30 MDTNo reproduction or networking permitted without license from IHS -,-,- IS0 3174:1994(E) Table 1 - Basic dimensions of aircraft connections Dimensions in millimetres DN Dimension 12 20 25 32 40 A f 0.12
18、 IO,28 14.48 18.8 28,58 32,77 B C max 15.90 20.65 26,92 34.98 41,32 min 15.88 20,62 26,90 34,92 41,27 + 0,25 38.73 44,91 51,82 59,71 71.63 D k 0.25 41.3 47.5 54,36 62.96 74,42 E +- 0.25 29.65 35.65 43.63 50,63 59,56 F 34 -:; 38,i 1;:; 46,5 I;:;$ 53,5 r;g; 63 1; I 1) In accordance with IS0 2903 -1 3
19、Copyright International Organization for Standardization Provided by IHS under license with ISO Licensee=NASA Technical Standards 1/9972545001 Not for Resale, 04/23/2007 21:10:30 MDTNo reproduction or networking permitted without license from IHS -,-,- IS0 3174:1994(E) 0 IS0 Dimensions in millimetre
20、s (inches) Minimum distance between two connections 60 (2.362) min. f6 (1,811) max; 6 Technical requirements -Circumferential clearance .E 8 z c % II Fuselage of aircraft 6.1 Design 6.1 .I Operating temperature Figure 3 - Clearance envelope The connection shall be capable of continuous oper- ation w
21、ithin a fluid temperature range from - 40 “ C to + 96 “ C. There shall be no damage when subjected to nonoperating (i.e. static) fluid temperatures of - 54 “ C and + 135 “ C. Table 2 - Operating Dressures Thread size DN Pressure mm kPa 12 28000 20 28000 25 28 000 32 14000 40 14000 6.1.3 Ambient pres
22、sure 6.9.2 Operating pressure The operating pressure shall be as specified in table 2. The connection shall be capable of continuous oper- ation within an ambient pressure range from 3.8 kPa abs to 108,O kPa abs. Copyright International Organization for Standardization Provided by IHS under license
23、with ISO Licensee=NASA Technical Standards 1/9972545001 Not for Resale, 04/23/2007 21:10:30 MDTNo reproduction or networking permitted without license from IHS -,-,- 0 IS0 6.1.4 Fire resistance IS0 3174:1994(E) 6.3 Performance tests The connection shall be designed such that it will not promote comb
24、ustion, or in the event of fire, will not sustain or support combustion. 6.1.5 Fungus resistance The connection shall be designed such that it will not support fungus growth. 6.2 Functional 6.2.1 Coupling device The coupling device shall be of a screw-together type. The airborne connection shall be
25、a fixed male half and a cap supplied with an attachment chain or lanyard. The caps shall be capable of withstanding all static and dynamic pressure conditions of the respective connection. 6.2.2 Handling The mating ground connection and blanking caps shall be hand operated for coupling and uncouplin
26、g oper- ations. It shall be possible to couple and uncouple with static pressures from 0 to 415 kPa at fluid tem- peratures from - 40 “ C to + 70 “ C. Connections supplied in accordance with this Inter- national Standard shall be representative of products which have been subjected to and which have
27、 suc- cessfully passed the requirements and tests specified in this International Standard. 6.3.1 Classification of tests Tests specified in this International Standard are clas- sified as follows: a) acceptance tests (see 6.4) b) qualification tests (see 6.5) 6.3.2 Test fluid Unless otherwise speci
28、fied, testing shall be con- ducted with a hydraulic fluid which is used in the in- tended application of the connection. 6.4 Acceptance tests 6.4.1 Examination of product Each connection shall be examined as specified in 6.5.1. 6.4.2 Proof pressure Each connection shall be tested as specified in 6.5
29、2. 6.2.3 Positive locking 6.4.3 Leakage Upon completion of coupling, there shall be an auto- matic engagement of a positive lock. 6.2.4 Accidental disconnection Accidental disconnection shall be impossible. 6.4.3.1 Leakage at low pressure Each connection shall be tested as specified in 6.5.3.1 excep
30、t that the total time of pressurization shall be 1 min. 6.4.3.2 Leakage at high pressure 6.2.5 Seal disconnection There shall be no damage of the seals as a result of rotary and lateral movement during coupling and uncoupling operations. Each connection shall be tested as specified in 6.5.3.2 except
31、 that the total time of pressurization shall be 1 min. 6.5 Qualification tests 6.2.6 Cross-coupling 6.5.1 Examination of product Airborne connections shall be incapable of cross- coupling with ground connections of different sizes. Airborne connections shall also be incapable of cross-coupling with
32、other airborne connections of the same or different sizes. The connection shall be examined to determine con- formance to this International Standard with respect to design, basic connection elements and connecting threads. 5 Copyright International Organization for Standardization Provided by IHS u
33、nder license with ISO Licensee=NASA Technical Standards 1/9972545001 Not for Resale, 04/23/2007 21:10:30 MDTNo reproduction or networking permitted without license from IHS -,-,- IS0 3174:1994(E) 0 IS0 6.5.2 Proof pressure 6.5.8 Sand and dust The coupled and uncoupled connections shall not leak when
34、 pressurized to 150 % of the appropriate oper- ating pressure for 1 min (see table2). Testing shall be conducted at a temperature of + 135 “ C. The coupled connection shall withstand 28 h of ex- posure to a sand and dust environment. The particle size shall be 0,150 mm and the relative humidity shal
35、l be maintained at less than 22 % throughout testing. Testing shall consist of the following three cycles: 6.5.3 Leakage 6.5.3.1 Leakage at low pressure The coupled connection shall not leak when pressur- ized to 35 kPa for 12 min. The uncoupled connection shall not leak in excess of one drop per 10
36、 min when pressurized to 35 kPa. After uncoupling, a waiting period of 2 min shall be allowed to establish a constant leakage rate before testing the uncoupled connection. 6.5.3.2 Leakage at, high pressure Cycle 1 Time. 6 h Air velocity. 533 m/min f 76 m/min Chamber temperature: + 23 “ C Density: IO
37、,6 g/m3 f 7 g/m3 Cycle 2 Time: 16 h Air velocity: 91 m/min f 61 m/min Chamber temperature: + 63 “ C Density: 10,6 g/m3 + 7 g/m3 Cycle 3 Repeat cycle 1 The coupled and u.ncoupled connection shall not leak when pressurized to the appropriate operating press- ure for 15 min (see table 2). Fluid loss du
38、ring uncoup- ling shall not exceed the appropriate value specified in 6.5.13. 6.5.9 Operational shocks 6.5.4 Ultimate burst pressure The coupled connection shall withstand twelve impact shocks of 196 m/s* without leakage or other mal- function. The duration of each impact shock shall be lOms+l ms. T
39、he coupled and uncoupled connection shall with- stand a burst pressure of not less than 250 % of the appropriate operating pressure (see table 2). 6.5.10 Endurance 6.5.5 Humidity The connection shall be subjected to ten cycles of the humidity test, method 507.2, procedure III, Figure 507.2-3 of MIL-
40、STD-810D. Following this test, the connection shall be subjected to the proof pressure test specified in 6.5.2. There shall be no leakage as a result of the proof pressure test or malfunction as a result of the humidity test. The connection shall withstand 500 coupljng and uncoupling operations with
41、out malfunction or degra- dation. Testing shall be conducted while the con- nection is pressurized to 100 kPa. 6.5.11 Pressure drop 6.5.6 Vibration Connections shall have a maximum pressure drop of 20 kPa with a fluid temperature of 38 “ C I!I 3 “ C at the flowrates given in table3. The connection s
42、hall be subjected to the vibration test specified ain MIL-STD81OC, method 514.2, category b.2, procedure IA. Table 3 - Pressure drop flowrates 6.5.7 Salt spray The connection shall be exposed for 48 h to a salt spray environment consisting of 5 % salt and 95 % distilled or demineralized water. Throu
43、ghout testing, the relative humidity shall be a minimum of 85 % and the temperature shall be + 35 “ C. DN Flowrate mm I/min 12 11.5 20 39 25 75 32 135 40 210 Copyright International Organization for Standardization Provided by IHS under license with ISO Licensee=NASA Technical Standards 1/9972545001
44、 Not for Resale, 04/23/2007 21:10:30 MDTNo reproduction or networking permitted without license from IHS -,-,- 0 IS0 IS0 3174:1994(E) 6.512 Impulse 6.5.13 Air inclusion and fluid loss The connection shall withstand 250 000 impulse cycles without leakage or malfunction. Testing shall be conducted at
45、a temperature of + 135 “ C for the first 12,5 h, + 107 “ C for 37,5 h and room tempera- ture for the remainder of testing. The impulse rate shall be 35 mine1 f 5 min- I. The impulse curve shall conform to figure 4 Slope ofthiscurve gives rate of pressure rise Peak pressure i? 2 fi h F 75 f ,d H 2 k$
46、 50 z z k a 25 Air inclusion and fluid loss shall not exceed the values given in table4. Table 4 - Maximum air inclusion and fluid loss I I DN Maximum air inclusion Maximum average fluid loss per cycle I Operating pressure 517 kpamaximumback 15% of cycle I Half-cycle One cycle pressure NOTE - The cu
47、rve shown above is the approximate pressure/time cycle determined to be of proper severity for impulse testing Although it is mandatory only that pressure peak rises to 143 % to 157 % of the operating pressure at some point prior to levelling off at operating pressure, it is considered highly desira
48、ble that the pressure time curve be confined to the shaded area indicated. One advantage of this method is that results of tests performed on different test machines will be more com- parable Figure 4 - Impulse trace 7 Copyright International Organization for Standardization Provided by IHS under license with ISO Licensee=NASA Technical Standards 1/9972545001 Not for Resale, 04/23/2007 21:10:30 MDTNo reproduction or networking permitted without license from IHS -,-,- F - IS0 3174:1994(E) 0 IS0 7 Marking Connections shall be marked in accordance w