1、STD-AECMA PREN i.5bO-EtJGL 2000 101231iL 0038720 bLb Edition approved for publication 2000-09-29 AECMA STANDARD NORME AECMA AECMA NORM Comments should be sent within six months after the date of publication to AECMA Gulledelle 94 8-1200 BRUXELLES prEN 4560 Edition P 1 September 2000 PUBLISHED BY THE
2、 EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES (AECMA) Gulledelle 94 - 8-1200 BRUXELLES - Tel. (t32) 2 775 81 10 - Fax. (+32) 2 775 81 1 I ICs: 49.080 Descriptors: aircraft industry, hydraulic system, fluid circuit, pipe fitting, quality assurance, specification, characteristic, inspection, test ENGL
3、ISH VERSION Aerospace series Pipe coupling, 37O, spherical, up to 21 O00 kPa Inch series Technical specification Srie arospatiale Luft- und Raumfahrt Systme de raccordement sphrique 37“, jusqu 21 O00 kPa Srie inch Inch-Rei he Rohrverschraubung mit Kugelbuchsen 37“, bis 21 O00 kPa Spcification techni
4、que Technische Lieferbedingungen This “Aerospace Series“ Prestandard has been drawn up under the responsibility of AECMA (The European Association of Aerospace Industries). It is published on green paper for the needs of AECMA- Members. It has been technically approved by the experts of the concerne
5、d Technical Committee following comment by the Member countries. Subsequent to the publication of this Prestandard, the technical content shall not be changed to an extent that interchangeability is affected, physically or functionally, without re-identification of the standard. After examination an
6、d signature of the AECMA Standard Checking Centre (NPS) and formal agreement of the Official Services of the Member countries it will be submitted as a draft European Standard to CEN (European Committee for Standardization) for formal vote. Nota - Extra copies can be supplied by B.N.A.E. - Technopol
7、is 54 - 199. rue Jean-Jacques Rousseau - 92138 ISSY-LES-MOULINEAUX CEDEX C4 Chairman Mr Staib I I 0 aecma 2000 COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling ServicesSTD-AECMA PREN LiSbO-ENGL 2000 9 1012311 0018723 552 9 Page 2 prEN 4560: 2000
8、 Contents I Scope . 3 2 Normative references . 3 3 Terms and definitions 4 4 Requirements, inspections and test methods . 6 5 Quality assurance 11 6 Preparation for delivery . 12 COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling ServicesSTD*AECMA
9、 PREN 95bO-ENGL 2OOU 10323L3 0038722 q77 = Page 3 prEN 4560: 2000 1 Scope This standard specifies the required characteristics, inspection and test methods, quality assurance and procurement requirements for inch series, pipe couplings, 37“, spherical, for temperature ranges from type II to type V a
10、ccording to IS0 6771 and nominal pressure up to 21 O00 kPa. In addition to the requirements of this technical specification, the coupling assemblies shall be qualified in accordance with equipment or component specification requirements. 2 Normative references IS0 468 IS0 2685 IS0 2859-1 IS0 6771 IS
11、0 6772 IS0 7137 IS0 8625-1 EN 2951 EN 3042 EN 10204 TR 2674 MI L-L-23699 Surface roughness - Parameters, their values and general rules for specifying requirements Aircraft - Environmental test procedure for airborne equipment - Resistance to fire in designated fire zones Sampling procedures for ins
12、pection by attributes - Part 1: Sampling schemes indexed by acceptance quality limit (AQL) for lot-by-lot-inspection Aerospace - Fluid systems and components - Pressure and temperature classifications Aerospace - Fluid systems - Impulse testing of hydraulic hose, tubing and fitting assemblies Aircra
13、ft - Environmental conditions and test procedures for airborne equipment Aerospace - Fluid systems - Vocabulary - Part 1: General terms and definitions related to pressure Aerospace series - Metallic materials - Test method - Micrographic determination of content of non-metallic inclusions 1) Aerosp
14、ace series - Quality assurance - EN aerospace products - Qualification procedure Metallic products - Types of inspection documents Aerospace series- Design and construction of pipelines for fluids in liquid or gaseous condition - Rigid lines, installation 2) Lubricating Oil, Aircraft Turbine Engine,
15、 Synthetic Base, NATO Code Number 0-156 3) 1) Published as AECMA Prestandard at the date of publication of this standard 2) Published as AECMA Technical Report at the date of publication of this standard 3) Published by: Department of Defense (DoD). the Pentagon, Washington, D.C. 20301, USA COPYRIGH
16、T Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling ServicesSTD-AECMA PREN YSbO-ENGL 2000 II 1012311 0038723 325 II Page 4 prEN 4560: 2000 3 Terms and definitions For the purposes of this standard, the following terms and definitions apply. 3.1 pressure no
17、minal pressure, proof pressure, impulse pressure, burst pressure according to IS0 8625-1 3.2 Coupling and assembling 3.2.1 coupling assembly assembled nut, ferrule and pipe mating with e.g. nipple, union, elbow, see figure 1. Straight union / Ferrule I Figure 1 - Example of coupling assembly 3.2.2 .
18、 dimensional code corresponds to the nominal diameter given in 16th of inches within two digits. 3.3.3 snug moment when positive resistance to rotation is observed during assembling COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling ServicesSTD.AE
19、CMA PREN qSbO-ENGL 2000 LOL23LL OOL872Li 2bL W Page 5 prEN 4560: 2000 3.3 Surface defects 3.3.1 surface irregularity nonconformity with general surface appearance, possible defect 3.3.2 crack clean (crystalline) fracture passing through or across the grain boundaries that possibly follows inclusions
20、 of foreign elements. Cracks are normally caused by overstressing the metal during forging or other forming operations, or during heat treatment. Where parts are subject to significant reheating, cracks are usually discoloured by scale. 3.3.3 fold doubling over of metal, which can occur during the f
21、orging operation. Folds can occur at or near the intersection of diameter changes and are especially prevalent with non-circular necks, shoulders and heads. 3.3.4 fold-like machining defect lap 3.3.5 seam (1) usually a surface opening or crack resulting from a defect obtained during casting or forgi
22、ng (2) extraneous material, stringer in the material, which is not homogeneous with base metal 3.3.6 pit void or hole in the surface as caused, for example, by corrosion. 3.4 Quality assurance 3.4.1 production batch a definite quantity of some commodity or service produced at one time under conditio
23、ns that are presumed uniform 3.4.2 delivery batch batch consisting of couplings with the same identity block which may come from different production batches 3.4.3 acceptance quality limit AQL when a continuing series of lots is considered, a quality level which for the purposes of sampling inspecti
24、on is the limit of a satisfactory process average 3.4.4 qualification testing required to demonstrate successful performance of the coupling assembly in simulated service (overload, destructive and fatigue tests) 3.4.5 major defect a defect other than critical, that is likely to result in a failure
25、or to reduce materially the usability of the considered product for its intended purpose 3.4.6 minor defect a defect that is not likely to reduce materially the usability of the considered product for its intended purpose, or that is a departure from established specification having little bearing o
26、n the effective use or operation of this product. COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling Services STDOAECMA PREN qSbO-ENGL 2000 W LO12311 0018725 1T8 9 - Page 6 prEN 4560: 2000 4 Requirements, inspection and test methods See table 1 an
27、d table 2. Qualification tests given from 4.12 to 4.15 shall only be made when required. Complementary qualification tests may be determined in direct relation with the application (e.9. vibration test, thermal shock test). The coupling shown on the figures of this standard are for information only.
28、 The test specimens shall be assembled with the part to test (e.g. elbow fitting instead of straight fitting). Non removable coupling (e.g. welded elbow, welded reducer) shall be tested on sample pipes in combination with removable (threaded) couplings. 4.2 4.1 .I Tests fluids Unless othenivise spec
29、ified, tests shall be carried out using e.g. oil compatible with the test temperature range. Water may be used, whenever practical, for proof, burst, stress corrosion and re-use capability testing. Test conditions and preparation of specimens for qualification 4.1.2 Specimen preparation Shaped parts
30、 shall be machined with the grain flow of the bar or plate in the direction of the fluid. Installations on the coupling shall be in accordance with TR2674. The coupling shall not be lubricated prior the first assembling. For the next assembling they shall be lubricated with engine oil (e.g. accordin
31、g to MIL-L-23699) at the interface between the nut and the ferrule. Prior to testing, and unless otherwise specified, all couplings with dimensional code up to 12 shall be assembled using either of the following methods. For couplings with dimensional code greater than 12 the assembling shall be mad
32、e by using the torque tightening method: torque tightening method: A torque value comprised between the minimum and the maximum given in table 3 shall be apply to the nut per TR 2674. angle tightening method: The following sequence shall be apply: 1 tighten the nut with a wrench to snug: 2 turn the
33、nut an additional 60 (see figure 2a); 3 loosen the nut: (for new parts assembling only); 4 retighten the nut with a wrench to snug; 5 turn the nut an additional 30“ (see figure 2b). Figure 2c give also a checking method by using and returning an open end wrench with a 15 offset. The torque tightenin
34、g method used for the test and value apply shall be recorded. 4.1.3 Pipe assembly The method of joining the pipe to the coupling (brazing, welding, mechanical attachment, etc.) shall not be detrimental to the properties, strength or geometry of the pipe assembly. The joint shall be in accordance wit
35、h the design instructions and shall be inspected by direct measurement, X-ray or other non-destructive methods. COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling ServicesSTDmAECMA PREN 45bO-ENGL 2000 m LOL23LL 00L72b O34 Characterlstlc Requiremen
36、t Inspection and test method Materials Metallic materials shall meet the Metallic materials shall be tested in I acceptance criteria given in EN 2951. accordance with EN 2951. 100 % 4 100 % X 100 % X 100 % X 2 ;pecimenz Thread flanks in rolled threads sha be examined by micro-examinatior Specimens s
37、hall be taken from th finished part by sectioning on longitudinal plane across th threaded area. The specimens sha be polished and etched to reveal th surface defects. The coupling assembly shall b connected to a pressure source at pressure equal to twice the nomin, pressure for at least five minute
38、s i ambient temperature with one en free to move. roughness Surface I 4*5b I Conformity with the product standards Suitable measuring instruments or Interpreted in accordance with Is0 468 samples I Visual examination Visual inspection using suitable methods L continued Dimensional code 03 o4 05 06 0
39、8 loto 16 Depth mm 0.15 0,18 0,18 02 0,23 0,25 Page 7 prEN 4560: 2000 Table 1 - Requirements, inspection and test methods Clause k Q I A X 100 % X 100 % Certificate of compliance to EN 10204 issued by the semi-finished product manufacturer Conformity with the product standards I 4.3 I Dimensions I C
40、onformity with the product standards 1 Suitable measuring instruments X 100 % X 20 % Visual examination Marking according to product standards. adversely affect the material or the X 100 % X 20 % I 4.6b 1 Surface I Conformity with the product standards coating or treatment X 50 % X 100 % - X 100 % l
41、ark shall be free from surface defects idicated in 3.3 liable to have an dverse affect on their characteristics nd endurance. rhreads 1 Proof pressure test he external threads of couplings #hould be rolled and, 1 machined, shall lave a maximal value of 1,6 pn for i?. i accordance with IS0 468. .aps,
42、 cracks, surface irregularities and ieams (see 3.3) are not acceptable on iny part of the pressure thread flank, in he thread root or on the non-pressure hread flank. aps and seams, depths of which are vithin the limits of table, are acceptable in the crest and the non-pressure hread flank above the
43、 pitch diameter. Visual examination The grain flow in rolled threads shall be rontinuous and follow the general thread :ontour with the maximum density at the thread root. The coupling assembly shall withstand and shall not show any evidence of permanent deformation or other malfunction that would a
44、ffect assembly or disassembly without any relative pressure when using the specified torque values. X COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling ServicesPage 8 prEN 4560: 2000 Table I (continued) - Clause - 4.9 Requlrement Inspection and t
45、est method Q Characteristic There shall be no visible formation oi bubble. X Gaseous wessure test The coupling assembly shall be solvent cleaned and air dried prior to testing. It shall be assembled and tightened to the toque value specified in table 3. It shall be immersed in water bath at ambient
46、temperature. It shall then be pressurised with air or nitrogen to 500 kPa f 50 kPa with 0,5 % to I % of wetting agent (make up by volume) for at least five minutes, at ambient temperature. The coupling assembly shall be connected to a pressure source at a pressure equal to four times the nominal pre
47、ssure for at least five minutes, when tested at ambient temperature with one end free to move. 3umt pressure :est The coupling assembly shall withstanc this test without leakage. Pipe expansion Is permissible. Thc coupling assemblies need not meet an) disassembly or assemblies requiremen - nut defon
48、nation; - excessive galling or damage to an) surfaces of the coupling assembl) which prevents the specified tightening toque from being applied smoothly; - inability to tighten the coupling b) hand. The following values shall also be recorded: - stress level in pipe while torquing and after assembli
49、ng; - axial distance between the nut anc the corresponding threaded part atla each assembling; - hole dimensions of each coupling assembly part after each disas sembling. The coupling assembly shall be tested according to figure 3 with one end torqued to the maximum and the other to the minimum value of the tightening toque with no additional lubricant permitted for the first tightening. Each coupling assembly shall then be disassembled, and the sealing face rotated 60 to 90; the coupling assembly shall then be lubricated with the
