1、CEN PREN*3275 93 m 3404589 0053970 9T3 m AECMA STANDARD prEN 3275 NORME AECMA Edition P1 AECMA NORM November 1993 DIT PAR LASSOCIATION EUROPENNE DES CONSTRUCTEURS DE MATRIEL AROSPATIAL Technopolis - 175, rue Jean-Jacques Rousseau - F-92138 Issy-les-Moulineaux Cedex - Tl. (i) 47.36.98.76 UDC Descript
2、ors : ENGLISH VERSION Aerospace series Pipe coupling 8O30 Dynamic beam seal up to 28 O00 kPa Metric series Technical specification Srie arospatiale Raccordement 8O30 Joint lvre jusqu 28 O00 kPa Srie mtrique Spcification technique Luft- und Raumfahrt Rohrverschraubung 8O30 Dichtlippe bis zu 28 O00 kP
3、a Metrische Reihe Technische Lieferbedingungen This “Aerospace Series“ Prestandard has been drawn up under the responsibility of AECMA (Association Europenne des Constructeurs de Matriel Arospatial). It is published on green paper for the needs of AECMA-Members. It has been technically approved by t
4、he experts of the concerned 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 stan
5、dard. After examination and 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 suppli
6、ed by B.N.A.E. - Technopolis 54 - 199, rue Jean-Jacques Rousseau - 921 38 ISSY-LES-MOULINEAUX CEDEX C4 Chairman Comments should be sent within six months after the date of publication to I Edition approved for publication 1993-1 1-30 AECMA Technopolis - 175, rue Jean-Jacques Rousseau 921 38 Issy-les
7、-Moulineaux Cedex - FRANCE M. Staib aecma 1993 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,- CEN PREN+3275 93 m 3404589 0053973 83T m prEN 3275 Page
8、 2 Contents list 1 Scope 2 Normative references 3 Symbols 4 Definitions 5 Required characteristics, methods of inspection and tests 6 Quality assurance 7 Preparation for delivery Annex A (normative) Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under licen
9、se with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,- CEN PREN*3275 93 3404589 O053972 77b W prEN 3275 Page 3 1 Scope This standard establishes the basic performance and quality criteria for metric series 8O30 dynamic beam seal tube fitting assemblies. It s
10、tandardizes the qualification test and procurement requirements for tube fittings. The test requirements are intended to satisfy the most strenuous demands encountered in a high performance aircraft hydraulic system. The procurement requirements are intended to ensure that fittings which are bought
11、to this standard are of the same quality as the fittings used during the original qualification testing. Performance and quality requirements are stated to which standard metric series 8O30 dynamic beam seal tube fittings shall be qualified and manufactured to ensure reliable performance in aircraft
12、 hydraulic systems. Fittings covered by this standard shall be of the temperature types and pressure classes specified in IS0 6771, Types II and 111, Classes B,D and E. This standard applies whenever it is referenced. 0 2 Normative references IS0 468 IS0 2685 IS0 2859-1 IS0 6771 IS0 6772 IS0 7137 IS
13、0 7257 IS0 9538 EN 2000 EN 2491 EN 3042 EN 3120 EN 3314 EN 3315 ARP 1185A Surface roughness - Parameters, their values and general rules for specifying requirements Aircraft - Environmental conditions and test procedures for airborne equipment - Resistance to fire in designated fire zones Sampling p
14、rocedures for inspection by attributes - Part 1 : Sampling plans indexed by acceptable quality level (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 a
15、ssemblies Aircraft - Environmental conditions and test procedures for airborne equipment (Endorsement of EUROCAE/ED-l4C and RTCA/DO-l60C) Aircraft - Hydraulic tubing joints and fittings - Rotary flexure test Aircraft - Hydraulic tubing joints and fittings - Planar flexure test 1) Aerospace series -
16、Quality assurance - EN aerospace products - Approval of the quality systems of manufacturers Aerospace series - Molybdenium disulphide dry film lubricants for application to removable fasteners in titanium, titanium alloy, corrosion resisting steels and cadmium plating steels Aerospace series - Qual
17、ity assurance - EN aerospace products - Qualification procedure Aerospace series - Titanium alloy TI-P69 - Cold worked and stress relieved 690 MPa 5 Rm s 1030 MPa - Seamless tube for pressure systems D 15; 50 mm 2, Aerospace series - Titanium alloy TI-P63 - Solution treated and aged - Rm 2 - Bar for
18、 machining - De I 50 mm 2, Aerospace series - Titanium alloy TI-P63 - Solution treated and aged - Rm 2 - Forgings - De 5 50 mm 2, Flexure testing of hydraulic tubing joints and fittings 3, 070 MPa 070 MPa 1 ) 2) 3) In preparation at the date of publication of this standard Published as AECMA Prestan
19、dard at the date of publication of this standard Published by: Society of Automotive Engineers Inc. (SAE), 400 Commonwealth Drive, Warrendale, PA 15096-0001. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproductio
20、n or networking permitted without license from IHS-,-,-CEN PREN*3275 93 = 3Y04589 0053973 602 prEN 3275 Page 4 MIL-H-5606F Hydraulic fluid, petroleum base, aircraft, missile and ordnance 4, MIL-L-4601 OB Lubricant, solid film, heat cure, corrosion inhibiting 4, 3 Symbols ID Internal diameter OD Outs
21、ide Diameter P Working pressure Do D1 ox DN Nominal tube outside diameter R, Tensile strenght A Elongation actual OD of the tube actual ID of the tube axial stress due to pressure 0,2% Proof stress RrJ0.2 mm mm M Pa mm mm M Pa M Pa M Pa % 4 Definitions Fitting assembly and part designation see figur
22、e 1. 4.1 Pressure terms 4.1 . 1 Nominal pressure The maximum steady working pressure (operating pressure) to which a fitting assembly or components may be subjected. The basic operating pressure without regard to operating pressure variations. 4.1.2 Proof pressure The static pressure for testing an
23、assembly, a prescribed multiple of the nominal pressure. 4.1.3 Impulse pressure A rapidly occuring pressure rise, peaking at a prescribed multiple of the nominal pressure. After the impulse peak, the pressure trace follows a prescibed curve, with a hold at nominal and zero pressure during one impuls
24、e pressure cycle. 4.1.4 Burst pressure The static pressure for testing an assembly to destruction. 4.2 Fitting terms 4.2.1 Fitting assembly Assembled and torque-tightened fitting, nuts, ferrules and tubing. 4.2.2 Port (also boss) Threaded connection with a seal, component to pipe line, machined into
25、 the component. 4.2.3 Straight fittings Parts such as union, machined out of bar stock, connecting to a port, or tube-to-tube. 4) Published by: Department of Defence (DOD), the Pentagon, Washington, D.C. 20301. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS
26、 under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CEN PREN*3275 73 3404587 0053974 547 prEN 3275 Page 5 4.2.4 Forged parts (also “shapes“) Fitting parts such as elbows and tees, machined out of individual forging blanks. The term “shape“ is a
27、lso used for cross, tee and elbow fittings machined out of bar or plate stock. e NOTE: For qualification, tee shapes should be machined with the grain flow in the direction of the branch 4.3 Surface defects (Workmanship) 4.3.1 Surface irregularity Nonconformity with general surface appearance, possi
28、ble defect. 4.3.2 Crack A clean (crystalline) fracture passing through or across the grain boundaries and may possibly follow inclusions of foreign elements. Cracks are normally caused by overstressing the metal during forging or other forming operations, or during heat treatment. Where parts are su
29、bject to significant reheating, cracks usually are diccoloured by scale. O 4.3.3 Fold A doubling over of metal which may occur during the forging operation. Folds may occur at or near the intersection of diameter changes and are especially prevalent with non-circular necks, shoulders and heads. 4.3.
30、4 Lap Fold-like machining defect. 4.3.5 Seam Usually a surface crack resulting from a defect obtained during casting or forging, also extraneous material, stringer in the material, not homogenous with base metal. 4.3.6 Pit Void, hole in the surface as caused, for example, by corrosion. 4.4 Quality a
31、ssurance 4.4.1 Batch A manufacture run of a given part number from the same batch of material processed at the same time and in the same manner. 4.4.2 Accepted Quality Level (AQL) Defect classification, etc. NOTE: Quality control definitions see IS0 2859-1. 4.4.3 Qualification, quality The performan
32、ce testing required to demonstrate successful performance of the fitting in simulated service and overload, destructive and accelerated tests. a Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networki
33、ng permitted without license from IHS-,-,-CEN PREN*3275 93 m 3404589 0053975 485 m prEN 3275 Page 6 5 Required characteristics, methods of inspection and tests See table 1 5.1 Test conditions and preparation of specimens for qualification Tests fluids. Unless otherwise specified, tests shall be cond
34、ucted using a petroleum base hydraulic fluid for type II and a silicate ester base hydraulic fluid for type III (see IS0 6771) systems fittings. Water may be used, whenever practical, for proof, burst, stress corrosion and repeated assembly (re- use) testing. For other than hydraulic system applicat
35、ions, it is preferable to use system fluid for leakage and proof testing. Specimen preparation. Test specimens shall be assembled as illustrated in table 2. Sleeve installations on the tube end shall be in accordance with users instructions. Prior to testing, all fittings shall be assembled using th
36、e maximum specified torque to assure maximum stress has been applied to the dynamic beam. For each test, the fitting shall be assembled using the minimum installation torque for at least half of the test specimens, and maximum torques for the remainder. Tube attachment. The method of joining the tub
37、ing to the end fitting (brazing, welding, mechanical attachment, swaging etc) shall not adversely affect the properties, strength or geometry of the tubing and the end fitting to the extent that the performance would be impaired. The joint shall be of a quality compatible with the design and perform
38、ance requirements of this specification and shall be inspectable by direct measurement, x-ray, or other such means. The method of tubing attachment of the test assemblies shall be as specified or approved by the procuring activity. Installation tooling. Size of tool envelope required to install fitt
39、ings on tubing in the vehicle system, to repair the system, or to replace fittings within the system shall be kept to a minimum. The wrench flats or pads of the fittings shall permit the use of standard wrenches. Heat generation. Fittings attached by thermal process shall be attached by tooling desi
40、gned to permit installation in vehicles without heat damage to adjacent structure or components. Lubricants. Hydraulic system fittings shall be assembled using the system fluid as lubricant, or another lubricant which is compatible with the system fluid and which has essentially the same lubricity c
41、haracteristics, specified in this standard or by the user. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CEN PREN*3275 93 m 3404589 00536 311 m prEN
42、3275 Page 7 Table 1 : Required characteristics, inspections and test methods Clause 5.2 5.3 Characteristic Materials Dimensions Fluid passages 5.5 Surface protection Surface texture Surface appearance Threads Requirement Conformity with the product standards Conformity with the product standards On
43、fittings where the fluid passage is drilled from each end, the offset shall not exceed 0,4 mm Conformity with the product standards including batch identification of Annex A. It shall be legible and shall not adversely affect the materials or the functioning of the products Conformity with the produ
44、ct standards Interpreted in accordance with IS0 468 Sealing surface shall not contain any radial tool marks Conformity with the product standards ) Parts shall be free from burrs and slivers, as well as surface defects liable to have an adverse affect on their characteristics and endurance (see 4.3
45、for definitions). Threads may be cut or rolled or, except for titanium, ground. The external threads of fittings should be rolled but, if machined,they shall have a surface finish of 3,2 pm. The grain flow in rolled threads should be continuous and follow the general thread contour with the maximum
46、density at the thread root. Surface defects are not acceptable on any part of the thread except the crest. Inspection or test method Chemical analysis or certificate of conformity issued by the semi-finished product manufacturer Suitable measuring instruments A ball with a diameter 0,5mm less than t
47、he minimum diameter specified for the passage shall pass through the fitting Visual examination Suitable measuring instruments or visual-tactile samples Visual examination Visual inspection using suitable methods Visual examination Specimens shall be taken from finished parts by sectioning on a long
48、itudinal plane across the thread area. 1) Until EN 2491 is issued the lubricant may be applied using MIL-L-46010B. Abrasive blasting shall be carried out using Aluminium oxide within the grade 90-220 mesh at a pressure of 480 kPa maximum for a time to give a clean even surface and then rinsed in cle
49、an cold water. Lubricant shall be applied within 3 h. (continued) Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CEN PREN83275 93 3404589 0053977 258 = prEN 3275 Page 8 Table 1 (continued) Clause 5.8 5.9 5.10 5.1 1 Characteristic Proof pressure Gase
