1、STD-AECMA PREN i335-ENGL 1777 W 1012311 001L507 TAT Edition approved for publication 1997-03-28 AECMA STANDARD NORME AECMA AECMA NORM Comments should be sent within six months after the date of publication to AECMA Gulledelle 94 B-1200 BRUXELLES prEN 4335 Edition P 1 March 1997 PUBLISHED BY THE EURO
2、PEAN ASSOCIATION OF AEROSPACE INDUSTRIES (AECMA) Gulledelle 94 - B-1200 BRUXELLES - Tel. (32) 2 775 81 10 - Fax. (32) 2 775 81 11 ICs : Descriptors : ENGLISH VERSION Aerospace series Steel FE-WA2602 (X4NiCrTiMoV26-I 5) Filler metal for welding Wire and rod Srie arospatiale Acier FE-WA2602 (X4NiCrTiM
3、oV26-I 5) Mtal dapport de soudage Fil et baguette Luft- und Raumfahrt Stahl FE-WA2602 (X4NiCrTiMoV26-I 5) Schweizusatz Draht und Stbe This “Aerospace Series Prestandard has been drawn up under the responsibility of AECMA (The European Association of Aerospace Industries). It is published on green pa
4、per for the needs of AECMA-Members. It has been technically approved by the 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 af
5、fected, physically or functionally, without re-identification of the standard. 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 Committe
6、e for Standardization) for formal vote. Nota - Extra copies can be supplied by B.N.A.E. - Technopolis 54 - 199, rue Jean-Jacques Rousseau - 921 38 ISSY-LES-MOULINEAUX CEDEX C5 Chairman Mr Odorico aecma 1997 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS und
7、er license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 3 prEN 4335 : 1997 O Introduction This standard is part of the series of EN metallic material standards for aerospace applications. The general organization of this series is described in EN
8、4258. This standard has been prepared in accordance with EN 4500-5. I Scope This standard specifies the requirements relating to : Steel FE-WA2602 (X4NiCrTiMoV26-I 5) Filler metal for welding Wire and rod for aerospace applications. 2 Normative references This European Standard incorporates by dated
9、 or undated reference provisions from other publications. These normative references are cited at the appropriate places in the text and the publications are listed hereafter. For dated references, subsequent amendments to or revisions of any of these publications apply to this European Standard onl
10、y when incorporated in it by amendment or revision. For undated references the latest edition of the publication referred to applies. EN 2043 Aerospace series - Metallic materials - General requirements for semi-finished product qualification (excluding forgings and castings) 1) EN 3879 Aerospace se
11、ries - Metallic materials - Filler metal for welding - Technical specification 1) EN 425% Aerospace series - Metallic materials - General organization of standardization - Links between types of EN standards and their use 1) EN 4500-5 Aerospace series - Metallic materials - Rules for drafting and pr
12、esentation of material standards - Part 5 : Specific rules for steel 1) 1) Published as AECMA Prestandard at the date of publication of this standard previous page is blank Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for Resal
13、eNo reproduction or networking permitted without license from IHS-,-,-STD-AECMA PREN 4335-ENGL 1777 = LOL23LL 0011509 852 Form Method of production Limit dimension(c) mm 1 Wire and rod Cold drawn - Page 4 prEN 4335 : 1997 Heat treatment Delivery condition code Use condition Heat treatment - U Delive
14、ry condition - EN 3879 . I I1 Direction of test piece - 12 Temperature f3 “C - - 16.1 1 Delivery condition I Cold drawn and annealed I - 14 T Strength R, MPa - 15 Elongation A% - 16 Reductionofarea Z % - 17 Hardness - - - Rupture stress Elongation at rupture Characteristics OR MPa - A yo - 18.1 I Te
15、st sample(s) 18.2 1 Test piece(s) FlHeat treatment I 9 I Dimensions concerned I mm I - 1%1 Thickness of ciadding on - Il01 each face I 13 I I Proof stress I Rpo,z( MPa I - Il I I I - Shear strength R, MPa Bending k- - Impact strength - Il I I I I23 t- I 24 I- l 26 L Cl Elongation I a I % I I 1 27 I
16、Notes (see line 98) I *) I 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-,-,-STD-AECMA PREN Li335-ENGL 1797 10123LL OOLLSLO 574 External defects Residual
17、 stress Internal defects Marking inspection Dimensional inspection Notes Typical use Page 5 prEN 4335 : 1997 See EN 3879 See EN 3879 See EN 3879 See EN 3879 See EN 3879 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo
18、reproduction or networking permitted without license from IHS-,-,-Page 6 prEN 4335 : 1997 Jroduct qualification See EN 2043 Clualification programme to be agreed between manufacturer and purchaser. 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-,-,-
