AECMA PREN 3886-2001 Aerospace Series Heat Resisting Alloy NI-WH1303 Filler Metal for Welding Edition P 2 Supersedes Edition P 1 January 1995 Replaced by EN 3886《航空航天系列抗热铝合金 NI-WH1.pdf

《AECMA PREN 3886-2001 Aerospace Series Heat Resisting Alloy NI-WH1303 Filler Metal for Welding Edition P 2 Supersedes Edition P 1 January 1995 Replaced by EN 3886《航空航天系列抗热铝合金 NI-WH1.pdf》由会员分享，可在线阅读，更多相关《AECMA PREN 3886-2001 Aerospace Series Heat Resisting Alloy NI-WH1303 Filler Metal for Welding Edition P 2 Supersedes Edition P 1 January 1995 Replaced by EN 3886《航空航天系列抗热铝合金 NI-WH1.pdf（4页珍藏版）》请在麦多课文档分享上搜索。

1、 AECMA STANDARD NORME AECMA AECMA NORM prEN 3886 Edition P 2 September 2001 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES - STANDARDIZATION (AECMA-STAN) Gulledelle 94 - 8-1200 BRUXELLES - Tel. (+32) 2 775 81 10 - Fax. (+32) 2 775 81 11 Supersedes edition P 1 ICs: January 1995 Descrip

2、tors: ENGLISH VERSION Aerospace series Heat resisting alloy NI-WH1 303 Filler metal for welding Srie arospatiale Alliage rsistant chaud NI-WH1303 Mtal dapport de soudage Luft- und Raumfahrt Hochwarmfeste Legierung NI-WH1303 Schweizusatz needs of the European Aerospace Industry. It has been tech conc

3、erned Domain following member comments. Subsequent to the publication of extent that interchangeability is After examinati not be changed to an re-identification of the Replace page 1 of the previous edition by this page Nota - Extra copies can be supplied by B.N.A.E. - Technopolis 54 - 199. rue Jea

4、n-Jacques Rousseau - 92138 ISSY-LES-MOULINEAUX CEDEX I I Withdrawal approved 2001-09-28 Comments should be sent within six months after the date of publication to Gulledelle 94 AECMA-STAN B-1200 BRUXELLES Material Domain Mr Evetts I I aecma 20( Copyright Association Europeene des Constructeurs de Ma

5、teriel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 3 prEN 3886 : 1995 O Introduction For the use of this standard, see EN 2500-3. 1 Scope This standard specifies the requirements relating to filler metal

6、for welding, cold drawn and annealed, in heat resisting alloy NI-WH 1303 for aerospace application. 2 Normative references This European Standard incorporates by dated or undated reference provisions from other publications. These normative references are cited at the appropriate places in the text

7、and the publications are listed hereafter. For dated references, subsequent amendments to or revisions of any of these publications apply to this European Standard only when incorporated in it by amendment or revision. For undated references the latest edition of the publication referred to applies.

8、 EN 2500-3 Aerospace series - Instructions for the drafting and use of metallic material standards - Part 3 : Specific requirements for heat resisting alloys 1) EN 2600 Aerospace series - Designation of metallic semi-finished - Rules EN 3879 Aerospace series - Metallic materials - Filler metals for

9、welding - Technical specification 2) EN 4060 Aerospace series - Heat resisting alloys - Filler rods and filler wires for welding - Diameter 0,5 mm 0 I 5,O mm - Dimensions 2, 1) Published as AECMA Prestandard at the date of publication of this standard 2) In preparation at the date of publication of

10、this standard Previous page is blank 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 388b-ENGL 1775 m 101231L OOL255q 773 Form Method of

11、 production Limit dimensions mm) Page 4 prEN 3886 : 1995 Filler wire and filler rods Cold drawn - 8 Sample Test piece Heat treatment 6.1 Technical specification - - - EN 3879 Dimensions concerned Thickness of cladding on each face 5.2 Dimensional standards mm - % - EN 4060 Direction of test piece Te

12、mperature U OC 6.1 Delivery condition and heat treatment - - 6.2 Delivery condition code T Use condition and heat treatment Proof stress Rp0,2 MPa - Strength R, MPa - Cold drawn and annealed Reduction of area U 2 YO - Delivery condition - Impact strength I Temperature I O 1 OC - - C L Elongation a O

13、h - Rupture stress OR MPa - rumure Elongation at A % - I I Elongation I A I % I - 17 I Hardness I I Shear strength I R, I MPa I Bending 1kl-l I Stress I27 I Notes (see line 98) I *) I Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANo

14、t for ResaleNo reproduction or networking permitted without license from IHS-,-,-STD*AECMA PREN 388h-ENGL 1795 1012311 0012555 b2T Page 5 prEN 3886 : 1995 External defects Residual stress internal defects Designation Notes Typical use See EN 3879 See EN 3879 I See EN 3879 See EN 2600 *) p.p.m. 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-,-,-