1、STD.AECMA PREN 3qb7-ENGL L7L LOL23LL 001L85b 311 m AECMA STANDARD NORME AECMA AECMA NORM prEN 3467 Edition P 2 December 1996 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES (AECMA) Gulledelle 94 - B-1200 BRUXELLES - Tel. (32) 2 775 81 1 O - Fax. (32) 2 775 81 11 ICs : Supersedes issue
2、P 1 March 1988 Descriptors : ENGLISH VERSION Aerospace series Titanium alloy TI-C64001 Not heat treated Remelting stock De I 300 mm Srie arospatiale Alliage de titane TI-C64001 Non trait Demi-produit pour refusion De I 300 mm Luft- und Raumfahrt Titanlegierung TLC6400 1 Nicht wrmebahandelt Guvormate
3、rial O, I 300 mm 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 concerned Technical Commi
4、ttee 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 and signature of th
5、e 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. - Technopolis 54 - 199, rue
6、Jean-Jacaues Rousseau - 921 38 ISSY-LES-MOULINEAUX CEDEX Comments should be sent within six months after the date of publication to I Edition approved for publication I 1 996- 1 2-3 1 AECMA Gulledelle 94 C5 Chairman Mr Odorico B-1200 BRUXELLES aecma 199i Copyright Association Europeene des Construct
7、eurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,- STD-AECMA PREN 3Lib7-ENGL 377b - LOLI?IIII 0033857 258 m Page 3 prEN 3467 : 1996 O Introduction This standard is part of the series of EN metallic
8、material standards for aerospace applications. The general organization of this series is described in EN 4258. This standard has been prepared in accordance with EN 4500-4. 1 Scope This standard specifies the requirements relating to : Titanium alloy TI-C64001 Not heat treated Remelting stock De I
9、300 mm for aerospace applications. 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 and the publications are listed hereafter. For dated references,
10、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. EN 2545-2 Aerospace series - Titanium and titanium alloy remelti
11、ng stock and castings - Technical specification - Part 2 : Remelting stock EN 4258 Aerospace series - Metallic materials - General organization of standardization - Links between types of EN standards and their use EN 4500-4 Aerospace series - Metallic materials - Rules for drafting and presentation
12、 of material standards - Part 4 : Specific rules for titanium and titanium alloys 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
13、 for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 4 prEN 3467 : 1996 Chemical Element 2 composition % min. max. I 1 I Material designation I Titanium alloy TLC64001 Others 1 Each Total AI V 02+2N2 N2 H2 Fe C Ti 53 3.5 - - - - - - - Base 6,75 4.5 0.25 0,03 0,0125 0,
14、30 0,08 0,lO 0,40 3 4.1 4.2 4.3 5 Method of melting EN 2545-2 Form Remelting stock Method of production Cast or wrought 2, Limit dimension(s) mm 0,1300 Technical specifcation EN 2545-2 6.1 Delivery condition Heat treatment 6.2 Deliverv condition code Not heat treated - U Characteristics 7 Use condit
15、ion Delivery condition Heat treatment - I 8.3 I Heat treatment 8.1 8.2 Test sample(s) - Test piece(s) - Il I I I I 9 Dimensions concerned mm - lo Thickness of cladding on % - 11 Direction of test piece - 12 Temperature B “C - 13 Proofstress R,-,2 MPa - 14 T Strength R, MPa - 15 Elongation A% - each
16、face - - - 1.i61 I Reductionof area I 2 I % -1 17 8 Hardness - Shear strength I R, MPa - I 19 I Bending IkI-1 ;Ieperature e - “C h - C Stress Elongation Rupturestress ua MPa - a% - uR MPa - A% - 27 1 Notes (cee line 98) I 1) 2) I Copyright Association Europeene des Constructeurs de Materiel Aerospat
17、ial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 5 prEN 3467 : 1996 ixternal defects I Typical use Marking inspection Dimensional inspection Notes See EN 2545-2 - - See EN 2545-2 - 1) Determination not required for ro
18、utine acceptance. 2) Wrought products correspond to bars, billet or plates made in TLP64001 according to EF material standard. See EN 2545-2 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking p
19、ermitted without license from IHS-,-,-Page 6 prEN 3467 : 1996 Product qualification Qualification programme to be agreed beiween 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-,-,-
