1、CEN PRENg3499 93 D 3401.1589 0044674 895 D Edition approved for publication Comments should be sent within six months after the date of publication to AECMA Technopolis - 1 75, rue Jean-Jacques Rousseau 921 38 Issy-les-Moulineaux Cedex - FRANCE 1993-04-26 AECMA STANDARD NORME AECMA AECMA NORM C5 Cha
2、irman M. ODORICO prEN 3499 Edition P 2 April 1993 EDITE PAR LASSOCIATION EUROPEENNE DES CONSTRUCTEURS DE MATERIEL AEROSPATIAL Technopolis - 175, rue Jean-Jacques Rousseau - F-92138 Issy-les-Moulineaux Cedex - Tl. (1) 47.36.98.76 Supersedes Issue P 1 UDC : March 1988 Descriptors : ENGLISH VERSION Aer
3、ospace series Titanium TLP99003 Annealed Sheet and strip, cold rolled aI6mm 570 MPa I Rm 5 730 MPa Srie arospatiale Titane TI-P99003 Recuit Tles et bandes, lamines froid al6mm 570 MPa l Rm I 730 MPa Luft- und Raumfahrt Titan TI-P99003 Geglht Bleche und Bnder, kaltgewalzt aI6mm 570 MPa I Rm I 730 MPa
4、 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 the experts of the concerned Technical Committe
5、e 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 the A
6、ECMA Standard Checking Centre (NPSI 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. COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed
7、 by Information Handling ServicesCEN PRENa3499 93 3404589 0044b75 721 9 prEN 3499 Page 3 O Introduction For the use of this standard, see EN 2500-4. 1 Scope and field of application This standard specifies the requirements relating to sheet and strip, cold rolled, a s 6 mm, annealed, 570 MPa I R, I7
8、30 MPa in titanium TLP99003 for aerospace applications. 2 References EN 2339 Sheets, titanium and titanium alloys - Cold rolled - Thickness 0,2 mm I a I 3 mm - Dimensions - Aerospace series Aerospace series - Instructions for the drafting and use of metallic material standards - Part 4 - Specific re
9、quirements for titanium and titanium alloys 2, Aerospace series - Designation of metallic semi-finished products - Rules 2, EN 2500-4 EN 2600 EN 3544-1 Aerospace series - Titailium and titanium alloys - Wrought products - Technical specification - Part 1 - General requirements 3, EN 3544-2 Aerospace
10、 series - Titanium and titanium alloys - Wrought products - Technical specification - Part 2 - Plate, sheet and strip 3, I) Published as AECMA standard at the date of publication of this standard 2) Published as AECMA pre-standard at the date of publication of this standard 3) In preparation at the
11、date of publication of this standard Previous page is blank COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling ServicesprEN 3499 Page 4 1 Material designation 2 Chemical Element composition min. % max. Titanium TI - P99003 o2 N2 H2 Fe C Others Ti
12、Each Total 0,40 0,05 0,0125 0,35 0,08 0,IO 1 0,601) Base 3 4 Method of melting See EN 35461 Form Sheet and strip Method of production Cold rolled Limit dimensions (mm) as6 - 8 _ 5 5.1 Technical specification 5.2 Dimensional standards 9 i0 - - 11 12 13 14 15 16 - - - - - - 17 I8 19 20 21 22 23 24 25
13、26 27 - - - - - - - - - - - EN 3544-2 EN 2339 6.1 Delivery condition and heat treatment 6.2 Delivery condition code Use condition and heat treatment Annealed 600 C s 8 s 840 C I t 2 1 min I AC or inert atmosphere U Delivery condition Sample Test piece Heat treatment Dimensions concerned mm Thickness
14、 of cladding on % each face Direction of test piece Temperature e C Use condition as2 2as5 5as6 - See EN 3544-2 Ambient T 2 460 Proof stress Rpo,2 MPa Strength Rm MPa 570 5 R, 730 Elongation A% A50mm216 Reduction of 2% area Shear strength Bending R, MPa k 2,5 ; a = 105“ 3,O ; a = 105“ Temperature e
15、“C Time Stress ua h MPa C Elongation a % Rupturestress UR MPa Elongation at A% rupture Notes (see line 98) 1) COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling ServicesCEN PRENr3499 93 m 3404589 0044b77 5T4 m prEN 3499 Page 5 ixternal defects ;utface contamination lesig nation Jotes -ypicai use -I See EN 3544-2 See EN 3544-2 6 5 mm as6 mm See EN 2600 ) Determination not required for routine acceptance COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling Services
