1、CEN PRENx3497 93 3404587 0044bbb 719 Edition approved for publication AECMA STANDARD NORME AECMA AECMA NORM C5 Chairman Comments should be sent within six months after the date of publication to prEN 3497 Edition P 2 ApriJ 1993 UDC : DIT PAR LASSOCIATION EUROPENNE DES CONSTRUCTEURS DE MATERIEL AROSP
2、ATIAL Technopolis - 175, rue Jean-Jacques Rousseau - F-92138 Issy-les-Moulineaux Cedex - Tl. (1) 47.36.98.76 Supersedes Issue P 1 March 1988 Descriptors : ENGLISH VERSION Aerospace series Titanium TLP99001 Annealed Sheet and strip, cold rolled a56mm 290 MPa I Rm I420 MPa Srie arospatiale Titane TI-P
3、99001 Recuit Tles et bandes, lamines froid aS6mm 290 MPa 5 Rm I420 MPa Luft- und Raumfahrt Titan TLP99001 Geglht Bleche und Bnder, kaltgewalzt aI6mm 290 MPa I R, I420 MPa This “Aerospace Series“ Prestandard has been drawn up under the responsibility of AECMA (Association Europenne des Constructeurs
4、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 Committee following comment by the Member countries. Subsequent to the publication of this prestandard, the technical content shall not be
5、 changed to an extent that interchangeability is affected, 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
6、a draft European Standard to CEN (European Committee for Standardization) for formal vote. 1993-04-26 AECMA Technopolis - 175, rue Jean-Jacques Rousseau 921 38 Issy-les-Moulineaux Cedex - FRANCE M. ODORICO I I aecrna 199 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provi
7、ded by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CEN PREN*3477 73 m 3404587 0044667 b55 m prEN 3497 Page 3 O Introduction For the use of this standard, see EN 2500-4. 1 Scope and field of application This standard specifies the req
8、uirements relating to sheet and strip, cold rolled, a 5 6 mm, annealed, 290 MPa I R, s 420 MPa in titanium TI-P99001 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 - In
9、structions for the drafting and use of metallic material standards - Part 4 - Specific requirements 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 - Titanium and titanium alloys - Wrought p
10、roducts - Technical specification - Part 1 - General requirements 3, EN 3544-2 Aerospace series - Titanium and titanium alloys - Wrought products - Technical specification - Part 2 - Plate, sheet and strip 3, 1) Published as AECMA standard at the date of publication of this standard 2) Published as
11、AECMA pre-standard at the date of publication of this standard 3) In preparation 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 ResaleNo reproduction or netwo
12、rking permitted without license from IHS-,-,-CEN PREN*3497 93 m 3404589 0044bb8 591 m - Chemical Element prEN 3497 Page 4 02 N2 H2 Fe C Others Ti Each 1 Total Material designation I Titanium il - P99001 composition % min. I- Base max. 0,20 0,05 0,0125 0,20 0,08 I 0,lOl) O,6Oi) Method of melting Form
13、 Method of production Limit dimensions (mm) 5.1 Technical specification 5.2 Dimensional standards See EN 3544-1 Sheet and strip Cold rolled a56 EN 3544-2 EN 2339 6 7 - 21 22 23 24 25 26 - - - - - 27 - 6.1 Delivery condition Annealed and heat treatment 600 “C i 8 s 840 “C It 2 1 min I AC or inert atm
14、osphere 6.2 Delivery condition code U Use condition Delivery condition and heat treatment C 8 Sample Test piece Heat treatment 9 Dlmensions concerned mm 10 Thidmess of cladding on % each face I I Direction of the test pieces 12 Temperature 6 “C - 13 Proofstress Rpo,2 MPa - 14 T Strength R, MPa 15 El
15、ongation A% 16 Reductionof 2 % 17 Hardness 19 Bending k 20 Impact strength - -I area ITemperature I 6 - Use condition a52 2as5 5as6 See EN 3544-2 Ambient 2 200 290 5 R, 420 A50m224 1,0 ; a = 105“ 1,5 ; a = 105“ Stress Elongation IRupturestress I y Elongation at rupture Notes (see line 98) “C h MPa %
16、 MPa % 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 PRENx3497 93 3404589 O044669 428 prEN 3497 Page 5 External defects Surface contamination les
17、ignation rlotes rypical use See EN 3544-2 See EN 3544-2 5 mrn a 16 rnm See EN 2600 i) Determination not required for routine acceptance 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-,-,-
