AECMA PREN 2635-2003 Aerospace Series Aluminium Alloy AL-P2014A T6511 Extruded Bars and Section a or D Less Than or Equal to 200 mm with Peripheral Coarse Grain Control Edition P 2.pdf

《AECMA PREN 2635-2003 Aerospace Series Aluminium Alloy AL-P2014A T6511 Extruded Bars and Section a or D Less Than or Equal to 200 mm with Peripheral Coarse Grain Control Edition P 2.pdf》由会员分享，可在线阅读，更多相关《AECMA PREN 2635-2003 Aerospace Series Aluminium Alloy AL-P2014A T6511 Extruded Bars and Section a or D Less Than or Equal to 200 mm with Peripheral Coarse Grain Control Edition P 2.pdf（6页珍藏版）》请在麦多课文档分享上搜索。

1、AECMA STANDARD NORME AECMA AECMA NORM prEN 2635 Edition P 2 October 2003 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES - STANDARDIZATION b Gulledelle 94 - 8-1200 Brussels -Tel. 32 2 775 81 10 - Fax. 32 2 775 811 1 - www.aecma-stan.org ICs: Descriptors: Supersedes edition P 1 Decem be

2、r 1998 ENGLISH VERSION Aerospace se ries Aluminium alloy AL-P2014A T6511 Extruded bar and section a or DI 200 mm with peripheral coarse grain control Srie arospatiale Luft- und Raumfahrt T6511 T6511 Al I age dah min um AL-P2014A Barres et profils fils aou D1200mm avec contrle de la zone priphrique g

3、ros grains Aluminiumlegierung AL-P2014A Stranggeprete Stangen und Profile a oder D I 200 mm mit Kontrolle der Grobkornrandzone This “Aerospace Series“ Prestandard has been drawn up under the responsibility of AECMA-STAN (The European Association of Aerospace Industries - Standardization). It is publ

4、ished for the needs of the European Aerospace Industry. It has been technically approved by the experts of the concerned Domain following member comments. Subsequent to the publication of this Prestandard, the technical content shall not be changed to an extent that interchangeability is afiected, p

5、hysically or functionally, without re-identification of the standard. After examination and review by users and formal agreement of AECMA-STAN, it will be submitted as a draft European Standard (prEN) to CEN (European Committee for Standardization) for formal vote and transformation to full European

6、 Standard (EN). The CEN national members have then to implement the EN at national level by giving the EN the status of a national standard and by withdrawing any national standards conflicting with the EN. Edition approved for publication 31 October 2003 Comments should be sent within six months af

7、ter the date of publication to AECMA-STAN Metallic Material Domain Copyright 2003 O by AECMA-STA! 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-,-,-Page

8、2 prEN 26352003 Foreword This standard was reviewed by the Domain Technical Coordinator of AECMA-STANS Metallic Material Domain. After inquiries and votes carried out in accordance with the rules of AECMA-STAN defined in AECMA- STANS General Process Manual, this standard has received approval for Pu

9、blication. 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-,-,-Page 3 prEN 26352003 O Introduction This standard is part of the series of EN metallic mater

10、ial standards for aerospace applications. The general organization of this series is described in EN 4258. This standard has been prepared in accordance with EN 4500-2. 1 Scope This standard specifies the requirements relating to: Aluminium alloy AL-P2014A T6511 Extruded bar and section a or D 5 200

11、 mm with peripheral coarse grain control for aerospace application. This standard may also be used to supply material for use in the T6510 condition if specified by the purchaser on the order and the product is marked accordingly. 2 Normative references This European Standard incorporates by dated o

12、r 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 only

13、when incorporated in it by amendment or revision. For undated references the latest edition of the publication referred to applies. EN 4258, Aerospace series - Metallic materials - General organization of standardization - Links between types of EN standards and their use EN 4400-3, Aerospace series

14、 - Aluminium and aluminium alloy wrought products - Technical specification - Part 3: Bar and section EN 4500-2 Aerospace series - Metallic materials - Rules for drafting and presentation of material standards - Part 2: Specific rules for aluminium, aluminium alloys and magnesium alloys 1) Published

15、 as AECMA Prestandard at the date of publication of this standard 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-,-,-1 Method of melting I Material design

16、ation Aluminium alloy AL-P2014A Form Bar and section Method of production Extruded Limit dimension(s) mm a or D 5 200 Technical specification EN 4400-3 Dimensions concerned mm each face Thickness of cladding on % - 3.1 - 3.2 7 - - - 3.1 3.2 3.3 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27

17、 - - - - - - - - - - - - - - - - - - - - - - a or 2,5 23 2 7; D 10 a or D 25 a or D 75 a or D 100 a or D 150 a or D 5 25 5 75 5 100 5 150 5 200 - - - - - - - I T6511 I T4511 a I Delivery condition Reduction ofarea Heat treatment Z % - 500 “C 5 5 510 “CI WQ 5 40 “C + 1 % 5 controlled stretched 5 3 %

18、+ 155 “C 5 5 165 “C I 12 h 5 t 5 20 h or 170 “C 5 5 180 “C I 5 h 5 t 5 12 h 500 “C 5 5 510 “CI WQ 5 40 “C + 1 % 5 controlled stretched 5 3 % + = ambient It 2 5 d Hardness Shear strength & MPa Bending k- I U I K I Delivery condition code - - - I T6511 I T6511 I Use condition “ Elongation Rupture stre

19、ss Heat treatment a% - OR MPa - Delivery condition 155 “C 5 5 165 “C I 12 h 5 t 5 20 h or 170 “C 5 5 180 “C I 5 h 5 t 5 12 h Elongation at rupture Delivery condition A % - Characteristics Test sample(s) I See EN 4400-3. Test piece(s) I See EN 4400-3. Heat treatment I Use condition Direction of test

20、piece ILILILILILILIL I Temperature I I “C I Ambient I Ambient I Ambient I Ambient I Ambient I Ambient I Ambient I Proofstress I Rm,? IMPal 2370 I 2385 I 2415 I 2440 I 2435 I 2420 I 2390 T I Strength I Rm IMPal 2415 I 2435 I 2460 I 2490 I 2480 I 2465 I 2435 Impact strength I I Time Ihl Copyright Asso

21、ciation Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 5 prEN 26352003 - ixternal defects See EN 4400-3. nternal defects 3atch uniformity Electrical conductivity ixtru

22、sion back-end defect eripheral coarse grain y MSlm 18,5 (Typical value) 22,O (Typical value) Marking inspection Iimensional inspection 7 Votes 115 (Typical value) 135 (Typical value) Hardness HB 2 16 per product 2 20 per product 2 24 per batch 2 30 per batch rypical use - - See EN 4400-3. See EN 440

23、0-3. -I See EN 4400-3. - - See EN 4400-3. -I See EN 4400-3. See EN 4400-3. 71 I T4511 I T6511 71 Level A - I a T451 O if the use condition is T651 O. -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-,-,-100 Page 6 prEN 26352003 - Product qualification 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-,-,-