1、AECMA STANDARD NORME AECMA AECMA NORM prEN 2702 Edition P 3 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: ENGLISH VERSION Aerospace se ri
2、es Aluminium alloy AL-P6061- T6 or T62 Drawn or extruded bar and section a or DI 200 mm Supersedes edition P 2 Decem ber 1998 Srie arospatiale Alliage daluminium AL-P6061- T6 ou T62 Barres et profils fils ou tirs aou D1200mm Luft- und Raumfahrt Aluminiumlegierung AL-P6061- T6 oder T62 Gezogene oder
3、Stranggeprete Stangen und Profile a oder D I 200 mm This “Aerospace Series“ Prestandard has been drawn up under the responsibility of AECMA-STAN (The European Association of Aerospace Industries - Standardization). It is published for the needs of the European Aerospace Industry. It has been technic
4、ally 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, physically or functionally, without re-identification of the standard. After
5、 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 Standard (EN). The CEN national members have then to implement the EN at n
6、ational 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 after the date of publication to AECMA-STAN Metallic Material Domain Copyrigh
7、t 2003 O by AECMA-STA! Page 2 prEN 2702:2003 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
8、 has received approval for Publication. Page 3 prEN 2702:2003 O Introduction This standard is part of the series of EN metallic 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 4500-2
9、. 1 Scope This standard specifies the requirements relating to: Aluminium alloy AL-P6061- T6 or T62 Drawn or extruded bar and section a or D 5 200 mm for aerospace application. 2 Normative references This European Standard incorporates -y dated or undated reference provisions from other publications
10、. 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 when incorporated in it by amendment or revision. For
11、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 - Aluminium and aluminium alloy wrought products - Te
12、chnical 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 as AECMA Prestandard at the date of publication of th
13、is standard Page 4 prEN 2702:2003 520 “C 82 540 “C I WQ 82 40 “C + 8= ambient It t 5d Method of melting I 520 “C 82 540 “C I WQ 82 40 “C + 155 “C 82 175 “C 8 ht 16 h Form Bar and section Method of production Limit dimension(s) mm a or D 200 Drawn or extruded Technical specification EN 4400-3 Deliver
14、y condition + 520 “C 82 540 “CI WQ 82 40 “C + 155 “C 82 175 “C I8 h t 16 h - 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 - - - - - - - - - - - - - - - - - - - - - - Delivery condition + 155 “C 82 175 “CI 8 h t 16 h Delivery condition I F I O I I T6 I T4 Deli
15、very condition Heat treatment Dimensions concerned mm Heat treatment Use condition a or D 200 Thickness of cladding on each face I U I K I A I F I Delivery condition code % - I T62 I T6 I T6 I Use condition Hardness Shear strength & MPa Bending k- Heat treatment - - - Tem perature Characteristics 8
16、“C - Test sample(s) I See EN 4400-3. Time Test piece(s) I See EN 4400-3. - h “ Elongation Rupture stress a% - OR MPa - L I Direction of test piece Elongation at rupture ITemperature I 8 I “C I Ambient A % - I Proof stress I R,z I MPa I t 245 Notes (see line 98) T I Strength I Rm IMPal t 270 - I Elon
17、gation I A I % I A or komm t 10 I Reductionofarea I Z I % I - Impact strength I - ixternal defects - nternal defects 3atch uniformity See EN 4400-3. ixtrusion back-end defect - - Marking inspection Iimensional inspection See EN 4400-3. See EN 4400-3. Votes - - rypical use See EN 4400-3. See EN 4400-3. 51 T4 T6 60 (Typical value) 90 (Typical value) Hardness HB 2 16 per product 2 20 per product 7 2 24 per batch 2 30 per batch I See EN4400-3. -I -I 100 Page 6 prEN 2702:2003 - Product qualification
