1、AECMA STANDARD NORME AECMA AECMA NORM prEN 3338 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: Supersedes edition P 2 February
2、 1999 ENGLISH VERSION Aerospace se ries Al u min i um alloy AL-P7050- T74511 Extruded bar and section a or D I 150 mm with peripheral coarse grain control Srie arospatiale Luft- und Raumfahrt Alliage daluminium AL-P7050- Aluminiumlegierung AL-P7050- T74511 T74511 Barres et profils fils aou DI 150 mm
3、 avec contrle de la zone priphrique gros grains Stranggeprete Stangen und Profile a oder D I 150 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
4、 is published 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 aff
5、ected, physically 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
6、European 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 m
7、onths after the date of publication to AECMA-STAN Metallic Material Domain Copyright 2003 O by AECMA-STA! Page 2 prEN 3338:2003 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 th
8、e rules of AECMA-STAN defined in AECMA- STANS General Process Manual, this standard has received approval for Publication. Page 3 prEN 3338:2003 O Introduction This standard is part of the series of EN metallic material standards for aerospace applications. The general organization of this series is
9、 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-P7050- T74511 Extruded bar and section a or D 5 150 mm with peripheral coarse grain control for aerospace application. This standard m
10、ay also be used to supply material in the T74510 condition if specified by the purchaser on the order and the product is marked accordingly. 2 Normative references This European Standard incorporates by dated or undated reference provisions from other publications. These normative references are cit
11、ed 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 undated references the latest editio
12、n 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 - Technical specification - Part 3: Bar
13、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 this standard 1 3 t.1 t.2 t.3 5 - - -
14、- Material designation Aluminium alloy AL-P7050- Method of melting I Form Method of production Limit dimension(s) mm Technical specification Bar and section Extruded a or D 5 150 EN 4400-3 3.1 Delivery condition T74511 470 “C 5 5 485 “CI WQ 5 40 “C Heat treatment Heat treatment Dimensions concerned
15、mm + 1 % 5 controlled stretched 5 3 % + 105 “C 5 B5 125 “C I6 h 5 t 5 24 h + 167 “C 5 B5 180 “C I6 h 5 t 5 16 h Use condition aorD5150 I U I 3.2 I Delivery condition code Thickness of cladding on each face I T74511 I 7 I Use condition % - I Heat treatment I Delivery condition I Proof stress Strength
16、 T - 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 - - - - - - - - - - - - - - - - - - - - - - RPO,Z MPa t 435 R, MPa t 505 Characteristics Hardness Shear strength & MPa Bending k- Test sample(s) I See EN 4400-3. - - - Test piece(s) I See EN 4400-3. Tem perature B “C - Time L I
17、 Direction of test piece - h ITemperature I 6 I “C I Ambient “ Elongation Rupture stress a% - OR MPa - I Elongation I A I % I A or&, t 7 Elongation at rupture I Reductionofarea I Z I % I - A % - Notes (see line 98) Impact strength I - - Page 5 prEN 3338:2003 - See EN 4400-3. 7 y t 23,O MSlm Acceptab
18、le I - y L 2 495 MPa or if stress corrosion test results are acceptable (see line 39). 22,O MSlm 2 y 2 23,O MSlm Stress corrosion 61 o = 240 MPa 3acture toughness t 22 I I 50aorD2100 I t 27 ixternal defects ixfoliation corrosion nternal defects -I See EN 4400-3. 3atch uniformity 71 Hardness -I See EN 4400-3. ixtrusion back-end defect eripheral coarse grain See EN 4400-3. -I 71 Level A Marking inspection Iimensional inspection Votes -I rypical use -I 100 Page 6 prEN 3338:2003 - Product qualification
