AECMA PREN 3344-2003 Aerospace Series Aluminium Alloy AL-P7050-T76511 Extruded Bars and Section a or D Less Than or Equal to 150 mm with Peripheral Coarse Grain Control Edition P 3.pdf

1、AECMA STANDARD NORME AECMA AECMA NORM prEN 3344 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- T76511 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- T76511 T76511 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 afi

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! 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-,

8、-,-Page 2 prEN 3344:2003 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 has received approv

9、al for Publication. 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 3344:2003 O Introduction This standard is part of the series of EN meta

10、llic 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. 1 Scope This standard specifies the requirements relating to: Aluminium alloy AL-P7050- T76511 Extruded bar and section a

11、 or D 5 150 mm with peripheral coarse grain control for aerospace application. This standard may also be used to supply material in the T76510 condition if specified by the purchaser on the order and the product is marked accordingly. 2 Normative references This European Standard incorporates by dat

12、ed or 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 o

13、nly 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 se

14、ries - 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) Publi

15、shed 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 de

16、signation Aluminium alloy AL-P7050- Form Bar and section Method of production Extruded Limit dimension(s) mm a or D 5 150 Technical specification EN 4400-3 Heat treatment Dimensions concerned mm - 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、 - - - - - - - - - - - - - Use condition aorD510 10 a or D 5 150 Delivery condition I T76511 Thickness of cladding on each face Heat treatment % - - 470 “C 5 5 485 “CI WQ 5 40 “C + 1 % 5 controlled stretched 5 3 % + 110 “C 5 B5 125 “C I3 h 5 t 5 24 h + 157 “C 5 B5 177 “C I6 h 5 t 5 18 h Hardness She

18、ar strength & MPa Bending k- Delivery condition code I U - - - T76511 I Use condition Tem perature Delivery condition I Heat treatment B “C - Characteristics Time Test sample(s) I See EN 4400-3. - h Test piece(s) I See EN 4400-3. “ Elongation Rupture stress a% - OR MPa - Elongation at rupture L I L

19、I Direction of test piece A % - Ambient I ITemperature I B I “C I Ambient Notes (see line 98) t 475 I I Proof stress I R,z I MPa I t 470 - T I Strength I Rm IMPal t 530 I t 545 I Elongation I A I % I At 7 or ASOmm t 6 I 27 I Reductionofarea I Z I % I - Impact strength I - Copyright Association Europ

20、eene 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 3344:2003 - See EN 4400-3. 7 - y t 22,5 MSlm Acceptable Acceptable if Rp0,2 L 2 Rp0,2 min. + 60 MPa ( see line 13) or

21、if stress corrosion test results are acceptable (see line 39). 21,5 MSlm 2 y 2 22,5 MSlm y21,5MSlm Not acceptable See EN 4400-3. 7 - tt20d See EN 4400-3. 7 Dimensions L-T T-L (mm) MPa & MPa & t 27 25 a or D 2 50 t 22 - 100 a or D 2 150 t 25 t 20 See EN 4400-3. - 7 See EN 4400-3. Exfoliation corrosio

22、n shall not be greater than that of grade EB. - 7 See EN 4400-3. Electrical conductivity See EN 4400-3. 6 2 20 per product A 2 30 per batch - - See EN 4400-3. See EN 4400-3. ilectrical conductivity Stress corrosion 61 o= 170 MPa 3acture toughness t 21 I I 50aorD2100 I t 26 ixternal defects ixfoliati

23、on corrosion nternal defects -I See EN 4400-3. 3atch uniformity or 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 - Copyright Association Europeene des Constructeurs de Ma

24、teriel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-100 Page 6 prEN 3344:2003 - 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-,-,-