AECMA PREN 2632-2003 Aerospace Series Aluminium Alloy AL-P7075-T73511 - Extruded Bar and Section a or D Less Than or Equal to 150 mm with Peripheral Coarse Grain Control Edition P1.pdf

1、a Date: 16 May 2003 Origin: European Latest date for receipt of comments: 2003.08.31 Project no.: 2003/01281 Responsible committee: ACE/24 Wrought And Cast Aluminium And Magnesium Alloys For Aerospace Interested committees: Title: Draft EN 2632 Aerospace series - Aluminim alloy AL-P7075-T73511 - Ext

2、ruded bar and section a or D 150 mm with peripheral coarse grain control Supersession information: If you are aware of a current national standard which may be affected, please notify the secretary (contact details below). WARNING: THIS IS A DRAFT AND MUST NOT BE REGARDED OR USED AS A BRITISH STANDA

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15、F THE SECRETARIAT 3.1 1st definition Editorial Definition is ambiguous and needs clarifying. Amend to read . so that the mains connector to which no connection . 6.4 2 Technical The use of the UV photometer as an alternative cannot be supported as serious problems have been encountered in its use in

16、 the UK. Delete reference to UV photometer. Microsoft and MS-DOS are registered trademarks, and Windows is a trademark of Microsoft Corporation. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for Resale No reproduction or networ

17、king permitted without license from IHS -,-,- DRAFT EN 2632 Date : January 2003 Edition : P1 STUDY : MMD DRAFT N : 1 STAGE : Superseding Ref.: 1EN Dated December 1993 ENGLISH VERSION Aerospace series Aluminium alloy AL-P7075- T73511 Extruded bar and section a or D 150 mm with peripheral coarse grain

18、 control Srie arospatiale Luft- und Raumfahrt Alliage daluminium AL-P7075- Aluminiumlegierung AL-P7075- T73511 T73511 Barres et profils fils Stranggeprete Stange und Profile a ou D 150 mm a oder D 150 mm avec contrle de la zone priphrique gros grains mit Kontrolle der Grobkornrandzone Master documen

19、t : X en fr de THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES - STANDARDIZATION Gulledelle 94, B - 1200 Bruxelles Tel. : (32) 2 775 8110 Fax.: (32) 2 775 8111 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for Resale No reprod

20、uction or networking permitted without license from IHS -,-,-Page 2 EN 2632 : 2003 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for Resale No reproduction or networking permitted without license from IHS -,-,-Page 3 EN 2632 :

21、2003 0 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. 1 Scope This standard specifies the requirements relati

22、ng to : Aluminium alloy AL-P7075- T73511 Extruded bar and section a or D 150 mm with peripheral coarse grain control for aerospace applications. This standard may also be used to supply material in the T73510 condition if specified by the purchaser on the order and the product is marked accordingly.

23、 2 Normative references This Standard incorporates by dated 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 an

24、y of these publications apply to this Standard only when incorporated in it by amendment or revision. For undated references the latest edition of the publication referred to applies. EN 4400-3 Aerospace series - Aluminium and aluminium alloy wrought products - Technical specification - Part 3 : Bar

25、 and section EN 4258 Aerospace series - Metallic materials - General organization of standardization - Links between types of EN standards and their use 1)EN 4500-2 Aerospace series - Metallic materials - Rules for drafting and presentation of material standards - Part 2 : Specific rules for alumini

26、um, aluminium alloys and magnesium alloys 1)_ 1) Published 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 AECMA Not for Resale No reproduction or networking permitted withou

27、t license from IHS -,-,-Page 4 EN 2632 : 2003 1 Material designation Aluminium alloy AL-P7075- 2 Chemical Element Si Fe Cu Mn Mg Cr Zn Ti Zr + Ti a Others Al composition min. 1,2 2,1 0,18 5,1 - Each Total Base% max. 0,40 0,50 2,0 0,30 2,9 0,28 6,1 0,2 0,25 0,05 0,15 3 Method of melting 4.1 Form Bar

28、and section 4.2 Method of production Extruded 4.3 Limit dimensions mm a or D 150 5 Technical specification EN 4400-3 6.1 Delivery condition T6511 bT73511 Heat treatment 460 C 470 C / WQ 40 C + 1 % controlled stretched 3 % + 105 C 125 C / 20 h t 30 h 460 C 470 C / WQ 40 C + 1 % controlled stretched 3

29、 % + 105 C 125 C / 20h t 30 h + 172 C 182 C / 5 h t 12 h 6.2 Delivery condition code P U 7 Use condition T73511 T73511 Heat treatment Delivery condition + 172 C 182 C / 5 h t 12 h Delivery condition Characteristics 8.1 Test sample(s) See EN 4400-3 8.2 Test piece(s) See EN 4400-3 8.3 Heat treatment U

30、se condition 9 Dimensions concerned mm a or D 10 10 a or D 20 20 a or D 50 50 a or D 75 75 a or D 100 100 a or D 150 10 Thickness of cladding on each face % 11 Direction of test piece L L L L L L 12 Temperature C Ambient Ambient Ambient Ambient Ambient Ambient 13 Proof stress R p0,2MPa 400 420 415 4

31、10 390 370 14 T Strength R mMPa 470 485 485 475 470 450 15 Elongation A % A 8 or A 50mm 7 8 8 8 7 7 16 Reduction of area Z % 17 Hardness 18 Shear strength R cMPa 19 Bending k 20 Impact strength 21 Temperature C 22 Time h 23 Stress aMPa 24 C Elongation a % 25 Rupture stress RMPa 26 Elongation at rupt

32、ure A % 27 Notes (see line 98) a,b BM/07/03/2003/T6 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for Resale No reproduction or networking permitted without license from IHS -,-,-Page 5 EN 2632 : 2003 32 Electrical conductivity

33、 See EN 4400-3 7 23,0 MS/m Acceptable 22,0 MS/m 23,0 MS/m Acceptable if R p0,2L R p0,2min. L + 85 MPa ( see line 13) or if stress corrosion results are acceptable (see line 39 ) . 22,0 MS/m Not acceptable 39 Stress corrosion See EN 4400-3 6 = 75 % R p0,2min. L ( see line 13 ) 7 t 20d 44 External def

34、ects See EN 4400-3 61 Internal defects See EN 4400-3 82 Batch uniformity See EN 4400-3 5 T6511 bT73511 7 Electrical conductivity MS/m 19,0 (Typical value) 23,2( Typical value) or 150 (typical value) 140 (typical value) Hardness HB 20 per product 20 per product 30 per batch 30 per batch 87 Extrusion

35、back-end defect - See EN 4400-3 - See EN 4400-3 88 Peripheral coarse grain 7 Peripheral coarse grain : Level A 96 Marking inspection See EN 4400-3 97 Dimensional inspection See EN 4400-3 98 Notes a) A (Zr + Ti) addition may only be made subject to agreement with the purchaser. b) T6510 if the use co

36、ndition is T73510. 99 Typical use BM/07/03/2003/T6 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for Resale No reproduction or networking permitted without license from IHS -,-,-Page 6 EN 2632 : 2003 BM/07/03/2003/T6 100 Produc

37、t qualification See EN 4400-3 Qualification programme to be agreed between manufacturer and purchaser. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for Resale No reproduction or networking permitted without license from IHS -,-,-