1、AECMA STANDARD NORME AECMA AECMA NORM Edition approved for publication 15 May 2003 prEN 2511 Edition P 2 May 2003 Comments should be sent within six months after the date of publication to AECMA-STAN ICs: Descriptors: ENGLISH VERSION Supersedes edition P 1 October 1998 Aerospace series Al um i ni um
2、 alloy AL-P7075- T7351 Plate 6 mm a 100 mm Srie arospatiale Alliage daluminium AL-P7075- T7351 Tles paisses 6 mm ai 100 mm Luft- und Raumfahrt Aluminiumlegierung AL-P7075- T7351 Platten 6 mm ai 100 mm This “Aerospace Series“ Prestandard has been drawn up under the responsibility of AECMA-STAN (The E
3、uropean Association of Aerospace Industries - Standardization). It is published on green paper 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 t
4、echnical content shall not be changed to an extent that interchangeability is affected, 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 to CEN (European C
5、ommittee for Standardization) for formal vote. Metallic Material Domain I I Copyright 2003 O by AECMA-STA1 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-
6、Page 2 prEN 251 1 : 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 ap
7、proval 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 251 1: 2003 O Introduction This standard is part of the series of E
8、N 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 relating to: Aluminium alloy AL-P7075- T7351 Plate 6 mm a 100 mm f
9、or aerospace application. 2 Normative references This European Standard incorporates by dated or undated refere ce provisia s from other publicatic S. These normative references are cited at the appropriate places in the text and the publications are listed hereafter. For dated references, subsequen
10、t 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 edition of the publication referred to applies. EN 4258, Aerospace series - Metallic materials - General organization of
11、standardization - Links between types of EN standards and their use EN 4400-1, Aerospace series - Aluminium and aluminium alloy wrought products - Technical specification - Part I: Plate 1) EN 4500-2, Aerospace series - Metallic materials - Rules for drafting and presentation of material standards -
12、 Part 2: Specific rules for aluminium, 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 AECMANot for ResaleNo reproductio
13、n or networking permitted without license from IHS-,-,-Page 4 prEN 251 1: 2003 5 4.2 I Method of production I Rolled Technical specification EN 4400-1 4.3 I Limit dimension(s) I mm I 6a100 6.1 Delivery condition W51 T7351 Heat treatment 460 OC e 500 OC I WQ e 40 OC 460 OC e 500 OC I WQ e 40 OC + 1,5
14、 % controlled stretched 3 % + 1,5 % controlled stretched 3 % + 100 “C 6% 135 “C I3 h t 24 h a + 155 “C 6% 175 “C I8 h t 30 h a 6.2 7 Delivery condition code W U Use condition T7351 T7351 Heat treatment Delivery condition + 100 “C 6% 135 “C I3 h t 24 h a + 155 “C 6% 175 “C I8 h t 30 h a Delivery cond
15、ition 8.1 8.2 Test sample(s) See EN 4400-1. Test piece(s) See EN 4400-1. I12 I ITemperature I 0 I “C I Ambient I Ambient I Ambient I 8.3 9 11 Il I Heat treatment Use condition. 123 a 25 Dimensions concerned mm 6 a 12,5 each face Direction of test piece L LT L LT L LT I ST 25 a 40 Thickness of claddi
16、ng on % - - - Proof stress Elongation Il I I I I I I I I I I Rp0,2 MPa 2 390 2 390 2 390 2 390 2390 2390 2360 R, MPa 2 480 2 480 2 480 2 480 2470 2470 2440 A % Ammm27 Ammm 2 7 27 27 26 26 233 I I 16 I I Reductionofarea I Z I % I - 9 11 Dimensions concerned mm 40 a 60 60 a 80 80 a 100 each face Direc
17、tion of test piece L I LT I ST LI LT I ST LI LT I ST Thickness of cladding on % - - - I12 I ITemperature I 0 I “C I Ambient I Ambient I Ambient I 14 15 16 17 - - 113 I I Proofstress I Rp,2 I MPal 2370 I 2370 I 2340 I 2350 I 2350 I 2330 I 2340 I 2340 I 2320 I T Strength R, MPa 2460 2460 2430 2440 244
18、0 2420 2430 2430 2410 Elongation A % 26 26 233 26 26 233 26 26 233 Reduction ofarea Z % - Hardness - Il I 19 20 21 Bending k- - Impact strength - I Temperature I eloc - I I 18 I Shear strength I R, I MPa I - :;:;stress Elongation at OR MPa - A % - Il I I I I I22 I ITime Ihl Il I I I I a, b I 27 I No
19、tes see line 98) 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-,-,-Page 5 prEN 251 1 : 2003 - ilectrical conductivity See EN 4400-1. Stress corrosion 7
20、 ixternal defects y 2 23,O MSlm Acceptable Acceptable if Rw:2 LT Rp0,2 min. LT + 85 MPa (see line 13) or if stress corrosion test results (see line 39) are acceptable. 22,O MSlm y 23,O MSlm nternal defects - 3atch uniformity y 22,O MSlm Not acceptable See EN 4400-1. Marking inspection 7 - Iimensiona
21、l inspection Votes t220d See EN 4400-1. rypical use - a Artificial ageing may be carried out using the following alternative single stage method: heating to a temperature of 155 “C I 81 175 “C at a rate not exceeding 20 “C I h and soaking at this temperature for 8 h I t I30 h. Or hD 2 4 if required
22、by the purchaser. 61 O = 75 % Rp0,2 min. LT -I See EN 4400-1. -I See EN 4400-1. See EN 4400-1. -I -I See EN 4400-1. -I Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without licen
23、se from IHS-,-,-100 See EN 4400-1. Qualification programme to be agreed between manufacturer and purchaser. Page 6 prEN 251 1: 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-,-,-
