ASD-STAN PREN 3983-2000 Aerospace Series Alumunium Aloy AL-P7050-T7651 Plate 6mm a Greater Than or Equal to 160 mm (Edition P 2 Supersedes Edition P 1 June 1995)《航空航天系列 铝合金AL-P705.pdf

1、STD-AECMA PREN 3983-ENGL 2000 m 1012311 00184b7 904 Nota - Extra copies can be supplied by B.N.A.E. - Technopolis 54 - 199, rue JeanJacques Rousseau - 92138 ISSY-LES-MOULINEAUX CEDEX Comments should be sent within six months after the date of publication to 2000-06-30 AECMA Mr Evetts Gulledelle 94 E

2、dition approved for publication C5 Chairman 8-1200 BRUXELLES aecma 20t AECMA STANDARD NORME AECMA AECMA NORM prEN 3983 Edition P 2 June 2000 ICs: Descriptors: PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES (AECMA) Gulledelle 94 - 8-1200 BRUXELLES - Tel. (+32) 2 775 81 10 - Fax. (+32)

3、2 775 81 11 Supersedes edition P 1 June 1995 ENGLISH VERSION Aerospace series Aluminium alloy AL-P7050- T7651 Plate 6 mm a I 160 mm Srie arospatiale Alliage daluminium AL-P7050- T7651 Tles paisses 6 mm a I 160 mm Luft- und Raumfahrt Aluminiumlegierung AL-P7050- T7651 Platten 6 mm a I 160 mm This “Ae

4、rospace Series“ Prestandard has been drawn up under the responsibility of AECMA (The European Association of Aerospace industries). It is published on green paper for the needs of AECMA- Members. It has been technically approved by the experts of the concerned Technical Committee following comment b

5、y the Member countries. Subsequent to the publication of this Prestandard, the technical content shall not be changed to an extent that interchangeability is affected, physically or functionally, without re-identification of the standard. Affer examination and signature of the AECMA Standard Checkin

6、g Centre (NPS) and formal agreement of the Officiai Services of the Member countries it will be submitted as a draft European Standard to CEN (European Commiffee for Standardization) for formal vote. COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handl

7、ing ServicesSTD-AECMA PREN 3983-ENGL 2000 10123LL 00189b8 840 page3 prEN 3983: 2000 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 acc

8、ordance with EN 4500-2. I Scope This standard specifies the requirements relating to: Aluminium alloy AL-P7050- T7651 Plate 6 mm ai 160 mm for aerospace applications. 2 Normative references This European Standard incorporates by dated or undated reference provisions from other publications. These no

9、rmative 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 undated re

10、ferences 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 1) EN 4400-1 Aerospace series - Aluminium and aluminium alloy wrought products - Technical s

11、pecification - Part 1: Plate 1) 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) 1) Published as AECMA Prestandard at the date of publication of this standard -

12、 COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling Services4.1 1.2 t.3 5 I Technical specification I EN 4400-1 I Form Plate Method of production Rolled Limit dimension(s) mm 6a1160 Delivery condition Heat treatment W5 1 Ti65 1 OCIICIWQ s40 + 1,5

13、% I controlled stretched 3 % + e= ambient 470 “C s 81 485 “C I WQ 81 40 “C + 1,5 % 5 controlled stretched s 3 % + 115 “C e 125 “C I4 h s t 2 24 h a + 157 “C I 0s 175 “C I8 h I t520 h a Delivery condition code Use condition Heat treatment W U T765 1 T7651 Delivery condition Delivery condition + 115 “

14、C I 6% 125 “C 14 h t s 24 h a + 157 “C I 6% 175 “C 18 h I t I 20 h a 8.1 Test sample(s) 8.2 Test piece(s) ITemperature 1 e 1 “C 1 Ambient I Ambient I Ambient I See EN 4400-1 See EN 4400-1 I I Reduction of areal 2 I % I - 8.3 9 Heat treatment Use condition Dimensions concerned I mm 6 i a I 12,5 12,5

15、a I 50 50 a s 75 I1 I Thickness of cladding % - - - on each face Direction of test piece L LT L LT LI LT 1 ST 17 1 Hardness - I 18 I Shear strength I R, IMPal - Proof stress Strength Elongation I 19 I Bending R, MPa 2 455 2 455 2 455 2 455 2455 2455 2415 A % A50mm29 Afiomm28 29 28 28 2 7 223 R, MPa

16、2525 2 525 t 525 t 525 2525 2525 2485 I20 1 ImpaGstrenqth I 11 I Thickness of cladding % - - - on each face Direction of test piece LI LT I ST LI LT I ST LI LT I ST 23 ;rneperature I e C - h - Stress I sa MPa - M Elongation a% - Rupture stress mR MPa - I l Elongation at A % rupture Notes (see line 9

17、8) - abcd COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling Services STD.AECMA PREN 373-ENGL 2000 E LOL23LL 0038470 477 9 Page 5 - - Electrical conductivity See EN 4400-1 Stress corrosion 7 Fracture toughness (Ki c) y 2 22,5 MSlm Acceptable I 213

18、 MSlrn 5 y 223 MSlm Acceptable if Rp0,2 LT 5 Rp0,2 min. LT + 70 MPa or if stress corrosion test is acceptable. Not acceptable 7 21,5 MSlm See EN 4400-1 ixternal defects ? 5 lotch/yield ratio e/Rp0,2 The “capability clause“ applies o=175MPa Ixfoliation corrosion 7 nternai defects 3atch uniformity Dim

19、ensions LT TL SL (mm) MPa fi MPa fi MPa fi 25as 50 2 28 t 26 - 50as 75 2 26 t 25 t 22 75a5 100 t 26 t 24 2 22 Marking inspection 100 a I 125 125 a I 160 Dimensional inspection 2 25 2 24 t 22 t 25 2 23 2 22 Notes - - Typical use See EN 4400-1 See EN 4400-1 - See EN 4400-1 I 7 Exfoliation corrosion sh

20、all not be greater than that of grade EB. - - See EN 4400-1 See EN 4400-1 71 t 2 20d -1 See EN 4400-1 1 See EN 4400-1 See EN 4400-1 a Artificial ageing may be carried out using the following alternative single stage method : heating to a temperature of 157 C I 81 175 “C at a rate not exceeding 20 “C

21、/h and soaking at this temperature for 8 h s t I 20 h. Alternatively AI t 3 if required by the purchaser. Alternatively & 2 2,5 if required by the purchaser. Alternatively & t 2 if required by the purchaser. b d COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Infor

22、mation Handling ServicesPage 6 prEN 3983: 2000 STD-AECMA PREN 3983-ENGL 2000 m LOL23LL 0018471 335 = Product qualification See EN 4400-1 lualification programme to be agreed between manufacturer and purchaser. COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling Services