1、AECMA STANDARD NORME AECMA AECMA NORM Edition approved for publication 31 March 2003 prEN 3333 Edition P 3 March 2003 Comments should be sent within six months after the date of publication to AECMA-STAN ICs: Descriptors: ENGLISH VERSION Supersedes edition P 2 February 1999 Aerospace series Al um i
2、ni um alloy AL-P7475- T762 Sheet and strip 0,6 mm las 6 mm Srie arospatiale Alliage daluminium AL-P7475- T762 Tles et bandes 0,6 mm I ai 6 mm Luft- und Raumfahrt Aluminiumlegierung AL-P7475- T762 Bleche und Bnder 0,6 mm I a I 6 mm This “Aerospace Series“ Prestandard has been drawn up under the respo
3、nsibility of AECMA-STAN (The European 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 publicat
4、ion 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. After examination and review by users and formal agreement of AECMA-STAN it will be submitted as a draft Europe
5、an Standard to CEN (European Committee 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 permi
6、tted without license from IHS-,-,-Page 2 prEN 3333: 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, t
7、his standard has received approval 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 3333: 2003 O Introduction This standard
8、 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 relating to: Aluminium alloy AL-P7475-
9、T762 Sheet and strip 0,6 mm a6 mm for 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 hereaft
10、er. 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 edition of the publication referred to applies. EN 4258, Aerospace series - Metallic m
11、aterials - General organization of standardization - Links between types of EN standards and their use EN 4400-2, Aerospace series - Aluminium and aluminium alloy wrought products - Technical specification - Part 2: Sheet and strip 1) EN 4500-2, Aerospace series - Metallic materials - Rules for draf
12、ting 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 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under
13、license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1 - 2 Material designation Aluminium alloy AL-P7475- si - 0,IO Others Each Total Fe Cu Mn Mg Cr Zn Ti AI - - 1,9 0,18 5,2 - - - 12 0,12 1,9 0,06 2,6 025 6,2 0,06 0,05 0,15 Base Form Method of product
14、ion Limit dimension(s) mm Technical specification Sheet and strip Rolled 0,6 a 6 EN 4400-2 Delivery condition F O T761 Ambient 137 137 144 248 262 268 hmm 2 10 Ambient 2 410 2 490 A50mm27 A50mm 2 9 “C h - - Chemical composition % I Element I min. I max. I - Method of melting I Heat treatment + 460 “
15、C O 485 “Ca I WQ O 40 “C + 115 “C 6% 125 “C I 3 h t 6 h + 158 “C 6% 178 “C I 14 h t 70 h I P I A I F I Delivery condition code I T762 I Use condition Deliverv condition +460 “C &485 “C b/WQ Os40 “C + 115 OC 6% 125 “CI3 ht6 h + 158 “C 6% 178 “C I 14 h t 70 h Heat treatment Characteristics - 3.1 See E
16、N 4400-2. I Test sample(s) See EN 4400-2. 3.2 I Test piece(s) I Use condition: T762 I Delivery condition: O I 3.3 I Heat treatment Dimensions concerned mm 0,6 I a I 1,6 I1,6 a I2,3 12,3 a I3,2 I 3,2 a I6 I 0,6 a 1,0 I 1,0 a 6 Thickness of cladding on each face % 11 I Direction of test piece I LT I L
17、T 12 13 14 15 - - - “C MPa MPa % - - - Temperature Proof stress Strength Elongation T - I I6 I I Reductionofarea I Z I % I - - I - I 17 I Hardness 18 I Shearstrength I R, I MPa I I 19 I Bending Ikl- 20 21 22 23 24 - - - - Ir - n pact strength Time Stress Elongation MPa I - C I Rupture stress I Elong
18、ation at ru Dtu re MPa I - 25 26 - a, b, c 27 I Notes (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 3333: 2003 - ilectric
19、al conductivity See EN 4400-2. 3acture toughness (KJ y 2 22,7 MSlm 22,0 MSlm y 22,7 MSlm ixternal defects Acceptable Acceptable if R,Z 470 MPa and/or if exfoliation corrosion tests meet the acceptance criteria: see line 49. Votch/yield ratio (RJRp0,2) - ixfoliation corrosion y 22,O MSlm Not acceptab
20、le See EN 4400-2. Marking inspection 7 Iimensional inspection T-L Dimensions (mm) MPa 1,0 a 3,2 2 95 Votes - rypical use 3,2 a 6 2 85 See EN 4400-2. 7 51 T762 -I See EN 4400-2. -I See EN 4400-2. The “capability clause“ shall apply unless testing is required to determine acceptance: see line 32. In t
21、hat case, frequency of testing shall be agreed between the manufacturer and purchaser. 71 Exfoliation corrosion shall not be greater than that of grade EB. - -I See EN 4400-2. -I See EN 4400-2. a This temperature range may be extended to 525 “C (particularly to facilitate the use of a continuous sol
22、ution heat treatment furnace) with the proviso that appropriate prior homogenisation heat treatments are applied to the rolling ingot and/or sheetlstrip to avoid incipient melting (overheating). It is recommended that material in the O delivery condition shall not be formed, stretched andlor straigh
23、tened in excess of approximately 3 % before solution heat treatment, in order to avoid the development of coarse grain. Due to possible problems of test piece distortion after solution heat treatment and quenching by the purchaser, fracture toughness tests may be carried out on material in the T761
24、condition, in which case tensile tests shall be carried out in both T761 and T762 tempers. However, although T761 and T762 properties should be similar, it should be recognised that the latter may be affected by the purchasers processing and practices and, accordingly, T762 properties cannot be guar
25、anteed by the manufacturer. -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-,-,-100 See EN 4400-2. Qualification programme to be agreed between manufacturer and purchaser. Page 6 prEN 3333: 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-,-,-
