1、AECMA STANDARD NORME AECMA AECMA NORM Edition approved for publication 31 March 2003 prEN 3332 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 Clad sheet and strip 1,0 mm I al 6 mm Srie arospatiale Alliage daluminium AL-P7475- T762 Tles et bandes plaques 1,0 mm I a16 mm Luft- und Raumfahrt Aluminiumlegierung AL-P7475- T762 Bleche und Bnder, plattiert 1,0 mm ia16 mm This “Aerospace Series“ Prestandard has been dra
3、wn up under the responsibility 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. Subse
4、quent 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. After examination and review by users and formal agreement of AECMA-STAN it will be submit
5、ted as a draft European 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 reproductio
6、n or networking permitted without license from IHS-,-,-Page 2 prEN 0000: 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 Gene
7、ral Process Manual, this 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 3332: 2003 O Intro
8、duction 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 relating to: Alumi
9、nium alloy AL-P7475- T762 Clad sheet and strip 1,0 mm a 6 mm for aerospace application. 2 Normative references This European 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 publ
10、ications 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 references the latest edition of the publication referred to applies. EN 4258, Ae
11、rospace series - Metallic materials - 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
12、 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 Copyright Association Europeene des Constructeurs de Materiel Aerospa
13、tial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1 - 2 Material designation Aluminium alloy AL-P7475- Chemical composition % 12 1,9 Si I Fe - 1,9 0,18 5,2 - - - 0,06 2,6 0,25 6,2 0,06 0,05 0,15 Base Cu I Mn I Mg I Cr I Zn
14、 I Ti l+l AI Each Total Form Method of production Limit dimension(s) mm Technical specification Element Clad sheet and strip Rolled 1,0 a 6 EN 4400-2 I Delivery condition I min. F O T761 -I- I max. 0,lO I 0,12 I I I I I I I I I - Method of melting I Heat treatment + 460 “C O 485 “Ca I WQ O 40 “C + 1
15、15 “C O 125 “C I3 h t 6 h + 158 “C O 178 “CI 14 h t 70 h I P I A I F I Delivery condition code I T762 I Use condition Delivery condition +460 “C Os485 “C bIWQ Os40 “C + 115 OC O 125 “CI3 ht6 h Heat treatment + 158 “C O 178 “C I 14 h t 70 h Characteristics - 3.1 See EN 4400-2. I Test sample(s) See EN
16、 4400-2. 3.2 I Test piece(s) I 3.3 I Heat treatment I Delivery condition: O I Use condition: T762 Dimensions concerned mm Thickness of cladding on each face % 11 I Direction of test piece I LT I LT 12 13 14 15 - - - “C MPa MPa % - - - Temperature Proof stress Strength Elongation Ambient Ambient 137
17、137 144 2 370 2 380 2 390 248 262 268 2 450 2 460 2 470 hmm 2 10 hmm 2 9 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 - Il:a=180“ I k I 20 21 22 23 24 25 26 27 - - - - - - - Im pact strength Time Stress Elongation Rupture stress I Elon
18、gation at ru Dtu re - I MPa I - Notes (see line 98) a, b, c 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 3332: 2003 ilectrical conductiv
19、ity 3acture toughness (KJ ixternal defects Votch/yield ratio (RJRp0,2) ixfoliation corrosion 2ladding chemical mmposition % Marking inspection Iimensional inspection Votes rypical use See EN 4400-2. y 2 22,7 MSlm Acceptable 22,0 MSlm y 22,7 MSlm Acceptable if R,z R,z min. LT + 60 MPa and/or if exfol
20、iation corrosion tests meet the acceptance criteria: see line 49. y 22,O MSlm Not acceptable See EN 4400-2. T762 T-L Dimensions (mm) MPa 1,0 a 3,2 2 95 3,2 a 6 2 85 See EN 4400-2. See EN 4400-2. See EN 4400-2. The “capability clause“ shall apply unless testing is required to determine acceptance: se
21、e line 32. In that case, frequency of testing shall be agreed between the manufacturer and purchaser. Exfoliation corrosion shall not be greater than that of grade EB See EN 4400-2. Material designation Aluminium alloy AL-P7072- Element I Si+Fe I Cu I Mn I Mg I Zn 1-1 AI Each Total max. 0,7 0,lO 0,l
22、O 0,lO 13 0,05 0,15 See EN 4400-2. See EN 4400-2. a This temperature range may be extended to 525 “C (particularly to facilitate the use of a continuous solution heat treatment furnace) with the proviso that appropriate prior homogenisation heat treatments are applied to the rolling ingot and/or she
23、etlstrip to avoid incipient melting (overheating). It is recommended that material in the O delivery condition shall not be formed, stretched andlor straightened in excess of approximately 3 % before solution heat treatment, in order to avoid the development of coarse grain. Due to possible problems
24、 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 condition, in which case tensile tests shall be carried out in both T761 and T762 tempers. However, although T761 and T762 properties should be
25、similar, it should be recognised that the latter may be affected by the purchasers processing and practices and, accordingly, T762 properties cannot be guaranteed by the manufacturer. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANo
26、t 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 3332: 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-,-,-
