1、STD.AECMA PREN 3337-ENGL 1798 LIIL23Ll 00L53b2 77T Edition approved for publication 1998-1 2-31 AECMA STANDARD NORME AECMA AECMA NORM Comments should be sent within six months after the date of publication to AECMA Gulledelle 94 B-I 200 BRUXELLES prEN 3339 Edition P 2 December 1998 ICs: PUBLISHED BY
2、 THE EUROPEAN ASSOCIATION F AEROSPACE INDUSTRIES (AECMA) Gulledelle 94 - 8-1200 BRUXELLES - Tel. (+32) 2 775 81 10 - Fax. (+32) 2 775 81 11 Supersedes issue P 1 October 1988 Descriptors: ENGLISH VERSION Aerospace series Aluminium alloy AL-P7010- T76 Die forgings a I 200 mm Srie arospatiale Alliage d
3、aluminium AL-P7010- T76 Pices matrices a I 200 mm Luft- und Raumfahrt Aluminiumlegierung AL-P701 0- i76 Gesen kschmiedestcke a I 200 mm This %Aerospace Series“ Prestandard has been drawn up under the responsibility of AECMA (The European Association of Aerospace Industries). It is published on green
4、 paper for the needs of AECMA-Members. It has been technically approved by the experts of the concerned Technical Committee following comment by the Member countries. Subsequent to the publication of this Prestandard, the technical content shall not be changed to an extent that interchangeability is
5、 affected, physically or functionally, without re-identification of the standard. After examination and signature of the AECMA Standard Checking Centre (NPS) and formal agreement of the Official Services of the Member countries it will be submitted as a draft European Standard to CEN (European Commi
6、ttee for Standardization) for formal vote. Nota -Extra copies can be supplied by B.N.A.E. - Technopolis 54 - 199, rue Jean-Jacques Rousseau - 92138 ISSY-LES-MOULINEAUX CEDEX C5 Chairman Mr Evetts STD-AECMA PREN 3337-ENGL 1998 1Ol123LL 00L53b3 bOb M Page 3 prEN 3339: 1998 O In trod ucti on This stand
7、ard 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. I Scope This standard specifies the requirements relating to: Aluminium alloy AL-P701
8、0- T76 Die forgings a I 200 mm for aerospace applications. 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 dat
9、ed references, subsequent amendments to or revisions of any 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 2082-3 Aerospace series - Aluminium alloy forging stock
10、 and forgings - Technical specification - Part 3: Pre-production and production forgings EN 4258 Aerospace series - Metallic materials - General organization of standardization - Links between types of EN standards and their use EN 4287 Aerospace series - Aluminium alloy AL-P7010 - Forging stock 1)
11、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 2) EN 4527 Aerospace series - Test methods for aluminium and aluminium alloy products - Determining susceptibility
12、 to stress-corrosion cracking 1) 1) Published as AECMA Prestandard at the date of publication of this standard Previous page is blaiik 4.2 I Method of DrOdUctiOn I 4.3 5 Forged from forging stock EN 4287 Limit dimension(s) mm a 1200 Technical specification EN 2082-3 6.1 I Delivery condition 176 Il I
13、 6.2 Heat treatment 470 OC 5 es 480 OC I wo e 80 OC 1) + I10 “C e 120 “C I8 h t 24 h 2) + 170 “C 6% 180 “C I6 h t 16 h 2) Delivery condition code U 7 18.1 I Test sample(s) I See EN 2082-3 I Use condition 176 Heat treatment Delivery condition aZ 8.3 I 9 I Dimensions concerned I mm I 5 80 I 80as100 I
14、100as120 I 120ai;160 I 1608200 I Test piece) See EN 2082-3 Heat treatment Use condition I 17 I Hardness 18 19 I Shear strength R, MPa - Bending k- - 20 21 Impact strength - ITemperature I 6I0c - I I _ _ - h - oa MPa 24 C Elongation a% - I 27 I Notes (see line 98) I I - _ STD-AECMA PREN 3337-ENGL 197
15、8 m LOI12311 00153b5 487 m - 3 ilectrical conductivity See EN 2082-3 Measurement on the surface of the sample from which tensile specimens are taken. Stress corrosion 1 3acture toughness :KIC) y 21,O MSlm Not acceptable EN 4527 External defects 3 4 Macrostructure ar25rnm ST Internal defects - 7 - -
16、Batch uniformity See EN 2082-3 Dimensions L-T T-L s-L (mm) MPa & MPa 6 MPa & a 100 2 25 2 24 2 22 100 a 2 150 2 25 2 22 2 21 150 a I 200 2 25 2 21 2 20 See EN 2082-3 See EN 2082-3 Marking inspection Electrical conductivity _ _ Dimensional inspection See EN 2082-3 Notes 6 I 20 per product Typical use
17、 A 5 30 per batch 71 y 2 22,O MSh I Acceptable I I 21 ,O MS/m 5 y 22,O MSlm Acceptable if Rp0,2 L 5 Rp0,2 L min. 3) + 70 MPa or if stress corrosion test is acceptable The “capability clause“ applies or as per line 32 I 61 O = 175 MPa 71 t 2 20d I -I See EN 2082-3 or See EN 2082-3 See EN 2082-3 1) Th
18、e use of quench additives or higher quenchant temperature shall be subject to agreement between manufacturer and purchaser. 2) Artificial ageing may be carried out using the following alternative single stage method : heating to a temperature of 170 “C 5 6s 180 “C at a rate not exceeding 20 “C / h and soaking at this temperature for 6 h c t : 16 h. 3) If L specimen cannot be cut, LT specimen shall be used by agreement between manufacturer and purchaser.
