1、STD-AECMA PREN 2b70-ENGL 1778 m LO22311 0015343 818 m Edition approved for publication AECMA STANDARD NORME AECMA AECMA NORM C5 Chairman Comments should be sent within six months after the date of Publication to prEN 2690 Edition P 1 December 1998 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE I
2、NDUSTRIES (AECMA) Gulledelle 94 - 8-1200 BRUXELLES - Tel. (+32) 2 775 81 10 - Fax. (+32) 2 775 81 11 ICs: Descriptors: ENGLISH VERSION Aerospace series Al um i ni um alloy AL-P7050- T7452 Hand forgings a I 200 mm Srie arospatiale Alliage daluminium AL-P7050- Ti452 Pices forges a I 200 mm Luft- und R
3、aumfahrt Aluminiumlegierung AL-P7050- T7452 Freiformschmiedestcke 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 paper for the needs of AECMA-Members. It has been technica
4、lly 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 affected, physically or functionally, without re-identific
5、ation 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 Committee for Standardization) for formal vote. 1998-1 2-31 AECM
6、A Gulledelle 94 Mr Evetts 8-1200 BRUXELLES aecma 1998 STDDAECMA PREN 2b70-ENGL 2778 U LOL232L 0025344 754 Page 3 prEN 2690: 1998 O In trod uc ti on This standard is part of the series of EN metallic material standards for aerospace applications The general organization of this series is described in
7、 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-P7050- T7452 Hand forgings a I 200 mm for aerospace applications. 2 Normative references This Standard incorporates by dated or undated reference p
8、rovisions from other publications. These normative 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 Standard only when incorporated in it by ame
9、ndment or revision. For undated references the latest edition of the publication referred to applies. EN 2082-3 Aerospace series - Aluminium alloy forging stock and forgings - Technical specification - Part 3: Pre-production and production forgings EN 4258 Aerospace series - Metallic materials - Gen
10、eral organization of standardization - Links between types of EN standards and their use EN 4288 Aerospace series - Aluminium alloy AL-P7050- - Forging stock 1) EN 4500-2 Aerospace series - Metallic materials - Rules for drafting and presentation of material standards - Part 2: Specific rules for al
11、uminium, aluminium alloys and magnesium alloys 1) EN 4527 Aerospace series - Test methods for aluminium and aluminium alloy products - Determining susceptibility to stress-corrosion cracking 1) 1) Published as AECMA Prestandard at the date of publication of this standard Previous page is blank STD4E
12、CMA PREN 2bSD-ENGL 1998 = LOL23LL OOL53Li5 b90 - Page 4 prEN 2690: 1998 4.2 4.3 14.1 I Form Method of production Limit dimension(s) mm a c 200 Forged from forging stock EN 4288 I Hand forainss 16.2 I Deliverv condition code I 5 I Technical soecification Delivery condition Heat treatment I T7452 470
13、“C c BI 485 “C I WQ 82 80 “C + I % I cold cornpressed I 5 % + 105 “C 4 85125 “C I 3 h I t I24 h + 172 “C 2 82 182 “C I 6 h I; t I 16 h EN 2082-3 1 Use condition Heat treatment 6.1 U452 Delivery condition 13 Proof stress Rp0,2 MPa 2435 2420 2400 2425 2415 2380 2420 2405 2380 2415 2400 2370 14 T Stren
14、gth Rm MPa 2495 2490 2475 2495 2480 2460 2490 2480 2460 2480 2475 2455 15 Elongation A % 28 25 24 28 25 24 28 25 24 28 24 23 (continued) - - 9 11 12 I Dimensions concerned mm 125 a 5 150 150 a I 175 175 a 2 200 on each face Direction of test piece L LT ST L LT ST L LT I ST - - - Thickness of claddin
15、g % Temperature I eloc Ambient Ambient Ambient U Proof stress Elongation I %0,2 MPa 2405 2385 2365 2400 2370 2350 2390 2360 2345 Rm MPa 2475 2470 2455 2470 2460 2450 2460 2455 2440 A % 28 24 23 28 24 23 28 24 23 17 16 17 Reduction ofarea Z I - Hardness - Characteristics 18.1 I Test sample(s) I See E
16、N 2082-3 I 18 19 18.2 I Test piece) I Shear strength R, MPa - ending k- - See EN 2082-3 I 20 21 Impact strength - I Temperature I e IT - ua 24 C Elonaation - h MPa - a% - 25 Rupturestress UR MPa - 26 Elongation at A % - - NPtUR 27 Notes (see line 98) i) I I Page 5 prEN 2690: 1998 y 2 23,O MS/m Elect
17、rical conductivity Acceptable Stress corrosion 75a 100 100 a c 200 Fracture toughness (KI c) 2 28 2 25 2 21 2 27 2 24 2 21. External defects Electrical conductivity Macrostructure See EN 2082-3 Internal defects Hardness Batch uniformity 155 (Typical value) HB 6 5 20 per product A i 30 per batch Mark
18、ing inspection Dimensional inspection Notes Typical use 22,O MS/m i y 23,O MS/m Acceptable if Rp9,2 LT c Rp0,2 LT min. + 70 MPa 2) or if stress corrosion test is acceptable y 22,O MSlm I Not acceptable EN 4527 The “capability clause“ applies or as per line 32 ST o = 240 MPa t 2 20d See EN 2082-3 Dim
19、ensions L-T T-L s-L (mm) 1 MPaG 1 MPaL 1 MPaL a c 75 I 2 29 I 2 26 I 2 21 See EN 2082-3 See EN 2082-3 See EN 2082-3 See EN 2082-3 See EN 2082-3 1) The use of quench additives or higher quenchant temperature shall be subject tc agreement between manufacturer and purchaser. 2) If LT specimen cannot be cut, L specimen shall be used by agreement betweer. manufacturer and purchaser. - Page 6 prEN 2690: 1998 Product qualification - I Qualification programme to be agreed between manufacturer and purchaser.
