AECMA PREN 2091-1996 Aerospace Series Aluminium Alloy AL-P2024-T4 Clad Sheet and Strip for Stretch Forming 0 3 mm Less Than or Equal to a Less Than or Equal to 6 mm Edition EN《 航空航.pdf

1、Latest date for receipt of comments 28 Februarv 1997 Project No 9 4128 ACE/24 Our ref Technical Camittee ACE/24 Date 9 December I996 Wrought and cast aluminium and magnesium alloys for aerospace DRAFI? EROPEAN SANDm - AEROSPACE SERIES ALUMINIUIM AL-P2024-T4 CLAD sI“ AND STRIP FOR ,!TEEEH 3DRMING O,

2、3m o( series aluminium alloys *) Aerospace series - Metallic materials - General organization of standardization - Links between types of EN standards and their use 2, Aerospace series - Aluminium and aluminium alloy wrought products Technical specification - Part 3 : Sheet, strip and formed profile

3、s Aerospace series - Metallic materials - Rules for drafting and presentation of material standards - Part 2 : Specific rules for aluminium, aluminium alloys and magnesium alloys *) 1) In preparation at the date of publication of this standard 2) Published as AECMA Prectandard at the date of publica

4、tion of this standard 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-,-,-P 6.1 Delivery condition Page 4 prEN 2091 : 1996 T4 Method of melting - Form Cl

5、ad sheet and strip Method of production Rolled Limit dimension(s) mm 0,3 1 a 1 6 Technical specification EN 4400-3 I Heat treatment 490 “C 1 45 500 “CI WQ O1 40 “C + O= ambient It 2 5 d Characteristics rest sample(s) See EN 4400-3 rest piece(s) See EN 4400-3 I I I Temperature 8 “C Ambient Ambient Am

6、bient Ambient Proof stress IRp0,21 MPa I 2 240 2 240 I 2 250 2 250 Strength 2 390 2 400 2 420 2 420 Elongation A% A50 mm A50mm18 *50mm2* mm 18 Reduction of area Z % - - - - Hardness - - - - Shear strength Rc MPa Bending k- 1,5;a=18Oo 1 2;a=180 ) 23; a= 180“ $1 3,5;a=180 1 Impact strength - - - - - 1

7、 Temperature I 6 I “C I - Time h - MPa Stress - C Elongation a% - Oa 1 Rupture stress I 1 MPa 1 .I I Elongation A Oh at rupture Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted with

8、out license from IHS-,-,-ntergranular corrosion External defects liffusion in the cladding Cladding chemical :om position % Marking inspection Dimensional inspection Notes Typical uses Page 5 prEN 2091 : 1996 1 EN 2716 1 EN 2007 2 The “capability clause“ applies. Thickness (mm) Maximum diffusion of

9、Cu in the cladding (Oh of the actual cladding thickness) I 0,3 5 a 5 0,6 I To be agreed between purchaser and manufacturer I I 0,8 a 1,2 I50 1,2 a 1,6 140 1,6 a 52,5 I I 50 2,5 a S4,O I 140 4,O a 6,0 I 120 - - - - - - - - - 99,50 min. max. 0,25 0,40 0,05 0,05 0,05 0,07 0,05 0,03 - - or as an alterna

10、tive, if agreed between purchaser and manufacturer See EN 4400-3 See EN 4400-3 1) The “capability clause“ applies. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license f

11、rom IHS-,-,-Page 6 prEN 2091 : 1996 roduct qualification See EN 4400-3 !ualification programme to be agreed between manufacturer and purchaser 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-,-,-