1、-_ AECMA PREN2070-02 4 m LOL23LL 0007.583 m #- A. E .C .M .A. STAND AR D prE N 2070-2 NORME A.E.C.M.A. Edition 1 July 1984 A,E .C.M.A. NORM Approved by COMITE DE NORMALISATION of A.EAA. 1984I01-25 ENG J 7 The equivalent versions in French and German languages can be supplied by 6.NA.E 8, rue Moreau-
2、Vauthier 92100 BOULOGNE-BILLANCOURT - FRANCE. ERS ON Aluminium and aluminium alloy wrought products - Technical specification - Part 2 - Sheet, strip formed profiles and plate Aerospace series Demi-produits corroys en aluminium et alliages daluminium - Spcification technique - Partie 2 - Tles minces
3、, bandes profils plis et tles paisses Srie arospatiale Luft- und Raumfahrt Halbzeug aus Aluminium und Aluminium- Knetlegierungen - Technische Lieferbedingungen - Teil 2 - Bleche, Bnder, Bandprofile und Platten This industrial standard for the aerospace sector has been drawn up under the responsibili
4、ty of AECMA (Association Europenne des Constructeurs de Matriel Arospatial). It is published on yellow paper in three equivalent versions (English, French, German). It will be submitted to CEN (European Committee for Standardization) as a draft European Standrd. r Copyright Association Europeene des
5、 Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECMA PREN2070-02 84 l10123Ll 000758Y T m - prEN2070-2 Page 2 Con tents 4 5 9 10 11 12 13 14 a Scope and field of application References B
6、atch size Dimensions Internal defects for plate External defects Tensile test Bend test Batch uniformity C1 adding Fracture toughness and notch yield PO $2 ratio Re/R Stress corrosion testing tests for plate Special tests Marking 7 - _ 1 i Copyright Association Europeene des Constructeurs de Materie
7、l Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECMA PREN2070-02 4 LOL231L 0007585 I = prEN2070-2 Page 3 1 The present standard specifies the particular requirements for sheet, strip and formed profiles, clad o
8、r unclad, and plate machined or unmachined in aluminium and aluminium alloy. This standard shall be used in conjunction with EN2070-1. Scope and field of application 2 References EN2002-1, Test methods for metallic materials - Part 1 - Tensile tests at room temperature 9 EN2002-6, Test methods for m
9、etallic materials - Part 6 - Bend test 1) EN2002-7, Test methods for metallic materials - Part 7 - Hardness test 1) EN2002-16,Test methog7 for metallic materials - Part 16 - Penetrant flaw detection EN2002-22,Test methods for m allic materials - Part 22 - Plane strain fracture toughness testing fY E
10、N2002-23,Test methods for metallic materials Part 23 - Sharp notch tension testing with cylindrical specimens u EN2004-1, Test methods for alum ium and aluminium alloys - Part 1 - Electrical EN2004-2, Test methods for aluminium and aluminium alloys - Part 2 - Ultrasonic conductivity testing ir testi
11、ng of plates, forgings and extrusions EN2004-4, Test methods for a EN2004-5, Test methods for aluminium and aluminium alloys - Part 5 minium and aluminium alloys - Part 4 - Stress corrosion testing u cladding thickness and of the diffusion into the cladding -1 ontrol of EN2070-1, Aluminium and alumi
12、nium alloy wrought products - Technical specification - Part 1 - General requirements . 3 Batch size See table 1. i) In preparation O Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitte
13、d without license from IHS-,-,-AECMA PREN2070-02 84 LOL23LL0075Bb 3 W prEN2070-2 Page 4 TABLE 1 20 coils of strip or 1) 2) 2 1500 kg is permissable providing that the material is rolled to Fird thickness as on2 single plat 3000 kg is permissable for a seamless coil of strip. 4 Dimensions standard or
14、 drawing. Dimensions and tolerances shall conform to the relevant semi-finished product O The frequency of examination shall be sufficient to permit the manufacturer to certify compliance with the requirements. 5 Internal defects for plate Unless otherwise specified on the order or the inspection sc
15、hedule all plate over 12 mm in thickness shall be ultrasonically tested in accordance with EN2004-2 and shall satisfy the requirements of class A when the plates are delivered in the machined condition they shall have been tested before machining. 6 External defects 6.1 Surface quality of sheet, str
16、ip and formed profiles Unless otherwise specified on the order or the inspection schedule the surface quality shall be determined by visual examination in accordance with table 2. 0 The frequency of examination shall be sufficient to permit the manufacturer to certify compliance with the requirement
17、s of table 2. Penetrant flaw detection may be applied in accordance with EN2002-16, to verify the extent or existence of surface defects. 6.2 Surface quality and metal removal of machined plates 6.2.1 Surface finish shall conform to the roughness requirements specified on the order or inspection sch
18、edule. Plate shall be free from machining damage which may change the characteristics of the material, 6.2.2 The quantity of metal to be removed shall be agreed by the purchaser and the manufacturer. 6.2.3 Witness of the removed metal quantity shall be given by the following method (or any other equ
19、ivalent method) : - 10 mm diameter circles shall be hard stamped on the four edges of the plate, O tangental to the face(s) to be machined. On each edge, at least 3 circles shall be stamped, one at each end and at the middle of the length, - after machining the remainder of the circles give witness
20、of the,meta 1 removed. 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-,-,-O O 2 p 6 t- U m u i3 8- - .A O ic In WL u* m i- CX L U4 oc inal +u Wu- n no um
21、me 4- cw O +l “In WU W u) I I I C .rl 42 m .rl U A- ti. L cn O U ir z .- - U U # I m d .* u. o L Q -D aJ L O Li. -0 C 0. L U .rl U W d= Lo - 5: - m C U m U G - I N 4 dl w QI Ln - s 8 E N m e U W w e VI O L U in VI aJ L L, CB .n .A V L U C * ?-4 4 m L w m aJ L U O U m .rl n O u u e - l-, LLL WOIW ann
22、 r P C 2 L1 +J ln u VI W U x m .+_A N i- w 4 u) W 4J U c CJ m II III III II 4 m V L V U m II U 0 L O LI- U E L o u. II -cl c mc O cias WL ww cc (o3 Co m U c. r m VI a2 c .I= 3 O u aJ 2 u m m IL u rn W w U c W ir. 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-,-,-
