AECMA PREN 2387-1981 Aluminium Alloy 2014 A-T6 Tubes for Structures 0 6 Less Than or Equal to a Less Than or Equal to 12 5 mm Aerospace Series Edition 1《航空和航天系列铝合金2014 A-T6结构用管材a≥6.pdf

《AECMA PREN 2387-1981 Aluminium Alloy 2014 A-T6 Tubes for Structures 0 6 Less Than or Equal to a Less Than or Equal to 12 5 mm Aerospace Series Edition 1《航空和航天系列铝合金2014 A-T6结构用管材a≥6.pdf》由会员分享，可在线阅读，更多相关《AECMA PREN 2387-1981 Aluminium Alloy 2014 A-T6 Tubes for Structures 0 6 Less Than or Equal to a Less Than or Equal to 12 5 mm Aerospace Series Edition 1《航空和航天系列铝合金2014 A-T6结构用管材a≥6.pdf（3页珍藏版）》请在麦多课文档分享上搜索。

1、A.E.C.M.A. STANDARD NORME A.E.C.M.A. A. E.C.M.A. NORM pcEN2387 Edition 1 Septembw 1981 ENGLISH VERSION ALUMINIUM ALLOY 2014 A-T6 TUBES FOR STRUCTURES 0,6 mm a 12,5 mm AEROSPACE SERIES ALLIAGE DALUMINIUM 2014 A-T6 TUBES POUR STRUCTURES 0,6 mm a 12,5 rnm LUFT-UND RAUMFAHRT ALUMINI UM-LEG IERUNG 201 4

2、A-T6 SERIE AEROSPATIALE KONSTRUKTIONSROHRE 0,6 rnm a 12,5 mm This industrial standard for the aerospace sector has been drawn up under the responsibility of AECMA (Association Europenne des Constructeurs de Matriel Arospatial), It is published on yell0 w paper in three equiwfent Versions (English, F

3、rench, German). It will be submitted to CEN (European Committee for Standardization) as a draft European Standard. The equivalent venions in French and German languages COMITI! DE NORMALISATION can be supplied by B.N.A.E., 8, rue . Moreau-Vauthier 92100 BOULOGNE-BILLANCOURT - FRANCE. I Approved by o

4、f A.E.C.M.A. 1980-11-21 I 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-,-,-AECMA PREN237 1 U 1012311 0003089 3 U ., .- - A.E.C.M.A. STANDARD prEN2387

5、Page 3 - 1 ALUMINIUM ALLOY 2014 A-T6 Tube6 for structures 0,6 mm g a 4 12,5 mm Element Chemical _ Composition min. max. % 2 - 3 1 Method of melting 4 Form Method of production Limit dimensions - - 6 - 7 Dimensions Iconcerned . I a I mm 5.1 Acceptance standards 5.2 Dinensional standards Condition and

6、 Heat ?raatment Delivery Condition and Heat treatment Use . Thickness of -1 cladding on each face I % 11 Direction of sample 8 -I I Test piece Heat treatment Sampling Proof Stress 3 14 Strength - 1 u - 0,6 4 a Q 1,2 1,2 a s 6 Etongation 6 4 a L 12,5 17 Hardness -I 18 Shear Strength 370 - 3 370 19 IB

7、ending 8 370 20 21 22 - - impact Time Rupture Elangatlon 27 INotw -I- * Drawn tube Wall thickness: 0,6 mm 1 a d 12,5 mm E1207t. sock h t 20 h or 175 * 5OC/ 5 h t 12 h Qr 185 f 5OC/ 3 h C t C 6 h Delivery condition L I L I L - 145 (for information) - I l t I *) lMPa=1N/mm2 i) In preparation. 21, 31,

8、see line 98. - -*= 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-,-,-I AECMA PREN2387 81 m LOL2311 0003085 5 m prEN2387 Page 4 i Flattening test Re sidua

9、l stress test Uotm 2 3 4 EN2002-10 z Q 3 a (If required by order) EN2004-6 I) 1) in preparation 2) Full section. 3) Cut-out section, 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-,-,-