1、 7 - d. - - ,. i.- . .- - -3 _- AECMA PREN2508 82 LOL23LL 0003368 b M - - A.E.C.M.A. STANDARD prEN2508 NORME A.E.C.M.A. Edition 1 June 1982 A.E.C.M.A. NORM ENGLISH VERSION ALUMINIUM ALLOY 5086-HI11 DRAWN TUBES FOR STRUCTURAL APPLICATIONS AERQSPACE SERTES ALLIAGE DALUMINIUM 5086-HI11 TUBES ET1 R ES P
2、OUR LUFT- UND RAUMFAHRT ALUMINIUM-LEGIERUNG 5086-HI 11 APPLICATIONS STRUCTURALES GEZOGENE ROHRE FR SERIE AEROSPATIALE KONSTR U KTI ONSZW ECKE This industrial standard for the aerospace sector has been drawn up under the responsibility of AECMA (Association Europenne des Constructeurs de Matriel Aros
3、patial), It is published on yell0 w paper in three equivalent versions (English, French, German). It will be submitted to CEN (European Committee for Standardization) as a draft European Standard. -_ Approved by The equivalent versions in French and German languages COMITE DE NORMALISATION can be su
4、pplied by E.N.A.E., 8, rue Moreau-Vauthier of A.E.C.M.A. 1981-08-14 92100 BOULOGNE-EILLANCOURT - FRANCE. 1 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
5、IHS-,-,-Si Fe Cu Mn Mg Cr Zn Ti - - - - - Q,20 3,5 0,05 0940 Op50 Oil0 097 4,5 0,25 0,25 O,I5 Others . each total - - 005 0,15 Chemical Composition Element min. AECMA PREN2508 82 LOL23LL 0003364 8 A. E .C.M .A. STAN DARD prEN2508 Page 3 ALUMINIUM ALLOY 5086-H111 Drawn tubes for structural applicatio
6、ns % I rnax. 2 1 Method of melting Form Wethod of production Limit dimensions Draw tube Wall thickness : 0,5 mm 6 a 6 3 mm EN2257 H111 - EN207C-1 dl and j.1 Acceptance standards j.2 Dimensional standards Zondition snd Heat treatment Delivery H111 :ondition snd Heat treatment Use Test piece Heat trea
7、tment Sampling Dimensions concerned . 0,5 s a 3 - Thickness of cladding on each face Direction of sample L Temperature Proof i th . I- Elongation Reduction of area Hardness Room temperature & 110 3 250 Full section . : t 18 Cut aut section : L 16 - A % - 70 (for information) Shear Strength RC k K _
8、Bending I rnpact ITernperature e OC t h Time aa a Sb Rupture Stress Elongation 1) iMPa=lN/mm 2 Notes In preparation. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license
9、 from IHS-,-,-AECMA PREN2508 82 W LOL23LL 0003370 4 prtN2508 Paqe 4 1 Flattening test Notes Typical usa 2 EN2002-10 2, ZG 3 a (if required by order) 2) fn preparation. t 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-,-,-
