1、AECMA PREN2806 86 LOI12311 OOOL1209 2 9 A.E.C. M .A. STANDARD NORM E A.E,C. M .A. A.E.C.M.A. NORM prEN2806 Issue P 1 April 1986 DIT PAR LASSOCIATION EUROPEENNE DES CONSTRUCTEURS DE MATRIEL AROSPATIAL 88, boulevard Malesherbes, 75008 PARIS -TL. 45-63-82-85 ENGLISH VERSION Aerospace series Aluminium a
2、lloy 2024-T42 extruded section 1,2 Irectlon of sample - t % MPa - Room temperature 3 285 I + 310 I 5 300 Tempersturo Proof W Stress z Srrength w I- 2 Elongation Rm A Reduction of moa iardness ;hear Strength - i20 (for information) MPa 1 3 end i ng k K - O Tompersture Time Stress Elongation P UI w K
3、o - Ruptura stro1c Elongation ot tupture *) 1 MPa = 1 N/rnmz l), see line 98 Noteo 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 PREN280b 8b 10
4、12311 0004211 O m prEXu2806 Page 4 1 lestrical I y /,i, .onduct ivity eriphera! coarse grain -4. htergranular corrosion Designation Notes 4 -I_.- 2L ER2004-1 2) T42 : y & 19 : acceptable I_ EFi2070-3 Level A (Table 5) I EN2717 2, 6 rnm only the depth of attack must in principle For 1,2 s a not exceed the second layer of grains from the surface. i) 40 mm where a 5 10 mm. 2) In preparation. .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-,-,-
