1、LI6011976 - UDC 629-7 : 669.7155721326 -42 L 162 Cold compressed hand forgings. The latest issues of these standards should be used. Element 46 min. . max. British Standard Specification: Aerospace Series Bars and extruded sections of aluminium-zinc- mag nesi um -Co p per- chro mi u m alloy (Zn 5.6,
2、 Mg 2.5, Cu 1.6, Cr 0.22) (Zn 5.6, Mg 2.5, Cu 1.6, Cr 0.22) .L - -. . (Solution treated and artificially aged to an overaged condition) Barres et profils fils en alliage daluminium-zinc-magnksium-cuivre-chrome (Trait pour mise en solution et vieilli artificiellement un tat sur-vieilli) i Stabe und a
3、usgepresste Profile aus Aluminium-Zink-Magnesium-Kupfer-Chrornlegierung . I , -. _- ( Lsungsgeglht und knstlich veraltert zur Erzielung eines beralteten Zustand) (Zn 5.6, Mg 2.5, Cu 1.6, Cr 0.22) O . . .- -_ 1. Inspection and testing procedure This British Standard shall be used in conjunction with
4、the relevant sections of the latest issue of British Standard L 100 as follows: sections one and five Bars for machining and , sections one and six Bars for machining and extruded sections extruded sections for highly stressed structures 2. Quality of material The material shall be made from alumini
5、um and alloying constituents, with or without approved scrap at the discretion of the manufacturer. e British Standards Institution Silicon Iron Copper Manganese . Magnesium Chromium Zinc Titanium *Titanium plus zirconium *Others: each total Aluminium - 1.2 . - 2.1 0.18 5.1 0.40 0.50 - 2.0 0.30 2.9
6、0.28 6.1 0.20 0.25 0.05 0.1 5 Remainder Subject to the discretion of the Quality Assurance Authority, determination of these elements need be made on a small proportion only of the samples analysed. BSI Cal60 76 E l624b69 0099245 T m rnm Over Up toand including 10 10 20 20 50 50 75 75 100 100 150 L
7、160 : 1976 0.2 96 proof stress M Pa (= N/mm21 400 420 415 410 380 365 4. Condition Unless otherwise agreed and stated on the order, the material shall be supplied solution treated, controlled stretched and subsequently artificially aged to an overaged condition. NOTE. This condition is equivalent to
8、 the AECMA temper designation T.7351, Tensile strength 5. Heat treatment Elongation on gauge length of 50mm I 5,65JS0 The material shall be heat treated as follows: 470 485 485 475 450 425 (al solution treat by heating at a temperature of 465 f 5 OC and quenching in water at a temperature not exceed
9、ing 40 OC; . 7 - - - - - (b) artificially age by heating at a temperature of 110 f 5 OC for 6 h to 24 h, followed, with or without cooling, by further heating at a temperature of 177 f 6 OC for 5 h to 12 h, followed by air cooling. .- 6. Mechanical properties 6.1 .Tensile test. The mechanical proper
10、ties obtained, in the longitudinal direction, from test pieces selected and prepared in accordance with the relevant requirements of L 100 shall be not less than the following v.alues: 7. Resistance to stress corrosion cracking 7.1 Electrical conductivity 7.1.1 The electrical conductivity of the ten
11、sile test piece and of each piece of material in each batch shall be deter- mined by a method approved by the Quality Assurance Authority. The material shall be acceptable only if (a) the conductivity is not less than 23 MS/m, or , (b) the conductivity is less than 23 MS/m but not less than 22 MS/m
12、and the 0.2 % proof stress is not more than 85 MPa greater than the appropriate minimum specified in 6.1. 7.1.2 If the conductivity is less than 23 MS/m and not less than 22 MS/m but the proof stress requirement of 7.1.1(b) is not met, the material shall be retested in accordance with one of the fol
13、lowing procedures. (a) The batch shall be re-heat treated in accordance with clause 5 and retested, and the material shall comply with the requirements of 6.1 and 7.1.1. (b) The batch shall be given such a period of additional artificial ageing at the higher temperature that, when retested, the mate
14、rial shall comply with the requirements of 6.1 and 7.1.1. -_ (c) A sample taken from the batch shall be re-solution I MPa I % I % (= N/rnrn2) treated, by heating at a temperature of 465 ? 5 “C for not less than 30 min and quenching in cold water, and the conductivity shall be determined within 15 mi
15、n. The conductivity of this sample shall be at least 3.5 MS/m below that of the original fully heat treated sample. 7.2 Stress corrosion test. Material in the fully heat treated condition shall be capable of being subjected to the test described in appendix A without failure. This shall be demonstra
16、ted by testing at a frequency to be determined by the Quality Assurance Authority. NOTE. Information on SI units is given in ES 3763 The International System of units (SI) and ES 350 Conversion factors and tables. 2 L 160 : 1976 Appendix A - a Test for resistance to stress corrosion cracking A.l Tes
17、t piece. Cut a test piece, in the transverse direction . where the section size permits, from a test sample selected in accordance with the requirements of L 100, section five or section six as appropriate, and machined, subsequent to heat treatment, to the dimensions shown in figure 1 (a) or lib).
18、A.2 Preparation of test piece. Prepare the test piece, prior to loading, as follows: (a) degrease by washing in acetone; (b) rinse in distilled water and dry. A.3 Test solution. Use a solution of 3.5 f 0.5 % sodium chloride (AR grade) in distilled or deionized water having a pH value within the rang
19、e 6.4 to 7.2 and maintained at a temperature of 24 k 1 OC. Thread 4 - 20 UNC Check the solution each working day to determine the amount of water lost due to evaporation and add distilled or deionized water as necessary to bring the salt concentra- tion to 3.5 f 0.5 %. Prepare a fresh solution weekl
20、y. Maintain the pH value within the required range by adding dilute hydrochloric acid or dilute sodium hydroxide as necessary. . A.4 Procedure A.4.1 Load the test piece to 75 % of the appropriate minimum 0.2 % proof stress specified in 6.1 and hold at a constant strain in a suitable fixture. A.4.2 I
21、mmerse the loaded test piece in the test solution for 10 * 1 min. A.4.3 Remove from the test solution and suspend in air for 50 f 1 min. A.4.4 Repeat the cycle in A.4.2 and A.4.3 for 30 days. . 12.7 parallel- r -+ ,4 a4.0 1 .y , . ?O“ 3.175 2 0.025 ._ . i min. 6.5 w -c 9.5 6.5 19.0 M 51 .O 4 -. 4. N
22、OTE. Ends symmetrical. (a) Tensile test piece O 020.025 I 20 . I_ -+ 25 2.0 30 I 2.5 b) C-ring test piece t All dimensions are in miiiimetres. Figure 1. Test pieces for stress cwrosion test 3 ES1 L*lbCi 7b lb24bb9 8099247 3 I e i60 : 1976 This British Standard, having been prepared under the directi
23、on of the Aerospace Industry Standards Committee, was published under the authority of the E,Fecutive Board on 28 May 1976. British Standards Institution, 1976 ISBN: O 580 08979 7 Copyright Users of British Standards are reminded that copyright subsists in all BSI publications. No part of this publi
24、cation may be reproduced in any form without the prior permission in writing of BSI. This does not preclude the free use, in the course of implementing the standard, of necessary details such as symbols and size, type or grade designations. Enquiries should be addressed to the Publications Manager,
25、1 O1 Pentonville Road, London N1 9ND (Telephone O1 -837 8801 : Telex 2321 8). Contract requirements Attention is drawn to the fact that this British Standard does not purport to include all the necessary provisions of a contract. Revision of British Standards British Standards are revised, when nece
26、ssary, by the issue either of amendment slips or of revised editions. It is important that usersof British Standardsshould ascertain that they are in possession of the latest amendments or editions. The following BSI references relate to the work on this standard: Committee reference ACE/24 Draft fo
27、r comment 72/36415 DC Amendments issued since publication Amd. No. Date of issue Text affected British Standards Institution . 2 Park Street London WIA 2BS . Telephone 01-629 9000 . Telex 266933 7605 -1.4k-B AMD 5583 I Amendment No. 1 published and effective from 31 July 1987 to British Standard L 1
28、60 : 1976 (Aerospace Series) Bars and extruded sections of aluminium-zinc-magnesium-copper-chromium alloy Revised text Clause 6. Mechanical properties Delete the existing table and substitute the following new table. AMD 5583 July 1987 Sectional thickness 0.2 % proof stress Tensile strength Elongati
29、on on gauge length of 50 rnrn I 5.65 &o MPa (= Nlrnm2) MPa (= N/mm2 1% % mm Over Up toand including 10 10 20 20 50 50 75 75 100 100 150 400 420 415 410 380 365 470 485 485 475 450 42 5 NOTE. Information on SI units is given in BS 3763-The International System of units (SI) and BS 350 Conversion factors and tables. r ACE124 7 8707-O-1.2k-B
