SAE AMS 4206C-2017 Aluminum Alloy Plate (7055-T7751) 8 0Zn - 2 3Cu - 2 0Mg - 0 16Zr Solution Heat Treated Stress Relieved and Overaged (UNS A97055).pdf

《SAE AMS 4206C-2017 Aluminum Alloy Plate (7055-T7751) 8 0Zn - 2 3Cu - 2 0Mg - 0 16Zr Solution Heat Treated Stress Relieved and Overaged (UNS A97055).pdf》由会员分享，可在线阅读，更多相关《SAE AMS 4206C-2017 Aluminum Alloy Plate (7055-T7751) 8 0Zn - 2 3Cu - 2 0Mg - 0 16Zr Solution Heat Treated Stress Relieved and Overaged (UNS A97055).pdf（6页珍藏版）》请在麦多课文档分享上搜索。

1、_ SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the state of technical and engineering sciences. The use of this report is entirely voluntary, and its applicability and suitability for any particular use, including any patent infringement arising there

2、from, is the sole responsibility of the user.” SAE reviews each technical report at least every five years at which time it may be revised, reaffirmed, stabilized, or cancelled. SAE invites your written comments and suggestions. Copyright 2017 SAE International All rights reserved. No part of this p

3、ublication may be reproduced, stored in a retrieval system or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without the prior written permission of SAE. TO PLACE A DOCUMENT ORDER: Tel: 877-606-7323 (inside USA and Canada) Tel: +1 724-776-497

4、0 (outside USA) Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org SAE values your input. To provide feedback on this Technical Report, please visit http:/standards.sae.org/AMS4206C AEROSPACE MATERIAL SPECIFICATION AMS4206 REV. C Issued 1999-01 Revised 2017-10 Superse

5、ding AMS4206B Aluminum Alloy, Plate (7055-T7751) 8.0Zn - 2.3Cu - 2.0Mg - 0.16Zr Solution Heat Treated, Stress Relieved, and Overaged (Composition similar to UNS A97055) RATIONALE AMS4206C revises Properties (3.4), Tables 3 and 4, Sampling and Testing (4.3), Reports (4.4), Identification (5.1.1), and

6、 is a Five-Year Review and update of this specification. 1. SCOPE 1.1 Form This specification covers an aluminum alloy in the form of plate 0.500 to 1.500 inches (12.70 to 38.10 mm) inclusive, in thickness (see 8.4). 1.2 Application This product has been used typically for parts requiring a high lev

7、el of mechanical properties and moderate exfoliation corrosion resistance, but usage is not limited to such applications. 2. APPLICABLE DOCUMENTS The issue of the following documents in effect on the date of the purchase order forms a part of this specification to the extent specified herein. The su

8、pplier may work to a subsequent revision of a document unless a specific document issue is specified. When the referenced document has been cancelled and no superseding document has been specified, the last published issue of that document shall apply. 2.1 SAE Publications Available from SAE Interna

9、tional, 400 Commonwealth Drive, Warrendale, PA 15096-0001, Tel: 877-606-7323 (inside USA and Canada) or +1 724-776-4970 (outside USA), www.sae.org. AMS2355 Quality Assurance, Sampling and Testing Aluminum Alloys and Magnesium Alloy Wrought Products (Except Forging Stock), and Rolled, Forged, or Flas

10、h Welded Rings ARP1917 Clarification of Terms Used in Aerospace Metals Specifications SAE INTERNATIONAL AMS4206C Page 2 of 6 2.2 ANSI Accredited Publications Copies of these documents are available online at http:/webstore.ansi.org/. ANSI H35.2 Dimensional Tolerances for Aluminum Mill Products ANSI

11、H35.2M Dimensional Tolerances for Aluminum Mill Products (Metric) 2.3 ASTM Publications Available from ASTM International, 100 Barr Harbor Drive, P.O. Box C700, West Conshohocken, PA 19428-2959, Tel: 610-832-9585, www.astm.org. ASTM B594 Ultrasonic Inspection of Aluminum-Alloy Wrought Products ASTM

12、B645 Linear-Elastic Plane Strain Fracture Toughness Testing of Aluminum Alloys ASTM B666/B666M Identification Marking of Aluminum and Magnesium Products ASTM E399 Linear-Elastic Plane-Strain Fracture Toughness KIc of Metallic Materials ASTM E561 K-R Curve Determination ASTM G34 Exfoliation Corrosion

13、 Susceptibility in 2XXX and 7XXX Series Aluminum Alloys (EXCO Test) 3. TECHNICAL REQUIREMENTS 3.1 Composition Shall conform to the percentages by weight shown in Table 1, determined in accordance with AMS2355. Table 1 - Composition Element Min Max Silicon - 0.10 Iron - 0.15 Copper 2.0 2.6 Manganese

14、- 0.05 Magnesium 1.8 2.3 Chromium - 0.04 Zinc 7.6 8.4 Titanium - 0.06 Zirconium 0.08 0.25 Other Elements, each - 0.05 Other Elements, total - 0.15 Aluminum remainder SAE INTERNATIONAL AMS4206C Page 3 of 6 3.2 Condition Solution heat treated, stress relieved by stretching to produce a nominal permane

15、nt set of 1.5%, but not less than 1% nor more than 3%, and overaged. 3.2.1 Product shall receive no further straightening operations after stretching. 3.3 Heat Treatment Shall be in accordance with AMS2772 and as follows: 3.3.1 Overaging Heat Treatment Overaging shall be performed at a specific temp

16、erature and time as required to meet requirements of 3.4 (see 8.2). 3.4 Properties The product shall conform to the following requirements, determined in accordance with AMS2355. 3.4.1 Tensile Properties Shall be as specified in Table 2. Table 2 Table 2A - Minimum tensile properties, inch/pound unit

17、s Nominal Thickness Inch Specimen Orientation Tensile Strength ksi Yield Strength at 0.2% Offset ksi Elongation in 2 inches or 4D % 0.500 to 1.500, incl Long-Transverse Longitudinal 89.0 89.0 85.0 86.0 8 7 Table 2B - Minimum tensile properties, SI units Nominal Thickness Millimeters Specimen Orienta

18、tion Tensile Strength MPa Yield Strength at 0.2% Offset MPa Elongation in 50.8 mm or 5D % 12.70 to 38.10, incl Long-Transverse Longitudinal 614 614 586 593 8 7 3.4.2 Compressive Yield Strength When specified, longitudinal compressive yield strength shall be 86.0 ksi (593 MPa), minimum. 3.4.3 Exfolia

19、tion Corrosion Test The product shall exhibit exfoliation-corrosion at a T/10 plane not greater than that illustrated by Photograph EB, Figure 2, of ASTM G34. SAE INTERNATIONAL AMS4206C Page 4 of 6 3.4.4 Fracture Toughness 3.4.4.1 Plane Strain Fracture Toughness Plane strain fracture toughness shall

20、 be tested in the L-T orientation in accordance with ASTM E399 and ASTM B645 for plate 0.750 to 1.500 inches (19.05 to 38.1 mm) inclusive in nominal thickness. A valid KIc meeting the requirements of ASTM E399 or a KQ “useable for lot release” in accordance with ASTM B645 shall meet or exceed the va

21、lues specified in Table 3. Table 3 - Plane strain fracture toughness parameters Specimen Orientation Nominal Thickness Inches Nominal Thickness Millimeters Minimum KIc or KQ “useable for lot release” Minimum KIc or KQ “useable for lot release” L-T 0.750 to 1.250, incl 19.05 to 31.75, incl 22.0 24.2

22、L-T Over 1.250 to 1.500, incl Over 31.75 to 38.1, incl 21.0 23.1 3.4.4.2 Plane Stress Fracture Toughness For plate less than 0.750 inches (19.05 mm), plane stress fracture toughness (Kc) shall be tested in accordance with ASTM E561 and ASTM B646. Plane-stress fracture toughness (Kc) shall meet or ex

23、ceed the values specified in Table 4. Table 4 - Plane stress fracture toughness parameters Specimen Orientation Nominal Thickness Inches Nominal Thickness Millimeters Minimum Kc Minimum Kc L-T Less than 0.750 Less than 19.05 60.0 65.9 3.4.5 Mechanical property requirements for product outside of the

24、 range covered by 1.1 shall be agreed upon between purchaser and producer. 3.5 Quality The product, as received by purchaser, shall be uniform in quality and condition, sound, and free from foreign materials and from imperfections detrimental to usage of the product. 3.5.1 Each product shall be ultr

25、asonically inspected in accordance with ASTM B594 and shall meet the following requirements: 3.5.1.1 Products 0.500 to 1.500 inches (12.70 to 38.10 mm), inclusive, in nominal thickness shall meet the requirements for ultrasonic class A in accordance with ASTM B594. 3.6 Tolerances Shall conform to al

26、l applicable requirements of ANSI H35.2 or ANSI H35.2M. 4. QUALITY ASSURANCE PROVISIONS 4.1 Responsibility for Inspection The producer of the product shall supply all samples for producers tests and shall be responsible for the performance of all required tests. Purchaser reserves the right to sampl

27、e and to perform any confirmatory testing deemed necessary to ensure that the product conforms to specified requirements. ksi inchksi inchM P a m M P a m SAE INTERNATIONAL AMS4206C Page 5 of 6 4.2 Classification of Tests 4.2.1 Acceptance Tests Composition (3.1), long-transverse and longitudinal tens

28、ile properties (3.4.1), fracture toughness (3.4.4), ultrasonic soundness (3.5.1), dimensional tolerances (3.6) and, when specified, longitudinal compressive yield strength (3.4.2), are acceptance tests and, except for composition, shall be performed on each lot. 4.2.2 Periodic Tests Exfoliation-corr

29、osion resistance (3.4.3) is a periodic test and shall be performed at a frequency selected by the producer unless frequency of testing is specified by purchaser. 4.3 Sampling and Testing Shall be in accordance with AMS2355 and the following. 4.3.1 Tensile specimens shall be taken at the T/2 location

30、 with the axis of specimens in the long-transverse and in the longitudinal direction (see 3.4.1). 4.3.2 Plane strain fracture toughness specimens shall be taken from the center width of at least one plate in each lot (see 3.4.4.1). 4.3.2.1 For plate 0.750 to 1.000 inches (19.05 to 25.40 mm) inclusiv

31、e in nominal thickness, use full-thickness specimens having a width (W) of 2.0 inches (50.8 mm). 4.3.2.2 For plate 1.001 to 1.500 inches (25.43 to 38.10 mm) inclusive in nominal thickness, use specimens having a thickness (B) of 1.00 inches (25.4 mm) and a width (W) of 2.0 inches (50.8 mm), centered

32、 at mid-thickness (T/2). 4.3.3 Plane stress fracture toughness specimens shall be taken from the center width of at least one plate in each lot (see 3.4.4.2). 4.3.3.1 Plane stress fracture toughness specimens shall be of the M(T) type and have a width (W) of 16 inches (406 mm), a thickness (B) of 0.

33、25 inch (6.35 mm) and shall be centered at mid-thickness (T/2). The original crack size (2ao) shall be 4 inches (102 mm). 4.4 Reports The producer of product shall furnish with each shipment a report stating that the product conforms to the composition, tolerances and ultrasonic inspection; and show

34、ing the numerical results of tests on each inspection lot to determine conformance to the other acceptance test requirements and to the periodic test, if performed. This report shall include the purchase order number, inspection lot number(s), AMS4206C, size and quantity. 4.4.1 When the product size

35、 is outside the range covered by 1.1, the report shall contain a statement to that effect. 4.4.2 When material produced to this specification is beyond the sizes allowed in the scope of tables, or other exceptions are taken to the technical requirements listed in Section 3 (see 5.1.1), the report sh

36、all contain a statement “This material is certified as AMS4206C(EXC) because of the following exceptions.” and the specific exceptions shall be listed. 4.5 Resampling and Retesting Shall be in accordance with AMS2355. SAE INTERNATIONAL AMS4206C Page 6 of 6 5. PREPARATION FOR DELIVERY 5.1 Identificat

37、ion Shall be in accordance with ASTM B666/B666M. 5.1.1 When technical exceptions are taken (see 4.4.2), the material shall be marked with AMS4206(EXC). 5.2 Packaging The product shall be prepared for shipment in accordance with commercial practice and in compliance with applicable rules and regulati

38、ons pertaining to the handling, packaging, and transportation of the product to ensure carrier acceptance and safe delivery. 6. ACKNOWLEDGMENT A producer shall mention this specification number and its revision letter in all quotations and when acknowledging purchase orders. 7. REJECTIONS Product no

39、t conforming to this specification, or to modifications authorized by purchaser, will be subject to rejection. 8. NOTES 8.1 Revision Indicator A change bar (I) located in the left margin is for the convenience of the user in locating areas where technical revisions, not editorial changes, have been

40、made to the previous issue of this document. An (R) symbol to the left of the document title indicates a complete revision of the document, including technical revisions. Change bars and (R) are not used in original publications, nor in documents that contain editorial changes only. 8.2 Actual overa

41、ging heat treatments are proprietary. 8.3 Terms used in AMS are clarified in ARP1917. Dimensions and properties in inch/pound units and the Fahrenheit temperatures are primary; dimensions and properties in SI units and the Celsius temperatures are shown as the approximate equivalents of the primary

42、units and are presented only for information. 8.4 Purchase documents should specify not less than the following: AMS4206C Size of plate desired Quantity of plate desired Compressive yield strength (if required) (see 3.4.2) Property and acceptance requirements from the cognizant engineering organization applicable to sizes outside the range listed in 1.1 PREPARED by AMS COMMITTEE “D”