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/AMS4464A AEROSPACE MATERIAL SPECIFICATION AMS4464 REV. A Issued 2012-01 Revised 2017-10 Superse
5、ding AMS4464 Aluminum Alloy Plate (2624-T351) 4.1Cu - 1.4Mg - 0.6Mn Solution Heat Treated, Cold Worked and Naturally Aged (Composition similar to UNS A92624) RATIONALE AMS4464A revises 3.2 Condition, 3.3 Heat Treatment, 3.4 Properties, and 4.4 Reports and is a Five-Year Review and update of this spe
6、cification. 1. SCOPE 1.1 Form This specification covers an aluminum alloy in the form of plate 0.500 to 1.500 inch, incl (12.70 to 38.10 mm, incl) in thickness (see 8.4). 1.2 Application This product has been used typically for structural parts requiring a high level of mechanical properties and goo
7、d damage tolerance, 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 supplier may work to a subsequent revision of a document
8、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 International, 400 Commonwealth Drive, Warrendale, PA 15096-00
9、01, 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 Flash Welded Rings AMS2772 Heat Treatment of Aluminum Alloy
10、 Raw Materials ARP1917 Clarification of Terms Used in Aerospace Metals Specifications SAE INTERNATIONAL AMS4464A Page 2 of 6 2.2 ANSI Accredited Publications Copies of these documents are available online at http:/webstore.ansi.org/. ANSI H35.1/ H35.1M Standard Alloy and Temper Designation System Fo
11、r Aluminum ANSI H35.2 Dimensional Tolerances for Aluminum Mill Products ANSI 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.
12、org. ASTM B594 Ultrasonic Inspection of Aluminum-Alloy Wrought Products ASTM B645 Linear-Elastic Plane-Strain Fracture Toughness Testing of Aluminum Alloys ASTM B646 Fracture Toughness Testing of Aluminum Alloys ASTM B660 Packaging/Packing of Aluminum and Magnesium Products ASTM B666/B666M Identific
13、ation Marking of Aluminum and Magnesium Products ASTM E399 Linear-Elastic Plane-Strain Fracture Toughness KIc of Metallic Materials ASTM E561 K-R Curve Determination 3. TECHNICAL REQUIREMENTS 3.1 Composition Shall conform to the percentages by weight shown in Table 1, determined in accordance with A
14、MS2355. Table 1 - Composition Element Min Max Silicon - 0.08 Iron - 0.08 Copper 3.8 4.3 Manganese 0.45 0.7 Magnesium 1.2 1.6 Chrome - 0.05 Zinc - 0.15 Titanium - 0.10 Other Elements, each - 0.05 Other Elements, total - 0.15 Aluminum remainder SAE INTERNATIONAL AMS4464A Page 3 of 6 3.2 Condition Solu
15、tion heat treated and stretched 1.5 to 3% after solution heat treatment to produce a T351 temper (see ANSI H35.1/H35.1M). 3.3 Heat Treatment Solution heat treatment shall be in accordance with AMS2772. The solution heat treat temperature shall be 910 to 930 F (488 to 499 C). 3.4 Properties Product s
16、hall conform to the following requirements, determined on the mill product 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 units Nominal Thickness Inches Specimen Orientation Tensile Strength ksi Yield S
17、trength at 0.2% Offset ksi Elongation in 2 inches or 4D % 0.500 to 1.000, incl. Over 1.000 to 1.500 Longitudinal Long-Transverse Longitudinal Long-Transverse 63.0 65.0 62.0 64.0 48.0 44.0 47.0 44.0 16 15 16 15 Table 2B - Minimum tensile properties, SI units Nominal Thickness Millimeters Specimen Ori
18、entation Tensile Strength MPa Yield Strength at 0.2% Offset MPa Elongation in 50.8 mm or 5D % 12.70 to 25.40, incl. Over 25.40 to 38.10 Longitudinal Long-Transverse Longitudinal Long-Transverse 434 448 427 441 331 303 324 303 14 13 14 13 3.4.2 Plane Strain Fracture Toughness When required by purchas
19、er (see 8.4), plane strain fracture toughness shall be tested 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
20、 shall meet or exceed the values specified in Table 3. SAE INTERNATIONAL AMS4464A Page 4 of 6 3.4.2.1 The test specimens shall meet the following requirements: For L-T and T-L test orientations use a test specimen having a width (W) of 3.0 inches (76 mm) and a thickness (B) of full plate thickness.
21、Table 3 - Minimum plane-strain fracture toughness Nominal Thickness Inches Nominal Thickness Millimeters Specimen Orientation KIc or KQ “useable for lot release” ksi inch KIc or KQ “useable for lot release” MPa m 0.750 to 1.500, incl 19.05 to 38.10, incl L-T T-L 42 41 46 45 3.4.3 Plane Stress Fractu
22、re Toughness Plane-stress fracture toughness (Kapp), shall be tested in accordance with ASTM E561 and ASTM B646. A Kapp value meeting the requirements of ASTM E561 and ASTM B646 shall meet or exceed the values shown in Table 4. 3.4.3.1 The test specimens shall meet the following requirements: 3.4.3.
23、2 The specimen shall be of the M(T) type and have a width (W) of 16 inches (406 mm), a thickness (B) of 0.25 inch (6.35 mm) and shall be centered at mid-thickness (T/2). The original crack size (2ao) shall be 4 inches (102 mm). Table 4 - Minimum plane-stress fracture toughness Nominal Thickness Inch
24、es Nominal Thickness Millimeters Specimen Orientation ksi inch MPa m 0.500 to 1.500, incl 12.70 to 38.10, incl L-T 97 107 3.4.4 Mechanical property requirements for product outside the range covered by 1.1 shall be agreed upon between purchaser and producer. 3.5 Quality Plate, as received by purchas
25、er, 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 plate 0.500 inch (12.70 mm) and over in nominal thickness shall be ultrasonically inspected in accordance with ASTM B594 and shall meet ultraso
26、nic class A requirements. 3.6 Tolerances Shall conform to all applicable requirements of ANSI H35.2 or ANSI H35.2M. 4. QUALITY ASSURANCE PROVISIONS 4.1 Responsibility for Inspection The vendor of the product shall supply all samples for vendors tests and shall be responsible for the performance of a
27、ll required tests. Purchaser reserves the right to sample and to perform any confirmatory testing deemed necessary to ensure that the product conforms to specified requirements. SAE INTERNATIONAL AMS4464A Page 5 of 6 4.2 Classification of Tests 4.2.1 Acceptance Tests Composition (3.1), long-transver
28、se and longitudinal tensile properties (3.4.1), plane-stress fracture toughness (3.4.3), ultrasonic soundness (3.5.1), dimensional tolerances (3.6) and, when required by purchaser, plane-strain fracture toughness (3.4.2) are acceptance tests and, except for composition, shall be performed on each in
29、spection lot. 4.3 Sampling and Testing Shall be in accordance with AMS2355 and the following: 4.3.1 Tensile specimens shall be taken with axis of specimens parallel to each applicable grain flow direction specified in Table 2. 4.4 Reports The vendor of the product shall furnish with each shipment a
30、report stating that the product conforms to the composition, tolerances and ultrasonic inspection; and showing 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 th
31、e purchase order number, inspection lot number(s), AMS4464A, size and quantity. The report shall also identify the mill producer and the size of the mill product. 4.4.1 When the product size is outside the range covered by 1.1, the report shall contain a statement to that effect. 4.4.2 When material
32、 produced to this specification, is beyond the sizes allowed in the scope or tables or other exceptions are taken to the technical requirements listed in Section 3 (see 5.1.1), the report shall contain a statement “This material is certified as AMS4464A(EXC) because of the following exceptions.” and
33、 the specific exceptions shall be listed. 4.5 Resampling and Retesting Shall be in accordance with AMS2355. 5. PREPARATION FOR DELIVERY 5.1 Identification 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 AMS4464(EXC
34、). 5.2 Packaging The product shall be prepared for shipment in accordance with ASTM B660 and in compliance with applicable rules and regulations pertaining to the handling, packaging, and transportation of the product to ensure carrier acceptance and safe delivery. 6. ACKNOWLEDGMENT A vendor shall m
35、ention this specification number in all quotations and when acknowledging purchase orders. 7. REJECTIONS Product not conforming to this specification, or to modifications authorized by purchaser, will be subject to rejection. SAE INTERNATIONAL AMS4464A Page 6 of 6 8. NOTES 8.1 Revision Indicator A c
36、hange 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 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, includ
37、ing technical revisions. Change bars and (R) are not used in original publications, nor in documents that contain editorial changes only. 8.2 Terms used in AMS are clarified in ARP1917. 8.3 Dimensions and properties in inch/pound units and the Fahrenheit temperatures are primary; dimensions and prop
38、erties in SI units and the Celsius temperatures are shown as the approximate equivalents of the primary units and are presented only for information. 8.4 Purchase documents should specify not less than the following: AMS4464A Size of plate desired Quantity of plate desired Property and acceptance requirements from the cognizant engineering organization applicable to sizes outside the range listed in 1.1 Plane-strain fracture toughness testing (if required) and specimen orientation (3.4.2) PREPARED BY AMS COMMITTEE “D”
