1、_ SAE Technical Standards Board Rules provide that7KLVUHSRUWLVSXEOLVKHGE6$(WRDGYDQFHWKHVWDWHRIWHFKQLFD ODQGHQJLQHHULQJVFLHQFHV7KHXVHRIWKLVUHSRUWLVHQWL rely voluntary, and its applicability and suitability for any particular use, including any patent infringement arising therefrom, LVWKHVROHUHVSRQVLE
2、LOLWRIWKHXVHU 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 2016 SAE International All rights reserved. No part of this publication may be reproduced, sto
3、red 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: +1 724-776-4970 (outside USA) Fax: 724-776-0790
4、 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org SAE values your input. To provide feedback on this Technical Report, please visit http:/www.sae.org/technical/standards/AMS4327A AEROSPACE MATERIAL SPECIFICATION AMS4327 REV. A Issued 2003-12 Reaffirmed 2009-06 Revised 2016-05 Superse
5、ding AMS4327 Aluminum Alloy, Plate (2098-O) 3.5Cu - 1.1Li - 0.50Mg - 0.40Ag - 0.11Zr Annealed (Composition similar to UNS A92098) RATIONALE AMS4327A revises Properties (3.3.1) and Reports (4.4), and is a Five Year Review and update of this specification. 1. SCOPE 1.1 Form This specification covers a
6、n aluminum alloy in the form of plate 0.250 to 0.300 inches (6.35 to 7.62 mm), inclusive, in thickness (see 8.6). 1.2 Application This product has typically been used in aerospace applications where low density is needed in combination with high strength, high toughness, high damage tolerance, and i
7、mproved stiffness, 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 u
8、nless 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 15096-000
9、1, 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 Alloys, 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 AMS4327A Page 2 of 6 2.2 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 Ult
11、rasonic Inspection of Aluminum-Alloy Wrought Products ASTM B646 Fracture Toughness Testing of Aluminum Alloys ASTM B660 Packaging/Packing of Aluminum and Magnesium Products ASTM B666 / B66M Identification Marking of Aluminum Products ASTM E561 K-R Curve Determination ASTM G47 Determining Susceptibil
12、ity to Stress-Corrosion Cracking of High-Strength Aluminum Alloy Products 2.3 ANSI Accredited Publications Copies of these documents are available online at http:/webstore.ansi.org/. ANSI H35.1/H35.1M Alloy and Temper Designation Systems for Aluminum ANSI H35.2 Dimensional Tolerances for Aluminum Mi
13、ll Products ANSI H35.2M Dimensional Tolerances for Aluminum Mill Products (Metric) 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 - 0.12 Iron - 0.15 Copper 3.2 3
14、.8 Manganese - 0.35 Magnesium 0.25 0.8 Zinc - 0.35 Titanium - 0.10 Silver 0.25 0.6 Lithium 0.8 1.3 Zirconium 0.04 0.18 Other Elements, each - 0.05 Other Elements, total - 0.15 Aluminum remainder SAE INTERNATIONAL AMS4327A Page 3 of 6 3.2 Condition 3.2.1 -O Condition (see ANSI H35.1/H35.1M) Annealed
15、by heating, holding at heat for a time commensurate with section thickness and slow cooling (see 8.2). May receive minor stretching to improve flatness. 3.2.2 T82P Temper Solution heat treated in accordance with AMS2772, stretched to produce a permanent set of at least 1.5% but not more than 4.0%, a
16、nd precipitation heat treated to T82P temper in accordance with AMS2772 (see 8.3). 3.3 Properties Plate shall conform to the following requirements, determined on the mill produced size, in accordance with AMS2355 and as specified herein. 3.3.1 Mechanical property requirements for product outside of
17、 the range covered by 1.1 shall be agreed upon between purchaser and producer. 3.3.2 As Received (O Temper) The material shall meet the O temper requirements shown in Table 2 in the as-supplied condition. 3.3.3 Response to Heat Treat (T82P). The material shall also be capable of meeting the T82 prop
18、erty requirements shown in Tables 2 and 3 after proper solution heat treatment, stretching, and artificial aging per 3.2.2. 3.3.3.1 Tensile Properties Shall be as specified in Table 2. Table 2A Minimum tensile properties, inch/pound units Temper Thickness, Inclusive (Inches) Grain Direction Ultimate
19、 Tensile Strength (ksi) Yield Strength 0.2% Offset (ksi) % Elongation in 2 Inches O 0.250 - 0.300 LT 35 max 25 max 11 T82P 0.250 - 0.300 L 73.0 68.0 6 LT 73.0 68.0 6 Table 2B Minimum tensile properties, SI units Temper Thickness, Inclusive (mm) Grain Direction Ultimate Tensile Strength (MPa) Yield S
20、trength 0.2% Offset (MPa) % Elongation in 50.8 mm O 6.35 - 7.62 LT 241 max 172 max 11 T82P 6.35 - 7.62 L 503 476 6 LT 503 476 6 SAE INTERNATIONAL AMS4327A Page 4 of 6 3.3.3.2 Stress-Corrosion Resistance Demonstration of capability on mill produced plate in the -T82P temper (see 4.3.1), tested in acc
21、ordance with ASTM G47, shall show no evidence of stress corrosion failure when stressed in the long-transverse direction at 35.0 ksi (241 MPa) and exposed for 30 days. 3.3.3.3 Fracture Toughness Demonstration of capability on mill produced plate in the -T82P temper (see 4.3.1), tested in accordance
22、with ASTM E561 and ASTM B646, shall meet the requirements for Kc specified in Table 3. The specimen type shall be M(T) and have a width of 16 inches. The specimen shall be fatigue pre-cracked in accordance with ASTM E561. The initial crack length (i.e., machine notch plus fatigue pre-crack) shall ha
23、ve a total initial crack length (2ao) of 4 inches. Table 3A Minimum fracture toughness, inch/pound units Temper Thickness, Inclusive (Inches) Specimen Orientation Required Minimum Plane Strain Fracture Toughness, Kc (ksi-in 1/2) T82P 0.250 to 0.300 L-T 120 T-L 80 Table 3B Minimum fracture toughness,
24、 SI units Temper Thickness, Inclusive (mm) Specimen Orientation Required Minimum Plane Strain Fracture Toughness, Kc (MPa-m 1/2) T82P 6.35 to 7.62 L-T 132 T-L 88 3.4 Quality Plate, as received by the purchaser, shall be uniform in quality and condition, sound, and free from foreign materials and fro
25、m imperfections detrimental to usage of the plate. Light scratches and discoloration or streaking shall not be reason for rejection. 3.4.1 Plate shall be ultrasonically inspected at an intermediate gauge of at least 2 inches in accordance with ASTM B594 and shall meet the requirements of Class B. 3.
26、5 Tolerances Shall conform to all applicable requirements of ANSI H35.2 or H35.2M. 4. QUALITY ASSURANCE PROVISIONS 4.1 Responsibility for Inspection The vendor of plate shall supply all samples for vendors tests and shall be responsible for the performance of all required tests. Purchaser reserves t
27、he right to sample and to perform any confirmatory testing deemed necessary to ensure that the plate conforms to specified requirements. 4.2 Classification of Tests 4.2.1 Acceptance Tests Composition (3.1), tensile properties (3.3.3.1), fracture toughness (3.3.3.3), and ultrasonic inspection (3.4.1)
28、 are acceptance tests, and except for composition shall be performed on each lot. SAE INTERNATIONAL AMS4327A Page 5 of 6 4.2.2 Periodic Tests Stress-corrosion resistance (3.3.3.2) is a periodic test and shall be performed on the first three lots and thereafter at a frequency selected by the vendor u
29、nless frequency of testing is specified by purchaser. 4.3 Sampling and Testing 4.3.1 One plate from each lot shall be processed to T82P temper and sampled by removing material for one set of two tensile specimens from the center width location on one end. The set of two tensile specimens shall consi
30、st of one longitudinal and one long transverse. Specimen thickness location shall be as specified in AMS2355. 4.3.2 Fracture toughness specimens shall be taken from each parent plate at the center width location on the end from which the set of two tensile specimens is removed. 4.3.3 Ultrasonic insp
31、ection shall be performed on the entirety of each parent (intermediate thickness) plate (see 3.4.1). 4.4 Reports The vendor shall furnish with each shipment a report stating that the plate conforms to the chemical composition and tolerances, ultrasonic inspection requirements, and all other technica
32、l requirements. The report shall show the numerical results of tests on each inspection lot to prove conformance to acceptance test requirements. The report shall include the producer, purchase order number, product form, inspection lot number, AMS4327A, size, and quantity. 4.4.1 When the product si
33、ze is outside the range covered by 1.1, the report shall contain a statement to that effect. 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. 5.2 Packaging Plate shall be prepared for shipmen
34、t in accordance with ASTM B660 and in compliance with applicable rules and regulations pertaining to the handling, packaging, and transportation of the plate to ensure carrier acceptance and safe delivery. 6. ACKNOWLEDGMENT A vendor shall mention this specification number and its revision letter in
35、all quotations and when acknowledging purchase orders. 7. REJECTIONS Plate not conforming to this specification, or to modifications authorized by purchaser, will be subject to rejections. SAE INTERNATIONAL AMS4327A Page 6 of 6 8. NOTES 8.1 Revision Indicator A change bar (l) located in the left mar
36、gin 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, including technical revisions. Change bars
37、and (R) are not used in original publications, nor in documents that contain editorial changes only. 8.2 Annealing treatment is proprietary. 8.3 The T82P temper designation is used because the specific process conditions were considered proprietary at the time the specification was first issued. 8.4
38、 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 units and are presented only for information. 8.5 Terms used in AMS are clarified in
39、ARP1917 and defined as follows: 8.5.1 Lot Material of the same mill form, alloy, temper, section and size traceable to one melt and one annealing furnace load. 8.5.2 Parent Plate A plate that has been processed to final temper as a single unit. The parent plate may subsequently be cut into two or mo
40、re smaller plates to provide the required width and length. 8.6 Purchase documents should specify not less than the following: AMS4327A Size of plate desired Quantity of plate desiredProperty and acceptance requirements from the cognizant engineering organization applicable to sizes outside the range listed in 1.1. PREPARED BY AMS COMMITTEE “D“
