SAE AMS 6356J-2020

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For more information on this standard, visit

https://www.sae.org/standards/content/AMS6356J

AEROSPACE

MATERIAL SPECIFICATION

AMS6356™

REV. J

Issued 1962-01

Revised 2020-03

Superseding AMS6356H

Steel, Sheet, Strip, and Plate

0.95Cr - 0.20Mo - (0.30 - 0.35C) (4132)

(Composition similar to UNS G41300)

RATIONALE

AMS6356J is a Five-Year Review and update of this specification that revises composition testing analytical methods (3.1),

adds ASTM E1077 (3.3.2.1), and prohibits unauthorized exceptions (3.6, 4.4.2, 5.1, 8.6).

1. SCOPE

1.1 Form

This specification covers an aircraft-quality, low-alloy steel in the form of sheet, strip, and plate.

1.2 Application

These products have been used typically for heat-treated parts and structures that may require welding during fabrication,

but usage is not limited to such applications. Product, 0.375 inch (9.52 mm) and under in nominal thickness, can be through-

hardened to a minimum tensile strength of 180 ksi (1241 MPa) and proportionately lower strength in heavier section

thicknesses.

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 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 15096-0001, Tel: 877-606-7323 (inside USA

and Canada) or +1 724-776-4970 (outside USA), www.sae.org.

AMS2252 Tolerances, Low-Alloy Steel Sheet, Strip, and Plate

AMS2259 Chemical Check Analysis Limits, Wrought Low-Alloy and Carbon Steels

AMS2301 Steel Cleanliness, Aircraft Quality Magnetic Particle Inspection Procedure

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SAE INTERNATIONAL AMS6356™J Page 2 of 6

AMS2370 Quality Assurance Sampling and Testing, Carbon and Low-Alloy Steel Wrought Products and Forging Stock

AMS2807 Identification, Carbon and Low-Alloy Steels, Corrosion and Heat-Resistant Steels and Alloys, Sheet, Strip,

Plate, and Aircraft Tubing

ARP1917 Clarification of Terms Used in Aerospace Metals Specifications

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 A255 Determining the Hardenability of Steel

ASTM A370 Mechanical Testing of Steel Products

ASTM A751 Standard Test Methods, Practices, and Terminology for Chemical Analysis of Steel Products

ASTM E112 Determining Average Grain Size

ASTM E140 Hardness Conversion Tables for Metals Relationship Among Brinell Hardness, Vickers Hardness, Rockwell

Hardness, Superficial Hardness, Knoop Hardness, Scleroscope Hardness, and Leeb Hardness

ASTM E290 Bend Testing of Material for Ductility

ASTM E384 Microindentation Hardness of Materials

ASTM E1077 Estimating the Depth of Decarburization of Steel Specimens

3. TECHNICAL REQUIREMENTS

3.1 Composition

Shall conform to the percentages by weight shown in Table 1, determined in accordance with ASTM A751, by

spectrochemical methods, or by other analytical methods acceptable to purchaser.

Table 1 - Composition

Element

Min

Max

Carbon

0.30

0.35

Manganese

0.40

0.60

Silicon

0.15

0.50

Phosphorus

0.025

Sulfur

0.025

Chromium

0.80

1.10

Molybdenum

0.15

0.25

Nickel

0.25

Copper

0.35

3.1.1 Aluminum, vanadium and columbium are optional grain refining elements and need not be determined or reported

unless used to satisfy the average grain size requirements of 3.3.1.2.

3.1.2 Check Analysis

Composition variations shall meet the applicable requirements of AMS2259.

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3.2 Condition

The product shall be supplied in the following condition; hardness shall be determined in accordance with ASTM A370:

3.2.1 Sheet and Strip

Cold finished, bright or atmosphere annealed, and descaled if necessary; or hot rolled, annealed if necessary, and descaled;

having hardness not higher than 95 HRB, or equivalent (see 8.2).

3.2.2 Plate

Hot rolled, annealed if necessary, and descaled, having hardness not higher than 95 HRB, or equivalent (see 8.2).

3.2.2.1 If allowed by the purchaser, cold rolled, annealed if necessary, and descaled, having hardness not higher than

95 HRB, or equivalent (see 8.2).

3.2.3 If product is ordered spheroidize annealed, the degree of spheroidization shall be as agreed upon by purchaser

and producer.

3.3 Properties

The product shall conform to the following requirements; hardness testing shall be performed in accordance with

ASTM A370:

3.3.1 Average Grain Size

Average grain size shall be determined by either 3.3.1.1 or 3.3.1.2.

3.3.1.1 Shall be ASTM No. 5 or finer, determined in accordance with ASTM E112.

3.3.1.2 The product of a heat shall be considered to have an ASTM No. 5 or finer austenitic grain size if one or more of

the following are determined by heat analysis (see 8.5):

3.3.1.2.1 A total aluminum content of 0.020 to 0.050%.

3.3.1.2.2 An acid soluble aluminum content of 0.015 to 0.050%.

3.3.1.2.3 A vanadium content of 0.02 to 0.08%.

3.3.1.2.4 A columbium content of 0.02 to 0.05%.

3.3.2 Decarburization

Decarburization shall be evaluated by one of the two methods of 3.3.2.1 or 3.3.2.2.

3.3.2.1 Metallographic Method

A cross section taken perpendicular to the surface shall be prepared in accordance with ASTM E1077, etched, and visually

examined metallographically at a magnification not to exceed 100X. The product shall not show a layer of complete (ferrite)

or partial decarburization exceeding the limits of Table 2.

3.3.2.2 Hardness Traverse Method

The total depth of decarburization shall be determined by a traverse method using microindentation hardness testing in

accordance with ASTM E384, at a magnification not exceeding 100X, conducted on a hardened but untempered specimen

protected during heat treatment to prevent changes in surface carbon content. Tempering is generally not recommended,

but if tempered, the tempering temperature shall be not higher than 300 °F (149 °C). Depth of decarburization is defined as

the perpendicular distance from the surface to the depth under that surface where there is not further increase in hardness.

Such measurements shall be far enough away from any adjacent surface to be uninfluenced by any decarburization on the

adjacent surface. Acceptance shall be as listed in Table 2.

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摘要：

SAE AMS 6356J-2020 是美国汽车工程师学会（SAE）发布的最新版航空材料规范，针对高强度、可焊接的合金钢板（通常指 18Ni 马氏体时效钢或类似高合金钢）提出了严格的技术要求。该标准覆盖了热轧、冷轧及热处理状态下的板材、带材与棒材，主要应用于航空航天领域的关键结构件，如起落架、机翼部件和发动机支架等。AMS 6356J-2020 在上一版基础上更新了化学成分范围、力学性能指标（包括抗拉强度、屈服强度、延伸率和冲击韧性）、热处理工艺参数以及无损检测要求，确保材料在极端工况下的可靠性

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