SAE AMS 5644E-2017

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AEROSPACE

MATERIAL SPECIFICATION

AMS5644™

REV. E

Issued 1954-05

Revised 1964-06

Noncurrnet 1982-10

Reaf. Nonc. 2012-04

Stabilized 2017-04

Superseding AMS5644D

Steel, Bars and Forgings, Corrosion Resistant

17Cr - 7Ni - 1Al

UNS S17700

RATIONALE

AMS5644E stabilizes this document because it contains mature technology that is not expected to change and thus no

further revisions are anticipated.

STABILIZED NOTICE

AMS5644E has been declared "STABILIZED" by the SAE AMS F Corrosion Heat Resistant Alloys Committee. This

document was stabilized because this document contains mature technology that is not expected to change and thus no

further revisions are anticipated. Previously this document was non-current. The last technical update of this document

occurred in June, 1964. Users of this document should refer to the cognizant engineering organization for disposition of

any issues with reports/certifications to this specification; including exceptions listed on the certification.

NOTE: In many cases, the purchaser may represent a sub tier supplier and not the cognizant engineering organization.

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1. ACKNOWLEDGMENT:

A vendor shall mention this specification number and its revision letter in all quotations and when

acknowledging purchase orders.

2. FORM:

Bars, wire, forgings, and forging stock.

3. APPLICATION:

Primarily for parts requiring corrosion resistance and high strength up to 600 F (315 C), and when such

parts may require welding during fabrication.

4. COMPOSITION:

4.1 Check Analysis:

Composition variations shall meet the requirements of the latest issue of AMS 2248.

5. CONDITION:

5.1 Bars:

Solution heat treated at 1900 F ± 25 (1037.8 C ± 14) and water quenched, having hardness as

indicated below when tested midway between center and surface.

5.1.1 Rounds: Unless otherwise specified, ground, turned, or polished, having hardness not higher than

Brinell 229 or equivalent, except that rounds ordered cold drawn for size after solution heat

treatment may have hardness not higher than Brinell 255 or equivalent.

min max

Carbon -- 0.09

Manganese -- 1.00

Silicon -- 1.00

Phosphorus -- 0.040

Sulfur -- 0.030

Chromium 16.00 18.00

Nickel 6.50 7.75

Aluminum 0.75 1.50

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AMS5644™E

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5.1.2 Hexagons: Cold drawn for size after solution treatment, having hardness not higher than Brinell

255 or equivalent.

5.1.3 Flats: Unless otherwise specified, hot finished and descaled, having hardness not higher than

Brinell 229 or equivalent, except that flats ordered cold drawn for size after solution heat treatment

may have hardness not higher than 255 Brinell or equivalent.

5.2 Forgings:

Unless otherwise specified, solution heat treated at 1900 F ± 25 (1037.8 C ± 14) and water

quenched, having hardness not higher than Brinell 229 or equivalent.

5.3 Forging Stock:

As ordered by the forging manufacturer.

6. TECHNICAL REQUIREMENTS:

6.1 Bars and Forgings:

Material shall conform to the following requirements after heating to 1400 F ± 25 (760 C ± 14), for

1-1/2 hr, cooling to 55 F ± 5 (12.8 C ± 2.8) within 1 hr, holding at that temperature for not less than

30 min., followed by heating rapidly to 1050 F ± 10 (565.6 C ± 5.6), holding at that temperature for

1-1/2 hr, and cooling.

6.1.1 Hardness: Shall be not lower than Brinell 363 or equivalent.

6.1.2 Longitudinal Tensile Properties: Specimens taken in the longitudinal direction from bars 3 in. and

under in diameter or distance between parallel sides and from forgings 3 in. and under in section

thickness with the axis approximately parallel to the grain direction shall conform to the following

requirements:

6.1.2.1 Tensile properties of sizes over 3 in. in diameter or distance between parallel sides shall be as

agreed upon by purchaser and vendor.

Tensile Strength, psi 170,000 min

Yield Strength at 0.2% Offset or at 0.0137 in.

in 2 in. Extension Under Load (E = 29,000,000), psi 140,000 min

Elongation, % in 2 in. or 4D 6 min

Reduction of Area, % 25 min

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AMS5644™E

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摘要：

SAE AMS 5644E-2017 是航空航天材料规范（AMS）中关于耐腐蚀钢棒材、线材、锻件及管材的技术标准，主要针对440C型不锈钢（一种高碳马氏体不锈钢）的材料性能、热处理工艺、化学成分及机械性能要求。该标准取代了之前的AMS 5644D版本，适用于航空航天领域中需要高硬度、耐磨性及耐腐蚀性的关键零部件制造。文档详细规定了材料在退火或其它状态下的检验要求，包括拉伸强度、硬度、尺寸公差及表面质量等关键参数，是航空航天、精密机械及高端制造业中材料选型与质量控制的重要参考依据。

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