SAE AMS 4973J-2020

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For more information on this standard, visit

https://www.sae.org/standards/content/AMS4973J

AEROSPACE

MATERIAL SPECIFICATION

AMS4973™

REV. J

Issued 1966-05

Revised 2020-06

Superseding AMS4973H

Titanium Alloy Forgings

8Al - 1Mo - 1V

Solution Heat Treated and Stabilized

(Composition similar to UNS R54810)

RATIONALE

AMS4973J results from a Five-Year Review and update of this specification that adds analytical methods (3.1) and prohibits

unauthorized exceptions (3.5.1.1.4, 3.8, 4.4.3).

1. SCOPE

1.1 Form

This specification covers a titanium alloy in the form of forgings up to 4.000 inches (101.60 mm) inclusive and forging stock.

1.2 Application

This alloy has been used typically for parts requiring strength up to 800 °F (427 °C), but usage is not limited to such

applications.

1.2.1 Certain processing procedures and service conditions may cause these forgings to become subject to stress-

corrosion cracking. ARP982 recommends practices to minimize such conditions.

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.

AMS2249 Chemical Check Analysis Limits Titanium and Titanium Alloys

AMS2750 Pyrometry

AMS2808 Identification Forgings

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SAE INTERNATIONAL AMS4973™J Page 2 of 7

ARP982 Minimizing Stress-Corrosion Cracking in Wrought Titanium Alloy Products

ARP1917 Clarification of Terms Used in Aerospace Metals Specifications

AS1814 Terminology for Titanium Microstructures

AS6279 Standard Practice for Production, Distribution, and Procurement of Metal Stock

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 E8/E8M Tension Testing of Metallic Materials

ASTM E21 Elevated Temperature Tension Tests of Metallic Materials

ASTM E539 Analysis of Titanium Alloys by X-Ray Fluorescence Spectrometry

ASTM E1409 Determination of Oxygen and Nitrogen in Titanium and Titanium Alloys by Inert Gas Fusion

ASTM E1447 Determination of Hydrogen in Titanium and Titanium Alloys by the Inert Gas Fusion Thermal

Conductivity/Infrared Detection Method

ASTM E1941 Determination of Carbon in Refractory and Reactive Metals and Their Alloys by Combustion Analysis

ASTM E2371 Analysis of Titanium and Titanium Alloys Direct Current Plasma and Inductively Coupled Plasma by

Atomic Emission Spectrometry

ASTM E2994 Analysis of Titanium and Titanium Alloys by Spark Atomic Emission Spectrometry and Glow Discharge

Atomic Emission Spectrometry

3. TECHNICAL REQUIREMENTS

3.1 Composition

Shall conform to the percentages by weight shown in Table 1; carbon shall be determined in accordance with ASTM E1941,

hydrogen in accordance with ASTM E1447, oxygen and nitrogen in accordance with ASTM E1409, and other elements in

accordance with ASTM E539, ASTM E2371, and ASTM E2994. Other analytical methods may be used if acceptable to the

purchaser.

Table 1 - Composition

Element

Min

Max

Aluminum

7.35

8.35

Molybdenum

0.75

1.25

Vanadium

0.75

1.25

Iron

0.30

Oxygen

0.12

Carbon

0.08

Nitrogen

0.05

(500 ppm)

Hydrogen

0.0150

(150 ppm)

Yttrium (3.1.1)

0.005

( 50 ppm)

Other Elements, each (3.1.1)

0.10

Other Elements, total (3.1.1)

0.40

Titanium

remainder

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SAE INTERNATIONAL AMS4973™J Page 3 of 7

3.1.1 Determination not required for routine acceptance.

3.1.2 Check Analysis

Composition variations shall meet the applicable requirements of AMS2249; no variation over maximum will be permitted

for yttrium.

3.2 Melting Practice

Alloy shall be multiple melted. The first melt shall be made by vacuum consumable electrode, nonconsumable electrode,

electron beam cold hearth, or plasma arc cold hearth melting practice. The subsequent melt or melts shall be made using

vacuum arc remelting (VAR) practice. Alloy additions are not permitted in the final melt cycle.

3.2.1 The atmosphere for nonconsumable electrode melting shall be vacuum or shall be argon and/or helium at an

absolute pressure not higher than 1000 mm of mercury.

3.2.2 The electrode tip for nonconsumable electrode melting shall be water-cooled copper.

3.3 Condition

The product shall be supplied in the following condition:

3.3.1 Forgings

Solution heat treated, stabilized, and descaled.

3.3.2 Forging Stock

As ordered by the forging manufacturer.

3.4 Heat Treatment

Forgings shall be heat treated as follows; furnace surveys and calibration of temperature controllers and recorders shall be

in accordance with AMS2750:

3.4.1 Solution Heat Treatment

Shall be as specified in 3.4.1.1 unless purchaser permits treatment as specified in 3.4.1.2.

3.4.1.1 Heat to a temperature within the range 1800 to 1850 °F (982 to 1010 °C), hold at the selected temperature within

±25 °F (±14 °C) for 60 minutes ± 5 minutes, and quench in oil or water. When permitted by purchaser, forgings

may be air cooled.

3.4.1.2 Heat to a temperature within the range 1650 to 1700 °F (899 to 927 °C), hold at the selected temperature within

±25 °F (±14 °C) for 60 minutes ± 5 minutes, and cool at a rate equivalent to an air cool or faster.

3.4.2 Stabilization Heat Treatment

Heat to a temperature within the range 1050 to 1100 °F (566 to 593 °C), hold at the selected temperature within ±15 °F

(±8 °C) for not less than 8 hours, and cool in air.

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摘要：

SAE AMS 4973J-2020 是国际自动机工程师学会（SAE International）发布的一项最新修订版航空航天材料规范，主要规定了钛合金棒材、线材、锻件及环形件的化学成分、力学性能、热处理工艺及检验要求。该标准适用于高强度、耐腐蚀及高温环境下的航空航天零部件制造，是航空航天工业中用于确保钛合金材料质量一致性、可靠性与可追溯性的关键技术文件。本标准取代了之前的 AMS 4973H 版本，更新了材料验收标准与试验方法，适用于发动机部件、结构件及紧固件等关键应用场景。

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