SAE AMS 4964C-2019

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AEROSPACE

MATERIAL SPECIFICATION

AMS4964™

REV. C

Issued 2000-07

Reaffirmed 2015-04

Revised 2019-05

Superseding AMS4964B

Titanium Alloy Bars, Wire, Forgings, and Rings

4.5Al - 3V - 2Fe - 2Mo

Annealed

RATIONALE

AMS4964C results from a Five-Year Review and update of this specification that includes the addition of ASTM E539 and

ASTM E2994 (3.1), removes sample size (covered by ASTM E1447) (Table 1), requires agreement between purchaser and

producer for tensile tests outside size limits (3.5.1.1.5), adds meeting AS6279 (3.8), prohibits unauthorized exceptions (3.9),

and revises reporting (4.4) and marking (5.1.1).

1. SCOPE

1.1 Form

This specification covers a titanium alloy in the form of bars, wire, forgings, flash welded rings, and stock for forging or flash

welded ring up through 6.000 inches (152.40 mm) in nominal diameter or distance between parallel sides.

1.2 Application

These products have been used typically for parts requiring good fatigue strength, formability, and strength up to 480 °F

(249 °C), but usage is not limited to such applications. The alloy is superplastic below 1520 °F (827 °C) and hot formable

from 1200 to 1560 °F (649 to 849 °C).

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.

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SAE INTERNATIONAL AMS4964™C Page 2 of 9

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.

AMS2241 Tolerances, Corrosion and Heat-Resistant Steel, Iron Alloy, Titanium, and Titanium Alloy Bars and Wire

AMS2249 Chemical Check Analysis Limits, Titanium and Titanium Alloys

AMS2750 Pyrometry

AMS2808 Identification Forgings

AMS2809 Identification Titanium and Titanium Alloy Wrought Products

AMS7498 Rings, Flash Welded, Titanium and Titanium Alloys

ARP1917 Clarification of Terms Used in Aerospace Metals Specifications

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 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 by Atomic Emission Plasma 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, or ASTM E2994. Other analytical methods may be used if acceptable to the

purchaser.

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SAE INTERNATIONAL AMS4964™C Page 3 of 9

Table 1 - Composition

Element

Min

Max

Aluminum

4.00

5.00

Vanadium

2.50

3.50

Molybdenum

1.80

2.20

Iron

1.70

2.30

Oxygen

0.18

Carbon

0.08

Nitrogen

0.05

(500 ppm)

Hydrogen

0.015

(150 ppm)

Yttrium (3.1.1)

0.005

( 50 ppm)

Other Elements, each (3.1.1)

0.10

Other Elements, total (3.1.1)

Titanium

remainder

0.40

3.1.1 Determination not required for routine acceptance.

3.1.2 Check Analysis

Composition variations shall meet the applicable requirements of AMS2249.

3.2 Melting Practice

Alloy shall be multiple melted. The first melt shall be made by 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 Bars

Hot finished (with or without subsequent cold reduction), annealed, and descaled. Unless prohibited by purchaser, bars may

be solution heat treated before annealing. The product shall be processed to the final thickness/diameter by metallurgical

working operations prior to any straightening, dimensional sizing or surface finishing operations. Bar shall not cut from plate.

3.3.2 Wire

Cold drawn, annealed, and descaled.

3.3.3 Forgings and Flash Welded Rings

Annealed and descaled. Unless prohibited by purchaser, product may be solution heat treated before annealing.

3.3.3.1 Flash welded rings shall not be supplied unless specified or permitted on purchaser’s part drawing. When

supplied, rings shall be manufactured in accordance with AMS7498.

3.3.4 Stock for Forging or Flash Welded Rings

As ordered by the forging or flash welded ring manufacturer.

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摘要：

SAE AMS 4964C-2019 是一项由国际自动机工程师学会（SAE）发布的最新版本航空航天材料规范，主要规定了对钛合金（Ti-6Al-4V）棒材、线材及锻件的技术要求和质量控制标准。该标准取代了之前的 4964B 版本，适用于航空航天领域关键结构件、发动机部件及紧固件的制造。内容涵盖材料的化学成分、力学性能、热处理工艺、无损检测以及验收检验程序等要求，旨在确保钛合金材料在高温、高压和疲劳载荷环境下的可靠性与一致性。对于从事航空材料采购、质量检测及制造工艺设计的专业人员而言，该规范是确保产

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