SAE AMS 5410C-2017

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AEROSPACE

MATERIAL SPECIFICATION

AMS5410™

REV. C

Issued 1984-10

Revised 2017-06

Superseding AMS5410B

Nickel Alloy, Corrosion and Heat Resistant, Investment Castings

61Ni - 16Cr - 8.5Co - 1.8Mo - 2.6W - 0.85Cb (Nb) - 3.4Ti - 1.8Ta - 3.4Al - 0.010B - 0.05Zr

Vacuum Melted, Vacuum Cast As Cast, or Solution Treated, or Solution and

Precipitation Hardened

RATIONALE

AMS5410C revises Classification of Tests (4.2), Reports (4.5.1), and Identification (5.1.1), and is a Five Year Review and

update of this specification.

1. SCOPE

1.1 Form

This specification covers a corrosion and heat resistant vacuum melted nickel alloy in the form of investment castings.

1.2 Application

These castings have been used typically for parts, such as turbine blades or vanes, requiring good strength and hot

corrosion resistance up to 1800 °F (982 °C), but usage is not limited to such applications.

1.3 Classification

Castings conforming to this specification are classified as follows:

Type A - Castings supplied in the as cast condition

Type B - Castings supplied in the solution heat treated condition

Type C - Castings supplied in the solution treated and precipitation heat treated condition

Class 1 - Trace element limits conforming to AMS2280-1

Class 2 - Trace element limits conforming to AMS2280-2

Class 3 - Trace element limits do not apply

1.3.1 Castings shall be supplied in the Type A condition unless Type B or Type C is specified by purchaser.

1.3.2 Castings shall conform to Class 1 unless Class 2 or Class 3 is specified by purchaser.

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SAE INTERNATIONAL AMS5410™C Page 2 of 11

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.

AMS2175 Castings, Classification and Inspection of

AMS2269 Chemical Check Analysis Limits, Nickel, Nickel Alloys, and Cobalt Alloys

AMS2280 Trace Element Control, Nickel Alloy Castings

AMS2360 Room Temperature Tensile Properties of Castings

AMS2362 Stress-Rupture Properties of Castings

AMS2694 In-Process Welding of Castings

AMS2750 Pyrometry

AMS2804 Identification Castings

ARP1917 Clarification of Terms Used in Aerospace Metals Specifications

AS5491 Calculation of Electron Vacancy Number in Superalloys

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 E139 Conducting Creep, Creep-Rupture, and Stress-Rupture Tests of Metallic Materials

ASTM E354 Chemical Analysis of High-Temperature, Electrical, Magnetic, and Other Similar Iron, Nickel, and

Cobalt Alloys

ASTM E1417/E1417M Liquid Penetrant Testing

ASTM E1742/E1742M Radiographic Testing

3. TECHNICAL REQUIREMENTS

3.1 Composition

Castings shall conform to the percentages by weight shown in Table 1, determined by wet chemical methods in

accordance with ASTM E354, by spectrochemical methods, or by other analytical methods acceptable to purchaser (see

8.2.1 and 8.2.2).

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SAE INTERNATIONAL AMS5410™C Page 3 of 11

Table 1 - Composition

Element

Min

Max

Carbon (3.1.1)

0.09

0.20

Manganese

0.20

Silicon

0.30

Phosphorus

0.015

Sulfur

0.015

Chromium

15.70

16.30

Cobalt

8.00

9.00

Molybdenum

1.50

2.00

Tungsten

2.40

2.80

Columbium (Niobium)

0.60

1.10

Titanium

3.20

3.70

Tantalum

1.50

2.00

Aluminum

3.20

3.70

Aluminum + Titanium

6.50

7.20

Boron

0.005

0.015

Zirconium

0.025

0.08

Iron

0.50

Copper

0.10

Other Elements (3.1.2)

Nickel

remainder

3.1.1 The preferred range for carbon is 0.09 to 0.13.

3.1.2 Producer may test for any element not listed in Table 1 and include this analysis in the report of 4.5. Limits of

acceptability may be specified by purchaser (see 8.2.3).

3.1.3 Trace Elements

Shall conform to AMS2280-1, unless AMS5410 Class 2 or Class 3 is specified by purchaser (see 1.3 and 8.5).

3.1.4 Check Analysis

Composition variations shall meet the applicable requirements of AMS2269.

3.1.5 Phacomp Electron Vacancy Number (Nv)

The phacomp electron vacancy number shall not exceed a value of 2.31 when calculated in accordance with AS5491.

3.2 Melting Practice

3.2.1 Master Heat Preparation

3.2.1.1 Revert (gates, sprues, risers, and rejected castings) may be used only in the preparation of master heats; revert

shall not be remelted directly, without refining, for pouring of castings.

3.2.1.2 Master heat metal shall be melted and poured under vacuum without loss of vacuum between melting and

pouring.

3.2.1.3 The master heat source shall establish effective control procedures including parameters for the critical

variables that will consistently produce material suitable for remelting of castings meeting the requirements of

this specification. Control procedures shall be acceptable to purchaser and casting producer.

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SAE AMS 5410C-2017 是一项针对航空用耐腐蚀钢（尤其是17-4PH型马氏体沉淀硬化不锈钢）的标准化材料规范，由国际自动机工程师学会（SAE International）发布。该标准详细规定了材料化学成分、力学性能、热处理要求、检验方法及验收标准，适用于航空发动机、机身结构件及高应力紧固件等关键部件的制造。通过严格的金相组织控制和硬度检测，AMS 5410C-2017确保了材料在高温、腐蚀及疲劳环境下的可靠性与长寿命，是航空航天领域设计、采购与质量认证的重要技术依据。该规范的更新版

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