iTeh StandardsiTeh Standards
EURUSD
Your shopping cart is empty.
ASTM

ASTM E3205-20

(Test Method)

Standard Test Method for Small Punch Testing of Metallic Materials

Standard Test Method for Small Punch Testing of Metallic Materials

SIGNIFICANCE AND USE
4.1 The safety margins provided in the design for a component or structure can be reduced throughout its service life by aging. Aging is the process by which the physical and mechanical characteristics of component or structure materials change with time or use; this process may proceed by a single aging mechanism or a combination of several aging mechanisms.  
4.2 The term “safety margin” is used in a broad sense, meaning the safety state (that is, integrity and functional capability) of components in excess of their normal operational requirements (1).3  
4.3 The determination of mechanical properties such as yield strength, tensile strength, and ductile-to-brittle transition temperature of structural components is, hence, desirable for optimization of operating procedures and inspection intervals, as well as repair strategies and residual lifetime assessment. Current standardized mechanical tests require relatively large volumes of test material that cannot be extracted from in-service equipment without post-sampling removal repair (2).  
4.4 The need to obtain estimates of the mechanical properties of components without post-sampling removal repair has led to the development of small punch (SP) test techniques based on penetration/bulge tests of miniaturized test specimens (often disk-shaped, or square) (3, 4, 5). It can be considered as a quasi-nondestructive technique because of the very limited amount of material to be sampled. It is an efficient and cost-effective technique and has the potential to provide estimates of the material properties of the specific component, identifying the present state of damage and focusing on the most critical (most stressed, most damaged) locations in the component. Examples of empirical correlations that have been established between small punch test results and mechanical properties for specific classes of materials are provided in Appendix X1.  
4.5 This test method can be also used for identifying the most suitable ma...
SCOPE
1.1 This test method covers procedures for conducting the small punch deformation test for metallic materials. The results can be used to derive estimates of yield and tensile strength up to 450 °C, and estimates of the ductile-to-brittle transition temperature from the results of small punch bulge tests in the temperature range from -193 °C to 350 °C for iron based materials or 0.4 Tm for other metallic materials, where Tm is their melting temperature in K.  
1.2 The values stated in SI units are to be regarded as standard. No other units of measurement are included in this standard.  
1.3 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.  
1.4 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.

General Information

Status
Published
Publication Date
30-Jun-2020
ICS
49.035 - Components for aerospace construction
Technical Committee
E10 - Nuclear Technology and Applications
Drafting Committee
E10.02 - Behavior and Use of Nuclear Structural Materials
Current Stage
Ref Project

Buy Standard

ASTM E3205-20 - Standard Test Method for Small Punch Testing of Metallic MaterialsASTM E3205-20 - Standard Test Method for Small Punch Testing of Metallic Materials
PreviousNext
Standard
ASTM E3205-20 - Standard Test Method for Small Punch Testing of Metallic Materials
English language
12 pages
sale 15% off
Preview
sale 15% off
Preview

Standards Content (Sample)

This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the
Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
Designation: E3205 − 20
Standard Test Method for
1
Small Punch Testing of Metallic Materials
This standard is issued under the fixed designation E3205; the number immediately following the designation indicates the year of
original adoption or, in the case of revision, the year of last revision.Anumber in parentheses indicates the year of last reapproval.A
superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
1. Scope E691Practice for Conducting an Interlaboratory Study to
Determine the Precision of a Test Method
1.1 This test method covers procedures for conducting the
E220Test Method for Calibration of Thermocouples By
smallpunchdeformationtestformetallicmaterials.Theresults
Comparison Techniques
can be used to derive estimates of yield and tensile strength up
to 450 °C, and estimates of the ductile-to-brittle transition
3. Terminology
temperature from the results of small punch bulge tests in the
temperature range from -193 °C to 350 °C for iron based 3.1 Definitions:
materials or 0.4 T for other metallic materials, where T is
3.1.1 force, F [F], n—force applied to the test specimen by
m m
their melting temperature in K.
the punch.
3.1.1.1 Discussion—This includes the weights of the equip-
1.2 The values stated in SI units are to be regarded as
ment acting on the punch.
standard. No other units of measurement are included in this
standard. 3.1.2 force-punch displacement (F-v) curve, n—relationship
between force and punch displacement, which is continuously
1.3 This standard does not purport to address all of the
recorded during the small punch (SP) bulge test.
safety concerns, if any, associated with its use. It is the
responsibility of the user of this standard to establish appro- 3.1.3 force-specimen deflection (F-u) curve, n—relationship
priate safety, health, and environmental practices and deter-
between force and deflection, which is continuously recorded
mine the applicability of regulatory limitations prior to use. during the SP bulge test.
1.4 This international standard was developed in accor-
3.1.4 punch displacement, v [L], n—displacement of the
dance with internationally recognized principles on standard-
center of the top of the punch in contact with the specimen.
ization established in the Decision on Principles for the
3.1.4.1 Discussion—Determination of the punch displace-
Development of International Standards, Guides and Recom-
ment from the measurement of machine crosshead displace-
mendations issued by the World Trade Organization Technical
ment requires correcting for machine compliance.
Barriers to Trade (TBT) Committee.
3.1.4.2 Discussion—In this test method, specimen
deflection, u, is used as the reference displacement signal.
2. Referenced Documents
However, if specimen deflection is unavailable or not
2
2.1 ASTM Standards:
measured, punch displacement, v, may be used instead.
E8/E8MTest Methods for Tension Testing of Metallic Ma-
3.1.5 small punch (SP) bulge test, n—mechanical test con-
terials
sisting of loading a small disk-shaped specimen clamped
E21TestMethodsforElevatedTemperatureTensionTestsof
between two dies by means of a hemispherical-shaped punch,
Metallic Materials
deforming it to failure, and analyzing the resulting F-u curve.
E74Practices for Calibration and Verification for Force-
3.1.6 specimen deflection, u [L], n—displacement of a point
Measuring Instruments
at the center of the specimen opposite to the punch during the
E177Practice for Use of the Terms Precision and Bias in
small punch (SP) bulge test.
ASTM Test Methods
4. Significance and Use
1
ThistestmethodisunderthejurisdictionofASTMCommitteeE10onNuclear
4.1 The safety margins provided in the design for a compo-
Technology and Applications and is the direct responsibility of Subcommittee
nent or structure can be reduced throughout its service life by
E10.02 on Behavior and Use of Nuclear Structural Materials.
aging. Aging is the process by which the physical and
Current edition approved July 1, 2020. Published August 2020. DOI: 10.1520/
E3205-20.
mechanical characteristics of component or structure materials
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
change with time or use; this process may proceed by a single
contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
aging mechanism or a combination of several aging mecha-
Standards volume information, refer to the standard’s Document Summary page on
the ASTM website. nisms.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1

---------------------- Page: 1 ----------------------
E3205 − 20
4.2 Th
...

Questions, Comments and Discussion

Ask us and Technical Secretary will try to provide an answer. You can facilitate discussion about the standard in here.

This May Also Interest You

ASTM
ASTM E2662-15(2022)(Practice)
Standard Practice for Radiographic Examination of Flat Panel Composites and Sandwich Core Materials Used in Aerospace Applications

SIGNIFICANCE AND USE
5.1 Radiographic examination may be used during product and process design optimization, on line process control, after manufacture inspection, and in service inspection. In addition to verifying structural placement, radiographic examination can be used in the case of honeycomb core materials to detect node bonds, core-to-core splices, and core-to-structure splices. Radiographic examination is especially well suited for detecting sub-surface flaws. The general types of defects detected by radiographic examination include blown core, core corrosion, damaged filaments, density variation, entrapped fluid, fiber debonding, fiber misalignment, foreign material, fractures, inclusions, micro-cracks, node bond failure, porosity/voids, and thickness variation.  
5.2 Factors that influence image formation and X-ray attenuation in radiographic examination, and which are relevant to interpreting the images for the conditions of interest, should be included in the examination request. Examples include, but not limited to, the following: laminate (matrix and fiber) material, lay-up geometry, fiber volume fraction (flat panels); facing material, core material, facing stack sequence, core geometry (cell size); core density, facing void content, adhesive void content, and facing volume percent reinforcement (sandwich core materials); overall thickness, specimen alignment, and specimen geometry relative to the beam (flat panels and sandwich core materials).  
5.3 Information regarding discontinuities that are detectable using radiographic examination methods can be found in Guide E2533.
SCOPE
1.1 This practice is intended to be used as a supplement to Practices E1742, E1255, E2033, and E2698.  
1.2 This practice describes procedures for radiographic examination of flat panel composites and sandwich core materials made entirely or in part from fiber-reinforced polymer matrix composites. Radiographic examination is: a) Film Radiography (RT), b) Computed Radiography (CR) with Imaging Plate, c) Digital Radiography (DR) with Digital Detector Array’s (DDA), and d) Radioscopic (RTR) Real Time Radiography with a detection system such as an Image Intensifier. The composite materials under consideration typically contain continuous high modulus fibers (> 20 GPa), such as those listed in 1.4.  
1.3 This practice describes established radiographic examination methods that are currently used by industry that have demonstrated utility in quality assurance of flat panel composites and sandwich core materials during product process design and optimization, process control, after manufacture inspection, in service examination, and health monitoring. Additional guidance can be found in E2533, Guide for Nondestructive Testing of Polymer Matrix Composites Used in Aerospace.  
1.4 This practice has utility for examination of flat panel composites and sandwich constructions containing, but not limited to, bismaleimide, epoxy, phenolic, poly(amide imide), polybenzimidazole, polyester (thermosetting and thermoplastic), poly(ether ether ketone), poly(ether imide), polyimide (thermosetting and thermoplastic), poly(phenylene sulfide), or polysulfone matrices; and alumina, aramid, boron, carbon, glass, quartz, or silicon carbide fibers. Typical as-fabricated geometries include uniaxial, cross ply and angle ply laminates; as well as honeycomb core sandwich constructions.  
1.5 This practice does not specify accept-reject criteria and is not intended to be used as a means for approving flat panel composites or sandwich core materials for service.  
1.6 To ensure proper use of the referenced standards, there are recognized nondestructive testing (NDT) specialists that are certified according to industry and company NDT specifications. It is recommended that a NDT specialist be a part of any composite component design, quality assurance, in service maintenance or damage examination.  
1.7 This standard does not purport to address a...

  • Standard
    5 pages
    English language
    sale 15% off
ASTM
ASTM F3572-22(Practice)
Standard Practice for Additive Manufacturing – General Principles – Part Classifications for Additive Manufactured Parts Used in Aviation

SCOPE
1.1 This practice is intended to be used to assign part classifications across the aviation industries that use AM to produce parts.  
1.2 This practice is applicable to all AM technologies defined in ISO/ASTM 52900 used in aviation.  
1.3 This practice is intended to be used to establish a metric for AM parts in downstream documents.  
1.4 This practice is not intended to establish criteria for any downstream processes, but rather to establish a metric that these processes can use.  
1.5 The part classification metric could be utilized by the engineering, procurement, non-destructive inspection, testing, qualification, or certification processes used for AM aviation parts.  
1.6 The classification scheme in this practice establishes a consistent methodology to define and communicate the consequence of failure associated with AM aviation parts.  
1.7 This practice is not intended to supersede the requirements and definitions of the applicable regulations or policies, including but not limited to the ones listed in Annex A1.  
1.8 Tables A1.1-A1.3 align the existing regulations and guidance with the four part classes established herein. However, this alignment should not be construed as an alignment of the existing regulations to each other.  
1.9 The material or process, or both, in general does not affect the consequence of failure of a part, therefore the classification scheme defined in this document may be used outside AM.  
1.10 The user of this standard should not assume regulators’ endorsement of this standard as accepted mean of compliance.  
1.11 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.  
1.12 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.

  • Standard
    8 pages
    English language
    sale 15% off
ASTM
ASTM F2156-17(2022)(Test Method)
Standard Test Method for Measuring Optical Distortion in Transparent Parts Using Grid Line Slope

SIGNIFICANCE AND USE
5.1 Transparent parts, such as aircraft windshields, canopies, cabin windows, and visors, shall be measured for compliance with optical distortion specifications using this test method. This test method is suitable for assessing optical distortion of transparent parts as it relates to the visual perception of distortion. It is not suitable for assessing distortion as it relates to pure angular deviation of light as it passes through the part. Either Test Method F801 or Practice F733 is appropriate and shall be used for this latter application. This test method is not recommended for raw material.
SCOPE
1.1 When an observer looks through an aerospace transparency, relative optical distortion results, specifically in thick, highly angled, multilayered plastic parts. Distortion occurs in all transparencies but is especially critical to aerospace applications such as combat and commercial aircraft windscreens, canopies, or cabin windows. This is especially true during operations such as takeoff, landing, and aerial refueling. It is critical to be able to quantify optical distortion for procurement activities.  
1.2 This test method covers the apparatus and procedures that are suitable for measuring the grid line slope (GLS) of transparent parts, including those that are small or large, thin or thick, flat or curved, or already installed. This test method is not recommended for raw material.  
1.3 The values stated in SI units are to be regarded as standard. No other units of measurement are included in this standard.  
1.3.1 Exception—The values given in parentheses are for information only.  
1.4 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.  
1.5 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.

  • Standard
    6 pages
    English language
    sale 15% off
ASTM
ASTM F801-21(Test Method)
Standard Test Method for Measuring Optical Angular Deviation of Transparent Parts

SIGNIFICANCE AND USE
5.1 One of the measures of optical quality of a transparent part is its angular deviation. It is possible that excessive angular deviation, or variations in angular deviation throughout the part, will result in visible distortion of scenes viewed through the part. Angular deviation, its detection, and quantification are of extreme importance in the area of certain aircraft transparency applications, that is, aircraft equipped with Heads-up Displays (HUD). It is possible that HUDs will require stringent control over the optics of the portion of the transparency (windscreen or canopy) which lies between the HUD combining glass and the external environment. Military aircraft equipped with HUDs or similar devices require precise knowledge of the effects of the windscreen or canopy on image position in order to maintain weapons aiming accuracy.  
5.2 Two optical parameters have the effect of changing image position. The first, lateral displacement, is inherent in any transparency which is tilted with respect to the line of sight. The effect of lateral displacement is constant over distance, and seldom exceeds a fraction of an inch. The second parameter, angular deviation, is usually caused by a wedginess or nonparallelism of the transparency surfaces. The effect of angular deviation is related to the tangent of the angle of deviation, thus the magnitude of the image position displacement increases as does the distance between image and transparency. The quantification of angular deviation is then the more critical of the two parameters. Both parameters are illustrated in Fig. X1.1.
SCOPE
1.1 This test method covers measuring the angular deviation of a light ray imposed by transparent parts such as aircraft windscreens and canopies. The results are uncontaminated by the effects of lateral displacement, and it is possible to perform the procedure in a relatively short optical path length. This is not intended as a referee standard. It is one convenient method for measuring angular deviations through transparent windows.  
1.2 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.  
1.3 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.

  • Standard
    9 pages
    English language
    sale 15% off
  • Standard
    9 pages
    English language
    sale 15% off
ASTM
ASTM E2582-21(Practice)
Standard Practice for Infrared Flash Thermography of Composite Panels and Repair Patches Used in Aerospace Applications

SIGNIFICANCE AND USE
5.1 Typically, FT is used to identify flaws that occur in the manufacture of composite structures, or to identify and track flaws that develop during the service lifetime of the structure. Flaws detected with FT include delamination, disbonds, voids, inclusions, foreign object debris, porosity, or the presence of fluid that is in contact with the backside of the inspection surface. For example, the effect of variable ply number (or thickness), bridging, and an insert simulating delamination on heat flow into a composite is shown in Fig. 1 (left). Bridging (Fig. 1, right) or delaminated areas show up as hot spots due to discontinuous heat flow, causing heating to be localized close to the inspection surface. With dedicated signal processing and the use of representative test samples, characterization of flaw depth and size, or measurement of component thickness and thermal diffusivity, may be performed.
FIG. 1 Variation of Heat Flow Into a Composite With Variable Ply Thickness (Scenarios 1, 3, and 4), Bridging (Scenario 2) And an Insert (Scenario 5) (Left), And a Post Layup Line Scan Showing Bright Spots Attributed to Bridging (Right) (Courtesy of NASA Langley Research Center)  
5.2 Since FT is based on the diffusion of thermal energy from the inspection surface of the specimen to the opposing surface (or the depth plane of interest), the practice requires that data acquisition allows sufficient time for this process to occur, and that at the completion of the acquisition process, the radiated surface temperature signal collected by the IR camera is strong enough to be distinguished from spurious IR contributions from background sources or system noise.  
5.3 This method is based on accurate detection of changes in the emitted IR energy emanating from the inspection surface during the cooling process. As the emissivity of the inspection surface falls below that of an ideal blackbody (blackbody emissivity = 1), the signal detected by the IR camera may include comp...
SCOPE
1.1 This practice describes a procedure for detecting subsurface flaws in composite panels and repair patches using Flash Thermography (FT), in which an infrared (IR) camera is used to detect anomalous cooling behavior of a sample surface after it has been heated with a spatially uniform light pulse from a flash lamp array.  
1.2 This practice describes established FT test methods that are currently used by industry, and have demonstrated utility in quality assurance of composite structures during post-manufacturing and in-service examinations.  
1.3 This practice has utility for testing of polymer composite panels and repair patches containing, but not limited to, bismaleimide, epoxy, phenolic, poly(amide imide), polybenzimidazole, polyester (thermosetting and thermoplastic), poly(ether ether ketone), poly(ether imide), polyimide (thermosetting and thermoplastic), poly(phenylene sulfide), or polysulfone matrices; and alumina, aramid, boron, carbon, glass, quartz, or silicon carbide fibers. Typical as-fabricated geometries include uniaxial, cross ply, and angle ply laminates; as well as honeycomb core sandwich core materials.  
1.4 This practice has utility for testing of ceramic matrix composite panels containing, but not limited to, silicon carbide, silicon nitride, and carbon matrix and fibers.  
1.5 This practice applies to polymer or ceramic matrix composite structures with inspection surfaces that are sufficiently optically opaque to absorb incident light, and that have sufficient emissivity to allow monitoring of the surface temperature with an IR camera. Excessively thick samples, or samples with low thermal diffusivities, require long acquisition periods and yield weak signals approaching background and noise levels, and may be impractical for this technique.  
1.6 This practice applies to detection of flaws in a composite panel or repair patch, or at the bonded interface between the panel and a supporting ...

  • Standard
    7 pages
    English language
    sale 15% off
  • Standard
    7 pages
    English language
    sale 15% off
ASTM
ASTM F3498-21(Practice)
Standard Practice for Developing Simplified Fatigue Load Spectra

SIGNIFICANCE AND USE
4.1 This standard practice provides one means for determining fatigue load spectra for aeroplane durability assessments. This information can be used in conjunction with Specification F3115/F3115M, Section 5, Load Considerations.  
4.1.1 Users of this practice may propose alternate spectra, subject to the approval of their CAA.  
4.2 The methods are applicable to the durability evaluation of wings of small aeroplanes. Additional calculation (such as methods noted in ACE-100-01) are needed to properly develop load spectra for fatigue evaluation of empennage and/or configurations with canards (or forward wings) and/or winglets (or tip fins), fuselage, and potentially other components, with approval from appropriate regulatory agency.  
4.3 Much of the material presented herein is directly taken from AC 23-13A. The FAA developed the flight load spectra, presented herein, based on a statistical analysis of the data presented in DOT/FAA/CT-91/20. The ground load spectra are directly from AFS-120-73-2.  
4.4 The flight load spectra, presented in Section 7, includes an adjustment (1.5 standard deviations) to the average measured load frequency. The adjustment accounts for the variability in the loading spectra experienced by individual aeroplanes, as well as across aeroplane types. The magnitude of the adjustment was selected to maintain the probability that a component will reach its safe-life without a detectable fatigue crack established by scatter factor (see paragraph 2–15 of AC 23-13A).
SCOPE
1.1 This practice provides data to develop simplified loading spectra that can be used to perform structural durability analysis for aeroplanes, specifically for wings of small aeroplanes. The material was developed through open consensus of international experts in general aviation. The information was created by focusing on Level 1, 2, 3, and 4 Normal Category aeroplanes. The content may be more broadly applicable; it is the responsibility of the applicant to substantiate broader applicability as a specific means of compliance.  
1.2 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable civil aviation authorities, or CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this standard (whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to the ASTM Committee F44 web page (www.astm.org/COMMITTEE/F44.htm).  
1.3 The values stated in inch-pound units are to be regarded as standard. No other units of measurement are included in this standard.  
1.4 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.  
1.5 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.

  • Standard
    35 pages
    English language
    sale 15% off
ASTM
ASTM F311-08(2020)(Practice)
Standard Practice for Processing Aerospace Liquid Samples for Particulate Contamination Analysis Using Membrane Filters

SIGNIFICANCE AND USE
4.1 This practice provides for the processing of liquid samples obtained in accordance with Practice F302 and Practices F303. It will provide the optimum sample processing for visual contamination methods such as Method F312, and Test Method F314.
SCOPE
1.1 This practice covers the processing of liquids in preparation for particulate contamination analysis using membrane filters and is limited only by the liquid-to-membrane filter compatibility.  
1.2 The practice covers the procedure for filtering a measured volume of liquid through a membrane filter. When this practice is used, the particulate matter will be randomly distributed on the filter surface for subsequent contamination analysis methods.  
1.3 The practice describes procedures to allow handling particles in the size range between 2 and 1000 μm with minimum losses during handling.  
1.4 The values stated in SI units are to be regarded as standard. No other units of measurement are included in this standard.  
1.5 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.

  • Standard
    3 pages
    English language
    sale 15% off
ASTM
ASTM F331-13(2020)(Test Method)
Standard Test Method for Nonvolatile Residue of Solvent Extract from Aerospace Components (Using Flash Evaporator)

ABSTRACT
This test method covers the determination of non-volatile matter, that is, residue on evaporation, in solvent extract from aerospace components, using a rotary flash evaporator. The summary of the test method, the apparatus for testing, reagents and materials for testing, and procedure for testing are all presented in details.
SCOPE
1.1 This test method covers the determination of nonvolatile matter, that is, residue on evaporation, in solvent extract from aerospace components, using a rotary flash evaporator.  
1.2 The procedure for extraction from components is described in practices such as Practice F303. Before subjecting the extract to the following method, it should be processed to remove the insoluble particulate in accordance with Practice F311 (Note 1). Particle count analysis of the removed particulate may then be performed in accordance with Test Method F312. If particulate is not removed from the extract prior to performing this method, this should be noted on the test report.
Note 1: Membrane filters with a maximum extractable content of 0.5 weight % should be used on samples to be processed by this test method. Conventional membranes contain 5 to 10 % extractables. For obtaining very low background levels, consideration should be given to using membranes without grid marks.  
1.3 The values stated in SI units are to be regarded as standard.  
1.4 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.  
1.5 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.

  • Standard
    3 pages
    English language
    sale 15% off
ASTM
ASTM E3166-20e1(Guide)
Standard Guide for Nondestructive Examination of Metal Additively Manufactured Aerospace Parts After Build

SIGNIFICANCE AND USE
4.1 Metal parts made by additive manufacturing differ from their traditional metal counterparts made by forging, casting, or welding. Additive manufacturing produces layers melted or sintered on top of each other. The part’s shape is controlled by a computer as well as by the layers. The computer directs energy from a laser or electron beam onto a powder bed or wire input material. These processing approaches have the potential of creating flaws that are undesirable in the as-built or finished part. In general, processing parameter anomalies and disruptions during a build may induce such “flaws.” Flaws can also be introduced because of contaminants present in the input material.  
4.2 Established NDT procedures such as those given in ASTM E07 standards are the basis for the NDT procedures discussed in this guide. These NDT procedures are used to inspect production parts before or after post-processing or finishing operations, or after receipt of finished parts by the end user prior to installation. The NDT procedures described in this guide are based on procedures developed for conventionally manufactured cast, wrought, or welded production parts.  
4.3 Application of the NDT procedures discussed in this guide is intended to reduce the likelihood of material or component failure, thus mitigating or eliminating the attendant risks associated with loss of function, and possibly, the loss of ground support personnel, crew, or mission.  
4.4 Input Materials—The input materials covered in this guide consist of, but are not limited to, ones made from aluminum alloys, titanium alloys, nickel-based alloys, cobalt-chromium alloys, and stainless steels. Input materials are either powders or wire.
Note 3: When electron beams are used, the beam couples effectively with any electrically conductive material, including aluminum and copper-based alloys.  
4.4.1 Powders—High-quality powders required for AM process are produced by (1) plasma atomization, (2) inert gas atomizati...
SCOPE
1.1 This guide discusses the use of established and emerging nondestructive testing (NDT) procedures used to inspect metal parts made by additive manufacturing (AM).  
1.2 The NDT procedures covered produce data related to and affected by microstructure, part geometry, part complexity, surface finish, and the different AM processes used.  
1.3 The parts tested by the procedures covered in this guide are used in aerospace applications; therefore, the inspection requirements for discontinuities and inspection points in general are different and more stringent than for materials and components used in non-aerospace applications.  
1.4 The metal materials under consideration include, but are not limited to, aluminum alloys, titanium alloys, nickel-based alloys, cobalt-chromium alloys, and stainless steels.  
1.5 The manufacturing processes considered use powder and wire feedstock, and laser or electron energy sources. Specific powder bed fusion (PBF) and directed energy deposition (DED) processes are discussed.  
1.6 This guide discusses NDT of parts after they have been fabricated. Parts will exist in one of three possible states: (1) raw, as-built parts before post-processing (heat treating, hot isostatic pressing, machining, etc.), (2) intermediately machined parts, or (3) finished parts after all post-processing is completed.  
1.7 The NDT procedures discussed in this guide are used by cognizant engineering organizations to detect both surface and volumetric flaws in as-built (raw) and post-processed (finished) parts.  
1.8 The NDT procedures discussed in this guide are computed tomography (CT, Section 7, including microfocus CT), eddy current testing (ET, Section 8), optical metrology (MET, Section 9), penetrant testing (PT, Section 10), process compensated resonance testing (PCRT, Section 11), radiographic testing (RT, Section 12), infrared thermography (IRT, Section 13), and ultrasonic testing (UT, Section 14)....

  • Guide
    63 pages
    English language
    sale 15% off
ASTM
ASTM A370-23(Test Method)
Standard Test Methods and Definitions for Mechanical Testing of Steel Products

SIGNIFICANCE AND USE
4.1 The primary use of these test methods is testing to determine the specified mechanical properties of steel, stainless steel, and related alloy products for the evaluation of conformance of such products to a material specification under the jurisdiction of ASTM Committee A01 and its subcommittees as designated by a purchaser in a purchase order or contract.  
4.1.1 These test methods may be and are used by other ASTM Committees and other standards writing bodies for the purpose of conformance testing.  
4.1.2 The material condition at the time of testing, sampling frequency, specimen location and orientation, reporting requirements, and other test parameters are contained in the pertinent material specification or in a general requirement specification for the particular product form.  
4.1.3 Some material specifications require the use of additional test methods not described herein; in such cases, the required test method is described in that material specification or by reference to another appropriate test method standard.  
4.2 These test methods are also suitable to be used for testing of steel, stainless steel and related alloy materials for other purposes, such as incoming material acceptance testing by the purchaser or evaluation of components after service exposure.  
4.2.1 As with any mechanical testing, deviations from either specification limits or expected as-manufactured properties can occur for valid reasons besides deficiency of the original as-fabricated product. These reasons include, but are not limited to: subsequent service degradation from environmental exposure (for example, temperature, corrosion); static or cyclic service stress effects, mechanically-induced damage, material inhomogeneity, anisotropic structure, natural aging of select alloys, further processing not included in the specification, sampling limitations, and measuring equipment calibration uncertainty. There is statistical variation in all aspects of mechanical testin...
SCOPE
1.1 These test methods2 cover procedures and definitions for the mechanical testing of steels, stainless steels, and related alloys. The various mechanical tests herein described are used to determine properties required in the product specifications. Variations in testing methods are to be avoided, and standard methods of testing are to be followed to obtain reproducible and comparable results. In those cases in which the testing requirements for certain products are unique or at variance with these general procedures, the product specification testing requirements shall control.  
1.2 The following mechanical tests are described:    
Sections  
Tension  
7 to 14  
Bend  
15  
Hardness  
16  
Brinell  
17  
Rockwell  
18  
Portable  
19  
Impact  
20 to 30  
Keywords  
32  
1.3 Annexes covering details peculiar to certain products are appended to these test methods as follows:    
Annex  
Bar Products  
Annex A1  
Tubular Products  
Annex A2  
Fasteners  
Annex A3  
Round Wire Products  
Annex A4  
Significance of Notched-Bar Impact Testing  
Annex A5  
Converting Percentage Elongation of Round Specimens to
Equivalents for Flat Specimens  
Annex A6    
Testing Multi-Wire Strand  
Annex A7  
Rounding of Test Data  
Annex A8  
Methods for Testing Steel Reinforcing Bars  
Annex A9  
Procedure for Use and Control of Heat-cycle Simulation  
Annex A10  
1.4 The values stated in inch-pound units are to be regarded as standard. The values given in parentheses are mathematical conversions to SI units that are provided for information only and are not considered standard.  
1.5 When these test methods are referenced in a metric product specification, the yield and tensile values may be determined in inch-pound (ksi) units then converted into SI (MPa) units. The elongation determined in inch-pound gauge lengths of 2 in. or 8 in. may be report...

  • Standard
    51 pages
    English language
    sale 15% off
  • Standard
    51 pages
    English language
    sale 15% off