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ASTM E2580-07

(Practice)

Standard Practice for Ultrasonic Testing of Flat Panel Composites and Sandwich Core Materials Used in Aerospace Applications

Standard Practice for Ultrasonic Testing of Flat Panel Composites and Sandwich Core Materials Used in Aerospace Applications

SIGNIFICANCE AND USE
This practice is intended primarily for the testing of flat panel composites and sandwich core panels to an acceptance criteria most typically specified in a purchase order or other contractual document.
Basis of Application—There are areas in this practice that require agreement between the cognizant engineering organization and the supplier, or specific direction from the cognizant engineering organization.
SCOPE
1.1 This practice establishes two procedures for ultrasonic testing (UT) of flat panel composites and flat sandwich core panels (parallel surfaces). Typical as-fabricated lay-ups include uniaxial, cross ply and angle ply laminates; as well as honeycomb sandwich core materials. These procedures can be used throughout the life cycle of the materials; product and process design optimization, on line process control, after manufacture inspection, and in service inspection. Contact methods such as angle-beam techniques using shear waves, or surface-beam techniques using Lamb waves, are not discussed.
1.2 Ultrasonic testing is a common sub surface method for detection of laminar oriented discontinuities. Two techniques can be considered based on panel surface accessibility; pulse echo for one sided and through transmission (bubblers/squirters) for two sided. As used in this practice, both require the use of a pulsed straight-beam ultrasonic longitudinal wave followed by observing indications of either the reflected (pulse-echo) or received (through transmission) wave. The general types of anomalies detected by both techniques include foreign materials, delamination, disbond/un-bond, fiber de-bonding, inclusions, porosity, and voids.
1.3 This practice provides two ultrasonic test procedures. Each has its own merits and requirements for inspection and shall be selected as agreed upon in a contractual document.
1.3.1 Test Procedure A, Pulse Echo (non-contacting and contacting) is at a minimum a single transducer transmitting and receiving a longitudinal wave in the range of 0.5 to 20 MHz (see Fig. 1). This procedure requires access to only one side of the specimen. This procedure can be conducted by automated or manual means. Automated and manual test results may be imaged or recorded.
1.3.2 Test Procedure B, Through Transmission is a combination of two transducers. One transmits a longitudinal wave and the other receives the longitudinal wave in the range of 0.5 MHz to 20 MHz (see Fig. 2). This procedure requires access to both sides of the specimen. This procedure is automated and the examination results are recorded.
1.4 This practice does not specify accept-reject criteria.
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 and health practices and determine the applicability of regulatory limitations prior to use.

General Information

Status
Historical
Publication Date
30-Jun-2007
ICS
49.035 - Components for aerospace construction
Technical Committee
E07 - Nondestructive Testing
Drafting Committee
E07.06 - Ultrasonic Method
Current Stage
Ref Project

Relations

Replaced By
ASTM E2580-12 - Standard Practice for Ultrasonic Testing of Flat Panel Composites and Sandwich Core Materials Used in Aerospace Applications
Effective Date
15-Jun-2012
Referred By
ASTM E543-21 - Standard Specification for Agencies Performing Nondestructive Testing
Effective Date
01-Jul-2007
Referred By
ASTM E3370-23 - Standard Practice for Matrix Array Ultrasonic Testing of Composites, Sandwich Core Constructions, and Metals
Effective Date
01-Jul-2007
Referred By
ASTM E2533-21 - Standard Guide for Nondestructive Examination of Polymer Matrix Composites Used in Aerospace Applications
Effective Date
01-Jul-2007
Referred By
ASTM E2981-21 - Standard Guide for Nondestructive Examination of Composite Overwraps in Filament Wound Pressure Vessels Used in Aerospace Applications
Effective Date
01-Jul-2007

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ASTM E2580-07 - Standard Practice for Ultrasonic Testing of Flat Panel Composites and Sandwich Core Materials Used in Aerospace ApplicationsASTM E2580-07 - Standard Practice for Ultrasonic Testing of Flat Panel Composites and Sandwich Core Materials Used in Aerospace Applications
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ASTM E2580-07 - Standard Practice for Ultrasonic Testing of Flat Panel Composites and Sandwich Core Materials Used in Aerospace Applications
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Standards Content (Sample)

NOTICE: This standard has either been superseded and replaced by a new version or withdrawn.
Contact ASTM International (www.astm.org) for the latest information
Designation:E2580–07
Standard Practice for
Ultrasonic Testing of Flat Panel Composites and Sandwich
1
Core Materials Used in Aerospace Applications
This standard is issued under the fixed designation E2580; the number immediately following the designation indicates the year of
original adoption or, in the case of revision, the year of last revision. A number in parentheses indicates the year of last reapproval. A
superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
1. Scope both sides of the specimen. This procedure is automated and
the examination results are recorded.
1.1 This practice establishes two procedures for ultrasonic
1.4 This practice does not specify accept-reject criteria.
testing (UT) of flat panel composites and flat sandwich core
1.5 This standard does not purport to address all of the
panels (parallel surfaces).Typical as-fabricated lay-ups include
safety concerns, if any, associated with its use. It is the
uniaxial, cross ply and angle ply laminates; as well as honey-
responsibility of the user of this standard to establish appro-
comb sandwich core materials. These procedures can be used
priate safety and health practices and determine the applica-
throughout the life cycle of the materials; product and process
bility of regulatory limitations prior to use.
design optimization, on line process control, after manufacture
inspection, and in service inspection. Contact methods such as
2. Referenced Documents
angle-beam techniques using shear waves, or surface-beam
2
2.1 ASTM Standards:
techniques using Lamb waves, are not discussed.
C274 Terminology of Structural Sandwich Constructions
1.2 Ultrasonic testing is a common sub surface method for
D3878 Terminology for Composite Materials
detection of laminar oriented discontinuities. Two techniques
D5687/D5687M Guide for Preparation of Flat Composite
can be considered based on panel surface accessibility; pulse
Panels with Processing Guidelines for Specimen Prepara-
echo for one sided and through transmission (bubblers/
tion
squirters) for two sided. As used in this practice, both require
E114 Practice for Ultrasonic Pulse-Echo Straight-Beam Ex-
the use of a pulsed straight-beam ultrasonic longitudinal wave
amination by the Contact Method
followed by observing indications of either the reflected
E543 Specification for Agencies Performing Nondestruc-
(pulse-echo) or received (through transmission) wave. The
tive Testing
general types of anomalies detected by both techniques include
E1309 Guide for Identification of Fiber-Reinforced
foreign materials, delamination, disbond/un-bond, fiber de-
Polymer-Matrix Composite Materials in Databases
bonding, inclusions, porosity, and voids.
E1316 Terminology for Nondestructive Examinations
1.3 This practice provides two ultrasonic test procedures.
E1434 Guide for Recording Mechanical Test Data of Fiber-
Each has its own merits and requirements for inspection and
Reinforced Composite Materials in Databases
shall be selected as agreed upon in a contractual document.
E1471 Guide for Identification of Fibers, Fillers, and Core
1.3.1 Test Procedure A, Pulse Echo (non-contacting and
Materials in Computerized Material Property Databases
contacting), is at a minimum a single transducer transmitting
3
2.2 SAE Standards:
and receiving a longitudinal wave in the range of 0.5 to 20
ARP 5605 Solid Composite Laminate NDI Reference Stan-
MHz (see Fig. 1). This procedure requires access to only one
dards, Issued 2001-09
side of the specimen. This procedure can be conducted by
ARP 5606 Composite Honeycomb NDI Reference Stan-
automated or manual means. Automated and manual test
dards, Issued 2001-09
results may be imaged or recorded.
4
2.3 AIA Standard:
1.3.2 Test Procedure B, Through Transmission, is a combi-
NAS-410 Nondestructive Testing Certification of Personnel
nation of two transducers. One transmits a longitudinal wave
and the other receives the longitudinal wave in the range of 0.5
2
MHz to 20 MHz (see Fig. 2).This procedure requires access to
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
Standards volume information, refer to the standard’s Document Summary page on
1
This practice is under the jurisdiction of ASTM Committee E07 on Nonde- the ASTM website.
3
structive Testing and is the direct responsibility of Subcommittee E07.06 on Available from Society of Automotive Engineers (SAE), 400 Commonwealth
Ultrasonic Method. Dr., Warrendale, PA 15096-0001, http://www.sae.org.
4
Current edition approved July 1, 2007. Published July 2007. DOI: 10.1520/ Available fromAerospace IndustriesAssociation ofAmerica, Inc. (AIA), 1000
E2580-07. WilsonBlvd.,Suite1700,Arlington,VA22209-3928,http://www.aia-aerospace.org.
Copyright © ASTM Intern
...

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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.  
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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.  
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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.  
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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.  
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Standard Practice for Ultrasonic Testing of Flat Panel Composites and Sandwich Core Materials Used in Aerospace Applications

SIGNIFICANCE AND USE
5.1 This practice is intended primarily for the testing of flat panel composites and sandwich core panels to an acceptance criteria most typically specified in a purchase order or other contractual document.  
5.2 Basis of Application—There are areas in this practice that require agreement between the cognizant engineering organization and the supplier, or specific direction from the cognizant engineering organization.
SCOPE
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1.3 This practice provides two ultrasonic test procedures. Each has its own merits and requirements for inspection and shall be selected as agreed upon in a contractual document.  
1.3.1 Test Procedure A, Pulse Echo (non-contacting and contacting), is at a minimum a single transducer transmitting and receiving a longitudinal wave in the range of 0.5 to 20 MHz (see Fig. 1). This procedure requires access to only one side of the specimen. This procedure can be conducted by automated or manual means. Automated and manual test results may be imaged or recorded.
FIG. 1 Test Procedure A, Pulse Echo Apparatus Set-up  
1.3.2 Test Procedure B, Through Transmission, is a combination of two transducers. One transmits a longitudinal wave and the other receives the longitudinal wave in the range of 0.5 MHz to 20 MHz (see Fig. 2). This procedure requires access to both sides of the specimen. This procedure is automated and the examination results are recorded.
FIG. 2 Test Procedure B, Through Transmission Apparatus Set-up  
1.4 This practice does not specify accept-reject criteria.  
1.5 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, environmental practices and determine the applicability of regulatory limitations prior to use.  
1.6 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.

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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.  
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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.  
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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...

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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.

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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.

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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.

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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 ...

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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.

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