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ASTM F331-00

(Test Method)

Standard Test Method for Nonvolatile Residue of Solvent Extract from Aerospace Components (Using Flash Evaporator)

Standard Test Method for Nonvolatile Residue of Solvent Extract from Aerospace Components (Using Flash Evaporator)

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 PracticesF303 and Practice F305. In cases where analysis of particulate contamination is also required, prior to subjecting the extract to the following method, it should be processed in accordance with Practice F311 (Note 1). Particle count analysis should then be performed in accordance with Method F312. Identification of particulate material, if required, may be performed by Test Method F314.  
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 This standard does not purport to address all of the safety problems, 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
09-May-2000
ICS
49.035 - Components for aerospace construction
Technical Committee
E21 - Space Simulation and Applications of Space Technology
Drafting Committee
E21.05 - Contamination
Current Stage
Ref Project

Relations

Replaced By
ASTM F331-05 - Standard Test Method for Nonvolatile Residue of Solvent Extract from Aerospace Components (Using Flash Evaporator)
Effective Date
01-Nov-2005
Referred By
ASTM G131-96(2023)e1 - Standard Practice for Cleaning of Materials and Components by Ultrasonic Techniques
Effective Date
10-May-2000
Referred By
ASTM G144-01(2022) - Standard Test Method for Determination of Residual Contamination of Materials and Components by Total Carbon Analysis Using a High Temperature Combustion Analyzer
Effective Date
10-May-2000
Referred By
ASTM G120-15(2023) - Standard Practice for Determination of Soluble Residual Contamination by Soxhlet Extraction
Effective Date
10-May-2000
Referred By
ASTM G93/G93M-19 - Standard Guide for Cleanliness Levels and Cleaning Methods for Materials and Equipment Used in Oxygen-Enriched Environments
Effective Date
10-May-2000
Referred By
ASTM G136-03(2023)e1 - Standard Practice for Determination of Soluble Residual Contaminants in Materials by Ultrasonic Extraction
Effective Date
10-May-2000
Referred By
ASTM G121-18 - Standard Practice for Preparation of Contaminated Test Coupons for the Evaluation of Cleaning Agents
Effective Date
10-May-2000

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ASTM F331-00 - Standard Test Method for Nonvolatile Residue of Solvent Extract from Aerospace Components (Using Flash Evaporator)ASTM F331-00 - Standard Test Method for Nonvolatile Residue of Solvent Extract from Aerospace Components (Using Flash Evaporator)
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ASTM F331-00 - Standard Test Method for Nonvolatile Residue of Solvent Extract from Aerospace Components (Using Flash Evaporator)
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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:F331–00
Standard Test Method for
Nonvolatile Residue of Solvent Extract from Aerospace
Components (Using Flash Evaporator)
This standard is issued under the fixed designation F 331; 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 (e) indicates an editorial change since the last revision or reapproval.
1. Scope F 311 PracticeforProcessingAerospaceLiquidSamplesfor
Particulate Contamination Analysis Using Membrane Fil-
1.1 Thistestmethodcoversthedeterminationofnonvolatile
ters
matter, that is, residue on evaporation, in solvent extract from
F 312 Methods for Microscopical Sizing and Counting
aerospace components, using a rotary flash evaporator.
Particles from Aerospace Fluids on Membrane Filters
1.2 The procedure for extraction from components is de-
F 314 Test Methods for Identification of Metallic and Fi-
scribed in practices such as Practices F 303 and Practice F 305.
brous Contaminants in Aerospace Fluids
In cases in which analysis of particulate contamination is also
2.2 Military Standard:
required,beforesubjectingtheextracttothefollowingmethod,
MIL-STD-1246 Product Cleanliness Levels and Contami-
it should be processed in accordance with Practice F 311 (Note
nation Control Program
1). Particle count analysis should then be performed in accor-
dance with Methods F 312. Identification of particulate mate-
3. Summary of Test Method
rial, if required, may be performed by Test Method F 314.
3.1 A sample of fluid or the filtrate (Note 1) from a sample
NOTE 1—Membrane filters with a maximum extractable content of 0.5
of extract from components is evaporated as necessary to
weight % should be used on samples to be processed by this test method.
approximately 20 mLin a flash evaporator. The residue is then
Conventional membranes contain 5 to 10 % extractables. For obtaining
transferred to a foil dish and the evaporation completed by
very low background levels, consideration should be given to using
heating to a constant weight.
membranes without grid marks.
1.3 This standard does not purport to address all of the
4. Apparatus
safety concerns, if any, associated with its use. It is the
4.1 Oven, gravity convection provided with suitable ther-
responsibility of the user of this standard to establish appro-
mometer and a temperature range suitable for the solvent being
priate safety and health practices and determine the applica-
evaporated.
bility of regulatory limitations prior to use.
4.2 Analytical Balance, single pan or magnetically damped
double pan.
2. Referenced Documents
NOTE 2—Sensitivity shall be suitable to obtain the required precision
2.1 ASTM Standards:
noted in 9.1.
D 1193 Specification for Reagent Water
D 2021 Specification for Neutral Detergent, 40 Percent
4.3 Evaporator, flash, batch-type.
Akylbenzene Sulfonate Type
4.4 Graduated Cylinder.
F 303 Practices for Sampling Aerospace Fluids from Com-
4.5 Tongs, laboratory, for manipulating weighing foil
ponents
dishes.
F 305 Method of Sampling Particulates from Reservoir-
4.6 Desiccator, balance, to be placed in balance case.
Type Pressure-Sensing Instruments by Fluid Flushing
4.7 Desiccator, cooling with plate.
4.8 Weighing Vessels, aluminum foil weighing dishes.
4.9 Pressure Source, capable of providing 85 KPa (25-in.
This test method is under the jurisdiction ofASTM Committee E–21 on Space
Hg) for short interval.
Simulation andApplications of Space Technology and is the direct responsibility of
Subcommittee E21.05 on Contamination.
Current edition approved May 10, 2000. Published August 2000. Originally
published as F 331 - 70 T. Last previous edition F 331 - 98.
2 6
Annual Book of ASTM Standards, Vol 11.01. Annual Book of ASTM Standards, Vol 14.02.
3 7
Withdrawn. See 1999 Annual Book of ASTM Standards, Vol 15.04. Withdrawn. See 1988 Annual Book of ASTM Standards, Vol 14.02.
4 8
Annual Book of ASTM Standards, Vol 15.03. Available from Standardization Document Order Desk, Bldg. 4 Section D, 700
Withdrawn. See 1988 Annual Book of ASTM Standards, Vol 15.03. Robbins Ave., Philadelphia, PA 19111-5094, Attn: NPODS.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.
F331
4.10 Bottles, sample. operate at a pressure of 35 to 80 KPa (vacuum of 10- to 24-in.
4.11 Distillation Apparatus, laboratory, all glass (required Hg)(Note8).Continueuntilvolumeisreducedto10to20mL.
where solvents with sufficiently low residue are not available).
NOTE 4—The solvent used for testing should be recorded with the
Do not use grease or oil to lubricate glass joints.
collected data for each sample.
NOTE 5—All transfers should be accomplished with a double-rinse,
5. Reagents and Materials
using three aliquots of a total volume of 20 to 25 mL, which is to be added
to the sample.
5.1 Purity of Reagents—Reagent grade chemicals shall be
NOTE 6—Use a temperature that is appropriate for the solvent used, but
used in all tests. Unless otherwise indicated, it is intended that
do not exceed the weighing vessel drying temperature in 6.2.
all reagents shall conform to the specifications of the Commit-
NOTE 7—In some models of flash evaporators a water-cooled con-
tee on Analytical Reagents of the American Chemical Society
denser is used instead of the cooling flask.
...

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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.
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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.
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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.  
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ASTM E2580-24(Practice)
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
1.1 This practice covers two procedures for ultrasonic testing (UT) of flat panel (parallel surfaces) composites and flat sandwich core panels. 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, are not discussed.  
1.2 Ultrasonic testing is a common subsurface method for detection of laminar 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. These test procedures can be applied to small area manual scanning and large area automated scanning. 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 MHz 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, Example Pulse Echo Apparatus Set-ups  
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 for an example set-up using squirters). 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 Using Squirters  
1.4 This practice does not specify accept-reject criteria.  
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ASTM E2662-15(2022)(Practice)
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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.  
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.  
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ASTM F2156-17(2022)(Test Method)
Standard Test Method for Measuring Optical Distortion in Transparent Parts Using Grid Line Slope

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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.  
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1.3.1 Exception—The values given in parentheses are for information only.  
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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.  
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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.  
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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.  
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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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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ASTM
ASTM E3205-20(Test Method)
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.

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