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ASTM F311-08(2013)

(Practice)

Standard Practice for Processing Aerospace Liquid Samples for Particulate Contamination Analysis Using Membrane Filters

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.

General Information

Status
Historical
Publication Date
31-Oct-2013
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

Replaces
ASTM F311-08 - Standard Practice for Processing Aerospace Liquid Samples for Particulate Contamination Analysis Using Membrane Filters
Effective Date
01-Nov-2013
Replaced By
ASTM F311-08(2020) - Standard Practice for Processing Aerospace Liquid Samples for Particulate Contamination Analysis Using Membrane Filters
Effective Date
01-Apr-2020
Referred By
ASTM D4174-23 - Standard Practice for Cleaning, Flushing, and Purification of Petroleum Fluid Hydraulic Systems
Effective Date
01-Nov-2013
Referred By
ASTM F303-08(2023)e1 - Standard Practices for Sampling for Particles in Aerospace Fluids and Components
Effective Date
01-Nov-2013
Referred By
ASTM D6224-22 - Standard Practice for In-Service Monitoring of Lubricating Oil for Auxiliary Power Plant Equipment
Effective Date
01-Nov-2013
Referred By
ASTM F331-13(2020) - Standard Test Method for Nonvolatile Residue of Solvent Extract from Aerospace Components (Using Flash Evaporator)
Effective Date
01-Nov-2013
Referred By
ASTM F310-07(2020) - Standard Practice for Sampling Cryogenic Aerospace Fluids
Effective Date
01-Nov-2013
Referred By
ASTM F309-18 - Standard Practice for Liquid Sampling of Noncryogenic Aerospace Propellants
Effective Date
01-Nov-2013
Referred By
ASTM F302-09(2021) - Standard Practice for Field Sampling of Aerospace Fluids in Containers
Effective Date
01-Nov-2013
Referred By
ASTM F3335-20 - Standard Guide for Assessing the Removal of Additive Manufacturing Residues in Medical Devices Fabricated by Powder Bed Fusion
Effective Date
01-Nov-2013
Referred By
ASTM F312-08(2023) - Standard Test Methods for Microscopical Sizing and Counting Particles from Aerospace Fluids on Membrane Filters
Effective Date
01-Nov-2013
Referred By
ASTM G131-96(2023)e1 - Standard Practice for Cleaning of Materials and Components by Ultrasonic Techniques
Effective Date
01-Nov-2013
Referred By
ASTM D4378-22 - Standard Practice for In-Service Monitoring of Mineral Turbine Oils for Steam, Gas, and Combined Cycle Turbines
Effective Date
01-Nov-2013
Referred By
ASTM D6439-23 - Standard Guide for Cleaning, Flushing, and Purification of Steam, Gas, and Hydroelectric Turbine Lubrication Systems
Effective Date
01-Nov-2013

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ASTM F311-08(2013) - Standard Practice for Processing Aerospace Liquid Samples for Particulate Contamination Analysis Using Membrane FiltersASTM F311-08(2013) - Standard Practice for Processing Aerospace Liquid Samples for Particulate Contamination Analysis Using Membrane Filters
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ASTM F311-08(2013) - Standard Practice for Processing Aerospace Liquid Samples for Particulate Contamination Analysis Using Membrane Filters
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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: F311 − 08 (Reapproved 2013)
Standard Practice for
Processing Aerospace Liquid Samples for Particulate
Contamination Analysis Using Membrane Filters
ThisstandardisissuedunderthefixeddesignationF311;thenumberimmediatelyfollowingthedesignationindicatestheyearoforiginal
adoption or, in the case of revision, the year of last revision.Anumber in parentheses indicates the year of last reapproval.Asuperscript
epsilon (´) indicates an editorial change since the last revision or reapproval.
1. Scope F302 Practice for Field Sampling of Aerospace Fluids in
Containers
1.1 This practice covers the processing of liquids in prepa-
F303 Practices for Sampling for Particles in Aerospace
ration for particulate contamination analysis using membrane
Fluids and Components
filters and is limited only by the liquid-to-membrane filter
F312 Test Methods for Microscopical Sizing and Counting
compatibility.
Particles from Aerospace Fluids on Membrane Filters
1.2 The practice covers the procedure for filtering a mea-
sured volume of liquid through a membrane filter. When this
3. Definition
practice is used, the particulate matter will be randomly
3.1 filtered liquid dispenser—as used in this practice, a
distributed on the filter surface for subsequent contamination
dispensercapableofdeliveringrinseliquidthroughafilterwith
analysis methods.
pore size no larger than half the size of the smallest particle
1.3 The practice describes procedures to allow handling
being considered for measurement.
particles in the size range between 2 and 1000 µm with
4. Significance and Use
minimum losses during handling.
4.1 This practice provides for the processing of liquid
1.4 The values stated in SI units are to be regarded as
samples obtained in accordance with Practice F302 and Prac-
standard. No other units of measurement are included in this
tices F303. It will provide the optimum sample processing for
standard.
visual contamination methods such as Method F312, and Test
2. Referenced Documents
Method F314.
2.1 ASTM Standards:
5. Apparatus and Materials
D287 Test Method for API Gravity of Crude Petroleum and
Petroleum Products (Hydrometer Method) 5.1 Filtration Funnel—The funnel opening in contact with
the membrane shall be approximately 35.0 mm in inside
D1078 Test Method for Distillation Range of Volatile Or-
ganic Liquids diameter. The effective area shall be calibrated. If the funnel is
to be used for measuring the sample volume, the funnel shall
D1193 Specification for Reagent Water
D1353 Test Method for Nonvolatile Matter in Volatile Sol- be calibrated within 62 % of the required volume.
vents for Use in Paint, Varnish, Lacquer, and Related
5.2 Membrane Filter Support—Either a fritted-glass,
Products
sintered-metal, polyphenyl-sulfone or stainless steel screen
D1836 Specification for Commercial Hexanes
may be used. The support shall be so designed as to enable
D2021 Specification for Neutral Detergent, 40 PercentAlky-
attachment to a vacuum flask.
lbenzene Sulfonate Type (Withdrawn 2000)
5.3 Vacuum Flask.
5.4 Funnel-Holding Device—A provision should be made
This practice is under the jurisdiction of ASTM Committee E21 on Space
for the dissipation of static electricity from the funnel.
Simulation andApplications of Space Technology and is the direct responsibility of
Subcommittee E21.05 on Contamination. 5.5 A clean bench or hood, supplied with unidirectional
Current edition approved Nov. 1, 2013. Published November 2013. Originally
flow filtered air, in which uncovered components may be
approved in 1969. Last previous edition approved in 2008 as F311 – 08. DOI:
placed.
10.1520/F0311-13.
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
5.6 Vacuum Source—Minimum vacuum gage reading of 61
contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
kPa (or other metric units acceptable to ASTM).
Standards volume information, refer to the standard’s Document Summary page on
the ASTM website.
5.7 Forceps, unserrated tips.
The last approved version of this historical standard is referenced on
www.astm.org. 5.8 Filtered Liquid Dispenser.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
F311 − 08 (2013)
used to avoid inhalation of the vapors.
5.9 Membrane Filter, pore size no greater than half the size
of the smallest particle being considered for measurement.The
6.6 Rinse Liquid—This liquid shall be specified by the user
filter shall have an imprinted grid on 3.10 6 0.02-mm centers.
and shall be compatible with the sample liquid the plastic film
The color shall be chosen to provide maximum contrast with
(see section 5.12) and the membrane filter.
the particulate contamination to be observed.
7. Preparation of Apparatus
NOTE 1—When testing military hydraulic fluids, a white cellulose
membrane of 0.45-µm pore size, capable of filtering 80 mL of distilled 7.1 Wash the apparatus thoroughly in a solution of liquid
water per square centimeter per minute at 93 kPa (or other metric units
detergent and hot water and rinse with hot tap water (Note 3).
acceptable to ASTM) and 25°C is required.
Rinse with filtered isopropyl alcohol to remove the water; then
5.10 Petri Dishes, glass. Plastic Petri dishes may be used rinse twice with filtered solvent.
only if the selected plastic is known to be compatible with the
NOTE 3—Distilled or deionized water shall be used in areas where
filtered liquid.
hardness or contamination increase the blank count over the allowable
level.
5.11 Glass Bottles, small-mouth, screw-capped, perma-
nently marked to indicate sample volume.
7.2 Sample Bottle Preparation—Repeattheprocedureof7.1
for both the sample bottles and caps, then allow them to drip
5.12 Plastic Film, 0.002-in. (0.05-mm) minimum thickness.
dry. Place a piece of plastic film that has been rinsed with
5.13 Contrasting Pigment Suspension, to be used in calibra-
filtered liquid over the mouth of the bottle. Hold the film while
tion of the funnel.
screwing on the cap to prevent the film from rotating.
5.14 Slides, glass, 50 by 50-mm.
NOTE 4—It is important to hold the film when applying and removing
the cap to prevent serration.
5.15 Tape, transparent, pressure-sensitive.
8. Funnel Calibration
6. Reagents and Materials
8.1 Disperse a small quantity of pigment into 100 mL of
6.1 Purity of Reagents—Reagent grade chemicals shall be
liquid in a glass bottle. Prepare for a filtration as described in
used in all tests. Unless otherwise indicated, it is intended that
9.1. Filt
...

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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.
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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.  
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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.  
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FIG. 1 Test Procedure A, Example Pulse Echo Apparatus Set-ups  
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FIG. 2 Test Procedure B, Through Transmission Apparatus Set-up Using Squirters  
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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.  
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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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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.  
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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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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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