49.025.40 - Rubber and plastics
ICS 49.025.40 Details
Rubber and plastics
Kunststoffe. Gummi
Caoutchouc et plastiques
Guma in polimerni materiali
General Information
Frequently Asked Questions
ICS 49.025.40 is a classification code in the International Classification for Standards (ICS) system. It covers "Rubber and plastics". The ICS is a hierarchical classification system used to organize international, regional, and national standards, facilitating the search and identification of standards across different fields.
There are 244 standards classified under ICS 49.025.40 (Rubber and plastics). These standards are published by international and regional standardization bodies including ISO, IEC, CEN, CENELEC, and ETSI.
The International Classification for Standards (ICS) is a hierarchical classification system maintained by ISO to organize standards and related documents. It uses a three-level structure with field (2 digits), group (3 digits), and sub-group (2 digits) codes. The ICS helps users find standards by subject area and enables statistical analysis of standards development activities.
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This document specifies methods for determining the resin content, fibre content and mass of fibre per unit area of fibre preimpregnates for aerospace use.
- Amendment4 pagesEnglish languagee-Library read for1 day
This document specifies methods for determining the resin content, fibre content and mass of fibre per unit area of fibre preimpregnates for aerospace use.
- Amendment4 pagesEnglish languagee-Library read for1 day
ABSTRACT
This specification establishes the requirements for parts intended for aerospace use and machined from polychlorotrifluoroethylene (PCTFE) homopolymers. This specification, however, does not cover parts machined from PCTFE copolymer, PCTFE film or tape, or modified PCTFE. Material covered by this specification is on four types, differentiated based on intended uses and exposures: Types I (high service pressure) and II (low service pressure) for use in air and oxygen media, Type II for use in inert and reactive media, and Type IV for use in other media. The parts shall be manufactured from virgin, unplasticized, pure PCTFE homopolymer, and the use of recycled polymer or regrind shall be prohibited. The base material shall be free of defects and contaminants. The finished parts shall be white or gray in color with a natural translucent appearance, and shall be free of voids, scratches, fissures, inclusions, or entrapped air bubbles. Tests for specific gravity, melting point, tensile strength and elongation, deformation under load, zero strength time, mechanical impact (in ambient liquid oxygen and pressurized liquid and gaseous oxygen environments), and dimensional stability shall be performed and shall conform to the requirements specified.
SCOPE
1.1 This specification is intended to be a means of calling out finished machined parts ready for aerospace use. Such parts may also find use in selected commercial applications where there are clear benefits derived from the use of parts with high molecular weight, good molecular weight retention during processing, dimensional stability, controlled crystallinity, and tightly controlled engineering tolerances.
1.2 This specification establishes requirements for parts machined from virgin, unplasticized, 100 % polychlorotrifluoroethylene (PCTFE) homopolymers.
1.3 This specification does not cover parts machined from PCTFE copolymers, PCTFE film or tape less than 0.25-mm (0.010-in.) thick, or modified PCTFE (containing pigments or plasticizers).
1.4 This specification does not allow parts containing recycled material.
1.5 The specification does not cover PCTFE parts intended for general use applications, in which control of dimensional stability, molecular weight, and crystallinity are not as important. For machined PCTFE parts intended for general use, use Specification D7211.
1.6 This specification classifies parts into three classes based upon intended uses and exposures: oxygen-containing media, reactive media, and inert media.
1.7 Application—PCTFE components covered by this specification are virgin, 100 % PCTFE resin, free of plasticizers and other additives. The components are combustion resistant in oxygen, dimensionally stable, and meet other specific physical characteristics appropriate for their end use. They are used in valves, regulators, and other devices in oxygen, air, helium, nitrogen, hydrogen, ammonia, and other aerospace media systems. The components typically are used as valve seats, o-rings, seals, and gaskets. They are removed and replaced during normal maintenance procedures. The components provide reliable sealing surfaces resulting in proper closure of valves and related devices and no leakage from the system into the environment. They will experience static mechanical loading, cyclic mechanical loading, temperatures ranging from cryogenic to 71°C (160°F), and pressures up to 68.9 MPa (10,000, psig) for oxygen and air media, and 103.4 MPa (15,000 psig) for inert media.
1.8 The values stated in SI units are to be regarded as standard. The values in parentheses are for information only.
1.9 The following precautionary caveat pertains only to the test methods portion, Section 13, of this specification: 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 pra...
- Technical specification7 pagesEnglish languagesale 15% off
This test method describes the principles applicable to infrared transmission spectrophotometric analysis of organic compounds (elastomers, basic resins, resin mixes or resin systems) used as the matrix in reinforced polymers, adhesives, bonding primers and, in general terms, all organic compounds.
The method could also be applied to some inorganic products.
It is intended to be used jointly with special test conditions specified in the materials specification invoking the test.
This document does not give any directions necessary to meet the health and safety requirements. It is the responsibility of the user of this document to adopt appropriate health and safety precautions.
- Standard27 pagesEnglish languagee-Library read for1 day
This document specifies the required characteristics of loop style clamps ("P" type) in aluminium alloy with various cushion materials.
These clamps are used for supporting aerospace pipe assemblies and electrical cable bundles.
They are used up to 80 °C max.
Usage at a higher temperature is at the option of the user.
For temperature range and environmental considerations, see the various cushion material standards.
- Standard10 pagesEnglish languagee-Library read for1 day
This document specifies the required characteristics for heat-shrinkable limited fire hazard identification sleeves for use in aircraft electrical systems at operating temperatures between −40 °C and 105 °C.
This document is only applicable for the characterization of identification sleeves. This sleeving is flexible, flame retarded and emits minimum smoke, gases and corrosive by-products when exposed to fire. This sleeving is only applicable for use in areas where smoke, gases or corrosive by-products would constitute a particular hazard.
It is available with a shrink ratio of 2 : 1.
The product is normally supplied with internal diameters up to 51 mm.
The standard colours are white or yellow.
Sizes or colours other than those specifically listed in this document can be available. These items are considered to comply with this document if they comply with the property requirements listed in Table 2 and Table 3, except for dimensions and mass.
As the sleeving to be tested is a printed article, the complete system is to be recorded as part of the evaluation. The sleeve will only be considered as meeting the requirements of this document if printed with the printer, ribbon, inks and settings referenced within the test report.
Mark adherence and print permanence are determined in this specification using method EN 6059-407.
- Standard10 pagesEnglish languagee-Library read for1 day
This document lists the product standards, covered by technical specification EN 4708-001, for heat shrinkable sleeves.
- Standard8 pagesEnglish languagee-Library read for1 day
This test method describes the principles applicable to infrared transmission spectrophotometric analysis of organic compounds (elastomers, basic resins, resin mixes or resin systems) used as the matrix in reinforced polymers, adhesives, bonding primers and, in general terms, all organic compounds.
The method could also be applied to some inorganic products.
It is intended to be used jointly with special test conditions specified in the materials specification invoking the test.
This document does not give any directions necessary to meet the health and safety requirements. It is the responsibility of the user of this document to adopt appropriate health and safety precautions.
- Standard27 pagesEnglish languagee-Library read for1 day
This document specifies the required characteristics for heat-shrinkable semi rigid polyvinylidene identification sleeves for use in aircraft electrical systems at operating temperatures between -55 °C and 225 °C.
This specification is for the characterisation of Identification sleeves only.
This sleeving is a semi rigid tough product and is suitable for use where high temperatures and extreme fluid resistance properties are required.
It is available with a shrink ratio of 2:1.
The product is normally supplied with internal diameters up to 38 mm
The standard colours are white, black or yellow
For use at temperatures above 200 °C black with white or silver ink is recommended
Sizes or colours other than those specifically listed in this standard may be available. These items shall be considered to comply with this document if they comply with the property requirements listed in tables 2 and 3 except for dimensions and mass.
As the sleeving to be tested is a printed article the complete system is to be recorded as part of the evaluation. The sleeve will only be considered as meeting the requirements of this specification if printed with the printer, ribbon/inks and settings referenced within the test report.
Mark adherence and print permanence are determined in this document using method EN 6059-407.
- Standard11 pagesEnglish languagee-Library read for1 day
This document specifies the required characteristics for heat-shrinkable polyolefin identification
sleeving for use in aircraft electrical systems at operating temperatures between −55 °C and 135 °C.
This specification is for the characterisation of identification sleeves only.
This sleeving is flexible and flame retarded, and is available with 2:1 and 3:1 shrink ratios.
The product is normally supplied with internal diameters up to 57 mm.
The standard colours are white or yellow.
Sizes or colours other than those specifically listed in this standard may be available. These items are
considered to comply with this document if they comply with the property requirements listed in tables 3
and 4 except for dimensions and mass.
As the sleeving to be tested is a printed article the complete system is to be recorded as part of the
evaluation. The sleeve will only be considered as meeting the requirements of this document if printed
with the printer, ribbon, inks, and settings referenced within the test report.
Mark adherence and print permanence are determined in this document using method EN 6059-407.
- Standard13 pagesEnglish languagee-Library read for1 day
This document specifies the characteristics of self-extinguishing and low smoke emission semi-finished polycarbonate sheets with and without UV radiation protection requirement, as used for aircraft equipment, such as internal panelling, simple internal glazing, sound-proofing panels, light covers, etc.
- Standard6 pagesEnglish languagee-Library read for1 day
This document specifies the characteristics of self-extinguishing and low smoke emission semi-finished polycarbonate sheets with and without UV radiation protection requirement, as used for aircraft equipment, such as internal panelling, simple internal glazing, sound-proofing panels, light covers, etc.
- Standard6 pagesEnglish languagee-Library read for1 day
This document specifies methods for determining the resin content, fibre content and mass of fibre per unit area of fibre preimpregnates for aerospace use.
- Standard13 pagesEnglish languagee-Library read for1 day
This document specifies methods for determining the resin content, fibre content and mass of fibre per unit area of fibre preimpregnates for aerospace use.
- Standard13 pagesEnglish languagee-Library read for1 day
This document specifies the requirements for a range of one part anaerobic polymerisable compounds
which polymerises upon the exclusion of oxygen and activation by a metal surface.
- Standard17 pagesEnglish languagee-Library read for1 day
This document specifies the requirements of a thermoplastic composite stock shape material (e.g. tape,
rod etc.) consisting of polyetheretherketone with 55 % continuous glass fibres by volume (PEEK–GF55)
for aerospace applications, which is presupposed to be used in a further thermal moulding process for
forming parts described in EN 4714 1).
- Standard7 pagesEnglish languagee-Library read for1 day
This document specifies the requirements of a thermoplastic composite stock shape material (e.g. tape,
rod, etc.) consisting of polyetheretherketone with 55 % continuous carbon fibres by volume (PEEK–
CF55) for aerospace applications, which is presupposed to be used in a further thermal moulding
process for forming parts described in EN 4714 1).
- Standard7 pagesEnglish languagee-Library read for1 day
ABSTRACT
This test method covers the determination of the char density profile of a charred ablator. The total thickness of the char and degradation zone must be larger than the machining thicknesses required. Density variation throughout a charred ablator material is determined by successively measuring, machining, and weighing a sample of known size to obtain the density of the material removed by machining. The apparatus required for this method includes a laboratory balance capable of measuring to the nearest ten thousandth gram, and a machining technique capable of removing material in increments as small as a thousandth mm.
SCOPE
1.1 This test method covers the determination of the char density profile of a charred ablator that can be used with the following limitations:
1.1.1 The local surface imperfections must be removed, and the char must be able to be machined off in a plane parallel to the char-virgin material interface before the density profiles can be determined.
1.1.2 The char must be strong enough to withstand the machining and handling techniques employed.
1.1.3 The material should have orderly density variations. The total thickness of the char and degradation zone must be larger than the machining thicknesses required.
1.2 Units—The values stated in SI units are to be regarded as standard. No other units of measurement are included in this standard.
1.2.1 Exception—Certain inch-pound equivalent units are included in parentheses for information only.
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.
- Standard3 pagesEnglish languagesale 15% off
- Standard3 pagesEnglish languagesale 15% off
This document specifies the requirements for a range of one part anaerobic polymerisable compounds
which polymerises upon the exclusion of oxygen and activation by a metal surface.
- Standard17 pagesEnglish languagee-Library read for1 day
SIGNIFICANCE AND USE
5.1 At this writing, aerospace quality extruded transparent polycarbonate material is not available in thicknesses greater than 0.5 in. (12.7 mm). When a requirement exists for sheets thicker than 0.5 in. (12.7 mm), two or more sheets are fusion bonded together to form a single sheet of the desired thickness.
5.2 The structural integrity of the completed transparency depends on the integrity of the fusion bond. This test applies torsional shear loads to measure the structural integrity of the fusion bond. This test method is considered more reliable and more reproducible than shear tests in tension or compression.
SCOPE
1.1 This test method determines the shear yield strength Fsy and shear ultimate strength Fsu of fusion bonds in polycarbonate by applying torsional shear loads to the fusion-bond line.
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.
- Standard5 pagesEnglish languagesale 15% off
This document specifies the requirements of a thermoplastic composite stock shape material (e.g. tape,
rod etc.) consisting of polyetheretherketone with 55 % continuous glass fibres by volume (PEEK–GF55)
for aerospace applications, which is presupposed to be used in a further thermal moulding process for
forming parts described in EN 4714 1).
- Standard7 pagesEnglish languagee-Library read for1 day
This document specifies the requirements of a thermoplastic composite stock shape material (e.g. tape,
rod, etc.) consisting of polyetheretherketone with 55 % continuous carbon fibres by volume (PEEK–
CF55) for aerospace applications, which is presupposed to be used in a further thermal moulding
process for forming parts described in EN 4714 1).
- Standard7 pagesEnglish languagee-Library read for1 day
SIGNIFICANCE AND USE
4.1 These test methods provide a means to measure quantitatively the bond integrity between the outer layers of the transparency and the interlayer, or to measure the cohesive properties of the interlayer, under various loading conditions.
4.2 These test methods provide empirical results useful for control purposes, correlation with service results, and as quality control tests for acceptance of production parts.
4.3 Test results obtained on small, laboratory-size samples shown herein are indicative of full-size part capability, but not necessarily usable for design purposes.
SCOPE
1.1 These test methods cover determination of the bond integrity of transparent laminates. The laminates are usually made of two or more glass or hard plastic sheets held together by an elastomeric material. These test methods are intended to provide a means of determining the strength of the bond between the glass or plastic and the elastomeric interlayer under various mechanical or thermal loading conditions.
1.2 The test methods appear as follows:
Test Methods
Sections
Test Method A—Flatwise Bond Tensile Strength
5 – 11
Test Method B—Interlaminar Shear Strength
12 – 17
Test Method C—Creep Rupture
18 – 25
Test Method D—Thermal Exposure
26 – 30
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.
- Standard9 pagesEnglish languagesale 15% off
- Standard9 pagesEnglish languagesale 15% off
SIGNIFICANCE AND USE
5.1 The tendency of the insulation toward wicking can result in an increase in weight and a resultant potential degradation in the properties of the insulation.
SCOPE
1.1 This test method covers a laboratory procedure for evaluating the tendency of, aircraft type, fibrous glass blanket insulation to wick water.
1.2 The wicking characteristics of materials can be affected by environmental conditions such as temperature and humidity. Values obtained as a result of this test method does not adequately describe the wicking characteristics of materials subject to conditions other than those indicated in the test method. (See Specification C800.)
1.3 The values stated in inch-pound units are to be regarded as standard. The values given in parentheses are mathematical conversions to SI units that are provided for information only and are not considered standard.
1.4 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.
- Standard3 pagesEnglish languagesale 15% off
SIGNIFICANCE AND USE
5.1 The water retention of the insulation can result in an increase in weight and a resultant potential degradation in the properties of the insulation.
SCOPE
1.1 This test method covers a laboratory procedure for evaluating the water absorption potential of blanket insulation for aircraft, thereby providing a measure of potential weight increase due to water retention in an aircraft.
1.2 The water repellency (or retention) characteristics of materials can be affected by conditions such as contamination or temperature of the water. Values obtained as a result of this test method does not adequately describe the water repellency characteristics of materials subject to these conditions.
1.3 The values stated in inch-pound units are to be regarded as standard. The values given in parentheses are mathematical conversions to SI units that are provided for information only and are not considered standard.
1.4 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.
- Standard2 pagesEnglish languagesale 15% off
This document defines the requirements of ethylene propylene elastomer (EPM/EPDM) for seal elements for use as static seals in hydraulic systems using phosphate ester fluids, hardness 80 IRHD (International Rubber Hardness Degree) for long term application for aerospace application.
Unless otherwise specified in the drawing, order or inspection schedule, this document shall be used in conjunction with the referenced documents.
Applicable temperature range:
- Continuous service: −55 °C to 107 °C
- Intermittent service: −55 °C to 120 °C
- Standard7 pagesEnglish languagee-Library read for1 day
SIGNIFICANCE AND USE
5.1 This guide references requirements that are intended to control the quality of NDT data. The purpose of this guide, therefore, is not to establish acceptance criteria and therefore approve composite materials or components for aerospace service.
5.2 Following the discretion of the cognizant engineering organization, NDT for fracture control of composite and bonded materials should follow additional guidance described in MIL-HDBK-6870, NASA-STD-(I)-5019, or MSFC-RQMT-3479, or a combination thereof, as appropriate (not covered in this guide).
5.3 Certain procedures referenced in this guide are written so they can be specified on the engineering drawing, specification, purchase order, or contract, for example, Practice E1742/E1742M (Radiography).
5.4 Acceptance Criteria—Determination about whether a composite material or component meets acceptance criteria and is suitable for aerospace service should be made by the cognizant engineering organization. When examinations are performed in accordance with the referenced documents in this guide, the engineering drawing, specification, purchase order, or contract should indicate the acceptance criteria.
5.4.1 Accept/reject criteria should consist of a listing of the expected kinds of imperfections and the rejection level for each.
5.4.2 The classification of the articles under test into zones for various accept/reject criteria should be determined from contractual documents.
5.4.3 Rejection of Composite Articles—If the type, size, or quantities of defects are found to be outside the allowable limits specified by the drawing, purchase order, or contract, the composite article should be separated from acceptable articles, appropriately identified as discrepant, and submitted for material review by the cognizant engineering organization, and dispositioned as (1) acceptable as is, (2) subject to further rework or repair to make the materials or component acceptable, or (3) scrapped when required by contractu...
SCOPE
1.1 This guide provides information to help engineers select appropriate nondestructive testing (NDT) methods to characterize aerospace polymer matrix composites (PMCs). This guide does not intend to describe every inspection technology. Rather, emphasis is placed on established NDT methods that have been developed into consensus standards and that are currently used by industry. Specific practices and test methods are not described in detail, but are referenced. The referenced NDT practices and test methods have demonstrated utility in quality assurance of PMCs during process design and optimization, process control, after manufacture inspection, in-service inspection, and health monitoring.
1.2 This guide does not specify accept-reject criteria and is not intended to be used as a means for approving composite materials or components for service.
1.3 This guide covers the following established NDT methods as applied to PMCs: Acoustic Emission (AE, Section 7); Computed Tomography (CT, Section 8); Leak Testing (LT, Section 9); Radiographic Testing, Computed Radiography, Digital Radiography, and Radioscopy (RT, CR, DR, RTR, Section 10); Shearography (Section 11); Strain Measurement (Contact Methods, Section 12); Thermography (Section 13); Ultrasonic Testing (UT, Section 14); and Visual Testing (VT, Section 15).
1.4 The value of this guide consists of the narrative descriptions of general procedures and significance and use sections for established NDT practices and test methods as applied to PMCs. Additional information is provided about the use of currently active standard documents (an emphasis is placed on applicable standard guides, practices, and test methods of ASTM Committee E07 on Nondestructive Testing), geometry and size considerations, safety and hazards considerations, and information about physical reference standards.
1.5 To ensure proper use of the referenced standard documents, there are recogni...
- Guide49 pagesEnglish languagesale 15% off
- Guide49 pagesEnglish languagesale 15% off
ABSTRACT
This practice describes the standard procedures for providing exposure of thermal control materials to a simulated space environment comprising of the major features of vacuum, electromagnetic radiation, charged particle radiation, and temperature control. Broad recommendations relating to spectral reflectance measurements, as well as test parameters and other information that should be reported as an aid in interpreting test results are delineated. Specifications are provided for the vacuum system, solar simulator, charged particle sources, safety precautions, and data interpretation.
SCOPE
1.1 This practice describes procedures for providing exposure of thermal control materials to a simulated space environment comprising the major features of vacuum, electromagnetic radiation, charged particle radiation, and temperature control.
1.2 Broad recommendations relating to spectral reflectance measurements are made.
1.3 Test parameters and other information that should be reported as an aid in interpreting test results are delineated.
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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SIGNIFICANCE AND USE
2.1 Internal temperature measurements are made on both in-flight vehicles and on-ground test specimens; and, because of the importance of the temperature measurements to the design of various missile and spacecraft heat shields, it is essential that care be taken to minimize the sources of error in obtaining these measurements.
2.2 Over the past several years, the problems of using thermocouples to obtain accurate temperature measurements in low-conductivity specimens have been studied by various people to isolate the sources of error and to establish improved temperature measurement techniques. The major sources of error are listed in this document and recommended solutions to the problems are given.
SCOPE
1.1 This practice covers methods for instrumenting low-conductivity specimens for testing in an environment subject to rapid thermal changes such as produced by rocket motors, atmospheric re-entry, electric-arc plasma heaters, and so forth. Specifically, practices for bare-wire thermocouple instrumentation applicable to sheath-type thermocouples are discussed.
1.2 The values stated in inch-pound units are to be regarded as the standard. The metric equivalents of inch-pound units may be approximate.
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.
- Standard4 pagesEnglish languagesale 15% off
This document defines the requirements of ethylene propylene elastomer (EPM/EPDM) for seal elements for use as static seals in hydraulic systems using phosphate ester fluids, hardness 80 IRHD (International Rubber Hardness Degree) for long term application for aerospace application.
Unless otherwise specified in the drawing, order or inspection schedule, this document shall be used in conjunction with the referenced documents.
Applicable temperature range:
- Continuous service: −55 °C to 107 °C
- Intermittent service: −55 °C to 120 °C
- Standard7 pagesEnglish languagee-Library read for1 day
SIGNIFICANCE AND USE
5.1 This AE examination is useful to detect micro-damage generation, accumulation, and growth of new or existing flaws. The examination is also used to detect significant existing damage from friction-based AE generated during loading or unloading of these regions. The damage mechanisms that can be detected include matrix cracking, fiber splitting, fiber breakage, fiber pull-out, debonding, and delamination. During loading, unloading, and load holding, damage that does not emit AE energy will not be detected.
5.2 When the detected signals from AE sources are sufficiently spaced in time so as not to be classified as continuous AE, this practice is useful to locate the region(s) of the 2-D test sample where these sources originated and the accumulation of these sources with changing load or time, or both.
5.3 The probability of detection of the potential AE sources depends on the nature of the damage mechanisms, flaw characteristics, and other aspects. For additional information, see X1.4.
5.4 Concentrated damage in fiber/polymer composites can lead to premature failure of the composite item. Hence, the use of AE to detect and locate such damage is particularly important.
5.5 AE-detected flaws or damage concentrated in a certain region may be further characterized by other NDE techniques (for example, visual, ultrasonic, etc.) and may be repaired as appropriate. Repair procedure recommendations and the subsequent examination of the repair are outside the scope of this practice. For additional information, see X1.5.
5.6 This practice does not address sandwich core, foam core, or honeycomb core plate-like composites due to the fact that currently there is little in the way of published work on the subject resulting in a lack of a sufficient knowledge base.
5.7 Refer to Guide E2533 for additional information about types of defects detected by AE, general overview of AE as applied to polymer matrix composites, discussion of the Felicity ratio (FR) and Ka...
SCOPE
1.1 This practice covers acoustic emission (AE) examination or monitoring of panel and plate-like composite structures made entirely of fiber/polymer composites.
1.2 The AE examination detects emission sources and locates the region(s) within the composite structure where the emission originated. When properly developed AE-based criteria for the composite item are in place, the AE data can be used for nondestructive examination (NDE), characterization of proof testing, documentation of quality control, or for decisions relative to structural-test termination prior to completion of a planned test. Other NDE methods may be used to provide additional information about located damage regions. For additional information, see X1.1 in Appendix X1.
1.3 This practice can be applied to aerospace composite panels and plate-like elements as a part of incoming inspection, during manufacturing, after assembly, continuously (during structural health monitoring), and at periodic intervals during the life of a structure.
1.4 This practice is meant for fiber orientations that include cross-plies, angle-ply laminates, or two-dimensional woven fabrics. This practice also applies to 3-D reinforcement (for example, stitched, z-pinned) when the fiber content in the third direction is less than 5 % (based on the whole composite).
1.5 This practice is directed toward composite materials that typically contain continuous high modulus greater than 20 GPa [3 Msi] fibers.
1.6 Units—The values stated in either SI units or inch-pound units are to be regarded separately as standard. The values stated in each system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used independently of the other, and values from the two systems shall not be combined.
1.7 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsi...
- Standard19 pagesEnglish languagesale 15% off
This document specifies the required characteristics for heat-shrinkable elastomeric semi-rigid, boots for use in aircraft electrical systems at operating temperatures between -75 °C and 150 °C.
The moulded shapes may be supplied with a pre-coated adhesive. Refer to the manufacturers/suppliers for options. A guide to adhesive compatibility is given in Annex A (informative).
These moulded shapes are normally supplied in the styles and dimensions given in EN 4840-002 Table 1 to Table 22. The colour is normally black.
Styles and dimensions other than those specifically listed in EN 4840-002 Table 1 to Table 22 may be available as custom items. These items shall be considered to comply with this standard if they comply with the property requirements listed in Table 1 with the exception of dimensions.
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- Standard10 pagesEnglish languagee-Library read for1 day
This document specifies the properties of fluorocarbon rubber (FKM)1), hardness 80 IRHD, for aerospace
applications.
- Standard7 pagesEnglish languagee-Library read for1 day
This document specifies the properties of fluorocarbon rubber (FKM)1), hardness 70 IRHD, for aerospace
applications.
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This document specifies the properties of fluorocarbon rubber (FKM)1), hardness 90 IRHD, for aerospace applications.
- Standard7 pagesEnglish languagee-Library read for1 day
This European Standard specifies the properties of fluorocarbon rubber (FKM) ), low compression set, hardness 80 IRHD, for aerospace applications.
- Standard7 pagesEnglish languagee-Library read for1 day
This document specifies the required characteristics for four types of heat-shrinkable limited fire hazard sleevings for use in aircraft electrical systems at operating temperatures between 65 °C and 150 °C.
This sleeving is flexible, flame retarded and emits minimum smoke, gases and corrosive by-products when exposed to fire. It is available with various wall thicknesses and also in a higher shrink ratio according to the application and degree of mechanical protection required. It is suitable for use (e.g. as cable protection) in areas where smoke, gases or corrosive by-products would constitute a particular hazard.
Type A: Medium wall, shrink ratio 2:1 and is normally supplied with internal diameters up to 30 mm.
The standard colour is black.
Sizes or colours other than those specifically listed in this document may be available. These items shall be considered to comply with this document if they comply with the property requirements listed in Table 2 except for dimensions and mass.
- Standard11 pagesEnglish languagee-Library read for1 day
This document specifies the required characteristics for a heat-shrinkable, polytetrafluoroethylene sleeving for use in aircraft electrical systems at operating temperatures between 65 °C and 260 °C. This sleeving is basically translucent. It is semi-rigid, and suitable for use where resistance to chemicals and high temperature performance are required. It is flame resistant and available in low and high shrink ratios.
- Standard12 pagesEnglish languagee-Library read for1 day
This document specifies the required characteristics for a heat-shrinkable, semi-flexible polyvinylidene sleeving for use in aircraft electrical systems at operating temperatures between 55 °C and 150 °C. This sleeving is basically transparent, but may be tinted. It is semi-flexible tough and abrasion resistant, and is suitable for use where strain relief and mechanical protection are required, or where their transparent properties are desirable.
It is not suitable for use where contamination from phosphate ester based hydraulic fluid is possible.
These sleevings are normally supplied with internal diameters up to 25,4 mm for shrink ratios of 2:1.
Sizes other than those specifically listed in this standard may be available. These items shall be considered to comply with this standard if they comply with the property requirements listed in Tables 2, 3 and 4 except for dimensions and mass.
- Standard10 pagesEnglish languagee-Library read for1 day
This document specifies the required characteristics, test methods, qualification and production routine testing of Heat shrinkable sleeving for binding, insulation and identification.
- Standard11 pagesEnglish languagee-Library read for1 day
This European Standard specifies the properties of fluorocarbon rubber (FKM) ), low compression set, hardness 80 IRHD, for aerospace applications.
- Standard7 pagesEnglish languagee-Library read for1 day
This document specifies the properties of fluorocarbon rubber (FKM)1), hardness 70 IRHD, for aerospace
applications.
- Standard7 pagesEnglish languagee-Library read for1 day
This document specifies the properties of fluorocarbon rubber (FKM)1), hardness 90 IRHD, for aerospace applications.
- Standard7 pagesEnglish languagee-Library read for1 day
This European Standard specifies the required characteristics for two types a heat-shrinkable, fluoroelastomer sleeving for use in aircraft electrical systems at operating temperatures between -55 °C and 200 °C.
Type A Thick wall
Type B Thin wall
This sleeving has good flexibility, is flame retarded and has a thick wall for mechanical protection. It is for use in areas subject to prolonged contamination by aircraft fuel and fluids with the exception of phosphate ester-based hydraulic fluids. The standard colour is black.
These sleevings are normally supplied with internal diameters up to 50 mm for shrink ratios of 2:1. They are available in black only.
Sizes other than those specifically listed in this standard may be available. These items shall be considered to comply with this standard if they comply with the property requirements listed in Tables 2, 3 and 4 except for dimensions and mass.
- Standard12 pagesEnglish languagee-Library read for1 day
This document specifies the properties of fluorocarbon rubber (FKM)1), hardness 80 IRHD, for aerospace
applications.
- Standard7 pagesEnglish languagee-Library read for1 day
This European Standard specifies the methods for determining the fibre content by volume and mass and, by correlation, the resin content by volume and mass and void content by volume, of carbon fibre laminates, for aerospace applications.
- Standard10 pagesEnglish languagee-Library read for1 day
This European Standard specifies the properties of fluorocarbon rubber (FKM) 1), low compression set, hardness 60 IRHD, for aerospace applications.
1) Symbol as per ISO 1629.
- Standard6 pagesEnglish languagee-Library read for1 day
This European Standard specifies the properties of fluorocarbon rubber (FKM) ), low compression set, hardness 90 IRHD, for aerospace applications.
- Standard6 pagesEnglish languagee-Library read for1 day
This document defines tests on the susceptibility to corrosion in a damp atmosphere of metals in contact with vulcanized rubbers.
- Standard9 pagesEnglish languagee-Library read for1 day
SIGNIFICANCE AND USE
5.1 This test method is designed to produce in-plane shear property data for material specifications, research and development, quality assurance, and structural design and analysis. Factors that influence the shear response and should therefore be reported include the following: material, methods of material preparation and lay-up, specimen stacking sequence and overall thickness, specimen preparation, specimen conditioning, environment of testing, specimen alignment and gripping, speed of testing, time at temperature, void content, and volume percent reinforcement. Properties that may be derived from this test method include the following:
5.1.1 In-plane shear stress versus shear strain response,
5.1.2 In-plane shear chord modulus of elasticity,
5.1.3 Offset shear properties,
5.1.4 Maximum in-plane shear stress for a ±45° laminate, and
5.1.5 Maximum in-plane engineering shear strain for a ±45° laminate.
SCOPE
1.1 This test method determines the in-plane shear response of polymer matrix composite materials reinforced by high-modulus fibers. The composite material form is limited to a continuous-fiber-reinforced composite ±45° laminate capable of being tension tested in the laminate x direction.
1.2 The values stated in either SI units or inch-pound units are to be regarded separately as standard. The values stated in each system are not exact equivalents; therefore, each system must be used independently of the other. Combining values from the two systems may result in nonconformance with the standard.
1.2.1 Within the text, the inch-pound units are shown in brackets.
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.
- Standard8 pagesEnglish languagesale 15% off
- Standard8 pagesEnglish languagesale 15% off