49.025.99 - Other materials
ICS 49.025.99 Details
Other materials
Weitere Materialien der Luft- und Raumfahrttechnik
Autres materiaux
Drugi materiali
General Information
Frequently Asked Questions
ICS 49.025.99 is a classification code in the International Classification for Standards (ICS) system. It covers "Other materials". 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 155 standards classified under ICS 49.025.99 (Other materials). 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 the requirements for hexavalent chromium free anodizing of aluminium and aluminium alloys for corrosion protection, bonding and painting.
This document does not apply to hard anodizing and plasma electrolytic anodizing (micro-arc oxidation).
The purpose of this document is to give design, quality and manufacturing requirements. It does not give complete in-house process instructions; these are given in the processor's detailed process instructions.
- Standard33 pagesEnglish languagee-Library read for1 day
SIGNIFICANCE AND USE
5.1 The freezing point of an aviation fuel is the lowest temperature at which the fuel remains free of solid hydrocarbon crystals. These crystals can restrict the flow of fuel through the fuel system of the aircraft. The temperature of the fuel in the aircraft tank normally decreases during flight depending on aircraft speed, altitude, and flight duration. The freezing point of the fuel must always be lower than the minimum operational fuel temperature.
5.2 Petroleum blending operations require precise measurement of the freezing point.
5.3 This test method produces results which have been found to be equivalent to Test Method D2386 and expresses results to the nearest 0.1 °C, with improved precision over Test Method D2386. This test method also eliminates most of the operator time and judgment required by Test Method D2386.
5.4 When specification requires Test Method D2386, do not substitute this test method or any other test method.
SCOPE
1.1 This test method covers the determination of the temperature below which solid hydrocarbon crystals form in aviation turbine fuels.
1.2 This test method is designed to cover the temperature range of −80 °C to 20 °C; however, 2003 Joint ASTM/IP Interlaboratory Cooperative Test Program mentioned in 12.4 has only demonstrated the test method with fuels having freezing points in the range of −42 °C to −60 °C.
1.3 The values stated in SI units are to be regarded as standard. No other units of measurement are included in this standard.
1.4 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. For specific warning statements, see 7.1, 7.3, and 7.5.
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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- Standard6 pagesEnglish languagesale 15% off
This document specifies the requirements relating to:
Heat-resisting alloy NI-PH1301 (NiCr19Co18Mo4Ti3Al3)
Solution treated and precipitation treated
Bars and sections
De ≤ 200 mm
for aerospace applications.
- Standard9 pagesEnglish languagee-Library read for1 day
This document specifies the requirements relating to:
Heat-resisting alloy NI-PH1301 (NiCr19Co18Mo4Ti3Al3)
Solution treated and precipitation treated
Bars and sections
De ≤ 200 mm
for aerospace applications.
- Standard9 pagesEnglish languagee-Library read for1 day
SIGNIFICANCE AND USE
5.1 Aircraft turbine lubricants, upon standing at low temperatures for prolonged periods of time, may show an increase in kinematic viscosity. This increase may cause lubrication problems in aircraft engines. Thus, this test method is used to ensure that the kinematic viscosity does not exceed the maximum kinematic viscosity in certain specifications for aircraft turbine lubricants.
SCOPE
1.1 This test method covers the determination of the kinematic viscosity of aircraft turbine lubricants at low temperature, and the percent change of viscosity after a 3 h and a 72 h standing period at low temperature.
1.1.1 The range of kinematic viscosities covered by this test method is from 7700 mm2/s to 14 000 mm2/s at –40 °C and from 7000 mm2/s to 17 500 mm2/s at –51 °C. The precision has only been determined for those materials, kinematic viscosity ranges, and temperatures as shown in the precision section. Kinematic viscosities and percent change of viscosity may be measured and reported at other temperatures and other thermal soak period intervals as agreed by the contracting parties.
1.2 The values stated in SI units are to be regarded as standard. No other units of measurement are included in this standard.
1.2.1 The SI unit used in this test method for Kinematic Viscosity is mm2/s. For user reference, 1 mm2/s = 10-6 m2/s = 1 cSt.
1.3 Warning—Mercury has been designated by many regulatory agencies as a hazardous substance that can cause serious medical issues. Mercury, or its vapor, has been demonstrated to be hazardous to health and corrosive to materials. Use caution when handling mercury and mercury-containing products. See the applicable product Safety Data Sheet (SDS) for additional information. The potential exists that selling mercury or mercury-containing products, or both, is prohibited by local or national law. Users must determine legality of sales in their location.
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. For specific hazard statements, see Section 7.
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.
- Standard5 pagesEnglish languagesale 15% off
- Standard5 pagesEnglish languagesale 15% off
This document specifies the general organization of the EN standards for non-metallic materials and their links with other types of standards for aerospace applications.
It corresponds to level 0 (see 4.1).
- Standard8 pagesEnglish languagee-Library read for1 day
This document specifies the general rules for drafting and presentation of EN aerospace series non-metallic material technical specifications.
- Standard21 pagesEnglish languagee-Library read for1 day
The scope includes metallic Powder Bed Fusion technologies for space applications.
A clear definition and implementation of quality monitoring and control means is mandatory and shall address the full end to end metallic PBF process, encompassing:
- Design / Simulation
- Materials management (Powder, shielding gases, other consumables, recycling, etc.)
- Processing
- Post Processing
- Testing
By developing a single standard which can be tailored in the Project definition phase, it will help the Space Industry in performing the following functions
related to metallic PBF technologies over the full end to end process:
(i) select and qualify metallic PBF processes for the appropriate application,
(ii) select and validate raw materials for the appropriate applications,
(iii) define monitoring and control means during production to ensure that metallic PBF parts are produced with the required quality,
(iv) define requirements for applying Non-Destructive Inspection methods for the different metallic PBF parts,
(v) define requirements to verify/qualify space parts produced by metallic PBF processes for the selected applications and associated environment,
(vi) define specific requirements for operators/inspectors/instructors certification,
(vii) define requirements for metallic PBF machines certification,
(viii) define requirements for metallic PBF Companies certification.
The Standard will be complemented with informative Annexes, listing guidelines and best practices on specific technical aspects.
- Standard78 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 general organization of the EN standards for non-metallic materials and their links with other types of standards for aerospace applications.
It corresponds to level 0 (see 4.1).
- Standard8 pagesEnglish languagee-Library read for1 day
This document specifies the general rules for drafting and presentation of EN aerospace series non-metallic material technical specifications.
- Standard21 pagesEnglish languagee-Library read for1 day
This document specifies the method for depositing cadmium layers according to the vacuum deposition process, for use in aerospace construction.
According to this process, cadmium metal is vaporized under vacuum and deposited directly on the base material with an interlayer. The coating produced in this way is ductile and electrically conductive.
This document is applicable whenever referenced.
- Standard15 pagesEnglish languagee-Library read for1 day
SIGNIFICANCE AND USE
5.1 Certain sandwich panel analyses require the Poisson's ratio of the honeycomb core. It is not possible to measure the honeycomb's Poisson's ratio by conventional methods.
5.2 This test method provides a standard method of determining the Poisson’s ratio of honeycomb core materials for design properties, material specifications, research and development applications, and quality assurance.
5.3 Factors that influence the Poisson’s ratio of honeycomb core materials and shall therefore be reported include the following: core material, methods of material fabrication, core geometry, core thickness, core thickness uniformity, cell wall thickness, specimen geometry, specimen preparation, and specimen conditioning.
SCOPE
1.1 This test method covers the determination of the sandwich honeycomb core Poisson's ratio from the anticlastic curvature radii; see Fig. 1.
FIG. 1 Anticlastic Curvature
1.2 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.
1.2.1 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.
- Standard4 pagesEnglish languagesale 15% off
- Standard4 pagesEnglish languagesale 15% off
The scope includes metallic Powder Bed Fusion technologies for space applications.
A clear definition and implementation of quality monitoring and control means is mandatory and shall address the full end to end metallic PBF process, encompassing:
- Design / Simulation
- Materials management (Powder, shielding gases, other consumables, recycling, etc.)
- Processing
- Post Processing
- Testing
By developing a single standard which can be tailored in the Project definition phase, it will help the Space Industry in performing the following functions
related to metallic PBF technologies over the full end to end process:
(i) select and qualify metallic PBF processes for the appropriate application,
(ii) select and validate raw materials for the appropriate applications,
(iii) define monitoring and control means during production to ensure that metallic PBF parts are produced with the required quality,
(iv) define requirements for applying Non-Destructive Inspection methods for the different metallic PBF parts,
(v) define requirements to verify/qualify space parts produced by metallic PBF processes for the selected applications and associated environment,
(vi) define specific requirements for operators/inspectors/instructors certification,
(vii) define requirements for metallic PBF machines certification,
(viii) define requirements for metallic PBF Companies certification.
The Standard will be complemented with informative Annexes, listing guidelines and best practices on specific technical aspects.
- Standard78 pagesEnglish languagee-Library read for1 day
This document provides a list of terms with their definitions illustrated by typical photographs, in order
to define a common vocabulary on the imperfections and damage that may occur during the
manufacture of organic matrix composite materials (which will be called “resin” in this document).
Some types of damage may also be encountered in use.
This document is restricted to their definitions and does not give any acceptance criteria. The word
“imperfection” will be preferred to the word “defect”, although the word “defect” might be usually used.
Defect acceptance criteria to be discussed between the user and customer and documented
appropriately between the two parties.
- Standard54 pagesEnglish languagee-Library read for1 day
SIGNIFICANCE AND USE
4.1 This test method is intended to screen the most obvious poor materials from further consideration. Since the combustion gases more closely resemble the environment generated in rocket motors, this test method is more applicable to screening materials for nozzles and motor liners than for aerodynamic heating.
4.2 The environment for any specific high-temperature thermal protection problem is peculiar to that particular application. The conditions generated by the oxyacetylene heat source in this test method represent only one set of conditions; they do not simulate any specific application. Thus, the test results cannot be used to predict directly the behavior of materials for specific environments, nor can they be used for design purposes. However, over a number of years, the test has been useful in determining the relative merit of materials, particularly in weeding out obviously poor materials from more advanced data-generation programs. It has also been considered for use as a production quality-control test for rocket insulation materials.
4.3 The tester is cautioned to use prudence in extending the usefulness of the test method beyond its original intent, namely, screening. For situations having environments widely different from those of the test, the user is urged to modify the oxyacetylene burner conditions to suit his requirements or perhaps change to a different heat-generating device that provides better simulation.
SCOPE
1.1 This test method covers the screening of ablative materials to determine the relative thermal insulation effectiveness when tested as a flat panel in an environment of a steady flow of hot gas provided by an oxyacetylene burner.
1.2 This test method should be used to measure and describe the properties of materials, products, or assemblies in response to heat and flame under controlled laboratory conditions and should not be used to describe or appraise the fire hazard of materials, products, or assemblies under actual fire conditions. However, results of this test method may be used as elements of a fire risk assessment which takes into account all of the factors which are pertinent to an assessment of the fire hazard of a particular end use.
1.3 The values stated in SI units are to be regarded as the 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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SIGNIFICANCE AND USE
5.1 The data generated by this test method shall be used to determine whether aircraft structural aluminum alloys are liable to be corroded or damaged by application of the test material during routine maintenance operations.
5.2 Interpretation of the sandwich corrosion test results is based on a comparison of the appearance of faying surfaces of three sets of coupons. One set of test coupons is exposed with reagent water only in the faying surfaces, to establish the baseline (controls) against which the panels exposed to the test material are compared. Disregard corrosion at cut edges of the test coupons.
5.3 The relative corrosion severity rating system is provided in order to allow a numerical classification of the test results and to eliminate the necessity for elaborate weight loss measurements. Pitting corrosion, which is rated 4—extensive (severe) corrosion, may involve only a negligible weight loss.
5.4 Relative corrosion severity rating system:
Appearance/Corrosion:
0—No visible corrosion and no discoloration present
1—Very slight corrosion or very slight discoloration, and/or up to 5 % of areaA corroded
2—Discoloration and/or up to 10 % of areaA corroded
3—Discoloration and/or up to 25 % of areaA corroded
4—Discoloration and/or more than 25 % of areaA corroded, and/or pitting
present (A) ”Area” refers to area under the filter paper, or if no filter paper is used, the area where the test material was applied.
SCOPE
1.1 This test method defines the procedure for evaluating the corrosivity of aircraft maintenance chemicals, when present between faying surfaces (sandwich) of aluminum alloys commonly used for aircraft structures. This test method is intended to be used in the qualification and approval of compounds employed in aircraft maintenance operations.
1.2 The values stated in SI units are to be regarded as the standard. The values given in parentheses are for information.
1.3 This standard may involve hazardous materials, operations, and equipment. 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. Specific hazard statements appear in Section 9.
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.
- Standard5 pagesEnglish languagesale 15% off
This document specifies the requirements relating to:
Heat resisting nickel base alloy (NI-P101HT)
Cold worked and solution treated
Bars for machining for fasteners
3 mm ≤ D ≤ 50 mm
for aerospace applications.
- Standard8 pagesEnglish languagee-Library read for1 day
This document specifies the requirements relating to:
Heat resisting alloy FE-PM1708
Vacuum arc remelted
Hardened and tempered
Bars
a or D ≤ 200 mm
1 000 MPa ≤ Rm ≤ 1 140 MPa
for aerospace applications.
- Standard8 pagesEnglish languagee-Library read for1 day
This document specifies the requirements relating to:
Heat resisting alloy FE-PM1708
Vacuum arc remelted
As forged
Forging stock
De ≤ 300 mm
for aerospace applications.
- Standard8 pagesEnglish languagee-Library read for1 day
This document specifies the requirements relating to:
Heat resisting alloy NI-PH2601
Solution treated and cold worked
Bar for forged fasteners
D ≤ 50 mm
1 550 MPa ≤ Rm ≤ 1 830 MPa
for aerospace applications.
- Standard8 pagesEnglish languagee-Library read for1 day
This document specifies the requirements relating to:
Heat resisting nickel base alloy (NI-P100HT)
Cold worked and softened
Bar and wire for continuous forging or extrusion for fasteners
3 mm ≤ D ≤ 30 mm
- Standard8 pagesEnglish languagee-Library read for1 day
This document specifies the requirements relating to:
Heat resisting alloy FE-PM1708
Vacuum arc remelted
Hardened and tempered
Bars
a or D ≤ 200 mm
1 000 MPa ≤ Rm ≤ 1 140 MPa
for aerospace applications.
- Standard8 pagesEnglish languagee-Library read for1 day
This document specifies the requirements relating to:
Heat resisting nickel base alloy (NI-P101HT)
Cold worked and solution treated
Bars for machining for fasteners
3 mm ≤ D ≤ 50 mm
for aerospace applications.
- Standard8 pagesEnglish languagee-Library read for1 day
This document specifies the requirements relating to:
Heat resisting alloy FE-PM1708
Vacuum arc remelted
As forged
Forging stock
De ≤ 300 mm
for aerospace applications.
- Standard8 pagesEnglish languagee-Library read for1 day
This document defines the requirements for the preparation of forged test samples.
Unless otherwise specified on the drawing, order, or inspection schedule, this document shall be applied when referenced in the relevant EN material standard or EN technical specification.
This document applies to round products of ≥ 20 mm diameters or other shapes of equivalent cross-section.
- Standard7 pagesEnglish languagee-Library read for1 day
This document specifies the requirements relating to:
Heat resisting nickel base alloy (NI-P100HT)
Cold worked and softened
Bar and wire for continuous forging or extrusion for fasteners
3 mm ≤ D ≤ 30 mm
- Standard8 pagesEnglish languagee-Library read for1 day
This document specifies the requirements relating to:
Heat resisting alloy NI-PH2601
Solution treated and cold worked
Bar for forged fasteners
D ≤ 50 mm
1 550 MPa ≤ Rm ≤ 1 830 MPa
for aerospace applications.
- Standard8 pagesEnglish languagee-Library read for1 day
This document specifies the requirements relating to:
Heat resisting alloy NI-PH1302 (NiCr20Co13Mo4Ti3Al)
Solution treated and cold worked
Bar for forged fasteners
3 mm ≤ D ≤ 30 mm
for aerospace applications.
- Standard8 pagesEnglish languagee-Library read for1 day
This document defines the requirements for the preparation of forged test samples.
Unless otherwise specified on the drawing, order, or inspection schedule, this document shall be applied when referenced in the relevant EN material standard or EN technical specification.
This document applies to round products of ≥ 20 mm diameters or other shapes of equivalent cross-section.
- Standard7 pagesEnglish languagee-Library read for1 day
SIGNIFICANCE AND USE
3.1 The data generated by this test method shall be used to determine whether low embrittling cadmium plated parts are liable to be corroded or damaged by application of the test material during routine maintenance operations.
SCOPE
1.1 This test method is intended as a means of determining the corrosive effects of aircraft maintenance chemicals on low-embrittling cadmium plating used on aircraft high-strength steel, under conditions of total immersion by quantitative measurements of weight change.
1.2 This standard may involve hazardous materials, operations, and equipment. 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. For specific hazard statements see Section 6, 4.1.
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.
- Standard3 pagesEnglish languagesale 15% off
This European Standard specifies the requirements relating to:
Heat resisting alloy NI-PH2601
Solution treated and cold worked
Bar for forged fasteners
D ≤ 50 mm
1 270 MPa ≤ Rm ≤ 1 550 MPa
for aerospace applications.
- Standard8 pagesEnglish languagee-Library read for1 day
This document specifies the requirements relating to:
Heat resisting nickel base alloy (Ni-P101HT)
Cold worked and softened
Bar and wire for continuous forging or extrusion for fasteners
3 mm ≤ D ≤ 30 mm
for aerospace applications.
- Standard8 pagesEnglish languagee-Library read for1 day
SIGNIFICANCE AND USE
5.1 The NVR obtained by this test method is that amount which is available for release by wipers in normal use.
5.2 Evaporation of the solvent at the stated temperature is to quantify the NVR that can be expected to exist at room temperature, since the slight difference between room temperature and test temperature has not been shown to result in significant variances.
5.3 This test method may be more aggressive than necessary for the evaluation of wipers that will be restricted to dry use only.
5.4 Numerous other methods are being used to determine NVR. This test method is not intended to replace test methods used for other applications.
SCOPE
1.1 This test method covers the determination of solvent extractable nonvolatile residue (NVR) from wipers used in assembly, cleaning, or testing of spacecraft, but not from those used for analytical surface sampling of hardware.
1.2 The NVR of interest is that which can be extracted from cleanroom wipers using a specified solvent that has been selected for its extractive qualities. Alternative solvents may be selected, but since their use may result in different values being generated, they must be identified in the procedure data sheet.
1.3 The values stated in SI units are to be regarded as standard. No other units of measurement are included in this standard.
1.3.1 Exception—The inch-pound units are included for information only.
1.4 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.
1.5 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
- Standard5 pagesEnglish languagesale 15% off
- Standard5 pagesEnglish languagesale 15% off
SIGNIFICANCE AND USE
5.1 The NVR obtained by this test method is that amount which is available for release by the gloves onto handled surfaces.
5.2 Evaporation of solvent at the stated temperature is to quantify the NVR that can be expected to exist at room temperature, since the slight difference between room temperature and the test temperature is not likely to result in significant variances.
5.3 This method may be more aggressive than necessary to determine the suitability of cleanroom gloves that are restricted to dry operations only.
5.4 Various other methods exist for determining NVR, for example Practice G120 and IEST-RP-CC005. This test is not intended to replace test methods used for other purposes.
SCOPE
1.1 This test method covers the determination of solvent extractable nonvolatile residue (NVR) from gloves used in cleanrooms where spacecraft are assembled, cleaned, or tested.
1.2 The NVR of interest is that which can be extracted from gloves using a specified solvent that has been selected for its extracting qualities, or because it is representative of solvents used in the particular facility. Alternative solvents may be used, but since their use may result in different values being generated, they must be identified in the procedure data sheet.
1.3 The values stated in SI units are to be regarded as standard. No other units of measurement are included in this standard.
1.4 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.
- Standard5 pagesEnglish languagesale 15% off
This European Standard specifies two methods for the determination of the application time of sealants.
- Standard6 pagesEnglish languagee-Library read for1 day
This European Standard specifies two methods for the determination of the application time of sealants.
- Standard6 pagesEnglish languagee-Library read for1 day
This standard describes the preparation of panels with any desired fibre orientation of unidirectional orientated carbon fibre or fabric with thermosetting resins.
The purpose of this standard is to describe recommended processes for the preparation of the panels from which test specimens subsequently are machined.
Standard specimens prepared in this manner may be used either for evaluating the components i.e. the carbon reinforcement, finishes, resins, catalysts, curing agents, etc. or for verifying the overall quality of the finished products.
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This standard specifies the requirements for glass fabric/phenolic resin preimpregnates.
It shall be used together with EN 2833-1.
- Standard9 pagesEnglish languagee-Library read for1 day
This European Standard defines the requirements for the determination of the modulus of rupture of glass transparencies for aircraft applications, whether in the annealed or chemically or thermally tempered condition.
- Standard9 pagesEnglish languagee-Library read for1 day
This European Standard defines the requirements for the determination of the flatness of monolithic glass transparencies for aircraft applications. The method is designed to eliminate the effect of the glass deflecting under its own weight, thus eliminating false results.
- Standard9 pagesEnglish languagee-Library read for1 day
This European Standard specifies the requirements relating to universally available and high light transmission, chemically tempered float glass plies, for aerospace applications.
- Standard8 pagesEnglish languagee-Library read for1 day
This European Standard specifies the requirements relating to universally available and high light transmission, thermally tempered float glass plies, for aerospace applications.
- Standard8 pagesEnglish languagee-Library read for1 day
This European Standard defines a qualitative method for the determination of the ream and surface ripple in glass transparencies for aircraft applications.
- Standard7 pagesEnglish languagee-Library read for1 day
This European Standard defines the requirements for the determination of the modulus of rupture of glass transparencies for aircraft applications, whether in the annealed or chemically or thermally tempered condition.
- Standard9 pagesEnglish languagee-Library read for1 day
This European Standard defines the test method for the determination of the operability of a cured sealant during and after submission to a bending load at low temperatures (low-temperature flexibility).
- Standard7 pagesEnglish languagee-Library read for1 day
This European Standard defines a qualitative method for the determination of the ream and surface ripple in glass transparencies for aircraft applications.
- Standard7 pagesEnglish languagee-Library read for1 day
This European Standard specifies the requirements relating to universally available and high light transmission, thermally tempered float glass plies, for aerospace applications.
- Standard8 pagesEnglish languagee-Library read for1 day
This European Standard specifies the requirements relating to universally available and high light transmission, chemically tempered float glass plies, for aerospace applications.
- Standard8 pagesEnglish languagee-Library read for1 day
This European Standard defines the requirements for the determination of the flatness of monolithic glass transparencies for aircraft applications. The method is designed to eliminate the effect of the glass deflecting under its own weight, thus eliminating false results.
- Standard9 pagesEnglish languagee-Library read for1 day