This document provides a series of standard testing methods to determine the resistance of flat or curved surfaces against abrasion, scratch or punch under high dynamics as may occur for example by manually operating actuators or due to impacts of materials like shoes, cases, bags and other common objects of everyday’s usage inside an aircraft cabin. The method is also suitable to test the resistance of a surface against all other high dynamic strains.

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This document specifies requirements and test methods for the qualification of laser beam machines for metal powder bed additive manufacturing for aerospace applications.

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  • Standard
    19 pages
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This European Standard specifies the dimensions and tolerances of cold rolled sheets and strips in heat resisting alloys used in aerospace construction.

  • Standard
    9 pages
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This document specifies the dimensions and tolerances of cold rolled sheets and strips in heat resisting alloys used in aerospace construction.

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This European Standard specifies the marking rules for aerospace products, semi-finished products, and
ready to use parts, which need surface marking by discoloration using a laser source to identify the part
and/or enhance its traceability.
This type of marking can be used on a wide range of materials (both metallic and non-metallic) and
coatings (paints, varnishes…). It is in line with the part definition.

  • Standard
    16 pages
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This European Standard specifies the marking rules for aerospace products, semi-finished products, and ready to use parts, which need surface marking by discoloration using a laser source to identify the part and/or enhance its traceability.
This type of marking can be used on a wide range of materials (both metallic and non-metallic) and coatings (paints, varnishes…). It is in line with the part definition.

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This European Standard specifies the dimensions and tolerances of heat resisting alloys wire used in aerospace construction.

  • Standard
    6 pages
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This European Standard specifies the dimensions and tolerances of heat resisting alloys wire used in aerospace construction.

  • Standard
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This test method defines the procedure for the determination of the curing-characteristic and glass transition temperature of non-metallic materials (e.g. preimpregnated and neat resin systems, adhesives) for aerospace use by Differential Scanning Calorimetry (DSC).
The results obtained by this method may be useful for:
   derivation of the optimum cure cycle (only together with other test methods e.g. Tg determination)
   assessment of the condition of the resin
   assessment of the ageing behavior of the resin
This standard does not give any directions necessary to meet the health and safety requirements. It is the responsibility of the user of this standard to adopt appropriate health and safety precautions.

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This test method defines the procedure for the determination of the curing-characteristic and glass transition temperature of non-metallic materials (e.g. preimpregnated and neat resin systems, adhesives) for aerospace use by Differential Scanning Calorimetry (DSC).
The results obtained by this method may be useful for:
-   derivation of the optimum cure cycle (only together with other test methods e.g. Tg determination)
-   assessment of the condition of the resin
-   assessment of the ageing behavior of the resin
This European Standard does not give any directions necessary to meet the health and safety requirements. It is the responsibility of the user of this European Standard to adopt appropriate health and safety precautions.

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This test method defines the procedure for the estimation of the extent of cure of certain non-metallic materials (e.g. preimpregnated and neat resin systems, adhesives) for aerospace use. The extent of cure is estimated by Differential Scanning Calorimetry (DSC) measurements of uncured (reference) and cured materials. Additional evidence on the extent of cure may be gained by combining results from this method with those obtained by other techniques.
This standard does not give any directions necessary to meet the health and safety requirements. It is the responsibility of the user of this standard to adopt appropriate health and safety precautions.

  • Standard
    11 pages
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This test method defines the procedure for the estimation of the extent of cure of certain non-metallic materials (e.g. preimpregnated and neat resin systems, adhesives) for aerospace use. The extent of cure is estimated by Differential Scanning Calorimetry (DSC) measurements of uncured (reference) and cured materials. Additional evidence on the extent of cure may be gained by combining results from this method with those obtained by other techniques.
This standard does not give any directions necessary to meet the health and safety requirements. It is the responsibility of the user of this standard to adopt appropriate health and safety precautions.

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    11 pages
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This European Standard defines the determination of density according to displacement method for metallic materials.

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    4 pages
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This European Standard specifies the requirements relating to:
Heat resisting alloy NiCr19Fe19Nb5Mo3 (2.4668)
Solution treated and precipitation treated
Bar and section
De ≤ 200 mm
for aerospace applications.

  • Standard
    9 pages
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This European Standard specifies the requirements relating to:
Heat resisting alloy NI-PH2601 (NiCr19Fe19Nb5Mo3)
Solution treated and precipitation treated
Bar and section
De  200 mm
for aerospace applications.

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This European Standard specifies the characteristics of screws, 100° countersunk normal head, offset cruciform recess, coarse tolerance normal shank, medium length thread, in alloy steel, cadmium plated.
Classification: 1 100 MPa  / 235 °C.

  • Standard
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This European Standard specifies the requirements relating to:
Heat resisting alloy NiCr19Fe19Nb5Mo3 (2.4668)
Non heat treated
Forging stock
a or D ≤ 300 mm
for aerospace applications.

  • Standard
    7 pages
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This European Standard specifies the requirements relating to:
Heat resisting alloy NiCr19Fe19Nb5Mo3 (2.4668)
Non heat treated
Forging stock
a or D <= 300 mm
for aerospace applications.

  • Standard
    7 pages
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This Standard covers the following processes of the general materials, mechanicals parts and processes (MMPP) flow of ECSS-Q-ST-70:
•   The selection of metal alloys for which preference is given to approved data sources (Table 5 1 to Table 5 3)
•   The criticality analysis to determine if a stress corrosion cracking (SCC) evaluation is necessary
This Standard sets forth the criteria to be used in the selection of materials for spacecraft and associated equipment and facilities so that failure resulting from stress-corrosion is prevented.
It is intended to provide general criteria to be used in stress-corrosion cracking control, which begins during design thanks to a methodological material selection.
This document does not intend to include all factors and criteria necessary for the total control of stress­corrosion cracking in all alloys.
The criteria established in this Standard are only applicable to designs for service involving exposure conditions similar to testing conditions
As regards weldments, this Standard is applicable to aluminium alloys, selected stainless steels in the 300 series and alloys listed in Table 5 1.
This Standard is not applicable to listed materials whose behaviour differs at elevated temperature and in specific chemical.
This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.

  • Standard
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Several classes of materials depend on a chemical reaction for their application and their final properties are sensitive to the exact composition of the reactants. The final properties vary with the reactants’ age and storage condition.
This Standard defines the requirements for the identification, handling, storage and control of limited shelf­life materials employed in the fabrication of spacecraft and associated equipment.
This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.

  • Standard
    13 pages
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This Standard describes a thermal vacuum test to determine the outgassing screening properties of materials proposed for use in the fabrication of spacecraft and associated equipment, for vacuum facilities used for flight hardware tests and for certain launcher hardware.
This Standard covers the following:
• critical design parameters of the test system;
• critical test parameters such as temperature, time, pressure;
• material sample preparation;
• conditioning parameters for samples and collector plates;
• presentation of the test data;
• acceptance criteria;
• certification of test systems and their operators by audits and round robin tests.
The test described in this Standard is applicable for all unmanned spacecraft, launchers, payloads, experiments. The test is also valid for external hardware of inhabited space systems and for hardware to be used in terrestrial vacuum test facilities.
The outgassing and condensation acceptance criteria for a material depend upon the application and location of the material and can be more severe than the standard requirements as given in clause 5.5.3.1.
This standard may be tailored for the specific characteristics and constrains of a space project in conformance with ECSS‐S‐ST‐00. 7

  • Standard
    44 pages
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This Standard specifies requirements for mechanical testing of metallic materials to be used in the fabrication of spacecraft hardware.
This Standard establishes the requirements for most relevant test methods carried out to assess the tensile, fatigue and fracture
properties of metallic materials. It does not give a complete review of all the existing test methods for the evaluation of mechanical
properties of metallic materials.
Furthermore, this Standard specifies requirements for the evaluation, presentation and reporting of test results.
This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.

  • Standard
    32 pages
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    32 pages
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Materials used in space applications need to be evaluated for their behaviour under Particle and UV Radiation. As part of this evaluation often an exposure to a simulated space environment is performed that can raise questions regarding its accuracy and representativeness. The role of this Standard is to establish a baseline for the testing specification. NOTE The environments covered are electromagnetic radiation and charged particles. This Standard defines the procedures for electromagnetic radiation and charged particles testing of spacecraft materials. These materials include for instance thermal control materials, windows, coatings, and structural materials. The procedures include simulation of the environment and the properties to be verified. This Standard excludes electronic components. This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.

  • Standard
    27 pages
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This Standard defines a multi­test procedure for the determination of the flammability characteristics of non­metallic materials under a set of closely controlled conditions. The test procedure covers both individual materials and materials used in configuration. This Standard describes a series of tests to provide data for aid in the evaluation of the suitability of materials for use in a space vehicle crew compartment. The data obtained are in respect to the ease of ignition and the flame propagation characteristics of materials.
All non­metallic materials are inherently flammable, the degree to which this is true is dependant on the chemical nature of the material itself and the environment to which the material is exposed. In the closed environment of a manned spacecraft this can lead to a potentially dangerous situation and close control is therefore required.
This standard may be tailored for the specific characteristics and constrains of a space project in conformance with ECSS-S-ST-00.

  • Standard
    47 pages
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Several classes of materials depend on a chemical reaction for their application and their final properties are sensitive to the exact composition of the reactants. The final properties vary with the reactants’ age and storage condition.
This Standard defines the requirements for the identification, handling, storage and control of limited shelf­life materials employed in the fabrication of spacecraft and associated equipment.
This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.

  • Standard
    13 pages
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    13 pages
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This Standard specifies requirements for mechanical testing of metallic materials to be used in the fabrication of spacecraft hardware.
This Standard establishes the requirements for most relevant test methods carried out to assess the tensile, fatigue and fracture
properties of metallic materials. It does not give a complete review of all the existing test methods for the evaluation of mechanical
properties of metallic materials.
Furthermore, this Standard specifies requirements for the evaluation, presentation and reporting of test results.
This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.

  • Standard
    32 pages
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    32 pages
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This document defines the requirements for the evaluation of the susceptibility of the SCC resistance.
It defines the preferred way to determine the susceptibility of metals and weldments to stress-corrosion cracking by alternate immersion
in 3.5 % sodium chloride under constant load.
The results obtained from test programmes made according to this specification are used to classify alloys, weldments and their individual heat treatment conditions. When sufficient stress-corrosion data exists, the alloy designations can be submitted for inclusion into the
various tables contained in ECSS-Q-ST-70-36.
In this document, the supplier is identified as the entity that performs the test.
This standard may be tailored for the specific characteristics and constrains of a space project in conformance with ECSS-S-ST-00.

  • Standard
    32 pages
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    32 pages
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This Standard covers the following processes of the general materials, mechanicals parts and processes (MMPP) flow of ECSS-Q-ST-70:
•   The selection of metal alloys for which preference is given to approved data sources (Table 5 1 to Table 5 3)
•   The criticality analysis to determine if a stress corrosion cracking (SCC) evaluation is necessary
This Standard sets forth the criteria to be used in the selection of materials for spacecraft and associated equipment and facilities so that failure resulting from stress-corrosion is prevented.
It is intended to provide general criteria to be used in stress-corrosion cracking control, which begins during design thanks to a methodological material selection.
This document does not intend to include all factors and criteria necessary for the total control of stress­corrosion cracking in all alloys.
The criteria established in this Standard are only applicable to designs for service involving exposure conditions similar to testing conditions
As regards weldments, this Standard is applicable to aluminium alloys, selected stainless steels in the 300 series and alloys listed in Table 5 1.
This Standard is not applicable to listed materials whose behaviour differs at elevated temperature and in specific chemical.
This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.

  • Standard
    39 pages
    English language
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  • Draft
    39 pages
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This Standard defines a multi­test procedure for the determination of the flammability characteristics of non­metallic materials under a set of closely controlled conditions. The test procedure covers both individual materials and materials used in configuration. This Standard describes a series of tests to provide data for aid in the evaluation of the suitability of materials for use in a space vehicle crew compartment. The data obtained are in respect to the ease of ignition and the flame propagation characteristics of materials.
All non­metallic materials are inherently flammable, the degree to which this is true is dependant on the chemical nature of the material itself and the environment to which the material is exposed. In the closed environment of a manned spacecraft this can lead to a potentially dangerous situation and close control is therefore required.
This standard may be tailored for the specific characteristics and constrains of a space project in conformance with ECSS-S-ST-00.

  • Standard
    47 pages
    English language
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This Standard describes a thermal vacuum test to determine the outgassing screening properties of materials proposed for use in the fabrication of spacecraft and associated equipment, for vacuum facilities used for flight hardware tests and for certain launcher hardware.
This Standard covers the following:
• critical design parameters of the test system;
• critical test parameters such as temperature, time, pressure;
• material sample preparation;
• conditioning parameters for samples and collector plates;
• presentation of the test data;
• acceptance criteria;
• certification of test systems and their operators by audits and round robin tests.
The test described in this Standard is applicable for all unmanned spacecraft, launchers, payloads, experiments. The test is also valid for external hardware of inhabited space systems and for hardware to be used in terrestrial vacuum test facilities.
The outgassing and condensation acceptance criteria for a material depend upon the application and location of the material and can be more severe than the standard requirements as given in clause 5.5.3.1.
This standard may be tailored for the specific characteristics and constrains of a space project in conformance with ECSS‐S‐ST‐00. 7

  • Standard
    44 pages
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This European Standard specifies the method of performing ultrasonic testing. The general requirements are given in EN 4050-1.

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    13 pages
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This European Standard specifies the requirements for the manufacture, checking and marking of the series of ultrasonic testing reference blocks containing flat bottom holes (FBH) which define the indicated defect size to which reference is made in EN standards.

  • Standard
    11 pages
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This European Standard defines the ultrasonic inspection procedure for rolled, drawn, extruded and forged billets, bars and plates, rolled rings and forgings with a uniform square, rectangular or round cross section. It does not cover critical rotating parts in steel, titanium, titanium alloys, aluminium alloys and heat resisting alloys that are to be inspected in accordance with the technical supply conditions of the relevant EN standards or internal specifications.

  • Standard
    13 pages
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This European Standard specifies the acceptance criteria for products ultrasonically inspected in accordance with EN 4050-1.

  • Standard
    5 pages
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ISO 16691:2014 defines general requirements for thermal control coatings (TCC) that are applied on metallic and/or non-metallic surfaces of spacecraft and payloads in order to provide the following thermo-optical properties: αs: solar absorptance; ε: emittance. The function of TCC is to reduce external heat absorption and/or to regulate radiant heat exchange between on-board equipment on spacecraft.

  • Standard
    17 pages
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This standard specifies the requirements relating to:
Heat resisting alloy FE-PA4901 (X12CrNiCoMoW21-20)
As forged
Forging stock
a or D 200 mm
690 MPa  Rm  880 MPa
for aerospace applications.

  • Standard
    8 pages
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This standard specifies the requirements relating to:
Heat resisting alloy FE-PA4901 (X12CrNiCoMoW21-20)
As forged
Forging stock
a or D  200 mm
690 MPa  Rm  960 MPa
for aerospace applications.

  • Standard
    8 pages
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This European Standard defines degrees of weldability and brazeability for materials or families of materials used in the aerospace applications.
It comprises a series of sheets, by materials or by material family, which:
- indicate the main titles, the typical chemical composition and the main characteristics,
- contain recommendations for welding and brazing,
- indicate a degree of weldability or brazeability for a given process under defined conditions.
It is applicable without restriction for the manufacturing of new parts or for repair.

  • Standard
    26 pages
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This European Standard specifies the general rules for the drafting and presentation of metallic material standards for aerospace applications.
It is supported by additional rules specific to:
-   Aluminium, aluminium alloys and magnesium alloys   EN 4500-2;
-   Heat resisting alloys   EN 4500-003;
-   Titanium and titanium alloys   EN 4500-004;
-   Steels   EN 4500-005;
-   Filler metals for welding   EN 4500-2 to EN 4500-005;
-   Filler metals for brazing   EN 4500-6.

  • Standard
    23 pages
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This European Standard specifies the specific rules for the drafting and presentation of titanium and titanium alloy material standards for aerospace applications.
It should be used in conjunction with EN 4500-001.

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    20 pages
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This European Standard specifies the specific rules for the drafting and presentation of heat resisting alloy material standards for aerospace applications.
It should be used in conjunction with EN 4500-001.

  • Standard
    21 pages
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This European Standard specifies the specific rules for the drafting and presentation of steels material standards for aerospace applications.
It should be used in conjunction with EN 4500-001.

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    20 pages
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This European Standard specifies the weldability and brazeability of materials or material families used in the
aerospace industry.
It comprises a series of sheets, by materials or material family, which:
- indicate the main titles, the typical chemical composition and the main characteristics,
- contain recommendations for welding and brazing,
- indicate a degree of weldability or brazeability for a given process under defined conditions,
- indicate a value for the welded joint mechanical resistance coefficient for each welding process when
extracted from relevant bibliographical references. Joint coefficient is the ratio of stress resistance
transversally to welded joint over tensile strength of parent alloy.
It recommends ISO/TR 17671-3 and EN 1011-3 for pre-heating conditions specially for the welding of
martensitic steels. These conditions depend on the line energy of welding, thickness, arc welding process and
of hydrogen rate in filler metal.
It applies unreservedly to the manufacturing of new parts or for repair.

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    35 pages
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ISO/TS 16697:2012 provides a method to determine the oxygen concentration threshold when a material exposed to a standard ignition source self-extinguishes at a given constant total pressure, temperature, convective flow, and gravity-level conditions. The method can also be used to determine other flammability limits, such as the total pressure or forced convective velocity thresholds, while maintaining other test conditions constant.

  • Technical specification
    8 pages
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This European Standard specifies the requirements for ultrasonic inspection of tubes in metallic materials with an external diameter  5 mm.
For other cases, the use of this standard is by agreement between the manufacturer and the purchaser.
The purpose of the ultrasonic inspection is the detection of defects within the wall thickness and at the outer and inner surfaces of the tube. The method will detect two dimensional defects in the longitudinal and circumferential directions perpendicular to the tube wall. Where inspection for other types of defects is required, this requirements shall be stated on the order.

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This standard defines the test equipment, apparatus and media required for determination of the smoke density according to EN 2825 and the concentration of the gas components in the smoke according to EN 2826 due to pyrolitic decomposition of solid materials and composite materials of up to 25 mm in thickness under the influence of radiant heat only or with simultaneous flame application.
This test method applies exclusively to materials whose specific standard requires this type of test. It cannot be substituted for the statutory tests required for a final specific use of the material concerned.
NOTE   The smoke gas density and the gas components in the smoke are determined according to the specific environmental and test conditions defined in this standard, in EN 2825 and EN 2826. No studies have been made up to now to determine whether the results can be transferred to differing conditions, particularly to actual fire conditions. The inhalatory toxical risk and irritancy affect cannot be assessed by merely measuring the concentration of individual gas components in the smoke.

  • Standard
    18 pages
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This standard defines the test equipment, apparatus and media required for determination of the smoke density according to EN 2825 and the concentration of the gas components in the smoke according to EN 2826 due to pyrolitic decomposition of solid materials and composite materials of up to 25 mm in thickness under the influence of radiant heat only or with simultaneous flame application.
This test method applies exclusively to materials whose specific standard requires this type of test. It cannot be substituted for the statutory tests required for a final specific use of the material concerned.
NOTE   The smoke gas density and the gas components in the smoke are determined according to the specific environmental and test conditions defined in this standard, in EN 2825 and EN 2826. No studies have been made up to now to determine whether the results can be transferred to differing conditions, particularly to actual fire conditions. The inhalatory toxical risk and irritancy affect cannot be assessed by merely measuring the concentration of individual gas components in the smoke.

  • Standard
    18 pages
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This standard defines a test method for determination of the smoke density due to pyrolitic decomposition of solid materials and composite materials of up to 25 mm in thickness under the influence of radiant heat only or with simultaneous flame application.
The test results enable a comparison of the smoke production of different materials or material configurations under the conditions specified in this standard.
NOTE 1   The smoke gas density is determined according to the specific environmental and test conditions defined in EN 2824 and this standard. No studies have been made up to now to determine whether the results can be transferred to differing conditions, particularly to actual fire conditions.
NOTE 2   The burning behaviour - and consequently the smoke density - of aerospace materials are not only influenced by the type of material but also to a large extent by the configuration, the specific surface and mass, the combination with other materials, the means of joining as well as the processing technique.

  • Standard
    9 pages
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This standard defines a test method to determine the concentration of certain gas components due to pyrolitic decomposition of solid materials and composite materials under the influence of radiant heat only or with simultaneous flame application.
NOTE 1   The gas components in the smoke are determined according to the specific environmental and test conditions defined in EN 2824 and this standard. No studies have been made up to now to determine whether the results can be transferred to different conditions, particularly to actual fire conditions. The inhalatory toxical risk and irritancy affect cannot be assessed by merely measuring the concentration of individual gas components in the smoke.
NOTE 2   The burning behaviour - and consequently the gas components in the smoke - of aerospace materials are not only influenced by the type of material but also to a large extent by the configuration, the specific surface and mass, the combination with other materials, the means of joining as well as the processing technique.
NOTE 3   These influences should be taken into account in the preparation of tests, the selection of test specimens and the interpretation of test results.

  • Standard
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This standard specifies the requirements for shear testing rivet wire and rivets in metallic materials for aerospace applications.
It shall be applied when referred to in the EN technical specification or material standard unless otherwise specified on the drawing, order or inspection schedule.

  • Standard
    10 pages
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