49.045 - Structure and structure elements

ASTM F1362-18(2023)(Test Method)

Standard Test Method for Shear Strength and Shear Modulus of Aerospace Glazing Interlayer Materials

SIGNIFICANCE AND USE
5.1 The basic material properties obtained from this test method can be used in the control of the quality of interlayers, in the theoretical equations for designing laminated transparencies, and in the evaluation of new interlayers.
SCOPE
1.1 This test method covers the determination of the shear strength and shear modulus of interlayer materials that are restrained by relatively high modulus plies in laminated transparencies. This test method can be used with single or multiple plies of the same interlayer materials.
1.2 The values stated in SI units are to be regarded as the standard. The values in parentheses are 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.

Standard
5 pages
English language
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30-Apr-2023
49.045
F07

Standard Guide for Testing Materials for Aerospace Plastic Transparent Enclosures

ASTM F790-23(Guide)

SIGNIFICANCE AND USE
3.1 This guide is intended for use by material suppliers, aircraft transparent enclosure fabricators, air-frame manufacturers, government agencies, and others that may become involved in the testing of transparency components. These test methods provide data on both individual materials and material combinations commonly utilized in the fabrications of aerospace transparent enclosures comprised of monolithic plastic, coated monolithic plastic or laminated constructions containing plastics.
3.2 Primary properties and their long term stability are critical to the performance of aerospace transparent enclosures. Property measurement tests define as-manufactured material properties of these materials. Aging procedures provide for exposure of parts or representative sections to environments that induce changes in material properties as determined in property measurement tests. Property measurement tests performed before and after aging exposure provide a means of estimating the potential usable life span of a transparency or to compare the durability of one material with another.
3.3 When employing these test methods for comparison of materials for weathering effects the user should be aware that the many factors influencing degradation due to weathering vary from one location to another. For direct weathering comparisons, all material(s) shall undergo exposure conditions and property measurements testing at the same time.
3.4 The test methods listed include those considered critical to the performance of aircraft transparent enclosures. Other test methods to evaluate materials shall also be performed where necessary. Additional test methods are in preparation and will be incorporated. The user is advised to employ the latest revision of any test method.
3.5 The dominant component of all transparent enclosures is one, or more, rigid transparent sheet(s). The sheet(s) must permit the necessary visibility while providing structural integrity and protecting the ...
SCOPE
1.1 This guide is intended to summarize the standard test methods available on individual and composite materials utilized in fabrication of aerospace plastic transparent enclosures. As such, it is intended to specifically include transparent thermoplastics, transparent elastomers, and reinforced plastics, whether thermoplastic or thermosetting.
1.2 This guide is intended as an aid in the search for test methods pertinent to Aerospace Plastic Transparent Enclosures. It should be understood that all methods listed may not apply to all enclosures.
1.3 The standards included refer to the properties or aspects listed in Table 1. The properties or aspects are listed in alphabetical order and the descriptions used are intended to facilitate the search.
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.

Guide
5 pages
English language
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Guide
5 pages
English language
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31-Dec-2022
49.045
F07

ASTM F3114-21(Specification)

Standard Specification for Structures

ABSTRACT
This specification prescribes structural requirements that apply to all portions of the airframe regardless of component, system, or structure. The applicant for a design approval must seek individual guidance from their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
The structural requirements described in this specification cover strength (loads, factor of safety, strength and deformation, proof of structure, vibration and buffeting, canard or tandem wing configurations, windshields and windows, landing gear, testing of wings and control surfaces, pressurization tests); mass and mass distribution (load distribution limits, leveling means; materials, processes, and methods of fabrication (materials and workmanship, fabrication methods, material strength properties and design values; and protection of structure (fasteners, accessibility provisions, fire protection of engine mounts, and other flight structure). Also addressed are special factors of safety, including casting factors, bearing factors, fitting factors, and configuration based factors.
SCOPE
1.1 This specification addresses the structural requirements that apply to all portions of the airframe regardless of component, system, or structure.
1.2 This specification was originally conceived for small airplanes as defined in the F44 terminology standard but may find broader applicability. Use of the term aircraft throughout this specification is intended to allow the relevant CAA(s) to accept this standard as a means of compliance as they determine it to be appropriate, whether for small airplanes or for other types of aircraft.
1.3 The applicant for a design approval must seek individual guidance from their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Small Airplane Airworthiness Rules (hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMMITTEE/F44.htm) which includes CAA website links.
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.

Technical specification
5 pages
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Technical specification
5 pages
English language
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30-Apr-2021
49.045
F44

ASTM F520-21(Test Method)

Standard Test Method for Environmental Resistance of Aerospace Transparencies to Artificially Induced Exposures

SIGNIFICANCE AND USE
4.1 This test method, when applied to aerospace transparencies of either monolithic glass/plastic or laminated combinations, is a measure of the ability of the transparency to withstand the effects of artificially induced environments. The test applies to configurations employing electrically conductive coatings, and also to uncoated materials.
4.2 The resistance of the transparent enclosure to environmental effects may vary appreciably depending on the size, geometry, material of construction, coating integrity, coating density, and other factors.
SCOPE
1.1 This test method covers determination of the effects of exposure to thermal shock, condensing humidity, and simulated weather on aerospace transparent enclosures.
1.2 This test method is not recommended for quality control, nor is it intended to provide a correlation to actual service life.
1.3 Units—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 Exceptions—Certain inch-pound units are furnished in parentheses (not mandatory) and certain temperatures in Fahrenheit associated with other standards are also furnished.
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.

Standard
4 pages
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Standard
4 pages
English language
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30-Apr-2021
49.045
F07

ASTM F330-21(Test Method)

Standard Test Method for Bird Impact Testing of Aerospace Transparent Enclosures

SIGNIFICANCE AND USE
4.1 This test method shall be used for: bird impact testing of aircraft crew compartment transparencies and supporting structure to verify the design; compilation of test data for use in verification of future transparency and supporting structure design and analytical methods; and comparative evaluation of materials.
SCOPE
1.1 This test method covers conducting bird impact tests under a standard set of conditions by firing a packaged bird at a stationary aerospace transparency (windshield, canopy, or window) mounted in a support structure.
1.2 Units—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.
1.3 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. For specific hazard statements, see Section 8.
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.

Standard
5 pages
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Standard
5 pages
English language
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30-Apr-2021
49.045
F07

ASTM F320-21(Test Method)

Standard Test Method for Hail Impact Resistance of Aerospace Transparent Enclosures

SIGNIFICANCE AND USE
4.1 This test method shall be used to determine the hail impact resistance of windshields for acceptance, design, service, or research purposes. By using this method with the installed windshield angle and velocity of a specific aerospace vehicle, design allowables, criteria, and tolerances can be established for that vehicle's windshield.
SCOPE
1.1 This test method covers the determination of the impact resistance of an aerospace transparent enclosure (windshield, canopy, window, lens cover, etc.), hereinafter called windshield, during hailstorm conditions using simulated hailstones consisting of ice balls molded under tightly controlled conditions. This test shall also be used to meet hail test or performance requirements that are specified by design or contract.
1.2 Units—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.
1.3 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. For specific hazard statements, see Section 7.
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.

Standard
8 pages
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Standard
8 pages
English language
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30-Apr-2021
49.045
F07

ASTM F3120/F3120M-20(Specification)

Standard Specification for Ice Protection for General Aviation Aircraft

ABSTRACT
This specification provides international standards for ice protection aspects of airworthiness and design for ”general aviation” aircraft. The applicant for a design approval must seek the individual guidance of their respective civil aviation authority (CAA) body concerning the use of this standard as part of a certification plan.
The standards cover: types of aircraft operational requirements; crew external visibility (windshields and windows); ice shedding (engine inlet ice ingestion, propeller ice shedding, airframe ice shedding, ice protection system failure considerations); engine installation and induction system ice protection (propellers, turbine engines in flight, turbine engines on ground).
Also addressed in this specification are instrumentation ice protection, flight into icing conditions, aircraft not approved for flight in icing, and atmospheric icing conditions.
SCOPE
1.1 This specification covers international standards for ice protection aspects of airworthiness and design for “general aviation” aircraft.
1.2 The applicant for a design approval must seek the individual guidance of their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan. For information on which CAA regulatory bodies have accepted this specification (in whole or in part) as a means of compliance to their Small Aircraft Airworthiness regulations (hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMMITTEE/F44.htm) which includes CAA website links.
1.3 Units—The values are stated in units common to the field of aircraft icing. Typically SI or inch-pound units are used, but in some cases this has resulted in the use of mixed units due to the historical development of these values. In cases where values are given in one system with the other system following in brackets, 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.
1.4 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.

Technical specification
33 pages
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Technical specification
33 pages
English language
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14-Aug-2020
49.045
49.100
F44

Aerospace series - Tempered float glass plies for aircraft applications - Technical specification

EN 3001:2019(Main)

SIST EN 3001:2019

This document specifies the requirements for tempered soda-lime float glass plies which are made from annealed glass either of the universally available type or of high light transmission type. The annealed glass is manufactured by a continuous process for general use.
The plies are tempered by either a thermal or chemical process.
The tempered glass is used mainly for cockpit glazing.

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04-Jun-2019
30-Dec-2019
49.045
TRRTP121
ASD-STAN

ASTM F428-19(Test Method)

Standard Test Method for Intensity of Scratches on Aerospace Glass Enclosures

SIGNIFICANCE AND USE
4.1 Scratches exist on all glass surfaces. Often there are very fine scratches from cleaning operations that are not visible when looking through the glass. Visible scratches may be distracting to the observer looking through the transparency. Therefore, a procedure to define the severity of scratches is useful. A visual standard is used because it is not practical to measure the dimensions of the fine scratches in the scope of this test method.
SCOPE
1.1 This test method covers the visual inspection of scratches on the glass surface of aerospace transparent enclosures.
1.2 The values stated in SI units are to be regarded as standard. No other units of measurement are included in this standard.
1.3 This standard 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.
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.

Standard
4 pages
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Standard
4 pages
English language
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31-Oct-2019
49.045
F07

ASTM F3409-19e1(Practice)

Standard Practice for Simplified Aircraft Loads Determination

SCOPE
1.1 This practice provides an acceptable, and simplified, means of determining certain design loads criteria and conditions for fixed wing aircraft. In particular, the practice provides overall aircraft flight loads and flight conditions as well as control surface loads, wing loads, gust load factors, and gust loads on stabilizing surfaces.
1.2 This practice is intended to be referenced by other standards that define requirements for comprehensive aircraft loads. This practice does not provide all aircraft loads required for structural compliance. In addition, each load or condition determined through this practice has limitations on its use within the relevant section to which it must adhere.
1.3 Units—The values given in this standard are in SI units and are to be regarded as standard. Any values given in parentheses are mathematical conversions to inch-pound (or other) units that are provided for information only and are not considered standard. The values stated in each system may not be exact equivalents. Where it may not be clear, some equations provide the units of the result directly following the equation.
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.

Standard
8 pages
English language
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31-Oct-2019
49.045
F37

ASTM F548-19(Test Method)

Standard Test Method for Intensity of Scratches on Aerospace Transparent Plastics

SIGNIFICANCE AND USE
4.1 Scratches exist on all transparent plastic surfaces. Usually they are very fine scratches from cleaning operations that are not visible when looking through the plastic. Deeper scratches may result from careless cleaning or handling. While these may not be deep enough to affect the structural integrity of the part, their appearance in certain locations may be distracting to the observer looking through the plastic. Therefore, a procedure to define these scratches is useful.
SCOPE
1.1 This test method covers the visual inspection of shallow or superficial scratches on the surface of aerospace transparent plastic materials.
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.

Standard
4 pages
English language
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Standard
4 pages
English language
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31-Oct-2019
49.045
F07

Aerospace series - Tempered float glass plies for aircraft applications - Technical specification

SIST EN 3001:2019(Main)

EN 3001:2019

Standard
9 pages
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18-Jun-2019
49.045
I13

Aerospace series - Aluminium alloy 2014A- - T6 - Tubes for structures - 0,6 mm ≤ a ≤ 12,5 mm

SIST EN 2387:2018(Main)

EN 2387:2018

This European Standard specifies the requirements relating to:
Aluminium alloy 2014A-
T6
Tubes for structures
0,6 mm ≤ a ≤12,5 mm

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8 pages
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04-Sep-2018
49.025.20
49.045
I13

ASTM F3310-18(Specification)

Standard Specification for Non-Essential Ice Detectors for Aircraft

ABSTRACT
This specification establishes the requirements for non-essential ice detection system aspects of airworthiness and design for aeroplanes. The term ”aeroplane” as used in this specification was originally conceived for normal category fixed wing aircraft with a certified maximum takeoff weight (MTOW) of 19,000 lb or less and a passenger seating configuration up to 19 as defined in the Rules. However, these standards may be more broadly applicable, and their usage should not be unnecessarily limited. The installation of a non-essential ice detector is limited to level 1, 2, 3 and 4 Aeroplanes and normal, utility, acrobatic, or commuter category Aeroplanes. This specification prohibits the installation of a non-essential ice detector as a replacement for or modification to an existing Primary or Advisory ice detection system.
This specification covers the general requirements (product identification, operating conditions, installation manual, user's manual); functional requirements (intended function, performance, accessibility of controls, software); environmental requirements (operating temperature range, storage/survival temperature range, operating humidity range, operating altitude range, operating airspeed range, vibration, icing, deicing fluids, emissions of radiofrequency energy, electrical power input). Also covered by this specification are installation requirements, crew interface, system safety analysis, and operating limitations.
SCOPE
1.1 This specification covers international standards for non-essential ice detection system aspects of airworthiness and design for aeroplanes.
1.2 The term “aeroplane” is utilized in this specification as it was originally conceived for normal category fixed wing aircraft with a certified maximum takeoff weight (MTOW) of 19 000 lb or less and a passenger seating configuration up to 19 as defined in the Rules. However, these standards may be more broadly applicable and their usage should not be unnecessarily limited.
1.3 The applicant for a design approval must seek the individual guidance of their respective CAA body concerning the use of this specification as part of a certification plan. For information on which CAA regulatory bodies have accepted this specification (in whole or in part) as a means of compliance to their Small Aircraft Airworthiness regulations (hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMMITTEE/F44.htm) which includes CAA website links. It is the responsibility of the Applicant to validate any applicability beyond that identified in this specification and request acceptance from the applicable CAA.
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.

Technical specification
4 pages
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31-Mar-2018
49.045
F44

SIST EN 2155-13:2001(Main)

Aerospace series - Test methods for transparent materials for aircraft glazing - Part 13: Determination of temperature at deflection under load

EN 2155-13:1993

This standard specifies a procedure for determining the temperature at which an arbitrary deformation occurs when the specimens are subjected to arbitrary bending loads, under conditions of continually rising temperatures.

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31-May-2001
49.045
SS SPL

SIST EN 2155-21:2001(Main)

Aerospace series - Test methods for transparent materials for aircraft glazing - Part 21: Determination of resistance to crack propagation (K factor)

EN 2155-21:1989

This standard specifies how the resistance to crack propagation of rigid transparent sheet is to be determined.

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31-May-2001
49.045
SS SPL

SIST EN 2155-12:2001(Main)

Aerospace series - Test methods for transparent materials for aircraft glazing - Part 12: Determination of linear thermal expansion

EN 2155-12:1997

This standard specifies the method to determine the reversible linear thermal expansion of plastics with exclusion of changes in length due to accidental factors such as changes in moisture content, degree of polymerization and stressrelease. Since it will not be possible to exclude all these accidental factors, the method can be expected to give only approximate values.

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31-May-2001
49.045
SS SPL

SIST EN 2155-7:2001(Main)

Aerospace series - Test methods for transparent materials for aircraft glazing - Part 7: Determination of optical deviation

EN 2155-7:1997

This standard specifies the method used for the determination of optical deviation caused to beam of light passing through a transparent element materialperpendicular to the optical axis of the system.

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4 pages
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31-May-2001
49.045
SS SPL

SIST EN 2155-5:2001(Main)

Aerospace series - Test methods for transparent materials for aircraft glazing - Part 5: Determination of visible light transmission

EN 2155-5:1989

This standard specifies the determination of visible light transmission for transparent materials by using a photometer employing a defined light source and a photocell matched to the response of the human eye.
Because the materials under test are basically colourless, certain deviations from ideal conditions, indicated in the test, are allowable.

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SIST EN 2155-8:2001(Main)

Aerospace series - Test methods for transparent materials for aircraft glazing - Part 1: Determination of optical distortion

EN 2155-8:1989

This standard specifies the method of measurement of optical distortion of sheets in transparent materials, which consists of determining the change of deviation over the entire area of the sheet.
The method allows sheets to be viewed at differing angles which are specified according to the quality of the sheet under test.

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31-May-2001
49.045
SS SPL

SIST EN 2155-9:2001(Main)

Aerospace series - Test method for transparent materials for aircraft glazing - Part 9 : Determination of haze

EN 2155-9:1989

This standard specifies the determination of the haze of planar sections of transparent plastics, using a hazemeter based on an integrating sphere. This method is not recommended for the measurement of haze values greater than 30 % as determined by this method.

Standard
7 pages
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31-May-2001
49.045
SS SPL

SIST EN 2155-14:2001(Main)

Aerospace series - Test methods for tranparent materials for aircraft glazing - Part 14: Determination of the 1/10 Vicat softening temperature

EN 2155-14:1993

This standard specifies the method used for the determination of the 1/10 Vicat softening temperature of transparent thermoplastic materials used for aircraft glazing.

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6 pages
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31-May-2001
49.045
SS SPL

SIST EN 2155-3:2001(Main)

Aerospace series - Test methods for transparent materials for aircraft glazing - Part 3: Determination of refractive index

EN 2155-3:1993

This standard specifies the method used for the determination of the refractive index applicable for transparent materials used in aircraft glazing.

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31-May-2001
49.045
SS SPL

SIST EN 2155-2:2001(Main)

Aerospace series - Test methods for transparent materials for aircraft glazing - Part 2: Determination of water absorption

EN 2155-2:1993

This standard specifies the method used for the determination of the water absorption by means of immersion in conformance with ISO 62, method 1, applicable for transparent materials. In addition, it specifies the particular conditions for aircraft glazing.

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4 pages
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31-May-2001
49.045
SS SPL

SIST EN 2155-19:2001(Main)

Aerospace series - Test methods for transparent materials for aircraft materials for aircraft glazing - Part 19: Determination of craze resistance

EN 2155-19:1996

This standard specifies the resistance of transparent sheet to the effect of a solvent environment while set up as a cantilever beam with a load applied at the free end. No method has been developed yet for specimens with a thickness < 6 mm; for such material, a test method shall be agreed between the supplier and the customer.

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31-May-2001
49.045
SS SPL

Aerospace series - Marking of parts and assemblies other than engines - Indications on drawings

SIST EN 2851:2001(Main)

EN 2851:1992

This standard defines the method of indicating on drawings, with the exception of engine drawings, the instructions for the marking of parts and assemblies for aerospace applications

Standard
7 pages
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31-Dec-2000
01.100.20
49.045
SS SPL

Aerospace series - Test methods for transparent materials for aircraft glazing - Part 12: Determination of linear thermal expansion

EN 2155-12:1997(Main)

SIST EN 2155-12:2001

Standard
6 pages
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22-Jul-1997
30-Jan-1998
49.045
ASD-STAN

Aerospace series - Test methods for transparent materials for aircraft glazing - Part 7: Determination of optical deviation

EN 2155-7:1997(Main)

SIST EN 2155-7:2001

Standard
4 pages
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22-Jul-1997
30-Jan-1998
49.045
ASD-STAN

Aerospace series - Test methods for transparent materials for aircraft materials for aircraft glazing - Part 19: Determination of craze resistance

EN 2155-19:1996(Main)

SIST EN 2155-19:2001

Standard
5 pages
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20-Aug-1996
27-Feb-1997
49.045
ASD-STAN

ISO

ISO 10046:1996(Main)

Aircraft - Methodology of calculating cargo compartment volumes

Covers the methodology of calculating for the determination of the internal volumes of both the main deck and the lower deck aircraft cargo compartments. The minimum required clearance between the compartment envelope and the unit load devices (ULDs) is also stated in order to provide the maximum ULD external contour and the methodology to define the ULD internal volumes.

Standard
7 pages
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Standard
8 pages
French language
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Aerospace series - Test methods for transparent materials for aircraft glazing - Part 13: Determination of temperature at deflection under load

EN 2155-13:1993(Main)

SIST EN 2155-13:2001

Standard
8 pages
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25-Feb-1993
30-Aug-1993
49.045
ASD-STAN

Aerospace series - Test methods for tranparent materials for aircraft glazing - Part 14: Determination of the 1/10 Vicat softening temperature

EN 2155-14:1993(Main)

SIST EN 2155-14:2001

This standard specifies the method used for the determination of the 1/10 Vicat softening temperature of transparent thermoplastic materials used for aircraft glazing.

Standard
6 pages
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25-Feb-1993
30-Aug-1993
49.045
ASD-STAN

Aerospace series - Test methods for transparent materials for aircraft glazing - Part 2: Determination of water absorption

EN 2155-2:1993(Main)

SIST EN 2155-2:2001

Standard
4 pages
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12-Jan-1993
30-Jul-1993
49.045
ASD-STAN

Aerospace series - Test methods for transparent materials for aircraft glazing - Part 3: Determination of refractive index

EN 2155-3:1993(Main)

SIST EN 2155-3:2001

This standard specifies the method used for the determination of the refractive index applicable for transparent materials used in aircraft glazing.

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4 pages
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12-Jan-1993
30-Jul-1993
49.045
ASD-STAN

Aerospace series - Marking of parts and assemblies other than engines - Indications on drawings

EN 2851:1992(Main)

SIST EN 2851:2001

This standard defines the method of indicating on drawings, with the exception of engine drawings, the instructions for the marking of parts and assemblies for aerospace applications

Standard
7 pages
English language
e-Library read for
AI-Chat
1 day

24-Mar-1992
29-Sep-1992
01.100.20
49.045
ASD-STAN

Aerospace series - Test method for transparent materials for aircraft glazing - Part 9 : Determination of haze

EN 2155-9:1989(Main)

SIST EN 2155-9:2001

Standard
7 pages
English language
e-Library read for
AI-Chat
1 day

19-Mar-1989
19-Sep-1989
49.045
ASD-STAN

Aerospace series - Test methods for transparent materials for aircraft glazing - Part 1: Determination of optical distortion

EN 2155-8:1989(Main)

SIST EN 2155-8:2001

Standard
5 pages
English language
e-Library read for
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1 day

19-Mar-1989
19-Sep-1989
49.045
ASD-STAN

Aerospace series - Test methods for transparent materials for aircraft glazing - Part 5: Determination of visible light transmission

EN 2155-5:1989(Main)

SIST EN 2155-5:2001

Standard
8 pages
English language
e-Library read for
AI-Chat
1 day

19-Mar-1989
19-Sep-1989
49.045
305/2011
89/106/EEC
M/111
ASD-STAN