49 - AIRCRAFT AND SPACE VEHICLE ENGINEERING
ICS 49 Details
AIRCRAFT AND SPACE VEHICLE ENGINEERING
LUFT- UND RAUMFAHRTTECHNIK
AERONAUTIQUE ET ESPACE
LETALSKA IN VESOLJSKA TEHNIKA
General Information
Frequently Asked Questions
ICS 49 is a classification code in the International Classification for Standards (ICS) system. It covers "AIRCRAFT AND SPACE VEHICLE ENGINEERING". 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 10474 standards classified under ICS 49 (AIRCRAFT AND SPACE VEHICLE ENGINEERING). 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 requirements for the classification and grading of civil uncrewed aircraft systems (UAS). This document applies to heavier-than-air aircraft as well as aerostats of any possible architecture. This document applies to the industrial conception, development, design, production and delivery of civil UAS. It also applies to operations, modification, repair and maintenance of civil UAS. NOTE The characteristics in this document can be used individually or in combination, to meet specific needs of the classification and grading of civil UAS. This document does not apply to taxonomies of: automation levels; vertiports; UTM services.
- Standard11 pagesEnglish languagesale 15% off
This document is applicable to whole body vibration as a significant hazard. It also specifies the methods for determining the vibration emission transmitted to the whole body of drivers standing or seated on freely moveable ground support equipment (GSE) when driving, for purposes of type evaluation and declaration. This document also specifies methods for verifying vibration emission. This document is applicable to self-powered GSE only.
The test results do not apply to the determination of whole body vibration exposure of persons.
This document is intended to be used in conjunction with the different parts of the EN 1915 series and the EN 12312 series.
This document does not apply to GSE manufactured before the date of its publication.
- Draft19 pagesEnglish languagee-Library read for1 day
This document deals with all significant hazards, hazardous situations or hazardous events relevant for electrical ground power units as listed in Clause 4 and specifies the technical requirements to minimize the hazards which can arise during the commissioning, operation and maintenance of ground power equipment, when it is used as intended and under conditions of misuse which are reasonably foreseeable by the manufacturer or his authorized representative. It also takes into account some performance requirements recognized as essential by authorities, aircraft and ground support equipment (GSE) manufacturers as well as airlines and service companies.
This document is applicable to:
- ground power units either self-propelled or towable;
- ground power equipment when mounted on other GSE;
- ground power accessories intended for ground power equipment (including accessories for fixed equipment).
This document does not apply to:
- the electrical characteristics of the supply, the type of power supply system and related measures against contact;
- any electrical supply system not intended for aircraft use;
- the on-board electrical system of the aircraft.
This document does not specify requirements for noise and vibration.
Noise and vibration are dealt with respectively in EN 1915-4:2004+A1:2009 and EN ISO 31915-3:2026.
This document does not deal with hazards in respect to a standard automotive chassis and from other vehicles on the apron.
This part of EN 12312 does not apply to ground power equipment which is manufactured before the date of publication of this document by CEN.
This part of EN 12312 is intended to be used in conjunction with EN 1915-1:2023, EN 1915-2:2026, EN ISO 31915-3:2026 (for vehicles) and EN 1915-4:2004+A1:2009.
- Draft23 pagesEnglish languagee-Library read for1 day
This document specifies the conditions to be taken into consideration when calculating the strength and the stability of GSE. It also specifies general test methods.
This part of EN 1915 is intended to be used in conjunction with EN 1915-1:2023, EN ISO 31915-3:2026 (for self-propelled GSE) and EN 1915-4:2004+A1:2009, and with the relevant part of EN 12312 to give the requirements for the types of GSE within the scope of EN 12312.
When EN 12312 does not contain a relevant part for a GSE, EN 1915 (all parts) gives general requirements that may apply, although additional machine specific requirements, to be determined by the manufacturer, are likely to be required.
NOTE The methods given in this document demonstrate one way of achieving an acceptable safety level. Methods that produce comparable results can be used.
This document does not establish additional requirements for the following:
a) operation elsewhere than in an airport environment;
b) operation in severe conditions, e.g. ambient temperature below −20 °C or over 50 °C, tropical or saturated salty atmospheric environment;
c) hazards caused by wind velocity in excess of the figures given in this document;
d) earthquake, flood, landslide, lightning and more generally any natural catastrophe.
This document is not applicable to GSE which are manufactured before the date of publication by CEN of this document.
- Draft39 pagesEnglish languagee-Library read for1 day
This document is intended for the validation of codes used for the calculation of doses received by individuals on board aircraft. It gives guidance to radiation protection authorities and code developers on the basic functional requirements which the code fulfils.
Depending on any formal approval by a radiation protection authority, additional requirements concerning the software testing can apply.
- Draft13 pagesEnglish languagee-Library read for1 day
This document provides an overview description for the recommended processes for archiving of model-based product data, (e.g. 3D CAD and PDM data). The detailed processes are described in additional process parts of the EN 9300 series.
- Standard12 pagesEnglish languagee-Library read for1 day
This document specifies the fundamentals and concepts for the long-term preservation of digital product and technical data. The EN 9300 series specifies various regulatory and business requirements, applicable domain specific methodologies and are extensible for future long-term archiving formats and data management practices.
- Standard27 pagesEnglish languagee-Library read for1 day
This document specifies the dimensions of uncoated double hexagon head bolts, close tolerance, with MJ-thread, medium thread length, in heat-resisting nickel base alloy NI-P100HT for aerospace applications.
Maximum test temperature of the parts is 650 °C.
These bolts are used in aerospace fastening systems mainly stressed in shearing force.
- Standard11 pagesEnglish languagee-Library read for1 day
This document specifies the characteristics of bolts, normal hexagonal head, coarse tolerance normal shank, medium length thread, in heat resisting nickel base alloy, aluminium IVD coated.
Classification: 1 250 MPa / 425 °C
- Standard11 pagesEnglish languagee-Library read for1 day
This document specifies the characteristics of screws, 100° countersunk normal head, offset cruciform recess, threaded to head, in titanium alloy, anodized, with aluminium pigmented coating, metric series.
Classification: 1 100 MPa /315 °C .
- Draft10 pagesEnglish languagee-Library read for1 day
This document specifies the characteristics of bolts, 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 .
- Draft11 pagesEnglish languagee-Library read for1 day
This document specifies the required characteristics of sealing plugs, class T, for use in elements of electrical and optical connection containing cable (wire) sealing grommets, according to EN 4529-002. It is used together with EN 4529-001.
- Draft12 pagesEnglish languagee-Library read for1 day
This document is intended for the validation of codes used for the calculation of doses received by individuals on board aircraft. It gives guidance to radiation protection authorities and code developers on the basic functional requirements which the code fulfils. Depending on any formal approval by a radiation protection authority, additional requirements concerning the software testing can apply.
- Standard7 pagesEnglish languagesale 15% off
- Standard8 pagesFrench languagesale 15% off
This document defines the contents, methods and requirements of configuration management for space projects, and the responsibilities and authorities of related parties. It is intended to be used in conjunction with ISO 14300-1:2023, Clause 10. This document is applicable to the configuration management of space projects from the mission analysis phase to the disposal phase.
- Standard28 pagesEnglish languagesale 15% off
This document specifies the minimum requirements for the qualification, acceptance, delivery and inspection of standard parts by the aerospace industry and its manufacturers.
This document is valid for standard parts and their assemblies as described in a product standard, if mentioned therein. This specification can also be applied to other parts when specifically invoked by the terms of delivery.
Parts/sections of this document are not applicable in cases where the product standard stipulates requirements that differ from this specification.
- Draft9 pagesEnglish languagee-Library read for1 day
This document specifies the characteristics of bolts, shouldered, thin hexagonal head, close tolerance shank, short thread, in titanium alloy, anodized, MoS2 dryfilm coated, for aerospace applications.
Classification: 1 100 MPa1/315 °C2..
- Draft10 pagesEnglish languagee-Library read for1 day
This document specifies the characteristics of bolts, normal hexagonal head, coarse tolerance normal shank, medium length thread, in heat resisting nickel base alloy, aluminium IVD coated.
Classification: 1 250 MPa / 425 °C
- Standard11 pagesEnglish languagee-Library read for1 day
This document provides an overview description for the recommended processes for archiving of model-based product data, (e.g. 3D CAD and PDM data). The detailed processes are described in additional process parts of the EN 9300 series.
- Standard12 pagesEnglish languagee-Library read for1 day
This document specifies the dimensions of uncoated double hexagon head bolts, close tolerance, with MJ-thread, medium thread length, in heat-resisting nickel base alloy NI-P100HT for aerospace applications.
Maximum test temperature of the parts is 650 °C.
These bolts are used in aerospace fastening systems mainly stressed in shearing force.
- Standard11 pagesEnglish languagee-Library read for1 day
This document specifies the fundamentals and concepts for the long-term preservation of digital product and technical data. The EN 9300 series specifies various regulatory and business requirements, applicable domain specific methodologies and are extensible for future long-term archiving formats and data management practices.
- Standard27 pagesEnglish languagee-Library read for1 day
This document specifies the safety programme and the technical safety requirements that are implemented in order to conform to the safety policy defined in ISO 14300-2. It is intended to protect flight and ground personnel, the launch vehicle, associated payloads, ground support equipment, the general public, public and private property, and the environment from hazards associated with space systems. This document is applicable to all space projects where during any project phase there exists the potential for hazards to personnel or the general public, space flight systems, ground support equipment, facilities, public or private property, or the environment.
- Standard35 pagesEnglish languagesale 15% off
This document specifies the female coding and attachment system for mounting on free housing in the family of rectangular electrical connectors with sealed and non-sealed rear, plastic housing, locking device, for operating temperatures from -55 °C to 175 °C.
- Standard7 pagesEnglish languagee-Library read for1 day
This document specifies the characteristics and quality assurance requirements for solid rivets and slugs made in aluminium or aluminium alloys, inch series, for aerospace application. This document is applicable to the following aluminium alloys: 1050A-H14, 2017A-T42, 2117-T42, 5056A-H32 and 7050-T73.
- Standard17 pagesEnglish languagee-Library read for1 day
This document specifies the protective cover for all receptacles series 2 and series 31 used in the family of rectangular electrical connectors.
The receptacle connectors corresponding to those protective covers are specified in EN 4165-004, EN 4165-011 and EN 4165-025.
- Standard10 pagesEnglish languagee-Library read for1 day
This document specifies the procedures for training personnel who will be involved in the operation of uncrewed aircraft systems (UAS). This document defines: knowledge, skill, attitude and qualification criteria required for UAS remote pilots (RP), remote pilot in command (rPIC) and UAS training organizations (UTO) that provide training to UAS remote pilots and other personnel involved in UAS operations; training curriculum and contents for specific learning courses; qualification and criteria for verification of achieved competence by the training organizations; general procedures for providing training of UAS personnel. NOTE 1 An UTO can include additional topics or learning objectives, such as when required by legally binding rules in the applicable jurisdiction. NOTE 2 A UAS operator can also act as the UTO, providing that possible conflict of interest between training and operations is properly managed.
- Standard138 pagesEnglish languagesale 15% off
This document specifies the interfaces between a launch vehicle (LV) and the spacecraft (SC) being launched, to provide LV and SC organizations with the necessary format for presenting the required technical data on existing and future interfaces. Its intended purpose is to minimize costs and reduce the risks from errors resulting from miscommunication. It does not limit the ability of LV or SC organizations to specify unique requirements.
- Standard52 pagesEnglish languagesale 15% off
This document specifies the requirements for safe commercial operations of uncrewed aircraft system (UAS), including the external safety-critical service providing command and control (C2) Link. This document applies to all commercial UAS regardless of size, application or location and represents the international best practice for the safe commercial operation of any UAS.
- Standard46 pagesEnglish languagesale 15% off
This document defines terms used in the field of pilot training with the use of technical equipment, called flight simulators, enhancing safety by allowing pilots to practice various scenarios in a controlled environments, without the need of an actual aircraft. This document establishes the terms and definitions of the basic concepts applied in science, engineering and manufacturing in the field of flight simulation training devices (airplane and helicopter).
- Standard6 pagesEnglish languagesale 15% off
This document specifies the female coding and attachment system for mounting on free housing in the family of rectangular electrical connectors with sealed and non-sealed rear, plastic housing, locking device, for operating temperatures from -55 °C to 175 °C.
- Standard7 pagesEnglish languagee-Library read for1 day
This document specifies the characteristics and quality assurance requirements for solid rivets and slugs made in aluminium or aluminium alloys, inch series, for aerospace application. This document is applicable to the following aluminium alloys: 1050A-H14, 2017A-T42, 2117-T42, 5056A-H32 and 7050-T73.
- Standard17 pagesEnglish languagee-Library read for1 day
This document specifies the protective cover for all receptacles series 2 and series 31 used in the family of rectangular electrical connectors.
The receptacle connectors corresponding to those protective covers are specified in EN 4165-004, EN 4165-011 and EN 4165-025.
- Standard10 pagesEnglish languagee-Library read for1 day
This document specifies the required characteristics, inspection and test methods, quality assurance and delivery conditions, for P, Q and saddle clamps with rubber cushion, used for aerospace applications.
- Standard11 pagesEnglish languagee-Library read for1 day
This document provides a framework to assess, reduce and control the potential risks that spacecraft and launch vehicle orbital stages (referred to hereinafter as “space vehicles”) pose to people and the environment when those space vehicles re-enter the Earth's atmosphere and impact the Earth’s surface. It applies to the planning, design and review of space vehicle missions for which controlled or uncontrolled re-entry is inevitable. This document applies to the following objects when assessing their risk to the ground: objects re-entering from orbit; launch vehicles (including payloads, other objects separated during the ascent phase, etc.) that are mentioned in flight safety activities under ISO 14620-2:2019[1], 6.2; interplanetary spacecraft returning to Earth. This document does not apply to systems with wings and control functions intended for targeted landing. This document assumes that the main specifications and operational procedures for ensuring safety on the ground against the re-entry of spacecraft containing radioactive material have already been determined in the mission requirements definition stage, system definition stage, operational concept definition stage, etc. Therefore, apart from matters related to re-entry safety, the main parts of the mission design and operational concept of spacecraft containing radioactive material are outside the scope of this standard.
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This document specifies the design requirements (and tests) for the crimping of insulated and non-insulated joints to general purpose electrical cables for aircraft, with conductors of copper, copper alloy, aluminium or aluminium alloy, in locations in which the stabilized conductor temperature does not exceed the values specified for the relevant type of cable, i.e. 105 °C, 190 °C or 260 °C. This document specifies the type of cable to use for the joints (see 4.1). The document also contains recommendations relating to the inspection of such connections and the tools used to perform the crimping operation. Because satisfactory crimping is dependent upon the maintenance and setting of tools, it also contains recommendations for tests to confirm their serviceability. NOTE Testing of crimped joints to assess their suitability for aircraft shows that certain environmental conditions, for example vibration, have no significant effect on the performance of the joints. Therefore, such tests are not provided in this document.
- Standard13 pagesEnglish languagesale 15% off
This document specifies the required characteristics, inspection and test methods, quality assurance and delivery conditions, for P, Q and saddle clamps with rubber cushion, used for aerospace applications.
- Standard11 pagesEnglish languagee-Library read for1 day
This document is applicable to whole body vibration as a significant hazard. It also specifies the methods for determining the vibration emission transmitted to the whole body of drivers standing or seated on freely moveable ground support equipment (GSE) when driving, for purposes of type evaluation and declaration. This document also specifies methods for verifying vibration emission. This document is applicable to self-powered GSE only. The test results do not apply to the determination of whole body vibration exposure of persons. This document is intended to be used in conjunction with the different parts of the EN 1915 series and the EN 12312 series. This document does not apply to GSE manufactured before the date of its publication.
- Standard12 pagesEnglish languagesale 15% off
- Standard12 pagesFrench languagesale 15% off
- Standard12 pagesFrench languagesale 15% off
This document specifies the requirements relating to:
Steel X5CrNiCu17-4 (1.4542)
Air melted
Solution treated and precipitation treated
Bars
a or D ≤ 200 mm
Rm ≥ 930 MPa
for aerospace applications.
W.nr: 1.4542.
ASD-STAN: FE-PM3801.
- Standard9 pagesEnglish languagee-Library read for1 day
This document specifies the requirements relating to:
Steel X5CrNiCu17-4 (1.4542)
Air melted
Solution treated and precipitation treated
Bars
a or D ≤ 200 mm
Rm ≥ 1 310 MPa
for aerospace applications.
W.nr: 1.4542.
ASD-STAN: FE-PM3801.
- Standard9 pagesEnglish languagee-Library read for1 day
This document provides the workflow and technical requirements for perceiving, evaluating and avoiding collisions among orbiting objects, data requirements for these tasks, identifies techniques that can be used to estimate either the probability or the consequence of collisions, or both, and provides requirements and guidance for executing collision avoidance manoeuvres.
- Standard43 pagesEnglish languagesale 15% off
IEC TS 62564-1:2026 defines the minimum requirements for integrated circuits and semiconductors which are designated as an "aerospace qualified electronic component (AQEC)".
This edition includes the following significant technical changes with respect to the previous edition:
a) addition of optional ADHP PPAP;
b) revision to Annex B; addition of Annex C and Annex D;
c) removal of STACK;
d) general update to referenced standards throughout.
- Technical specification23 pagesEnglish languagesale 15% off
- Technical specification47 pagesEnglish languagesale 15% off
This document specifies the required characteristics for metric plain or slotted (castellated) nuts, with MJ threads according to ISO 5855-2, for use in aerospace construction. It is applicable to nuts as defined above, provided that reference is made to this document in the relevant definition document.
- Standard17 pagesEnglish languagesale 15% off
- Standard17 pagesFrench languagesale 15% off
This document provides test methods and test requirements for design either qualification or acceptance, or both of small spacecraft or units. It provides the minimum test requirements and test methods to qualify the design and manufacturing methods of commercial small spacecraft and their units and to accept the final products. This document is applicable to satellites whose development methods are different from the ones used for traditional satellites that have little room for risk tolerance. The scope of this document encompasses different categories of small spacecraft, so-called mini-, micro-, nano-, pico- and femto spacecraft. This document includes CubeSat, as long as it is developed with the untraditional processes. This document does not cover satellite deployment mechanisms, such as picosatellite orbital deployer (POD), as the verification requirements are defined in the interface control document (ICD) with the launcher, such as ISO 26869[1]. This document does not cover software testing, although some tests such as functional test, mission test and end-to-end test are inherently used to test the software installed in the hardware being tested. General requirements and processes of satellite software testing can be found in various references, such as ECSS-E-ST40[2]. This document does not cover requirements regarding safety nor debris mitigation. Appropriate documents such as ISO 14620-1[3] or ISO 24113[4] can be referred to. Other common requirements for small spacecraft can be found in ISO 20991[5].
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This document specifies test methods for fitting assemblies used in aircraft fluid systems in the pressure and temperature ranges covered by pressure from classes B, to K, and temperature types I, II and III of ISO 6771. This document applies each time that it is referred to in a procurement specification or other definition document which contains the pass and fail criteria for these tests.
- Standard6 pagesEnglish languagesale 15% off
- Standard6 pagesFrench languagesale 15% off
This document specifies the required characteristics for metric self-locking nuts, with MJ threads, for use in aerospace construction at a maximum temperature less than or equal to 425 °C. It is applicable to nuts as defined above, provided that reference is made to this document in the relevant definition document.
- Standard30 pagesEnglish languagesale 15% off
This document specifies the requirements relating to:
Steel X5CrNiCu17-4 (1.4542)
Air melted
Solution treated and precipitation treated
Bars
a or D ≤ 200 mm
Rm ≥ 930 MPa
for aerospace applications.
W.nr: 1.4542.
ASD-STAN: FE-PM3801.
- Standard9 pagesEnglish languagee-Library read for1 day
This document specifies the requirements relating to:
Steel X5CrNiCu17-4 (1.4542)
Air melted
Solution treated and precipitation treated
Bars
a or D ≤ 200 mm
Rm ≥ 1 310 MPa
for aerospace applications.
W.nr: 1.4542.
ASD-STAN: FE-PM3801.
- Standard9 pagesEnglish languagee-Library read for1 day
This document specifies the requirements relating to:
Steel GX5CrNiCuNb16-4 (1.4525)
Homogenized
Solution treated and precipitation hardened
Investment casting
De ≤ 50 mm
Rm ≥ 900 MPa
for aerospace applications.
ASD-STAN designation FE-CM3801
Material number 1.4525
- Standard9 pagesEnglish languagee-Library read for1 day
This document specifies the required characteristics of a light weight coaxial cable, 50 Ω, type KW for use in aircraft electrical systems at operating temperature between −55 °C and 180 °C and specially for high frequency up to 6 GHz. Nevertheless, if needed, −65 °C is also acceptable as shown by rapid change of temperature test.
- Standard18 pagesEnglish languagee-Library read for1 day
This document specifies the required characteristics of a light weight coaxial cable, 50 Ω, type KX for use in aircraft electrical systems at operating temperature between −55 °C and 200 °C and specially for high frequency up to 6 GHz. Nevertheless, if needed, −65 °C is also acceptable as shown by rapid change of temperature test.
- Standard18 pagesEnglish languagee-Library read for1 day
This document gives guidance on the use of regrinds and recycled materials for thermoplastic parts for aerospace use.
This document does not apply to reinforced thermoplastic materials, such as short fibre-reinforced plastics, due to their distinct processing characteristics, material degradation concerns, and stringent aerospace performance requirements.
The intended manufacturing processes for these virgin/regrind blends include standard thermoplastic methods such as injection moulding, extrusion, and blow moulding, among others as appropriate to the application.
- Standard5 pagesEnglish languagee-Library read for1 day