This document specifies the characteristics of electrical cables for use in the on-board electrical systems of aircraft at operating temperatures between -55 °C and 260 °C for cross sections equal to and greater than 5 mm2.

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This document specifies a method of testing flexure endurance of the cable when it is subjected to alternating flexing.
It shall be used together with EN 3475-100.

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20200205: Corrigendum requested by ASD-STAN due to a mistake of the key in Figure 2 (symbols inverted in the original text provided to CCMC). SS

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20200205: Corrigendum requested by ASD-STAN due to a mistake of the key in Figure 2 (symbols inverted in the original text provided to CCMC). SS

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IEC 62396-8:2020 is intended to provide awareness and guidance with regard to the effects of small particles (that is, protons, electrons, pions and muon fluxes) and single event effects on avionics electronics used in aircraft operating at altitudes up to 60 000 feet (18 300 m). This is an emerging topic and lacks substantive supporting data. This document is intended to help aerospace or ground level electronic equipment manufacturers and designers by providing awareness guidance for this new emerging topic.
Details of the radiation environment are provided together with identification of potential problems caused as a result of the atmospheric radiation received. Appropriate methods are given for quantifying single event effect (SEE) rates in electronic components.

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IEC TS 62686-1:2020 is available as IEC TS 62686-1:2020 RLV which contains the International Standard and its Redline version, showing all changes of the technical content compared to the previous edition.
IEC TS 62686-1:2020 defines the minimum requirements for general purpose "off the shelf" COTS (commercial off-the-shelf) integrated circuits and discrete semiconductors for ADHP (aerospace, defence and high performance) applications. This Technical Specification applies to all components that can be operated in ADHP applications within the manufacturers' publicly available data sheet limits in conjunction with IEC TS 62239-1. It may be used by other high performance and high reliability industries, at their discretion. This new edition includes the following significant technical changes with respect to the previous edition:
- update related to obsolescence of STACK Specification S/0001 revision 14 notice 3;
- addition of alternative automotive methods of compliance and revision of Annex B initially related to cross-reference to STACK Specification S/0001;
- addition of an Annex C to include a requirement matrix for IEC TS 62686-1 verification.

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1.1   General
Part 001 of EN 4533 examines the termination of optical fibre cables used in aerospace applications. Termination is the act of installing an optical terminus onto the end of a buffered fibre or fibre optic cable. It encompasses several sequential procedures or practices. Although termini will have specific termination procedures, many share common elements and these are discussed in this document. Termination is required to form an optical link between any two network or system components or to join fibre optic links together.
The fibre optic terminus features a precision ferrule with a tight tolerance central bore hole to accommodate the optical fibre (suitably bonded in place and highly polished). Accurate alignment with another (mating) terminus will be provided within the interconnect (or connector) alignment mechanism. As well as single fibre ferrules, it is noted that multi-fibre ferrules exist (e.g. the MT ferrule) and these will also be discussed in this part of the handbook.
Another technology used to connect 2 fibres is the expanded beam. 2 ball lenses are used to expand, collimate and then refocus the light from and to fibres. Contacts are not mated together. It helps reducing the wear between 2 contacts and allows more mating cycles. This technology is less sensitive to misalignments and dust. Losses are remaining more stable than butt joint contact even if the nominal loss is higher.
A Note on Terminology
Current terminology in the aerospace fibre optics community refers to an optical terminus or termini. The term optical contact may be seen in some documents and has a similar meaning. However, the term contact is now generally reserved for electrical interconnection pins. The optical terminus (or termini) is housed within an interconnect (connector is an equivalent term). Interconnects can be single-way or multi-way. The interconnect or connector will generally house the alignment mechanism for the optical termini (usually a precision split-C sleeve made of ceramic or metal). The reader should be aware of these different terms.
An optical link can be classified as a length of fibre optic cable terminated at both ends with fibre optic termini. The optical link provides the transmission line between any two components via the optical termini which are typically housed within an interconnecting device (typically a connector) with tight tolerancing within the alignment mechanisms to ensure a low loss light transmission.
Part 001 will explain the need for high integrity terminations, provide an insight into component selection issues and suggests best practice when terminating fibres into termini for high integrity applications. A detailed review of the termination process can be found in section 4 of this part and is organised in line with the sequence of a typical termination procedure.
The vast number of cable constructions and connectors available make defining a single termination instruction that is applicable to all combinations very difficult. Therefore, this handbook concentrates on the common features of most termination practices and defining best practice for current to near future applications of fibre optics on aircraft. This has limited the studies within this part to currently available ‘avionic’ silica fibre cables and adhesive filled butt-coupled type connectors. Many of the principles described however would still be applicable for other termination techniques. Other types of termination are considered further in the repair part of this handbook.
It is noted that the adhesive based pot-and-polish process is applicable to the majority of single-way fibre optic interconnects connectors and termini for multi-way interconnects and connectors. They share this commonality.
1.2   Need to high integrity terminations
(...)

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EN 3475-513 defines the test methods to evaluate the performance of coaxial, quadrax and databus cables after the installation of plastic cable ties.It shall be used together with EN 3475-100.

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This document defines the test methods to evaluate the performance of coaxial, quadrax and databus cables after the installation of plastic cable ties.
It shall be used together with EN 3475-100.

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  • Standard
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1.1   General
Part 001 of EN 4533 examines the termination of optical fibre cables used in aerospace applications. Termination is the act of installing an optical terminus onto the end of a buffered fibre or fibre optic cable. It encompasses several sequential procedures or practices. Although termini will have specific termination procedures, many share common elements and these are discussed in this document. Termination is required to form an optical link between any two network or system components or to join fibre optic links together.
The fibre optic terminus features a precision ferrule with a tight tolerance central bore hole to accommodate the optical fibre (suitably bonded in place and highly polished). Accurate alignment with another (mating) terminus will be provided within the interconnect (or connector) alignment mechanism. As well as single fibre ferrules, it is noted that multi-fibre ferrules exist (e.g. the MT ferrule) and these will also be discussed in this part of the handbook.
Another technology used to connect 2 fibres is the expanded beam. 2 ball lenses are used to expand, collimate and then refocus the light from and to fibres. Contacts are not mated together. It helps reducing the wear between 2 contacts and allows more mating cycles. This technology is less sensitive to misalignments and dust. Losses are remaining more stable than butt joint contact even if the nominal loss is higher.
A Note on Terminology
Current terminology in the aerospace fibre optics community refers to an optical terminus or termini. The term optical contact may be seen in some documents and has a similar meaning. However, the term contact is now generally reserved for electrical interconnection pins. The optical terminus (or termini) is housed within an interconnect (connector is an equivalent term). Interconnects can be single-way or multi-way. The interconnect or connector will generally house the alignment mechanism for the optical termini (usually a precision split-C sleeve made of ceramic or metal). The reader should be aware of these different terms.
An optical link can be classified as a length of fibre optic cable terminated at both ends with fibre optic termini. The optical link provides the transmission line between any two components via the optical termini which are typically housed within an interconnecting device (typically a connector) with tight tolerancing within the alignment mechanisms to ensure a low loss light transmission.
Part 001 will explain the need for high integrity terminations, provide an insight into component selection issues and suggests best practice when terminating fibres into termini for high integrity applications. A detailed review of the termination process can be found in section 4 of this part and is organised in line with the sequence of a typical termination procedure.
The vast number of cable constructions and connectors available make defining a single termination instruction that is applicable to all combinations very difficult. Therefore, this handbook concentrates on the common features of most termination practices and defining best practice for current to near future applications of fibre optics on aircraft. This has limited the studies within this part to currently available ‘avionic’ silica fibre cables and adhesive filled butt-coupled type connectors. Many of the principles described however would still be applicable for other termination techniques. Other types of termination are considered further in the repair part of this handbook.
It is noted that the adhesive based pot-and-polish process is applicable to the majority of single-way fibre optic interconnects connectors and termini for multi-way interconnects and connectors. They share this commonality.
1.2   Need to high integrity terminations
(...)

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This standard specifies the required characteristics, tests and tooling applicable to male contacts 018, type A, crimp, class S, used in elements of connection according to EN 3155-002. It shall be used together with EN 3155-001. The associated female contacts are defined in EN 3155-019.

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This standard specifies the required characteristics, tests and tooling applicable to female electrical contacts 017, type A, crimp, class P, used in elements of connection (relay bases) according to EN 3155-002.It shall be used together with EN 3155-001.The associated male contacts are defined in the standards of relays associated to the relay bases listed in EN 3155-002.

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This document specifies the required characteristics, tests and tooling applicable to female electrical contacts 045, type A, double crimping, class T, used in elements of connection according to EN 3155-002. It shall be used together with EN 3155-001. The associated male contact is defined in EN 3155-044. Double crimping contact has a barrel which is design to crimp conductor and jacket of cable in two locations, one on the conductor and the other on the jacket. This way protect the conductor from mechanical strengths.

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This document specifies the required characteristics, tests and tooling applicable to male contacts 018, type A, crimp, class S, used in elements of connection according to EN 3155-002.
It shall be used together with EN 3155-001.
The associated female contacts are defined in EN 3155-019.

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This document specifies the required characteristics, tests and tooling applicable to female electrical contacts 017, type A, crimp, class P, used in elements of connection (relay bases) according to EN 3155-002.
It shall be used together with EN 3155-001.
The associated male contacts are defined in the standards of relays associated to the relay bases listed in EN 3155-002.

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This document specifies the required characteristics, tests and tooling applicable to female contacts 019, type A, crimp, class S, used in elements of connection according to EN 3155-002. It shall be used together with EN 3155-001. The associated male contacts are defined in EN 3155-018.

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This document specifies the required characteristics, tests and tooling applicable to male electrical contacts, type A, crimp, class S, used in elements of connection according to EN 3155-002. It shall be used together with EN 3155-001. The tests as applied in this standard do not permit the full qualification and shall be completed with associated components.

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This document specifies the required characteristics and tests applicable to electrical contacts, male 044, type A, double crimping, class T, used in elements of connection according to EN 3155-002. It shall be used together with EN 3155-001. The associated female contact is defined in EN 3155-045.

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This document specifies the required characteristics, tests and tooling applicable to female contacts size 22, 20, 16, 12, 8 and 5, type A, crimp, class R, used in elements of connection according to EN 3155-002. It should be used together with EN 3155-001. The associated male contacts are defined in EN 3155-076.

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This document specifies the required characteristics, tests and tooling applicable to male contacts size 22, 20, 16, 12, 8 and 5, type A, crimp, class R, used in elements of connection according to EN 3155-002. It should be used together with EN 3155-001. The associated female contacts are defined in EN 3155-077.

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This document specifies the required characteristics of a coaxial cable, -50 °C, type WN, for use in aircraft electrical systems at operating temperature between  -55 °C and 200 °C and especially for high frequency up to 6 GHz.

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This document specifies the characteristics of dummy receptacles in the family of circular electrical connectors coupled by threaded ring. It applies to the class defined in Table 3. For plugs associated with these dummy receptacles, see EN 2997-008.

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This European Standard specifies the required characteristics for heat-shrinkable elastomeric semi-rigid, boots for use in aircraft electrical systems at operating temperatures between -75 °C and 150 ° C. The moulded shapes may be supplied with a pre-coated adhesive. Refer to the manufacturers/suppliers for options. A guide to adhesive compatibility is given in Annex A (informative). These moulded shapes are normally supplied in the styles and dimensions given in EN 4840-002 Table 1 to Table 22. The colour is normally black. Styles and dimensions other than those specifically listed in EN 4840-002 Table 1 to Table 22 may be available as custom items. These items shall be considered to comply with this standard if they comply with the property requirements listed in Table 1 with the exception of dimensions.

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This document specifies the characteristics, test methods, qualification and acceptance conditions of single and multicore electric cables for general purpose with conductors in aluminium or copper-clad aluminium, intended for installation in aircraft electrical systems. The insulation of these cables is designed to withstand aircraft voltages at a frequency not exceeding 2 000 Hz. Unless specified by individual product standards the maximum demonstrated voltage of rating of these cables is ac 115 V rms phase to neutral and 200 V rms phase to phase and 28 Vdc. They are divided into types, the characteristics of which are given in the product standards. Unless otherwise specified in the product standard, the tests defined in this standard apply.

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This document specifies the required characteristics, tests and tooling applicable to male electrical contacts, type A, crimp, class S, used in elements of connection according to EN 3155-002.
It shall be used together with EN 3155-001.
The tests as applied in this standard do not permit the full qualification and shall be completed with associated components.

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This document specifies the required characteristics, tests and tooling applicable to female electrical contacts 045, type A, double crimping, class T, used in elements of connection according to EN 3155-002.
It shall be used together with EN 3155-001.
The associated male contact is defined in EN 3155-044.
Double crimping contact has a barrel which is design to crimp conductor and jacket of cable in two locations, one on the conductor and the other on the jacket. This way protect the conductor from mechanical strengths.

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This document specifies the required characteristics, tests and tooling applicable to female contacts 019, type A, crimp, class S, used in elements of connection according to EN 3155-002.
It shall be used together with EN 3155-001.
The associated male contacts are defined in EN 3155-018.

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This document specifies the required characteristics of a coaxial cable, 50 , type WN, for use in aircraft electrical systems at operating temperature between  55 °C and 200 °C and especially for high frequency up to 6 GHz.

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This document specifies the required characteristics, tests and tooling applicable to female contacts size 22, 20, 16, 12, 8 and 5, type A, crimp, class R, used in elements of connection according to EN 3155-002.
It should be used together with EN 3155-001.
The associated male contacts are defined in EN 3155-076.

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This document specifies the required characteristics, tests and tooling applicable to male contacts size 22, 20, 16, 12, 8 and 5, type A, crimp, class R, used in elements of connection according to EN 3155-002.
It should be used together with EN 3155-001.
The associated female contacts are defined in EN 3155-077.

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This standard specifies the required characteristics and tests applicable to electrical contacts, male 044, type A, double crimping, class T, used in elements of connection according to EN 3155-002.
It shall be used together with EN 3155-001.
The associated female contact is defined in EN 3155-045.

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This document specifies the characteristics, test methods, qualification and acceptance conditions of single and multicore electric cables for general purpose with conductors in aluminium or copper-clad aluminium, intended for installation in aircraft electrical systems.
The insulation of these cables is designed to withstand aircraft voltages at a frequency not exceeding 2 000 Hz. Unless specified by individual product standards the maximum demonstrated voltage of rating of these cables is ac 115 V rms phase to neutral and 200 V rms phase to phase and 28 Vdc.
They are divided into types, the characteristics of which are given in the product standards. Unless otherwise specified in the product standard, the tests defined in this standard apply.

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This document specifies the required characteristics for heat-shrinkable elastomeric semi-rigid, boots for use in aircraft electrical systems at operating temperatures between -75 °C and 150 °C.
The moulded shapes may be supplied with a pre-coated adhesive. Refer to the manufacturers/suppliers for options. A guide to adhesive compatibility is given in Annex A (informative).
These moulded shapes are normally supplied in the styles and dimensions given in EN 4840-002 Table 1 to Table 22. The colour is normally black.
Styles and dimensions other than those specifically listed in EN 4840-002 Table 1 to Table 22 may be available as custom items. These items shall be considered to comply with this standard if they comply with the property requirements listed in Table 1 with the exception of dimensions.

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This document specifies the characteristics of dummy receptacles in the family of circular electrical connectors coupled by threaded ring.
It applies to the class defined in Table 3.
For plugs associated with these dummy receptacles, see EN 2997-008.

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This document specifies the required characteristics, inspection and test methods, qualification and acceptance conditions for spherical plain bearings in corrosion resisting steel with self- lubricating liner, low starting torque and low friction coefficient, elevated duty cycles under low oscillations at different operating conditions. This standard applies whenever referenced. These self-lubricating spherical plain bearings are intended for use in fixed or moving parts of the aircraft structure especially for control mechanism and operating systems. The bearings are designed subjected under low dynamic radial loads and slow rotations in the temperature range of -55 °C to 120 °C (-67 °F to 248 °F). The liner may be of a fabric or composite material bonded to the inside diameter of the outer ring or in a composite material moulded into a pre-formed cavity between the inner and outer rings.

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This document defines a banding band, style Z, for terminating individual and/or overall cable screens to cable outlets. The bands delivered in flat condition F (see Clause 6) which need to be double wrapped prior to their installation. The bands delivered in condition C (see Clause 6) are factory pre-double wrapped and ready for installation.

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This document specifies the required characteristics, tests and tooling applicable to female electrical contacts 003, type A, crimp, class S used in elements of connection according to EN 3155‑002.
It shall be used together with EN 3155-001.
The associated male contacts are defined in EN 3155-008.

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This document defines the insertion/extraction tool for removal of modules used in the family of rectangular electrical connectors.

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IEC 62668-1:2019 defines requirements for avoiding the use of counterfeit, recycled and fraudulent components used in the aerospace, defence and high performance (ADHP) industries. It also defines requirements for ADHP industries to maintain their intellectual property (IP) for all of their products and services. The risks associated with purchasing components outside of franchised distributor networks are considered in IEC 62668-2. Although developed for the avionics industry, this document can be applied by other high performance and high reliability industries at their discretion. This first edition cancels and replaces the third edition of IEC TS 62668-1 published in 2016. This edition includes the following significant technical changes with respect to the previous edition: a) added a reference to AS/EN/JISQ 9100 and AS/EN/JISQ 9110 which contain anti-counterfeit requirements b) added reference to USA DFAR rule 252.246.7008 and to UK Defence Standard 05-135; c) added reference to more GAO, OECD and ICC reports d) updated weblinks and other references; e) added new Annex E with figures describing how anti-counterfeit documents can be used in supply chains; f) added a reference to the new IECQ OD 3702 traceability audit; g) added new definition for re-manufactured components with a warning that these are not recommended.

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This document specifies the required characteristics, tests and tooling applicable to female electrical contacts 003, type A, crimp, class S used in elements of connection according to EN 3155-002.
It shall be used together with EN 3155-001.
The associated male contacts are defined in EN 3155-008.

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This document defines a banding band, style Z, for terminating individual and/or overall cable screens to cable outlets. The bands delivered in flat condition F (see Clause 6) which need to be double wrapped prior to their installation. The bands delivered in condition C (see Clause 6) are factory pre-double wrapped and ready for installation.

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This document defines the insertion/extraction tool for removal of modules used in the family of rectangular electrical connectors.

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This standard specifies the required characteristics for four types of heat-shrinkable limited fire hazard sleevings for use in aircraft electrical systems at operating temperatures between - 65 °C and 150 °C. This sleeving is flexible, flame retarded and emits minimum smoke, gases and corrosive by-products when exposed to fire. It is available with various wall thicknesses and also in a higher shrink ratio according to the application and degree of mechanical protection required. It is suitable for use (e.g. as cable protection) in areas where smoke, gases or corrosive by-products would constitute a particular hazard. Type A: Medium wall, shrink ratio 2:1 and is normally supplied with internal diameters up to 30 mm. The standard colour is black. Sizes or colours other than those specifically listed in this document may be available. These items shall be considered to comply with this document if they comply with the property requirements listed in Table 2 except for dimensions and mass.

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This standard specifies the required characteristics of a coaxial cable, 50 ?, type WM, for use in aircraft electrical systems at operating temperature between - 55 °C and 200 °C and specially for high frequency up to 5 GHz.

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This standard specifies the required characteristics for a heat-shrinkable, polytetrafluoroethylene sleeving for use in aircraft electrical systems at operating temperatures between ? 65 °C and 260 °C. This sleeving is basically translucent. It is semi-rigid, and suitable for use where resistance to chemicals and high temperature performance are required. It is flame resistant and available in low and high shrink ratios. Type A Low Shrink Ratio; Type B High Shrink Ratio .

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This standard specifies the characteristics of a UV laser printable coaxial cable, 50 ?, type WZ, for use in aircraft electrical systems at operating temperatures between ? 65 °C and 200 °C and especially for high frequency up to 3 GHz.

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This document specifies the characteristics of UV laser printable jacket, silver plated copper conductor, electrical cables Crosslinked Ethylene Tetra Fluoro Ethylene co-polymer (XLETFE) family for use in the on-board electrical systems of aircraft operating at temperatures between - 65 °C and 150 °C, operating at voltages not exceeding 600 V rms at sea level. This insulation system has been used in aerospace applications using 115 V (phase-to-neutral) 400 Hz ac and 28 Vdc. Verification of the suitability of cables for use in other electrical systems is the responsibility of the user.
These jacketed cables are suitable for airframe use without additional protection when the jacket is present. When the jacket is stripped back the cores may need additional protection. In case of conflict between this document and other referenced documents the requirements of this document shall take precedence.

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This document specifies a method to determine the effects of thermal shock on an optical fibre or cable.

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This document specifies the characteristics of UV laser printable jacket, nickel plated copper conductor, electrical cables Crosslinked Ethylene Tetra Fluoro Ethylene co-polymer (XLETFE) family for use in the on-board electrical systems of aircraft at operating temperatures between – 65 °C and 150 °C, operating at voltages not exceeding 600 V rms. This insulation system has been used in aerospace applications using 115 V (phase-to-neutral) 400 Hz ac and 28 Vdc. Verification of the suitability of cables for use on other electrical systems is the responsibility of the user.
These cables are suitable for airframe use without additional protection. In case of conflict between this document and other referenced documents the requirements of this document shall take precedence.

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This document specifies the characteristics of UV laser printable jacket, silver plated copper conductor, electrical cables Crosslinked Ethylene Tetra Fluoro Ethylene co-polymer (XLETFE) family for use in the on-board electrical systems of aircraft operating at temperatures between 65 °C and 150 °C, operating at voltages not exceeding 600 V rms at sea level. This insulation system has been used in aerospace applications using 115 V (phase-to-neutral) 400 Hz ac and 28 Vdc. Verification of the suitability of cables for use in other electrical systems is the responsibility of the user.
These cables are suitable for airframe use without additional protection when the jacket is present. When the jacket is stripped back the cores may need additional protection. In case of conflict between this document and other referenced documents the requirements of this document shall take precedence.

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