This European standard specifies the characteristics of inch based spherical plain bearing, metal to metal, in corrosion resisting steel, narrow series.
They are intended for use in fixed or moving parts of the aircraft structure and their control mechanisms.
They shall be used in the temperature range as determined by the grease capability as below:
- code A: grease as per MIL PRF 23827 Type I, operating temperature range −73 °C to 121 °C;
- code B: grease as per MIL PRF 81322, operating temperature range −54 °C to 177 °C.
The range of application for bearings lubricated with grease per code A is limited to 121 °C.
In both cases the spherical surface of the outer or inner ring have to be provided with a dry film lubricant as per MIL PRF 46010 or equivalent (anti seizing protection).

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This document specifies the requirements relating to:
Heat resisting nickel base alloy (NI-P101HT)
Cold worked and solution treated
Bars for machining for fasteners
3 mm ≤ D ≤ 50 mm
for aerospace applications.

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This document specifies the requirements for the determination of conductivity and pH of aqueous extracts of textile materials.
This method has been written in response to an aerospace requirement for a method of extraction using hot water as the EN 1413 requires only a cold water extraction method.

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This document specifies the requirements relating to:
Heat resisting alloy FE-PM1708
Vacuum arc remelted
Hardened and tempered
Bars
a or D ≤ 200 mm
1 000 MPa ≤ Rm ≤ 1 140 MPa
for aerospace applications.

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This document specifies the requirements relating to:
Heat resisting alloy X12CrNiCoMoW21-20
Solution treated
Forgings
De ≤ 100 mm
for aerospace applications.
ASD-STAN Designation: FE-PA4901.

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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 document specifies the requirements relating to:
Heat resisting alloy FE-PM1708
Vacuum arc remelted
As forged
Forging stock
De ≤ 300 mm
for aerospace applications.

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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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This document specifies the requirements relating to:
Heat resisting alloy X4NiCrMoTi43-13
As forged
Forging stock
a or D ≤ 200 mm
for aerospace applications.
ASD-STAN designation: FE-PA2501.

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This document specifies the requirements relating to:
Heat resisting alloy X12CrNiCoMoW21-20
Solution treated and precipitation treated
Forgings
De ≤ 100 mm
for aerospace applications.
ASD-STAN designation: FE-PA4901.

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This document specifies the requirements relating to:
Heat resisting alloy X12CrNiCOMoW21-20
Solution treated and descaled
Sheets and plates
3 mm < a ≤ 50 mm
for aerospace applications.
ASD-STAN designation: FE-PA4901.

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This document describes the measurement method for the lifetime behaviour of aircraft cabin light units in a standardized aircraft-related environment.

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This document specifies the requirements relating to:
Heat resisting alloy X12CrNiCoMoW21-20
Solution treated
Bars and sections
De ≤ 100 mm
for aerospace applications.
ASD-STAN Designation: FE-PA4901.

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This document specifies the requirements relating to:
Heat resisting alloy X12CrNiCoMoW21-20
Solution treated
Sheets and strips
a ≤ 3 mm
for aerospace applications.
ASD-STAN designation: FE-PA4901.

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This document specifies the requirements relating to:
Heat resisting alloy X12CrNiCoMoW21-20
Solution treated and precipitation treated
Bars and sections
De ≤ 100 mm
for aerospace applications.
ASD-STAN Designation: FE-PA4901.

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This document defines the test procedures and calculations to determine the ECO efficiency of the following catering equipment installed in an aircraft:
- Chilling equipment (with freeze function);
- Ovens (steam and convection ovens);
- Beverage makers (coffee maker, water heater).
Based on the results it will be possible to derive the energy consumption index and a performance index of the considered equipment type. The two index values represent the ECO efficiency.

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This European standard describes a test procedure to identify performance characteristics and a weight rating of a galley chilling equipment used on aircraft. Furthermore it describes the calculation procedure to determine an energy consumption index and a performance index. Only galley chilling equipment with a freeze function will be considered. The effect of the chilling equipment on food quality is not addressed in this standard.

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This European standard describes a test procedure to identify performance characteristics and a weight rating of beverage maker products used on aircraft. Furthermore it describes the calculation procedure to determine an energy consumption index and a performance index. The effect of the beverage makers on beverage quality is not addressed in this standard.

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This European standard describes a test procedure to identify performance characteristics and a weight rating of convection and steam ovens used on aircraft. Furthermore it describes the calculation procedure to determine an energy consumption index and a performance index. There is no direct correlation between the Eco efficiency and cooking performance in terms of food quality and appearance. The two index values represent the Eco efficiency.

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This document specifies the acid pickling of aluminium and aluminium alloys free from hexavalent chromium.

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This document specifies the requirements relating to:
Heat resisting alloy FE-PA2601
Softened and cold worked
Bar for forged fasteners
D ≤ 50 mm
1 100 MPa ≤ Rm ≤ 1 300 MPa
for aerospace applications.

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This document specifies the requirements relating to:
Steel FE-PM1503 (X3CrNiMoAl 13-8-2)
Vacuum induction melted and consumable electrode remelted
Solution treated and precipitation treated
Bar for machining
a or D ≤ 150 mm
Rm ≥ 1 400 MPa
for aerospace applications.

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This document specifies the requirements relating to:
Heat resisting alloy NI-PH2601
Solution treated and cold worked
Bar for forged fasteners
D ≤ 50 mm
1 550 MPa ≤ Rm ≤ 1 830 MPa
for aerospace applications.

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This document specifies the requirements relating to:
Heat resisting nickel base alloy (NI-P100HT)
Cold worked and softened
Bar and wire for continuous forging or extrusion for fasteners
3 mm ≤ D ≤ 30 mm

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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 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 describes the electrical contact resistance testing method applicable to conductive and non-conductive coatings applied on test specimens made of conductive materials (unless otherwise specified) for aerospace applications. An objective of this practice is to define and control many of the known variables in such a way that valid comparisons of the contact properties of materials can be made.
This test may be locally destructive depending on the process tested.

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This standard specifies several chemical methods of passivation for corrosion resisting steels (austenitic, ferritic, martensitic and precipitation hardenable) and of decontamination for nickel or cobalt base alloys.

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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 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 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 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 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 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 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 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 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 requirements relating to:
Steel X8CrNiTi18-10 (1.4878/1.4544)
Softened
500 ≤ Rm ≤ 750 MPa
Tubes for structures
0,5 ≤ a ≤ 5 mm
for aerospace applications.
ASD-STAN designation: FE-PA13.

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This document specifies the requirements relating to:
Steel X5CrNiCuNb16-4 (1.4549 type 1.4542)
As cast
Reference heat treatment:
homogenised, solution treated, precipitation hardened and sub zero
Remelting stock
for aerospace applications.
ASD-STAN designation: FE-CM61.

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This European Standard specifies the requirements relating to:
Heat resisting alloy NI-PH2801 (NiCr16Fe7Ti3Nb1Al1)
Consumable electrode remelted
Cold drawn wire for the manufacture
of the thread inserts
D  3 mm
for aerospace applications.

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This document specifies the requirements relating to:
Steel X5CrNoMoCuNb14-5 (1.4594)
930 MPa ≤ Rm ≤ 1 080 MPa
Forgings
De ≤ 150 mm
for aerospace applications.
ASD-STAN designation: FE-PM66.

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This document specifies the requirements relating to:
Steel X5CrNoMoCuNb14-5 (1.4594)
930 MPa ≤ Rm ≤ 1 080 MPa
Bars
De ≤ 150 mm
for aerospace applications.
ASD-STAN designation: FE-PM66.

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This document specifies the requirements relating to:
Steel 30CrNiMo8 (1.6580)
1 100 MPa ≤ Rm ≤ 1 300 MPa
Forgings
De ≤ 100 mm
for aerospace applications.
W.nr: 1.6580
ASD-STAN designation: FE-PL74.

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This document specifies the requirements relating to:
Steel X3CrNiMoAl13-8-2 (1.4534)
Solution annealed and precipitation hardened
1 400 ≤ Rm ≤ 1 550 MPa
Forgings
De ≤ 100 mm
for aerospace applications.
ASD-STAN designation: FE-PM67.

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This document specifies the requirements relating to:
Steel 31Ni10
1 230 MPa ≤ Rm ≤ 1 420 MPa
Forgings
De ≤ 40 mm
for aerospace applications.
ASD-STAN designation: FE-PL73.

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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 requirements relating to:
Heat resisting nickel base alloy Ni-P96-HT
Cold drawn and precipitation treated
Wire
D ≤ 10 mm
for aerospace applications.

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This document specifies the requirements for the radiographic testing of castings for aerospace applications.
It shall be applied when referred to in the EN technical specification or material standard unless otherwise specified on the drawing, order or testing schedule.

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This document specifies the requirements relating to:
Steel X8CrNiTi18-10 (1.4878/1.4544)
Softened
500 MPa ≤ Rm ≤ 700 MPa
Forgings
De ≤ 100 mm
for aerospace applications.
ASD-STAN designation: FE-PA13.

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This document specifies the requirements relating to:
Steel X8CrNiTi18-10 (1.4878/1.4544)
Annealed
Reference heat treatment: softened
Forging stock
De ≤ 100 mm
for aerospace applications.
ASD-STAN designation: FE-PA13.

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