ASD-STAN - Aerospace

This document specifies the plugs series 2, for 2 and 4 modules used in the family of rectangular electrical connectors, operating temperature 175 °C continuous. The receptacles and accessories corresponding to those plugs are specified in EN 4165 002.

This document specifies the rack and panel plug for 2 and 4 modules, series 2 used in the family of rectangular electrical connectors, operating temperature 175 °C continuous. The receptacles and accessories corresponding to those plugs are specified in EN 4165-002.

This document specifies the plug series 3, for 2 and 4 modules used in the family of rectangular electrical connectors, operating temperature 175 °C continuous. The receptacles and accessories corresponding to those plugs are specified in EN 4165 002.

This document specifies the rack and panel rear mounted plug 2 and 4 modules, series 2 used in the family of rectangular electrical connectors, operating temperature 175 °C continuous. The receptacles and accessories corresponding to those plugs are specified in EN 4165-002.

This document specifies the stackable mounting receptacles series 3, for 2 or 4 modules used in the family of rectangular electrical modular connectors, operating temperature 175 °C continuous. The plugs, flight caps and accessories corresponding to those receptacles are specified in EN 4165 002.

This document specifies the characteristics of spherical plain bearings in corrosion resisting steel, with assembly slots, metric series, with or without lubrication holes and groove, intended for use in fixed or moving parts of aircraft structure and control mechanisms, within the temperature range from −54 °C to 150 °C.
It also applies to the following temperature ranges when lubricated with the following greases (see EN 2337):
-   ester type very high pressure grease (code letter A), operating range from −73 °C to 121 °C;
-   synthetic hydrocarbon type very high pressure grease general purpose (code letter B), operating range from −54 °C to 177 °C.
Their field of application when lubricated with grease code letter A is limited to 121 °C.

This document specifies the single module plug used in the family of rectangular electrical connectors, operating temperature 175 °C continuous. The receptacles and accessories corresponding to this plug are specified in EN 4165-002. The cavity of this connector is uncoded, so it can accept polarized modules N, A, B, C and D as specified in EN 4165-002.

This document specifies the general requirements for the methods of testing elements of electrical, optical and data transmission system connections used in aerospace applications.

This document defines the structure and content for the long-term preservation of digital product and technical data. EN 9300 is broken into a series of separate standard parts to make the standard applicable for different business requirements and extensible for further long-term archiving formats.
The following outlines the total scope of this document:
-   for the purpose of this document, structure, and content of EN 9300 standard parts are detailed.

This document specifies the general characteristics, conditions for qualification, acceptance and quality assurance for a fibre optic cable with a bend-insensitive, 50 µm/125 µm Graded Index fibre core, 1,8 mm outside diameter for non pull-proof contact designs.

This document specifies the general conditions for test methods applicable to circuit breakers for aerospace applications.

This document specifies minimum reliability test requirements for sub-components of commercial
aircraft passenger seats. Test procedures including in-service load cases regarding passenger behaviour
for sub-seat components are specified. Abuse loads are excluded. This document is applicable to the
sub-seat components such as but not limited to backrest, headrest, armrest, table, literature pocket and
control elements.
This document does not apply to belts, Inflight-Entertainment, seat dress cover and cushions.
Additional environmental influences like temperature, radiation, gases and liquids may also alter the
reliability of the aircraft passenger seats and their sub-components over their lifetime but are not taken
into consideration in this document.
Tests on abrasion and surface durability are specified in EN 4860, EN 4864 and EN 4876.

The EN 4500 series specifies the rules for the drafting and presentation of metallic material standards for aerospace applications.
This Part 001 specifies the "General rules" framework valid for all parts.

The EN 4500 series specifies the rules for the drafting and presentation of metallic material standards for aerospace applications. This Part 005 specifies the "Specific rules for steels".

The EN 4500 series specifies the rules for the drafting and presentation of metallic material standards for aerospace applications. This Part 003 specifies the "Specific rules for heat resisting alloys".

The EN 4500 series specifies the rules for the drafting and presentation of metallic material standards for aerospace applications. This Part 006 specifies the "Specific rules for filler metals for brazing".

The EN 4500 series specifies the rules for the drafting and presentation of metallic material standards for aerospace applications.
This Part 002 specifies the "Specific rules for aluminium, aluminium alloys and magnesium alloys".

The EN 4500 series specifies the rules for the drafting and presentation of metallic material standards for aerospace applications. This Part 004 specifies the "Specific rules for titanium and titanium alloys".

This document specifies the requirements relating to:
Steel X5CrNiCu15-5 (1.4545)
Consumable electrode remelted
Solution treated and precipitation treated
Sheets and strips
a ≤ 6 mm
1 070 MPa ≤ Rm ≤ 1 220 MPa
for aerospace applications.

This document specifies the general organization of metallic material standards for aerospace applications, their links with other types of European standards and their use.
It corresponds to level 0 (see 4.2).
From the date of publication of this document, specifications for different welding and brazing products can be written in only one standard instead of separated material standards. Already existing material standards for filler metals for welding and for brazing can continue to follow this organization.

This document enables the specific needs of the aeronautical, space and defence fields to be met. It can also apply to other fields.
However, the specificity of some fields can lead to the use of existing sectorial standards such as EN 16601-80, Space project management - Risk management (derived from ECSS-M-80).
This document:
-   proposes a framework for implementing organization of risk management and opportunity management within programme management; this framework may serve as a basis for writing risk management specifications and opportunity management specifications;
-   describes a process for keeping programme risks within the defined limitations that are considered tolerable; this standard process can be used as a methodological guide for writing the programme risk control plan;
-   describes a process for addressing and developing opportunities that have positive consequences on the execution of a programme; this standard process can be used as a methodological guide for writing the strategic programme opportunity control plan;
-   recognizes the need for knowledge management in order to capitalize and to share lessons learned with other programmes, as well as the maturity assessment of the risk management and opportunity management processes;
-   identifies useful documents for risk management and opportunity management;
-   proposes an example of a typical list of risks and opportunities.

This document specifies the requirements relating to:
Steel X4CrNiMo16-5-1 (1.4418)
Air melted
Hardened and tempered
Bars
De ≤ 200 mm
900 MPa ≤ Rm ≤ 1 050 MPa
for aerospace applications.
NOTE   Other common designations:
AIR: Z 8 CND 17 04.
Only the chemical composition of this document are considered.

This document specifies the requirements relating to:
Steel X4CrNiMo16-5-1 (1.4418)
Air melted
Hardened and tempered
Forgings
De ≤ 200 mm
900 MPa ≤ Rm ≤ 1 050 MPa
for aerospace applications.
NOTE   Other common designations:
AIR: Z 8 CND 17 04.
Only the chemical composition of this document are considered.

This document specifies the general characteristics, conditions for qualification, acceptance and quality assurance for a fibre optic cable with a 50/125 µm Graded Index fibre core, 1,8 mm outside diameter for non-pull-proof contact designs.

This document specifies the requirements relating to:
Steel X5CrNiCu15-5 (1.4545)
Consumable electrode remelted
Solution treated and precipitation treated
Bars for machining
a or D ≤ 200 mm
Rm ≥ 1 310 MPa
for aerospace applications.

This document specifies the characteristics of jam-nuts for jam-nut receptacles in the family of circular electrical connectors coupled by threaded ring.
It is applicable to classes specified in Table 3.
For receptacles using these jam-nuts, see EN 2997-004, and EN 2997-006 for class SE only.

This document specifies minimum requirements for life rafts carried on helicopters operating in a hostile sea area or over very rough sea conditions. Life rafts covered by this document are for use by helicopter crew members and passengers in the event of a ditching or water impact.
They are intended either for integration into the helicopter, or stowed in the cabin before being manhandled out of the helicopter. This document does not cover air-drop life rafts.

This European Standard specifies the requirements relating to:
Steel X4CrNiMo16-5-1
Air melted
Hardened and tempered
Sheets and plates
0,3 mm ≤ a ≤ 50 mm
900 MPa ≤ Rm ≤ 1 050 MPa
for aerospace applications.
ASD-STAN designation: FE-PM 3504.

This document specifies the characteristics for screws, 100° countersunk reduced head, offset cruciform recess, close tolerance shank, short thread, in titanium alloy, anodized, MoS2 lubricated, classification 1 100 MPa/315 °C, inch series, for aerospace applications.

This document provides a list of removable sealing sleeves as defined in the product standards for use in connectors or other electrical elements of connection.

This document specifies the characteristics of self-locking shank nuts in NI-P101HT, silver plated, for use in 30° cone holes, for aerospace applications.
Classification: 1 210 MPa /730 °C .

This document specifies a method of measuring the semi loose effect of a semi loose cable.
Pull proof optical contacts are used. The optical contact (ferrule) is longitudinally moving to preserve the optical performance even when cables are pulled.
Consequently, the buffered fibre moves beneath the strength members (called semi loose effect).
This document describes a test methodology to assess the quality of the cable when contact is pulled or pushed.

This document specifies methods for determining the resin content, fibre content and mass of fibre per unit area of fibre preimpregnates for aerospace use.

This document specifies the characteristics of three-pole circuit breakers, temperature compensated with a rated current from 1 A to 25 A, used in aircraft on-board circuits at a temperature between −55 °C and 125 °C for ratings ≤ 15 A and −55 °C to 90 °C for ratings > 15 A and at an altitude of 22 000 m max.
These circuit breakers are operated by a push-pull type single pushbutton (actuator), with delayed action “trip-free” tripping.
They will continue to function up to the short-circuit current.

This document specifies the requirements for the ordering, manufacture, testing, inspection and delivery of all forms of filler metal. It is presupposed to be applied when referred to and in conjunction with the product procurement specification unless otherwise specified on the drawing, order or inspection schedule.

This document specifies the characteristics of screws with 100° countersunk head, offset cruciform recess, threaded to head, in FE-PA92HT, for aerospace applications.
Classification: 900 MPa /650 °C .

1.1   General
This document establishes the requirements for performing and documenting FAI. It is emphasized the requirements specified in this document are complementary (not alternative) to customer and applicable statutory and regulatory requirements.
1.2   Purpose
The primary purpose of FAI is to verify and validate product realization processes are capable of producing characteristics that meet engineering and design requirements. A well-planned and executed FAI by a multi-disciplinary team (e.g. members from responsible functions) provides objective evidence the manufacturer’s processes can produce compliant product; having effectively understood and incorporated the associated requirements.
NOTE   A FAI is not a product acceptance document. While interrelated, FAI and product acceptance are separate activities. The focus of FAI is verification of production processes via assessment of product. FAI and supporting documentation do not provide assurance regarding conformance for product acceptance purposes; neither does the lack of a FAI necessarily imply product is nonconforming to engineering and design requirements.
FAI will:
-   provide confidence, through objective evidence, the product realization processes are capable of producing conforming product;
-   demonstrate the manufacturers and processors of the product have an understanding of the associated requirements;
-   provide assurance of product conformance at the start of production and after changes, as outlined in this document.
A FAI is intended to:
-   mitigate risks associated with production startup and process changes;
-   reduce future escapes;
-   help ensure product safety;
-   improve quality, delivery, and customer satisfaction;
-   reduce costs and production delays associated with product nonconformances;
-   identify product realization processes not capable of producing conforming characteristics and initiate and/or validate associated corrective actions.
-
1.3   Application
This document applies to organizations and their suppliers responsible for product realization processes that produce the design characteristics of the product. The organization shall flow down the requirements of this document to suppliers who produce design characteristics.
This document also applies to suppliers performing special process(es). A certificate of conformance (CoC) provided by processors attests to satisfying the requirements. External suppliers providing special process(es) can satisfy this document's requirements by either:
-   documenting the design characteristics and associated results on a first article inspection report (FAIR); or
-   documenting the design characteristics and associated results on a detailed CoC.
This document applies to assemblies, sub-assemblies, and detail parts including castings, forgings, and modifications to standard catalogue or commercial-off-the-shelf (COTS) items. Each of these items have a separate FAI.
Unless contractually required, this document does not apply to:
-   development and prototype parts that are not considered as part of the first production run;
-   procured standard catalogue item, COTS, or deliverable software. When these items are included in an assembly, they shall be documented in the index of part numbers in an assembly FAIR.
1.4   Informative
If there is a conflict between the requirements of this document, and customer or applicable statutory/regulatory requirements, the latter takes precedence.
In this document, the following verbal forms are used:
-   "shall" indicates a requirement;
-   "should" indicates a recommendation;
-   "may" indicates a permission;
-   "can" indicates a possibility or a capability.
Information marked as "NOTE" is for guidance in understanding or clarifying the associated requirement .

This document specifies the characteristics, qualification and acceptance requirements for helical coil screw thread inserts.
It is applicable whenever referenced.

This document defines the performances and contact arrangements for threaded ring coupling circular connectors, fire resistant or non-fire resistant, intended for use in a temperature range from -65 °C to 175 °C or 200 °C continuous.

This document specifies the characteristics of hermetic jam-nut mounted receptacles in the family of circular electrical connectors coupled by threaded ring.
It is applicable to the class specified in Table 4.
For plugs and protective covers, see EN 2997-008 and EN 2997-009 respectively. For spare jam-nuts and O-rings, see EN 2997-012 and EN 2997-013 respectively.

This document specifies the dimensions, tolerances, required characteristics and the mass of an
AWG 24 shielded quad cable, type KD, intended for high speed (100 Mbit/s) full duplex Ethernet
networks.
Linked to this particular application, the operating temperatures of the cable are between −65 °C and
125 °C.
The cable resists a long-term temperature between −65 °C and +200 °C.
Moreover, cable materials are compatible with 200 °C peak exposure.
This cable is laser markable, this marking satisfies the requirements of EN 3838.
The characteristics impedance is (100 ± 15) Ω.

This document specifies the characteristics of jam-nut mounted receptacles in the family of circular electrical connectors coupled by threaded ring.
It is applicable to the class specified in Table 4.
For contacts, filler plugs, and rear accessories associated with this receptacle, see EN 2997-002. For plugs and protective covers, see EN 2997-008 and EN 2997-009 respectively. For spare jam-nuts and o-rings, see EN 2997-012 and EN 2997-013 respectively.

This document specifies the required characteristics for fluoroelastomeric, heat-shrinkable boots for use in aircraft electrical systems at operating temperatures between −55 °C and 200 °C.
The moulded shapes can be supplied with a pre-coated adhesive. Refer to the manufacturers/suppliers for options. A guide to adhesive compatibility is given in Annex A.
These moulded shapes are normally supplied in the styles and dimensions given in EN 4840 002. The colour is normally black.
Styles and dimensions other than those specifically listed in EN 4840 002 can be available as custom items. These items are considered to comply with this document if they comply with the property requirements listed in Table 1 with the exception of dimensions.

This document specifies the requirements relating to:
Titanium alloy TI-P64001 (Ti-6Al-4V)
Annealed
Bars for machining
D < 300 mm
900 MPa ≤ Rm ≤ 1 160 MPa
for aerospace applications

This document specifies the required characteristics of loop style clamps ("P" type) in aluminium alloy with various cushion materials.
These clamps are used for supporting aerospace pipe assemblies and electrical cable bundles.
They are used up to 80 °C max.
Usage at a higher temperature is at the option of the user.
For temperature range and environmental considerations, see the various cushion material standards.

This document specifies the characteristics of UV laser printable electrical wires DZ family for use in the on board:
- 115 VAC (phase to neutral) or 200 VAC (phase to phase) electrical network of aircraft;
- 230 VAC (phase to neutral) or 400 VAC (phase to phase) electrical network of aircraft and particularly use in non-pressurized areas.
This cable family is used at operating temperature between -65 °C and 260 °C. These cables are demonstrated to be arc resistant for both networks (115 VAC and 230 VAC).

This test method describes the principles applicable to infrared transmission spectrophotometric analysis of organic compounds (elastomers, basic resins, resin mixes or resin systems) used as the matrix in reinforced polymers, adhesives, bonding primers and, in general terms, all organic compounds.
The method could also be applied to some inorganic products.
It is intended to be used jointly with special test conditions specified in the materials specification invoking the test.
This document does not give any directions necessary to meet the health and safety requirements. It is the responsibility of the user of this document to adopt appropriate health and safety precautions.

This document specifies the requirements relating to:
Steel 15CrMoV6 (1.7334)
Air melted
Hardened and tempered
Sheets and strips
2 mm ≤ a ≤ 6 mm
1 080 MPa ≤ Rm ≤ 1 280 MPa
for aerospace applications.
W.nr: 1.7334.
ASD-STAN designation: FE-PL1505.