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This Part of EN 1915 specifies the conditions to be taken into consideration when calculating the strength and the stability of GSE according to EN 1915-1 and the EN 12312 series under intended use conditions. It also specifies general test methods. NOTE The methods given in this standard demonstrate one way of achieving an acceptable safety level. Methods that produce comparable results may be used. This Part of EN 1915 does not establish additional requirements for the following: - operation elsewhere than in an airport environment; - operation in severe conditions, e.g. ambient temperature below -20 C or over 50 C, tropical or saturated salty atmospheric environment; - hazards caused by wind velocity in excess of the figures given in this European Standard; - earthquake, flood, landslide, lightning and more generally any natural catastrophe. This Part of EN 1915 is not applicable to GSE which are manufactured before the date of publication by CEN of this Standard.

This document specifies: — the tests for finished wiring, including connectors and, if necessary, terminals, terminal ends, junction boxes, circuit breakers, etc.; — the requirements for verification of aircraft electrical wiring; — continuity of circuits; — dielectric strength; — insulation resistance; — partial discharge for operating voltages above 230/400 V a.c. (see also TR 4907 ). These tests do not concern equipment installed in the aircraft (see operation of systems) and do not apply to the wiring used in instrumentation.

This document is applicable to the marking of aerospace vehicle electrical wires and cables using ultraviolet (UV) lasers. This document specifies the process requirements for the implementation of UV laser marking of aerospace electrical wires and cables and fibre optic cables to achieve an acceptable quality mark using equipment designed for UV laser wire marking of identification codes on aircraft wire and cable subject to EN 3475 100, Aerospace series — Cables, electrical, aircraft use — Test methods — Part 100: General. Wiring specified as UV laser markable, and which has been marked in accordance with this document, will conform to the requirements of EN 3838. This document is applicable to the marking of airframe electrical wires and cables using ultraviolet (UV) lasers. The laser process practices defined in this document are mandatory.

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.

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 MPa /315 °C . These bolts are intended to be used with washers according to EN 2414 and nuts according to EN 3230.

1.1       This document is intended to be used to assign part classifications across the aviation industries that use AM to produce parts. 1.2       This document is applicable to all AM technologies defined in ISO/ASTM 52900 used in aviation. 1.3       This document is intended to be used to establish a metric for AM parts in downstream documents. 1.4       This document is not intended to establish criteria for any downstream processes, but rather to establish a metric that these processes can use. 1.5       The part classification metric could be utilized by the engineering, procurement, non-destructive inspection, testing, qualification, or certification processes used for AM aviation parts. 1.6       The classification scheme in this document establishes a consistent methodology to define and communicate the consequence of failure associated with AM aviation parts. 1.7       This document is not intended to supersede the requirements and definitions of the applicable regulations or policies, including but not limited to the ones listed in Annex A1. 1.8       Tables A.1.1-A.1.3 align the existing regulations and guidance with the four part classes established herein. However, this alignment should not be construed as an alignment of the existing regulations to each other. 1.9       The material or process, or both, in general does not affect the consequence of failure of a part, therefore the classification scheme defined in this document may be used outside AM. 1.10    The user of this document should not assume regulators’ endorsement of this document as accepted mean of compliance. 1.11    This document does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this document to establish appropriate safety, health, and environmental documents and determine the applicability of regulatory limitations prior to use. 1.12    This document was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.