ASD-STAN/D 4 - Metallic

This document specifies the requirements relating to:
Steel X3CrNiMoAl (13-8-2)
Vacuum induction melted and consumable electrode remelted
Solution treated and precipitation treated
Bars for machining
a or D ≤ 200 mm
1 200 MPa ≤ Rm ≤ 1 350 MPa
for aerospace applications.
Material no (W.L): 1.4534.

This document specifies the requirements relating to:
Heat-resisting alloy NI-PH1301 (NiCr19Co18Mo4Ti3Al3)
Solution treated and precipitation treated
Bars and sections
De ≤ 200 mm
for aerospace applications.

This document specifies the requirements relating to:
Steel X5CrNiCu 17 4 (1.4542)
Air melted
Solution treated and precipitation treated
Plates
6 mm ≤ a ≤ 100 mm
Rm ≥ 1 070 MPa
for aerospace applications.

This document specifies the requirements relating to:
Steel X5CrNiCu15-5 (1.4545)
Consumable electrode remelted, softened
Forging stocks
a or D ≤ 300 mm
for aerospace applications.

This document specifies the requirements relating to:
Heat-resisting alloy X6NiCrTiMnMoV26-15 (1.4944)
Softened and cold worked
Wire for forged fasteners
D ≤ 15 mm
1 100 MPa ≤ Rm ≤ 1 300 MPa
for aerospace applications.

This document specifies the requirements relating to:
Aluminium alloy AL-P6061-T4
Drawn tube for pressure applications
0,6 mm ≤ a ≤ 3 mm
for aerospace applications.

This document specifies the requirements relating to:
Steel 36NiCrMo16
1 000 MPa ≤ Rm ≤ 1 200 MPa
Bars
100 mm ≤ D ≤ 250 mm
for aerospace applications.

This document specifies the characteristics of self-extinguishing and low smoke emission semi-finished polycarbonate sheets with and without UV radiation protection requirement, as used for aircraft equipment, such as internal panelling, simple internal glazing, sound-proofing panels, light covers, etc.

This document specifies a list of procurement specifications and standards for welding products authorized for the welding of parts.

This document defines the requirements for the ordering, manufacture, testing, inspection and delivery of all forms of filler metal. It shall be applied when referred to and in conjunction with the EN material standard unless otherwise specified on the drawing, order or inspection schedule.

This document specifies the Izod impact test method for steel products used 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 inspection schedule.

This document specifies the requirements relating to:
Steel X6CrNiTi18-10 (1.4541)
Air melted
Softened
Wires
0,25 mm ≤ De ≤ 3 mm
Rm ≤ 780 MPa
for aerospace applications.
Material number: 1.4541.
ASD-STAN designation: FE-PA3601.

This document specifies the requirements relating to:
Steel X5CrNiCu15-5 (1.4545)
Consumable electrode remelted
Solution treated and precipitation treated
Plates
6 mm < a ≤ 20 mm
1 070 MPa ≤ Rm ≤ 1 220 MPa
for aerospace applications.

This document specifies the requirements relating to:
Steel X4CrNiMo16-5-1 (1.4418)
Air melted
Hardened and tempered
Bars
De ≤ 200 mm
1 150 MPa ≤ Rm ≤ 1 300 MPa
for aerospace applications.
NOTE   Other common designations:
-   AIR: Z 8 CND 17-04.
-   Only the chemical composition according to this document is considered.

This document specifies the requirements relating to:
Steel X4CrNiMo16-5-1 (1.4418)
Air melted
Hardened and tempered
Forgings
De ≤ 200 mm
1 150 MPa ≤ Rm ≤ 1 300 MPa
for aerospace applications.
NOTE   Other common designations:
-   AIR: Z 8 CND 17-04.
-   Only the chemical composition according to this document is considered.

This document specifies the sampling plan for acceptance testing of aramid, carbon fibre and textile glass filament yarns in terms of sample size and rejection criteria.
This document serves as a basis for the corresponding technical specification. It covers the inspection by attributes. The inspection by measurements (variables) will be added in subsequent edition. It is also planned to extend its scope of application to reinforcing woven fabrics.

This document specifies the requirements relating to:
Steel X5CrNiCu 17 4 (1.4542)
Air melted
Solution treated and precipitation treated
Sheets and strips
a ≤ 6 mm
Rm ≥ 1 070 MPa
for aerospace applications.
Material no (W.nr): 1.4542.
The ASD STAN designation of this material is FE PM3801.

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 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 requirements for a range of one part anaerobic polymerisable compounds
which polymerises upon the exclusion of oxygen and activation by a metal surface.

This document specifies the general organization of the EN standards for non-metallic materials and their links with other types of standards for aerospace applications.
It corresponds to level 0 (see 4.1).

This document specifies the requirements relating to:
Aluminium alloy 5086
H111
Extruded bars
10 mm ≤ D ≤ 300 mm
for aerospace applications.

This document defines the general terms to be used in the standards of metallic materials for aerospace applications. It is intended only to give terms which are truly general and where definition, in this context, is required. The definitions of more specific terms are to be found in the technical specifications, test methods, etc. which are referenced in the material standard concerned.

This document specifies the method for depositing cadmium layers according to the vacuum deposition process, for use in aerospace construction.
According to this process, cadmium metal is vaporized under vacuum and deposited directly on the base material with an interlayer. The coating produced in this way is ductile and electrically conductive.
This document is applicable whenever referenced.

This document specifies the general rules for drafting and presentation of EN aerospace series non-metallic material technical specifications.

This document specifies the rules for the drafting and presentation of technical specifications for metallic materials.

This document specifies the rules for the drafting and presentation of test method standards.

This document specifies the requirements of a thermoplastic composite stock shape material (e.g. tape,
rod etc.) consisting of polyetheretherketone with 55 % continuous glass fibres by volume (PEEK–GF55)
for aerospace applications, which is presupposed to be used in a further thermal moulding process for
forming parts described in EN 4714 1).

This document specifies the requirements of a thermoplastic composite stock shape material (e.g. tape,
rod, etc.) consisting of polyetheretherketone with 55 % continuous carbon fibres by volume (PEEK–
CF55) for aerospace applications, which is presupposed to be used in a further thermal moulding
process for forming parts described in EN 4714 1).

This document specifies the requirements relating to:
Heat resisting alloy CO-PH4101 (CoCr20W15Ni)
Vacuum melted
Solution treated
Forgings
De ≤ 100 mm
for aerospace applications.

1.1 Purpose
This document establishes the minimum requirements for the qualification and certification of personnel performing non-destructive testing (NDT), non-destructive inspection (NDI), or non-destructive evaluation (NDE) in the aerospace manufacturing, service, maintenance and overhaul industries. For the purposes of this document, the term NDT will be used and will be considered equivalent to NDI and NDE.
In Europe, the term "approval" is used to denote a written statement by an employer that an individual meets specific requirements and has operating approval. The term "certification" as defined in 3.2 is used throughout this document as a substitute for the term "approval". Except when otherwise specified in the written practice, certification in accordance with this document includes operating approval.
1.2 Applicability
1.2.1 General
This document applies to personnel using NDT methods to test and/or accept materials, products, components, assemblies or sub-assemblies. This document also applies to personnel: directly responsible for the technical adequacy of the NDT methods used, who approve NDT procedures and/or work instructions, who audit NDT facilities, or who provide technical NDT support or training.
This document does not apply to individuals who only have administrative or supervisory authority over NDT personnel or to research personnel developing NDT technology for subsequent implementation and approval by a certified Level 3.
Personnel performing specialized inspections using certain direct readout instruments as determined by a Level 3 person certified in the test method, do not require qualification or certification to this document.
1.2.2 Implementation
This document addresses the use of a National Aerospace NDT Board (NANDTB). NANDTBs are only used as specified according to Annex C and it is not mandatory to have such a board for compliance with this document. Personnel certified to previous revisions of NAS 410 or EN 4179 need not recertify to the requirements of this document until their current certification expires.
1.3 Test Methods
1.3.1 Common test methods
This document contains detailed requirements for the following common NDT methods:
Eddy Current Testing   (ET)
Magnetic Particle Testing   (MT)
Penetrant Testing   (PT)
Radiographic Testing   (RT)
Thermographic Testing   (TT)
Ultrasonic Testing   (UT)
1.3.2 Other test methods
When invoked by engineering, quality, cognizant engineering organization or prime contractor requirements, this document applies to other current and emerging NDT methods used to determine the acceptability or suitability for intended service of a material, part, component, assembly or sub-assembly. Such test methods can include, but are not limited to, acoustic emission testing (AT), neutron radiography, leak testing, holography, and shearography. The requirements for personnel training, experience, and examination for these other test methods are established in accordance with 6.4 and are documented by the employer.

This document provides a list of terms with their definitions illustrated by typical photographs, in order
to define a common vocabulary on the imperfections and damage that may occur during the
manufacture of organic matrix composite materials (which will be called “resin” in this document).
Some types of damage may also be encountered in use.
This document is restricted to their definitions and does not give any acceptance criteria. The word
“imperfection” will be preferred to the word “defect”, although the word “defect” might be usually used.
Defect acceptance criteria to be discussed between the user and customer and documented
appropriately between the two parties.

This document defines the requirements for the ordering, manufacture, testing, inspection and delivery of steel and heat resisting alloy bars and sections. It shall be applied when referred to and in conjunction with the EN material standard unless otherwise specified on the drawing, order or inspection schedule.

This document specifies the requirements relating to:
Steel X12CrNiMoV12-3 (1.4938)
Air melted and consumable electrode remelted
Hardened and tempered
Bars
De ≤ 150 mm
900 MPa ≤ Rm ≤ 1 100 MPa
for aerospace applications.

This document specifies the requirements relating to:
Heat resisting alloy X6NiCrTiMoV26-15 (1.4980)
Softened and cold worked
Wires for forged fasteners
D ≤ 15 mm
900 MPa ≤ Rm ≤ 1 100 MPa
for aerospace applications.
W.nr: 1.4980.
ASD-STAN designation: FE-PA2601.

This document specifies the dimensions and tolerances of plates in aluminium alloy 2024 with close-tolerance flatness, thickness 6 mm < a ≤ 55 mm, for aerospace applications.

This document defines the requirements for a two-components, chromate and lead-free primer.
The coating shall be suitable for use on fibre reinforced composite materials, titanium and corrosion resistant steels and other suitably prepared corrosion resistant substrates.

This document specifies the requirements for a two-components flexible polyurethane topcoat to be applied over EN 4687 and/or EN 4688 primers mainly for exterior aerospace applications.
The primer and the finish tested to this document will be from the same manufacturer applied in accordance with (i.a.w.) their instructions/Table 1.

This document defines the requirements for a two-components, high corrosion inhibiting epoxy primer.
The coating shall be suitable for use on suitably prepared metallic substrates, chromic acid anodised, or conversion coated aluminium alloys and other suitably prepared substrates.

This document specifies the electrolytic cadmium plating of parts and fasteners in steel of tensile strength Rm (max.)  1 450 MPa, copper, copper alloys and nickel alloys, whose temperature in service does not exceed 235 °C.

This document specifies the monitoring of mechanical tests and inspections performed both at the material (coupon) and at the structural scale by the implementation of kinematic field measurements by digital image correlation. This document describes an in situ method for evaluating the metrological performance of an extensometer system using image correlation for the delivery of displacement fields, and by extrapolation, of deformation fields. It can be implemented prior to the actual start of the test (or inspection). It will inform of the metrological performance in testing conditions.
This document allows the metrological performance of the measuring technology to be quantified. The methodology described herein is not to be considered as a calibration step. This reference document does not exhaustively specify the constitutive elements of a generic system of Digital Image Correlation measurement. This reference does not address the measurement of 3D shapes via stereocorrelation systems.

This document provides a series of standard testing methods to determine the resistance of flat or curved surfaces against abrasion, scratch or punch under high dynamics as may occur for example by manually operating actuators or due to impacts of materials like shoes, cases, bags and other common objects of everyday’s usage inside an aircraft cabin. The method is also suitable to test the resistance of a surface against all other high dynamic strains.

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.

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.

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.

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.

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.

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.

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.

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.