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ASTM F3361-18e1

(Guide)

Standard Guide for Classifying Alterations for In-Service Aircraft under FAA Authority Oversight

Standard Guide for Classifying Alterations for In-Service Aircraft under FAA Authority Oversight

SIGNIFICANCE AND USE
5.1 To standardize applications of CFR Title 14, as applicable.
SCOPE
1.1 This guide is intended for Part 23 and predecessor aircraft (see Civil Air Regulations (CAR) 3) and:  
1.1.1 Is applicable to aircraft to which Part 43 applies.  
1.1.2 Addresses both initial installation and replacement of aircraft articles.  
1.1.3 Is a guide for classifying an alteration.  
1.1.4 The intended audience of this guide is individuals who have been tasked with evaluating alterations for the purpose of categorizing an alteration for the purpose of satisfying the regulations.  
1.1.5 Is an alteration to an article.  
1.2 This standard 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 standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.  
1.3 This international standard 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.

General Information

Status
Published
Publication Date
30-Nov-2018
ICS
49.035 - Components for aerospace construction
Technical Committee
F39 - Aircraft Systems
Drafting Committee
F39.02 - Inspection, Alteration, Maintenance, and Repair
Current Stage
Ref Project

Relations

Replaces
ASTM F3361-18 - Standard Guide for Classifying Alterations for In-Service Aircraft under FAA Authority Oversight
Effective Date
01-Dec-2018

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ASTM F3361-18e1 - Standard Guide for Classifying Alterations for In-Service Aircraft under FAA Authority OversightASTM F3361-18e1 - Standard Guide for Classifying Alterations for In-Service Aircraft under FAA Authority Oversight
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ASTM F3361-18e1 - Standard Guide for Classifying Alterations for In-Service Aircraft under FAA Authority Oversight
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This international standard 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.
´1
Designation: F3361 − 18
Standard Guide for
Classifying Alterations for In-Service Aircraft under FAA
1
Authority Oversight
This standard is issued under the fixed designation F3361; the number immediately following the designation indicates the year of
original adoption or, in the case of revision, the year of last revision. A number in parentheses indicates the year of last reapproval. A
superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
1
ε NOTE—Section references in Fig. 2 were corrected editorially in August 2019.
1. Scope 14 CFRAeronautics and Space,Vol 1, Chapter I, Subchapter
C, Part 23 Airworthiness Standards: Normal, Utility,
1.1 This guide is intended for Part 23 and predecessor
Acrobatic, and Commuter Category Airplanes
aircraft (see Civil Air Regulations (CAR) 3) and:
14 CFRAeronautics and Space,Vol 1, Chapter I, Subchapter
1.1.1 Is applicable to aircraft to which Part 43 applies.
C, Part 43 Maintenance, Preventive Maintenance,
1.1.2 Addresses both initial installation and replacement of
Rebuilding, and Alteration, including Amendments 43-1
aircraft articles.
through 43-49
1.1.3 Is a guide for classifying an alteration.
14 CFRAeronautics and Space,Vol 2, Chapter I, Subchapter
1.1.4 Theintendedaudienceofthisguideisindividualswho
D, Part 65 Certification:Airmen Other Than Flight Crew-
have been tasked with evaluating alterations for the purpose of
members
categorizing an alteration for the purpose of satisfying the
14 CFRAeronautics and Space,Vol 3, Chapter I, Subchapter
regulations.
H, Part 145 Repair Stations
1.1.5 Is an alteration to an article.
3
2.2 FAA Standards:
1.2 This standard does not purport to address all of the
Civil Aeronautics Manual (CAM) 18 Maintenance, Repair,
safety concerns, if any, associated with its use. It is the
and Alteration of Airframes, Powerplants, Propellers, and
responsibility of the user of this standard to establish appro-
Appliances, dated 12/15/1959
priate safety, health, and environmental practices and deter-
Civil Air Regulations (CAR) 3 Airplane Airworthiness -
mine the applicability of regulatory limitations prior to use.
Normal, Utility, Acrobatic, and Restricted Purpose
1.3 This international standard was developed in accor-
Categories, dated 5/15/1996, including Amendments 3-1
dance with internationally recognized principles on standard-
to 3-8
ization established in the Decision on Principles for the
AC 25.571-1( ) Damage Tolerance and Fatigue Evaluation
Development of International Standards, Guides and Recom-
of Structure
mendations issued by the World Trade Organization Technical
AC 43-210( ) Standardized Procedures for Obtaining Ap-
Barriers to Trade (TBT) Committee.
proval of Data Used in the Performance of Major Repairs
and Major Alterations
2. Referenced Documents
AFS-300 Major Repair andAlteration DataApproval Online
2 4
2.1 Code of Federal Regulations: Job Aid
14 CFRAeronautics and Space,Vol 1, Chapter I, Subchapter
Order 8110.46 MajorAlterations that Require Supplemental
5
A, Part 1 Definitions and Abbreviations, including Type Certificates, dated 9/30/2002, Cancelled
Amendments 1-1 through 1-69
Order 8300.16 Major Repair and Alteration Data Approval,
14 CFRAeronautics and Space,Vol 1, Chapter I, Subchapter dated 4/18/2014, including Change 1, dated 12/7/2015
C, Part 21 Certification Procedures for Products and
Order 8900.1 Flight Standards Information Management
Articles, including Amendments 21-1 through 21-100 System (FSIMS)
FAA Special Policy on Addressing New Technology as
Applicable as Valid
1
This guide is under the jurisdiction of ASTM Committee F39 on Aircraft
Systems and is the direct responsibility of Subcommittee F39.02 on Inspection,
3
Alteration, Maintenance, and Repair. Available from Federal Aviation Administration (FAA), 800 Independence
Current edition approved Dec. 1, 2018. Published January 2019. DOI: 10.1520/ Ave., SW, Washington, DC 20591, http://rgl.faa.gov.
4
F3361–18E01. As published by AFS-300, https://www.faa.gov/about/office_org/headquarters
2
Available from U.S. Government Publishing Office (GPO), 732 N. Capitol St., _offices/avs/offices/afx/afs/afs300/.
5
NW, Washington, DC 20401, https://www.govinfo.gov/app/collection/cfr. Used as reference for 6.2.2 through 6.2.2.6 inclusive.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1

---------------------- Page: 1 ----------------------
´1
F3361 − 18
3. Terminology 3.2.3 ASI—Aviation Safety Inspector (FAA)
3.2.4 DAR—Designated Airworthiness Representative (an
3.1 Definitions:
FAA designation)
3.1.1 accepted practices, n—practices demonstrated to co
...

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ASTM E2662-15(2022)(Practice)
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SIGNIFICANCE AND USE
5.1 Radiographic examination may be used during product and process design optimization, on line process control, after manufacture inspection, and in service inspection. In addition to verifying structural placement, radiographic examination can be used in the case of honeycomb core materials to detect node bonds, core-to-core splices, and core-to-structure splices. Radiographic examination is especially well suited for detecting sub-surface flaws. The general types of defects detected by radiographic examination include blown core, core corrosion, damaged filaments, density variation, entrapped fluid, fiber debonding, fiber misalignment, foreign material, fractures, inclusions, micro-cracks, node bond failure, porosity/voids, and thickness variation.  
5.2 Factors that influence image formation and X-ray attenuation in radiographic examination, and which are relevant to interpreting the images for the conditions of interest, should be included in the examination request. Examples include, but not limited to, the following: laminate (matrix and fiber) material, lay-up geometry, fiber volume fraction (flat panels); facing material, core material, facing stack sequence, core geometry (cell size); core density, facing void content, adhesive void content, and facing volume percent reinforcement (sandwich core materials); overall thickness, specimen alignment, and specimen geometry relative to the beam (flat panels and sandwich core materials).  
5.3 Information regarding discontinuities that are detectable using radiographic examination methods can be found in Guide E2533.
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1.1 This practice is intended to be used as a supplement to Practices E1742, E1255, E2033, and E2698.  
1.2 This practice describes procedures for radiographic examination of flat panel composites and sandwich core materials made entirely or in part from fiber-reinforced polymer matrix composites. Radiographic examination is: a) Film Radiography (RT), b) Computed Radiography (CR) with Imaging Plate, c) Digital Radiography (DR) with Digital Detector Array’s (DDA), and d) Radioscopic (RTR) Real Time Radiography with a detection system such as an Image Intensifier. The composite materials under consideration typically contain continuous high modulus fibers (> 20 GPa), such as those listed in 1.4.  
1.3 This practice describes established radiographic examination methods that are currently used by industry that have demonstrated utility in quality assurance of flat panel composites and sandwich core materials during product process design and optimization, process control, after manufacture inspection, in service examination, and health monitoring. Additional guidance can be found in E2533, Guide for Nondestructive Testing of Polymer Matrix Composites Used in Aerospace.  
1.4 This practice has utility for examination of flat panel composites and sandwich constructions containing, but not limited to, bismaleimide, epoxy, phenolic, poly(amide imide), polybenzimidazole, polyester (thermosetting and thermoplastic), poly(ether ether ketone), poly(ether imide), polyimide (thermosetting and thermoplastic), poly(phenylene sulfide), or polysulfone matrices; and alumina, aramid, boron, carbon, glass, quartz, or silicon carbide fibers. Typical as-fabricated geometries include uniaxial, cross ply and angle ply laminates; as well as honeycomb core sandwich constructions.  
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1.1 This practice is intended to be used to assign part classifications across the aviation industries that use AM to produce parts.  
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ASTM F2156-17(2022)(Test Method)
Standard Test Method for Measuring Optical Distortion in Transparent Parts Using Grid Line Slope

SIGNIFICANCE AND USE
5.1 Transparent parts, such as aircraft windshields, canopies, cabin windows, and visors, shall be measured for compliance with optical distortion specifications using this test method. This test method is suitable for assessing optical distortion of transparent parts as it relates to the visual perception of distortion. It is not suitable for assessing distortion as it relates to pure angular deviation of light as it passes through the part. Either Test Method F801 or Practice F733 is appropriate and shall be used for this latter application. This test method is not recommended for raw material.
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1.1 When an observer looks through an aerospace transparency, relative optical distortion results, specifically in thick, highly angled, multilayered plastic parts. Distortion occurs in all transparencies but is especially critical to aerospace applications such as combat and commercial aircraft windscreens, canopies, or cabin windows. This is especially true during operations such as takeoff, landing, and aerial refueling. It is critical to be able to quantify optical distortion for procurement activities.  
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ASTM F801-21(Test Method)
Standard Test Method for Measuring Optical Angular Deviation of Transparent Parts

SIGNIFICANCE AND USE
5.1 One of the measures of optical quality of a transparent part is its angular deviation. It is possible that excessive angular deviation, or variations in angular deviation throughout the part, will result in visible distortion of scenes viewed through the part. Angular deviation, its detection, and quantification are of extreme importance in the area of certain aircraft transparency applications, that is, aircraft equipped with Heads-up Displays (HUD). It is possible that HUDs will require stringent control over the optics of the portion of the transparency (windscreen or canopy) which lies between the HUD combining glass and the external environment. Military aircraft equipped with HUDs or similar devices require precise knowledge of the effects of the windscreen or canopy on image position in order to maintain weapons aiming accuracy.  
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Standard Practice for Infrared Flash Thermography of Composite Panels and Repair Patches Used in Aerospace Applications

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ASTM F3498-21(Practice)
Standard Practice for Developing Simplified Fatigue Load Spectra

SIGNIFICANCE AND USE
4.1 This standard practice provides one means for determining fatigue load spectra for aeroplane durability assessments. This information can be used in conjunction with Specification F3115/F3115M, Section 5, Load Considerations.  
4.1.1 Users of this practice may propose alternate spectra, subject to the approval of their CAA.  
4.2 The methods are applicable to the durability evaluation of wings of small aeroplanes. Additional calculation (such as methods noted in ACE-100-01) are needed to properly develop load spectra for fatigue evaluation of empennage and/or configurations with canards (or forward wings) and/or winglets (or tip fins), fuselage, and potentially other components, with approval from appropriate regulatory agency.  
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1.1 This practice provides data to develop simplified loading spectra that can be used to perform structural durability analysis for aeroplanes, specifically for wings of small aeroplanes. The material was developed through open consensus of international experts in general aviation. The information was created by focusing on Level 1, 2, 3, and 4 Normal Category aeroplanes. The content may be more broadly applicable; it is the responsibility of the applicant to substantiate broader applicability as a specific means of compliance.  
1.2 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable civil aviation authorities, or CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this standard (whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to the ASTM Committee F44 web page (www.astm.org/COMMITTEE/F44.htm).  
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ASTM E3205-20(Test Method)
Standard Test Method for Small Punch Testing of Metallic Materials

SIGNIFICANCE AND USE
4.1 The safety margins provided in the design for a component or structure can be reduced throughout its service life by aging. Aging is the process by which the physical and mechanical characteristics of component or structure materials change with time or use; this process may proceed by a single aging mechanism or a combination of several aging mechanisms.  
4.2 The term “safety margin” is used in a broad sense, meaning the safety state (that is, integrity and functional capability) of components in excess of their normal operational requirements (1).3  
4.3 The determination of mechanical properties such as yield strength, tensile strength, and ductile-to-brittle transition temperature of structural components is, hence, desirable for optimization of operating procedures and inspection intervals, as well as repair strategies and residual lifetime assessment. Current standardized mechanical tests require relatively large volumes of test material that cannot be extracted from in-service equipment without post-sampling removal repair (2).  
4.4 The need to obtain estimates of the mechanical properties of components without post-sampling removal repair has led to the development of small punch (SP) test techniques based on penetration/bulge tests of miniaturized test specimens (often disk-shaped, or square) (3, 4, 5). It can be considered as a quasi-nondestructive technique because of the very limited amount of material to be sampled. It is an efficient and cost-effective technique and has the potential to provide estimates of the material properties of the specific component, identifying the present state of damage and focusing on the most critical (most stressed, most damaged) locations in the component. Examples of empirical correlations that have been established between small punch test results and mechanical properties for specific classes of materials are provided in Appendix X1.  
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SCOPE
1.1 This test method covers procedures for conducting the small punch deformation test for metallic materials. The results can be used to derive estimates of yield and tensile strength up to 450 °C, and estimates of the ductile-to-brittle transition temperature from the results of small punch bulge tests in the temperature range from -193 °C to 350 °C for iron based materials or 0.4 Tm for other metallic materials, where Tm is their melting temperature in K.  
1.2 The values stated in SI units are to be regarded as standard. No other units of measurement are included in this standard.  
1.3 This standard 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 standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.  
1.4 This international standard 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.

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ASTM F311-08(2020)(Practice)
Standard Practice for Processing Aerospace Liquid Samples for Particulate Contamination Analysis Using Membrane Filters

SIGNIFICANCE AND USE
4.1 This practice provides for the processing of liquid samples obtained in accordance with Practice F302 and Practices F303. It will provide the optimum sample processing for visual contamination methods such as Method F312, and Test Method F314.
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1.1 This practice covers the processing of liquids in preparation for particulate contamination analysis using membrane filters and is limited only by the liquid-to-membrane filter compatibility.  
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ASTM F331-13(2020)(Test Method)
Standard Test Method for Nonvolatile Residue of Solvent Extract from Aerospace Components (Using Flash Evaporator)

ABSTRACT
This test method covers the determination of non-volatile matter, that is, residue on evaporation, in solvent extract from aerospace components, using a rotary flash evaporator. The summary of the test method, the apparatus for testing, reagents and materials for testing, and procedure for testing are all presented in details.
SCOPE
1.1 This test method covers the determination of nonvolatile matter, that is, residue on evaporation, in solvent extract from aerospace components, using a rotary flash evaporator.  
1.2 The procedure for extraction from components is described in practices such as Practice F303. Before subjecting the extract to the following method, it should be processed to remove the insoluble particulate in accordance with Practice F311 (Note 1). Particle count analysis of the removed particulate may then be performed in accordance with Test Method F312. If particulate is not removed from the extract prior to performing this method, this should be noted on the test report.
Note 1: Membrane filters with a maximum extractable content of 0.5 weight % should be used on samples to be processed by this test method. Conventional membranes contain 5 to 10 % extractables. For obtaining very low background levels, consideration should be given to using membranes without grid marks.  
1.3 The values stated in SI units are to be regarded as standard.  
1.4 This standard 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 standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.  
1.5 This international standard 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.

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ASTM E3166-20e1(Guide)
Standard Guide for Nondestructive Examination of Metal Additively Manufactured Aerospace Parts After Build

SIGNIFICANCE AND USE
4.1 Metal parts made by additive manufacturing differ from their traditional metal counterparts made by forging, casting, or welding. Additive manufacturing produces layers melted or sintered on top of each other. The part’s shape is controlled by a computer as well as by the layers. The computer directs energy from a laser or electron beam onto a powder bed or wire input material. These processing approaches have the potential of creating flaws that are undesirable in the as-built or finished part. In general, processing parameter anomalies and disruptions during a build may induce such “flaws.” Flaws can also be introduced because of contaminants present in the input material.  
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4.3 Application of the NDT procedures discussed in this guide is intended to reduce the likelihood of material or component failure, thus mitigating or eliminating the attendant risks associated with loss of function, and possibly, the loss of ground support personnel, crew, or mission.  
4.4 Input Materials—The input materials covered in this guide consist of, but are not limited to, ones made from aluminum alloys, titanium alloys, nickel-based alloys, cobalt-chromium alloys, and stainless steels. Input materials are either powders or wire.
Note 3: When electron beams are used, the beam couples effectively with any electrically conductive material, including aluminum and copper-based alloys.  
4.4.1 Powders—High-quality powders required for AM process are produced by (1) plasma atomization, (2) inert gas atomizati...
SCOPE
1.1 This guide discusses the use of established and emerging nondestructive testing (NDT) procedures used to inspect metal parts made by additive manufacturing (AM).  
1.2 The NDT procedures covered produce data related to and affected by microstructure, part geometry, part complexity, surface finish, and the different AM processes used.  
1.3 The parts tested by the procedures covered in this guide are used in aerospace applications; therefore, the inspection requirements for discontinuities and inspection points in general are different and more stringent than for materials and components used in non-aerospace applications.  
1.4 The metal materials under consideration include, but are not limited to, aluminum alloys, titanium alloys, nickel-based alloys, cobalt-chromium alloys, and stainless steels.  
1.5 The manufacturing processes considered use powder and wire feedstock, and laser or electron energy sources. Specific powder bed fusion (PBF) and directed energy deposition (DED) processes are discussed.  
1.6 This guide discusses NDT of parts after they have been fabricated. Parts will exist in one of three possible states: (1) raw, as-built parts before post-processing (heat treating, hot isostatic pressing, machining, etc.), (2) intermediately machined parts, or (3) finished parts after all post-processing is completed.  
1.7 The NDT procedures discussed in this guide are used by cognizant engineering organizations to detect both surface and volumetric flaws in as-built (raw) and post-processed (finished) parts.  
1.8 The NDT procedures discussed in this guide are computed tomography (CT, Section 7, including microfocus CT), eddy current testing (ET, Section 8), optical metrology (MET, Section 9), penetrant testing (PT, Section 10), process compensated resonance testing (PCRT, Section 11), radiographic testing (RT, Section 12), infrared thermography (IRT, Section 13), and ultrasonic testing (UT, Section 14)....

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