iTeh StandardsiTeh Standards
EURUSD
Your shopping cart is empty.
ASTM

ASTM F2639-07e1

(Practice)

Standard Practice for Design, Alteration, and Certification of Airplane Electrical Wiring Systems

Standard Practice for Design, Alteration, and Certification of Airplane Electrical Wiring Systems

SIGNIFICANCE AND USE
Design—The design procedures defined in this practice are intended to provide acceptable guidance in the original design of electrical systems.
Alteration—The alteration procedures defined in this practice are intended to provide acceptable guidance for modification of general aviation aircraft. Design of any modification shall follow the practices and processes defined in the design sections of this practice.
Certification—Certification guidance provided in this practice is intended to provide generally accepted procedures and processes for certification of original and modified electrical systems and equipment. Requirements for certification shall be coordinated with the applicable National Aeronautics Association/Civil Aeronautics Administration (NAA/CAA) regulatory agency.
SCOPE
1.1 Definition—This practice defines acceptable practices and processes for the design, alteration, and certification of electric systems and installations in general aviation aircraft. This practice does not change or create any additional regulatory requirements nor does it authorize changes in or permit deviations from existing regulatory requirements.
1.2 Applicability—The guidance provided in this practice is directed to air carriers, air operators, design approval holders, Supplemental Type Certificate (STC) holders, maintenance providers, repair stations, and anyone performing field approval modifications or repairs.
1.3 Protections and Cautions—This practice provides guidance for developing actions and cautionary statements to be added to maintenance instructions for the protection of wire and wire configurations. Maintenance personnel will use these enhanced procedures to minimize contamination and accidental damage to electrical wiring interconnection system (EWIS) while working on aircraft.
1.4 “Protect and Clean As You Go” Philosophy—This philosophy is applied to aircraft wiring through inclusion in operators’ maintenance and training programs. This philosophy stresses the importance of protective measures when working on or around wire bundles and connectors. It stresses how important it is to protect EWIS during structural repairs, STC installations, or other alterations by making sure that metal shavings, debris, and contamination resulting from such work are removed.
1.5 This practice includes the following sections:
TitleSection Wire Selection5  General5.1  Aircraft Wire Materials5.2  Table of Acceptable Wires5.3  Severe Wind and Moisture Problems (SWAMP)5.4  Grounding and Bonding5.5  Electrical Wire Chart5.6 Wire and Cable Identification6  General6.1  Wire and Cable Identification6.2  Types of Markings6.3  Sleeve and Cable Marker Selection6.4  Placement of Identification Markings6.5 Wiring Installation7  General7.1  Wire Harness Installation7.2  Power Feeders7.3  Service Loops7.4  Drip Loops7.5  Soldering7.6  Strain Relief7.7  Grounding and Bonding7.8  Splicing7.9  Fuel Tank Wiring7.10  Corrosion Preventative Compounds (CPC)
(MIL-C-81309)7.11 Electrical Load Considerations8  General8.1  Methods for Determining the Current-Carrying
Capacity of Wires8.2  Acceptable Means of Monitoring and
Controlling the Electrical Load8.3 Electrical System Components9  General9.1  Alternators9.2  Generators9.3  Ground Power Units9.4  Auxiliary Power Units9.5  Batteries9.6  Circuit Protection Devices9.7  Conduit9.8  Connectors9.9  Inverters and Power Converters9.10  Junctions9.11  Junction Boxes9.12  Electronic Assemblies9.13  Relays9.14  Studs9.15  Switches9.16  Terminals and Terminal Blocks9.17  Waveguides9.18 Electrical System Component Installation10  General10.1  Alternators10.2  Generators10.3  Auxiliary Power Units (APUs)10.4  Batteries10.5  Circuit Protection Devices10.6  Conduit10.7  Connectors10.8  Inverters and Power Converters10.9  Junctions10.10  Junction Boxes, Panels, Shields, and
Microswitch Housings10.11  PC Board Assemblies10.12  Relays10.13  Studs10.14  Switches10.15  Te...

General Information

Status
Historical
Publication Date
31-Aug-2007
ICS
49.060 - Aerospace electric equipment and systems
Technical Committee
F39 - Aircraft Systems
Drafting Committee
F39.01 - Design, Alteration, and Certification of Electrical Systems
Current Stage
Ref Project

Relations

Replaces
ASTM F2639-07 - Standard Practice for Design, Alteration, and Certification of Airplane Electrical Wiring Systems
Effective Date
01-Sep-2007
Replaced By
ASTM F2639-15 - Standard Practice for Design, Alteration, and Certification of Aircraft Electrical Wiring Systems
Effective Date
01-Aug-2015
Referred By
ASTM F2799-14(2019) - Standard Practice for Maintenance of Aircraft Electrical Wiring Systems
Effective Date
01-Sep-2007
Referred By
ASTM F3231/F3231M-23 - Standard Specification for Electrical Systems for Aircraft with Combustion Engine Electrical Power Generation
Effective Date
01-Sep-2007
Referred By
ASTM F3316/F3316M-19 - Standard Specification for Electrical Systems for Aircraft with Electric or Hybrid-Electric Propulsion
Effective Date
01-Sep-2007
Referred By
ASTM F3060-20 - Standard Terminology for Aircraft
Effective Date
01-Sep-2007

Buy Standard

ASTM F2639-07e1 - Standard Practice for Design, Alteration, and Certification of Airplane Electrical Wiring SystemsASTM F2639-07e1 - Standard Practice for Design, Alteration, and Certification of Airplane Electrical Wiring Systems
PreviousNext
Standard
ASTM F2639-07e1 - Standard Practice for Design, Alteration, and Certification of Airplane Electrical Wiring Systems
English language
101 pages
sale 15% off
Preview
sale 15% off
Preview

Standards Content (Sample)

NOTICE: This standard has either been superseded and replaced by a new version or withdrawn.
Contact ASTM International (www.astm.org) for the latest information
´1
Designation:F2639 −07
StandardPractice for
Design, Alteration, and Certification of Airplane Electrical
1
Wiring Systems
This standard is issued under the fixed designation F2639; the number immediately following the designation indicates the year of
original adoption or, in the case of revision, the year of last revision.Anumber in parentheses indicates the year of last reapproval.A
superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
1
ε NOTE—Added 1.5 editorially in September 2012.
1. Scope
Title Section
Wire Selection 5
1.1 Definition—This practice defines acceptable practices
General 5.1
and processes for the design, alteration, and certification of Aircraft Wire Materials 5.2
Table of Acceptable Wires 5.3
electric systems and installations in general aviation aircraft.
Severe Wind and Moisture Problems (SWAMP) 5.4
This practice does not change or create any additional regula-
Grounding and Bonding 5.5
tory requirements nor does it authorize changes in or permit Electrical Wire Chart 5.6
Wire and Cable Identification 6
deviations from existing regulatory requirements.
General 6.1
Wire and Cable Identification 6.2
1.2 Applicability—The guidance provided in this practice is
Types of Markings 6.3
directed to air carriers, air operators, design approval holders,
Sleeve and Cable Marker Selection 6.4
Supplemental Type Certificate (STC) holders, maintenance
Placement of Identification Markings 6.5
Wiring Installation 7
providers, repair stations, and anyone performing field ap-
General 7.1
proval modifications or repairs.
Wire Harness Installation 7.2
Power Feeders 7.3
1.3 Protections and Cautions—This practice provides guid-
Service Loops 7.4
ance for developing actions and cautionary statements to be
Drip Loops 7.5
Soldering 7.6
added to maintenance instructions for the protection of wire
Strain Relief 7.7
and wire configurations. Maintenance personnel will use these
Grounding and Bonding 7.8
enhanced procedures to minimize contamination and acciden-
Splicing 7.9
Fuel Tank Wiring 7.10
tal damage to electrical wiring interconnection system (EWIS)
Corrosion Preventative Compounds (CPC) 7.11
while working on aircraft.
(MIL-C-81309)
Electrical Load Considerations 8
1.4 “Protect and Clean As You Go” Philosophy—This
General 8.1
philosophy is applied to aircraft wiring through inclusion in
Methods for Determining the Current-Carrying 8.2
operators’maintenanceandtrainingprograms.Thisphilosophy
Capacity of Wires
Acceptable Means of Monitoring and 8.3
stresses the importance of protective measures when working
Controlling the Electrical Load
on or around wire bundles and connectors. It stresses how
Electrical System Components 9
important it is to protect EWIS during structural repairs, STC
General 9.1
Alternators 9.2
installations, or other alterations by making sure that metal
Generators 9.3
shavings, debris, and contamination resulting from such work
Ground Power Units 9.4
are removed. Auxiliary Power Units 9.5
Batteries 9.6
1.5 This practice includes the following sections:
Circuit Protection Devices 9.7
Conduit 9.8
Connectors 9.9
1
Inverters and Power Converters 9.10
This practice is under the jurisdiction of ASTM Committee F39 on Aircraft
Junctions 9.11
Systems and is the direct responsibility of Subcommittee F39.01 on Design,
Junction Boxes 9.12
Alteration, and Certification of Electrical Systems.
Electronic Assemblies 9.13
Current edition approved Sept. 1, 2007. Published October 2007. DOI: 10.1520/
Relays 9.14
F2639-07E01.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1

---------------------- Page: 1 ----------------------
´1
F2639−07
3
2.3 ANSI Standards:
Studs 9.15
Switches 9.16
ANSI/EIA-5200000Generic Specification for Special-Use
Terminals and Terminal Blocks 9.17
Electromechanical Switches of Certified Quality
Waveguides 9.18
ANSI EIA/TIA-568-BCommercial Building Telecommuni-
Electrical System Component Installation 10
General 10.1
cations Cabling Standard
Alternators 10.2
ANSI J-STD-004Requirements for Soldering Fluxes
Generators 10.3
4
Auxiliary Power Units (APUs) 10.4
2.4 FAA Standards:
Batteries 10.5
Advisory Circular 20-53AProtection of Aircraft Fuel Sys-
Circuit Protection Devices 10.6
tems Against Fuel Vapor Ignition Due To Lightning
Conduit 10.7
Connectors 10.8
AC 20-136Protection of Aircraft Electrical/Electronic Sys-
Inverters and Power Converters 10.9
tems Against the Indirect Effects of Lightning
Junctions 10.10
AC 21-160ERTCA Document DO-160E
Junction Boxes, Panels, Shields, and 10.11
Microswitch Housings
AC 23.1309-1CEquipment, Systems, and Installations in
PC Board Assemblies 10.12
Part 23 Airplanes
Relays 10.13
AC 25-16Electrical Fault and Fire Prevention and Protec-
Studs 10.14
Switches 10.15
tion
Terminals and Terminal Block
...

Questions, Comments and Discussion

Ask us and Technical Secretary will try to provide an answer. You can facilitate discussion about the standard in here.

This May Also Interest You

ASTM
ASTM F2490-20(Guide)
Standard Guide for Aircraft Electrical Load and Power Source Capacity Analysis

SIGNIFICANCE AND USE
4.1 To show compliance with 14 CFR 23.1351, you must determine the electrical system capacity.  
4.2 14 CFR 23.1351(a)(2) states that:  
4.2.1 For normal, utility, and acrobatic category airplanes, by an electrical load analysis or by electrical measurements that account for the electrical loads applied to the electrical system in probable combinations and for probable durations; and  
4.2.2 For commuter category airplanes, by an electrical load analysis that accounts for the electrical loads applied to the electrical system in probable combinations and for probable durations.  
4.3 The primary purpose of the electrical load analysis (ELA) is to determine electrical system capacity (including generating sources, converters, contactors, bus bars, and so forth) needed to supply the worst-case combinations of electrical loads. This is achieved by evaluating the average demand and maximum demands under all applicable flight conditions. A summary can then be used to relate the ELA to the system capacity and can establish the adequacy of the power sources under normal, abnormal, and emergency conditions.
Note 1: The ELA should be maintained throughout the life of the aircraft to record changes to the electrical system, which may add or remove electrical loads to the system.  
4.4 The ELA that is produced for aircraft-type certification should be used as the baseline document for any subsequent changes. When possible, the basic format of the original ELA should be followed to ensure consistency in the methodology and approach.  
4.5 The original ELA may be lacking in certain information, for instance, time available on emergency battery. It may be necessary to update the ELA using the guidance material contained in this guide.
SCOPE
1.1 This guide covers how to prepare an electrical load analysis (ELA) to meet Federal Aviation Administration (FAA) requirements.  
1.2 This guide is intended to address aircraft level electrical load analysis. Electric propulsive power load analysis was not considered in the development of this guide.  
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.

  • Guide
    8 pages
    English language
    sale 15% off
  • Guide
    8 pages
    English language
    sale 15% off
ASTM
ASTM F2696-14(2019)(Practice)
Standard Practice for Inspection of Aircraft Electrical Wiring Systems

SIGNIFICANCE AND USE
4.1 The term “electrical system” as used in this practice means those parts of the aircraft that generate, distribute, and use electrical energy, including their support and attachments.  
4.2 The satisfactory performance of an aircraft is dependent upon the continued reliability of the electrical system.  
4.3 Damaged wiring or equipment in an aircraft, regardless of how minor it may appear to be, cannot be tolerated. It is, therefore, important that maintenance be accomplished using the best techniques and practices to minimize the possibility of failure.  
4.4 When inspecting and evaluating EWIS, improper wiring, routing, or repairs shall be corrected regardless of the origin of the error.  
4.5 This practice is not intended to supersede or replace any government specification or specific manufacturer’s instruction regarding electrical system inspection and repair
SCOPE
1.1 This practice covers basic inspection procedures for electrical wiring interconnect systems for aircraft electrical wiring systems.  
1.2 This practice is not intended to replace any instructions for continued airworthiness published by the aircraft or accessory manufacturer or type design holder.  
1.3 The values stated in inch-pound units are to be regarded as standard. The values given in parentheses are mathematical conversions to SI units that are provided for information only and are not considered 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.

  • Standard
    7 pages
    English language
    sale 15% off
ASTM
ASTM F2799-14(2019)(Practice)
Standard Practice for Maintenance of Aircraft Electrical Wiring Systems

SIGNIFICANCE AND USE
4.1 This practice is intended to be used as a standard wiring practice for aircraft when not contrary to standards published by the aircraft original equipment manufacturer (OEM) or regulations. This practice is intended to be used for maintenance and preventive maintenance of electrical wiring interconnection systems (EWIS).  
4.2 This practice is not intended to supersede or replace any government specification or specific manufacturer’s instructions regarding EWIS maintenance or repair.
SCOPE
1.1 Definition—This practice defines acceptable practices and processes for the maintenance, preventative maintenance, and repair of electric systems in general aviation aircraft. This practice does not change or create any additional regulatory requirements nor does it authorize changes in or permit deviations from existing regulatory requirements.  
1.2 Applicability—The guidance provided in this practice is directed to air carriers, air operators, maintenance providers, repair stations, and anyone performing maintenance or repairs.  
1.3 Protections and Warnings—This practice provides guidance to minimize contamination and accidental damage to electrical wiring interconnection systems (EWIS) while working on aircraft.  
1.4 “Protect and Clean As You Go” Philosophy—This philosophy is applied to aircraft wiring through inclusion in operators’ maintenance and training programs. This philosophy stresses the importance of protective measures when working on or around wire bundles and connectors. It stresses how important it is to protect EWIS during structural repairs, (STC) installations, or other alterations by ensuring that metal shavings, debris, and contamination resulting from such work are removed.  
1.5 Units—The values stated in inch-pound units are to be regarded as standard. The values given in parentheses are mathematical conversions to SI units that are provided for information only and are not considered standard.
Note 1: When SI units are required, refer to Annex 5 of ICAO.  
1.6 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.  
1.7 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.

  • Standard
    23 pages
    English language
    sale 15% off
ASTM
ASTM F2639-18(Practice)
Standard Practice for Design, Alteration, and Certification of Aircraft Electrical Wiring Systems

SIGNIFICANCE AND USE
4.1 Design—The design procedures defined in this practice are intended to provide acceptable guidance in the original design of electrical systems.  
4.2 Alteration—The alteration procedures defined in this practice are intended to provide acceptable guidance for modification of general aviation aircraft. Design of any modification shall follow the practices and processes defined in the design sections of this practice.  
4.3 Certification—Certification guidance provided in this practice is intended to provide generally accepted procedures and processes for certification of original and modified electrical systems and equipment. Requirements for certification shall be coordinated with the applicable National Aeronautics Association/Civil Aeronautics Administration (NAA/CAA) regulatory agency.
SCOPE
1.1 Definition—This practice defines acceptable practices and processes for the design, alteration, and certification of electric systems and installations in general aviation aircraft. This practice does not change or create any additional regulatory requirements nor does it authorize changes in or permit deviations from existing regulatory requirements.  
1.2 Applicability—The guidance provided in this practice is directed to air carriers, air operators, design approval holders, Supplemental Type Certificate (STC) holders, maintenance providers, repair stations, and anyone performing field approval modifications or repairs.  
1.3 Protections and Cautions—This practice provides guidance for developing actions and cautionary statements to be added to maintenance instructions for the protection of wire and wire configurations. Maintenance personnel will use these enhanced procedures to minimize contamination and accidental damage to electrical wiring interconnection system (EWIS) while working on aircraft.  
1.4 “Protect and Clean As You Go” Philosophy—This philosophy is applied to aircraft wiring through inclusion in operators’ maintenance and training programs. This philosophy stresses the importance of protective measures when working on or around wire bundles and connectors. It stresses how important it is to protect EWIS during structural repairs, STC installations, or other alterations by making sure that metal shavings, debris, and contamination resulting from such work are removed.  
1.5 This practice includes the following sections:    
Title  
Section  
Wire Selection  
5  
General  
5.1  
Aircraft Wire Materials  
5.2  
Table of Acceptable Wires  
5.3  
Severe Wind and Moisture Problems (SWAMP)  
5.4  
Grounding and Bonding  
5.5  
Electrical Wire Chart  
5.6  
Wire and Cable Identification  
6  
General  
6.1  
Wire and Cable Identification  
6.2  
Types of Markings  
6.3  
Sleeve and Cable Marker Selection  
6.4  
Placement of Identification Markings  
6.5  
Wiring Installation  
7  
General  
7.1  
Wire Harness Installation  
7.2  
Power Feeders  
7.3  
Service Loops  
7.4  
Drip Loops  
7.5  
Soldering  
7.6  
Strain Relief  
7.7  
Grounding and Bonding  
7.8  
Splicing  
7.9  
Fuel Tank Wiring  
7.10  
Corrosion Preventative Compounds (CPC)
(MIL-C-81309)  
7.11  
Electrical Load Considerations  
8  
General  
8.1  
Methods for Determining the Current-Carrying
Capacity of Wires  
8.2  
Acceptable Means of Monitoring and
Controlling the Electrical Load  
8.3  
Electrical System Components  
9  
General  
9.1  
Alternators  
9.2  
Generators  
9.3  
Ground Power Units  
9.4  
Auxiliary Power Units  
9.5  
Batteries  
9.6  
Circuit Protection Devices  
9.7  
Conduit  
9.8  
Connectors  
9.9  
Inverters and Power Converters  
9.10  
Junctions  
9.11  
Junction Boxes  
9.12  
Electronic Assemblies  
9.13  
Relays  
9.14  
Studs  
9.15  
Switches  
9.16  
Terminals and Terminal Blocks  
9.17 ...

  • Standard
    101 pages
    English language
    sale 15% off
  • Standard
    101 pages
    English language
    sale 15% off
ASTM
ASTM F3239-22a(Specification)
Standard Specification for Aircraft Electric Propulsion Systems

SCOPE
1.1 This specification addresses airworthiness requirements for the design and installation of electric propulsion systems for aeroplanes. Hybrid-electric propulsion systems are addressed implicitly unless explicitly stated otherwise. This specification was written with the focus on electric propulsion systems with conventional system layout, propulsion characteristics, and operation. 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 CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this standard (in 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). Annex A1 maps the Means of Compliance described in this specification to EASA CS-23, amendment 5, or later, and FAA 14 CFR Part 23, amendment 64, or later.  
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.

  • Technical specification
    9 pages
    English language
    sale 15% off
  • Technical specification
    9 pages
    English language
    sale 15% off
ASTM
ASTM F2490-20(Guide)
Standard Guide for Aircraft Electrical Load and Power Source Capacity Analysis

SIGNIFICANCE AND USE
4.1 To show compliance with 14 CFR 23.1351, you must determine the electrical system capacity.  
4.2 14 CFR 23.1351(a)(2) states that:  
4.2.1 For normal, utility, and acrobatic category airplanes, by an electrical load analysis or by electrical measurements that account for the electrical loads applied to the electrical system in probable combinations and for probable durations; and  
4.2.2 For commuter category airplanes, by an electrical load analysis that accounts for the electrical loads applied to the electrical system in probable combinations and for probable durations.  
4.3 The primary purpose of the electrical load analysis (ELA) is to determine electrical system capacity (including generating sources, converters, contactors, bus bars, and so forth) needed to supply the worst-case combinations of electrical loads. This is achieved by evaluating the average demand and maximum demands under all applicable flight conditions. A summary can then be used to relate the ELA to the system capacity and can establish the adequacy of the power sources under normal, abnormal, and emergency conditions.
Note 1: The ELA should be maintained throughout the life of the aircraft to record changes to the electrical system, which may add or remove electrical loads to the system.  
4.4 The ELA that is produced for aircraft-type certification should be used as the baseline document for any subsequent changes. When possible, the basic format of the original ELA should be followed to ensure consistency in the methodology and approach.  
4.5 The original ELA may be lacking in certain information, for instance, time available on emergency battery. It may be necessary to update the ELA using the guidance material contained in this guide.
SCOPE
1.1 This guide covers how to prepare an electrical load analysis (ELA) to meet Federal Aviation Administration (FAA) requirements.  
1.2 This guide is intended to address aircraft level electrical load analysis. Electric propulsive power load analysis was not considered in the development of this guide.  
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.

  • Guide
    8 pages
    English language
    sale 15% off
  • Guide
    8 pages
    English language
    sale 15% off
ASTM
ASTM F3425-20(Guide)
Standard Guide for Aircraft Electronics Installation Technician Certification

SIGNIFICANCE AND USE
4.1 The guide is intended to be used to assess competencies of qualified individuals who wish to become certified as an aircraft electronics installation technician through a program such as the National Center for Aerospace and Transportation Technologies (NCATT).  
4.2 The guide is intended to be used in concert with a certification provider’s structure and materials for management, exam delivery, and candidate preparation.
SCOPE
1.1 The purpose of this guide is to address the fundamental subject knowledge activities and functions for avionics professionals to be titled Aircraft Electronics Installation Technicians (AEIT).  
1.2 This guide is the basis for the Aircraft Electronics Installation Technician (AEIT) certification, an endorsement to the Aircraft Electronics Technician (AET) certification. Candidates must be a certified AET to take the certification exam associated with this guide.  
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.

  • Guide
    5 pages
    English language
    sale 15% off
ASTM
ASTM F2339-19a(Practice)
Standard Practice for Design and Manufacture of Reciprocating Spark Ignition Engines for Light Sport Aircraft

SIGNIFICANCE AND USE
3.1 This practice provides designers and manufacturers of engines for light sport aircraft design references and criteria to use in designing and manufacturing engines.  
3.2 Declaration of compliance is based on testing and documentation during the design and testing or flight testing of the engine type by the manufacturer or under the manufacturers' guidance.
SCOPE
1.1 This practice covers minimum requirements for the design and manufacture of reciprocating spark ignition engines for light sport aircraft, VFR use.  
1.2 The values stated in inch-pound 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.

  • Standard
    4 pages
    English language
    sale 15% off
  • Standard
    4 pages
    English language
    sale 15% off
ASTM
ASTM F3316/F3316M-19(Specification)
Standard Specification for Electrical Systems for Aircraft with Electric or Hybrid-Electric Propulsion

ABSTRACT
This specification applies to the electrical systems, electrical equipment, and electrical power distribution aspects of airworthiness and design for aircraft with electric or hybrid-electric propulsion. Developed through open consensus of international experts in general aviation, this material focused on Normal Category Airplanes. The content may be more broadly applicable; it is the responsibility of the applicant to substantiate broader applicability as a specific means of compliance.
This specification establishes the Aircraft Type Code (ATC) compliance matrix based on certification level, number of engines, type of engine(s), stall speed, cruise speed, meteorological conditions, altitude, and maneuvers. An ATC is defined by taking into account both the technical considerations regarding the design of the aircraft and the airworthiness level established based upon risk-based criteria. Requirements for electrical systems for electric propulsion cover power source capacity and distribution, electrical systems and equipment, circuit protective devices, master switch arrangement, switches, electrical cables and equipment, electrical system fire protection, electronic equipment, and storage battery design and installation.
SCOPE
1.1 This specification covers the electrical systems, electrical equipment, and electrical power distribution aspects of airworthiness and design for aircraft with Electric or Hybrid-Electric Propulsion. This specification was written with the focus on electric propulsion systems with conventional system layout, characteristics, and operation. This specification does not address all of the requirements that may be necessary for possible hybrid-electric configurations where an EPU and a combustion engine are used in combination to provide propulsion. The use of this specification combined with the applicable portions of Specification F3231/F3231M may be necessary for hybrid-electric configurations. This material was developed through open consensus of international experts in general aviation. This material was created by focusing on 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 a means of compliance for design approval shall seek guidance from their respective oversight authority (for example, published guidance from applicable CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this standard (in whole or in part) as a Means of Compliance to their regulatory requirements (Hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMMITTEE/F44.htm).  
1.3 Units—This standard may present information in either SI units, English Engineering units, or both. The values stated in each system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used independently of the other, and values from the two systems shall not be combined.  
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.

  • Technical specification
    7 pages
    English language
    sale 15% off
  • Technical specification
    7 pages
    English language
    sale 15% off
ASTM
ASTM F319-19(Practice)
Standard Practice for Polarized Light Detection of Flaws in Aerospace Transparency Heating Elements

SIGNIFICANCE AND USE
4.1 This practice is useful as a screening basis for acceptance or rejection of transparencies during manufacturing so that units with identifiable flaws will not be carried to final inspection for rejection at that time.  
4.2 This practice may also be employed as a go-no go technique for acceptance or rejection of the finished product.  
4.3 This practice is simple, inexpensive, and effective. Flaws identified by this practice, as with other optical methods, are limited to those that produce temperature gradients when electrically powered. Any other type of flaw, such as minor scratches parallel to the direction of electrical flow, are not detectable.
SCOPE
1.1 This practice covers a standard procedure for detecting flaws in the conductive coating (heater element) by the observation of polarized light patterns.  
1.2 This practice applies to coatings on surfaces of monolithic transparencies as well as to coatings imbedded in laminated structures.  
1.3 The values stated in SI units are to be regarded as standard. No other units of measurement are included in this 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. For specific precautionary statements, see Section 6.  
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.

  • Standard
    4 pages
    English language
    sale 15% off
  • Standard
    4 pages
    English language
    sale 15% off