F39.01 - Design, Alteration, and Certification of Electrical Systems

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.

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 ...

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 ...

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 The values given in SI units are to be regarded as the 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 and health practices and determine the applicability of regulatory limitations prior to use.

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...

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 CautionsThis 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 Values - The values given in inch-pound units are to be regarded as the standard. The values in parentheses are for information only. See Appendix X2 for SI-based prefixes and powers of 10.Note 1
Where SI units are required, refer to Annex 5 of ICAO.
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 and health practices and determine the applicability of regulatory limitations prior to use.

SCOPE
1.1 This guide covers how to prepare an electrical load analysis (ELA) to meet Federal Aviation Administration (FAA) requirements.
1.2 The values given in SI units are to be regarded as the 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 and health practices and determine the applicability of regulatory limitations prior to use.

SIGNIFICANCE AND USE
To show compliance with 14 CFR 23.1351, you must determine the electrical system capacity.
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.
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.
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.
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 The values given in SI units are to be regarded as the standard.
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 and health practices and determine the applicability of regulatory limitations prior to use.