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SAE ARP5412B

Superseded

Superseded

A superseded Standard is one, which is fully replaced by another Standard, which is a new edition of the same Standard.

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Aircraft Lightning Environment and Related Test Waveforms

Available format(s)

Hardcopy , PDF

Superseded date

17-10-2024

Superseded by

SAE ARP5412C

Language(s)

English

Published date

11-01-2013

€164.75
Excluding VAT

1. SCOPE
2. REFERENCES
3. BACKGROUND
4. NATURAL LIGHTNING DESCRIPTION
5. LIGHTNING INTERACTIONS WITH AIRCRAFT
6. IDEALIZED STANDARD EXTERNAL LIGHTNING ENVIRONMENT
7. IDEALIZED STANDARD INDUCED TRANSIENT WAVEFORMS
8. SUMMARY OF WAVEFORMS/WAVEFORM SETS
9. NOTES
APPENDIX A - MEASURED LIGHTNING PARAMETER DATA

The environment and test waveforms defined in this SAE Aerospace Recommended Practice (ARP) account for the best lightning data and analysis currently available.

DocumentType
Standard
Pages
63
PublisherName
SAE International
Status
Superseded
SupersededBy
Supersedes

The environment and test waveforms defined in this SAE Aerospace Recommended Practice (ARP) account for the best lightning data and analysis currently available. The quantified environment and levels herein represent the minimum currently required by certifying authorities, consistent with the approach applied in related lightning documents.Lightning, like other weather phenomenon, is probabilistic in nature. Levels and waveforms vary considerably from one flash to the next. Within this document, standardized voltage and current waveforms have been derived to represent the lightning environment external to an aircraft. These standardized waveforms are used to assess the effects of lightning on aircraft. The standardized external current waveforms have in turn been used to derive standardized transient voltage and current test waveforms that can be expected to appear on cable bundles and at equipment interfaces within an aircraft. When deriving these latter internal induced test waveforms, considerations such as testability and important waveform characteristics that can demonstrate lightning design effectiveness, have been taken into account.The parameters of the standardized waveforms, both external and derived internal induced transients, represent severe versions of each of the characteristics of natural lightning flashes and include all parameters of interest with respect to lightning protection for aircraft. These standardized waveforms are thus referred to as idealized standard lightning environment waveforms, idealized standard waveforms, or just idealized waveforms within this document. The waveforms associated with the external environment are termed, the idealized standard external lightning environment. The waveforms associated with the internal induced environment are termed the idealized standard induced transient waveforms.In every case more severe versions of each of the individual characteristics of the idealized standard external lightning environment waveforms have been recorded in natural lightning flashes. The more severe individual characteristics of the idealized standard external lightning environment waveforms have never been recorded together within a single lightning flash. Therefore the parameters combined in the idealized standard lightning environment waveforms provided in this document represent a very severe environment.The waveforms provided in this ARP are considered to be adequate for the demonstration of compliance for the protection of an aircraft and its systems against the lightning environment and should be applied in accordance with the aircraft lightning strike zones (see ARP5414) and test methods (see ARP5416), and applicable FAA and EASA advisory and interpretive material.

FAA AC 20-155 : 2013 INDUSTRY DOCUMENTS TO SUPPORT AIRCRAFT LIGHTNING PROTECTION CERTIFICATION
BS ISO 14302:2002 Aerospace series. Space systems. Electromagnetic compatibility requirements
SAE AS6116A Aluminum Fittings, Axially Swaged Tube with Flareless Separable, Fluid System Up to 1500 psi (10340 kPa) Maximum, Specification for
SAE ARP5416A Aircraft Lightning Test Methods
SAE ARP5414A Aircraft Lightning Zone
SAE AIR 6464 : 2013 EUROCAE/SAE WG80/AE-7AFC HYDROGEN FUEL CELLS AIRCRAFT FUEL CELL SAFETY GUIDELINES
MIL-STD-461 Revision G:2015 REQUIREMENTS FOR THE CONTROL OF ELECTROMAGNETIC INTERFERENCE CHARACTERISTICS OF SUBSYSTEMS AND EQUIPMENT
FAA AC 25-11 : 2014 ELECTRONIC FLIGHT DISPLAYS
SAE AIR5691A Guidance for the Design and Installation of Fuel Quantity Indicating Systems
SAE AS5958F Fittings, Axially Swaged Tube with Flareless Separable, Fluid System for Operating Pressures up to and Including 5080 psi (35000 kPa), Specification for
S.R. CWA 17044:2016 AEROSPACE SERIES - MODULES FOR ELECTRO-MECHANICAL ACTUATORS IN AIRCRAFT
NASA STD 4003 : 2013 ELECTRICAL BONDING FOR NASA LAUNCH VEHICLES, SPACECRAFT, PAYLOADS, AND FLIGHT EQUIPMENT
SAE AS5830A Coupling Assembly, Threadless, Flexible, Fixed Cavity, Current Carrying, Self-Bonding, Procurement Specification
MIL-HDBK-516 Revision C:2014 AIRWORTHINESS CERTIFICATION CRITERIA
MIL-STD-464 Revision C:2010 ELECTROMAGNETIC ENVIRONMENTAL EFFECTS REQUIREMENTS FOR SYSTEMS
14/30310862 DC : 0 BS EN 4832 - AEROSPACE SERIES - ADAPTOR, PIPE COUPLING 24 DEGREES CONE UP TO 35000 KPA (5080 PSI) RING-LOCKED FITTING AND RING-LOCKED FITTING-REDUCER - INCH SERIES - TECHNICAL SPECIFICATION
SAE AIR6185 Aerospace - Lightning Effects on Hydraulic Transport Elements on Aircraft
SAE AIR 5774 : 2012 COMPOSITE FUEL TANKS, FUEL SYSTEM DESIGN CONSIDERATIONS
SAE AS7510 Coupling Assembly, Threadless, Flexible, Self-Locking, Fixed Cavity, High Conductivity, Self-Bonding, Part Specification
NASA JSC 08080-2 : 2015 JSC DESIGN AND PROCEDURAL STANDARDS
AEP-41 VOL 1 : 2004 UNIFIED ELECTROMAGNETIC ENVIRONMENTAL EFFECTS (UE[3]) PROTECTION, PHILOSOPHY AND METHODOLOGY
SAE AIR1184B : 2016 CAPACITIVE FUEL GAUGING SYSTEM ACCURACIES
SAE AS5000C Fitting, Plug-in Union, Ring Locked, 24 Degree Cone, Fluid Connection, 5080 psi (35 000 kPa), Specification for
FAA AC 20-136 : 2011 AIRCRAFT ELECTRICAL AND ELECTRONIC SYSTEM LIGHTNING PROTECTION
ISO 14302:2002 Space systems Electromagnetic compatibility requirements
09/30190333 DC : 0 BS EN 61400-24 - WIND TURBINES - PART 24: LIGHTNING PROTECTION
API 545 : 2009 RECOMMENDED PRACTICE FOR LIGHTNING PROTECTION OF ABOVEGROUND STORAGE TANKS FOR FLAMMABLE OR COMBUSTIBLE LIQUIDS
SAE ARP5415A User\'s Manual for Certification of Aircraft Electrical/Electronic Systems for the Indirect Effects of Lightning
SAE AIR 4004 : 2015 GUIDE FOR INSTALLATION OF ELECTRICAL WIRE AND CABLE ON AIRCRAFT LANDING GEAR

FAA AC 27-1 : 2008 CERTIFICATION OF NORMAL CATEGORY ROTORCRAFT
FAA AC 21-16 : 2011 RTCA DOCUMENT DO-160 VERSIONS D, E, F, AND G, "ENVIRONMENTAL CONDITIONS AND TEST PROCEDURES FOR AIRBORNE EQUIPMENT"
FAA AC 20-53 : 2006 PROTECTION OF AIRCRAFT FUEL SYSTEMS AGAINST FUEL VAPOR IGNITION CAUSED BY LIGHTNING
FAA AC 20-136 : 2011 AIRCRAFT ELECTRICAL AND ELECTRONIC SYSTEM LIGHTNING PROTECTION
SAE ARP 5415 : 2002 USER'S MANUAL FOR CERTIFICATION OF AIRCRAFT ELECTRICAL/ELECTRONIC SYSTEMS FOR THE INDIRECT EFFECTS OF LIGHTNING
FAA AC 23.1309-1 : 2011 SYSTEM SAFETY ANALYSIS AND ASSESSMENT FOR PART 23 AIRPLANES
SAE ARP5416A Aircraft Lightning Test Methods
FAA AC 29-2 : 2008 CERTIFICATION OF TRANSPORT CATEGORY ROTORCRAFT
FAA AC 20-155 : 2013 INDUSTRY DOCUMENTS TO SUPPORT AIRCRAFT LIGHTNING PROTECTION CERTIFICATION
FAA AC 25.1309-1 : 0 SYSTEM DESIGN AND ANALYSIS
SAE ARP5414A Aircraft Lightning Zone

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