SAE ARP5412B
Superseded
A superseded Standard is one, which is fully replaced by another Standard, which is a new edition of the same Standard.
View Superseded by
Aircraft Lightning Environment and Related Test Waveforms
Hardcopy , PDF
17-10-2024
English
11-01-2013
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
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Pages |
63
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PublisherName |
SAE International
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Status |
Superseded
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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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