This content is not included in your SAE MOBILUS subscription, or you are not logged in.
Aircraft Precipitation Static Certification
- Aerospace Standard
Published April 13, 2016 by SAE International in United States
Downloadable datasets availableAnnotation ability available
Aircraft surface precipitation static (p-static) charge can be generated when aircraft fly through ice particles, rain, snow and dust. However, in the context of p-static protection, this document is used for providing guidance for any thing that charges the outer surface of the aircraft (e.g. engine exhaust). P-static discharges from the aircraft can disrupt aircraft communication, navigation, and surveillance radios, and can damage aircraft radomes and windshields. This SAE Aerospace Recommended Practice (ARP) defines design considerations for aircraft p-static control and related methods to verify acceptable aircraft p-static performance. This ARP addresses p-static charging due to the aircraft flying through ice particles, rain, snow and dust. It does not address other triboelectric charging that may be present in an aircraft, such as triboelectric fuel charging or environmental control system or air conditioning static charging. It does not address electrostatic charging created by passengers or crewmembers, or electrostatic discharge hazards to electronics and systems.
The purpose of this document is to provide information and guidance concerning an acceptable means, but not the only means, of compliance with Parts 23, 25, 27, and 29 (23.867, 25.899, 27.610, and 29.610) of the Federal Aviation Regulations (FAR) and European Aviation Safety Agency (EASA), applicable to aircraft for protection against the adverse effects of precipitations static. This ARP provides general information on aircraft surface p-static charging mechanisms and the impact p-static has on aircraft systems. It addresses elements of effective aircraft p-static control design. Finally, it defines methods for verifying acceptable aircraft p-static control. Accordingly, this material is neither mandatory nor regulatory in nature and does not constitute a regulation.
Aircraft p-static control should be addressed early in the aircraft design to be effective. Effective aircraft design features and effective verification methods will result in an aircraft that can be operated in p-static charging conditions without adverse impact to the aircraft systems.
The existing reports and guidance do not provide standards for aircraft design to control p-static or standard methods to verify acceptable aircraft p-static control. This document provides acceptable approaches to design effective aircraft p-static control, and provides acceptable methods to verify the design effectiveness.
Existing aircraft certification regulations in Title 14 CFR 25.899, 27.610(d) and 29.610(d), specifically address aircraft p-static control. These regulations include the requirement to minimize the accumulation of electrostatic charge in order to reduce to an acceptable level the effects of static electricity on the functioning of essential electrical and electronic equipment. Compliance may be shown by bonding the components to the airframe, or incorporating other acceptable means to dissipate the static charge. Title 14 CFR 23 is an exception, as it does not specifically address aircraft p-static control, however p-static is considered a foreseeable operating condition, so all aircraft designed for operation in instrument meteorological conditions (IMC) should have certified p-static control. Prior to this document, the absence of specific standards or guidance material resulted in inconsistent application and verification of the requirements for aircraft p-static control.
ARP5672 has been reaffirmed to comply with the SAE five-year review policy.
Data Sets - Support Documents
|[Unnamed Dataset 1]|
|[Unnamed Dataset 2]|
|TABLE 1||PRECIPITATION PARTICLE PARAMETERS FOR SUBSONIC AIRCRAFT|
|TABLE 2||ELECTROSTATIC DISCHARGE TYPES AND PREVENTION|
|TABLE 3||STATIC DISCHARGER COMPLEMENT|
|TABLE 4||STATIC DISCHARGER CHARACTERISTICS (FROM MIL-STD-9129E)|
SAE AE-2 LIGHTNING COMMITTEE It is the duty of the AE-2 committee to produce advisory materials for the aerospace community in the following areas:The natural lightning environment and related environment standards Protection of aerospace vehicles from the effects of lightning and other atmospheric electrical environments. Means of verifying the adequacy of protection measures. Standardized and other atmospheric electrical environments for lightning simulation and test methods.
|AC23.1309-1C||This document is not part of the subscrption.|
|AC25.1309-1A||This document is not part of the subscrption.|
|AC25.899-1||This document is not part of the subscrption.|
|AC27.1B||This document is not part of the subscrption.|
|AC29.2C||This document is not part of the subscrption.|
|ARP1870A||Aerospace Systems Electrical Bonding and Grounding for Electromagnetic Compatibility and Safety|
|MIL-DTL-9129||This document is not part of the subscrption.|
|MIL-STD-464||This document is not part of the subscrption.|