Browse Topic: Lightning protection
This SAE Aerospace Information Report (AIR) describes the aspects of hydraulic system design and installation to minimize the effects of lightning. Techniques for effective electrical bonding, hydraulic system lightning protection, and lightning protection verification techniques are discussed
This SAE Aerospace Standard (AS) provides general design and test requirements for a flat cut-off pressure compensated, variable delivery hydraulic pump for use in a civil aircraft hydraulic system with a rated system pressure up to 5000 psi (34500 kPa). NOTE: Hydraulic pumps may incorporate features such as a clutch in the input drive, which will not be covered by this standard
This SAE Aerospace Information Report (AIR) is limited to the subject of aircraft fuel systems and the questions concerning the requirements for electrical bonding of the various components of the system as related to Static Electric Charges, Fault Current, Electromagnetic Interference (EMI) and Lightning Strikes (Direct and Indirect Effects). This AIR contains engineering guidelines for the design, installation, testing (measurement) and inspection of electrical bonds
This ARP provides detailed information, guidance, and methods in support of the Federal Aviation Administration (FAA) Advisory Circular (AC) 20-136. AC 20-136 provides a means, but not the only means, for demonstrating compliance with Title 14 of the Code of Federal Regulations (14 CFR) 23.1306 (Amendment 23-61), 23.2515 (Amendment 23-64), 25.1316, 27.1316, and 29.1316. It is also intended for this ARP to provide the same information, guidance, and methods, to the European Aviation Safety Agency (EASA) certification specifications CS 23.1306 (Amendment 23/4), 23.2515 (Amendment 23/5), 25.1316, 27.1316, and 29.1316, and associated Acceptable Means of Compliance (AMC) 20-136. This ARP provides references relevant to identifying: (1) acceptance criteria for the indirect effects of lightning compliance approaches, (2) verification (analysis and test) methods including those associated with multiple stroke and multiple burst, (3) recommended design options to optimize needed system immunity
This SAE Aerospace Recommended Practice (ARP) defines lightning strike zones and provides guidelines for locating them on particular aircraft, together with examples. The zone definitions and location guidelines described herein are applicable to Parts 23, 25, 27, and 29 aircraft. The zone location guidelines and examples are representative of in-flight lightning exposures
This SAE Aerospace Standard (AS) defines the requirements for a threadless, flexible, self-bonding coupling assembly which, when installed on machined fixed-cavity ferrules, provides a flexible connection for joining tubing and components in aircraft fuel, vent, or other systems. This assembled coupling, hereafter referred to as the assembly, is designed for use from -65 to +400 °F and at 125 psig nominal operating pressure. AS1650 was not designed for the new certification requirements for flammable leakage zones and fuel tanks for lightning protection and assembly redundancy. As such, their use and installation may require additional efforts and equipment to support new FAA CFR compliance. The AS7510 flexible coupling should be the preferred coupling for use in flammable leakage zones and fuel tanks that require service life and functionality for lightning protection and part redundancy
This specification covers the general design, testing, and safety requirements for aircraft tank mounted fuel booster pumps used for engine fuel feed, transfer, and jettison
This SAE Aerospace Standard (AS) defines the requirements for a threadless, flexible, self-bonding coupling assembly which, when installed on machined fixed cavity ferrules, provides a flexible connection for joining tubing and components in aircraft fuel, vent or other systems. This assembled coupling, hereafter referred to as the assembly, and is designed for use from −65 to +400 °F and at 125 psig nominal operating pressure. AS1650 was not designed for the new certification requirements for flammable leakage zones and fuel tanks for lightning protection and assembly redundancy. As such their use and installation may require additional efforts and equipment to support new FAA CFR compliance. The AS7510 flexible coupling should be the preferred coupling for use in flammable leakage zones and fuel tanks that require service life and functionality for lightning protection and part redundancy
This SAE Aerospace Recommended Practice (ARP) provides technical design and application information related to the generation, distribution, control, and utilization of aircraft 270 V DC electrical power systems and support equipment. This document also provides references and definitions to permit comparisons of various electrical systems and components
This document establishes techniques for validating that an Aircraft Station Interface (ASI) complies with the interface requirements delineated in MIL-STD-1760B Notice 3. For validation of aircraft designed to MIL-STD-1760A Notice 2 AS4764 Issued 1995-04 applies
This document establishes techniques for validating that a mission store complies with the interface requirements delineated in MIL-STD-1760
This document establishes techniques for validating that an aircraft station complies with the interface requirements delineated in MIL-STD-1760
This aerospace specification defines the requirements for a threadless, flexible, conductive, self-bonding coupling assembly which, when installed on fixed cavity ferrules, provides a flexible, current carrying connection for joining tubing and components in aircraft fuel, vent and other systems. The assembled coupling is designed to provide interchangeability of parts and components between qualified manufacturers for the service life of the aircraft system. The assembled coupling is for use from -65 to +200 °F at nominal operating pressures (125 psig for -08 through -64 and 30 psig for -72 through -88). This aerospace specification is a departure from prior qualification practices for assembled couplings. Prior practice sought to validate this type of assembled coupling design by conducting a sequence of tests on sets of coupling assemblies. There were multiple test sequences and each was conducted on a different set of coupling assemblies. Each of these test sequences challenged a
This specification covers flexible couplings for joining tubing with AS5131 Type A beaded ends for use in aircraft fuel and vent systems (see 6.1
This SAE Aerospace Standard (AS) establishes the general requirements for the design, construction, acceptance and qualification testing of flat cut-off pressure compensated, variable delivery hydraulic pumps, used in civil aircraft hydraulic systems. It also provides parameters for a Procurement Specification to be used in conjunction with this AS for each pump. NOTE: Hydraulic pumps may incorporate features such as a clutch in the input drive, which will not be covered by this standard
This SAE Aerospace Recommended Practice (ARP) covers the requirements for a Stationary Runway Weather Information System (referred to as the system) to monitor the surface conditions of airfield operational areas to ensure safer ground operations of aircraft. The system provides (1) temperature and condition information of runway, taxiway, and ramp pavements and (2) atmospheric weather conditions that assist airport personnel to maintain safer and more efficient airport operations. The system can be either a wired system or a wireless system
This SAE Aerospace Information Report (AIR) describes hydraulic system design and installation to minimize the effects of lightning, especially when the aircraft structure is composite. Techniques for effective electrical bonding, hydraulic system lightning protection, and lightning protection verification techniques are discussed
The purpose of this specification is to allow procurement of a defined material corresponding to the statistically derived material properties published in CMH-17 Volume II
This specification establishes the requirements for a nominal 250 °F cure epoxy preimpregnated 7781 glass fabric. The prepreg has a nominal fiber areal weight of 294 gsm, and nominal resin content of 38
This specification covers flexible couplings for joining tubing with AS5131 Type A beaded ends for use in aircraft fuel and vent systems (see 6.1
Since the 1960's, lightning protection of aircraft has been an important design aspect, a concern for the flying public, aircraft manufacturers and the Federal Aviation Administration (FAA). With the implementation of major aircraft structures fabricated from carbon fiber reinforced plastic (CFRP) materials, lightning protection has become a more complicated issue to solve. One widely used material for lightning strike protection of CFRP structures within the aerospace industry is expanded metal foil (EMF). EMF is currently used in both military and commercial passenger aircraft. An issue that has historically been an area of concern with EMF is micro cracking of paint on the composite structure which can result in corrosion of the metal foil and subsequent loss of conductivity. This paper addresses the issues of stress and displacement in the composite structure layup which contribute to paint cracking caused by aircraft thermal cycling. The analysis of EMF by computer modeling is
This specification covers the general requirements for the installation and test of electronic equipment in piloted aircraft
This SAE Aerospace Recommended Practice (ARP) covers the requirements for a Stationary Runway Weather Information System (referred to as the system) to monitor the surface conditions of airfield operational areas to ensure safer ground operations of aircraft. The system provides (1) temperature and condition information of runway, taxiway, and ramp pavements and (2) atmospheric weather conditions that assist airport personnel to maintain safer and more efficient airport operations. The system can be either a wired system or a wireless system
This SAE Aerospace Information Report (AIR) identifies and summarizes the various factors that should be considered during design, development, certification, or testing of helicopter rotor blade ice protection systems. Although various concepts of ice protection are mentioned in this report, the text is limited generally to those factors associated with design and substantiation of cyclic electrothermal ice protection systems as applicable to the protection of helicopter rotor blades. Other systems are described briefly in Appendix A. Applications consider main rotor blades, conventional tail rotor blades, and other types of antitorque devices. The information contained in this report is also limited to the identification of factors that should be considered and why the factor is important. Specific design, analysis and test methodologies are not included. For additional information refer to the references listed in 2.1
This SAE Aerospace Recommended Practice (ARP) establishes overall system electromagnetic compatibility (EMC) control requirements. EMC includes the following: a Electromagnetic Environmental Effects (E3) b Electrostatic Discharge (ESD) c Electromagnetic Interference (EMI) d Electromagnetic Vulnerability (EMV) e Electromagnetic Pulse (EMP) f Hazards of Electromagnetic Radiation to Ordnance (HERO) g Hazards of Electromagnetic Radiation to Personnel (HERP) h Hazards of Electromagnetic Radiation to Fuels (HERF) i High Intensity Radiated Fields (HIRF) j Lightning Protection k Static Electricity I TEMPEST This document is intended to be used for the procurement of land, sea, air, or space systems by any procurement activity. Tailoring of specific requirements is necessary and Appendix A has been provided for guidance
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
This aerospace specification defines the requirements for a threadless, flexible, conductive, self-bonding coupling assembly which, when installed on fixed cavity ferrules, provides a flexible, current carrying connection for joining tubing and components in aircraft fuel, vent and other systems. The assembled coupling is designed to provide interchangeability of parts and components between qualified manufacturers for the service life of the aircraft system. The assembled coupling is for use from -65 to +200 °F at nominal operating pressures (125 psig for -08 through -64 and 30 psig for -72 through -88). This aerospace specification is a departure from prior qualification practices for assembled couplings. Prior practice sought to validate this type of assembled coupling design by conducting a sequence of tests on sets of coupling assemblies. There were multiple test sequences and each was conducted on a different set of coupling assemblies. Each of these test sequences challenged a
This document is one of a set covering the whole spectrum of aircraft interaction with lightning. This document is intended to describe how to conduct lightning direct effects tests and indirect system upset effects tests. Indirect effects upset and damage tolerance tests for individual equipment items are addressed in DO-160/ED-14. Documents relating to other aspects of the certification process, including definition of the lightning environment, zoning, and indirect effects certification are listed in Section 2. This document presents test techniques for simulated lightning testing of aircraft and the associated systems. This document does not include design criteria nor does it specify which items should or should not be tested. Acceptable levels of damage and/or pass/fail criteria for the qualification tests must be approved by the cognizant certification authority for each particular case. When lightning tests are a part of a certification plan, the test methods described herein
This SAE Aerospace Recommended Practice (ARP) defines lightning strike zones and provides guidelines for locating them on particular aircraft, together with examples. The zone definitions and location guidelines described herein are applicable to Parts 23, 25, 27, and 29 aircraft. The zone location guidelines and examples are representative of in-flight lightning exposures
Highvoltage.dk is a Danish consulting engineering firm with expertise in lightning protection and high-voltage engineering. The company, founded in 2005, tackles complex problems such as general high-voltage design engineering for the power industry, lightning protection concepts and findings for wind turbines, and high-voltage material tests. The engineers at Highvoltage.dk are experienced users of numerical analysis tools to simulate magnetic and electric fields, current distribution, and lightning attachment points
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