Browse Topic: Fixed-wing aircraft

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LED Landing, Taxiing, Runway Turnoff, and Recognition LightsARP6402B (Current)11/26/2025
This document includes recommendations of installations of adequate landing and taxiing lighting systems in aircraft of the following categories: a. Single engine personal and/or liaison type b. Light twin engine c. Large multiengine propeller d. Large multiengine turbojet e. Military high performance fighter and attack f. Helicopter which are subject to the following CFR Parts certification: Part 23 – Airworthiness Standards: Normal, Utility, Acrobatic and Commuter Aircrafts Part 25 – Airworthiness Standards: Transport Category Aircrafts Part 27 – Airworthiness Standards: Normal Category Rotorcraft Part 29 – Airworthiness Standards: Transport Category Rotorcraft
A-20B Exterior Lighting Committee
Environment Spectra and Corrosivity Monitoring Using Electrochemical and Electrical Resistance SensorsAIR6970 (Current)11/26/2025
This Aerospace Informational Report (AIR) provides guidance on using environmental, electrochemical, and electrical resistance measurements to monitor environment spectra and corrosivity of service environments, focusing on parameters of interest, existing measurement platforms, deployment requirements, and data processing techniques. The sensors and monitoring systems provide discrete time-based records of 1) environmental parameters such as temperature, humidity, and contaminants; 2) measures of alloy corrosion in the sensor; and 3) protective coating performance in the sensor. These systems provide measurements of environmental parameters, sensor material corrosion rate, and sensor coating condition for use in assessing the risk of atmospheric corrosion of the structure. Time-based records of environment spectra and corrosivity can help determine the likelihood of corrosion to assess the risk of corrosion damage of the host structure for managed assets, aiding in establishing
HM-1 Integrated Vehicle Health Management Committee
Arresting Hook Installation, Land-Based AircraftARP1538C (Current)11/11/2025
This SAE Aerospace Recommended Practice (ARP) covers the recommended criteria and performance requirements for the design and installation of land-based aircraft emergency and operational arresting hooks for use on runway arresting systems. Design criteria for fully operational hooks and for carrier-based aircraft hook installations are contained in specification MIL-A-18717.
A-5B Gears, Struts and Couplings CommitteeNEW
Next-Gen Maintenance Framework for Urban Air Mobility Vehicles2022-26-116505/26/2022
Urban Air Mobility (UAM) vehicles are set to revolutionize the mobility of man and material in near future. One of the key areas to explore is how operational efficiency can be maximized through the next generation Maintenance framework. Compared to the traditional aircrafts, the UAM vehicles will introduce many new and unique maintenance challenges such as: 1. The volume of UAM vehicles is going to be very high and involves frequent, short trips resulting in increased need for maintenance. 2. UAMs may be of hybrid nature (rotary and fixed wing) with a complex interplay of actuation and propeller-based controls. In addition, UAMs will have Electric Motors which involve complex maintenance of parts. 3. High Power Battery is another key component which involves handling the removal, replacement and charging, which requires an effective Battery Management System. 4. Efficient Inventory/Parts Management including NFF reduction is going to play a vital role because Parts, not labor, are the
Kulkarni, Sandeep, Elahi, Imtiaz, Kadeppagari, Murali, Panicker, Renju
Minimum Operational and Maintenance Responsibilities for Aircraft Tire UsageARP5265C (Current)09/20/2021
This SAE Aerospace Recommended Practice (ARP) sets forth criteria for the installation, inflation, inspection, and maintenance of aircraft tires and the maintenance of the operating environment to ensure the safety of support personnel and the safe operation of the aircraft.
A-5C Aircraft Tires Committee
Minimum Operational and Maintenance Responsibilities for Aircraft Tire UsageARP5265C-TEST-REC (Historical)09/20/2021
This SAE Aerospace Recommended Practice (ARP) sets forth criteria for the installation, inflation, inspection, and maintenance of aircraft tires and the maintenance of the operating environment to ensure the safety of support personnel and the safe operation of the aircraft.
A-5C Aircraft Tires Committee
Night Vision Imaging System (NVIS) Compatible Illuminated Pushbutton Switches and IndicatorsARP4822A (Current)09/03/2021
This SAE Aerospace Recommended Practice (ARP) reviews the basics of NVIS compatibility and discusses the specific illuminated pushbutton switch and indicator requirements for sunlight readability, color, luminance, and NVIS radiance when used in NVIS compatible cockpits. The recommendations and special considerations set forth in this document are made to give the design engineer a better understanding of MIL-L-85762A and MIL-STD-3009 NVIS compatibility requirements and to provide information on the visual characteristics of NVIS compatible pushbutton switch and indicators. The recommendations are primarly for military aircraft since civilian aircraft FAR requirements typically do not cover NVIS applications with the exception of those covered by RTCA/DO-275.
A-20A Crew Station Lighting Committee
Rotorcraft: Application of Existing Aircraft Designed Tires, Wheels and BrakesARP5632 (Current)04/23/2021
This document covers recommendations for the application of existing qualified and approved in-service fixed wing aircraft tires, wheels and brakes to military and commercial rotorcraft. NOTE: This document does not address the use of radial tires due to insufficient data to support their approved use on rotorcraft, see paragraph 4.3.14 for specific impact on ground resonance.
A-5 Aerospace Landing Gear Systems Committee
7.0.112 - Design and Development of Variable Valve Actuation (VVA) Mechanism Concept for Multi-Cylinder EngineSAE-PP-0028802/04/2021
The desire for higher fuel economy, improved performance and driveability expectations of customers from engines are gradually increasing along with stringent emission regulations set by the government. Many original engine manufacturing companies are prompted to consider the application of higher function variable valve actuation mechanisms in their next generation vehicles as a solution. The VVA is a generalized term used to describe any mechanism or method that can alter the shape or timing of a valve lift event within an internal combustion engine. The VVA allows lift, duration or timing (in various combinations) of the intake and/or exhaust valves to be changed while the engine is in operation. Engine designers are prompted to consider Variable Valve Actuation (VVA) system because of the inherent compromises with fixed valve events. The major goal of a VVA engine is to control the amount of air inducted into the engine which is a direct measure of torque. This work presents a
6.0.109 - Comparison Study on Fuel Properties of Biodiesel from Jatropha, Palm and Petroleum Based Diesel FuelSAE-PP-0026502/04/2021
The increase of air pollution and global warming is a threat for human life. Besides, the price of petroleum is increasing rapidly and the resources are diminishing. This obliged scientists and engineers to look for alternative sources of energy, which are cleaner and more sustainable. Biodiesel, defined as mono-alkyls of esters from vegetable oils and animals fat, is a cleaner renewable fuel and has been considered as the best alternative for petroleum based diesel fuel hence it can be used in any compression ignition engines without any significant modification. The main advantages of using biodiesel are its renewability and better quality of exhaust gas emissions due to their higher content of oxygen. The produce less soot and hence the feed stuck is plant it will regenerate the CO2 by the photosynthesis which ensures the renewability and reduces global warming. But these alternative fuels have faced some obstacles while utilizing in CI engines which are due to some of their
Mutagaana, Festo
Enhancing Flight Path Separation to Reduce Birdstrikes with Ultraviolet Radiation 02032021084035SAE-PP-0024302/03/2021
In the autumn of 2018 a pilot study using a prototype (PAR46 sized) landing light incorporating 5 ultraviolet light emitting diodes (UVLEDs) was attached on a one-quarter scale remote controlled (RC) 6 plane. The plane was flown in the direction of birds to measure their behavioral response to the 7 approaching plane with landing light either turned ON or OFF. Data were collected from multiple sources 8 including cameras on the plane and the ground, and a bird radar unit to measure the flight path separation 9 between the plane and the birds. The purpose of this study was to determine the effectiveness of using 10 UVLEDs integrated into a PAR46 landing light to trigger bird avoidance behavioral responses that would 11 increase flight path separation to reduce the incidence of birdstrikes. The findings showed the mean 12 distance of the avoidance response was statistically significantly greater when the PAR46 with UVLEDs 13 were turned ON than OFF. Field test data were used to create a
Anthony, Lindsay
Enhancing Flight Path Separation to Reduce Birdstrikes 1 with Ultraviolet RadiationSAE-PP-0023402/03/2021
In the autumn of 2018 a pilot study using a prototype (PAR46 sized) landing light incorporating 5 ultraviolet light emitting diodes (UVLEDs) was attached on a one-quarter scale remote controlled (RC) 6 plane. The plane was flown in the direction of birds to measure their behavioral response to the 7 approaching plane with landing light either turned ON or OFF. Data were collected from multiple sources 8 including cameras on the plane and the ground, and a bird radar unit to measure the flight path separation 9 between the plane and the birds. The purpose of this study was to determine the effectiveness of using 10 UVLEDs integrated into a PAR46 landing light to trigger bird avoidance behavioral responses that would 11 increase flight path separation to reduce the incidence of birdstrikes. The findings showed the mean 12 distance of the avoidance response was statistically significantly greater when the PAR46 with UVLEDs 13 were turned ON than OFF. Field test data were used to create a
Anthony, Lindsay
Aircraft Protection SystemsTBMG-3789410/01/2020
Northrop Grumman Corporation Falls Church, VA 1-703-280-2900
Designing Connectivity Solutions for an Electric Aircraft FutureTBMG-3788710/01/2020
The levels of voltage and current needed in electric-powered vertical takeoff and landing aircraft (eVTOL), personal air vehicles (PAVs), and rotorcraft systems are high and going higher. That’s because electric propulsion motors, inverters, controllers, batteries, and sensor-laden electric aircraft require significant amounts of power.
Designing Connectivity Solutions for an Electric Aircraft Future20AERP10_0310/01/2020
The levels of voltage and current needed in electric-powered vertical takeoff and landing aircraft (eVTOL), personal air vehicles (PAVs), and rotorcraft systems are high and going higher. That's because electric propulsion motors, inverters, controllers, batteries, and sensor-laden electric aircraft require significant amounts of power. High voltages and high kW peak outputs present many implementation challenges. Designers can meet these challenges by understanding how proper product selection and a “follow-the-wire” design approach enable high-power connectivity solutions. Some of the hurdles that designers need to overcome include the following.
Aircraft Asset Lifecycle and Digital Data Standards OverviewAIR7501 (Current)09/18/2020
This SAE Aerospace Information Report (AIR) reviews technical, operational, and maintenance data being exchanged between key stakeholders in aerospace asset lifecycle and data standards available for such exchanges. It identifies gaps and non-availability of data standards in certain areas. The scope of the current document is limited to aircraft operations, maintenance and disposal stages post-build phase, and does not include the detailed interactions during the aircraft build phase.
G-31 Electronic Transactions for Aerospace Committee
Aircraft Asset Lifecycle and Digital Data Standards OverviewAIR7501-TEST-REC (Historical)09/18/2020
This SAE Aerospace Information Report (AIR) reviews technical, operational, and maintenance data being exchanged between key stakeholders in aerospace asset lifecycle and data standards available for such exchanges. It identifies gaps and non-availability of data standards in certain areas. The scope of the current document is limited to aircraft operations, maintenance and disposal stages post-build phase, and does not include the detailed interactions during the aircraft build phase.
G-31 Electronic Transactions for Aerospace Committee
Information on Parking Brake SystemsAIR6441 (Current)09/16/2020
This SAE Aerospace Information Report (AIR) provides information on the parking brake system design for a variety of aircraft including part 23, 25, 27, and 29. The document includes a discussion of key technical issues with parking brakes. This document does NOT provide recommended practices for parking brake system design.
A-5A Wheels, Brakes and Skid Controls Committee
Lighting, Aircraft Interior, Installation ofAS18276B (Current)08/28/2020
This specification covers the installation of aircraft interior lighting for military aircraft.
A-20C Interior Lighting
Series Fuzzy PID with Anti-windup Controller for Intelligent Vehicle2020-01-011304/14/2020
A series fuzzy PID controller with anti-windup scope (SFPCA) is proposed in this paper to address saturation nonlinear problem and control disturbance caused by uncertainty of actuator model. In order to achieve novel dynamic and steady-state performance, the fuzzy controller and PID controller are fused into series, which realizes excellent dynamic performance of fast response and low overshoot like pure fuzzy controller at the initial response stage, and the excellent steady-state performance of stable and no static difference like PID control at the later response stage. The Hurwitz low is employed to configure PID parameters and 49 rules are designed for fuzzy controller. Since the input of the actuator could not be infinite, the actuator being saturated for a long time could reduce the stability of system and, even lead to irreversible damage. Moreover, after exiting the saturation state, it is difficult to quickly recover to the fast and stable response state of the original
Luo, Chao
High-Performance, Piezoelectric, Hybrid Synthetic Jet ActuatorsTBMG-3618103/01/2020
NASA Langley Research Center has invented three serial high-performance, piezoelectric, hybrid synthetic jet actuators to provide active flow control for current and future wing-borne vehicles in subsonic, transonic, and supersonic flow. Effective active flow control results in reduced vehicle drag and the prevention of events that can lead to catastrophic loss.
Ice and Rain Minimum Qualification Standards for Pitot and Pitot-static ProbesAS5562 (Current)02/11/2020
This SAE Aerospace Standard (AS) establishes minimum ice and rain performance criteria for electrically-heated pitot and pitot-static probes intended for use on the following classes of fixed-wing aircraft and rotorcraft. The classes of fixed-wing aircraft are defined by aircraft flight envelopes and are shown in Figure 1. The flight envelopes generally fall into the classes as shown below: The user of this standard must evaluate the aircraft level installation requirements for the probe against the class definition criteria to ensure adequate coverage for the application. It may be necessary to step up in class or modify the test conditions in order to meet the applicable installation requirements. NOTE: Class 2 is divided into two subgroups identified as either Class 2a or Class 2b. Class 2a probe applications typically include aircraft that operate within the mid to lower end of the Class 2 altitude range and that only use probe output to display basic airspeed and/or altitude. As
AC-9C Aircraft Icing Technology Committee
Specification Guide for Power Drive Units (PDUs)ARP5384 (Current)01/06/2020
This Recommended Practice provides a guide for specifying general design, performance, and test requirements for power drive units (PDUs) for flight controls and other applications.
A-6B3 Electro-Mechanical Actuation Committee
Aircraft Vertical Takeoff and LandingTBMG-3528410/01/2019
NASA’s Langley Research Center developed an inexpensive, long-endurance, vertical takeoff and landing (VTOL) unmanned aerial vehicle (UAV). It is capable of flying for 24 hours, landing in a 50 × 50 zone, and can be loaded into the back of a cargo van for easy transport. In addition, it can land in either a horizontal or vertical flight configuration.
Air Conditioning Systems for Subsonic AirplanesARP85G (Current)09/25/2019
This SAE Aerospace Recommended Practice (ARP) contains guidelines and recommendations for subsonic airplane air conditioning systems and components, including requirements, design philosophy, testing, and ambient conditions. The airplane air conditioning system comprises that arrangement of equipment, controls, and indicators that supply and distribute air to the occupied compartments for ventilation, pressurization, and temperature and moisture control. The principal features of the system are: a A supply of outside air with independent control valve(s). b A means for heating. c A means for cooling (air or vapor cycle units and heat exchangers). d A means for removing excess moisture from the air supply. e A ventilation subsystem. f A temperature control subsystem. g A pressure control subsystem. Other system components for treating cabin air, such as filtration and humidification, are included, as are the ancillary functions of equipment cooling and cargo compartment conditioning
AC-9 Aircraft Environmental Systems Committee
Perspectives on Integrating Structural Health Monitoring Systems into Fixed-Wing Military AircraftAIR6245 (Current)09/18/2019
This SAE Aerospace Information Report (AIR) is prepared for stakeholders seeking information about the evolution, integration, and approval of SHM technologies for military aircraft systems. The report provides this information in the form of (a) two military organizations’ perspectives on requirements, and (b) general SHM challenges and industry perspectives. The report only provides information to generate awareness of perspectives for military aircraft and, hence, assists those who are involved in developing SHM systems understanding the broad range of regulations, requirements, and standards published by military organizations that are available in the public domain from the military organizations.
Aerospace Industry Steering Committee on Structural Health
Flight Optimization Model on Global and Interval Ranges for Conceptual Studies of MEA Systems2019-01-190609/16/2019
In development of more electric aircraft applications, it is important to discuss aircraft energy management on various level of aircraft operation. This paper presents a computationally efficient optimization model for evaluating flight efficiency on global and interval flight ranges. The model is described as an optimal control problem with an objective functional subjected to state condition and control input constraints along a flight path range. A flight model consists of aircraft point-mass equations of motion including engine and aerodynamic models. The engine model generates the engine thrust and fuel consumption rate for operation condition and the aerodynamic model generates the drag force and lift force of an aircraft for flight conditions. These models is identified by data taken from a published literature as an example. First, approximate optimization process is performed for climb, cruise, decent and approach as each interval range path. Next, optimization for global
Shibuya, Yotsugi, Oyori, Hitoshi, Sugawara, Hirotaka, Seki, Naoki
Collins Aerospace provides avionics for C-130H modernization programSAE-MA-0000209/03/2019
The Lockheed C-130H Hercules fleet operated by the Air National Guard and U.S. Air Force Reserve is getting new Collins Aerospace Systems avionics that will help extend the life of the legacy aircraft by 20 years.
Kucinski, William
Safety Assessment of General Aviation Airplanes and Rotorcraft in Commercial ServiceARP5151A (Current)08/20/2019
This document describes a process that may be used to perform the ongoing safety assessment for (1) GAR aircraft and components (hereafter, aircraft), and (2) commercial operators of GAR aircraft. The process described herein is intended to support an overall safety management program. It is to help a company establish and meet its own internal standards. The process described herein identifies a systematic means, but not the only means, to assess continuing airworthiness. Ongoing safety management is an activity dedicated to assuring that risk is identified and properly eliminated or controlled. The safety management process includes both safety assessment and economic decision-making. While economic decision-making (factors related to scheduling, parts, and cost) is an integral part of the safety management process, this document addresses only the ongoing safety assessment process. This ongoing safety assessment process includes safety problem identification and corrective action
S-18C ARP5150A and ARP5151A Working Group
Facing the Challenges of Supercooled Large Droplet Icing: Results of a Flight Test Based Joint DLR-Embraer Research Project2019-01-198806/10/2019
Today’s airplanes are well equipped to cope with most common icing conditions. However, some atmospheric conditions consisting of supercooled large droplets (SLD) have been identified as cause of severe accidents over the last decades as existing countermeasures even on modern aircraft are not necessarily effective against SLD-ice. In 2014, the new Appendix O to the certification regulations (FAR Part 25 / CS-25) had been issued to guarantee the safe operation of future airplane when encountering SLD conditions. But as the SLD topic is quite new for the majority of aircraft manufacturers and research institutes in a same way, DLR (German Aerospace Center) and Embraer established a joint research cooperation in 2012 to obtain a better understanding of the distinct influences of SLD-ice shapes on aircraft characteristics and to evaluate proper ways for future airplane certification under App. O. Furthermore, one additional scientific goal of the cooperation was to develop and test new
Deiler, Christoph, Ohme, Per, Raab, Christian, Mendonca, Celso, Silva, Daniel
Experimental Aerodynamic Simulation of Glaze Ice Accretion on a Swept Wing2019-01-198706/10/2019
Aerodynamic assessment of icing effects on swept wings is an important component of a larger effort to improve three-dimensional icing simulation capabilities. An understanding of ice-shape geometric fidelity and Reynolds and Mach number effects on iced-wing aerodynamics is needed to guide the development and validation of ice-accretion simulation tools. To this end, wind-tunnel testing was carried out for 8.9% and 13.3% scale semispan wing models based upon the Common Research Model airplane configuration. Various levels of geometric fidelity of an artificial ice shape representing a realistic glaze-ice accretion on a swept wing were investigated. The highest fidelity artificial ice shape reproduced all of the three-dimensional features associated with the glaze ice accretion. The lowest fidelity artificial ice shapes were simple, spanwise-varying horn ice geometries intended to represent the maximum ice thickness on the wing upper surface. The results presented in this paper show
Broeren, Andy P., Potapczuk, Mark G., Lee, Sam, Woodard, Brian S., Bragg, Michael B., Smith, Timothy G.
JAUS Autonomous Capabilities Service SetAS8024 (Current)06/10/2019
This document defines a set of standard application layer interfaces called JAUS Autonomous Capabilities Services. JAUS Services provide the means for software entities in an unmanned system or system of unmanned systems to communicate and coordinate their activities. The Autonomous Behaviors Services represent the platform-independent capabilities commonly found in platforms across domains, including air, maritime, and ground. At present five (5) services are defined in this document. These services are: Comms Lost Policy Manager: Detect and recover from loss of communications with a control station Retrotraverse: Return along a path previously traveled Self-Righting: Attempt to recover from a tip over condition Cost Map 2D: Provides information about the current operating environment of the platform Path Reporter: Provides information about the previous or future planned path of the platform
AS-4JAUS Joint Architecture for Unmanned Systems Committee
Coating Technology Enables Effective Missile CountermeasuresTBMG-3453006/01/2019
Heat-seeking missiles have been in use against both rotorcraft and fixed wing aircraft since the mid-1950s, and countermeasures to deceive their guidance systems have been employed for nearly as long. Typically, countermeasures operate by generating a strong infrared signature which confuses the missile tracking system. At the heart of these systems is some form of powerful infrared emitting source. Often this source requires optical coating(s) to perform wavelength filtering needed for optimum operation. However, both the mechanical configuration of the thin film filter coatings used and the operating extremes to which they are subjected present challenges for the manufacturer.
Coating Technology Enables Effective Missile Countermeasures19AERP06_0406/01/2019
Heat-seeking missiles have been in use against both rotorcraft and fixed wing aircraft since the mid-1950s, and countermeasures to deceive their guidance systems have been employed for nearly as long. Typically, countermeasures operate by generating a strong infrared signature which confuses the missile tracking system. At the heart of these systems is some form of powerful infrared emitting source. Often this source requires optical coating(s) to perform wavelength filtering needed for optimum operation. However, both the mechanical configuration of the thin film filter coatings used and the operating extremes to which they are subjected present challenges for the manufacturer.
Landing Gear Structural Health MonitoringAIR6168A (Current)05/23/2019
This SAE Aerospace Information Report (AIR) discusses past and present approaches for monitoring the landing gear structure and shock absorber (servicing), opportunities for corrosion detection, methods for transient overload detection, techniques for measuring the forces seen by the landing gear structure, and methods for determining the fatigue state of the landing gear structure. Landing gear tire condition and tire pressure monitoring are detailed in ARP6225, AIR4830, and ARP6137, respectively. Aircraft Brake Temperature Monitoring Systems (BTMS) are detailed in AS1145.
A-5 Aerospace Landing Gear Systems Committee
Interface Standard, Airborne EO/IR Systems, DataAS6135A (Current)05/14/2019
This standard defines the data interfaces between a host aircraft (“platform”) and an Electro-Optic/Infrared (EO/IR) sensor. These data interfaces cover various types of data including: imagery, metadata, command, status, and responses (CSR), geospatial postion, time, test and maintenance, and hand-controller. This standard does not cover mechanical or electrical interfaces.
AS-1C Avionic Subsystems Committee
Arresting Hook Installation, Land-Based AircraftARP1538B (Historical)04/17/2019
This SAE Aerospace Recommended Practice (ARP) covers the recommended criteria and performance requirements for the design and installation of land-based aircraft emergency and operational arresting hooks for use on runway arresting systems. Design criteria for fully operational hooks and for carrier-based aircraft hook installations are contained in specification MIL-A-18717.
A-5B Gears, Struts and Couplings Committee
Aircraft Parachute Recovery SystemsTBMG-3376102/01/2019
BRS Aerospace South St. Paul, MN 651-457-7491
Cargo Compartment Lighting for Transport Category Aircraft and RotorcraftARP1283C (Current)01/14/2019
This SAE Aerospace Recommended Practice (ARP) establishes design guidance and photometric values for adequate cargo compartment and cargo access lighting systems for ground handling. The adoption of a standard set of illuminance values, found appropriate for the performance of the task in specified areas, should expedite ground handling.
A-20C Interior Lighting
Vertical Take Off and Landing (VTOL) Aircraft with Vectored Thrust for Control and Continuously Variable Pitch Attitude in HoverTBMG-3358401/01/2019
Most fixed-wing VTOL unmanned aerial vehicles (UAVs) take off vertically, then transition to horizontal flight. This is a new type of UAV that has unique capability. It can vary its hover position from “nose up” (tailsitter) to “nose forward” (non-tailsitter) incrementally and continuously, and even hold a position at any angle in between.
Exhaust Plume AnalyzerTBMG-3360001/01/2019
Exhaust plumes emanating from smoke stacks at power plants or other industrial facilities can have adverse impacts on local aviation during periods of calm winds. Adverse impacts can be exacerbated if the temperature is low or the atmosphere is unstable. While low oxygen concentrations and elevated temperatures inside the plume can be detrimental to slow-flying or hovering helicopters, the turbulence generated from the upward motion of the plume is the main potential hazard to light, fixed-wing aircraft at low altitudes.
2018 Create the Future Design Contest: Aerospace & Defense Category WinnerTBMG-3331811/01/2018
Integrated Rudder and Brake Pedal Unit, General Requirements for Fly-By Wire Transport and Business AircraftARP6252 (Current)10/15/2018
This Aerospace Recommended Practice (ARP) provides general requirements for a generic, integrated rudder and brake pedal unit, incorporating a passive force-feel system that could be used for fixed-wing fly-by wire transport and business aircraft. This ARP addresses the following: The functions to be implemented The mechanical interconnection between captain and F/O station The geometric and mechanical characteristics The mechanical, electrical, and electronic interfaces The safety and certification requirements
A-6A3 Flight Control and Vehicle Management Systems Cmt
Wing Inspection Lights – Design CriteriaARP4087C (Current)10/10/2018
This SAE Aerospace Recommend Practice (ARP) is intended to cover the external lights on fixed wing aircraft for illuminating the wing leading edge and engine nacelles and the upper surfaces of the wing. The addition of an ice detection system should be implemented when the areas to inspect are not visible from the aircraft cockpit. It is not intended that this Recommended Practice require the use of any particular light source such as Halogen, LED or other specific design of lamp.
A-20B Exterior Lighting Committee
Wing Inspection Lights – Design CriteriaARP4087C-TEST-REC (Historical)10/10/2018
This SAE Aerospace Recommend Practice (ARP) is intended to cover the external lights on fixed wing aircraft for illuminating the wing leading edge and engine nacelles and the upper surfaces of the wing. The addition of an ice detection system should be implemented when the areas to inspect are not visible from the aircraft cockpit. It is not intended that this Recommended Practice require the use of any particular light source such as Halogen, LED or other specific design of lamp.
A-20B Exterior Lighting Committee
Radar SystemTBMG-3301710/01/2018
RADA Electronic Industries Ltd. Netanya, Israel +972-9-892-1111
Aircraft Flashtube Anticollision Lighting SystemsAIR1276B (Current)08/28/2018
This document covers red and white anticollision lights using flashtubes as the light source.
A-20B Exterior Lighting Committee
Airborne Hydraulic and Control System Survivability for Military AircraftAIR1083C (Current)08/23/2018
This SAE Aerospace Information Report (AIR) provides the hydraulic and flight-control system designer with the various design options and techniques that are currently available to enhance the survivability of military aircraft. The AIR addresses the following major topics: a Design concepts and architecture (see 3.2, 3.5, and 3.6) b Design implementation (see 3.3, 3.6, and 3.7) c Means to control external leakage (see 3.4) d Component design (see 3.8)
A-6A2 Military Aircraft Committee
Vehicle Management Systems - Flight Control Function, Design, Installation and Test of Piloted Military Aircraft, General Specification ForAS94900A (Current)08/13/2018
This SAE Aerospace Standard (AS) provides the general performance, design, installation, test, development, and quality assurance requirements for the flight control related functions of the Vehicle Management Systems (VMS) of military piloted aircraft. It also provides specification guidance for the flight control interfaces with other systems and subsystems of the aircraft.
A-6A3 Flight Control and Vehicle Management Systems Cmt
Some Factors Affecting Visibility of Aircraft Navigation and Anticollision LightsAIR1106B (Current)08/13/2018
The scope of this SAE Aerospace Information Report (AIR) is to discuss factors affecting visibility of aircraft navigation and anticollision lights, enabling those concerned with their use to have a better technical understanding of such factors, and to aid in exercising appropriate judgment in the many possible flight eventualities.
A-20B Exterior Lighting Committee
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