Browse Topic: Freighter aircraft

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AIR120425-1AIR120425-1 (Current)12/4/2025
AIR120425-1
A-10 Aircraft Oxygen Equipment Committee
Measurement of Exterior Noise Produced by Aircraft Auxiliary Power Units (APUs) and Associated Aircraft Systems During Ground OperationARP1307C (Current)11/26/2025
Test procedures are described for measuring noise at specific receiver locations (passenger and cargo doors, and servicing positions) and for conducting general noise surveys around aircraft. Procedures are also described for measuring noise level and directivity at noise source locations to facilitate the understanding and interpretation of the data. Requirements are identified with respect to instrumentation; acoustic and atmospheric environment; data acquisition, reduction and presentation, and such other information as is needed for reporting the results. This document makes no provision for predicting APU or component noise from basic engine characteristics or design parameters, nor for measuring noise of more than one aircraft operating at the same time. No attempt is made to suggest acceptable levels of noise or suitable subjective criteria for judging acceptability. ICAO Annex 16 Volume I Attachment C provides guidance on recommended maximum noise levels.
A-21 Aircraft Noise Measurement Aviation Emission Modeling
Nitrogen Absorption/Desorption (Gas Dissolution) in Aircraft Shock AbsorbersAIR6942 (Current)11/26/2025
This document outlines the current state of the art in the understanding of gas in solution in shock absorber oils in unseperated shock absorbers. A literature review, overview of Henry's law, Henry's law coefficients for known gas and oil couples, in-service operational problems, lessons learned, and potential future work will be discussed in the document.
A-5B Gears, Struts and Couplings CommitteeNEW
Aircraft Lightning Test MethodsARP5416B (Current)11/26/2025
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 are an acceptable means, but not the only means, of meeting the test requirements of the certification plan. Each test method is set out in a uniform format, describing the test purpose, test object, test setup, test waveforms (voltage and/or current), measurements and data recording, test procedure and data interpretation. Guidance is provided on how to select the appropriate test or series of tests, and how the test results can be assessed. Natural lightning is a complex and variable phenomenon and its interaction with different types of vehicles may be manifested in many different ways. It is not intended that every test described herein be applied to every system requiring lightning verification tests. The document is written so that specific aspects of the environment can be called out for each specific program as dictated by the vehicle design, performance and mission constraints.
AE-2 Lightning Committee
Fuel Flowmeters and IndicatorsAS407E (Current)11/26/2025
To specify minimum requirements for Fuel Flowmeters for use primarily in reciprocating engine powered civil transport aircraft, the operation of which may subject the instruments to the environmental conditions specified in Section 3.3. This Aeronautical Standard covers two basic types of instruments, or combinations thereof, intended for use in indicating fuel consumption of aircraft engines as follows: TYPE I - Measure rate of flow of fuel used. TYPE II - Totalize amount of fuel consumed or remaining.
AS407 Fuel Flowmeters
Guidelines for the Integration of Electronic Engine Control Systems for Transport Category (Part 25) and General Aviation (Part 23) AircraftAIR5924B (Current)11/26/2025
This SAE Aerospace Information Report (AIR) provides methodologies and approaches that have been used to install and integrate full-authority-digital-engine-control (FADEC) systems on transport category aircraft. Although most of the information provided is based on turbofan engines installed on large commercial transports, many of the issues raised are equally applicable to corporate, general aviation, regional and commuter aircraft, and to military installations, particularly when commercial aircraft are employed by military users. The word “engine” is used to designate the aircraft propulsion system. The engine station designations used in this report are shown in Figure 1. Most of the material concerns an Electronic Engine Control (EEC) with its associated software, and its functional integration with the aircraft. However, the report also addresses the physical environment associated with the EEC and its associated wiring and sensors. Since most of today’s transport category engines use dual-channel full-authority digital engine control (FADEC) systems, this is the configuration which is addressed. A typical FADEC system configuration is shown in Figure 2.
E-36 Electronic Engine Controls Committee
Electrohydrostatic Actuation Applications on Aircraft ProgramsAIR6353 (Current)11/26/2025
This document will maintain a listing of all current and new EHA/EBHA aircraft applications, including parameters such as power, force, rate, etc, as is permissible for public offering.
A-6B2 Electrohydrostatic Actuation Committee
Verifying large alternate product code for an ARP document - ARP112425-1ARP112425/AABC/X000100000000000-1 (Current)11/24/2025
Verifying large alternate product code for an ARP document - ARP112425-1
A-10 Aircraft Oxygen Equipment Committee
Verifying large alternate product code for an AIR document - AIR112425-1AIR1124250000000000000000/NEW1--1 (Current)11/24/2025
Verifying large alternate product code for an AIR document
A-10 Aircraft Oxygen Equipment Committee
Extraordinary and Special Purpose Landing Gear SystemsAIR4846B (Current)11/11/2025
A landing gear system comprises the most compelling assembly of engineering skills. Its importance to the successful design of an aircraft can be favorably compared with that of the aircraft's wings and engines. A landing gear system consists of several different engineering disciplines, and is continually in the public eye especially with regard to safety. The primary objective of AIR4846 is to present a record of a variety of interesting gears, gear/aircraft systems and patents, and to discuss wherever possible the lessons learned, and the reasons for the design. Thus, the document is not only a historical account, but a means of recording technical knowledge for the practical benefit of future landing gear designers. Commendable efforts have been made over the years by several individuals to make such recordings, and AIR4846 will make continual reference to them. This applies to all books, papers, or specifications that have the approval of the SAE A 5 Committee. AIR4846 also accepts the premise that an essential aircraft requirement can often justify a gears' complexity and consequent weight. However, the document's purpose is not to recommend, but to provide reliable, authenticated information. Hence, the gear designer would be better equipped to adjudicate trade studies rationally, while not restricting his/her innovative skills. Each gear design feature will be associated with as many aircraft examples as possible, and every effort will be made to ensure accuracy, authenticity, and detail clarity. Section 2 of this document describes the features of landing gear which are addressed in the specific descriptions of various landing gears (Category A). Also, special types of landing gear are categorized as Category B.
A-5B Gears, Struts and Couplings CommitteeNEW
Landing Gear Component Heat DamageAIR5913B (Current)11/11/2025
The purpose of this report is to outline types of in-service heat damage that have been observed in high strength steel landing gear components, with an emphasis on a particular type that is referred to as “Ladder Cracking” which can develop in landing gear shock struts. The report discusses how ladder cracking can be detected visually and evaluated by non-destructive inspection methods, and how it can be repaired at overhaul with the prior approval of the Original Equipment Manufacturer. This report also describes the use of a bearing material that has resolved this problem without introducing other problems. Examples of other types of service induced heat damage are also discussed.
A-5B Gears, Struts and Couplings CommitteeNEW
Sponsor ChjangeARP050911 (Current)10/13/2025
Test
A-6A Systems Subsystem Integration Steering Group
How the Development Assurance Value-Based Acquisition (DAVBA) Approach Could Have Saved the Army’s Future Attack Reconnaissance Aircraft (FARA) ProgramF-0081-2025-02015/20/2025
The Primary Author has been involved in Army Aviation Development and Acquisition since the Utility Tactical Transport Aircraft System (UTTAS), Advanced Attack Helicopter (AAH), Army Helicopter Improvement Program (AHIP), and Light Helicopter Experimental (LHX) Programs in the mid-1970s to the mid-1980s. The first three of these programs successfully made it to production aircraft, while the LHX became the RAH-66 Comanche and was canceled primarily due to technical problems and cost overruns. The initiation of the next phase by the Army Aviation Development (ADD) Directorate for Future Vertical Lift (FVL) did not occur until the beginning of the 2015-2000 timeframe. This was 35 years since the last Army Aviation Development in 1980. To help sustain this FVL development, the Primary Author led, oversaw, and helped conduct a program through the National Rotorcraft Technology Center (NRTC) in the 2015-2016 timeframe. It was called the Development Assurance Value-Based Acquisition (DAVBA) Program1. It included the following team members: Georgia Tech, University of Alabama Huntsville (UAH), Dassault Systèmes, and Clausewitz Technology. The Army ADD plan funded it for FY2015- 2016 through the NRTC. The objectives were to provide the Future Vertical Lift (FVL) Program with a Development Assurance for Airworthiness Qualification and a Value-Based Acquisition Overall Evaluation Criterion (OEC) for FARA and FLRAA concepts.. However, Army Aviation only funded the first phase in 2015, as FVL funds were then transferred to the new Army Futures Command. This paper will illustrate how DAVBA could have saved the Future Attack and Reconnaissance Aircraft Program (FARA) Program as well as providing a more cost effective Future Long Range Assault Aircraft (FLRAA) Program.
Schrage, Daniel
Aircraft Brake Temperature MonitoringARP6812 (Current)10/28/2021
This SAE Aerospace Recommended Practice (ARP) provides recommendations for the function, design, construction, and testing of an on-aircraft Brake Temperature Monitoring System (BTMS), sometimes referred to as a Brake Temperature Indication System (BTIS). NOTE: This ARP does not address: Cockpit ergonomics and Aircraft operating procedures. Various handheld methods of temperature sensing or readouts, as these are not associated with transport aircraft during normal operation. Temperature sensitive paints as a means to indicate exceedance of a landing gear axle temperature threshold due to brake temperature.
A-5A Wheels, Brakes and Skid Controls Committee
Basic Aircraft Oxygen Systems DesignAIR825/14 (Current)8/11/2021
This slash document collects general reference material related to gaseous oxygen system flow requirements and sizing calculations. This document will assist oxygen system equipment designers and operators to establish systems and equipment requirements. The document consists of charts, tables, system schematics, system requirements, and sample calculations for system sizing.
A-10 Aircraft Oxygen Equipment Committee
Aircraft Flotation AnalysisAIR1780A (Current)4/23/2021
This document is divided into five parts. The first part deals with flotation analysis features and definitions to acquaint the engineer with elements common to the various methods and the meanings of the terms used. The second part identifies and describes the various methods used. To accomplish the minimum intent of this document, techniques could be limited to those needed for flotation analysis only; however, because of the close relation between flotation analysis and runway design, methods for the latter are also included. In fact, runway design criteria are used for flotation and evaluation in some cases, and are periodically the governing procedure in specific, if isolated, instances. From time to time, it may be necessary to deal with runways built to obsolete criteria. Therefore, a listing of most of these constitutes the third part. The fourth part of this document tabulates the recommended documents, categorizing them for commercial and civil versus military usage, by military service to be satisfied, and by type of pavement. The document concludes with brief elaborations of some concepts for broadening the analyst’s understanding of the subject.
A-5 Aerospace Landing Gear Systems Committee
Main Line Aircraft Tow Bar Attach Fitting InterfaceAS1614D (Current)4/8/2021
This SAE Aerospace Standard (AS) specifies the interface requirements for tow bar attachment fittings on the nose gear (when towing operations are performed from the nose gear) of conventional tricycle type landing gears of commercial civil transport aircraft with a maximum ramp weight higher than 50,000 kg (110,000 pounds), commonly designated as “main line aircraft”. Its purpose is to achieve tow bar attachment fittings interface standardization by aircraft weight category (which determines tow bar forces) in order to ensure that one single type of tow bar with a standard connection can be used for all aircraft types within or near that weight category, so as to assist operators and airport handling companies in reducing the number of different tow bar types used.
AGE-3 Aircraft Ground Support Equipment Committee
Wheel ChocksAIR4905A (Current)4/8/2021
The purpose of this document is to present general considerations for the design and use of aircraft wheel chocks. The design and use of aircraft wheel chocks is a good deal more complicated than it may appear at first glance.
AGE-3 Aircraft Ground Support Equipment Committee
Generalizing Aspects of System Safety to Broaden Applicability2021-01-00373/2/2021
The Safety Assessment Process, defined by SAE ARP4761 and associated regulatory guidance, is described in the context of conventional, crewed civil aircraft. While this material has been used for decades to evaluate airplanes and rotorcraft, the evolution of technology challenges it. As new entrants venture into aviation, they bring perspectives, which may not clearly align to those conventional concepts. For those skilled in the art of aviation safety assessment, the approach to new technologies might appear straight forward. Such an individual might easily perceive the accommodations for unconventional applications. Once accommodations are made, and failure conditions are established and classified to those new architectures, the rest of the process is somewhat mechanical -they flow out of these conditions. However, the context of their experience betrays the reality of the process description in the ARP and guidance. Such accommodations are not discussed in them, and the process objectives, which are fulfilled by the process, are not explicit. One example of such a challenge regards how failure condition effects and classification are described. The guidelines state that the effects and classification should consider the aircraft, flight crew, and occupants. What are the safety considerations for an unmanned cargo airplane the size of a transport aircraft? How is the “crew effect” of a ground station considered? Is a passenger who simply provides a waypoint to a full autonomous vehicle considered the “crew”? Such cases easily demonstrate how the conventional ARP process limits its own universality in its initial process step. This paper recommends ways to broaden SAE ARP4761 and some regulatory guidance through improving the description of functions, failure conditions, and their classifications. This paper discusses aspects of these concepts and their downstream processes. The intent of this paper is to identify how to make the ARP’s processes accessible to future applications while supporting conventional applications, towards providing comprehensive safety coverage for all air and space vehicles.
Voros, Robert
Maximum-Allowable-Airspeed Instruments (Turbine Powered Subsonic Aircraft)AS437B (Current)12/22/2020
This SAE Aerospace Standard (AS) covers one type of maximum-allowable-airspeed instrument which gives a continuous indication of both indicated airspeed and maximum allowable airspeed not exceeding 650 knots.
A-4 Aircraft Instruments Committee
Flight Test Procedures for Static Pressure Systems Installed in Subsonic Transport AircraftARP921B (Current)12/22/2020
This SAE Aerospace Recommended Practice (ARP) covers the test procedures and equipment for performing flight testing on pitot-static systems installed in subsonic transport type aircraft.
A-4 Aircraft Instruments Committee
Automatic Pilots (Turbine Powered Subsonic Aircraft)AS440B (Current)12/22/2020
This SAE Aerospace Standard (AS) covers automatic pilots intended for use on aircraft to automatically operate the primary and trim aerodynamic controls to maintain stable flight and/or to provide maneuvering about any of the three axes through servo control. Automatic control functions essential for primary or augmented flight control are excluded.
A-4 Aircraft Instruments Committee
Air Cargo Unit Load Devices - Performance Requirements and Test ParametersAS36100C (Current)9/29/2020
This SAE Aerospace Standard (AS) defines the minimum performance requirements and test parameters for air cargo unit load devices requiring approval of airworthiness for installation in an approved aircraft cargo compartment and restraint system that complies with the cargo restraint requirements of Title 14 CFR Part 25, except for the 9.0-g forward ultimate inertia force of § 25.561 (b)(3)(ii).
AGE-2 Air Cargo
Safety Considerations for Airplane LavatoriesARP1315E (Current)6/25/2020
This SAE Aerospace Recommended Practice (ARP) establishes safety recommendations for lavatories in transport category airplanes.
S-9B Cabin Interiors and Furnishings Committee
Approach to Landing Guidance System for Transport AircraftARP4102/12B (Current)6/11/2020
This document specifies requirements for an Approach to Landing Guidance System (ALGS) electronic device. This equipment shall display relative aircraft position and situation information for flight along precision three-dimensional paths within the appropriate coverage area. The precision three-dimensional path may be an ILS straight-in look-alike path or a complex, curved path. The requirements are applicable to electronic devices capable of receiving signals or other information from one or more sources, including but not limited to ILS, GNSS, or IRU inputs.
S-7 Flight Deck Handling Qualities Stds for Trans Aircraft
Aircraft Ground Deicing/Anti-Icing Training and Qualification ProgramAS6286B (Historical)6/11/2020
This document establishes the minimum training and qualification requirements for ground-based aircraft deicing/anti-icing methods and procedures. All guidelines referred to herein are applicable only in conjunction with the applicable documents. Due to aerodynamic and other concerns, the application of deicing/anti-icing fluids shall be carried out in compliance with engine and aircraft manufacturers’ recommendations. The scope of training should be adjusted according to local demands. There are a wide variety of winter seasons and differences of the involvement between deicing operators, and therefore the level and length of training should be adjusted accordingly. However, the minimum level of training shall be covered in all cases. As a rule of thumb, the amount of time spent in practical training should equal or exceed the amount of time spent in classroom training.
G-12T Training and Quality Programs Committee
Air Conditioning of Aircraft CargoAIR806B (Current)5/12/2020
The report presents air conditioning data for aircraft cargo which is affected by temperature, humidity, ventilation rate and atmospheric pressure. The major emphasis is on conditioning of perishable products and warm-blooded animals. The report also covers topics peculiar to cargo aircraft or which are related to the handling of cargo.
AC-9 Aircraft Environmental Systems Committee
Aircraft Ground Support Equipment - Wind Stability DeterminationARP1328D (Current)4/29/2020
This SAE Aerospace Recommended Practice (ARP) is intended to recommend: a Uniform criteria for determination of wind loads that aircraft ground support equipment can encounter and yet allow personnel to work safely, b Uniform systems for maintaining stability (i.e., stabilizers, outriggers, spring lockout devices), c Standardization of specific types of interlock systems and actuation systems, d A standard formula with its associated design criteria for calculating the steady-state wind stability (i.e., tip point) for aircraft ground support equipment, e A standard method for testing these systems.
AGE-3 Aircraft Ground Support Equipment Committee
Aircraft Markings for Ground Support Equipment AlignmentAS6896 (Current)4/24/2020
The purpose of this document is to provide a standard for aircraft fuselage markings located at the doors used for ground servicing operations. These markings can be used by all GSE that will dock at the aircraft. These markings may be used for one or several phases of the GSE positioning relative to the aircraft process: GSE alignment during approach, GSE final docking, and GSE auto leveling. It is not the purpose of this standard to describe the different technologies, cameras, or other equipment that can be mounted on GSE to utilize these markings. The aircraft that may use these markings will have a fuselage diameter of 3 m or more.
AGE-3 Aircraft Ground Support Equipment Committee
Aerospace - Passive Side Stick Unit General Requirements for Fly-by Wire Transport and BusinessARP6001B (Current)4/23/2020
This SAE Aerospace Recommended Practice (ARP) provides recommendations for design and test requirements for a generic “passive” side stick that could be used for fly-by wire transport and business aircraft. It addresses the following: The functions to be implemented The geometric and mechanical characteristics The mechanical and electrical interfaces The safety and certification requirements
A-6A3 Flight Control and Vehicle Management Systems Cmt
Fire Containment Cover - Operation and UseARP6905 (Current)4/23/2020
This SAE Aerospace Recommended Practice (ARP) provides guidelines for the effective operation and use of fire containment covers (FCCs). Technical Standard Orders (TSOs) C203 and C90e (and later revisions) incorporate AS6453, and provide the Minimum Performance Standards (MPS) for an FCC design. The net and pallet used with the FCC must be approved using the updated net and flammability requirements in TSO C90e and later revisions. However, fire containment performance also requires this equipment is properly used. Fire safety is compromised when FCCs are used in an inadequate manner.
AGE-2 Air Cargo
Automatic Pilot InstallationsARP419B (Current)4/14/2020
These recommendations cover the mechanical and electrical installation and installation test procedures for automatic pilots of the type normally used in transport type aircraft. The material in this ARP does not supercede any airworthiness requirement in the Civil Air Regulations.
A-4 Aircraft Instruments Committee
Aircraft Oxygen Replenishment Coupling for Civil Transport Aircraft (Design Standard)AS1219A (Current)2/28/2020
This SAE Aerospace Design Standard defines a coupling, which is installed in a high pressure (1850 to 2000 psig) oxygen system of a civil transport aircraft for the purpose of mating to ground oxygen replenishment facilities. Dimensions developed from AND10089, Detail Specification Sheet for Fitting End, Design Standard, For Cone Connection.
A-10 Aircraft Oxygen Equipment Committee
Landing Gear Fatigue Spectrum Development For Part 25 AircraftAIR5914 (Current)2/28/2020
This SAE Aerospace Information Report (AIR) provides guidelines for the development of landing gear fatigue spectra for the purpose of designing and certification testing of Part 25 landing gear. Many of the recommendations herein are generalizations based on data obtained from a wide range of landing gears. The aircraft manufacturer or the landing gear supplier is encouraged to use data more specific to their particular undercarriage whenever possible.
A-5B Gears, Struts and Couplings Committee NEW Name Goes Her
Maintenance of Pitot-Static Systems of Transport AircraftAIR975B (Current)2/20/2020
In efforts to increase the accuracy and reliability of altimetry, speed measurement and other aspects of air data, a great deal of attention and money have been expended on new and refined pressure transducing and computing systems and on the standards by which they are calibrated. So much progress has been made in this that the limiting factor is, or may soon be, the sensing and transmitting in the aircraft of the pressures to be transduced. Until the appearance of References 1-13 and 18 there was little guidance available on the maintenance of pitot and static systems. This report presents what information is available, suggests limits, and lists the principal original papers on the subject.
A-4 Aircraft Instruments Committee
Flight Deck Interior Doors for Transport AircraftARP4101/8A (Current)2/18/2020
This document recommends criteria for standardizing flight deck interior doors and their operation to optimize their use under normal and emergency conditions.
S-7 Flight Deck Handling Qualities Stds for Trans Aircraft
Magnesium Alloys in Aircraft Seats - Developments in Magnesium Alloy Flammability TestingAIR6160A (Current)1/9/2020
This document provides informational background, rationale and a technical case to allow consideration of the removal of the magnesium alloy restriction in aircraft seat construction as contained in AS8049B. The foundation of this argument is flammability characterization work performed by the FAA at the William J. Hughes Technical Center (FAATC), Fire Safety Branch in Atlantic City, New Jersey, USA. The rationale and detailed testing results are presented along with flammability reports that have concluded that the use of specific types of magnesium alloys in aircraft seat construction does not increase the hazard level potential in the passenger cabin in a post-crash fire scenario. Further, the FAA has developed a lab scale test method, reference DOT/FAA/TC-13/52, to be used as a certification test, or method of compliance (MOC) to allow acceptability of the use of magnesium in the governing TSO-C127 and TSO-C39C. Other flammability studies are also cited in the AIR document to substantiate the FAA findings.
Aircraft SEAT Committee
Performance Standards for Oblique Facing Passenger Seats in Transport AircraftARP6316A (Current)11/19/2019
This SAE Aerospace Recommended Practice (ARP) documents a common understanding of terms, compliance issues, and occupant injury criteria to facilitate the design and certification of oblique facing passenger seat installations specific to Part 25 aircraft. The applicability of the criteria listed in this current release is limited to seats with an occupant facing direction greater than 18 and no greater than 30 degrees relative to the aircraft longitudinal axis. Later revisions are intended to provide criteria for other facing directions. Performance criteria for side facing seats installed with the occupant facing direction at 90 degrees relative to the aircraft longitudinal axis are provided in AS8049/1. Seats installed at angles greater than 30 degrees relative to the aircraft longitudinal axis must have an energy absorbing rest or shoulder harness. However, this document does not provide the criteria for oblique facing seats incorporating such rests. Satisfying the criteria listed in Table 2 may satisfy the requirement for a rest. Although the issues and criteria presented in this document are common with oblique facing seats installed in Part 23 aircraft and Parts 27 and 29 rotorcraft, these recommendations have not been validated for these types of aircraft.
Aircraft SEAT Committee
MARK I AVIATION KU-BAND AND KA-BAND SATELLITE COMMUNICATION SYSTEM PART 1 PHYSICAL INSTALLATION AND AIRCRAFT INTERFACESARINC791P1-3 (Current)9/19/2019
This standard sets forth the desired characteristics of Aviation Ku-band Satellite Communication (Satcom) and Ka-band Satcom Systems intended for installation in all types of commercial air transport aircraft. The intent of this characteristic is to provide guidance on the interfaces, form, fit, and function of the systems. This document also describes the desired operational capability of the equipment needed to provide a broadband transport link that can be used for data, video, and voice communications typically used for passenger communications and/or entertainment. The systems described in this characteristic are not qualified, at this writing, for aviation safety functions.
Airlines Electronic Engineering Committee
Flight Deck Lighting for Commercial Transport AircraftARP4103A (Current)9/17/2019
This document recommends design and performance criteria for aircraft lighting systems used to illuminate flight deck controls, luminous visual displays used for transfer of information, and flight deck background and instrument surfaces that form the flight deck visual environment. This document is for commercial transport aircraft except for applications requiring night vision compatibility.
A-20A Crew Station Lighting Committee
Aircraft Ground Deicing/Anti-Icing Training and Qualification ProgramAS6286A (Historical)6/26/2019
This document establishes the minimum training and qualification requirements for ground-based aircraft deicing/anti-icing methods and procedures. All guidelines referred to herein are applicable only in conjunction with the applicable documents. Due to aerodynamic and other concerns, the application of deicing/anti-icing fluids shall be carried out in compliance with engine and aircraft manufacturers’ recommendations. The scope of training should be adjusted according to local demands. There are a wide variety of winter seasons and differences of the involvement between deicing operators, and therefore the level and length of training should be adjusted accordingly. However, the minimum level of training shall be covered in all cases. As a rule of thumb, the amount of time spent in practical training should equal or exceed the amount of time spent in classroom training.
G-12T Training and Quality Programs Committee
High Altitude Ice Crystal Detection with Aircraft X-band Weather Radar2019-01-20266/10/2019
During participation on EU FP7 HAIC project, Honeywell has developed methodology to detect High Altitude Ice Crystals with the Honeywell IntuVue® RDR-4000 X-band Weather Radar. The algorithm utilizes 3D weather buffer of RDR-4000 weather radar and is based on machine learning. The modified RDR-4000 Weather Radar was successfully flight tested during 2016 HAIC Validation Campaign; the technology was granted Technology Readiness Level 6 by HAIC consortium. After the end of HAIC project, the method was also evaluated with respect to newly set preliminary industry standard performance requirements1. This paper discuses technology design rationale, high level technology architecture, technology performance, and challenges associated with performance evaluation.
Lukas, Jan, Badin, Pavel
Facing the Challenges of Supercooled Large Droplet Icing: Results of a Flight Test Based Joint DLR-Embraer Research Project2019-01-19886/10/2019
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 tools for the in-flight monitoring of aircraft characteristics as well as the on-board identification of simulation models. During the 4 years of the project, a distinct way to better understand icing-induced degradations on a specific aircraft was followed: first, data of the clean aircraft was gathered in flight test to identify a dynamic simulation model as base for the subsequent evaluations. Second, data of test flights with artificial App. C ice configurations were analyzed and used for the development of distinct modifications of the base aircraft simulation model; a first evaluation of the icing-induced changes of aircraft characteristics was conducted. Third, after the generation of SLD-ice shapes, wind tunnel testing and flight clearance, a second flight test campaign with these artificial SLD-ice shapes delivered the data for an additional model modification and identification. The results of the final data and model evaluation provide the observable degradation of SLD-ice in flight, which is well comparable to results obtained from the App. C ice configurations.
Deiler, Christoph, Ohme, Per, Raab, Christian, Mendonca, Celso, Silva, Daniel
Setting the Record Straight on Failures and Successes in Army Aviation Development Programs Over the Past Forty-Five YearsF-0075-2019-146225/13/2019
Army Aviation Development Programs have had more failures than successes since beginning with the successful Utility Tactical Transport Aircraft System (UTTAS) and Advanced Attack Helicopter (AAH) development programs in the early 1970s. While these follow-on failures have often been blamed on either the Army user, Army developer or industry; they often come with biases from sideline participants without firsthand knowledge. The author of this paper has had mostly firsthand involvement and knowledge on these Army Aviation Development Programs over the past 45 years and he will seek to set the record straight. It will start with a review of Army Aviation Air Mobility Doctrine in the 1960s and it development and implementation in Southeast Asia, for which the author directly participated in. The initial implementation in South Vietnam was based on using off the shelf modified aircraft, predominantly helicopters. These lessons learned had a major impact on developing new aircraft and major modifications in the 1970s, e.g. UTTAS, AAH, CH-47D and OH-58D for which the author also directly participated in. There are critical lessons learned from this Air Mobility Doctrine development and the major aircraft programs which resulted from it, which are especially critical as the Army seeks major new development programs over the next decade. Also, it appears that the current focus on Urban Air Mobility (UAM) with the incorporation of new eVTOL aircraft, such as air taxis and unmanned aerial systems (UAS) into a low altitude Traffic Management (UTM) environment, also has a lot to learn from the Army's Air Mobility Doctrine development and the vertical takeoff and landing aircraft, e.g. helicopters, that were developed to implement it.
Schrage, Daniel
ARINC 661 Third Party Toolkit User ExperienceF-0075-2019-145485/13/2019
Over the past several years, there has been a trend from airframe vendors to move from procuring federated components (individual control panels and computers) to integrated avionics systems provided by a single vendor. This integration has reduced size, weight, power, and increased the usability of the system for the pilots. These latest cockpits are typically made up of larger displays and integrated controls, including touch screens. This level of integration has significantly increased the difficulty in incorporating third party (OEM and other vendor) mission specific avionics into the cockpit. This is especially noted in military aircraft and rotorcraft, which frequently have needs beyond a typical fixed wing passenger transport aircraft, which have been the baseline of integrated avionics systems (Ref [1]). The industry has been focused on several different methods to address incorporation of third party mission specific avionics into these highly integrated systems. Initiatives such as Future Airborne Capability Environment (FACETM) (Ref [5]) are joint ventures between industry and the government to solve this evolving issue. Additionally, ARINC 661 has been implemented in such a way to allow the merging of the user interface from multiple software applications into a single, seamless display. This paper documents Collins Aerospace' experience with providing our ARINC 661 3rd party toolkit to OEMs and OEM selected 3rd party developers to allow development of new "mission" features into highly integrated cockpit systems. A survey was provided to multiple users of this toolkit and the results are documented. From these results, we developed a set of conclusions, both positive and negative, providing lessons learned and recommendations as the industry continues to move towards more 3rd party integration.
Weaver, Jacob, Lam, Joel
Air Cargo Pallets - Utilization GuidelinesARP5486 (Current)4/1/2019
Air cargo pallets and their cargo restraint nets constitute aircraft Unit Load Devices, defined by industry standards and airworthiness certified based on Technical Standard Order (TSO) C90c in accordance with the requirements of NAS 3610. This guarantees their design to be intrinsically safe for flight on board compatible aircraft types. However, actual flight safety also requires these certified pieces of equipment to be properly used: numerous occurrences have demonstrated a certified ULD can nevertheless jeopardize flight safety if loaded or restrained in an inadequate manner.
AGE-2 Air Cargo
Aircraft Jacking Pads Adapters and Sockets Design and Installation ofAS8091A (Current)3/29/2019
This SAE Aerospace Standard (AS) provides requirements for design and installation of aircraft jacking pad adapters and the mating jack socket interface to permit use of standard jacking equipment to be used in civil and military transport aircraft. The adapter defined herein shall be the key interface between the aircraft and the aircraft jack(s).
AGE-3 Aircraft Ground Support Equipment Committee
Deployable – Instrument Landing SystemTBMG-337652/1/2019
Thales Group Cedex, France + 33(0)1 57 77 86 26
Highly Efficient Civil Aviation, Now via Operations - AAR and Challenges2018-01-192510/30/2018
Global civil aviation growth at 5+% yearly poses extreme environmental challenges. Advances have appeared gradually through improved aerodynamic shapes, using carbon fibres, and enhanced engines; however, as these technologies mature, direct efficiency advances require increasing effort. Often Passenger convenience is forgotten e.g. the long-range air traffic has developed on hub-spoke basis implying extra feeder flights, transit passenger inconveniences, capacity issues. Efficiency metrics emphasize “Why, How & What”, with an understanding of the range sensitivities, operational concepts and performance goals via the important “X-factor”. For given range, current aircraft are “greener” than previous generations. Medium range aircraft s are always greener than those for short or long ranges. However, currently, the major trend is for the latter: twin-aisle A350, A380, B787, B777X (10+% payload, 40+% fuel to MTOW). Shorter range single-aisle aircraft are “feeders” or newer derivatives: A320, B737 class (20+% payload, 20+% fuel to MTOW). New technologies could feature in future e.g. Natural Laminar flow, riblets, enhanced loads allevation, composite tailoring, morphing structures, distributed propulsion, bio-fuels etc. These may make significant improvements and lead to unconventional layouts e.g. blended wing bodies, high aspect ratio wings, oblique wings, and joined wings. Additionally, significant environmental gains can be made via operations e.g. AAR and Formation flying. Air-to-air refuelling (AAR) has been practised and perfected by the Military for 80+ years. Tankers are sky “gas- stations”. The Military objective is for mission success rather than fuel economy. Tankers accompany and refuel short- range aircraft over longer missions. AAR can be a strong enabler for the civil aviation. Small dedicated tankers (A320 size) can operate over short radii, refuelling longer range cruisers. AAR will always retain top hierarchy over any technological advances, offering step change towards highly efficient aviation. We discuss the pros and cons of operational issues, routing and constraints, turbulence, air navigation and environmental impact. Replacing today´s inter-continental system with AAR gives fuel and CO2 reductions of 15-30% depending on range. Additionally, 30-40% weight savings lead manufacturers focus on smaller aircraft. Major COC and DOC reductions of a similar order occur. Noise, emissions, wake effects are favourable, meeting ACARE/NASA goals. A by-product is that laminar-flow aircraft introduction can be eased. Increasing AAR benefits occur as Point A to B system replaces the hub--spoke system. The smaller AAR-cruisers imply ground-based opportunities: smaller airports and new connections, easing the transit passenger handling and reducing travel time. For sustainable aviation growth and future urbanisation, short flights are replaced by other means. The capacity relief becomes available for long flights (only aviation is suitable). Maintaining transport capacity, less AAR enabled cruisers are needed; these operate at 20+% payload to MTOW. More likely is that the total airborne mass is lower. Certification and Operational rules will need revision. New tankers or other types modified from civil aircraft respect most CS-25 regulations. We aim for automatic refuelling (as demonstrated by A330 tanker recently and as in US-UCAV programme). We allude to newer versatile twin-aisle cruisers with differing capacities operating world-wide ranges with AAR, blending with formation flying. All this should “spur/re-vitalise” Aviation. We propose practical demonstrations. A game changer in sight!
Nangia, R K
Air Cargo Unit Load Devices - Use of Airworthiness Reference DocumentsAIR36106A (Current)10/18/2018
This SAE Aerospace Information Report (AIR) provides instructions for intended proper use of Aerospace Standard AS36100A, published 2006-04 [TSO pending], as the technical reference for airworthiness approval of air cargo unit load devices (pallets, nets and containers) to be loaded on board civil transport aircraft. For consistency and cross-checking purposes, it also includes instructions for proper use of previous NAS 3610 [Revision 10, 1990, referenced in TSO C90c], as commonly understood by the industry.
AGE-2 Air Cargo
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