Browse Topic: Commercial aircraft

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This document provides information on provisions for passengers with disabilities on board commercial aircraft. In this context the term "provision of medical oxygen" shall be understood as application of oxygen on board an aircraft not linked to (post) decompression in the sense of Airworthiness Requirements FAR/CS 25 and Operational Regulations of FAR 121/135. Information about available equipment and physiological treatment in clinical practice will be provided in this document. It covers the use of oxygen concentrators according to guidance of FAR Advisory Circular AC120-95.
A-10 Aircraft Oxygen Equipment Committee
AIR120425-1
A-10 Aircraft Oxygen Equipment Committee
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
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
This information report provides general guidance for the design considerations, qualification in endurance, strength and fatigue of landing gear using composite components as principle structural elements. The information discussed herein includes the development and evaluation of design data considering: the potential for imbedded manufacturing defects, manufacturing process variations, the component operating environment, potential damage threats in service, rework and overhaul, and inspection processes. This AIR mainly discusses the use of thick composites for landing gear structural components. Considerations and recommendations provided in this AIR may therefore differ greatly from considerations and recommendations found in widely accepted composite design references such as CMH-17 and Advisory Circulars such as AC 20-107(B).
A-5B Gears, Struts and Couplings CommitteeNEW
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
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
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
SAE CACRC has produced several standards, each representing the best-practice, recommended minimum training syllabus for the aforementioned target groups. The purpose of this document is to promote the use of these SAE standards, particularly for developing training programs for employee training, qualification in airlines and maintenance organizations, and as reference in regulatory guidance material. It summarizes, as a quick reference, the content of each training document and its relation to and interaction with other training documents. Thereby it allows users to select the appropriate training documents and syllabi to establish a comprehensive, sequential training program build-up customized to the specific needs of the aforementioned functions (see figure). This document does not intend to introduce new training content/syllabus.
AMS CACRC Commercial Aircraft Composite Repair Committee
This document provides an overview of the tests and issues related to testing that are unique to Electrohydrostatic Actuators (EHAs). An EHA incorporates a linear or rotary hydraulic actuator and a variable speed, reversible electric servomotor driving a fixed displacement hydraulic pump for actuator control, and associated power drive electronics. The tests and issues documented are not necessarily all-inclusive. This document discusses both, the tests applicable to EHAs and the test methodologies to accomplish the test objectives. This document also lists tests that are not unique to EHAs, but are still applicable to EHAs. In these instances a discussion of such tests is not contained in this document, and as applicable, the reader may reference ARP1281 (Actuators: Aircraft Flight Controls, Power Operated, Hydraulic, General Specification For), which addresses test issues applicable to electrohydraulic flight control servoactuators. In the discussion of the tests and test methodologies contained in this document, numerical definition or specification of the test parameters to be imposed or measured is not included. These definitions or specifications should be developed to conform to the requirements of the applicable EHA technical specification document, considering the usual influencing factors such as instrumentation accuracy, test temperature, etc.
A-6B2 Electrohydrostatic Actuation Committee
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
As per Committee/Henry E. Harschburger recommendations
A-6B1 Hydraulic Servo Actuation Committee

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.

My new committee for commercial aircrafts
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
A-10 Aircraft Oxygen Equipment Committee
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
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
Test
A-6A Systems Subsystem Integration Steering Group
This standard is intended to apply to portable compressed gaseous oxygen equipment. When properly configured, this equipment is used either for the administration of supplemental oxygen, first aid oxygen or smoke protection to one or more occupants of either private or commercial transport aircraft.
A-10 Aircraft Oxygen Equipment Committee
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
The rotorcraft community faces significantly higher accident rates compared to fixed-wing commercial aircraft, underscoring the critical need for enhanced safety measures. While Helicopter Flight Data Monitoring programs hold promise in improving safety, their widespread adoption remains limited, partly due to challenges associated with the acquisition and analysis of flight data. This paper proposes a Deep Learning (DL) solution to address safety concerns within the rotorcraft community by efficiently acquiring and analyzing flight data for a more automated and comprehensive safety assessment. Specifically, we leverage data obtained with cost-effective off-the-shelf cameras, and process it through Convolutional Neural Networks for automated detection and classification of gauges from several helicopters' cockpits. Our DL pipeline integrates a classifier for helicopter identification, an object detector for cockpit gauges detection and classification, and a network to infer the reading of each detected gauge. The contribution of this work is two-fold: (1) enhance rotorcraft safety by developing a DL framework capable of detecting, classifying, and inferring gauge readings for different helicopter types, and (2) boost research in the field by constructing a curated dataset valuable for aviation and machine learning communities.
Khelifi, AmineJohnson, Charles C.Thompson, LaceyBouaynaya, Nidhal C.Carannante, GiuseppinaTrabelsi, Mohamed Ali
This SAE Aerospace Recommended Practice (ARP) is an application guide for fixed and variable displacement hydraulic motors. It provides details of the characteristics of fixed and variable displacement hydraulic motors, architectures, circuit designs, controls, and typical applications. The applications include airborne and defense vehicles with emphasis on high performance applications.
A-6C4 Power Sources Committee
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
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
Location of Crew and Passenger Oxygen Masks, Portable Oxygen System, and Protective Breathing EquipmentARP6390 (Current)8/10/2021
Various emergency situations may require the dispensing of oxygen to all occupants of aircraft during flight. During an emergency event, depending on the aircraft operational flight capability, all cabin occupants must be serviced by a mask presentation system connected to an operational oxygen source. Several regulations specify the functional characteristics and requirements of the oxygen systems for aircraft in support of different missions. These should be referred to for the exact functional performance requirements. It is not the intent of this document to ensure conformance with these regulations, but only to recommend general concepts for the location of the oxygen masks and oxygen system outlets for proper accessibility by the aircraft occupants, whether cabin occupants or crew members. Different requirements may apply when the mission of the pressurized aircraft or the operational altitude of the aircraft is not in excess of FL250. When the aircraft is operating above FL100, oxygen masks, either distributed to each cabin occupant or stowed and readily accessible, must be available in the event of a pressurization failure. Oxygen masks must also be connected to an operational source, available and within easy reach of each seated flight deck crew member and observer. For unpressurized aircraft, during flight operations above FL125, oxygen masks connected to an operational oxygen source must be available to all occupants. This document defines the accessibility requirements that should be considered in the placement of oxygen masks for presentation to the user and the connections for such oxygen masks to the operational oxygen systems. This is of interest when designing the interior of the aircraft, placing the seats in relationship to such outlets and mask connections, or placing oxygen mask outlets in relation to the seats. The accessibility requirements contained in this document are applicable to installation and arrangement of such equipment in different locations in the aircraft as shown on typical examples of installation areas as shown in Figures 3 through 15. Furthermore, this document does not discuss operational needs with respect to oxygen supply duration, nor the detail design of portable oxygen system or protective breathing equipment. Please refer to other SAE documents for such information. Portable Oxygen System and Protective Breathing Equipment are to be installed to meet the requirements of 25.1447(c) and 25.1439. Also, if portable oxygen equipment is installed, they need to meet the requirements of 14 CFR Part 25, Section 25.1443(d)& (e).
A-10 Aircraft Oxygen Equipment Committee
This ARP is intended to cover the warning, caution, and advisory indicating system required for commercial and military aerospace vehicles.
A-20A Crew Station Lighting Committee
Improved Energy Management System for Airplane Electrical Power2021-01-00083/2/2021
As commercial transport aircraft progress toward a future More Electric Airplane (MEA) there are numerous opportunities to improve energy management of the electrical power system. Improved energy management of the airplane electrical power system not only has the potential to decrease the weight and improve the efficiency of the system, but also to improve system stability and reliability. This paper analyzes re-architecting of an MEA airplane electrical power system in order to better manage the current electrical loads. It also considers the use of new sources of power generation and energy storage that would enable improved energy management for a new improved MEA such as fuel cells, batteries and super capacitors. The analysis uses data associated with current methods for calculating electrical loads and evaluates how the energy management of those loads can be improved with a better understanding of their usage in various flight phases, their criticality, and their power quality requirements. It also investigates how the re-architecting of different loads can be used to improve airplane dispatch reliability and improve system stability. Finally, it examines how the efficiency of various systems, in conjunction with improved energy management, can be used to result in a better controlled, more efficient and reliable airplane. The results of these improvements in energy management are included in new MEA power system architecture to summarize the benefits.
Breit, Joseph Sherman
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
6.0.115 - Legal and Consumer Requirements in ASEAN CountriesSAE-PP-002702/4/2021
South East Asia is one of the regions with highest traffic-related fatality rates worldwide −18.5 fatalities per 100.000 inhabitants-. In response to that, governments of ASEAN countries are currently introducing new regulations, which will help to improve the road safety standards in the region. This paper reviews new safety regulations in force of following ASEAN countries: Singapore, Thailand, Malaysia, Indonesia, Vietnam and the Philippines. General safety trends promote the approach to international standards as well as the adoption of UNECE regulations. In fact, the 1958 agreement was signed by Thailand and Malaysia in 2006. Besides, Malaysia has gradually adopted fifty-three UNECE regulations so far and is currently considering the inclusion of twenty-four more. After the success of other NCAP organizations, the ASEAN NCAP assessment program was established in 2011. This program is powered by the Malaysian Institute of Road Safety Research (MIROS) and the Global New Car Assessment Program (GNCAP). Its purpose is to encourage manufacturers to improve the safety performance of their products by providing consumers with reliable and objective information about the protection provided by these vehicles. Vehicles launched in Cambodia, Indonesia, Lao People's Democratic Republic, Malaysia, Philippines, Singapore, Thailand and/or Vietnam can be tested, assessed and rated by this organization. The program performs a frontal impact test at 64 km/h and 40% overlap to analyze, through objective and subjective methods; the protection provided to both adult and child occupants. Scores are weighted and translated to a star rating. This paper also analyzes these assessment methods, emphasizing the innovations incorporated by this new program. Practical cases are explained to better illustrate the functioning of this new system. Safety regulations are the mainstay of road safety. Thus, the introduction of new or existing safety regulations represents a remarkable achievement but also a necessary step towards safer roads. Additionally, initiatives such as NCAP programs have also proved their effectiveness in other markets as well as its contribution to the implementation of new and safer technologies.
Mutagaana, Festo
Particle Swarm Optimization with Required Time of Arrival Constraint for Aircraft TrajectorySAE-PP-002552/3/2021
Global warming has motivated the aeronautical industry to develop new technologies that will reduce polluting emissions. A direct way to achieve this goal is to reduce fuel consumption. Reference trajectory optimization contributes to this goal by guiding aircraft to zones where meteorological conditions are favorable to execute their required missions and thereby to reduce flight costs. In this paper, the reference trajectory was optimized in terms of geographical position, altitude, and speed, by taking into account a required time of its arrival constraint and weather conditions. The algorithm assumes that there is no traffic and that the aircraft can fly anywhere in the search space. The search space was modeled in the form of a unidirectional weighted graph, fuel burn was computed using a numerical model, and the weather forecast was taken into account. The methodology utilized in this paper to determine the most economical combinations of parameters that delivered the optimal trajectory was inspired by the particle swarm optimization algorithm. Results showed that the algorithm provided acceptable solutions under traffic management constraints. It was observed that the developed algorithm was able to save up to 9.1% (6800 kg) of fuel burn when there was no RTA constraint for flight trajectories and up to 1.8% (600 kg) of fuel against real, as-flown trajectories with an RTA constraint of +/- 30 seconds. Because of the nature of the Particle Swarm Optimization Algorithm, the local best trajectories are extracted and provided as a Trajectory Option Set which is similar in cost as the optimal trajectory.
Anthony, Lindsay
062 - An Investigation on the Auto-Ignition of Fuel-Air Mixture Induced by Release of Oil-Fuel Droplets from Cylinder-Liner Using Multi-Zone ModelSAE-PP-002011/30/2021
This study investigated effects of gas inhomogeneity induced by droplets of fuels and oils on the auto ignition timing and temperature in the direct-injection spark ignition (DISI) engine by means of detailed numerical calculation using multi zone model. Recent researchers pointed out that droplets are made of fuels and oils which mix on the cylinder liner and released from the cylinder liner [1]. During the compression stroke released droplets reach the auto ignition temperature before flame propagation induced by spark ignition. It is called Pre-ignition. In combustion chamber, there is inhomogeneity caused by temperature and mixture distribution. In this study, the effects of gas inhomogeneity produced by droplet on the auto ignition timing and temperature have been investigated using Multi-Zone model of CHEMKIN-PRO by changing initial temperature and initial equivalence ratio. Especially, the volume of first ignition zone is focused on. As for fuels, this study used n-heptane to observe the impacts which the gas inhomogeneity has on low-temperature heat release (LTHR). As for calculation conditions, 15 zones model were assumed. Based on the assumption that the volume of the droplets from cylinder-liner is not always constant, ignition delay time and ignition temperature of mixture were confirmed, changing the volume of first ignition zone. Consequently, we found that the volume of first ignition zone affects the auto-ignition of air-fuel mixture and there is possibility to lead to cause Pre-ignition.
Mutagaana, Festo
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
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
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