Browse Topic: Aircraft certification

Items (148)

System Process Assurance Plan (SyPAP) Template - ARP4754A - AFuzion

ARP4754A_PL_00108/13/2021

Job Aid for Aircraft Certification for ARP4754A Reviews - AFuzion

ARP4754A_CK_00208/12/2021

Generalizing Aspects of System Safety to Broaden Applicability

2021-01-003703/02/2021

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

High-Fidelity Sonic Boom Propagation Tool

TBMG-3848402/01/2021

The primary challenge with supersonic flight remains the mitigation of the sonic boom to levels that will be acceptable to humans on the ground. As industry progresses towards realizing a commercial supersonic aircraft, the push from regulators to reduce noise levels has intensified. Innovators at NASA Langley Research Center have developed a system for predicting sonic boom propagation of supersonic aircraft. The sBOOMTraj tool enables efficient computation and mitigation of sonic boom loudness across the entire duration of a flight mission.

Aircraft Asset Lifecycle and Digital Data Standards Overview

AIR7501-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

Aircraft Asset Lifecycle and Digital Data Standards Overview

AIR7501 (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

Unsettled Topics in Unmanned Aerial Vehicle Icing

04/27/2020

Unmanned aerial vehicles (UAVs) are an emerging technology with a large variety of commercial and military applications. In-flight icing occurs during flight in supercooled clouds or freezing precipitation and is a potential hazard to all aircraft. In-flight icing on UAVs imposes a major limitation on the operational envelope. This report describes the unsettled topics related to UAV icing. First, typical UAV applications and the general hazards of icing are described. Second, an overview of the special technical characteristics of icing on autonomous and unmanned aircraft is given. Third, the operational challenges for flight in icing conditions are discussed. Fourth, technologies for ice protection that mitigate the icing hazard are introduced. Fifth, the tools and methods required to understand UAV icing and to develop aircraft with cold-weather capabilities are presented. Finally, an assessment of the current and future regulations regarding icing on UAVs is provided.Icing is a key

Hann, Richard, Johansen, Tor A.

User’s Manual for Certification of Aircraft Electrical/Electronic Systems for the Indirect Effects of Lightning

ARP5415B (Current)03/05/2020

This ARP provides detailed information, guidance, and methods in support of the Federal Aviation Administration (FAA) Advisory Circular (AC) 20-136. AC 20-136 provides a means, but not the only means, for demonstrating compliance with Title 14 of the Code of Federal Regulations (14 CFR) 23.1306 (Amendment 23-61), 23.2515 (Amendment 23-64), 25.1316, 27.1316, and 29.1316. It is also intended for this ARP to provide the same information, guidance, and methods, to the European Aviation Safety Agency (EASA) certification specifications CS 23.1306 (Amendment 23/4), 23.2515 (Amendment 23/5), 25.1316, 27.1316, and 29.1316, and associated Acceptable Means of Compliance (AMC) 20-136. This ARP provides references relevant to identifying: (1) acceptance criteria for the indirect effects of lightning compliance approaches, (2) verification (analysis and test) methods including those associated with multiple stroke and multiple burst, (3) recommended design options to optimize needed system immunity

AE-2 Lightning Committee

Safety Assessment of General Aviation Airplanes and Rotorcraft in Commercial Service

ARP5151A (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

Air Cargo Pallets - Utilization Guidelines

ARP5486 (Current)04/01/2019

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

Highly Efficient Civil Aviation, Now via Operations - AAR and Challenges

2018-01-192510/30/2018

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

Constructing Development Assurance Plan for Integrated Systems

AIR6218 (Current)10/22/2018

This SAE Aerospace Information Report (AIR) supplements ARP4754A by identifying the crucial elements to be considered when constructing the development assurance plans described in Chapter 3 (Development Planning) of ARP4754A for integrated systems. This AIR presents a collection of lessons learned from past certification programs involving integrated systems. This AIR is not guidance for system integration technologies.

S-18 Aircraft and Sys Dev and Safety Assessment Committee

AS36100 Background and Development Record

AIR36108 (Current)10/18/2018

This Aerospace Information Report (AIR) provides a record of the development by SAE AGE-2A Air Cargo Sub-Committee of Aerospace Standard AS36100, Air Cargo Unit Load Devices — Performance Requirements and Test Parameters, published 2005-02, and its revision A published 2006-04, intended as a technical reference for airworthiness approval of air cargo unit load devices (pallets, nets and containers) to be loaded with either baggage or freight on board civil transport aircraft, and to partly supersede previously used NAS 3610, Cargo unit load devices - Specification for — [ Revision 10, 1990, referenced in TSO C90(c) ].

AGE-2 Air Cargo

Networked In-Flight Validation Environment for Air Traffic Management Concepts

TBMG-2798312/01/2017

Modernization of the National Airspace System (NAS) will involve future air traffic management (ATM) concepts of operation and technology frameworks that rely on the automated exchange of information between aircraft, and between aircraft and ground-based air traffic control systems. In-flight validation is critical to the acceptance and ultimate implementation of these concepts, so an approach and enabling infrastructure are needed to reduce the costs of flight tests. The approach and infrastructure must also support refinement and validation of interoperability standards for enabling communications and surveillance technologies. The innovation described here is a concept to develop an in-situ test environment for advanced ATM concepts by leveraging existing computing and network infrastructure and existing simulations of future surveillance equipage.

Cargo Restraint Straps – Utilization Guidelines

ARP5595B (Current)11/13/2017

This Aerospace Recommended Practice aims at providing general utilization guidelines and calculation methods adequate to guarantee the effectiveness and ultimate load strength of tie-down/lashing arrangements performed to restrain cargo on board civil transport aircraft during flight: a Cargo loaded and tied down onto airworthiness approved air cargo pallets, themselves restrained into aircraft lower deck, main deck or upper deck cargo systems meeting the restraint requirements of air cargo pallets approved in accordance with NAS 3610 or AS36100, or b Additional tie-down on aircraft structure when necessitated by pallet maximum gross mass or centre of gravity location, or c Individual pieces of cargo, or pieces of cargo placed onto an unrestrained (“floating”) pallet into either lower deck, main deck or upper deck containerized cargo compartments of an aircraft, or d Individual pieces of load loaded in non-containerized (bulk loaded) baggage or cargo compartments.

AGE-2 Air Cargo

Minimum Performance Standard for Anticollision Light Systems

AS8017D (Current)08/24/2017

This SAE Aerospace Standard (AS) establishes minimum performance standards for new equipment anticollision light systems. This Aerospace Standard defines minimum light intensity in terms of "effective intensity" as defined in paragraph 3.5 of this standard and specified vertical and horizontal directions about the longitudinal and vertical axis of the airplane. It will also define flash rate and color for the anticollision light system. It is not intended that this standard require the use of any particular light source such as Xenon, LED or any other specific design of lamp.

A-20B Exterior Lighting Committee

Metallic Materials Properties Development and Standardization (MMPDS) Handbook - 12

B-98407/01/2017

The Metallic Materials Properties Development and Standardization (MMPDS) Handbook is an accepted source for metallic material and fastener system allowables, recognized by the Federal Aviation Administration (FAA), all departments and agencies of the Department of Defense (DoD), and the National Aeronautics and Space Administration (NASA), within the limitations of the certification requirements of the specific government agency. 2017 saw the release of MMPDS-12, superseding MMPDS-11 and prior editions of the MMPDS, as well as all editions of its predecessor MIL-HDBK-5. The MMPDS Handbook is revised regularly to ensure that reliable, statistically-based design properties are available for as many mature materials and/or product forms as possible. Changes specific to this version, MMPDS-12, include: • Revision of modulus (chapter 5) • Re-evaluation of some fatigue curves (chapter 6) • Update of shear strength basis footnotes (chapter 8) • Changes in strain rate requirement for full

Replacement and Modified Brakes and Wheels

ARP1619B (Current)10/21/2016

This SAE Aerospace Recommended Practice (ARP) defines recommended planning and substantiation procedures and associated reviewing and approval processes to confirm that proposed changes do not compromise the demonstrated safety of the originally certified aircraft, and performance and aircraft compatibility are appropriately addressed in aircraft documentation. Successful demonstration also requires that failure modes be identified and mitigation provided for each. These procedures apply to modifications made by the original component or assembly supplier as well as approval of an alternate supplier.

A-5A Wheels, Brakes and Skid Controls Committee

Research on the Quad Tilt Wing Future Civil VTOL Transport

2016-01-205509/20/2016

JAXA (Japan Aerospace Exploration Agency) has been conducting a research on a future commercial tilt wing VTOL (Vertical TakeOff and Landing) transport under JAXA's "Sky Frontier" Program aiming to develop technologies for aircraft innovation. The research focuses on QTW (Quad Tilt Wing) civil VTOL transport, which features tandem tilt wings with propellers mounted at the mid-span of each wing. The goals of the research in the present phase are to propose a concept of a QTW business VTOL transport system and to pursue the essential technologies development such as OEI (One-Engine-Inoperative) safe recovery, transition flight control and cruise efficient aerodynamic design. Nine passengers business QTW concept was designed and trade-off analysis of the propulsion system architecture for OEI safety was conducted. The result suggests the architecture having no cross-shaft mechanism with auto-failure-compensation is the most effective in terms of the system weight and operating cost

Muraoka, Koji, Hirabayashi, Daisuke, Sato, Masayuki, Aoki, Yoshihisa

Wearable Technologies as a Path to Single-Pilot Part 121 Operations

2015-01-244009/15/2015

Labor costs rank second only to fuel in expenses for commercial air transports. Labor issues are a growing concern in the airline industry, with an impending worldwide pilot shortage. One solution proposed and requested by some of the industry leaders is to allow a single flight crew member to operate the aircraft. Safety concerns represent the dominant barrier to single-pilot Part 121 operations. The FAA and Congress consistently demonstrate a bias toward conservatism in their regulation of airlines and commercial aircraft. Bureaucrats and the general public fall prey to isolated news stories that highlight pilot error and anchor their viewpoint on further regulating a two-person crew. Yet, in an alarming spate of recent airline accidents, the presence of multiple crewmembers did nothing to prevent, and actually may have contributed to, the crash. Technology is not the problem. The real challenge is to convince Federal regulators and the flying public that Part 121 operations can be

Moehle, Robert, Clauss, Jason

Reduced Order Model Approach for Efficient Aircraft Loads Prediction

2015-01-256809/15/2015

Flight loads calculations play a fundamental role in the development and certification of an aircraft and have an impact on the structural sizing and weight. The number of load cases required by the airworthiness regulations is in the order of tens of thousands and the analysis must be repeated for each design iteration. On large aircraft, CS-25 explicitly requires taking into account for loads prediction, airframe flexibility, unsteady aerodynamics and interaction of systems and structure, leading to computationally expensive numerical models. Thus there is a clear benefit in speeding-up this calculation process. This paper presents a methodology aiming to significantly reduce the computational time to predict loads due to gust and maneuvers. The procedure is based on Model Order Reduction, whose goal is the generation of a Reduced Order Model (ROM) able to limit the computational cost compared to a full analysis whilst retaining accuracy. The method is applied to a commercial

Castellani, Michele, Lemmens, Yves, Cooper, Jonathan

Test Requirements and Means for Commercial Aircraft Hydraulic Systems

ARP6200 (Current)10/08/2014

This SAE Aerospace Recommended Practice (ARP) describes the recommended tests and their associated test means for commercial aircraft hydraulic systems at the system level that are required to demonstrate compliance with the 14 CFR Part 25 and EASA CS 25 airworthiness regulations, and to show that the required level of maturity at the aircraft entry into service (EIS) has been achieved.

A-6A1 Commercial Aircraft Committee

Weight Analysis for Low-Speed and Sun-Powered Aircraft

2014-36-050809/30/2014

One of the critical tasks of aircraft design is the definition of mass of aircraft's main items, and the aircraft mass distribution. Depending on the type of aircraft (e.g. commercial, general aviation, highly-maneuverable) different types of mass distribution data or trend curves are available; and in general these curves are based on the existing aircraft. But some lack of data is noticeable in terms of solar aircraft, i.e. the available information in terms of mass trends does not fulfill the needs of the designers of this type of aircraft. Considering this perspective, the main motivation of this study is to provide some information, in terms of mass trends and mass analysis for sun-powered aircraft, which could fill part of the gap, and stimulate other efforts in the same direction. Through this work, studies of mass breakdown of different examples of sun-powered aircraft are presented. The values have been obtained directly or estimated from the available data of aircraft

Barbosa, Luciano Magno Frágola, Andrade de Oliveira, Paulo Henriques Iscold

Lithium Battery Powered Portable Electronic Devices

AIR5561 (Current)10/04/2013

This SAE Aerospace Information Report (AIR) is intended to cover any type of portable electronic device, powered by a rechargeable lithium battery that has application in operating the aircraft. This includes devices such as laptop computers, electronic tablets, and electronic book-reading devices, used as Electronic Flight Bags (EFBs), and similar applications.

AE-7B Power Management, Distribution and Storage

Regulatory and Standardization Process for Unconventional Aircraft in Light UAV Segment

2013-01-210309/17/2013

In this paper the regulatory and standardization aspects regarding the light UAV segment are described reporting main steps and activities carried out during the FP7 European SkyMedia funded project. With respect to the Unmanned Aircraft Vehicle regulation achievements, a detailed process conducted beside the Italian Flight Regulation Authority (ENAC) is reported emphasizing the key points that led to receive multiple Permit to Fly for Nimbus novel hybrid UAV platform, the first case in Italy in the category of “light UAV”. With specific reference to the UAV segment, after showing the complex procedure defined with such Authority to receive authorization to fly for project final demo, some light on the future perspectives for light UAV regulation will be provided underlining efforts and contributions to define a clear track on the UAV development in civil applications. In this context, further experimental procedures can be implemented in the next future to extend such procedures to

Grimaccia, Francesco

Preforming of a Fuselage C-Shaped Frame Manufactured by Resin Transfer Molding

2013-01-221409/17/2013

The need for efficient manufacturing approaches has emerged with the increasing usage of composites for structural components in commercial aviation. Resin Transfer Molding (RTM), a process where a fiber preform is injected with resin into a closed tool, can achieve high fiber content required for structural components as well as improved dimensional accuracy since all surfaces are controlled by a tool surface. Moreover, RTM is well suited for parts that can be standardized throughout the aircraft, such as a fuselage frames and stringers. The objective of this investigation is to develop a preforming approach for a C-Shaped Fuselage frame. Two approaches are proposed: tri-axial braiding and hand lay-up of Non-Crimp Fabrics. The fiber architecture of the basic materials as well as the complete preforms is explained. The necessary preforming operations are detailed. The quality control measurement of fiber orientation and thickness are presented. A relation between the fabric lay-up

Laberge Lebel, Louis, Trudeau, Paul

Electromagnetic Protection Hazards on Composite versus Metallic Aircraft

2013-01-215709/17/2013

The lightning represents a fundamental threat to the proper operation of aircraft systems. For aircraft protection, Electromagnetic Compatibility requires conductive structure that will provide among all, electromagnetic shielding and protection from HIRF and atmospheric electricity threat. The interaction of lightning with aircraft structure, and the coupling of induced energy with harnesses and systems inside the airframe, is a complex subject mainly for composite aircraft. The immunity of systems is governed by their susceptibility to radiated or conducted electromagnetic energy. The driving mechanism of such susceptibility to lightning energy is the exposure to the changing magnetic field inside the aircraft and IR voltage produced by the flow of current through the structural resistance of the aircraft. The amplitude of such magnetic field and IR voltage is related to the shielding effectiveness of the aircraft skin (wiremesh, composite conductivity). However, it is also known

Moupfouma, Fidele, Klim, Zdzislaw, Skorek, Adam

Effects of Hanging Loads (e.g., GOH) on ULD Performance

AIR4359 (Historical)08/12/2013

This SAE Aerospace Information Report (AIR) provides information on the subject of Air Mode containers used for transporting “Hanging Loads” such as Garment-On-Hangers (GOH), or other roof supported cargo. It suggests considerations and recommendations for roof loaded containers to transport hanging loads efficiently and safely by air and to protect the aircraft floor and cargo system from damage due to overload conditions.

AGE-2 Air Cargo

Air Cargo Unit Load Devices – Center of Gravity Control Methods

ARP36103A (Current)11/21/2012

This SAE Aerospace Recommended Practice (ARP) provides the industry agreed methods to keep the center of gravity (C.G.) location of loaded air cargo Unit Load Devices (ULDs) within the maximum horizontal and vertical limits allowed by their airworthiness approval.

AGE-2 Air Cargo

The Necessity to Perform a “Traditional” Fault Tree Analysis Process when Conducting a Model-based Safety Assessment

2012-01-213010/22/2012

Fault tree analyses and the associated safety assessment process plays an essential role in demonstrating acceptable avionic system compliance to the system safety requirements derived from safety related regulations associated with the civil aircraft certification process (e.g. 14CFR/CS §25.1309). SAE ARP4754A and SAE ARP4761 are established industry guidelines for the safety process and fault tree methodology applicable to civil aircraft certification based on techniques which have now been in use for decades. System model-based techniques, used for some time in system and software development, are now being applied in the safety assessment process. These system behavior models of functions with their associated dependencies and assignments have been supplemented with failure modes and effects to “automatically” generate fault tree like outputs. These system model-based fault trees are intended to become integral to the safety assessment process. This paper contrasts the “traditional

Fritz, Klaus, Kurz, Nikolaus, Peterson, Eric

External Software Loading of Electronic Engine Controls

ARP4714A (Current)09/25/2012

This paper presents guidelines for development of a procedure for external software loading of an electronic engine control (EEC) for a commercial application, on-wing or in a qualified service shop. This paper makes the following assumptions: a The EEC is designed to accept external software loading. b The EEC is certified as part of an engine. c The support equipment is qualified in accordance with procedures set forth by the engine (and aircraft, if necessary) certifying authority if the EEC cannot detect an integrity violation of the loaded program. d The software to be loaded has been approved by the engine and aircraft certifying authorities. e One or more configurations of EEC hardware has been identified for each version of software which is to be loaded in the EEC. It is appropriate to use these guidelines in the initial development phase, although the certification issues would not be applicable. Approval as used herein means approval by the engine (and aircraft, if necessary

E-36 Electronic Engine Controls Committee

Cargo Shoring Guidelines

ARP5596B (Current)01/05/2012

This SAE Aerospace Recommended Practice (ARP) specifies guidelines for calculating and performing shoring (load spreading) required on board civil transport aircraft whenever a piece of cargo to be carried exceeds the aircraft's maximum allowable limits in area load, running load, or both. It provides both the engineering methods needed to properly design a shoring arrangement, and the main practical dos and donts known from experience to ensure its effectiveness in protecting the aircraft's structure against overload.

AGE-2 Air Cargo

AS36100 Background and Development

AIR36107A (Current)11/23/2011

This SAE Aerospace Information Report (AIR) provides a record of the development by SAE AGE-2A Air Cargo Sub-Committee of Aerospace Standard AS36100, Air Cargo Unit Load Devices - Performance Requirements and Test Parameters, published 2005-02, intended as a technical reference for airworthiness approval of air cargo unit load devices (pallets, nets and containers) to be loaded with either baggage or freight on board civil transport aircraft, and to partly supersede previously used NAS 3610, Cargo unit load devices - Specification for - [Revision 10, 1990, referenced in TSO C90c].

AGE-2 Air Cargo

Cargo Restraint Straps - Utilization Guidelines

ARP5595A (Historical)11/04/2011

This Aerospace Recommended Practice aims at providing general utilization guidelines and calculation methods adequate to guarantee the effectiveness and ultimate load strength of tie-down / lashing arrangements performed to restrain cargo on board civil transport aircraft during flight: a cargo loaded and tied down onto airworthiness approved air cargo pallets, themselves restrained into aircraft lower deck, main deck or upper deck cargo systems meeting the restraint requirements of air cargo pallets approved in accordance with NAS3610 or AS36100A, or b additional tie-down on aircraft structure when necessitated by pallet maximum gross mass or CG, or c individual pieces of cargo, or pieces of cargo placed onto an unrestrained (“floating”) pallet into either lower deck, main deck or upper deck containerized cargo compartments of an aircraft, or d individual pieces of load loaded in non containerized (bulk loaded) baggage or cargo compartments.

AGE-2 Air Cargo

Air Cargo Unit Load Devices – Reference Documents

AIR36105A (Historical)11/04/2011

The present Aerospace Information Report (AIR) provides a list of the main government regulations, SAE and international standards, and standing industry recommendations applying to air cargo unit load devices (pallets, nets and containers) to be loaded with either baggage or freight on board civil transport aircraft.

AGE-2 Air Cargo

Flight Parameter Estimation for Augmented Flight Control System Autonomy

2011-01-280110/18/2011

In the framework of the aircraft global optimization, for future and upcoming programs, current research interests include more Electrical Flight Control System (EFCS) autonomy for a more easy-to-handle aircraft. A possible solution is to increase the number of redundant flight parameter sensors but to the detriment of the aircraft weight and so to the cost and performances. This paper proposes an algorithm using PLS (Partial Least Squares) to estimate a flight parameter from independent sensor measurements. The estimates are then used as so-called “software” or “virtual” sensors, allowing aircraft weight saving. This algorithm is based on an iterative processing and thus can be used in real time in the embedded flight control computer. Furthermore, the resulting flight parameter estimates can be used to detect failures. Different detection strategies are proposed and results show that this method can lead to robust detections.

Cazes, Florian, Mailhes, Corinne, Chabert, Marie, Goupil, Philippe, Dayre, Rémy, Le Berre, Hervé

Advanced Diagnosis for Sustainable Flight Guidance and Control: The European ADDSAFE Project

2011-01-280410/18/2011

The state-of-practice for aircraft manufacturers to diagnose guidance & control faults and obtain full flight envelope protection at all times is to provide high levels of dissimilar hardware redundancy. This ensures sufficient available control action and allows performing coherency tests, cross and consistency checks, voting mechanisms and built-in test techniques of varying sophistication. This hardware-redundancy based fault detection and diagnosis (FDD) approach is nowadays the standard industrial practice and fits also into current aircraft certification processes while ensuring the highest level of safety standards. In the context of future “sustainable” aircraft (More Affordable, Smarter, Cleaner and Quieter), the Electrical Flight Control System (EFCS) design objectives, originating from structural loads design constraints, are becoming more and more stringent. The main issue is weight saving as this improves aircraft performance (e.g. consumption, noise, range) and

Goupil, Philippe, Marcos, Andres

Longitudinal Handling Qualities of Conventional and Unconventional Aircraft Configurations

2011-01-276210/18/2011

During the conceptual design phase, the aircraft stability and control derivatives (aerodynamic coefficients) can be estimated by using fast computational means. Aerodynamic potential codes like the Vortex Lattice Method (VLM) or the Doublet Lattice Method (DLM) are very easy to use and are capable of estimating these coefficients accurately as well as providing remarkable insight into wing aerodynamics and components interaction. Compared to the VLM, the DLM (originally used for aeroelastic computations) allows prediction of the steady as well as unsteady stability and control derivatives. The relationships involving these coefficients and the airplane's dynamic behaviour are well known, like for example the one relating the pitch damping derivative and the damping ratio of the Short Period mode. Previous research work (see references 1 and 3 for further details) based on panel methods, has modelled analytically the rigid aircraft aerodynamic coefficients, leading to an interesting

Gonzalez, Oscar, Bazile, Jérôme

ARP4754A/ ED-79A - Guidelines for Development of Civil Aircraft and Systems - Enhancements, Novelties and Key Topics

2011-01-256410/18/2011

ARP4754A/ED-79A guidelines addresse the development cycle for aircraft and systems that implement aircraft functions. The current trend in system design is an increasing level of integration between aircraft functions and the systems that implement them. While there can be considerable value gained when integrating systems with other systems, the increased complexity yields increased possibilities for errors, particularly with functions that are performed jointly across multiple systems. Following the Aviation Rulemaking Advisory Committee (ARAC) recommendations to respond to this increased integration which referenced ARP4754/ED-79 in advisory materials for compliance to 14CFR/CS 25.1309 (see AMC 25.1309, published in 2002 and AC25.1309-Arsenal draft) the use of ARP4754A/ED79A in aircraft certification has become increasingly widespread. This presentation constitutes a comparison between the documents SAE [1] / EUROCAE [2] and SAE [3] / EUROCAE [4]; it highlights ARP4754A/ED79A

Landi, Alessandro, Nicholson, Mark

Minimum Performance Standard for Anticollision Light Systems

AS8017C (Historical)06/20/2011

This SAE Aerospace Standard (AS) establishes minimum performance standards for new equipment anticollision light systems. This Aerospace Standard defines minimum light intensity in terms of "effective intensity" as defined in paragraph 3.5 of this standard and specified vertical and horizontal directions about the longitudinal and vertical axis of the airplane. It will also define flash rate and color for the anticollision light system. It is not intended that this standard require the use of any particular light source such as Xenon, LED or any other specific design of lamp.

A-20B Exterior Lighting Committee

A Regional Comparison of Icing Conditions in Boundary Layer Clouds

2011-38-002106/13/2011

A large database is being created from icing flight programs completed by aircraft manufacturers for certification and by the NASA-Glenn Research Center for basic research. Although not yet complete, this database already provides an excellent opportunity to study aircraft icing conditions sampled in a wide variety of environments across eastern Canada and most of the United States, including Alaska. In this study, the focus is a comparison of conditions found within boundary-layer stratocumulus icing clouds over the Great Lakes, Pacific Northwest and Alaskan Interior. The clouds will be characterized in terms of temperature, liquid water content, median volumetric diameter, and drop concentration. Critical factors driving these parameters will be discussed.

Bernstein, Ben C., Mcdonough, Frank, Wolff, Cory

Air Cargo Unit Load Devices - Reference Standards

AIR36105 (Historical)04/06/2011

The present Aerospace Information Report (AIR) provides a list of the main government regulations, SAE and international standards, and standing industry recommendations applying to air cargo unit load devices (pallets, nets and containers) to be loaded with either baggage or freight on board civil transport aircraft.

AGE-2 Air Cargo

Aircraft Modification and Integration Enables SOFIA to Fly

TBMG-658401/01/2010

Man Machine Interface Requirement Validation in Military Aircraft Certification

2009-01-311211/10/2009

Increasing electronic controls in aircraft flight deck, especially in military aircrafts, demands special attention from crew workload assessment and human error analysis point of view. The main objective for the Authority is to validate that the crew workload is adequate for different and complicated military missions. Besides, human error analysis is a regulatory requirement in Airworthiness Certification of airplanes. Human errors need to be observed during simulated operational use of novelties and analyzed later (during the debriefing with pilots or during the results analysis). The main objective during the debriefing is to identify their causes, their consequence, their criticality and the current safety barriers in terms of human errors management. Simulators offer wide range of capability to identify the problems in early stages of the design. Degree of fidelity needed on evaluation media is related with the complexity of the military mission and project budget. Especially in

UAV Operation, Crash Analysis, and Measurement of Particle Concentrations above a Forest and Surrounding Farmland

2009-01-312911/10/2009

The Nucleation In ForesTs (NIFTY) campaign was conducted in the Morgan Monroe State Forest (MMSF) during the month of May 2008. The objectives of this campaign were to understand the principal mechanisms of nucleation, the limitations of nucleation and growth, the spatial extent of nucleation events, subsequent particle growth after nucleation in MMSF, and the link between particle nucleation and breakdown of the nocturnal boundary layer which enhances vertical mixing. This paper discusses the use of a UAV to perform selected aspects of this project, mission that was accomplished by a team of students during the campaign, and analysis of a crash which concluded the mission.

Valyou, Daniel, Dhaniyala, Suresh, Marzocca, Pier, Hopke, Philip, Nallathamby, Punith D., Pryor, Sara C.

Use Of TC ODAS May Cause Unforeseen Litigation Turbulence For Designers

2008-01-225708/19/2008

Administrative burdens greatly restrict the availability of the FAA to participate fully in the certification process of new aircraft. Recent TC ODA regulations and a corresponding FAA Order authorizing manufacturers to assume a greater role in new aircraft certifications may lead to new and interesting product liability skies ahead for the aircraft industry. This article reviews the legal foundation of product defect lawsuits against the aircraft industry and proposes several risk management strategies to strengthen your litigation defenses.

Mattioli, Mark L., Wickersham, Richard B.

Jam-Free, Fail-Safe Flight Control System with Asymmetric Load Alleviation Capability

2008-01-226308/19/2008

A dual cable flight control Driving System presented here functions the same way as current flight control systems in normal operation. However, if a jam occurs this System automatically transfers the command to the non-jammed side without pilot’s intervention. It enables either pilot to continue controlling the aircraft despite jamming, with no extra effort, no delay in action, and no threat of over-controlling the aircraft as a result of jamming. Current designs always require pilot’s action involving critical time delays in controlling the aircraft. For the same flight regime this System retains the same pilot effort force and the same cockpit control deflection as the non-jammed system. If unjamming occurs (icing condition) it automatically reverts back to normal operation without any pilot’s intervention. In normal operation the System is able to automatically balance-out asymmetric loads between surfaces thus leading to some load reduction and possible weight saving. It is also

Djuric, Mihailo (Mimi) P.

Commercial Aircraft Certification for ETOPS Operations

2007-01-252111/28/2007

The ETOPS (Extended Range Operation with Two Engine Airplanes) certification is required for two engine airplanes which operate over a route that contains a point farther than one hour flying time at the normal one-engine inoperative cruise speed from an adequate airport. ETOPS regulations are applicable to routes over water as well as remote land areas. This paper summarizes the ETOPS certification process for Commercial Aircraft, including the following topics: Brief ETOPS history; Scope and Applicability; Regulations and Guidelines Applicable for ETOPS Certification; Relevant Aircraft Manufacturer Activities; Aircraft Operator Responsibilities

Martins, Fabio Saunier, Nerosky, Luiz Augusto Rodrigues, Fernandez, Felipe Eudes Pontes, Senna, José Carlos Silva Menezes

Certification of Aircraft Electrical/Electronic Systems for the Indirect Effects of Lightning

ARP5413A (Current)

03/21/2007

AE-2 Lightning Committee

The 747-400 Dreamlifter - Overview & Mission

2007-01-388801/17/2007

The development of new commercial airliners is a very risky proposition. To get it right, airframe manufacturers must balance new technologies and manufacturing methods with global participation and business considerations. The 787 is Boeing's popular new wide body aircraft incorporating state of the art composites design and manufacturing methods. But new technology alone is not enough. A new logistics system was needed to integrate global partners in order to fully benefit from new technologies. The Boeing 747-400 Dreamlifter is a special purpose 747-400 modified to transport Boeing 787 airplane components through various stages of manufacturing.

Funke, Christopher C.

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