Supporting the ARP4761 Safety Assessment Process with AADL
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A Zonal Safety Analysis Methodology for Preliminary Aircraft Systems and Structural Design
A Zonal Safety Analysis Methodology for Preliminary Aircraft Systems and Structural Design Chen, Z. and Fielding, J. P. School of Aerospace, Transport and Manufacturing, Cranfield University ABSTRACT Zonal Safety Analysis (ZSA) is a major part of the civil aircraft safety assessment process described in Aerospace Recommended Practice 4761 (ARP4761). It considers safety effects that systems/items installed in the same zone (i.e. a defined area within the aircraft body) may have on each other. Although the ZSA may be conducted at any design stage, it would be most cost-effective to do it during preliminary design, due to the greater opportunity for influence on system and structural designs and architecture. The existing ZSA methodology of ARP4761 was analysed but it was found to be more suitable for detail design rather than preliminary design. The authors therefore developed a methodology that would be more suitable for preliminary design and named it the Preliminary Zonal Safety Analysis (PZSA). This new methodology was verified by means of the use of a case-study, based on the NASA N3-X project. Several lessons were learnt from the case study, leading to refinement of the proposed method. These lessons included focusing on the positional layout of major components for the zonal safety inspection, and using the Functional Hazard Analysis (FHA)/Fault Tree Analysis (FTA) to identify system external failure modes. The resulting PZSA needs further refinement, but should prove to be a useful design tool for the preliminary design process. _____________________________________ INTRODUCTION This paper outlines the development of a methodology, hereafter referred to as the Preliminary Zonal Safety Historically, system safety analysis was primarily based Analysis (PZSA). -
Before You Continue
NASA/CR–2015-218982 Application of SAE ARP4754A to Flight Critical Systems Eric M. Peterson Electron International II, Inc., Phoenix, Arizona November 2015 NASA STI Program . in Profile Since its founding, NASA has been dedicated to the CONFERENCE PUBLICATION. advancement of aeronautics and space science. The Collected papers from scientific and technical NASA scientific and technical information (STI) conferences, symposia, seminars, or other program plays a key part in helping NASA maintain meetings sponsored or this important role. co-sponsored by NASA. The NASA STI program operates under the auspices SPECIAL PUBLICATION. Scientific, of the Agency Chief Information Officer. It collects, technical, or historical information from NASA organizes, provides for archiving, and disseminates programs, projects, and missions, often NASA’s STI. The NASA STI program provides access concerned with subjects having substantial to the NTRS Registered and its public interface, the public interest. NASA Technical Reports Server, thus providing one of the largest collections of aeronautical and space TECHNICAL TRANSLATION. science STI in the world. Results are published in both English-language translations of foreign non-NASA channels and by NASA in the NASA STI scientific and technical material pertinent to Report Series, which includes the following report NASA’s mission. types: Specialized services also include organizing TECHNICAL PUBLICATION. Reports of and publishing research results, distributing completed research or a major significant phase of specialized research announcements and feeds, research that present the results of NASA providing information desk and personal search Programs and include extensive data or theoretical support, and enabling data exchange services. analysis. Includes compilations of significant scientific and technical data and information For more information about the NASA STI program, deemed to be of continuing reference value. -
Quality Assurance, Process Engineer
THOMMEN AIRCRAFT EQUIPMENT Renowned Swiss manufacturer of high precision Aviation Instruments, Air Data Computers, Digital Chronometers and Mission Equipment Established in 1853 under Revue Thommen AG, Thommen Aircraft Equipment Ltd is a renowned Swiss manufacturer of high precision aviation instruments, avionics and mission equipment. The company has celebrated its 100 years anniversary of supplying aviation products to its customers. Thommen Aircraft Equipment AG is currently in the phase of introducing several innovative and exciting products to the market and will gradually increase the general product offering in the course of 2018/2019. To sustain the new company plans, product development, we are looking to hire a skilled and experienced Quality Assurance / Process Engineer – Avionics 100% (m/f) The person will be responsible for leading activities involving Product Lifecycle Management processes. Focused on improving processes and tools, the position is ideal for a candidate seeking a broad technical and business process career. The position offers the opportunity to work as part of a global team which will require flexibility to support activities across multiple time zones for following process development activities. Our culture is to hire only the finest talent and to uphold our values of teamwork, accountability, humor, efficiency, candor and continual improvement. Responsibilities & Tasks • Develop DO-178C and DO-254 process compliance and quality plan, (QAP, SQAP HQAP) • Responsible for reporting assessment and evaluation -
Risk Assesment: Fault Tree Analysis
RISK ASSESMENT: FAULT TREE ANALYSIS Afzal Ahmed+, Saghir Mehdi Rizvi*Zeshan Anwer Rana* Faheem Abbas* +COMSAT Institute of Information and Technology, Sahiwal, Pakistan *Navy Engineering College National University of Sciences and Technology, Islamabad drafzal@ciitsahiwal>edu.pk, 03452325972 ABSTRACT The failure of engineering equipment causes loss of capital as well as human loss, injuries, and stoppage of production line. The hazards can be classified as safe, minor, major, critical and catastrophic Risk analysis or hazard analysis pin points the potential failures of engineering systems and or components when being used.. Failure mode and effects analysis is used to identify hazard and to make system safer. A system is broken down up to level of components and using reliability data the safety or probability of failure of assemblies and the system can be calculated. The failure mode and effects analysis is used with fault tree analysis to point the areas of a complex system where failure mode effect analysis is required. Fault tree analysis (FTA) is a technique which pinpoints any failure or severe accidents. It tells how things fail rather than emphasize on the design performance. It is a logic diagram connecting inputs an outputs using Boolean algebra. This paper shows how FTA can be applied to car carburetor failure and car brake failure. Key words : Risk Management, Reliability, Fault tree, Failure mode INTRODUCTION The world is full risk. We are at risk of accident minor. A failure of an aircraft may cause death when crossing a road or driving. We are at risk to passengers, while a machine may cause living in an apartment not properly designed. -
NASA Fault Tree Handbook with Aerospace Applications
Fault Tree Handbook with Aerospace Applications Version 1.1 FFFaaauuulllttt TTTrrreeeeee HHHaaannndddbbbooooookkk wwwiiittthhh AAAeeerrrooossspppaaaccceee AAAppppppllliiicccaaatttiiiooonnnsss Prepared for NASA Office of Safety and Mission Assurance NASA Headquarters Washington, DC 20546 August, 2002 Fault Tree Handbook with Aerospace Applications Version 1.1 FFFaaauuulllttt TTTrrreeeeee HHHaaannndddbbbooooookkk wwwiiittthhh AAAeeerrrooossspppaaaccceee AAAppppppllliiicccaaatttiiiooonnnsss NASA Project Coordinators: Dr. Michael Stamatelatos, NASA Headquarters Office of Safety and Mission Assurance Mr. José Caraballo, NASA Langley Research Center Authors: NASA Dr. Michael Stamatelatos, NASA HQ, OSMA Lead Author: Dr. William Vesely, SAIC Contributing Authors (listed in alphabetic order): Dr. Joanne Dugan, University of Virginia Mr. Joseph Fragola, SAIC Mr. Joseph Minarick III, SAIC Mr. Jan Railsback, NASA JSC Fault Tree Handbook with Aerospace Applications Version 1.1 FFFaaauuulllttt TTTrrreeeeee HHHaaannndddbbbooooookkk wwwiiittthhh AAAeeerrrooossspppaaaccceee AAAppppppllliiicccaaatttiiiooonnnsss Acknowledgements The project coordinators and the authors express their gratitude to NASA Office of Safety and Mission Assurance (OSMA) management (Dr. Michael Greenfield, Deputy Associate Administrator and Dr. Peter Rutledge, Director of Enterprise Safety and Mission Assurance) and to Mr. Frederick Gregory, NASA Deputy Administrator, for their support and encouragement in developing this document. The authors also owe thanks to a number of reviewers -
Hazard Analysis of Complex Spacecraft Using Systems- Theoretic Process Analysis *
Hazard Analysis of Complex Spacecraft using Systems- Theoretic Process Analysis * Takuto Ishimatsu†, Nancy G. Leveson‡, John P. Thomas§, and Cody H. Fleming¶ Massachusetts Institute of Technology, Cambridge, Massachusetts 02139 Masafumi Katahira#, Yuko Miyamoto**, and Ryo Ujiie†† Japan Aerospace Exploration Agency, Tsukuba, Ibaraki 305-8505, Japan Haruka Nakao‡‡ and Nobuyuki Hoshino§§ Japan Manned Space Systems Corporation, Tsuchiura, Ibaraki 300-0033, Japan Abstract A new hazard analysis technique, called System-Theoretic Process Analysis, is capable of identifying potential hazardous design flaws, including software and system design errors and unsafe interactions among multiple system components. Detailed procedures for performing the hazard analysis were developed and the feasibility and utility of using it on complex systems was demonstrated by applying it to the Japanese Aerospace Exploration Agency H-II Transfer Vehicle. In a comparison of the results of this new hazard analysis technique to those of the standard fault tree analysis used in the design and certification of the H-II Transfer Vehicle, System-Theoretic Hazard Analysis found all the hazardous scenarios identified in the fault tree analysis as well as additional causal factors that had not been) identified by fault tree analysis. I. Introduction Spacecraft losses are increasing stemming from subtle and complex interactions among system components. The loss of the Mars Polar Lander is an example [1]. The problems arise primarily because the growing use of software allows engineers to build systems with a level of complexity that precludes exhaustive testing and thus assurance of the removal of all design errors prior to operational use [2,3] Fault Tree Analysis (FTA) and Failure Modes and Effects Analysis (FMEA) were created long ago to analyze primarily electro-mechanical systems and identify potential losses due to component failure. -
Safety Assessment Processes of ARP4761: Major Revision
Safety Assessment Processes of ARP4761: Major Revision Jim Marko Manager, Aircraft Integration & Safety Assessment 14 November 2018 Presentation Outline • What is changing • ARP4761 Relationship to ARP4754A Development Assurance • New methods • Changes to existing methods • Safety methods other than ARP4761A 14 November 2018 2 ARP4761A Safety Assessment Process What’s happening to ARP 4761? • Revision commenced in early 2012 within the SAE S18 Aircraft & Systems Development and Safety Assessment Committee. • Essentially a near complete revision of the document that is nearing publication. • New processes and analytical methods being added to reflect the trend towards more highly integrated and increasingly complex system designs. • Introduces the concept of Aircraft-Level safety assessment to complement the traditional system-level safety assessment approach. 14 November 2018 3 Current ARP 4761 Rev- New Appendices for ARP 4761 Other Appendices Rev A Developments Functional Hazard Aircraft Functional Hazard Assessment Single Event Effects Assessment AIR 6218 Preliminary System Safety Preliminary Aircraft Safety Assessment Assessment System Functional Hazard Assessment In-Service Safety System Safety Assessment Aircraft Safety Assessment Assessment ARP 5150/5151 FTA, DD, FMEA, Markov Cascading Effects Analysis Common Mode Analysis Development Assurance Assignment Particular Risk Analysis Model Based Safety Assessment Zonal Safety Analysis Contiguous Example Contiguous Example 14 November 2018 4 ARP4761A Safety Assessment Process Interactions ARP 4754A Development Assurance Processes 14 November 2018 5 ARP4761 Relationship to ARP4754A Development Assurance • Modern aircraft architecture is increasingly becoming a “system-of-systems”, where many systems interact with and are dependent upon each other to perform aircraft functional objectives. • The era of having federated systems that can be correctly and completely assessed in silos, independent from other systems, is rapidly closing. -
A Simulation Tool for Extended Dynamic Fault Trees
DFTSim: A Simulation Tool for Extended Dynamic Fault Trees H. Boudali, A.P. Nijmeijer, M.I.A. Stoelinga University of Twente, CS Department, Enschede, NL. hboudali, andre, marielle @cs.utwente.nl { } Keywords: Dependability analysis, dynamic fault trees, simulation computation-time required to solve the DFT. tool, reliability benchmark. A simulation-based approach of standard DFTs has been sug- gested (but not implemented) in [11] as a possible solution tech- Abstract nique. In this paper, we propose DFTSim, a tool for simulating We present DFTSim, a simulation tool for dynamic fault trees (DFT). extended DFTs, where the input DFT file is compatible with the The simulation is carried out by directly sampling the failure distri- Galileo and the Coral textual DFT format. Such compatibility is butions attached to the leaves (called basic events) of the tree and indeed desired because it allows interoperability and integration propagating the failure times upwards in the tree. among these DFT tools. Sampling the distributions of the DFT leaves is however not ob- One of the major problems in DFT simulation-based approaches vious. To sample from the correct distributions, the analytical ex- is to sample from the correct distributions. In order to carry out such pression of the failure distributions of all basic events (BE) must be sampling the analytical expression of the failure distributions of all known. These are indeed known for non-spare BEs; but for spare basic events must be known. Such failure distributions are indeed BEs, they become conditional on the failure of other BEs. Hence, known for non-spare basic events; unfortunately, for spare basic the derivation of the analytical expression of the spares’ failure dis- events the failure distribution becomes conditional on the primary’s tributions and their sampling is not a trivial task. -
An Overview of Fault Tree Analysis (FTA) Method for Reliability Analysis & Life Cycle Cost (LCC) Management
IOSR Journal of Mechanical & Civil Engineering (IOSR-JMCE) ISSN: 2278-1684, PP: 14-18 www.iosrjournals.org An Overview of Fault Tree Analysis (FTA) Method for Reliability Analysis & Life Cycle Cost (LCC) Management Rajkumar B. Patil1, L. Y. Waghmode2, P. B. Chikali3, T. S. Mulla4. 1,3,4 ( Department of Mechanical Engineering ,Dr. J. J. Magdum College of Engineering, Jaysingpur, Shivaji University, Kolhapur, Maharashtra India). 2 ( Department of Mechanical Engineering, Annasaheb Dange College of Engineering and Technology, Ashta, Shivaji University, Kolhapur, Maharashtra(India). Abstract – Reliability analysis plays crucial role in the design process. In order to increase reliability of a system, analysis of failure data is essential. Fault Tree Analysis (FTA) is a method that directly focuses on the modes of failures. FTA is a graphical representation of the major faults or critical failures associated with a product and the causes for the faults and potential countermeasures. This paper presents the FTA of Lathe Machine. Qualitative and quantitative analysis helps to identify critical design parameters, maintenance suggestions. It also includes how reliability analysis fruitful for Life cycle cost management. Keywords – Fault Tree Analysis, FRACAS, Life Cycle Cost, MTBF, MTTF, Reliability Analysis. I.INTRODUCTION Reliability based design focuses on three terms as reliability, availability and maintainability. Reliability is defined to be the probability that the component or system will perform its intended functions for a specified period of time when used under stated operating conditions [1]. In simple words, reliability is nothing but the non-failure of the system over a given period of time. Reliability engineering is a sub-discipline within system engineering. -
Overview of DO-178C
Table of Contents Overview of Section 450.141 ................................................................................2 Overview of Section AC 450.141-1 ........................................................................2 Overview of DO-178C ............................................................................................3 Implementing AC 450.141-1 Using DO-178C.........................................................4 Identification of Computing System Safety Items ................................................... 5 Levels of Criticality ........................................................................................................... 7 Safety Requirements ................................................................................................ 9 Development Processes ........................................................................................ 12 Application Materials ............................................................................................. 21 AC 450.141-1 Process Summary ........................................................................ 22 References ......................................................................................................... 23 List of Tables Table 1 Identification of Computing System Safety Items ......................................... 6 Table 2 Levels of Criticality .......................................................................................... 7 Table 3 Safety Requirements ...................................................................................... -
A Course Material on Maintenance Engineering by Mr. ERSIVAKUMAR
A Course Material on Maintenance Engineering By Mr. E.R.SIVAKUMAR.M.E,(Ph.D), HEAD & ASSOCIATE PROFESSOR DEPARTMENT OF MECHANICAL ENGINEERING SASURIE COLLEGE OF ENGINEERING VIJAYAMANGALAM – 638 056 QUALITY CERTIFICATE This is to certify that the e-course material Subject Code : ME2037 Scubject : Maintenance Engineering Class : IV Year being prepared by me and it meets the knowledge requirement of the university curriculum. Signature of the Author Name: Mr.E.R.SIVAKUMAR.M.E,(Ph.D) Designation: This is to certify that the course material being prepared by Mr.E.R.Sivakumar M.E,(Ph.D) is of adequate quality. He has referred more than five books among them minimum one is from abroad author. Signature of HD Name:Mr.E.R.SIVAKUMAR.M.E,(Ph.D), SEAL CONTENTS SL. PAGE TOPICS NO. NO. SYLLABUS UNIT – I PRINCIPLES AND PRACTICES OF MAINTENANCE PLANNING 1.1 Maintenance Engineering 1 1.1.1.Introduction 1 1.1.2. Maintenance Manager 2 1.1.3.Maintenance Engineering Jobs 2 1.1.4.Definition of Maintenance 2 1.1.5.Purpose of Maintenance 2 1.1.6.Principle Objectives in Maintenance 2 1.1.7.Problems in Maintenance 2 1.2 Basic Principles of maintenance planning 3 1.2.1.Maintenance Planning 3 1.2.2. Planning Objectives 3 1.2.3. Planning Procedures 3 1.2.4.Basic Levels of Planning Process (Depend on The Planning 4 Horizon) 1.2.4.1.Long Range Planning 4 1.2.4.2. Medium-Range Planning 4 1.2.4.3. Short-Range Planning 4 1.3 Objectives and Principles of Planned Maintenance Activity 4 1.4 Importance and benefits of sound Maintenance systems 5 1.5 1.5.1.Maintenance organization 5 1.5.2.Maintenance Organization Objectives and Responsibility 5 1.5.3.Determinants of a Maintenance Organization 6 1.5.4.Maintenance Capacity Planning 6 1.5.5. -
Intro to ARP4754A 140723
Guidelines for Development of Civil Aircraft and Systems Introduction to ARP4754A 23 July, 2014 Avionics Systems Evolution • Early Aviation: mainly mechanical equipment • 1960’s: increased electronic controls • 1970’s: analog equipment supported by low level, simple software DO-178 • 1980’s: integrated digital systems ARP4754 • 1990’s: PLDs, ASICs, FPGAs and other CEH ARP4761 • 2000’s: highly integrated & complex DO-254 ARP4754A systems Esterline Control Systems Introduction to ARP4754A SAE ARP4754 Background • During preparation of DO178B, it was determined that system level information was needed as input to Software Development process. • FAA requested SAE to prepare an ARP for demonstrating regulatory compliance for highly-integrated or complex avionics systems. • A Systems Integration Requirements Task group (SIRT) was formed to draft the ARP, which became ARP4754. Esterline Control Systems Introduction to ARP4754A SAE ARP4754 Background • Since harmonization was deemed highly desirable, representatives of both the FAA and JAA were engaged. • Working group WG-42 was formed to coordinate European input to the SIRT group. • The SIRT group members included those with direct design & support experience in: – Large commercial aircraft – Commuter aircraft – Commercial & general aviation avionics – Jet engines, and – Engine controls Esterline Control Systems Introduction to ARP4754A SAE ARP4754 Background • Formal & informal links with RTCA & SAE committees SC-167, SC-180 and S-18. • 14CFR/CS 25.1309 harmonization working group was involved. • Decision to focus on fundamental principles of certification Vs providing a “very specific list of certification steps” • ARP4754 published in 1996 Esterline Control Systems Introduction to ARP4754A SAE ARP4754A Background • Written / published in Dec 2010 by S-18 & WG- 63 committees.