AAIB Bulletin 1/2014
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Joint Aviation Requirements JAR–FCL 1 ЛИЦЕНЗИРОВАНИЕ ЛЕТНЫХ ЭКИПАЖЕЙ (САМОЛЕТЫ)
Joint Aviation Requirements JAR–FCL 1 ЛИЦЕНЗИРОВАНИЕ ЛЕТНЫХ ЭКИПАЖЕЙ (САМОЛЕТЫ) Joint Aviation Authorities 1 JAR-FCL 1 ЛИЦЕНЗИРОВАНИЕ ЛЕТНЫХ ЭКИПАЖЕЙ (САМОЛЕТЫ) Издано 14 февраля 1997 года ПРЕДИСЛОВИЕ ПРЕАМБУЛА ЧАСТЬ 1 - ТРЕБОВАНИЯ ПОДЧАСТЬ A – ОБЩИЕ ТРЕБОВАНИЯ JAR-FCL 1.001 Определения и Сокращения JAR-FCL 1.005 Применимость JAR-FCL 1.010 Основные полномочия членов летного экипажа JAR-FCL 1.015 Признание свидетельств, допусков, разрешений, одобрений или сер- тификатов JAR-FCL 1.016 Кредит, предоставляемый владельцу свидетельства, полученного в государстве не члене JAA JAR-FCL 1.017 Разрешения/квалификационные допуски для специальных целей JAR-FCL 1.020 Учет военной службы JAR-FCL 1.025 Действительность свидетельств и квалификационных допусков JAR-FCL 1.026 Свежий опыт для пилотов, не выполняющих полеты в соответствии с JAR-OPS 1 JAR-FCL 1.030 Порядок тестирования JAR-FCL 1.035 Годность по состоянию здоровья JAR-FCL 1.040 Ухудшение состояния здоровья JAR-FCL 1.045 Особые обстоятельства JAR-FCL 1.050 Кредитование летного времени и теоретических знаний JAR-FCL 1.055 Организации и зарегистрированные предприятия JAR-FCL 1.060 Ограничение прав владельцев свидетельств, достигших 60-летнего возраста и более JAR-FCL 1.065 Государство выдачи свидетельства 2 JAR-FCL 1.070 Место обычного проживания JAR-FCL 1.075 Формат и спецификации свидетельств членов летных экипажей JAR-FCL 1.080 Учет летного времени Приложение 1 к JAR-FCL 1.005 Минимальные требования для выдачи свиде- тельства/разрешения JAR-FCL на основе нацио- нального свидетельства/разрешения, выданного в государстве-члене JAA. Приложение 1 к JAR-FCL 1.015 Минимальные требования для признания дейст- вительности свидетельств пилотов, выданных государствами не членами JAA. -
Introduction
CHAPTER 1 Introduction "For some years I have been afflicted with the belief that flight is possible to man." Wilbur Wright, May 13, 1900 1.1 ATMOSPHERIC FLIGHT MECHANICS Atmospheric flight mechanics is a broad heading that encompasses three major disciplines; namely, performance, flight dynamics, and aeroelasticity. In the past each of these subjects was treated independently of the others. However, because of the structural flexibility of modern airplanes, the interplay among the disciplines no longer can be ignored. For example, if the flight loads cause significant structural deformation of the aircraft, one can expect changes in the airplane's aerodynamic and stability characteristics that will influence its performance and dynamic behavior. Airplane performance deals with the determination of performance character- istics such as range, endurance, rate of climb, and takeoff and landing distance as well as flight path optimization. To evaluate these performance characteristics, one normally treats the airplane as a point mass acted on by gravity, lift, drag, and thrust. The accuracy of the performance calculations depends on how accurately the lift, drag, and thrust can be determined. Flight dynamics is concerned with the motion of an airplane due to internally or externally generated disturbances. We particularly are interested in the vehicle's stability and control capabilities. To describe adequately the rigid-body motion of an airplane one needs to consider the complete equations of motion with six degrees of freedom. Again, this will require accurate estimates of the aerodynamic forces and moments acting on the airplane. The final subject included under the heading of atmospheric flight mechanics is aeroelasticity. -
Volume 2 – General Navigation (JAR Ref 061) Table of Contents
Volume 2 – General Navigation (JAR Ref 061) Table of Contents CHAPTER 1 The Form of the Earth Shape of the Earth ........................................................................................................................................1-1 The Poles......................................................................................................................................................1-2 East and West...............................................................................................................................................1-2 North Pole and South Pole ...........................................................................................................................1-2 Cardinal Directions........................................................................................................................................1-3 Great Circle...................................................................................................................................................1-3 Vertex of a Great Circle ................................................................................................................................1-4 Small Circle...................................................................................................................................................1-5 The Equator ..................................................................................................................................................1-5 Meridians ......................................................................................................................................................1-6 -
CS-Definitions / Amendment 2
Annex to Decision 2010/014/R European Aviation Safety Agency Definitions and abbreviations used in Certification Specifications for products, parts and appliances CS-Definitions Amendment 2 23 December 2010 Amendment 2 Annex to Decision 2010/014/R CS-Definitions CONTENTS CS—Definitions Definitions and abbreviations used in Certification Specifications for products, parts and appliances PREAMBLE 1 GENERAL DEFINITIONS 2 ABBREVIATIONS AND SYMBOLS C-2 Amendment 2 Annex to Decision 2010/014/R CS-Definitions PREAMBLE CS-Definitions Amendment 2 Effective: 23/12/2010 The following is a list of paragraphs affected by this amendment. General Definitions ETOPS New (NPA 2008-01) CS-Definitions Amendment 1 The following is a list of definitions affected by this amendment. 1. GENERAL DEFINITIONS Aircraft-Supplied Data Created (NPA 04/2005) Aircraft-Supplied Electrical Power Created (NPA 04/2005) Alternate Mode (Engine related definition) Created (NPA 04/2005) Back-up Mode (Engine related definition) Created (NPA 04/2005) Back-up System Created (NPA 04/2005) Control Mode (Engine related definition) Created (NPA 04/2005) Covered Fault Created (NPA 04/2005) Electronic Engine Control System (EECS) Created (NPA 04/2005) Engine Control System Created (NPA 04/2005) Fault (or) Failure Created (NPA 04/2005) Fault (or) Failure Accommodation Created (NPA 04/2005) Full-up Configuration (Engine related definition) Created (NPA 04/2005) Primary Mode (Engine related definition) Created (NPA 04/2005) Primary System Created (NPA 04/2005) Programmable Logic Device (PLD) Created (NPA 04/2005) Propeller Amended to align with CS-P definition of “Propeller System” introduced by NPA 05/2005. Reversible Pitch Propeller Created (NPA 05/2005) Uncovered Fault Created (NPA 04/2005) Variable Pitch Propeller Amended (NPA 05/2005) P-1 Amendment 2 Annex to Decision 2010/014/R CS-Definitions 1. -
Use of the GPS Reciprocal Heading Method for Determining Pitot-Static Position Error in Helicopter Flight Testing
University of Tennessee, Knoxville TRACE: Tennessee Research and Creative Exchange Masters Theses Graduate School 12-2004 Use of the GPS Reciprocal Heading Method for Determining Pitot- Static Position Error in Helicopter Flight Testing Rucie James Moore University of Tennessee, Knoxville Follow this and additional works at: https://trace.tennessee.edu/utk_gradthes Part of the Management and Operations Commons Recommended Citation Moore, Rucie James, "Use of the GPS Reciprocal Heading Method for Determining Pitot-Static Position Error in Helicopter Flight Testing. " Master's Thesis, University of Tennessee, 2004. https://trace.tennessee.edu/utk_gradthes/4692 This Thesis is brought to you for free and open access by the Graduate School at TRACE: Tennessee Research and Creative Exchange. It has been accepted for inclusion in Masters Theses by an authorized administrator of TRACE: Tennessee Research and Creative Exchange. For more information, please contact [email protected]. To the Graduate Council: I am submitting herewith a thesis written by Rucie James Moore entitled "Use of the GPS Reciprocal Heading Method for Determining Pitot-Static Position Error in Helicopter Flight Testing." I have examined the final electronic copy of this thesis for form and content and recommend that it be accepted in partial fulfillment of the equirr ements for the degree of Master of Science, with a major in Aviation Systems. Rodney C. Allison, Major Professor We have read this thesis and recommend its acceptance: Peter Solies, Ralph Kimberlin Accepted for the -
Aerospace Micro-Lesson Aiaa
AIAA AEROSPACE MICRO-LESSON Easily digestible Aerospace Principles revealed for K-12 Students and Educators. These lessons will be sent on a bi-weekly basis and allow grade-level focused learning. - AIAA STEM K-12 Committee AIR SPEED One of the most important pieces of knowledge for any pilot is the speed of an aircraft. There are two ways to measure the speed of an airplane: airspeed and ground speed. Airspeed is the speed of the airplane with respect to the air through which it is flying; ground speed is its speed relative to the ground over which it is flying. Airspeed is important when calculating lift and drag; ground speed is important when calculating flight times between different places. Calculating speeds is a major part of designing and flying aircraft. G RADES K-2 Flying a paper airplane on a windy day shows the difference between airspeed and ground speed very well. Fly the paper airplane indoors—in the classroom or down the hall, if you have permission—and note how far it goes and in what direction. Then go outside to a place where the wind is blowing and fly the paper airplane again. There does not need to be much wind at all. For the clearest illustration of the difference, launch the paper airplane at right angles to the wind, so that it flies through a crosswind and gets blown sideways. The airspeed is the same as it was when it flew indoors, but the ground speed now has a serious sideways component. You can also launch it into the wind and downwind, showing that even though the airspeed is the same, the wind always adds a component to the ground speed in the direction in which it is blowing. -
Development of Air Data Computation Function of a Combined Air Data and Aoa Computer
DEVELOPMENTOFAIRDATACOMPUTATIONFUNCTIONOFACOMBINEDAIR DATAANDAOACOMPUTER ATHESISSUBMITTEDTO THEGRADUATESCHOOLOFNATURALANDAPPLIEDSCIENCESOFÇANKAYA UNIVERSITY BY RAFETIL)IN INPARTIALFULLFILLMENTOFTHEREQUIREMENTS FOR THEDEGREEOFMASTEROFSCIENCE IN ELECTRONICSANDCOMMUNICATIONSENGINEERING SEPTEMBER,2011 ACKNOWLEDGEMENTS The author wishes to express his deepest gratitude to his supervisor Prof. Dr. Celal Ăŝŵ7> for his guidance, advice, criticism, encouragements and insight throughout the research. The author would also like to thank Mehmet Mustafa KARABULUT for his suggestions and comments iv ABSTRACT DEVELOPMENT OF AIR DATA COMPUTATION FUNCTION OF A COMBINED AIR DATA AND AOA COMPUTER />)/E, Rafet M.Sc., Department of Electronics and Communication Engineering ^ƵƉĞƌǀŝƐŽƌ͗WƌŽĨ͘ƌ͘ĞůĂůĂŝŵ7> September 2011, 51 Pages In this thesis, Air Data Computer part of a Combined Air Data System (CADS) and the simulator environment to test the developed CADS are developed on standard personal computers. Normally, a CADS system on an aircraft is composed of two separate equipments, the Air Data Computer (ADC) and the Angle of Attack (AOA) system. Therefore the developed CADS system combines both functionalities in an integral manner on a card. This approach not only reduces the volume but the total cost of the CADS system as well. Keywords: Avionic, System Integration, Flight Simulation, Software, Air Data Calculation, Sensor Simulation v Y dmD>b7<,ssZ7s,mhD/^/7>'7^zZ/ ,ssZ7 &KE<^7zKE>Z/HESAPLAMALARI '>7bd7ZDE>Z7 />)/E, Rafet zƺŬƐĞŬ>ŝƐĂŶƐ͕ůĞŬƚƌŽŶŝŬǀĞ,ĂďĞƌůĞƔŵĞDƺŚĞŶĚŝƐůŝŒŝŶĂďŝůŝŵĂůŦ -
6 TADS BM65 Is
CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS) NO: BM65 ISSUE: 6 TYPE: Flight Design CT2K (1) MANUFACTURER: P&M Aviation Ltd, Unit B, Crawford St, Rochdale. (UK type approval holder for Flight Design GMBH) (2) UK IMPORTER: P&M Aviation Ltd. (3) CERTIFICATION: BCAR section S issue 2, JAR-VLA parts C & D. (4) DEFINITION OF CT2K Drawings set issue 2, 18/6/01. BASIC STANDARD: (5) COMPLIANCE WITH THE MICROLIGHT DEFINITION (a) MTOW 450 kg (b) No. Seats 2 (c) Maximum Wing Loading 41.6 kg/m² (d) Vso 34 kt CAS (e) Permitted range of pilot weights 55 – 100 kg per seat. (180 kg total) (f) Typical Empty Weight (ZFW) 264 kg (g) ZFW + 172 kg crew + 1 hr fuel 450 kg (14litres / 10kg) (h) ZFW + 86 kg pilot + full fuel 448kg (130 litres / 93kg) (i) Max ZFW at initial permit issue 268kg TADS BM65 Issue 6 Page 1 of 9 CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS) NO: BM65 ISSUE: 6 (6) POWER PLANTS Designation Rotax 912 ULS Rotax 912 ULS Engine Type 4 cylinder 4 stroke 4 cylinder 4 stroke horizontally opposed horizontally opposed Reduction Gear 2.43:1 2.43:1 Exhaust System Rotax underslung Rotax underslung muffler muffler Intake System 2 x K&N filters 2 x K&N filters Propeller Type Neuform Novaprop Warp Drive 3 bladed TXR2 carbon composite Propeller Dia x Pitch 1660mm x 21o at blade 1676mm x 19o at blade undersurface at 75% undersurface at tip radius Noise Type Cert No. -
Comparison Study and Sensitivity Analysis of Flight Test Techniques for Air Data Position Error Correction in Small Aircraft
Trans. Japan Soc. Aero. Space Sci. Vol. 53, No. 182, pp. 250–257, 2011 Comparison Study and Sensitivity Analysis of Flight Test Techniques for Air Data Position Error Correction in Small Aircraft By Sang-Jong LEE,1Þ Jae Won CHANG,1Þ Jeong Ho PARK,2Þ Byoung Soo KIM3Þ and Kie Jeong SEONG1Þ 1ÞFlight Control Team, Korea Aerospace Research Institute, Daejeon, Republic of Korea 2ÞPGM R&D Lab, LIG Nex1 Co. Ltd., Yongin, Republic of Korea 3ÞSchool of Mechanical and Aerospace Engineering, Gyeongsang National University, Jinju, Republic of Korea (Received May 18th, 2009) The flight test is important in the development and certification phases of an aircraft. It is composed of various tests, but the position error correction test should be performed first to determine error of the pitot-static measurement system that is the basis for evaluating flight characteristics. This paper investigates and compares recent test methods using real flight test results. The ground course and arbitrary heading method are both considered using GPS and DGPS to measure ground speed. The arbitrary heading method was most efficient and precise. In addition, new method is proposed and successfully used to determine accurate position error by comparison with DGPS results. Finally, sensitivity analysis was performed to analyze the effect of error sources. It shows that the most important error is the measured indicated airspeed following by measured true airspeed, outside air temperature, and pressure altitude. Key Words: Flight Testing, Aircraft, Airworthiness, Position Error Correction, Analysis Nomenclature CAM: measured by camcorder DGPS: measured by DGPS aSL: speed of sound at sea level GPS: measured by GPS HI: indicated pressure altitude s: standard day condition HIC: indicated pressure altitude corrected for instrument W: wind error x: vector component of x-axis ÁHPC: altimeter position error y: vector component of y-axis Pa: ambient pressure PSL: pressure at sea level 1. -
National Advisory Committee for Aeronautics
. .—- NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS , TECHNICAL NOTE No. 1120 , STANDARD NOMENCLATURE FOR AIRSPEEDS WITH TABLES AND CHARTS FOR USE IN CALCULATION OF AIRSPEED . By William S. Aiken, Jr. Langley hCemoriaI Aeronautical Laboratory Langley Field, Va. Washington September 1946 ,. * -.. * NA!215EAL ADVW3RY COMMITTEE FOR AERONAUTICS . .● ✌. TECHNICAL NOTE No, 1120 . .- . AND CEM?TS FOR USE IN CALCULATION W AIRSPEED -. By William S . Mbn, Jr. Symbols and definitions of various airspeed terms that have been adopted as st~dard by the NACA SubcGEP mittee on Aircraft structural Design are presented. The ● equations, charts, and tablgs required In the evaluation of true sirspeed, calibrated airspeeds equivalent air~ s-peed,im-p.actand dynamic nressures, and }:achand Reynolds nlmnbers have been cor,piled~ Tables of the standard . akmosghera to an alt?tude of 65,.200feet and a tentative extension to an altitude of 1009000 feet are given along .“ with tha basic equations and ccfistants on whi~h both the standard atmosphere and the tentative extension are based~ INTI?ODUCTION In s.nalyses of aerodynamic data very often wind- tunnel or fligb.t measurements must bs converted into air- speed and related quar.ttties that are used in engineering calculatt ons, Attsmpts to accomplish such confers!.on by use of available m.etkods have been corc~licated by the diversity of s~mbols and definitions and by the necessity of referring to equations, charts, and tables from a nwn”oer of different sources. A standard set of symbols and definitions of v.micms atrsgaad terms that were adopted by the KACA Subcommittee on Aircraft Structural Design and a cow~ilation of th~ necessary equations, charts, ‘ and tables f~r converting measured pressures and temper- atures into airs~eeds, determining Mach numbars sand Re~~~ds zi’~ber~, snd determtnir.g otker quantities such as dynamic and iwqp.ct pressures that are of interest are therefore presented Mrein. -
Microlight Accident and Incident Summary 0 /201
Microlight Accident and Incident Summary 03/2011 This accident report summary is collated by the BMAA from information gathered. The information sources used are the Air Accident Investigation Branch of the Department for Transport (AAIB), the Civil Aviation Authority Mandatory Occurrence Reports (CAA MOR) and reports made directly to the BMAA by members and operators. The individual reports within the accident summary are taken from the information available to the BMAA and where the BMAA has made comment this is clearly shown. The BMAA does not investigate accidents and incidents, this role being the responsibility of the AAIB and the CAA who have the expertise, experience and funding for investigation. All pilots reading the reports should try to make their own assessment of underlying causes and use the experience of others to enhance their own knowledge to help them become safer pilots. AAIB Bulletin: 1/2011 EW/G2010/09/22 ACCIDENT Aircraft Type and Registration: Ikarus C42 FB80 No & Type of Engines: 1 Rotax 912-UL piston engine Year of Manufacture: 2005 Date & Time (UTC): 21 September 2010 at 1400 hrs Location: Type of Flight: Training Persons on Board: Crew - 1 Passengers - None Injuries: Crew - None Passengers - N/A Nature of Damage: Significant damage to forward fuselage and right wing Commander’s Licence: Student pilot Commander’s Age: 53 years Commander’s Flying Experience: 40 hours (of which 40 were on type) Last 90 days - 6 hours Last 28 days - 6 hours Information Source: Aircraft Accident Report Form submitted by the pilot The student pilot was undertaking a solo flight from edge marker and applied full power. -
Effectiveness of Adaptive Flight Planning in the Occurrence of Total Loss of Thrust Due to Bird Strike by Kivanç A. Avrenli Di
EFFECTIVENESS OF ADAPTIVE FLIGHT PLANNING IN THE OCCURRENCE OF TOTAL LOSS OF THRUST DUE TO BIRD STRIKE BY KIVANÇ A. AVRENLİ DISSERTATION Submitted in partial fulfillment of the requirements for the degree of Doctor of Philosophy in Civil Engineering in the Graduate College of the University of Illinois at Urbana-Champaign, 2015 Urbana, Illinois Doctoral Committee: Professor William Buttlar, Chair Professor Barry Dempsey, Director of Research Associate Professor Paolo Gardoni Assistant Professor Lavanya Marla ABSTRACT As of today, more than 96 percent of air travelers are transported on twin-engine jets. Although contemporary twin- engine jets are more reliable and efficient than yesterday’s three- and four-engine jets, they have reduced engine redundancy. A statistical analysis of the FAA Wildlife Strike Database shows that contemporary twin-engine jets are approximately 15 times more likely to undergo total loss of thrust in the event of a bird strike compared to yesterday’s three- and four-engine jets. To address the total-loss-of-thrust emergency, quick reference handbooks are designed to enable speedy and successful recovery of at least one engine. Airliner type-rating programs assume that total loss of thrust culminates in at least one engine recovery. If an engine restart cannot be achieved in a real-life emergency, airline pilots are left with virtually no guidance on how to manage the emergency situation. This dissertation hypothesizes that “an adaptive flight planner can significantly increase the odds of safe landing in the occurrence of total loss of thrust”. The objective is to test the research hypothesis through a designed experiment.