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Pitot-Static System Blockage Effects on Airspeed Indicator
The Dramatic Effects of Pitot-Static System Blockages and Failures by Luiz Roberto Monteiro de Oliveira . Table of Contents I ‐ Introduction…………………………………………………………………………………………………………….1 II ‐ Pitot‐Static Instruments…………………………………………………………………………………………..3 III ‐ Blockage Scenarios – Description……………………………..…………………………………….…..…11 IV ‐ Examples of the Blockage Scenarios…………………..……………………………………………….…15 V ‐ Disclaimer………………………………………………………………………………………………………………50 VI ‐ References…………………………………………………………………………………………….…..……..……51 Please also review and understand the disclaimer found at the end of the article before applying the information contained herein. I - Introduction This article takes a comprehensive look into Pitot-static system blockages and failures. These typically affect the airspeed indicator (ASI), vertical speed indicator (VSI) and altimeter. They can also affect the autopilot auto-throttle and other equipment that relies on airspeed and altitude information. There have been several commercial flights, more recently Air France's flight 447, whose crash could have been due, in part, to Pitot-static system issues and pilot reaction. It is plausible that the pilot at the controls could have become confused with the erroneous instrument readings of the airspeed and have unknowingly flown the aircraft out of control resulting in the crash. The goal of this article is to help remove or reduce, through knowledge, the likelihood of at least this one link in the chain of problems that can lead to accidents. Table 1 below is provided to summarize -
Jeweltex Manufacturing Inc., Retirement Plan, Et Al. V. The
Case 1:19-cv-02020-WFK-PK Document 1 Filed 04/08/19 Page 1 of 41 PageID #: 1 UNITED STATES DISTRICT COURT EASTERN DISTRICT OF NEW YORK _________________________________________ ) JEWELTEX MANUFACTURING INC., ) CASE NO. RETIREMENT PLAN, Individually and On ) Behalf of All Others Similarly Situated, ) ) Plaintiff, ) CLASS ACTION COMPLAINT ) vs. ) ) JURY TRIAL DEMANDED THE BOEING COMPANY, DENNIS A. ) MUILENBURG, ROBERT A. BRADWAY, ) DAVID L. CALHOUN, ARTHUR D. COLLINS, ) JR., KENNETH M. DUBERSTEIN, ADMIRAL ) EDMUND P. GIAMBASTIANI, JR., LYNN J. ) GOOD, NIKKI R. HALEY, LAWRENCE W. ) KELLNER, CAROLINE B. KENNEDY, ) EDWARD M. LIDDY, SUSAN C. SCHWAB, ) RONALD A. WILLIAMS, and MIKE S. ) ZAFIROVSKI, ) ) Defendants. ) _________________________________________ Plaintiff Jeweltex Manufacturing Inc., Retirement Plan (“Plaintiff”), by and through its undersigned attorneys, alleges the following based upon information and belief, except as to those allegations concerning Plaintiff, which are alleged upon personal knowledge. Plaintiff’s information and belief is based upon, among other things, the investigation conducted by his counsel which included, among other things: (a) a review and analysis of regulatory filings of The Boeing Company (“Boeing” or the “Company”) filed with the United States Securities and Exchange Commission (“SEC”); (b) a review and analysis of press releases and media reports issued and disseminated by Boeing; (c) a review of other publicly available information concerning Boeing, including articles in the news media and analyst reports; (d) a review and analysis of regulatory investigations and reports; and (e) complaints and related materials in litigation commenced against some or all of the Defendants Case 1:19-cv-02020-WFK-PK Document 1 Filed 04/08/19 Page 2 of 41 PageID #: 2 pertaining to Boeing and the fatal accidents involving the 737 Max series of aircraft (the “737 Max Accidents”) and their causes and aftermath. -
Validation of Wind Tunnel Test and Cfd Techniques for Retro-Propulsion (Retpro): Overview on a Project Within the Future Launchers Preparatory Programme (Flpp)
VALIDATION OF WIND TUNNEL TEST AND CFD TECHNIQUES FOR RETRO-PROPULSION (RETPRO): OVERVIEW ON A PROJECT WITHIN THE FUTURE LAUNCHERS PREPARATORY PROGRAMME (FLPP) D. Kirchheck, A. Marwege, J. Klevanski, J. Riehmer, A. Gulhan¨ German Aerospace Center (DLR) Supersonic and Hypersonic Technologies Department Cologne, Germany S. Karl O. Gloth German Aerospace Center (DLR) enGits GmbH Spacecraft Department Todtnau, Germany Gottingen,¨ Germany ABSTRACT and landing (VTVL) spacecraft, assisted by retro-propulsion. Up to now, in Europe, knowledge and expertise in that field, The RETPRO project is a 2-years activity, led by the Ger- though constantly growing, is still limited. Systematic stud- man Aerospace Center (DLR) in the frame of ESA’s Future ies were conducted to compare concepts for possible future Launchers Preparatory Program (FLPP), to close the gap of European launchers [2, 3], and activities on detailed inves- knowledge on aerodynamics and aero-thermodynamics of tigations of system components of VTVL re-usable launch retro-propulsion assisted landings for future concepts in Eu- vehicles (RLV) recently started in the RETALT project [4, 5]. rope. The paper gives an overview on the goals, strategy, and Nevertheless, validated knowledge on the aerodynamic current status of the project, aiming for the validation of inno- and aerothermal characteristics of such vehicles is still lim- vative WTT and CFD tools for retro-propulsion applications. ited to a small amount of experimental and numerical inves- Index Terms— RETPRO, retro-propulsion, launcher tigations mostly on lower altitude VTVL trajectories, e. g. aero-thermodynamics, wind tunnel testing, CFD validation within the CALLISTO project [6, 7, 8]. Other studies were conducted to analyze the aerothermodynamics of a simplified generic Falcon 9 geometry during its re-entry and landing 1. -
Airspeed Indicator Calibration
TECHNICAL GUIDANCE MATERIAL AIRSPEED INDICATOR CALIBRATION This document explains the process of calibration of the airspeed indicator to generate curves to convert indicated airspeed (IAS) to calibrated airspeed (CAS) and has been compiled as reference material only. i Technical Guidance Material BushCat NOSE-WHEEL AND TAIL-DRAGGER FITTED WITH ROTAX 912UL/ULS ENGINE APPROVED QRH PART NUMBER: BCTG-NT-001-000 AIRCRAFT TYPE: CHEETAH – BUSHCAT* DATE OF ISSUE: 18th JUNE 2018 *Refer to the POH for more information on aircraft type. ii For BushCat Nose Wheel and Tail Dragger LSA Issue Number: Date Published: Notable Changes: -001 18/09/2018 Original Section intentionally left blank. iii Table of Contents 1. BACKGROUND ..................................................................................................................... 1 2. DETERMINATION OF INSTRUMENT ERROR FOR YOUR ASI ................................................ 2 3. GENERATING THE IAS-CAS RELATIONSHIP FOR YOUR AIRCRAFT....................................... 5 4. CORRECT ALIGNMENT OF THE PITOT TUBE ....................................................................... 9 APPENDIX A – ASI INSTRUMENT ERROR SHEET ....................................................................... 11 Table of Figures Figure 1 Arrangement of instrument calibration system .......................................................... 3 Figure 2 IAS instrument error sample ........................................................................................ 7 Figure 3 Sample relationship between -
Reusable Launch Vehicle Technology Program{
Acta Astronautica Vol. 41, No. 11, pp. 777±790, 1997 # 1998 Published by Elsevier Science Ltd. All rights reserved Printed in Great Britain PII: S0094-5765(97)00197-5 0094-5765/98 $19.00 + 0.00 REUSABLE LAUNCH VEHICLE TECHNOLOGY PROGRAM{ DELMA C. FREEMAN{ JR. and THEODORE A. TALAY} NASA Langley Research Center, Hampton, Virginia 23681-0001, USA R. EUGENE AUSTIN} NASA Marshall Space Flight Center, Marshall Space Flight Center, Alabama 35812-1000, USA (Received 25 April 1997) AbstractÐIndustry/NASA reusable launch vehicle (RLV) technology program eorts are underway to design, test, and develop technologies and concepts for viable commercial launch systems that also satisfy national needs at acceptable recurring costs. Signi®cant progress has been made in understanding the technical challenges of fully reusable launch systems and the accompanying management and oper- ational approaches for achieving a low-cost program. This paper reviews the current status of the RLV technology program including the DC-XA, X-33 and X-34 ¯ight systems and associated technology programs. It addresses the speci®c technologies being tested that address the technical and operability challenges of reusable launch systems including reusable cryogenic propellant tanks, composite structures, thermal protection systems, improved propul- sion, and subsystem operability enhancements. The recently concluded DC-XA test program demon- strated some of these technologies in ground and ¯ight tests. Contracts were awarded recently for both the X-33 and X-34 ¯ight demonstrator systems. The Orbital Sciences Corporation X-34 ¯ight test ve- hicle will demonstrate an air-launched reusable vehicle capable of ¯ight to speeds of Mach 8. -
Initial Piloted Simulation Study of Geared Flap R Tilt-Wing V/STOL
R NASA Technical Memorandum 103872 Initial Piloted Simulation Study of Geared Flap Control r Tilt-Wing V/STOL Aircraft Lourdes M. Guerrero and Lloyd Da Corliss [NASA-TM-103872) INITIAL PILOTED N93-10741 ~~~U~A~~~NSTUDY QF GEARft) FLAP ~Q~~~~~ fOR TILT-WING V/STOL AIRCRAFT (NASA) 39 p Wncfas 63/08 01180?6 October 1991 National Aeronautics and Space Administration NASA Technical Memorandum 103872 Initial Piloted Simulation Study of Geared Flap Control For Tilt-Wing V/STOL Aircraft Lourdes M. Guerrero and Lloyd D Corliss, Ames Research Center, Moffett Field, California October 1991 National Aeronautics and Space Administration Ames Research Center Moffett Field, Califorrlia94035 -1000 SUMMARY A simulation model was developed for piloted evaluations of a representative tilt-wing V/STOL (Vertical/Short Takeoff and Landing) aircraft. Using this model an initial tilt-wing simulation study was conducted in 1990 on the Ames Vertical Motion Simulator In the past, all tilt-wing aircraft have required a horizontal tail rotor or reaction jets to provide pitch control in hover and low speeds. To alleviate this need, devices such as monocyclic propellers and a geared flap have been proposed for providing control at low speed. The geared flap is the sub- ject of this study and it is compared to the conventional flap used in previous tilt-wing aircraft. Objectives of the study were to simulate a tilt-wing V/STOL aircraft, to evaluate and compare the control effectiveness and handling qualities of both a conventional (programmed flap) and the geared flap control configurations, and to determine the feasibility of eliminating the horizontal tail rotor or reaction jets of prior designs through the use of the geared flap control configuration. -
American Eagle Flight 3008 ALPA Submission
SUBMISSION OF THE AIR LINE PILOTS ASSOCIATION TO THE NATIONAL TRANSPORTATION SAFETY BOARD REGARDING AN INCIDENT INVOLVING AMERICAN EAGLE AIRLINES FLIGHT 3008 Santa Maria, CA January 2, 2006 1 SUMMARY..........................................................................................................................................3 2 HISTORY OF FLIGHT......................................................................................................................3 3 WEATHER ..........................................................................................................................................5 3.1 WEATHER RADAR ........................................................................................................................ 5 3.2 AIRMETS ................................................................................................................................... 5 3.3 CONCLUSION................................................................................................................................5 4 OPERATIONS.....................................................................................................................................5 4.1 DEFERRED DE-ICE TIMER CONTROL SYSTEM .............................................................................. 5 4.2 STALL WARNING SYSTEM............................................................................................................ 6 4.3 STALL RECOVERY TRAINING ...................................................................................................... -
Mandatory Passenger Requirements on Lion Air Group Air Travel Last Updated August 24, 2021 | 23:00 WIB (GMT+ 07)
www.lionair.co.id @lionairgroup (+6221) 6379 8000 www.batikair.com @batikair @lionairgroup Lion Air Group Lion Air Group 0804 1 778899 PRESS RELEASE Latest Flight Information: Mandatory Passenger Requirements on Lion Air Group Air Travel Last Updated August 24, 2021 | 23:00 WIB (GMT+ 07) Running Period: 25 - 30 August 2021 “Please Pay Attention to and Meet the Health Test Conditions, Validity Period and Other Specified Requirements Documents” Flying is Safe and Healthy: Use of Caring Apps Protect Before Departure, as part of Digitalization Gradually. J A K A R T A – August 25, 2021. Lion Air (JT flight code), Wings Air (IW flight code), Batik Air (ID flight code) member of Lion Air Group said that the entire implementation of Lion Air Group flight operations while maintaining safety, security, and comfort (safety first). And already run according to health protocol guidelines. In connection with the terms and conditions required for each prospective passenger who will carry out air travel (flights) during the Corona Virus Disease 2019 (Covid-19) pandemic alert period, current period: August 25 – August 30, 2021. Domestic flight provisions in that period, to support government policies related to the implementation (implementation) of efforts to prevent, handle and control Covid-19, namely the Enactment of Restrictions on Community Activities (PPKM), category: 1. Level 4, Level 3, Level 2 Java and Bali, 2. Level 4 Sumatra, Kalimantan, Sulawesi, Nusa Tenggara, Maluku and Papua, 3. Level 3, Level 2, Level 1 Sumatra, Kalimantan, Sulawesi, Nusa Tenggara, Maluku and Papua. Key Notes: 1. Please arrive at the airport departure early, which is 3-4 hours before the scheduled flight. -
PROPULSION SYSTEM/FLIGHT CONTROL INTEGRATION for SUPERSONIC AIRCRAFT Paul J
PROPULSION SYSTEM/FLIGHT CONTROL INTEGRATION FOR SUPERSONIC AIRCRAFT Paul J. Reukauf and Frank W. Burcham , Jr. NASA Dryden Flight Research Center SUMMARY The NASA Dryden Flight Research Center is engaged in several programs to study digital integrated control systems. Such systems allow minimization of undesirable interactions while maximizing performance at all flight conditions. One such program is the YF-12 cooperative control program. In this program, the existing analog air-data computer, autothrottle, autopilot, and inlet control systems are to be converted to digital systems by using a general purpose airborne computer and interface unit. First, the existing control laws are to be programed and tested in flight. Then, integrated control laws, derived using accurate mathematical models of the airplane and propulsion system in conjunction with modern control techniques, are to be tested in flight. Analysis indicates that an integrated autothrottle-autopilot gives good flight path control and that observers can be used to replace failed sensors. INTRODUCTION Supersonic airplanes, such as the XB-70, YF-12, F-111, and F-15 airplanes, exhibit strong interactions between the engine and the inlet or between the propul- sion system and the airframe (refs. 1 and 2) . Taking advantage of possible favor- able interactions and eliminating or minimizing unfavorable interactions is a chal- lenging control problem with the potential for significant improvements in fuel consumption, range, and performance. In the past, engine, inlet, and flight control systems were usually developed separately, with a minimum of integration. It has often been possible to optimize the controls for a single design point, but off-design control performance usually suffered. -
The Westcliff Diary T: 01702 475443 F: 01702 470495 E: [email protected] W: Issue 83 / SPRING 2018
Westcliff High School for Boys The Westcliff Diary T: 01702 475443 F: 01702 470495 E: [email protected] W: www.whsb.essex.sch.uk ISSUE 83 / SPRING 2018 IN THIS ISSUE: STEM ACTIVITIES ESSEX YOUNG POET OF THE YEAR MUSIC VISTS TO SEE WICKED AND PHILHARMONIA ORCHESTRA SCHOOL PLAY: THE RESISTABLE RISE OF ARTORIO UI THE WESTCLIFF DIARY PAGE 1 correlation between levels of attendance to provide coherent and consistent GCSE AND A LEVEL TRIAL INTERNET USE FROM THE and academic performance. By way of guidance and support. I hope that this example drawing on the most recent Year information is helpful in understanding EXAMINATIONS 10 Report data issued in November 2017, why the School does not authorise I wrote about the matter of appropriate DESK OF THE we had 25 pupils who had attendance holidays during term time. I thank all The Spring Term brings preparations use of the Internet this time last year. I below 96% and their average progress parents for their continued support with for the Public Examinations sharply into noted that some pupils were spending HEADMASTER was half a grade behind the cohort as a this matter. focus. Year 11 pupils have completed an inordinate amount of time on the whole. By the same token, it will probably their trial examinations and should use Internet, often playing games (sometimes come as no surprise that the 15 Year 10 PUPIL PARTICIPATION the feedback provided by their teachers late at night and into the early hours of WELCOME BACK FROM you would like to make a donation to the pupils with the least favourable conduct to inform their study and revision plans. -
University of Groningen Technology Operations and Management Master's Thesis Aviation in a Pandemic: the Profitability Approac
Aviation in a Pandemic: The profitability approach for an airline's operation in a pandemic context - University of Groningen Technology Operations and Management Master’s Thesis Written by: Barran Haunan Supervisor: dr. N.B. Szirbik Co-assesor: dr. ir. D.J. van der Zee March 2, 2021 Contents Abstract .................................................................................................................................................. 2 1. Introduction ................................................................................................................................... 3 2. Theoretical background ............................................................................................................... 8 2.1 Revenue Framework ............................................................................................................. 9 2.2 Cost Framework .................................................................................................................. 10 2.3 Revenue and Cost Conditions during the Pandemic ....................................................... 11 3. Methodology .................................................................................................................................... 14 3.1 Selecting case study as the main research design ................................................................... 14 3.2 Design Science Research ........................................................................................................... 15 3.3 Subject Selection: -
GENERAL ENGINE BLEED Fokker 50
Fokker 50 - Bleed Air System GENERAL Bleed-air is used for airconditioning, pressurization, airframe and engine air intake de-icing, and for pressurizing the hydraulic tank. Bleed-air is supplied by the engines. For aircraft equipped with APU On the ground bleed-air can be supplied by the APU for air conditioning. ENGINE BLEED Tappings Bleed-air is obtained via tappings on each engine, referred to as Low-Pressure (LP) bleed and High-Pressure (HP) bleed. LP-bleed is normally in use during flight. HP-bleed will be used at idling and low engine speeds, when LP-bleed is insufficient. The HP-bleed valve will open automatically provided the BLEED push button, located at the AIR CONDITIONING panel, is blank. Bleed-air from the HP-Bleed is prevented from flowing into the LP-bleed by a check valve. Duct leak detection A duct leak between the engine tappings and the firewall, resulting in a significant leakage of bleed-air, is monitored by the engine fire detection and warning system. Distribution Bleed-air from both engines is used to supply the following services: • Airframe, and engine air intake de-icing, see ICE AND RAIN PROTECTION • Hydraulic tank pressurization, see HYDRAULIC SYSTEM. • Airconditioning and pressurization, see below. • If mentioned in aircraft system deviation table: Watertank pressurization, see AIRCRAFT GENERAL. Page 1 Fokker 50 - Bleed Air System BLEED AIR FOR AIRCONDITIONING Supply Controls and indicators are located at the AIRCONDITIONING panel. Bleed-air is available when the engines are running and the BLEED push buttons are blank. When a BLEED push button is depressed to OFF, the Pressure Regulating/Shut-Off valve (PR/SO) and the HP- bleed valve close.