Dash8-200/300 - Flight Instruments
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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 -
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 -
Sept. 12, 1950 W
Sept. 12, 1950 W. ANGST 2,522,337 MACH METER Filed Dec. 9, 1944 2 Sheets-Sheet. INVENTOR. M/2 2.7aar alwg,57. A77OAMA). Sept. 12, 1950 W. ANGST 2,522,337 MACH METER Filed Dec. 9, 1944 2. Sheets-Sheet 2 N 2 2 %/ NYSASSESSN S2,222,W N N22N \ As I, mtRumaIII-m- III It's EARAs i RNSITIE, 2 72/ INVENTOR, M247 aeawosz. "/m2.ATTORNEY. Patented Sept. 12, 1950 2,522,337 UNITED STATES ; :PATENT OFFICE 2,522,337 MACH METER Walter Angst, Manhasset, N. Y., assignor to Square D Company, Detroit, Mich., a corpora tion of Michigan Application December 9, 1944, Serial No. 567,431 3 Claims. (Cl. 73-182). is 2 This invention relates to a Mach meter for air plurality of posts 8. Upon one of the posts 8 are craft for indicating the ratio of the true airspeed mounted a pair of serially connected aneroid cap of the craft to the speed of sound in the medium sules 9 and upon another of the posts 8 is in which the aircraft is traveling and the object mounted a diaphragm capsuler it. The aneroid of the invention is the provision of an instrument s: capsules 9 are sealed and the interior of the cas-l of this type for indicating the Mach number of an . ing is placed in communication with the static aircraft in fight. opening of a Pitot static tube through an opening The maximum safe Mach number of any air in the casing, not shown. The interior of the dia craft is the value of the ratio of true airspeed to phragm capsule is connected through the tub the speed of sound at which the laminar flow of ing 2 to the Pitot or pressure opening of the Pitot air over the wings fails and shock Waves are en static tube through the opening 3 in the back countered. -
Acnmanual.Pdf
Advanced Coastal Navigation Coast Guard Auxiliary Association Inc. Washington, D. C. First Edition..........................................................................1987 Second Edition .....................................................................1990 Third Edition ........................................................................1999 Fourth Edition.......................................................................2002 ii iii iv v vi Advanced Coastal Navigation TABLE OF CONTENTS Introduction...................................................................................................ix Chapter 1 INTRODUCTION TO COASTAL NAVIGATION . .1-1 Chapter 2 THE MARINE MAGNETIC COMPASS . .2-1 Chapter 3 THE NAUTICAL CHART . .3-1 Chapter 4 THE NAVIGATOR’S TOOLS & INSTRUMENTS . .4-1 Chapter 5 DEAD RECKONING . .5-1 Chapter 6 PILOTING . .6-1 Chapter 7 CURRENT SAILING . .7-1 Chapter 8 TIDES AND TIDAL CURRENTS . .8-1 Chapter 9 RADIONAVIGATION . .9-1 Chapter 10 NAVIGATION REFERENCE PUBLICATIONS . .10-1 Chapter 11 FUEL AND VOYAGE PLANNING . .11-1 Chapter 12 REFLECTIONS . .12-1 Appendix A GLOSSARY . .A-1 INDEX . .Index-1 vii Advanced Coastal Navigation viii intRodUction WELCOME ABOARD! Welcome to the exciting world of completed the course. But it does marine navigation! This is the fourth require a professional atti tude, care- edition of the text Advanced Coastal ful attention to classroom presenta- Navigation (ACN), designed to be tions, and diligence in working out used in con cert with the 1210-Tr sample problems. chart in the Public Education (PE) The ACN course has been course of the same name taught by designed to utilize the 1210-Tr nau - the United States Coast Guard tical chart. It is suggested that this Auxiliary (USCGAUX). Portions of chart be readily at hand so that you this text are also used for the Basic can follow along as you read the Coastal Navigation (BCN) PE text. We recognize that students course. -
Beforethe Runway
EDITORIAL Before the runway By Professor Sidney dekker display with fl ight information. My airspeed is leaking out of Editors Note: This time, we decided to invite some the airplane as if the hull has been punctured, slowly defl at- comments on Professor Dekker’s article from subject ing like a pricked balloon. It looks bizarre and scary and the matter experts. Their responses follow the article. split second seems to last for an eternity. Yet I have taught myself to act fi rst and question later in situations like this. e are at 2,000 feet, on approach to the airport. The big So I act. After all, there is not a whole lot of air between me W jet is on autopilot, docile, and responsively follow- and the hard ground. I switch off the autothrottle and shove ing the instructions I have put into the various computer the thrust levers forward. From behind, I hear the engines systems. It follows the heading I gave it, and stays at the screech, shrill and piercing. Airspeed picks up. I switch off altitude I wanted it at. The weather is alright, but not great. the autopilot for good measure (or good riddance) and fl y Cloud base is around 1000 feet, there is mist, a cold driz- the jet down to the runway. It feels solid in my hands and zle. We should be on the ground in the next few minutes. docile again. We land. Then everything comes to a sudden I call for fl aps, and the other pilot selects them for me. -
Inflight Data Collection N75-14745 Fob Ride Quality
NASA CR-127492 INFLIGHT DATA COLLECTION FOR RIDE QUALITY AND ATMOSPHERIC TURBULENCE RESEARCH Paul W. Kadlec and Roger G. Buckman Continental Air Lines, Inc. Los Angeles, California 90009 (NASA-CR-127492) INFLIGHT DATA COLLECTION N75-14745 FOB RIDE QUALITY AND ATMOSPHERIC TURBULENCE RESEARCH Final Report (Continental Airlines, Inc.) 57 p HC $4.25 CSCL 01C Unclas ..- - ___G3/0 5 05079 December 1974 Prepared for NASA FLIGHT RESEARCH CENTER P.O. Box 273 Edwards, California 93523 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA CR-127492 4. Title and Subtitle 5. Report Date INFLIGHT DATA COLLECTION FOR RIDE QUALITY AND December 1974 ATMOSPHERIC TURBULENCE RESEARCH 6. Performing Organization Code 7. Author(s) 8. Performing Organization Report No. Paul W. Kadlec and Roger G. Buckman 10. Work Unit No. 9. Performing Organization Name and Address 504-29-21 Continental Air Lines, Inc. 11. Contract or Grant No. Los Angeles, California 90009 NAS 4-1982 13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address Contractor Report - Final National Aeronautics and Space Administration 14. Sponsoring Agency Code Washington, D. C., 20546 H-876 15. Supplementary Notes NASA Technical Monitor: Shu W. Gee 16. Abstract In 1971 Continental Air Lines and the National Center for Atmospheric Research originated a joint program to study the genesis and nature of clear air turbulence. With the support of the NASA Flight Research Center, the program was expanded to include an investigation of the effects of atmospheric turbu- lence on passenger ride quality in a large wide-body commercial aircraft. -
FAA Advisory Circular AC 91-74B
U.S. Department Advisory of Transportation Federal Aviation Administration Circular Subject: Pilot Guide: Flight in Icing Conditions Date:10/8/15 AC No: 91-74B Initiated by: AFS-800 Change: This advisory circular (AC) contains updated and additional information for the pilots of airplanes under Title 14 of the Code of Federal Regulations (14 CFR) parts 91, 121, 125, and 135. The purpose of this AC is to provide pilots with a convenient reference guide on the principal factors related to flight in icing conditions and the location of additional information in related publications. As a result of these updates and consolidating of information, AC 91-74A, Pilot Guide: Flight in Icing Conditions, dated December 31, 2007, and AC 91-51A, Effect of Icing on Aircraft Control and Airplane Deice and Anti-Ice Systems, dated July 19, 1996, are cancelled. This AC does not authorize deviations from established company procedures or regulatory requirements. John Barbagallo Deputy Director, Flight Standards Service 10/8/15 AC 91-74B CONTENTS Paragraph Page CHAPTER 1. INTRODUCTION 1-1. Purpose ..............................................................................................................................1 1-2. Cancellation ......................................................................................................................1 1-3. Definitions.........................................................................................................................1 1-4. Discussion .........................................................................................................................6 -
Aviation Glossary
AVIATION GLOSSARY 100-hour inspection – A complete inspection of an aircraft operated for hire required after every 100 hours of operation. It is identical to an annual inspection but may be performed by any certified Airframe and Powerplant mechanic. Absolute altitude – The vertical distance of an aircraft above the terrain. AD - See Airworthiness Directive. ADC – See Air Data Computer. ADF - See Automatic Direction Finder. Adverse yaw - A flight condition in which the nose of an aircraft tends to turn away from the intended direction of turn. Aeronautical Information Manual (AIM) – A primary FAA publication whose purpose is to instruct airmen about operating in the National Airspace System of the U.S. A/FD – See Airport/Facility Directory. AHRS – See Attitude Heading Reference System. Ailerons – A primary flight control surface mounted on the trailing edge of an airplane wing, near the tip. AIM – See Aeronautical Information Manual. Air data computer (ADC) – The system that receives and processes pitot pressure, static pressure, and temperature to present precise information in the cockpit such as altitude, indicated airspeed, true airspeed, vertical speed, wind direction and velocity, and air temperature. Airfoil – Any surface designed to obtain a useful reaction, or lift, from air passing over it. Airmen’s Meteorological Information (AIRMET) - Issued to advise pilots of significant weather, but describes conditions with lower intensities than SIGMETs. AIRMET – See Airmen’s Meteorological Information. Airport/Facility Directory (A/FD) – An FAA publication containing information on all airports, seaplane bases and heliports open to the public as well as communications data, navigational facilities and some procedures and special notices. -
Use of the MS Flight Simulator in the Teaching of the Introduction to Avionics Course
Session 1928 Use of the MS Flight Simulator in the teaching of the Introduction to avionics course Iulian Cotoi, Ruxandra Mihaela Botez Ecole de technologie supérieure Département de génie de la production automatisée 1100 Notre Dame Ouest Montréal, Qué., Canada, H3C 1K3 Introduction The course Introduction to avionics GPA-745 is an optional course in the Aerospace program given in the Department of Automated Production Engineering at École de technologie supérieure in Montreal, Canada. The main objectif of this course is the study of electronic avionics instrumentation installed in aircraft. In this course, the following chapters are presented : History of avionics, Methods of navigation and orientation, Pilot cockpit and board instrumentation, Communication systems, Radio-navigation systems, Landing systems, Engine signalization instruments, Central alarm systems, Maintenance systems and Warning systems. The presentation of the course in the class to the students is shown on PowerPoint slides and videos on modern aircraft such as Airbus and Boeing. Also, regarding the pilot induced oscillations a video film is provided from Bombardier Aerospace. However, the presentation of the course in the class may be improved and become more efficient grace to the use of MS Flight Simulator. The main idea of this paper is to show how the participation of the students in the class will be increased by use of the MS Flight Simulator. The use of the systems and the electronic board instrumentation will be shown with the help of the new flight simulations modules realized within the MS Flight Simulator. For each instrument, one module will be created and presented in the class, which will result in a more interesting course presentation, stimulating and dynamical from pedagogical point of view, than the theory of the course by use of PowerPoint. -
Module-7 Lecture-29 Flight Experiment
Module-7 Lecture-29 Flight Experiment: Instruments used in flight experiment, pre and post flight measurement of aircraft c.g. Module Agenda • Instruments used in flight experiments. • Pre and post flight measurement of center of gravity. • Experimental procedure for the following experiments. (a) Cruise Performance: Estimation of profile Drag coefficient (CDo ) and Os- walds efficiency (e) of an aircraft from experimental data obtained during steady and level flight. (b) Climb Performance: Estimation of Rate of Climb RC and Absolute and Service Ceiling from experimental data obtained during steady climb flight (c) Estimation of stick free and fixed neutral and maneuvering point using flight data. (d) Static lateral-directional stability tests. (e) Phugoid demonstration (f) Dutch roll demonstration 1 Instruments used for experiments1 1. Airspeed Indicator: The airspeed indicator shows the aircraft's speed (usually in knots ) relative to the surrounding air. It works by measuring the ram-air pressure in the aircraft's Pitot tube. The indicated airspeed must be corrected for air density (which varies with altitude, temperature and humidity) in order to obtain the true airspeed, and for wind conditions in order to obtain the speed over the ground. 2. Attitude Indicator: The attitude indicator (also known as an artificial horizon) shows the aircraft's relation to the horizon. From this the pilot can tell whether the wings are level and if the aircraft nose is pointing above or below the horizon. This is a primary instrument for instrument flight and is also useful in conditions of poor visibility. Pilots are trained to use other instruments in combination should this instrument or its power fail. -
Avidyne PFD & MFD Study Guide
Eric Gideon Avidyne Study Guide 1 of 7 General overview 1. Because we often rely on the MFD for navigational information, we need to make sure that the database is current with the most up-to- date information. 2. Diferences between glass and ‘steam gauge’ cockpits • OAT probe is now located on the underside of the left wing • Standby instruments • Airspeed • Attitude indicator • Altimeter • System is all electric – no vacuum system 3. Data sources • AHRS – Attitude Heading Ref- erence System • This computer collects and gives information to the Attitude Indicator and HSI. • Replaces the gyroscopic vacuum system • ADC – Air Data Computer • This computer collects and gives information to the Airspeed, VSI, and Altimeter. • Replaces the pitot/static system • These 2 computers are located in the PFD and make up the ADAHRS – Air Data and Attitude Heading Reference System • System must be aligned before flight • MFD uses external GPS to receive information for the flight display and position. • Probes get engine data directly. 4. Limitations • The PFD and MFD are not interchangeable and cannot share atti- tude or air data. • Don’t shut them down in flight, or AHRS won’t come back. Eric Gideon Avidyne Study Guide 2 of 7 Primary Flight Display (PFD) The Primary Flight Display is a 10.4 inch color LCD, with one knob and four bezel keys per side. Brightness is controlled with the rocker switch at top right. Attitude and air data – the PFD’s upper half 1. % power tape or tachometer 2. Autopilot Annunciation Area – Displays the autopilot annunciations 3. Airspeed Tape – Indicated airspeed with a range of 20-300 kts. -
Radar Altimeter True Altitude
RADAR ALTIMETER TRUE ALTITUDE. TRUE SAFETY. ROBUST AND RELIABLE IN RADARDEMANDING ENVIRONMENTS. Building on systems engineering and integration know-how, FreeFlight Systems effectively implements comprehensive, high-integrity avionics solutions. We are focused on the practical application of NextGen technology to real-world operational needs — OEM, retrofit, platform or infrastructure. FreeFlight Systems is a community of respected innovators in technologies of positioning, state-sensing, air traffic management datalinks — including rule-compliant ADS-B systems, data and flight management. An international brand, FreeFlight Systems is a trusted partner as well as a direct-source provider through an established network of relationships. 3 GENERATIONS OF EXPERIENCE BEHIND NEXTGEN AVIONICS NEXTGEN LEADER. INDUSTRY EXPERT. TRUSTED PARTNER. SHAPE THE SKIES. RADAR ALTIMETERS FreeFlight Systems’ certified radar altimeters work consistently in the harshest environments including rotorcraft low altitude hover and terrain transitions. RADAROur radar altimeter systems integrate with popular compatible glass displays. AL RA-4000/4500 & FreeFlight Systems modern radar altimeters are backed by more than 50 years of experience, and FRA-5500 RADAR ALTIMETERS have a proven track record as a reliable solution in Model RA-4000 RA-4500 FRA-5500 the most challenging and critical segments of flight. The TSO and ETSO-approved systems are extensively TSO-C87 l l l deployed worldwide in helicopter fleets, including ETSO-2C87 l l l some of the largest HEMS operations worldwide. DO-160E l l l DO-178 Level B l Designed for helicopter and seaplane operations, our DO-178B Level C l l radar altimeters provide precise AGL information from 2,500 feet to ground level.