ST3400 INSTALLATION MANUAL 82002-IM-K Updated King Air STC
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Robust Integrated Ins/Radar Altimeter Accounting Faults at the Measurement Channels
ICAS 2002 CONGRESS ROBUST INTEGRATED INS/RADAR ALTIMETER ACCOUNTING FAULTS AT THE MEASUREMENT CHANNELS Ch. Hajiyev, R.Saltoglu (Istanbul Technical University) Keywords: Integrated Navigation, INS/Radar Altimeter, Robust Kalman Fillter, Error Model, Abstract was a milestone, and we were witnesses to these improvements in the near past. A great amount of In this study, the integrated navigation system, study has already been made about this issue. consisting of radio and INS altimeters, is Many more seem to be observed in the future. As presented. INS and the radio altimeter have many of these studies were examined, and some different benefits and drawbacks. The reason for useful information was reached. integrating these two navigators is mainly to Integrated navigation systems combine the combine the best features, and eliminate the best features of both autonomous and stand-alone shortcomings, briefly described above. systems and are not only capable of good short- The integration is achieved by using an term performance in the autonomous or stand- indirect Kalman filter. Hereby, the error models alone mode of operation, but also provide of the navigators are used by the Kalman filter to exceptional performance over extended periods estimate vertical channel parameters of the of time when in the aided mode. Integration thus navigation system. In the open loop system, INS brings increased performance, improved is the main source of information, and radio reliability and system integrity, and of course altimeter provides discrete aiding data to support increased complexity and cost [1,2]. Moreover, the estimations. outputs of an integrated navigation system are At the next step of the study, in case of digital, thus they are capable of being used by abnormal measurements, the performance of the other resources of being transmitted without loss integrated system is examined. -
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. -
Performance Improvement Methods for Terrain Database Integrity
PERFORMANCE IMPROVEMENT METHODS FOR TERRAIN DATABASE INTEGRITY MONITORS AND TERRAIN REFERENCED NAVIGATION A thesis presented to the Faculty of the Fritz J. and Dolores H. Russ College of Engineering and Technology of Ohio University In partial fulfillment of the requirements for the degree Master of Science Ananth Kalyan Vadlamani March 2004 This thesis entitled PERFORMANCE IMPROVEMENT METHODS FOR TERRAIN DATABASE INTEGRITY MONITORS AND TERRAIN REFERENCED NAVIGATION BY ANANTH KALYAN VADLAMANI has been approved for the School of Electrical Engineering and Computer Science and the Russ College of Engineering and Technology by Maarten Uijt de Haag Assistant Professor of Electrical Engineering and Computer Science R. Dennis Irwin Dean, Russ College of Engineering and Technology VADLAMANI, ANANTH K. M.S. March 2004. Electrical Engineering and Computer Science Performance Improvement Methods for Terrain Database Integrity Monitors and Terrain Referenced Navigation (115pp.) Director of Thesis: Maarten Uijt de Haag Terrain database integrity monitors and terrain-referenced navigation systems are based on performing a comparison between stored terrain elevations with data from airborne sensors like radar altimeters, inertial measurement units, GPS receivers etc. This thesis introduces the concept of a spatial terrain database integrity monitor and discusses methods to improve its performance. Furthermore, this thesis discusses an improvement of the terrain-referenced aircraft position estimation for aircraft navigation using only the information from downward-looking sensors and terrain databases, and not the information from the inertial measurement unit. Vertical and horizontal failures of the terrain database are characterized. Time and frequency domain techniques such as the Kalman filter, the autocorrelation function and spectral estimation are designed to evaluate the performance of the proposed integrity monitor and position estimator performance using flight test data from Eagle/Vail, CO, Juneau, AK, Asheville, NC and Albany, OH. -
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. -
Helicopter Solutions the Proof Is in the Performance Content
HELICOPTER SOLUTIONS THE PROOF IS IN THE PERFORMANCE CONTENT G500H TXi Flight Display 06 HSVT™ Synthetic Vision Technology 07 GTN™ Xi Series Navigators 08 Terrain Awareness and Warning System 10 GFC™ 600H Flight Control System 11 GNC® 255/GTR 225 Nav/Comm Radios 12 GMA™ Series Digital Audio Control 12 Flight Stream 110/210 Wireless Gateways 13 SiriusXM® Satellite Weather 14 GSR 56H Global Weather/Voice/Text 14 GTS™ Series Active Traffic 14 ADS-B Solutions 15 GTX™ Series All-in-one ADS-B Transponders 16 GDL® Series ADS-B Datalinks 16 GWX™ 75H Digital Weather Radar 17 GRA™ 55 Radar Altimeter 18 FltPlan.com Services 19 Product Specifications 20 PUT BETTER DECISION-MAKING TOOLS AT YOUR FINGERTIPS WITH GARMIN HELICOPTER AVIONICS The versatility that helicopters bring to the world of aviation is reflected in the wide range of missions they fly: emergency medical services, law enforcement, offshore logistics, search and rescue, aerial touring, heavy-lift, executive transport, pilot training and many more. Each has its own operational challenges. And for some, these challenges have grown — as busier airspace and ever-more- demanding flight environments have increased the focus on safety, industry wide. An FAA task force identified three primary areas where operational risks for helicopters need special attention: 1) inadvertent flight into instrument meteorological (IMC) conditions, 2) night operations, and 3) controlled flight into terrain (CFIT). Many ongoing studies have reinforced these findings. And in response, many operators are now asking for technologies that can proactively (and affordably) help address these safety issues. To that end, Garmin is focusing our decades of experience in aviation safety technology on the specialized needs of today’s helicopter community. -
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. -
Digital Air Data Computer Type Ac32
DIGITAL AIR DATA COMPUTER TYPE AC32 GENERAL THOMMEN is a leading manufacturer of Air Data Systems It also supports the Air Data for enhanced safety and aircraft instruments used worldwide on a full range infrastructure capabilities for Transponders and an ICAO aircraft types from helicopters to corporate turbine aircraft encoded altitude output is also available as an option. and commercial airliners. The AC32 measures barometric altitude, airspeed and temperature in the atmosphere with Its power supply is designed for 28 VDC. The low power integrated vibrating cylinder pressure sensors with high consumption of less than 7 Watts and its low weight of only accuracy and stability for both static and pitot ports. 2.2 Ibs (1000 grams) have been optimized for applications in state-of-the-art avionics suites. The extensive Built-in-Test The THOMMEN AC32 Digital Air Data Computer exceeds FAA capability guarantees safe operation. Technical Standard Order (TSO) and accuracy requirements. The computed air data parameters are transmitted via the The AC32 is designed to be modular which allows easy configurable ARINC 429 data bus. There are two ARINC 429 maintenance by the operator thanks to the RS232 transmit channels and two receive channels with which baro maintenance interface. The THOMMEN AC32 can be confi correction can be accomplished also. gured for different applications and has excellent hosting capabilities for supplying data to next generation equipment The AC32 meets the requirements for multiple platforms for without altering the system architecture. TAWS, ACAS/TCAS, EGPWS or FMS systems. For customized versions please contact THOMMEN AIRCRAFT EQUIPMENT AG sales department. -
Computer Aided Diagnosis of Technical Condition of the Swpl-1 Helmet Mounted Flight Parameters Display System
Journal of KONBiN 3(31)2014 ISSN 1895-8281 DOI 10.2478/jok-2014-0025 COMPUTER AIDED DIAGNOSIS OF TECHNICAL CONDITION OF THE SWPL-1 HELMET MOUNTED FLIGHT PARAMETERS DISPLAY SYSTEM KOMPUTEROWE DIAGNOZOWANIE STANU TECHNICZNEGO SYSTEMU NAHEŁMOWEGO WYŚWIETLANIA PARAMETRÓW LOTU SWPL-1 Sławomir Michalak, Jerzy Borowski, Andrzej Szelmanowski Air Force Institute of Technology e-mail: [email protected], [email protected], [email protected] Abstract: The paper presents selected results of the work carried out at the Air Force Institute of Technology (AFIT) in the scope of computer diagnostic tests of the SWPL-1 Cyklop helmet mounted flight parameters display system. This system has been designed in such a way that it warns the pilot of dangerous situations occurring on board the helicopter and threatening the flight safety (WARN) or faults (FAIL), which inform about a failure in given on-board equipment. The SWPL-1 system has been awarded the Prize of the President of the Republic of Poland during the 17. International Defense Industry Exhibition in Kielce. Keywords: flight parameters display systems, test methods Streszczenie: W artykule przedstawiono wybrane wyniki prac realizowanych w Instytucie Technicznym Wojsk Lotniczych (ITWL) w zakresie komputerowych badań diagnostycznych nahełmowego systemu wyświetlania parametrów lotu SWPL-1 Cyklop. System ten został zaprojektowany w taki sposób, aby alarmować pilota o wystąpieniu na pokładzie śmigłowca sytuacji niebezpiecznych, zagrażających bezpieczeństwu lotu (WARN) lub stanów awaryjnych (FAIL), informujących o niesprawności wybranych urządzeń pokładowych. Zbudowany system SWPL-1 otrzymał Nagrodę Prezydenta RP na XVII Międzynarodowym Salonie Przemysłu Obronnego MSPO’2009 w Kielcach. Słowa kluczowe: systemy wyświetlania parametrów lotu, metody badań 73 Computer aided diagnosis of technical condition of the SWPL-1 helmet mounted.. -
Airbus Erroneous Radio Altitudes Date Model Phase of Altitude Display / Messages/ Warning Flight 1
Airbus Erroneous Radio Altitudes Date Model Phase of Altitude Display / Messages/ Warning Flight 1. 18.8.2010 A320-232 During 3000 ft low read out & approach Too Low Gear Alert 2. 22.8.2010 A320-232 During 2500 ft Both RAs RA’s fluctuating down to approach 1500 ft + TAWS alerts 3. 23.8.2010 A320-232 RWY 30 200 ft "Retard” + Nav RA degraded 4. 059.2010 . A320-232 RWY 30 200 ft "Retard” + Nav RA degraded 5. 069.2010 . A320-232 After landing Nav RA degraded 6. 13.92010 . A320-232 After landing Nav RA degraded 7. 7.10.2010 A320-232 During Final 170 ft “Retard” RWY 30 8. 24.10.2010 A320-232 During 2500 ft “NAV RA2 fault" approach Date Model Phase of Flight Altitude Display / Messages/ Warning 9. 2610.2010 . A320-232 Right of RWY 30 4000 ft terrain + Pull Up 10. 2401.2011 . A340-300 Visual RWY 30, RA2 showed 50ft, RA1 diduring base turn shdhowed 2400ft, & “LDG no t down” 11. 2601.2011 . A320-232 Right of RWY 30 5000 ft “LDG not down” 12. 13.2.2011 A320-232 After landing Nav RA degraded 13. 15.2.2011 A330-200 PURLA 1C, 800 ft “too low terrain” RWY12 14..2 22 2011 . A320-232 RWY 30 4000 ft 3000ft & low gear and pull takeoff up 15. 23.2.2011 A330-200 SID RWY 30, 500 ft “LDG not down” during climb 11 14 15 9 3, 4, 7 13 1 2,8 10 • All the fa u lty readouts w ere receiv ed from pilots of Airbu s aeroplanes equipped with Thales ERT 530/540 radar altimeter . -
Aviation Occurrence Report Gear-Up Landing Cougar Helicopters Inc. Eurocopter As332l Super Puma (Helicopter) C-Gqch St. John=S
AVIATION OCCURRENCE REPORT GEAR-UP LANDING COUGAR HELICOPTERS INC. EUROCOPTER AS332L SUPER PUMA (HELICOPTER) C-GQCH ST. JOHN=S, NEWFOUNDLAND 01 JULY 1997 REPORT NUMBER A97A0136 The Transportation Safety Board of Canada (TSB) investigated this occurrence for the purpose of advancing transportation safety. It is not the function of the Board to assign fault or determine civil or criminal liability. Aviation Occurrence Report Gear-Up Landing Cougar Helicopters Inc. Eurocopter AS332L Super Puma (Helicopter) C-GQCH St. John=s, Newfoundland 01 July 1997 Report Number A97A0136 Summary The crew of the Super Puma helicopter, serial number 2139, were conducting an instrument landing system (ILS) approach to runway 29 in St. John=s, Newfoundland. As the helicopter was about to touch down, the crew realized that the helicopter was lower than normal and that the landing gear was still retracted. The crew began to bring the helicopter into a hover; however, as collective pitch was applied, the nose of the helicopter contacted the runway surface. Once the hover was established, the landing gear was lowered and the helicopter landed without further incident. Damage was confined to two communications antennae, and the supporting fuselage structure of the aircraft. There were no injuries to the 2 crew members or 11 passengers. 2 Other Factual Information The flight crew were certified and qualified for the flight in accordance to exsisting regulations. The occurrence flight was the second flight of the day for the flight crew. For the first flight of the day, the first crew member arrived at 0700 Newfoundland daylight time (NDT) for the planned morning flight. -
Possibilities of Increasing the Low Altitude Measurement Precision of Airborne Radio Altimeters
electronics Article Possibilities of Increasing the Low Altitude Measurement Precision of Airborne Radio Altimeters Ján Labun 1 , Martin Krch ˇnák 1, Pavol Kurdel 1 , Marek Ceškoviˇcˇ 1, Alexey Nekrasov 2,3,4,* and Mária Gamcová 5 1 Faculty of Aeronautics, Technical University of Košice, Rampová 7, Košice 041 21, Slovakia; [email protected] (J.L.); [email protected] (M.K.); [email protected] (P.K.); [email protected] (M.C.)ˇ 2 Institute for Computer Technologies and Information Security, Southern Federal University, Chekhova 2, Taganrog 347922, Russia 3 Department of Radio Engineering Systems, Saint Petersburg Electrotechnical University, Professora Popova 5, Saint Petersburg 197376, Russia 4 Institute of High Frequency Technology, Hamburg University of Technology, Denickestraße 22, Hamburg 21073, Germany 5 Faculty of Electrical Engineering and Informatics, Technical University of Košice, Letná 9, Košice 042 00, Slovakia; [email protected] * Correspondence: [email protected]; Tel.: +7-8634-360-484 Received: 7 August 2018; Accepted: 9 September 2018; Published: 11 September 2018 Abstract: The paper focuses on the new trend of increasing the accuracy of low altitudes measurement by frequency-modulated continuous-wave (FMCW) radio altimeters. The method of increasing the altitude measurement accuracy has been realized in a form of a frequency deviation increase with the help of the carrier frequency increase. In this way, the height measurement precision has been established at the value of ±0.75 m. Modern digital processing of a differential frequency cannot increase the accuracy limitation considerably. It can be seen that further increase of the height measurement precision is possible through the method of innovatory processing of so-called height pulses. -
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.