NBAA Automated Flight Deck Training Guidelines
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Cessna 182P ©2010 Axenty Aviation LLC Cessna 182P ©2010 Axenty Aviation LLC V SPEEDS (KIAS) EXTERIOR INSPECTION FLOODED START EXTERIOR INSPECTION Vso
Cessna 182P ©2010 Axenty Aviation LLC Cessna 182P ©2010 Axenty Aviation LLC V SPEEDS (KIAS) EXTERIOR INSPECTION FLOODED START EXTERIOR INSPECTION Vso..........................................48 Aft Fuselage (CONT.) Master....................................ON Vs............................................53 Baggage Door..............LOCKED Throttle....................FULL OPEN Vr.......................................50-60 Fuselage.........................CHECK Stall Warning...................CLEAR Mixture................IDLE CUT OFF Vx (sea level)..........................59 Empennage Tie Down.....................REMOVE Ignition.........................ENGAGE Vx (10,000 ft.).........................63 Horiz. Stabilizer..............CHECK Leading Edge.................CHECK *When engine fires advance Vy (sea level)..........................80 Elevator..........................CHECK Left Aileron.....................CHECK mixture, retard throttle* Vy (10,000 ft.).........................73 Tail Tie-Down..............REMOVE Left Flap........................CHECK Vfe (10°)................................140 Trim Tab.........................CHECK COLD WEATHER START Vfe (10°-40°)...........................95 Rudder............................CHECK PRE-ENGINE START Vno........................................141 Antennas........................CHECK Prime.........................6-8 TIMES Vne........................................176 Horiz. Stabilizer..............CHECK Preflight...................COMPLETE Mixture......................FULL RICH -
Downloading the Better Data Available in the FMS for All Aircraft Appears to Be Lower
EUROPEAN ORGANISATION FOR THE SAFETY OF AIR NAVIGATION EUROCONTROL EUROCONTROL EXPERIMENTAL CENTRE STUDY OF THE ACQUISITION OF DATA FROM AIRCRAFT OPERATORS TO AID TRAJECTORY PREDICTION CALCULATION EEC Note No. 18/98 EEC Task R23 EATCHIP Task ODP.ET5.ST03 Issued: September 1998 The information contained in this document is the property of the EUROCONTROL Agency and no part should be reproduced in any form without the Agency’s permission. The views expressed herein do not necessarily reflect the official views or policy of the Agency. REPORT DOCUMENTATION PAGE Reference: Security Classification: EEC Note No. 18/98 Unclassified Originator: Originator (Corporate Author) Name/Location: EEC - FDR EUROCONTROL Experimental Centre (Flight Data Research) B.P.15 F - 91222 Brétigny-sur-Orge CEDEX FRANCE Telephone : +33 (0)1 69 88 75 00 Sponsor: Sponsor (Contract Authority) Name/Location: EUROCONTROL Agency Directorate of EATCHIP Development Rue de la Fusée, 96 - Division DED2 (Peter Bailey) B -1130 BRUXELLES Telephone : +32 2 729 3339 TITLE: STUDY OF THE ACQUISITION OF DATA FROM AIRCRAFT OPERATORS TO AID TRAJECTORY PREDICTION CALCULATION Author Date Pages Figures Tables Appendix References G. Mykoniatis, P. Martin 9/98 xii+96 1+59 4+4 7 13 EATCHIP Task EEC Task No. Task No. Sponsor Period Specification R23 ODP-5-E3 1997 to 1998 ODP.ET5.ST03 Distribution Statement: (a) Controlled by: Head of FDR (b) Special Limitations: None (c) Copy to NTIS: YES / NO Descriptors (keywords): trajectory prediction - aircraft operators - airlines - flight plans - data link - take-off weight - route - flight plan data processing Abstract: Several aircraft operators were consulted to determine if they could supply flight data to ATS which would make a significant difference to the trajectories calculated by flight data processing systems, particularly in the initial climb phase. -
Guidance for the Implementation of Fdm Precursors
EUROPEAN OPERATORS FLIGHT DATA MONITORING WORKING GROUP B SAFETY PROMOTION Good Practice document GUIDANCE FOR THE IMPLEMENTATION OF FDM PRECURSORS June 2019 Rev 02 Guidance for the Implementation of FDM Precursors | Rev 02 Contents Table of Revisions .............................................................................................................................5 Introduction ......................................................................................................................................6 Occurrence Reporting and FDM interaction ............................................................................................ 6 Precursor Description ................................................................................................................................ 6 Methodology for Flight Data Monitoring ................................................................................................. 9 Runway Excursions (RE) ..................................................................................................................11 RE01 – Incorrect Performance Calculation ............................................................................................. 12 RE02 – Inappropriate Aircraft Configuration .......................................................................................... 14 RE03 – Monitor CG Position .................................................................................................................... 16 RE04 – Reduced Elevator Authority ....................................................................................................... -
A Brief Review on Electromagnetic Aircraft Launch System
International Journal of Mechanical And Production Engineering, ISSN: 2320-2092, Volume- 5, Issue-6, Jun.-2017 http://iraj.in A BRIEF REVIEW ON ELECTROMAGNETIC AIRCRAFT LAUNCH SYSTEM 1AZEEM SINGH KAHLON, 2TAAVISHE GUPTA, 3POOJA DAHIYA, 4SUDHIR KUMAR CHATURVEDI Department of Aerospace Engineering, University of Petroleum and Energy Studies, Dehradun, India E-mail: [email protected] Abstract - This paper describes the basic design, advantages and disadvantages of an Electromagnetic Aircraft Launch System (EMALS) for aircraft carriers of the future along with a brief comparison with traditional launch mechanisms. The purpose of the paper is to analyze the feasibility of EMALS for the next generation indigenous aircraft carrier INS Vishal. I. INTRODUCTION maneuvering. Depending on the thrust produced by the engines and weight of aircraft the length of the India has a central and strategic location in the Indian runway varies widely for different aircraft. Normal Ocean. It shares the longest coastline of 7500 runways are designed so as to accommodate the kilometers amongst other nations sharing the Indian launch for such deviation in takeoff lengths, but the Ocean. India's 80% trade is via sea routes passing scenario is different when it comes to aircraft carriers. through the Indian Ocean and 85% of its oil and gas Launch of an aircraft from a mobile platform always are imported through sea routes. Indian Ocean also requires additional systems and methods to assist the serves as the locus of important international Sea launch because the runway has to be scaled down, Lines Of Communication (SLOCs) . Development of which is only about 300 feet as compared to 5,000- India’s political structure, industrial and commercial 6,000 feet required for normal aircraft to takeoff from growth has no meaning until its shores are protected. -
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 -
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. -
Using an Autothrottle to Compare Techniques for Saving Fuel on A
Iowa State University Capstones, Theses and Graduate Theses and Dissertations Dissertations 2010 Using an autothrottle ot compare techniques for saving fuel on a regional jet aircraft Rebecca Marie Johnson Iowa State University Follow this and additional works at: https://lib.dr.iastate.edu/etd Part of the Electrical and Computer Engineering Commons Recommended Citation Johnson, Rebecca Marie, "Using an autothrottle ot compare techniques for saving fuel on a regional jet aircraft" (2010). Graduate Theses and Dissertations. 11358. https://lib.dr.iastate.edu/etd/11358 This Thesis is brought to you for free and open access by the Iowa State University Capstones, Theses and Dissertations at Iowa State University Digital Repository. It has been accepted for inclusion in Graduate Theses and Dissertations by an authorized administrator of Iowa State University Digital Repository. For more information, please contact [email protected]. Using an autothrottle to compare techniques for saving fuel on A regional jet aircraft by Rebecca Marie Johnson A thesis submitted to the graduate faculty in partial fulfillment of the requirements for the degree of MASTER OF SCIENCE Major: Electrical Engineering Program of Study Committee: Umesh Vaidya, Major Professor Qingze Zou Baskar Ganapathayasubramanian Iowa State University Ames, Iowa 2010 Copyright c Rebecca Marie Johnson, 2010. All rights reserved. ii DEDICATION I gratefully acknowledge everyone who contributed to the successful completion of this research. Bill Piche, my supervisor at Rockwell Collins, was supportive from day one, as were many of my colleagues. I also appreciate the efforts of my thesis committee, Drs. Umesh Vaidya, Qingze Zou, and Baskar Ganapathayasubramanian. I would also like to thank Dr. -
Boeing Submission for Asiana Airlines (AAR) 777-200ER HL7742 Landing Accident at San Francisco – 6 July 2013
Michelle E. Bernson The Boeing Company Chief Engineer P.O. Box 3707 MC 07-32 Air Safety Investigation Seattle, WA 98124-2207 Commercial Airplanes 17 March 2014 66-ZB-H200-ASI-18750 Mr. Bill English Investigator In Charge National Transportation Safety Board 490 L’Enfant Plaza, SW Washington DC 20594 via e-mail: [email protected] Subject: Boeing Submission for Asiana Airlines (AAR) 777-200ER HL7742 Landing Accident at San Francisco – 6 July 2013 Reference: NTSB Tech Review Meeting on 13 February 2014 Dear Mr. English: As requested during the reference technical review, please find the attached Boeing submission on the subject accident. Per your request we are sending this electronic version to your attention for distribution within the NTSB. We would like to thank the NTSB for giving us the opportunity to make this submission. If you have any questions, please don’t hesitate to contact us. Best regardsregards,, Michelle E. E Bernson Chief Engineer Air Safety Investigation Enclosure: Boeing Submission to the NTSB for the subject accident Submission to the National Transportation Safety Board for the Asiana 777-200ER – HL7742 Landing Accident at San Francisco 6 July 2013 The Boeing Company 17 March 2014 INTRODUCTION On 6 July 2013, at approximately 11:28 a.m. Pacific Standard Time, a Boeing 777-200ER airplane, registration HL7742, operating as Asiana Airlines Flight 214 on a flight from Seoul, South Korea, impacted the seawall just short of Runway 28L at San Francisco International Airport. Visual meteorological conditions prevailed at the time of the accident with clear visibility and sunny skies. -
Boeing 737 Postmaintenance Test Flight Encounters Uncommanded Roll-And-Yaw Oscillations
FLIGHT SAFETY FOUNDATION Accident Prevention Vol. 55 No. 5 For Everyone Concerned with the Safety of Flight May 1998 Boeing 737 Postmaintenance Test Flight Encounters Uncommanded Roll-and-yaw Oscillations Fluid leaking from the cabin onto the yaw-damper coupler in the electronic-and-equipment bay affected electronic signals transmitted to the yaw-damper actuator and caused a dutch-roll oscillation. FSF Editorial Staff On Oct. 22, 1995, a Boeing 737-236 Advanced was • “Sufficiently conductive contaminant paths in straight-and-level flight at Flight Level (FL) 200 between certain adjacent pins had affected the (20,000 feet), at an indicated airspeed of 290 knots phase and magnitude of the signals transmitted when roll-and-yaw oscillations began. The flight crew to the yaw-damper actuator, thereby stimulating disengaged the autopilot, autothrottles and yaw a forced dutch-roll mode of the aircraft; damper, but the uncommanded roll-and-yaw oscillations continued. • “The location of the E&E bay — beneath the cabin floor in the area of the aircraft doors, galleys The crew declared an emergency and descended to and toilets — made it vulnerable to fluid ingress 7,000 feet. The oscillations stopped when airspeed was from a variety of sources; [and,] reduced to about 250 knots. After a satisfactory check of the aircraft’s low-speed handling characteristics, the • “The crew actions immediately following the crew returned to London (England) Gatwick Airport onset of the dutch-roll oscillations did not result and landed without further incident. in the disengagement of the malfunctioning yaw- damper system.” The U.K. Air Accidents Investigation Branch (AAIB), in its final report on the incident, identified four causal factors: The B-737, operated by British Airways, was built in 1980 and had accumulated 37,871 hours in service. -
Human Factors of Flight-Deck Checklists: the Normal Checklist
NASA Contractor Report 177549 Human Factors of Flight-Deck Checklists: The Normal Checklist Asaf Degani San Jose State University Foundation San Jose, CA Earl L. Wiener University of Miami Coral Gables, FL Prepared for Ames Research Center CONTRACT NCC2-377 May 1990 National Aeronautics and Space Administration Ames Research Center Moffett Field, California 94035-1000 CONTENTS 1. INTRODUCTION ........................................................................ 2 1.1. The Normal Checklist .................................................... 2 1.2. Objectives ...................................................................... 5 1.3. Methods ......................................................................... 5 2. THE NATURE OF CHECKLISTS............................................... 7 2.1. What is a Checklist?....................................................... 7 2.2. Checklist Devices .......................................................... 8 3. CHECKLIST CONCEPTS ......................................................... 18 3.1. “Philosophy of Use” .................................................... 18 3.2. Certification of Checklists ........................................... 22 3.3. Standardization of Checklists ...................................... 24 3.4. Two/three Pilot Cockpit ............................................... 25 4. AIRLINE MERGERS AND ACQUISITIONS .......................... 27 5. LINE OBSERVATIONS OF CHECKLIST PERFORMANCE.. 29 5.1. Initiation ...................................................................... -
Ac 120-67 3/18/97
Advisory u.s. Department ofTransportation Federal Aviation Circular Ad.nnlstratlon Subject: CRITERIA FOR OPERATIONAL Date: 3/18/97 AC No: 120-67 APPROVAL OF AUTO FLIGHT Initiated By: AFS-400 Change: GUIDANCE SYSTEMS 1. PURPOSE. This advisory circular (AC) states an acceptable means, but not the only means, for obtaining operational approval of the initial engagement or use of an Auto Flight Guidance System (AFGS) under Title 14 of the Code of Federal Regulations (14 CFR) part 121, section 121.579(d); part 125, section 125.329(e); and part 135, section 135.93(e) for the takeoff and initial climb phase of flight. 2. APPLICABILITY. The criteria contained in this AC are applicable to operators using commercial turbojet and turboprop aircraft holding Federal Aviation Administration (FAA) operating authority issued under SPAR 38-2 and 14 CFR parts 119, 121, 125, and 135. The FAA may approve the AFGS operation for the operators under these parts, where necessary, by amending the applicant's operations specifications (OPSPECS). 3. BACKGROUND. The purpose of this AC is to take advantage of technological improvements in the operational capabilities of autopilot systems, particularly at lower altitudes. This AC complements a rule change that would allow the use of an autopilot, certificated and operationally approved by the FAA, at altitudes less than 500 feet above ground level in the vertical plane and in accordance with sections 121.189 and 135.367, in the lateral plane. 4. DEFINITIONS. a. Airplane Flight Manual (AFM). A document (under 14 CFR part 25, section 25.1581) which is used to obtain an FAA type certificate. -
Gemini Series PFD
Gemini Series PFD Installation/User Manual 8300-083 Rev D Table of Contents Table of Contents ............................................................................................................................... 2 Document Revision Level & Notes ................................................................................................................ 4 Instrument Installation ................................................................................................................................... 5 Mounting Considerations................................................................................................................ 5 Wiring Considerations ..................................................................................................................... 5 Pitot and Static Connections .......................................................................................................... 5 RFI/EMI Considerations .................................................................................................................. 6 Getting Acquainted With Your Gemini PFD................................................................................................. 7 Gemini PFD Display........................................................................................................................... 7 Using the Touch Screen.................................................................................................................... 8 Info Page Display...............................................................................................................................