Advisory Circular (AC)
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Lighting up to 7 Times Brighter Than Other LED Landing Lights!
Lighting FAA-PMA Approved AeroLEDs Lighting Increase safety and reduce operating cost! See the Difference... Lighting Know the Difference... • Increased safety • Direct replacement • Up to 80% reduced power consumption • Long life - over 50,000 hours! • Lighter weight - no heavy power supply - save up to 3 lbs • Reduced drag • Zero maintenance • 10x more efficient than incandescent! Increased Safety AeroLED lights allow you to comply with the latest FAA recommendations (Operation Lights On) regarding extended use of taxi, landing, and anti-collision lights without fear of reduced light performance or life. They all feature optimized light color (6500k sunlight equivalent) for proven superior air-to-air recognition. The landing and taxi lights also feature an optional pulsed recognition light mode. Reduced Power Consumption High efficiency LED lights use less than 1/3 the power of halogen bulbs. They significantly reduce the load on the electrical system and they won't dim due to low voltage, typical of low RPM final approaches when you need them most! Postition lights aerodynamic design results in less drag than original equipment! Longer Life - Zero Maintenance All AeroLED products are designed to be a "lifetime buy". They last over 50,000 hours when properly installed and do not degrade with on/off cycles. They are extremely rugged and hardened against all kinds of electrical damage, shock, and vibration. Up to 7 times brighter than other LED landing lights! PAR36 Landing Light Comparison Measured Brightness at 50 Ft. Manufacturer Intensity -
Bell 429 Product Specifications
BELL 429 SPECIFICATIONS BELL 429 SPECIFICATIONS Publisher’s Notice The information herein is general in nature and may vary with conditions. Individuals using this information must exercise their independent judgment in evaluating product selection and determining product appropriateness for their particular purpose and requirements. For performance data and operating limitations for any specific mission, reference must be made to the approved flight manual. Bell Helicopter Textron Inc. makes no representations or warranties, either expressed or implied, including without limitation any warranties of merchantability or fitness for a particular purpose with respect to the information set forth herein or the product(s) and service(s) to which the information refers. Accordingly, Bell Helicopter Textron Inc. will not be responsible for damages (of any kind or nature, including incidental, direct, indirect, or consequential damages) resulting from the use of or reliance on this information. Bell Helicopter Textron Inc. reserves the right to change product designs and specifications without notice. © 2019 Bell Helicopter Textron Inc. All registered trademarks are the property of their respective owners. FEBRUARY 2019 © 2019 Bell Helicopter Textron Inc. Specifications subject to change without notice. i BELL 429 SPECIFICATIONS Table of Contents Bell 429 ..................................................................................................................................1 Bell 429 Specification Summary (U.S. Units) ........................................................................4 -
Estimation of Aircraft Taxi-Out Fuel Burn Using Flight Data Recorder Archives
Estimation of Aircraft Taxi-out Fuel Burn using Flight Data Recorder Archives Harshad Khadilkar∗ and Hamsa Balakrishnany Massachusetts Institute of Technology, Cambridge, MA 02139, USA The taxi-out phase of a flight accounts for a significant fraction of total fuel burn for aircraft. In addition, surface fuel burn is also a major contributor to CO2 emissions in the vicinity of airports. It is therefore desirable to have accurate estimates of fuel consumption on the ground. This paper builds a model for estimation of on-ground fuel consumption of an aircraft, given its surface trajectory. Flight Data Recorder archives are used for this purpose. The taxi-out fuel burn is modeled as a linear function of several factors including the taxi-out time, number of stops, number of turns, and number of acceleration events. The statistical significance of each potential factor is investigated. The parameters of the model are estimated using least-squares regression. Since these parameters are estimated using data from operational aircraft, they provide more accurate estimates of fuel burn than methods that use idealized physical models of fuel consumption based on aircraft velocity profiles, or the baseline fuel consumption estimates provided by the International Civil Aviation Organization. Our analysis shows that in addition to the total taxi time, the number of acceleration events is a significant factor in determining taxi fuel consumption. Nomenclature ICAO International Civil Aviation Organization FDR Flight Data Recorder MTOW Maximum TakeOff Weight Tamb Ambient absolute temperature f Total fuel consumed during taxi-out t Taxi-out time ns Number of stops nt Number of turns na Number of acceleration events I. -
Cockpit Acceptance Check Primo Ingresso Nel Cockpit E Preparazione – PAG 1/2 1. BATTERY SWITCH
Cockpit Acceptance Check Primo Ingresso nel Cockpit e Preparazione – PAG 1/2 1. BATTERY SWITCH ..................................................................ON 2. DC Selector ……………………..…………………………………..…….BAT 3. Panel Lights..........................................................ON if required 4. GROUND POWER (If Available) ..............................................ON 5. AC Selector (if GND POWER On) …………………………...GRD PWR 6. ELECTRICAL HYDRAULIC PUMP SWITCHES (ALL) …..........OFF 7. PAX/CARGO/SERVICE DOOR LIGHT …….…….…CHECK ALL OFF 8. EMERGENCY EXIT lights switch ………...ARMED (Guard DOWN) 9. WING/ENG ANTI-ICE ………………………….…….……………….….OFF 10. EQUIP COOLINGS ……………………………….….………….…NORMAL 11. NO SMOKING / FASTEN BELTS ....…………..………………..….…ON -------------------------------------------------------------------------------------------------------------------------------------- 12. POSITION LIGHT ……………………………………………..…………………ON 13. LOGO LIGHT ………………………………. ON (Night) …………. OFF (Day) Cockpit Acceptance Check Primo Ingresso nel Cockpit e Preparazione – PAG 2/2 Prima dell’accensione dell’APU eseguire il “Test Sistemi Antincendio” Overheat/Fire Protection before APU Start 1. OVERHEAT DETECTOR SWITCHES…………………………………NORMAL 2. TEST SWITCHES …………..………Hold to FAUL/INOP then OVHT/FIRE 3. During TEST Verify: - the FAULT and WHEEL WELL lights illuminate - the FIRE HORN WILL SOUND - the THREE FIRE HANDLES WILL ILLUMINATE - the ENGINE OVERHEAT WILL ILLUMINATE -------------------------------------------------------------------------------------------------------------------------------------- -
Assessment Method of Fuel Consumption and Emissions of Aircraft During Taxiing on Airport Surface Under Given Meteorological Conditions
sustainability Article Assessment Method of Fuel Consumption and Emissions of Aircraft during Taxiing on Airport Surface under Given Meteorological Conditions Ming Zhang * , Qianwen Huang, Sihan Liu and Huiying Li College of Civil Aviation, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China; [email protected] (Q.H.); [email protected] (S.L.); [email protected] (H.L.) * Correspondence: [email protected] or [email protected] Received: 27 September 2019; Accepted: 31 October 2019; Published: 2 November 2019 Abstract: Reducing fuel consumption and emissions of aircrafts during taxiing on airport surfaces is crucial to decrease the operating costs of airline companies and construct green airports. At present, relevant studies have barely investigated the influences of the operation environment, such as low visibility and traffic conflict in airports, reducing the assessment accuracy of fuel consumption and emissions. Multiple aircraft ground propulsion systems on airport surfaces, especially the electric green taxiing system, have attracted wide attention in the industry. Assessing differences in fuel consumption and emissions under different taxiing modes is difficult because environmental factors were hardly considered in previous assessments. Therefore, an innovative study was conducted based on practical running data of quick access recorders and climate data: (1) Low visibility and taxiing conflict on airport surfaces were inputted into the calculation model of fuel consumption to set up a modified model of fuel consumption and emissions. (2) Fuel consumption and emissions models under full- and single-engine taxiing, external aircraft ground propulsion systems, and electric green taxiing system could accurately estimate fuel consumption and emissions under different taxiing modes based on the modified model. -
Ice and Rain Protection
SECTION II AIRPLANE AND SYSTEMS MODEL 680 ICE AND RAIN PROTECTION The anti-ice systems are designed to prevent ice formation on the pitot tubes, static ports, angle-of-attack probes, ram air temperature (RAT) probes, engines, wings, wing roots, horizontal stabilizer leading edges, windshields, and overboard water drain lines. The vertical stabilizer does not require anti-icing. The various anti-icing systems use electrical heating elements or hot engine bleed air, and are activated by switches and knobs on the instrument panels. There are many engine instrument and crew alerting system (EICAS) messages that pertain to operation of the anti-icing systems. Some are discussed here, but most are covered in detail under Engine Indicating and Crew Alerting System (EICAS), in Section Three of this manual. ICE AND RAIN PROTECTION Figure 2-23 2-70 Configuration AA 68OM-00 SECTION II MODEL 680 AIRPLANE AND SYSTEMS ANTI-ICE CONTROL PANEL Figure 2-24 DC electric power is used to anti-ice the pitot tubes and static ports, the AOA probes, the ram air temperature (RAT) probes. AC electric power is used for the cockpit windshields and front side windows. High-pressure, or low-pressure bleed air is used to anti-ice the wing leading edges, the wing-mounted landing lights, and the horizontal stabilizer leading edges. Windshield, pitot/static and AOA anti-ice are normally operated full-time in flight. 68OM-00 Configuration AA 2-71 SECTION II AIRPLANE AND SYSTEMS MODEL 680 PITOT-STATIC AND ANGLE-OF-ATTACK (AOA) PROBE ANTI-ICE Electric elements heat the pilot and copilot pitot tubes, static ports, AOA probes, and standby pitot/static system. -
Automation of Taxiing Jaroslav Burs´Ik1, Jakub Kraus1*, Marek Stumperˇ 1
Czech Technical University in Prague Magazine of Aviation Development Faculty of Transportation Sciences 5(1):6-11, 2017, ISSN: 1805-7578 Department of Air Transport DOI: 10.14311/MAD.2017.01.01 Automation of Taxiing Jaroslav Burs´ık1, Jakub Kraus1*, Marek Stumperˇ 1 1Department of Air Transport, Faculty of Transportation Sciences, Czech Technical University in Prague, Prague, Czech Republic *Corresponding author: Czech Technical University in Prague, Faculty of Transportation Sciences, Department of Air Transport, Horska´ 3, 128 03 Prague, Czech Republic, Email: [email protected] Abstract The article focuses on the possibility of automation of taxiing, which is the part of a flight, which, under adverse weather conditions, greatly reduces the operational usability of an airport, and is the only part of a flight that has not been affected by automation, yet. Taxiing is currently handled manually by the pilot, who controls the airplane based on information from visual perception. The article primarily deals with possible ways of obtaining navigational information, and its automatic transfer to the controls. Analyzed wand assessed were currently available technologies such as computer vision, Light Detection and Ranging and Global Navigation Satellite System, which are useful for navigation and their general implementation into an airplane was designed. Obstacles to the implementation were identified, too. The result is a proposed combination of systems along with their installation into airplane’s systems so that it is possible to use the automated taxiing. Keywords Aircraft control — Automation — Safety — Taxiing — Taxiway 1. Introduction The use of GNSS (with or without augmentation) as a single source of navigational data, for navigating on taxiways, has certain limitations. -
Part 27 Instructions for Continued Airworthiness
Part 27 Instructions for Continued Airworthiness (ICA) INCLUDING INSTALLATION INSTRUCTIONS SunSpot 36 AND 46 LANDING AND TAXI LIGHTS INSTALLED ON AIRCRAFT LISTED IN APPROVED MODEL LIST, ST-20-502-01-1 AeroLEDs, LLC 8475 W. Elisa St. Boise, ID, 83709 208-850-3294 NOTE: A printed copy of this document may not be the latest revision. It is the responsibility of the user to ensure that the latest revision is used. The latest revision of this document may be printed from the AeroLEDs electronic document repository. Revision history follows on page 2 This document contains proprietary information of AeroLEDs. Neither receipt nor possession thereof confer any right to reproduce or use, or disclose, in whole or in part, any such information without written permission from AeroLEDs. Approval Name Intent Author Ryan Edmark Check Nate Calvin Installation and Operation Instructions for the Sunspot 36 and 46 series Quality Mark McCormack lights. Date: 23 February 2021 Typed signatures indicate approval. Handwritten, Status: or electronic signature approval of this document Document Number Revision Released is on file at AeroLEDs, Boise, Idaho. 0027-0001 A 0027-0001 Part 27 Instructions for Continued Airworthiness including Installation Instructions Rev_A.docx Page 1 of 20 REVISION RECORD Rev Description Date Author IR Initial Revision 12/01/2020 R. Edmark A Updated to include Pulse Function use on lights 02/23/2021 E. Allen Please visit www.aeroleds.com to verify the revision is current. 0027-0001 Part 27 Instructions for Continued Airworthiness including Installation Instructions Rev_A.docx Page 2 of 20 TABLE OF CONTENTS System Description ....................................................................................................................................................... 4 Model Numbers ............................................................................................................................................................ -
Chapter 5: Airport 5: Airport Facility Facilityrequirements Requirements 75 75
LAST UPDATE JULY 2013 Acknowledgements The preparation of this document was financed in part by a grant from the Federal Aviation Administration (Project No: 3-27-0000-07-10), with the financial support of the MnDOT Office of Aeronautics. The contents do not necessarily reflect the official views or the policy of the FAA. Acceptance of this report does not in any way constitute a commitment to fund the development depicted herin. Document prepared by MnDOT Office of Aeronautics and HNTB Corporation. MINNESOTA GO STATE AVIATION SYSTEM PLAN TABLE OF CONTENTS Chapter 1: Introduction and System Goals 1 Chapter 2: Inventory 29 Chapter 3: Forecast 43 Chapter 4: Airline Service 63 ChapterChapter 5: Airport 5: Airport Facility FacilityRequirements Requirements 75 75 Chapter 6: Performance Report 97 Chapter 7: Investment Plan and System Recommendations 161 Chapter 8: A Future Vision of Aviation 195 Appendices 215 CHAPTER 5 AIRPORT FACILITY REQUIREMENTS This page intentionally left blank. MINNESOTA GO STATE AVIATION SYSTEM PLAN Chapter 5 AIRPORT FACILITY REQUIREMENTS CHAPTER 5 AIRPORT FACILITY REQUIREMENTS PAGE 75 This page intentionally left blank. PAGE 76 MINNESOTA GO STATE AVIATION SYSTEM PLAN AIRPORT FACILITY REQUIREMENTS This chapter outlines the state’s airport facility requirements necessary to accommodate aviation demand in Minnesota over the next 20 years as well as the processes and assumptions used to analyze them. Airport facility requirements are useful in planning how to expend anticipated revenues and are identified through consideration of an individual airport’s existing facilities (Chapter 2: Inventory), airport activity forecasts (Chapter 3: Forecast), and certain minimum objectives established for the system (Table 5-2). -
Greener Aircraft Taxiing: Single-Engine Taxi-Out Evaluations
Greener Aircraft Taxiing: Single-Engine Taxi-out Evaluations Giuseppe Pillirone Air France Aviation Commitment to Environmental Sustainability • Aviation’s contribution to man-made greenhouse gas emissions is 2 - 3% • The Aviation Industry is aware of its environmental impact, and is committed to reducing it further in its mission to "bring people and cargo all over the world" … • Airlines continue to invest into more efficient aircraft, more efficient operations, and the development of sustainable aviation fuels • Key figures for AF-KLM Group (Source: AF-KLM Sustainability Report 2019) 30% 22 32% 43% 31% less CO2 emissions lower CO2 emissions new, quieter, more noise reduction per less non- recycled by ground per passenger/km efficient aircraft movement waste compared to operations compared to 2005 added to the fleet compared to 2000 2011 compared to 2018 • Focusing on Flight Operations • Fuel-efficient procedures are constantly studied and applied in operations whenever possible: Flight plan precision, Speed adjustments and Optimized procedures, Landing configurations, and, on the ground, Taxiing with one engine off Single-Engine Taxiing • Aircraft taxiing operations are a significant source of energy consumption and emissions at airports • Moving on ground ("taxiing") is a short part of a flight, but in this phase jet engines are not at their optimal use • Several measures can reduce fuel-burn during ground operations • "wait on stand" thanks to A-CDM/TSAT, minimize usage of APU, optimum taxi speed, … • One improvement is to taxi with -
National Transportation Safety Board Aviation Accident Final Report
National Transportation Safety Board Aviation Accident Final Report Location: COLO SPRINGS, CO Accident Number: FTW98FA074 Date & Time: 12/21/1997, 0626 MST Registration: N100BE Aircraft: Beech A100 Aircraft Damage: Destroyed Defining Event: Injuries: 2 Fatal, 1 Serious Flight Conducted Under: Part 135: Air Taxi & Commuter - Non-scheduled Analysis The pilot was cleared for an ILS DME approach to runway 17L. During the final stage of the approach, the aircraft entered fog and disappeared from view of the control tower personnel. Radar and radio communications were lost also. After searching for 31 minutes, the aircraft was found by airport operations personnel over half way down the runway and 600 feet east of the runway. There was no evidence the aircraft touched down on the runway. The aircraft was configured with the landing gear up and the flaps deployed. Missed approach procedures require the flaps and landing gear to be retracted after initiating the procedure. The decision height for the approach is 6,384 feet msl (200 feet above ground level) and the required RVR for a 14 CFR Part 135 flight to commence and approach is 2400 (1/2 mile). When on the glide slope, the decision height is 0.4 miles from the runway touchdown zone. Examination of the airplane did not disclose evidence of mechanical malfunction.. Probable Cause and Findings The National Transportation Safety Board determines the probable cause(s) of this accident to be: Failure of the pilot to follow IFR Procedures and maintain the minimum descent altitude (MDA). A related factor was fog. Findings Occurrence #1: IN FLIGHT COLLISION WITH TERRAIN/WATER Phase of Operation: MISSED APPROACH (IFR) Findings 1. -
(VL for Attrid
ECCAIRS Aviation 1.3.0.12 Data Definition Standard English Attribute Values ECCAIRS Aviation 1.3.0.12 VL for AttrID: 391 - Event Phases Powered Fixed-wing aircraft. (Powered Fixed-wing aircraft) 10000 This section covers flight phases specifically adopted for the operation of a powered fixed-wing aircraft. Standing. (Standing) 10100 The phase of flight prior to pushback or taxi, or after arrival, at the gate, ramp, or parking area, while the aircraft is stationary. Standing : Engine(s) Not Operating. (Standing : Engine(s) Not Operating) 10101 The phase of flight, while the aircraft is standing and during which no aircraft engine is running. Standing : Engine(s) Start-up. (Standing : Engine(s) Start-up) 10102 The phase of flight, while the aircraft is parked during which the first engine is started. Standing : Engine(s) Run-up. (Standing : Engine(s) Run-up) 990899 The phase of flight after start-up, during which power is applied to engines, for a pre-flight engine performance test. Standing : Engine(s) Operating. (Standing : Engine(s) Operating) 10103 The phase of flight following engine start-up, or after post-flight arrival at the destination. Standing : Engine(s) Shut Down. (Standing : Engine(s) Shut Down) 10104 Engine shutdown is from the start of the shutdown sequence until the engine(s) cease rotation. Standing : Other. (Standing : Other) 10198 An event involving any standing phase of flight other than one of the above. Taxi. (Taxi) 10200 The phase of flight in which movement of an aircraft on the surface of an aerodrome under its own power occurs, excluding take- off and landing.