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852 Subpart D—Block Tests; Reciprocating Aircraft Engines
§ 33.37 14 CFR Ch. I (1–1–10 Edition) all attitudes that the applicant estab- installation on the engine must be es- lishes as those the engine can have tablished and recorded. when the aircraft in which it is in- [Amdt. 33–6, 39 FR 35465, Oct. 1, 1974] stalled is in the static ground attitude. (e) If provided as part of the engine, § 33.43 Vibration test. the applicant must show for each fluid (a) Each engine must undergo a vi- injection (other than fuel) system and bration survey to establish the tor- its controls that the flow of the in- sional and bending vibration character- jected fluid is adequately controlled. istics of the crankshaft and the pro- [Doc. No. 3025, 29 FR 7453, June 10, 1964, as peller shaft or other output shaft, over amended by Amdt. 33–10, 49 FR 6851, Feb. 23, the range of crankshaft speed and en- 1984] gine power, under steady state and transient conditions, from idling speed § 33.37 Ignition system. to either 110 percent of the desired maximum continuous speed rating or Each spark ignition engine must 103 percent of the maximum desired have a dual ignition system with at takeoff speed rating, whichever is high- least two spark plugs for each cylinder er. The survey must be conducted and two separate electric circuits with using, for airplane engines, the same separate sources of electrical energy, configuration of the propeller type or have an ignition system of equiva- which is used for the endurance test, lent in-flight reliability. and using, for other engines, the same configuration of the loading device § 33.39 Lubrication system. -
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. -
Turbofan Engine Malfunction Recognition and Response Final Report
07/17/09 Turbofan Engine Malfunction Recognition and Response Final Report Foreword This document summarizes the work done to develop generic text and video training material on the recognition and appropriate response to turbofan engine malfunctions, and to develop a simulator upgrade package improving the realism of engine malfunction simulation. This work was undertaken as a follow-on to the AIA/AECMA report on Propulsion System Malfunction Plus Inappropriate Crew Response (PSM+ICR), published in 1998, and implements some of the recommendations made in the PSM+ICR report. The material developed is closely based upon the PSM+ICR recommendations. The work was sponsored and co-chaired by the ATA and FAA. The organizations involved in preparation and review of the material included regulatory authorities, accident investigation authorities, pilot associations, airline associations, airline operators, training companies and airplane and engine manufacturers. The FAA is publishing the text and video material, and will make the simulator upgrade package available to interested parties. Reproduction and adaptation of the text and video material to meet the needs of individual operators is anticipated and encouraged. Copies may be obtained by contacting: FAA Engine & Propeller Directorate ANE-110 12 New England Executive Park Burlington, MA 01803 1 07/17/09 Contributing Organizations and Individuals Note: in order to expedite progress and maximize the participation of US airlines, it was decided to hold all meetings in North America. European regulators, manufacturers and operators were both invited to attend and informed of the progress of the work. Air Canada Capt. E Jokinen ATA Jim Mckie AirTran Capt. Robert Stienke Boeing Commercial Aircraft Van Winters CAE/ Flight Safety Boeing Capt. -
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. -
Safe Flight Autopower® for Hawker 800 Series Aircraft
® Safe Flight AutoPower For ® Hawker 800 Series Aircraft Chesterfield, MO 636-681-5600 Safe Flight AutoPower® Installed With Experience By West Star Aviation Safe Flight AutoPower® Installed With Experience By West Star Aviation The Mission To deliver the precise management of speed through the control of thrust during all phases of flight to maximize safety, performance and efficiency to the Hawker 800 series of aircraft. The Solution AutoPower® – the automatic throttle system (ATS) from Safe Flight Instrument Corporation. In cruise, the Auto Throttle system is continuously Safe Flight pioneered the development of automatic throttle technology which is now monitoring and adjusting the power levers to standard equipment on most large and medium business jets. AutoPower® systems and offset acceleration due to fuel burn. This results components from Safe Flight are installed on more than 9,000 corporate, commercial, in a fuel saving of 3% or more depending on the length of the flight. and military aircraft worldwide. The Benefits From takeoff to touchdown, AutoPower® ATS is designed to provide precise air speed control and engine target settings. The results are significant performance and safety advantages ranging from reduced crew workload and improved situational awareness to greater passenger comfort and increased aircraft value. Operators also report a 3.5 percent increase in range with the system by better controlling speed at cruise and maximizing fuel burn. The AutoPower® system manages engine power by automatically moving the thrust levers, When the flight crew selects a lower altitude on keeping the pilot aware of the adjustments at all times. Overriding the throttles never takes the Proline 21 system, the Auto Throttle system more force than when the system is not engaged. -
Heavy-Fueled Intermittent Ignition Engines: Technical Issues
Publications 9-2009 Heavy-Fueled Intermittent Ignition Engines: Technical Issues Jeffrey Arthur Schneider Embry-Riddle Aeronautical University Timothy Wilson Embry-Riddle Aeronautical University, [email protected] Christopher Griffis Peter Pierpont Follow this and additional works at: https://commons.erau.edu/publication Part of the Aeronautical Vehicles Commons, and the Propulsion and Power Commons Scholarly Commons Citation Schneider, J. A., Wilson, T., Griffis, C., & Pierpont,. P (2009). Heavy-Fueled Intermittent Ignition Engines: Technical Issues. , (). Retrieved from https://commons.erau.edu/publication/145 This Report is brought to you for free and open access by Scholarly Commons. It has been accepted for inclusion in Publications by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. DOT/FAA/AR-08/42 Heavy-Fueled Intermittent Air Traffic Organization NextGen & Operations Planning Ignition Engines: Office of Research and Technology Development Technical Issues Washington, DC 20591 September 2009 Final Report This document is available to the U.S. public through the National Technical Information Services (NTIS), Springfield, Virginia 22161. U.S. Department of Transportation Federal Aviation Administration NOTICE This document is disseminated under the sponsorship of the U.S. Department of Transportation in the interest of information exchange. The United States Government assumes no liability for the contents or use thereof. The United States Government does not endorse products or manufacturers. Trade or manufacturer's names appear herein solely because they are considered essential to the objective of this report. This document does not constitute FAA certification policy. Consult your local FAA aircraft certification office as to its use. This report is available at the Federal Aviation Administration William J. -
DNVGL-RU-SHIP-Pt4ch3 Rotating Machinery
RULES FOR CLASSIFICATION Ships Edition July 2016 Part 4 Systems and components Chapter 3 Rotating machinery - drivers The content of this service document is the subject of intellectual property rights reserved by DNV GL AS ("DNV GL"). The user accepts that it is prohibited by anyone else but DNV GL and/or its licensees to offer and/or perform classification, certification and/or verification services, including the issuance of certificates and/or declarations of conformity, wholly or partly, on the basis of and/or pursuant to this document whether free of charge or chargeable, without DNV GL's prior written consent. DNV GL is not responsible for the consequences arising from any use of this document by others. The electronic pdf version of this document, available free of charge from http://www.dnvgl.com, is the officially binding version. DNV GL AS FOREWORD DNV GL rules for classification contain procedural and technical requirements related to obtaining and retaining a class certificate. The rules represent all requirements adopted by the Society as basis for classification. © DNV GL AS July 2016 Any comments may be sent by e-mail to [email protected] If any person suffers loss or damage which is proved to have been caused by any negligent act or omission of DNV GL, then DNV GL shall pay compensation to such person for his proved direct loss or damage. However, the compensation shall not exceed an amount equal to ten times the fee charged for the service in question, provided that the maximum compensation shall never exceed USD 2 million. -
Getting to Grips with A320 Family Performance Retention and Fuel Savings
Flight Operations Support & Services Customer Services 1, rond-point Maurice Bellonte, BP 33 31707 BLAGNAC Cedex FRANCE Telephone (+33) 5 61 93 33 33 65 getting to grips with A320 Family performance retention and fuel savings Issue 2 - January 2008 Getting to grips with A320 Family Performance Preface Retention and Fuel Saving TABLE OF CONTENTS 1 Scope .................................................................................................................... 4 2 Introduction....................................................................................................... 4 3 Industry issues................................................................................................. 9 3.1 Environmental Issues..........................................................................10 4 Initiatives ......................................................................................................... 12 4.1 Introduction ........................................................................................12 4.2 Operational Initiatives ........................................................................14 4.2.1 Aircraft operations ..............................................................................14 4.2.2 Cost index ...........................................................................................14 4.2.3 Fuel economy ......................................................................................15 4.2.3.1 Cruise speed.........................................................................................15 -
The Applicability of Electrically Driven Accessories for Turboshaft Engines
E AMEICA SOCIEY O MECAICA EGIEES G 4 E. 4 S., Yr, .Y. 00 e Sociey sa o e esosie o saemes o oiios aace i aes o iscussio a meeigs o e Sociey o o is iisios o Secios, m ® o ie i is uicaios. iscussio is ie oy i e ae is u ise i a ASME oua. aes ae aaiae om ASME o mos ae e meeig. ie i U.S.A. Copyright © 1993 by ASME h Applblt f Eltrll rvn Ar fr rbhft Enn Downloaded from http://asmedigitalcollection.asme.org/GT/proceedings-pdf/GT1993/78910/V03BT16A069/2403672/v03bt16a069-93-gt-313.pdf by guest on 26 September 2021 M. Simon Jarvis Warren J. Ostergren General Electric Aircraft Engines Lynn, Massachusetts Bert Smith Aviation Applied Technology Directorate U. S. Army Aviation and Troop Command Fort Eustis, Virginia Abstract more detailed description of the electric accessories and the engine Improved electrical power generation and actuation systems mounting, and electronics cooling considerations. Given the pre- offer new design approaches for performing the engine control and liminary design of an electric system, a trade study was completed accessory functions in helicopter propulsion systems. Present and the results are presented with a summary of the hardware helicopter technology utilizes turboshaft engines with mechanically experience. driven accessories. These accessories perform the functions of starting, fuel and lube pumping, variable stator actuation and inlet particle separation. This paperdiscusses the applicability of replacing Current Accessory Systems the mechanically driven accessories with their electrically driven Present gas turbine aircraft engines require control and accessory counterparts. -
Wings Over the Bay NEW ZEALAND DIVISION Journal of the Bay of Plenty Branch of the NZ Division, Raes: 02-17 ______
Wings Over the Bay NEW ZEALAND DIVISION Journal of the Bay of Plenty Branch of the NZ Division, RAeS: 02-17 __________________________________________________________________________________________ Welcome to the newsletter for the Bay of was reflected in a graphic which noted composites Plenty Branch, NZ Division, RAeS for February at 50% and metal content down to 20% on leading 2017 edges, engine pylon mounts and elsewhere. Engine cowls too are made from composites. Meeting Recap The February meeting of the Bay of Plenty Branch was held at the clubrooms of the Tauranga Gliding Club on the north west of Tauranga airfield. This was the same venue we had used for the Branch meeting and BBQ last year which was a great place for the AGM and accompanying lecture this year, titled: B787 Operations. The lecture was delivered by Owen Bieleski who holds an ATPL with military transport experience with the RNZAF before embarking on a commercial The extensive use of electric-based systems has career with major airlines overseas. Recently, he almost entirely replaced bleed-air and a good returned home with his family to Tauranga from number of hydraulic-based services. Flight Dubai, where he had flown all six variants B777 controls, too, use fly-by-wire (FBW) with no with Emirates. manual back-up. Owen suggested with the extent of the changes to electrically-based systems, the B787 is sometimes called the ‘electric jet’. Owen explained the B787 is a very different design to its predecessors, with a heavy emphasis on electrical powered systems and multiple layers of automatically managed redundancy. Pilots are alerted to most failures via the EICAS (Engine Indicating and Crew Alerting System) as a Warning, Owen Bieleski showing an RNZAF F27 – Friendship at the start of his Caution or Advisory. -
Aircraft Engine Operation and Malfunction
Airplane Turbofan Engine Operation and Malfunctions Basic Familiarization for Flight Crews Chapter 1 General Principles Introduction the flight crew's understanding and Today's modern airplanes are powered working knowledge of airplane turbine by turbofan engines. These engines are engine operation and malfunctions to the quite reliable, providing years of trouble- topics and depth covered here. Upon free service. However, because of the completing this material, flight crews rarity of turbofan engine malfunctions, should understand that some engine and the limitations of simulating those malfunctions can feel and sound more malfunctions, many flight crews have severe than anything they have ever felt unprepared to diagnose engine experienced; however, the airplane is malfunctions that have occurred. still flyable, and the first priority of the flight crew should remain "fly the The purpose of this text is to provide airplane." straightforward material to give flight crews the basics of airplane engine Propulsion operational theory. This text will also provide pertinent information about malfunctions that may be encountered during the operation of turbofan- powered airplanes, especially those malfunctions that cannot be simulated well and may thus cause confusion. While simulators have greatly improved pilot training, many may not have been programmed to simulate the actual noise, vibration and aerodynamic forces that certain malfunctions cause. In addition, Fig 1 showing balloon with no escape path for it appears that the greater the sensations, the air inside. All forces are balanced. the greater the startle factor, along with greater likelihood the flight crew will try Propulsion is the net force that results to diagnose the problem immediately from unequal pressures. -
Hoofdblad IE 31 December 2020
Nummer 53/20 31 december 2020 Nummer 53/20 2 31 december 2020 Inleiding Introduction Hoofdblad Patent Bulletin Het Blad de Industriële Eigendom verschijnt The Patent Bulletin appears on the 3rd working op de derde werkdag van een week. Indien day of each week. If the Netherlands Patent Office Octrooicentrum Nederland op deze dag is is closed to the public on the above mentioned gesloten, wordt de verschijningsdag van het blad day, the date of issue of the Bulletin is the first verschoven naar de eerstvolgende werkdag, working day thereafter, on which the Office is waarop Octrooicentrum Nederland is geopend. Het open. Each issue of the Bulletin consists of 14 blad verschijnt alleen in elektronische vorm. Elk headings. nummer van het blad bestaat uit 14 rubrieken. Bijblad Official Journal Verschijnt vier keer per jaar (januari, april, juli, Appears four times a year (January, April, July, oktober) in elektronische vorm via www.rvo.nl/ October) in electronic form on the www.rvo.nl/ octrooien. Het Bijblad bevat officiële mededelingen octrooien. The Official Journal contains en andere wetenswaardigheden waarmee announcements and other things worth knowing Octrooicentrum Nederland en zijn klanten te for the benefit of the Netherlands Patent Office and maken hebben. its customers. Abonnementsprijzen per (kalender)jaar: Subscription rates per calendar year: Hoofdblad en Bijblad: verschijnt gratis Patent Bulletin and Official Journal: free of in elektronische vorm op de website van charge in electronic form on the website of the Octrooicentrum