Section 3 - British Airways Fleet
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Limits to Principles of Electric Flight
AIRCRAFT DESIGN AND SYSTEMS GROUP (AERO) Limits to Principles of Electric Flight Dieter Scholz Hamburg University of Applied Sciences https://doi.org/10.5281/zenodo.4072283 Deutscher Luft- und Raumfahrtkongress 2019 German Aerospace Congress 2019 Darmstadt, Germany, 30.09. - 02.10.2019 Abstract Purpose – This presentation takes a critical look at various electric air mobility concepts. With a clear focus on requirements and first principles applied to the technologies in question, it tries to bring inflated expectations down to earth. Economic, ecologic and social (noise) based well accepted evaluation principles are set against wishful thinking. Design/methodology/approach – Aeronautical teaching basics are complemented with own thoughts and explanations. In addition, the results of past research and student projects are applied to the topic. Find ings – Electric air mobility may become useful in some areas of aviation. Small short-range general aviation aircraft may benefit from battery-electric or hybrid-electric propulsion. Urban air mobility in large cities will give time advantages to super-rich people, but mass transportation in cities will require a public urban transport system. Battery- electric passenger aircraft are neither economic nor ecologic. How overall advantages can be obtained from turbo- electric distributed propulsion (without batteries) is not clear. Maybe turbo-hydraulic propulsion has some weight advantages over the electric approach. Research limitations/implications – Research findings are from basic considerations only. A detailed evaluation of system principles on a certain aircraft platform may lead to somewhat different results. Practical implications – The discussion about electric air mobility concepts may get more factual. Investors may find some of the information provided easy to understand and helpful for their decision making. -
CRD) to Notice of Proposed Amendment (NPA) 03-2006
Comment Response Document (CRD) to Notice of Proposed Amendment (NPA) 03-2006 for amending the Executive Director Decision No. 2005/07/R of 19 December 2005 on acceptable means of compliance and guidance material to Commission Regulation (EC) No 2042/2003 of 20 November 2003 on the continuing airworthiness of aircraft and aeronautical products, parts and appliances, and on the approval of organisations and personnel involved in these tasks APPENDIX I AIRCRAFT TYPE RATINGS FOR PART-66 AIRCRAFT MAINTENANCE LICENCE CRD to NPA 03/2006 Explanatory Note I. General 1. The purpose of the Notice of Proposed Amendment (NPA) 03/2006, dated 20 April 2006 was to propose an amendment to Decision N° 2005/07/R of the Executive Director of the Agency of 19 December 2005 on acceptable means of compliance and guidance material to Commission Regulation (EC) No 2042/2003 of 20 November 2003 on the continuing airworthiness of aircraft and aeronautical products, parts and appliances, and on the approval of organisations and personnel involved in these tasks (ED Decision 2005/07/R). II. Consultation 2. The draft Executive Director Decision (ED Decision) amending ED Decision 2005/07/R was published on the web site (www.easa.europa.eu) on 21 April 2006. By the closing date of 2 June 2006, European Aviation Safety Agency (the Agency) had received 107 comments from 20 National Aviation Authorities, professional organisations and private companies. III. Publication of the CRD 3. All comments received have been acknowledged and incorporated into a Comment Response Document (CRD). This CRD contains a list of all persons and/or organisations that have provided comments and the answers of the Agency. -
Download This Investigation Report In
AVIATION INVESTIGATION REPORT A10P0242 LOSS OF ENGINE POWER AND LANDING ROLLOVER TRANSWEST HELICOPTERS LTD. BELL 214B-1 (HELICOPTER), C-GTWV LILLOOET, BRITISH COLUMBIA, 20 NM NW 29 JULY 2010 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 Investigation Report Loss of Engine Power and Landing Rollover Transwest Helicopters Ltd. Bell 214B-1 (Helicopter), C-GTWV Lillooet, British Columbia, 20 nm NW 29 July 2010 Report Number A10P0242 Summary The Transwest Helicopters Ltd. Bell 214B-1 helicopter (registration C-GTWV, serial number 28048), with 2 pilots onboard, was engaged in firefighting operations approximately 20 nautical miles northwest of Lillooet, British Columbia. At 1124 Pacific Daylight Time, after refilling the water bucket, the helicopter was on approach to its target near a creek valley. As the helicopter slowed and started to descend past a ridgeline into the creek valley, the engine lost power. The pilot-in-command, seated in the left-hand seat, immediately turned the helicopter left to climb back over the ridgeline to get to a clearing, released the water bucket and the 130-foot long-line from the belly hook, and descended toward an open area to land. The helicopter touched down hard on uneven, sloping terrain, and pitched over the nose. When the advancing main-rotor blade contacted the ground, the airframe was in a near-vertical, nose-down attitude, which then rotated the fuselage, causing it to land on the left side. -
Design of a Business Jet
Design of a Business Jet a project presented to The Faculty of the Department of Aerospace Engineering San José State University in partial fulfillment of the requirements for the degree Master of Science in Aerospace Engineering by Nicholas Dea August 2018 approved by Dr. Nikos Mourtos Faculty Advisor Chapter 1 Introductory Literature Review 1.1 Motivation Currently, there are several factors that contribute to the negative connotations that come with air travel. Some issues that are most often negatively associated with flying are personal space and safety. These issues are at the forefront of today’s topics as airlines are doing their best to maximize profits, while leaving passengers in the rear-view mirror. One example of a reduction in one’s personal space would be in the journal article presented by Govindaraju and Crossley [1]. In their observations and analysis, they determined that the most profitable travel for airlines were not on large passenger transports with maximized seating, but rather with smaller regional jets whom are able to fly shorter distances, yet make a higher number of trips between the destinations. Others may argue that a reduction in personal space may be a hinderance on emergency evacuations as the volume of passengers that must exit the plane in confined spaces will take considerably more time than fewer passengers in wider more open aisles and seats. Safety refers to a multitude of factors, for instance, security checkpoints as well as turbulence or airplane mechanical or technical issues. Safety is an issue as the public and those setting the regulations have a distance between the two as to what the objective of the security measures are meant for, as discussed in the article by David Caskey [2]. -
United States Patent (Io) Patent No.: US 9,909,505 B2 Gallagher Et Al
11111111111111111111111111111111111111111111111111111111111111111111111111 (12) United States Patent (io) Patent No.: US 9,909,505 B2 Gallagher et al. (45) Date of Patent: *Mar. 6, 2018 (54) EFFICIENT, LOW PRESSURE RATIO (58) Field of Classification Search PROPULSOR FOR GAS TURBINE ENGINES CPC ... F02K 3/06; F02K 1/06; FO1D 5/282; FO1D 17/14; FO1D 5/147; FO1D 15/12; (71) Applicant: United Technologies Corporation, Hartford, CT (US) (Continued) (72) Inventors: Edward J. Gallagher, West Hartford, (56) References Cited CT (US); Byron R. Monzon, Cromwell, CT (US); Shari L. Bugaj, U.S. PATENT DOCUMENTS Haddam, CT (US) 3,287,906 A 11/1966 McCormick 3,468,473 A 9/1969 Davies et al. (73) Assignee: United Technologies Corporation, (Continued) Farmington, CT (US) FOREIGN PATENT DOCUMENTS (*) Notice: Subject to any disclaimer, the term of this patent is extended or adjusted under 35 EP 1712738 10/2006 U.S.C. 154(b) by 17 days. G13 1516041 6/1978 This patent is subject to a terminal dis- (Continued) claimer. OTHER PUBLICATIONS (21) Appl. No.: 14/695,373 Gray, D.E. et al. (1978). Energy efficient engine preliminary design (22) Filed: Apr. 24, 2015 and integration study. United Technologies Corporation; Pratt & Whitney Aircraft Group. Prepared for NASA. Nov. 1, 1978. pp. (65) Prior Publication Data 1-366. US 2016/0201607 Al Jul. 14, 2016 (Continued) Related U.S. Application Data Primary Examiner Carlos A Rivera (63) Continuation-in-part of application No. 13/484,858, (74) Attorney, Agent, or Firm Carlson, Gaskey & Olds, filed on May 31, 2012, now Pat. No. 9,121,368, and P.C. -
DEVELOPMENT of ACTIVE SURGE CONTROL DEVICES for CENTRIFUGAL COMPRESSORS (Centrifugális Kompresszorok Aktív Pompázs Szabályozó Eszközeinek Fejlesztése)
DEVELOPMENT OF ACTIVE SURGE CONTROL DEVICES FOR CENTRIFUGAL COMPRESSORS (Centrifugális kompresszorok aktív pompázs szabályozó eszközeinek fejlesztése) by KÁROLY BENEDA Submitted in partial fulfillment of the requirements for the degree of Doctor of Philosophy Supervisor Prof. József Rohács DEPARTMENT OF AERONAUTICS, NAVAL ARCHITECTURE AND RAILWAY VEHICLES Budapest University of Technology and Economics BUDAPEST, HUNGARY June 2013 NYILATKOZAT Alulírott Beneda Károly kijelentem, hogy ezt a doktori értekezést magam készítettem és abban csak a megadott forrásokat használtam fel. Minden olyan részt, amelyet szó szerint, vagy azonos tartalomban, de átfogalmazva más forrásból átvettem, egyértelműen, a forrás megadásával megjelöltem. Budapest, 2013. június ___________________________ Beneda Károly Az értekezésről készült bírálatok és a jegyzőkönyv a későbbiekben a Budapesti Műszaki és Gazdaságtudományi Egyetem Közlekedésmérnöki és Járműmérnöki Karának Dékáni Hivatalában elérhetőek. ACKNOWLEDGEMENTS As first my deepest grateful acknowledgements are due to my wife, Csilla, who has made me it possible to keep up with my work taking all the duties in the family, caring about our two sons unsparing her efforts. Her true love has helped me through all the hard periods. Then I have to thank my parents who have supported me to find my way in the life. I would like to express my gratitude to my present advisor, Professor József Rohács for the valuable support, guidance and suggestions throughout my work. I also wish to thank Professor Imre Sánta for his conscientious assistance even after his retirement. I am thankful to Árpád Veress, my roommate, for the useful remarks during our frequent discussions. I would like to express my special thanks for Vilmos Csomor and György Székely, the colleagues in the Department Laboratory, who have manufactured all required devices for my work. -
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1111111111111111111inuuu1111111111u~ (12) United States Patent (io) Patent No.: US 9,926,885 B2 Gallagher et al. (45) Date of Patent: Mar. 27, 2018 (54) EFFICIENT, LOW PRESSURE RATIO (56) References Cited PROPULSOR FOR GAS TURBINE ENGINES U.S. PATENT DOCUMENTS (71) Applicant: United Technologies Corporation, 2,258,792 A 4/1941 New Farmington, CT (US) 2,936,655 A 5/1960 Peterson et al. (Continued) (72) Inventors: Edward J. Gallagher, West Hartford, CT (US); Byron R. Monzon, FOREIGN PATENT DOCUMENTS Cromwell, CT (US) EP 0791383 8/1997 (73) Assignee: UNITED TECHNOLOGIES EP 1142850 10/2001 CORPORATION, Farmington, CT (Continued) (US) OTHER PUBLICATIONS (*) Notice: Subject to any disclaimer, the term of this patent is extended or adjusted under 35 McMillian, A.(2008) Material development for fan blade contain- U.S.C. 154(b) by 0 days. ment casing. Abstract. p. 1. Conference on Engineering and Physics: Synergy for Success 2006. Journal of Physics: Conference Series (21) Appl. No.: 15/709,540 vol. 105. London, UK. Oct. 5, 2006. (22) Filed: Sep. 20, 2017 (Continued) (65) Prior Publication Data Primary Examiner Zelalem Eshete US 2018/0023511 Al Jan. 25, 2018 (74) Attorney, Agent, or Firm Carlson, Gaskey & Olds, Related U.S. Application Data P.C. (63) Continuation of application No. 15/252,689, filed on Aug. 31, 2016, which is a continuation of application (57) ABSTRACT (Continued) A gas turbine engine includes a bypass flow passage that has (51) Int. Cl. an inlet and defines a bypass ratio in a range of approxi- F02K 3/075 (2006.01) mately 8.5 to 13.5. -
The Revista Aérea Collection
The Revista Aérea Collection Dan Hagedorn and Pedro Turina 2008 National Air and Space Museum Archives 14390 Air & Space Museum Parkway Chantilly, VA 20151 [email protected] https://airandspace.si.edu/archives Table of Contents Collection Overview ........................................................................................................ 1 Administrative Information .............................................................................................. 1 Historical Note.................................................................................................................. 2 Arrangement..................................................................................................................... 2 Scope and Content Note................................................................................................. 2 Names and Subjects ...................................................................................................... 3 Container Listing ............................................................................................................. 4 Series A: Aircraft...................................................................................................... 4 Series B: Propulsion............................................................................................. 218 Series C: Biography............................................................................................. 262 Series D: Organizations...................................................................................... -
REPARACIÓN Y MANTENIMIENTO DE AERONAVES CLASE 2 Los Alcances Y Limitaciones Arriba Listados Quedan
(SERVICIO AL PÚBLICO) REPARACIÓN Y MANTENIMIENTO DE AERONAVES CLASE 2 Los alcances y limitaciones arriba listados quedan sujetos conforme al documento Certificado de Estación de Reparación núm. WTXR173J, de la tabla de contenido parte A 003 Rev. 17, Autorizado por la Federal Aviation Administration (FAA) de los Estados Unidos de Norteamérica. REPARACIÓN Y MANTENIMIENTO DE AERONAVES CLASE 3 Los alcances y limitaciones arriba listados quedan sujetos conforme al documento Certificado de Estación de Reparación núm. MARCA MODELO WTXR173J, de la tabla de contenido parte A 003 Rev. 17, Autorizado por la CESSNA 441, Federal Aviation Administration (FAA) 525, de los Estados Unidos de 525A. Norteamérica. EMBRAER EMB-500 (PHENOM 100) MARCA MODELO CESSNA 441, 525, 525A. EMBRAER EMB-500 (PHENOM 100) MARCA MODELO CESSNA 550, S550, 560/XL, MARCA MODELO REPARACIÓN Y MANTENIMIENTO DE AERONAVES CLASE 4 Los alcances y limitaciones arriba listados quedan sujetos conforme al documento Certificado de Estación de Reparación núm. WTXR173J, de la tabla de contenido parte A 003 Rev. 17, Autorizado por la Federal Aviation Administration (FAA) de los Estados Unidos de Norteamérica. REPARACIÓN Y MANTENIMIENTO DE MOTORES CLASE 3 MARCA MODELO CESSNA 441, 525, 525A. EMBRAER EMB-500 (PHENOM 100) MARCA MODELO CESSNA 550, S550, 560/XL MARCA MODELO CESSNA 441, 525, 525A. EMBRAER EMB-500 (PHENOM 100) MARCA MODELO CESSNA 550, S550, MARCA MODELO 560/XL REPARACIÓN Y MANTENIMIENTO DE MOTORES CLASE 3 (Continuación) Los alcances y limitaciones arriba listados quedan sujetos conforme al documento Certificado de Estación de Reparación núm. WTXR173J, de la tabla de contenido parte A 003 Rev. 17, Autorizado por la Federal Aviation Administration (FAA) de los Estados Unidos de Norteamérica. -