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STOL CH 701 / 750 Rudder Assembly Manual
STOL CH 701 / 750 Rudder Parts are labeled for easy identification with a part number and description: Part number example: 7R2-1 Rudder Spar 7 - STOL CH 701 model. R - Rudder section of the aircraft drawings. 2 - Page 2 of the Rudder drawings. 1 - Part 1 on page 2. Kit parts that make up the rudder skeleton. Drawing 7-R-0 is for reference only: for building sequence use this step by step photo assembly guide. This manual has been prepared for assembly of the Rudder Starter Kit supplied with the predrilled Rudder Spar, (starting May 2007), and match drilled Bottom Rib, (starting Jan. 2008). Previous versions did not include the predrilled Rudder Spar or match drilled Bottom Rib. In addition to the photo assembly guide, also refer to drawings 7-R-1, 7-R-2 and 7-R-3 (701) or 75-R-1, 75-R-2, and 75RA-1 (750) (drawing number in right bottom corner of the title block). Always refer to the drawings for technical information: material thickness, part dimension, part orientation, layout distances, and rivet sizes, location and spacing. STOL Zenith Aircraft Company Revision 1.7 (02/2010) RUDDER SKELETON, 7-R-2 CH 701 / 750 www.zenithair.com © 2005 Zenith Aircraft Co SECTION 1 - Page 1 of 12 7R2-1 Spar or 75R2-3 Spar Spar Web - term used to refer to the flat area between the flanges. Tool: half round 6” fine (smooth) double cut hand file. Use a file to remove any burs on the edges of the parts and lightly round off corners. -
Easy Access Rules for Auxiliary Power Units (CS-APU)
APU - CS Easy Access Rules for Auxiliary Power Units (CS-APU) EASA eRules: aviation rules for the 21st century Rules and regulations are the core of the European Union civil aviation system. The aim of the EASA eRules project is to make them accessible in an efficient and reliable way to stakeholders. EASA eRules will be a comprehensive, single system for the drafting, sharing and storing of rules. It will be the single source for all aviation safety rules applicable to European airspace users. It will offer easy (online) access to all rules and regulations as well as new and innovative applications such as rulemaking process automation, stakeholder consultation, cross-referencing, and comparison with ICAO and third countries’ standards. To achieve these ambitious objectives, the EASA eRules project is structured in ten modules to cover all aviation rules and innovative functionalities. The EASA eRules system is developed and implemented in close cooperation with Member States and aviation industry to ensure that all its capabilities are relevant and effective. Published February 20181 1 The published date represents the date when the consolidated version of the document was generated. Powered by EASA eRules Page 2 of 37| Feb 2018 Easy Access Rules for Auxiliary Power Units Disclaimer (CS-APU) DISCLAIMER This version is issued by the European Aviation Safety Agency (EASA) in order to provide its stakeholders with an updated and easy-to-read publication. It has been prepared by putting together the certification specifications with the related acceptable means of compliance. However, this is not an official publication and EASA accepts no liability for damage of any kind resulting from the risks inherent in the use of this document. -
Exec Summary (PDF)
BEECHCRAFT® AT-6 The Future of Light Attack is Here. Capable. Affordable. Sustainable. Interoperable. One platform with multiple missions: initial pilot training, weapons training, operational NetCentric ISR and Light Attack capabilities for irregular warfare. The Beechcraft AT-6 is a multi-role, multi-mission aircraft system designed to meet a wide spectrum of warfighter needs: • Based on the proven Beechcraft USAF T-6A and USN T-6B • Designed to accommodate 95% of the aircrew population; widest range in its class • Lockheed Martin plug-and-play mission system architecture adapted from A-10C • Sensor suite adapted from the MC-12W • Flexible, reconfigurable hardpoints with six external store stations Unparalleled attributes with • Long persistence with two aircrew and weapons; up to 1,485 nm self-deployment range a wide range of options. • Extensive variety of weapons including general purpose, laser guided and inertially-aided munitions AIRFRAME AND POWERPLANT • 1,600 shaft horsepower engine • The only fixed-wing aircraft to fire laser guided rockets • ISR suite and six external store hardpoints • Light armor COMBAT MISSION SYSTEMS • Mission systems by Lockheed Martin • NVIS cockpit • Helmet-mounted cueing system • Infrared missile warning and countermeasures COMMUNICATIONS SUITE • Secure voice and data • Rover-compatible full motion video • SADL/Link-16 compatible • SATCOM ISR SUITE • MX-15Di WEAPONS INTEGRATION • 17 60 capable stores management system • .50 Cal Gun • 20mm Gun • 250/500 lb. laser guided GPS or GP bombs • Laser guided missiles • Laser guided rockets • Small 1760 weapons Learn more. Call +1.316.676.0800 or visit Beechcraft.com 13LSAT6HW Specifications and performance are subject to change without notice. -
767, Awl, D622t001-9-01
767-200/300/300F/400ER AIRWORTHINESS LIMITATIONS 767-200/300/300F/400ER AIRWORTHINESS LIMITATIONS (AWLs) D622T001-9-01 JUNE 2019 This document has EAR data with an Export Control Classification Number (ECCN) of 9E991. Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. Boeing claims copyright in each page of this document on to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by the Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact the Boeing Company, P.O. Box 3707, Seattle WA 98124. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, BBJ, DC-8, DC-9, DC-10, MD-10, MD-11, MD-80, MD-88, MD-90, and the red-white-blue Boeing livery are all trademarks owned by The Boeing Company; no trademark license is granted in connection with this document unless provided in writing by Boeing. COMPILED AND PUBLISHED BY: MAINTENANCE PROGRAMS ENGINEERING BOEING COMMERCIAL AIRPLANE GROUP SEATTLE, WASHINGTON D622T001-9-01 JUN 2019 BOEING PROPRIETARY - Copyright -
Air Force Airframe and Powerplant (A&P) Certification Program
Air Force Airframe and Powerplant (A&P) Certification Program Introduction: Most military aircraft maintenance technicians are eligible to pursue the Federal Aviation Administration (FAA) Airframe & Powerplant (A&P) certification based on documented evidence of 30 months practical aircraft maintenance experience in airframe and powerplant systems per Title 14, Code of Federal Regulations (CFR), Part 65- Certification: Airmen Other Than Flight Crew Members; Subpart D-Mechanics. Air Force education, training and experience and FAA eligibility requirements per Title 14, CFR Part 65.77. This FAA-approved program is a voluntary program which benefits the technician and the Air Force, with consideration to professional development, recruitment, retention, and transition. Completing this program, outlined in the program Qualification Training Package (QTP), will assist technicians in meeting FAA eligibility requirements and being better-prepared for the FAA exams. Three-Tier Program: The program is a three-tier training and experience program. These elements are required for program completion and are important for individual development, knowledge assessment, meeting FAA certification eligibility, and preparation for the FAA exams: Three Online Courses (02AF1-General, 02AF2-Airframe, & 02AF3-Powerplant). On the Job Training (OJT) Qualification Training Package(QTP). Documented evidence of 30 months practical experience in airframe and powerplant systems. Program Eligibility: Active duty, guard and reserve technicians who possess at least a 5-skill level in one of the following aircraft maintenance AFSCs are eligible to enroll: 2A0X1, 2A090, 2A2X1, 2A2X2, 2A2X3, 2A3X3, 2A3X4, 2A3X5, 2A3X7, 2A3X8, 2A390, 2A300, 2A5X1, 2A5X2, 2A5X3, 2A5X4, 2A590, 2A500, 2A6X1, 2A6X3, 2A6X4, 2A6X5, 2A6X6, 2A690, 2A691, 2A600 (except AGE), 2A7X1, 2A7X2, 2A7X3, 2A7X5, 2A790, 2A8X1, 2A8X2, 2A9X1, 2A9X2, and 2A9X3. -
Conceptual Design Study of a Hydrogen Powered Ultra Large Cargo Aircraft
Conceptual Design Study of a Hydrogen Powered Ultra Large Cargo Aircraft R.A.J. Jansen University of Technology Technology of University Delft Delft Conceptual Design Study of a Hydrogen Powered Ultra Large Cargo Aircraft Towards a competitive and sustainable alternative of maritime transport by R.A.J. Jansen to obtain the degree of Master of Science at the Delft University of Technology, to be defended publicly on Tuesday January 10, 2017 at 9:00 AM. Student number: 4036093 Thesis registration: 109#17#MT#FPP Project duration: January 11, 2016 – January 10, 2017 Thesis committee: Dr. ir. G. La Rocca, TU Delft, supervisor Dr. A. Gangoli Rao, TU Delft Dr. ir. H. G. Visser, TU Delft An electronic version of this thesis is available at http://repository.tudelft.nl/. Acknowledgements This report presents the research performed to complete the master track Flight Performance and Propulsion at the Technical University of Delft. I am really grateful to the people who supported me both during the master thesis as well as during the rest of my student life. First of all, I would like to thank my supervisor, Gianfranco La Rocca. He supported and motivated me during the entire graduation project and provided valuable feedback during all the status meeting we had. I would also like to thank the exam committee, Arvind Gangoli Rao and Dries Visser, for their flexibility and time to assess my work. Moreover, I would like to thank Ali Elham for his advice throughout the project as well as during the green light meeting. Next to these people, I owe also thanks to the fellow students in room 2.44 for both their advice, as well as the enjoyable chats during the lunch and coffee breaks. -
Airframe Integration
Aerodynamic Design of the Hybrid Wing Body Propulsion- Airframe Integration May-Fun Liou1, Hyoungjin Kim2, ByungJoon Lee3, and Meng-Sing Liou4 NASA Glenn Research Center, Cleveland, Ohio, 44135 Abstract A hybrid wingbody (HWB) concept is being considered by NASA as a potential subsonic transport aircraft that meets aerodynamic, fuel, emission, and noise goals in the time frame of the 2030s. While the concept promises advantages over conventional wing-and-tube aircraft, it poses unknowns and risks, thus requiring in-depth and broad assessments. Specifically, the configuration entails a tight integration of the airframe and propulsion geometries; the aerodynamic impact has to be carefully evaluated. With the propulsion nacelle installed on the (upper) body, the lift and drag are affected by the mutual interference effects between the airframe and nacelle. The static margin for longitudinal stability is also adversely changed. We develop a design approach in which the integrated geometry of airframe (HWB) and propulsion is accounted for simultaneously in a simple algebraic manner, via parameterization of the planform and airfoils at control sections of the wingbody. In this paper, we present the design of a 300-passenger transport that employs distributed electric fans for propulsion. The trim for stability is achieved through the use of the wingtip twist angle. The geometric shape variables are determined through the adjoint optimization method by minimizing the drag while subject to lift, pitch moment, and geometry constraints. The design results clearly show the influence on the aerodynamic characteristics of the installed nacelle and trimming for stability. A drag minimization with the trim constraint yields a reduction of 10 counts in the drag coefficient. -
Fly-By-Wire - Wikipedia, the Free Encyclopedia 11-8-20 下午5:33 Fly-By-Wire from Wikipedia, the Free Encyclopedia
Fly-by-wire - Wikipedia, the free encyclopedia 11-8-20 下午5:33 Fly-by-wire From Wikipedia, the free encyclopedia Fly-by-wire (FBW) is a system that replaces the Fly-by-wire conventional manual flight controls of an aircraft with an electronic interface. The movements of flight controls are converted to electronic signals transmitted by wires (hence the fly-by-wire term), and flight control computers determine how to move the actuators at each control surface to provide the ordered response. The fly-by-wire system also allows automatic signals sent by the aircraft's computers to perform functions without the pilot's input, as in systems that automatically help stabilize the aircraft.[1] Contents Green colored flight control wiring of a test aircraft 1 Development 1.1 Basic operation 1.1.1 Command 1.1.2 Automatic Stability Systems 1.2 Safety and redundancy 1.3 Weight saving 1.4 History 2 Analog systems 3 Digital systems 3.1 Applications 3.2 Legislation 3.3 Redundancy 3.4 Airbus/Boeing 4 Engine digital control 5 Further developments 5.1 Fly-by-optics 5.2 Power-by-wire 5.3 Fly-by-wireless 5.4 Intelligent Flight Control System 6 See also 7 References 8 External links Development http://en.wikipedia.org/wiki/Fly-by-wire Page 1 of 9 Fly-by-wire - Wikipedia, the free encyclopedia 11-8-20 下午5:33 Mechanical and hydro-mechanical flight control systems are relatively heavy and require careful routing of flight control cables through the aircraft by systems of pulleys, cranks, tension cables and hydraulic pipes. -
For Improved Airplane Performance
BLENDED WINGLETS FORFOR IMPROVEDIMPROVED AIRPLANEAIRPLANE PERFORMANCEPERFORMANCE New blended winglets on the Boeing Business Jet and the 737-800 commercial airplane offer operational benefits to customers. Besides giving the airplanes a distinctive appear- ance, the winglets create more efficient flight characteristics in cruise and during takeoff and climbout, which translate into additional range with the same fuel and payload. ROBERT FAYE ROBERT LAPRETE MICHAEL WINTER TECHNICAL DIRECTOR ASSOCIATE TECHNICAL FELLOW PRINCIPAL ENGINEER BOEING BUSINESS JETS AERODYNAMICS TECHNOLOGY STATIC AEROELASTIC LOADS BOEING COMMERCIAL AIRPLANES BOEING COMMERCIAL AIRPLANES BOEING COMMERCIAL AIRPLANES TECHNOLOGY/PRODUCT DEVELOPMENT AERO 16 vertical height of the lifting system (i.e., increasing the length of the TE that sheds the vortices). The winglets increase the spread of the vortices along the TE, creating more lift at the wingtips (figs. 2 and 3). The result is a reduction in induced drag (fig. 4). The maximum benefit of the induced drag reduction depends on the spanwise lift distribution on the wing. Theoretically, for a planar wing, induced drag is opti- mized with an elliptical lift distribution that minimizes the change in vorticity along the span. For the same amount of structural material, nonplanar wingtip 737-800 TECHNICAL CHARACTERISTICS devices can achieve a similar induced drag benefit as a planar span increase; however, new Boeing airplane designs Passengers focus on minimizing induced drag with 3-class configuration Not applicable The 737-800 commercial airplane wingspan influenced by additional 2-class configuration 162 is one of four 737s introduced BBJ TECHNICAL CHARACTERISTICS The Boeing Business Jet design benefits. 1-class configuration 189 in the late 1990s for short- to (BBJ) was launched in 1996 On derivative airplanes, performance Cargo 1,555 ft3 (44 m3) medium-range commercial air- Passengers Not applicable as a joint venture between can be improved by using wingtip Boeing and General Electric. -
Issue No. 4, Oct-Dec
Focal Product Support: Commitment, Cooperation, Communication A SERVICE PUBLICATION OF The Lockheed Aeronautical Systems Company LOCKHEED AERONAUTICAL Product Support organization is determined to provide SYSTEMS COMPANY the highest level of service to each of our customers and every one of our airplanes. This level of support Editor is focused toward our personal commitment to our Charles I. Gale customers, quick and open lines of communication to provide information and receive feedback from our Art Director customers, and full cooperation with our customers Cathy E. Howard to develop a team approach to support. Vol. 20, No. 4, October-December 1993 The support arena has undergone vast change in John Gaffney recent years and LASC Product Support has had to CONTENTS evolve to keep pace and meet our customers’ needs. This evolution has resulted in the customer becoming 2 Focal Point more and more prominent in the market place, competition intensifying, and change John L. Gaffney, Director itself becoming constant. LASC Product Support Product Support has made changes and continues to make changes to respond 3 Ramp Hook Retainer to market conditions. Our customers indicated they wanted: Mislocation Playing mix and match with the A “one-stop shop” for all support services. We have become that “one- hook retainers makes cargo ramp stop shop.” Any element of support needed by a customer can be rigging an exercise in frustration. obtained from a single source within LASC Product Support. 10 Making a Ramp Hook Retainer Competitive prices. We are finalizing teaming arrangements which will Identification Tool allow us to offer customers a full spectrum of parts-new, used, and This locally manufactured shop aid overhauled-at competitive prices, all under the auspices of the original can correctly identify the retainers equipment manufacturer. -
Jason Dunham Cmd Inv
DEPARTMENT OF THE NAVY UNITED STATES FLEET FORCES COMMAND 1562 MITSCHER AVENUE SUITE 250 NORFOLK VA 23551-2487 5830 SerN 00/15 1 7 May 19 FINAL ENDORSEMENT on bf(& ltr of27 Jul 18 From : Commander , U.S. Fleet Forces Command To: File Subj : COMNIAND INVESTIGATION INTO THE DEATH OF ENS SARAH JOY MITCHELL, USN , AT SEA ON 8 JULY 2018 Encl: (64) Voluntary Statement of 16R6 dtd 1 Apr 19 (65) Voluntary Statement of -----b){&) dtd 1 Apr 19 1. I thoroughly reviewed the subject investigation and its endorsements . I approve the findings of fact opinions , and recommendations as previously endorsed and as modified below. 2. Findings of Facts: a. FF 312 added: On the morning of 8 July=~-=--==-=-=,-,,-,:--e-=--==-=-=--=--~ was on the bridge prior to launchino RIB KELLY MILLER and RIB BILLY HAMPTON . After confening with the OOD bJl&J , ll>H& made the decision to execute planned RIB operations . [Encl (21)] b. FF 313 added: The OOD is cha1·ged with "the direct supervi sion of the ship's boats" and is responsible for "ensming that all boat safety regulations are observed" in accordance with reference (c). c. FF 314 added: lliR6 wa s the scheduled OOD for the 0700 - 0930 watch and assumed the watch at 0700. [Encl (17), (22), (64)] d. FF 3 15 added: The boat deck was given pennission from "6f( , thrnugh 6)l6J b)(&) , to load lower , and launch RIB KELLY MILLER and RIB BILLY HAMPTON. Both Rill s were in the water at approxima tely 0910. [Encl (17), (21) , (64)] gave u·ip and shove off orders to the two RIBs before breakaway and then gave them,------- pennission to load , lower and launch when they were rnady. -
B-52, the “Stratofortress”
B-52, The “StratoFortress” Aerodynamics and Performance Build-up Service • Crew – Upper Deck • 2 Pilots • Electronic Warfare Officer • Latest Model – Lower Deck – B-52H • Bombardier – Last B-52H delivered in 1962 • Radar Navigator • Transonic Bomber – Nuclear Payload capable • Deployment – 20 Cruise Missiles – 102 B-52H’s • AGM-86C – 192 B-52G’s • AGM-12 Have Nap • AGM-84 Harpoon – All in Service of USAF as – Up to 50,000 lb ordnance far as we can tell payload – $53.4 million each [1998$] – 51 bombs of 750-lb class Additional Payload • In addition to attack ordnance, B-52H carries: – Norden APQ-156 Multi-mode targeting radar – Terrain Avoidance Radar – Electro-Optical Viewing System (EVS) • Infra-red and low light display used in conjunction with terrain avoidance sensors to navigate in bad weather at low altitudes, or with the nuclear windscreen shielding in place – ECM • ALT-28 jammer • ALQ-117, -115, -172 deception jammers – Optional Stinger Air to Air missiles in aft gun-turret Weight Breakdown • Max TOGW – 505,000 lb • Fuel Weight – 299,434 lb internal – 9,114 lb on non-jettisonable under- wing pylons • Ordnance Weight – 50,000 lb • Airframe operational empty – 146452 lb Basic Geometry • Length: 160.9 ft • Tail Plane • Wing – Horizontal Tail Span: – Span: 185 ft 55.625 ft – Horizontal Tail Plan Area: – Area: 4000 ft^2 ~1004 ft^2 – Root Chord: ~34.5 ft – Mean Chord: 21.62 ft – Vertical Tail Height: – Taper Ratio: 0.37 24.339 ft – Leading Edge Sweep: – Vertical Tail Plan Area: 35° ~451 ft^2 – AR: 8.56 Wing Geometry • Wing Root: 14%