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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. -
Use of Rudder on Boeing Aircraft
12ADOBL02 December 2011 Use of rudder on Boeing aircraft According to Boeing the Primary uses for rudder input are in crosswind operations, directional control on takeoff or roll out and in the event of engine failure. This Briefing Leaflet was produced in co-operation with Boeing and supersedes the IFALPA document 03SAB001 and applies to all models of the following Boeing aircraft: 707, 717, 727, 737, 747, 757, 767, 777, 787, DC-8, DC-9, DC-10, MD-10, md-11, MD-80, MD-90 Sideslip Angle Fig 1: Rudder induced sideslip Background As part of the investigation of the American Airlines Flt 587 crash on Heading Long Island, USA the United States National Transportation Safety Board (NTSB) issued a safety recommendation letter which called Flight path for pilots to be made aware that the use of “sequential full opposite rudder inputs can potentially lead to structural loads that exceed those addressed by the requirements of certification”. Aircraft are designed and tested based on certain assumptions of how pilots will use the rudder. These assumptions drive the FAA/EASA, and other certifica- tion bodies, requirements. Consequently, this type of structural failure is rare (with only one event over more than 45 years). However, this information about the characteristics of Boeing aircraft performance in usual circumstances may prove useful. Rudder manoeuvring considerations At the outset it is a good idea to review and consider the rudder and it’s aerodynamic effects. Jet transport aircraft, especially those with wing mounted engines, have large and powerful rudders these are neces- sary to provide sufficient directional control of asymmetric thrust after an engine failure on take-off and provide suitable crosswind capability for both take-off and landing. -
Faa Ac 20-186
U.S. Department Advisory of Transportation Federal Aviation Administration Circular Subject: Airworthiness and Operational Date: 7/22/16 AC No: 20-186 Approval of Cockpit Voice Recorder Initiated by: AFS-300 Change: Systems 1 GENERAL INFORMATION. 1.1 Purpose. This advisory circular (AC) provides guidance for compliance with applicable regulations for the airworthiness and operational approval for required cockpit voice recorder (CVR) systems. Non-required installations may use this guidance when installing a CVR system as a voluntary safety enhancement. This AC is not mandatory and is not a regulation. This AC describes an acceptable means, but not the only means, to comply with Title 14 of the Code of Federal Regulations (14 CFR). However, if you use the means described in this AC, you must conform to it in totality for required installations. 1.2 Audience. We, the Federal Aviation Administration (FAA), wrote this AC for you, the aircraft manufacturers, CVR system manufacturers, aircraft operators, Maintenance Repair and Overhaul (MRO) Organizations and Supplemental Type Certificate (STC) applicants. 1.3 Cancellation. This AC cancels AC 25.1457-1A, Cockpit Voice Recorder Installations, dated November 3, 1969. 1.4 Related 14 CFR Parts. Sections of 14 CFR parts 23, 25, 27, 29, 91, 121, 125, 129, and 135 detail design substantiation and operational approval requirements directly applicable to the CVR system. See Appendix A, Flowcharts, to determine the applicable regulations for your aircraft and type of operation. Listed below are the specific 14 CFR sections applicable to this AC: • Part 23, § 23.1457, Cockpit Voice Recorders. • Part 23, § 23.1529, Instructions for Continued Airworthiness. -
CESSNA WING TIPS - EMPENNAGE TIPS CESSNA WING TIPS These Wing Tip Kits Consist of a Left and Right Hand Drooped Fiberglass Wing Tip
CESSNA WING TIPS - EMPENNAGE TIPS CESSNA WING TIPS These wing tip kits consist of a left and right hand drooped fiberglass wing tip. These wing tips are better than those manufactured by Cessna because they are made of fiberglass rather than a royalite type material, that bends and CM cracks after a short time on the aircraft. The superior epoxy rather than polyester fiberglass is used. Epoxy fiberglass has major advantages over a royalite type material; It is approximately six timesstronger and twelve times stiffer, it resists ultraviolet light and weathers better, and it keeps its chemical composition intact much longer. With all these advantages, they will probably be the last wingtips that will ever have to be installed on the aircraft. Should these wing tips be damaged through some unforeseen circumstances, they are easily repairable due to their fiberglass construc- tion. These kits are FAA STC’d and manufactured under a FAA PMA authority. The STC allows you to install these WP modern drooped wing tips, even if your aircraft was not originally manufactured with this newer, more aerodynamically efficient wingtip. *Does not include the Plate lens. Plate lens must be purchased separately. **Kits includes the left hand wing tip, right hand wing tip, hardware, and the plate lens Cessna Models Kit No.** Price Per Kit All 150, A150, 152, A152, 170A & B, P172, 175, 205 &L19, 172, 180, 185 for model year up through 1972.182, 206 for 05-01526 . model year up through 1971, 207 from 1970 and up (219-100) ME 05-01545 172, R172K(172XP), 172RG, 180, 185 for model year 1973 and up, 182, 206 for model year 1972 and up. -
Aircraft Winglet Design
DEGREE PROJECT IN VEHICLE ENGINEERING, SECOND CYCLE, 15 CREDITS STOCKHOLM, SWEDEN 2020 Aircraft Winglet Design Increasing the aerodynamic efficiency of a wing HANLIN GONGZHANG ERIC AXTELIUS KTH ROYAL INSTITUTE OF TECHNOLOGY SCHOOL OF ENGINEERING SCIENCES 1 Abstract Aerodynamic drag can be decreased with respect to a wing’s geometry, and wingtip devices, so called winglets, play a vital role in wing design. The focus has been laid on studying the lift and drag forces generated by merging various winglet designs with a constrained aircraft wing. By using computational fluid dynamic (CFD) simulations alongside wind tunnel testing of scaled down 3D-printed models, one can evaluate such forces and determine each respective winglet’s contribution to the total lift and drag forces of the wing. At last, the efficiency of the wing was furtherly determined by evaluating its lift-to-drag ratios with the obtained lift and drag forces. The result from this study showed that the overall efficiency of the wing varied depending on the winglet design, with some designs noticeable more efficient than others according to the CFD-simulations. The shark fin-alike winglet was overall the most efficient design, followed shortly by the famous blended design found in many mid-sized airliners. The worst performing designs were surprisingly the fenced and spiroid designs, which had efficiencies on par with the wing without winglet. 2 Content Abstract 2 Introduction 4 Background 4 1.2 Purpose and structure of the thesis 4 1.3 Literature review 4 Method 9 2.1 Modelling -
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. -
Touring Rudder Sit-On Top Kit Kit to Fit Rudder Enabled Sit-On Tops with a 10Mm Rudder Fixing Point
touring rudder sit-on top kit Kit to fit rudder enabled sit-on tops with a 10mm rudder fixing point. Note: It is easier to fit the Touring Rudder System if you have a screw hatch fitted to the rear stowage area of the kayak. If your kayak does not have this screw hatch and you wish to fit one, please contact a Perception dealer for advice. These instructions explain how to fit the rudder kit to a kayak with or without a rear screw hatch in place. Please make sure you follow the correct steps for your version of sit-on top kayak. This kit should contain the following: 1x rudder assembly with up-haul rope & split ring 4x deck fittings 4x length of rudder hose 5x self tapping screws 2x Dyneema control line - with cord end assembly 2x oval toggle 1x pair of Tip-Toes control footrests with foam washers 1x length of 4mm shock cord 6x footrest screws, washers and nuts - pre-fitted 1x rudder park - inc. hook, shock cord & fixing block You will also require some tools to fit this kit: Drill with 3mm, 5mm and 6mm drill bits Marker pen Short phillips screwdriver Wire cutters Small adjustable spanner or pair of pliers Lighter Tape measure Small amount of sticky tape Please read these instructions carefully before fitting! Step 1 - Control line entry points The rudder will need to have two control lines attached, each one running through hose sections inside the kayak from the rudder to the Tip-Toes footrests. This kit has four hose sections (two pairs) as two sections are needed per control line. -
FEDERAL REGISTER VOLUME 30 • Liulvibeil 249
FEDERAL REGISTER VOLUME 30 • liulviBEil 249 Tuesday, December 28, 1965 • Washington, D.C. Pages 16099-16180 Agencies in this issue— Agricultural Research Service Agricultural Stabilization and Conservation Service Atomic Energy Commission Civil Aeronautics Board Commodity Credit Corporation Consumer and Marketing Service Federal Aviation Agency Federal Home Loan Bank Board Federal Housing Administration Federal Maritime Commission Federal Power Commission Federal Trade Commission Food and Drug Administration General Services Administration Interstate Commerce Commission Land Management Bureau Maritime Administration Public Health Service Reclamation Bureau Detailed list of Contents appears inside. Volume 7 8 UNITED STATES STATUTES AT LARGE [88th Cong., 2d Sess.l Contains laws and concurrent resolu merical listing of bills enacted into tions enacted by the Congress during public and private law, and a guide 1964, the twenty-fourth amendment to the legislative history of bills en to the Constitution, and Presidential acted into public law. proclamations. Included is a nu- Price: $8.75 Published by Office of the Federal Register, National Archives and Records Service, General Services Administration Order from Superintendent of Documents, U.S. Government Printing Office, Washington, D.C., 20402 ¿f' Published, daily, Tuesday through Saturday (no publication on Sundays, Mondays, or on the day after an official Federal holiday), by the Office of the Federal Register, National FERERAL*REGISTER Archives and Records Service, General Services Administration (mail address National Area Code 202 V , »3 4 Phone 963-3261 Archives Building, Washington, D.C. 20408), pursuant to the authority contained in the Federal Register Act, approved July 26, 1935 (49 Stat. 500, as amended; 44 U.S.C., ch. -
Aerosport Modeling Rudder Trim
AEROSPORT MODELING RUDDER TRIM Segment: MOBILITY PARTS PROVIDERS | Engineering companies Application vertical: MOBILITY AND TRANSPORTATION | AircraFt Application type: FINAL PART: Short runs THE CUSTOMER FINAL PART: SHORT RUNS AEROSPORT MODELING RUDDER TRIM COMPANY DESCRIPTION APPLICATION TRADITIONAL MANUFACTURING Some planes are equipped with small tabs on the control surfaces (e.g., rudder trim Assembly of 26 different machined and standard parts Aerosport Modeling & Design was established in tabs, aileron tabs, elevator tabs) so the pilot can make minute adjustments to pitch, September 1996, and since then, they have worked to yaw, and roll to keep the airplane flying a true, clean line through the air. This produce the highest-possible quality prototypes, improves speed by reducing drag from the larger, constant movements of the full appearance models, working models, and machined rudder, aileron, and elevator. parts, and to meet or exceed client expectations. The company strives to be seen as a partner to their Many airplanes also have rudder and/or aileron trim systems. On some, the rudder clients and an extension of their design and trim tab is rigid but adjustable on the ground by bending: It is angled slightly to the development team, not just a supplier of prototyping left (when viewed from behind) to lessen the need for the pilot to push the rudder services. pedal constantly in order to overcome the left-turning tendencies of many prop- driven aircraft. Some aircraft have hinged rudder trim tabs that the pilot can adjust Aerosport Products spun off from sister company in flight. Aerosport Modeling & Design in 2009 to develop products for experimental aircraft, the first of which When a servo tab is employed, it is moved into the slipstream opposite of the was the RV-10 Carbon Fiber Instrument Panel. -
Nonlinear Control of an Aerobatic RC Airplane
Nonlinear Control of an Aerobatic RC Airplane MASSA CHUSETTS INSTITUTE by 0F TECHNOLOGY Joshua John Bialkowski J UN 2 3 2010 B.S., Georgia Institute of Technology (2007) LIBRARIES Submitted to the Department of Aeronautics and Astronautics in partial fulfillment of the requirements for the degree of Master of Science in Aeronautics and Astronautics ARCHIVES at the MASSACHUSETTS INSTITUTE OF TECHNOLOGY May 2010 @ Massachusetts Institute of Technology 2010. All rights reserved. Author .......... .~. .....-.--...--.-.- D ar o % autics and Astronautics May 21, 2010 Certified by..... Prof Emilio Frazzoli Associate Professor of Aeronautics and Astronautics Thesis Supervisor / / IA Accepted by............. / Eytan H. Modiano Associate Professor of Aeronautics and Astronautics Chair, Committee on Graduate Students Nonlinear Control of an Aerobatic RC Airplane by Joshua John Bialkowski Submitted to the Department of Aeronautics and Astronautics on May 21, 2010, in partial fulfillment of the requirements for the degree of Master of Science in Aeronautics and Astronautics Abstract An automatic flight controller based on the ideas of backstepping is applied to an aerobatic RC airplane. The controller asymptotically tracks a time-parameterized position reference, and depends on an orientation look-up rule to detemine the vehicle orientation from a desired acceleration. A coordinated-flight look-up rule compatible with the controller provides a nominal level of capability for traditional flight trajec- tories. A generalized coordinated look-up rule compatible with the controller provides more advanced capability, including stability for high angle of attack and hovering maneuvers, at the expense of an additional requirement from the reference trajectory. Basic simulation results are used to verify the controller, and a simulation software framework is described which will enable more extensive simulation and provide a platform for the final controller implementation. -
Small Lightweight Aircraft Navigation in the Presence of Wind Cornel-Alexandru Brezoescu
Small lightweight aircraft navigation in the presence of wind Cornel-Alexandru Brezoescu To cite this version: Cornel-Alexandru Brezoescu. Small lightweight aircraft navigation in the presence of wind. Other. Université de Technologie de Compiègne, 2013. English. NNT : 2013COMP2105. tel-01060415 HAL Id: tel-01060415 https://tel.archives-ouvertes.fr/tel-01060415 Submitted on 3 Sep 2014 HAL is a multi-disciplinary open access L’archive ouverte pluridisciplinaire HAL, est archive for the deposit and dissemination of sci- destinée au dépôt et à la diffusion de documents entific research documents, whether they are pub- scientifiques de niveau recherche, publiés ou non, lished or not. The documents may come from émanant des établissements d’enseignement et de teaching and research institutions in France or recherche français ou étrangers, des laboratoires abroad, or from public or private research centers. publics ou privés. Par Cornel-Alexandru BREZOESCU Navigation d’un avion miniature de surveillance aérienne en présence de vent Thèse présentée pour l’obtention du grade de Docteur de l’UTC Soutenue le 28 octobre 2013 Spécialité : Laboratoire HEUDIASYC D2105 Navigation d'un avion miniature de surveillance a´erienneen pr´esencede vent Student: BREZOESCU Cornel Alexandru PHD advisors : LOZANO Rogelio CASTILLO Pedro i ii Contents 1 Introduction 1 1.1 Motivation and objectives . .1 1.2 Challenges . .2 1.3 Approach . .3 1.4 Thesis outline . .4 2 Modeling for control 5 2.1 Basic principles of flight . .5 2.1.1 The forces of flight . .6 2.1.2 Parts of an airplane . .7 2.1.3 Misleading lift theories . 10 2.1.4 Lift generated by airflow deflection . -
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.