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Remote Pilot – Small Unmanned Aircraft Systems Study Guide
F FAA-G-8082-22 U.S. Department of Transportation Federal Aviation Administration Remote Pilot – Small Unmanned Aircraft Systems Study Guide August 2016 Flight Standards Service Washington, DC 20591 This page intentionally left blank. Preface The Federal Aviation Administration (FAA) has published the Remote Pilot – Small Unmanned Aircraft Systems (sUAS) Study Guide to communicate the knowledge areas you need to study to prepare to take the Remote Pilot Certificate with an sUAS rating airman knowledge test. This Remote Pilot – Small Unmanned Aircraft Systems Study Guide is available for download from faa.gov. Please send comments regarding this document to [email protected]. Remote Pilot – Small Unmanned Aircraft Systems Study Guide i This page intentionally left blank. Remote Pilot – Small Unmanned Aircraft Systems Study Guide ii Table of Contents Introduction ........................................................................................................................... 1 Obtaining Assistance from the Federal Aviation Administration (FAA) .............................................. 1 FAA Reference Material ...................................................................................................................... 1 Chapter 1: Applicable Regulations .......................................................................................... 3 Chapter 2: Airspace Classification, Operating Requirements, and Flight Restrictions .............. 5 Introduction ........................................................................................................................................ -
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. -
Aero Twin, Inc. STC for Rudder Gust Lock
-- ST02540AK Aero Twin, Inc. 2403 Merrill Field Drive Anchorage, AK 99501 A43EU Airbus Defense and Space S. A. C-212-CB, CC, CD, CE, CF, DF, DE Fabrication and installation of Aero Twin, Inc., Rudder Gust Lock Kit No. 4111-212 on Airbus Defense and Space S. A. C-212 aircraft in accordance with Aero Twin, Inc., Master Data List No. 4111-212-MDL, Original Issue, dated May 8, 2020, or later FAA approved revision. : 1. The compatibility of this design change with previously approved modifications must be determined by the installer. 2. If the holder agrees to permit another person to use this Certificate to alter the product, the holder shall give the other person written evidence of that permission. 3. Instructions for Continued Airworthiness, Aero Twin, Inc. document number 4111-212-ICA, Original Issue, dated May 8, 2020, or later FAA accepted revision is a required part of this modification. 4. Airplane Flight Manual Supplement (AFMS), Aero Twin Doc. No. 4111-212-AFMS, Original Issue, dated August 27, 2020, or later FAA approved revision is a required part of this modification. November 20, 2017 September 8, 2020 _______________________________________________________ (Signature) August A. Asay Manager, Anchorage Aircraft Certification Office _______________________________________________________ (Title) _____________________________________________________________________________________________________________________________________ Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both. _____________________________________________________________________________________________________________________________________ FAA FORM 8110-2(10-68) PAGE 1 of 2 PAGES This certificate may be transferred in accordance with FAR 21.47. INSTRUCTIONS: The transfer endorsement below may be used to notify the appropriate FAA Regional Office of the transfer of this Supplemental Type Certificate. -
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 -
The Effects of Design, Manufacturing Processes, and Operations Management on the Assembly of Aircraft Composite Structure by Robert Mark Coleman
The Effects of Design, Manufacturing Processes, and Operations Management on the Assembly of Aircraft Composite Structure by Robert Mark Coleman B.S. Civil Engineering Duke University, 1984 Submitted to the Sloan School of Management and the Department of Aeronautics and Astronautics in Partial Fulfillment of the Requirements for the Degrees of Master of Science in Management and Master of Science in Aeronautics and Astronautics in conjuction with the LEADERS FOR MANUFACTURING PROGRAM at the MASSACHUSETTS INSTITUTE OF TECHNOLOGY June 1991 © 1991, MASSACHUSETTS INSTITUTE OF TECHNOLOGY ALL RIGHTS RESERVED Signature of Author_ .• May, 1991 Certified by Stephen C. Graves Professor of Management Science Certified by A/roJ , Paul A. Lagace Profes s Aeron icand Astronautics Accepted by Jeffrey A. Barks Associate Dean aster's and Bachelor's Programs I.. Jloan School of Management Accepted by - No U Professor Harold Y. Wachman Chairman, Department Graduate Committee Aero Department of Aeronautics and Astronautics MASSACHiUSEITS INSTITUTE OFN Fr1 1'9n.nry JUJN 12: 1991 1 UiBRARIES The Effects of Design, Manufacturing Processes, and Operations Management on the Assembly of Aircraft Composite Structure by Robert Mark Coleman Submitted to the Sloan School of Management and the Department of Aeronautics and Astronautics in Partial Fulfillment of the Requirements for the Degrees of Master of Science in Management and Master of Science in Aeronautics and Astronautics June 1991 ABSTRACT Composite materials have many characteristics well-suited for aerospace applications. Advanced graphite/epoxy composites are especially favored due to their high stiffness, strength-to-weight ratios, and resistance to fatigue and corrosion. Research emphasis to date has been on the design and fabrication of composite detail parts, with considerably less attention given to the cost and quality issues in their subsequent assembly. -
PC-6/B2-H4 Airplane Flight Manual Doc. No. 1820 at Revision 8
PILOT’S INFORMATION MANUAL PC-6/B2-H4 applicable from AC S/N 825 PILOT’S INFORMATION MANUAL PC-6/B2-H4 applicable from AC S/N 825 WARNING •This PC-6 Pilot’s Information Manual is published for general and familiarization purposes only. •This Pilot’s Information Manual does NOT meet FAA, FOCA or any other civil aviation authority regulations for operation of ANY Aircraft. •This Pilot’s Information Manual is a reproduction of a PC-6 Airplane Flight Manual, however, it is NOT revised or updated. •This Pilot’s Information Manual does NOT reflect the configuration or operating parameters of any actual aircraft. •Only the Approved Airplane Flight Manual issued for a specific serial number aircraft may be used for actual operation of that serial number aircraft. Pilatus Aircraft Ltd P.O. Box 992 6371 Stans, Switzerland Phone +41 41 619 67 00 Fax +41 41 619 92 00 [email protected] www.pilatus-aircraft.com AIRPLANE FLIGHT MANUAL PC-6/B2-H4 ONLY REPORT NO. 1820 PURPOSES REGISTRATION ._____ __. SERIAL NO . APPLICABLE FROM A/C SIN 825 FAMILIARIZATION THIS AIRPLANDANE IS TO BE OPERAT ED IN COMPLIANCE WITH INFORMATION AND LIMI TATIONS CONTAINED HEREIN THIS FLIGHT MANUAL IS TO BE KEPT GENERAL IN THE AIRCRAFT AT ALL TIMES FOR Approved by: SWISS FEDERAL OFF FOR CIVIL AVIATION · �L Nov 20, JS�S" Date of Approval : ____·- ______ PILATUS AIRCRAFT LTD STANS/SWITZERLAND ONLY PURPOSES FAMILIARIZATION AND GENERAL FOR © Pilatus Aircraft Ltd. This document contains proprietary information that is protected by copyright. All rights are reserved, No part of this document may be copied, reproduced or translated to other languages without the prior written consent of Pilatus Aircraft Ltd. -
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. -
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. -
Electrically Heated Composite Leading Edges for Aircraft Anti-Icing Applications”
UNIVERSITY OF NAPLES “FEDERICO II” PhD course in Aerospace, Naval and Quality Engineering PhD Thesis in Aerospace Engineering “ELECTRICALLY HEATED COMPOSITE LEADING EDGES FOR AIRCRAFT ANTI-ICING APPLICATIONS” by Francesco De Rosa 2010 To my girlfriend Tiziana for her patience and understanding precious and rare human virtues University of Naples Federico II Department of Aerospace Engineering DIAS PhD Thesis in Aerospace Engineering Author: F. De Rosa Tutor: Prof. G.P. Russo PhD course in Aerospace, Naval and Quality Engineering XXIII PhD course in Aerospace Engineering, 2008-2010 PhD course coordinator: Prof. A. Moccia ___________________________________________________________________________ Francesco De Rosa - Electrically Heated Composite Leading Edges for Aircraft Anti-Icing Applications 2 Abstract An investigation was conducted in the Aerospace Engineering Department (DIAS) at Federico II University of Naples aiming to evaluate the feasibility and the performance of an electrically heated composite leading edge for anti-icing and de-icing applications. A 283 [mm] chord NACA0012 airfoil prototype was designed, manufactured and equipped with an High Temperature composite leading edge with embedded Ni-Cr heating element. The heating element was fed by a DC power supply unit and the average power densities supplied to the leading edge were ranging 1.0 to 30.0 [kW m-2]. The present investigation focused on thermal tests experimentally performed under fixed icing conditions with zero AOA, Mach=0.2, total temperature of -20 [°C], liquid water content LWC=0.6 [g m-3] and average mean volume droplet diameter MVD=35 [µm]. These fixed conditions represented the top icing performance of the Icing Flow Facility (IFF) available at DIAS and therefore it has represented the “sizing design case” for the tested prototype. -
AMA FPG-9 Glider OBJECTIVES – Students Will Learn About the Basics of How Flight Works by Creating a Simple Foam Glider
AEX MARC_Layout 1 1/10/13 3:03 PM Page 18 activity two AMA FPG-9 Glider OBJECTIVES – Students will learn about the basics of how flight works by creating a simple foam glider. – Students will be introduced to concepts about air pressure, drag and how aircraft use control surfaces to climb, turn, and maintain stable flight. Activity Credit: Credit and permission to reprint – The Academy of Model Aeronautics (AMA) and Mr. Jack Reynolds, a volunteer at the National Model Aviation Museum, has graciously given the Civil Air Patrol permission to reprint the FPG-9 model plan and instructions here. More activities and suggestions for classroom use of model aircraft can be found by contacting the Academy of Model Aeronautics Education Committee at their website, buildandfly.com. MATERIALS • FPG-9 pattern • 9” foam plate • Scissors • Clear tape • Ink pen • Penny 18 AEX MARC_Layout 1 1/10/13 3:03 PM Page 19 BACKGROUND Control surfaces on an airplane help determine the movement of the airplane. The FPG-9 glider demonstrates how the elevons and the rudder work. Elevons are aircraft control surfaces that combine the functions of the elevator (used for pitch control) and the aileron (used for roll control). Thus, elevons at the wing trailing edge are used for pitch and roll control. They are frequently used on tailless aircraft such as flying wings. The rudder is the small moving section at the rear of the vertical stabilizer that is attached to the fixed sections by hinges. Because the rudder moves, it varies the amount of force generated by the tail surface and is used to generate and control the yawing (left and right) motion of the aircraft. -
Hoffmann Aircraft
HOFFMANN AIRCRAFT HOFFMANN AIRCRAFT CORP P.0: Box No. 100 A-1214 Vienna Austria Phone (0 22 2/39 88 18 or 39 89 05 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS H36 DIMONA This Service and Maintenance Manual is for U.S. registered gliders. (Type Certificate Data Sheet No.: ………………….EU) Reg. No.:……………………… Ser. No.. ……………………………. Owner: …………………………………………………………………. ………………………………………………………………….. ………………………………………………………………….. Published 15 Nov 1985 Approval of translation has been done by best knowledge and judgment. In any case the original text in German language is authoritative. —1— Hoffmann General H 36 DIMONA 1. GENERAL: Table of contents Page 1. General ------------------------------------ 1 2. List of Revisions --------------------------- 2 3. System Description -------------------------- 3 4. Maintenance and Inspections --------- 23 5. Rigging ------------------------------------ 35 6. Weight and Balance --------------------------- 39 7 . Servicing ------------------------------------ 42 8. Repair ------------------------------------ 45 9. Table of consumables ------------------ 57 10. Airworthiness Limitations ------------------ 60 -2- Hoffmann Revisions H 36 Dimona 2. REVISIONS: 2. Revisions . Revision No Affected Pages Source Date Signature -3- Hoffmann Systems H 36 Dimona Description 3. SYSTEMS DESCRIPTION: Table of Contents Paragraph page 3.1 FLIGHT CONTROLS ------------------ 4 3.2 AIRBRAKES & WHEEL-BRAKES --- 5 3.3 TRIM UNIT ------------------------------- 5 3.4 FUEL SYSTEM ---------------------- 10 3.5 POWER PLANT ----------------------