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MANUAL REVISION TRANSMITTAL Manual 146 (61-00-46) Propeller Owner's Manual and Logbook
HARTZELL PROPELLER INC. One Propeller Place Piqua, Ohio 45356-2634 U.S.A. Telephone: 937.778.4200 Fax: 937.778.4391 MANUAL REVISION TRANSMITTAL Manual 146 (61-00-46) Propeller Owner's Manual and Logbook REVISION 3 dated June 2012 Attached is a copy of Revision 3 to Hartzell Propeller Inc. Manual 146. Page Control Chart for Revision 3: Remove Insert Page No. Page No. COVER AND INSIDE COVER COVER AND INSIDE COVER REVISION HIGHLIGHTS REVISION HIGHLIGHTS pages 5 and 6 pages 5 and 6 SERVICE DOCUMENTS LIST SERVICE DOCUMENTS LIST pages 11 and 12 pages 11 and 12 LIST OF EFFECTIVE PAGES LIST OF EFFECTIVE PAGES pages 15 and 16 pages 15 and 16 TABLE OF CONTENTS TABLE OF CONTENTS pages 17 thru 24 pages 17 thru 26 INTRODUCTION INTRODUCTION pages 1-1 thru 1-14 pages 1-1 thru 1-16 DESCRIPTION AND DESCRIPTION AND OPERATION OPERATION pages 2-1 thru 2-20 pages 2-1 thru 2-24 INSTALLATION AND INSTALLATION AND REMOVAL REMOVAL pages 3-1 thru 3-22 pages 3-1 thru 3-24 TESTING AND TESTING AND TROUBLESHOOTING TROUBLESHOOTING pages 4-1 thru 4-10 pages 4-1 thru 4-10 continued on next page Page Control Chart for Revision 3 (continued): Remove Insert Page No. Page No. INSPECTION AND INSPECTION AND CHECK CHECK pages 5-1 thru 5-24 pages 5-1 thru 5-26 MAINTENANCE MAINTENANCE PRACTICES PRACTICES pages 6-1 thru 6-36 pages 6-1 thru 6-38 DE-ICE SYSTEMS DE-ICE SYSTEMS pages 7-1 thru 7-6 pages 7-1 thru 7-6 NOTE 1: When the manual revision has been inserted in the manual, record the information required on the Record of Revisions page in this manual. -
DLE-20 Operator’S Manual
DLE-20 Operator’s Manual Specifications Displacement: 20cc [1.2cu. in.] Performance: 2.5HP / 9,000 rpm Idle Speed: 1,700 rpm Ignition Style: Electronic Ignition Recommended Propellers: 14u10, 15 u8, 16u6, 16u8, 17u6 Spark Plug Type: CM6 (Gap) 0.018in.– 0.020 in. [0.45mm –0.51mm] Diameter × Stroke: 1.26in. [32mm] u0.98in. [25 mm] Compression Ratio: 10.5 :1 Carburetor: DLE MP 148 100424 with Manual Choke Weight: Main Engine − 1.43 lb [650g] Muffler − 1.76 oz [50 g] Electronic Ignition − 4.23oz [120 g] ™ Fuel: 87− 93 Octane Gasoline with a 30:1 gas/2-stroke (2-cycle) oil mixture 1 © 2010 Hobbico®, Inc. DLEG0020 Mnl Parts List (1) DLE-20cc Gas Engine w/DLE MP 148 100424 (1) DLE Spark Plug (NGK CM6 size) with additional spring (1) Muffl er with gasket (2) 4 x 14 mm SHCS (muffl er mounting) (1) Electronic Ignition Module with additional tachometer lead (1) Silicone Pick-up Wire Cover / Ignition Wire Cover (1) Red Three Pin Connector Lead with Pig Tail (ignition switch) (1) Long Throttle Arm Extension with installation screw and nut (2) Three Pin Connector Securing Clips (1) DLE Decal (not pictured) Safety Tips and Warnings ● This engine is not a toy. Please place your safety and the safety of others paramount while operating. DLE will not be held responsible for any safety issues or accidents involving this engine. ● Operate the engine in a properly ventilated area. ● Before starting the engine, please make sure all components including the propeller and the engine mount are secure and tight. -
Propeller Operation and Malfunctions Basic Familiarization for Flight Crews
PROPELLER OPERATION AND MALFUNCTIONS BASIC FAMILIARIZATION FOR FLIGHT CREWS INTRODUCTION The following is basic material to help pilots understand how the propellers on turbine engines work, and how they sometimes fail. Some of these failures and malfunctions cannot be duplicated well in the simulator, which can cause recognition difficulties when they happen in actual operation. This text is not meant to replace other instructional texts. However, completion of the material can provide pilots with additional understanding of turbopropeller operation and the handling of malfunctions. GENERAL PROPELLER PRINCIPLES Propeller and engine system designs vary widely. They range from wood propellers on reciprocating engines to fully reversing and feathering constant- speed propellers on turbine engines. Each of these propulsion systems has the similar basic function of producing thrust to propel the airplane, but with different control and operational requirements. Since the full range of combinations is too broad to cover fully in this summary, it will focus on a typical system for transport category airplanes - the constant speed, feathering and reversing propellers on turbine engines. Major propeller components The propeller consists of several blades held in place by a central hub. The propeller hub holds the blades in place and is connected to the engine through a propeller drive shaft and a gearbox. There is also a control system for the propeller, which will be discussed later. Modern propellers on large turboprop airplanes typically have 4 to 6 blades. Other components typically include: The spinner, which creates aerodynamic streamlining over the propeller hub. The bulkhead, which allows the spinner to be attached to the rest of the propeller. -
CHAPTER TWO - Static Aeroelasticity – Unswept Wing Structural Loads and Performance 21 2.1 Background
Static aeroelasticity – structural loads and performance CHAPTER TWO - Static Aeroelasticity – Unswept wing structural loads and performance 21 2.1 Background ........................................................................................................................... 21 2.1.2 Scope and purpose ....................................................................................................................... 21 2.1.2 The structures enterprise and its relation to aeroelasticity ............................................................ 22 2.1.3 The evolution of aircraft wing structures-form follows function ................................................ 24 2.2 Analytical modeling............................................................................................................... 30 2.2.1 The typical section, the flying door and Rayleigh-Ritz idealizations ................................................ 31 2.2.2 – Functional diagrams and operators – modeling the aeroelastic feedback process ....................... 33 2.3 Matrix structural analysis – stiffness matrices and strain energy .......................................... 34 2.4 An example - Construction of a structural stiffness matrix – the shear center concept ........ 38 2.5 Subsonic aerodynamics - fundamentals ................................................................................ 40 2.5.1 Reference points – the center of pressure..................................................................................... 44 2.5.2 A different -
Aircraft Service Manual
Propeller Technical Manual Jabiru Aircraft Pty Ltd JPM0001-1 4A482U0D And 4A484E0D Propellers Propeller Technical Manual FOR 4A482U0D and 4A484E0D Propellers DOCUMENT No. JPM0001-1 DATED: 1st Feb 2013 This Manual has been prepared as a guide to correctly operate & maintain Jabiru 4A482U0D and 4A484E0D propellers. It is the owner's responsibility to regularly check the Jabiru web site at www.jabiru.net.au for applicable Service Bulletins and have them implemented as soon as possible. Manuals are also updated periodically with the latest revisions available from the web site. Failure to maintain the propeller, engine or aircraft with current service information may render the aircraft un-airworthy and void Jabiru’s Limited, Express Warranty. This document is controlled while it remains on the Jabiru server. Once this no longer applies the document becomes uncontrolled. Should you have any questions or doubts about the contents of this manual, please contact Jabiru Aircraft Pty Ltd. This document is controlled while it remains on the Jabiru server. Once this no longer applies the document becomes uncontrolled. ISSUE 1 Dated : 1st Feb 2013 Issued By: DPS Page: 1 of 32 L:\files\Manuals_For_Products\Propeller_Manuals\JPM0001-1_Prop_Manual (1).doc Propeller Technical Manual Jabiru Aircraft Pty Ltd JPM0001-1 4A482U0D And 4A484E0D Propellers 1.1 TABLE OF FIGURES ............................................................................................................................................. 3 1.2 LIST OF TABLES ................................................................................................................................................. -
Chapter 26: Firewall Forward (Part Ii)
REVISION LIST CHAPTER 26: FIREWALL FORWARD (PART II) The following list of revisions will allow you to update the Legacy construction manual chapter listed above. Under the “Action” column, “R&R” directs you to remove and replace the pages affected by the revision. “Add” directs you to insert the pages shows and “R” to remove the pages. PAGE(S) AFFECTED REVISION # & DATE ACTION DESCRIPTION 26-1 through 26-21 0/02-15-02 None Current revision is correct 26-22 1/09-18-02 R&R Text Correction 26-23 through 26-32 0/02-15-02 None Current revision is correct 26-33 1/09-18-02 R&R Corrected Fig. 26:H:1 26-34 through 26-35 0/02-15-02 None Current revision is correct 26-1 3/12-15-04 R&R Updated table of contents with page numbers and part nbrs. 26-2 through 26-3 3/12-15-04 R&R Updated part nbrs. 26-4 3/12-15-04 R&R Updated engine isolator kit information. 26-6 3/12-15-04 R&R Updated part nbrs. 26-18 3/12-15-04 R&R Updated part nbrs. 26-20 through 26-21 3/12-15-04 R&R Updated part nbrs. 26-26 3/12-15-04 R&R Updated location of bulkhead fitting. 26-3 4/09/30/06 R&R Corrected plug part nbr. 26-26 4/09/30/06 R&R Corrected plug part nbr. 26-27 through 26-33 4/09-30-06 R&R Updated hose numbers and bolded so easier to read. -
Aero-Structural Design and Analysis of an Unmanned Aerial Vehicle and Its Mission Adaptive Wing
AERO-STRUCTURAL DESIGN AND ANALYSIS OF AN UNMANNED AERIAL VEHICLE AND ITS MISSION ADAPTIVE WING A THESIS SUBMITTED TO THE GRADUATE SCHOOL OF NATURAL AND APPLIED SCIENCES OF MIDDLE EAST TECHNICAL UNIVERSITY BY ERDOĞAN TOLGA İNSUYU IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREE OF MASTER OF SCIENCE IN AEROSPACE ENGINEERING FEBRUARY 2010 Approval of the thesis: AERO-STRUCTURAL DESIGN AND ANALYSIS OF AN UNMANNED AERIAL VEHICLE AND ITS MISSION ADAPTIVE WING submitted by ERDOĞAN TOLGA İNSUYU in partial fulfillment of the requirements for the degree of Master of Science in Aerospace Engineering Department, Middle East Technical University by, Prof. Dr. Canan Özgen _____________________ Dean, Graduate School of Natural and Applied Sciences Prof. Dr. Ozan Tekinalp _____________________ Head of Department, Aerospace Engineering Assist. Prof. Dr. Melin Şahin _____________________ Supervisor, Aerospace Engineering Dept., METU Examining Committee Members: Prof. Dr. Yavuz Yaman _____________________ Aerospace Engineering Dept., METU Assist Prof. Dr. Melin Şahin _____________________ Aerospace Engineering Dept., METU Prof. Dr. Serkan Özgen _____________________ Aerospace Engineering Dept., METU Assist. Prof. Dr. Ender Ciğeroğlu _____________________ Mechanical Engineering Dept., METU Özcan Ertem, M.Sc. _____________________ Executive Vice President, TAI Date: I hereby declare that all information in this document has been obtained and presented in accordance with academic rules and ethical conduct. I also declare that, as required by these rules and conduct, I have fully cited and referenced all material and results that are not original to this work. Name, Last Name : Signature : iii ABSTRACT AERO-STRUCTURAL DESIGN AND ANALYSIS OF AN UNMANNED AERIAL VEHICLE AND ITS MISSION ADAPTIVE WING İnsuyu, Erdoğan Tolga M.Sc., Department of Aerospace Engineering Supervisor : Assist. -
Checklist DA42 LEP 18.1
Checklist for Diamond DA42 TDI “Twin Star” Edition #: 18.1 Edition date: 08.05.2018 Comments explaining Edition # 18 Normal Procedures: Please observe: No change The file you are receiving hereby combines all three sections of the checklist: Normal Emergency Procedures: Checklist, Emergency Checklist and Abnormal Checklist. Pages rearranged and renumbered All pages of a new edition will have the same new “edition #” and “edition date”, even if Major changes: only one page was amended and all other pages still have the same, unchanged content. Page 5: L/R STARTER Therefore the “List of Effective Pages” (LEP) is provided. It is here where you can see Pages 6/7: Engine Fire whether a particular page was amended. Pages which have been amended by a new edition will be marked yellow. For all other pages you will see which original “edition #” Abnormal Procedures: (and of course any higher “edition #”) is still valid. Pages renumbered Note: The system of assigning “Edition #” is as follows: Comments explaining Edition # 18.1 if the revision affects all types, a new edition # (without a decimal figure) will be assigned to all of the checklists Normal Procedures: if the revision does not affect all types, the affected checklists will get subsequent No change “decimal figures” until a major revision affecting all checklists is issued. Emergency Procedures: Have a lot of nice flights and happy landings! No change Peter Schmidleitner Abnormal Procedures: Comments explaining Edition # 18.1 are on page 2 of this document Pages 16,17,18,20: editorial -
DESCRIPTION Fokker 50
Fokker 50 - Power Plant DESCRIPTION The aircraft is equipped with two Pratt and Whitney PW 125B turboprop engines, which are enclosed, in wing-mounted nacelles. Each engine drives a Dowty Rotol six-bladed reversible- pitch constant-speed propeller. The engine is essentially a twin-spool turbojet combined with a free power-turbine assembly, which drives the reduction gearbox and propeller via a third concentric shaft. Engine layout Air intake The air intake is located below the propeller spinner. The intake has an anti-icing system. Combustion section The combustion section comprises an annular combustion chamber, fourteen fuel nozzles, and two igniters. Fuel control is through combined mechanical and electronic control systems. High pressure spool This spool comprises a centrifugal compressor and a single stage axial turbine. HP-spool rpm (NH) is governed by fuel metering. The spool drives the HP fuel pump and the lubrication oil pumps. Low pressure spool This spool comprises a centrifugal compressor and a single stage axial turbine. The LP spool is ungoverned; it is free to adapt itself to the operating conditions. LP-spool rpm is designated NL. To ease the gas flow paths and to minimize the gyroscopic moment, the LP spool rotates in a direction opposite to the HP spool and power-turbine shaft. Power turbine The two-stage axial power turbine drives the propeller via the reduction gearbox. The propeller shaft line is set above the engine shaft centerline. Propeller rpm is designated NP. The reduction gearbox also drives an integrated drive generator, a hydraulic pump, a propeller-pitch-control oil pump, a propeller overspeed governor, and the NP indicator. -
Cessna Model 150M Performance- Cessna Specifications Model 150M Performance - Specifications
PILOT'S OPERATING HANDBOOK ssna 1977 150 Commuter CESSNA MODEL 150M PERFORMANCE- CESSNA SPECIFICATIONS MODEL 150M PERFORMANCE - SPECIFICATIONS SPEED: Maximum at Sea Level 109 KNOTS Cruise, 75% Power at 7000 Ft 106 KNOTS CRUISE: Recommended Lean Mixture with fuel allowance for engine start, taxi, takeoff, climb and 45 minutes reserve at 45% power. 75% Power at 7000 Ft Range 340 NM 22.5 Gallons Usable Fuel Time 3.3 HRS 75% Power at 7000 Ft Range 580 NM 35 Gallons Usable Fuel Time 5. 5 HRS Maximum Range at 10,000 Ft Range 420 NM 22. 5 Gallons Usable Fuel Time 4.9 HRS Maximum Range at 10,000 Ft Range 735 NM 35 Gallons Usable Fuel Time 8. 5 HRS RATE OF CLIMB AT SEA LEVEL 670 FPM SERVICE CEILING 14, 000 FT TAKEOFF PERFORMANCE: Ground Roll 735 FT Total Distance Over 50-Ft Obstacle 1385 FT LANDING PERFORMANCE: Ground Roll 445 FT Total Distance Over 50-Ft Obstacle 107 5 FT STALL SPEED (CAS): Flaps Up, Power Off 48 KNOTS Flaps Down, Power Off 42 KNOTS MAXIMUM WEIGHT 1600 LBS STANDARD EMPTY WEIGHT: Commuter 1111 LBS Commuter II 1129 LBS MAXIMUM USEFUL LOAD: Commuter 489 LBS Commuter II 471 LBS BAGGAGE ALLOWANCE 120 LBS WING LOADING: Pounds/Sq Ft 10.0 POWER LOADING: Pounds/HP 16.0 FUEL CAPACITY: Total Standard Tanks 26 GAL. Long; Range Tanks 38 GAL. OIL CAPACITY 6 QTS ENGINE: Teledyne Continental O-200-A 100 BHP at 2750 RPM PROPELLER: Fixed Pitch, Diameter 69 IN. D1080-13-RPC-6,000-12/77 PILOT'S OPERATING HANDBOOK Cessna 150 COMMUTER 1977 MODEL 150M Serial No. -
Sample Airplane Setup Instructions
Airplane Section SAMPLE AIRPLANE SETUP INSTRUCTIONS The following example shows how the PCM 7. Adjust Servo Throws 1024Z may be programmed for a pattern airplane. Check the proper direction of throw for each The settings presented here are for a typical servo. Use Reversing Function REV in the Model model. Your model's settings are likely to vary menu to set proper throw directions for each servo. Double check that each servo moves the proper direc- from these, but the procedures given will still be tion. applicable. 1. Model Selection Use the Model Select function MSL to select a vacant model memory (or one you don't mind erasing) and choose the AIRPLANE Setup using the Type TYP function from Model menu. 2. Name The New Model Rename the model using the Model Name MNA function in the model menu. Switch to the Condition menu CND and name the default flight condition 8. Limit Servo Throws (we recommend NORM L). Later you may add other Now use the ATV function to limit servo throws. flight conditions, which may also be named to make The travel of the ailerons should be limited to roughly them easier to identify. 10—12° maximum in both directions with the ATV 3. Activate Special Mixing function. Repeat for elevator. Adjust rudder lateral Activate Flaperon FPN or Aileron Diferential motion to about ±45°. Be sure that no servo "bottoms ADF if you desire these functions (you may only out" at maximum control throw. After setting maxi- choose one; both require two aileron servos). FPN is mum throws, ATV is rarely used. -
Assembly Manual
SIZE .75 - .91 MS:123 ASSEMBLY MANUAL “Graphics and specifications may change without notice”. Specifications: Wing span ----------------------------66.9in (170cm). Wing area -----------------761.1sq.in (49.1sq dm). Weight -------------------------------------9.3lbs (4.2kg). Length ------------------------------51.1in (129.8cm). Engine ------------------ 0.75-0.91cu.in ----2-stroke. 0.91-1.25cu.in ---4-stroke. Radio -------------------6 channels with 8 servos. Retracts landing gear (included). Electric conversion: optional ZERO. Instruction Manual. INTRODUCTION. Thank you for choosing the ZERO ARTF by SEAGULL MODELS. The ZERO was designed with the intermediate/advanced sport flyer in mind. It is a semi scale airplane which is easy to fly and quick to assemble. The airframe is conventionally built using balsa, plywood to make it stronger than the average ARTF , yet the design allows the aeroplane to be kept light. You will find that most of the work has been done for you already.The motor mount has been fitted and the hinges are pre-installed . Flying the ZERO is simply a joy. This instruction manual is designed to help you build a great flying aeroplane. Please read this manual thoroughly before starting assembly of your ZERO . Use the parts listing below to identify all parts. WARNING. Please be aware that this aeroplane is not a toy and if assembled or used incorrectly it is capable of causing injury to people or property. WHEN YOU FLY THIS AEROPLANE YOU ASSUME ALL RISK & RESPONSIBILITY. If you are inexperienced with basic R/C flight we strongly recommend you contact your R/C supplier and join your local R/C Model Flying Club.