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Instrument Flying Handbook [复制链接]

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发表于 2008-12-9 15:29:24 |只看该作者 |倒序浏览
Instrument Flying Handbook U.S. Department of Transportation FEDERAL AVIATION ADMINISTRATION FAA-H-8083-15A Instrument Flying Handbook U.S. Department of Transportation FEDERAL AVIATION ADMINISTRATION Flight Standards Service 2007 ii iii This Instrument Flying Handbook is designed for use by instrument fl ight instructors and pilots preparing for instrument rating tests. Instructors may fi nd this handbook a valuable training aid as it includes basic reference material for knowledge testing and instrument fl ight training. Other Federal Aviation Administration (FAA) publications should be consulted for more detailed information on related topics. This handbook conforms to pilot training and certifi cation concepts established by the FAA. There are different ways of teaching, as well as performing, fl ight procedures and maneuvers and many variations in the explanations of aerodynamic theories and principles. This handbook adopts selected methods and concepts for instrument fl ying. The discussion and explanations refl ect the most commonly used practices and principles. Occasionally the word “must” or similar language is used where the desired action is deemed critical. The use of such language is not intended to add to, interpret, or relieve a duty imposed by Title 14 of the Code of Federal Regulations (14 CFR). All of the aeronautical knowledge and skills required to operate in instrument meteorological conditions (IMC) are detailed. Chapters are dedicated to human and aerodynamic factors affecting instrument fl ight, the fl ight instruments, attitude instrument fl ying for airplanes, basic fl ight maneuvers used in IMC, attitude instrument fl ying for helicopters, navigation systems, the National Airspace System (NAS), the air traffi c control (ATC) system, instrument fl ight rules (IFR) fl ight procedures, and IFR emergencies. Clearance shorthand and an integrated instrument lesson guide are also included. This handbook supersedes FAA-H-8081-15, Instrument Flying Handbook, dated 2001. This handbook may be purchased from the Superintendent of Documents, United States Government Printing Offi ce (GPO), Washington, DC 20402-9325, or from GPO's web site. http://bookstore.gpo.gov This handbook is also available for download, in PDF format, from the Regulatory Support Division's (AFS-600) web site. http://www.faa.gov/about/offi ce_org/headquarters_offi ces/avs/offi ces/afs/afs600 This handbook is published by the United States Department of Transportation, Federal Aviation Administration, Airman Testing Standards Branch, AFS-630, P.O. Box 25082, Oklahoma City, OK 73125. Comments regarding this publication should be sent, in email form, to the following address. AFS630comments@faa.gov Preface iv v This handbook was produced as a combined Federal Aviation Administration (FAA) and industry effort. The FAA wishes to acknowledge the following contributors: The laboratory of Dale Purves, M.D. and Mr. Al Seckel in providing imagery (found in Chapter 1) for visual illusions from the book, The Great Book of Optical Illusions, Firefl y Books, 2004 Sikorsky Aircraft Corporation and Robinson Helicopter Company for imagery provided in Chapter 9 Garmin Ltd. for providing fl ight system information and multiple display systems to include integrated fl ight, GPS and communication systems; information and hardware used with WAAS, LAAS; and information concerning encountering emergencies with high-technology systems Universal Avionics System Corporation for providing background information of the Flight Management System and an overview on Vision–1 and Traffi c Alert and Collision Avoidance systems (TCAS) Meggitt/S-Tec for providing detailed autopilot information regarding installation and use Cessna Aircraft Company in providing instrument panel layout support and information on the use of onboard systems Kearfott Guidance and Navigation Corporation in providing background information on the Ring-LASAR gyroscope and its history Honeywell International Inc., for Terrain Awareness Systems (TAWS) and various communication and radio systems sold under the Bendix-King name Chelton Flight Systems and Century Flight Systems, Inc., for providing autopilot information relating to Highway in the Sky (Chelton) and HSI displays (Century) Avidyne Corporation for providing displays with alert systems developed and sold by Ryan International, L3 Communications, and Tectronics. Additional appreciation is extended to the Aircraft Owners and Pilots Association (AOPA), the AOPA Air Safety Foundation, and the National Business Aviation Association (NBAA) for their technical support and input. Acknowledgements vi vii Is an Instrument Rating Necessary? The answer to this question depends entirely upon individual needs. Pilots may not need an instrument rating if they fl y in familiar uncongested areas, stay continually alert to weather developments, and accept an alternative to their original plan. However, some cross-country destinations may take a pilot to unfamiliar airports and/or through high activity areas in marginal visual or instrument meteorological conditions (IMC). Under these conditions, an instrument rating may be an alternative to rerouting, rescheduling, or canceling a fl ight. Many accidents are the result of pilots who lack the necessary skills or equipment to fl y in marginal visual meteorological conditions (VMC) or IMC and attempt fl ight without outside references. Pilots originally fl ew aircraft strictly by sight, sound, and feel while comparing the aircraft’s attitude to the natural horizon. As aircraft performance increased, pilots required more infl ight information to enhance the safe operation of their aircraft. This information has ranged from a string tied to a wing strut, to development of sophisticated electronic fl ight information systems (EFIS) and fl ight management systems (FMS). Interpretation of the instruments and aircraft control have advanced from the “one, two, three” or “needle, ball, and airspeed” system to the use of “attitude instrument fl ying” techniques. Navigation began by using ground references with dead reckoning and has led to the development of electronic navigation systems. These include the automatic direction fi nder (ADF), very-high frequency omnidirectional range (VOR), distance measuring equipment (DME), tactical air navigation (TACAN), long range navigation (LORAN), global positioning system (GPS), instrument landing system (ILS), microwave landing system (MLS), and inertial navigation system (INS). Perhaps you want an instrument rating for the same basic reason you learned to fl y in the fi rst place—because you like fl ying. Maintaining and extending your profi ciency, once you have the rating, means less reliance on chance and more on skill and knowledge. Earn the rating—not because you might Introduction need it sometime, but because it represents achievement and provides training you will use continually and build upon as long as you fl y. But most importantly it means greater safety in fl ying. Instrument Rating Requirements A private or commercial pilot must have an instrument rating and meet the appropriate currency requirements if that pilot operates an aircraft using an instrument fl ight rules (IFR) fl ight plan in conditions less than the minimums prescribed for visual fl ight rules (VFR), or in any fl ight in Class A airspace. You will need to carefully review the aeronautical knowledge and experience requirements for the instrument rating as outlined in Title 14 of the Code of Federal Regulations (14 CFR) part 61. After completing the Federal Aviation Administration (FAA) Knowledge Test issued for the instrument rating, and all the experience requirements have been satisfi ed, you are eligible to take the practical test. The regulations specify minimum total and pilot-in-command time requirements. This minimum applies to all applicants regardless of ability or previous aviation experience. Training for the Instrument Rating A person who wishes to add the instrument rating to his or her pilot certifi cate must fi rst make commitments of time, money, and quality of training. There are many combinations of training methods available. Independent studies may be adequate preparation to pass the required FAA Knowledge Test for the instrument rating. Occasional periods of ground and fl ight instruction may provide the skills necessary to pass the required test. Or, individuals may choose a training facility that provides comprehensive aviation education and the training necessary to ensure the pilot will pass all the required tests and operate safely in the National Airspace System (NAS). The aeronautical knowledge may be administered by educational institutions, aviation-oriented schools, correspondence courses, and appropriately rated instructors. Each person must decide for themselves which training program best meets his or her needs and at the same time maintain a high quality of training. Interested persons viii should make inquiries regarding the available training at nearby airports, training facilities, in aviation publications, and through the FAA Flight Standards District Office (FSDO). Although the regulations specify minimum requirements, the amount of instructional time needed is determined not by the regulation, but by the individual’s ability to achieve a satisfactory level of profi ciency. A professional pilot with diversifi ed fl ying experience may easily attain a satisfactory level of proficiency in the minimum time required by regulation. Your own time requirements will depend upon a variety of factors, including previous fl ying experience, rate of learning, basic ability, frequency of fl ight training, type of aircraft fl own, quality of ground school training, and quality of fl ight instruction, to name a few. The total instructional time you will need, the scheduling of such time, is up to the individual most qualifi ed to judge your profi ciency—the instructor who supervises your progress and endorses your record of fl ight training. You can accelerate and enrich much of your training by informal study. An increasing number of visual aids and programmed instrument courses is available. The best course is one that includes a well-integrated fl ight and ground school curriculum. The sequential nature of the learning process requires that each element of knowledge and skill be learned and applied in the right manner at the right time. Part of your instrument training may utilize a fl ight simulator, fl ight training device, or a personal computer-based aviation training device (PCATD). This ground-based fl ight training equipment is a valuable tool for developing your instrument cross-check and learning procedures, such as intercepting and tracking, holding patterns, and instrument approaches. Once these concepts are fully understood, you can then continue with infl ight training and refi ne these techniques for full transference of your new knowledge and skills. Holding the instrument rating does not necessarily make you a competent all-weather pilot. The rating certifi es only that you have complied with the minimum experience requirements, that you can plan and execute a fl ight under IFR, that you can execute basic instrument maneuvers, and that you have shown acceptable skill and judgment in performing these activities. Your instrument rating permits you to fl y into instrument weather conditions with no previous instrument weather experience. Your instrument rating is issued on the assumption that you have the good judgment to avoid situations beyond your capabilities. The instrument training program you undertake should help you to develop not only essential fl ying skills but also the judgment necessary to use the skills within your own limits. Regardless of the method of training selected, the curriculum in Appendix B, Instrument Training Lesson Guide, provides guidance as to the minimum training required for the addition of an instrument rating to a private or commercial pilot certifi cate. Maintaining the Instrument Rating Once you hold the instrument rating, you may not act as pilotin- command under IFR or in weather conditions less than the minimums prescribed for VFR, unless you meet the recent fl ight experience requirements outlined in 14 CFR part 61. These procedures must be accomplished within the preceding 6 months and include six instrument approaches, holding procedures, and intercepting and tracking courses through the use of navigation systems. If you do not meet the experience requirements during these 6 months, you have another 6 months to meet these minimums. If the requirements are still not met, you must pass an instrument profi ciency check, which is an infl ight evaluation by a qualifi ed instrument fl ight instructor using tasks outlined in the instrument rating practical test standards (PTS). The instrument currency requirements must be accomplished under actual or simulated instrument conditions. You may log instrument fl ight time during the time for which you control the aircraft solely by reference to the instruments. This can be accomplished by wearing a view-limiting device, such as a hood, fl ying an approved fl ight-training device, or fl ying in actual IMC. It takes only one harrowing experience to clarify the distinction between minimum practical knowledge and a thorough understanding of how to apply the procedures and techniques used in instrument fl ight. Your instrument training is never complete; it is adequate when you have absorbed every foreseeable detail of knowledge and skill to ensure a solution will be available if and when you need it.

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发表于 2008-12-9 15:31:03 |只看该作者
ix Preface ...................................................................iii Acknowledgements ................................................v Introduction ...........................................................vii Is an Instrument Rating Necessary? ............................ vii Instrument Rating Requirements ................................. vii Training for the Instrument Rating .............................. vii Maintaining the Instrument Rating ............................viii Table of Contents ..................................................ix Chapter 1 Human Factors ....................................................1-1 Introduction ....................................................................1-1 Sensory Systems for Orientation ...................................1-2 Eyes ............................................................................1-2 Vision Under Dim and Bright Illumination ............1-3 Ears .............................................................................1-4 Nerves .........................................................................1-5 Illusions Leading to Spatial Disorientation ....................1-5 Vestibular Illusions ....................................................1-5 The Leans ................................................................1-5 Coriolis Illusion ......................................................1-6 Graveyard Spiral .....................................................1-6 Somatogravic Illusion .............................................1-6 Inversion Illusion ....................................................1-6 Elevator Illusion ......................................................1-6 Visual Illusions ...........................................................1-7 False Horizon ..........................................................1-7 Autokinesis .............................................................1-7 Postural Considerations .................................................1-7 Demonstration of Spatial Disorientation .......................1-7 Climbing While Accelerating .....................................1-8 Climbing While Turning ............................................1-8 Diving While Turning ................................................1-8 Tilting to Right or Left ...............................................1-8 Reversal of Motion .....................................................1-8 Diving or Rolling Beyond the Vertical Plane ............1-8 Coping with Spatial Disorientation ................................1-8 Optical Illusions .............................................................1-9 Runway Width Illusion ..............................................1-9 Runway and Terrain Slopes Illusion ..........................1-9 Featureless Terrain Illusion ........................................1-9 Water Refraction ........................................................1-9 Haze ............................................................................1-9 Fog ..............................................................................1-9 Ground Lighting Illusions ..........................................1-9 How To Prevent Landing Errors Due To Optical Illusions ..........................................................................1-9 Physiological and Psychological Factors .....................1-11 Stress ........................................................................1-11 Medical Factors ............................................................1-12 Alcohol .....................................................................1-12 Fatigue ......................................................................1-12 Acute Fatigue ........................................................1-12 Chronic Fatigue ....................................................1-13 IMSAFE Checklist ...................................................1-13 Hazard Identifi cation ....................................................1-13 Situation 1 ................................................................1-13 Situation 2 ................................................................1-13 Risk Analysis ............................................................1-13 Crew Resource Management (CRM) and Single-Pilot Resource Management (SRM) .....................................1-14 Situational Awareness ..................................................1-14 Flight Deck Resource Management .............................1-14 Human Resources .....................................................1-14 Equipment ................................................................1-14 Information Workload ..............................................1-14 Task Management ........................................................1-15 Aeronautical Decision-Making (ADM) .......................1-15 The Decision-Making Process .................................1-16 Defi ning the Problem ...............................................1-16 Choosing a Course of Action ...................................1-16 Implementing the Decision and Evaluating the Outcome .............................................................1-16 Improper Decision-Making Outcomes ....................1-16 Models for Practicing ADM ........................................1-17 Perceive, Process, Perform .......................................1-17 The DECIDE Model .................................................1-17 Hazardous Attitudes and Antidotes .............................1-18 Table of Contents x Chapter 2 Aerodynamic Factors ..........................................2-1 Introduction ....................................................................2-1 The Wing ....................................................................2-2 Review of Basic Aerodynamics .....................................2-2 The Four Forces .........................................................2-2 Lift ..........................................................................2-2 Weight .....................................................................2-3 Thrust ......................................................................2-3 Drag ........................................................................2-3 Newton’s First Law, the Law of Inertia .....................2-4 Newton’s Second Law, the Law of Momentum ........2-4 Newton’s Third Law, the Law of Reaction ................2-4 Atmosphere ....................................................................2-4 Layers of the Atmosphere ..........................................2-5 International Standard Atmosphere (ISA) ..................2-5 Pressure Altitude .....................................................2-5 Density Altitude ......................................................2-5 Lift ..................................................................................2-6 Pitch/Power Relationship ...........................................2-6 Drag Curves ...................................................................2-6 Regions of Command .................................................2-7 Control Characteristics ...........................................2-7 Speed Stability ............................................................2-7 Normal Command ..................................................2-7 Reversed Command ................................................2-8 Trim ................................................................................2-8 Slow-Speed Flight ..........................................................2-8 Small Airplanes ..........................................................2-9 Large Airplanes ..........................................................2-9 Climbs ..........................................................................2-10 Acceleration in Cruise Flight ...................................2-10 Turns ............................................................................2-10 Rate of Turn .............................................................2-10 Radius of Turn ..........................................................2-11 Coordination of Rudder and Aileron Controls .........2-11 Load Factor ..................................................................2-11 Icing .............................................................................2-12 Types of Icing ..............................................................2-13 Structural Icing .........................................................2-13 Induction Icing .........................................................2-13 Clear Ice ...................................................................2-13 Rime Ice ...................................................................2-13 Mixed Ice ..................................................................2-14 General Effects of Icing on Airfoils .........................2-14 Piper PA-34-200T (Des Moines, Iowa) ................2-15 Tailplane Stall Symptoms ........................................2-16 Propeller Icing ..........................................................2-16 Effects of Icing on Critical Aircraft Systems ...........2-16 Flight Instruments .................................................2-16 Stall Warning Systems ..........................................2-16 Windshields ..........................................................2-16 Antenna Icing ...........................................................2-17 Summary ......................................................................2-17 Chapter 3 Flight Instruments ...............................................3-1 Introduction ....................................................................3-1 Pitot/Static Systems .......................................................3-2 Static Pressure ............................................................3-2 Blockage Considerations ............................................3-2 Indications of Pitot Tube Blockage ........................3-3 Indications from Static Port Blockage ....................3-3 Effects of Flight Conditions ....................................3-3 Pitot/Static Instruments ..................................................3-3 Sensitive Altimeter .....................................................3-3 Principle of Operation .............................................3-3 Altimeter Errors ......................................................3-4 Cold Weather Altimeter Errors ...............................3-5 ICAO Cold Temperature Error Table ........................3-5 Nonstandard Pressure on an Altimeter ...................3-6 Altimeter Enhancements (Encoding) .....................3-7 Reduced Vertical Separation Minimum (RVSM) ..3-7 Vertical Speed Indicator (VSI) ...................................3-8 Dynamic Pressure Type Instruments .............................3-8 Airspeed Indicator (ASI) ............................................3-8 Types of Airspeed ...................................................3-9 Airspeed Color Codes ...........................................3-10 Magnetism ....................................................................3-10 The Basic Aviation Magnetic Compass ..................3-11 Magnetic Compass Overview ...............................3-11 Magnetic Compass Induced Errors .......................3-12 The Vertical Card Magnetic Compass .....................3-14 The Flux Gate Compass System ..............................3-14 Remote Indicating Compass .....................................3-15 Gyroscopic Systems .....................................................3-16 Power Sources .........................................................3-16 Pneumatic Systems ..............................................3-16 Vacuum Pump Systems ........................................3-17 Electrical Systems .................................................3-18 Gyroscopic Instruments ...............................................3-18 Attitude Indicators ....................................................3-18 Heading Indicators ...................................................3-19 Turn Indicators .........................................................3-20 Turn-and-Slip Indicator ........................................3-20 Turn Coordinator ..................................................3-21 Flight Support Systems ................................................3-22 Attitude and Heading Reference System (AHRS) ...3-22 Air Data Computer (ADC) .......................................3-22 Analog Pictorial Displays ............................................3-22 Horizontal Situation Indicator (HSI) .......................3-22 xi Attitude Direction Indicator (ADI) .........................3-23 Flight Director System (FDS) ..................................3-23 Integrated Flight Control System ............................3-24 Autopilot Systems .................................................3-24 Flight Management Systems (FMS) ............................3-25 Electronic Flight Instrument Systems ......................3-27 Primary Flight Display (PFD) ......................................3-27 Synthetic Vision .......................................................3-27 Multi-Function Display (MFD) ................................3-28 Advanced Technology Systems ...................................3-28 Automatic Dependent Surveillance— Broadcast (ADS-B) ..................................................3-28 Safety Systems .............................................................3-30 Radio Altimeters ......................................................3-30 Traffi c Advisory Systems ........................................3-31 Traffi c Information System ..................................3-31 Traffi c Alert Systems ...........................................3-31 Traffi c Avoidance Systems ...................................3-31 Terrain Alerting Systems .....................................3-34 Required Navigation Instrument System Inspection ...3-34 Systems Prefl ight Procedures ...................................3-34 Before Engine Start ..................................................3-36 After Engine Start .....................................................3-37 Taxiing and Takeoff .................................................3-37 Engine Shut Down ...................................................3-37 Chapter 4, Section I Airplane Attitude Instrument Flying Using Analog Instrumentation ...........................4-1 Introduction ....................................................................4-1 Learning Methods ..........................................................4-2 Attitude Instrument Flying Using the Control and Performance Method .................................................4-2 Control Instruments ...............................................4-2 Performance Instruments .......................................4-2 Navigation Instruments ..........................................4-2 Procedural Steps in Using Control and Performance ............................................................4-2 Aircraft Control During Instrument Flight .............4-3 Attitude Instrument Flying Using the Primary and Supporting Method .....................................................4-4 Pitch Control ...........................................................4-4 Bank Control ...........................................................4-7 Power Control .........................................................4-8 Trim Control ...........................................................4-8 Airplane Trim .........................................................4-8 Helicopter Trim ....................................................4-10 Example of Primary and Support Instruments .........4-10 Fundamental Skills.......................................................4-10 Instrument Cross-Check ...........................................4-10 Common Cross-Check Errors ...............................4-11 Instrument Interpretation ..........................................4-13 Chapter 4, Section II Airplane Attitude Instrument Flying Using an Electronic Flight Display ..................4-15 Introduction ..................................................................4-15 Learning Methods ........................................................4-16 Control and Performance Method ............................4-18 Control Instruments ..............................................4-18 Performance Instruments ......................................4-19 Navigation Instruments .........................................4-19 The Four-Step Process Used to Change Attitude .....4-20 Establish ................................................................4-20 Trim ......................................................................4-20 Cross-Check ..........................................................4-20 Adjust ....................................................................4-20 Applying the Four-Step Process ...............................4-20 Pitch Control .........................................................4-20 Bank Control .........................................................4-20 Power Control .......................................................4-21 Attitude Instrument Flying—Primary and Supporting Method ...................................................4-21 Pitch Control .........................................................4-21 Straight-and-Level Flight ......................................4-22 Primary Pitch ........................................................4-22 Primary Bank ........................................................4-23 Primary Yaw .........................................................4-23 Primary Power ......................................................4-23 Fundamental Skills of Attitude Instrument Flying ......4-23 Instrument Cross-Check ...........................................4-24 Scanning Techniques ...................................................4-24 Selected Radial Cross-Check ...................................4-24 Starting the Scan ...................................................4-24 Trend Indicators ....................................................4-26 Common Errors ............................................................4-28 Fixation .....................................................................4-28 Omission ...................................................................4-28 Emphasis ..................................................................4-28 Chapter 5, Section I Airplane Basic Flight Maneuvers Using Analog Instrumentation ...........................5-1 Introduction ....................................................................5-1 Straight-and-Level Flight ...............................................5-2 Pitch Control ..............................................................5-2 Attitude Indicator ....................................................5-2 Altimeter .................................................................5-3 Vertical Speed Indicator (VSI) ...............................5-4 xii Airspeed Indicator (ASI) ........................................5-6 Bank Control ..............................................................5-6 Attitude Indicator ....................................................5-6 Heading Indicator ...................................................5-7 Turn Coordinator ....................................................5-7 Turn-and-Slip Indicator (Needle and Ball) .............5-8 Power Control ............................................................5-8 Power Settings ........................................................5-9 Airspeed Changes in Straight-and-Level Flight ...5-11 Trim Technique ........................................................5-12 Common Errors in Straight-and-Level Flight .........5-12 Pitch ......................................................................5-12 Heading .................................................................5-13 Power ....................................................................5-13 Trim ......................................................................5-13 Straight Climbs and Descents ......................................5-14 Climbs ......................................................................5-14 Entry .....................................................................5-14 Leveling Off ..........................................................5-16 Descents ...................................................................5-16 Entry .....................................................................5-17 Leveling Off ..........................................................5-17 Common Errors in Straight Climbs and Descents ...5-17 Turns ............................................................................5-19 Standard Rate Turns .................................................5-19 Turns to Predetermined Headings ............................5-20 Timed Turns .............................................................5-21 Compass Turns .........................................................5-21 Steep Turns ...............................................................5-22 Climbing and Descending Turns ..............................5-24 Change of Airspeed During Turns ...........................5-24 Common Errors in Turns ..........................................5-25 Pitch ......................................................................5-25 Bank ......................................................................5-25 Power ....................................................................5-26 Trim ......................................................................5-26 Errors During Compass Turns ..............................5-26 Approach to Stall .........................................................5-26 Unusual Attitudes and Recoveries ...............................5-26 Recognizing Unusual Attitudes ................................5-27 Recovery from Unusual Attitudes ............................5-27 Nose-High Attitudes .................................................5-27 Nose-Low Attitudes .................................................5-28 Common Errors in Unusual Attitudes ......................5-28 Instrument Takeoff .......................................................5-29 Common Errors in Instrument Takeoffs ..................5-29 Basic Instrument Flight Patterns ..................................5-30 Racetrack Pattern ......................................................5-30 Procedure Turn .........................................................5-30 Standard 45° Procedure Turn ...................................5-30 80/260 Procedure Turn .............................................5-31 Teardrop Patterns .....................................................5-31 Circling Approach Patterns ......................................5-32 Pattern I .................................................................5-32 Pattern II ...............................................................5-32 Chapter 5, Section II Airplane Basic Flight Maneuvers Using an Electronic Flight Display ..................5-33 Introduction ..................................................................5-33 Straight-and-Level Flight .............................................5-34 Pitch Control ............................................................5-34 Attitude Indicator ..................................................5-34 Altimeter ...............................................................5-36 Partial Panel Flight ...............................................5-36 VSI Tape ...............................................................5-36 Airspeed Indicator (ASI) ......................................5-37 Bank Control ............................................................5-37 Attitude Indicator ..................................................5-37 Horizontal Situation Indicator (HSI) ....................5-38 Heading Indicator .................................................5-38 Turn Rate Indicator ...............................................5-38 Slip/Skid Indicator ................................................5-39 Power Control ..........................................................5-39 Power Settings ......................................................5-39 Airspeed Changes in Straight-and-Level Flight ...5-40 Trim Technique ........................................................5-43 Common Errors in Straight-and-Level Flight ..........5-43 Pitch ......................................................................5-43 Heading .................................................................5-44 Power ....................................................................5-45 Trim ......................................................................5-45 Straight Climbs and Descents ......................................5-46 Entry .........................................................................5-46 Constant Airspeed Climb From Cruise Airspeed ................................................................5-46 Constant Airspeed Climb from Established Airspeed ................................................................5-47 Constant Rate Climbs ...........................................5-47 Leveling Off ..........................................................5-48 Descents ...................................................................5-49 Entry .........................................................................5-49 Leveling Off ..........................................................5-50 Common Errors in Straight Climbs and Descents ...5-50 Turns ............................................................................5-51 Standard Rate Turns .................................................5-51 Establishing A Standard Rate Turn ......................5-51 Common Errors ....................................................5-51 Turns to Predetermined Headings ............................5-52 xiii Timed Turns .............................................................5-53 Compass Turns .........................................................5-53 Steep Turns ...............................................................5-53 Unusual Attitude Recovery Protection .................5-55 Common Errors Leading to Unusual Attitudes ....5-58 Instrument Takeoff .......................................................5-60 Common Errors in Instrument Takeoffs ..................5-61 Basic Instrument Flight Patterns ..................................5-61 Chapter 6 Helicopter Attitude Instrument Flying ...............6-1 Introduction ....................................................................6-1 Flight Instruments ..........................................................6-2 Instrument Flight ............................................................6-2 Instrument Cross-Check .............................................6-2 Instrument Interpretation ............................................6-3 Aircraft Control ..........................................................6-3 Straight-and-Level Flight ...............................................6-3 Pitch Control ..............................................................6-3 Attitude Indicator ....................................................6-3 Altimeter .................................................................6-4 Vertical Speed Indicator (VSI) ...............................6-5 Airspeed Indicator ..................................................6-5 Bank Control ..............................................................6-5 Attitude Indicator ....................................................6-5 Heading Indicator ...................................................6-6 Turn Indicator .........................................................6-7 Common Errors During Straight-and-Level Flight ....6-7 Power Control During Straight-and-Level Flight ......6-7 Common Errors During Airspeed Changes .............6-10 Straight Climbs (Constant Airspeed and Constant Rate) ..............................................................6-10 Entry .........................................................................6-10 Level Off ..................................................................6-12 Straight Descents (Constant Airspeed and Constant Rate) ..............................................................6-12 Entry .........................................................................6-12 Level Off ..................................................................6-13 Common Errors During Straight Climbs and Descents ...................................................................6-13 Turns ............................................................................6-13 Turn to a Predetermined Heading ............................6-13 Timed Turns .............................................................6-13 Change of Airspeed in Turns ...................................6-14 Compass Turns .........................................................6-15 30° Bank Turn ......................................................6-15 Climbing and Descending Turns ..............................6-15 Common Errors During Turns .................................6-15 Unusual Attitudes .........................................................6-16 Common Errors During Unusual Attitude Recoveries ................................................................6-16 Emergencies .................................................................6-16 Autorotations ............................................................6-17 Common Errors During Autorotations .................6-17 Servo Failure ............................................................6-17 Instrument Takeoff .......................................................6-17 Common Errors During Instrument Takeoffs ..........6-18 Changing Technology ..................................................6-18 Chapter 7 Navigation Systems ............................................7-1 Introduction ....................................................................7-1 Basic Radio Principles ...................................................7-2 How Radio Waves Propagate .....................................7-2 Ground Wave ..........................................................7-2 Sky Wave ................................................................7-2 Space Wave ............................................................7-2 Disturbances to Radio Wave Reception .....................7-3 Traditional Navigation Systems .....................................7-3 Nondirectional Radio Beacon (NDB) ........................7-3 NDB Components ...................................................7-3 ADF Components ...................................................7-3 Function of ADF .....................................................7-4 Operational Errors of ADF .....................................7-8 Very High Frequency Omnidirectional Range (VOR) ..............................................................7-8 VOR Components .................................................7-10 Function of VOR ..................................................7-12 VOR Operational Errors .......................................7-14 VOR Accuracy ......................................................7-16 VOR Receiver Accuracy Check ...........................7-16 VOR Test Facility (VOT) .....................................7-16 Certifi ed Checkpoints ...........................................7-16 Distance Measuring Equipment (DME) ...................7-16 DME Components ................................................7-17 Function of DME ..................................................7-17 DME Arc ..............................................................7-17 Intercepting Lead Radials .....................................7-19 DME Errors ..........................................................7-19 Area Navigation (RNAV) ........................................7-19 VOR/DME RNAV ................................................7-23 VOR/DME RNAV Components ..........................7-23 Function of VOR/DME RNAV ............................7-23 VOR/DME RNAV Errors .....................................7-24 Long Range Navigation (LORAN) ..........................7-24 LORAN Components ...........................................7-25 Function of LORAN .............................................7-26 LORAN Errors ......................................................7-26 Advanced Technologies ...............................................7-26 Global Navigation Satellite System (GNSS) ...........7-26 xiv Global Positioning System (GPS) ............................7-27 GPS Components ..................................................7-27 Function of GPS ...................................................7-28 GPS Substitution ...................................................7-28 GPS Substitution for ADF or DME .....................7-29 To Determine Aircraft Position Over a DME Fix: ........................................................................7-29 To Fly a DME Arc: ...............................................7-29 To Navigate TO or FROM an NDB/Compass Locator: .................................................................7-29 To Determine Aircraft Position Over an NDB/ Compass Locator: .................................................7-29 To Determine Aircraft Position Over a Fix Made up of an NDB/Compass Locator Bearing Crossing a VOR/LOC Course: .............................7-30 To Hold Over an NDB/Compass Locator: ...........7-30 IFR Flight Using GPS ...........................................7-30 GPS Instrument Approaches .................................7-31 Departures and Instrument Departure Procedures (DPs) ..................................................7-33 GPS Errors ............................................................7-33 System Status ........................................................7-33 GPS Familiarization ..............................................7-34 Differential Global Positioning Systems (DGPS) ....7-34 Wide Area Augmentation System (WAAS) ............7-34 General Requirements ..........................................7-34 Instrument Approach Capabilities ........................7-36 Local Area Augmentation System (LAAS) .............7-36 Inertial Navigation System (INS) .............................7-36 INS Components ...................................................7-37 INS Errors .............................................................7-37 Instrument Approach Systems .....................................7-37 Instrument Landing Systems (ILS) ..........................7-37 ILS Components ...................................................7-39 Approach Lighting Systems (ALS) ..........................7-40 ILS Airborne Components ....................................7-42 ILS Function .............................................................7-42 ILS Errors .................................................................7-44 Marker Beacons ....................................................7-44 Operational Errors ................................................7-45 Simplifi ed Directional Facility (SDF) ......................7-45 Localizer Type Directional Aid (LDA) ....................7-45 Microwave Landing System (MLS) .........................7-45 Approach Azimuth Guidance ...............................7-45 Required Navigation Performance ...............................7-46 Flight Management Systems (FMS) ............................7-48 Function of FMS ......................................................7-48 Head-Up Display (HUD) .............................................7-49 Radar Navigation (Ground Based) ...............................7-49 Functions of Radar Navigation ................................7-49 Airport Surface Detection Equipment ..................7-50 Radar Limitations .....................................................7-50 Chapter 8 The National Airspace System ...........................8-1 Introduction ....................................................................8-1 Airspace Classifi cation ...............................................8-2 Special Use Airspace ..................................................8-2 Federal Airways .........................................................8-4 Other Routing .............................................................8-5 IFR En Route Charts ......................................................8-6 Airport Information ....................................................8-6 Charted IFR Altitudes ................................................8-6 Navigation Features ....................................................8-7 Types of NAVAIDs ................................................8-7 Identifying Intersections .........................................8-7 Other Route Information .......................................8-10 Weather Information and Communication Features .................................................................8-10 New Technologies .......................................................8-10 Terminal Procedures Publications ...............................8-12 Departure Procedures (DPs) .....................................8-12 Standard Terminal Arrival Routes (STARs) ............8-12 Instrument Approach Procedure (IAP) Charts ............8-12 Margin Identifi cation ................................................8-12 The Pilot Briefi ng .....................................................8-16 The Plan View ..........................................................8-16 Terminal Arrival Area (TAA) ......................................8-18 Course Reversal Elements in Plan View and Profi le View ..............................................................8-20 Procedure Turns ....................................................8-20 Holding in Lieu of Procedure Turn ......................8-20 Teardrop Procedure ..............................................8-21 The Profi le View ...................................................8-21 Landing Minimums ..................................................8-23 Airport Sketch /Airport Diagram .............................8-27 Inoperative Components ..........................................8-27 RNAV Instrument Approach Charts ........................8-32 Chapter 9 The Air Traffi c Control System ...........................9-1 Introduction ....................................................................9-1 Communication Equipment ...........................................9-2 Navigation/Communication (NAV/COM) Equipment ..................................................................9-2 Radar and Transponders .............................................9-3 Mode C (Altitude Reporting) ..................................9-3 Communication Procedures ...........................................9-4 Communication Facilities ..............................................9-4 xv Automated Flight Service Stations (AFSS) ...............9-4 ATC Towers ...............................................................9-5 Terminal Radar Approach Control (TRACON) .........9-6 Tower En Route Control (TEC) .................................9-7 Air Route Traffi c Control Center (ARTCC) ..............9-7 Center Approach/Departure Control ..........................9-7 ATC Infl ight Weather Avoidance Assistance ..............9-11 ATC Radar Weather Displays ..................................9-11 Weather Avoidance Assistance ................................9-11 Approach Control Facility ...........................................9-12 Approach Control Advances ........................................9-12 Precision Runway Monitor (PRM) ..........................9-12 Precision Runway Monitor (PRM) Radar ............9-12 PRM Benefi ts ........................................................9-13 Control Sequence .........................................................9-13 Letters of Agreement (LOA) ....................................9-14 Chapter 10 IFR Flight ............................................................10-1 Introduction ..................................................................10-1 Sources of Flight Planning Information .......................10-2 Aeronautical Information Manual (AIM) ................10-2 Airport/Facility Directory (A/FD) ............................10-2 Notices to Airmen Publication (NTAP) ...................10-2 POH/AFM ................................................................10-2 IFR Flight Plan .............................................................10-2 Filing in Flight ..........................................................10-2 Cancelling IFR Flight Plans .....................................10-3 Clearances ....................................................................10-3 Examples ..................................................................10-3 Clearance Separations ..............................................10-4 Departure Procedures (DPs) ........................................10-5 Obstacle Departure Procedures (ODP) ....................10-5 Standard Instrument Departures ...............................10-5 Radar Controlled Departures ....................................10-5 Departures From Airports Without an Operating Control Tower .........................................10-7 En Route Procedures ....................................................10-7 ATC Reports ............................................................10-7 Position Reports .......................................................10-7 Additional Reports ...................................................10-7 Planning the Descent and Approach ........................10-8 Standard Terminal Arrival Routes (STARs) ............10-9 Substitutes for Inoperative or Unusable Components ..............................................................10-9 Holding Procedures ......................................................10-9 Standard Holding Pattern (No Wind) .......................10-9 Standard Holding Pattern (With Wind) ....................10-9 Holding Instructions .................................................10-9 Standard Entry Procedures .....................................10-11 Time Factors ...........................................................10-12 DME Holding .........................................................10-12 Approaches ................................................................10-12 Compliance With Published Standard Instrument Approach Procedures .............................................10-12 Instrument Approaches to Civil Airports ...............10-13 Approach to Airport Without an Operating Control Tower .....................................................10-14 Approach to Airport With an Operating Tower, With No Approach Control ....................10-14 Approach to an Airport With an Operating Tower, With an Approach Control .....................10-14 Radar Approaches ..................................................10-17 Radar Monitoring of Instrument Approaches ........10-18 Timed Approaches From a Holding Fix ................10-18 Approaches to Parallel Runways ............................10-20 Side-Step Maneuver ...............................................10-20 Circling Approaches ...............................................10-20 IAP Minimums .......................................................10-21 Missed Approaches ................................................10-21 Landing ...................................................................10-22 Instrument Weather Flying ........................................10-22 Flying Experience ..................................................10-22 Recency of Experience .......................................10-22 Airborne Equipment and Ground Facilities ........10-22 Weather Conditions ................................................10-22 Turbulence ..........................................................10-23 Structural Icing ...................................................10-24 Fog ......................................................................10-24 Volcanic Ash ......................................................10-24 Thunderstorms ....................................................10-25 Wind Shear .........................................................10-25 VFR-On-Top ..........................................................10-26 VFR Over-The-Top ................................................10-27 Conducting an IFR Flight ..........................................10-27 Prefl ight ..................................................................10-27 Departure ................................................................10-31 En Route .................................................................10-32 Arrival ....................................................................10-33 Chapter 11 Emergency Operations .....................................11-1 Introduction ..................................................................11-1 Unforecast Adverse Weather .......................................11-2 Inadvertent Thunderstorm Encounter .......................11-2 Inadvertent Icing Encounter .....................................11-2 Precipitation Static ...................................................11-3 Aircraft System Malfunctions ......................................11-3 Electronic Flight Display Malfunction .....................11-4 Alternator/Generator Failure ....................................11-4 Techniques for Electrical Usage ..............................11-5 xvi Master Battery Switch ..........................................11-5 Operating on the Main Battery .............................11-5 Loss of Alternator/Generator for Electronic Flight Instrumentation .........................................................11-5 Techniques for Electrical Usage ..............................11-6 Standby Battery ....................................................11-6 Operating on the Main Battery .............................11-6 Analog Instrument Failure ...........................................11-6 Pneumatic System Failure ............................................11-7 Pitot/Static System Failure ...........................................11-7 Communication/Navigation System Malfunction .......11-8 GPS Nearest Airport Function .....................................11-9 Nearest Airports Using the PFD ...............................11-9 Additional Information for a Specifi c Airport ......11-9 Nearest Airports Using the MFD ...........................11-10 Navigating the MFD Page Groups .....................11-10 Nearest Airport Page Group ...............................11-10 Nearest Airports Page Soft Keys ........................11-10 Situational Awareness ................................................11-11 Summary .............................................................11-12 Traffi c Avoidance ...................................................11-14 Appendix A Clearance Shorthand .........................................A-1 Appendix B Instrument Training Lesson Guide ...................B-1 Glossary ..............................................................G-1 Index ......................................................................I-1 1-1 Introduction Human factors is a broad fi eld that examines the interaction between people, machines, and the environment for the purpose of improving performance and reducing errors. As aircraft became more reliable and less prone to mechanical failure, the percentage of accidents related to human factors increased. Some aspect of human factors now accounts for over 80 percent of all accidents. Pilots who have a good understanding of human factors are better equipped to plan and execute a safe and uneventful fl ight. Flying in instrument meteorological conditions (IMC) can result in sensations that are misleading to the body’s sensory system. A safe pilot needs to understand these sensations and effectively counteract them. Instrument fl ying requires a pilot to make decisions using all available resources. The elements of human factors covered in this chapter include sensory systems used for orientation, illusions in fl ight, physiological and psychological factors, medical factors, aeronautical decision-making, and crew resource management (CRM). Human Factors Chapter 1 1-2 Figure 1-1. Rubic’s Cube Graphic. Sensory Systems for Orientation Orientation is the awareness of the position of the aircraft and of oneself in relation to a specifi c reference point. Disorientation is the lack of orientation, and spatial disorientation specifi cally refers to the lack of orientation with regard to position in space and to other objects. Orientation is maintained through the body’s sensory organs in three areas: visual, vestibular, and postural. The eyes maintain visual orientation. The motion sensing system in the inner ear maintains vestibular orientation. The nerves in the skin, joints, and muscles of the body maintain postural orientation. When healthy human beings are in their natural environment, these three systems work well. When the human body is subjected to the forces of fl ight, these senses can provide misleading information. It is this misleading information that causes pilots to become disoriented. Eyes Of all the senses, vision is most important in providing information to maintain safe flight. Even though the human eye is optimized for day vision, it is also capable of vision in very low light environments. During the day, the eye uses receptors called cones, while at night, vision is facilitated by the use of rods. Both of these provide a level of vision optimized for the lighting conditions that they were intended. That is, cones are ineffective at night and rods are ineffective during the day. Rods, which contain rhodopsin (called visual purple), are especially sensitive to light and increased light washes out the rhodopsin compromising the night vision. Hence, when strong light is momentarily introduced at night, vision may be totally ineffective as the rods take time to become effective again in darkness. Smoking, alcohol, oxygen deprivation, and age affect vision, especially at night. It should be noted that at night, oxygen deprivation such as one caused from a climb to a high altitude causes a significant reduction in vision. A return back to the lower altitude will not restore a pilot’s vision in the same transitory period used at the climb altitude. The eye also has two blind spots. The day blind spot is the location on the light sensitive retina where the optic nerve fi ber bundle (which carries messages from the eye to the brain) passes through. This location has no light receptors, and a message cannot be created there to be sent to the brain. The night blind spot is due to a concentration of cones in an area surrounding the fovea on the retina. Because there are no rods in this area, direct vision on an object at night will disappear. As a result, off-center viewing and scanning at night is best for both obstacle avoidance and to maximize situational awareness. [See the Pilot’s Handbook of Aeronautical Knowledge and the Aeronautical Information Manual (AIM) for detailed reading.] The brain also processes visual information based upon color, relationship of colors, and vision from objects around us. Figure 1-1 demonstrates the visual processing of information. The brain assigns color based on many items to include an object’s surroundings. In the fi gure below, the orange square on the shaded side of the cube is actually the same color as the brown square in the center of the cube’s top face. 1-3 Figure 1-2. Shepard’s Tables. Isolating the orange square from surrounding infl uences will reveal that it is actually brown. The application to a real environment is evident when processing visual information that is infl uenced by surroundings. The ability to pick out an airport in varied terrain or another aircraft in a light haze are examples of problems with interpretation that make vigilance all the more necessary. Figure 1-2 illustrates problems with perception. Both tables are the same lengths. Objects are easily misinterpreted in size to include both length and width. Being accustomed to a 75-foot-wide runway on fl at terrain is most likely going to influence a pilot’s perception of a wider runway on uneven terrain simply because of the inherent processing experience. Vision Under Dim and Bright Illumination Under conditions of dim illumination, aeronautical charts and aircraft instruments can become unreadable unless adequate fl ight deck lighting is available. In darkness, vision becomes more sensitive to light. This process is called dark adaptation. Although exposure to total darkness for at least 30 minutes is required for complete dark adaptation, a pilot can achieve a moderate degree of dark adaptation within 20 minutes under dim red fl ight deck lighting. Red light distorts colors (fi lters the red spectrum), especially on aeronautical charts, and makes it very diffi cult for the eyes to focus on objects inside the aircraft. Pilots should use it only where optimum outside night vision capability is necessary. White fl ight deck lighting (dim lighting) should be available when needed for map and instrument reading, especially under IMC conditions. Since any degree of dark adaptation is lost within a few seconds of viewing a bright light, pilots should close one eye when using a light to preserve some degree of night vision. During night fl ights in the vicinity of lightning, fl ight deck lights should be turned up to help prevent loss of night vision due to the bright fl ashes. Dark adaptation is also impaired by exposure to cabin pressure altitudes above 5,000 feet, carbon monoxide inhaled through smoking, defi ciency of Vitamin A in the diet, and by prolonged exposure to bright sunlight. During fl ight in visual meteorological conditions (VMC), the eyes are the major orientation source and usually provide accurate and reliable information. Visual cues usually prevail over false sensations from other sensory systems. When these visual cues are taken away, as they are in IMC, false sensations can cause the pilot to quickly become disoriented. An effective way to counter these false sensations is to recognize the problem, disregard the false sensations, rely on the fl ight instruments, and use the eyes to determine the aircraft attitude. The pilot must have an understanding of the problem and the skill to control the aircraft using only instrument indications. 1-4 Figure 1-4. Angular Acceleration and the Semicircular Tubes. Figure 1-3. Inner Ear Orientation. Ears The inner ear has two major parts concerned with orientation, the semicircular canals and the otolith organs. [Figure 1-3] The semicircular canals detect angular acceleration of the body while the otolith organs detect linear acceleration and gravity. The semicircular canals consist of three tubes at right angles to each other, each located on one of three axes: pitch, roll, or yaw as illustrated in Figure 1-4. Each canal is fi lled with a fl uid called endolymph fl uid. In the center of the canal is the cupola, a gelatinous structure that rests upon sensory hairs located at the end of the vestibular nerves. It is the movement of these hairs within the fl uid which causes sensations of motion. Because of the friction between the fl uid and the canal, it may take about 15–20 seconds for the fl uid in the ear canal to reach the same speed as the canal’s motion. To illustrate what happens during a turn, visualize the aircraft in straight and level fl ight. With no acceleration of the aircraft, the hair cells are upright and the body senses that no turn has occurred. Therefore, the position of the hair cells and the actual sensation correspond. Placing the aircraft into a turn puts the semicircular canal and its fl uid into motion, with the fl uid within the semicircular canal lagging behind the accelerated canal walls.[Figure 1-5] This lag creates a relative movement of the fl uid within the canal. The canal wall and the cupula move in the opposite direction from the motion of the fl uid. The brain interprets the movement of the hairs to be a turn in the same direction as the canal wall. The body correctly senses that a turn is being made. If the turn continues at a constant rate for several seconds or longer, the motion of the fl uid in 1-5 Figure 1-6. Linear Acceleration. Figure 1-5. Angular Acceleration. the canals catches up with the canal walls. The hairs are no longer bent, and the brain receives the false impression that turning has stopped. Thus, the position of the hair cells and the resulting sensation during a prolonged, constant turn in either direction will result in the false sensation of no turn. When the aircraft returns to straight-and-level fl ight, the fl uid in the canal moves briefl y in the opposite direction. This sends a signal to the brain that is falsely interpreted as movement in the opposite direction. In an attempt to correct the falsely perceived turn, the pilot may reenter the turn placing the aircraft in an out of control situation. The otolith organs detect linear acceleration and gravity in a similar way. Instead of being fi lled with a fl uid, a gelatinous membrane containing chalk-like crystals covers the sensory hairs. When the pilot tilts his or her head, the weight of these crystals causes this membrane to shift due to gravity and the sensory hairs detect this shift. The brain orients this new position to what it perceives as vertical. Acceleration and deceleration also cause the membrane to shift in a similar manner. Forward acceleration gives the illusion of the head tilting backward. [Figure 1-6] As a result, during takeoff and while accelerating, the pilot may sense a steeper than normal climb resulting in a tendency to nose-down. Nerves Nerves in the body’s skin, muscles, and joints constantly send signals to the brain, which signals the body’s relation to gravity. These signals tell the pilot his or her current position. Acceleration will be felt as the pilot is pushed back into the seat. Forces created in turns can lead to false sensations of the true direction of gravity, and may give the pilot a false sense of which way is up. Uncoordinated turns, especially climbing turns, can cause misleading signals to be sent to the brain. Skids and slips give the sensation of banking or tilting. Turbulence can create motions that confuse the brain as well. Pilots need to be aware that fatigue or illness can exacerbate these sensations and ultimately lead to subtle incapacitation. Illusions Leading to Spatial Disorientation The sensory system responsible for most of the illusions leading to spatial disorientation is the vestibular system. Visual illusions can also cause spatial disorientation. Vestibular Illusions The Leans A condition called the leans can result when a banked attitude, to the left for example, may be entered too slowly to set in motion the fl uid in the “roll” semicircular tubes. [Figure 1-5] An abrupt correction of this attitude sets the fl uid in motion, creating the illusion of a banked attitude to the right. The disoriented pilot may make the error of rolling the aircraft into the original left banked attitude, or if level fl ight is maintained, will feel compelled to lean in the perceived vertical plane until this illusion subsides. 1-6 Figure 1-7. Graveyard Spiral. Coriolis Illusion The coriolis illusion occurs when a pilot has been in a turn long enough for the fl uid in the ear canal to move at the same speed as the canal. A movement of the head in a different plane, such as looking at something in a different part of the fl ight deck, may set the fl uid moving and create the illusion of turning or accelerating on an entirely different axis. This action causes the pilot to think the aircraft is doing a maneuver that it is not. The disoriented pilot may maneuver the aircraft into a dangerous attitude in an attempt to correct the aircraft’s perceived attitude. For this reason, it is important that pilots develop an instrument cross-check or scan that involves minimal head movement. Take care when retrieving charts and other objects in the fl ight deck—if something is dropped, retrieve it with minimal head movement and be alert for the coriolis illusion.

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Graveyard Spiral As in other illusions, a pilot in a prolonged coordinated, constant rate turn, will have the illusion of not turning. During the recovery to level fl ight, the pilot will experience the sensation of turning in the opposite direction. The disoriented pilot may return the aircraft to its original turn. Because an aircraft tends to lose altitude in turns unless the pilot compensates for the loss in lift, the pilot may notice a loss of altitude. The absence of any sensation of turning creates the illusion of being in a level descent. The pilot may pull back on the controls in an attempt to climb or stop the descent. This action tightens the spiral and increases the loss of altitude; hence, this illusion is referred to as a graveyard spiral. [Figure 1-7] At some point, this could lead to a loss of control by the pilot. Somatogravic Illusion A rapid acceleration, such as experienced during takeoff, stimulates the otolith organs in the same way as tilting the head backwards. This action creates the somatogravic illusion of being in a nose-up attitude, especially in situations without good visual references. The disoriented pilot may push the aircraft into a nose-low or dive attitude. A rapid deceleration by quick reduction of the throttle(s) can have the opposite effect, with the disoriented pilot pulling the aircraft into a nose-up or stall attitude. Inversion Illusion An abrupt change from climb to straight-and-level fl ight can stimulate the otolith organs enough to create the illusion of tumbling backwards, or inversion illusion. The disoriented pilot may push the aircraft abruptly into a nose-low attitude, possibly intensifying this illusion. Elevator Illusion An abrupt upward vertical acceleration, as can occur in an updraft, can stimulate the otolith organs to create the illusion of being in a climb. This is called elevator illusion. The disoriented pilot may push the aircraft into a nose-low attitude. An abrupt downward vertical acceleration, usually 1-7 Figure 1-8. Sensations From Centrifugal Force. in a downdraft, has the opposite effect, with the disoriented pilot pulling the aircraft into a nose-up attitude. Visual Illusions Visual illusions are especially hazardous because pilots rely on their eyes for correct information. Two illusions that lead to spatial disorientation, false horizon and autokinesis, are concerned with only the visual system. False Horizon A sloping cloud formation, an obscured horizon, an aurora borealis, a dark scene spread with ground lights and stars, and certain geometric patterns of ground lights can provide inaccurate visual information, or false horizon, for aligning the aircraft correctly with the actual horizon. The disoriented pilot may place the aircraft in a dangerous attitude. Autokinesis In the dark, a stationary light will appear to move about when stared at for many seconds. The disoriented pilot could lose control of the aircraft in attempting to align it with the false movements of this light, called autokinesis. Postural Considerations The postural system sends signals from the skin, joints, and muscles to the brain that are interpreted in relation to the Earth’s gravitational pull. These signals determine posture. Inputs from each movement update the body’s position to the brain on a constant basis. “Seat of the pants” fl ying is largely dependent upon these signals. Used in conjunction with visual and vestibular clues, these sensations can be fairly reliable. However, because of the forces acting upon the body in certain fl ight situations, many false sensations can occur due to acceleration forces overpowering gravity. [Figure 1-8] These situations include uncoordinated turns, climbing turns, and turbulence. Demonstration of Spatial Disorientation There are a number of controlled aircraft maneuvers a pilot can perform to experiment with spatial disorientation. While each maneuver will normally create a specifi c illusion, any false sensation is an effective demonstration of disorientation. Thus, even if there is no sensation during any of these maneuvers, the absence of sensation is still an effective demonstration in that it shows the inability to detect bank or roll. There are several objectives in demonstrating these various maneuvers. 1. They teach pilots to understand the susceptibility of the human system to spatial disorientation. 2. They demonstrate that judgments of aircraft attitude based on bodily sensations are frequently false. 3. They help lessen the occurrence and degree of disorientation through a better understanding of the relationship between aircraft motion, head movements, and resulting disorientation. 4. They help instill a greater confi dence in relying on fl ight instruments for assessing true aircraft attitude. 1-8 A pilot should not attempt any of these maneuvers at low altitudes, or in the absence of an instructor pilot or an appropriate safety pilot. Climbing While Accelerating With the pilot’s eyes closed, the instructor pilot maintains approach airspeed in a straight-and-level attitude for several seconds, and then accelerates while maintaining straight-andlevel attitude. The usual illusion during this maneuver, without visual references, will be that the aircraft is climbing. Climbing While Turning With the pilot’s eyes still closed and the aircraft in a straightand- level attitude, the instructor pilot now executes, with a relatively slow entry, a well-coordinated turn of about 1.5 positive G (approximately 50° bank) for 90°. While in the turn, without outside visual references and under the effect of the slight positive G, the usual illusion produced is that of a climb. Upon sensing the climb, the pilot should immediately open the eyes and see that a slowly established, coordinated turn produces the same feeling as a climb. Diving While Turning Repeating the previous procedure, with the exception that the pilot’s eyes should be kept closed until recovery from the turn is approximately one-half completed can create this sensation. With the eyes closed, the usual illusion will be that the aircraft is diving. Tilting to Right or Left While in a straight-and-level attitude, with the pilot’s eyes closed, the instructor pilot executes a moderate or slight skid to the left with wings level. This creates the illusion of the body being tilted to the right. Reversal of Motion This illusion can be demonstrated in any of the three planes of motion. While straight and level, with the pilot’s eyes closed, the instructor pilot smoothly and positively rolls the aircraft to approximately a 45° bank attitude while maintaining heading and pitch attitude. This creates the illusion of a strong sense of rotation in the opposite direction. After this illusion is noted, the pilot should open his or her eyes and observe that the aircraft is in a banked attitude. Diving or Rolling Beyond the Vertical Plane This maneuver may produce extreme disorientation. While in straight-and-level fl ight, the pilot should sit normally, either with eyes closed or gaze lowered to the fl oor. The instructor pilot starts a positive, coordinated roll toward a 30° or 40° angle of bank. As this is in progress, the pilot tilts his or her head forward, looks to the right or left, then immediately returns his or her head to an upright position. The instructor pilot should time the maneuver so the roll is stopped as the pilot returns his or her head upright. An intense disorientation is usually produced by this maneuver, and the pilot experiences the sensation of falling downward into the direction of the roll. In the descriptions of these maneuvers, the instructor pilot is doing the fl ying, but having the pilot do the fl ying can also be a very effective demonstration. The pilot should close his or her eyes and tilt the head to one side. The instructor pilot tells the pilot what control inputs to perform. The pilot then attempts to establish the correct attitude or control input with eyes closed and head tilted. While it is clear the pilot has no idea of the actual attitude, he or she will react to what the senses are saying. After a short time, the pilot will become disoriented and the instructor pilot then tells the pilot to look up and recover. The benefi t of this exercise is the pilot experiences the disorientation while fl ying the aircraft. Coping with Spatial Disorientation To prevent illusions and their potentially disastrous consequences, pilots can: 1. Understand the causes of these illusions and remain constantly alert for them. Take the opportunity to understand and then experience spatial disorientation illusions in a device such as a Barany chair, a Vertigon, or a Virtual Reality Spatial Disorientation Demonstrator. 2. Always obtain and understand preflight weather briefi ngs. 3. Before fl ying in marginal visibility (less than 3 miles) or where a visible horizon is not evident such as fl ight over open water during the night, obtain training and maintain profi ciency in airplane control by reference to instruments. 4. Do not continue fl ight into adverse weather conditions or into dusk or darkness unless profi cient in the use of fl ight instruments. If intending to fl y at night, maintain night-fl ight currency and profi ciency. Include crosscountry and local operations at various airfi elds. 5. Ensure that when outside visual references are used, they are reliable, fi xed points on the Earth’s surface. 6. Avoid sudden head movement, particularly during takeoffs, turns, and approaches to landing. 7. Be physically tuned for fl ight into reduced visibility. That is, ensure proper rest, adequate diet, and, if fl ying at night, allow for night adaptation. Remember that illness, medication, alcohol, fatigue, sleep loss, and mild hypoxia are likely to increase susceptibility to spatial disorientation. 1-9 Water Refraction Rain on the windscreen can create an illusion of being at a higher altitude due to the horizon appearing lower than it is. This can result in the pilot fl ying a lower approach. Haze Atmospheric haze can create an illusion of being at a greater distance and height from the runway. As a result, the pilot will have a tendency to be low on the approach. Conversely, extremely clear air (clear bright conditions of a high attitude airport) can give the pilot the illusion of being closer than he or she actually is, resulting in a high approach, which may result in an overshoot or go around. The diffusion of light due to water particles on the windshield can adversely affect depth perception. The lights and terrain features normally used to gauge height during landing become less effective for the pilot. Fog Flying into fog can create an illusion of pitching up. Pilots who do not recognize this illusion will often steepen the approach quite abruptly. Ground Lighting Illusions Lights along a straight path, such as a road or lights on moving trains, can be mistaken for runway and approach lights. Bright runway and approach lighting systems, especially where few lights illuminate the surrounding terrain, may create the illusion of less distance to the runway. The pilot who does not recognize this illusion will often fl y a higher approach. How To Prevent Landing Errors Due to Optical Illusions To prevent these illusions and their potentially hazardous consequences, pilots can: 1. Anticipate the possibility of visual illusions during approaches to unfamiliar airports, particularly at night or in adverse weather conditions. Consult airport diagrams and the Airport/Facility Directory (A/FD) for information on runway slope, terrain, and lighting. 2. Make frequent reference to the altimeter, especially during all approaches, day and night. 3. If possible, conduct aerial visual inspection of unfamiliar airports before landing. 8. Most importantly, become profi cient in the use of flight instruments and rely upon them. Trust the instruments and disregard your sensory perceptions. The sensations that lead to illusions during instrument fl ight conditions are normal perceptions experienced by pilots. These undesirable sensations cannot be completely prevented, but through training and awareness, pilots can ignore or suppress them by developing absolute reliance on the flight instruments. As pilots gain proficiency in instrument fl ying, they become less susceptible to these illusions and their effects. Optical Illusions Of the senses, vision is the most important for safe fl ight. However, various terrain features and atmospheric conditions can create optical illusions. These illusions are primarily associated with landing. Since pilots must transition from reliance on instruments to visual cues outside the fl ight deck for landing at the end of an instrument approach, it is imperative they be aware of the potential problems associated with these illusions, and take appropriate corrective action. The major illusions leading to landing errors are described below. Runway Width Illusion A narrower-than-usual runway can create an illusion the aircraft is at a higher altitude than it actually is, especially when runway length-to-width relationships are comparable. [Figure 1-9A] The pilot who does not recognize this illusion will fl y a lower approach, with the risk of striking objects along the approach path or landing short. A wider-than-usual runway can have the opposite effect, with the risk of leveling out high and landing hard, or overshooting the runway. Runway and Terrain Slopes Illusion An upsloping runway, upsloping terrain, or both, can create an illusion the aircraft is at a higher altitude than it actually is. [Figure 1-9B] The pilot who does not recognize this illusion will fl y a lower approach. Downsloping runways and downsloping approach terrain can have the opposite effect. Featureless Terrain Illusion An absence of surrounding ground features, as in an overwater approach, over darkened areas, or terrain made featureless by snow, can create an illusion the aircraft is at a higher altitude than it actually is. This illusion, sometimes referred to as the “black hole approach,” causes pilots to fl y a lower approach than is desired. 1-10 Figure 1-9. Runway Width and Slope Illusions. 6. Recognize that the chances of being involved in an approach accident increase when some emergency or other activity distracts from usual procedures. 7. Maintain optimum profi ciency in landing procedures. 4. Use Visual Approach Slope Indicator (VASI) or Precision Approach Path Indicator (PAPI) systems for a visual reference, or an electronic glide slope, whenever they are available. 5. Utilize the visual descent point (VDP) found on many nonprecision instrument approach procedure charts. 1-11 Figure 1-10. Stress and Performance. Physiological and Psychological Factors Physiological or psychological factors can affect a pilot and compromise the safety of a fl ight. These factors are stress, medical, alcohol, and fatigue. Any of these factors, individually or in combination, signifi cantly degrade the pilot’s decision-making or fl ying abilities. Stress Stress is the body’s response to demands placed upon it. These demands can be either pleasant or unpleasant in nature. The causes of stress for a pilot can range from unexpected weather or mechanical problems while in fl ight, to personal issues unrelated to fl ying. Stress is an inevitable and necessary part of life; it adds motivation to life and heightens an individual’s response to meet any challenge. The effects of stress are cumulative and there is a limit to a person’s adaptive nature. This limit, called the stress tolerance level (or channel capacity), is based on the ability to cope with the situation. At fi rst, some amount of stress can be desirable and can actually improve performance. However, higher stress levels, particularly over long periods of time, can adversely affect performance. Performance will generally increase with the onset of stress, but will peak and then begin to fall off rapidly as stress levels exceed the ability to cope. [Figure 1-10] At this point, a pilot’s performance begins to decline and judgment deteriorates. Complex or unfamiliar tasks require higher levels of performance than simple or overlearned tasks. Complex or unfamiliar tasks are also more subject to the adverse effects of increasing stress than simple or familiar tasks. [Figure 1-10] The indicators of excessive stress often show as three types of symptoms: (1) emotional, (2) physical, and (3) behavioral. Emotional symptoms may surface as over-compensation, denial, suspicion, paranoia, agitation, restlessness, or defensiveness. Physical stress can result in acute fatigue while behavioral degradation will be manifested as sensitivity to criticism, tendency to be argumentative, arrogance, and hostility. Pilots need to learn to recognize the symptoms of stress as they begin to occur. There are many techniques available that can help reduce stress in life or help people cope with it better. Not all of the following ideas may be a solution, but some of them should be effective. 1. Become knowledgeable about stress. 2. Take a realistic self-assessment. (See the Pilot’s Handbook of Aeronautical Knowledge). 3. Take a systematic approach to problem solving. 4. Develop a lifestyle that will buffer against the effects of stress. 5. Practice behavior management techniques. 6. Establish and maintain a strong support network. Good fl ight deck stress management begins with good life stress management. Many of the stress coping techniques practiced for life stress management are not usually practical in fl ight. Rather, pilots must condition themselves to relax and think rationally when stress appears. The following checklist outlines some methods of fl ight deck stress management. 1. Avoid situations that distract from fl ying the aircraft. 2. Reduce fl ight deck workload to reduce stress levels. This will create a proper environment in which to make good decisions. Typically, fl ying involves higher stress levels during takeoff and landing phases. Between the two generally lies a period of low activity resulting in a lower stress level. Transitioning from the cruise phase to the landing phase is generally accompanied by a significant workload that, if not properly accommodated, will increase stress significantly. Proper planning and prioritization of flight deck duties are key to avoiding events that affect the pilot's capacity to maintain situational awareness.

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1-12 3. If a problem occurs, remain calm. If time is not a pressing factor, follow the analytical approach to decision-making: think for a moment, weigh the alternatives, select and take an appropriate course of action, and then evaluate its effects. If an emergency situation occurs, remain calm and use the aeronautical decision-making (ADM) process to resolve the emergency. This process relies on the pilot’s training and experience to accurately and automatically respond to an emergency situation. Constant training in handling emergency procedures will help reduce pilot stress when an emergency occurs. 4. Become thoroughly familiar with the aircraft, its operation, and emergency procedures. Also, maintain fl ight profi ciency to build confi dence. 5. Know and respect personal limits. Studies have suggested that highly experienced pilots have taken more chances when flying into potential icing conditions than low time or inexperienced pilots. Very low time pilots without experience may analyze and interpret the likelihood for “potential” fl ight into icing without the benefi t of life experience, thereby making decisions closely aligned with the compilation of their training and recent academic knowledge. Highly experienced pilots may evaluate the current situation based upon the empirical information (sometimes diluted with time) coupled with their vast experience. This may lead to a level of greater acceptability of the situation because their experience has illustrated successful navigation of this problem before. Therefore, the automatic decision may be in error because not all salient facts are evaluated. 6. Do not allow small mistakes to be distractions during fl ight; rather, review and analyze them after landing. 7. If flying adds stress, either stop flying or seek professional help to manage stress within acceptable limits. Medical Factors A “go/no-go” decision based on a pilot’s medical factors is made before each fl ight. The pilot should not only prefl ight check the aircraft, but also himself or herself before every fl ight. A pilot should ask, “Can I pass my medical examination right now?” If the answer is not an absolute “yes,” do not fl y. This is especially true for pilots embarking on fl ights in IMC. Instrument fl ying is much more demanding than fl ying in VMC, and peak performance is critical for the safety of fl ight. Pilot performance can be seriously degraded by both prescribed and over-the-counter medications, as well as by the medical conditions for which they are taken. Many medications, such as tranquilizers, sedatives, strong pain relievers, and cough suppressants, have primary effects that impair judgment, memory, alertness, coordination, vision, and the ability to make calculations. Others, such as antihistamines, blood pressure drugs, muscle relaxants, and agents to control diarrhea and motion sickness, have side effects that impair the same critical functions. Any medication that depresses the nervous system, such as a sedative, tranquilizer, or antihistamine, makes a pilot much more susceptible to hypoxia. Title 14 of the Code of Federal Regulations (14 CFR) prohibits pilots from performing crewmember duties while using any medication that affects the faculties in any way contrary to safety. The safest rule is not to fl y as a crewmember while taking any medication, unless approved to do so by the Federal Aviation Administration (FAA). If there is any doubt regarding the effects of any medication, consult an Aviation Medical Examiner (AME) before fl ying. Alcohol 14 CFR part 91 prohibits pilots from performing crewmember duties within 8 hours after drinking any alcoholic beverage or while under the infl uence. Extensive research has provided a number of facts about the hazards of alcohol consumption and fl ying. As little as one ounce of liquor, one bottle of beer, or four ounces of wine can impair fl ying skills and render a pilot much more susceptible to disorientation and hypoxia. Even after the body completely metabolizes a moderate amount of alcohol, a pilot can still be impaired for many hours. There is simply no way of increasing the metabolism of alcohol or alleviating a hangover. Fatigue Fatigue is one of the most treacherous hazards to fl ight safety, as it may not be apparent to a pilot until serious errors are made. Fatigue can be either acute (short-term) or chronic (long-term). Acute Fatigue A normal occurrence of everyday living, acute fatigue is the tiredness felt after long periods of physical and mental strain, including strenuous muscular effort, immobility, heavy mental workload, strong emotional pressure, monotony, and lack of sleep. Adequate rest, regular exercise, and proper nutrition prevent acute fatigue. 1-13 Indications of fatigue are generally subtle and hard to recognize because the individual being assessed is generally the person making the assessment, as in single pilot operations. Therefore, the pilot must look at small errors that occur to provide an indication of becoming fatigued. These include: • Misplacing items during the prefl ight; • Leaving material (pencils, charts) in the planning area; • Missing radio calls; • Answering calls improperly (read-backs); and • Improper tuning of frequencies. Chronic Fatigue Chronic fatigue occurs when there is not enough time for a full recovery from repeated episodes of acute fatigue. Chronic fatigue’s underlying cause is generally not “rest-related” and may have deeper points of origin. Therefore, rest alone may not resolve chronic fatigue. Chronic fatigue is a combination of both physiological problems and psychological issues. Psychological problems such as fi nancial, home life, or job related stresses cause a lack of qualifi ed rest that is only resolved by mitigating the underpinning problems. Without resolution, performance continues to fall off, judgment becomes impaired, and unwarranted risks are taken. Recovery from chronic fatigue requires a prolonged and deliberate solution. In either case, unless adequate precautions are taken, personal performance could be impaired and adversely affect pilot judgment and decision-making. IMSAFE Checklist The following checklist, IMSAFE, is intended for a pilot’s personal prefl ight use. A quick check of the items on this list will help a pilot make a good self-evaluation prior to any fl ight. If the answer to any of the checklist questions is yes, then the pilot should consider not fl ying. Illness Do I have any symptoms? Medication Have I been taking prescription or over-the-counter drugs? Stress Am I under psychological pressure from the job? Do I have money, health, or family problems? Alcohol Have I been drinking within 8 hours? Within 24 hours? Fatigue Am I tired and not adequately rested? Eating Have I eaten enough of the proper foods to keep adequately nourished during the entire fl ight? Hazard Identifi cation In order to identify a hazard, it would be useful to defi ne what a hazard is. The FAA System Safety course defi nes a hazard as: “a present condition, event, object, or circumstance that could lead or contribute to an unplanned or undesired event.” Put simply, a hazard is a source of danger. Potential hazards may be identifi ed from a number of internal and external sources. These may be based upon several concurrent factors that provide an indication and ultimate identifi cation of a hazard. Consider the following situations: Situation 1 The pilot has just taken off and is entering the clouds. Suddenly, there is an explosive sound. The sudden noise is disturbing and occurs as the pilot is given a new heading, a climb restriction, and the frequency for the departure control. Situation 2 The pilot took off late in a rented aircraft (fi rst time fl ying this model), and is now in night conditions due to the delay, and fl ying on an instrument fl ight rules (IFR) fl ight plan in IMC conditions. The radios do not seem to work well and develop static. They seem to be getting weaker. As the pilot proceeds, the rotating beacon stops fl ashing/rotating, and the lights become dimmer. As the situation progresses, the pilot is unaware of the problem because the generator warning light, (on the lower left of the panel) is obscured by the chart on the pilot’s lap. Both situations above represent hazards that must be dealt with differently and a level of risk must be associated with each depending on various factors affecting the fl ight. Risk Analysis Risk is defi ned as the future impact of a hazard that is not eliminated or controlled. It is the possibility of loss or injury. Risk analysis is the process whereby hazards are characterized by their likelihood and severity. Risk analysis evaluates the hazards to determine the outcomes and how abrupt that outcome will occur. The analysis applied will be qualitative to the degree that time allows resulting in either an analytical or automatic approach in the decision-making process. 1-14 In the fi rst situation, the decision may be automatic: fl y the airplane to a safe landing. Since automatic decision-making is based upon education and experience, an inexperienced pilot may react improperly to the situation which results in an inadequate action. To mitigate improper decision-making, immediate action items from emergency procedures should be learned. Training, education, and mentorship are all key factors in honing automatic decision-making skills. In the second situation, if the pilot has a fl ashlight onboard, it can be used for illumination, although its light may degrade night vision. After changing the appropriate transponder code, and making calls in the blind, awareness of present location becomes imperative, especially if the pilot must execute a controlled descent to VMC conditions. Proper prefl ight planning conducted before departure and constant awareness of location provide an element of both comfort (reduces stress) and information from which the pilot can draw credible information. In both cases, the outcomes can be successful through systems understanding, emergency procedures training, and correctly analyzing the risks associated with each course of action. Crew Resource Management (CRM) and Single-Pilot Resource Management (SRM) Crew resource management (CRM) and single-pilot resource management (SRM) is the ability for the crew or pilot to manage all resources effectively to ensure the outcome of the fl ight is successful. In general aviation, SRM will be most often used and its focus is on the single-pilot operation. SRM integrates the following: • Situational Awareness • Flight Deck Resource Management • Task Management • Aeronautical Decision-making (ADM) and Risk Management SRM recognizes the need to seek proper information from these sources to make a valid decision. For instance, the pilot may have to request assistance from others and be assertive to resolve situations. Pilots should understand the need to seek information from other sources until they have the proper information to make the best decision. Once a pilot has gathered all pertinent information and made the appropriate decision, the pilot needs to perform an assessment of the action taken. Situational Awareness Situational awareness is the accurate perception of operational and environmental factors that affect the fl ight. It is a logical analysis based upon the machine, external support, environment, and the pilot. It is knowing what is going on. Flight Deck Resource Management CRM is the effective use of all available resources: human, equipment, and information. It focuses on communication skills, teamwork, task allocation, and decision-making. While CRM often concentrates on pilots who operate in crew environments, the elements and concepts also apply to single-pilot operations.

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Human Resources Human resources include everyone routinely working with the pilot to ensure fl ight safety. These people include, but are not limited to: weather briefers, fl ight line personnel, maintenance personnel, crew members, pilots, and air traffi c personnel. Pilots need to effectively communicate with these people. This is accomplished by using the key components of the communication process: inquiry, advocacy, and assertion. Pilots must recognize the need to seek enough information from these resources to make a valid decision. After the necessary information has been gathered, the pilot’s decision must be passed on to those concerned, such as air traffi c controllers, crew members, and passengers. The pilot may have to request assistance from others and be assertive to safely resolve some situations. Equipment Equipment in many of today’s aircraft includes automated fl ight and navigation systems. These automatic systems, while providing relief from many routine fl ight deck tasks, present a different set of problems for pilots. The automation intended to reduce pilot workload essentially removes the pilot from the process of managing the aircraft, thereby reducing situational awareness and leading to complacency. Information from these systems needs to be continually monitored to ensure proper situational awareness. Pilots should be thoroughly familiar with the operation of and information provided by all systems used. It is essential that pilots be aware not only of equipment capabilities, but also equipment limitations in order to manage those systems effectively and safely. Information Workload Information workloads and automated systems, such as autopilots, need to be properly managed to ensure a safe 1-15 Figure 1-11. The Margin of Safety. fl ight. The pilot fl ying in IMC is faced with many tasks, each with a different level of importance to the outcome of the fl ight. For example, a pilot preparing to execute an instrument approach to an airport needs to review the approach chart, prepare the aircraft for the approach and landing, complete checklists, obtain information from Automatic Terminal Information Service (ATIS) or air traffi c control (ATC), and set the navigation radios and equipment. The pilot who effectively manages his or her workload will complete as many of these tasks as early as possible to preclude the possibility of becoming overloaded by last minute changes and communication priorities in the later, more critical stages of the approach. Figure 1-11 shows the margin of safety is at the minimum level during this stage of the approach. Routine tasks delayed until the last minute can contribute to the pilot becoming overloaded and stressed, resulting in erosion of performance. By planning ahead, a pilot can effectively reduce workload during critical phases of fl ight. If a pilot enters the fi nal phases of the instrument approach unprepared, the pilot should recognize the situation, abandon the approach, and try it again after becoming better prepared. Effective resource management includes recognizing hazardous situations and attitudes, decision-making to promote good judgment and headwork, and managing the situation to ensure the safe outcome of the IFR fl ight. Task Management Pilots have a limited capacity for information. Once information fl ow exceeds the pilot’s ability to mentally process the information any additional information will become unattended or displace other tasks and information already being processed. This is termed channel capacity and once reached only two alternatives exist: shed the unimportant tasks or perform all tasks at a less than optimal level. Like an electrical circuit being overloaded, either the consumption must be reduced or a circuit failure is experienced. The pilot who effectively manages the tasks and properly prioritizes them will have a successful fl ight. For example, do not become distracted and fi xate on an instrument light failure. This unnecessary focus displaces capability and prevents the pilot’s ability to appreciate tasks of greater importance. By planning ahead, a pilot can effectively reduce workload during critical phases of a fl ight. Aeronautical Decision-Making (ADM) Flying safely requires the effective integration of three separate sets of skills. Most obvious are the basic stick-andrudder skills needed to control the airplane. Next, are skills related to profi cient operation of aircraft systems, and last, but not least, are ADM skills. ADM is a systematic approach to the mental process used by pilots to consistently determine the best course of action in response to a given set of circumstances. The importance of learning effective ADM skills cannot be overemphasized. While progress is continually being made in the advancement of pilot training methods, airplane equipment and systems, and services for pilots, accidents still occur. Despite all the changes in technology to improve fl ight safety, one factor remains the same—the human factor. While the FAA strives to eliminate errors through training and safety programs, one fact remains: humans make errors. It is estimated that approximately 80 percent of all aviation accidents are human factors related. 1-16 The ADM process addresses all aspects of decision making in the fl ight deck and identifi es the steps involved in good decision making. While the ADM process will not eliminate errors, it will help the pilot recognize errors, and in turn enable the pilot to manage the error to minimize its effects. These steps are: 1. Identifying personal attitudes hazardous to safe fl ight; 2. Learning behavior modifi cation techniques; 3. Learning how to recognize and cope with stress; 4. Developing risk assessment skills; 5. Using all resources; and 6. Evaluating the effectiveness of one’s ADM skills. Historically, the term “pilot error” has been used to describe the causes of these accidents. Pilot error means that an action or decision made by the pilot was the cause, or a contributing factor that led to the accident. This defi nition also includes the pilot’s failure to make a decision or take action. From a broader perspective, the phrase “human factors related” more aptly describes these accidents since it is usually not a single decision that leads to an accident, but a chain of events triggered by a number of factors. The poor judgment chain, sometimes referred to as the “error chain,” is a term used to describe this concept of contributing factors in a human factors related accident. Breaking one link in the chain normally is all that is necessary to change the outcome of the sequence of events. The Decision-Making Process An understanding of the decision-making process provides a pilot with a foundation for developing ADM skills. Some situations, such as engine failures, require a pilot to respond immediately using established procedures with a little time for detailed analysis. This is termed automatic decision-making and is based upon training, experience, and recognition. Traditionally, pilots have been well trained to react to emergencies, but are not as well prepared to make decisions requiring a more refl ective response where greater analysis is required. Typically during a fl ight, there is time to examine any changes that occur, gather information, and assess risk before reaching a decision. The steps leading to this conclusion constitute the decision-making process. Defi ning the Problem Problem defi nition is the fi rst step in the decision-making process. Defi ning the problem begins with recognizing that a change has occurred or that an expected change did not occur. A problem is perceived fi rst by the senses, then is distinguished through insight and experience. One critical error that can be made during the decision-making process is incorrectly defi ning the problem. For example, a low oil pressure reading could indicate that the engine is about to fail and an emergency landing should be planned, or it could mean that the oil pressure sensor has failed. The actions to be taken in each of these circumstances would be signifi cantly different. One requires an immediate decision based upon training, experience, and evaluation of the situation; whereas the latter decision is based upon an analysis. It should be noted that the same indication could result in two different actions depending upon other infl uences. Choosing a Course of Action After the problem has been identifi ed, the pilot must evaluate the need to react to it and determine the actions that may be taken to resolve the situation in the time available. The expected outcome of each possible action should be considered and the risks assessed before deciding on a response to the situation. Implementing the Decision and Evaluating the Outcome Although a decision may be reached and a course of action implemented, the decision-making process is not complete. It is important to think ahead and determine how the decision could affect other phases of fl ight. As the fl ight progresses, the pilot must continue to evaluate the outcome of the decision to ensure that it is producing the desired result. Improper Decision-Making Outcomes Pilots sometimes get in trouble not because of defi cient basic skills or system knowledge, but rather because of faulty decision-making skills. Although aeronautical decisions may appear to be simple or routine, each individual decision in aviation often defi nes the options available for the next decision the pilot must make and the options, good or bad, they provide. Therefore, a poor decision early on in a fl ight can compromise the safety of the fl ight at a later time necessitating decisions that must be more accurate and decisive. Conversely, good decision-making early on in an emergency provide greater latitude for options later on. FAA Advisory Circular (AC) 60-22, defi nes ADM as a systematic approach to the mental process of evaluating a given set of circumstances and determining the best course of action. ADM thus builds upon the foundation of conventional decision-making, but enhances the process to decrease the probability of pilot error. Specifi cally, ADM provides a structure to help the pilot use all resources to develop comprehensive situational awareness. 1-17 Figure 1-12. The 3P Model for Aeronautical Decision-Making. Models for Practicing ADM Two models for practicing ADM are presented below. Perceive, Process, Perform The Perceive–Process–Perform (3P) model for ADM offers a simple, practical, and systematic approach that can be used during all phases of fl ight. [Figure 1-12] To use it, the pilot will: • Perceive the given set of circumstances for a fl ight; • Process by evaluating their impact on fl ight safety; and • Perform by implementing the best course of action. In the fi rst step, the goal is to develop situational awareness by perceiving hazards, which are present events, objects, or circumstances that could contribute to an undesired future event. In this step, the pilot will systematically identify and list hazards associated with all aspects of the fl ight: pilot, aircraft, environment, and external pressures. It is important to consider how individual hazards might combine. Consider, for example, the hazard that arises when a new instrument pilot with no experience in actual instrument conditions wants to make a cross-country fl ight to an airport with low ceilings in order to attend an important business meeting. In the second step, the goal is to process this information to determine whether the identifi ed hazards constitute risk, which is defi ned as the future impact of a hazard that is not controlled or eliminated. The degree of risk posed by a given hazard can be measured in terms of exposure (number of people or resources affected), severity (extent of possible loss), and probability (the likelihood that a hazard will cause a loss). If the hazard is low ceilings, for example, the level of risk depends on a number of other factors, such as pilot training and experience, aircraft equipment and fuel capacity, and others. In the third step, the goal is to perform by taking action to eliminate hazards or mitigate risk, and then continuously evaluate the outcome of this action. With the example of low ceilings at destination, for instance, the pilot can perform good ADM by selecting a suitable alternate, knowing where to fi nd good weather, and carrying suffi cient fuel to reach it. This course of action would mitigate the risk. The pilot also has the option to eliminate it entirely by waiting for better weather. Once the pilot has completed the 3P decision process and selected a course of action, the process begins anew because now the set of circumstances brought about by the course of action requires analysis. The decision-making process is a continuous loop of perceiving, processing and performing. The DECIDE Model Another structured approach to ADM is the DECIDE model, which is a six-step process intended to provide a logical way of approaching decision-making. As in the 3P model, the elements of the DECIDE model represent a continuous loop process to assist a pilot in the decision-making required when faced with a situational change that requires judgment. [Figure 1-13C] The model is primarily focused on the intellectual component, but can have an impact on the motivational component of judgment as well. If a pilot continually uses the DECIDE Model in all decision-making, it becomes natural and results in better decisions being made under all types of situations. The steps in this approach are listed in Figure 1-13C. In conventional decision-making, the need for a decision is triggered by recognition that something has changed or an expected change did not occur. Recognition of the change, or lack of change, is a vital step in any decision making process. Not noticing change in a situation can lead directly to a mishap. [Figure 1-13A] The change indicates that an appropriate response or action is necessary in order to modify the situation (or, at least, one of the elements that comprise it) and bring about a desired new situation. Therefore, situational awareness is the key to successful and safe decision making. At this point in the process, the pilot is faced with a need to evaluate the entire range of possible responses to the detected change and to determine the best course of action. Figure 1-13B illustrates how the ADM process expands conventional decision-making, shows the interactions of the

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1-18 Figure 1-13. Decision-Making. ADM steps, and how these steps can produce a safe outcome. Starting with the recognition of change, and following with an assessment of alternatives, a decision to act or not act is made, and the results are monitored. Pilots can use ADM to enhance their conventional decision-making process because it: 1. Increases their awareness of the importance of attitude in decision-making; 2. Teaches the ability to search for and establish relevance of information; and 3. Increases their motivation to choose and execute actions that ensure safety in the situational timeframe. Hazardous Attitudes and Antidotes Hazardous attitudes, which contribute to poor pilot judgment, can be effectively counteracted by redirecting that hazardous attitude so that correct action can be taken. Recognition of hazardous thoughts is the fi rst step toward neutralizing them. After recognizing a thought as hazardous, the pilot should label it as hazardous, then state the corresponding antidote. Antidotes should be memorized for each of the hazardous attitudes so they automatically come to mind when needed. Each hazardous attitude along with its appropriate antidote is shown in Figure 1-14. 1-19 Figure 1-14. The Five Antidotes to Hazardous Attitudes. Research has identifi ed fi ve hazardous attitudes that can affect a pilot’s judgment, as well as antidotes for each of these fi ve attitudes. ADM addresses the following: 1. Anti-authority (“Don’t tell me!”). This attitude is found in pilots who do not like anyone telling them what to do. They may be resentful of having someone tell them what to do or may regard rules, regulations, and procedures as silly or unnecessary. However, there is always the prerogative to question authority if it is perceived to be in error. 2. Impulsivity (“Do something quickly!”). This attitude is found in pilots who frequently feel the need to do something—anything—immediately. They do not stop to think about what they are about to do, they do not select the best course of action, and they do the fi rst thing that comes to mind. 3. Invulnerability (“It won’t happen to me!”). Many pilots feel that accidents happen to others, but never to them. They know accidents can happen, and they know that anyone can be affected. They never really feel or believe that they will be personally involved. Pilots who think this way are more likely to take chances and increase risk. 4. Macho (“I can do it!”). Pilots who are always trying to prove that they are better than anyone else are thinking, “I can do it—I’ll show them.” Pilots with this type of attitude will try to prove themselves by taking risks in order to impress others. This pattern is characteristic in both men and women. 5. Resignation (“What’s the use?”). These pilots do not see themselves as being able to make a great deal of difference in what happens to them. When things go well, these pilots are apt to think it is due to good luck. When things go badly, they may feel that someone is out to get them, or attribute it to bad luck. The pilot will leave the action to others, for better or worse. Sometimes, they will even go along with unreasonable requests just to be a “nice guy.” 1-20 2-1 Introduction Several factors affect aircraft performance including the atmosphere, aerodynamics, and aircraft icing. Pilots need an understanding of these factors for a sound basis for prediction of aircraft response to control inputs, especially with regard to instrument approaches, while holding, and when operating at reduced airspeed in instrument meteorological conditions (IMC). Although these factors are important to the pilot fl ying visual fl ight rules (VFR), they must be even more thoroughly understood by the pilot operating under instrument fl ight rules (IFR). Instrument pilots rely strictly on instrument indications to precisely control the aircraft; therefore, they must have a solid understanding of basic aerodynamic principles in order to make accurate judgments regarding aircraft control inputs. Aerodynamic Factors Chapter 2 2-2 Figure 2-1. The Airfoil. Figure 2-2. Angle of Attack and Relative Wind. The Wing To understand aerodynamic forces, a pilot needs to understand basic terminology associated with airfoils. Figure 2-1 illustrates a typical airfoil. The chord line is the straight line intersecting the leading and trailing edges of the airfoil, and the term chord refers to the chord line longitudinal length (length as viewed from the side). The mean camber is a line located halfway between the upper and lower surfaces. Viewing the wing edgewise, the mean camber connects with the chord line at each end. The mean camber is important because it assists in determining aerodynamic qualities of an airfoil. The measurement of the maximum camber; inclusive of both the displacement of the mean camber line and its linear measurement from the end of the chord line, provide properties useful in evaluating airfoils. Review of Basic Aerodynamics The instrument pilot must understand the relationship and differences between several factors that affect the performance of an aircraft in fl ight. Also, it is crucial to understand how the aircraft reacts to various control and power changes, because the environment in which instrument pilots fl y has inherent hazards not found in visual fl ying. The basis for this understanding is found in the four forces acting on an aircraft and Newton’s Three Laws of Motion. Relative Wind is the direction of the airfl ow with respect to an airfoil. Angle of Attack is the acute angle measured between the relative wind, or fl ight path and the chord of the airfoil. [Figure 2-2] Flight path is the course or track along which the aircraft is fl ying or is intended to be fl own. The Four Forces The four basic forces [Figure 2-3] acting upon an aircraft in fl ight are lift, weight, thrust, and drag. Lift Lift is a component of the total aerodynamic force on an airfoil and acts perpendicular to the relative wind. Relative wind is the direction of the airfl ow with respect to an airfoil. This force acts straight up from the average (called mean) center of pressure (CP), which is called the center of lift. It should be noted that it is a point along the chord line of an airfoil through which all aerodynamic forces are considered to act. The magnitude of lift varies proportionately with speed, air density, shape and size of the airfoil, and angle of attack. During straight-and-level fl ight, lift and weight are equal. 2-3 Figure 2-3. The Four Forces and Three Axes of Rotation. Weight Weight is the force exerted by an aircraft from the pull of gravity. It acts on an aircraft through its center of gravity (CG) and is straight down. This should not be confused with the center of lift, which can be signifi cantly different from the CG. As an aircraft is descending, weight is greater than lift. Thrust Thrust is a force that drives an aircraft through the air and can be measured in thrust and/or horsepower. It is a component that is parallel to the center of thrust and overcomes drag providing the aircraft with its forward speed component. Drag Drag is the net aerodynamic force parallel to the relative wind and is generally a sum of two components: induced drag and parasite drag. Induced drag Induced drag is caused from the creation of lift and increases with airspeed. Therefore, if the wing is not producing lift, induced drag is zero. Conversely, induced drag increases with airspeed.

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Parasite drag Parasite drag is all drag not caused from the production of lift. Parasite drag is created by displacement of air by the aircraft, turbulence generated by the airfoil, and the hindrance of airfl ow as it passes over the surface of the aircraft or components. All of these forces create drag not from the production of lift but the movement of an object through an air mass. Parasite drag increases with speed and includes skin friction drag, interference drag, and form drag. • Skin Friction Drag Covering the entire “wetted” surface of the aircraft is a thin layer of air called a boundary layer. The air molecules on the surface have zero velocity in relation to the surface; however, the layer just above moves over the stagnant molecules below because it is pulled along by a third layer close to the free stream of air. The velocities of the layers increase as the distance from the surface increases until free stream velocity is reached, but all are affected by the free stream. The distance (total) between the skin surface and where free stream velocity is reached is called the boundary layer. At subsonic levels the cumulative layers are about the thickness of a playing card, yet their motion sliding over one another creates a drag force. This force retards motion due to the viscosity of the air and is called skin friction drag. Because skin friction drag is related to a large surface area its affect on smaller aircraft is small versus large transport aircraft where skin friction drag may be considerable. • Interference Drag Interference drag is generated by the collision of airstreams creating eddy currents, turbulence, or restrictions to smooth fl ow. For instance, the airfl ow around a fuselage and around the wing meet at some point, usually near the wing’s root. These airfl ows interfere with each other causing a greater 2-4 Figure 2-4. Newton’s First Law of Motion: the Law of Inertia. drag than the individual values. This is often the case when external items are placed on an aircraft. That is, the drag of each item individually, added to that of the aircraft, are less than that of the two items when allowed to interfere with one another. • Form Drag Form drag is the drag created because of the shape of a component or the aircraft. If one were to place a circular disk in an air stream, the pressure on both the top and bottom would be equal. However, the airfl ow starts to break down as the air fl ows around the back of the disk. This creates turbulence and hence a lower pressure results. Because the total pressure is affected by this reduced pressure, it creates a drag. Newer aircraft are generally made with consideration to this by fairing parts along the fuselage (teardrop) so that turbulence and form drag is reduced. Total lift must overcome the total weight of the aircraft, which is comprised of the actual weight and the tail-down force used to control the aircraft’s pitch attitude. Thrust must overcome total drag in order to provide forward speed with which to produce lift. Understanding how the aircraft’s relationship between these elements and the environment provide proper interpretation of the aircraft’s instruments. Newton’s First Law, the Law of Inertia Newton’s First Law of Motion is the Law of Inertia. It states that a body at rest will remain at rest, and a body in motion will remain in motion, at the same speed and in the same direction until affected by an outside force. The force with which a body offers resistance to change is called the force of inertia. Two outside forces are always present on an aircraft in fl ight: gravity and drag. The pilot uses pitch and thrust controls to counter or change these forces to maintain the desired fl ight path. If a pilot reduces power while in straightand- level fl ight, the aircraft will slow due to drag. However, as the aircraft slows there is a reduction of lift, which causes the aircraft to begin a descent due to gravity. [Figure 2-4] Newton’s Second Law, the Law of Momentum Newton’s Second Law of Motion is the Law of Momentum, which states that a body will accelerate in the same direction as the force acting upon that body, and the acceleration will be directly proportional to the net force and inversely proportional to the mass of the body. Acceleration refers either to an increase or decrease in velocity, although deceleration is commonly used to indicate a decrease. This law governs the aircraft’s ability to change fl ight path and speed, which are controlled by attitude (both pitch and bank) and thrust inputs. Speeding up, slowing down, entering climbs or descents, and turning are examples of accelerations that the pilot controls in everyday fl ight. [Figure 2-5] Newton’s Third Law, the Law of Reaction Newton’s Third Law of Motion is the Law of Reaction, which states that for every action there is an equal and opposite reaction. As shown in Figure 2-6, the action of the jet engine’s thrust or the pull of the propeller lead to the reaction of the aircraft’s forward motion. This law is also responsible for a portion of the lift that is produced by a wing, from the downward defl ection of the airfl ow around it. This downward force of the relative wind results in an equal but opposite (upward) lifting force created by the airfl ow over the wing. [Figure 2-6] Atmosphere The atmosphere is the envelope of air which surrounds the Earth. A given volume of dry air contains about 78 percent nitrogen, 21 percent oxygen, and about 1 percent other gases such as argon, carbon dioxide, and others to a lesser degree. Although seemingly light, air does have weight and a one square inch column of the atmosphere at sea level weighs approximately 14.7 pounds. About one-half of the air by weight is within the fi rst 18,000 feet. The remainder of the air is spread over a vertical distance in excess of 1,000 miles. Air density is a result of the relationship between temperature and pressure. Air density is inversely related to temperature and directly related to pressure. For a constant pressure to be 2-5 Figure 2-5. Newton’s Second Law of Motion: the Law of Figure 2-6. Newton’s Third Law of Motion: the Law of Reaction. Momentum. maintained as temperature increases, density must decrease, and vice versa. For a constant temperature to be maintained as pressure increases, density must increase, and vice versa. These relationships provide a basis for understanding instrument indications and aircraft performance. Layers of the Atmosphere There are several layers to the atmosphere with the troposphere being closest to the Earth’s surface extending to about 60,000 feet. Following is the stratosphere, mesosphere, ionosphere, thermosphere, and fi nally the exosphere. The tropopause is the thin layer between the troposphere and the stratosphere. It varies in both thickness and altitude but is generally defi ned where the standard lapse (generally accepted at 2° C per 1,000 feet) decreases signifi cantly (usually down to 1° C or less). International Standard Atmosphere (ISA) The International Civil Aviation Organization (ICAO) established the ICAO Standard Atmosphere as a way of creating an international standard for reference and performance computations. Instrument indications and aircraft performance specifi cations are derived using this standard as a reference. Because the standard atmosphere is a derived set of conditions that rarely exist in reality, pilots need to understand how deviations from the standard affect both instrument indications and aircraft performance. In the standard atmosphere, sea level pressure is 29.92" inches of mercury (Hg) and the temperature is 15° C (59° F). The standard lapse rate for pressure is approximately a 1" Hg decrease per 1,000 feet increase in altitude. The standard lapse rate for temperature is a 2° C (3.6° F) decrease per 1,000 feet increase, up to the top of the stratosphere. Since all aircraft performance is compared and evaluated in the environment of the standard atmosphere, all aircraft performance instrumentation is calibrated for the standard atmosphere. Because the actual operating conditions rarely, if ever, fi t the standard atmosphere, certain corrections must apply to the instrumentation and aircraft performance. For instance, at 10,000 ISA predicts that the air pressure should be 19.92" Hg (29.92" - 10" Hg = 19.92") and the outside temperature at -5°C (15° C - 20° C). If the temperature or the pressure is different than the International Standard Atmosphere (ISA) prediction an adjustment must be made to performance predictions and various instrument indications. Pressure Altitude There are two measurements of the atmosphere that affect performance and instrument calibrations: pressure altitude and density altitude. Pressure altitude is the height above the standard datum pressure (SDP) (29.92" Hg, sea level under ISA) and is used for standardizing altitudes for fl ight levels (FL). Generally, fl ight levels are at or above 18,000 feet (FL 180), providing the pressure is at or above 29.92"Hg. For calculations involving aircraft performance when the altimeter is set for 29.92" Hg, the altitude indicated is the pressure altitude. Density Altitude Density altitude is pressure altitude corrected for nonstandard temperatures, and is used for determining aerodynamic performance in the nonstandard atmosphere. Density altitude increases as the density decreases. Since density varies directly with pressure, and inversely with temperature, a wide range of temperatures may exist with a given pressure altitude, which allows the density to vary. However, a known density occurs for any one temperature and pressure altitude combination. The density of the air has a signifi cant effect on aircraft and engine performance. Regardless of the 2-6 Figure 2-7. Relationship of Lift to Angle of Attack. actual altitude above sea level an aircraft is operating at, its performance will be as though it were operating at an altitude equal to the existing density altitude. If a chart is not available the density altitude can be estimated by adding 120 feet for every degree Celsius above the ISA. For example, at 3,000 feet pressure altitude (PA), the ISA prediction is 9° C (15° C - [lapse rate of 2° C per 1,000 feet x 3 = 6° C]). However, if the actual temperature is 20° C (11° C more than that predicted by ISA) then the difference of 11° C is multiplied by 120 feet equaling 1,320. Adding this fi gure to the original 3,000 feet provides a density altitude of 4,320 feet (3,000 feet + 1,320 feet). Lift Lift always acts in a direction perpendicular to the relative wind and to the lateral axis of the aircraft. The fact that lift is referenced to the wing, not to the Earth’s surface, is the source of many errors in learning fl ight control. Lift is not always “up.” Its direction relative to the Earth’s surface changes as the pilot maneuvers the aircraft. The magnitude of the force of lift is directly proportional to the density of the air, the area of the wings, and the airspeed. It also depends upon the type of wing and the angle of attack. Lift increases with an increase in angle of attack up to the stalling angle, at which point it decreases with any further increase in angle of attack. In conventional aircraft, lift is therefore controlled by varying the angle of attack and speed. Pitch/Power Relationship An examination of Figure 2-7 illustrates the relationship between pitch and power while controlling fl ight path and airspeed. In order to maintain a constant lift, as airspeed is reduced, pitch must be increased. The pilot controls pitch through the elevators, which control the angle of attack. When back pressure is applied on the elevator control, the tail lowers and the nose rises, thus increasing the wing’s angle of attack and lift. Under most conditions the elevator is placing downward pressure on the tail. This pressure requires energy that is taken from aircraft performance (speed). Therefore, when the CG is closer to the aft portion of the aircraft the elevator downward forces are less. This results in less energy used for downward forces, in turn resulting in more energy applied to aircraft performance. Thrust is controlled by using the throttle to establish or maintain desired airspeeds. The most precise method of controlling flight path is to use pitch control while simultaneously using power (thrust) to control airspeed. In order to maintain a constant lift, a change in pitch requires a change in power, and vice versa. If the pilot wants the aircraft to accelerate while maintaining altitude, thrust must be increased to overcome drag. As the aircraft speeds up, lift is increased. To prevent gaining altitude, the pitch angle must be lowered to reduce the angle of attack and maintain altitude. To decelerate while maintaining altitude, thrust must be decreased to less than the value of drag. As the aircraft slows down, lift is reduced. To prevent losing altitude, the pitch angle must be increased in order to increase the angle of attack and maintain altitude. Drag Curves When induced drag and parasite drag are plotted on a graph, the total drag on the aircraft appears in the form of a “drag curve.” Graph A of Figure 2-8 shows a curve based on thrust versus drag, which is primarily used for jet aircraft. Graph B of Figure 2-8 is based on power versus drag, and it is used for propeller-driven aircraft. This chapter focuses on power versus drag charts for propeller-driven aircraft. Understanding the drag curve can provide valuable insight into the various performance parameters and limitations of the aircraft. Because power must equal drag to maintain a steady airspeed, the curve can be either a drag curve or a power required curve. The power required curve represents the amount of power needed to overcome drag in order to maintain a steady speed in level fl ight. The propellers used on most reciprocating engines achieve peak propeller effi ciencies in the range of 80 to 88 percent. As airspeed increases, the propeller effi ciency increases until it reaches its maximum. Any airspeed above this maximum point causes a reduction in propeller effi ciency. An engine that produces 160 horsepower will have only about 80 percent of that power converted into available horsepower, 2-7 Figure 2-8. Thrust and Power Required Curves. Figure 2-9. Regions of Command. approximately 128 horsepower. The remainder is lost energy. This is the reason the thrust and power available curves change with speed. Regions of Command The drag curve also illustrates the two regions of command: the region of normal command, and the region of reversed command. The term “region of command” refers to the relationship between speed and the power required to maintain or change that speed. “Command” refers to the input the pilot must give in terms of power or thrust to maintain a new speed once reached. The “region of normal command” occurs where power must be added to increase speed. This region exists at speeds higher than the minimum drag point primarily as a result of parasite drag. The “region of reversed command” occurs where additional power is needed to maintain a slower airspeed. This region exists at speeds slower than the minimum drag point (L/DMAX on the thrust required curve, Figure 2-8) and is primarily due to induced drag. Figure 2-9 shows how one power setting can yield two speeds, points 1 and 2. This is because at point 1 there is high induced drag and low parasite drag, while at point 2 there is high parasite drag and low induced drag. Control Characteristics Most fl ying is conducted in the region of normal command: for example, cruise, climb, and maneuvers. The region of reversed command may be encountered in the slow-speed phases of fl ight during takeoff and landing; however, for most general aviation aircraft, this region is very small and is below normal approach speeds. Flight in the region of normal command is characterized by a relatively strong tendency of the aircraft to maintain the trim speed. Flight in the region of reversed command is characterized by a relatively weak tendency of the aircraft to maintain the trim speed. In fact, it is likely the aircraft exhibits no inherent tendency to maintain the trim speed in this area. For this reason, the pilot must give particular attention to precise control of airspeed when operating in the slow-speed phases of the region of reversed command. Operation in the region of reversed command does not imply that great control diffi culty and dangerous conditions exist. However, it does amplify errors of basic fl ying technique— making proper fl ying technique and precise control of the aircraft very important. Speed Stability Normal Command The characteristics of fl ight in the region of normal command are illustrated at point A on the curve in Figure 2-10. If the aircraft is established in steady, level fl ight at point A, lift is equal to weight, and the power available is set equal to the power required. If the airspeed is increased with no changes 2-8 Figure 2-10. Region of Speed Stability. to the power setting, a power defi ciency exists. The aircraft has a natural tendency to return to the initial speed to balance power and drag. If the airspeed is reduced with no changes to the power setting, an excess of power exists. The aircraft has a natural tendency to speed up to regain the balance between power and drag. Keeping the aircraft in proper trim enhances this natural tendency. The static longitudinal stability of the aircraft tends to return the aircraft to the original trimmed condition. An aircraft fl ying in steady, level fl ight at point C is in equilibrium. [Figure 2-10] If the speed were increased or decreased slightly, the aircraft would tend to remain at that speed. This is because the curve is relatively fl at and a slight change in speed does not produce any signifi cant excess or defi ciency in power. It has the characteristic of neutral stability, i.e., the aircraft’s tendency is to remain at the new speed. Reversed Command The characteristics of fl ight in the region of reversed command are illustrated at point B on the curve in Figure 2-10. If the aircraft is established in steady, level fl ight at point B, lift is equal to weight, and the power available is set equal to the power required. When the airspeed is increased greater than point B, an excess of power exists. This causes the aircraft to accelerate to an even higher speed. When the aircraft is slowed to some airspeed lower than point B, a defi ciency of power exists. The natural tendency of the aircraft is to continue to slow to an even lower airspeed.

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This tendency toward instability happens because the variation of excess power to either side of point B magnifi es the original change in speed. Although the static longitudinal stability of the aircraft tries to maintain the original trimmed condition, this instability is more of an infl uence because of the increased induced drag due to the higher angles of attack in slow-speed fl ight. Trim The term trim refers to employing adjustable aerodynamic devices on the aircraft to adjust forces so the pilot does not have to manually hold pressure on the controls. One means is to employ trim tabs. A trim tab is a small, adjustable hinged surface, located on the trailing edge of the elevator, aileron, or rudder control surfaces. (Some aircraft use adjustable stabilizers instead of trim tabs for pitch trim.) Trimming is accomplished by defl ecting the tab in the direction opposite to that in which the primary control surface must be held. The force of the airfl ow striking the tab causes the main control surface to be defl ected to a position that corrects the unbalanced condition of the aircraft. Because the trim tabs use airfl ow to function, trim is a function of speed. Any change in speed results in the need to re-trim the aircraft. An aircraft properly trimmed in pitch seeks to return to the original speed before the change. It is very important for instrument pilots to keep the aircraft in constant trim. This reduces the pilot’s workload signifi cantly, allowing attention to other duties without compromising aircraft control. Slow-Speed Flight Anytime an aircraft is fl ying near the stalling speed or the region of reversed command, such as in fi nal approach for a normal landing, the initial part of a go around, or maneuvering in slow fl ight, it is operating in what is called slow-speed fl ight. If the aircraft weighs 4,000 pounds, the lift produced by the aircraft must be 4,000 pounds. When lift is less than 4,000 pounds, the aircraft is no longer able to sustain level fl ight, and consequently descends. During intentional descents, this is an important factor and is used in the total control of the aircraft. However, because lift is required during low speed fl ight and is characterized by high angles of attack, fl aps or other high lift devices are needed to either change the camber of the airfoil, or delay the boundary level separation. Plain and split fl aps [Figure 2-11] are most commonly used to change the camber of an airfoil. It should be noted that with the application of fl aps, the aircraft will stall at a lower angle of attack. The basic wing stalls at 18° without fl aps but with the application of the fl aps extended (to CL-MAX position) the new angle of attack at which point the aircraft will stall is 15°. However, the value of lift (fl aps extended to the CL-MAX position) produces more lift than lift at 18° on the basic wing. Delaying the boundary layer separation is another way to increase CL-MAX. Several methods are employed (such as suction and use of a blowing boundary layer control), but the 2-9 Figure 2-11. Various Types of Flaps. Figure 2-12. Vortex Generators. If allowed to slow several knots, the airplane could enter the region of reversed command. At this point, the airplane could develop an unsafe sink rate and continue to lose speed unless the pilot takes a prompt corrective action. Proper pitch and power coordination is critical in this region due to speed instability and the tendency of increased divergence from the desired speed. Large Airplanes Pilots of larger airplanes with higher stall speeds may fi nd the speed they maintain on the instrument approach is near 1.3 VSO, putting them near point C [Figure 2-10] the entire time the airplane is on the fi nal approach segment. In this case, precise speed control is necessary throughout the approach. It may be necessary to temporarily select excessive, or defi cient thrust in relation to the target thrust setting in order to quickly correct for airspeed deviations. most common device used on general aviation light aircraft is the vortex generator. Small strips of metal placed along the wing (usually in front of the control surfaces) create turbulence. The turbulence in turn mixes high energy air from outside the boundary layer with boundary layer air. The effect is similar to other boundary layer devices. [Figure 2-12] Small Airplanes Most small airplanes maintain a speed well in excess of 1.3 times VSO on an instrument approach. An airplane with a stall speed of 50 knots (VSO) has a normal approach speed of 65 knots. However, this same airplane may maintain 90 knots (1.8 VSO) while on the fi nal segment of an instrument approach. The landing gear will most likely be extended at the beginning of the descent to the minimum descent altitude, or upon intercepting the glide slope of the instrument landing system. The pilot may also select an intermediate fl ap setting for this phase of the approach. The airplane at this speed has good positive speed stability, as represented by point A on Figure 2-10. Flying in this regime permits the pilot to make slight pitch changes without changing power settings, and accept minor speed changes knowing that when the pitch is returned to the initial setting, the speed returns to the original setting. This reduces the pilot’s workload. Aircraft are usually slowed to a normal landing speed when on the fi nal approach just prior to landing. When slowed to 65 knots, (1.3 VSO), the airplane will be close to point C. [Figure 2-10] At this point, precise control of the pitch and power becomes more crucial for maintaining the correct speed. Pitch and power coordination is necessary because the speed stability is relatively neutral since the speed tends to remain at the new value and not return to the original setting. In addition to the need for more precise airspeed control, the pilot normally changes the aircraft’s confi guration by extending landing fl aps. This confi guration change means the pilot must be alert to unwanted pitch changes at a low altitude. 2-10 Figure 2-13. Forces In a Turn. Turns Like any moving object, an aircraft requires a sideward force to make it turn. In a normal turn, this force is supplied by banking the aircraft in order to exert lift inward, as well as upward. The force of lift is separated into two components at right angles to each other. [Figure 2-13] The upward acting lift together with the opposing weight becomes the vertical lift component. The horizontally acting lift and its opposing centrifugal force are the horizontal lift component, or centripetal force. This horizontal lift component is the sideward force that causes an aircraft to turn. The equal and opposite reaction to this sideward force is centrifugal force, which is merely an apparent force as a result of inertia. The relationship between the aircraft’s speed and bank angle to the rate and radius of turns is important for instrument pilots to understand. The pilot can use this knowledge to properly estimate bank angles needed for certain rates of turn, or to determine how much to lead when intercepting a course. Rate of Turn The rate of turn, normally measured in degrees per second, is based upon a set bank angle at a set speed. If either one of these elements changes, the rate of turn changes. If the aircraft increases its speed without changing the bank angle, the rate of turn decreases. Likewise, if the speed decreases without changing the bank angle, the rate of turn increases. Changing the bank angle without changing speed also causes the rate of turn to change. Increasing the bank angle without changing speed increases the rate of turn, while decreasing the bank angle reduces the rate of turn. For example, a pilot is on an instrument approach at 1.3 VSO, a speed near L/DMAX, and knows that a certain power setting maintains that speed. The airplane slows several knots below the desired speed because of a slight reduction in the power setting. The pilot increases the power slightly, and the airplane begins to accelerate, but at a slow rate. Because the airplane is still in the “fl at part” of the drag curve, this slight increase in power will not cause a rapid return to the desired speed. The pilot may need to increase the power higher than normally needed to maintain the new speed, allow the airplane to accelerate, then reduce the power to the setting that maintains the desired speed. Climbs The ability for an aircraft to climb depends upon an excess power or thrust over what it takes to maintain equilibrium. Excess power is the available power over and above that required to maintain horizontal fl ight at a given speed. Although the terms power and thrust are sometimes used interchangeably (erroneously implying they are synonymous), distinguishing between the two is important when considering climb performance. Work is the product of a force moving through a distance and is usually independent of time. Power implies work rate or units of work per unit of time, and as such is a function of the speed at which the force is developed. Thrust, also a function of work, means the force which imparts a change in the velocity of a mass. During take off, the aircraft does not stall even though it may be in a climb near the stall speed. The reason is that excess power (used to produce thrust) is used during this fl ight regime. Therefore, it is important if an engine fails after take off, to compensate the loss of thrust with pitch and airspeed. For a given weight of the aircraft, the angle of climb depends on the difference between thrust and drag, or the excess thrust. When the excess thrust is zero, the inclination of the fl ight path is zero, and the aircraft is in steady, level fl ight. When thrust is greater than drag, the excess thrust allows a climb angle depending on the amount of excess thrust. When thrust is less than drag, the defi ciency of thrust induces an angle of descent. Acceleration in Cruise Flight Aircraft accelerate in level fl ight because of an excess of power over what is required to maintain a steady speed. This is the same excess power used to climb. Upon reaching the desired altitude with pitch being lowered to maintain that altitude, the excess power now accelerates the aircraft to its cruise speed. However, reducing power too soon after level off results in a longer period of time to accelerate. 2-11 Figure 2-14. Turns. The standard rate of turn, 3° per second, is used as the main reference for bank angle. Therefore, the pilot must understand how the angle of bank varies with speed changes, such as slowing down for holding or an instrument approach. Figure 2-14 shows the turn relationship with reference to a constant bank angle or a constant airspeed, and the effects on rate of turn and radius of turn. A rule of thumb for determining the standard rate turn is to divide the airspeed by ten and add 7. An aircraft with an airspeed of 90 knots takes a bank angle of 16° to maintain a standard rate turn (90 divided by 10 plus 7 equals 16°). Radius of Turn The radius of turn varies with changes in either speed or bank. If the speed is increased without changing the bank angle, the radius of turn increases, and vice versa. If the speed is constant, increasing the bank angle reduces the radius of turn, while decreasing the bank angle increases the radius of turn. This means that intercepting a course at a higher speed requires more distance, and therefore, requires a longer lead. If the speed is slowed considerably in preparation for holding or an approach, a shorter lead is needed than that required for cruise fl ight. Coordination of Rudder and Aileron Controls Any time ailerons are used, adverse yaw is produced. Adverse yaw is caused when the ailerons are defl ected as a roll motion (as in turn) is initiated. In a right turn, the right aileron is defl ected downward while the left is defl ected upward. Lift is increased on the left side and reduced on the right, resulting in a bank to the right. However, as a result of producing lift on the left, induced drag is also increased on the left side. The drag causes the left wing to slow down, in turn causing the nose of the aircraft to initially move (left) in the direction opposite of the turn. Correcting for this yaw with rudder, when entering and exiting turns, is necessary for precise control of the airplane when fl ying on instruments. The pilot can tell if the turn is coordinated by checking the ball in the turn-andslip indicator or the turn coordinator. [Figure 2-15] As the aircraft banks to enter a turn, a portion of the wing’s vertical lift becomes the horizontal component; therefore, without an increase in back pressure, the aircraft loses altitude during the turn. The loss of vertical lift can be offset by increasing the pitch in one-half bar width increments. Trim may be used to relieve the control pressures; however, if used, it has to be removed once the turn is complete. In a slipping turn, the aircraft is not turning at the rate appropriate to the bank being used, and the aircraft falls to the inside of the turn. The aircraft is banked too much for the rate of turn, so the horizontal lift component is greater than the centrifugal force. A skidding turn results from excess of centrifugal force over the horizontal lift component, pulling the aircraft toward the outside of the turn. The rate of turn is too great for the angle of bank, so the horizontal lift component is less than the centrifugal force. The ball instrument indicates the quality of the turn, and should be centered when the wings are banked. If the ball is off of center on the side toward the turn, the aircraft is slipping and rudder pressure should be added on that side to increase the rate of turn or the bank angle should be reduced. If the ball is off of center on the side away from the turn, the aircraft is skidding and rudder pressure toward the turn should be relaxed or the bank angle should be increased. If the aircraft is properly rigged, the ball should be in the center when the wings are level; use rudder and/or aileron trim if available. The increase in induced drag (caused by the increase in angle of attack necessary to maintain altitude) results in a minor loss of airspeed if the power setting is not changed. Load Factor Any force applied to an aircraft to defl ect its fl ight from a straight line produces a stress on its structure; the amount of this force is termed load factor. A load factor is the ratio of 2-12 Figure 2-15. Adverse Yaw. the aerodynamic force on the aircraft to the gross weight of the aircraft (e.g., lift/weight). For example, a load factor of 3 means the total load on an aircraft’s structure is three times its gross weight. When designing an aircraft, it is necessary to determine the highest load factors that can be expected in normal operation under various operational situations. These “highest” load factors are called “limit load factors.” Aircraft are placed in various categories, i.e., normal, utility, and acrobatic, depending upon the load factors they are designed to take. For reasons of safety, the aircraft must be designed to withstand certain maximum load factors without any structural damage.

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The specifi ed load may be expected in terms of aerodynamic forces, as in turns. In level fl ight in undisturbed air, the wings are supporting not only the weight of the aircraft, but centrifugal force as well. As the bank steepens, the horizontal lift component increases, centrifugal force increases, and the load factor increases. If the load factor becomes so great that an increase in angle of attack cannot provide enough lift to support the load, the wing stalls. Since the stalling speed increases directly with the square root of the load factor, the pilot should be aware of the fl ight conditions during which the load factor can become critical. Steep turns at slow airspeed, structural ice accumulation, and vertical gusts in turbulent air can increase the load factor to a critical level. Icing One of the greatest hazards to fl ight is aircraft icing. The instrument pilot must be aware of the conditions conducive to aircraft icing. These conditions include the types of icing, the effects of icing on aircraft control and performance, effects of icing on aircraft systems, and the use and limitations of aircraft deice and anti-ice equipment. Coping with the hazards of icing begins with prefl ight planning to determine where icing may occur during a fl ight and ensuring the aircraft is 2-13 Figure 2-16. Clear Ice. free of ice and frost prior to takeoff. This attention to detail extends to managing deice and anti-ice systems properly during the fl ight, because weather conditions may change rapidly, and the pilot must be able to recognize when a change of fl ight plan is required. Types of Icing Structural Icing Structural icing refers to the accumulation of ice on the exterior of the aircraft. Ice forms on aircraft structures and surfaces when super-cooled droplets impinge on them and freeze. Small and/or narrow objects are the best collectors of droplets and ice up most rapidly. This is why a small protuberance within sight of the pilot can be used as an “ice evidence probe.” It is generally one of the fi rst parts of the airplane on which an appreciable amount of ice forms. An aircraft’s tailplane is a better collector than its wings, because the tailplane presents a thinner surface to the airstream. Induction Icing Ice in the induction system can reduce the amount of air available for combustion. The most common example of reciprocating engine induction icing is carburetor ice. Most pilots are familiar with this phenomenon, which occurs when moist air passes through a carburetor venturi and is cooled. As a result of this process, ice may form on the venturi walls and throttle plate, restricting airfl ow to the engine. This may occur at temperatures between 20° F (-7° C) and 70° F (21° C). The problem is remedied by applying carburetor heat, which uses the engine’s own exhaust as a heat source to melt the ice or prevent its formation. On the other hand, fuel-injected aircraft engines usually are less vulnerable to icing but still can be affected if the engine’s air source becomes blocked with ice. Manufacturers provide an alternate air source that may be selected in case the normal system malfunctions. In turbojet aircraft, air that is drawn into the engines creates an area of reduced pressure at the inlet, which lowers the temperature below that of the surrounding air. In marginal icing conditions (i.e., conditions where icing is possible), this reduction in temperature may be suffi cient to cause ice to form on the engine inlet, disrupting the airfl ow into the engine. Another hazard occurs when ice breaks off and is ingested into a running engine, which can cause damage to fan blades, engine compressor stall, or combustor fl ameout. When anti-icing systems are used, runback water also can refreeze on unprotected surfaces of the inlet and, if excessive, reduce airfl ow into the engine or distort the airfl ow pattern in such a manner as to cause compressor or fan blades to vibrate, possibly damaging the engine. Another problem in turbine engines is the icing of engine probes used to set power levels (for example, engine inlet temperature or engine pressure ratio (EPR) probes), which can lead to erroneous readings of engine instrumentation operational diffi culties or total power loss. The type of ice that forms can be classifi ed as clear, rime, or mixed, based on the structure and appearance of the ice. The type of ice that forms varies depending on the atmospheric and fl ight conditions in which it forms. Signifi cant structural icing on an aircraft can cause serious aircraft control and performance problems. Clear Ice A glossy, transparent ice formed by the relatively slow freezing of super cooled water is referred to as clear ice. [Figure 2-16] The terms “clear” and “glaze” have been used for essentially the same type of ice accretion. This type of ice is denser, harder, and sometimes more transparent than rime ice. With larger accretions, clear ice may form “horns.” [Figure 2-17] Temperatures close to the freezing point, large amounts of liquid water, high aircraft velocities, and large droplets are conducive to the formation of clear ice. Rime Ice A rough, milky, opaque ice formed by the instantaneous or very rapid freezing of super cooled droplets as they strike the aircraft is known as rime ice. [Figure 2-18] The rapid freezing results in the formation of air pockets in the ice, giving it an opaque appearance and making it porous and brittle. For larger accretions, rime ice may form a streamlined extension of the wing. Low temperatures, lesser amounts of liquid water, low velocities, and small droplets are conducive to the formation of rime ice. 2-14 Figure 2-19. Aerodynamic Effects of Icing. Figure 2-17. Clear Ice Buildup. Figure 2-18. Rime Ice. Mixed Ice Mixed ice is a combination of clear and rime ice formed on the same surface. It is the shape and roughness of the ice that is most important from an aerodynamic point of view. General Effects of Icing on Airfoils The most hazardous aspect of structural icing is its aerodynamic effects. [Figure 2-19] Ice alters the shape of an airfoil, reducing the maximum coeffi cient of lift and angle of attack at which the aircraft stalls. Note that at very low angles of attack, there may be little or no effect of the ice on the coeffi cient of lift. Therefore, when cruising at a low angle of attack, ice on the wing may have little effect on the lift. However, note that the ice signifi cantly reduces the CL-MAX, and the angle of attack at which it occurs (the stall angle) is much lower. Thus, when slowing down and increasing the angle of attack for approach, the pilot may fi nd that ice on the wing, which had little effect on lift in cruise now, causes stall to occur at a lower angle of attack and higher speed. Even a thin layer of ice at the leading edge of a wing, especially if it is rough, can have a signifi cant effect in increasing stall speed. For large ice shapes, especially those with horns, the lift may also be reduced at a lower angle of attack. The accumulation of ice affects the coeffi cient of drag of the airfoil. [Figure 2-19] Note that the effect is signifi cant even at very small angles of attack. A signifi cant reduction in CL-MAX and a reduction in the angle of attack where stall occurs can result from a relatively small ice accretion. A reduction of CL-MAX by 30 percent is not unusual, and a large horn ice accretion can result in reductions of 40 percent to 50 percent. Drag tends to increase steadily as ice accretes. An airfoil drag increase of 100 percent is not unusual, and for large horn ice accretions, the increase can be 200 percent or even higher. 2-15 Figure 2-20. Effect of Ice and Frost on Lift. Figure 2-21. Downward Force on the Tailplane. Figure 2-22. Ice on the Tailplane. Ice on an airfoil can have other effects not depicted in these curves. Even before airfoil stall, there can be changes in the pressure over the airfoil that may affect a control surface at the trailing edge. Furthermore, on takeoff, approach, and landing, the wings of many aircraft are multi-element airfoils with three or more elements. Ice may affect the different elements in different ways. Ice may also affect the way in which the air streams interact over the elements. Ice can partially block or limit control surfaces, which limits or makes control movements ineffective. Also, if the extra weight caused by ice accumulation is too great, the aircraft may not be able to become airborne and, if in fl ight, the aircraft may not be able to maintain altitude. Therefore any accumulation of ice or frost should be removed before attempting fl ight. Another hazard of structural icing is the possible uncommanded and uncontrolled roll phenomenon, referred to as roll upset, associated with severe in-fl ight icing. Pilots fl ying aircraft certifi cated for fl ight in known icing conditions should be aware that severe icing is a condition outside of the aircraft’s certifi cation icing envelope. Roll upset may be caused by airfl ow separation (aerodynamic stall), which induces selfdefl ection of the ailerons and loss of or degraded roll handling characteristics [Figure 2-20]. These phenomena can result from severe icing conditions without the usual symptoms of ice accumulation or a perceived aerodynamic stall. Most aircraft have a nose-down pitching moment from the wings because the CG is ahead of the CP. It is the role of the tailplane to counteract this moment by providing a downward force. [Figure 2-21] The result of this confi guration is that actions which move the wing away from stall, such as deployment of fl aps or increasing speed, may increase the negative angle of attack of the tail. With ice on the tailplane, it may stall after full or partial deployment of fl aps. [Figure 2-22] Since the tailplane is ordinarily thinner than the wing, it is a more effi cient collector of ice. On most aircraft the tailplane is not visible to the pilot, who therefore cannot observe how well it has been cleared of ice by any deicing system. Thus, it is important that the pilot be alert to the possibility of tailplane stall, particularly on approach and landing. Piper PA-34-200T (Des Moines, Iowa) The pilot of this fl ight, which took place on January 9, 1996, said that upon crossing the runway threshold and lowering the fl aps 25°, “the airplane pitched down.” The pilot “immediately released the fl aps and added power, but the airplane was basically uncontrollable at this point.” The pilot reduced power and lowered the fl aps before striking the runway on its centerline and sliding 1,000 feet before 2-16 coming to a stop. The accident resulted in serious injury to the pilot, the sole occupant. Examination of the wreckage revealed heavy impact damage to the airplane’s forward fuselage, engines, and wings. Approximately one-half inch of rime ice was observed adhering to the leading edges of the left and right horizontal stabilizers and along the leading edge of the vertical stabilizer. The National Transportation Safety Board (NTSB) determined the probable cause of the accident was the pilot’s failure to use the airplane’s deicing system, which resulted in an accumulation of empennage ice and a tailplane stall. Factors relating to this accident were the icing conditions and the pilot’s intentional fl ight into those known conditions. Tailplane Stall Symptoms

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Any of the following symptoms, occurring singly or in combination, may be a warning of tailplane icing: • Elevator control pulsing, oscillations, or vibrations; • Abnormal nose-down trim change; • Any other unusual or abnormal pitch anomalies (possibly resulting in pilot induced oscillations); • Reduction or loss of elevator effectiveness; • Sudden change in elevator force (control would move nose-down if unrestrained); and • Sudden uncommanded nose-down pitch. If any of the above symptoms occur, the pilot should: • Immediately retract the fl aps to the previous setting and apply appropriate nose-up elevator pressure; • Increase airspeed appropriately for the reduced fl ap extension setting; • Apply sufficient power for aircraft configuration and conditions. (High engine power settings may adversely impact response to tailplane stall conditions at high airspeed in some aircraft designs. Observe the manufacturer’s recommendations regarding power settings.); • Make nose-down pitch changes slowly, even in gusting conditions, if circumstances allow; and • If a pneumatic deicing system is used, operate the system several times in an attempt to clear the tailplane of ice. Once a tailplane stall is encountered, the stall condition tends to worsen with increased airspeed and possibly may worsen with increased power settings at the same flap setting. Airspeed, at any fl ap setting, in excess of the airplane manufacturer’s recommendations, accompanied by uncleared ice contaminating the tailplane, may result in a tailplane stall and uncommanded pitch down from which recovery may not be possible. A tailplane stall may occur at speeds less than the maximum fl ap extended speed (VFE). Propeller Icing Ice buildup on propeller blades reduces thrust for the same aerodynamic reasons that wings tend to lose lift and increase drag when ice accumulates on them. The greatest quantity of ice normally collects on the spinner and inner radius of the propeller. Propeller areas on which ice may accumulate and be ingested into the engine normally are anti-iced rather than deiced to reduce the probability of ice being shed into the engine. Effects of Icing on Critical Aircraft Systems In addition to the hazards of structural and induction icing, the pilot must be aware of other aircraft systems susceptible to icing. The effects of icing do not produce the performance loss of structural icing or the power loss of induction icing but can present serious problems to the instrument pilot. Examples of such systems are flight instruments, stall warning systems, and windshields. Flight Instruments Various aircraft instruments including the airspeed indicator, altimeter, and rate-of-climb indicator utilize pressures sensed by pitot tubes and static ports for normal operation. When covered by ice these instruments display incorrect information thereby presenting serious hazard to instrument flight. Detailed information on the operation of these instruments and the specifi c effects of icing is presented in Chapter 3, Flight Instruments. Stall Warning Systems Stall warning systems provide essential information to pilots. These systems range from a sophisticated stall warning vane to a simple stall warning switch. Icing affects these systems in several ways resulting in possible loss of stall warning to the pilot. The loss of these systems can exacerbate an already hazardous situation. Even when an aircraft’s stall warning system remains operational during icing conditions, it may be ineffective because the wing stalls at a lower angle of attack due to ice on the airfoil. Windshields Accumulation of ice on fl ight deck windows can severely restrict the pilot’s visibility outside of the aircraft. Aircraft equipped for fl ight into known icing conditions typically have some form of windshield anti-icing to enable the pilot to see 2-17 outside the aircraft in case icing is encountered in fl ight. One system consists of an electrically heated plate installed onto the airplane’s windshield to give the pilot a narrow band of clear visibility. Another system uses a bar at the lower end of the windshield to spray deicing fl uid onto it and prevent ice from forming. On high performance aircraft that require complex windshields to protect against bird strikes and withstand pressurization loads, the heating element often is a layer of conductive fi lm or thin wire strands through which electric current is run to heat the windshield and prevent ice from forming. Antenna Icing Because of their small size and shape, antennas that do not lay fl ush with the aircraft’s skin tend to accumulate ice rapidly. Furthermore, they often are devoid of internal anti-icing or deicing capability for protection. During fl ight in icing conditions, ice accumulations on an antenna may cause it to begin to vibrate or cause radio signals to become distorted and it may cause damage to the antenna. If a frozen antenna breaks off, it can damage other areas of the aircraft in addition to causing a communication or navigation system failure. Summary Ice-contaminated aircraft have been involved in many accidents. Takeoff accidents have usually been due to failure to deice or anti-ice critical surfaces properly on the ground. Proper deicing and anti-icing procedures are addressed in two other pilot guides, Advisory Circular (AC) 120-58, Pilot Guide: Large Aircraft Ground Deicing and AC 135-17, Pilot Guide: Small Aircraft Ground Deicing. The pilot of an aircraft, which is not certifi cated or equipped for fl ight in icing conditions, should avoid all icing conditions. The aforementioned guides provide direction on how to do this, and on how to exit icing conditions promptly and safely should they be inadvertently encountered. The pilot of an aircraft, which is certifi cated for fl ight in icing conditions can safely operate in the conditions for which the aircraft was evaluated during the certifi cation process but should never become complacent about icing. Even short encounters with small amounts of rough icing can be very hazardous. The pilot should be familiar with all information in the Aircraft Flight Manual (AFM) or Pilot’s Operating Handbook (POH) concerning flight in icing conditions and follow it carefully. Of particular importance are proper operation of ice protection systems and any airspeed minimums to be observed during or after fl ight in icing conditions. There are some icing conditions for which no aircraft is evaluated in the certifi cation process, such as super-cooled large drops (SLD). These subfreezing water droplets, with diameters greater than 50 microns, occur within or below clouds and sustained fl ight in these conditions can be very hazardous. The pilot should be familiar with any information in the AFM or POH relating to these conditions, including aircraft-specifi c cues for recognizing these hazardous conditions within clouds. The information in this chapter is an overview of the hazards of aircraft icing. For more detailed information refer to AC 91-74, Pilot Guide: Flight in Icing Conditions, AC 91-51A, Effect of Icing on Aircraft Control and Airplane Deice and Anti-Ice Systems, AC 20-73A, Aircraft Ice Protection and AC 23.143-1, Ice Contaminated Tailplane Stall (ICTS). 2-18 3-1 Introduction Aircraft became a practical means of transportation when accurate fl ight instruments freed the pilot from the necessity of maintaining visual contact with the ground. Flight instruments are crucial to conducting safe fl ight operations and it is important that the pilot have a basic understanding of their operation. The basic fl ight instruments required for operation under visual fl ight rules (VFR) are airspeed indicator (ASI), altimeter, and magnetic direction indicator. In addition to these, operation under instrument fl ight rules (IFR) requires a gyroscopic rate-of-turn indicator, slip-skid indicator, sensitive altimeter adjustable for barometric pressure, clock displaying hours, minutes, and seconds with a sweep-second pointer or digital presentation, gyroscopic pitch-and-bank indicator (artifi cial horizon), and gyroscopic direction indicator (directional gyro or equivalent). Flight Instruments Chapter 3 3-2 Figure 3-1. A Typical Electrically Heated Pitot-Static Head. Aircraft that are fl own in instrument meteorological conditions (IMC) are equipped with instruments that provide attitude and direction reference, as well as navigation instruments that allow precision fl ight from takeoff to landing with limited or no outside visual reference.

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