CESSNA MODEL 208B G1000

Total Distance Over 50 Foot Obstacle . . . . . . . . . . . . . . . . 1795 Feet STALL SPEED (KCAS): Flaps Up, Idle Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 78 Knots Flaps Full, Idle Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 61 Knots MAXIMUM WEIGHT: Ramp . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8785 Pounds Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8750 Pounds Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8500 Pounds STANDARD EMPTY WEIGHT . . . . . . . . . . . . . . . . . . . . . .4511 Pounds Maximum USEFUL LOAD . . . . . . . . . . . . . . . . . . . . . . . . 4274 Pounds *Speeds are based on mid-cruise weight. (Continued Next Page) Revision 1 iv CESSNA INTRODUCTION MODEL 208B G1000 U.S. PERFORMANCE - SPECIFICATIONS PASSENGER VERSION (Continued) WING LOADING . . . . . . . . . . . . . . . . . . . . . . 31.3 Pounds/Square Foot POWER LOADING . . . . . . . . . . . . . . . 13.0 Pounds/Shaft Horsepower FUEL CAPACITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 335.6 Gallons OIL CAPACITY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 Quarts ENGINE: Pratt & Whitney Canada . . . . . . . . . . . . . . . . . . . PT6A-114A Free Turbine Flat Rated at 675 Shaft Horsepower PROPELLER: McCauley 3-bladed, Constant Speed, Full Feathering, Reversible. Diameter . . . . . . . . . . . . . . . . . 106 Inches NOTE The above performance figures are based on indicated weights, standard atmospheric conditions, level, hard- surfaced dry runways and no wind. They are calculated values derived from flight tests conducted by Cessna Aircraft Company under carefully documented conditions and will vary with individual airplanes and numerous factors affecting flight performance. Performance for other operational conditions can be derived by reference to operational data in other sections of this POH/AFM. Revision 1 v/vi CESSNA INTRODUCTION MODEL 208B G1000 U.S. Cessna Aircraft Company Model 208B G1000 This manual incorporates information issued in the Pilot's Operating Handbook and FAA approved Airplane Flight Manual at Revision 1, Dated 5 June 2008 (Part Number 208BPHBUS-01). COPYRIGHT © 2008 CESSNA AIRCRAFT COMPANY WICHITA, KANSAS, USA 208BIMBUS-01 vii/viii CESSNA INTRODUCTION MODEL 208B G1000 U.S. TABLE OF CONTENTS SECTION GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 EMERGENCY PROCEDURES . . . . . . . . . . . . . . . . . .3 NORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . .4 PERFORMANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 WEIGHT AND BALANCE/EQUIPMENT LIST . . . . . . .6 AIRPLANE AND SYSTEM DESCRIPTION . . . . . . . . .7 HANDLING, SERVICE AND MAINTENANCE . . . . . . .8 SUPPLEMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . .9 Revision 1 ix INTRODUCTION CESSNA MODEL 208B G1000 U.S. WARNINGS, CAUTIONS, AND NOTES Throughout the text, warnings, cautions, and notes pertaining to airplane handling and operations are utilized. These adjuncts to the text are used to highlight or emphasize important points. WARNING Operating procedures, techniques, etc., which can result in personal injury or loss of life if not carefully followed. CAUTION Operating procedures, techniques, etc., which can result in damage to equipment if not carefully followed. NOTE An operating procedure, technique, etc., which is considered essential to emphasize. Revision 1 x CESSNA INTRODUCTION MODEL 208B G1000 U.S. TABLE OF CONTENTS SECTION GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 EMERGENCY PROCEDURES . . . . . . . . . . . . . . . . . .3 NORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . .4 PERFORMANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 WEIGHT AND BALANCE/EQUIPMENT LIST . . . . . . .6 AIRPLANE AND SYSTEM DESCRIPTION . . . . . . . . .7 HANDLING, SERVICE AND MAINTENANCE . . . . . . .8 SUPPLEMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . .9 208BPHBUS-00 xiii/xiv CESSNA SECTION 1 MODEL 208B G1000 GENERAL U.S. GENERAL TABLE OF CONTENTS Page Three View. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-3 Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-5 Descriptive Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-6 Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-6 Propeller . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-6 Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-7 Oil . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-8 Maximum Certificated Weights . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-9 Cabin and Entry Door Dimensions . . . . . . . . . . . . . . . . . . . . . . . . 1-9 Baggage/Cargo Compartment and Cargo Door Entry Dimensions . . . . . . . . . . . . . . . . . . . . . 1-9 Specific Loadings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-9 Symbols, Abbreviations and Terminology . . . . . . . . . . . . . . . . . . . . 1-10 General Airspeed Terminology and Symbols. . . . . . . . . . . . . . . . . . 1-10 Engine Power Terminology . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-11 Airplane Performance and Flight Planning Terminology . . . . . . . 1-13 Weight and Balance Terminology . . . . . . . . . . . . . . . . . . . . . . . . 1-13 Autopilot/Flight Director and TFS Terminology . . . . . . . . . . . . . . 1-15 Warning, Cautions, and Notes . . . . . . . . . . . . . . . . . . . . . . . . . . 1-16 Metric/Imperial/U.S. Conversion Charts. . . . . . . . . . . . . . . . . . . . . . 1-16 Weight Conversions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-17 Length Conversions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-19 Distance Conversions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-23 Volume Conversions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-24 Temperature Conversions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-27 Pressure Conversions. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-28 1-1/1-2 208BPHBUS-00 CESSNA SECTION 1 MODEL 208B G1000 GENERAL U.S. Figure 1-1 (Sheet 1 of 2) 1-3 208BPHBUS-00 SECTION 1 CESSNA GENERAL MODEL 208B G1000 U.S. Figure 1-1 (Sheet 2) NOTE 1. Dimensions shown are based on standard empty weight and proper inflation of nose and main gear tires. 2. Wing span dimension includes strobe lights. 3. Maximum height shown with nose gear depressed as far as possible. 4. Wheel base length is 13’-3 1/2”. 5. Wing area is 279.4 square feet. 6. Minimum turning radius (*pivot point to outboard wing tip strobe light) is 33’ -8”. 7. Propeller ground clearance with standard tires and nose gear fork: a. Nose tire inflated and nose gear barrel extended 3 5/8”: 11 1/4”. b. Nose tire deflated and nose strut fully compressed: 2 1/2”. 8. Propeller ground clearance with standard tires and extended nose gear fork: a. Nose tire inflated and nose gear barrel extended 3 5/8”: 14 3/4”. b. Nose tire deflated and nose strut fully compressed: 5 7/8”. 208BPHBUS-00 1-4 CESSNA SECTION 1 MODEL 208B G1000 GENERAL U.S. INTRODUCTION This POH/AFM contains 9 sections, and includes the material required to be furnished to the pilot by Federal Aviation Regulations and additional information provided by Cessna Aircraft Company. This handbook constitutes the FAA Approved Airplane Flight Manual. WARNING • This POH/AFM is not intended to be a guide for basic flight instruction or a training manual and should not be used as one. It is not a substitute for adequate and competent flight instruction, pilot skill, and pilot knowledge of current Airworthiness Directives, applicable federal aviation regulations and/or advisory circulars. • Assuring the airworthiness of the airplane is the responsibility of the airplane owner or operator. Determining if the airplane is safe for flight is the responsibility of the pilot in command. The pilot is also responsible for adhering to the operating limitations set forth by instrument markings, placards, and this POH/AFM. Generally, information in this POH/AFM is applicable to both the cargo version and the passenger version of the Model 208B. Some equipment differences exist between these versions. Specific versions are identified through use of the terms “Cargo Version” and “Passenger Version”. When one of these terms appears in text or on an illustration, the information applies only to that group of airplanes. If no term appears, the information applies to all airplanes. Section 1 provides basic data and information of general interest. It also contains definitions or explanations of symbols, abbreviations, and terminology commonly used. 1-5 208BPHBUS-00 SECTION 1 CESSNA GENERAL MODEL 208B G1000 U.S. DESCRIPTIVE DATA ENGINE Number of Engines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Engine Manufacturer . . . . . . . . . . . . . Pratt & Whitney Canada, Inc. Engine Model Number . . . . . . . . . . . . . . . . . . . . . . . . . . . PT6A-114A Engine Type: Free turbine, two-shaft engine utilizing a compressor section having three axial stages and one centrifugal stage, an annular reverse-flow combustion chamber, a one-stage compressor turbine, a one-stage power turbine, and a single exhaust. The power turbine drives the propeller through a two-stage planetary gearbox at the front of the engine. Horsepower . . . . . . . . . . . . . . . . Flat rated at 675 shaft horsepower. PROPELLER Propeller Manufacturer . . . . . . . . . . . McCauley Accessory Division Propeller Model Number . . . . . . . . . . . . . . . 3GFR34C703/106GA-0 Number of Blades . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 Propeller Diameter. . . . . . . . . . . . . . . . . . . . . . Maximum 106 Inches Minimum 104 Inches Propeller Type: Constant-speed, full-feathering, reversible, hydraulically-actuated aluminum-bladed propeller, with a feathered blade angle of 88°, a low pitch blade angle of 15.6°, and a maximum reverse blade angle of -14° (30-inch station). 208BPHBUS-00 1-6 CESSNA SECTION 1 MODEL 208B G1000 GENERAL U.S. FUEL Approved Fuel Grade (Specification): JET A (ASTM-D1655) JET A-1 (ASTM-D1655) JET B (ASTM-D1655) JP-1 (MIL-L-5616) JP-4 (MIL-T-5624) JP-5 (MIL-T-5624) JP-8 (MIL-T-83133A) Alternate/Emergency Fuels: Aviation Fuel (All grades of military and commercial aviation gasoline). CAUTION Aviation gasoline is restricted to emergency use and shall not be used for more than 150 hours in one overhaul period; a mixture of one part aviation gasoline and three parts of Jet A, Jet A-1, JP-5 or JP-8 may be used for emergency purposes for a maximum of 450 hours per overhaul period. Approved Fuel Additives: One of the following additives is required for anti-icing protection: Ethylene Glycol Monomethyl Ether Diethylene Glycol Monomethyl Ether CAUTION JP-4 and JP-5 fuel per MIL-T-5624 and JP-8 fuel per MIL-T-83133A contain the correct premixed quantity of an approved type of anti-icing fuel additive and no additional anti-ice compounds should be added. If additional anti-static protection is desired, the following additive is approved for use: Dupont Stadis 450 If additional biocidal protection is desired, the following additives are permitted for use in certain conditions: Sohio Biobor JF Kathon FP 1.5 (Continued Next Page) 1-7 208BPHBUS-00 SECTION 1 CESSNA GENERAL MODEL 208B G1000 U.S. FUEL (Continued) NOTE Refer to Section 8 for allowable concentrations of the above additives and additional information. Fuel Capacity: Total Capacity . . . . . . . . . . . . . . . . . . . . . . . . . . . 335.6 U.S. Gallons Total Capacity Each Tank . . . . . . . . . . . . . . . . . . 167.8 U.S. Gallons Total Usable . . . . . . . . . . . . . . . . . . . . . . . . . . . . 332.0 U.S. Gallons OIL Oil Grade (Specification): Oil conforming to Pratt & Whitney Engine Service Bulletin No. 1001, and all revisions or supplements thereto, must be used. Refer to Section 8 for a listing of approved oils. Total Oil Capacity: . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 U.S. Quarts (including filter, cooler, and hoses) Drain and Refill Quantity . . . . . . . . . . . . . . . . . . . . . .9.5 U.S. Quarts (approximately) Oil Quantity Operating Range: Fill to within 1 1/2 quarts of MAX HOT or MAX COLD (as appropriate) on dipstick. Quart marking indicate U.S. quarts low if oil is hot. For example, a dipstick reading of 3 indicates the system is within 2 quarts of MAX if the oil is cold and within 3 quarts of MAX if the oil is hot. WARNING Make sure oil dipstick cap is securely latched down. Operating the engine with less than the recommended oil level and with the dipstick cap unlatched will result in excessive oil loss and eventual engine stoppage. (Continued Next Page) 208BPHBUS-00 1-8 CESSNA SECTION 1 MODEL 208B G1000 GENERAL U.S. OIL (Continued) NOTE To obtain an accurate oil level reading, it is recommended the oil level be checked within 10 minutes after engine shutdown while the oil is hot (MAX HOT marking) or prior to the first flight of the day while the oil is cold (MAX COLD marking). If more than 10 minutes has elapsed since engine shutdown and engine oil is still warm, perform an engine dry motoring run before checking oil level. MAXIMUM CERTIFICATED WEIGHTS Ramp. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8785 Pounds Takeoff. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8750 Pounds Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8500 Pounds NOTE Refer to Section 6 of this POH/AFM for recommended loading arrangements. CABIN AND ENTRY DOOR DIMENSIONS Detailed dimensions of the cabin interior and entry door openings are illustrated in Section 6. BAGGAGE/CARGO COMPARTMENT AND CARGO DOOR ENTRY DIMENSIONS Detailed dimensions of the baggage/cargo area and cargo door openings are illustrated in Section 6. SPECIFIC LOADINGS Wing Loading . . . . . . . . . . . . . . . . . . . . . . 31.3 Pounds/Square Foot Power Loading . . . . . . . . . . . . . . . . 13.0 Pounds/Shaft Horsepower 1-9 208BPHBUS-00 SECTION 1 CESSNA GENERAL MODEL 208B G1000 U.S. SYMBOLS, ABBREVIATIONS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS (Continued Next Page) KCAS Knots Calibrated Airspeed is indicated airspeed corrected for position and instrument error and expressed in knots. Knots calibrated airspeed is equal to KTAS in standard atmosphere at sea level. KIAS Knots Indicated Airspeed is the speed shown on the airspeed indicator and expressed in knots. KTAS Knots True Airspeed is the airspeed expressed in knots relative to undisturbed air which is KCAS corrected for altitude and temperature. VA Maneuvering Speed is the maximum speed at which full or abrupt control movements may be used without overstressing the airframe. V FE Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position. V MO Maximum Operating Speed is the speed that may not be deliberately exceeded at any time. V S Stalling Speed or the minimum steady flight speed is the minimum speed at which the airplane is controllable. V SO Stalling Speed or the minimum steady flight speed is the minimum speed at which the airplane is controllable in the landing configuration at the most forward center of gravity. V X Best Angle-of-Climb Speed is the speed which results in the greatest gain of altitude in a given horizontal distance. V Y Best Rate-of-Climb Speed is the speed which results in the greatest gain in altitude in a given time. 208BPHBUS-00 1-10 CESSNA SECTION 1 MODEL 208B G1000 GENERAL U.S. SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (Continued) ENGINE POWER TERMINOLOGY OAT Outside Air Temperature is the free air static temperature. It may be expressed in either degrees Celsius (°C) or degrees Fahrenheit (°F). Pressure Altitude Pressure Altitude is the altitude read from an altimeter when the altimeter's barometric scale has been set to 29.92 inches of mercury (inHg) (1013.2 mb). ISA International Standard Atmosphere is an atmosphere in which: 1. The air is a perfect dry gas; 2. The temperature at sea level is 15°C; 3. The pressure at sea level is 29.92 inches of mercury (inHg) (1013.2 mb); 4. The temperature gradient from sea level to the altitude at which the temperature is -56.5°C is -1.98°C per 1000 feet. Beta Mode Beta Mode is the engine operational mode in which propeller blade pitch is controlled by the power lever. The beta mode may be used during ground operations only. Flameout Flameout is the unintentional loss of combustion chamber flame during operation. Flat Rated Flat Rated denotes constant horsepower over a specific altitude and/or temperature. Gas Generator RPM (Ng ) Gas Generator RPM indicates the percent of gas generator RPM based on a figure of 100% being 37,500 RPM. GCU GCU is the generator control unit. Hot Start Hot Start is an engine start, or attempted start, which results in an ITT exceeding 1090°C. ITT ITT signifies interstage turbine temperature. Maximum Climb Power Maximum Climb Power is the maximum power approved for normal climb. Use of this power setting is limited to climb operations. This power corresponds to that developed at the maximum torque limit, ITT of 765°C or Ng limit, whichever is less. This power corresponds to that shown in the Maximum Engine Torque for Climb figure of Section 5. (Continued Next Page) 1-11 208BPHBUS-00 SECTION 1 CESSNA GENERAL MODEL 208B G1000 U.S. SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (Continued) Maximum Rated Power Maximum Rated Power is the maximum power rating not limited by time. Use of this power should be limited to those abnormal circumstances which require maximum aircraft performance (i.e., severe icing conditions or windshear downdrafts). This power corresponds to that developed at the maximum torque limit, ITT of 805°C or N g limit, whichever is less. N g N g signifies gas generator RPM. Propeller RPM Propeller RPM indicates propeller speed in RPM. Reverse Thrust Reverse Thrust is the thrust produced when the propeller blades are rotated past flat pitch into the reverse range. RPM RPM is revolutions per minute. SHP SHP is shaft horsepower and is the power delivered at the propeller shaft. SHP = Propeller RPM x Torque (foot-pounds) 5252 Takeoff Power Takeoff Power is the maximum power rating and is limited to a maximum of 5 minutes under normal operation. Use of this power should be limited to normal takeoff operations. This power corresponds to that shown in the Maximum Engine Torque For Takeoff figure of Section 5. Torque Torque is a measurement of rotational force exerted by the engine on the propeller. Windmill Windmill is propeller rotation from airstream inputs. (Continued Next Page) 208BPHBUS-00 1-12 CESSNA SECTION 1 MODEL 208B G1000 GENERAL U.S. AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY WEIGHT AND BALANCE TERMINOLOGY SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (Continued) Demonstrated Crosswind Velocity Demonstrated Crosswind Velocity is the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing was actually demonstrated during certification tests. The value shown is not considered to be limiting. g g is acceleration due to gravity. NM/1000 lbs Nautical Miles Per Thousand Pounds of Fuel is the distance which can be expected per 1000 Pounds of fuel consumed at a specific engine power setting and/ or flight configuration. PPH PPH signifies pounds per hour and is the amount of fuel used per hour. Usable Fuel Usable Fuel is the fuel available for flight planning. Unusable Fuel Unusable Fuel is the quantity of fuel that can not be safely used in flight. Arm Arm is the horizontal distance from the reference datum to the center of gravity (C.G.) of an item. Basic Empty Weight Basic Empty Weight is the standard empty weight plus the weight of optional equipment. Center of Gravity (C.G.) Center of Gravity is the point at which an airplane would balance if suspended. Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane. C.G. Arm Center of Gravity Arm is the arm obtained by adding the airplane's individual moments and dividing the sum by the total weight. C.G. Limits Center of Gravity Limits are the extreme center of gravity locations within which the airplane must be operated at a given weight. MAC MAC (Mean Aerodynamic Chord) of a wing is the chord of an imaginary airfoil which throughout the flight range will have the same force vectors as those of the wing. (Continued Next Page) 1-13 208BPHBUS-00 SECTION 1 CESSNA GENERAL MODEL 208B G1000 U.S. SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (Continued) Maximum Landing Weight Maximum Landing Weight is the maximum Landing weight approved for the landing touchdown. Maximum Ramp Weight Maximum Ramp Weight is the maximum weight approved for ground maneuver, and includes the weight of fuel used for start, taxi and runup. Maximum Takeoff Weight Maximum Takeoff Weight is the maximum weight approved for the start of the takeoff roll. Moment Moment is the product of the weight of an item multiplied by its arm. (Moment divided by the constant 1000 is used in this POH/AFM to simplify balance calculations by reducing the number of digits.) Reference Datum Reference Datum is an imaginary vertical plane 100 inches forward of the front face of the firewall. Residual Fuel Residual Fuel is the fuel remaining when the airplane is defueled in a specific attitude by the normal means and procedures specified for draining the tanks. Scale Drift Scale Drift may occur on some types of electronic scales because of the inability of the scale to return to a true zero reading after weighing. If present, this deviation from zero should be accounted for when calculating the net weight of the airplane. Standard Empty Weight Standard Empty Weight is the weight of a standard airplane, including unusable fuel, full operating fluids and full engine oil. Fuselage Station Fuselage Station is a location along the airplane fuselage given in terms of the distance from the reference datum. Tare Tare is the weight of chocks, blocks, stands, etc. used when weighing an airplane, and is included in the scale readings. Tare is deducted from the scale reading to obtain the actual (net) airplane weight. Useful Load Useful Load is the difference between ramp weight and the basic empty weight. 208BPHBUS-00 1-14 CESSNA SECTION 1 MODEL 208B G1000 GENERAL U.S. AUTOPILOT/FLIGHT DIRECTOR AND AFCS TERMINOLOGY CAUTION A thorough understanding of the difference between an autopilot, a flight director, and an AFCS is required before operating any of the components of the Garmin G1000/GFC 700 Flight Control System. Refer to Garmin Cockpit Resource Guide (CRG) for complete operating details. Autopilot Autopilot is a system which automatically controls attitude and/or flight path of the airplane as directed by the pilot through the system's computer. Flight Director Flight Director is a system which provides visual recommendations to the pilot to allow him to manually control the airplane attitude and/or flight path in response to his desires as selected through the system's computer. Automated Flight Control System (AFCS) AFCS applies to the union of autopilot and flight director systems which allows the pilot to manage his flight by observing computed visual recommendations while the autopilot automatically follows these recommendations as selected by the pilot using the system's controls. Course Datum C/D is the compass reference used by the autopilot, along with course deviation, to provide laterial control when tracking a navigation signal. 1-15 208BPHBUS-00 SECTION 1 CESSNA GENERAL MODEL 208B G1000 U.S. WARNINGS, CAUTIONS, AND NOTES WARNING An operating procedure, technique, or maintenance practice which may result in personal injury or loss of life if not carefully obeyed. CAUTION An operating procedure, technique, or maintenance practice which may result in damage to equipment if not carefully obeyed. NOTE An operating procedure, technique, or maintenance condition which is considered essential to emphasize. METRIC/IMPERIAL/U.S. CONVERSION CHARTS The following charts have been provided to help international operators convert U.S. measurement supplied with the POH/AFM into metric and imperial measurements. The standard followed for measurement units shown is the National Institute of Standards Technology (NIST), Publication 811, "Guide for the Use of the International System of Units (SI)." Please refer to the following pages for these charts. 208BPHBUS-00 1-16 CESSNA SECTION 1 MODEL 208B G1000 GENERAL U.S. WEIGHT CONVERSIONS Figure 1-2 (Sheet 1 of 2) 1-17 208BPHBUS-00 SECTION 1 CESSNA GENERAL MODEL 208B G1000 U.S. WEIGHT CONVERSIONS Figure 1-2 (Sheet 2) 208BPHBUS-00 1-18 CESSNA SECTION 1 MODEL 208B G1000 GENERAL U.S. LENGTH CONVERSIONS Figure 1-3 (Sheet 1 of 4) 1-19 208BPHBUS-00 SECTION 1 CESSNA GENERAL MODEL 208B G1000 U.S. LENGTH CONVERSIONS Figure 1-3 (Sheet 2) 208BPHBUS-00 1-20 CESSNA SECTION 1 MODEL 208B G1000 GENERAL U.S. LENGTH CONVERSIONS Figure 1-3 (Sheet 3) 1-21 208BPHBUS-00 SECTION 1 CESSNA GENERAL MODEL 208B G1000 U.S. LENGTH CONVERSIONS Figure 1-3 (Sheet 4) 208BPHBUS-00 1-22 CESSNA SECTION 1 MODEL 208B G1000 GENERAL U.S. DISTANCE CONVERSIONS Figure 1-4 1-23 208BPHBUS-00 SECTION 1 CESSNA GENERAL MODEL 208B G1000 U.S. VOLUME CONVERSIONS Figure 1-5 (Sheet 1 of 3) 208BPHBUS-00 1-24 CESSNA SECTION 1 MODEL 208B G1000 GENERAL U.S. VOLUME CONVERSIONS Figure 1-5 (Sheet 2) 1-25 208BPHBUS-00 SECTION 1 CESSNA GENERAL MODEL 208B G1000 U.S. VOLUME CONVERSIONS Figure 1-5 (Sheet 3) 208BPHBUS-00 1-26 CESSNA SECTION 1 MODEL 208B G1000 GENERAL U.S. TEMPERATURE CONVERSIONS Figure 1-6 1-27 208BPHBUS-00 SECTION 1 CESSNA GENERAL MODEL 208B G1000 U.S. PRESSURE CONVERSION HECTOPASCALS TO INCHES OF MERCURY Figure 1-7 208BPHBUS-00 1-28 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS U.S. FAA APPROVED LIMITATIONS TABLE OF CONTENTS Page Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3 Airspeed Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4 Airspeed Indicator Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5 Power Plant Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6 Power Plant Instrument Markings . . . . . . . . . . . . . . . . . . . . . . . . . . 2-10 Miscellaneous Instrument Markings . . . . . . . . . . . . . . . . . . . . . . . . 2-11 Preflight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12 Visual and Tactile Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12 Weight Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12 Center of Gravity Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-13 Maneuver Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-13 Flight Load Factor Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14 Flight Crew Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14 Kinds of Operation Limits. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14 Fuel Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-17 Maximum Operating Altitude Limit. . . . . . . . . . . . . . . . . . . . . . . . . . 2-26 Outside Air Temperature Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-26 Maximum Passenger Seating Limits . . . . . . . . . . . . . . . . . . . . . . . . 2-26 Other Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-26 Flap Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-26 Type II, Type III or Type IV Anti-ice Fluid Takeoff Limitations . . . . . 2-27 Flap Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-27 Airspeed Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-27 Flight in Known Icing Visual Cues . . . . . . . . . . . . . . . . . . . . . . . . . . 2-27 (Continued Next Page) 208BPHBUS-00 2-1 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 U.S. FAA APPROVED Table of Contents (Continued) G1000 Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-28 Operational Approvals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-29 Garmin GFC-700 AFCS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-30 L3 Communications WX 500 Stormscope . . . . . . . . . . . . . . . . . . . 2-31 Traffic Advisory System (TAS) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-31 Terrain Awareness and Warning System (TAWS-B) . . . . . . . . . . . 2-31 Optional Equipment User’s Guide . . . . . . . . . . . . . . . . . . . . . . . . . 2-31 Placards . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-32 208BPHBUS-00 2-2 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS U.S. FAA APPROVED INTRODUCTION Section 2 includes the operating limitations, instrument markings, and basic placards necessary for the safe operation of the airplane, its engine, standard/non-standard systems and standard/non-standard equipment. WARNING The limitations included in this section and in Section 9 have been approved by the Federal Aviation Administration. Observance of these operating limitations is required by federal aviation regulations. NOTE • Operation in countries other than the United States may require observance of other limitations, procedures or performance data. • Refer to Section 9 of this POH/AFM for amended operating limitations, procedures, performance data and other necessary information for supplemental systems. • The airspeeds listed in Airspeed Limitations chart, and Airspeed Indicator Markings chart are based on Airspeed Calibration data shown in Section 5 with the normal static source. If the alternate static source is being used, ample margins should be observed to allow for the airspeed calibration variations between the normal and alternate static sources as shown in Section 5. Your Cessna is certificated under FAA Type Certificate No. A37CE as Cessna Model No. 208B. 2-3 208BPHBUS-00 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 U.S. FAA APPROVED AIRSPEED LIMITATIONS Airspeed limitations and their operational significance are shown in Airspeed Limitations chart. Figure 2-1 208BPHBUS-00 2-4 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS U.S. FAA APPROVED AIRSPEED INDICATOR MARKINGS Airspeed indicator markings and their color code significance are shown in Airspeed Indicator Markings chart. Figure 2-2 2-5 208BPHBUS-00 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 U.S. FAA APPROVED POWER PLANT LIMITATIONS Engine Manufacturer . . . . . . . . . . . . . . Pratt & Whitney Canada Inc. Engine Model Number . . . . . . . . . . . . . . . . . . . . . . . . . . . PT6A-114A Engine Operating Limits . . . Refer to Engine Operating Limits chart Fuel Grade and Approved Fuel Additives . .Refer to Fuel Limitations Oil Grade (Specification): Oil conforming to Pratt & Whitney Engine Service Bulletin No. 1001, and all revisions or supplements thereto, must be used. Refer to Section 8 for a listing of approved oils. When adding oil, service the engine with the type and brand which is currently being used in the engine. CAUTION Do not mix types or brands of oil. PROPELLER: Propeller Manufacturer . . . . . . . . . . . . McCauley Propeller Systems Propeller Model Number . . . . . . . . . . . . . . . 3GFR34C703/106GA-0 Propeller Diameter Maximum. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 106 Inches Minimum . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 104 Inches Propeller Blade Angle at 30-inch Station: Feathered . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 88° Low Pitch. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.6° Maximum Reverse . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . -14° (Continued Next Page) 208BPHBUS-00 2-6 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS U.S. FAA APPROVED POWER PLANT LIMITATIONS (Continued) Propeller System Operating Limits: An overspeed governor check shall be performed before the first flight of the day, after engine control system maintenance, or if adjustment has been made. Propeller RPM must be set at 1900 during all instrument approaches. Engine Control Operating Limits: Flight operation with the POWER Lever retarded below the IDLE position is prohibited. Such positioning may lead to loss of airplane control or may result in an engine overspeed condition and consequent loss of engine power. Operation of the EMERGENCY POWER Lever is prohibited with the POWER Lever out of the IDLE position. Engine Starting Cycle Limits: Using the airplane battery, the starting cycle shall be limited to the following intervals and sequence: 30 seconds ON - 60 seconds OFF, 30 seconds ON - 60 seconds OFF, 30 seconds ON - 30 minutes OFF. Repeat the above cycle as required. Using external power, the starting cycle shall be limited to the following intervals and sequence: 20 seconds ON - 120 seconds OFF, 20 seconds ON - 120 seconds OFF, 20 seconds ON - 60 minutes OFF. Repeat the above cycle as required. (Continued Next Page) 2-7 208BPHBUS-00 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 U.S. FAA APPROVED POWER PLANT LIMITATIONS (Continued) ENGINE OPERATING LIMITS Figure 2-3 (Sheet 1 of 2) 208BPHBUS-00 2-8 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS U.S. FAA APPROVED POWER PLANT LIMITATIONS (Continued) ENGINE OPERATING LIMITS Figure 2-3 (Sheet 2) 2-9 208BPHBUS-00 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 U.S. FAA APPROVED POWER PLANT INSTRUMENT MARKINGS Power plant instrument markings and their color significance are shown in Power Plant Instrument Markings chart. NOTE 1. Incorporates red line that moves to compensate for propeller RPM variation. 2. Incorporates enlarged ITT scaling with engine OFF and during start (STRT) sequence to aid temperature monitoring. 3. Incorporates red line that moves to compensate for OAT. 100% Ng is 37,500 RPM. 4. Propeller RPM must be set so as not to exceed 675 SHP with torque above 1865 foot-pounds. Full 675 SHP rating is available only at RPM settings of 1800 or greater. Figure 2-4 208BPHBUS-01 2-10 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS U.S. FAA APPROVED MISCELLANEOUS INSTRUMENT MARKINGS Power plant instrument markings and their color significance are shown in Miscellaneous Instrument Markings chart. Figure 2-5 2-11 208BPHBUS-00 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 U.S. FAA APPROVED PREFLIGHT Takeoff is prohibited with any frost, ice, snow, or slush adhering to the wings, horizontal stabilizer, vertical stabilizer, control surfaces, propeller blades, and/or engine inlets. WARNING Even small amounts of frost, ice, snow or slush on the wing may adversely change lift and drag. Failure to remove these contaminants will degrade airplane performance and will prevent a safe takeoff and climb. VISUAL AND TACTILE CHECK If the outside air temperature (OAT) is below 10°C (50°F) a tactile check of the wing leading edge and upper surface per Section 4 of the POH/AFM is required in addition to a visual inspection. During ground icing conditions, takeoff must be accomplished within five minutes of completing the tactile inspection unless the airplane is operated per 14 CFR 135.227(b)(3). Ground icing conditions are defined as: 1. The OAT is 2°C (36°F) or below and visible moisture is present (i.e. rain, drizzle, sleet, snow, fog, water is present on the wing, etc.), or, 2. The OAT is 5°C (41°F) or below and conditions are conducive to active frost formation (e.g. clear night with a dew point temperature/OAT difference of 3°C (5°F) or less). Takeoff is prohibited if frost, ice or snow may reasonably be expected to adhere to the airplane between the tactile check and takeoff (e.g. snow near freezing temperature with no deicing/anti-ice fluid application). Refer to the preflight procedures in Section 4 of this POH/AFM. WEIGHT LIMITS Maximum Ramp Weight . . . . . . . . . . . . . . . . . . . . . . . 8785 Pounds Maximum Takeoff Weight . . . . . . . . . . . . . . . . . . . . . . 8750 Pounds Maximum Landing Weight . . . . . . . . . . . . . . . . . . . . . 8500 Pounds NOTE Refer to Section 6 of this POH/AFM for recommended loading arrangements in the Standard 208B (Passenger and Cargo Version). 208BPHBUS-00 2-12 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS U.S. FAA APPROVED CENTER OF GRAVITY LIMITS Center of Gravity Range: Reference Datum: 100 inches forward of front face of firewall. Mean Aerodynamic Chord (MAC): The leading edge of the MAC is 177.57 inches aft of the datum. The MAC length is 66.40 inches. MANEUVER LIMITS This airplane is certificated in the normal category. The normal category is applicable to aircraft intended for non-aerobatic operations. These include any maneuvers incidental to normal flying, stalls (except whip stalls), lazy eights, chandelles, and turns in which the angle of bank is not more than 60°. Aerobatic maneuvers, including spins, are not approved. Forward: 179.60 inches (3.06% MAC) aft of datum at 5500 pounds or less, with straight line variation to 193.37 inches (23.80% MAC) aft of datum at 8000 pounds, and straight line variation to 199.15 inches (32.50% MAC) aft of datum at 8750 pounds. Aft: 204.35 inches (40.33% MAC) aft of datum at all weights up to 8750 pounds. 2-13 208BPHBUS-00 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 U.S. FAA APPROVED FLIGHT LOAD FACTOR LIMITS Flight Load Factors: (Maximum Takeoff Weight - 8750 pounds) *Flaps UP. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . +3.8g, -1.52g *Flaps Down (All Settings) . . . . . . . . . . . . . . . . . . . . . . . . . . . . +2.4g *The design load factors are 150% of the above, and in all cases, the structure meets or exceeds design loads. FLIGHT CREW LIMITS One pilot required in left seat. KINDS OF OPERATIONS EQUIPMENT LIST The Cessna 208B with Garmin G1000 is equipped for day or night VFR or IFR operations and flight into known icing conditions when appropriate equipment is installed. The operating limitation placard reflects the limits applicable at the time of Airworthiness Certificate issuance. The following equipment lists identify the systems and equipment upon which type certification for each kind of operation was predicated. These systems and equipment items must be installed and operable unless: 1. The airplane is approved to be operated in accordance with a current Minimum Equipment List (MEL) issued by the FAA. Or; 2. An alternate procedure is provided in the basic FAA Approved Airplane Flight Manual for the inoperative state of the listed equipment and all limitations are complied with. NOTE The following systems and equipment list does not included all equipment required by the 14 CFR Parts 91 and 135 Operating Requirements. It also does not include components obviously required for the airplane to be a i r w o r t h y s u c h a s w i n g s , p r i m a r y f l i g h t c o n t r o l s , empennage, engine, etc. (Continued Next Page) 208BPHBUS-00 2-14 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS U.S. FAA APPROVED KINDS OF OPERATIONS EQUIPMENT LIST (Continued) (Continued Next Page) 2-15 208BPHBUS-01 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 U.S. FAA APPROVED (Continued Next Page) 208BPHBUS-01 2-16 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS U.S. FAA APPROVED (Continued Next Page) 2-17 208BPHBUS-01 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 U.S. FAA APPROVED (Continued Next Page) 208BPHBUS-01 2-18 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS U.S. FAA APPROVED (Continued Next Page) 2-19 208BPHBUS-01 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 U.S. FAA APPROVED (Continued Next Page) 208BPHBUS-01 2-20 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS U.S. FAA APPROVED (Continued Next Page) 2-21 208BPHBUS-01 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 U.S. FAA APPROVED (Continued Next Page) 208BPHBUS-01 2-22 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS U.S. FAA APPROVED 2-23 208BPHBUS-01 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 U.S. FAA APPROVED FUEL LIMITATIONS NOTE To achieve full capacity, fill fuel tank to the top of the filler neck. Filling fuel tanks to the bottom of the fuel filler collar (level with flapper valve) allows space for thermal expansion and results in a decrease in fuel capacity of four gallons per side (eight gallons total). With low fuel quantity (FUEL LOW CAS MSG(s) ON), continuous uncoordinated flight is prohibited. Unusable fuel quantity increases when more severe sideslip is maintained. Due to possible fuel starvation, maximum full rudder sideslip duration time is three minutes. Maximum fuel unbalance in flight is 200 pounds. Fuel Grade (Specification) and Fuel Additives: CAUTION Aviation gasoline is restricted to emergency use and shall not be used for more than 150 hours in one overhaul period; a mixture of one part aviation gasoline and three parts of Jet A, Jet A-1, JP-1, or JP-5 may be used for emergency purposes for a maximum of 450 hours per overhaul period. (Continued Next Page) 208BPHBUS-00 2-24 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS U.S. FAA APPROVED FUEL LIMITATIONS (Continued) Fuel Grade Specification and Fuel Additives Figure 2-7 Refer to Section 8 for additional approved additives and concentrations. 2-25 208BPHBUS-00 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 U.S. FAA APPROVED MAXIMUM OPERATING ALTITUDE LIMIT Certificated Maximum Operating Altitudes: Non-Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . 25,000 Feet Icing Conditions (if so equipped) . . . . . . . . . . . . . . . . . 20,000 Feet Any conditions with any ice on the airplane . . . . . . . . . 20,000 Feet OUTSIDE AIR TEMPERATURE LIMITS Cold Day. . . . . . . . . . . . . . . . . . . -54°C from Sea Level to 25,000 Feet. Hot Day: Ground Operations. . . . . . . . . +53°C from Sea Level to 5000 Feet ISA +37°C above 5000 Feet Flight Operations . . . . . ISA +35°C from Sea Level to 25,000 Feet Refer to ISA Conversion and Operating Temperature Limits chart in Section 5, for a graphical presentation of the operating air temperature limits. NOTE • With both deck skin fans inoperative, ground operations are limited to 46°C for 30 minutes. • Ground operations up to 38°C are not time limited with both deck skin fans inoperative. MAXIMUM PASSENGER SEATING LIMITS In the Cargo Version, a maximum of one seat may be installed to the right of the pilot’s seat for use by a second crew member or a passenger. In the Passenger Version, up to eleven seats may be installed. the right front seat may be occupied by either a second crew member or passenger. When the right front seat is occupied by a passenger, only eight seats in the aft cabin can be occupied. Refer to Section 6 for seat locations. OTHER LIMITATIONS FLAP LIMITATIONS Approved Takeoff Range . . . . . . . . . . . . . . . . . . . . . . . . . . UP to 20° Approved Landing Range . . . . . . . . . . . . . . . . . . . . . . . .UP to FULL Approved Landing Range in Icing Conditions . . . . . . . . . . UP to 20° 208BPHBUS-00 2-26 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS U.S. FAA APPROVED TYPE II, TYPE III OR TYPE IV ANTI-ICE FLUID TAKEOFF LIMITATIONS FLAP LIMITATIONS Takeoff Flaps Setting. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP AIRSPEED LIMITATIONS Takeoff Rotation Speed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 83 KIAS FLIGHT IN KNOWN ICING VISUAL CUES As Required by AD 96-09-15, Paragraph (a) (1) WARNING Severe icing may result from environmental conditions outside of those for which the airplane is certificated. Flight in freezing rain, freezing drizzle, or mixed icing conditions (supercooled liquid water and ice crystals) may result in ice build-up on protected surfaces exceeding the capability of the ice protection system, or may result in ice forming aft of the protected surfaces. This ice may not be shed using the ice protection systems, and may seriously degrade the performance and controllability of the airplane. During flight, severe icing conditions that exceed those for which the airplane is certificated shall be determined by the following visual cues. If one or more of these visual cues exists, immediately request priority handling from Air Traffic Control to facilitate a route or an altitude change to exit the icing conditions. 1. Unusually extensive ice is accreted on the airframe in areas not normally observed to collect ice. 2. Accumulation of ice on the upper or lower surface of the wing aft of the protected area. 3. Heavy ice accumulations on the windshield, or when ice forms aft of the curved sections on the windshield. 4. Ice forms aft of the protected surfaces of the wing struts. NOTE This supersedes any relief provided by the Master Minimum Equipment List (MMEL), or the Kinds of Equipment Limits (KOEL). 2-27 208BPHBUS-00 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 U.S. FAA APPROVED G1000 LIMITATIONS The current Garmin G1000 Cockpit Reference Guide (CRG) Part Number and System Software Version that must be available to the pilot during flight are displayed on the MFD AUX group, SYSTEM STATUS page. GPS based IFR enroute, oceanic and terminal navigation is prohibited unless the pilot verifies the currency of the database or verifies each selected waypoint for accuracy by reference to current approved data. RNAV/GPS instrument approaches must be accomplished in accordance with approved instrument approach procedures that are retrieved from the G1000 navigation database. The G1000 database must incorporate the current update cycle. Use of the NAVIGATION MAP page for pilotage navigation is prohibited. The Navigation Map is intended only to enhance situational awareness. Navigation is to be conducted using only current charts, data and authorized navigation facilities. Use of the TERRAIN PROXIMITY information for primary terrain avoidance is prohibited. The Terrain Proximity map is intended only to enhance situational awareness. It is the pilot’s responsibility to provide terrain clearance at all times. Navigation using the G1000 is not authorized north of 70° North latitude or south of 70° South latitude due to unsuitability of the magnetic fields near the Earth's poles. In addition, operations are not authorized in the following two regions: 1. North of 65° North latitude between longitude 75° W and 120° W (Northern Canada). 2. South of 55° South latitude between longitude 120° E and 165° E (region south of Australia and New Zealand). (Continued Next Page) 208BPHBUS-00 2-28 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS U.S. FAA APPROVED G1000 LIMITATIONS (Continued) The COM 1/2 (split COM) function of the Audio Panel is not approved for use. During COM 1/2 operation, transmission by one crew member inhibits reception by the other crew member. The fuel quantity, fuel used and fuel remaining functions of the G1000 are advisory information only and must be verified by the pilot. Dispatch with GIA1, 2, PFD, or MFD cooling advisory message is prohibited. OPERATIONAL APPROVALS The Garmin G1000 GPS receivers are approved under TSO C145a Class 3. The Garmin G1000 system has been demonstrated capable of, and has been shown to meet the accuracy requirements for, the following operations provided it is receiving usable navigation data. These do not constitute operational approvals. 1. Enroute, terminal, non-precision instrument approach operations using GPS and WAAS (including "GPS", "or GPS", and "RNAV" approaches), and approach procedures with vertical guidance (including "LNAV/VNAV", "LNAV + V", and "LPV") within the U.S. National Airspace System in accordance with AC 20-138A. 2. As a required Long Range Navigation (LRN) system for use in the following types of airspace when used in conjunction with Garmin WAAS Fault Detection/Exclusion Prediction Program, part number 006-A0154-01 or later approved version: a. Oceanic/Remote - RNP-10 (per FAA AC 20-138A, FAA Notice 8110-60, FAA Order 8400-12A, and FAA Order 8700- 1). Both GPS receivers are required to be operating and receiving usable signals except for routes requiring only one Long Range Navigation (LRN) sensor. NOTE Each display computes an independent navigation solution based on the on-side GPS sensor. However, either display will automatically revert to the cross-side sensor if the on- side sensor fails or if the cross-side sensor is determined to be more accurate. A “BOTH ON GPS1” or “BOTH ON GPS2” message does not necessarily mean that one GPS has failed. Refer to the MFD AUX-GPS STATUS page to determine the status of the unused GPS. (Continued Next Page) 2-29 208BPHBUS-00 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 U.S. FAA APPROVED OPERATIONAL APPROVALS (Continued) b. North Atlantic (NAT) Minimum Navigational Performance Specifications (MNPS) Airspace per AC 91-49 and AC 120- 33. Both GPS receivers are required to be operating and receiving usable signals except for routes requiring only one Long Range Navigation sensor. c. Enroute and Terminal including RNP5/BRNAV and PRNAV (RNP-1) - In accordance with JAA TGL-10, ACJ 20X4, AC 90-96A, and AC 90-100A, provided the FMS is receiving usable navigation information from one or more GPS receivers. GARMIN GFC 700 AUTOMATED FLIGHT CONTROL SYSTEM (AFCS) 1. The GFC 700 AFCS preflight test must be successfully completed prior to use of the autopilot, flight director or manual electric trim. 2. A pilot, with the seat belt fastened, must occupy the left pilot’s seat during all autopilot operations. 3. The autopilot and yaw damper must be off during all takeoff and landings. 4. Autopilot maximum engagement speed . . . . . . . . . . . 175 KIAS Autopilot minimum engagement speed . . . . . . . . . . . . . 80 KIAS Electric Trim maximum operating speed . . . . . . . . . . . 175 KIAS 5. The autopilot must be disengaged below 200 feet AGL during approach operations and below 800 feet AGL during all other operations. 6. ILS approaches using the autopilot/flight director are limited to Category I approaches only. 7. Raw data ILS approaches below 400 feet AGL are prohibited. 8. Use of the autopilot is prohibited when the audio panel is inoperative (since the aural alert will not be provided when autopilot is disengaged). 9. Use of the autopilot is prohibited when conducting missed approach procedures until an established rate of climb that ensures all altitude requirements of the procedure will be met. L3 COMMUNICATIONS WX 500 STORMSCOPE (if installed) Use of the WEATHER MAP (WX-500 Stormscope) for hazardous weather (thunderstorm) penetration is prohibited. LTNG information on the NAVIGATION MAP or WEATHER MAP is approved only as an aid to hazardous weather avoidance, not penetration. User’s guide should be available to the pilot in flight. 208BPHBUS-00 2-30 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS U.S. FAA APPROVED TRAFFIC ADVISORY SYSTEM (TAS) (if installed) Use of the TRAFFIC MAP to maneuver the airplane to avoid traffic is prohibited. TAS is intended for advisory use only. TAS is intended only to help the pilot to visually locate traffic. It is the responsibility of the pilot to see and maneuver to avoid traffic. TAS is unable to detect any intruding aircraft without an operating transponder. TAS can detect and track aircraft with either an ATCRBS (operating in Mode A or C) or Mode S transponders. ATC procedures and the “see and avoid concept” will continue to be the primary means of aircraft separation. However, if communication is lost with ATC, TAS adds a significant backup for collision avoidance. TERRAIN AWARENESS AND WARNING SYSTEM (TAWS-B) (if installed) Use of the Terrain Awareness and Warning System (TAWS-B) to navigate to avoid terrain or obstacles is prohibited. TAWS-B is only approved as an aid to help the pilot to see-and-avoid terrain or obstacles. TAWS-B must be inhibited when landing at a location not included in the airport database. Use of TAWS-B is prohibited when operating using the QFE altimeter setting (altimeter indicates 0 feet altitude when the airplane is on the runway). The pilot is authorized to deviate from the current ATC clearance only to the extent necessary to comply with TAWS-B warnings. The geographic area of the TAWS-B database must match the geographic area in which the airplane is being operated. OPTIONAL EQUIPMENT USER’S GUIDE The pilot is responsible for ensuring the appropriate user’s guide(s) for all optional equipment installed in the aircraft is accessible to the pilot in flight. 2-31 208BPHBUS-00 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 U.S. FAA APPROVED PLACARDS WARNING The following information must be displayed in the form of composite or individual placards. As a minimum, the exact wording of these placards is required as specified in this section. Placard wording can be from part numbered placards obtained from Cessna Aircraft Company or equivalent placards installed by an approved repair station in accordance with normal maintenance practices/procedures. 1. In full view of the pilot on the sunvisor or windshield trim strip on airplanes equipped for flight into known icing: In full view of the pilot on the sunvisor or windshield trim strip on airplanes not equipped for flight into known icing: (Continued Next Page) 208BPHBUS-00 2-32 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS U.S. FAA APPROVED PLACARDS (Continued) 2. In full view of the pilot on the sunvisor or windshield trim on airplanes not equipped for flight into known icing and on airplanes equipped for flight into known icing not incorporating SK208-175: 3. On pedestal: 4. On control lock: 5. On left sidewall below and forward of instrument panel and (when right flight instrument panel is installed) on right sidewall below and forward of instrument panel: 6. On sunvisor or windshield trim-strip: 7. Above Pilot PFD: (Continued Next Page) THIS AIRPLANE IS PROHIBITED FROM FLIGHT IN KNOWN OR FORECAST ICING DO NOT TAKEOFF WITH ICE/FROST/SNOW ON THE AIRCRAFT CAUTION CONTROL LOCK REMOVE BEFORE STARTING ENGINE MAX WT. MANEUVER SPEED 148 KIAS SEE POH FOR OTHER WEIGHTS 2-33 208BPHBUS-01 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 U.S. FAA APPROVED PLACARDS (Continued) 8. A calibration card must be provided to indicate the accuracy of the magnetic compass in 30° increments. 9. Near wing flap position indicator: 10. Below power lever: 11. On fuel tank selector: (Continued Next Page) UP to 10° 175 KIAS (partial flap range with dark blue color code; also mechanical detent at 10°) 10° to 20° 150 KIAS (light blue code; also mechanical detent at 20°) 20° to FULL 125 KIAS (white color code) CAUTION USE BETA AND REVERSE ONLY WITH ENGINE RUNNING AND PROPELLER OUT OF FEATHER 208BPHBUS-00 2-34 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS U.S. FAA APPROVED PLACARDS (Continued) 12. Adjacent to each outboard fuel tank filler cap: 13. Adjacent to each inboard fuel tank filler cap (when installed): (Continued Next Page) 2-35 208BPHBUS-00 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 U.S. FAA APPROVED PLACARDS (Continued) 14. Adjacent to fuel filter: 15. Adjacent to fuel drain can: 16. On the brake fluid reservoir: (Continued Next Page) 208BPHBUS-00 2-36 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS U.S. FAA APPROVED PLACARDS (Continued) 17. Adjacent to oil dipstick/filler cap (on inertial separator duct): 18. On side of inertial separator duct: 19. On firewall above battery tray: (Continued Next Page) 208BPHBUS-00 2-37 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 U.S. FAA APPROVED PLACARDS (Continued) 20. Near ground service plug receptacle: 21. On access panel on bottom of both wings just forward of aileron: 22. On each side of nose strut fairing near tow limit marking (rudder lock placard required when rudder lock installed): 23. Adjacent to left crew door inside door handle: (Continued Next Page) EXTERNAL POWER 28 VOLTS D.C. NOMINAL 800 AMP STARTING CAPACITY MIN. DO NOT EXCEED 1700 AMPS FLUX VALVE USE NON-MAGNETIC TOOLS AND SCREWS WARNING MAXIMUM TOW LIMIT CAUTION DO NOT TOW AIRCRAFT WITH RUDDER LOCK ENGAGED 208BPHBUS-00 2-38 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS U.S. FAA APPROVED PLACARDS (Continued) 24. Adjacent to upper passenger door outside pushbutton and door handle (Passenger version only): 25. Adjacent to upper passenger door inside door handle (Passenger version only): 26. At center of lower passenger door on inside and outside (Passenger Version only): (Continued Next Page) 208BPHBUS-00 2-39 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 U.S. FAA APPROVED PLACARDS (Continued) 27. Adjacent to upper cargo door outside pushbutton and door handle: 28. Adjacent to upper cargo door inside door handle (Passenger Version only): 29. On right sidewall of lower passenger door (Passenger Version only): (Continued Next Page) 208BPHBUS-00 2-40 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS U.S. FAA APPROVED PLACARDS (Continued) 30. On left and right sides of aft cargo barrier (Cargo Version/ Passenger Version with cargo barrier installed): 31. On inside of lower cargo door (Cargo Version only) 32. On right sidewall adjacent to Zone 5 (Cargo Version only): (Continued Next Page) MAX LOAD BEHIND BARRIER 3400 LBS TOTAL ZONES FWD OF LAST LOADED ZONE MUST BE AT LEAST 75% FULL BY VOLUME. SEE POH FOR EXCEPTIONS. -CHECK WEIGHT AND BALANCE- MAX LOAD BEHIND BARRIER 3400 LBS TOTAL ZONES FWD OF LAST LOADED ZONE MUST BE AT LEAST 75% FULL BY VOLUME. SEE POH FOR EXCEPTIONS. -CHECK WEIGHT AND BALANCE- LOAD MUST BE PROTECTED FROM SHIFTING - SEE POH - IF LOAD IN ZONE 5 EXCEEDS 400 LBS A PARTITION NET IS REQD AFT OR LOAD MUST BE SECURED TO FLOOR 208BPHBUS-00 2-41 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 U.S. FAA APPROVED PLACARDS (Continued) 33. On left and right sides of cabin in appropriate zones (Cargo Version only): (Continued Next Page) ZONE 1 MAX LOAD 1780 LBS ZONE 2 MAX LOAD 3100 LBS ZONE 3 MAX LOAD 1900 LBS ZONE 4 MAX LOAD 1380 LBS ZONE 5 MAX LOAD 1270 LBS ZONE 6 MAX LOAD 320 LBS 208BPHBUS-00 2-42 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS U.S. FAA APPROVED PLACARDS (Continued) 34. On inside of cargo pod doors (if installed): 35. At each sidewall and ceiling anchor plate (except heavy duty anchor plates with additional structural support) and at anchor plate at center of lower cargo door (Cargo Version only): FWD. COMPARTMENT MAX. WEIGHT 230 LBS. MAX. FLOOR LOADING 30 LBS. PER SQ. FT. NO SHARP EDGES CTR. COMPARTMENT MAX. WEIGHT 310 LBS. MAX. FLOOR LOADING 30 LBS. PER SQ. FT. NO SHARP EDGES AFT COMPARTMENT MAX. WEIGHT 270 LBS. MAX. FLOOR LOADING 30 LBS. PER SQ. FT. NO SHARP EDGES AFT COMPARTMENT MAX. WEIGHT 280 LBS. MAX. FLOOR LOADING 30 LBS. PER SQ. FT. NO SHARP EDGES 208BPHBUS-00 2-43/2-44 CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES U.S. FAA APPROVED SECTION 3 EMERGENCY PROCEDURES TABLE OF CONTENTS Page Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-5 Airspeeds for Emergency Operation . . . . . . . . . . . . . . . . . . . . . . . . . 3-5 Operating Procedures - General . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-6 Engine Failures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-8 Engine Failure During Takeoff Roll . . . . . . . . . . . . . . . . . . . . . . . . 3-8 Engine Failure Immediately After Takeoff . . . . . . . . . . . . . . . . . . 3-8 Engine Failure During Flight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-8 Engine Flameout During Flight . . . . . . . . . . . . . . . . . . . . . . . . . 3-10 Airstart . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-10 Starter Assist (Preferred Procedure) . . . . . . . . . . . . . . . . . . . . . . 3-10 No Starter Assist . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-11 Forced Landings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-13 Emergency Landing without Engine Power . . . . . . . . . . . . . . . . 3-13 Precautionary Landing with Engine Power . . . . . . . . . . . . . . . . . 3-13 Ditching . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-14 Smoke and Fire . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-14 Engine Fire in Flight (Red ENGINE FIRE CAS MSG). . . . . . . . 3-14 Electrical Fire in Flight. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-15 Cabin Fire . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-16 Wing Fire. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-17 Cabin Fire During Ground Operations . . . . . . . . . . . . . . . . . . . . 3-17 Engine Fire During Start on Ground (Red ENGINE FIRE CAS MSG) . . . . . . . . . . . . . . . . 3-18 Ice and Rain Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-19 The Following Weather Conditions can be Conducive to Severe In-flight Icing - as Required by AD 96-09-15, Paragraph (a) (2) . . . . . . . . . . . . . . . . . . . . . . . 3-19 Procedures For Exiting the Severe Icing Environment - as Required by AD 96-09-15, Paragraph (a) (2) . . . . . . . . . . 3-19 Inadvertent Icing Encounter . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-20 (Continued Next Page) 208BPHBUS-01 3-1 SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 U.S. FAA APPROVED TABLE OF CONTENTS Page Avionics/Autopilot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-22 Pitch Trim Failure (Red PTRIM on PFD) . . . . . . . . . . . . . . . . . . 3-22 Yaw Damper Inoperative (Red AFCS or YAW CAS MSG) . . . . 3-22 Electrical Failures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-23 Generator Failure (Amber GENERATOR OFF CAS MSG) . . . . 3-23 Voltage High (Red VOLTAGE HIGH CAS MSG) . . . . . . . . . . . . 3-25 Voltage Low (Red VOLTAGE LOW CAS MSG) . . . . . . . . . . . . . 3-25 Engine Malfunctions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-27 Loss of Oil Pressure (Red OIL PRESSURE LOW CAS MSG) . . . . . . . . . . . . . . . . . . . . . . . 3-27 Fuel Control Unit Malfunction in the Pneumatic or Governor Sections (Engine Power Rolls Back to Idle) . . . . . 3-27 Emergency Power Lever not Stowed (Red EMERG PWR LVR CAS MSG) . . . . . . . . . . . . . . . . . . 3-27 Fuel System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-28 Fuel Flow Interruption to Fuel Reservoir (Red RSVR FUEL LOW CAS MSG). . . . . . . . . . . . . . . . . . . 3-28 Fuel Tank Selector OFF During Engine Start (Red FUEL SELECT OFF CAS MSG and Both Fuel Selector Warning Horns Activated) . . . . . . . . 3-28 Fuel Level Low and Single Fuel Selector Off (Red FUEL SELECT OFF and Amber L, R, L-R FUEL LOW CAS MSG(s)) and or Both Fuel Tank Selectors Off (Red FUEL SELECT OFF CAS MSG and One Fuel Warning Horn Activated). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-28 EXPANDED EMERGENCY Engine Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-30 Maximum Glide Chart . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-32 Forced Landings. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-34 Ditching . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-34 Landing without Elevator Control . . . . . . . . . . . . . . . . . . . . . . . . . . 3-35 Smoke and Fire . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-35 (Continued Next Page) 208BPHBUS-01 3-2 CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES U.S. FAA APPROVED TABLE OF CONTENTS Page Emergency Operation in Clouds . . . . . . . . . . . . . . . . . . . . . . . . . . 3-36 Executing a 180° Turn in Clouds (AHRS Failure) . . . . . . . . . . . 3-37 Emergency Descent Through Clouds (AHRS Failure) . . . . . . . 3-37 Recovery from Spiral Dive in the Clouds (AHRS Failure) . . . . . 3-38 Spins . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-39 Engine Malfunctions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-40 Loss of Oil Pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-40 Fuel Control Unit Malfunctions in the Pneumatic or Governor Sections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-41 Emergency Power Lever Not Stowed . . . . . . . . . . . . . . . . . . . . . 3-41 Fuel System Malfunction/Inadvertent Fuel Flow Interruption Procedures . . . . . . . . . . . . . . . . . . . . . . . . 3-42 Electrical Failures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-43 Generator or Main Bus Malfunctions. . . . . . . . . . . . . . . . . . . . . 3-43 Loss of Electrical Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-44 Partial Avionics Power Failure . . . . . . . . . . . . . . . . . . . . . . . . . 3-44 Standby Electrical System Malfunctions . . . . . . . . . . . . . . . . . . 3-44 Emergency Exits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-45 Emergency Exits Figure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-46 3-3/3-4 208BPHBUS-01 SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 U.S. FAA APPROVED CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES U.S. FAA APPROVED INTRODUCTION Section 3 provides checklist and amplified procedures for coping with emergencies that can occur. Emergencies caused by airplane or engine malfunctions are extremely rare if proper preflight inspections and maintenance are practiced. Enroute weather emergencies can be minimized or eliminated by careful flight planning and good judgment when unexpected weather is encountered. However, should an emergency arise, the basic guidelines described in this section should be considered and applied as necessary to correct the problem. Emergency procedures associated with standard avionics, the ELT, or any optional systems can be found in Section 9. WARNING There is no substitute for correct and complete preflight planning habits and continual review to minimize emergencies. Be thoroughly knowledgeable of hazards and conditions which represent potential dangers. Also be aware of the capabilities and limitations of the airplane. AIRSPEEDS FOR EMERGENCY OPERATION Engine Failure After Takeoff: WING FLAPS Handle UP . . . . . . . . . . . . . . . . . . . . . . . . . 100 KIAS WING FLAPS Handle FULL . . . . . . . . . . . . . . . . . . . . . . . . 80 KIAS Maneuvering Speed: 8750 lbs. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 148 KIAS 7500 lbs. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 137 KIAS 6250 lbs. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 125 KIAS 5000 lbs. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 112 KIAS Maximum Glide: With Cargo Pod Without Cargo Pod 8750 lbs 95 KIAS 97 KIAS 7500 lbs 87 KIAS 90 KIAS 6250 lbs 79 KIAS 82 KIAS 5000 lbs 71 KIAS 74 KIAS Precautionary Landing (Engine Power/Flaps FULL) . . . . . . . . 80 KIAS Landing Without Engine Power: WING FLAPS Handle UP . . . . . . . . . . . . . . . . . . . . . . . . . 100 KIAS WING FLAPS Handle FULL . . . . . . . . . . . . . . . . . . . . . . . . 80 KIAS 208BPHBUS-00 3-5 SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 U.S. FAA APPROVED GENERAL OPERATING PROCEDURES - GENERAL The operating procedures contained in this manual have been developed and recommended by Cessna Aircraft Company and are approved for use in the operation of this airplane. This section contains the Emergency and Abnormal Procedures for your airplane. For your convenience, definitions of these terms are listed in Section I. Operating procedures in this airplane flight manual are organized into Emergency, Abnormal, and Normal Procedures. Normal procedures are those recommended for routine day-to-day preflight, flight, and postflight operation and include expanded systems information and procedures. Some checks, as noted in the Limitations Section of this airplane flight manual, are required to assure proper system integrity. The Garmin G1000 Integrated Avionics System monitors most of the airplane systems for faults or failures and displays this information to the crew as messages in the Crew Alerting System (CAS) portion of the Primary Flight Display (PFD) in front of each pilot. Some Garmin G1000 faults are also displayed as messages in the Primary Flight Display (PFD) or Multi Function Display (MFD). These messages are listed within the appropriate portion of the Emergency and Abnormal procedures sections of the FAA Approved POH/AFM or appropriate Garmin Cockpit Reference Guide for the 208 series aircraft. Emergency procedures are generally associated with Red CAS MSG(s) or Garmin G1000 messages. Some procedures, such as Maximum Glide/Emergency Landing, are not associated with any particular message, but can involve one or more messages. All emergency procedures are organized by appropriate systems and include each Red CAS or Garmin message if applicable exactly as it appears on the PFD, or MFD. Emergency Procedures require immediate pilot recognition and corrective action by the crew. Red CAS MSG(s) will flash and pressing the WARNING softkey will silence the repeating chime and change the CAS MSG to steady. (Continued Next Page) 208BPHBUS-01 3-6 CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES U.S. FAA APPROVED OPERATING PROCEDURES - GENERAL (Continued) Some emergency situations require immediate memorized corrective action. These numbered steps are printed in boxes within the emergency procedures and should be accomplished without the aid of the checklist. Abnormal Procedures are general procedures that can be associated with one or more Amber CAS, or Garmin G1000 messages. Some procedures are not associated with any particular CAS or Garmin G1000 message but can involve one or more messages. These procedures are organized by related systems. An Abnormal Procedure is one requiring the use of special systems and/or the alternate use of regular systems that will maintain an acceptable level of airworthiness. These procedures require immediate pilot awareness and subsequent crew action may be required. Amber CAS MSG(s) will initially flash. Pressing the CAUTION softkey will change the CAS message to a steady state. NOTE • White CAS MSG(s) provide general information, indicate the need for additional crew awareness and the possible necessity of future pilot action. • In order to avoid confusion due to multiple messages, at critical times, some CAS MSG(s) are inhibited when a Line Replaceable Unit (LRU), such as the GEA-71 (Garmin Engine Airframe Computer), has failed. • Generally, the following Emergency and Abnormal Procedures do not direct the pilot to check/reset circuit breakers. This is considered basic airmanship and can be accomplished at the pilot's discretion. • Except where specific action is required, these procedures do not specify action when on the ground. Conditions resulting in a Red or Amber message should be corrected prior to flight. Reasons for White CAS MSG(s) should be determined prior to flight. • If a Red or Amber CAS MSG occurs in flight, consideration should be given to landing at an airport where corrective maintenance can be performed. 208BPHBUS-01 3-7 SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 U.S. FAA APPROVED ENGINE FAILURES ENGINE FAILURE DURING TAKEOFF ROLL 3. WING FLAPS Handle . . . . . . . . . . . . . . . . . . . . . . . . RETRACT IF AIRPLANE CANNOT BE STOPPED ON REMAINING RUNWAY: 4. FUEL CONDITION Lever . . . . . . . . . . . . . . . . . . . . . . CUTOFF 5. FUEL SHUTOFF Knob . . . . . . . . . . . . . . . . . . . . . . . PULL OFF 6. FUEL TANK SELECTORS . . . . OFF (warning horn will sound) 7. BATTERY Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF 2. PROP RPM Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . FEATHER 3. WING FLAPS Handle . . . . AS REQUIRED (20° recommended) 4. FUEL CONDITION Lever . . . . . . . . . . . . . . . . . . . . . . CUTOFF 5. FUEL SHUTOFF Knob . . . . . . . . . . . . . . . . . . . . . . . PULL OFF 6. FUEL TANK SELECTORS . . . . OFF (warning horn will sound) 7. BATTERY Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF ENGINE FAILURE DURING FLIGHT 5. WING FLAPS Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP 6. FUEL BOOST Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 7. FUEL SHUTOFF Knob . . . . . . . . . . . . . . . . . . . . . . . PULL OFF 8. IGNITION Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NORM (Continued Next Page) 1. POWER Lever. . . . . . . . . . . . . . . . . . . . . . . . . . BETA RANGE 2. Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY 1. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 85 KIAS 1. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 95 KIAS 2. POWER Lever. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE 3. PROP RPM Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . FEATHER 4. FUEL CONDITION Lever . . . . . . . . . . . . . . . . . . . . . . CUTOFF 208BPHBUS-00 3-8 CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES U.S. FAA APPROVED ENGINE FAILURE DURING FLIGHT (Continued) 9. STBY ALT PWR Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 10. Electrical Load . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REDUCE a. AVIONICS STBY PWR Switch . . . . . . . . . . . . . . . . . . . OFF b. AVIONICS BUS TIE Switch . . . . . . . . . . . . . . . . . . . . . OFF c. PRIMARY Switch (if installed) . . . . . . . . . . . . . . . . . NORM NOTE TKS Ice Protection System PRIMARY switch must be kept in NORM in order to keep the electrical load within limits on BATTERY power ONLY. d. PROP HEAT Switch (if installed) . . . . . . . . . . . . . . . . . OFF e. CABIN Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF f. STROBE lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF g. LDG and TAXI/RECOG lights. . . . . . . . . . . . . . . . . . . . OFF NOTE Keep LDG and TAXI/RECOG lights OFF until required for approach and landing. Prior to landing, only turn the LEFT LDG light ON to keep electrical load below limit. h. VENT AIR FANS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF i. AIR CONDITIONING (if installed) . . . . . . . . . . . . . . . . OFF j. GEN CONT and GEN FIELD Circuit Breakers. . . . . . PULL (top row, last two breakers on forward end) k. RIGHT PITOT HEAT Circuit Breaker . . . . . . . . . . . . . PULL (second row, third breaker from aft end) l. RDNG LIGHT Circuit Breaker . . . . . . . . . . . . . . . . . . PULL (third row, second breaker from aft end) m. RADAR R/T Circuit Breaker . . . . . . . . . . . . . . . . . . . . PULL (AVN BUS 1, second row, sixth breaker from left side) n. AVIONICS No. 2 Switch . . . . . . . . . . . . . . . . . . . . . . . . OFF 11. BATT AMPS . . . . . . . . . . . . . . . . . . VERIFY BELOW 45 AMPS 12. FLIGHT . . . . . . . . . . . . . . . TERMINATE (as soon as possible) (as described in Emergency Landing Without Engine Power) 208BPHBUS-00 3-9 SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 U.S. FAA APPROVED ENGINE FLAMEOUT DURING FLIGHT AFTER SATISFACTORY RELIGHT AS EVIDENCED BY NORMAL ITT AND N g . 3. POWER Lever. . . . . . . . . . . . . . . . . . . . . . . . . . . . AS DESIRED 4. IGNITION Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NORM (if cause of flameout has been corrected.) 6. Refer to Airstart checklists for engine restart AIRSTART STARTER ASSIST (Preferred Procedure) 1. BATTERY Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 2. AVIONICS No. 1 Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 3. Electrical Load. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REDUCE a. STBY ALT PWR Switch . . . . . . . . . . . . . . . . . . . . . . . . OFF b. AVIONICS Bus 2 Switch . . . . . . . . . . . . . . . . . . . . . . . . OFF c. IGNITION Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . NORM d. Left LIGHTS Panel Switches (9 total) . . . . . . . . . . . . . . OFF e. POWER OUTLET Switch . . . . . . . . . . . . . . . . . . . . . . . OFF f. VENT AIR FANS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF g. AIR CONDITIONING (if installed) . . . . . . . . . . . . . . . . . OFF h. BLEED AIR HEAT Switch . . . . . . . . . . . . . . . . . . . . . . . OFF 4. EMERGENCY POWER Lever. . . . . . . . . . . . . . . . . . . NORMAL 5. POWER Lever. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE 6. PROP RPM Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . MIN RPM 7. FUEL CONDITION Lever . . . . . . . . . . . . . . . . . . . . . . CUTOFF 8. FUEL SHUTOFF Knob . . . . . . . . . . . . . . . . . . . . . ON (push in) 9. FUEL TANK SELECTORS . . . . . . . . . . . . . . . . . . . . BOTH ON 10. FUEL BOOST Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 11. Altitude . . . . . . . . . . . . . . . . . . . . . . . . 20,000 FEET MAXIMUM (Continued Next Page) IF GAS GENERATOR SPEED (N G ) IS ABOVE 50%: 1. POWER Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE 2. IGNITION Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON IF GAS GENERATOR SPEED (N G) IS BELOW 50%: 5. FUEL CONDITION Lever . . . . . . . . . . . . . . . . . . . . . . CUTOFF 208BPHBUS-00 3-10 CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES U.S. FAA APPROVED STARTER ASSIST (Preferred Procedure) (Continued) 12. STARTER Switch . . . . . . . . . . . . . . . . . START and OBSERVE a. IGNITION ON CAS MSG . . . . . . . . . . . . . . . . . CHECK ON b. Engine Oil Pressure Indication. . . . . . . . . . . . . . . . CHECK c. Ng . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12% MINIMUM 13. FUEL CONDITION Lever . . . . . . . . LOW IDLE and OBSERVE a. FFLOW PPH . . . . . . . . . . . . . . . . . . . . . . . . . . 90-140 pph b. ITT . . . . . . . . . . . . . . . . . . . MONITOR (1090°C maximum) c. Ng . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52% MINIMUM 14. STARTER Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF WARNING If conditions exist such as heavy precipitation or nearly empty fuel tanks, turn the IGNITION Switch ON. 15. FUEL BOOST Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . NORM (unless it cycles on and off; then leave ON) 16. FUEL CONDITION Lever . . . . . . . . . . . . . . . . . . . . . HIGH IDLE 17. PROP RPM Lever. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET 18. POWER Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET 19. STBY ALT PWR Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 20. AVIONICS No. 2 Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 21. Electrical equipment . . . . . . . . . . . . . . . . . . . . . AS REQUIRED NO STARTER ASSIST 1. BATTERY Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 2. GENERATOR Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TRIP a. STBY ALT PWR Switch . . . . . . . . . . . . . . . . . . . . . . . . OFF b. AVIONICS Bus 2 Switch. . . . . . . . . . . . . . . . . . . . . . . . OFF c. Left LIGHTS Panel Switches (9 total). . . . . . . . . . . . . . OFF d. POWER OUTLET Switch . . . . . . . . . . . . . . . . . . . . . . . OFF e. VENT AIR FANS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF f. AIR CONDITIONING (if installed) . . . . . . . . . . . . . . . . OFF g. BLEED AIR HEAT Switch. . . . . . . . . . . . . . . . . . . . . . . OFF 3. EMERGENCY POWER Lever . . . . . . . . . . . . . . . . . . NORMAL 4. POWER Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE 5. PROP RPM Lever. . . . . . . . . . . . . . . . . . . . . . . . . . . . MIN RPM (Continued Next Page) 208BPHBUS-00 3-11 SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 U.S. FAA APPROVED NO STARTER ASSIST (Continued) 6. FUEL CONDITION Lever . . . . . . . . . . . . . . . . . . . . . . CUTOFF 7. FUEL SHUTOFF Knob . . . . . . . . . . . . . . . . . . . . . ON (push in) 8. FUEL TANK SELECTORS . . . . . . . . . . . . . . . . . . . . BOTH ON 9. FUEL BOOST Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 10. IGNITION Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 11. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . 100 KIAS MINIMUM (140 KIAS if propeller is feathered) 12. Altitude . . . . . . . . . . . . . . . . . . . . . . . . . 20,000 feet MAXIMUM (15,000 feet if propeller is feathered) CAUTION Do not attempt a restart without starter assist if N g indications indicates zero RPM. 13. Ng Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK STABLE 14. FUEL CONDITION Lever . . . . . . . . LOW IDLE and OBSERVE a. FFLOW PPH. . . . . . . . . . . . . . . . . . . . . . . . . . . 90-140 pph b. ITT . . . . . . . . . . . . . . . . . . . MONITOR (1090°C maximum) c. Ng . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52% MINIMUM 15. IGNITION Switch. . . . . . . . . . . . . . . . NORM (Ng 52% or above) (unless conditions warrant leaving ON) WARNING If conditions exist, such as heavy precipitation or nearly empty fuel tanks, turn the IGNITION Switch ON. 16. FUEL BOOST Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . NORM (unless it cycles on and off; then leave ON) 17. FUEL CONDITION Lever . . . . . . . . . . . . . . . . . . . . HIGH IDLE 18. PROP RPM Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET 19. POWER Lever. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET 20. GENERATOR Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET 21. STBY ALT PWR Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 22. AVIONICS No. 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 208BPHBUS-00 3-12 CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES U.S. FAA APPROVED FORCED LANDINGS EMERGENCY LANDING WITHOUT ENGINE POWER 1. Seats, Seat Belts, Shoulder Harnesses . . . . . . . . . . . SECURE 2. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . 100 KIAS (flaps UP) 80 KIAS (flaps FULL) 3. POWER Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE 4. PROP RPM Lever. . . . . . . . . . . . . . . . . . . . . . . . . . . FEATHER 5. FUEL CONDITION Lever . . . . . . . . . . . . . . . . . . . . . . . CUTOFF 6. FUEL BOOST Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 7. IGNITION Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NORM 8. STBY ALT PWR Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 9. Nonessential Equipment. . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 10. FUEL SHUTOFF Knob . . . . . . . . . . . . . . . . . . . . . . PULL OFF 11. FUEL TANK SELECTORS . . . . . OFF (warning horn will sound) 12. WING FLAPS Handle . . AS REQUIRED (FULL recommended) 13. Crew Doors. . . . . . . . . . . UNLATCH PRIOR TO TOUCHDOWN 14. GENERATOR Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TRIP 15. BATTERY Switch . . . . . . . . . . . OFF (when landing is assured) 16. Touchdown . . . . . . . . . . . . . . . . . . . . . . . SLIGHTLY TAIL LOW 17. Brakes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY HEAVILY PRECAUTIONARY LANDING WITH ENGINE POWER 1. Seats, Seat Belts, Shoulder Harnesses . . . . . . . . . . . SECURE 2. WING FLAPS Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10° 3. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 90 KIAS 4. Selected Field . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY OVER (noting terrain and obstructions) 5. Nonesential Equipment (except BATTERY, GENERATOR and STBY ALT). . . . OFF 6. WING FLAPS Handle . . . . . . . FULL DOWN (on final approach) 7. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 80 KIAS 8. Crew Doors. . . . . . . . . . . UNLATCH PRIOR TO TOUCHDOWN 9. STBY ALT PWR Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 10. GENERATOR Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TRIP 11. BATTERY Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 12. Touchdown . . . . . . . . . . . . . . . . . . . . . . . SLIGHTLY TAIL LOW 13. POWER Lever . . . . . . . . . . . . . . . . . . . . . . . . . . BETA RANGE 14. FUEL CONDITION Lever . . . . . . . . . . . . . . . . . . . . . . . CUTOFF 15. Brakes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY HEAVILY 208BPHBUS-00 3-13 SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 U.S. FAA APPROVED DITCHING 1. Radio . . . . . . . . . . . . . . . TRANSMIT MAYDAY (on 121.5 MHz) Give location, intentions and SQUAWK 7700 if transponder is installed. 2. Heavy Objects in Cabin. . . . . . . . . . . . . . . . . . . . . . . . SECURE (if passenger is available to assist) 3. Seats, Seat Belts, Shoulder Harnesses . . . . . . . . . . . SECURE 4. WING FLAPS Handle . . . . . . . . . . . . . . . . . . . . . . FULL DOWN 5. POWER. . . . ESTABLISH 300 FT/MIN DESCENT AT 80 KIAS 6. Approach a. High Winds . . . . . . . . . . . . . . . . . . . . . . . . INTO THE WIND b. Light Winds, Heavy Swells . . . . . PARALLEL TO SWELLS 7. Face . . . . . . . . . . . . . . . . . . . . . . . CUSHION at TOUCHDOWN (with folded coat or similar object) 8. Touchdown . . . . . . . . . . NO FLARE (maintain descent attitude) 9. Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EVACUATE 10. Life Vests and Raft . . . . . . . . . . INFLATE (when outside cabin) WARNING The airplane has not been flight tested in actual ditchings, thus the above recommended procedure is based entirely on the best judgment of Cessna Aircraft Company. SMOKE AND FIRE ENGINE FIRE IN FLIGHT (Red ENGINE FIRE CAS MSG) 6. Forward Side Vents . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSE 7. Overhead Vents. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN 8. VENT AIR FANS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 9. WING FLAPS Handle . . . . . . . . . . . . . . . . . . . . . . . . 20° - FULL 10. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 80 - 85 KIAS 11. Forced Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXECUTE (as described in Emergency Landing Without Engine Power) 1. POWER Lever. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE 2. PROP RPM Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . FEATHER 3. FUEL CONDITION Lever . . . . . . . . . . . . . . . . . . . . . . CUTOFF 4. FUEL SHUTOFF Knob . . . . . . . . . . . . . . . . . . . . . . PULL OFF 5. CABIN HEAT FIREWALL SHUTOFF CONTROL . . PULL OFF 208BPHBUS-00 3-14 CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES U.S. FAA APPROVED ELECTRICAL FIRE IN FLIGHT WARNING Without electrical power all electrically operated flight and engine indications, fuel boost pump, CAS messages, WING FLAPS Handle and all navigation and communications will be inoperative. All standby instruments, including torque indicator and vacuum-driven standby attitude indicator, will be operative. WARNING Occupants should use oxygen masks (if installed) until smoke clears. After discharging an extinguisher within a closed cabin, ventilate the cabin. 7. AVIONICS Power Switches . . . . . . . . . . . . . . . . . . . . . . . . OFF WARNING With AVIONICS No. 1 and No. 2 OFF, use standby flight instruments. 8. All Other Electrical Switches. . . . . . . . . . . . . . . . . . . . . . . . OFF IF FIRE APPEARS OUT AND ELECTRICAL POWER IS NECESSARY FOR CONTINUANCE OF FLIGHT: 9. BATTERY Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 10. GENERATOR Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET 11. STBY ALT PWR Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 12. Circuit Breakers . . . . . . CHECK (for faulty circuit; do not reset) 13. AVIONICS No. 1 Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON (Continued Next Page) 1. STBY ALT PWR Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 2. GENERATOR Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . TRIP 3. BATTERY Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 4. Vents . . . . . . . . . . . . . . . . . . . . . . . . CLOSED (to avoid drafts) a. Forward Side Vents . . . . . . . . . . . . . . . . . . . . . . . CLOSE b. Overhead Vents . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSE c. VENT AIR FANS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 5. BLEED AIR HEAT Switch . . . . . . . . . . . . . . . . . . . . . . . . . OFF 6. Fire Extinguisher . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE 208BPHBUS-00 3-15 SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 U.S. FAA APPROVED ELECTRICAL FIRE IN FLIGHT (Continued) 14. Electrical Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Turn switches on one at a time, with a delay after each until short circuit is localized. 15. Vents . . . . . . . . . .