Cessna Grand Caravan 208B G1000 Manual

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CESSNA

INTRODUCTION

MODEL 208B G1000

NOTICE

AT THE TIME OF ISSUANCE, THIS INFORMATION MANUAL

WAS AN EXACT DUPLICATE OF THE OFFICIAL PILOT'S

OPERATING HANDBOOK AND FAA APPROVED AIRPLANE

FLIGHT MANUAL AND IS TO BE USED FOR GENERAL

PURPOSES ONLY.

IT WILL NOT BE KEPT CURRENT AND, THEREFORE, CANNOT

BE USED AS A SUBSTITUTE FOR THE OFFICIAL PILOT'S

OPERATING HANDBOOK AND FAA APPROVED AIRPLANE

FLIGHT MANUAL INTENDED FOR OPERATION OF THE

AIRPLANE.

THE PILOT'S OPERATING HANDBOOK MUST BE CARRIED IN

THE AIRPLANE AND AVAILABLE TO THE PILOT AT ALL TIMES.

Revision 1

U.S.

Table of Contents

Chapters

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Summary of Contents for Cessna Grand Caravan 208B G1000

Page 1 CESSNA INTRODUCTION MODEL 208B G1000 NOTICE AT THE TIME OF ISSUANCE, THIS INFORMATION MANUAL WAS AN EXACT DUPLICATE OF THE OFFICIAL PILOT’S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL AND IS TO BE USED FOR GENERAL PURPOSES ONLY. IT WILL NOT BE KEPT CURRENT AND, THEREFORE, CANNOT BE USED AS A SUBSTITUTE FOR THE OFFICIAL PILOT’S...
Page 2 INTRODUCTION CESSNA MODEL 208B G1000 PERFORMANCE - SPECIFICATIONS CARGO VERSION *SPEED (KTAS): Maximum Cruise at 10,000 Feet ....175 Knots Maximum Cruise at 20,000 Feet ....164 Knots RANGE:With 2224 pounds usable fuel and fuel allowance for engine start, taxi, takeoff, climb, descent and 45 minutes reserve.
Page 3 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.
Page 4 INTRODUCTION CESSNA MODEL 208B G1000 PERFORMANCE - SPECIFICATIONS PASSENGER VERSION * SPEED (KTAS): Maximum Cruise at 10,000 Feet ....184 Knots Maximum Cruise at 20,000 Feet .
Page 5 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.
Page 7 CESSNA INTRODUCTION MODEL 208B G1000 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...
Page 9 CESSNA INTRODUCTION MODEL 208B G1000 TABLE OF CONTENTS SECTION GENERAL ........1 LIMITATIONS .
Page 10 INTRODUCTION CESSNA MODEL 208B G1000 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.
Page 11 CESSNA INTRODUCTION MODEL 208B G1000 TABLE OF CONTENTS SECTION GENERAL ........1 LIMITATIONS .
Page 13: Table Of Contents
CESSNA SECTION 1 MODEL 208B G1000 GENERAL GENERAL TABLE OF CONTENTS Page Three View..........1-3 Introduction .
Page 15 CESSNA SECTION 1 MODEL 208B G1000 GENERAL Figure 1-1 (Sheet 1 of 2) 208BPHBUS-00 U.S.
Page 16 SECTION 1 CESSNA GENERAL MODEL 208B G1000 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.
Page 17: Introduction
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 •...
Page 18: Descriptive Data
SECTION 1 CESSNA GENERAL MODEL 208B G1000 DESCRIPTIVE DATA ENGINE Number of Engines ........1 Engine Manufacturer .
Page 19: Fuel
CESSNA SECTION 1 MODEL 208B G1000 GENERAL 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).
Page 20: Oil
SECTION 1 CESSNA GENERAL MODEL 208B G1000 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 .
Page 21: Maximum Certificated Weights
CESSNA SECTION 1 MODEL 208B G1000 GENERAL (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).
Page 22: Symbols, Abbreviations And Terminology
SECTION 1 CESSNA GENERAL MODEL 208B G1000 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS 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.
Page 23: Engine Power Terminology
CESSNA SECTION 1 MODEL 208B G1000 GENERAL SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (Continued) Outside Air Temperature is the free air static temperature. It may be expressed in either degrees Celsius (°C) or degrees Fahrenheit (°F). Pressure Pressure Altitude is the altitude read from an altimeter...
Page 24 SECTION 1 CESSNA GENERAL MODEL 208B G1000 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (Continued) Maximum Maximum Rated Power is the maximum power rating Rated not limited by time. Use of this power should be limited to Power those abnormal circumstances which require maximum aircraft performance (i.e., severe icing conditions or...
Page 25: Airplane Performance And Flight Planning Terminology
CESSNA SECTION 1 MODEL 208B G1000 GENERAL SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (Continued) AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Demonstrated Demonstrated Crosswind Velocity is the velocity of Crosswind the crosswind component for which adequate control Velocity of the airplane during takeoff and landing was actually demonstrated during certification tests.
Page 26 SECTION 1 CESSNA GENERAL MODEL 208B G1000 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (Continued) Maximum Maximum Landing Weight is the maximum Landing Landing weight approved for the landing touchdown. Weight Maximum Maximum Ramp Weight is the maximum weight Ramp approved for ground maneuver, and includes the weight Weight of fuel used for start, taxi and runup.
Page 27 CESSNA SECTION 1 MODEL 208B G1000 GENERAL AUTOPILOT/FLIGHT DIRECTOR 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.
Page 28: Warning, Cautions, And Notes
SECTION 1 CESSNA GENERAL MODEL 208B G1000 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.
Page 29: Weight Conversions
CESSNA SECTION 1 MODEL 208B G1000 GENERAL WEIGHT CONVERSIONS Figure 1-2 (Sheet 1 of 2) 208BPHBUS-00 1-17 U.S.
Page 30 SECTION 1 CESSNA GENERAL MODEL 208B G1000 WEIGHT CONVERSIONS Figure 1-2 (Sheet 2) 208BPHBUS-00 1-18 U.S.
Page 31: Length Conversions
CESSNA SECTION 1 MODEL 208B G1000 GENERAL LENGTH CONVERSIONS Figure 1-3 (Sheet 1 of 4) 208BPHBUS-00 1-19 U.S.
Page 32 SECTION 1 CESSNA GENERAL MODEL 208B G1000 LENGTH CONVERSIONS Figure 1-3 (Sheet 2) 208BPHBUS-00 1-20 U.S.
Page 33 CESSNA SECTION 1 MODEL 208B G1000 GENERAL LENGTH CONVERSIONS Figure 1-3 (Sheet 3) 208BPHBUS-00 1-21 U.S.
Page 34 SECTION 1 CESSNA GENERAL MODEL 208B G1000 LENGTH CONVERSIONS Figure 1-3 (Sheet 4) 208BPHBUS-00 1-22 U.S.
Page 35: Distance Conversions
CESSNA SECTION 1 MODEL 208B G1000 GENERAL DISTANCE CONVERSIONS Figure 1-4 208BPHBUS-00 1-23 U.S.
Page 36: Volume Conversions
SECTION 1 CESSNA GENERAL MODEL 208B G1000 VOLUME CONVERSIONS Figure 1-5 (Sheet 1 of 3) 208BPHBUS-00 1-24 U.S.
Page 37 CESSNA SECTION 1 MODEL 208B G1000 GENERAL VOLUME CONVERSIONS Figure 1-5 (Sheet 2) 208BPHBUS-00 1-25 U.S.
Page 38 SECTION 1 CESSNA GENERAL MODEL 208B G1000 VOLUME CONVERSIONS Figure 1-5 (Sheet 3) 208BPHBUS-00 1-26 U.S.
Page 39: Temperature Conversions
CESSNA SECTION 1 MODEL 208B G1000 GENERAL TEMPERATURE CONVERSIONS Figure 1-6 208BPHBUS-00 1-27 U.S.
Page 40: Pressure Conversions
SECTION 1 CESSNA GENERAL MODEL 208B G1000 PRESSURE CONVERSION HECTOPASCALS TO INCHES OF MERCURY Figure 1-7 208BPHBUS-00 1-28 U.S.
Page 41 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS LIMITATIONS TABLE OF CONTENTS Page Introduction ..........2-3 Airspeed Limitations .
Page 42 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 Table of Contents (Continued) G1000 Limitations ........2-28 Operational Approvals .
Page 43: Introduction
Section Your Cessna is certificated under FAA Type Certificate No. A37CE as Cessna Model No. 208B. FAA APPROVED 208BPHBUS-00 U.S.
Page 44: Airspeed Limitations
SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 AIRSPEED LIMITATIONS Airspeed limitations and their operational significance are shown in Airspeed Limitations chart. Figure 2-1 FAA APPROVED 208BPHBUS-00 U.S.
Page 45: Airspeed Indicator Markings
CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS AIRSPEED INDICATOR MARKINGS Airspeed indicator markings and their color code significance are shown in Airspeed Indicator Markings chart. Figure 2-2 FAA APPROVED 208BPHBUS-00 U.S.
Page 46: Power Plant Limitations
SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 POWER PLANT LIMITATIONS Engine Manufacturer ....Pratt & Whitney Canada Inc. Engine Model Number ......PT6A-114A Engine Operating Limits .
Page 47 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS 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.
Page 48 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 POWER PLANT LIMITATIONS (Continued) ENGINE OPERATING LIMITS Figure 2-3 (Sheet 1 of 2) FAA APPROVED 208BPHBUS-00 U.S.
Page 49 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS POWER PLANT LIMITATIONS (Continued) ENGINE OPERATING LIMITS Figure 2-3 (Sheet 2) FAA APPROVED 208BPHBUS-00 U.S.
Page 50: Power Plant Instrument Markings
SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 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.
Page 51: Miscellaneous Instrument Markings
CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS MISCELLANEOUS INSTRUMENT MARKINGS Power plant instrument markings and their color significance are shown in Miscellaneous Instrument Markings chart. Figure 2-5 FAA APPROVED 208BPHBUS-00 2-11 U.S.
Page 52: Preflight
SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 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.
Page 53: Center Of Gravity Limits
CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS CENTER OF GRAVITY LIMITS Center of Gravity Range: 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...
Page 54: Flight Load Factor 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.
Page 55 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS KINDS OPERATIONS EQUIPMENT LIST (Continued) (Continued Next Page) FAA APPROVED 208BPHBUS-01 2-15 U.S.
Page 56 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 (Continued Next Page) FAA APPROVED 208BPHBUS-01 2-16 U.S.
Page 57 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS (Continued Next Page) FAA APPROVED 208BPHBUS-01 2-17 U.S.
Page 58 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 (Continued Next Page) FAA APPROVED 208BPHBUS-01 2-18 U.S.
Page 59 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS (Continued Next Page) FAA APPROVED 208BPHBUS-01 2-19 U.S.
Page 60 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 (Continued Next Page) FAA APPROVED 208BPHBUS-01 2-20 U.S.
Page 61 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS (Continued Next Page) FAA APPROVED 208BPHBUS-01 2-21 U.S.
Page 62 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 (Continued Next Page) FAA APPROVED 208BPHBUS-01 2-22 U.S.
Page 63 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS FAA APPROVED 208BPHBUS-01 2-23 U.S.
Page 64: Fuel Limitations
SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 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).
Page 65 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS FUEL LIMITATIONS (Continued) Fuel Grade Specification and Fuel Additives Figure 2-7 Refer Section additional approved additives concentrations. FAA APPROVED 208BPHBUS-00 2-25 U.S.
Page 66: Maximum Operating Altitude Limit
SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 MAXIMUM OPERATING ALTITUDE LIMIT Certificated Maximum Operating Altitudes: Non-Icing Conditions ......25,000 Feet Icing Conditions (if so equipped) .
Page 67: Type Ii, Type Iii Or Type Iv Anti-Ice Fluid Takeoff Limitations
CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS TYPE II, TYPE III OR TYPE IV ANTI-ICE FLUID TAKEOFF LIMITATIONS FLAP LIMITATIONS Takeoff Flaps Setting........UP AIRSPEED LIMITATIONS Takeoff Rotation Speed .
Page 68: G1000 Limitations
SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 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.
Page 69: Operational Approvals
CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS 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.
Page 70: L3 Communications Wx 500 Stormscope
SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 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.
Page 71: Traffic Advisory System (Tas)
CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS 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.
Page 72: Placards
SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 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...
Page 73 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS 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:...
Page 74 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 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: UP to 10° 175 KIAS (partial flap range with dark blue color code;...
Page 75 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS 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) FAA APPROVED 208BPHBUS-00 2-35 U.S.
Page 76 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 PLACARDS (Continued) 14. Adjacent to fuel filter: 15. Adjacent to fuel drain can: 16. On the brake fluid reservoir: (Continued Next Page) FAA APPROVED 208BPHBUS-00 2-36 U.S.
Page 77 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS 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) FAA APPROVED 208BPHBUS-00 2-37 U.S.
Page 78 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 PLACARDS (Continued) 20. Near ground service plug receptacle: EXTERNAL POWER 28 VOLTS D.C. NOMINAL 800 AMP STARTING CAPACITY MIN. DO NOT EXCEED 1700 AMPS 21. On access panel on bottom of both wings just forward of aileron:...
Page 79 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS 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...
Page 80 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 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...
Page 81 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS PLACARDS (Continued) 30. On left and right sides of aft cargo barrier (Cargo Version/ Passenger Version with cargo barrier installed): MAX LOAD BEHIND BARRIER 3400 LBS TOTAL ZONES FWD OF LAST LOADED ZONE MUST BE AT LEAST 75% FULL BY VOLUME.
Page 82 SECTION 2 CESSNA LIMITATIONS MODEL 208B G1000 PLACARDS (Continued) 33. On left and right sides of cabin in appropriate zones (Cargo Version only): ZONE 1 MAX LOAD 1780 LBS ZONE 2 MAX LOAD 3100 LBS ZONE 3 MAX LOAD 1900 LBS...
Page 83 CESSNA SECTION 2 MODEL 208B G1000 LIMITATIONS PLACARDS (Continued) 34. On inside of cargo pod doors (if installed): FWD. COMPARTMENT MAX. WEIGHT 230 LBS. MAX. FLOOR LOADING 30 LBS. PER SQ. FT. NO SHARP EDGES CTR. COMPARTMENT MAX. WEIGHT 310 LBS.
Page 85 CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES SECTION 3 EMERGENCY PROCEDURES TABLE OF CONTENTS Page Introduction ..........3-5 Airspeeds for Emergency Operation .
Page 86 SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 TABLE OF CONTENTS Page Avionics/Autopilot ........3-22 Pitch Trim Failure (Red PTRIM on PFD) .
Page 87 CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES TABLE OF CONTENTS Page Emergency Operation in Clouds ......3-36 Executing a 180°...
Page 88 SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 FAA APPROVED U.S.
Page 89: Introduction
CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES 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.
Page 90: Operating Procedures - 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.
Page 91 CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES 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.
Page 92: Engine Failures
SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 ENGINE FAILURES ENGINE FAILURE DURING TAKEOFF ROLL 1. POWER Lever......BETA RANGE 2.
Page 93 CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES ENGINE FAILURE DURING FLIGHT (Continued) 9. STBY ALT PWR Switch ......OFF 10.
Page 94: Engine Flameout During Flight
SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 ENGINE FLAMEOUT DURING FLIGHT IF GAS GENERATOR SPEED (N ) IS ABOVE 50%: POWER Lever ....... . . IDLE IGNITION Switch .
Page 95: No Starter Assist
CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES STARTER ASSIST (Preferred Procedure) (Continued) 12. STARTER Switch ....START and OBSERVE a. IGNITION ON CAS MSG ....CHECK ON b.
Page 96 SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 NO STARTER ASSIST (Continued) 6. FUEL CONDITION Lever ..... . CUTOFF 7. FUEL SHUTOFF Knob ..... ON (push in) 8.
Page 97: Forced Landings
CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES 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.
Page 98: Ditching
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) 1.
Page 99: Electrical Fire In Flight
CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES ELECTRICAL FIRE IN FLIGHT 1. STBY ALT PWR Switch ......OFF 2.
Page 100: Cabin Fire
SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 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.
Page 101: Wing Fire
CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES WING FIRE 1. PITOT/STATIC HEAT Switch ..... . . OFF 2. STALL HEAT Switch ......OFF 3.
Page 102: Engine Fire During Start On Ground (Red Engine Fire Cas Msg)
SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 ENGINE FIRE DURING START ON GROUND (Red ENGINE FIRE CAS MSG) 1. FUEL CONDITION Lever ..... . CUTOFF 2.
Page 103: Ice And Rain Protection
CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES ICE AND RAIN PROTECTION THE FOLLOWING WEATHER CONDITIONS CAN BE CONDUCIVE TO SEVERE IN-FLIGHT ICING - As Required by AD 96-09-15, Paragraph (a) (2): 1. Visible rain at temperatures below 0°C (32°F) ambient air temperature.
Page 104: Inadvertent Icing Encounter
SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 INADVERTENT ICING ENCOUNTER 1. IGNITION Switch ....... . . ON 2.
Page 105 CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES INADVERTENT ICING ENCOUNTER (Continued) With an ice accumulation of 1/4 inch or more on the wing leading edges, be prepared for a significantly higher power requirement, approach speed, stall speed, and longer landing roll.
Page 106: Avionics/Autopilot
SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 AVIONICS/AUTOPILOT PITCH TRIM FAILURE (Red PTRM ON PFD) 1. Control Wheel ......GRIP FIRMLY 2.
Page 107: Electrical Failures
CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES ELECTRICAL FAILURES GENERATOR FAILURE (Amber GENERATOR OFF CAS MSG) 1. BUS VOLTS ....... . . CHECK Monitor voltage and generator output.
Page 108 SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 GENERATOR FAILURE (Amber GENERATOR OFF CAS MSG) (Continued) IF GEN AMPS IS STILL ZERO: d. GENERATOR Switch ......TRIP e.
Page 109: Voltage High (Red Voltage High Cas Msg)
CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES VOLTAGE HIGH (Red VOLTAGE HIGH CAS MSG) 1. BUS VOLTS ....... MONITOR If BUS VOLTS increases past 32.5, expect the generator to...
Page 110 SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 VOLTAGE LOW (Red VOLTAGE LOW CAS MSG) (Continued) 8. Electrical Load....... REDUCE a.
Page 111: Engine Malfunctions
CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES ENGINE MALFUNCTIONS LOSS OF OIL PRESSURE (Red OIL PRESS LOW CAS MSG) 1. Oil Pressure Indication ..... . . MONITOR...
Page 112: Fuel System
SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 FUEL SYSTEM FUEL FLOW INTERRUPTION TO FUEL RESERVOIR (Red RSVR FUEL LOW CAS MSG) FUEL TANK SELECTORS ....BOTH ON .
Page 113 CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES START CONT AND/OR FUEL SELECT WARN CIRCUIT BREAKER(S) TRIPPED (Red FUEL SELECT OFF CAS MSG) 1. Tripped Circuit Breaker(s)......RESET...
Page 114: Expanded Emergency
SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 EXPANDED EMERGENCY ENGINE FAILURE If an engine failure occurs during the takeoff roll, the most important thing to do is stop the airplane on the remaining runway. Those extra items on the checklist will provide added safety after a failure of this type.
Page 115 CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES ENGINE FAILURE (Continued) While gliding toward a suitable landing area, an effort should be made to identify the cause of the power loss. An engine failure might be identified by abnormal temperatures, mechanical noises or high vibration levels in conjunction with the power loss.
Page 116 SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 ENGINE FAILURE (Continued) MAXIMUM GLIDE Figure 3-1 Propeller feathering is dependent on circumstances and is at the discretion of the pilot. However, if engine oil pressure drops below 15 psi, the propeller should be feathered.
Page 117 CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES ENGINE FAILURE (Continued) CAUTION T h e F U E L C O N D I T I O N L e v e r c a n b e m o v e d momentarily to CUTOFF and then back to LOW IDLE if overtemperature tendencies are encountered.
Page 118: Forced Landings
SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 FORCED LANDINGS If all attempts to restart the engine fail and a forced landing is imminent, select a suitable field and prepare for the landing as discussed under the Emergency Landing Without Engine Power checklist.
Page 119: Landing Without Elevator Control
CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES LANDING WITHOUT ELEVATOR CONTROL Using power lever and elevator trim control, trim for approximately 500 fpm descent with 20° flaps at 85 KIAS. Then control the glide angle by adjusting power. If required, make small trim changes to maintain approximately 85 KIAS as power is adjusted during the approach.
Page 120: Emergency Operation In Clouds
SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 SMOKE AND FIRE (Continued) Engine fires originating in flight must be controlled as quickly as possible in an attempt to prevent major structural damage. Immediately shut off all fuel to the engine and shut down the engine. Close the cabin heat firewall shutoff control and forward side vents to avoid drawing fire into the cabin, open the overhead vents, extend 20°...
Page 121: Executing A 180° Turn In Clouds (Ahrs Failure)
CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES EXECUTING A 180° TURN IN CLOUDS (AHRS FAILURE) Upon inadvertently entering the clouds, an immediate turn to reverse course and return to VFR conditions should be made as follows: DUAL AHRS FAILURE 1.
Page 122: Recovery From Spiral Dive In The Clouds (Ahrs Failure)
SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 DUAL AHRS FAILURE (Continued) Before descending into the clouds, prepare for a stabilized descent as follows: 1. Set rudder trim to neutral position. 2. Turn pitot heat on. 3. Set power for a 500 to 800 feet per minute rate of descent.
Page 123: Spins
CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES SPINS Intentional spins are prohibited in this airplane. Should an inadvertent spin occur, the following recovery technique can be used. 1. RETARD POWER LEVER TO IDLE POSITION. 2. PLACE AILERONS IN NEUTRAL POSITION.
Page 124: Engine Malfunctions
SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 ENGINE MALFUNCTIONS LOSS OF OIL PRESSURE The complete loss of oil pressure, as evidenced by the Red OIL PRESS LOW CAS MSG and confirmed by the oil pressure indication reading, implies that the pilot will eventually lose control of the propeller as the propeller springs and counterweights drive the propeller blades into feather.
Page 125: Emergency Power Lever Not Stowed
CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES FUEL CONTROL UNIT MALFUNCTION PNEUMATIC OR GOVERNOR SECTIONS A malfunction in the pneumatic or governor sections of the fuel control unit can cause engine power to decrease to minimum flow idle. Symptoms of this type failure would be an ITT indication in the typical idle range of 500°C to 600°C, N...
Page 126: Fuel System Malfunction/Inadvertent Fuel Flow Interruption Procedures
SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 FUEL SYSTEM MALFUNCTION/INADVERTENT FUEL FLOW INTERRUPTION PROCEDURES Fuel flows by gravity from the wing tanks, through fuel tank shutoff valves at the inboard end of each wing tank, and on to the reservoir located under the center cabin floorboard.
Page 127: Electrical Failures
CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES ELECTRICAL FAILURES GENERATOR OR MAIN BUS MALFUNCTIONS Illumination of the VOLTAGE LOW CAS MSG is a warning that the power distribution bus voltage is low enough to start discharging the battery. BUS VOLTS reading is used to verify the low bus voltage. A low or zero reading of the GEN AMPS confirms that the charge is insufficient or generator output current is zero.
Page 128: Loss Of Electrical Power
SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 LOSS OF ELECTRICAL POWER The design of the electrical power system, due to the self-exciting feature of the generator and the multiple protected busing system, minimizes the possibility of a complete electrical power loss. However,...
Page 129: Emergency Exits
CESSNA SECTION 3 MODEL 208B G1000 EMERGENCY PROCEDURES STANDBY ELECTRICAL SYSTEM MALFUNCTIONS (Continued) If, due to a power system malfunction, the standby electrical system is carrying part of the electrical load (more than 10 amps), the STBY PWR ON CAS MSG will be illuminated and the ALT AMPS in the EIS Systems page will indicate the amount of current being supplied by the standby electrical system.
Page 130 SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B G1000 EMERGENCY EXITS (TYPICAL) Figure 3-2 FAA APPROVED 208BPHBUS-01 3-46 U.S.
Page 131 CESSNA SECTION 3 MODEL 208B G1000 ABNORMAL PROCEDURES SECTION 3 ABNORMAL PROCEDURES Table Of Contents Page Abnormal Landing ........3-51 Landing with Flat Main Tire .
Page 132 SECTION 3 CESSNA ABNORMAL PROCEDURES MODEL 208B G1000 Table of Contents (Continued) BOTH ON GPS1/2........3-66 XSIDE ADC .
Page 133 CESSNA SECTION 3 MODEL 208B G1000 ABNORMAL PROCEDURES Table of Contents (Continued) Fuel ..........3-72 Auxilliary Fuel Boost Pump ON (Amber FUEL BOOST ON CAS MSG) .
Page 135: Abnormal Landing
CESSNA SECTION 3 MODEL 208B G1000 ABNORMAL PROCEDURES ABNORMAL LANDING LANDING WITH FLAT MAIN TIRE 1. Airplane....FLY (as desired to lighten fuel load) 2. FUEL SELECTORS ... . POSITION ONE SIDE OFF...
Page 136: Elevator Mistrim ( Ele Or Ele Indication Pfd)
SECTION 3 CESSNA ABNORMAL PROCEDURES MODEL 208B G1000 ELEVATOR MISTRIM ( ELE OR ELE INDICATION PFD) 1. Control Wheel ......GRIP FIRMLY 2.
Page 137: Rudder Mistrim ( Rud Or Rud Indication Pfd)
CESSNA SECTION 3 MODEL 208B G1000 ABNORMAL PROCEDURES RUDDER MISTRIM ( RUD OR RUD INDICATION PFD) 1. Rudder Pedals ......HOLD FIRMLY 2.
Page 138: Altitude Miscompare (Amber Alt Miscomp Indication Pfd)
SECTION 3 CESSNA ABNORMAL PROCEDURES MODEL 208B G1000 ALTITUDE MISCOMPARE (Amber MISCOMP INDICATION PFD) (Continued) IF PILOT PFD AND STANDBY ALTIMETER AGREE (COPILOT PFD STILL DIFFERS) 6. Compare indicated altitude to GPS altitude on MFD AUX-GPS STATUS page to aid in determining which primary system is most accurate.
Page 139: Airspeed Miscompare
CESSNA SECTION 3 MODEL 208B G1000 ABNORMAL PROCEDURES ALTITUDE MISCOMPARE (Amber MISCOMP INDICATION PFD) (Continued) 10. Reference ILS Decision Height to most accurate altimeter based on FAF crossing. WARNING TAWS alerts are based on GPS altitude and position information and are independent of ADC data. If a...
Page 140 SECTION 3 CESSNA ABNORMAL PROCEDURES MODEL 208B G1000 AIRSPEED MISCOMPARE (Amber MISCOMP INDICATION PFD) (Continued) IF STANDBY AIRSPEED AND COPILOT PFD AGREE (PILOT PFD DIFFERS) 2. SENSOR Softkey (pilot PFD) ....PRESS 3.
Page 141: Pitch/Roll/Heading Miscompare (Amber Pit/Rol/Hdg Miscomp Indication Pfd)
CESSNA SECTION 3 MODEL 208B G1000 ABNORMAL PROCEDURES PITCH/ROLL/HEADING MISCOMPARE (Amber PIT/ROLL/ HDG MISCOMP INDICATION PFD) This message is displayed when the G1000 detects a difference between the pilot’s and copilot’s attitude or heading information (displayed in the upper right of the PFD). Refer to GARMIN G1000 Cockpit Reference Guide for additional information.
Page 142: Display Unit Failure
SECTION 3 CESSNA ABNORMAL PROCEDURES MODEL 208B G1000 DISPLAY UNIT FAILURE This is indicated by a complete loss of image on a display. If only individual elements of the display are failed, refer to appropriate procedures for the individual failures.
Page 143: Dual Gps Failure (Amber "Dr" Or "Loi" On Hsi Indication Pfd)
CESSNA SECTION 3 MODEL 208B G1000 ABNORMAL PROCEDURES DUAL GPS FAILURE (Amber “DR” OR “LOI” ON HSI INDICATION PFD) IF ALTERNATE NAVIGATION SOURCES (ILS, LOC, VOR, DME, ADF) ARE AVAILABLE 1. Navigation....USE ALTERNATE SOURCES...
Page 144: Audio Panel Failure
SECTION 3 CESSNA ABNORMAL PROCEDURES MODEL 208B G1000 DUAL GPS FAILURE (Amber “DR” OR “LOI” ON HSI INDICATION PFD) (Continued) Loss of integrity (LOI) mode - active when the airplane is within 30 nautical miles of the destination airport (as calculated from the previous GPS or DR position).
Page 145: Loss Of Radio Tuning Functions
CESSNA SECTION 3 MODEL 208B G1000 ABNORMAL PROCEDURES LOSS OF RADIO TUNING FUNCTIONS 1. COM Frequency Toggle Button (affected PFD) ..PRESS AND HOLD (for 2 seconds) NOTE This procedure will tune the active COM field to the emergency frequency 121.5.
Page 146: Failed Attitude And/Or Heading (Attitude Fail And/Or Red "X" Over Heading Display On Pdf)
SECTION 3 CESSNA ABNORMAL PROCEDURES MODEL 208B G1000 FAILED AIRSPEED, ALTITUDE, AND/OR VERTICAL SPEED (Red "X" ON PFD AIRSPEED, ALTITUDE, AND/OR VERTICAL SPEED INDICATORS) (Continued) IF ONE SIDE ONLY 1. Affected PFD SENSOR Softkey ....PRESS 2.
Page 147 CESSNA SECTION 3 MODEL 208B G1000 ABNORMAL PROCEDURES FAILED ATTITUDE AND/OR HEADING (ATTITUDE FAIL AND/OR Red "X" OVER HEADING DISPLAY ON PFD) (Continued) NOTE • The autopilot will disconnect and may not be re- engaged. • Reference the GPS track on MFD/PFD map to improve situational awareness.
Page 148: Loss Of Navigation Data
SECTION 3 CESSNA ABNORMAL PROCEDURES MODEL 208B G1000 LOSS OF NAVIGATION DATA (LATERAL DEVIATION BAR NOT PRESENT AND/OR GLIDESLOPE INDEX CLEARS) This indicates a loss of data from the selected NAV source. Refer to GARMIN G1000 Cockpit Reference Guide for additional information.
Page 149: Inaccurate Flight Director Display
CESSNA SECTION 3 MODEL 208B G1000 ABNORMAL PROCEDURES INACCURATE FLIGHT DIRECTOR DISPLAY Indicated by one or both flight directors commanding attitude contrary to intended flight path. 1. AP/TRIM DISC Button ......PRESS 2.
Page 150: Both On Gps1/2
SECTION 3 CESSNA ABNORMAL PROCEDURES MODEL 208B G1000 BOTH ON AHRS 1/2 1. PFD SENSOR softkey....PRESS on PFD (displaying data from opposite side AHRS) 2.
Page 151: Doors
CESSNA SECTION 3 MODEL 208B G1000 ABNORMAL PROCEDURES MULTI-FUNCTION DISPLAY FAN FAILED (White MFD FAN FAIL CAS MSG) 1. DECK SKIN FAN Circuit Breaker ....CHECK IN...
Page 152: Lower Half Of Passenger Airstair Door Open
SECTION 3 CESSNA ABNORMAL PROCEDURES MODEL 208B G1000 LOWER HALF OF PASSENGER AIRSTAIR DOOR OPEN 1. Airspeed ....MAINTAIN LESS THAN 100 KIAS 2. Flight Controls ..MANEUVER (for return for landing) 3.
Page 153: Standby Power Inoperative (Amber Stby Pwr Inop Cas Msg)
CESSNA SECTION 3 MODEL 208B G1000 ABNORMAL PROCEDURES STANDBY POWER INOPERATIVE (Amber STBY PWR INOP CAS MSG) 1. STBY ALT PWR Switch ..... CHECK ON IF CAS MESSAGE REMAINS: 2.
Page 154: Engine
SECTION 3 CESSNA ABNORMAL PROCEDURES MODEL 208B G1000 ENGINE GEAR BOX CONTAMINATION (Amber CHIP DETECT CAS MSG) 1. Engine Indications ....CAREFULLY MONITOR (for abnormal oil pressure,...
Page 155 CESSNA SECTION 3 MODEL 208B G1000 ABNORMAL PROCEDURES FLAPS FAIL TO EXTEND OR RETRACT 1. FLAP MOTOR and STBY FLAP MOTOR Circuit Breakers ......CHECK IN 2.
Page 156: Fuel
SECTION 3 CESSNA ABNORMAL PROCEDURES MODEL 208B G1000 FUEL AUXILIARY FUEL BOOST PUMP ON (Amber FUEL BOOST ON CAS MSG) 1. FUEL BOOST Switch ..... . . CHECK ON IF CONDITIONS DO NOT WARRANT ITS USE: 2.
Page 157: Ice And Rain Protection
CESSNA SECTION 3 MODEL 208B G1000 ABNORMAL PROCEDURES ICE AND RAIN PROTECTION PITOT/ STATIC HEAT FAILURE (Amber L, R OR L-R P/S HEAT CAS MSG) 1. PITOT HEAT Circuit Breakers (L and R) ..CHECK IN...
Page 158 SECTION 3 CESSNA ABNORMAL PROCEDURES MODEL 208B G1000 PITOT STATIC HEATER FAILURE (Amber L, R OR L-R P/S HEATER CAS MSG) (Continued) IF ALTITUDES AGREE 1. Airspeed ..120 KIAS MINIMUM (on slowest indicator) 2.
Page 159 CESSNA SECTION 3 MODEL 208B G1000 ABNORMAL PROCEDURES PITOT STATIC HEATER FAILURE (Amber L, R OR L-R P/S HEATER CAS MSG) (Continued) IF PILOT PFD AND STANDBY ALTIMETER AGREE (COPILOT PFD DIFFERS) 1. Autopilot ....DISENGAGE (altitude hold mode) 2.
Page 160 SECTION 3 CESSNA ABNORMAL PROCEDURES MODEL 208B G1000 PITOT STATIC HEATER FAILURE (Amber L, R OR L-R P/S HEATER CAS MSG) (Continued) IF UNABLE TO IDENTIFY ACCURATE ALTITUDE SOURCE 1. Land as soon as practical. Consider diversion to visual conditions.
Page 161: Stall Heat Failure (Amber Stall Heat Cas Msg)
CESSNA SECTION 3 MODEL 208B G1000 ABNORMAL PROCEDURES STALL HEAT FAILURE (Amber STALL HEAT CAS MSG) If ice is observed forming on the stall warning vane or its mounting plate: 1. STALL WARN Circuit Breaker ....CHECK...
Page 162: Expanded Abnormal
SECTION 3 CESSNA ABNORMAL PROCEDURES MODEL 208B G1000 EXPANDED ABNORMAL ELEVATOR MISTRIM Indicates a mistrim of the elevator while the autopilot is engaged. The autopilot will normally trim automatically as required. However, during rapid acceleration, deceleration, or configuration changes, momentary illumination of this message may occur accompanied by minor fluctuations in the flight path.
Page 163: Failed Attitude And/Or Heading
CESSNA SECTION 3 MODEL 208B G1000 ABNORMAL PROCEDURES FAILED ATTITUDE AND/OR HEADING This message indicates a loss of pitch, roll, and/or heading information from AHRS. Refer to GARMIN G1000 Cockpit Reference Guide for additional information. Interference from GPS repeaters operating inside nearby hangars can cause an intermittent loss of attitude and heading displays while the aircraft is on the ground.
Page 164: Xside Ahrs
SECTION 3 CESSNA ABNORMAL PROCEDURES MODEL 208B G1000 XSIDE AHRS This message is displayed on both PFDs and indicates that both PFDs are displaying data from the opposite side Attitude Heading Reference System. Normally the pilot’s side displays ADC1 and the copilot’s side displays ADC 2.
Page 165 CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES NORMAL PROCEDURES Table of Contents Page Introduction ..........4-3 Speeds for Normal Operation .
Page 166 SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 Table of Contents (Continued) Page After Landing ......... 4-31 Shutdown and Securing Airplane .
Page 167: Introduction
CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES INTRODUCTION Section 4 provides checklist and amplified procedures for the conduct of normal operation. Normal procedures associated with optional systems can be found in Section 9. WARNING There is no substitute for proper and complete...
Page 168 SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 AIRSPEEDS FOR NORMAL OPERATION (Continued) BALKED LANDING: Takeoff Power, Flaps 20° ......80 KIAS...
Page 169: Preflight Inspection Warnings
CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES PREFLIGHT INSPECTION WARNINGS WARNING • Visually check airplane for general condition during walk-around inspection and remove any inlet, exit or exhaust covers. If cargo pod is installed, check its installation for security during the walk-around inspection.
Page 170: Preflight Inspection
SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 CHECKLIST PROCEDURES PREFLIGHT INSPECTION Figure 4-1 CABIN 1. PITOT/ STATIC Tube Covers ....REMOVED 2. Pilot's Operating Handbook..ACCESSIBLE TO PILOT 3.
Page 171 CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES CABIN (Continued) 6. All Switches ........OFF 7.
Page 172: Left Side
SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 LEFT SIDE 1. WING LIGHT ....CHECK (verify condition) 2. Fuel Reservoir Drain (bottom of fuselage or left side of cargo pod) .
Page 173 CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES LEFT WING Leading Edge (Continued) WARNING • Prior to any flight in known or forecast icing conditions, check that PITOT/STATIC tube(s) and STALL warning heaters are warm to touch after turning PITOT/STATIC and STALL HEAT switches ON for 30 seconds, then OFF.
Page 174 SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 LEFT WING Trailing Edge 1. Fuel Tank Vent ....... CHECK (verify no obstructions) 2.
Page 175: Measured Fuel Depth Vs. Fuel Quantity
CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES MEASURED FUEL DEPTH VS. FUEL QUANTITY Universal XL Fuel Quantity Generic Fuel Fuel Quantity Fuel Gage Gage-Inches Gage Scale Gallons Pounds Inches Gallons Pounds 0.50 87.4 0.50 88.4 0.75 91.1 0.75 92.6 1.00...
Page 176: Empennage
SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 EMPENNAGE WARNING It is essential in cold weather to remove even the smallest accumulations of frost, ice, snow, or slush from the tail and control surfaces. Exercise caution to avoid distorting the vortex generators on horizontal stabilizer while deicing.
Page 177: Right Wing Trailing Edge
CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES RIGHT WING Trailing Edge 1. Flap........CHECK (verify condition and security) 2.
Page 178 SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 RIGHT WING Leading Edge (Continued) 1. NAV and STROBE Lights ..... . . CHECK (verify condition and cleanliness) 2.
Page 179: Nose
CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES NOSE WARNING It is essential in cold weather to remove even the smallest accumulations of frost, ice, snow, or slush from the propeller blades and spinner, and the air inlets (starter/generator, oil cooler and engine inlets).
Page 180 SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 NOSE (Continued) 11. Propeller ........CHECK Inspect blades for nicks, gouges, looseness of material, erosion and cracks.
Page 181: Before Starting Engine
CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES NOSE (Continued) 21. Brake Fluid Reservoir ....CHECK LEVEL 22. Cowling ....CLOSE and LATCH (left side) 23.
Page 182: Starting Engine (Battery Start)
SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 BEFORE STARTING ENGINE (Continued) CAUTION Leaving the BLEED AIR HEAT Switch ON (up) can result in a hot start or abnormal acceleration to idle. 15. CABIN HEAT MIXING AIR Control ....FLT-PUSH 16.
Page 183 CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES STARTING ENGINE (Battery Start) (Continued) 7. Propeller Area....... . . CLEAR 8.
Page 184: Starting Engine (External Power Start)
SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 STARTING ENGINE (External Power Start) (24-28 Volt, Minimum 800 Amp and Maximum 1700 Amp Capacity) 1. BATTERY Switch ....... . . ON 2.
Page 185 CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES STARTING ENGINE (External Power Start) (Continued) 19. FUEL CONDITION Lever ..... LOW IDLE a.
Page 186: Taxiing
SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 TAXIING 1. Brakes ........CHECK...
Page 187 CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES BEFORE TAKEOFF (Continued) 14. Overspeed Governor ......CHECK (first flight of the day and after maintenance) a.
Page 188 SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 BEFORE TAKEOFF (Continued) 17. Manual Electric Pitch Trim (MEPT) ..CHECK and SET a. Push both sides of trim switch NOSE DOWN (verify correct trim wheel and pointer movement). Press AP DISC/TRIM INTER Switch (verify trim wheel stops moving).
Page 189: Takeoff
CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES BEFORE TAKEOFF (Continued) WARNING • When ground icing conditions are present, a pre- takeoff visual and tactile check should be conducted by the pilot in command within five minutes of takeoff, preferably just prior to taxiing onto the active runway.
Page 190: Short Field Takeoff
SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 SHORT FIELD TAKEOFF 1. WING FLAPS Handle ......20°...
Page 191: Maximum Performance Climb
CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES CRUISE CLIMB (Continued) 6. POWER Lever ........SET...
Page 192: Cruise
SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 CRUISE 1. Ice Protection (if installed) ....AS REQUIRED a. PITOT/STATIC HEAT . ON (when OAT is below 5°C (41°F)) b.
Page 193: Before Landing
CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES DESCENT (Continued) CAUTION Set PROP RPM Lever at 1900 RPM prior to beginning any instrument approach procedure. 6. POWER Lever ......AS REQUIRED...
Page 194: Short Field Landing
SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 SHORT FIELD LANDING 1. WING FLAPS Handle ......FULL 2.
Page 195: After Landing
CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES AFTER LANDING 1. WING FLAPS Handle ......UP 2.
Page 196: Shutdown And Securing Airplane
SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 SHUTDOWN AND SECURING AIRPLANE 1. PARKING BRAKE ....... . SET 2.
Page 197: Amplified Procedures
CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES AMPLIFIED PROCEDURES PREFLIGHT INSPECTION The Preflight Inspection, described in Figure 4-1 and adjacent checklist, is recommended. If the airplane has been in extended storage, has had recent major maintenance, or has been operated from rough or unprepared surfaces, an extensive exterior inspection is recommended.
Page 198: Before Starting Engine
SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 PREFLIGHT INSPECTION (Continued) If any water is detected in the fuel system, the inboard fuel tank sump and external sump quick-drain valves, fuel reservoir quick-drain valve, and fuel filter quick-drain valve should all be thoroughly drained until there is no evidence of water or sediment contamination.
Page 199 CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES BEFORE STARTING ENGINE (Continued) The Before Starting Engine checklist procedures should be followed closely to assure a satisfactory engine start. Most of the checklist items are self-explanatory. Those items that may require further explanation are noted in the following discussion.
Page 200: Starting Engine
SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 BEFORE STARTING ENGINE (Continued) Before starting the engine, the POWER Lever is placed at the IDLE position (against the BETA gate), the propeller control lever is moved to the MAX RPM position (full forward), and the FUEL CONDITION Lever is stowed in the CUTOFF position.
Page 201 CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES STARTING ENGINE (Continued) After the engine reaches stabilized idle (52% N or above), return the starter switch to the OFF position. With a cold engine or after making a battery start (high initial generator load into battery), it may be...
Page 202 SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 STARTING ENGINE (Continued) • When an external power unit is used, make sure the unit is negatively grounded and regulated to 28 volts DC with a capability of providing a minimum of 800 amperes during the starting cycle.
Page 203: Engine Clearing Procedures (Dry Motoring Run)
CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES ENGINE CLEARING PROCEDURES (DRY MOTORING RUN) The following procedure is used to clear an engine at any time when it is deemed necessary to remove internally trapped fuel and vapor, or if there is evidence of a fire within the engine.
Page 204: Engine Ignition Procedures
SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 ENGINE IGNITION PROCEDURES For most operations, the IGNITION Switch is left in the NORM position. With the switch in this position, ignition is on only when the starter switch is in the START position.
Page 205: Taxiing
CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES TAXIING POWER Lever BETA range can be used during taxi to control taxi speed and improve brake life. A leaf spring is installed in the control quadrant which the POWER Lever contacts and provides the pilot with a noticeable "feel".
Page 206: Taxiing Diagram
SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 TAXIING DIAGRAM NOTE Strong quartering tail winds require caution. Avoid excessive use of power and sharp braking when the airplane is in this attitude. Use the steerable nose wheel and rudder to maintain direction.
Page 207: Before Takeoff
CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES BEFORE TAKEOFF The FUEL TANK SELECTORS are normally both ON for takeoff and all flight operations. However, one side can be turned OFF as required to balance the fuel load. WARNING •...
Page 208: Takeoff
SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 TAKEOFF POWER SETTING Refer to the Maximum Engine Torque for Takeoff chart in Section 5 to determine the torque corresponding to the surface altitude and OAT conditions. This torque should be obtainable without exceeding 805°C ITT or 101.6% N...
Page 209: Type Ii, Type Iii Or Type Iv Anti-Ice Fluid Takeoff
CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES SHORT FIELD TAKEOFF (Continued) After clearing the obstacle, and reaching a safe altitude, the flaps can be retracted slowly as the airplane accelerates to the normal climb airspeed. Minimum ground roll takeoffs are accomplished by using 20° flaps, lifting the nose wheel off the ground as soon as practical and leaving the ground in a slightly tail-low attitude.
Page 210 SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 ENROUTE CLIMB (Continued) At lower altitudes and cool outside air temperatures (below approximately 10,000 feet), the engine will reach the torque limit before reaching the ITT or N limit. As the climb progresses and the torque is...
Page 211: Cruise
CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES CRUISE Normal cruise is performed using any desired power setting up to the maximum cruise power (observe ITT, torque, and N cruise limits). Do not exceed the maximum cruise torque or 740°C ITT shown in Cruise Performance or Cruise Maximum Torque charts in Section 5 for the particular altitude and temperature.
Page 212 SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 SAMPLE CRUISE PERFORMANCE CHART PARAMETERS: Standard Conditions 1900 RPM Zero Wind ALTITUDE Maximum Cruise Power Maximum Range Power (Feet) KTAS NM/1000 LBS KTAS NM/1000 LBS 5,000 10,000 15,000 20,000 (WITHOUT CARGO POD)
Page 213 CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES CRUISE (Continued) These systems are designed to prevent ice formation, rather than removing it after it has formed. Even if the airplane is equipped with the "Flight Into Known Icing" package, accumulation of some airframe ice is unavoidable;...
Page 214: Stalls
SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 CRUISE (Continued) WARNING • Operation maximum allowable operating altitude predicated availability and use of supplemental oxygen above 12,500 feet as specified by 14 CFR 91.211. • Smoking is prohibited when using oxygen. Oil,...
Page 215: Landing
CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES LANDING NORMAL LANDING Normal landing approaches can be made with power-on or idle power with any flap setting desired and the PROP RPM Lever set at 1900. Use of FULL flaps is normally preferred to minimize touchdown speed and subsequent need for braking.
Page 216: Crosswind Landing
SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 SHORT FIELD LANDING (Continued) The landing performance in Section 5 is based on the above procedure. A reduction in ground roll of approximately 10% will result from the use of reverse thrust (POWER Lever full aft to provide increased power from the gas generator and a reverse thrust propeller blade angle).
Page 217: After Shutdown
CESSNA SECTION 4 MODEL 208B G1000 NORMAL PROCEDURES AFTER SHUTDOWN If dusty conditions exist or if the last flight of the day has been completed, install engine inlet covers to protect the engine from debris. The covers can be installed after the engine has cooled (ITT indicator showing "off scale"...
Page 218: Engine Compressor Stalls
SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B G1000 ENGINE COMPRESSOR STALLS An engine compressor stall can be noted by a single or multiple loud popping noise from the engine compartment. This situation can be resolved by reducing the engine power to a point where the "popping"...
Page 219 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE PERFORMANCE TABLE OF CONTENTS Page Introduction ..........5-3 Use of Performance Charts .
Page 220 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 TABLE OF CONTENTS (Continued) Page Cruise Performance ........5-35 Cruise Maximum Torque .
Page 221: Introduction
CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE INTRODUCTION Performance data charts on the following pages are presented so that you may know what to expect from the airplane under various conditions, and also, to facilitate the planning of flights in detail and with reasonable accuracy.
Page 222: Sample Problem
SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 SAMPLE PROBLEM The following sample flight problem utilizes information from the various charts to determine the predicted performance data for a typical flight of an airplane equipped with a cargo pod. A similar calculation can be made for an airplane without a cargo pod using charts identified as appropriate for this configuration.
Page 223: Takeoff
CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE TAKEOFF The Takeoff Distance chart shows distances that are based on the short field technique. Conservative distances can be established by reading the chart at the next higher value of weight, altitude and temperature.
Page 224: Cruise
SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 CRUISE The cruising altitude should be selected based on a consideration of trip length, winds aloft, and the airplane’s performance. A cruising altitude and the expected wind enroute have been given for this sample problem.
Page 225 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE FUEL REQUIRED (Continued) Similarly, Time, Fuel, and Distance to Descend chart shows that a descent from 12,000 feet to sea level results in the following: Time 15 Minutes Fuel 72 Pounds Distance 43 Nautical Miles The distances shown on the climb and descent charts are for zero wind.
Page 226: Landing
SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 FUEL REQUIRED (Continued) The total estimated fuel required is as follows: Engine start, taxi, and takeoff 35 Pounds Climb +94 Pounds Cruise +1194 Pounds Descent +72 Pounds Reserve +230 Pounds Total fuel required...
Page 227 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-1 (Sheet 1 of 2) FAA APPROVED 208BPHBUS-00 U.S.
Page 228 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-1 (Sheet 2) FAA APPROVED 208BPHBUS-00 U.S. 5-10...
Page 229 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-2 FAA APPROVED 208BPHBUS-00 5-11 U.S.
Page 230: Pressure Conversion
SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 PRESSURE CONVERSION Example: Pressure = 29.55 inches of mercury. Pressure = 1000.6 millibars. Figure 5-3 FAA APPROVED 208BPHBUS-00 U.S. 5-12...
Page 231 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE TEMPERATURE CONVERSION CHART Figure 5-4 FAA APPROVED 208BPHBUS-00 5-13 U.S.
Page 232: Isa Conversion And Operating Temperature Limits
SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 ISA CONVERSION AND OPERATING TEMPERATURE LIMITS CAUTION Do not Operate in shaded area of chart. Figure 5-5 FAA APPROVED 208BPHBUS-00 U.S. 5-14...
Page 233 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-6 FAA APPROVED 208BPHBUS-00 5-15 U.S.
Page 234: Wind Components
SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 WIND COMPONENTS NOTE Maximum demonstrated crosswind velocity is 20 knots (not a limitation). Figure 5-7 FAA APPROVED 208BPHBUS-00 U.S. 5-16...
Page 235: Maximum Engine Torque For Takeoff
CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE MAXIMUM ENGINE TORQUE FOR TAKEOFF CONDITIONS: 1900 RPM 60 KIAS INERTIAL SEPARATOR NORMAL NOTE 1. Torque increases approximately 10 Ft-Lbs from 0 to 60 KIAS. 2. Torque on this chart shall be achieved without exceeding 805°C ITT or 101.6 percent N...
Page 236 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 MAXIMUM ENGINE TORQUE FOR CLIMB CONDITIONS: 1900 RPM KIAS INERTIAL SEPARATOR NORMAL NOTE 1. Torque on this chart shall be achieved without exceeding 765°C ITT or 101.6 percent N 2. With the inertial separator in BYPASS, decrease torque setting by 100 Ft-Lbs.
Page 237 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-10 (Sheet 1 of 5) FAA APPROVED 208BPHBUS-00 5-19 U.S.
Page 238 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-10 (Sheet 2) FAA APPROVED 208BPHBUS-00 U.S. 5-20...
Page 239 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-10 (Sheet 3) FAA APPROVED 208BPHBUS-00 5-21 U.S.
Page 240 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-10 (Sheet 4) FAA APPROVED 208BPHBUS-00 U.S. 5-22...
Page 241 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-10 (Sheet 5) FAA APPROVED 208BPHBUS-00 5-23 U.S.
Page 242 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-11 (Sheet 1 of 3) FAA APPROVED 208BPHBUS-00 U.S. 5-24...
Page 243 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-11 (Sheet 2) FAA APPROVED 208BPHBUS-00 5-25 U.S.
Page 244 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-11 (Sheet 3) FAA APPROVED 208BPHBUS-00 U.S. 5-26...
Page 245 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-12 FAA APPROVED 208BPHBUS-00 5-27 U.S.
Page 246 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-13 FAA APPROVED 208BPHBUS-00 U.S. 5-28...
Page 247 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-14 FAA APPROVED 208BPHBUS-00 5-29 U.S.
Page 248 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-15 FAA APPROVED 208BPHBUS-00 U.S. 5-30...
Page 249 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-16 FAA APPROVED 208BPHBUS-00 5-31 U.S.
Page 250 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-17 FAA APPROVED 208BPHBUS-00 U.S. 5-32...
Page 251 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-18 (Sheet 1 of 2) 208BPHBUS-01 5-33 U.S.
Page 252 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-18 (Sheet 2) 208BPHBUS-01 U.S. 5-34...
Page 253 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-19 (Sheet 1 of 11) 208BPHBUS-01 5-35 U.S.
Page 254 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-19 (Sheet 2) 208BPHBUS-01 U.S. 5-36...
Page 255 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-19 (Sheet 3) 208BPHBUS-01 5-37 U.S.
Page 256 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-19 (Sheet 4) 208BPHBUS-01 U.S. 5-38...
Page 257 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-19 (Sheet 5) 208BPHBUS-01 5-39 U.S.
Page 258 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-19 (Sheet 6) 208BPHBUS-01 U.S. 5-40...
Page 259 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-19 (Sheet 7) 208BPHBUS-01 5-41 U.S.
Page 260 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-19 (Sheet 8) 208BPHBUS-01 U.S. 5-42...
Page 261 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-19 (Sheet 9) 208BPHBUS-01 5-43 U.S.
Page 262 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-19 (Sheet 10) 208BPHBUS-01 U.S. 5-44...
Page 263 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-19 (Sheet 11) 208BPHBUS-01 5-45 U.S.
Page 264 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-20 (Sheet 1 of 7) 208BPHBUS-01 U.S. 5-46...
Page 265 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-20 (Sheet 2) 208BPHBUS-01 5-47 U.S.
Page 266 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-20 (Sheet 3) 208BPHBUS-01 U.S. 5-48...
Page 267 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-20 (Sheet 4) 208BPHBUS-01 5-49 U.S.
Page 268 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-20 (Sheet 5) 208BPHBUS-01 U.S. 5-50...
Page 269 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-20 (Sheet 6) 208BPHBUS-01 5-51 U.S.
Page 270 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-20 (Sheet 7) 208BPHBUS-01 U.S. 5-52...
Page 271 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE CARGO POD INSTALLED FUEL AND TIME REQUIRED MAXIMUM CRUISE POWER (40-200 Nautical Miles) CONDITIONS: 8750 Pounds Standard Temperature 1900 RPM INERTIAL SEPARATOR NORMAL NOTE 1. Fuel required includes the fuel used for engine start, taxi, takeoff, maximum climb from sea level, descent to sea level and 45 minutes reserve.
Page 272 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 CARGO POD INSTALLED FUEL AND TIME REQUIRED MAXIMUM CRUISE POWER (200-1000 Nautical Miles) CONDITIONS: 8750 Pounds Standard Temperature 1900 RPM INERTIAL SEPARATOR NORMAL NOTE 1. Fuel required includes the fuel used for engine start, taxi, takeoff, maximum climb from sea level, descent to sea level and 45 minutes reserve.
Page 273 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE CARGO POD INSTALLED FUEL AND TIME REQUIRED MAXIMUM RANGE POWER (40-200 Nautical Miles) CONDITIONS: 8750 Pounds Standard Temperature 1900 RPM INERTIAL SEPARATOR NORMAL NOTE 1. Fuel required includes the fuel used for engine start, taxi, takeoff, maximum climb from sea level, descent to sea level and 45 minutes reserve.
Page 274 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 CARGO POD INSTALLED FUEL AND TIME REQUIRED MAXIMUM RANGE POWER (200-1000 Nautical Miles) CONDITIONS: 8750 Pounds Standard Temperature 1900 RPM INERTIAL SEPARATOR NORMAL NOTE 1. Fuel required includes the fuel used for engine start, taxi, takeoff, maximum climb from sea level, descent to sea level and 45 minutes reserve.
Page 275 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE CARGO POD INSTALLED RANGE PROFILE 45 MINUTES RESERVE 2224 POUNDS USABLE FUEL CONDITIONS: 8750 Pounds Standard Temperature 1900 RPM INERTIAL SEPARATOR NORMAL Zero Wind NOTE 1. This chart allows for the fuel used for engine start, taxi, takeoff, climb and descent.
Page 276 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 CARGO POD INSTALLED ENDURANCE PROFILE 45 MINUTES RESERVE 2224 POUNDS USABLE FUEL CONDITIONS: 8750 Pounds Standard Temperature 1900 RPM INERTIAL SEPARATOR NORMAL NOTE 1. This chart allows for the fuel used for engine start, taxi, takeoff, climb and descent.
Page 277 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-25 208BPHBUS-01 5-59 U.S.
Page 278 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-26 (Sheet 1 of 5) FAA APPROVED 208BPHBUS-00 U.S. 5-60...
Page 279 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-26 (Sheet 2) FAA APPROVED 208BPHBUS-00 5-61 U.S.
Page 280 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-26 (Sheet 3) FAA APPROVED 208BPHBUS-00 U.S. 5-62...
Page 281 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-26 (Sheet 4) FAA APPROVED 208BPHBUS-00 5-63 U.S.
Page 282 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-26 (Sheet 5) FAA APPROVED 208BPHBUS-00 U.S. 5-64...
Page 283 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-27 (Sheet 1 of 5) FAA APPROVED 208BPHBUS-00 5-65 U.S.
Page 284 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-27 (Sheet 2) FAA APPROVED 208BPHBUS-00 U.S. 5-66...
Page 285 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-27 (Sheet 3) FAA APPROVED 208BPHBUS-00 5-67 U.S.
Page 286 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-27 (Sheet 4) FAA APPROVED 208BPHBUS-00 U.S. 5-68...
Page 287 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-27 (Sheet 5) FAA APPROVED 208BPHBUS-00 5-69 U.S.
Page 288 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-28 (Sheet 1 of 3) FAA APPROVED 208BPHBUS-00 U.S. 5-70...
Page 289 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-28 (Sheet 2) FAA APPROVED 208BPHBUS-00 5-71 U.S.
Page 290 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-28 (Sheet 3) FAA APPROVED 208BPHBUS-00 U.S. 5-72...
Page 291 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-29 FAA APPROVED 208BPHBUS-00 5-73 U.S.
Page 292 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-30 FAA APPROVED 208BPHBUS-00 U.S. 5-74...
Page 293 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-31 FAA APPROVED 208BPHBUS-00 5-75 U.S.
Page 294 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-32 FAA APPROVED 208BPHBUS-00 U.S. 5-76...
Page 295 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-33 FAA APPROVED 208BPHBUS-00 5-77 U.S.
Page 296 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-34 FAA APPROVED 208BPHBUS-00 U.S. 5-78...
Page 297 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-35 (Sheet 1 or 2) 208BPHBUS-01 5-79 U.S.
Page 298 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-35 (Sheet 2) 208BPHBUS-01 U.S. 5-80...
Page 299 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-36 (Sheet 1 of 12) 208BPHBUS-01 5-81 U.S.
Page 300 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-36 (Sheet 2) 208BPHBUS-01 U.S. 5-82...
Page 301 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-36 (Sheet 3) 208BPHBUS-01 5-83 U.S.
Page 302 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-36 (Sheet 4) 208BPHBUS-01 U.S. 5-84...
Page 303 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-36 (Sheet 5) 208BPHBUS-01 5-85 U.S.
Page 304 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-36 (Sheet 6) 208BPHBUS-01 U.S. 5-86...
Page 305 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-36 (Sheet 7) 208BPHBUS-01 5-87 U.S.
Page 306 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-36 (Sheet 8) 208BPHBUS-01 U.S. 5-88...
Page 307 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-36 (Sheet 9) 208BPHBUS-01 5-89 U.S.
Page 308 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-36 (Sheet 10) 208BPHBUS-01 U.S. 5-90...
Page 309 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-36 (Sheet 11) 208BPHBUS-01 5-91 U.S.
Page 310 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-36 (Sheet 12) 208BPHBUS-01 U.S. 5-92...
Page 311 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-37 (Sheet 1 of 7) 208BPHBUS-01 5-93 U.S.
Page 312 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-37 (Sheet 2) 208BPHBUS-01 U.S. 5-94...
Page 313 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-37 (Sheet 3) 208BPHBUS-01 5-95 U.S.
Page 314 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-37 (Sheet 4) 208BPHBUS-01 U.S. 5-96...
Page 315 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-37 (Sheet 5) 208BPHBUS-01 5-97 U.S.
Page 316 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-37 (Sheet 6) 208BPHBUS-01 U.S. 5-98...
Page 317 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-37 (Sheet 7) 208BPHBUS-01 5-99 U.S.
Page 318 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 WITHOUT CARGO POD FUEL AND TIME REQUIRED MAXIMUM CRUISE POWER (40-200 Nautical Miles) CONDITIONS: 8750 Pounds Standard Temperature 1900 RPM INERTIAL SEPARATOR NORMAL NOTE 1. Fuel required includes the fuel used for engine start, taxi, takeoff, maximum climb from sea level, descent to sea level and 45 minutes reserve.
Page 319 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE WITHOUT CARGO POD FUEL AND TIME REQUIRED MAXIMUM CRUISE POWER (200-1000 Nautical Miles) CONDITIONS: 8750 Pounds Standard Temperature 1900 RPM INERTIAL SEPARATOR NORMAL NOTE 1. Fuel required includes the fuel used for engine start, taxi, takeoff, maximum climb from sea level, descent to sea level and 45 minutes reserve.
Page 320 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 WITHOUT CARGO POD FUEL AND TIME REQUIRED MAXIMUM RANGE POWER (40-200 Nautical Miles) CONDITIONS: 8750 Pounds Standard Temperature 1900 RPM INERTIAL SEPARATOR NORMAL NOTE 1. Fuel required includes the fuel used for engine start, taxi, takeoff, maximum climb from sea level, descent to sea level and 45 minutes reserve.
Page 321 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE WITHOUT CARGO POD FUEL AND TIME REQUIRED MAXIMUM RANGE POWER (200-1000 Nautical Miles) CONDITIONS: 8750 Pounds Standard Temperature 1900 RPM INERTIAL SEPARATOR NORMAL NOTE 1. Fuel required includes the fuel used for engine start, taxi, takeoff, maximum climb from sea level, descent to sea level and 45 minutes reserve.
Page 322 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 WITHOUT CARGO POD RANGE PROFILE 45 MINUTES RESERVE 2224 POUNDS USABLE FUEL CONDITIONS: 8750 Pounds Standard Temperature 1900 RPM INERTIAL SEPARATOR NORMAL Zero Wind NOTE 1. This chart allows for the fuel used for engine start, taxi, takeoff, climb and descent.
Page 323 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE WITHOUT CARGO POD ENDURANCE PROFILE 45 MINUTES RESERVE 2224 POUNDS USABLE FUEL CONDITIONS: 8750 Pounds Standard Temperature 1900 RPM INERTIAL SEPARATOR NORMAL NOTE 1. This chart allows for the fuel used for engine start, taxi, takeoff, climb and descent.
Page 324 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-42 208BPHBUS-01 U.S. 5-106...
Page 325 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-43 (Sheet 1 of 5) FAA APPROVED 208BPHBUS-00 5-107 U.S.
Page 326 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-43 (Sheet 2) FAA APPROVED 208BPHBUS-00 U.S. 5-108...
Page 327 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-43 (Sheet 3) FAA APPROVED 208BPHBUS-00 5-109 U.S.
Page 328 SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 Figure 5-43 (Sheet 4) FAA APPROVED 208BPHBUS-00 U.S. 5-110...
Page 329 CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE Figure 5-43 (Sheet 5) FAA APPROVED 208BPHBUS-00 5-111/5-112 U.S.
Page 331 CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST WEIGHT AND BALANCE/ EQUIPMENT LIST TABLE OF CONTENTS Page Introduction ..........6-3 Airplane Weighing Form .
Page 333: Introduction
CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST INTRODUCTION This section describes the procedure for establishing the basic empty weight and moment of the airplane. Sample forms are provided for reference. Procedures for calculating the weight and moment for various operations are also provided.
Page 334: Airplane Weighing Form
SECTION 6 CESSNA WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 AIRPLANE WEIGHING FORM Figure 6-1 208BPHBUS-00 U.S.
Page 335 CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST WEIGHT AND BALANCE RECORD Figure 6-2 208BPHBUS-00 U.S.
Page 336: Airplane Weighing Procedures
SECTION 6 CESSNA WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 INTRODUCTION (Continued) A properly loaded airplane, however, will perform as intended. Before the airplane is licensed, a basic empty weight, center of gravity (C.G.) and moment are computed. Specific information regarding the weight,...
Page 337 CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST AIRPLANE WEIGHING PROCEDURES (Continued) 2. Leveling: a. Place scales under each wheel (minimum scale capacity, 2000 pounds nose, 4000 pounds each main). The main landing gear must be supported by stands, blocks, etc., on the main gear scales to a position at least four inches higher than the nose gear as it rests on an appropriate scale.
Page 338: Weight And Balance
WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 WEIGHT AND BALANCE The following information will enable you to operate your Cessna within the prescribed weight and center of gravity limitations. To figure weight and balance, use the sample Loading Problem, Weight and Moment Tables, and Center of Gravity Moment Envelope as follows: 1.
Page 339 CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST WEIGHT AND BALANCE (Continued) 3. Calculate the revised fuel weight by multiplying the total usable fuel by the sum of the average density (stated on chart) plus the increase in density estimated for the lower fuel temperature. In...
Page 340 SECTION 6 CESSNA WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 WEIGHT AND BALANCE (Continued) NOTE Information on the Weight and Moment Tables for crew, passenger, and cargo is based on the pilot and front passenger sliding seats positioned for average occupants (e.g., Fuselage Station 135.5), the aft passenger fixed seats...
Page 341: Weight And Balance Plotter
CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST WEIGHT AND BALANCE PLOTTER A Weight and Balance Plotter is available to quickly determine the weight and balance of the airplane when loading cargo. If the plotter shows a marginal condition developing, or if there is a question...
Page 342 SECTION 6 CESSNA WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 WEIGHT AND BALANCE RECORD (LOAD MANIFEST) (Continued) NOTE If weight to be loaded does not match one of the weight increments provided, and a more precise weight index is needed, use the LOAD ITEM INDEX formula on the backside of the Weight and Balance Record (Load Manifest) to calculate the index.
Page 343 CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST WEIGHT AND BALANCE RECORD (LOAD MANIFEST) (Continued) 7. Add aircraft empty weight and index to payload weight and index to acquire a zero fuel weight and index. A plot of this weight and index on the adjacent chart indicates the location of the zero fuel weight center of gravity in terms of % MAC.
Page 344 SECTION 6 CESSNA WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 WEIGHT AND BALANCE RECORD (LOAD MANIFEST) Figure 6-3 (Sheet 1 of 2) 208BPHBUS-00 U.S. 6-14...
Page 345 CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST WEIGHT AND BALANCE RECORD (LOAD MANIFEST) Figure 6-3 (Sheet 2) 208BPHBUS-00 6-15 U.S.
Page 346: Crew And Passenger Loading
SECTION 6 CESSNA WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 CREW AND PASSENGER LOADING The pilot and front passenger positions in all airplanes have six-way adjustable seats. These seats slide fore and aft on tracks that have adjustment holes for seat position.
Page 347: Baggage/Cargo Loading
CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST BAGGAGE/CARGO LOADING CABIN CARGO AREA Cargo may be carried in the cabin of either the Cargo Version or the Passenger Version. The cabin interior of the Cargo Version is specifically equipped for the carriage of cargo. However, after seat removal and the installation of miscellaneous equipment, the Passenger Version will also fulfill the requirements of cargo missions.
Page 348 SECTION 6 CESSNA WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 CABIN CARGO AREA (Continued) With all seats except the pilot’s seat removed, a large cabin volume is available for baggage/cargo. If a cargo barrier is installed, the total volume available for cargo behind the barrier is 340 cubic feet. Cargo can be loaded through the large, almost square, two-piece cargo door.
Page 349 CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST CABIN CARGO AREA (Continued) CAUTION The maximum load values marked in each zone are predicated on all cargo being tied down within the zones. On Cargo Versions, a horizontal line labeled “75%” is prominently marked along each sidewall as a loading reference.
Page 350 SECTION 6 CESSNA WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 CABIN CARGO AREA (Continued) WARNING • When utilized, the cargo barrier and its attached nets provide cargo forward crash load restraint and protection of the pilot and front passenger; however, the cargo must still be secured to...
Page 351 CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST CABIN CARGO AREA (Continued) CAUTION The maximum cargo partition load is the sum of any two zones. No more than two adjacent zones can be divided by one partition. The partitions are designed to prevent the cargo from shifting forward and aft in flight.
Page 352: Cargo Pod
SECTION 6 CESSNA WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 CARGO POD The airplane may be equipped with a 111.5 cubic foot capacity cargo pod attached to the bottom of the fuselage. The pod is divided into four compartments (identified as Zones A, B, C, and D) by bulkheads and has a maximum floor loading of 30 pounds per square foot and maximum load weight limit of 1090 pounds.
Page 353: Center Of Gravity Precautions
CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST CENTER OF GRAVITY PRECAUTIONS Since the airplane can be used for cargo missions, carrying various types of cargo in a variety of loading configurations, precautions must be taken to protect the forward and aft C.G. limits. Load planning should...
Page 354: Cargo Load Restraint
SECTION 6 CESSNA WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 CARGO LOAD RESTRAINT PREVENTION OF MOVEMENT Cargo restraint requires the prevention of movement in five principal directions: forward, aft, upward (vertical), left (side), and right (side). These movements are the result of forces exerted upon the cargo due to acceleration or deceleration of the airplane in takeoffs and landings as well as forces due to air turbulence in flight.
Page 355 CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST PREVENTION OF MOVEMENT (Continued) WARNING In special loading arrangements which allow the carriage of passengers as well as cargo behind the barrier in the passenger version, all cargo must be...
Page 356: Transportation Of Hazardous Materials
SECTION 6 CESSNA WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 TRANSPORTATION OF HAZARDOUS MATERIALS Special protection of the airplane and training of personnel are key considerations in conducting approved transportation of hazardous materials. Protection against hazardous materials has been provided in the fuselage bilge area under the cargo compartment from Fuselage Station 168.0 to 356.0, and these materials may be carried in any...
Page 357 CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST CABIN INTERNAL DIMENSIONS (CARGO VERSION) Figure 6-4 (Sheet 1 of 2) 208BPHBUS-00 6-27 U.S.
Page 358: Cabin Internal Dimensions
SECTION 6 CESSNA WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 CABIN INTERNAL DIMENSIONS (PASSENGER VERSION) Figure 6-4 (Sheet 2) 208BPHBUS-00 U.S. 6-28...
Page 359: Pod Internal Dimensions And Load Markings
CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST POD INTERNAL DIMENSIONS AND LOAD MARKINGS Figure 6-5 208BPHBUS-00 6-29 U.S.
Page 360: Cabin Internal Load Markings
SECTION 6 CESSNA WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 CABIN INTERNAL LOAD MARKINGS (CARGO VERSION) Figure 6-6 208BPHBUS-00 U.S. 6-30...
Page 361: Cargo Barrier And Barrier Nets
CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST CARGO BARRIER AND BARRIER NETS NOTE 1. Installation of the fire extinguisher on the cargo barrier is not shown. 2. The cargo barrier and attached barrier nets must be installed to provide forward crash load restraint.
Page 362: Cargo Partition Net
SECTION 6 CESSNA WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 CARGO PARTITION NETS NOTE 1. Partition nets are available for installation at Fuselage Stations 188.7, 246.8, 282.0, 307.0 and 332.0. 2. If partitions are used, they must be used in conjunction with the cargo barrier.
Page 363: Maximum Cargo Sizes
CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST MAXIMUM CARGO SIZES NOTE 1. Approximately one inch clearance allowed from sidewall and ceiling. 2. Subtract roller height and pallet thickness, if applicable. Figure 6-9 208BPHBUS-00 6-33 U.S.
Page 364: Cargo Tie-Down Attachments
SECTION 6 CESSNA WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 CARGO TIE-DOWN ATTACHMENTS Figure 6-10 (Sheet 1 of 2) 208BPHBUS-00 U.S. 6-34...
Page 365 CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST CARGO TIE-DOWN ATTACHMENTS Figure 6-10 (Sheet 2) 208BPHBUS-00 6-35 U.S.
Page 366: Cabin Internal Loading Arrangements
SECTION 6 CESSNA WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 CABIN INTERNAL LOADING ARRANGEMENTS (CARGO VERSION) NOTE 1. *Pilot or front passenger center of gravity on adjustable seats positioned for an average occupant with the seat locking pin at Fuselage Station 145.0. Numbers in parentheses indicate forward and aft limits of occupant center of gravity range.
Page 367 CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST CABIN INTERNAL LOADING ARRANGEMENTS (PASSENGER VERSION) NOTE 1. *Pilot or front passenger center of gravity on adjustable seats positioned for an average occupant with the seat locking pin at Fuselage Station 145.0. Numbers in parentheses indicate forward and aft limits of occupant center of gravity range.
Page 368 SECTION 6 CESSNA WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 CABIN INTERNAL LOADING ARRANGEMENTS (PASSENGER VERSION) Figure 6-11 (Sheet 3) 208BPHBUS-00 U.S. 6-38...
Page 369: Cargo Pod Loading Arrangement
CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST CARGO POD LOADING ARRANGEMENT NOTE 1. *Cargo bay center of gravity in Zones A, B, C, and D. 2. Compartment bulkheads that separate Zones A and B (Station 154.75), Zones B and C (Station 209.35), and Zones C and D (Station 257.35) can be used as a reference point for...
Page 370: Loading-Tie-Down By Zone And Load
SECTION 6 CESSNA WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 LOADING/TIE-DOWN BY ZONE AND LOAD (OFF- LOADING SEQUENCE) NOTE 1. If cargo partitions are not utilized, individual loads must be secured by adequate tie-downs over tarps. 2. Protection against hazardous materials has been provided in the fuselage bilge area under the cargo compartment from Fuselage Station 168.0 to 356.0.
Page 371: Typical Cargo Restraint Methods
CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST TYPICAL CARGO RESTRAINT METHODS Figure 6-14 208BPHBUS-00 6-41 U.S.
Page 372 SECTION 6 CESSNA WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 Figure 6-15 (Sheet 1 of 7) 208BPHBUS-00 U.S. 6-42...
Page 373 CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST Figure 6-15 (Sheet 2) 208BPHBUS-00 6-43 U.S.
Page 374 SECTION 6 CESSNA WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 Figure 6-15 (Sheet 3) 208BPHBUS-00 U.S. 6-44...
Page 375 CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST Figure 6-15 (Sheet 4) 208BPHBUS-00 6-45 U.S.
Page 376 SECTION 6 CESSNA WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 Figure 6-15 (Sheet 5) 208BPHBUS-00 U.S. 6-46...
Page 377 CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST Figure 6-15 (Sheet 6) 208BPHBUS-00 6-47 U.S.
Page 378 SECTION 6 CESSNA WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 Figure 6-15 (Sheet 7) 208BPHBUS-00 U.S. 6-48...
Page 379 CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST Figure 6-16 (Sheet 1 of 2) 208BPHBUS-00 6-49 U.S.
Page 380 SECTION 6 CESSNA WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 Figure 6-16 (Sheet 2) 208BPHBUS-00 U.S. 6-50...
Page 381: Center Of Gravity Limits
CESSNA SECTION 6 MODEL 208B G1000 WEIGHT & BALANCE/EQUIPMENT LIST CENTER OF GRAVITY LIMITS WARNING It is the responsibility of the pilot to make sure that the airplane is loaded correctly. Operation outside of prescribed weight and balance limitations could result in an accident and serious or fatal injury.
Page 382: Center Of Gravity Moment Envelope
SECTION 6 CESSNA WEIGHT & BALANCE/EQUIPMENT LIST MODEL 208B G1000 CENTER OF GRAVITY MOMENT ENVELOPE WARNING • Because loading personnel may not always be able to achieve an ideal loading, a means of protecting the C.G envelope is provided by supplying an aft C.G.
Page 383 CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION SECTION 7 AIRPLANE & SYSTEMS DESCRIPTIONS TABLE OF CONTENTS PAGE Introduction ..........7-7 Airframe .
Page 384 SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 TABLE OF CONTENTS (Continued) Page Cargo Doors ......... . 7-37 Cabin Windows .
Page 385 CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION TABLE OF CONTENTS (Continued) Page Propeller Overspeed Governor ......7-59 Engine Fire Detection System.
Page 386 SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 TABLE OF CONTENTS (Continued) Page External Power Switch....... . 7-78 Circuit Breakers .
Page 387 CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION TABLE OF CONTENTS (Continued) Page Pitot-Static System And Instruments ......7-91 Airspeed Indicators .
Page 389: Introduction
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION INTRODUCTION This section provides description and operation of the airplane and its systems. Refer to Section 9, Supplements for details of other supplemental systems and equipment. WARNING Complete familiarity with the airplane and its...
Page 390: Cargo Pod
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 AIRFRAME (Continued) The empennage (tail assembly) consists of a conventional vertical stabilizer, rudder, horizontal stabilizer, and elevator. The vertical stabilizer consists of a forward and aft spar, sheet metal ribs and reinforcements, four skin panels, formed leading edge skins, and a dorsal fin.
Page 391: Flight Controls
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION CARGO POD (Continued) The volume of the cargo pod is 111.5 cubic feet and has a load-carrying capacity of 1090 pounds. The pod has aluminum bulkheads that divide it into four separate compartments. Each compartment has a door on the left side of the pod that is hinged at the bottom.
Page 392: Flight Control And Trim System
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 FLIGHT CONTROL AND TRIM SYSTEMS Figure 7-1 (Sheet 1 of 3) 208BPHBUS-00 U.S. 7-10...
Page 393 CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION FLIGHT CONTROL AND TRIM SYSTEMS Figure 7-1 (Sheet 2 of 3) 208BPHBUS-00 7-11 U.S.
Page 394 SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 FLIGHT CONTROL AND TRIM SYSTEMS Figure 7-1 (Sheet 3 of 3) 208BPHBUS-00 U.S. 7-12...
Page 395: Instrument Panel
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION INSTRUMENT PANEL The instrument panel is designed around the Garmin G1000 Integrated Avionics System. The instrument panel is of all metal construction and is installed in sections so equipment can be easily removed for maintenance.
Page 396: Panel Layout
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 PANEL LAYOUT To the left of the pilot PFD is a switch panel which has many of the switches necessary to operate the airplane systems. At lower left are a...
Page 397: Typical Instrument Panel
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION TYPICAL INSTRUMENT PANEL Figure 7-2 (Sheet 1 of 2) 208BPHBUS-00 7-15 U.S.
Page 398 SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 TYPICAL INSTRUMENT PANEL Figure 7-2 (Sheet 1 of 2) 208BPHBUS-00 U.S. 7-16...
Page 399: Left Sidewall Switch And Circuit Breaker Panel
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION LEFT SIDEWALL SWITCH AND CIRCUIT BREAKER PANEL Most of the engine control switches and non-avionics circuit breakers are located on a separate panel mounted on the left cabin sidewall adjacent to the pilot. Switches and controls on this panel are illustrated in the Typical Left Sidewall Switch and Circuit Breaker Panel figure.
Page 400: Overhead Panel
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 OVERHEAD PANEL Figure 7-3 208BPHBUS-00 U.S. 7-18...
Page 401: Typical Left Sidewall Switch And Circuit Breaker Panel
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION TYPICAL LEFT SIDEWALL SWITCH AND CIRCUIT BREAKER PANEL Figure 7-4 208BPHBUS-00 7-19 U.S.
Page 402: Cas Messages
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 CAS MESSAGES 1. OIL PRESS LOW (RED) - Indicates engine oil pressure is less than 40 psi. 2. VOLTAGE LOW (RED) - Indicates electrical system bus voltage is less than 24.5 volts and power is being supplied from the battery.
Page 403 CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION CAS MESSAGES (Continued) 11.R FUEL LEVEL LOW (AMBER) - Indicates fuel quantity in the right fuel tank is 25 gallons (170 lbs) or less. 12.L-R FUEL LEVEL LOW (AMBER) Indicates fuel quantity in both the left and right fuel tanks is 25 gallons (170 lbs) or less.
Page 404: Ground Control
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 CAS MESSAGES (Continued) 23.GENERATOR AMPS (AMBER) - Indicates that the generator output is less than -10 amps or greater than 200 amps (-15/300 with 300 amp starter generator). 24.ALTNR AMPS (AMBER) - Indicates that the alternator output is less than -10 amps or greater than 75 amps.
Page 405: Minimum Turning Radius
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION MINIMUM TURNING RADIUS Figure 7-5 208BPHBUS-00 7-23 U.S.
Page 406: Wing Flap System
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 WING FLAP SYSTEM The wing flaps are large span, single-slot type (see Wing Flap System figure) and incorporate a trailing edge angle and leading edge vortex generators to reduce stall speed and provide enhanced lateral stability.
Page 407: Landing Gear System
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION WING FLAP SYSTEM Figure 7-6 LANDING GEAR SYSTEM The landing gear is of the tricycle type with a steerable nose wheel and two main wheels. Shock absorption is provided by the tubular spring-...
Page 408: Baggage/Cargo Compartment
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 BAGGAGE/CARGO COMPARTMENT In the passenger version, the space normally used for baggage consists of the raised area from the back of the cargo doors to the aft cabin bulkhead. Access to the baggage area is gained through the cargo doors, the aft passenger door or from within the cabin.
Page 409: Aft Passengers' Seat (Commuter) (Passenger Version)
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION PILOT'S AND COPILOT'S SEATS (Continued) The seat is not locked if the pin is retracted or only partially extends. Raise or lower the seat by rotating a large crank under the front right corner of the seat.
Page 410: Seat Belts And Shoulder Harnesses
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 SEAT BELTS AND SHOULDER HARNESSES PILOT’S AND COPILOT’S SEAT (Typical) Figure 7-7 (Sheet 1 of 3) 208BPHBUS-00 U.S. 7-28...
Page 411 CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION SEAT BELTS AND SHOULDER HARNESSES AFT PASSENGERS’ SEATS (Individual Commuter Seating Shown) Figure 7-7 (Sheet 2 of 3) 208BPHBUS-00 7-29 U.S.
Page 412 SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 SEAT BELTS AND SHOULDER HARNESSES AFT PASSENGERS’ SEATS (Dual Commuter Seating Shown) Figure 7-7 (Sheet 3 of 3) 208BPHBUS-00 U.S. 7-30...
Page 413: Seat Belts, Strap, And Shoulder Harnesses (Pilot And Copilot's Seats)
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION SEAT BELTS AND SHOULDER HARNESSES All seat positions are equipped with seat belts and shoulder harnesses. The pilot’s and copilot’s seat positions are equipped with shoulder harnesses with inertia reels.
Page 414 SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 SEAT BELTS, STRAP, AND SHOULDER HARNESSES (PILOT AND COPILOT SEATS) (Continued) To use the restraint system, lengthen each half of the belt as necessary by pulling the buckle (or connecting link) to the lap with one hand while pulling outward on the narrow adjuster strap with the other hand.
Page 415: Cabin Entry Doors
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION CABIN ENTRY DOORS Entry to, and exit from the airplane is accomplished through a door on each side of the cabin at the pilot’s and copilot’s positions and, on the...
Page 416: Passenger Entry Door (Passenger Version Only)
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 PASSENGER ENTRY DOOR (Passenger Version Only) The entry door for passengers consists of an upper and lower section. When opened, the upper section swings upward and the lower section drops down providing integral steps to aid in boarding or exiting the airplane.
Page 417 CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION PASSENGER ENTRY DOOR (Passenger Version Only) (Continued) To close the passenger entry door from the inside of the airplane, grasp the support cables of the lower door section and pull the door up until the top edge is within reach, then grasp the center of the door and pull inboard until the door is held snugly against the fuselage door frame.
Page 418 SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 PASSENGER ENTRY DOOR (Passenger Version Only) (Continued) To close the passenger entry door from outside the airplane, raise the lower door section until the door is held firmly against the door frame in the fuselage.
Page 419: Cargo Doors
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION CARGO DOORS A two-piece cargo door is installed on the left side of the airplane just aft of the wing trailing edge. The cargo door is divided into an upper and a lower section.
Page 420 SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 CARGO DOORS (Continued) To close the cargo door from outside the airplane, disconnect the holding strap or chain from the fuselage, swing the door aft to the closed position, and hold the door firmly against the fuselage door frame to assure engagement of the latching pawls.
Page 421: Cabin Windows
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION CABIN WINDOWS The airplane is equipped with a two-piece windshield reinforced with a metal center strip. The passenger version has sixteen cabin side windows of the fixed type including one each in the two crew entry doors, two windows in the cargo door upper section, and one window in the upper section of the passenger entry door.
Page 422: Engine
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 CONTROL LOCKS (Continued) The Rudder Gust Lock has a fail-safe connection to the elevator control system to ensure that it will always be disengaged before the airplane becomes airborne. This fail-safe connection automatically disengages the lock when the elevator is deflected upward about one-fourth of its travel from neutral.
Page 423 CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION ENGINE (Continued) The combustion chamber liner located in the gas generator case consists of an annular reverse-flow weldment provided with varying sized perforations which allow entry of compressed air. The flow of air changes direction to enter the combustion chamber liner where it reverses direction and mixes with fuel.
Page 424: Typical Engine Components
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 TYPICAL ENGINE COMPONENTS 1. Propeller Shaft 13. Accessory Gearbox Drive Shaft 2. Propeller Governor Drive Pad 14. Accessory Gearbox Cover 3. Second Stage Planetary Gear 15. Starter-Generator Drive Shaft 4. First Stage Planetary Gear 16.
Page 425: Engine Controls
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION ENGINE CONTROLS The engine is operated by four separate controls consisting of a power lever, EMERGENCY POWER Lever, PROP RPM Lever, and a FUEL CONDITION Lever. The power and FUEL CONDITION Levers are engine controls while the PROP RPM Lever controls propeller speed and feathering.
Page 426: Emergency Power Lever
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 EMERGENCY POWER LEVER The EMERGENCY POWER Lever is connected through linkage to the manual override lever on the fuel control unit and governs fuel supply to the engine should a pneumatic malfunction occur in the fuel control unit.
Page 427: Propeller Control Lever
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION EMERGENCY POWER LEVER (Continued) Operation of the EMERGENCY POWER Lever is prohibited with the primary power lever out of the IDLE position. The EMERGENCY POWER Lever overrides normal fuel control functions and results in the direct operation of the fuel metering valve.
Page 428: Quadrant Friction Lock
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 QUADRANT FRICTION LOCK A quadrant friction lock, located on the right side of the pedestal, is provided to minimize creeping of the engine controls once they have been set. The lock is a knurled knob which increases friction on the engine controls when rotated clockwise.
Page 429: Torque Indications
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION TORQUE INDICATIONS Torque (TRQ) indication is displayed at the top of both the ENGINE and SYSTEM pages. The indicator is a round gage with a white pointer. The transmitter senses the difference between the engine torque pressure and the pressure in the engine case and transmits this data to the G1000.
Page 430: Fuel Flow Indications
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 FUEL FLOW INDICATIONS Details of the fuel flow indicator are included under Fuel System in a later paragraph in this section. OIL PRESSURE INDICATION Oil Pressure (OIL PSI) is displayed using a varied color tape and 3 digit display on the ENGINE page.
Page 431: Engine Lubrication System
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION ENGINE LUBRICATION SYSTEM The lubrication system consists of a pressure system, a scavenge system and a breather system. The main components of the lubrication system include an integral oil tank at the back of the engine, an oil...
Page 432: Ignition System
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 ENGINE LUBRICATION SYSTEM (Continued) Breather air from the engine bearing compartments and from the accessory and reduction gearboxes is vented overboard through a centrifugal breather installed in the accessory gearbox. The bearing compartments are connected to the accessory gearbox by cored passages and existing scavenge oil return lines.
Page 433: Air Induction System
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION IGNITION SYSTEM (Continued) The main function of the starter switch is control of the starter for rotating the gas generator portion of the engine during starting. However, it also provides ignition during starting. For purposes of this discussion, only the ignition functions of the switch are described.
Page 434: Inertial Separator System
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 INERTIAL SEPARATOR SYSTEM An inertial separator system in the engine air inlet duct prevents moisture particles from entering the compressor air inlet plenum when in bypass mode. The inertial separator consists of two movable vanes and a fixed airfoil which, during normal operation, route the inlet air through a gentle turn into the compressor air inlet plenum.
Page 435: Engine Air Flow
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION ENGINE AIR FLOW NOTE The above view shows inertial separator in NORMAL position. Auxiliary view shows inertial separator in BYPASS position. Figure 7-9 208BPHBUS-00 7-53 U.S.
Page 436: Exhaust System
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 EXHAUST SYSTEM The exhaust system consists of a primary exhaust pipe attached to the right side of the engine just aft of the propeller reduction gearbox. A secondary exhaust duct, fitted over the end of the primary exhaust pipe carries the exhaust gases away from the cowling and into the slipstream.
Page 437 CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION ENGINE FUEL SYSTEM (Continued) The fuel control unit consists of a fuel metering section, a temperature compensating section, and a gas generator (N ) pneumatic governor. The fuel control unit determines the proper fuel schedule to provide the power required as established by the power lever input.
Page 438: Starting System
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 STARTING SYSTEM The starting system consists of a starter-generator, a starter switch, and an Amber STARTER ON CAS MSG. The starter-generator functions as a motor for engine starting and will motor the gas...
Page 439: Oil Pump
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION OIL PUMP Pressure oil is circulated from the integral oil tank through the engine lubrication system by a self-contained, gear-type pressure pump located in the lowest part of the oil tank. The oil pump is contained in a cast housing which is bolted to the front face of the accessory diaphram, and is driven by the accessory gear shaft.
Page 440: Propeller Tachometer-Generator
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 PROPELLER TACHOMETER-GENERATOR The propeller tachometer-generator produces an electric signal which is used in conjunction with the propeller RPM indicator. The propeller tachometer- generator drive and mount pad is located on the right side of the reduction gearbox case and rotates clockwise with a drive ratio of 0.1273:1.
Page 441: Propeller Governor
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION PROPELLER GOVERNOR The propeller governor is located in the 12 o’clock position on the front case of the reduction gearbox. Under normal conditions, the governor acts as a constant speed unit, maintaining the propeller speed selected by the pilot by varying the propeller blade pitch to match the load to the engine torque.
Page 442: Engine Gear Reduction System
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 ENGINE GEAR REDUCTION SYSTEM The reduction gear and propeller shaft, located in the front of the engine, are housed in two magnesium alloy castings which are bolted together at the exhaust outlet. The gearbox contains a two-stage planetary gear train, three accessory drives, and propeller shaft.
Page 443: Propeller
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION PROPELLER The airplane is equipped with a McCauley aluminum material, three- bladed propeller. The propeller is constant-speed, full-feathering, reversible, single-acting, governor-regulated propeller. A setting introduced into the governor with the PROP RPM Lever establishes the propeller speed.
Page 444: Overspeed Governor Test Switch
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 OVERSPEED GOVERNOR TEST SWITCH An overspeed governor test switch is located on the left side of the instrument panel. The switch is the push-to-test type and is used to test the propeller overspeed governor during engine run-up.
Page 445 CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION FUEL SYSTEM (Continued) The reservoir is located at the low point in the fuel system which maintains a head of fuel around the ejector boost pump and auxiliary boost pump which are contained within the reservoir. This head of fuel prevents pump cavitation in low-fuel quantity situations, especially during in-flight maneuvering.
Page 446 SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 FUEL SYSTEM Figure 7-10 208BPHBUS-00 U.S. 7-64...
Page 447: Fuel Quantity Data
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION FUEL QUANTITY DATA FUEL QUANTITY DATA FUEL LEVEL TOTAL UNITS OF (QUANTITY EACH TOTAL TOTAL USABLE ALL MEASURE TANK) FUEL UNUSABLE CONDITIONS FULL (OUTBOARD FILLERS) POUNDS 1124.25 2248.5 24.1 2224.4 GALLONS (U.S.)
Page 448: Firewall Fuel Shutoff Valve
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 FIREWALL FUEL SHUTOFF VALVE A manual firewall fuel shutoff valve, located on the aft side of the firewall, enables the pilot to shut off all fuel flow from the fuel reservoir to the engine.
Page 449 CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION FUEL FLOW INDICATION A fuel flow indicator, located beneath the quantity indicators on both the ENGINE and SYSTEM pages, indicates the fuel consumption of the engine in pounds per hour based on Jet A fuel. The indicator measures the flow of fuel downstream of the fuel control unit just before being routed into the flow divider.
Page 450: Fuel Pressure Low Warning Cas Message
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 RESERVOIR FUEL LOW WARNING CAS MESSAGE A Red RSVR FUEL LOW CAS MSG is located on the PFD, and will illuminate when the level of fuel in the reservoir drops to approximately one-half full.
Page 451: Fuel Drain Can
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION DRAIN VALVES (Continued) Before each flight of the day and after each refueling, use a clear sampler and drain fuel from the inboard fuel tank sump, external sump quick-drain valves, fuel reservoir quick-drain valve, and fuel filter quick- drain valve to determine if contaminants are present, and that the airplane has been fueled with the proper fuel.
Page 452: Brake System
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 BRAKE SYSTEM The airplane has a single-disc, hydraulically-actuated brake on each main landing gear wheel. Each brake is connected, by a hydraulic line, to a master cylinder attached to each of the pilot's rudder pedals. The...
Page 453: Electrical System
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION ELECTRICAL SYSTEM The airplane is equipped with a 28-volt, direct-current electrical system (see Typical Electrical System figure). The system uses a 24-volt sealed lead acid battery; located on the front right side of the firewall, as a source of electrical energy.
Page 454: Generator Control Unit
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 GENERATOR CONTROL UNIT The generator control unit (GCU) is mounted inside the cabin on the left forward fuselage sidewall. The unit provides the electrical control functions necessary for the operation of the starter-generator. The GCU provides for automatic starter cutoff when engine RPM is above 46%.
Page 455: Starter Switch
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION STARTER SWITCH The starter switch is a three-position toggle-type switch, labeled STARTER, on the left sidewall switch and circuit breaker panel. The switch has OFF, START, and MOTOR positions. For additional details of the starter switch, refer to the Starting System paragraph in this section.
Page 456: Avionics Power Switches
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 AVIONICS POWER SWITCHES Electrical power from the airplane power distribution bus to the avionics buses (see Typical Electrical System figure) is controlled by two toggle- type switch breakers located on the left sidewall switch and circuit breaker panel.
Page 457: Typical Electrical System
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION TYPICAL ELECTRICAL SYSTEM Figure 7-12 (Sheet 1 of 3) 208BPHBUS-00 7-75 U.S.
Page 458 SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 TYPICAL ELECTRICAL SYSTEM Figure 7-12 (Sheet 2 of 3) 208BPHBUS-00 U.S. 7-76...
Page 459 CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION TYPICAL ELECTRICAL SYSTEM Figure 7-12 (Sheet 3 of 3) 208BPHBUS-00 7-77 U.S.
Page 460: External Power Switch
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 EXTERNAL POWER SWITCH The external power switch is a three-position guarded toggle-type switch located on the left sidewall switch and circuit breaker panel. The switch has OFF, STARTER, and BUS positions and is guarded in the OFF position.
Page 461: Ground Service Plug Receptacle
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION GROUND SERVICE PLUG RECEPTACLE A ground service plug receptacle permits the use of an external power source for cold weather starting and during lengthy maintenance work on the electrical and avionics equipment. External power control circuitry is provided to prevent the external power and the battery from being connected together during starting.
Page 462: Landing Lights
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 LANDING LIGHTS Two landing lights are installed on the airplane, one in each wing leading edge mounted outboard. The lights provide illumination forward and downward during takeoff and landing. The lights are protected by two pull-off type circuit breakers, labeled LEFT LDG LIGHT and RIGHT LDG LIGHT, on the left sidewall switch and circuit breaker panel.
Page 463: Interior Lighting
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION FLASHING BEACON LIGHT A red flashing beacon light is installed on the top of the vertical fin as additional anti-collision protection in flight and for recognition during ground operation. The light is visible through 360°. The flashing beacon light circuit is protected by a pull-off type circuit breaker, labeled BEACON LIGHT, on the left sidewall switch and circuit breaker panel.
Page 464: Standby Indicator Control Knob
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 STANDBY INDICATOR CONTROL KNOB The knob labeled STANDBY IND varies the intensity of the integral lighting of the standby airspeed indicator, attitude indicator, altimeter, torque indicator, and magnetic compass. Clockwise rotation of the knob increases light brightness and counterclockwise rotation decreases brightness.
Page 465: Cabin Lights Without Timer (208B Passenger)
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION CABIN LIGHTS WITHOUT TIMER (208B Passenger) The 208B passenger cabin light system without timer consists of four cabin lights installed on the interior of the airplane and courtesy lights under each wing to facilitate boarding or loading cargo during night operations.
Page 466: Cabin Heating, Ventilating And Defrosting System
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 PASSENGER READING LIGHTS (Passenger Version Only) Passenger reading lights may be installed near each of the aft passengers positions. The lights are located in 14 small convenience panels above each seat. A pushbutton-type ON, OFF switch, mounted in each panel, controls the lights.
Page 467: Bleed Air Heat Switch
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION BLEED AIR HEAT SWITCH A two-position toggle switch, labeled BLEED AIR HEAT, is located on the cabin heat switch and control panel. The switch controls the operation of the bleed air flow control valve. The ON position of the switch opens the flow control valve, allowing hot bleed air to flow to the cabin heating system.
Page 468: Cabin Heating, Ventilating And
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 CABIN HEATING, VENTILATING AND DEFROSTING SYSTEM (CARGO VERSION) Figure 7-13 (Sheet 1 of 2) 208BPHBUS-00 U.S. 7-86...
Page 469 CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION CABIN HEATING, VENTILATING AND DEFROSTING SYSTEM (PASSENGER VERSION) Figure 7-13 (Sheet 2 of 2) 208BPHBUS-00 7-87 U.S.
Page 470: Mixing Air Push-Pull Control
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 MIXING AIR PUSH-PULL CONTROL A push-pull control, labeled MIXING AIR, GRD-PULL, FLT-PUSH, is located on the cabin heat switch and control panel. With the push-pull control in the GRD position (pulled out), warm compressor bleed valve air is mixed with hot compressor outlet air in the mixer/muffler.
Page 471: Aft/Forward Cabin Push-Pull Control
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION AFT/FORWARD CABIN PUSH-PULL CONTROL A push-pull control, labeled AFT CABIN-PULL, FWD CABIN-PUSH, is located on the cabin heat switch and control panel. With the control in the AFT CABIN position (pulled out), heated air is directed to the aft...
Page 472: Vent Air Control Knobs
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 VENT AIR CONTROL KNOBS Two vent air control knobs, labeled VENT AIR, are located on the overhead console. The knobs control the operation of the shutoff valves in each wing which control the flow of ventilating air to the cabin. The...
Page 473: Pitot-Static System And Instruments
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION PITOT-STATIC SYSTEM AND INSTRUMENTS There are two independent pitot-static systems on the airplane. The left pitot-static system supplies ram air pressure to Air Data Computer #1 and to the standby airspeed indicator, and supplies static pressure to Air Data Computer #1 and to the standby airspeed indicator, vertical speed indicator, and altimeter.
Page 474: Altimeter (Standby Instrument Panel)
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 AIRSPEED INDICATIORS The Garmin PFDs are the primary sources of airspeed information. Standby airspeed information is depicted by a mechanical indicator calibrated in knots, connected to the left pitot-static system. Limitation and range markings (in KIAS) match the markings on the PFD as listed in Section 2, Limitations.
Page 475: Vacuum System And Instruments
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION VACUUM SYSTEM AND INSTRUMENTS A vacuum system (see Typical Vacuum System figure) provides the suction necessary to operate the standby attitude indicator. Vacuum is obtained by passing regulated compressor outlet bleed air through a vacuum ejector.
Page 476: Typical Vacuum System
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 TYPICAL VACUUM SYSTEM Figure 7-14 208BPHBUS-00 U.S. 7-94...
Page 477: Stall Warning System
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION STALL WARNING SYSTEM The airplane is equipped with a vane-type stall warning unit, in the leading edge of the left wing, which is electrically connected to a stall warning horn located overhead of the pilot's position. The vane in the...
Page 478: Avionics Support Equipment
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 AVIONICS SUPPORT EQUIPMENT Various avionics support equipment is installed in the airplane, and includes a microphone/speaker, mic/phone jacks, avionics cooling fans, 12VDC power outlets, an auxiliary audio input jack, and control surface static dischargers.
Page 479: Static Dischargers
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION STATIC DISCHARGERS As an aid in IFR flights, wick-type static dischargers are installed to improve radio communications during flight through dust or various forms of precipitation (rain, snow or ice crystals). Under P-Static...
Page 480 SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 AUXILIARY AUDIO INPUT JACK An auxiliary audio input jack (AUX AUDIO IN) is mounted on the lower aft face of the pedestal (Refer to Typical Instrument Panel figure). It allows connection of entertainment audio devices such as cassette, compact disc, and MP3 players to play music over the airplane's headsets.
Page 481: Sun Visors
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION CABIN FIRE EXTINGUISHER (Continued) WARNING Ventilate the cabin promptly after successfully extinguishing the fire to reduce the gases produced by thermal decomposition. Occupants should use oxygen masks until the smoke clears.
Page 482: Crew Entry Step Assembly
SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 CREW ENTRY STEP ASSEMBLY The airplane may be equipped with a crew entry step for each crew entry door. The step assembly attaches to the floorboard just inside the entry door and extends toward ground level, providing two steps for entering or exiting the airplane.
Page 483: Cargo/Airplane Tie-Down Equipment
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION CARGO/AIRPLANE TIE-DOWN EQUIPMENT Various items of tie-down equipment are available for securing cargo within the airplane and/or tying down the airplane. This equipment consists of tie-down belt assemblies having various load ratings and...
Page 485 Identification Plate ........8-4 Cessna Owner Advisories ....... . . 8-4 Publications.
Page 486 SECTION 8 CESSNA HANDLING, SERVICE, AND MAINTENANCE MODEL 208B G1000 TABLE OF CONTENTS (Continued) Cleaning and Care ........8-38 Windshield and Windows.
Page 487: Introduction
INTRODUCTION This section contains factory-recommended procedures for proper ground handling and routine care and servicing of your Cessna. It also identifies certain inspection and maintenance requirements which must be followed if your airplane is to retain that new-plane performance and dependability.
Page 488: Identification Plate
Parts Catalog if finish and trim information is needed. CESSNA OWNER ADVISORIES Cessna Owner Advisories are sent to Cessna airplane owners at no charge to inform them about mandatory and/or beneficial airplane service requirements and product improvements: United States Airplane Owners If your airplane is registered in the U.S., appropriate Cessna Owner...
Page 489: Publications
Cessna Service Stations have a Customer Care Supplies and Publications Catalog covering all available items, many of which are kept on hand. The Cessna Service Station representative can place an order for any item which is not in stock. NOTE...
Page 490: Airplane File
United States should check with their own aviation officials to determine their individual requirements. Cessna recommends that these items, plus the Pilot’s Checklists, CESCOM/Customer Care Program Handbook; and Customer Care Card be carried in the airplane at all times.
Page 491: Cessna Progressive Care
The procedures for the Progressive Care Program and the 100-hour inspection have been carefully worked out by the factory and are followed by the Cessna Service Organization. The complete familiarity of Cessna Authorized Caravan Service Stations with Cessna equipment and factory- approved procedures provides the highest level of service for Cessna owners/operators.
Page 492: Phasecard Inspection
MODEL 208B G1000 CESSNA CUSTOMER CARE PROGRAM (Continued) Contact a Cessna Service Station either at 100 hours for the first Progressive Care Operation, or for the first 100-hour inspection depending on the program chosen for the airplane. While these important inspections will be performed by any Cessna Caravan Service Station, in most cases it is preferable to have the facility where the airplane was purchased accomplish this work.
Page 493: Pilot Conducted Preventive Maintenance
A current 208 Series Maintenance Manual should be obtained prior to performing any preventive maintenance to ensure that proper procedures are followed. The Cessna Service Station should be contacted for further information or for required maintenance that must be accomplished by appropriately licensed personnel.
Page 494: Alterations Or Repairs
SECTION 8 CESSNA HANDLING, SERVICE, AND MAINTENANCE MODEL 208B G1000 ALTERATIONS OR REPAIRS It is essential that the FAA be contacted prior to any alterations on the airplane to ensure that airworthiness of the airplane is not violated. Alterations or repairs to the airplane must be accomplished by licensed personnel.
Page 495: Parking
CESSNA SECTION 8 MODEL 208B G1000 HANDLING, SERVICE, AND MAINTENANCE PARKING When parking the airplane, head into the wind and set the parking brakes. Do not set the parking brakes during cold weather when accumulated moisture may freeze the brakes, or when the brakes are overheated.
Page 496: Jacking
SECTION 8 CESSNA HANDLING, SERVICE, AND MAINTENANCE MODEL 208B G1000 TIE DOWN (Continued) 5. Install pitot tube cover(s), if available. 6. Secure ropes or chains of sufficiently strong tensile strength to the wing tie-down fittings and secure to ground anchors.
Page 497: Leveling
CESSNA SECTION 8 MODEL 208B G1000 HANDLING, SERVICE, AND MAINTENANCE JACKING (Continued) CAUTION • A tail jack stand must be used when conducting maintenance inside the tail section, and should be installed in most jacking operations. Be sure the stand is suitably heavy enough to keep the tail stable under all conditions and is strong enough to support the airplane.
Page 498: Servicing
200, and 400-hour intervals, plus those items that require servicing, inspection, and/or testing at special intervals. Since Cessna Service Stations have the training and equipment necessary to conduct all service, inspection, and test procedures in accordance with applicable maintenance manuals, it is recommended...
Page 499: Oil
CESSNA SECTION 8 MODEL 208B G1000 HANDLING, SERVICE, AND MAINTENANCE OIL GRADE (SPECIFICATION) Oil conforming to Pratt & Whitney Engine Service Bulletin No. 1001, and all revisions or supplements thereto, must be used. The oils listed below comply with the engine manufacturers specification PWA521 and have a viscosity Type II rating.
Page 500 SECTION 8 CESSNA HANDLING, SERVICE, AND MAINTENANCE MODEL 208B G1000 (Continued) NOTE The oils listed above are recommended when operation will result in frequent cold soaking at ambient temperatures of 0°F (-18°C). Refer to Pratt & Whitney Engine Service Bulletin No. 1001 for additional approved oils:...
Page 501 CESSNA SECTION 8 MODEL 208B G1000 HANDLING, SERVICE, AND MAINTENANCE (Continued) 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.
Page 502 SECTION 8 CESSNA HANDLING, SERVICE, AND MAINTENANCE MODEL 208B G1000 FUEL (Continued) ALTERNATE/EMERGENCY FUEL: • 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.
Page 503 CESSNA SECTION 8 MODEL 208B G1000 HANDLING, SERVICE, AND MAINTENANCE FUEL ADDITIVES (Continued) CAUTION • JP-4 and JP-5 fuels 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.
Page 504 SECTION 8 CESSNA HANDLING, SERVICE, AND MAINTENANCE MODEL 208B G1000 FUEL ADDITIVES (Continued) CAUTION • Diethylene Glycol Monomethyl Ether (DIEGME) is slightly toxic if swallowed and may cause eye r e d n e s s , s w e l l i n g a n d i r r i t a t i o n . I t i s a l s o combustible.
Page 505 CESSNA SECTION 8 MODEL 208B G1000 HANDLING, SERVICE, AND MAINTENANCE FUEL ADDITIVES (Continued) If additional anti-static protection is desired, the following additive is approved for use: • Dupont Stadis 450 CAUTION Additives shall not exceed a maximum concentration of 1 part per million by weight.
Page 506 SECTION 8 CESSNA HANDLING, SERVICE, AND MAINTENANCE MODEL 208B G1000 FUEL CONTAMINATION Fuel contamination is usually the result of foreign material present in the fuel system and may consist of water, rust, sand, dirt, microbes, or bacterial growth. In addition, additives that are not compatible with fuel or fuel system components can cause the fuel to become contaminated.
Page 507 Airplane Maintenance Manual. Only the proper fuel, as recommended in this POH/AFM, should be used, and fuel additives must not be used unless approved by Cessna and the Federal Aviation Administration. WARNING •...
Page 508: Landing Gear
SECTION 8 CESSNA HANDLING, SERVICE, AND MAINTENANCE MODEL 208B G1000 LANDING GEAR NOSE WHEEL TIRE PRESSURE: 30-42 psi on 22x8.00-8, 6-Ply Rated Tire. MAIN WHEEL TIRE PRESSURE: 53-57 psi on 8.50-10, 8-Ply Rated Tires. 35-45 psi on 29x11.00-10, 10-Ply Rated Tires.
Page 509 1994 or later. • FAA Advisory Circular AC20-117, dated 17 December 1982 or later. • Cessna Aircraft Company SNL 08-1 and FAA notice 8900.22: FAA-Approved deicing program updates, winter 2007-2008. Deicing and anti-icing fluids are aqueous solutions which work by lowering the freezing point of water in either the liquid or crystal phase, thus delaying the onset of freezing.
Page 510 SECTION 8 CESSNA HANDLING, SERVICE, AND MAINTENANCE MODEL 208B G1000 GROUND DEICE/ANTI-ICE OPERATIONS (Continued) The procedure involves applying Type II, Type III, or type IV anti-ice fluid to make sure the airplane remains clean after deicing. Type II, Type III, or Type IV fluid is used to provide longer-term anti-icing protection.
Page 511 CESSNA SECTION 8 MODEL 208B G1000 HANDLING, SERVICE, AND MAINTENANCE GROUND DEICE/ANTI-ICE OPERATIONS (Continued) Deicing may be accomplished using the ambient temperature available from a heated hangar or by mechanical means using a glycol-based Freezing Point Depressant (FPD) Type I fluid. A heated hangar is an excellent option to deice airplanes and must be utilized whenever possible.
Page 512: Holdover Timetable (Type I, Type Ii, Type Iii, And Type Iv Fluids)
SECTION 8 CESSNA HANDLING, SERVICE, AND MAINTENANCE MODEL 208B G1000 GROUND DEICE/ANTI-ICE OPERATIONS (Continued) CAUTION Type I fluids should never be used full strength (undiluted). Undiluted glycol fluid is quite viscous below 14°F (-10°C) and can actually produce lift reductions of about 20 percent.
Page 513 CESSNA SECTION 8 MODEL 208B G1000 HANDLING, SERVICE, AND MAINTENANCE HOLDOVER TIMETABLE (TYPE I, TYPE II, TYPE III, AND TYPE IV FLUIDS) (Continued) Guidelines for maximum holdover times anticipated by SAE Type I, Type II, Type III or Type IV, and ISO Type I, Type II, Type III, or Type IV fluid mixtures are a function of weather conditions and outside air temperature (OAT).
Page 514 SECTION 8 CESSNA HANDLING, SERVICE, AND MAINTENANCE MODEL 208B G1000 HOLDOVER TIMETABLE (TYPE I, TYPE II, TYPE III, AND TYPE IV FLUIDS) (Continued) WARNING When ground icing conditions are present, a pretakeoff contamination check must be conducted by the pilot in command within 5 minutes of takeoff, preferably just prior to taxiing onto the active runway.
Page 515 CESSNA SECTION 8 MODEL 208B G1000 HANDLING, SERVICE, AND MAINTENANCE TYPE II ANTI-ICE FLUID NOTE • Freezing point of Type II fluid mixture must be at least 10°C (18°F) below OAT. • Holdover time starts when last application has begun.
Page 516 SECTION 8 CESSNA HANDLING, SERVICE, AND MAINTENANCE MODEL 208B G1000 TYPE III ANTI-ICE FLUID NOTE • Freezing point of Type III fluid mixture must be at least 10°C (18°F) below OAT. • Holdover time starts when last application has begun.
Page 517 CESSNA SECTION 8 MODEL 208B G1000 HANDLING, SERVICE, AND MAINTENANCE TYPE IV ANTI-ICE FLUID (Continued) NOTE • Freezing point of Type IV fluid mixture must be at least 10°C (18°F) below OAT. • Holdover time starts when last application has begun.
Page 518: Essential Areas To Be Deiced
SECTION 8 CESSNA HANDLING, SERVICE, AND MAINTENANCE MODEL 208B G1000 ESSENTIAL AREAS TO BE DEICED SHADED AREAS INDICATE ESSENTIAL AREAS TO BE DEICED. NOTE 1. Give special attention to the gaps between the flight controls. All snow, ice, and slush must be removed from these gaps.
Page 519: Essential Areas To Apply Anti-Ice Fluid
CESSNA SECTION 8 MODEL 208B G1000 HANDLING, SERVICE, AND MAINTENANCE ESSENTIAL AREAS TO APPLY ANTI-ICE FLUID Shaded areas indicate essential areas where anti-ice fluid is applied. NOTE Anti-ice fluid must be applied at low pressure to form a thin film on surfaces. Fluid must just cover airplane without runoff.
Page 520: Deice And Anti-Ice Fluid Direct Spray Avoidance Areas
SECTION 8 CESSNA HANDLING, SERVICE, AND MAINTENANCE MODEL 208B G1000 DEICE AND ANTI-ICE FLUID DIRECT SPRAY AVOIDANCE AREAS DIRECT SPRAY AVOIDANCE AREAS: Engine Inlets and Exhaust, Brakes, Pitot-static Tubes, Windshields, Cabin Windows, and Stall Warning Vane. Figure 8-3 208BPHBUS-00 U.S.
Page 521: Deicing And Anti-Icing Application
CESSNA SECTION 8 MODEL 208B G1000 HANDLING, SERVICE, AND MAINTENANCE DEICING AND ANTI-ICING APPLICATION NOTE Start the deice and anti-ice application at the left front area of the airplane. The pilot can then get a conservative estimate of how quickly ice forms by observation from inside the cockpit.
Page 522: (Continued Next Page)
SECTION 8 CESSNA HANDLING, SERVICE, AND MAINTENANCE MODEL 208B G1000 CLEANING AND CARE WINDSHIELD AND WINDOWS The windshield and windows are constructed of cast acrylic. The surface hardness of acrylic is approximately equal to that of copper or brass. Do not use a canvas cover on the windshield unless freezing rain or sleet is anticipated.
Page 523 On acrylic surfaces, use only rain repellents that conform to specification MIL-W-6882. Refer to the Materials For Acrylic Windshields and Windows chart for specific rain repellent products approved by Cessna. NOTE When applying or removing wax or polish, use a clean soft cloth.
Page 524 SECTION 8 CESSNA HANDLING, SERVICE, AND MAINTENANCE MODEL 208B G1000 WINDSHIELD WINDOW PREVENTIVE MAINTENANCE CAUTION Utilization of the following techniques will help minimize windshield and window crazing. 1. Keep all surfaces of windshields and windows clean. 2. If desired, wax acrylic surfaces.
Page 525 1. These are the only polishing waxes tested and approved for use by Cessna Aircraft Company. 2. This is the only rain repellent approved for use by Cessna Aircraft Company for use on Cessna Model 208B series airplanes. Figure 8-5...
Page 526: Painted Surfaces
MODEL 208B G1000 PAINTED SURFACES The painted exterior surfaces of the Cessna 208B have a durable, long- lasting finish. Approximately 10 days are required for the paint to cure completely; in most cases, the curing period will have been completed prior to delivery of the airplane.
Page 527: Stabilizer Abrasion Boot Care
Do not scrub the boots and be sure to wipe off all solvent before it dries. Boots with loosened edges or small tears must be repaired. Your Cessna Service Station has the proper material and knowledge how to do this correctly.
Page 528: Engine Care
SECTION 8 CESSNA HANDLING, SERVICE, AND MAINTENANCE MODEL 208B G1000 ENGINE CARE ENGINE EXTERIOR/COMPARTMENT CLEANING The engine exterior and compartment may be cleaned using a suitable solvent. Most efficient cleaning is done using a spray-type cleaner. Before spray cleaning, make sure that protection is afforded for components that might be adversely affected by the solvent.
Page 529: Engine Compressor Wash
CESSNA SECTION 8 MODEL 208B G1000 HANDLING, SERVICE, AND MAINTENANCE ENGINE COMPRESSOR WASH A number of cleaning agents are recommended for addition to water to form the cleaning solution used for compressor wash. However, the mixture proportion of all the cleaning agents is not identical. Depending on the prevalent ambient temperature, aviation kerosene and methanol must be added to the cleaning solution in various proportions.
Page 530: Interior Care
SECTION 8 CESSNA HANDLING, SERVICE, AND MAINTENANCE MODEL 208B G1000 INTERIOR CARE The instrument panel, control wheel, and control knobs need only be wiped off with a damp cloth. Oil and grease on the control wheel and control knobs can be removed with a cloth moistened with Stoddard solvent.
Page 531: Prolonged Out-Of-Service Care
CESSNA SECTION 8 MODEL 208B G1000 HANDLING, SERVICE, AND MAINTENANCE PROLONGED OUT-OF-SERVICE CARE Prolonged out-of-service care applies to all airplanes that will not be flown for an indefinite period (less than 60 days) but which are to be kept ready to fly with the least possible preparation. If the airplane is to be stored temporarily or indefinitely, refer to the Airplane Maintenance Manual for proper storage procedures.
Page 532: Bulb Replacement During Flight
SECTION 8 CESSNA HANDLING, SERVICE, AND MAINTENANCE MODEL 208B G1000 PROLONGED OUT-OF-SERVICE CARE (Continued) c. 29 to 90 Days - An engine inactive for a period exceeding 28 days, but less than 91 days, need only have the fuel system preserved, engine openings covered, and desiccant bags and humidity indicators installed.
Page 533: Bulb Replacement
CESSNA SECTION 8 MODEL 208B G1000 HANDLING, SERVICE, AND MAINTENANCE BULB REPLACEMENT Figure 8-6 208BPHBUS-00 8-49/8-50 U.S.
Page 535 CESSNA SECTION 9 MODEL 208B (675 SHP) SUPPLEMENTS SUPPLEMENTS INTRODUCTION This section consists of a series of supplements, each covering a single system which may be installed in the airplane. Each supplement contains a brief description, and when applicable, Limitations, Emergency Procedures, Normal Procedures, and Performance.

Cessna Grand Caravan 208B G1000 Manual

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Section 3 Emergency Procedures

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Model 208B G1000 Airplane and Systems Description Section 7 Airplane & Systems Descriptions

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