Textron Cessna Grand Caravan Ex 208B Pilot'S Operating Handbook And Faa Approved Airplane Flight Manual Download

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U.S.

CESSNA MODEL 208B

867 SHP - GARMIN G1000

Serials 208B2197 and 208B5000 and On

SUPPLEMENT 5

CONFIGURATION DEVIATION LIST (CDL)

This supplement must be inserted into Section 9 of the Pilot's Operating Handbook

and FAA Approved Airplane Flight Manual.

SERIAL NO.

REGISTRATION NO.

208BPHCUS-S5-00

CESSNA AIRCRAFT COMPANY

WICHITA, KANSAS, USA

S5-1

19 DECEMBER 2012

Summary of Contents for Cessna Grand Caravan Ex 208B

Page 1: ...IAL NUMBER REGISTRATION NUMBER Model 208B 867 SHP Garmin G1000 Serials 208B2197 and 208B5000 and On This publication includes the material required to be furnished to the pilot by 14 CFR 23 ORIGINAL I...

Page 2: ......

Page 3: ...1000 U S PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL CESSNA MODEL 208B 867 SHP GARMIN G1000 SERIALS 208B2197 AND 208B5000 AND ON ORIGINAL ISSUE 19 DECEMBER 2012 REVISION 1 22 MA...

Page 4: ...INTRODUCTION CESSNA MODEL 208B 867 SHP GARMIN G1000 U S This Page Intentionally Left Blank 208BPHCUS 00 ii...

Page 5: ...ontained in the Customer Care Program Handbook supplied with your airplane The Customer Care Card assigned to you at delivery will establish your eligibility under warranty and should be presented to...

Page 6: ...URS Max Cruise at 18 000 Feet Range 985 NM Time 5 6 HOURS Max Range at 10 000 Feet Range 918 NM Time 6 0 HOURS Max Range at 18 000 Feet Range 1052 NM Time 6 6 HOURS RATE OF CLIMB AT SEA LEVEL 1275 FPM...

Page 7: ...ree Turbine Flat Rated at 867 SHP PROPELLER Hartzell Propeller Systems 3 bladed Constant Speed Full Feathering Reversible Propeller Diameter 106 Inches 2 7 m The above performance figures are based on...

Page 8: ...HOURS Max Cruise at 18 000 Feet Range 1040 NM Time 5 7 HOURS Max Range at 10 000 Feet Range 973 NM Time 6 0 HOURS Max Range at 18 000 Feet Range 1125 NM Time 6 8 HOURS RATE OF CLIMB AT SEA LEVEL 1330...

Page 9: ...Free Turbine Flat Rated at 867 SHP PROPELLER Hartzell Propeller Systems 3 bladed Constant Speed Full Feathering Reversible Propeller Diameter 106 INCHES 2 7 m The above performance figures are based o...

Page 10: ...vailable at the time of publication This POH consists of nine sections that cover all operational aspects of a standard equipped airplane Section 9 contains the supplements which provide amended opera...

Page 11: ...mple below for a breakdown It is the responsibility of the owner to maintain this POH in a current status when it is being used for operational purposes Owners should contact a Cessna Authorized Servi...

Page 12: ...ry revisions to the POH AFM may be issued These temporary revisions are to be filed in the applicable section in accordance with filing instructions appearing on the first page of the temporary revisi...

Page 13: ...or spelling grammar changes and or that information has moved to or from that page A bar located adjacent to the figure number in the margin on the left side of the page will be used to indicate that...

Page 14: ...to equipment if not carefully obeyed NOTE An operating procedure technique or maintenance condition which is considered essential to emphasize LAND AS SOON AS POSSIBLE Land at the nearest suitable air...

Page 15: ...Date of Issue Original Issue 19 December 2012 Revision 1 22 May 2013 Page Number Page Status Revision Number Title Revised 1 Assignment Record Original 0 i Revised 1 ii thru xii Original 0 xiii thru...

Page 16: ...4 thru 3 66 Original 0 3 67 thru 3 69 Revised 1 3 70 thru 3 102 Original 0 4 1 thru 4 56 Original 0 4 57 thru 4 58 Revised 1 4 59 thru 4 63 Original 0 4 64 Revised 1 4 65 thru 4 67 Original 0 4 68 Rev...

Page 17: ...age Status Revision Number 7 60 Original 0 7 61 Revised 1 7 62 thru 7 75 Original 0 7 76 thru 7 78 Revised 1 7 79 thru 7 126 Original 0 8 1 thru 8 16 Original 0 8 17 thru 8 18 Revised 1 8 19 thru 8 20...

Page 18: ...INTRODUCTION CESSNA MODEL 208B 867 SHP GARMIN G1000 U S This Page Intentionally Left Blank 208BPHCUS 01 xvi...

Page 19: ...s a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this manual This list contains only those Service Bulletins that are currently active...

Page 20: ...INTRODUCTION CESSNA MODEL 208B 867 SHP GARMIN G1000 U S This Page Intentionally Left Blank 208BPHCUS 01 xviii...

Page 21: ...S TABLE OF CONTENTS SECTION GENERAL 1 LIMITATIONS 2 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT AND BALANCE EQUIPMENT LIST 6 AIRPLANE AND SYSTEM DESCRIPTION 7 AIRPLANE HANDLING SER...

Page 22: ...INTRODUCTION CESSNA MODEL 208B 867 SHP GARMIN G1000 U S This Page Intentionally Left Blank 208BPHCUS 01 xx...

Page 23: ...1 11 Specific Loadings 1 11 Symbols Abbreviations and Terminology 1 12 General Airspeed Terminology And Symbols 1 12 Meteorological Terminology 1 13 Engine Power Terminology 1 13 Airplane Performance...

Page 24: ...SECTION 1 CESSNA GENERAL MODEL 208B 867 SHP GARMIN G1000 U S This Page Intentionally Left Blank 208BPHCUS 00 1 2...

Page 25: ...CESSNA SECTION 1 MODEL 208B 867 SHP GENERAL GARMIN G1000 U S THREE VIEW NORMAL GROUND ATTITUDE Figure 1 1 Sheet 1 of 2 208BPHCUS 00 1 3...

Page 26: ...th nose gear strut depressed as far as possible Wheel base length is 13 feet 3 5 inches 4 05 m Wing area is 279 4 square feet 25 9 sq m Minimum turning radius pivot point to outboard wing tip strobe l...

Page 27: ...esponsibility of the airplane owner or operator Determining if the airplane is safe for flight is the responsibility of the pilot in command The pilot is also responsible for adhering to the operating...

Page 28: ...Maximum 106 Inches 2 7 m Minimum 104 Inches 2 6 m Propeller Type Constant speed full feathering reversible hydraulically actuated aluminum propeller with a feathered blade angle of 78 0 1 0 a low pit...

Page 29: ...ONENTS RESULTING IN POSSIBLE ENGINE FAILURE APPROVED FUEL GRADES NOTE Refer to Section 2 Limitations Fuel Limitations for more information on Approved Fuels Continued Next Page JET A ASTM D1655 JP 8 1...

Page 30: ...percent by volume GOST 8313 Fluid I Type Anti Ice Additive in a concentration of 0 10 to 0 30 percent by volume CIS TU6 10 1458 Fluid I M Type Anti Ice Additive in a concentration of 0 10 to 0 30 perc...

Page 31: ...339 1 U S Gallons 1283 l Both Tanks 335 6 U S Gallons 1270 l Each Tank 167 8 U S Gallons 635 l TOTAL USABLE FUEL Both Tanks ON and Reservoir 335 3 U S Gallons 1268 l Both Tanks ON 332 0 U S Gallons 1...

Page 32: ...uarts low if oil is hot For example a dipstick reading of 3 indicates the system is within 2 quarts of MAX if the oil is cold and within 3 quarts of MAX if the oil is hot WARNING Make sure oil dipstic...

Page 33: ...DIMENSIONS Refer to Section 6 Weight and Balance Cabin Internal Dimensions for detailed dimensions of the cabin interior and entry door openings BAGGAGE CARGO COMPARTMENT AND CARGO DOOR AND ENTRY DIME...

Page 34: ...hich full or abrupt control movements may be used without overstressing the airframe VFE Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position...

Page 35: ...1000 feet Standard Temperature Standard Temperature is 15 C at sea level pressure altitude and decreases by 2 C for each 1000 feet of altitude Pressure Altitude Pressure Altitude is the altitude read...

Page 36: ...ne performance i e severe icing conditions or windshear downdrafts This power corresponds to that developed at the maximum torque limit ITT of 825 C or Ng limit whichever is less Ng Ng signifies gas g...

Page 37: ...he distance which can be expected per 1000 pounds of fuel consumed at a specific engine power setting and or flight configuration g g is acceleration due to gravity Course Datum Course Datum is the co...

Page 38: ...cally controls attitude and or flight path of the airplane as directed by the pilot through the system s computer Flight Director Flight Director is a system which provides visual recommendations to t...

Page 39: ...ng the number of digits Center of Gravity C G Center of Gravity is the point at which an airplane or equipment would balance if suspended Its distance from the reference datum is found by dividing the...

Page 40: ...ht is the maximum weight approved for ground maneuver and includes the weight of fuel used for start taxi and runup Maximum Takeoff Weight Maximum Takeoff Weight is the maximum weight approved for the...

Page 41: ...tional operators convert U S measurement supplied with the POH AFM into metric and imperial measurements The standard followed for measurement units shown is the National Institute of Standards Techno...

Page 42: ...SECTION 1 CESSNA GENERAL MODEL 208B 867 SHP GARMIN G1000 U S WEIGHT CONVERSIONS Figure 1 2 Sheet 1 of 2 208BPHCUS 00 1 20...

Page 43: ...CESSNA SECTION 1 MODEL 208B 867 SHP GENERAL GARMIN G1000 U S WEIGHT CONVERSIONS Figure 1 2 Sheet 2 208BPHCUS 00 1 21...

Page 44: ...SECTION 1 CESSNA GENERAL MODEL 208B 867 SHP GARMIN G1000 U S LENGTH CONVERSIONS Figure 1 3 Sheet 1 of 4 208BPHCUS 00 1 22...

Page 45: ...CESSNA SECTION 1 MODEL 208B 867 SHP GENERAL GARMIN G1000 U S LENGTH CONVERSIONS Figure 1 3 Sheet 2 208BPHCUS 00 1 23...

Page 46: ...SECTION 1 CESSNA GENERAL MODEL 208B 867 SHP GARMIN G1000 U S LENGTH CONVERSIONS Figure 1 3 Sheet 3 208BPHCUS 00 1 24...

Page 47: ...CESSNA SECTION 1 MODEL 208B 867 SHP GENERAL GARMIN G1000 U S LENGTH CONVERSIONS Figure 1 3 Sheet 4 208BPHCUS 00 1 25...

Page 48: ...SECTION 1 CESSNA GENERAL MODEL 208B 867 SHP GARMIN G1000 U S DISTANCE CONVERSIONS Figure 1 4 208BPHCUS 00 1 26...

Page 49: ...CESSNA SECTION 1 MODEL 208B 867 SHP GENERAL GARMIN G1000 U S VOLUME CONVERSIONS Figure 1 5 Sheet 1 of 3 208BPHCUS 00 1 27...

Page 50: ...SECTION 1 CESSNA GENERAL MODEL 208B 867 SHP GARMIN G1000 U S VOLUME CONVERSIONS Figure 1 5 Sheet 2 208BPHCUS 00 1 28...

Page 51: ...CESSNA SECTION 1 MODEL 208B 867 SHP GENERAL GARMIN G1000 U S VOLUME CONVERSIONS Figure 1 5 Sheet 3 208BPHCUS 00 1 29...

Page 52: ...SECTION 1 CESSNA GENERAL MODEL 208B 867 SHP GARMIN G1000 U S TEMPERATURE CONVERSIONS Figure 1 6 208BPHCUS 00 1 30...

Page 53: ...CESSNA SECTION 1 MODEL 208B 867 SHP GENERAL GARMIN G1000 U S PRESSURE CONVERSION HECTOPASCALS TO INCHES OF MERCURY Figure 1 7 208BPHCUS 00 1 31...

Page 54: ...SECTION 1 CESSNA GENERAL MODEL 208B 867 SHP GARMIN G1000 U S This Page Intentionally Left Blank 208BPHCUS 00 1 32...

Page 55: ...Limits 2 14 Kinds Of Operations Limits 2 15 Kinds of Operations Equipment List 2 16 Fuel Limitations 2 25 Maximum Operating Altitude Limit 2 28 Outside Air Temperature Limits 2 28 Maximum Passenger Se...

Page 56: ...nal Equipment User s Guide 2 37 Type II Type III or Type IV Anti ice Fluid Takeoff Limitations 2 37 Flight in Known Icing Visual Cues 2 38 Placards 2 39 Interior Placards 2 39 Flight Crew Area 2 39 Pa...

Page 57: ...nited States may require observance of other limitations procedures or performance data Refer to Section 9 Supplements of this POH AFM for amended operating limitations operating procedures performanc...

Page 58: ...OVED AIRSPEED LIMITATIONS The airspeed limitations below are based on the maximum gross takeoff weight of 8807 pounds 3994 kg The maximum operating maneuvering speeds VA and applicable gross weight li...

Page 59: ...e PFD and standby airspeed indicator is indicated with an airspeed tape with colored bands refer to Section 7 Flight Instruments for more information on airspeed indication The indicator markings and...

Page 60: ...nd all revisions or supplements thereto must be used Refer to Section 8 Airplane Handling Service and Maintenance Servicing Oil for a listing of approved oils When adding oil service the engine with t...

Page 61: ...oss of airplane control or may result in an engine overspeed condition and consequent loss of engine power Operation of the EMERGENCY POWER Lever is prohibited with the POWER Lever out of the IDLE pos...

Page 62: ...SECTION 2 CESSNA OPERATING LIMITATIONS MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED POWERPLANT LIMITATIONS Continued ENGINE OPERATING LIMITS Figure 2 3 Sheet 1 of 2 208BPHCUS 00 2 8...

Page 63: ...e engine be shut down or a landing be made as soon as possible using the minimum power required to maintain flight 4 2090 PROP RPM may be used in an emergency condition to complete a flight and may be...

Page 64: ...OAT and pressure altitude Takeoff torque is displayed up to 16 000 feet MSL while maximum rated torque is displayed at 16 000 feet MSL and above 2 Incorporates blue torque bug that moves to compensat...

Page 65: ...A APPROVED MISCELLANEOUS INSTRUMENT MARKINGS Power plant instrument markings and their color significance are shown in Figure 2 5 NOTE 1 OFF mode is defined as anytime the engine is not running and th...

Page 66: ...n 4 Normal Procedures is required in addition to a visual inspection if the OAT is below 10 C 50 F During ground icing conditions takeoff must be accomplished within 5 minutes of completing the tactil...

Page 67: ...UT CARGO POD 185 00 inches 4699 mm 11 19 MAC aft of datum at 6500 pounds 2948 kg or less with straight line variation to 193 37 inches 4912 mm 23 80 MAC aft of datum at 8000 pounds 3628 kg and straigh...

Page 68: ...ental to normal flying stalls except whip stalls lazy eights chandelles and turns in which the angle of bank is not more than 60 Aerobatic maneuvers including spins are not approved FLIGHT LOAD FACTOR...

Page 69: ...ipment List KOEL identifies the systems and equipment upon which type certification for each kind of operation was predicated These systems and equipment items must be installed and operable unless 1...

Page 70: ...SECTION 2 CESSNA OPERATING LIMITATIONS MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED KINDS OF OPERATIONS EQUIPMENT LIST Continued Next Page 208BPHCUS 01 2 16...

Page 71: ...CESSNA SECTION 2 MODEL 208B 867 SHP OPERATING LIMITATIONS GARMIN G1000 U S FAA APPROVED KINDS OF OPERATIONS EQUIPMENT LIST Continued Continued Next Page 208BPHCUS 01 2 17...

Page 72: ...SECTION 2 CESSNA OPERATING LIMITATIONS MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED KINDS OF OPERATIONS EQUIPMENT LIST Continued Continued Next Page 208BPHCUS 01 2 18...

Page 73: ...CESSNA SECTION 2 MODEL 208B 867 SHP OPERATING LIMITATIONS GARMIN G1000 U S FAA APPROVED KINDS OF OPERATIONS EQUIPMENT LIST Continued Continued Next Page 208BPHCUS 01 2 19...

Page 74: ...SECTION 2 CESSNA OPERATING LIMITATIONS MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED KINDS OF OPERATIONS EQUIPMENT LIST Continued Continued Next Page 208BPHCUS 01 2 20...

Page 75: ...CESSNA SECTION 2 MODEL 208B 867 SHP OPERATING LIMITATIONS GARMIN G1000 U S FAA APPROVED KINDS OF OPERATIONS EQUIPMENT LIST Continued Continued Next Page 208BPHCUS 01 2 21...

Page 76: ...SECTION 2 CESSNA OPERATING LIMITATIONS MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED KINDS OF OPERATIONS EQUIPMENT LIST Continued Continued Next Page 208BPHCUS 01 2 22...

Page 77: ...CESSNA SECTION 2 MODEL 208B 867 SHP OPERATING LIMITATIONS GARMIN G1000 U S FAA APPROVED KINDS OF OPERATIONS EQUIPMENT LIST Continued Continued Next Page 208BPHCUS 01 2 23...

Page 78: ...SECTION 2 CESSNA OPERATING LIMITATIONS MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED KINDS OF OPERATIONS EQUIPMENT LIST Continued 208BPHCUS 01 2 24...

Page 79: ...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...

Page 80: ...FAA APPROVED FUEL LIMITATIONS It is assumed that fuel temperature is the same as Outside Air Temperature OAT AN8 is JP 8 fuel with a reduced freeze point specified for Antarctic operations Figure 2 6...

Page 81: ...ive in a concentration of 0 10 to 0 15 percent by volume 2 MIL DTL 27686 EGME or MIL DTL 85470 DiEGME Type Anti Ice Additive in a concentration of 0 10 to 0 20 percent by volume 3 GOST 8313 Fluid I Ty...

Page 82: ...l presentation of the operating air temperature limits NOTE With both deck skin fans inoperative ground operations are limited to 42 C for 30 minutes Ground operations up to 38 C are not time limited...

Page 83: ...tronic Devices PED such as cellular telephones games cassette CD or MP3 players is prohibited under IFR unless the operator of the airplane has determined that the use of the Aux Audio System and the...

Page 84: ...eed air heat position ON GROUND IN FLIGHT MAXIMUM GENERATOR LOAD GROUND OPERATIONS AIR CONDITIONING OFF BLEED AIR HEAT ON or OFF AIR CONDITIONING ON BLEED AIR HEAT OFF Ng AMPS Ng AMPS 55 65 55 35 60 1...

Page 85: ...base The G1000 database must incorporate the current update cycle Use of the NAVIGATION MAP page for pilotage navigation is prohibited The Navigation Map is intended only to enhance situational awaren...

Page 86: ...f for current altitude and temperature The dynamic redline is a graphical representation of takeoff power below 16 000 feet MSL and Maximum Rated Power above 16 000 feet MSL as depicted in Section 5 P...

Page 87: ...er approved version a Oceanic Remote RNP 10 per FAA AC 20 138C FAA Order 8400 12C and FAA Order 8900 1 Both GPS receivers are required to be operating and receiving usable signals except for routes re...

Page 88: ...ngagement speed 175 KIAS Autopilot minimum engagement speed 80 KIAS Electric Trim maximum operating speed 175 KIAS 5 The autopilot must be disengaged below 200 feet AGL during approach operations and...

Page 89: ...ermine the age of the weather information shown by the XM data link weather product Due to time delays inherent in gathering and processing weather data for XM data link transmission the weather infor...

Page 90: ...nhibited when landing at a location not included in the airport database Use of TAWS B is prohibited when operating using the QFE altimeter setting altimeter indicates 0 feet altitude when the airplan...

Page 91: ...E The pilot is responsible for ensuring the appropriate user s guide s for all optional equipment installed in the airplane is accessible to the pilot in flight TYPE II TYPE III OR TYPE IV ANTI ICE FL...

Page 92: ...ed those for which the airplane is certificated shall be determined by the following visual cues If one or more of these visual cues exists immediately request priority handling from Air Traffic Contr...

Page 93: ...ds is required as specified in this section Placard wording can be from part numbered placards obtained from Cessna Aircraft Company or equivalent placards installed by an approved repair station in a...

Page 94: ...ITATIONS MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED PLACARDS Continued INTERIOR PLACARDS Continued FLIGHT CREW AREA Continued In full view of the pilot on the sunvisor or windshield trim Continu...

Page 95: ...RATING LIMITATIONS GARMIN G1000 U S FAA APPROVED PLACARDS Continued INTERIOR PLACARDS Continued FLIGHT CREW AREA Continued On overhead panel adjacent to fuel tank selectors Located on magnetic compass...

Page 96: ...TIONS MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED PLACARDS Continued INTERIOR PLACARDS Continued FLIGHT CREW AREA Continued Above left side PFD On instrument panel below standby instruments Conti...

Page 97: ...NG LIMITATIONS GARMIN G1000 U S FAA APPROVED PLACARDS Continued INTERIOR PLACARDS Continued FLIGHT CREW AREA Continued On pedestal adjacent to wing flap position indicator On pedestal below the power...

Page 98: ...208B 867 SHP GARMIN G1000 U S FAA APPROVED PLACARDS Continued INTERIOR PLACARDS Continued FLIGHT CREW AREA Continued On left and right lower sidewall below and forward of instrument panel On the contr...

Page 99: ...208B 867 SHP OPERATING LIMITATIONS GARMIN G1000 U S FAA APPROVED PLACARDS Continued INTERIOR PLACARDS Continued FLIGHT CREW AREA Continued Adjacent to left crew door inside door handle Continued Next...

Page 100: ...S FAA APPROVED PLACARDS Continued INTERIOR PLACARDS Continued PASSENGER AREA Adjacent to upper passenger door inside door handle Passenger version only Adjacent to the interior door handle of lower pa...

Page 101: ...APPROVED PLACARDS Continued INTERIOR PLACARDS Continued PASSENGER AREA Continued On right sidewall aft of lower passenger door below window trim Passenger version only Adjacent to upper cargo door int...

Page 102: ...AA APPROVED PLACARDS Continued INTERIOR PLACARDS Continued CARGO AREA On left and right sides of the cargo barrier Cargo version or Passenger version when cargo barrier is installed On right sidewall...

Page 103: ...HP OPERATING LIMITATIONS GARMIN G1000 U S FAA APPROVED PLACARDS Continued INTERIOR PLACARDS Continued CARGO AREA Continued On left and right sides of cabin in appropriate zones Cargo version only Cont...

Page 104: ...ERIOR PLACARDS Continued CARGO AREA Continued On inside of lower cargo door Cargo version only At each sidewall and ceiling anchor plate except heavy duty anchor plates with additional structural supp...

Page 105: ...SSNA SECTION 2 MODEL 208B 867 SHP OPERATING LIMITATIONS GARMIN G1000 U S FAA APPROVED PLACARDS Continued EXTERIOR PLACARDS On inside of cargo pod doors if installed Continued Next Page 208BPHCUS 00 2...

Page 106: ...ITATIONS MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED PLACARDS Continued EXTERIOR PLACARDS Continued Adjacent to upper cargo door outside pushbutton and door handle Passenger version only Continue...

Page 107: ...CESSNA SECTION 2 MODEL 208B 867 SHP OPERATING LIMITATIONS GARMIN G1000 U S FAA APPROVED PLACARDS Continued EXTERIOR PLACARDS Continued Continued Next Page 208BPHCUS 00 2 53...

Page 108: ...SECTION 2 CESSNA OPERATING LIMITATIONS MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED PLACARDS Continued EXTERIOR PLACARDS Continued WINGS Continued Next Page 208BPHCUS 00 2 54...

Page 109: ...ODEL 208B 867 SHP OPERATING LIMITATIONS GARMIN G1000 U S FAA APPROVED PLACARDS Continued EXTERIOR PLACARDS Continued WINGS Continued On bottom of each wing just forward of aileron Continued Next Page...

Page 110: ...CESSNA OPERATING LIMITATIONS MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED PLACARDS Continued EXTERIOR PLACARDS Continued ENGINE COMPARTMENT On the brake fluid reservoir Continued Next Page 208BPHC...

Page 111: ...SHP OPERATING LIMITATIONS GARMIN G1000 U S FAA APPROVED PLACARDS Continued EXTERIOR PLACARDS Continued ENGINE COMPARTMENT Continued Adjacent to oil dipstick filler cap on inertial separator duct Conti...

Page 112: ...OPERATING LIMITATIONS MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED PLACARDS Continued EXTERIOR PLACARDS Continued ENGINE COMPARTMENT Continued On firewall above battery tray Continued Next Page 2...

Page 113: ...N 2 MODEL 208B 867 SHP OPERATING LIMITATIONS GARMIN G1000 U S FAA APPROVED PLACARDS Continued EXTERIOR PLACARDS Continued FORWARD FUSELAGE Above ground service plug receptacle Continued Next Page 208B...

Page 114: ...MITATIONS MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED PLACARDS Continued EXTERIOR PLACARDS Continued FORWARD FUSELAGE Continued On each side of nose strut fairing near tow limit marking Continued...

Page 115: ...B 867 SHP OPERATING LIMITATIONS GARMIN G1000 U S FAA APPROVED PLACARDS Continued EXTERIOR PLACARDS Continued AFT FUSELAGE On the left side of the tailcone stinger affixed to the rudder lock shaft cove...

Page 116: ...SECTION 2 CESSNA OPERATING LIMITATIONS MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED This Page Intentionally Left Blank 208BPHCUS 00 2 62...

Page 117: ...mediately After Takeoff 3 9 Engine Failure During Flight 3 10 Engine Flameout During Flight 3 11 AIRSTART 3 12 Starter Assist 3 12 FORCED LANDINGS 3 14 Emergency Landing Without Engine Power 3 14 Prec...

Page 118: ...MERG PWR LVR Annunciator Comes On Prior To or During Engine Start 3 27 FUEL SYSTEM 3 28 Red RSVR FUEL LOW Annunciator Comes On 3 28 Red FUEL SELECT OFF Annunciator Comes On During Engine Start and Aur...

Page 119: ...6 Emergency Descent Through Clouds Dual AHRS Failure 3 47 Recovery From Spiral Dive In The Clouds Dual AHRS Failure 3 48 Spins 3 49 Engine Malfunctions 3 50 Loss of Oil Pressure 3 50 Uncommanded Engin...

Page 120: ...SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED This Page Intentionally Left Blank 208BPHCUS 00 3 4...

Page 121: ...r should an emergency arise the basic guidelines described in this section should be considered and applied as necessary to correct the problem In any emergency situation the most important task is co...

Page 122: ...kg 125 KIAS 5000 POUNDS 2267 kg 112 KIAS MAXIMUM GLIDE WITH CARGO POD 8807 POUNDS 3994 kg 95 KIAS 7500 POUNDS 3401 kg 87 KIAS 6250 POUNDS 2834 kg 79 KIAS 5000 POUNDS 2267 kg 71 KIAS MAXIMUM GLIDE WITH...

Page 123: ...gency procedures require immediate pilot recognition and corrective action by the crew Red annunciators will flash and pressing the WARNING softkey will silence the repeating chime and change the annu...

Page 124: ...r white annunciators should be determined prior to flight If a red or amber annunciation occurs in flight consideration should be given to landing at an airport where corrective maintenance can be per...

Page 125: ...OT BE STOPPED ON REMAINING RUNWAY 4 FUEL CONDITION Lever CUTOFF 5 FUEL OIL SHUTOFF Knob PULL OFF 6 FUEL TANK SELECTORS OFF aural warning horn will sound 7 BATTERY Switch OFF ENGINE FAILURE IMMEDIATELY...

Page 126: ...to landing turn both LEFT and RIGHT LDG light switches to ON f VENT AIR FANS OFF g AIR CONDITIONING if installed OFF h GEN CONT and GEN FIELD Circuit Breakers OPEN pull out top row last two breakers...

Page 127: ...VIDENCED BY NORMAL ITT AND Ng INDICATIONS 3 POWER Lever AS DESIRED 4 IGNITION Switch NORM if cause of flameout has been corrected 2 2 Refer to AIRSTART procedure on following page for engine restart i...

Page 128: ...e torque bug will become inoperative and will not be shown on the EIS torque indicator c IGNITION Switch NORM d Circuit Breakers CLOSE push in e Left LIGHTS Panel Switches 9 total OFF f POWER OUTLET S...

Page 129: ...rising c Ng Indicator 12 RPM minimum 14 FUEL CONDITION Lever LOW IDLE and OBSERVE a FFLOW PPH Indicator 90 140 PPH b ITT Indicator MONITOR 1090 C maximum c Ng Indicator 55 RPM minimum 15 STARTER Swit...

Page 130: ...E 5 PROP RPM Lever FEATHER 6 FUEL CONDITION Lever CUTOFF 7 FUEL BOOST Switch OFF 8 IGNITION Switch NORM 9 STBY ALT PWR Switch OFF 10 Nonessential Equipment OFF 11 FUEL OIL SHUTOFF Knob PULL OFF 12 FUE...

Page 131: ...irspeed 90 KIAS 5 Selected Field FLY OVER noting terrain and obstructions 6 Nonessential Equipment OFF except BATTERY GENERATOR and STBY ALT PWR 7 WING FLAPS Handle LAND on final approach 8 Airspeed 8...

Page 132: ...Winds Heavy Seas INTO THE WIND b Light Winds Heavy Swells PARALLEL TO SWELLS 7 Cabin Doors UNLATCH 8 Face CUSHION AT TOUCHDOWN with folded coat or similar object 9 Touchdown LEVEL ATTITUDE AT ESTABLI...

Page 133: ...tarting cycle limitations Refer to Section 2 Limitations Engine Starting Cycle Limits 4 STARTER Switch OFF 5 FUEL OIL SHUTOFF Knob PULL OFF 6 BATTERY Switch OFF 7 Airplane EVACUATE 8 Fire EXTINGUISH C...

Page 134: ...h in b Overhead Air Vents OPEN c VENT AIR Control Knobs OPEN FAN POSITION d AIR CONDITIONING Switch if installed OFF 7 WING FLAPS Handle TO APR LAND 8 Airspeed 80 85 KIAS 9 Forced Landing EXECUTE refe...

Page 135: ...ould use oxygen masks if installed until smoke clears After discharging an extinguisher within a closed cabin ventilate the cabin 8 AVIONICS No 1 and No 2 Power Switches OFF WARNING With AVIONICS No 1...

Page 136: ...itches ON 15 Electrical Switches ON Slowly turn switches on one at a time while monitoring current draw until faulty circuit is identified 16 Vents OPEN when sure that fire is completely extinguished...

Page 137: ...indicator will be operative WARNING Occupants should use oxygen masks if installed until smoke clears After discharging an extinguisher within a closed cabin ventilate the cabin 8 Land airplane as so...

Page 138: ...T Switch OFF 3 STROBE Lights Switch OFF 4 NAV Lights Switch OFF 5 LDG and TAXI RECOG Lights Switches OFF 6 LEFT FUEL QTY Circuit Breakers OPEN pull out second row third breaker from forward end 7 RIGH...

Page 139: ...sses SECURE 2 POWER Lever IDLE 3 PROP RPM Lever MAX full forward 4 WING FLAPS UP 5 Airspeed 175 KIAS ROUGH AIR 1 Seats Seat Belts Shoulder Harnesses SECURE 2 POWER Lever IDLE 3 PROP RPM Lever MAX full...

Page 140: ...es around freezing with visible moisture present If the visual cues specified in Section 2 Limitations for identifying severe icing conditions are observed accomplish the following 1 Immediately reque...

Page 141: ...ove the control full forward Cycling the PROP RPM flexes the propeller blades and high RPM increases centrifugal force causing ice to shed more readily If the INERTIAL SEPARATOR is set to BYPASS at an...

Page 142: ...PR for landing 18 Landing Distance MULTIPLY POH AFM DISTANCE BY 2 2 FLAPS UP 2 1 FLAPS TO APR 19 Minimum Approach Airspeed AT OR ABOVE 120 KIAS Flaps UP 110 KIAS Flaps TO APR WARNING With heavy ice ac...

Page 143: ...nnunciator will come on once EMERGENCY POWER lever is moved out of NORMAL CAUTION The EMERGENCY POWER lever overrides normal fuel control functions and results in the direct operation of the fuel mete...

Page 144: ...nd determine cause of the red RSVR FUEL LOW annunciation IF RED RSVR FUEL LOW ANNUNCIATOR REMAINS ON AND AMBER FUEL PRESS LOW ANNUNCIATOR COMES ON 6 Land as soon as possible refer to EMERGENCY LANDING...

Page 145: ...ight IF RED FUEL SELECT OFF ANNUNCIATOR GOES OFF AND AURAL WARNING HORNS SILENCED 2 Continue with engine start procedure RED FUEL SELECT OFF AND AMBER L R OR L R FUEL LOW ANNUNCIATORS COME ON 2 Fuel B...

Page 146: ...r CLOSE push in second row first breaker from forward end NOTE When the START CONT or FUEL SEL WARN Circuit Breakers are in the open position the FUEL SELECT OFF annunciator will come on and aural war...

Page 147: ...Breakers CLOSE push in top row first and second breakers from forward end 3 GENERATOR Switch RESET IF GENERATOR OUTPUT RESUMES 4 BUS VOLTS and GEN AMPS MONITOR IF GENERATOR TRIPS OFFLINE AGAIN WITH BU...

Page 148: ...cuit Breaker OPEN pull out third row second breaker from aft end i RADAR R T Circuit Breaker OPEN pull out AVN BUS 1 second row sixth breaker from left side j HF RCVR and HF AMP Circuit Breakers OPEN...

Page 149: ...Prior to landing turn both LEFT and RIGHT LDG light switches to ON e VENT AIR FANS OFF f AIR CONDITIONING if installed OFF g GEN CONT and GEN FIELD Circuit Breakers OPEN pull out top row last two bre...

Page 150: ...WR VERIFY ON IF BUS VOLTS IS LESS THAN 24 5 WITH GENERATOR OFF AND STBY PWR INOP ANNUNCIATORS ON 3 GEN CONT and GEN FIELD Circuit Breakers CLOSE push in top row last two breakers on forward end 4 GENE...

Page 151: ...Breakers OPEN pull out top row last two breakers on forward end j RIGHT PITOT HEAT Circuit Breaker OPEN pull out second row third breaker from aft end k RDNG LIGHT Circuit Breaker OPEN pull out third...

Page 152: ...es not actuate with only one half switch IF RED PTRM MESSAGE REMAINS ON 4 Autopilot DO NOT RE ENGAGE 5 A P CONT Circuit Breaker OPEN pull out AVN BUS 1 second row third breaker from left side WARNING...

Page 153: ...P CONT Circuit Breaker CLOSE push in AVN BUS 1 second row third breaker from left side IF RED AFCS OR YAW MESSAGE REMAINS ON 2 Continue flight as planned without the use of the autopilot WARNING Follo...

Page 154: ...fficient to execute a 180 gliding turn necessary to return to the runway The checklist procedures assume that adequate time exists to secure the fuel and electrical systems prior to touchdown After an...

Page 155: ...to attempt a restart Regardless of airspeed or altitude there is always the possibility that the engine can restart successfully just as soon as the IGNITION is switched ON In an emergency turn the IG...

Page 156: ...ow 10 starting temperatures tend to be higher and caution is required CAUTION The FUEL CONDITION lever can be moved momentarily to CUTOFF and then back to LOW IDLE if overtemperature tendencies are en...

Page 157: ...CESSNA SECTION 3 MODEL 208B 867 SHP EMERGENCY PROCEDURES GARMIN G1000 U S FAA APPROVED MAXIMUM GLIDE Figure 3 1 208BPHCUS 00 3 41...

Page 158: ...ion during the final phase of an approach to an off airport landing With the FUEL TANK SELECTORS turned OFF there is adequate fuel in the fuel reservoir for 3 minutes of maximum continuous power opera...

Page 159: ...n on the nosewheel first After touchdown set the POWER lever to IDLE SMOKE AND FIRE In the event a fire is encountered the following information will be helpful in dealing with the emergency as quickl...

Page 160: ...knob and shut down the engine Close the CABIN HEAT FIREWALL SHUTOFF control and forward side air vents to avoid drawing fire into the cabin open the overhead air vents set WING FLAPS to LAND and reduc...

Page 161: ...ingle AHRS unit fails in flight red X s shown through the PFD attitude and heading indicators the pilot must rely on the cross side AHRS for attitude and heading information The autopilot will not ope...

Page 162: ...ate a 15 bank left turn Keep feet off rudder pedals Maintain altitude and 15 bank angle Continue the turn for 60 seconds then roll back to level flight 4 When the compass card becomes sufficiently sta...

Page 163: ...the compass heading and make minor corrections to hold an approximate course The autopilot will not operate if the AHRS unit fails The pilot must manually fly the airplane without AHRS input Before d...

Page 164: ...carefully leveling the wings using aileron control to align the roll index and roll pointer of the standby attitude indicator 4 Cautiously apply elevator back pressure to slowly reduce the airspeed t...

Page 165: ...ENOUGH TO BREAK THE STALL Full down elevator will be required at aft center of gravity loadings to assure optimum recoveries 5 HOLD THESE CONTROL INPUTS UNTIL ROTATION STOPS Premature relaxation of t...

Page 166: ...of the onset of propeller feathering or engine seizure The ENGINE FAILURE DURING FLIGHT checklist should be completed at that time Operation of the engine at a reduced power setting preferably at the...

Page 167: ...WER lever forward of IDLE and advance as required CAUTION When using the fuel control manual override system engine response can be more rapid than when using the POWER lever Utilize slow and smooth m...

Page 168: ...approximately 2 5 PSI Anytime the level of fuel in the fuel reservoir drops to approximately one half full the red RSVR FUEL LOW annunciator will come on If this occurs the pilot should immediately v...

Page 169: ...below approximately 25 gallons The warning system includes a red FUEL SELECT OFF annunciator and two aural warning horns If the FUEL SEL WARN circuit breaker has opened or the START CONT circuit brea...

Page 170: ...r distribution bus The most likely causes of a generator trip disconnection are line surges open circuit breakers or accidental switch operation In these cases follow the AMBER GENERATOR OFF ANNUNCIAT...

Page 171: ...ition The electrical power distribution system consists of a primary power distribution bus in the engine compartment which receives power from the battery and the generator and two No 1 and No 2 main...

Page 172: ...MPS BAT AMPS and BUS VOLTS indicators on the ELECTRICAL section of the EIS Systems page will provide further information concerning the location of the fault or the system affected by the fault In the...

Page 173: ...failure both avionics buses can be connected to the remaining feeder by setting the AVIONICS BUS TIE switch to the ON position If a ground fault has occurred on one feeder it will be necessary to veri...

Page 174: ...alternator power If the standby electrical system is carrying more than 10 amps of the electrical load the white STBY PWR ON annunciator will be shown and the ALT AMPS indicator will indicate the amo...

Page 175: ...Figure 3 2 Emergency Exits Diagram Emergency ground egress from the 208B Cargomaster is accomplished by exiting the airplane through the left and right crew entry doors as shown in Figure 3 2 WARNING...

Page 176: ...SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED EMERGENCY EXITS TYPICAL Figure 3 2 208BPHCUS 00 3 60...

Page 177: ...cation Comes On HSI Indicator 3 73 Audio Panel Failure 3 74 Loss of Radio Tuning Functions 3 75 Transponder Failure 3 75 Red X on PFD Airspeed Altitude and or Vertical Speed Indicators 3 76 Attitude F...

Page 178: ...em Malfunctions 3 84 Amber GENERATOR OFF Annunciator Comes On 3 84 Amber STARTER ON Annunciator Comes On After Engine Start 3 86 Amber GENERATOR AMPS Annunciator Comes On 3 86 Amber ALTNR AMPS Annunci...

Page 179: ...mes On 3 93 Amber STALL HEAT Annunciator Comes On 3 98 Amplified Abnormal Procedures 3 99 Elevator Mistrim 3 99 Altitude Miscompare 3 99 Airspeed Miscompare 3 99 Dual GPS Failure 3 99 Transponder Fail...

Page 180: ...SECTION 3 CESSNA ABNORMAL PROCEDURES MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED This Page Intentionally Left Blank 208BPHCUS 00 3 64...

Page 181: ...e is 200 pounds 3 Approach NORMAL 4 WING FLAPS LAND 5 Touchdown INFLATED TIRE FIRST hold airplane off flat tire as long as possible with aileron control 6 Directional Control MAINTAIN using brake on w...

Page 182: ...RETRIM 4 Autopilot ENGAGE as desired AMBER ELE OR ELE INDICATION COMES ON 1 Control Wheel GRIP FIRMLY 2 AP TRIM DISC Button PRESS high elevator control forces possible NOTE The yaw damper does not ne...

Page 183: ...mputer ADC1 Do not use standby altimeter as sole source in determining correct altitude IF COPILOT PFD AND STANDBY ALTIMETER AGREE PILOT PFD DIFFERS 4 SENSOR Softkey pilot PFD PRESS 5 ADC2 Softkey PRE...

Page 184: ...m GPS altitude These errors are largest at high altitude and can amount to over 2 500 feet under some conditions However below 10 000 feet with the correct local altimeter setting set GPS altitude wil...

Page 185: ...able to descend into visual conditions plan ILS approach with course intercept well outside the Final Approach Fix FAF 11 Once glideslope is captured determine most accurate altitude source when cross...

Page 186: ...tkey PRESS 5 PFD ADI Displays CONFIRM amber BOTH ON ADC2 shown on both PFDs IF PILOT PFD AND STANDBY AIRSPEED AGREE COPILOT PFD DIFFERS 3 Pilot and Copilot Altitude COMPARE IF ALTITUDES AGREE 4 Airspe...

Page 187: ...is providing the most accurate heading information 2 Use SENSOR reversion to select the most accurate AHRS on the affected PFD NOTE Operation of the air conditioner may cause compass deviation of mor...

Page 188: ...and BARO SYNC settings must be ON to allow the copilot s PFD controls to affect settings on the MFD These settings are accessible using the PFD MENU button 2 Flight Director TRANSFER Press XFR button...

Page 189: ...DR Mode active when airplane more than 30 NM from destination airport 1 Navigation USE DR MODE use airplane symbol and magenta course line on map display WARNING All information normally derived from...

Page 190: ...ane symbol is removed from all maps The map will remain centered at the last known position NO GPS POSITION shown in center of map TAWS will be inoperative AUDIO PANEL FAILURE Audio panel failure may...

Page 191: ...ocedure will tune the active COM field to the emergency frequency 121 5 Certain failures of the tuning system will automatically tune 121 5 without pilot action TRANSPONDER FAILURE 1 TRANSPONDER SELEC...

Page 192: ...indicates a loss of valid air data system information to the respective system IF BOTH SIDES 1 Airspeed and Attitude MONITOR using standby instruments 2 Land as soon as practical IF ONE SIDE ONLY 1 Af...

Page 193: ...cal NOTE The autopilot will disconnect and may not be reengaged Reference the GPS track on MFD PFD map to improve situational awareness GPS will continue to display correct GPS based map position and...

Page 194: ...pposite NAV Source SELECT 2 PFD HSI Displays CONFIRM OPPOSITE LOC1 LOC2 or VOR1 VOR2 shown on both PFDs INACCURATE OVERSPEED WARNING Indicated by overspeed warning tone sounding when airspeed is below...

Page 195: ...de CROSS CHECK BOTH PFDs with the standby attitude indicator 3 Flight Director Modes RESELECT as desired NOTE If continued use of the flight director is desired it is recommended that only basic modes...

Page 196: ...no red X on PFD 1 or PFD 2 attitude indicator AMBER BOTH ON GPS1 OR GPS2 MESSAGE COMES ON 1 GPS Status CHECK a Select MFD AUX GPS STATUS PAGE b Select GPS1 then GPS2 softkeys and verify sufficient sat...

Page 197: ...ys CONFIRM amber BOTH ON ADC1 or ADC2 message goes off of both PFDs and no red X on PFD 1 or PFD 2 airspeed indicator AMBER USING ADC1 OR ADC2 MESSAGE COMES ON 1 Pilot s PFD SENSOR Softkey PRESS 2 PFD...

Page 198: ...K SKIN FAN Circuit Breaker CLOSE push in fourth row last breaker on forward end DOORS AMBER DOOR UNLATCHED ANNUNCIATOR COMES ON IN FLIGHT 1 Airspeed MAINTAIN LESS THAN 100 KIAS 2 WING FLAPS LAND NOTE...

Page 199: ...ight Controls MANEUVER for return for landing 3 WING FLAPS LAND 4 Approach NORMAL 5 Landing SLIGHTLY TAIL LOW avoid nose high flare RIGHT OR LEFT CREW DOOR OPENS 1 Airspeed MAINTAIN LESS THAN 125 KIAS...

Page 200: ...rward end b GENERATOR Switch RESET IF GENERATOR OUTPUT RESUMES c BUS VOLTS and GEN AMPS MONITOR IF GENERATOR TRIPS OFFLINE AGAIN WITH BUS VOLTS ABOVE 32 5 d GENERATOR Switch TRIP e AVIONICS BUS TIE Sw...

Page 201: ...IGHT Circuit Breaker OPEN pull out third row second breaker from aft end 9 RADAR R T Circuit Breaker OPEN pull out AVN BUS 1 second row sixth breaker from left side 10 HF RCVR and HF AMP Circuit Break...

Page 202: ...ER ENGINE START 4 Engine Shutdown COMPLETE AMBER GENERATOR AMPS ANNUNCIATOR COMES ON 1 GEN AMPS CHECK IF GEN AMPS INDICATION ABOVE 200 2 Electrical Load REDUCE AMBER ALTNR AMPS ANNUNCIATOR COMES ON 1...

Page 203: ...n the alternator system may still be operational A bus voltage surge may have temporarily tripped the Alternator Control Unit ACU offline The ACU can be restored by cycling the STBY ALT PWR Switch IF...

Page 204: ...d operations with CONDITION lever at LOW IDLE it is possible that a generator underspeed condition may occur allowing the standby alternator to automatically assist with the electrical load In this ca...

Page 205: ...possible refer to ENGINE FAILURE DURING FLIGHT and EMERGENCY LANDING WITHOUT ENGINE POWER IF ENGINE INDICATIONS ARE WITHIN NORMAL OPERATING RANGE 2 Continue flight as planned while monitoring engine p...

Page 206: ...eed at 50 feet by 15 KIAS 6 Increase published landing distance by 40 NOTE Refer to Section 5 Performance Figure 5 26 or Figure 5 43 Short Field Landing Distance tables IF BOTH FLAPS CANNOT BE RETRACT...

Page 207: ...h Guard MOVE breaking safety wire b Switch UP or DOWN hold switch UP or DOWN until flaps reach desired position release switch before flaps reach full up or full down travel CAUTION With the standby f...

Page 208: ...NG Watch for signs of fuel starvation 5 Land as soon as possible IF AMBER FUEL PRESS LOW ANNUNCIATOR GOES OFF 4 FUEL QTY Indicators CHECK maximum fuel imbalance 200 pounds WARNING Carefully monitor fu...

Page 209: ...indicator uses the same pitot static sources as the pilot s side air data computer ADC1 Do not use standby airspeed indicator as sole source in determining correct airspeed 4 Autopilot ALT Mode PRESS...

Page 210: ...dications of inaccurate airspeed include 1 No change in indicated airspeed when power changed and altitude maintained 2 Indicated airspeed increases when climbing or decreases when descending c Use SE...

Page 211: ...s displayed on both PFDs IF PILOT PFD AND STANDBY ALTIMETER AGREE COPILOT PFD DIFFERS c Autopilot ALT Mode PRESS disengage altitude hold mode d ALT STATIC AIR Control Knob PULL ON NOTE The alternate s...

Page 212: ...PS altitude These errors are largest at high altitude and can amount to over 2500 feet under some conditions However below 10 000 feet with the correct local altimeter setting set GPS altitude will us...

Page 213: ...ability to verify correct altitude i If unable to descend into visual conditions plan ILS approach with course intercept well outside the Final Approach Fix FAF j Once glideslope is captured determine...

Page 214: ...continued ice buildup expect no stall warning horn during slow speed operation The autopilot will not automatically disconnect during a stall without the stall warning vane working properly 2 Airspee...

Page 215: ...n displayed in the upper right of the PFD Refer to Garmin G1000 Cockpit Reference Guide for additional information AIRSPEED MISCOMPARE This message is displayed when the G1000 detects a difference of...

Page 216: ...fer to Garmin G1000 Cockpit Reference Guide for additional information BOTH ON AHRS 1 OR AHRS2 This message is displayed on both PFDs and indicates that both pilot s and copilot s PFDs are displaying...

Page 217: ...es if necessary PRIMARY FLIGHT DISPLAY 1 FAN FAILED An overheat condition may arise in the associated display In this case screen brightness will be reduced automatically by 50 to lower internal tempe...

Page 218: ...or upper half of the passenger door on the Standard 208B can be accomplished after airspeed has been reduced by pulling the door forcefully closed and latching the door If the door cannot be closed i...

Page 219: ...Fuel Quantity 4 13 Left Wing Trailing Edge 4 14 Empennage 4 15 Right Wing Trailing Edge 4 16 Right Wing Leading Edge 4 16 Nose 4 19 Before Starting Engine 4 22 Starting Engine With Battery 4 24 Start...

Page 220: ...Ignition Procedures 4 52 Engine Inertial Separator Procedures 4 53 Taxiing 4 54 Taxiing Diagram 4 55 Before Takeoff 4 56 Takeoff 4 57 Power Setting 4 57 Wing Flap Settings 4 57 Short Field Takeoff 4...

Page 221: ...uipment Normal procedures associated with optional systems can be found in Section 9 Supplements WARNING There is no substitute for proper and complete preflight planning habits and their continual re...

Page 222: ...eoff FLAPS TO APR Speed at 50 Feet 86 KIAS Type II Type III or Type IV Anti ice Fluid Takeoff FLAPS UP 83 KIAS ENROUTE CLIMB FLAPS UP Cruise Climb 110 120 KIAS Best Rate of Climb Sea Level to 3000 Fee...

Page 223: ...all fuel drain locations during each preflight inspection and after every refueling It is essential in cold weather to remove even the smallest accumulations of frost ice snow or slush from the wing t...

Page 224: ...low for accurate sampling In cold weather remove even small accumulations of frost ice or snow from wing tail and control surfaces Also make sure that control surfaces contain no internal accumulation...

Page 225: ...8 Circuit Breakers CLOSE push in 9 ALT STATIC AIR Control Knob OFF push in 10 INERTIAL SEPARATOR NORMAL push in 11 STBY FLAP MOTOR Switch GUARDED NORM 12 OXYGEN SUPPLY PRESSURE if installed CHECK 13 O...

Page 226: ...PFD 1 CHECK verify PFD 1 comes on 27 AVIONICS No 2 Switch ON 28 PFD 2 and MFD CHECK verify PFD 2 and MFD come on 29 FUEL QTY CHECK QUANTITY 30 ENGINE Softkey SELECT SYSTEM 31 SYSTEM Softkey RST FUEL...

Page 227: ...er to Section 7 Airplane and System Description Fuel System Schematic for drain locations If contaminants are still present refer to WARNING below and do not fly airplane NOTE Collect all sampled fuel...

Page 228: ...l fuel drain points until all contamination has been removed Refer to Section 7 Airplane and System Description Fuel System Schematic for drain locations If contaminants are still present refer to WAR...

Page 229: ...rformed airplane performance will be degraded to a point where a safe takeoff and climb may not be possible Prior to any flight in known or forecast icing conditions check that PITOT STATIC tube s and...

Page 230: ...ear Take repeated samples from all fuel drain points until all contamination has been removed Refer to Section 7 Airplane and System Description Fuel System Schematic for drain locations If contaminan...

Page 231: ...27 2 00 108 6 727 2 00 112 4 753 2 25 111 9 750 2 25 116 1 778 2 50 115 1 771 2 50 119 7 802 2 75 118 3 793 2 75 123 2 826 3 00 121 5 814 3 00 126 7 849 3 25 124 5 834 3 25 130 1 871 3 50 127 5 855 3...

Page 232: ...Fuel Tank Vent Opening CHECK verify opening is clear 2 Aileron and Servo Tab CHECK verify condition and security 3 Static Wicks 4 total CHECK verify condition 4 Spoiler CHECK verify condition and sec...

Page 233: ...requirements are not performed airplane performance will be degraded to a point where a safe takeoff and climb may not be possible 1 Baggage CHECK SECURE through cargo door 2 Cargo Door CLOSED and LAT...

Page 234: ...now or slush from the wing and control surfaces To assure complete removal of contamination conduct a visual and tactile inspection up to two feet behind the protected surfaces at one location along t...

Page 235: ...is observed take further samples until clear Take repeated samples from all fuel drain points until all contamination has been removed Refer to Section 7 Airplane and System Description Fuel System S...

Page 236: ...all fuel drain points until all contamination has been removed Refer to Section 7 Airplane and System Description Fuel System Schematic for drain locations If contaminants are still present refer to...

Page 237: ...ll be degraded to a point where a safe takeoff and climb may not be possible 1 Right Crew Door CHECK closed and latched 2 Exhaust Cover if installed REMOVE 3 Cowling OPEN right side of upper cowling f...

Page 238: ...for lightning strike darkened area near tips boots for security condition and evidence of grease and oil leaks 14 Propeller Spinner CHECK verify condition and security 15 Nosewheel Strut and Tire CHEC...

Page 239: ...engine stoppage 21 Electrical Power Box Circuit Breakers and Diodes CHECK verify all circuit breakers including standby alternators are IN and diodes are clear 22 Standby Alternator and Belt CHECK ver...

Page 240: ...heck aft doors 5 Left Crew Door Lock Override Knob and Right Crew Door Inside Lock UNLOCKED 6 PARKING BRAKE SET depress brake pedals and pull handle out 7 Control Lock REMOVE 8 Seats Seat Belts and Sh...

Page 241: ...T MIXING AIR Control Knob FLT PUSH 18 EMERGENCY POWER Lever NORMAL 19 POWER Lever IDLE 20 PROP RPM Lever MAX full forward 21 FUEL CONDITION Lever CUTOFF 22 FUEL OIL SHUTOFF Knob CHECK verify FULL in 2...

Page 242: ...NCY POWER lever is in the NORMAL full aft position or an over temperature condition will result during engine start 8 Propeller Area CLEAR verify that all people and equipment are at a safe distance f...

Page 243: ...itch OFF 13 Amber STARTER ON Annunciator CHECK verify annunciator is not shown 14 Engine Indicating System CHECK PARAMETERS verify all parameters in normal range 15 GEN AMPS CHECK LOAD 16 Amber GENERA...

Page 244: ...ONICS No 1 Switch OFF 7 BATTERY Switch OFF 8 External Power Unit ENGAGE then ON 9 EXTERNAL POWER Switch BUS CAUTION Make sure the EMERGENCY POWER lever is in the NORMAL position or an over temperature...

Page 245: ...n 19 STARTER Switch START a White IGNITION ON Annunciator CHECK verify annunciator is shown b OIL PSI CHECK verify oil pressure indicated c Ng STABLE 12 minimum 20 FUEL CONDITION Lever LOW IDLE a FFLO...

Page 246: ...shown positive 29 FUEL BOOST Switch NORM 30 Amber FUEL BOOST ON Annunciator CHECK verify annunciator is not shown 31 AVIONICS No 2 Switch ON NOTE With AVIONICS No 2 Switch ON verify white TORQUE GAGE...

Page 247: ...and PFD 2 BARO SET b Standby Altimeter SET 6 ALT SEL SET 7 Standby Flight Instruments CHECK 8 FUEL BOOST Switch NORM 9 FUEL TANK SELECTORS BOTH ON 10 FUEL QTY CHECK 11 FUEL OIL SHUTOFF Knob CHECK ver...

Page 248: ...propeller RPM to stabilize Rapid movement of the POWER lever will cause the propeller to surge d POWER Lever IDLE e OVERSPEED GOVERNOR TEST Button RELEASE 15 Quadrant Friction Lock ADJUST 16 Standby P...

Page 249: ...CHECK verify annunciator is not shown m STBY ALT PWR Switch OFF n Amber STBY PWR INOP Annunciator CHECK verify annunciator is shown o STBY ALT PWR Switch ON 17 Manual Electric Pitch Trim MEPT CHECK a...

Page 250: ...nd LATCHED 28 Brakes RELEASE 29 FUEL CONDITION Lever HIGH IDLE WARNING When ground icing conditions are present a pre takeoff visual and tactile check should be conducted by the pilot in command withi...

Page 251: ...AS 6 WING FLAPS Handle RETRACT to UP after reaching 95 KIAS SHORT FIELD TAKEOFF 1 WING FLAPS Handle TO APR 2 Brakes APPLY 3 POWER Lever SET FOR TAKEOFF observe Takeoff ITT and Ng limits 4 Annunciators...

Page 252: ...APPROVED TAKEOFF Continued TYPE II TYPE III OR TYPE IV ANTI ICE FLUID TAKEOFF 1 WING FLAPS Handle UP 2 Power Lever SET FOR TAKEOFF observe Takeoff ITT and Ng limits 3 Annunciators CHECK verify no ann...

Page 253: ...o NORMAL or BYPASS as conditions warrant 3 Airspeed 110 120 KIAS 4 PROP RPM Lever 1600 1900 RPM NOTE To achieve maximum flat rated horsepower PROP RPM lever must be set at 1900 RPM 5 POWER Lever SET F...

Page 254: ...ition INERTIAL SEPARATOR to NORMAL or BYPASS as conditions warrant 3 Airspeed 108 KIAS from sea level to 3000 feet decreasing to 92 KIAS at 20 000 feet 4 PROP RPM Lever 1900 RPM 5 POWER Lever SET FOR...

Page 255: ...r BYPASS as conditions warrant 3 PROP RPM Lever 1600 to 1900 RPM 4 POWER Lever SET observe Maximum Cruise Torque ITT and Ng limits Refer to Section 5 Performance Figure 5 19 or Figure 5 36 Cruise Perf...

Page 256: ...s warrant 3 SEAT BELT Light Switch if installed ON 4 NO SMOKE Light Switch if installed ON 5 Altimeters SET 6 NAV Source SELECT NOTE The overspeed warning horn and MAXSPD annunciation will activate wh...

Page 257: ...total distance requirements 1 Seats Seat Belts and Shoulder Harnesses SECURE WARNING Failure to correctly use seat belts and shoulder harnesses could result in serious or fatal injury in the event of...

Page 258: ...eld Landing Distance for speeds at reduced weights 3 POWER Lever REDUCE to IDLE after clearing obstacles 4 Touchdown MAIN WHEELS FIRST 5 POWER Lever BETA RANGE AFTER TOUCHDOWN 6 Brakes MAXIMUM while h...

Page 259: ...Switch OFF 6 LDG and TAXI RECOG Lights Switches SET 7 FUEL CONDITION Lever LOW IDLE when clear of the runway CAUTION If the FUEL CONDITION lever is moved past the LOW IDLE position and the engine Ng...

Page 260: ...g the AVIONICS No 1 switch to OFF Engine indications will not be shown after AVIONICS No 1 switch is positioned to OFF 13 AVIONICS No 1 and No 2 Switches OFF 14 BATTERY Switch OFF 15 Control Lock INST...

Page 261: ...e And Maintenance Examine tire sidewalls for patterns of shallow cracks called weather checks These cracks are evidence of tire deterioration caused by age improper storage or prolonged exposure to we...

Page 262: ...on has been removed If after repeated sampling evidence of contamination still exists the fuel tanks should be completely drained and the fuel system cleaned If any water is suspected in the static so...

Page 263: ...tightly sealed after any fuel system check or servicing Fuel system vents should also be inspected for obstructions ice or water especially after exposure to cold wet weather The interior inspection w...

Page 264: ...ing switches that are necessary for a night time engine start should be turned on All other switches including exterior lights ventilation fans air conditioning if installed switches should be turned...

Page 265: ...position aft of the IDLE gate during engine starts With the EMERGENCY POWER lever forward of this gate excessive quantities of fuel will be discharged through the fuel nozzles when the FUEL CONDITION...

Page 266: ...N it indicates the starter has not been automatically disengaged during the engine starting sequence due to a failed speed sensor CAUTION If no ITT rise is observed within 10 seconds after moving the...

Page 267: ...d cause a hot start Should a loss of external power occur immediately place the FUEL CONDITION lever to CUTOFF monitor ITT and make sure the engine is shutting down Turn the EXTERNAL POWER switch OFF...

Page 268: ...r accelerates the gas generator rapidly above 20 suspect gear train decouple Do not continue start Rapid acceleration through 35 Ng suggests a start on the secondary nozzles Anticipate a hot start Aft...

Page 269: ...or the starter motor 4 AVIONICS No 1 Switch ON 5 FUEL OIL SHUTOFF Knob CHECK verify FULL in 6 FUEL BOOST Switch OFF WARNING If fire is suspected leave the FUEL BOOST switch OFF otherwise turn it ON to...

Page 270: ...n system component life The IGNITION switch should be turned ON to provide continuous ignition under the following conditions 1 Operation on wet or contaminated runways 2 Flight in heavy precipitation...

Page 271: ...s or takeoffs with dusty sandy field conditions to minimize ingestion of foreign particles into the compressor Refer to Section 5 Performance for performance losses associated with the INERTIAL SEPARA...

Page 272: ...esult in increased engine power and reverse thrust from the propeller blades CAUTION The use of reverse thrust should be minimized especially on unprepared surfaces to minimize propeller blade erosion...

Page 273: ...FAA APPROVED TAXIING Continued NOTE Strong quartering tail winds require caution Avoid sudden bursts of power and sharp braking when the airplane is in this attitude Use the steerable nosewheel and ru...

Page 274: ...LB drop in torque when the T handle is pulled to the BYPASS position This torque drop will vary some with wind conditions during static check A neutral index mark is added to the pedestal cover which...

Page 275: ...s and continue advancing the POWER Lever until the takeoff torque is reached NOTE As airspeed increases during takeoff an increase in torque at a fixed POWER lever position is normal and need not be r...

Page 276: ...ng 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 TO APR Fl...

Page 277: ...s first At lower altitudes and cool outside air temperatures below approximately 6000 feet the engine will reach the torque limit before reaching the ITT or Ng limit As the climb progresses and the to...

Page 278: ...ngine Torque for Climb chart located in Section 5 of the POH with the PROP RPM set at 1900 to prevent exceeding the maximum allowable shaft horsepower for the ambient conditions After Climb Torque is...

Page 279: ...rates the advantage of higher altitude on both true airspeed and nautical miles per 1000 pounds of fuel In addition the beneficial effect of lower cruise power on nautical miles per 1000 pounds of fue...

Page 280: ...SECTION 4 CESSNA NORMAL PROCEDURES MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED CRUISE Continued Continued Next Page SAMPLE CRUISE PERFORMANCE CHART Figure 4 4 208BPHCUS 00 4 62...

Page 281: ...e tank with less fuel should be turned OFF until the fuel quantity is balanced With one FUEL TANK SELECTOR OFF and fuel remaining in the tank being used is less than approximately 170 lbs 25 gallons t...

Page 282: ...tty materials constitute a serious fire hazard when in contact with oxygen Be sure hands and clothing are oil free before handling oxygen equipment STALLS Stall characteristics are conventional and au...

Page 283: ...ently lowered to the runway the POWER lever repositioned to the BETA range and brakes applied as required When clear of the runway reposition the FUEL CONDITION lever from HIGH IDLE to LOW IDLE This w...

Page 284: ...n the main wheels first Immediately after touchdown lower the nose gear reposition the POWER lever against the spring in the BETA range and apply heavy braking as required For maximum brake effectiven...

Page 285: ...LKED LANDING In a balked landing go around climb the wing flap setting should be reduced to TO APR after takeoff power is applied After all obstacles are cleared and a safe altitude and airspeed are o...

Page 286: ...ication Even small accumulations of frost ice snow or slush must be removed particularly from wing tail and all control surfaces to assure satisfactory flight performance and handling Also control sur...

Page 287: ...ing the BLEED AIR HEAT switch ON and adjusting the TEMP HOT control knob to the mid point setting ENGINE COMPRESSOR STALLS An engine compressor stall can be noted by a single or multiple loud popping...

Page 288: ...at the noise levels of this airplane are or should be acceptable or unacceptable for operation at into or out of any airport The following procedures are suggested to minimize the effect of airplane n...

Page 289: ...ting Temperature Limits 5 17 Stall Speeds 5 18 Wind Components 5 19 Maximum Engine Torque for Takeoff 5 20 Maximum Engine Torque for Climb 5 22 AIRPLANES WITH CARGO POD Short Field Takeoff Distance 5...

Page 290: ...Distance 5 77 Rate of Climb Takeoff Flap Setting 5 80 Climb Gradient Takeoff Flap Setting 5 81 Maximum Rate of Climb Flaps UP 5 82 Climb Gradient Takeoff Flaps UP 5 83 Cruise Climb Flaps UP 115 KIAS...

Page 291: ...les such as engine and propeller condition and air turbulence may account for variations of 10 or more in range and endurance Therefore it is important to utilize all available information to estimate...

Page 292: ...g information has already been determined AIRPLANE CONFIGURATION CARGO POD INSTALLED Takeoff weight 8600 Pounds Usable fuel 2246 Pounds TAKEOFF CONDITIONS Field pressure altitude 3500 Feet Temperature...

Page 293: ...n the following These distances are well within the available takeoff field length However a correction for the effect of wind may be made based on information presented in the note section of the tak...

Page 294: ...eoff power setting For the above ambient conditions the power setting is The Maximum Engine Torque For Climb chart should be consulted for climb power setting from field elevation to cruise altitude F...

Page 295: ...istics presented in the Cruise Performance Cruise Maximum Torque charts Fuel and Time Required and the Range and Endurance Profile charts The Range Profile chart shows range at maximum cruise power an...

Page 296: ...ired Maximum Range Power charts will provide the desired information for most flight planning purposes START UP TAXI AND TAKEOFF The fuel required for a standard start up taxi and takeoff is approxima...

Page 297: ...may be made as follows Similarly the distance for descent may be corrected for the effect of wind and results in the following Continued Next Page Time 15 Minutes Fuel 77 Pounds Distance 43 Nautical M...

Page 298: ...ground speed for cruise is predicted to be Therefore the time required for the cruise portion of the trip is The fuel required for cruise is A 45 minute reserve requires Continued Next Page Total dis...

Page 299: ...Fuel required for climb cruise and descent 1773 Pounds Landing weight 6827 Pounds The Short Field Landing Distance chart presents landing distance information for the short field technique The landing...

Page 300: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED Figure 5 1 Sheet 1 of 2 208BPHCUS 00 5 12...

Page 301: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S FAA APPROVED Figure 5 1 Sheet 2 208BPHCUS 00 5 13...

Page 302: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED Figure 5 2 208BPHCUS 00 5 14...

Page 303: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S FAA APPROVED Example Pressure 29 55 inches of mercury Pressure 1000 6 millibars Figure 5 3 PRESSURE CONVERSION 208BPHCUS 00 5 15...

Page 304: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED TEMPERATURE CONVERSION CHART Figure 5 4 208BPHCUS 00 5 16...

Page 305: ...ESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S FAA APPROVED CAUTION Do not operate in shaded area of chart Figure 5 5 ISA CONVERSION AND OPERATING TEMPERATURE LIMITS 208BPHCUS 00 5 17...

Page 306: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED Figure 5 6 208BPHCUS 00 5 18...

Page 307: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S FAA APPROVED NOTE Maximum demonstrated crosswind velocity is 20 knots not a limitation Figure 5 7 WIND COMPONENTS 208BPHCUS 00 5 19...

Page 308: ...ION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED MAXIMUM ENGINE TORQUE FOR TAKEOFF CONDITIONS 1900 RPM 60 KIAS INERTIAL SEPARATOR NORMAL Figure 5 8 Sheet 1 of 2 208BPHCUS 00 5...

Page 309: ...exceeding 850 C ITT or 103 7 percent Ng When the ITT exceeds 825 C this power setting is time limited to 5 minutes 3 With the inertial separator in BYPASS where altitude and temperature do not permit...

Page 310: ...TION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED MAXIMUM ENGINE TORQUE FOR CLIMB CONDITIONS 1900 RPM Vy KIAS INERTIAL SEPARATOR NORMAL Figure 5 9 Sheet 1 of 2 208BPHCUS 00 5...

Page 311: ...NE TORQUE FOR CLIMB NOTE 1 Torque on this chart shall be achieved without exceeding 825 C ITT or 103 7 percent Ng 2 With the inertial separator in BYPASS decrease torque setting by 115 FT LB 3 With th...

Page 312: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED Figure 5 10 Sheet 1 of 5 208BPHCUS 00 5 24...

Page 313: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S FAA APPROVED Figure 5 10 Sheet 2 208BPHCUS 00 5 25...

Page 314: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED Figure 5 10 Sheet 3 208BPHCUS 00 5 26...

Page 315: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S FAA APPROVED Figure 5 10 Sheet 4 208BPHCUS 00 5 27...

Page 316: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED Figure 5 10 Sheet 5 208BPHCUS 00 5 28...

Page 317: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S FAA APPROVED Figure 5 11 Sheet 1 of 3 208BPHCUS 00 5 29...

Page 318: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED Figure 5 11 Sheet 2 208BPHCUS 00 5 30...

Page 319: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S FAA APPROVED Figure 5 11 Sheet 3 208BPHCUS 00 5 31...

Page 320: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED Figure 5 12 208BPHCUS 00 5 32...

Page 321: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S FAA APPROVED Figure 5 13 208BPHCUS 00 5 33...

Page 322: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED Figure 5 14 208BPHCUS 00 5 34...

Page 323: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S FAA APPROVED Figure 5 15 208BPHCUS 00 5 35...

Page 324: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED Figure 5 16 208BPHCUS 00 5 36...

Page 325: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S FAA APPROVED Figure 5 17 208BPHCUS 00 5 37...

Page 326: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED This Page Intentionally Left Blank 208BPHCUS 00 5 38...

Page 327: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S Figure 5 18 Sheet 1 of 2 208BPHCUS 00 5 39...

Page 328: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S Figure 5 18 Sheet 2 208BPHCUS 00 5 40...

Page 329: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S Figure 5 19 Sheet 1 of 11 208BPHCUS 00 5 41...

Page 330: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S Figure 5 19 Sheet 2 208BPHCUS 00 5 42...

Page 331: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S Figure 5 19 Sheet 3 208BPHCUS 00 5 43...

Page 332: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S Figure 5 19 Sheet 4 208BPHCUS 00 5 44...

Page 333: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S Figure 5 19 Sheet 5 208BPHCUS 00 5 45...

Page 334: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S Figure 5 19 Sheet 6 208BPHCUS 00 5 46...

Page 335: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S Figure 5 19 Sheet 7 208BPHCUS 00 5 47...

Page 336: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S Figure 5 19 Sheet 8 208BPHCUS 00 5 48...

Page 337: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S Figure 5 19 Sheet 9 208BPHCUS 00 5 49...

Page 338: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S Figure 5 19 Sheet 10 208BPHCUS 00 5 50...

Page 339: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S Figure 5 19 Sheet 11 208BPHCUS 00 5 51...

Page 340: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S Figure 5 20 Sheet 1 of 7 208BPHCUS 00 5 52...

Page 341: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S Figure 5 20 Sheet 2 208BPHCUS 00 5 53...

Page 342: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S Figure 5 20 Sheet 3 208BPHCUS 00 5 54...

Page 343: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S Figure 5 20 Sheet 4 208BPHCUS 00 5 55...

Page 344: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S Figure 5 20 Sheet 5 208BPHCUS 00 5 56...

Page 345: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S Figure 5 20 Sheet 6 208BPHCUS 00 5 57...

Page 346: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S Figure 5 20 Sheet 7 208BPHCUS 00 5 58...

Page 347: ...ed for engine start taxi takeoff maximum climb from sea level descent to sea level and 45 minutes reserve Time required includes the time during a maximum climb and descent 2 With INERTIAL SEPARATOR i...

Page 348: ...e start taxi takeoff maximum climb from sea level descent to sea level and 45 minutes reserve Time required includes the time during a maximum climb and descent 2 With INERTIAL SEPARATOR in BYPASS inc...

Page 349: ...start taxi takeoff maximum climb from sea level descent to sea level and 45 minutes reserve Time required includes the time during a maximum climb and descent 2 With INERTIAL SEPARATOR in BYPASS incre...

Page 350: ...e start taxi takeoff maximum climb from sea level descent to sea level and 45 minutes reserve Time required includes the time during a maximum climb and descent 2 With INERTIAL SEPARATOR in BYPASS inc...

Page 351: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S Figure 5 23 208BPHCUS 00 5 63...

Page 352: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S Figure 5 24 208BPHCUS 00 5 64...

Page 353: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S Figure 5 25 208BPHCUS 00 5 65...

Page 354: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S The Page Intentionally Left Blank 208BPHCUS 00 5 66...

Page 355: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S FAA APPROVED Figure 5 26 Sheet 1 of 5 208BPHCUS 00 5 67...

Page 356: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED Figure 5 26 Sheet 2 208BPHCUS 00 5 68...

Page 357: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S FAA APPROVED Figure 5 26 Sheet 3 208BPHCUS 00 5 69...

Page 358: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED Figure 5 26 Sheet 4 208BPHCUS 00 5 70...

Page 359: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S FAA APPROVED Figure 5 26 Sheet 5 208BPHCUS 00 5 71...

Page 360: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED Figure 5 27 Sheet 1 of 5 NOTE Figures 5 27 thru 5 43 apply to airplanes configured WITHOUT a cargo pod 208BPHCUS 00 5 72...

Page 361: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S FAA APPROVED Figure 5 27 Sheet 2 208BPHCUS 00 5 73...

Page 362: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED Figure 5 27 Sheet 3 208BPHCUS 00 5 74...

Page 363: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S FAA APPROVED Figure 5 27 Sheet 4 208BPHCUS 00 5 75...

Page 364: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED Figure 5 27 Sheet 5 208BPHCUS 00 5 76...

Page 365: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S FAA APPROVED Figure 5 28 Sheet 1 of 3 208BPHCUS 00 5 77...

Page 366: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED Figure 5 28 Sheet 2 208BPHCUS 00 5 78...

Page 367: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S FAA APPROVED Figure 5 28 Sheet 3 208BPHCUS 00 5 79...

Page 368: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED Figure 5 29 208BPHCUS 00 5 80...

Page 369: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S FAA APPROVED Figure 5 30 208BPHCUS 00 5 81...

Page 370: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED Figure 5 31 208BPHCUS 00 5 82...

Page 371: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S FAA APPROVED Figure 5 32 208BPHCUS 00 5 83...

Page 372: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED Figure 5 33 208BPHCUS 00 5 84...

Page 373: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S FAA APPROVED Figure 5 34 208BPHCUS 00 5 85...

Page 374: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED This Page Intentionally Left Blank 208BPHCUS 00 5 86...

Page 375: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S Figure 5 35 Sheet 1 of 2 208BPHCUS 00 5 87...

Page 376: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S Figure 5 35 Sheet 2 208BPHCUS 00 5 88...

Page 377: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S Figure 5 36 Sheet 1 of 12 208BPHCUS 00 5 89...

Page 378: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S Figure 5 36 Sheet 2 208BPHCUS 00 5 90...

Page 379: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S Figure 5 36 Sheet 3 208BPHCUS 00 5 91...

Page 380: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S Figure 5 36 Sheet 4 208BPHCUS 00 5 92...

Page 381: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S Figure 5 36 Sheet 5 208BPHCUS 00 5 93...

Page 382: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S Figure 5 36 Sheet 6 208BPHCUS 00 5 94...

Page 383: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S Figure 5 36 Sheet 7 208BPHCUS 00 5 95...

Page 384: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S Figure 5 36 Sheet 8 208BPHCUS 00 5 96...

Page 385: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S Figure 5 36 Sheet 9 208BPHCUS 00 5 97...

Page 386: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S Figure 5 36 Sheet 10 208BPHCUS 00 5 98...

Page 387: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S Figure 5 36 Sheet 11 208BPHCUS 00 5 99...

Page 388: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S Figure 5 36 Sheet 12 208BPHCUS 00 5 100...

Page 389: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S Figure 5 37 Sheet 1 of 7 208BPHCUS 00 5 101...

Page 390: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S Figure 5 37 Sheet 2 208BPHCUS 00 5 102...

Page 391: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S Figure 5 37 Sheet 3 208BPHCUS 00 5 103...

Page 392: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S Figure 5 37 Sheet 4 208BPHCUS 00 5 104...

Page 393: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S Figure 5 37 Sheet 5 208BPHCUS 00 5 105...

Page 394: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S Figure 5 37 Sheet 6 208BPHCUS 00 5 106...

Page 395: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S Figure 5 37 Sheet 7 208BPHCUS 00 5 107...

Page 396: ...d for engine start taxi takeoff maximum climb from sea level descent to sea level and 45 minutes reserve Time required includes the time during a maximum climb and descent 2 With INERTIAL SEPARATOR in...

Page 397: ...start taxi takeoff maximum climb from sea level descent to sea level and 45 minutes reserve Time required includes the time during a maximum climb and descent 2 With INERTIAL SEPARATOR in BYPASS incr...

Page 398: ...tart taxi takeoff maximum climb from sea level descent to sea level and 45 minutes reserve Time required includes the time during a maximum climb and descent 2 With INERTIAL SEPARATOR in BYPASS increa...

Page 399: ...e start taxi takeoff maximum climb from sea level descent to sea level and 45 minutes reserve Time required includes the time during a maximum climb and descent 2 With INERTIAL SEPARATOR in BYPASS inc...

Page 400: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S Figure 5 40 208BPHCUS 00 5 112...

Page 401: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S Figure 5 41 208BPHCUS 00 5 113...

Page 402: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S Figure 5 42 208BPHCUS 00 5 114...

Page 403: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S FAA APPROVED Figure 5 43 Sheet 1 of 5 208BPHCUS 00 5 115...

Page 404: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED Figure 5 43 Sheet 2 208BPHCUS 00 5 116...

Page 405: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S FAA APPROVED Figure 5 43 Sheet 3 208BPHCUS 00 5 117...

Page 406: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED Figure 5 43 Sheet 4 208BPHCUS 00 5 118...

Page 407: ...CESSNA SECTION 5 MODEL 208B 867 SHP PERFORMANCE GARMIN G1000 U S FAA APPROVED Figure 5 43 Sheet 5 208BPHCUS 00 5 119...

Page 408: ...SECTION 5 CESSNA PERFORMANCE MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED This Page Intentionally Left Blank 208BPHCUS 00 5 120...

Page 409: ...tions 6 27 Cargo Load Restraint 6 28 Prevention of Movement 6 28 Loading of Piercing or Penetrating Items 6 29 Transportation of Hazardous Materials 6 30 Equipment List 6 30 Cabin Internal Dimensions...

Page 410: ...SECTION 6 CESSNA WEIGHT AND BALANCE MODEL 208B 867 SHP EQUIPMENT LIST GARMIN G1000 U S This Page Intentionally Left Blank 208BPHCUS 00 6 2...

Page 411: ...ding zones filled to maximum capacity The pilot must utilize the loading flexibility to make sure the airplane does not exceed its maximum weight limits and is loaded within the center of gravity rang...

Page 412: ...ded 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 arm moment an...

Page 413: ...CESSNA SECTION 6 MODEL 208B 867 SHP WEIGHT AND BALANCE GARMIN G1000 EQUIPMENT LIST U S AIRPLANE WEIGHING FORM Figure 6 1 208BPHCUS 00 6 5...

Page 414: ...SECTION 6 CESSNA WEIGHT AND BALANCE MODEL 208B 867 SHP EQUIPMENT LIST GARMIN G1000 U S WEIGHT AND BALANCE RECORD Figure 6 2 208BPHCUS 01 6 6...

Page 415: ...n Internal Loading Arrangements figure In the event the aft seats were moved to accommodate a custom loading they should be returned to the standard locations prior to weighing g Raise flaps to fully...

Page 416: ...en the main wheel centers to a plumb bob dropped from the center of the nose jack point located below the firewall and housed within the nose strut fairing b Obtain measurement B by measuring horizont...

Page 417: ...roblem The moment which is shown must be divided by 1000 and this value used as the moment 1000 on the loading problem 2 Use the Weight and Moment Tables to determine the moment 1000 for each addition...

Page 418: ...r fuel temperature will be 32 0 pounds over the 2246 pounds for 335 gallons shown on the chart which might be significant in an actual loading situation 335 gallons X 6 7 0 1 pounds per gallon 2278 po...

Page 419: ...ght and C G arm Fuselage Station of the item being loaded must be made if the position of the load is different from that shown on the Weight and Moment Tables For example if seats are in any position...

Page 420: ...tive source to the FAA Approved Weight and Balance Manual to determine weight and balance data for a particular flight CLCalc and the Weight and Balance Manual methods are each equally valid sources o...

Page 421: ...ITEM WEIGHT spaces Total cabin cargo weights in space provided as a check that maximum allowable cabin cargo weight of 3400 pounds is not exceeded Refer to other portions of the POH AFM for additiona...

Page 422: ...es do not affect the weight index significantly The ARM used in the following calculation is the centroid of cabin Zone 1 as shown on the diagram on the backside of the record 315 X 172 1 192 12 5 500...

Page 423: ...AC space is provided to enter this value If the zero fuel weight C G falls well within clear area of chart envelope the loading will likely be acceptable however if the C G at this weight fall near or...

Page 424: ...SECTION 6 CESSNA WEIGHT AND BALANCE MODEL 208B 867 SHP EQUIPMENT LIST GARMIN G1000 U S WEIGHT AND BALANCE RECORD LOAD MANIFEST Figure 6 3 Sheet 1 of 2 208BPHCUS 00 6 16...

Page 425: ...CESSNA SECTION 6 MODEL 208B 867 SHP WEIGHT AND BALANCE GARMIN G1000 EQUIPMENT LIST U S WEIGHT AND BALANCE RECORD LOAD MANIFEST Figure 6 3 Sheet 1 of 2 208BPHCUS 00 6 17...

Page 426: ...ting The first Commuter Seating configuration has three individual fixed position passenger seats on the left side of the cabin and three two place fixed position bench seats located on the right side...

Page 427: ...installed the basic empty weight and C G moment of the airplane should be adjusted so that these values accurately represent the weight and moment of the airplane before loading To calculate the new...

Page 428: ...board raised approximately five inches above the main cabin floor The raised baggage cargo area contains eight anchor plates where quick release tiedown fittings can be attached This raised area is li...

Page 429: ...of six loading zones Markings located on the sidewalls between the lines identify each zone by number and display the maximum load which can be carried within the zones Refer to Figure 6 6 Cabin Inte...

Page 430: ...nets consist of three nets one for the left sidewall one for the right sidewall and one for the center The left and right nets fill in the space between the barrier assembly and the airplane sidewalls...

Page 431: ...nd taxi accelerations and decelerations On the passenger version if passengers as well as cargo are located aft of the barrier cargo placement must allow movement and exit of the passengers and the ca...

Page 432: ...nd other anchor plates on the sidewalls and ceiling Four straps have adjustable buckles for tightening the straps during installation of the partition Refer to Figure 6 8 Cargo Partition Nets for addi...

Page 433: ...pound rated belts with ratchet type adjusters and six double stud quick release anchors Three 5000 pound rated belts with overcenter type locking devices are also available for heavy duty use The six...

Page 434: ...the horizontal position with the doors closed the doors are secured Refer to Figure 6 5 Pod Internal Dimension and Load Markings and Figure 6 12 Cargo Pod Loading Arrangements for additional informat...

Page 435: ...ormly around the C G of the cabin cargo area zone and or cargo pod compartment Loading personnel must maintain strict accountability for loading correctly and accurately but may not always be able to...

Page 436: ...of these loading criteria is important and it is the responsibility of the pilot to make sure the cargo is restrained properly When a cargo barrier is installed cargo aft of the barrier must also be...

Page 437: ...takeoff flight and landing by any two zones forward or aft of the partition Use of the partitions will allow loading of the zones without tying down the cargo if the load density is not more than 7 9...

Page 438: ...command and flight crew member if used other personnel such as cargo receiving and loading personnel should be properly trained concerning the acceptance handling storage loading and unloading of haz...

Page 439: ...CESSNA SECTION 6 MODEL 208B 867 SHP WEIGHT AND BALANCE GARMIN G1000 EQUIPMENT LIST U S CABIN INTERNAL DIMENSIONS CARGO VERSION Figure 6 4 Sheet 1 of 2 208BPHCUS 00 6 31...

Page 440: ...SECTION 6 CESSNA WEIGHT AND BALANCE MODEL 208B 867 SHP EQUIPMENT LIST GARMIN G1000 U S CABIN INTERNAL DIMENSIONS PASSENGER VERSION Figure 6 4 Sheet 2 208BPHCUS 00 6 32...

Page 441: ...CESSNA SECTION 6 MODEL 208B 867 SHP WEIGHT AND BALANCE GARMIN G1000 EQUIPMENT LIST U S POD INTERNAL DIMENSIONS AND LOAD MARKINGS Figure 6 5 208BPHCUS 00 6 33...

Page 442: ...SECTION 6 CESSNA WEIGHT AND BALANCE MODEL 208B 867 SHP EQUIPMENT LIST GARMIN G1000 U S CABIN INTERNAL LOAD MARKINGS CARGO VERSION Figure 6 6 208BPHCUS 00 6 34...

Page 443: ...er is not shown The cargo barrier and attached barrier nets must be installed to provide forward crash load restraint The quick release fasteners which secure the center and side barrier nets allow mo...

Page 444: ...they cannot be considered as a replacement for the barrier Each partition will withstand the forward and aft operational loads applied during takeoff flight and landing by any two zones forward or af...

Page 445: ...WEIGHT AND BALANCE GARMIN G1000 EQUIPMENT LIST U S NOTE 1 Approximately one inch clearance allowed from sidewall and ceiling 2 Subtract roller height and pallet thickness if applicable Figure 6 9 MAX...

Page 446: ...SECTION 6 CESSNA WEIGHT AND BALANCE MODEL 208B 867 SHP EQUIPMENT LIST GARMIN G1000 U S CARGO TIEDOWN ATTACHMENTS Figure 6 10 Sheet 1 of 2 208BPHCUS 00 6 38...

Page 447: ...CESSNA SECTION 6 MODEL 208B 867 SHP WEIGHT AND BALANCE GARMIN G1000 EQUIPMENT LIST U S CARGO TIEDOWN ATTACHMENTS Figure 6 10 Sheet 2 208BPHCUS 00 6 39...

Page 448: ...dicate forward and aft limits of occupant center of gravity range 2 Cargo area center of gravity in Zones 1 thru 6 based on the mid point of the zone 3 Vertical lines marked on the cargo area sidewall...

Page 449: ...a center of gravity in Zones 1 thru 6 based on the mid point of the zone 3 The forward face of the raised floor FS 332 0 can be used as a convenient reference point for determining the location of occ...

Page 450: ...SECTION 6 CESSNA WEIGHT AND BALANCE MODEL 208B 867 SHP EQUIPMENT LIST GARMIN G1000 U S CABIN INTERNAL LOADING ARRANGEMENTS PASSENGER VERSION Figure 6 11 Sheet 3 208BPHCUS 00 6 42...

Page 451: ...center of gravity in Zones A B C and D 2 Compartment bulkheads that separate Zones A and B FS 154 75 Zones B and C FS 209 35 and Zones C and D FS 257 35 can be used as a reference point for determini...

Page 452: ...l loads must be secured by adequate tiedowns over tarps 2 Protection against hazardous materials has been provided in the fuselage bilge area under the cargo compartment from FS 168 0 to 356 0 These m...

Page 453: ...CESSNA SECTION 6 MODEL 208B 867 SHP WEIGHT AND BALANCE GARMIN G1000 EQUIPMENT LIST U S TYPICAL CARGO RESTRAINT METHODS Figure 6 14 208BPHCUS 00 6 45...

Page 454: ...SECTION 6 CESSNA WEIGHT AND BALANCE MODEL 208B 867 SHP EQUIPMENT LIST GARMIN G1000 U S WEIGHT AND MOMENT TABLES PILOT AND FRONT PASSENGER CARGO VERSION Figure 6 15 Sheet 1 of 7 208BPHCUS 00 6 46...

Page 455: ...CESSNA SECTION 6 MODEL 208B 867 SHP WEIGHT AND BALANCE GARMIN G1000 EQUIPMENT LIST U S Figure 6 15 Sheet 2 208BPHCUS 00 6 47...

Page 456: ...SECTION 6 CESSNA WEIGHT AND BALANCE MODEL 208B 867 SHP EQUIPMENT LIST GARMIN G1000 U S Figure 6 15 Sheet 3 208BPHCUS 00 6 48...

Page 457: ...CESSNA SECTION 6 MODEL 208B 867 SHP WEIGHT AND BALANCE GARMIN G1000 EQUIPMENT LIST U S Figure 6 15 Sheet 4 208BPHCUS 00 6 49...

Page 458: ...SECTION 6 CESSNA WEIGHT AND BALANCE MODEL 208B 867 SHP EQUIPMENT LIST GARMIN G1000 U S Figure 6 15 Sheet 6 208BPHCUS 00 6 50...

Page 459: ...CESSNA SECTION 6 MODEL 208B 867 SHP WEIGHT AND BALANCE GARMIN G1000 EQUIPMENT LIST U S Figure 6 15 Sheet 7 208BPHCUS 00 6 51...

Page 460: ...SECTION 6 CESSNA WEIGHT AND BALANCE MODEL 208B 867 SHP EQUIPMENT LIST GARMIN G1000 U S Figure 6 16 Sheet 1 of 2 208BPHCUS 00 6 52...

Page 461: ...CESSNA SECTION 6 MODEL 208B 867 SHP WEIGHT AND BALANCE GARMIN G1000 EQUIPMENT LIST U S Figure 6 16 Sheet 2 208BPHCUS 00 6 53...

Page 462: ...000 U S 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 r...

Page 463: ...ation warning shaded area between 38 33 mac and the maximum aft c g of 40 33 mac on the center of gravity moment envelope Points falling within this shaded area should be used only if accurate C G det...

Page 464: ...SECTION 6 CESSNA WEIGHT AND BALANCE MODEL 208B 867 SHP EQUIPMENT LIST GARMIN G1000 U S This Page Intentionally Left Blank 208BPHCUS 00 6 56...

Page 465: ...9 Overhead Panel 7 19 Left Sidewall Switch and Circuit Breaker Panel 7 21 Annunciators 7 22 Ground Control 7 25 Minimum Turning Radius 7 26 Wing Flap System 7 27 Landing Gear System 7 29 Baggage Cargo...

Page 466: ...7 52 Engine Indicating System EIS 7 53 Torque Indications 7 54 Propeller RPM Indications 7 55 ITT Indication 7 55 Gas Generator RPM Indications 7 56 Fuel Flow Indications 7 56 Oil Pressure Indication...

Page 467: ...e Gear Reduction System 7 73 Chip Detectors 7 74 Oil Breather Drain Can 7 74 Propeller 7 75 Overspeed Governor Test Switch 7 76 Fuel System 7 76 Fuel Quantity Data 7 79 Firewall Fuel Shutoff Valve 7 8...

Page 468: ...Alternator Power Switch 7 92 Avionics Power Switches 7 92 Avionics Standby Power Switch 7 92 Avionics Bus Tie Switch 7 93 Electrical System 7 94 External Power Switch 7 97 Circuit Breakers 7 97 Volta...

Page 469: ...04 Cabin Lights with Timer Super Cargomaster 7 105 Passenger Reading Lights Passenger Version Only 7 105 No Smoke Seat Belt Sign Passenger Version Only 7 105 Cabin Heating Ventilating And Defrosting S...

Page 470: ...em 7 118 Avionics Support Equipment 7 119 Avionics Cooling Fan 7 119 Microphone Headset Installations 7 119 Static Dischargers 7 120 12 VDC Power Outlet 7 120 Auxiliary Audio Input Jack 7 121 Cabin Fe...

Page 471: ...Supplements for details of other optional systems and equipment WARNING Complete familiarity with the airplane and its systems will not only increase the pilot s proficiency and ensure optimum operati...

Page 472: ...heet metal ribs doublers and stringers The entire structure is covered with aluminum skin The front spars are equipped with wing to fuselage and wing to strut attach fittings The aft spars are equippe...

Page 473: ...our lower skin panels and two left and two right wrap around skin panels which also form the leading edges The horizontal stabilizer also contains dual jack screw type actuators for the elevator trim...

Page 474: ...n outer layer of fiberglass Complete instructions for removal and installation of the cargo pod are contained in the 208 Maintenance Manual Chapter 25 52 00 Cargo Pod Maintenance Practices The volume...

Page 475: ...m systems are provided refer to Figure 7 1 The aileron is trimmed by a servo tab attached to the right aileron which is mechanically controlled by the AILERON TRIM control knob located on the control...

Page 476: ...SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B 867 SHP GARMIN G1000 U S FLIGHT CONTROL AND TRIM SYSTEMS Figure 7 1 Sheet 1 of 3 208BPHCUS 00 7 12...

Page 477: ...CESSNA SECTION 7 MODEL 208B 867 SHP AIRPLANE AND SYSTEMS DESCRIPTION GARMIN G1000 U S FLIGHT CONTROL AND TRIM SYSTEMS Figure 7 1 Sheet 2 of 3 208BPHCUS 00 7 13...

Page 478: ...SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B 867 SHP GARMIN G1000 U S FLIGHT CONTROL AND TRIM SYSTEMS Figure 7 1 Sheet 3 of 3 208BPHCUS 00 7 14...

Page 479: ...1000 CRG for specific operating information on all Garmin equipment The PFDs centered above the control wheels in front of the pilot and copilot show the primary flight instruments and display any Cre...

Page 480: ...t right fresh air outlet and pull knob and microphone and headset jacks At upper right are the hour meter and ELT remote switch Mounted above the glare shield is a magnetic compass For details concern...

Page 481: ...CESSNA SECTION 7 MODEL 208B 867 SHP AIRPLANE AND SYSTEMS DESCRIPTION GARMIN G1000 U S INSTRUMENT PANEL Figure 7 2 Sheet 1 of 2 208BPHCUS 00 7 17...

Page 482: ...f installed 22 WING FLAPS Selector Lever and Position Indicator 23 PROP RPM Control Lever 24 Quadrant Friction Lock 25 FUEL CONDITION Lever 26 FUEL OIL SHUTOFF Control Knob 27 RUD TRIM Control Wheel a...

Page 483: ...instruments switches and controls on this panel refer to the ELECTRICAL EQUIPMENT descriptions in this section OVERHEAD PANEL The overhead panel located above and between the pilot and copilot contain...

Page 484: ...SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B 867 SHP GARMIN G1000 U S OVERHEAD PANEL Figure 7 3 208BPHCUS 00 7 20...

Page 485: ...CESSNA SECTION 7 MODEL 208B 867 SHP AIRPLANE AND SYSTEMS DESCRIPTION GARMIN G1000 U S LEFT SIDEWALL SWITCH AND CIRCUIT BREAKER PANEL Figure 7 4 208BPHCUS 00 7 21...

Page 486: ...when the EMERGENCY POWER lever is out of the stowed NORMAL position prior to and during the engine start ITT in the OFF and STRT modes ONLY 7 FUEL SELECT OFF RED Indicates LEFT and RIGHT FUEL TANK SE...

Page 487: ...mode 18 CHIP DETECT AMBER Indicates that metal chips have been detected in either or both the accessory gearbox or reduction gearbox 19 L P S HEAT AMBER Indicates that either the left side pitot stati...

Page 488: ...s than 10 amps or greater than 75 amps 25 IGNITION ON WHITE Indicates electrical power is being supplied to the engine ignition system 26 STBY PWR ON WHITE Indicates that the standby alternator is gen...

Page 489: ...hing a towbar stowed in aft cargo compartment to the nose gear fork axle holes If a towbar is not available or pushing is required use the wing struts as push points Do not use the propeller blades or...

Page 490: ...SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B 867 SHP GARMIN G1000 U S MINIMUM TURNING RADIUS Figure 7 5 208BPHCUS 00 7 26...

Page 491: ...p down switch located on the overhead panel Both switches have guards which are safetied in the closed position with breakable copper wire The guarded STBY FLAP MOTOR switch has NORM and STBY position...

Page 492: ...SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B 867 SHP GARMIN G1000 U S WING FLAP SYSTEM Figure 7 6 208BPHCUS 00 7 28...

Page 493: ...improved runways 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...

Page 494: ...ILOT S AND COPILOT S SEATS The six way adjustable pilot s or copilots seats may be moved forward or aft adjusted for height and the seat back angle changed Position the seat by pulling on the small T...

Page 495: ...eats are lightweight and quick removable to facilitate cargo hauling AFT PASSENGERS SEATS UTILITY Passenger Version Individual collapsible seats are available for the aft eight passenger positions The...

Page 496: ...SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B 867 SHP GARMIN G1000 U S SEAT BELTS AND SHOULDER HARNESSES PILOT S AND COPILOT S SEAT Typical Figure 7 7 Sheet 1 of 3 208BPHCUS 00 7 32...

Page 497: ...ECTION 7 MODEL 208B 867 SHP AIRPLANE AND SYSTEMS DESCRIPTION GARMIN G1000 U S SEAT BELTS AND SHOULDER HARNESSES AFT PASSENGERS SEATS Individual Commuter Seating Shown Figure 7 7 Sheet 2 of 3 208BPHCUS...

Page 498: ...ON 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B 867 SHP GARMIN G1000 U S SEAT BELTS AND SHOULDER HARNESSES AFT PASSENGERS SEATS Dual Commuter Seating Shown Figure 7 7 Sheet 3 of 3 208BPHCUS 00...

Page 499: ...a five point restraint system which combines the function of conventional type seat belts a crotch strap and an inertial reel equipped double strap shoulder harness in a single assembly The seat belts...

Page 500: ...ally position each strap of the shoulder harness over the shoulders and insert their links into the upper slots in the buckle the seat belts should be tightened for a snug fit by grasping the free end...

Page 501: ...airplane if unlocked rotate the handle down and forward to the OPEN position To close the door from inside the airplane use the conventional door handle and door pull The inside door handle is a thre...

Page 502: ...oor support cables and a door lowering device A cabin door unlatched warning system is provided as a safety feature so that if the upper door is not properly latched an amber DOOR UNLATCHED annunciato...

Page 503: ...ed position but do not use excessive force If the handle will not rotate easily the door is not fully closed Use a more firm closing motion to get the latching pawls to engage and rotate the door hand...

Page 504: ...receptacle unless cargo obstructs access to the door If desired when leaving the airplane parked use the key in the outside key lock to lock the handle in the horizontal position WARNING Do not use t...

Page 505: ...lifts which raise the door to the fully open position when opened A cargo door open warning system is provided as a safety feature so that if the upper door is not properly latched an amber annunciat...

Page 506: ...ect 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 Rotate th...

Page 507: ...cargo doors Because the inside of the upper door has no handle exit from the airplane through these doors is not possible without outside assistance To close the cargo door from inside the airplane Pa...

Page 508: ...bout its removal before starting the engine To install the control lock align the hole in the right side of the pilot s control wheel shaft with the hole in the right side of the shaft collar on the i...

Page 509: ...flecting the elevator to the full up position after the control lock is removed and before starting the engine If these procedures are not followed the rudder and rudder pedals will be locked in the n...

Page 510: ...mber 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...

Page 511: ...is 33 000 RPM at a propeller shaft speed of 1900 RPM All engine driven accessories with the exception of the propeller tachometer generator and the propeller governors are mounted on the accessory ge...

Page 512: ...ne 8 Combustion Chamber 9 Compressor Turbine 10 Centrifugal Compressor Impeller 11 Axial Flow Compressor Impellers 3 12 Compressor Air Inlet 13 Accessory Gearbox Drive Shaft 14 Accessory Gearbox Cover...

Page 513: ...rear of the engine The POWER lever controls engine power through the full range from maximum takeoff power back through idle to full reverse The lever also selects propeller pitch when in the BETA ran...

Page 514: ...nge from IDLE position to MAX governs engine power and is used when a pneumatic malfunction has occurred in the fuel control unit and the power lever is ineffective A mechanical stop in the lever slot...

Page 515: ...when using the POWER lever Additional care is required during engine acceleration to avoid exceeding engine limitations Operation of the EMERGENCY POWER lever is prohibited with the primary POWER lev...

Page 516: ...e is shut down minimizes propeller windmilling during windy conditions A mechanical stop in the lever slot requires that the PROP RPM lever be moved to the left to clear the stop before it can be move...

Page 517: ...T Gas Generator RPM Propeller RPM Oil Pressure Oil Temperature Fuel Quantity Fuel Flow Battery Amps and Bus Voltage When the ENGINE softkey is pressed the SYSTEM softkey will appear adjacent to the EN...

Page 518: ...The dynamic redline automatically compensates for altitude and temperature changes and adjusts displayed takeoff torque for inertial separator deployment and bleed air heat switch position Failure to...

Page 519: ...RPM and white numerals on a red background when RPM is greater than or equal to 1910 after a 20 second delay The instrument is electrically operated from the propeller tachometer generator which is mo...

Page 520: ...RPM Once Ng RPM is greater than or equal to 103 7 for more than a 20 seconds the pointer switches to red and numerals switch to white on a red background If Ng RPM ever reaches 105 4 the pointer will...

Page 521: ...he warning range indications 0 to 39 PSI or 106 to 130 PSI the OIL PSI label and pointer will turn red and the digital value will change to red background with white text to show that oil pressure is...

Page 522: ...NGINE BREAK IN AND OPERATION There are no specific break in procedures required for the Pratt Whitney Canada Inc PT6A 140 turboprop engine The engine may be safely operated throughout the normal range...

Page 523: ...il and precluded from further circulation Pressure oil is then routed through passageways to the engine bearings reduction gears accessory drives torquemeter and propeller governor Also pressure oil i...

Page 524: ...s low if the oil is hot are provided on the dipstick to facilitate oil servicing The oil tank capacity is 9 5 U S quarts and total system capacity is 14 U S quarts For engine oil type and brand refer...

Page 525: ...on is controlled by an IGNITION switch and a STARTER switch located on the left sidewall switch and circuit breaker panel The IGNITION switch has two positions ON and NORM The NORM position of the swi...

Page 526: ...engine ignition system provided the ignition switch is in the NORMAL position After the engine has started during a ground or air start the starter switch must be manually positioned to OFF for genera...

Page 527: ...led BYPASS PULL NORMAL PUSH The inertial separator control should be moved to the BYPASS position prior to running the engine during ground or flight operation in visible moisture clouds rain snow ice...

Page 528: ...ND SYSTEMS DESCRIPTION MODEL 208B 867 SHP GARMIN G1000 U S ENGINE AIR FLOW NOTE The above view shows inertial separator in NORMAL position Auxiliary view shows inertial separator in BYPASS position Fi...

Page 529: ...unit a flow divider and dump valve a dual fuel manifold with 14 simplex nozzles and two fuel drain lines The system provides fuel flow to satisfy the speed and power demands of the engine Fuel from t...

Page 530: ...ations in compressor inlet air temperature Engine characteristics vary with changes in inlet air temperature and the acceleration fuel schedule must in turn be altered to prevent compressor stall and...

Page 531: ...n the NORMAL position When the engine has started the starter switch must be manually placed in the OFF position to de energize the ignition system and activate the generator system The MOTOR position...

Page 532: ...extends the drive to the fuel control unit which is bolted to the rear face of the pump Fuel from the oil to fuel heater enters the fuel pump through a 74 micron inlet screen Then fuel enters the pump...

Page 533: ...tion gearbox front case and to a pressure transducer which is electrically connected to the G1000 which indicates the correct torque For standby indication the pressures are routed to bosses on the to...

Page 534: ...rnal leads to the ITT indicator in the airplane cabin PROPELLER GOVERNOR The propeller governor is located in the 12 o clock position on the front case of the reduction gearbox Under normal conditions...

Page 535: ...ore entering the bellows The restrictor dampens torque pressure fluctuation and prevents damage to the bellows assembly When torque pressure reaches 2500 FT LB the bellows expands and compresses the s...

Page 536: ...sensor in the engine compartment a red ENGINE FIRE annunciator located on the PFD and a warning horn above the pilot The heat sensor consists of three flexible closed loops When high engine compartmen...

Page 537: ...ction gear and then to the propeller shaft The reduction ratio is from a maximum power turbine speed of 33 000 RPM down to a propeller speed of 1900 RPM The accessories located on the front case of th...

Page 538: ...ce Manual for more information on inspection and removal of the engine chip detectors OIL BREATHER DRAIN CAN Model 208 airplanes have an oil breather drain can mounted on the right lower engine mount...

Page 539: ...spring tension will continue to twist the propeller blades through high pitch and into the streamlined or feathered position Unfeathering the propeller is accomplished by positioning the PROP RPM lev...

Page 540: ...ve a fuel filter an oil to fuel heater an engine driven fuel pump a fuel control unit a flow divider dual manifolds and 14 fuel nozzle assemblies An ecology tank is also provided to collect unused fue...

Page 541: ...ted through a fuel filter located on the right side of the engine The fuel filter incorporates a bypass feature which allows fuel to bypass the filter in the event the filter becomes blocked with fore...

Page 542: ...SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B 867 SHP GARMIN G1000 U S FUEL SYSTEM Figure 7 10 208BPHCUS 01 7 78...

Page 543: ...OARD FILLERS 1124 25 167 8 2272 339 1 24 1 3 6 2246 5 335 3 NOTE Pounds are based on a fuel specific weight of 6 7 pounds per U S gallon WARNING To achieve full capacity fill fuel tank to the top of t...

Page 544: ...one for each tank are located on the overhead console The selectors labeled LEFT ON and OFF and RIGHT ON and OFF mechanically control the position of the two fuel tank shutoff valves at each wing tan...

Page 545: ...el tank selectors in the OFF position the red FUEL SELECT OFF annunciator illuminates and both of the fuel select off warning horns are activated 3 With one fuel tank selector in the OFF position and...

Page 546: ...be shut off The ON position is used for engine start and any other time that the auxiliary boost pump cycles on and off with the switch in the NORM position due to low fuel pressure The high pressure...

Page 547: ...e 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 be...

Page 548: ...circuit breaker The breakers are labeled LEFT FUEL QTY and RIGHT FUEL QTY respectively and are located on the left sidewall switch and circuit breaker panel WARNING Because of the relatively long fuel...

Page 549: ...f maximum continuous power or approximately 9 minutes at idle power FUEL PRESSURE LOW WARNING ANNUNCIATOR An amber FUEL PRESS LOW annunciator is located on the PFD and will illuminate when fuel pressu...

Page 550: ...rain pipe located adjacent to the drain valve The drain valve for the fuel filter consists of a drain pipe which can be depressed upward to drain fuel from the filter The fuel sampler can be used in c...

Page 551: ...d provide a way to determine if fuel is leaking past the fuel pump seal this airplanes is equipped with a drainable reservoir to collect this allowable discharge of oil and any fuel seepage The reserv...

Page 552: ...roper level prior to each flight For maximum brake life keep the brake system properly maintained Airplanes are equipped with metallic type brakes and require a special brake burn in before delivery o...

Page 553: ...rator system malfunctions in flight The system includes an alternator operated at a 75 amp capacity rating The alternator is belt driven from an accessory pad on the rear of the engine The system also...

Page 554: ...e generator contactor controlled by the GCU connects the generator output to the airplane bus If any GCU function causes the generator contactor to de energize the amber GENERATOR OFF annunciator will...

Page 555: ...hree position toggle type switch labeled GENERATOR on the left sidewall switch and circuit breaker panel The switch has ON RESET and TRIP positions With the switch in the ON position the GCU will auto...

Page 556: ...r switch controls power to the No 2 avionics bus The switches are labeled AVIONICS 1 and 2 and are ON in the forward position and OFF in the aft position The AVIONICS power switches should be placed i...

Page 557: ...the AVN BUS 1 and AVN BUS 2 together in the event of failure of either bus feeder circuit Because power for each avionics bus is supplied from a separate current limiter on the power distribution bus...

Page 558: ...SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B 867 SHP GARMIN G1000 U S ELECTRICAL SYSTEM Figure 7 12 Sheet 1 of 3 208BPHCUS 00 7 94...

Page 559: ...CESSNA SECTION 7 MODEL 208B 867 SHP AIRPLANE AND SYSTEMS DESCRIPTION GARMIN G1000 U S ELECTRICAL SYSTEM Figure 7 12 Sheet 2 of 3 208BPHCUS 00 7 95...

Page 560: ...SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B 867 SHP GARMIN G1000 U S ELECTRICAL SYSTEM Figure 7 12 Sheet 3 of 3 208BPHCUS 00 7 96...

Page 561: ...le in this position When the EXTERNAL POWER switch is in the BUS position external power is applied to the main bus and no power is available to the starter The battery can be connected to the main bu...

Page 562: ...e electrical load or increase Ng to maintain battery charge GROUND SERVICE PLUG RECEPTACLE A ground service plug receptacle permits the use of an external power source for cold weather starting and du...

Page 563: ...type circuit breaker labeled NAV LIGHT on the left sidewall switch and circuit breaker panel LANDING LIGHTS Two LED landing lights are installed on the airplane one in each wing leading edge mounted o...

Page 564: ...anti collision lights can be considerable annoyance to ground personnel and other pilots Do not operate the anti collision lights in conditions of fog clouds or haze as the reflection of the light bea...

Page 565: ...ng strut for ice detection The WING LIGHT switch is on the left hand switch panel and is protected by a pull type circuit breaker labeled WING ICE DET LIGHT COURTESY LIGHTS Two LED courtesy lights are...

Page 566: ...ing provided or available includes control wheel map LED lights cabin lights LED passenger reading lights and a no smoking seat belt sign Discussion of these lights and their controls is also included...

Page 567: ...verhead panel This floodlight may be used to illuminate the pilot s map or chart Clockwise rotation of this control knob increases lamp brightness while counterclockwise rotation decreases brightness...

Page 568: ...ne bay CABIN LIGHTS WITH TIMER if installed The 208B cabin light system with timer consists of four LED cabin lights installed on the interior of the airplane and courtesy lights under each wing to fa...

Page 569: ...e panels above each seat A pushbutton type ON OFF switch mounted in each panel controls the lights The lights can be pivoted in their mounting sockets to provide the most comfortable angle of illumina...

Page 570: ...dshield for defrosting Ventilating air is obtained from an inlet on each side at the forward fuselage and through two ram air inlets one on each wing at the upper end of the wing struts The wing inlet...

Page 571: ...GRD position pulled out of the MIXING AIR control Some hysteresis may be encountered when adjusting bleed air temperature The resulting amount and temperature of bleed air may be different when approa...

Page 572: ...SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B 867 SHP GARMIN G1000 U S CABIN HEATING VENTILATING AND DEFROSTING SYSTEM CARGO VERSION Figure 7 13 Sheet 1 of 2 208BPHCUS 00 7 108...

Page 573: ...CESSNA SECTION 7 MODEL 208B 867 SHP AIRPLANE AND SYSTEMS DESCRIPTION GARMIN G1000 U S CABIN HEATING VENTILATING AND DEFROSTING SYSTEM PASSENGER VERSION Figure 7 13 Sheet 2 of 2 208BPHCUS 00 7 109...

Page 574: ...n return air is mixed with the hot compressor outlet air in the mixer muffler This recirculation of cabin return air enables the heating system to maintain the desired temperature for proper cabin hea...

Page 575: ...hrough four heater outlets located behind the instrument panel and or the two windshield defroster outlets The push pull control can be positioned at any intermediate setting desired for proper distri...

Page 576: ...se a compressor stall will occur at low power settings when the compressor bleed valve is open The engine must be shut down to relieve back pressure on the valves prior to opening the valves VENT AIR...

Page 577: ...permits individual ventilation to the airplane occupants The outlets are the swivel type for optimum positioning and airflow volume is controlled by rotating the outlet nozzle controlling an internal...

Page 578: ...urce valve should be PULLED ON Pressures within the cabin will vary with vents open or closed Refer to Section 5 Performance for the effect of varying cabin pressures on airspeed and altimeter reading...

Page 579: ...re altitude on the standby altimeter Be sure to return the standby altimeter barometric scale to the original barometric setting after pressure altitude has been obtained Having set the knob to correc...

Page 580: ...a vacuum driven attitude indicator Bank attitude is presented by a pointer at the top of the indicator relative to the bank scale which has index marks at 10 20 30 60 and 90 either side of the center...

Page 581: ...CESSNA SECTION 7 MODEL 208B 867 SHP AIRPLANE AND SYSTEMS DESCRIPTION GARMIN G1000 U S VACUUM SYSTEM Figure 7 14 208BPHCUS 00 7 117...

Page 582: ...The system is operational if the warning horn sounds as the vane is pushed upward The elevator must be off the forward stop before the stall warning horn is enabled due to the fact that the airplane...

Page 583: ...ower switch is ON MICROPHONE HEADSET INSTALLATIONS Radio communications are accomplished by the use of a hand held microphone and the airplane speaker or by aviation style headsets The hand held micro...

Page 584: ...io signals even with static dischargers installed Whenever possible avoid known severe precipitation areas to prevent loss of dependable radio signals If avoidance is impractical minimize airspeed and...

Page 585: ...ay music over the airplane s headsets The signal from AUX AUDIO IN is automatically muted during radio communications or pilot selection of CREW ICS ISOLATION modes located on the audio panel The AUX...

Page 586: ...operating lever lock pin and press lever while directing the discharge at the base of the fire at the near edge Progress toward the back of the fire by moving the nozzle rapidly with a side to side sw...

Page 587: ...and other small objects MISCELLANEOUS EQUIPMENT ENGINE INLET COVERS AND PROPELLER ANCHOR Various covers and an anchor are available to close engine openings and restrain the propeller during inclemen...

Page 588: ...eclude loose cargo from moving forward into the pilot s and copilot s stations during an abrupt deceleration The barrier consists of a U shaped assembly of honeycomb composite construction The assembl...

Page 589: ...on the inside of the airplane over the cargo door opening The net precludes loose articles from falling out the cargo door when the doors are opened The restraining net consists of two halves which pa...

Page 590: ...gs when installed it is necessary to remove the wing to fuselage fairing strips RELIEF TUBE Provisions are made for the installation of a relief tube in the aft cabin area on the Passenger Version The...

Page 591: ...8 4 Publications 8 5 Airplane File 8 6 Airplane Inspection Periods 8 7 FAA Required Inspections 8 7 Inspection Programs 8 7 Cessna Customer Care Program 8 8 CESCOM System 8 8 Pilot Conducted Preventi...

Page 592: ...i Ice Operations 8 31 Holdover Timetable Type I Type II Type III and Type IV Fluids 8 35 Essential Areas to be Deiced 8 42 Essential Areas to Apply Anti Ice Fluid 8 43 Deice and Anti Ice Fluid Direct...

Page 593: ...ins and service letters All service bulletins pertaining to the airplane by serial number should be accomplished and the airplane should receive repetitive and required inspections Cessna does not con...

Page 594: ...rplane is registered in the U S appropriate Cessna Owner Advisories will be mailed to you automatically according to the latest airplane registration name and address which you have provided to the FA...

Page 595: ...Company P O Box 7706 Attn Dept 569 Wichita KS 67277 The following additional publications plus many other supplies that are applicable to your airplane are available from a Cessna Authorized Service...

Page 596: ...ing Handbook and FAA Approved Airplane Flight Manual 2 Garmin G1000 Cockpit Reference Guide 190 00384 00 Rev B or subsequent 3 Weight and Balance and associated papers latest copy of the Repair and Al...

Page 597: ...nder a CFR Part 135 Certificate the operator can choose to use an Approved Aircraft Inspection Program INSPECTION PROGRAMS Refer to the 208 Maintenance Manual Chapter 4 00 00 Airworthiness Limitations...

Page 598: ...l times Contact a Cessna Authorized Service Facility for the first 100 hour or annual inspection depending on the program chosen for the airplane These inspections can be performed by any Cessna Autho...

Page 599: ...reventive maintenance that may be performed by pilots A Maintenance Manual must be obtained prior to performing any preventive maintenance to ensure that proper procedures are followed A Cessna Author...

Page 600: ...ear turning angle limit of 51 5 either side of center as shown by the steering limit marks If excess force is exerted beyond the turning limit a red over travel indicator block frangible stop will fra...

Page 601: ...he rudder lock and chock the wheels if the brakes are not utilized to prevent airplane movement In severe weather and high wind conditions tie the airplane down as outlined in the tiedown section CAUT...

Page 602: ...l position so that tabs fair with control surfaces 5 Install pitot tube cover s if available 6 Secure ropes or chains of sufficiently strong tensile strength to the wing tiedown fittings and secure to...

Page 603: ...lled Their use is generally reserved for maintenance such as main gear removal or raising the entire airplane whenever the cargo pod is not installed Anytime the cargo pod is installed if the main gea...

Page 604: ...not used for jacking will provide additional stability Do not use cargo pod structure for jacking or as a blocking surface Raise the airplane no more than required for the maintenance being performed...

Page 605: ...at FS 239 05 WL 97 50 and FS 272 13 WL 97 50 Remove screws located at leveling screw location on the left side of the fuselage just forward of the cargo doors Install two screws of sufficient length...

Page 606: ...ining and equipment necessary to conduct all service inspection and test procedures in accordance with applicable maintenance manuals it is recommended that owner operators contact the Cessna Authoriz...

Page 607: ...MIN G1000 AND MAINTENANCE U S OIL OIL SPECIFICATION Continued Next Page APPROVED OILS REFER TO PRATT WHITNEY CANADA SERVICE BULLETIN NO 1001 REVISION 28 OR SUBSEQUENT REVISON FOR A COMPLETE LISTING OF...

Page 608: ...ontinued OIL SPECIFICATION Continued OIL SYSTEM SERVICING Pratt Whitney Canada has determined that regular oil changes are no longer required and engine oil is to be changed on condition Refer to Prat...

Page 609: ...e oil is cold and within 3 quarts of MAX if the oil is hot WARNING Make sure oil dipstick cap is securely latched down Operating the engine with less than the recommended oil level and with the dipsti...

Page 610: ...MAINTENANCE GARMIN G1000 U S FUEL It is assumed that fuel temperature is the same as Outside Air Temperature OAT AN8 is JP 8 fuel with a reduced freeze point specified for Antarctic operations Figure...

Page 611: ...IL DTL 85470 DiEGME Type Anti Ice Additive in a concentration of 0 10 to 0 20 percent by volume 3 GOST 8313 Fluid I Type Anti Ice Additive in a concentration of 0 10 to 0 30 percent by volume 4 CIS TU...

Page 612: ...acceptable protection from microorganisms such as bacteria and fungi that can rapidly multiply and cause serious corrosion in tanks and may block filters screens and fuel metering equipment CAUTION JP...

Page 613: ...hrough the skin and will cause eye irritation It is also combustible Before using this material refer to all safety information on the container CAUTION Diethylene Glycol Monomethyl Ether DIEGME is sl...

Page 614: ...ration test kit Refer to 208 Maintenance Manual Chapter 12 11 01 Fuel Servicing for additional information on the anti icing additive concentration test kit It is imperative that the instructions for...

Page 615: ...obial growth therefore occasional use of a biocide may be required Biocide additive may be used on a limited basis defined as intermittent or non continuous use in a single application to sterilize ai...

Page 616: ...anks ON 3 6 U S Gallons 13 l Single Tank ON 2 8 U S Gallons 10 l Maximum Fuel Imbalance 200 Pounds 90 kg NOTE To achieve full fuel capacity fill fuel tank to the top of the filler neck Filling fuel ta...

Page 617: ...outboard fuel tank sump quick drain valves if installed is also recommended If contamination is detected drain all fuel drain points again Take repeated samples from all fuel drain points until all c...

Page 618: ...ved by Cessna and the Federal Aviation Administration WARNING It is the pilot s responsibility to make sure that the airplane s fuel supply is clean before flight Do not fly the airplane with contamin...

Page 619: ...ded on reservoir Maintain fluid level between MIN and MAX markings 2 Keep strut filled with MIL H 5606 hydraulic fluid per filling instructions placard No air pressure is required in strut COMPONENT S...

Page 620: ...ssure of 1850 PSI at 21 C 70 F Filling pressures will vary however due to ambient temperature in the filling area and the temperature rise resulting from compression of the oxygen Because of this mere...

Page 621: ...ith a VR speed of 85 knots or greater Whenever Type II Type III or Type IV anti ice fluid is applied to the airplane the takeoff flap setting is limited to UP and the VR is 88 KCAS 83 KIAS Refer to Se...

Page 622: ...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 Type I Type II Type III and Type IV flui...

Page 623: ...I deicing fluids should be sprayed on the airplane with engine shutdown in a manner that minimizes heat loss of fluid to the air The fluid should be applied in a temperature range from 160 F to 180 F...

Page 624: ...er to FAA Notice 8900 196 dated 8 16 12 or later 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 lif...

Page 625: ...times are based on the mixture ratio appropriate for the OAT Holdover times start when the last application has begun Guidelines for maximum holdover times anticipated by the FAA in coordination with...

Page 626: ...he time of protection may be shortened considerably This is also the case when fuel temperature is significantly lower than OAT NOTE Holdover timetables in FAA Notice 8900 196 dated 11 25 09 or later...

Page 627: ...hould be sprayed in a solid cone pattern of large coarse droplets at a temperature of 160 F to 180 F The fluid should be sprayed as close as possible to the airplane surfaces but not closer than 10 fe...

Page 628: ...fluid is however sometimes heated and sprayed as a deicing fluid For this case it should be considered a Type I fluid as the heat may change the characteristics of the thickening agents in the fluid...

Page 629: ...fter deicing is completed due to the limited holdover times of Type I deice fluid However Type III fluid is sometimes heated and sprayed as a deicing fluid For this case it should be considered a Type...

Page 630: ...T Holdover time starts when last application has begun Application techniques for Type IV fluid are the same as for Type I except that since the airplane is already clean the application should last o...

Page 631: ...ION Some Type IV fluids could form a thick or high strength gel during dry out and when rehydrated can freeze restricting movement of flight control surfaces while in flight Some Type IV fluids exhibi...

Page 632: ...special attention to the gaps between the flight controls All snow ice and slush must be removed from these gaps 2 Remove snow ice and slush from pitot tubes by hand only DIRECT SPRAY AVOIDANCE AREAS...

Page 633: ...AS 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 DIRECT SPRAY AVOIDANCE AREAS Pitot...

Page 634: ...867 SHP AND MAINTENANCE GARMIN G1000 U S DIRECT SPRAY AVOIDANCE AREAS Engine Inlets and Exhaust Brakes Pitot static Tubes Windshields Cabin Windows and Stall Warning Vane Figure 8 6 DEICE AND ANTI ICE...

Page 635: ...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 Because the cockpit is the first area...

Page 636: ...ratches and protect against corrosion the airplane must be waxed regularly with a good automotive wax applied in accordance with the manufacturer s instructions If the airplane is operated in a sea co...

Page 637: ...most current information regarding cleaning and servicing windshields and windows Improper cleaning or use of unapproved cleaning agents can cause damage to these surfaces CLEANING INSTRUCTIONS CAUTIO...

Page 638: ...asive particles 5 Rinse surface thoroughly with clean fresh water and dry with a clean cloth 6 Hard polishing wax should be applied to acrylic surfaces The wax has an index of refraction nearly the sa...

Page 639: ...Masking Paper St Regis Newton MA c 5 X N Poly Spotstick St Regis Newton MA d Protex 40 Mask Off Company Monrovia CA and Southwest Paper Co Wichita KS e Protex 10VS Mask Off Company Monrovia CA and Sou...

Page 640: ...mild soap solution on acrylic windshields and windows Polishing wax Refer to Note 1 Turtle Wax paste Great Reflections Paste Wax Slip Stream Wax paste Turtle Wax Inc Chicago IL 60638 E I duPont de Ne...

Page 641: ...ight inspection check the blades for nicks gouges scratches corrosion pits etc the propeller hub for evidence of grease and oil leaks and the propeller spinner for condition and security Repair of sma...

Page 642: ...essor blades during normal operation A compressor wash ring is installed on the top of the engine adjacent to the induction air inlet screen to facilitate this maintenance program Refer to 208 Mainten...

Page 643: ...commended for light soil and multiple motoring or a running wash is suggested for heavy soil CAUTION Observe engine starting cycle limits when conducting motoring wash procedures Refer to Section 2 Li...

Page 644: ...ol solution is injected directly into the combustion chamber by way of a special spray tube which is installed in one of the igniter plug ports This method of engine wash does not replace the need for...

Page 645: ...liner door panels and floor covering in the crew area of both versions and the rear cabin headliner and sidewalls of the Passenger Version need only be wiped off with a damp cloth In Cargo Versions th...

Page 646: ...o minimize wetting the fabric keep the foam as dry as possible and remove it with a vacuum cleaner The protective plywood floor panels if installed and aft bulkhead covering in the cargo area must be...

Page 647: ...engine maintenance record and on tags secured to the engine The following preservation schedule lists procedures to be followed CAUTION Under no circumstances should preservative oil be sprayed into t...

Page 648: ...ize condensation in the tanks 4 If the airplane will be out of service for 5 days or more disconnect the battery If the battery is left in the airplane it must be removed and serviced regularly to pre...

Page 649: ...to ensure all applicable supplements have been placed in the Pilot s Operating Handbook POH Supplements for both standard and installed optional equipment must be maintained to the latest revision Th...

Page 650: ...d to make proper and precise responses in every situation Limitations contained in the following supplements are FAA approved Observance of these operating limitations is required by Federal Aviation...

Page 651: ...ssna Customer Care at 316 517 5800 Continued Next Page Supplement Number Name Revision Level Equipment Installed 1 TKS Ice Protection System for Cargo Pod Equipped Airplanes 0 2 Artex ME406 Emergency...

Page 652: ...G1000 U S 208BPHCUSLOG LOG OF APPROVED SUPPLEMENTS Continued Supplement Number Name Revision Level Equipment Installed 16 Reserved 17 Reserved 18 Reserved 19 Reserved 20 L 3 Communications FA2100 Cock...

Page 653: ...IPPED AIRPLANES This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the TKS Ice Protection System for Cargo Pod Equipped Airp...

Page 654: ...ED AIRPLANES Use the Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number LOG OF EFFE...

Page 655: ...he following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that ar...

Page 656: ...t s Operating Handbook and FAA Approved Airplane Flight Manual POH AFM Revision 1 dated 22 May 2013 or later when the TKS Ice Protection System is installed on Cargo Pod Equipped Airplanes The informa...

Page 657: ...for such conditions REQUIRED TRAINING Specific training for flight into known or forecast icing conditions provided by Cessna Aircraft Company is required to be successfully completed by the pilot in...

Page 658: ...ons Takeoff is prohibited with any frost ice snow or slush adhering to the wings tail control surfaces propeller blades or engine air inlets WARNING The TKS Ice Protection System is not approved for a...

Page 659: ...visible moisture is present i e rain drizzle sleet snow fog water is present on the wing etc or 2 The OAT is 5 C 41 F or below and conditions are conducive to active frost formation e g clear night w...

Page 660: ...0 Pounds 3855 kg MINIMUM DISPATCH FLUID Minimum ice protection fluid for takeoff for flight into known or forecast icing conditions is 11 7 U S gallons 44 27 Liters This minimum amount of fluid allows...

Page 661: ...roportions WARNING Under no circumstances are fluids other than those listed above to be used in the TKS Ice Protection System Some fluids currently used for ground de icing purposes contain thickenin...

Page 662: ...FLAPS UP 110 KIAS if climbing and refer to the Emergency Procedure Section of this supplement FLAP SETTING IN ICING CONDITIONS WING FLAPS must be UP when holding in icing conditions WARNING With ice...

Page 663: ...ters 6 Windshield spray bar 7 Heated lift detector stall warning vane 8 Alternate Static Source 9 Left and Right Pitot Static Tube Heat System 10 Wing Ice Inspection Light 11 Engine Driven Generator 1...

Page 664: ...spinner installed in accordance with the Cessna Model 208 Series Maintenance Manual ENVIRONMENTAL CONDITIONS Icing conditions are defined as visually detected ice or the presence of visible moisture...

Page 665: ...ct ice 2 Accumulation of ice on the upper or lower surface of the wing aft of the protected area 3 Heavy ice accumulations on the windshield or when ice forms aft of the curved sections on the windshi...

Page 666: ...nditions listed in the Limitations section of this supplement The autopilot must be disengaged when the BELOW ICING MIN SPD flashing amber and white annunciation is activated The airspeeds listed in t...

Page 667: ...ese placards is required as specified in this section Placard wording can be from part numbered placards obtained from Cessna Aircraft Company or equivalent placards installed by an approved repair st...

Page 668: ...HP GARMIN G1000 U S FAA APPROVED LIMITATIONS Continued PLACARDS Continued INTERIOR PLACARDS Continued FLIGHT CREW AREA Continued Adjacent to the TKS Ice Protection System controls Above the Standby Ai...

Page 669: ...ENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 U S FAA APPROVED LIMITATIONS Continued PLACARDS Continued EXTERIOR PLACARDS Around the TKS Ice Protection Fluid Tank filler assembly Continued Next Pa...

Page 670: ...NA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED LIMITATIONS Continued PLACARDS Continued EXTERIOR PLACARDS Continued On the front of the TKS Ice Protection System Tank Continued Next...

Page 671: ...N 9 SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 U S FAA APPROVED LIMITATIONS Continued PLACARDS Continued EXTERIOR PLACARDS Continued Adjacent to TKS Ice Protection Porous Panels S1 19 20...

Page 672: ...AINTAIN 120 KIAS or greater until final approach and landing 7 Icing Conditions EXIT AS SOON AS POSSIBLE IF A ICE PRESS LOW ANNUNCIATOR GOES OFF 2 TKS Ice Protection System MONITOR 3 Icing Conditions...

Page 673: ...AS SOON AS POSSIBLE 4 Landing Distance MULTIPLY POH AFM DISTANCE BY 2 2 WING FLAPS UP 2 1 WING FLAPS TO APR 5 Minimum Approach Airspeed AT OR ABOVE 120 KIAS WING FLAPS UP 110 KIAS WING FLAPS TO APR WA...

Page 674: ...R and maintain extra airspeed consistent with available field length Do not retract the flaps once they have been extended unless required for go around When executing a go around retract flaps while...

Page 675: ...approach and landing follow the procedures listed under Inadvertent Icing Encounters in Section 3 Emergency Procedures of the POH AFM With an accumulation of 0 25 inch 6 35 mm or more on the wing lead...

Page 676: ...LL out CAUTION If the INERTIAL SEPARATOR is set to BYPASS at any point due to suspected or actual icing conditions do not return it to NORMAL until the inertial separator door has been visually inspec...

Page 677: ...and ice protection fluid 2 Engine TRQ Indicator MONITOR torque redline and torque bug should drop approximately 100 to 200 foot pounds IF INERTIAL SEPARATOR FAILS TO MOVE TO BYPASS 3 IGNITION Switch...

Page 678: ...reaker CHECK verify circuit breaker is IN second row fifth breaker from forward end 2 MAX FLOW Switch WINDSHIELD HOLD 6 SECONDS wait for total of 10 seconds IF WINDSHIELD ANTI ICE SYSTEM STILL DOES NO...

Page 679: ...AT ANNUNCIATOR SHOWN ON PFD 3 SENSOR Softkey PRESS 4 ADC 1 2 Softkey SELECT OPPOSITE SYSTEM 5 PFD ADI Displays CHECK amber BOTH ON ADC 1 or 2 shown on both PFDs IF AMBER L R P S HEAT ANNUNCIATOR SHOWN...

Page 680: ...L WARN Circuit Breaker CHECK verify circuit breaker is IN bottom row third breaker from forward end 2 Airspeed MONITOR NOTE With continued ice buildup expect no stall warning horn during slow speed op...

Page 681: ...g to exit icing condition 3 Ice Protection ON a PRIMARY Switch HIGH b MAX FLOW Switch AIRFRAME then WINDSHIELD press momentarily c P S HEAT LOW A S AWARE Switch ON d STALL HEAT Switch ON e LED PANELS...

Page 682: ...IGH b MAX FLOW Switch AIRFRAME then WINDSHIELD press momentarily c P S HEAT LOW A S AWARE Switch ON d STALL HEAT Switch ON e LED PANELS ANNUN Rheostat ADJUST for ambient lighting conditions f IGNITION...

Page 683: ...nditions EXIT IMMEDIATELY 4 Airspeed 95 KIAS minimum or greater during exit 5 Autopilot AS DESIRED WARNING WING Flaps must be extended to TO APR anytime airspeed is below 95 KIAS IF ON APPROACH WING F...

Page 684: ...Ice Protection System with ice forming on the airplane In order to minimize ice accumulations on unprotected lower surfaces maintain a minimum speed of 95 KIAS with WING FLAPS UP during operations in...

Page 685: ...e and Systems Descriptions TKS Ice Protection System Operation Indication and Messaging in this supplement for description and operation of TKS indications CAUTION Other than the prescribed preflight...

Page 686: ...re on the following pages 3 BACKUP Switch ON FOR 4 MINUTES THEN OFF NOTE Listen for pump operation verify red A ICE PRESS LOW annunciator initially comes ON then goes OFF as system flow and pressure b...

Page 687: ...mely important to visually inspect each TKS panel for proper fluid flow across a portion of the active area of each panel prior to flight into known or forecast icing conditions NOTE At these higher t...

Page 688: ...witch ON 8 Windshield Ice Detection Light CHECK FOR ILLUMINATION 9 WING LIGHT Switch ON verify wing inspection light on 10 LED PANELS ANNUN Rheostat ADJUST for ambient lighting conditions 11 P S HEAT...

Page 689: ...URED Min 11 7 U S gallons CAUTION The airplane must be level to assure accurate TKS Ice Protection System fluid quantity when using the fluid tank sight gage on the TKS Ice Protection System tank 6 Po...

Page 690: ...verify white A ICE NORM annunciator comes on 3 MAX FLOW Switch AIRFRAME press momentarily and check operation 4 PRIMARY Switch OFF verify white A ICE NORM annunciator goes off c BACKUP Switch ON verif...

Page 691: ...ading edges Usually this will take only three to five minutes The PRIMARY switch may then be reset to NORM b MAX FLOW Switch WINDSHIELD press momentarily and repeat if necessary to keep windshield fre...

Page 692: ...IMARY switch to HIGH If ice is observed building on the leading edge of the wing with PRIMARY switch in HIGH immediately select MAX FLOW switch to AIRFRAME and execute the Emergency Procedure for Fail...

Page 693: ...d TAKEOFF 1 WING FLAPS Handle UP or TO APR TO APR recommended WING FLAPS UP if using Type II III or IV anti ice fluid 2 POWER Lever SET FOR TAKEOFF observe Takeoff ITT and Ng limits 3 ANNUNCIATOR s CH...

Page 694: ...tate counterclockwise and PULL out CAUTION If the INERTIAL SEPARATOR is set to BYPASS at any point due to suspected or actual icing conditions do not return it to NORMAL until the inertial separator d...

Page 695: ...ert for out of trim forces Pilot control wheel input should be applied as required to prevent potential undesired flight path deviations Monitor airspeed in icing conditions with the autopilot engaged...

Page 696: ...Switch ON d STALL HEAT Switch ON e BELOW ICING MIN SPD Switch Light PRESS TO TEST f LED PANELS ANNUN Rheostat ADJUST for ambient lighting conditions g INERTIAL SEPARATOR BYPASS rotate counterclockwise...

Page 697: ...ng to allow windshield to clear NOTE Multiply normal POH AFM landing distance by 2 2 for WING FLAPS UP 120 KIAS maximum If the shortest landing distance is required due to field length WING FLAPS TO A...

Page 698: ...ch OFF d STALL HEAT Switch OFF 2 IGNITION NORM SHUTDOWN AND SECURING AIRPLANE If the INERTIAL SEPARATOR was set to BYPASS during flight perform the following after engine shutdown 1 Inertial Separator...

Page 699: ...e airframe protected areas and propeller normal performance will only degrade slightly If ice is allowed to accrete on the airframe protected areas however significant climb and cruise performance deg...

Page 700: ...increasing power to Maximum Rated Setting Promptly extend the flaps to TO APR to help stabilize the airplane Increase airspeed to 95 KIAS or greater before retracting flaps If the flaps are subsequent...

Page 701: ...that the pilot exit the icing conditions as soon as practical AREA C If current route leg MEA or MOCA if applicable falls in this area the pilot must exit icing conditions immediately CAUTION Regardl...

Page 702: ...ION 9 SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED PERFORMANCE Continued ENROUTE TOOL FOR EXITING ICING Continued Continued Next Page Figure S1 1 208BPHCUS S1 00 S1...

Page 703: ...airplane to climb to this altitude ENROUTE LIMITATIONS If icing is encountered the pilot must exit icing immediately since enroute operation fell in Area C Alternate Route KSLC to KCPR KSLC to FBR to...

Page 704: ...when any type of visible moisture is present 1 Reference recommended 50 foot airspeed with ice on airframe in the Normal Procedures of this supplement correct the applicable Short Field Landing Dista...

Page 705: ...G1000 U S FAA APPROVED WEIGHT AND BALANCE CARGO POD LOADING ARRANGEMENTS TKS TANK INSTALLED NOTE The 195 77 inch station reference for TKS is for the fluid and tank installation and is not valid for c...

Page 706: ...SECTION 9 SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED WEIGHT AND BALANCE Continued Figure S1 3 208BPHCUS S1 00 S1 54...

Page 707: ...ion System equipped Cessna Caravan the TKS Ice Protection System must be drained of all fluid Drain fluid from tank through the drain valve on the left side of the tank sump When drained no appreciabl...

Page 708: ...SECTION 9 SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED WEIGHT AND BALANCE Continued Figure S1 4 Sheet 1 of 2 208BPHCUS S1 00 S1 56...

Page 709: ...CESSNA SECTION 9 SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 U S FAA APPROVED WEIGHT AND BALANCE Continued Figure S1 4 Sheet 2 S1 57 208BPHCUS S1 00...

Page 710: ...limb speed to maximum operating speed The back plates of the panels are also manufactured out of titanium and are formed to create reservoirs for the ice protection fluid allowing fluid supply to the...

Page 711: ...MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 U S FAA APPROVED AIRPLANE SYSTEMS AND DESCRIPTIONS Continued SYSTEM DESCRIPTION Continued Continued Next Page TKS ICE PROTECTION SYSTEM INSTALLATION Figur...

Page 712: ...ON 9 SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED AIRPLANE SYSTEMS AND DESCRIPTIONS Continued TKS ICE PROTECTION SYSTEM FLUID SCHEMATIC Figure S1 6 208BPHCUS S1 00...

Page 713: ...ank has a maximum capacity of 20 8 gallons 78 7 l It is the pilot s responsibility to make sure that an adequate quantity of TKS fluid is carried for the planned mission A minimum of 11 7 gallons 44 3...

Page 714: ...es with the PRIMARY switch in HIGH ANTI ICE fluid quantity and time values displayed against an amber background with black text alerts the pilot of less than 20 minutes of ice protection with the PRI...

Page 715: ...switch NORM mode is the lowest fluid flow rate of the system The flow rate is achieved by running both metering pumps of the system on a continuous repeat cycle of operation The two pumps will run for...

Page 716: ...RAME mode only when in heavy or extreme icing conditions If conditions require MAX FLOW AIRFRAME use exit the icing conditions immediately The windshield system may be activated by selecting the WINDS...

Page 717: ...CESSNA SECTION 9 SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 U S FAA APPROVED TKS ICE PROTECTION SYSTEM OPERATION INDICATION AND MESSAGING Figure S1 7 S1 65 208BPHCUS S1 00...

Page 718: ...e and runs continuously like HIGH mode BACKUP mode is independent and isolated from the other ice protection operational modes It is provided as a redundant capability in the event the normal operatio...

Page 719: ...N AND MESSAGING Continued For the four modes of airframe ice protection operation the resulting endurance with a full tank of fluid is MAXIMUM FLUID ENDURANCE PRIMARY NORM selected 3 hours 25 minutes...

Page 720: ...trated in Figure S1 10 the sight gage may be viewed through the cargo pod door located ahead of the filler To assure the minimum dispatch quantity is achieved specific steps must be taken First the ai...

Page 721: ...67 SHP SUPPLEMENT 1 GARMIN G1000 U S FAA APPROVED AIRPLANE SYSTEMS AND DESCRIPTION Continued TKS ICE PROTECTION SYSTEM OPERATION INDICATION AND MESSAGING Continued Continued Next Page FLUID TANK SIGHT...

Page 722: ...selecting either NORM or HIGH the white A ICE NORM or white A ICE HIGH advisory message appears in the annunciation window The appropriate white message A ICE NORM or A ICE HIGH will remain displayed...

Page 723: ...system operation and may be indicative of potential substandard ice protection performance In BACKUP mode the red A ICE PRESS LOW annunciator is armed immediately upon selecting BACKUP ON If a low pre...

Page 724: ...ibiting the red A ICE PRESS LOW annunciator in HIGH and NORM modes has been implemented to avoid nuisance CAS alerts PITOT STATIC HEAT SYSTEMS A left and right pitot static heat system is installed to...

Page 725: ...ed in the instrument panel directly in front of the pilot and is activated by an airspeed switch plumbed off the pilot s pitot and static lines A remote mounted relay box provides logic for the annunc...

Page 726: ...above 97 5 2 2 knots Pressing the flashing BELOW ICING MIN SPD annunciator which incorporates a momentary switch silences the stall warning horn and causes the annunciator to stop flashing The annunc...

Page 727: ...etection light is activated anytime the NAV Switch is in the ON position The wing inspection light is flush mounted in the left wing leading edge to fuselage fairing to help detect ice on the wing at...

Page 728: ...ations Approved Ice Protection Fluid in this supplement for a list of approved TKS ice protection fluid type The filler cap is located on the left side of the cargo pod To prevent the possibility of c...

Page 729: ...ximity of the porous panels Refer to the Maintenance Manual for detailed information on cleaning painting interior and exterior painted surfaces on the airplane Only the following fluids are approved...

Page 730: ...SECTION 9 SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED This Page Intentionally Left Blank 208BPHCUS S1 00 S1 78...

Page 731: ...ANSMITTER ELT This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Artex ME406 Emergency Locator Transmitter ELT is instal...

Page 732: ...ELT Use the Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number LOG OF EFFECTIVE PA...

Page 733: ...he following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that ar...

Page 734: ...n the ELT transmitter unit is a panel containing an ARM ON Switch and a transmitter warning light The ELT installation uses two different warnings to tell the pilot when the ELT is energized The aural...

Page 735: ...ANSMITTER WARNING LIGHT Light comes on RED to indicate the transmitter is transmitting a distress signal 3 ANTENNA RECEPTACLE Connects to the antenna mounted on top of tailcone 4 15 PIN D SUB RECEPTAC...

Page 736: ...ELT with the applicable Civil Aviation Authority before use to make sure that the identification code transmitted by the ELT is in the COSPAS SARSAT database Refer to www cospas sarsat org for registr...

Page 737: ...requires manual switching of the ELT panel switch which is located on the ELT unit 1 MAKE SURE THE ELT IS ENERGIZED a If the red warning light above the remote switch is not flashing set the remote sw...

Page 738: ...nd arm the ELT after it has been accidentally energized no emergency The ELT can be energized by a lightning strike or hard landing If the red light above the remote switch is flashing and the aural w...

Page 739: ...ANSMITTER ELT This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Artex C406 N Emergency Locator Transmitter ELT is insta...

Page 740: ...ELT Use the Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number LOG OF EFFECTIVE PA...

Page 741: ...he following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that ar...

Page 742: ...located in the dorsal fin right side On the ELT transmitter unit is a panel containing an ON OFF Switch and a transmitter warning light The ELT installation uses two different warnings to tell the pi...

Page 743: ...TRANSMITTER WARNING LIGHT Light comes on RED to indicate the transmitter is transmitting a distress signal 3 ANTENNA RECEPTACLE Connects to the antenna mounted on top of tailcone 4 REMOTE CABLE JACK...

Page 744: ...ELT with the applicable Civil Aviation Authority before use to make sure that the identification code transmitted by the ELT is in the COSPAS SARSAT database Refer to www cospas sarsat org for regist...

Page 745: ...requires manual switching of the ELT panel switch which is located on the ELT unit 1 MAKE SURE THE ELT IS ENERGIZED a If the red warning light above the remote switch is not flashing set the remote sw...

Page 746: ...nd arm the ELT after it has been accidentally energized no emergency The ELT can be energized by a lightning strike or hard landing If the red light above the remote switch is flashing and the aural w...

Page 747: ...ECHNOLOGY SVT This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Garmin G1000 Synthetic Vision Technology SVT is install...

Page 748: ...Y Use the Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number LOG OF EFFECTIVE PAGES...

Page 749: ...he following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that ar...

Page 750: ...rence Guide CRG NOTE Not all airport runways are depicted with SVT OPERATING LIMITATIONS The G1000 limitations listed in Section 2 of the POH apply when using SVT In addition SVT is not available in l...

Page 751: ...lot during flight is displayed on the MFD AUX group SYSTEM STATUS page EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when the Garmin G1000 Synthetic Vision Technology is...

Page 752: ...rocedures when the Garmin G1000 Synthetic Vision Technology is installed PERFORMANCE There is no change to the airplane performance when the Garmin G1000 Synthetic Vision Technology is installed WEIGH...

Page 753: ...EMENT 5 CONFIGURATION DEVIATION LIST CDL This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual SERIAL NO REGISTRATION NO 208BPHCUS S...

Page 754: ...e the Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number LOG OF EFFECTIVE PAGES Sup...

Page 755: ...he following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that ar...

Page 756: ...imitations must be listed on a placard affixed in the cockpit in clear view of the pilot in command and other appropriate crew member s 3 The pilot in command must be notified of each operation with a...

Page 757: ...er 2200 The parts within each system are identified by functional description and when necessary by part numbers ATA System or Unit 1 Number Installed 2 Number Required for Dispatch Requirements for F...

Page 758: ...Deviation List CDL NORMAL PROCEDURES There is no change to the airplane normal procedures when utilizing the Configuration Deviation List CDL PERFORMANCE There is no change to the airplane performanc...

Page 759: ...OXYGEN SYSTEM This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Oxygen System is installed SERIAL NO REGISTRATION NO 20...

Page 760: ...of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number LOG OF EFFECTIVE PAGES Supplement St...

Page 761: ...he following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that ar...

Page 762: ...as part of the regulator assembly The system also contains an altitude compensating regulator located between the pressure regulator and the oxygen supply lines which varies the flow of oxygen to the...

Page 763: ...h control wheel to operate the corresponding microphone A remote OXYGEN control lever is located in the overhead console above the pilot s and copilot s seats and is used to shutoff the supply of oxyg...

Page 764: ...ate a serious fire hazard and such contact must be avoided when handling oxygen equipment OXYGEN FILLING PRESSURES Figure S6 1 OPERATING LIMITATIONS There are no additional airplane operating limitati...

Page 765: ...nting the altitude at which the flight will be conducted After intersecting the line drop down vertically to the bottom of the chart and read the duration in hours given on the scale This duration is...

Page 766: ...SECTION 9 SUPPLEMENTS CESSNA SUPPLEMENT 6 MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED OXYGEN DURATION CHART 51 CUBIC FEET CAPACITY Figure S6 2 208BPHCUS S6 00 S6 8...

Page 767: ...CESSNA SECTION 9 SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 6 GARMIN G1000 U S FAA APPROVED OXYGEN DURATION CHART 117 CUBIC FEET CAPACITY Figure S6 3 S6 9 208BPHCUS S6 00...

Page 768: ...efore handling oxygen equipment 2 Oxygen Hose PLUG INTO OUTLET nearest to the seat you are occupying NOTE When the oxygen system is turned ON oxygen will flow continuously at the proper rate of flow f...

Page 769: ...IONING SYSTEM This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Air Conditioning System is installed SERIAL NO REGISTRA...

Page 770: ...Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number LOG OF EFFECTIVE PAGES Suppleme...

Page 771: ...e following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that are...

Page 772: ...ards and in the fuselage sides interconnect the compressor evaporators and the condenser Controls for the air conditioning system are located at the lower edge of the instrument panel directly above t...

Page 773: ...from the aft cabin bulkhead The pilot s and passenger s overhead outlets are the swivel type for optimum positioning and airflow volume is controlled by rotating the outlet nozzle which controls an in...

Page 774: ...SECTION 9 SUPPLEMENTS CESSNA SUPPLEMENT 7 MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED GENERAL Continued AIR CONDITIONING SYSTEM Figure S7 2 208BPHCUS S7 00 S7 6...

Page 775: ...2397 foot pounds the air conditioner must be turned off for any takeoff or landing under those conditions Refer to Section 5 Performance Figure 5 8 Maximum Engine Torque For Takeoff for takeoff torque...

Page 776: ...walk around inspection open cabin doors to aid in cool down of the cabin before flight Air conditioning system components should be inspected as follows 1 Compressor CHECK verify condition 2 Drive Be...

Page 777: ...ions the idle ITT may exceed the maximum idle ITT limitation of 700 C Advance the FUEL CONDITION Lever toward HIGH IDLE to increase the idle Ng as required to maintain a satisfactory ITT 700 C or lowe...

Page 778: ...f when temperatures in the evaporators nears 32 F 0 C If frost does form as evidenced by reduced cooling airflow turn the AIR CONDITIONING Switch to VENTILATE and select the HIGH speed AC FANS positio...

Page 779: ...KTAS decrease in cruise performance and approximately 1 increase in fuel required for a given trip as a result of the air conditioner installation This reduction in climb and cruise performance may b...

Page 780: ...rate of climb CRUISE When cruising at altitudes where the maximum allowable cruise power is below the torque limit reduce this setting by 40 FT LBS when the air conditioner is operating refer to Secti...

Page 781: ...TER GENERATOR This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the 300 Amp Starter Generator is installed SERIAL NO REGIST...

Page 782: ...he Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number LOG OF EFFECTIVE PAGES Supple...

Page 783: ...he following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that ar...

Page 784: ...rical system When operating as a starter a speed sensing switch in the starter generator will automatically shutdown the starter thereby providing overspeed protection and automatic shutoff The starte...

Page 785: ...at 55 64 Ng 2 Do not exceed 170 amps as indicated by the GEN AMPS indicator with engine power settings at or above 65 Ng or 3 The maximum generator load listed below as a function Ng air conditioning...

Page 786: ...he 300 amp starter generator is limited to a maximum load of 250 amps as indicated by the GEN AMPS indicator when operating at a speeds below 100 KIAS or 2 The maximum generator load listed below as a...

Page 787: ...erator is installed NORMAL PROCEDURE STARTING ENGINE Battery Start After engine start the amber GENERATOR AMPS annunciator may come on while the battery is recharging This is normal and should go out...

Page 788: ...SECTION 9 SUPPLEMENTS CESSNA SUPPLEMENT 8 MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED This Page Intentionally Left Blank 208BPHCUS S8 00 S8 8...

Page 789: ...N FINDER ADF This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Bendix King KR 87 Automatic Direction Finder ADF is inst...

Page 790: ...ADF Use the Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number LOG OF EFFECTIVE PA...

Page 791: ...he following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that ar...

Page 792: ...requency display allows switching between preselected standby and active frequencies by pushing the frequency transfer button Both preselected frequencies are stored in a nonvolatile memory circuit no...

Page 793: ...CESSNA SECTION 9 SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 9 GARMIN G1000 U S FAA APPROVED BENDIX KING KR87 AUTOMATIC DIRECTION FINDER ADF Figure S9 1 S9 5 208BPHCUS S9 00...

Page 794: ...the carrier wave and its morse code identifier can be heard NOTE CW signals Morse Code are unmodulated and no audio will be heard without use of BFO This type of signal is not used in the United State...

Page 795: ...R BUTTON SET RST The SET RST button resets the elapsed timer whether it is being displayed or not 9 FLIGHT TIMER ELAPSED TIMER MODE SELECTOR BUTTON FLT ET The FLT ET button selects either Flight Timer...

Page 796: ...ECTION FINDER 1 OFF VOL Control ON 2 Frequency Selector Knobs SELECT desired frequency in the standby frequency display 3 FRQ Button PUSH to move the desired frequency from the standby to the active p...

Page 797: ...a system malfunction TO OPERATE BFO 1 OFF VOL Control ON 2 BFO Button PRESS ON 3 ADF Selector Button on audio control panel SET to desired mode 4 VOL Control ADJUST to desired listening level NOTE A...

Page 798: ...tive position 5 ADF Selector Button on audio control panel SET to desired mode 6 VOL Control ADJUST to desired listening level TO OPERATE ELAPSED TIME TIMER COUNT UP MODE 1 OFF VOL Control ON 2 FLT ET...

Page 799: ...tune the 1 s The small knob is pushed in to tune the 10 s The outer knob tunes minutes up to 59 minutes NOTE Selector knobs remain in the time set mode for 15 seconds after the last entry or until the...

Page 800: ...n being tuned by switching the function selector to ANT and listening for station call letters ELECTRICAL STORMS In the vicinity of electrical storms an ADF indicator pointer tends to swing from the s...

Page 801: ...PERFORMANCE There is no change in airplane performance when the Bendix King KR 87 Automatic Direction Finder ADF is installed However the installation of an externally mounted antenna or related exte...

Page 802: ...SECTION 9 SUPPLEMENTS CESSNA SUPPLEMENT 9 MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED This Page Intentionally Left Blank 208BPHCUS S9 00 S9 14...

Page 803: ...RS REMOVED KIT This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Cargo Doors Removed Kit is installed SERIAL NO REGISTR...

Page 804: ...he Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number LOG OF EFFECTIVE PAGES Supple...

Page 805: ...he following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that ar...

Page 806: ...ations such as skydiving aerial photography emergency air drops etc The kit consists of a vented spoiler installed on the forward cargo door hinges to minimize airflow buffeting within the cabin with...

Page 807: ...OPERATING LIMITATIONS PLACARDS WARNING With the cargo doors removed and the spoiler installed the following placards must be installed On aft side of spoiler Adjacent to the ALT STATIC AIR valve cont...

Page 808: ...d be removed or secured Face protection is also recommended for passengers near the door opening With the Cargo Doors Removed Kit installed flight characteristics are essentially unchanged PERFORMANCE...

Page 809: ...7 AUDIO PANELS This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when Dual Garmin GMA 1347 Audio Panels are installed SERIAL NO...

Page 810: ...ELS Use the Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number LOG OF EFFECTIVE PAG...

Page 811: ...LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins t...

Page 812: ...o is controlled by the individual audio selector switches and adjusted for volume level by using the selected receiver volume controls The system is designed so that microphones are voice activated wi...

Page 813: ...copilot attempting to transmit over COM1 using audio panel number 2 the onside pilot s push to talk switch will override the transmission when selected If both pilots have COM1 selected on their resp...

Page 814: ...the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual GARMIN GFC 700 AUTOMATED FLIGHT CONTROL SYSTEM AFCS Use of the autopilot is prohibited when both audio panels are inoperati...

Page 815: ...n MFD NOTE The PFD CDI SYNC and BARO SYNC settings must be ON to allow the copilot s PFD controls to affect settings on the MFD These settings are accessible using the PFD MENU button 2 Flight Directo...

Page 816: ...ON SIDE RADIO FOR COMMUNICATION NOTE In the event of an AUDIO 1 failure a fail safe circuit connects the pilot s headset directly to the COM 1 radio The speakers on the affected side will be inoperat...

Page 817: ...L DISPLAY UNIT This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when Honeywell KHF 1050 HF Transceiver with PS440 Control Displ...

Page 818: ...DISPLAY UNIT Use the Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number LOG OF EFF...

Page 819: ...he following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that ar...

Page 820: ...nd control interface Frequency channel mode audio gain and squelch level selections are entered via its controls Fault monitoring and fault annunciation are also provided by the PS440 The PS440 provid...

Page 821: ...re is no change to the airplane abnormal procedures for airplanes equipped with Honeywell KHF 1050 HF Transceiver with PS440 Control Display Unit NORMAL PROCEDURES There is no change to the airplane n...

Page 822: ...SECTION 9 SUPPLEMENTS CESSNA SUPPLEMENT 13 MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED This Page Intentionally Left Blank 208BPHCUS S13 00 S13 6...

Page 823: ...WER OUTLETS This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when 115 Volt AC Power Outlets option is installed SERIAL NO REGIS...

Page 824: ...TLETS Use the Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number LOG OF EFFECTIVE P...

Page 825: ...ts and is protected by two circuit breaker s on the left sidewall circuit breaker panel The two breakers are labeled 115 VAC OUTLET CTRLR and 115 VAC PWR INVTR located on the bottom row fifth and sixt...

Page 826: ...st be switched to OFF when not in use 5 The 115 VAC power outlets may not be used to power flight critical communication navigation or attitude reference devices 6 Use of the 115 VAC power system is p...

Page 827: ...ical Load REDUCE a 115 VAC POWER OUTLETS Switch OFF ABNORMAL PROCEDURES LOSS OF 115 VAC ELECTRICAL POWER AT ALL POWER OUTLETS AND 115 VAC PWR INVTR CIRCUIT BREAKER OPENS 1 Electrical Devices DISCONNEC...

Page 828: ...r will be momentarily off as the 115 VAC system is reset 3 115 VAC POWER OUTLETS Switch OFF THEN ON 4 Electrical Devices RECONNECT AS NECESSARY CAUTION Maximum electrical load for all power outlets is...

Page 829: ...115 VAC POWER OUTLETS 1 115 VAC POWER OUTLETS Switch ON CAUTION Maximum electrical load for all power outlets is 4 3 amps 500 watts maximum individual outlet load is limited to 2 0 amps 230 watts BEF...

Page 830: ...SECTION 9 SUPPLEMENTS CESSNA SUPPLEMENT 14 MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED This Page Intentionally Left Blank 208BPHCUS S14 00 S14 8...

Page 831: ...NiCAD BATTERY This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Nickel Cadmium NiCAD Battery is installed SERIAL NO RE...

Page 832: ...he Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number LOG OF EFFECTIVE PAGES Supple...

Page 833: ...he following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that ar...

Page 834: ...ately stop providing charging current to the battery from the airplane power system This is accomplished by turning the BATTERY Switch to OFF and using the appropriate checklist procedures contained i...

Page 835: ...operated flight and engine indications fuel boost pump EIS annunciators WING FLAPS Handle and all navigation and communications will be inoperative All standby instruments including torque indicator a...

Page 836: ...GEN FIELD Circuit Breakers OPEN pull out first row last two breakers on forward end h RDNG LIGHT Circuit Breaker OPEN pull out third row second breaker from aft end i RADAR R T Circuit Breaker OPEN p...

Page 837: ...ITION POSITIVE a GENERATOR Switch TRIP b STBY ALT PWR Switch OFF WARNING Without electrical power all electrically operated flight and engine indications fuel boost pump EIS annunciators WING FLAPS Ha...

Page 838: ...GEN FIELD Circuit Breakers OPEN pull out first row last two breakers on forward end h RDNG LIGHT Circuit Breaker OPEN pull out third row second breaker from aft end i RADAR R T Circuit Breaker OPEN p...

Page 839: ...FAA APPROVED NORMAL PROCEDURES There is no change to the airplane normal procedures for airplanes equipped with Nickel Cadmium NiCAD battery PERFORMANCE There is no change to the airplane performance...

Page 840: ...SECTION 9 SUPPLEMENTS CESSNA SUPPLEMENT 15 MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED This Page Intentionally Left Blank 208BPHCUS S15 00 S15 10...

Page 841: ...DATA RECORDER This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the L 3 Communications FA2100 Cockpit Voice and Flight Dat...

Page 842: ...DATA RECORDER Use the Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number LOG OF EF...

Page 843: ...he following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that ar...

Page 844: ...tentiometer located in the cabin overhead The Voice Recorder uses two audio summing amplifiers located in the forward pedestal structure recording audio from the cockpit area microphone located direct...

Page 845: ...S There is no change to the airplane emergency procedures when the L 3 Communications FA2100 Cockpit Voice and Flight Data recorder is installed NORMAL PROCEDURES There is no change to the airplane no...

Page 846: ...SECTION 9 SUPPLEMENTS CESSNA SUPPLEMENT 20 MODEL 208B 867 SHP GARMIN G1000 U S FAA APPROVED This Page Intentionally Left Blank 208BPHCUS S20 00 S20 6...

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