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CESSNA

SECTION 6

MODEL 208B 867 SHP

WEIGHT AND BALANCE/

GARMIN G1000

EQUIPMENT LIST

U.S.

NOTE

Pilot or front passenger center of gravity on adjustable seats

positioned for an average occupant with the seat locking pin

at FS 145.0. Numbers in parentheses indicate forward and

aft limits of occupant center of gravity range.

Cargo area center of gravity in Zones 1 thru 6 based on the

mid point of the zone.

The forward face of the raised floor (FS 332.0) can be used

as a convenient reference point for determining the location

of occupant or cargo Fuselage Stations.

When a cargo barrier is installed, two-place Commuter seat

4 and 5 or individual Commuter seats 3 and 4 must be

removed. Mission requirements will dictate if any aft

passenger seating is to remain installed.

Figure 6-11 (Sheet 2)

CABIN INTERNAL LOADING ARRANGEMENTS

(PASSENGER VERSION)

208BPHCUS-00

6-41

Содержание Cessna Grand Caravan Ex 208B

Страница 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...

Страница 2: ......

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

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

Страница 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...

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

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

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

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

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

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

Страница 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...

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

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

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

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

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

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

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

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

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

Страница 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...

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

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

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

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

Страница 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...

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

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

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

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

Страница 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...

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

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

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

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

Страница 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...

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

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

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

Страница 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...

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

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

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

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

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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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