CESSNA CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL SECOND EDITION Revision 0 NOTICE: These commodities, technology or software were exported from the United States in accordance with the Export Administration Regulations. Diversion contrary to U.S. law is prohibited. Courses for the Cessna Caravan 208 aircraft are taught at the following FlightSafety learning center: FlightSafety International Wichita Cessna Maintenance Learning Center 2021 S. Eisenhower Wichita, Kansas 67209-1960 Phone: (316) 361-3900 Toll-Free: (800) 491-9796 FAX: 316-361-3899 Copyright © 2016 FlightSafety International, Inc. Unauthorized reproduction or distribution is prohibited. All rights reserved. ii INSERT LATEST REVISED PAGES, DESTROY SUPERSEDED PAGES LIST OF EFFECTIVE PAGES Dates of issue for original and changed pages are: Original..................... 0........... April 2016 NOTE: For printing purposes, revision numbers in footers occur at the bottom of every page that has changed in any way (grammatical or typographical revisions, reflow of pages, and other changes tha­­t do not necessarily affect the meaning of the manual). THIS PUBLICATION CONSISTS OF THE FOLLOWING: Page No. *Revision No. Cover.......................................................... Copyright.................................................... LEP............................................................. i—x............................................................. 1-1—1-4..................................................... 2-1—2-4..................................................... 5-1—5-4..................................................... 20-1—20-2................................................. 21-1—21-8................................................. 22-1—22-6................................................. 23-1—23-6................................................. 24-1—24-28............................................... 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 25-1—25-4................................................. 26-1—26-2................................................. 27-1—27-10............................................... 28-1—28-18............................................... 30-1—30-20............................................... 31-1—31-10............................................... 32-1—32-4................................................. 33-1—33-2................................................. 34-1—34-8................................................. 35-1—35-2................................................. 36-1—36-2................................................. 51-1—51-2................................................. 61-1—61-8................................................. 71-1—71-20............................................... 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 *Zero in this column indicates an original page. iii Introduction 01 ATA 2200 02 5-12 Aircraft General NOTICE The material contained in this training manual is based on information ­obtained from the aircraft manufacturer’s pilot manuals and maintenance manuals. It is to be used for familiarization and training purposes only. At the time of printing it contained then-current information. In the event of conflict between data provided herein and that in publications issued by the manufacturer or the applicable regulatory agency, that of the manufacturer or the regulatory agency shall take precedence. We at FlightSafety want you to have the best training possible. We welcome any suggestions you might have for improving this manual or any other aspect of our training program. Standard Practices 20 Air Conditioning 21 Autoflight 22 Communications 23 Electrical Power 24 Equipment and Furnishings 25 Fire Protection 26 Flight Controls 27 Fuel 28 Ice and Rain Protection 30 Indicating and Recording 31 v Landing Gear 32 Lights 33 Navigation 34 Oxygen 35 Pneumatics 36-37 Structures 51-57 Propellers 61 Powerplant 71-80 71-80 vii CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CONTENTS CONTENTS Page Page INTRODUCTION......................................................................................................................... 1-1 ICE AND RAIN PROTECTION................................................................................................. 30-1 ATA 2200....................................................................................................................................... 2-1 General................................................................................................................................. 30-1 Maintenance Publications........................................................................................................ 2-1 INDICATING AND RECORDING............................................................................................. 31-1 AIRCRAFT GENERAL................................................................................................................ 5-1 General................................................................................................................................. 31-1 General Organization.............................................................................................................. 5-1 LANDING GEAR....................................................................................................................... 32-1 STANDARD PRACTICES.......................................................................................................... 20-1 General................................................................................................................................. 32-1 General................................................................................................................................. 20-1 LIGHTS....................................................................................................................................... 33-1 AIR CONDITIONING................................................................................................................ 21-1 General................................................................................................................................. 33-1 General................................................................................................................................. 21-1 NAVIGATION............................................................................................................................. 34-1 AUTO FLIGHT............................................................................................................................ 22-1 General................................................................................................................................. 34-1 General................................................................................................................................. 22-1 OXYGEN..................................................................................................................................... 35-1 Description........................................................................................................................... 22-2 Oxygen Systems................................................................................................................... 35-1 COMMUNICATIONS................................................................................................................. 23-1 PNEUMATICS/VACUUM.......................................................................................................... 36-1 General................................................................................................................................. 23-1 Pneumatic System—General................................................................................................ 36-1 ELECTRICAL POWER.............................................................................................................. 24-1 Vacuum System—General................................................................................................... 36-1 General................................................................................................................................. 24-1 STRUCTURES............................................................................................................................ 51-1 EQUIPMENT & FURNISHINGS............................................................................................... 25-1 General................................................................................................................................. 51-1 Flight Compartment - General............................................................................................. 25-1 PROPELLERS............................................................................................................................. 61-1 FIRE PROTECTION................................................................................................................... 26-1 General................................................................................................................................. 61-1 Fire Detection System.......................................................................................................... 26-1 POWERPLANT........................................................................................................................... 71-1 FLIGHT CONTROLS................................................................................................................. 27-1 General................................................................................................................................. 71-1 General................................................................................................................................. 27-1 FUEL............................................................................................................................................ 28-1 General................................................................................................................................. 28-1 Revision 0 FOR TRAINING PURPOSES ONLY ix CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL x FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL ILLUSTRATIONS Figure Title ILLUSTRATIONS Page Figure Title Page 1-1 Cessna Caravan 208 King................................................................................................. 1-2 24-4 G1000 Overview—Typical Electrical System............................................................... 24-5 1-2 Cessna Caravan 208 G530................................................................................................. 1-3 24-5 1-3 Cessna Caravan 208 G1000............................................................................................... 1-4 Non-G1000 Overview— Typical Electrical System (with Optional Standby Electrical System).......................... 24-6 2-1 ATA 2200 Overview......................................................................................................... 2-2 24-6 Power Distribution Box.................................................................................................. 24-8 2-2 Electrical Symbols............................................................................................................. 2-3 24-7 Electrical Circuit........................................................................................................... 24-10 5-1 Zones Overview................................................................................................................. 5-2 24-8 Standby Alternator Circuit........................................................................................... 24-24 5-2 Lifting and Shoring............................................................................................................ 5-3 24-9 Volt—Ammeter............................................................................................................ 24-26 21-1 Bleed Air Heat................................................................................................................ 21-2 25-1 Pilot and Copilot Seats................................................................................................... 25-2 21-2 Heating System Overview.............................................................................................. 21-3 25-2 ME 406 ELT................................................................................................................... 25-3 21-3 Air Conditioning Components Location........................................................................ 21-4 26-1 Fire Warning Circuit....................................................................................................... 26-2 21-4 Ventilation Blowers........................................................................................................ 21-5 27-1 Aileron Control System.................................................................................................. 27-2 21-5 Vapor Cycle AC Electrical ............................................................................................ 21-6 27-2 Elevator Control System................................................................................................. 27-3 21-6 Bleed Air Heat................................................................................................................ 21-7 27-3 Rudder System................................................................................................................ 27-4 22-1 Garmin GFC 700 Interconnect....................................................................................... 22-2 27-4 Flap Drive System.......................................................................................................... 27-5 22-2 KFC—225 Schematic..................................................................................................... 22-3 27-5 Flap System Components............................................................................................... 27-6 22-3 King KAP 150—3 Axis Autopilot................................................................................. 22-4 27-6 Legacy Series Normal Flap System............................................................................... 27-7 22-4 King KFC 150 —3 Axis Autopilot................................................................................ 22-5 27-7 Legacy Series Standby Flap System............................................................................... 27-8 23-1 208 King Audio Control System.................................................................................... 23-2 27-8 Caravan EX Standby Flap System................................................................................. 27-9 23-2 208 G1000 Audio Panel Controls (GMA 1347)............................................................. 23-3 28-1 Caravan G1000 Fuel System General Overview............................................................ 28-2 23-3 G1000 Communications Block Diagram....................................................................... 23-4 28-2 Non-G1000 Fuel Select and Warning System................................................................ 28-4 23-4 G1000 Navigation/Communication Data Paths............................................................. 23-5 28-3 G1000 Fuel Select and Warning..................................................................................... 28-7 24-1 Electrical Switch Panel and Annunciator Panel............................................................. 24-2 28-4 Fuel Reservoir.............................................................................................................. 28-12 24-2 Power Distribution—Battery Power............................................................................... 24-3 28-5 Auxiliary Fuel Pump.................................................................................................... 28-13 24-3 Power Distribution—External Power............................................................................. 24-4 28-6 Non-G1000 Fuel Quantity Indicating........................................................................... 28-15 28-7 G1000 Fuel Quantity Indicating................................................................................... 28-17 Revision 0 FOR TRAINING PURPOSES ONLY xi CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL ILLUSTRATIONS Figure Title ILLUSTRATIONS Page Figure Title Page 30-1 TKS Ice System Overview............................................................................................. 30-2 61-4 Reversing Propeller Engine Controls (Full Reverse)..................................................... 61-8 30-2 Pneumatic De-Ice System Overview.............................................................................. 30-3 71-1 PT6A Small Turboprop.................................................................................................. 71-2 30-3 Dual Element Windshield Anti-Ice................................................................................ 30-4 71-2 Compressor Bleed Valve—Pre SB 1588........................................................................ 71-4 30-4 Single Element Windshield Anti-Ice.............................................................................. 30-5 71-3 Compressor Bleed Valve—Post SB 1588...................................................................... 71-5 30-5 De-Ice Boot System........................................................................................................ 30-7 71-4 Lubrication System Overview (PT6A-114 & PT6A-114A).......................................... 71-6 30-6 TKS Anti-Ice System with G1000................................................................................. 30-9 71-5 Lubrication System Overview (PT6A-140) .................................................................. 71-8 30-7 Legacy Series Propeller Anti-Ice System..................................................................... 30-10 71-6 Thermostatic Bypass & Check Valve Overview (PT6A-140)....................................... 71-9 30-8 G1000 Prop Anti-Ice System........................................................................................ 30-12 71-7 Oil Filter Components.................................................................................................. 71-10 31-1 Annunciator Panels......................................................................................................... 31-2 71-8 Engine Controls............................................................................................................ 71-11 31-2 G1000 Invalid Display Fields......................................................................................... 31-5 71-9 Fuel Pump Overview.................................................................................................... 71-12 32-1 Main Landing Gear......................................................................................................... 32-2 71-10 Fuel Control Unit—Cross Section (PT6A-114/114A)................................................. 71-13 32-2 Drag Link Spring............................................................................................................ 32-3 71-11 Fuel Control System (PT6A-140)................................................................................ 71-14 34-1 Avionics Systems (King)................................................................................................ 34-2 71-12 Engine Indicating System............................................................................................. 71-16 34-2 Avionics Systems (G530)............................................................................................... 34-3 71-13 Inter Turbine Temperature Indicator............................................................................ 71-17 34-3 Avionics Systems (G1000)............................................................................................. 34-4 71-14 T5 Wiring Diagram...................................................................................................... 71-18 34-4 G1000 MFD Power-Up Page......................................................................................... 34-5 34-5 Garmin G1000 Integrated Avionics Architecture.......................................................... 34-6 34-6 G1000 Flight Instrument Data Paths.............................................................................. 34-7 34-7 G1000 Navigation/Communication Data Paths............................................................. 34-8 35-1 Oxygen System Overview.............................................................................................. 35-2 36-1 Model 208B Vacuum System Overview........................................................................ 36-2 61-1 Hartzell Propeller............................................................................................................ 61-2 61-2 McCauley Propeller........................................................................................................ 61-3 61-3 Propeller Governor......................................................................................................... 61-4 xii FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL TABLES Table Title Page 31-1 Non-G1000 Annunciators.............................................................................................. 31-3 31-2 G1000 CAS Messages.................................................................................................... 31-6 Revision 0 FOR TRAINING PURPOSES ONLY xiii CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CHAPTER 1 INTRODUCTION INTRODUCTION This training manual provides a description of the major airframe and engine systems on the Cessna 208 Caravan aircraft. This information is an instructional aid only; it does not supersede, nor is it meant to substitute for, any of the manufacturer’s maintenance or operating manuals. This material has been prepared from basic design data and all subsequent changes in aircraft appearance or system operation will be covered during academic training and subsequent revisions to this manual. Revision 0 FOR TRAINING PURPOSES ONLY 1-1 01 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL FOR N 30 60 E 120 150 STEER 359 028 059 090 120 148 N 24 21 S FOR S 210 240 W 300 330 STEER 176 207 238 270 302 330 ON A NO 01 MAX RPM TORQUE 1900 1865 1800 1970 1700 1970 1600 1970 ANNUN PANEL LAMP NIGHT FIRE DETECT GENERATOR OFF EMERGENCY POWER LEVER AUX FUEL PUMP ON FUEL PRESS LOW VACUUM LOW RESERVOIR FUEL LOW LEFT FUEL LOW RIGHT FUEL LOW STBY ELEC PWR ON BATTERY OVERHEAT BATTERY HOT CHIP DETECTOR STBY ELEC PWR INOP DOOR WARNING DAY STARTER ENERGIZED IGNITION ON WINDSHIELD ANTI-ICE 5 10 TORQUE 0 FUEL SELECT OFF FT-LB X100 DE-ICE PRESSURE 8 15 20 25 12 16 4 20 0 PROP T.O OFF 3456 12 ITT 7 ¡C x 100 ST.LIM 1090¡ 10 11 RPM X 100 40 Ng %R 20 8 0 9 9 120 60 PSI 40 100 2 6 5 -40 4 4 3 4 0 4 2 E 2 1 E PPHX100 5 0 3 7 2 3 1FUEL FLOW 140 110 55 ¡C 10 OIL 85 80 1 8 F N208FS TEST OIL PRESS LOW OF TEST ENGINE FIRE VOLTAGE LOW BA 5 6 7 8 8 10 6 FUEL 9 12 14 16 QTY 11 4 3 4 2 E 2 1 E GA LLONS X 10 BA SE LBSX100 GAL D ON 6.7 LBS 5 6 7 8 8 10 6 FUEL 9 12 14 16 QTY 11 SE LBSX100 GAL D ON 6.7 LBS AIR S 15 12 --.- NM' - - - KT - - MIN N1 OFF HLD .5 VERTICAL SPEED 1 2 3 6 E ON MIC PITOT/STATIC HEAT 2 S OB TO NAV DH MSG V ENG S 0 CCW 1 2 RADAR ALT X 100 FEET 2 MIN TURN D.C. ELEC. FR D 2:3 1 BFO FRQ CAL SET >CLR AIRSPEED CRSR PULL SCAN ENT ADF FLT ET FLT FRQ ET SET IDT FL 80 140 BRT 1 2 0 0 7 100 0 FEET 1 ALTITUDE 2 29.7 29.8 6 PULL FOR QUICK ER T EC 100 4 5 3 0 0 0 1 9 ON ALT TST V L 8888 ALT ON R GND SBY TST SBY GND W 30 24 R ON ALT OFF PUSH VFR 2 MIN TURN D.C. ELEC. SBY OFF RNG 8 TOTAL HOURS SBY OFF ON TST 0 80 0 0 OFF VFR 888 120 2 1 VOL RST 1200 SBY 9 60 240 40 160 STBY / TIMER BFO 40 KNOTS 200 180 OTH KT 71 TSO VACUUM .5 1 0 .5 1 VERTICAL SPEED FT/MIN X 1000 2 VENT PULL ON 3 2 PUSH XPDR 1 10 A ARM L T SET 3,000 FT RNG VP PULL VS 60 MAP ASSURE THAT SEAT IS LOCKED IN POSITION PRIOR TO TAXI, TAKEOFF, AND LANDING. FAILING TO PROPERLY LATCH SEAT AND HEED THE SAFETY INSTRUCTIONS CAN RESULT IN BOTH INJURY OR DEATH. TRK 20 3 5 WARNING XPDR 2 TRK 40 TEST NAV 4 UP PHONE WARNING DN GAIN PULL STAB OFF FD ALT HDG ALT HDG GS NAV APR BC NAV APR BC KFC 150 FD TRIM TEST ASSURE THAT ALL CONTAMINANTS, INCLUDE WATER, ARE REMOVED FROM FUEL AND ALL SYSTEM BEFORE FLIGHT. FAILURE TO AS???? INSTRUCTIONS AND OWNER ADVISORIES ???? TO FLIGHT CAN RESULT IN BODILY INJURY DEATH. AP MIC AP ENG CABIN STALL HEAT ON DEICE/ANTI-ICE WING W/S LIGHT PROP L FLT PANEL L FLOOD BOOT PRESS AUTO YAW DAMP LOCK R FLT PANEL R FLOOD INERTIAL SEPARATOR BYPASS-PULL NORMAL-PUSH OFF LWR PANEL/ PED/OVHD SW/CKT BKR ALT STATIC AIR PULL ON OFF FPL NRST IDT NAV PULL RAD PULL IDENT DN OFF EXTERNAL POWER ALT NAV KT 79 TSO COMM PULL TEST TEST MANUAL OFF STBY / RAD PULL 25K OFF ACT USE 071 068 USE KX 165 TSO USR KR 87 TSO ADF 117.90 STBY OBS 323 ANT ADF PULL RAD 123.25 NDB STBY / RAD PULL IDENT 128.55 W MSG NAV PULL TEST NDB KLN 89B TSO GPS ¡¡¡¡¡¡¡¡¡¡¡ Alt 1400ft OBS ---¡ Pass Ok? T GPS WAYPOINT RIGHT LDG ON START VOR TIL SLAVE 34.5 nm Baro:30.00" RMI 130¡ ANNUN ON OFF ON CW ARM ACTV R KMA 24 TSD 068 USE Wx WxA L COM 1 COM 2 TEL INT EXT OFF COMM USE LIGHTS BRT BUS ADF AUTO 117.90 STBY UP PHONE MKR MIC 123.25 KX 165 TSO GS NAV FREE BCN DME PULL 25K 24 21 3 FT/MIN X 1000 1 NAV 2 PHONE USE N2 S 1 .5 0 1 COM 2 128.55 29.8 15 GS TEL 3 SEAT BELT SPEAKER HI LO S E N S N NO SMOKE MKR T S T A O M APT 12 24 W 20 15 NAV ON VS 29.7 E HDG GPS APR STROBE TRIM N NAV BATT VOLT OVERSPEED GOVERNOR PUSH TO TEST GA M 33 21 ALT 200 -50 LIGHTS TAXI/ RECOG ON CAP O 33 A D F GEN 150 LEFT LDG 5 ALT GS A 30 NAV A D F 30 4 ENCODING REV APR OFF 25 0 6 3 NAV BC DC 33 N 5 0 7 100 8 100 15 10 VOLTS 20 1005 30 50 IN.Hg AP HDG 7 GS AMPS 2 6 SUCTION IN HG VENT PULL ON 1 ALT 1010 mb FEET S 21 10 20 9 MP H 10 20 8 6 15k 20k 25k 30k 20 10 3 5 4 3 20 10 15 80 140 120 2 MP H 160 30 PROP ANTI-ICE AMPS DH 60 E 12 5 0 100 40 6 6 KNOTS 240 40 H 7 180 MP QUARTZ 3 4 H 10 20 2 MP 0 200 CLOCK E L T RESET MAX WT MANEUVER SPEED 148 KIAS SEE POH FOR OTHER WEIGHTS AIRSPEED 10 9 8 11 12 1 ON A U T O GA LLONS X 10 BATTERY CABIN HEAT AIR CONDITIONING ENG INST RADIO AC FANS AFT HIGH LEFT COOL RIGHT TEMP HOT BLEED AIR HEAT ON MIXING AIR GND-PULL FLT-PUSH AFT CABIN-PULL FWD CABIN-PUSH DEFROST-PULL FWD CABIN-PUSH OFF PARKING BRAKE PULL OFF LOW VENTILATE ON RESET NORM ON OFF TRIP FUEL BOOST GENERATOR ON ON OFF NORM MIC START A/P DISC TRIM INTER OFF STBY PWR TRIM DN CWS TRIM UP MOTOR IGNITION STARTER 1 - ON - 2 Cessna LEFT TURN/ BANK ANNUN PANEL GEN CONT GEN FIELD 5 5 5 5 15 ANNUN PANEL STALL WARN AIR COND CONT T R I M MAP LIGHT LO HI 0705028-3 30 40 10 10 BUS 2 PWR STBY PWR LEFT VENT BLWR RIGHT VENT BLWR 30 40 BUS 1 PWR FIRE DET 30 5 BUS 2 PWR ITT GAGE 30 BUS 1 PWR 5 FUEL TOTAL FUEL FLOW 5 FUEL RIGHT AUX CONT TURN FUEL PUMP HEATER BANK 10 10 5 10 LEFT FUEL QTY OIL TEMP BLEED AIR HEAT AFT VENT BLWR W/S W/S LEFT PITOT ANTI-ICE ANTI-ICE CONT HEAT 5 5 5 RIGHT FUEL QTY AIR SPEED WARN PROP O-SPD TEST 20 5 LEFT STROBE BEACON MAP LIGHT LIGHT LIGHT LDG LIGHT DE-ICE BOOT 5 INST WING LIGHT ICE DET LIGHT 20 15 30 10 5 10 5 5 RIGHT LDG LIGHT TAXI LIGHT NAV LIGHT RADIO FLOOD LIGHT RH ATT GYRO ENC ALTM 30 10 15 10 5 5 2 XPDR 1 10 5 COM/NAV 2 XPDR 2 5 2 5 AVIONICS BUS 2 ADF DME 2 15 T. O. 5 NOSE UP P R O P P O W E R R P M I D L E I D L E N O R M A L F U E L O N C O N D I T I O N M I N UP H I I D G L H E L I OD L WE -20 100 40 -40 C -60 C U T O F F 60 120 140 F 10¡ 1 5 0 20¡ F U L L MAX CAUTION STBY FLAP MOTOR DOWN NORMAL 1 2 5 F L A P S K I A S USE BETA AND REVERSE ONLY WITH ENGINE RUNNING AND PROPELLER OUT OF FEATHER UP AILERON TRIM L R 5 80 20 -20 -40 F E A T H E R B ER TE AV E R S E 60 0 0 1 7 5 STBY FUEL SHUTOFF PULL OFF TORQUE IND SEAT BELT SIGN 30 AVIONICS BUS 1 WX ADF DG RADAR 1 NOSE DOWN RIGHT PROP PROP PITOT ANTI-ICE ANTI-ICE CONT HEAT BUS 2 PWR COM/NAV 1 2 5 15 P O W E R M A X 5 NOSE L RMI AUD/ MKR A/P FD ELEV TRIM 2 5 10 5 RNAV RADIO ALT AVN FAN AUDIO AMP ENGINE FIRE OIL PRESS LOW GENERATOR OFF EMERGENCY POWER LEVER AUX FUEL PUMP ON FUEL PRESS LOW VOLTAGE LOW VACUUM LOW RESERVOIR FUEL LOW LEFT FUEL LOW RIGHT FUEL LOW STBY ELEC PWR ON BATTERY OVERHEAT BATTERY HOT CHIP DETECTOR STBY ELEC PWR INOP DOOR WARNING STARTER ENERGIZED RUD TRIM NOSE R IGNITION ON FUEL SELECT OFF WINDSHIELD ANTI-ICE V E N T FAN/OP EN AN OPEN/F OFF O X Y G E N A I R CLOSE DE-ICE PRESSURE PSI 5 START CONT M A X V E N T A I R MADE IN USA 15 IGN M A X 1000 500 1500 2000 STBY FLAP MOTOR 40 20 E M E R G E N C Y OXYGEN SUPPLY PRESSURE STDBY FLAP PWR MOTOR Caravan I E L E V A T O R 0 BUS 1 PWR Cessna Caravan I OFF AVIONICS USE NO OIL AVIONICS AVIONICS BUS TIE STBY PWR CLOSE ON Cessna YAW GYRO 5 1 1 2 5 5 5 OFF 2 FT LE CABIN HEAT FIREWALL SHUTOFF PULL OFF OFF FUEL TANK SELECTORS ON 165 GAL HT 5 GPS/ LORAN RIG 10 FUEL SEL WARN ON 165 GAL 332 GAL WITH BOTH TANKS ON MAXIMUM FUEL UNBALANCE IN FLIGHT 200 LBS Figure 1-1. Cessna Caravan 208 King 1-2 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL N FOR 30 60 E 120 150 STEER 359 028 059 090 120 148 N 24 21 FOR S 210 240 W 300 330 STEER 176 207 238 270 302 330 AUX FUEL PUMP ON FUEL PRESS LOW LEFT FUEL LOW RIGHT FUEL LOW STBY ELEC PWR ON SPARE SPARE CHIP DETECTOR STBY ELEC PWR INOP DOOR WARNING DAY STARTER ENERGIZED IGNITION ON WINDSHIELD ANTI-ICE 10 15 5 TORQUE 20 0 FUEL SELECT OFF FT-LB X 100 DE-ICE PRESSURE 12 8 16 4 TO 20 0 PROP 25 OFF 12 3456 40 ITT 7 °C X 100 ST.LIM 1090° 10 11 RPM X 100 MAX WT MANEUVER SPEED 148 KIAS SEE POH FOR OTHER WEIGHTS 120 60 Ng 0 9 1 8 6 AIRSPEED DISCONNECT AUTOPILOT AT FIRST INDICATION OF ICE ACCRETION. QUARTZ 3 4 5 160 80 140 120 30 5 SENS TERR TERR INHIB TEST COM1 COM2 COM3 NAV1 COM1 MIC COM2 MIC COM3 MIC COM 1/2 HDG gs TERR N/A TERR INHIB P ALT AP a lt A YD R M DME FT/MIN X 1000 1 FD L HDG CREW A LER T PULL PASS VOL APR REV BATTLE GROUND KSPB 27 D 40 (H)----116.60 BTG PDX VS ALT SEL UP KFC 225 17S 18 9 2S6 KUAO 2 S ––– O M O 240 M DIS ––– 0.0 Trk: GS: 343° 135 kt Pan O M SLAVE GPS WAYPOINT NAV DH MSG 0 CCW 1 RADAR ALT X 100 FEET 2 MIN TURN ELEC CDI PUSH C/V 10 MSG FPL VNAV CLR IDENT ENT VFR Custom Map Info N1 OFF HLD STBY ALT 1 PUSH CRSR 2 ANT ADF 4363 3 4 C COM C PWR 121.900 118.200 VOL/ PUSH SQ V 4 332 BFO FRQ COM TEST 19R 110.30 113.80 VLOC ENR PUSH C/V ––––– 19L DIS DIK 14 KICT GS 2.0 –2 n m overzoom VLOC MSG ––– N M ––– N M 0.0 NAV OBS FPL ADF RNG DPT N VLOC V VOL/ PUSH ID BUS PITOT/STATIC HEAT STALL HEAT ON ON W/S PROP SECONDARY AUTO OFF STARTER OFF OFF L FLT PANEL L FLOOD BOOT PRESS ALT STATIC AIR PULL ON BATTERY ALT HDG ALT HDG GS FL 6 13.5 nm 013 7 20 10 8 10 20 10 20 7 100 FOR QUICK 100 0 FEET ALTITUDE 1 2 29.7 6 5 4 3 29.8 ECT 24 D.C. ELEC. MENU ENT FUNC CRSR START STOP CLR 8 9 L W 21 2 MIN. NO PITCH INFORMATION R VACUUM .5 1 0 .5 1 VERTICAL SPEED FT/MIN X 1000 2 VENT PULL ON 3 2 PUSH D MENU CLR ENT DEFAULT NAV K L ADF 6 : 1 1 FLTET STBY / TIMER BFO FLT FRQ ET SET RST VOL OFF CONTINUED FLIGHT IN ICING CONDITIONS IS PROHIBITED AFTER ENCOUNTERING ONE OR MORE OF THE FOLLOWING: RES VIR APR BC AIRSPEED DECREASE OF 10 KIAS THAT CANNOT BE PREVENTED BY INCREASE TO MAX CONTINUOUS POWER. RES RES PUSH CRSR RNG FD NAV APR BC TEST RNG: 80 TRK:240 GS: 18 KT POS: 0.5SE KICT WICHITA n AP ENG DATA m OVLY WARNING OFF ON INERTIAL SEPARATOR MAP BYPASS-PULL NORMAL-PUSH WX TRFC TERR ASSURE THAT SEAT IS LOCKED IN POSITION PRIOR TO TAXI, TAKEOFF, AND LANDING. FAILURE TO PROPERLY LATCH SEAT AND HEED ALL SAFETY INSTRUCTIONS CAN RESULT IN BODILY INJURY OR DEATH.LLLLLLLLLLLLLLLLLLLLLLLLLL AUX SKYWATCH 0705097-1 ON OFF OPERATION OF THE ANTI-ICE PANEL MAY CAUSE COMPASS DEVIATION OF MORE THAN 10 DEGREES 2605028-2 RADIO AC FANS AFT HIGH LEFT COOL WARNING CABIN HEAT AIR CONDITIONING ENG INST TEMP HOT RIGHT BLEED AIR HEAT ON MIXING AIR GND-PULL FLT-PUSH AFT CABIN-PULL FWD CABIN-PUSH ASSURE THAT ALL CONTAMINATES, INCLUDING WATER, ARE REMOVED FROM FUEL AND FUEL SYSTEM BEFORE FLIGHT. FAILURE TO ASSURE CONTAMINATE FREE FUEL AND HEED ALL SAFETY INSTRUCTIONS AND OWNER ADVISORIES PRIOR TO FLIGHT CAN RESULT IN BODILY INJURY OR D E AT H . L L L L L L L L L L L L L L L L L L L L L L L L L L L L L L L L L L DEFROST-PULL FWD CABIN-PUSH 0705098-1 OFF PARKING BRAKE PULL MIC MEA OR MOCA IF APPLICABLE ON CURRENT LEG FALLS INTO AREA “C” OF ICING SERVICE CEILING CHART CONTAINED IN SECTION 5 OF THE POH/AFM KNOWN ICING EQUIPMENT SUPPLIMENT. 2605070–8 RNG AP TRIM PHONE AIRSPEED OF 120 KIAS CANNOT BE MAINTAINED IN LEVEL FLIGHT. N GPS PROC NAV KFC 150 UP LOCK R FLT PANEL R FLOOD LWR PANEL/ PED/OVHD SW/CKT BKR ON RESET 20 10 PULL OFF MANUAL OFF EXTERNAL POWER FD DN LIGHTS BRT MIC Distance: PRESSURE ALT 5 USE KR 87 TSO GNS 430 N2 CABIN DEICE/ANTI-ICE W/S WING PRIMARY LIGHT 120 OFF ALT ON 80 140 GTX 330 ON 0 GPS PROC --.- NM' - - - KT - - MIN 2 3 5 OBS CDI PHONE 9 60 TURN COORDINATOR DEFAULT NAV K L NAV 40 4S9 Baro: Out KNOTS 240 40 160 MENU GS 72K 10 nm –2 overzoom VLOC 7S9 200 180 FN D TRK 71K KICT ENR VLOC Alt: KC ER 10,300 ft 29.92” In ––– 110.30 113.80 ICT KICT ILS 01R LOC VOLPUSH ID Zoom:(Trk Up) 50 nm RNG DTK VLOC V V COM XTK N 343° 03S S48 5S9 27 117.40 UBG 065°FR 15NM DN ALT NEWBERG AIRSPEED + ON OFF Wpt Bearing: W58 7S3 0 D (H) 9 18 18 W56 40 400 40 PORTLAND 27 11 KVOO 20 59S201W1 D PORTLAND 9 AP KPDX 4S4 (L)---- 114.80 PDX 40 18 KTTD KHIO 17 40 23 COPILOT ARM FT K32 COM C VOL SQ LL O NS X 10 L BS X 100 E D O N 6 .7 LBS /GA L GMX 200 Waypoint: SQ PILOT ICS ISOLATION VOL PA 1.300 A R M NAV 126.700 126.700 PWR PUSH GPS OB ARM ACTV R NAV VLOC 15 3 C W B AS E D O N 6 .7 LB S /GA L CW RIGHT LDG BCN S 2 24 5 6 7 8 8 10 6 FUEL 9 12 14 16 QTY. 11 GA TEST ADF SPKR OFF .5 VERTICAL SPEED 21 L BS X 100 4 2 E 2605070-6 NAV2 CABIN AUDIO R AP 12 15 S 12 E SEAT BELT HI LO YD TERR 4 3 2 1 E LL O NS X 10 33 N NO SMOKE MKR MUTE SQ OFF/ VOL Y STB NAV ON 3 GA GMA 340 A O M 29.8 4 2 E 30 1 .5 0 20 15 STROBE VS N FREE GPS APR OVERSPEED GOVERNOR PUSH TO TEST TRIM 29.7 NAV VOLT LIGHTS TAXI/ RECOG ON 5 GA M 33 NAV BATT GS N 200 W 21 24 ALT 25 -50 LEFT LDG 4 CAP O 30 A D F GEN 150 HDG 33 A D F 30 IN.Hg ENCODING ALT GS KMMV NAV 30 5 0 6 REV A PILOT 1005 7 NAV APR BC DC 8 GS 0 2 AP HDG 7 100 AMPS 15 10 VOLTS 20 1 ALT 1010 mb 100 SUCTION IN HG 50 10 20 8 FEET 6 2 VENT PULL ON 10 20 6 4 15k 20k 25k 30k 3 20 10 3 PROP ANTI-ICE AMPS 20 10 0 100 E 6 60 240 40 9 6 7 180 DH MP H 2 40 3 10 20 CLOCK KNOTS 2 1 E H MP 0 200 H MP 10 9 8 ICE DET P/TEST 11 12 1 5 6 7 8 8 10 6 FUEL 9 12 14 16 QTY. 11 4 3 4 5 BAS AIR ICE DETECTOR SYSTEM IS ADVISORY ONLY PPH X 100 0 4 5 0 -40 3 7 °C 10 PSI 40 100 2 2 1FUEL FLOW3 140 110 55 OIL 85 20 % RPM 80 8 9 15 S EMERGENCY POWER LEVER RESERVOIR FUEL LOW 12 GENERATOR OFF VACUUM LOW MP H N208FS TEST OIL PRESS LOW F OF TEST ENGINE FIRE VOLTAGE LOW E ANNUN PANEL LAMP NIGHT FIRE DETECT MAX RPM TORQUE 1900 1865 1800 1970 1700 1970 1600 1970 BELOW ICING MIN SPD ETM 01 6 ENGINE 120 KIAS MINIMUM IN ICING FLAPS UP EXCEPT 110 KIAS IF CLIMBING TO EXIT ICING. 2605070-5 NO 3 ON A OFF LOW VENTILATE NORM ON OFF TRIP FUEL BOOST GENERATOR MIC ON ON START A/P DISC TRIM INTER TRI DN M CWS OFF OFF NORM STBY PWR TRIM UP MOTOR IGNITION STARTER 1 - ON - 2 Cessna Cessna Caravan I AVIONICS AVIONICS STBY BUS TIE PWR BUS 1 PWR STBY PWR FLAP MOTOR 2605070-9 STBY FLAP MOTOR 40 10 10 STBY PWR LEFT VENT BLWR RIGHT VENT BLWR IGN 5 START CONT 5 LEFT TURN/ BANK 5 AUX FUEL RIGHT FUEL CONT TURN PUMP HEATER BANK 30 40 15 15 10 10 5 BUS 1 PWR FIRE DET FUEL TOTAL LEFT FUEL QTY OIL TEMP BLEED AIR HEAT AFT VENT BLWR 30 5 5 5 5 5 15 BUS 2 PWR ITT GAGE FUEL FLOW RIGHT FUEL QTY AIR SPEED WARN PROP O-SPD TEST DE-ICE BOOT 5 5 5 5 5 5 30 LEFT STROBE BEACON MAP LDG LIGHT LIGHT LIGHT LIGHT 30 10 5 BUS 2 PWR RIGHT LDG LIGHT TAXI LIGHT 30 10 15 COM 1 GPS 1 XPDR 1 5 10 10 A/P COMP 5 5 5 GPS/ LORAN 2 HF XMT 5 AVIONICS BUS 2 A/P DME ALERT 5 5 AVIONICS BUS 2 HF HF XMT RCVR 5 5 15 ANNUN PANEL STALL WARN AIR COND CONT 5 10 15 20 15 SEAT BELT SIGN 5 30 T. O. 5 NOSE UP M A X M A X P R O P P O W E R R P M I D L E I D L E N O R M A L C O N D I T I O N UP H I I D G L H E F U E L O N M I N L I O D L WE 1 7 5 UNLOCK C U T O F F 10° 1 5 0 F E A T H E R B ER TE AV E R S E 20° F U L L MAX CAUTION STBY FLAP MOTOR DOWN NORMAL 1 2 5 F L A P S K I A S UP STBY USE BETA AND REVERSE ONLY WITH ENGINE RUNNING AND PROPELLER OUT OF FEATHER AILERON TRIM R L 20 30 FUEL SHUTOFF PULL OFF SERVO 20 ELEV TRIM 2 5 5 10 SKY WATCH RADIO ALT AVN FAN AUDIO AMP 5 5 5 RADAR TAWS R/T 5 M A X PROP PROP ANTI-ICE ANTI-ICE CONT 5 AUD/ MKR E M E R G E N C Y P O W E R NOSE DOWN 15 RIGHT W/S TORQUE PITOT ANTI-ICE IND HEAT SEC 5 5 T R I M LEFT W/S W/S PITOT ANTI-ICE ANTI-ICE HEAT PRI CONT ENC ALTM MFD E L E V A T O R MAP LIGHT LO HI 0705028-3 RH ATT GYRO RMI GEN FIELD 5 ENGINE FIRE OIL PRESS LOW GENERATOR OFF EMERGENCY POWER LEVER AUX FUEL PUMP ON FUEL PRESS LOW VOLTAGE LOW VACUUM LOW RESERVOIR FUEL LOW LEFT FUEL LOW RIGHT FUEL LOW STBY ELEC PWR ON SPARE SPARE CHIP DETECTOR STBY ELEC PWR INOP DOOR WARNING STARTER ENERGIZED NOSE L IGNITION ON RUD TRIM NOSE R FAN/OP EN 1000 500 1500 2000 0 O X Y G E N USE NO OIL V E N T A I R PSI OXYGEN SUPPLY PRESSURE MADE IN USA 15 CLOSE ON DE-ICE PRESSURE OFF Cessna STM SCP N OPEN/FA OFF A I R CLOSE FUEL SELECT OFF WINDSHIELD ANTI-ICE V E N T FT LE OFF FUEL TANK SELECTORS HT HSI 2 5 5 GEN CONT RIG 5 GPS 2 2 15 AVIONICS BUS 1 ADF HSI 1 1 5 1 5 ICE RADIO NAV LIGHT DETECTOR FLOOD LIGHT COM 2 FUEL SEL WARN 2 INST WING LIGHT ICE DET LIGHT ANNUN PANEL WING FLAPS 30 BUS 2 PWR BUS 1 PWR Caravan I DO NOT TAKEOFF WITH ICE/FROST/SNOW ON THE AIRCRAFT. OFF AVIONICS CABIN HEAT FIREWALL SHUTOFF PULL OFF ON 165 GAL ON 165 GAL 5 332 GAL WITH BOTH TANKS ON MAXIMUM FUEL UNBALANCE IN FLIGHT 200 LBS Figure 1-2. Cessna Caravan 208 G530 Revision 0 FOR TRAINING PURPOSES ONLY 1-3 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL 30 33 N 01 HDG 20 10 130 30 CABIN 33 N 21 ?????? INSET S OAT__– 5°c 37.9NM EHF NAV1 SENSOR PFD OBS 15 BACKUP ON CDI DME FRAME 324° 73.2NM 334° 10.0NM KFAT R LCL NRST 08:44:27 ALERTS OFF FPL PROC CLR ENT DFLT MAP PFD 1 XPDR 1 ADF 1 5 5 5 2 A/P SERVOS A/P CONT ELT NAV INTFC RADIO ALT RADAR R/T 5 5 5 5 5 5 COM 2 NAV 2 MFD ADC 2 AHRS 2 PFD 2 XPDR 2 5 5 5 5 5 5 AVN BUS 1 AUDIO TEST SWITCH FIRE DETECT–UP FUEL SELECT OFF–DN PHONE PASS FMS 2605070-10 TAS XM–DATA LINK STM SCOPE HF RCVR HF AMP 5 5 5 5 5 30 V107 1900 KRFL KSMX 95 85 V27 GMN 379 BAT AMPS BUS VOLTS 4 28.5 A–ICE GAL 4.7 V107 V137 V22 AVIONICS MAP WPT AUX NRST TERRAIN AIRWY LO STRMSCP NEXRAD XM LTNG PARKING BRAKE PULL D MENU FPL PROC CLR ENT DFLT MAP BACK 10 10200 10100 HDG 328° 33 GPS CRS OAT__– 5°c FMS ?????? INSET 331° N ENR OBS CDI 0 5 1 0 0 1 PUSH 1-2 ON BARO -900 ARM PUSH STD 9700 29.92IN 1 10 ARTEX ELT 1 9800 328° 30 37.9NM EHF NAV1 SENSOR PFD 9900 10 80 PUSH VOL SQ COM EMERG 2 2 TEST/RESET PRESS ON WAIT 1 SECOND PRESS ARM RANGE – + PUSH PAN D DME FPL 50.0NM FLW NAV2 XPDR XPDR1 IDENT 4234 ALT TMR/REF R LCL NRST 08:44:27 ALERTS MENU PROC CLR DFLT MAP ENT FMS SQ PUSH CRSR TEMP °C 30+ 0 –30 100 40 200 PRESS ALT 180 AIRSPEED 60 160 80 140 KNOTS 120 100 8 9 7 6 PUSH CRSR 1 4 5 VENT–PULL ON HF FEET 0 ALTIMETER 1015 1010 VACUUM 1 2 3 10 E 15 5 TORQUE 29.8 29.9 30.0 20 0 FT–LB X 100 EMER T.O. VOL 25 PUSH PWR 5.000 R 1 TEST FUNC FREQ CHAN MOD RX PHONE TUNE ENT TX SQL OPT MIC LOCK 332 ADF INERTIAL SEPARATOR KR 87 TSO BYPASS–PULL NORMAL–PUSH BENDIX / KING CB/PED/ OVHD LEFT FLOOD 3:10 USE ADF WARNING ADF FLT ASSURE THAT ALL CONTAMINATES, INCLUDING WATER, ARE REMOVED FROM FUEL AND FUEL SYSTEM BEFORE FLIGHT. FAILURE TO ASSURE CONTAMINATE FREE FUEL AND HEED ALL SAFETY INSTRUCTIONS AND OWNER ADVISORIES PRIOR TO FLIGHT CAN RESULT IN BODILY INJURY OR DEATH.LLLLLLLLLLLLLLLLLLLLLLLLLLLLLLLLLL 07 050 98 -1 STBY/TIMER BFO FRQ FLT ET SET RST AIR CONDITIONING RIGHT FLOOD COOL ALTSTATIC AIR PULL ON 150NM V197 V23 DISPLAY BACKUP DIMMING SW/CB PNLS / ANNUN STANDBY IND KVCV V386 XWHP V107 XBUR V107 TOPO V12 V201 KCMA KNTD 10 10 PUSH KPMD 127.100 COM1 122.450 COM2 128.375 121.500 20 PAN KWJP V27 316 + KEDW V12 KSBA V25 V186 – KMHV FUEL QTY LBS R FFLOW PPH 120 331° 310000 100 130 PUSH STD V23 V137 V183 BRG 150 RANGE V25 20 145 L KNID 20 140 V459 KVBC 1-2 V165 EHF DIS 38.0NM EHF AP YD ALT 10000FT 10 000 10300 160 PUSH 1-2 BARO V485 0 AVN BUS 2 DME KSBP GMN GPS 115.40 EHF 117.80 FLW NAV PUSH KDLO V113 V27 NAV1 116.90 NAV2 112.50 PUSH VOL ID COM KPTV V23 16 CONTINUED FLIGHT IN ICING CONDITIONS IS PROHIBITED AFTER ENCOUNTERING ONE OR MORE OF THE FOLLOWING: AIRSPEED OF 120 KIAS CANNOT BE MAINTAINED IN LEVEL FLIGHT. AIRSPEED DECREASE OF 10 KIAS THAT CANNOT BE PREVENTED BY INCREASE TO MAX CONTINUOUS POWER. MEA OR MOCA IF APPLICABLE ON CURRENT LEG FALLS INTO AREA”C” OF ICING SERVICE CEILING CHART CONTAINED IN SECTION 5 OF THE POH/ AFM KNOWN ICING EQUIPMENT SUPPLEMENT. PUSH VOL SQ TRACK UP 170 2 141618 ADF 2 10KT V165 V459 R 96.5 TRAFFIC 180 AHRS 1 5 700 O F F COPLT 127.100 COM1 122.450 COM2 128.375 121.500 DIS 38 KVISV459 24CL TAS ADC 1 5 900 PLAY PILOT KHJO V137 KPRB 100 OIL °C 200 ENG INTFC 5 PROP RPM ICS ISOLATION PUSH CRSR NAV 1 12 % RPM CREW PILOT THE SIGHT GAGE ON THE TKS TANK IS THE ONLY APPROVED MEANS OF ASSURING ADEQUATE DISPATCH FLUID QTY COM 1 °C L MAN SQ MENU GS 175 600 50 NAV2 VOL 700026 MIC PUSH 331° MAP - NAVIGATION MAP EMERG 1650 0 AUX 38.0NM DTK C80 V248 ITT 1-2 NAV1 ADF PAN D 331° 4234 ALT HI SENS + DTK DIS – – –° – – – –NM TMR/REF SPKR ETE 13:47 N 20 OIL PSI – EHF XPDR1 TEL PA MKR MUTE 115.40 EHF 117.80 FLW 15 FT–LB X100 10 0 COM 1/2 DME RANGE KLGB / KFAT VENT–PULL ON OVERSPEED GOVERNOR PUSH TO TEST 2 116.90 112.50 NAV Ng PUSH STD GMN IDENT NAV 1 NAV 2 TRQ PUSH VOL ID PUSH 1-2 V23.FRAME 50.0NM FLW NAV2 XPDR COM3 PUSH BARO -900 FLIGHT PLAN 12 OFF FLUID CONTROL MAX FLOW AIRFRAME N O R M WINDSHIELD COM2 COM3 MIC E PRIMARY HIGH COM1 COM2 MIC 6 24 ENR 1 1 9700 29.92IN E ANTI-ICE 331° 2 COM1 MIC PUSH DIR 3 GPS CRS 6 MANUAL WINDSHIELD ANTI-ICE MUST BE OFF FOR TAKEOFF AND LANDING 328° 80 9800 3 SEAT BELT ON HDG 9900 10 328° W NO SMOKE WING LIGHT 10100 3100 00 100 O F F STALL HEAT ON 10 PUSH VOL SQ COM EMERG PUSH DIR EMERGENCY USE ONLY 10 140 120 127.100 COM1 122.450 COM2 128.375 121.500 2605076-5 C R E W 331° 10200 150 BCN CRS2 SPD W NAV ON FLC DN 24 160 20 VS VNV 21 20 145 STROBE PROP HEAT AUTO P/S HEAT / LOW A/S AWARE BRG ALT ALT SEL YD UP PUSH SYNC 10 000 10300 170 1-2 OFF DIS 38.0NM EHF AP YD ALT 10000FT XFR AP S RIGHT LDG PUSH POWER OUTLET ALL GMN GPS 115.40 EHF 117.80 FLW NAV FD BANK 15 LEFT LDG NAV1 116.90 NAV2 112.50 PUSH VOL ID NAV CRS1 BC 12 N208FS LIGHTS TAXI/ RECOG ON APR HDG BELOW ICING MIN SPD WHEN TAKEOFF TORQUE SETTINGS ARE BELOW 1865 FT-LBS, THE AIR CONDITIONER MUST BE OFF FOR TAKEOFF AND LANDING 2605031-3 MAX WT MANEUVERING SPEED 148 KIAS SEE POH OTHER WEIGHTS LEFT AC FANS AFT HIGH RIGHT OFF VOL TEMP HOT BLEED AIR HEAT ON WARNING ASSURE THAT SEAT IS LOCKED IN POSITION PRIOR TO TAXI, TAKEOFF, AND LANDING. FAILURE TO PROPERLY LATCH SEAT AND HEED ALL SAFETY INSTRUCTIONS CAN RESULT IN BODILY INJURY OR DEATH.LLLLLLLLLLLLLLLLLLLLLLLLLL 07 050 97 -1 CABIN HEAT MIXING AIR AFT CABIN–PULL GND–PULL FWD CABIN–PUSH FLT–PUSH DEFROST–PULL FWD CABIN–PUSH OFF DAY VENTILATE OFF LOW DO NOT TAKEOFF WITH ICE/FROST/SNOW ON THE AIRCRAFT. 2605070-9 M TRI DN M TRI UP WING FLAPS Caravan ON BUS STARTER OFF OFF RESET EXTERNAL POWER NORM OFF TRIP NORM PRI ANTI– ICE TORQUE IGN START CONT GEN CONT 30 5 5 5 5 5 GEN FIELD 15 BUS 2 PWR STBY PWR RIGHT PITOT HEAT PROP ANTI–ICE CONT BACKUP ANTI– ICE W/S ANTI–ICE AUX 12V DC PWR LEFT FUEL QTY AUX FUEL PUMP FUEL SEL WARN 40 15 5 5 2 10 5 10 RDNG LIGHT INST LIGHT LEFT LDG LIGHT STROBE LIGHT BEACON LIGHT WING ICE DET LIGHT RIGHT FUEL QTY F FLOW NG & NP STARTER 30 7 5 10 5 10 5 5 2 10 2 BUS 2 PWR SEAT BELT SIGN AVN FLOOD LIGHT RIGHT LDG LIGHT TAXI LIGHT NAV LIGHT FIRE DET PROP O-SPD TEST AIR COND CONT DECK SKIN FAN 30 5 5 10 15 10 MOTOR IGNITION 1 ON OFF AVIONICS AVIONICS AVIONICS BUS TIE STBY PWR PROP ANTI– ICE 15 30 FUEL BOOST START OFF STBY ALT PWR LEFT PITOT HEAT 40 BUS 1 PWR GENERATOR ON OFF STBY PWR 30 BATTERY ON ON ON BUS 1 PWR Caravan BUS 1 PWR 30 7 5 10 5 BUS 2 PWR 30 7 5 10 5 FUEL CONT HEATER 5 5 5 5 FLAP MOTOR AIR SPEED WARN AFT VENT BLWR LEFT VENT BLWR 10 5 10 10 STBY FLAP MOTOR STALL WARN BLEED AIR HEAT RIGHT VENT BLWR 10 10 5 10 AUX AUDIO IN Figure 1-3. Cessna Caravan 208 G1000 1-4 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CHAPTER 2 ATA 2200 02 INTRODUCTION This chapter describes the arrangement, numbering system, and special features of the Air Transport Association (ATA 2200) format for aircraft technical publications. To take advantage of all the material presented in an ATA 2200 format manual, the maintenance technician must become thoroughly familiar with the outline and contents presented. The ATA 2200 format is a standard for the presentation of information that includes section numbering, chapter numbering, and page numbering for maintenance manuals, parts catalogs, wiring diagram manuals, avionics installation manuals and structural repair manuals. MAINTENANCE PUBLICATIONS The Cessna Caravan I Maintenance Manual, Illustrated Parts Catalog, Wiring Diagram Manual, and Structural Repair Manual are prepared in accordance with the Air Transport Association Specification for manufacturers’ technical data. These manuals assist maintenance perRevision 0 FOR TRAINING PURPOSES ONLY sonnel in servicing and maintaining Caravan I aircraft. They provide the necessary information to service, inspect, troubleshoot, remove and replace components, and repair systems. 2-1 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL WIRE IDENTIFICATION EQUIPMENT LIST The wiring diagrams in the 208 manual do not show the wire number for each wire; however, the wires in the aircraft have wire numbers as shown in the following example: All electrical and electronic equipment used in the wiring diagrams are identif ied by an alphanumeric reference designator. This reference designator is used as a cross-reference symbol to the equipment list where the part number, part description, zone, and five -digit Federal Supply Code are given. Manufacturer’s names and addresses that correspond with the Federal Supply Code may be found in the Introduction. 02 / * B JT007-PA002 (24) (SP 2-B) Color of Wire Numerical Sequence** TP—Twisted Pair TT—Twisted Triple SS—Single Conductor Shielded SP—Shielded Pair ST—Shielded Triple CX—Coax Wire Size Connector (or Other Component) Connector Pin Connector (or Other Component) Connector Pin Connector Pin Following is Lower Case Indicates Wire is Spliced with Other Wires within 3 Inches of Component Figure 2-1. Wire identification ** A numerical sequence for each type of wire (SP1, SP2, SP3; ST1, ST2, ST3) on a diagram page. May be used to identify wires within a shield or twisted group when they are not drawn adjacent and enclosed by a twisted or shielded symbol. Example: SP2-B and SP2-W are the two wires within a shield. Reference designators consist of two letters followed by three numbers. A reference designator assigned by this method provides information about where a component is located in the aircraft. The following list shows the categories assigned to basic equipment designator letters: COLUMN A EQUIPMENT LIST Splice .................................................................................... A%### Controller ............................................................................. B%### Capacitor .............................................................................. C%### Diode .................................................................................... D%### Instrument ............................................................................ E%### Light ...................................................................................... F%### Ground.................................................................................. G%### CB/Fuse/Bus Bar ................................................................ H%### Receptacle ............................................................................. J%### Relay ..................................................................................... K%### Inductor ................................................................................ L%### Servo/Motor ........................................................................ M%### Printed CKT BD.................................................................. N%### Plug........................................................................................ P%### Transistor ............................................................................. Q%### Resistor................................................................................. R%### Switch ................................................................................... S%### Thermal................................................................................. T%### Element Unit/Module ........................................................ U%### Valve ..................................................................................... V%### Solenoid .............................................................................. W%### JCT/Terminal BD................................................................ X%### Cessna Assembly ................................................................. Z%### COLUMN B LOCATION IN AIRCRAFT Aft Bulkhead......................................................................... *A### FWD Fuselage Bulkhead .................................................... *B### Fuselage (Cabin)—LH ........................................................ *C### LH Engine (Nacelle) ........................................................... *D### RH Engine (Nacelle)............................................................ *E### Fuselage (Cabin)—RH ........................................................ *F### Landing Gear ........................................................................ *G### Horizontal Stabilizer ........................................................... *H### Instrument Panel .................................................................... *I### Aft Baggage Area ................................................................. *K### LH Wing ................................................................................. *L### LH Wing Feedthrough ........................................................ *M### Forward Nose ........................................................................ *N### RH Wing ................................................................................ *R### RH Wing Feedthrough ......................................................... *S### Tail Cone................................................................................ *T### Vertical Stabilizer ................................................................ *V### **Insertion Cable ..................................................................... *X### Fuselage Fairing ................................................................... *Y### Inside Cessna Assembly ...................................................... *Z### Code: %—Letter from Column B *—Letter from Column A #—0, 1, 2, 3, 4, 5, 6, 7, 8, or 9 (001–299 to be used for electrical diagrams; 300–999 to be used for avionics diagrams) Examples: PB105 Forward Bulkhead Plug EI302 Instrument in Instrument Panel **Def inition: Insertion Cable—A cable which originates from optional equipment and plugs into a break in a standard cable, and will have an “XX” reference designator as indicated above. The reference designator codes for a bulkhead feedthrough receptacle and its attaching plugs contain the same numeric value. For example: JS140—Receptacle, RH Wing Feedthrough PR140—Plug in RH Wing PF140—Plug in RH Cabin Figure 2-1. ATA 2200 Overview 2-2 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL + BATTERY – DIODE REGULAR—Low resistance forward, high resistance reverse. IN OUT WHT ZENER—Low resistance forward, high resistance reverse until a specific voltage is applied, then conducts freely. BUS TRANSORB—A transorb is similar to a zener, but with higher peak current limit. CAP AND STOW VARISTOR—High resistance either way until a specific voltage is applied, then conducts freely. Example: V47ZA1 conducts freely above 47 volts. CAPACITOR CIRCUIT BREAKER VARISTOR—Encapsulated for moisture protection. IN OUT IN OUT + IN OUT FILTER Passes direct current but opposes pulsating current; used to reduce noise in sensitive avionics equipment. The switch contacts connect to an annunciator system to warn when a circuit breaker is open. 28V LOAD CURRENT A1 SENSOR MOT OR GATE—Output is low until either or both inputs are high, then output is high. FUSE/LIMITER NOR GATE—Output is high until either or both inputs are high, then output is low. INVERTER—Output is low when input is high, output is high when input is low. OPERATIONAL AMPLIFIER (OP AMP)— Amplifies the difference in voltage between the two inputs. The minus input is the inverting input, and the plus is the noninverting input. If an input is applied to the minus input, with the plus input grounded, the polarity of the output will be opposite to the input. If an input is applied to the plus input, with the minus input grounded, the polarity of the output will be the same as that of the input. MOT WHT HI LOW GROUND RELAY CURRENT FLOW WITH POWER APPLIED HEADSET HEATER CONNECTOR INTEGRATED CIRCUIT MOTOR HORN/SPEAKER Integrated circuits do not necessarily work on the principle of ON–OFF as a switch; instead some work on high and low voltage. Example: high might be 5.0 volts and low might be 0.5 volts. IN OUT RED AND GATE—Output is low until both inputs are high, then the output is high. IN OUT NAND GATE—Output is high until both inputs are high, then the output is low. REVERSIBLE MOTOR—Direction of rotation is controlled by reversing power and ground on input wires. BLK CW CURRENT TRANSFORMER Current flowing in wire produces a voltage in coil. MOT P M MOT CURRENT SENSOR Current flowing in coil opens switch to indicate circuit is functioning correctly. M Basic symbol for motor. The black circle indicates contact will accept 16 gage wire. A black triangle indicates contact will accept 12 gage wire. Unmarked contacts accept 20 gage wire. CURRENT FLOW THE INSTANT POWER IS REMOVED A diode is connected across the input wires of relays and solenoid-operated devices, such as valves, to protect voltage sensitive navigation and electronics equipment. The diode is reverse-biased for normal power and no current flows through the diode. Current flowing through the coil of wire produces a magnetic field to operate the relay or valve. The instant power is removed from the coil, the collapsing magnetic field produces a momentary spike of high voltage which can be several hundred volts, depending on the current and the number of turns of wire in the coil. The diode is forwardbiased for the power generated in the coil and the high voltage spike is dissipated through the diode. A varistor is used in place of the diode on some relays. CONTROL SWITCH (RELAY) Remote circuit breakers combine the functions of circuit breaker and relay. A 1 amp or 0.5 amp circuit breaker is used at pilot’s circuit breaker panel to indicate an overload and can be opened by the pilot to disable the system. Remote circuit breakers have a visual indicator to the right of the connector. OPEN and CLOSED labels on red and green backgrounds indicate the position of relay contacts. The symbol for the solenoid may be a box or a coil, the operation is identical. + – LAMP LOGIC 3 02 NONREVERSIBLE MOTOR—Two-speed controlled by applying power to either input wire. PHONE JACK TIMER—Changes the output from high to low in a regular pattern. A2 NONREVERSIBLE MOTOR—Direction of rotation is controlled by design; input wires may be connected either way. MOT CCW REVERSIBLE MOTOR—Direction of rotation is controlled by applying power to either field winding input wire. 28 DVC ANNUNCIATOR LOAD An annunciator relay has a connection on the material contact to indicate by a light or annunciator panel when the relay is energized. Figure 2-2. Electrical Symbols (Sheet 1 of 2) Revision 0 FOR TRAINING PURPOSES ONLY 2-3 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL RELAY (Cont.) The contacts of a time delay relay do not move to the energized position usually when power is applied. TIME DELAY 02 7 3 Jumper wire gives 0.1 seconds of delay. 6 1 2C 4 This symbol with no sp reference designator is a permanent splice; when identified with an sp reference designator, it is an environmental disconnect splice. 1C 2C 3C ENVIRONMENTAL DISCONNECT 4C SWITCH VARIABLE OR ADJUSTABLE— Resistance changes with mechanical input. RHEOSTAT—Type of variable resistor with two wires. POTENTIOMETER—Type of variable resistor with three wires. SOLENOID/SOLENOID VALVE NO (normally open) or NC (normally closed) by a solenoid-operated valve indicates the position of the valve with no power applied to the solenoid. E CLOSED F B CLOSE B CLOSE D CLOSED M E MOTOR F ANNUNCIATOR (MOTOR ON) A OPEN C OPENED SHOWN OPEN G MOTOR A OPEN C OPENED D SHOWN OPEN MOTOR-OPERATED—Limit switches stop power when limit of travel is reached. C OPPOSITE SINGLE-POLE/SINGLE-THROW (SPST) SINGLE-POLE/DOUBLE-THROW (SPDT)— May have OFF position in the center. DOUBLE-POLE/DOUBLE-THROW (DPDT)— May have OFF position in the center. Dashed line indicates all parts move simultaneously. E D E C K A D E C K B 4NO Handle position is reference to the flat side of the mounting threads. E PNP NOTE: Some switches of this type do not have a center position. COLLECTOR BASE EMITTER 1C 2C 3C 5C TWO-POLE ROTARY—On rotary or multipole switches controlled by a knob, the poles (or decks) are identified on wiring diagrams as A, B, C, with A being the part on the knob or shaft end. B 2NC 3NC 3NO 4NC C TO FLAT 1NC 2NO 4-POLE 4C ROTARY OR MULTI-POSITION 1NO 6C 1NO 1NC 2NO 2NC 3NO 3NC 4NC 4NO 5NC 5NO 6NC 6NO Contact 1 of 2-pole Contacts 1 and 2 of 4-pole Contacts 1, 2, and 3 of 6-pole Contact 2 of 2-pole Contacts 3 and 4 of 4-pole Contacts 4, 5, and 6 of 6-pole TO FLAT CENTER* NO NO C C NC C NC C NO NC NO CONTROL SIGNAL MAIN CURRENT FLOW OPPOSITE C NC C IS THE COMMON TERMINAL NC IS THE NORMALLY CLOSED TERMINAL NO IS THE NORMALLY OPEN TERMINAL NO C B DARLINGTON NC C E NC NO WIRE 6-POLE TWISTED PRESSURE-OPERATED D E C K C SHIELDED C C C 1 1 1 2 2 2 2 3 3 3 3 1 10 9 TEMPERATURE-OPERATED 8 GRAYHILL M Transistor contacts are identified as base, collector and emitter. Flow of current through a transistor is controlled by the signal applied to the base. The control current (3–5% of total current) flows between base and emitter. The main flow of current (95–97%) is between the collector and emitter. Transistors may be drawn without the circle. CENTER (NOTE) ENVIRONMENTAL TEMPERATURE-CONTROLLED— Resistance changes with the temperature. TRANSISTOR B 2NO SPLICE EXTERNAL RESISTOR REGULAR—Resistance does not change. 1NC 2NC TWO-STAGE—Two-pole, four-pole or sixpole switch designed so that all moveable switch contacts do not move simultaneously. NPN Other resistors give a delay time between 0.1 second and 10 seconds. RESISTOR 1NO 2-POLE 160,000 OHM resistor gives a 10-second delay. TIME A DELAY 2 5 B 1C For some time delay relays, the delay time is part of the relay design. For some time delay relays, the delay time is controlled by the size of an external resistor. 9 SHUNT SIDE VIEW WITH TYPICAL TERMINAL NUMBERING 4 5 6 Q12A20 7 REAR VIEW HIGH-TEMPERATURE WIRE TERMINAL STRIP C = Common terminal for each deck 1—10 = Switch terminal position EXAMPLE: AC = Common terminal of deck A B1 = Switch position 1 on deck B TRANSFORMER Figure 2-2. Electrical Symbols (Sheet 2 of 2) 2-4 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CHAPTER 5-12 AIRCRAFT GENERAL 5-12 INTRODUCTION This chapter presents information pertaining to Chapters 5 through 12 of the Model 208 and 208B Airplane Maintenance Manuals (AMMs). It is meant to be an overview or guide to the information found in these chapters and not a specific source. References for this chapter and further specific information can be found in Chapter 5—“Time Limits/Maintenance Checks,”Chapter 6—“Dimensions and Areas,” Chapter 7—“Lifting and Shoring,” Chapter 8—“Leveling and Weighing,” Chapter 9—“Towing and Taxiing,” Chapter 10—“Parking and Mooring,”and Chapter 12—“Servicing” of the AMMs. GENERAL ORGANIZATION The Cessna 208 can be either a Caravan I or Cargomaster. Cessna 208B is a Caravan I, Super Cargomaster, or a Grand Caravan. The basic airframe difference between the 208 and 208B is the length of the fuselage; 208B is a lengthened version. This is ­immediately visible in the distance between the windshield and the wing leading edge also the length of the fuselage. The aircraft has a fuselage of conventional formed sheet metal bulkhead, stringer, and skin (semi-monocoque). The wings, which are externally braced, contain integral fuel tanks. The aircraft is all metal, high-wing, single-­engine aircraft with fixed tricycle spring steel landing gear. The Amphibian model has ­retractable dual/main landing gear. The nose gear f­ eatures a full castering nose wheel mounted on a composite nose spring, which retracts into the float nose to provide a dock bumper. The empennage has conventional vertical s­ tabilizer, rudder, horizontal stabilizer, and e­ levator. Each elevator has trim tabs. Revision 0 The aircraft has ailerons and Fowler type flaps. The left aileron incorporates a servo tab while the right aileron incorporates a trim-able servo tab. FOR TRAINING PURPOSES ONLY The engine is either PT6A-114 (600 HP), PT6A-114A (675 HP), or PT6A140 (867 HP). Propellers are Hartzell or McCauley with three blades. Cessna 208 Cargomaster has no passenger door or passenger windows. Cessna 208B Super Cargomaster has a lengthened fuselage. Cessna 208B Grand Caravan has windows installed with a passenger door at the rear of the fuselage. 5-1 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 110 211 (212) 215 (216) 231 (232) 251 (252) 213 (214) 217 (218) 233 (234) 801 (802) 255 (256) 311 (312) 5-12 130 253 (254) 257 (258) 803 (804) 320 330 MODEL 208 FUSELAGE ZONES 110 130 211 (212) 215 (216) 231 (232) 251 (252) 213 (214) 217 (218) 233 (234) 801 (802) 255 (256) 253 (254) 257 (258) 311 (312) 803 (804) 320 330 MODEL 208B FUSELAGE ZONES 240 243 242 244 122 121 MODEL 208B TOP DOWN VIEW 241 Figure 5-1. Zones Overview 5-2 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES JACK POINT ASSEMBLY TAIL JACK STAND TAIL TIE-DOWN HYDRAULIC MAIN/NOSE JACK 5-12 JACK CAP FS 100.00 FS 207.44 A JACK CAP B HYDRAULIC MAIN/NOSE JACK HYDRAULIC MAIN/NOSE JACK RBL 23.77 LBL 23.77 .125” LANDING GEAR TRUNNION BEARING CAP MAIN LANDING GEAR INTEGRAL JACK PAD 1.00” JACK BRAKE ASSEMBLY DETAIL B DETAIL A Figure 5-2. Lifting and Shoring Revision 0 FOR TRAINING PURPOSES ONLY 5-3 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 5-12 5-4 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CHAPTER 20 STANDARD PRACTICES 20 INTRODUCTION Maintenance practices unique to a particular system or subject are described in the appropriate ATA chapter in the manufacturer’s maintenance manual. Standard maintenance practices, however, for maintaining and repairing items of the airframe and systems are discussed in Chapter 20. The chapter contains sections on airframe hardware, electrical/electronic practices, and solvents, sealants, and adhesives. Conversion data is also provided. GENERAL This chapter is divided into sections. A short description of each section is given below. Refer to the Table of Contents at the start of this chapter to find an applicable maintenance practice concept or subject. The section on Airplane and Systems Hardware gives the maintenance procedures for the items that follow: • Tubing, hoses, and fittings • Tube bending criteria • Non-flare fittings and nylon tubing • Packing and backup rings • Safetying • Control cables, seals, and pulleys Revision 0 FOR TRAINING PURPOSES ONLY • Rivetless nutplates • Torque data for bolts, screws, nuts, and fittings The section on Electric/Electronic Practices gives data for electrical examination and requirements for installation and repair of electrical wiring and interconnecting hardware components, wire bundle repair, and electrical bonding. The section on Solvents, Sealants, and Adhesives gives the description and uses for the items that follow: • Solvents and cleaners • Fuel, weather, pressure, and high temperature sealing • Application of adhesives and solvent bonding 20-1 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 20 20-2 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CHAPTER 21 AIR CONDITIONING 21 INTRODUCTION This chapter provides a description of the heating, ventilation, and air conditioning systems. For each system, emphasis is on component location and system operation. References for this chapter and further specific information are available in the Manufacturer’s Maintenance Manual under the following chapters: 36 Pneumatics, 21 Air Conditioning, 5 Time Limits/Maintenance Checks, and 12 Servicing. GENERAL The environmental system consists of heating, defrosting, ventilation, and the vapor cycle air conditioning subsystems and the ducts associated with each system. The environmental system is identical for all 208 series aircraft except for the following: Air Distribution System The environmental subsystems regulate the temperature and volume of airflow to the cabin. Each system uses separate plenums and ducts. • Model 208 and 208B passenger ventilation systems include wemac valves, ducts, and plenums for pilot, copilot, and each passenger seat position. For cockpit ventilation, ram air is ducted from each side of the aircraft just aft of the firewall to outlets on the left and right sides of the instrument panel. Push-pull control knobs are above each outlet. • Model 208B cargo ventilation systems include wemac valves and plenums for pilot and copilot seat positions only. Defroster nozzles are on each side of the glareshield below the windshield. Revision 0 FOR TRAINING PURPOSES ONLY For cabin ventilation, all aircraft are equipped with a fresh air vent system mounted in the wing and cabin overhead. The 208 and 208B passenger models may have optional blower fans upstream of the plenum. These are used during ground operations to provide a more comfortable cabin environment. If desired, the blower fans may be operated during flight. 21-1 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES LEGEND HIGH PRESSURE BLEED AIR P3 AIR P2.5 AIR LOW PRESSURE BLEED AIR REGULATED BLEED AIR SUCTION/VACUUM CABIN AIR VACUUM EJECTOR HEATING AIR CONDITION: IN FLIGHT FLOW CONTROL VALVE PRESSURE REGULATOR 21 DE-ICE AIR SOURCE MIXING AIR VALVE - FLT CONTROL PANEL MIXER / MUFFLER TEMP LIMIT SWITCH FIREWALL SHUTOFF VALVES SAFETY SWITCH COCKPIT OUTLETS CABIN OUTLETS Figure 21-1. Bleed Air Heat 21-2 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL P3 AIR FLOW CONTROL VALVE NOTES MIXER / MUFFLER P2.5 AIR FIREWALL SHUTOFF VALVE CONTROL (2) MIXING AIR VALVE CABIN HEAT SELECTOR VALVE VENTILATING AIR DOOR (ONE EACH SIDE) DEFROST AIR / FORWARD CABIN AIR SELECTOR VALVE DEFROSTER OUTLETS (2 EA) INSTRUMENT PANEL VENTILATING OUTLETS AND CONTROLS (2) 21 ADJUSTABLE PILOT AND FRONT PASSENGER OVERHEAD VENTILATING OUTLETS (2 EA) VENTILATING AIR INLET IN UPPER WING STRUT FAIRING (2) VENT AIR CONTROL ON OVERHEAD CONSOLE VENT AIR CONTROL ON OVERHEAD CONSOLE SHUTOFF VALVE SHUTOFF VALVE HEATER OUTLETS 2 ON EACH CABIN SIDEWALL AT FLOOR LEVEL ADJUSTABLE REAR PASSENGER OVERHEAD VENTILATING OUTLETS (8) LEGEND HEATED AIR VENTILATION AIR Figure 21-2. Heating System Overview Revision 0 FOR TRAINING PURPOSES ONLY 21-3 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES AFT EVAPORATOR WING EVAPORATORS 21 RECEIVER/DRYER SIGHT GLASS (R12 ONLY) SERVICE PORTS CONDENSER COMPRESSOR Figure 21-3. Air Conditioning Components Location 21-4 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL RH VENT BLWR LH VENT BLWR 10 10 HF1 HF7 L L K K HF15 HF17 HF22 HF23 RH VENT FAN MOTOR 6 78 5 6 78 5 HF10 HF20 HF4 HF8 RH VENT BLWR 10 RH WING 9 9 8 8 HF5 HF6 LH VENT BLWR 10 1 1 2 2 HF1 HF7 L L K K HF15 HF17 RH VENT FAN MOTOR 6 78 5 6 78 5 HF10 HF4 HF8 A RH WING HF22 HF23 HF20 9 9 8 8 HF5 HF6 1 1 2 2 HF21 9 9 19 19 HF11 HF12 1 1 2 2 A RH SWITCH RH SWITCH HF21 HF2 9 9 19 19 HF11 HF12 I LEGEND LH SWITCH POSITIVE POWER OR SWITCHABLE POWER CONDITION: BATTERY ON LH WING OVERHEAD CONSOLE LEGEND 1 1 2 2 BATTERY POWER LH VENT FAN MOTOR HF2 I LH SWITCH POSITIVE POWER OR SWITCHABLE POWER GROUND CONDITION: BATTERY ON LH SELECTED ON Figure 21-4. Ventilation Blowers (Sheet 1 of 2) LH WING LH VENT FAN MOTOR OVERHEAD CONSOLE 21 Figure 21-4. Ventilation Blowers (Sheet 2 of 2) NOTES Revision 0 FOR TRAINING PURPOSES ONLY 21-5 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CONTROL SWITCH CONTROL SWITCH AFT VENT BLO BLOWER SWITCHES VENT 10 HE1 N N HE5 HE21 HE22 OFF HE10 COOL RH VENT BLO LH VENT BLO AC 10 10 5 HE2 r r HE6 HE56 HE57 1 2 1 2 3 RH WING CONN. HE23 HE24 HE11 1 2 1 2 HE51 HE50 1 3 4 2 1 3 4 2 HE33 HE34 HE46 1 2 3 1 2 3 1 2 3 ORN RED BLK AFT VENT BLO M 10 HE1 N N HE5 AFT EVAP. HE21 HE22 OFF HE10 COOL 1 2 HE56 HE57 1 2 RH WING CONN. HE58 ORN RED BLK X M RH VENT BLO RH EVAP. 10 HE2 r r HE6 HE3 HE74 EE EE s s HE7 HE78 HE25 HE26 HE12 POSITIVE POWER OR SWITCHABLE POWER 3 4 HE52 HE53 HE35 HE36 HE47 1 2 3 1 2 3 ORN RED BLK M LH VENT BLO LH EVAP. LH WING CONN. HE82 HE83 1 2 1 2 BLK/GRN 1 4 3 2 10 AC ORN COMPRESSOR CLUTCH N M 5 1 2 3 ORN RED BLK M AFT EVAP. HE58 HE11 1 2 1 2 HE51 HE50 1 3 4 2 1 3 4 2 HE33 HE34 HE46 1 2 3 1 2 3 ORN RED BLK HE12 HE25 HE26 3 4 3 4 HE52 HE53 1 4 3 2 1 4 3 2 HE35 HE36 HE47 1 2 3 1 2 3 ORN RED BLK X M RH EVAP. HE55 HE3 EE EE HE7 HE54 RH & LH VENT & AC CONN. 16 GA. JUMPER BATTERY POWER 3 4 1 4 3 2 1 2 3 HE23 HE24 HE55 LEGEND 21 1 2 BLOWER SWITCHES VENT HE74 s s HE78 LEGEND LH EVAP. HE54 RH & LH VENT & AC CONN. 16 GA. JUMPER M LH WING CONN. HE82 HE83 1 2 1 2 ORN COMPRESSOR CLUTCH N M BATTERY POWER GROUND BLK/GRN BLK/GRN BLK/GRN POSITIVE POWER OR SWITCHABLE POWER CONDITION: BATTERY ON PRESSURE SWITCH CONDITION: BATTERY ON COOL SELECTED Figure 21-5. Vapor Cycle AC Electrical (Sheet 1 of 2) PRESSURE SWITCH Figure 21-5. Vapor Cycle AC Electrical (Sheet 2 of 2) NOTES 21-6 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL (G1000 ONLY) 20 GA. JUMPER A HB16 A A B B BLEED AIR HEAT SWITCH CABIN HEAT HB16 B HB20 Z HB17 THERMAL SWITCH A A C C A A B B Z A A C C HB14 HB14 LEGEND CONDITION: POWER ON BUS HB20 THERMAL SWITCH HB21 LEGEND POSITIVE POWER OR SWITCHABLE POWER CABIN HEAT Z HB17 FLOW CONTROL VALVE SOLENOID Z FLOW CONTROL VALVE SOLENOID HB21 #1 GIA63W ON #1 GIA63W ON CABIN HEAT OFF HB15 A BLEED AIR HEAT SWITCH B 20 GA. JUMPER CABIN HEAT OFF HB15 #2 GIA63W (G1000 ONLY) #2 GIA63W NC NO 5 BATTERY POWER 5 POSITIVE POWER OR SWITCHABLE POWER GROUND BLEED AIR HEAT C CONDITION: ON SELECTED SAFETY SWITCH Figure 21-6. Bleed Air Heat (Sheet 1 of 2) NC NO 21 BLEED AIR HEAT C SAFETY SWITCH Figure 21-6. Bleed Air Heat (Sheet 2 of 2) NOTES Revision 0 FOR TRAINING PURPOSES ONLY 21-7 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 21 21-8 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CHAPTER 22 AUTO FLIGHT 22 INTRODUCTION The Cessna 208 has several options for autoflight. Typical installations include the Garmin G1000 integrated avionics system, the King KFC-225 or the King KFC/KAP-150 autopilot/flight control system (AFCS). Other installations include the Sperry 400B navomatic autopilot or the Sperry 400B integrated flight control system and the King KFC-250 flight control system. GENERAL Any of these systems allows the crew to automatically or manually control the flight of the aircraft. • Pitch command The systems provide the following functions: • Back course switching • Tracking of any magnetic heading • NAV 1 or NAV 2 receiver selection • Automatic intercept and tracking of VOR radials or ILS localizer and glide slope beams • Pitch attitude disengagement with associated warning tone • Automatic pitch synchronization and trim • Manual turn (400B only) Revision 0 • Altitude hold FOR TRAINING PURPOSES ONLY The autoflight system includes annunciator lights. The Sperry 400B system includes an A/P ROLL TRIM indicator that signals any adjustments necessary to neutralize autopilot roll effort and a prior-to-flight test function. 22-1 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL DESCRIPTION HDG APR NAV HDG FD XFR ALT CRS1 VS BC BANK YD AP The Cessna Caravan aircraft has the GFC 700 AFCS to help decrease the pilot workload during flight. This section describes the controller and autopilot servo installations used by the AFCS. This section also has references to the Garmin G1000 integrated avionics system. For a general description of the G1000 system, refer to Chapter —”Navigation.” FLC DN ALT SEL CRS2 VNV SPD UP E 160 1-2 20 20 10 10 10200 10100 150 20 3100 00 100 145 140 10 130 120 HDG 10 21 15 CDI + DME IDENT 331° 38.0NM FRAME 324° 73.2NM 334° 10.0NM R LCL NRST 08:44:27 ALERTS D MENU FPL PROC ENT DFLT MAP 700 24CL V107 FMS EHF FFLOW PPH 379 4 28.0 A–ICE GAL 4.7 TRAFFIC V25 V186 V22 V137 V201 V107 AIRWY XWHP V107 XBUR V23 10 HDG GDC 74A #1 Air Data Computer OAT Airspeed Altitude Vertical Speed GRS 77 #1 AHRS Attitude Pitch Rate Of Turn Slip/Skid GMU 44 #1 Magnetometer Heading GSA 81 Pitch Trim 10200 10100 V12 MAP WPT AUX NRST D MENU FPL PROC CLR ENT TERRAIN KVCV-- 100FT 80NM BACK –1000FT DFLT MAP 33 GPS OAT__– 5°c FMS ?????? INSET 37.9NM EHF NAV1 SENSOR PFD 80 127.100 COM1 122.450 COM2 CRS 331° N ENR OBS CDI PUSH VOL SQ COM EMERG 2 1 PUSH 1-2 BARO -900 1 9800 328° 30 PUSH 9900 10 328° PAN V386 V197 128.375 121.500 20 + KWJP KPMD V27 316 10 PUSH STD 9700 29.92IN 2 RANGE – + GDC 74A #2 Air Data Computer OAT Airspeed Altitude Vertical Speed GRS 77 #2 AHRS Attitude Pitch Rate Of Turn Slip/Skid GMU 44 #2 Magnetometer Heading GSA 81 Yaw Servo The GRS 77 AHRS, 74A Air Data Computer, and GMU 44 Magnetometer are responsible for providing the G1000 system with flight instrumentation. Data consists of aircraft attitude, heading, altitude, airspeed vertical speed and outside air temperature information, all displayed on the Primary Flight Display (PFD) (data is displayed on the MFD in reversionary mode). PUSH PAN D DME MENU FPL 50.0NM FLW NAV2 XPDR XPDR1 IDENT 4234 ALT TMR/REF R LCL NRST 08:44:27 ALERTS PROC CLR DFLT MAP ENT FMS PUSH CRSR PUSH CRSR S 22 GSA 81 Pitch Servo 120 331° 310000 100 130 – KEDW KCMA KNTD 20 10 150 PUSH STD V23 KMHV V107 20 145 RANGE V137 V183 TERRIAN 160 1-2 BRG 10 000 10300 170 L V459 V25 PUSH CRSR No. 1 GIA 63W Integrated Avionics Unit VHF COM VHF NAV/LOC GPS Glideslope AFCS Mode Logic Flight Director Computations Servo Management KNID V12 KSBA TOPO PUSH DIS 38.0NM EHF AP YD ALT 10000FT 140 GMN BAT AMPS BUS VOLTS NAV PUSH 1-2 KRFL FUEL QTY LBS R O F F COM GMN GPS 115.40 EHF 117.80 FLW V165 KSMX V27 VOL ID BARO V485 KVBC NAV1 116.90 NAV2 112.50 PUSH PUSH VOL SQ TRACK UP KDLO KSBP 1900 95 10KT KPTV V23 V113 V27 127.100 COM1 122.450 COM2 128.375 121.500 V165 V459 R V137 96.5 85 PAN CLR 900 OIL °C L GMN TMR/REF DIS 38 KVISV459 EMERG V248 KPRB 100 OIL PSI PUSH DTK DIS – – –° – – – –NM 4234 ALT % RPM PROP RPM RANGE – V23.FRAME XPDR1 °C 0 12 2 KFAT KHJO 600 50 FLIGHT PLAN 12 OBS 1-2 1-2 BARO KLGB / KFAT 50.0NM FLW NAV2 XPDR GS 175 N 20 1650 0 331° MAP - NAVIGATION MAP ITT -900 GMN FT–LB X100 10 DTK C80 E INSET PUSH 1 PUSH STD 9700 29.92IN E ?????? NAV PUSH 2 ETE 13:47 6 24 ENR 6 OAT__– 5°c 331° COM 15 3 GPS CRS N 3 W 33 VOL ID 1 9800 328° 328° 30 37.9NM EHF NAV1 SENSOR PFD 9900 80 EMERG 115.40 EHF 117.50 FLW NAV 2 112.50 TRQ PUSH PUSH VOL SQ W 170 NAV 1 116.90 127.100 COM1 122.450 COM2 128.375 121.500 10 000 10300 NAV PUSH 331° 24 BRG 21 DIS 38.0NM EHF AP YD ALT 10000FT S GMN GPS 115.40 EHF 117.80 FLW PUSH DIR 15 NAV1 116.90 NAV2 112.50 PUSH VOL ID PUSH DIR 12 PUSH SYNC Data outputs from the GRS and GDC 74A are sent directly to the PFD 1 and 2 and the MFD via ARINC 429. Additional communications paths connect the GRS and GDC 74A to on-side GIA 63W units, providing quadruple redundant interface. The GRS 77 received GPS data from both GIAs, airspeed data from the GDC 74A, and magnetic heading from the GMU. Using these three external sources, combined with internal sensor data, the GRS accurately calculates aircraft attitude and heading. No. 2 GIA 63W Integrated Avionics Unit VHF COM VHF NAV/LOC GPS Glideslope AFCS Mode Logic Flight Director Computations Servo Management NOTES GSA 81 Roll Servo Figure 22-1. Garmin GFC 700 Interconnect 22-2 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL A/P Master Switch AP NAV REV ALT VS HDG APR GS CAP GA YD ARM ARM ALT TRIM AP Audio Alert Remote Terminal I/F Connector (AFCS Maint. Plug) TRIM FAIL OR KA 285 Remote Mode Annunciator Trim Fail Annunciator DH HDG YD 20 10 10 20 10 20 gs P KCM 100 Configuration Module KC 225 Flight Computer AIR 20 10 NOTES ALT AP a lt A YD R M A R M 1.300 ALERT FT ARM VS ALT SEL Aircraft Static Port UP R AP FD HDG NAV APR REV ALT DN KFC 225 KI 256 Attitude Gyro ALT 0 9 6001 0, 500 400 8 ALT 7 9 8 2 mb 100 FEET 0 1 ALT 1010 MB IN HG 29.99 3 1016 5 6 7 4 5 6 OR B ENCODING 5 4 KS 271C Roll Servo 2 IN.Hg 1005 3 29.7 29.8 KEA 130A Encoding Altimeter KEA 346 Servoed Altimeter DC TST CRS 1 2 N W 21 12 G S 12 1 H S I E 33 OR KS 272C Trim Servo REF 11. 5 3 6 30 24 L O C N A V N 30 33 24 GS S W 15 S 4. NM 5120 KT 350 12 HDG 21 15 NAV GS 22 KS 270C Pitch Servo A R C 330° 3 ADF 2 6 E CRS HDG BRT KCS 55A Compass System Optional Yaw Axis EHI40 EFIS KS 271C Yaw Servo CRSR NAV FPL MODE TRIP CRSR CALC STAT SETUP OTHER MSG ALT D CLR ENT Optional ARINC 429 GPS Interface NAV D/T ACTV REF CTR PULL SCAN 20 15 APT VOR NDB INT SUPL KRG 331 OR KRG 332 Rate Gyro O G 33 2 2 KR 1 GYR 0 RADAR ALT X 100 FEET RA TE BRT ı DH GPS B KLN 90B TSO 3 10 5 4 TEST Optional KRA 10A Radar Altimeter System TRIM DN TRIM UP Cessna Cessna Caravan I Caravan I MAP LIGHT LO HI 0705028-3 Optional Dual Control Wheel Switches Control Wheel Switches Figure 22-2. KFC—225 Schematic Revision 0 FOR TRAINING PURPOSES ONLY 22-3 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL AP NAV REV ALT HDG APR GS CAP GA BC A O M TRIM NOTES VOR/LOC/RNAV Deviation VS Glideslope Deviation KA 185 Mode Annunciator (Optional on some aircraft) Static Pressure Middle Marker KC 191 Computer/ Controller/Annunciator contains computer functions, mode control buttons and annunciator lights in a single unit. Also contains altitude sensor. AIR DH Pitch Attitude/Roll Attitude 10 20 10 20 DC TO BC TRIM TEST ALT HDG NAV APR BC AP AP ENG KS 178 Roll Servo 15 N FR 12 N 3 S OB E 15 S APR 33 GS 33 12 NAV W S GS 30 6 E 22 GS 30 W 24 24 21 HDG 21 GS HDG KAP Heading Select & Course Datum KG258 Attitude Reference Indicator NAV ALT DN UP 6 20 10 3 20 10 KS 177 Pitch Servo KI 204 OR other Course Deviation Indicator (not included) KG 107 Directional Gyro KS 179 Pitch Trim Servo OR DC NAV KG 102A Slaved DG HDG W 21 GS Autopilot Disconnect Trim Interrupt 30 33 15 S GS ING WARN N 12 24 3 TRIM DN 6 E TRIM UP KMT 112 Flux Detector KI 525A Pictorial Navigation Indicator Cessna Caravan I - KCS 55A Slaved Compass System (Optional) + FREE CW SLAVE CCW MAP LIGHT LO HI 0705028-3 OR SLAVE IN KA 51A Manual Electric Trim KA 51B Control Wheel Steering Slaving Accessory DN UP ALT HDG ALT HDG GS NAV APR BC NAV APR BC KAP TRIM TEST O GYR ı RA TE KR G 33 2 KC 191 Autopilot Computer/Controller Annunciator AP AP ENG YD Annunciator Panel-Mounted Yaw Control Switch YAW DAMP (May not be included in all Yaw Damper installations) YD Engage & Roll Crossfeed K296 THIS IS A PUTER YAW COM KRG 331 Rate Gyro KS 178 Yaw Servo KC 296 Yaw Computer Figure 22-3. King KAP 150—3 Axis Autopilot 22-4 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES VOR/LOC/RNAV Deviation AP NAV REV ALT VS HDG APR GS CAP GA BC A O M TRIM Glideslope Deviation KA 185 Mode Annunciator (Optional on some aircraft) Static Pressure Middle Marker AIR DH 20 10 20 10 10 20 10 20 Pitch Altitude/ Roll Altitude FD DN ALT HDG ALT HDG GS NAV APR BC NAV APR BC TRIM KFC 150 UP FD TEST AP AP ENG Pitch Command/ Roll Command KC 192 Computer/ Controller/Annunciator contains computer functions, mode control buttons and annunciator lights in a single unit. Also contains altitude sensor. KI 256 Flight Command Indicator DC NAV HDG W 21 GS Heading Select & Course Datum 30 33 15 S GS KS 178 Roll Servo N 12 24 3 E 6 KI 525A Pictorial Navigation Indicator KS 177 Pitch Servo KMT 112 Flux Detector KG 102A Slaved DG 22 KS 179 Trim Servo ING WARN Autopilot Disconnect / Trim Interrupt TRIM DN TRIM UP Manual Electric Trim - FREE + CW Cessna SLAVE SLAVE IN Caravan I Control Wheel Steering OR CCW MAP LIGHT LO HI 0705028-3 KA 51B KA 51A Slaving Accessory DN UP ALT HDG ALT HDG GS NAV APR BC NAV APR BC KAP TRIM TEST G KR ı RA TE GYR O 33 2 KC 191 Autopilot Computer/Controller Annunciator AP AP ENG YD Annunciator Panel-Mounted Yaw Control Switch YAW DAMP (May not be included in all Yaw Damper installations) YD Engage & Roll Crossfeed K296 THIS IS A PUTER YAW COM KRG 331 Rate Gyro KS 178 Yaw Servo KC 296 Yaw Computer Figure 22-4. King KFC 150—3 Axis Autopilot Revision 0 FOR TRAINING PURPOSES ONLY 22-5 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 22 22-6 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CHAPTER 23 COMMUNICATIONS 23 INTRODUCTION This chapter briefly describes various communication systems, units and components that permit internal, airplane-to-airplane, or airplane-to-ground communications. The aircraft can be configured with multiple configurations from Garmin, Sperry and King GENERAL Revision 0 Garmin G1000 Non-G1000 The Garmin system uses G1000®­line replaceable units (LRU’s) for the major subsystems and supporting equipment. The system is regulated and coordinated by central processing computers in the two Garmin® integrated avionics units (GIA’s), which contain essential navigation and communications avionics equipment. A typical installation includes the King KX 165 NAV/COMM system and the King KMA-24 audio console with two communication jacks, a handheld microphone on the center pedestal, a yoke microphone switch on the pilot yoke, two headsets, and an antenna. FOR TRAINING PURPOSES ONLY 23-1 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 23 Figure 23-1. 208 King Audio Control System 23-2 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES COM1 MIC COM1 COM2 MIC COM2 COM3 MIC COM3 COM 1/2 PA MKR/MUTE DME TEL SPKR HI SENS NAV1 23 ADF NAV2 AUX MAN SQ PILOT PILOT KNOB PLAY COPLT PASS KNOB REVERSIONARY MODE (DISPLAY BACKUP) BUTTON Figure 23-2. 208 G1000 Audio Panel Controls (GMA 1347) Revision 0 FOR TRAINING PURPOSES ONLY 23-3 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES GDL 69A XM SATELLITE RADIO RECEIVER REAL-TIME WEATHER DIGITAL AUDIO ENTERTAINMENT 15 FT–LB X100 170 1-2 E 20 20 10 10 10200 10100 150 20 3100 00 100 145 140 10 130 120 HDG N ENR 2 12 DME IDENT 4234 ALT TMR/REF OIL PSI 95 OIL °C 85 MKR MUTE HI SENS NAV1 ADF NAV2 331° 324° 334° R LCL NRST D MENU FPL PROC CLR ENT 38.0NM 73.2NM 10.0NM 08:44:27 ALERTS DFLT MAP MAN SQ CREW PILOT 1900 EHF KRFL KSMX V137 V183 GMN 379 BAT AMPS BUS VOLTS 4 28.0 A–ICE GAL 4.7 V25 V186 V107 V137 316 V107 AIRWY XWHP V107 XBUR V23 V12 V197 20 10 10 KVCV-- 100FT 80NM BACK –1000FT FPL 10 HDG 30 ENT FMS COPLT PASS PUSH CRSR OAT__– 5°c ?????? INSET 37.9NM EHF NAV1 SENSOR PFD 9900 10 33 GPS 80 127.100 COM1 122.450 COM2 CRS 331° N ENR OBS CDI PUSH VOL SQ COM EMERG 2 1 PUSH 1-2 BARO -900 1 9800 328° 328° PROC CLR DFLT MAP 10100 20 130 120 128.375 121.500 10200 140 MENU 331° 310000 100 TERRAIN V386 MAP WPT AUX NRST 20 150 PUSH D KPMD BRG 145 PAN KWJP V201 KCMA KNTD TERRIAN 1-2 + KEDW V22 V27 TOPO 160 PUSH – KMHV V12 KSBA O F F FFLOW PPH L PUSH STD V23 DIS 38.0NM EHF AP YD ALT 10000FT 10 000 10300 170 RANGE V25 V27 FUEL QTY L LBS R TRAFFIC KNID V459 KVBC GMN GPS 115.40 EHF 117.80 FLW V165 FMS 15 S PUSH CRSR NAV1 116.90 NAV2 112.50 NAV ICS ISOLATION PILOT VOL 23 PLAY V107 96.5 12 TEL SPKR 1-2 BARO V485 100 COM3 DME KSBP VOL ID PUSH KDLO V113 V27 PUSH STD 9700 29.92IN 2 RANGE – + PUSH PAN D E FRAME KFAT XPDR1 PAN 700 PA PUSH DTK DIS – – –° – – – –NM % RPM 900 6 21 + COM PUSH °C 0 COM 1/2 AUX V23.FRAME E CDI RANGE – GMN OBS 1-2 KLGB / KFAT 50.0NM FLW NAV2 XPDR 1-2 PUSH VOL SQ TRACK UP KPTV V23 600 PUSH PROP RPM PUSH BARO -900 GMN COM2 COM3 MIC 1 PUSH STD 9700 29.92IN COM1 COM2 MIC 127.100 COM1 122.450 COM2 10KT EMERG R V137 KPRB ITT COM1 MIC 50 FLIGHT PLAN 6 INSET 331° 2 1 9800 CRS 24 GPS 80 PUSH VOL SQ COM EMERG 128.375 121.500 V165 V459 3 W 33 3 ?????? 37.9NM EHF NAV1 SENSOR PFD 9900 10 328° 328° 30 OAT__– 5°c 127.100 COM1 122.450 COM2 128.375 121.500 10 000 10300 160 PUSH 331° DIS 38 KVISV459 24CL W BRG KHJO 24 DIS 38.0NM EHF AP YD ALT 10000FT GS 175 S GMN GPS 115.40 EHF 117.80 FLW NAV 331° MAP - NAVIGATION MAP 15 NAV1 116.90 NAV2 112.50 PUSH DTK C80 V248 1650 0 ETE 13:47 N 20 21 10 VOL ID 115.40 EHF 117.50 FLW NAV 2 112.50 TRQ NAV 12 NAV 1 116.90 PUSH VOL ID DME FPL 50.0NM FLW NAV2 XPDR XPDR1 IDENT 4234 ALT TMR/REF R LCL NRST 08:44:27 ALERTS MENU PROC CLR DFLT MAP ENT FMS SQ PUSH CRSR DISPLAY BACKUP NO. 1 GIA 63W INTEGRATED AVIONICS UNIT NO. 2 GIA 63W INTEGRATED AVIONICS UNIT SYSTEM INTEGRATION PROCESSORS I/O PROCESSORS VHF COM VHF NAV/LOC GPS GLIDESLOPE AFCS MODE LOGIC FLIGHT DIRECTOR CALCULATIONS SERVO MANAGEMENT GPS OUTPUT SYSTEM INTEGRATION PROCESSORS I/O PROCESSORS VHF COM VHF NAV/LOC GPS GLIDESLOPE AFCS MODE LOGIC FLIGHT DIRECTOR CALCULATIONS SERVO MANAGEMENT GPS OUTPUT Figure 23-3. G1000 Communications Block Diagram 23-4 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL GMA 1347 #2 (OPT) AUDIO PANEL NOTES REVERSIONAL CONTROL MARKER BEACON INTERCOM CONTROL DIGITAL AUDIO CONTROL REV. MODE GDU 1040A MFD HIGH-SPEED DATA BUS (ETHERNET) REV. MODE TRANSPONDER INTERFACE (REVERSIONARY MODE ONLY) HIGH-SPEED DATA BUS (ETHERNET) CONTROL & DISPLAY OF: COM/NAV RADIOS VARIOUS NAVIGATIONAL FUNCTIONS GDU 1040A PFD GDU 1040A PFD CONTROL & DISPLAY OF: COM/NAV RADIOS TRANSPONDER INTERFACE VARIOUS NAVIGATIONAL FUNCTIONS CONTROL & DISPLAY OF: COM/NAV RADIOS TRANSPONDER INTERFACE VARIOUS NAVIGATIONAL FUNCTIONS HIGH-SPEED DATA BUS (ETHERNET) NO. 1 GIA 63W INTEGRATED AVIONICS UNIT VHF COM VHF NAV/LOC GPS GLIDESLOPE VARIOUS I/O PROCESSORS DIGITAL COM/NAV AUDIO VOICE ALERTS GMA 1347 AUDIO PANEL REVERSIONAL CONTROL 23 MARKER BEACON INTERCOM CONTROL DIGITAL AUDIO CONTROL NO. 2 GIA 63W INTEGRATED AVIONICS UNIT GTX 33 MODE S TRANSPONDER VHF COM VHF NAV/LOC GPS GLIDESLOPE VARIOUS I/O PROCESSORS DIGITAL COM/NAV AUDIO VOICE ALERTS GTX 33 MODE S TRANSPONDER (OPTIONAL) Figure 23-4. G1000 Navigation/Communication Data Paths Revision 0 FOR TRAINING PURPOSES ONLY 23-5 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 23 23-6 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CHAPTER 24 ELECTRICAL POWER 24 INTRODUCTION This chapter provides a description of the electrical system used on the CARAVAN I series aircraft. Included is information on system regarding generation, distribution, monitoring and system controls. Accompanying this chapter is a selection of electrical system schematics, found in the program supplemental book, which will be used to enhance understanding of the aircraft electrical systems and components. References for this chapter and further specific information can be found in Chapter 24–Electrical Power, Chapter 80–Starting; Chapter 5–Time Limits/Maintenance Checks, and Chapter 12–Servicing of the Model 208 Maintenance Manual. GENERAL The electrical system is a 28-volt, single wire, negative ground, direct current system. The system has two general buses, two avionics buses with a normally open bus tie switch, and a battery bus. A 200-amp starter/generator and a battery supply power. Revision 0 FOR TRAINING PURPOSES ONLY An optional 300-amp starter/generator may be installed. An optional 75-amp alternator provides standby electrical power. An external power source is available through an airframe-mounted receptacle. 24-1 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL ALTERNATOR STARTER-GENERATOR GENERATOR CONTACTOR ALT SHUNT GEN SHUNT ALTERNATOR CONTACTOR ALTERNATOR CONTROL UNIT EXTERNAL POWER SWITCH GENERATOR CONTROL UNIT NOTES STANDBY ALTERNATOR POWER SWITCH NO. 1 BUS INTERNAL START CONTACTOR EXTERNAL START CONTACTOR ALTERNATOR BUS GROUND POWER MONITOR AVIONICS STANDBY POWER SWITCH EXTERNAL POWER NO. 2 BUS EXTERNAL POWER CONTACTOR 24 BATTERY CONTACTOR NO. 1 AVIONICS POWER SWITCH BATT SHUNT BATTERY SWITCH BUS TIE SWITCH NO. 1 TO HOURMETER NO. 2 AVIONICS POWER SWITCH TO CABIN LIGHTS BATTERY TO ELT TO ETM TO ANTICYCLE SWITCH BATTERY BUS LEGEND BATTERY POWER POWER DISTRIBUTION BUS NO. 2 CONDITIONS: BATTERY CONNECTED BATTERY SWITCH—OFF GROUND Figure 24-1. Electrical Switch Panel and Annunciator Panel 24-2 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL ALTERNATOR STARTER-GENERATOR ALT SHUNT GEN SHUNT GENERATOR CONTACTOR ALTERNATOR CONTACTOR ALTERNATOR CONTROL UNIT EXTERNAL POWER SWITCH GENERATOR CONTROL UNIT NOTES STANDBY ALTERNATOR POWER SWITCH NO. 1 BUS INTERNAL START CONTACTOR EXTERNAL START CONTACTOR ALTERNATOR BUS GROUND POWER MONITOR AVIONICS STANDBY POWER SWITCH EXTERNAL POWER NO. 2 BUS EXTERNAL POWER CONTACTOR BATTERY CONTACTOR NO. 1 AVIONICS POWER SWITCH 24 BATT SHUNT BATTERY SWITCH BUS TIE SWITCH NO. 1 TO HOURMETER NO. 2 AVIONICS POWER SWITCH TO CABIN LIGHTS BATTERY TO ELT TO ETM TO ANTICYCLE SWITCH BATTERY BUS LEGEND BATTERY POWER POWER DISTRIBUTION BUS NO. 2 CONDITIONS: BATTERY CONNECTED—ON BATTERY SWITCH—ON GROUND Figure 24-2. Power Distribution—Battery Power Revision 0 FOR TRAINING PURPOSES ONLY 24-3 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL ALTERNATOR STARTER-GENERATOR ALT SHUNT GEN SHUNT GENERATOR CONTACTOR ALTERNATOR CONTACTOR ALTERNATOR CONTROL UNIT EXTERNAL POWER SWITCH GENERATOR CONTROL UNIT NOTES STANDBY ALTERNATOR POWER SWITCH NO. 1 BUS INTERNAL START CONTACTOR EXTERNAL START CONTACTOR ALTERNATOR BUS GROUND POWER MONITOR AVIONICS STANDBY POWER SWITCH EXTERNAL POWER NO. 2 BUS EXTERNAL POWER CONTACTOR 24 BATTERY CONTACTOR NO. 1 AVIONICS POWER SWITCH BATT SHUNT BATTERY SWITCH BUS TIE SWITCH NO. 1 TO HOURMETER NO. 2 AVIONICS POWER SWITCH TO CABIN LIGHTS BATTERY TO ELT TO ETM POWER DISTRIBUTION BUS TO ANTICYCLE SWITCH BATTERY BUS LEGEND BATTERY POWER NO. 2 CONDITIONS: EXTERNAL POWER CONNECTED—ON EXTERNAL POWER SWITCH—BUS GROUND Figure 24-3. Power Distribution—External Power 24-4 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL GENERATOR FIELD GENERATOR CONTACTOR L PITOT HT BUS 1 FROM START CONTROL CIRCUIT BREAKER STARTER SWITCH TO NO. 1 BUS GEN CONTROL GENERATOR OFF PROP ANTI-ICE PRIM PRIM ANTI-ICE FUEL SEL WARN LINE CONT SENSE START CONT TRQ IND IGNITION SWITCH STARTER/ GENERATOR GEN AMPS TO NO. 1 BUS INTERNAL START CONTACTOR RDNG LIGHT BUS 1 INST LIGHT L LDNG LIGHT STROBE LIGHT BEACON LIGHT TO NO. 1 BUS WING ICE DET LIGHT R FUEL QTY GROUND SNUBBER DIODE GROUND GENERATOR INTERPOLE FUEL FLOW NG & NP IGNITION ON FUEL CONT HEATER SPEED SENSOR TO NO. 2 BUS START INPUT POWER INPUT GENERATOR EXITATION GENERATOR TRIP GENERATOR ON GENERATOR SWITCH BUS 1 AIRSPEED WARN LEFT VENT BLWR AFT VENT BLWR TO NO. 2 BUS POINT OF REGULATION ANTI-CYCLE SIGNAL LINE CONTACTOR SENSE FROM START CONTROL CIRCUIT BREAKER FLAP MTR EXTERNAL START CONTACTOR GENERATOR RESET STBY PWR INOP STBY PWR GENERATOR SHUNT START POWER TO LEFT PITOT HEAT TO PRIM ANTI-ICE ALTERNATOR BUS TO FUEL SELECTOR OFF WARNING SYSTEM ALTERNATOR ON ALTERNATOR OUT POWER IN REMOTE SENSE FIELD AUXILIARY SENSE LINE CONTACTOR REMOTE SENSE ALTERNATOR CONTROL UNIT TO STARTER SW. AND GCU TO TORQ IND TO IGNITION TO READING LIGHT ALT SHUNT TO INST LIGHT TO LEFT LDG LIGHT TO STROBE LIGHT TO BEACON LIGHT TO WING ICE DET LIGHT AVIONICS STANDBY POWER SWITCH/ BREAKER ALTERNATOR CONTACTOR STBY REGULATOR ALT AMPS ALTERNATOR TO RIGHT FUEL QTY LED TO FUEL FLOW NG & NP TO FUEL CONT HEATER TO FLAP MOTOR FROM HOURMETER/ACU C/B STANDBY POWER SWITCH TO AUDIO AUDIO TO AIRSPEED WARN A/P SERVOS TO LEFT VENT BLWR/AIR COND TO AFT VENT BLWR AVIONICS BUS SPARE SPARE SPARE SPARE SPARE RT PITOT HT BUS VOLTS EXTERNAL POWER SWITCH GROUND TO NO. 2 BUS BUS 2 PROP ANTI-ICE CONT BACKUP ANTI-ICE EXTERNAL POWER CONTACTOR W/S ANTI-ICE AUX 12VDC PWR BAT AMPS L FUEL QTY TO NO. 1 AVIONICS POWER SWITCH/ BREAKER EXTERNAL POWER RECEPTACLE AUX FUEL PUMP ELT NAV INTFC FUEL SEL WARN TO RADAR R/T RADAR R/T SPARE SPARE SPARE SEAT BELT SIGN TO PROP ANTI-ICE CONT COM 1 TO BACKUP ANTI-ICE NAV 1 TO W/S ANTI-ICE ENG INTFC TO AUX 12VDC POWER ADC 1 TO LEFT FUEL QTY AHRS 1 TO FUEL SEL WARN BUS 2 GROUND POWER MONITOR TAXI LIGHT TO NO. 2 AVIONICS POWER SWITCH/ BREAKER BATTERY CONTACTOR RT LANDING LIGHT NAV LIGHT FIRE DET PROP OVRSPD TST AIR COND CONT BATTERY SWITCH BAT SWITCH TO HOURMETER HOURMETER/ACU CABIN LTS BCN MONITOR TO CABIN LIGHTS BATTERY SHUNT DECK SKIN FANS STBY FLAP MTR POWER DISTRIBUTION BUS BUS 2 STALL WARN BLEED AIR HT RIGHT VENT BLWR TO RIGHT LANDING LIGHT TO TAXI LIGHT TO ETM ETM CONTINUOUS POWER AVIONICS BUS 1 ADF 1 AVIONICS BUS TIE SWITCH/ BREAKER COM 2 NAV 2 MFD AVIONICS BUS 2 TO FIRE DETECTION TO PROP OVERSPEED TST TO AIR CONDITIONING CONTROL TO DECK SKIN FANS TO STANDBY FLAP MOTOR TO STALL WARNING ADC 2 AHRS 2 PFD 2 NUMBER 2 AVIONICS POWER SWITCH/ BREAKER XPDR 2 TO COMMUNICATION RECEIVER 1 TO NAVIGATION RECEIVER 1 TO ENGINE INTERFACE TO ATTITUDE HEADING REF SYSTEM 1 TO PRIMARY FLIGHT DISPLAY 1 TO TRANSPONDER 1 TO AUTO DIRECTION FINDER SPARE TO COMMUNICATION RECEIVER 2 TO NAVIGATION RECEIVER 2 TO MFD TO AIR DATA COMPUTER 2 TO ATTITUDE HEADING REF SYSTEM 2 TO PRIMARY FLIGHT DISPLAY 2 TO TRANSPONDER 2 SPARE SPARE TAS TO RIGHT VENT BLOWER XM DATA LINK AVIONICS BUS 2 STORM SCOPE HF RCVR HF AMP 24 TO AIR DATA COMPUTER 1 DME TO BLEED AIR HEAT ANTI-CYCLE SWITCH PFD 1 XPDR 1 TO NAVIGATION LIGHT SPARE SPARE SPARE SPARE SPARE TO ELT NUMBER 1 AVIONICS POWER SWITCH/ BREAKER TO SEAT BELT SIGN TO AVN FLOOD LIGHT TO ELT NAV INTFC TO RADIO ALT RADIO ALT TO RIGHT PITOT HEAT TO AUX FUEL PUMP TO A/P SERVOS TO A/P CONT A/P CONT STBY PWR START OUT LINE CONTACTOR GENERATOR CONTROL UNIT BATTERY STBY PWR ON TO PROP ANTI-ICE TO DISTANCE MEASURING EQUIPMENT TO TRAFFIC ADVISORY SYSTEM TO XM – DATA LINK TO STORM SCOPE TO HIGH FREQUENCY RECEIVER TO HIGH FREQUENCY AMP SPARE SPARE SPARE BATTERY BUS Figure 24-4. G1000 Overview—Typical Electrical System Revision 0 FOR TRAINING PURPOSES ONLY 24-5 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL STBY PWR FLAP MOTOR STANDBY FLAP MOTOR GENERATOR FIELD GENERATOR SHUNT GENERATOR CONTACTOR BUS 1 IGN FUEL SEL WARN TO PRIMARY FLAP MOTOR TO STANDBY FLAP MOTOR TO IGNITION EXCITER TO FUEL SELECTOR OFF WARNING SYSTEM TO STARTER SW AND GCU FROM START CONTROL CIRCUIT BREAKER STARTER SWITCH START CONT LEFT TURN BANK GEN CONTROL LINE CONT SENSE ANNUN PANEL FIRE DET BUS 1 STARTER/ GENERATOR FUEL TOTAL LEFT FUEL QTY OIL TEMP INTERNAL START CONTACTOR BLEED AIR TEMP AFT VENT BLWR LEFT PITOT HEAT W/S ANTI/ICE W/S A/ICE CONT GROUND SNUBBER DIODE GROUND GENERATOR INTERPOLE LEFT LDG LIGHT BUS 1 VOLT AMMETER SPEED SENSOR BEACON LIGHT START INPUT POWER INPUT GENERATOR EXITATION GENERATOR TRIP GENERATOR ON GENERATOR SWITCH ANTI-CYCLE SIGNAL LINE CONTACTOR SENSE 24 INST LIGHT WING ICE DET LIGHT SEAT BELT SIGN VOLT/ AMMETER SELECTOR SWITCH POINT OF REGULATION FROM START CONTROL CIRCUIT BREAKER MAP LIGHT EXTERNAL START CONTACTOR GENERATOR RESET STROBE LIGHT AMPHIB GEAR CONT AMPHIB GEAR PUMP START POWER START OUT LINE CONTACTOR LEFT VENT BLWR BUS 2 EXTERNAL POWER SWITCH GROUND RIGHT VENT BLWR AUX FUEL PUMP EXTERNAL POWER CONTACTOR FUEL CONT HEATER RIGHT TURN/BANK ANNUN PANEL STALL WRN AIR COND CONT ITT GAGE FROM ANNUN CIRCUIT BREAKER BUS 2 FUEL FLOW RIGHT FUEL QTY AIR SPEED WARN GROUND POWER MONITOR PROP O-SPD TEST DE-ICE BOOT BATTERY CONTACTOR RIGHT PITOT HEAT PROP ANTI-ICE BATTERY SWITCH + CLOCK – BATTERY SWITCH TO CLOCK AND HOURMETER TO CABIN LIGHTS POWER DISTRIBUTION BUS PROP ANTI-ICE CONTROL RIGHT LDG LIGHT BUS 2 TAXI LIGHT NAV LIGHT RADIO/FLOOD LIGHT KEEP ALIVE 2 KEEP ALIVE 1 BATTERY SHUNT TO AVIONICS FREQUENCY MEMORY RDNG LIGHT RH ATT GYRO BATTERY ANTI-CYCLE SIGNAL BATTERY BUS RH DIR GYRO ENC ALTM ELEV TRIM ALTERNATOR BUS TO ANNUNCIATOR PANEL AUXILIARY SENSE LINE CONTACTOR REMOTE SENSE ALTERNATOR CONTROL UNIT TO FIRE DETECTOR SYSTEM TO FUEL TOTALIZER TO LEFT FUEL QUANTITY INDICATOR TO OIL TEMPERATURE GAGE ALT SHUNT TO BLEED AIR HEATER AVIONICS STANDBY CIRCUIT BREAKER TO AIR CONDITIONING SYSTEM TO LEFT PITOT HEATER TO WINDSHIELD ANTI-ICE HEATER TO WINDSHIELD ANTI-ICE CONTROL ALTERNATOR CONTACTOR TO VOLT/ B ALTERNATOR AMMETER I SELECTOR F SWITCH G TO LEFT LANDING LIGHT TO STROBE LIGHTS STANDBY POWER SWITCH TO BEACON LIGHTS COM 1 TO MAP LIGHTS NAV 1 TO INSTRUMENT LIGHTS AVIONICS STANDBY POWER SWITCH/ BREAKER TO WING ICE DETECTOR LIGHT TO FASTEN SEAT BELT & NO SMOKING SIGN TO LANDING GEAR CONTROL (AMPHIBIAN) TO LANDING GEAR PUMP (AMPHIBIAN) STBY PWR GENERATOR CONTROL UNIT EXTERNAL POWER RECEPTACLE TO LEFT TURN AND BANK INDICATOR ALTERNATOR ON ALTERNATOR OUT POWER IN REMOTE SENSE FIELD TO LEFT VENTILATION BLOWER TO RIGHT VENTILATION BLOWER TO AUXILIARY FUEL PUMP TO ENGINE FUEL CONTROL HEATER TO RIGHT TURN AND BANK INDICATOR AVIONICS BUS 1 ADF 1 GYRO SLAVE NUMBER 1 AVIONICS POWER SWITCH/ BREAKER AUD/MKR A/P ACTR A/P CONT AVIONICS BUS TIE SWITCH/ BREAKER COM 2 NAV 2 AVIONICS BUS 2 TO STALL WARNING SYSTEM DME TO ITT INDICATOR TO AIRSPEED WARNING SYSTEM TO PROPELLER OVERSPEED VALVE ASSEMBLY TO WING AND STABILIZER DE-ICE SYSTEM TO RIGHT PITOT HEATER GLSP 2 ADF 2 TO AIR CONDITIONER TO RIGHT FUEL QUANTITY INDICATOR GLSP 1 HSI 1 TO ANNUNCIATOR PANEL TO FUEL FLOW INDICATOR XPDR 1 RNAV RADIO ALT NUMBER 2 AVIONICS POWER SWITCH/ BREAKER TO PROPELLER ANTI-ICING SYSTEM AVN FAN AUDIO AMP AVIONICS BUS 2 HF XMT TO PROPELLER ANTI-ICING CONTROL TO RIGHT LANDING LIGHT HF RCVR TO TAXI LIGHTS RADAR CONT TO RADIO AND FLOOD LIGHTS TO NAVIGATION RECEIVER 1 TO TRANSPONDER 1 TO GLIDE SLOPE RECEIVER 1 TO ADF RECEIVER 1 TO HORIZONTAL SITUATION INDICATOR 1 TO GYRO SLAVING TO AUDIO CONTROL CONSOLE AND MARKER BEACON RECEIVER TO AUTO PILOT ACTUATOR TO AUTOPILOT CONTROL TO COMMUNICATION RECEIVER 2 TO NAVIGATION RECEIVER 2 SPARE TO GLIDE SLOPE RECEIVER 2 TO ADF RECEIVER 2 TO DME TO AREA NAVIGATION SYSTEM TO RADIO ALTIMETER TO AVIONICS FAN TO AUDIO AMPLIFIER SPARE SPARE SPARE HF XMT TO NAVIGATION LIGHTS TO COMMUNICATIONS RECEIVER 1 RADAR R-T TO HIGH FREQUENCY TRANSMITTER TO HIGH FREQUENCY TRANSMITTER TO HIGH FREQUENCY RECEIVER TO WEATHER RADAR TO WEATHER RADAR SPARE SPARE TO READING LIGHTS TO RH ATTITUDE INDICATOR TO RH DIRECTIONAL INDICATOR TO ENCODING ALTIMETER TO ELECTRIC ELEVATOR TRIM Figure 24-5. Non-G1000 Overview—Typical Electrical System (with Optional Standby Electrical System) 24-6 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 24 Revision 0 FOR TRAINING PURPOSES ONLY 24-7 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 3 2 1 6 4 5 24 7 9 8 10 1. Ground Power Monitor 2. External Start Contactor 3. External Power Contactor 4. Internal Start Contactor 5. Battery Contactor 6. Generator Contactor 7. Battery Shunt 8. Generator Shunt 9. Bus Feeder Current Limiters 10. Field Current Limiter Figure 24-6. Power Distribution Box 24-8 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 24 Revision 0 FOR TRAINING PURPOSES ONLY 24-9 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL OPEN ELECTRICAL GROUND STARTER CUTOFF OVERVOLTAGE PROTECTION >40VDC DIFFERENTIAL VOLTAGE SENSING FIELD WEAKENING CONTROL OVERVOLTAGE PROTECTION GENERATOR CONTROL UNIT H Z V PB 86 PC 20 PC 21 PC 17 PC 19 PC 18 PA 12 PA 11 PA 8 DA 20 DA 22 DA 21 DA 23 ANNUN PB 36 PB 98 MM ANNUN STARTER ENERGIZED GEN OFF A* PB 20 PB 21 A C B WHT BLK PB 5 PB 25 PB 4 PB 6 40 YEL PB 28 BATT SHUNT 40 3 3 PB 65 PB 47 6 6 PB 67 30 30 PB 49 12 12 PB 69 30 PB 46 2 PB 66 30 PB 48 5 5 PB 68 PB 50 11 11 PB 70 PB 73 1 1 PB 59 PB 74 10 10 PB 60 PB 87 7 7 POWER BOX 8 12 11 5 5 2 IGN. EXC. V GEN. FLD. 10 9 7 6 A B PB 42 PB 41 40 11 KA 13 KA 6 15 PB 30 4 3 1 KA 11 KA 8 KA 4 KA 14 PB 45 2 KA 12 PB 42 PB 41 40 KA 15 PB 81 40 GEN. SW. PB 13 PB 12 PB 11 PB 10 GRN 40 40 POL SENSE LOW V SENSE b 6 PB 20 30 AVN 1 PWR 30 AVN 2 PWR 20 GEN CONT 20 5 BUS 2 PWR GND PWR MONITOR WJ 1 12 4 E BUS 1 PWR CONDITIONS: BATTERY IN AIRPLANE AND CONNECTED BATTERY BUS BELOW 24.5 VDC PWR DISTRIBUTION BUS GROUND WHT ORN VOLTAGE LOW A+ 40 a b j 8 PA 9 PA 10 GEN SHUNT h k 9 10 ANTI CYCLE 40 T S U M 2 BLU/WHT EXT PWR – POSITIVE POWER OR SWITCHABLE POWER 3 7 S BLU/WHT WHT WHT PC 14 PC 4 ANNUN 1 EXT. PWR. 1 PB 82 PB 83 PB 84 PB 85 5 BATT CONT A W S F D K L PB 23 PB 16 PC 2 PC 1 PB 33 RED BLK BLU 1 4 3 2 PB 29 EXT START BATTERY POWER 3 2 PA 1 PA 2 BATT BUS D PB 80 PB 16 PB 15 PB 8 PB 34 LEGEND BATT. 4 5 + PA 5 BAT. SW. PC 7 PC 8 PC 3 PC 6 PC 5 PB 1 PB 40 PC 10 PC 9 PC 12 V B A G VOLTAM SW START/GEN + E N P A B DA 30 B+ B+ INT START 1 2 3 4 5 6 7 8 9 PB 35 A B H J PA 4 24 PB 26 PB 9 PB 31 PB 32 VOLTAMM. W V T U PA 7 PC 3 PA 6 PB 2 PB 3 PC 11 LINE CONT SENSE PB 27 5 GEN E E F N H A C J L K P R S M E T R J U ANNUN IGN ON DA 24 DA 25 E D PB 13 PB 93 A E PB 17 PB 92 B D START POWER START INPUT POWER INPUT E POINT OF REGULATION LINE CONTACT SENSE M GEN. RESET GEN. ON GEN. TRIP GROUND X Y ANTI-CYCLE SIGNAL SPEED SENSOR SPEED SENSOR B F Q C G FROM A START OUT GEN. ON LINE GEN. INTERPOLE SNUBBER DIODE GND GROUND GROUND GEN. EXCITATION REVERSE CURRENT PROTECTION START RELAY CONTROL LINE CONTACTOR CONTROL VOLTAGE REGULATOR IGN 5 KA 5 KA 2 KA 1 KA 3 TRUTHTABLE FOR SWITCHES KA 7 5 START CONTROL KA 9 STR. SW. IGN. SW KA 10 PB 61 PB 57 AVN BUS 1 20 PB 58 PB 62 AVN BUS TIE CIRCUIT BREAKER PANEL AVN BUS 2 PB 15 GENERATOR SWITCH POSITION RESET (ON) TRIP 1–2 4–5 7–8 10–11 2–3 4–5 7–8 11–12 2–3 5–6 8–9 11–12 OFF START BUS EXT. POWER SWITCH POSITION PB 42 Figure 24-7. Electrical Circuit (Sheet 1 of 7) 24-10 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 24 Revision 0 FOR TRAINING PURPOSES ONLY 24-11 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL OPEN ELECTRICAL GROUND STARTER CUTOFF OVERVOLTAGE PROTECTION >40VDC DIFFERENTIAL VOLTAGE SENSING FIELD WEAKENING CONTROL OVERVOLTAGE PROTECTION GENERATOR CONTROL UNIT H Z V PB 86 PC 20 PC 21 PC 17 PC 19 PC 18 PA 12 PA 11 PA 8 DA 20 DA 22 DA 21 DA 23 ANNUN PB 36 PB 98 MM ANNUN STARTER ENERGIZED GEN OFF A* PB 20 PB 21 A C B WHT BLK PB 5 PB 25 PB 4 PB 6 GRN YEL 11 5 5 2 40 PB 28 BATT SHUNT 40 3 3 PB 65 PB 47 6 6 PB 67 30 30 PB 49 12 12 PB 69 30 PB 46 2 PB 66 30 PB 48 5 5 PB 68 PB 50 11 11 PB 70 PB 73 1 1 PB 59 PB 74 10 10 PB 60 PB 87 7 7 POWER BOX IGN. EXC. V GEN. FLD. 10 9 7 6 A B 15 PB 30 4 3 1 KA 11 KA 8 KA 4 KA 14 PB 45 2 8 12 KA 13 KA 6 PB 42 PB 41 b 40 40 POL SENSE LOW V SENSE WJ 1 40 KA 12 PB 42 PB 41 CONDITIONS: BATTERY SWITCH—ON BATTERY BUS—BELOW 24.5 VDC 40 KA 15 PB 81 SECONDARY POWER GND PWR MONITOR VOLTAGE LOW A+ 6 PB 20 30 AVN 1 PWR 30 AVN 2 PWR 20 GEN CONT 20 5 BUS 2 PWR ORN ANNUN 12 4 E BUS 1 PWR GROUND PWR DISTRIBUTION BUS POSITIVE POWER OR SWITCHABLE POWER WHT 40 GEN. SW. 11 8 PA 9 PA 10 – a b j 2 BLU/WHT 40 h k 9 10 ANTI CYCLE 40 GEN SHUNT BATTERY POWER S BLU/WHT WHT WHT EXT PWR LEGEND 3 7 T S U M PB 13 PB 12 PB 11 PB 10 5 PC 14 PC 4 RED BLK BLU 1 EXT. PWR. 1 PB 82 PB 83 PB 84 PB 85 PB 33 BATT CONT PB 29 EXT START + PA 1 PA 2 BATT BUS 5 A W S F D K L PB 23 PB 16 PC 2 PC 1 PB 8 PB 34 D PB 80 PB 16 PB 15 PB 1 PB 40 PC 10 PC 9 PC 12 1 4 3 2 PC 7 PC 8 PC 3 PC 6 PC 5 4 3 2 PA 5 BAT. SW. VOLTAM SW START/GEN + V B A G BATT. E N P A B DA 30 B+ B+ INT START 1 2 3 4 5 6 7 8 9 PB 35 A B H J PA 4 24 W V T U PB 26 PB 9 PB 31 PB 32 VOLTAMM. PA 7 PC 3 PA 6 PB 2 PB 3 PC 11 LINE CONT SENSE PB 27 5 GEN E E F N H A C J L K P R S M E T R J U ANNUN IGN ON DA 24 DA 25 E D PB 13 PB 93 A E PB 17 PB 92 B D START POWER START INPUT POWER INPUT E POINT OF REGULATION LINE CONTACT SENSE M GEN. RESET GEN. ON GEN. TRIP GROUND X Y ANTI-CYCLE SIGNAL SPEED SENSOR SPEED SENSOR B F Q C G FROM A START OUT GEN. ON LINE GEN. INTERPOLE SNUBBER DIODE GND GROUND GROUND GEN. EXCITATION REVERSE CURRENT PROTECTION START RELAY CONTROL LINE CONTACTOR CONTROL VOLTAGE REGULATOR IGN 5 KA 5 KA 2 KA 1 KA 3 TRUTHTABLE FOR SWITCHES KA 7 5 START CONTROL KA 9 STR. SW. IGN. SW KA 10 PB 61 PB 57 AVN BUS 1 20 PB 58 PB 62 AVN BUS TIE CIRCUIT BREAKER PANEL AVN BUS 2 PB 15 GENERATOR SWITCH POSITION RESET (ON) TRIP 1–2 4–5 7–8 10–11 2–3 4–5 7–8 11–12 2–3 5–6 8–9 11–12 OFF START BUS EXT. POWER SWITCH POSITION PB 42 Figure 24-7. Electrical Circuit (Sheet 2 of 7) 24-12 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 24 Revision 0 FOR TRAINING PURPOSES ONLY 24-13 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL OPEN ELECTRICAL GROUND STARTER CUTOFF 14 DIFFERENTIAL VOLTAGE SENSING FIELD WEAKENING CONTROL PB 86 PC 20 PC 21 PC 17 PC 19 PC 18 PA 12 PA 11 PA 8 DA 20 DA 22 DA 21 DA 23 ANNUN PB 36 ANNUN STARTER ENERGIZED GEN OFF A* PB 20 PB 21 A C B WHT BLK PB 5 PB 25 PB 4 PB 6 RED BLK BLU GROUND SECONDARY POWER SIGNAL OR SENSE CONDITIONS: BATTERY SWITCH—ON BATTERY BUS—BELOW 24.5 VDC STARTER SWITCH—START ENGINE—BELOW 41 TO 46% Ng WHT ORN GND PWR MONITOR ANNUN VOLTAGE LOW A+ b GRN 40 40 40 40 40 40 POL SENSE LOW V SENSE WJ 1 YEL 6 5 5 2 PB 28 POWER BOX BATT SHUNT 40 3 3 PB 65 PB 47 6 6 PB 67 PB 49 12 12 PB 69 30 PB 46 2 PB 66 30 PB 48 5 5 PB 68 PB 50 11 11 PB 70 PB 73 1 1 PB 59 PB 74 10 10 PB 60 PB 87 7 7 11 4 4 3 1 KA 11 KA 8 KA 4 KA 14 PB 45 2 15 PB 30 7 6 11 IGN. EXC. V GEN. FLD. 10 9 8 A B 3 PB 20 30 30 30 AVN 1 PWR 30 AVN 2 PWR 20 GEN CONT 20 BUS 2 PWR POSITIVE POWER OR SWITCHABLE POWER PWR DISTRIBUTION BUS BATTERY POWER 40 12 KA 13 KA 6 PB 42 PB 41 GEN SHUNT – KA 12 PB 42 PB 41 + 12 4 E BUS 1 PWR LEGEND 40 GEN. SW. 11 8 BLU/WHT EXT PWR PC 10 PC 9 PC 12 a b j 2 PA 9 PA 10 PC 14 PC 4 h k 9 10 ANTI CYCLE BLU/WHT WHT WHT KA 15 PB 81 5 T S U M PB 13 PB 12 PB 11 PB 10 PB 33 3 7 2 S EXT. PWR. 1 PB 82 PB 83 PB 84 PB 85 EXT START BATT CONT PB 29 5 + PA 1 PA 2 BATT BUS A W S F D K L PB 23 PB 16 PC 2 PC 1 PB 8 PB 34 9 START/GEN 1 VOLTAM SW INT START PB 1 PB 40 1 4 3 2 DA 30 B+ B+ 3 2 8 PA 5 BAT. SW. PC 7 PC 8 PC 3 PC 6 PC 5 10 4 E N P A B PA 4 A B 10 BATT. PB 35 INTERPOLE WINDINGS SENSES REV CURR. H J V B A G PA 7 PC 3 PA 6 24 PB 32 VOLTAMM. 1 2 3 4 5 6 7 8 9 PB 9 PB 31 13 PIN D ANNUN IGN ON W V T U PB 26 PC 11 PB 2 PB 3 LINE CONT SENSE PB 27 5 GEN E E D PB 80 PB 16 PB 15 16 F N H A C J L K P R S M E T R J U 5 PIN W START SIG IN W START SIG OUT Z DA 24 DA 25 B D E D PB 13 PB 93 A E PB 17 PB 92 7 PIN Z H Z V START POWER START INPUT POWER INPUT GENERATOR CONTROL UNIT POINT OF REGULATION E GEN. RESET GEN. ON GEN. TRIP LINE CONTACT SENSE M ANTI-CYCLE SIGNAL GROUND X Y MM 6 FROM A START OUT GEN. ON LINE SPEED SENSOR SPEED SENSOR B F Q C G PB 98 START RELAY CONTROL LINE CONTACTOR CONTROL VOLTAGE REGULATOR OVERVOLTAGE PROTECTION GEN. INTERPOLE SNUBBER DIODE GND GROUND GROUND GEN. EXCITATION 15 PIN B REVERSE CURRENT PROTECTION OVERVOLTAGE PROTECTION >40VDC IGN 5 KA 3 1 KA 7 5 START CONTROL KA 9 STR. SW. IGN. SW KA 10 PB 61 PB 57 AVN BUS 1 20 PB 58 PB 62 AVN BUS TIE CIRCUIT BREAKER PANEL AVN BUS 2 PB 15 5 12 KA 5 KA 2 KA 1 TRUTHTABLE FOR SWITCHES GENERATOR SWITCH POSITION RESET (ON) TRIP 1–2 4–5 7–8 10–11 2–3 4–5 7–8 11–12 2–3 5–6 8–9 11–12 OFF START BUS EXT. POWER SWITCH POSITION PB 42 Figure 24-7. Electrical Circuit (Sheet 3 of 7) 24-14 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 24 Revision 0 FOR TRAINING PURPOSES ONLY 24-15 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL OPEN ELECTRICAL GROUND STARTER CUTOFF OVERVOLTAGE PROTECTION >40VDC DIFFERENTIAL VOLTAGE SENSING FIELD WEAKENING CONTROL OVERVOLTAGE PROTECTION GENERATOR CONTROL UNIT H Z V PB 86 PC 20 PC 21 PC 17 PC 19 PC 18 PA 12 PA 11 PA 8 DA 20 DA 22 DA 21 DA 23 ANNUN PB 36 PB 98 MM ANNUN STARTER ENERGIZED GEN OFF A* PB 20 PB 21 A C B WHT BLK PB 5 PB 25 PB 4 PB 6 CONDITIONS: BATTERY SWITCH—ON BATTERY BUS—BELOW 24.5 VDC STARTER SWITCH—START ENGINE—ABOVE 41 TO 46% Ng GND PWR MONITOR ANNUN VOLTAGE LOW A+ b GRN 40 40 40 POL SENSE LOW V SENSE WJ 1 40 YEL 11 5 5 2 PB 28 BATT SHUNT 40 3 3 PB 65 PB 47 6 6 PB 67 30 30 PB 49 12 12 PB 69 30 PB 46 2 PB 66 30 PB 48 5 5 PB 68 PB 50 11 11 PB 70 PB 73 1 1 PB 59 PB 74 10 10 PB 60 PB 87 7 7 POWER BOX IGN. EXC. V GEN. FLD. 10 9 7 6 A B 15 PB 30 4 3 1 KA 11 KA 8 KA 4 KA 14 PB 45 2 8 12 KA 13 KA 6 PB 42 PB 41 SIGNAL OR SENSE ORN 40 KA 12 PB 42 PB 41 SECONDARY POWER WHT 40 KA 15 PB 81 GROUND 6 PB 20 30 AVN 1 PWR 30 AVN 2 PWR 20 GEN CONT 20 5 BUS 2 PWR RED BLK BLU 12 4 E BUS 1 PWR – 40 GEN. SW. 11 8 PA 9 PA 10 GEN SHUNT a b j 9 10 ANTI CYCLE 40 h k 2 BLU/WHT EXT PWR POSITIVE POWER OR SWITCHABLE POWER S BLU/WHT WHT WHT PWR DISTRIBUTION BUS BATTERY POWER 3 7 T S U M PB 13 PB 12 PB 11 PB 10 5 PC 14 PC 4 + 1 EXT. PWR. 1 PB 82 PB 83 PB 84 PB 85 PB 33 BATT CONT PB 29 EXT START LEGEND PA 1 PA 2 BATT BUS 5 A W S F D K L PB 23 PB 16 PC 2 PC 1 PB 8 PB 34 D PB 80 PB 16 PB 15 PB 1 PB 40 PC 10 PC 9 PC 12 1 4 3 2 PC 7 PC 8 PC 3 PC 6 PC 5 4 3 2 PA 5 BAT. SW. VOLTAM SW START/GEN + V B A G BATT. E N P A B DA 30 B+ B+ INT START 1 2 3 4 5 6 7 8 9 PB 35 A B H J PA 4 24 W V T U PB 26 PB 9 PB 31 PB 32 VOLTAMM. PA 7 PC 3 PA 6 PB 2 PB 3 PC 11 LINE CONT SENSE PB 27 5 GEN E E F N H A C J L K P R S M E T R J U ANNUN IGN ON DA 24 DA 25 E D PB 13 PB 93 A E PB 17 PB 92 B D START POWER START INPUT POWER INPUT E POINT OF REGULATION LINE CONTACT SENSE M GEN. RESET GEN. ON GEN. TRIP GROUND X Y ANTI-CYCLE SIGNAL SPEED SENSOR SPEED SENSOR B F Q C G FROM A START OUT GEN. ON LINE GEN. INTERPOLE SNUBBER DIODE GND GROUND GROUND GEN. EXCITATION REVERSE CURRENT PROTECTION START RELAY CONTROL LINE CONTACTOR CONTROL VOLTAGE REGULATOR IGN 5 KA 5 KA 2 KA 1 KA 3 TRUTHTABLE FOR SWITCHES KA 7 5 START CONTROL KA 9 STR. SW. IGN. SW KA 10 PB 61 PB 57 AVN BUS 1 20 PB 58 PB 62 AVN BUS TIE CIRCUIT BREAKER PANEL AVN BUS 2 PB 15 GENERATOR SWITCH POSITION RESET (ON) TRIP 1–2 4–5 7–8 10–11 2–3 4–5 7–8 11–12 2–3 5–6 8–9 11–12 OFF START BUS EXT. POWER SWITCH POSITION PB 42 Figure 24-7. Electrical Circuit (Sheet 4 of 7) 24-16 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 24 Revision 0 FOR TRAINING PURPOSES ONLY 24-17 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL OPEN ELECTRICAL GROUND STARTER CUTOFF DIFFERENTIAL VOLTAGE SENSING FIELD WEAKENING CONTROL H Z V PB 86 PC 20 PC 21 PC 17 PC 19 PC 18 PA 12 PA 11 PA 8 DA 20 DA 22 DA 21 DA 23 ANNUN PB 36 PB 98 ANNUN STARTER ENERGIZED GEN OFF A* PB 20 PB 21 A C B WHT BLK PB 5 PB 25 PB 4 PB 6 YEL PB 28 BATT SHUNT 40 6 3 3 PB 65 PB 47 6 6 PB 67 PB 49 12 12 PB 69 30 PB 46 2 2 PB 66 30 PB 48 5 5 PB 68 30 PB 50 11 11 PB 70 AVN 1 PWR 30 AVN 2 PWR 20 GEN CONT 20 PB 73 1 1 PB 59 PB 74 10 10 PB 60 PB 87 7 7 GEN. SW. 2 11 8 8 12 11 IGN. EXC. V GEN. FLD. 10 9 7 6 A B 15 PB 30 4 3 2 5 1 KA 11 KA 8 KA 4 KA 14 PB 45 POWER BOX a b j KA 13 KA 6 PB 42 PB 41 GRN 40 KA 12 PB 42 PB 41 b 40 40 POL SENSE LOW V SENSE WJ 1 40 KA 15 PB 81 VOLTAGE LOW A+ 40 h k PB 13 PB 12 PB 11 PB 10 GND PWR MONITOR 40 PB 82 PB 83 PB 84 PB 85 CONDITIONS: BATTERY SWITCH—ON AVIONICS PWR—1 & 2 ON BATTERY BUS—28.5 VDC STARTER SWITCH—OFF ENGINE RUNING—GEN ONLINE WHT ORN ANNUN 12 4 E PB 20 30 30 5 BUS 2 PWR SIGNAL OR SENSE PWR DISTRIBUTION BUS POSITIVE POWER OR SWITCHABLE POWER 40 T S U M 9 10 BUS 1 PWR GEN SHUNT SECONDARY POWER 3 7 2 ANTI CYCLE 40 – RED BLK BLU 1 BLU/WHT EXT PWR GROUND EXT. PWR. PA 9 PA 10 BATTERY POWER 1 S BLU/WHT WHT WHT A W S F D K L PB 23 PB 16 PC 2 PC 1 5 BATT CONT PB 29 PB 33 PC 14 PC 4 PC 10 PC 9 PC 12 3 2 PA 1 PA 2 BATT BUS D PB 80 PB 16 PB 15 PB 8 PB 34 EXT START + 1 4 DA 30 PB 1 PB 40 5 + 3 2 BAT. SW. PC 7 PC 8 PC 3 PC 6 PC 5 4 PA 5 PA 4 BATT. E N P A B VOLTAM SW START/GEN LEGEND DA 24 DA 25 B+ B+ INT START V B A G PB 35 A B H J 1 2 3 4 5 6 7 8 9 PB 9 PB 31 PB 32 VOLTAMM. W V T U PB 26 T R J U ANNUN IGN ON PA 7 PC 3 PA 6 24 LINE CONT SENSE PB 27 5 GEN E E F N H A C J L K P R S M E PC 11 PB 2 PB 3 E D PB 13 PB 93 A E PB 17 PB 92 B D START POWER START INPUT POWER INPUT GENERATOR CONTROL UNIT POINT OF REGULATION E GEN. RESET GEN. ON GEN. TRIP LINE CONTACT SENSE M ANTI-CYCLE SIGNAL GROUND X Y FROM A START OUT GEN. ON LINE SPEED SENSOR SPEED SENSOR B F Q C G MM START RELAY CONTROL LINE CONTACTOR CONTROL VOLTAGE REGULATOR OVERVOLTAGE PROTECTION GEN. INTERPOLE SNUBBER DIODE GND GROUND GROUND GEN. EXCITATION REVERSE CURRENT PROTECTION OVERVOLTAGE PROTECTION >40VDC IGN 5 KA 5 KA 2 KA 1 KA 3 TRUTHTABLE FOR SWITCHES KA 7 5 START CONTROL KA 9 STR. SW. IGN. SW KA 10 PB 61 PB 57 AVN BUS 1 20 PB 58 PB 62 AVN BUS TIE CIRCUIT BREAKER PANEL AVN BUS 2 PB 15 GENERATOR SWITCH POSITION RESET (ON) TRIP 1–2 4–5 7–8 10–11 2–3 4–5 7–8 11–12 2–3 5–6 8–9 11–12 OFF START BUS EXT. POWER SWITCH POSITION PB 42 Figure 24-7. Electrical Circuit (Sheet 5 of 7) 24-18 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 24 Revision 0 FOR TRAINING PURPOSES ONLY 24-19 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL OPEN ELECTRICAL GROUND STARTER CUTOFF DIFFERENTIAL VOLTAGE SENSING FIELD WEAKENING CONTROL H Z V PB 86 PC 20 PC 21 PC 17 PC 19 PC 18 PA 12 PA 11 PA 8 DA 20 DA 22 DA 21 DA 23 ANNUN PB 36 PB 98 ANNUN STARTER ENERGIZED GEN OFF A* PB 20 PB 21 A C B WHT BLK PB 5 PB 25 PB 4 PB 6 GEN SHUNT – 6 11 8 8 GROUND WHT ORN GND PWR MONITOR ANNUN VOLTAGE LOW A+ b GRN 40 40 40 40 40 POL SENSE LOW V SENSE WJ 1 40 YEL PB 28 BATT SHUNT 40 PB 45 3 3 PB 65 PB 47 6 6 PB 67 PB 49 12 12 PB 69 30 PB 46 2 2 PB 66 30 PB 48 5 5 PB 68 30 PB 50 11 11 PB 70 AVN 1 PWR 30 AVN 2 PWR 20 GEN CONT 20 PB 73 1 1 PB 59 PB 74 10 10 PB 60 PB 87 7 7 POWER BOX 12 11 IGN. EXC. V GEN. FLD. 10 9 7 6 A B 15 PB 30 4 3 5 2 1 KA 11 KA 8 KA 4 KA 14 PB 20 30 30 5 BUS 2 PWR PWR DISTRIBUTION BUS RED BLK BLU 40 GEN. SW. KA 13 KA 6 PB 42 PB 41 12 4 E BUS 1 PWR 40 a b j 2 PA 9 PA 10 EXT PWR h k 9 10 ANTI CYCLE BLU/WHT WHT WHT KA 12 PB 42 PB 41 S KA 15 PB 81 3 7 T S U M PB 13 PB 12 PB 11 PB 10 1 PB 82 PB 83 PB 84 PB 85 5 BATT CONT A W S F D K L PB 23 PB 16 PC 2 PC 1 1 EXT. PWR. BLU/WHT PC 10 PC 9 PC 12 POSITIVE POWER OR SWITCHABLE POWER CONDITIONS: BATTERY SWITCH—OFF EXTERNAL POWER UNIT—ON EXTERNAL POWER SWITCH—BUS 1 4 3 2 PB 29 PB 33 BATTERY POWER SECONDARY POWER 3 2 PA 1 PA 2 BATT BUS D PB 80 PB 16 PB 15 PB 8 PB 34 PC 14 PC 4 EXTERNAL POWER PC 7 PC 8 PC 3 PC 6 PC 5 PB 1 PB 40 EXT START + PA 5 BAT. SW. BATT. 4 5 LEGEND V B A G VOLTAM SW START/GEN + E N P A B DA 30 B+ B+ INT START 1 2 3 4 5 6 7 8 9 PB 35 A B PB 26 PB 9 PB 31 PB 32 H J PA 4 24 E E VOLTAMM. W V T U PA 7 PC 3 PA 6 PB 2 PB 3 PC 11 LINE CONT SENSE PB 27 5 GEN F N H A C J L K P R S M E T R J U ANNUN IGN ON DA 24 DA 25 E D PB 13 PB 93 A E PB 17 PB 92 B D START POWER START INPUT POWER INPUT GENERATOR CONTROL UNIT POINT OF REGULATION E GEN. RESET GEN. ON GEN. TRIP LINE CONTACT SENSE M ANTI-CYCLE SIGNAL GROUND X Y FROM A START OUT GEN. ON LINE SPEED SENSOR SPEED SENSOR B F Q C G MM START RELAY CONTROL LINE CONTACTOR CONTROL VOLTAGE REGULATOR OVERVOLTAGE PROTECTION GEN. INTERPOLE SNUBBER DIODE GND GROUND GROUND GEN. EXCITATION REVERSE CURRENT PROTECTION OVERVOLTAGE PROTECTION >40VDC IGN 5 KA 5 KA 2 KA 1 KA 3 TRUTHTABLE FOR SWITCHES KA 7 5 START CONTROL KA 9 STR. SW. IGN. SW KA 10 PB 61 PB 57 AVN BUS 1 20 PB 58 PB 62 AVN BUS TIE CIRCUIT BREAKER PANEL AVN BUS 2 PB 15 GENERATOR SWITCH POSITION RESET (ON) TRIP 1–2 4–5 7–8 10–11 2–3 4–5 7–8 11–12 2–3 5–6 8–9 11–12 OFF START BUS EXT. POWER SWITCH POSITION PB 42 Figure 24-7. Electrical Circuit (Sheet 6 of 7) 24-20 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 24 Revision 0 FOR TRAINING PURPOSES ONLY 24-21 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL OPEN ELECTRICAL GROUND STARTER CUTOFF DIFFERENTIAL VOLTAGE SENSING FIELD WEAKENING CONTROL OVERVOLTAGE PROTECTION >40VDC OVERVOLTAGE PROTECTION GENERATOR CONTROL UNIT H Z V PB 86 PC 20 PC 21 PC 17 PC 19 PC 18 PA 12 PA 11 PA 8 DA 20 DA 22 DA 21 DA 23 ANNUN PB 36 MM ANNUN STARTER ENERGIZED GEN OFF A* PB 20 PB 21 A C B WHT BLK PB 5 PB 25 PB 4 PB 6 ANNUN VOLTAGE LOW A+ b GRN 40 40 40 POL SENSE LOW V SENSE WJ 1 40 YEL PB 28 BATT SHUNT 40 3 3 PB 65 PB 47 6 6 PB 67 PB 49 12 12 PB 69 30 PB 46 2 PB 66 30 PB 48 5 5 PB 68 PB 50 11 11 PB 70 PB 73 1 1 PB 59 PB 74 10 10 PB 60 PB 87 7 7 8 12 11 IGN. EXC. V GEN. FLD. 10 9 7 6 A B 15 PB 30 4 3 5 2 1 KA 11 KA 8 KA 4 KA 14 PB 45 2 11 KA 13 KA 6 PB 42 PB 41 GND PWR MONITOR 40 KA 12 PB 42 PB 41 ORN SECONDARY POWER CONDITIONS: BATTERY SWITCH—ON EXTERNAL POWER UNIT—ON BATTERY BUS—BELOW 24.5 VDC EXTERNAL POWER SWITCH—START STARTER SWITCH—START ENGINE—BELOW 41 TO 46% Ng WHT 40 KA 15 PB 81 EXTERNAL POWER 6 PB 20 POWER BOX 30 30 30 AVN 1 PWR 30 AVN 2 PWR 20 GEN CONT 20 5 BUS 2 PWR RED BLK BLU 40 GEN. SW. PB 13 PB 12 PB 11 PB 10 GROUND 12 4 E BUS 1 PWR POSITIVE POWER OR SWITCHABLE POWER – GEN SHUNT a b j 8 PA 9 PA 10 + h k 9 10 ANTI CYCLE 40 T S U M 2 BLU/WHT EXT PWR PWR DISTRIBUTION BUS BATTERY POWER 3 7 S BLU/WHT WHT WHT PC 14 PC 4 EXT. PWR. 1 PB 82 PB 83 PB 84 PB 85 5 BATT CONT PB 29 PB 33 EXT START PC 10 PC 9 PC 12 PA 1 PA 2 BATT BUS A W S F D K L PB 23 PB 16 PC 2 PC 1 PB 8 PB 34 D PB 80 PB 16 PB 15 PB 1 PB 40 5 + 1 VOLTAM SW START/GEN LEGEND 1 4 3 2 PA 5 BAT. SW. DA 30 B+ B+ INT START 4 3 2 PB 35 A B V B A G BATT. E N P A B PC 7 PC 8 PC 3 PC 6 PC 5 PB 9 PB 31 PB 32 H J 1 2 3 4 5 6 7 8 9 PA 7 PC 3 PA 6 24 W V T U PB 26 PC 11 PB 2 PB 3 VOLTAMM. PA 4 LINE CONT SENSE PB 27 5 GEN E E F N H A C J L K P R S M E T R J U ANNUN IGN ON DA 24 DA 25 E D PB 13 PB 93 A E PB 17 PB 92 B D START POWER START INPUT POWER INPUT E POINT OF REGULATION LINE CONTACT SENSE M GEN. RESET GEN. ON GEN. TRIP GROUND X Y ANTI-CYCLE SIGNAL SPEED SENSOR SPEED SENSOR B F Q C G FROM A START OUT GEN. ON LINE GEN. INTERPOLE SNUBBER DIODE GND GROUND GROUND GEN. EXCITATION REVERSE CURRENT PROTECTION PB 98 START RELAY CONTROL LINE CONTACTOR CONTROL VOLTAGE REGULATOR IGN 5 KA 5 KA 2 KA 1 KA 3 TRUTHTABLE FOR SWITCHES KA 7 5 START CONTROL KA 9 STR. SW. IGN. SW KA 10 PB 61 PB 57 AVN BUS 1 20 PB 58 PB 62 AVN BUS TIE CIRCUIT BREAKER PANEL AVN BUS 2 PB 15 GENERATOR SWITCH POSITION RESET (ON) TRIP 1–2 4–5 7–8 10–11 2–3 4–5 7–8 11–12 2–3 5–6 8–9 11–12 OFF START BUS EXT. POWER SWITCH POSITION PB 42 Figure 24-7. Electrical Circuit (Sheet 7 of 7) 24-22 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 24 Revision 0 FOR TRAINING PURPOSES ONLY 24-23 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL SHUNT ALTERNATOR B G S F PH5 PH4 100 Ω CARBON RESISTOR PH37 40 AMP CURRENT LIMITERS F19 PH38 40 F20 PH39 40 PH3 PH2 PH33 F14 F15 2 2 2 F16 F17 2 RELAY PH8 PH25 PH7 ALTERNATOR CONTROL UNIT GROUND – REM SENSE FIELD AUX SENSE LINE CONT. + REM SENSE CURRENT (–) POWER IN ALT. OUT ALT. ON PH40 30 PH41 40 PH42 PH20 12 12 5 5 13 13 7 7 9 9 2 2 10 10 3 3 6 6 4 4 7 1 2 7 1 2 3 3 4 4 5 5 40 6 6 PH6 PH30 PH29 PH32 PH10 PH11 PH24 DA35 DA36 TO ANNU. PANEL x x PH18 PH12 C C PH19 WF20 V V z z PH35 PH14 CLOCK 5 BATTERY POWER DC1 PH26 a a TO INDICATING AND RECORDING 100 Ω CARBON RESISTOR PH3 PH2 POSITIVE POWER OR SWITCHABLE POWER GROUND SIGNAL OR SENSE F14 F15 2 2 2 F16 F17 2 RELAY PH8 ALTERNATOR CONTROL UNIT GROUND – REM SENSE FIELD AUX SENSE LINE CONT. + REM SENSE CURRENT (–) POWER IN ALT. OUT ALT. ON OFF ON PH13 STBY PWR SWITCH 30 PH41 PH25 5 7 1 2 7 1 2 3 3 4 4 5 5 6 6 PH6 PH30 PH29 PH32 PH10 PH11 PH24 40 STBY PWR 40 STBY PWR PH42 PH20 12 12 5 5 13 13 7 7 9 9 2 2 10 10 3 3 6 6 4 4 DA35 DA36 TO ANNU. PANEL PH28 x x PH18 PH12 C C PH19 WF20 V V z z PH35 PH14 PH13 22 LEGEND ANNUNCIATOR PANEL CLOCK 5 Figure 24-8. Standby Alternator Circuit (Sheet 1 of 4) BATTERY POWER PH36 DC1 PH26 a a TO INDICATING AND RECORDING 15 COM 1 OFF ON STBY PWR SWITCH 18 GA JUMPER TO VOLT AMMETER 23 CONDITIONS: BATTERY INSTALLED AND ON STBY PWR SWITCH OFF / < 7VDC PIN 7 GENERATOR ON LINE / NORMAL ENGINE RUNNING PH40 16 GA JUMPER DA33 PH31 PH9 DA34 18 GA JUMPER LEGEND PH36 PH5 PH4 PH7 STBY PWR PH28 TO VOLT AMMETER ANNUNCIATOR PANEL S F STBY PWR 22 23 15 B G COM 1 PH33 5 F18 PH37 40 AMP CURRENT LIMITERS F19 PH38 40 F20 PH39 40 PH1 16 GA JUMPER DA33 PH31 PH9 DA34 SHUNT ALTERNATOR F18 PH1 POSITIVE POWER OR SWITCHABLE POWER GROUND SIGNAL OR SENSE CONDITIONS: BATTERY INSTALLED AND ON STBY PWR SWITCH ON / < 7VDC PIN 7 GENERATOR ON LINE / NORMAL ENGINE RUNNING Figure 24-8. Standby Alternator Circuit (Sheet 2 of 4) NOTES 24 24-24 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL SHUNT ALTERNATOR B G S F PH5 PH4 100 Ω CARBON RESISTOR PH3 PH2 PH33 F14 F15 PH37 40 AMP CURRENT LIMITERS F19 PH38 40 F20 PH39 40 2 2 2 F16 F17 2 RELAY PH8 PH25 PH7 ALTERNATOR CONTROL UNIT GROUND – REM SENSE FIELD AUX SENSE LINE CONT. + REM SENSE CURRENT (–) POWER IN ALT. OUT ALT. ON PH40 30 PH41 40 PH42 PH20 12 12 5 5 13 13 7 7 9 9 2 2 10 10 3 3 6 6 4 4 7 1 2 7 1 2 3 3 4 4 5 5 40 6 6 PH6 PH30 PH29 PH32 PH10 PH11 PH24 DA35 DA36 B G COM 1 TO ANNU. PANEL x x PH18 PH12 C C PH19 WF20 V V z z PH35 PH14 PH5 PH4 100 Ω CARBON RESISTOR PH3 PH2 5 DC1 PH26 a a TO INDICATING AND RECORDING 2 2 F16 F17 2 PH8 ALTERNATOR CONTROL UNIT GROUND – REM SENSE FIELD AUX SENSE LINE CONT. + REM SENSE CURRENT (–) POWER IN ALT. OUT ALT. ON OFF ON PH13 PH40 7 1 2 7 1 2 3 3 4 4 PH41 PH25 5 5 DA35 DA36 5 40 STBY PWR 40 STBY PWR PH42 6 6 TO ANNU. PANEL PH28 x x PH18 PH12 C C PH19 WF20 V V z z PH35 PH14 PH13 22 COM 1 OFF ON STBY PWR SWITCH 18 GA JUMPER TO VOLT AMMETER 23 15 16 GA JUMPER PH6 PH30 PH29 PH32 PH10 PH11 PH24 30 PH20 12 12 5 5 13 13 7 7 9 9 2 2 10 10 3 3 6 6 4 4 STBY PWR SWITCH 18 GA JUMPER LEGEND PH36 2 DA33 PH31 PH9 DA34 LEGEND ANNUNCIATOR PANEL BATTERY POWER BATTERY POWER CLOCK F14 F15 RELAY PH7 STBY PWR PH28 TO VOLT AMMETER ANNUNCIATOR PANEL S F STBY PWR 22 23 15 PH33 5 F18 PH37 40 AMP CURRENT LIMITERS F19 PH38 40 F20 PH39 40 PH1 16 GA JUMPER DA33 PH31 PH9 DA34 SHUNT ALTERNATOR F18 PH1 POSITIVE POWER OR SWITCHABLE POWER CLOCK 5 GROUND PH36 DC1 SIGNAL OR SENSE CONTROLLING POWER PH26 a a TO INDICATING AND RECORDING GROUND SIGNAL OR SENSE CONTROLLING POWER CONDITIONS: BATTERY INSTALLED AND OFF STBY PWR SWITCH ON / < 7VDC PIN 7 GENERATOR OFF LINE / FAILED ENGINE NOT RUNNING ALTERNATOR POWER CONDITIONS: BATTERY INSTALLED AND ON STBY PWR SWITCH ON / > 10 AMPS GENERATOR OFF LINE / FAILED ENGINE RUNNING Figure 24-8. Standby Alternator Circuit (Sheet 3 of 4) 24 Figure 24-8. Standby Alternator Circuit (Sheet 4 of 4) NOTES Revision 0 FOR TRAINING PURPOSES ONLY 24-25 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL LEGEND LEGEND BATTERY POWER BATTERY POWER SECONDARY POWER SECONDARY POWER DA46 ALTERNATOR POWER FIRST DECK NO. 1 GENERATOR CONDITIONS: GEN POSITION SELECTED GENERATOR ON LINE VOLT 4 JUMPER SECOND DECK 4 GEN 1 1 DA41 2 BATT ALT 3 + FIRST DECK NO. 1 GENERATOR AMMETER 3 DA46 ALTERNATOR POWER CONDITIONS: ALT POSITION SELECTED GENERATOR ON LINE – 2 VOLT 4 JUMPER SECOND DECK AMMETER 1 3 DA38 1 1 DA42 DA39 2 2 DA40 3 3 4 4 DA44 DA43 5 5 6 6 + DA40 DA44 DA43 DA45 7 7 8 8 1 1 9 9 2 2 3 3 4 4 5 5 6 6 7 7 8 8 TO GENERATOR CONTACTOR WHT T T DA21 DA23 DA25 DA30 DA22 D WHT PH29 DA35 DA36 PH32 2 3 4 5 2 3 4 5 PH9 DA33 DA34 PH31 WHT T T DA21 BLU/WHT U U DA23 DA30 TO RELAY DA22 LOAD BUS ALTERNATOR SHUNT D TO LIMITERS V V BLU/WHT W W GEN SHUNT TO RELAY LOAD BUS 9 9 DA24 DA24 BLU/WHT U U – 2 DA45 DA25 BATT SHUNT 3 DA42 DA39 DA38 TO GENERATOR CONTACTOR GEN SHUNT 1 DA41 2 BATT ALT DA37 DA37 4 GEN BATT SHUNT DA20 WHT PH29 DA35 DA36 PH32 2 3 4 5 2 3 4 5 PH9 DA33 DA34 PH31 TO LIMITERS V V BLU/WHT W W ALTERNATOR SHUNT DA20 TO BATTERY CONTACTOR TO BATTERY CONTACTOR Figure 24-9. Volt—Ammeter (Sheet 1 of 4) Figure 24-9. Volt—Ammeter (Sheet 2 of 4) 24 NOTES 24-26 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL LEGEND LEGEND BATTERY POWER BATTERY POWER GROUND SECONDARY POWER DA46 ALTERNATOR POWER FIRST DECK NO. 1 GENERATOR CONDITIONS: BATT POSITION SELECTED GENERATOR ON LINE VOLT 4 JUMPER SECONDARY POWER SECOND DECK AMMETER 3 1 DA41 2 BATT ALT DA37 4 GEN 1 DA40 CONDITIONS: GEN POSITION SELECTED GENERATOR ON LINE DA44 DA43 FIRST DECK NO. 1 GENERATOR – 2 DA42 DA39 DA38 3 + DA46 ALTERNATOR POWER VOLT 4 JUMPER SECOND DECK AMMETER 1 3 DA39 DA37 DA38 1 1 2 2 3 3 4 4 5 5 6 6 7 7 8 8 TO GENERATOR CONTACTOR 9 9 1 1 WHT T T BLU/WHT U U 4 4 DA22 D WHT 5 5 6 6 DA45 7 7 8 8 9 9 DA24 PH29 DA35 DA36 PH32 2 3 4 5 2 3 4 5 PH9 DA33 DA34 PH31 GEN SHUNT ALTERNATOR SHUNT WHT T T DA21 BLU/WHT U U DA23 DA30 TO RELAY DA22 LOAD BUS D TO LIMITERS V V BLU/WHT W W DA43 DA25 TO RELAY LOAD BUS BATT SHUNT DA44 DA42 DA40 3 3 – 2 DA30 DA21 DA23 3 + TO GENERATOR CONTACTOR DA24 DA25 GEN SHUNT 2 2 1 DA41 2 BATT ALT DA45 4 GEN DA20 BATT SHUNT TO BATTERY CONTACTOR WHT PH29 DA35 DA36 PH32 2 3 4 5 2 3 4 5 PH9 DA33 DA34 PH31 TO LIMITERS V V BLU/WHT W W ALTERNATOR SHUNT DA20 TO BATTERY CONTACTOR Figure 24-9. Volt—Ammeter (Sheet 3 of 4) Figure 24-9. Volt—Ammeter (Sheet 4 of 4) 24 NOTES Revision 0 FOR TRAINING PURPOSES ONLY 24-27 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 24 24-28 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CHAPTER 25 EQUIPMENT & FURNISHINGS INTRODUCTION 25 This chapter describes the equipment and furnishings of the flight and passenger compartments as well as the cargo area. In addition, the section on the emergency locator transmitter discusses five different versions available throughout the Cessna 208 fleet. FLIGHT COMPARTMENT - GENERAL The flight compartment equipment includes the pilot seat, optional copilot seat, seat belts, shoulder harnesses, and optional right side controls. Two beverage cup holders are underneath the forward edge of the instrument panel. On the 208 and 208B Passenger aircraft, the pilot and copilot seats have dual strap shoulder harness, lap belt, and inertia reel as one assembly. Shoulder harness and lap belts are bolted to the lower seat frame. The inertia reel is mounted at the bottom of the seat back frame. Sunvisors are standard equipment for the pilot and optional for the copilot. They are fully adjustable. On the 208B, the pilot and copilot seats have a five-point restraint system that consists of seat belts, crotch strap, and an inertia reel with double strap shoulderharness. Pilot and Copilot Seats The pilot seat and optional copilot seat are adjustable forward or aft and up or down. The angle of the seat also can be changed depending on the aircraft serial number. There are three variants of the seat belt layouts. Revision 0 FOR TRAINING PURPOSES ONLY 25-1 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES SCREW AIRPLANES 20800001 THRU 20800110 RIVET SPACER STOP BOLT SEAT PANEL PILOT OR COPILOT CREW SEAT SCREW RIVET STOP BOLT SPACER SPACER NUT NUT DETAIL A SPACER A SEAT PANEL ARMREST SEAT PANEL 25 PILOT OR COPILOT CREW SEAT PILOT OR COPILOT CREW SEAT FIVE-POINT RESTRAINT SYSTEM FIVE-POINT RESTRAINT SYSTEM CROTCH STRAP CROTCH STRAP AIRPLANES 2080011 THRU 20800237 AIRPLANES 208B0001 THRU 208B0381 AIRPLANES 20800238 AND SUBSEQUENT AIRPLANES 208B0382 AND SUBSEQUENT Figure 25-1. Pilot and Copilot Seats 25-2 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES EMERGENCY LOCATOR TRANSMITTER (ELT) A ELECTRICAL CONNETOR (PZ153) DETAIL A BNC CONNECTOR (PZ148) TO ELT ANTENNA BRACKET BUZZER 25 ELT STRAP ASSEMBLY FWD LATCH Figure 25-2. ME 406 ELT Revision 0 FOR TRAINING PURPOSES ONLY 25-3 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 25 25-4 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CHAPTER 26 FIRE PROTECTION 26 INTRODUCTION This chapter presents the fire protection system, which includes fire detection and fire extinguishing. Component location and operation as well as general maintenance considerations and functional and operational checks are covered. References for this chapter and further specific information can be found in Chapter 26—”Fire Protection”; Chapter 5—”Time Limits/Maintenance Checks” and Chapter 12— “Servicing” of the Manufacturer’s Maintenance Manual. (MMM) FIRE DETECTION SYSTEM The fire detection system detects an overheat condition or fire in the engine compartment, and alerts the crew by a visual and audible indication. The system consists of a heat detector loop, control box, alarm module, test switch, and annunciator warning light or CAS message on G1000 models. Revision 0 FOR TRAINING PURPOSES ONLY Bus 1 powers system components through the 5-amp FIRE DET circuit breaker 26-1 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES LEGEND LEGEND BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND DETECTION LOOP BATTERY POWER ALARM MODULE GROUND SIGNAL OR SENSE CONDITION: BATTERY ON FIREWALL CONTROL BOX OPERATE GRN YEL VIO ORN BLK 1 2 3 4 5 1 2 3 4 5 BRN RED 6 6 7 7 2 3 1 4 FD5 WC12 W WC10 H GRN YEL VIO ORN BLK 1 2 3 4 5 1 2 3 4 5 BRN RED 6 6 7 7 FD6 1 FF 46 20 GA. JUMPER FIRE DET WC8 Figure 26-1. Fire Warning Circuit (Sheet 1 of 3) 5 WC10 H FROM A/S WARNING MODULE 4 TEST 2 3 4 2 3 4 FD5 WC12 20 GA. JUMPER WC7 TO AUDIO PANEL W WC9 BLK YEL BRN VIO 3 WC5 WC6 WC3 WC1 ANNUNCIATOR PANEL FF 20 GA. JUMPER 5 2 OPERATE WC2 7 7 8 8 WC7 TO AUDIO PANEL WC1 WC11 20 GA. JUMPER WC4 CONTROL BOX 2 3 4 2 3 4 20 GA. JUMPER WC2 FROM A/S WARNING MODULE TEST WC5 WC6 WC3 FIREWALL CONDITION: BATTERY ON—HIGH TEMP BLK YEL BRN VIO 20 GA. JUMPER WC4 FIRE DET ALARM MODULE SECONDARY POWER SIGNAL OR SENSE WC9 DETECTION LOOP 7 7 8 8 WC11 FD6 ANNUNCIATOR PANEL 46 WC8 Figure 26-1. Fire Warning Circuit (Sheet 2 of 3) LEGEND BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND DETECTION LOOP ALARM MODULE SECONDARY POWER 26 FIREWALL CONDITION: BATTERY ON—TEST 20 GA. JUMPER WC4 2 CONTROL BOX OPERATE GRN YEL VIO ORN BLK 1 2 3 4 5 1 2 3 4 5 BRN RED 6 6 7 7 WC2 1 FF 20 GA. JUMPER FIRE DET 5 WC10 H 4 TEST 2 3 4 2 3 4 FD5 WC12 20 GA. JUMPER WC7 TO AUDIO PANEL W WC9 FROM A/S WARNING MODULE 3 WC5 WC6 WC3 WC1 BLK YEL BRN VIO 7 7 8 8 WC11 FD6 ANNUNCIATOR PANEL 46 WC8 Figure 26-1. Fire Warning Circuit (Sheet 3 of 3) 26-2 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CHAPTER 27 FLIGHT CONTROLS INTRODUCTION This chapter provides a description of the flight control system with special emphasis on components and operation. General maintenance considerations are included along with an introduction to functional and operational checks. References and further specific information are in Chapter 27— “Flight Controls”, Chapter 20—”Standard Practices-Airframe”, Chapter 5—”Time Limits/Maintenance Checks”, and Chapter 12—”Servicing” of the Manufacturer’s Maintenance Manual. GENERAL 27 The flight controls for the Caravan are conventional systems that provide roll, pitch and yaw control for the aircraft. The system consists of the following: • Aileron, elevator, and rudder control surfaces • Aileron, elevator, and rudder trim systems • Roll spoilers • Wing flaps Cockpit controls include pilot and copilot wheels for aileron and elevator controls. Rudder pedals are on the pilot and copilot sides of the cockpit floor. Rudder trim, aileron trim, and elevator trim wheels are located on the control pedestal. The primary flap selector handle and position indicator are also on the control pedestal. Circuit breakers for the system are the 10-amp FLAP MOTOR, 10amp STBY FLAP MOTOR, and 10-amp STALL. • Stall warning system Revision 0 FOR TRAINING PURPOSES ONLY 27-1 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES TRIM TAB AILERON SPOILER SPOILER AILERON SERVO TAB 27 CONTROL WHEELS Figure 27-1. Aileron Control System 27-2 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES ELEVATOR AFT BELLCRANK ELEVATOR 27 ELEVATOR FWD BELLCRANK Figure 27-2. Elevator Control System Revision 0 FOR TRAINING PURPOSES ONLY 27-3 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES RUDDER 27 RUDDER PEDALS Figure 27-3. Rudder System 27-4 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES INTERCONNECT ROD BELLCRANK AUXILIARY FLAP MOTOR INTERCONNECT ROD CONNECTING ROD PRIMARY FLAP MOTOR BARREL PUSHROD BELLCRANK D FW FLAP CABLE BELLCRANK 27 Figure 27-4. Flap Drive System Revision 0 FOR TRAINING PURPOSES ONLY 27-5 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES PINIION GEAR FLAP SWITCH ASSEMBLY 27 FLAP TRANSMISSION Figure 27-5. Flap System Components 27-6 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL LEGEND LEGEND BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER POSITIVE POWER OR SWITCHABLE POWER GROUND CC 53 CONDITION: FLAPS SELECTED UP CC 55 CC 30 d d CC 51 CC 51 CC 54 FLAP MOTOR CC 60 CC 58 CC 59 CC 63 10 CC 67 CC 66 f f CC 68 CC 65 BLK PRIMARY MOTOR 10 CC 30 d d CC 51 CC 51 CC 54 16 GA JUMPER MANUAL SWITCH STBY CC 56 CC 61 CC 70 CC 62 1 1 BLK YEL STANDBY MOTOR STANDBY FLAP MOTOR 10 DOWN CC 66 f f CC 65 16 GA JUMPER MANUAL SWITCH Figure 27-6. Legacy Series Normal Flap System (Sheet 1 of 3) CC 58 2 2 YEL BLK PRIMARY MOTOR UP DOWN SWITCH CC 64 1 1 NORM PRIMARY STANDBY SWITCH CC 63 2 2 CC 57 CC 60 CC 59 UP DOWN SWITCH CC 64 2 2 CC 55 YEL NORM PRIMARY STANDBY SWITCH CC 70 CC 62 STANDBY FLAP MOTOR 1 1 GIA63W AFCS 10K Ω CC 69 STBY CC 56 10K Ω CC 52 10K Ω CC 57 CC 61 CC 53 GIA63W AFCS CC 69 GUARDED TO NORM UP SWITCH 10K Ω CC 52 FLAP MOTOR 10 CONDITION: FLAPS STATIONARY GUARDED TO NORM UP SWITCH CC 67 2 2 CC 68 1 1 BLK YEL STANDBY MOTOR DOWN Figure 27-6. Legacy Series Normal Flap System (Sheet 2 of 3) NOTES LEGEND BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND GUARDED TO NORM UP SWITCH CC 53 CONDITION: FLAPS SELECTED DOWN 10K Ω CC 69 CC 55 CC 30 GIA63W AFCS CC 52 FLAP MOTOR 10 10K Ω d d CC 51 CC 51 CC 54 CC 56 CC 59 CC 70 CC 62 10 CC 66 f f CC 65 CC 58 2 2 YEL BLK PRIMARY MOTOR UP DOWN SWITCH CC 64 1 1 NORM PRIMARY STANDBY SWITCH CC 63 STANDBY FLAP MOTOR CC 57 CC 60 CC 61 27 STBY 16 GA JUMPER MANUAL SWITCH CC 67 2 2 CC 68 1 1 BLK YEL STANDBY MOTOR DOWN Figure 27-6. Legacy Series Normal Flap System (Sheet 3 of 3) Revision 0 FOR TRAINING PURPOSES ONLY 27-7 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL LEGEND LEGEND BATTERY POWER BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER POSITIVE POWER OR SWITCHABLE POWER GROUND GROUND SIGNAL OR SENSE CONDITION: FLAPS SELECTED UP CC 53 GIA63W AFCS CC 55 CC 30 d d CC 51 CC 51 CC 54 CC 58 CC 63 CC 67 CC 66 f f BLK PRIMARY MOTOR 10 CC 30 d d CC 51 CC 51 CC 54 CC 68 CC 65 16 GA JUMPER MANUAL SWITCH 10K Ω STBY CC 56 CC 61 CC 70 CC 62 1 1 BLK YEL STANDBY MOTOR STANDBY FLAP MOTOR 10 DOWN CC 66 f f CC 65 16 GA JUMPER MANUAL SWITCH Figure 27-7. Legacy Series Standby Flap System (Sheet 1 of 3) CC 58 2 2 YEL BLK PRIMARY MOTOR UP DOWN SWITCH CC 64 1 1 NORM PRIMARY STANDBY SWITCH CC 63 2 2 CC 57 CC 60 CC 59 UP DOWN SWITCH CC 64 2 2 CC 55 YEL NORM PRIMARY STANDBY SWITCH CC 70 CC 62 10 1 1 10K Ω GIA63W AFCS CC 52 FLAP MOTOR CC 60 CC 59 STANDBY FLAP MOTOR CC 53 CC 69 STBY CC 56 CC 57 CC 61 CONDITION: FLAPS UP / STATIONARY 10K Ω CC 69 GUARD OPEN STANDBY SELECTED UP SWITCH 10K Ω CC 52 FLAP MOTOR 10 SIGNAL OR SENSE GUARD OPEN STANDBY SELECTED UP SWITCH CC 67 2 2 CC 68 1 1 BLK YEL STANDBY MOTOR DOWN Figure 27-7. Legacy Series Standby Flap System (Sheet 2 of 3) NOTES LEGEND BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND SIGNAL OR SENSE GUARD OPEN STANDBY SELECTED UP SWITCH CC 53 CONDITION: FLAPS SELECTED DOWN 27 GIA63W AFCS CC 52 10K Ω CC 69 FLAP MOTOR CC 55 10 CC 30 d d CC 51 CC 51 CC 54 STBY CC 56 CC 59 CC 70 CC 62 CC 66 f f CC 65 CC 58 2 2 YEL BLK PRIMARY MOTOR UP DOWN SWITCH CC 64 1 1 NORM PRIMARY STANDBY SWITCH CC 63 10 CC 57 CC 60 CC 61 STANDBY FLAP MOTOR 10K Ω 16 GA JUMPER MANUAL SWITCH CC 67 2 2 CC 68 1 1 BLK YEL STANDBY MOTOR DOWN Figure 27-7. Legacy Series Standby Flap System (Sheet 3 of 3) 27-8 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL UP SWITCH UP SWITCH GUARD OPEN STANDBY SELECTED CC 53 CC 52 CC 52 CC 69 FLAP MOTOR CC 30 d d CC 51 CC 51 CC 54 CC 60 CC 61 CC 69 CC 56 CC 55 10 PRIMARY STANDBY SWITCH CC 57 CC 59 CC 58 1 1 2 2 YEL PRIMARY MOTOR BLK FLAP MOTOR CC 30 d d CC 51 CC 51 CC 67 CC 63 2 2 BLK PRIMARY STANDBY SWITCH CC 57 1 1 CC 59 CC 58 2 2 YEL PRIMARY MOTOR BLK NORM CC 70 CC 68 1 1 CC 66 DOWN MANUAL SWITCH 16 GA JUMPER CC 68 f f UP 2 2 BLK STANDBY MOTOR YEL STBY FLAP MOTOR CC 65 CC 67 CC 63 DOWN SWITCH STANDBY MOTOR f f CC 64 CC 60 CC 62 DOWN SWITCH 10 CC 54 CC 61 NORM CC 70 CC 56 CC 55 10 CC 62 STANDBY FLAP MOTOR GUARD OPEN STANDBY SELECTED CC 53 LEGEND 1 1 YEL STBY FLAP MOTOR BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND CONDITION: FLAPS SELECTED UP UP STANDBY FLAP MOTOR CC 66 10 CC 64 Figure 27-8. Caravan EX Standby Flap System (Sheet 1 of 3) DOWN CC 65 16 GA JUMPER MANUAL SWITCH LEGEND BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND CONDITION: FLAPS STATIONARY Figure 27-8. Caravan EX Standby Flap System (Sheet 2 of 3) NOTES UP SWITCH GUARD OPEN STANDBY SELECTED CC 53 CC 52 CC 69 FLAP MOTOR CC 56 CC 55 10 CC 30 d d CC 51 CC 51 CC 54 CC 60 CC 61 PRIMARY STANDBY SWITCH CC 57 1 1 CC 59 CC 58 2 2 YEL PRIMARY MOTOR BLK NORM CC 70 CC 62 CC 63 CC 67 2 2 CC 68 1 1 27 BLK DOWN SWITCH STANDBY MOTOR f f YEL STBY FLAP MOTOR UP STANDBY FLAP MOTOR CC 66 10 CC 64 DOWN CC 65 16 GA JUMPER LEGEND BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND CONDITION: FLAPS SELECTED DOWN MANUAL SWITCH Figure 27-8. Caravan EX Standby Flap System (Sheet 3 of 3) Revision 0 FOR TRAINING PURPOSES ONLY 27-9 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 27 27-10 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CHAPTER 28 FUEL INTRODUCTION The fuel system description is limited to the airframe fuel system in this chapter. Discussion begins with fuel storage. Components and operations are emphasized. General maintenance considerations are included. References are in Chapter 28—”Fuel”, Chapter 5—”Time Limits/Maintenance Checks”, and Chapter 12—”Servicing” of the Manufacturer’s Maintenance Manual. GENERAL The fuel system consist of one wet wing fuel tank in each wing, two fuel shutoff valves for each main tank, a fuel selectors off warning system, a float type fuel quantity indicating system, low fuel level sensors, reservoir tank, electric auxiliary fuel boost pump, main ejector pump, motive flow check valve, manifold assembly with low pressure switch, firewall shut-off valve, fuel filter and a EPA fuel canister. On S/N 5000 and on, the fuel system will have the following additional components installed: Larger inlet screens, Motive Flow Shutoff valve, Larger Fuel Oil Heat Exchanger, and Ecology Tank, along with the removal of the Fuel Filter &EPA Can. Revision 0 The two wing tanks of the fuel system hold a total of 332.0 usable gallons. Filling is through outboard (non-vented) filler caps as the fuel gravity feeds through shutoff valves. Each tank contains a low fuel sensor that illuminates an annunciator in the cockpit when quantity is 25 gallons or less. Fuel quantity indicators in each tank provide indication on the cockpit fuel gage. Approved fuels have been tested in the aircraft fuel delivery system to ensure they meet FAA certification requirements. The list i ncludes several types of jet fuel and avgas for emergency use only: FOR TRAINING PURPOSES ONLY • Jet A and Jet A-1 28 • Jet B • JP-1, JP-4, JP-5, JP-8 • Russian RT • Russian TS-1 Use of avgas and a nonspecific combination of avgas and jet fuel is limited to 150 hours between engine overhauls. A mixture of one part avgas and three parts jet fuel is limited to 450 hours between engine overhauls. 28-1 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL FUEL SELECT OFF RES FUEL LOW FUEL PRESS LOW AUX FUEL PMP ON FUEL LVL LOW L FUEL LVL LOW R FUEL LVL LO L-R TRQ 15 FUEL MANIFOLD FT–LB X100 10 20 1666 0 FUEL CAN AND DRAIN ITT VENT 600 FUEL FLOW TRANSDUCER 900 °C 700 0 12 % RPM 100 96.5 OIL PSI 95 OIL °C 85 L FUEL FILTER BYPASS INDICATOR 1900 PROP RPM ON FUEL CONTROL UNIT Ng 50 FLOW DIVIDER/ DUMP VALVE OFF ENGINE DRIVEN FUEL PUMP BATTERY FUEL HEATER ON NORM OFF FUEL BOOST FUEL FILTER START FIREWALL SHUTOFF VALVE FUEL QTY LBS R FIREWALL GEN FIELD STARTER 5 5 15 2 LEFT FUEL QTY AUX FUEL PUMP FUEL SEL WARN 5 10 MOTOR P 1 BOOST PUMP MAIN EJECTOR PUMP 379 GEN CONT OFF VENT RESERVOIR MANIFOLD ASSEMBLY FFLOW PPH START CONT RESERVOIR LOW-FUEL SENSOR ON OFF AVIONICS FUEL QUANTITY TRANSMITTERS FUEL QUANTITY TRANSMITTERS FUEL DRAIN RESERVOIR FUEL CAP FUEL CAP SHUTOFF VALVES 28 LEFT FUEL TANK RIGHT FUEL TANK FUEL LOW SWITCH FUEL LOW SWITCH FUEL SWITCH VENT WITH FLOAT VALVE AND PRESSURE RELIEF VALVE FUEL DRAINS SHUTOFF VALVES FUEL DRAINS VENT WITH FLOAT VALVE AND PRESSURE RELIEF VALVE Figure 28-1. Caravan G1000 Fuel System General Overview 28-2 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 28 Revision 0 FOR TRAINING PURPOSES ONLY 28-3 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL LEGEND RELAY ASSEMBLY 37 BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND 4 HORN NO 1 D5 P2 2 1 – + CONDITIONS: BATTERY ON RIGHT ON LEFT OFF NO WARNING 9 R1 7 10 BB 1/2 12 X1 1 5 d 2 X1 1 K3 D8 X X2 2 2 D9 D10 3 7 7 4 4 8 8 6 – + 2 1 P1 L LOW FUEL 10 12 32 D4 K3 X 5 2 2 D9 D10 6 7 7 4 4 8 8 K1 12 OPEN START SW ANNUNCIATOR TEST SWITCH P3 S4 OPEN 28 VDC Figure 28-2. Non-G1000 Fuel Select and Warning System (Sheet 1 of 7) – + b D6 2 1 P1 W GCU 9 D1 10 D2 3 4 8 6 L LOW FUEL 10 R LOW FUEL 12 X1 12 32 D4 X2 3 6 26 9 5 11 K2 RES LOW 2 P3 FUEL VALVE MONITOR SWITCHES CLOSED CLOSED S3 5 30 X2 d D8 X2 1 3 D3 P 2 X1 1 1 6 12 X1 1 START 3 HORN NO 2 OPEN BB 1/2 CLOSED CLOSED W GCU 11 FUEL SEL WARN FUEL VALVE MONITOR SWITCHES S2 10 11 P3 S1 R1 7 CIRCUIT BKR PANEL RES LOW 9 f CONDITIONS: BATTERY ON RIGHT OFF LEFT OFF HORN #1 ON LIGHT ON 9 D5 P2 2 1 – + 5 2 OPEN b D6 6 4 HORN NO 1 X2 4 R2 8 R LOW FUEL 12 X1 K2 9 RELAY ASSEMBLY 37 BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND 26 5 11 3 D7 HORN NO 2 D1 10 D2 6 CLOSED START SW 9 X2 P 3 5 K1 D3 START 5 3 11 11 1 6 CIRCUIT BKR PANEL FUEL SEL WARN 1 LEGEND 30 S1 R2 OPEN D7 CLOSED CLOSED S2 OPEN 12 9 f OPEN S3 CLOSED P3 ANNUNCIATOR TEST SWITCH S4 OPEN 28 VDC Figure 28-2. Non-G1000 Fuel Select and Warning System (Sheet 2 of 7) NOTES LEGEND RELAY ASSEMBLY 37 BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND 4 HORN NO 1 P2 2 1 – + CONDITIONS: BATTERY ON RIGHT OFF LEFT ON START ON HORN #1 ON HORN #2 ON LIGHT ON 9 D5 R1 7 11 3 1/2 5 28 K3 d D8 X2 X D10 6 7 4 4 8 8 3 6 4 – + b D6 2 1 P1 W GCU 6 L LOW FUEL 10 5 11 R LOW FUEL 12 X1 K2 8 12 32 D4 RES LOW 2 P3 FUEL VALVE MONITOR SWITCHES S1 CLOSED S2 OPEN 12 9 D7 HORN NO 2 10 D2 26 9 X2 OPEN R2 D1 3 CLOSED START SW 9 X2 P 2 X1 2 D9 7 K1 D3 START 3 1 12 X1 1 5 6 CIRCUIT BKR PANEL BB 1 5 2 10 11 FUEL SEL WARN 1 30 f CLOSED OPEN S3 CLOSED S4 OPEN P3 ANNUNCIATOR TEST SWITCH 28 VDC Figure 28-2. Non-G1000 Fuel Select and Warning System (Sheet 3 of 7) 28-4 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL LEGEND RELAY ASSEMBLY 37 BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND 4 HORN NO 1 D5 P2 2 1 – + CONDITIONS: BATTERY ON RIGHT ON LEFT ON START ON HORN #1 OFF HORN #2 OFF LIGHT OFF 9 R1 7 10 BB 1/2 5 2 X1 K3 X2 X 2 2 D9 D10 6 7 7 4 4 8 8 3 6 4 – + b D6 2 1 P1 W GCU 6 L LOW FUEL 10 R LOW FUEL 12 X1 f 4 HORN NO 1 12 32 D4 CLOSED OPEN BB 1/2 5 K3 X CLOSED 5 2 2 D9 D10 6 7 7 4 4 8 8 K1 12 P3 START SW ANNUNCIATOR TEST SWITCH S4 OPEN – + 28 VDC Figure 28-2. Non-G1000 Fuel Select and Warning System (Sheet 4 of 7) b D6 2 1 P1 W GCU 9 D1 10 D2 3 4 8 6 L LOW FUEL 10 R LOW FUEL 12 X1 12 32 D4 X2 3 6 26 9 5 11 K2 RES LOW 2 P3 FUEL VALVE MONITOR SWITCHES CLOSED CLOSED OPEN 5 30 X2 d D8 X2 1 3 D3 P 2 X1 1 1 6 12 X1 1 START 3 HORN NO 2 S3 11 FUEL SEL WARN FUEL VALVE MONITOR SWITCHES S2 10 11 P3 S1 R1 7 CIRCUIT BKR PANEL RES LOW 2 9 D5 P2 2 1 – + CONDITIONS: BATTERY ON RIGHT ON LEFT ON RIGHT FUEL LOW RIGHT LOW LIGHT ON HORN #1 OFF LIGHT OFF 5 11 K2 8 9 D7 HORN NO 2 10 D2 9 RELAY ASSEMBLY 37 BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND 26 X2 OPEN R2 D1 3 CLOSED START SW 9 X2 d D8 5 K1 D3 P 3 1 12 X1 1 START 5 3 11 11 1 6 CIRCUIT BKR PANEL FUEL SEL WARN 1 LEGEND 30 S1 R2 OPEN D7 CLOSED CLOSED S2 OPEN 12 9 f OPEN S3 CLOSED P3 ANNUNCIATOR TEST SWITCH S4 OPEN 28 VDC Figure 28-2. Non-G1000 Fuel Select and Warning System (Sheet 5 of 7) NOTES 28 Revision 0 FOR TRAINING PURPOSES ONLY 28-5 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL LEGEND RELAY ASSEMBLY 37 BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND 4 HORN NO 1 D5 P2 2 1 – + CONDITIONS: BATTERY ON RIGHT ON LEFT OFF RIGHT FUEL LOW RIGHT LOW LIGHT ON HORN #1 ON LIGHT ON 9 R1 7 10 BB 1/2 5 2 X1 K3 2 2 D9 D10 6 – + b D6 2 1 P1 W GCU 10 D2 7 7 4 4 8 8 9 8 6 L LOW FUEL 10 R LOW FUEL 12 X1 4 HORN NO 1 X 6 4 32 5 RES LOW K3 OPEN f CLOSED 12 P3 START SW ANNUNCIATOR TEST SWITCH HORN NO 2 OPEN S3 5 2 2 D9 D10 6 7 7 4 4 8 8 K1 S4 OPEN – + 28 VDC Figure 28-2. Non-G1000 Fuel Select and Warning System (Sheet 6 of 7) b D6 2 1 P1 W GCU 9 D1 10 D2 3 4 8 6 L LOW FUEL 10 R LOW FUEL 12 X1 12 32 D4 X2 3 6 26 9 5 11 K2 RES LOW 2 P3 FUEL VALVE MONITOR SWITCHES CLOSED 9 CLOSED X 5 30 X2 d D8 X2 1 3 D3 P 2 X1 1 6 12 X1 1 START 3 CLOSED S2 BB 1/2 D4 FUEL VALVE MONITOR SWITCHES S1 11 FUEL SEL WARN P3 OPEN R2 10 11 12 2 R1 7 CIRCUIT BKR PANEL X2 3 9 D5 P2 2 1 – + CONDITIONS: PUSH TO TEST 5 11 K2 BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND 26 RELAY ASSEMBLY 37 1 D7 HORN NO 2 D1 3 CLOSED START SW 9 X2 d D8 X2 5 K1 D3 P 3 1 12 X1 1 START 5 3 11 11 1 6 CIRCUIT BKR PANEL FUEL SEL WARN 1 LEGEND 30 S1 R2 OPEN D7 CLOSED CLOSED S2 OPEN 12 9 f OPEN S3 CLOSED P3 ANNUNCIATOR TEST SWITCH S4 OPEN 28 VDC Figure 28-2. Non-G1000 Fuel Select and Warning System (Sheet 7 of 7) NOTES 28 28-6 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL JS001 PS001 DOOR POST/RH WING JR007 PR007 LOW FUEL SW 16 (20) (20) A B C GR002 REFER TO 91-20-02 FUEL SELECT OFF NOTES SR002 LOW FUEL SW DECENDING FUEL R FUEL TANK FUEL SELECT OFF – One or both fuel tank selectors are off. GDU PFDs OFF UI005 GEA 71 PC001 JC001 ELEFUS/L DOOR POST PI001 R FUEL SELECT SW OFF (20) (20) 12 71 10 12 (20) (20) ON NO SR001 R FUEL SELECT SW C NC JC035 PC035A PC035B AUX FUEL PUMP RESERVOIR LOW FUEL 41 5 5 RESERVOIR TANK FLOAT SWITCH OFF PC043 JC043 ELEFUS/L DOOR POST RIGHT LOW FUEL 3 1 (20) JM001 PM001 DOOR POST/LH WING L FUEL SELECT SW OFF 70 6 (20) 22 12 (20) LEFT LOW FUEL 2 FUEL SELECT WARN HORN (GND) FUEL SELECT WARN HORN (GND) 2 3 ON (20) (20) NO C NC 5 SL001 L FUEL SELECT SW GC002 GND PI002 B (20) JL007 PL007 LOW FUEL SW (20) 16 (20) (20) GL003 REFER TO 91-20-02 SL002 LOW FUEL SW A B C DECENDING FUEL L FUEL TANK SI031 TEST WARN UI006 #1 GIA63W PI507 P605 FUEL SELECT WARN CB ENGAGE 16 PI005 JI005 AVN/ELECT DISC 34 (20) GC001 GND (REFER TO FIRE DETECT) 26-10-01 (20) (20) F UI007 #2 GIA63W PI506 P605 FUEL SELECT WARN CB ENGAGE 3 1 5 6 4 FIRE WARN (MOM) OFF FUEL WARN (MOM) 16 DC003 JC005 PC005 L CB PNL LEGEND BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND 2 BB (20) BLK WHT JC047 PC047 ELEFUS/L DOORPOST (20) (20) 2 1 JC045 PC045 WARN HORN (20) (20) 2 1 (20) (20) – (20) + UC004 SONALERT FUEL SEL WARN 28 VDC REFER TO 24-60-03 28 DC004 WHT BLK (20) (20) 3 (20) 3 (20) + – UC003 SONALERT CONDITIONS: FUEL SELECTORS—OFF L AND R SELECTORS—OFF BATTERY SWITCH—ON AVIONICS SWITCHES—1 AND 2 ON HORNS—ONE SOUNDING Figure 28-3. G1000 Fuel Select and Warning (Sheet 1 of 5) Revision 0 FOR TRAINING PURPOSES ONLY 28-7 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL JS001 PS001 DOOR POST/RH WING JR007 PR007 LOW FUEL SW 16 (20) (20) A B C GR002 REFER TO 91-20-02 FUEL SELECT OFF NOTES SR002 LOW FUEL SW DECENDING FUEL R FUEL TANK FUEL SELECT OFF – One or both fuel tank selectors are off. GDU PFDs OFF UI005 GEA 71 PC001 JC001 ELEFUS/L DOOR POST PI001 R FUEL SELECT SW OFF (20) (20) 12 71 10 12 (20) (20) ON NO SR001 R FUEL SELECT SW C NC JC035 PC035A PC035B AUX FUEL PUMP RESERVOIR LOW FUEL 41 5 5 RESERVOIR TANK FLOAT SWITCH OFF PC043 JC043 ELEFUS/L DOOR POST RIGHT LOW FUEL 3 1 (20) JM001 PM001 DOOR POST/LH WING L FUEL SELECT SW OFF 70 6 (20) 22 12 (20) LEFT LOW FUEL 2 FUEL SELECT WARN HORN (GND) FUEL SELECT WARN HORN (GND) 2 3 ON (20) (20) NO C NC 5 SL001 L FUEL SELECT SW GC002 GND PI002 B (20) JL007 PL007 LOW FUEL SW (20) 16 (20) (20) GL003 REFER TO 91-20-02 SL002 LOW FUEL SW A B C DECENDING FUEL L FUEL TANK SI031 TEST WARN UI006 #1 GIA63W PI507 P605 FUEL SELECT WARN CB ENGAGE 16 PI005 JI005 AVN/ELECT DISC 34 (20) GC001 GND (REFER TO FIRE DETECT) 26-10-01 (20) (20) F UI007 #2 GIA63W PI506 P605 FUEL SELECT WARN CB ENGAGE 3 1 5 6 4 FIRE WARN (MOM) OFF FUEL WARN (MOM) 16 DC003 JC005 PC005 L CB PNL BB 28 2 LEGEND BATTERY POWER GROUND (20) WHT BLK JC047 PC047 ELEFUS/L DOORPOST (20) (20) JC045 PC045 WARN HORN 2 1 (20) (20) 2 1 (20) (20) 3 (20) 3 (20) – (20) + UC004 SONALERT FUEL SEL WARN 28 VDC REFER TO 24-60-03 DC004 WHT BLK (20) (20) + – UC003 SONALERT CONDITIONS: START CONTROL AND FUEL SELECT CBs—IN R FUEL SELECTOR—OFF BATTERY SWITCH—ON AVIONICS SWITCHES—1 AND 2 ON START SWITCH—START BOTH HORNS—SOUNDING Figure 28-3. G1000 Fuel Select and Warning (Sheet 2 of 5) 28-8 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL JS001 PS001 DOOR POST/RH WING JR007 PR007 LOW FUEL SW 16 FUEL SELECT OFF (20) (20) FUEL SELECT OFF – One or both fuel tank selectors are off. FUEL LVL R LOW A B C GR002 REFER TO 91-20-02 NOTES SR002 LOW FUEL SW DECENDING FUEL R FUEL TANK FUEL LVL LOW R – Right fuel tank is low. GDU PFDs OFF UI005 GEA 71 PC001 JC001 ELEFUS/L DOOR POST PI001 R FUEL SELECT SW OFF (20) (20) 12 71 10 12 (20) (20) ON NO SR001 R FUEL SELECT SW C NC JC035 PC035A PC035B AUX FUEL PUMP RESERVOIR LOW FUEL 41 5 5 RESERVOIR TANK FLOAT SWITCH OFF PC043 JC043 ELEFUS/L DOOR POST RIGHT LOW FUEL 3 1 (20) JM001 PM001 DOOR POST/LH WING L FUEL SELECT SW OFF 70 6 (20) 22 12 (20) LEFT LOW FUEL 2 FUEL SELECT WARN HORN (GND) FUEL SELECT WARN HORN (GND) 2 3 ON (20) (20) NO C NC 5 SL001 L FUEL SELECT SW GC002 GND PI002 B (20) JL007 PL007 LOW FUEL SW (20) 16 (20) (20) GL003 REFER TO 91-20-02 SL002 LOW FUEL SW A B C DECENDING FUEL L FUEL TANK SI031 TEST WARN UI006 #1 GIA63W PI507 P605 FUEL SELECT WARN CB ENGAGE 16 PI005 JI005 AVN/ELECT DISC 34 (20) GC001 GND (REFER TO FIRE DETECT) 26-10-01 (20) (20) F UI007 #2 GIA63W PI506 P605 FUEL SELECT WARN CB ENGAGE 2 3 1 5 6 4 FIRE WARN (MOM) OFF FUEL WARN (MOM) 16 LEGEND BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND DC003 JC005 PC005 L CB PNL BB (20) JC047 PC047 ELEFUS/L DOORPOST (20) (20) 2 1 JC045 PC045 WARN HORN (20) (20) 2 1 (20) (20) – (20) + UC004 SONALERT FUEL SEL WARN 28 VDC REFER TO 24-60-03 28 DC004 WHT CONDITIONS: START CONTROL AND FUEL SELECT CBs—IN R FUEL SELECTOR—ON L FUEL SELECTOR—OFF BATTERY SWITCH—ON AVIONICS SWITCHES—1 AND 2 ON R FUEL LEVEL—25 GALS OR LESS HORNS UC004—SOUNDING BLK WHT BLK (20) (20) 3 (20) 3 (20) + – UC003 SONALERT Figure 28-3. G1000 Fuel Select and Warning (Sheet 3 of 5) Revision 0 FOR TRAINING PURPOSES ONLY 28-9 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL JS001 PS001 DOOR POST/RH WING JR007 PR007 LOW FUEL SW (20) (20) 16 FUEL SELECT OFF FUEL SELECT OFF – One or both fuel tank selectors are off. FUEL LVL L LOW A B C GR002 REFER TO 91-20-02 NOTES SR002 LOW FUEL SW DECENDING FUEL R FUEL TANK FUEL LVL LOW L – Left fuel tank is low. GDU PFDs OFF UI005 GEA 71 PC001 JC001 ELEFUS/L DOOR POST PI001 R FUEL SELECT SW OFF (20) (20) 12 71 10 12 (20) (20) ON NO SR001 R FUEL SELECT SW C NC JC035 PC035A PC035B AUX FUEL PUMP RESERVOIR LOW FUEL 41 5 5 RESERVOIR TANK FLOAT SWITCH OFF PC043 JC043 ELEFUS/L DOOR POST RIGHT LOW FUEL 3 1 (20) JM001 PM001 DOOR POST/LH WING L FUEL SELECT SW OFF 70 6 (20) 22 12 (20) LEFT LOW FUEL 2 FUEL SELECT WARN HORN (GND) FUEL SELECT WARN HORN (GND) 2 3 ON (20) (20) NO SL001 L FUEL SELECT SW C NC 5 GC002 GND PI002 B (20) JL007 PL007 LOW FUEL SW (20) 16 (20) (20) GL003 REFER TO 91-20-02 SL002 LOW FUEL SW A B C DECENDING FUEL L FUEL TANK SI031 TEST WARN UI006 #1 GIA63W PI507 P605 FUEL SELECT WARN CB ENGAGE 16 JI005 PI005 AVN/ELECT DISC 34 (20) GC001 GND (REFER TO FIRE DETECT) 26-10-01 (20) (20) F UI007 #2 GIA63W PI506 P605 FUEL SELECT WARN CB ENGAGE 3 1 5 6 4 FIRE WARN (MOM) OFF FUEL WARN (MOM) 16 LEGEND BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER 28 2 GROUND DC003 JC005 PC005 L CB PNL BB (20) WHT JC047 PC047 ELEFUS/L DOORPOST (20) (20) JC045 PC045 WARN HORN 2 1 (20) (20) 2 1 (20) (20) 3 (20) 3 (20) – (20) + UC004 SONALERT FUEL SEL WARN 28 VDC REFER TO 24-60-03 DC004 WHT CONDITIONS: START CONTROL AND FUEL SELECT CBs—IN R FUEL SELECTOR—OFF L FUEL SELECTOR—ON BATTERY SWITCH—ON AVIONICS SWITCHES—1 AND 2 ON L FUEL LEVEL—25 GALS OR LESS HORNS UC004—SOUNDING BLK BLK (20) (20) + – UC003 SONALERT Figure 28-3. G1000 Fuel Select and Warning (Sheet 4 of 5) 28-10 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL JS001 PS001 DOOR POST/RH WING JR007 PR007 LOW FUEL SW 16 (20) (20) A B C GR002 REFER TO 91-20-02 FUEL SELECT OFF NOTES SR002 LOW FUEL SW DECENDING FUEL R FUEL TANK FUEL SELECT OFF – One or both fuel tank selectors are off. GDU PFDs OFF UI005 GEA 71 PC001 JC001 ELEFUS/L DOOR POST PI001 R FUEL SELECT SW OFF (20) (20) 12 71 10 12 (20) (20) ON NO SR001 R FUEL SELECT SW C NC JC035 PC035A PC035B AUX FUEL PUMP RESERVOIR LOW FUEL 41 5 5 RESERVOIR TANK FLOAT SWITCH OFF PC043 JC043 ELEFUS/L DOOR POST RIGHT LOW FUEL 3 1 (20) JM001 PM001 DOOR POST/LH WING L FUEL SELECT SW OFF 70 6 (20) 22 12 (20) LEFT LOW FUEL 2 FUEL SELECT WARN HORN (GND) FUEL SELECT WARN HORN (GND) 2 3 ON (20) (20) NO C NC 5 SL001 L FUEL SELECT SW GC002 GND PI002 B (20) JL007 PL007 LOW FUEL SW (20) 16 (20) (20) GL003 REFER TO 91-20-02 SL002 LOW FUEL SW A B C DECENDING FUEL L FUEL TANK SI031 TEST WARN UI006 #1 GIA63W PI507 P605 FUEL SELECT WARN CB ENGAGE 16 PI005 JI005 AVN/ELECT DISC 34 (20) GC001 GND (REFER TO FIRE DETECT) 26-10-01 (20) (20) F UI007 #2 GIA63W PI506 P605 FUEL SELECT WARN CB ENGAGE 2 3 1 5 6 4 FIRE WARN (MOM) OFF FUEL WARN (MOM) 16 DC003 JC005 PC005 L CB PNL LEGEND BATTERY POWER GROUND CONDITIONS: START CONTROL AND FUEL SELECT CBs—IN R FUEL SELECTOR—ON L FUEL SELECTOR—ON BATTERY SWITCH—ON AVIONICS SWITCHES—1 AND 2 ON FUEL SELECT OFF, TEST SWITCH—DOWN BOTH HORNS—SOUNDING BB (20) WHT BLK JC047 PC047 ELEFUS/L DOORPOST (20) (20) 2 1 JC045 PC045 WARN HORN (20) (20) 2 1 (20) (20) – (20) + UC004 SONALERT FUEL SEL WARN 28 VDC REFER TO 24-60-03 28 DC004 WHT BLK (20) (20) 3 (20) 3 (20) + – UC003 SONALERT Figure 28-3. G1000 Fuel Select and Warning (Sheet 5 of 5) Revision 0 FOR TRAINING PURPOSES ONLY 28-11 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL FUEL INLET FROM AUX PUMP NOTES FROM MAIN EJECTOR VENT OUTLET FLAPPER CHECK VALVE (FOUR EACH) VENT OUTLET VENT LINE FUEL INLET (FOUR EACH) LOW LEVEL SWITCH MAIN EJECTOR PUMP MOTIVE FLOW CHECK VALVE AUXILIARY ELECTRIC FUEL PUMP 28 DRAIN VALVE Figure 28-4. Fuel Reservoir 28-12 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL AUX FUEL 10 PUMP QA1 FUEL BOOST 3 2 1 6 4 5 QA16 R R QA2 QA13 QA15 e e WW QA17 AUX FUEL 10 PUMP KK QA3 PRESSURE SWITCH BLK (REF) 1 1 QA5 4 4 QA6 QA12 QA14 RED (REF) WHT (REF) QA4 2 2 QA7 QA1 AUX FUEL PUMP QA10 QA11 FUEL BOOST 3 2 1 6 4 5 QA16 R R QA2 QA13 QA15 e e WW QA17 AUX FUEL 10 PUMP KK 3 5 QA3 PRESSURE SWITCH 3 5 BLK (REF) FUEL PUMP RELAY QA5 4 4 QA6 QA12 QA14 RED (REF) QA4 WHT (REF) OPEN > 6.0 PSI CLOSED < 4.75 PSI 1 1 2 2 QA7 QA10 QA11 G1000 ONLY 26 29 QA8 QA9 ANNUNCIATOR PANEL LEGEND POSITIVE POWER OR SWITCHABLE POWER GROUND 4 Figure 28-5. Auxiliary Fuel Pump (Sheet 1 of 6) R R QA2 QA13 QA15 e e WW QA17 KK QA3 PRESSURE SWITCH 3 5 BLK (REF) FUEL PUMP RELAY 1 1 QA5 4 4 QA6 QA12 2 2 QA7 QA14 RED (REF) WHT (REF) QA4 AUX FUEL PUMP QA10 3 5 QA11 3 5 FUEL PUMP RELAY OPEN > 6.0 PSI CLOSED < 4.75 PSI GEA71 FUEL PRESSURE LOW AUX FUEL PUMP ON G1000 ONLY CONDITIONS: OFF SELECTED PRESSURE < 4.75 PSI ENGINE NOT RUNNING 5 QA16 3 5 GEA71 65 71 6 OPEN > 6.0 PSI CLOSED < 4.75 PSI GEA71 FUEL PRESSURE LOW AUX FUEL PUMP ON QA1 AUX FUEL PUMP FUEL BOOST 3 2 1 65 71 26 29 QA8 QA9 ANNUNCIATOR PANEL LEGEND BATTERY POWER GROUND FUEL PRESSURE LOW AUX FUEL PUMP ON G1000 ONLY CONDITIONS: ON SELECTED RELAY ENERGIZED PUMP RUNNING Figure 28-5. Auxiliary Fuel Pump (Sheet 2 of 6) 65 71 26 29 QA8 QA9 ANNUNCIATOR PANEL LEGEND POSITIVE POWER OR SWITCHABLE POWER CONDITIONS: NORM SELECTED PRESSURE > 6.0 PSI PRESSURE SWITCH OPEN Figure 28-5. Auxiliary Fuel Pump (Sheet 3 of 6) NOTES 28 Revision 0 FOR TRAINING PURPOSES ONLY 28-13 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL AUX FUEL 10 PUMP QA1 FUEL BOOST 3 2 1 6 4 5 QA16 R R QA2 QA13 QA15 e e WW QA17 AUX FUEL 10 PUMP KK QA3 PRESSURE SWITCH BLK (REF) 1 1 QA5 4 4 QA6 QA12 QA14 RED (REF) WHT (REF) QA4 2 2 QA7 QA1 AUX FUEL PUMP QA10 QA11 FUEL BOOST 3 2 1 6 4 5 QA16 R R QA2 QA13 QA15 e e WW QA17 AUX FUEL 10 PUMP KK 3 5 QA3 PRESSURE SWITCH 3 5 BLK (REF) FUEL PUMP RELAY QA5 4 4 QA6 QA12 QA14 RED (REF) QA4 WHT (REF) OPEN > 6.0 PSI CLOSED < 4.75 PSI 1 1 2 2 QA7 QA10 QA11 G1000 ONLY 26 29 QA8 QA9 ANNUNCIATOR PANEL LEGEND POSITIVE POWER OR SWITCHABLE POWER GROUND 4 Figure 28-5. Auxiliary Fuel Pump (Sheet 4 of 6) R R QA2 QA13 QA15 e e WW QA17 KK QA3 PRESSURE SWITCH 3 5 BLK (REF) FUEL PUMP RELAY 1 1 QA5 4 4 QA6 QA12 2 2 QA7 QA14 RED (REF) WHT (REF) QA4 AUX FUEL PUMP QA10 3 5 QA11 3 5 FUEL PUMP RELAY OPEN > 6.0 PSI CLOSED < 4.75 PSI GEA71 FUEL PRESSURE LOW AUX FUEL PUMP ON G1000 ONLY CONDITIONS: OFF SELECTED PRESSURE < 4.75 PSI ENGINE NOT RUNNING 5 QA16 3 5 GEA71 65 71 6 OPEN > 6.0 PSI CLOSED < 4.75 PSI GEA71 FUEL PRESSURE LOW AUX FUEL PUMP ON QA1 AUX FUEL PUMP FUEL BOOST 3 2 1 65 71 26 29 QA8 QA9 ANNUNCIATOR PANEL LEGEND BATTERY POWER GROUND FUEL PRESSURE LOW AUX FUEL PUMP ON G1000 ONLY CONDITIONS: ON SELECTED RELAY ENERGIZED PUMP RUNNING Figure 28-5. Auxiliary Fuel Pump (Sheet 5 of 6) 65 71 26 29 QA8 QA9 ANNUNCIATOR PANEL LEGEND POSITIVE POWER OR SWITCHABLE POWER CONDITIONS: NORM SELECTED PRESSURE > 6.0 PSI PRESSURE SWITCH OPEN Figure 28-5. Auxiliary Fuel Pump (Sheet 6 of 6) NOTES 28 28-14 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES RH FUEL QUANTITY 5 EB1 J J EB14 A C B RH WING RH FUEL INDICATOR EB11 3 EB2 2 2 EB23 EB7 3 3 EB24 3 EB3 EB6 DD DD EB13 EB17 EB18 3 EB8 LH WING 5 XMTR6 INBD 3 LH FUEL QUANTITY XMTR4 INBD XMTR5 EB20 XMTR8 XMTR3 B A C EB21 LH FUEL INDICATOR EB19 XMTR7 OUTBD EB12 EB22 H XMTR10 EB5 OUTBD XMTR9 LEGEND CONDITIONS: FUEL QUANTITY INDICATING BATTERY SWITCH—ON BATTERY POWER GROUND EB10 SECONDARY POWER Figure 28-6. Non-G1000 Fuel Quantity Indicating (Sheet 1 of 4) RH FUEL QUANTITY 5 EB1 J J A C B EB14 RH WING RH FUEL INDICATOR EB11 3 EB2 2 2 EB23 EB7 3 3 EB24 3 EB3 EB6 DD DD EB17 EB18 3 EB8 LH WING 5 XMTR6 INBD 3 LH FUEL QUANTITY OPEN CIRCUIT XMTR4 INBD XMTR5 EB20 XMTR8 XMTR3 B A C EB13 LH FUEL INDICATOR EB21 EB19 XMTR7 OUTBD EB12 XMTR10 EB5 OUTBD XMTR9 LEGEND BATTERY POWER GROUND SECONDARY POWER 28 EB22 H CONDITIONS: FUEL QUANTITY INDICATING BATTERY SWITCH—ON OPEN CIRCUIT—MAXIMUM QUANTITY INDICATION RH EB10 Figure 28-6. Non-G1000 Fuel Quantity Indicating (Sheet 2 of 4) Revision 0 FOR TRAINING PURPOSES ONLY 28-15 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES RH FUEL QUANTITY 5 EB1 J J EB14 A C B RH WING RH FUEL INDICATOR EB11 3 EB2 2 2 EB23 EB7 3 3 EB24 3 EB3 EB6 DD DD EB13 EB17 EB18 3 EB8 LH WING 5 XMTR6 INBD 3 LH FUEL QUANTITY SHORT CIRCUIT XMTR4 INBD XMTR5 EB20 XMTR8 XMTR3 B A C EB21 LH FUEL INDICATOR EB19 XMTR7 OUTBD EB12 EB22 H XMTR10 EB5 OUTBD XMTR9 LEGEND CONDITIONS: FUEL QUANTITY INDICATING BATTERY SWITCH—ON SHORT CIRCUIT—LOW QUANTITY INDICATION RH BATTERY POWER GROUND SECONDARY POWER EB10 Figure 28-6. Non-G1000 Fuel Quantity Indicating (Sheet 3 of 4) RH FUEL QUANTITY 5 EB1 J J EB14 A C B RH WING RH FUEL INDICATOR EB11 3 EB2 2 2 EB23 EB7 3 3 EB24 3 EB3 EB18 3 EB8 LH WING 5 EB6 DD DD EB13 B A C LH FUEL INDICATOR XMTR6 EB17 INBD 3 LH FUEL QUANTITY XMTR4 INBD XMTR5 EB20 XMTR8 XMTR3 EB21 230 OHM RESISTOR EB19 XMTR7 OUTBD EB12 28 EB22 H XMTR10 EB5 OUTBD XMTR9 LEGEND BATTERY POWER GROUND CONDITIONS: FUEL QUANTITY INDICATING BATTERY SWITCH—ON CALIBRATE FULL EB10 SECONDARY POWER Figure 28-6. Non-G1000 Fuel Quantity Indicating (Sheet 4 of 4) 28-16 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL LEGEND UR002 R FUEL LEVEL SENSOR (OUTBD) PR002 BATTERY POWER 11 13 8 9 6 12 5 GROUND SIGNAL OR SENSE CONDITIONS: BATTERY ON NOTES CONFIG RETURN CONFIG 3 CONFIG 2 CONFIG 1 CONFIG 0 CAN TERM RES START CAN TERM RES END 120Ω (WHT) (BLU) (BLU) (WHT) 2 1 3 4 GROUND 28 VDC CAN (HI) CAN (LO) 1 UR001 R FUEL LEVEL SENSOR (INBD) PR001 11 13 8 9 6 12 5 JS001 PS001 L DOOR POST/R WING CONFIG RETURN CONFIG 3 CONFIG 2 CONFIG 1 CONFIG 0 CAN TERM RES START CAN TERM RES END 120Ω PC043 JC043 CAB/L DOOR POST JC011 PC011 L CB PNL R FUEL QTY 28 VDC J 5 REFER TO 24-60-03 (20) AC006 (WHT) (20) (BLU) (20) 2 3 (WHT) (20) (BLU) (20) (BLU) (20) (WHT) (20) 4 10 11 (BLU) (20) (WHT) (20) (WHT) (20) (BLU) (20) 12 13 (BLU) (20) (WHT) (20) 14 15 16 GC001 GND 17 3 (WHT) (BLU) 4 3 18 19 20 (BLU) (WHT) 1 2 CAN (LO) CAN (HI) 28 VDC GROUND 1 L U M JC005 PC005 L CB PNL L FUEL QTY 28 VDC DD 5 (20) AC007 REFER TO 24-60-03 JM001 PM001 L DOOR POST/L WING UL001 L FUEL LEVEL SENSOR (INBD) PL001 (WHT) (20) (BLU) (20) 14 15 (WHT) (BLU) 2 1 (BLU) (20) (WHT) (20) 3 18 20 (BLU) (WHT) 3 4 GROUND 28 VDC CAN (HI) CAN (LO) 120Ω 5 12 6 9 8 13 11 JI005 PI005 ELE/AVN DISC UI007 GIA2 (WHT) (20) (BLU) (20) 14 15 1 PI502 CAN BUS (LO) CAN BUS (HI) 30 32 UL002 L FUEL LEVEL SENSOR (OUTBD) PL002 (WHT) (BLU) (BLU) (WHT) UI006 GIA1 4 3 1 2 32 30 28 CAN (LO) CAN (HI) 28 VDC GROUND 120Ω PI503 CAN BUS (HI) CAN BUS (LO) CAN TERM RES END CAN TERM RES START CONFIG 0 CONFIG 1 CONFIG 2 CONFIG 3 CONFIG RETURN 5 12 6 9 8 13 11 (BLU) (20) (WHT) (20) (BLU) (20) (WHT) (20) 16 17 26 CAN TERM RES END CAN TERM RES START CONFIG 0 CONFIG 1 CONFIG 2 CONFIG 3 CONFIG RETURN 1 Figure 28-7. G1000 Fuel Quantity Indicating Revision 0 FOR TRAINING PURPOSES ONLY 28-17 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 28 28-18 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CHAPTER 30 ICE AND RAIN PROTECTION INTRODUCTION This chapter presents the ice and rain protection systems. Emphasis is on component location and operation. Discussions include methods of ice protection and removal. General maintenance considerations are included along with an introduction to operational and functional checks. References for this chapter and further specific information are in Chapter 30—”Ice and Rain Protection”, Chapter 5—”Time Limits and Maintenance Checks”, and Chapter 12—”Servicing” of the Manufacturer’s Maintenance Manual. GENERAL The ice and rain protection systems detect, remove, or prevent ice formation on critical surfaces of the aircraft. Pneumatic deice boots protect the wing surfaces while electrothermal boots protect the propeller. Electrical heaters are available for the stall warning vane, pitot probe, and windshield. The DEICE/ANTI-ICE panel on the lower left instrument panel controls the various systems. Revision 0 FOR TRAINING PURPOSES ONLY These items coupled with an airspeed awareness system and ice detection lights fulfill the FAA regulations for flight into known icing conditions. 208 units 500 and on and 208B units 2000 and on are ice protected with an optional TKS porous system. 30-1 30 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES PROPELLER BOOTS LEFT WING PANELS RIGHT WING PANELS W/S SPRAY BAR PROPORTIONING UNIT PROPELLER NOZZLE PROPORTIONING UNIT STRUT PANELS STRUT PANELS FILTERS LEVEL SENDER VENT LOW LEVEL SWITCH TANK SOLENOID VALVE PROPORTIONING UNIT VENT HIGH PRESSURE SWITCH METERING PUMPS CRACKING VALVES WINDSHEILD PUMP LOW PRESSURE SWITCH 30 LOW PRESSURE SWITCH LEGEND 1/2” 5/16” 3/16” TAIL PANELS Figure 30-1. TKS Ice System Overview 30-2 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES P3 BLEED AIR BLEED AIR PRESSURE REGULATOR (18 PSI) RELAY FIREWALL TIMER EJECTOR FLOW CONTROL VALVES PRESSURE SWITCHES (15 PSI) RH OUTBD WING LH OUTBD WING LH INBD WING RH INBD WING LH WING STRUT RH WING STRUT LH GEAR RH GEAR POD LEGEND P3 BLEED AIR REGULATED BLEED AIR (18 PSI) 1st CYCLE 2nd CYCLE VERTICAL STABILIZER 30 3rd CYCLE LH HORIZONTAL STABILIZER RH HORIZONTAL STABILIZER Figure 30-2. Pneumatic De-Ice System Overview Revision 0 FOR TRAINING PURPOSES ONLY 30-3 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL 19 HA18 ANNUNCIATOR PANEL 19 HA65 W/S ANTI ICE HA12 Y Y (BLK) A B C D E HA60 HA64 HA1 K26 (BLK) A B C D E BLK BLK BLU BLU W/S ANTI ICE PRIMARY HEATING ELEMENT HA54 20 HA12 Y Y HA64 HA1 (BLK) K26 WHT WHT HA68 HA61 W/S ANTI ICE CONT 5 HA13 U U AUTO OFF HA4 SECONDARY HEATING ELEMENT HA62 HA3 HA66 HA57 HA52 HA53 MANUAL 7 4 W/S ANTI ICE CONT 5 HA13 U U HA4 1 3 SECONDARY POWER CONDITIONS: PRIMARY—AUTO SECONDARY—AUTO HA51 KA25 HA56 HA55 SECONDARY SWITCH 19 SECONDARY HEATING ELEMENT W/S ANTI ICE SEC 5 2 20 A A LEGEND 8 6 BATTERY POWER HA9 1 3 GND BLOCK POSITIVE POWER OR SWITCHABLE POWER N R HA49 OFF HA17 MANUAL HA56 HA55 SECONDARY SWITCH GROUND KA25 HA51 SECONDARY POWER CONDITIONS: PRIMARY—AUTO SECONDARY—OFF HA63 HA19 PRIMARY HEATING ELEMENT HA54 HA64 HA1 7 4 Figure 30-3. Dual Element Windshield Anti-Ice (Sheet 2 of 3) HA65 Y Y WHT WHT HA18 ANNUNCIATOR PANEL HA12 L L M M HA62 HA3 HA66 HA57 HA52 HA53 AUTO Figure 30-3. Dual Element Windshield Anti-Ice (Sheet 1 of 3) 20 SENSE ELEMENT HA59 HA5 CONTROLLER GROUND N R HA49 OFF MANUAL W/S ANTI ICE BLK BLK BLU BLU MANUAL BATTERY POWER HA9 5 2 GND BLOCK HA17 AUTO OFF LEGEND 8 6 AUTO A A A B C D E PRIMARY SWITCH CONTROLLER 20 A B C D E HA61 HA5 PRIMARY SWITCH W/S ANTI ICE SEC HA60 (BLK) SENSE ELEMENT HA59 L L M M HA68 HA63 HA19 HA65 PRIMARY HEATING ELEMENT HA54 20 HA18 ANNUNCIATOR PANEL HA63 HA19 (BLK) HA60 K26 (BLK) HA68 A B C D E A B C D E L L M M NOTES BLK BLK BLU BLU SENSE ELEMENT HA59 WHT WHT HA61 W/S ANTI ICE CONT 5 HA13 U U AUTO OFF HA4 HA5 SECONDARY HEATING ELEMENT HA62 HA3 HA66 HA57 HA52 HA53 MANUAL PRIMARY SWITCH CONTROLLER 30 7 4 5 2 HA9 1 3 GND BLOCK AUTO W/S ANTI ICE SEC 20 A A HA49 OFF HA17 MANUAL LEGEND 8 6 HA56 HA55 SECONDARY SWITCH N R BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND KA25 HA51 CONDITIONS: PRIMARY—MANUAL SECONDARY—MANUAL Figure 30-3. Dual Element Windshield Anti-Ice (Sheet 3 of 3) 30-4 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL 19 19 ANNUNCIATOR PANEL ANNUNCIATOR PANEL HA11 HA15 HEATING ELEMENT JUMPERS W/S ANTI ICE 20 HA12 Y Y HA14 HA1 HA11 HA15 RELAY 5 2 6 3 7 4 1 8 HA2 A B C D E A B C D E BLK BLK WHT WHT W/S ANTI ICE 20 HA12 Y Y HA14 HA1 RELAY SENSE ELEMENT 5 2 6 3 7 4 1 8 HA2 HA35 W/S ANTI ICE CONT 5 HA13 U U HA4 AUTO OFF HA7 HA8 MANUAL CONTROLLER 7 4 5 2 8 6 HA3 HA6 HA10 W/S ANTI ICE CONT BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND 5 HA13 3 GND BLOCK N R A B C D E BLK BLK WHT WHT SENSE ELEMENT U U HA4 AUTO OFF HA5 HA7 HA8 MANUAL HA3 HA6 HA10 LEGEND BATTERY POWER GROUND SIGNAL OR SENSE CONTROLLER HA9 1 A B C D E HA35 LEGEND HA5 HEATING ELEMENT JUMPERS CONDITIONS: W/S ANTI-ICE AUTO SELECTED SENSOR < 359Ω RELAY ENERGIZED 7 4 5 2 8 6 SIGNAL OR SENSE HA9 1 3 GND BLOCK Figure 30-4. Single Element Windshield Anti-Ice (Sheet 1 of 4) N R CONDITIONS: W/S ANTI-ICE AUTO SELECTED SENSOR = 359Ω RELAY DEENERGIZED Figure 30-4. Single Element Windshield Anti-Ice (Sheet 2 of 4) NOTES 30 Revision 0 FOR TRAINING PURPOSES ONLY 30-5 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL 19 19 ANNUNCIATOR PANEL ANNUNCIATOR PANEL HA11 HA15 HEATING ELEMENT JUMPERS W/S ANTI ICE 20 HA12 Y Y HA14 HA1 HA11 HA15 RELAY 5 2 6 3 7 4 1 8 HA2 A B C D E A B C D E BLK BLK WHT WHT W/S ANTI ICE 20 HA12 Y Y HA14 HA1 RELAY SENSE ELEMENT 5 2 6 3 7 4 1 8 HA2 LEGEND 5 HA13 U U HA4 AUTO OFF HA5 HA7 HA8 MANUAL CONTROLLER 7 4 5 2 8 6 W/S ANTI ICE CONT BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND 5 HA13 SIGNAL OR SENSE HA9 1 HA3 HA6 HA10 3 GND BLOCK N R A B C D E A B C D E BLK BLK WHT WHT SENSE ELEMENT HA35 HA35 W/S ANTI ICE CONT HEATING ELEMENT JUMPERS U U HA4 AUTO OFF HA5 HA7 CONTROLLER CONDITIONS: W/S ANTI-ICE AUTO SELECTED SENSOR = 354Ω RELAY ENERGIZED HA8 MANUAL 7 4 5 2 HA9 3 GND BLOCK Figure 30-4. Single Element Windshield Anti-Ice (Sheet 3 of 4) LEGEND BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND 8 6 1 HA3 HA6 HA10 N R CONDITIONS: W/S ANTI-ICE MANUAL SELECTED Figure 30-4. Single Element Windshield Anti-Ice (Sheet 4 of 4) NOTES 30 30-6 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL LH WING LH WING DEICE BOOT AUTO HD1 5 C C OFF HD2 MANUAL HD4 11 11 HD3 7 7 HD27 HD28 14 14 HD5 15 15 HD6 HD21 6 6 HD29 20 20 18 18 DEICE BOOT AUTO HD1 5 C C OFF HD2 MANUAL HD4 11 11 HD3 7 7 HD27 HD28 HD21 6 6 HD29 LH WING 14 14 HD5 15 15 HD6 DEICE BOOT 20 20 18 18 HD16 4 4 HD30 HD20 36 3 HD22 HD17 HD7 ANNUNCIATOR PANEL HD16 4 4 HD30 7 HD8 HD9 HD19 1 OFF HD2 MANUAL 14 14 HD5 15 15 HD6 HD21 6 6 HD29 20 20 18 18 4 4 HD30 8 HD20 JUMPER TIMER 36 3 HD22 HD17 HD7 ANNUNCIATOR PANEL 6 9 C C HD27 HD28 TIMER TIMER 36 AUTO HD1 5 HD4 11 11 HD3 7 7 7 9 HD19 1 3 HD22 HD17 HD7 ANNUNCIATOR PANEL 6 HD8 HD9 HD16 8 HD20 6 7 HD8 HD9 9 HD19 1 JUMPER JUMPER HD18 HD18 8 HD18 1 1 2 3 4 5 6 HD10 HD13 2 7 CYCLE 1 2 3 3 4 TIME ACTIVE (SEC) 6 6 6 CYCLE 3 CYCLE 2 CYCLE 1 OUTBD INBD TAIL WING & WING STRUT HD14 LEGEND BATTERY POWER HD12 HD15 GROUND CONDITION: DE-ICE BOOTS AUTO SELECTED MOMENTARILY Figure 30-5. De-Ice Boot System (Sheet 1 of 6) 6 7 1 CYCLE 1 2 3 HD13 HD11 HD11 5 HD10 CYCLE 3 CYCLE 2 CYCLE 1 OUTBD INBD TAIL WING & WING STRUT HD12 HD14 2 TIME ACTIVE (SEC) 6 6 6 HD15 CONDITION: DE-ICE BOOTS AUTO / CYCLE 1 Figure 30-5. De-Ice Boot System (Sheet 2 of 6) 4 5 6 HD10 HD13 LEGEND BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND 3 CYCLE 3 CYCLE 2 CYCLE 1 OUTBD TAIL INBD WING & WING STRUT HD11 HD14 HD12 HD15 7 CYCLE 1 2 3 TIME ACTIVE (SEC) 6 6 6 LEGEND BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND CONDITION: DE-ICE BOOTS AUTO / CYCLE 2 Figure 30-5. De-Ice Boot System (Sheet 3 of 6) NOTES 30 Revision 0 FOR TRAINING PURPOSES ONLY 30-7 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL DEICE BOOT AUTO HD1 5 C C OFF HD2 HD21 6 6 MANUAL 14 14 HD5 15 15 HD6 HD29 LH WING LH WING LH WING HD27 HD28 HD4 11 11 HD3 7 7 DEICE BOOT 20 20 18 18 AUTO HD1 5 C C OFF HD2 MANUAL HD4 11 11 HD3 7 7 HD27 HD28 14 14 HD5 15 15 HD6 HD21 6 6 HD29 20 20 18 18 DEICE 7.5 BOOT HD16 4 4 HD30 HD20 36 3 HD22 HD17 HD7 ANNUNCIATOR PANEL HD16 4 4 HD30 7 9 HD19 1 OFF HD2 MANUAL 14 14 HD5 15 15 HD6 HD21 6 6 HD29 20 20 18 18 4 4 HD30 TIMER 8 HD20 36 3 HD22 HD17 HD7 ANNUNCIATOR PANEL 6 HD8 HD9 C C HD27 HD26 TIMER TIMER 36 AUTO HD1 HD4 11 11 HD3 7 7 7 9 HD19 1 8 HD20 1 2 3 4 5 6 HD10 HD13 2 3 4 CYCLE 1 2 3 CYCLE 3 CYCLE 2 CYCLE 1 INBD TAIL OUTBD WING WING & STRUT HD12 HD14 HD15 6 HD10 TIME ACTIVE (SEC) 6 6 6 HD13 HD11 HD11 5 7 LEGEND BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND CONDITION: DE-ICE BOOTS AUTO / CYCLE 3 Figure 30-5. De-Ice Boot System (Sheet 4 of 6) CYCLE 3 CYCLE 2 CYCLE 1 INBD TAIL OUTBD WING WING & STRUT HD12 HD14 HD8 HD9 9 HD19 1 HD18 HD18 1 1 7 CYCLE 1 2 3 2 CONDITION: DE-ICE BOOTS MANUAL SELECTED Figure 30-5. De-Ice Boot System (Sheet 5 of 6) 5 6 7 7 7 HD34 1 1 HD44 8 8 HD10 CYCLE 3 CYCLE 2 CYCLE 1 OUTBD TAIL INBD WING & WING STRUT HD50 HD49 4 4 HD48 FIREWALL HD35 HD36 HD11 HD14 HD12 HD15 HD51 3 3 2 2 HD45 HD47 3 3 HD46 LEGEND HD15 4 CYCLE TIME ACTIVE (SEC) 1 6 6 2 3 6 8 9 9 TIME ACTIVE (SEC) 6 6 6 BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND 3 7 1 1 2 2 JUMPER HD18 6 HD39 HD40 JUMPER JUMPER 3 HD22 HD17 HD7 ANNUNCIATOR PANEL 6 HD8 HD9 HD16 LH WING CYCLE 2 CARGO POD & LDG GEAR FAIRINGS LEGEND BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GROUND CONDITION: DE-ICE BOOTS WITH CARGO POD AND LANDING GEAR FAIRING BOOTS Figure 30-5. De-Ice Boot System (Sheet 6 of 6) NOTES 30 30-8 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES JC011 PC011 L CB PNL W/S ANTI-ICE 28VDC A BACKUP ANTI-ICE 28VDC C PRIMARY ANTI-ICE 28 VDC B PI003 L SW PNL TKS BELLY FEEDTHROUGH JI003 ELEFUS GC001 20 21 22 HH N JD002 ELEFUS SI024 6 BACKUP ON B A BKP PUMP GND BKP PUMP PWR J V U T W/S POWER BKP LOW PRESS CMN LOW PRESS CMN MAX FLOW CMN 16 S MAX FLOW ACTIVATE 15 R W/S ACTIVATE 14 P W/S ACTIVATE CMN 11 23 5 4 3 19 2 OFF JD001 ELEFUS 18 1 17 SI023 MAX FLOW 6 AIRFRAME (MOM) 5 4 3 2 WINDSHIELD (MOM) 1 SI022 PRIMARY HIGH 6 5 NORM 4 3 OFF 2 OFF C 1 L HIGH POWER 10 K NORM TIMER POWER 12 M MAX FLOW POWER 13 N NORM PUMP POWER *A Z Y LOW PRESS 1 CMN LOW PRESS 2 CMN LOW PRESS ACTIVE F GROUND B A W C LOW PRESS ANNUN HIGH PRESS ANNUN LOW FLUID ANNUN HIGH MODE ANNUN D NORM MODE ANNUN G SYSTEM ON X ANNUN TEST GND E H *B LVL SENDR SIGNAL LVL SENDR POWER LVL SENDR GND (VEND) 1 (VEND) (VEND) R LO PRESS SW 2 (VEND) C (VEND) 1 (VEND) 1 2 (VEND) L LO PRESS SW 2 (VEND) 3 NC NC PT003 TAILCONE R UI005 GEA71 PI002 (P702) A/I LOW PRESS A/I HIGH PRESS A/I FLUID LOW A/I HIGH A/I NORMAL LEGEND BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER GC001 77 67 70 69 68 GROUND SECONDARY POWER SIGNAL OR SENSE CONDITION: SYSTEM OFF UI005 GEA71 PI001 (P701) A/I QTY SIGNAL SENDER PWR (12V) SENDER PWR GND A/I QTY LO 22 16 13 23 (ORN) (WHT) (BLU) 30 Figure 30-6. TKS Anti-Ice System with G1000 Revision 0 FOR TRAINING PURPOSES ONLY 30-9 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES TIMER PROP ANTI-ICE 30 CONDITION: BATTERY ON AUTO OFF MANUAL HA27 5 HA26 HA26 S S HA40 B HA22 HA34 OIL PRESSURE SWITCH NO C HA41 3 2 1 NC POSITIVE POWER OR SWITCHABLE POWER CONTROL SWITCH HA30 PROP ANTI-ICE CONTROL LEGEND A HA37 HA36 F C 3 2 1 BRUSHES TRANSORB AMMETER HA42 BOOTS HA38 HA30 HA24 ED4 HH Figure 30-7. Legacy Series Propeller Anti-Ice System (Sheet 1 of 4) TIMER PROP ANTI-ICE 30 A HA37 HA36 POSITIVE POWER OR SWITCHABLE POWER GROUND HA27 5 HA26 HA26 S S HA40 B HA22 HA34 OIL PRESSURE SWITCH NO C 30 NC BATTERY POWER AUTO OFF MANUAL HA30 PROP ANTI-ICE CONTROL LEGEND CONTROL SWITCH HA41 3 2 1 3 2 1 F C CONDITION: BATTERY ON BOOTS HEATING 90 SECONDS BRUSHES TRANSORB AMMETER HA42 HA30 BOOTS HA38 HA24 ED4 HH Figure 30-7. 30-10 Legacy Series Propeller Anti-Ice System (Sheet 2 of 4) FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES TIMER PROP ANTI-ICE 30 HA37 HA36 POSITIVE POWER OR SWITCHABLE POWER GROUND HA27 5 HA26 HA26 S S HA40 OIL PRESSURE SWITCH C HA41 3 2 1 NC CONDITION: BATTERY ON / AUTO SELECTED BOOTS COOLING 90 SECONDS B HA22 HA34 NO BATTERY POWER AUTO OFF MANUAL HA30 PROP ANTI-ICE CONTROL LEGEND A CONTROL SWITCH F C 3 2 1 BRUSHES TRANSORB AMMETER HA42 HA30 BOOTS HA38 HA24 ED4 HH Figure 30-7. Legacy Series Propeller Anti-Ice System (Sheet 3 of 4) TIMER PROP ANTI-ICE 30 A HA37 HA36 POSITIVE POWER OR SWITCHABLE POWER GROUND HA27 5 HA26 HA26 S S HA40 B HA22 HA34 OIL PRESSURE SWITCH NO C NC BATTERY POWER AUTO OFF MANUAL HA30 PROP ANTI-ICE CONTROL LEGEND CONTROL SWITCH HA41 3 2 1 3 2 1 F C CONDITION: BATTERY ON / MANUAL SELECTED BOOTS HEATING CONTINUOUSLY BRUSHES TRANSORB AMMETER HA42 HA30 BOOTS HA38 HA24 30 ED4 HH Figure 30-7. Revision 0 Legacy Series Propeller Anti-Ice System (Sheet 4 of 4) FOR TRAINING PURPOSES ONLY 30-11 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL PROP ANTI-ICE CONT 28 VDC (20) 5 PC057 PROP ANTI-ICE 28 VDC (12) 30 LEGEND UC011 TIMER POSITIVE POWER OR SWITCHABLE POWER GROUND PROP POWER IN A CONDITIONS: ENGINE RUNNING SYSTEM OFF PI023 JI023 L SWITCH PNL DISC (12) (12) 2 1 3 (12) (12) PI003 JI003 L SWITCH PNL DISC (20) 6 (20) 3 SI032 PROP DEICE 5 AUTO OFF (12) 2 6 4 3 1 (20) PROP HEAT POWER PROP HEAT POWER ON 4 10 TIMER POWER C PROP POWER OUT F GND GC001 LH FIREWALL 4 WH1 WH2 RC005 10.0K OHMS PI505 P604 B (12) 5 WH1 WH2 RC006 10.0K OHMS MANUAL (MOM) UI006 #1 GIA63W (20) ELEFUS ENGINE (20) (20) AA 3 1 2 NO (VEND) C (VEND) NC (VEND) 37 36 12 AN005 (12) (VEND) PROP HEAT POWER PROP HEAT POWER ON PI504 P604 4 10 30 AN004 (12) I G 1 2 RN002 VARISTOR PI002 (1P702) PROP HEAT CURRENT HI 50 PROP HEAT CURRENT LO 51 PI506 P605 PROP HEAT AUTO POWER (VEND) UN026 BRUSH BLOCK ASSY 38 UI005 GEA71 ENGINE/AIRFRAME UI007 #2 GIA63W 40 PSI JI005 PI005 AVN/ELE DISC PI507 P605 PROP HEAT AUTO POWER UN025 OIL PRESSURE SWITCH JN027 PN027 OIL PRESS SWITCH DISC 4 RZ006 PST 1 PST (12) (12) GN009 REFER TO 91-20-02 12 Figure 30-8. G1000 Prop Anti-Ice System (Sheet 1 of 4) 30-12 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 30 Revision 0 FOR TRAINING PURPOSES ONLY 30-13 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL PROP ANTI-ICE CONT 28 VDC (20) 5 PC057 PROP ANTI-ICE 28 VDC (12) 30 LEGEND UC011 TIMER BATTERY POWER GROUND PROP POWER IN A SIGNAL OR SENSE PI023 JI023 L SWITCH PNL DISC (12) (12) 2 1 3 CONDITIONS: ENGINE RUNNING IN AUTO 90 SECONDS ON (12) (12) PI003 JI003 L SWITCH PNL DISC (20) 6 (20) 3 SI032 PROP DEICE 5 AUTO OFF (12) 2 6 4 3 1 (20) PROP HEAT POWER PROP HEAT POWER ON 4 10 TIMER POWER C PROP POWER OUT F GND GC001 LH FIREWALL 4 WH1 WH2 RC005 10.0K OHMS PI505 P604 B (12) 5 WH1 WH2 RC006 10.0K OHMS MANUAL (MOM) UI006 #1 GIA63W (20) ELEFUS ENGINE (20) (20) AA 3 1 2 NO (VEND) C (VEND) NC (VEND) 37 36 12 AN005 (12) (VEND) PROP HEAT POWER PROP HEAT POWER ON PI504 P604 4 10 30 AN004 (12) I G 1 2 RN002 VARISTOR PI002 (1P702) PROP HEAT CURRENT HI 50 PROP HEAT CURRENT LO 51 PI506 P605 PROP HEAT AUTO POWER (VEND) UN026 BRUSH BLOCK ASSY 38 UI005 GEA71 ENGINE/AIRFRAME UI007 #2 GIA63W 40 PSI JI005 PI005 AVN/ELE DISC PI507 P605 PROP HEAT AUTO POWER UN025 OIL PRESSURE SWITCH JN027 PN027 OIL PRESS SWITCH DISC 4 RZ006 PST 1 PST (12) (12) GN009 REFER TO 91-20-02 12 Figure 30-8. G1000 Prop Anti-Ice System (Sheet 2 of 4) 30-14 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 30 Revision 0 FOR TRAINING PURPOSES ONLY 30-15 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL PROP ANTI-ICE CONT 28 VDC (20) 30 PC057 PROP ANTI-ICE 28 VDC (12) 5 LEGEND UC011 TIMER BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER PROP POWER IN A GROUND PI023 JI023 L SWITCH PNL DISC (12) (12) 2 1 3 CONDITIONS: ENGINE RUNNING IN AUTO 90 SECONDS OFF (12) (12) PI003 JI003 L SWITCH PNL DISC (20) 6 (20) 3 SI032 PROP DEICE 5 AUTO OFF (12) 2 6 4 3 1 (20) PROP HEAT POWER PROP HEAT POWER ON 4 10 TIMER POWER (12) C PROP POWER OUT F GND GC001 LH FIREWALL 4 WH1 WH2 RC005 10.0K OHMS PI505 P604 B 5 WH1 WH2 RC006 10.0K OHMS MANUAL (MOM) UI006 #1 GIA63W (20) ELEFUS ENGINE (20) (20) AA 3 1 2 NO (VEND) C (VEND) NC (VEND) 37 36 12 AN005 (12) (VEND) PROP HEAT POWER PROP HEAT POWER ON PI504 P604 4 10 30 AN004 (12) I G 1 2 RN002 VARISTOR PI002 (1P702) PROP HEAT CURRENT HI 50 PROP HEAT CURRENT LO 51 PI506 P605 PROP HEAT AUTO POWER (VEND) UN026 BRUSH BLOCK ASSY 38 UI005 GEA71 ENGINE/AIRFRAME UI007 #2 GIA63W 40 PSI JI005 PI005 AVN/ELE DISC PI507 P605 PROP HEAT AUTO POWER UN025 OIL PRESSURE SWITCH JN027 PN027 OIL PRESS SWITCH DISC 4 RZ006 PST 1 PST (12) (12) GN009 REFER TO 91-20-02 12 Figure 30-8. G1000 Prop Anti-Ice System (Sheet 3 of 4) 30-16 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 30 Revision 0 FOR TRAINING PURPOSES ONLY 30-17 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL PROP ANTI-ICE CONT 28 VDC (20) 5 PC057 PROP ANTI-ICE 28 VDC (12) 30 LEGEND UC011 TIMER BATTERY POWER POSITIVE POWER OR SWITCHABLE POWER PROP POWER IN A GROUND SIGNAL OR SENSE PI023 JI023 L SWITCH PNL DISC (12) (12) 2 1 3 (12) CONDITIONS: ENGINE OFF SWITCH IN MANUAL (12) PI003 JI003 L SWITCH PNL DISC (20) 6 (20) 3 SI032 PROP DEICE 5 AUTO OFF (12) 2 6 4 3 1 (20) PROP HEAT POWER PROP HEAT POWER ON 4 10 TIMER POWER C PROP POWER OUT F GND GC001 LH FIREWALL 4 WH1 WH2 RC005 10.0K OHMS PI505 P604 B (12) 5 WH1 WH2 RC006 10.0K OHMS MANUAL (MOM) UI006 #1 GIA63W (20) ELEFUS ENGINE (20) (20) AA 3 1 2 NO (VEND) C (VEND) NC (VEND) 37 36 12 AN005 (12) (VEND) PROP HEAT POWER PROP HEAT POWER ON PI504 P604 4 10 30 AN004 (12) I G 1 2 RN002 VARISTOR PI002 (1P702) PROP HEAT CURRENT HI 50 PROP HEAT CURRENT LO 51 PI506 P605 PROP HEAT AUTO POWER (VEND) UN026 BRUSH BLOCK ASSY 38 UI005 GEA71 ENGINE/AIRFRAME UI007 #2 GIA63W 40 PSI JI005 PI005 AVN/ELE DISC PI507 P605 PROP HEAT AUTO POWER UN025 OIL PRESSURE SWITCH JN027 PN027 OIL PRESS SWITCH DISC 4 RZ006 PST 1 PST (12) (12) GN009 REFER TO 91-20-02 12 Figure 30-8. G1000 Prop Anti-Ice System (Sheet 4 of 4) 30-18 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 30 Revision 0 FOR TRAINING PURPOSES ONLY 30-19 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 30 30-20 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CHAPTER 31 INDICATING AND RECORDING INTRODUCTION This chapter helps to familiarize the technician with the indicating and recording systems in the cockpit. It also assists in locating specific components. GENERAL The instrument and switch panels section provides a description of the instrument panel and switch panels. The Garmin G1000 system section gives a description of the G1000 system and the different subsystems that interface with the computer to supply flight instrumentation, position, navigation, communication, and identification data to the flight crew. Revision 0 FOR TRAINING PURPOSES ONLY The central warning system section includes information on how visual or aural warnings are sent to the flight crew. It includes the engine indication and crew alerting system (EICAS) system. 31 31-1 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES ENGINE FIRE OIL PRESS LOW GENERATOR OFF EMERGENCY POWER LEVER AUX FUEL PUMP ON FUEL PRESS LOW VOLTAGE LOW VACUUM LOW RESERVOIR FUEL LOW LEFT FUEL LOW RIGHT FUEL LOW STBY ELEC PWR ON BATTERY OVERHEAT BATTERY HOT CHIP DETECTOR STBY ELEC PWR INOP WINDSHIELD ANTI-ICE DE-ICE PRESSURE STARTER ENERGIZED IGNITION ON DOOR WARNING STARTER ENERGIZED IGNITION ON FUEL SELECT OFF 208 KING ANNUNCIATOR PANEL ENGINE FIRE OIL PRESS LOW GENERATOR OFF EMERGENCY POWER LEVER AUX FUEL PUMP ON FUEL PRESS LOW VOLTAGE LOW VACUUM LOW RESERVOIR FUEL LOW LEFT FUEL LOW RIGHT FUEL LOW STBY ELEC PWR ON SPARE SPARE CHIP DETECTOR STBY ELEC PWR INOP DOOR WARNING FUEL SELECT OFF WINDSHIELD ANTI-ICE DE-ICE PRESSURE 208 G530 ANNUNCIATOR PANEL 31 Figure 31-1. Annunciator Panels 31-2 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL Table 31-1. NON-G1000 ANNUNCIATORS ANNUNCIATOR NOTES DESCRIPTION An excessive temperature condition and/or possible fire has occured in the engine compartment. Indicates engine oil pressure is less than 38 psi. The generator is not connected to the power distribution bus. The emergency power lever is advanced out of the NORMAL position. Electrical system bus voltage is below 24.5 volts, and power is being supplied from the battery. The vacuum system suction is less than approximately 3.0 in. Hg. The fuel level in the reservoir tank is approximately one-half or less. One or both fuel tank selectors are off, the fuel selector warning circuit breaker is not set or the start control circuit breaker is not set. One or both upper rear doors are not properly secured. The auxiliary fuel pump is operating. Fuel pressure in the fuel manifold assembly is below 4.75 psi. The starter-generator is operating in the starter mdoe. Fuel quantity in the left fuel tank is 25 gallons or less. Fuel quantity in the right fuel tank is 25 gallons or less. 31 Standby alternator is supplying electrical power to the bus. Revision 0 FOR TRAINING PURPOSES ONLY 31-3 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL Table 31-1. NON-G1000 ANNUNCIATORS (CONTINUED) ANNUNCIATOR NOTES DESCRIPTION *The left and right Chip Detector annunciator bulbs illuminate independent of one another. The left side will illuminate indicating that metal chips have been detected in the accessory gearbox case of the engine. The right side will illuminate indicating that metal chips have been detected in the reduction gearbox case of the engine. Electrical power is not available from the standby alternator. Electrical power is being supplied to the engine ignition system. Electrical power is being suppled to the windshield anti-ice power relay. (not available on TKS equipped aircraft) Pressure in the deice boot system has reached approximately 15 psig. (not available on TKS equipped aircraft) BATTERY OVERHEAT BETA GENERATOR OVERHEAT BATTERY HOT STDBY ALT OVRHT ENGINE Indicates that the temperature of the cooling air being exhausted from the startergenerator exceeds 300°F. (not required for US certification.) The electrolyte temperature in the NiCad battery is at least 140°F. (included only with NiCad equipped aircraft.) The 75-amp alternator cooling air is at least 300°F. (not required for US certification.) ETM BELOW ICING MIN SPD The annunciator illuminates for aircraft equipped with boots when the prop heat switch is in the AUTO position and the airspeed has been reduced to less than 110 KIAS. For TKS equipped aircraft, the annunciator illuminates when the P/S HEAT/LOW A/S AWARE switch is in the ON position and the airspeed has been reduced to less than 97.5 +/- 2 knots. CAUT WARN 31-4 Indicates when the propeller blade angle has been reduced into the beta range. (not required for US certification.) Engine Trend Monitor has two annunciators. The white annunciator illuminates if an engine limitation has been exceeded. The amber annunciator illuminates if the event exceeds Pratt & Whitney time frames. (not available on TKS equipped aircraft.) ANTI-ICE ON 31 The electrolyte temperature in the NiCad battery is at least 160°F. (included only with NiCad battery-equipped aircraft.) The upper element ANTI-ICE ON illuminates when the primary switch is in either NORM or HIGH. The amber CAUT element illuminates if there is high pressure in the system or due to low fluid quantity. The red WARN element illuminates if a low pressure condition exists. (TKS equipped aircraft only) FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES NO. 1 GIA 63W GDC 74A AIR DATA COMPUTER ALTITUDE: GRS 77 AHRS HEADING: GRS 77 OR GMU 44 NO. 1 GIA 63W NO. 2 GIA 63W NO. 2 GIA 63W GDC 74A AIR DATA COMPUTER NO.1 AND 2 GIA 63W OR GEA 71 OR EQUIVALENT ENGINE/AIRFRAME SENSORS GDC 74A AIR DATA COMPUTER GIA 63W NO. 1 AND 2 GDC 74A AIR DATA COMPUTER GIA 63W NO. 1 AND 2 GTX 33 TRANSPONDER OR GIA 63 NO.1 AND 2 31 Figure 31-2. G1000 Invalid Display Fields Revision 0 FOR TRAINING PURPOSES ONLY 31-5 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES Table 31-2. G1000 CAS MESSAGES A-ICE PRESS LOW FUEL SELECT OFF DESCRIPTION Anti-ice system pressure is low. DESCRIPTION OPTIONAL AUDIO ALERT Yes Repeating Chime OPTIONAL AUDIO ALERT OIL PRESS LOW One or both fuel tank selectors are off. No Repeating Chime DESCRIPTION Engine oil pressure is low. OPTIONAL No AUDIO ALERT Repeating Chime BATTERY OVHT GENERATOR OVHT VOLTAGE LOW DESCRIPTION Battery temperature is critically high. DESCRIPTION Generator temperature is critically DESCRIPTION Bus voltage is low. high. OPTIONAL AUDIO ALERT Yes Repeating Chime OPTIONAL AUDIO ALERT Yes Repeating Chime BETA ENGINE FIRE DESCRIPTION Propeller is operating in beta mode. DESCRIPTION Excessive temperature or fire in OPTIONAL AUDIO ALERT No Repeating Chime VOLTAGE HIGH DESCRIPTION Bus voltage is high. engine compartment. OPTIONAL Yes Repeating Chime OPTIONAL No AUDIO ALERT Repeating Chime EMERG PWR LVR RSVR FUEL LOW DESCRIPTION Emergency power lever is not DESCRIPTION Fuel starvation imminent. OPTIONAL No AUDIO ALERT Repeating Chime normal. OPTIONAL No AUDIO ALERT Repeating Chime OPTIONAL No AUDIO ALERT Repeating Chime 31 31-6 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES Table 31-2. G1000 CAS MESSAGES (CONTINUED) A-ICE FLUID LO BATTERY HOT DESCRIPTION Anti-ice system fluid level is low. DESCRIPTION OPTIONAL AUDIO ALERT Yes Single Chime OPTIONAL AUDIO ALERT FUEL BOOST ON DESCRIPTION Auxiliary fuel pump is operating. Battery temperature is high. OPTIONAL Yes AUDIO ALERT Single Chime No Single Chime A-ICE PRESS HI CHIP DETECT FUEL PRESS LOW DESCRIPTION Anti-ice system pressure is high. DESCRIPTION Metal chips detected in oil. DESCRIPTION Fuel pressure is low. OPTIONAL AUDIO ALERT Yes Single Chime OPTIONAL AUDIO ALERT No OPTIONAL Single Chime No AUDIO ALERT Single Chime ALTNR AMPS DOOR UNLATCHED GENERATOR AMPS DESCRIPTION Check alternator current. DESCRIPTION Upper cargo/aft passenger door not DESCRIPTION Check generator current. latched. OPTIONAL AUDIO ALERT No Single Chime OPTIONAL AUDIO ALERT DESCRIPTION Standby alternator temperature is AUDIO ALERT No Single Chime DESCRIPTION Engine Trend Monitor has detected an exceedance. critically high. OPTIONAL Single Chime ETM EXCEED ALTNR OVHT AUDIO ALERT OPTIONAL No Yes Single Chime OPTIONAL AUDIO ALERT No Single Chime 31 Revision 0 FOR TRAINING PURPOSES ONLY 31-7 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES Table 31-2. G1000 CAS MESSAGES (CONTINUED) GENERATOR OFF L P/S HEAT DESCRIPTION Generator is not connected to the DESCRIPTION aircraft bus. OPTIONAL AUDIO ALERT No Single Chime OPTIONAL AUDIO ALERT STALL HEAT Left pitot/static heater is inoperative. No Single Chime DESCRIPTION Stall vane heater is inoperative. OPTIONAL AUDIO ALERT No Single Chime L-R FUEL LOW PROP DE-ICE STARTER ON DESCRIPTION Both fuel tanks are low. DESCRIPTION Propeller heater is inoperative. DESCRIPTION Starter-generator is in starter mode. OPTIONAL AUDIO ALERT No Single Chime L-R P/S HEAT DESCRIPTION Both pitot/static heaters are inoperative. OPTIONAL AUDIO ALERT No Single Chime OPTIONAL AUDIO ALERT Yes Single Chime DESCRIPTION Right fuel tank is low. DESCRIPTION OPTIONAL AUDIO ALERT No Single Chime DESCRIPTION Left fuel tank is low. DESCRIPTION Right pitot/static heater is in- No Single Chime AUDIO ALERT Single Chime STBY PWR INOP R P/S HEAT OPTIONAL No R FUEL LOW L FUEL LOW AUDIO ALERT OPTIONAL OPTIONAL AUDIO ALERT Standby alternator is inoperative. No Single Chime operative. OPTIONAL AUDIO ALERT No Single Chime 31 31-8 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES Table 31-2. G1000 CAS MESSAGES (CONTINUED) A-ICE HIGH ETM FAULT DESCRIPTION Anti-ice system is operating in high DESCRIPTION mode. OPTIONAL AUDIO ALERT Yes None A-ICE NORM DESCRIPTION Anti-ice system is operating in normal mode. OPTIONAL AUDIO ALERT Yes None ETM CAPTURE DESCRIPTION Engine Trend Monitor is logging trend data. OPTIONAL AUDIO ALERT No None ETM EXCEED DESCRIPTION Engine Trend Monitor has detected OPTIONAL AUDIO ALERT PFD2 FAN FAIL Engine Trend Monitor is experiencing a problem. No None DESCRIPTION PFD2 cooling fan has failed. OPTIONAL AUDIO ALERT No None IGNITION ON PREV EXCEED DESCRIPTION Engine ignition is active. DESCRIPTION Engine Trend Monitor shows a pre- OPTIONAL AUDIO ALERT No None vious exceedance. OPTIONAL AUDIO ALERT None MFD FAN FAIL SPD NOT AVAIL DESCRIPTION MFD cooling fan has failed. DESCRIPTION OPTIONAL AUDIO ALERT No None No OPTIONAL AUDIO ALERT PFD1 FAN FAIL STBY PWR ON DESCRIPTION PFD1 cooling fan has failed. DESCRIPTION “SPD” key pressed on Autopilot Mode Control Panel. No None Standby alternator is on. an event. OPTIONAL AUDIO ALERT No None OPTIONAL AUDIO ALERT No None OPTIONAL AUDIO ALERT No None 31 Revision 0 FOR TRAINING PURPOSES ONLY 31-9 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 31 31-10 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CHAPTER 32 LANDING GEAR INTRODUCTION This chapter presents the landing gear and brake system. General maintenance considerations are included. References for this chapter and further specific information are in Chapter 32 Landing Gear, Chapter 5 Time Limits/Maintenance Checks, and Chapter 12 Servicing of the Manufacturer’s Maintenance Manual. GENERAL The Cessna Caravan I employs a fixed, tricycle landing gear assembly. The steerable nose gear is supported with a tubular spring drag link. Within the trunnion is an oil snubber assembly that dampens stresses to the gear caused by landing and taxiing. The main gear is a rugged three-piece tubular spring design. Revision 0 FOR TRAINING PURPOSES ONLY A tubular spring steel main gear spring provides main gear shock absorption. The spring has a center main gear tube that connects the two outer main gear legs at the gear attach trunnions. The main gear has hydraulically actuated disc brakes. 32-1 32 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 32 BRAKE HYDRAULIC LINE TRUNNION MAIN GEAR SPRING WHEEL ALIGNMENT SHIM AXLE BRAKE CALIPER ANCHOR PLATE Figure 32-1. Main Landing Gear 32-2 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 32 NOSE GEAR SPRING SUPPORT ASSEMBLY NOSE GEAR ASSEMBLY NOSE GEAR SPRING FORK ASSEMBLY Figure 32-2. Drag Link Spring Revision 0 FOR TRAINING PURPOSES ONLY 32-3 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 32 32-4 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CHAPTER 33 LIGHTS 33 INTRODUCTION This chapter presents the interior and exterior lighting systems on the Cessna 208 ­series aircraft. General maintenance considerations are included in each section along with a description of components and operation. References for this chapter and further specific information are in Chapter 33 Lights, Chapter 5 Time Limits/Maintenance Checks, and Chapter 12 Servicing of the Manufacturer’s Maintenance Manual. GENERAL The aircraft lighting systems are described in one of the following two lighting sections in this chapter. The interior lighting section consists of: • Cockpit lighting • Overhead console lighting • Floodlights • Passenger cargo lights • All associated controls The exterior lighting section consists of: • Landing lights • Taxi and recognition lights Revision 0 • Navigation lights • 5-amp INST LIGHT • Anti-collision lights • 5-amp WING ICE DET LIGHT • Courtesy light • 5-amp SEAT BELT SGN • Ice detector lights • 10-amp RIGHT LDG LIGHT Circuit breakers for the system include the following: • 15-amp TAXI LIGHT • 10-amp LEFT LDG LIGHT • 10-amp NAV LIGHT • 5-amp STROBE LIGHT • 5-amp RADIO FLOOD LIGHT • 10-amp BEACON LIGHT • 2-amp MAP LIGHT FOR TRAINING PURPOSES ONLY 33-1 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 33 33-2 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CHAPTER 34 NAVIGATION 34 INTRODUCTION This chapter describes the various systems and instruments that allow the crew to navigate the aircraft. These include the pitot-static system, Garmin G1000 Integrated Avionics System, gyros, compasses, VOR and indicators. Because Federal Aviation Regulations require malfunctioning instruments be sent to an approved instrument overhaul and repair station or returned to the manufacturer for servicing, the chapter does not deal with specific instrument repairs GENERAL The Garmin G1000 integrated avionics system presents flight instrumentation, position, navigation, communication, hazard, and identification information to the pilot through large format displays. The system includes a weather radar, terrain avoidance and warning system (TAWS) information, flight information, and traffic advisory system (TAS). Revision 0 FOR TRAINING PURPOSES ONLY The system uses G1000 line replaceable units (LRUs) for major subsystems and supporting equipment. The system is regulated and coordinated by central processing computers in the two Garmin integrated avionics units (GIAs), which contain essential navigation and communications avionics equipment. 34-1 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL FOR N 30 60 E 120 150 STEER 359 028 059 090 120 148 N 24 21 S FOR S 210 240 W 300 330 STEER 176 207 238 270 302 330 ON A MAX RPM TORQUE 1900 1865 1800 1970 1700 1970 1600 1970 ANNUN PANEL LAMP NIGHT FIRE DETECT TEST GENERATOR OFF EMERGENCY POWER LEVER AUX FUEL PUMP ON FUEL PRESS LOW VOLTAGE LOW VACUUM LOW RESERVOIR FUEL LOW LEFT FUEL LOW RIGHT FUEL LOW STBY ELEC PWR ON DOOR WARNING DAY BATTERY OVERHEAT BATTERY HOT CHIP DETECTOR STARTER ENERGIZED IGNITION ON FUEL SELECT OFF STBY ELEC PWR INOP WINDSHIELD ANTI-ICE 5 10 TORQUE 0 FT-LB X100 DE-ICE PRESSURE 8 15 20 25 12 16 4 20 0 PROP T.O RPM X 100 OFF 3456 12 ITT 7 ¡C x 100 ST.LIM 1090¡ 10 11 40 Ng %R 20 8 0 9 9 1 3 5 PSI 2 3 1FUEL FLOW 140 110 55 ¡C 10 40 100 2 7 OIL 85 80 8 6 120 60 -40 5 6 7 8 8 10 6 FUEL 9 12 14 16 QTY 11 G 4 3 4 2 E 2 1 E PPHX100 5 0 4 4 3 4 0 2 1 E 0 AL LONS X 1 BA SE LBSX100 GAL D ON 6.7 LBS 5 6 7 8 8 10 6 FUEL 9 12 14 16 QTY 11 G RESET 1 6 E N1 OFF HLD 128.55 USE STBY ON SEAT BELT PITOT/STATIC HEAT NAV TO GS 15 OFF 2 S FR ALT NAV FPL D NRST 2:3 1 BFO FRQ CAL SET >CLR AIRSPEED CRSR OTH PULL SCAN ENT ADF FLT ET FRQ FLT ET SET IDT NAV PULL RAD H 160 80 140 120 1 2 0 0 7 100 0 FEET 1 ALTITUDE 2 29.7 29.8 6 P U LL FOR QUICK ER T EC 5 4 3 0 0 0 1 9 TST V 8888 ALT ON R GND SBY TST SBY GND L W 30 24 R ON ALT OFF PUSH VFR 2 MIN TURN D.C. ELEC. SBY OFF RNG 8 ON ALT OFF ON TST 0 80 0 0 100 KT 71 TSO BRT 2 1 TOTAL HOURS SBY VFR 888 FL IDT PULL IDENT 9 60 OFF KT 79 TSO COMM 240 40 VOL RST 1200 SBY 40 KNOTS 200 180 STBY / TIMER BFO 071 STBY / RAD PULL 25K PULL TEST ACT USE 068 USE KX 165 TSO USR KR 87 TSO ADF 117.90 STBY NDB OBS 323 ANT ADF PULL RAD 123.25 NDB MSG PULL IDENT 128.55 W VOR ¡¡¡¡¡¡¡¡¡¡¡ Alt 1400ft OBS ---¡ Pass Ok? STBY / RAD COMM USE NAV DH MSG V ENG S 0 CCW 1 2 RADAR ALT X 100 FEET 2 MIN TURN D.C. ELEC. 10 A ARM L T SET 3,000 FT PULL VS VACUUM .5 1 0 .5 1 VERTICAL SPEED FT/MIN X 1000 2 3 VENT PULL ON 2 PUSH XPDR 1 RNG VP 60 MAP TEST NAV 5 WARNING XPDR 2 ASSURE THAT SEAT IS LOCKED IN POSITION PRIOR TO TAXI, TAKEOFF, AND LANDING. FAILING TO PROPERLY LATCH SEAT AND HEED THE SAFETY INSTRUCTIONS CAN RESULT IN BOTH INJURY OR DEATH. TRK 40 TRK 20 3 4 UP PHONE WARNING DN GAIN PULL STAB OFF FD TEST DN ALT HDG ALT HDG GS NAV APR BC NAV APR BC KFC 150 FD TRIM TEST ASSURE THAT ALL CONTAMINANTS, INCLUDE WATER, ARE REMOVED FROM FUEL AND ALL SYSTEM BEFORE FLIGHT. FAILURE TO AS???? INSTRUCTIONS AND OWNER ADVISORIES ???? TO FLIGHT CAN RESULT IN BODILY INJURY DEATH. AP MIC AP ENG CABIN YAW DAMP LIGHTS BRT MIC 34.5 nm Baro:30.00" RMI 130¡ ANNUN ON OFF ON 068 USE PULL TEST UP NO SMOKE KMA 24 TSD T SLAVE GPS WAYPOINT 20 15 PHONE 117.90 PULL 25K S 2 123.25 KX 165 TSO N2 24 21 OB RIGHT LDG BCN MIC PHONE CW ARM ACTV R COM 1 COM 2 TEL INT EXT OFF TIL FREE L ADF AUTO Wx WxA GPS APR NAV ON --.- NM' - - - KT - - MIN NAV VOLT STROBE 29.8 3 FT/MIN X 1000 MKR APT 12 S 15 12 .5 3 -50 0 VERTICAL SPEED DME 3 BATT 1 .5 1 NAV 2 N NAV GS 1 COM 2 29.7 E 24 HDG W TEL N 200 LEFT LDG SPEAKER HI LO S E N S 33 21 ALT OVERSPEED GOVERNOR PUSH TO TEST MKR T S T A O M 33 A D F GEN 150 25 LIGHTS TAXI/ RECOG ON VS 30 NAV A D F 30 5 TRIM DC 8 100 AMPS 15 10 VOLTS 20 4 ENCODING GA M 7 33 N 5 0 6 3 CAP O OFF 30 50 7 100 GS 0 1005 ALT GS 6 SUCTION IN HG VENT PULL ON IN.Hg REV A MP 10 20 1010 mb 2 ALT NAV APR BC 6 15k 20k 25k 30k 10 20 8 AP HDG 3 3 2 20 10 1 S 21 120 5 4 H 80 140 30 PROP ANTI-ICE AMPS MP 160 20 10 FEET 15 5 60 9 E 12 6 240 40 DH H 7 180 0 100 40 KLN 89B TSO GPS MP QUARTZ 3 4 KNOTS H 10 20 2 MP 0 200 CLOCK E L T MAX WT MANEUVER SPEED 148 KIAS SEE POH FOR OTHER WEIGHTS AIRSPEED 11 12 1 A U T O 0 AL LONS X 1 BA SE LBSX100 GAL D ON 6.7 LBS AIR 10 9 8 ON 4 2 E 6 N208FS TEST OIL PRESS LOW OFF 34 ENGINE FIRE NO STALL HEAT ON DEICE/ANTI-ICE W/S WING LIGHT PROP BOOT PRESS AUTO OFF L FLT PANEL L FLOOD LOCK R FLT PANEL R FLOOD INERTIAL SEPARATOR BYPASS-PULL NORMAL-PUSH OFF LWR PANEL/ PED/OVHD SW/CKT BKR MANUAL ALT STATIC AIR PULL ON PARKING BRAKE PULL CABIN HEAT AIR CONDITIONING ENG INST RADIO COOL LEFT AC FANS AFT HIGH RIGHT TEMP HOT BLEED AIR HEAT ON MIXING AIR GND-PULL FLT-PUSH AFT CABIN-PULL FWD CABIN-PUSH DEFROST-PULL FWD CABIN-PUSH OFF VENTILATE LOW OFF NOTES Figure 34-1. Avionics Systems (King) 34-2 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL N FOR 30 60 E 120 150 STEER 359 028 059 090 120 148 N 24 21 FOR S 210 240 W 300 330 STEER 176 207 238 270 302 330 RESERVOIR FUEL LOW SPARE LEFT FUEL LOW RIGHT FUEL LOW STBY ELEC PWR ON SPARE CHIP DETECTOR STBY ELEC PWR INOP IGNITION ON 20 0 FUEL SELECT OFF WINDSHIELD ANTI-ICE 10 15 5 TORQUE FT-LB X 100 DE-ICE PRESSURE 12 8 16 4 TO 20 0 PROP 25 OFF 12 3456 ITT 7 °C X 100 ST.LIM 1090° MAX WT MANEUVER SPEED 148 KIAS SEE POH FOR OTHER WEIGHTS 120 60 Ng % RPM 0 9 9 10 11 RPM X 100 40 20 8 1 8 PSI -40 4 5 DISCONNECT AUTOPILOT AT FIRST INDICATION OF ICE ACCRETION. AIRSPEED 3 4 5 120 VS MKR MUTE HI LO SQ OFF/ VOL 29.7 SENS TERR INHIB TEST TERR COM2 COM3 NAV1 COM1 MIC COM2 MIC COM3 MIC COM 1/2 gs TERR N/A TERR COM1 HDG YD 29.8 TERR INHIB P ALT AP a lt A YD R M NAV2 DME FD PA CREW 1.300 A R M ALE RT PULL PASS VOL HDG NAV APR VS ALT SEL UP NEWBERG D (H) KFC 225 17S 18 9 2S6 KUAO 2 15 S 3 6 E FREE CW SLAVE CCW ARM ACTV R GPS WAYPOINT NAV 0 1 RADAR ALT X 100 FEET 20 15 2 MIN TURN ELEC VOLPUSH ID VLOC 10 2 N1 OFF HLD 71K KICT 240 DIS ––– O M O M GS 72K 10 nm –2 overzoom VLOC CDI OBS 0.0 FPL VNAV C C VOL/ PUSH SQ V COM 121.900 118.200 VLOC V VOL/ PUSH ID COM 110.30 113.80 VLOC ENR PUSH C/V VLOC CDI 19R VFR DIS DIK 14 KICT GS 2.0nm –2 overzoom OBS N M ––– N M 0.0 NAV MSG ––– 0 STBY 1 2 ANT ADF FPL D MENU CLR ENT DEFAULT NAV K L Trk: GS: Custom Map 4363 NO SMOKE ON SEAT BELT CABIN MIC PITOT/STATIC HEAT STALL HEAT ON DEICE/ANTI-ICE W/S WING PRIMARY LIGHT W/S PROP SECONDARY AUTO OFF OFF BOOT PRESS L FLT PANEL L FLOOD 3 4 KR 87 TSO 332 BFO FRQ ADF FL LOCK R FLT PANEL R FLOOD FD ALT HDG ALT HDG GS NAV APR BC NAV APR BC 13.5 nm 5 6 013 7 TEST LWR PANEL/ PED/OVHD SW/CKT BKR FUNC CRSR START STOP CLR 8 FLT ET SET OPERATION OF THE ANTI-ICE PANEL MAY CAUSE COMPASS DEVIATION OF MORE THAN 10 DEGREES 2605028-2 PARKING BRAKE PULL W R VACUUM 29.7 6 5 4 3 29.8 .5 1 0 .5 1 VERTICAL SPEED FT/MIN X 1000 2 3 RST 2 OFF WX AIRSPEED DECREASE OF 10 KIAS THAT CANNOT BE PREVENTED BY INCREASE TO MAX CONTINUOUS POWER. TRFC BLEED AIR HEAT ON LOW MIXING AIR GND-PULL FLT-PUSH PHONE AIRSPEED OF 120 KIAS CANNOT BE MAINTAINED IN LEVEL FLIGHT. TERR MIC MEA OR MOCA IF APPLICABLE ON CURRENT LEG FALLS INTO AREA “C” OF ICING SERVICE CEILING CHART CONTAINED IN SECTION 5 OF THE POH/AFM KNOWN ICING EQUIPMENT SUPPLIMENT. 2605070–8 RNG DATA RNG: 80 n m TRK:240 GS: 18 KT POS: 0.5SE KICT WICHITA AP ENG VENT PULL ON PUSH AP TEMP HOT 2 24 21 RNG OFF VENTILATE 2 MIN. NO PITCH INFORMATION 1 VOL OVLY WARNING ASSURE THAT SEAT IS LOCKED IN POSITION PRIOR TO TAXI, TAKEOFF, AND LANDING. FAILURE TO PROPERLY LATCH SEAT AND HEED ALL SAFETY INSTRUCTIONS CAN RESULT IN BODILY INJURY OR DEATH.LLLLLLLLLLLLLLLLLLLLLLLLLL 0705097-1 AUX WARNING CABIN HEAT RIGHT L FEET ADF 6 : 1 1 FLTET FRQ ON OFF AC FANS AFT HIGH PULL FOR QUICK E RECT RES RES AIR CONDITIONING LEFT 7 0 ALTITUDE 9 SKYWATCH COOL 10 20 N MAP RADIO 10 20 100 D.C. ELEC. MENU ENT OFF ON ENG INST 8 100 CONTINUED FLIGHT IN ICING CONDITIONS IS PROHIBITED AFTER ENCOUNTERING ONE OR MORE OF THE FOLLOWING: GPS INERTIAL SEPARATOR BYPASS-PULL NORMAL-PUSH 20 10 RES VIR PUSH CRSR TRIM 20 10 STBY / TIMER BFO PROC KFC 150 UP Distance: OFF MANUAL ALT STATIC AIR PULL ON FD DN LIGHTS BRT 120 PRESSURE ALT ALT PHONE 80 140 GTX 330 ALT RNG ––––– 19L 9 60 OFF ON PUSH CRSR DPT N 40 160 343° 135 kt Info USE PWR TEST IDENT ENT GPS PROC KNOTS 240 40 TURN COORDINATOR CLR DEFAULT NAV K L NAV MSG Baro: Pan 200 180 4S9 10,300 ft 29.92” Out KC MENU GNS 430 N2 4 Alt: 7S9 AIRSPEED + ON OFF 343° FN D --.- NM' - - - KT - - MIN 3 5 O M TRK ENR COM Zoom:(Trk Up) 50 nm RNG In ––– 110.30 113.80 LOC ICT KICT ILS 01R PUSH C/V DH MSG RIGHT LDG BCN S OB ––– DTK VLOC V V GPS N BY L VOL SQ XTK K32 COM 126.700 126.700 C PWR PUSH 34 0 LONS X 1 03S S48 5S9 27 117.40 UBG 065°FR 15NM ST 1 NAV VLOC AL L S E DB S X 1 0 0 /G A L O N 6. 7 L B S Wpt Bearing: W58 7S3 0 DN ALT 9 18 18 W56 40 400 40 PORTLAND 27 11 KVOO 20 59S201W1 D PORTLAND 9 AP KPDX 4S4 (L)---- 114.80 PDX 40 18 KTTD KHIO 17 40 23 COPILOT ARM FT REV BATTLE GROUND KSPB 27 D 40 (H)----116.60 BTG PDX F FT/MIN X 1000 C W BA 5 6 7 8 8 10 6 FUEL 9 12 14 16 QTY. 11 GMX 200 Waypoint: SQ PILOT ICS ISOLATION VOL OF .5 3 24 0 LONS X 1 S E DB S X 1 0 0 /G A L O N 6. 7 L B S 4 2 E 33 N 0 VERTICAL SPEED S .5 21 2 N 12 1 15 GS AL L 4 3 2 1 E TEST ADF SPKR CABIN AUDIO R AP 5 6 7 8 8 10 6 FUEL 9 12 14 16 QTY. 11 30 24 GPS APR NAV ON TRIM PILOT NAV VOLT -50 STROBE GA M 33 BATT W N NAV HDG 21 ALT 200 OVERSPEED GOVERNOR PUSH TO TEST CAP O 30 A D F GEN 150 LEFT LDG 5 ALT GS 12 NAV 25 LIGHTS TAXI/ RECOG ON 4 ENCODING REV A DC 8 100 30 6 3 NAV APR BC 4 2 E GMA 340 A O M AP HDG BA KMMV A D F 15 10 VOLTS 20 7 33 5 0 10 20 30 50 2 IN.Hg 1005 100 GS 0 1 5 7 SUCTION IN HG AMPS FEET ALT 1010 mb 0 100 6 15k 20k 25k 30k 2 VENT PULL ON 8 20 10 10 20 80 140 5 4 3 20 10 160 30 PROP ANTI-ICE AMPS 60 9 E 6 DH 6 7 240 40 H QUARTZ 180 MP 2 40 3 10 20 CLOCK KNOTS PPH X 100 2 1 E H MP 0 200 H MP 10 9 8 ICE DET P/TEST 11 12 1 0 4 3 4 2605070-6 AIR ICE DETECTOR SYSTEM IS ADVISORY ONLY 2 1FUEL FLOW3 0 3 6 °C 10 40 100 2 7 140 110 55 OIL 85 80 15 S VACUUM LOW STARTER ENERGIZED 12 FUEL PRESS LOW H VOLTAGE LOW DOOR WARNING DAY AUX FUEL PUMP ON MP EMERGENCY POWER LEVER G GENERATOR OFF G N208FS TEST OIL PRESS LOW OFF TEST ENGINE FIRE MAX RPM TORQUE 1900 1865 1800 1970 1700 1970 1600 1970 BELOW ICING MIN SPD ETM E ANNUN PANEL LAMP NIGHT FIRE DETECT ENGINE 6 120 KIAS MINIMUM IN ICING FLAPS UP EXCEPT 110 KIAS IF CLIMBING TO EXIT ICING. 2605070-5 NO 3 ON A AFT CABIN-PULL FWD CABIN-PUSH DEFROST-PULL FWD CABIN-PUSH ASSURE THAT ALL CONTAMINATES, INCLUDING WATER, ARE REMOVED FROM FUEL AND FUEL SYSTEM BEFORE FLIGHT. FAILURE TO ASSURE CONTAMINATE FREE FUEL AND HEED ALL SAFETY INSTRUCTIONS AND OWNER ADVISORIES PRIOR TO FLIGHT CAN RESULT IN BODILY INJURY OR DEATH.LLLLLLLLLLLLLLLLLLLLLLLLLLLLLLLLLL 0705098-1 OFF NOTES Figure 34-2. Avionics Systems (G530) Revision 0 FOR TRAINING PURPOSES ONLY 34-3 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL 30 33 N HDG HDG 10100 9800 328° 30 33 N 21 INSET S ?????? OBS 15 OAT__– 5°c CDI GMN 331° 38.0NM FRAME 324° 73.2NM 334° 10.0NM 50.0NM FLW NAV2 XPDR1 4234 ALT R LCL 08:44:27 XPDR IDENT TMR/REF NRST ALERTS MKR MUTE HI SENS DME NAV1 ADF NAV2 PAN D MENU PROC OFF DFLT MAP ENG INTFC ADC 1 AHRS 1 PFD 1 XPDR 1 ADF 1 5 5 5 5 5 5 2 50 A/P CONT ELT NAV INTFC RADIO ALT RADAR R/T 5 5 5 5 5 5 COM 2 NAV 2 MFD ADC 2 AHRS 2 PFD 2 XPDR 2 5 5 5 5 5 5 PROP RPM XM–DATA LINK STM SCOPE HF RCVR HF AMP 5 5 5 5 5 30 700 KHJO PASS FMS V27 V107 96.5 1900 OIL PSI 95 OIL °C 85 KRFL KSMX V27 V137 V183 FFLOW PPH 379 BAT AMPS BUS VOLTS 4 28.5 A–ICE GAL 4.7 V107 V25 V186 V137 V22 V386 XWHP V107 XBUR V107 150NM V197 V23 MAP WPT AUX NRST TERRAIN AIRWY LO STRMSCP NEXRAD XM LTNG D MENU FPL PROC CLR DFLT MAP BACK 10 10200 10100 HDG ENT OAT__– 5°c FMS ?????? INSET 37.9NM EHF NAV1 SENSOR PFD 9900 10 33 GPS 80 127.100 COM1 122.450 COM2 CRS 331° N ENR OBS CDI PUSH VOL SQ 0 5 1 0 0 COM EMERG 2 1 PUSH 1-2 ON BARO -900 ARM PUSH STD 9700 29.92IN 1 10 ARTEX ELT 1 9800 328° 328° 30 PUSH CRSR TEMP °C 30+ 0 –30 100 40 200 180 AIRSPEED 160 140 KNOTS 120 100 8 60 9 2 TEST/RESET PRESS ON WAIT 1 SECOND PRESS ARM RANGE – + PUSH PAN DME 50.0NM FLW NAV2 XPDR XPDR1 IDENT 4234 ALT TMR/REF R LCL NRST 08:44:27 ALERTS D MENU FPL PROC CLR DFLT MAP ENT FMS 7 VACUUM ALTIMETER 6 PUSH CRSR 1 4 5 VENT–PULL ON HF FEET 0 1015 1010 80 1 2 3 10 15 5 TORQUE 29.8 29.9 30.0 20 0 FT–LB X 100 5.000 E R 1 EMER T.O. VOL 25 PUSH PWR TEST FUNC FREQ CHAN MOD RX PHONE TUNE ENT TX SQL OPT MIC LOCK 332 ADF INERTIAL SEPARATOR KR 87 TSO BYPASS–PULL NORMAL–PUSH ADF BENDIX / KING CB/PED/ OVHD LEFT FLOOD 3:10 USE FRQ FLT ET SET RST AIR CONDITIONING RIGHT FLOOD WARNING ADF FLT ASSURE THAT ALL CONTAMINATES, INCLUDING WATER, ARE REMOVED FROM FUEL AND FUEL SYSTEM BEFORE FLIGHT. FAILURE TO ASSURE CONTAMINATE FREE FUEL AND HEED ALL SAFETY INSTRUCTIONS AND OWNER ADVISORIES PRIOR TO FLIGHT CAN RESULT IN BODILY INJURY OR DEATH.LLLLLLLLLLLLLLLLLLLLLLLLLLLLLLLLLL 0705098-1 STBY/TIMER BFO COOL PARKING BRAKE PULL KVCV DISPLAY BACKUP DIMMING SW/CB PNLS / ANNUN STANDBY IND V12 10 10 PAN KPMD 128.375 121.500 20 PUSH KWJP V201 KCMA KNTD 316 + KEDW V27 TOPO 120 331° 310000 100 130 – KMHV GMN V12 KSBA 20 145 PUSH STD V23 20 150 RANGE V25 BRG 140 V459 KVBC 1-2 L KNID DIS 38.0NM EHF AP YD ALT 10000FT 10 000 10300 160 PUSH 1-2 V165 EHF FUEL QTY LBS R TRAFFIC PUSH BARO V485 GMN GPS 115.40 EHF 117.80 FLW NAV KPTV V23 KDLO KSBP NAV1 116.90 NAV2 112.50 PUSH VOL ID COM 170 0 AVIONICS PUSH VOL SQ TRACK UP V165 V459 R 16 CONTINUED FLIGHT IN ICING CONDITIONS IS PROHIBITED AFTER ENCOUNTERING ONE OR MORE OF THE FOLLOWING: AIRSPEED OF 120 KIAS CANNOT BE MAINTAINED IN LEVEL FLIGHT. AIRSPEED DECREASE OF 10 KIAS THAT CANNOT BE PREVENTED BY INCREASE TO MAX CONTINUOUS POWER. MEA OR MOCA IF APPLICABLE ON CURRENT LEG FALLS INTO AREA”C” OF ICING SERVICE CEILING CHART CONTAINED IN SECTION 5 OF THE POH/ AFM KNOWN ICING EQUIPMENT SUPPLEMENT. 10KT SQ PRESS ALT ADF 2 127.100 COM1 122.450 COM2 128.375 121.500 DIS 38 KVISV459 24CL V113 100 PLAY COPLT ENT 2605070-10 TAS GS 175 V137 KPRB 900 O F F 2 141618 AVN BUS 2 DME % RPM 12 180 A/P SERVOS V248 20 CREW PUSH CRSR NAV 1 °C ICS ISOLATION PILOT 331° MAP - NAVIGATION MAP 600 0 L PILOT DTK C80 ITT 1-2 TAS PHONE SPKR 200 TEST SWITCH FIRE DETECT–UP FUEL SELECT OFF–DN TEL PA VOL AVN BUS 1 AUDIO COM 1/2 ETE 13:47 EMERG 1650 0 MAN SQ FPL CLR FT–LB X100 10 AUX EHF KFAT DME COM3 + PUSH THE SIGHT GAGE ON THE TKS TANK IS THE ONLY APPROVED MEANS OF ASSURING ADEQUATE DISPATCH FLUID QTY COM 1 ALTSTATIC AIR PULL ON – V23.FRAME 700026 MIC PUSH STD RANGE DTK DIS – – –° – – – –NM N Ng 1 KLGB / KFAT VENT–PULL ON OVERSPEED GOVERNOR PUSH TO TEST BARO 2 115.40 EHF 117.80 FLW 15 PUSH 1-2 -900 116.90 112.50 NAV PUSH FLIGHT PLAN 12 BACKUP ON NAV 1 NAV 2 TRQ PUSH VOL ID E OFF FLUID CONTROL MAX FLOW AIRFRAME N O R M WINDSHIELD 9700 29.92IN COM2 COM3 MIC 2 1 COM2 MIC PUSH DIR 6 24 ENR E PRIMARY HIGH 331° PUSH VOL SQ COM EMERG PUSH DIR 3 GPS CRS 6 ANTI-ICE 37.9NM EHF NAV1 SENSOR PFD 9900 10 328° CABIN O F F WINDSHIELD ANTI-ICE MUST BE OFF FOR TAKEOFF AND LANDING 10200 3 SEAT BELT ON 127.100 COM1 122.450 COM2 COM1 EMERGENCY USE ONLY 10 130 W NO SMOKE WING LIGHT 10 140 120 128.375 121.500 20 3100 00 100 80 MANUAL STALL HEAT ON 10 150 BCN PUSH SYNC COM1 MIC 2605076-5 C R E W PROP HEAT AUTO P/S HEAT / LOW A/S AWARE 20 CRS2 SPD W NAV ON 331° FLC DN 24 160 20 145 STROBE BRG VS VNV UP 10 000 10300 170 1-2 OFF DIS 38.0NM EHF AP YD ALT 10000FT ALT ALT SEL YD 21 RIGHT LDG PUSH POWER OUTLET ALL GMN GPS 115.40 EHF 117.80 FLW NAV XFR AP S LEFT LDG NAV1 116.90 NAV2 112.50 PUSH VOL ID FD BANK 15 N208FS LIGHTS TAXI/ RECOG ON NAV CRS1 BC 12 34 APR HDG BELOW ICING MIN SPD WHEN TAKEOFF TORQUE SETTINGS ARE BELOW 1865 FT-LBS, THE AIR CONDITIONER MUST BE OFF FOR TAKEOFF AND LANDING 2605031-3 MAX WT MANEUVERING SPEED 148 KIAS SEE POH OTHER WEIGHTS LEFT AC FANS AFT HIGH RIGHT OFF VOL TEMP HOT BLEED AIR HEAT ON WARNING ASSURE THAT SEAT IS LOCKED IN POSITION PRIOR TO TAXI, TAKEOFF, AND LANDING. FAILURE TO PROPERLY LATCH SEAT AND HEED ALL SAFETY INSTRUCTIONS CAN RESULT IN BODILY INJURY OR DEATH.LLLLLLLLLLLLLLLLLLLLLLLLLL 0705097-1 CABIN HEAT MIXING AIR AFT CABIN–PULL GND–PULL FWD CABIN–PUSH FLT–PUSH DEFROST–PULL FWD CABIN–PUSH OFF DAY VENTILATE LOW OFF NOTES Figure 34-3. Avionics Systems (G1000) 34-4 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES NAV 1 NAV 2 TRQ PUSH VOL ID 116.90 112.50 115.40 EHF 117.80 FLW 15 NAV FT–LB X100 10 DTK 331° GS 175 C80 KHJO °C 0 Ng 50 12 % RPM PROP RPM V248 20 KPRB 900 700 V27 COM KPTV V23 96.5 95 OIL °C 85 1-2 BARO V485 V107 1900 PUSH KDLO KSBP EHF V165 KRFL KSMX V27 PUSH STD RANGE V25 V137 V183 V23 GMN FFLOW PPH 379 BAT AMPS BUS VOLTS 4 28.5 A–ICE GAL 4.7 V107 PUSH PAN KWJP KPMD V201 V107 TOPO V137 V22 KCMA KNTD 316 + KEDW V12 KSBA V25 V186 V27 – KMHV FUEL QTY L LBS R O F F L KNID V459 KVBC 34 V165 V459 R V137 V113 100 OIL PSI TRAFFIC 10KT PUSH VOL SQ TRACK UP EMERG 24CL 600 1-2 127.100 COM1 122.450 COM2 KVISV459 ITT PUSH 128.375 121.500 DIS 38 MAP - NAVIGATION MAP N 1650 0 ETE 13:47 V12 KVCV V386 XWHP V107 XBUR 150NM V197 V23 MAP WPT AUX NRST TERRAIN AIRWY LO STRMSCP NEXRAD XM LTNG BACK D MENU FPL PROC CLR ENT DFLT MAP FMS PUSH CRSR Figure 34-4. G1000 MFD Power-Up Page Revision 0 FOR TRAINING PURPOSES ONLY 34-5 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES HIGH-SPEED DATA BUS (ETHERNET) GDL 69A XM SATELLITE RADIO RECEIVER REAL-TIME WEATHER DIGITAL AUDIO ENTERTAINMENT 34 NO. 1 GIA 63W INTEGRATED AVIONICS UNIT SYSTEM INTEGRATION PROCESSORS I/O PROCESSORS VHF COM VHF NAV/LOC GPS GLIDE SLOPE AFCS MODE LOGIC FLIGHT DIRECTOR CALCULATIONS SERVO MANAGEMENT GPS OUTPUT GDC 74A #1 AIR DATA COMPUTER OAT AIRSPEED ALTITUDE VERTICAL SPEED GWX 68 ONBOARD RADAR GDC 74A #2 AIR DATA COMPUTER OAT AIRSPEED ALTITUDE VERTICAL SPEED GRS 77 #1 AHRS ATTITUDE RATE OF TURN SLIP/SLID GRS 77 #2 AHRS ATTITUDE RATE OF TURN SLIP/SLID NO. 2 GIA 63W INTEGRATED AVIONICS UNIT SYSTEM INTEGRATION PROCESSORS I/O PROCESSORS VHF COM VHF NAV/LOC GPS GLIDE SLOPE AFCS MODE LOGIC FLIGHT DIRECTOR CALCULATIONS SERVO MANAGEMENT GPS OUTPUT GEA 71 ENGINE/AIRFRAME UNIT GTX 33 TRANSPONDER GMU 44 #1 MAGNETOMETER HEADING GSA 81 PITCH TRIM GMU 44 #2 MAGNETOMETER HEADING GSA 81 PITCH GSA 80 ROLL GTX 33 TRANSPONDER GSA 80 YAW Figure 34-5. Garmin G1000 Integrated Avionics Architecture 34-6 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES HIGH SPEED DATA BUS (ETHERNET) GDU 1040A PFD HIGH SPEED DATA BUS (ETHERNET) DISPLAY OF FLIGHT INSTRUMENTATION DISPLAY OF FLIGHT INSTRUMENTATION NO. 1 GIA 63W INTEGRATED AVIONICS UNIT GDU 1040A MFD HIGH SPEED DATA BUS (ETHERNET) HIGH SPEED DATA BUS (ETHERNET) NO. 1 GDC 74A AIR DATA COMPUTER NO. 2 GDC 74A AIR DATA COMPUTER OAT AIRSPEED ALTITUDE VERTICAL SPEED OAT AIRSPEED ALTITUDE VERTICAL SPEED GDU 1040A PFD 34 DISPLAY OF FLIGHT INSTRUMENTATION NO. 2 GIA 63W INTEGRATED AVIONICS UNIT GPS OUTPUT GPS OUTPUT NO. 1 GRS 77 AHRS NO. 2 GRS 77 AHRS ATTITUDE RATE OF TURN SLIP/SKID ATTITUDE RATE OF TURN SLIP/SKID NO. 1 GMU 44 MAGNETOMETER NO. 1 GMU 44 MAGNETOMETER HEADING HEADING Figure 34-6. G1000 Flight Instrument Data Paths Revision 0 FOR TRAINING PURPOSES ONLY 34-7 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL GMA 1347 #2 (OPT) AUDIO PANEL NOTES REVERSIONAL CONTROL MARKER BEACON INTERCOM CONTROL DIGITAL AUDIO CONTROL REV. MODE 34 GDU 1040A MFD HIGH-SPEED DATA BUS (ETHERNET) REV. MODE TRANSPONDER INTERFACE (REVERSIONARY MODE ONLY) HIGH-SPEED DATA BUS (ETHERNET) CONTROL & DISPLAY OF: COM/NAV RADIOS VARIOUS NAVIGATIONAL FUNCTIONS GDU 1040A PFD GDU 1040A PFD CONTROL & DISPLAY OF: COM/NAV RADIOS TRANSPONDER INTERFACE VARIOUS NAVIGATIONAL FUNCTIONS CONTROL & DISPLAY OF: COM/NAV RADIOS TRANSPONDER INTERFACE VARIOUS NAVIGATIONAL FUNCTIONS HIGH-SPEED DATA BUS (ETHERNET) NO. 1 GIA 63W INTEGRATED AVIONICS UNIT VHF COM VHF NAV/LOC GPS GLIDESLOPE VARIOUS I/O PROCESSORS DIGITAL COM/NAV AUDIO VOICE ALERTS GMA 1347 AUDIO PANEL REVERSIONAL CONTROL MARKER BEACON INTERCOM CONTROL DIGITAL AUDIO CONTROL NO. 2 GIA 63W INTEGRATED AVIONICS UNIT GTX 33 MODE S TRANSPONDER VHF COM VHF NAV/LOC GPS GLIDESLOPE VARIOUS I/O PROCESSORS DIGITAL COM/NAV AUDIO VOICE ALERTS GTX 33 MODE S TRANSPONDER (OPTIONAL) Figure 34-7. G1000 Navigation/Communication Data Paths 34-8 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CHAPTER 35 OXYGEN 35 INTRODUCTION This chapter describes the oxygen systems. In addition to system description, the chapter emphasizes maintenance and servicing precautions along with functional testing. References for this chapter and further specific information is in Chapter 35 Oxygen, Chapter 5 Time Limits/Maintenance Checks, and Chapter 12 Servicing of the Manufacturer’s Maintenance Manual. OXYGEN SYSTEMS There are seven oxygen systems that are ­available for the 208 Caravan: • 17-port system with two pressure compensated regulators • 14-port system with two pressure compensated regulators • 13-port system with two compensated regulators • 10-port system with two pressure compensated regulators • 10-port system with a single pressure compensated regulator • 8-port system with two pressure compensated regulators • 2-port system with a non-pressure compensated regulator Revision 0 The two-port system uses a 50.67 cubic-foot capacity oxygen cylinder. The 8-port, 10-port, 13-port, 14-port, and 17-port systems use a 116.95 cubic-foot capacity oxygen cylinder. Both oxygen cylinders are composite c­ onstruction and include a shutoff valve. All 116.95 cubic-foot capacity oxygen cylinders have an altitude compensated regulator that changes oxygen pressure with altitude. 208B0466 through thru 208B1170), and 17-port system (airplanes 208B0466 and on), there are two altitude compensated regulators to change the oxygen output with altitude. The 50.67 cubic-foot oxygen cylinders without an altitude compensated regulator keep an operating pressure of 70 psi and must have quick-don oxygen masks with a mounted diluter demand regulator. On aircraft equipped with the 10-port system, (aircraft 20800208 through 20800395), there is a single pressure compensated regulator to change the oxygen output with altitude. On aircraft that have the 8-port system (aircraft 20800396 and on), 10-port system (airplanes FOR TRAINING PURPOSES ONLY 35-1 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL 0 NOTES 1000 500 1500 2000 USE NO OIL PSI OXYGEN SUPPLY PRESSURE MADE IN USA 15 ON OFF TO COPILOT’S FACE MASK TO PILOT’S FACE MASK 35 NOTE: TEN PORT SYSTEM WITH ALTITUDE COMPENSATOR REGULATOR LEGEND REGULATED/COMPENSATED PRESSURE OXYGEN ALTITUDE COMPENSATOR MODEL 208 PASSENGER HIGH-PRESSURE OXYGEN MECHANICAL ACTUATOR CONTINUOUS FLOW COUPLING FILLER VALVE Figure 35-1. Oxygen System Overview 35-2 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CHAPTER 36-37 PNEUMATICS/VACUUM 36-37 INTRODUCTION This chapter describes two small systems in the Caravan I: Pneumatic and vacuum. The pneumatic system distributes engine P3 bleed air to the heating and the ice and rain ­protection systems. The vacuum system furnishes vacuum air (suction) to operate the horizon and directional gyros. PNEUMATIC SYSTEM—GENERAL VACUUM SYSTEM—GENERAL The system consists of a pressure regulator valve and a pressure line that delivers engine bleed air to the primary heating system of the aircraft and the pneumatic deice boots. The manufacturer’s maintenance manual includes procedures on removal and installation of the pressure regulator and the distribution line. The horizontal indicator gyro in the left ­removable flight panel visually indicates the aircraft pitch and roll attitude with respect to the earth. The directional gyro directly below the horizontal indicator displays a stable indication of the aircraft heading when properly set to agree with the magnetic compass. Optional directional gyros also provide the ­autopilot with electrical heading information. Revision 0 FOR TRAINING PURPOSES ONLY 36-1 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES BLEED AIR BLEED AIR EXHAUST VACUUM EJECTOR 18 PSI PRESSURE REGULATOR 22 PSI PRESSURE RELIEF VALVE VACUUM LOW VACUUM RELIEF VALVE VACUUM LOW WARNING ANNUNCIATOR 36-37 ATTITUDE INDICATOR (VACUUM) VACUUM LOW WARNING SWITCH ATTITUDE INDICATOR (ELECTRICAL) VACUUM SYSTEM AIR FILTER DIRECTIONAL INDICATOR (ELECTRICAL) LEGEND INLET AIR DIRECTIONAL INDICATOR (VACUUM) SUCTION GAGE VACUUM BLEED AIR ELECTRIC Figure 36-1. Model 208B Vacuum System Overview 36-2 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CHAPTER 51-57 STRUCTURES 51-57 INTRODUCTION This chapter provides a general overview and description of the structural makeup of the Caravan I series aircraft. The information is general in nature and not intended to be all-inclusive. References for this chapter and further specific information are in Chapter 20 Standard Practices-Airframe, Chapter 51 Standard Practices and Structures-General, Chapter 52 Doors, Chapter 53 Fuselage, Chapter 55 Stabilizers, Chapter 56 Windows, and Chapter 57 Wings in the Maintenance Manual and the Structural Repair Manual. GENERAL Standard practices for work on the aircraft structures are in the manufacturer’s manuals. These include general descriptions along with general repair practices, materials, and procedures. Chapter 51 of the maintenance manual describes categories of damage for the many types of permissible repairs that can be performed. These include negligible damage, repairable damage, and major replacement damage. The categories provide the mechanic with some general guidelines to use in determining the extent and criticalness of any damage. Revision 0 FOR TRAINING PURPOSES ONLY In addition, extensive information on corrosion and severity maps of the world are included. The corrosion resistance of materials in the aircraft can drastically change with only small environmental changes. Corrosion is also divided into categories: light, moderate, and severe. Aircraft exposed to salt air, heavy atmospheric industrial pollution, warm humid environments, and/or over-water operations require more stringent corrosion prevention and control programs than aircraft operated in dry environments. Corrosion repair information is also available. 51-1 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 51-57 51-2 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CHAPTER 61 PROPELLERS 61 INTRODUCTION This chapter describes the propellers on the aircraft. It also includes topics such as the propeller control system, propeller governor, overspeed governor, and beta valve. Emphasis is on component locations and operation. The information also covers maintenance considerations, inspections, and functional checks. References and further specific information are Chapter 61 Propellers, Chapter 76 Engine Controls, Chapter 5 Time Limits/Maintenance Checks, and Chapter 12 Servicing of the Manufacturer’s Maintenance Manual. GENERAL There are two possible Hartzell propeller installations for the Model 208/208B airplanes. Airplanes 208B5000 and On have a HC-B3TN3AFX/T10890CNB propeller assembly installed. Airplanes 20800001 thru 20800188 and airplanes 208B0001 thru 208B0217 have a Hartzell Model HC-B3MN-3/M10083 propeller assembly installed. Revision 0 FOR TRAINING PURPOSES ONLY 1. The Model HC-B3TN-3AFX/T10890CNB propeller is a three-bladed, constant-speed, full-feathering, reversible, governorregulated propeller equipped with aluminum blades. 2. The Model HC-B3MN-3/M10083 propeller is a three-bladed, constant-speed, full-feathering, reversible, governor-regulated propeller equipped with composite blades. 61-1 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL FEEDBACK RING NOTES BLADE BASE FEATHER SPRING PISTON LOCK NUT 61 BETA ROD BLADE CLAMP LOW PITCH STOP NUT PITCH CHANGE LINK COUNTERWEIGHT Figure 61-1. Hartzell Propeller 61-2 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES BLADE ACTUATING PIN BLADE BASE PITCH CHANGE LINK FEATHER SPRING LOCK RINGS 61 PISTON PISTON ROD BETA ROD FEEDBACK RING Figure 61-2. McCauley Propeller Revision 0 FOR TRAINING PURPOSES ONLY 61-3 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL PROP. SPEED ADJ. LEVER AIR BLEED ORIFICE NOTES SPEEDER SPRING Py RELIEF VALVE AIR BLEED LINK PILOT VALVE MAX. STOP MIN. GOV. ADJ. 61 BETA VALVE TO SUMP TO PROPELLER PUMP GEARS LEGEND OIL SUPPLY PRESSURIZED OIL STATIC OIL PRESSURE BYPASS OIL PY (CDP AIR) NO FLOW GOV. PUMP CONDITION: ON SPEED ENGINE OIL SUPPLY Figure 61-3. Propeller Governor (Sheet 1 of 4) 61-4 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL PROP. SPEED ADJ. LEVER AIR BLEED ORIFICE NOTES SPEEDER SPRING Py RELIEF VALVE AIR BLEED LINK PILOT VALVE MAX. STOP MIN. GOV. ADJ. 61 BETA VALVE TO SUMP TO PROPELLER PUMP GEARS LEGEND OIL SUPPLY PRESSURIZED OIL BYPASS OIL PY (CDP AIR) NO FLOW GOV. PUMP CONDITION: UNDER SPEED ENGINE OIL SUPPLY Figure 61-3. Propeller Governor (Sheet 2 of 4) Revision 0 FOR TRAINING PURPOSES ONLY 61-5 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL PROP. SPEED ADJ. LEVER AIR BLEED ORIFICE NOTES SPEEDER SPRING Py RELIEF VALVE AIR BLEED LINK PILOT VALVE MAX. STOP MIN. GOV. ADJ. 61 BETA VALVE TO SUMP TO PROPELLER PUMP GEARS LEGEND OIL SUPPLY PRESSURIZED OIL RETURN OIL BYPASS OIL PY (CDP AIR) NO FLOW GOV. PUMP CONDITION: OVER SPEED ENGINE OIL SUPPLY Figure 61-3. Propeller Governor (Sheet 3 of 4) 61-6 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL PROP. SPEED ADJ. LEVER AIR BLEED ORIFICE NOTES SPEEDER SPRING Py RELIEF VALVE AIR BLEED LINK PILOT VALVE MAX. STOP MIN. GOV. ADJ. 61 BETA VALVE TO SUMP TO PROPELLER PUMP GEARS LEGEND OIL SUPPLY PRESSURIZED OIL RETURN OIL BYPASS OIL PY (CDP AIR) NO FLOW GOV. PUMP CONDITION: FEATHERED ENGINE OIL SUPPLY Figure 61-3. Propeller Governor (Sheet 4 of 4) Revision 0 FOR TRAINING PURPOSES ONLY 61-7 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CRUISE POSITION LEGEND OIL PRESSURE PUSH-PULL CONTROL NOTES CONDITION: BETA MODE RETURN OIL PY AIR CAM STATIC OIL IT OS EP UIS CR ION SEEDER SPRING PILOT VALVE F.C.U ARM Py AIR FUEL CONTROL UNIT RESET POST BETA VALVE AIR BLEED LINK 61 MIN. GOVERNING ADJ. TO SUMP ENGINE OIL SUPPLY BETA ROD BETA NUT Figure 61-4. Reversing Propeller Engine Controls (Full Reverse) 61-8 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL CHAPTER 71-80 POWERPLANT INTRODUCTION 71-80 This chapter describes the Pratt and Whitney PT6A powerplant installed on the Caravan I Series aircraft. Components or operational differences among models are listed in the appropriate section such as fuel, lubrication, ignition, and engine controls. General maintenance considerations in each section accompanies information on functional and operational checks. References for this chapter and further information are in Chapters 71-80, Chapter 5 Time Limits/Maintenance Checks, and Chapter 12 Servicing of the Manufacturer’s Maintenance Manual. GENERAL Power plant installed in Model 208 Series airplanes is a Pratt and Whitney Aircraft of Canada, Ltd., Model PT6A-114 (600 SHP) gas turbine engine. Airplanes 20800277 and On, Airplanes 208B0179 thru 208B2196, and 208B2198 thru 208B4999, and 208B0001 thru 208B0178, incorporating SK208-80, have a PT6A-114A (675 SHP) gas turbine engine is installed. The power plant installed in Model 208B Airplane 208B2197 and Airplanes 208B5000 and On is a Pratt and Whitney Aircraft of Canada, Ltd., PT6A-140 (867 SHP) engine. The PT6A is a free turbine engine with two independent turbine sections: One drives the compressor in the gas generator section while the second drives the propeller shaft through a reduction gearbox. Revision 0 The engine is self-sufficient because the gas generator-driven lubrication system provides lubrication for all areas of the engine. A hydro-pneumatic fuel control unit (FCU) schedules fuel flow to maintain power settings selected with a power lever. The propeller governor keeps constant propeller speeds between 1,600 rpm to 1,900 rpm (governing range). Circuit breakers for the powerplant include the following on the cockpit CB panel: • 5-amp IGN • 5-amp OIL TEMP • 5-amp ITT GAGE • 5 amp FUEL FLOW • 5 amp TORQUE IND (if electrical torque gage installed) • 10 amp FUEL CONT HEATER Cockpit controls include engine controls, ignition and start switches, engine instruments, and annunciators. • 5-amp START CONT FOR TRAINING PURPOSES ONLY 71-1 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL COMPRESSOR TURBINE REDUCTION GEARBOX ACCESSORY GEAR BOX POWER TURBINE COMPRESSOR DIFFUSER PIPE EXHAUST PROPELLER SHAFT OIL TANK 71-80 AIR INLET COMBUSTION CHAMBER FUEL NOZZLE BLEED VALVE CASE DRAIN Figure 71-1. PT6A Small Turboprop 71-2 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 71-80 Revision 0 FOR TRAINING PURPOSES ONLY 71-3 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES P2.5 LEGEND P2.5 AXIAL COMPRESSOR AIR PRESSURE P3 COMPRESSOR DISCHARGE AIR PRESSURE Pa AMBIENT AIR PRESSURE CONDITION: ENGINE RUNNING P3 SEAT SPRING PIN METERING ORIFICE Pa ROLLING DIAPHRAGM VALVE OPEN - LOW POWER SETTING 71-80 SLEEVE PISTON GUIDE PIN COTTER PIN VALVE CLOSED - HIGH POWER SETTING CONVERGENT DIVERGENT ORIFICE Figure 71-2. Compressor Bleed Valve—Pre SB 1588 71-4 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES LEGEND P2.5 AXIAL COMPRESSOR AIR PRESSURE P3 COMPRESSOR DISCHARGE AIR PRESSURE Pa AMBIENT AIR PRESSURE CONDITION: ENGINE RUNNING P2.5 P2.5 AIRAIR P3 AIR P3 AIR PISTON ADJUSTABLE PRIMARY ORIFICE TESTDIAPHRAGM PORT 71-80 FINAL METERING FINAL METERING PLUGPLUG PORT TEST TEST PORT DIFFUSER DIFFUSER Px PRESSURE Px PRESSURE Figure 71-3. Compressor Bleed Valve—Post SB 1588 Revision 0 FOR TRAINING PURPOSES ONLY 71-5 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL OIL TANK BREATHER LEGEND SCAVENGE OIL PRESSURE OIL TORQUE OIL CONTROL VALVE AIR DEAERATOR FROM OIL COOLER CHECK VALVE FUEL HEATER 40 PSI CHECK VALVE PROP GOVENOR OIL FILLER AND DIPSTICK OIL SUPPLY TO PROP FILTER BYPASS TO OIL COOLER CENTRIFUGAL BREATHER OIL FILTER AND CHECK VALVE ASSEMBLY RELEIF VALVE RETURN TO OIL TANK 71-80 AGB DRAIN RELEIF VALVE OIL PRESSURE PUMP SCAVAGE OIL FROM PROP AND RGB TO COCKPIT INSTRUMENTS OIL TANK DRAIN OIL SUPPLY TO PROP AND RGB CHIP DETECTOR—DRAIN Figure 71-4. Lubrication System Overview (PT6A-114 & PT6A-114A) 71-6 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 71-80 Revision 0 FOR TRAINING PURPOSES ONLY 71-7 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES FUEL HEATER OIL IN FROM AIRFRAME COOLER THERMOSTATIC BYPASS & CHECK VALVE CENTRIFUGAL BREATHER TO OIL AIRFRAME COOLER MAIN OIL FILTER OIL PRESS. PUMP P R V 71-80 PRESSURE TRANSMITTER TEMP. BULB SCAVENGE OIL OIL SUPPLY TO PROPELLER & REDUCTION TANK DRAIN LEGEND SCAVENGE OIL PRESSURE OIL SUPPLY OIL Figure 71-5. Lubrication System Overview (PT6A-140) 71-8 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES EXPANSIVE MATERIAL THERMOSTATIC ELEMENT OIL OUT TO TANK BYPASS VALVE RETURN SPRING OIL FROM AGB SCAVENGE RELIEF SPRING RETURN FROM COOLER AGB CHECK VALVE OIL TANK OIL OUT TO AIR FRAME COOLER FCU 71-80 FUEL OUT LEGEND SCAVENGE OIL FUEL IN FUEL HEATER THERMOSTATIC BYPASS AIR & OIL MIST AIRCRAFT BOOST FUEL PRESSURE CONDITION: ENGINE RUNNING OUT TO COOLER RGB SCAVENGE Figure 71-6. Thermostatic Bypass & Check Valve Overview (PT6A-140) Revision 0 FOR TRAINING PURPOSES ONLY 71-9 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES LEGEND OIL PRESSURE - UNFILTERED OIL PRESSURE - FILTERED STATIC OIL CONDITION: ENGINE RUNNING FILTER ELEMENT COVER OIL FILTER HOUSING OIL PUMP HOUSING INLET CASE CHECK VALVE SEAT 71-80 CHECK VALVE BY-PASS CHECK VALVE SPRING BY-PASS VALVE SECONDARY FILTER Figure 71-7. Oil Filter Components 71-10 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES POWER LEVER PROPELLER LEVER TRIGGER CONDITION LEVER FRICTION KNOB 71-80 EMERGENCY POWER LEVER Figure 71-8. Engine Controls Revision 0 FOR TRAINING PURPOSES ONLY 71-11 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES HIGH PRESSURE FUEL TO FCU OUTLET FILTER FILTER BYPASS VALVE CARBON SEAL CARBON SEAL BRASS BUSHINGS COUPLING TO ACCESSORY GEARBOX FCU BYPASS RETURN 71-80 INLET FILTER (SELF RELIEVING) LEGEND FUEL INLET PRESSURE BYPASS PRESSURE REGULATING VALVE BYPASS FUEL PUMP DELIVERY PRESSURE LOW PRESSURE FUEL FROM FUEL HEATER Figure 71-9. Fuel Pump Overview 71-12 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES P2 ACCELERATION ADJUSTMENT MAX FLOW STOP GAS GEN. SPEED SCHEDULING CAM BYPASS VALVE GOV. BELLOWS RETURN TO TANK IDLE SPEED ADJ. TO THROTTLE RETURN TO PUMP TO PROP. GOV. TORQUE TUBE HIGH PRESSURE RELIEF VALVE P1 FROM FUEL PUMP 71-80 ACCEL. BELLOWS EVACUATED Pa LEGEND Px METERING ORIFICE P1 PUMP DELIVERY FUEL Py METERING ORIFICE P2 METERED FUEL P0 BYPASS FUEL P3 COMPRESSOR DISCHARGE AIR P3 AIR Px ACCELERATION AIR PRESSURE Py GOVERNING AIR PRESSURE CONDITION: Engine Running Figure 71-10. Fuel Control Unit—Cross Section (PT6A-114/114A) Revision 0 FOR TRAINING PURPOSES ONLY 71-13 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES FUEL CONTROL UNIT (FCU) FUEL PUMP FUEL METERING MAIN FLOW FUEL CONDITION LEVER AND HIGH IDLE CAM Po PUMP UNLOADING VALVE Po P2 FUEL INLET (FROM FUEL HEATER) HIGH PRESSURE RELIEF VALVE Po PUMP P1 POWER LEVER P1 3D CAM FUEL VALVE FOLLOWER Po Po MINIMUM FLOW Pt Pt BLEED TO Po 71-80 BYPASS VALVE FUEL VALVE 3D CAM FOLLOWER P1 P2 P2 P1 Po P2 FLYWEIGHT GOVERNOR COMPRESSOR SPEED (NG) DRAIN Pz Py P3 COMPRESSOR PRESSURE (P3) TO DISTRIBUTION SYSTEM MINIMUM PRESSURIZING AND SHUTDOWN VALVE P2 Py LEGEND P1 PUMP DELIVERY FUEL P2 METERED FUEL P0 BYPASS FUEL P3 AIR FILTER P3 SENSOR BELLOWS P3 COMPRESSOR DISCHARGE AIR TO PROPELLER GOVERNOR Px ACCELERATION AIR PRESSURE Pt FUEL SERVO PRESSURE Pz INTERMEDIATE FUEL PRESSURE CONDITION: Engine Running Figure 71-11. Fuel Control System (PT6A-140) 71-14 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 71-80 Revision 0 FOR TRAINING PURPOSES ONLY 71-15 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES GARMIN G1000 71-80 208 CARAVAN Figure 71-12. Engine Indicating System 71-16 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES JK4 ITT GAGE 5 CB402 P74 L EK 1 L EK 3 ITT HARNESS 20 GA JUMPER J30 IND8 ENGINE TEMP HI 36 ENGINE TEMP LO 38 T5 TERMINAL BLOCK SIDE OF ENGINE F GEA71 ITT GAGE A (GRN) B (WHT) G G1000 ONLY C 71-80 (YEL) 4 (RED) EK 4 EK 2 LEGEND BATTERY POWER GROUND TRIMMING THERMOCOUPLE ALUMEL CHROMEL J M J9 TRIM PROBE (+) TRIM PROBE (–) CONDITION: POWER ON Figure 71-13. Inter Turbine Temperature Indicator Revision 0 FOR TRAINING PURPOSES ONLY 71-17 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL EX 1 0.190-32 UNF-3B ALUMEL EX 2 EX 3 EX 4 X X X EX 5 0.164-32 UNC-3B CHROMEL CHROMEL RESISTOR X T1 TRIM THERMOCOUPLE HARNESS (BUS BAR) X X X X X X X X 8 THERMOCOUPLES 71-80 X Trim Value = (R1 + R2 + R3 + R4 + R5 + R6 + R7 + R8) / 8 OR To Instrument Sum of all functional thermocouples divided by number of functional thermocouples. Figure 71-14. T5 Wiring Diagram 71-18 FOR TRAINING PURPOSES ONLY Revision 0 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 71-80 Revision 0 FOR TRAINING PURPOSES ONLY 71-19 CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL NOTES 71-80 71-20 FOR TRAINING PURPOSES ONLY Revision 0