Entités

Avion Produit TIME LIMITSI MAINTENANCE CHECKS 05 Système TIME LIMITS 05-00-00 Sous-système UNSCHEDULED 05-50-00 Sous-système DIMENSIONS AND AREAS 06-00-00 Système FTING AND SHORING 07-00-00 Système JACKING 07-10-00 Sous-système EMERGENCY LIFTING/HOISTING 07-11-00 Sous-système EVELING AND WEIGHING 08-00-00 Système LEVELING 08-10-00 Sous-système TOWING AND TAXIING 09-00-00 Système TOWING 09-10-00 Sous-système PARKING AND MOORING 10-00-00 Système PARKING 10-10-00 Sous-système STORAGE 10-11-00 Sous-système MOORING 10-20-00 Sous-système RETURN TO SERVICE 10-30-00 Sous-système Deck Skin Cover 12-23-00 Composant PLACARDS AND MARKINGS 11-00-00 Système SERVICING 12-00-00 Système STANDARD PRACTICES AIRFRAME 20-00-00 Système TORQUE DATA 20-11-00 Sous-système SAFETYING 20-12-00 Sous-système CONTROL CABLE WIRE BREAKAGE AND CORROSION LIMITATIONS 20-13-00 Sous-système ELECTRICAL BONDING 20-20-00 Sous-système FUEL, WEATHER, AND HIGH-TEMPERATURE SEALING 20-32-00 Sous-système AIR CONDITITIONING 21-00-00 Système FRESH AIR DISTRIBUTION 21-20-00 Sous-système Air Outlet Valve (Wemac) 21-20-00 Composant Cabin Air Control Cable 21-20-00 Composant Distribution Duct 21-20-00 Composant AVIONICS COOLING 21-21-00 Sous-système Firewall Avionics Fan 21-21-00 Composant Primary Flight Display (PFD) Fan 21-21-00 Composant Multi-Function Display (MFD) Fan 21-21-00 Composant Deck Skin Fan 21-21-00 Composant Tailcone Avionics Fan 21-21-00 Composant HEATING AND DEFROSTING 21-40-00 Sous-système Shutoff Valve 21-40-00 Composant Cabin Heat Control Cable 21-40-00 Composant Defrost Control Cable 21-40-00 Composant Distribution System Components 21-40-00 Composant AUTO FLIGHT 22-00-00 Système AUTOPILOT 22-10-00 Sous-système KC-140 (Single-Axis) Autopilot Flight Computer 22-10-00 Composant KC-140 (Dual-Axis). Autopilot Flight Computer 22-10-00 Composant Roll Servo 22-10-00 Composant Pitch Servo 22-10-00 Composant Pitch Trim Servo 22-10-00 Composant GFC-700 AUTOPILOT 22-11-00 Sous-système Roll Servo Actuator 22-11-00 Composant Roll Servo and Cable 22-11-00 Composant Pitch Servo Actuator 22-11-00 Composant Pitch Servo and Cable 22-11-00 Composant Pitch Trim Servo Actuator 22-11-00 Composant Pitch Trim Servo and Cable 22-11-00 Composant COMMUNICATIONS 23-00-00 Système COMMUNICATIONS 23-10-00 Sous-système NAV/COM Radio 23-10-00 Composant GIA-63 Integrated Avionics Unit 23-10-00 Composant VHF Antenna 23-10-00 Composant NAV Antenna 23-10-00 Composant Microphone Switch 23-10-00 Composant AUDIO PANEL 23-50-00 Sous-système Audio Panel 23-50-00 Composant Intercom Jacks 23-50-00 Composant STATIC DISCHARGING 23-60-00 Sous-système Static Wicks 23-60-00 Composant Bonding Straps 23-60-00 Composant ELECTRICAL POWER 24-00-00 Système ALTERNATOR 24-20-00 Sous-système Alternator 24-20-00 Composant BATTERY 24-30-00 Sous-système Battery 24-30-00 Composant STANDBY BATTERY 24-30-10 Sous-système Standby Battery 24-30-10 Composant Standby Battery PC Board 24-30-10 Composant POWER JUNCTION BOX 24-60-00 Sous-système Power Junction Box 24-60-00 Composant Component 24-60-00 Composant ALTERNATOR CONTROL UNIT 24-60-01 Sous-système Alternator Control Unit 24-60-01 Composant CIRCUIT BREAKER 24-61-00 Sous-système Circuit Breaker 24-61-00 Composant ESSENTIAL AND CROSSFEED BUS DIODES 24-61-01 Sous-système Essential and Crossfeed Bus Diode 24-61-01 Composant EQUIPMENT FURNISHINGS 25-00-00 Système FRONT SEATS AND RAILS 25-10-00 Sous-système Seat 25-10-00 Composant Seat Rail 25-10-00 Composant Seat Recline Control Assembly 25-10-00 Composant Seat Ultraloc Actuator 25-10-00 Composant Seat Height Adjustment Handle Assembly 25-10-00 Composant MAP COMPARTMENT 25-10-04 Sous-système Map Compartment 25-10-04 Composant INFLATABLE RESTRAINT SYSTEM 25-00-00 Sous-système Inflatable Restraint System 25-10-10 Composant SEAT BELTS/RESTRAINTS 25-11-00 Sous-système Seat Belt/Restraints 25-11-00 Composant CENTER SEATS AND RAILS 25-20-00 Sous-système Center Seat 25-20-00 Composant Seat Rail 25-20-00 Composant REAR SEAT 25-21-00 Sous-système Rear Seat 25-21-00 Composant INTERIOR UPHOLSTERY 25-22-00 Sous-système Cabin Panels 25-22-00 Composant Door Panels and Carpet 25-22-00 Composant CARGO TIE-DOWNS 25-50-00 Sous-système CARGO PACK 25-51-00 Sous-système Cargo Pack 25-51-00 Composant POINTER EMERGENCY LOCATOR TRANSMITTER 25-60-00 Sous-système Pointer ELT 25-60-00 Composant Pointer ELT Remote Switch 25-60-00 Composant ELT Antenna 25-60-00 Composant ELT Whip Antenna 25-60-00 Composant Pointer ELT Battery Pack 25-60-00 Composant ARTEX C406-N EMERGENCY LOCATOR TRANSMITTER SYSTEM 25-60-01 Sous-système Artex C406-N ELT 25-60-01 Composant ELT Remote Switch 25-60-01 Composant ELT Rod Antenna 25-60-01 Composant Buzzer 25-60-01 Composant ARTEX ME406 EMERGENCY LOCATOR TRANSMITTER SYSTEM 25-60-02 Sous-système Emergency Locator Transmitter (ELT) 25-60-02 Composant ELT Buzzer 25-60-02 Composant Remote Switch 25-60-02 Composant ELT Antenna 25-60-02 Composant CARBON MONOXIDE DETECTOR 25-60-10 Sous-système Carbon Monoxide Detector 25-60-10 Composant SOUNDPROOFING AND INSULATION 25-80-00 Sous-système FIRE PROTECTION 26-00-00 Système FLIGHT CONTROLS 27-00-00 Système AILERON CONTROL SYSTEM 27-10-00 Sous-système Control Wheel 27-10-00 Composant Control Column 27-10-00 Composant Aileron 27-10-00 Composant Aileron Bellcrank 27-10-00 Composant RUDDER CONTROL SYSTEM 27-20-00 Sous-système Rudder Pedal Assembly 27-20-00 Composant Rudder 27-20-00 Composant Rudder Control Cables 27-20-00 Composant RUDDER TRIM CONTROL 27-21-00 Sous-système Rudder Trim System 27-21-00 Composant ELEVATOR CONTROL SYSTEM 27-30-00 Sous-système Elevator 27-30-00 Composant Cables and Pulleys 27-30-00 Composant Elevator Bell Crank 27-30-00 Composant Aft Elevator Arm Assembly 27-30-00 Composant ELEVATOR TRIM CONTROL 27-31-00 Sous-système Trim Tab Actuator 27-31-00 Composant Trim Tab Control Cables and Pulleys 27-31-00 Composant Trim Tab Control Wheel 27-31-00 Composant Pedestal Cover 27-31-00 Composant FLAP CONTROL SYSTEM 27-50-00 Sous-système Flap Motor and Transmission Assembly 27-50-00 Composant Flap 27-50-00 Composant Flap Drive Pulleys 27-50-00 Composant Cables and Pulleys 27-50-00 Composant FLAP FOLLOW-UP AND INDICATING SYSTEM 27-51-00 Sous-système Flap Follow-Up and Indicating System 27-51-00 Composant FUEL 28-00-00 Système FUEL CONTAMINATION 28-10-00 Sous-système FUEL STORAGE AND DISTRIBUTION 28-20-00 Sous-système Fuel Drain Valve 28-20-00 Composant Fuel Reservoirs 28-20-00 Composant Fuel Selector Shaft 28-20-00 Composant Fuel Selector Valve 28-20-00 Composant Electric Auxiliary Fuel Pump 28-20-00 Composant FUEL BAY SEALING 28-21-00 Sous-système Float-type Fuel Level Sender 28-40-00 Composant Fuel Quantity Indicator 28-40-00 Composant Can Bus Fuel Level Sensor 28-40-00 Composant ICE AND RAIN PROTECTION 30-00-00 Système WINTERIZATION KIT 30-20-00 Sous-système PROPELLER HEAT 30-60-00 Sous-système Propeller Heat Timer 30-60-00 Composant Propeller Heat Indicator 30-60-00 Composant Deice Boots 30-60-00 Composant Brush Block 30-60-00 Composant INDICATINGI RECORDING SYSTEMS 31-00-00 Système INSTRUMENT AND CONTROL PANELS 31-10-00 Sous-système Pilot's Center Panel 31-10-00 Composant Pilot's Inboard/Outboard Panel 31-10-00 Composant Copilot's Panel 31-10-00 Composant Center Panel 31-10-10 Composant Switch Panel 31-10-10 Composant Instrument Panel 31-10-10 Composant DIGITAL CLOCK 31-20-00 Sous-système HOUR METER 31-30-00 Sous-système Hour Meter 31-30-00 Composant ANNUNCIATOR PANEL 31-50-00 Sous-système Annunciator Panel 31-50-00 Composant ANDING GEAR 32-00-00 Système MAIN LANDING GEAR 32-10-00 Sous-système Main Landing Gear Speed Fairing 32-10-00 Composant Main Landing Gear Brake Fairing 32-10-00 Composant Main Landing Gear 32-10-00 Composant Brake Line Fairing 32-10-00 Composant Main Landing Gear Step 32-10-00 Composant Main Landing Brake Clip 32-10-00 Composant NOSE LANDING GEAR 32-20-00 Sous-système Nosewheel Speed Fairing 32-20-00 Composant Nose Landing Gear 32-20-00 Composant Shimmy Damper 32-20-00 Composant Nose Wheel Steering 32-20-00 Composant MAIN LANDING GEAR WHEEL 32-40-00 Sous-système Main Wheel 32-40-00 Composant Main Wheel Axle 32-40-00 Composant NOSE LANDING GEAR WHEEL 32-41-00 Sous-système Nose Landing Gear Wheel 32-41-00 Composant BRAKE SYSTEM 32-42-00 Sous-système Brake Master Cylinders 32-42-00 Composant LIGHTS 33-00-00 Système FLOOD LIGHTING 33-10-00 Sous-système Floodlight Bulb 33-10-00 Composant Light Assembly 33-10-00 Composant Light Assembly Switch 33-10-00 Composant Potentiometer 33-10-00 Composant Oxygen Panel Light Bulb 33-10-00 Composant Oxygen Panel Light Assembly 33-10-00 Composant GLARESHIELD LIGHT 33-11-00 Sous-système Glareshield Light 33-11-00 Composant Power Supply 33-11-00 Composant Glareshield Lighting Dimming Control 33-11-00 Composant PEDESTAL LIGHTING 33-12-00 Sous-système Pedestal Lighting Dimming Control 33-12-00 Composant INSTRUMENT LIGHTING 33-13-00 Sous-système Dimming Assembly 33-13-00 Composant Instrument Lighting Dimming Control 33-13-00 Composant RADIO LIGHTING 33-14-00 Sous-système Dimming Assembly 33-14-00 Composant Radio Lighting Dimming Control 33-14-00 Composant PILOT CONTROL WHEEL LIGHTING 33-15-00 Sous-système Map Light Assembly 33-15-00 Composant Map Light Potentiometer 33-15-00 Composant NAVIGATION AND STROBE LIGHTS 33-40-00 Sous-système Navigation Light Lamp 33-40-00 Composant LED Navigation Lights 33-40-00 Composant Strobe Tube Assembly 33-40-00 Composant Strobe Power Supply 33-40-00 Composant Strobe Light Assembly 33-40-00 Composant LED Strobe Lights 33-40-00 Composant VERTICAL FIN FLASHING BEACON 33-41-00 Sous-système Flashing Beacon Lamp 33-41-00 Composant LED Beacon 33-41-00 Composant LANDING/TAXI LIGHTS 33-42-00 Sous-système Light 33-42-00 Composant High-Intensity Discharge (HID) Ballast 33-42-00 Composant LANDING/TAXI/RECOGNITION LIGHTS 33-42-05 Sous-système LED Landing, Taxi and Recognition Light 33-42-05 Composant COURTESY LIGHTS 33-43-00 Sous-système LED Courtesy Wing Light Assembly 33-43-00 Composant Courtesy Light Lamp 33-43-00 Composant NAVIGATION 34-00-00 Système PITOT AND STATIC SYSTEMS 34-11-00 Sous-système Pitot Tube Assembly 34-11-00 Composant Static Button 34-11-00 Composant Sump Assembly 34-11-00 Composant Alternate Static Source Valve 34-11-00 Composant Blind Encoder 34-11-00 Composant Vertical Speed Indicator 34-11-00 Composant Altimeter Indicator 34-11-00 Composant Airspeed Indicator 34-11-00 Composant OUTSIDE AIR TEMPERATURE (OAT) INDICATING SYSTEM 34-12-00 Sous-système Outside Air Temperature Indicator 34-12-00 Composant Outside Air Temperature Probe 34-12-00 Composant GTP 59 OUTSIDE. AIR TEMPERATURE (OAT) PROBE 34-12-01 Sous-système Outside Air Temperature (OAT) Sensor 34-12-01 Composant AIR DATA SYSTEM 34-13-00 Sous-système GDC-74 Air Data Unit 34-13-00 Composant STALL WARNING SYSTEM 34-18-00 Sous-système Stall Warning Horn Assembly 34-18-00 Composant Stall Detector 34-18-00 Composant OPTIONAL ANGLE OF ATTACK SYSTEM 34-18-01 Sous-système Safe Flight SCc AOA Indexer Computer 34-18-01 Composant Safe Flight SCc AOA Lift Transducer 34-18-01 Composant GYROSCOPES 34-21-00 Sous-système Horizon Gyro 34-21-00 Composant Directional Gyro 34-21-00 Composant Turn Coordinator 34-21-00 Composant COMPASS INSTALLATION 34-22-00 Sous-système Compass 34-22-00 Composant MAGNETOMETER 34-22-10 Sous-système GMU-44 Magnetometer 34-22-10 Composant ATTITUDE HEADING REFERENCE SYSTEM (AHRS) 34-23-00 Sous-système GRS-77 AHRS 34-23-00 Composant MARKER BEACON 34-30-00 Sous-système Marker Beacon Antenna 34-30-00 Composant KMA-26 Audio Amplifier/Intercom/Marker Beacon Receiver 34-30-00 Composant EVS-600 ENHANCED VISION SYSTEM 34-31-00 Sous-système EVS-600 Camera 34-31-00 Composant KMH-880 MULTI-HAZARD AWARENESS SYSTEM 34-40-01 Sous-système KMH-820 Processor 34-40-01 Composant KMH-880 Interface Adapter 34-40-01 Composant Omnidirectional Antenna 34-40-01 Composant Traffic Awareness System (TAS) Directional Antenna 34-40-01 Composant KTA-870 TRAFFIC ADVISORY SYSTEM (TAS) 34-40-05 Sous-système KTA-810 Processor 34-40-05 Composant KCM-805 Configuration Module 34-40-05 Composant WX-500 STORMSCOPE 34-40-10 Sous-système WX-500 Stormscope 34-40-10 Composant GTS 800 TRAFFIC ADVISORY SYSTEM (TAS) 34-41-00 Sous-système GTS 800 Traffic Advisory System (TAS) Processor 34-41-00 Composant GA58 Directional Antenna 34-41-00 Composant Omni-Directional Antenna 34-41-00 Composant KX-155A COMM/NAV SYSTEM 34-50-00 Sous-système KX-155A/165A VHF COMM Transceiver/Navigation/VOR/LOC Glideslope Receiver 34-50-00 Composant Omni (Nav) Antenna 34-50-00 Composant Nav. Antenna Coupler 34-50-00 Composant KI-209A and KI-208 Navigation Indicators 34-50-00 Composant GIA - 63 INTEGRATED AVIONICS INSTALLATION 34-50-10 Sous-système GIA-63 NAVICOM 34-50-10 Composant KLN-79/KLN-89B GPS 34-51-00 Sous-système GPS Receiver 34-51-00 Composant KA-92 GPS Antenna 34-51-00 Composant KR-87 ADF SYSTEM 34-52-00 Sous-système KR- 87 ADF Receiver 34-52-00 Composant KA-44B ADF Antenna 34-52-00 Composant KI-227 ADF Indicator 34-52-00 Composant KT-76C TRANSPONDER 34-53-00 Sous-système KT-76C Transponder 34-53-00 Composant CI-105 Transponder Antenna 34-53-00 Composant KT-73 MODE S TRANSPONDER 34-53-01 Sous-système KT-73 Mode S Transponder 34-53-01 Composant GTX-33 TRANSPONDER 34-53-10 Sous-système GTX-33 Transponder 34-53-10 Composant GDL-69A FIS 34-54-00 Sous-système GDL-69A XM Weather Data Link 34-54-00 Composant DME 34-55-00 Sous-système KN-63 DME Receiver 34-55-00 Composant DME Antenna 34-55-00 Composant KMD-540 MULTI-FUNCTION DISPLAY 34-60-01 Sous-système KMD-540 Multi-Function Display (MFD) 34-60-01 Composant CONTROL DISPLAY UNIT 34-00-00 Sous-système Control Display Unit 34-60-10 Composant OXYGEN 35-00-00 Système OXYGEN 35-01-00 Sous-système VACUUM 37-00-00 Système VACUUM SYSTEM 37-10-00 Sous-système Vacuum Pump 37-10-00 Composant Vacuum Manifold 37-10-00 Composant Vacuum Regulator Filter 37-10-00 Composant Gyro Filter 37-10-00 Composant Vacuum Gage 37-10-00 Composant Vacuum Transducer 37-10-00 Composant STANDARD PRACTICES STRUCTURES 51-00-00 Système DOORS 52-00-00 Système CABIN DOORS 52-10-00 Sous-système Cabin Door 52-10-00 Composant Cabin Door Weatherstrip 52-10-00 Composant Cabin Door Latch Lock 52-10-00 Composant Cabin Door Latch Assembly 52-10-00 Composant Cabin Door Latch Cable Assembly 52-10-00 Composant Cabin Door Lock, Assembly 52-10-00 Composant Cabin Door Lock Cam Assembly 52-10-00 Composant CARGO DOORS 52-30-00 Sous-système Cargo Door 52-30-00 Composant Forward Cargo Door Latch Assembly 52-30-00 Composant Cargo Door Weatherstrip 52-30-00 Composant Cargo Door Lock Assembly 52-30-00 Composant Cabin Door Lock Cam Assembly 52-30-00 Composant Cargo Door Lock Cam Assembly 52-30-00 Composant STABILIZERS 55-00-00 Système HORIZONTAL STABILIZER 55-10-00 Sous-système Horizontal Stabilizer 55-10-00 Composant Horizontal Stabilizer Abrasion Boot 55-10-00 Composant VERTICAL STABILIZER FIN 55-30-00 Sous-système Vertical Stabilizer Fin 55-30-00 Composant WINDOWS 56-00-00 Système WINDSHIELD 56-10-00 Sous-système Windshield 56-10-00 Composant CABIN WINDOWS 56-20-00 Sous-système Rear Window 56-20-00 Composant Side Window 56-20-00 Composant CABIN DOOR WINDOWS 56-30-00 Sous-système Cabin Door Window 56-30-00 Composant WINGS 57-00-00 Système WINGS AND WING STRUTS 57-10-00 Sous-système Wing and Strut 57-10-00 Composant Wing Tip 57-10-00 Composant PROPELLERS 61-00-00 Système PROPELLER 61-10-00 Sous-système Spinner 61-10-00 Composant Propeller 61-10-00 Composant PROPELLER GOVERNOR 61-20-00 Sous-système Propeller Governor 61-20-00 Composant POWER PLANT 71-00-00 Système ENGINE 71-00-01 Sous-système Engine 71-00-01 Composant COWLS 71-10-00 Sous-système Cowl 71-10-00 Composant Cowl Flap 71-10-00 Composant ENGINE MOUNT 71-20-00 Sous-système AIR INDUCTION SYSTEM NON-TURBOCHARGED) 71-60-00 Sous-système Air Induction System 71-60-00 Composant DRAIN LINES 71-70-00 Sous-système Drain Line 71-70-00 Composant Cylinder Drain Can 71-70-00 Composant ENGINE FUEL AND CONTROL 73-00-00 Système FUEL INJECTION SYSTEM 73-00-01 Sous-système Fuel/Air Control Unit 73-00-01 Composant Fuel Distribution Valve 73-00-01 Composant Injection Nozzles 73-00-01 Composant FUEL FLOW INDICATION SYSTEM 73-30-00 Sous-système Manifold Pressure/Fuel Flow Indicator 73-30-00 Composant Fuel Pressure Transducer 73-30-00 Composant Fuel Flow Transducer 73-30-00 Composant IGNITION SYSTEM 74-00-00 Système IGNITION SYSTEM 74-10-00 Sous-système Magneto 74-10-00 Composant ENGINE CONTROLS 76-00-00 Système THROTTLE CONTROL 76-10-00 Sous-système Throttle Control 76-10-00 Composant FUEL MIXTURE CONTROL 76-11-00 Sous-système Fuel Mixture Control 76-11-00 Composant ENGINE INDICATING 77-00-00 Système TACHOMETER 77-10-00 Sous-système Tachometer and Drive Cable 77-10-00 Composant Tachometer Sending Unit 77-10-00 Composant ENGINE TEMPERATURE 77-20-00 Sous-système EGT/CHT Indicator 77-20-00 Composant TIT/CHT Indicator 77-20-00 Composant EGT Probe 77-20-00 Composant TIT Probe 77-20-00 Composant CHT Probe 77-20-00 Composant MANIFOLD PRESSURE TRANSDUCER 77-00-00 Sous-système Manifold Pressure Transducer 77-30-00 Composant GEA-71 ENGINEIAIRFRAME UNIT 77-40-00 Sous-système GEA-71 Engine/Airframe Unit 77-40-00 Composant EXHAUST 78-00-00 Système EXHAUST SYSTEM (NON-TURBOCHARGED) 78-10-00 Sous-système Exhaust System 78-10-00 Composant EXHAUST SYSTEM (TURBOCHARGED) 78-10-01 Sous-système Exhaust Tailpipe Assembly 78-10-01 Composant Heat Shroud 78-10-01 Composant OIL 79-00-00 Système OIL COOLER 79-20-00 Sous-système Oil Cooler 79-20-00 Composant AIR/OIL SEPARATOR ASSEMBLY 79-20-10 Sous-système Air/Oil Separator Assembly 79-20-10 Composant OIL PRESSURE INDICATORS 79-30-00 Sous-système Oil Pressure Indicator and Transducer 79-30-00 Composant Low Oil Pressure Switch 79-30-00 Composant OIL TEMPERATURE INDICATOR 79-31-00 Sous-système Sending Unit 79-31-00 Composant Pressure Indicator 79-31-00 Composant STARTING 80-00-00 Système STARTER 80-10-00 Sous-système Starter 80-10-00 Composant TURBINES 81-00-00 Système TURBOCHARGER CONTROLS 81-20-00 Sous-système TIME LIMITS - MAINTENANCE 05-00-00 Processus NOTE: When inspections criteria is required, this criteria is spelled out in the text. If more detailed instructions are required for an inspection, these instructions will be referenced out to appropriate locations (supplier publications and/or the 05-00-00 Note NOTE: The inspection guidelines contained in this section are not intended to be all-inclusive, for no such charts can replace the good judgment of certified airframe and power plant mechanics in performance of their duties. As the one primarily resp 05-10-00 Note Hinge bearings. NOTE: Corrosion 05-10-01 Note Prevention and Control Inspection 05-10-01 Note Item (baseline interval, refer to 05-10-01 Note Section 5-30-00 for additional 05-10-01 Note inspection information). NOTE: Do 05-10-01 Note not apply LPS-3 Heavy Duty Rust 05-10-01 Note Inhibitor on hinge bearing 05-10-01 Note hinge locations. NOTE: Corrosion 05-10-01 Note inspection information) 05-10-01 Note NOTE: Corrosion Prevention and 05-10-01 Note Control Inspection Item (baseline 05-10-01 Note interval, refer to Section 5-30-00 for 05-10-01 Note additional inspection information) 05-10-01 Note Corrosion Prevention and Control 05-10-01 Note Inspection Item (baseline interval 05-10-01 Note refer to Section 5-30-00 for additional 05-10-01 Note inspection information). NOTE: Do 05-10-01 Note not apply LPS-3 Heavy Duty Rust 05-10-01 Note Inhibitor on hinge bearing 05-10-01 Note fork. 5. Nose gear axle. NOTE 05-10-01 Note Corrosion Prevention and Control 05-10-01 Note Inspection Item (baseline interval 05-10-01 Note refer to Section 5-30-00 for additional 05-10-01 Note inspection information) 05-10-01 Note fork lug inner bore surface. NOTE 05-10-01 Note and lower collar assembly. NOTE 05-10-01 Note Corrosion Prevention and Control 05-10-01 Note Inspection Item (baseline interval 05-10-01 Note refer to Section 5-30-00 for additional 05-10-01 Note inspection information). NOTE: do 05-10-01 Note not apply LPS-3 Heavy Duty Rust 05-10-01 Note Inhibitor to the sliding surfaces of the 05-10-01 Note oleo strut 05-10-01 Note Program Inspection Item (baseline 05-10-01 Note interval, refer to Section 5-30-00 for 05-10-01 Note additional inspection information) 05-10-01 Note NOTE: Do not apply LPS-3 Heavy 05-10-01 Note Duty Rust Inhibitor to the bearing 05-10-01 Note NOTE: Coordinate with tire change 05-10-01 Note halves. NOTE: Corrosion Prevention 05-10-01 Note and Control Program Inspection Item 05-10-01 Note (baseline interval, refer to Section 05-10-01 Note 5-30-00 for additional inspection 05-10-01 Note information). NOTE: Disassemble the 05-10-01 Note nose gear strut to get access. NOTE 05-10-01 Note Do not apply LPS-3 Heavy Duty Rust 05-10-01 Note Inhibitor to the sliding surfaces of the 05-10-01 Note oleo strut. NOTE: Coordinate with tire 05-10-01 Note change 05-10-01 Note additional inspection information) 05-10-01 Note Note: Remove interior panels for 05-10-01 Note access 05-10-01 Note structure under floorboards. NOTE 05-10-01 Note Corrosion Prevention and Control 05-10-01 Note Program Inspection Item (baseline 05-10-01 Note interval, refer to Section 5-30-00 for 05-10-01 Note additional inspection information) 05-10-01 Note NOTE: Corrosion Prevention and 05-10-01 Note Control Program Inspection Item 05-10-01 Note (baseline interval, refer to Section 05-10-01 Note 5-30-00 for additional inspection 05-10-01 Note information) 05-10-01 Note NOTE: Corrosion Prevention and 05-10-01 Note Control Program Inspection Item 05-10-01 Note (baseline interval, refer to Section 05-10-01 Note 5-30-00 for additional inspection 05-10-01 Note information) 05-10-01 Note hinges. NOTE: Corrosion Prevention 05-10-01 Note and Control Program Inspection Item 05-10-01 Note skins. NOTE: Corrosion Prevention 05-10-01 Note and Control Program Inspection Item 05-10-01 Note (baseline interval, refer to Section 05-10-01 Note 5-30-00 for additional inspection 05-10-01 Note information) 05-10-01 Note support structure. NOTE: Corrosion 05-10-01 Note Prevention and Control Inspection 05-10-01 Note Item (baseline interval, refer to 05-10-01 Note Section 5-30-00 for additional 05-10-01 Note inspection information). NOTE: Do 05-10-01 Note not apply LPS-3 Heavy Duty Rust 05-10-01 Note Inhibitor on hinge bearing 05-10-01 Note support brackets. NOTE: Corrosion 05-10-01 Note Prevention and Control Program 05-10-01 Note Inspection Item (refer to Section 05-10-01 Note 5-30-00 for additional inspection 05-10-01 Note information) 05-10-01 Note Practices. Note: This inspection 05-10-01 Note is specifically required for German 05-10-01 Note (LBA) certification 05-10-01 Note NOTE: DOT Ratings are used to find the correct hydrostatic test and service life intervals 05-11-00 Note NOTE: US DOT Exemption E 8162 was superseded by US DOT Special Permit SP 8162 dated May 11, 2007. DOT-SP 8162 applies to all cylinders manufactured after September 30, 2007 and DOT-E 8162 cylinders hydrostatic tested after July 1, 2006. Reference AVO 05-11-00 Note NOTE: DOT-SP 8162 applies to DOT3FC1850 cylinders 05-11-00 Note NOTE 1: The DOT3AA text requirement is 5 years. Ift the hydrostatic test is overdue, you can complete the test at the next inspection phase interval 05-11-00 Note NOTE: This life limit is intended not to let flexible, fluid-carrying Teflon hoses in a deteriorated or damaged condition stay in service. Replace the flexible, fluid-carrying Teflon hoses in the engine compartment (Cessna-installed only) every 10 ye 05-11-00 Note NOTE: The inspection charts contained within the Progressive Care Program are not intended to be all inclusive, for no such charts can replace the good judgment of a certified airframe and powerplant mechanic in performance of his duties. As the one 05-12-00 Note Practices. Note: This inspection is specifically 05-12-01 Note required for German (LBA) certification 05-12-01 Note Practices. Note: This inspection is specifically 05-12-02 Note required for German (LBA) certification 05-12-02 Note Practices. Note: This inspection is specifically 05-12-03 Note required for German (LBA) certification 05-12-03 Note Practices. Note: This inspection is specifically 05-12-04 Note required for German (LBA) certification 05-12-04 Note THERE ARE CURRENTLY NO PROGRESSIVE CARE OPERATIONS CONTAINED IN THIS SECTION 05-12-06 Note THERE ARE CURRENTLY NO PROGRESSIVE CARE OPERATIONS CONTAINED IN THIS SECTION 05-12-08 Note THERE ARE CURRENTLY NO PROGRESSIVE CARE OPERATIONS CONTAINED IN THIS SECTION 05-12-13 Note corrosion. NOTE: Corrosion Prevention and Control 05-12-26 Note Inspection Item (baseline interval, refer to Section 05-12-26 Note 5-30-00 for additional inspection information) 05-12-26 Note additional inspection information) 05-12-26 Note refer to Section 5-30-00 for additional inspection 05-12-27 Note information). NOTE: Do not apply LPS-3 Heavy 05-12-27 Note Duty Rust Inhibitor on hinge bearing 05-12-27 Note locations. NOTE: Corrosion Prevention and Control 05-12-27 Note Inspection Item (baseline interval, refer to Section 05-12-27 Note 5-30-00 for additional inspection information) 05-12-27 Note NOTE: Corrosion Prevention and Control Inspection 05-12-27 Note Item (baseline interval, refer to Section 5-30-00 for 05-12-27 Note additional inspection information). NOTE: Do not 05-12-27 Note apply LPS-3 Heavy Duty Rust Inhibitor on hinge 05-12-27 Note bearing 05-12-27 Note Corrosion Prevention and Control Inspection Item 05-12-28 Note (baseline interval, refer to Section 5-30-00 for 05-12-28 Note additional inspection information) 05-12-28 Note inner bore surface. NOTE: Corrosion Prevention 05-12-28 Note and Control Inspection Item (baseline interval 05-12-28 Note refer to Section 5-30-00 for additional inspection 05-12-28 Note information) 05-12-28 Note assembly. NOTE: Corrosion Prevention and Control 05-12-28 Note Inspection Item (baseline interval, refer to Section 05-12-28 Note 5-30-00 for additional inspection information) 05-12-28 Note NOTE: do not apply LPS-3 Heavy Duty Rust 05-12-28 Note Inhibitor to the sliding surfaces of the oleo strut 05-12-28 Note additional inspection information). NOTE: Do not 05-12-28 Note apply LPS-3 Heavy Duty Rust Inhibitor to the 05-12-28 Note bearing. NOTE: Coordinate with tire change 05-12-28 Note door framing. NOTE: Corrosion Prevention and 05-12-29 Note Control Program Inspection Item (baseline interval 05-12-29 Note refer to Section 5-30-00 for additional inspection 05-12-29 Note information). Note: Remove interior panels for 05-12-29 Note access 05-12-29 Note Prevention and Control Program Inspection Item 05-12-29 Note (baseline interval, refer to Section 5-30-00 for 05-12-29 Note additional inspection information) 05-12-29 Note 1. Cabin structure under floorboards. NOTE 05-12-30 Note Corrosion Prevention and Control Program 05-12-30 Note Inspection Item (baseline interval, refer to Section 05-12-30 Note 5-30-00 for additional inspection information) 05-12-30 Note (baseline interval, refer to Section 5-30-00 for 05-12-30 Note additional inspection information) 05-12-30 Note NOTE: Corrosion Prevention and Control Program 05-12-30 Note Cabin Bulkhead. NOTE: Corrosion Prevention and 05-12-30 Note Control Program Inspection Item (baseline interval 05-12-30 Note refer to Section 5-30-00 for additional inspection 05-12-30 Note information) 05-12-30 Note rudder hinges. NOTE: Corrosion Prevention and 05-12-30 Note NOTE: Corrosion Prevention and Control Program 05-12-30 Note Inspection Item (baseline interval, refer to Section 05-12-30 Note 5-30-00 for additional inspection information) 05-12-30 Note Prevention and Control Program Inspection Item 05-12-30 Note (baseline interval, refer to Section 5-30-00 for 05-12-30 Note additional inspection information) 05-12-30 Note information). NOTE: Disassemble the nose gear 05-12-30 Note strut to get access. NOTE: Do not apply LPS-3 05-12-30 Note Heavy Duty Rust Inhibitor to the sliding surfaces of 05-12-30 Note the oleo strut. NOTE: Coordinate with tire change 05-12-30 Note NOTE: This system does not replace the normal channels to send information for items not included in the SID 05-13-00 Note NOTE: Accomplishment. of the SID inspections does not in any way replace preflight inspections, good maintenance practices or maintenance and inspections specified in the applicable Model 206 Maintenance Manual 05-13-00 Note NOTE: Inspection intervals are given in both hour and calendar time. After the completion of each initial SID inspection, repeat inspections may be completed based on hour time if the Corrosion Prevention and Control Program (CPCP) in Section 5-30-00 05-13-00 Note NOTE 1: The style and length of the surface probe will vary with the inspection situation 05-13-01 Note NOTE 2: Be sure that the reference standard has the necessary hole size for bolthole inspections. If used only for surface eddy current inspection, it is not necessary that the reference standard have holes. This part number was included to allow the 05-13-01 Note NOTE: Instrument frequency may need adjustment for the instrument and probe combination used 05-13-01 Note NOTE: This adjustment is used to set the sensitivity of the inspection. It is not intended as accept or reject criteria 05-13-01 Note NOTE: Filters may be used to improve the signal to noise ratio 05-13-01 Note NOTE 1: Bolthole probe diameter and lengths will vary with the inspection situation 05-13-01 Note NOTE 2: Be sure that the reference standard has the necessary hole size for the bolthole inspection. The reference standard material (aluminum, steel, stainless steel) will vary with the material of the hole for inspection 05-13-01 Note NOTE: Instrument frequency may need adjustment for the instrument and probe combination used 05-13-01 Note NOTE: This adjustment is used to set the sensitivity of the inspection. It is not intended as accept or reject criteria 05-13-01 Note NOTE: Filters may be used to improve the signal to noise ratio 05-13-01 Note NOTE: Cessna conductivity information is based on an instrument frequency of 60 kHz. Use of a frequency other than 60 kHz will cause differences in the conductivity reading when compared to the 60 kHz value on thinner material 05-13-01 Note NOTE: Since conductivity values are affected by variations in material properties, material stacking and geometry, conductivity values alone must not be used to decide to accept the affected area without reference to the applicable material specifica 05-13-01 Note NOTE: A detailed map is needed of the inspection area to include dimensions to locate the reference point and enough information to allow the responsible engineering activity to find the sites of the conductivity data 05-13-01 Note NOTE: Structural considerations may not allow the test points to follow the pattern of Figure 4. It is up to the inspector to decide on a pattern that best works with the area for inspection 05-13-01 Note NOTE: Do not use Type 2 (Visible Dye Penetrant) on this airplane or components. If Type 2 penetrant was previously used for this inspection, penetrant is no longer an approved method of inspection. Another NDT method such as eddy current must be used 05-13-01 Note NOTE: Cleaning materials and methods must be approved for use by the applicable Cessna Aircraft Maintenance Manual, Structural Repair Manual, or Component Maintenance Manual 05-13-01 Note NOTE: Mechanical methods to clean and remove paint should be avoided when practical. Take care to avoid filing in or sealing the entrance to a surface discontinuity when using mechanical methods to clean or remove paint. Mechanical methods can result 05-13-01 Note NOTE: Do not use the same dampened cloth more than one time. This could cause penetrant removed the first time to be put back on the surface with the second use of the cloth. This could cause non-relevant indications 05-13-01 Note NOTE: Take care not to use too much developer. If the developer puddles or begins to drip across the surface, the part or assembly must be processed again from the start 05-13-01 Note NOTE: Magnetic particle inspection cannot be used to examine nonmagnetic parts or parts with weak magnet properties 05-13-01 Note NOTE: Be aware of objects near the area of the inspection. Other parts may become magnetized during the inspection process. Be aware of the location of airplane systems that may be sensitive to magnetic fields in the area of the inspection 05-13-01 Note NOTE: Cleaning materials and methods must be approved for use by the applicable Cessna Aircraft Maintenance Manual, Structural Repair Manual, or Component Maintenance Manual 05-13-01 Note NOTE: Mechanical methods to clean and remove paint should be avoided when practical. Take care to avoid filing in or sealing the entrance to a surface discontinuity when using mechanical methods to clean or remove paint. Mechanical methods can result 05-13-01 Note NOTE: It may take several inspections in several directions to find discontinuities that are oriented in different directions 05-13-01 Note NOTE: Experience with magnetic particle inspection is necessary to find the amount of magnetic flux necessary to show discontinuities 05-13-01 Note NOTE: If the strength of the magnetization cannot be adjusted on the electromagnetic yoke, adjust the distance between the legs to adjust the strength of the magnetic field. Put the legs closer together to increase the magnetic field. Put the legs fa 05-13-01 Note NOTE: AC current is preferred, but DC current may be needed for increased penetration into the part 05-13-01 Note NOTE: Materials and methods must be approved for use by the applicable Cessna Aircraft Maintenance Manual, Structural Repair Manual, or Component Maintenance Manual 05-13-01 Note NOTE: When gage material is used; mechanically measure the thickness of the material 05-13-01 Note NOTE: It is important that the expected material thickness be between the range of the steps chosen on the reference standard 05-13-01 Note NOTE: Instruments used as an aid for visual inspection must be capable of resolving four line pairs per mm (41p/mm) 05-13-01 Note NOTE: If you leave corrosion in place or do a treatment of the corrosion before inspection, it may hide other discontinuities 05-13-01 Note NOTE: The use of a center punch or awl to indent a surface should be used with care, since awl or center punch pricks can cause fatigue cracks 05-13-01 Note NOTE 1: Time limits for the INITIAL inspections are set by either flight hours or calendar time, whichever occurs first. Except for Section 5-14-20, Supplemental inspection document 71-20-01, corresponding calendar inspection times are per REPEAT fli 05-14-00 Note NOTE: Refer to Note 1, Section 5-14-00 05-14-01 Note NOTE 05-14-02 Note Coordinate this inspection with the trim tab actuator overhaul 05-14-02 Note NOTE 05-14-03 Note Refer to Chapter 51, Corrosion - Description and Operation and associated maps to determine 05-14-03 Note corrosion severity 05-14-03 Note NOTE: The main landing gear flat springs are made from high strength steel that is shot peened on the lower surface to increase the fatigue life of the part. If the protective layer of paint is chipped or worn away, corrosion (rust) is likely to occu 05-14-03 Note NOTE: Refer to Note 1, Section 5-14-00 05-14-04 Note NOTE 05-14-05 Note Refer to Note 1, Section 5-14-00 05-14-05 Note NOTE 05-14-06 Note Refer to Chapter 51, Corrosion - Description and Operation and associated maps to 05-14-06 Note determine corrosion severity 05-14-06 Note NOTE: Refer to Note 1, Section 5-14-00 05-14-07 Note NOTE: Refer to Note 1, Section 5-14-00 05-14-08 Note NOTE 05-14-09 Note Refer to Chapter 51, Corrosion - Description and Operation and associated maps to determine 05-14-09 Note corrosion severity 05-14-09 Note NOTE 05-14-10 Note Refer to Chapter 51, Corrosion - Description and Operation and associated maps to determine 05-14-10 Note corrosion severity 05-14-10 Note NOTE: Refer to Note 1, Section 5-14-00 05-14-11 Note NOTE 05-14-12 Note Refer to Note 1, Section 5-14-00 05-14-12 Note NOTE 05-14-13 Note Refer to Note 1, Section 5-14-00 05-14-13 Note NOTE: Working rivets will have a trail of black dust downwind from the fastener. The dust is oxidized aluminum produced by the fastener moving in the hole 05-14-13 Note NOTE: With the front spar in position, there are three segments through the hole. There is a fabrication joint in the center segment (wing side), So expect a crack-like indication at about 2:00 and 10:00 o'clock positions. Indications caused by the f 05-14-13 Note NOTE 05-14-14 Note Refer to Chapter 51, Corrosion - Description and Operation and associated maps to determine 05-14-14 Note corrosion severity 05-14-14 Note NOTE: Particularly if corrosion is detected using a borescope, significant disassembly my be required to remove corrosion, and to refinish and repair surfaces. Contact Cessna Customer Services for assistance prior to beginning the repair if the disas 05-14-14 Note NOTE 05-14-15 Note Refer to Note 1, Section 5-14-00 05-14-15 Note NOTE 05-14-16 Note Refer to Chapter 51, Corrosion - Description and Operation and associated maps to determine 05-14-16 Note corrosion severity 05-14-16 Note NOTE 05-14-17 Note Refer to Note 1, Section 5-14-00 05-14-17 Note NOTE 05-14-18 Note Refer to Note 1, Section 5-14-00 05-14-18 Note NOTE: The inspection is for the aluminum structure outside of the bearing, make sure the instrument is set for aluminum material prior to starting the Eddy Current inspection 05-14-18 Note NOTE 05-14-19 Note See Section 5-30-01 and associated maps to determine corrosion severity 05-14-19 Note NOTE 05-14-20 Note Refer to Note 1, Section 5-14-00 05-14-20 Note NOTE: For tools and equipment used in checking and rigging, refer to the appropriate sections of the applicable Model 172 Service Manual 05-20-01 Note NOTE: Flight control cable inspections are normally performed without removing or disconnecting any part of the flight control system. However, it may be necessary to derig or remove the cable to get access to the entire cable 05-20-01 Note NOTE: Some systems use rub blocks, it is permissible for control cables to rub against these blocks 05-20-01 Note NOTE: It may be necessary to have a second person move the flight control system being inspected to ensure that the entire cable run in an affected area is checked 05-20-01 Note NOTE: A good quality program is one that will control all structural corrosion at Level 1 or better 05-30-00 Note NOTE: In this manual the corrosion inspection tasks are referred to as the corrosion program inspection 05-30-00 Note NOTE: Areas that need a careful inspection are given in the corrosion inspection 05-30-00 Note NOTE 05-30-00 Note If Level 3 corrosion is determined at the implementation threshold or any 05-30-00 Note repeat inspection, it should be reported. Any corrosion that is more than the 05-30-00 Note maximum acceptable to the design approval holder or the FAA (or applicable 05-30-00 Note regulatory authority) must be reported in accordance with current regulations 05-30-00 Note This determination should be conducted jointly with the design approval holder 05-30-00 Note NOTE 1: Use Cor-Ban 23 or ARDOX AV-8 in areas where a high penetration of corrosion inhibiting compound is necessary 05-30-00 Note NOTE 2: Do not use any Simple Green products other than Extreme Simple Green, as some have been found to be corrosive to some parts of the airplane structure 05-30-00 Note NOTE: You can use equivalent alternatives for the items that follow 05-30-00 Note NOTE: In some areas it may be necessary to use equipment such as a borescope to see the inspection area 05-30-00 Note NOTE: A magnifying glass can be a valuable tool to use to make sure all the corrosion has been removed 05-30-00 Note NOTE: If the surface dries before the rinse, apply the cleaner again 05-30-00 Note NOTE: Do not apply corrosion inhibiting compound to a wet surface 05-30-00 Note NOTE: It is not necessary to apply masking tape to aluminium or stainless steel tubes, plastics, sealants, adhesives, placards, and rubber before the corrosion inhibiting compound is applied 05-30-00 Note NOTE: Refer to the manufacturer's specifications for the proper application temperature 05-30-00 Note NOTE: The applied area of corrosion inhibiting compound will show as a light yellow or amber color 05-30-00 Note NOTE: The airplane must stay in the paint facility until tack-free 05-30-00 Note NOTE: The minimum cure temperature must not be below 50° F (10° C) 05-30-00 Note NOTE: Use the extension tube one-time only 05-30-00 Note NOTE: In this manual the Basic Tasks are referred to as the Corrosion Program Inspection (CPI) 05-30-00 Note NOTE: Areas that need a careful inspection are given in the corrosion inspection 05-30-00 Note NOTE: The airworthiness concern is because of the possibility to have similar but more severe corrosion on any other airplane in the operator's fleet prior to the next scheduled inspection of that area 05-30-00 Note NOTE: You do not have to contact the Cessna Aircraft Company about corrosion that is found on structure that is not on the list in the Baseline Program, for example the secondary structure 05-30-00 Note WARNING: If the flight control cable system(s) are removed, disconnected or cable section(s) are replaced, make sure that all rigging, travel checks, cable tensions and control surface checks are done in accordance with the procedures in the appropri 05-20-01 Warning WARNING: Always use the proper level of Personal Protective Equipment when using cleaning compounds. Personnel Injury or death may occur 05-30-00 Warning WARNING: Always use the proper level of Personal Protective Equipment when you use cleaning compounds. Personnel Injury or death can occur 05-30-00 Warning CAUTION: Torque values listed in this manual are not to be used for checking tightness of installed parts during service 05-00-00 Caution CAUTION: Components intended for use in liquid oxygen systems must be examined with special penetrants designated as LOX usage penetrants. These are compatible with a liquid oxygen environment. Reaction between a liquid oxygen environment and penetra 05-13-01 Caution CAUTION: Do not use the penetrant cleaner directly on the surface of the part or assembly. Do not saturate the cloth used to clean the area with the penetrant cleaner. This may remove penetrant from discontinuities 05-13-01 Caution CAUTION: Do not use visible or dry magnetic particles for inspection of airplanes or components 05-13-01 Caution CAUTION: Do not use permanent magnets for inspection of airplanes or components 05-13-01 Caution CAUTION: Do not use contact prods for inspection of airplanes or components 05-13-01 Caution Replace any cracked or excessively corroded (10% or more of the material thickness is missing in 05-14-02 Caution any loose or sheared fasteners. Make repairs in accordance with applicable Chapter(s) of the Single 05-14-02 Caution Replace cracked or excessively corroded parts. If corrosion is present, it must be removed before 05-14-13 Caution refinishing. Contact Customer Service for assistance prior to beginning the repair if the disassembly 05-14-13 Caution Replace any cracked parts. If corroded, sand area lightly to remove corrosion. If more than 10% of 05-14-15 Caution the thickness has been removed in any one area, replace the part 05-14-15 Caution CAUTION: Remove only the minimum amount of material to completely remove the corrosion. Removal of too much material can result in additional repairs and rework 05-30-00 Caution CAUTION: Use Extreme Simple Green or approved equivalent to clean the corrosion inhibiting compound application area 05-30-00 Caution CAUTION: Prevent the direct contact of cleaner or rinse water spray on wheel bearings or lubrication bearings 05-30-00 Caution UNSCHEDULED - MAINTENANCE 05-50-00 Processus NOTE: If the hard/overweight landing also has high drag/side loads, more checks are necessary 05-50-00 Note NOTE: Inspections due to transient overspeed events that occur in normal flight (no high G maneuvers, gusts, etc.) may be deferred to the next regularly scheduled inspection 05-50-00 Note NOTE: Entire report must be filled out following any lightning strike incident. If lightning strike is discovered after the fact, complete as much of report as possible. File form immediately following incident. Attach additional sheet(s) to provide 05-50-00 Note NOTE: Attach additional sheet(s) to provide complete description. Photos and sketches of damage are recommended and must be itemized and referenced in their description 05-50-00 Note NOTE: If damage is severe, please report the lightning strike as soon as possible. Inspection by Cessna Engineering Representative(s) may be required 05-50-00 Note NOTE: Panels that have hinges attached to them (like the oil door for example) are not referred to as panels and are not included in this section 06-20-02 Note NOTE: Equivalent substitutes may be used for the following listed items 07-00-00 Note JACKING - MAINTENANCE 07-10-00 Processus NOTE: For airplanes that are changed with MK206-57-02, aj padded block is not necessary for the jacking procedure. MK206-57-02 is a modification kit that gives procedures and parts to install a jack pad on the bottom side of the wing. Refer to MK206- 07-10-00 Note CAUTION: Do not let the tail move up during the jacking procedure. When put on jacks, the airplane is nose-heavy. Tail stands must have sufficient weight in all conditions. Also, the tail stand must be sufficiently strong to hold all the weight that 07-10-00 Caution EMERGENCY LIFTING/HOISTING - MAINTENANCE 07-11-00 Processus NOTE: Equivalent substitutes may be used for the following items 08-00-00 Note CAUTION: Airplane should be at minimum weight if slings are used. Fuel and all other items such as cargo etc, should be removed 07-11-00 Caution LEVELING - MAINTENANCE 08-10-00 Processus TOWING - MAINTENANCE 09-10-00 Processus NOTE: Equivalent substitutes may be used for the following items 10-00-00 Note CAUTION: When towing the airplane, never turn the nose wheel more than 29 degrees either side of center or the gear will be damaged. Do not push on control surfaces or outboard empennage surfaces. When pushing on the tailcone, always apply pressure a 09-10-00 Caution PARKING - MAINTENANCE 10-10-00 Processus CAUTION: Do not set parking brake during cold weather, when accumulated moisture may freeze brakes, or when brakes are overheated 10-10-00 Caution STORAGE - MAINTENANCE 10-11-00 Processus NOTE: The airplane is constructed of corrosion resistant, epoxy primed aluminum, which will last indefinitely under normal conditions, if kept clean. However, these alloys are subject to oxidation. The first indication of corrosion on unpainted surfa 10-11-00 Note NOTE: Tiedown rings should be used as grounding points for all grounding wires during refueling procedures 10-11-00 Note NOTE: Engines treated in accordance with the following procedure are protected against normal atmospheric corrosion for an indefinite period. However, periodic inspections should be performed to assure the integrity of preservation methods. Refer to 10-11-00 Note NOTE: Attach a red streamer to each location where a plug or tape is installed. Either attach red streamers outside the sealed area with tape or to the inside of the sealed area with safety wire to prevent wicking of moisture into the sealed area 10-11-00 Note NOTE: The corrosion preventative mixture is harmful to paint and should be wiped from painted surfaces immediately 10-11-00 Note NOTE: As an alternate method of indefinite storage, the airplane may be serviced according to Temporary Storage procedures, run up at maximum intervals of 90 days, and then serviced again according to procedures in Temporary Storage 10-11-00 Note NOTE: Do not move crankshaft when inspecting interior of cylinder for corrosion 10-11-00 Note NOTE: Before spraying, inspect the interior of one cylinder for corrosion through the spark plug hole and remove at least one rocker box cover and inspect the valve mechanism 10-11-00 Note WARNING: During all fueling procedures, fire fighting equipment must be available. Two ground wires from different points on the airplane connected to separate approved ground stakes shall be used in case of accidental disconnection of one ground wir 10-11-00 Warning MOORING - MAINTENANCE 10-20-00 Processus NOTE: This is for first time installation 10-20-00 Note NOTE: Ensure proper hardware. Referto The Model 206/T206 1997 And On Illustrated Parts Catalog, Chapter 10, Brace Installation - Float Plane 10-20-00 Note NOTE: Discard any extra washers as required 10-20-00 Note NOTE: Cut a straight line on outside of window molding, then cut a hole in the top and bottom. This allows it to be opened up and snapped around the brace allowing the brace to pass through the upholstery 10-20-00 Note CAUTION: Protect electrical and avionics from shavings 10-20-00 Caution RETURN TO SERVICE - MAINTENANCE 10-30-00 Processus NOTE: At the end of the first 25 hours of engine operation, drain engine oil, change oil filter and service engine with correct grade and quantity of engine oil 10-30-00 Note NOTE: Preservative oil which remains in sump will mix with engine oil. Flushing of the oil system is not required 10-30-00 Note NOTE: This section gives an inspection procedure for all placards, decals, and markings on the airplane 11-00-00 Note NOTE: If the wire insertion is less than 3.81 inches (95.25 mm), the floating piston will not move freely in the shaft 12-12-00 Note NOTE: An exception to this can be found when operated under the combined effect of the use of certain fuels with high humidity conditions on the ground and followed by flight at high altitude and low temperature. Under these unusual conditions, small 12-14-01 Note NOTE: An inspection of the oil filter can help find unusual engine wear. Refer to the Lycoming Service Bulletin 480F or the latest revision 12-14-02 Note NOTE: Non-turbocharged airplanes are from the factory with aviation grade mineral oil which agrees with SAE J1966 12-14-02 Note NOTE: The airplane must be in a level position for the best indication 12-14-02 Note NOTE: Normal temperature operation is within the green arc of the oil temperature gage. The engine oil must drain while the engine is still warm 12-14-02 Note NOTE: Total oil capacity with oil filter and oil cooler is 12 quarts (12.30 liters) 12-14-02 Note NOTE: The filter assembly may be cleaned with compressed air a maximum of 30 times or washed a maximum of 20 times. A new filter should be installed according to time limits set forth in Chapter 5, Inspection Time Limits, or anytime the filter become 12-15-00 Note NOTE: The filtering panels of the filter may become distorted when wet, but will return to their original shape when dry 12-15-00 Note NOTE: Smoking in cabin will significantly decrease the vacuum system central air filter life. If air filter becomes sufficiently clogged to cause suction gage readings to drop below 4.6 in.Hg, air filter must be replaced regardless of time remaining 12-16-00 Note NOTE: Recommended tire pressures should be maintained, especially in cold weather. Any drop in temperature of the air inside a tire causes a corresponding drop in air pressure 12-18-00 Note NOTE: Tire air pressure will decrease somewhat as the temperature drops, but excessive deflation could indicate cold weather leakage at the air valve. Avoid unnecessary pressure checks 12-18-00 Note NOTE: Equivalent alternatives can be used for the items that follow 12-21-00 Note NOTE: It is not necessary to remove actuator from airplane to clean or lubricate threads 12-21-03 Note NOTE: Equivalent substitutes can be used for the following items 12-22-00 Note NOTE: Windshields and windows must be cleaned before the application of wax. A clean, soft cloth is used to apply and remove wax and polish 12-22-00 Note NOTE: For additional information on the exterior paint finish, refer to Chapter 20, Interior and Exterior Finish - Cleaning/Painting 12-22-00 Note NOTE: Equivalent alternatives can be used for the items that follow 12-23-00 Note NOTE: The Primary Flight Display (PFD) and Multi-Function Display (MFD) are the GDU 1040 displays in airplanes with Garmin G1000 12-23-00 Note NOTE: JetFlex WR dry paint thickness should be 0.0012 inch (1.2 mils) to 0.002 inch (2.0 mils). Mankiewicz Soft Coating 404-78 dry paint thickness should be 0.001 inch (1.0 mils) to 0.0015 inch (1.5 mils) 12-23-00 Note NOTE: During operation at outside air temperatures below International Standard Atmosphere (ISA) Standard, the engine can develop more than its rated power at normal-rated RPM. This occurs more at lower altitudes 12-30-00 Note NOTE: The ground power receptacle circuit incorporates a polarity reversal protection. Power from the external power source will flow only if the ground service plug is connected correctly to the airplane 12-30-00 Note NOTE: When the temperature is less than 0°C (32°F), water from combustion can freeze to the engine spark plugs if the engine does not continue to operate after it is started. This will prevent the engine from starting again 12-30-00 Note NOTE: If there is no warning that an instrument is not operating correctly, all other instruments will operate continuously until at the minimum temperature of the airplane 12-30-00 Note NOTE: Equivalent alternatives can be used for the items that follow 20-00-00 Note WARNING: Only aviation-grade fuels are approved for use 12-10-00 Warning WARNING: The U.S. Environmental Protection Agency advises mechanics and other workers who handle oil to minimize skin contact with used oil and promptly remove used oil from skin 12-10-00 Warning WARNING: Fire fighting equipment must be available for all fuel system service procedures. To prevent accidental disconnection of a ground wire, you must use two ground wires from the tiedown rings on the airplane attached to approved ground stakes. 12-14-01 Warning WARNING: MIL-DTL-85470 NATO code S-1745 anti-ice additive is toxic. It is dangerous to the health when it is breathed and/or absorbed into the skin. When you service fuel with the anti-ice additive in an unventilated area, use acceptable personal pro 12-14-01 Warning WARNING: You must call medical personnel for help 12-14-01 Warning WARNING: Do not induce vomiting or give anything by mouth to an unconscious person 12-14-01 Warning WARNING: You must prevent skin contact with engine oil. Any engine oil that gets on the skin must be removed immediately 12-14-02 Warning WARNING: The tendency of a bursting tire is to rupture along the bead. Standing in any position in front of either bead area could cause injury if the tire should burst 12-18-00 Warning WARNING: When cleaning wheel bearings, use low pressure shop air to dry bearings. Do not spin bearing cones with compressed air. Dry bearings without lubrication may explode at high rpm 12-21-02 Warning WARNING: Make sure that the magneto switches are off, the throttle is closed, the mixture control is in the idle cut-off position, and the airplane wheels have chocks on them before you turn the propeller by hand. Do not stand within the arc of the p 12-22-00 Warning WARNING: Use safety precautions when mixing painting materials 12-23-00 Warning I WARNING: Do not put open flames near the airplane. If you use a heater with an open flame to preheat the engine, it can cause injury to personnel and damage to the airplane 12-30-00 Warning WARNING: During maintenance, repair and servicing of the airplane, many substances and environments encountered can cause injury if correct precautions are not obeyed 20-10-00 Warning CAUTION: Make sure that you do not push or pull on the shaft of the shimmy damper after it has reached its limit in either the up or the down position. If you continue to push a fully compressed, bottomed-out shaft, you can damage the shimmy damper. 12-12-00 Caution CAUTION: Make sure that the correct grade and type of fuel is used to service the airplane. Refer to Pilot's Operating Handbook and FAA Approved Airplane Flight Manual for a list of approved fuels 12-14-01 Caution CAUTION: Use only equipment that is recommended by the manufacturer to supply the correct quantities. The correct mixture of anti-ice additives with the fuel is very important. A quantity that is more than recommended will result in damage to the fue 12-14-01 Caution CAUTION: Do not let the concentrated anti-ice additive come in contact with the airplane finish and fuel cell or damage will result 12-14-01 Caution CAUTION: During the engine break-in period, the turbocharged engines use only ashless dispersant oil which agrees with SAE J1899 12-14-02 Caution CAUTION: A non-turbocharged airplane can operate with SAE J1966 straight mineral oil during the initial break-in period or after an overhaul. After the break-in period, use an ashless dispersant oil that agrees with SAE J1899. Make sure you use the c 12-14-02 Caution CAUTION: Do not operate the vacuum system with air filter removed or with a vacuum line disconnected. Particles or dust or other foreign matter may enter the system and damage the vacuum operated instruments 12-16-00 Caution CAUTION: Applying a tire sealant to the tire may cause wheel corrosion 12-18-00 Caution CAUTION: Do not use gasoline, alcohol, benzene, acetone, carbon tetrachloride, fire extinguisher fluid, deicer fluid, lacquer thinner, or glass window cleaning spray. These solvents will make the plastic soft and can cause crazing 12-22-00 Caution CAUTION: Use care and correct techniques during the handling and cleaning of the windshields. Damage easily occurs to windshields and windows 12-22-00 Caution CAUTION: Do not use any of the following to clean windshields and windows: methanol, denatured alcohol, gasoline, benzene, xylene, acetone, carbon tetrachloride, lacquer thinners, commercial, or household window cleaning sprays 12-22-00 Caution CAUTION: Remove all jewelry before you begin to clean the airplane. The jewelry can cause scratches or other damage to the surface of the windshield 12-22-00 Caution CAUTION: Do not use rain repellent on acrylic surfaces 12-22-00 Caution CAUTION: Do not use gasoline or other highly flammable substances to wash the engine 12-22-00 Caution CAUTION: Do not try to wash an engine that is hot or turned on. Let the engine cool before you start to clean it 12-22-00 Caution CAUTION: Use care to not get cleaning agents or water on the openings of the starter, magnetos, alternator, or vacuum pump 12-22-00 Caution CAUTION: Do not leave cleaning agents on the engine components for a long period of time. If they are not removed, they can cause damage to the components. Damage can occur to the neoprene seals and silicone fire sleeves, and corrosion can also occur 12-22-00 Caution CAUTION: Do not touch the lens, if possible. The GDU 1040 lens has a layer of anti- reflective material which is very sensitive to skin oils, waxes and abrasive cleaners 12-23-00 Caution CAUTION: Do not use cleaners that contain ammonia. Ammonia will cause damage to the anti-reflective material 12-23-00 Caution CAUTION: Do not use air with a temperature of more than 120°C (248°F) when you preheat the engine. Air with a temperature of more than 120°C (248°F) can do damage to the exterior paint of the airplane 12-30-00 Caution CAUTION: Thermometers and other test equipment that contain mercury must not be used on the airplane 20-10-00 Caution B. Fuel Removal Procedures 12-14-01 Étape Figure 301 (Sheet 1) 12-14-01 Document Figure 301 (Sheet 1) 12-14-02 Document Vacuum System Air Filter - Servicing Figure 301 (Sheet 1) 12-16-00 Document 1 BATTERY PL HAND TERMINALS PL - GREASE, PETROLATUM - VV-P236 1210T1001 A07181016 Battery Terminals Lubrication Figure 301 (Sheet 1) 12-21-01 Document NUMBER DESCRIPTION TYPE APPLICATION 1 WHEEL BEARINGS GR HAND 2 TORQUE LINKS STEERING BUNGEE GR GUN 3 SHIMMY DAMPER PIVOTS STEERING SHAFT OG OIL CAN 4 STEERING BUNGEE THREADS GL HAND 1242T1005 A1242T1016 5 STEERING SYSTEM NEEDLE BEARING GH HAND 0741T1 12-21-02 Document OG-OIL, GENERAL PURPOSE - (MIL-L-81322) 12601003 Aileron System Lubrication Figure 301 (Sheet 1) 12-21-03 Document OG-OIL, GENERAL PURPOSE - (MIL-L-7870) 12241001 07241002 Aileron System Lubrication Figure 301 (Sheet 2) 12-21-03 Document (1) Electrically ground the airplane and vehicle. Refer to Safety and Maintenance Precautions. Make sure the ALT/BAT MASTER switch is set to off 12-14-01 Opération 0 Remove the fuel filler caps 12-14-01 Opération 4) Insert the fuel nozzle into the fuel bay 12-14-01 Opération 0 Remove the fuel 12-14-01 Opération 6) Remove the fuel nozzle and install the fuel filler caps 12-14-01 Opération Set a container under each drain valve 12-14-01 Opération 8) Remove the safety wire from the drain valves 12-14-01 Opération (9) Remove the drain valves from the bottom of the fuel tank to drain any fuel that remains 12-14-01 Opération (10) Install the drain valves 12-14-01 Opération (11) Install safety wire to the drain valves. Refer to Chapter 20, Safetying - Maintenance Practices 12-14-01 Opération (12) Remove the electrical ground equipment 12-14-01 Opération C. Deck Skin Cover Removal 12-23-00 Étape NOTE: Other semi-gloss or flat gloss coatings such as Acry Glo AS Series (Sherwin Williams) are acceptable for the color coat 12-23-00 Note WARNING: Use safety precautions when using flammable materials during the cleaning and painting procedures 12-23-00 Warning WARNING: Use only approved solvents and cleaning materials 12-23-00 Warning (1) Remove the Deck Skin Cover 12-23-00 Étape NOTE: Do not saturate the wiping cloth until the solvent drips 12-23-00 Note NOTE: Do not dip the wiping cloth into an open solvent container. This will contaminate the solvent 12-23-00 Note NOTE: Work in a small area, SO that the surface being cleaned remains wet 12-23-00 Note NOTE: If the clear surface coating of the aluminum of the deck skin has been scratched or removed, it will need to chemically pretreated and to be primed. Refer to Chapter 20, Interior and Exterior Finish - Cleaning/Painting 12-23-00 Note CAUTION: Do not have direct contact with or vapors of Methanol, Denatured Alcohol, Gasoline, Benzene, Xylene, Methyl N-Propyl Ketone, Acetone, Carbon Tetrachloride, Lacquer Thinners, paint strippers, commercial or household window cleaning sprays on 12-23-00 Caution CAUTION: Acrylic windshields and windows are easily damaged by improper handling and cleaning techniques 12-23-00 Caution DETAIL C A1211R1025 B0511R3002 C0511R3002 D0511R3002 Deck Skin Cover Removal/Installation Figure 701 (Sheet 1) 12-23-00 Document (a) Carefully remove the existing deck skin paint by doing the following 12-23-00 Opération 1 Lift a corner of the deck skin cover and pull the deck skin cover away from the deck skin 12-23-00 Opération 2 Start at the edge and use a clean wiping cloth to carefully apply Toluene or Methyl Propyl Ketone (MPK) solvent per CSFS039 to loosen and remove the deck skin adhesive. Refer to Chapter 20, General Solvents/Cleaners - Maintenance Practices 12-23-00 Opération 3 Use a plastic scraper to gradually remove the adhesive, if necessary 12-23-00 Opération 4 If the surface dries before the adhesive is removed, apply more solvent and clean again 12-23-00 Opération 5 Wipe the area being cleaned with a clean dry cloth. Do not allow the surface to evaporate dry 12-23-00 Opération 6 Carefully remove small surface defects such as dirt, dust, and scratches by blending with 120 or 150 grit sandpaper 12-23-00 Opération (b) Remove all dust, lint, chips, and shavings with a vacuum cleaner 12-23-00 Opération TORQUE DATA - MAINTENANCE 20-11-00 Processus B842 NOTE: WHEN USING A TORQUE WRENCH ADAPTER WHICH CHANGES THE DISTANCE FROM THE TORQUE WRENCH DRIVE TO THE ADAPTER DRIVE, APPLY THE FOLLOW- ING FORMULAS TO OBTAIN THE CORRECTED TORQUE READING 20-11-00 Note NOTE: This table is used with MS21042 self- locking nuts 20-11-00 Note NOTE: There is no satisfactory method of determining the torque previously applied to a threaded fastener. When retorquing, always back off approximately 1/4 turn or more before reapplying torque 20-11-00 Note CAUTION: NEVER INSTALL STANDARD WASHER OR COUNTERSUNK WASHER IN REVERSE WHEN USING BOLTS WITH RADIUS UNDER THE HEAD 20-11-00 Caution SAFETYING - MAINTENANCE 20-12-00 Processus NOTE: Surface treatments which obscure visual identification of safety wire are prohibited 20-12-00 Note NOTE: You can use safety cable as an alternative to safety wire. Refer to Safety Cable Installation, in this section 20-12-00 Note NOTE: This does not necessarily apply to castellated nuts when the slot is close to the top of the nut, the wire will be more secure if it is made to pass along the side of the stud 20-12-00 Note NOTE: Do not use a tool as the locking clip could be distorted 20-12-00 Note NOTE: Safety cable that is not of the correct type, length, and dimension can break. This can occur when there is more than the specified tension limit for that type and dimension of safety cable 20-12-00 Note NOTE: The two-bolt pattern is the recommended procedure when there is an even number of fasteners 20-12-00 Note NOTE: PULL WITH YOUR FINGERS FOR AN INSPECTION TO MAKE SURE THE CLIP WILL NOT COME OUT 20-12-00 Note NOTE: IF THERE IS NO SAFETY WIRE HOLE TO USE, PUT THE SAFETY WIRE AROUND THE CIRCUMFERENCE OF THE EYEBOLT 20-12-00 Note CAUTION: Screws in closely spaced geometric patterns which secure hydraulic or air seals, hold hydraulic pressure, or are used in critical areas should use the double twist method of safety wiring 20-12-00 Caution CAUTION: Do not use the safety cable or the ferrule again after you remove it. It can break if you apply too much force to it and cause damage to the equipment 20-12-00 Caution CONTROL CABLE WIRE BREAKAGE AND CORROSION LIMITATIONS - MAINTENANCE 20-13-00 Processus ELECTRICAL BONDING - MAINTENANCE 20-20-00 Processus NOTE: If a component is moved or the bond of an installed component is otherwise broken, the resistance of the connection must be verified again after installation 20-20-00 Note NOTE: If you can bond through the fasteners, it is recommended that you use Method B to install static wicks. If you cannot bond through the fasteners, it is necessary that you use Method B to install static wicks 20-20-00 Note NOTE: Bonds between two metal surfaces and bonding jumper attachment points must be free of insulating material, such as paint, primer, grease, oil, and materials that prevent corrosion. A clean area is needed to make sure there is an adequate bond a 20-20-00 Note NOTE: You are permitted to use 400 through 600 grit emery paper or cloth, or an equivalent fine sandpaper and/or aluminum oxide paper or cloth, stainless steel wool, or a stainless steel or monel bonding brush 20-20-00 Note NOTE: You can use aluminum wool only on aluminum 20-20-00 Note NOTE: If the cleaned area is more than 0.50 inch (12.7 mm) more than the connector, you must apply primer, let it dry, then clean it again 20-20-00 Note NOTE: This will give the bond electrical and some corrosion protection 20-20-00 Note NOTE: If the cleaned area is larger than the diameter of the bonding surface, the surface must be primed, dried, then cleaned again 20-20-00 Note NOTE: You are permitted to use 400 through 600 grit emery paper or cloth, or an equivalent fine sandpaper 20-20-00 Note NOTE: You are permitted to use 400 through 600 grit emery paper or cloth, or an equivalent fine sandpaper 20-20-00 Note NOTE: Although you must apply a corrosion inhibitor to seal the perimeter of some electrical bonds after they are assembled, some electrical bonds must have a finish applied before you can apply the corrosion inhibitor 20-20-00 Note NOTE: Method A nonconductive) Sealing is done after the electrical bond is assembled. To make sure that the finish is nonconductive, it is necessary that you use a micro-ohmmeter to do an electrical bonding test 20-20-00 Note NOTE: Method B (conductive) Sealing is done during the electrical bond assembly 20-20-00 Note NOTE: In areas where the surface already has chemical film applied, such as feed-thru plates on pressure bulkheads, it is not required to remove this finish and reapply chemical film to achieve bonding unless the bonding requirements cannot be met 20-20-00 Note NOTE: A cleaned area must not be refinished until the electrical bond connection has been inspected and approved 20-20-00 Note NOTE: Bonding jumpers do not need painting 20-20-00 Note NOTE: For Method A sealing, it is recommended that you use corrosion-inhibitive polysulfide-based sealant 20-20-00 Note NOTE: If you can bond through the fasteners, it is recommended that you use Method B to install static wicks. If you cannot bond through the fasteners, it is necessary that you use Method B to install static wicks 20-20-00 Note NOTE: For Method B sealing, you must use corrosion-inhibitive polysulfide-based sealant 20-20-00 Note NOTE: In many cases the object to be grounded is mounted on or attached to secondary structure, or otherwise separated from direct contact with primary structure. Grounding depends on both the satisfactory bonding of the mounting tray to secondary st 20-20-00 Note NOTE: To make sure that the finish is nonconductive, it is necessary that you use a micro-ohmmeter to do an electrical bonding test 20-20-00 Note NOTE: The classes of electrical bonds are given in accordance to the type of material that is bonded together and the method used to bond the materials 20-20-00 Note NOTE: Current return grounds must be avoided in fuel vapor areas 20-20-00 Note NOTE: To make sure that the finish is nonconductive, it is necessary that you use a micro-ohmmeter to do an electrical bonding test 20-20-00 Note NOTE: Upon completion of the electrical bonding test, the metallic surface must be refinished to protect from corrosion 20-20-00 Note NOTE: Apply sealant or corrosion resistant primer to bare metal for corrosion protection 20-20-00 Note NOTE: To make sure that the finish is nonconductive, it is necessary that you use a micro-ohmmeter to do an electrical bonding test 20-20-00 Note NOTE: The outer layer will usually be the lightning protection material and care must be taken not to sand through the layer and conductive sealant used in conduction with the fasteners to achieve the bond 20-20-00 Note NOTE: If ground stud is positioned where it will be exposed to moisture, such as in wheel well, RTV 108 sealant must be used to seal ground stud 20-20-00 Note NOTE: If you can bond through the fasteners, it is recommended that you use Method B to install static wicks. If you cannot bond through the fasteners, it is necessary that you use Method B to install static wicks 20-20-00 Note NOTE: USE METHOD A OR METHOD B CLEANING AND SEALING PROCEDURES 20-20-00 Note NOTE: USE METHOD A OR METHOD B CLEANING AND SEALING PROCEDURES 20-20-00 Note NOTE: USE METHOD A OR METHOD B CLEANING AND SEALING PROCEDURES 20-20-00 Note NOTE: USE METHOD A OR METHOD B CLEANING AND SEALING PROCEDURES 20-20-00 Note NOTE: USE METHOD A OR METHOD B CLEANING AND SEALING PROCEDURES 20-20-00 Note NOTE: USE METHOD A OR METHOD B CLEANING AND SEALING PROCEDURES. 5580T2023 AA5580T2023 20-20-00 Note NOTE: USE METHOD A OR METHOD B CLEANING AND SEALING PROCEDURES. AA5580T2023 5580T2023 Electrical Bonding - Typical Bonding Jumper Installation for Continuity of Plumbing 20-20-00 Note NOTE: THIS METHOD IS NOT APPLICABLE FOR USE ON FUEL CELL ACCESS PANELS 20-20-00 Note NOTE: USE METHOD B CLEANING AND SEALING PROCEDURES. 6280T1001 20-20-00 Note NOTE: REMOVE THE PRIMER SEALANT FROM THIS AREA 20-20-00 Note NOTE: USE METHOD B TO APPLY A FILLET SEAL TO THE PERIMETER OF THE BONDING AREA 20-20-00 Note NOTE: USE METHOD B TO APPLY A FILLET SEAL TO THE PERIMETER OF THE BONDING AREA ON BOTH SIDES. 7080T1017 20-20-00 Note NOTE: METHOD B CLEANING AND SEALING PROCEDURES ARE RECOMMENDED FOR ALL APPLICATIONS 20-20-00 Note NOTE: All hazardous air pollutants (HAP) or volatile organic compounds (VOC) hand-wipe solvents that clean, must meet a composition requirement, have a vapor pressure less than or equal to 0.87 psi at 68°F (6 kPa at 20°C), or meet the requirements sp 20-31-00 Note (1) of the Clean Air Act 20-31-00 Note NOTE: Priming operations cannot be more than the maximum Hazardous Air Pollutant (HAP) limit of 20-31-00 Note 2.9 Ib./Gallon (350 Grams/Liter) (less water) per application. Priming operations cannot be 20-31-00 Note more than the volatile organic compounds (VOC) limit of 2.9 Ib./Gallon (350 Grams/Liter) (less 20-31-00 Note water and exempt solvents) per application. Compliance of this limit can be completed through 20-31-00 Note the use of layers that are less than the content limits, or with a monthly volume-weighted 20-31-00 Note average to meet content limits 20-31-00 Note NOTE 1: Any primers which meet MIL-PRF-23377G or later requirements may be used 20-31-00 Note NOTE 2: This primer is restricted to the fuel bay area 20-31-00 Note NOTE 3: Any pretreatment primers that meet DOD-P-15328 can be used 20-31-00 Note NOTE 4: Specific application techniques must be used. If an alternative is necessary, it can only be used if 20-31-00 Note the missions are less than or equal to HVLP or electrostatic spray application techniques. All application 20-31-00 Note equipment must be operated according to the manufacturer's specifications, company procedures, or locally 20-31-00 Note specified operating procedures 20-31-00 Note NOTE: Topcoat operations cannot be more than the maximum Hazardous Air Pollutant (HAP) limit of 20-31-00 Note 3.5 Ib./Gallon (420 Grams/Liter) (less water) per application. Topcoat operations cannot be 20-31-00 Note more than the volatile organic compounds (VOC) limit of 3.5 Ib./Gallon (420 Grams/Liter) (less 20-31-00 Note water and exempt solvents) per application. Compliance of this limit can be completed through 20-31-00 Note the use of layers that are less than the content limits, or by the monthly volume-weighted 20-31-00 Note average to meet content limits. Topcoats that meet the requirements of MIL-C-85285 can 20-31-00 Note also be used 20-31-00 Note NOTE: Unless exempted, no organic Hazardous Air Pollutant (HAP) are to be emitted from chemical strippers or solvents. Use of organic HAP materials for spot stripping and decal removal is limited to 190 pounds per airplane per year 20-31-00 Note NOTE 5: Mechanical and hand-sanding operations are exempt from these requirements 20-31-00 Note WARNING: Do not use conductive sealant in fuel tanks. Use only nonconductive sealants that are approved for use in fuel tanks. The metal material in the conductive sealant can create a spark (arcing) in the fuel tank 20-20-00 Warning CAUTION: Do not use steel wool, stainless steel wool, or aluminum wool to clean magnesium alloys 20-20-00 Caution CAUTION: Do not use steel wool, stainless steel wool, or aluminum wool to clean magnesium alloys 20-20-00 Caution GENERAL SOLVENTS/CLEANERS - MAINTENANCE 20-31-01 Processus NOTE: Equivalent substitutes may be used for the following items 20-31-01 Note NOTE: Prior to bonding or priming, lightly abrade surface with either a ScotchBrite pad or sandpaper prior to cleaning 20-31-01 Note NOTE: If cleaning a bonding surface, lightly abrade the bonding surface with sandpaper prior to cleaning 20-31-01 Note NOTE: Do not use masking tape 20-31-02 Note NOTE: Do not sand rivet heads 20-31-02 Note NOTE: Surface conditioning disc will wear rapidly, it will be necessary to resharpen (retaper) disc frequently 20-31-02 Note WARNING: All paint strippers are harmful to eyes and skin. All operators should wear goggle-type eyeglasses, rubber gloves, aprons and boots. In case of contact with skin, flush with water. In case of contact with eyes, flush eyes thoroughly with wat 20-31-02 Warning WARNING: Use normal safety precautions when using flammable materials during cleaning and painting procedures 20-31-02 Warning WARNING: Paint stripper solution is harmful to eyes and skin. Wear goggles, rubber gloves, apron and boots when working with paint stripper. Also wear appropriate respirator when applying "spray-on" strippers. The chemical supplier bulletins and inst 20-31-02 Warning WARNING: Work in a well ventilated area free from sources of ignition. Use only approved solvents and materials 20-31-02 Warning CAUTION: All plastic and fiberglass parts, except bushings, bearings, grommets and certain purchased antenna covers which are not colored or painted, shall be colored or painted to match adjacent surface. The head of the pitot tube must be open and f 20-31-02 Caution CAUTION: Do not use chemical strippers on plastic, fiberglass, Kevlar and graphite composite assemblies. Paint stripper solvent will damage these assemblies 20-31-02 Caution CAUTION: Sanding of paint and/or sanding surfacer must be very carefully accomplished. Do not sand into the fabric layers of composite assemblies as this will result in loss of strength 20-31-02 Caution CAUTION: Do not use low carbon steel brushes on aluminum, magnesium, copper, stainless steel or titanium surfaces. Steel particles may become embedded in the surfaces, and later rust or cause galvanic corrosion of the metal surfaces 20-31-02 Caution CAUTION: Use of a heater with an open flame in an area in which stripping with a methylene chloride type stripper is used produces hydrochloric acid fumes. If acid is deposited on airplane it will corrode all surfaces 20-31-02 Caution CAUTION: Acrylic windows may be softened or otherwise damaged by paint stripper, solvent or paint. Use water and grease-proof barrier material and polyethylene coated tape to protect windows 20-31-02 Caution CAUTION: High strength steel parts are very susceptible to hydrogen embrittlement. Acidic solutions, such as rust removers and paint strippers have been found to cause hydrogen embrittlement. Hydrogen embrittlement is an undetectable, time delayed pr 20-31-02 Caution CAUTION: Excessive pressure or dwell time will cause scratches or grooves in metal. Ensure doubler at bottom of joint is not damaged or gouged in any way by this process 20-31-02 Caution CAUTION: Airplane shall be grounded during solvent wipe 20-31-02 Caution FUEL, WEATHER, AND HIGH-TEMPERATURE SEALING - MAINTENANCE 20-32-00 Processus NOTE: Specified sealants, solvents that clean, parting agents, adhesion inhibitors and equipment are listed for use. Acceptable alternatives can be used to seal equipment only 20-32-00 Note NOTE: Time periods presented below are based on a temperature of 77°F (25°C) and 50 percent relative humidity. Any increase in either temperature or relative humidity may shorten these time periods and accelerate the sealant cure 20-32-00 Note NOTE: Bond primer must not be removed 20-32-00 Note NOTE: Extra force will be needed on the ramrod at the beginning of accelerator injection into the base material 20-32-00 Note NOTE: The accelerator has been fully injected into the cartridge when the ramrod is fully inserted into the dasher rod 20-32-00 Note NOTE: CARTRIDGE IS DISPOSABLE AFTER USE 20-32-00 Note NOTE: Mixing the accelerator and base material can be accomplished manually, or as an alternate method, with the use of a drill motor 20-32-00 Note NOTE: Do not rotate the dasher rod counterclockwise. The four blade dasher inside the cartridge will unscrew and separate from the dasher rod 20-32-00 Note NOTE: If streaks are present in the sealant (viewing through the side of the cartridge), the sealant is not completely mixed 20-32-00 Note NOTE: A tapered rotary file or a 25/64 inch drill bit may be used with a drill motor to turn the dasher rod 20-32-00 Note NOTE: THE EXAMPLES SHOW TYPICAL CROSS SECTIONS OF DIFFERENT SEAL METHODS USED IN THE FUEL COMPARTMENT. THE MINIMUM SEALANT THICKNESS AT ANY POINT MUST NOT BE LESS THAN 0.060 INCH (1.5 mm) 20-32-00 Note NOTE: Fabrication and changes done after the seal are not recommended 20-32-00 Note NOTE: Type I, Class B-1/2 is recommended for use during cold weather to obtain an accelerated cure 20-32-00 Note NOTE: Type 1, Quick Repair sealant may be used as a repair for sealant in fuel tanks if desired for fast cure and rapid dispatch 20-32-00 Note NOTE: For outside operations only, the temperature of the structure may be allowed to drop below 60°F (15°C) but not below 58°F (14°C), after application for a period of time not to exceed 48 hours. The structure must be subsequently heated to above 20-32-00 Note NOTE: Always pour solvent on the cloth to maintain a clean solvent supply 20-32-00 Note NOTE: In fuel tanks which have been in operation, the sealant will be soaked and must be dried in area of the repair with a vapor proof heat lamp or hot air blower before new sealant is applied 20-32-00 Note NOTE: Care must be taken to obtain a uniform thin coat of adhesion promoter. Thin enough to cover the surface, but not heavy enough to run 20-32-00 Note NOTE: Sealant may be applied up to 8 hours after the application of adhesion promoter. After 8 hours, the surface must be recleaned and adhesion promoter reapplied 20-32-00 Note NOTE: Equivalent substitutes may be used for the following items 21-00-00 Note NOTE: Air temperature in the distribution system can be altered by use of the CABIN HT control. As the CABIN HT control is gradually pulled out, more and more heated air will blend with the fresh air from the scoop, and is distributed into the cabin. 21-20-00 Note WARNING: The cartridge must be held firmly, but must not be squeezed, as the dasher blades may penetrate the cartridge and injure the hand 20-32-00 Warning WARNING: The cartridge must be held firmly, but not squeezed, as the dasher blades may penetrate the cartridge and injure the hand 20-32-00 Warning CAUTION: Quick repair sealant must be applied within its working life of 15 minutes. Attempts to work quick repair sealant beyond working life will result in incomplete wetting of surface and will result in a failed seal 20-32-00 Caution FRESH AIR DISTRIBUTION - MAINTENANCE 21-20-00 Processus A. Remove Air Outlet Valve (Wemac) 21-20-00 Étape Fresh Air System Installation Figure 201 (Sheet 1) 21-20-00 Document Fresh Air System Installation Figure 201 (Sheet 2) 21-20-00 Document (1) Remove retaining ring from air outlet valve (Wemac). Remove upholstery panel or headliner. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 21-20-00 Opération (3) Remove clamp securing ducting hose to air outlet valve adapter 21-20-00 Opération (4) Remove air outlet valve and adapter 21-20-00 Opération A. Remove Cabin Air Control Cable 21-20-00 Étape (1) Carefully straighten end of CABIN AIR control cable. Loosen clamp bolt on control arm and withdraw cable from control arm 21-20-00 Opération 3) Remove screws securing clamp 21-20-00 Opération (4) Gain access to the backside of the CABIN AIR control cable 21-20-00 Opération (5) Loosen nut on backside of control cable 21-20-00 Opération (6) Carefully withdraw cable from instrument panel 21-20-00 Opération AVIONICS COOLING - MAINTENANCE 21-21-00 Processus CAUTION: If the engine is removed, make sure that there is a tailcone stand in position before you get inside the tailcone 21-21-00 Caution A. Remove the fan from the firewall 21-21-00 Étape NOTE: The procedures that follow are for airplanes with standard avionics 21-21-00 Note Firewall Avionics Fan Installation Figure 201 (Sheet 1) 21-21-00 Document (1) Make sure that the MASTER and AVIONICS switches are in the off position 21-21-00 Opération (2) Remove the screws that attach the fan to the firewall 21-21-00 Opération (3) Disconnect the electrical connector (PC901) from the fan 21-21-00 Opération (4) Disconnect the flexible ducts from the fan and remove the fan from the airplane 21-21-00 Opération A. Remove the PFD Fan 21-21-00 Étape NOTE: The procedures that follow are for airplanes with Garmin G1000 21-21-00 Note Avionics Cooling Installation Figure 202 (Sheet 1) 21-21-00 Document (1) Record the fan airflow direction 21-21-00 Opération L Make sure that the Master and Avionic switches are in the off position 21-21-00 Opération 3) Remove the PFD. Refer to Chapter 34, Control Display Unit - Maintenance Practices 21-21-00 Opération 4) Remove the screws and nuts that attach the fan to the fan bracket 21-21-00 Opération 5) Disconnect the electrical connector (PC1316) from the avionics fan 21-21-00 Opération (6) Remove the fan from the airplane 21-21-00 Opération A. Remove the MFD Fan 21-21-00 Étape NOTE: The procedures that follow are for airplanes with Garmin G1000 21-21-00 Note (1) Record the fan airflow direction 21-21-00 Opération 2) Make sure that the MASTER and AVIONIC switches are in the off position 21-21-00 Opération (3) Remove the turn coordinator. Refer to Chapter 34, Turn Coordinator - Maintenance Practices 21-21-00 Opération (4) Remove the screws and nuts that attach the fan to the fan bracket 21-21-00 Opération (5) Disconnect the electrical connector (PI315) from the avionics fan 21-21-00 Opération 6) Remove the fan through the turn coordinator hole 21-21-00 Opération (7) Remove the fan from the airplane 21-21-00 Opération A. Remove the Deck Skin Fan 21-21-00 Étape NOTE: The procedures that follow are for airplanes with Garmin G1000 21-21-00 Note (1) Record the fan airflow direction 21-21-00 Opération 2) Make sure that the MASTER and AVIONICS switches are in the off position 21-21-00 Opération (3) Remove the PFD. Refer to Chapter 34, Control Display Unit - Maintenance Practices 21-21-00 Opération 4) Remove the screws and nuts that attach the fan to the deck skin 21-21-00 Opération (5) Disconnect the electrical connector (P1314) from the deck skin fan 21-21-00 Opération (6) Remove the fan from the airplane 21-21-00 Opération A. Remove the Tailcone Avionics Fan 21-21-00 Étape NOTE: The procedures that follow are for airplanes with Garmin G1000 21-21-00 Note CAUTION: If the engine is removed, make sure there is a tailcone stand in position before you get inside the tailcone 21-21-00 Caution Tailcone Avionics Fan Installation Figure 203 (Sheet 1) 21-21-00 Document (1) Make sure that the MASTER and AVIONICS switches are in the off position 21-21-00 Opération 2) Remove the baggage divider to get access inside the tailcone 21-21-00 Opération 3) Remove the caps from the unused ports, if necessary 21-21-00 Opération (4) Disconnect the electrical connector (PT901) from the fan 21-21-00 Opération (5) Disconnect the ducts from the fan 21-21-00 Opération (6) Remove the fan from the avionics shelf 21-21-00 Opération HEATING AND DEFROSTING - MAINTENANCE 21-40-00 Processus NOTE: The cockpit-area distribution plenum is also set to receive outside fresh air from the left and right external air scoops (doors). This arrangement lets a combination of fresh air and heated air to be mixed and supplied to the entire system. Fo 21-40-00 Note A. Remove the Control Cable 21-40-00 Étape PLENUM TO EXHAUST FORWARD CABIN FLOOR DUCT HEAT HEAT SHUTOFF VALVE EXCHANGER HEAT CONTROL CABLE B DETAIL A A12141012 1210T1001 Heating System Installation Figure 201 (Sheet 1) 21-40-00 Document Heating System Installation Figure 201 (Sheet 2) 21-40-00 Document (1) Remove the engine cowling. Refer to Chapter 71, Cowls - Maintenance Practices 21-40-00 Opération L) Carefully make the end of the cabin heat control cable straight 21-40-00 Opération 3) Loosen the clamp bolt on the control arm and remove the cable from the control arm 21-40-00 Opération 4) Remove the screws that attache the clamps to the firewall 21-40-00 Opération 5) From the inside of the cabin, get access to the backside of the CABIN HT control cable 21-40-00 Opération 6) Loosen the nut on the backside of the control cable 21-40-00 Opération (7) Carefully remove the cable from the instrument panel and firewall 21-40-00 Opération A. Remove the Defrost Control Cable 21-40-00 Étape (1) Carefully make the end of the defrost control cable straight 21-40-00 Opération (2) Loosen the clamp bolt on the control arm and remove the cable from the control arm 21-40-00 Opération (3) Remove the screws that connect the clamps 21-40-00 Opération (4) From the inside of the cabin, get access to the backside of the DEFROST control cable 21-40-00 Opération (5) Loosen the nut on the backside of the control cable 21-40-00 Opération (6) Carefully remove the cable from the instrument panel 21-40-00 Opération AUTOPILOT - MAINTENANCE 22-10-00 Processus NOTE: Removal of servo mount requires disconnecting the servo cable. Consequently, servo cable rigging is required upon reinstallation of the servo mount 22-10-00 Note NOTE: System rigging should be accomplished with aileron and bellcrank in neutral position 22-10-00 Note NOTE: Wrap cable around servo drum approximately 1.25 turns each direction from swaged ball when rigging (drum ball detent facing inboard) 22-10-00 Note NOTE: When installing cable guard, ensure that the legs of the cable guard do not touch the cable. Be sure that feet of cable guard straddle notches around perimeter of mount 22-10-00 Note NOTE: Removal of servo mount requires disconnecting the servo cable. Consequently, servo cable rigging is required upon reinstallation of the servo mount 22-10-00 Note NOTE: System rigging should be accomplished with elevator and bell crank in neutral position 22-10-00 Note NOTE: Wrap cable around pitch servo drum approximately 1.25 turns each direction from swaged ball when rigging (drum ball detent facing forward) 22-10-00 Note NOTE: Removal of servo mount requires disconnecting the servo cable. Consequently, servo cable rigging is required upon reinstallation of the servo mount 22-10-00 Note NOTE: Servo trim chain must be located on aft sprocket of actuator prior to rigging manual trim system. Manual trim system must be rigged prior to rigging servo trim system. Refer to Chapter 27, Elevator Trim Control - Maintenance Practices, Trim Tab 22-10-00 Note NOTE: This will place the chain sprocket on the actuator at approximately the halfway point in its rotation from its mechanical stops 22-10-00 Note NOTE: When installing cable guard, ensure that the legs of the cable guard do not touch the cable. Be sure that feet of cable guard straddle notches around perimeter of mount 22-10-00 Note NOTE: Take care not to move the positions of any wires, wire ties, or the counterweight spring clamp. Their positions are preset at the factory, and are important to insure proper performance of the unit 22-10-00 Note NOTE: This adjustment compensates for offsets in the roll axes, including the Turn Coordinator 22-10-00 Note CAUTION: Any disassemblylassembly/assembly of the servo must be done at a static- safe workstation. The inspector and bench should be grounded 22-10-00 Caution CAUTION: Any disassembly/assembly of the servo must be done at a static- safe workstation. The inspector and bench should be grounded 22-10-00 Caution CAUTION: Any disassemblylassembly of the servo must be done at a static- safe workstation. The inspector and bench should be grounded 22-10-00 Caution A. Remove Autopilot (Single-Axis) Flight Computer 22-10-00 Étape DETAIL B A1218T1001 B1218T1002 KAP-140 Autopilot Installation Figure 201 (Sheet 1) 22-10-00 Document (1) Make sure that power is OFF to autopilot flight computer 22-10-00 Opération 2) Loosen mounting screw on face of autopilot flight computer 22-10-00 Opération (3) Pull autopilot flight computer out and away from mounting tray 22-10-00 Opération A. Remove Autopilot (Dual-Axis) Flight Computer (For Airplanes without the Garmin G1000 22-10-00 Étape (1) Make sure that power is OFF to autopilot flight computer 22-10-00 Opération 2) Loosen mounting screw on face of autopilot flight computer 22-10-00 Opération (3) Pull autopilot flight computer out and away from mounting tray 22-10-00 Opération A. Remove Roll Servo 22-10-00 Étape NOTE: CABLES MUST NOT CONTACT CABLE GUARD LEGS. A1260T1006 AA1214T1029 Autopilot Servo Installation Figure 203 (Sheet 1) 22-10-00 Document NOTE: CABLES MUST NOT CONTACT CABLE GUARD LEGS. B1260T1008 BB1214T1030 Autopilot Servo Installation Figure 203 (Sheet 2) 22-10-00 Document NOTE: CABLES MUST NOT CONTACT CABLE GUARD LEGS. CC1214T1031 C1260T1009 Autopilot Servo Installation Figure 203 (Sheet 3) 22-10-00 Document (1) Remove access plate (610AB) - Refer to Chapter 6, Access/Inspection Plates - Description and Operation 22-10-00 Opération (2) Disconnect electrical connector from roll servo 22-10-00 Opération (3) Release cable tension, loosen roll servo cable at turnbuckle 22-10-00 Opération (4) Remove bolts securing roll servo to bracket assembly 22-10-00 Opération (5) Remove roll servo from airplane 22-10-00 Opération A. Remove Pitch Servo 22-10-00 Étape (1) Remove access plates 310AR, 340AL and 340AR. Refer to Chapter 6, Access/Inspection Plates - Description and Operation 22-10-00 Opération (2) Disconnect electrical connector from pitch servo 22-10-00 Opération (3) Release cable tension, loosen pitch servo cable at turnbuckle 22-10-00 Opération (4) Remove bolts securing pitch servo to bracket assembly 22-10-00 Opération (5) Remove pitch servo from airplane 22-10-00 Opération A. Remove Pitch Trim Servo 22-10-00 Étape (1) Remove access plates 310AR, 340AL and 340AR. Refer to Chapter 6, Access/Inspection Plates - Description and Operation 22-10-00 Opération 2) Disconnect electrical connector from pitch trim servo 22-10-00 Opération (3) Release cable tension, loosen pitch trim servo cable at turnbuckle 22-10-00 Opération (4) Remove bolts securing pitch trim servo to bracket assembly 22-10-00 Opération (5) Remove pitch trim servo from airplane 22-10-00 Opération GFC-700 AUTOPILOT - MAINTENANCE 22-11-00 Processus NOTE: The chain sprocket on the actuator will be at approximately the halfway point in its rotation from the mechanical stops 22-11-00 Note NOTE: One chain link adjustment is related to approximately 17 degrees of travel on the capstan 22-11-00 Note NOTE: Equivalent substitutes may be used for the following items 23-00-00 Note A. Remove the Roll Servo Actuator 22-11-00 Étape DETAIL A A1260T1014 AA1260T1014 Autopilot Servo Installation Figure 201 (Sheet 1) 22-11-00 Document NOTE: CABLES MUST NOT TOUCH THE CABLE GUARD LEGS B1260T1008 BB1260T1008 Autopilot Servo Installation Figure 201 (Sheet 2) 22-11-00 Document NOTE: CABLES MUST NOT TOUCH THE CABLE GUARD LEGS VIEW B-B C1214T1072 CC1214T1072 Autopilot Servo Installation Figure 201 (Sheet 3) 22-11-00 Document (1) Make sure the MASTER and AVIONICS switches are in the OFF position 22-11-00 Opération (2) Remove the 610AB access panel. Refer to Chapter 6, Access/Inspection Plates - Description and Operation 22-11-00 Opération (3) Disconnect the electrical connector from the roll servo actuator 22-11-00 Opération (4) Remove the bolts and washers that attach the roll servo actuator to the torque mount 22-11-00 Opération (5) Remove the roll servo actuator from the airplane 22-11-00 Opération A. Remove the Roll Servo and Cable 22-11-00 Étape (1) Make sure the MASTER and AVIONICS switches are in the OFF position 22-11-00 Opération (2) Remove the 610AB access panel to get access to the roll servo and the cable. Refer to Chapter 6, Access/Inspection Plates - Description and Operation 22-11-00 Opération (3) Disconnect the electrical connector 22-11-00 Opération (4) Release the servo cable tension at the turnbuckle 22-11-00 Opération (5) Remove the cable guard 22-11-00 Opération 6) Record how the cable is installed on the capstan 22-11-00 Opération 1) Disconnect the cable from the turnbuckle 22-11-00 Opération 8) Remove the cable from the capstan 22-11-00 Opération (9) Remove the bolts that attach the servo assembly to the bracket 22-11-00 Opération (10) Remove the servo from the airplane 22-11-00 Opération A. Remove Pitch Servo Actuator 22-11-00 Étape (1) Make sure the MASTER and AVIONICS switches are in the OFF position 22-11-00 Opération (2) Remove the 310AR, 340AL and 340AR access panels. Refer to Chapter 6, Access/Inspection Plates - Description and Operation 22-11-00 Opération (3) Disconnect the electrical connector from the pitch servo 22-11-00 Opération (4) Remove the bolts and washers that attach the pitch servo to the torque mount 22-11-00 Opération (5) Remove the pitch servo actuator from the airplane 22-11-00 Opération A. Remove the Pitch Servo and Cable 22-11-00 Étape (1) Make sure the MASTER and AVIONICS switches are in the OFF position. Remove the 310AR, 340AL and 340AR access panels to get access to the pitch servo and the cable. Refer to Chapter 6, Access Plates and Panels Identification - Description and Oper 22-11-00 Opération 3) Disconnect the electrical connector 22-11-00 Opération Release the servo cable tension at the turnbuckle 22-11-00 Opération 5) Remove the cable guard 22-11-00 Opération 6) Record how the cable is installed on the capstan 22-11-00 Opération I Disconnect the cable from the turnbuckle 22-11-00 Opération (8) Remove the cable from the capstan 22-11-00 Opération (9) Remove the bolts that attach the servo assembly to the bracket 22-11-00 Opération (10) Remove the servo from the airplane 22-11-00 Opération A. Remove the Pitch Trim Servo 22-11-00 Étape (1) Make sure the MASTER and AVIONICS switches are in the OFF position. Remove the 310AR, 340AL and 340AR access panels. Refer to Chapter 6, Access/Inspection Plates - Description and Operation 22-11-00 Opération (3) Disconnect the electrical connector from the pitch trim servo 22-11-00 Opération (4) Remove the bolts and washers that attach the pitch trim servo to the torque mount 22-11-00 Opération (5) Remove the pitch trim servo from the airplane 22-11-00 Opération (1) Make sure the MASTER and AVIONICS switches are in the OFF position 22-11-00 Opération (2) Remove the 310AR, 340AL and 340AR access panels. Refer to Chapter 6, Access/Inspection Plates - Description and Operation 22-11-00 Opération (3) Disconnect the electrical connector from the pitch trim servo 22-11-00 Opération (4) Release the control cable tension and loosen the pitch trim servo control cable at the turnbuckle 22-11-00 Opération (5) Remove the bolts and washers that attach the pitch trim servo to the bracket 22-11-00 Opération (6) Remove the pitch trim servo from the airplane 22-11-00 Opération COMMUNICATIONS - MAINTENANCE 23-10-00 Processus NOTE: The unit must be in position in the mounting rack to let the locking stud engage the channel 23-10-00 Note NOTE: The electrical cleaner will help to remove oil and dirt from the internal electrical contacts of the switch. The recommended contact cleaner is Zip-Chem Aviation Products D-5026 NS Aerosol or equivalent 23-10-00 Note NOTE: The transmit light on the com radio will come on when the power is turned on 23-10-00 Note CAUTION: Make sure the unit goes into position without resistance. Damage to the connectors, unit, or mounting rack will occur if the unit is pushed into position with force 23-10-00 Caution CAUTION: Make sure that oil and dirt do not collect on the internal electrical contacts of the switch and cause the button to operate incorrectly 23-10-00 Caution A. Remove the NAV/COM with the Glide Slope 23-10-00 Étape NOTE: The airplane has dual NAVICOM units installed. One NAVICOM unit has glideslope. The removal and installation is typical 23-10-00 Note NOTE: The procedures that follow are for airplanes with standard avionics 23-10-00 Note CAUTION: Do not interchange the KX-155A and the KX-165A NAV/COM radios. The wiring is not the same for the two different radios. If these radios are interchanged and used with the same wiring, damage can occur to the KX-155A and/or the KX-165A NAV/CO 23-10-00 Caution Figure 201 (Sheet 1) 23-10-00 Document (1) Make sure the NAVICOM power is OFF 23-10-00 Opération (2) Disengage the NAV COM 1 and/or NAV COM 2 circuit breaker 23-10-00 Opération (3) On the face of the NAV/COM unit, turn the mounting screw counterclockwise until locking paw releases the unit from the back of the tray 23-10-00 Opération (4) Hold the NAVICOM unit and gently pull it out of the tray 23-10-00 Opération (5) Pull the NAV/COM panel out from the mounting tray to disconnect the COM 1 electrical connectors and/or COM 2 connectors from the back of the NAVICOM panel 23-10-00 Opération A. Remove the Integrated Avionics Unit 23-10-00 Étape NOTE: The procedures that follow are for airplanes with Garmin G1000 23-10-00 Note NOTE: The airplane has dual integrated avionics units installed. The removal and installation is typical 23-10-00 Note CAUTION: Use a tailcone stand when you get in the tailcone 23-10-00 Caution Figure 202 (Sheet 1) 23-10-00 Document (1) Disconnect electrical power to the airplane 23-10-00 Opération 2) Set the MASTER switch and AVIONICS switch to the off position 23-10-00 Opération (3) Disengage the applicable COM 1 or COM 2 circuit breaker 23-10-00 Opération (4) Get access to the avionics inside the tailcone 23-10-00 Opération (a) Remove the baggage divider 23-10-00 Opération (5) Push on the D-Ring and turn it 90 degrees counterclockwise to release the lever on the unit 23-10-00 Opération (6) Move the lever up to disengage the locking stud with the dogleg slot in the mounting rack 23-10-00 Opération (7) Remove the unit from the mounting rack 23-10-00 Opération A. Remove the Antenna 23-10-00 Étape NOTE: The removal/installation procedures are typical for both antennas 23-10-00 Note NOTE: On airplanes with Garmin G1000 avionics, the left VHF antenna is also the GDL-69A antenna and a GPS antenna 23-10-00 Note NOTE: ANTENNA CAN BE DIFFERENT THAN ILLUSTRATION. 1210T1001 A0518T1025 VHF Communication Antenna Installation Figure 203 (Sheet 1) 23-10-00 Document COMM 2 - LEFT ANTENNA AIRPLANES WITH GARMIN G1000 A0518T1107 VHF Communication Antenna Installation Figure 203 (Sheet 2) 23-10-00 Document (1) Make sure all electrical power to the airplane is disconnected 23-10-00 Opération (2) Get access to the top of the wing 23-10-00 Opération (3) Remove the four screws and lock washers, which attach the antenna to the top of the fuselage 23-10-00 Opération (4) Pull the antenna away from the fuselage far enough to disconnect the coaxial connector COMM 1 and/or COMM 2 from the antenna 23-10-00 Opération (a) Attach the coax cable to the airplane structure to prevent the cable from falling down into the headliner area 23-10-00 Opération A. Remove the NAV Antenna 23-10-00 Étape DETAIL B 1210T1001 A0718T1061 B0718T1062 NAV Antenna Installation Figure 204 (Sheet 1) 23-10-00 Document (1) Put the MASTER switch in the off position 23-10-00 Opération (2) Remove the screws that attach the NAV antenna to the tail 23-10-00 Opération (3) Pull the antenna away from the fuselage to disconnect the coax connector from the antenna 23-10-00 Opération (4) Carefully remove thet fillet seal from the junction of the NAV antenna and the skin of the airplane 23-10-00 Opération A. Remove the Microphone Switch 23-10-00 Étape DETAIL B 1210T1001 A0760R1007 B0715T1004 Microphone Switch Figure 205 (Sheet 1) 23-10-00 Document (1) Remove the nut that attaches the microphone switch (S1) to the escutcheon 23-10-00 Opération LI Remove the screw that attaches the escutcheon to the control wheel 23-10-00 Opération (3) Lift up the escutcheon to get access to the microphone switch and disconnect the microphone switch from the control wheel connection 23-10-00 Opération AUDIO PANEL - MAINTENANCE 23-50-00 Processus NOTE: Ensure audio panel is properly connected to electrical connectors at rear of mounting tray 23-50-00 Note A. Remove the Audio Panel 23-50-00 Étape NOTE: Removal and installation procedures are typical for airplanes with standard avionics and airplanes with Garmin G1000 23-50-00 Note Figure 201 (Sheet 1) 23-50-00 Document DETAIL D A0718T1053A C0518T1041 DO718T1053A Audio Panel Installation Figure 201 (Sheet 2) 23-50-00 Document (1) Make sure the AVIONIC switch is in off position 23-50-00 Opération (2) On the face of the audio panel, turn the recessed screw counterclockwise until the lock releases the unit from the back of the tray 23-50-00 Opération (3) Carefully pull the audio panel out from the tray and disconnect the electrical connectors from the audio panel 23-50-00 Opération A. Remove Pilot/Front Passenger Intercom Jacks 23-50-00 Étape (1) Ensure avionic and master switches are in the OFF position 23-50-00 Opération (2) To gain access to backside of jacks, remove interior sidewall panel located between instrument panel and forward door post. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 23-50-00 Opération (3) Loosen and remove jamnuts securing jacks to interior panel 23-50-00 Opération (4) Carefully label all wires to microphone jack (small plug) and headphone jack (large plug) 23-50-00 Opération (5) Cut wires near solder point at each jack 23-50-00 Opération C. Remove Rear Passenger Intercom Jacks 23-50-00 Étape (1) Ensure avionics and master switches are in the OFF position 23-50-00 Opération 2) Remove rear seat. Refer to Chapter 25, Rear Seats - Maintenance Practices 23-50-00 Opération (3) Remove rear sidewall panel. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 23-50-00 Opération (4) Carefully label all wires to microphone jack (small plug) and headphone jack (large plug) 23-50-00 Opération 5) Cut wires near solder point at each jack 23-50-00 Opération (6) Loosen and remove jamnuts securing jacks to rear sidewall panel 23-50-00 Opération STATIC DISCHARGING - MAINTENANCE 23-60-00 Processus NOTE: Equivalent substitutes can be used for the following items 24-00-00 Note NOTE: Refer to the Lamar TE04 MCU Test Set and the LI-0021 instructions for additional testing procedures of the alternator: system. Refer to Electrical Power - General, Tools, Equipment, and Materials 24-20-00 Note WARNING: Use precaution when you use a high voltage megonmmeter to prevent an electrical shock 23-60-00 Warning A. Remove Static Wick 23-60-00 Étape NUT SCREW 1210T1001 A0518T1024 DETAIL D DETAIL C B05182002 C05182002 D05182002 Static Discharger Installation Figure 201 (Sheet 1) 23-60-00 Document (1) Carefully drill out mounting rivets which attach static wick to structure. Ensure holes are not drilled oversize 23-60-00 Opération (2) Remove static wick from the airplane skin 23-60-00 Opération ALTERNATOR - MAINTENANCE 24-20-00 Processus CAUTION: On airplanes with a new alternator belt installed and on new airplanes, do a check of the belt tension again in the first 10 to 25 hours of operation 24-20-00 Caution A. Alternator Removal 24-20-00 Étape CAUTION: Make sure that you are careful when you remove and install the power and ground ring terminals. Do not bend or twist the terminals. If possible, always remove the terminals from the alternator before you remove the alternator. If possible, a 24-20-00 Caution Figure 201 (Sheet 1) 24-20-00 Document (1) Remove the upper cowl. Refer to Chapter 71, Cowls - Maintenance Practices 24-20-00 Opération L Disconnect the battery cables. Refer to Battery - Maintenance Practices 24-20-00 Opération (3) Disconnect the electrical connectors from the alternator 24-20-00 Opération (4) Remove the safety wire from the adjustment bolt. Loosen the bolt 24-20-00 Opération (5) Loosen the alternator mounting bolt 24-20-00 Opération (6) Rotate the alternator and remove the drive belt from the alternator pulley 24-20-00 Opération (7) Remove the adjustment bolt and the mounting bolt, and remove the alternator from the airplane 24-20-00 Opération BATTERY - MAINTENANCE 24-30-00 Processus NOTE: The Amp-hour rating is based on a five hour discharge rate 24-30-00 Note NOTE: For correct operation, the battery and connections must be clean at all times 24-30-00 Note NOTE: The procedures that follow are for batteries that use a Gill TSC-01V or a Gill TDMC Battery Charger 24-30-00 Note NOTE: The Gill TSC-01V is automated with a typical charge time of approximately two hours. Some batteries will take more time to charge as a result of the battery condition 24-30-00 Note NOTE: The EMPTY battery level indicator shows that the battery is correctly connected and charging 24-30-00 Note NOTE: Make sure that you let thel battery fully charge. This will make sure of a good battery life and performance 24-30-00 Note NOTE: The electrolyte level decreases as the battery temperature decreases 24-30-00 Note NOTE: The charger is in a constant current mode when the timer is on 24-30-00 Note NOTE: The charge is measured across the battery terminals with the charger on 24-30-00 Note NOTE: The electrolyte level decreases as the battery temperature decreases 24-30-00 Note NOTE: Some hydrometers will have a built-in temperature compensation chart and a thermometer 24-30-00 Note NOTE: For increased temperatures, the values will be lower. For decreased temperatures, the values will be higher 24-30-00 Note NOTE: For more accurate results, you can use a load type tester after you charge the battery 24-30-00 Note NOTE: A specific gravity check can be completed after the charge. This check will not find cells that short circuit under loads or have broken connectors between cell plates 24-30-00 Note WARNING: You must keep sparks and open flame away from the battery. The battery makes hydrogen and oxygen gases when it is charged. The gases will collect and create a hazardous, explosive condition. You must have free ventilation of the battery area 24-30-00 Warning WARNING: The battery cell temperature must not be more than 115°F (46°C). Reduce the charge rate if the temperature increases more than 115°F (46°C). The charge must not cause acid to be blown from the vents 24-30-00 Warning CAUTION: Do not tighten the hold-down bolts too much or you will damage the hold-down strap 24-30-00 Caution CAUTION: Connect the positive battery cable first, then the negative cable. This will prevent an accidental short of the battery from hand tools 24-30-00 Caution CAUTION: Do not let the battery charger charge at 32 volts for more than thirty minutes 24-30-00 Caution A. Remove the Battery 24-30-00 Étape CAUTION: Disconnect the negative battery cable first, then the positive cable. This will prevent an accidental short of the battery from hand tools 24-30-00 Caution Figure 201 (Sheet 1) 24-30-00 Document (1) Remove the upper right cowl. Refer to Chapter 71, Cowls - Maintenance Practices 24-30-00 Opération (2) Remove the battery box top cover 24-30-00 Opération (3) Disconnect the negative and positive cable from the battery 24-30-00 Opération (4) Remove the battery from the airplane 24-30-00 Opération STANDBY BATTERY - MAINTENANCE 24-30-10 Processus NOTE: If necessary, washers can be installed in the gap between the bracket and the bracket assembly. The combined thickness of the washers can not be more than 0.25 inch 24-30-10 Note NOTE: To charge the standby battery, a constant voltage charger, constant current charger or a modification of - both can be used. Use only chargers that are made to charge lead acid batteries. A constant voltage "fast" charge can be done with a char 24-30-10 Note NOTE: There is no limit on the initial charge current as long as the voltage is not more than 24-30-10 Note 30.0 volts. Ifit is necessary to set the charger to the battery capacity, use 8 Amp-hour 24-30-10 Note as the standby battery capacity. 8 Amp-hour is thel battery's capacity at a 10-hour rate 24-30-10 Note NOTE: If the state of charge of the battery is satisfactory, charge times of less than 16 hours are possible. The battery is completely charged if the charge current stays stable (approximately .1 to .2 amps) for a minimum of one hour. Charge times g 24-30-10 Note NOTE: It is important that the photocell on the PFD controls the PFD light level to FULL BRIGHT. The manual AVIONICS rheostat is not operational with the primary alternator and main battery power turned off 24-30-10 Note NOTE: A stopwatch will be necessary in the following steps to measure the time of the standby battery discharge 24-30-10 Note NOTE: After initialization, the PFD will operate in full bright mode with only red X's over the NAV 2, COM 2, and XPDR functions 24-30-10 Note NOTE: The standby battery initial current discharge will be between 2.1 and 3.1 amps as shown on the PFD standby battery ammeter. The essential bus initial voltage will be approximately 24.2 volts as shown on the PFD essential bus voltmeter 24-30-10 Note NOTE: Ifthe standby battery voltage does not stay more than. 20.0 volts for 55 minutes during the on aircraft standby battery capacity test, the battery is not acceptable for return to service 24-30-10 Note NOTE: A stopwatch will be necessary in the following steps to time the battery discharge. Some aircraft capacity testers have a built-in timer which may be used instead of a stopwatch 24-30-10 Note NOTE: The battery capacity is satisfactory if the battery voltage stays more than 20.0 volts for 60 minutes 24-30-10 Note NOTE: If the standby battery does not stay more than 20.0 volts for 60 minutes during the bench capacity test, the battery is not acceptable for return to service 24-30-10 Note CAUTION: Make sure you use a wrist strap when the standby battery pc board is installed. The standby battery pc board is sensitive to electrostatic discharge 24-30-10 Caution CAUTION: Never set the charger to a level that is higher than 30.0 volts or you can cause damage to the battery 24-30-10 Caution CAUTION: Do not let the essential bus voltage decrease below 20.0 volts or the standby battery can be damaged. Set the STDBY BATT switch to the OFF position before the voltage decreases to less than 20.0 volts. Voltage values less than 22.5 volts can 24-30-10 Caution 20.0 volts, charge the battery immediately and do the test again 24-30-10 Caution CAUTION: Do not let the battery voltage decrease below 20.0 volts or the standby battery can be damaged. Set the tester to stop discharge before the voltage drops to less than 20.0 volts. Voltage values less than 22.5 volts can decrease quickly, SO m 24-30-10 Caution A. Remove the Standby Battery 24-30-10 Étape Standby Battery Installation Figure 201 (Sheet 1) 24-30-10 Document (1) Make sure the STDBY BATT switch is in the OFF position 24-30-10 Opération 2 Make sure that the MASTER ALT BAT switch is in the OFF position 24-30-10 Opération (3) Remove the Primary Flight Display. Refer to Chapter 34, Control Display Unit - Maintenance Practices 24-30-10 Opération (4) Disconnect the electrical connection to the battery 24-30-10 Opération (5) Remove the nut and washer from the bracket 24-30-10 Opération (6) Loosen the forward nut on the bracket 24-30-10 Opération (7) Carefully remove the battery from the airplane 24-30-10 Opération A. Remove the Standby Battery PC Board 24-30-10 Étape CAUTION: Make sure you use a wrist strap when the standby battery pc board is removed. The standby battery pc board is sensitive to electrostatic discharge 24-30-10 Caution Standby Battery PC Board Installation Figure 202 (Sheet 1) 24-30-10 Document (1) Make sure the STDBY BATT switch is in the OFF position. Make sure that the MASTER ALT BAT switch is in the OFF position 24-30-10 Opération 3) Remove the switch panel. Refer to Chapter 31, Instrument and Control Panels - Maintenance Practices 24-30-10 Opération (4) Put on a wrist strap and ground the wrist strap to the airframe 24-30-10 Opération 5) Disconnect the PC board from electrical connector 24-30-10 Opération 6) Remove the screws that attach the board to the extrusion. Carefully remove the board from the extrusion 24-30-10 Opération 8) If applicable, put the PC board in an electrostatic safe bag 24-30-10 Opération POWER JUNCTION BOX - MAINTENANCE 24-60-00 Processus NOTE: Turbocharged airplanes do not have a cooling shield installed on the power junction box 24-60-00 Note NOTE 2: THE POSITION OF THE CIRCUIT BREAKERS (F1) AND (F3) ARE INTERCHANGED ON SOME AIRPLANES WITH POWER JUNCTION BOXES WITH I.C.1.1 ON THE LABEL. AA0558T1007 24-60-00 Note CAUTION: Make sure that all electrical power is removed from the airplane and that the battery is disconnected before you do work on power junction box components 24-60-00 Caution A. Remove the Power Junction Box 24-60-00 Étape NOTE: Turbocharged airplanes do not have a cooling shield installed on the power junction box 24-60-00 Note Power Junction Box Installation Figure 201 (Sheet 1) 24-60-00 Document CLAMP COOLING SCREW SHIELD SPACER NUT WASHER DETAIL A AIRPLANES 20608215 AND ON A1218T1004 A1258T1007 Power Junction Box Installation Figure 201 (Sheet 2) 24-60-00 Document DO NOT INCORPORATE SB00-24-01 AA0558T1002 Power Junction Box Installation Figure 201 (Sheet 3) 24-60-00 Document Power Junction Box Installation Figure 201 (Sheet 4) 24-60-00 Document (1) Remove the upper cowl, refer to Chapter 71, Cowls - Maintenance Practices 24-60-00 Opération 2 Disconnect the battery cables, refer to Battery - Maintenance Practices 24-60-00 Opération (3) Remove the cover from the power junction box 24-60-00 Opération (4) Disconnect the electrical connectors, cables, and ground strap from the power junction box 24-60-00 Opération (5) Remove the cooling shield 24-60-00 Opération (a) Remove the bolts that connect the cooling shield to the power junction box 24-60-00 Opération (b) Disconnect the cooling shield from the power junction box 24-60-00 Opération (6) Remove the bolts that connect the power junction box to the firewall 24-60-00 Opération (7) Remove the power junction box from the airplane 24-60-00 Opération ALTERNATOR CONTROL UNIT - MAINTENANCE 24-60-01 Processus NOTE: It is necessary to use two general non-rechargeable 9 volt batteries in new condition to apply a temporary over-voltage condition on the ACU Sense wire. A locally fabricated battery test harness is also necessary. The test harness uses two 9-vo 24-60-01 Note NOTE: The ACU sense wire is connected to Pin B in the ACU connector 24-60-01 Note NOTE: This will help prevent accidental electrical shorts 24-60-01 Note NOTE: The ACU regulation circuit is non operational. The ALT FLD circuit breaker should open if the voltage is more than 32 volts 24-60-01 Note A. Remove the Alternator Control Unit 24-60-01 Étape CIRCUIT BREAKER - MAINTENANCE 24-61-00 Processus NOTE: To install or align the circuit breaker cover, it is permitted to add an additional nut between each circuit breaker and circuit breaker panel 24-61-00 Note NOTE: The flanges on the cover fit between the circuit breakers and the panel. Indentions in the cover must match screw holes in panel 24-61-00 Note A. Remove the Circuit Breaker 24-61-00 Étape OPTIONAL PROP DE ICE VIEW A-A B1218T1003 A1218T1002 AA0518T1005 C1218T1003 Circuit Breaker Panel Installation Figure 201 (Sheet 1) 24-61-00 Document (1) Remove the top right cowl. Refer to Chapter 71, Cowl - Maintenance Practices 24-61-00 Opération 2) Disconnect the battery cables. Refer to Battery - Maintenance Practices 24-61-00 Opération (3) Remove the screws that attach the circuit breaker panel to the bottom instrument panel 24-61-00 Opération (4) Remove the circuit panel 24-61-00 Opération (5) Identify with a label the wires for the circuit breaker and disconnect them 24-61-00 Opération (6) Remove the nut and washer that attach the circuit breaker to the circuit breaker panel 24-61-00 Opération (7) Remove the circuit breaker 24-61-00 Opération ESSENTIAL AND CROSSFEED BUS DIODES - MAINTENANCE 24-61-01 Processus NOTE: When the diodes are replaced, the inspections that follow (3A, 3B, or 3C) must be done to make sure that all of the diodes operate correctly 24-61-01 Note NOTE: The Lamar TE04 MCU Test Set is used as an alternative to inspections 3A, 3B, or 3C. Refer to the Lamar TE04 MCU Test Set, instructions LI-0021 steps 4.3.A through 4.3.E 24-61-01 Note NOTE: Airplanes 20608095 and ON, Airplanes T20608165 and ON, and Airplanes incorporating SB00-24-01 do not use fuses in the power junction box 24-61-01 Note NOTE: The inspection procedure that follows is for airplanes without Garmin G1000 avionics 24-61-01 Note NOTE: A minimum of 20 volts shows thatt there is power to the crossfeed and essential buses. The GEA-71 must be on to show the voltage of the crossfeed bus. If there are no red X's on the engine indications, the GEA-71 is on 24-61-01 Note NOTE: Do the essential or crossfeed bus diode inspection procedure applicable to your airplane before the test that follows is done. Refer to Essential and Crossfeed Bus Diode Inspection 24-61-01 Note NOTE: The test that follows must be done only if required by the essential or crossfeed bus diode inspections. The replacement of all the essential/crossfeed diodes is an alternative to the test procedure that follows 24-61-01 Note NOTE: Equivalent substitutes may be used for the following listed items 25-00-00 Note CAUTION: Do not remove fuses with the MASTER BAT switch in the on position 24-61-01 Caution CAUTION: Do not remove bus wires from the circuit breakers with MASTER BAT switch in the on position 24-61-01 Caution CAUTION: Do not remove bus wires from the circuit breakers with the MASTER BAT or the STDBY BATT switches in the on position 24-61-01 Caution A. Remove the essential or crossfeed bus diode 24-61-01 Étape Essential and Crossfeed Bus Diode Installation Figure 201 (Sheet 1) 24-61-01 Document NOTE 2: CROSSFEED BUS DIODES A0718T1053A B0718T1056 C0718T1055 Essential and Crossfeed Bus Diode Installation Figure 201 (Sheet 2) 24-61-01 Document (1) Remove the circuit breaker panel. Refer to Circuit Breaker - Maintenance Practices 24-61-01 Opération (2) Carefully remove thel heat shrinkable tubing from the diode. Refer to the 206H/T206H 1997 and On Wiring Diagram Manual, Chapter 20, Heat Shrinkable Tubing - Maintenance Practices 24-61-01 Opération (3) Remove the solder from the wire and from the diode. Refer to the Model 206H/T206H 1997 and On Wiring Diagram Manual, Chapter 20, Soldering - Maintenance Practices 24-61-01 Opération (4) Remove the nut and washer from the diode 24-61-01 Opération (5) Remove the diode 24-61-01 Opération FRONT SEATS AND RAILS - MAINTENANCE 25-10-00 Processus NOTE: The installation procedures for the pilot's, copilot's, and center seat recline control assemblies are typical 25-10-00 Note NOTE: The installation procedures for the pilot's, copilot's, and center seat ultraloc actuators are typical 25-10-00 Note NOTE: The installation procedures for the pilot's, copilot's, and center seat height adjustment handle assemblies are typical 25-10-00 Note WARNING: If the airplane has the AMSAFE inflatable restraints, do not do maintenance on the seats or seat rails until you have first looked at and obeyed all the applicable precautions and instructions supplied in the AMSAFE publications and this Mai 25-10-00 Warning WARNING: Make sure the seat stops are set correctly. Incorrectly installed seat stops can let the seat move during flight, with the result of serious injury or death 25-10-00 Warning WARNING: IT IS EXTREMELY IMPORTANT THAT PILOT'S SEAT STOPS ARE INSTALLED, SINCE ACCELERATION AND DECELERATION COULD POSSIBLY PERMIT SEAT TO BECOME DISENGAGED FROM SEAT RAILS AND CREATE. A HAZARDOUS SITUATION, ESPECIALLY DURING TAKEOFF AND LANDING 25-10-00 Warning WARNING: Make sure that there is a 0.12 inch (3.04 mm) minimum clearance between the ultraloc actuator and the seat crank arm bell crank. If there is not sufficient clearance, failure of the ultraloc actuator can occur and cause injury or death 25-10-00 Warning safety precautions, damage to equipment and injury to personnel 25-10-00 Caution can occur 25-10-00 Caution CAUTION: Do not tighten the cable too much. If the cable is too tight, it will cause the seat recline lock mechanism to release from the locked position uncommanded 25-10-00 Caution CAUTION: Make sure that the ultraloc end fitting is installed with the 0.68 inch 25-10-00 Caution (17.27 mm) end towards the outside of the seat base frame. If the 25-10-00 Caution end fitting is installed incorrectly, the ultraloc actuator will not be in 25-10-00 Caution the correct alignment, and the seat will not operate correctly 25-10-00 Caution CAUTION: Make sure that the adjustment nut is installed in the position shown in Figure 204. If the adjustment nut is installed incorrectly, the seat can be lowered too far and cause damage to the ultraloc actuator 25-10-00 Caution A. Seat Removal 25-10-00 Étape WARNING: If the airplane has the AMSAFE inflatable restraints, do not remove the seats with the seat belts buckled or the EMA connected. Damage can occur to the system and an accidental deployment of the system can cause injury to personnel 25-10-00 Warning CRANK SEAT HEIGHT LOCK 0 ADJUSTMENT HANDLE SEAT SEAT BELL CRANKS LOCK BASE ASSEMBLY DETAIL A 1210T1001 A0519T1036 Seat Installation Figure 201 (Sheet 1) 25-10-00 Document BUSHING 1210T1001 BUSHING A0519T1036 DETAIL D B0519T1037 DETAIL C C0519T1038 D0519T1039 E0511T1001 Seat Installation Figure 201 (Sheet 2) 25-10-00 Document (1) Disarm the AMSAFE inflatable restraints. Refer to AMSAFE Inflatable Restraint Disarm/Arm 25-10-00 Opération 2) Remove the seat stops from the front and the rear of the outboard seat rail 25-10-00 Opération (3) Unlatch the seat from the seat rail and move the seat forward on the seat rail until the forward roller clears the seat rail 25-10-00 Opération (4) Move the seat backward on the seat rail until the rear rollers clear the seat rail 25-10-00 Opération (5) Remove the seat from the airplane 25-10-00 Opération A. Seat Rail Removal 25-10-00 Étape Figure 202 (Sheet 1) 25-10-00 Document (1) Remove the bolts that attach the seat rails to the fuselage 25-10-00 Opération A. Remove the Seat Recline Control Assembly 25-10-00 Étape NOTE: The removal procedures for the pilot's, copilot's, and center seat recline control assemblies are typical 25-10-00 Note WASHER VIEW B-B B0519T1085 CSP-22306 BB0719T013 Seat Ultraloc Actuator Installation Figure 203 (Sheet 1) 25-10-00 Document WASHER VIEW B-B B0519T1085 CSP-22306 BB0719T013 Seat Ultraloc Actuator Installation Figure 203 (Sheet 2) 25-10-00 Document (1) Put the seat to the fully reclined and raised position 25-10-00 Opération (2) If necessary, remove the seat from the airplane 25-10-00 Opération (a) For the pilot's and the copilot's seat, refer to the Seat Removal/Installation in this section 25-10-00 Opération (b) For the center seat, refer to Center Seats and Rails - Maintenance Practices, Center Seat Removal/Installation 25-10-00 Opération (3) Disconnect the cable end from the recline lock mechanism on the ultraloc actuator kit 25-10-00 Opération (4) Remove the lock ring that attaches the control cable housing to the ultraloc actuator kit 25-10-00 Opération (5) Remove the screws and the nuts that attach the seat recline control to the seat bracket 25-10-00 Opération (a) Pull the control assembly with cable through the seat bracket and remove it from the seat 25-10-00 Opération A. Remove the Seat Ultraloc Actuator 25-10-00 Étape NOTE: The removal procedures for the pilot's, copilot's, and center seat ultraloc actuators are typical 25-10-00 Note (1) Put the seat to the fully reclined and raised position 25-10-00 Opération 2) If necessary, remove the seat from the airplane 25-10-00 Opération (a) For the pilot's and the copilot's seat, refer to the Seat Removal/Installation in this section 25-10-00 Opération (b) For the center seat, refer to Center Seats and Rails - Maintenance Practices, Center Seat Removal/Installation 25-10-00 Opération (3) Remove the bolt, washers, and nut that attaches the aft end of the ultraloc actuator to the seat back frame and the ultraloc clevis bracket 25-10-00 Opération (4) Disconnect the ultraloc actuator kit from the ultraloc actuator 25-10-00 Opération (5) Remove the bolts and the washers that attach the ultraloc end fitting to the ultraloc clevis fitting and the angle on the seat base frame 25-10-00 Opération (a) Remove the ultraloc actuator and the ultraloc end fitting from the seat 25-10-00 Opération (6) If necessary, remove the jam nut that attaches the ultraloc end fitting to the ultraloc actuator 25-10-00 Opération (a) Remove the end fitting from the ultraloc actuator 25-10-00 Opération A. Remove the Height Adjustment Handle Assembly 25-10-00 Étape NOTE: The removal procedures for the pilot's, copilot's, and center seat height adjustment handle assemblies are typical 25-10-00 Note NOTE: THE HEIGHT ADJUSTMENT NUT MUST BE INSTALLED AS SHOWN UP FOR THE SEAT TO FUNCTION FWD CORRECTLY AND TO GIVE DETAIL D 25-10-00 Note Seat Ultraloc Actuator Installation Figure 204 (Sheet 1) 25-10-00 Document THE SEATCRANK ARM BELL CRANK. C0790T007 DO790T007 Seat Ultraloc Actuator Installation Figure 204 (Sheet 2) 25-10-00 Document (1) Put the seat to the fully reclined and raised position 25-10-00 Opération 2) If necessary, remove the seat from the airplane 25-10-00 Opération (a) For the pilot's and the copilot's seat, refer to the Seat Removal/Installation in this section 25-10-00 Opération b) For the center seat, refer to Center Seats and Rails - Maintenance Practices, Center Seat Removal/Installation 25-10-00 Opération (3) Remove the screw and the washer that attaches the bearing block for the height adjustment handle assembly to the seat base 25-10-00 Opération (4) Remove and discard the cotter pin from the pin that attaches the height adjustment nut to the bracket on the bell crank assembly 25-10-00 Opération (a) Remove the pin and the washer from the adjustment nut and the bracket 25-10-00 Opération (b) Remove the height adjustment handle assembly from the seat 25-10-00 Opération MAP COMPARTMENT - MAINTENANCE 25-10-04 Processus A. Remove Map Compartment 25-10-04 Étape Map Compartment Installation Figure 201 (Sheet 1) 25-10-04 Document (1) Remove interior screws securing map compartment to instrument panel structure 25-10-04 Opération INFLATABLE RESTRAINT SYSTEM - MAINTENANCE 25-10-10 Processus NOTE: The AMSAFE Aviation Inflatable Restraint (AAIR) must be examined in accordance with the time intervals in Chapter 5, Inspection Time Limits. The AMSAFE Aviation Inflatable Restraint (AAIR) assemblies have a time life associated with them. Refer 25-10-10 Note NOTE: The maximum continuous storage time for the inflator assembly is seven years from the date of manufacture. After seven years, send the inflator assembly to AMSAFE Aviation for inspection and repair 25-10-10 Note NOTE: The maximum continuous storage time for the EMA is seven years from the date of manufacture. After seven years, send the EMA to AMSAFE Aviation for inspection and repair 25-10-10 Note NOTE: Leave the protective plastic bag on the air bag belt during installation to keep it clean 25-10-10 Note NOTE: The shipping caps can be used again 25-10-10 Note NOTE: If aligned correctly, the gas hose will be on top of the seat belt attachment hardware. The label will be on aft side of the belt 25-10-10 Note NOTE: The fitting assembly must be attached to the hose before it is connected to the inflator assembly 25-10-10 Note NOTE: The inflator hose connector fitting is a pressure fitting which must be fully extended onto the gas hose barb to make an airtight connection 25-10-10 Note NOTE: There are two seats in each AAIR system. This functional test must be completed for each AAIR system on the airplane 25-10-10 Note NOTE: For the second seat location, the 2 LED light will be used to give an indication 25-10-10 Note WARNING: Do not try to open the inflator assembly. Do not apply an electric current to the electronics connection. The inflator assembly is a stored, gaslenergetic material device and can cause injury if accidentally deployed 25-10-10 Warning WARNING: Make sure that the end-release connector for each inflator assembly is disconnected to prevent accidental firing of the inflator squibs. Accidental deployment of the system can cause injury 25-10-10 Warning WARNING: Keep all magnetic fields away from the electronics module assembly (EMA) during the removal and installation procedure. Accidental deployment of the system can cause injury 25-10-10 Warning CAUTION: Use care to keep contamination and cleaning agents away from the hardware assemblies 25-10-10 Caution CAUTION: Do not let any part of the AAIR soak in any solution. This can cause damage to the AAIR system. Do not use too much water when you clean the AAIR parts. Too much water can cause damage to the internal components and cause them to be unservic 25-10-10 Caution CAUTION: Only use sufficient cleaning agent to make minimal suds. You must remove excess soap before the you install the part in the system.Do not dry the belt assembly in sunlight or near any source of heat. Do not dry clean the belt assembly. Do no 25-10-10 Caution CAUTION: Keep the isopropyl alcohol away from the webbing, air bag cover, and the gas hose material 25-10-10 Caution CAUTION: Do not use soap or water on metal parts 25-10-10 Caution CAUTION: Calibrate the V23 system diagnostic tool again before use if it is hit or shaken or if it falls to the floor 25-10-10 Caution A. Restraint System Removal 25-10-10 Étape NOTE: The gas hose barb has a layer of Loctite and is tightly attached to the fitting. Use soft-grip channel-lock type pliers to hold the barb while you disconnect the hose 25-10-10 Note WARNING: Keep all magnetic fields away from the electronics module assembly (EMA) during the removal and installation procedure. Accidental deployment of the system can cause injury 25-10-10 Warning WARNING: Do not remove seats from the airplane with the seat belts buckled or the EMA connected. Damage can occur to the system and an accidental deployment of the system can cause injury 25-10-10 Warning WARNING: Do not connect the EMA to the cable interface assembly unless the EMA is mounted to the airplane structure first. Accidental deployment can cause injury 25-10-10 Warning AIR BAG BUCKLE WASHER WASHER BUSHING WASHER BOLT DETAIL D 1210T1001 A1219T1052 DO719T1045 E0519T1090 Inflatable Restraint System Figure 201 (Sheet 1) 25-10-10 Document WASHER BUSHING WASHER WASHER AIR BAG BUCKLE d0 WASHER WASHER BUSHING WASHER BOLT DETAIL F B1219T1052 F0719T1045 G0519T1091 Inflatable Restraint System Figure 201 (Sheet 2) 25-10-10 Document K END-RELEASE CONNECTOR SQUIB FITTING ASSEMBLY C1219T1043 DETAIL H H0519T1093 K0519T1092 Inflatable Restraint System Figure 201 (Sheet 3) 25-10-10 Document DETAIL J 34 BENCH SEAT NUT J0514T1054 Inflatable Restraint System Figure 201 (Sheet 4) 25-10-10 Document (1) Disarm the AMSAFE inflatable restraints. Refer to AMSAFE Inflatable Restraint Disarm/Arm. Disconnect the squib connector from the inflator assembly 25-10-10 Opération (3) Disconnect the gas hose from the inflator assembly 25-10-10 Opération (4) Loosen the clamps on the inflator-assembly mounting bracket 25-10-10 Opération (5) Remove the inflator assembly from the mounting bracket 25-10-10 Opération (6) Put shipping caps on the inflator-hose connector fitting and torque to 5 - 10 inch pounds (0.56 to 1.12 N-m) 25-10-10 Opération (7) Remove the inertia reel (three-point air bag belt) from the airplane. Refer to Chapter 25, Seat Belts/Restraints- Maintenance Practices 25-10-10 Opération (8) Remove the end-release buckle assembly from the airplane. Refer to Chapter 25, Seat Belts/ Restraints - Maintenance Practices 25-10-10 Opération (9) Disconnect the cable interface assembly from the EMA 25-10-10 Opération (a) Push down on the locking clip on the EMA connector and pull on the connector 25-10-10 Opération (10) Remove the cable interface assembly from the airplane 25-10-10 Opération (11) Remove the EMA from the airplane 25-10-10 Opération (a) Remove the nuts, washers, bolts and spacers that attach the EMA to the aircraft structure 25-10-10 Opération (b) Carefully remove the EMA from the airplane 25-10-10 Opération SEAT BELTS/RESTRAINTS - MAINTENANCE 25-11-00 Processus NOTE: The restraint system components are non-repairable field items. If any component in the restraint system is not operating properly, the system must be replaced 25-11-00 Note WARNING: If the airplane has the AMSAFE inflatable restraints, do not do maintenance on the seats or the seat restraint system until you have first looked at and obeyed all the applicable precautions and instructions supplied in the AMSAFE publicatio 25-11-00 Warning A. Pilot's and Copilot's Restraints Removal 25-11-00 Étape NOTE: Seat belt/restraint assembly removal/installinstallation is typical for restraints in all locations 25-11-00 Note NUT ATTACH WASHER PLATE INERTIA REEL ASSEMBLY ANTI-CHAFE BRACKET WASHER PLATE ASSEMBLY BOLT WASHER WASHER BOLT BOLT 1210T1001 A0519T1045 DO719T1008 DETAIL E DETAIL D E0519T1008 F1219T1001 Seat Belts/Restraints Installation Figure 201 (Sheet 1) 25-11-00 Document Seat Belts/Restraints Installation Figure 201 (Sheet 2) 25-11-00 Document Seat Belts/Restraints Installation Figure 201 (Sheet 3) 25-11-00 Document (1) Remove access cover on overhead console to gain access to the restraint inertia reel assemblies 25-11-00 Opération (2) Remove nuts, bolts and washers securing inertia reel assembly to bracket assembly 25-11-00 Opération (3) Remove nuts, washers, bolts and bushing securing restraint assembly to seats 25-11-00 Opération C. Center Seat Restraints Removal 25-11-00 Étape (1) Remove bolts, washers, and bushings securing inertia assembly to bracket 25-11-00 Opération (2) Remove nuts, washers, bolts, and bushings securing restraint assemblies to seats 25-11-00 Opération E. Bench Seat Restraints Removal 25-11-00 Étape (1) Remove bolt and washer securing seat restraint inertia reel to aft cabin structure 25-11-00 Opération (2) Remove bolts, washers, and bushings securing restraint inertia reels to seat frames 25-11-00 Opération CENTER SEATS AND RAILS - MAINTENANCE 25-20-00 Processus NOTE: The removal and installation procedures for the pilot's, copilot's, and center seat component are typical 25-20-00 Note WARNING: If the airplane has the AMSAFE inflatable restraints, do not do maintenance on the seats or seat rails until you have first looked at and obeyed all the applicable precautions and instructions supplied in the AMSAFE publications and this Mai 25-20-00 Warning WARNING: Improperly installed seat stops could allow seat movement during flight maneuvers, resulting in serious injury or death 25-20-00 Warning A. Center Seat Removal 25-20-00 Étape WARNING: If the airplane has the AMSAFE inflatable restraints, do not remove seats with the seat belts buckled or the EMA connected. Damage can occur to the system and an accidental deployment of the system can cause injury 25-20-00 Warning CRANK SEAT HEIGHT LOCK 0 ADJUSTMENT HANDLE SEAT SEAT BELL CRANKS LOCK BASE ASSEMBLY DETAIL A 1210T1001 A0519T1036 Center Seats Installation Figure 201 (Sheet 1) 25-20-00 Document BUSHING 1210T1001 BUSHING A0519T1036 DETAIL D B0519T1037 DETAIL C C0519T1038 D0519T1039 E0511T1001 Center Seats Installation Figure 201 (Sheet 2) 25-20-00 Document (1) Remove restraints prior to seat removal. Refer to Seat Belts/Restraints - Maintenance Practices 25-20-00 Opération 2) Remove seat stops from front and rear of the outboard seat rail 25-20-00 Opération 3) Unlatch seat from seat rail and move seat forward on seat rail until forward roller clears seat rail 25-20-00 Opération (4) Remove seat from airplane 25-20-00 Opération A. Seat Rail Removal 25-20-00 Étape (1) Remove bolts securing seat rails to fuselage 25-20-00 Opération REAR SEAT - MAINTENANCE 25-21-00 Processus WARNING: If the airplane has the AMSAFE inflatable restraints, do not do maintenance on the seats until you have first looked at and obeyed all the applicable precautions and instructions supplied in the AMSAFE publications and this Maintenance Manua 25-21-00 Warning A. Rear Seat Removal 25-21-00 Étape WARNING: If the airplane has the AMSAFE inflatable restraints, do not remove seats with the seat belts buckled or the EMA connected. Damage can occur to the system and an accidental deployment of the system can cause injury 25-21-00 Warning ADJUSTMENT LEVER NUT COTTER PIN WASHER WASHER WASHER PIN BOLT DETAIL B 1210T1001 A1219T1002 BOLT B1219T1002 Aft Bench Seat Installation Figure 201 (Sheet 1) 25-21-00 Document (1) Remove restraints prior to seat removal. Refer to Seat Belts/Restraints - Maintenance Practices. Remove bolts securing seat frame to fuselage 25-21-00 Opération (3) Remove seat from airplane 25-21-00 Opération INTERIOR UPHOLSTERY - MAINTENANCE 25-22-00 Processus CARGO TIE-DOWNS - MAINTENANCE 25-50-00 Processus CARGO PACK - MAINTENANCE 25-51-00 Processus NOTE: The exhaust extension is only installed on T206H airplanes. Refer to Figure 202 25-51-00 Note A. Cargo Pack Removal 25-51-00 Étape NOTE: The exhaust extension is only installed on T206H airplanes. Refer to Figure 202 25-51-00 Note Cargo Pack Main Landing Gear Fairing Screw DETAIL C DETAIL B 1210T1001 A1214T1041 B1214T1042 C1214T1045 Cargo Pack Figure 201 (Sheet 1) 25-51-00 Document (1) Remove the screws, fairing, and rubber seal from around the left and right main landing gear springs 25-51-00 Opération (2) Position a suitable support under the cargo pack 25-51-00 Opération 3) Remove the screws, lock washers, and washers that attach the cargo pack to the aircraft 25-51-00 Opération (4) Remove the cargo pack from the airplane 25-51-00 Opération (5) Do the following if the airplane is going to return to its original (no cargo pack) configuration 25-51-00 Opération (a) Remove the screws that attach the exhaust extension to the exhaust stack 25-51-00 Opération (b) Remove the exhaust extension from the airplane 25-51-00 Opération (c) Install original the left and right main landing gear fairings. Refer to Chapter 32, Main Landing Gear - Maintenance Practices 25-51-00 Opération POINTER EMERGENCY LOCATOR TRANSMITTER - MAINTENANCE 25-60-00 Processus NOTE: ON AIRPLANES THAT HAVE THE GARMIN G1000 AVIONICS, THE REMOTE MOUNTED SWITCH IS FOUND NEXT TO THE MULTI-FUNCTION DISPLAY (MFD) 25-60-00 Note NOTE: When the new battery pack expiration date is put in the airplane records, it is also recommended that you record the expiration date in the ELT owner's manual for quick reference 25-60-00 Note NOTE: The airplane's VHF receiver or ADF will not correctly do a check of the power of the ELT audio signal 25-60-00 Note CAUTION: Make sure that the direction-of-ilight arrow on the ELT points to the nose of the airplane 25-60-00 Caution CAUTION: Make sure that the ELT master switch is in the OFFIRESET position. ELT internal fuse failure can occur if the ELT remote connector is installed with the ELT master switch in the ON or AUTO position 25-60-00 Caution CAUTION: Make sure that the ELT master switch is in the OFFIRESET position. An ELT internal fuse failure can occur if you install the ELT remote connector with the ELT master switch in the ON or AUTO position 25-60-00 Caution CAUTION: Use only the recommended battery pack for the ELT, or the operating life and/or signal strength of the ELT will decrease. The incorrect battery pack can also change the mechanical configuration and cause it to make too much vibration as well 25-60-00 Caution CAUTION: Do not tighten the ELT gasket and screws too much 25-60-00 Caution CAUTION: Operate the Emergency Locator Transmitter (ELT) system only during the first five minutes of each hour. Refer to the FAA Advisory Circular AC-91-44A 25-60-00 Caution CAUTION: Do not operate the ELT system for more than three pulses of the audio signal. Longer operation can decrease the ELT battery power supply 25-60-00 Caution CAUTION: Operate the Emergency Locator Transmitter (ELT) system only during the first five minutes of each hour. Refer to the FAA Advisory Circular AC-91-44A 25-60-00 Caution CAUTION: Do not operate the ELT system for more than three pulses of the audio signal. Longer operation can decrease the ELT battery power supply 25-60-00 Caution A. ELT Removal 25-60-00 Étape CAUTION: Do not disconnect the ELT remote connector before you put the ELT master switch in the OFFIRESET (center) position. ELT internal fuse failure can occur if the ELT remote connector is disconnected before the ELT master switch is put in the OF 25-60-00 Caution T20608361 AND T20608370 AND ON 1210T1001 A1218T1021 Pointer Emergency Locator Transmitter Installation Figure 201 (Sheet 1) 25-60-00 Document Pointer Emergency Locator Transmitter Installation Figure 201 (Sheet 2) 25-60-00 Document Pointer Emergency Locator Transmitter Installation Figure 201 (Sheet 3) 25-60-00 Document (1) Put a support stand under the tail tie-down ring to support the tailcone. Refer to Chapter 7, Jacking - Maintenance Practices 25-60-00 Opération (2) Remove the rear seat. Refer to Rear Seat - Maintenance Practices 25-60-00 Opération (3) Remove thel baggage curtain to get access to the ELT. Refer to Interior Upholstery - Maintenance Practices 25-60-00 Opération (4) Remove the bolts, tiedowns, and plastic closeout from the lower baggage area (Zone 240). Refer to Airplane Zoning - Description and Operation 25-60-00 Opération (5) Put the ELT master switch in the OFF/RESET (center) position 25-60-00 Opération (6) Disconnect the ELT antenna coaxial cable from the ELT 25-60-00 Opération (7) Disconnect the ELT remote connector from the ELT 25-60-00 Opération (8) Disengage the attach strap from around the ELT and remove the ELT from the airplane 25-60-00 Opération A. ELT Remote Switch Removal 25-60-00 Étape CAUTION: Do not disconnect the ELT remote connector before you put the ELT master switch in the OFFIRESET (center) position. An ELT internal fuse failure can occur if you disconnect the ELT remote connector before you 25-60-00 Caution CAUTION: Disconnect the ELT remote connector from the ELT before you remove the ELT remote switch or disconnect the ELT remote switch connector. An ELT internal fuse failure can occur if the ELT remote switch or disconnect is removed before the ELT r 25-60-00 Caution (1) Put the airplane master switch (ALT/BAT) in the OFF position 25-60-00 Opération (2) Remove the bolts, tiedowns, and plastic closeout from the lower baggage area (Zone 240). Refer to Airplane Zoning - Description and Operation 25-60-00 Opération (3) Put the ELT master switch in OFFIRESET (center) position 25-60-00 Opération (4) Disconnect the ELT remote connector from the ELT 25-60-00 Opération (5) Get access to backside of remote mounted switch. Compress the locking tabs on each side of the switch and, at the same time, pull the switch aft and away from the instrument panel 25-60-00 Opération (6) Disconnect electrical connector from switch 25-60-00 Opération A. ELT Antenna Removal 25-60-00 Étape NOTE: The ELT antenna has an integral base and a coaxial cable 25-60-00 Note (1) Put a support stand under the tail tie-down ring SO that the tailcone does not fall while the person is inside. Refer to Chapter 7, Jacking - Maintenance Practices 25-60-00 Opération (2) Remove the rear seat. Refer to Rear Seat - Maintenance Practices 25-60-00 Opération (3) Remove thel baggage curtain to get access to the ELT. Refer to Interior Upholstery - Maintenance Practices 25-60-00 Opération (4) Remove the bolts, tiedowns, and plastic closeout from the lower baggage area (Zone 240). Refer to Airplane Zoning - Description and Operation 25-60-00 Opération (5) Disconnect the ELT antenna coaxial cable from the ELT 25-60-00 Opération (6) Remove all of the tie straps that attach the ELT antenna coaxial cable to the fuselage 25-60-00 Opération (7) On the external skin of the airplane, remove the six internal locking screws that attach the ELT antenna to the fuselage 25-60-00 Opération (8) Remove the ELT antenna from the inside of the airplane 25-60-00 Opération A. ELT Whip Antenna Removal 25-60-00 Étape (1) Put a support stand under the tail tie-down ring SO that the tailcone does not fall while the person is inside. Refer to Chapter 7, Jacking - Maintenance Practices 25-60-00 Opération (2 Remove the rear seat. Refer to Rear Seat - Maintenance Practices 25-60-00 Opération 0 Remove thel baggage curtain to get access to thel ELT. Refer to Interior Upholstery. - Maintenance Practices 25-60-00 Opération (4) Remove the bolts, tiedowns, and plastic closeout from the lower baggage area (Zone 240). Refer to Airplane Zoning - Description and Operation 25-60-00 Opération (5) Disconnect the ELT whip antenna coaxial cable from the ELT whip antenna 25-60-00 Opération (6) From inside the airplane, remove the nut and washer that attach the ELT whip antenna to the fuselage 25-60-00 Opération (7) Remove the ELT whip antenna from the external skin of the airplane 25-60-00 Opération A. ELT Battery Pack Removal 25-60-00 Étape WARNING: Obey the correct procedures to discard the unserviceable ELT battery pack to prevent damage to the environment or personal injury 25-60-00 Warning 1 Remove the ELT from the airplane. Refer to ELT Removal/Installation. Remove the screws that attach the base plate to the ELT 25-60-00 Opération 3) Disconnect the ELT battery pack and the electrical connectors 25-60-00 Opération (4) Remove the ELT battery pack from the ELT 25-60-00 Opération ARTEX C406-N EMERGENCY LOCATOR TRANSMITTER SYSTEM - MAINTENANCE 25-60-01 Processus NOTE: The maximum allowable resistance (in ohms) at each of the four measured positions is 0.0025 25-60-01 Note NOTE: The SARSAT tester is used as an example to gather test information. However, other equivalent test equipment such as the Aeroflex IFR 4000 Communications Test Set is acceptable 25-60-01 Note NOTE: The ELT will not activate with the G-switch unless electrical pins 12 and 13 have a jumper wire installed between them (this happens automatically when the ELT is locked into the mount tray with the electrical connector in position). Because of 25-60-01 Note CAUTION: Make sure that the direction-of-flight arrow on the ELT points to the nose of the airplane 25-60-01 Caution CAUTION: Operate the emergency locator transmitter (ELT) system only during the first five minutes of each hour. If you must complete the functional test at a time other than the first five minutes of the hour, you must do the test with a direct conn 25-60-01 Caution CAUTION: Do not operate the emergency locator transmitter (ELT) for more than five seconds at a time. Do not operate the ELT again for 15 seconds. The ELT will transmit a 406.028 MHz signal after the ELT is active for approximately 50 seconds. This s 25-60-01 Caution CAUTION: Operate the Emergency Locator Transmitter system only during the first five minutes of each hour. If you must complete the functional test at a time otherthan the first five minutes of the hour, you must do the test with a direct connection 25-60-01 Caution CAUTION: Do not operate the emergency locator transmitter for more than five seconds at a time. Do not operate the ELT again for 15 seconds. The ELT will transmit a 406.028 MHz signal after the ELT is active for approximately 50 seconds. This signal 25-60-01 Caution CAUTION: Operate the emergency locator transmitter (ELT) system only during the first five minutes of each hour. If you must complete the functional test at a time other than the first five minutes of the hour, you must do the test with a direct conn 25-60-02 Caution CAUTION: Do not operate the emergency locator transmitter (ELT) for more than five seconds at a time. Do not operate the ELT again for 15 seconds. The ELT will transmit a 406.028 MHz signal after the ELT is active for approximately 50 seconds. This s 25-60-02 Caution CAUTION: Operate the Emergency Locator Transmitter system only during the first five minutes of each hour. If you must complete the functional test at a time other than the first five minutes of the nour, you must do the test with a direct connection 25-60-02 Caution CAUTION: Do not operate the emergency locator transmitter for more than five seconds at a time. Do not operate the ELT again for 15 seconds. The ELT will transmit a 406.028 MHz signal after the ELT is active for approximately 50 seconds. This signal 25-60-02 Caution A. ELT Removal 25-60-01 Étape BUZZER CONNECTOR AD CABLE ELT COVER SWITCH MOUNTING TRAY ELECTRICAL CONNECTOR END CAP DETAIL A A1218T1088 1210T1001 Artex C406-N ELT Installation Figure 201 (Sheet 1) 25-60-01 Document Artex C406-N ELT Installation Figure 201 (Sheet 2) 25-60-01 Document (1) Put a support stand under the tail tie-down ring to support the tailcone. Refer to Chapter 7, Jacking - Maintenance Practices 25-60-01 Opération 2) Remove the rear: seat. Refer to Rear Seat - Maintenance Practices 25-60-01 Opération (3) Remove thel baggage curtain to get access to the ELT. Refer to Interior Upholstery - Maintenance Practices 25-60-01 Opération (4) Remove the bolts, tiedowns, and plastic closeout from the lower baggage area (Zone 240). Refer to Airplane Zoning - Description and Operation 25-60-01 Opération (5) Put the ELT master switch in the OFF position 25-60-01 Opération (6) Disconnect the electrical connector (PT905) and the coaxial connector (PT1029) from the ELT 25-60-01 Opération (7) Loosen the knurl nuts on the end cap of the transmitter and the mounting tray 25-60-01 Opération (8) Pull the front cover away from the transmitter and the mounting tray 25-60-01 Opération (9) Carefully pull the mounting tray end and the tray away from the ELT 25-60-01 Opération (10) Remove the ELT from the mounting tray 25-60-01 Opération (11) Remove the screws that attach the mounting tray to the shelf assembly 25-60-01 Opération A. ELT Remote Switch Removal 25-60-01 Étape (1) Put the airplane master switch (ALT/BAT) in the OFF position 25-60-01 Opération 2) Get access to the ELT 25-60-01 Opération 3) Put the ELT master switch in the OFF position 25-60-01 Opération 4) Disconnect the electrical connector (PT905) from the ELT 25-60-01 Opération (5) Get access to the back of the ELT remote switch (Zone 221) 25-60-01 Opération 6) Disconnect the ELT remote switch connector 25-60-01 Opération (7) Remove the screws that attach the ELT remote switch to the instrument panel 25-60-01 Opération (8) Remove the ELT remote switch from the airplane 25-60-01 Opération A. ELT Antenna Removal 25-60-01 Étape (1) Put a support stand under the tail tie-down ring to support the tailcone. Refer to Chapter 7, Jacking - Maintenance Practices. Remove the rear seat. Refer to Rear Seat - Maintenance Practices 25-60-01 Opération (3) Remove thel baggage curtain to get accessi to thel ELT. Refer to Interior Upholstery - Maintenance Practices 25-60-01 Opération (4) Remove the bolts, tiedowns, and plastic closeout from the lower baggage area (Zone 240). Refer to Airplane Zoning - Description and Operation 25-60-01 Opération (5) Disconnect the coaxial cable connector (PT1030) for the ELT antenna from the ELT 25-60-01 Opération (6) Remove the tie strap that attaches the ELT antenna coaxial cable to the fuselage 25-60-01 Opération (1) Remove the four screws that attach the ELT antenna to the fuselage 25-60-01 Opération (8) Remove the ELT antenna from the airplane 25-60-01 Opération A. Buzzer Removal 25-60-01 Étape (1) Put a support stand under the tail tie-down ring to support the tailcone. Refer to Chapter 7, Jacking - Maintenance Practices 25-60-01 Opération (2) Remove the rear seat. Refer to Rear Seat - Maintenance Practices 25-60-01 Opération (3) Remove thel baggage curtain to get access to the ELT. Refer to Interior Upholstery - Maintenance Practices 25-60-01 Opération (4) Remove the bolts, tiedowns, and plastic closeout from the lower baggage area (Zone 240). Refer to Airplane Zoning - Description and Operation 25-60-01 Opération (5) Make sure that the ELT switch on the ELT transmitter is in the OFF position 25-60-01 Opération (6) Tag the wires and terminals for identification 25-60-01 Opération 7) Remove the screws that attach the electrical terminals to the buzzer 25-60-01 Opération (8) Loosen the black retainer ring on the outboard side of the buzzer 25-60-01 Opération (9) Remove the buzzer from the bracket 25-60-01 Opération ARTEX ME406 EMERGENCY LOCATOR TRANSMITTER SYSTEM - MAINTENANCE 25-60-02 Processus NOTE: The ELT is off when the electrical connector is removed from the ELT 25-60-02 Note NOTE: The maximum allowable resistance (in ohms) at each of the four measured positions is 0.0025 25-60-02 Note NOTE: The battery manufacturer puts a mark on the battery to show the battery life limit. When you install a new battery in an ELT, make sure a record of the expiration date is put in the space given on the ELT name and data plate 25-60-02 Note NOTE: If possible, do the test procedure for the emergency locator transmitter inside a metal hangar with the doors closed to decrease the signal transmission from the ELT unit during the test 25-60-02 Note NOTE: The ELT will not activate with the G-switch unless electrical pins 5 and 12 have a jumper wire installed between them (this happens automatically when the ELT is locked into the mount tray with the electrical connector in position) 25-60-02 Note NOTE: The SARSAT tester is used as an example to gather test information. However, other equivalent test equipment such as the Aeroflex IFR 4000 Communications Test Set is acceptable 25-60-02 Note NOTE: The SARSAT tester must be less than 15 feet from the ELT antenna and must have a line-of-sight between the ELT antenna and SARSAT tester 25-60-02 Note NOTE: The person with the SARSAT tester must make sure that the ELT buzzer is heard during the test 25-60-02 Note NOTE: If it is necessary to do the transmitter test after the first five minutes of the hour, the SARSAT tester is connected directly to the ELT with a coaxial cable and a 30 dB attenuator. You will not hear the sweep tone from the ELT on the airplan 25-60-02 Note NOTE: This will take one second. The ELT remote switch will start to flash 25-60-02 Note NOTE: The ELT will do a self-test. The LED will stay on for one second and the ELT sweeps are not audible on the airplane speakers if the ELT operation is normal 25-60-02 Note NOTE: The ELT does not transmit a 406.028 MHz test signal to the SARSAT tester until the ELT remote switch is set back to the ARM position 25-60-02 Note NOTE: The information that follows must match the data on the ELT placard: COUNTRY code 15-digit Hex code ID 25-60-02 Note NOTE: When ownership of an aircraft is transferred within the same country, the ME406 ELT should be reregistered with the applicable authority. When an aircraft with a ME406 ELT changes tail number or country registration, the ELT will need to have t 25-60-02 Note CAUTION: Although the ELT is off with the electrical connector removed, the ELT can be activated if the switch on the front is moved to the ON position. Be careful not to move the switch to the ON position 25-60-02 Caution CAUTION: Do not use solvents to clean the ELT, mounting tray, or electrical contacts. Solvents used in these areas can cause damage to the ELT housing 25-60-02 Caution CAUTION: Operate the Emergency Locator Transmitter (ELT) system only during the first five minutes of each hour. If you must complete the functional test at a time other than the first five minutes of the hour, you must do the test with a direct conn 25-60-02 Caution CAUTION: Do not operate the Emergency Locator Transmitter (ELT) for more than five seconds at a time. Do not operate the ELT again for 15 seconds. The ELT will transmit a 406.028 MHz distress signal after it is activated for approximately 50 seconds 25-60-02 Caution CAUTION: Itis recommended that an experienced technician do this procedure because of the potential physical damage that can occur if the jumper wire is not installed correctly 25-60-02 Caution A. Remove the Emergency Locator Transmitter (ELT) 25-60-02 Étape NOTE: The ELT is off when the electrical connector is removed from the ELT 25-60-02 Note CAUTION: Although the ELT is off with the electrical connector removed, the ELT can be activated if the switch on the front is moved to the ON position. Be careful not to move the switch to the ON position 25-60-02 Caution Artex ME406 Emergency Locator Transmitter System Installation Figure 201 (Sheet 1) 25-60-02 Document Artex ME406 Emergency Locator Transmitter System Installation Figure 201 (Sheet 2) 25-60-02 Document (1) Make sure the MASTER switch is in the OFF position 25-60-02 Opération (2) Get access to the ELT 25-60-02 Opération (a) Put a support stand under the tail tie-down ring to support the tailcone. Refer to Chapter 7, Jacking - Maintenance Practices 25-60-02 Opération (b) Remove the rear seat. Refer to Rear Seat - Maintenance Practices 25-60-02 Opération (c) Remove the baggage curtain to get access to the ELT. Refer to Interior Upholstery Maintenance Practices 25-60-02 Opération (3) Make sure the ON/ARM switch on the ELT in the ARM position 25-60-02 Opération (4) Disconnect the BNC connector (PT1029) and the electrical connector (PT907) from the ELT 25-60-02 Opération (5) Open the metal strap that holds the ELT to the mounting tray 25-60-02 Opération (6) Remove the ELT from the airplane 25-60-02 Opération A. Remove the ELT Buzzer 25-60-02 Étape (1) Get access to the ELT 25-60-02 Opération (a) Put a support stand under the tail tie-down ring to support the tailcone. Refer to Chapter 7, Jacking - Maintenance Practices 25-60-02 Opération (b) Remove the rear seat. Refer to Rear Seat - Maintenance Practices 25-60-02 Opération (c) Remove the baggage curtain to get access to the ELT. Refer to Interior Upholstery - Maintenance Practices 25-60-02 Opération Make sure that the ELT master switch on the ELT transmitter is in the ARM position 25-60-02 Opération 3) Tag the wires and terminals for identification 25-60-02 Opération (4) Remove the screws that attach the electrical terminals to the buzzer 25-60-02 Opération (5) Loosen the black retainer ring on the outboard side of the buzzer 25-60-02 Opération (6) Remove the buzzer from the bracket 25-60-02 Opération A. Remove the Remote Switch 25-60-02 Étape (1) Remove electrical power from the aircraft 25-60-02 Opération (2) Get access to the ELT 25-60-02 Opération (a) Put a support stand under the tail tie-down ring to support the tailcone. Refer to Chapter 7, Jacking - Maintenance Practices 25-60-02 Opération (b) Remove the rear seat. Refer to Rear Seat - Maintenance Practices 25-60-02 Opération (C) Remove the baggage curtain to get access to the ELT. Refer to Interior Upholstery - Maintenance Practices 25-60-02 Opération (3) Disconnect the electrical connector (PT907) from the ELT 25-60-02 Opération (4) Remove the screws from the front of the switch 25-60-02 Opération (5) Pull the remote switch from the panel to get to the electrical connector 25-60-02 Opération (a) Disconnect the connector from the back of the switch 25-60-02 Opération A. Remove the ELT Antenna 25-60-02 Étape (1) Remove the screws that attach the antenna to the fuselage. Pull the antenna upward from fuselage and disconnect the BNC connector (PT1030) from antenna 25-60-02 Opération (3) Remove the antenna from the airplane 25-60-02 Opération (4) Remove sealant from antenna and airplane 25-60-02 Opération CARBON MONOXIDE DETECTOR - MAINTENANCE 25-60-10 Processus A. Carbon Monoxide Detector Removal 25-60-10 Étape Carbon Monoxide Detector Installation Figure 201 (Sheet 1) 25-60-10 Document (1) Put the AVIONICS MASTER switch in the off position 25-60-10 Opération (2) Remove the MFD from the copilot side of the instrument panel. Refer to Chapter 34, Control Display Unit - Maintenance Practices 25-60-10 Opération (3) Disconnect the electrical connector (P1903) from the CO detector 25-60-10 Opération (4) Remove and keep the screws and washers that connect the CO detector to the avionics support structure 25-60-10 Opération (5) Remove the CO detector from the airplane 25-60-10 Opération SOUNDPROOFING AND INSULATION - MAINTENANCE 25-80-00 Processus NOTE: Equivalent substitutes may be used for the following items 27-00-00 Note AILERON CONTROL SYSTEM - MAINTENANCE 27-10-00 Processus NOTE: If control tube assembly was not removed, proceed to step (2) 27-10-00 Note NOTE: Allow 0.030" minimum clearance between bearing block and nut after tightening 27-10-00 Note NOTE: Refer to Cessna Service Bulletin SEB-27-01, or latest revision for additional information concerning the location and method to install the safety wire that secures the attach screw to the glide plug and control tube assembly 27-10-00 Note NOTE: Do not leave the screw loose when adjusting drag. This adjustment is similar to a typical wheel bearing adjustment, for example, tighten until all freeplay is removed and drag can be detected. Gradually back off (loosen) the adjustment screw in 27-10-00 Note NOTE: Each bearing assembly has an 0.062" eccentric adjustment when installed, for aligning the control tube weld assembly and push-pull tube with the guide assembly 27-10-00 Note NOTE: Prior to rigging the aileron system remove stop bolts. Clean the bolt(s) and the threads of the boss(es) per Loctite Manufacturer's instructions 27-10-00 Note NOTE: Pushrod is adjustable at the aileron end only 27-10-00 Note NOTE: Apply LOCTITE GRADE "C", Loctite #290 to threads and reinstall in bellcrank, or Loctite #242 may be applied by capillary action after bolt is adjusted 27-10-00 Note WARNING: Make sure ailerons move in the correct direction when operated by the control wheel 27-10-00 Warning CAUTION: Maintain specified control tension 27-10-00 Caution A. Remove Control Wheel 27-10-00 Étape NOTE: Pilot and copilot control wheel removal/installinstallation is typical 27-10-00 Note DETAIL J TURNBUCKLE E DIRECT CABLE H C B CABLE GUARD PULLEY DIRECT CABLE TURNBUCKLE G K K F DETAIL A CABLE CABLE GUARD GUARD PULLEY. PULLEY PULLEY CABLE PULLEY CABLE GUARD 1210T1001 GUARD DETAIL E A12631006 B07631015 DETAIL H C12631005 CABLE DETAIL G 27-10-00 Document NOTE: ALLOW 0.030" NUT BEARING BLOCK MIMIMUM CLEARANCE BETWEEN BEARING BLOCK DETAIL K K12601005 AND NUT AFTER TIGHTENING. AA12631007 Aileron Control System Installation Figure 201 (Sheet 2) 27-10-00 Document CABLE NOTE: PUSHROD IS ADJUSTABLE AT THE AILERON END ONLY. PRIOR TO RIGGING THE AILERON CABLE LOCK SYSTEM, REMOVE STOP BOLTS. BELLCRANK CLEAN THE BOLTS(S) AND THE THREADS OF THE BOSS(ES) PER ASSEMBLY LOCTITE MANUFACTURER'S INSTRUCTIONS. BEARING APPLY 27-10-00 Document DETAIL N L07601001 M12631009 Aileron Control System Installation Figure 201 (Sheet 4) 27-10-00 Document (1) Disconnect electrical connector P1 from control wheel 27-10-00 Opération L Remove screws and washers securing control wheel to control tube 27-10-00 Opération (3) Remove control wheel 27-10-00 Opération A. Remove Control Column 27-10-00 Étape NOTE: Refer to Cessna Service Bulletin SEB-27-01, or latest revision, for additional information concerning the location of the safety wire that secures the attach screw to the glide plug and control tube assembly 27-10-00 Note NOTE: To ease removal of control wheel tube assembly, snap ring may be removed from its locking groove to allow sleeve assembly additional movement 27-10-00 Note NOTE: USE WASHERS AS REQUIRED CONTROL TUBE Il TO ADJUST FREE PLAY. ASSEMBLY DO NOT EXCEED 4 WASHERS PER ASSEMBLY 27-10-00 Note NOTE: If removal of control tube assembly is necessary, proceed to step (6) 27-10-00 Note (1) Remove control wheel 27-10-00 Opération (2) For airplane serial numbers 20608336 and On and airplanes T20609038 and On. Airplane serial numbers 20608001 thru 20608335 and T20608001 thru T20609037 that are in compliance with Cessna Service Bulletin SEB-27-01, or latest revision 27-10-00 Opération (a) Remove and discard the safety wire from the screw that attaches the glide plug 27-10-00 Opération (3) Remove the screw that attaches the glide plug to the control tube assembly 27-10-00 Opération (a) Remove the plug and glide assembly 27-10-00 Opération (4) Disconnect push-pull tube at sleeve assembly 27-10-00 Opération (5) Remove screws securing column support bracket assembly at instrument panel 27-10-00 Opération (6) Using care, pull control wheel tube assembly aft and work assembly out through instrument panel 27-10-00 Opération (7) Remove column support bracket assembly, remove safety clips and relieve direct cable tension at turnbuckles. Refer to Chapter 6, Access/Inspection Plates - Description and Operation 27-10-00 Opération (8) Remove safety wire and relieve interconnect cable tension at turnbuckle 27-10-00 Opération (9) Remove safety wire and remove roll pin through quadrant and control tube assembly 27-10-00 Opération (10) Remove cotter pin, nut and washerf from control tube assembly from bearing block on thei forward side of the firewall 27-10-00 Opération (11) Using care, pull control tube assembly aft and remove quadrant 27-10-00 Opération A. Remove Aileron 27-10-00 Étape (1) Disconnect aileron pushrod at aileron 27-10-00 Opération 2) Disconnect electrical bonding straps 27-10-00 Opération (3) Remove screws and nuts attaching aileron hinges to trailing edge of wing 27-10-00 Opération (4) Using care, pull aileron out and down to slide hinges from under wing skin and auxiliary spar reinforcements 27-10-00 Opération A. Remove Aileron Bellcrank 27-10-00 Étape NOTE: Left and right aileron bellcrank removal/installation is typical 27-10-00 Note NOTE: Brass washers may be used as shims between lower end of bellcrank and lower bracket. Retain these shims. Tape open ends of bellcrank to prevent dust and dirt from entering bellcrank needle bearings 27-10-00 Note (1) Remove access plates (520AB, 520BB, 620AB, and 620BB) inboard of bellcrank on underside of each wing. Refer to Chapter 6, Access/Inspection Plates - Description and Operation 27-10-00 Opération (2) Remove safety clip from carry through cable turnbuckle and relieve control cable tension by loosening turnbuckle 27-10-00 Opération (3) Disconnect control cables from bellcrank 27-10-00 Opération (4) Remove safety clip from direct cable turnbuckle and relieve control cable tension by loosening turnbuckle 27-10-00 Opération (5) Disconnect control cables from bellcrank 27-10-00 Opération (6) Disconnect aileron pushrod at bellcrank 27-10-00 Opération 7) Remove nuts, washers and bolts securing bellcrank to wing structure 27-10-00 Opération (8) Remove bellcrank through access opening, using care that bearing bushing is not dropped from bellcrank 27-10-00 Opération RUDDER CONTROL SYSTEM - MAINTENANCE 27-20-00 Processus NOTE: Do not overtighten. Shackle must pivot freely 27-20-00 Note NOTE: Figure 202 may be used as a guide to attain correct rudder travel 27-20-00 Note NOTE: ALLOW AIRPLANE TEMPERATURE TO STABILIZED FOR. A PERIOD OF FOUR (4) HOURS BEFORE CHECKING CABLE TENSION 27-20-00 Note WARNING: Make sure that the rudder moves in the correct direction when operated by the rudder pedals 27-20-00 Warning CAUTION: Maintain specified control tension 27-20-00 Caution A. Remove Rudder Pedal Assembly 27-20-00 Étape NOTE: The two inboard bearing blocks contain clearance holes for the rudder bars at one end and a bearing hole at the other. Tag these bearing blocks for reference on reinstallation 27-20-00 Note DETAIL G H12331014 J12331002 Rudder Control System Installation Figure 201 (Sheet 1) 27-20-00 Document DETAIL N K12331019 M12331018 N12331020 Rudder Control System Installation Figure 201 (Sheet 2) 27-20-00 Document Rudder Control System Installation Figure 201 (Sheet 3) 27-20-00 Document (1) Remove pilot's and copilot's seats. Refer to Chapter 25, Front Seats - Maintenance Practices 27-20-00 Opération (2) Remove carpet and shield assemblies. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 27-20-00 Opération (3) Disconnect master cylinders and parking brake cables at pilot rudder pedals 27-20-00 Opération (4) Remove rudder pedals and brake links 27-20-00 Opération (5) Remove fairings (340AL and 340AR) for access to rudder cable turnbuckles. Refer to Chapter 6, Access/Inspection Plates - Description and Operation 27-20-00 Opération (6) Remove safety clips from turnbuckles and relieve cable tension 27-20-00 Opération ) Disconnect right forward and left forward cables from rudder bar arms 27-20-00 Opération (8) Disconnect nose gear steering bungee from rudder bar arm. The bungee serves for both rudder trim and nosewheel steering 27-20-00 Opération (9) Disconnect the whiffletree link rod assemblies at arms 27-20-00 Opération (10) Remove bolts securing bearing blocks and work rudder bars out of tunnel area 27-20-00 Opération A. Remove Rudder 27-20-00 Étape (1) Remove stinger 27-20-00 Opération (2) Disconnect tail navigation light quick-disconnect JV001 at bottom of rudder 27-20-00 Opération (3) Remove fairing from either side of vertical fin, remove safety wire and relieve cable tension by loosening turnbuckles 27-20-00 Opération (4) Disconnect cables from rudder bell crank 27-20-00 Opération (5) With rudder supported, remove hinge bolts (including electrical bonding strap) and, using care, lift rudder free of vertical fin 27-20-00 Opération A. Remove Rudder Cables 27-20-00 Étape NOTE: To ease routing of cables, a length of wire may be attached to the end of the cable before being withdrawn from airplane. Leave wire in place, routed through structure; then attach cable being installed and pull the cable into position 27-20-00 Note (1) Remove pilot's and copilot's seats. Refer to Chapter 25, Front Seats and Rails - Maintenance Practices 27-20-00 Opération L/ Remove center seats. Refer to Chapter 25, Center Seats and Rails - Maintenance Practices 27-20-00 Opération (3) Remove rear seat. Refer to Chapter 25, Rear Seat - Maintenance Practices 27-20-00 Opération (4) Remove shield assemblies, carpet and baggage wall. Refer to Chapter 25, Interior Upholstery Maintenance Practices 27-20-00 Opération (5) Remove plates (231AB, 231BB, 231DB, 231EB, 231HB, 231JB, and310AR ). Refer to Chapter 6, Access/Inspection Plates - Description and Operation 27-20-00 Opération (6) Remove fairings (340AL and 340AR). Refer to Chapter 6, Access/Inspection Plates - Description and Operation 27-20-00 Opération (7) Remove safety clips from turnbuckles and relieve tension on rudder cables 27-20-00 Opération (8) Disconnect left and right rudder cables from rudder bell crank 27-20-00 Opération (9) Disconnect left and right rudder cables from rudder bar arms 27-20-00 Opération (10) Remove pulleys and cable guards as necessary to remove cables 27-20-00 Opération (11) Remove rudder cables 27-20-00 Opération RUDDER TRIM CONTROL - MAINTENANCE 27-21-00 Processus NOTE: Rudder control system must be rigged prior to rigging rudder trim system 27-21-00 Note WARNING: Ensure rudder moves in the correct direction when operated by the rudder trim control wheel 27-21-00 Warning A. Remove Rudder Trim System 27-21-00 Étape Figure 201 (Sheet 1) 27-21-00 Document (1) Remove pilot's and copilot's seats. Refer to Chapter 25, Front Seats and Rails - Maintenance Practices 27-21-00 Opération (2) Remove pedestal cover, carpet and shield assemblies. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 27-21-00 Opération (3) Loosen bolt securing idler sprocket and relieve tension on chain 27-21-00 Opération (4) Disconnect steering bungee from rudder bar arm 27-21-00 Opération (5) Remove chain guard from steering bungee sprocket 27-21-00 Opération (6) Remove chain from steering bungee sprocket and forward trim shaft sprocket 27-21-00 Opération ) Remove clamp from nose gear steering bungee 27-21-00 Opération (8) Remove nose gear for access to steering bungee. Refer to Chapter 32, Nose Landing Gear - Maintenance Practices 27-21-00 Opération ELEVATOR CONTROL SYSTEM - MAINTENANCE 27-30-00 Processus NOTE: Set right hand elevator maintaining 0.18 inch dimension specified in Figure 202 27-30-00 Note NOTE: Set right hand elevator maintaining 0.18-inch dimension specified in Figure 202 27-30-00 Note NOTE: Do not attempt to align the elevator trailing edges as there is a 0 degree 54' twist designed into the connecting torque tube. This twist causes the right elevator to be higher than the left 27-30-00 Note NOTE: Disregard counterweight areas of the elevator when streamlining. These areas are contoured to be streamlined at cruising speed (elevators approximately 3 degrees down) 27-30-00 Note NOTE: The elevators must be supported to obtain correct cable tension 27-30-00 Note NOTE: The holes in the bell crank stops are off center to give elevator travel adjustment 27-30-00 Note NOTE: The bell crank stops can be turned in 90-degree increments to give approximately 1 degree of elevator travel 27-30-00 Note NOTE: DO NOT. ATTEMPT TO ALIGN THE ELEVATOR TRAILING EDGES AS THERE IS A054' TWIST DESIGNED INTO THE CONNECTING TORQUE TUBE. THIS TWIST CAUSES THE RIGHT ELEVATOR TO BE HIGHER THAN THE LEFT 27-30-00 Note NOTE: DISREGARD COUNTERWEIGHT AREAS OF THE ELEVATOR WHEN STREAMLINING. THESE AREAS ARE CONTOURED TO BE STREAMLINED AT CRUISING SPEED (ELEVATORS APPROXIMATELY 3° DOWN) 27-30-00 Note NOTE: ALLOW AIRPLANE TEMPERATURE TO STABILIZED FOR. A PERIOD OF FOUR (4) HOURS BEFORE CHECKING CABLE TENSION 27-30-00 Note 300 27-30-00 Note WARNING: Ensure elevators travel in the proper direction when operated by the control column 27-30-00 Warning WARNING: Ensure that elevators travel in the proper direction when operated by the control column 27-30-00 Warning CAUTION: Position a support stand under tail tie-down to prevent the tailcone from dropping while working inside 27-30-00 Caution CAUTION: Maintain specified control cable tension 27-30-00 Caution A. Remove Elevator 27-30-00 Étape NOTE: If removing left elevator, omit this step 27-30-00 Note NOTE: If trim system is not moved and actuator screw is not turned, re-rigging of trim system should not be necessary after reinstallation of elevator 27-30-00 Note NOTE: Bolts are installed using EA9309-25GR adhesive. It may be necessary to apply heat in the area of the bolt shank to soften the epoxy prior to removing bolts 27-30-00 Note Figure 201 (Sheet 1) 27-30-00 Document Figure 201 (Sheet 2) 27-30-00 Document (1) Remove Stinger 27-30-00 Opération (2) Disconnect trim tab push-pull tube at tab actuator 27-30-00 Opération (3) Remove bolts securing elevator torque tubes to arm assembly 27-30-00 Opération (4) Remove bolts from elevator hinges and electrical bonding straps 27-30-00 Opération (5) Using care, remove elevator 27-30-00 Opération A. Remove Cables and Pulleys 27-30-00 Étape NOTE: To ease routing of cables, a length of wire may be attached to the end of the cable before being withdrawn from airplane. Leave wire in place, routed through structure, then attach cable being installed and pull the cable into position 27-30-00 Note CAUTION: Position a support stand under tail tiedown ring to prevent the tailcone from dropping while working inside 27-30-00 Caution (1) Remove pilot's and copilot's seats. Refer to Chapter 25, Front Seats and Rails - Maintenance Practices 27-30-00 Opération (2) Remove Center seats. Refer to Chapter 25. Center Seats and Rails - Maintenance Practices 27-30-00 Opération (3) Remove rear seat. Refer to Chapter 25, Rear Seat - Maintenance Practices 27-30-00 Opération (4) Remove carpet. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 27-30-00 Opération (5) Remove access plates (310BB, 230EB, 230HB, 231CB, 231FB, 231JB, 231MB and 310AB) Refer to Chapter 6, Access/Inspection Plates - Description and Operation 27-30-00 Opération (6) Remove safety clips/safety wire to relieve cable tension at turnbuckles and disconnect cables from cable links 27-30-00 Opération (7) Disconnect cables from torque tube at control arm assemblies, left and right 27-30-00 Opération (8) Remove cable guards and pulleys as necessary to work cables free of airplane 27-30-00 Opération (9) Remove cables 27-30-00 Opération A. Remove Elevator Bell Crank 27-30-00 Étape (1) Remove access plates (231JB and 310AB) Refer to Chapter 6, Access/Inspection Plates - Description and Operation 27-30-00 Opération Remove safety clips/safety wire to relieve cable tension at turnbuckles and disconnect cables from cable links 27-30-00 Opération (3) Remove bolt and washer securing push-pull tube to bell crank 27-30-00 Opération (4) Remove nut, washers, spacers, elevator down springs, cable links and bolt from upper end of bell crank 27-30-00 Opération (5) Remove nut, bolt and cotter pin securing cable links to lower end of bell crank 27-30-00 Opération (6) Remove pivot bolt attaching bell crank to brackets 27-30-00 Opération (7) Remove bell crank 27-30-00 Opération A. Remove Aft Elevator Arm Assembly 27-30-00 Étape (1) Remove stinger 27-30-00 Opération (2 Remove bolt securing push-pull tube to arm assembly 27-30-00 Opération (3) Remove bolts securing elevator torque tubes to arm assembly. A heat gun may be required to soften epoxy adhesive on bolts 27-30-00 Opération (4) Remove pivot bolt securing arm assembly and slide assembly from between elevator torque tubes 27-30-00 Opération ELEVATOR TRIM CONTROL - MAINTENANCE 27-31-00 Processus NOTE: This supplies the lubrication for the screw assembly 27-31-00 Note NOTE: The screw assembly must move smoothly in the actuator 27-31-00 Note NOTE: The linear free play at the sprocket end must not be more than 0.010 inch (0.254 mm) maximum 27-31-00 Note NOTE: Allow airplane temperature to stabilize for a period of four (4) hours before checking cable tension 27-31-00 Note NOTE: If chains or cables are being installed, permit actuator screw to rotate freely as chains and cables are connected 27-31-00 Note NOTE: Pointer must not rub against pedestal cover or clear cover more than 0.125 inch (3.18 mm) maximum 27-31-00 Note NOTE: Allow airplane temperature to stabilize for a period of four (4) hours before checking cable tension 27-31-00 Note NOTE: If chains or cables are being installed, let the actuator screw rotate freely as chains and cables are connected 27-31-00 Note NOTE: Do not install the pedestal cover until rigging is complete 27-31-00 Note NOTE: MAKE SURE THE ELEVATOR AND TRIM TAB ARE IN THE NEUTRAL POSITION WHEN STOP BLOCK (1) IS INSTALLED. 1210T1001 27-31-00 Note NOTE: Pointer must not rub against pedestal cover or clear cover more than 0.125 inch (3.18 mm) maximum 27-31-00 Note NOTE: Nose down trim indication corresponds to the trim tab in an UP position 27-31-00 Note CAUTION: Be sure trim tab moves in correct direction when the trim tab control wheel is moved toward the nose down position, the elevator trim tab moves up 27-31-00 Caution CAUTION: Be sure trim tab moves in correct direction when operated by trim control wheel. Nose down trim corresponds to tab up position 27-31-00 Caution CAUTION: Maintain specified control cable tension 27-31-00 Caution CAUTION: Maintain the specified control cable tension 27-31-00 Caution CAUTION: Make sure the elevator and trim tab are in the neutral position when stop block (1) is installed 27-31-00 Caution A. Remove Trim Tab Actuator 27-31-00 Étape CHAIN à BOLT NUT 1210T1001 DETAIL C A1234R1013 B1234R1017 C1234R1018 Elevator Trim Tab Control System Figure 201 (Sheet 1) 27-31-00 Document PIN CABLE GUARD COTTER PIN D1234R1026 E1234R1027 DETAIL G F1234R1020 G1234R1004 H1234R1028 Elevator Trim Tab Control System Figure 201 (Sheet 2) 27-31-00 Document Elevator Trim Tab Control System Figure 201 (Sheet 3) 27-31-00 Document Elevator Trim Tab Control System Figure 201 (Sheet 4) 27-31-00 Document (1) Position a support stand under tail tiedown ring to prevent tailcone from dropping while person is working inside. Refer to Chapter 7, Jacking - Maintenance Practices 27-31-00 Opération (2) Remove access plate (310CB) from lower side of right stabilizer. Refer to Chapter 6, Access/ Inspection Plates - Description and Operation 27-31-00 Opération (3) Remove rear seat. Refer to Chapter 25, Rear Seat - Maintenance Practices 27-31-00 Opération (4) Remove baggage curtain for access to elevator trim control cable stop blocks. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 27-31-00 Opération (5) Remove safety clip and relieve cable tension at turnbuckle 27-31-00 Opération (6) At the elevator hinge gap, disconnect push-pull tube from actuator 27-31-00 Opération 7) Remove chain guard 27-31-00 Opération 8) Remove chain from actuator sprocket 27-31-00 Opération (9) Remove screws attaching actuator to bracket, and carefully work actuator out through access opening 27-31-00 Opération A. Remove Cables and Pulleys 27-31-00 Étape NOTE: To ease routing of cables, a length of wire may be attached to the end of the cable before being withdrawn from airplane. Leave the wire in place, routed through the structure; then attach cable being installed and pull the cable into position 27-31-00 Note (1) Position a support stand under tail tie-down ring to prevent tailcone from dropping while person is working inside. Refer to Chapter 7, Jacking - Maintenance Practices 27-31-00 Opération L) Remove pilot and copilot seats. Refer to Chapter 25, Front Seats - Maintenance Practices 27-31-00 Opération (3) Remove center seats. Refer to Chapter 25, Center Seats and Rails - Maintenance Practices 27-31-00 Opération (4) Remove rear seat. Refer to Chapter 25, Rear Seat - Maintenance Practices 27-31-00 Opération (5) Remove carpet and baggage curtain. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 27-31-00 Opération (6) Remove pedestal cover. Refer to, Remove Pedestal Cover 27-31-00 Opération (7) Remove access plates (230DB, 230GB, 231LB, 310BB, and 310CB), and fairings (340AL and 340AR) Refer to Chapter 6, Access/Inspection Plates - Description and Operation 27-31-00 Opération (8) Remove stop blocks from control cables 27-31-00 Opération (9) Remove cable guard from actuator 27-31-00 Opération (10) Remove safety clip from turnbuckle and disconnect cable 27-31-00 Opération (11) Disconnect cables at cable ends 27-31-00 Opération (12) Remove cable guards and pulleys 27-31-00 Opération (13) Disengage chains from sprockets and remove cables from airplane structure 27-31-00 Opération A. Remove Trim Tab Control Wheel 27-31-00 Étape (1) Remove pilot and copilot seats. Refer to Chapter 25, Front Seat And Rails - Maintenance Practices 27-31-00 Opération (2) Remove pedestal cover. Refer to Pedestal Cover Removal/Installation 27-31-00 Opération 3) Remove screws and nuts securing chain guard to pedestal 27-31-00 Opération 4) Remove nut securing indicator to pivot stud. Retain washers 27-31-00 Opération (5) Loosen bolts securing idler sprockets to pedestal structure, slide idler sprockets in slotted holes and disengage drive chain from sprockets 27-31-00 Opération (6) Remove bolts and remove chain guard using care not to bend pointer or drop parts into tunnel area 27-31-00 Opération (7) Remove drive chain from trim wheel sprocket and carefully slide trim wheel from pivot stud 27-31-00 Opération A. Remove Pedestal Cover 27-31-00 Étape (1) Turn fuel selector valve to OFF position and drain fuel from strainer and lines. Remove fuel selector handle and placard 27-31-00 Opération 3) Remove cowl flap handle knob and microphone mounting bracket 27-31-00 Opération (4) Fold carpet back as necessary and remove screws securing cover to floor and pedestal 27-31-00 Opération (5) Disconnect electrical wiring to pedestal lights 27-31-00 Opération (6) Carefully work cover from pedestal to prevent damage 27-31-00 Opération FLAP CONTROL SYSTEM - MAINTENANCE 27-50-00 Processus NOTE: It is permitted to apply 3M Y8671 or equivalent polyurethane tape on upper flap skins as necessary to prevent chafing against the wing trailing edge 27-50-00 Note NOTE: If push-pull rod adjustment was not disturbed, flap rigging will not be required 27-50-00 Note NOTE: ALLOW AIRPLANE TEMPERATURE TO STABILIZE FOR A PERIOD OF FOUR (4) HOURS 27-50-00 Note BEFORE CHECKING CABLE TENSION 27-50-00 Note NOTE: The right flap and actuator must be correctly rigged before cables and left flap can be rigged 27-50-00 Note NOTE: Since the flap rollers may not touch the bottom in the flap tracks with the flaps fully extended, some free play can be noticed in this position 27-50-00 Note A. Remove the Flap Motor and Transmission Assembly 27-50-00 Étape Wing Flap Control System Installation Figure 201 (Sheet 1) 27-50-00 Document Wing Flap Control System Installation Figure 201 (Sheet 2) 27-50-00 Document BUSHING ROLLER WASHER: WASHER BOLT NUT NUT WASHER G1225R1008 DETAIL H HO725R1003 L0564R1006 Wing Flap Control System Installation Figure 201 (Sheet 3) 27-50-00 Document BOLT NUTPLATE WASHER NUT DETAIL K JO725R1002 KO725R1003 Wing Flap Control System Installation Figure 201 (Sheet 4) 27-50-00 Document (1) Lower the flaps 27-50-00 Opération (2) Disconnect the electrical power 27-50-00 Opération (3) Remove access plate 610JB - Refer to Chapter 6, Access/Inspection Plates - Description and Operation 27-50-00 Opération (4) Remove the bolt that attaches the actuating tube to the drive pulley 27-50-00 Opération (5) Turn the actuating tube in toward transmission as far as possible by hand 27-50-00 Opération (6) Remove the bolt that attaches the flap motor hinge to the wing. Keep the brass washer between the hinge and the wing structure for use on installation 27-50-00 Opération (7) Disconnect the electrical connectors from the motor, and the limit switches 27-50-00 Opération (8) Carefully remove the assembly from the wing through the access opening 27-50-00 Opération A. Remove the Flaps 27-50-00 Étape (1) Put the Master Switch (S1009) to ON 27-50-00 Opération (2) Lower the flaps using flap selector switch (S1008) 27-50-00 Opération (3) Put the BAT portion of the Master Switch to BAT (off) 27-50-00 Opération (4) Remove the access plates 511AT (611AT), 511BT (611BT), 511CT (611CT), 511DT (611DT), and 511ET (611ET) from the leading edge of the flap 27-50-00 Opération (5) Disconnect the push-pull rod at the flap bracket 27-50-00 Opération (6) Remove the bolts at each flap track. As the flap is removed from the wing, all of the washers, rollers and bushings will fall. Keep this hardware for installation 27-50-00 Opération A. Remove the Flap Drive Pulleys 27-50-00 Étape NOTE: Left and right are typical except as noted 27-50-00 Note NOTE: The actuating tube is only on the right wing flap 27-50-00 Note (1) In the cockpit/cabin area, remove overhead center console. Refer to Chapter 25, Interior Upholstery - Maintenance Practices. Remove the safety clips and loosen the flap adjustment turnbuckles 27-50-00 Opération 0 Remove access plates 610JB and 610FB for the right flap, and 510JB and 510FB for the left flap. Refer to Chapter 6, Access/Inspection Plates - Description and Operation 27-50-00 Opération (4) Remove the bolt that attaches the flap push-pull rod to the drive pulley 27-50-00 Opération (5) Remove the bolt that attaches the synchronizing push-pull tube to the drive pulley, and gently lower the right flap 27-50-00 Opération (6) Remove the bolt that attaches the actuating tube to the drive pulley and lower right flap 27-50-00 Opération ) Remove the cable locks that attach the control cables to the drive pulley 27-50-00 Opération (8) Tag the cables for identification 27-50-00 Opération (9) Remove the bolt that attaches the drive pulley to the wing structure 27-50-00 Opération (10) Remove the drive pulley through the access opening, without dropping the bushing. Keep the brass washer between the drive pulley and wing structure for use during installation 27-50-00 Opération (11) Tape the open ends ofthe drive pulley after removalto preventt the bearings from being damaged 27-50-00 Opération A. Remove the Cables and Pulleys 27-50-00 Étape NOTE: Allow airplane temperature to stabilize for a period of four (4) hours before checking cable tension 27-50-00 Note NOTE: Airplanes 20608001 thru 20608173, and Airplanes T20608001 thru T20608361 have a 0.094 inch (2.4 mm) diameter cable. Airplanes 20608174 and On, and Airplanes T20608362 and On have a 0.125 inch (3.2 mm) diameter cable 27-50-00 Note (1) Remove the overhead center console. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 27-50-00 Opération (2) Remove access plates 610CB, 610DB, 610FB, 610HB, 610JB, 610LB, 610NB, 610QB, 610SB, 610WB on the right flap, and 510CB, 510DB, 510FB, 510HB, 510JB, 510LB, 510NB, 510QB, 510SB, 510WB on the left flap. Refer to Chapter 6, Access/Inspection Plates - 27-50-00 Opération (3) Disconnect the flap follow-up cable from the retract cable 27-50-00 Opération (4) Remove the safety clips from the forward retract cable and aft extend cable turnbuckles 27-50-00 Opération (5) Relieve the cable tension by carefully lowering the left flap 27-50-00 Opération (6) Remove the cable guards and pulleys 27-50-00 Opération (7) Attach a length of wire long enough to go through the structure, to the end of the cable being withdrawn from the airplane 27-50-00 Opération (8) Remove the cables 27-50-00 Opération (9) Leave the wire in place, routed through structure 27-50-00 Opération FLAP FOLLOW-UP AND INDICATING SYSTEM - MAINTENANCE 27-51-00 Processus NOTE: Before installing knob on control lever, clean threads on control lever with methyl n-propyl ketone or equivalent. After threads have thoroughly dried, prime with grade T primer. Allow primer to flash off or dry for three to five minutes. Apply 27-51-00 Note NOTE: Flap travel on UP cycle may deviate a maximum of 4 degrees from indicated position 27-51-00 Note NOTE: Equivalent substitutes may be used for the following items 28-00-00 Note A. Remove Flap Control Lever 27-51-00 Étape NOTE: Insulators are installed between switches and switch mounting arm 27-51-00 Note Wing Flap Control and Follow-Up System Figure 201 (Sheet 1) 27-51-00 Document DETAIL C NUT C12251002 Wing Flap Control and Follow-Up System Figure 201 (Sheet 2) 27-51-00 Document (1) Remove pedestal cover 27-51-00 Opération (2) Remove flap UP and DOWN operating switches from switch mounting arm. Do not disconnect electrical wiring at switches 27-51-00 Opération (3) Disconnect spring from bellcrank assembly 27-51-00 Opération (4) Remove knob from control lever 27-51-00 Opération (5) Remove cotter pin, washers, and pin securing switch mounting arm to bellcrank assembly. Discard cotter pin 27-51-00 Opération (6) Remove remaining washers, bushings, switch mounting arm, and control lever by removing mounting bolt. Use care not to drop parts into tunnel area 27-51-00 Opération FUEL CONTAMINATION - MAINTENANCE 28-10-00 Processus NOTE: Water suspended in fuel appears in the form of droplets that reflect light. High concentration of water droplets will cause fuel to have a cloudy or hazy appearance 28-10-00 Note NOTE: Fuel with known dirt, sand or rust particle contamination must be discarded as waste fuel 28-10-00 Note NOTE: As an alternative, the improper mixture may be corrected by the addition of the proper amount of non-preblended fuel or the addition of anti-ice to bring the mixture ratio to within the specified concentration by volume. The reblended fuelladdi 28-10-00 Note NOTE: All fuels contaminated with unapproved additives or foreign liquids must be discarded as waste fuel 28-10-00 Note NOTE: The illustration that shows the fuel return system is installed on Airplanes 206008174 and On and Airplanes T206008362 and On 28-20-00 Note CAUTION: Observe all applicable local and facility safety regulations when performing fuel system maintenance. Refer to Fuel Storage and Distribution - Maintenance Practices 28-10-00 Caution FUEL STORAGE AND DISTRIBUTION - MAINTENANCE 28-20-00 Processus NOTE: A vent line is installed in the outboard end of each fuel bay. The vent line extends overboard through the lower wing skin near the point where the lift struts attach to the underside of the wings 28-20-00 Note NOTE: Fuel vents may become blocked and not supply the engine with sufficient fuel. If the bleed hole in the vent valve becomes blocked, then pressurization can occur due to normal temperature variation. This would usually occur when the airplane eng 28-20-00 Note FOR ICE PROTECTION 28-20-00 Note NOTE: IF THE PRESSURE TEST SHOWS THE BYPASS PORT IS BLOCKED, THE FUEL VENT CHECK VALVE MUST BE REPLACED. INSTALL A NEW FUEL VENT CHECK VALVE WITH THE 1210T1001 A1226T1001 28-20-00 Note NOTE: A serviceable wing fuel vent check valve will let positive pressure bleed through the bypass port from the fuel tank. An unserviceable wing fuel vent check valve will not let positive pressure to bleed through the bypass port from the fuel tank 28-20-00 Note NOTE: The distance from the strut to the end of the fuel vent line must be 1.12 inches +0.03 or -0.03 (28.45mm +0.762 or -0.762) 28-20-00 Note NOTE: Uneven fuel feed may occur with the fuel selector valve set in the BOTH position. This is caused by unequal pressure that act on the each of the fuel tank vents. This may be corrected if you use the procedures that follow 28-20-00 Note NOTE: The procedures that follow can be completed during a sequence of routine flight operations. Flights for the only purpose of a check and to adjust the fuel tank feed rates is not recommended due to the amount of time required 28-20-00 Note NOTE: The step-washer at the bottom of bowl is installed SO that the step fits against the O-ring 28-20-00 Note WARNING: Blocked vent lines and bleed holes will cause insufficient fuel or the pressurization of tanks by fuel expansion. Any fuel vent found blocked or restricted must be corrected before you return the airplane to service 28-20-00 Warning WARNING: One of the fuel vent lines must be positioned behind a lift strut. Use the dimensions called out in Figure 205. This position will supply protection from ice in at least one vent tube 28-20-00 Warning CAUTION: One of the vents must remain positioned behind the strut as illustrated in Figure 205 for ice protection 28-20-00 Caution A. Remove the Fuel Drain Valve 28-20-00 Étape NOTE: The left and right fuel drain valve removal/installation is typical. Five fuel drains are installed in each wing 28-20-00 Note Figure 202 (Sheet 1) 28-20-00 Document (1) Remove the fuel from the airplane. Refer to Chapter 12, Fuel - Servicing 28-20-00 Opération (2) Use a fuel sampler cup and press the fuel drain valve up to make sure the fuel bay is empty of fuel 28-20-00 Opération (3) Remove the safety wire from the fuel drain valve 28-20-00 Opération (4) Remove the fuel drain valve from the fuel bay 28-20-00 Opération A. Remove the Fuel Reservoir 28-20-00 Étape NOTE: The fuel reservoir removal/installation is typical for the left and right reservoirs 28-20-00 Note NOTE: Each fuel reservoir holds 0.41 gallons (1.55 liters) 28-20-00 Note (TYPICAL) DRAIN VALVE DETAIL A 1210T1001 A1216T1007 Fuel Reservoir Installation Figure 203 (Sheet 1) 28-20-00 Document (1) Set the fuel shutoff valve to the OFF position 28-20-00 Opération (2) Defuel the fuel tanks. Refer to Chapter 12, Fuel - Servicing 28-20-00 Opération (3) Remove the pilot and copilot seat and carpet. Refer to Chapter 25, Front Seats - Maintenance Practices 28-20-00 Opération (4) Remove the carpet from the forward cabin. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 28-20-00 Opération (5) Remove the access panels 230CB and 230DB to get access to the reservoirs. Refer to Chapter 6, Access/Inspection Plates - Description and Operation 28-20-00 Opération (6) Set a container under the fuel drain in the bottom of the fuselage and drain the fuel from the reservoir 28-20-00 Opération (7) Disconnect the reservoir vent tube 28-20-00 Opération (8) Disconnect the reservoir inlet tube 28-20-00 Opération (9) Disconnect the reservoir outlet tube 28-20-00 Opération (10) Remove the screws installed in the reservoir to the airplane structure 28-20-00 Opération (11) Remove the reservoir from the airplane 28-20-00 Opération A. Remove the Fuel Selector Shaft 28-20-00 Étape Fuel Selector Valve Installation Figure 204 (Sheet 1) 28-20-00 Document (1) Remove the button plug on the top of the fuel selector valve handle to show the screw in the handle 28-20-00 Opération 2) Remove the screw and lift up on the handle to disconnect it from the fuel selector shaft 28-20-00 Opération 3) Remove the metal placard from the pedestal 28-20-00 Opération (4) Remove the pedestal cover. Refer to Chapter 27, Pedestal Cover 28-20-00 Opération 5) Remove the carpet as required. Referto Chapter 25, Interior Upholstery - Maintenance Practices 28-20-00 Opération (6) Remove the support assembly 28-20-00 Opération (7) Remove the floor access plate 230BB. Refer to Chapter 6, Access/Inspection Plates Description and Operation 28-20-00 Opération (8) Remove and discard the cotter pin from the pin that attaches the fuel selector shaft to the fitting 28-20-00 Opération (9) Remove the washer and pin from the fuel selector shaft 28-20-00 Opération (10) Remove the fuel selector shaft from the fitting 28-20-00 Opération A. Remove the Fuel Selector Valve 28-20-00 Étape (1) Defuel the airplane. Refer to Chapter 12, Fuel - Servicing 28-20-00 Opération (a) Set an applicable container under the fuel selector quick drain 28-20-00 Opération (b) Make sure the fuel selector valve is in the OFF position and remove the drain plug from the fuel selector valve 28-20-00 Opération (c) Turn the fuel selector valve to the BOTH position and drain the fuel from the door post fuel lines 28-20-00 Opération (d) Install the drain plug in the fuel selector valve and install safety wire. Refer to Chapter 20, Safetying - Maintenance Practices 28-20-00 Opération Remove the button plug on the top of the fuel selector valve handle to show the screw 28-20-00 Opération ) Remove the screw and lift up on handle to disconnect it from the fuel selector valve shaft 28-20-00 Opération 4) Remove the metal placard from the pedestal to get access to the valve, plumbing and universal joints 28-20-00 Opération (5) Remove the pedestal cover. Refer to Chapter 27, Elevator Trim Control - Maintenance Practices 28-20-00 Opération (6) Remove the support assembly 28-20-00 Opération 1) Remove the pilot and copilot seat. Refer to Chapter 25, Front Seats - Maintenance Practices 28-20-00 Opération (8) Remove thet forward carpet as required to gett to the access plate 230BB thati is aft oft the pedestal. Refer to Chapter 6, Access/Inspection Plates - Description and Operation 28-20-00 Opération (9) Remove access plate 230BB 28-20-00 Opération (10) Disconnect the lower universal joint at the selector valve shaft 28-20-00 Opération (11) Disconnect and put a cap on the fuel lines to selector valve, fuel supply and fuel return 28-20-00 Opération (12) Remove the screws attaching the selector valve to the mounting plate and remove the valve from the airplane 28-20-00 Opération A. Remove the Electric Auxiliary Fuel Pump 28-20-00 Étape Electric Auxiliary Fuel Pump Figure 208 (Sheet 1) 28-20-00 Document (1) Make sure the ALT/BAT MASTER switch is set in the OFF position 28-20-00 Opération L Disconnecti thel battery ground cable from thel battery. Referto Chapter 24, Battery -I Maintenance Practices 28-20-00 Opération 3 Set the fuel selector in the OFF position 28-20-00 Opération 4) Remove the pilot seat. Refer to Chapter 25, Front Seats - Maintenance Practices 28-20-00 Opération 5) Remove the carpet as necessary. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 28-20-00 Opération (6) Remove access plate 230AB to get access to the pump. Refer to Chapter 6, Access/Inspection Plates - Description and Operation 28-20-00 Opération ) Disconnect the fuel lines 28-20-00 Opération (8) Disconnect the electrical connection (JN003) from the electric auxiliary fuel pump (UN007) 28-20-00 Opération (9) Loosen the clamps to the pump and remove the pump from the airplane 28-20-00 Opération FUEL BAY SEALING - MAINTENANCE 28-21-00 Processus NOTE: A closed area is defined as the wing leading edge and the section of wing inboard or outboard of the fuel bays 28-21-00 Note NOTE: Fuel can flow along a seam or structure of the wing for several inches which can make the leak source difficult to find. A stained area is an indication of the leak source 28-21-00 Note NOTE: The PFD is now in the configuration mode 28-40-00 Note NOTE: This diagram shows CAN Bus related wiring only 28-40-00 Note NOTE: If this is a new fuel quantity sender, use the new screws and insulators that came with the fuel quantity sender 28-40-00 Note NOTE: Fuel quantity calibration must be done after installing sender. Refer to Fuel Quantity Calibration 28-40-00 Note NOTE: If the fuel level senders are replaced, the system must be calibrated. Refer to Fuel Quantity Calibration and Check 28-40-00 Note NOTE: When the sensor tube is put into the tank correctly, the sensor tip should point forward 28-40-00 Note NOTE: The internal light for the fuel quantity indicator will not work when the test box is connected 28-40-00 Note NOTE: A nonmagnetic screwdriver must be used when you adjust the potentiometers on the fuel quantity indicator 28-40-00 Note NOTE: The airplane's digital clock can be used in the timer mode to measure the time of the annunciators. The interval for this test is from switch operation until the annunciator begins to flash. The annunciators will flash for approximately 10 seco 28-40-00 Note NOTE: All G1000 airplanes must have software version 563.03 or later. The software version is shown on the upper right corner of the MFD on the first after the MFD is powered on in normal operation 28-40-00 Note NOTE: If the fuel quantity indicator on the Garmin G1000 system has a red X on it during normal operation, examine the fuel quantity sender and wiring and refer to the Garmin G1000 Line Maintenance Manual for more Garmin system troubleshooting 28-40-00 Note NOTE: The annunciations will be seen when the fuel quantity indicates less than 8 gallons for 60 seconds 28-40-00 Note NOTE: The PFD is now in the configuration mode 28-40-00 Note NOTE: The MFD is now in the configuration mode 28-40-00 Note NOTE: After turning the inner FMS knob, some versions of software will make it necessary to push the ENT button to select the tank 28-40-00 Note NOTE: After turning the inner FMS knob, some versions of software will make it necessary to push the ENT button to select the tank 28-40-00 Note NOTE: All G1000 airplanes must have software version 563.03 or later. The software version is shown on the upper right corner of the MFD on the first after the MFD is powered on in normal operation 28-40-00 Note NOTE: If the fuel quantity indicator on the Garmin G1000 system has a red X on it during normal operation, examine the fuel quantity sensors and wiring and refer to the Garmin G1000 Line Maintenance Manual for more Garmin system troubleshooting. If t 28-40-00 Note NOTE: The annunciations will be seen when the fuel quantity indicates less than 8 gallons for 60 seconds 28-40-00 Note NOTE: The MFD is now in the configuration mode 28-40-00 Note NOTE: The PFD is now in the configuration mode 28-40-00 Note NOTE: The SCALE softkey will be gray with black letters when it is selected 28-40-00 Note NOTE: The scale function needs to be selected when overwriting the 0.00 GL calibration points for both the left and right tank 28-40-00 Note NOTE: After turning the inner FMS knob, some versions of software will make it necessary to push the ENT button to select the tank 28-40-00 Note NOTE: There should be several calibration points in the CALIBRATION TABLE 28-40-00 Note NOTE: After turning the inner FMS knob, some versions of software will make it necessary to push the ENT button to select the tank 28-40-00 Note NOTE: For example, if the 0.00 GL CALIBRATED VALUE is 6.00000 then the 2.00 GL CALIBRATED VALUE should be 13.70000, +0.3 or -0.3 28-40-00 Note NOTE: After turning the inner FMS knob, some versions of software will make it necessary to push the ENT button to select the tank 28-40-00 Note NOTE: The MFD is now in the configuration mode 28-40-00 Note NOTE: The PFD is now in the configuration mode 28-40-00 Note NOTE: Every time after the "INITIALIZE FUEL CAL DATA" is loaded the Fuel Quantity System Calibration (Airplanes with Garmin G1000 and CAN bus type fuel level sensors) must be performed for each tank 28-40-00 Note NOTE: The MFD is now in the configuration mode 28-40-00 Note NOTE: The PFD is now in the configuration mode 28-40-00 Note the connector on the opposite 28-40-00 Caution side. If the problem follows 28-40-00 Caution the sensor, replace it. Refer 28-40-00 Caution to Fuel Quantity Indication 28-40-00 Caution System-Removal/Intallation. If 28-40-00 Caution the problem does not follow the 28-40-00 Caution sensor, contact Cessna Customer 28-40-00 Caution Services at 316-517-5800 28-40-00 Caution CAUTION: Make sure the wires or probes do not touch when the NAV1 ENG circuit breaker is engaged. If the wires or probes touch, the inline system protection fuse will open 28-40-00 Caution CAUTION: Do not bend the fuel level sender float arm 28-40-00 Caution CAUTION: Do not attach the screw to the nut ring without the insulator. The fuel level sender can operate incorrectly without the insulator 28-40-00 Caution CAUTION: Do not bend the fuel level sensor tube on the structure inside or outside the tank. A bent tube will give incorrect operation 28-40-00 Caution CAUTION: Before you do the calibration procedure, you must turn on the G1000 system and let it become stable for a minimum of three minutes 28-40-00 Caution CAUTION: Before you do the calibration procedure, you must turn on the G1000 system and let it become stable for a minimum of three minutes 28-40-00 Caution A. Remove the Fuel Level Sender 28-40-00 Étape NOTE: The removal and installation of the float-type fuel level senders is typical for the left and right fuel bays 28-40-00 Note CAUTION: Do not bend the fuel level sender float arm 28-40-00 Caution EMPTY ADJUSTMENT FULL ADJUSTMENT FUEL QUANTITY INDICATOR DETAIL B 1210T1001 AIRPLANES WITH STANDARD AVIONICS A0714T1027 BS3277T-2 Fuel Quantity System Installation Figure 401 (Sheet 1) 28-40-00 Document (1) Drain the fuel from the airplane. Refer to Chapter 12, Fuel - Servicing 28-40-00 Opération (2) Remove the headliner to get access to the wing root. Refer to Chapter 25, Cabin Panels - Removal/Installation 28-40-00 Opération (3) Disconnect the wire ring terminals from the fuel level sender 28-40-00 Opération (4) Remove the screws that attach the fuel level sender to the nut ring and retain for installation 28-40-00 Opération (5) Carefully remove the fuel sender and gasket from the fuel bay 28-40-00 Opération B. Remove the Indicator 28-40-00 Étape (1) Make sure the electrical power is OFF 28-40-00 Opération 2) Get access to the forward of the fuel quantity indicator and disconnect the electrical connector 28-40-00 Opération (3) Remove the screws that attach the indicator to the instrument panel and remove the indicator from the airplane 28-40-00 Opération A. Remove the Sensor 28-40-00 Étape CAUTION: Do not bend the fuel level sensor tube on the structure inside or outside the tank. A bent tube will give incorrect operation 28-40-00 Caution CONNECTOR - GROUND NUT STUD LOCK WASHER GROUND BRAID DETAIL A RIGHT SIDE SHOWN (LEFT SIDE OPPOSITE) 0510T1007 A0526T1019 Fuel Level Sensor Figure 402 (Sheet 1) 28-40-00 Document (1) Make sure the electrical power is OFF. Defuel the airplane. Refer to Chapter 12, Fuel - Servicing 28-40-00 Opération (3) Remove the headliner to get access to the wing root. Refer to Chapter 25, Cabin Panels - Removal/Installation 28-40-00 Opération (4) Disconnect the electrical connector from the fuel level sensor 28-40-00 Opération (5) Disconnect the fuel level sensor ground braid 28-40-00 Opération (6) Remove the screws that attach the fuel level sensor to the bracket 28-40-00 Opération (7) Carefully remove the fuel level sender from the fuel bay 28-40-00 Opération (a) Carefully rotate the sensor tip forward of the mounting hole 28-40-00 Opération (b) Carefully pull the sensor out and forward of the mounting hole 28-40-00 Opération WINTERIZATION KIT - MAINTENANCE 30-20-00 Processus NOTE: Be sure existing holes on nose covers align with existing holes in nosecap 30-20-00 Note NOTE: Operation of the propeller heat system for longer than 60 seconds without the propeller rotation can cause damage to the de-icing boots 30-60-00 Note NOTE: Operation of the propeller heat system at below 24 volts can result in less than sufficient power for normal operation 30-60-00 Note PROPELLER HEAT - MAINTENANCE 30-60-00 Processus WARNING: Make sure all electrical power is removed from the airplane when work is done near the propeller 30-60-00 Warning WARNING: Make sure all electrical power to the airplanes is removed when you work near the propeller 30-60-00 Warning A. Remove the Timer for the Propeller Heat 30-60-00 Étape (1) Make sure the electrical power is off. Disconnect the electrical plug from the timer 30-60-00 Opération (3) Remove the four screws that attach the timer to the bracket 30-60-00 Opération (4) Remove the timer from the airplane 30-60-00 Opération A. Remove the Propeller Heat Indicator 30-60-00 Étape NOTE: The procedures that follow are for airplanes with standard avionics 30-60-00 Note (1) Make sure the airplane electrical power is off 30-60-00 Opération 2) Remove the screws that attach the annunciator panel to the instrument panel 30-60-00 Opération (3) Pull the annunciator panel forward 30-60-00 Opération (4) Disconnect the electrical plug from the indicator 30-60-00 Opération 5) Remove the screws that attach the indicator to the mounting clip 30-60-00 Opération 6) Pull the mounting clip from indicator 30-60-00 Opération 7) Pull the indicator from the annunciator panel 30-60-00 Opération A. Remove the Brush Block 30-60-00 Étape WARNING: Make sure all electrical power is removed from the airplane when work is done near the propeller 30-60-00 Warning (1.63 MM, +0.381 OR -0.381 MM) AA2614T1355 A26501006 VIEW A-A B26141355 BB26141356 Brush Block Installation Figure 201 (Sheet 1) 30-60-00 Document (1) Disengage the Prop Deice circuit breaker 30-60-00 Opération (2) Remove the nose cap. Refer to Chapter 71, Cowling - Maintenance Practices 30-60-00 Opération (3) Identify and attach tags to the electrical leads (I) and (G) from the brush block (XN001) 30-60-00 Opération (4) Disconnect the electrical leads (I) and (G) 30-60-00 Opération (5) Remove the screws, washers, nuts, spacers and shims that are attached with the brush block to the bracket and remove the brush block 30-60-00 Opération INSTRUMENT AND CONTROL PANELS - MAINTENANCE 31-10-00 Processus A. Remove Pilot's Center panel 31-10-00 Étape PANEL CONTROLS DETAIL A AIRPLANES WITH STANDARD AVIONICS 1210T1001 A1218T1021 Instrument Panels Figure 201 (Sheet 1) 31-10-00 Document (1) Disconnect negative cable from airplane battery. Refer to Chapter 24, Battery - Maintenance Practices 31-10-00 Opération (2) Remove screws securing control column collar 31-10-00 Opération (3) Remove screws securing center panel to pilot's outboard and inboard panels 31-10-00 Opération (4) Disconnect all electrical leads from instruments and tag for reinstallation 31-10-00 Opération (5) Disconnect all lines from instruments. Cap all fittings and plug all lines 31-10-00 Opération (6) Remove panel assembly 31-10-00 Opération A. Remove Pilot's Inboard/Outboard Panel 31-10-00 Étape (1) Disconnect negative cable from airplane battery. Refer to Chapter 24, Battery - Maintenance Practices 31-10-00 Opération (2) Remove screws securing control column collar 31-10-00 Opération 3) Remove screws securing center panel to the pilot's inboard/outboard panel 31-10-00 Opération (4) Disconnect all electrical leads from instruments and tag for reinstallation 31-10-00 Opération (5) Disconnect all lines from instruments. Tag, cap and plug all lines 31-10-00 Opération (6) Remove panel assembly 31-10-00 Opération A. Remove Copilot's Panel 31-10-00 Étape (1) Disconnect negative cable from airplane battery. Refer to Chapter 24, Battery - Maintenance Practices 31-10-00 Opération 2) Remove screws securing control column collar 31-10-00 Opération (3) Remove screws securing panel 31-10-00 Opération (4) Disconnect all electrical leads from instruments and tag for reinstallation 31-10-00 Opération (5) Remove panel assembly 31-10-00 Opération A. Remove the Center Panel 31-10-10 Étape Instrument and Control Panel Installation Figure 201 (Sheet 1) 31-10-10 Document (1) Make sure the MASTER ALTIBAT and Avionics switch is in the off position 31-10-10 Opération (2) Disengage the STDBY IND-LTS circuit breaker 31-10-10 Opération 3) Remove the screws that attach the center panel to the instrument panel 31-10-10 Opération (4) Carefully pull out the center panel as necessary to get access behind the panel 31-10-10 Opération 5) Install tags for identification on the electrical connectors and hoses and disconnect them from the instruments 31-10-10 Opération A. Remove the Switch Panel 31-10-10 Étape (1) Make sure the Master ALT/BAT switch is in the off position. Remove the screws that attach the switch panel to the instrument panel 31-10-10 Opération 3) Carefully pull the switch panel out from the instrument panel to get access to the aft side of the panel 31-10-10 Opération (4) Disconnect the switches from the electrical connections 31-10-10 Opération A. Throttle/Flap Panel Removal 31-10-10 Étape (1) Disconnect the negative cable from airplane battery. Refer to Chapter 24, Battery - Maintenance Practices 31-10-10 Opération 2) Make sure the MASTER ALT/BAT and AVIONICS switches are in the off position 31-10-10 Opération 3) Remove the screws that attach the throttle/flap panel to the instrument panel 31-10-10 Opération 4) Carefully pull the throttle/flap panel outt from the instrument panel to get access behind the panel 31-10-10 Opération 5) Disconnect the switches from the electrical connections 31-10-10 Opération A. Remove the Instrument Panel 31-10-10 Étape NOTE: The ELT switch can only be removed from the forward side of the instrument panel 31-10-10 Note (1) Disconnect electrical power to the airplane 31-10-10 Opération (a) Make sure the AVIONICS switch is in the off position 31-10-10 Opération (b) Disengage the twol PFD circuit breakers, the MFD, STDBY BATT, STDBY IND-LTS. AUDIO circuit breakers 31-10-10 Opération Remove the center panel. Refer to Center Panel - Removal/Installation 31-10-10 Opération Remove the switch panel. Refer to Switch Panel - Removal/Installation 31-10-10 Opération Remove the throttle/flap panel. Refer to Throttle/Flap Panel - Removal/Installation 31-10-10 Opération b) Remove the Audio Panel 31-10-10 Opération 6) Remove the screws that attach the control column collars the instrument panel 31-10-10 Opération I Remove the hourmeter to the instrument panel 31-10-10 Opération (a) Remove the screws for the hourmeter 31-10-10 Opération (b) Pull the hourmeter out and disconnect the connector 31-10-10 Opération (8) Remove the Control Display Units (CDU) 31-10-10 Opération (a) Disengage the quick release fasteners 31-10-10 Opération (b) Carefully pull the CDU away from the instrument panel and disconnect the electrical connector 31-10-10 Opération (9) Remove the screws from the instrument panel 31-10-10 Opération (10) Disconnect and remove the ELT switch from the instrument panel 31-10-10 Opération (11) Remove the instrument panel 31-10-10 Opération DIGITAL CLOCK - MAINTENANCE 31-20-00 Processus HOUR METER - MAINTENANCE 31-30-00 Processus A. Remove Hour Meter 31-30-00 Étape Figure 201 (Sheet 1) 31-30-00 Document (1) Gain access to backside of instrument panel and hold nuts while loosening screws 31-30-00 Opération (2) Disconnect electrical connectors leading into hour meter 31-30-00 Opération ANNUNCIATOR PANEL - MAINTENANCE 31-50-00 Processus NOTE: Equivalent substitutes may be used for the following items 32-00-00 Note display 31-50-00 Warning A. Remove the Annunciator Panel 31-50-00 Étape NOTE 1: ANNUNCIATOR PANEL CONFIGURATION CAN BE DIFFERENT THAN SHOWN. DETAIL C 1210T1001 A1218T1001 B1218T1068 C1218T1068 D1218T1068 Annunciator Panel Installation Figure 201 (Sheet 1) 31-50-00 Document (1) Disconnect the main battery. Refer to Chapter 24, Battery - Maintenance Practices 31-50-00 Opération 2 Get access to the back side of the annunciator panel 31-50-00 Opération 3) Disconnect the electrical connectors from the annunciator 31-50-00 Opération 4) Remove the screws that attach the annunciator panel to the instrument panel 31-50-00 Opération 5) Carefully remove the annunciator from the airplane 31-50-00 Opération MAIN LANDING GEAR - MAINTENANCE 32-10-00 Processus NOTE: The convex surface of the channel is installed against the lower side of the strut. The concave side of the channel is to be installed pointed down, So that it touches the lower edge of the slot in the forging 32-10-00 Note NOTE: Aluminum shims are installed at the inboard end of the spring, as necessary, to make the wings level within a total tolerance of 3.00 inches. The maximum number of shims permitted is two. Do not use steel washers for shims 32-10-00 Note NOTE: You can get main wheel alignment through the use of tapered shims between the flange of the axle and axle mounting fitting 32-10-00 Note NOTE: The setting is zero toe-in and zero camber at normal operating weight 32-10-00 Note NOTE: Always use the least number of shims possible to get the desired result 32-10-00 Note NOTE: The cover plate is located aft of the nose gear on the bottom of the fuselage 32-10-00 Note NOTE: The bottom surface of the gear leg has a 0.012 Inch compressive distance to prevent stress risers and to extend the spring fatigue life 32-10-00 Note CAUTION: You must do a check of the clearance every time the scraper has been moved, the tire changed and when you install the speed fairings. Damage can occur if the correct clearance is not set between the tire and scraper. If any mud, snow or ice 32-10-00 Caution CAUTION: Set the tire pressure to the correct pressure. Damage can occur to the fairings if the tire pressure is not correct 32-10-00 Caution NUT OR COUNTERSUNK WASHER IN THE BRAKE LINE OPPOSITE POSITION WHEN YOU USE 32-10-00 Caution CAUTION: Do not use chemical strippers as they are not approved for use on high strength steels due to hydrogen embrittlement 32-10-00 Caution CAUTION: Do not use a power sander as it is not approved on high strength steels because of the possibility of heat 32-10-00 Caution A. Remove the Main Landing Gear Speed Fairing 32-10-00 Étape NOTE: Shims are necessary to set the fairing on the wheel to center when wheel alignment shims are installed 32-10-00 Note Main Landing Gear Installation Figure 201 (Sheet 1) 32-10-00 Document Main Landing Gear Installation Figure 201 (Sheet 2) 32-10-00 Document (1) Remove the screws that attach the brake fairing to the main wheel speed fairing 32-10-00 Opération 2) Remove the screws that attach the speed fairing to the mounting plate 32-10-00 Opération (3) If the heavy-duty main wheel speed fairings are installed, record the part number, position, and location of shims between the fairing and mounting plate 32-10-00 Opération (4) Remove the bolt that connects the outboard side of the main-wheel speed-fairing to the axle nut 32-10-00 Opération (5) Loosen the scraper if necessary, and remove the main-wheel speed-fairing from the wheel 32-10-00 Opération A. Remove the Main Landing Gear Brake Fairing 32-10-00 Étape (1) Remove the screws from the perimeter of the brake fairing 32-10-00 Opération 2 Remove the screws from the nutplates that hold the fairing together 32-10-00 Opération (3) Remove the brake fairing from the landing gear 32-10-00 Opération A. Remove the Main Landing Gear 32-10-00 Étape NOTE: This procedure is for the removal of the landing gear as a complete assembly 32-10-00 Note CAUTION: Make sure that you are careful when the channel is removed SO that damage does not occur to it 32-10-00 Caution (1) Remove the pilot and copilot seats. Refer to Chapter 25, Front Seats - Maintenance Practices. Remove access plate 230JB or 230KB. Refer to Chapter 6, Access/Inspection Plates - Description and Operation. Jack the airplane. Refer to Chapter 7, Jac 32-10-00 Opération 4) Remove the screws that connect the fuselage fairing to the fuselage 32-10-00 Opération 5) Remove the brake bleeder screw and drain the hydraulic fluid from the brake line on the strut 32-10-00 Opération 6) Disconnect the hydraulic brake line at the fitting where the brake line comes out of the fuselage skin 32-10-00 Opération (a) Put a cover on or put a plug in the disconnected fittings to prevent contamination 32-10-00 Opération (7) Remove the bolt, countersunk washer, flat washer, and nut that connects the spring strut and to the inboard forging 32-10-00 Opération (8) Remove any shims and record the position and location of shims, if removed 32-10-00 Opération (9) Remove the bolts, washers, and nuts that attach the spring strut and channel to the outboard forging 32-10-00 Opération (10) Remove the spring strut from the fuselage forgings 32-10-00 Opération (a) Record the shims put below the inboard end of the spring 32-10-00 Opération (b) Identify the shims to be sure they are replaced correctly after the installation of the landing gear 32-10-00 Opération A. Remove the Brake Line Fairing 32-10-00 Étape NOTE: It is important for the surfaces to be dry and clean 32-10-00 Note CAUTION: Solvent must not be used on vinyl fairing 32-10-00 Caution (1) Remove the brake fairing. Refer to Remove Main Landing Gear Brake Fairing 32-10-00 Opération 2) Disconnect the brake line at the brake assembly 32-10-00 Opération (a) Put a cap on or a plug in the line and fitting to prevent contamination 32-10-00 Opération (3) Remove the brake line out of the clip and move the line away from the strut 32-10-00 Opération (4) Remove the brake line fairing from the airplane 32-10-00 Opération (5) Remove all of the original adhesive, as well as any rust, paint or scale, with a wire brush and sandpaper 32-10-00 Opération (6) Sand the inner surface of the brake fairing 32-10-00 Opération (a) Move the sandpaper marks lengthwise to leave primer on the strut 32-10-00 Opération (7) Thoroughly clean the bonding surfaces 32-10-00 Opération (a) Remove all of the solvent with a clean, dry cloth if a solvent is used 32-10-00 Opération (8) Let the surfaces be slightly roughed or abraded, and prevent deep scratches or nicks 32-10-00 Opération A. Remove The Main Landing Gear Step 32-10-00 Étape CAUTION: Do not finish sand the parts. A slightly roughened surface is necessary to achieve a good bond 32-10-00 Caution (1) Tap the main landing gear step out of position to remove it. Use a non-metallic tool 32-10-00 Opération (2) Use 180 grit aluminum oxide sandpaper or cloth to remove all the corrosion and old adhesive from the step 32-10-00 Opération (3) Use 180 grit aluminum oxide sandpaper or cloth to remove the old adhesive and any corrosion from the area on the main landing gear spring that the step will be bonded to 32-10-00 Opération (4) Remove all the deep nicks or scratches 32-10-00 Opération A. Remove The Main Landing Gear Brake Clip 32-10-00 Étape CAUTION: Do not finish sand the parts. A slightly roughened surface is necessary to achieve a good bond 32-10-00 Caution (1) Tap the brake clip out of position with a non-metallic tool 32-10-00 Opération (2) Remove all corrosion and old adhesive by hand sanding. Use 180 grip aluminum oxide cloth or paper 32-10-00 Opération (3) Remove all deep nicks or scratches 32-10-00 Opération NOSE LANDING GEAR - MAINTENANCE 32-20-00 Processus NOTE: Hydraulic fluid will drain from strut as lower strut is pulled from upper strut 32-20-00 Note NOTE: Lower strut and fork are press fit, drilled on assembly. Separation of these parts is not recommended, except for installation of new parts 32-20-00 Note NOTE: Install backup rings with concave surface next to O-ring 32-20-00 Note NOTE: Ensure that beveled edge of bearing is installed up next to lock ring 32-20-00 Note NOTE: Hydraulic fluid will drain from strut as lower strut is pulled from upper strut 32-20-00 Note NOTE: Lower strut and fork are press fit, drilled on assembly. Separation of these parts is not recommended, except for installation of new parts 32-20-00 Note NOTE: Ensure that beveled edge of bearing is installed up next to lock ring 32-20-00 Note NOTE: There is no inspection or overhaul requirement for the Lord Shimmy Damper 32-20-00 Note NOTE: Shop low pressure air applied to the filler port may be needed to force floating piston from rod assembly. Care must be exercised to prevent too much air being applied, shooting the piston out of the rod and creating a safety hazard. It is advi 32-20-00 Note NOTE NOTE 32-20-00 Note WARNING: Make sure the strut is fully deflated before removing bolt through collar and upper trunnion, lock ring from lower strut, or bolt securing fork to lower strut 32-20-00 Warning WARNING: Make sure strut is fully deflated before removing bolt through collar and upper trunnion, lock ring from lower strut, or bolt securing fork to lower strut 32-20-00 Warning WARNING: Make sure rudder moves in the correct direction when you operate the trim wheel 32-20-00 Warning CAUTION: Damage will result if correct clearance is not set between the tire and scraper. You must do a check of the clearance every time the scraper has been disturbed or the tire is changed and when you install the speed fairings. If any mud, snow 32-20-00 Caution CAUTION: Damage can result to the fairings if the tire pressure is not correct 32-20-00 Caution CAUTION: Damage will result if correct clearance is not set between the tire and scraper. You must do a check of the clearance every time the scraper has been disturbed or the tire is changed and when you install the speed fairings. If any mud, snow 32-20-00 Caution CAUTION: Damage will result to the fairings if the tire pressure is not correct 32-20-00 Caution bearing is defective 32-20-00 Caution CAUTION: Rig the rudder control system before you rig the trim system 32-20-00 Caution A. Remove the Nose Wheel Speed Fairing 32-20-00 Étape WARNING: Ensure strut is deflated completely before removing bolt that attaches speed fairing to strut or disconnecting torque link 32-20-00 Warning DETAIL A 1210T1001 A12421005 Nose Landing Gear Installation Figure 201 (Sheet 1) 32-20-00 Document FULL EXTENSION OF THE STRUT. 1210T1001 AA12421013 C12421014 D12421010 Nose Landing Gear Installation Figure 201 (Sheet 2) 32-20-00 Document STANDARD NOSE LANDING GEAR SHOCK STRUT VIEW B-B E12421007 BB07421011 Nose Landing Gear Installation Figure 201 (Sheet 3) 32-20-00 Document HEAVY-DUTY NOSE LANDING GEAR SHOCK STRUT VIEW B-B E12421007 BB07421011 Nose Landing Gear Installation Figure 201 (Sheet 4) 32-20-00 Document (281.99 mm, +6.35 OR -6.35 mm) Y F12101008 VIEW D-D F12421009 CC12421011 HEAVY-DUTY DD12421012 Nose Landing Gear Installation Figure 201 (Sheet 5) 32-20-00 Document (1) Deflate the nose gear strut completely 32-20-00 Opération (2) Weight or tie down tail of airplane to raise nose wheel from floor 32-20-00 Opération (3) Remove the nose wheel axle stud 32-20-00 Opération (4) Disconnect the lower torque link from the lower strut. Let the strut extend 32-20-00 Opération (5) Remove the bolt that attach the speed fairing, cover plate and tow bar spacers to the strut 32-20-00 Opération (6) Slide the speed fairing up and remove the nose wheel. Loosen the scraper as necessary 32-20-00 Opération (7) Turn the speed fairing 90 degrees to the center line of the airplane and move the fairing down over the fork to remove 32-20-00 Opération C. Remove the Heavy Duty Nose Wheel Speed Fairing 32-20-00 Étape NOTE: Hydraulic fluid will drain from strut as lower strut is pulled from upper strut 32-20-00 Note WARNING: Ensure strut is deflated completely before removing bolt that attaches speed fairing to strut or disconnecting torque link 32-20-00 Warning (1) Weight or tie down tail of airplane to raise nose wheel from floor 32-20-00 Opération (2) Remove nose wheel axle stud 32-20-00 Opération (3) Deflate nose gear strut completely 32-20-00 Opération 4) Disconnect lower torque link from aft fork fitting and allow strut to extend 32-20-00 Opération 5) Remove bolt securing speed fairing, long spacer and tow bar spacers to forward fork fitting 32-20-00 Opération 6) Slide speed fairing up and remove nose wheel. Loosen scraper as necessary 32-20-00 Opération Use a rod or long punch inserted through one ferrule to tap the opposite ferrule out of the fork. Remove both ferrules and remove nose wheel from fork 32-20-00 Opération (8) Remove lock ring from inside of lower end of upper strut. A small hole is provided in the lock ring groove to facilitate removal. Refer to Heavy-Duty Nose Gear Shock Strut Disassembly/ Assembly 32-20-00 Opération (9) Using a straight, sharp pull, remove lower strut from upper strut 32-20-00 Opération (10) Remove speed fairing up over lower strut 32-20-00 Opération A. Remove the Nose Landing Gear 32-20-00 Étape (1) Weight or tie down tail of airplane to raise nose wheel from floor. Remove engine cowl. Refer to Chapter 71, Cowl - Maintenance Practices 32-20-00 Opération (3) Disconnect nose wheel steering bungee from steering arm 32-20-00 Opération (4) Remove bolt and washers to disconnect drag link where it attaches to lower trunnion. Note position of washers during removal of bolt for reinstallation 32-20-00 Opération (5) Remove carpet on each side of tunnel at firewall for access to upper trunnion bolts. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 32-20-00 Opération (6) Remove bolts to disconnect upper trunnion from fittings in tunnel structure 32-20-00 Opération (7) Remove nose gear 32-20-00 Opération A. Shimmy Damper Removal 32-20-00 Étape (1) Remove cotter pin, nut, bolt, and washers from the damper piston rod end. Remove the safety wire, bolts, and washers that attach the barrel to the nose wheel steering torque arm 32-20-00 Opération (3) Remove the shimmy damper. For airplanes with the Lord Shimmy Damperi installed, discard the Lord Shimmy Damper. Do not do a disassembly/assembly of the Lord Shimmy Damper 32-20-00 Opération A. Remove the Nose Wheel Steering 32-20-00 Étape BUNGEE CLAMP RUDDER BAR ARM DETAIL B XXXXTXXXX Nose Wheel Steering Installation Figure 203 (Sheet 1) 32-20-00 Document (1) Remove pilot's and copilot's seats. Refer to Chapter 25, Front Seats - Maintenance Practices Remove pedestal cover 32-20-00 Opération (3) Loosen rudder trim chain on lower idler sprocket, on forward side of pedestal 32-20-00 Opération 4) Remove nut, bolt, stop, and chain guard 32-20-00 Opération 5) Remove cable guard from steering bungee sprocket 32-20-00 Opération 6) Remove nut, washer, and bolt securing steering bungee to rudder bar arm 32-20-00 Opération (7) Remove chain from steering bungee sprocket 32-20-00 Opération 8) Remove clamp securing boot to steering bungee 32-20-00 Opération (9) Remove nut, washer, and bolt securing bungee to nose gear steering arm and remove bungee 32-20-00 Opération MAIN LANDING GEAR WHEEL - MAINTENANCE 32-40-00 Processus NOTE: Make sure the wheel alignment shims are installed in the same position from where they where removed 32-40-00 Note NOTE: A soft bristle brush can be used to remove hardened grease, dust or dirt 32-40-00 Note Inspect the wheel halves for cracks or damage 32-40-00 Note NOTE: The tire and tube manufacturing process tolerance lets a specified quantity of static unbalance 32-40-00 Note WARNING: Do not separate the wheel halves with the tire and tube inflated or serious injury will result 32-40-00 Warning CAUTION: Damage will result if the correct clearance is not set between the tire and scraper. You must do a check of the clearance every time the scraper is disturbed, the tire is changed, or when you install the speed fairings. If any mud, snow or i 32-40-00 Caution CAUTION: Damage can result to the fairings if the tire pressure is not correct 32-40-00 Caution CAUTION: You must be careful to prevent tire tool damage when you remove the tire from the wheel halves 32-40-00 Caution CAUTION: Bearing cups (races) are a press fit in wheel halves, and must not be removed unless a new part is to be installed 32-40-00 Caution CAUTION: Incorrect torque of the nuts will cause failure of the bolts and wheel 32-40-00 Caution CAUTION: Do not use impact wrenches on thru-bolts or nuts 32-40-00 Caution A. Remove the Main Wheel 32-40-00 Étape NOTE: The wheel removal is not necessary to reline the brakes or to remove the brake parts, other than the brake disc on the torque plate 32-40-00 Note Main Landing Gear Wheel and Axle Installation Figure 201 (Sheet 1) 32-40-00 Document (1) Jack the airplane. Refer to Chapter 7, Jacking - Maintenance Practices 32-40-00 Opération 2) Remove the speed fairing if installed. Refer to Main Landing Gear - Maintenance Practices 32-40-00 Opération (3) Remove the hub caps (if installed), cotter pin and axle nut 32-40-00 Opération (4) Remove the bolts that attach the brake back plate to the brake cylinder and remove the back plate 32-40-00 Opération (5) Pull the wheel from the axle 32-40-00 Opération A. Remove the Main Wheel Axle 32-40-00 Étape (1) Jack the airplane. Refer to Chapter 7, Jacking - Maintenance Practices 32-40-00 Opération (2) Remove the main wheel speed fairing and brake fairing. Refer to Main Landing Gear - Maintenance Practices 32-40-00 Opération (3) Remove main landing gear wheel. Refer to Main Wheel Removal/Installation 32-40-00 Opération (4) Disconnect, drain and put a cap or plug on the hydraulic brake line at the wheel brake cylinder 32-40-00 Opération (5) Write the number and position of the wheel alignment shims between axle and fitting when you remove the axle from the strut fitting 32-40-00 Opération (6) Mark the shims or tape together SO they can be installed in the same position to make sure the wheel alignment is not disturbed 32-40-00 Opération (7) Remove nuts, washers, and bolts that attach the shims, axle, brake components, and speed fairing mounting plate from the strut 32-40-00 Opération NOSE LANDING GEAR WHEEL - MAINTENANCE 32-41-00 Processus NOTE: Bearing cups are a press fit in wheel half and should not be removed unless a new part is to be installed 32-41-00 Note WARNING: Serious injury can result from attempting to separate wheel halves with tire and tube inflated 32-41-00 Warning CAUTION: Uneven or improper torque of the nuts can cause failure of the bolts with resultant wheel failure 32-41-00 Caution CAUTION: Do not use impact wrenches on thru-bolts or nuts 32-41-00 Caution A. Remove Nose Landing Gear Wheel 32-41-00 Étape Nose Landing Gear Wheel Installation Figure 201 (Sheet 1) 32-41-00 Document FERRULE DETAIL C B1242R1001 C1242R1008 Nose Landing Gear Wheel Installation Figure 201 (Sheet 2) 32-41-00 Document (1) Weight or tie down tail of airplane to raise nose wheel from floor 32-41-00 Opération (2) Airplanes equipped with speed fairing remove: speed fairing. Refer to Nose' Wheel Speed Fairing Removal/Installation 32-41-00 Opération (3) Remove nose wheel axle stud 32-41-00 Opération (4) Remove furrels from nose wheel and pull nose wheel assembly from fork 32-41-00 Opération BRAKE SYSTEM - MAINTENANCE 32-42-00 Processus NOTE: Brake assemblies described are normally for left hand-reverse fittings and torque plate bushings for right hand installation 32-42-00 Note NOTE: A special tool, brake master cylinder wrench Proto Stanley Par No. C418 to remove brake master cylinder cover 32-42-00 Note NOTE: FILLER PLUG MUST BE VENTED SO PRESSURE CANNOT BUILD UP IN THE RESERVOIR DURING BRAKE OPERATION 32-42-00 Note NOTE: A rivet setting kit is available from Cessna Aircraft Company 32-42-00 Note A. Remove Brake Master Cylinders 32-42-00 Étape Brake Master Cylinder Installation Figure 201 (Sheet 1) 32-42-00 Document (1) Remove brake fairings for access to brake bleeder screws 32-42-00 Opération 2) Drain hydraulic fluid from brake master cylinders 32-42-00 Opération (3) Remove pilot's seat. Refer to Chapter 25, Front Seats - Maintenance Practices 32-42-00 Opération (4) Remove shield assembly from pilot's rudder pedals 32-42-00 Opération (5) Disconnect hoses from master cylinders and cap or plug hoses 32-42-00 Opération (6) Disconnect master cylinders at pilot's rudder pedals 32-42-00 Opération (7) Remove cotter pins and pins securing lower end of brake master cylinders and remove brake master cylinders 32-42-00 Opération A. Remove Brake Lining 32-42-00 Étape (1) Remove brake fairing and speed fairing. Refer to Main Landing Gear - Maintenance Practices 32-42-00 Opération (2) Remove bolts securing back plate and remove back plate 32-42-00 Opération (3) Pull brake cylinder out of torque plate and slide pressure plate off anchor bolts 32-42-00 Opération (4) Place back plate on a table with lining side down flat 32-42-00 Opération 5) Center a 9/64-inch (3.58 mm) (or slightly smaller) punch in the rolled rivet and hit the punch sharply with a hammer. Punch out all rivets securing the linings to the back plate and pressure plate in the same manner 32-42-00 Opération A. Remove parking Brake System 32-42-00 Étape Parking Brake Installation Figure 203 (Sheet 1) 32-42-00 Document (1) Remove pilot's seat. Refer to Chapter 25, Front Seats - Maintenance Practices 32-42-00 Opération 2) Remove shield assembly from pilot's rudder pedals 32-42-00 Opération (3) Disconnect spring from bellcrank 32-42-00 Opération (4) Remove cotter pin from positioning pin and remove pin and cable from rod 32-42-00 Opération (5) Remove nut, bolt, and pulley from lower end of bellcrank 32-42-00 Opération (6) Remove nuts from both ends of tube and remove tube and cable assembly 32-42-00 Opération 7) Remove cotter pins and disconnect park brake cable from rudder pedals 32-42-00 Opération (8) Remove nut, washer, and bolt and remove pulley and brake cable from upper end of bellcrank 32-42-00 Opération FLOOD LIGHTING - MAINTENANCE 33-10-00 Processus WARNING: Obey all oxygen safety precautions on airplanes that have the oxygen panel installed in the overhead console. Refer to the oxygen maintenance practices for correct procedures to use when you must do maintenance on or near the oxygen lines 33-10-00 Warning A. Floodlight Bulb Removal 33-10-00 Étape NOTE: Removal/Installation is typical for all floodlight bulbs 33-10-00 Note CAUTION: The floodlight bulb can break if too much pressure is applied when you remove and install it 33-10-00 Caution CONSOLE DETAIL A 1210T1001 AIRPLANES WITHOUT GARMIN G1000 A1219T1011 A1219T1012 B0519T1059 Flood Light Installation Figure 201 (Sheet 1) 33-10-00 Document B D LIGHT C LIGHT ASSEMBLY DETAIL A AIRPLANES WITH GARMIN G1000 OXYGEN RUBBER PANEL LENS WASHER FILTER 1210T1001 CAP A1219T1058 B0519T1105 DETAIL D C2618T1153 D0719T1055 Flood Light Installation Figure 201 (Sheet 2) 33-10-00 Document (1) Press the lens holder up and turn it counterclockwise 33-10-00 Opération 2) Remove the lens holder 33-10-00 Opération (3) Carefully push the bulb up and turn it counterclockwise 33-10-00 Opération (4) Remove the bulb 33-10-00 Opération A. Light Assembly Removal 33-10-00 Étape NOTE: Removal and installation is typical for the three overhead dome light assemblies 33-10-00 Note CAUTION: Support the overhead console when you remove the screws to prevent damage to the electrical wiring in the overhead console 33-10-00 Caution (1) Put the ALT/BAT MASTER switch in the off position 33-10-00 Opération L Remove the screws that attach the overhead console to the attach brackets 33-10-00 Opération 3) Identify, tag, and disconnect the electrical wires from the light assembly 33-10-00 Opération (4) Remove the light assembly from the overhead console 33-10-00 Opération A. Light Assembly Switch Removal 33-10-00 Étape NOTE: Removal and installation of the overhead dome light assembly switches is typical. The switch for the rear light assembly also controls lighting for the under wing courtesy lights 33-10-00 Note CAUTION: Support the overhead console when you remove the screws to prevent damage to the electrical wiring in the overhead console 33-10-00 Caution (1) Put the ALT/BAT MASTER switch in the off position 33-10-00 Opération Remove the overhead console from the attach brackets 33-10-00 Opération (3) Identify, tag, and disconnect the wires from the switch 33-10-00 Opération (4) Remove the switch from the overhead console 33-10-00 Opération A. Potentiometer Removal 33-10-00 Étape CAUTION: Support the overhead console when you remove the screws to prevent damage to the electrical wiring in the overhead console 33-10-00 Caution (1) Put the ALT/BAT MASTER switch in the off position 33-10-00 Opération Remove the overhead console from the attach brackets 33-10-00 Opération 3) Identify, tag, and disconnect the wires from the switch 33-10-00 Opération (4) Remove the knob assembly and the jam nut from the potentiometer 33-10-00 Opération (5) Remove the potentiometer from the overhead console 33-10-00 Opération A. Oxygen Panel Light Bulb Removal 33-10-00 Étape CAUTION: The floodlight bulb can break if too much pressure is applied when you remove and install it 33-10-00 Caution (1) Put the ALT/BAT MASTER switch in the off position. Remove the oxygen panel light assembly 33-10-00 Opération (3) Carefully turn the bulb counterclockwise 33-10-00 Opération (4) Remove the bulb from the light assembly 33-10-00 Opération A. Oxygen Panel Light Assembly Removal 33-10-00 Étape (1) Put the ALT/BAT MASTER switch in the off position 33-10-00 Opération (2) Turn the cap on the oxygen panel light assembly counterclockwise 33-10-00 Opération (3) Remove the cap, washer, and light assembly from the oxygen panel 33-10-00 Opération GLARESHIELD LIGHT - MAINTENANCE 33-11-00 Processus NOTE: Apply the Velcro strips to the edge of the lens as necessary to prevent light leakage around lens 33-11-00 Note NOTE: Two spacers are installed between the panel and bulkhead that use two screws which attach the right side of the panel 33-11-00 Note CAUTION: Do not bend the light strip. The light strip will be easily damaged when it is not supported in the glareshield 33-11-00 Caution A. Remove the Glareshield Light 33-11-00 Étape NOTE: Note location of the two spacers installed between the panel and bulkhead for installation of copilot instrument panel assembly 33-11-00 Note NOTE: Velcro strips are located on the edge of the lens to prevent light leakage around the lens 33-11-00 Note LOOKING UP FROM UNDER GLARESHIELD 1210T1001 A1219T1015 AA1218T1038 Glareshield Light Figure 201 (Sheet 1) 33-11-00 Document (1) Set the MASTER ALT/BAT switch to the off position 33-11-00 Opération (2) Remove the screws in the copilot instrument panel to get access to the glareshield light connector. Refer to Chapter 31, Instrument and Control Panels - Maintenance Practices 33-11-00 Opération (3) Disconnect the glareshield light connector 33-11-00 Opération (4) Remove the screws that attach the lens to the glareshield 33-11-00 Opération (5) Remove the light from the light clips 33-11-00 Opération CAUTION: Do not bend the light strip. The light strip will be easily damaged when it is not supported in the glareshield 33-11-00 Caution LOOKING UP FROM UNDER GLARESHIELD 1210T1001 A1214T1033 AA0719T1015 Glareshield Light Figure 202 (Sheet 1) 33-11-00 Document (1) Set the MASTER ALTIBAT switch to the off position 33-11-00 Opération L) Remove the screws that attach the light strip to the glareshield 33-11-00 Opération 3) Remove the front screw in each outboard offset plate 33-11-00 Opération (4) Loosen the aft screw installed in each outboard offset plate SO that the offset plate can turn 33-11-00 Opération (5) Carefully remove the light strip from the glareshield 33-11-00 Opération A. Remove the Power Supply (U1001) 33-11-00 Étape (1) Set the MASTER BATIALT switch to the off position. Remove the copilot instrument panel. Refer to Chapter 31, Instrument and Control Panels - Maintenance Practices 33-11-00 Opération (3) Disconnect the glareshield light connector (J2) and the glareshield power: supply connector (P2) 33-11-00 Opération (4) Disconnect the connectors (P1) and (JI032) 33-11-00 Opération (5) Remove the screws that attach the power supply (U1001) and remove it from the airplane 33-11-00 Opération PEDESTAL LIGHTING - MAINTENANCE 33-12-00 Processus CAUTION: For proper heat dissipation, attaching tab of reflector must be sandwiched between panel assembly and light cover assembly 33-12-00 Caution CAUTION: For proper heat dissipation, attaching tab of reflector must be sandwiched between pedestal cover assembly and light cover assembly 33-12-00 Caution INSTRUMENT LIGHTING - MAINTENANCE 33-13-00 Processus A. Remove the Dimming Assembly 33-13-00 Étape AND AIRPLANES T20608438 AND ON A1218T1005 A1218T1074 Dimming Module Assembly Installation Figure 202 (Sheet 1) 33-13-00 Document (1) Remove electrical power from airplane 33-13-00 Opération (2) Set the MASTER ALT BAT switch to the OFF position 33-13-00 Opération (3) Remove the copilot instrument panel assembly to get access to the dimming assembly. Refer to Chapter 31, Instrument and Control Panels - Maintenance Practices 33-13-00 Opération (4) Disconnect the electrical connectors (J1003 and J1026) 33-13-00 Opération (5) Remove the screws that attach the dimming assembly to the support assembly 33-13-00 Opération (6) Remove the dimming assembly from the airplane 33-13-00 Opération RADIO LIGHTING - MAINTENANCE 33-14-00 Processus A. Remove Dimming Control 33-14-00 Étape NOTE: Two dimming control potentiometers are located on the circuit panel assembly. One dimming control serves as the radio lighting (RADIO LT) and instrument lighting (PANEL LT) dimming control, the second dimming control serves as the glareshield l 33-14-00 Note Dimming Control Installation Figure 201 (Sheet 1) 33-14-00 Document (1) Remove electrical power from airplane. Position MASTER BATIALT switch to OFF 33-14-00 Opération (2) Remove circuit panel assembly. Refer to Chapter 31, Instrument and Control Panels - Maintenance Practices 33-14-00 Opération (3) Loosen setscrew on knob and remove knob to access nut securing dimming control to circuit panel assembly 33-14-00 Opération (4) Remove nut securing dimmer control to circuit panel assembly 33-14-00 Opération (5) Identify, tag, and unsolder wires connected to dimming control 33-14-00 Opération (6) Remove dimming control from airplane 33-14-00 Opération PILOT CONTROL WHEEL LIGHTING - MAINTENANCE 33-15-00 Processus NOTE: Once a discrepancy has been found and repaired, iti is not necessary to do the remainder of the troubleshooting procedure 33-40-00 Note A. Remove Map Light Assembly 33-15-00 Étape Map Light Assembly and Potentiometer Installation Figure 201 (Sheet 1) 33-15-00 Document (1) Remove electrical power from airplane. Position the LIGHTS NAV switch to the OFF position 33-15-00 Opération L Remove nut, washer, and bolt securing map light bracket to control wheel 33-15-00 Opération 3) Remove map light assembly from control wheel 33-15-00 Opération (4) Identify, tag, and disconnect map light assembly wiring 33-15-00 Opération (5) Remove map light assembly from airplane 33-15-00 Opération A. Remove Map Light Potentiometer 33-15-00 Étape (1) Remove electrical power from airplane. Position the LIGHTS NAV switch to the OFF position 33-15-00 Opération 2) Loosen setscrew securing knob assembly to map light potentiometer. Remove knob assembly 33-15-00 Opération (3) Remove nut and washer securing map light potentiometer to control wheel 33-15-00 Opération (4) Pull map light potentiometer out of control wheel to access electrical wires 33-15-00 Opération (5) Identify, tag, and disconnect wires from map light potentiometer 33-15-00 Opération (6) Remove map light potentiometer from airplane 33-15-00 Opération NAVIGATION AND STROBE LIGHTS - MAINTENANCE 33-40-00 Processus NOTE: If wing tip was removed to access strobe connector, then strobe connector will already be positioned in the wing tip 33-40-00 Note CAUTION: Use protective gloves or cotton wrap to ensure fingertip oil does not come in contact with strobe tube assembly 33-40-00 Caution CAUTION: Following placing lens unto strobe tube assembly, verify that braided ground wire is properly positioned inside of lens and between the lens and strobe tube assembly 33-40-00 Caution A. Wing Tip Navigation Light Lamp Removal and Installation 33-40-00 Étape NOTE: Removal and installation is typical for the left and right wing tip navigation light lamps 33-40-00 Note (1) Remove Wing Tip Navigation Light Lamp 33-40-00 Étape DETAIL C GROUND WIRE DETAIL B 1210T1001 Navigation and Strobe Light Installation Figure 201 (Sheet 1) 33-40-00 Document Navigation and Strobe Light Installation Figure 201 (Sheet 2) 33-40-00 Document Navigation and Strobe Light Installation Figure 201 (Sheet 3) 33-40-00 Document (a) Remove electrical power from airplane. Position LIGHTS NAVIOFF switch on circuit panel assembly to OFF 33-40-00 Opération (b) Remove screws securing lens shield to wing tip 33-40-00 Opération (C) Remove lens from navigation light assembly 33-40-00 Opération d) Grasp lamp, depress slightly and turn counterclockwise to release and remove lamp from bayonet mount 33-40-00 Opération B. Tail Navigation Light Lamp Removal and Installation 33-40-00 Étape (1) Remove Tail Navigation Light Lamp 33-40-00 Étape (a) Remove electrical power from airplane. Position LIGHTS NAVIOFF switch on circuit panel assembly to OFF 33-40-00 Opération (b) Remove screws securing lens retainer to mount 33-40-00 Opération (c) Remove lens to gain access to lamp 33-40-00 Opération (d) Grasp lamp, depress slightly and turn counterclockwise to release and remove lamp from bayonet mount 33-40-00 Opération A. Remove the LED Wing Tip Navigation Lights 33-40-00 Étape LED Navigation Light Installation Figure 202 (Sheet 1) 33-40-00 Document (1) Make sure the electrical power is off 33-40-00 Opération (2) Remove the wing tip 33-40-00 Opération (3) Disconnect the electrical connections for the navigation light and strobe light 33-40-00 Opération (4) Remove the lens shield from the wing tip 33-40-00 Opération (5) Remove the shroud from the light assembly 33-40-00 Opération (6) Remove the light assembly 33-40-00 Opération C. Remove Tailcone-Mounted Navigation Light 33-40-00 Étape (1) Make sure the electrical power is off 33-40-00 Opération 2) Remove the screws that attach the light assembly 33-40-00 Opération (3) Pull the light out of the stinger 33-40-00 Opération (4) Disconnect the electrical connector 33-40-00 Opération A. Remove Strobe Tube Assembly 33-40-00 Étape NOTE: Removal and installation is typical for both the right and left strobe tube assemblies 33-40-00 Note NOTE: Following removal of lens shield and prior to removing the strobe light lens, note the placement of the braided ground wire positioned on the inside of the lens between the lens and strobe tube assembly 33-40-00 Note NOTE: If the strobe connector cannot be retrieved from inside of wing tip, it will be necessary to remove wing tip to gain access to strobe connector 33-40-00 Note CAUTION: If strobe tube assembly is being removed to facilitate other maintenance and not being replaced with new strobe tube assembly, then use protective gloves or cotton wrap to ensure fingertip oil does not come in contact with strobe tube assemb 33-40-00 Caution (1) Remove electrical power from airplane. Position LIGHTS STROBE/OFF switch on circuit panel assembly to OFF 33-40-00 Opération (2) Remove screws securing lens shield to wing tip 33-40-00 Opération (3) Remove lens from front of strobe tube assembly 33-40-00 Opération (4) Carefully pull the strobe light assembly wiring to retrieve the strobe connector from inside the wing tip. Disconnect strobe connector 33-40-00 Opération (5) Remove strobe tube assembly from base assembly and remove from wing tip 33-40-00 Opération A. Remove Strobe Power Supply 33-40-00 Étape NOTE: Removal and installation is typical for both the left and right strobe power supplies 33-40-00 Note NOTE: Note the screw location used for installation of the strobe power supply ground wire and the braided ground wire from the lens for the strobe tube assembly 33-40-00 Note (1) Remove electrical power from airplane. Position LIGHTS STROBE/OFF switch on circuit panel assembly to OFF 33-40-00 Opération Remove wing tip to access strobe power supply 33-40-00 Opération (3) Disconnect the strobe connector and strobe power supply connector 33-40-00 Opération (4) Remove screws securing strobe power supply to wing tip rib assembly 33-40-00 Opération (5) Remove strobe power supply from airplane 33-40-00 Opération A. Remove the Strobe Light Assembly 33-40-00 Étape NOTE: Removal and installation is typical for both the right and left strobe light assemblies 33-40-00 Note (1) Remove the electrical power from airplane 33-40-00 Opération (a) Put the LIGHTS STROBE/OFF switch to the OFF position 33-40-00 Opération L Remove the wing tip 33-40-00 Opération J Remove the screws, nuts, and washers that attach the strobe light to wing tip 33-40-00 Opération 4) Remove the shield from airplane 33-40-00 Opération 5) Disconnect the electrical connector from the strobe light 33-40-00 Opération 6) Remove the strobe light from airplane 33-40-00 Opération A. Remove the LED strobe light assembly 33-40-00 Étape NOTE: Removal and installation is typical for both the right (FR008) and left (FL012) LED strobe light assemblies 33-40-00 Note (1) Make sure the electrical power to the airplane is OFF. Remove the wing-tip. Refer to Chapter 57, Wings and Wing Struts - Maintenance Practices, Wing-Tip Removal/Installation 33-40-00 Opération 0 Remove the screws that secure the shield and LED strobe light assembly to the airplane. Remove the shield from the airplane 33-40-00 Opération (5) Disconnect the electrical connector for the LED strobe light assembly 33-40-00 Opération (6) Remove the LED strobe light assembly from the wing-tip 33-40-00 Opération VERTICAL FIN FLASHING BEACON - MAINTENANCE 33-41-00 Processus NOTE: During correct operation the beacon will flash at a rate of 45 flashes per minute, +5 or -5 flashes per minute 33-41-00 Note NOTE: The troubleshooting procedure is typical for the landing light and taxi light 33-42-00 Note CAUTION: Use protective gloves or cotton wrap to ensure fingertip oil does not come in contact with lamp assembly 33-41-00 Caution A. Remove Flashing Beacon Lamp 33-41-00 Étape CAUTION: Use protective gloves or cotton wrap to ensure fingertip oil does not come in contact with lamp assembly 33-41-00 Caution Flashing Beacon Light Installation Figure 201 (Sheet 1) 33-41-00 Document (1) Remove electrical power from airplane. Position LIGHTS BCN/OFF switch to OFF 33-41-00 Opération 2 Loosen screw on clamp around flashing beacon light assembly and remove clamp 33-41-00 Opération (3) Remove lens from flasher base assembly 33-41-00 Opération (4) Remove lamp assembly from flasher base assembly 33-41-00 Opération A. Remove the LED Beacon 33-41-00 Étape LED Flashing Beacon Light Installation Figure 202 (Sheet 1) 33-41-00 Document (1) Make sure the electrical power is off 33-41-00 Opération 2) Remove the screws and washers that attach the lens retainer 33-41-00 Opération (3) Remove the lens retainer, lens and lens gasket 33-41-00 Opération (4) Remove the screws that attach the beacon 33-41-00 Opération (5) Lift the beacon out of the cap assembly 33-41-00 Opération (a) Make sure the mounting gasket is removed 33-41-00 Opération (6) Disconnect the electrical connector 33-41-00 Opération LANDING/TAXI LIGHTS - MAINTENANCE 33-42-00 Processus NOTE: The tops of the nuts are not flush with the lip of the plate. The remaining parts of the nuts are behind the plate at the screw opening 33-42-00 Note NOTE: Some airplanes that have the HID landing and taxi lights will have an aluminum ring installed between the HID landing and taxi lights and the bracket 33-42-00 Note NOTE: The troubleshooting procedure is typical for the left and right LED LTR lights 33-42-05 Note CAUTION: Do not install the HID ballast to the support bracket without the nylon shoulder washers between the HID ballast and the support bracket and the nylon washers between the HID ballast and the screw head. Ifthe HID ballast is installed without 33-42-00 Caution A. Remove the Light 33-42-00 Étape NOTE: Removal and installation is typical for incandescent and HID landing and taxi lights 33-42-00 Note NOTE: Some airplanes that have the HID landing and taxi lights will have an aluminum ring installed between the HID landing and taxi lights and the bracket 33-42-00 Note NOT INCORPORATING MK206-33-01 1210T1001 A0728T001 Landing and Taxi Light Installation Figure 201 (Sheet 1) 33-42-00 Document INCORPORATING MK206-33-01 1210T1001 A1228T1001 Landing and Taxi Light Installation Figure 201 (Sheet 2) 33-42-00 Document (1) Disconnect the main battery from the airplane. Refer to Chapter 24, Battery - Maintenance Practices 33-42-00 Opération 2) Set the landing light and the taxi light switches to OFF 33-42-00 Opération 3) Remove the screws that attach the lens assembly to the leading edge of the wing 33-42-00 Opération (4) Remove the screws, brackets, and nuts which hold the light in position against the plate 33-42-00 Opération (5) Disconnect the electrical wires from the back side of the light and remove the light from the airplane 33-42-00 Opération A. Remove the HID ballast 33-42-00 Étape NOTE: The procedures that follow are for airplanes that have the HID landing and taxi light installation 33-42-00 Note NOTE: Removal and installation procedures are typical for the HID landing and taxi lights 33-42-00 Note (1) Disconnect the main battery from the airplane. Refer to Chapter 24, Battery - Maintenance Practices 33-42-00 Opération 2) Put the landing and taxi light switches in the OFF position 33-42-00 Opération 3) Remove the HID landing and taxi lights. Refer to Light Removal and Installation 33-42-00 Opération (4) Remove the screws and nylon washers that attach the HID ballast to the support bracket on the wing leading-edge rib 33-42-00 Opération (5) Disconnect the electrical connectors from the HID ballast 33-42-00 Opération (a) Landing light connectors: PLO10 and UL005 33-42-00 Opération (b) Taxi light connectors: PL011 and UL006 33-42-00 Opération (6) Remove the HID ballast from the airplane 33-42-00 Opération LANDING/TAXI/RECOGNITION LIGHTS - MAINTENANCE 33-42-05 Processus NOTE: The light is symmetrical. There is not a defined top or bottom of the light 33-42-05 Note NOTE: The procedures that follow are typical for the left and right LED LTR lights 33-42-05 Note NOTE: A digital inclinometer that can measure to the nearest tenth of a degree is necessary for this procedure 33-42-05 Note NOTE: For this procedure, it is assumed that the light's center beam emits normal to the face of the light 33-42-05 Note NOTE: The approved factory-set vertical aiming is with the light pointing down 3.0 degrees, +0.5 or -0.5 degrees, from the waterline zero 33-42-05 Note NOTE: The horizontal aiming must be checked visually at night on a flat, level, and light colored surface 33-42-05 Note NOTE: To keep the vertical aiming for this adjustment, you must add one washer of half the thickness (0.016 inch) on the center lower mounting screw 33-42-05 Note CAUTION: LEDs are bright to the eye to look at. When you make sure that the LEDs are on, do not look directly into the light face. Look from at least a 45 degree angle 33-42-05 Caution CAUTION: Do not apply a pitot pressure of more than 200 knots or less than 0 knots. This can cause damage to the Standby Airspeed indicator 33-42-05 Caution CAUTION: Do not apply a pitot pressure of less than 0 knots. This can cause damage to the Standby Airspeed indicator 33-42-05 Caution A. Remove the LED Landing, Taxi and Recognition (LTR) Light 33-42-05 Étape NOTE: The removal and installation is typical for the left and right LED LTR lights 33-42-05 Note LED Landing, Taxi and Recognition Light Installation Figure 201 (Sheet 1) 33-42-05 Document (1) Set the MASTER switches to the OFF position Set the Landing/Taxi/Recognition light switch to the OFF position 33-42-05 Opération 3) Disengage the LAND LTS and RECOG/TAXI LTS circuit breakers 33-42-05 Opération 4) Disconnect external power from the airplane 33-42-05 Opération (5) Disconnect the negative terminal from the battery. Refer to Chapter 24 Battery - Maintenance Practices 33-42-05 Opération (6) Remove the screws that attach the lens assembly to the leading edge of the wing 33-42-05 Opération (a) Remove the lens assembly from the airplane 33-42-05 Opération (7) Disconnect the electrical connector (JL012 left or JRO13 right) from the light assembly 33-42-05 Opération (8) Remove the nut and washers that attach the bracket to the spar 33-42-05 Opération (a) Remove the light and bracket from the airplane 33-42-05 Opération (9) Remove the six screws and lock washers that attach the light to the bracket 33-42-05 Opération (a) Remove the light from the bracket 33-42-05 Opération COURTESY LIGHTS - MAINTENANCE 33-43-00 Processus A. Remove the LED Courtesy Wing Light Assembly 33-43-00 Étape NOTE: Removal and Installation is typical for the left and right wing courtesy light lamps 33-43-00 Note SCREW NOTE: RIGHT WING SHOWN, LEFT WING TYPICAL DETAIL A 1210T1001 A1228T1003 Courtesy Light Installation Figure 201 (Sheet 1) 33-43-00 Document Courtesy Light Installation Figure 201 (Sheet 2) 33-43-00 Document (1) Make sure the electrical power is off. Remove the screws that attach the light assembly to the airplane 33-43-00 Opération (3) Disconnect the electrical connector 33-43-00 Opération (4) Remove the light from the airplane 33-43-00 Opération A. Remove the Courtesy Light Lamp 33-43-00 Étape NOTE: Removal and Installation is typical for the left and right wing courtesy light lamps 33-43-00 Note (1) Remove electrical power from the airplane 33-43-00 Opération L Remove the screws that attach the cover assembly to the underside of wing 33-43-00 Opération (3) Remove the bulb 33-43-00 Opération (a) Push the bulb into the socket 33-43-00 Opération (b) Turn the bulb counterclockwise 33-43-00 Opération (c) Remove the bulb from the airplane 33-43-00 Opération PITOT AND STATIC SYSTEMS - MAINTENANCE 34-11-00 Processus NOTE: For airplanes with the optional KAP-140 Two Axis Autopilot but without Garmin G1000, an additional static tube is connected to the autopilot from a tee from the blind encoder 34-11-00 Note NOTE: Apply tape as necessary where plastic and metal connections interface 34-11-00 Note NOTE: If the leakage rate is more than the maximum allowable, first tighten all connections, then do the leakage test again. If the leakage rate is still more than the maximum allowable, do the procedure that follows 34-11-00 Note CAUTION: When you apply or release suction, do not exceed the range of the vertical speed indicator or the airspeed indicator 34-11-00 Caution CAUTION: Do not apply positive pressure with the airspeed indicator or the vertical speed indicator connected to the static pressure system 34-11-00 Caution A. Pitot Tube Assembly Removal 34-11-00 Étape AIRPLANES WITHOUT GARMIN G1000 B1218T1018 Pitot and Static Systems Installation Figure 202 (Sheet 1) 34-11-00 Document Pitot and Static Systems Installation Figure 202 (Sheet 2) 34-11-00 Document (1) Remove electrical power from the airplane. Put thel PITOTI HEAT/OFF switch in the OFF position 34-11-00 Opération 2) Get access to the pitot tube assembly in the left wing 34-11-00 Opération (3) Remove the screws that attach the pitot tube assembly to the wing structure 34-11-00 Opération (4) Disconnect the ram air tube from the pitot tube assembly nipple 34-11-00 Opération (5) Disconnect the electrical wires for the pitot tube heater at the pitot disconnects 34-11-00 Opération (6) Remove the pitot tube assembly from the airplane 34-11-00 Opération A. Remove the Static Button 34-11-00 Étape WARNING: Do not damage the airplane skin or paint while removing the static button. Damage to the airplanes skin or paint can cause disrupt airflow around the static button. This condition can lead to incorrect indication by flight instruments 34-11-00 Warning (1) Remove electrical power from the airplane 34-11-00 Opération 2) Remove the sidewall interior piece. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 34-11-00 Opération (3) Disconnect the static line from static button 34-11-00 Opération (4) Remove the nut and washer from the static button 34-11-00 Opération (5) Break the seal of the sealant around the button 34-11-00 Opération (6) Carefully push the button through the skin from inside the airplane 34-11-00 Opération (7) Remove the sealant that remains 34-11-00 Opération A. Sump Assembly Removal 34-11-00 Étape NOTE: Removal and installation is typical for the left and the right sump assembly 34-11-00 Note (1) Get access to the sump assembly at FS 18.00 34-11-00 Opération (2) Loosen the nut that attaches the static tube to the sump assembly nipple 34-11-00 Opération (3) Turn the sump assembly to remove the sump assembly from the elbow 34-11-00 Opération (4) Remove sump assembly from airplane 34-11-00 Opération A. Alternate Static Source Valve Removal 34-11-00 Étape (1) Behind the stationary control panel, loosen the nuts that attach the two static tubes to the alternate static source valve. Disconnect the static tubes from the alternate static source valve 34-11-00 Opération (2) Remove the screws that attach the alternate static source valve to the stationary control panel 34-11-00 Opération (3) Remove the alternate static source valve from the airplane 34-11-00 Opération A. Blind Encoder Removal 34-11-00 Étape NOTE: The blind encoder is behind the stationary instrument panel on the the right forward fuselage at WL 6.50, at FS 12.35 34-11-00 Note (1) Remove electrical power from the airplane. Disengage the XPNDR and GPS circuit breakers on the avionics circuit breaker panel 34-11-00 Opération 2 Disconnect the static tube from the blind encoder 34-11-00 Opération (3) Disconnect the electrical connector from the blind encoder 34-11-00 Opération (4) Loosen the knurl nut that attaches the blind encoder to the mounting tray 34-11-00 Opération (5) Remove the blind encoder from the airplane 34-11-00 Opération A. Vertical Speed Indicator (VSI) Removal 34-11-00 Étape GYRO TUBE ALTERNATE STATIC TUBE TO AIR DATA SOURCE VALVE COMPUTER TO AIR DATA COMPUTER ROUTES UP FORWARD DETAIL A DOORPOST TO LEFT 1210T1001 WING A0718R1006 AIRPLANES WITH GARMIN G1000 A1218T1045 Airspeed, Altimeter, and Vertical Speed Indicator Inst 34-11-00 Document (1) Remove electrical power from the airplane. Disengage the INST LTS circuit breaker on the circuit panel assembly 34-11-00 Opération (2) Remove the screws that attach the pilot center panel assembly to the structure to get access to the rear of the VSI. Refer to Chapter 31, Instrument and Control Panels - Maintenance Practices 34-11-00 Opération (3) Disconnect the static tube and the vertical speed connector from the VSI 34-11-00 Opération (4) Remove the screws that attach the VSI to the pilot center panel assembly 34-11-00 Opération (5) Remove the VSI from the airplane 34-11-00 Opération A. Altimeter Indicator Removal 34-11-00 Étape (1) Make sure that the MASTER and AVIONIC switches are in the off position. Disengage the INST LTS circuit breaker on the circuit panel 34-11-00 Opération 3) Remove the screws that hold the altimeter to the panel 34-11-00 Opération 4) Carefully pull the panel out to get access to the back of the altimeter 34-11-00 Opération 5) Disconnect the static tubes from the tee on the altimeter indicator 34-11-00 Opération 6) Disconnect the connector from the altimeter 34-11-00 Opération 7) Remove the screws that attach the altimeter to the panel 34-11-00 Opération 8) Remove the altimeter from the airplane 34-11-00 Opération A. Airspeed Indicator Removal 34-11-00 Étape (1) Make sure that the MASTER and AVIONICS switches are in the off position. Disengage the INST LTS circuit breaker on the circuit breaker panel 34-11-00 Opération 3) Remove the screws that hold the airspeed indicator to the panel 34-11-00 Opération 4) Disconnect the pitot tube from the airspeed indicator 34-11-00 Opération 5) Disconnect the static tube from the airspeed indicator 34-11-00 Opération 6) Disconnect the electrical connector (JI009) from the airspeed indicator 34-11-00 Opération 7) Remove the screws that attach the airspeed indicator to the panel 34-11-00 Opération (8) Remove the airspeed indicator from the airplane 34-11-00 Opération OUTSIDE AIR TEMPERATURE (OAT) INDICATING SYSTEM - MAINTENANCE 34-12-00 Processus A. Remove Outside Air Temperature Indicator 34-12-00 Étape a 1210T1001 A0518R1067 Outside Air Temperature System Installation Figure 201 (Sheet 1) 34-12-00 Document (1) Remove electrical power from airplane 34-12-00 Opération 2) Remove screws securing OAT indicator in instrument panel 34-12-00 Opération (3) Gently pull OAT indicator away from instrument panel and disconnect electrical connector 34-12-00 Opération (4) Remove OAT indicator from airplane 34-12-00 Opération A. Remove Outside Air Temperature Probe 34-12-00 Étape (1) Remove electrical power from airplane 34-12-00 Opération (2) Remove headliner to gain access to oat probe. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 34-12-00 Opération (3) Disconnect electrical wiring at splices 34-12-00 Opération (4) Remove jamnut and o-ring from probe, outside of fuselage 34-12-00 Opération (5) Remove probe from airplane 34-12-00 Opération GTP 59 OUTSIDE AIR TEMPERATURE (OAT) PROBE - MAINTENANCE 34-12-01 Processus A. Remove the OAT Sensor 34-12-01 Étape GTP 59 Outside Air Temperature (OAT) Probe Figure 201 (Sheet 1) 34-12-01 Document (1) Disconnect electrical power from the airplane 34-12-01 Opération (2) Remove the headliner above the crew seats. Refer to Interior Upholstery - Maintenance Practices 34-12-01 Opération (3) Remove the jam nut and washer from the OAT sensor 34-12-01 Opération (4) Disconnect the electrical connector 34-12-01 Opération (5) Remove the OAT sensor from the airplane 34-12-01 Opération AIR DATA SYSTEM - MAINTENANCE 34-13-00 Processus NOTE: To prevent friction welding and galling, apply an Anaerobic adhesive such as Loctite 242, to the threads of both screws that hold the air data unit in position on the tray. Wipe any excess from the adjacent surfaces 34-13-00 Note A. Remove the GDC-74 Air Data Unit 34-13-00 Étape COORDINATOR DETAIL A AIRPLANES WITH GARMIN G1000 1210T1001 A1218T1044 Air Data Installation Figure 201 (Sheet 1) 34-13-00 Document (1) Make sure that the MASTER and AVIONICS switches are in the off position 34-13-00 Opération (2) Remove the MFD. Refer to Chapter 34, Control Display Unit - Maintenance Practices 34-13-00 Opération (3) Loosen the screws that hold the air data unit in position 34-13-00 Opération (4) Move the air data unit aft to get access to the hose and the electrical connector (P741) 34-13-00 Opération (5) Disconnect the hose and the electrical connector from the air data unit 34-13-00 Opération STALL WARNING SYSTEM - MAINTENANCE 34-18-00 Processus NOTE: The lip of the stall detector needs to be approximately 0.06 of an inch (1.52 mm) below the centerline of the wing skin cutout 34-18-00 Note WARNING: Do not touch the hot pitot probe, static port, and stall detector. This will help you prevent personal injury 34-18-00 Warning WARNING: Do not allow airspeed to drop below airplane stall speed 34-18-00 Warning CAUTION: Do not leave the PITOT HEAT/OFF switch in the PITOT HEAT position for more than one minute. This will help you prevent damage to the pitot probe, static port, and stall detector 34-18-00 Caution A. Remove Stall Warning Horn Assembly 34-18-00 Étape Stall Warning Horn and Detector Installation Figure 201 (Sheet 1) 34-18-00 Document (1) Remove electrical power from airplane 34-18-00 Opération (2) Disengage WARN circuit breaker on circuit panel assembly 34-18-00 Opération (3) Remove headliner to access stall warning horn assembly. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 34-18-00 Opération (4) Disconnect the wiring at the stall warning horn connectors (P1) and (JC030) 34-18-00 Opération (5) Remove nuts and washers securing stall warning horn assembly to adapter plate 34-18-00 Opération (6) Remove stall warning horn assembly from airplane 34-18-00 Opération A. Remove Stall Detector 34-18-00 Étape (1) Remove electrical power from airplane 34-18-00 Opération L) Disengage WARN and PITOT HEAT circuit breakers on circuit panel assembly 34-18-00 Opération (3) Move the PITOT HEAT/OFF switch to OFF 34-18-00 Opération (4) Remove access plate 510GB to access stall detector. Refer to Chapter 6, Access/Inspection Plates - Description and Operation 34-18-00 Opération (5) Disconnect the wiring at the stall detector connectors (PLO21) and (JL021) 34-18-00 Opération (6) Remove screws and nuts securing stall detector to wing leading edge 34-18-00 Opération (7) Remove stall detector from airplane 34-18-00 Opération OPTIONAL ANGLE OF ATTACK SYSTEM - MAINTENANCE 34-18-01 Processus NOTE: The software level of the index computer is identified on the Safe Flight SCc AOA Indexer Computer nameplate 34-18-01 Note NOTE: After the self-test, the audio warning will stop and the LEDs on the indexers will indicate the current state of the system and the position of the transducer 34-18-01 Note NOTE: Locking the cover, locks the locking rings on the base assembly 34-18-01 Note NOTE: The audio panel must be turned on and initialized (3 to 6 seconds) or AOA audio will not be heard during self test 34-18-01 Note NOTE: The single red LED will continue to blink at 1 Hz until the system has been calibrated in flight 34-18-01 Note NOTE: The audio alert will also sound and start when the two amber LEDs are illuminated at a low frequency and will increase in frequency as the AOA increases 34-18-01 Note NOTE: Do not use the SCc until a system calibration is completed. Refer to the In-Flight Final Calibration Adjustment 34-18-01 Note NOTE: All of the red, yellow, and green indicators will begin flashing 34-18-01 Note NOTE: The two red light will begin slowly flashing for five seconds. Refer to Figure 204 34-18-01 Note NOTE: During this time, maintain the stall warning target speed (at a constant power setting) 34-18-01 Note NOTE: Pressing and holding both top and bottom buttons for two seconds at any time will exit the calibration mode 34-18-01 Note NOTE: NUMBERS PLACED ON 34-18-01 Note INDEXER LEDs IN THIS FIGURE 34-18-01 Note FOR TROUBLESHOOTING 34-18-01 Note PURPOSES ONLY 34-18-01 Note CAUTION: The aircraft's stall warning system is the primary stall warning. The AOA System is non-required equipment and is to be used only as supplemental information to the pilot 34-18-01 Caution CAUTION: DO NOT paint or otherwise coat the vane of the lift transducer. All parts are adequately protected against corrosion. Any additional coating will interfere with proper operation 34-18-01 Caution CAUTION: DO NOT attempt to bend the vane of the lift transducer 34-18-01 Caution CAUTION: If you lift one end of a gyroscopic instrument 3a inch and let if fall on a hard surface, it is the equivalent of approximately a 20g shock to the gyro. This can cause damage to the instrument 34-20-00 Caution CAUTION: Always be very careful when you move or hold gyroscopic instruments, because damage can easily occur 34-20-00 Caution A. Remove the Indexer Computer 34-18-01 Étape Safe Flight SCc AOA Indexer Computer Removal/Installation Figure 202 (Sheet 1) 34-18-01 Document (1) Disconnect the cable assemblies from the indexer computer 34-18-01 Opération (2) Insert. a flat-head screwdriver into the slot at the end of each leg and lift up to release the cover 34-18-01 Opération (3) Rotate the cover to access the screw heads 34-18-01 Opération (4) Pull gently on the indexer computer to remove after the cover has been lifted 34-18-01 Opération A. Remove the SCc Lift Transducer 34-18-01 Étape NOTE: Cover the location with a cover plate if necessary 34-18-01 Note Safe Flight SCc AOA Lift Transducer Removal/Installation Figure 203 (Sheet 1) 34-18-01 Document (1) Remove the screws, washers, and nuts from lift transducer slotted holes 34-18-01 Opération (2) Disconnect the lift transducer from the cable assembly 34-18-01 Opération (3) Remove the lift transducer from the aircraft 34-18-01 Opération GYROSCOPES - MAINTENANCE 34-21-00 Processus NOTE: The permitted limits for gyro drift on the ground or in flight is 4 degrees from a fixed heading, during a 10-minute period 34-21-00 Note NOTE: After you stop operation of the airplane, it is usual for the directional gyro dial to continue to turn. This is not a cause to remove the gyro 34-21-00 Note NOTE: This adjustment is for offsets in the roll axes, including the turn coordinator 34-21-00 Note CAUTION: Do not remove the horizon attitude gyro from the box in which it was shipped until it is ready to be installed into the airplane. This will minimize the possibility of accidentally causing damage to the gyro 34-21-00 Caution CAUTION: Remove all plugs from the horizon attitude gyro before you install it in the airplane 34-21-00 Caution CAUTION: Be careful with the gyroscopic instruments. Do not hit, shake, or put the instruments on a hard surface. Put soft material between the gyroscopic instruments and any hard surface. Damage to the instruments will occur if the instruments are n 34-21-00 Caution CAUTION: Do not remove the directional gyro from the box in which it was shipped until it is ready to be installed into the airplane. This will minimize the possibility of accidentally causing damage to the gyro 34-21-00 Caution CAUTION: Remove all plugs from the directional gyro before you install it in the airplane 34-21-00 Caution CAUTION: Be careful with the gyroscopic instruments. Do not hit, shake, or put the instruments on a hard surface. Use soft material between the gyroscopic instruments and any hard surface. Damage to the instruments will occur if the instruments are n 34-21-00 Caution CAUTION: Do not remove the turn coordinator from the box in which it was shipped until it is ready to be installed into the airplane. This will minimize the possibility of accidentally causing damage to the gyro 34-21-00 Caution CAUTION: Remove all plugs from the turn coordinator before you install it in the airplane 34-21-00 Caution CAUTION: Be careful with the gyroscopic instruments. Do not hit, shake, or put the instruments on a hard surface. Put: soft material between the gyroscopic instruments and any hard surface. Damage to the instruments will occur if the instruments are 34-21-00 Caution CAUTION: Do not remove the turn coordinator from the box in which it was shipped until it is ready to be installed into the airplane. This will minimize the possibility of accidentally causing damage to the gyro 34-21-00 Caution CAUTION: Remove all plugs from the turn coordinator before you install it in the airplane 34-21-00 Caution CAUTION: Be careful with the gyroscopic instruments. Do not hit, shake, or put the instruments on a hard surface. Put soft material between the gyroscopic instruments and any hard surface. Damage to the instruments will occur if the instruments are n 34-21-00 Caution A. Horizon Gyro Removal 34-21-00 Étape CAUTION: Make sure that the gyro rotor has fully stopped before you move the instrument. The gyro rotor will not stop for approximately 15 minutes after the electrical power or vacuum source is removed. Damage to the instrument will occur if the inst 34-21-00 Caution CAUTION: Be careful with the gyroscopic instruments. Do not hit, shake, or put the instruments on a hard surface. Put soft material between the gyroscopic instruments and any hard surface. Damage to the instruments will occur if the instruments are n 34-21-00 Caution CAUTION: Make sure that you put soft material between the horizon attitude gyro and the control column before you remove the gyro. If you put the sub panel on the control column without any protection, you can damage the horizon attitude gyro and/or 34-21-00 Caution CAUTION: Put a cover on the applicable hose or port, or on the applicable electrical connector when the gyroscopic instrument is out of the airplane or is to be shipped. Damage to the instrument will occur from contamination if a cover is not used 34-21-00 Caution AIRPLANES WITH GARMIN G1000 1210T1001 A1214T1058 A1214T1057 Attitude and Direction Instrument Installation Figure 201 (Sheet 1) 34-21-00 Document (1) Put the MASTER switch and the AVIONICS switch in the off position 34-21-00 Opération (2) Remove the screws from the center panel 34-21-00 Opération (3) Carefully pull the panel out to get access to the back of the horizon gyro 34-21-00 Opération (4) Identify and tag the hoses which are attached to the horizon gyro 34-21-00 Opération (5) Loosen the clamps and remove the hoses from the horizon gyro 34-21-00 Opération (6) Disconnect the horizon gyro connector 34-21-00 Opération 7) Put female plugs over the ports and put a connector cap on the electrical connector 34-21-00 Opération (8) Remove the screws that attach the horizon gyro to the center panel 34-21-00 Opération (9) Remove the horizon gyro from the airplane 34-21-00 Opération A. Directional Gyro Removal 34-21-00 Étape CAUTION: Make sure that the gyro rotor has fully stopped before you move the instrument. The gyro rotor will not stop for approximately 15 minutes after the vacuum source is removed. Damage to the instrument will occur if the instrument is moved befo 34-21-00 Caution CAUTION: Be careful with the gyroscopic instruments. Do not hit, shake, or put the instruments on a hard surface. Put soft material between the gyroscopic instruments and any hard surface. Damage to the instruments will occur if the instruments are n 34-21-00 Caution CAUTION: Make sure that you put soft material between the directional gyro and the control column before you remove the gyro. If you put the sub panel on the control column without any protection, you can damage the directional gyro and/or the other 34-21-00 Caution CAUTION: Put a cover on the applicable hose or port, or on the applicable electrical connector when the gyroscopic instrument is out of the airplane or is to be shipped. Damage to the instrument will occur from contamination if you do not use a cover 34-21-00 Caution (1) Put the MASTER switch and the. AVIONICS switch in the off position. Disengage the INST LTS circuit breaker on circuit panel assembly and the AUTO PILOT circuit breaker on avionics circuit breaker panel 34-21-00 Opération (3) Remove the screws that connect the pilot center panel assembly to the structure to get access to the back of the directional gyro 34-21-00 Opération (4) Identify and tag two hoses connected to directional gyro 34-21-00 Opération 5) Loosen the clamps and remove the hoses from the directional gyro 34-21-00 Opération 6) Disconnect the directional gyro connector and the electrical connector from the directional gyro 34-21-00 Opération (1) Put female plugs over the ports and put a connector cap on the electrical connector 34-21-00 Opération 8) Remove the screws that connect the directional gyro to the pilot center panel assembly 34-21-00 Opération 9) Remove the directional gyro from the airplane 34-21-00 Opération (10) Remove the directional gyro from the airplane 34-21-00 Opération A. Turn Coordinator Removal 34-21-00 Étape CAUTION: Make sure that the gyro rotor has fully stopped before you move the instrument. The gyro rotor will not stop for approximately 15 minutes after the vacuum source is removed. Damage to the instrument will occur if the instrument is moved befo 34-21-00 Caution CAUTION: Be careful with the gyroscopic instruments. Do not hit, shake, or put the instruments on a hard surface. Put soft material between the gyroscopic instruments and any hard surface. Damage to the instruments will occur if the instruments are n 34-21-00 Caution CAUTION: Make sure that you put soft material between the turn coordinator and the control column before you remove the turn coordinator. If you put the sub-panel on the control column without any protection, you can damage the turn coordinator and/o 34-21-00 Caution CAUTION: Put a cover on the applicable electrical connector when the gyroscopic instrument is out of the airplane or is to be shipped. Damage to the instrument will occur from contamination if a cover is not used 34-21-00 Caution (1) Put the MASTER switch and the. AVIONICS switch in the off position. Disengage the INST LTS and the TURN COORD circuit breakers on circuit breaker panel assembly and the AUTO PILOT circuit breaker on the avionics circuit breaker panel 34-21-00 Opération (3) Remove the screws that attach the pilot center panel assembly to the structure to get access to the back of the turn coordinator 34-21-00 Opération (4) Disconnect the turn coordinator connector and the electrical connectori from the turn coordinator 34-21-00 Opération (5) Put connector caps on the turn coordinator avionics connector and electrical connector 34-21-00 Opération (6) Remove the screws that attach the turn coordinator to the pilot center panel assembly 34-21-00 Opération (7) Remove the turn coordinator from the airplane 34-21-00 Opération CAUTION: Make sure that the gyro rotor has fully stopped before you move the instrument. The gyro rotor will not stop for approximately 15 minutes after the vacuum source is removed. Damage to the instrument will occur if the instrument is moved befo 34-21-00 Caution CAUTION: Be careful with the gyroscopic instruments. Do not hit, shake, or put the instruments on a hard surface. Use soft material between the gyroscopic instruments and any hard surface. Damage to the instruments will occur if the instruments are n 34-21-00 Caution CAUTION: Put a cover on the applicable electrical connector when the gyroscopic instrument is out of the airplane or is to be shipped. Damage to the instrument will occur from foreign object debris if a cover is not used 34-21-00 Caution COORDINATOR DETAIL A AIRPLANES WITH GARMIN G1000 1210T1001 A1218T1044 Turn Coordinator Installation (Airplanes with Garmin G1000) Figure 202 (Sheet 1) 34-21-00 Document (1) Put the MASTER switch and the AVIONICS switch in the off position 34-21-00 Opération (2) Disengage the AUTO PILOT and STDBY INST LTS circuit breakers on the circuit breaker panel 34-21-00 Opération (3) Remove the Multi-Function Display (MFD). Refer to Chapter 34, Control Display Unit - Maintenance Practices 34-21-00 Opération (4) Remove the screws that attach the turn coordinator to the structure 34-21-00 Opération (5) Move the turn coordinator to get access to the electrical connector (P1307) 34-21-00 Opération (6) Disconnect the electrical connector and remove the turn coordinator from the airplane 34-21-00 Opération (7) Put connector caps on the avionics connector and the electrical connector 34-21-00 Opération COMPASS INSTALLATION - MAINTENANCE 34-22-00 Processus A. Remove Compass 34-22-00 Étape NOTE: Splices are located under upper windshield trim 34-22-00 Note Figure 201 (Sheet 1) 34-22-00 Document (1) Remove electrical power from airplane. Disengage INST LTS circuit breaker on circuit panel assembly 34-22-00 Opération (2) Identify, tag, and disconnect electrical wires for compass lighting 34-22-00 Opération (3) Remove screw, post, and washer securing compass to compass base 34-22-00 Opération (4) Remove compass from airplane 34-22-00 Opération MAGNETOMETER - MAINTENANCE 34-22-10 Processus A. Remove the Magnetometer 34-22-10 Étape CAUTION: Do not use magnetic tools and screws when work is done on the magnetometer. Magnetic tools and screws will cause the magnetometer to malfunction 34-22-10 Caution NOTE: ELECTRICAL CABLE THAT EXTENDS TO THE A DETAIL ELECTRICAL CONNECTOR. (PL302) 1210T1001 A0714T1048 GMU-44 Magnetometer Installation Figure 201 (Sheet 1) 34-22-10 Document (1) Make sure the MASTER and AVIONICS switches are in the off position 34-22-10 Opération (2) Remove the access/inspection plate (520DB) to get access to the magnetometer. Refer to Chapter 6, Access/Inspection Plates - Description and Operation 34-22-10 Opération (3) Remove the screws that attach the magnetometer to the flux detector bracket 34-22-10 Opération (4) Disconnect the electrical connector (PL302) from the magnetometer 34-22-10 Opération ATTITUDE HEADING REFERENCE SYSTEM (AHRS) - MAINTENANCE 34-23-00 Processus A. Remove the AHRS Unit 34-23-00 Étape CAUTION: Make sure to use a tailcone stand when you get in the tailcone 34-23-00 Caution Tailcone Avionics Installation Figure 201 (Sheet 1) 34-23-00 Document (1) Make sure the MASTER and AVIONICS switches are in the off position 34-23-00 Opération (2) Remove the baggage divider to get access to the aft tailcone interior 34-23-00 Opération (3) Disconnect the electrical connector (P771) 34-23-00 Opération (4) Remove the screws that attach the AHRS unit to the mounting tray 34-23-00 Opération (5) Remove the AHRS unit from the airplane 34-23-00 Opération MARKER BEACON - MAINTENANCE 34-30-00 Processus NOTE: The EVS wiring should be examined for loose connections and checked for continuity with a multimeter before any components are replaced 34-31-00 Note vice versa. Note if a valid video 34-31-00 Note image appears on the Garmin 34-31-00 Note Display Unit (GDU) in the MFD 34-31-00 Note position. Return the units to their 34-31-00 Note original position. If a valid image 34-31-00 Note appears when the units were 34-31-00 Note A. Remove the Marker Beacon Antenna 34-30-00 Étape Marker Beacon Antenna Installation Figure 201 (Sheet 1) 34-30-00 Document (1) Make sure the MASTER and AVIONIC switches are in the off position 34-30-00 Opération (2) Remove the tailcone access panel 310AB to get access to the marker beacon antenna connections. Refer to Chapter 6, Access/Inspection Plates - Description and Operation 34-30-00 Opération (3) Disconnect the coaxial cable from the antenna 34-30-00 Opération (4) Remove the screws that attach the antenna to the panel 34-30-00 Opération EVS-600 ENHANCED VISION SYSTEM - MAINTENANCE 34-31-00 Processus NOTE: This environmental seal is to help keep out the moisture in the wind stream 34-31-00 Note NOTE: The airplane should be connected to a ground power unit before attempting any configuration procedure 34-31-00 Note NOTE: The part number for SD database cards should be 010-00330-43 34-31-00 Note NOTE: If the MFD did not enter the CONFIG mode, then open the MFD (AVN BUS 34-31-00 Note 2) circuit breaker again. Press and hold the ENT key on the MFD and close 34-31-00 Note the MFD (AVN BUS 2) circuit breaker 34-31-00 Note NOTE: If the PFD did not enter the CONFIG mode, then open both the ESS and PFD (AVN BUS 1) circuit breakers again. Press and hold the ENT key on the PFD and close both the ESS and PFD (AVN BUS 1) circuit breakers 34-31-00 Note NOTE: The enhanced vision SD loader card is to stay with the aircraft 34-31-00 Note CAUTION: Be careful when you attach the camera to the spacer. This can cause damage to the bonding tabs 34-31-00 Caution A. Remove the EVS-600 Camera 34-31-00 Étape CAUTION: Be careful when you remove the camera from the spacer. This can cause damage to the oonding straps 34-31-00 Caution EVS-600 Camera Installation Figure 201 (Sheet 1) 34-31-00 Document (1) Set the BUS 3 switch, the MASTER switch and the AVIONICS switch to the OFF position 34-31-00 Opération 2) Remove the screws that attach the camera and spacer to the bottom of the right wing 34-31-00 Opération 3) Carefully pull the camera away from the wing sufficiently to get access to the jumper 34-31-00 Opération (4) Remove the jumper 34-31-00 Opération (a) Remove the fillet seal from the screw that attach the jumper and bonding strap to the spacer 34-31-00 Opération (b) Remove the screw and lock washer that attach the jumper and bonding strap to the spacer 34-31-00 Opération (c) Identify and mark the bonding strap that the jumper is attached to on the spacer 34-31-00 Opération (5) Disconnect the coaxial connector from the camera 34-31-00 Opération (6) Remove the camera, the spacer, and the gasket from the airplane 34-31-00 Opération 7) Remove the fillet seal from the screw installed through the other bonding strap 34-31-00 Opération (8) Remove the remaining screws and washers that attach the camera to the spacer 34-31-00 Opération (9) Carefully remove the camera from the spacer 34-31-00 Opération (a) Make sure that the bonding straps are serviceable 34-31-00 Opération (10) Use a nonmetallic scraper to carefully remove the sealant from the camera and spacer 34-31-00 Opération KMH-880 MULTI-HAZARD AWARENESS SYSTEM - MAINTENANCE 34-40-01 Processus NOTE: The correct location for the doubler is on the top side of the airplane skin below the floorboard on the left side of the airplane between FS 112.00 and FS 124.00 34-40-01 Note A. Remove the KMH-820 Processor 34-40-01 Étape CAUTION: Use a tailcone stand when you get in the tailcone. If you do not use a tailcone stand, the tail of the airplane can fall to the floor 34-40-01 Caution KMH-820 Processor Installation Figure 201 (Sheet 1) 34-40-01 Document (1) Set the MASTER and AVIONICS switches to the off position 34-40-01 Opération (2) Disengage the IHAS circuit breaker on the circuit breaker panel 34-40-01 Opération (3) Remove the rear seat to get access to the aft baggage divider. Refer to Chapter 25, Rear Seat - Maintenance Practices 34-40-01 Opération (4) Remove the aft baggage divider to get access to the tailcone 34-40-01 Opération (5) Disconnect the electrical connectors (J5, J6, and J8) from the forward side of the processor 34-40-01 Opération (6) Remove the screws that attach the rack assembly to the support bracket assembly 34-40-01 Opération 7) Remove the processor from the airplane 34-40-01 Opération (8) Remove the screws that attach the processor to the rack assembly 34-40-01 Opération A. Remove the KMH-880 Interface Adapter 34-40-01 Étape CAUTION: Use a tailcone stand when you get in the tailcone. If you do not use a tailcone stand, the tail of the airplane can fall to the floor 34-40-01 Caution KMH-880 Interface Adapter Installation Figure 202 (Sheet 1) 34-40-01 Document (1) Set the MASTER and AVIONICS switches to the off position 34-40-01 Opération 2) Disengage the IHAS circuit breaker on the circuit breaker panel 34-40-01 Opération (3) Remove the rear seat to get access to the aft baggage divider. Refer to Chapter 25, Rear Seat - Maintenance Practices 34-40-01 Opération (4) Remove the aft baggage divider to get access to the tailcone 34-40-01 Opération (5) Disconnect the electrical connectors (PT703 and PT704) from the interface adapter 34-40-01 Opération (6) Disconnect the electrical connector (PT705) from the configuration module 34-40-01 Opération (7) Disconnect the electrical connectors (PT706 and PT707) from the support bracket assembly 34-40-01 Opération (8) Remove the screws that attach the support bracket to the airplane structure 34-40-01 Opération (9) Remove the support bracket from the airplane 34-40-01 Opération (10) Remove the screws that attach the interface adapter to the support bracket 34-40-01 Opération (11) Remove the screws that attach the configuration module to the support bracket 34-40-01 Opération A. Remove the Omnidirectional Antenna 34-40-01 Étape Omnidirectional Antenna Installation Figure 203 (Sheet 1) 34-40-01 Document (1) Set the MASTER and AVIONICS switches to the off position 34-40-01 Opération (2) Disengage the IHAS circuit breaker on the circuit breaker panel 34-40-01 Opération 3) Remove the rear seat to get access to the aft baggage divider. Refer to Chapter 25, Rear Seat - Maintenance Practices 34-40-01 Opération (4) Pull the interior upholstery back to get sufficient access to the rear access panels on the floorboard 34-40-01 Opération 5) Remove the access panel (231NB) to get access to the omnidirectional antenna installation 34-40-01 Opération o) Disconnect the right-angle adapter (coax cable) from the omnidirectional antenna 34-40-01 Opération ) Remove the screws that attach the omnidirectional antenna to the bottom of the fuselage 34-40-01 Opération (8) Remove the doubler and omnidirectional antenna from the airplane 34-40-01 Opération A. Remove the TAS Directional Antenna 34-40-01 Étape TAS Directional Antenna Installation Figure 204 (Sheet 1) 34-40-01 Document (1) Set the MASTER and AVIONICS switches to the off position. Disengage the IHAS circuit breaker on the circuit breaker panel 34-40-01 Opération 3) Remove the headliner to get access to the directional antenna 34-40-01 Opération 4) Put a label on each (four) of the right-angle adapters and disconnect them from the directional antenna 34-40-01 Opération (5) Remove the screws that attach the directional antenna to the top of the fuselage 34-40-01 Opération (6) Remove the directional antenna and doubler from the airplane 34-40-01 Opération KTA-870 TRAFFIC ADVISORY SYSTEM (TAS) - MAINTENANCE 34-40-05 Processus A. KTA-810 Processor Removal 34-40-05 Étape CAUTION: Use a tailcone stand when you get in the tailcone. If you do not use a tailcone stand, the tail of the airplane can fall to the floor 34-40-05 Caution (J8) ELECTRICAL CONNECTOR (J4) ELECTRICAL CONNECTOR SUPPORT (J2) BRACKET 50-OHM ASSEMBLY TERMINATION (J6) DETAIL A 1210T1001 A1218T1084 KTA-810 Processor Installation Figure 201 (Sheet 1) 34-40-05 Document (1) Set the MASTER and AVIONICS switches to the OFF position. Disengage the TAS circuit breaker on the circuit breaker panel 34-40-05 Opération (3) Remove the rear seat to get access to the aft baggage divider. Refer to Chapter 25, Rear Seat - Maintenance Practices 34-40-05 Opération (4) Remove the aft baggage divider to get access to the tailcone 34-40-05 Opération (5) Disconnect the electrical connectors (J1, J2, J3, J4, J7, and J10) from the forward side of the processor 34-40-05 Opération (6) Remove the 50-ohm terminations from J5, J6, and J8 electrical connections on the forward side of the processor 34-40-05 Opération ) Loosen the two lock nuts that attach the processor to the rack assembly 34-40-05 Opération (8) Remove the processor from the rack assembly 34-40-05 Opération (9) Remove the screws that attach the rack assembly to the support bracket assembly 34-40-05 Opération (10) Remove the rack assembly from the airplane 34-40-05 Opération A. KCM-805 Configuration Module Removal 34-40-05 Étape CAUTION: Use a tailcone stand when you get in the tailcone. If you do not use a tailcone stand, the tail of the airplane can fall to the floor 34-40-05 Caution KCM-805 Configuration Module Installation Figure 202 (Sheet 1) 34-40-05 Document (1) Set the MASTER and AVIONICS switches to the OFF position 34-40-05 Opération (2) Disengage the TAS circuit breaker on the circuit breaker panel 34-40-05 Opération (3) Remove the rear: seat to get access to the aft baggage divider. Refer to Chapter 25, Rear Seat - Maintenance Practices 34-40-05 Opération (4) Remove the aft baggage divider to get access to the tailcone 34-40-05 Opération (5) Disconnect the electrical connector (PT705) from the configuration module 34-40-05 Opération (6) Remove the screws that attach the configuration module to the support bracket 34-40-05 Opération WX-500 STORMSCOPE - MAINTENANCE 34-40-10 Processus NOTE: The maximum allowable resistance (in ohms) at each of the four measured positions is 0.0025 34-40-10 Note A. Remove the Stormscope 34-40-10 Étape CAUTION: Make sure to use a tailcone stand when you get in the tailcone 34-40-10 Caution WX-500 Stormscope Installation Figure 201 (Sheet 1) 34-40-10 Document (1) Make sure the MASTER and AVIONICS switches are in the off position 34-40-10 Opération (2) Remove the baggage divider to get access to the aft tailcone interior 34-40-10 Opération (3) Disconnect the electrical connection 34-40-10 Opération (4) Remove the screws that hold the stormscope to the shelf 34-40-10 Opération (5) Remove the stormscope from the airplane 34-40-10 Opération GTS 800 TRAFFIC ADVISORY SYSTEM (TAS) - MAINTENANCE 34-41-00 Processus NOTE: You will hear an audible click when the QMA connectors are fully engaged 34-41-00 Note NOTE: You will hear an audible click when the QMA connectors are fully engaged 34-41-00 Note NOTE: When the aircraft is connected to a GPU, make sure that the STBY BATT switch is in the ARM position in order to charge the battery 34-41-00 Note NOTE: The serial number is not reported for the following equipment: COM1, COM2, GS1, GS2, GTX, NAV1, and NAV2 34-41-00 Note NOTE: The version number is not reported for the CO GUARDIAN 34-41-00 Note NOTE: The KR 87 ADF and KN 63 DME systems are not listed on the system status page 34-41-00 Note NOTE: If the status column indicates a red X, refer to Chapter 34, GTS 800 Traffic Advisory System (TAS) - Troubleshooting 34-41-00 Note NOTE: If the SERIAL NUMBER or VERSION is dashed, refer to Chapter 34, GTS 800 Traffic Advisory System (TAS) - Troubleshooting 34-41-00 Note NOTE: If one of the messages in Table 502 does appear, refer to Chapter 34, GTS 800 Traffic Advisory System (TAS) - Troubleshooting 34-41-00 Note NOTE: Per the IFR 6000's specifications, its transponder transmit range is limited to 250 feet 34-41-00 Note NOTE: Aircraft must be configured in Air Mode for the recognition lights to operate. Air Mode can be simulated with a pitot-static test unit 34-41-00 Note NOTE: This test can be conducted in conjunction with a functional test of the landing, recognition, and taxi lights 34-41-00 Note NOTE: Coordinate with airport ground control prior to setting the transponder to operate in ALT mode 34-41-00 Note NOTE: If a traffic advisory occurs, make sure the wiring between 48PT711 and 31PT800 is correct. Refer to the 206H/T206H Wiring Diagram Manual 34-41-00 Note NOTE: The Ground Test simulates the GTS to be airborne at 50000 feet with a magnetic heading of 0° 34-41-00 Note NOTE: The tests in this section must be performed outdoors clear of buildings that may reflect traffic signals 34-41-00 Note NOTE: If traffic is not acquired at approximately 10 nautical miles, increase the ANT RANGE setting on the IFR 6000 test set (maximum of 250 feet) 34-41-00 Note NOTE: If a traffic annunciation is heard, make sure the wiring between 10PT711 and 47PT312 is correct. Refer to the 206H/T206H Wiring Diagram Manual 34-41-00 Note NOTE: Initial acquisition of the target is sufficient for these repeat conditions; it is not necessary to wait for the traffic advisory to occur 34-41-00 Note A. Remove the GTS 800 Traffic Advisory System (TAS) Processor 34-41-00 Étape CAUTION: If you pull on or disengage the QMA connectors with too much force you can cause damage to both the connectors and the coaxial cable 34-41-00 Caution GTS 800 TAS Processor Installation Figure 201 (Sheet 1) 34-41-00 Document T206H09108 AND ON 115-00781-0 1210T1001 GTS 800 TAS Processor Installation Figure 201 (Sheet 2) 34-41-00 Document (1) Make sure that the MASTER ALT BAT and AVIONICS switches are in the OFF position 34-41-00 Opération 2) Disengage the TAS circuit breaker on the circuit breaker panel 34-41-00 Opération 3) Open the baggage compartment door 34-41-00 Opération 4) Remove the aft baggage carpet to gain access to the aft baggage floorboard 34-41-00 Opération (5) Remove the aft baggage floorboard to get access to the GTS 800 TAS processor. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 34-41-00 Opération (6) Tag and disconnect the coaxial cable connectors (PT1045, PT1046, PT1047, PT1048, PT1049) from the processor by pulling back firmly on the outer sleeves of the QMA plug 34-41-00 Opération (7) Tag and disconnect the electrical connectors (P8001, P8002, P8003) from the processor 34-41-00 Opération (8) Loosen the knurled knob that holds the processor in its position on the mounting rack 34-41-00 Opération (9) Carefully remove the processor by grasping it and pulling it it out of the mounting rack 34-41-00 Opération A. Remove the GA58 Directional Antenna 34-41-00 Étape CAUTION: If you pull on or disengage the QMA connectors with too much force, you can cause damage to both the connectors and the coaxial cable 34-41-00 Caution GA58 Directional Antenna Installation Figure 202 (Sheet 1) 34-41-00 Document (1) Make sure that the MASTER ALT BAT and AVIONICS switches are in the OFF position 34-41-00 Opération (2) Disengage the TAS circuit breaker on the circuit breaker panel 34-41-00 Opération (3) Remove the headliner to gain access to the lower side of the GA58 Directional Antenna. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 34-41-00 Opération (4) Tag and disconnect the coaxial cable connectors (PF1013, PF1014, PF1015, PF1016) from the antenna 34-41-00 Opération (5) Remove the fillet seal (white) around the base of the antenna and in the top antenna screws. Refer to Chapter 20, Fuel, Weather, and High-Temperature Sealing - Maintenance Practices 34-41-00 Opération (6) Remove the screws that attach the antenna to the fuselage 34-41-00 Opération (a) Lift the antenna away from the fuselage and carefully remove it 34-41-00 Opération A. Remove the Omni-Directional Antenna 34-41-00 Étape (1) Make sure that the MASTER ALT BAT and. AVIONICS switches are in the OFF position 34-41-00 Opération (2) Disengage the TAS circuit breaker on the circuit breaker panel 34-41-00 Opération (3) Remove the aft seats to gain access to the aft carpet. Refer to Chapter 25, Passenger Compartment - Maintenance Practices 34-41-00 Opération (4) Remove the aft carpet to gain access to the aft floorboard access panels. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 34-41-00 Opération (5) Remove floorboard access panel 231NB to gain access to the upper: side of the omni-directional antenna. Refer to Chapter 6, Access/Inspection Plates - Description and Operation 34-41-00 Opération (6) Disconnect the coaxial cable connector (PF1017) from the antenna 34-41-00 Opération (7) Remove the fillet seal (white) around the antenna and in the top antenna screws. Refer to Chapter 20, Fuel, Weather, and High-Temperature Sealing - Maintenance Practices 34-41-00 Opération (8) Remove the screws that attach the antenna to the fuselage 34-41-00 Opération (a) Carefully lift the antenna away from the fuselage 34-41-00 Opération KX-155A COMM/NAV SYSTEM - MAINTENANCE 34-50-00 Processus CAUTION: Do not interchange the KX-155A and the KX-165A NAV/COM radios. The wiring is not the same for the two different radios. If these radios are interchanged and used with the same wiring, damage can occur to the KX-155A and/or the KX-165A NAV/CO 34-50-00 Caution CAUTION: When screwing antenna radiators into self-locking hex nuts, do not over-tighten antenna radiators 34-50-00 Caution A. Remove Omni Antenna 34-50-00 Étape COAX CONNECTOR Caer COAX CONNECTOR Son G/S NAV ANTENNA ANT COUPLER DETAIL B 1210T1001 A0718T1011 B1218T1016 Navigation Components Installation Figure 201 (Sheet 1) 34-50-00 Document Navigation Components Installation Figure 201 (Sheet 2) 34-50-00 Document (1) Remove electrical power from airplane. Disengage NAV COM 1 and NAV COM 2 circuit breakers on avionics circuit breaker panel 34-50-00 Opération (2) Remove boots over antenna radiators 34-50-00 Opération (3) Remove antenna radiators from antenna base by unscrewing radiators out of the self-locking hex nuts 34-50-00 Opération (4) Gain access to omni antenna by removing fin tip 34-50-00 Opération (5) Remove screws securing antenna base to fin rib 34-50-00 Opération (6) Lift antenna base to gain access to coax connector. Disconnect coax connector from antenna base 34-50-00 Opération (7) Remove omni antenna from airplane 34-50-00 Opération A. Remove Nav Antenna Coupler 34-50-00 Étape NOTE: The nav antenna coupler is located at RBL 4.51 and WL 18.58, on the aft side of the firewall 34-50-00 Note (1) Remove electrical power from airplane. Disengage NAV COM 1 and NAV COM 2 circuit breakers on avionics circuit breaker panel 34-50-00 Opération L Gain access to nav antenna coupler 34-50-00 Opération 3) Identify, tag, and disconnect antenna coax connectors from nav antenna coupler 34-50-00 Opération 4) Remove screws and washers securing nav antenna coupler to firewall 34-50-00 Opération 5) Remove nav antenna coupler from airplane 34-50-00 Opération A. Remove Navigation Indicator 34-50-00 Étape NOTE: KI-209A Navigation Indicator is the NAV 1 indicator and KI-208 is the NAV 2 indicator. Removal and installation are typical for the NAV 1 and 2 indicators 34-50-00 Note (1) Remove electrical powert from airplane. Disengage NAV COM 1 and NAV COM 2 circuit breakers on avionics circuit breaker panel and INST LTS circuit breaker on circuit panel assembly 34-50-00 Opération (2) Remove pilot inboard panel assembly to gain access to rear of navigation indicator. Refer to Chapter 31, Instrument and Control Panels - Maintenance Practices 34-50-00 Opération (3) Disconnect electrical connector (NAV 1 or NAV 2) from navigation indicator 34-50-00 Opération (4) Remove screws securing navigation indicator to pilot inboard panel assembly 34-50-00 Opération (5) Remove navigation indicator from airplane 34-50-00 Opération GIA - 63 INTEGRATED AVIONICS INSTALLATION - MAINTENANCE 34-50-10 Processus A. Remove the Integrated Avionics Unit 34-50-10 Étape (1) Refer to Chapter 23, Communications - Maintenance Practices 34-50-10 Opération KLN-79/KLN-89B GPS - MAINTENANCE 34-51-00 Processus A. Remove GPS Receiver 34-51-00 Étape DETAIL B 1210T1001 A1218T1001 B1218T1017 KLN-89/KLN-89B GPS Installation Figure 201 (Sheet 1) 34-51-00 Document (1) Remove electrical power from airplane. Disengage GPS circuit breaker on avionics circuit breaker panel and INST LTS circuit breaker on circuit panel assembly. Additionally, disengage the NAV COM 1 circuit breaker for airplanes with the KR-87 ADF 34-51-00 Opération (2) Loosen single hex screw, located in recessed hole on face of GPS receiver, counterclockwise. Continue turning hex screw until unit is free to be removed from avionics radio panel rack 34-51-00 Opération (3) Pull GPS receiver from radio panel rack and remove from airplane 34-51-00 Opération A. Remove GPS Antenna 34-51-00 Étape NOTE: Secure coax cable using a tie strap, tape, or other suitable material, to prevent connector from slipping through the opening in the fuselage once it has been disconnected from GPS antenna 34-51-00 Note (1) Remove electrical power from airplane. Disengage the GPS circuit breaker on the avionics circuit breaker panel 34-51-00 Opération (2) Remove screws securing GPS antenna to fuselage skin 34-51-00 Opération (3) Carefully lift GPS antenna and disconnect coax connector from GPS antenna 34-51-00 Opération (4) Remove GPS antenna and gasket from airplane 34-51-00 Opération KR-87 ADF SYSTEM - MAINTENANCE 34-52-00 Processus A. ADF Receiver Removal 34-52-00 Étape DETAIL B 1210T1001 A1218T1001 B1218T1015 KR-87 ADF Installation Figure 201 (Sheet 1) 34-52-00 Document (1) Remove electrical power from airplane. Disengage ADF circuit breaker on avionics circuit breaker panel and INST LTS circuit breaker on circuit panel assembly 34-52-00 Opération (2) Loosen the single locking screw located in the recessed hole on the face of the receiver 34-52-00 Opération (3) Pull the. ADF receiver from the radio rack and remove from airplane 34-52-00 Opération Figure 202 (Sheet 1) 34-52-00 Document (1) Remove electrical power from the airplane and turn the master switch to off. Disengage the ADF circuit breaker on the avionics circuit breaker panel 34-52-00 Opération L Loosen the single locking screw located in the recessed hole on the face of the receiver 34-52-00 Opération (3) Carefully pull the ADF receiver and the bezel from the instrument panel to disengage the electrical connector (P1602) from the ADF receiver 34-52-00 Opération (4) Remove the ADF receiver, with the bezel, from the airplane 34-52-00 Opération A. ADF Antenna Removal 34-52-00 Étape (1) Remove electrical power from airplane and turn the master switch to off. Disengage ADF circuit breaker on avionics circuit breaker panel 34-52-00 Opération Remove the screws that attach the ADF antenna to the fuselage skin 34-52-00 Opération (3) Disconnect the antenna connector (PC600) from the ADF antenna 34-52-00 Opération (4) Remove the ADF antenna from the airplane 34-52-00 Opération A. ADF Indicator Removal 34-52-00 Étape (1) Remove electrical power from airplane and turn the master switch to off. Disengage ADF circuit breaker on avionics circuit breaker panel and INST LTS circuit breaker on circuit panel assembly 34-52-00 Opération (2) Remove the pilot inboard panel assembly to gain access to the ADF indicator. Refer to Chapter 31, Instrument and Control Panels - Maintenance Practices 34-52-00 Opération (3) Disconnect the electrical connector (P1603) from the ADF indicator 34-52-00 Opération (4) Remove the screws that attach the ADF indicator to the inboard pilot panel assembly 34-52-00 Opération (5) Remove the ADF indicator from the airplane 34-52-00 Opération KT-76C TRANSPONDER - MAINTENANCE 34-53-00 Processus A. Remove Transponder 34-53-00 Étape DETAIL B A0518T1042 B1218T1001 KT-76C Transponder Installation Figure 201 (Sheet 1) 34-53-00 Document (1) Remove electrical power from airplane. Disengage XPNDR circuit breaker on avionics circuit breaker panel and INST LTS circuit breaker on circuit panel assembly 34-53-00 Opération (2) Loosen single hex screw, located in recessed hole on face of transponder, counterclockwise. Continue turning hex screw until unit is free to be removed from avionics radio panel rack 34-53-00 Opération (3) Pull transponder from avionics radio panel rack and remove from airplane 34-53-00 Opération A. Remove Transponder Antenna 34-53-00 Étape NOTE: Identify locations of washers for use during transponder antenna installation 34-53-00 Note (1) Remove electrical power from airplane. Disengage XPNDR circuit breaker on avionics circuit breaker panel 34-53-00 Opération (2) Remove antenna access plate to gain access to antenna 34-53-00 Opération (3) Remove nuts and washers securing transponder antenna to fuselage 34-53-00 Opération (4) From outside of airplane, support transponder antenna and remove coax connector from transponder antenna 34-53-00 Opération (5) Remove transponder antenna from airplane 34-53-00 Opération KT-73 MODE S TRANSPONDER - MAINTENANCE 34-53-01 Processus A. Remove the KT-73 Transponder 34-53-01 Étape DETAIL B 1210T1001 A0518T1042 B1218T1067 KT-73 Mode S Transponder Installation Figure 201 (Sheet 1) 34-53-01 Document (1) Disconnect the main battery. Refer to Chapter 24, Battery - Maintenance Practices 34-53-01 Opération (2) Disengage the XPNDR circuit breaker on the avionics circuit breaker panel and the INST LTS circuit breaker on the circuit breaker panel 34-53-01 Opération (3) Turn the single hex-screw, found in the recessed hole on the face of the transponder, counterclockwise 34-53-01 Opération (4) Remove the single hex-screw from the transponder 34-53-01 Opération (5) Pull the transponder from the radio mounting rack 34-53-01 Opération (6) Disconnect the coaxial cable and electrical connector from the transponder 34-53-01 Opération (/) Remove the transponder from the airplane 34-53-01 Opération GTX-33 TRANSPONDER - MAINTENANCE 34-53-10 Processus A. Remove the Transponder 34-53-10 Étape CAUTION: Make sure to use a tailcone stand when you get into the tailcone 34-53-10 Caution GTX-33 Transponder Installation Figure 201 (Sheet 1) 34-53-10 Document (1) Disconnect electrical power to the airplane 34-53-10 Opération (2) Set the MASTER switch and AVIONICS switch to the off position 34-53-10 Opération (3) Disengage the circuit breaker 34-53-10 Opération (4) Get access to the avionics inside the tailcone 34-53-10 Opération (a) Remove the baggage divider 34-53-10 Opération (5) Disconnect the electrical connection 34-53-10 Opération (6) Remove the screws that hold the transponder on the avionics shelf 34-53-10 Opération (7) Remove the transponder from the airplane 34-53-10 Opération GDL-69A FIS - MAINTENANCE 34-54-00 Processus NOTE: THE INSTRUMENT PANEL IS SHOWN WITH THE MULTI-FUNCTION DISPLAY (MFD) SCREEN REMOVED 34-54-00 Note A. Data Link Removal 34-54-00 Étape GDL-69A XM Weather Data Link Installation Figure 201 (Sheet 1) 34-54-00 Document (1) Set the MASTER switch and the AVIONICS switch to the off position 34-54-00 Opération (2) Remove the GDU 1040 Multi-Function Display (MFD) unit. Refer to Chapter 34, Control Display Unit - Maintenance Practices 34-54-00 Opération (3) Turn the quarter-turn fastener 90 degrees counterclockwise and lift the locking levert to disengage the data link 34-54-00 Opération (4) Move the data link aft out of the mounting rack 34-54-00 Opération (5) Remove the data link from the airplane 34-54-00 Opération DME - MAINTENANCE 34-55-00 Processus A. KN-63 DME Receiver Removal 34-55-00 Étape CAUTION: Use a tailcone stand when you get in the tailcone. If you do not use a tailcone stand, the tail of the airplane can fall to the floor 34-55-00 Caution KN-63 DME Receiver Installation Figure 201 (Sheet 1) 34-55-00 Document (1) Set the MASTER and the AVIONICS switches to the off position 34-55-00 Opération (2) Disengage the DMEIADF circuit breaker on the avionics circuit breaker panel 34-55-00 Opération (3) Remove the rear seat to get access to the aft baggage divider. Refer to Chapter 25, Rear Seat - Maintenance Practices 34-55-00 Opération (4) Remove the aft baggage divider to get access to the tailcone 34-55-00 Opération (5) Disconnect the electrical connector (PT1031) from the receiver 34-55-00 Opération (6) Disconnect the electrical connector (PT801) from the receiver 34-55-00 Opération 1) Loosen the hold down screw 34-55-00 Opération 8) Remove the screws that attach the mounting rack to the hold down bars 34-55-00 Opération (9) Remove the hold down bars, rack, DME unit, and attaching hardware from the airplane 34-55-00 Opération A. DME Antenna Removal 34-55-00 Étape Figure 202 (Sheet 1) 34-55-00 Document (1) Set the MASTER and the AVIONICS switches to the off position 34-55-00 Opération (2) Disengage the DME/ADF circuit breaker on the avionics circuit breaker panel 34-55-00 Opération (3) Remove noise-damping material as necessary to get access to the antenna installation 34-55-00 Opération (4) Remove the nuts and the washers that attach the DME antenna to the airplane at FS 106.00 34-55-00 Opération (5) Disconnect the electrical connector (PF1011) from the antenna 34-55-00 Opération (6) Remove the antenna from the airplane 34-55-00 Opération KMD-540 MULTI-FUNCTION DISPLAY - MAINTENANCE 34-60-01 Processus A. Remove the KMD-540 MFD 34-60-01 Étape DETAIL B A1218T1069 1210T1001 A1218T1070 KMD-540 MFD Installation Figure 201 (Sheet 1) 34-60-01 Document (1) Disconnect the main battery. Refer to Chapter 24, Battery - Maintenance Practices 34-60-01 Opération 2) Disengage the MFD circuit breaker on the circuit breaker panel 34-60-01 Opération (3) Remove the screw in the face of the MFD 34-60-01 Opération 4) Carefully, pull the unit out of the avionics rack 34-60-01 Opération (5) Disconnect the electrical connector from the MFD 34-60-01 Opération (6) Remove the MFD from the airplane 34-60-01 Opération CONTROL DISPLAY UNIT - MAINTENANCE 34-60-10 Processus NOTE: Equivalent substitutes may be used for the items that following 35-00-00 Note NOTE: Each oxygen port contains a spring-loaded valve which prevents flow of oxygen until a mask hose is plugged in. Each mask hose contains an oxygen flow indicator for visual proof of oxygen flow 35-01-00 Note WARNING: Oil, grease or other lubricants in contact with high-pressure oxygen, create a serious fire hazard and such contact should be avoided. Do not permit smoking or open flame in or near aircraft while work is performed on oxygen systems 35-01-00 Warning CAUTION: If possible, do not touch the lens. The GDU 1040 lens has a layer of anti-reflective material which is very sensitive to skin oils, waxes and abrasive cleaners 34-60-10 Caution CAUTION: Do not use cleaners that contain ammonia. Ammonia will cause damage to the anti-reflective material. It is very important to clean the lens with a clean, lint-free cloth and an eyeglass lens cleaner that is specified as safe for anti-reflect 34-60-10 Caution A. Remove the Control Display Unit (CDU) 34-60-10 Étape NOTE: To prevent altering the G1000 configuration settings, make sure that the PFD circuit breakers are disengaged on the ESSENTIAL BUS and AVIONICS BUS 1 sections of the circuit breaker panel before electrical power is applied to the aircraft with t 34-60-10 Note CAUTION: If possible, do not touch the lens. The GDU 1040 lens has a layer of anti- reflective material which is very sensitive to skin oils, waxes and abrasive cleaners 34-60-10 Caution CAUTION: Do not use cleaners that contain ammonia. Ammonia will cause damage to the anti-reflective material. It is very important to clean the lens with a clean, lint-free cloth and an eyeglass lens cleaner that is specified as safe for anti-reflect 34-60-10 Caution Control Display Unit Installation Figure 201 (Sheet 1) 34-60-10 Document (1) Disengage the applicable PFD or MFD circuit breaker for the CDU. Disconnect the quick release fasteners from the CDU 34-60-10 Opération (3) Carefully pull the CDU from the instrument panel and disconnect the electrical connector that is attached to the back of the CDU 34-60-10 Opération OXYGEN - MAINTENANCE 35-01-00 Processus NOTE: Clockwise on standard threads, counter-clockwise on left-hand threads 35-01-00 Note NOTE: Resulted ragged end is the key to the tape staying in place. The tape may unwind if it is cut 35-01-00 Note NOTE: A correct record of the number of charges must be maintained by the owner or his agent if the cylinder is charged an average of once every other day 35-01-00 Note NOTE: Oxygen cylinder and regulator assemblies may not always be installed in the field exactly as illustrated. Important points to remember are as follows 35-01-00 Note NOTE: The above data may be used to determine that oxygen cylinders are acceptable for service. This criteria must be used prior to charging cylinders 35-01-00 Note NOTE: This solution must contain 1/5 teaspoon of merthiolate per one quart of water 35-01-00 Note NOTE: The Precise Flight Oxygen Flow Meter can become static charged because of friction. This charge does not let the ball move freely inside the flow meter. This treatment will remove the static charge 35-01-00 Note NOTE: If pressure specified in the foregoing procedures is not obtained, the oxygen regulator is not operating properly. Remove and replace cylinder-regulator assembly with another unit and repeat test procedure 35-01-00 Note NOTE: Use only aviator's breathing oxygen per MIL-0-27210 35-01-00 Note Example: If ambient temperature is 70°F, fill aircraft cylinders to approximately 1,975 PSI or as close to this 35-01-00 Note pressure as the gage may read. Upon cooling, cylinders must have approximately 1,850 PSI of pressure 35-01-00 Note WARNING: Do not smoke tobacco or let open flame near the airplane while maintenance is performed on the oxygen system. Make sure the electrical power is disconnected and that the airplane is correctly grounded. Oils, grease, and solvents may burn or 35-01-00 Warning WARNING: Use only non-sparking tools 35-01-00 Warning WARNING: Cap all lines immediately 35-01-00 Warning WARNING: Be sure to ground aircraft and ground servicing equipment before charging oxygen system 35-01-00 Warning CAUTION: A water-lubricated compressor must be used to blow the tubing clean only when nitrogen or argon are not available. The air must be clean, dry, and filtered. Most air compressors are oil-lubricated and a minimum amount of oil will be carried 35-01-00 Caution CAUTION: Do not place the control in the on position with outlet ports (low pressure) open to atmosphere with the oxygen bottle charged. Damage to regulator metering poppet will occur 35-01-00 Caution CAUTION: You must do a leak check and purge of the oxygen system when a component of the oxygen system is removed, installed, replaced, or the system has been disassembled 35-01-00 Caution CAUTION: The pressure regulator, pressure gage and line, and filler valve must be removed and replaced only by personnel familiar with high-pressure fittings. Obey all maintenance precautions 35-01-00 Caution CAUTION: Do not attempt to tighten any connections while the system is charged 35-01-00 Caution CAUTION: A cylinder which is completely empty may be contaminated. The regulator and cylinder assembly must then be disassembled, inspected and cleaned by an FAA approved facility, before filling. Contamination, as used here, means dirt, dust or any 35-01-00 Caution C. Remove the filler valve 35-01-00 Étape CLAMP WASHER REFER TO SCREW FIGURE 203 35-01-00 Document SPACER VALVE COVER FILLER VALVE SCREW SCREW 1210T1001 DETAIL B A1214T1074 B1214R1008 Oxygen Cylinder Installation Figure 203 (Sheet 1) 35-01-00 Document (1) Remove line from quick-disconnect valve at the regulator. Disconnect chain, but do not remove cap from filler valve 35-01-00 Opération 3 Remove screws securing valve and disconnect pressure line 35-01-00 Opération 4) Cap pressure line and seat 35-01-00 Opération 5) Remove filler valve 35-01-00 Opération E. Pressure Gage Removal 35-01-00 Étape DETAIL B 1210T1001 A1214T1004 B2614T1031 Oxygen Controller Installation Figure 201 (Sheet 1) 35-01-00 Document Oxygen Controller Installation Figure 201 (Sheet 2) 35-01-00 Document (1) At the oxygen bottle, disconnect the capillary line from the regulator 35-01-00 Opération (2) Get access to the pressure gage through the center overhead console, headliner, and headliner trim. Refer to Interior Upholstery - Maintenance Practices 35-01-00 Opération (3) Disconnect the pressure gage from the oxygen pressure line at the elbow 35-01-00 Opération (4) Remove the hex nuts from the pressure gage 35-01-00 Opération (5) Remove the u-clamp from the pressure gage 35-01-00 Opération (6) Remove the pressure gage from the airplane 35-01-00 Opération VACUUM SYSTEM - MAINTENANCE 37-10-00 Processus NOTE: Before the adjustment procedure, the entire pneumatic system must be inspected and tested for leaks, restrictions, and unserviceable components. Failure to correct all system anomalies will lead to reduced dry air pump service life 37-10-00 Note NOTE: At engine speeds between 1200 RPM and full throttle, suction must fall between 4.5 In. Hg. and 5.5 In. Hg. (green range on gage) 37-10-00 Note NOTE: As you face the adjustment screw, when you turn it clockwise the pressure increases. When you turn it counterclockwise, the pressure decreases 37-10-00 Note NOTE: Wax only clean surfaces. Wax applied over salt deposits will almost guarantee a trapped salt deposit, which is capable of accumulating moisture and developing into filiform corrosion 51-11-00 Note NOTE: Corrosion inhibiting solid film lubricants, Specification MIL-PRF-46010 and/or MIL-L-46147, may be used to protect attaching parts from corrosion 51-11-00 Note NOTE: Do not use metallic wool. Metal particles will be embedded in the surface, which will initiate additional corrosion 51-11-00 Note CAUTION: Do not set the pump directly in a vise. If you clamp the vise across the center, the carbon rotor in the pump can be damaged. Protect the pump mount flange with soft metal or wood. Never install a vacuum pump that has been dropped 37-10-00 Caution CAUTION: Do not use Teflon tape, pipe dope, or thread lubricants of any type 37-10-00 Caution CAUTION: Do not turn the elbow fitting more than 1.5 turns beyond the hand tight position 37-10-00 Caution CAUTION: Do not use any cork-type gaskets when you install the vacuum pump 37-10-00 Caution CAUTION: Do not apply grease to the splines of the vacuum pump 37-10-00 Caution CAUTION: Make sure that the temperature of the engine does not go above the maximum engine temperature during the adjustment/test ofthe regulator valve 37-10-00 Caution CAUTION: Be careful when you turn the adjustment screw. Do not turn it too much in either direction. When you turn it too much in either direction, damage can occur to the equipment 37-10-00 Caution CAUTION: Do not use metallic wools or solvents to clean installed cables. Metallic wools will embed dissimilar metal particles in the cables and create further corrosion. Solvents will remove internal cable ubricant, allowing cable strands to abrade 51-11-00 Caution CAUTION: Solid film lubricants containing graphite, either alone or in mixture with any other lubricants, should not be used since graphite is cathodic to most metals and will cause galvanic corrosion in the presence of electrolytes 51-11-00 Caution A. Remove the Vacuum Pump 37-10-00 Étape NOTE: The removal/installation is typical for each vacuum pump 37-10-00 Note Vacuum System Installation Figure 201 (Sheet 1) 37-10-00 Document Vacuum System Installation Figure 201 (Sheet 2) 37-10-00 Document Vacuum System Installation Figure 201 (Sheet 3) 37-10-00 Document (1) Remove the engine cowl. Refer to Chapter 71, Cowls - Maintenance Practices. Disconnect the hoses from the inlet and outlet ports of the vacuum pump 37-10-00 Opération 3) Cap the hoses and vacuum pump ports to keep out foreign material 37-10-00 Opération 4 Remove the nuts, lock washers, and flat washers that attach the shroud and vacuum pump to the engine 37-10-00 Opération (5) Remove the shroud and vacuum pump from the studs on the engine 37-10-00 Opération (6) Remove the elbow from the pump 37-10-00 Opération (7) Discard any damaged fittings or nuts with rounded corners 37-10-00 Opération A. Remove the Vacuum Manifold 37-10-00 Étape NOTE: The procedures that follow are for airplanes with standard avionics 37-10-00 Note (1) Remove the engine cowls. Refer to Chapter 71, Cowls - Maintenance Practices. Remove the hoses from the vacuum manifold 37-10-00 Opération (3) Identify with a tag and disconnect electrical connectors from vacuum manifold 37-10-00 Opération 4) Loosen the nut that attaches the vacuum manifold to the nipple in the firewall 37-10-00 Opération 5) Remove the vacuum manifold from the airplane 37-10-00 Opération A. Remove the Filter to the Vacuum Regulator 37-10-00 Étape (1) Remove the pilot seat. Refer to Chapter 25, Front Seats - Maintenance Practices 37-10-00 Opération (2) Reach behind the radio: stack and stretch the foam element overt the top retaining bezel to remove the filter 37-10-00 Opération (3) Remove the filter from the airplane 37-10-00 Opération A. Remove the Gyro Filter 37-10-00 Étape (1) Remove the bolt and retainer from the mount 37-10-00 Opération (2) Remove the gyro filter 37-10-00 Opération A. Remove the Vacuum Gage 37-10-00 Étape NOTE: The procedures that follow are for airplanes with standard avionics 37-10-00 Note NOTE: The vacuum gage and ammeter are incorporated into a single instrument 37-10-00 Note (1) Disconnect the vacuum and air hoses from the vacuum gage 37-10-00 Opération (2) Disconnect the electrical connector from the ammeter 37-10-00 Opération (3) Remove the screws thata attach the vacuum gage to the instrument panel and remove the vacuum gage 37-10-00 Opération A. Remove the Vacuum Transducer 37-10-00 Étape NOTE: Only airplanes with the Garmin G1000 have a vacuum transducer 37-10-00 Note (1) Remove the center panel. Refer to Chapter 31, Instrument and Control Panels - Maintenance Practices 37-10-00 Opération (2) Remove the screw and clamp that hold the vacuum transducer in position 37-10-00 Opération (3) Remove the vacuum transducer 37-10-00 Opération CABIN DOORS - MAINTENANCE 52-10-00 Processus NOTE: Do not oversize holes in the latch base and do not rivet the base to the skin at this time 52-10-00 Note NOTE: The cabin doors must be smooth with the fuselage skin 52-10-00 Note NOTE: Do not install a cotter pin 52-10-00 Note NOTE: The rod must be attached to the latch assembly before the rigging can be accomplished 52-10-00 Note NOTE: This adjustment will make sure that when the door is opened from the outside, the push rod will engage the latch catch, and the exterior handle will stay open until the door is closed again 52-10-00 Note NOTE: If the cabin door is too far forward and the door latch will not operate, the latch assembly push rod cannot ride up on the actuator and trigger thej pull bar. Install shims as necessary below the actuator, which is on the cover assembly 52-10-00 Note NOTE: When you make this adjustment on the over centering of the latch, there can be a sharp, loud canning noise when the inside handle is pushed down. It is preferred that the outside door handle be flush, even if the canning noise is noticeable 52-10-00 Note CAUTION: Do not make the holes oversize in the latch base 52-10-00 Caution CAUTION: Do not adjust the bonded door flange or the airplane structure with force. Damage to the bonded areas and the structural components can occur 52-10-00 Caution A. Cabin Door Removal 52-10-00 Étape STOP ARM NUT WASHER 0710T1001 A0711T1023 DETAIL C C0511T1005 B0711T1025 DETAIL D AIRPLANES WITH STANDARD LOCK AA0711T1026 D0711T1027 Cabin Door Installation Figure 201 (Sheet 1) 52-10-00 Document CAM CODDIS SPRING 6 CATCH SPRING CATCH BASE CATCH ASSEMBLY DETAIL G OUTSIDE DOOR HANDLE F0711R1030 G0711R1030 Cabin Door Installation Figure 201 (Sheet 2) 52-10-00 Document Figure 201 (Sheet 3) 52-10-00 Document ASSEMBLY VIEW C-C LOCK SHOWN IN UNLOCKED POSITION CC1211T1038 BB1211T1038 Cabin Door Installation Figure 201 (Sheet 4) 52-10-00 Document (1) Open the cabin door 52-10-00 Opération L Remove the nut, screw, and spacers from the stop arm 52-10-00 Opération (3) Remove the screws and nuts that attach the hinges to the fuselage 52-10-00 Opération (4) Remove the cabin door from the airplane 52-10-00 Opération A. Cabin Door Weatherstrip Removal 52-10-00 Étape (1) Use a nonmetallic scraper to remove the weatherstrip and adhesive from the door assembly 52-10-00 Opération (2) Use solvent to remove all remaining adhesive from the door surface 52-10-00 Opération A. Cabin Door Latch Lock Removal 52-10-00 Étape (1) Remove the cam from the latching side of the locking arm 52-10-00 Opération L Remove the washers between the cam and the locking arm 52-10-00 Opération (3) Remove the locking arm pin from the locking arm and the catch base assembly 52-10-00 Opération A. Cabin Door Latch Assembly Removal 52-10-00 Étape (1) Remove the cabin door lock assembly. Refer to Cabin Door Lock Assembly Removall Installation 52-10-00 Opération (2) Remove the rivets that attach the latch base to the door skin 52-10-00 Opération 3) Remove the screws that attach the latch to the door pan 52-10-00 Opération (4) Remove the pushrod and bolt 52-10-00 Opération 5) Pull the latch handle through the cutout in the door skin 52-10-00 Opération (6) Remove the latch assembly from the airplane 52-10-00 Opération A. Cabin Door Latch Cable Assembly Removal 52-10-00 Étape (1) Remove the screw and the clamp that attach the cable assembly to the door 52-10-00 Opération (2) Remove the plug button 52-10-00 Opération (3) Remove the pin from the pin guide 52-10-00 Opération 4) Pull the pin end of the cable from the top of the door 52-10-00 Opération (5) Remove the nut and clamp from the opposite end of the cable casing 52-10-00 Opération (6) Remove the cable assembly from the door 52-10-00 Opération A. Cabin Door Lock Assembly Removal 52-10-00 Étape (1) Remove the lower door accent panel and main door panel to get access to the cabin door lock assembly. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 52-10-00 Opération (2) Remove the armrest door plugs, door panel insert at armrest, door handle, and cover plate from the door to get access to the cabin door lock assembly 52-10-00 Opération (3) Remove the nut and washer 52-10-00 Opération (4) Remove the cabin door lock assembly 52-10-00 Opération (2) Remove the armrest door plugs, door panel insert, armrest, door handle, and cover plate from the door to get access to the cabin door lock assembly 52-10-00 Opération (3) Remove the cotter pin, washer, locking arm, and spacer from the lock assembly 52-10-00 Opération (4) Remove the hex nut and the anti-rotational washer that attach the lock tumbler assembly to the door structure and the cam assembly 52-10-00 Opération (5) Remove the lock assembly from the door 52-10-00 Opération A. Cabin Door Lock Cam Assembly Removal 52-10-00 Étape (1) Remove the lower door accent panel and main door panel to get access to the cabin door lock cam assembly. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 52-10-00 Opération (2) Remove the armrest door plugs, door panel insert at armrest, door handle, and cover plate from the door to get access to the cabin door lock cam assembly 52-10-00 Opération (3) Remove the cam stop screw from the cabin door lock cam assembly 52-10-00 Opération (4) Remove the cam assembly 52-10-00 Opération (2) Remove the armrest door plugs, door panel insert, armrest, door handle, and cover plate from the door to get access to the cabin door lock cam assembly 52-10-00 Opération (3) Remove the machine screws, serrated washers, and retaining washer from the cabin door lock cam assembly 52-10-00 Opération CARGO DOORS - MAINTENANCE 52-30-00 Processus NOTE: A flap interrupt switch is installed to prevent the operation of the flaps with the cargo doors open. The switch is adjusted through the slotted holes on the forward cargo door frame 52-30-00 Note NOTE: Refer to Figure 202. The outside door handle on the forward cargo door can be used to close and lock the forward cargo door. Lift the handle out of the recess and grasp the vertical tab of the pull bar behind the handle. Pull the vertical tab o 52-30-00 Note CAUTION: If cargo door is closed and locked from the outside, the inside door handle must be turned fully forward to disengage the outside locking mechanism, and allow the door to be unlocked and opened from the inside 52-30-00 Caution A. Cargo Door Removal 52-30-00 Étape WASHER yo UPPER SOCKET 1210T1001 A1211R1008 DETAIL C DETAIL B B1211R1003 C1211R1003 Cargo Door Installation Figure 201 (Sheet 1) 52-30-00 Document SHIM LATCH PLATE VIEW A-A D1211R1004 E1211R1007 AA1211R1005 Cargo Door Installation Figure 201 (Sheet 2) 52-30-00 Document Figure 201 (Sheet 3) 52-30-00 Document (1) Open the cargo door 52-30-00 Opération (2) Disconnect the doorstop chain 52-30-00 Opération (3) Remove the cotter pins and remove the pins that attach the door 52-30-00 Opération A. Cargo Door Latch Assembly Removal 52-30-00 Étape Cargo Door Latch Installation Figure 202 (Sheet 1) 52-30-00 Document (1) Remove the clip, inside door handle, and washer. Remove the door upholstery panel. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 52-30-00 Opération (3) Remove the spring 52-30-00 Opération (4) Remove the screws that attach the door latch assembly and remove the door latch assembly 52-30-00 Opération A. Cargo Door Weatherstrip Removal 52-30-00 Étape (1) Remove the cargo door 52-30-00 Opération (2) With a nonmetallic scraper, remove the seal and adhesive from the cargo door 52-30-00 Opération (3) Remove the adhesive residue and clean the door seal area with DeSoclean 110 Solvent 52-30-00 Opération (4) Install the cargo door 52-30-00 Opération A. Cargo Door Lock Assembly Removal 52-30-00 Étape (1) Remove the cargo door panel to get access to the cargo door lock assembly. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 52-30-00 Opération (2) Remove the nut and washer 52-30-00 Opération (3) Remove the cabin door lock assembly 52-30-00 Opération (2) Remove the 0.75-inch hex nut and the anti-rotational washer that attach the lock tumbler assembly to the door structure and the cam assembly 52-30-00 Opération (3) Remove the lock assembly from the door 52-30-00 Opération A. Cabin Door Lock Cam Assembly Removal 52-30-00 Étape (1) Remove the cargo door panel to get access to the cargo door lock assembly. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 52-30-00 Opération (2) Remove the cam stop screw from the cabin door lock cam assembly 52-30-00 Opération (3) Remove the cam assembly 52-30-00 Opération A. Cargo Door Lock Cam Assembly Removal 52-30-00 Étape (1) Remove the cargo door panel to get access to the cargo door lock assembly. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 52-30-00 Opération (2) Remove the hex nut and the serrated washer that attach the cam assembly to the cargo door lock 52-30-00 Opération (3) Remove the cam assembly 52-30-00 Opération HORIZONTAL STABILIZER - MAINTENANCE 55-10-00 Processus NOTE: The installation of the left and the right horizontal stabilizer abrasion boot is typical 55-10-00 Note NOTE: You can remove material from the boot as necessary to get the specified clearances 55-10-00 Note A. Remove Horizontal Stabilizer 55-10-00 Étape DETAIL A B0732R1008 C0732R1009 D0732R1010 E0732R1011 Horizontal Stabilizer Installation Figure 201 (Sheet 1) 55-10-00 Document (1) Remove upper fairings (340AL and 340AR) and tailcone stinger (310BB). Refer to Chapter 6, Access/Inspection Plates - Description and Operation 55-10-00 Opération (2) Remove elevators. Refer to Chapter 27, Elevator Control System - Maintenance Practices 55-10-00 Opération (3) Remove rudder. Refer to Chapter 27, Rudder Control System - Maintenance Practices 55-10-00 Opération (4) Remove vertical stabilizer fin. Refer to Vertical Stabilizer Fin - Maintenance Practices 55-10-00 Opération (5) Disconnect elevator trim control cables at clevis and turnbuckle inside tailcone 55-10-00 Opération (6) Remove pulleys which route the aft cables into horizontal stabilizer, and pull cables out of tailcone. Refer to Chapter 27, Elevator Trim Control - Maintenance Practices 55-10-00 Opération (7) Remove bolts securing horizontal stabilizer to fuselage 55-10-00 Opération (8) Remove horizontal stabilizer 55-10-00 Opération A. Remove the Horizontal Stabilizer Abrasion Boot 55-10-00 Étape NOTE: The removal of the left and the right horizontal stabilizer abrasion boot is typical 55-10-00 Note WARNING: Make sure that the airplane stays grounded during the removal and the installation of the abrasion boots. Static sparks can cause solvent vapors to ignite and cause damage to the airplane or injury to personnel 55-10-00 Warning Horizontal Stabilizer Abrasion Boot Installation Figure 202 (Sheet 1) 55-10-00 Document Horizontal Stabilizer Abrasion Boot Installation Figure 202 (Sheet 2) 55-10-00 Document (1) Make sure that the airplane is correctly grounded. Make sure that all switches are in the OFF position 55-10-00 Opération 3) Disconnect the external electrical power unit from the airplane 55-10-00 Opération (4) Disconnect the battery cables from the battery. Refer to Chapter 24, Battery - Maintenance Practices 55-10-00 Opération (e) Apply a coating of corrosion resistant primer. Refer to Chapter 20, Interior and Exterior Finish - Cleaning/Painting 55-10-00 Opération (f) Let the corrosion resistant primer cure 55-10-00 Opération (g) Remove the masking tape 55-10-00 Opération VERTICAL STABILIZER FIN - MAINTENANCE 55-30-00 Processus NOTE: Equivalent substitutes may be used for the following listed items 56-00-00 Note NOTE: When applying and removing wax and polish, use a clean, soft cloth, such as cotton or cotton flannel 56-00-01 Note NOTE: Utilization of the following techniques will help minimize windshield and window crazing 56-00-01 Note CAUTION: Windshields and windows (acrylic-faced) are easily damaged by improper handling and cleaning techniques 56-00-01 Caution CAUTION: Do not use methanol, denatured alcohol, gasoline, benzene, xylene, methyl n-propyl ketone, acetone, carbon tetrachloride, lacquer thinners, commercial or household window cleaning sprays on windshields or windows 56-00-01 Caution A. Remove Vertical Stabilizer Fin 55-30-00 Étape BOLT WASHERS @ 0731R1008 DETAIL D A0731R1006 DETAIL C C0731R1003 B0731R1004 DO731R1007 Vertical Stabilizer Fin Installation Figure 201 (Sheet 1) 55-30-00 Document (1) Remove rudder. Refer to Chapter 27, Rudder Control System -- Maintenance Practices 55-30-00 Opération (2) Remove upper fairings (340AL and 340AR) and tailcone stinger (310BB). Refer to Chapter 6, Access/Inspection Plates - Description and Operation 55-30-00 Opération (3) Disconnect all electrical and navigation leads from base of fin area 55-30-00 Opération (4) Remove screws attaching dorsal to fin 55-30-00 Opération (5) Disconnect elevator cable from elevator bellcrank 55-30-00 Opération 6) Remove bolts attaching fin rear spar to fuselage fitting 55-30-00 Opération 7) Remove upper elevator stop bolts 55-30-00 Opération (8) Remove bolts attaching fin front spar to fuselage bulkhead and remove fin from fuselage 55-30-00 Opération WINDSHIELD - MAINTENANCE 56-10-00 Processus NOTE: Use care not to crack windshield when installing. If not previously removed, top retainer may be removed if necessary 56-10-00 Note NOTE: Screws and self-locking nuts may be used instead of rivets which fasten front retaining strip to cowl deck. If at least No. 6 screws are used, no loss of strength will result 56-10-00 Note A. Remove Windshield 56-10-00 Étape CAUTION: Ifwindshield is to be reinstalled, be sure to protect windshield during removal 56-10-00 Caution DETAIL C A1211R1025 B0511R3002 C0511R3002 DO511R3002 Windshield Installation Figure 201 (Sheet 1) 56-10-00 Document (1) Remove wing fairings 56-10-00 Opération (2) Remove magnetic compass. Refer to Chapter 34, Compass Installation - Maintenance Practices 56-10-00 Opération (3) Remove air vent tubes. Refer to Chapter 21, Fresh Air Distribution - Maintenance Practices 56-10-00 Opération (4) Drill out rivets securing front retainer strip 56-10-00 Opération (5) Pull windshield straight forward, out of side and top retainers. Remove top retainer if necessary 56-10-00 Opération (6) Clean sealer from inner sidewalls and bottom of retainers 56-10-00 Opération CABIN WINDOWS - MAINTENANCE 56-20-00 Processus NOTE: The fillet seal should be done after the airplane has been painted, if applicable 56-20-00 Note A. Remove Rear Window 56-20-00 Étape SKIN 1210T1002 A0711T1003 B0711T1004 DETAIL C C0711T1005 D0711T1006 Cabin Windows Installation Figure 201 (Sheet 1) 56-20-00 Document (1) Remove upholstery as necessary to expose retainer strips inside cabin. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 56-20-00 Opération (2) Remove the fillet seal around the exterior edges of the window. Refer to Chapter 20, Fuel, Weather and High-lemperature Sealing - Maintenance Practices 56-20-00 Opération (3) Remove rivets as necessary to remove outer retainer strip along aft edge of window 56-20-00 Opération (4) Remove window by lifting aft edge and pulling window aft. If difficulty is encountered, rivets securing retainer strips inside cabin may also be drilled out and retainer strips loosened or removed 56-20-00 Opération A. Remove Side Window 56-20-00 Étape (1) Remove upholstery as required to gain access to retainer strips inside cabin. Refer to Chapter 25, Interior Upholstery - Maintenance Practices 56-20-00 Opération (2) Remove the fillet seal around the exterior edges of the window. Refer to Chapter 20, Fuel, Weather and High-lemperature Sealing - Maintenance Practices 56-20-00 Opération (3) Remove the rivets securing retainer strips to the airplane 56-20-00 Opération (4) Remove the window from the airplane 56-20-00 Opération CABIN DOOR WINDOWS - MAINTENANCE 56-30-00 Processus NOTE: Equivalent substitutes may be used for the following listed items 57-00-00 Note A. Remove Cabin Door Window 56-30-00 Étape Cabin Door Window Installation Figure 201 (Sheet 1) 56-30-00 Document (1) Disconnect arm from window assembly 56-30-00 Opération (2) Remove hinge pins from hinge 56-30-00 Opération WINGS AND WING STRUTS - MAINTENANCE 57-10-00 Processus NOTE: Lightly lubricate wing attach bolt shanks and holes with MIL-G-21164 grease before installing bolts 57-10-00 Note NOTE: Wrap wing strut using 1 inch wide 3M Y8671 polyurethane tape centered at point where strut cuff terminates 57-10-00 Note NOTE: If considerable control wheel pressure is required to keep the wings level in normal flight, a "wing heavy" condition exists and can be corrected by the following procedure 57-10-00 Note NOTE: The eccentric cams should only be adjusted after all other systems have been adjusted and rigged 57-10-00 Note NOTE: If the strut is severely dented, cracked or deformed, it should be replaced. The following procedures are applicable only to the specific areas of the strut 57-10-00 Note NOTE: The following applies to wing struts with grooves worn in the lower trailing edge. This type of damage can occur after extensive cabin door usage with a missing or improperly adjusted door stop, which allows the door to contact the aft edge of 57-10-00 Note WARNING: Some right wings have a spar cap 0.100 inches thick, and are not to be used on increased weight STC's (such as float planes) 57-10-00 Warning CAUTION: Do not lubricate the threads of the bolts 57-10-00 Caution CAUTION: Ensure the eccentric bushings are rotated simultaneously. Rotating them separately will destroy the alignment between the off-center bolt holes in the bushings, thus exerting a shearing force on the bolt, with possible damage to the hole in 57-10-00 Caution A. Remove Wing and Strut 57-10-00 Étape NOTE: Wings are most easily removed if four people are available to handle the wing. Otherwise, the wing should be supported with a sling or maintenance stand when the fasteners are loosened 57-10-00 Note NOTE: To ease rerouting of cables, a guide wire may be attached to each cable before it is pulled free from the wing. Cable may then be disconnected from the guide wire. Leave the guide wire routed through the wing; it will be reattached to the cable 57-10-00 Note NOTE: Tape flaps in the streamlined position during wing removal. This will prevent flap movement during handling 57-10-00 Note SHOULD BE TAKEN TO INSTALL THE SHORT BUSHING 57-10-00 Note IN THE FORWARD SIDE AND THE LONG BUSHING IN C 57-10-00 Note NOTE: It may be necessary to rock the wings slightly and/or to use a long drift punch to remove attaching bolts 57-10-00 Note WARNING: DO NOT LUBRICATE THE THREADS OF THE BOLT. AA1220R1002 C0520R1003 Wing and Strut Installation Figure 201 (Sheet 1) 57-10-00 Document NOTE 3: WRAP WING STRUT USING 3M Y8671 POLYURETHANE TAPE (1 INCH WIDE) DETAIL F D1220R1004 CENTERED AT POINT WHERE STRUT E1220R1006 CUFF TERMINATES. G1220R1007 F1220R1005 Wing and Strut Installation Figure 201 (Sheet 2) 57-10-00 Document (1) Remove fairings from wing/fuselage intersection. Remove inspection plates as required to allow for disconnection of all electrical, mechanical and fuel connections 57-10-00 Opération (3) Drain fuel from wing bay. Refer to Chapter 12, Fuel Servicing 57-10-00 Opération (4) Disconnect electrical wires at wing root disconnects 57-10-00 Opération (5) Disconnect fuel lines at wing root 57-10-00 Opération 6) On left wing, disconnect pitot line 57-10-00 Opération 7) Disconnect fresh air distribution duct at wing root 57-10-00 Opération 8) Loosen turnbuckle and disconnect aileron cables at aileron bellcrank. Remove cable guard and pull cable from wing. Refer to Chapter 27, Aileron Control System - Maintenance Practices 57-10-00 Opération (9) Disconnect aileron carry-through cables at turnbuckle above cabin headliner, and pull cables into wing root area. Refer to Chapter 27, Aileron Control System - Maintenance Practices 57-10-00 Opération (10) Disconnect flap cables at turnbuckles above cabin headliner, and pull cables into wing root area. Refer to Chapter 27, Flap Control System - Maintenance Practices 57-10-00 Opération (11) Remove screws from strut fairings and slide fairings toward center of strut 57-10-00 Opération (12) Support wing at outboard end. Remove strut-to-wing attach bolt and strut-to-fuselage attach bolt 57-10-00 Opération (13) Remove strut from between wing and fuselage 57-10-00 Opération (14) Mark position of wing attachment eccentric bushings in relationship to fittings. These bushings 57-10-00 Opération (15) Remove nuts, washers, bushings and bolts attaching wing spars to fuselage 57-10-00 Opération (16) Remove wing and lay on padded stand 57-10-00 Opération A. Remove Wing Tip 57-10-00 Étape Figure 202 57-10-00 Document (1) Remove screws securing wing tip to wing 57-10-00 Opération 2) Remove screw securing strobe light and navigation light ground straps to power supply 57-10-00 Opération (3) Disconnect navigation light electrical connector 57-10-00 Opération (4) Disconnect strobe light electrical connector 57-10-00 Opération (5) Remove wing tip from wing 57-10-00 Opération PROPELLER - MAINTENANCE 61-10-00 Processus WARNING: Do not stand or let anyone stand close to the propeller. Do maintenance as if the power to the propeller is always on 61-10-00 Warning CAUTION: Make sure you remove minimal spinner material as necessary to give minimum clearance between the spinner and the propeller blades 61-10-00 Caution A. Remove the Spinner 61-10-00 Étape WARNING: Do not stand or let anyone stand close to the propeller. Do maintenance as if the power to the propeller is always on 61-10-00 Warning Propeller and Spinner Installation Figure 201 (Sheet 1) 61-10-00 Document (1) Disconnect all electrical power from the airplane 61-10-00 Opération (2) Make sure the magneto switch is in the off position and is electrically grounded before you turn the propeller 61-10-00 Opération (3) Remove the screws and washers that attach the spinner to the spinner bulkhead assembly 61-10-00 Opération (4) Remove the spinner, spinner stabilizer and spacers from the propeller assembly 61-10-00 Opération (a) Write the number of spacers that is removed for installation of the spinner 61-10-00 Opération A. Remove the Propeller 61-10-00 Étape NOTE: As the propeller assembly is separated from the engine crankshaft, oil will drain from the propeller and engine crankshaft cavities 61-10-00 Note WARNING: Do not stand or let anyone stand close enough to the propeller to be hit by it. Maintenance must be done as if the power to the propeller is always on 61-10-00 Warning (1) Disconnect all electrical power from the airplane 61-10-00 Opération (2) Make sure the magneto switch is in the off position and is electrically grounded before you turn the propeller 61-10-00 Opération (3) Remove the spinner. Refer to Spinner Removal/Installation 61-10-00 Opération (4) Remove the cowl assemblies as necessary to get access to the propeller mounting bolts 61-10-00 Opération (a) If the airplane is installed with a optional prop deice system, remove the brush block assembly before you remove the propeller to prevent possible damage to the brush 61-10-00 Opération (5) Remove the safety wire from the mounting bolts 61-10-00 Opération (6) Remove the mounting bolts 61-10-00 Opération (a) The propeller mounting bolts must be magnetic particle inspected per ASTM E-1444 or liquid penetrant inspected per ASTM E-1417 or replaced at every overhaul. Propeller mounting bolts must be replaced whenever the propeller is involved in a blade 61-10-00 Opération (b) Equally loosen the mounting bolts approximately 0.25 inch (6 mm) 61-10-00 Opération (c) Pull the propeller assembly forward, using the 0.25 inch (6 mm) given from the loosened bolts 61-10-00 Opération (d) Continue to equally loosen the bolts and pull the propeller assembly forward, 0.25 inch (6 mm) at a time, until all the nuts are removed 61-10-00 Opération (7) Remove the propeller assembly and O-ring from the engine propeller shaft 61-10-00 Opération PROPELLER GOVERNOR - MAINTENANCE 61-20-00 Processus NOTE: THESE SCREWS MAY ONLY BE USED ONCE. WHEN REMOVED, THESE SCREWS MUST BE REPLACED WITH NEW SCREWS. REFERENCE MCCAULEY SERVICE LETTER 2000-11, VIEW A-A FOR SCREW AND TORQUE RECOMMENDATIONS 61-20-00 Note NOTE: Due to climate conditions, field elevation, low pitch propeller blade angle, and other factors, an engine may not reach rated RPM on the ground. It may be necessary to readjust the governor high RPM stop screw after test flying to obtain maximu 61-20-00 Note NOTE: The result of rigging of the governor control is full travel of the governor control arm (bottomed out against both high and low pitch stops) with some cushion at both ends of the control travel 61-20-00 Note NOTE: Identify washers and position of washers for use when reconnecting control cable to control arm 61-20-00 Note NOTE: This allows cushion which will assure full contact with governor high RPM stop screw 61-20-00 Note NOTE: Maintain sufficient thread engagement during adjustments. It may be necessary to adjust the position of the control cable in the control cable bracket restraint to achieve proper alignment and thread engagement 61-20-00 Note NOTE: Iflow power is suspected, the following static runup procedures may by used in conjunction with the troubleshooting chart to develop a diagnosis 71-00-01 Note NOTE: Variances in atmospheric pressure, temperature and humidity can have a significant impact on runup RPM. Low static runup RPM information should be used only in conjunction with other troubleshooting procedures to determine if a problem actually 71-00-01 Note WARNING: Exercise care when working with the propeller. Always treat the propeller as if the ignition switch were on. Do not stand, nor allow anyone else to stand, within the arc of the propeller. Ensure magneto switch is in the off position before t 61-20-00 Warning WARNING: Ensure magneto is grounded before turning propeller 61-20-00 Warning WARNING: Exercise care when working with the propeller. Always treat the propeller as if the ignition switch were on. Do not stand, nor allow anyone else to stand, within the arc of the propeller. Ensure magneto switch is in the off position before t 61-20-00 Warning WARNING: Ensure magneto is grounded before turning propeller 61-20-00 Warning WARNING: Exercise care when working with the propeller. Always treat the propeller as if the ignition switch were on. Do not stand, nor allow anyone else to stand, within the arc of the propeller. Ensure magneto switch is in the off position before t 61-20-00 Warning CAUTION: Do not force spline engagement. Rotate crankshaft slightly and splines will mesh smoothly when properly aligned 61-20-00 Caution CAUTION: Do not exceed 50 in-lbs when tightening nut to line up cotter pin hole with castellations in nut 61-20-00 Caution CAUTION: Do not exceed 50 in-lbs when tightening nut to line up cotter pin hole with castellations in nut 61-20-00 Caution A. Remove Propeller Governor 61-20-00 Étape NOTE: Identify washers and position of washers for use when reconnecting control cable to control arm 61-20-00 Note WARNING: Exercise care when working with the propeller. Always treat the propeller as if the ignition switch were on. Do not stand, nor allow anyone else to stand, within the arc of the propeller. Ensure magneto switch is in the off position before t 61-20-00 Warning GOLO 0 As JAMNUT CONTROL CABLE ROD END CONTROL. ARM WASHER Coymumero NUT AND COTTER PIN BOLT A WASHER WASHER DETAIL A A0755T1003 1210T1001 AA0755R1006 Propeller Governor Installation Figure 201 (Sheet 1) 61-20-00 Document (1) Remove all power from airplane 61-20-00 Opération (2) Remove cowl assemblies as required for access to propeller governor located forward on left side of engine 61-20-00 Opération (3) Remove cotter pin, nut, washers, and bolt securing control cable to control arm 61-20-00 Opération (4) Loosen bolts to restraint bracket securing control cable to control cable bracket. Remove control cable from bracket 61-20-00 Opération (5) Remove nuts and washers securing propeller governor to engine 61-20-00 Opération (6) Remove propeller governor and mount gasket 61-20-00 Opération A. Remove Propeller Control Cable 61-20-00 Étape CAUTION: The control cable is not repairable and must be replaced at every engine overhaul 61-20-00 Caution (1) Remove upper cowling. Refer to Chapter 71, Cowls Maintenance Practices 61-20-00 Opération 2) Remove cotter pin, nut, washers, and bolt securing control cable to control arm. Discard cotter pin 61-20-00 Opération (3) Remove control cable rod end 61-20-00 Opération (4) Loosen bolts securing cable restraint bracket to cable bracket. Remove cable 61-20-00 Opération (5) Remove nut, washer, bolt and clamp securing cable to manifold induction tube 61-20-00 Opération 6) Route cable through grommet in engine baffle 61-20-00 Opération (7) Remove control cable retaining nut and washer at firewall and pull control cable aft through firewall 61-20-00 Opération (8) Remove retaining nut and washer from control cable 61-20-00 Opération (9) Remove retaining nut and washer on forward side of instrument panel from control cable while pulling control cable from instrument panel 61-20-00 Opération ENGINE - MAINTENANCE 71-00-01 Processus A. Remove Engine 71-00-01 Étape WARNING: Disconnecting the P-lead wire from the magnetos will remove the electrical ground from the magneto circuit, resulting in hot magnetos. A separate ground wire must be run to the magnetos or the high tension wires removed from the spark plugs 71-00-01 Warning (1) Place all cabin switches and the fuel shutoff valve in the OFF position 71-00-01 Opération (2) Remove engine cowling 71-00-01 Opération (3) Disconnect positive and negative battery leads from battery 71-00-01 Opération 4) Loosen C-clamp securing flexible duct to nose cap. Remove flexible duct from nose cap 71-00-01 Opération (5) Loosen C-clamp securing flexible duct to firewall-mounted heater valve. Remove flexible duct from heater valve 71-00-01 Opération (6) On turbocharged airplanes, loosen clamp securing induction duct to turbocharger. Remove duct from turbocharger 71-00-01 Opération (7) Remove the propeller. Refer to Chapter 61, Propeller - Maintenance Practices, Propeller Removal/Installation 71-00-01 Opération (8) Disconnect P lead wires on magnetos 71-00-01 Opération (9) Remove propeller governor. Refer to Chapter 61, Propeller Governor - Maintenance Practices 71-00-01 Opération (10) For airplanes with standard avionics, disconnect the electrical connector from the EGT Probe (on non-turbocharged airplanes) or disconnect the electrical connector from the TIT Probe (on turbocharged airplanes) 71-00-01 Opération (11) For airplanes with standard avionics, disconnect the electrical terminal from the CHT probe 71-00-01 Opération (12) For airplanes with Garmin G1000 avionics, disconnect the EGT and the CHT thermocouple connectors 71-00-01 Opération (13) Disconnect fuel outlet line at the fuel strainer 71-00-01 Opération (14) Disconnect throttle and mixture cables at fuellair control unit. Note position of washers and spacers for later reassembly 71-00-01 Opération (15) Disconnect: throttle and mixture cables from cable attach bracket by removing screws, washers and nuts securing retaining clamps 71-00-01 Opération (16) On turbocharged airplanes, disconnect and cap oil lines from controller assembly 71-00-01 Opération (17) Disconnect drain lines and vent tubes 71-00-01 Opération (18) Disconnect vacuum hose at firewall connection 71-00-01 Opération (19) Disconnect manifold pressure line at firewall 71-00-01 Opération (20) Ont turbocharged airplanes, disconnecti manifold pressure line (from induction plenum) and upper deck pressure line (from induction elbow) from the controller assembly 71-00-01 Opération (21) If installed, disconnect and label electrical wires on vacuum switches 71-00-01 Opération (22) For airplanes with standard avionics, loosen and remove tachometer drive cable clamps in engine area. Disconnect tachometer drive cable from rear of accessory case 71-00-01 Opération (23) For airplanes with Garmin G1000 avionics, remove the tachometer sending unit. Refer to Chapter 77, Tachometer - Maintenance Practices 71-00-01 Opération (24) Cut tie wraps (sta straps) securing the various wire bundles to the engine 71-00-01 Opération (25) Loosen and remove clamp securing starter and alternator wires to forward baffle 71-00-01 Opération (26) Remove starter wires from starter 71-00-01 Opération (27) Remove alternator wires from alternator 71-00-01 Opération (28) Loosen and remove clamp securing starter and alternator wires to forward baffle 71-00-01 Opération (29) Disconnect ground wire from engine mount 71-00-01 Opération (30) Disconnect electrical connector from fuel pressure transducer (on non-turbocharged airplanes) or disconnect electrical connector from fuel flow transducer and electrical connector from upper deck pressure transducer (on turbocharged airplanes) 71-00-01 Opération (31) Disconnect electrical connector from low oil pressure switch 71-00-01 Opération (32) Disconnect electrical connector from oil pressure transducer 71-00-01 Opération (33) Disconnect electrical terminal from oil temperature sensor 71-00-01 Opération (34) Place stand under tail tie-down to allow for tail heavy condition, which will occur when engine is removed from airframe 71-00-01 Opération (35) Attach hoist to lifting strap on top of engine. Begin to take up engine weight using hoist 71-00-01 Opération (36) Remove bolts attaching engine shock mounts to engine mount assembly. Slowly raise engine using hoist until engine is free of structure 71-00-01 Opération COWLS - MAINTENANCE 71-10-00 Processus procedures 71-10-00 Note NOTE: Be sure threads are visible in clevis inspection holes 71-10-00 Note NOTE: Maintain sufficient thread engagement of clevis 71-10-00 Note NOTE: In all cases, the flexible controls must reach their internal stops in each direction to assure full travel of the controls 71-10-00 Note A. Remove Cowl 71-10-00 Étape FACE PLATE LOWER COWL INDUCTION AIR ASSEMBLY 1210T1001 A1252T1001 DETAIL A A1252T1002 A1213T1018 Engine Cowl Installation Figure 201 (Sheet 1) 71-10-00 Document DETAIL C B1213T1001 C0752T1007 Engine Cowl Installation Figure 201 (Sheet 2) 71-10-00 Document (1) Release quick- release fasteners around perimeter of left and right upper cowl 71-10-00 Opération 2) Remove left and right upper cowls 71-10-00 Opération (3) Remove screws securing left nose cap assembly from right nose cap assembly 71-10-00 Opération (4) Remove screws securing left and right nose cap assemblies to lower cowl 71-10-00 Opération (5) Remove nose cap assemblies 71-10-00 Opération (6) On turbocharged airplanes, remove screws around sides and bottom of lower right cowl 71-10-00 Opération (7) Remove lower right cowl 71-10-00 Opération A. Remove Cowl Flap 71-10-00 Étape Figure 202 (Sheet 1) 71-10-00 Document (1) Place cowl flap control lever in the OPEN position 71-10-00 Opération (2) Disconnect cowl flap control clevises from cowl flap shock mounts 71-10-00 Opération (3) Remove safety wire securing hinge pins to cowl flaps, pull hinge pins and remove cowl flaps 71-10-00 Opération ENGINE MOUNT - MAINTENANCE 71-20-00 Processus NOTE: Take caution to ensure that the bolts are not shanked out 71-20-00 Note AIR INDUCTION SYSTEM (NON-TURBOCHARGED) - MAINTENANCE 71-60-00 Processus A. Remove System Components 71-60-00 Étape Figure 201 (Sheet 1) 71-60-00 Document (1) Remove right side of upper cowling. Refer to Cowls - Maintenance Practices. Remove bolts securing air filter to air box assembly. Remove air filter 71-60-00 Opération 3) Loosen clamps on induction air box duct to disconnect induction air box from induction air manifold 71-60-00 Opération DRAIN LINES - MAINTENANCE 71-70-00 Processus NOTE: For a schematic of the entire fuel system, refer to Chapter 27, Fuel Storage and Distribution - Description and Operation 73-00-01 Note A. Remove the Drain Lines 71-70-00 Étape NOTE: A non-turbocharged airplane installed with a cylinder drain can, will have one cylinder drain that extends out of the lower left cowl 71-70-00 Note Non-lurbocharged Engine Drain Line Assembly Figure 201 (Sheet 1) 71-70-00 Document (1) Remove the cowls. Refer to Chapter 71, Cowls - Maintenance Practices 71-70-00 Opération (2) Remove the applicable clamps, fittings and drain line 71-70-00 Opération A. Remove the Cylinder Drain Can 71-70-00 Étape Non-lurbocharged Drain Line Assembly Figure 202 (Sheet 1) 71-70-00 Document (1) Remove the cowls to get access to the cylinder drain line. Refer to Chapter 71, Cowls - Maintenance Practices 71-70-00 Opération (2) Remove the upper and lower clamps that attach the cylinder drain lines to the cylinder drain can 71-70-00 Opération (3) Remove the two bolts that attach the cylinder drain can to the engine compartment and remove the cylinder drain can from the airplane 71-70-00 Opération FUEL INJECTION SYSTEM - MAINTENANCE 73-00-01 Processus NOTE: If the fuel injection system was opened for maintenance, the system must be flushed with fuel prior to closing to purge the system of contamination 73-00-01 Note NOTE: For additional information in conjunction with procedures below, refer to the Precision Airmotive Service Letter SIL RS-67 73-00-01 Note NOTE: It may not be possible to get an oil temperature of 150°F (65°C) at cooler ambient temperatures. In that condition it will be necessary to set idle speed and mixture at a lower temperature 73-00-01 Note NOTE: Do not mistake this as the total RPM rise 73-00-01 Note NOTE: To aid in the adjustment of the fuel mixture, the clevis on the fuel servo has an L (lean) and R (rich) stamp on it to indicate the direction that the thumb wheel should be moved to enrichen the fuel mixture and increase the RPM rise. If you tu 73-00-01 Note NOTE: If the mixture was excessively rich or lean when this procedure was started the engine speed will require readjustment as the fuel mixture is adjusted to the desired value. Set the idle speed to the specified RPM after the mixture has been set 73-00-01 Note NOTE: Small changes in the idle speed and RPM are permitted. Find the cause of any large variations in RPM 73-00-01 Note WARNING: During adjustment procedure stay clear of propeller and/or propeller blast to avoid possible injury or death 73-00-01 Warning WARNING: You must turn off the engine to adjust the fuel pump pressure and restart it to continue a check of the fuel pressure 73-00-01 Warning CAUTION: Use only fuel soluble lubricants (such as engine oil) on the nozzle threads during installation 73-00-01 Caution A. Remove Fuel/Air Control Unit 73-00-01 Étape (1) Place cockpit mounted FUEL SELECTOR SHUTOFF valve in the OFF position 73-00-01 Opération 2) Remove upper cowling. Refer to Chapter 71, Cowls - Maintenance Practices 73-00-01 Opération (3) Remove clamps securing induction duct to inlet adaptor (on non-turbocharged airplanes) or remove bolts, washers and nuts securing induction duct to control unit (on turbocharged airplanes) 73-00-01 Opération (4) Disconnect fuel inlet and outlet lines from control unit 73-00-01 Opération (5) Remove mixture and throttle control linkages from control unit. Note number and position of washers for reinstallation 73-00-01 Opération (6) Remove bolts, washers and nuts securing inlet adaptor (on non-turbocharged airplanes) and control cable bracket to base of control unit 73-00-01 Opération (7) Remove bolts, washers and nuts securing control unit to engine induction plenum. Cover induction plenum opening and place control unit in a sealed, dust free environment to prevent accumulation of foreign particles into unit 73-00-01 Opération A. Remove Fuel Distribution Valve 73-00-01 Étape (1) Remove upper cowling. Refer to Chapter 71, Cowls - Maintenance Practices 73-00-01 Opération L) Disconnect all lines leading in to and out of fuel distribution valve 73-00-01 Opération (3) Remove nuts, bolts, washers and spacers securing fuel distribution valve to engine case 73-00-01 Opération A. Remove Injection Nozzles 73-00-01 Étape NOTE: The nozzles consist of two pieces. Make sure that the nozzle inserts stay with the nozzle bodies and that the nozzles are reinstalled in the same cylinder 73-00-01 Note (1) Remove upper cowling. Refer to Chapter 71, Cowls - Maintenance Practices. Remove rigid fuel lines leading to individual nozzles 73-00-01 Opération (3) Remove nozzles from cylinders 73-00-01 Opération FUEL FLOW INDICATION SYSTEM - MAINTENANCE 73-30-00 Processus NOTE: Refer to the following table for tools, equipment and material used throughout the chapter 74-00-00 Note A. Remove the Manifold Pressure/Fuel Flow Indicator 73-30-00 Étape NOTE: The manifold pressure/fuel flow indicator is only installed on airplanes without the G1000 installed and is found on the left side of the instrument panel 73-30-00 Note (1) Make sure that all electrical power to the airplane is off 73-30-00 Opération L Disengage the INST circuit breaker on the circuit breaker panel 73-30-00 Opération (3) Remove the screws that attach the manifold pressure/fuel flow indicator to the instrument panel 73-30-00 Opération (4) Carefully remove the manifold pressure/fuel flow indicator from thel bottom side of the instrument panel 73-30-00 Opération (5) Disconnect the electrical connector from the manifold pressure/fuel flow indicator 73-30-00 Opération (6) Disconnect the manifold pressure tube from the manifold pressure/fuel flow indicator 73-30-00 Opération A. Remove the Fuel Pressure Transducer 73-30-00 Étape NOTE: The fuel pressure transducer is only installed on non-turbocharged airplanes without the G1000 installed. The fuel pressure transducer is used to indicate fuel flow on the manifold pressure/fuel flow indicator 73-30-00 Note FUEL HOSE- DETAIL C DETAIL D T206H08001 THRU T206H08168 T206H08169 AND ON 1210T1001 A1250T1009 Fuel Flow Indicating Installation Figure 201 (Sheet 1) 73-30-00 Document (1) Disconnect electrical power from the airplane 73-30-00 Opération 2) Disengage the INST circuit breaker on the circuit breaker panel 73-30-00 Opération (3) Remove the upper cowling. Refer to Chapter 71, Cowls - Maintenance Practices 73-30-00 Opération (4) Disconnect the fuel pressure transducer electrical connector 73-30-00 Opération (5) Remove the fuel pressure transducer and packing from the union 73-30-00 Opération A. Remove the Fuel Flow Transducer 73-30-00 Étape (1) Disconnect electrical power from the airplane. Disengage the INST circuit breaker on the circuit breaker panel 73-30-00 Opération (3) Remove the upper cowling. Refer to Chapter 71, Cowls - Maintenance Practices 73-30-00 Opération (4) Disconnect the electrical connector from the fuel flow transducer 73-30-00 Opération 5) Disconnect the fuel tubes from the fuel flow transducer 73-30-00 Opération (6) Remove the fuel flow transducer from the airplane 73-30-00 Opération (1) Disconnect electrical power from the airplane. Disengage the NAV I ENG circuit breakers on the ESS BUS and AVN BUS 1 on the circuit breaker panel 73-30-00 Opération (a) Airplanes without the G1000 installed disengage the INST circuit breaker on the circuit breaker panel 73-30-00 Opération (3) Remove the upper cowling. Refer to Chapter 71, Cowls - Maintenance Practices 73-30-00 Opération 4) Disconnect the electrical connector from the fuel flow transducer 73-30-00 Opération (5) Disconnect the fuel hoses from the fuel flow transducer 73-30-00 Opération (6) Remove the screws that hold the fuel flow transducer to the baffle 73-30-00 Opération (7) Remove the fuel flow transducer from the airplane 73-30-00 Opération IGNITION SYSTEM - MAINTENANCE 74-10-00 Processus NOTE: It is possible to adjust the Magneto-to-Engine timing a maximum total of 0.125 inch 74-10-00 Note (3.17 mm) movement from the original factory position, or between each internal timing 74-10-00 Note adjustment. The external timing movement of 0.125 inch (3.17 mm) approximately equals 74-10-00 Note 5 degrees of internal timing change 74-10-00 Note NOTE: Most standard aircraft magneto timing lights show open points with a Light On condition and/or a signal that you can hear 74-10-00 Note NOTE: Most standard aircraft magneto timing lights indicate open points with a Light On condition and/or an signal that you can hear 74-10-00 Note NOTE: You will hear a click sound from the impulse couplings when they release 74-10-00 Note NOTE: The timing light must indicate points open at. 20 degrees BTDC, with the number one cylinder on the compression stroke 74-10-00 Note NOTE: Refer to Figure 601 for the following steps 74-30-00 Note CAUTION: Make sure the gasket surfaces are clean to prevent oil leaks 74-10-00 Caution CAUTION: Make sure you remove the T-118 timing pin immediately after you attach the magneto to the accessory case and before the magneto or propeller is turned 74-10-00 Caution CAUTION: Make sure you remove the T-118 timing pin before the magneto or propeller is turned 74-10-00 Caution CAUTION: Do not torque the nuts more than 17 foot-pounds (23 N-m) or the mounting flange can crack 74-10-00 Caution A. Remove the Magneto 74-10-00 Étape NOTE: The removal and installation procedures for each magneto are typical 74-10-00 Note NOTE: You will hear a click sound from the impulse couplings when they release 74-10-00 Note WARNING: Make sure that each magneto P-lead is grounded 74-10-00 Warning WARNING: Before you turn the propeller, remove a minimum of one spark plug from each cylinder to prevent the start of the engine at that time 74-10-00 Warning Figure 201 (Sheet 1) 74-10-00 Document (1) Remove the engine cowl. Refer to Chapter 71, Engine Cowl - Maintenance Practices 74-10-00 Opération (2) Remove the screws that attach the high tension outlet cover to the magneto 74-10-00 Opération (3) Disengage the high tension cover from the magneto 74-10-00 Opération (4) For a reference point when you install the magneto, turn the propeller in the normal direction until each impulse coupling releases near Top Dead Center (TDC) on the number one cylinder compression stroke 74-10-00 Opération (9) Examine the magneto angle to help make sure you put it in the same position for installation 74-10-00 Opération (10) Remove the nuts, washers and clamps that attach the magneto to the engine housing 74-10-00 Opération (11) Remove the magneto from the housing 74-10-00 Opération A. Switch Removal 74-30-00 Étape NOTE: Wiring need notl be removed from posts of switch if wiring is of sufficient length to allow switch assembly to be moved to a position where disassembly can be accomplished. If wiring is to be disconnected, tag or mark wires for reinstallation 74-30-00 Note (1) Disconnect battery 74-30-00 Opération (2) Remove switch assembly from instrument panel by loosening locknut on the forward side of panel and removing decorative nut on aft side of panel 74-30-00 Opération (1) Hold switch body in position shown in Figure 601 74-30-00 Opération L) Remove screws and washers 74-30-00 Opération (3) Lift terminal board assembly from body, being careful not to lose springs and cups 74-30-00 Opération in switch body SO that no binding occurs. Secure terminal board assembly to switch body with 74-30-00 Opération retained washers and screws 74-30-00 Opération (3) Mark switch with a dab of red paint on the terminal board retaining screws 74-30-00 Opération (4) If removed, reconnect wiring to backside of switch 74-30-00 Opération (5) Install switch in panel and secure using existing hardware 74-30-00 Opération (6) Reconnect battery and perform an operational check of the switch 74-30-00 Opération (1) Start engine. Refer to Model 206 Pilot's Operating Handbook. and FAA Approved Airplane Flight Manual 74-30-00 Opération (2) Check magnetos for normal engine RPM drop 74-30-00 Opération (3) Verify that both magnetos are grounded when switch is in the OFF position 74-30-00 Opération (a) Reduce engine RPM to idle, and turn switch to the OFF position. Engine should quit immediately, signifying thatl both magnetos have been grounded through thei ignition switch 74-30-00 Opération (4) After engine stops, move mixture control to idle cutoff position 74-30-00 Opération THROTTLE CONTROL - MAINTENANCE 76-10-00 Processus NOTE: Steel AN bolts with an undrilled shank are identified with an "A" suffix (AN3-6A). A steel bolt of the same size, with the shank drilled for castellated nut and cotter pin is identified as AN3-6. Aluminum AN bolts are not to be used in this app 76-10-00 Note NOTE: When installing throttle control, ensure that control is routed exactly as previously installed. Ensure that no binding or preloading occurs from a too small bend radius 76-10-00 Note A. Remove Throttle Control 76-10-00 Étape Throttle Control Installation Figure 201 (Sheet 1) 76-10-00 Document (1) Remove engine cowl. Refer to Chapter 71, Cowl - Removal/Installation 76-10-00 Opération L Remove cotter pin, castellated nut, bolt, and washers securing throttle control rod end to fuellair control unit throttle arm. Discard cotter pin 76-10-00 Opération (3) Remove rod end and jamnut from throttle control 76-10-00 Opération (4) Remove nuts, bolts, and clamp securing throttle control cable to cable bracket 76-10-00 Opération (5) Remove throttle control jamnut and lock washer from forward side of firewall 76-10-00 Opération (6) Inside the cockpit/cabin area, loosen throttle control jamnuts and lockwashers from forward side of instrument panel and aft side of firewall 76-10-00 Opération (7) Carefully pull throttle control through firewall and instrument panel removing lock washers and jamnuts, and remove from airplane 76-10-00 Opération FUEL MIXTURE CONTROL - MAINTENANCE 76-11-00 Processus NOTE: Steel AN bolts with an undrilled shank are identified with an 'A' suffix (AN3-6A). A steel bolt of the same size, with the shank drilled for castellated nut and cotter pin is identified as AN3-6. Aluminum bolts and undrilled bolts must not be u 76-11-00 Note NOTE: When installing fuel mixture control, ensure that control is routed exactly as previously installed. Ensure that no binding or preloading occurs from a too small bend radius 76-11-00 Note A. Remove Fuel Mixture Control 76-11-00 Étape Figure 201 (Sheet 1) 76-11-00 Document (1) Remove engine cowl. Refer to Chapter 71, Cowls - Removal/Installation. Remove cotter pin, nut, bolt and washers securing mixture control rod end to fuellair control unit mixture arm. Discard cotter pin 76-11-00 Opération (3) Remove rod end, nut and jamnut from fuel mixture control 76-11-00 Opération (4) Remove nuts, bolts, and clamp securing fuel mixture control cable to cable bracket 76-11-00 Opération (5) Remove fuel mixture control nut and washer from forward side of firewall 76-11-00 Opération (6) In the cockpit/cabin area, remove fuel mixture control nuts and washers from forward side of instrument panel and aft side of firewall 76-11-00 Opération (7) Carefully pull fuel mixture control through firewall and instrument panel and remove from airplane 76-11-00 Opération TACHOMETER - MAINTENANCE 77-10-00 Processus NOTE: Apply a layer of sealant (Dapco 2100) to the firewall through which the drive cable passes 77-10-00 Note NOTE: If irregular tachometer indications have occurred, the use of Stabilant 22 contact enhancer on the electrical connector (PNO25) can possibly decrease the occurrence of these indications 77-10-00 Note TURBO AIRPLANE SIMILAR. TACHOMETER SENDING UNIT 77-10-00 Note A. Remove Tachometer and Drive Cable 77-10-00 Étape NOTE: The procedures that follow are for airplanes with standard avionics 77-10-00 Note Figure 201 (Sheet 1) 77-10-00 Document (1) On the backside of the instrument panel, disconnect the drive cable from the tachometer 77-10-00 Opération 2 Disconnect the electrical connector from the backside of the tachometer 77-10-00 Opération (3) Remove the screws that attach the tachometer to the instrument panel and remove the tachometer 77-10-00 Opération (4) Remove the upper engine cowling. Refer to Chapter 71, Cowls - Maintenance Practices 77-10-00 Opération (5) Disconnect the drive cable at the rear of the accessory case 77-10-00 Opération (6) Remove the two screws that attach the firewall shield to the firewall 77-10-00 Opération (7) Remove the drive cable through the firewall 77-10-00 Opération A. Remove the Tachometer Sending Unit 77-10-00 Étape NOTE: The procedures that follow are for airplanes with Garmin G1000 77-10-00 Note AIRPLANES INCORPORATING MK206-77-01 A0758T1003 Tachometer Sending Unit Installation Figure 202 (Sheet 1) 77-10-00 Document (1) Make sure that the MASTER switch is in the off position 77-10-00 Opération 2) Remove the top cowl. Refer to Chapter 71, Cowl - Maintenance Practices 77-10-00 Opération (3) Disconnect the electrical connector (PN025 or JNO28) 77-10-00 Opération 4) Loosen the knurled nut 77-10-00 Opération (5) Remove the tachometer sending unit from the airplane 77-10-00 Opération ENGINE TEMPERATURE - MAINTENANCE 77-20-00 Processus CAUTION: Damage to the lead wire can occur because of engine movement during startup and shutdown if there is not sufficient length in the lead wire 77-20-00 Caution A. Remove the EGT/CHT Indicator 77-20-00 Étape NOTE: The procedures that follow are for airplanes with standard avionics 77-20-00 Note NOTE: The EGT indicator has CHT readings on the right side of the instrument 77-20-00 Note NOTE 2: FOR. AIRPLANES T20608001 AND ON 1210T1001 A0718T1041 Exhaust Indicating System Figure 201 (Sheet 1) 77-20-00 Document (1) Get access to the back side of the indicator 77-20-00 Opération L) Disconnect the electrical connector from the indicator 77-20-00 Opération (3) Remove the screws that attach the indicator to the instrument panel and remove the indicator from the airplane 77-20-00 Opération A. Remove the TIT/CHT Indicator 77-20-00 Étape NOTE: The procedures that follow are for airplanes with standard avionics 77-20-00 Note NOTE: The cockpit-mounted TIT indicator also has CHT readings on the right side of the instrument 77-20-00 Note (1) Get access to the backside of the indicator 77-20-00 Opération L) Disconnect the electrical connector from the indicator 77-20-00 Opération (3) Remove the screws that attach the indicator to the instrument panel and remove the indicator from the airplane 77-20-00 Opération A. Remove the EGT Probe 77-20-00 Étape NOTE: Airplanes with the Garmin G1000 will have a probe for each exhaust riser 77-20-00 Note NOTE: The EGT probe is welded to the clamp 77-20-00 Note CAUTION: Make sure that the exhaust system is cool before the probe is removed 77-20-00 Caution NOTE 2: AIRPLANES WITH GARMIN G1000 HAVE AN EGT PROBE AT EACH CYLINDER. 1210T1001 A1255T1021 B1255T1022 EGT and CHT Probe Installation Figure 202 (Sheet 1) 77-20-00 Document (1) Remove the engine cowling. Refer to Chapter 71, Cowls - Maintenance Practices 77-20-00 Opération (2) Disconnect the electrical connector from the EGT probe 77-20-00 Opération 3) Cut and remove the safety wire from the EGT probe clamp and screw 77-20-00 Opération (4) Loosen the clamp screw 77-20-00 Opération (5) Remove the clamp with the attached probe from the exhaust pipe 77-20-00 Opération A. Remove the TIT Probe 77-20-00 Étape CAUTION: Make sure that the exhaust system is cool before the probe is removed 77-20-00 Caution (UN008) NOTE: AIRPLANES WITH GARMIN G1000 HAVE A CHT PROBE AT EACH DETAIL A CYLINDER. 1210T1001 A1258T1005 TIT and CHT Probe Installation Figure 203 (Sheet 1) 77-20-00 Document (1) Remove the engine cowling. Refer to Chapter 71, Cowls - Maintenance Practices 77-20-00 Opération (2) Disconnect the electrical connector from TIT probe 77-20-00 Opération (3) Remove the TIT probe from the turbine inlet 77-20-00 Opération A. Remove the CHT Probe 77-20-00 Étape NOTE: On airplanes with Garmin G1000, the CHT probes use a bayonet style connector 77-20-00 Note NOTE: Airplanes with the Garmin G1000 have a CHT probe at each cylinder. Removal and installation of the CHT probes is typical 77-20-00 Note NOTE: Airplanes with Garmin G1000 do not have a terminal to disconnect from the CHT probe 77-20-00 Note CAUTION: Make sure that the exhaust system and engine are cool before the probe is removed 77-20-00 Caution (1) Remove engine cowling. Refer to Chapter 71, Cowls - Maintenance Practices 77-20-00 Opération (2) Remove the nut and disconnect the terminal from the CHT probe 77-20-00 Opération (3) For non-turbo engines, Unscrew and remove the CHT probe from the Number 3 cylinder. For turbo engines, remove the CHT probe from the Number 5 cylinder 77-20-00 Opération MANIFOLD PRESSURE TRANSDUCER - MAINTENANCE 77-30-00 Processus A. Remove the Manifold Pressure Transducer 77-30-00 Étape AIRPLANES WITH GARMIN G1000 1210T1001 A0718T1060 B0718T1067 Manifold Pressure Transducer Installation Figure 201 (Sheet 1) 77-30-00 Document (1) Remove the PFD. Refer to Chapter 34, Control Display Unit - Maintenance Practices. Remove the bolt, washer and clamp that hold the manifold pressure transducer in position 77-30-00 Opération (3) Disconnect the pressure line and electrical connector 77-30-00 Opération (4) Remove the manifold pressure transducer 77-30-00 Opération GEA-71 ENGINEIAIRFRAME UNIT - MAINTENANCE 77-40-00 Processus A. Engine/Airframe Unit Removal 77-40-00 Étape COORDINATOR DETAIL A AIRPLANES WITH GARMIN G1000 1210T1001 A1218T1044 Forward Avionics Equipment Installation Figure 201 (Sheet 1) 77-40-00 Document (1) Put the AVIONICS MASTER switch in the off position 77-40-00 Opération 2) Remove the MFD. Refer to Chapter 34, Control Display Unit - Maintenance Practices 77-40-00 Opération (3) Remove the screws that attach the engine/airframe unit to the structure 77-40-00 Opération (4) Remove the engine/airframe unit from the airplane 77-40-00 Opération EXHAUST SYSTEM (NON-TURBOCHARGED) - MAINTENANCE 78-10-00 Processus NOTE: If exhaust assemblies were removed as a unit proceed to step (4) 78-10-00 Note NOTE: Ball joint flanges must not touch and must be approximately parallel 78-10-00 Note NOTE: Use the same washer sequence for each attaching point to ensure equal adjustment of the springs. New washers must be used 78-10-00 Note NOTE: The inside of vacuum cleaner hose should be free of any contamination that might be blown into the engine exhaust system 78-10-00 Note A. Exhaust System Removal 78-10-00 Étape NOTE: If exhaust assemblies are to be removed as a unit proceed to step (8) 78-10-00 Note Exhaust System Installation Figure 201 (Sheet 1) 78-10-00 Document (1) Remove upper engine cowling 78-10-00 Opération (2) Remove clamp from right shroud intake duct and retain 78-10-00 Opération (3) Remove clamps from duct interconnecting the left and right heat shrouds, and remove duct and retain 78-10-00 Opération (4) Remove clamp from left heat shroud duct and retain 78-10-00 Opération (5) Remove nuts, washers and bolts from clamps securing tailpipes to shock mounts on the firewall and retain bolts and clamps, discard nuts and washers 78-10-00 Opération (6) Remove nuts, washers, and bolts from clamps securing tail pipes to mufflers and retain. Remove tailpipes 78-10-00 Opération (7) Remove cotter pins, nuts, washers, bolts, and springs securing mufflers to exhaust stack and retain bolts and springs, discard cotter pins, nuts and washers. Remove mufflers 78-10-00 Opération (8) Disconnect electrical lead from EGT thermocouple 78-10-00 Opération (9) Remove nuts and washers securing exhaust stack to engine cylinders and retain 78-10-00 Opération (10) Remove exhaust stacks and gaskets. Discard gaskets 78-10-00 Opération EXHAUST SYSTEM TURBOCHARGED) - MAINTENANCE 78-10-01 Processus NOTE: Reference Lycoming Service Instruction SI1204D (or latest revision) Exhaust Flange Gaskets and Lycoming SI1562 (or latest revision) Turbocharged Exhaust System Installation prior to performing any exhaust system maintenance on Lycoming turbocha 78-10-01 Note NOTE: The inside of vacuum cleaner hose should be free of any contamination that might be blown into the engine exhaust system 78-10-01 Note NOTE: Bubbles are acceptable at the slip joint but not acceptable at weld joints 78-10-01 Note NOTE: Each removal and installation of the clamps will decrease the service life 78-10-01 Note NOTE: Deformation of the clamp is when the straightedge does not touch a sufficient area across the clamp when you do a flatness check 78-10-01 Note CAUTION: You must fully inspect the clamps each time they are removed 78-10-01 Caution A. Exhaust Tailpipe Assembly Removal 78-10-01 Étape NOTE: Each removal and installation of the clamps will decrease the service life 78-10-01 Note CAUTION: You must fully inspect the clamps each time they are removed 78-10-01 Caution NOTE: LOOK CAREFULLY FOR CRACKS IN ALL VISUAL, ACCESS AREAS DETAIL B 1210T1001 OF THE INSTALLED CLAMP. (TYPICAL) A1255T1003 B1255T1014 Exhaust System Installation Figure 201 (Sheet 1) 78-10-01 Document (1) Remove the top right engine cowl. Refer to Chapter 71, Cowl - Maintenance Practices 78-10-01 Opération (2) Remove the clamps that attaches the tailpipe to the turbocharger and wastegate 78-10-01 Opération (3) Remove the clamp that attaches the lanyard to the wastegate overboard-pipe 78-10-01 Opération A. Heat Shroud Removal 78-10-01 Étape (1) Remove the left and right top engine cowl. Refer to Chapter 71, Cowls - Maintenance Practices 78-10-01 Opération 2) Remove nosecaps, left and right 78-10-01 Opération (3) Remove screws from heat shroud intake duct and retain 78-10-01 Opération (4) Remove clamp from heat shroud outlet duct and retain 78-10-01 Opération (5) Remove screws securing the heat shroud assembly to the exhaust system and retain 78-10-01 Opération OIL COOLER - MAINTENANCE 79-20-00 Processus NOTE: Add or remove washers as required SO that the oil cooler flanges do not bend during installation 79-20-00 Note A. Remove the oil cooler 79-20-00 Étape Figure 201 (Sheet 1) 79-20-00 Document Figure 201 (Sheet 2) 79-20-00 Document (1) Remove the upper cowling. Refer to Chapter 71, Cowls - Maintenance Practices 79-20-00 Opération (2) Put a label on and disconnect the inlet and outlet hoses that are connected to the oil cooler. Put caps on the ends of the hoses 79-20-00 Opération (3) For airplanes that do not have a turbocharger, remove the bolts, washers, and spacers that attach the oil cooler to the back of the engine baffle 79-20-00 Opération (4) For airplanes that have a turbocharger, remove the bolts, washers, and spacers that attach the oil cooler to the air duct assembly 79-20-00 Opération (5) Remove the oil cooler from the airplane 79-20-00 Opération AIR/OIL SEPARATOR ASSEMBLY - MAINTENANCE 79-20-10 Processus A. Remove the Air/Oil Separator Assembly 79-20-10 Étape Air/Oil Separator Assembly Installation Figure 201 (Sheet 1) 79-20-10 Document (1) Remove the upper cowl to get access to the engine compartment. Refer to Chapter 71, Cowls - Maintenance Practices 79-20-10 Opération (2) Turn the screws on the clamps that connect the hoses to the air/oil separator counterclockwise to loosen them 79-20-10 Opération (3) Disconnect the hoses from the oil breather 79-20-10 Opération (4) Turn the screws on the clamps that connect the air/oil separator to the engine baffle counterclockwise to loosen them 79-20-10 Opération (5) Remove the air/oil separator from the airplane 79-20-10 Opération OIL PRESSURE INDICATORS - MAINTENANCE 79-30-00 Processus CAUTION: Do not use Teflon tape 79-30-00 Caution CAUTION: Clean any sealer or other debris from the switch fitting before installation. Make sure that foreign material is removed and clear of the pressure hole in the end of the switch fitting 79-30-00 Caution CAUTION: Do not use too much torque on the plastic switch connection nousing when you tighten by hand 79-30-00 Caution CAUTION: Use only the hex fitting to tighten. Too much torque will cause damage to the switch 79-30-00 Caution A. Remove the Oil Pressure Indicator 79-30-00 Étape Oil Pressure Indication Installation Figure 201 (Sheet 1) 79-30-00 Document (1) Make sure that electrical power to airplane is off. Remove the screws that attach the indicator to the instrument panel 79-30-00 Opération (3) Remove the electrical connector from back of the indicator 79-30-00 Opération 4) Carefully remove the indicator from back of the instrument panel 79-30-00 Opération Remove the Transducer 79-30-00 Étape (1) Remove the upper cowl. Refer to Chapter 71, Cowls - Maintenance Practices. Disconnect and put caps on the oil pressure line at the transducer 79-30-00 Opération (3) Disconnect the electrical connector from the transducer 79-30-00 Opération (4) Remove the nutt that connects the transducer to the rear of the baffle and remove the transducer 79-30-00 Opération A. Remove the Switch 79-30-00 Étape (1) Make sure that electrical power to airplane is off. Remove the upper cowl. Refer to Chapter 71, Cowls - Maintenance Practices 79-30-00 Opération (3) Disconnect the electrical connector from the switch 79-30-00 Opération (4) Remove the switch from the engine case 79-30-00 Opération OIL TEMPERATURE INDICATOR - MAINTENANCE 79-31-00 Processus A. Remove the Sending Unit 79-31-00 Étape Oil Temperature Installation Figure 201 (Sheet 1) 79-31-00 Document (1) Remove the upper engine cowl. Refer to Chapter 71, Cowls - Maintenance Practices 79-31-00 Opération (2) Disconnect the ring terminal wiring at the sending unit 79-31-00 Opération (3) Loosen and remove the sending unit from the accessory case 79-31-00 Opération STARTER - MAINTENANCE 80-10-00 Processus CAUTION: Use only a clean petroleum spirit. Do not use any other type of solvent 80-10-00 Caution CAUTION: Do not use grease, oil or graphite lubricants. Use only silicone spray lubricants which are recommended for correct operation 80-10-00 Caution A. Remove the Starter 80-10-00 Étape Figure 201 (Sheet 1) 80-10-00 Document (1) Remove the upper engine cowling and the nose cap. Refer to Chapter 71, Engine Cowling - Maintenance Practices 80-10-00 Opération (2) Disconnect the negative terminal from the battery 80-10-00 Opération (3) Disconnect the large electrical wire (positive lead) at starter 80-10-00 Opération (4) Remove the three nuts from the crankcase studs 80-10-00 Opération (5) Remove the bolt from the starter and remove starter from the engine 80-10-00 Opération TURBOCHARGER CONTROLS - MAINTENANCE 81-20-00 Processus NOTE: When adjusting rotate in VERY small increments as this is an extremely sensitive adjustment. Approximately 13 degrees rotation will change the manifold pressure reading about one inch Hg 81-20-00 Note manifold pressure of 39 +0.5 inches of Hg 81-20-00 Caution Added Figure 202 - Roll Servo Cable Tension Chart Document GFC-700 AUTOPILOT - Added Figure 203 - Pitch Servo Cable Tension Chart Document MAINTENANCE PRACTICES Added Figure 204 - Pitch Trim Servo Cable Tension Document 27-10-00 SYSTEM - MAINTENANCE Added Figure 204 Aileron Hinge Bonding Strap and Pushrod Document 27-20-00 Corrected cable size in Figure 203 Sheet 1 Document Analytical Assessment Flowchart Figure 1 (Sheet 1) 05-13-00 Document Figure 1 Document Figure 2 05-13-01 Document Figure 3 05-13-01 Document Figure 4 05-13-01 Document SURFACE TO SURFACE 1413T1010 Figure 5 05-13-01 Document Analytical Assessment Flowchart Figure 1 (Sheet 1) 05-14-01 Document SPROCKET DETAIL B A1232R1001 B1234R1017 C1234R1013 Analytical Assessment Flowchart Figure 1 (Sheet 1) 05-14-02 Document Analytical Assessment Flowchart Figure 1 (Sheet 2) 05-14-02 Document Analytical Assessment Flowchart Figure 1 (Sheet 1) 05-14-03 Document LOCATION 1210T1001 DETAIL B A1241R1016 B1241T1016 Analytical Assessment Flowchart Figure 1 (Sheet 1) 05-14-04 Document DETAIL B 1210T1001 Nose Landing Gear Inspection Figure 1 (Sheet 1) 05-14-05 Document RH WING DOORPOST ATTACH ASSEMBLY BOLT HOLE DETAIL B LH DETAIL C 1210T1001 Carry-Thru Structure Corrosion Inspection Figure 1 (Sheet 1) 05-14-06 Document VIEW B-B (LEFT SHOWN, RIGHT TYPICAL) Fuselage Forward Doorpost Inspection Figure 1 (Sheet 1) 05-14-07 Document Fuselage Forward Doorpost Inspection Figure 1 (Sheet 1) 05-14-10 Document LOOKING AFT AT HORIZONTAL STABILIZER FRONT SPAR 1210T1001 Vertical Stabilizer, Rudder and Attachments Inspection Figure 1 (Sheet 1) 05-14-11 Document Vertical Stabilizer, Rudder and Attachments Inspection Figure 1 (Sheet 2) 05-14-11 Document Vertical Stabilizer, Rudder and Attachments Inspection Figure 1 (Sheet 1) 05-14-12 Document Vertical Stabilizer, Rudder and Attachments Inspection Figure 1 (Sheet 2) 05-14-12 Document RH WING DOORPOST ATTACH ASSEMBLY BOLT HOLE DETAIL B LH DETAIL C 1210T1001 Wing Structure Inspection Figure 1 (Sheet 1) 05-14-13 Document Wing Splice Joint At Strut Attach Inspection Figure 1 (Sheet 1) 05-14-15 Document Strut and Strut Wing Attachment Inspection Figure 1 (Sheet 1) 05-14-17 Document Aileron Support Structure Inspection Figure 1 (Sheet 1) 05-14-18 Document Flap Tracks Corrosion Inspection Figure 1 (Sheet 1) 05-14-19 Document Engine Mount Inspection Figure 1 (Sheet 1) 05-14-20 Document Cable Broken Wires and Pulley Wear Patterns Figure 1 (Sheet 1) 05-20-01 Document Cable Broken Wires and Pulley Wear Patterns Figure 1 (Sheet 2) 05-20-01 Document Corrosion Prevention and Control Program Damage Report Form Figure 1 (Sheet 1) 05-30-00 Document Figure 2 (Sheet 1) 05-30-00 Document Figure 2 (Sheet 2) 05-30-00 Document Figure 2 (Sheet 3) 05-30-00 Document Figure 2 (Sheet 4) 05-30-00 Document Corrosion Level Determination Chart Figure 3 (Sheet 1) 05-30-00 Document Corrosion Level Determination Chart Figure 3 (Sheet 2) 05-30-00 Document Corrosion Level Determination Chart Figure 3 (Sheet 3) 05-30-00 Document Airplane Dimensions and Areas Figure 1 (Sheet 1) 06-10-00 Document Airplane Dimensions and Areas Figure 1 (Sheet 2) 06-10-00 Document Figure 1 (Sheet 1) 06-15-00 Document Figure 2 (Sheet 1) 06-15-00 Document Figure 1 (Sheet 1) 06-20-00 Document Figure 1 (Sheet 2) 06-20-00 Document Figure 1 (Sheet 3) 06-20-00 Document CABIN FLOORBOARD PANELS 1210T1013 Cabin Floorboard Panels Figure 1 (Sheet 1) 06-20-02 Document Cabin Floorboard Panels Figure 1 (Sheet 2) 06-20-02 Document Figure 2 (Sheet 1) 06-20-02 Document Figure 3 (Sheet 1) 06-20-02 Document Figure 4 (Sheet 1) 06-20-02 Document Figure 201 (Sheet 1) 07-10-00 Document Figure 201 (Sheet 1) 08-10-00 Document NUT NUT GLARESHIELD DETAIL A 1210T1001 A1214T1032 Brace Installation - Float Planes Figure 201 (Sheet 1) 10-20-00 Document Airplane Service Points Figure 1 (Sheet 1) 12-10-00 Document Figure 302 (Sheet 1) 12-14-01 Document Figure 302 (Sheet 1) 12-14-02 Document Temperature Versus Oil Viscosity Figure 303 (Sheet 1) 12-14-02 Document 1 PARKING BRAKE OG OIL CAN HANDLE SHAFT OG-OIL, GENERAL PURPOSE - (MIL-L-7870) 07411002 Parking Brake Handle Shaft Lubrication Figure 302 (Sheet 1) 12-21-02 Document GR-GREASE, GENERAL PURPOSE - (MIL-L-81322) 1210T1001 A07181005 Flap System Lubrication Figure 302 (Sheet 1) 12-21-03 Document 3 TRIM TAB ACTUATOR GL HAND OG - OIL, GENERAL PURPOSE I (MIL-L-21164) PG = POWDERD GRAPHITE - (SS-G-659) 12341029 GL - GREASE, HIGH AND LOW TEMPERATURE (MIL-G-21164) 12331008 12341013 Elevator System Lubrication Figure 303 (Sheet 1) 12-21-03 Document OG - OIL, GENERAL PURPOSE - (MIL-L-7870) 12623001 Rudder Pedals Lubrication Figure 304 (Sheet 1) 12-21-03 Document ADAPTER E = 1.5 IN Y = 159 IN-LB 55982005 Torque Wrench and Adapter Formulas Figure 201 (Sheet 1) 20-11-00 Document Washer Installation Close Tolerance Bolts Figure 202 (Sheet 1) 20-11-00 Document HOLE METHOD. SINGLE HOLE METHOD 55992001 65981029 Lockwire Safetying Figure 201 (Sheet 1) 20-12-00 Document NOTE: RIGHT THREADED PARTS SHOWN. 5598T1024 5598T1003 REVERSE DIRECTION FOR LEFT THREADS. 5598T1024 5598T1024 Lockwire Safetying Figure 201 (Sheet 2) 20-12-00 Document Figure 201 (Sheet 3) 20-12-00 Document PIN APPLICATION 5598T1025 5598T1025 5598T1025 5598T1025 Cotter Pin Safetying Figure 202 (Sheet 1) 20-12-00 Document Safetying Turnbuckle Assemblies Figure 203 (Sheet 1) 20-12-00 Document NOTE 1: TWO LOCKING CLIPS REQUIRED FOR EACH 5598T1023 5598T1023 Safetying Turnbuckle Assemblies Figure 203 (Sheet 2) 20-12-00 Document Safetying Turnbuckle Assemblies Figure 204 (Sheet 1) 20-12-00 Document Figure 205 (Sheet 1) 20-12-00 Document Figure 205 (Sheet 2) 20-12-00 Document Cable Broken Wire Examination Figure 201 (Sheet 1) 20-13-00 Document Electrical Bonding - Typical Bonding Jumper Installation for Aluminum and Magnesium Alloys Figure 201 (Sheet 1) 20-20-00 Document Electrical Bonding - Typical Bonding Jumper Installation for Steel and Titanium Alloys Figure 202 (Sheet 1) 20-20-00 Document Electrical Bonding - Typical Bonding Joint Installation for Riveted Sheet Metal Construction Figure 203 (Sheet 1) 20-20-00 Document Electrical Bonding - Typical Bonding Joint Installation Using Sheet Metal Screws Figure 204 (Sheet 1) 20-20-00 Document Electrical Bonding - Typical Bonding Installation on Bracket and/or Angle Construction Figure 205 (Sheet 1) 20-20-00 Document Electrical Bonding - Typical Bonding Jumper Installation of Plumbing to Structure Figure 206 (Sheet 1) 20-20-00 Document (REFER TO FIGURE 206) Document Figure 207 (Sheet 1) 20-20-00 Document Electrical Bonding - Typical Inspection Plate Bonding Figure 208 (Sheet 1) 20-20-00 Document Electrical Bonding - Typical Antenna Bonding Figure 209 (Sheet 1) 20-20-00 Document Electrical Bonding - Typical Permanent Ground Stud Installation Figure 210 (Sheet 1) 20-20-00 Document Electrical Bonding - Cockpit Voice Recorder Removable Ground Stud Installation Figure 211 (Sheet 1) 20-20-00 Document Electrical Bonding - Electrical and Avionic Ground Stud Installation Figure 212 (Sheet 1) 20-20-00 Document Electrical Bonding - Typical Metallic Tubing Route with a Bulkhead Fitting and a Valve Figure 213 (Sheet 1) 20-20-00 Document Electrical Bonding - Typical Static Wick Installation Figure 214 (Sheet 1) 20-20-00 Document Two-Part Sealant Cartridge Figure 201 (Sheet 1) 20-32-00 Document LOWER SKIN 05261010 05261009 0526T1011 Integral Fuel Bay Sealing Figure 202 (Sheet 1) 20-32-00 Document Figure 202 (Sheet 2) 20-32-00 Document Figure 202 (Sheet 3) 20-32-00 Document Figure 202 (Sheet 4) 20-32-00 Document Fresh Air System Troubleshooting Chart Figure 101 (Sheet 1) 21-20-00 Document AIRPLANES WITH GARMIN G1000 A0718T1053 B0718T1053 KAP-140 Autopilot Installation Figure 202 (Sheet 1) 22-10-00 Document Roll Servo Cable Tension Chart Figure 202 (Sheet 1) 22-11-00 Document Pitch Servo Cable Tension Chart Figure 203 (Sheet 1) 22-11-00 Document Pitch Trim Servo Cable Tension Chart Figure 204 (Sheet 1) 22-11-00 Document Alternator System Troubleshooting Chart Figure 101 (Sheet 1) 24-20-00 Document Alternator System Troubleshooting Chart Figure 101 (Sheet 2) 24-20-00 Document Alternator System Troubleshooting Chart Figure 101 (Sheet 3) 24-20-00 Document Alternator System Troubleshooting Chart Figure 101 (Sheet 4) 24-20-00 Document Battery Troubleshooting Chart Figure 101 (Sheet 1) 24-30-00 Document Battery Troubleshooting Chart Figure 101 (Sheet 2) 24-30-00 Document Battery Troubleshooting Chart Figure 101 (Sheet 3) 24-30-00 Document Battery Troubleshooting Chart Figure 101 (Sheet 4) 24-30-00 Document Battery Troubleshooting Chart Figure 101 (Sheet 5) 24-30-00 Document Battery Troubleshooting Chart Figure 101 (Sheet 6) 24-30-00 Document Over-Voltage Protection Circuit Test with External Batteries Figure 201 (Sheet 1) 24-60-01 Document Over-Voltage Protection Circuit Test with External Batteries Figure 201 (Sheet 2) 24-60-01 Document Over-Voltage Protection Circuit Test with External Batteries Figure 201 (Sheet 3) 24-60-01 Document AIRPLANES WITH GARMIN G1000 AA1219T097 Cabin Power Interface Figure 101 (Sheet 1) 24-60-02 Document Figure 102 (Sheet 1) 24-60-02 Document Circuit Breaker Panel Installation Figure 202 (Sheet 1) 24-61-00 Document FIREWALL TUNNEL COVERS WINDLACE SIDEWALL DETAIL A 1210T1001 A1210T1010 Cabin Top and Interior Installation Figure 201 (Sheet 1) 25-22-00 Document Cabin Top and Interior Installation Figure 201 (Sheet 2) 25-22-00 Document Cabin Side Panel and Floorboard Upholstery Installation Figure 202 (Sheet 1) 25-22-00 Document Cabin Side Panel and Floorboard Upholstery Installation Figure 202 (Sheet 2) 25-22-00 Document DETAIL B 1211T1024 A1211T1024 B1211T1024 Cargo Tie - Down Installation Figure 201 (Sheet 1) 25-50-00 Document Figure 202 (Sheet 1) 25-51-00 Document Artex ME406 Emergency Locator Transmitter (ELT) SARSAT Test Set-up Figure 601 (Sheet 1) 25-60-02 Document Artex ME406 Emergency Locator Transmitter (ELT) SARSAT Test Set-up Figure 601 (Sheet 2) 25-60-02 Document Soundproofing Installation Figure 201 (Sheet 1) 25-80-00 Document Figure 202 (Sheet 1) 25-80-00 Document DETAIL B A0519T1038 1210T1001 B05781001 Fire Extinguisher Installation Figure 1 (Sheet 1) 26-20-00 Document Aileron System Troubleshooting Chart Figure 101 (Sheet 1) 27-10-00 Document Aileron System Troubleshooting Chart Figure 101 (Sheet 2) 27-10-00 Document Inclinometer for Measuring Control Surface Travel Figure 202 (Sheet 1) 27-10-00 Document LOWER LIMIT 100 TENSION 178 N. AT 21°C 50 AILERON CABLES (3.18-mm DIAMETER) 0 TIIHTmng - JTTTT I III III I TITTTTTTTTTTETT -40 -35 -30 -25 -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 DEGREES CELSIUS Aileron Cable Tension Figure 203 (Sheet 1) 27-10-00 Document Aileron Hinge Bonding Strap and Pushrod Figure 204 (Sheet 1) 27-10-00 Document Rudder System Troubleshooting Chart Figure 101 (Sheet 1) 27-20-00 Document Rudder System Troubleshooting Chart Figure 101 (Sheet 2) 27-20-00 Document Rudder Travel Adjustment Figure 202 (Sheet 1) 27-20-00 Document 0 TITTUOTpOETET II I I III II TIumpmTpEOIETEET -40 -35 -30 -25 -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 DEGREES CELSIUS Rudder Cable Tension Figure 203 (Sheet 1) 27-20-00 Document Rudder Trim System Troubleshooting Chart Figure 101 (Sheet 1) 27-21-00 Document Elevator System Troubleshooting Chart Figure 101 (Sheet 1) 27-30-00 Document Elevator System Troubleshooting Chart Figure 101 (Sheet 2) 27-30-00 Document DETAIL C B07601006 A07601007 C07601005 Elevator Control System Rigging Figure 202 (Sheet 1) 27-30-00 Document Elevator Control System Rigging Figure 202 (Sheet 2) 27-30-00 Document Figure 203 (Sheet 1) 27-30-00 Document Elevator Trim System Troubleshooting Chart Figure 101 (Sheet 1) 27-31-00 Document Elevator Trim System Troubleshooting Chart Figure 101 (Sheet 2) 27-31-00 Document Elevator Trim System Troubleshooting Chart Figure 101 (Sheet 3) 27-31-00 Document Elevator Trim Tab Actuator Cleaning and Inspection Figure 202 (Sheet 1) 27-31-00 Document Trim Tab Free Play Inspection Figure 203 (Sheet 1) 27-31-00 Document Elevator Trim Tab Travel Stop Adjustment for Airplanes 20608001 thru 20608319 and Airplanes T20608001 thru T20608953 Figure 204 (Sheet 1) 27-31-00 Document Elevator Trim Cable Tension Figure 205 (Sheet 1) 27-31-00 Document Elevator Trim Tab Travel Stop Adjustment for Airplanes 20608320 and On and Airplanes T20608954 and On Figure 206 (Sheet 1) 27-31-00 Document Flap System Troubleshooting Chart Figure 101 (Sheet 1) 27-50-00 Document Flap System Troubleshooting Chart Figure 101 (Sheet 2) 27-50-00 Document Flap System Troubleshooting Chart Figure 101 (Sheet 3) 27-50-00 Document Figure 202 (Sheet 1) 27-50-00 Document NOTE: AIRPLANES 20608001 THRU 20608173, AND AIRPLANES T20608001 THRU T20608361. Flap Cable Tension Figure 203 (Sheet 1) 27-50-00 Document NOTE: AIRPLANES 20608174 AND ON, AND AIRPLANES T20608362 AND ON. Flap Cable Tension Figure 203 (Sheet 2) 27-50-00 Document CONNECTION 12911001 Fuel System Schematic Figure 1 (Sheet 1) 28-20-00 Document FUELIAIR CONTROL UNIT FUEL RETURN AND EXCESS FUEL DRAIN VENT MECHANICAL LINKAGE ELECTRICAL CONNECTION 1285T1034A Fuel System Schematic Figure 1 (Sheet 2) 28-20-00 Document FUEL STRAINER RESERVOIR FUEL PUMP DETAIL A AIRPLANES 20608001 THRU 20608173 AND AIRPLANES T20608001 THRU T20608361 1210T1001 A1216T1006 Fuel System Installation Figure 201 (Sheet 1) 28-20-00 Document Figure 201 (Sheet 2) 28-20-00 Document VIEW LOOKING INBOARD 1226T1007 Fuel Vent Location Figure 205 (Sheet 1) 28-20-00 Document BYPASS PORT TO THE TOP OF THE FUEL BAY B12261004 C0516T1015 Wing Fuel Tank Vent Check Valve Figure 206 (Sheet 1) 28-20-00 Document Figure 207 (Sheet 1) 28-20-00 Document Figure 209 (Sheet 1) 28-20-00 Document Classification of Fuel Leaks Figure 201 (Sheet 1) 28-21-00 Document CANI BUS LOW CANI BUS LOW CONFIG RETURN 11 Jumpers used to configure 1200 11 CONFIG RETURN Document CAN Bus Wiring Diagram Figure 101 (Sheet 1) 28-40-00 Document Figure 201 (Sheet 1) 30-20-00 Document Propeller Heat Troubleshooting for Airplanes without Garmin G1000 Figure 101 (Sheet 1) 30-60-00 Document Propeller Heat Troubleshooting for Airplanes without Garmin G1000 Figure 101 (Sheet 2) 30-60-00 Document Propeller Heat Troubleshooting for Airplanes without Garmin G1000 Figure 101 (Sheet 3) 30-60-00 Document Propeller Heat Troubleshooting for Airplanes without Garmin G1000 Figure 101 (Sheet 4) 30-60-00 Document Propeller Heat Troubleshooting for Airplanes without Garmin G1000 Figure 101 (Sheet 5) 30-60-00 Document Propeller Heat Troubleshooting for Airplanes with Garmin G1000 Figure 102 (Sheet 1) 30-60-00 Document Propeller Heat Troubleshooting for Airplanes with Garmin G1000 Figure 102 (Sheet 2) 30-60-00 Document Propeller Heat Troubleshooting for Airplanes with Garmin G1000 Figure 102 (Sheet 3) 30-60-00 Document Propeller Heat Troubleshooting for Airplanes with Garmin G1000 Figure 102 (Sheet 4) 30-60-00 Document Main Landing Gear Troubleshooting Chart Figure 101 (Sheet 1) 32-10-00 Document Main Landing Gear Troubleshooting Chart Figure 101 (Sheet 2) 32-10-00 Document Main Wheel Alignment Check Figure 202 (Sheet 1) 32-10-00 Document Main Wheel Alignment Check Figure 202 (Sheet 2) 32-10-00 Document Nose Landing Gear Troubleshooting Chart Figure 101 (Sheet 1) 32-20-00 Document Nose Landing Gear Troubleshooting Chart Figure 101 (Sheet 2) 32-20-00 Document Nose Landing Gear Troubleshooting Chart Figure 101 (Sheet 3) 32-20-00 Document PACKING RING DETAIL A 1210T1001 A12421002 Shimmy Damper Figure 202 (Sheet 1) 32-20-00 Document Figure 202 (Sheet 1) 32-40-00 Document Brake System Troubleshooting Chart Figure 101 (Sheet 1) 32-42-00 Document Brake System Troubleshooting Chart Figure 101 (Sheet 2) 32-42-00 Document Brake System Troubleshooting Chart Figure 101 (Sheet 3) 32-42-00 Document Brake Master Cylinder Assembly Figure 202 (Sheet 1) 32-42-00 Document Pedestal Lighting Installation Figure 201 (Sheet 1) 33-12-00 Document Instrument Lighting Installation Figure 201 (Sheet 1) 33-13-00 Document Instrument Lighting Installation Figure 201 (Sheet 2) 33-13-00 Document Landing/Taxi Light Troubleshooting Figure 101 (Sheet 1) 33-42-00 Document BEAM 1 0.00 1 10 DEGREES TAXI LIGHT/LANDING LIGHT SECONDARY BEAM SPREAD 1210T1001 VIEW B-B AA0728T004-1 BB0728T004-1 LED Landing, Taxi and Recognition Light Aiming Figure 202 (Sheet 1) 33-42-05 Document Pitot and Static System Flow Diagram Figure 201 (Sheet 1) 34-11-00 Document AND KAP-140 AUTOPILOT 0795T1001 Pitot and Static System Flow Diagram Figure 201 (Sheet 2) 34-11-00 Document AND GFC-700 AUTOPILOT 0795T1001 Pitot and Static System Flow Diagram Figure 201 (Sheet 3) 34-11-00 Document Safe Flight SCc AOA System Wiring Diagram Figure 201 (Sheet 1) 34-18-01 Document Safe Flight SCc AOA System Indications Figure 204 (Sheet 1) 34-18-01 Document When completed, remove this place it in the aircraft log book. 083326-LTR-56201 Flight Check Data Sheet Figure 205 (Sheet 1) 34-18-01 Document VIEW LOOKING FORWARD AT INSTRUMENT PANEL 1210T1001 A-B6940T481- EVS-600 Enhanced Vision System Figure 1 (Sheet 1) 34-31-00 Document GTS 800 TAS Component Locations Figure 1 (Sheet 1) 34-41-00 Document GTS 800 TAS Component Locations Figure 1 (Sheet 2) 34-41-00 Document GTS 800 TAS Component Locations Figure 1 (Sheet 3) 34-41-00 Document GTS 800 TAS Interconnect Diagram Figure 2 (Sheet 1) 34-41-00 Document Figure 501 (Sheet 1) 34-41-00 Document TEE OXYGEN OUTLET ELBOW DETAIL D OXYGEN OUTLET LINE ASSEMBLY 1210T1001 A1214T1005 B1214T1007 DETAIL C C1214T1007 D1214T1007 Oxygen Distribution System Figure 202 (Sheet 1) 35-01-00 Document FIGURE 202_ Document Vacuum System Troubleshooting Chart Figure 101 (Sheet 1) 37-10-00 Document Vacuum System Troubleshooting Chart Figure 101 (Sheet 2) 37-10-00 Document Vacuum Pump Torque Wrench Adapter Figure 202 (Sheet 1) 37-10-00 Document SURFACE 6591T1001 6591T1001 6591T1001 6591T1002 6291T1013 6291T6004 Corrosion Figure 1 (Sheet 1) 51-11-00 Document North America Corrosion Severity Map Figure 2 (Sheet 1) 51-11-00 Document South America Corrosion Severity Map Figure 3 (Sheet 1) 51-11-00 Document Africa Corrosion Severity Map Figure 4 (Sheet 1) 51-11-00 Document Asia Corrosion Severity Map Figure 5 (Sheet 1) 51-11-00 Document Europe and Asia Minor Corrosion Severity Map Figure 6 (Sheet 1) 51-11-00 Document South Pacific Corrosion Severity Map Figure 7 (Sheet 1) 51-11-00 Document CRACKS AND HARD TO ASSURE HARDENED, SAND PERFECT FIT. THEN BEVELED OR FILL EDGES LEVEL SURFACE REMOVE PATCH FOR EDGE WITH SURFACE. PATCH CEMENTING BATH. 0511R1014 Windshield/Window Repair Figure 202 (Sheet 1) 56-10-00 Document VIEW LOOKING DOWN 1210T1001 A1250T1003 Engine Installation Figure 1 (Sheet 1) 71-00-01 Document VIEW LOOKING INBOARD LEFT SIDE 1210T1001 A1250T1001 Engine Installation Figure 1 (Sheet 2) 71-00-01 Document VIEW LOOKING FORWARD 1210T1001 A1250T1002 Engine Installation Figure 1 (Sheet 3) 71-00-01 Document Engine Troubleshooting Chart Figure 101 (Sheet 1) 71-00-01 Document Engine Troubleshooting Chart Figure 101 (Sheet 2) 71-00-01 Document Engine Troubleshooting Chart Figure 101 (Sheet 3) 71-00-01 Document Engine Troubleshooting Chart Figure 101 (Sheet 4) 71-00-01 Document Engine Troubleshooting Chart Figure 101 (Sheet 5) 71-00-01 Document Engine Troubleshooting Chart Figure 101 (Sheet 6) 71-00-01 Document Engine Troubleshooting Chart Figure 101 (Sheet 7) 71-00-01 Document Engine Troubleshooting Chart Figure 101 (Sheet 8) 71-00-01 Document Engine Troubleshooting Chart Figure 101 (Sheet 9) 71-00-01 Document Engine Troubleshooting Chart Figure 101 (Sheet 10) 71-00-01 Document Engine Troubleshooting Chart Figure 101 (Sheet 11) 71-00-01 Document Engine Troubleshooting Chart Figure 101 (Sheet 12) 71-00-01 Document Engine Troubleshooting Chart Figure 101 (Sheet 13) 71-00-01 Document Engine Shock Mount Installation Figure 201 (Sheet 1) 71-20-00 Document Turbo-Charged Drain Line Assembly Figure 203 (Sheet 1) 71-70-00 Document Turbo Charged Drain Line Assembly Figure 204 (Sheet 1) 71-70-00 Document PRESSURE 0516R2001 Fuel Injection System Schematic Figure 1 (Sheet 1) 73-00-01 Document IDLE VALVE DETAIL B 1210T1001 A1250T1009 B1255R1007 Idle and Mixture Adjustment Figure 201 (Sheet 1) 73-00-01 Document Engine Driven Fuel Pump Pressure Setting (T206) Figure 202 (Sheet 1) 73-00-01 Document Ignition System Troubleshooting Chart Figure 101 (Sheet 1) 74-10-00 Document Ignition System Troubleshooting Chart Figure 101 (Sheet 2) 74-10-00 Document ACS Ignition Switch Inspection/.ubrication Figure 601 (Sheet 1) 74-30-00 Document Figure 202 (Sheet 1) 78-10-01 Document Figure 202 (Sheet 2) 78-10-01 Document Figure 201 (Sheet 1) 81-20-00 Document filler valve 35-01-00 Composant Pressure Gage 35-01-00 Composant ACS Ignittion Switch 74-30-00 Composant