182SMM14 182/T182 SERIES (1997 AND ON) Cessna_182S_1997on_MM_182SMM Cessna 182S 1997on MM 182SMM
User Manual: Cessna_182S_1997on_MM_182SMM
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- 182SMM14 - MODEL 182/T182 SERIES (1997 AND ON)
- LIST OF EFFECTIVE PAGES
- RECORD OF REVISION
- RECORD OF TEMPORARY REVISIONS
- TABLE OF CONTENTS
- SERVICE BULLETIN LIST
- INTRODUCTION
- GENERAL
- CROSS REFERENCE LISTING OF POPULAR NAME VERSES MODEL NUMBERS AND SERIALS
- COVERAGE AND FORMAT
- TEMPORARY REVISIONS
- SERIALIZATION
- MATERIAL PRESENTATION
- SERVICE BULLETINS
- USING THE MAINTENANCE MANUAL
- EFFECTIVITY PAGES
- REVISION FILING INSTRUCTIONS
- IDENTIFYING REVISED MATERIAL
- WARNINGS, CAUTIONS AND NOTES
- CESSNA PROPELLER AIRCRAFT CUSTOMER CARE SUPPLIES AND PUBLICATIONS CATALOG
- CUSTOMER COMMENTS ON MANUAL
- LIST OF REVISIONS
- LIST OF MANUFACTURERS TECHNICAL PUBLICATIONS
- LIST OF CHAPTERS
- CHAPTER 5 - TIME LIMITS/MAINTENANCE CHECKS
- LIST OF EFFECTIVE PAGES
- RECORD OF TEMPORARY REVISIONS
- TABLE OF CONTENTS
- TIME LIMITS/MAINTENANCE CHECKS
- AIRWORTHINESS LIMITATIONS - FAA APPROVED DATA
- INSPECTION TIME INTERVALS
- INSPECTION TIME LIMITS
- COMPONENT TIME LIMITS
- PROGRESSIVE CARE PROGRAM
- INSPECTION OPERATION 1
- INSPECTION OPERATION 2
- INSPECTION OPERATION 3
- INSPECTION OPERATION 4
- INSPECTION OPERATION 5
- PROGRESSIVE CARE
- INSPECTION OPERATION 7
- PROGRESSIVE CARE
- INSPECTION OPERATION 9
- INSPECTION OPERATION 10
- INSPECTION OPERATION 11
- PROGRESSIVE CARE
- INSPECTION OPERATION 14
- INSPECTION OPERATION 15
- INSPECTION OPERATION 16
- INSPECTION OPERATION 17
- INSPECTION OPERATION 18
- INSPECTION OPERATION 19
- INSPECTION OPERATION 20
- INSPECTION OPERATION 21
- INSPECTION OPERATION 22
- INSPECTION OPERATION 23
- INSPECTION OPERATION 24
- INSPECTION OPERATION 25
- INSPECTION OPERATION 26
- UNSCHEDULED MAINTENANCE CHECKS
- CHAPTER 6 - DIMENSIONS AND AREAS
- LIST OF EFFECTIVE PAGES
- RECORD OF TEMPORARY REVISIONS
- TABLE OF CONTENTS
- DIMENSIONS AND AREAS - GENERAL
- AIRPLANE DIMENSIONS AND SPECIFICATIONS - DESCRIPTION AND OPERATION
- AIRPLANE STATIONS - DESCRIPTION AND OPERATION
- AIRPLANE ZONING - DESCRIPTION AND OPERATION
- ACCESS/INSPECTION PLATES - DESCRIPTION AND OPERATION
- CHAPTER 7 - LIFTING AND SHORING
- CHAPTER 8 - LEVELING AND WEIGHING
- CHAPTER 9 - TOWING AND TAXIING
- CHAPTER 10 - PARKING AND MOORING
- CHAPTER 11 - PLACARDS AND MARKINGS
- CHAPTER 12 - SERVICING
- LIST OF EFFECTIVE PAGES
- RECORD OF TEMPORARY REVISIONS
- TABLE OF CONTENTS
- SERVICING - GENERAL
- REPLENISHING - DESCRIPTION AND OPERATION
- NOSE LANDING GEAR SHOCK STRUT - SERVICING
- NOSE LANDING GEAR SHIMMY DAMPER - SERVICING
- HYDRAULIC BRAKES - SERVICING
- FUEL AND ENGINE OIL - DESCRIPTION AND OPERATION
- FUEL - SERVICING
- ENGINE OIL - SERVICING
- INDUCTION AIR FILTER - SERVICING
- VACUUM SYSTEM FILTERS - SERVICING
- BATTERY - SERVICING
- TIRES - SERVICING
- SCHEDULED SERVICING - DESCRIPTION AND OPERATION
- LUBRICANTS - DESCRIPTION AND OPERATION
- BATTERY TERMINALS - SERVICING
- LANDING GEAR AND PARKING BRAKE - SERVICING
- FLIGHT CONTROLS - SERVICING
- ENGINE CONTROL CABLES - SERVICING
- HEATING AND VENTILATION CONTROL CABLES - SERVICING
- AIRPLANE EXTERIOR - CLEANING/PAINTING
- INTERIOR - CLEANING/PAINTING
- UNSCHEDULED SERVICING - DESCRIPTION AND OPERATION
- CHAPTER 20 - STANDARD PRACTICES - AIRFRAME
- LIST OF EFFECTIVE PAGES
- RECORD OF TEMPORARY REVISIONS
- TABLE OF CONTENTS
- STANDARD PRACTICES AIRFRAME - GENERAL
- MATERIAL AND TOOL CAUTIONS - DESCRIPTION AND OPERATION
- TORQUE DATA - MAINTENANCE PRACTICES
- SAFETYING - MAINTENANCE PRACTICES
- CONTROL CABLE WIRE BREAKAGE AND CORROSION LIMITATIONS - MAINTENANCE PRACTICES
- SOLVENTS, SEALANTS, AND ADHESIVES - DESCRIPTION AND OPERATION
- ACCEPTABLE REPLACEMENTS FOR CHEMICALS AND SOLVENTS - DESCRIPTION AND OPERATION
- GENERAL SOLVENTS/CLEANERS - MAINTENANCE PRACTICES
- INTERIOR AND EXTERIOR FINISH - CLEANING/PAINTING
- FUEL, WEATHER AND HIGH - TEMPERATURE SEALING - MAINTENANCE PRACTICES
- CONVERSION DATA - DESCRIPTION AND OPERATION
- CHAPTER 21 - AIR CONDITIONING
- LIST OF EFFECTIVE PAGES
- RECORD OF TEMPORARY REVISIONS
- TABLE OF CONTENTS
- AIR CONDITIONING - GENERAL
- FRESH AIR DISTRIBUTION - DESCRIPTION AND OPERATION
- FRESH AIR DISTRIBUTION - TROUBLESHOOTING
- FRESH AIR DISTRIBUTION - MAINTENANCE PRACTICES
- AVIONICS COOLING FAN - MAINTENANCE PRACTICES
- GENERAL
- FIREWALL AVIONICS COOLING FAN REMOVAL/INSTALLATION (AIRPLANES WITHOUT GARMIN G1000)
- PRIMARY FLIGHT DISPLAY (PFD) FAN REMOVAL/INSTALLATION (AIRPLANES WITH GARMIN G1000)
- MULTI-FUNCTION DISPLAY (MFD) FAN REMOVAL/INSTALLATION (AIRPLANES WITH GARMIN G1000)
- DECK SKIN FAN REMOVAL/INSTALLATION (AIRPLANES WITH GARMIN G1000)
- REMOTE AVIONICS COOLING FAN REMOVAL/INSTALLATION (AIRPLANES WITH GARMIN G1000)
- PRIMARY FLIGHT DISPLAY (PFD) AND MULTI-FUNCTION DISPLAY (MFD) FAN OPERATIONAL CHECK (AIRPLANES WITH GARMIN G1000)
- HEATING AND DEFROSTING - TROUBLESHOOTING
- HEATING AND DEFROSTING - MAINTENANCE PRACTICES
- CHAPTER 22 - AUTO FLIGHT
- LIST OF EFFECTIVE PAGES
- RECORD OF TEMPORARY REVISIONS
- TABLE OF CONTENTS
- AUTO FLIGHT - GENERAL
- AUTOPILOT - MAINTENANCE PRACTICES
- GENERAL
- KC- 140 (SINGLE-AXIS) AUTOPILOT FLIGHT COMPUTER REMOVAL/INSTALLATION
- KC-140 (DUAL-AXIS) AUTOPILOT FLIGHT COMPUTER REMOVAL/INSTALLATION
- ROLL SERVO REMOVAL/INSTALLATION
- PITCH SERVO REMOVAL/INSTALLATION
- PITCH TRIM SERVO REMOVAL/INSTALLATION
- ROLL SERVO INSPECTION
- PITCH SERVO INSPECTION
- PITCH TRIM SERVO INSPECTION
- PITCH TRIM RIGGING INSPECTION
- SERVO CAPSTAN CLUTCH ADJUSTMENT
- SET THE AUTOPILOT ROLL NULL
- AUTOPILOT - MAINTENANCE PRACTICES
- GENERAL
- GFC-700 AUTOPILOT FLIGHT COMPUTER REMOVAL/INSTALLATION
- ROLL SERVO ACTUATOR REMOVAL/INSTALLATION
- ROLL SERVO AND CABLE REMOVAL/INSTALLATION
- PITCH SERVO MOTOR REMOVAL/INSTALLATION
- PITCH SERVO AND CABLE REMOVAL/INSTALLATION
- PITCH TRIM SERVO ACTUATOR REMOVAL/INSTALLATION
- PITCH TRIM SERVO AND CABLE REMOVAL/INSTALLATION
- PITCH TRIM RIGGING INSPECTION
- SERVO CAPSTAN CLUTCH ADJUSTMENT
- CHAPTER 23 - COMMUNICATIONS
- CHAPTER 24 - ELECTRICAL POWER
- LIST OF EFFECTIVE PAGES
- RECORD OF TEMPORARY REVISIONS
- TABLE OF CONTENTS
- ELECTRICAL POWER - GENERAL
- ALTERNATOR SYSTEM - TROUBLESHOOTING
- ALTERNATOR - MAINTENANCE PRACTICES
- BATTERY - TROUBLESHOOTING
- BATTERY - MAINTENANCE PRACTICES
- STANDBY BATTERY - MAINTENANCE PRACTICES AIRPLANES WITH GARMIN G1000
- 12-VOLT CABIN POWER SYSTEM - TROUBLESHOOTING
- POWER JUNCTION BOX - MAINTENANCE PRACTICES
- ALTERNATOR CONTROL UNIT - MAINTENANCE PRACTICES
- CIRCUIT BREAKER - MAINTENANCE PRACTICES
- ESSENTIAL AND CROSSFEED BUS DIODES - MAINTENANCE PRACTICES
- ELECTRICAL LOAD ANALYSIS - DESCRIPTION AND OPERATION
- CHAPTER 25 - EQUIPMENT/ FURNISHINGS
- LIST OF EFFECTIVE PAGES
- RECORD OF TEMPORARY REVISIONS
- TABLE OF CONTENTS
- EQUIPMENT/FURNISHING - GENERAL
- FRONT SEATS AND RAILS - MAINTENANCE PRACTICES
- MAP COMPARTMENT - MAINTENANCE PRACTICES
- SEAT BELTS/RESTRAINTS - MAINTENANCE PRACTICES
- INFLATABLE RESTRAINTS - MAINTENANCE PRACTICES AIRPLANES WITH AMSAFE INFLATABLE RESTRAINT SYSTEM
- GENERAL
- INFLATABLE RESTRAINT COMPONENT CLEANING
- INFLATABLE RESTRAINT - INSPECTION
- STORAGE OF SPARES
- AMSAFE INFLATABLE RESTRAINT DISARM/ARM
- INFLATABLE RESTRAINT - REMOVAL/INSTALLATION
- AMSAFE AVIATION INFLATABLE RESTRAINT (AAIR) SYSTEM ADJUSTMENT/TEST
- AMSAFE AVIATION INFLATABLE RESTRAINT (AAIR) SYSTEM TROUBLESHOOTING
- REAR SEAT - MAINTENANCE PRACTICES
- INTERIOR UPHOLSTERY - MAINTENANCE PRACTICES
- CARGO TIE-DOWNS - MAINTENANCE PRACTICES
- POINTER EMERGENCY LOCATOR TRANSMITTER - MAINTENANCE PRACTICES
- ARTEX C406-N EMERGENCY LOCATOR TRANSMITTER - MAINTENANCE PRACTICES
- ARTEX C406-N EMERGENCY LOCATOR TRANSMITTER - INSPECTION/CHECK
- ARTEX ME406 EMERGENCY LOCATOR TRANSMITTER SYSTEM - DESCRIPTION AND OPERATION
- ARTEX ME406 EMERGENCY LOCATOR TRANSMITTER SYSTEM - TROUBLESHOOTING
- ARTEX ME406 EMERGENCY LOCATOR TRANSMITTER SYSTEM - MAINTENANCE PRACTICES
- ARTEX ME406 EMERGENCY LOCATOR TRANSMITTER (ELT) SYSTEM - INSPECTION/CHECK
- CARBON MONOXIDE DETECTOR - MAINTENANCE PRACTICES
- SOUNDPROOFING AND INSULATION - MAINTENANCE PRACTICES
- CHAPTER 26 - FIRE PROTECTION
- CHAPTER 27 - FLIGHT CONTROLS
- LIST OF EFFECTIVE PAGES
- RECORD OF TEMPORARY REVISIONS
- TABLE OF CONTENTS
- FLIGHT CONTROLS - GENERAL
- AILERON CONTROL SYSTEM - TROUBLESHOOTING
- AILERON CONTROL SYSTEM - MAINTENANCE PRACTICES
- RUDDER CONTROL SYSTEM - TROUBLESHOOTING
- RUDDER CONTROL SYSTEM - MAINTENANCE PRACTICES
- RUDDER TRIM - TROUBLESHOOTING
- RUDDER TRIM CONTROL SYSTEM - MAINTENANCE PRACTICES
- ELEVATOR SYSTEM - TROUBLESHOOTING
- ELEVATOR CONTROL SYSTEM - MAINTENANCE PRACTICES
- ELEVATOR TRIM CONTROL - TROUBLESHOOTING
- ELEVATOR TRIM CONTROL - MAINTENANCE PRACTICES
- STALL WARNING SYSTEM - MAINTENANCE PRACTICES
- FLAP CONTROL SYSTEM - TROUBLESHOOTING
- FLAP CONTROL SYSTEM - MAINTENANCE PRACTICES
- FLAP FOLLOW-UP AND INDICATING SYSTEM - MAINTENANCE PRACTICES
- CHAPTER 28 - FUEL
- LIST OF EFFECTIVE PAGES
- RECORD OF TEMPORARY REVISIONS
- TABLE OF CONTENTS
- FUEL - GENERAL
- FUEL STORAGE AND DISTRIBUTION - DESCRIPTION AND OPERATION
- FUEL STORAGE AND DISTRIBUTION - MAINTENANCE PRACTICES
- GENERAL
- PRECAUTIONS
- FUEL DRAIN VALVE REMOVAL/INSTALLATION
- FUEL QUANTITY SENDER REMOVAL/INSTALLATION
- FUEL TANK VENTS ADJUSTMENT/TEST
- FUEL FILLER CAP VENT CLEANING/SEAL REPLACEMENT
- FUEL SELECTOR VALVE REMOVAL/INSTALLATION
- FUEL STRAINER DISASSEMBLY/CLEANING/ASSEMBLY
- ELECTRIC AUXILIARY FUEL PUMP REMOVAL/INSTALLATION (AIRPLANES 18280001 THRU 18280944)
- ELECTRIC AUXILIARY FUEL PUMP REMOVAL/INSTALLATION (AIRPLANES 18280945 AND ON AND AIRPLANES T18208001 AND ON)
- AUXILIARY FUEL PUMP SERVICEABILITY TEST (AIRPLANES 18280001 THRU 18280944)
- FUEL STORAGE AND DISTRIBUTION - ADJUSTMENT/TEST
- GENERAL
- FUEL QUANTITY CALIBRATION AND CHECK (AIRPLANES WITHOUT GARMIN G1000)
- FUEL QUANTITY CALIBRATION AND FUEL FLOW TEST (AIRPLANES WITH GARMIN G1000 WITH SOFTWARE VERSION 563.01 OR EARLIER)
- FUEL QUANTITY CALIBRATION AND FUEL FLOW TEST (AIRPLANES WITH GARMIN G1000 WITH SOFTWARE VERSION 563.02 OR LATER)
- FUEL BAY SEALING - MAINTENANCE PRACTICES
- CHAPTER 30 - ICE AND RAIN PROTECTION
- CHAPTER 31 - INDICATING/ RECORDING SYSTEMS
- LIST OF EFFECTIVE PAGES
- RECORD OF TEMPORARY REVISIONS
- TABLE OF CONTENTS
- INDICATING/RECORDING SYSTEMS - GENERAL
- INSTRUMENT AND CONTROL PANELS - MAINTENANCE PRACTICES
- INSTRUMENT AND CONTROL PANELS - MAINTENANCE PRACTICES AIRPLANES WITH GARMIN G1000
- DIGITAL CLOCK - MAINTENANCE PRACTICES
- HOUR METER - MAINTENANCE PRACTICES
- ANNUNCIATOR PANEL - MAINTENANCE PRACTICES
- CHAPTER 32 - LANDING GEAR
- LIST OF EFFECTIVE PAGES
- RECORD OF TEMPORARY REVISIONS
- TABLE OF CONTENTS
- LANDING GEAR - GENERAL
- MAIN LANDING GEAR - TROUBLESHOOTING
- MAIN LANDING GEAR - MAINTENANCE PRACTICES
- NOSE LANDING GEAR - TROUBLESHOOTING
- NOSE LANDING GEAR - MAINTENANCE PRACTICES
- GENERAL
- NOSEWHEEL SPEED FAIRING REMOVAL/INSTALLATION
- NOSE LANDING GEAR REMOVAL/INSTALLATION
- NOSE GEAR SHOCK STRUT DISASSEMBLY/ASSEMBLY
- NOSE GEAR SHOCK STRUT INSPECTION/REPAIR
- SHIMMY DAMPER REMOVAL/INSTALLATION
- SHIMMY DAMPER DISASSEMBLY/ASSEMBLY (FOR AIRPLANES THAT DO NOT HAVE THE LORD SHIMMY DAMPER)
- NOSE WHEEL STEERING REMOVAL/INSTALLATION
- RIGGING NOSE WHEEL STEERING
- MAIN LANDING GEAR WHEEL AND AXLE - MAINTENANCE PRACTICES
- NOSE LANDING GEAR WHEEL - MAINTENANCE PRACTICES
- BRAKE SYSTEM - TROUBLESHOOTING
- BRAKE SYSTEM - MAINTENANCE PRACTICES
- CHAPTER 33 - LIGHTS
- LIST OF EFFECTIVE PAGES
- RECORD OF TEMPORARY REVISIONS
- TABLE OF CONTENTS
- LIGHTING - GENERAL
- FLOOD LIGHTING - MAINTENANCE PRACTICES
- GENERAL
- FLOODLIGHT BULB REMOVAL/INSTALLATION
- LIGHT ASSEMBLY REMOVAL/INSTALLATION
- LIGHT ASSEMBLY SWITCH REMOVAL/INSTALLATION
- POTENTIOMETER REMOVAL/INSTALLATION
- OXYGEN PANEL LIGHT BULB REMOVAL/INSTALLATION (AIRPLANES WITH GARMIN G1000)
- OXYGEN PANEL LIGHT ASSEMBLY REMOVAL/INSTALLATION (AIRPLANES WITH GARMIN G1000)
- GLARESHIELD LIGHTING - MAINTENANCE PRACTICES
- PEDESTAL LIGHTING - MAINTENANCE PRACTICES
- INSTRUMENT LIGHTING - MAINTENANCE PRACTICES
- RADIO LIGHTING - MAINTENANCE PRACTICES
- PILOT CONTROL WHEEL LIGHTING - MAINTENANCE PRACTICES
- NAVIGATION AND STROBE LIGHTS - MAINTENANCE PRACTICES
- VERTICAL FIN FLASHING BEACON - MAINTENANCE PRACTICES
- LANDING/TAXI LIGHTS - TROUBLESHOOTING
- LANDING/TAXI LIGHTS - MAINTENANCE PRACTICES
- COURTESY LIGHTS - MAINTENANCE PRACTICES
- CHAPTER 34 - NAVIGATION
- LIST OF EFFECTIVE PAGES
- RECORD OF TEMPORARY REVISIONS
- TABLE OF CONTENTS
- NAVIGATION - GENERAL
- PITOT AND STATIC SYSTEMS - MAINTENANCE PRACTICES
- GENERAL
- PITOT TUBE REMOVAL/INSTALLATION
- SUMP ASSEMBLY REMOVAL/INSTALLATION
- ALTERNATE STATIC SOURCE VALVE REMOVAL/INSTALLATION
- BLIND ENCODER REMOVAL/INSTALLATION (ON AIRPLANES WITHOUT GARMIN G1000)
- VERTICAL SPEED INDICATOR REMOVAL/INSTALLATION
- ALTIMETER REMOVAL/INSTALLATION
- AIRSPEED INDICATOR REMOVAL/INSTALLATION
- STATIC PRESSURE SYSTEM LEAK TEST/INSPECTION
- PITOT SYSTEM LEAK TEST/INSPECTION
- OUTSIDE AIR TEMPERATURE GAUGE - MAINTENANCE PRACTICES
- AIR DATA SYSTEM - MAINTENANCE PRACTICES
- ATTITUDE AND DIRECTION - DESCRIPTION AND OPERATION
- ATTITUDE AND DIRECTION - MAINTENANCE PRACTICES
- GENERAL
- OPERATION NOTES
- PRECAUTIONS
- PREPARE THE GYROSCOPIC INSTRUMENTS FOR SHIPPING
- HORIZON ATTITUDE GYRO DESCRIPTION AND OPERATION
- HORIZON ATTITUDE GYRO REMOVAL AND INSTALLATION
- HORIZON ATTITUDE GYRO OPERATIONAL CHECK
- DIRECTIONAL GYRO DESCRIPTION AND OPERATION
- DIRECTIONAL GYRO REMOVAL AND INSTALLATION (AIRPLANES WITHOUT GARMIN G1000)
- DIRECTIONAL GYRO OPERATIONAL CHECK
- TURN COORDINATOR REMOVAL/INSTALLATION (AIRPLANES WITHOUT GARMIN G1000)
- TURN COORDINATOR REMOVAL AND INSTALLATION (AIRPLANES WITH GARMIN G1000)
- COMPASS INSTALLATION - MAINTENANCE PRACTICES
- MAGNETOMETER - MAINTENANCE PRACTICES
- ATTITUDE HEADING REFERENCE SYSTEM (AHRS) - MAINTENANCE PRACTICES
- MARKER BEACON - DESCRIPTION AND OPERATION
- MARKER BEACON - MAINTENANCE PRACTICES
- INDEPENDENT POSITION DETERMINING - DESCRIPTION AND OPERATION
- KMH-880 MULTI-HAZARD AWARENESS SYSTEM - MAINTENANCE PRACTICES
- KTA-870 TRAFFIC ADVISORY SYSTEM (TAS) - MAINTENANCE PRACTICES
- WX-500 STORMSCOPE - MAINTENANCE PRACTICES
- KX-155A COMM/NAV SYSTEM - MAINTENANCE PRACTICES
- GIA - 63 INTEGRATED AVIONICS INSTALLATION - MAINTENANCE PRACTICES
- KLN-89/KLN-89B/KLN-94 GPS - MAINTENANCE PRACTICES
- KR-87 ADF SYSTEM - MAINTENANCE PRACTICES
- KT-76C TRANSPONDER - MAINTENANCE PRACTICES
- KT-73 MODE S TRANSPONDER - MAINTENANCE PRACTICES
- GTX - 33 TRANSPONDER - MAINTENANCE PRACTICES
- GDL-69A FIS - DESCRIPTION AND OPERATION
- GDL-69A FIS - MAINTENANCE PRACTICES
- DME - MAINTENANCE PRACTICES
- KMD-540 MULTI-FUNCTION DISPLAY - MAINTENANCE PRACTICES
- CONTROL DISPLAY UNIT - MAINTENANCE PRACTICES
- CHAPTER 35 - OXYGEN
- CHAPTER 37 - VACUUM
- LIST OF EFFECTIVE PAGES
- RECORD OF TEMPORARY REVISIONS
- TABLE OF CONTENTS
- VACUUM SYSTEM - GENERAL
- VACUUM SYSTEM - TROUBLESHOOTING
- VACUUM SYSTEM - MAINTENANCE PRACTICES
- DESCRIPTION AND OPERATION
- VACUUM PUMP REMOVAL/INSTALLATION
- VACUUM MANIFOLD REMOVAL/INSTALLATION
- VACUUM REGULATOR FILTER REMOVAL/INSTALLATION
- GYRO FILTER REMOVAL/INSTALLATION
- VACUUM GAGE REMOVAL/INSTALLATION
- VACUUM TRANSDUCER REMOVAL/INSTALLATION
- VACUUM MANIFOLD TEST (FOR AIRPLANES WITH THE PARKER AIRBORNE MANIFOLD)
- VACUUM PRESSURE ADJUSTMENT/TEST (FOR AIRPLANES WITH THE PARKER AIRBORNE REGULATOR VALVE OR THE AERO ACCESSORIES REGULATOR VAL
- CHAPTER 51 - STANDARD PRACTICES - STRUCTURES
- CHAPTER 52 - DOORS
- LIST OF EFFECTIVE PAGES
- RECORD OF TEMPORARY REVISIONS
- TABLE OF CONTENTS
- DOORS - GENERAL
- CABIN DOORS - DESCRIPTION AND OPERATION
- CABIN DOORS - MAINTENANCE PRACTICES
- GENERAL
- CABIN DOOR REMOVAL/INSTALLATION
- CABIN DOOR WEATHERSTRIP REMOVAL/INSTALLATION
- CABIN DOOR LATCH LOCK REMOVAL/INSTALLATION
- CABIN DOOR LATCH ASSEMBLY REMOVAL/INSTALLATION
- CABIN DOOR LATCH CABLE ASSEMBLY INSTALLATION
- CABIN DOOR LOCK ASSEMBLY REMOVAL/INSTALLATION (ON AIRPLANES WITH STANDARD LOCKS)
- CABIN DOOR LOCK ASSEMBLY REMOVAL/INSTALLATION (ON AIRPLANES WITH MEDECO LOCKS)
- CABIN DOOR LOCK CAM ASSEMBLY REMOVAL/INSTALLATION (ON AIRPLANES WITH STANDARD LOCKS)
- CABIN DOOR LOCK CAM ASSEMBLY REMOVAL/INSTALLATION (ON AIRPLANES WITH MEDECO LOCKS)
- CABIN DOOR ADJUSTMENT/TEST
- CABIN DOOR LATCH CABLE ASSEMBLY RIGGING
- CABIN DOOR INSIDE HANDLE RIGGING
- LATCH ASSEMBLY ADJUSTMENT/TEST
- BAGGAGE DOOR - MAINTENANCE PRACTICES
- CHAPTER 55 - STABILIZERS
- CHAPTER 56 - WINDOWS
- CHAPTER 57 - WINGS
- CHAPTER 61 - PROPELLERS
- CHAPTER 71 - POWER PLANT
- LIST OF EFFECTIVE PAGES
- RECORD OF TEMPORARY REVISIONS
- TABLE OF CONTENTS
- POWERPLANT - GENERAL
- ENGINE - DESCRIPTION AND OPERATION
- ENGINE - TROUBLESHOOTING
- ENGINE - MAINTENANCE PRACTICES
- COWL - MAINTENANCE PRACTICES
- ENGINE MOUNT - MAINTENANCE PRACTICES
- AIR INDUCTION SYSTEM - MAINTENANCE PRACTICES
- DRAIN LINES - MAINTENANCE PRACTICES
- CHAPTER 73 - ENGINE FUEL AND CONTROL
- LIST OF EFFECTIVE PAGES
- RECORD OF TEMPORARY REVISIONS
- TABLE OF CONTENTS
- ENGINE FUEL AND CONTROL - GENERAL
- FUEL INJECTION SYSTEM - DESCRIPTION AND OPERATION
- FUEL INJECTION SYSTEM - TROUBLESHOOTING
- FUEL INJECTION SYSTEM - MAINTENANCE PRACTICES
- GENERAL
- PRECAUTIONS
- FUEL/AIR CONTROL UNIT REMOVAL/INSTALLATION
- FUEL DISTRIBUTION VALVE REMOVAL/INSTALLATION
- INJECTION NOZZLES REMOVAL/INSTALLATION
- INJECTION NOZZLE FLOW TEST
- IDLE AND MIXTURE ADJUSTMENT
- INJECTOR NOZZLE CLEANING
- FUEL STRAINER CLEANING
- AIR THROTTLE SHAFT LUBRICATION
- ENGINE DRIVEN FUEL PUMP PRESSURE SETTING (T182)
- FUEL FLOW INDICATOR - MAINTENANCE PRACTICES
- CHAPTER 74 - IGNITION
- CHAPTER 76 - ENGINE CONTROLS
- CHAPTER 77 - ENGINE INDICATING
- LIST OF EFFECTIVE PAGES
- RECORD OF TEMPORARY REVISIONS
- TABLE OF CONTENTS
- ENGINE INDICATING - GENERAL
- TACHOMETER - MAINTENANCE PRACTICES
- ENGINE TEMPERATURE - DESCRIPTION AND OPERATION
- ENGINE TEMPERATURE INDICATING SYSTEM - MAINTENANCE PRACTICES
- MANIFOLD PRESSURE TRANSDUCER - MAINTENANCE PRACTICES
- GEA-71 ENGINE/AIRFRAME UNIT - MAINTENANCE PRACTICES
- CHAPTER 78 - EXHAUST
- CHAPTER 79 - OIL
- CHAPTER 80 - STARTING
- CHAPTER 81 - TURBINES
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Camepn.
Maintenance
Manual
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Member
of
GAMA
COPYRIGHT©0
1997
CESSNA AIRCRAFT
COMPANY
WICHITA,
KANSAS,
USA
3
FEBRUARY
1997
182SMM 14
~~REVISION
141JUY20
1
JULY
2007
182SMM14
CESSNA AIRCRAFT
COMPANY
MODEL
182/Ti
82
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Supplies
and
Publications
Catalog
...
Customer
Comments
on
Manual
.......................
LIST
OF
REVISIONS
...............................
Revisions..................................
LIST
OF
MANUFACTURERS
TECHNICAL
PUBLICATIONS
.............
List
of
Manufacturers Technical Publications
..................
LIST
OF
CHAPTERS
...............................
00
-
CONTENTS
Page
1
of
1
Jul
1/2007
©
Cessna
Aircraft Company
Page
1
Page
1
Page
1
Page
1
Page
1
Page
2
Page
2
Page
2
Page
2
Page
3
Page
3
Page
6
Page
6
Page
6
Page
6
Page
7
Page
7
Page
1
Page
1
Page
1
Page
1
Page
1
CESSNA AIRCRAFT
COMPANY
MODEL
182/Ti182
MAINTENANCE
MANUAL
SERVICE
BULLETIN
LIST
1.
Service
Bulletins
Service
Bulletin
Date
Title
Manual
Incorporation
Pilot's Operating
Handbook Revision
Autopilot
Limitation
Placard
Installation
and
Control
Cable
Tension Inspection
Altimeter Certification
Logbook
Entry
Verification
Bendix/King Autopilot
Flight
Computer
Modification
Electrical
Wire
Bundle
Routing
Inspection
and
Modification
Fire
Extinguisher
Mounting
Bracket
Inspection
Fuel
Tank
Vent
Line
Inspection
Light
Dimming
Module
Resistor
Installation
Inspection
KLN 89B GPS
Navigation
System
Approach
Restrictions
Alternate
Static
Source
Valve
Inspection
Alternate
Air Door Hinge
Assembly Replacement
Engine Exhaust
Muffler
Inspection
Engine Exhaust
Muffler
Inspection
Pilot's
Operating
Handbook
and
Checklist
Revisions
Muffler Inspection Placard Installation
Brazilian
Pilot's
Operating
Handbook Revision
Firewall
Sealant
Replacement
KAP-140
Dual
Axis
Autopilot
Modification
KAP-140
Dual
Axis
Autopilot
Limitation
Alternator
Replacement
Pilot
and
Copilot
Seat
Back Pivot Fitting
Inspection
Pilot
and
Copilot
Seat
Roller
Inspection
Control
Column
Internal Slide
Attach
Screw
Inspection
©0
Cessna
Aircraft
Company
SERVICE
BULLETIN
LIST
Page
1
Jul
1/2007
Service
Bulletin
Number
Jul
1/97
Sep 21/98
Dec
15/97
Oct
6/97
Dec
22/97
Dec
1/98
Dec
1/98
Dec
1/98
Dec
1/98
Dec
1/98
Dec
Dec
Dec
1/98
1/98
1/98
SB97-1
1-02
SB97-11-03
R1
SB97-1
1-05
SB97-22-01
SB97-24-02
SB97-26-01
SB97-28-02
SB97-33-01
R1
SB97-34-01
SB897-34-02
R1
SB97-71-01
R1
SB97-78-01
SB897-78-02
R1
SB98-11-03
SB98-1
1-04
5898-11-07
SB98-20-01
Ri1
SB98-22-01
SB98-22-02
R2
SB98-24-01
SB98-25-01
SB98-25-02
SB98-27-04
Dec
22/97
Nov
14/97
Dec
14/98
Jul
2/97
Dec
8/97
Jul 27/97
Aug
11
/97
Dec
23/97
May 1/98
Dec
1/98
Dec
1/98
Dec
1/98
Dec
1/98
Dec
1/98
Dec
1/98
Aug
21/98
Oct
12/98
Dec
31/98
Dec
Dec
Dec
1/98
1/98
1/98
May
15/98
Feb
1/99
Mar
30/98
May
29/98
Sep
14/98
May
29/98
Dec
1/98
Dec
1/98
Dec
1/98
Dec
1/98
Dec
1/98
Dec
1/98
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti182
MAINTENANCE
MANUAL
Title
Flight
Control
Cables
and
Travel Inspection
Engine Fuel
Pressure
Transducer
Inspection
and
Replacement
KLN
89B
GPS
Navigation System
IFR
Non-Precision
Approach
Limitation
Engine Air
Filter Replacement
Engine
Exhaust
Muffler
Pressure
Test
and
Ball
Joint
Inspection
Airborne
Vacuum Pump
Inspection
Horizontal
Stabilizer
Forward
Inboard
Rib
To
Spar
Gap
Inspection
Engine
Exhaust
Muffler
Replacement
German Pilot's
Operating
Handbook
and
Checklist Revisions
Fresh Air Vent
Replacement
Electrical
Power
System
Modification
Circuit
Panel
Assembly
Cover Installation
Emergency Locator
Transmitter
(ELT)
Operational
Test
Wing
Fuel
Tank
Vent
Check
Valve
Inspection
Brake Torque
Plate
Inspection
KLN
89B
GPS
Navigation System
Modification
Service
Bulletin
Date
Jun
15/98
Mar
2/98
Aug
3/98
Jul
27/98
Dec
14/98
Mar 8/99
Nov
30/98
Feb
14/98
Sep
27/99
Mar 15/99
Mar
15/99
Dec
27/99
Dec
27/99
Apr
26/99
May
10/99
Apr 24/00
Manual
Incorporation
Dec
1/98
Dec
1/98
Dec
1/98
Dec
1/98
Dec
1/98
Dec
1/99
Dec
1/99
Dec
1/99
Dec
1/99
Dec
1/99
Dec
1/99
Nov
1/00
Jun
1/00
Dec
1/99
Dec
1/99
Dec
1/99
Vacuum
Hose Modification
Firewall
Doubler
Inspection
and
Engine
Cowl
Shock
Mount
Installation
Tailcone
Skin Installation Inspection
Engine
Piston
Pin
Plug
Wear Inspection
Engine
Valve Seat
Inspection
KAP-1
40
Autopilot
Servo
Inspection/Modification
Main
Power
Junction
Box
Circuit
Breaker
Retrofit
Kit
Installation
Electrical
Panel Wiring
Modifications
Lower
Forward Elevator
Control
Cable
Pulley
Brackets
Inspection
Pitot Tube
Heater
Assembly
Insulation
Installation
©D
Cessna
Aircraft
Company
SERVICE
BULLETIN
LIST
Page
2
Jul
1/2007
Service
Bulletin
Number
SB98-27-06
SB98-28-01
SB98-34-01
R1
SB98-71
-02
SB98-78-02
R1
SB98-37-01
R1
SB98-55-03
SB98-78-03
SB99-1
1-02
SB99-21
-01
SB99-24-01
SB99-24-02
SB99-25-01
R1
SB99-28-01
SB99-32-01
SB99-34-01
R1
SB99-37-01
SB99-53-01
SB99-53-02
SB99-71
-01
R2
SB99-71
-05
SBOO-22-01
SBOO-24-01
SBOO-24-02
SBOO-27-0
1
R1
SBOO-34-01
Dec
27/99
Mar
8/99
Apr 26/99
Jul
12/99
Oct
25/99
Feb
14/00
Mar
13/00
Jun
5/00
Aug
28/00
Apr
1
0/00
Nov
1 /00
Dec
1/99
Dec
1/99
Dec
1/99
Jun
1/00
Nov
1/00
Nov
1/00
Nov
1/00
Nov
1/00
Nov
1/00
CESSNA AIRCRAFT
COMPANY
MODEL
182/Ti
82
MAINTENANCE
MANUAL
Service
Bulletin
Date
Title
Manual
Incorporation
Vacuum
System
Air
Filter
Element
Inspection/Replacement
Center
Cabin
Rivet
Inspection/Installation
Engine
Fuel
Injection Lines
and
Support
Clamps
Inspection
Engine
Low
Oil
Pressure
Switch
Replacement
Pilot's Operating Handbook
and
Pilot's
Checklist
Revision
Aileron
Control
Cable
Quadrant
Inspection
Inspection/Modification
Engine
Driven
Fuel
Pump
Inspection
Ignition Switch
Center
Ground
Terminal
Inspection
Engine
Turbocharger
Mounting
Bolt
Replacement
Glareshield
Shroud
Installation
Fuel
Quantity
Level
Sender/Transmitter
Inspection
Coin
Antenna Replacement
Pilot's
Operating Handbook Revisions
Pilot's
Operating
Handbook
Revisions
Honeywell
Kap
140
Autopilot
System
Modification
Pilot
and
Copilot
Shoulder
Harness
Guide
Removal
Fuel
Line
Inspection
Goodrich
WX-500
Weather
Mapping Sensor
Modification
Vacuum
System
Reducer
Fitting
Replacement
Dry
Vacuum
Pump
and
Coupling
Replacement
Requirements
Vacuum
System Reducer
Fitting
Replacement
Airborne
Air
and
Fuel
Products Check
Valve
Manifold
Inspection
Cabin
Door
Handle
Replacement
Fuselage
Ballast
Weight
Installation
©
Cessna Aircraft
Company
SERVICE
BULLETIN
LIST
Page
3
Jul
1/2007
Service
Bulletin
Number
SBOO-37-01
SBOO-53-01
R1
SBOO-73-01
R2
SBOO-79-01
R1
S
BOO-i11-05
SBOO-27-02
R1
SBO1
-73-01
R2
SBO1
-74-01
SBO01
-71
-03
SBO1
-25-01
SBO1
-28-04
SBO1
-34-01
SB02-1
1
-1
SB02-11-02
SB02-22-01
SB02-25-01
SB02-28-01
R1
SB02-34-01
SB02-37-01
SB02-37-02
SB02-37-03
SB02-37-04
SB02-52-01
S
B02-53-01
Aug
14/00
Apr
1
0/00
Dec
24/01
Feb
21/00
Dec
26/00
Nov
6/00
Oct
10/05
Jun 25/01
Aug
20/01
Dec
24/01
Oct
1 /01
Sep
3/01
Jan
21/02
Jan
21/02
Nov
25/02
Apr
29/02
Dec
16/02
Nov
25/02
Jan
21/02
Feb
18/02
Feb
18/02
Oct
28/02
Jan
21/02
Sep 9/02
Nov
1/00
Jun
18/01
Jan
2/06
Nov
1/00
Jun
18/01
Jun
18/01
No Effect
Jun
18/01
No
Eff
ect
No
Eff
ect
No
Eff
ect
No Eff
ect
No
Effect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti
182
MAINTENANCE
MANUAL
Title
Elevator
Rivet
Installation
Engine
Crankshaft
Gear
Retaining
Bolt
Replacement
Engine
Induction
System
Fuel
Overboard
Drain
Relocation
Engine
Oil
Pump Plug
Inspection
Service
Bulletin
Date
Oct
14/02
May
10/04
Nov
25/02
Feb
03/03
Manual
Incorporation
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
SB03-23-01
SB03-24-01
SB03-24-02
SB03-27-01
SB03-27-02
SB03-28-01
SB03-32-01
SB03-34-01
SB03-34-02
R1
SB03-37-01
SB03-53-01
SB03-53-03
R1
SB03-71
-02
SB03-73-01
SB04-11-03
SB04-22-01
SB04-23-01
S
B04-24-0
1
SB04-25-01
R4
SB04-25-02
R1
SB04-25-04
SB04-27-01
R2
SB04-28-02
Honeywell
KMA 26
Audio
Panel
Modification
Alternator
Replacement
MC01
-3A
Main
Electrical Power
Junction
Box
Modification
Flap
Actuator
Motor
Inspection
Flap
Control Bracket
Attach Bolts
Replacement
Fuel
Cap
Lanyard
Removal
Nose
Landing
Gear Wheel
Fairing
Modification
Honeywell
KS
2700,
KS
271
C
and
KS
272C
Servo
Friction
Inspection
Altimeter
Inspection
Vacuum Manifold
Inspection/Replacement
Aft
Cabin Stringer
Inspection
Nose
Landing
Gear
Fairing
Attachment
Inspection
Fuel
Injection
Servo
Inspection
Throttle
Arm
Retention
Inspection
NAV
III
Pilot's
Checklist
Autopilot
Circuit Breaker
Extension
Cap
Installation
Garmin
GIA
63
Inspection/Modification
Alternator
Control
Unit
Inspection/Replacement
Crew Seat
Recline
Modification
Crew Seat
Back
Cylinder
Lock
Inspection
and
Crank
Arm
Modification
Crew
Seat
Back
Cylinder
Lock
Control
Inspection/Adjustment
Elevator
Rivet
Inspection
Fuel
Strainer
Installation
Inspection
C
Cessna
Aircraft
Company
SERVICE
BULLETIN
LIST
Page
4
Jul
1/2007
Service
Bulletin
Number
SB02-55-01
SB02-71
-03
R2
SB02-7
1-04
SB02-71
-05
R1
Jul
28/03
Jul
28/03
Oct 13/03
Sep
29/03
Dec
22/03
Oct 27/03
Sep 29/03
Oct
27/03
Feb
16/04
Nov
10/03
May
26/03
Mar
15/04
May
26/03
Nov
4/03
Aug
30/04
Sep
13/04
Sep
13/04
Mar
1/04
Dec
26/06
Oct
17/05
Oct
11/04
Sep
13/04
May
10/04
No
Eff
ect
No
Effect
No Effect
No
Eff
ect
No
Eff
ect
Jan 2/06
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti
82
MAINTENANCE
MANUAL
Title
Marker
Beacon
Placard
Installation
Vertical
Navigation
Placard
Installation
Security
Lock
Installation
Firewall
Doubler
Flange
Modification
and
Shock
Mount
Inspection
Forward
Door
Post
Bulkhead
Washer
Inspection
Engine
Cowl
Flap
Rivet
Inspection
Engine Starter
Inspection/Replacement
Engine
Fuel
Injection
Lines
and
Support
Clamps
Inspection
Pilot's
Operating
Handbook
Revisions
Trim
Servo
Cable
Chain
Inspection
Honeywell
KAP-140
Autopilot Software
Modification
MC01
-3A Main
Electrical
Power
Junction
Box
Circuit
Breakers
Inspection
Inflatable
Seat
Belt
Restraint
Installation
Inspection
Inflatable
Seat
Restraints
Installation
Fuel
Strainer
Gasket
Inspection
High
Intensity
Discharge
(HID)
Landing
and
Taxi
Light Installation
Garmin
G1000 System
Software
Upgrade
Garmin
GMA
1347
Audio
Panel
Modifications
Garmin
GMA
63
Integrated Avionics
Unit
Modification
Garmin
GMA
63
Integrated Avionics
Unit
Modification
Garmin G1000
System Software
Upgrade
Garmin G1000 GDL-69A Weather
and
Digital
Audio Entertainment
Interface
Installation
Garmin
G1lOQO
Obstacle
And Terrain
Avoidance
System
Database
Update
Garmin
G1000
System Software Upgrade
Garmin
G
1000
GDL-69A
Weather
And
Digital
Audio Entertainment
Interface
Installation
Aft
Avionics
And
Electrical
Wire
Bundle
Inspection
Service
Bulletin
Date
Nov
22/04
Dec
27/04
Jun
28/04
Apr
11/05
Oct
11
/04
Apr
26/04
Nov
8/04
Aug
30/04
Mar
28/05
Dec
5/05
Dec
5/05
Jan
31/05
Mar
7/05
Apr
25/05
Jan
17/05
May
9/05
Jan
31/05
Feb
14/05
Feb
14/05
Apr
25/05
Jul
29/05
Jul
29/05
Sep
26/05
Sep
26/05
Sep
26/05
Nov
21/05
Manual
Incorporation
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Effect
No
Eff
ect
Jan
2/06
No
Eff
ect
No
Effect
No
Effect
No
Effect
No
Eff
ect
No
Eff
ect
No
Eff
ect
Jan
2/06
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Effect
No
Effect
No
Effect
No
Eff
ect
No
Eff
ect
No
Eff
ect
©
Cessna Aircraft
Company
SERVICE
BULLETIN
LIST
Page
5
Jul
1/2007
Service
Bulletin
Number
SB04-34-01
SB04-34-02
SB04-52-01
SB04-53-02
R1
SB04-53-03
SB04-71
-01
SB04-71
-02
SB04-73-01
SB05-1
1-02
SB05-22-01
SB05-22-02
SB05-24-01
SB05-25-01
SB05-25-02
SB05-28-01
SB05-33-01
SB05-34-01
SB05-34-02
SB05-34-03
SB05-34-04
SB05-34-05
SB05-34-06
SB05-34-07
SB05-34-08
SB05-34-09
SB05-34-1 0
CESSNA AIRCRAFT
COMPANY
MODEL
182/7182
MAINTENANCE
MANUAL
Title
Garmin
GIA 63
Integrated
Avionics
Unit
Outside
Cover
Replacement
Garmin
G1000
Display
Unit
(GDU)
1040
Cover
Glass
Delamination
Vacuum
Pump
Inspection/Replacement
Tunnel Bulkhead
Rivet
Inspection
Wing
Trailing
Edge
Rib
Inspection
Engine
Crankshaft Replacement
Engine
Driven
Fuel
Pump
Inspection
Service
Bulletin
Date
Nov 21/05
Dec
5/05
Nov
7/05
Sep
12/05
Oct
10/05
Jul
18/05
Mar
7/05
Manual
Incorporation
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
Pilot's
Operating
Handbook Revisions
Pilot's
Checklist Revisions
Honeywell
KS270C
Pitch
Servo
and
KS271C
Roll
Servo
Tach
Generator
Modification
Electrical
Ground
Strap
Inspection
60
Ampere
Alternator
Rotor
Replacement
60
Ampere
Alternator
Brush
Replacement
Circuit
Breaker
Inspection
Circuit
Breaker
Panel
Assembly
Inspection
Flap
Aft
Roller
Bearing
Installation
Modification
Brake
Master Cylinder Covers Inspection
Honeywell
KT
73
MODE
S
Transponder
Installation
Garmin
G1000
System
Software
Upgrade
Enablement
of
Garmin
G1000
Terrain
Awareness
Warning
System
CLASS-B
(TAWS-B)
Automatic
Direction
Finder
(ADF)
and
Distance
Measuring Equipment
(DMVE)
Installation
Cabin
Door
Modification
Fuselage
Stringer
Rivet
Inspection
Engine
Crankshaft
Retirement
Engine
Compartment
Fuel
Hoses
Security
Inspection
©
Cessna
Aircraft
Company
SERVICE
BULLETIN
LIST
Page
6
Jul
1/2007
Service
Bulletin
Number
SB05-34-1
1
SB05-34-1
2
SB05-37-01
SB05-53-02
SB05-57-01
SB05-71
-01
SB05-73-01
SB06-11
-01
SB06-1
1-02
SB06-22-01
SB06-24-01
SB06-24-02
R1
SB06-24-03
SB06-24-04
SB06-24-05
SB06-27-0
1
SB06-32-01
SB06-34-01
SB06-34-02
R1
SB06-34-03
S
B06-34-04
SB06-52-01
SB06-53-01
SB06-71
-01
R1
SB06-71
-02
Mar 27/06
Nov
6/06
Apr 24/06
May
8/06
Dec
18/06
Dec
18/06
Dec
26/06
Dec
26/06
Apr
10/06
Sep
25/06
Feb
27/06
Mar 27/06
May 22/06
Oct 23/06
Mar
27/06
Oct 23/06
May 8/06
Jun
19/06
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
No
Eff
ect
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INTRODUCTION
1.
General
WARNING:
All
inspection
intervals,
replacement
time
limits,
overhaul
time
limits,
the
method
of
inspection,
life
limits,
cycle
limits,
etc.,
recommended
by Cessna
are
solely
based
on
the
use
of
new,
remanufactured,
or
overhauled
Cessna
approved
parts.
If
parts
are
designed,
manufactured, remanufactured,
overhauled,
and/or
approved
by
entities
other
than
Cessna,
then
the
data
in
Cessna's
maintenance/service
manuals
and
parts
catalogs
are
no
longer
applicable
and
the
purchaser
is
warned
not to
rely
on
such
data
for
non-Cessna parts.
All
inspection
intervals,
replacement
time
limits,
overhaul
time
limits,
the
method
of
inspection,
life
limits,
cycle
limits,
etc.,
for
such
non-Cessna
parts must
be
obtained
from
the
manufacturer and/or
seller
of
such
non-Cessna
parts.
A.
The information
in
this
publication
is
based
on
data
available
at
the time
of
publication
and
is
updated,
supplemented,
and
automatically
amended by
all
information
issued
in
Service
Newsletters, Service
Bulletins,
Supplier
Service
Notices,
Publication
Changes,
Revisions,
Reissues
and
Temporary
Revisions.
All
such
amendments become
part
of
and
are
specifically
incorporated within this
publication.
Users
are
urged to
keep
abreast
of
the latest amendments
to
this
publication
through
information
available
at
Cessna
Authorized
Service
Stations
or
through
the
Cessna
Propeller
Aircraft
Product
Support
subscription
services.
Cessna
Service Stations
have
also
been
supplied
with
a
group
of
supplier
publications
which
provide
disassembly,
overhaul, and
parts
breakdowns
for
some
of
the
various
supplier
equipment
items.
Suppliers
publications
are
updated,
supplemented,
and
specifically
amended
by
supplier
issued
revisions
and
service
information
which may
be
reissued
by
Cessna
thereby
automatically
amending
this publication
and
are
communicated
to
the
field
through
Cessna's
Authorized Service Stations
and/or
through
Cessna's subscription
services.
B.
Inspection,
maintenance
and
parts
requirements
for
STC
installations
are
not
included
in
this
manual.
When
an
STC
installation
is
incorporated
on
the
airplane,
those
portions
of
the
airplane
affected
by
the
installation
must
be
inspected
in
accordance
with
the
inspection
program
published
by
the
owner
of
the
STC.
Since
STC
installations
may
change
systems
interface, operating
characteristics
and
component
loads
or
stresses
on
adjacent structures.
Cessna
provided
inspection
criteria
may
not
be
valid
for
airplanes
with
STC
installations.
C.
REVISIONS,
REISSUES
and
TEMPORARY
REVISIONS
can
be
purchased
from
your
Cessna
Service Station
or
directly
from
Cessna Propeller Aircraft
Product Support,
Department
751,
Cessna
Aircraft Company,
P.O.
Box
7706,
Wichita,
Kansas
67277-7706.
D.
Information
in
this Maintenance
Manual
is
applicable
to
all
U.S.
and Foreign
Certified
Model
182
airplanes beginning
at
serial
18280001
and T182
airplanes
beginning
at
serial
T18208001.
Information unique
to
a
particular
country
is
identified
in
the
chapter
affected.
E.
All
supplemental
service
information
concerning this
manual
is
supplied
to
all
appropriate
Cessna
Service
Stations
so
they
have the
latest
authoritative
recommendations
for
servicing
these
Cessna
airplanes.
It is
recommended
that
Cessna
owners
utilize
the
knowledge
and
experience
of
the
Cessna
Service
Station.
2.
Cross
Reference
Listing
of
Popular
Name
Verses
Model Numbers
and
Serials
A.
All
airplanes regardless
of
the
manufacturer, are
certified
under
model
number
designations.
Popular
names
are
often
used
for
marketing
purposes.
To
provide
a
consistent
method
of
referring
to
these
airplanes,
the
model
number
will
be
used
in
this publication
unless
the
popular
name
is
necessary
to
differentiate
between
versions
of
the
same
basic
model.
The following
table
provides
a
listing
of
popular
names, model
numbers
and serial
numbers.
INTRODUCTION
Page
1
©
Cessna
Aircraft
Company
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
NAME
MODEL
SERIALS
SERIALS
ENDING
BEGINNING
Skylane
182S 18280001
18280944
Skylane
182T
18280945
Skylane
TC
T182T
T18208001
3.
Coverage
and Format
A.
The
Cessna
Model 182/T182
1996
And
On
Maintenance
Manual has been prepared
to
help
maintenance
personnel
in
servicing
and
maintaining
the Model
182/T182
airplanes
(beginning
at
Serial
18280001
and
T18208001).
This
manual
provides
the
necessary
information
required
to
enable the mechanic
to
service,
inspect, troubleshoot,
remove
and
replace
components
or
repair
systems.
NOTE:
This
manual
is
not
intended
to
cover
Model
182
airplanes produced
prior
to
1996.
For
manuals
related
to
these
airplanes,
please
refer
to
applicable
listings
in
the
Cessna
Propeller
Aircraft Customer
Care
Supplies
&
Publications
Catalog.
B.
This
manual
has been
prepared
in
accordance
with
the
Air
Transport
Association
(ATA)
Specification
Number
100
for Manufacturer's
Technical
Data.
C.
Information
beyond
the
scope
of
this
manual
may
be
found
in
the
applicable
Model
182
Wiring
Diagram
Manual,
Model
182
Illustrated
Parts
Catalog
and the
Single Engine
Models
172,
182,
T182,
206
and
T206
1996
And
On
Structural
Repair
Manual.
D.
Technical
Publications
are
also
available
for
the
various
components
and
systems
which
are
not
covered
in
this
manual.
These
manuals must
be
utilized
as
required
for
maintenance
of
those
components
and
systems,
and
may
be
purchased
from
the manufacturer.
4.
Temporary
Revisions
A.
Additional
information
which
becomes
available
may
be
provided
by
temporary
revision.
This
service
is
used
to
provide, without
delay,
new
information which
will
assist
in
maintaining
safe
flight/ground
operations.
Temporary
revisions
are
numbered
consecutively
within
the
ATA
chapter
assignment.
Page
numbering
utilizes
the
three-element
number
which matches
the
maintenance
manual.
Temporary
revisions
are
normally incorporated
into the
maintenance
manual
at
the next
regularly
scheduled
revision.
5.
Serialization
A.
All
Model
182
airplanes
are
issued
a
serial number.
This
number
is
assigned
as
construction
begins
and
remains with the
airplane
throughout
its
service
life.
This
serial number appears
on
the
airplane
ID
plate, located
below
the
horizontal
stabilizer,
and
on a
trim plate
located
on
the
pilot
side doorpost.
This serial number
is
used
to identify
changes
within
the
text
or
within
an
illustration.
The
absence
of
a
serial
number
in
text
or
illustration
indicates
the
material
is
applicable
to
all
airplanes.
6.
Material
Presentation
A.
This
Maintenance
Manual
is
available
on
paper,
aerofiche
or
Compact
Disc
(CD/ROM).
The
CD/ROM
contains
the Maintenance
Manual,
Illustrated
Parts
Catalog Manual, Wiring
Diagram Manual
and
Structural Repair
Manual
on
a
single
disc.
INTRODUCTION
Page
2
©
Cessna
Aircraft
Company
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
7.
Service
Bulletins
A.
Service
Bulletins
may
require
special
inspections
and
authorize
modifications
to
the
airplane
and/or
system.
As
service
bulletins
are
issued,
they
will
be
incorporated
in
the
next
scheduled
revision
and
noted
in
the
Service
Bulletin
List,
located
previous
to
the
Introduction.
The list
of
service
bulletins
utilizes
four
columns
to
summarize
information.
(1)
Service
Bulletin Number
-
This
Service
Bulletin number
column identifies
the
bulletin
by
number.
Service
Bulletins
are numbered
consecutively
within
ATA
chapter
assignment.
(2)
Service
Bulletin
Date
-
The
service
bulletin
date
column
indicates
the
initial
date
the
bulletin
became
active.
(3)
Title
-
The
title
column identifies
the
service
bulletin
by
nomenclature.
It is
the
same
title displayed
on
page
one
of the
service
bulletin.
(4)
Manual
Incorporation
-
The
manual
incorporation column
indicates
if
the
service
bulletin
has
been
incorporated
in
the
maintenance
manual
by
date,
if
the
service bulletin
had
no
effect
on
the
maintenance
manual
(No
Effect),
or
if
the
service bulletin
has
not
been
worked (dashed
lines).
8.
Using
the
Maintenance
Manual
A.
Division
of
Subject
Matter.
(1)
The
Maintenance
Manual
is
divided
into
four
major
sections.
The
major
sections
are
in
turn
separated
into
chapters,
with each
chapter
having
its
own
effectivity
page
and
table
of
contents.
The manual
divisions
are
as
follows:
(a)
Major
Section
1
-
Airplane
General
Chapter
Title
5
Time
Limits/Maintenance Checks
6
Dimensions
and
Areas
7
Lifting
and
Shoring
8
Leveling
and
Weighing
9
Towing and
Taxiing
10
Parking, Mooring,
Storage
and
Return
to
Service
11
Placards and
Markings
12
Servicing
(b)
Major Section
2
-
Airframe
Systems
Chapter
Title
20
Standard
Practices
-
Airframe
21
Air
Conditioning
22
Auto
Flight
23
Communications
24 Electrical
Power
25
Equipment/Furnishings
26
Fire
Protection
27 Flight
Controls
28
Fuel
INTRODUCTION
Page
3
©
Cessna
Aircraft
Company
April 1/2002
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
Chapter
Title
30
Ice
and
Rain
Protection
31
Indicating/Recording
Systems
32
Landing
Gear
33
Lights
34
Navigation
35
Oxygen
37
Vacuum
(c)
Major
Section
3
-
Structures
Chapter
Title
51
Standard Practices
and
Structures
-
General
52
Doors
55
Stabilizers
56
Windows
57
Wings
(d)
Major
Section
4
-
Power
Plant
Chapter
Title
61
Propeller
71
Power
Plant
73
Engine
Fuel
and
Control
74
Ignition
76
Engine
Controls
77
Engine
Indicating
78
Exhaust
79
Oil
80
Starting
81
Turbines
B.
Page
Numbering System.
(1)
The
page
numbering system
used
in
the
Maintenance
Manual
consists
of
three-element
numbers
separated
by
dashes.
Refer
to
the
example
below
for
an
illustration
of
typical
numbering layout
as
used
in
the
ATA
format.
INTRODUCTION
Page
4
©
Cessna
Aircraft
Company
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
Chapter/System
22-10-00
Subject/Unit
(Auto
Flight)
(Auto
Pilot)
Section/Subsystem
(Auto
Pilot)
(2)
When
the
chapter/system
element
number
is
followed
with
zeros
in
the
section/subsystem
and
subject/unit
element
number (21-00-00), the information
is
applicable
to
the entire
system.
(3)
When
the
section/subsystem
element
number
is
followed
with
zeros
in
the
subject/unit
element
number
(21-51-00),
the information
is
applicable
to
the
subsystem
within
the system.
(4)
The
subject/unit
element number
is
used
to
identify
information
applicable
to units
within
the
subsystems.
The
subject/unit
element
number
progresses
sequentially
from
the
number
-01
in
accordance
with
the
number
of
subsystem
units
requiring
maintenance
information.
(5)
All
system/subsystem/unit
(chapter/section/subject)
maintenance
data
is
separated
into
specific
types
of
information:
description
and
operation, troubleshooting,
maintenance practices.
Blocks
of
sequential
page
numbers
are
used
to identify
the
type
of
information:
Page
1
through
99
-
Description
and
Operation
Page
101
through
199
-
Troubleshooting
Page
201
through
299
-
Maintenance
Practices
Page
301
through
399
-
Servicing
Page
401
through
499
-
Removal/Installation
Page
501
through
599
-
Adjustment/Test
Page
601
through
699
-
Inspection/Check
Page
701
through
799
-
Cleaning/Painting
Page
801
through
899
-
Approved
Repairs
NOTE:
In
most
cases,
the
individual
topics
have been
combined
into
a
200-series
document
(Maintenance
Practices).
When
specific topics
require
lengthy
explanation, they
will
utilize
the
page
blocks
mentioned
above.
(6) A
typical
page
number:
22-10-00
Page
202
Second
Page
of
Nov
3/97
Auto Pilot
Auto Flight
Auto
Pilot
Date
of
Page
Issue
Auto
Pilot
(7)
Illustrations
are
also
tied into
the
page
block
numbering
system.
For
example,
all
illustrations
within
a
Maintenance
Practices section will
begin
with
the number
2
(i.e.
Figure
201,
Figure
202,
etc.).
Conversely,
all
illustrations
within
an
Approved
Repair
section
will
begin
with
the
number
8
(i.e.
Figure
801,
Figure
802,
etc.).
INTRODUCTION
Page
5
©
Cessna
Aircraft Company
April
1/2002
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
9.
Effectivity
Pages
A.
A
list of
effectivity
pages
are
provided
at
the
beginning
of
each
maintenance
manual
chapter.
All
pages
in
the
specific
chapter
are
listed
in
numerical
sequence
on
the
Effectivity
Page(s)
with
the date
of
issue
for
each
page.
10.
Revision
Filing
Instructions
A.
Regular Revision.
(1)
Pages
to
be
removed
or
inserted
in
the maintenance
manual
are
determined
by
the effectivity
page.
Pages
are
listed
in
sequence
by the
three-element
number
(chapter/section/subject)
and
then
by
page
number.
When two
pages
display
the
same
three-element
number
and
page
number,
the
page
with the
most
recent
Date
of
Page
Issue
shall
be
inserted
in
the
maintenance
manual.
The date
column
on
the
corresponding
chapter effectivity
page shall
verify
the
active
page.
B.
Temporary
Revision.
(1)
File
temporary
revisions
in
the
applicable chapter
in
accordance
with
filing
instructions
appearing
on
the
first
page
of
the temporary
revision.
(2)
The
rescission
of
a
temporary revision
is
accomplished
by
incorporation
into
the
maintenance
manual
or
by
a
superseding
temporary
revision.
A
Record
of
Temporary
Revisions
is
furnished
in
the
Temporary
Revision
List located
previous
to
the Introduction.
A
Manual
Incorporation
Date
column
on
the
Temporary Revision
List page
will
indicate
the
date
the
temporary
revision was
incorporated,
thus
authorizing
the
rescission
of
the
temporary
revision.
11.
Identifying
Revised
Material
A.
Additions
or
revisions
to
text
in
an
existing section
will
be
identified
by
a
revision
bar
in
the
left margin
of
the page and
adjacent
to
the
change.
B.
When
technical changes cause
unchanged
text
to appear
on
a
different
page(s),
a
revision
bar
will
be
placed
in
the
left margin
opposite the
chapter/section/subject,
page
number
and
date
of
all
affected
pages,
providing
no
other
revision
bar
appears
on
the
page.
These
pages will
display
the current
revision date
in
the Date of
Page Issue
location.
C.
Chapter
5
may
contain revision
bars to
indicate
revised
text.
However,
inspection
items are
noted
as
revised, added
or
deleted
by the
date
of
changed
item
code.
Also,
a
revision date
is
indicated
below
the
page number.
D.
When
extensive
technical
changes
are
made
to
text
in
an
existing
section
that
requires
extensive
revision, revision
bars
will
appear
the
full
length
of text.
E.
Revised and
new
illustrations
will
be
indicated
by
either
a
revision
bar
along
the
side
of
the
page
or
a
hand
indicator directing
attention
to
the area.
12.
Warnings,
Cautions
and
Notes
A.
Throughout
the
text
in
this
manual,
warnings,
cautions
and
notes
pertaining
to
the
procedures
being
accomplished
are
utilized. These
adjuncts
to
the
text
are
used
to
highlight
or
emphasize
important
points.
Warnings
and
Cautions
precede
the
text
they
pertain
to, and
Notes
follow
the
text
they
pertain
to.
(1)
WARNINGS
-
Calls attention
to
use of
materials,
processes,
methods,
procedures
or
limits
which
must
be
followed
precisely
to
avoid
injury
or death
to
persons.
(2)
CAUTIONS
-
Calls
attention
to
methods
and
procedures
which
must
be
followed
to
avoid
damage
to
airplane
and
equipment.
(3)
NOTES
-
Contains information
only.
INTRODUCTION
Page
6
0
Cessna
Aircraft
Company
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
13.
Cessna
Propeller
Aircraft
Customer
Care
Supplies
and
Publications
Catalog
A.
A
Cessna Propeller
Aircraft Customer
Care
Supplies
and
Publications
Catalog
is
available
from
a
Cessna
Service
Station
or
directly
from
Cessna Propeller Aircraft Product
Support
Dept.
751
Cessna
Aircraft
Company,
P.O.
Box
7706,
Wichita,
Kansas
67277-7706. The
catalog lists all
publications
and
Customer
Care
Supplies available
from
Cessna
for
prior
year
models
as
well
as
new
products.
To
maintain
this catalog
in
a
current status,
it
is
revised
yearly
and
issued
in
paper and
aerofiche
form.
14.
Customer
Comments
on
Manual
A.
Cessna
Aircraft Company
has
endeavored
to
furnish
you with
an
accurate,
useful,
up-to-date
manual.
This
manual
can
be
improved with
your
help.
Please
use the return
card, provided with
your
manual,
to
report
any
errors,
discrepancies,
and
omissions
in
this
manual
as
well
as
any
general
comments
you
wish
to
make.
INTRODUCTION
Page
7
©
Cessna
Aircraft
Company
April 1/2002
CESSNA AIRCRAFT
COMPANY
MODEL
182/Ti
82
MAINTENANCE
MANUAL
LIST
OF
REVISIONS
1.Revisions
A.
This
Maintenance
Manual
includes
the
original
issue
and
the
revisions
listed
in
Table
1.
Make
sure
that
the
information
in
this manual
is
current
and
that
the
latest maintenance
and
inspection
procedures
are
available.
The
revisions
must
be
incorporated
in
the
manual
as
they
are
issued.
Table
1.
Basic
Manual
-
Original
Issue
3
February
1997
Date
Writer
1
December
1998
3 1
June 2000
5
l8
June
2001
1
April
2002
1
March
2004
1 1 2
January
2006
1
13
1
January
2007
Revision
Number
2
Date
Writer
1
December
1999
4 1
November
2000
6
15
December
2001
8 4
August
2003
1 0 1
March
2005
12
3
July
2006
jgb
rdg
bjo
jcn
1
4
1
July
2007
©D
Cessna
Aircraft
Company
jgb
jgb
tks
bjo
jcn
LIST
OF
REVISIONS
Page
1
Jul
1/2007
Revision
Number
7
9
CESSNA AIRCRAFT
COMPANY
MODEL
182/Ti
82
MAINTENANCE
MANUAL
LIST
OF
MANUFACTURERS
TECHNICAL
PUBLICATIONS
1.
List
of
Manufacturers Technical
Publications
A.
Outlined
below
is a
list
of
manufacturers
publications.
Table
1.
CHAPTER
22
-
AUTOFLIGHT
Publica-
tion
Part
N
umber
Publication
Title
190-
G1000 Line
00352-00
Maintenance
Manual
GSA
190-
8X/GSM
85
00303-72 Installation
Manual
KAP
140
006-
00991-
0002
Manufacturer
Garmin
USA
1200
East
1
51
st
Street
Olathe,
KS
66062
Garmin
International,
Inc.
1200
E.
151st
Street
Olathe, Kansas
66062
Allied
Signal
101
N.
Industrial Parkway
New
Century,
KS
66031
Table
2.
CHAPTER
23
-
COMMUNICATIONS
Publication
Title
Manufacturer
KX-155A
006-
10542-
0000
KMA
26
006-
10544-
0000
Installation
Manual
Installation
Manual
Allied
Signal
101
N.
Industrial
Parkway
New
Century,
KS
66031
Allied
Signal
101
N.
Industrial
Parkway
New Century,
KS
66031
LIST
OF
MANUFACTURERS
TECHNICAL PUBLICATIONS
Page
1
©
Cessna
Aircraft
Company
Janl1/2007
Item
Cessna
Part
Number
Manufact-
urer's
Part
Number
GFC
-700
Autopilot
Autopilot
Servo
Autopilot
Item
Cessna
Part
Number
Manufact-
urer's
Part
Number
NAV/
Comm
Publica-
tion
Part
Number
Audio
Amplifier/
Intercom/
Marker
Beacon
Receiver
Item
CESSNA AIRCRAFT
COMPANY
MODEL
182/Ti
182
MAINTENANCE
MANUAL
Table
3.
CHAPTER
24
-
ELECTRICAL
POWER
Publication
Title
Cyclon
Selection
Guide
(Third
Edition)
(NOTE
1)
Manufacturer
AVT
Inc.
DBA
Electritek
-
AVT
400 East Mineral
Avenue
Littleton,
CO
80122-2604
Hawker
617
North
Ridgeview
Drive
Warrensburg,
MO
64093-9301
NOTE
1:
The
power cells
inside the
Standby
Battery
are
manufactured
by
Hawker
and
the
manufacturer
publication
that
is
shown
above
is
from
Hawker.
AVT
is
the
supplier
of
the
Standby Battery
pack
as
installed
in
the
airplane.
The
data
shown
in
the
Hawker
manual
is
informational
only.
Maintenance
procedures
for
the
Standby
Battery
given
in
Chapter
24,
Standby
Battery
-
Maintenance Practices
must
be
followed.
CHAPTER 25
-
EQUIPMENT
FURNISHING
Publica-
tion
Part
Number
Publication
Title
E508804 Supplemental
Maintenance
Manual
E508804 Supplemental
Maintenance
Manual
E508804
Supplemental
Maintenance
Manual
Manufacturer
AmSafe
Aviation
5456
E.
McDowell
Rd.
Mesa,
AZ
85215
www.amsafe.com
AmSafe
Aviation
5456
E.
McDowell
Rd.
Mesa,
AZ
85215
www.amsafe.com
AmSafe
Aviation
5456
E.
McDowell
Rd.
Mesa,
AZ
85215
www.amsafe.com
LIST
OF
MANUFACTURERS
TECHNICAL PUBLICATIONS
©
Cessna
Aircraft
Company
Item
Cessna
Part
Number
Standby
Battery
Manufact-
urer's
Part
Number
AVT-
200413
Publica-
tion
Part
Number
Item
Cessna
Part
Number
Manufac-
turer's
Part
Num-
ber
7035-1
-
011-
8105
(GO-Pilot
Seat)
7035-1
-
021-
8105
(Pilot
Seat)
7035-2-
011-
8105
(LH
Rear
Seat)
7035-2-
021-
8105
(RH
Rear
Seat)
508792-
401 (Co-
Pilot
Seat)
508794-
401
(Pilot
Seat)
508358-
409
Seat
Belt
Airbag
Assembly
Inflation
Assembly
Electronics
Module
Assembly
Page
2
an
1/2007
J
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti
182
MAINTENANCE
MANUAL
CHAPTER
25
-
EQUIPMENT FURNISHING
Publication
Title
Manufacturer
7035-
20301181
05
(Co-Pilot
Seat)
7035-
2040218105
(Pilot
Seat)
7035-
205021
8105
(LH
Rear
Seat)
7035-
206021
81
05
(RH
Rear
Seat)
508668-
201
E508804
Supplemental
Maintenance
Manual
E508804
Supplemental
Maintenance
Manual
AmSafe
Aviation
5456
E.
McDowell
Rd.
Mesa,
AZ
85215
www.amsafe.com
AmSafe
Aviation
5456
E.
McDowell
Rd.
Mesa,
AZ
85215
www.amsafe.com
Table
4.
CHAPTER
26
-
FIRE
PROTECTION
Publication
Title
Manufacturer
Fire
Extin- C421001-
A352
GS
guisher
0201
Hand
Portable
Halon
1211
Fire
Extinguisher
Maintenance
Manual
Amerex
Corp.
P.O.
Box
81
Trussville,
AL
351
73-0081
Table
5.
CHAPTER
32
-
LANDING
GEAR
Cessna
Part
Number
Manufact-
urer's
Part
Number
Publica-
tion
Part
Number
C163006-
40-75B
0301
30-
0521
9-1
30-52U
Publication
Title
Cleveland Wheels
&
Brakes
Component
Maintenance
Manual
Cleveland
Wheels
&
Brakes
Component
Maintenance
Manual
Manufacturer
Parker Hannifin Corporation
Aircraft
Wheel
&
Brake
1160
Center
Road
P.O.
Box
158
Avon,
OH
44011
Parker Hannifin
Corporation
Aircraft
Wheel
&
Brake
1160
Center
Road
P.O.
Box
158
Avon,
OH 44011
LIST
OF
MANUFACTURERS TECHNICAL
©
Cessna Aircraft
Company
PUBLICATIONS
Page
3
Janl1/2007
Part
Number
Man
ufac-
turer's
Part
Num-
ber
Publica-
tion
Part
Number
Three-
Point
Air
Bag
Belt
V23
System
Diagnostic
Tool
Item
Cessna
Part
Number
Manufact-
urer's
Part
Number
Publica-
tion
Part
Number
Item
Wheel
Brakes
Item
Item
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T
182
MAINTENANCE
MANUAL
Table
6.
CHAPTER
34
-
NAVIGATION
Item
Blind
Encoder
Cessna
Part
Number
Manufact-
urer's
Part
Number
3940408-1
SSD1
20-20
Navigation
066-
Indicator
03056-
0011
Automatic
Direction
Finder
Mode
C
Transpon-
der
066-
01
072-
0014
066-
01156-
0101
NAV
066-
Indicators
03056-
0002
GPS
066-
01148-
1111
Publica-
tion
Part
Number
Publication
Title
M881000D Altitude Encoder/
Digitizer
Owner/
Installation
Manual
KI
209A
006-
10543-
0000
KR
87
006-
001
84-
0005
KT
76C
006-
10545-
0000
KI
208/209
006-
00140-
0003
KLN
89/89B
Autopilot
3900008-1
KAP140
2-axis
006-
10522-
0001
Installation
Manual
Installation
Manual
Installation
Manual
Installation
Manual
Installation
Manual
Installation
Manual
Manufacturer
Trans-Cal
Industries,
Inc.
16141
Cohasset
St.
Van
Nuys,
CA
91406
Allied
Signal
101
N.
Industrial
Parkway
New
Century,
KS
66031
Allied
Signal
101
N.
Industrial
Parkway
New
Century,
KS
66031
Allied
Signal
101
N.
Industrial
Parkway
New
Century,
KS
66031
Allied
Signal
101
N.
Industrial Parkway
New
Century,
KS
66031
Allied
Signal
101
N.
Industrial Parkway
New
Century,
KS
66031
Allied
Signal
101
N.
Industrial
Parkway
New Century,
KS
66031
Table
7.
CHAPTER
71
-
POWER PLANT
Publica-
Publication
Title
tion
Part
Number
60294-7
Direct
Drive
Engine
Overhaul
Manual
Manufacturer
Textron
Lycoming
LIST
OF
MANUFACTURERS
TECHNICAL
PUBLICATIONS
Item
Cessna
Part
Number
Engine
Manufact-
urer's
Part
N
umber
10540-
AB1A5
Page
4
an
1/2007
i
Q
Cessna
Aircraft
Company
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti
182
MAINTENANCE
MANUAL
Table
8.
CHAPTER
73
-
ENGINE
FUEL
AND
CONTROL
Publica-
tion
Part
Number
Publication
Title
1
5-338D
RSA-5
&
RSA-
10
Fuel
Injection
Systems Operation
&
Service
Manual
15-81
OB
Troubleshooting
Techniques for
the
Precision
Airmotive
RSA
Fuel
Metering
System
15-895G
Index
of
Manuals,
Bulletins,
and
Service
Information
Letters
for
Precision
Airmotive
Fuel
Controls
Manufacturer
Precision
Airmotive
14800
40th
Ave.
NE
Marysville,
WA
98271
Precision
Airmotive
14800
40th
Ave.
NE
Marysville,
WA
98271
Precision
Airmotive
14800
40th
Ave.
NE
Marysville,
WA
98271
Table
9.
CHAPTER
74
-
IGNITION
Publica-
tion
Part
Number
Publication
Title
L-1363C
4300/6300
Series
Magneto
Maintenance
and
Overhaul
Manual
Manufacturer
Slick
Aircraft
Products
530
Blackhawk Park
Ave.
Rockford,
IL
61104
LIST
OF
MANUFACTURERS
TECHNICAL PUBLICATIONS
Page5
©
Cessna
Aircraft
Company
Janl1/2007
Item
Cessna
Part
Number
Fuel
Injection
System
Fuel
Injection
System
Fuel
Injection
System
Manufact-
urer's
Part
Number
RSA-5
RSA-5
RSA-5
Item
Cessna
Part
Number
Magneto
Manufact-
urer's
Part
Number
6351
CESSNA AIRCRAFT
COMPANY
MODEL
182/Ti
82
MAINTENANCE
MANUAL
LIST
OF
CHAPTERS
CHAPTER
Time
Limits/Maintenance
Checks
Dimensions
and
Areas
Lifting and
Shoring
Leveling
and
Weighing
Towing
and Taxiing
Parking
and
Mooring
Placards
and
Markings
Servicing
Standard
Practices
-
Airframe
Air
Conditioning
Auto
Flight
Communications
Electrical
Power
Equipment/Furnishings
Fire
Protection
Flight
Controls
Fuel
Ice
and
Rain
Protection
Indicating/Recording
Systems
Landing Gear
Lights
Navigation
Oxygen
Vacuum
Standard
Practices
-
Structures
Doors
Stabilizers
Windows
Wings
Propellers
Powerplant
Engine
Fuel
and
Control
Ignition
Engine
Controls
Engine
Indicating
Exhaust
Oil
Starting
Turbines
EFFECTIVE
DATE*
Jul
1/2007
Jul
1/2007
Mar
1/2004
Mar
1/2004
Mar
1/2004
Jul
1/2007
Mar
1/2005
Jul 3/2006
Jan
1/2007
Jan
1/2007
Jul
1/2007
Jan
1/2007
Jul 3/2006
Jan
1/2007
Mar 1/2004
Jul
1/2007
Jul
1/2007
Jan
1/2007
Jan 2/2006
Jul
3/2006
Jul 3/2006
Jul
1/2007
Jul 3/2006
Jan 2/2006
Mar
1/2004
Jul
1/2007
Mar
1/2004
Jan
2/2006
Mar
1/2004
Jul
1/2007
Jan
1/2007
Jan
1/2007
Jul 1/2007
Jan
2/2006
Jul 1/2007
Jan
1/2007
Jan
2/2006
Jul
1/2007
Mar 1/2004
FICHE/FRAME
1 B2
1
E14
1
F12
1 G2
1 G9
1
G16
1 H4
1
H10
2
A2
2 D7
2 E7
2 F6
2
G2
2
Ill
2
L2
3
A2
3
Dll
3 F2
3 G2
3 H2
3
Jill
4
A2
4
D16
4 E6
4 F2
4
F12
4 G7
4
G16
4 H7
4 12
4
115
4
L2
5 A2
5
A17
5
B4
5
C2
5
C15
5 D5
5
D12
NOTE
1:
*Represents date
of
page
one
of
each
chapter's
List
of
Effective Pages
which
is
applicable
to
Manual
revision
date.
LIST
OF
CHAPTERS
Page
1
©
Cessna
Aircraft
Company
Jul
1/2007
5
6
7
8
9
10
1
1
1
2
20
21
22
23
24
25
26
27
28
30
31
32
33
34
35
37
51
52
55
56
57
61
71
73
74
76
77
78
79
80
81
CHAPTER
TIME
LIMITS/
MAINTENANCE
CHECKS
CESSNA AIRCRAFT
COMPANY
MODEL
182/Ti
82
MAINTENANCE
MANUAL
LIST
OF
EFFECTIVE
PAGES
CHAPTER-SECTION-SUBJECT
05-Title
05-List
of Effective
Pages
05-Record
of
Temporary
Revisions
05-Table
of
Contents
5-00-00
5-00-10
5-10-00
5-1
0-01
5-11-00
5-12-00
5-12-0
1
5-1
2-02
5-12-03
5-12-04
5-1
2-05
5-12-06
5-12-07
5-1
2-08
5-1
2-09
5-12-10
5-12-11
5-12-13
5-12-14
5-12-15
5-12-16
5-12-17
5-12-18
5-12-19
5-12-20
5-12-2
1
5-1
2-22
5-1
2-23
5-12-24
5-1
2-25
5-12-26
5-50-00
Q
Cessna
Aircraft Company
05
-
LIST
OF
EFFECTIVE
PAGES
Page
1
of
1
Jul
1/2007
PAGE
Pages
1-2
Page
1
Pages
1-2
Pages
1-17
Pages
1-3
Pages
1-2
Pages
1-7
Pages
1-6
Pages
1-7
Pages
1-5
Page
1
Page
1
Page
1
Page
1
Page
1
Page
1
Page
1
Page
1
Page
1
Page
1
Page
1
Page
1
Page
1
Page
1
Page
1
Page
1
Page
1
Page
1
Page
1
Page
1
Page
1
Pages
1-5
DATE
Jul
1/2007
Mar
1/2004
Jul
3/2006
Jul
3/2006
Jul
1/2007
Jul
1/2007
Jul
3/2006
Jul
3/2006
Jul
3/2006
Jul 3/2006
Jul 3/2006
April
1/2002
Jul
3/2006
April 1/2002
Jul
3/2006
Jul
3/2006
Jul
3/2006
April
1/2002
Jul 3/2006
Jul
3/2006
Jul
3/2006
Jul
3/2006
Jul
3/2006
Jul
3/2006
Jul
3/2006
Jul
3/2006
Jul
3/2006
Jul
3/2006
Jul
3/2006
Jul
3/2006
Jul
3/2006
Jan
2/2006
Temporary
Revision
Number
RECORD
OF
TEMPORARY
REVISIONS
Page
Number
Issue
Date
By
Date
Removed
By
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti
82
MAINTENANCE
MANUAL
CONTENTS
TIME
LIMITS/MAINTENANCE
CHECKS
......................
Scope....................................
Inspection
Requirements...........................
Inspection
Program
Selection.........................
Description
.................................
General Inspection
Terms and
Guidelines
...................
AIRWORTHINESS
LIMITATIONS
-
FAA
APPROVED
DATA..............
Scope....................................
Airworthiness
Limitations...........................
INSPECTION
TIME
INTERVALS..........................
General...................................
Procedure..................................
Inspection
Terms
and
Guidelines
.......................
Chart Legend
................................
INSPECTION
TIME
LIMITS
............................
Inspection
Items...............................
COMPONENT
TIME
LIMITS............................
General...................................
Cessna-Supplied Replacement
Time
Limits
..................
Supplier-Supplied Replacement
Time Limits
..................
PROGRESSIVE
CARE
PROGRAM
........................
General...................................
Procedure..................................
Inspection
Terms and
Guidelines
.......................
INSPECTION
OPERATION
1 ...........................
Description
.................................
General
Inspection
Criteria
..........................
INSPECTION
OPERATION
2 ...........................
Description
.................................
General
Inspection Criteria
..........................
INSPECTION
OPERATION
3 ...........................
Description
.................................
General Inspection
Criteria
..........................
INSPECTION OPERATION
4 ...........................
Description
.................................
General Inspection
Criteria
..........................
INSPECTION OPERATION
S ...........................
Description
.................................
General
Inspection
Criteria
..........................
PROGRESSIVE
CARE
..............................
Operation
6 .................................
INSPECTION
OPERATION
7
...........................
Description
.................................
General
Inspection Criteria
..........................
PROGRESSIVE
CARE
..............................
Operation
8 .................................
5-00-00
Page
1
5-00-00
Page
1
5-00-00
Page
1
5-00-00
Page
1
5-00-00
Page
1
5-00-00
Page
2
5-00-10
Page
1
5-00-10
Page
1
5-00-10
Page
1
5-10-00
Page
1
5-10-00
Page
1
5-10-00
Page
1
5-10-00
Page
1
5-1
0-00
Page
1
5-1
0-01
Pagel1
5-1
0-01
Page
1
5-11
-00
Page
1
5-11
-00
Page
1
5-11
-00
Page
1
5-11
-00
Page
2
5-12-00
Page
1
5-12-00
Page
1
5-12-00
Page
2
5-12-00
Page
2
5-12-01
Page
1
5-12-01
Page
1
5-12-01
Page
1
5-12-02
Page
1
5-12-02
Page
1
5-12-02
Page
1
5-12-03
Page
1
5-12-03
Page
1
5-12-03
Page
1
5-12-04
Page
1
5-12-04
Page
1
5-12-04
Page
1
5-12-05
Page
1
5-12-05
Page
1
5-12-05
Page
1
5-12-06
Page
1
5-12-06
Page
1
5-12-07
Page
1
5-12-07
Page
1
5-1
2-07
Page
1
5-12-08
Page
1
5-12-08
Page
1
05
-
CONTENTS
Page
1
of
3
Jul
1/2007
©
Cessna
Aircraft
Company
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION
OPERATION
9 ...........................
Description
............
General Inspection
Criteria
..........................
INSPECTION
OPERATION
10...........................
Description
.................................
General Inspection
Criteria
..........................
INSPECTION OPERATION
11...........................
Description
.................................
General Inspection
Criteria
..........................
PROGRESSIVE
CARE
..............................
Operation
13
................................
INSPECTION OPERATION
14...........................
Description
.................................
General Inspection
Criteria
..........................
INSPECTION
OPERATION
15...........................
Description
.................................
General Inspection
Criteria
..........................
INSPECTION OPERATION
16...........................
Description
.................................
General Inspection
Criteria
..........................
INSPECTION
OPERATION
17...........................
Description
.................................
General Inspection
Criteria
..........................
INSPECTION OPERATION
18...........................
Description
.................................
General Inspection
Criteria
..........................
INSPECTION OPERATION
19...........................
Description
.................................
General Inspection
Criteria
..........................
INSPECTION
OPERATION
20...........................
Description
.................................
General Inspection
Criteria
..........................
INSPECTION OPERATION
21...........................
Description
.................................
General Inspection
Criteria
..........................
INSPECTION OPERATION
22
...........................
Description
.................................
General
Inspection
Criteria
..........................
INSPECTION OPERATION
23...........................
Description
.................................
General Inspection
Criteria
..........................
INSPECTION OPERATION
24...........................
Description
.................................
General Inspection
Criteria
..........................
INSPECTION
OPERATION
25...........................
Description
.................................
General Inspection
Criteria
..........................
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05
-
CONTENTS
Page
2
of
3
Jul
1/2007
©
Cessna
Aircraft
Company
CESSNA AIRCRAFT
COMPANY
MODEL
182/Ti
82
MAINTENANCE
MANUAL
INSPECTION
OPERATION
26...........................
Description
.................................
General
Inspection Criteria
..........................
UNSCHEDULED
MAINTENANCE
CHECKS
....................
General...................................
Unscheduled
Maintenance
Checks
Defined
and
Areas
of
Inspection
.......
5-12-26
Page
1
5-12-26
Page
1
5-12-26
Page
1
5-50-00
Page
1
5-50-00
Page
1
5-50-00
Page
1
05
-
CONTENTS
Page
3
of
3
Jul
1/2007
©
Cessna
Aircraft Company
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti
82
MAINTENANCE
MANUAL
TIME
LIMITS/MAINTENANCE CHECKS
1.Scope
A.
This
chapter
provides
the
time limits
and
maintenance
checks
for
the
Model
182
airplanes.
It is
divided
into
several
sections,
each
with
a
specific
purpose
toward
providing
information
necessary
to
establish
inspection
criteria.
2.
Inspection Requirements
A.
As
required
by
U.S.
Federal
Aviation
Regulations,
all
civil
aircraft
of
U.S.
registry
must
undergo
a
complete
inspection
(annual)
each
twelve
calendar
months.
In
addition
to
the
required
annual
inspection, aircraft
operated
commercially
(for hire)
must have
a
complete inspection every
100
hours
of
operation.
B.
Compliance
with the
regulations
is
accomplished
using
one
of
three methods:
(1)
Traditional
(Annual/i100
Hour)
inspection
program
which
utilizes
14
CFR
43,
Appendix
D
(scope
and
detail)
to
inspect
the
airplane.
In
addition,
Cessna recommends
certain
components
or
items
be
inspected
at
50 hour
intervals. These
inspection
items
are
listed
in
Inspection
Time
Intervals, Section
5-10-01.
(2)
Progressive
Care
inspection
program
which allows
the
work
load
to be
divided
into
smaller
operations
that
can
be
accomplished
in
a
shorter
time
period.
This
method
is
detailed
in
Progressive
Care
Program,
Section
5-12-00.
(3)
PhaseCard
inspection
program
which
is
geared toward
high-utilization
flight
operations
(approximately
600
flight
hours per
year).
This
system
utilizes
50-hour
intervals
(Phase
1
and
Phase
2)
to
inspect
high-usage systems
and
components.
At
12
months or
600
flight
hours,
whichever
occurs
first,
the
airplane undergoes
a
complete
(Phase
3)
inspection.
PhaseCard
Inspection
programs can
be
ordered through
Propeller Aircraft
Product
Support.
P.O.
Box
7706,
Wichita,
KS
67277,
Phone
(316)
517-5800,
Fax
(316)
942-9006.
3.
Inspection
Program
Selection
A.
The
selection
of an
inspection
program
(Annual,
Progressive
Care
or
PhaseCard)
is
primarily
based
on
owner/operator
preferences,
whether
an
airplane
is
flown
for
hire,
and
numbers
of
hours flown
during the
year.
4.
Description
A.
Listed
below
is a
brief
description
and
intended
purpose
of
each
section
of
this
chapter.
For
detailed
information
related
to
each
particular
inspection
program, refer
to
the specific section within this
chapter.
B.
Section
5-00-00,
Time
Limits/Maintenance
Checks
-
General.
This
section
provides
a
general
overview
of
inspection
requirements.
C.
Section
5-1 0-01,
Inspection
Time
Intervals.
The
primary
purpose
of
this
section
is
to
provide
a
central
location
for
inspection
time
intervals.
This
section
may
also
be
utilized
in
conjunction
with
14
CFR
Part 43
to
provide greater detail
on
inspection
criteria
when
performing
Annual/i
00
Hour
inspections.
D.
Section
5-11
-00,
Component
Time Limits.
This
section
provides
a
list
of
components
which
are life-
or
time-limited.
Although
these
components
are
not
listed
in
any
of
Cessna's
inspection
programs,
they
must
be
considered
and
included
in
whatever
inspection
program
is
used.
E.
Section
5-12-00, Progressive
Care
Program.
This
section
outlines
the
progressive
inspection
program.
The program
is
divided
into
four
primary
operations
which
cover
all
inspection
requirements
up
through
the
200-hour
interval inspection
items.
The
remaining
operations
cover inspections
which
are
at
intervals
other
than
what
the
four
primary
operations
cover. Refer
to
the
Progressive
Care
Program
section
for
a
more
detailed
description
of
the
Progressive
Care
Program.
5-00-00
Page
1
C
Cessna Aircraft Company
Jul
1/2007
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti
82
MAINTENANCE
MANUAL
5.
General
Inspection
Terms and
Guidelines
NOTE:
When
inspections
criteria
are
required,
these
criteria
are
spelled
out
in
the
text.
If
more
detailed
instructions
are
required
for
an
inspection,
these instructions
will
refer
to
the
appropriate
locations (supplier
publications
and/or
the
maintenance
manual).
A.
Definitions
of
terms
used
through the
inspection
programs
are
as
follows:
(1)
ON
CONDITION
is
defined
as
the
necessary inspections
and/or
checks
to
determine
that
a
malfunction
or
failure
of
the
component
will
not
occur
prior
to
the
next
scheduled inspection.
(2)
CONDITION
is
defined
as
inspection for
(but not
limited
to)
cleanliness,
cracks,
deformation,
corrosion,
wear,
and
loose
or
missing
fasteners.
(3)
SECURITY
is
defined
as
an
inspection
for
looseness
of
fasteners
and
fastener
securing
devices
such
as
safety
wire,
cotter
pins
and
self-locking
nuts.
B.
During
Inspections,
use
the
following
general guidelines:
(1)
MOVABLE PARTS:
Inspect
for
lubrication, servicing,
security
of
attachment,
binding,
excessive
wear,
safetying, proper operation,
proper
adjustment, correct
travel,
cracked fittings,
security
of
hinges,
defective
bearings,
cleanliness,
corrosion,
deformation, sealing,
and
tension.
(2)
FLUID
LINES
AND
HOSES:
Inspect
for
leaks,
cracks,
bulging,
collapsed,
twisted,
dents,
kinks,
chafing, proper
radius,
security, discoloration,
bleaching,
deterioration,
and
proper
routing;
rubber
hoses
for
hardness
or
flexibility
and
metal
lines
for
corrosion.
(3)
METAL PARTS:
Inspect for
security
of
attachment, cracks,
metal
distortion,
and
heat
deterioration.
(4)
WIRING:
Inspect
for
security, chafing,
burning, arcing,
defective insulation,
loose
or
broken
terminals,
heat
deterioration,
and
corroded
terminals.
CAUTION:
Torque
values
listed
in
this
manual
are
not to
be
used
for checking
tightness
of
installed
parts
during
service.
(5)
STRUCTURAL
FASTENERS:
Inspect for
correct
torque
in
accordance
with
applicable torque
values.
Refer
to
Chapter
20,
Torque
Data
-
Maintenance
Practices, during
installation
or
when
visual
inspection
indicates
the
need
for
a
torque
check.
(6)
FILTERS,
SCREENS,
AND
FLUIDS:
Inspect
for
cleanliness
and
the
need
for
replacement
at
specified
intervals.
(7) A
system
check
(operation
or
function) that
requires
electrical
power,
must
be
performed
using
28.5
Volts,
+0.25 or
-1
.00
Volts,
bus
voltage.
This
will
make
sure
that
all
components
are
I ~ ~~~operating
at
their
operational voltage.
C.
Airplane
file.
(1)
Miscellaneous
data,
information,
and
licenses
are
a
part
of
the
airplane
file.
Check
that
the
following documents
are
up-to-date
and
in
accordance
with
current
Federal
Aviation
Regulations.
Most
of
the
items
listed
are
required
by
the
Federal
Aviation
Regulations.
Since the
regulations
of
other
nations
may
require
other
documents
and
data,
owners
of
airplanes
operated
outside
the United
States
should
check
with
their
own
aviation
officials
to
determine
their
individual
requirements.
(a)
To
be
displayed
in
the
airplane
at
all
times:
1
Standard
Airworthiness
Certificate
(FAA
Form
8100-2).
2
Aircraft
Registration
Certificate
(FAA
Form
8050-3).
3
Aircraft Radio
Station License
(Federal
Communication Commission
Form
556
if
transmitter
is
installed).
(b)
To
be
carried
in
the
airplane
at
all
times:
1
Weight
and
Balance
Data
Sheets
and
associated
papers
(all
copies
of
the Repair
and
Alteration
Form,
FAA
Form
337, are
applicable).
2
Equipment
List.
3
Pilot's
Operating
Handbook
and
FAA
Approved
Airplane Flight Manual.
(c)
To
be
made
available
upon request:
1
Airplane,
Engine and
Propeller Logbooks.
5-00-00
Page
2
©
Cessna
Aircraft
Company
Jul
1/2007
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
AIRWORTHINESS
LIMITATIONS
-
FAA
APPROVED
DATA
1.
Scope
A.
The
Airworthiness
Limitations section
is
FAA
approved
and
specifies
maintenance required
under
Parts
43.16
and
91.403
of the Federal
Aviation
Regulations unless
an
alternative
program
has been
FAA
approved.
2.
Airworthiness
Limitations
A.
There
are
no
airworthiness
limitations
associated
with
this
airplane.
5-00-10
Page
1
Mar
1/2004
©
Cessna
Aircraft
Company
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION
TIME
INTERVALS
1.
General
A.
The primary
purpose
of
this
section
is
to
provide
for inspection
time
intervals.
The section
5-10-01
may
be
utilized
in
conjunction
with
14
CFR Part
43
inspection
scope
and
detail,
but
is
not
intended
to
be
utilized
as
the
primary
checklist
for
inspection
of
the
airplane.
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
powerplant mechanics
in
performance
of
their
duties.
As
the
one
primarily responsible for
the
airworthiness
of
the
airplane,
the
owner
or
operator
should
select
only
qualified personnel
to
maintain
the
airplane.
2.
Procedure
A.
A
complete
airplane inspection
includes
all
inspection
items
as
required
by
14
CFR
43,
Appendix
D,
Scope
and
Detail
of
annual/100
hour
inspections.
The
chart
provided
in
this
section
should
be
used
to
augment
the
inspection.
B.
The
Component
Time
Limits
section
(5-11-00)
should
be
checked
in
conjunction
with this
inspection
to
ensure
proper
overhaul
and replacement
requirements
are
accomplished
at
the specified
times.
C.
The
intervals
shown are recommended
intervals
at
which
items
are
to
be
inspected
based
on
normal
usage
under
average environmental conditions. Airplanes
operated
in
extremely
humid
areas
(tropics), or
in
exceptionally
cold,
damp
climates,
etc., may
need
more
frequent inspections
for
wear,
corrosion,
and
lubrication.
Under
these
adverse
conditions,
perform
periodic
inspections
in
compliance
with
this chart
at
more
frequent
intervals
until
the
operator
can
set
his
own
inspection
periods
based
on
field experience.
(1)
The
14
CFR
Part
91
operator's inspection
intervals
shall
not
deviate
from
the
inspection
time
limits
shown
in
this
manual except
as
provided
below: (Refer
to
14
CFR
91.409)
(a)
The
aircraft
can
only
exceed
its
inspection
point
up
to
ten
hours
if
the
aircraft
is
enroute
to
a
facility
to
have the
inspection completed.
(b) In
the
event
of
late
compliance
of
any
operation
scheduled,
the
next
operation
in
sequence
retains
a
due
point from
the
time
the
late
operation
was
originally
scheduled
(reschedule
if
late).
(c) In
the
event
of
early
compliance
of
any
operation scheduled, that
occurs
10
hours
or
less
ahead
of
schedule,
the
next
phase due point
may
remain
where
originally
set.
(d) In
the
event
of
early compliance
on
any
operation
scheduled,
that
occurs
more
than
10
hours
ahead
of
schedule,
the
next
phase due
point
must
be
rescheduled
to
establish
a
new
due
point
from
the
time
of
early accomplishment.
3.
Inspection
Terms and
Guidelines
A.
For
inspection
terms
and
guidelines,
refer
to
Chapter
5,
Time
Limits/Maintenance
Checks
-
General.
4.
Chart
Legend
A.
Each
page
of
the
inspection
listed
in
Inspection
Time Limits,
section
5-10-01
contains
the
following
five
columns:
(1)
REVISION
STATUS
-
This
column
provides
the
date
that
a
given
item
was added,
deleted
or
revised.
A
blank
entry
in
this
column
indicates
no
change
since the original
issue
of
this
manual.
(2)
INSPECTION
ITEM
CODE
NUMBER
-
This
column
lists
a
six-digit number
permanently
assigned
to
a
scheduled
maintenance
item.
A
given
inspection
item
code
number
will
never
change
and
will
not
be
reused
in
the
event
the
scheduled
maintenance
item is
deleted.
(3)
REQUIREMENTS
-
This
column
provides
a
short
description
of the
inspection and/or
servicing
procedures.
Where
a
more
detailed
description
of
the procedure
is
required,
a
reference
will
be
made
to
either another selection
located
within
the maintenance
manual or
a
specific
reference
to
a
supplier
publication.
5-10-00
Page
1
©
Cessna
Aircraft Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
(4)
INTERVAL
-
This
column
lists
the frequency
of
inspection
in
alphabetic
coded
form.
The
legend
for
the
alpha
code
is
listed
below.
(5)
OPERATION
-
The
Progressive
Care
inspection
program
allows the work
load
to
be
divided
into
smaller
operations
that
can
be
accomplished
in
a
shorter
time
period.
This
program
is
detailed
in
section 5-12-00,
which
is
the
Progressive
Care
Program.
(6)
ZONE
-
This column locates
the
components
within
a
specific zone.
For
a
breakdown
of
how
the
airplane
is
zoned,
refer
to
Chapter
6,
Airplane
Zoning
-
Description
and
Operation.
INTERVAL
A.
B.
C.
D.
E.
F.
G.
H.
1.
J.
K.
L.
M.
N.
O.
P.
Q.
R.
S.
T.
U.
V.
W.
X.
Y.
Z.
OPERATION
1, 2, 3,
4
1, 2, 3,
4
1, 2, 3,
4
5
7
9
10
11
14
15
16
17
18
19
20
21
22
23
24
25
26
INTERVAL
Every
50
hours.
Every
100
hours.
Every
200
hours.
Every
400
hours
or
1
year, whichever occurs
first.
(Not
used)
Every
600
hours
or
1
year, whichever occurs
first.
(Not
used)
Every
500
hours.
Every
1000
hours.
Every
2
years.
(Not
used)
(Not
used)
Every
2
years,
or
any
time components
are
added
or
removed
which
have the potential
to
affect
the
magnetic
accuracy and/or variation
of
the
compass
calibration,
or
any
time
the
accuracy
of
the
compass
is
in
question.
Every
2000
hours.
Every
1000
hours
or
1
year, whichever
occurs
first.
Every
12
calendar
months.
Every
6
years.
Every
12
years.
Every
1
year.
Every
3
years.
(Not
used)
Beginning
five
years
from
the
date
of
the
manufacture, you
must
make
sure
of
the
serviceability
of
the
components
every
twelve months.
Refer
to
Airborne Air
and
Fuel
Products
Service Letter
Number
39A
or
latest
revision.
Every
100
hours
or
every
one
year,
whichever
occurs
first.
Every
100
hours,
every
annual
inspection,
every overhaul,
and
any
time
fuel
lines
or
clamps
are
serviced,
removed
or
replaced.
First
600
hours and
as
defined
by
the
manufacturer thereafter.
Every
1000
hours or
3
years,
whichever occurs
first.
5-10-00
Page
2
©
Cessna
Aircraft
Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION
TIME
LIMITS
1.
Inspection
Items
REVISION
ITEM
TASK INTERVAL OPERATION
ZONE
STATUS
CODE
NUMBER
Added
110000
Interior Placards,
Exterior
Placards,
B
1,2,3,4
ALL
Mar
1/05
Decals,
Markings
and
Identification
Plates
-
Inspect
for
security
of
installation
and
legibility.
Refer
to
Chapter
11,
Placards
and
Markings
-
Inspection/Check.
Deleted
112101
Mar
1/04
Deleted
113101
Mar
1/04
212001
Ventilation
System
-
Inspect
clamps,
D 5
211
hoses,
and
valves
for
condition
and
security.
Revised
212002
Primary
Flight
Display
(PFD) Fan, W
23
220,
225
Mar
1/05
Multi-Function
Display
(MFD)
Fan,
Deck
Skin
Fan,
and
Remote
Avionics
Cooling
Fan
-
Operational
Check.
Refer
to
Chatper
21,
Avionics
Cooling
-
Maintenance
Practices.
214001
Cold
and
Hot
Air
Hoses
-
Check
B 2, 4
120
condition,
routing,
and
security.
Revised
214002
Heater Components,
Inlets,
and
B
1,3
211
Dec
1/98
Outlets
-
Inspect
all
lines,
ducts,
clamps,
seals,
and
gaskets
for
condition,
restriction,
and
security.
Revised
214003
Cabin
Heat
and
Ventilation
Controls
-
B 1
211
Jun
1/00
Check
freedom
of
movement
through
full
travel. Check
friction
locks
for
proper
operation.
221001
Autopilot
Rigging-
Refer
to
Autopilot-
F 7
610
Maintenance
Practices.
Added
221002
Autopilot
Servo Capstan
Assemblies.
O
16
610
Dec
1/98
Check
slip-clutch
torque
settings.
Refer
to
Autopilot
-
Maintenance
Practices.
Added
221003
Autopilot
Servo
Actuators. Inspect
for
O
16
610
Dec
1/98
evidence
of
corrosion
and
or
buildup
of
dirt
or
other
particulate
matter
which
may
interfere
with
servo
operation.
Refer
to
Autopilot
-
Maintenance
Practices.
5-10-01
Page
1
©
Cessna Aircraft
Company
Jul 3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE MANUAL
REVISION
ITEM
TASK
INTERVAL OPERATION
ZONE
STATUS
CODE
NUMBER
231001
Communication
Antennas and
Cables
C 3
210
-
Inspect
for
security
of
attachment,
connection,
and
condition.
235001
Microphones,
Headsets,
and Jacks
-
C 1
211
Inspect for cleanliness,
security,
and
evidence
of
damage.
Added 235002 Microphone
Push-To-Talk
Switch
B 1, 3
222,
223
4/03
-
Clean the
pilot's
and
copilot's
microphone
switches.
Refer
to
Chapter
23,
Communication
Maintenance
Practices.
242001
Alternator,
Mounting
Bracket,
and
A
1,2,
3,
4
120
Electrical Connections
-
Check
condition
and
security.
Check
alternator
belts
for
condition
and
proper adjustment. Check
belt
tension.
Revised
243001
Main
Battery
-
Examine
the
general
B
2,
4
310
Jun
3/06 condition
and security.
Complete
a
check
of the
level
of
electrolyte.
Refer
to
Chapter
12,
Battery
-
Servicing.
Revised
243002
Main
Battery
Box and
Cables
-
Clean
B 2,
4
310
Jun
3/06
and
remove
any
corrosion.
Examine
the
cables
for
routing,
support,
and
security
of
the
connections.
243003 General Airplane
and
System
Wiring
C 1
210
-
Inspect
for
proper
routing,
chafing,
broken
or
loose
terminals,
general
condition,
broken
or
inadequate
clamps,
and
sharp
bends
in
wiring.
243004
External Power
Receptacle
and
C 2
120
Power
Cables
-
Inspect
for
condition
and
security.
Added 243005 Standby
Battery
-
Complete
the
S
20
220
Mar
1/05
Standby
Battery
Capacity
Test.
Refer
to
Chapter
24,
Standby
Battery
-
Maintenance
Practices.
246001
Switch
and
Circuit
Breaker
Panel,
C 1
222
Terminal
Blocks,
and
Junction
Boxes
-
Inspect
wiring
and
terminals
for
condition
and
security.
Revised
246002 Power
Junction
Box
-
Check
B 1, 3
222
Jun
1/00
operation
and
condition.
Check
availability
and
condition
of
spare
fuse
(if
applicable).
5-10-01
Page
2
Cessna
Aircraft
Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
REVISION
ITEM
TASK
INTERVAL
OPERATION ZONE
STATUS CODE
NUMBER
Added
246003
Alternator
Control
Unit
-
Complete
J
11
222
Jul 3/06
the
Over-voltage
Protection
Circuit
Test.
Refer
to
Chapter
24,
Alternator
Control
Unit.
Revised
246101
Essential
and
Crossfeed
Bus
Diodes
-
S
20
224
Mar
1/05
Check
for
proper
operation.
Complete
the
Essential
and
Crossfeed
Bus
Diode
Inspection.
Refer
to
Chapter
24,
Essential
and
Crossfeed
Bus
Diodes
-
Maintenance
Practices.
Revised
251001
Seats
-
Examine
the
seats
to
make
B
1,
3
211
Jul 3/06
sure
they
are
serviceable
and
installed
correctly.
Make sure
the seat
stops
and
adjustment
mechanism
operate
correctly.
Examine the
seat
recline
control
and
attaching
hardware
to make sure
the hardware
and
lock are
not
damaged
and
are
correctly
installed.
Lubricate
the
threads
of
the
Seat Crank Handle
Assembly
with
MIL-PRF-81322
general
purpose
grease.
251002
Seat
Tracks
and Stops
-
Inspect
seat
B
2,
4
230
tracks
for
condition
and
security
of
installation.
Check
seat
track
stops
for
damage
and
correct location.
Inspect
seat
rails
for
cracks.
251101
Restraint
System, front
and
rear
-
B
1,3
211
Check
belts
for
thinning, fraying,
cutting,
broken stitches, or
ultra-violet
deterioration.
Check
system
hardware
for
security
of
installation.
Added
251102
AMSAFE
Aviation
Inflatable
Restraint
S
20
211
Mar
1/05
(AAIR)
-
Examine
the
restraint
for
dirt,
frayed
edges,
unserviceable
stitching,
loose
connections,
and
other
wear.
252201
Upholstery, Headliner,
Trim,
and
D 5
211
Carpeting
-
Check
condition
and
security.
Revised
256001
Emergency Locator Transmitter
-
B
1,
3 310
Jan 2/05 Inspect for
security
of
attachment
and
check
operation
by
verifying
transmitter
output.
Check
cumulative
time
and
useful
life
of
batteries
in
accordance
with
14
CFR Part
91.207.
262001
Portable
Hand
Fire
Extinguisher
-
B
1,
3
230
Inspect for proper
operating
pressure,
condition, security
of
installation,
and
servicing
date.
5-10-01
Page
3
©
Cessna
Aircraft
Companv
Jul 3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
REVISION
ITEM
TASK
INTERVAL
OPERATION
ZONE
STATUS CODE
NUMBER
Added
262002
Cockpit
Mounted
Halon Type
Fire
P
17
211
Dec 1/98
Extinguisher
-
Weigh
bottle.
Bottle
must be
reserviced
by
qualified
individual
if
more
than
2
ounces
is
lost.
Added
262003
Cockpit
Mounted
Halon
Type
Fire
R
19
211
Dec
1/98
Extinguishers
-
Perform
hydrostatic
test.
The
hydrostatic
test
shall
be
at
twelve-year
intervals
based
on
initial
servicing
or
date
of
last
hydrostatic
test.
Added 262004
Cockpit
Mounted
Halon
Type
Fire
Q
18
211
Dec
1/98
Extinguishers
-
Empty,
inspect
for
damage, and
recharge.
Revised
271001
Aileron
Controls
-
Check
freedom
B
1,3
120,
520,
Dec
1/98
of
movement
and proper
operation
620
through full
travel.
271002
Ailerons
and Cables
-
Check
C 3
120,
520,
operation
and
security
of
stops.
620
Check
cables
for tension,
routing,
fraying,
corrosion,
and
turnbuckle
safety.
Check
travel
if
cable
tension
requires
adjustment
or
if
stops
are
damaged.
Check
fairleads
and
rub
strips
for
condition.
271003 Aileron
Structure,
Control
Rods,
B
1,3
520,
620
Hinges,
Balance
Weights,
Bellcranks,
Linkage,
Bolts,
Pulleys,
and
Pulley
Brackets
-
Check condition,
operation,
and
security
of
attachment.
271004 Ailerons
and
Hinges
-
Check
B 1, 3
520,
620
condition,
security,
and
operation
271005
Control
Wheel
Lock
-
Check
general
C 1
222
condition
and operation.
Revised 271006
Control
Linkage
-
Inspect
pulleys,
C 1
222,
223
Dec 1/98
cables,
bearings,
and
turnbuckles
for
condition
and
security.
272001
Rudder
-
Check
internal
surfaces
for
C
3
340
corrosion,
condition
of
fasteners,
and
balance
weight
attachment.
5-1
0-01
Page
4
Jul 3/2006
Cessna
Aircraft
Company
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
REVISION
ITEM
TASK
INTERVAL OPERATION
ZONE
STATUS
CODE
NUMBER
Revised 272002
Rudder
-
Inspect
the
rudder
skins
for
B 1, 3
340
Jun
1/00
cracks
and loose rivets,
rudder hinges
for
condition, cracks
and
security;
hinge bolts, hinge
bearings,
hinge
attach fittings,
and
bonding
jumper
for
evidence
of
damage
and
wear,
failed
fasteners,
and
security.
Inspect
balance weight
for
looseness
and
the
supporting
structure
for
damage.
Revised 272003
Rudder, Tips,
Hinges,
Stops,
Clips
B 1, 3
340
Dec
1/98
and
Cable
Attachment
-
Check
condition,
security, and
operation.
272004
Rudder
Pedals
and
Linkage
-
Check
C 1
230
for general
condition,
proper
rigging,
and
operation.
Check for
security
of
attachment.
Added
272005
Rudder
Control
-
Check
freedom
B 1, 3
340
Dec
1/98
of
movement
and
proper
operation
through
full
travel. Check
rudder
stops
for
damage
and
security.
Revised
273001
Elevator
Control
-
Check
freedom
B
1,3
222,
223
Dec
1/98
of
movement
and
proper
operation
through
full
travel.
Revised 273002
Elevator
Control
System
-
Inspect
B 1, 3
222,
223
Jun
1/00
pulleys, cables,
sprockets,
bearings,
chains,
and
turnbuckles
for
condition,
security,
and
operation.
Check
cables
for
tension,
routing,
fraying,
corrosion,
and
turnbuckle
safety
Revised
273003
Elevator,
Hinges,
Stops,
and
Cable
B 1, 3
320, 330
Dec
1/98
Attachment
-
Check
condition,
security,
and
operation.
Added
273004
Elevator
Downspring
-
Check
B
1,3
310
Dec 1/98
structure,
bolts,
linkage,
bell
crank,
and
push-pull
tube for
condition,
operation,
and
security.
Check cables
for tension,
routing,
fraying,
corrosion,
and
turnbuckle
safety.
Check
travels
if
cables
require
tension adjustment
or
if
stops
are
damaged.
273101
ElevatorTrim System -
Check cables,
B 1, 3
224,
240,
push-pull
rods,
bellcranks, pulleys,
310
turnbuckles, fairleads,
rub
strips,
etc.
for
proper
routing,
condition,
and
security.
5-10-01
Page
5
©
Cessna Aircraft Company
Jul
3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
REVISION
ITEM
TASK
INTERVAL
OPERATION ZONE
STATUS
CODE
NUMBER
Revised
273102 Elevator
Trim
Control
and
Indicator
C 1
224,
240,
Jun
1/00
-
Check
freedom
of
movement
and
310
proper operation
through
full
travel.
Check
pulleys,
cables,
sprockets,
bearings, chains,
and
turnbuckles
for condition
and
security.
Check
electric
trim
controls
for
operation
as
applicable.
Check
cables
for
tension,
routing, fraying,
corrosion,
and
turnbuckle
safety
273103
ElevatorTrimTaband
Hinges-Check
B 1, 3
224
condition,
security,
and
operation.
Revised 273104 Elevator
Trim
Tab
Actuator
-
Examine
B 1,
3
320
Jul
3/06
the
free
play
limits. Refer
to
Chapter
27,
Elevator
Trim
Control
-
Maintenance
Practices,
Trim
Tab
Free
Play
Inspection.
If
the free
play
is
more
than
the permitted
limits,
lubricate
the
actuator
and
examine
the
free
play
limits
again.
If
the
free
play
is
still
more
than
the permitted
limits,
replace the
actuator.
Deleted
273105
Dec
1/98
273106
Elevator
Trim
Tab
Stop
Blocks
-
C
1
240
Inspect
for damage
and
security.
Added
273107 Elevator
Trim
Tab
Actuator
-
Remove,
Z
26
320
Jul
3/06
clean,
examine,
and
lubricate
the
actuator.
Refer
to
Chapter
27,
Elevator
Trim
Control
-
Maintenance
Practices.
Revised
275001
Flaps
-
Check
tracks,
rollers,
B
1,3
510,
610
Dec
1/98
and
control
rods
for
security
of
attachment. Check
rod
end
bearings
for
corrosion.
Check
operation.
275002
Wing
Flap
Control
-
Check
operation
C
1
221
through
full
travel
and
observe
Flap
Position indicator
for
proper
indication.
275003
Flap
Structure,
Linkage,
Bellcranks,
C 3
510,
610
Pulleys,
and
Pulley
Brackets
-
Check
for condition,
operation
and
security.
275004
Flaps
and
Cables
-
Check
cables
C 3
510,
610
for
proper tension,
routing,
fraying,
corrosion,
and
turnbuckle
safety.
Check
travel
if
cable
tension
requires
adjustment.
5-10-01
Page
6
C
Cessna
Aircraft
Comoanv
Jul 3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
REVISION
ITEM
TASK
INTERVAL
OPERATION
ZONE
STATUS
CODE
NUMBER
Revised
275005
Flap
Motor,
Actuator,
and
Limit
C 3
610
Dec 1/98
Switches
-
Check
wiring
and
terminals
for
condition
and
security.
Check
actuator for
condition
and security.
Revised 275006
Flap
Actuator
Threads
-
Clean
and
B 1, 3
610
Dec 1/98
lubricate.
Refer
to
Chapter
12-21-03.
282001
Fuel
System
-
Inspect plumbing
B
1,3
510,
610
and
components
for
mounting
and
security.
Revised 282002
Fuel Tank
Vent
Lines
and
Vent
Valves
B
1,3
510,
610
Dec
1/98
-
Check
vents for
obstruction
and
proper
positioning.
Check
valves
for
operation.
Revised
282003
Fuel
Selector
Valve
-
Check
controls
B 1, 3
224
Jun
1/00
for
detent
in
each
position,
security
of
attachment,
and
for
proper
placarding.
Revised
282004
Integral
Fuel Bays
-
Check
for
B 1,
3
510,
610
Dec 1/98
evidence
of
leakage
and
condition
of
fuel
caps,
adapters,
and
placards.
Using
quick
drains, ensure
no
contamination
exists.
Check quick
drains
for
proper
shut
off.
Deleted
282005
Aug
4/03
282006
Fuel
Selector
-
Using
quick
drain,
B
1,3
224
ensure
no
contamination
exists.
282007
Fuel
Strainer,
Drain
Valve,
and
B 1, 3
510,
610
Controls
-
Check
freedom
of
movement,
security,
and
proper
operation.
Disassemble, flush,
and
clean screen
and
bowl.
Revised
282008
Fuel
Quantity
Indicators
-
Examine
for
F 7
220
Mar
1/05
damage
and
security
of
installation.
Complete
a
fuel
quantity calibration
check.
Refer
to
Chapter
28,
Fuel
Storage
and
Distribution
-
Maintenance
Practices.
5-10-01
Page
7
©
Cessna
Aircraft
Company
Jul 3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
REVISION
ITEM
TASK
INTERVAL OPERATION
ZONE
STATUS
CODE
NUMBER
Revised 282009
Integral
Fuel Bays
-
Drain
the
I
10
510,
610
Jan 2/06
fuel
(Refer
to Chapter
12,
Fuel
-
Servicing)
and purge
tanks
(Refer
to
the
Single
Engine
Structural
Repair
Manual,
1996
and On).
Complete
an
inspection
of
the
tank
interior
and
outlet screens
and
remove
any
foreign
object
debris. Complete
an
inspection
of
the
tank
interior
surfaces
for
sealant
deterioration
and
corrosion
(especially
in
the
sump
areas).
Revised
282010
Auxiliary
(Electric)
Fuel
Pump
-
B 2, 4
120
Jun
1/00
Check pump
and
fittings for
condition,
operation,
security.
311001
Instruments -
Check general
condition
B 1, 3
220
and
markings
for legibility.
Deleted
311002
Mar
1/05
311003
Instrument
Lines,
Fittings,
Ducting,
C 1
220
and
Instrument
Panel
Wiring
-
Check
for
proper
routing,
support,
and
security
of
attachment.
Revised
321001
Main
Landing
Gear
Wheel Fairings
B 2,
4
721,722
Jun
1/00
and
Brake
Fairings
-
Check
for
cracks,
dents,
and
condition
of
paint.
Revised
321002
Main
Gear
Spring
Assemblies
-
B
2,4
721,722
Mar
1/05
Examine
for
cracks,
dents, corrosion,
condition
of
paint
or
other
damage.
Examine
for chips, scratches,
or
other
damage
that
lets
corrosion
get
to
the
steel
spring.
Examine
the
axles
for
condition
and
security.
321003
Main
Landing
Gear Attachment
B 2,
4
721,722
Structure
-
Check
for damage,
cracks,
loose rivets,
bolts
and
nuts
and
security
of
attachment.
322001
Nose
Gear
-
Inspect
torque
links,
B 2,
4
720
steering
rods, and
boots
for condition
and
security
of
attachment.
Check
strut
for
evidence
of
leakage
and
proper
extension.
Check strut
barrel
for corrosion,
pitting,
and
cleanliness.
Check shimmy damper
and/or
bungees
for
operation,
leakage,
and
attach
points
for
wear and
security.
322002
Nose
Landing
Gear
Wheel Fairings
B
2,
4
720
-
Check
for
cracks,
dents,
and
condition
of
paint.
5-10-01
Page
8
©
Cessna Aircraft
Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
REVISION
ITEM
TASK
INTERVAL OPERATION ZONE
STATUS
CODE
NUMBER
322003
Nose
Gear
Fork
-
Inspect
for
cracks,
C 4
720
general condition,
and
security
of
attachment.
322004
Nose
Gear
Attachment
Structure
-
B 2,
4
720
Inspect
for
cracks, corrosion,
or
other
damage
and
security
of
attachment.
324001
Brakes
-
Test
toe
brakes
and
parking
B 2,
4
230
brake
for
proper operation.
Revised 324002 Brakes, Master
Cylinders,
and
B 2,
4
224, 230
Dec 1/98
Parking
Brake
-
Check
master
cylinders
and
parking
brake
mechanism
for
condition
and
security.
Check fluid
level
and
test
operation
of
toe and
parking
brake.
Refer
to
Chapter
12-13-00
for
servicing
instructions.
324003
Brake
Lines, Wheel
Cylinders,
Hoses,
D 5
721,
722
Clamps,
and
Fittings
-
Check
for
leaks, condition,
and
security
and
hoses for
bulges
and
deterioration.
Check
brake lines
and
hoses
for
proper
routing
and
support.
324004
Tires
-
Check tread
wear
and
general
B 2,
4
720,
721,
condition.
Check
for
proper
inflation.
722
324005
Wheels,
Brake
Discs,
and
Linings
B 2,
4
721,722
-
Inspect
for
wear,
cracks,
warps,
dents,
or
other damage.
Check
wheel
through-bolts
and nuts
for
looseness.
Revised
324006
Wheel Bearings
-
Clean,
inspect
and
B 4
720,
721,
Dec
1/98
lube.
722
325001
Nose
Gear
Steering
Mechanism
-
C 4
720
Check
for
wear,
security,
and
proper
rigging.
331001
Instrument
and
Cabin
Lights
-
Check
B 1, 3
220,
211,
operation, condition
of
lens,
and
221
security
of
attachment.
334001
Navigation,
Beacon,
Strobe,
and
B 1, 3
340,
520,
Landing
Lights
-
Check
operation,
620
condition
of
lens,
and
security
of
attachment.
341101
Static
System
-
Inspect
for
security
of
C 3
210
installation,
cleanliness,
and
evidence
of
damage.
Revised
341102
Pitot and
Static
System
-
Examine
in J
11
220
Jul
3/06
accordance
with
14
CFR
Part
91.411.
5-10-01
Page
9
©
Cessna Aircraft
Company
Jul
3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
REVISION
ITEM
TASK
INTERVAL
OPERATION ZONE
STATUS CODE
NUMBER
341103
Pitot Tube
and
Stall Warning
Vane
-
A
1,2,
3, 4
510
Check
for
condition
and
obstructions
and
verify operation
of
anti-ice
heat.
342101
Magnetic
Compass
-
Inspect
for
C 1
225
security
of
installation, cleanliness,
and
evidence
of
damage.
Revised
342102
Magnetic
Compass
-
Calibrate.
M
14
220
Dec
1/98
Revised
345001
Instrument
Panel
Mounted
Avionics
C 1
225
Dec
1/98
Units
(Including
Audio
Panel,
VHF
Nav/Com(s),
ADF,
GPS,
Transponder, Compass
System,
Multi-function
Display, and
Primary
Flight
Display)
and Remote
Mounted
Avionics
Components.
Inspect
for
deterioration,
cracks,
and
security
of
instrument
panel
mounts.
Inspect
for
security
of
electrical
connections,
condition,
and
security
of
wire
routing.
345002
Avionics
Operating
Controls
-
Inspect
C 1
225
for security
and
proper
operation
of
controls
and
switches
and
ensure
that
all
digital
segments
will
illuminate
properly.
345003
Navigation
Indicators, Controls,
and
C 1
220,
225
Components
-
Inspect for
condition
and
security.
345004 Navigation Antennas
and
Cables
-
C 1
310
Inspect
for
security
of
attachment,
connection,
and
condition.
Added
351001
Oxygen
System
(if
applicable)
-
C 1
211
Nov
1/00
Inspect
masks, hoses, lines,
and
fittings
for
condition,
routing,
and
support.
Test
operation
and
check
for
leaks.
Added
351002
Oxygen
Cylinder
(if
applicable)
T
21 211
Nov
1/00
-
Inspect
for condition,
check
hydrostatic
test date
and
perform
hydrostatic
test,
if
due.
371001
Vacuum
System
-
Inspect
for
B
2, 4
120
condition
and
security.
371002
Vacuum Pumps
-
Check
for
condition
B 2,
4
120
and
security.
Check vacuum
system breather
line
for
obstructions,
condition,
and
security.
5-10-01
Page
10
©
Cessna
Aircraft Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
REVISION
ITEM
TASK
INTERVAL
OPERATION
ZONE
STATUS
CODE
NUMBER
371003
Vacuum
System Hoses
-
Inspect
for
B 2, 4
120
hardness,
deterioration, looseness,
or
collapsed
hoses.
Revised
371004
Gyro
Filter
-
Inspect
for
damage,
B 2, 4
120
Dec
1/98
deterioration
and
contamination.
Clean
or
replace
if
required.
Deleted
371005
Aug
4/03
Revised
371006
Vacuum
Manifold
Check
Valve
V
22
120
Jan
2/06
-
Complete
a
check
for
proper
operation.
(Only
airplanes
with
dual vacuum
pumps
and
Airborne
manifolds.
Refer
to
the
Airborne
Air
&
Fuel
Products
Service
Letter
Number
39A
or latest revision,
and
in
accordance
with
SB02-37-04.)
Refer
to
Chapter
37,
Vacuum
System
-
Maintenance Practices
for
the
removal
and
installation
of
the check
valve.
Added
371007
Do
an
inspection
of
the
wear
indicator
Y
25
120
Jan 2/06
ports
on
the
vacuum
pumps
described
in
Tempest
Service
Letter
004.
521001
Doors
-
Inspect general condition.
B
1,3
210
Check
latches,
hinges,
and
seals
for
condition,
operation,
and
security
of
attachment.
531001
Fuselage
Surface
-
Inspect for skin
B
1,3
210
damage,
loose
rivets,
condition
of
paint,
and
check
pitot-static
ports
and
drain
holes
for obstruction.
Inspect
covers
and
fairings
for
security.
531002
Firewall
Structure
-
Inspect for
C 2
120
wrinkles,
damage,
cracks,
sheared
rivets,
etc.
Check
cowl
shock
mounts
for
condition
and
security.
531003
Internal
Fuselage Structure
-
Inspect
C 1
211
bulkheads,
doorposts, stringers,
doublers,
and
skins for corrosion,
cracks,
buckles,
and
loose rivets,
bolts
and nuts.
5-10-01
Page
11
©
Cessna
Aircraft
Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
REVISION
ITEM
TASK
INTERVAL
OPERATION ZONE
STATUS
CODE
NUMBER
Revised
551001
Horizontal
Stabilizer
and
Tailcone
B 1, 3
320,
330
Dec 1/98
structure
-
Inspect bulkheads,
spars,
ribs,
and
skins,
for
cracks,
wrinkles,
loose
rivets,
corrosion,
or
other
damage.
Inspect horizontal stabilizer
attach
bolts
for looseness.
Retorque
as
necessary.
Check security
of
inspection
covers,
fairings,
and
tips.
Revised
551002 Horizontal
Stabilizer
and
Tips
-
B 1, 3
320,
330
Dec
1/98
Inspect
externally
for skin
damage
and
condition
of
paint.
Revised
553001
Vertical
Stabilizer
Fin
-
Inspect
B 1, 3
340
Dec 1/98
bulkheads,
spars,
ribs, and
skins
for
cracks, wrinkles,
loose
rivets,
corrosion,
or
other
damage.
Inspect
vertical
stabilizer
attach bolts
for
looseness. Retorque
as
necessary.
Check
security
of
inspection
covers,
fairings,
and
tip.
Revised
553002
Vertical
Stabilizer
Fin
and
Tailcone
B 1, 3
340
Dec 1/98
-
Inspect
externally
for
skin
damage
and
condition
of
paint.
561001
Windows
and
Windshield
-
Inspect
B 1, 3
210
general
condition.
Check
latches,
hinges,
and
seals
for
condition,
operation,
and
security
of
attachment.
571001
Wing
Surfaces
and
Tips
-
Inspect
B 1, 3
510, 520,
for
skin
damage,
loose rivets,
and
610,
620
condition
of
paint.
571002
Wing Struts
and
Strut Fairings
-
Check
B 1, 3
510,
610
for
dents,
cracks,
loose
screws
and
rivets,
and
condition
of
paint.
571003
Wing
Access
Plates
-
Check for
C 3
510, 520,
damage
and
security
of
installation.
610,
620
571004
Wing
Spar and
Wing Strut Fittings
C
3
510,
520,
-
Check
for
evidence
of
wear.
610,
620
Check
attach
bolts
for
indications
of
looseness
and retorque
as
required.
571005
Wing
Structure
-
Inspect spars,
C
3
510, 520,
ribs,
skins,
and
stringers
for
cracks, 610,
620
wrinkles,
loose
rivets,
corrosion,
or
other
damage.
611001
Spinner
- Check
general
condition
A
1, 2, 3,
4
110
and
attachment.
Revised
611002
Spinner
and
Spinner
Bulkhead
-
B
2,
4
110
Jan 3/05
Remove
spinner,
wash,
and
inspect
for
cracks
and
fractures.
5-10-01
Page
12
©
Cessna
Aircraft Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
REVISION
ITEM
STATUS CODE
NUMBER
611003
611004
611005
611006
Added
Nov
1/00
Added
Dec 1/98
Revised
Aug
4/03
Added
Dec
15/01
Added
Nov
1/00
Revised
Aug
4/03
611007
612001
612002
612003
710001
710002
TASK
Propeller Blades
-
Inspect
for
cracks,
dents,
nicks,
scratches,
erosion,
corrosion,
or
other
damage.
Propeller
Hub
-
Check
general
condition.
Propeller
Mounting
-
Check
for
security
of
installation.
Propeller
Mounting
Bolts
-
Inspect
mounting
bolts
and
safety
wire
for
signs
of
looseness.
Retorque
mounting
bolts
as
required.
Propeller Heat
Slip
Rings,
Brushes,
and
Boots
-
Inspect
for condition,
and
security. Perform
operational
check.
Propeller
Governor
and
Control
-
Inspect
for
oil
and
grease
leaks.
If
leakage
is
evident,
refer
to
McCauley
Service
Manual.
Propeller
Governor
and
Control
-
Check
for
security
and
operation
of
controls.
Maximum
linear
freeplay
is
0.050
inch.
Propeller
Control
Cable
-
Non-
repairable
item
and
must
be
replaced
at
every
interval
or whenever
maximum
linear
movement exceeds
0.050
inch.
Refer
to
Chapter
61-20-00,
Propeller
Control Cable.
Turbocharger
(if
applicable)
Inspect
turbocharger
mounting
brackets, ducting,
linkage,
and
attaching
parts
for
general
condition,
leakage
or
damage, and
security
of
attachment. Check
waste
gate,
actuator,
controller,
oil
and
vent
lines,
overboost
relief
valve,
and
compressor
housing
for
leakage,
apparent
damage,
security
of
attachment,
and
evidence
of
wear.
Check waste
gate return
spring
for
condition
and
security.
Turbocharger
(if
applicable)
Examine the
turbocharger
for
burned
areas,
bulges,
or
cracks.
Use
a
flashlight
and
mirror
in
the
tailpipe
to
examine
the
turbine
for
coking,
carbonization,
oil
deposits,
and
turbine
impellers
for
damage.
INTERVAL OPERATION ZONE
A
C
A
1,2,
3,4
2
110
110
1,2,3,4
110
C
A
2
1,2,3,4
110
110
1,2,3,4
110
A
C2
15
N
A
C
110
120,210
1,2,3,4
120
2
120
5-10-01
Page
13
Jul
3/2006
©
Cessna
Aircraft Company
CESSNA AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
REVISION
ITEM
STATUS
CODE
NUMBER
TASK
INTERVAL OPERATION ZONE
Cowling
and
Cowl
Flaps
-
Inspect
for cracks,
dents, other
damage
and
security
of
cowl
fasteners.
Check
cowl
flaps
for
condition,
security,
and
operation. Check
cowl
flap
controls
for
freedom
of
movement through
full
travel.
Engine
Shock
Mounts, Engine
Mount
Structure,
and
Ground
Straps
-
Check
condition,
security,
and
alignment.
Alternate
Induction
Air
System
-
Check
for obstructions,
operation,
and
security.
Induction System
-
Check
security
of
clamps,
tubes,
and
ducting.
Inspect
for
evidence
of
leakage.
Induction
Airbox,
Valves, Doors,
and
Controls
-
Remove
air
filter
and
inspect
hinges,
doors,
seals,
and
attaching
parts
for
wear
and
security.
Check
operation.
Induction
Air
Filter
-
Remove
and
clean.
Inspect
for
damage
and
service.
Fuel
line
(Stainless
steel tube
assembly)
and
support
clamp
inspection
and
installation.
Refer
to
Lycoming
Service
Bulletin Number
342E
or
later version.
Engine
-
Inspect for
evidence
of
oil
and
fuel
leaks.
Wash
engine
and
check for
security
of
accessories.
Crankcase,
Oil
Sump, and
Accessory
Section
-
Inspect for
cracks
and
evidence
of
oil
leakage. Check
bolts
and
nuts
for looseness
and
retorque
as
necessary. Check
crankcase
breather
lines
for
obstructions,
security,
and
general
condition.
Hoses,
Metal
Lines,
and Fittings
-
Inspect for
signs
of
oil
and fuel
leaks.
Check
for
abrasions, chafing,
security,
proper
routing and
support
and
for
evidence
of
deterioration.
A
C
A
A
1,2,3,4
120
2
1,2,3,4
120
120
1,2,3,4
120
B
2,
4
A
2,
4
X
A
24
120
120
120
1,2,3,4
120
B
2,
4
A
120
1,2,3,4
120
5-10-01
Page
14
Jul
3/2006
©
Cessna
Aircraft
Company
Revised
Dec
1/98
711001
712001
716001
716002
Revised
Jun
1/00
716003
716004
Added
Jan
2/06
720000
722001
722002
722003
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
.
REVISION
ITEM
TASK
INTERVAL
OPERATION ZONE
STATUS
CODE
NUMBER
723001
Engine Cylinders, Rocker
Box
B 2,
4
120
Covers,
and
Pushrod
Housings
-
Check
for
fin
damage,
cracks,
oil
leakage,
security
of
attachment,
and
general
condition.
723002
Engine
Metal
Lines,
Hoses,
Clamps,
C 2
120
and
Fittings
-
Check
for
leaks,
condition,
and
security.
Check
for
proper
routing
and
support.
723003
Engine
Baffles
and
Seals
-
Check
A
1,2,
3,
4
120
condition
and
security
of
attachment.
Revised
723004
Cylinder
Compression
-
Complete
B 2, 4
120
Jan
2/06
a
differential compression
test.
If
there
is
weak
cylinder
compression,
refer
to
Chapter
71,
Engine
-Troubleshooting,
for
further
procedures.
730001
Engine-Driven
Fuel
Pump
-
Check
B 2, 4
120
for
evidence
of
leakage,
security
of
attachment,
and
general
condition.
730002
Fuel
Injection System
-
Check system
B 2, 4
120
for
security
and
condition.
Clean
fuel
inlet
screen,
check
and
clean
injection
nozzles
and
screens
(if
evidence
of
contamination
is
found),
and
lubricate
air
throttle
shaft.
Added
730003
Idle
and
Mixture
-
Run
the
airplane
B 2,
4
120
Jun
18/01
engine
to
determine
satisfactory
performance.
If
required,
adjust
the
idle
rpm
and
fuel
mixture.
Refer
to
Chapter
73,
Fuel
Injection Systems
-
Maintenance
Practices.
Revised
741001
Magnetos
-
Examine
the
external
B 2,
4
120
Jan
2/06
condition
and
for
correct
installation
and
condition
of
the electrical
leads.
Complete
a
check
of
the engine
timing
(external timing).
You
must
set
the
internal
timing
if
the
total
of
all
external
adjustments
are
more
than
0.125
inch (3.17
mm)
from
the
original
factory
position,
or between
each
of
the
internal
timing
adjustments.
Refer
to
Chapter
74,
Ignition
System
-
Maintenance
Practices.
Revised
741002
Magnetos
-
Clean,
examine,
and
H 9
120
Jul
3/06
adjust
as
necessary.
Do
the
500-hour
inspection
in
accordance
with
the
Slick
4300/6300
Series
Magneto
Maintenance
and
Overhaul
Manual.
5-10-01
Page
15
©
Cessna
Aircraft
Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
REVISION
ITEM
STATUS
CODE
NUMBER
742001
742002
743001
Revised
Jun
1/00
Revised
Jan
2/06
Revised
Dec
1/98
Added
Nov
1/00
743002
761001
781001
781002
TASK
Ignition
Harness
Check
for
deterioration,
ar
terminals.
and
Insulators
proper
routing,
nd
condition
of
Spark Plugs
-
Remove, clean,
analyze,
test,
gap,
and
rotate
top
plugs
to
bottom
and
bottom
plugs
to
top.
Ignition
Switch and Electrical
Harness
-
Inspect for
damage, condition,
and
security.
Inspect
and
lubricate
ACS
brand
ignition
switch. Refer
to
Chapter
74,
Ignition
System
-
Maintenance
Practices.
Engine
Controls
and
Linkage
-
Examine
the
general
condition
and
freedom
of
movement
through
the
full
range.
Complete
a
check
for
the
proper
travel,
security
of
attachment,
and
for evidence
of
wear.
Complete
a
check
of
the
friction
lock
and
vernier
adjustment for
proper
operation.
Complete
a
check
to
make
sure
the
throttle,
fuel
mixture,
and
propeller
governor
arms
operate
through
their
full
arc of
travel. The
maximum
linear
freeplay
is
0.050
inch.
Exhaust
System
-
Inspect
for
cracks
and
security. Special check
in
area
of
heat
exchanger.
Refer
to
Chapter
78,
Exhaust
system
-
Maintenance
Practices.
Exhaust
System (turbocharged
engine)
-
Inspect
couplings,
seals,
clamps,
and
expansion
joints
for
cracks.
Special
check
in
area
of
heat
exchanger.
Refer
to Chapter
78,
Exhaust
System
-
Maintenance
Practices.
Note:
This
inspection
is
specifically
required
for
German
(LBA)
certification.
INTERVAL OPERATION
ZONE
2,
4
B
B
B
N
B
A
A
2,4
2,
4
15
120
120
120
224
1,2,3,4
120,225
1,2,3,4
120
1,
2, 3,4
5-10-01
©
Cessna Aircraft
Company
120
Page
16
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
REVISION
ITEM
STATUS
CODE
NUMBER
TASK
INTERVAL OPERATION
ZONE
Engine
Oil
-
Drain
oil
sump
and
oil
cooler.
Check
for metal
particles
or
foreign material
in
filter,
on
sump
drain
plug,
and
on
engine
suction
screen. Refer
to
Textron
Lycoming
Service Bulletin
#
480C
or
latest
revision.
Replace
filter,
and
refill
with
recommended
grade
aviation
oil.
Oil
Cooler
-
Check
for
obstructions,
leaks,
and
security
of
attachment.
Starter
and
Electrical Connections
-
Check
security
and condition
of
starter,
electrical connection,
and
cable.
Bendix
Drive
Starter
Assembly
-
Clean
and
lubricate starter
drive
assembly.
A
1,2,3,4
120
A
1,2,3,4
120
B
2,4
A
120
1,2,3,4
120
5-10-01
Page
17
Jul
3/2006
©
Cessna Aircraft
Company
Revised
Jun
1/00 791001
792001
Revised
Jun
1/00
Added
Apr
1/02
801001
801002
CESSNA AIRCRAFT
COMPANY
MODEL
182/Ti
82
MAINTENANCE
MANUAL
COMPONENT
TIME
LIMITS
1.General
A.
Most
components
given
in
Chapter
5
must
be
examined
as
shown
elsewhere
in
this
chapter
and
repaired,
overhauled,
or
replaced
as
necessary.
Some
components
have
a
time
or
life
limit
and
must
be
overhauled
or
replaced
on
or
before
the
specified
limit.
B.
The
terms
overhaul
and
replacement
as
used
within
this section
are
defined
as
follows:
(1)
Overhaul
-
Overhaul
the
item
as
given
in
14
CFR
43.2
or
replace
it.
(2)
Replacement
-
Replace
the
item
with
a
new
item
or
a
serviceable
item
that
is
within
its
service
life
and
time
limits or
has
been
rebuilt
as
given
in
14
CFR
43.2.
C.
This
section
(5-11
-00)
gives
a
list
of
items
which
must
be
overhauled
or
replaced
at
specific
time
limits.
Cessna-Supplied
Replacement
Time
Limits
shows
those
items
which
Cessna
has
found
necessary
to
overhaul
or
replace at
specific
time
limits.
Supplier-Supplied
Replacement
Time
Limits
shows
component
time
limits
which
have
been
given
by
an
outside
supplier
for
their
products.
In
addition
to
these
time
limits,
the
components
shown
in
this
section
are
also
examined
at
regular time
intervals
given
in
the
Inspection
Time
Intervals
section.
If
necessary,
based
on
service
use
and
inspection
results,
these components
can
be
overhauled
or
replaced
before
their
time
limit
is
reached.
2.
Cessna-Supplied
Replacement
Time
Limits
A.
Equipment/Furnishings
(Chapter
25).
(1)
504516-401
-XXXX
Restraint
System, Pilot's
Left
Hand
or
Right
Hand
Auto
Adjust
-
Replace
every
10
years.
(2)
504851-401-XXXX
Restraint
System,
Pilot's
Left
Hand
or
Right
Hand
Manual
Adjust
-
Replace
every
10
years.
(3)
50451
6-403-XXXX
Restraint System,
Aft
Bench Left
Hand
or
Right
Hand
Auto
Adjust
-
Replace
every
10
years.
(4)
504851-403-XXXX
Restraint
System,
Aft
Bench
Left
Hand
or
Right
Hand Manual
Adjust
-
Replace every
10
years.
(5)
2000031-09-201 Restraint Assembly,
Pilot's
Seat
-
Replace
every
10
years.
(6)
2000031-10-201
Restraint Assembly, Copilot's
Seat
-
Replace
every
10
years.
(7)
2000031-11
-201
Restraint Assembly,
Right
Rear
Seat
-
Replace
every
1 0
years.
(8)
2000031-12-201
Restraint Assembly,
Left
Rear
Seat
-
Replace
every
10
years.
B.
Flight
Controls (Chapter
27).
(1)
1260074-1
Trim
Tab
Actuator
-
Replace
the
trim
tab
actuators
when
the
free
play
cannot
be
kept
in
limits
by
the
adjustment
or
replacement
of
the
rod
ends,
rod
end
bolts,
screw
assembly,
and
the lubrication
of
the
trim
tab
actuator.
(2)
1260074-7
Trim
Tab
Actuator
(with
dual
axis
autopilot)
-
Replace
the
trim
tab
actuators
when
the
free
play
cannot
be
kept
in
limits
by the
adjustment
or
replacement
of
the
rod
ends,
rod
end
bolts,
screw
assembly,
and
the
lubrication
of
the
trim
tab
actuator.
C.
Vacuum
(Chapter
37).
(1)
C294502-0201
Gyro Filter
-
Replace
at
600 hours.
D.
Propeller
(Chapter
61).
(1)
565-580-038 Propeller
Control
Cable
-
Replace
at
engine
TBO.
E.
Powerplant
(Chapter
71).
(1)
Engine Compartment
Flexible
Fluid-Carrying
Teflon
Hoses (Cessna-Installed), Except
Drain
Hoses
-
Replace
every
1
0
years
or
at
the
engine
overhaul,
whichever
occurs
first.
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
years
or
at
the engine
overhaul,
whichever
occurs first.
This
does
not
include
drain
hoses.
Serviceable
hoses which
are
beyond
these limits must
be
put
on
order
immediately
and
replaced
within
30
days after
the
new
hose
is
received
from
Cessna.
5-1
1-00
Page
1
C
Cessna
Aircraft
Company
Jul
1/2007
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti82
MAINTENANCE
MANUAL
(2)
Engine
Compartment
Drain
Hoses
-
Replace
on
condition.
(3)
Engine
Flexible Hoses
(Textron
Lycoming Installed)
-
Refer
to
latest Textron
Lycoming
Engine
Service
Bulletins.
(4)
P1
98290.
P1
06150
Air
Filter
-
Replace
every
500
hours
or
if
the
condition
of
the part
shows
the
need
for
replacement.
(5)
CA3717
Air
Filter
-
Replace every
100
hours
or
if
the
condition
the
part
shows
the
need
for
replacement.
(6)
Mixture
and
Throttle
Cables
-
Replace
at
every engine
TBO.
(7)
31
B22207 Engine
Starter
-
Replace
at
every
engine
T1RO.
(8)
Engine
Shock
Mounts
-
Replace
at
every engine
TBO
or
if
the
condition
of the
part
shows
the
need
for
replacement.
F.
Chapter
79
(Oil).
(1)
83278
Oil
Pressure
Switch
-
Replace every
3000
hours.
NOTE:
If
the
83278
Oil
Pressure
Switch
has
more
than 3000 hours
and
is in
serviceable
condition,
you must
submit
an
order for
a
new
switch
immediately
and
replace
the
switch
within
60
days after
you
receive
it
from
Cessna.
3.
Supplier-Supplied
Replacement
Time
Limits
A.
Chapter
25
(Equipment/Furnishings).
(1)
2020-0
Pointer
ELT
Battery
-
Refer
to
14
CFR
91.207
for battery
replacement
time
limits.
(2)
508358-409
and
508358-421 AMSAFE
Aviation
Inflatable
Restraint
(AAIR)
Forward
and
Aft
Electronics
Module
Assemblies
(EMA)
-
Remove
and
return
the
forward
and
aft EMA's
to
AMSAFE
Aviation
after
seven
years
from
the
manufacture
date.
The
expiration
of
the
service
life,
that
is
the
total sum
of
storage
life
and
installation
life,
must
not
be
more
than
seven
years
from
the
manufacture
date.
Only
the
manufacturer
can
renew
the
EMA's.
(3)
508792-401 and 508794-401 Pilot's,
Copilot's,
Left
Passenger's,
and Right
Passenger's
AMSAFE
Aviation Inflatable
Restraint
(AAIR)
Inflator
Assemblies
-
Remove
and return
the0
pilot's, copilot's,
left
passenger's,
and
right
passenger's inflator
assemblies
to
AMSAFE
Aviation
after seven
years
from the
manufacture
date.
The
expiration
of
the
service
life,
that
is
the
total
sum
of
storage
life
and
installation
life, must
not
be
more
than
seven years
from
the
manufacture
date.
The
expiration
date
is
found
on the gas
cylinder.
Only
the
manufacturer
can
renew
the
inflator
assemblies.
(4)
452-201
-[X]
Remote
Mounted
CO
Detector
-
Replace
7
years.
B.
Chapter
28
(Fuel).
(1)
Dukes
Model
51
00 Electric
Fuel
Pump
-
Replace
at
1 0
Years
if
not
overhauled.
C.
Chapter
37
(Vacuum).
(1) 1
H5-25
Vacuum
Manifold
-
Refer
to
Airborne Air
&
Fuel
Product
Reference
Memo
No.
39
or
the
latest
revision
for replacement
time limits.
(2)
183-5-1
or
AR1B3-5-1
Regulator
Valve
Filter
-
Replace
at
1
00
hours.
(3)
Dry
Vacuum
Pump
-
Replace
the
engine-driven
vacuum
pump,
if it
does
not
have
a
wear
indicator,
every
500 hours
of
operation,
or replace
the
pump
at
the
vacuum
pump
manufacturer's
recommended
inspection
and
replacement
interval,
whichever
occurs
first.
For
vacuum
pumps
with
a
wear indicator,
replace
the
pump
at
the
manufacturer's
recommended
inspection
and
replacement
interval for
that
vacuum
pump.
(4)
Airborne
350
Vacuum Pump
Coupling
-
Replace
every
6
years.
D.
Chapter
61
(Propeller).
(1)
Propeller
-
Refer
to
the
latest
revision
of
McCauley Service Bulletin
137
for
the
overhaul time
limits.
(2)
C1
61031-0119 Propeller
Governor
-
Any
governor
damaged
by
a
propeller
blade strike,
propeller
or
engine lightning strike,
engine detonation,
oil
contamination,
or
sudden
engine
stop
must
not
be
returned
to
service.
All
such
parts
must
be
repaired
or
overhauled.
Refer
to
McCauley
Service
Bulletin
215SC
or
latest
revision.
5-11-00
Page2
C
Cessna
Aircraft
Company
Jul
1/2007
CESSNA AIRCRAFT
COMPANY
MODEL
1821T182
MAINTENANCE
MANUAL
E.
Chapter
71
(Powerplant).
(1)
10-540-ABlA5
and
T10540-AKl1A
Engine
-
Refer
to
Textron/Lycoming
Service
Instruction
S.I.
1009AJ
or
latest revision
for
time
limits.
(2)
CH48110
Engine
Oil
Filter
-
Refer
to
Textron/Lycoming
Service
Instructions
S.1.
1492B,
S.1.
1267C,
and
Service
Bulletin
SB.4800,
or
latest
revisions.
F.
Chapter
74
(Ignition).
(1)
6351
Slick
Magnetos
-
Refer
to
Slick
Service
Bulletin SB2-80C,
or
latest
revision,
for
time
limits.
5-1
1-00
Page
3
©
Cessna Aircraft Company
Jul
1
/2007
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti
82
MAINTENANCE
MANUAL
PROGRESSIVE
CARE
PROGRAM
General
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
or
her
duties.
As
the
one
primarily
responsible
for
the
airworthiness
of
the
airplane,
the
owner
or
operator
must
select only qualified
personnel
to
maintain
the airplane.
A.
The
program
is
divided
into
four
primary operations
(operations
1
thru
4)
which
cover
all
50-hour,
1
00-hour,
and
200-hour
inspection requirements.
The
other
operations
include
all
of
the
inspection
requirements
due
at
other
intervals.
B.
The
inspection
program
is
divided
into the
progressive
inspection operations.
Operation
1
-
Operation
2
-
Operation
3
-
Operation
4
-
Operation
5
-
Operation
6
-
Operation
7
-
Operation
8
-
Ope
ration
9
-
Operation
1
0-
Operation
11
-
Operation
12
-
Operation
13
-
Operation
14
-
Operation
15
-
Operation
16
-
Operation
17
-
Operation
1 8
-
Operation
19
-
Operation
20
-
Operation
21
-
Has
all
50-hour inspection
items,
and
the
100-
or
200-hour inspection
items
contained
in
the
fuselage
area.
Has
all
50-hour
inspection
items,
and
the
100-
or
200-hour inspection
items
contained
in
the
engine
compartment
area.
Has
all
50-hour
inspection
items,
and
the
100-
or
200-hour inspection
items
contained
in
the
wing.
Has
all
50-hour
inspection
items,
and
the
100-
or
200-hour
inspection
items
contained
in
the
landing
gear.
Has
all
400-hour
or
1
-year
inspection
items,
whichever
occur first.
Has
all
items
that
must
have
an
inspection
at the
first
100
hours,
and
each
500
hours
after
(NOT
CURRENTLY
USED).
Has
all
600-hour
or
1
-year
inspection
items,
whichever
occur
first.
Has
all
1000-hour or
3-year
inspection
items,
whichever
occur
first
(NOT
CURRENTLY
USED).
Has
all
500-hour
inspection
items.
Has
all
1
000-hour
inspection
items.
Has
all
2-year
inspection
items.
Has
all
items
that
must
have an
inspection
at
the
first
5
years, and
each
12
months
after,
until
replacement
at
1 0
years
(NOT
CURRENTLY
USED).
Has
all
50-hour
or
4-month
inspection
items,
whichever
occur
first
(NOT
CURRENTLY
USED).
Has
all
2-year
inspection
items,
or
inspections
of
components
that
are
added
or
removed
with
the
potential
to
change the magnetic accuracy
and/or variation
of
the
compass calibration,
or
any
time
the
accuracy
of
the
compass
is in
question.
Has
all
2000-hour inspection
items.
Has
all
1
000-hour
or
1
-year
inspection
items,
whichever
occur
first.
Has
all
12-month
inspection
items.
Has
all
6-year
inspection
items.
Has
all
12-year inspection items.
Has
all
1
-year
inspection
items.
Has
all
3-year
inspection
items.
5-12-00
Page
1
©
Cessna
Aircraft
Company
Jul
1/2007
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti
182
MAINTENANCE
MANUAL
Operation
22
-
Has
all
5-year inspection
items
from
the
date
of
manufacture.
Serviceability
of
the
components
must
be
examined
each
12
months.
Refer
to
Airborne
Air
and
Fuel
Products
Service Letter
Number
39A
or
latest
revision.
Operation
23
-
Has
all
1
00-hour
or
1
-year
inspection
items,
whichever
occur
first.
Operation
24
-
Every 100
hours,
every
annual
inspection,
every overhaul,
and any time
fuel
lines
or
clamps
are
serviced,
removed
or
replaced.
Operation
25
-
First
600
hours
and
as
defined
by
the manufacturer
thereafter.
Operation
26
-
Everyl1000hours
or
3years,
whichever
occurs
first.
2.
Procedure
A. A
FULL
AIRPLANE INSPECTION
includes
all
50-,
100-,
and
200-hour
inspection
items
plus those
Inspection
Items
contained
in
other
operations
which
are
due
at
the
specified
time.
B.
The
Component
Time
Limits Section
(5-11
-00)
must
be
read
at
each
inspection
interval
to
make
sure
that
the
correct
overhaul
and
replacement requirements
are
done
at
the
specified
times.
C.
The
Inspection
Operations
have been
develope
d
based
on normal
usage
under
average
environmental
conditions. Airplanes
operated
in
extremely
humid
areas
(tropics),
or
in
exceptionally
cold,
damp climates,
etc.,
may
need
more
frequent inspections
for
wear,
corrosion,
and
lubrication.
Under
these
adverse
conditions,
do
the
periodic
inspections
in
compliance
with
the
Inspection
Operations
at
more
frequent intervals
until
the
operator
can
set
his
own
inspection periods
based
on
field
experience.
The operator's
inspection
intervals
must
not
deviate
from
the
inspection
time
limits
shown
in
this manual
except
as
given
below:
(1)
Each
inspection
interval
can
be
extended
by
1 0
hours
(if
time-controlled),
or
by
30
days
(if
date-
controlled)
or can
be
performed early
at
any time prior
to
the
regular
interval
as
provided
below:
(a) In
the
event
of
late
compliance
of
any
operation
scheduled,
the next
operation
in
sequence
keeps
a
due
point
from
the
time
the
late
operation
was
originally
scheduled.
(b) In
the
event
of
early
compliance
of
any
operation scheduled, that
occurs
1
0
hours
or
less
ahead
of
schedule,
the
next
phase
due
point
can stay
where
originally
set.
(c) In
the
event
of
early
compliance
of
any
operation
scheduled, that occurs
more
than
10
hours ahead
of
schedule,
the
next
operation
due point
must
be
rescheduled
to
establish
a
new
due
point
from the
time
of
early
compliance.
3.
Inspection
Terms
and
Guidelines
A.
For
inspection
terms
and
guidelines,
refer
to
Time
Limits/Maintenance
Checks
-
General.
5-1
2-00
Page
2
©
Cessna
Aircraft Company
Jul
1/2007
I
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION
OPERATION
1
Date:
Registration
Number:
Serial Number:
Total
Time:
1.
Description
A.
Operation
1
gives
a
list
of
item(s),
which
has
all
50-hour
interval
inspection
items and
those
100- or
200-hour
interval
inspection
items
contained
in
the
fuselage
area.
Items from
other
areas
are
included
to meet
their
required
time interval.
B.
Inspection
items
are
given
in
the order
of
the
zone
in
which
the
inspection
is
to
be
completed.
A
general
description
of
the inspection
required
and
the
Item
Code
Number
for
cross-reference
to
section
5-10-01
are
shown. Frequently,
the
tasks
define
more
specifically
the
scope
and
extent
of
each
required
inspection. These tasks
are printed
in
the
individual chapters
of
this manual.
C.
The
right
portion
of
each
page
gives
space for
the
mechanic's
and
inspector's
initials
and
remarks.
A
copy
of
these
pages
can
be
used
as
a
checklist
when
these
inspections
are
completed.
2.
General
Inspection
Criteria
A.
During
each
of
the specified inspection tasks
in
this
section,
more
general
inspections
of
the
adjacent
areas
must
be
done
while
access
is
available. These
general
inspections
are
used to
find
apparent
conditions which
can need
more
maintenance.
B. If a
component
or
system
is
changed after
a
required
task
has
been
completed, then
that
specified
task
must
be
done
again
to
make
sure
it is
correct
before
the
system or
component
is
returned
to
service.
C.
Do
a
preflight inspection
after
these inspections
are
completed
to
make
sure
all
the
required
items
are
correctly
serviced.
Refer
to
the
Pilot's Operating
Handbook
and
FAA
Approved
Airplane
Flight
Manual.
ITEM
CODE
TASK
ZONE
MECH
INSP
REMARKS
NUMBER
611001
Spinner
-
Check
general
condition
and
attachment.
110
611003
Propeller
Blades
-
Inspect
for cracks,
dents,
nicks,
110
scratches,
erosion,
corrosion,
or
other
damage.
611005
Propeller
Mounting
-
Check
for
security
of
110
installation.
611007
Propeller
Heat
Slip
Rings, Brushes,
and Boots
110
-
Inspect for
condition,
and
security. Perform
operational check.
612001
Propeller
Governor
and Control
-
Inspect
for
oil
110
and
grease
leaks.
If
leakage
is
evident,
refer
to
McCauley
Service
Manual.
242001
Alternator, Mounting Bracket,
and
Electrical
120
Connections
-
Check condition
and
security. Check
alternator
belts for
condition
and
proper
adjustment.
Check
belt
tension.
5-12-01
Page
1
©
Cessna Aircraft
Company
Jul
3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
ITEM CODE
TASK
ZONE
MECH INSP
REMARKS
NUMBER
710001
Turbocharger
(if
applicable)
-
Inspect
turbocharger
120
mounting
brackets,
ducting,
linkage,
and
attaching
parts
for
general
condition,
leakage
or
damage,
and
security
of
attachment. Check
waste
gate, actuator,
controller,
oil
and vent lines,
overboost
relief
valve,
and
compressor
housing
for
leakage,
apparent
damage,
security
of
attachment,
and
evidence
of
wear.
Check
waste
gate
return
spring
for
condition
and
security.
711001
Cowling
and Cowl Flaps
-
Inspect for
cracks,
dents,
120
other
damage
and
security
of
cowl
fasteners.
Check
cowl
flaps
for
condition,
security,
and
operation.
Check
cowl
flap controls
for
freedom
of
movement
through
full
travel.
716001
Alternate
Induction
Air
System
-
Check
for
120
obstructions,
operation,
and
security.
716002
Induction
System
-
Check
security
of
clamps, tubes,
120
and
ducting.
Inspect
for
evidence
of
leakage.
722001
Engine
-
Inspect
for
evidence
of
oil
and
fuel
leaks.
120
Wash
engine
and
check
for security
of
accessories.
722003
Hoses,
Metal
Lines,
and
Fittings
-
Inspect
for
signs
120
of
oil
and
fuel
leaks.
Check for
abrasions,
chafing,
security, proper
routing
and
support
and
for
evidence
of
deterioration.
723003
Engine
Baffles
and
Seals
-
Check
condition
and
120
security
of
attachment.
781001
Exhaust
System
-
Inspect
for
cracks
and
security.
120
Special check
in
area
of
heat
exchanger.
Refer
to
Chapter
78,
Exhaust system
-
Maintenance
Practices.
781002 Exhaust
System
(turbocharged
engine)
-
Inspect
120
couplings,
seals, clamps,
and
expansion joints
for
cracks.
Special
check
in
area
of
heat
exchanger.
Refer to
Chapter
78,
Exhaust
System
-
Maintenance
Practices.
Note:
This
inspection
is
specifically
required for German
(LBA)
certification.
791001
Engine
Oil
-
Drain oil
sump
and
oil
cooler.
Check
for
120
metal
particles
or
foreign
material
in
filter,
on
sump
drain plug,
and
on
engine
suction
screen.
Refer
to
Textron
Lycoming
Service
Bulletin
#
480C
or
latest
revision.
Replace
filter,
and
refill
with
recommended
grade
aviation
oil.
792001
Oil
Cooler
-
Check
for
obstructions,
leaks,
and
120
security
of
attachment.
801002
Bendix
Drive
Starter Assembly
-
Clean
and
lubricate
120
starter
drive
assembly.
5-12-01
Page
2
©
Cessna
Aircraft
Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
ITEM
CODE
TASK
ZONE
MECH INSP
REMARKS
NUMBER
761001
Engine
Controls
and
Linkage
-
Examine
the
general
120,
225
condition
and
freedom
of
movement
through
the
full range.
Complete
a
check
for
the proper travel,
security
of
attachment,
and
for
evidence
of
wear.
Complete
a
check
of
the
friction
lock
and vernier
adjustment
for
proper
operation.
Complete
a
check
to
make sure
the
throttle,
fuel mixture,
and
propeller
governor
arms
operate
through
their
full
arc of
travel.
The
maximum
linear
freeplay
is
0.050
inch.
271001
Aileron
Controls
-
Check
freedom
of
movement
and
120, 520,
proper
operation
through
full
travel.
620
243003
General Airplane
and
System Wiring
-
Inspect
for
210
proper
routing,
chafing,
broken or
loose
terminals,
general
condition,
broken or
inadequate
clamps,
and
sharp
bends
in
wiring.
521001
Doors
-
Inspect general condition.
Check latches,
210
hinges,
and
seals
for condition,
operation,
and
security
of
attachment.
531001
Fuselage Surface
-
Inspect
for
skin damage, loose
210
rivets,
condition
of
paint,
and
check
pitot-static
ports
and
drain
holes
for
obstruction.
Inspect
covers
and
fairings
for
security.
561001
Windows
and
Windshield
-
Inspect general
210
condition.
Check
latches,
hinges,
and
seals
for
condition,
operation,
and
security
of
attachment.
214002
Heater
Components,
Inlets, and
Outlets
-
Inspect
211
all
lines, ducts,
clamps,
seals,
and
gaskets
for
condition, restriction,
and
security.
214003
Cabin
Heat
and
Ventilation Controls
-
Check
211
freedom
of
movement
through
full
travel.
Check
friction
locks
for
proper
operation.
235001
Microphones, Headsets,
and
Jacks
-
Inspect
for
211
cleanliness,
security,
and
evidence
of
damage.
251001
Seats
-
Examine the
seats
to
make sure
they
are
211
serviceable
and
installed
correctly.
Make
sure
the
seat
stops
and
adjustment
mechanism
operate
correctly.
Examine
the
seat
recline
control
and
attaching
hardware
to
make sure
the
hardware
and
lock are
not
damaged
and
are
correctly installed.
Lubricate
the
threads
of
the Seat
Crank
Handle
Assembly
with
MIL-PRF-81322 general purpose
grease.
251101
Restraint
System,
front
and rear
-
Check
belts
211
for
thinning, fraying,
cutting, broken
stitches,
or
ultra-violet
deterioration.
Check
system hardware
for
security
of
installation.
5-12-01
Page
3
©
Cessna
Aircraft
Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
ITEM
CODE TASK
ZONE
MECH
INSP
REMARKS
NUMBER
351001
Oxygen
System
(if
applicable)
-
Inspect
masks,
211
hoses,
lines,
and
fittings
for
condition,
routing,
and
support.
Test
operation
and
check for
leaks.
531003
Internal
Fuselage
Structure
-
Inspect
bulkheads,
211
doorposts,
stringers,
doublers,
and
skins for
corrosion, cracks, buckles,
and
loose
rivets,
bolts
and
nuts.
311001
Instruments
-
Check
general
condition
and
markings
220
for
legibility.
311003 Instrument
Lines, Fittings, Ducting,
and Instrument
220
Panel
Wiring
-
Check
for
proper
routing,
support,
and
security
of
attachment.
331001
Instrument
and
Cabin
Lights
-
Check operation,
220,
211,
condition
of
lens,
and
security
of
attachment.
221
345003
Navigation Indicators, Controls,
and
Components
-
220,
225
Inspect
for
condition
and
security.
275002
Wing
Flap
Control
-
Check
operation
through
full
221
travel
and
observe
Flap
Position
indicator for
proper
indication.
246001
Switch
and
Circuit
Breaker
Panel,
Terminal
Blocks,
222
and
Junction
Boxes
-
Inspect
wiring
and
terminals
for
condition
and
security.
246002
Power
Junction
Box
-
Check
operation
and
222
condition.
Check
availability
and
condition
of
spare
fuse
(if
applicable).
271005
Control
Wheel Lock
-
Check
general
condition
and
222
operation.
235002
Microphone
Push-To-Talk
Switch
-
Clean the pilot's
222, 223
and
copilot's microphone switches.
Refer
to
Chapter
23,
Communication
-
Maintenance
Practices.
271006
Control
Linkage
-
Inspect
pulleys,
cables,
bearings,
222, 223
and
turnbuckles
for
condition
and
security.
273001
Elevator
Control
-
Check freedom
of
movement and
222,
223
proper
operation through full
travel.
273002
Elevator
Control
System
-
Inspect
pulleys, cables,
222, 223
sprockets, bearings, chains,
and
turnbuckles
for
condition,
security,
and
operation. Check
cables
for
tension,
routing,
fraying, corrosion,
and
turnbuckle
safety
273103
Elevator
Trim
Tab
and
Hinges
-
Check
condition,
224
security, and
operation.
282003
Fuel
Selector
Valve
-
Check controls
for
detent
in
224
each
position,
security
of
attachment,
and
for
proper
placarding.
5-12-01
Page
4
©
Cessna
Aircraft
Company
Jul 3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
ITEM
CODE
TASK ZONE
MECH
INSP
REMARKS
NUMBER
282006
Fuel
Selector
-
Using
quick
drain,
ensure
no
224
contamination
exists.
273101
Elevator
Trim
System
-
Check
cables, push-pull
224, 240,
rods,
bellcranks,
pulleys,
turnbuckles,
fairleads,
310
rub
strips,
etc.
for
proper
routing,
condition,
and
security.
273102 Elevator
Trim
Control
and
Indicator
-
Check
freedom 224, 240,
of
movement and proper
operation
through
full
310
travel. Check
pulleys,
cables,
sprockets,
bearings,
chains,
and
turnbuckles
for
condition
and
security.
Check
electric
trim
controls
for
operation
as
applicable. Check
cables for tension,
routing,
fraying,
corrosion,
and
turnbuckle
safety
342101
Magnetic Compass
-
Inspect for
security
of
225
installation,
cleanliness,
and
evidence
of
damage.
345001
Instrument Panel
Mounted
Avionics
Units
(Including
225
Audio
Panel, VHF
Nav/Com(s),
ADF, GPS,
Transponder, Compass
System,
Multi-function
Display,
and
Primary
Flight Display)
and
Remote
Mounted
Avionics
Components. Inspect
for
deterioration,
cracks,
and
security
of
instrument
panel
mounts.
Inspect
for
security
of
electrical
connections,
condition,
and
security
of
wire
routing.
345002
Avionics Operating
Controls
-
Inspect
for
security
225
and
proper
operation
of
controls
and
switches
and
ensure
that
all
digital
segments
will
illuminate
properly.
262001
Portable
Hand
Fire
Extinguisher
-
Inspect for
230
proper
operating
pressure,
condition, security
of
installation,
and
servicing
date.
272004
Rudder Pedals
and
Linkage
-
Check for
general
230
condition, proper
rigging,
and
operation.
Check
for
security
of
attachment.
273106 Elevator
Trim
Tab
Stop
Blocks
-
Inspect
for
damage
240
and
security.
256001
Emergency
Locator Transmitter-
Inspect
for
security
310
of
attachment
and
check
operation
by
verifying
transmitter output.
Check
cumulative
time
and
useful
life
of
batteries
in
accordance
with
14
CFR
Part
91.207.
273004 Elevator Downspring
-
Check
structure,
bolts,
310
linkage,
bell
crank,
and
push-pull
tube for
condition,
operation,
and
security.
Check cables
for
tension,
routing,
fraying,
corrosion,
and
turnbuckle
safety.
Check
travels
if
cables
require
tension adjustment
or
if
stops
are
damaged.
345004 Navigation
Antennas
and
Cables
-
Inspect for
310
security
of
attachment,
connection,
and
condition.
5-12-01
Page
5
©
Cessna
Aircraft
Company
Jul
3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
ITEM
CODE
TASK
ZONE
MECH INSP
REMARKS
NUMBER
273104
Elevator
Trim
Tab
Actuator
-
Examine
the
free
320
play
limits.
Refer
to
Chapter
27,
Elevator
Trim
Control
-
Maintenance
Practices,
Trim
Tab
Free
Play
Inspection.
If
the
free
play
is
more
than
the
permitted
limits,
lubricate
the
actuator
and
examine
the
free
play
limits
again.
If
the
free
play
is
still
more
than the
permitted limits, replace
the
actuator.
273003
Elevator,
Hinges,
Stops,
and
Cable
Attachment
-
320,
330
Check
condition,
security,
and
operation.
551001
Horizontal
Stabilizer
and
Tailcone
structure
-
320,330
Inspect
bulkheads,
spars,
ribs,
and
skins,
for
cracks, wrinkles,
loose
rivets,
corrosion,
or
other
damage.
Inspect
horizontal
stabilizer
attach bolts
for
looseness.
Retorque
as
necessary.
Check
security
of
inspection covers, fairings,
and
tips.
551002
Horizontal
Stabilizer
and
Tips
-
Inspect
externally
for
320,
330
skin damage
and
condition
of
paint.
272002 Rudder
-
Inspect
the
rudder
skins for
cracks
and
340
loose
rivets,
rudder hinges
for
condition,
cracks
and
security;
hinge
bolts,
hinge
bearings, hinge
attach
fittings,
and
bonding
jumper
for
evidence
of
damage
and
wear, failed
fasteners,
and
security.
Inspect
balance
weight
for
looseness
and
the
supporting
structure
for
damage.
272003 Rudder,
Tips,
Hinges,
Stops,
Clips
and Cable
340
Attachment
-
Check
condition,
security,
and
operation.
272005
Rudder
Control
-
Check
freedom
of
movement
and
340
proper
operation through
full travel.
Check
rudder
stops
for damage and
security.
553001
Vertical
Stabilizer
Fin
-
Inspect
bulkheads,
spars,
340
ribs,
and
skins
for cracks, wrinkles,
loose
rivets,
corrosion,
or
other
damage.
Inspect
vertical
stabilizer
attach
bolts
for
looseness.
Retorque
as
necessary.
Check
security
of
inspection
covers,
fairings,
and
tip.
553002 Vertical
Stabilizer
Fin
and
Tailcone
-
Inspect
340
externally
for
skin
damage
and
condition
of
paint.
334001
Navigation,
Beacon, Strobe,
and
Landing
Lights
-
340,
520,
Check
operation,
condition
of
lens,
and
security
of
620
attachment.
341103
Pitot
Tube
and Stall Warning
Vane
-
Check
for
510
condition
and
obstructions
and
verify
operation
of
anti-ice
heat.
571001
Wing
Surfaces
and
Tips
-
Inspect
for
skin
damage,
510,
520,
loose
rivets, and
condition
of
paint. 610, 620
5-12-01
Page
6
©
Cessna
Aircraft
Company
Jul
3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
ITEM
CODE
TASK
ZONE
MECH
INSP
REMARKS
NUMBER
275001
Flaps
-
Check
tracks,
rollers, and
control
rods
for
510,
610
security
of
attachment.
Check
rod
end
bearings
for
corrosion.
Check
operation.
282001
Fuel
System
-
Inspect plumbing
and
components
for
510,
610
mounting
and
security.
282002
Fuel
Tank
Vent
Lines and
Vent
Valves
-
Check
vents 510,
610
for
obstruction
and
proper positioning. Check
valves
for operation.
282004
Integral
Fuel
Bays
-
Check
for
evidence
of
leakage
510,
610
and
condition
of
fuel
caps,
adapters,
and
placards.
Using
quick
drains,
ensure
no
contamination exists.
Check
quick
drains for proper
shut
off.
282007
Fuel
Strainer,
Drain Valve,
and
Controls
-
Check
510,
610
freedom
of
movement,
security,
and
proper
operation.
Disassemble, flush,
and
clean
screen
and
bowl.
571002
Wing
Struts
and Strut
Fairings
-
Check
for
dents,
510,
610
cracks,
loose
screws
and rivets,
and
condition
of
paint.
271003
Aileron
Structure,
Control
Rods,
Hinges, Balance
520,
620
Weights, Bellcranks, Linkage,
Bolts,
Pulleys,
and
Pulley
Brackets
-
Check condition, operation,
and
security
of
attachment.
271004
Ailerons
and
Hinges
-
Check condition,
security,
and
520,
620
operation
275006
Flap
Actuator Threads
-
Clean
and
lubricate.
Refer
610
to
Chapter
12-21-03.
110000
Interior
Placards, Exterior
Placards,
Decals,
ALL
Markings
and
Identification
Plates
-
Inspect
for
security
of
installation
and
legibility.
Refer
to
Chapter
11,
Placards
and
Markings
-
Inspection/Check.
***
End
of
Operation
1
Inspection
Items
***
5-12-01
Page
7
©
Cessna
Aircraft
Company
Jul
3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION
OPERATION
2
Date:
Registration
Number:
Serial Number:
Total
Time:
1.
Description
A.
Operation
2
gives
a
list
of
item(s),
which
has
all
50-hour
interval
inspection
items
and
those
100-
or
200-hour
interval
inspection
items
contained
in
the
engine
compartment.
Items
from
other areas
are
included
to
meet
their
required
time
interval.
B.
Inspection
items
are
given
in
the order
of
the zone
in
which
the
inspection
is
to
be
completed.
A
general
description
of
the
inspection
required
and the
Item
Code
Number for
cross-reference
to
section
5-10-01
are
shown.
Frequently,
the
tasks
define
more
specifically
the
scope
and
extent
of
each
required
inspection. These
tasks
are
printed
in
the
individual
chapters
of
this
manual.
C.
The
right
portion
of
each
page
gives space
for
the
mechanic's
and
inspector's
initials
and
remarks.
A
copy
of
these
pages can
be
used
as
a
checklist
when
these
inspections
are
completed.
2.
General
Inspection
Criteria
A.
During
each
of
the
specified inspection
tasks
in
this
section,
more
general
inspections
of
the
adjacent
areas
must
be
done
while
access
is
available.
These
general
inspections
are
used
to
find
apparent
conditions
which
can
need
more
maintenance.
B. If
a
component
or system
is
changed after
a
required
task
has
been
completed,
then
that
specified
task
must
be
done
again
to
make
sure
it is
correct
before
the system
or component
is
returned
to
service.
C.
Do
a
preflight
inspection
after
these inspections
are
completed
to
make
sure
all
the
required
items
are
correctly
serviced.
Refer
to
the
Pilot's
Operating
Handbook
and
FAA
Approved Airplane
Flight
Manual.
ITEM
CODE
TASK ZONE
MECH
INSP
REMARKS
NUMBER
611001
Spinner
-
Check
general
condition
and attachment.
110
611002
Spinner
and
Spinner
Bulkhead
-
Remove
spinner,
110
wash,
and
inspect
for
cracks
and
fractures.
611003
Propeller
Blades
-
Inspect
for
cracks,
dents, nicks,
110
scratches,
erosion, corrosion,
or
other
damage.
611004
Propeller
Hub
-
Check general
condition.
110
611005
Propeller Mounting
-
Check
for
security
of
110
installation.
611006
Propeller Mounting
Bolts
-
Inspect
mounting
bolts
110
and
safety
wire
for
signs
of
looseness.
Retorque
mounting
bolts
as required.
611007
Propeller Heat
Slip Rings,
Brushes, and
Boots
110
-
Inspect
for
condition,
and
security.
Perform
operational check.
5-12-02
Page
1
Cessna
Aircraft
Company
Jul
3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
ITEM
CODE
TASK
ZONE
MECH
INSP
REMARKS
NUMBER
612001
Propeller
Governor
and
Control
-
Inspect for
oil
110
and
grease
leaks.
If
leakage
is
evident,
refer
to
McCauley Service
Manual.
612002
Propeller
Governor
and
Control
-
Check for
security
110
and
operation
of
controls.
Maximum
linear
freeplay
is
0.050
inch.
214001
Cold
and
Hot Air
Hoses
-
Check
condition,
routing,
120
and
security.
242001
Alternator,
Mounting
Bracket,
and
Electrical
120
Connections -
Check condition
and
security.
Check
alternator
belts
for condition
and
proper
adjustment.
Check belt tension.
243004 External
Power
Receptacle
and Power Cables
-
120
Inspect
for
condition
and
security.
282010
Auxiliary
(Electric)
Fuel Pump
-
Check
pump
and
120
fittings
for
condition,
operation, security.
371001
Vacuum
System
-
Inspect for
condition
and
security.
120
371002
Vacuum
Pumps
-
Check for
condition
and
security.
120
Check
vacuum system
breather
line
for
obstructions,
condition,
and
security.
371003
Vacuum
System
Hoses
-
Inspect
for
hardness,
120
deterioration, looseness,
or
collapsed
hoses.
371004
Gyro
Filter
-
Inspect
for
damage,
deterioration
and
120
contamination.
Clean
or
replace
if
required.
531002 Firewall
Structure
-
Inspect
for
wrinkles,
damage,
120
cracks,
sheared
rivets,
etc.
Check
cowl shock
mounts
for condition
and
security.
710001
Turbocharger
(if
applicable) -
Inspect
turbocharger
120
mounting
brackets,
ducting,
linkage, and
attaching
parts
for
general
condition,
leakage
or
damage,
and
security
of
attachment.
Check waste
gate,
actuator,
controller,
oil
and
vent
lines,
overboost
relief
valve,
and
compressor
housing
for
leakage,
apparent
damage,
security
of
attachment,
and
evidence
of
wear.
Check waste
gate
return
spring
for
condition
and
security.
710002
Turbocharger
(if
applicable)
-
Examine
the
120
turbocharger
for burned areas, bulges,
or
cracks.
Use
a
flashlight
and
mirror
in
the
tailpipe
to examine
the
turbine
for
coking,
carbonization,
oil
deposits,
and
turbine
impellers
for
damage.
711001
Cowling and
Cowl
Flaps
-
Inspect
for
cracks,
dents,
120
other
damage
and
security
of
cowl
fasteners.
Check
cowl
flaps
for
condition,
security,
and operation.
Check
cowl flap
controls
for
freedom
of
movement
through
full
travel.
5-12-02
Page
2
©
Cessna
Aircraft
Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
ITEM CODE
TASK
ZONE
MECH
INSP
REMARKS
NUMBER
712001
Engine
Shock
Mounts,
Engine
Mount
Structure,
120
and
Ground
Straps
-
Check condition,
security,
and
alignment.
716001
Alternate
Induction
Air System
-
Check
for
120
obstructions,
operation,
and
security.
716002
Induction System
-
Check
security
of
clamps,
tubes,
120
and
ducting.
Inspect
for
evidence
of
leakage.
716003
Induction
Airbox,
Valves,
Doors,
and
Controls
-
120
Remove
air
filter
and
inspect
hinges,
doors, seals,
and
attaching
parts
for
wear
and
security.
Check
operation.
716004
Induction
Air
Filter
-
Remove
and
clean. Inspect
for
120
damage
and
service.
722001
Engine
-
Inspect
for
evidence
of
oil
and
fuel
leaks.
120
Wash
engine
and
check for
security
of
accessories.
722002 Crankcase,
Oil Sump,
and
Accessory
Section
-
120
Inspect for cracks
and evidence
of
oil
leakage.
Check
bolts
and
nuts
for
looseness
and
retorque
as
necessary.
Check crankcase breather
lines
for
obstructions,
security,
and
general
condition.
722003
Hoses,
Metal
Lines,
and
Fittings
-
Inspect for
signs
120
of
oil
and
fuel
leaks. Check
for
abrasions,
chafing,
security,
proper
routing
and
support
and
for
evidence
of
deterioration.
723001
Engine
Cylinders,
Rocker
Box
Covers,
and
Pushrod
120
Housings
-
Check
for
fin
damage,
cracks,
oil
leakage,
security
of
attachment,
and
general
condition.
723002
Engine
Metal
Lines,
Hoses,
Clamps,
and
Fittings
-
120
Check
for leaks,
condition,
and
security.
Check
for
proper
routing
and
support.
723003
Engine
Baffles
and
Seals
-
Check
condition
and
120
security
of
attachment.
723004
Cylinder
Compression
-
Complete
a
differential
120
compression
test.
If
there
is
weak cylinder
compression,
refer
to
Chapter
71,
Engine
-
Troubleshooting, for further
procedures.
730001
Engine-Driven
Fuel
Pump
-
Check
for
evidence
120
of
leakage,
security
of
attachment,
and
general
condition.
730002
Fuel
Injection System
-
Check
system
for
security
120
and
condition.
Clean
fuel
inlet
screen,
check
and
clean injection
nozzles
and
screens
(if
evidence
of
contamination
is
found),
and
lubricate
air throttle
shaft.
5-12-02
Page
3
©
Cessna Aircraft Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
ITEM CODE
TASK
ZONE
MECH
INSP
REMARKS
NUMBER
730003
Idle
and
Mixture
-
Run
the
airplane engine
to
120
determine
satisfactory
performance.
If
required,
adjust
the
idle
rpm
and
fuel
mixture.
Refer
to
Chapter
73,
Fuel
Injection Systems
-
Maintenance
Practices.
741001
Magnetos
-
Examine the
external
condition
and
for
120
correct
installation
and
condition
of
the
electrical
leads.
Complete
a
check
of
the
engine timing
(external
timing).
You
must
set
the
internal timing
if
the
total
of
all
external
adjustments
are
more
than
0.125
inch
(3.17
mm)
from
the
original
factory
position,
or
between each
of
the
internal timing
adjustments.
Refer
to
Chapter
74,
Ignition
System
-
Maintenance
Practices.
742001
Ignition
Harness
and
Insulators
-
Check
for
proper
120
routing,
deterioration,
and
condition
of
terminals.
742002
Spark
Plugs
-
Remove, clean,
analyze,
test,
gap,
120
and rotate
top
plugs
to
bottom
and
bottom plugs
to
top.
743001
Ignition
Switch
and
Electrical Harness
-
Inspect for
120
damage,
condition,
and
security.
781001
Exhaust
System
-
Inspect
for
cracks
and
security.
120
Special
check
in
area
of heat
exchanger.
Refer
to
Chapter
78,
Exhaust system
-
Maintenance
Practices.
781002
Exhaust
System
(turbocharged engine)
-
Inspect
120
couplings,
seals,
clamps,
and
expansion
joints
for
cracks.
Special
check
in
area
of
heat
exchanger.
Refer
to
Chapter
78,
Exhaust System
-
Maintenance
Practices.
Note:
This
inspection
is
specifically
required
for
German
(LBA)
certification.
791001
Engine
Oil
-
Drain
oil
sump
and
oil
cooler.
Check
for
120
metal
particles
or
foreign
material
in
filter,
on
sump
drain
plug,
and
on
engine
suction
screen. Refer
to
Textron
Lycoming
Service
Bulletin
#
480C
or
latest
revision.
Replace
filter,
and
refill
with
recommended
grade
aviation
oil.
792001
Oil
Cooler
-
Check
for obstructions,
leaks,
and
120
security
of
attachment.
801001
Starter
and
Electrical
Connections
-
Check
security
120
and
condition
of
starter, electrical
connection,
and
cable.
801002
Bendix
Drive
Starter Assembly
-
Clean
and
lubricate
120
starter drive
assembly.
5-12-02
Page
4
©
Cessna
Aircraft
Company
Jul
3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
ITEM
CODE
TASK ZONE
MECH
INSP
REMARKS
NUMBER
761001
Engine
Controls
and
Linkage
-
Examine
the
general
120,
225
condition
and
freedom of
movement
through
the
full
range.
Complete
a
check
for
the
proper
travel,
security
of
attachment,
and
for
evidence
of
wear.
Complete
a
check
of
the
friction
lock
and
vernier
adjustment
for
proper
operation.
Complete
a
check
to
make sure
the
throttle, fuel
mixture,
and
propeller
governor
arms
operate
through
their
full
arc
of
travel.
The maximum
linear
freeplay
is
0.050
inch.
324002
Brakes,
Master
Cylinders,
and
Parking Brake
224,230
-
Check
master
cylinders
and
parking
brake
mechanism
for
condition
and
security.
Check
fluid
level
and
test
operation
of
toe
and
parking
brake.
Refer
to
Chapter
12-13-00
for
servicing
instructions.
251002
Seat
Tracks
and
Stops
-
Inspect
seat
tracks
for
230
condition
and
security
of
installation.
Check seat
track
stops
for damage
and correct location. Inspect
seat
rails
for cracks.
324001
Brakes
-
Test
toe
brakes and
parking
brake
for
proper
230
operation.
243001
Main
Battery
-
Examine
the
general
condition
and
310
security.
Complete
a
check
of the
level
of
electrolyte.
Refer
to
Chapter
12,
Battery
-
Servicing.
243002
Main
Battery
Box
and
Cables
-
Clean
and
remove
310
any
corrosion.
Examine the
cables
for
routing,
support,
and
security
of
the
connections.
341103
Pitot
Tube
and
Stall
Warning
Vane
-
Check for
510
condition
and
obstructions
and
verify
operation
of
anti-ice
heat.
322001
Nose
Gear
-
Inspect
torque
links,
steering
rods, 720
and
boots for
condition
and
security
of
attachment.
Check
strut
for
evidence
of
leakage
and
proper
extension.
Check
strut
barrel
for
corrosion,
pitting,
and
cleanliness.
Check
shimmy
damper
and/or
bungees for
operation, leakage,
and
attach points
for
wear
and
security.
322002
Nose
Landing
Gear
Wheel
Fairings
-
Check
for
720
cracks, dents,
and
condition
of paint.
322004
Nose
Gear Attachment
Structure
-
Inspect
for
720
cracks,
corrosion,
or
other
damage
and
security
of
attachment.
324004
Tires
-
Check
tread
wear
and
general condition.
720,
721,
Check
for
proper
inflation.
722
321003
Main
Landing
Gear Attachment
Structure
-
Check
721,
722
for
damage,
cracks,
loose
rivets,
bolts
and
nuts
and
security
of
attachment.
5-12-02
Page
5
©
Cessna
Aircraft
Company
Jul
3/2006
CESSNA AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
Wheels,
Brake
Discs,
and
Linings
-
Inspect
for
wear,
721,
722
cracks,
warps, dents,
or
other
damage.
Check wheel
through-bolts
and
nuts
for
looseness.
Main
Landing
Gear
Wheel
Fairings
and
Brake
721,722
Fairings
-
Check
for
cracks,
dents,
and condition
of
paint.
Interior
Placards,
Exterior
Placards,
Decals,
ALL
Markings
and
Identification
Plates
-
Inspect
for
security
of
installation
and
legibility. Refer
to
Chapter
11,
Placards
and
Markings
-
Inspection/Check.
***
End
of
Operation
2
Inspection
Items
***
5-12-02
Page
6
Jul 3/2006
©
Cessna Aircraft
Company
ITEM
CODE
TASK
NUMBER
324005
321001
110000
ZONE
MECH INSP
REMARKS
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION
OPERATION
3
Date:
Registration
Number:
Serial
Number:
Total
Time:
1.
Description
A.
Operation
3
gives
a
list
of
item(s),
which
has all
50-hour
interval inspection
items
and
those
100-
or
200-hour
interval
inspection
items
contained
in
the
wing.
Items from
other
areas
are
included
to
meet
their
required time
interval.
B.
Inspection
items
are
given
in
the
order
of
the
zone
in
which
the
inspection
is
to
be
completed.
A
general
description
of
the
inspection
required
and the
Item
Code
Numberfor
cross-reference
to
section
5-10-01
are
shown. Frequently,
the
tasks
define
more
specifically
the scope
and
extent
of
each
required
inspection.
These
tasks
are
printed
in
the
individual chapters
of
this
manual.
C.
The
right
portion
of each
page gives
space
for
the mechanic's
and
inspector's
initials
and
remarks.
A
copy
of
these
pages
can
be
used
as
a
checklist
when
these
inspections
are
completed.
2.
General
Inspection Criteria
A.
During
each
of
the
specified
inspection
tasks
in
this
section,
more
general
inspections
of
the
adjacent
areas must
be
done
while
access
is
available. These general inspections
are
used to
find
apparent
conditions
which
can
need
more
maintenance.
B. If a
component
or
system
is
changed
after
a
required
task
has
been
completed,
then
that specified
task
must
be
done
again
to make sure
it is
correct before
the
system
or
component
is
returned
to
service.
C.
Do
a
preflight inspection after
these
inspections
are
completed
to
make
sure
all
the
required
items
are
correctly
serviced.
Refer
to
the
Pilot's
Operating
Handbook
and
FAA
Approved
Airplane
Flight
Manual.
ITEM CODE
TASK
ZONE
MECH
INSP
REMARKS
NUMBER
611001
Spinner
-
Check general
condition
and
attachment.
110
611003
Propeller
Blades
-
Inspect for
cracks,
dents,
nicks,
110
scratches,
erosion,
corrosion,
or
other
damage.
611005
Propeller
Mounting
-
Check
for
security
of
110
installation.
611007
Propeller
Heat
Slip
Rings,
Brushes,
and
Boots
110
-
Inspect
for
condition,
and
security.
Perform
operational
check.
612001
Propeller Governor
and
Control
-
Inspect for
oil
110
and
grease
leaks.
If
leakage
is
evident,
refer
to
McCauley
Service
Manual.
242001
Alternator, Mounting
Bracket,
and
Electrical
120
Connections
-
Check
condition
and
security.
Check
alternator
belts for
condition
and
proper
adjustment.
Check
belt
tension.
5-12-03
Page
1
©
Cessna Aircraft
Company
Jul
3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
ITEM
CODE
TASK ZONE
MECH
INSP
REMARKS
NUMBER
710001
Turbocharger
(if
applicable)
-
Inspect
turbocharger
120
mounting brackets,
ducting,
linkage,
and
attaching
parts for
general
condition,
leakage
or
damage,
and
security
of
attachment.
Check
waste
gate,
actuator,
controller,
oil
and
vent
lines,
overboost
relief
valve,
and
compressor
housing for leakage,
apparent
damage,
security
of
attachment,
and
evidence
of
wear. Check waste gate
return
spring
for
condition
and security.
711001
Cowling and
Cowl
Flaps
-
Inspect
for
cracks,
dents,
120
other
damage
and
security
of
cowl
fasteners.
Check
cowl flaps
for
condition,
security,
and
operation.
Check
cowl
flap controls
for freedom
of
movement
through full
travel.
716001
Alternate Induction
Air
System
-
Check for
120
obstructions,
operation,
and
security.
716002
Induction
System
-
Check
security
of
clamps,
tubes,
120
and
ducting.
Inspect
for
evidence
of
leakage.
722001
Engine
-
Inspect
for
evidence
of
oil
and
fuel leaks.
120
Wash
engine
and
check
for
security
of
accessories.
722003
Hoses,
Metal Lines,
and
Fittings
-
Inspect
for signs
120
of
oil
and
fuel
leaks.
Check
for
abrasions,
chafing,
security,
proper
routing
and
support
and
for
evidence
of
deterioration.
723003
Engine
Baffles
and
Seals
-
Check condition
and
120
security
of
attachment.
781001
Exhaust System
-
Inspect
for
cracks
and
security.
120
Special
check
in
area
of heat
exchanger.
Refer
to
Chapter
78,
Exhaust
system
-
Maintenance
Practices.
781002
Exhaust System
(turbocharged
engine)
-
Inspect
120
couplings,
seals, clamps,
and
expansion
joints
for
cracks. Special
check
in
area
of
heat
exchanger.
Refer
to
Chapter
78,
Exhaust
System
-
Maintenance
Practices.
Note:
This
inspection
is
specifically
required
for
German
(LBA)
certification.
791001
Engine
Oil
-
Drain
oil
sump
and
oil
cooler.
Check for
120
metal
particles
or
foreign
material
in
filter,
on
sump
drain
plug,
and
on
engine
suction
screen.
Refer
to
Textron
Lycoming
Service
Bulletin
#
480C or
latest
revision. Replace
filter,
and refill
with
recommended
grade
aviation
oil.
792001
Oil Cooler
-
Check for
obstructions,
leaks, and
120
security
of
attachment.
801002
Bendix
Drive
Starter Assembly
-
Clean
and
lubricate
120
starter
drive
assembly.
5-12-03
Page
2
©
Cessna Aircraft Company
Jul
3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
ITEM
CODE
TASK
ZONE
MECH
INSP
REMARKS
NUMBER
761001
Engine
Controls
and
Linkage
-
Examine
the general
120,
225
condition
and
freedom
of
movement through
the
full
range.
Complete
a
check
for
the proper travel,
security
of
attachment,
and
for evidence
of
wear.
Complete
a
check
of
the friction
lock
and
vernier
adjustment
for
proper operation.
Complete
a
check
to
make sure
the
throttle,
fuel
mixture,
and
propeller
governor
arms
operate
through
their
full
arc
of
travel.
The
maximum
linear
freeplay
is
0.050
inch.
271001
Aileron Controls
-
Check
freedom
of
movement
and
120, 520,
proper
operation through
full
travel.
620
271002 Ailerons
and
Cables
-
Check
operation
and
security
120,
520,
of
stops.
Check
cables
for tension,
routing,
fraying,
620
corrosion,
and
turnbuckle
safety.
Check
travel
if
cable
tension
requires
adjustment
or
if
stops
are
damaged.
Check fairleads
and
rub
strips
for
condition.
231001
Communication
Antennas
and
Cables
-
Inspect
for
210
security
of
attachment,
connection,
and
condition.
341101
Static
System
-
Inspect
for
security
of
installation,
210
cleanliness,
and
evidence
of
damage.
521001
Doors
-
Inspect
general condition.
Check latches,
210
hinges,
and
seals
for
condition,
operation,
and
security
of
attachment.
531001
Fuselage Surface
-
Inspect for skin
damage,
loose 210
rivets,
condition
of
paint,
and
check
pitot-static
ports
and
drain
holes
for
obstruction.
Inspect
covers
and
fairings
for
security.
561001
Windows
and
Windshield
-
Inspect
general
210
condition.
Check
latches,
hinges,
and
seals
for
condition, operation,
and
security
of attachment.
214002
Heater
Components,
Inlets,
and
Outlets
-
Inspect
211
all
lines, ducts,
clamps,
seals,
and
gaskets
for
condition, restriction,
and
security.
251001
Seats
-
Examine the
seats
to
make
sure
they
are
211
serviceable
and
installed
correctly.
Make
sure
the
seat
stops
and
adjustment
mechanism
operate
correctly. Examine
the
seat
recline
control
and
attaching
hardware
to
make
sure
the
hardware
and
lock
are
not
damaged
and
are
correctly
installed.
Lubricate
the
threads
of the
Seat
Crank
Handle
Assembly
with
MIL-PRF-81322
general purpose
grease.
251101
Restraint
System,
front
and
rear
-
Check belts
211
for
thinning,
fraying,
cutting,
broken stitches,
or
ultra-violet
deterioration.
Check
system
hardware
for
security
of
installation.
5-12-03
Page
3
©
Cessna
Aircraft
Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
ITEM CODE
TASK
ZONE
MECH
INSP
REMARKS
NUMBER
311001
Instruments
-
Check
general condition
and
markings
220
for
legibility.
331001
Instrument
and
Cabin
Lights
-
Check operation,
220,
211,
condition
of
lens, and
security
of
attachment.
221
246002 Power
Junction
Box
-
Check
operation
and
222
condition. Check
availability
and
condition
of
spare
fuse
(if
applicable).
235002 Microphone
Push-To-Talk Switch
-
Clean
the
pilot's
222, 223
and
copilot's microphone
switches. Refer
to
Chapter
23, Communication
-
Maintenance Practices.
273001
Elevator
Control
-
Check
freedom
of
movement
and
222,
223
proper
operation
through
full
travel.
273002 Elevator Control
System
-
Inspect
pulleys,
cables,
222, 223
sprockets, bearings, chains,
and
turnbuckles
for
condition, security,
and
operation. Check cables
for
tension,
routing,
fraying,
corrosion,
and
turnbuckle
safety
273103
Elevator
Trim
Tab
and
Hinges
-
Check
condition,
224
security,
and
operation.
282003
Fuel
Selector
Valve
-
Check
controls
for detent
in
224
each
position,
security
of
attachment,
and
for
proper
placarding.
282006
Fuel
Selector -
Using
quick
drain,
ensure
no
224
contamination exists.
273101
Elevator
Trim
System
-
Check
cables,
push-pull
224,
240,
rods,
bellcranks,
pulleys, turnbuckles,
fairleads,
310
rub
strips,
etc.
for
proper
routing,
condition,
and
security.
262001
Portable Hand
Fire
Extinguisher
-
Inspect
for
230
proper
operating
pressure,
condition,
security
of
installation,
and
servicing
date.
256001
Emergency
Locator
Transmitter
-
Inspect
for
security
310
of
attachment
and
check
operation
by
verifying
transmitter output.
Check cumulative
time
and
useful
life
of
batteries
in
accordance
with
14
CFR
Part
91.207.
273004 Elevator
Downspring
-
Check
structure,
bolts,
310
linkage,
bell
crank,
and
push-pull
tube
for
condition,
operation,
and
security. Check
cables
for tension,
routing,
fraying, corrosion,
and
turnbuckle
safety.
Check
travels
if
cables
require
tension
adjustment
or
if
stops are
damaged.
5-12-03
Page
4
©
Cessna
Aircraft Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
ITEM CODE
TASK
ZONE
MECH
INSP
REMARKS
NUMBER
273104
Elevator
Trim
Tab
Actuator
-
Examine
the
free
320
play limits. Refer
to
Chapter
27,
Elevator
Trim
Control
-
Maintenance
Practices,
Trim
Tab
Free
Play
Inspection.
If
the
free
play
is
more
than
the
permitted
limits, lubricate
the
actuator
and
examine
the
free play limits
again.
If
the
free play
is
still
more
than
the
permitted limits,
replace
the
actuator.
273003
Elevator,
Hinges, Stops,
and
Cable
Attachment
-
320,
330
Check
condition,
security,
and
operation.
551001
Horizontal
Stabilizer
and Tailcone
structure
-
320,330
Inspect
bulkheads, spars,
ribs,
and
skins,
for
cracks,
wrinkles,
loose
rivets,
corrosion,
or
other
damage.
Inspect
horizontal
stabilizer
attach
bolts
for
looseness.
Retorque as necessary. Check
security
of
inspection
covers,
fairings,
and
tips.
551002
Horizontal
Stabilizer
and
Tips
-
Inspect
externally
for
320,
330
skin damage
and
condition
of
paint.
272001
Rudder
-
Check
internal
surfaces for
corrosion,
340
condition
of
fasteners,
and
balance weight
attachment.
272002
Rudder
-
Inspect
the rudder
skins
for
cracks
and
340
loose rivets, rudder
hinges
for
condition,
cracks
and
security;
hinge
bolts,
hinge
bearings,
hinge attach
fittings,
and
bonding
jumper
for
evidence
of
damage
and
wear,
failed
fasteners,
and
security.
Inspect
balance weight
for
looseness
and
the
supporting
structure
for
damage.
272003
Rudder, Tips,
Hinges,
Stops,
Clips and
Cable
340
Attachment
-
Check
condition,
security,
and
operation.
272005
Rudder Control
-
Check freedom
of
movement
and
340
proper
operation through
full
travel. Check
rudder
stops for damage
and
security.
553001
Vertical
Stabilizer
Fin
-
Inspect
bulkheads,
spars,
340
ribs,
and
skins
for
cracks,
wrinkles,
loose rivets,
corrosion,
or
other
damage. Inspect
vertical
stabilizer
attach bolts
for
looseness. Retorque
as
necessary.
Check
security
of
inspection
covers,
fairings,
and
tip.
553002
Vertical
Stabilizer
Fin
and
Tailcone
-
Inspect
340
externally
for skin damage
and
condition
of
paint.
334001
Navigation,
Beacon,
Strobe,
and
Landing
Lights
-
340,
520,
Check
operation, condition
of
lens,
and
security
of
620
attachment.
341103
Pitot
Tube
and Stall
Warning
Vane
-
Check for
510
condition
and
obstructions
and
verify
operation
of
anti-ice
heat.
5-12-03
Page
5
©
Cessna Aircraft
Company
Jul 3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE MANUAL
ITEM CODE
TASK
ZONE
MECH
INSP
REMARKS
NUMBER
571001
Wing
Surfaces
and
Tips
-
Inspect
for
skin
damage,
510,
520,
loose
rivets,
and
condition
of
paint.
610,
620
571003
Wing
Access
Plates
-
Check
for damage
and
security
510,
520,
of
installation.
610,
620
571004
Wing
Spar
and
Wing Strut
Fittings
-
Check
for
510,
520,
evidence
of
wear.
Check attach
bolts
for
indications
610,
620
of
looseness
and retorque as required.
571005
Wing
Structure
-
Inspect
spars,
ribs,
skins, and
510,
520,
stringers
for
cracks,
wrinkles,
loose rivets,
corrosion,
610, 620
or
other
damage.
275001
Flaps
-
Check tracks,
rollers,
and
control
rods
for
510,
610
security
of
attachment.
Check
rod
end
bearings
for
corrosion.
Check operation.
275003
Flap
Structure,
Linkage, Bellcranks,
Pulleys,
and
510,
610
Pulley Brackets
-
Check for
condition,
operation
and
security.
275004
Flaps
and
Cables
-
Check
cables
for proper
tension,
510,
610
routing,
fraying,
corrosion,
and
turnbuckle
safety.
Check
travel
if
cable
tension
requires
adjustment.
282001
Fuel
System
-
Inspect plumbing
and
components
for
510,
610
mounting and
security.
282002
Fuel
Tank
Vent Lines
and Vent
Valves
-
Check
vents
510,
610
for
obstruction
and
proper positioning.
Check
valves
for
operation.
282004
Integral Fuel
Bays
-
Check
for
evidence
of
leakage
510,
610
and
condition
of
fuel
caps, adapters,
and
placards.
Using
quick
drains, ensure
no
contamination
exists.
Check
quick
drains
for
proper shut
off.
282007
Fuel
Strainer,
Drain
Valve, and
Controls
-
Check
510,
610
freedom
of
movement,
security,
and
proper
operation.
Disassemble,
flush,
and
clean
screen
and
bowl.
571002
Wing Struts and Strut
Fairings
-
Check
for dents,
510,
610
cracks, loose
screws
and
rivets,
and
condition
of
paint.
271003
Aileron
Structure,
Control
Rods,
Hinges,
Balance
520,
620
Weights,
Bellcranks,
Linkage,
Bolts,
Pulleys,
and
Pulley
Brackets
-
Check
condition, operation,
and
security
of
attachment.
271004
Ailerons and Hinges
-
Check
condition,
security,
and
520, 620
operation
275005
Flap
Motor,
Actuator,
and
Limit
Switches
- Check
610
wiring
and
terminals
for
condition
and
security.
Check
actuator
for
condition
and
security.
5-12-03
Page
6
©
Cessna
Aircraft Company
Jul
3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
ITEM
CODE
TASK
NUMBER
275006
110000
Flap
Actuator
Threads
-
Clean
and
lubricate.
Refer
610
to
Chapter
12-21-03.
Interior
Placards,
Exterior
Placards,
Decals,
ALL
Markings
and
Identification
Plates
-
Inspect
for
security
of
installation
and
legibility.
Refer to
Chapter
11,
Placards
and
Markings
-
Inspection/Check.
***
End
of
Operation
3
Inspection
Items
***
5-12-03
Page
7
Jul
3/2006
©
Cessna Aircraft
Company
ZONE
MECH
INSP
REMARKS
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION
OPERATION
4
Date:
Registration
Number:
Serial
Number:
Total
Time:
1.
Description
A.
Operation
4
gives
a
list
of
item(s), which
has all
50-hour
interval
inspection
items
and
those
100-
or
200-hour
interval
inspection
items
contained
in
the
landing
gear.
Items from
other
areas
are
included
to
meet
their
required
time
interval.
B.
Inspection
items
are
given
in
the
order
of
the
zone
in
which
the
inspection
is
to
be
completed.
A
general
description
of the
inspection
required
and
the
Item
Code
Number
for cross-reference
to
section
5-10-01
are
shown. Frequently,
the
tasks
define
more
specifically
the scope
and
extent
of
each
required
inspection. These
tasks
are
printed
in
the
individual
chapters
of
this manual.
C.
The
right
portion
of
each
page
gives space
for
the
mechanic's
and
inspector's initials
and
remarks.
A
copy
of
these
pages
can
be
used
as
a
checklist
when these
inspections
are
completed.
2.
General
Inspection Criteria
A.
During
each
of
the
specified inspection tasks
in
this section,
more
general
inspections
of
the
adjacent
areas
must
be
done while
access
is
available.
These
general
inspections
are
used
to
find
apparent
conditions
which
can
need more
maintenance.
B. If a
component
or
system
is
changed after
a
required
task
has
been
completed,
then
that
specified
task
must
be
done
again
to
make sure
it is
correct
before
the
system or
component
is
returned
to
service.
C.
Do
a
preflight inspection
after
these
inspections
are
completed
to make
sure
all
the
required
items
are
correctly
serviced.
Refer
to the
Pilot's
Operating Handbook
and
FAA
Approved
Airplane
Flight
Manual.
ITEM CODE
TASK ZONE
MECH
INSP
REMARKS
NUMBER
611001
Spinner
-
Check
general
condition
and
attachment.
110
611002
Spinner
and
Spinner
Bulkhead
-
Remove
spinner,
110
wash,
and
inspect for cracks
and
fractures.
611003
Propeller
Blades
-
Inspect
for
cracks,
dents,
nicks,
110
scratches,
erosion,
corrosion,
or
other
damage.
611005
Propeller
Mounting
-
Check
for
security
of
110
installation.
611007
Propeller
Heat
Slip
Rings,
Brushes,
and
Boots
110
-
Inspect
for
condition,
and
security.
Perform
operational check.
612001
Propeller
Governor
and
Control
-
Inspect
for
oil
110
and
grease
leaks.
If
leakage
is
evident,
refer
to
McCauley
Service
Manual.
214001
Cold
and
Hot
Air
Hoses
-
Check
condition,
routing,
120
and
security.
5-12-04
Page
1
©
Cessna
Aircraft
Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
ITEM
CODE
TASK
ZONE
MECH
INSP
REMARKS
NUMBER
242001
Alternator,
Mounting
Bracket,
and
Electrical
120
Connections
-
Check
condition
and
security.
Check
alternator
belts
for condition
and
proper
adjustment.
Check belt
tension.
282010
Auxiliary
(Electric)
Fuel
Pump
-
Check
pump
and
120
fittings for condition,
operation,
security.
371001
Vacuum
System
-
Inspect
for
condition
and
security.
120
371002
Vacuum
Pumps
-
Check
for
condition
and
security.
120
Check
vacuum
system
breather
line
for
obstructions,
condition,
and
security.
371003
Vacuum
System Hoses
-
Inspect
for
hardness,
120
deterioration, looseness, or collapsed
hoses.
371004
Gyro
Filter
-
Inspect
for
damage,
deterioration
and
120
contamination.
Clean
or
replace
if
required.
710001
Turbocharger
(if
applicable) -
Inspect
turbocharger
120
mounting brackets, ducting,
linkage, and
attaching
parts
for general
condition,
leakage
or
damage,
and
security
of
attachment. Check
waste
gate,
actuator,
controller,
oil
and
vent
lines,
overboost
relief
valve,
and
compressor
housing
for
leakage,
apparent
damage,
security
of
attachment,
and
evidence
of
wear.
Check
waste
gate return
spring
for
condition
and
security.
711001
Cowling and
Cowl Flaps
-
Inspect for
cracks, dents,
120
other
damage
and
security
of
cowl
fasteners.
Check
cowl
flaps for
condition,
security,
and
operation.
Check
cowl
flap controls
for
freedom
of
movement
through
full
travel.
716001
Alternate
Induction
Air System
-
Check
for
120
obstructions,
operation,
and
security.
716002
Induction System
-
Check
security
of
clamps,
tubes,
120
and
ducting. Inspect for
evidence
of
leakage.
716003
Induction Airbox,
Valves,
Doors,
and
Controls
-
120
Remove
air
filter
and
inspect
hinges,
doors,
seals,
and
attaching
parts
for
wear
and
security.
Check
operation.
716004
Induction
Air
Filter
-
Remove
and
clean.
Inspect
for
120
damage
and
service.
722001
Engine
-
Inspect
for
evidence
of
oil
and
fuel
leaks.
120
Wash
engine
and
check
for
security
of
accessories.
722002
Crankcase,
Oil Sump,
and
Accessory
Section
-
120
Inspect
for
cracks
and
evidence
of
oil
leakage.
Check
bolts
and
nuts
for
looseness
and
retorque
as
necessary.
Check crankcase
breather
lines
for
obstructions,
security,
and
general
condition.
5-12-04
Page
2
©
Cessna
Aircraft Company
Jul 3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
ITEM
CODE
TASK
ZONE
MECH
INSP
REMARKS
NUMBER
722003
Hoses,
Metal
Lines,
and
Fittings
-
Inspect
for
signs
120
of
oil
and fuel
leaks.
Check
for
abrasions,
chafing,
security,
proper
routing
and
support
and
for
evidence
of
deterioration.
723001
Engine
Cylinders,
Rocker
Box
Covers,
and
Pushrod
120
Housings
- Check
for
fin
damage,
cracks,
oil
leakage,
security
of
attachment,
and
general
condition.
723003
Engine Baffles
and
Seals
-
Check
condition
and
120
security
of
attachment.
723004
Cylinder
Compression
-
Complete
a
differential
120
compression
test.
If
there
is
weak
cylinder
compression,
refer
to
Chapter
71,
Engine
-
Troubleshooting,
for
further
procedures.
730001
Engine-Driven
Fuel
Pump
-
Check
for
evidence
120
of
leakage,
security
of
attachment,
and
general
condition.
730002
Fuel
Injection
System
-
Check
system
for
security
120
and
condition.
Clean
fuel
inlet
screen,
check
and
clean
injection
nozzles
and
screens
(if
evidence
of
contamination
is
found),
and
lubricate
air
throttle
shaft.
730003
Idle
and
Mixture
-
Run
the
airplane engine
to
120
determine
satisfactory
performance.
If
required,
adjust the
idle
rpm
and fuel
mixture.
Refer
to
Chapter
73,
Fuel
Injection
Systems
-
Maintenance
Practices.
741001
Magnetos
-
Examine the
external condition
and
for
120
correct
installation
and
condition
of the
electrical
leads.
Complete
a
check
of
the
engine
timing
(external
timing).
You
must set
the internal
timing
if
the
total
of
all
external
adjustments
are
more
than
0.125
inch
(3.17
mm)
from
the
original factory
position, or
between
each
of
the
internal timing
adjustments. Refer
to
Chapter
74,
Ignition
System
-
Maintenance
Practices.
742001
Ignition
Harness
and Insulators
-
Check
for
proper
120
routing,
deterioration,
and
condition
of
terminals.
742002
Spark
Plugs
-
Remove,
clean,
analyze,
test,
gap,
120
and rotate
top
plugs
to
bottom
and bottom
plugs
to
top.
743001
Ignition Switch and
Electrical
Harness
-
Inspect
for
120
damage,
condition,
and
security.
781001
Exhaust
System
-
Inspect
for
cracks
and
security.
120
Special
check
in
area of
heat
exchanger.
Refer
to
Chapter
78,
Exhaust
system
-
Maintenance
Practices.
5-12-04
Page
3
©
Cessna
Aircraft
Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
ITEM
CODE
TASK
ZONE
MECH
INSP
REMARKS
NUMBER
781002
Exhaust
System (turbocharged
engine)
-
Inspect
120
couplings,
seals,
clamps,
and
expansion joints
for
cracks.
Special
check
in
area
of heat
exchanger.
Refer
to
Chapter
78,
Exhaust
System
-
Maintenance
Practices.
Note:
This
inspection
is
specifically
required
for
German
(LBA)
certification.
791001
Engine
Oil
-
Drain
oil
sump and
oil
cooler.
Check
for
120
metal
particles
or
foreign
material
in
filter,
on
sump
drain
plug,
and
on
engine
suction
screen.
Refer
to
Textron
Lycoming Service
Bulletin
#
480C or
latest
revision.
Replace
filter,
and
refill
with
recommended
grade
aviation
oil.
792001
Oil
Cooler
-
Check
for
obstructions,
leaks,
and
120
security
of
attachment.
801001
Starter
and
Electrical Connections
-
Check security
120
and
condition
of
starter,
electrical connection,
and
cable.
801002
Bendix Drive
Starter Assembly
-
Clean
and
lubricate
120
starter
drive
assembly.
761001
Engine
Controls
and
Linkage
-
Examine
the
general
120,
225
condition
and
freedom
of
movement
through
the
full
range.
Complete
a
check
for
the
proper
travel,
security
of
attachment,
and
for
evidence
of
wear.
Complete
a
check
of the
friction
lock
and
vernier
adjustment for
proper operation.
Complete
a
check
to
make
sure
the
throttle,
fuel
mixture,
and
propeller
governor
arms
operate
through
their
full
arc
of
travel.
The
maximum
linear freeplay
is
0.050
inch.
324002
Brakes,
Master Cylinders,
and
Parking
Brake
224,
230
-
Check
master
cylinders
and
parking brake
mechanism
for
condition
and
security.
Check
fluid
level
and
test
operation
of
toe
and
parking
brake.
Refer
to
Chapter
12-13-00
for
servicing instructions.
251002
Seat
Tracks
and
Stops
-
Inspect seat
tracks
for
230
condition
and
security
of
installation. Check seat
track
stops
for damage
and
correct location.
Inspect
seat
rails
for
cracks.
324001
Brakes
-
Test
toe
brakes
and
parking
brake
for
proper
230
operation.
243001
Main
Battery
-
Examine the general
condition
and
310
security.
Complete
a
check
of
the
level
of
electrolyte.
Refer
to
Chapter
12,
Battery
-
Servicing.
243002
Main
Battery
Box
and
Cables
-
Clean
and remove
310
any
corrosion.
Examine the
cables for
routing,
support, and
security
of
the
connections.
341103
Pitot
Tube
and
Stall
Warning
Vane
-
Check
for
510
condition
and
obstructions
and
verify operation
of
anti-ice
heat.
5-12-04
Page
4
©
Cessna
Aircraft
Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
ITEM
CODE
TASK
ZONE
MECH
INSP
REMARKS
NUMBER
322001
Nose
Gear
-
Inspect
torque
links,
steering
rods,
720
and
boots for condition
and
security
of
attachment.
Check
strut for evidence
of
leakage
and proper
extension.
Check
strut
barrel
for
corrosion,
pitting,
and
cleanliness.
Check
shimmy
damper
and/or
bungees for
operation, leakage, and
attach points
for
wear
and
security.
322002
Nose
Landing
Gear
Wheel
Fairings
-
Check
for
720
cracks,
dents,
and
condition
of
paint.
322003
Nose
Gear
Fork
-
Inspect
for
cracks,
general
720
condition,
and
security
of
attachment.
322004
Nose
Gear Attachment
Structure
-
Inspect
for
720
cracks,
corrosion,
or
other
damage
and
security
of
attachment.
325001
Nose
Gear Steering
Mechanism
-
Check
for
wear,
720
security,
and
proper
rigging.
324004
Tires
-
Check
tread wear
and
general
condition.
720,
721,
Check
for
proper
inflation.
722
324006
Wheel Bearings
-
Clean,
inspect
and
lube. 720,
721,
722
321003
Main
Landing Gear Attachment
Structure
-
Check
721,
722
for damage,
cracks,
loose
rivets,
bolts
and
nuts
and
security
of
attachment.
324005
Wheels,
Brake
Discs,
and
Linings
-
Inspect
for
wear,
721, 722
cracks,
warps,
dents,
or
other damage.
Check
wheel
through-bolts
and
nuts
for
looseness.
321001 Main
Landing Gear
Wheel Fairings and
Brake
721,722
Fairings
-
Check
for
cracks, dents,
and
condition
of
paint.
110000
Interior
Placards,
Exterior
Placards,
Decals,
ALL
Markings and Identification
Plates
-
Inspect
for
security
of
installation
and
legibility.
Refer
to
Chapter
11,
Placards
and
Markings
-
Inspection/Check.
***
End
of
Operation
4
Inspection
Items
***
5-12-04
Page
5
©
Cessna
Aircraft
Company
Jul
3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION
OPERATION
5
Date:
Registration
Number:
Serial
Number:
Total
Time:
1.
Description
A.
Operation
5
gives
a
list
of
item(s), which
are
completed every
400
hours or
1
year,
whichever
occurs
first.
B.
Inspection
items
are
given
in
the
order
of
the
zone
in
which
the
inspection
is
to
be
completed.
A
general
description
of
the inspection
required
and
the
Item
Code
Number for
cross-reference
to
section
5-10-01
are shown.
Frequently,
the
tasks
define
more
specifically
the
scope and extent
of
each
required
inspection.
These
tasks
are
printed
in
the
individual
chapters
of
this
manual.
C.
The
right
portion
of
each
page
gives
space
for
the
mechanic's
and
inspector's
initials
and
remarks.
A
copy
of
these
pages
can
be
used
as
a
checklist
when these
inspections
are
completed.
2.
General
Inspection Criteria
A.
During
each
of
the
specified
inspection
tasks
in
this
section,
more
general
inspections
of
the
adjacent
areas must
be
done
while
access
is
available. These
general
inspections
are
used
to
find
apparent
conditions
which
can need
more
maintenance.
B. If
a
component
or
system
is
changed
after
a
required
task
has been
completed,
then
that
specified
task
must
be
done
again
to
make sure
it
is
correct before the
system
or
component
is
returned
to
service.
C.
Do
a
preflight inspection
after
these
inspections
are
completed
to
make
sure
all
the
required
items
are
correctly
serviced.
Refer
to
the
Pilot's
Operating Handbook
and
FAA
Approved Airplane
Flight
Manual.
ITEM
CODE
TASK ZONE
MECH
INSP REMARKS
NUMBER
212001
Ventilation
System
-
Inspect clamps,
hoses, and
211
valves
for
condition
and
security.
252201
Upholstery,
Headliner,
Trim,
and
Carpeting
-
Check
211
condition
and
security.
324003
Brake
Lines,
Wheel Cylinders,
Hoses, Clamps,
and
721,
722
Fittings
-
Check
for
leaks,
condition,
and
security
and
hoses
for
bulges
and
deterioration.
Check
brake
lines
and
hoses
for
proper
routing
and
support.
***
End
of
Operation
5
Inspection
Items
**
5-12-05
Page
1
©
Cessna
Aircraft
Company
Jul 3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
PROGRESSIVE
CARE
1.
Operation
6
THERE
ARE
CURRENTLY
NO
PROGRESSIVE
CARE
OPERATIONS
CONTAINED
IN
THIS
SECTION.
5-12-06
Page
1
©
Cessna Aircraft
Company
April
1/2002
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION OPERATION
7
Date:
Registration
Number:
Serial Number:
Total
Time:
1.
Description
A.
Operation
7
gives
a
list
of
item(s),
which
are
completed
every
600 hours
or
1
year,
whichever occurs
first.
B.
Inspection
items
are given
in
the
order of
the
zone
in
which
the
inspection
is
to
be
completed.
A
general
description
of
the
inspection
required
and
the
Item
Code
Number
for
cross-reference
to
section
5-10-01
are
shown. Frequently,
the
tasks
define
more
specifically
the
scope
and
extent
of
each
required
inspection. These
tasks
are
printed
in
the
individual
chapters
of
this
manual.
C.
The
right
portion
of
each
page
gives space for
the
mechanic's
and
inspector's
initials
and
remarks.
A
copy
of
these
pages
can
be
used
as
a
checklist
when
these
inspections
are
completed.
2.
General
Inspection
Criteria
A.
During
each
of
the
specified
inspection
tasks
in
this section,
more
general
inspections
of the
adjacent
areas
must
be
done while
access
is
available. These
general
inspections
are
used
to
find
apparent
conditions
which
can
need more
maintenance.
B.
If
a
component
or
system
is
changed after
a
required
task
has been
completed, then that
specified
task
must
be
done
again
to
make
sure
it
is
correct
before
the
system or
component
is
returned
to
service.
C.
Do
a
preflight
inspection
after
these
inspections
are
completed
to
make
sure
all
the
required
items
are
correctly serviced.
Refer
to
the
Pilot's
Operating Handbook
and
FAA
Approved
Airplane
Flight
Manual.
ITEM
CODE
NUMBER
282008
221001
TASK
ZONE
MECH
INSP
Fuel
Quantity
Indicators
-
Examine
for
damage
and
security
of
installation.
Complete
a
fuel
quantity
calibration
check.
Refer
to
Chapter 28,
Fuel
Storage
and
Distribution
-
Maintenance
Practices.
Autopilot
Rigging
-
Refer to
Autopilot
-
Maintenance
Practices.
***
End of
Operation
7
Inspection
Items
***
©
Cessna
Aircraft
Company
REMARKS
220
610
5-12-07
Page
1
Jul 3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
PROGRESSIVE
CARE
1.
Operation
8
THERE
ARE
CURRENTLY
NO
PROGRESSIVE
CARE
OPERATIONS
CONTAINED
IN
THIS
SECTION.
5-12-08
Page
1
©
Cessna Aircraft Company
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION OPERATION
9
Date:
Registration
Number:
Serial
Number:
Total
Time:
1.
Description
A.
Operation
9
gives
a
list
of
item(s),
which
are
completed
every 500 hours.
B.
Inspection
items
are
given
in
the
order
of
the
zone
in
which
the
inspection
is
to
be
completed.
A
general
description
of
the
inspection
required
and the
Item
Code
Number
for
cross-reference
to
section
5-10-01
are
shown.
Frequently,
the
tasks
define
more
specifically
the
scope
and
extent
of each
required
inspection.
These tasks
are
printed
in
the
individual
chapters
of
this manual.
C.
The
right
portion
of
each
page
gives
space
for
the
mechanic's
and
inspector's initials
and
remarks.
A
copy
of
these
pages
can
be
used
as
a
checklist
when
these
inspections
are
completed.
2.
General
Inspection
Criteria
A.
During
each
of
the
specified inspection tasks
in
this
section,
more
general
inspections
of
the
adjacent
areas
must
be
done while
access
is
available.
These
general
inspections
are used
to
find
apparent
conditions which
can
need
more
maintenance.
B. If a
component
or
system
is
changed
after
a
required
task
has
been
completed,
then
that
specified
task
must
be
done again
to
make
sure
it is
correct
before
the
system or
component
is
returned
to
service.
C.
Do
a
preflight inspection
after
these
inspections
are
completed
to
make
sure
all
the
required
items
are
correctly serviced.
Refer
to the
Pilot's
Operating
Handbook
and
FAA
Approved
Airplane
Flight
Manual.
ITEM
CODE
TASK
ZONE
MECH
INSP
REMARKS
NUMBER
741002
Magnetos
-
Clean,
examine,
and
adjust
as
120
necessary.
Do
the
500-hour
inspection
in
accordance
with
the
Slick
4300/6300
Series
Magneto
Maintenance
and
Overhaul
Manual.
***
End
of
Operation
9
Inspection
Items
***
5-12-09
Page
1
©
Cessna Aircraft
Company Jul
3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION
OPERATION
10
Date:
Registration Number:
Serial Number:
Total
Time:
1.
Description
A.
Operation
10
gives
a
list
of
item(s),
which
are
completed
every
1000
hours.
B.
Inspection
items
are
given
in
the
order
of
the zone
in
which
the
inspection
is
to
be
completed.
A
general
description
of
the
inspection
required
and
the
Item
Code
Number for
cross-reference
to
section
5-10-01
are
shown.
Frequently,
the
tasks
define
more
specifically
the
scope
and
extent
of
each
required
inspection. These tasks
are
printed
in
the
individual chapters
of
this manual.
C.
The
right
portion
of
each page
gives
space
for
the
mechanic's
and
inspector's initials
and
remarks.
A
copy
of
these
pages
can
be
used
as
a
checklist
when
these
inspections
are
completed.
2.
General
Inspection Criteria
A.
During
each
of the
specified inspection
tasks
in
this
section,
more
general
inspections
of
the
adjacent
areas
must
be
done
while
access
is
available.
These
general
inspections
are
used to
find
apparent
conditions
which
can
need
more
maintenance.
B. If a
component
or
system
is
changed
after
a
required
task
has
been
completed,
then that
specified
task
must
be
done
again
to make sure
it is
correct
before
the
system
or
component
is
returned
to
service.
C.
Do
a
preflight
inspection after these
inspections
are
completed
to
make
sure
all
the
required
items
are
correctly
serviced.
Refer
to
the Pilot's
Operating Handbook
and
FAA
Approved Airplane
Flight
Manual.
ITEM CODE
TASK
ZONE
MECH
INSP
REMARKS
NUMBER
282009
Integral
Fuel
Bays
-
Drain
the
fuel
(Refer
to
Chapter
510,
610
12,
Fuel
-
Servicing)
and purge
tanks
(Refer
to the
Single
Engine
Structural Repair
Manual,
1996
and
On).
Complete
an
inspection
of
the
tank
interior
and
outlet screens
and
remove
any foreign
object
debris.
Complete
an
inspection
of
the
tank
interior
surfaces
for
sealant
deterioration
and
corrosion (especially
in
the sump
areas).
***
End
of
Operation
10
Inspection
Items
***
5-12-10
Page
1
©
Cessna
Aircraft
Company
Jul 3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION
OPERATION
11
Date:
Registration
Number:
Serial
Number:
Total
Time:
1.
Description
A.
Operation
11
gives
a
list of
item(s),
which
are
completed every
2
years.
B.
Inspection
items
are
given
in
the
order
of the
zone
in
which
the
inspection
is
to be
completed.
A
general
description
of
the
inspection
required
and
the
Item
Code
Number
for
cross-reference
to
section
5-10-01
are shown. Frequently,
the
tasks
define
more
specifically
the
scope
and
extent
of
each
required
inspection.
These tasks
are
printed
in
the
individual chapters
of
this
manual.
C.
The
right
portion
of
each
page gives
space for
the
mechanic's
and
inspector's
initials
and
remarks.
A
copy
of
these
pages
can
be
used
as
a
checklist
when
these
inspections
are
completed.
2.
General
Inspection
Criteria
A.
During
each
of
the
specified
inspection
tasks
in
this
section,
more
general
inspections
of
the
adjacent
areas
must
be
done
while access
is
available. These
general
inspections
are
used
to
find
apparent
conditions which
can need
more
maintenance.
B. If
a
component
or
system
is
changed
after
a
required
task
has
been
completed,
then that
specified
task
must
be
done
again
to make
sure
it is
correct
before the
system
or
component
is
returned
to
service.
C.
Do
a
preflight inspection
after these
inspections
are
completed
to make
sure
all
the
required
items
are
correctly
serviced.
Refer
to
the
Pilot's
Operating
Handbook
and
FAA
Approved Airplane
Flight
Manual.
ITEM CODE
TASK
ZONE
MECH
INSP
REMARKS
NUMBER
341102
Pitot
and
Static
System
-
Examine
in
accordance
220
with
14
CFR Part 91.411.
246003 Alternator
Control
Unit
-
Complete the
Over-voltage
222
Protection
Circuit
Test.
Refer to
Chapter
24,
Alternator
Control
Unit.
***
End
of
Operation
11
Inspection
Items
***
5-12-11
Page
1
Jul
3/2006
0
Cessna
Aircraft
Company
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
PROGRESSIVE
CARE
1.
Operation
13
THERE
ARE
CURRENTLY
NO
PROGRESSIVE
CARE
OPERATIONS
CONTAINED
IN
THIS
SECTION.
5-12-13
Page
1
©
Cessna
Aircraft
Company
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION OPERATION
14
Date:
Registration
Number:
Serial
Number:
Total
Time:
1.
Description
A.
Operation
14
gives
a
list
of
item(s),
which
are
completed every
2
years,
or
anytime
components
are
added
or
removed from
the
airplane
which
have
the
potential
to
affect
the
magnetic
accuracy
and/or
variation
of
the compass calibration,
or
anytime the
accuracy
of
the
compass
is in
question.
B.
Inspection
items
are
given
in
the
order
of
the zone
in
which
the
inspection
is
to
be
completed.
A
general
description
of
the
inspection
required
and the
Item
Code
Number for
cross-reference
to
section
5-10-01
are
shown.
Frequently,
the
tasks
define
more
specifically
the
scope
and
extent
of
each
required
inspection.
These tasks
are
printed
in
the
individual chapters
of
this manual.
C.
The
right
portion
of
each
page
gives space
for
the
mechanic's
and
inspector's
initials
and
remarks.
A
copy
of
these
pages
can
be
used
as
a
checklist
when
these
inspections
are
completed.
2.
General
Inspection
Criteria
A.
During
each
of
the
specified
inspection
tasks
in
this
section,
more
general inspections
of
the
adjacent
areas
must
be
done while
access
is
available.
These general
inspections
are
used
to
find
apparent
conditions which
can
need
more
maintenance.
B. If a
component
or system
is
changed
after
a
required
task
has
been
completed,
then
that
specified
task
must
be
done
again
to make
sure
it is
correct
before the
system
or
component
is
returned
to
service.
C.
Do
a
preflight inspection
after
these
inspections
are
completed
to
make
sure
all
the
required
items
are
correctly
serviced.
Refer
to
the
Pilot's
Operating Handbook
and
FAA
Approved Airplane
Flight
Manual.
ITEM
CODE
NUMBER
342102
TASK
Magnetic Compass
-
Calibrate.
***
End
of
Operation
14
Inspection
Items
***
ZONE
MECH
INSP
REMARKS
220
5-12-14
Page
1
Jul
3/2006
©
Cessna
Aircraft
Company
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION
OPERATION
15
Date:
Registration Number:
Serial
Number:
Total
Time:
1.
Description
A.
Operation
15
gives
a
list
of
item(s),
which
are
completed
every
2000
hours.
B.
Inspection
items
are
given
in
the
order
of
the zone
in
which
the
inspection
is
to
be
completed.
A
general
description
of
the inspection
required
and the
Item
Code
Number
for
cross-reference
to
section
5-10-01
are
shown. Frequently,
the
tasks
define
more
specifically
the
scope
and
extent
of
each
required
inspection. These tasks
are
printed
in
the
individual
chapters
of
this
manual.
C.
The
right
portion
of
each
page
gives
space
for
the
mechanic's
and
inspector's
initials
and
remarks.
A
copy
of
these
pages
can
be
used
as
a
checklist
when
these
inspections
are
completed.
2.
General
Inspection Criteria
A.
During
each
of
the
specified
inspection tasks
in
this section,
more
general
inspections
of
the
adjacent
areas must
be
done
while access
is
available.
These
general
inspections
are
used
to
find apparent
conditions
which
can
need
more
maintenance.
B. If a
component or system
is
changed
after
a
required
task
has
been
completed,
then
that
specified
task
must
be
done
again
to
make
sure
it is
correct
before
the system
or
component
is
returned
to
service.
C.
Do
a
preflight
inspection
after
these
inspections
are
completed
to
make
sure
all
the required
items
are
correctly
serviced.
Refer
to
the
Pilot's
Operating
Handbook
and
FAA
Approved
Airplane
Flight
Manual.
ITEM
CODE
TASK
ZONE
MECH
INSP
REMARKS
NUMBER
612003
Propeller
Control
Cable
-
Non-repairable
item
and
120,210
must
be
replaced
at
every
interval
or
whenever
maximum
linear
movement exceeds 0.050
inch.
Refer
to
Chapter 61-20-00,
Propeller
Control
Cable.
743002
Inspect
and
lubricate
ACS
brand
ignition
switch.
224
Refer
to
Chapter
74,
Ignition System
-
Maintenance
Practices.
***
End
of
Operation
15
Inspection
Items
***
5-12-15
Page
1
©
Cessna
Aircraft Company
Jul 3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION OPERATION
16
Date:
Registration
Number:
Serial
Number:
Total
Time:
1.
Description
A.
Operation
16
gives
a
list
of
item(s),
which
are
completed every
1000
hours
or
1
year,
whichever occurs
first.
B.
Inspection
items
are given
in
the
order
of the
zone
in
which
the
inspection
is
to
be
completed.
A
general
description
of
the
inspection
required and
the
Item Code
Number
for
cross-reference
to
section
5-10-01
are
shown.
Frequently,
the
tasks
define
more
specifically
the
scope
and
extent
of
each
required
inspection.
These
tasks
are
printed
in
the
individual chapters
of
this manual.
C.
The
right portion
of
each
page
gives
space
for
the
mechanic's
and
inspector's
initials
and
remarks.
A
copy
of
these
pages
can
be
used
as
a
checklist
when
these
inspections
are
completed.
2.
General
Inspection Criteria
A.
During
each
of
the
specified
inspection
tasks
in
this
section,
more
general
inspections
of the
adjacent
areas
must
be
done
while
access
is
available.
These
general
inspections
are
used to
find
apparent
conditions
which
can
need
more
maintenance.
B. If
a
component or
system
is
changed after
a
required
task
has
been
completed,
then
that
specified
task
must
be
done
again
to make
sure
it
is
correct
before
the
system
or
component
is
returned
to
service.
C.
Do
a
preflight
inspection after
these
inspections
are
completed to
make sure
all
the
are
correctly
serviced.
Refer
to the
Pilot's
Operating Handbook
and
FAA
Approved
Manual.
required
items
Airplane
Flight
ITEM
CODE
NUMBER
221002
221003
TASK
Autopilot
Servo
Capstan
Assemblies.
Check
slip-clutch
torque
settings. Refer
to
Autopilot
-
Maintenance
Practices.
Autopilot
Servo Actuators.
Inspect for
evidence
of
corrosion
and
or
buildup
of
dirt
or
other
particulate
matter
which
may
interfere
with
servo
operation.
Refer
to
Autopilot
-
Maintenance Practices.
***
End
of
Operation
16
Inspection
Items
***
ZONE
MECH
INSP
610
610
5-12-16
Page
1
Jul 3/2006
©
Cessna Aircraft
Company
REMARKS
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION
OPERATION
17
Date:
Registration
Number:
Serial
Number:
Total
Time:
1.
Description
A.
Operation
17
gives
a
list
of
item(s),
which
are
completed every
12
calendar
months.
B.
Inspection
items
are
given
in
the
order
of
the zone
in
which
the
inspection
is
to
be
completed.
A
general
description
of
the
inspection
required
and
the
Item
Code
Number
for
cross-reference
to
section
5-10-01
are
shown. Frequently,
the
tasks
define
more
specifically
the scope
and
extent
of each
required
inspection. These
tasks
are
printed
in
the
individual
chapters
of
this manual.
C.
The
right
portion
of
each
page
gives
space
for
the
mechanic's
and inspector's
initials
and
remarks.
A
copy
of
these
pages
can
be
used
as
a
checklist
when
these inspections
are
completed.
2.
General
Inspection
Criteria
A.
During
each
of
the
specified
inspection tasks
in
this
section,
more
general
inspections
of the
adjacent
areas
must
be
done
while
access
is
available. These
general
inspections
are
used to
find
apparent
conditions
which
can
need more
maintenance.
B.
If
a
component
or
system
is
changed
after
a
required
task
has been
completed,
then that
specified
task
must
be
done
again to
make
sure
it
is
correct
before
the system
or
component
is
returned
to
service.
C.
Do
a
preflight
inspection
after
these inspections
are
completed
to
make
sure
all
the
required
items
are
correctly
serviced.
Refer
to
the Pilot's
Operating
Handbook
and
FAA
Approved
Airplane
Flight
Manual.
TASK
Cockpit
Mounted
Halon
Type
Fire
Extinguisher-
Weigh bottle.
Bottle
must
be
reserviced
by
qualified
individual
if
more
than
2
ounces
is
lost.
***
End
of
Operation
17
Inspection
Items
***
©
Cessna
Aircraft
Company
ZONE
MECH
INSP
REMARKS
211
5-12-17
Page
1
Jul
3/2006
ITEM CODE
NUMBER
262002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION
OPERATION
18
Date:
Registration
Number:
Serial Number:
Total
Time:
1.
Description
A.
Operation
18
gives
a
list
of
item(s),
which
are
completed
every
6
years.
B.
Inspection
items
are
given
in
the order
of the
zone
in
which
the
inspection
is
to
be
completed.
A
general
description
of
the
inspection
required
and
the
Item
Code
Number
for
cross-reference
to
section
5-10-01
are
shown.
Frequently, the
tasks
define
more
specifically
the
scope
and
extent
of
each
required
inspection. These
tasks
are
printed
in
the
individual
chapters
of
this
manual.
C.
The
right
portion
of
each
page
gives
space
for
the
mechanic's
and
inspector's initials
and
remarks.
A
copy
of
these
pages
can
be
used
as
a
checklist
when
these inspections
are
completed.
2.
General
Inspection Criteria
A.
During
each
of
the specified
inspection
tasks
in
this
section,
more
general
inspections
of
the
adjacent
areas
must
be
done
while
access
is
available. These
general
inspections
are used
to
find
apparent
conditions
which
can
need
more
maintenance.
B. If
a
component or
system
is
changed
after
a
required
task
has
been
completed,
then
that
specified
task
must
be
done
again
to make sure
it is
correct
before
the
system
or
component
is
returned
to
service.
C.
Do
a
preflight inspection
after these inspections
are
completed
to make sure
all
the
required
items
are
correctly serviced.
Refer
to the
Pilot's
Operating
Handbook
and
FAA
Approved
Airplane
Flight
Manual.
ITEM
CODE
NUMBER
262004
TASK
Cockpit
Mounted
Halon
Type
Fire
Extinguishers
-
Empty,
inspect
for
damage,
and
recharge.
***
End of
Operation
18
Inspection
Items
***
ZONE
MECH
INSP
211
5-12-18
Page
1
Jul
3/2006
©
Cessna
Aircraft
Company
REMARKS
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION
OPERATION
19
Date:
Registration
Number:
Serial
Number:
Total
Time:
1.
Description
A.
Operation
19
gives
a
list of
item(s), which
are
completed
every
12
years.
B.
Inspection
items
are
given
in
the
order
of
the zone
in
which the
inspection
is
to
be
completed.
A
general
description
of
the
inspection
required
and
the
Item
Code
Number for
cross-reference
to
section
5-10-01
are
shown.
Frequently,
the
tasks
define
more
specifically
the
scope
and
extent
of
each
required
inspection. These
tasks
are
printed
in
the
individual
chapters
of
this
manual.
C.
The
right
portion
of
each
page gives
space
for
the
mechanic's
and
inspector's initials
and
remarks.
A
copy
of
these
pages
can
be
used
as
a
checklist
when
these inspections
are
completed.
2.
General
Inspection Criteria
A.
During
each
of
the
specified inspection
tasks
in
this
section,
more
general
inspections
of
the
adjacent
areas
must
be
done while
access
is
available.
These
general
inspections
are
used
to
find
apparent
conditions
which can
need
more
maintenance.
B. If a
component or
system
is
changed after
a
required
task
has been
completed,
then
that specified
task
must
be
done again
to
make
sure
it is
correct
before
the
system
or
component
is
returned
to
service.
C.
Do
a
preflight inspection
after
these inspections
are
completed
to
make sure
all
the required
items
are
correctly
serviced.
Refer
to
the
Pilot's
Operating Handbook
and
FAA
Approved
Airplane
Flight
Manual.
ITEM
CODE
NUMBER
262003
TASK
Cockpit
Mounted
Halon
Type
Fire
Extinguishers
-
Perform
hydrostatic
test.
The
hydrostatic
test
shall
be
at
twelve-year
intervals
based
on
initial
servicing
or
date
of
last
hydrostatic
test.
***
End
of
Operation
19
Inspection
Items
***
ZONE
MECH
INSP
REMARKS
211
5-12-19
Page
1
Jul
3/2006
©
Cessna
Aircraft
Company
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION OPERATION
20
Date:
Registration
Number:
Serial
Number:
Total
Time:
1.
Description
A.
Operation
20
gives
a
list
of
item(s),
which
are
completed
every
1
year.
B.
Inspection
items
are
given
in
the
order
of
the zone
in
which
the
inspection
is
to
be
completed.
A
general
description
of the
inspection
required
and
the
Item
Code
Number for
cross-reference
to
section
5-10-01
are shown.
Frequently,
the
tasks define
more
specifically
the scope
and
extent
of each
required
inspection.
These
tasks
are
printed
in
the
individual chapters
of
this
manual.
C.
The
right
portion
of
each page gives
space for
the mechanic's
and
inspector's
initials
and
remarks.
A
copy
of
these
pages
can
be
used
as
a
checklist
when
these
inspections
are
completed.
2.
General
Inspection Criteria
A.
During
each
of
the
specified inspection tasks
in
this
section,
more
general
inspections
of
the
adjacent
areas
must
be
done
while
access
is
available.
These general
inspections
are
used
to
find
apparent
conditions
which
can
need more
maintenance.
B. If
a
component
or
system
is
changed after
a
required
task
has
been
completed,
then
that
specified
task
must
be
done again
to
make
sure
it is
correct
before
the
system
or
component
is
returned
to
service.
C.
Do
a
preflight inspection
after
these
inspections
are
completed
to
make
sure
all
the required
items
are
correctly
serviced.
Refer to the Pilot's
Operating
Handbook
and
FAA
Approved
Airplane
Flight
Manual.
ITEM
CODE
TASK
ZONE
MECH
INSP
REMARKS
NUMBER
251102
AMSAFE
Aviation
Inflatable Restraint
(AAIR)
-
211
Examine the restraint
for
dirt, frayed edges,
unserviceable stitching,
loose
connections,
and
other
wear.
243005
Standby
Battery
-
Complete
the
Standby
Battery
220
Capacity
Test.
Refer
to
Chapter
24,
Standby
Battery
-
Maintenance
Practices.
246101
Essential
and
Crossfeed
Bus
Diodes
-
Check
224
for
proper operation.
Complete
the
Essential
and
Crossfeed
Bus
Diode Inspection.
Refer
to
Chapter
24,
Essential
and
Crossfeed
Bus
Diodes
-
Maintenance
Practices.
***
End
of
Operation
20
Inspection
Items
***
5-12-20
Page
1
©
Cessna
Aircraft
Company
Jul 3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION OPERATION
21
Date:
Registration
Number:
Serial Number:
Total
Time:
1.
Description
A.
Operation
21
gives
a
list of item(s),
which
are
completed
every
3
years.
B.
Inspection
items
are
given
in
the
order
of the
zone
in
which
the
inspection
is
to
be
completed.
A
general
description
of
the
inspection
required and
the
Item
Code
Number for
cross-reference
to
section
5-10-01
are
shown. Frequently,
the
tasks
define
more
specifically
the
scope
and
extent
of
each
required
inspection. These
tasks
are
printed
in
the
individual
chapters
of
this manual.
C.
The
right
portion
of
each page
gives space
for
the
mechanic's
and
inspector's initials
and
remarks.
A
copy
of
these
pages
can
be
used
as
a
checklist
when
these inspections
are
completed.
2.
General
Inspection Criteria
A.
During
each
of
the
specified
inspection
tasks
in
this
section,
more
general
inspections
of
the
adjacent
areas must
be
done while
access
is
available.
These
general
inspections
are
used
to
find
apparent
conditions
which
can
need
more
maintenance.
B. If a
component
or
system
is
changed after
a
required
task
has been
completed,
then
that
specified
task
must
be
done again
to
make
sure
it is
correct
before the system
or
component
is
returned
to
service.
C.
Do
a
preflight
inspection after these
inspections
are
completed
to
make
sure
all
the
required
items
are
correctly
serviced. Refer
to
the
Pilot's
Operating
Handbook
and
FAA
Approved
Airplane
Flight
Manual.
ITEM CODE
TASK
ZONE
MECH
INSP
REMARKS
NUMBER
351002
Oxygen
Cylinder
(if
applicable)
-
Inspect
for
211
condition,
check
hydrostatic
test date
and
perform
hydrostatic
test,
if
due.
***
End
of
Operation
21
Inspection
Items
***
5-12-21
Page
1
©
Cessna
Aircraft Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION OPERATION
22
Date:
Registration Number:
Serial
Number:
Total
Time:
1.
Description
A.
Operation
22
gives
a
list
of
item(s),
which
are
completed beginning
five
years
from the
date
of
the
manufacture,
you
must
make
sure
of
the
serviceability
of
the components
every
twelve
months.
Refer
to
Airborne
Air
and
Fuel
Products
Service
Letter Number
39A or latest revision.
B.
Inspection
items
are
given
in
the
order
of
the
zone
in
which
the inspection
is
to
be
completed.
A
general
description
of
the
inspection
required
and
the
Item
Code Number
for
cross-reference
to
section
5-10-01
are shown.
Frequently,
the
tasks
define
more
specifically
the
scope
and
extent
of
each
required
inspection. These tasks
are
printed
in
the
individual
chapters of
this
manual.
C.
The
right
portion
of
each
page
gives space for
the mechanic's
and
inspector's
initials
and
remarks.
A
copy
of
these
pages
can
be
used
as
a
checklist
when
these
inspections
are
completed.
2.
General
Inspection Criteria
A.
During
each
of
the
specified
inspection
tasks
in
this
section,
more
general
inspections
of
the adjacent
areas
must
be
done
while access
is
available. These
general
inspections
are
used
to
find
apparent
conditions
which
can
need
more
maintenance.
B. If a
component
or
system
is
changed
after
a
required
task
has
been
completed,
then
that
specified
task
must
be
done again
to
make
sure
it is
correct before the
system
or
component
is
returned
to
service.
C.
Do
a
preflight
inspection
after these
inspections
are
completed
to
make
sure
all
the
required
items
are
correctly
serviced.
Refer
to
the
Pilot's
Operating
Handbook
and
FAA
Approved
Airplane
Flight
Manual.
ITEM
CODE
TASK
ZONE
MECH
INSP
REMARKS
NUMBER
371006
Vacuum
Manifold
Check
Valve
-
Complete
a
check
120
for
proper
operation. (Only airplanes
with
dual
vacuum
pumps
and
Airborne manifolds. Refer
to
the
Airborne Air
&
Fuel
Products
Service
Letter
Number
39A
or
latest
revision,
and
in
accordance
with
SB02-37-04.)
Refer
to
Chapter
37,
Vacuum
System
-
Maintenance
Practices
for
the
removal
and
installation
of
the
check
valve.
***
End
of
Operation
22
Inspection
Items
***
5-12-22
Page
1
©
Cessna
Aircraft Company
Jul
3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION
OPERATION
23
Date:
Registration
Number:
Serial Number:
Total
Time:
1.
Description
A.
Operation
23
gives
a
list
of
item(s), which
are
completed every
100
hours
or
every
one
year,
whichever
occurs
first.
B.
Inspection
items
are
given
in
the order
of
the
zone
in
which
the
inspection
is
to
be
completed.
A
general
description
of
the
inspection
required and the
Item
Code Number
for
cross-reference
to
section
5-10-01
are
shown.
Frequently,
the
tasks
define
more
specifically
the scope
and
extent
of
each
required
inspection. These
tasks
are
printed
in
the
individual
chapters
of
this manual.
C.
The
right
portion
of
each page
gives space for
the
mechanic's
and
inspector's
initials
and
remarks.
A
copy
of
these
pages
can
be
used
as
a
checklist
when
these
inspections
are
completed.
2.
General
Inspection Criteria
A.
During
each
of
the
specified
inspection tasks
in
this
section,
more
general
inspections
of
the
adjacent
areas
must
be
done
while
access
is
available. These
general
inspections
are
used
to
find
apparent
conditions
which
can
need
more
maintenance.
B. If a
component
or
system
is
changed after
a
required
task
has
been
completed, then
that
specified
task
must
be
done again
to
make
sure
it is
correct
before
the
system
or component
is
returned
to
service.
C.
Do
a
preflight inspection after these inspections
are
completed
to
make sure
all
the
required
items
are
correctly
serviced.
Refer
to
the
Pilot's
Operating Handbook
and
FAA
Approved
Airplane
Flight
Manual.
ITEM
CODE
NUMBER
212002
TASK
ZONE
MECH
INSP
Primary Flight
Display
(PFD) Fan,
Multi-Function
Display
(MFD)
Fan,
Deck
Skin
Fan,
and
Remote
Avionics
Cooling
Fan
-
Operational
Check.
Refer
to
Chatper
21,
Avionics
Cooling
-
Maintenance
Practices.
***
End
of
Operation
23
Inspection
Items
***
©
Cessna
Aircraft
Company
REMARKS
220,
225
5-12-23
Page
1
Jul
3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION OPERATION
24
Date:
Registration
Number:
Serial
Number:
Total
Time:
1. Description
A.
Operation
24
gives
a
list
of
item(s),
which are
completed
every
100
hours,
every annual
inspection,
every
overhaul,
and
any
time
fuel lines
or
clamps
are
serviced,
removed,
or
replaced.
B.
Inspection
items
are
given
in
the
order
of
the
zone
in
which
the
inspection
is
to
be
completed.
A
general
description
of
the
inspection
required
and
the
Item
Code
Numberfor
cross-reference
to
section
5-10-01 are
shown.
Frequently,
the
tasks define
more
specifically
the
scope
and
extent
of
each
required
inspection. These tasks
are
printed
in
the
individual chapters
of
this
manual.
C.
The
right
portion
of
each
page gives space
for
the
mechanic's
and
inspector's
initials
and
remarks.
A
copy
of
these
pages
can
be
used
as
a
checklist
when
these
inspections
are
completed.
2.
General
Inspection Criteria
A.
During
each
of
the
specified
inspection
tasks
in
this
section,
more
general
inspections
of
the
adjacent
areas
must
be
done while
access
is
available. These
general
inspections
are
used
to
find
apparent
conditions
which
can
need more
maintenance.
B. If
a
component
or
system
is
changed
after
a
required
task
has
been
completed,
then that
specified
task
must
be
done
again
to
make sure
it
is
correct
before
the system
or
component
is
returned
to
service.
C.
Do
a
preflight inspection
after
these
inspections
are
completed
to
make
sure
all
the
required
items
are
correctly
serviced.
Refer
to the Pilot's
Operating
Handbook
and
FAA
Approved Airplane
Flight
Manual.
ITEM
CODE
NUMBER
720000
TASK
Fuel
line
(Stainless steel tube
assembly)
and
support
clamp
inspection
and
installation.
Refer
to
Lycoming
Service
Bulletin
Number
342E
or later
version.
***
End of
Operation
24
Inspection
Items
***
ZONE
MECH
INSP
REMARKS
120
5-12-24
Page
1
Jul 3/2006
©
Cessna
Aircraft
Company
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION
OPERATION
25
Date:
Registration
Number:
Serial Number:
Total Time:
1.
Description
A.
Operation
25
gives
a
list
of
item(s),
which
are
completed
the
first
600
hours
and
as
defined
by
the
manufacturer thereafter
B.
Inspection
items
are
given
in
the order
of
the
zone
in
which
the
inspection
is
to
be
completed.
A
general
description
of
the
inspection
required
and
the
Item
Code
Number
for
cross-reference
to
section
5-10-01
are
shown.
Frequently,
the
tasks
define
more
specifically
the
scope
and
extent
of
each
required
inspection. These tasks
are printed
in
the
individual
chapters
of
this manual.
C.
The
right
portion
of
each
page
gives space
for
the
mechanic's
and
inspector's
initials
and
remarks.
A
copy
of
these
pages
can
be
used
as
a
checklist
when
these
inspections
are
completed.
2.
General
Inspection
Criteria
A.
During
each of
the specified inspection
tasks
in
this section,
more
general
inspections
of
the
adjacent
areas
must
be
done
while
access
is
available. These
general
inspections
are used
to
find
apparent
conditions
which
can
need
more
maintenance.
B. If
a
component or
system
is
changed
after
a
required
task
has
been
completed,
then
that
specified
task
must
be
done again
to
make sure
it
is
correct before
the
system
or
component
is
returned
to
service.
C.
Do
a
preflight
inspection
after
these inspections
are
completed
to
make sure
all
the
required
items
are
correctly serviced. Refer
to
the
Pilot's
Operating
Handbook
and
FAA
Approved
Airplane
Flight
Manual.
ITEM
CODE
NUMBER
371007
TASK
Do
an
inspection
of
the
wear
indicator
ports
on
the
vacuum
pumps
described
in
Tempest
Service
Letter
004.
***
End
of
Operation
25
Inspection
Items
***
ZONE
MECH
INSP
REMARKS
120
5-12-25
Page
1
Jul
3/2006
©
Cessna
Aircraft
Company
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INSPECTION
OPERATION
26
Date:
Registration
Number:
Serial
Number:
Total
Time:
1. Description
A.
Operation
26
gives
a
list
of item(s),
which
are
completed
every
1000 hours
or
3
years, whichever
occurs
first.
B.
Inspection
items
are
given
in
the order
of
the
zone
in
which
the
inspection
is
to
be
completed.
A
general
description
of
the
inspection
required and the
Item Code
Number
for
cross-reference
to
section
5-10-01
are shown. Frequently,
the
tasks
define
more
specifically
the
scope
and
extent
of
each
required
inspection. These tasks
are
printed
in
the
individual
chapters
of
this manual.
C.
The
right
portion
of
each page gives
space
for
the
mechanic's
and
inspector's
initials
and
remarks.
A
copy
of
these
pages can
be
used
as
a
checklist
when
these
inspections
are
completed.
2. General
Inspection Criteria
A.
During
each
of
the
specified
inspection
tasks
in
this section,
more
general
inspections
of the
adjacent
areas
must
be
done
while
access
is
available.
These
general
inspections
are
used
to
find
apparent
conditions
which
can
need
more
maintenance.
B. If
a
component
or
system
is
changed
after
a
required
task
has
been
completed,
then
that
specified
task
must
be
done
again
to make sure
it
is
correct
before
the system
or
component
is
returned
to
service.
C.
Do
a
preflight
inspection
after
these
inspections
are
completed
to make sure
all
the
required
items
are
correctly
serviced. Refer
to the Pilot's
Operating Handbook
and
FAA
Approved
Airplane
Flight
Manual.
TASK
Elevator
Trim
Tab
Actuator
-
Remove,
clean,
examine,
and
lubricate
the
actuator. Refer
to
Chapter
27,
Elevator
Trim
Control
-
Maintenance
Practices.
320
***
End
of
Operation
26
Inspection
Items
***
5-12-26
Page
1
Jul
3/2006
©
Cessna
Aircraft
Company
ITEM
CODE
NUMBER
273107
ZONE
MECH
INSP
REMARKS
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
UNSCHEDULED MAINTENANCE CHECKS
1.
General
A.
During
operation,
the
airplane
can
go
through:
(1)
Hard
landings.
(2)
Overspeed.
(3)
Extreme
turbulence
or
extreme
maneuvers.
(4)
Towing with
a
large
fuel unbalance
or
high
drag/side
loads
due
to ground
handling.
(5)
Lightning
strikes.
B.
When
the flight
crew
gives
a
report
of
any
of
these conditions,
complete
a
visual
inspection
of
the
airframe
and
specific inspections
of
components
and
areas
involved.
C.
Do
the
inspections
to
find
and examine the
damage
in
local
areas of visible
damage,
and
in
the
structure
and
components
adjacent
to
the
area
of
damage.
D. If
foreign object
damage
(FOD)
is
found, complete
a
visual
inspection
of
the
airplane
before
the
airplane
is
returned
to
service.
2.
Unscheduled
Maintenance
Checks
Defined
and
Areas
of
Inspection
A.
Hard/Overweight
Landings.
(1) A
hard
landing
is
any landing
made when
the
sink
rate
is
more
than
the
permitted
sink
rate
limit.
An
overweight
landing
is
any landing
made
when
the gross
weight
is
more
than
the
maximum
gross
landing
weight
given
in
the
approved
Pilot's
Operating
Handbook.
NOTE:
If
the
hard/overweight
landing
also has
high
drag/side
loads,
more
checks
are
necessary.
(2)
Hard
or
overweight
landing
check.
(a)
Landing
gear.
1
Main
gear
struts
-
Examine for
correct
attachment
and
permanent
set.
2
Main
gear
attachments
and
supporting
structure
-
Examine
for
loose
or
unserviceable
fasteners
and
signs
of
structural
damage.
3
Nose
gear trunnion supports
and
attaching
structure
-
Examine
for
loose
or
unserviceable fasteners
and
signs
of
structural damage.
4
Nose
gear attachments
and
supporting structure
-
Examine for
loose
or
unserviceable
fasteners
and
signs
of
structural
damage.
(b)
Wings.
1
Wing
surface
and
lift
strut
-
Examine
the
skin
for
buckles,
loose
or
unserviceable
fasteners,
and
fuel
leaks.
Examine
the
attach
fittings
for
security.
2
Trailing
edge
-
Examine
for any deformation that stops
the normal
flap
operation.
B.
Overspeed.
(1)
Overspeed
occurs
when one
of
the
conditions
that
follow
are
met:
(a)
The
airplane
was flown
at
a
speed
more
than
the
speed
limit
of
the
flaps.
(b)
The
airplane
was flown
at
a
speed
more
than
the
maximum
design speed.
(2)
Overspeed
(airspeed)
check.
(a)
Fuselage.
1
Windshield
and
Windows
-
Examine
for
buckling, dents,
loose
or
unserviceable
fasteners,
and
signs
of
structural damage.
2
All
hinged doors
-
Examine
the
hinges,
hinge
attach
points,
latches and
attachments,
and
skins
for deformation
and
signs
of
structural damage.
(b)
Cowling.
1
Skins
-
Examine
for
buckling, cracks, loose
or
unserviceable fasteners,
and
signs
of
structural
damage.
5-50-00
Page
1
©
Cessna
Aircraft
Company
Jan 2/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
(c)
Stabilizers.
1
Stabilizers
-
Examine the
skins,
hinges
and
attachments,
movable surfaces,
mass
balance weights,
and the
structure
for
cracks,
dents,
buckling,
loose
or
unserviceable
fasteners,
and
signs
of
structural
damage.
(d)
Wings.
1
Flaps
-
Examine
the
skin
for
buckling, cracks,
loose or
unserviceable
fasteners,
attachments,
and
signs
of
structural damage.
2
Fillets
and
fairings
-
Examine
for
buckling, dents,
cracks,
and
loose
or
unserviceable
fasteners.
C.
Extreme
Turbulence
or
Extreme
Maneuvers.
(1)
Extreme
turbulence
is
caused
by
atmospheric conditions
that produce
dangerous
quantities
of
stress
on
the
airplane.
Extreme
maneuvers
are
any
maneuvers
that
do
not
stay
within the
limits
given
in
the Pilot's Operating
Handbook.
(2)
Extreme
turbulence and/or
maneuvers
checks.
(a)
Stabilizers.
1
Horizontal
stabilizer
hinge
fittings,
actuator
fittings,
and
stabilizer
center
section
-
Examine
for
loose
or
unserviceable fasteners
and
signs
of
structural
damage.
2
Vertical
stabilizer
-
Examine
the
vertical
stabilizer for
signs
of
structural
damage,
skin
buckles,
loose
or
unserviceable fasteners,
and
damage
to
the
hinges
and
actuator
fittings.
3
Elevator
and rudder balance
weight
supporting
structure
-
Examine for
loose
or
unserviceable fasteners
and
signs
of
structural
damage.
(b)
Wing.
1
Wing
to
body
strut
fittings
and
supporting
structure
-
Examine
for
loose
or
unserviceable fasteners
and
signs
of
structural
damage.
2
Trailing
Edge
-
Examine
for
any deformation that stops
the normal
operation
of the
flap
and
aileron.
D.
Lightning
Strike.
(1) If
the
airplane
is
flown
through
an
electrically
charged
region
of
the
atmosphere,
it
can
be
struck
by
an
electrical discharge
moving
from
cloud
to
cloud or
from
cloud
to
ground.
During
a
lightning
strike,
the
current
goes
into
the airplane
at one
point
and
comes
out
of
another,
usually
at
opposite extremities.
The
wing
tips,
nose
and
tail
sections
are
the
areas
where
damage
is
most
likely
to
occur.
You
can
find bums
and/or erosion
of
small
surface areas
of
the
skin
and
structure
during inspection.
In
most cases,
the
damage
is
easily
seen.
In
some
cases,
however,
a
lightning strike
can
cause damage
that
is
not
easily
seen.
The
function
of
the
lightning
strike
inspection
is
to
find any damage
to
the
airplane
before
it
is
returned
to
service.
(2)
Lightning
strike
check.
As
the
checks
that
follow
are
performed,
complete the
Lightning
Strike/
Static Discharge
Incident
Reporting
Form
and
return
it
to
Cessna Propeller
Aircraft
Product
Support
Dept.
751,
Cessna
Aircraft
Company,
P.O.
Box
7706,
Wichita,
KS.
67277-7706.
If
there
are
components
listed
on
the
form
that
are
not
applicable
to
your airplane,
please
write
"Not
Applicable"
in
the
space
provided.
(a)
Communications.
1
Antennas
-
Examine all
antennas
for
burns
or
erosion.
If
you
find
damage, complete
the
functional
test
of
the communication
system.
(b)
Navigation.
1
Glideslope
antenna
-
Examine
for
burning and pitting.
If
damage
is
found, complete
a
functional
check
of
the
glideslope
system.
2
Compass
-
The
compass
is
serviceable
if
the
corrected
heading
is
within
plus
or minus
10
degrees of
the
heading
shown
by
the
remote
compass
system. Remove,
repair,
or
replace
the
compass
if
the
indication
is
not
within the
tolerance
limits.
(c)
Fuselage.
1
Skin
-
Examine the
surface
of
the fuselage
skin for
signs
of
damage.
2
Tailcone
-
Examine
the
tailcone
and
static
dischargers
for
damage.
(d)
Stabilizers.
1
Examine the
surfaces
of
the
stabilizers
for
signs
of
damage.
(e)
Wings.
1
Skins
-
Examine the
skin
for bums
and erosion.
5-50-00
Page
2
©
Cessna
Aircraft
Company
Jan
2/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
2
Wing
tips
-
Examine
the wing
tips
for
burns
and
pits.
3
Flight
surfaces
and
hinging
mechanisms
-
Examine for
burns and
pits.
(f)
Propeller.
1
Propeller
-
Remove
the
propeller
and
have
it
examined
at
an
authorized
repair
station.
(g)
Powerplant.
1
Engine
-
Refer
to
the
engine manufacturer's
overhaul
manual
for
inspection
procedures.
E.
Foreign
Object
Damage.
(1)
Foreign
object
damage
(FOD)
is
damage
to
the
airplane
caused
by
a
bird
strike
or
by
any
other
foreign object
while
operating
the
airplane
on
the
ground
or
in
normal
flight.
Tools,
bolts,
nuts,
washers,
rivets,
rags
or
pieces
of
safety-wire
left
in
the
aircraft
during
maintenance
operations
can
also
cause
damage.
The
function
of
the foreign object
damage
inspection
is
to
find
any
damage
before
the
airplane
is
repaired
or returned
to
service.
(2)
Use
caution
to
prevent unwanted
objects
from
hitting
the
airplane
during
towing
and
at all
times
when the
airplane
is
not
in
service.
(3)
The
aerodynamic
cleanliness
level
(degree
of
surface
smoothness),
has
an
effect
on
the
performance
of
the
airplane.
It
is
important
to
keep
a
high
level of
cleanliness.
(4)
Normal
operation
or
careless
maintenance
operations
can
cause
contour distortion
of
the
aerodynamic
surface. Careless
maintenance operations
can
also
cause
distortion
to
the doors
and
access
panels.
Be
careful
when
you
work
with
these
items.
(5)
Foreign
object
damage
check.
(a)
Landing
gear.
1
Fairings
-
Examine
for
dents,
cracks,
misalignment,
and
signs
of
structural damage.
(b)
Fuselage.
1
Skin
-
Examine the
forward
and
belly
areas
for
dents, punctures, cracks,
and
signs
of
structural
damage.
(c)
Cowling.
1
Skins
-
Examine
for dents,
punctures,
loose
or
unserviceable
fasteners,
cracks,
and
signs
of
structural damage.
(d)
Stabilizers.
1
Leading
edge
skins
-
Examine
for dents, cracks, scratches,
and
signs
of
structural
damage.
(e)
Windows.
1
Windshield
-
Examine
for
pits,
scratches,
and
cracks.
(f)
Wings.
1
Leading
edge
skins
-
Examine
for dents, cracks,
punctures,
and
signs
of
structural
damage.
(g)
Engine.
1
Propeller
-
Examine
the
propeller
for nicks,
bends, cracks,
and
worn
areas
on
the
blades.
F.
High
Drag/Side Loads
Due
To
Ground
Handling.
(1) A
high
drag/side
load
condition occurs
when
the
airplane skids
or
overruns
the
prepared surface
and
goes
onto
an
unprepared
surface.
It
also
includes
landings that
are
short
of the
prepared
surface,
or
landings
which
involve
the
damage
of
tires
or
skids
on a
runway
to
the
extent
that
the
safety of
the
airplane
is
in
question.
This
includes
takeoff
and
landings
or
unusual
taxi
conditions.
(2)
High
drag/side
loads
due
to ground
handling check.
(a)
Landing
gear.
1
Main
gear and
fairings
-
Examine
for
loose
or
unserviceable
fasteners, buckling,
cracks,
and
signs
of
structural damage.
2
Nose
gear and
fairing
-
Examine
for
loose
or
unserviceable
fasteners,
cracks,
loose
steering cable
tension, buckling,
and
signs
of
structural
damage.
(b)
Wings.
1
Wing
to
fuselage
attach
fittings
and
attaching structure
-
Examine
for
loose
or
unserviceable
fasteners
and
signs
of
structural damage.
5-50-00
Page
3
©
Cessna
Aircraft
Company
Jan 2/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
B4224
LIGHTNING
STRIKE/STATIC
DISCHARGE INCIDENT REPORTING
FORM
Part
1
1.
Flight
Crew
must
complete
Part
1.
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 complete
description.
A.
Flight
Information:
Flight
Number_
Strike
Date_
Model
_
Unit/Serial
Number
Altitude
_
ft
Airspeed knots
Geographical
Location
B.
Airplane Orientation:
Takeoff Climb
Approach Other
Cruise
Descent
C.
At
time
of
Strike,
aircraft
was:
Above
Clouds
__
Within
Clouds
__
Below Ceiling
D.
Precipitation
at
Strike:
Rain
Sleet
E.
Lightning
in
Vicinity:
Before
After
F.
Static
in
Comm/Nav
Before
After
Hail
None
None
None
G.
Was
St.
Elmo's
fire
(bluish
electrical
discharge
or
corona)
visible
before
strike?
Yes
_
No
H.
Interference
(I)
or Outage
(0)
report. Check
all
the following
which
apply,
and
list
affected
systems,
such
as
dimming
of
cabin lights,
total
system
outage, etc.
Engines
Navigation
Communication
Flight
Instruments
Flight
Control
AC
Power
System
DC
Power
System
0
0
0
0
0
0
0
I.
Additional
comments
and
descriptions:
Date
Part
1
completed
by:
©
Cessna
Aircraft Company
Phone
5-50-00
Page
4
Jan
2/2006
Snow
I
I
I
CESSNA
AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
B4227
LIGHTNING
STRIKE/STATIC
DISCHARGE
INCIDENT
REPORTING
FORM
Part
2
1.
Ground
Crew
must
complete
Part
2.
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.
NOTE:
If
damage
is
severe,
please
report the
lightning
strike
as
soon
as
possible.
Inspection
by
Cessna
Engineering
Representative(s)
may
be
required.
A.
List
any sweeping
points,
such
as
burn
marks,
divots,
etc.,
and
skin
penetrations
on
airplane
skin
believed
to be
the
result
of the
lightning strike.
Itemize
and
reference
location(s)
of
damage
on
drawing
provided.
Indicate top, bottom,
left
or
right.
B.
Describe
damage to
structure
and external
components
caused
by
previously
mentioned
damage
points.
In
the
case
of
skin
penetration(s),
indicate
hole
diameter(s). List
all
damage
to
radome
and
any
other composite
structure, such
as
fairings, control
surfaces,
etc.
If
lightning
diverter
strips
are
damaged,
include
lightning
diverter
strip
location(s)
on
radome.
For
damage
to
composite structure, paint
thickness
must
be
included
in
description.
C.
List
any damage to
avionics
and
electrical components
believed
to
be
the
result of
the
lightning
strike,
including damaged
wiring,
disengaged
circuit
breakers, etc. Include manufacturer,
model
number and
serial number
of
damaged units where applicable.
D.
Estimate
cost
of
repair.
E.
Mention
severity
of damage (light,
moderate, heavy).
F.
Additional
comments
and
descriptions:
Part
2
completed
by:
Date
©
Cessna
Aircraft
Company
Phone
5-50-00
Page
5
Jan 2/2006
CHAPTER
DIMENSIONS
AND
AREAS
CESSNA AIRCRAFT
COMPANY
MODEL
182/Ti
82
MAINTENANCE
MANUAL
LIST
OF
EFFECTIVE
PAGES
CHA
PTER-SECTION-SU
BJ
ECT
06-Title
06-List
of
Effective
Pages
06-Record
of
Temporary
Revisions
06-Table
of
Contents
6-00-00
6-1
0-00
6-1
5-00
6-20-00
6-20-02
Page
1
Pages
1-5
Pages
1-3
Pages
1-4
Pages
1-11
©D
Cessna
Aircraft
Company
06
-
LIST
OF
EFFECTIVE PAGES
Page
1
of
1
Jul
1/2007
PAGE
DATE
April
1/2002
April
1/2002
April
1/2002
Jul
1/2007
Jul 1/2007
Temporary
Revision
Number
RECORD
OF
TEMPORARY
REVISIONS
Page
Number
Issue
Date
By
Date
Removed
By
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
DIMENSIONS AND
AREAS
-
GENERAL
1.
Scope
A.
This
chapter includes statistical
information
and
illustrations
concerning
the
Model
182
airplane.
2.
Definition
A.
This
chapter
is
divided
into
sections
to
aid
maintenance
personnel
in
locating
information.
Consulting
the
Table
of
Contents
will
further
assist
in
locating
a
particular subject.
A
brief
definition
of
the
sections
incorporated
in
this
chapter
is
as
follows:
(1)
The
section
on
airplane dimensions
and
specifications
provides
information
on
overall
airplane dimensions,
maximum
weights,
fuel
and
oil
capacities,
propeller
type
and
pitch
range
information, tire
data,
and
control
surface travel/control
cable
tension settings.
(2)
The
section
on
stations
provides
illustrations
to
identify
fuselage
stations
(FS)
and
wing
stations
(WS)
used
on
the
Model
182
airplane.
(3)
This section
provides illustrations
of
all
airplane
zones
and
is
used
in
conjunction
with
the
Model
182
Illustrated
Parts
Catalog
to
provide location
information
for
required
placards
and
markings.
(4)
This section provides illustrations
of
all
access/inspection
plates
located
on
or
in
the airplane.
6-00-00
Page
1
©
Cessna
Aircraft
Company
April 1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
AIRPLANE
DIMENSIONS
AND
SPECIFICATIONS
-
DESCRIPTION
AND OPERATION
1.
General
A.
This section
identifies
dimensions
and
specifications
of
the
airplane.
Dimensions
are
selected
for
pertinent
information
of
measurements
to
assist
operators,
maintenance personal
and/or
ground
handling
personnel. Refer
to the
respective
charts
below.
B.
Airplane
dimensions
are
illustrated
in
Figure
1.
2.
Dimensions
and
Specifications
AIRPLANE
OVERALL
FUSELAGE DIMENSIONS
Length
(Overall)
Height (Maximum)
Wing Span
(Overall)
Tail
Span
Landing
Gear
Track
Width
Cabin
Width
(Maximum
Sidewall
to
Sidewall)
Cabin
Height
(Floorboard to
Headliner)
MAXIMUM
WEIGHT
Ramp
Takeoff
Landing
FUEL
CAPACITY
Total
Usable
ENGINE
DATA
Type
Oil
Capacity
RPM
(Maximum)
Horsepower
Type
Oil
Capacity
RPM
(Maximum)
Horsepower
PROPELLER
Type
Diameter
(Maximum
to
Minimum)
©
Cessna
Aircraft
Company
29.0
Feet
9
Feet
3
Inches
36.0
Feet
11
Feet
8
Inches
9.0 Feet
42.0
Inches
48.5 Inches
3110
Pounds
3100
Pounds
2950
Pounds
92.0 Gallons
88.0
Gallons
Lycoming
IO-540-AB1A5
9.0
Quarts
2400
RPM
230
HP
Lycoming TIO-540-AK1A
9.0
Quarts
2400
RPM
235
HP
McCauley
B2D34C235/90
DKB-08,
2-Blade
82.0
to
80.5 Inches
6-1
0-00
Page
1
April
1/2002
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
PROPELLER
Pitch
Range
(High
to
Low)
Type
Diameter
(Maximum
to
Minimum)
Pitch
Range
(High
to
Low)
Pitch
Range T182
(High
to Low)
TIRE,
STRUT AND WHEEL
ALIGNMENT
DATA
Main
Tire
Size
Main
Tire
Pressure
Nose
Tire
Size
Nose Tire
Pressure
Nose
Gear
Strut
Pressure
(Strut
Extended)
Camber (Measured
With
Airplane
Empty)
Toe-In
(Measured
With
Airplane
Empty)
31.8
to
17.0
Degrees
McCauley
B3D36C431/80
VSA-01,
3-Blade
79.0
to
77.5
Inches
31.7
to
14.9
Degrees
35.4
to
15.3
6.00
X
6,
6-Ply
Rating
42.0
PSI
5.00
X 5,
6-Ply
Rating
49.0
PSI
55
to 60
PSI
5
to
7
Degrees
0.00
to
0.06
Inch
CONTROL
SURFACE
TRAVELS/CABLE
TENSION
SETTINGS
AILERONS
Aileron
Up
Travel
Aileron
Down
Travel
Aileron
Carry
Through
Cable Tension
RUDDER
Rudder
Travel
(Measured Parallel
to
Water
Line)
Right
Left
Rudder
Travel
(Measured
Perpendicular
to Hinge
Line)
Right
Left
Rudder
Cable Tension
ELEVATOR
Up
Travel (Relative
to
Stabilizer)
Down
Travel
(Relative
to
Stabilizer)
©
Cessna Aircraft
Company
20
Degrees,
+2
or
-2
Degrees
15
Degrees,
+2
or
-2
Degrees
40
Pounds,
+10
or -10
Pounds
24
Degrees,
+0
or
-1
Degree
24
Degrees,
+0
or
-1
Degree
27
Degrees
13
Minutes,
+0
or
-1
Degree
27
Degrees
13
Minutes,
+0
or
-1
Degree
30
Pounds,
+10 or
-10
Pounds
28
Degrees,
+1
or
-1
Degree
21
Degrees,
+1 or-1
Degree
6-10-00
Page
2
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
TIRE,
STRUT AND
WHEEL ALIGNMENT
DATA
Cable
Tension
ELEVATOR TRIM TAB
Up
Travel
Down
Travel
Cable Tension
FLAPS
Flap
Setting:
0
Degree
(Up)
10
Degrees
20
Degrees
38 Degrees
(Full)
©
Cessna
Aircraft
Company
30
Pounds,
+10 or
-10
Pounds
24
Degrees,
+2 or -2
Degrees
15
Degrees,
+1 or-1
Degree
15
Pounds,
+0
or
-5
Pounds
0
Degree,
+0 or
-0
Degree
10
Degrees,
+2
or
-2
Degrees
20
Degrees,
+2
or
-2
Degrees
38
Degrees,
+0
or
-1
Degree
6-10-00
Page
3
April 1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
B1076
SPINNER
COWLING
WING
\
J
0
L
S
FLAP
AGE
HORIZONTAL
STABI
ELEVATOR
TRIM
TAB
1
FEET
8
INCHES
071 OT1002
Airplane
Dimensions
and
Areas
Figure
1
(Sheet
1)
6-10-00
Page
4
April
1/2002
©
Cessna
Aircraft
Company
Al
LERON
[
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
B1077
36.0
FEET
ino
I1
pg
29.0
FEET
A
EET
3
INCHES
v
0710T1003
0710T1002
Airplane
Dimensions
and
Areas
Figure
1
(Sheet
2)
6-10-00
Page
5
April 1/2002
©
Cessna
Aircraft Company
4
Z
I
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
AIRPLANE
STATIONS
-
DESCRIPTION
AND OPERATION
1.
General
A.
The
airplane
is
laid
out
according
to
fuselage
stations
(FS)
and wing
stations
(WS).
These stations
provide
fixed
reference
points
for
all
components
located
on or
within
the
airplane.
Fuselage
Stations
begin
at
the
firewall
(FS
0.00)
and
extend
to the
tailcone
area
(FS
230.18). Wing
Stations
begin
at
the
root
(WS
23.62) and
extend
to
the tip
(WS
208.00).
Both
Fuselage
Stations and Wing
Stations
are
measured
in
inches. For example,
FS
185.50
is
185.50
inches
aft of
the
firewall
(FS
0.00).
B.
For
an
illustration
of
Fuselage
Stations,
refer to Figure
1.
For an
illustration
of
Wing
Stations,
refer
to
Figure
2.
6-15-00
Page
1
©
Cessna
Aircraft
Company
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
B1078
FS
0.00
FS
FS
17.00
FS
156.00
FS
209.00
FS
124.00
FS
185.50
FS 230.18
FS
199.00
FS
140.00
FS8.12
FS56
.70
FS
110.00
FS
172.00
Fuselage
Stations
Figure
1
(Sheet
1)
6-15-00
Page
2
April
1/2002
©
Cessna
Aircraft
Company
0710T1006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
B1079
WS
40.12
WS
WS
136.00
WS
208.00
0710T1013
Wing
Stations
Figure
2
(Sheet
1)
6-15-00
Page
3
April
1/2002
©
Cessna
Aircraft
Company
.'-
.- .
AA
v
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti
82
MAINTENANCE
MANUAL
AIRPLANE
ZONING
-
DESCRIPTION AND
OPERATION
General
A.
The
Model
1
82fTi
82
is
divided
into
numbered zones
to
provide
a
method
for
locating
components
and/or
placards throughout
the
airplane.
The
zones
are
identified
by
a
three-digit number
as
shown
in
the
example
below. The
first
digit
in
the
sequence
denotes
the major
zone
(300
series
for
aft
of
cabin,
500
series
for
left
wing,
etc.).
The
second
digit
in
the
sequence
further
divides
the
zone
into
submajor
zones
(Zone
51
0
for
inboard
portion
of
the
left
wing
and
Zone
520
for
outboard
portion
of
the
left wing,
etc.).
The third
digit
further
divides
the
submajor
zones into
subdivisions
(if
no
subdivision
is
needed,
this digit
is
typically
assigned
as
0
(zero).
EXAMPLE
310
Major
Zone
I ISubdivision
Zone
Submajor
Zone
B.
Major Zones.
(1)
100
-
Forward
side
of
firewall
and forward.
(2)
200
-
Aft
side
of
firewall
to
end
of
cabin.
(3)
300
-
Aft
of
cabin
to
end
of
airplane.
(4)
500
-
Left
wing.
(5)
600
-
Right
wing.
(6)
700
-
Landing
gear.
2.
Description
A.
For
a
breakdown
of
airplane
zones,
refer
to
Figure
1.
6-20-00
Page
1
Jul
1/2007
©
Cessna
Aircraft
Company
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti82
MAINTENANCE
MANUAL
110
51
310
611
(INTERIOR)
Airplane
Zones
Figure
1
(Sheet
1)
6-20-00
Page
2
Jul
1/2007
0
Cessna
Aircraft
Company
21081
1
1
T1
003
Ti
003
T1
003
CESSNA AIRCRAFT
COMPANY
MODEL
182/Ti
82
MAINTENANCE
MANUAL
81082
INSTRUMENT
PANEL
FIREWALL
LOOKING
FORWARD
Airplane Zones
Figure
1
(Sheet
2)
6-20-00
Page
3
Jul 1/2007
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti
182
MAINTENANCE
MANUAL
B2143
230
INTERIOR FLOOR
071
OT
1
005
Airplane Zones
Figure
1
(Sheet
3)
6-20-00
Page
4
Jul 1/2007
©
Cessna
Aircraft Company
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti
82
MAINTENANCE
MANUAL
ACCESS/INSPECTION
PLATES
-
DESCRIPTION
AND
OPERATION
1.General
A.
There
are
access
and
inspection
panels
on
the
interior
and
exterior
of
the
airplane.
These
panels give
access
to
components
and
airframe
areas.
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.
B.
This
section
can
be
used
in
conjunction
with
inspection
practices
(Chapter
5)
or
standard
maintenance
practices
to
quickly
find
related
components
throughout
the
airplane.
2.
Access/inspection
Panel
Numbering
A.
All
access/inspection
panels
have
a
series
of
numbers
and
letters which
identify
their zone location,
sequence,
and
orientation.
(1)
Zone
Location
-
Zone
location
is
identified
by the
first
three
numbers
of
any
panels.
This
three-
number sequence
is
specified
in
Airplane
Zoning
-
Description
and Operation.
(2)
Sequence
-
The
sequence
is
identified
by
alphabetical
letters
follow
the
three-number
sequence.
The
first panel
is
identified
as
"A,"
the
second
panel
is
identified
as
"B",
and
so
on.
(3)
Orientation
-
The
orientation
for each panel
is
identified
by
one
of
four
letters
that
come
after
the
sequence
letter.
The
orientation
letters
are
"T"
for
top,
"B"
for
bottom,
"L"
for
left,
and
"R"
for
right.
B.
With
(1)
(2)
(3)
access
panel
510AB
as
an
example,
the
breakdown
is
as
follows:
Zone Location
=
51
0
(inboard portion
of
left
wing)
Sequence
=
A
(the
first panel within
the
zone)
Orientation
=
B
(
located
on
the
bottom
of
the
zone).
3.
Description
A.
Access/Inspection
Panels.
6-20-02
Page
1
Jul 1/2007
©
Cessna Aircraft
Company
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti
82
MAINTENANCE
MANUAL
Table
1.
Cabin
Floorboard Panels
Panel
Equipment Located
In
Area
(Refer
to
Figure
1)
230ABA
Nose
Gear
Steering
Bellcrank
230AB
Nose
Gear
Steering Bellcrank
230BB
Nose
Gear
Steering Bellcrank
230GB
Brake
Lines
230DB
Rudder Cables,
Elevator
Trim
Cables, Rudder
Pulleys,
Elevator
Trim
Pulleys
230EB
Structure
230FB
Fuel
Lines
230GB
Brake
Lines
230HB Structure
230JB
Structure
230KB
Fuel
Lines,
Brake
Lines
230LB Rudder Cables,
Elevator
Trim
Cables, Rudder
Pulleys,
Elevator
Trim
Pulleys
230MB
Structure
230NB
Landing
Gear
And
Brake
Lines
230PB Rudder Cables,
Elevator
Trim
Cables, Rudder Pulleys,
Elevator
Trim
Pulleys
230QB
Landing
Gear
And
Brake
Lines
231
AB
Rudder
Cables,
Elevator
Cables,
Elevator
Triri,
Cables
231
BB
Rudder Cables,
Elevator
Cables,
Elevator
Trim
Cables
231 CB
Structure
231
DB
Rudder Cables,
Elevator
Cables,
Elevator
Trim
Cables, Rudder
Pulleys,
Elevator
Pulleys,
Elevator
Trim
Pulleys
231 EB
Rudder Cables,
Elevator
Cables,
Elevator
Trim
Cables, Rudder
Pulleys,
Elevator
Pulleys,
Elevator
Trim
Pulleys,
Transponder
Antenna
231
FB
Structure
231
GB3
Structure
231
HB11
Rudder Cables,
Elevator
Cables,
Elevator
Trim
Cables,
Rudder Pulleys,
Elevator
Pulleys,
Elevator
Trim
Pulleys
231JB
Rudder Cables,
Elevator
Cables, Elevator
Trim
Cables,
Rudder
Pulleys,
Elevator
Pulleys,
Elevator
Trim
Pulleys
231
KB
Battery Cable
231
LB
Rudder Cables,
Elevator
Cables,
Elevator
Trim
Cables,
Rudder Pulleys, Elevator
Pulleys,
Elevator
Trim
Pulleys
231
MVB
Structure
231 NB
Rudder Cables,
Elevator
Cables, Elevator
Trim
Cables
231 PB
Structure
6-20-02
Page
3
Jul
1/2007
Q
Cessna
Aircraft Company
CESSNA AIRCRAFT
COMPANY
MODEL
182/Ti
82
MAINTENANCE
MANUAL
Table
2.
Fuselage
Panels
Panel
Equipment
Located
In
Area
(Refer
to
Figure
2)
210OAB
Fuel
Selector
21
ORB
Antenna
31
OAR
Antenna
31
OBR
Elevator
Bellcrank,
Rudder
Cables,
Elevator
Trim
Cables, Rudder Pulleys,
Elevator
Trim
Pulleys
31
OCB
Elevator
Trim
Actuator
31
0DB
Elevator
Horn,
Rudder
Cables
31
OAR
Emergency
Locator
Transmitter,
Rudder
Cables, Elevator
Cables,
Elevator
Trim
Cables
340AL Rudder
Cables,
Elevator
Trim
Cables,
Rudder Pulleys,
Elevator
Trim
Pulleys
(34OAR)
340BR
Antenna
T-Phasing
Combiner
6-20-02
Page
5
Jul 1/2007
Q
Cessna
Aircraft Company
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti
82
MAINTENANCE
MANUAL
B1
086
51
OCT
51
51
OBT
61
OCT
I
61
ODT
61
OBT
TOP
VIEW
WING
ACCESS
PANELS
0710T1002
Wing
Access
Panels
Figure
3
(Sheet
2)
6-20-02
Page
7
Jul
1/2007
©
Cessna Aircraft
Company
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti182
MAINTENANCE
MANUAL
Table
3.
Wing
Access
Panels
Panel
-
Equipment
Located
In
Area
(Refer to
Figure
3)
620AB Aileron Bellcrank
620BB
Aileron Bellcrank
620CB
Aileron
Cables
620DB
Wing
Structure
620EB
Aileron
Cable
620FB Aileron
Cable
620GB
Roll
Servo
620HB Aileron
Cable,
Aileron
Cable Pulley
620JB
Wing
Structure
620KB
Aileron
Cable
610OAB
Aileron
Cable
610OBB
Flap
Actuator
610OCB
Courtesy
Light
61
0DB
Wing
Structure
61
OET Fuel
Bay
Access
61
OFT
Fuel
Bay
Access
61
0GB
Wing
Structure
610HB
Wing
Strut
610OJB
Wing Strut
61
0KB
Fuel Vent
Line
61
OLT
Fuel
Bay
Access
61
0MB Aileron
Cable,
Electrical
Wiring
61
ONT
Fuel
Bay
Access
61
OPB
Aileron
Cable,
Electrical Wiring
6100OB
Aileron
Cable, Electrical
Wiring
61
ORB
Fresh Air Inlet
520AB
Aileron
Bellcrank
520BB
Aileron Bellcrank
520CB Aileron
Cables
520DB
Wing
Structure, Magnetometer
520FB Wing
Structure
520HB Aileron
Cable,
Aileron Cable Pulley
520JB
Wing
Structure
0
Cessna Aircraft
Company
0
6-20-02
Page
8
Jul
1/2007
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti
82
MAINTENANCE
MANUAL
Table
3.
Wing
Access
Panels
(continued)
Panel
Equipment
Located
In
Area
(Refer
to
Figure
3)
520KB Aileron Cable
51lOAB
Aileron Cable
51
OBB
Flap
Actuator
51
0GB
Courtesy
Light
51
0DB
Wing
Structure
51lOET
Fuel
Bay
Access
51
OFT
Fuel
Bay
Access
510OGB
Wing
Structure
51
OHB
_Wing
Strut
510JB
Wing
Strut,
Pitot Tube
51
0KB
Fuel Vent
Line
51lOLT
Fuel
Bay
Access
51
0MB
Aileron
Cable
51lONT
Fuel
Bay
Access
51
OPB
Pitot
Line,
Aileron Cable
51lOQB
Pitot
Line,
Aileron Cable
51
ORB
Fresh
Air
Inlet
©
Cessna
Aircraft
Company
6-20-02
Page
9
Jul
1/2007
CESSNA AIRCRAFT
COMPANY
MODEL
182/Ti
82
MAINTENANCE
MANUAL
Table
4.
Flap
Panels
Panel
Equipment
Located
In
Area
(Refer
to
Figure
4)
51ilAT
Flap
Access
511
BT Flap
Access
511
CT
Flap
Access
511
DT
Flap
Access
611
AT
Flap
Access
611
BT
Flap
Access
611
CT
Flap
Access
611
DT Flap
Access
©
Cessna Aircraft
Company
6-20-02
Page
11
Jul
1/2007
CHAPTER
LIFTING
AND
SHORING
CESSNA
AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
LIST
OF
EFFECTIVE PAGES
CHAPTER-SECTION-SUBJECT
07-Title
07-List
of
Effective
Pages
07-Record
of
Temporary
Revisions
07-Table
of
Contents
7-00-00
7-10-00
7-11-00
PAGE
Page
1
Pages 201-202
Page
201
©
Cessna Aircraft
Company
07
-
LIST
OF
EFFECTIVE
PAGES
Page
1
of
1
Mar 1/2005
DATE
April
1/2002
April
1/2002
April
1/2002
Temporary
Revision
Number
RECORD
OF
TEMPORARY REVISIONS
Page
Number
Issue
Date
By
Date
Removed
By
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
CONTENTS
LIFTING
AND
SHORING
-
GENERAL
.............................................
Scope
......................................................................
Tools,
Equipment
and
Material
...............................................
Definition
...................................................................
JACKING
-
MAINTENANCE PRACTICES
.......................................
General
....................................................................
Tools,
Equipment
and
Materials
..............................................
Jacking
Procedure
..........................................................
EMERGENCY
LIFTING/HOISTING
-
MAINTENANCE PRACTICES
..................
Lifting
Procedure............................................................
7-00-00
Page
1
7-00-00
Page
1
7-00-00
Page
1
7-00-00
Page
1
7-10-00
Page
201
7-10-00
Page
201
7-10-00
Page
201
7-10-00
Page
201
7-11-00
Page
201
7-11-00
Page
201
CONTENTS
Page
1
of
1
Mar
1/2005
©
Cessna Aircraft
Company
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
LIFTING
AND
SHORING
-
GENERAL
1.
Scope
A.
This
chapter
describes
both
standard
and
emergency
procedures
used
to
lift
the
airplane
off
the
ground.
2.
Tools,
Equipment
and Material
NOTE:
Equivalent
substitutes
may
be
used
for
the
following
listed items:
NAME
NUMBER
MANUFACTURER
USE
Jack
Obtain
locally
To
jack
wing.
Leg
Extension
Obtain
locally
To
extend
legs
on
jack.
Slide
Tube Obtain
locally
To
extend
jack
height.
Extension
Universal
Tail
Stand Obtain
locally
To
secure
tail.
Padded
Block Fabricate
locally
To
provide
cushion
between
wing
jack
and
wing
spar.
3.
Definition
A.
This
chapter
is
divided
into
sections
to
aid
maintenance
personnel
in
locating
information. Consulting
the
Table
of
Contents
will
further assist
in
locating
a
particular
subject.
A
brief
definition
of
the
sections
incorporated
in
this chapter
is
as follows:
(1)
The
section
on
jacking
provides
normal
procedures
and
techniques
used
to
jack
the
airplane
off
the ground.
(2)
The
section
on
emergency
lifting
provides procedures,
techniques
and
fabrication
information
needed
to
lift
the
airplane
by
overhead means.
7-00-00
Page
1
©
Cessna
Aircraft
Company
April
1/2002
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
JACKING
-
MAINTENANCE
PRACTICES
1.
General
A.
Normal
jacking
procedures
involve
lifting
one
main
wheel
at
a
time.
This
procedure
is
best
accomplished
using
a
floor
jack
in
conjunction
with
the
built-in
jack
pad
(located
directly
below
the
step
on
each
strut).
CAUTION:
Jacking
both
wheels
simultaneously
at
built-in
jack
pads
is
not
recommended.
When using
built-in
jack
pad,
flexibility
of
the
main
gear
strut
will
cause
the
main
wheel
to
slide inboard
as
the
wheel
is
raised,
tilting
the
jack.
If
this
occurs,
the
jack
must
be
lowered
for
a
second
operation.
B.
When
the
airplane
needs
to
be
raised
off
the
ground
at
all
points,
the following
procedure should
be
used.
2.
Tools,
Equipment
and
Materials
A.
For
a
list of
required
tools, equipment
and
materials,
refer
to
Lifting
and
Shoring
-
General.
3.
Jacking
Procedure
A.
Raise Airplane
(Refer
to
Figure
201).
(1)
Place
wing
jacks
and
padded
blocks
under front
spar,
just
outboard
of
wing
strut.
Ensure
that
padded
block
(1
inch
X
4
inch
X
4
inch
with
0.25
inch
rubber
pad)
is
resting
securely
between
spar
and
jack.
(2)
Raise
wing
jacks
evenly
until
desired
height
is
reached.
CAUTION: When placed
on
jacks
centered
under
the wing
front
spar,
the
airplane
is
slightly
tail
heavy.
Tail
stands
must
be
used
and
weigh
enough
to
keep
the
tail
down under
all
conditions.
Additionally,
the
tail
stand
must
be
strong enough
to
support
any
weight
which
might
be
transferred
to
the
tailcone
area
during maintenance, creating
a
greater
tail
heavy
condition.
(3)
Carefully
attach
tail stand
to
tail
tiedown
ring.
B.
Lower
Airplane (Refer
to
Figure
201).
(1)
Detach
tail
stand from
tail
tiedown
ring.
(2)
Slowly
lower
wing
jacks
simultaneously
until main
tires
are
resting
on
ground.
(3)
Remove wing
jacks
and pads
from
wing
area.
7-10-00
Page
201
©
Cessna
Aircraft
Company
April
1/2002
CESSNA AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
B1087
PADDED
ING
BUILT-IN
JACK
PAD
(PART OF
STEP BRACKET)
_
-TAIL
S
ASTAND
071
0T1008
Airplane
Jacking
Figure
201
(Sheet
1)
©
Cessna
Aircraft
Company
7-10-00
Page
202
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
EMERGENCY
LIFTING/HOISTING
-
MAINTENANCE
PRACTICES
1.
Lifting
Procedure
A.
The
airplane
may
be
lifted
by
means
of
suitable
slings.
The
front
sling
should
be
hooked
to
each
upper engine
mount
at
the firewall,
and
the
aft
sling
should
be
positioned
around
the
fuselage
at
the
first
bulkhead
forward
of
the
leading edge
of
the
stabilizer.
7-11-00
Page
201
©
Cessna
Aircraft Company
April
1/2002
CHAPTER
LEVELING
AND
WEIGHING
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
LIST
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CESSNA
AIRCRAFT
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MODEL
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MAINTENANCE
MANUAL
CONTENTS
LEVELING
AND
WEIGHING
-
GENERAL
..........................................
S
cope......................................................................
Tools,
Equipment
and Material
...............................................
Definition
...................................................................
LEVELING
-
MAINTENANCE
PRACTICES.........................................
General
....................................................................
Tools,
Equipment
and
Materials
..............................................
Leveling
Points
.............................................................
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Cessna Aircraft
Company
CESSNA
AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
LEVELING AND
WEIGHING
-
GENERAL
1.
Scope
A.
This
chapter provides
information
necessary
to
properly
level
the
airplane.
B.
For
information
on
airplane
weighing
procedures,
refer to
Section
6
of
the
Pilot's
Operating Handbook
And
FAA
Approved
Airplane
Flight Manual.
2.
Tools,
Equipment and
Material
NOTE:
Equivalent
substitutes
may
be
used
for
the
following
items:
MANUFACTURER
Commercially available
USE
Bubble
level
used
to
level
airplane.
3.
Definition
A.
This
chapter
is
divided
into
sections
to
aid
maintenance personnel
in
locating
information.
Consulting
the
Table
of
Contents
will
further
assist
in
locating
a
particular
subject.
A
brief
definition
of
the
sections
incorporated
in
this
chapter
is
as
follows:
(1)
The
section
on
leveling provides maintenance practices
and
instructions for
longitudinal
and
lateral
leveling
of
the
airplane.
8-00-00
Page
1
©
Cessna Aircraft
Company
April
1/2002
NAME
Spirit
Level
NUMBER
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
LEVELING
-
MAINTENANCE PRACTICES
1.
General
A.
This section provides
reference
points
for
leveling the
airplane
laterally
and
longitudinally.
B.
For
an
illustration
of
leveling
points,
refer
to
Figure
201.
2.
Tools,
Equipment
and
Materials
A.
For
a
list of
required
tools,
equipment
and
materials, refer
to
Leveling
And
Weighing
-
General.
3.
Leveling Points
A.
Lateral
Leveling.
(1)
The
airplane
may
be
leveled
laterally
by
selecting
two
corresponding
points
on
the
upper door
sills (left
and
right)
and
placing the
level
across
these
points.
NOTE:
Out
of
level
tolerance
for
wing
tips
is
3
inches
total.
B.
Longitudinal Leveling.
(1)
Locate
two
NAS221-7 screws
on
left
side
of
fuselage
at
FS
139.65
and
FS
171.65.
(2)
Remove screws
and
replace
with
studs
of
suitable
length
(approximately
2
inches
long).
(3)
Place
level
on
protruding studs.
NOTE:
The
screws
located
at
FS
139.65 and
FS
171.65
are
on
Water
Line
(WL
13.25).
8-10-00
Page
201
©
Cessna
Aircraft
Company
April
1/2002
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
B1088
<" \A/" IC'
AT
CC
F 4 'ro nI'
AK
Ir~
r-e
.
7x4
^1-
(NOTE)
NOTE:
CORRESPONDING
POINTS
ON
BOTH UPPER
DOOR SILLS
MAY
BE
USED
TO
LEVEL THE
AIRPLANE
LATERALLY.
0710T1007
Airplane Leveling
Figure
201
(Sheet
1)
8-10-00
©
Cessna
Aircraft
Company
Page
202
April
1/2002
CHAPTER
TOWING
AND TAXIING
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
LIST
OF
EFFECTIVE
PAGES
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CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
CONTENTS
TOWING
AND
TAXIING
-
GENERAL
..............................................
S
cope......................................................................
Definition
...................................................................
TOWING
-
MAINTENANCE PRACTICES
..........................................
G
eneral
....................................................................
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CONTENTS
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1/2005
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Cessna Aircraft
Company
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
TOWING
AND
TAXIING
-
GENERAL
1.
Scope
A.
This
chapter
describes
towing
procedures for
movement
of the
airplane
on
the
ground.
2.
Definition
A.
This
chapter
is
divided
into
sections
to
aid
maintenance
personnel
in
locating information. Consulting
the
Table
of
Contents
will
further assist
in
locating
a
particular
subject.
A
brief
definition
of the
section
incorporated
in
this chapter
is
as
follows;
(1)
The
section
on
towing describes
those
procedures
and
cautions
applicable
for
the
Model
182
airplanes.
9-00-00
Page
1
April
1/2002
©
Cessna
Aircraft
Company
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
TOWING
-
MAINTENANCE PRACTICES
1.
General
A.
Towing.
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
at
a
bulkhead
to
avoid
buckling
the
skin.
(1)
Moving
the airplane
by
hand
is
accomplished
by
using
the wing
struts and
nose
landing
gear
strut
as
push points.
A
tow
bar
attached
to the
nose
gear
should
be
used
for steering
and
maneuvering
the
airplane
on the ground.
(2)
When
no
tow
bar
is
available,
press
down at the
horizontal
stabilizer
front
spar
adjacent
to
the
fuselage
to
raise
the
nose wheel
off
the ground. With the
nose
wheel
clear
of
the
ground,
the
aircraft
can
be
turned
by
pivoting
it
about the
main
wheels.
9-10-00
Page
201
©
Cessna
Aircraft
Company
April
1/2002
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
TOW
BAR
ASSEMBLY
0710T1001
A0714T1016
Tow
Bar
Installation
Figure
201
(Sheet
1)
©
Cessna
Aircraft
Company
9-10-00
Page
202
April
1/2002
CHAPTER
PARKING
AND
MOORING
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti
82
MAINTENANCE
MANUAL
LIST
OF
EFFECTIVE
PAGES
CHAPTER-SECTION-SUBJECT
1
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-204
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201
©
Cessna
Aircraft
Company
10
-LIST
OF
EFFECTIVE
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1/2007
DATE
April
1/2002
April
1/2002
Jul
1/2007
April
1/2002
April
1/2002
Temporary
Revision
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OF
TEMPORARY
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CESSNA AIRCRAFT
COMPANY
MODEL
182/Ti
82
MAINTENANCE
MANUAL
CONTENTS
PARKING,
MOORING,
STORAGE
AND
RETURN
TO
SERVICE
-
GENERAL.
Scope....................................
Tools,
Equipment
and
Materials........................
Definition
..................................
PARKING
-
MAINTENANCE
PRACTICES......................
General...................................
Parking
Instructions
.............................
STORAGE
-
MAINTENANCE
PRACTICES
.....................
General...................................
Flyable
Storage
...............................
Temporary
Storage..............................
Indefinite Storage
..............................
Inspection
During
Flyable
Storage.......................
Inspection
During
Temporary
Storage
.....................
Inspection
During
Indefinite
Storage......................
MOORING
-
MAINTENANCE
PRACTICES
.....................
General...................................
Mooring
Procedures
.............................
RETURN
TO
SERVICE
-
MAINTENANCE
PRACTICES
...............
General...................................
Flyable
Storage
Return
to
Service.......................
Temporary Storage
Return
to
Service......................
Indefinite Storage Return
to
Service......................
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10-
CONTENTS
Pagel1ofl1
Jul
1/2007
©
Cessna
Aircraft
Company
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
PARKING,
MOORING,
STORAGE AND
RETURN
TO
SERVICE
-
GENERAL
1.
Scope
A.
This chapter
provides
maintenance instructions for
parking,
mooring,
storage
and
return
to
service.
2.
Tools,
Equipment
and
Materials
NOTE:
Equivalent
substitutes
may
be
used
for
the
following
items:
NAME
NUMBER
Wheel
Chocks
Engine
Air
Inlet
Cover
Pitot
Tube
Cover
Static
Ground
Cable
Rope (0.375
inch
diameter
minimum)
or
equivalent
Dehydrator
Plugs
Corrosion
Preventive
Oil
Preservative
Oil
MS27215-1
or
-2
One
part
MIL-L-6529,
Type
1,
with
one part
Royal
"D"
MIL-C-6529
MANUFACTURER
Available
Commercially
Cessna Aircraft
Cessna
Parts
Distribution
Department
701,
CPD
25800
East
Pawnee
Road
Wichita,
KS
67218-5590
Cessna
Aircraft
Available
Commercially
Available
Commercially
Available
Commercially
Royal
Lubricants
Co.
Inc.
72
Eagle Rock Ave.
East
Hanover,
NJ
07936
Available
Commercially
USE
To
chock
landing
wheels.
To
prevent entry
of
moisture
and/or foreign
particles
through
cowling.
To
prevent
entry
of
moisture
and/or
foreign
particles
in
pitot
tubes.
To
static
ground
airplane.
To
tie
down
wing
and
tail.
To
prevent moisture
in
cylinders
during
indefinite
storage.
Preserve
engine
during
long
term
storage.
Preserve
engine during
long
term
storage.
3.
Definition
A.
This
chapter
is
divided
into
sections
to
aid
maintenance personnel
in
locating
information.
Consulting
the
Table
of
Contents
will
further assist
in
locating
a
particular
subject.
A
brief
definition
of
the
sections
incorporated
in
this chapter
is
as
follows:
(1)
The
section
on
parking
describes
methods,
procedures
and
precautions
used when
parking
the
airplane.
(2)
The
section
on
mooring
describes
procedures
and
equipment
used
to
moor the
airplane.
(3)
The
section
on
storage
provides
information
on
recommended
storage procedures.
Recommendations
vary
with
the
length
of
time
the
airplane
is
to be stored.
(4)
The
section
on
return
to
service
describes procedures
used
when
returning
the
airplane
to
service
from
flyable,
temporary
or
indefinite storage.
10-00-00
Page
1
©
Cessna
Aircraft Company
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE MANUAL
PARKING
-
MAINTENANCE PRACTICES
1.
General
A.
These maintenance
practices
cover procedures
used
to
park
the
airplane.
B.
The
airplane
should
be
moored
if
high
winds
are
anticipated
or
anytime
the
airplane remains outside
for
extended
periods
of
time.
Refer to Mooring
-
Maintenance
Practices
for
mooring
procedures.
Refer
to
Storage
-
Maintenance Practices for
detailed
instructions
regarding short
term
or
long
term
storage.
2.
Parking
Instructions
A.
Hard
Surface
and Sod.
(1)
Position airplane
on
level
surface
headed
into
wind.
(2)
Set
parking
brake
or
chock
main
gear
wheels.
CAUTION:
Do
not
set
parking brake
during
cold
weather.
Accumulated
moisture
may
freeze
brakes,
or
when
brakes
are
overheated.
(3)
Install control column
lock.
©
Cessna
Aircraft
Company
10-10-00
Page
201
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti182
MAINTENANCE
MANUAL
STORAGE
-
MAINTENANCE PRACTICES
1.
General
A.
This
section provides maintenance
instructions
and
inspection
criteria for
airplanes
in
flyable,
temporary
and
indefinite
storage. Refer
to
the
Lycoming Service Letter
Li
80B
(or
latest revision).
(1)
Flyable
storage
is
defined
as
a
maximum
of
30
days
of
nonoperational status
and/or
the
first
25
hours
of
intermittent
engine
operation.
(2)
Temporary
storage
is
defined
as
a
maximum
of 90
days
of
nonoperational
status.
(3)
Indefinite
storage
is
defined
as
more
than
90
days
of
nonoperational
status.
2.
Flyable Storage
A.
Flyable
storage
is a
maximum
of
30
days storage
with
no
engine operation and/or
the
first
25
hours
of
intermittent
engine
operation.
B.
Engine
temperature
and
length
of
operation
time
are
very important
in
the
control
of
corrosion. The
desired
flight
time
for
air cooled
engines
is
at
least
one
continuous
hour
at
oil
temperatures
of 165
degrees
F
(74
degrees
C)
to
200
degrees
F
(93
degrees
C)
at
intervals
not to
exceed
30
days.
The
one
hour
does
not
include
taxi,
take-off,
and
landing
time.
C.
The
aircraft
temperature gages
must
operate correctly.
D.
The
cooling
air baffles must
be
in
good
condition
and
fitted
properly.
E.
The
oil
cooler
system
must
be
of
the
proper
size
for
the
engine
and
airframe.
Oil
coolers
that
are
not
the
correct
size
can
cause
an
engine
to
operate
at
too high or low
a
temperature.
Low
temperatures
are as
dangerous
as
high
temperatures
because
of
build-up
of
water
and
acids.
F.
Pulling
the
propeller
through
by
hand
is
not
recommended
when
the
airplane
has
not
operated
for
approximately
aweek.
Pulling
the
propellerthrough
by
hand
before
you
start
the
engine
orto
minimize
corrosion
can
cause damage.
When
the
propeller
is
pulled
through
by hand,
the
rings
can
remove
oil
from
the
cylinder
walls. The
cam
load
made
by
the
valve train
removes
oil from
the
cam
and
followers.
After two
or
three
times
of
pulling
the
propeller
through
by
hand
without
engine
starts, the
cylinders,
cam, and
followers
are left
without
the
correct
quantity
of
oil
film. Engine
starts
without
the
correct
lubrication
can
cause
the
engine
parts
to
score,
which
can
cause
damage
to
the
engine.
G.
The pitot
tube,
static
air
vents,
air
vents,
openings
in
the
engine
cowl,
and
other
openings
must
have
protective
covers
installed
to
prevent entry
of
foreign
object
debris.
3.
Temporary
Storage
NOTE: The
airplane
is
constructed
of
corrosion
resistant,
epoxy
primed
aluminum,
which
will
last
indefinitely
under
normal
conditions,
if
kept
clean.
The
alloys
are
subject
to
oxidation.
The
first
indication
of
corrosion
on
unpainted
surfaces
is in
the
form
of
white
deposits
or
spots.
Corrosion
on
painted
surfaces shows
up
as
the
paint
being
discolored
or
blistered.
Storage
in
a
dry
hangar
is
necessary
for
good
preservation
and
must
be
procured
if
possible.
A.
Temporary
Storage
of
the
Airplane
(1)
The
tiedown
rings
must
be
used
as
electrical
ground
points
for
all ground
wires
during
the
refuel
procedures.
(2)
Fill
the
fuel
tanks
with the
correct
grade
of
gasoline.
WARNING:
During
all
fueling
procedures, fire
fighting
equipment
must
be
available.
In
case
of
an
accidental
disconnect
of
a
ground
wire.
Two
ground
wires must
be
used
from
different
points
on
the
airplane
which
are
attached
to
separate
ground
stakes
.
Make
sure to
ground
the
fuel
nozzle the
airplane.
(3)
Clean
and
wax
the
airplane
thoroughly.
(4)
Clean
all
oil or
grease
from
the
tires.
1
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201
C
Cessna
Aircraft
Company
Jul
1
/2007
CESSNA
AIRCRAFT
COMPANY
MODEL
182rT182
MAINTENANCE
MANUAL
(5)
Apply
a
tire
preservative
to
the
tires.
(6)
Cover
the
tires
to
protect
against
grease
and
oil.
(7)
Block
up
the
fuselage
to
relieve
the
pressure
on
the
tires
or
rotate
the
wheels
every
30
days.
NOTE:
This
aids
to
change supporting
points
and
prevent
flat
spotting
on the
tires.
(8)
Lubricate
all
airframe
items
and
cover
all
openings
which allow moisture
and/or
dust
to
enter.
(9)
Turn
battery
and
store
in a
cool,
dry place.
Service
the
battery
periodically
and
charge
as
required.
(1 0)
Disconnect
the
spark
plug leads.
(1 1)
Remove
the upper
and
lower
spark
plugs
from each
cylinder.
(12)
Use
a
portable
pressure
sprayer
to
spray
a
preservative
oil
in
the
upper
spark
plug
hole
of
each
cylinder
(the
piston
must
be
in a
down
position).
Rotate
the
crankshaft
as
each
pair
of
cylinders
is
sprayed.
(13)
Rotate
the
crankshaft
so
that
no
piston
is
at
a
top
position.
(14)
If
the
airplane
is
to
be
stored
outside,
set
the
two
bladed
propeller
in a
horizontal position
to
provide
maximum
clearance
for
passing airplanes.
(15)
Spray
each
cylinder
without
moving
the
crankshaft
to
cover
all
interior
surfaces
of
the
cylinder
above
the
piston.
(16)
Install the
spark
plugs
and
attach
the
spark
plug
leads.
(17)
Spray
two
ounces
of the
preservative
oil
into the
engine
interior
through
the
oil
filler
tube.
(18)
Seal
all
engine
openings exposed
to
the
atmosphere
using
suitable
plugs.
Attach
a
red
streamer
at
each
point
that
a
plug
is
installed.
CAUTION:
The
pitot
tube,
static
source
vents,
air
vent
openings
in
the
engine
cowling
and
other
similar
openings
must
have
protective covers
installed
to
prevent
entry
of
foreign
material.
(1 9) If
the
airplane
is
to
be
stored
outside,
tie
it
down
using the
procedures
outlined
in
Chapter
1 0,
Mooring
-
Maintenance
Practices.
(20)
Attach
a
warning placard
to
the
propeller
to
identify
that
the
propeller
must
not
be
moved
while
the
engine
is in
storage.
4.
Indefinite
Storage
A.
Put
the
airplane
in
indefinite storage.
NOTE:
Periodic inspections
must
be
performed
to
make sure
of
the
integrity
of
preservation
methods..
Refer
to
Chapter
10,
Inspection
During
Indefinite
Storage.
(1)
Operate
the
engine
for
the
oil
temperature
to
reach
the normal
operating
temperature.
NOTE:
Normal
operating
temperature
is
within
the
green
arc
of
the
oil temperature
gage.
The
engine
oil
must
be
drained while
the
engine
is
still
warm.
(2)
Shut
off
the
engine
and
remove
the
lower cowling
to
drain
the engine
oil.
Refer
to
Chapter
71,
Cowling
-
Maintenance
Practices.
(3)
Lift
the
nose
of
the
airplane
slightly
to
aid
in
the
removal
of
sludge
in
the
engine
oil
sump.
WARNING: Avoid
skin
contact
with
engine
oil.
Any
engine
oil
that
inadvertently
gets
on
the
skin
should
be
immediately
removed.
(4)
Remove
and
discard
the
wire
from
the
drain
plug.
(5)
Remove
the
drain
plug
and
let
the
oil
drain
into
an
applicable
container.
(6)
Install
plug
in
sump
when
all oil
is
drained.
1
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0
Cessna
Aircraft Company
Jul
1/2007
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti182
MAINTENANCE
MANUAL
CAUTION:
The
corrosion preventive
mixture
is
harmful
to
paint
and
shall
be
wiped
from
painted
surfaces
immediately.
(7)
Fill
oil
sump
to
normal
capacity
with
thoroughly
mixed
corrosion preventative
oil. Refer
to
Chapter
10,
Parking,
Mooring,
Storage
and
Return
to
Service
-
General.
(8)
Remove
the top spark
plugs.
(9)
Slowly
turn
the
propeller
with
the
crankcase
full
of
oil,
through
two
revolutions.
(1 0)
Allow
the
engine
to
stand
for
ten
minutes, then
turn
the
propeller
back
and
forth
through
90
degrees
for
twelve
cycles.
(1 1)
Drain
the
preservative
oil.
(12)
Use
MIL-C-6529
oil
Type
1,
to
spray
the
exhaust
port and
valve
of
each
cylinder.
The
piston
must
be
approximately
1/4
turn
before
top
center
of
the
exhaust
stroke.
(13)
Use
an
airless
spray
gun
to
spray
two
ounces
of
MIL-C-6529
oil,
Type
1,
into each
cylinder
through
the
spark
plug
hole.
(14)
For
all
spraying,
the
spray
nozzle
temperature
must
be
maintained
between
200'F
(93.33
0C)
and
220
0F
(104.44
0C).
(15)
Install
dehydrator
plugs
in
the
upper
spark
plug
holes.
Make
sure
the
dehydrator
plugs
are
blue
in
color
when installed.
(16)
Cover
spark
plug lead
terminals
with
shipping
plugs
or
other
suitable
covers.
(17)
Set
the
throttle
in
the full
open
position.
(18)
Place
a
bag
of
desiccant
in
the
induction
air
intake
and
seal the
opening
with
moisture resistant
paper
and
tape.
(19)
Place
a
bag
of
desiccant
in
the
exhaust
tailpipe
and
seal
openings
with
moisture
resistant
tape.
(20)
Seal the
cold
air
inlet
to
the
heater
muff
with
moisture resistant
tape.
(21)
Seal
the
engine breather
tube
by
inserting
a
plug
in
the
breather
hose
and
clamping
it in
place.
(22)
Seal
all
other
engine
openings
exposed
to
the
atmosphere.
Use
applicable
plugs
or
non-hydroscopic
tape.
(23)
Attach
a
red
streamer
to
each
location where plugs
or
tapes
are
installed. Attach the
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.
CAUTION:
The
corrosion
preventive
mixture
is.
harmful
to
paint
and
must
be
wiped
from
painted
surfaces
immediately.
(24)
Drain
corrosion
preventative
mixture
from
engine
sump.
(25)
Install
and
safety
the drain
plug
with
wire. Refer
to
Chapter
20,
Safetying
-
Maintenance
Practices.
(26)
Install
the
lower
cowling.
Refer
to
Chapter
71,
Cowling
-
Maintenance
Practices.
(27)
Attach
a
warning
placard
on
the
throttle
control
knob
to
identify
that
the
engine
contains
no
lubricating
oil.
(28)
Placard
the
propeller
to the
effect that
it
must
not
be
moved while
the
engine
is in
storage.
NOTE: As
an
alternate
method
of
indefinite storage,
the
airplane
may
be
serviced according
to the
temporary storage procedures.
Run
up
at
the
maximum
intervals
of 90
days,
and
then
service
again
according
to the
procedures
in
temporary storage.
5.
Inspection
During
Flyable
Storage
A.
There
are
no
inspection
requirements
for
airplanes
in
flyable
storage.
6.
Inspection
During Temporary
Storage
A.
Airplanes
in
temporary
storage
must use
the
following
procedure
to
complete
an
inspection.
(1)
Inspect
the
airframe
for
corrosion
every
30
days.
(2)
Remove
the
dust
collections
as
frequently
as
possible.
(3)
Clean
and
wax
airplane
as
necessary.
1
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203
©
Cessna
Aircraft
Company
Jul
1/2007
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti 182
MAINTENANCE
MANUAL
(4)
Every
30
days
do
a
minimum
of
one
cylinder
inspection for
interior corrosion.
NOTE:
Do
not
move
the
crankshaft
during
an
inspection
of
the
interior
of
cylinder.
7.
Inspection
During
Indefinite
Storage
A.
Airplanes
in
indefinite storage
must
use the
following
procedure
to
complete
an
inspection.
(1)
Inspect
cylinder
Protex
plugs every seven
days.
Change
Protex plugs
if
their color
indicates
an
unsafe
condition.
(2) If
Protex plugs
have
changed
color
in
one
half
of the
cylinders,
all
desiccant
material
in
the
engine
must
be
replaced with
new
material.
(3)
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.
CAUTION:
The
corrosion
preventive
mixture
is
harmful
to
paint
and
shall
be
wiped
from
painted
surfaces immediately.
(4)
Spray
cylinder
interiors
with
corrosion
preventative
mixture
every
six
months
and
replace
the
desiccant
and
Protex
plugs.
1
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Page 204
©
Cessna
Aircraft
Company
Jul
1/2007
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
MOORING
-
MAINTENANCE PRACTICES
1.
General
A.
This section
provides
instructions
for
mooring
the
airplane.
2.
Mooring
Procedures
A.
When
mooring
the airplane
in
the
open,
head into the
wind
if
possible.
Tie
down
the
airplane
as
follows:
(1)
Tie ropes,
cables,
or
chains
to
the
wing
tie-down
fittings
located
at
the
upper
end
of
each
wing
strut. Secure
the
opposite
ends
of ropes,
cables,
or
chains to
ground
anchors.
(2)
Secure
a
tie-down
rope
(no
chains
or
cables)
to
upper
strut
of
the
nose
gear,
and
secure
opposite
end of
rope
to
a
ground
anchor.
(3)
Secure the
middle
of
a
rope
to
the
tail tie-down
ring.
Pull
each end
of rope
away
at
a
45°angle
and
secure
to
ground
anchors
at
each
side
of
tail.
(4)
Secure
control
lock
on
pilot
control
column.
If
control
lock
is not
available,
tie
pilot
control
wheel
back
with
front
seat
belt.
(5)
These
aircraft
are
equipped
with
a
spring-loaded
steering
bungee
which affords
protection
against
normal
wind
gusts.
However,
if
extremely
high
wind
gusts
are
anticipated,
additional
external
locks
may
be
installed.
10-20-00
Page
201
©
Cessna
Aircraft
Company
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
RETURN
TO
SERVICE
-
MAINTENANCE
PRACTICES
1.
General
A.
Airplanes
which
have
been
in
storage
must
be
returned to
service
prior
to
first
flight.
Procedures
for
returning
an
airplane
to
service
depend
on
length
of
time
the airplane
was
stored.
Refer
to
the following
procedures for
return
to
service after flyable storage,
temporary
storage
and
indefinite
storage.
2.
Flyable
Storage
Return to
Service
A.
Accomplish
the
following:
(1)
Perform
a
thorough
preflight inspection.
NOTE: At
the
end
of
the
first
25
hours
of
engine
operation,
drain
engine oil,
change
oil
filter
and
service
engine correct
grade
and
quantity
of
engine
oil.
3.
Temporary
Storage Return
to
Service
A.
Accomplish
the
following:
(1)
Remove
airplane
from
blocks
and
check
tires
for proper inflation.
Check
for
proper
nose
gear
strut
inflation.
(2)
Check
battery
and
install.
(3)
Ensure
oil
sump
has
proper
grade
and
quantity
of
engine
oil.
(4)
Service
induction air
filter
and
remove
warning
placard
from
propeller.
(5)
Remove
materials
used to
cover
openings.
(6)
Remove,
clean
and
gap
spark
plugs.
(7)
While
spark
plugs
are
removed,
rotate
propeller
several revolutions
to
clear excess
rust
preventative
oil
from
cylinders.
(8)
Install
spark
plugs.
Torque
plugs
to 330
inch-pounds
and
connect
spark
plug leads.
(9)
Check
fuel
strainer.
Remove
and
clean
filter
screen
if
necessary.
Check fuel
tanks
and
fuel lines
for
moisture
and
sediment.
Drain
enough
fuel
to
eliminate
any
moisture
and
sediment.
(10)
Perform
a
thorough preflight inspection, then
start
and
warm
up
engine.
4.
Indefinite
Storage
Return to
Service
A.
Accomplish
the
following:
(1)
Remove
aircraft
from
blocks.
Check tires
for
correct Inflation.
(2)
Check
and
install
battery.
(3)
Remove all
materials
used
to
seal
and
cover
openings.
(4)
Remove
warning placards
posted
at
throttle
and
propeller.
(5)
Remove
drain
plug and
allow preservative
oil
to drain from
engine
sump.
NOTE:
Preservative
oil
which
remains
in
sump
will
mix
with
engine
oil.
Flushing
of
the
oil
system
is
not
required.
(6)
Remove old
oil
filter.
Install
new
oil
filter.
(7)
Reinstall
drain
plug
and
service
engine
with
correct
quantity
and grade
of
engine
oil.
(8)
Service
and
install induction
air
filter.
(9)
Remove
dehydrator
plugs
and
spark plugs/plugs installed
in
spark
plug
holes. Rotate
propeller
several
revolutions
by hand
to
clear corrosion
preventative mixture
from
cylinders.
(10)
Clean,
gap
and install spark
plugs.
(11)
Rotate
propeller
by hand
through
compression stroke
of
each
cylinders
to
check
for
possible
liquid
lock.
Torque
plugs
to
330
inch-pounds.
(12)
Check
fuel
strainer.
Remove
and
clean
filter
screen
if
necessary.
Check
fuel
tanks
and
fuel
lines
for
moisture and sediment.
Drain
enough
fuel
to
eliminate
any
moisture
and
sediment.
(13)
Perform
a
thorough preflight inspection, then
start
and
warm
up
engine.
(14)
Thoroughly
clean and
test
fly
airplane.
10-30-00
Page
201
©
Cessna
Aircraft Company
April
1/2002
CHAPTER
PLACARDS
AND
MARKINGS
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
LIST
OF
EFFECTIVE
PAGES
11-Title
11-List
of
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11-Record
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Company
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CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
CONTENTS
PLACARDS
AND
MARKINGS
-
GENERAL.........................................
General
....................................................................
PLACARDS
AND
MARKINGS
-
INSPECTION/CHECK
..............................
S
cope......................................................................
Interior
and
Exterior
Placard
and
Decal
Inspection
.............................
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©
Cessna Aircraft
Company
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
PLACARDS
AND
MARKINGS
-
GENERAL
1.
General
A.
Placards
and
markings
on
the
exterior
surfaces
of
the
airplane
are
found
in
the
Model
182
Illustrated
Parts
Catalog,
Chapter
11.
11-00-00
Page
1
©
Cessna
Aircraft
Company
Mar
1/2004
I
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
PLACARDS
AND
MARKINGS
-
INSPECTION/CHECK
1.
Scope
A.
This
section
gives
information
about the
inspection
of
interior
and
exterior
placards.
2.
Interior
and
Exterior
Placard
and
Decal
Inspection
NOTE:
This
inspection
is
intended
to
be
an
overall
inspection
of
all
placards, decals,
and
markings
on
the
airplane.
A.
Inspect
the
Placards,
Decals
and
Markings.
(1)
Examine
the
interior
of the
airplane,
including
the
aft baggage
areas,
for
the installation
of
all
necessary
placards, decals
and
markings.
(a)
For
necessary
placards, decals,
and markings,
refer to
the
Model 182,
Illustrated
Parts
Catalog.
(2)
Examine the
exterior
of the
airplane for
the
installation
of
all
necessary
placards,
decals,
and
markings.
(a)
For
necessary
placards, decals,
and markings,
refer to
the
Model 182,
Illustrated
Parts
Catalog.
(3)
Examine
the
airplane identification
plate.
(a)
The
ID
plate
is
found
on
the
left
side
of
the
stinger, Zone
310.
Refer
to
the
Model
182,
Illustrated
Parts Catalog
and
Chapter
6,
Airplane
Zoning
-
Description
and
Operation.
11-00-00
Page
601
©
Cessna
Aircraft Company
Mar
1/2005
CHAPTER
SERVICING
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
LIST
OF
EFFECTIVE PAGES
CHAPTER-SECTION-SUBJECT
12-Title
12-List
of
Effective
Pages
12-Record
of
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12-Table
of
Contents
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12-11-00
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12-13-00
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Pages
701-705
Pages
701-703
Pages
1-2
DATE
April
1/2002
Jan
2/2006
Aug
4/2003
Jul
3/2006
Aug
4/2003
April
1/2002
Jul
3/2006
April
1/2002
April
1/2002
April
1/2002
April
1/2002
April
1/2002
April
1/2002
Jan
2/2006
April
1/2002
April
1/2002
April
1/2002
April 1/2002
April 1/2002
Mar 1/2005
Jan
2/2006
Jan
2/2006
©
Cessna
Aircraft
Company
12
-
LIST
OF
EFFECTIVE
PAGES
Page
1
of
1
Jul 3/2006
Temporary
Revision
Number
RECORD
OF
TEMPORARY REVISIONS
Page
Number
Issue
Date
By
Date
Removed
By
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
CONTENTS
SERVICING
-
GENERAL
.........
................................................
Scope....
..................................................................
Definition
...................................................................
REPLENISHING
-
DESCRIPTION
AND
OPERATION
...............................
G
e n e
ra
l.
.....
.......
. ...
......
............
.......
....................
.....
D
escription
................................................................
Fuel
Capacity
Table
.........................................................
Approved
Fuel
Table
........................................................
Engine
Oil
Capacity
Table....................................................
NOSE
LANDING GEAR
SHOCK
STRUT
-
SERVICING
.............................
General
....................................................................
Shock
Strut
Servicing Procedures
............................................
NOSE
LANDING GEAR
SHIMMY
DAMPER
-
SERVICING
..........................
General...................................................................
Shimmy
Damper
Servicing
(For
airplanes that
do
not
have
the Lord
Shimmy
Damper)
.................. .........
..
..........
Shimmy Damper
Servicing
(On
Airplanes
with
the
Lord
Shimmy
Damper)
........
HYDRAULIC
BRAKES
-
SERVICING
..............................................
G
eneral
............................
........................................
FUEL AND
ENGINE
OIL
-
DESCRIPTION
AND
OPERATION........................
G
en
eral
....................................................................
Fuel
Precautions
.........
............................
.....................
O
il
Precautions
.............................................................
FUEL
-
SERVICING
..............................................................
General
....................................................................
Safety
and
Maintenance Precautions
.........................................
Fuel
Servicing
..............................................................
Fuel
Additive
(DiEGME)
Precautions
.........................................
Fuel
Additive Procedures
............................
........................
ENGINE
OIL
-
SERVICING
.......................................................
General
............................
.........
...............................
Oil
Change
Intervals..........
.........
.....................................
Checking
Engine
Oil.........................................................
Changing Engine
Oil
........................................................
INDUCTION AIR
FILTER
-
SERVICING
..........................................
General
....................................................................
Air
Filter
Servicing...........................................................
VACUUM
SYSTEM
FILTERS
-
SERVICING
........................................
General
....................................................................
Central
Air
Filter
Servicing
...................................................
Vacuum
System Relief
Valve
Filter............................................
BATTERY
-
SERVICING
..........................................................
G
eneral
....................................................................
Battery
Servicing............................................................
TIRES
-
SERVICING
.........
....................................................
General
............................
........................................
Safety
Precautions
and
Notes............................
....................
Tire
Servicing
...............................................................
Cold
Weather
Servicing......................................................
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301
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301
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301
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302
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303
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301
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301
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301
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301
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301
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301
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301
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301
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301
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301
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301
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301
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301
12-18-00
Page
302
CONTENTS
Page
1
of
3
Jul 3/2006
©
Cessna Aircraft
Company
CESSNA
AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
SCHEDULED SERVICING
-
DESCRIPTION
AND
OPERATION.....................
General
....................................................................
Description
.................................................................
LUBRICANTS
-
DESCRIPTION
AND
OPERATION
.................................
General
....................................................................
Lubrication Service
Notes....................................................
Definition
of
"As
Needed"
...................................................
Recommended
Lubricants
Table
.............................................
BATTERY
TERMINALS
-
SERVICING
............................................
General
....................................................................
Battery
Terminal
Lubrication..................................................
LANDING
GEAR
AND
PARKING BRAKE
-
SERVICING
.............................
General
....................................................................
Wheel
Bearing
Lubrication...................................................
Nose
Gear
Torque
Link
Lubrication
...........................................
Shimmy
Dampener
Pivots
Lubrication
........................................
Steering
System
Needle
Bearing
Lubrication
..................................
Nose
Gear
Steering
Pushrods
Lubrication
....................................
Parking
Brake
Handle
Shaft
Lubrication.......................................
FLIGHT
CONTROLS
-
SERVICING..............................................
General
....................................................................
Aileron System
Lubrication...................................................
Flap
System
Lubrication
.....................................................
Elevator
System
Lubrication
.................................................
Rudder
System
Lubrication
..................................................
ENGINE
CONTROL
CABLES
-
SERVICING
.......................................
General
...................................................................
Engine
Control
Cables
Lubrication
...........................................
HEATING
AND
VENTILATION
CONTROL
CABLES
-
SERVICING
...................
General
....................................................................
Heating
And
Ventilation Control
Cables
Lubrication.............................
AIRPLANE
EXTERIOR
-
CLEANING/PAINTING
....................................
General
....................................................................
P
recautio
ns
................................................................
Preventive Maintenance
.....................................................
Windshield
and
Window Cleaners
............................................
Cleaning
Windshield
and
Windows
...........................................
Waxing
and
Polishing
Windshield
and
Windows
...............................
Aluminum Surfaces
.........................................................
Painted
External
Surfaces
...................................................
Cleaning
the
Engine
and Engine
Compartment
................................
Propeller
...................................................................
Tires
and
Wheels
...........................................................
Stabilizer
Abrasion
Boots
....................................................
INTERIOR
-
CLEANING/PAINTING................................................
General
....................................................................
Interior Cleaning
Materials
...................................................
Cleaning Interior
Panels
.....................................................
Cleaning
Carpet
............................................................
Cleaning
Seats
.........
....................................................
Cleaning
the
GDU
1040
Display Lens
.........................................
12-20-00
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1
12-20-00
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1
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1
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301
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Page 301
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301
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301
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301
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Page 301
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Page
301
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301
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301
12-21-04
Page 301
12-21-05
Page
301
12-21-05
Page
301
12-21-05
Page
301
12-22-00
Page
701
12-22-00
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701
12-22-00
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701
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701
12-22-00
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702
12-22-00 Page
702
12-22-00
Page 703
12-22-00
Page
703
12-22-00
Page
703
12-22-00
Page
703
12-22-00
Page
705
12-22-00
Page
705
12-22-00
Page
705
12-23-00
Page
701
12-23-00
Page
701
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Page
701
12-23-00
Page
701
12-23-00
Page
701
12-23-00
Page
702
12-23-00
Page
703
CONTENTS
Page
2
of
3
Jul
3/2006
©
Cessna
Aircraft
Company
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
UNSCHEDULED
SERVICING
-
DESCRIPTION AND
OPERATION
..................
G eneral
....................................................................
Extreme
Weather
Maintenance...............................................
Ground
Power
Receptacle
...................................................
Cold
Soak
............................
......................................
12-30-00
Page
1
12-30-00
Page
1
12-30-00
Page
1
12-30-00
Page
1
12-30-00
Page
1
CONTENTS
Page
3
of
3
Jul
3/2006
©
Cessna
Aircraft Company
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
SERVICING
-
GENERAL
1.
Scope
A.
This
chapter provides instructions
for
the
replenishment
of
fluids,
scheduled
and
unscheduled
servicing
applicable
to
the
entire
airplane. Personnel
shall
observe
safety
precautions
pertaining
to
the
individual
servicing
application.
2.
Definition
A.
This
chapter
is
divided
into
sections
to
aid
maintenance
personnel
in
locating
information. Consulting
the
Table
of
Contents
will
further assist
in
locating
a
particular subject.
A
brief
description
of
each
section
follows.
(1)
The
section
on
replenishing
is
subdivided
into
categories
to
group
servicing
information,
such
as,
systems
requiring
hydraulic
fluid
or
compressed
gas.
A
brief
description
of
the
subdivision
subjects
follows.
(a)
Replenishing
charts for
the
liquids
most
commonly
used
to
service
the
airplane
are
grouped
together
to
aid
maintenance personnel
in
servicing.
(b)
The
subdivision
of
fuel
and
oil
provides maintenance
personnel with general
servicing
procedures. Safety
precautions
and
servicing
procedures
required
by
federal
and
local
regulations
may
supersede
the
procedures
described.
(c)
The
subject
on
hydraulic fluid
servicing
provides
servicing
procedures
for
the
airplane
hydraulic
brake system,
nose
gear shimmy
damper
and
nose
gear
strut.
(d)
The
remaining subject
subdivisions
provide
service
information
on
either
a
system,
an
assembly
or
a
component.
(2)
The
section
on
scheduled
servicing includes lubrication
information,
external
cleaning
and
internal
cleaning.
The
section
is
subdivided
to
provide individual
system,
assembly
or
component
service
information.
12-00-00
Page
1
April 1/2002
©
Cessna
Aircraft
Company
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
REPLENISHING
-
DESCRIPTION
AND OPERATION
1.
General
A.
This section
provides maintenance
personnel
with
servicing
information
for
replenishing
fuel
and
oil.
2.
Description
A.
For
an
illustration of
service
points located
on
the airplane,
refer
to Figure
1.
This illustration
may
be
used
in
conjunction
with
replenishing
tables
to
aid
maintenance
technicians
in
servicing
the
airplane.
B.
The
following
tables
are
provided
to
establish replenishment
capacities
of
various
systems:
(1)
Fuel
Capacity
(Table
1)
(2)
Approved
Fuels
(Table
2)
(3)
Engine
Oil
Capacity
(Table
3)
3.
Fuel
Capacity
Table
A.
The
following table
lists
airplane
fuel
capacity.
WARNING:
Only aviation
grade
fuels
are
approved
for
use.
Table
1.
Fuel
Capacity
TANK
Fuel
Capacity
Usable
Fuel
U.S.
92.0
Gallons
88.0
Gallons
4.
Approved
Fuel
Table
A.
The
following
table
lists
approved
fuels
for
use
in
the
airplane.
Table
2.
Approved
Fuels
TYPE
OF
FUEL
100
LL
100
SPECIFICATION
ASTM-D910
ASTM-D910
For
other fuels that
can
be
used
in
Russia,
refer
to
Lycoming
Service
Instruction
No.
1070M
(or
subsequently
approved
Lycoming
Service
Instruction
revision).
5.
Engine
Oil Capacity
Table
A.
The
following
table
lists oil
capacity
for
the
airplane.
12-10-00
Page
1
Jan
2/2006
©
Cessna Aircraft
Company
COLOR
Blue
Green
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
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.
In
a
laboratory
study,
mice
developed
skin
cancer
after
skin
was
exposed
to
used
engine
oil
twice
a
week
without
being
washed
off.
Substances
found to
cause
cancer
in
laboratory
animals
may
also
cause
cancer
in
humans.
Table
3.
Engine
Oil
Capacity
SYSTEMS
U.S.
Quarts
Engine
Oil (total with
filter,
oil
cooler
and
cooler
13.0
quarts
hoses)
©
Cessna
Aircraft
Company
12-10-00
Page
2
Jan
2/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
B1090
FUEL
SELECTOR
AND
DRAINS
GROUND
SERVICE
RECEPTACLE
NOSE
LANDING
GEAR
SHOCK
STRUT
NOSE
GEAR
TIRE
0710T1014
Airplane Service
Points
Figure
1
(Sheet
1)
12-10-00
Page3
Jan
2/2006
©
Cessna
Aircraft
Company
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
NOSE
LANDING
GEAR
SHOCK
STRUT
-
SERVICING
1.
General
A.
It
is
necessary
to
examine
the
nose
gear
shock
strut
at
intervals
to make sure
the
strut
is
filled
with
hydraulic
fluid
and
is
inflated
to
the
correct
air
pressure. This
procedure
only
gives
instructions
to
fill
the
nose
gear
shock
strut
and to
service
the
nose
gear
shock
strut.
For
procedures
to
disassemble
and
repair, refer
to Chapter
32,
Nose
Landing
Gear
-
Maintenance
Practices.
2.
Shock
Strut Servicing
Procedures
A.
Service
the
nose
gear
shock
strut
as
follows:
(1)
Remove the
air
valve
cap
and
release
all
air.
(2)
Remove the air
valve
housing
assembly.
(3)
Compress
the
strut
fully
until
the strut's bottom fork
touches
the
top
barrel
housing.
(4)
Examine
the
hydraulic
fluid
level
and add
fluid
as
necessary.
NOTE:
Fluid
used must agree with
specification
MIL-PRF-5606.
(5)
(6)
(7)
(a)
Make
sure
the
hydraulic
fluid
level
is
at
the
bottom
of
the
air
valve
installation
hole.
Fully extend
the
strut.
Install
the
air valve housing
assembly.
With
strut
fully
extended
and
the
nose
wheel
off
of
the
ground,
inflate
the strut to
55
to 60
PSI.
NOTE:
The
nose
landing gear
shock
strut
will use
only
minimum
service.
Strut
extension
pressure
must
be
kept
at
55
to 60
PSI.
Use
a
clean,
lint-free
cloth
soaked
with
MIL-
PRF-5606
or
kerosene
to
clean the machined
surfaces
of
dirt
and
dust.
12-11-00
Page
301
©
Cessna Aircraft Company
Aug
4/2003
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
NOSE
LANDING
GEAR
SHIMMY
DAMPER
-
SERVICING
1.
General
A.
The
nose
gear
shimmy damper
(on
airplanes
that
do
not
have
the
Lord
Shimmy
Damper)
contains
a
compensating
mechanism
in
the
hollow
piston
rod.
This
is
for
thermal
expansion
and
contraction
of
the
hydraulic
fluid
in
the damper.
The
shimmy
damper
must
be
filled fully
with
hydraulic
fluid
and
be
free
of
air.
Before
the
servicing
of
the
shimmy damper,
make
sure that
the
compensating
piston
is at
the bottom
in
the
piston
rod.
To
disassemble
the
shimmy
damper, refer
to
Chapter
32,
Nose
Gear
-
Maintenance Practices.
B.
The nose
gear
shimmy damper
(on
airplanes
with
the
Lord
Shimmy
Damper)
uses
rubber
with
a
lubricant
to
absorb
nose
wheel
vibration.
The
damper
piston
shaft
is
attached
to
a
stationary
part,
and
the
housing
is
attached
to the
nosewheel
steering
torque
arm
assembly, which moves
as
the
nosewheel turns,
causing
relative
motion between
the
damper shaft
and the
housing.
2.
Shimmy
Damper
Servicing
(For
airplanes that
do
not
have
the
Lord
Shimmy
Damper)
A.
Do
the servicing
of
the shimmy
damper
as
follows
(Refer
to
Figure
301).
(1)
Remove the
shimmy
damper
from
the
airplane.
Refer
to
Chapter
32,
Nose
Landing Gear
-
Maintenance
Practices.
(2)
Hold
the
shimmy damper
in a
vertical
position
with
the
filler
plug
pointed
up.
(3)
Loosen the
filler
plug
to
drain
the
unwanted
fluid.
(4)
Let
the
spring
go
to
the
bottom of
the
floating
piston
in
the
shimmy damper
rod.
(5)
When
the
flow
of the
fluid
stops,
put
a
length
of
rigid
wire
through
the
bleed
air
hole
in
the
setscrew
which
is
found
at the
end
of
the
piston
rod
until the
rigid
wire
touches
the
floating
piston.
(6)
Insert
the
wire
to
the
depth
of
3.81
inches (95.25
mm).
NOTE:
If
the
wire
insertion
is
less than
3.81
inches (95.25
mm),
the
floating
piston
will
not
move
freely
in
the
shaft.
(a)
Use
the
rigid
wire
to
release
the
floating
piston.
(b) If
the
floating
piston cannot
be
released
with
the
rigid
wire,
you
must
replace
the
rod
assembly
and
the piston.
(7)
Make
sure
that
the
floating
piston
is at
the
bottom.
(8)
Move
the
damper
rod
to put the
piston
at
the
end
of
the
barrel
which
is
opposite
of
the
filler
plug.
CAUTION:
Dirt
and
dust
can
cut
the
seals
in
the
barrel.
Use
a
clean,
lint-free
cloth
soaked
with
MIL-PRF-5606
hydraulic
fluid
or
kerosene
to
keep
the
machined
surfaces
clean.
(9)
Remove the
filler
plug
and
fill
the shimmy
damper
with
hydraulic
fluid.
(a)
To
fill
the
shimmy
damper,
make sure
the
shimmy
damper
and
MIL-PRF-5606
hydraulic
fluid
are
at
70°F
to
80°F
(21°C
to
26°C).
(b)
Keep
the
shimmy
damper
and
the
visual
parts of the
piston shaft
clean
from
dirt and
dust.
(10)
Install the
filler
plug and
clean the damper
in
cleaning agent.
(11)
Dry
the
damper
with
a
clean cloth.
(12)
Install the
damper
on
the
airplane.
Refer
to Chapter
32,
Nose
Landing
Gear
-
Maintenance
Practices.
12-12-00
Page
301
©
Cessna Aircraft Company
Jul 3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
M
FILLER
BARREL
SNAP
RING
N
HEAD
BACKUP
RING
PACKING
RING
BACKUP
RING
RING
ROLL
PIN
RING
PISTON
SETSCREW
DETAIL
A
Shimmy
Damper
Servicing
Figure
301
(Sheet
1)
©
Cessna Aircraft
Company
12-12-00
Page 302
Jul
3/2006
0710T1001
A0741R
1010
CESSNA
AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
3.
Shimmy
Damper
Servicing
(On
Airplanes with
the
Lord
Shimmy
Damper)
A.
Lord
Shimmy
Dampers
do
not
need
special servicing.
However,
you
must
lubricate
the
nose
wheel
shimmy
damper
pivots
with
general
purpose
oil
MIL-L-7870.
B.
Keep
the
shimmy damper
clean.
(1)
Clean
the
shimmy
damper
with
a
clean,
lint-free cloth
to
prevent the
collection
of
dust and
grit.
(2)
Make
sure
that
the
part
of the
damper
piston
shaft
that
you
can
see
is
always
clean.
(3)
Clean
the
machined surfaces
of
the
shimmy damper
with
a
clean,
lint-free
cloth
to
prevent
the
collection
of
dust
and
dust.
C. If
necessary,
exercise
a
shimmy
damper
before
installation.
(1) If a
shimmy
damper
has
been
in
storage
for
a
long period, make
sure
that
it
moves
freely
before
you
install
it.
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
cause
damage
to
the
shimmy
damper.
If
you
continue
to
pull
on
a
fully
extended
shaft,
you
can
cause
damage
to
the
shimmy
damper.
(2) If
the
shimmy damper
does
not
move
freely,
push
and pull
the
shaft
through
complete
cycles
until
it
does
move
freely.
When
the
shimmy damper shaft
has
come
to
its
limit of
travel
up and
down
as
you
push
and
pull, make sure
that
you
do
not
continue
to push
or pull
it
beyond
that
limit
of
travel.
12-12-00
©
Cessna
Aircraft
Company
Page
303
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
HYDRAULIC
BRAKES
-
SERVICING
1.
General
A.
Complete
the
brake
master
cylinders servicing
as
specified
in
the
time
intervals set
in
Chapter
5,
Inspection
Time
Limits.
B.
Brake
master
cylinders
are
found
on
the rudder pedals
and
are
filled
with
MIL-PRF-5606
hydraulic
fluid.
To
fill
and
bleed
the
brake system,
refer
to
Chapter
32,
Brakes
-
Maintenance
Practices.
12-13-00
Page
301
©
Cessna
Aircraft Company
Aug
4/2003
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
FUEL
AND
ENGINE
OIL
-
DESCRIPTION
AND
OPERATION
1.
General
A.
This
section provides
servicing
procedures
for
the
fuel
and
engine
oil system.
It is
subdivided
as
follows:
(1)
The
fuel
system section
includes
procedures
for
adding
fuel,
defueling
the
airplane
and
mixing
anti-icing additives
to
the
fuel.
(2)
The engine
oil
section includes
procedures
for
checking,
adding
and
changing
engine
oil.
2.
Fuel
Precautions
A.
Safety
Precautions.
(1)
The
safety precautions
on
fueling
and
defueling
may
be
superseded
by
local
directives.
However,
following
is
a
typical
list
of
precautions.
(a)
Ground,
by
designated
grounding
cables,
the
fueling and/or defueling
vehicle
to
the
airplane.
Also,
a
static
ground
device
shall
contact the fueling
or
defueling
vehicle
and
ground.
(b)
Fire
fighting
equipment
shall
be
immediately
available.
(c)
Wear proper
clothing.
1
Do
not
wear
clothing that
has
a
tendency
to
generate
static
electricity,
such
as,
nylon
or
synthetic
fabrics.
2
Do
not
wear
metal
taps
on
shoes
when
working
in
areas
where
fuel
fumes
may
accumulate
at
ground
level.
(d)
The
airplane
shall
be
in a
designated
fuel
loading
or
unloading
area.
(e)
High
wattage,
pulse
transmitting
avionics
equipment
shall
not
be
operated
in
the immediate
vicinity.
B.
Maintenance Precautions.
(1)
Use
designated equipment
for
fuel
loading
and
unloading
to
prevent contamination.
(2)
Use
proper
procedures
when adding
fuel
inhibitors.
(3)
Use
specified
type
of
fuel.
3.
Oil Precautions
A.
Maintenance Precautions.
(1)
Use
proper
servicing
procedures; do
not
overfill,
do not
mix
manufacturers brands
of
oil.
12-14-00
Page
1
©
Cessna
Aircraft
Company
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
FUEL
-
SERVICING
1.
General
A.
Fuel Tanks.
(1)
Each
wing
has
a
fuel
tank.
You
can
find
the
fuel
tanks
between
the
forward
and aft
spars
that
extend
from
WS
23.62
to
WS
85.96.
You
must
fill the
fuel
tanks
immediately
after
each
flight
to
decrease
the amount
of
condensation that
can
be
produced
in
the
tanks
and
fuel
lines.
A
fuel
filler
cap
that
vents
is
found
on
top
of
each
wing
to
fuel
and
defuel
each fuel
tank.
B.
Fuel
Drains.
(1)
Fuel
drains
are
at
various
places
throughout
the
fuel
system,
and
are
used
to
collect
fuel
samples
for
analysis.
To
collect
fuel
samples,
you put
a
fuel
sample
cup
up
to
the
valve
and
push
up on
the
valve
with
the
rod
on
the
cup.
NOTE:
For
detailed description
and
maintenance
practices
related
to
the
fuel
system,
refer
to
Chapter
28,
Fuel
-
General.
2.
Safety
and
Maintenance
Precautions
A.
Safety
Precautions.
WARNING:
Keep
fire
fighting
equipment
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.
Make
sure the
battery
switch
is
turned
off,
unless
otherwise
specified.
(1)
Connect
an
electrical
ground.
(a)
Ground the
airplane
with
two
ground wires.
Connect
the
wires
from
the
tie-down
rings
to
the
ground
stakes.
(b)
Ground the
vehicle
(or hose
cart)
to
the same ground
stakes
as
the
airplane.
(c)
Ground
the
vehicle
(or hose
cart)
to
the
airplane.
(d)
Ground the
refuel
nozzle
to
the airplane.
(2)
Make sure
the
equipment
to
fight fires
is
available.
(3)
Do
not
wear
clothes such
as
nylon
or
synthetic
fabrics
that
can
make
static
electricity.
(4)
Do
not
wear
metal
taps
on
shoes.
(5)
The
airplane
must
be
in
a
designated
fuel
loading/unloading
area.
(6)
High
wattage,
pulse
transmitted
avionics
equipment
must
not be
operated
in
the area
when
you
fill
or
drain the
fuel.
B.
Maintenance
Precautions.
(1)
Use
approved equipment
to
fill
or
remove
fuel
to
prevent
contamination.
(2)
Use
the authorized
type
of
fuel
and
anti-ice additive.
It is
very
important that
the
correct anti-ice
additive
mix
procedures
be
followed.
Incorrect
mixture
of
the
fuel
and
anti-ice additive
will
cause
damage
to the
interior finish
of
the
fuel
tank, which
increases
corrosion.
(3)
Use
an
authorized
type
of
fuel
and
anti-ice additive.
(4)
When
you
fuel
the
airplane,
make
sure
you
do
not
mix the
fuel
with
the
anti-ice
additive
and
the
fuel without
the
anti-ice
additive.
3.
Fuel
Servicing
A.
Fuel
Fill
Procedures.
12-14-01
Page
301
©
Cessna
Aircraft
Company
Jul 3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
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.
(1)
Electrically ground
airplane
and
vehicle.
Refer
to
the
Safety
and
Maintenance
Precautions.
(2)
Make
sure
that
the battery
switch
is
turned
to
OFF.
(3)
Put
a
protective
mat
around
the
fuel
filler
area
and
remove
the
fuel
filler
caps.
(4)
Fuel
the
airplane
with the
correct
grade
of
aviation
fuel.
(5)
Install
the
filler
caps.
Wipe
up
the
excess
fuel
from
the
wing area.
(6)
Remove
the
equipment
that
you
used to
ground
the
airplane.
B.
Fuel
Removal
Procedures.
(1)
Electrically ground
the
airplane
and
the
vehicle.
(2)
Make sure
that
the
battery
switch
is
turned
to
OFF.
(3)
Remove
the
fuel
filler
caps.
(4)
Put
the
defueling
nozzle
into
the
fuel
bay
and
begin
to
defuel.
(5)
Remove
as
much
fuel
as
possible
with
the defuel
nozzle.
(6)
Remove
the drain
valves
from
the
bottom
of
the
fuel
tank
and
drain
the
remaining fuel.
(7)
Remove
grounding equipment.
4.
Fuel
Additive
(DiEGME)
Precautions
WARNING:
WARNING:
CAUTION:
CAUTION:
MIL-1-85470
anti-ice additive
is
toxic.
It
is
dangerous
to
health
when
breathed
and/or
absorbed
into
the
skin.
When
you
service
fuel
with
the
anti-ice
additive
in
an
unventilated
area,
use
applicable
personal
protective
equipment
such
as
eye
goggles/shield,
respirator
with
organic
vapor
cartridges,
non-absorbing
gloves
and
additional skin
protection
from
spraying
or
splashing
anti-ice
additive.
If
anti-ice
additive
enters
the eyes,
flush
with
water
and
contact
a
physician
immediately.
Anti-icing
additives
that
contain
DiEGME
are
harmful
if
inhaled,
swallowed,
or
absorbed
through
the
skin
and
will
cause
eye
irritation.
DIEGME
is
also
combustible.
Before
you
use
this
material,
refer
to
all
of
the safety
information
on
the
container.
It
is
extremely
important
to
mix
anti-ice
additives
with
fuel
correctly,
because
more
concentration
than
recommended
can
cause damage
to
the
fuel
tanks,
such
as
deterioration
of
protective
primer
and
sealants
and
damage
to
O-rings
and
seals
in
the
fuel
system
and
engine
compounds.
Use
only equipment that
is
recommended
by
the
manufacturer
to make
sure
that
you
get the
correct
proportion
when
you
blend the
anti-ice
additives
with the
fuel.
Do
not
let
the
concentrated
anti-ice
additive
come
in
contact
with
the
airplane
finish
or fuel
cell,
as
it
can
cause
damage.
A.
When you
service
fuel with
anti-icing
additives
that
contain Diethylene
glycol
monomethyl
ether
(DiEGME,
MIL-I-
85470), remember that
they
are
harmful
if
inhaled,
swallowed,
or
absorbed
through
the
skin,
and will
cause
eye
irritation.
Also,
they
are
combustible.
Before
you
use
this
material,
refer
to
all
safety
information
on
the container.
B.
DiEGME
is
toxic
under
sustained
exposure environments.
When
inhaled,
DiEGME
is
primarily
a
central
nervous
system depressant, although various
animal
studies
have
revealed
that
acute
inhalation
overexposure
may
cause kidney
injury.
The
primary symptoms
of
inhalation
overexposure
12-14-01
Page
302
©
Cessna
Aircraft
Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
in
confined
or
poorly
ventilated
areas
include
headache, drowsiness,
blurred
vision,
weakness,
lack
of
coordination,
tremor,
unconsciousness,
and
even
death.
When
ingested (swallowed)
in
massive
doses,
DiEGME
is
reported
to
exhibit
a
narcotic
action,
but
at
lower dosage levels,
death
is
delayed
and
is
accompanied
by
lung
edema
(excessive serious
fluid
in
lungs),
slight
liver
injury
and
marked
kidney
injury.
DiEGME
is
only mildly
irritating
to the
eyes
and
skin;
however,
it
can
be
readily
absorbed
through the
skin
in
toxic
amounts.
Symptoms
of
overexposure
due
to
skin
absorption
are
essentially
the
same
as
those
outlined
for inhalation.
C. In
the
event
DiEGME
contact
is
experienced,
the
following
emergency
and
first
aid
procedures
should
be
used.
(1) If
DiEGME
is
inhaled,
remove
person
to
fresh
air.
If
the
person
is
not
breathing, give
artificial
respiration, preferably
mouth-to-mouth;
however,
if
breathing
is
difficult,
administer
oxygen.
Always
call
a
physician.
(2) If
ingested (swallowed),
drink
large
quantities
of water.
Then
induce vomiting by placing
a
finger
far
back
into
the
throat.
Contact
a
physician
immediately.
If
vomiting cannot
be
induced,
take
victim
immediately
to
the
hospital
or
a
physician.
If
victim
is
unconscious
or
in
convulsions,
take
victim
immediately
to the
hospital
or
a
physician.
Do not
induce
vomiting
or
give anything
by
mouth to
an
unconscious
person.
(3) If
eye
or
skin
contact
is
experienced, flush
with
plenty
of
water
(use
soap
and
water
for skin)
for
at
least
15
minutes
while
removing
contaminated clothing
and
shoes.
Call
a
physician. Thoroughly
wash
contaminated
clothing
and
shoes
before
reuse.
D.
Additional
antistatic
and
biocidal
protection
may
be
provided
using
approved products.
Refer
to
the
Tools,
Equipment
and
Materials
section
for
approved
manufacturers. Refer
to
the
Pilot's
Operating
Handbook
and
FAA
Approved Airplane
Flight Manual
for
concentration levels
of
these products.
5.
Fuel
Additive
Procedures
A.
Strict
adherence
to
recommended preflight draining
instructions
will
eliminate
any
free water
accumulations
from
the
tank
sumps.
While
small amounts
of
water
may
still
remain
in
solution
in
the
gasoline,
it
will
normally
be
consumed
and
go
unnoticed
in
the
operation
of
the
engine.
B.
One
exception
to
this
can
be
encountered
when
operating
under
the
combined effect
of:
1)
use
of
certain
fuels,
with
2)
high
humidity
conditions
on
the
ground
3)
followed
by
flight
at
high
altitude
and
low
temperature.
Under
these
unusual
conditions
small
amounts
of
water
in
solution
can
precipitate
from the
fuel
stream and
freeze
in
sufficient quantities
to
induce
partial
icing
of
the
engine fuel
system.
C.
While
these
conditions
are
quite
rare
and
will not
normally
pose
a
problem
to
owners
and
operators,
they
do
exist
in
certain
areas
of
the world
and
consequently
must
be
dealt
with,
when
encountered.
D.
Therefore,
to
alleviate
the
possibility
of
fuel
icing
occurring
under
these
unusual
conditions,
it
is
acceptable
to add
isopropyl
alcohol
or
Diethylene glycol
monomethyl
ether
(DiEGME)
compound
to
the
fuel
supply.
E.
The
introduction
of
alcohol
or
DIEGME
compound
into
the
fuel gives
two
distinct
effects:
1)
it
absorbs
the
dissolved
water
from
the
gasoline
and
2)
alcohol
has
a
freezing temperature
depressant
effect.
F.
Alcohol
which
meets
specification
MIL-F-5566
or
Federal
Specification
TT-I-735
and has
a
maximum
water
content
not
exceeding
0.4
percent
by
volume,
may be
used.
If
used,
it is
to
be
blended
with
the
fuel
in
a
concentration
of
1%
by
volume.
Concentrations
greater
than
1%
are
not
recommended
since they
can
be
detrimental
to
fuel
tank
materials.
G.
The manner
in
which
the
alcohol
is
added
to
the
fuel
is
significant
because alcohol
is
most
effective
when
it
is
completely dissolved
in
the
fuel.
To
ensure
proper
mixing,
the
following
is
recommended:
(1)
For
best
results
the
alcohol
should
be
added
during
the
fueling operation
by
pouring
the
alcohol
directly
on
the
fuel
stream
issuing
from
the fueling
nozzle.
(2)
An
alternate
method
that
may
be
used
is
to premix
the
complete alcohol dosage
with
some
fuel
in a
separate
clean
container (approximately
2
to
3
gallon
capacity)
and
then
transfer this
mixture
to
the
tank
prior
to
the
fuel
operation.
12-14-01
Page
303
©
Cessna
Aircraft Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
H.
Diethylene
glycol
monomethyl
ether
(DiEGME)
compound
in
compliance
with
MIL-I-85470,
if
used,
must
be
carefully
mixed. Refer
to
Pilot's
Operating Handbook
And
FAA
Approved Airplane
Flight
Manual
for
fuel/DiEGME
mixing ratios.
I.
Prolonged
storage
of
the
airplane
will result
in a
water
buildup
in
the
fuel
which
"leeches
out"
the
additive.
An
indication
of
this
is
when
an
excessive
amount
of
water
accumulates
in
the
fuel
tank
sumps.
The
concentration
can
be
checked
using
a
concentration
tester.
It
is
imperative
that
the
technical
manual for
the
tester
be
followed
explicitly
when
checking
the
additive concentration.
12-14-01
Page
304
©
Cessna
Aircraft
Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
ENGINE
OIL
-
SERVICING
1.
General
A.
This
section provides instructions
to
examine
and
change
the
engine
oil.
2.
Oil
Change
Intervals
NOTE:
An
inspection
of the
filter
can
aid
in
the
detection
of
premature
engine
wear.
Refer to Lycoming
Service Bulletin
480D
or
latest
revision.
A.
Oil
Change Intervals.
(1)
Airplanes
are
delivered
from
the
factory
with
aviation
grade
mineral
oil
conforming
to SAE
J1966.
During
the
first
25
hours
of
engine operation,
it
may
be
necessary
to
add
oil.
Use
an
aviation
grade mineral
oil
of
the recommended
viscosity
conforming
to
SAE
J1966.
After
the first
25
hours,
drain
the
engine
oil
and
change
the
filter.
Fill
the
oil
sump
with
aviation grade mineral
oil
of
the
recommended
viscosity,
conforming
to
SAE
J1966.
Use
it
until
a
total
of
50
hours
of
engine
operation
has
occurred
or oil
consumption
has
stabilized.
Then
the
sump
must
be
drained
and
ashless dispersant
oil
conforming
to
SAE
J1899, must
be
added
to
the
engine.
NOTE:
The
turbocharged
engines
use
only
ashless
dispersant
oil
conforming
to
SAE
J1899,
even
during
the
engine
break-in period.
(2)
For
other
engine change
intervals,
refer to
Chapter
5,
Inspection
Time
Limits.
3.
Checking
Engine
Oil
A.
Engine
Oil
Checking
Procedures.
Refer
to
Chapter
71,
Engine
-
Description
And
Operation,
Figure
1.
(1)
Five
to
ten
minutes
after
the
engine
has
been
stopped,
exam
the
engine
oil
with
the
dipstick .
The
airplane
must
be
in
a
level
position
as
much
as
possible
for
the best
indication.
(2)
Open
the engine
oil
door
on
the
upper
cowling.
(3)
Remove
the
dipstick
from
the
engine
and
wipe
down with
a
clean
cloth.
(4)
Insert
the
dip
stick
fully
and
remove.
(5)
Exam
the
oil
level
on
the
dipstick.
(6)
If
the
oil
is
low,
add
the correct
quantity
and
viscosity
of
aviation
grade
engine
oil.
NOTE:
The airplane
may be
operating
with
SAE
J1966
(straight mineral
oil)
during
the
initial
break-in
period or
after
an
overhaul.
After
the
break-in
period,
use
a
ashless
dispersant
oil
conforming
to
SAE
J1899.
Make sure
the
proper
oil
type
is
used when
servicing
the
engine.
(7)
Insert
the
dipstick
in
the
filler
tube
and do
a
check for
correct
seating.
(8)
Close
the engine
oil door.
4.
Changing
Engine
Oil
A.
Oil
Changing
Procedures. Refer
to
Chapter
71,
Figure
1
Engine
-
Description
And
Operation.
NOTE:
The nose
of
the
airplane
must
be
raised
slightly
for
more
positive draining
of
any
sludge
which
may have
collected
in
the engine
oil
sump.
(1)
Operate
engine
until
oil
temperature
is
at
a
normal
operating
temperature.
NOTE: Normal
operating temperature
is
within
the
green
arc
of
the oil
temperature
gage.
The
engine
oil
must
be
drained
while
the
engine
is
still
warm.
(2)
Shut
off
engine
and
remove
the
upper
and
lower
cowling
to get
access
to the
oil
drain plug
and
external
oil
filter.
Refer
to
Chapter
71,
Cowling
-
Maintenance
Practices.
12-14-02
Page
301
©
Cessna Aircraft Company
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
WARNING:
Avoid
skin contact
with
engine
oil.
Any
engine
oil
that
inadvertently
gets
on
the
skin
should
be
immediately
removed.
(3)
Remove
and
discard
the
wire
from
the
drain
plug.
(4)
Remove the drain
plug
and
let
the
oil
drain
into
an
applicable
container.
(5)
After the
engine
oil
has
drained, install
and
safety
the
drain
plug
with wire. Refer
to
the
Lycoming
SSP-1776
Table of
Limits
or latest
revision, for torque
requirements
and
refer to
Chapter
20,
Safetying
-
Maintenance
Practices.
(6)
Remove the
suction screen
from
the
oil
sump.
(a)
Do
an
inspection
for
metal
particles.
1 If
metal
content
is
shown,
keep the
material
for
identification.
Additional
investigation
will
be
required
to
determine
the
source
of
the
metal
and
possible
need
for
corrective
maintenance.
Refer
to
Lycoming
SSP500
(or
latest
revision)
and
contact
a
Textron
Lycoming
representative.
(b)
Install
the
suction
screen
with
a
new
gasket.
Refer
to
the Lycoming
SSP-1776
Table
of
Limits
or latest
revision,
for
torque
requirements.
(c)
Safety the suction
screen
with
wire. Refer
to
Chapter
20,
Safetying
-
Maintenance
Practices.
(7)
Remove the
external
oil
filter.
(a)
Open
the
filter
can
and
check the
oil
from
the
filter
for signs
of
metal
in
the filter.
(b)
Carefully
remove
and
unfold
the
paper
element. Examine the material
in
the
filter.
1 If
metal
content
is
shown,
keep
the
material
for identification. Additional
investigation
will
be
required
to
determine
the
source
of
the
metal
and
possible
need
for
corrective
maintenance. Refer
to
Lycoming
SSP500
and
contact
a
Textron
Lycoming
representative.
(c)
Install
a
new
external
oil
filter.
(d)
Safety the
oil
filter
with wire.
Refer
to
Chapter
20,
Safetying
-
Maintenance
Practices.
(8)
Fill
the engine
oil
sump through
the
filler
tube.
Use
the
correct
grade
and
quantity
of
oil.
Refer
to
Replenishing
-
Description
and
Operation
for
oil quantity. Refer
to
Figure
301
for
oil
grade
verses
temperature chart.
(9)
Install
the
dipstick
and
make sure
proper seating
on
the
filler
tube.
(10)
Operate
the
engine
until
the
normal
operating
temperature
is
reached.
(11)
Shut
down
the
engine
and do
a
leak
check.
12-14-02
Page 302
©
Cessna
Aircraft
Company
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
B1091
SPECIFIED
AVIATION
GRADE
OIL:
AVERAGE AMBIENT
TEMPERATURE/OIL
GRADE
0OF
10OF
20OF
30OF
40OF 50OF 60OF 70OF 80OF
90°F
-18°C
-120
C
-7
0C -1°C 40
C
10°C
15°C
21°C
270C
32°C
|
SAE
60
SAE
40
or
SAE
50
SAE 40
SAE
30,
SAE
40
or
SAE
20W-40
SAE
30
or
SAE
20
SAE
20W-30
SAE
15W-50 or
SAE
20W-50
'I
MAXIMUM
OIL
TEMPERATURE
245°F
(118°C)
245°F
(118°C)
245°F (118°C)
245°F
(118°C)
210°F
(99°C)
245°F
(118°C)
0598T1001
Temperature
Versus
Oil
Viscosity
Figure
301
(Sheet
1)
©
Cessna
Aircraft Company
12-14-02
Page
303
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INDUCTION AIR
FILTER
-
SERVICING
1.
General
A.
The
induction
airfilter
keeps
dust
and dirt
from
entering
the
induction
system. The value
of
maintaining
the
air
filter
in
a
good
clean
condition
can
never
be
over
stressed.
More
engine
wear
is
caused
through
the
use
of
a
dirty
or
damaged air
filter
than
is
generally
believed.
The
frequency
with
which
the
filter
should
be
removed,
inspected,
and
cleaned
will be
determined
primarily
by
airplane operating
conditions.
Under
extremely
dusty
conditions,
daily
servicing
of
the
filter
may
be
required.
2.
Air
Filter
Servicing
A.
The
CA3717
Induction
Air
Filter
should
be
serviced
at
50
hours,
is
life
limited and must
be
replaced
at
100
hours.
The P198290 Induction
Air
Filter
should
be
serviced
at
50
hours,
is
life
limited
and must
be
replaced
at
500
hours.
(Refer
to
Chapter
5,
Inspection
Time
Limits.)
B.
Servicing Procedures.
(1)
To
service
the
CA3717 Air filter:
(a)
Remove
filter
from
airplane.
If
damaged
or
split,
replace
filter.
If
filter
is
in
serviceable
condition,
proceed
with
following steps.
(b)
Clean
filter
by
blowing with
compressed
air
from direction opposite
of
normal
air
flow.
(c)
Ensure
air
box
is
clean
and
free
of
debris
before
installing
filter.
(d)
Install
filter
at
entrance
to
air
box.
(2)
To
service
the
P198290
Air
filter:
(a)
Remove
the
filter
from the
airplane.
NOTE: Use
care
to
prevent damage
to filter element
when
cleaning filter
with
compressed air.
(b)
Clean
filter
by
blowing
with
compressed
air
(not
over
100
psi)
from
direction
oppposite
of
normal
air
flow.
Arrows
on
filter
case
indicate
direction
of
normal
air
flow.
(c)
Check
bonding
of
the
paper
pleats
to
the
face
screen. The bonding holds the
paper
pleats
in
place
and
if
broken,
the
pleats
are
free
to
shift
which
can
impair
filtration.
A
face
screen
that
is
loose or
gapping away
from
the
paper
pleats
is
indicative
of
broken
bonding
and
is
cause
to
replace
the
filter
element.
CAUTION:
Do
not
use
solvent
or
cleaning
fluids
to
wash
filter.
Use
only
a
water
and
household
detergent
solution
when
washing
the
filter.
(d)
After cleaning
as
outlined
in
step
"b",
the
filter
may be
washed,
if
necessary,
in a
solution
of warm
water
and
a
mild
household
detergent.
A
cold water
solution
may
be
used.
NOTE:
The
filter
assembly
may be
cleaned with
compressed
air
a
maximum
of
30
times
or
it
may
be
washed
a
maximum
of
20
times.
A
new
filter
must
be
installed
after
using
500
hours of
engine
operating
time
or
one
year,
whichever
should
occur
first.
However,
a
new
filter
must
be
installed
anytime
the
existing
filter
is
damaged.
A
damaged
filter
may have
sharp
or
broken
edges
in
the
filtering
panels
which
would
allow
unfiltered
air
to
enter
the
induction
system. Any
filter
that
appears doubtful,
shall
have
a
new
filter
installed
in
its
place.
(e)
After washing,
rinse
filter
with
clear water
until
rinse
water
draining
from
the
filter
is
clear.
Allow
water
to drain
from
filter
and
dry
with
compressed
air (not
over
100 psi).
NOTE:
The
filtering
panels
of
the
filter
may
become distorted
when
wet,
but
they
will
return
to
their
original
shape
when
dry.
(f)
Be
sure
airbox
is
clean,
and
inspect
filter.
If
filter
is
damaged,
a new
filter
must
be
installed.
12-15-00
Page
301
©
Cessna Aircraft
Company
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
(g)
Install
filter
at
entrance
to
airbox with
gasket
on
aft face
of
filter
frame
and
with
flow
arrows
on
filter
frame
pointed
in
the
correct
(normal
air
flow)
direction.
12-15-00
Page
302
©
Cessna
Aircraft
Company
April
1/2002
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
VACUUM
SYSTEM
FILTERS
-
SERVICING
1.
General
A.
The
vacuum system
contains
two
filters
which
require
occasional
servicing.
The
vacuum
system
central
air
filter
is
located
behind
the instrument
panel,
and
the
vacuum
system relief
valve
filter
is
located
in
the engine compartment.
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
until
inspection/replacement.
2.
Central
Air
Filter
Servicing
A.
The
central
air
filter
should
be
serviced
using
time
intervals
set
forth
in
Chapter
5,
Inspection
Time
Limits.
B.
Servicing Procedures
(Refer
to
Figure
301).
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.
(1)
(2)
(3)
(4)
Locate
air
filter
forward
of
instrument panel.
Remove
bolt
and
washer
securing
air
filter
to
cover.
Check
for
damage,
deterioration
and
contamination.
Clean
(or replace)
as
required.
Install
air
filter
in
cover
and
secure
using
bolt
and
washer.
3.
Vacuum
System
Relief
Valve
Filter
A.
The
relief
valve
filter
should
be
serviced
using
time
intervals
set
forth
in
Chapter
5,
Limits.
©
Cessna
Aircraft
Company
Inspection Time
12-16-00
Page
301
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
SUCTION
RELIEF
COVER
AIR
FILTER
BRACKET
NASHER
DETAIL
A
A07183001
07nTfins:
Vacuum
System
Air Filter
-
Servicing
Figure
301
(Sheet
1)
© Cessna
Aircraft
Company
12-16-00
Page
302
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
BATTERY
-
SERVICING
1.
General
A.
This
procedure
provides instructions
for
adding water to
the
battery.
For
testing,
charging
and
maintenance
on
the
battery,
refer to
Chapter
24, Battery
-
Maintenance
Practices.
2.
Battery
Servicing
A.
The
battery
should
be
serviced
according
to
time
limits
set
forth
in
Chapter
5,
Inspection
Time
Limits.
B.
Battery
servicing
involves
adding
distilled
water
to
maintain
the
electrolyte
even with
the
horizontal
baffle plate
at
the bottom
of the
filler
holes,
checking
the
battery cable
connections,
and
neutralizing
and
cleaning
off
any spilled electrolyte or
corrosion.
Use
bicarbonate
of
soda
(baking soda)
and
water
to
neutralize
electrolyte or
corrosion.
Follow
with
a
thorough
flushing
with
a
wire
brush,
then coat
with petroleum
jelly
before
connecting.
The
battery
box
should also
be
checked
and
cleaned
if
any
corrosion
is
noted.
Distilled
water,
not
acid
or
"rejuvenators" should
be
used
to
maintain
electrolyte
level.
Inspect
the
battery
in
accordance
with
time
limits
spelled out
in
Chapter
5,
Inspection
Time
Limits.
12-17-00
Page
301
©
Cessna
Aircraft Company
April 1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
TIRES
-
SERVICING
1.
General
A.
Servicing
the tire by maintaining
correct
inflation
pressure
is
the
most
important
job
in
any
tire
preventative
maintenance
program.
Improper inflation pressure
causes
uneven
tread wear.
(1)
Under
inflation,
indicated
by
excessive
wear
in
the
shoulder
area,
is
particularly
damaging.
It
increases
the
chance
of
bruising
sidewalls
and
shoulders
against
rim
flanges.
In
addition,
it
shortens
tire
life
by
permitting
excessive
heat
buildup.
(2)
Over
inflation
is
indicated
by
excessive
wear
in
the
center
of
the
tire.
This
condition
reduces
traction,
increases
tire
growth
and
makes
treads
more
susceptible
to
cutting.
2.
Safety
Precautions
and
Notes
A.
Safety
Precautions.
(1)
Tire
should
be
allowed
to
cool before
attempting
to
service.
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.
(2)
Personnel
should stand
at
a
90-degree angle
to
the
axle
along
the
centerline
of the tire
during
servicing.
CAUTION:
Applying
a
tire
sealant
to
the
tire
may
cause
wheel
corrosion.
(3)
The
use
of
tire
sealant
is
not
recommended.
B.
Notes.
(1)
A
tube type
tire that
has
been
freshly
mounted
and
installed should
be
closely
monitored during
the first week
of
operation,
ideally
before
every takeoff.
Air
trapped
between
the
tire
and
the
tube
at
the
time
of
mounting could seep
out
under
the
bead,
through sidewall vents
or around
the
valve
stem, resulting
in
an
under
inflated assembly.
(2)
The
initial
stretch
or
growth
of
a
tire
results
in a
pressure
drop
after
mounting.
Consequently, tires
should
not
be
placed
in
service
until
they
have
been
inflated
a
minimum
of
12
hours,
pressures
rechecked,
and tires reinflated
if
necessary.
(3)
Inaccurate tire
pressure
gages
are
a
major
cause
of
improper inflation
pressures.
Ensure
gages
used are
accurate.
3.
Tire
Servicing
A.
Check
tire
pressure
regularly.
(1)
Tire
pressure should
be
checked
when
tire
is
cold
(at
least
2
or
3
hours
after
flight)
on
a
regular
basis.
Tire
pressure should
be
checked
prior
to
each
flight
when practical.
(2)
When
checking
tire
pressure,
examine
tires for
wear,
cuts,
and bruises.
Remove
oil,
grease
and
mud
from
tires
with
soap
and
water.
B.
Use
recommended
tire
pressure. Consult
the
table
below.
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.
Main Gear
Tire
Type: Pressure
6.00
x 6,
6-ply
rated
tire
42
PSI
(2895
pa)
Nose
Gear
Tire
Type:
5.00
x 5,
6-ply
rated
tire
49
PSI(3378
pa)
12-18-00
Page 301
©
Cessna
Aircraft Company
April 1/2002
CESSNA AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
4.
Cold Weather
Servicing
A.
Cold
Weather
Servicing.
(1)
Check
tires
for
excessive
deflation.
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.
(2) If it
is
necessary
to
pressure
check
tires
in
cold
climates,
always
apply
heat
to
air
valves
and
surrounding
areas
before
unseating valves.
(3)
Continue
application
of heat
during
reinflation
to
ensure air
valve
seal
flexibility
when
valve
closes.
(4)
Do
not
allow
tires
to
stand
in
snow soaked
with
fuel,
or
on
fuel covered
ramp
areas.
(5) If
tires become
frozen
to parking
ramp,
use
hot
air
or
water
to
melt
ice
bond before
attempting
to
move
airplane.
12-18-00
Page 302
©
Cessna Aircraft
Company
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
SCHEDULED
SERVICING
-
DESCRIPTION AND OPERATION
1.
General
A.
This
section
provides instructions
necessary
to
carry
out
scheduled
servicing
as
well
as
internal/external
cleaning.
It
also
includes
instructions
for
lubricating
specific
points identified
in
periodic
inspection and/or preventive
maintenance
programs.
This section does
not
include
lubrication procedures
required
for
the
accomplishment
of
maintenance
practices.
2.
Description
A.
This
section
is
subdivided
to
provide maintenance
personnel with charts,
text
and
illustrations
to
prevent
confusion.
Also
included
in
this
section
is
a
table
containing
a
list
of
lubricants.
(1)
The
subdivisions
are
separated
according
to
airplane
systems. This
aids
maintenance
personnel
in
locating
service
information.
12-20-0
©
Cessna
Aircraft
Company
10
Page
1
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
LUBRICANTS
-
DESCRIPTION
AND OPERATION
1.
General
A.
This
section
is
designed
to
assist
the
operator
in
selecting recommended
lubricants.
For
best
results
and
continued trouble
free service,
use
clean
and
approved lubricants.
B.
For
a
list
of
recommended lubricants,
refer
to
Recommended Lubricants
Table.
2.
Lubrication
Service
Notes
A.
Lubricant
Application.
(1)
Cleanliness
is
essential
to
good
lubrication.
Lubricants
and
dispensing equipment
must
be
kept
clean.
Use
only
one
lubricant
in
a
grease
gun
or oil can.
(2)
Store
lubricants
in a
protected
area.
Containers
should
be
closed
at
all
times
when
not
in
use.
(3)
Wipe
grease
fittings
and
areas
to
be
lubricated
with
clean,
dry
cloths
before
lubricating.
(4)
When
lubricating
bearings
which
are
vented,
force grease
into
fitting
until
old
grease
is
extruded.
(5)
After any
lubrication,
clean
excess lubricant
from all
but
actual working
parts.
(6)
All
sealed
or
prepacked antifriction
bearings
are
lubricated
with
grease
by
the
manufacturer
and
require
no
further
lubrication.
(7)
Friction
bearings
of the
porous, sintered-
type
are
prelubricated.
An
occasional squirt
can
oiling
of
such
bearings
with
general
purpose oil
(MIL-L-7870)
extends
its
service
life.
(8)
Lubricate
unsealed pulley bearings,
rod
ends,
pivot
end
hinge
points
and
any other friction
point
obviously
needing lubrication,
with
general
purpose
oil
(MIL-L-
7870).
(9)
Paraffin
wax
rubbed
on
seat
rails
will
ease
sliding
the
seats
fore
and aft.
(10)
Do
not
lubricate roller chains
or
cables
except
under
sea coast conditions.
Wipe with
a
clean,
dry
cloth.
(11)
All
piano
hinges
may
be
lubricated
using
(PG)
powered
graphite
(SS-G-659)
when
assembly
is
installed.
(12)
Lubricate
door
latching
mechanism
with
MIL-G-81322 general
purpose
grease,
applied sparingly
to
friction points,
if
binding
occurs.
No
lubrication
is
recommended
on
the
rotary
clutch.
3.
Definition
of
"As
Needed"
A. In
the following
sections,
time
requirements for lubrication
are
presented
in
one of
two
formats.
When
specific
time
intervals
for
lubrication
exist, those
intervals
are
defined
in
Chapter
5,
Inspection
Time
Limits. When
no time
limit has
been
established,
lubrication
is
on an
"as
needed"
basis.
This
leaves
much
of
the
decision
making
process
in
the
hands of
the airframe
and
powerplant
mechanic,
who
has
been
trained
to
make
these types
of
decisions.
B. In
an
effort to
standardize
the
decision
making
process,
the
following
guidelines
may
be
considered
to
determine
if
a
component
needs
lubrication.
Any one
of
the
following conditions
would
indicate
a
need
for lubrication,
and
may
additionally
indicate
the
need
for inspection:
(1) A
visual
inspection
which
indicates
dirt
or
wear
residue
near
the movement
contact
area.
(2)
An
audible inspection
which
indicates
squeaks,
grinding
or
other
abnormal
sounds.
(3)
A
tactile
(touch
and
feel)
inspection
which
indicates
jerky
or restricted
movement
throughout
portions
of the
travel
range.
4.
Recommended
Lubricants
Table
NOTE:
Equivalent
substitutes
may
be
used
for
the following
items:
12-21-00
Page
1
©
Cessna
Aircraft
Company
Jan
2/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
Table
1.
Recommended
Lubricants
PROCURE-
MENT
SPECI-
FICATION
LUBRICANT
DESCRIPTION
MIL-G-81322
Grease,
wide
temperature
range.
Mobil
grease
28
Mobil
Oil
Corp.
150
E.
42nd
Street
New
York,
NY
10017
Royco
22C
Royal
Lubricants
Co.,
Inc.
River
Road
East
Hanover,
NJ
07936
Aeroshell
Shell
Oil
Co.
grease
22
One Shell
Plaza
Houston,
TX 77001
MIL-G-23827
Grease,
aircraft
and
instrument,
gear
and
actuator
screw.
Southwest
Grease
16215
Aeroshell
grease
7
Southwest
Petro- Chem,
Inc.
Division
-
Witco
1400
S.
Harrison
Olathe,
KS
66061
Shell
Oil
Co.
Royco
27A
Royal
Lubricants
Co.,
Inc.
Amoco
Oil
Co.
200
East
Randolph
Dr.
Chicago,
IL
60601
Burmah-Castrol,
Inc.
Bray
Products
Div.
16815
Von
Karman Ave.
Irving,
CA
92714
Burmah-Castrol,
Inc.
Southwest Petro-Chem,lnc.
Brumah-Castrol,
Inc.
Royco
363
Royal
Lubricants
Co.,
Inc.
Petrotect
7870A
Windsor
lube
L-1018
Octoil
70
Penreco
106
South
Main
Street
Butler,
PA
16001
Anderson
Oil
&
Chemical
Co.,
Inc.
Portland,
CT
06480
Octagon
Process, Inc.
596
River
Road
Edgewater,
NJ
07020
12-21-01
©
Cessna Aircraft
Company
O
Page
2
Jan
2/2006
SYMBOL
GR
PRODUCT
PART
NUMBER
SUPPLIER
GH
Supermil
grease
No.
A72832
Braycote
6275
Castrolease
A1
TG-11900
low
temp
grease
EP
Brayco
885
OG
MIL-L-7870
Oil,
general
purpose
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
Table
1.
Recommended Lubricants
(continued)
PROCURE-
MENT
SPECI-
FICATION
VV-P-236
SS-G-659
MIL-G-21164
LUBRICANT
DESCRIPTION
Petrolatum
technical
Powdered
Graphite
High and
Low
Temperature
Grease
PRODUCT
PART
NUMBER
Everlube
211-G Moly
Grease
SUPPLIER
Available
Commercially
Available
Commercially
E/M
Corporation
Box
2200
Highway
52
N.W.
West Lafayette,
IN
47906
Number
10
weight,
nondetergent
oil
Light
Oil
Grease,
general
purpose
Royco
64
Royal
Lubricants
Co.,
Inc.
Available
Commercially
U000992
©
Cessna Aircraft
Company
Available
Commercially
Cessna Aircraft
Co.
1
Cessna
Blvd.
Wichita,
Ks
67277-7704
12-21-00
Page
3
Jan 2/2006
SYMBOL
PL
PG
GL
GP
NONE
VV-L-800
OL
I
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
BATTERY
TERMINALS
-
SERVICING
1.
General
A.
It
is
recommended
the
airplane
be
secured
in
an
area
free
of
contamination
from
sand,
dust
or
other
environmental conditions
that
may
contribute
to
improper lubrication
practices.
2.
Battery
Terminal
Lubrication
A.
Battery
terminals
should
be
lubricated
when
cables
are
installed
to
terminals.
B.
Refer
to
Figure
301
for
lubrication
requirements
of
the battery
terminals.
12-21-01
Page
301
©
Cessna Aircraft Company
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
LANDING
GEAR
AND PARKING
BRAKE
-
SERVICING
1.
General
A.
It
is
recommended
that
the
airplane
be
secured
in
an
area
free
of
contamination
from sand,
dust
or
other
environmental
conditions
that
may
contribute
to
improper lubrication
practices.
2.
Wheel
Bearing
Lubrication
A.
Wheel bearings should
be
lubricated
using
time
intervals
set
forth
in
Chapter
5,
Inspection
Time
Limits.
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.
B.
Refer
to
Figure
301
for lubrication requirements
of
the
wheel
bearings.
3.
Nose
Gear
Torque
Link Lubrication
A.
Nose
gear torque
links
should
be
lubricated using
time
intervals
set forth
in
Chapter
5,
Inspection
Time
Limits.
B.
Refer
to
Figure
301
for lubrication requirements
of the
nose gear
torque
links.
4.
Shimmy
Dampener
Pivots
Lubrication
A.
Shimmy
dampener
pivots
should
be
lubricated
on
an
"as
needed"
basis
and
when
assembled
or
installed.
B.
Refer
to
Figure
301
for
lubrication requirements
of
the
shimmy
dampener
pivots.
5.
Steering
System
Needle
Bearing
Lubrication
A.
Steering
system
needle
bearings
should
be
lubricated
on an
"as
needed"
basis and
when
assembled
or
installed.
B.
Refer
to
Figure
301
for
lubrication requirements
of
the steering system
needle
bearings.
6.
Nose Gear
Steering
Pushrods
Lubrication
A.
Nose
gear steering pushrods should
be
lubricated
using
time
intervals
set
forth
in
Chapter
5,
Inspection
Time
Limits.
B.
Refer
to
Figure
301
for
lubrication requirements
of the
nose gear
steering
pushrods.
7.
Parking
Brake Handle
Shaft
Lubrication
A.
The parking brake handle
shaft should
be
lubricated
on
an
"as
needed"
basis and
when
assembled
or
installed.
B.
Refer
to
Figure
302
for lubrication requirements
of the
parking brake handle
shaft.
12-21-02
Page
301
©
Cessna
Aircraft
Company
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
B1094
3
5
DETAIL
A
NOSE
GEAR
1
MAIN
GEAR
ITEM
DESCRIPTION
LUBE
TYPE
APPLICATION
1
WHEEL BEARINGS
2
TORQUE
LINKS
3
SHIMMY
DAMPER
PIVOTS
4
STEERING
SYSTEM
NEEDLE
BEARINGS
5
NOSE
GEAR STEERING
PUSHRODS
GR
GR
GR
GR
OG
HAND
GUN
OIL
CAN
HAND
OIL
CAN
GR
-
GREASE,
GENERAL
PURPOSE
-
(MIL-G-81322)
OG
-
OIL,
GENERAL
PURPOSE
-
(MIL-L-7870)
Landing Gear
Lubrication
Figure
301
(Sheet
1)
©
Cessna Aircraft
Company
12-21-02
Page
302
April
1/2002
ITEM
NUMBER
0742T1001
A0742T1002
0741T1001
r
L
l
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
FLIGHT
CONTROLS
-
SERVICING
1.
General
A. It
is
recommended
that
the
airplane
be
secured
in
an
area
free
of
contamination
from
sand,
dust
or
other
environmental
conditions
that
may
contribute
to
improper
lubrication
practices.
2.
Aileron
System
Lubrication
A.
Bearings
in
the
control
column
should
be
lubricated
on
an
"as
needed"
basis
and
when
assembled
or
installed.
B.
Piano
hinges
on
the
ailerons should
be
lubricated
on
an
"as
needed"
basis
and
when
assembled
or
installed.
C.
Needle
bearings
on
the
aileron
bellcrank should
be
lubricated
on
an
"as
needed"
basis
and when
assembled
or
installed.
D.
Rod
end
bearings
on
the aileron
bellcrank
should
be
lubricated
using
time
intervals
set
forth
in
Chapter
5,
Inspection
Time
Limits.
E.
Refer
to
Figure
301
for
lubrication
requirements
of
the
aileron system.
3.
Flap
System
Lubrication
A.
Flap
motor
screw
jack
threads should
be
lubricated
using time
intervals set
forth
in
Chapter
5,
Inspection
Time Limits.
To
lubricate
the
jack
screw,
operate flaps
to
full
down
position, clean
screw
threads
with
solvent
rag,
and
dry
with
compressed
air.
NOTE:
It
is not
necessary
to
remove
actuator
from
airplane
to
clean
or
lubricate
threads.
B.
Needle
bearings
should
be
lubricated
on
an
"as
needed"
basis
and
when
assembled
or
installed.
C.
Refer
to
Figure
302
for
lubrication
requirements
of
the
flap
system.
4.
Elevator
System
Lubrication
A.
Bearings
in
the
trim
wheel
controls
should
be
lubricated
on
an
"as
needed"
basis
and
when
assembled
or
installed.
B.
The
elevator
down
spring
link
rub
strip should
be
lubricated
using
time intervals
set forth
in
Chapter
5,
Inspection
Time
Limits.
C.
Trim
tab
piano
hinges
should
be
lubricated
on
an
"as
needed"
basis
and
when
assembled
or
installed.
D.
The
trim
tab
actuator
should
be
lubricated
using time
intervals
set
forth
in
Chapter
5,
Inspection
Time
Limits.
E.
Refer
to
Figure
303
for
lubrication
requirements
of
the
elevator
system.
5.
Rudder
System
Lubrication
A.
The
rudder bar bearing
block halves
should
be
lubricated
on an
"as
needed"
basis
and
when
assembled
or
installed.
B.
The
oilite
bearings
in
the
rudder bar ends and
linkage point pivots should
be
lubricated
using time
intervals
set
forth
in
Chapter
5,
Inspection
Time Limits.
C.
Refer
to
Figure
304
for
lubrication
requirements
of
the
rudder system.
12-21-03
Page
301
©
Cessna
Aircraft
Company
April
1/2002
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
B1096
ITEM
DESCRIPTION
NEEDLE
BEARINGS
NEEDLE
BEARING
ROLLERS
NEEDLE BEARING
THRUST
BEARING
LUBE
TYPE
GR
GR
GR
GR
APPLICATION
HAND
HAND
HAND
HAND
GR
-
GREASE, GENERAL PURPOSE
-
(MIL-G-81322)
0724T1001
Aileron
System
Lubrication
Figure
301
(Sheet
1)
12-21-03
©
Cessna
Aircraft
Company
ITEM
NUMBER
1
2
3
4
Page
302
April
1/2002
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
B1097
2
AILERON
BELLCRANK
1
AILERON
HINGES
EM ITEM
MBER
DESCRIPTION
1
AILERON PIANO
HINGES
2
BELLCRANK
NEEDLE
BEARINGS
3
ROD
END
BEARINGS
LUBE
TYPE
PG
GR
OG
APPLICATION
SYRINGE
HAND
OIL
CAN
PG
-
POWDERED GRAPHITE
(SS-G-659)
GR
-
GREASE, GENERAL PURPOSE
-
(MIL-G-81322)
OG
-
OIL,
GENERAL PURPOSE
-
(MIL-L-7870)
0724T1002
0724T1003
Aileron
System
Lubrication
Figure
301
(Sheet
2)
©
Cessna
Aircraft Company
12-21-03
Page 303
April 1/2002
IT
NUW
3
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
DETAIL
A
ELECTRIC
FLAP DRIVE
MECHANISM
'EM
ITEM
ABER
DESCRIPTION
1
FLAP
MOTOR
SCREW
JACK
THREADS
2
NEEDLE
BEARINGS
LUBE
TYPE
GP
GR
APPLICATION
OIL
CAN
HAND
GP
-
OIL
NO.
1
-WEIGHT,
NON-DETERGENT
GR
-
GREASE, GENERAL
PURPOSE
-
(MIL-G-81322)
0718T1005
Flap System
Lubrication
Figure 302 (Sheet
1)
12-21-03
©
Cessna
Aircraft
Company
IT
NUN
Page
304
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
RB10n
TRIM
WHEEL
5
4
II
I
I
.I
ELEVATOR
RUB
STRIP
ACTUATOR
AND
TRIM TAB
ITEM
DESCRIPTION
NEEDLE
BEARINGS
OILITE BEARINGS
TRIM
TAB
PIANO
HINGES
TRIM
TAB ACTUATOR
ELEVATOR
DOWN
SPRING
LINK
RUB
STRIP
LUBE
TYPE
GR
OG
PG
GL
GR
APPLICATION
HAND
OIL
CAN
SYRINGE
HAND
HAND
GR
-
GREASE, GENERAL PURPOSE
-
(MIL-G-81322)
OG
-
OIL,
GENERAL
PURPOSE
-
(MIL-L-7870)
PG
-
POWDERED
GRAPHITE (SS-G-659)
GL
-
GREASE,
HIGH
AND
LOW TEMPERATURE (MIL-G-21164)
Elevator
System
Lubrication
Figure
303
(Sheet
1)
©
Cessna Aircraft
Company
12-21-03
Page
305
April 1/2002
3
ITEM
NUMBER
1
2
3
4
5
0718T4001
0734T1001
0734T1002
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
B1100
ITEM
ITEM
NUMBER DESCRIPTION
~1
OILITE
BEARING
(RUDDER
BAR
ENDS)
ALL
LINKAGE
PIVOT POINTS
BEARING
BLOCK
HALVES
LUBE
TYPE
OG
OG
OG
APPLICATION
OIL
CAN
OIL
CAN
OIL
CAN
OG
-
OIL, GENERAL PURPOSE
-
(MIL-L-7870)
0562T2002
Rudder
Pedals
Lubrication
Figure 304
(Sheet
1)
©
Cessna
Aircraft Company
12-21-03
Page
306
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
ENGINE
CONTROL CABLES
-
SERVICING
1.
General
A. It
is
recommended
that
the
airplane
be
secured
in
an
area
free
of
contamination
from
sand, dust
or
other environmental
conditions
that
may
contribute
to
improper lubrication
practices.
2.
Engine
Control
Cables
Lubrication
A.
All
housed,
pull-type,
push-pull
or
vernier controls
should
have
each
outer
housing
lightly lubricated
internally
with
VV-L-800
General Purpose
Lube
Oil.
12-21-04
Page
301
©
Cessna
Aircraft
Company
April 1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
HEATING
AND VENTILATION
CONTROL CABLES
-
SERVICING
1.
General
A. It is
recommended that the
airplane
be
secured
in
an
area
free
of
contamination
from
sand, dust
or
other
environmental
conditions
that
may
contribute
to
improper lubrication practices.
2.
Heating
And
Ventilation Control
Cables
Lubrication
A.
All
housed,
pull-type,
push-pull
or
vernier
controls
should
have
each
outer
housing
lightly lubricated
internally with VV-L-800 General Purpose
Lube
Oil.
12-21-05
Page
301
©
Cessna Aircraft
Company
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
AIRPLANE
EXTERIOR
-
CLEANING/PAINTING
1.
General
A.
The
airplane
must
be
cleaned
frequently
to
keep
the
external
surface
in
good
condition
and
to
prevent
corrosion. The
painted
area
of
the
airplane
must
be
polished
at
intervals
to remove
chalking
paint
and
to
make sure
that
it
has
a
smooth,
glossy
finish.
B.
Use
water
and
detergent
when you
clean
the
external
surface
of
the
airplane.
2.
Precautions
A.
Obey
all
manufacturer instructions, warnings,
and
cautions
about
all
cleaning
agents
and
solvent
compounds.
B.
Do
not
use
silicone-based
wax
to
polish
the
external
surface
of
the
airplane.
Silicone-based
wax,
especially
if
buffed to
a
high
shine,
can
help
to cause
the
buildup
of
P-static.
C.
Do
not
park or keep
the
airplane
in
an
area where
it
can
come
into
direct
contact
with
fluid
or
vapors
from
methanol,
denatured alcohol,
gasoline,
benzene,
xylene, methyl-propyl ketone, acetone,
carbon
tetrachloride,
lacquer thinners,
commercial
or
household
window
cleaners,
paint
strippers, or
other
types
of
solvents.
D.
Do
not
leave
sun
visors
against
the
windshield
when not
in
use.
The
reflected
heat
from
these
items
increases
the
temperature
on
the
windshield.
If
solar
screens
are
installed
on
the
inside
of
the
airplane,
make sure
that
they
are
the
silver,
reflective type.
E.
Do
not use
a
power
drill
motor or
other
powered device
to
clean,
polish,
or
apply
wax
to
surfaces.
3.
Preventive
Maintenance
A.
Keep
all
surfaces
of
the windshield
and
the
windows
clean.
B. If
necessary,
apply
wax
to
acrylic surfaces.
C.
Put
a
cover
over
all
surfaces
while
the
airplane
is
painted, the
engine
is
cleaned,
or
other procedure
is
done
that uses any
type
of
solvent or
chemical.
Table
701
gives
approved
protective
coatings
to
prevent
solvent
damage.
Table 701.
Approved
Protective
Coatings
NUMBER
MIL-C-6799,
Type
1,
Class
II
Masking
Paper
Poly-Spotstick
WPL-3
SXN
MANUFACTURER
Commercially
Available
Champion
Intl.
Corp.
Forest
Product
Division
7785 Bay
Meadows
Way
Jacksonville,
FL
32256
Champion
Intl.
Corp.
Mask Off
Company
345
Marie
Avenue
Monrovia,
CA
USE
Gives
surfaces
protection
from
solvents.
Gives
surfaces
protection
from
solvents.
Gives
surfaces
protection
from
solvents.
Gives
surfaces
protection
from
solvents.
12-22-00
©
Cessna Aircraft
Company
NAME
Spray
Protex
40
Page
701
Mar
1/2005
CESSNA
AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
4.
Windshield
and
Window
Cleaners
CAUTION:
Do
not use
methanol,
gasoline,
denatured
alcohol,
benzene,
xylene,
acetone, carbon
tetrachloride,
fire
extinguisher
fluid,
deicer fluid,
lacquer
thinner,
or
commercial
or
household
glass
window
cleaner
when
you
clean
the
windshield
and
windows
of
the airplane.
These solvents
will
cause
damage
to
the
plastic.
Table
702.
Windshield
and
Window
Cleaners/Polishers
NAME
Mild
soap
or
detergent
(household
type
without
abrasives)
Aliphatic
Naphtha
Type
II
NUMBER
Federal
Specification
TT-N-95
Turtle Wax (paste)
MANUFACTURER
Commercially Available
Commercially
Available
Commercially Available
USE
Cleans
windshields
and
windows.
Removes
deposits which
cannot
be
removed
with
mild
soap solution
on
acrylic
windshields
and
windows.
Gives
protection
to
acrylic
windshields
and
windows.
Permatex
Plastic
Cleaner
No.
403D
Federal
Specification
P-P-560
Soft
cloth
(cotton
flannel
or
cotton
terry
cloth)
Permatex
Company,
Inc.
Kansas
City,
KS
66115
Commercially Available
Gives
protection
to
acrylic
windshields
and
windows.
Applies
and
removes
wax
and
cleaning
agents.
NOTE:
Equivalent
substitutes
can
be
used
for
the items
given
in
Table
702.
5.
Cleaning
Windshield
and
Windows
CAUTION:
CAUTION:
Obey
all
the
correct procedures
when
you
touch
and
clean
the
windshield
and
windows
of
the airplane.
If
you do not
obey
the
correct
procedures, you
can
easily cause
damage to
the
windshield
and
windows.
Do
not
use
methanol,
gasoline,
denatured
alcohol,
benzene,
xylene,
acetone, carbon
tetrachloride,
fire
extinguisher
fluid,
deicer
fluid, lacquer
thinner,
or
commercial
or
household glass
window
cleaner
when
you
clean
the
windshield
and
windows
of
the airplane.
These
solvents
will
cause
damage
to
the
plastic.
A.
Refer
to
Table
702
for
cleaning
materials.
B.
Windshield
Cleaning
Procedures.
(1)
Put
the
airplane
inside
a
hanger
or
in
a
shaded
area
and
let
the
surface
of the
airplane
cool.
(2)
Let
clean
water
flow
over
the
surface
of
the
windshield.
Use
bare
hands
with
no
jewelry
to
feel
and
rub
away
any dirt
or
abrasive
materials.
12-22-00
Page
702
©
Cessna
Aircraft Company
Mar
1/2005
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
(3)
Use
a
mild
soap
or
detergent
(such
as
dishwashing
liquid)
in
water
to
clean
the
surface
of the
windshield.
Use
bare
hands
to rub
the
solution over
the surface.
A
clean
cloth
can
be
used
to
apply
the
soap solution
to
the
surface,
but
you
must
be
very careful
to
prevent
scratches.
(4)
On
acrylic
windshields
and
windows
only,
if
the
windshield
and
windows
are still
dirty
after they
are
cleaned
with
a
mild
detergent,
use
Type
II
aliphatic
naphtha
as
a
cleaning
agent. Apply
the
agent
only
with
a
soft, clean
cloth. Make
sure
that the
cloth
is
frequently folded
to
avoid
scratching
the
windshield
with any
abrasive particles.
(5)
Flush
the
surface
with clean
water
and
dry
with
a
clean cloth.
6.
Waxing
and
Polishing Windshield
and
Windows
CAUTION:
Do
not use
rain
repellent
on
acrylic
surfaces
because
it
can
cause
damage.
NOTE:
Windshields
and
windows
must
be
cleaned
before
you apply
wax.
When
you
apply
and
remove
wax
and
cleaning
agents,
use
a
soft,
clean cloth.
A.
Refer
to
Table
702
for polishing
materials.
B.
Hand
polishing
wax
(or
other
materials that
meet
Federal
Specification
P-P-560)
must
be
applied
to
acrylic surfaces.
The
wax
has
an
index of
refraction
almost
the same
as
transparent
acrylic
and
masks
any
scratches
on
the
windshield
surface.
7.
Aluminum
Surfaces
A.
The aluminum
surfaces
of the
airplane
can
be
cleaned
with
water
to remove
dirt
and
can
be
cleaned
with
non-alkaline
grease
solvents
to
remove oil
and/or grease. Household detergent
soap powders
are
good
cleaners,
but
must
be
used
carefully,
since
some
of
them are
strongly
alkaline.
Many
good
aluminum
cleaners, polishes,
and
waxes
are
available
from
commercial
suppliers
of
airplane products.
8.
Painted
External Surfaces
A.
The
painted
surfaces
of
the
airplane
can
be
cleaned
with
water
and
mild
soap,
followed
by
a
rinse with
water
and
dried with
cloths
or
a
chamois.
Abrasive
soaps
or
detergents
which
can
cause corrosion
or
scratches
must
not
be
used. Remove
oil
and
grease
with
a
cloth
that
is
moist
with
Stoddard
solvent.
NOTE:
For
more
information
on
the
external
paint
finish,
refer
to
Chapter
20,
Exterior
Finish
-
Cleaning/Painting.
B.
To
seal
any
small
surface chips
or
scratches
and
give protection
from
corrosion,
you
must
regularly
apply
wax
to
the airplane
with
a
good
automotive
wax,
in
accordance
with
the
manufacturer's
instructions.
If
the
airplane
is
operated
in a
seacoast
area
or
other
salt
water
environment,
it
must
be
cleaned
and
wax
must
be
applied
more
frequently
to make
sure
that
the
surface
has
sufficient
protection. Special
care must
be
taken
to
seal
around
rivet
heads
and
skin
laps,
which
are
the
areas
more
susceptible
to
corrosion.
A
thicker
layer
of
wax
on
the
leading
edges
of
the
wings
and
tail
and
on
the
cowl
nose
cap
and
propeller
spinner
will help
decrease
the
abrasion found
in
these
areas.
A
new
layer
of
wax will
be
necessary
after
you clean
the
airplane
with soap
solutions
or
after
chemical
deicing operations.
9.
Cleaning
the
Engine
and
Engine
Compartment
A.
Notes and
Precautions.
(1)
Clean
the
engine
and engine
accessories
during
each
100-hour inspection
to
remove
oil,
grease,
salt
corrosion,
or
other
contamination
that
can
conceal
component problems.
Also,
clean
regularly
to
help
prevent
engine
problems.
12-22-00
Page 703
©
Cessna
Aircraft Company
Mar 1/2005
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
WARNING:
WARNING:
Put
on
protective
devices
(rubber
gloves, aprons,
face
shields,
etc.)
and
work only
in
a
well-ventilated
area
when
you
use
solvents
and
cleaning
agents.
These
materials
and
their
fumes
are
poisonous.
Do
not
smoke
or
have
an
open
flame
within
100
feet
of
the
work
area
because
it
can
cause
a
fire.
Many
solvents
and
cleaning
agents
are
very
flammable.
Make
sure
that
sufficient
fire
and
safety equipment
are
available.
NOTE:
If
you use
compressed air
to
apply
solvent
or
to
dry
components,
adjust
the
pressure
to
the
lowest
possible
setting.
(2)
Use
a
stiff-bristle
brush
as
an
alternative
to
a
steel
brush
if
cleaning
agents
do
not remove
unwanted
grease
and
contamination
while
flushing
the area.
B.
Cleaning Procedures.
(1)
Remove
the
engine
cowl.
(2)
Carefully
put
a
cover
on
the
coupling
area
between the
vacuum
pump
and the
engine
drive
shaft
so
no
cleaning
agent
or
solvent
can
touch
the
coupling
or
seal.
(3)
Put
a
cover
on
the open
end
of
the
vacuum
discharge tube.
(4)
If
the
engine
has
salt
or
corrosive
chemical
contamination,
first
flush
the
engine compartment
with
clean
water.
WARNING:
WARNING:
CAUTION:
Do
not
use
gasoline
or other
flammable materials
to
clean
the
engine
compartment.
If
used,
these materials
can
cause
a
fire.
Do
not
try
to
clean
an
engine
that
is
hot
or
in
operation.
This
can
cause
a
fire,
serious
injury,
or
death.
Always
stop
the
engine
and
let
the
engine
cool
before
cleaning.
Do
not
let
cleaning
agents
or
water
touch
the openings
on
the
starter,
magnetos, alternator,
or
vacuum
pump.
This
can
cause
damage
to
these
engine
components.
(5)
Apply
the
solvent
or
cleaning agent
to the
engine
compartment.
The
solutions
that
follow
(or
their
equivalent)
can
be
used
to
satisfactorily
clean the
engine
compartment:
(a)
Stoddard
Solvent
(Specification
P-D-680,
Type
II).
(b)
Water
alkaline
detergent
cleaner
(MIL-C-25769
mixed
1
part
cleaner,
with
2
to
3
parts
water
and
8
to
12
parts
Stoddard
Solvent).
(c)
Solvent-based emulsion
cleaner
(MIL-C-4361
mixed
1
part
cleaner
with
3
parts Stoddard
Solvent).
(6)
After
you
apply
the
cleaning agent
or
solvent,
flush
the
engine
compartment
with clean
warm
water.
NOTE:
Cleaning
agents
must
not
be
left
on
engine
components
for
an
extended
period
of
time. Failure
to
remove them can
cause damage
to
the
components
and cause
more
corrosion.
For
example,
solvents
and
cleaning
agents
can
easily
cause
damage
to
neoprene seals
and
silicone
fire
sleeves.
(7)
Fully
dry
the engine and engine
accessories
with
compressed
air.
(8)
Remove
the
cover
from
the
coupling
area.
(9)
Remove
the
cover
from the
vacuum discharge
tube.
12-22-00
©
Cessna Aircraft
Company
Page
704
Mar
1/2005
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
(10)
If
necessary, the
engine
cowl
can
be
cleaned
with
the
same cleaning
agents,
then
flushed
with
water
and
dried
with
a
soft,
clean cloth.
After
you
clean
the
engine,
lubricate
all
the
control
arms
and
moving
parts,
as
necessary.
(11)
Install the engine
cowl.
WARNING:
Make
sure
that
the
magneto
switches
are
off,
the
throttle is
closed,
the
mixture
control
is
in
the
idle
cutoff
position,
and
the
airplane
is
stable
before
you
turn
the propeller
by
hand.
Do
not
stay
within
the
arc
of
the
propeller
blades
while you
turn
the
propeller. If
the
engine
accidentally
starts,
the
propeller
blades
can
cause
serious
injury
or
death.
(12)
Before
you
start
the
engine,
turn
the
propeller
by
hand
a
minimum
of
four
full
revolutions.
10.
Propeller
A.
Rub
clean, lightweight
oil
onto
the
propeller
with
a
soft,
clean cloth
to
remove
grass
and
bug
stains.
In
salt water
areas,
the
oil
will
also
help
prevent
corrosion
of
the
propeller.
11.
Tires
and
Wheels
A.
Remove
oil,
grease,
and mud
from
the tires and wheels with
soap
and
water.
12.
Stabilizer Abrasion Boots
A.
Stabilizer
abrasion
boots
must
be
cleaned
and
examined
regularly.
Keep
the
boots
clean
and
free
from
oil,
grease,
and
other solvents
which
can
cause
damage
to
the
rubber.
12-22-00
Page
705
©
Cessna
Aircraft Company
Mar
1/2005
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INTERIOR
-
CLEANING/PAINTING
1.
General
A.
This
section
recommends
different
types
of
cleaning materials
and
cleaning
procedures
for
the interior
of
the
airplane.
WARNING:
Do
these
cleaning operations
in
an
area
with
good
airflow.
Use
the
applicable
safety
precautions
for
each
cleaning
material
that
you
use.
2.
Interior
Cleaning Materials
NOTE:
Equivalent
substitutes
can
be
used
for
the
following
items:
NAME
NUMBER
Protectant
All-Purpose
Cleaner
Aliphatic
Naphtha
Son-Of-A-Gun
Fantastik
TT-N-94
Rug
Shampoo
Perchloroethylene
Cleaning Solvent
Household
Ammonia
MANUFACTURER
Commercially
available
Commercially
available
Commercially
available
Commercially available
Commercially
available
Commercially
available
USE
To
protect
and
shine interior
components
(excluding
fabric
materials).
For
general
purpose
cleaning
of
interior
components.
To
remove
tar,
asphalt,
and
similar
materials
from
interior
components.
To
clean
carpet.
To
spot
clean carpet
and
seats.
To
clean
seat
fabric.
Household Vinegar
Rubbing
Alcohol
Ivory
Liquid
(white
or
colorless)
Detergent
Commercially
available
Commercially available
Commercially
available
Commercially
available
Cheer
To
clean
seat
fabric.
To
clean
seat
fabric.
To
clean
seat
fabric.
To
clean
seat fabric.
3.
Cleaning
Interior
Panels
A.
Clean
interior panels
(headliners, sidewalls,
door
panels,
and
similar
surfaces)
with
mild
detergent
solutions
or
premixed commercial
cleaners.
Remove
stubborn
deposits
with
aliphatic
naphtha.
Make
sure
that
cleaners
are
compatible
with
the
interior
of
the
airplane.
If
in
doubt,
apply
a
small
amount
of
cleaner
to
an
inconspicuous
place
and
test
for
reaction
and
fading.
4.
Cleaning
Carpet
A.
The
carpet
is
made
of
a
polypropylene weave
combined
with
a
fire-retardant backing.
The
polypropylene
provides inherent
stain-resistant
qualities
and
normally
requires only
a
minimal
amount
of
maintenance.
B.
If
the
carpet
is
soiled,
it
can be
cleaned
with
commercially-available carpet cleaning
products.
12-23-00
©
Cessna
Aircraft
Company
Page
701
Jan 2/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
5.
Cleaning Seats
A.
The
seats
are
made
of
a
flame-retardant
Trevira
polyester
fiber
and
have
inherent
fire-retardant
and
stain-resistant
properties.
Seats
must
be
vacuumed
and
cleaned
on
a
regular basis
to
keep
their
appearance.
Spills
and
stains
must
be
blotted
up
immediately
and the
fabric
cleaned
as
soon
as
possible.
B.
Table
701
gives
instructions
for
specific
stain
removal. The
table
has
two
columns.
The
first
column
lists
the
stain
and
the
second
column
lists
the
method
and
sequence
of
cleaning.
For
example,
remove
coffee
and
tea
stains
with
processes
2, 4, 5,
and
1.
First,
apply
the
ingredients
in
process
2
(dishwashing
liquid
with
warm
water)
to
the
stain.
Then apply
the
ingredients
in
process
4
(vinegar
and
water) to
the
stain. The
third
step
is
process
5
(laundry powder
and
warm
water
followed
by
blotting).
Then
apply process
1
(dry
cleaning
solvent
applied
to
the stain)
to
finish
the stain
removal
of
coffee
or
tea
stains.
Table
701.
Methods
To
Clean Trevira
Fabric
on
Seats
STAIN
PROCESS
AND STAIN
PROCESS
AND
SEQUENCE SEQUENCE
Antacid
(Maalox)
1
Infant
Formula
2,1
Betadine
(Iodine)
2,3,4,6
Ink
(ball
point)
8
Blood
*
2,3,5
Motor
Oil
1,2,3,4
Catsup
2,3,5
Mud
2,1
Chewing
Gum
7,1,2
Petroleum
Jelly
1,2
Chocolate
Syrup
5,1
Pepto
Bismol
6,1
Coffee/Tea
2,4,5,1
Urine
2,3,4
Cola
2,3,4
Suntan
Lotion
1,2
Cough
Syrup
2
Shoe
Polish
1,2,3
Egg
2,3,5,1
Vomit
2,3,4,5
Grape
Drink
2,3,4,5
Wax
7,1
Ice
Cream
2,3,4,5,1
Wine
2,3,4
.
Process
1
-
Apply
a
small
amount
of
dry
cleaning
solvent
to the
stain.
Do
not
smoke
or
use
near
open
flame.
Make
sure
that
there
is
good
airflow
in
the
area
when you
clean.
.
Process
2
-
Mix
one
teaspoon
of
white
or
colorless dishwashing
liquid
with
a
cup
of
lukewarm
water.
.
Process
3
-
Mix
one
tablespoon
of
household
ammonia
with
half
a
cup
of
water.
.
Process
4
-
Mix
one
part
household
vinegar
with two
parts
water.
.
Process
5
-
Mix
a
solution
of
laundry
powder
with
water
and
allow
to
remain
on
stain.
Follow
label
directions.
Rinse
with
warm
water
and
blot
dry.
.
Process
6
-
Mix
one
part
household bleach
with
nine parts
water.
Apply
with
dropper
to
stain.
Rinse
with
water
and
blot
dry.
.
Process
7-
Chill
area with
an
ice
cube
wrapped
in
a
plastic
bag.
Crack
gum
or
wax
off
surface
of
fabric.
.
Process
8
-
Apply
a
small
amount
of
rubbing
alcohol
to
ink
stain and
blot
to
remove ink.
Continue
until
ink
is
removed.
NOTE:
*
All
solutions
must
be
cool
when
applied,
or
heat from
the
solutions
will
set
the
stain.
12-23-00
Page
702
©
Cessna
Aircraft
Company
Jan
2/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
6.
Cleaning
the GDU
1040
Display
Lens
NOTE: The
Primary
Flight
Display
(PFD)
and
Multi-Function
Display
(MFD) are
the
GDU
1040
displays
in
airplanes
with
Garmin G1000.
CAUTION:
If
possible,
do not
touch
the
GDU
1040
display
lens.
The lens has
a
layer
of
anti-reflective
material
which
is
very sensitive
to
skin
oils, waxes,
and
abrasive
cleaners.
CAUTION:
Do
not
use
cleaners
that
contain
ammonia.
Ammonia
will
cause damage
to
the
anti-reflective
material.
A.
Clean
the
GDU
1040
Display
Lens.
(1)
To
clean
the
lens,
use
a
clean, lint-free
cloth
and
an
eyeglass
lens
cleaner
that
is
specified
as
safe
for
anti-reflective
material.
12-23-00
Page
703
C
Cessna
Aircraft Company
Jan 2/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
UNSCHEDULED
SERVICING
-
DESCRIPTION
AND
OPERATION
1.
General
A.
This
section
gives
procedures
and
recommendations for normally unscheduled
servicing.
B.
Instructions
are
given
in
the
Cold
Soak procedures
for
operation
of
the
airplane
during
very
cold
temperatures.
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.
2.
Extreme
Weather
Maintenance
A.
Seacoast
and
Humid
areas.
(1) In
salt
water areas,
special
care
should
be
taken
to keep
engine,
accessories,
and
airframe
clean
to
help
prevent
oxidation.
(2)
In
humid
areas,
fuel
and
oil
should
be
checked
frequently
and
drained
of
condensation
to
prevent
corrosion.
3.
Ground
Power
Receptacle
A.
Connect
to
24-volt
DC,
negative
ground
power
unit
with
a
maximum
output
of
28.8
volts, for
cold
weather
starting, and
lengthy
ground
maintenance
of the
airplane electrical equipment,
with
exception
of
electronic
equipment.
Refer to
Pilot's
Operating
Handbook
and
FAA
Approved Airplane
Flight
Manual
for
engine
starting instructions
with
auxiliary
power.
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.
4.
Cold
Soak
A.
If
extended exposure
to
cold
weather
is
expected,
refer to
this
procedure
to
prepare
the
airplane
for
cold soak.
If
the
airplane
has
cold
soaked
for
more than
two hours
at
temperatures
colder
than
-10
°C (14
°F),
refer
to
this
procedure
and
the Pilot's
Operating Handbook
and
FAA
Approved Airplane
Flight Manual
to
prepare the
airplane
for
flight.
(1)
Cold
temperatures
have
an
effect
on
control
cable
tension.
Refer
to
Chapter
27,
Aileron
Control
System
-
Maintenance Practices,
Rudder
Control
System
-
Maintenance Practices,
Elevator
Control
System
-
Maintenance Practices,
Elevator
Trim
Control
-
Maintenance Practices,
and
Flap
Control
System
-
Maintenance
Practices
for
flight
control
cable
tensions.
(2)
For
information
on
lubrication
and
greasing
of
moving
parts,
refer
to
Chapter
12,
Lubricants
-
Description and Operation.
(3)
Refer
to
the
Pilot's
Operating Handbook
and
FAA
Approved
Airplane
Flight
Manual
for
the
correct
engine
oil
viscosity.
(4)
Refer
to
the
Pilot's
Operating
Handbook
and
FAA
Approved Airplane
Flight
Manual
for additional
information
on
procedures
for
operation
of
the
airplane
in
cold
temperatures.
B.
The
engine
must
be
preheated
before
an
engine
start
when
exposed
to
very
cold
temperatures.
Preheat
the
engine
as
follows:
(1)
Direct
warm
air
into
the engine cooling
inlets behind
the
propeller.
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.
(2)
Make
sure
that
the
temperature
of the
warm
air
is
no more
than
120 °C
(248
°F).
12-30-00
Page
1
©
Cessna Aircraft
Company
Jan
2/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
WARNING:
Never
bring
open
flames
near
the
airplane.
Use
of
a
heater
with
an
open flame
to
preheat
the
engine
can
cause
damage
to
the
airplane
and
injury to
personnel.
(3)
(4)
(5)
Do
not use
a
heater
with open
flames
to
supply
the
warm
air
to preheat
the
engine.
Preheat
the
engine
before
an
engine start
if
the
engine temperature
is
less
then
-6
°C (20
°F).
When
the
temperature
is
less
than
0
°C
(32
°F),
preheat
the
engine
to
more
than
0 °C (32
°F)
before
you
start
the
engine
again
after
an
engine start
and
stop.
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.
C.
The
Garmin
GDU
1040 PFD/MFD
requires
warm-up time
when
exposed
to
very
cold
temperatures.
(1) A
warm-up time
of
up
to
30
minutes
is
necessary
when
the
GDU
is
exposed
to
down
to -40
°C
(-40
°F)
for
an
extended
period.
(2) A
warm-up time
of
up
to
15
minutes
is
necessary
when
the
GDU
is
exposed
to
down
to
-30 °C
(-22
°F)
for
an
extended
period.
D.
Before
takeoff,
preheat
the
airplane
cabin
to
more
than
-30
°C (-22
°F)
for
correct
operation
of
the
standby
altimeter.
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
Page
2
©
Cessna
Aircraft
Company
Jan
2/2006
CHAPTER
STA
MDAR
PRACICE
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
LIST
OF
EFFECTIVE PAGES
CHAPTER-SECTION-SUBJECT
20-Title
20-List
of
Effective Pages
20-Record
of
Temporary
Revisions
20-Table
of
Contents
20-00-00
20-10-00
20-11-00
20-12-00
20-1
3-00
20-30-00
20-3
1-00
20-31
-00
20-31-00
20-32-00
20-50-00
©
Cessna Aircraft
Company
PAGE
Page
1
Pages
1-4
Pages
201
-207
Pages
201
-211
Pages 201-202
Page
1
Pages
1-3
Pages 201-204
Pages 701-705
Pages
201 -218
Pages
1-17
DATE
April
1/2002
Mar
1/2004
Janl1/2007
Mar
1/2004
Mar
1/2004
April
1/2002
Mar
1/2004
Mar
1/2005
April
1/2002
Jul
3/2006
April
1/2002
20
-
LIST
OF
EFFECTIVE
PAGES
Page
1
of
1
Jan11/2007
Temporary
Revision
Number
RECORD
OF
TEMPORARY
REVISIONS
Page
Number
Issue
Date
By
Date
Removed
By
CESSNA AIRCRAFT
COMPANY
MODEL
182/T1
82
MAINTENANCE
MANUAL
CONTENTS
STANDARD PRACTICES AIRFRAME
-
GENERAL
.................
Scope....................................
Definition
..................................
MATERIAL
AND
TOOL
CAUTIONS
-
DESCRIPTION
AND
OPERATION........
Titanium...................................
Mercury...................................
Asbestos
..................................
Cadmium
Plated
Fasteners..........................
Maintenance
Precautions...........................
General
Usage
Solvents
...........................
National
Emissions Standards
for
Hazardous
Air
Pollutants
...........
Facilities
and
Equipment
...........................
TORQUE
DATA
-
MAINTENANCE
PRACTICES...................
General...................................
Torque
Requirements
for Bolts,
Screws
and
Nuts................
Torque
Requirements
for
Hi-Lok
Fasteners...................
Torque
Requirements for
Electrical
Current
Carrying
And
Airframe
Ground
Fasteners.................................
Torque
Requirements
for
Rigid
Tubing
and
Hoses................
SAFETYING
-
MAINTENANCE PRACTICES
....................
General...................................
Safety
Wire
.................................
Safety
Wire
Installation............................
Cotter
Pin
Installation.............................
Safetying Turnbuckles
............................
CONTROL
CABLE
WIRE BREAKAGE
AND
CORROSION
LIMITATIONS
-
MAINTENANCE PRACTICES
...........................
Examination
of
Control
Cables
........................
SOLVENTS, SEALANTS,
AND
ADHESIVES
-
DESCRIPTION
AND
OPERATION
...
General...................................
Description
.................................
ACCEPTABLE
REPLACEMENTS
FOR
CHEMICALS
AND
SOLVENTS
-
DESCRIPTION
AND
OPERATION
................................
General...................................
Hand-Wipe
Cleaning Operations
.......................
Priming
Operations..............................
Topcoat
Operations
.............................
Paint
Stripping
Operations
..........................
GENERAL SOLVENTS/CLEANERS
-
MAINTENANCE PRACTICES
.........
General...................................
Tools,
Equipment
and
Materials........................
Safety
Precautions..............................
D
escription
......
. . . . ...... . . . ........... . . . . .
INTERIOR
AND
EXTERIOR
FINISH
-
CLEANING/PAINTING.............
General...................................
Interior
and
Exterior Finishes
.........................
Paint
Facility.................................
Sanding
Surfacer
..............................
Paint
Stripping................................
Hand
Solvent
Cleaning............................
Maintenance
of
the
Interior
and
Exterior
Primary
Coatings
and
Topcoat......
©
Cessna
Aircraft Company
20-00-00
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1
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1
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1
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1
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1
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2
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3
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3
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201
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204
20-11
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205
20-11
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206
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206
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208
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1
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1
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1
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1
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2
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3
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201
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201
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201
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701
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701
20-31
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701
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701
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701
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704
20-3
1
-00
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705
20
-
CONTENTS
Page
1
of
2
Janl1/2007
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti
182
MAINTENANCE
MANUAL
FUEL,
WEATHER
AND
HIGH-TEMPERATURE
SEALING
-
MAINTENANCE
PRACTICES
...................................
General...................................
Tools
and
Equipment.............................
Definition
of
Sealing
Terms
..........................
Materials
..................................
General
Requirements............................
Sealant
Curing................................
Mixing
of
Sealants..............................
Cleaning
..................................
Sealing
Application..............................
Sealant
Repair................................
CONVERSION
DATA
-
DESCRIPTION
AND
OPERATION
..............
General...................................
Formulas for
Conversion
Computations
....................
20-32-00
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201
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201
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201
20-32-00
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20
-
CONTENTS
Page
2
of
2
Janl1/2007
©D
Cessna
Aircraft Company
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
STANDARD PRACTICES AIRFRAME
-
GENERAL
1.
Scope
A.
This
Chapter
describes
the standard
maintenance
practices for
maintaining
and
repairing
items
of
the
airframe
and
systems
that
are
typical
to
more
than
one
area or system.
Maintenance
practices
which
are
unique
to
a
particular
system or
subject
are
described
in
the
appropriate
chapter
and
section
in
the
maintenance
manual.
B.
For
repairs
beyond the scope
of
this manual,
refer
to
the
1996
and On
100
Series Structural
Repair
Manual.
2.
Definition
A.
This
chapter
is
divided
into
sections
to
aid
maintenance personnel
in
locating
information. Consulting
the
Table
of
Contents
will
further
assist
in
locating
a
particular
subject.
A
brief
definition
of
the
subjects
and
sections
incorporated
in
this
chapter
is
as
follows.
(1)
The
section
on
Material
and
Tool
Cautions describes
general
cautions
and
warnings
applicable
to
maintenance
on
or
around
the
airplane.
(2)
The
section
on
Torque
Data
provides
tables, formulas, requirements
and
torque
limits
for
various
type
fasteners.
(3)
The
section
on
Safetying
describes
the proper methods
and use of
safety
wire/lockwire,
cotter
pins and
lock
clip
installations.
(4)
The
section
on
Control
Cables and Pulleys
describes
the
construction, examination
and
storage
of
cable
assemblies
and
pulleys.
(5)
The
section
on
Solvents,
Sealants
and
Adhesives provides
the
description
and
uses
for solvents
and
cleaners;
fuel,
weather,
pressure
and
high
temperature
sealing; and the
application
of
adhesives
and
solvent
bonding.
(6)
The
section
on
Conversion
Data
contains
information
converting
the
more
commonly
used
measuring units found
in
the
Maintenance
Manual.
20-00-00
Page
1
©
Cessna
Aircraft
Company
April 1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
MATERIAL
AND
TOOL
CAUTIONS
-
DESCRIPTION AND
OPERATION
1.
Titanium
CAUTION:
Do
not
use
cadmium-plated tools
on
titanium
parts.
Cadmium
particles
can
stay
on
such parts.
The
cadmium
particles
will
cause
an
unwanted
condition
with
the
titanium
when
heated. The
titanium
part
will
become brittle
in
the
area
of
the
unwanted
condition
and
make
cracks.
CAUTION:
Do
not
let
cadmium-plated
fasteners
touch
titanium
parts.
2.
Mercury
CAUTION:
Do
not use
thermometers
and
other mercury-based
test
equipment
on
the
airplane.
A.
Corrosion Caused
by Mercury.
(1)
There
is
no
known
procedure
to
stop
corrosion
when
it
has
started.
(2)
Mercury
can
go
into
any
crack
in
the
finish,
paint,
or
seal
layer
of
a
metal.
An
oxide
layer
on
a
dry metal
surface
will
prevent
corrosion.
A
bright
surface,
a
polished
surface,
or
a
surface
with
scratches
will
increase
the
rate
of
corrosion.
(3)
Dirt,
grease,
or
other
contaminants that
have
no
effect
on
the
metal
surfaces
will help
prevent
corrosion.
(4)
The
corrosion
and
the
embrittlement caused
by
corrosion
can
be
very
fast
in
structural
members.
3.
Asbestos
WARNING:
Do
not
let
asbestos
fibers
make
entry
into
the
body
of
personnel.
Asbestos
fibers
can
cause
injury
or
death.
A.
Do
not
breathe
the
dust
of
asbestos fibers.
To
not
breathe
the
dust
of
asbestos
fibers,
use
either
of
the methods
that
follows.
(1)
Use
engineering
control,
which
includes
work
in a
correctly
filtered
exhaust
chamber.
Use
wet
procedures
to keep
personnel
less
than
Occupational
Safety
Health
Administration
(OSHA)
personnel exposure
limits.
(2)
Use
breathing
equipment
with
high
quality
filters. Other protection
must
include
protective
clothing, gloves
and
eye
protection.
B.
Refer
to
all
local,
state,
and
federal
regulations
to
discard
asbestos
material.
4.
Cadmium
Plated Fasteners
CAUTION:
Put
a
complete layer
of
fuel
sealant
on
cadmium
plated
fasteners
that
are
used
in
fuel
areas.
Cadmium
particles
from
cadmium
plated
fasteners
can
cause damage
to
the
engine.
5.
Maintenance
Precautions
WARNING:
Obey
the
precautions
during
maintenance,
repair, and
service
procedures
of
the airplane
to
prevent
injury
because
of
the
different
materials
and
environmental
conditions.
A.
Carefully
read
and
follow
all
instructions.
(1)
Obey
all
cautions
and
warnings
given
by
the
manufacturer
of
the
product
that
is
used.
(a)
Use
the
applicable safety equipment
such
as
goggles,
face
shields,
breathing
equipment,
protective
clothing
and
gloves.
(2)
Do
not get
dangerous
chemicals
in
the
eyes
or
on
the
skin.
20-10-00
Page
1
©
Cessna
Aircraft Company
Mar 1/2004
CESSNA
AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
(3)
Do
not
breathe
the fumes
of
dangerous
chemicals.
(4)
Make sure
the work area
has
good
airflow
and
the
applicable
breathing
equipment
is
used when
composites
or metals
are
sanded
or
work
is
done
in
an
area
where
small
particles
can
be
made.
6.
General
Usage
Solvents
A.
Airplane
maintenance
procedures
frequently
use
solvents.
A
solvent
is
a
material,
usually
a
liquid,
that
can
break
down
another
material.
Solvents usually
have
no
color,
dry
quickly,
and
give
off
fumes
in
high
quantities.
Examples
of
general
use
solvents
are as
follows:
·
Methyl
n-Propyl
Ketone
Toluene
·
Isopropyl
Alcohol
Acetone
·
Methylene Chloride
1,1,1
-
Trichlorethane
·
Naptha
ASTM
D4080
B.
Solvents
can
cause
injury or
death.
Solvents usually
have
no
color,
dry quickly,
and
give
off
fumes
in
high
quantities.
The fumes
are
usually heavier
than
air.
The
fumes
can
collect
in
low-level
areas
and
push
air
out
of
the
areas
that
are
not
ventilated.
This
can
remove
the supply
of
oxygen
from the
area.
(1)
The
solvent
fumes
are
usually
heavier
than
air.
(2)
The
solvent
fumes
can
be
breathed.
Use
applicable
breathing
equipment.
(3)
Solvents
can
cause
damage
to
the hands
and the
skin.
(a)
Solvents
dry out the
skin
and
remove
the
natural oils.
Damaged skin
allows
other
contamination
to the
make
the
condition
worse.
(b)
The
contamination
has
easier
access
to
the
lowest levels
of
the
skin.
1
The
human
body
can
filter
small
amounts
of
solvents
out
of itself.
This filtration
function takes
place
in
the
liver.
The
liver
receives
blood
which
can
be
contaminated
with
solvents
from both
the
lungs and the
skin.
If
the
quantities
are
low
enough
and not
too
frequent,
the
liver
can
filter
out
the
contaminants.
This
is
one
of
the
scientific facts
on
which OSHA based
its
Permissible
Exposure
Limits. However, when
exposures
are
constantly
above
these
levels over
an
extended
period
of
many
years,
the
filter
(liver)
becomes
clogged
and
the
solvents
can then
affect
other parts/portions
of the
body.
C.
Solvents
are
hazardous
materials
because
of
flammability.
The
rate
of
evaporation
is
related
to
flammability.
The
fumes
are
usually
needed
to
ignite
the
liquid. Any ignition
source
can
ignite
solvent
fumes.
The low
flash
point
of
the
solvent
shows that
the solvent
can
ignite
easily.
Usually the
flash
points
of
less
than
100'F
(37.8"C)
are
thought
to
be
flammable.
Examples
of
solvent flash
points
are
as
follows.
SOLVENT
FLASH
POINT
Methyl
n-Propyl
45F
(7.2'C)
Ketone
Toluene
39F
(3.9;C)
Isopropyl
Alcohol
53.6F
(12cC)
Acetone
1.4F
(-17cC)
D.
Solvents
can
be
explosive
when mixed with
chemicals
that release
oxygen (oxidizer).
For
this
reason,
it
is
very
important
for personnel
to
know
which
chemicals
are
in
use
in
the
work
area
to
avoid
accidental
mixture
of
solvents
and
oxidizers.
(1)
Know
the
container
labels.
(a)
Chemical manufacturers
are
required
to
put
a
label
with
a
diamond-shaped
symbol
on
each
container.
1
The
red
symbol
on
the
label shows
that
the
contents
are
flammable.
2
The
yellow
symbol
on
the
label
shows
that
the
contents
are
oxidizers.
20-10-00
Page
2
©
Cessna Aircraft Company
Mar
1/2004
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
7.
National
Emissions
Standards
for
Hazardous
Air
Pollutants
A.
National
Emissions Standards
for
Hazardous
Air
Pollutants
(NESHAP).
(1)
The
NESHAP
standards
have put
a
limit
on
the
use of
certain chemicals
and
solvents.
(2)
For
complete details
of the
regulatory
standards, see
the Federal
Register,
40
CFR
Part
63,
[Ad-FRL-5636-1],
RIN
2060-AG65.
B.
NESHAP
Requirements.
(1)
Hand-Wipe Cleaning.
(a)
All
hazardous
air
pollutants
or
organic compounds that
release
dangerous fumes that
are
used
as hand
wipe
cleaning
solvents
must
meet
a
composition requirement and have
a
vapor
pressure
less
than
or
equal
to
1.75
Hg
at
69°(45
mm
Hg
at
2
O'C.)
(b)
The
requirements specified
may be met
by
an
alternative
compliance
plan used by
the
permitting
authority
and
approved
under
Section
112(1)
of
the
Clean
Air
Act.
(2)
Primer
Application.
(a)
The
organic
hazardous air
pollutant content
is
limited
to
350
g/l
(2.9
pounds-per-gallon),
less
water,
as
applied.
(b)
The
volatile organic
compound limit
is
350
g/l
(2.9
pounds
per
gallon),
less
water,
as
applied.
(c)
Use
coatings
below
the
content
limit or
use
monthly volume-weighted
averaging
to
get
the
content
limits
to meet
content
limits.
(3)
Topcoat
Application.
(a)
The base coat
organic
hazardous air pollutant
content
must
be
less than
420
g/l
(3.5
pounds-per-gallon),
less water,
as
applied.
(b)
The
volatile
organic
compound
limit
is
420
g/l
(3.5
pounds
per
gallon),
less water,
as
applied.
(c)
The
topcoats
must
meet
the
requirements
of
MIL-C-85285.
(d)
Stripe paint requirements
are
the
same
as
the
base coat
requirements.
If
the
recommended
supplier
cannot
be
used,
then
use
base coat
materials
to
paint
stripes.
NOTE:
All
paints
and
primers must
have
specific
application
techniques.
If
an
alternative
is
supplied,
use
only
the
materials
that
are
less than or
equal
in
emissions,
to
less than
the
HVLP
or
electrostatic
spray
application
techniques.
NOTE:
Operate
all
application
equipment
according
to
the
manufacturer's
specifications,
company
procedures
or locally
specified
operating procedures.
(4)
Paint
Removal
(a)
Paint removal
operations apply
to
the
outer
surface
of
the
airplane
and
do not
apply
to
parts
or
units
normally
removed.
Fuselage,
wings
and
stabilizers
are
covered. Radomes
and
parts
normally
removed
are
exempt
from
the
following
requirements:
1
No
organic hazardous
air
pollutants
are
to
come
from
chemical
strippers
or
softeners.
2
Inorganic
hazardous
air pollutant
fumes
must
be
kept
to
a
minimum during
periods
of
non-chemical
based
equipment malfunctions.
3
The
use
of organic
hazardous air pollutant
material
for
spot
stripping and
decal
removal
is
kept
to
a
minimum
of
190
pounds
per
airplane
per
year.
(b)
Operating requirements
for
paint
removal
operations that
give
airborne
inorganic
hazardous
air
pollutants
include control
with
particulate filters
or
water
wash
systems.
(c)
Mechanical
and hand
sanding
are
exempt
from
these
requirements.
8.
Facilities
and
Equipment
A.
Facilities
(1) A
system
must
be
supplied
to
collect
processing waters
to
treat
for
chromium
and
pH
or
to
be
removed.
(2)
Facilities
must
have
proper
safety
equipment.
20-10-00
Page
3
©
Cessna
Aircraft
Company
Mar 1/2004
CESSNA AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
B.
Equipment
(1)
Applied
spray
of
cleaning
solvents,
paint
removers or
color
chemical
film
treatment
solutions
is
to be
prevented unless
all
requirements
of
NESHAP
are met.
(2)
Spraying equipment to wash
the
airplane
with
alkaline
cleaner
can
be used.
This
equipment
is
sufficient
to
spray
deoxidizer, chemical
film
solutions
and
rinse
water.
(3)
A
high
pressure
washer
is
recommended,
with or
without
hot
water.
(4)
Respirators
and/or
dust
masks
must
be
used.
20-10-00
Page
4
©
Cessna
Aircraft
Company
Mar 1/2004
CESSNA AIRCRAFT
COMPANY
MODEL
182/Ti
82
MAINTENANCE
MANUAL
TORQUE
DATA
-
MAINTENANCE PRACTICES
General
A.
To
ensure
security
of
installation
and
prevent
over
stressing
of
components
during
installation,
the
torque
values
outlined
in
this
section
and
other
applicable
chapters
of
this
manual
should
be
used
during
installation
and
repair
of
components.
B.
The
torque
value
tables,
listed
in
this section,
are
standard
torque
values for
the
nut
and
bolt
combinations
shown.
If a
component
requires
special torque
values,
those
values
will be
listed
in
the
applicable
maintenance
practices section.
C.
Torque
is
typically
applied
and
measured
using
a
torque wrench.
Different
adapters,
used
in
conjunction
with
the
torque
wrench,
may
produce
an
actual
torque
to
the
nut
or bolt
which
is
different
from
the torque reading.
Figure
201
is
provided
to
help
calculate
actual
torque
in
relation
to
specific
adaptors
used
with
the
torque
wrench.
D.
Running
Torque
Value.
(1)
Running torque value
is
the
torque
value
required
to
rotate
a
nut
on
a
threaded
shaft,
without
tightening.
Running torque
value does
not
represent the
torque values
listed
in
the
tables
of
this
section.
Torque
values
listed
in
the
tables
represent
the
torque
values above
running
torque.
For
example,
if
final
torque
required
is
to
be 150
inch-pounds
and
the
running
torque
is
25
inch-
pounds,
then
the
running
torque must
be
added
to
the
required
torque
to
achieve final
torque
of
150
+25
=
175
inch-pounds.
(2)
Breakaway
torque
value
is
the
value
of
torque required
to
start
a
nut
rotating
on
a
thread shaft,
and
does
not
represent
running torque
value.
It
should
be
noted
that
on
some
installations
the
breakaway
torque
value
cannot
be
measured.
E.
General
Torquing
Notes.
(1)
These
requirements
do
not
apply
to
threaded
parts
used
for
adjustment,
such
as
turnbuckles
and
rod
ends.
(2)
Torque
values
shown
are
for
clean,
non-lubricated
parts.
Threads should
be
free
of
any
contamination.
Lubricants,
other
than
those
on
the
nut as
purchased,
should
not
be
used
on
any
bolt
installation
unless
specified.
(3)
Assembly
of
threaded fasteners, such
as
bolts,
screws
and
nuts,
should
conform
to
torque
values
shown
in
Table
201.
(4)
When
necessary
to
tighten
from
the bolt
head,
increase
maximum
torque
value
by
an
amount
equal
to
shank friction.
Measure
shank
friction
with
a
torque
wrench.
(5)
Sheet
metal
screws should
be
tightened
firmly,
but not
to
a
specific
torque
value.
(6)
Countersunk washers
used with
close
tolerance
bolts
must
be
installed
correctly
to
ensure
proper
torquing
(refer
to
Figure 202).
(7)
For
Hi-Lok
fasteners
used
with
MS21
042
self-locking
nuts,
fastener
and
nut
should
be
lubricated
prior
to
tightening.
(8)
Tighten
accessible
nuts
to
torque values per
Table
201.
Screws
attached
to
nutplates,
or
screws
with
threads
not
listed
in
Table
201
should
be
tightened
firmly,
but
not
to
a
specific
torque value.
Screws
used
with
dimpled
washers
should
not
be
drawn
tight
enough
to
eliminate
the
washer
crown.
(9)
Table
201
is
not
applicable
to
bolts,
nuts and
screws
used
in
control
systems
or
installations
where
the
required
torque would
cause
binding,
or
would interfere
with
proper
operation
of
parts.
On
these installations,
the
assembly
should
be
firm
but not
binding.
(1
0)
Castellated
Nuts.
(a)
Self-locking
and
non
self-locking
castellated
nuts,
except
MS1
7826,
require
cotter
pins
and
should
be
tightened
to
the
minimum
torque
value
shown
in
Table
201.
The
torque
may
be
increased
to
install
the
cotter
pin,
but
this
increase
must
not
exceed
the
alternate torque
values.
(b)
MS1
7826
self-locking, castellated
nuts
shall
be
torqued per
Table
201.
(c)
The
end of
the bolt or
screw
should
extend
through
the
nut at
least
two
full
threads including
the
chamfer.
20-1
1-00
Page
201
(D
Cessna
Aircraft
Company
Jan11/2007
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T1
182
MAINTENANCE
MANUAL
NOTE:
A
TORQUE
WRENCH ADAPTER
CHANGES
THE
DISTANCE
FROM
THE
TORQUE
WRENCH
ATTACHMENT
FITTING
TO
THE
ADAPTER CENTERLINE.
THE
FORMULAS
THAT
FOLLOW
CAN
BE
USED
TO
GET
THE
CORRECTED
TORQUE
INDICATION.
B1
101
SHORT
OPEN-END
ADAPTER
ADAPTER
CENTERLINE
SETSCREW
ADAPTER
TORQUE
WRENCH
WRENCH
ATTACHMENT
FITTING
CENTERLINE
FORMULA
Tx
L
- Y
L+E
EXAMPLE (WITH
"E"
AS
PLUS
DIMENSION)
T
=
135
IN-LB
Y
=
UNKNOWN
E
=
1.5
IN
L
=
10.0
IN
HOSE
CLAMP
ADAPTER
Y =
135
x
10
=
117.39
10
+ 1.5
Y
=
1 17
IN-LB
LEGEND
T
=
TORQUE
TO
BE
FOUND
Y
=
TORQUE
SHOWN
ON
TORQUE
WRENCH
L
=
LENGTH
OF
LEVER
E
=
LENGTH
OF
EXTENSION
OPEN-END
WRENCH
ADAPTER
FLARE
NUT
WRENCH
ADAPTER
SPANNER
WRENCH
ADAPTER
ADAPTER
%AIDE:MrLJ
CENTERILINE
ATTACHM
CENTERLI
HANDLE
CENTERLINE
FORMULA
Tx
L
=
y
L
-E
EXAMPLE (WITH
"E"
AS
MINUS
DIMENSION)
T
=
135
IN-LB
Y
=
UNKNOWN
L
=
1
0.0
IN
E
=
1.5
IN
TORQUE
WRENCH
Y
= 135
x
10
=
1350
=
158.82
10
-
1.5
8.5
Y
=
159
IN-LB
5598T2005
Torque
Wrench
and
Adapter
Formulas
Figure
201
(Sheet
1)
©
Cessna Aircraft Company
20-1
1-00
Page
202
Janl1/2007
JO)
6
CESSNA AIRCRAFT
COMPANY
MODEL
182/Ti182
MAINTENANCE
MANUAL
EXTERNAL
WRENCHING
HEAD
CORRECT
INSTALLATION
INSTALL WASHER
WITH
COUNTERSUNK
FACE
NEXT TO
BOLT HEAD
RADIUS
INTERNAL
WRENCHING
HEAD
COUNTERSUNK
WASHER
INCORRECT
INSTALLATION
CAUTION:
NEVER
INSTALL
STANDARD
WASHER
OR
COUNTERSUNK
WASHER
IN
REVERSE
WHEN
USING
BOLTS
WITH
RADIUS
UNDER THE
HEAD
5598T1
004
5598T1
004A
Washer
Installation
Close
Tolerance
Bolts
Figure
202
(Sheet
1)
Q
Cessna
Aircraft
Company
20-1
1-00
Page
203
Janl1/2007
Bi
102
STANDAR[
WASHER
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti 182
MAINTENANCE
MANUAL
(11)
Joints
containing
wood,
plastics,
rubber
or
rubberlike materials
should
be
torqued
to
values
approximately
80
percent
of
the
torque
at
which crushing
is
observed,
or
to
the
requirements
of
Table
201,
whichever
is
lower, or
as
specified.
2.
Torque
Requirements
for
Bolts,
Screws
and
Nuts
A.
Use
Table
201
to
determine
torque requirements
for
bolts,
screws
and
nuts.
Table
201.
Torque
Requirements
For
Steel
Bolts,
Screws,
and
Nuts
(Inch-Pounds)
SIZE
Standard
Torque
8-36
12
tolS5
10-32
20
to
25
1/4-28
50
to
70
5/16-24
100
to
140
3/8-
24 160
to
190
7/16-20
450
to
500
1/2-20
480
to
690
9/16-18
800
to
1
000
5/8-18
llO
to1300
3/4-16
2300
to
2500
7/8-14
2500
to
3000
1-14
3700
to
4500
1-1/8-12
5000
to
7000
1-1/4-12
9000
to
11000
FINE
THREADED
SERIES
(SHEAR TYPE NUTS
EXCEPT
IVI17826)
Alternate
Standard
Torque
Torque
--
~~7
to
9
20
to
28
12
to
15
50
to
75 30
to
40
100
tolSO0
60
to
85
160
to 260
95
to
110
450
to
560
270
to
300
480
to
730 290
to41
0
800
to
1070 480
to
600
llO
00tol1600
660
to 780
2300
to
3350
1300
to
1500
2500
to
4650
1500
to
1800
3700
to
6650
5000
to
10000
9000
to
16700
2200
to
3300
3000
to
4200
5400
to
6600
12
to
19
30
to
48
60Oto
100
95
to
170
270
to
390
290
to
500
480
to
750
660
to
1060
1300
to
2200
1500
to
2900
2200
to
4400
3000
to
6300
5400
to
10000
Fine
Thread
Tension
application
nuts
include:
AN310, AN315,
AN345,
MS17825,
MVS20365,
NASM21
044
through
MVS21
048,
MVS21
078,
NAS679,
NASi
291
Fine
Thread
Shear application
nuts include: AN316,
AN320,
MVS21025, MVS21042,
IVS21043,
MVS21083,
MVS21245,
NAS1022,
S1117
Coarse
Thread
application
nuts
include:
AN340,
MVS20341, MVS20365,
MS35649
20-1
1-00
Page
204
©
Cessna
Aircraft
Company
Janl1/2007
FINE
THREADED
SERIES
(TENSION
TYPE
NUTS)
MS1
7826
NUTS
Alternate
Standard
Alternate
Torque Torque Torque
12
to
15
30
to
40
60
to
80
95
to
110
180
to
210
240
to
280
320
to
370
480
to
550
880
to
1010
1500
to
1750
2200
to
2700
3200
to
4200
5900
to
6400
12
to
20
30
to
45
60
to
90
95
to
125
180
to
225
240
to
300
320
to
400
480
to
600
880
to
1
100
1500
to
1900
2200
to
3000
3200 to
5000
5900
to
7000
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti182
MAINTENANCE
MANUAL
Meters)
FINE
THREADED
SERIES
(TENSION
TYPE
NUTS)
FINE
THREADED SERIES
(SHEAR TYPE NUTS
EXCEPT
MS1
7826)
MS17826
NUTS
Alternate
Standard
- -
~~0.8-1
.0
2.3-3.2
1.4-1.7
5.6-8.5
3.4-4.5
11.3-16.9
6.8-9.6
18.1-29.4
10.7-12.4
50.8-63.3 30.5-33.9
54.2-82.5
32.8-46.3
90.4-120.9
54.2-67.8
124.3-180.8
74.6-88.1
259.9-378.5
146.9-169.5
282.5-525.4
169.5-203.4
418.0-751.3
248.6-372.9
564.9-1129.9
339.0-
474.5
1016.9-
610.1-745.7
1886.9
Alternate
1.4-2.1
3.4-5.4
6.8-11.3
10.7-19.2
30.5-44.1
32.8-56.5
54.2-84.7
74.6-119.8
146.9-248.6
169.5-327.7
248.6-497.1
339.0-711.8
61
0.1-1129.9
3.
Torque
Requirements
for
Hi-Lok
Fasteners
A.
Use
Table
202
to
determine
torque
requirements
for
Hi-Lok
fasteners.
NOTE:
This
table
is
used
in
conjunction
with
MS21042
self- locking
nuts.
Table
202.
Torque
Values
Hi-Lok Fasteners
(Used
with
MS21042
Self-Locking
Nuts)
NOMINAL
FASTENER
DIAMETER
6-32
8-32
10-32
1/4-28
5/16-24
3/8-24
7/16-20
1/2-20
ALLOY
STEEL 180
-
200
KSI
(INCH-POUNDS)
8-10
12-15
20-25
50-70
100-1
40
160-1 90
450-500
480-690
©
Cessna
Aircraft
Company
20-1
1-00
Page
205
Janl1/2007
(Newton
SIZE
OF
BOLT,
NUT
OR
SCREW
8-36
.10-32
1/4-28
5/16-24
3/8-
24
7/16-20
1/2-20
9/16-18
5/8-18
3/4-16
7/8-14
1-14
1-1/8-12
1-1/4-12
Standard
1.4-
1.7
2.3-2.8
5.6-7.9
11.3-15.8
18.1-21.5
50.8-56-5
54.2-78.0
90.4-113.0
124.3-146.9
259.9-282.5
282.5-339.0
418.0-508.4
564.9-790.9
1016.9-
1242.8
Standard
1.4-1.7
3.4-4.5
6.8-9.0
10.7-12.4
20.3-23.7
27.1-31.6
36.2-41.8
54.2-62.1
99.4-114.1
169.5-197.7
248.6-305.1
361.6-474.5
666.6-723.1
Alternate
1.4-2.3
3.4-5.1
6.8-10.2
10.7-14.
1
20.3-25.4
27.1-33.9
36.2-45.2
54.2-67.8
99.4-124.3
169.5-214.7
248.6-339.0
361.6-564.9
666.6-790.9
CESSNA
AIRCRAFT
COMPANY
MODEL
182/Ti
182
MAINTENANCE
MANUAL
4.
Torque
Requirements
for
Electrical Current
Carrying
And
Airframe
Ground
Fasteners
A.
Use
Table
203
to
determine
torque
requirements
for
threaded
electrical
current carrying
fasteners.
(1)
Torque
values
shown
are
clean,
nonlubricated
parts.
Threads
shall
be
free
of
dust
and
metal
filings.
Lubricants,
other
than
on
the
nut
as
purchased,
shall
not
be
used
on
any
bolt
installations
unless
specified
in
the
applicable
chapters
of
this
manual.
(2)
All
threaded
electrical
current
carrying
fasteners
for
relay
terminals, shunt terminals,
fuse
limiter
mount
block terminals
and
bus
bar
attaching
hardware
shall
be
torqued per
Table
203.
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.
B.
Use
Table 204
to
determine
torque
requirements
for
threaded
fasteners
used
as
airframe
electrical
ground
terminals.
Table
203.
Torque
Values
Electrical
Current Carrying
Fasteners
FASTENER
DIAMETER
6-32
8-32
10-32
3/16
1/4
5/16
3/8
11/2
TORQUE VALUE
(INCH-POUNDS)
8-12
13-17
20-30
20-30
40-60
80-100
105-125
130-150
Table
204. Torque
Values
Airframe
Electrical Ground
Terminals
FASTENER
DIAMETER
5/16
3/8
TORQUE
VALUE
(INCH-POUNDS)
130-1
50
160-19go
5.
Torque
Requirements
for Rigid
Tubing
and
Hoses
A.
Use
Table
205 to
determine torque requirements
for
tubes
and
hoses.
20-11-00
©
Cessna
Aircraft
Company
Page
206
Janl1/2007
CESSNA
AIRCRAFT
COMPANY
MODEL
1821T182
MAINTENANCE
MANUAL
Table
205.
Tubing/HoseTorque
Limits
(Inch-Pounds)
Hose
Tubing
Size
O.D.
-2
-3
-4
-5
-6
-8
-10
-12
-16
-20
-24
1
/8
3/16
1/4
5/16
3/8
1/2
5/8
3/4
1
1 1/4
1 1/2
Flared
or
Flareless
fitting
with
Aluminum
or
Annealed
Stainless
Steel
Tubing,
and
Hose
with
Aluminum
Inserts
Min
Max
20
25
50
70
110
230
330
460
500
800
800
30
35
65
90
130
260
360
500
700
900
900
Flared
or Flareless
fitting
with
Steel
Tubing,
and
Hose
with
Steel
Inserts
Min
75
95
135
170
270
450
650
900
1200
1520
1900
Max
85
105
150
200
300
500
700
1000
1400
1680
2100
Q
Cessna
Aircraft
Company
20-11
-00
Page
207
Janl1/2007
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
SAFETYING
-
MAINTENANCE PRACTICES
1.
General
A.
Safety
Wire.
(1)
Inconel
(Uncoated),
Monel
(Uncoated).
(a)
Used
for
general safety
wiring purposes.
Safety
wiring
is
the
application
of
wire
to
prevent
relative
movement
of
structural
or
other critical components
subjected
to
vibration,
tension,
torque,
etc.
Monel
to
be
used
at
temperatures
up
to
700'F
(370
'C)
and
inconel to
be
used
at temperatures
up
to
1500F
(8151C).
Identi
fled
by
the
color
of
the
finish,
monel
and
inconel
color
is
natural
wire color.
(2)
Copper, Cadmium
Plated
and
Dyed
Yellow
in
accordance
with
FED-STD 595.
(a)
This
wire
will
be
used
for shear
and
seal
wiring
applications.
Shear
applications
are
those
where
it
is
necessary
to
purposely
break
or
shear
the
wire
to permit
operation
or
actuation
of
emergency
devices.
Seal
applications
are
those
where
the
wire
is
used
with
a
lead
seal
to
prevent tampering
or
use of
a
device
without indication.
Identified
by
the
color
of the
finish,
copper
wire
is
dyed
yellow.
(3)
Aluminum
Alloy
(Alclad 5056),
Anodized
and Dyed Blue
in
accordance
with
FED-STD
595.
(a)
This
wire
will be
used
exclusively for
safety
wiring
magnesium
parts.
NOTE:
Surface treatments
which
obscure
visual
identification
of
safety
wire
are
prohibited.
(4)
Inconel,
monel,
wire can
be
substituted
for
same
diameter
and
length
of
carbon
steel
or
corrosion
resistant
wire.
(5)
Wires
are
visually
identifiable
by
their
colors:
natural
for inconel
and
monel,
yellow
for
copper,
and
blue
for
aluminum.
B.
Cotter
Pin.
(1)
The
selection
of
material
shall
be
in
accordance
with
temperature, atmosphere
and
service
limitations.
2.
Safety
Wire
A.
Wire
Size.
(1)
The
size
of
the safety
wire
shall
be
in
accordance
with
the
requirements
of
Table
201.
(a)
0.032
inch
diameter safety
wire
is
for
general
purpose
use,
however,
0.020
inch
diameter
safety
wire
may be
used
on
parts having
a
nominal
hole
diameter
of
less than
0.045
inch;
on
parts having
a
nominal
hole
diameter
between
0.045
and
0.062
with
spacing
between
parts
of
less
than two
inches;
or on
closely
spaced screws
and bolts
of
0.25
inch
diameter
and
smaller.
(b)
0.020
inch
diameter
copper
wire
shall
be
used
for
shear
and
seal
wire
applications.
(c)
When
employing
the
single
wire method
of
locking, the
largest
nominal
size
wire
for
the
applicable
material or
part
which the
hole
will
accommodate
shall
be
used.
Table
201.
Safety
Wire
MATERIAL
SIZE
AND
NUMBER
(NASM20995-XXX)
.015
.020
.032
.040
.041
.047
.051
.091
Ni-Cu
Alloy
NC20 NC32
NC40
NC51
NC91
(Monel)
Ni-Cr-Fe
Alloy
N20 N32 N40
N51
N91
(Inconel)
Carbon
Steel
F20 F32
F41
F47
F91
20-12-00
Page
201
©
Cessna
Aircraft
Company
Mar
1/2004
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
Table
201.
Safety
Wire
(continued)
MATERIAL
SIZE
AND
NUMBER
(NASM20995-XXX)
.015
.020
.032 .040
.041
.047
.051
.091
Corrosion
C15
C20
C32
C41
C47
C91
Resistant
Steel
Aluminum Alloy
AB20 AB32
AB41
AB47 AB91
(Blue)
Copper
(Yellow) CY15
CY20
3.
Safety
Wire
Installation
A.
Method
(Refer
to
Figure
201).
CAUTION:
Screws
in
closely
spaced geometric
patterns which secure
hydraulic
or
air
seals,
hold
hydraulic
pressure,
or
used
in
critical
areas
should
use
the
double
twist
method
of
safety
wiring.
(1)
Single
wire method
of
safety
wiring
shall
use the
largest nominal
size
wire
listed
in
Table
201,
which
will
fit
the
hole.
(2)
The
double
twist
method
of
safety
wiring shall
be
used
as
the common
method of
safety
wiring.
It
is
really one
wire
twisted
on
itself
several times. The
single
wire
method
of
safety
wiring
may
be
used
in a
closely
spaced,
closed geometrical
pattern
(triangle,
square,
circle,
etc.),
on
parts
in
electrical
systems,
and
in
places that would
make the
single
wire
method
more
advisable.
Closely
spaced
shall
be
considered
a
maximum
of
two
inches
between
centers.
(3)
Use
single
wire method
for
shear
and
seal wiring
application.
Make sure
the
wire
is
installed
so
that
it
can
be
easily
broken when
required
in
an
emergency
situation.
For
securing
emergency
devices
where
it
is
necessary
to
break
the wire
quickly,
use
copper
only.
(4)
Safety
wiring
by the
double
twist
method
shall
be
done
as
follows:
(a)
One
end
of
the
safety
wire
shall
be
inserted
through one
set
of
safety
wire
holes
in
the
bolt
head.
The
other
end
of
the safety
wire shall
preferably
be
looped
firmly around the
head
to the
next
set
of
safety
wire
holes
in
the same
unit
and
inserted through
this
set
of
safety
wire
holes.
The
"other
end"
may go
over
the head
when
the clearances
around the
head
are
obstructed by
adjacent
parts.
(b)
The
strands,
while
taut,
shall
be
twisted
until
the
twisted
part
is
just
short
of
the
nearest
safety
wire hole
in
the
next
unit.
The twisted
portion
shall
be
within
1/8
inch
of
the
holes
in
each
unit.
The actual number
of
twists
will
depend
upon
the wire
diameter,
with smaller
diameters
being
able
to
have
more
twists
than
larger
diameters. The
twisting shall
keep
the
wire
taut
without over stressing or
allowing
it
to
become
nicked,
kinked
or
mutilated.
Abrasions
from
commercially
available twist
pliers
shall
be
acceptable.
(c)
The wire shall
be
twisted
to form
a
pigtail
of
3
to
5
twists
after
wiring the last
unit.
The
excess
wire
shall
be
cut
off.
The
pigtail
shall
be
bent
toward
the
part
to
prevent
it
from
becoming
a
snag.
Safety
wiring multiple groups
by
the
double
twist
double
hole
method
shall
be
the
same
as
the
previous
double twist single
hole
method
except
the
twist
direction
between
subsequent
fasteners
may
be
clockwise or counterclockwise.
B.
Spacing.
(1)
When
safety
wiring
widely
spaced multiple
groups
by
the double
twist
method,
three
units shall
be
the
maximum
number
in
a
series.
(2)
When
safety
wiring
closely
spaced multiple
groups, the number
of
units
that
can
be
safety
wired
by
a
twenty four
inch
length
of
wire
shall
be
the
maximum
number
in
a
series.
(3)
Widely
spaced
multiple groups
shall
mean
those
in
which
the
fastenings
are
from
four
to
six
inches apart. Safety wiring
shall
not be
used
to
secure
fasteners
or
fittings
which are
spaced
more
than
six
inches apart, unless
tie points
are
provided
on
adjacent
parts
to
shorten
the
span
of
the
safety
wire
to
less
than
six
inches.
20-12-00
Page
202
©
Cessna Aircraft Company
Mar
1/2004
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
!OLT
A
STEP
1.
INSERT
WIRE
THROUGH BOLT
A
AND
Mrklr% A
rD
i *kirK -t
- /-
r
.
kl1Thr
SI(C
A
MV/
DtINU
MnUUINU
DULI
1ir
NICUCOOMI-iT,
BEND
WIRE
ACROSS
BOLT HEAD).
TWIST
WIRES
CLOCKWISE
UNTIL
THEY
REACH
BOLT
B.
FEP
2.
INSERT
ONE
END
OF
WIRE
THROUGH
BOLT
B.
BEND
OTHER
END
AROUND
BOLT
(IF
NECESSARY, BEND WIRE
ACROSS
HEAD
OF
BOLT).
TWIST
WIRES COUNTERCLOCKWISE
1/2
INCH
OR SIX
TWISTS.
CLIP ENDS.
BEND
PIGTAIL
BACK
AGAINST
PART.
3TE:
RIGHT
THREADED
PARTS
SHOWN:
REVERSE
DIRECTIONS
FOR
LEFT
PARTS.
DOUBLE-WIRE
SAFETYING
-COUNTER-
CLOCKWISE
MULTIPLE FASTENER
APPLICATION
DOUBLE
TWIST- MULTIPLE
HOLE
METHOD.
DOUBLE-TWIST
SAFETYING
SINGLE
HOLE METHOD
Lockwire Safetying
Figure
201
(Sheet
1)
20-12-00
©
Cessna
Aircraft
Company
1
T
l
5598T2001
5599T2001
6598T1029
Page
203
Mar
1/2004
U-VLL
I
L
-
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
EXTERNAL
SNAP
RING
SINGLE-WIRE
METHOD
BOLTS
IN
CLOSELY
SPACED, CLOSED
GEOMETRICAL
PATTERN,
SINGLE
WIRE
METHOD
SINGLE
FASTENER
APPLICATION
DOUBLE-TWIST
METHOD
SMALL SCREWS
IN
CLOSELY
SPACED,
CLOSED
GEOMETRICAL
PATTERN,
SINGLE
WIRE
METHOD
NOTE:
RIGHT THREADED
PARTS
SHOWN. REVERSE
DIRECTION
FOR
LEFT
THREADS
Lockwire
Safetying
Figure
201
(Sheet
2)
20-12-00
©
Cessna
Aircraft Company
5598T1003
5598T1024
5598T1024
5598T1024
Page
204
Mar
1/2004
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
B1105
hllllllllllll
1111111111111
II1illlllllll
AN500A
5598T1001
5598T1001
Lockwire
Safetying
Figure
201
(Sheet
3)
©
Cessna Aircraft
Company
20-12-00
Page 205
Mar
1/2004
CESSNA
AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
C.
Tension.
(1)
Parts
shall
be
safety
wired
in
such
a
manner that
the
safety
wire
shall
be
put
in
tension
when
the
part
tends
to
loosen. The
safety
wire
should
always
be
installed
and
twisted
so
that
the
loop
around
the
head
stays
down and
does
not
tend
to
come
up
over
the
bolt head
and
leave
a
slack
loop.
NOTE:
The
safety
wire
on
a
castellaed
nut
can
be more
secure
if it is
on
the
side
of
the
stud
when
the slot
is
close
to
the
top
of
the
nut.
(2)
Care
shall
be
exercised
when
installing
safety
wire to
ensure
that
it is
tight
but
not
over
stressed.
D.
Usage.
(1)
A
pigtail
of
0.25 to
0.50
inch
(3
to
5
twists)
shall
be made
at
the end
of
the
wiring.
This
pigtail
shall
be
bent
back
or
under
to
prevent
it
from
becoming
a
snag.
(2)
Safety wire
shall
be
new upon
each
application.
(3)
When
castellated
nuts
are
to
be
secured
with
safety
wire,
tighten the
nut
to
the
low
side
of
the
selected
torque
range,
unless otherwise specified,
and
if
necessary,
continue
tightening
until
a
slot
aligns
with
the hole.
(4)
In
blind
tapped
hole
applications
of
bolts
or
castellated
nuts
on
studs,
the
safety
wiring shall
be
as
described
in
these
instructions.
(5)
Hollow
head
bolts
are
safetied
in
the
manner
prescribed for regular
bolts.
(6)
Drain
plugs
and
cocks
may
be
safetied
to
a
bolt,
nut
or
other
part having
a
free
lock
hole
in
accordance
with
the
instructions described
in
this
text.
(7)
External
snap
rings
may
be
locked,
if
necessary,
in
accordance
with
the
general
locking
principles
as
described
and
illustrated.
Internal
snap
rings
shall
not
be
safety
wired.
(8)
When
safety
wiring
is
required
on
electrical connectors
which
use
threaded
coupling
rings,
or
on
plugs
which employ
screws
or
rings to
fasten
the
individual
parts of
the
plug
together,
they
shall
be
safety
wired with
0.020
inch
diameter
wire
in
accordance
with
the
safety
wiring
principles
as
described
and
illustrated.
It is
preferable
to
safety
wire
all
electrical connectors
individually.
Do
not
safety
wire
one
connector
to
another
unless
it
is
necessary
to do
so.
(9)
Drilled
head
bolts
and
screws
need
not
be
safety
wired
if
installed
into
self-locking
nuts
or
installed
with lock
washers. Castellated
nuts
with
cotter
pins
or
safety
wire
are preferred
on
bolts
or
studs
with drilled
shanks
but
self-locking
nuts
are
permissible
within
the
limitations
of
MS33588.
(10)
Larger
assemblies, such
as
hydraulic
cylinder
heads
for
which
safety
wiring
is
required
but
not
specified,
shall
be
safety
wired
as
described
in
these instructions.
(11)
Safety
wire
shall
not
be
used
to
secure
nor
shall safety
wire
be
dependent
upon
fracture
as
the
basis for
operation
of
emergency
devices
such
as
handles,
switches,
guards covering
handles,
etc.,
that
operate emergency mechanism
such
as
emergency
exits,
fire
extinguishers,
emergency cabin pressure
release,
emergency landing
gear
release
and
the
like.
However,
where
existing
structural equipment
or
safety
of
flight
emergency
devices
require
shear
wire
to
secure equipment while
not
in
use, but
which
are
dependent
upon
shearing
or
breaking
of the
safety
wire
for successful
emergency
operation
of
equipment,
particular
care
shall
be
exercised
to
that
wiring under
these
circumstances
shall
not
prevent emergency operations
of
these
devices.
4.
Cotter
Pin
Installation
A.
General
instruction for
the
selection
and
application
of
cotter
pins
(Refer
to
Figure 202).
(1)
Select
cotter
pin
material
in
accordance
with
temperature,
atmosphere
and
service
limitations.
(2)
Cotter pins
shall
be new
upon
each
application.
(3)
When nuts
are
to
be
secured to
the
fastener
with
cotter
pins,
tighten
the
nut
to
the
low
side
(minimum)
of
the
applicable
specified
or
selected torque
range,
unless
otherwise specified,
and
if
necessary, continue tightening
until
the slot aligns
with
the
hole.
In
no
case
shall
the
high
side
(maximum)
torque
range
be
exceeded.
(4)
Castellated
nuts
mounted
on
bolts
may
be
safetied
with
cotter
pins
or
safety
wire.
The preferred
method
is with
the
cotter
pin.
An
alternate
method
where
the
cotter
pin
is
mounted
normal
to
the
axis
of the
bolt
may
be
used
where
the
cotter
pin
in
the
preferred method
is
apt
to
become
a
snag.
20-12-00
Page
206
©
Cessna Aircraft Company
Mar
1/2004
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
B1106
TO
PROVIDE
CLEARANCE
PRONG
MAY
BE
CUT
HERE
CASTELLATED
NUT ON
BOLT
PREFERRED
METHOD
CASTELLATED
NUT
ON
BOLT
ALTERNATE
METHOD
TANGENT
TO
PIN
MAXIMUM
COTTER
PIN
LENGTH
MINIMUM
COTTER
PIN
LENGTH
THREAD
SIZE
6
8
10
1/4
5/16
3/8
7/16
1/2
9/16
5/8
3/4
7/8
1
1
1/8
1 1/4
1
3/8
1
1/2
PIN
APPLICATION
Cotter
Pin
Safetying
Figure
202
(Sheet
1)
©
Cessna Aircraft
Company
20-12-00
Page
207
Mar
1/2004
MINIMUM
PIN
SIZE
(INCH)
0.028
0.044
0.044
0.044
0.044
0.072
0.072
0.072
0.086
0.086
0.086
0.086
0.086
0.116
0.116
0.116
0.116
5598T1025
5598T1025
5598T1025
5598T1025
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
(5) In
the event
of
more
than
50
percent
of
the
cotter
pin
diameter
is
above the
nut
castellation,
a
washer
should
be
used
under
the
nut or
a
shorter
fastener
should
be
used.
A
maximum
of
two
washers
may
be
permitted
under
a
nut.
(6)
The largest
nominal
diameter
cotter
pin
listed
in
MS24665,
which
the
hole and
slots will
accommodate,
shall
be
used;
but
in
no
application
to
a
nut,
bolt or
screw
shall
the
pin
size
be
less than
the
sizes
described
in
Figure
202.
(7)
Install
the
cotter
pin
with the
head
firmly
in
the
slot
of
the nut
with
the
axis
of
the
eye
at
right
angles
to
the
bolt
shank,
and
bend
prongs so that the
head and
upper
prong
are
firmly seated
against
the
bolt.
(8) In
the
pin
applications,
install
the
cotter
pin
with
the
axis
of
the
eye
parallel
to
the shank
of
the
clevis
pin
or
rod
end.
Bend
the
prongs
around
the
shank
of
the
pin
or
rod
end.
(9)
Cadmium plated
cotter
pins
shall
not
be
used
in
applications
bringing
them
in
contact
with
fuel,
hydraulic
fluid
or synthetic
lubricants.
5.
Safetying
Turnbuckles
A.
Use
of
Locking
Clips
(Refer
to
Figure 203).
(1)
Prior
to
safetying,
both
threaded
terminals
should
be
screwed
an
equal
distance
into
the
turnbuckle
barrel,
and
should
be
screwed
in,
at
a
minimum,
so
no
more
than
three threads
of
any terminal
are
exposed outside
the body.
(2)
After
the turnbuckle
has
been
adjusted
to
its
locking position, with the groove
on
terminals
and
slot indicator
notch
on
barrel aligned,
insert
the
end
of the
locking
clip
into
the
terminal
and
barrel
until
the
"U"
curved end
of
the locking
clip
is
over
the
hole
in
the
center
of
the
barrel.
(a)
Press
the
locking clip
into
the
hole
to
its
full
extent.
(b)
The curved
end
of
the
locking
clip
will
latch
in
the
hole
in
the
barrel.
(c)
To
check
proper
seating
of
locking clip, attempt
to
remove
pressed
"U"
end
from barrel
hole
with
fingers
only.
NOTE:
Do
not use
a
tool
as
the
locking
clip
could
be
distorted.
(3)
Locking
clips
are
for
one time
use
only
and
should
not
be
reused.
(4) Both
locking
clips
may
be
inserted
in
the same
hole of
the
turnbuckle
barrel
or
in
opposite
holes
of
the
turnbuckle
barrel.
B.
Use
of
Safety
Wire
(Refer
to
Figure
204).
(1)
Some
turnbuckles
use
safety
wire.
For more
information,
refer
to
Federal
Publication
AC
43-
13.1B,
Safety
Methods
For
Turnbuckles.
20-12-00
Page
208
©
Cessna
Aircraft
Company
Mar
1/2004
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
B1107
(NOTE)
BARREL
CABLE
TERMINAL
I I -./
(NOTE)
NOTE: PULL WITH
YOUR FINGERS
FOR
AN
INSPECTION
TO
MAKE
SURE
THE
CLIP
WILL
NOT
COME
OUT.
STRAIGHT
END
HOOK
SHOULDER
END
LOOP
HOOK
LIP
HOOK
LOOP
SAFETY
CLIP
INSTALLATION
SAFETY CLIP
INSTALLATION
0798T1005
0798T1003
0798T1004
Safetying
Turnbuckle Assemblies
with
Safety
Clips
Figure
203
(Sheet
1)
20-12-00
©
Cessna Aircraft
Company
Page
209
Mar
1/2004
B
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
Bto108
LOCKING
CLIP
TURNBUCKLE
MS21256
CLEVIS
0 I
I
TURNBUCKLE
BARREL
MS21251
TURNBUCKLE
EYE
][
TYPICAL
TURNBUCKLE ASSEMBLY
LOCKING
CLIP
MS21256
L1n I \ \ \
'
\
'\
X
"
\ \ \ \
I
'A
\
'
['
' '
\
-
EID
SWAGED
TERMINAL
METHOD
OF
ASSEMBLING
LOCKING CLIPS,
TURNBUCKLE
BARREL
AND
TERMINAL
LOCKING
CLIP
MS21256
(NOTE)
-1
-2
-1
-2
-1
-2
TURNBUCKLE
BODY
MS21251
-2S
-3S
-3L
-4S
-4L
-5S
-5L
-6S
-1
-2
-3
-6L
-7L
-8L
-9L
-10L
NOTE:
TWO
LOCKING
CLIPS REQUIRED
FOR
EACH
TURNBUCKLE.
Safetying
Turnbuckle
Assemblies
with
Safety
Clips
Figure
203
(Sheet
2)
5598T1023
5598T1023
20-12-00
©
Cessna
Aircraft
Company
CARI
F
THIMBLE
NOMINAL
CABLE
DIA
1/16
3/32
THREAD
UNF-3
No.
6-40
No.
10-32
1/8
5/32
1/4-28
3/16
7/32
1/4
9/32
5/16
5/16-24
3/8-24
7/16-20
1/2-20
Page
210
Mar
1/2004
I
CESSNA AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
B2495
SINGLE WRAP SPIRAL
EYEBOLT
NOTE:
IF
THERE
IS
NO
SAFETY
WIRE
HOLE
TO
USE,
PUT
THE
SAFETY WIRE
AROUND
THE
CIRCUMFERENCE
OF
THE
EYEBOLT
A0714R1047
Safetying
Turnbuckle
Assemblies
with
Lockwire
Figure
204
(Sheet
1)
©
Cessna
Aircraft
Company
20-12-00
Page
211
Mar
1/2004
ED
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
CONTROL CABLE
WIRE
BREAKAGE
AND CORROSION
LIMITATIONS
-
MAINTENANCE
PRACTICES
1.
Examination
of
Control
Cables
A.
Control
cable assemblies
are
subject
to
a
variety
of
environmental conditions
and
forms
of
deterioration.
Some
deterioration,
such
as
wire
or
strand
breakage,
is
easy to
recognize.
Other
deterioration,
such
as
internal
corrosion
or
cable
distortion,
is
harder
to
identify.
The
following
information
will
aid
in
detecting
these
cable
conditions.
B.
Broken
Wire
Examination
(Refer
to
Figure
201).
(1)
Examine
cables
for
broken
wires
by
passing
a
cloth
along
length
of
cable.
This
will
detect
broken
wires,
if
cloth
snags
on
cable.
Critical
areas
for
wire
breakage
are those
sections
of
cable
which
pass through
fairleads,
across
rub
blocks,
and
around
pulleys.
If
no
snags
are
found, then
no
further inspection
is
required.
If
snags
are
found
or
broken
wires
are
suspected,
then
a
more
detailed inspection
is
necessary,
which
requires
that
the
cable
be
bent
in a
loop
to
confirm
broken
wires.
Loosen
or
remove
cable
to
allow
it
to
be
bent
in a
loop
as
shown.
While rotating
cable,
inspect
bent
area
for
broken wires.
(2)
Wire breakage criteria
for cables
in
flap, aileron,
rudder,
and
elevator
systems
are as
follows:
(a)
Individual
broken
wires at
random
locations
are
acceptable
in
primary
and
secondary
control
cables
when
there
are
no
more
than
six
broken
wires
in
any
given
ten-inch
cable
length.
C.
Corrosion.
(1)
Carefully examine any cable for
corrosion that
has
a
broken wire
in a
section
not
in
contact
with
wear-producing
airframe
components,
such as
pulleys,
fairleads,
rub
blocks,
etc.
It
may
be
necessary
to
remove
and bend
cable
to
properly
inspect
it
for
internal
strand
corrosion,
as
this
condition
is
usually
not
evident
on
outer
surface
of
cable. Replace
cable
if
internal
corrosion
is
found.
If
a
cable
has
been
wiped
clean
of
its
corrosion-preventive
lubricant
and
metal-brightened,
the
cable
shall
be
examined
closely
for corrosion.
For
description
of control
cable
corrosion,
refer
to
Chapter
51,
Corrosion
and
Corrosion Control
-
Maintenance
Practices.
20-13-00
Page
201
©
Cessna
Aircraft
Company
Mar
1/2004
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
B1109
BROKEN
WIRE UNDETECTED
BY
WIPING
CLOTH
ALONG
CABLE
a
=-5=5
~
~
BROKEN WIRE
DETECTED
VISUALLY
WHEN
AND
BE
DO
NOT
BEND
INTO
LOOP
SMALLER
THAN
50 CABLE DIAMETERS
NORMAL TECHNIQUE
FOR
BENDING
CABLE
AND
CHECKING
FOR
BROKEN
WIRES
5561T1119
Cable
Broken
Wire Examination
Figure
201
(Sheet
1)
20-13-00
©
Cessna
Aircraft
Company
Page
202
Mar
1/2004
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
SOLVENTS,
SEALANTS,
AND ADHESIVES
-
DESCRIPTION
AND
OPERATION
1.
General
A.
Solvents,
sealants
and
adhesives
are
composed
of
a
group
of
chemicals
that
often
prove
toxic.
Anyone engaged
in
maintenance,
repair
and
operation
of
airplane
and
airplane
accessories
may
be
exposed
to
these
chemicals.
B.
To
help
avoid
the
effects
of
these
toxic
substances,
work
only
in a
clean,
well-lighted
and
well-ventilated
area.
Rubber
gloves
and
protective
clothing should
be worn.
Avoid breathing
spray
vapors as
they
are
highly
toxic.
C.
When
working
with
toxic
substances,
always
be
alert
for symptoms of
poisoning.
If
symptoms
are
observed,
immediate
removal
of
the
victim
from the
contaminated
area
is
most
important.
2.
Description
A.
For
clarification,
the
description
of
solvents,
sealants
and
adhesives
are
presented
in
individual
paragraphs.
(1)
Solvents.
(a)
Solvents
are
composed
of
chemicals
which
are
capable
of
dissolving other
materials
and
are
primarily
used as
a
cleaning
agent.
Solvent
cleaning
should
be
used
when
it
is
not
practical
to
clean
parts
by
vapor
degreasing
or
immersion
in
chemical
cleaners.
(2)
Sealants.
(a)
Sealants
are
composed
of
chemical
compounds
which
are
primarily
used
as
a
seal
against
the
passage of
air
and
liquids. Classification
of
sealants
are
categorized
by
type
according
to
their
application.
(3)
Adhesives.
(a)
Adhesives
are
composed
of
a
mixture
of
chemicals which
make an
adherent
that
is
primarily
used
for bonding
like
or
unlike
materials,
and
are
classified according
to
their
application.
20-30-00
Page
1
©
Cessna
Aircraft
Company
April 1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
ACCEPTABLE REPLACEMENTS
FOR
CHEMICALS
AND
SOLVENTS
-
DESCRIPTION AND
OPERATION
1.
General
A.
In
response
to
the
Aerospace
National Emissions
Standards
for
Hazardous
Air
Pollutants
(NESHAP),
this
data
is
being
issued
to inform
customers
of
acceptable
replacements
for
chemicals
and
solvents
in
the
Maintenance
Manual
that
have
been
restricted
or
prohibited
by
the
standards.
B.
For
complete
details
of
the regulatory
standards,
refer
to
Federal
Register,
40
CFR
Part
63
(AD-FRL-
5636-1),
RIN
2060-AG65.
C.
Compliance
with
the
standard
is
mandatory by
September
1,
1998.
2.
Hand-Wipe Cleaning
Operations
NOTE:
All
hazardous
air
pollutants
(HAP) or
volatile
organic
compounds
(VOC)
hand-wipe
cleaning
solvents
must
meet
a
composition
requirement, have
a
vapor
pressure
less
than
or
equal
to 45
MM
Hg
at
209C,
or
meet
the
requirements
specified
in
an
alternative
compliance
plan
administered
by
the
permitting
authority
and
approved
under Section
112
(1)
of
the
Clean
Air
Act.
Table
1.
Replacement
Products
for
Hand-Wipe Cleaning
Operations
All
Plastics
(Except
Windows
and
Windshields)
All
Rubber
(Natural
or
Synthetic)
and
Silicone
APPROVED
PRODUCT/NUMBER
Methyl
n-propyl
ketone
(CAS
No.
107-87-9)
Desoclean
110
(020K19)
DS108
Isopropyl
Alcohol
(TT-I-735)
Isopropyl
Alcohol
SUPPLIER
ADDRESS
Eastman
Chemical
Products
Wilcox
Dr.
and
Lincoln
St
Kingsport,
TN
Courtaulds Aerospace
Glendale,
CA
91203
Dynamold
Solvents,
Incorporated
2905
Shamrock
Ave
Fort
Worth,
TX 76107
Available
Commercially
Available
Commercially
3.
Priming Operations
NOTE:
Priming
operations
may
not
exceed
a
maximum
Hazardous Air Pollutant
(HAP)
limit
of
2.9
lb./Gallon
(350
Grams/Liter)
(less
water) per
application.
Priming
operations
may not
exceed
a
volatile organic
compounds
(VOC) limit of 2.9
lb./Gallon
(350
Grams/Liter)
(less
water
and
exempt
solvents)
per
application.
Compliance
of
this
limit
may
be
achieved through
the
use
of
coatings
which
fall
below
content
limits, or
by
using
monthly
volume-weighted averaging
to
meet
content
limits.
20-31-00
Page
1
©
Cessna
Aircraft
Company
Mar
1/2004
SURFACE
All
Metals
and
Painted
Surfaces
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
Table
2.
Replacement
Products
for
Priming
Operations
PRIMER
APPLICATION
Corrosion
Primer
(Notes
1,4)
APPROVED
PRODUCT/NUMBER
Corrosion
Primer
(513
X
419)(910
X
942)
Corrosion
Primer
(02-Y-40)(02-4-40
CATA)
Corrosion
Primer
(U-1201
F/U-1202F)
Corrosion
Primer
R4001-K14
MAX
COR
Fuel
Bay
Primer
(Notes
2,
4)
Pretreatment
Primer
(Notes
3,
4)
Fuel
Bay
Primer
(10P30-5)
Pretreatment
Primer
(728-
013/702-701)
SUPPLIER
ADDRESS
Courtaulds
Aerospace
1608 Fourth
St.
Berkeley,
CA
94710
DEFT,
Inc.
17451
Von
Karman
Ave.
Irvine,
CA
92714
Sterling
Lacquer
Mfg.
3150
Brannon Ave.
St.
Louis,
MO
63139
U.S.
Paint Corp.
831
S.
21st
St.
St.
Louis,
MO
63103
Dexter
Crown
Metro
Aerospace
East
Water
St.
Waukegan,
IL
60085
Pratt
&
Lambert
Industrial Coatings
630
E.
13th
St.
Andover,
KS
67002
NOTE
1:
Primers
with
MIL-PRF-23377G
or later
requirements
can
be
used.
NOTE
2:
This primer
is
restricted
to
the
fuel
bay
area.
NOTE
3:
Any
pretreatment
primers
which
meet
DOD-P-15328
may
be
used.
NOTE
4:
Specific application
techniques
must
be
used.
If
alternative
is
sought,
it
can
only
be
used
if
emissions
are
less
than or
equal
to
HVLP or
electrostatic
spray
application techniques.
All
application
equipment
must
be
operated
according
to
manufacturer's
specifications,
company procedures,
or
locally specified operating
procedures.
4.
Topcoat
Operations
NOTE:
Topcoat
operations
may
not
exceed
a
maximum
Hazardous
Air Pollutant
(HAP)
limit
of
3.5
Ib./Gallon
(420
Grams/Liter)
(less
water)
per
application.
Topcoat
operations
may
not
exceed
a
volatile
organic
compounds
(VOC)
limit
of
3.5
Ib./Gallon
(420
Grams/Liter)
(less
water
and
exempt
solvents)
per
application.
Compliance
of
this
limit may be
achieved through
the
use
of
coatings
which
fall
below
content
limits,
or
by
using
monthly
volume-weighted averaging
to meet
content
limits.
Topcoats which
meet
the
requirements
of
MIL-C-85285 may
also
be
used.
20-31-00
Page
2
©
Cessna Aircraft Company
Mar
1/2004
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
Table
3.
Replacement
Products
for
Topcoat
Painting Operations
TOPCOAT
APPLICATION APPROVED
PRODUCT/NUMBER
Basecoat
830 Series
High
Solids
Acry
Glo
(Note
4)
Low
VOC
Enamel
24-F
20
Series
Paint
Stripes
(Note
4)
Low VOC
Acrylic
830
Series
SUPPLIER ADDRESS
Pratt
&
Lambert
Sterling
Lacquer
Mfg.
Dexter
Crown
Metro
Aerospace
Pratt
&
Lambert
5.
Paint
Stripping
Operations
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.
Table
4.
Replacement
Products
for
Paint
Stripping Operations
APPLICATION
Chemical
Stripping
Mechanical
Stripping
(Note
5)
APPROVED
PRODUCT/NUMBER
Turco
T-6776
LO
180
Grit
or
finer
SUPPLIER ADDRESS
Turco
Products,
Inc.
Westminster,
CA
92684
Available
Commercially
NOTE
5:
Mechanical
and
hand-
sanding
operations
are
exempt
from
these
requirements.
20-31-00
Page
3
©
Cessna
Aircraft
Company
Mar
1/2004
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
GENERAL
SOLVENTS/CLEANERS
-
MAINTENANCE
PRACTICES
1.
General
A.
Solvents
are
used
in
a
wide
range
of
cleaning
activities.
Selected
solvents,
which
are
used to
remove
oil,
grease,
and dirt
from objects,
cause
no
damage
to
metal,
plastics,
or
elastomeric
parts.
2.
Tools, Equipment
and
Materials
NOTE:
Equivalent substitutes
may
be
used
for
the following
items.
NAME
NUMBER
MANUFACTURER
USE
Detergent
Commercially
available
General
cleaning.
ScotchBrite
Pads
Type
A
Minnesota
Mining
and
Mfg. Co.
Light
abrasion
of
metal
3M
Center surfaces.
St. Paul,
MN
55101
Sandpaper
320 Grit
Commercially
available
Light
abrasion
of
metal
surfaces.
Rymple
Cloth
Commercially
available
Wiping
and
applying
cleaning
agents.
Wiping
cloth
white,
Commercially
available
Wiping
and
applying
oil
free,
absorbent cleaning
agents.
3.
Safety
Precautions
A.
Solvents
are
composed
of
a
group
of chemicals
that
often
proves
toxic.
Anyone
engaged
in
maintenance,
repair
and
operation
of
airplane
and
airplane
accessories
may
be
exposed
to
these
chemicals.
B.
To
help
avoid the
effects
of
these
toxic
substances,
work
only
in
a
clean,
well-lighted,
and
well-
ventilated
area. Rubber
gloves
and
protective clothing
must
be
worn.
Avoid
breathing
spray
vapors
as
they
are
highly toxic.
C.
When
working
with
toxic
substances,
always
be
alert
for symptoms of
poisoning.
If
symptoms
are
observed,
immediate
removal of
the
victim
from
the
contaminated
area
is
most
important.
4.
Description
A.
Solvents
exhibit
a
selective
solvent
action
which permits
its
use
in
the
removal
of
oil,
grease
or dirt.
For
selection
of
proper
solvent,
refer
to
Table
201.
For
the
cleaning
of
metal,
plastics
or
rubber,
proceed
as
follows:
(1)
Metal.
NOTE:
Prior
to
bonding
or
priming,
lightly
abrade
surface
with
either
a
ScotchBrite
pad
or
sandpaper
prior
to
cleaning.
(a)
Wipe
off
all
excess
oil,
grease
or
dirt
from
surface.
(b)
Apply
solvent
to
a
clean
cloth
by
pouring
solvent
on
the
cloth
from
a
safety
can
or
other
approved container.
The
cloth should
be
well
saturated
but not
to
the
point
of
dripping.
(c)
Wipe
the
surface
with
the moistened cloth
as
required
to
dissolve or
loosen
soil.
Work
on
small enough area so
the
surface
being
cleaned
remains
wet.
(d)
With
a
clean dry cloth,
immediately wipe
the
surface while
the
solvent
is
still
wet.
Do
not
allow
the
surface
to
evaporate
dry.
(e)
Repeat
steps
(b)
through
(d)
until
there
is
no
discoloration
on
the
drying
cloth.
20-31-00
Page
201
©
Cessna
Aircraft
Company
Mar 1/2005
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
(2)
Plastic
or
Rubber.
NOTE:
If
cleaning
a
bonding surface, lightly
abrade the
bonding surface
with
sandpaper
prior
to
cleaning.
(a)
Remove
heavy
soil from
surface
by
washing
with
a
water
detergent solution.
(b)
Apply
solvent
to
a
clean
cloth
by pouring
solvent
onto
cloth
from
a
safety
can
or
other
approved container.
The
cloth
should
be
well
saturated
but not
to the
point
where
dripping.
(c)
Wipe
the
surface
with
the moistened cloth as required
to
dissolve
or
loosen soil.
Work
on
a
small
enough area so
that
the surface
being
clean
remains
wet.
(d)
Using
a
clean
dry
cloth, immediately
wipe the
surface
while the
surface
is
still
wet.
Do
not
allow the
surface
to
evaporate
dry.
(e)
Repeat
steps
(b)
through
(d)
until
there
is
no
discoloration
on
the drying
cloth.
Table
201.
General
Solvents
FED-
ERAL
SPECIFI-
CATION
TYPE
CLASSIFI-
CATION
MIL-
Type
I
-100F
PRF-680
Type
II
-140'F
1,1,1
O-T-620
Type
I
-
Inhibited
Regular Type
Technical
II -
with
Trichloroethane dauber
Type
III
-
Aerosol
USE/
DESCRIPTION
FUNCTION
General
cleaning solvent.
Dry
cleaning
of
textile
materials.
Grease
removal.
Spot removing from
fabrics.
General
cleaning
solvent.
Cleaning
of
assembled
equipment.
CAUTION/
WARNING
FLAMMABLE.
USE
WITH ADEQUATE
VENTILATION.
AVOID
PROLONGED
BREATHING
OF
VAPOR.
AVOID
PROLONGED
CONTACT
WITH
SKIN.
Turco
Seal
Solvent
Turco
Products
Penwalt
2331
Carbon
Removing
Compound
Cleaning
Compound
Cleaning/Degreasing
metal parts.
Preparing
metal
plate
for
painting.
P-C-
111A
Use
in
soak
tank
to
facilitate
removal
of
carbon,
gum,
oil
and
other
surface
contaminants
except
rust
or
corrosion
from
engine
and
other
metal parts.
Heavy duty
electro
cleaner
used
for
removal
of
soils
from
ferrous
metal
surfaces
prior
to
electroplating or
other
treatments.
P-
C-535
©
Cessna
Aircraft
Company
ACID
ACTIVATED
SOLVENT,
DO
NOT
USE
ON
PLASTICS.
REMOVES
PAINT.
AVOID
CONTACT WITH SKIN.
20-31-00
CLEANER/
SOLVENT
Dry
Page
202
Mar 1/2005
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
Table 201.
General
Solvents
(continued)
CLEANER/
SOLVENT
Cleaning
Compound,
Unfinished
Aluminum
Trichloroethy-
lene
Polish,
Metal
Aluminum
Naphtha,
Aliphatic
Methyl
Propyl
Ketone
Isopropyl
Alcohol
FED-
ERAL
SPECIFI-
CATION
TYPE
CLASSIFI-
CATION
MIL-C- Type
I -
5410
Viscous
Emulsion
Type
II -
Clear
Liquid
O-T-
634B
Type
I -
Regular
Type
II -
Vapor
Degreasing
MIL-P-
Type
I
-Liquid
6888C
Type
II
Paste
TT-N-
958
Type
I
Type
II
TT-1-735
Grade
B
-0.4%
water
USE/
DESCRIPTION
FUNCTION
Used
full
strength
for
overhaul
of
unfinished
aluminum
surfaces.
Use
full
strength
or
diluted
with
mineral
spirits
and
water
for
maintenance
of
airplane
unfinished
aluminum
surfaces.
Cleaning
of metal
parts.
Degreasing
of
metal
parts.
Special purpose
solvent.
Metal
polish
for
use
on
airplane
aluminum
surfaces.
For
use
with
organic
coatings only. Cleaner
for
acrylic
plastics
and
may
be
used
in
place
of
Type
I
General
cleaning
agent.
Paint
and
adhesive
thinner,
cleaning
agent.
For
use
with
organic
coatings
and
as
an
anti-icing fluid.
General
Solvent for synthetic
rubbers.
CAUTION/
WARNING
REMOVES
PAINT
AND
DAMAGES
PLASTICS.
USE
ONLY
WITH ADEQUATE
VENTILATION. HIGH
CONCENTRATIONS
OF
VAPOR
ARE
ANESTHETIC
AND
DANGEROUS TO
LIFE.
VERY
TOXIC.
FLAMMABLE.
FLAMMABLE.
VAPOR
HARMFUL.
AVOID
PROLONGED
OR
REPEATED
BREATHING
OR CONTACT
WITH
SKIN.
FLAMMABLE.
DO
NOT
USE
WITH
ACRYLIC
PLASTICS.
20-31-00
©
Cessna
Aircraft
Company
Page
203
Mar
1/2005
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
Table
201.
General
Solvents (continued)
CLEANER/
SOLVENT
Wax,
Airplane,
Waterproof
Solvent Type
Cleaning
Compound,
Aluminum
Toluene
FED-
ERAL
SPECIFI-
CATION
MIL- W-
18723C
TYPE
CLASSIFI-
CATION
USE/
DESCRIPTION
FUNCTION
A
waterproof
wax
that
can
be
dissolved or dispersed
with
an
organic
solvent.
MIL-C-
Type
I -
Vis-
5410B
cous
Emul-
sionType
II -
Clear
Liquid
A-A-
59107
Use
full
strength
for
maintenance
of
unfinished
aluminum
surfaces.
Use
full
strength
or
diluted
with
mineral
spirits
and
water for maintenance
of
unfinished
aluminum
surfaces.
Use
as
a
solvent
or
thinner
for
organic
layers,
various
resins,
and
chlorinated
rubber.
Also
used
to
dilute cellulose lacquers
and
dopes.
CAUTION/
WARNING
DO
NOT
USE
SOLVENTS
THAT
MAY
DAMAGE
PAINT
OR
FINISH
FOR
REMOVAL
OF
WAX.
RUBBER
OR
SYNTHETIC
RUBBER
GLOVES
AND
EYE
PROTECTION
SHOULD
BE
USED
WHEN
HANDLING
THE
COMPOUND.
WASH FROM
SKIN
IMMEDIATELY
WITH
WATER
OR
A
SOLUTION
OF
SODIUM
BICARBONATE
AND
APPLY GLYCERIN
OR
PETROLEUM
JELLY.
WASH
FROM EYES
AS
PER
MANUFACTURER'S
INSTRUCTIONS
AND
REPORT
TO
NEAREST
MEDICAL
FACILITY.
FLAMMABLE
VAPOR.
VAPOR
HARMFUL.
20-31-00
©
Cessna Aircraft
Company
Page
204
Mar 1/2005
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
INTERIOR
AND
EXTERIOR
FINISH
-
CLEANING/PAINTING
1.
General
A.
Interior
and
exterior
finish
cleaning/painting consists
of
general
information
and
instructions
for
applying
chemical
film
treatments,
primer
and
topcoats to
the
airplane.
2.
Interior
and
Exterior
Finishes
A.
Detail
aluminum
parts
are
chemically
pretreated
and
epoxy
primed
prior
to
assembly. The
chem-film
pretreatment
and
the
epoxy
primer
are
primary
coatings
and
must
be
maintained
and
preserved
for
corrosion
control.
Exterior assemblies that
are
to
be
topcoated receive
ScotchBrite, hand
solvent
cleaning
and
another
overall
application
of
epoxy
primer.
The
airplane
exterior
then
receives
an
overall
topcoat
of
polyurethane
paint including stripes.
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
free
from
paint
and other
foreign
objects.
The
surface
adjacent
to
static
port
must
be
smooth
and
free
from all
paint
imperfection.
Do
not
paint
pitot tube,
fuel
caps,
trim
tab
pushrods where
they
operate
in
an
actuator,
oleo
strut
sliding
surfaces,
standard
polished
spinners, exhausts,
stall
warning
vanes, chromed
items
(handles,
locks,
etc.)
or
the
tie-down
lugs
(located
on
struts)
or
light
lens.
Paint
the
landing gear
barrels
and
torque
links
to
match
the
overall
color.
3.
Paint
Facility
A.
Painting
facilities
must
include
the
ability
to maintain
environmental
control
of
temperature
at
a
minimum
of
65'F
(18IC).
All
paint
equipment
must
be
clean.
Ac
curate
measuring
containers
should
be
available
for
mixing
protective coatings.
Use
of
approved respirators
while
painting
is
a
must
for
personal
safety.
All
solvent containers
should
be
grounded
to
prevent
static
buildup. Catalyst
materials
are
toxic,
therefore,
breathing
fumes or
allowing
contact
with
skin can
cause serious
irritation.
Material
stock should
be
rotated
to
allow
use
of
older
materials
first,
because
its
useful
life
is
limited.
All
supplies should
be
stored
in
an
area
where
temperature
is
higher
than
50F
(1
'C),
but
lower
than
90'F
(32'C).
Storage
at
90F
(32@C)
is
allowable
f
or no
more
than
sixty days,
providing
it
is
returned
to
room
temperature for
mixing
and
use.
(1)
Areas
in
which
cleaning
or
painting
are
done
shall
have
adequate ventilation
and
shall
be
protected
from
uncontrolled
spray,
dust, or fumes.
(2)
Areas
for
prolonged storage
of
cleaned
parts
and
assemblies
awaiting
painting
shall
be
free
from
uncontrolled
spray,
dust,
or
fumes,
or
else
positive
means
of
protecting
part
cleanliness
such
as
enclosed
bins
or
wrapping
in
kraft
paper
shall
be
provided.
(3)
Areas
in
which
cleaning
or
painting
are
done
shall
be
periodically
cleaned
and
dusted.
(4)
Compressed air
used
for dusting
and
paint
spraying
shall
be
free
from
oil,
water
and
particulate
matter.
4.
Sanding
Surfacer
A.
Purpose
and
Requirements.
(1)
Surfacer
is
applied
over
fiberglass
and
ABS
assemblies
to
provide
aerodynamic
contour,
smoothness
and
to
seal porous surfaces.
Application
of
surfacer
also
provides
a
good
surface
for
a
polyurethane finish.
(2)
The
objective
of
a
surfacer
is
to
fill
local
depressions,
pits,
pin
holes
and
other
small
surface
defects
so
a
smooth
surface
is
obtained
for
paint.
The
total
surfacer
thickness
shall
not
be
greater
than
15
mils (0.38
mm).
Only
enough
surfacer shall
be applied to
obtain
a
smooth
surface for
paint.
If
less
thickness
will
provide
a
smooth
surface,
this
is
better.
A
thick
layer
of
surfacer
is
less
flexible
and
may
crack
in
service.
20-31-00
Page
701
©
Cessna
Aircraft Company
April
1/2002
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
(3)
To
complete
the
airplane's
polyurethane
finish
over
surfacer,
begin
by
applying
the
intermediate
coat.
Apply
topcoat (polyurethane
enamel)
using
same procedure.
(4)
Should
a
repair
be
required
(cracked
or
chipped
paint)
to
areas
where
surfacer
is
applied,
sanding
surfacer
should
be
removed
to
expose
fiberglass
or
Kevlar.
It
may
be
necessary
to
remove
all
sanding surfacer
on
that individual
assembly
and/or
component
to
obtain
a
satisfactory
finish.
For
additional
information,
refer
to
Cleaning.
(5)
Sanding
surfacer
methods.
(a)
Do
not
intermix
vendor
material or
substitute
material. Also,
do
not
substitute
instructions.
Select
and use
one
vendor's
material and
use
the
corresponding
instructions.
B.
Cleaning.
CAUTION:
Do
not
use
chemical strippers
on
ABS
plastic
and
fiberglass
assemblies.
Paint
stripper
solvent
will
damage
these
assemblies.
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.
(1)
Remove
paint
covering sanding surfacer
by
sanding.
Paint
should
be
removed
well
beyond
damaged
area.
For
best
results,
it is
recommended
to
remove
all
paint
covering
sanding
surfacer
of
that
individual composite component.
(2)
Remove sanding
surfacer
by
sanding
from
individual component
to
expose
fabric.
(3)
Scuff sand
area
to
be
refinished
with
320
grit paper.
Do
not
over
expose
fabric.
(4)
Clean
surface
with Methyl n-Propyl
Ketone.
Follow
manufacturer's
instructions
for
final
cleaning
prior
to
sanding
surfacer application.
5.
Paint
Stripping
A.
Mechanical
Stripping
(1)
Mechanical
methods
of
stripping
include power
sanding
with
a
disc
or
jitterbug
type sander,
grinder,
hand
sanding,
and
wire
brushing.
(a)
Ensure
mechanical
methods
do not
damage
surfaces
being
stripped.
Damage
may
include,
but
is
not
limited
to,
cutting
fibers
of
composite structures or
scratches
in
the
surface
of
metallic
surfaces.
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.
(2)
Mechanical stripping
must
be used
for
stripping
composite
or
plastic
surfaces.
(3)
Mechanical stripping
is
recommended
for
surfaces
which
might
entrap
chemical
strippers
and
result
in
corrosion.
(4)
Mechanical
stripping
is
required
for
painted
surfaces
masked during
chemical
stripping.
B.
Chemical
Stripping.
20-31-00
Page
702
©
Cessna Aircraft Company
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
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
water
and
consult
physician
immediately.
Paint
stripping
should
be
done
in
a
well
ventilated
area.
WARNING:
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.
(1)
Thoroughly
clean
airplane surfaces
to
remove all grease
and
other dirt which
might
keep
stripping agent
from
attacking
paint.
(2)
All
seams
and
joints
must
be
protected
by
applying
a
tape,
resistant
to
strippers,
to every
joint
to
prevent
stripping
chemicals
from
entering
the
skin
joints.
Chemicals
used
for
stripping
polyurethane
paint
are
very
difficult
to
remove
from
joints,
and
may
promote
corrosion
or
deteriorate
bonding agents
used
in
assembly
of
airplane.
(3)
Mask
following
surfaces
using
plastic sheeting
or
waxed
paper and
plastic
tape
so as
to
make
a
safety
margin
of at
least
one-half
inch
(13
mm)
between
protected
surface
and
surface
to
be
stripped.
NOTE:
Do
not
use
masking
tape.
(a)
Mask
all
windows
and
transparencies.
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.
1
Place barrier
material
over
window
and seal
around
periphery
with
polyethylene
backed
masking
tape.
2
Cut
second sheet
of
barrier
material
an
inch
(26 mm)
or
more
larger
than
window.
3
Place
second
sheet
of
barrier
material
over
window and
seal
with
polyethylene
tape.
(b)
Mask all rubber
and
other
non
metals.
(c)
Composites
if
possible,
shall
be
removed
from
airplane prior
to
stripping.
(d)
Mask
all
honeycomb
panels
and
all
fasteners
which
penetrate
honeycomb panels.
(e)
Mask all
pivots, bearings
and
landing
gear.
(f)
Titanium,
if
used
on
airplane,
must
be
protected
from
strippers.
(g)
Mask
all
skin laps,
inspection
holes,
drain holes,
or
any
opening
that
would
allow
stripper
to
enter
airplane structure.
CAUTION:
Do
not
allow
paint
stripper
to
contact
high
heat
treated
steel
pins,
such
as
pins
attaching
landing
gear
components.
Paint
strippers
may
induce hydrogen
embrittlement
in
high
heat
treated
steel.
(4)
Apply
approved
stripper
by
spray
or
brush method.
20-31-00
Page 703
©
Cessna
Aircraft Company
April 1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
WARNING:
Use
normal safety
precautions
when
using
flammable
materials
during
cleaning
and
painting
procedures.
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
instructions
should
be
closely
followed
for
proper
mixing
of
solution,
application
methods
and
safety
precautions.
(a)
If
using
spray
method,
apply
a
mist
coat
to
area
to
be
stripped,
then when
paint
begins
to
lift,
apply
a
second
heavy coat.
(b) If
applying
with
brush, brush
across
the
surface only once,
in
one
direction.
(5)
Allow
stripper coating
to
lay
on
the
surface
until
paint
lifts.
(6)
After
paint begins
to
lift,
use
a
propylene bristle
brush to
agitate stripper
to
allow
deeper
penetration
of
stripper.
(7)
Remove
lifted
paint with
a
plastic
squeegee.
Dispose
of
residue
in
accordance
with
local
regulations.
(8)
Inspect
all
surfaces
for
incomplete
paint
removal.
(a)
Repeat
previous procedural
steps
as
necessary
until
all
paint
is
removed.
(9)
After
stripping
airplane,
thoroughly
rinse
to remove
any stripping
residue.
(10)
Remove
tape applied to
protect
joints
and
other
masked
areas.
(11)
Carefully
remove
remaining
paint
at
skin
joints
and
masked
areas
by
sanding with
a
hand
or
jitterbug
type sander.
(12)
If
necessary
to remove
paint
from
inside
skin
joints,
refer to
Cleanout
of
Skin
Joints.
(13)
If
corrosion
is
encountered,
refer
to
Structural Repair
Manual,
Chapter
51,
Corrosion/Repair,
for
corrosion treatment.
C.
Cleanout
of
Skin
Joints.
(1)
Install
a
surface
conditioning disc
on a
pneumatic
drill.
(2)
Taper
edge
of
disc
to
an
edge which
will
allow
edge to
fit
into
skin
joint
seam.
(a)
Run
disc against
a
piece
of
coarse
abrasive
paper
or
a
mill
file
until
edge
is
tapered.
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.
(3)
Using
tapered surface
conditioning
disc, remove
paint
and
other
material
from
joint
seams.
(4)
Carefully,
and
using
as
low
speed
as
possible,
remove
paint and
all
other
material
from
joint.
NOTE:
Surface
conditioning
disc will
wear
rapidly,
it
will
be
necessary
to
resharpen
(retaper)
disc frequently.
6.
Hand
Solvent
Cleaning
WARNING:
Work
in
a
well
ventilated
area
free
from
sources of
ignition.
Use
only
approved
solvents
and
materials.
CAUTION:
Airplane
shall
be
grounded during
solvent
wipe.
A.
Surface
Cleaning.
(1)
Apply
solvent
to
a
clean
wiping
cloth
by
pouring
from
a
safety can
or
other approved
container.
The
cloth
should
be
well
saturated
with
solvent.
Avoid
dipping
wipers
into
open
solvent
containers
as
this
contaminates
the
solvent.
(2)
Wipe
the
surface
with
the
wet
cloth
as
required
to
dissolve
or
loosen
soils. Work
on a
small
enough
area
so that
the
area
being
cleaned
remains
wet
with
solvent.
20-31-00
Page 704
©
Cessna
Aircraft
Company
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
(3)
With
a
clean
dry
cloth, immediately
wipe
dry
the
area
being
cleaned.
Do
not
allow
the
surface
to
evaporate
dry.
(4)
Repeat
steps
(1)
through
(3)
as
required and
change cloths often.
7.
Maintenance
of
the
Interior
and
Exterior
Primary
Coatings
and
Topcoat
A.
Rework and repair
primary
coatings
on
airplane
interior
and
exterior
surfaces
for
protection
and
corrosion
control.
(1)
Minor
scratches
or
defects,
which
do not
penetrate
the
epoxy
primer
or
which
penetrate
the
primer
and
expose
bare
metal,
with
the
total
area
of
exposed
bare
metal
less
than
the
size
of
a
dime,
touch
up
as
follows:
(a)
Hand
solvent
clean
and
sand
with
320
grit
or
finer
sandpaper.
(b)
Clean with
compressed
air,
hand
solvent
clean again,
then
wipe
with
a
tack
rag.
(c)
Mix
and reapply
epoxy
primer (MIL
P-23377
or
equivalent)
as
directed
by
the
primer
manufacturer
or
supplier.
(d)
On
a
properly
prepared surface,
mix and
apply
polyurethane
topcoat
as
directed
by
the
paint manufacturer
or
supplier.
(2)
Major
defects
which
expose
bare
metal
to
an
area
larger than
the
size
of
a
dime,
touch
up
as
follows:
(a)
Hand
solvent
clean
and
sand
with
320
grit
or
finer
sandpaper.
(b)
Clean
with
compressed
air,
hand
solvent
clean
again, then
wipe
with
a
tack
rag.
(c)
Apply
a
spray wash
primer
or
(preferred method)
brush
chem
film
primer. Mask
the
area
to
minimize
the
amount
of
primer
from
spreading over
the
existing
epoxy
primer.
Let
cure
according
to
the
product manufacturers
recommendations.
(d)
Mix
and
apply
epoxy
primer
(MIL
P-23377
or equivalent)
to
the
affected
area
within
four
hours.
(e) If
an
exterior
painted
surface,
mix
and
apply
polyurethane
topcoat
as
directed
by
the
paint
manufacturer
or supplier.
20-31-00
Page
705
©
Cessna
Aircraft Company
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
FUEL, WEATHER AND HIGH-TEMPERATURE
SEALING
-
MAINTENANCE
PRACTICES
1.
General
A.
Procedures for
application
of
sealants
are
provided
for
various types
of
sealing
required
for
the
airplane.
2.
Tools
and
Equipment
NOTE:
Specified sealants, cleaning
solvents,
parting
agents,
adhesion
inhibitors
and
equipment
are
listed
for
use.
Suitable
substitutes
may
be
used
for
sealing equipment
only.
SEALANTS
TYPE
I,
CLASS
A-
1/2,
OR
A-2
-
AMS-S-8802
NUMBER
GC-408
Pro-Seal
890
PR-1440
MANUFACTURER
Goal Chemical Sealant
Corp.
3137
East 26th
Street
Los
Angeles,
CA
90023
PRC-DeSoto
International
5454
San
Fernando
Rd.
Glendale,
CA
91209
PRC-DeSoto
International
USE
Fuel,
pressure
and
weather
sealant
brush
application.
SEALANTS
TYPE
I,
CLASS
B-1/4, QUICK
REPAIR
-
MIL-S-83318
Goal Chemical
Sealant
Corp.
Fuel,
pressure
and
weather
sealant.
For
limited
repairs
requiring
rapid
curing
sealant.
SEALANTS
TYPE
I,
CLASS
B-1/2,
B-
2
OR B-4
-
AMS-S-8802
MANUFACTURER
PRC-DeSoto
International
USE
Fuel
pressure
and
weather
sealant,
suitable
for application
by extrusion
gun
and
spatula.
AC-236
CS
3204
Pro
Seal
890
Advanced
Chemistry
And
Technology
Flamemaster Corporation
PRC-DeSoto
International
SEALANTS
TYPE
I,
CLASS
C-20, C-48
OR
C-80
Pro-Seal
890
PRC-DeSoto
International
Fuel,
pressure
and
weather
sealant.
Suitable
for
faying surface
sealing.
©
Cessna Aircraft
Company
20-32-00
Page
201
Jul
3/2006
NAME
Sealants
Sealant GC-435
NAME
Sealants
NUMBER
PR-1440
Sealant
CESSNA AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
SEALANTS
TYPE
IV
Dapco 2100
Pro
Seal
700
Q3-6077
D.
Aircraft
Inc.
Anaheim,
CA
92807
PRC-DeSoto
International
Dow
Corning
Firewall
and
wire
bundle
sealing.
Firewall
sealing
(except
wire
bundles).
Wire
bundle
firewall
sealing.
SEALANTS
TYPE
VI
FA-0606
125
SM8500
HB
Fuller
St.
Paul,
MN
55116
Schnee-Moorehead
Irving,
TX
75017
Water
and
weather-tight
acrylic
latex
sealant
for
windows
and
metal
lap
joints.
Water
and
weather-tight
acrylic
latex
sealant
for
windows
and
metal
lap
joints.
SEALANT
TYPE
VIII,
CLASS
B-1/2
ORB2
-
MIL-S-8784
PR-1428 Class
PRC-DeSoto
International
Low
adhesion
access
door,
fuel,
pressure
and
weather
sealing.
PR-1081
Class
PRC-DeSoto
International
SEALANT TYPE
XI
Sealant
U000927S
CLEANING SOLVENTS
NAME
1, 1,
1 -
Trichloroethane
Technical
Inhibited
(Methyl
Chloroform)
Methyl
Propyl
Ketone
NUMBER
Federal
Specification
ASTM D4126
Available
from
Cessna
Parts
Distribution
Cessna
Aircraft
Company
Department
701
5800
E.
Pawnee
Rd.
Wichita,
KS
67218-5590
MANUFACTURER
Commercially
Available
Commercially
Available
Permanently
pliable
extruded tape
for
fixed
windows.
USE
Before
sealing
cleaning.
Cleaning organic
coating.
©
Cessna
Aircraft
Company
20-32-00
Page
202
Jul
3/2006
Sealant
Sealant
Sealant
Sealant
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
CLEANING
SOLVENTS
NAME
Naphtha
Type
II
Cleaning
compound
Isopropyl
alcohol
PARTING
AGENTS
NAME
Silicone
compound
Petrolatum
technical
EQUIPMENT
Pneumatic sealing
gun.
Hand-operated
sealing
gun
Nozzles,
Round
1/16
orifice
Round
1/8
orifice
Duckbill
Duckbill
Comb
NUMBER
Federal
Specification
TT-N-95
A-A-59281
Federal
Specification
TT-I-735
NUMBER
AS
8660
Federal
Specification
VV-P-236
Semco
Number
250
with
accessories
(or
equivalent)
Semco
Number
850
MANUFACTURER
Commercially
Available
Commercially Available
Commercially
Available
MANUFACTURER
Commercially
available
Commercially
available
PRC-DeSoto
International
PRC-DeSoto
International
PRC-DeSoto
International
USE
Before
sealing cleaning.
Before
sealing cleaning.
Cleaning
plastic.
(Except
plastic
transparencies)
USE
Prevent
sealant
sticking.
Prevent
sealant
sticking.
Injection
sealing.
Injection
sealing.
Application
of
sealant.
Semco
Number
420
Semco
Number
440
Semco
Number
8615
Semco
Number
8648
Semco
Number
8646
Polyethylene
cartridges
with
plungers
and
caps
for
sealant
gun.
Metal
spatulas
with
either stainless
steel
or
glass
plates.
Commercially
available
Commercially available
Application
of
sealant.
Mixing
sealant.
20-32-00
©
Cessna
Aircraft
Company
Page
203
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
EQUIPMENT
Plastic
lined
cups, Commercially available
Mixing
sealant.
wax-free
with
caps
Sealant
fairing
Commercially available
To
fair-in
sealant.
tools
Cheesecloth,
Commercially
available
Cleaning.
lint-free
Plastic
scraper,
Commercially available
Removing
old
sealant.
45-
degree
cutting
edge.
Durometer
Rex
Model
Rex
Gauge
Company,
Inc.
Testing
cure
of
sealant.
1500
(or
3230
West
Lake
Avenue
equivalent)
P.O.
Box
46
Glenview,
IL
60025
Gloves,
lightweight
Commercially
available
Removing
old
sealant.
lint-free
white
cotton
Nylon
bristle
Commercially available
Removing
old
sealant.
brushes
Pipe
cleaners Commercially available
Cleaning.
Funnel
brushes Commercially
available
Cleaning.
3.
Definition
of
Sealing
Terms
A.
The
following
definitions
are
included
to
provide
a
basic
concept
of
the
special
terms
used
in
sealing.
This
list
is
not
all
inclusive
but the
more
common terms
are
listed.
(1)
Absolute Sealing
-
There
can
be
no
leakage allowed.
All
openings
of
any
nature
through
the seal
plane
are
positively
sealed.
This
is
the
first
level
of
sealing. (All
holes,
slots,
joggles,
fasteners
and
seams
must
be
sealed.)
(2)
Accelerator (Activator)
-
Curing
agent
for sealants.
(3)
Application
Time
-
The
length
of
time
sealant
remains
workable
or
suitable
for
application
to
structure
by
brush,
extrusion
gun,
spatula
or
roller.
(4)
Base
Compound
-
The
major
component
of
a
two-part
sealing
compound
which
is
mixed
with
the
accelerator
prior
to
application
to
produce
a
fuel, temperature, pressure,
weather
and/or
firewall
sealing
material.
(5)
Brush
Coat
-
Apply
an
overcoat
or
continuous
film
of
appropriate
sealing
compound
by
use
of
a
brush.
(6)
Fay Seal
or
Faying
Surface
Seal
-
A
seal barrier created
by
the sandwiching
of
sealant
between
mating
surfaces
of
structure.
Special
attention
must
be
taken
to
avoid
metal
chips
or
dirt
at the
faying
surface.
(7)
Fillet Seal
-
Sealant
material
applied at
the
seam,
joint
or
fastener
after
the
assembly
has
all
permanent
fasteners
installed
and
shall
conform
to the
dimension
in
applicable
figure.
(8)
Hole
-
An
opening
that
has
no
appreciable
depth,
such
as
a
tool
hole.
Holes
that penetrate
the
seal plane must
be
metal
filled
with
a
fastener,
gusset
or
patch.
(9)
Injection
Seal
-
Filling
of
channels
by
forcing
sealant
into
a
void
or
cavity
after
assembly.
(10)
Integral
Tank
-
Composition
of
structure
and
sealant
material
which
forms
a
tank that
is
capable
of
containing
fuel
without
a
bladder.
(11)
Intermediate
Seal
-
The second
level of
sealing.
All
holes,
slots, joggles
and
seams
in
the
seal
plane must
be
sealed.
A
minor
amount
of
leakage
is
tolerable
and
permanent
fasteners
are
not
required
to
be
sealed.
(12)
Post-Assembly
Seal
-
A
seal
that
is
applied after
the
structure
is
assembled.
(Fillet
and
injection
seals.)
20-32-00
Page
204
©
Cessna
Aircraft
Company
Jul 3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
(13)
Preassembly
Seal
-
Sealant
material
that
must
be
applied
during or
prior
to
the
assembly
of the
structure.
(Faying
surface
and
pre-pack seals.)
(14)
Pre-Pack
Seal
-
A
preassembly
seal
used
to
fill
voids
and
cavities;
can
be
a
primary seal
used
to
provide
seal
continuity
when used
in
conjunction
with
a
fillet
seal.
It
can
be
used
as
a
backup
seal to
support
a
fillet
across
a
void.
Fill
the entire
cavity
to
be
prepacked.
Usage
as
a
primary
seal
should
be
kept
to
a
minimum.
(15)
Primary
Seal
-
Sealant
material
that prevents leakage
and
forms
a
continuous
seal
plane.
This
seal
is
in
direct contact
with
fuel, vapor,
air, acid,
etc.
With
few
exceptions,
it
is
in
the form
of
a
fillet seal.
(16)
Sealant
-
A
compound applied
to
form
a
seal barrier.
(17)
Seal
Plane
-
A
surface
composed
of
structure,
sealant
and
fasteners
on
which
the
continuity
of
seal
is
established.
(18)
Shank Sealing
-
Sealant
compound
shall
be
applied
to the
hole
or
to both
the shank
and
the
under
head
area
of
the
fastener
in
sufficient quantity that the
entire
shank
is
coated
and
a
small
continuous
bead of
sealant
is
extruded
out around the
complete
periphery
of
each
end
of
the
fastener
when
installed.
The
fastener
shall
be
installed
within
the
application
time
of
the
sealing
compound
used.
(19)
Squeeze-Out
Life
-
Length
of
time sealant
remains
suitable
for structure
assembly
in
faying
surface
seal
application.
(20) Tack-Free
Time
-
Tack-free
time
is
a
stage,
during
the
cure
of
the
sealant compound,
after which
the
sealant
compound
is
no
longer
tacky.
When
the
sealant
compound
is
pressed firmly
with
the
knuckles,
but
no
longer
adheres
to the
knuckles,
the
sealant
compound
is
tack-free.
4.
Materials
A.
Type
of
Sealants
-
Sealants
are
categorized
by
type
of
usage.
Type
I
sealants
are
separated
into
classes
to
differentiate
the
materials according
to
method
of
application.
Dash
numbers
following
the
class designation
indicate
the
minimum
application
time
(in
hours)
for
Class
A
and Class
B,
and
minimum work
life
(in
hours)
for
Class
C.
Refer
to
Table
201
for
application
time, curing
rate,
etc., for
Type
I
sealants.
(1)
Type
I
-
Fuel,
pressure,
and
weather
sealant.
(a)
Class
A
-
Sealant
which
is
suitable
for
brush
application.
(b)
Class
B
-
Sealant which
is
suitable
for
application
by
extrusion
gun,
spatula,
etc.
(c)
Class
C
-
Sealant
which
is
suitable
in
faying
surface applications.
(d)
Quick
Repair Sealant
-
This
material
is
for
use
only
in
making
repairs when
an
extremely
rapid
curing
sealant
is
required.
A
possible
application
includes
sealing
a
leaking fuel
tank
on an
airplane
which
must
be
dispatched
within
a
few
hours.
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.
(2)
Type
VIII
-
Low
Adhesion
Access
Door
Sealant.
This Class
B
sealant
is
designed
for
sealing
faying surfaces
where
easy
separation
of
the
joined
surfaces
is
required.
The
sealant
has
low
adhesion
and
forms
a
gasket
that
molds
itself
to
fill
all
irregularities
between
two
surfaces.
The
sealant
is
exceptionally
resistant
to
fuels,
greases,
water,
most
solvents
and
oils
including
hydraulic
oil.
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
Page 205
©
Cessna
Aircraft
Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
Table 201.
Curing
Properties
of Type
I
Sealant
CLASS
APPLICATION
WORK
LIFE TACK-FREE
CURING
RATE
TIME
(HOURS,
(HOURS,
TIME
(HOURS,
(HOURS,
MINIMUM)
MINIMUM)
MAXIMUM) MAXIMUM)
A-1/2
1/2
10
40
A-2
2
40
72
B-1/2
1/2
4
6
B-2 2
40
72
B-4
4
48
90
C-24
8
24
96
168 (7
days)
C-48
12
48
120
336
(14
days)
C-80
8
80
120
504
(21
days)
5.
General
Requirements
A.
When
working
with
sealants observe
the
following
requirements.
(1)
Unmixed
sealants
shall
not be more
than
two
months
old
when
received. These
sealants
shall
not
be more
than
six
months
old
when
used.
(2)
Unmixed
sealants
stored
at
temperatures exceeding
80°F
(27°C)
shall
be
used within
five
weeks.
(3)
Sealants
which
have
been
premixed,
degassed
and
flash frozen
shall
be
maintained
at
-40°F
(-40°C)
or
lower
and
shall
not
be
received
more
than
two
weeks
beyond the
date
of mixing.
These sealants
shall
not be
used more
than
six
weeks
after
the
date
of
mixing.
(4)
Frozen
sealant
shall
be
thawed
before being
used.
If
sealant
were
applied
at
a
temperature
below
60°F
(15°C),
it
would
not
be
sufficiently
pliable for
proper
application
and
adhesion
could
be
critically
reduced
by
condensation
of
moisture.
On the
other
hand,
although
sealant
must
extrude
freely
for
proper application,
it
would
be
subject
to
excessive
slumping
if
applied
at
a
temperature
above
80°F
(27°C).
Frozen
sealant
may
be
thawed
by
any
suitable
means
which
does
not
cause
contamination
or
overheating
of the
sealant
and
does
not
shorten
the
application
time
of
the
sealant
to
an
impractical
period.
Examples:
Thawing
by
exposure
to
ambient
air
temperature,
accelerated
thawing
by
exposure
in a
constant temperature
bath (using
clean,
hot
water),
accelerated
thawing
in
a
microwave
oven.
In
any
case,
thawing
temperature
and
time
shall
be
adjusted
to
give
a
thawed
sealant
temperature
between
60°F,
and
80°F
(15°C
and
27°C)
at
the
time
the
sealant
is
applied.
(5)
Mixed, frozen
sealants
which
have
thawed shall
not be
refrozen.
(6)
Complete
preassembly operations, such
as
fitting,
filing,
drilling,
countersinking, dimpling
and
deburring,
prior
to
cleaning
and
sealant
application.
(7)
Surfaces
must
be
clean
and
dry,
free
from
dust,
lint,
grease, chips,
oil
condensation
or
other
moisture
and
all
other contaminating
substances
prior
to
the
application
of
sealant.
(a)
All
exposed bonding
primer
or
bonded
assemblies
which
are
to
be
sealed
shall
be
cleaned
using Scotch
Brite
followed
by
solvent
cleaning
using
Trichloroethane.
NOTE: Bond
primer
shall
not be
removed;
just
lightly scuffed
with
Scotch
Brite.
(8)
Sealant
materials
may
be
applied
to
unprimed
or
primed
surfaces. Nonchromated
or epoxy
primers shall
have
good
adhesion
to
the
substrate
material
and
shall have
aged at
least
48
hours prior to sealant
application.
Adhesive
bonding
primer
shall
be
scotchbrited
and
cleaned
before
applying
sealant.
(9)
Sealants
shall
not be
applied
when
the
temperature
of
either
the
sealant
or
the
structure
is
below
60°F
(15°C).
(10)
Sealant
applied
by
the
fillet
or
brush
coat
methods
shall
always
be
applied
to the
pressure
side
of
a
joint
if
possible.
20-32-00
Page
206
©
Cessna
Aircraft
Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
(11)
After
application,
sealants
shall
be
free
of
entrapped air bubbles
and
shall
not
exhibit
poor
adhesion.
All
fillets
shall
be
smoothed
down
and
pressed
into
the
seam
or
joint
with
a
filleting
tool before
the
sealant
application
time
has
expired.
(12)
Where
fasteners
have
been
shank
or under
head
sealed, extruded
sealant
shall
be
evident
around
the
complete
periphery
of
the
fastener
to
indicate adequate sealing.
Sealant extruded
through
a
hole
by
a
rivet
shall
be
wiped
from
the
end
of
the rivet before
bucking. Threaded
fasteners
which
have
been shank or under
head
sealed
shall
not
be
retorqued
after
the
expiration
of
the
application
time
of the
sealant.
Prior
to
torquing, sealant
shall
be
removed
from
the
threads.
In
torquing,
turn
the
nut
rather than
the
bolt,
if
possible.
(13)
Pressure
testing shall
not
be
accomplished
until
the
sealant
is
cured.
(14)
Sealant shall
not be
applied
over
ink,
pencil
or
wax pencil
marks.
If
these
materials
extend
into
the
sealing
area,
they
must
be
removed.
(15)
If
sealing
is
to
be
accomplished
over
primer
and
the
primer
is
removed
during
the
cleaning
process,
it
is
permissible
to seal
directly over
the
cleaned
area
and
then
touch
up
the
exposed
areas after
the
sealant
has
been
applied
and
is
tack
free.
(16)
Sealed
structure
shall
not
be
handled
or moved
until
sealant
is
tack free
(sealant
may
be
dislodged
or
have
the
adhesion damaged). Excessive vibration
of
structure,
such
as
riveting,
engine
run
up,
etc.
is
not
permitted.
(17)
Drilling
holes
and
installing
fasteners
through
a
fay sealed
area
shall
be
performed during
the
working
life
of
the
faying
sealant
or
the
entire
shank
and
area under
fastener
head
shall
be
fay
sealed.
6.
Sealant Curing
A.
Room
Temperature.
(1)
Room
temperature
curing properties
are
based
on
a
temperature
of
77°F,
+5
or -5°F
(25°C,
+3
or
-
3°C)
and
a
relative humidity
of
50
percent
unless otherwise
indicated.
(2)
Room
temperature
curing properties
of
Type
I
sealants
are
given
in
Table 201.
(3)
Curing
properties
of Type
VIII,
Class
B
sealants
are
the same
as
for
Type
I,
Class
B.
Adhesion
to
aluminum
should
be
(peel)
less
than two
pounds
per inch width
(1.4
N
per
10 mm
width).
B.
Accelerated
Curing.
(1)
Accelerated curing
of
sealant
can
be
accomplished
in
several
ways.
The
procedure
to
be
used
is
dependent
on
the
type
of
sealant
and
other
factors.
(2)
The cure
of
Type
I
sealants
can be
accelerated
by
an
increase
in
temperature
and/or
relative
humidity.
Warm
circulating
air
at
a
temperature
not
to
exceed
140°F
(60°C) may be
used
to
accelerate
cure.
Heat
lamps
may
be
used
if
the
surface
temperature
of
the
sealant
does
not
exceed
140°F
(60°C).
At
temperatures
above
120°F
(49°C),
the
relative
humidity
will normally
be
so low
(below
40
percent)
that
sealant
curing
will
be
retarded.
If
necessary,
the relative
humidity
may
be
increased
by
the
use
of
water containing
less
than
100
parts
per
million
total
solids
and
less
than
10
parts per million
chlorides.
7.
Mixing
of
Sealants
A.
Requirements.
(1)
Sealants
shall
be
mixed or
thinned
in
accordance
with
the
manufacturers
recommendations
and
thoroughly
blended
prior
to
application.
All
mixed
sealant
shall
be
as
void
free
as
possible.
(2)
Prior
to
mixing,
the sealing
compound base
and
its
curing
agent,
both
in
their respective
original
unopened
containers, shall
be
brought
to
a
temperature
between 75°F
and 90°F
(24°C
and
32°C)
along
with
all
required mixing
equipment.
B.
Hand Mixing
of
Sealant.
(1)
Weigh into
clean,
wax free
containers the correct
amount
of
base and
curing
agent,
per
manufacturers
instructions,
immediately prior
to
mixing.
An
alternate method
is
to
mix
the
sealant
on
a
flat
plate with
a
spatula.
The
scales
and
weighing
process
must
be
controlled
within
+2
or
-2
percent
to
ensure
good
quality.
(2)
Do
not
allow
the
accelerator
to
come
into
contact
with
the
sides
of
the container.
(3)
Materials
shall
be
accurately
weighed
on
scales
that
are
calibrated
and
maintained
for
required
accuracy.
20-32-00
Page
207
©
Cessna Aircraft Company
Jul
3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
(4)
Mix
the
components
until
the
color
is
uniform
taking
care
not
to
trap
air
in
the
sealant.
(5)
Transfer
the sealant
to
another
clean
container
and complete
the
mix.
C.
Sem-Kit
Mixing.
(Refer
to
Figure
201)
WARNING:
The
cartridge should
be
held
firmly,
but
must
not
be
squeezed,
as
the
dasher
blades
may
penetrate
the
cartridge
and
injure
the
hand.
(1)
Pull
dasher
rod
to the
FULL
OUT
position
so
that the
dasher
is
at
the
nozzle
end of
the
cartridge.
(2)
Insert ramrod
in
the
center
of
the
dasher
rod
against
the piston
and
push
the
piston
in
approximately
one
inch
(25 mm).
NOTE:
Extra
force
will
be
needed
on
the
ramrod
at
the
beginning
of
accelerator
injection
into
the
base
material.
(3)
Move
the
dasher
rod
in
approximately
one
inch
(25
mm),
then push
the
piston
in
another
inch
(25
mm).
Repeat
this
action
until
accelerator
is
distributed
along
the
entire length
of
the
cartridge.
NOTE:
The
accelerator
has
been
fully
injected
into
the
cartridge
when
the
ramrod
is
fully
inserted
into
the
dasher
rod.
(4)
Remove
and
properly
discard
the
ramrod.
NOTE:
Mixing
the
accelerator
and
base
material
can
be
accomplished
manually, or
as
an
alternate
method,
with
the
use
of
a
drill
motor.
(5)
Manual
Mixing.
(a)
Begin
mixing
operation
by
rotating
the
dasher
rod
in a
clockwise direction
while
slowly
moving
it
to
the
FULL
OUT
position.
NOTE:
Do
not
rotate the
dasher
rod
counterclockwise;
the
four blade
dasher
inside
the
cartridge
will
unscrew
and
separate
from
the
dasher
rod.
(b)
Continue
clockwise
rotation
and
slowly
move the
dasher
rod
to
the
FULL
IN
position.
1
A
minimum
of
five
full
clockwise
revolutions
must
be
made
for
each
full
out
stroke
and
for
each full
in
stroke
of
the
dasher
rod.
Approximately sixty
strokes
are
necessary
for
a
complete
mix.
NOTE:
If
streaks
are
present
in
the
sealant
(viewing
through
the side
of
the
cartridge),
the
sealant
is
not
completely
mixed.
(c)
End
mixing
operation
with
the
four
blade
dasher
at
the
bottom
of
the
cartridge.
(d)
Hold
cartridge
upright;
unscrew
dasher
rod
from the
four
blade
dasher
by
gripping
the
cartridge
at
the
four
blade
dasher
and turn
the
dasher
rod
counterclockwise.
Remove
dasher
rod.
(e)
Screw
appropriate
nozzle
into
the
cartridge.
If
sealant
gun
is
to
be
used,
install
cartridge
in
gun.
(6)
Drill
motor
mixing.
NOTE:
A
tapered
rotary file or
a
25/64
inch
drill
bit
may be
used
with
a
drill
motor
to
turn
the
dasher
rod.
(a)
Insert
the rotary
file/drill
bit
into
the
dasher
rod
approximately
1/2
inch
(13 mm).
20-32-00
Page
208
©
Cessna
Aircraft
Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
B1110
CARTRIDGE
FOUR-BLADE
DASHER
ROD
ATERIAL
ACCELERATOR
DASHER
HANDLE
NOTE:
CARTRIDGE
IS
DISPOSABLE
AFTER
USE.
5580T1044
Two-Part
Sealant
Cartridge
Figure
201
(Sheet
1)
20-32-00
©
Cessna Aircraft
Company
Page
209
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
WARNING:
The
cartridge should
be
held
firmly,
but
not
squeezed,
as
the
dasher
blades
may
penetrate the
cartridge
and
injure
the
hand.
(b)
Verify
the
drill motor
will rotate the
dasher
rod
clockwise
(looking
toward
the
nozzle
end
of
the
cartridge).
(c)
With
the
cartridge
held
firmly
in
one
hand
and
the
drill
motor
in
the
other,
rotate the
dasher
rod
at
approximately
50
revolutions-per-minute
while
moving
the
dasher
rod
to
FULL
IN
and FULL
OUT
positions.
1
Mix
sealant
for
at least 50
strokes
(a
stroke
is
one
complete
full
in
and
full
out
stroke
of
the
dasher
rod).
NOTE:
If
streaks
are
present
in
the
sealant (viewing
through the side
of
the
cartridge),
the
sealant
is
not
completely
mixed.
(d)
End
mixing
operation
with
the
four blade
dasher
at
the
bottom
of
the
cartridge.
(e)
Hold
cartridge
upright; remove
drill
motor and
rotary
file/drill
bit
from the
dasher
rod;
unscrew
dasher
rod
from
the four
blade
dasher
by
gripping
the
cartridge
at
the
four blade
dasher
and
turn
the
dasher
rod
counterclockwise.
Remove
dasher
rod.
(f)
Screw
appropriate
nozzle
into
the
cartridge.
If
sealant
gun
is
to
be
used,
install
cartridge
in
gun.
8.
Cleaning
A.
All
surfaces
to
which
sealant
is
to
be
applied
shall
be
clean
and
dry.
B.
Remove
all
dust,
lint,
chips, shavings,
etc.
with
a
vacuum
cleaner
where
necessary.
C.
Cleaning
shall
be
accomplished
by
scrubbing
the
surface
with
clean cheesecloth
moistened
with
solvent.
The
cloth
shall
not
be
saturated
to
the
point
where dripping
will
occur.
For
channels
and
joggles,
pipe
cleaners
and/or
funnel brushes
may
be
used
instead
of
cheesecloth.
(1)
Use
solvent
A-A-59281 to
first
clean
the
integral
fuel
tank.
(2)
Use
0-T-620,
1, 1, 1
-
Trichloroethane,
Technical, Inhibited
only
must
be
used
last
to
finish
clean.
D.
The
cleaning solvent
should
never
be
poured
or
sprayed
on the
structure.
E.
The
cleaning
solvent
shall
be
wiped
from the
surfaces
before
evaporation
using
a
piece
of
clean, dry
cheesecloth
in
order that
oils,
grease,
wax
etc., will
not
be
redeposited.
F. It is
essential that
only clean
cheesecloth
and
clean
solvent
be
used
in
the
cleaning
operations.
Solvents
shall
be kept
in
safety
containers
and
shall
be
poured
onto
the
cheesecloth.
The
cheesecloth
shall
not
be
dipped
into
the solvent containers
and
contaminated
solvents
shall
not
be
returned to the
clean
solvent containers.
G.
Final
cleaning
shall
be
accomplished
immediately
prior
to
sealant
application
by
the
person
who
is
going
to
apply the
sealant.
(1)
The
area
which
is
to
be
sealed
shall
be
thoroughly
cleaned.
A
small
clean
paint
brush
may
be
needed
to
clean
corners,
gaps,
etc.
Always
clean
an
area
larger
than
the
area
where
the
sealant
is
to
be
applied.
Never clean
an
area
larger
than
30 inches
(0.8
m) in
length
when
practical.
When
the
area
is
being
scrubbed
with
a
moistened
cloth
in
one
hand,
another clean
dry
cloth
shall
be
held
in
the
other
hand
and
shall
be
used
to
dry
the
structure.
The
solvent
must
be
wiped from the
surfaces
before
it
evaporates.
(2)
The
above procedure
shall
be
repeated until there
is
no
discoloration
on
the
clean
drying
cloth.
Marks
resulting
from wax
or
grease
pencils
must
be
removed
from
parts
prior
to
sealing.
H.
Allow
all
cleaned surfaces
to
dry
a
minimum
of
5
minutes
before
the
application
of
sealant
materials.
I.
Sealant shall
be
applied
as soon
as
possible
after
cleaning
and
drying
the
surfaces
to
be
sealed.
Do
not
handle the
parts
between
the
cleaning
and
sealing operations.
Sealant
application
personnel
handling
cleaned
surfaces
shall
wear
clean
white gloves
to
prevent
surface
contamination.
In
the
event
contamination does
occur, the
surfaces
shall
be
recleaned.
20-32-00
Page
210
©
Cessna Aircraft
Company
Jul
3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
J.
Safety
precautions should
be
observed
during
the
cleaning
and
sealing
operation.
Cleaning
solvents
are
toxic and
flammable
in
most cases.
Fresh
air
masks and/or
adequate
ventilation
are
required
for
all
closed areas. The
structure
shall
be
electrically
grounded
before
starting any
cleaning
or
sealing
operation.
9.
Sealing
Application
A.
General
(Refer
to
Figure 202).
(1)
All
new
sealing shall
be
accomplished
using
the
type
of
sealing
material
required
for
the
area
being
sealed.
All
sealant
repairs shall
be
accomplished
using
the
same type
of
sealing
material
as
that
which
is
being
repaired.
(2)
Application
time
of
the
sealing compound
shall
be
strictly
observed.
Material which becomes
too
stiff
and
difficult
to
work
or
which does
not
wet
the
surface properly
shall be
discarded
even
though
the
application
time
has
not
expired.
(3)
Prior
to
sealant
application,
all
surfaces
to
be
sealed
must
be
cleaned.
Refer
to Cleaning.
B.
Fay
Surface Sealing
(Refer
to
Figure
202).
(1) A
fay
surface seal
must
be
made
when
a
new
structure
is
added
to
the airplane
and
a
fay surface
seal
is
necessary.
(a)
The
fay
sealed joints
must
be
closed
and
attached
before
the
work
life
is
expired
as
given
in
Table
201.
(2) A
fay
surface
seal
must
be
made when
the
structure
and/or
parts have been
disassembled
for
causes
other
than
a
defective
seal.
(a)
Fay
sealed
joints
must
be
closed
and
attached
before
the
work
life
is
expired
as
given
in
Table
201.
(3) A
fay
sealed
joint
must
have
sufficient sealant
applied
so
the
space
between
the assembled
fay
surfaces
is
filled
with
sealant.
(a)
A
small
quantity
of
sealant
must
come
out
in a
continuous
bead
around
the
edges.
(4)
Countersink
or
ream
the
holes
through
the
fay
sealed
joints
with
temporary
or
permanent
fasteners
installed.
(a)
Metal
work
operations
must
be
completed
before the
clean
and
seal
operations.
NOTE:
Fabrication
and
changes
done
after
the seal
are
not
recommended.
(b)
Countersink or
ream
holes
through the
fay
sealed
joint
with
permanent
fasteners
in
every
other
hole.
1
Use
temporary
fasteners
(Clecos
or
bolts)
if
assembly
with
permanent
fasteners
is
not
possible.
2
Temporary
fasteners
must
be
replaced
by
permanent
fasteners
before
the
expiration
of
the
fay
surface
sealant.
3
Remove
temporary
fasteners
and install
permanent
fasteners
with wet
sealing
compound.
(5)
Immediately
after
the assembly
is
completed
and
all
permanent fasteners
are
installed,
remove
any
sealant that
has
not
cured
and
unwanted
sealant
with clean
rags
moist
with A-A-59107,
Toluene or
Methyl Propyl
Ketone.
C.
Injection
Sealing (Refer
to
Figure
202).
(1)
Sealant
must be
put
into
the
channel,
void
or any open
space
from
one
point
only
with
a
pneumatic
sealant
tool.
(a)
After
sealant
is
added,
air
must
not be
trapped
and
the
channel,
void
or
any
open
area.
(b)
Sealant
must
be
seen
at
the
opposite
opening.
1
Cause
a
blockage
at
each
channel
or exit
as
the
sealer
is
applied
in
the
area
so
that
sealant
is
seen
at
the
openings
of
all
applicable channels.
(2)
Sealant
must be
put
into
wire
bundles
that
go
through
firewalls
and
bulkheads
to
fill
any
voids
and
open areas
between
the wires.
(a)
Bundle
ties
must
be
no
more
than
6
inches
(152.4
mm)
from the
location
to
be
sealed.
(b)
Pull
the
wires
apart
from
each
other.
1
Layer each
wire with
sealant
over
the
length
which
goes
through the
bulkhead
or
seal
assembly.
20-32-00
Page
211
©
Cessna Aircraft Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL 182/T182
MAINTENANCE
MANUAL
B1111
INSPECTION
PANEL
(TYPICAL)
RAILING
SKIN
TO
SK
NG EDGE
STIFFENER
BO
05261010
05261009
05261011
Integral
Fuel
Compartment
Sealing
Figure 202
(Sheet
1)
20-32-00
©
Cessna
Aircraft Company
Page
212
Jul 3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
81112
FAYING
SURFACE
SEAL
TYPICAL
RIB
SECTION
SEALANT
EXTRUDED
CONTINUOUSLY
FAY
SEAL
(SEALANT
EXTRUDED
CONTINUOUSLY)
Integral
Fuel
Compartment
Sealing
Figure 202 (Sheet
2)
20-32-00
Cessna
Aircraft
Company
5598T2007
5598T2007
Page
213
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
B1377
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).
5598T1010
6280T 1003
Integral
Fuel
Compartment
Sealing
Figure
202
(Sheet
3)
©
Cessna Aircraft
Company
20-32-00
Page
214
Jul
3/2006
I
I
II
I
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
B1113
PNEUMATIC
SEAL
TOOL
55981009
Integral
Fuel
Compartment Sealing
Figure 202
(Sheet
4)
20-32-00
©
Cessna Aircraft
Company
Page
215
Jul
3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
2
Layer
each
wire with
sealant
0.5
inch (12.7
mm)
added
length
on
each side
of the
bulkhead
or
seal
assembly.
3
Pull
the
wires
through
the
bulkhead
or
seal
assembly
into
position.
4
Fill
the
open
areas
of
the
wires
that
remain
until
the
sealant
is
seen
from
the
opposite
side.
(3)
Remove
unwanted
sealant
before
the
work
life
of
the
sealant
is
expired.
(4)
Use
an
applicable
tool
to
make
the
sealant
smooth
and
flush
with
the
surface.
D.
Fillet
Sealing.
(1)
Fastener
considerations:
(a)
Do
not
fillet
seal
any
parts
until
they
are
held
completely
together
by
permanent
fasteners.
(b)
Prior to
filleting
the
periphery
of
bolted
structure
and
fittings,
it is
necessary
that
all
bolts,
accomplishing
the
attachment,
be
properly torqued.
(2)
The
sealant
shall
be
applied
using
a
sealant
gun
or
spatula.
(3)
When
using
a
sealant
gun
for
fillet
sealing,
the
nozzle
tip shall
be
pointed
into
the
seam
or
joint
and
shall
be
maintained
nearly
perpendicular
to
the
line
of
travel.
A
continuous
bead
of
sealant
shall
precede
the
tip
and the
tip
size,
shape and
rate
of
travel
shall
be
such
that
sufficient
sealant
shall
be
applied
to
produce
the
required
fillet.
(4)
Fillets
shall
be
shaped
or
formed
to
meet the
size
and
shape
requirements
as
shown
in
applicable
figures using
the
nozzle
tip
and/or fairing
tools
to
press
against
the
sealant
while
moving
parallel
to
the
bead.
Exercise
caution
to
prevent
folds
and entrapment
of
air
during
application
and
shaping
of
the
fillet
and work out
any visible
air bubbles. The
fillet
shall
be
formed
so
that
the
highest
portion
of
the
fillet
is
centered over
the
edge
of
the
structure
or
fitting. Lubrication
in
any form
shall
not
be used
for smoothing
purposes.
In
all
cases,
fillet
size
shall
be
kept
as
near
minimum
as
practical.
(5)
Where
it
is
more
convenient
or
fillet
slumping
is
encountered,
the
fillet may
be
applied
in
two
stages.
A
small
first
fillet
should
be
applied which
is
allowed
to
cure
to
a
tack-free
state,
followed
by
a
second
application
of
sealant sufficient
to
form the final
fillet
conforming
to
the
specified
dimensions for
a
fillet
seal.
If
the first fillet
has
cured,
it
must
be
cleaned
before
the
second
application
of
sealant
is
made.
If
the
fillet
has
only
cured
to
a
tack-free
state,
it
shall
be
wiped
lightly
with
a
gauze
pad
or
cheesecloth
pad
dampened
with
cleaning
solvent.
(6)
Allow the
sealant to cure
to
a
tack-free condition
prior
to the
airplane
being moved,
handled
and/or worked
on.
(7) In
cases
where
a
fillet
seal
connects
to
an
injection
seal, the
full bodied
fillet
shall
extend past
the
end
of
the
injection
and
then
taper
out.
(8)
Lap
joint
and seam
fillets
shall
be
as
shown
in
Figure
202,
Sheet
3.
(9)
Butt
joint
fillets
shall
be
as
shown
in
Figure
202,
Sheet
3.
(10)
Bolts
shall
be
fillet
sealed
as
shown
in
Figure
202,
Sheet
3.
The
area
for
sealing
shall
consist
of
the
area
of
the
structure surrounding
the base
of
the
fastener
end
plus
the
entire exposed
area
of
the
fastener.
An
optional
method
of
sealing threaded fasteners
is
to
apply
a
brush
coat
of
Type
I,
Class
A
sealant.
Where
brush
coating
is
used
as
the
method
of
sealing
threaded
fasteners,
the
sealant
must be
worked
around each
fastener
with
a
stiff
brush
and
considerable
care
to
be
effective.
A
simple pass
of
the
brush
with
the
sealant
is
not
sufficient
to
produce
an
effective
seal.
(11)
Dome
type
nutplates shall
be
fillet
sealed
as
shown
in
Figure 202,
Sheet
3.
The
area
for sealing
shall
consist
of
the
area
of
the
structure surrounding
the
base
of
the
fastener
and
from
there
up
over
the
rivets
to
the
dome.
(12)
Hole
filling
and
slot
fillets
shall
be
as
shown
in
Figure 202,
Sheet
3.
(a)
Tooling holes
shall
be
plugged
with
a
shank
sealed
soft
rivet and
then
brush
coated
with
Type
I,
Class
A
sealant.
20-32-00
Page
216
©
Cessna Aircraft
Company
Jul
3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
10.
Sealant
Repair
A.
Materials
-
Repairs,
in
general,
shall
be
accomplished
with
the
same
type
of
material
as
that
being
repaired.
NOTE: Type
I,
Class
B-1/2
is
recommended
for
use
during
cold
weather
to
obtain
an
accelerated
cure.
NOTE: Type
I,
Quick
Repair sealant
may
be
used
as
a
repair
for sealant
in
fuel tanks
if
desired
for
fast
cure
and
rapid
dispatch.
B.
Temperature
Requirements.
(1)
The
structure
shall
be
above
60°F
(15°C)
before the
sealant
is
applied
and shall
remain
above
60°F
(15°C)
until the
sealant
is
tack-free.
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;
however,
the
structure
must
be
subsequently
heated
to
above
60°F
(15°C)
and the
sealant
allowed
to
become
tack-free
before
the
tanks
are
refueled.
(2)
The maximum
air
temperature allowed
to
come
in
contact
with
the
curing
sealant
is
120°F (49°C).
C.
Fillet
and
Fastener
Sealing
Repairs.
(1)
Repair
of
damaged
or
faulty
sealant
applications
shall
be
accomplished
as
follows:
(a)
Remove all
damaged
or
faulty
sealant
to
ensure solid residual
material.
(b)
Sealant
shall
be
cut
to
produce
a
smooth
continuous
scarfed face.
The
sealant
shall
be
completely
removed
in
the
affected
areas.
The cutting
tools
should
only
be
made
from
nonmetallic
materials
that
are
softer
than
aluminum.
(c)
Inspect
repair
areas
for
clean
and
smooth
cuts.
Loose
chunks
or
flaps
of
sealant
on
the
cut
areas
shall
be
removed.
(d)
Clean
the
area
to
be
sealed,
including
the scarfed face
of
the old
seal.
Refer
to
Cleaning.
(e)
Apply new
fillet
seals. Slight
overlapping
of
the
fresh
material
over
the
existing fillet
is
permissible.
A
large
buildup
of
sealant
shall
not be
allowed.
(f)
Rework
of
a
fillet
which
has
been
oversprayed
or
brushed with primer shall
be
accomplished
by
a
scarfed
joint
and
removal
of
the
fillet
having primer
on
it, in
the
area
of
the
repair.
The
primer shall
not
be
sandwiched
between
the
old
and new
sealants.
(g) If
the
primer
is
removed
during
the
cleaning operation,
it
is
permissible
to
apply
the
new
fillet
seal
directly
over
the
clean
bare metal
and
then
touch
up
with
the
proper
primer
all
exposed
areas
of
bare
metal
after
the
sealant
has
been
applied.
D.
Faying
Surface
Sealing
Repair
-
After
determining
the
area which
contains
the
faulty
and/or
leaking
faying surface
seal,
the
repair shall
be
accomplished
by
applying
a
fillet
seal
along
the edge
of the
part
adjacent
to
the
faying
surface
seal long
enough
to
fully
cover
the
area
of
the
faulty
and/or
leaking
seal.
E.
Brush
Coat
Sealing
Repair
-
Repair
of
damaged
or
leaking
brush
coat
seals
shall
be
accomplished
by
removing
the
discrepant
brush
coat. Clean
the
area
of
sealant
removal
and
the
surrounding structure
and
sealant.
Refer
to
Cleaning.
F.
Integral
Fuel
Tank
Sealing
Using
PR-1826 Class
B
Rapid
Curing
Sealant.
(1)
Remove
damaged section
of
sealant
with
a
sharp
plexiglass
scraper.
Taper
all
cuts
in
old
sealant
at
45-degree
angles.
20-32-00
Page
217
©
Cessna Aircraft
Company
Jul
3/2006
CESSNA AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
(2)
Thoroughly
clean with
solvent
and
abrade
old
areas which
are
to
be
over
coated.
Clean
one
small area
at
a
time,
then
dry
with
a
clean
cloth
before
the
solvent evaporates.
NOTE:
Always pour solvent
on
the
cloth
to
maintain
a
clean solvent
supply.
NOTE:
In
fuel
tanks
which
have been
in
operation,
the
sealant
will
be
soaked
and
should
be
dried
in
area
of
the
repair
with
a
vapor
proof
heat
lamp
or
hot
air
blower
before
new
sealant
is
applied.
(3)
After
the
surface has
been
cleaned
and
dried,
apply
a
sufficient
layer
of
PR-1826
Adhesion
Promoter
with
a
clean
brush
or
gauze
pad.
Allow
adhesion
promoter
a
minimum
of
30
minutes
to
dry.
NOTE: Care
must
be
taken
to
get
a
equal,
thin
layer
of
adhesion promoter
applied
to the
surface. There
must
be
a
sufficient
layer
for
the
full
surface,
but
not
too
much
that
will
cause
it
to
drip.
(4)
(5)
Mix
PR-1826 Class
B
sealant according
to
instructions
supplied
with
the
material.
Apply
PR-1826
Class
B
sealant,
0.125
to
0.375
inch
(3.2
to
9.5
mm)
thick,
to
the repair
area
with
a
spatula
or
paddle
shaped tool.
Firmly
press
sealant
in
place
and
form to
desired
shape.
Overlap
PR-1826 Class
B
sealant over
old
sealant
from
0.125
to
0.25
inch
(3.2
to
6.4
mm).
NOTE:
Sealant
may
be
applied
up
to
8
hours
after
the
application
of
adhesion
promoter. After
8
hours,
the
surface
should
be
recleaned
and
adhesion
promoter
reapplied.
(6)
Allow
sealant
to
cure
a
minimum
of
2
hours at
77°F
(25°C)
before refueling.
Curing
time
is
based
solely
on
temperature
and
will
be
halved
for
every
18°F
(10°C)
increase,
and
doubled
for
every
18°F
(10°C)
decrease
from
the
standard
77°F (25°C).
G.
Firewall
Wire
Bundle
Seal Assembly.
(1)
Fay
surface
seal
the
mating
parts
of
the
seal
assembly
plate
and
the
firewall.
Refer
to
Sealing
Application.
(a)
Seal
only
with Type
IV
DAPCO
2100 from
D.
Aircraft
Inc. or
seal
with
Type
IV
Q3-6077
from
Dow
Corning.
Refer
to Tools and
Equipment.
(2)
Injection
seal
the wire bundle
that passes through
the seal
assembly.
Refer
to
Sealing
Application.
(a)
Seal
only
with
Type
IV
DAPCO
2100
from
D.
Aircraft
Inc. or
seal
with
Type
IV
Q3-6077
from
Dow
Corning.
Refer
to
Tools
and
Equipment.
20-32-00
Cessna Aircraft
Company
Page
218
Jul 3/2006
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
CONVERSION
DATA
-
DESCRIPTION AND OPERATION
1.
General
A.
This
section
contains
information converting
the
more
commonly
used
measuring
units
found
in
this
manual
from
the
North
American
system
to
the
metric
system.
B.
Tables have been
prepared
for
the
convenience
of
the
user.
Formulas,
examples
and
a
table
of
conversion
factors
are
included for
individual
computations.
2.
Formulas
for
Conversion
Computations
A.
Work
and
Energy.
(1)
Mechanical
Energy
Formula
-
Refer
to
conversion
factors
in
Figure
1
to
convert inch-pounds
and
foot-pounds
into
metric
measure
of
centimeter
kilograms
and
meter
kilograms.
(2)
Figure
2
is
a
table containing
conversion
data
for
converting
inch-pounds to
centimeter
kilograms,
centimeter
kilograms
to
inch-pounds, foot-pounds
to
meter
kilograms,
meter
kilograms
to
foot-pounds.
B.
Distance
and
Length.
(1)
Formula
-
One
multiplied
by
2.540
=
centimeter;
inch
=
2.54 cm.
One
multiplied
by
25.40
=
millimeter;
inch
=
25.40
mm.
NOTE:
Reference
conversion
factors
in
Figure
1.
(2)
Figure
3
is
a
table
containing
conversion
data
for
converting inches to
millimeters.
The
procedure
for
converting
inches
to
millimeters
by
using
figure
as
follows:
Example,
convert 0.032
inches
to
millimeters.
(a)
Read down
inch
column
to
0.003.
(b)
Read
across
top
inch
column
to
0.0002.
(c)
Locate
where
these
two
columns intersect
(0.0032
inch
is
0.0812
millimeters).
(3)
Figure
4
is
a
table containing
conversion
data
for
converting
fraction
of
an inch
to
decimal
equivalent
and
to
millimeter. Locate
fraction
of
an
inch
figure
and
move
to
the
right
horizontally
to
locate
decimal
equivalent
figure
in
the
decimal
equivalent
column
and
millimeter
numeral
in
the
millimeter
column.
C.
Temperature.
(1)
Formula:
'F
=
9/5
('C
+32)
'C
=
5/9
(F
-32)
(2)
Figure
5
is
a
table containing conversion
data
for converting
temperature
from
either Celsius
to
Fahrenheit
or Fahrenheit
to
Celsius.
(a)
Select
the
desired
number
in
the
middle column
of
the
three
column
presentation.
If
the
number
you
selected
is
in
degrees
Celsius,
read
the
degrees
Fahrenheit
equivalent
in
the
right
column
of
the
three-column presentation.
(b)
Select
the
desired
number
in
the
middle
column
of the
three-column
presentation.
If
the
number
selected
is
in
degrees
Fahrenheit,
read
degrees
Celsius
equivalent
in
the
left
column
of
the three-column presentation.
D.
Drill
Sizes
and
Tap
Sizes.
(1)
Figure
6
is
a
table containing conversion
data
for
converting standard
and
millimeter
drill
sizes
to
decimal
equivalents.
Also
included
is
a
chart
for
determining
tap
size
when
a
hole
ID
is
known.
(a)
To
find decimal equivalent
of
a
standard
drill
size,
go
down
the chart to
the
standard
drill
size
and
read
decimal
equivalent
in
the
right
column.
(b)
To
find
standard drill
size for
a
known
decimal
equivalent
size,
go
down
decimal column
to
decimal
size
and
read
drill
size
in
the
left
column.
(c)
To
find
decimal
equivalent
of
a
millimeter
drill
size,
go
down
the
chart
to
the
millimeter
drill
size
and
read
decimal
equivalent
in
the
right
column.
(d)
To
find millimeter
drill
size
for
a
known decimal
equivalent size,
go
down
the
chart
to
the
decimal
equivalent
size
and
read
millimeter
drill
size
in
the
left
column.
(e)
To
find
a
tap
size,
go
down
the
hole
ID
chart
to
the
size
hole
to
be
tapped
and
read
the
tap
size
in
the
left
column.
20-50-00
Page
1
©
Cessna
Aircraft Company
April
1/2002
CESSNA
AIRCRAFT
COMPANY
MODEL
182/T182
MAINTENANCE
MANUAL
MULTIPLY
CENTIMETERS
CUBIC
CENTIMETERS
BY
0.3937
0.03281
0.001
0.06102
0.0002642
TO
OBTAIN
INCHES
FEET
LITERS
CUBIC INCHES
U.S.
GALLONS
CUBIC
FEET
CUBIC INCHES
CUBIC
METERS
FEET
FOOT-POUNDS
28,320
1,728