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Maintenance Manual

a)

Member of GAMA

COPYRIGHT©0 1997
CESSNA AIRCRAFT COMPANY
WICHITA, KANSAS, USA
182SMM14

3 FEBRUARY 1997
182SMM
14

~~REVISION 141JUY201 JULY 2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82
MAINTENANCE MANUAL

LIST OF EFFECTIVE PAGES
PAGE

CHAPTER-SECTION-SUBJECT

DATE

00-Title
00-List of Effective Pages
00-Record of Revisions
00-Record of Temporary Revisions
00-Table of Contents
SERVICE BULLETIN LIST

Pages 1-6

Jul 1/2007

INTRODUCTION

Pages 1-7

April 1/2002

Page 1

Jul 1/2007

Pages 1-5
Page 1

Janl1/2007

LIST OF REVISIONS
LIST OF MANUFACTURERS TECHNICAL
PUBLICATIONS
LIST OF CHAPTERS

00
©Cessna Aircraft Company

-

Jul 1/2007

LIST OF EFFECTIVE PAGES

Page 1of 1
Jul 1/2007

Revision
Number

Date
Inserted

Date
Removed

Page
Number

Revision
Number

Date
Inserted

Date
Removed

Page
Number

RECORD OF TEMPORARY REVISIONS
Temporary Revision
Number

Page Number

Issue Date

By

Date Removed

By

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82

MAINTENANCE MANUAL

CONTENTS
SERVICE BULLETIN LIST.............................
Service Bulletins...............................

Page 1
Page 1

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 ...............................
Revisions..................................

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

LIST OF MANUFACTURERS TECHNICAL PUBLICATIONS .............
List of Manufacturers Technical Publications ..................

Page
Page
Page
Page

LIST OF CHAPTERS ...............................

Page 1

©Cessna Aircraft Company

00

-

CONTENTS

1
1
1
1

Page 1of 1
Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182
MAINTENANCE MANUAL
SERVICE BULLETIN LIST

1.

Service Bulletins

Service
Bulletin
Number

Title

SB97-1 1-02

Pilot's Operating Handbook Revision

SB97-11-03
R1

Service
Bulletin Date

Manual
Incorporation

Jul 1/97

Dec 1/98

Autopilot Limitation Placard Installation and
Control Cable Tension Inspection

Sep 21/98

Dec 1/98

SB97-1 1-05

Altimeter Certification Logbook Entry Verification

Dec 15/97

Dec 1/98

SB97-22-01

Bendix/King Autopilot Flight Computer
Modification

Oct 6/97

Dec 1/98

SB97-24-02

Electrical Wire Bundle Routing Inspection and
Modification

Dec 22/97

Dec 1/98

SB97-26-01

Fire Extinguisher Mounting Bracket Inspection

Dec 22/97

Dec 1/98

SB97-28-02

Fuel Tank Vent Line Inspection

Nov 14/97

Dec 1/98

SB97-33-01
R1
SB97-34-01

Light Dimming Module Resistor Installation
Inspection

Dec 14/98

Dec 1/98

KLN 89B GPS Navigation System Approach
Restrictions

Jul 2/97

Dec 1/98

SB897-34-02
R1
SB97-71-01
R1

Alternate Static Source Valve Inspection

Dec 8/97

Dec 1/98

Alternate Air Door Hinge Assembly Replacement

Jul 27/97

Dec 1/98

SB97-78-01

Engine Exhaust Muffler Inspection

Aug 11 /97

Dec 1/98

SB897-78-02
R1

Engine Exhaust Muffler Inspection

Dec 23/97

Dec 1/98

SB98-11-03

Pilot's Operating Handbook and Checklist
Revisions

May 1/98

Dec 1/98

SB98-1 1-04

Muffler Inspection Placard Installation

Aug 21/98

Dec 1/98

5898-11-07

Brazilian Pilot's Operating Handbook Revision

Oct 12/98

Dec 1/98

SB98-20-01
Ri1

Firewall Sealant Replacement

Dec 31/98

Dec 1/98

SB98-22-01

KAP-140 Dual Axis Autopilot Modification

May 15/98

Dec 1/98

SB98-22-02
R2

KAP-140 Dual Axis Autopilot Limitation

Feb 1/99

Dec 1/98

SB98-24-01

Mar 30/98

Dec 1/98

SB98-25-01

Alternator Replacement
Pilot and Copilot Seat Back Pivot Fitting
Inspection

May 29/98

Dec 1/98

SB98-25-02

Pilot and Copilot Seat Roller Inspection

Sep 14/98

Dec 1/98

SB98-27-04

Control Column Internal Slide Attach Screw
Inspection

May 29/98

Dec 1/98

SERVICE BULLETIN LIST
©0
Cessna Aircraft Company

Page 1
Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182
MAINTENANCE MANUAL
Service
Bulletin Date

Manual
Incorporation

Flight Control Cables and Travel Inspection

Jun 15/98

Dec 1/98

SB98-28-01

Engine Fuel Pressure Transducer Inspection
and Replacement

Mar 2/98

Dec 1/98

SB98-34-01

KLN 89B GPS Navigation System IFR
Non-Precision Approach Limitation

Aug 3/98

Dec 1/98

R1
SB98-71 -02

Engine Air Filter Replacement

Jul 27/98

Dec 1/98

SB98-78-02
R1
SB98-37-01
R1
SB98-55-03

Engine Exhaust Muffler Pressure Test and Ball
Joint Inspection

Dec 14/98

Dec 1/98

Airborne Vacuum Pump Inspection

Mar 8/99

Dec 1/99

Horizontal Stabilizer Forward Inboard Rib To
Spar Gap Inspection

Nov 30/98

Dec 1/99

SB98-78-03

Engine Exhaust Muffler Replacement

Feb 14/98

Dec 1/99

SB99-1 1-02

German Pilot's Operating Handbook and
Checklist Revisions

Sep 27/99

Dec 1/99

SB99-21 -01

Fresh Air Vent Replacement

Mar 15/99

Dec 1/99

SB99-24-01

Electrical Power System Modification

Mar 15/99

Dec 1/99

SB99-24-02

Circuit Panel Assembly Cover Installation

Dec 27/99

Nov 1/00

SB99-25-01
R1

Dec 27/99

Jun 1/00

SB99-28-01

Emergency Locator Transmitter (ELT)
Operational Test
Wing Fuel Tank Vent Check Valve Inspection

Apr 26/99

Dec 1/99

SB99-32-01

Brake Torque Plate Inspection

May 10/99

Dec 1/99

SB99-34-01
R1

KLN 89B GPS Navigation System Modification

Apr 24/00

Dec 1/99

SB99-37-01

Vacuum Hose Modification

Dec 27/99

Nov 1/00

SB99-53-01

Firewall Doubler Inspection and Engine Cowl
Shock Mount Installation

Mar 8/99

Dec 1/99

SB99-53-02

Tailcone Skin Installation Inspection

Apr 26/99

Dec 1/99

SB99-71 -01
R2

Engine Piston Pin Plug Wear Inspection

Jul 12/99

Dec 1/99

SB99-71 -05

Engine Valve Seat Inspection

Oct 25/99

Jun 1/00

SBOO-22-01

KAP-1 40 Autopilot Servo Inspection/Modification

Feb 14/00

Nov 1/00

SBOO-24-01

Main Power Junction Box Circuit Breaker
Retrofit Kit Installation

Mar 13/00

Nov 1/00

SBOO-24-02

Electrical Panel Wiring Modifications

Jun 5/00

Nov 1/00

SBOO-27-0 1
R1

Lower Forward Elevator Control Cable Pulley
Brackets Inspection

Aug 28/00

Nov 1/00

SBOO-34-01

Pitot Tube Heater Assembly Insulation
Installation

Apr 10/00

Nov 1/00

Service
Bulletin
Number

Title

SB98-27-06

SERVICE BULLETIN LIST
©D
Cessna Aircraft Company

Page 2
Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82
MAINTENANCE MANUAL
Service
Bulletin
Number

Service
Bulletin Date

Manual
Incorporation

Title

SBOO-37-01

Vacuum System Air Filter Element
Inspection/Replacement

Aug 14/00

Nov 1/00

SBOO-53-01
R1

Center Cabin Rivet Inspection/Installation

Apr 10/00

Jun 18/01

SBOO-73-01
R2

Engine Fuel Injection Lines and Support Clamps
Inspection

Dec 24/01

Jan 2/06

SBOO-79-01
R1

Engine Low Oil Pressure Switch Replacement

Feb 21/00

Nov 1/00

S BOO-i11-05

Pilot's Operating Handbook and Pilot's Checklist
Revision

Dec 26/00

Jun 18/01

SBOO-27-02
R1

Aileron Control Cable Quadrant Inspection
Inspection/Modification

Nov 6/00

Jun 18/01

SBO1 -73-01
R2

Engine Driven Fuel Pump Inspection

Oct 10/05

No Effect

SBO1 -74-01

Ignition Switch Center Ground Terminal
Inspection

Jun 25/01

Jun 18/01

SBO01 -71 -03

Engine Turbocharger Mounting Bolt
Replacement

Aug 20/01

No Eff ect

SBO1 -25-01

Glareshield Shroud Installation

Dec 24/01

No Eff ect

SBO1 -28-04

Oct 1/01

No Eff ect

SBO1 -34-01

Fuel Quantity Level Sender/Transmitter
Inspection
Coin Antenna Replacement

Sep 3/01

No Eff ect

SB02-1 1-1

Pilot's Operating Handbook Revisions

Jan 21/02

No Effect

SB02-11-02

Pilot's Operating Handbook Revisions

Jan 21/02

No Eff ect

SB02-22-01

Honeywell Kap 140 Autopilot System
Modification

Nov 25/02

No Eff ect

SB02-25-01

Pilot and Copilot Shoulder Harness Guide
Removal

Apr 29/02

No Eff ect

SB02-28-01
R1

Fuel Line Inspection

Dec 16/02

No Eff ect

SB02-34-01

Goodrich WX-500 Weather Mapping Sensor
Modification

Nov 25/02

No Eff ect

SB02-37-01

Vacuum System Reducer Fitting Replacement

Jan 21/02

No Eff ect

SB02-37-02

Dry Vacuum Pump and Coupling Replacement
Requirements

Feb 18/02

No Eff ect

SB02-37-03

Vacuum System Reducer Fitting Replacement

Feb 18/02

No Eff ect

SB02-37-04

Airborne Air and Fuel Products Check Valve
Manifold Inspection

Oct 28/02

No Eff ect

SB02-52-01

Cabin Door Handle Replacement

Jan 21/02

No Eff ect

SB02-53-01

Fuselage Ballast Weight Installation

Sep 9/02

No Eff ect

SERVICE BULLETIN LIST
©Cessna Aircraft Company

Page 3
Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182

MAINTENANCE MANUAL
Service
Bulletin Date

Manual
Incorporation

Elevator Rivet Installation

Oct 14/02

No Eff ect

Engine Crankshaft Gear Retaining Bolt
Replacement
Engine Induction System Fuel Overboard Drain
Relocation
Engine Oil Pump Plug Inspection

May 10/04

No Eff ect

Nov 25/02

No Eff ect

Feb 03/03

No Eff ect

SB03-23-01

Honeywell KMA 26 Audio Panel Modification

Jul 28/03

No Eff ect

SB03-24-01

Alternator Replacement

Jul 28/03

No Effect

SB03-24-02

MC01 -3A Main Electrical Power Junction Box
Modification

Oct 13/03

No Effect

SB03-27-01

Flap Actuator Motor Inspection

Sep 29/03

No Eff ect

SB03-27-02

Flap Control Bracket Attach Bolts Replacement

Dec 22/03

No Eff ect

SB03-28-01

Fuel Cap Lanyard Removal

Oct 27/03

Jan 2/06

SB03-32-01

Nose Landing Gear Wheel Fairing Modification

Sep 29/03

No Eff ect

SB03-34-01

Honeywell KS 2700, KS 271 C and KS 272C
Servo Friction Inspection

Oct 27/03

No Eff ect

SB03-34-02
R1

Altimeter Inspection

Feb 16/04

No Eff ect

SB03-37-01

Vacuum Manifold Inspection/Replacement

Nov 10/03

No Eff ect

SB03-53-01

Aft Cabin Stringer Inspection

May 26/03

No Eff ect

SB03-53-03
R1

Nose Landing Gear Fairing Attachment
Inspection

Mar 15/04

No Eff ect

SB03-71 -02

Fuel Injection Servo Inspection

May 26/03

No Eff ect

SB03-73-01

Throttle Arm Retention Inspection

Nov 4/03

No Eff ect

SB04-11-03

NAV III Pilot's Checklist

Aug 30/04

No Eff ect

SB04-22-01

Sep 13/04

No Eff ect

SB04-23-01

Autopilot Circuit Breaker Extension Cap
Installation
Garmin GIA 63 Inspection/Modification

Sep 13/04

No Eff ect

SB04-24-0 1

Alternator Control Unit Inspection/Replacement

Mar 1/04

No Eff ect

SB04-25-01
R4

Crew Seat Recline Modification

Dec 26/06

No Eff ect

SB04-25-02
R1

Crew Seat Back Cylinder Lock Inspection and
Crank Arm Modification

Oct 17/05

No Eff ect

SB04-25-04

Crew Seat Back Cylinder Lock Control
Inspection/Adjustment

Oct 11/04

No Eff ect

SB04-27-01
R2

Elevator Rivet Inspection

Sep 13/04

No Eff ect

SB04-28-02

Fuel Strainer Installation Inspection

May 10/04

No Eff ect

Service
Bulletin
Number

Title

SB02-55-01
SB02-71 -03
R2
SB02-7 1-04
SB02-71 -05
R1

SERVICE BULLETIN LIST
C Cessna Aircraft Company

Page 4
Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82

MAINTENANCE MANUAL
Service
Bulletin
Number

Title

SB04-34-01

Service
Bulletin Date

Manual
Incorporation

Marker Beacon Placard Installation

Nov 22/04

No Eff ect

SB04-34-02

Vertical Navigation Placard Installation

Dec 27/04

No Eff ect

SB04-52-01

Security Lock Installation

Jun 28/04

No Eff ect

SB04-53-02
R1
SB04-53-03

Firewall Doubler Flange Modification and Shock
Mount Inspection

Apr 11/05

No Eff ect

Forward Door Post Bulkhead Washer Inspection

Oct 11 /04

No Eff ect

SB04-71 -01

Engine Cowl Flap Rivet Inspection

Apr 26/04

No Effect

SB04-71 -02

Engine Starter Inspection/Replacement

Nov 8/04

No Eff ect

SB04-73-01

Engine Fuel Injection Lines and Support Clamps
Inspection

Aug 30/04

Jan 2/06

SB05-1 1-02

Pilot's Operating Handbook Revisions

Mar 28/05

No Eff ect

SB05-22-01

Trim Servo Cable Chain Inspection

Dec 5/05

No Effect

SB05-22-02

Honeywell KAP-140 Autopilot Software
Modification

Dec 5/05

No Effect

SB05-24-01

MC01 -3A Main Electrical Power Junction Box
Circuit Breakers Inspection

Jan 31/05

No Effect

SB05-25-01

Inflatable Seat Belt Restraint Installation
Inspection

Mar 7/05

No Eff ect

SB05-25-02

Inflatable Seat Restraints Installation

Apr 25/05

No Eff ect

SB05-28-01

Fuel Strainer Gasket Inspection

Jan 17/05

No Eff ect

SB05-33-01

High Intensity Discharge (HID) Landing and Taxi
Light Installation

May 9/05

Jan 2/06

SB05-34-01

Garmin G1000 System Software Upgrade

Jan 31/05

No Eff ect

SB05-34-02

Garmin GMA 1347 Audio Panel Modifications

Feb 14/05

No Eff ect

SB05-34-03

Garmin GMA 63 Integrated Avionics Unit
Modification

Feb 14/05

No Eff ect

SB05-34-04

Garmin GMA 63 Integrated Avionics Unit
Modification

Apr 25/05

No Eff ect

SB05-34-05

Garmin G1000 System Software Upgrade

Jul 29/05

No Effect

SB05-34-06

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

Jul 29/05

No Effect

Sep 26/05

No Effect

Sep 26/05

No Eff ect

SB05-34-09

Garmin G 1000 GDL-69A Weather And Digital
Audio Entertainment Interface Installation

Sep 26/05

No Eff ect

SB05-34-1 0

Aft Avionics And Electrical Wire Bundle
Inspection

Nov 21/05

No Eff ect

SB05-34-07
SB05-34-08

SERVICE BULLETIN LIST
©Cessna Aircraft Company

Page 5
Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/7182

MAINTENANCE MANUAL

Service
Bulletin
Number

Service
Bulletin Date

Manual
Incorporation

Title

SB05-34-1 1

Garmin GIA 63 Integrated Avionics Unit Outside
Cover Replacement

Nov 21/05

No Eff ect

SB05-34-1 2

Garmin G1000 Display Unit (GDU) 1040 Cover
Glass Delamination

Dec 5/05

No Eff ect

SB05-37-01

Vacuum Pump Inspection/Replacement

Nov 7/05

No Eff ect

SB05-53-02

Tunnel Bulkhead Rivet Inspection

Sep 12/05

No Eff ect

SB05-57-01

Wing Trailing Edge Rib Inspection

Oct 10/05

No Eff ect

SB05-71 -01

Engine Crankshaft Replacement

Jul 18/05

No Eff ect

SB05-73-01

Engine Driven Fuel Pump Inspection

Mar 7/05

No Eff ect

SB06-11 -01

Pilot's Operating Handbook Revisions

Mar 27/06

No Eff ect

SB06-1 1-02

Pilot's Checklist Revisions

Nov 6/06

No Eff ect

SB06-22-01

Apr 24/06

No Eff ect

SB06-24-01

Honeywell KS270C Pitch Servo and KS271C
Roll Servo Tach Generator Modification
Electrical Ground Strap Inspection

May 8/06

No Eff ect

SB06-24-02

60 Ampere Alternator Rotor Replacement

Dec 18/06

No Eff ect

SB06-24-03

60 Ampere Alternator Brush Replacement

Dec 18/06

No Eff ect

SB06-24-04

Circuit Breaker Inspection

Dec 26/06

No Eff ect

SB06-24-05

Circuit Breaker Panel Assembly Inspection

Dec 26/06

No Eff ect

SB06-27-0 1

Flap Aft Roller Bearing Installation Modification

Apr 10/06

No Eff ect

SB06-32-01

Brake Master Cylinder Covers Inspection

Sep 25/06

No Eff ect

SB06-34-01

Honeywell KT 73 MODE S Transponder
Installation
Garmin G1000 System Software Upgrade

Feb 27/06

No Eff ect

Mar 27/06

No Eff ect

SB06-34-03

Enablement of Garmin G1000 Terrain
Awareness Warning System CLASS-B
(TAWS-B)

May 22/06

No Eff ect

SB06-34-04

Automatic Direction Finder (ADF) and Distance
Measuring Equipment (DMVE) Installation

Oct 23/06

No Eff ect

SB06-52-01

Cabin Door Modification

Mar 27/06

No Eff ect

SB06-53-01

Fuselage Stringer Rivet Inspection

Oct 23/06

No Eff ect

SB06-71 -01

Engine Crankshaft Retirement

May 8/06

No Eff ect

Engine Compartment Fuel Hoses Security
Inspection

Jun 19/06

No Eff ect

R1

SB06-34-02
R1

R1
SB06-71 -02

SERVICE BULLETIN LIST
© Cessna Aircraft Company

Page 6
Jul 1/2007

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.

2.

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.

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
© Cessna Aircraft Company

Page 1

April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

NAME

MODEL

SERIALS
BEGINNING

SERIALS ENDING

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:

4.

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.

Temporary Revisions
A.

5.

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.

Serialization
A.

6.

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.

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.

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
© Cessna Aircraft Company

Page 2

April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

7.

Service Bulletins
A.

8.

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 isthe 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).

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
© Cessna Aircraft Company

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April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
Chapter

(c)

Title

30

Ice and Rain Protection

31

Indicating/Recording Systems

32

Landing Gear

33

Lights

34

Navigation

35

Oxygen

37

Vacuum

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

B.

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

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
©Cessna Aircraft Company

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April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

Chapter/System
(Auto Flight)

22-10-00

Subject/Unit
(Auto Pilot)

Section/Subsystem
(Auto Pilot)

(2)
(3)
(4)
(5)

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.
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.
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.
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:

(6)

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.

A typical page number:

22-10-00 Page 202
Nov 3/97

Auto Pilot

Auto Flight

Second Page of
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
© Cessna Aircraft Company

Page 5

April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

9.

Effectivity Pages
A.

10.

11.

12.

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.

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.

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.

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
0 Cessna Aircraft Company

Page 6

April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

13.

Cessna Propeller Aircraft Customer Care Supplies and Publications Catalog
A.

14.

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.

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
© Cessna Aircraft Company

Page 7

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
Revision
Number

1

-

Original Issue 3 February 1997

Date

Writer

Revision
Number

Date

Writer

1 December 1998

2

1 December 1999

3

1 June 2000

4

1 November 2000

5

l8 June 2001

6

15 December
2001

jgb

7

1 April 2002

jgb

8

4 August 2003

jgb

9

1 March 2004

rdg

10

1 March 2005

tks

11

2 January 2006

bjo

12

3 July 2006

bjo

13

1 January 2007

jcn

14

1 July 2007

jcn

LIST OF REVISIONS
©D
Cessna Aircraft Company

Page 1
Jul 1/2007

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
Item

Cessna
Part
Number

Manufacturer's Part
Number

GFC -700
Autopilot

Publication Part
Number

Publication Title

Manufacturer

19000352-00

G1000 Line
Maintenance Manual

Garmin USA
1200 East 151 st Street
Olathe, KS 66062

Installation Manual

Garmin International, Inc.
1200 E. 151st Street
Olathe, Kansas 66062

Autopilot
Servo

GSA
8X/GSM 85

19000303-72

Autopilot

KAP 140

006009910002

Allied Signal
101 N. Industrial Parkway
New Century, KS 66031

Table 2. CHAPTER 23 - COMMUNICATIONS
Item
Cessna
Part
Number

Manufacturer's Part
Number

Publication Part
Number

Publication Title

Manufacturer

NAV/
Comm

KX-155A

006105420000

Installation Manual

Allied Signal
101 N. Industrial Parkway
New Century, KS 66031

Audio
Amplifier/
Intercom/
Marker
Beacon
Receiver

KMA 26

006105440000

Installation Manual

Allied Signal
101 N. Industrial Parkway
New Century, KS 66031

Item

LIST OF MANUFACTURERS TECHNICAL PUBLICATIONS
©Cessna Aircraft Company

Page 1
Janl1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182

MAINTENANCE MANUAL

Table 3. CHAPTER 24 - ELECTRICAL POWER
Item

Cessna
Part
Number

Manufacturer's Part
Number

Publication Part
Number

AVT200413

Standby
Battery

Publication Title

Manufacturer

Cyclon Selection
Guide (Third Edition)
(NOTE 1)

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
Item

Seat Belt
Airbag
Assembly

-

EQUIPMENT FURNISHING

Cessna
Part
Number

Manufacturer's
Part Number

Publication Part
Number

Publication Title

Manufacturer

7035-1 011- 8105
(GO-Pilot
Seat)

E508804

Supplemental
Maintenance Manual

AmSafe Aviation
5456 E. McDowell Rd.
Mesa, AZ 85215
www.amsafe.com

E508804

Supplemental
Maintenance Manual

AmSafe Aviation
5456 E. McDowell Rd.
Mesa, AZ 85215
www.amsafe.com

E508804

Supplemental
Maintenance Manual

AmSafe Aviation
5456 E.McDowell Rd.
Mesa, AZ 85215
www.amsafe.com

7035-1 021- 8105
(Pilot Seat)
7035-2011- 8105
(LH Rear
Seat)
7035-2021- 8105
(RH Rear
Seat)
Inflation
Assembly

508792401 (CoPilot Seat)
508794401 (Pilot
Seat)

Electronics
Module
Assembly

508358409

LIST OF MANUFACTURERS TECHNICAL PUBLICATIONS
©Cessna Aircraft Company

Page 2
J an 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182

MAINTENANCE MANUAL
CHAPTER 25 - EQUIPMENT FURNISHING
Item
Part
Number
ThreePoint Air
Bag Belt

Man ufacturer's
Part Number

Publication Part
Number

7035E508804
20301181 05
(Co-Pilot
Seat)

Publication Title

Manufacturer

Supplemental
Maintenance Manual

AmSafe Aviation
5456 E. McDowell Rd.
Mesa, AZ 85215
www.amsafe.com

Supplemental
Maintenance Manual

AmSafe Aviation
5456 E. McDowell Rd.
Mesa, AZ 85215
www.amsafe.com

Publication Title

Manufacturer

Hand Portable
Halon 1211 Fire
Extinguisher
Maintenance Manual

Amerex Corp.
P.O. Box 81
Trussville, AL 351 73-0081

Publication Title

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

70352040218105
(Pilot Seat)
7035205021 8105
(LH Rear
Seat)
7035206021 81 05
(RH Rear
Seat)
V23
System
Diagnostic
Tool

508668201

E508804

Table 4. CHAPTER 26 - FIRE PROTECTION
Item

Fire Extinguisher

Item
Cessna
Part
Number
C4210010201

Manufacturer's Part
Number
A352 GS

Publication Part
Number

Table 5. CHAPTER 32 - LANDING GEAR
Item

Cessna
Part
Number

Wheel

C163006- 40-75B
0301

Cleveland Wheels &
Brakes Component
Maintenance Manual

Brakes

300521 9-1

Cleveland Wheels &
Brakes Component
Maintenance Manual

Manufacturer's Part
Number

30-52U

Publication Part
Number

LIST OF MANUFACTURERS TECHNICAL PUBLICATIONS
©Cessna Aircraft Company

Page 3

Janl1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/T 182

MAINTENANCE MANUAL

Table 6. CHAPTER 34 - NAVIGATION
Publication Part
Number

Publication Title

Manufacturer

M881000D

Altitude Encoder/
Digitizer Owner/
Installation Manual

Trans-Cal Industries, Inc.
16141 Cohasset St.
Van Nuys, CA 91406

KI 209A

006105430000

Installation Manual

Allied Signal
101 N. Industrial Parkway
New Century, KS 66031

06601 0720014

KR 87

006001 840005

Installation Manual

Allied Signal
101 N. Industrial Parkway
New Century, KS 66031

Mode C
Transponder

066011560101

KT 76C

006105450000

Installation Manual

Allied Signal
101 N. Industrial Parkway
New Century, KS 66031

NAV
Indicators

066030560002

KI 208/209

006001400003

Installation Manual

Allied Signal
101 N. Industrial Parkway
New Century, KS 66031

GPS

066011481111

KLN
89/89B

006105220001

Installation Manual

Allied Signal
101 N. Industrial Parkway
New Century, KS 66031

Autopilot

3900008-1 KAP140
2-axis

Installation Manual

Allied Signal
101 N. Industrial Parkway
New Century, KS 66031

Manufacturer's Part
Number

Item

Cessna
Part
Number

Blind
Encoder

3940408-1 SSD1 20-20

Navigation
Indicator

066030560011

Automatic
Direction
Finder

Table 7. CHAPTER 71
Item

Engine

Cessna
Part
Number

-

POWER PLANT
Manufacturer's Part
Number

Publication Part
Number

Publication Title

Manufacturer

10540AB1A5

60294-7

Direct Drive Engine
Overhaul Manual

Textron Lycoming

LIST OF MANUFACTURERS TECHNICAL PUBLICATIONS
Q Cessna Aircraft Company

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CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182

MAINTENANCE MANUAL

Table 8. CHAPTER 73
Item

-

Cessna
Part
Number

ENGINE FUEL AND CONTROL
Manufacturer's Part
Number

Publication Part
Number

Publication Title

Fuel
Injection
System

RSA-5

15-338D

Fuel
Injection
System

RSA-5

15-81 OB

RSA-5 & RSAPrecision Airmotive
10 Fuel Injection
14800 40th Ave. NE
Systems Operation & Marysville, WA 98271
Service Manual
Troubleshooting
Precision Airmotive
Techniques for the
14800 40th Ave. NE
Precision Airmotive
Marysville, WA 98271
RSA Fuel Metering
System

Fuel
Injection
System

RSA-5

15-895G

Index of Manuals,
Bulletins, and
Service Information
Letters for Precision
Airmotive Fuel
Controls

Precision Airmotive
14800 40th Ave. NE
Marysville, WA 98271

Manufacturer's Part
Number

Publication Part
Number

Publication Title

Manufacturer

6351

L-1363C

4300/6300
Series Magneto
Maintenance and
Overhaul Manual

Slick Aircraft Products
530 Blackhawk Park Ave.
Rockford, IL 61104

Table 9. CHAPTER 74
Item

Magneto

Cessna
Part
Number

-

Manufacturer

IGNITION

LIST OF MANUFACTURERS TECHNICAL PUBLICATIONS
©Cessna Aircraft Company

Page5
Janl1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82
MAINTENANCE MANUAL
LIST OF CHAPTERS
5
6
7
8
9
10
11
12
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
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
1
1
1
1
1
1
1
2
2
2
2
2
2
2
3
3
3
3
3
3
4
4
4
4
4
4
4
4
4
4
4
5
5
5
5
5
5
5

B2
E14
F12
G2
G9
G16
H4
H10
A2
D7
E7
F6
G2
Ill
L2
A2
Dll
F2
G2
H2
Jill
A2
D16
E6
F2
F12
G7
G16
H7
12
115
L2
A2
A17
B4
C2
C15
D5
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
©Cessna Aircraft Company

Page 1
Jul 1/2007

CHAPTER

TIME LIMITS/
MAINTENANCE

CHECKS

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82
MAINTENANCE MANUAL

LIST OF EFFECTIVE PAGES
PAGE

DATE

5-00-00

Pages 1-2

Jul 1/2007

5-00-10

Page 1

Mar 1/2004

5-10-00

Pages 1-2

Jul 3/2006

CHAPTER-SECTION-SUBJECT
05-Title
05-List of Effective Pages
05-Record of Temporary Revisions
05-Table of Contents

5-1 0-01

Pages 1-17

Jul 3/2006

5-11-00

Pages 1-3

Jul 1/2007

5-12-00

Jul 1/2007

5-12-0 1

Pages 1-2
Pages 1-7

5-1 2-02

Pages 1-6

Jul 3/2006

5-12-03
5-12-04

Pages 1-7
Pages 1-5

Jul 3/2006

5-1 2-05
5-12-06

Page 1

Jul 3/2006
Jul 3/2006

Page 1

April 1/2002

5-12-07

Page 1

Jul 3/2006

5-1 2-08

Page 1

April 1/2002

5-1 2-09

Jul 3/2006

5-12-10

Page 1
Page 1

5-12-11

Page 1

Jul 3/2006

5-12-13

Page 1
Page 1

April 1/2002

5-12-15
5-12-16

Page 1
Page 1

Jul 3/2006
Jul 3/2006

5-12-17

Page 1

Jul 3/2006

5-12-18

Page 1

Jul 3/2006

5-12-19

Page 1

Jul 3/2006

5-12-20

Page 1

Jul 3/2006

5-12-2 1

Page 1

Jul 3/2006

5-1 2-22

Page 1

Jul 3/2006

5-1 2-23

Page 1

Jul 3/2006

5-12-24

Page 1

Jul 3/2006

5-1 2-25

Page 1

Jul 3/2006

5-12-26

Page 1

Jul 3/2006

5-50-00

Pages 1-5

Jan 2/2006

5-12-14

Jul 3/2006

Jul 3/2006

Jul 3/2006

05 - LIST OF EFFECTIVE PAGES
Q Cessna Aircraft Company

Page 1 of 1
Jul 1/2007

RECORD OF TEMPORARY REVISIONS
Temporary Revision
Number

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...............................

5-00-00
5-00-00
5-00-00
5-00-00
5-00-00
5-00-00

COMPONENT TIME LIMITS............................
General...................................
Cessna-Supplied Replacement Time Limits ..................
Supplier-Supplied Replacement Time Limits ..................
PROGRESSIVE CARE PROGRAM ........................
General...................................
Procedure..................................
Inspection Terms and Guidelines .......................

5-11 -00 Page
5-11 -00 Page
5-11 -00 Page
5-11 -00 Page

1
1
1
2

5-12-00
5-12-00
5-12-00
5-12-00

1
1
2
2

INSPECTION OPERATION 1...........................
Description .................................
General Inspection Criteria..........................

5-12-01 Page 1
5-12-01 Page 1
5-12-01 Page 1

INSPECTION OPERATION 2 ...........................
Description .................................
General Inspection Criteria ..........................

5-12-02 Page 1
5-12-02 Page 1
5-12-02 Page 1

INSPECTION OPERATION 3 ...........................
Description .................................
General Inspection Criteria ..........................

5-12-03 Page 1
5-12-03 Page 1
5-12-03 Page 1

INSPECTION OPERATION 4 ...........................
Description .................................
General Inspection Criteria ..........................

5-12-04 Page 1
5-12-04 Page 1
5-12-04 Page 1

INSPECTION OPERATION S...........................
Description .................................
General Inspection Criteria ..........................

5-12-05 Page 1
5-12-05 Page 1
5-12-05 Page 1

PROGRESSIVE CARE ..............................
Operation 6.................................

5-12-06 Page 1
5-12-06 Page 1

INSPECTION OPERATION 7 ...........................
Description .................................
General Inspection Criteria ..........................

5-12-07 Page 1
5-12-07 Page 1
5-1 2-07 Page 1

PROGRESSIVE CARE ..............................
Operation 8.................................

5-12-08 Page 1
5-12-08 Page 1

© Cessna Aircraft Company

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05 - CONTENTS

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Page 1 of 3
Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
INSPECTION OPERATION 9 ...........................
Description ............
General Inspection Criteria ..........................

5-12-09 Page 1
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INSPECTION OPERATION 10...........................
Description .................................
General Inspection Criteria ..........................
INSPECTION OPERATION 11...........................
Description .................................
General Inspection Criteria ..........................

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PROGRESSIVE CARE ..............................
Operation 13 ................................
INSPECTION OPERATION 14...........................
Description .................................
General Inspection Criteria ..........................
INSPECTION OPERATION 15...........................
Description .................................
General Inspection Criteria ..........................

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INSPECTION OPERATION 16...........................
Description .................................
General Inspection Criteria ..........................

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INSPECTION OPERATION 17...........................
Description .................................
General Inspection Criteria ..........................

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INSPECTION OPERATION 18...........................
Description .................................
General Inspection Criteria ..........................
INSPECTION OPERATION 19...........................
Description .................................
General Inspection Criteria ..........................

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INSPECTION OPERATION 20...........................
Description .................................
General Inspection Criteria ..........................

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INSPECTION OPERATION 21...........................
Description .................................
General Inspection Criteria ..........................
INSPECTION OPERATION 22 ...........................
Description .................................
General Inspection Criteria ..........................

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INSPECTION OPERATION 23...........................
Description .................................
General Inspection Criteria ..........................

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INSPECTION OPERATION 24...........................
Description .................................
General Inspection Criteria ..........................

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INSPECTION OPERATION 25...........................
Description .................................
General Inspection Criteria ..........................

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05 - CONTENTS
© Cessna Aircraft Company

Page 2 of 3
Jul 1/2007

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 .......

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05 - CONTENTS
© Cessna Aircraft Company

Page 3of 3
Jul 1/2007

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
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 lifeor 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.
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.

E.

C Cessna Aircraft Company

-

General.

This section provides a general

5-00-00

Page 1

Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82
MAINTENANCE MANUAL

5.

General Inspection Terms and Guidelines
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).

NOTE:

A.

B.

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.
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.

I

(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

~
C.

~~~operating
at their operational voltage.

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).
Aircraft Radio Station License (Federal Communication Commission Form 556 if
3
transmitter is installed).
(b) To be carried in the airplane at all times:
Weight and Balance Data Sheets and associated papers (all copies of the Repair and
1
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
© Cessna Aircraft Company

Page 2
Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
AIRWORTHINESS LIMITATIONS - FAA APPROVED DATA
1.

Scope
A.

2.

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.

Airworthiness Limitations
A.

There are no airworthiness limitations associated with this airplane.

5-00-10
© Cessna Aircraft Company

Page 1

Mar 1/2004

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:

2.

3.

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.

Inspection Terms and Guidelines
A.

4.

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.

For inspection terms and guidelines, refer to Chapter 5, Time Limits/Maintenance Checks - General.

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
© Cessna Aircraft Company

Page 1
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

INTERVAL

OPERATION

A.

1, 2, 3, 4

Every 50 hours.

B.

1, 2, 3, 4

Every 100 hours.

C.

1, 2, 3, 4

Every 200 hours.

D.

5

(Not used)

E.
F.

Every 400 hours or 1 year, whichever occurs first.

7

Every 600 hours or 1 year, whichever occurs first.
(Not used)

G.

H.

9

Every 500 hours.

1.

10

Every 1000 hours.

J.

11

Every 2 years.

K.

(Not used)

L.

(Not used)

M.

14

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.

N.

15

Every 2000 hours.

O.

16

Every 1000 hours or 1 year, whichever occurs first.

P.

17

Every 12 calendar months.

Q.

18

Every 6 years.

R.

19

Every 12 years.

S.

20

Every 1 year.

T.

21

Every 3 years.
(Not used)

U.
V.

22

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.

W.

23

Every 100 hours or every one year, whichever occurs first.

X.

24

Every 100 hours, every annual inspection, every overhaul, and any
time fuel lines or clamps are serviced, removed or replaced.

Y.

25

First 600 hours and as defined by the manufacturer thereafter.

Z.

26

Every 1000 hours or 3 years, whichever occurs first.

5-10-00
© Cessna Aircraft Company

Page 2
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INSPECTION TIME LIMITS
1.

Inspection Items

REVISION
STATUS

ITEM
CODE
NUMBER

TASK

Added
Mar 1/05

110000

Interior Placards, Exterior Placards, B
Decals, Markings and Identification
Plates - Inspect for security of
installation and legibility. Refer to
Chapter 11, Placards and Markings Inspection/Check.

1,2,3,4

ALL

Deleted
Mar 1/04

112101

Deleted
Mar 1/04

113101
212001

Ventilation System - Inspect clamps,
hoses, and valves for condition and
security.

5

211

212002

Primary Flight Display (PFD) Fan, W
Multi-Function Display (MFD) Fan,
Deck Skin Fan, and Remote Avionics
Cooling Fan - Operational Check.
Refer to Chatper 21, Avionics Cooling
- Maintenance Practices.

23

220, 225

214001

Cold and Hot Air Hoses - Check B
condition, routing, and security.

2, 4

120

Revised
Dec 1/98

214002

Heater Components, Inlets, and B
Outlets - Inspect all lines, ducts,
clamps, seals, and gaskets for
condition, restriction, and security.

1,3

211

Revised
Jun 1/00

214003

Cabin Heat and Ventilation Controls - B
Check freedom of movement through
full travel. Check friction locks for
proper operation.

1

211

221001

Autopilot Rigging- Refer to AutopilotMaintenance Practices.

7

610

Added
Dec 1/98

221002

Autopilot Servo Capstan Assemblies. O
Check slip-clutch torque settings.
Refer to Autopilot - Maintenance
Practices.

16

610

Added
Dec 1/98

221003

Autopilot Servo Actuators. Inspect for O
evidence of corrosion and or buildup
of dirt or other particulate matter which
may interfere with servo operation.
Refer to Autopilot - Maintenance
Practices.

16

610

Revised
Mar 1/05

INTERVAL

D

F

OPERATION ZONE

5-10-01
© Cessna Aircraft Company

Page 1
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
REVISION
STATUS

ITEM
CODE
NUMBER

TASK

INTERVAL

OPERATION ZONE

231001

Communication Antennas and Cables
- Inspect for security of attachment,
connection, and condition.

C

3

210

235001

Microphones, Headsets, and Jacks - C
Inspect for cleanliness, security, and
evidence of damage.

1

211

235002

Microphone Push-To-Talk Switch B
- Clean the pilot's and copilot's
microphone switches.
Refer to
Chapter 23,
Communication
Maintenance Practices.

1, 3

222, 223

242001

Alternator, Mounting Bracket, and A
Electrical Connections - Check
Check
condition and security.
alternator belts for condition and
proper adjustment.
Check belt
tension.

1,2, 3, 4

120

Revised
Jun 3/06

243001

Main Battery - Examine the general B
condition and security. Complete a
check of the level of electrolyte. Refer
to Chapter 12, Battery - Servicing.

2, 4

310

Revised
Jun 3/06

243002

Main Battery Box and Cables - Clean
and remove any corrosion. Examine
the cables for routing, support, and
security of the connections.

B

2, 4

310

243003

General Airplane and System Wiring
- Inspect for proper routing, chafing,
broken or loose terminals, general
condition, broken or inadequate
clamps, and sharp bends in wiring.

C

1

210

243004

External Power Receptacle and C
Power Cables - Inspect for condition
and security.

2

120

243005

Standby Battery - Complete the S
Standby Battery Capacity Test. Refer
to Chapter 24, Standby Battery Maintenance Practices.

20

220

246001

Switch and Circuit Breaker Panel,
Terminal Blocks, and Junction Boxes
- Inspect wiring and terminals for
condition and security.

C

1

222

246002

Power Junction Box - Check
operation and condition.
Check
availability and condition of spare
fuse (if applicable).

B

1, 3

222

Added
4/03

Added
Mar 1/05

Revised
Jun 1/00

5-10-01
Cessna Aircraft Company

Page 2
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
REVISION
STATUS

ITEM
CODE
NUMBER

TASK

Added
Jul 3/06

246003

Alternator Control Unit - Complete J
the Over-voltage Protection Circuit
Test. Refer to Chapter 24, Alternator
Control Unit.

11

222

Revised
Mar 1/05

246101

Essential and Crossfeed Bus Diodes - S
Check for proper operation. Complete
the Essential and Crossfeed Bus
Diode Inspection. Refer to Chapter
24, Essential and Crossfeed Bus

20

224

INTERVAL

OPERATION ZONE

Diodes - Maintenance Practices.
Revised
Jul 3/06

Added
Mar 1/05

Revised
Jan 2/05

251001

Seats - Examine the seats to make
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.

B

1, 3

211

251002

Seat Tracks and Stops - Inspect seat
tracks for condition and security of
installation. Check seat track stops
for damage and correct location.
Inspect seat rails for cracks.

B

2, 4

230

251101

Restraint System, front and rear - B
Check belts for thinning, fraying,
cutting, broken stitches, or ultra-violet
deterioration.
Check system
hardware for security of installation.

1,3

211

251102

AMSAFE Aviation Inflatable Restraint
(AAIR) - Examine the restraint for dirt,
frayed edges, unserviceable stitching,
loose connections, and other wear.

S

20

211

252201

Upholstery, Headliner, Trim, and
Carpeting - Check condition and
security.

D

5

211

256001

Emergency Locator Transmitter - B
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.

1, 3

310

262001

Portable Hand Fire Extinguisher - B
Inspect for proper operating pressure,
condition, security of installation, and
servicing date.

1, 3

230

5-10-01
© Cessna Aircraft Companv

Page 3
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
REVISION
STATUS

ITEM
CODE
NUMBER

TASK

INTERVAL

OPERATION ZONE

Added
Dec 1/98

262002

Cockpit Mounted Halon Type Fire P
Extinguisher - Weigh bottle. Bottle
must be reserviced by qualified
individual if more than 2 ounces is
lost.

17

211

Added
Dec 1/98

262003

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.

R

19

211

Added
Dec 1/98

262004

Cockpit Mounted Halon Type Fire
Extinguishers - Empty, inspect for
damage, and recharge.

Q

18

211

Revised
Dec 1/98

271001

Aileron Controls - Check freedom
of movement and proper operation
through full travel.

B

1,3

120, 520,
620

271002

Ailerons and Cables - Check C
operation and security of stops.
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.

3

120, 520,
620

271003

Aileron Structure, Control Rods,
Hinges, Balance Weights, Bellcranks,
Linkage,
Bolts,
Pulleys,
and

B

1,3

520, 620

B

1, 3

520, 620

Pulley Brackets - Check condition,

operation, and security of attachment.

Revised
Dec 1/98

271004

Ailerons and Hinges - Check
condition, security, and operation

271005

Control Wheel Lock - Check general C
condition and operation.

1

222

271006

Control Linkage - Inspect pulleys, C
cables, bearings, and turnbuckles for
condition and security.

1

222, 223

272001

Rudder - Check internal surfaces for
corrosion, condition of fasteners, and
balance weight attachment.

3

340

C

5-1 0-01
Cessna Aircraft Company

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Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
REVISION
STATUS

ITEM
CODE
NUMBER

TASK

Revised
Jun 1/00

272002

Rudder - Inspect the rudder skins for B
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.

1, 3

340

Revised
Dec 1/98

272003

Rudder, Tips, Hinges, Stops, Clips
and Cable Attachment - Check
condition, security, and operation.

1, 3

340

272004

Rudder Pedals and Linkage - Check C
for general condition, proper rigging,
and operation. Check for security of
attachment.

1

230

Added
Dec 1/98

272005

Rudder Control - Check freedom
of movement and proper operation
through full travel.
Check rudder
stops for damage and security.

B

1, 3

340

Revised
Dec 1/98

273001

Elevator Control - Check freedom
of movement and proper operation
through full travel.

B

1,3

222, 223

Revised
Jun 1/00

273002

Elevator Control System - Inspect
pulleys, cables, sprockets, bearings,
chains, and turnbuckles for condition,
security, and operation. Check cables
for tension, routing, fraying, corrosion,
and turnbuckle safety

B

1, 3

222, 223

Revised
Dec 1/98

273003

Elevator, Hinges, Stops, and Cable
Attachment - Check condition,
security, and operation.

B

1, 3

320, 330

Added
Dec 1/98

273004

Elevator Downspring - Check
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.

B

1,3

310

273101

ElevatorTrim System - Check cables, B
push-pull rods, bellcranks, pulleys,
turnbuckles, fairleads, rub strips, etc.
for proper routing, condition, and
security.

1, 3

224, 240,
310

INTERVAL

B

OPERATION ZONE

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© Cessna Aircraft Company

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
INTERVAL

REVISION
STATUS

ITEM
CODE
NUMBER

TASK

Revised
Jun 1/00

273102

Elevator Trim Control and Indicator C
- Check freedom of movement and
proper operation through full travel.
Check pulleys, cables, sprockets,
bearings, chains, and turnbuckles
for condition and security. Check
electric trim controls for operation
Check cables for
as applicable.
tension, routing, fraying, corrosion,
and turnbuckle safety

273103

ElevatorTrimTaband Hinges-Check
condition, security, and operation.

Revised
Jul 3/06

273104

Elevator Trim Tab Actuator - Examine
Refer to
the free play limits.
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
Dec 1/98

273105

OPERATION ZONE

1

224, 240,
310

B

1, 3

224

B

1, 3

320

1

240

273106

Elevator Trim Tab Stop Blocks
Inspect for damage and security.

- C

Added
Jul 3/06

273107

Elevator Trim Tab Actuator - Remove,
clean, examine, and lubricate the
actuator.
Refer to Chapter 27,
Elevator Trim Control - Maintenance
Practices.

Z

26

320

Revised
Dec 1/98

275001

rollers,
Flaps - Check tracks,
and control rods for security of
attachment. Check rod end bearings
for corrosion. Check operation.

B

1,3

510, 610

275002

Wing Flap Control - Check operation
through full travel and observe
Flap Position indicator for proper
indication.

C

1

221

275003

Flap Structure, Linkage, Bellcranks,
Pulleys, and Pulley Brackets - Check
for condition, operation and security.

C

3

510, 610

275004

Flaps and Cables - Check cables
for proper tension, routing, fraying,
corrosion, and turnbuckle safety.
Check travel if cable tension requires
adjustment.

C

3

510, 610

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C Cessna Aircraft Comoanv

Page 6
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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
REVISION
STATUS

ITEM
CODE
NUMBER

TASK

Revised
Dec 1/98

275005

Flap Motor, Actuator, and Limit C
Switches - Check wiring and terminals
for condition and security. Check
actuator for condition and security.

3

610

Revised
Dec 1/98

275006

Flap Actuator Threads - Clean and
lubricate. Refer to Chapter 12-21-03.

B

1, 3

610

282001

Fuel System - Inspect plumbing
and components for mounting and
security.

B

1,3

510, 610

Revised
Dec 1/98

282002

Fuel Tank Vent Lines and Vent Valves
- Check vents for obstruction and
proper positioning. Check valves for
operation.

B

1,3

510, 610

Revised
Jun 1/00

282003

Fuel Selector Valve - Check controls
for detent in each position, security
of attachment, and for proper
placarding.

B

1, 3

224

Revised
Dec 1/98

282004

Integral Fuel Bays - Check for B
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.

1, 3

510, 610

Deleted
Aug 4/03

282005
282006

Fuel Selector - Using quick drain,
ensure no contamination exists.

B

1,3

224

282007

Fuel Strainer,

B

1, 3

510, 610

7

220

Controls

INTERVAL

-

Drain
Check

Valve,
freedom

and

OPERATION ZONE

of

movement, security, and proper
operation. Disassemble, flush, and
clean screen and bowl.
Revised
Mar 1/05

282008

Fuel Quantity Indicators - Examine for F
damage and security of installation.
Complete a fuel quantity calibration
check.
Refer to Chapter 28,
Fuel Storage and Distribution Maintenance Practices.

5-10-01
© Cessna Aircraft Company

Page 7
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
REVISION
STATUS

ITEM
CODE
NUMBER

TASK

Revised
Jan 2/06

282009

Integral Fuel Bays - Drain the I
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).

10

510, 610

Revised
Jun 1/00

282010

Auxiliary (Electric) Fuel Pump - B
Check pump and fittings for condition,
operation, security.

2, 4

120

311001

Instruments - Check general condition
and markings for legibility.

B

1, 3

220

311003

Instrument Lines, Fittings, Ducting,
and Instrument Panel Wiring - Check
for proper routing, support, and
security of attachment.

C

1

220

Revised
Jun 1/00

321001

Main Landing Gear Wheel Fairings
and Brake Fairings - Check for cracks,
dents, and condition of paint.

B

2, 4

721,722

Revised
Mar 1/05

321002

Main Gear Spring Assemblies - B
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.

2,4

721,722

321003

Main Landing Gear Attachment
Structure - Check for damage, cracks,
loose rivets, bolts and nuts and
security of attachment.

B

2, 4

721,722

322001

Nose Gear - Inspect torque links,
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.

B

2, 4

720

Nose Landing Gear Wheel Fairings

B

2, 4

720

Deleted
Mar 1/05

INTERVAL

OPERATION ZONE

311002

322002

- Check for cracks,

dents,

and

condition of paint.

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© Cessna Aircraft Company

Page 8
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
REVISION
STATUS

Revised
Dec 1/98

Revised
Dec 1/98

Revised
Jul 3/06

ITEM
CODE
NUMBER

TASK

322003

Nose Gear Fork - Inspect for cracks, C
general condition, and security of
attachment.

4

720

322004

Nose Gear Attachment Structure - B
Inspect for cracks, corrosion, or other
damage and security of attachment.

2, 4

720

324001

Brakes - Test toe brakes and parking
brake for proper operation.

B

2, 4

230

324002

Brakes, Master Cylinders, and B
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.

2, 4

224, 230

324003

Brake Lines, Wheel Cylinders, Hoses,
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.

D

5

721, 722

324004

Tires - Check tread wear and general
condition. Check for proper inflation.

B

2, 4

720, 721,
722

324005

Wheels, Brake Discs, and Linings
- Inspect for wear, cracks, warps,
dents, or other damage. Check wheel
through-bolts and nuts for looseness.

B

2, 4

721,722

324006

Wheel Bearings - Clean, inspect and
lube.

B

4

720, 721,
722

325001

Nose Gear Steering Mechanism - C
Check for wear, security, and proper
rigging.

4

720

331001

Instrument and Cabin Lights - Check
operation, condition of lens, and
security of attachment.

B

1, 3

220, 211,
221

334001

Navigation, Beacon, Strobe, and
Landing Lights - Check operation,
condition of lens, and security of
attachment.

B

1, 3

340, 520,
620

341101

Static System - Inspect for security of C
installation, cleanliness, and evidence
of damage.

3

210

341102

Pitot and Static System - Examine in J
accordance with 14 CFR Part 91.411.

11

220

INTERVAL

OPERATION ZONE

5-10-01
© Cessna Aircraft Company

Page 9
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INTERVAL

OPERATION ZONE

ITEM
CODE
NUMBER

TASK

341103

Pitot Tube and Stall Warning Vane - A
Check for condition and obstructions
and verify operation of anti-ice heat.

1,2, 3, 4

510

342101

Magnetic Compass - Inspect for C
security of installation, cleanliness,
and evidence of damage.

1

225

Revised
Dec 1/98

342102

Magnetic Compass - Calibrate.

14

220

Revised
Dec 1/98

345001

Instrument Panel Mounted Avionics C
Audio Panel,
Units (Including
ADF, GPS,
VHF Nav/Com(s),
Compass System,
Transponder,
Multi-function Display, and Primary
Flight Display) and Remote Mounted
Avionics Components. Inspect for
deterioration, cracks, and security of
Inspect
instrument panel mounts.
for security of electrical connections,
condition, and security of wire routing.

1

225

345002

Avionics Operating Controls - Inspect C
for security and proper operation of
controls and switches and ensure
that all digital segments will illuminate
properly.

1

225

C

1

220, 225

345004

Navigation Antennas and Cables - C
Inspect for security of attachment,
connection, and condition.

1

310

Added
Nov 1/00

351001

Oxygen System (if applicable) - C
Inspect masks, hoses, lines, and
fittings for condition, routing, and
support. Test operation and check for
leaks.

1

211

Added
Nov 1/00

351002

Oxygen Cylinder (if applicable) T
- Inspect for condition, check
hydrostatic test date and perform
hydrostatic test, if due.

21

211

371001

Vacuum System - Inspect
condition and security.

for

B

2, 4

120

371002

Vacuum Pumps - Check for condition
Check vacuum
and security.
system breather line for obstructions,
condition, and security.

B

2, 4

120

REVISION
STATUS

345003

M

Navigation Indicators, Controls, and
Components - Inspect for condition

and security.

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© Cessna Aircraft Company

Page 10
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
REVISION
STATUS

ITEM
CODE
NUMBER

TASK

371003

Vacuum System Hoses - Inspect for B
hardness, deterioration, looseness, or
collapsed hoses.

2, 4

120

Revised
Dec 1/98

371004

Gyro Filter - Inspect for damage,
deterioration and contamination.
Clean or replace if required.

2, 4

120

Deleted
Aug 4/03

371005

Revised
Jan 2/06

371006

22

120

25

120

INTERVAL

B

Vacuum Manifold Check Valve V
- 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

OPERATION ZONE

for the

removal and installation of the check
valve.
Added
Jan 2/06

371007

Do an inspection of the wear indicator
ports on the vacuum pumps described
in Tempest Service Letter 004.

521001

Doors - Inspect general condition. B
Check latches, hinges, and seals for
condition, operation, and security of
attachment.

1,3

210

531001

Fuselage Surface - Inspect for skin
damage, loose rivets, condition of
paint, and check pitot-static ports and
drain holes for obstruction. Inspect
covers and fairings for security.

1,3

210

531002

Firewall Structure - Inspect for C
wrinkles, damage, cracks, sheared
rivets, etc. Check cowl shock mounts
for condition and security.

2

120

531003

Internal Fuselage Structure - Inspect C
bulkheads, doorposts, stringers,
doublers, and skins for corrosion,
cracks, buckles, and loose rivets,
bolts and nuts.

1

211

Y

B

5-10-01
© Cessna Aircraft Company

Page 11
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

REVISION
STATUS

ITEM
CODE
NUMBER

TASK

INTERVAL

OPERATION ZONE

Revised
Dec 1/98

551001

Horizontal Stabilizer and Tailcone
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.

B

1, 3

320, 330

Revised
Dec 1/98

551002

Horizontal Stabilizer and Tips - B
Inspect externally for skin damage
and condition of paint.

1, 3

320, 330

Revised
Dec 1/98

553001

Vertical Stabilizer Fin - Inspect B
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.

1, 3

340

Revised
Dec 1/98

553002

Vertical Stabilizer Fin and Tailcone
- Inspect externally for skin damage
and condition of paint.

B

1, 3

340

561001

Windows and Windshield - Inspect
general condition. Check latches,
hinges, and seals for condition,
operation, and security of attachment.

B

1, 3

210

571001

Wing Surfaces and Tips - Inspect
for skin damage, loose rivets, and
condition of paint.

B

1, 3

510, 520,
610, 620

571002

Wing Struts and Strut Fairings - Check B
for dents, cracks, loose screws and
rivets, and condition of paint.

1, 3

510, 610

571003

Wing Access Plates - Check for C
damage and security of installation.

3

510, 520,
610, 620

571004

Wing Spar and Wing Strut Fittings C
- Check for evidence of wear.
Check attach bolts for indications of
looseness and retorque as required.

3

510, 520,
610, 620

571005

Wing Structure - Inspect spars,
ribs, skins, and stringers for cracks,
wrinkles, loose rivets, corrosion, or
other damage.

C

3

510, 520,
610, 620

611001

Spinner - Check general condition
and attachment.

A

1, 2, 3, 4

110

611002

Spinner and Spinner Bulkhead - B
Remove spinner, wash, and inspect
for cracks and fractures.

2, 4

110

Revised
Jan 3/05

5-10-01
© Cessna Aircraft Company

Page 12
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

REVISION
STATUS

ITEM
CODE
NUMBER

TASK

INTERVAL

OPERATION ZONE

611003

Propeller Blades - Inspect for cracks,
dents, nicks, scratches, erosion,
corrosion, or other damage.

A

1,2, 3,4

110

611004

Propeller Hub
condition.

C

2

110

611005

Propeller Mounting security of installation.

for

A

1,2,3,4

110

611006

Propeller Mounting Bolts - Inspect
mounting bolts and safety wire
for signs of looseness.
Retorque
mounting bolts as required.

C

2

110

Added
Nov 1/00

611007

Propeller Heat Slip Rings, Brushes,
and Boots - Inspect for condition, and
security. Perform operational check.

A

1,2,3,4

110

Added
Dec 1/98

612001

Propeller Governor and Control - A
Inspect for oil and grease leaks. If
leakage is evident, refer to McCauley
Service Manual.

1,2,3,4

110

Revised
Aug 4/03

612002

Propeller Governor and Control - C
Check for security and operation of
controls. Maximum linear freeplay is
0.050 inch.

2

110

Added
Dec 15/01

612003

Propeller Control Cable - Nonrepairable 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.

N

15

120,210

Added
Nov 1/00

710001

Turbocharger
(if
applicable)
mounting
turbocharger
Inspect
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.

A

1,2,3,4

120

Revised
Aug 4/03

710002

Turbocharger
(if applicable)
C
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.

2

120

- Check

general

Check

5-10-01
© Cessna Aircraft Company

Page 13
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
REVISION
STATUS

ITEM
CODE
NUMBER

Revised
Dec 1/98

711001

Revised
Jun 1/00

TASK

INTERVAL

OPERATION ZONE

Cowling and Cowl Flaps - Inspect

A

1,2,3,4

120

C

2

120

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.
712001

Engine Shock Mounts, Engine Mount
Structure, and Ground Straps - Check
condition, security, and alignment.

716001

Alternate Induction Air System - A
Check for obstructions, operation,
and security.

1,2,3,4

120

716002

Induction System - Check security of
clamps, tubes, and ducting. Inspect
for evidence of leakage.

A

1,2,3,4

120

Induction Airbox, Valves, Doors, and

B

2, 4

120

A

2, 4

120

716003

Controls - 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 damage and

service.

Added
Jan 2/06

720000

Fuel line (Stainless steel tube
assembly) and support clamp
inspection and installation.
Refer
to Lycoming Service Bulletin Number
342E or later version.

X

24

120

722001

Engine - Inspect for evidence of oil
and fuel leaks. Wash engine and
check for security of accessories.

A

1,2,3,4

120

722002

Crankcase, Oil Sump, and Accessory

B

2, 4

120

1,2,3,4

120

Section - Inspect for cracks and

evidence of oil leakage. Check bolts
and nuts for looseness and retorque
Check crankcase
as necessary.
breather lines for obstructions,
security, and general condition.
722003

Hoses, Metal Lines, and Fittings A
- Inspect for signs of oil and fuel
leaks. Check for abrasions, chafing,
security, proper routing and support
and for evidence of deterioration.

5-10-01
© Cessna Aircraft Company

Page 14
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

.

REVISION
STATUS

ITEM
CODE
NUMBER

TASK

723001

Engine Cylinders, Rocker Box B
Covers, and Pushrod Housings Check for fin damage, cracks, oil
leakage, security of attachment, and
general condition.

2, 4

120

Engine Metal Lines, Hoses, Clamps,

2

120

723002

and

INTERVAL

Fittings

- Check for

C

OPERATION ZONE

leaks,

condition, and security. Check for
proper routing and support.

Revised
Jan 2/06

723003

Engine Baffles and Seals - Check A
condition and security of attachment.

1,2, 3, 4

120

723004

Cylinder Compression - Complete B
a differential compression test. If
there is weak cylinder compression,
refer to Chapter 71,
Engine

2, 4

120

-Troubleshooting,

for

further

procedures.
730001

Engine-Driven Fuel Pump - Check B
for evidence of leakage, security of
attachment, and general condition.

2, 4

120

730002

Fuel Injection System - Check system B
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.

2, 4

120

Added
Jun 18/01

730003

Idle and Mixture - Run the airplane B
engine to determine satisfactory
performance. If required, adjust the
idle rpm and fuel mixture. Refer to
Chapter 73, Fuel Injection Systems Maintenance Practices.

2, 4

120

Revised
Jan 2/06

741001

Magnetos - Examine the external B
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

2, 4

120

9

120

- Maintenance Practices.

Revised
Jul 3/06

741002

Magnetos - Clean, examine, and H
adjust as necessary. Do the 500-hour
inspection in accordance with the
Slick 4300/6300 Series Magneto
Maintenance and Overhaul Manual.

5-10-01
© Cessna Aircraft Company

Page 15
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

ITEM
CODE
NUMBER

TASK

INTERVAL

OPERATION ZONE

742001

Ignition Harness and Insulators
proper
routing,
Check
for
ar nd condition of
deterioration,
terminals.

B

2, 4

120

742002

Spark Plugs - Remove, clean,
analyze, test, gap, and rotate top
plugs to bottom and bottom plugs to
top.

B

2,4

120

743001

Ignition Switch and Electrical Harness
- Inspect for damage, condition, and
security.

B

2, 4

120

Revised
Jun 1/00

743002

Inspect and lubricate ACS brand
Refer to Chapter
ignition switch.
74, Ignition System - Maintenance
Practices.

N

15

224

Revised
Jan 2/06

761001

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.

B

1,2,3,4

120,225

Revised
Dec 1/98

781001

Exhaust System - Inspect for cracks
and security. Special check in area
of heat exchanger. Refer to Chapter
78, Exhaust system - Maintenance
Practices.

A

1,2,3,4

120

Added
Nov 1/00

781002

(turbocharged
Exhaust
System
engine) - Inspect couplings, seals,
clamps, and expansion joints for
Special check in area of
cracks.
heat exchanger. Refer to Chapter
78, Exhaust System - Maintenance
Practices.
Note: This inspection
is specifically required for German
(LBA) certification.

A

1, 2, 3,4

120

REVISION
STATUS

5-10-01
© Cessna Aircraft Company

Page 16
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
REVISION
STATUS

ITEM
CODE
NUMBER

TASK

Revised
Jun 1/00

791001

Engine Oil - Drain oil sump and oil A
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.

1,2,3,4

120

792001

Oil Cooler - Check for obstructions,
leaks, and security of attachment.

A

1,2,3,4

120

Revised
Jun 1/00

801001

Starter and Electrical Connections
- Check security and condition of
starter, electrical connection, and
cable.

B

2,4

120

Added
Apr 1/02

801002

Bendix Drive Starter Assembly - A
Clean and lubricate starter drive
assembly.

1,2,3,4

120

INTERVAL

OPERATION ZONE

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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.

B.

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 10 years.
(8) 2000031-12-201 Restraint Assembly, Left Rear Seat - Replace every 10 years.
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 10 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.

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F.

(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.
Chapter 79 (Oil).
(1) 83278 Oil Pressure Switch - Replace every 3000 hours.
NOTE:

3.

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.

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 10 Years if not overhauled.

C.

Chapter 37 (Vacuum).
(1) 1H5-25 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 100 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
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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.

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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,
100-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 -

Has all 50-hour inspection items, and the 100- or 200-hour inspection items
contained in the fuselage area.

Operation 2 -

Has all 50-hour inspection items, and the 100- or 200-hour inspection items
contained in the engine compartment area.

Operation 3 -

Has all 50-hour inspection items, and the 100- or 200-hour inspection items
contained in the wing.

Operation 4 -

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.

Operation 5 Operation 6 -

Has all items that must have an inspection at the first 100 hours, and each 500
hours after (NOT CURRENTLY USED).

Operation 7 -

Has all 600-hour or 1-year inspection items, whichever occur first.

Operation 8 -

Has all 1000-hour or 3-year inspection items, whichever occur first (NOT
CURRENTLY USED).

Ope ration 9 -

Has all 500-hour inspection items.

Operation 10-

Has all 1000-hour inspection items.

Operation 11

-

Has all 2-year inspection items.

Operation 12

-

Has all items that must have an inspection at the first 5 years, and each 12 months
after, until replacement at 10 years (NOT CURRENTLY USED).

Operation 13

-

Has all 50-hour or 4-month inspection items, whichever occur first (NOT
CURRENTLY USED).

Operation 14

-

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.

Operation 15

-

Has all 2000-hour inspection items.

Operation 16

-

Has all 1000-hour or 1-year inspection items, whichever occur first.

Operation 17

-

Has all 12-month inspection items.

Operation 18 - Has all 6-year inspection items.
Operation 19

-

Has all 12-year inspection items.

Operation 20

-

Has all 1-year inspection items.

Operation 21

-

Has all 3-year inspection items.

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I
2.

-

Operation 23

-

Operation 24

-

Operation 25

-

First 600 hours and as defined by the manufacturer thereafter.

Operation 26

-

Everyl1000hours or 3years, whichever occurs first.

Has all 100-hour or 1-year inspection items, whichever occur first.
Every 100 hours, every annual inspection, every overhaul, and any time fuel
lines or clamps are serviced, removed or replaced.

Procedure
A.
B.
C.

3.

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 22

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.
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.
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 10 hours (if time-controlled), or by 30 days (if datecontrolled) 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 10 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.

Inspection Terms and Guidelines
A.

For inspection terms and guidelines, refer to Time Limits/Maintenance Checks - General.

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MAINTENANCE MANUAL
INSPECTION OPERATION 1
Date:
Registration Number:
Serial Number:
Total Time:
1.

Description
A.

B.

C.
2.

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.
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.
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.

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

TASK

ZONE

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
installation.

for security of

110

611007

Propeller Heat Slip Rings, Brushes, and Boots
- Inspect for condition, and security.
Perform
operational check.

110

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
Connections - Check condition and security. Check
alternator belts for condition and proper adjustment.
Check belt tension.

- Check

MECH INSP

REMARKS

120

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ITEM CODE
NUMBER

TASK

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,
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.

120

716001

Alternate Induction Air System - Check for
obstructions, operation, and security.

120

716002

Induction System - Check security of clamps, tubes,
and ducting. Inspect for evidence of leakage.

120

722001

Engine - Inspect for evidence of oil and fuel leaks.
Wash engine and check for security of accessories.

120

722003

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.

120

723003

Engine Baffles and Seals - Check condition and
security of attachment.

120

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
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
security of attachment.

120

801002

Bendix Drive Starter Assembly - Clean and lubricate
starter drive assembly.

120

ZONE

MECH INSP REMARKS

120

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ITEM CODE
NUMBER

TASK

ZONE

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.

MECH INSP

REMARKS

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ZONE

ITEM CODE
NUMBER

TASK

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.
Instrument Lines, Fittings, Ducting, and Instrument 220
Panel Wiring - Check for proper routing, support, and
security of attachment.
Instrument and Cabin Lights - Check operation, 220, 211,
221
condition of lens, and security of attachment.

311003

331001
345003
275002

246001

246002

271005
235002

271006
273001

MECH INSP

REMARKS

Navigation Indicators, Controls, and Components - 220, 225
Inspect for condition and security.
Wing Flap Control - Check operation through full 221
travel and observe Flap Position indicator for proper
indication.
Switch and Circuit Breaker Panel, Terminal Blocks, 222
and Junction Boxes - Inspect wiring and terminals for
condition and security.
Power Junction Box - Check operation and 222
condition. Check availability and condition of spare
fuse (if applicable).
Control Wheel Lock - Check general condition and 222
operation.
Microphone Push-To-Talk Switch - Clean the pilot's 222, 223
and copilot's microphone switches. Refer to Chapter
23, Communication - Maintenance Practices.
Control Linkage - Inspect pulleys, cables, bearings, 222, 223
and turnbuckles for condition and security.
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,
security, and operation.

282003

Fuel Selector Valve - Check controls for detent in 224
each position, security of attachment, and for proper
placarding.

224

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MAINTENANCE MANUAL
ITEM CODE
NUMBER

TASK

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
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.

ZONE

MECH INSP

REMARKS

240

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ITEM CODE
NUMBER

TASK

ZONE

273104

Elevator Trim Tab Actuator - Examine 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.

320

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
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.

340

272003

Rudder, Tips, Hinges, Stops, Clips and Cable
Attachment - Check condition, security, and
operation.

340

272005

Rudder Control - Check freedom of movement and
proper operation through full travel. Check rudder
stops for damage and security.

340

553001

Vertical Stabilizer Fin - Inspect bulkheads, spars, 340
ribs, and skins for cracks, wrinkles, loose rivets,
Inspect vertical
corrosion, or other damage.
Retorque
stabilizer attach bolts for looseness.
as necessary. Check security of inspection covers,
fairings, and tip.

553002

Vertical Stabilizer Fin and Tailcone - Inspect
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,
loose rivets, and condition of paint.

MECH INSP

REMARKS

340

510, 520,
610, 620

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ITEM CODE
NUMBER

TASK

ZONE

275001

Flaps - Check tracks, rollers, and control rods for
security of attachment. Check rod end bearings for
corrosion. Check operation.

510, 610

282001

Fuel System - Inspect plumbing and components for
mounting and security.

510, 610

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
Weights, Bellcranks, Linkage, Bolts, Pulleys, and
Pulley Brackets - Check condition, operation, and
security of attachment.

520, 620

271004

Ailerons and Hinges - Check condition, security, and
operation

520, 620

275006

Flap Actuator Threads - Clean and lubricate. Refer
to Chapter 12-21-03.

610

110000

Interior Placards, Exterior Placards, Decals,
Markings and Identification Plates - Inspect for
security of installation and legibility. Refer to Chapter
11, Placards and Markings - Inspection/Check.

ALL

MECH INSP REMARKS

*** End of Operation 1 Inspection Items ***

5-12-01
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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INSPECTION OPERATION 2
Date:
Registration Number:
Serial Number:
Total Time:
1.

2.

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.

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

TASK

ZONE

611001

Spinner - Check general condition and attachment.

110

611002

Spinner and Spinner Bulkhead - Remove spinner,
wash, and inspect for cracks and fractures.

110

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
installation.

for security of

110

611006

Propeller Mounting Bolts - Inspect mounting bolts
and safety wire for signs of looseness. Retorque
mounting bolts as required.

110

611007

Propeller Heat Slip Rings, Brushes, and Boots
- Inspect for condition, and security.
Perform
operational check.

110

- Check

MECH INSP REMARKS

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
ZONE

ITEM CODE
NUMBER

TASK

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
and operation of controls. Maximum linear freeplay
is 0.050 inch.

110

214001

Cold and Hot Air Hoses - Check condition, routing,
and security.

120

242001

Alternator, Mounting Bracket, and Electrical
Connections - Check condition and security. Check
alternator belts for condition and proper adjustment.
Check belt tension.

120

243004

External Power Receptacle and Power Cables - 120
Inspect for condition and security.

282010

Auxiliary (Electric) Fuel Pump - Check pump and
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,
deterioration, looseness, or collapsed hoses.

120

371004

Gyro Filter - Inspect for damage, deterioration and
contamination. Clean or replace if required.

120

531002

Firewall Structure - Inspect for wrinkles, damage,
cracks, sheared rivets, etc. Check cowl shock
mounts for condition and security.

120

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
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.

120

711001

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.

120

MECH INSP

REMARKS

120

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
ITEM CODE
NUMBER

TASK

ZONE

712001

Engine Shock Mounts, Engine Mount Structure,
and Ground Straps - Check condition, security, and
alignment.

120

716001

Alternate Induction Air System - Check for
obstructions, operation, and security.

120

716002

Induction System - Check security of clamps, tubes,
and ducting. Inspect for evidence of leakage.

120

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
damage and service.

120

722001

Engine - Inspect for evidence of oil and fuel leaks.
Wash engine and check for security of accessories.

120

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
of oil and fuel leaks. Check for abrasions, chafing,
security, proper routing and support and for evidence
of deterioration.

120

723001

Engine Cylinders, Rocker Box Covers, and Pushrod
Housings - Check for fin damage, cracks, oil
leakage, security of attachment, and general
condition.

120

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
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.

MECH INSP REMARKS

120

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
ITEM CODE
NUMBER

TASK

ZONE

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
routing, deterioration, and condition of terminals.

120

742002

Spark Plugs - Remove, clean, analyze, test, gap,
and rotate top plugs to bottom and bottom plugs to
top.

120

743001

Ignition Switch and Electrical Harness - Inspect for
damage, condition, and security.

120

781001

Exhaust System - Inspect for cracks and security.
Special check in area of heat exchanger. Refer
to Chapter 78, Exhaust system - Maintenance
Practices.

120

781002

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.

120

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
security of attachment.

120

801001

Starter and Electrical Connections - Check security
and condition of starter, electrical connection, and
cable.

120

801002

Bendix Drive Starter Assembly - Clean and lubricate
starter drive assembly.

120

MECH INSP

REMARKS

5-12-02
© Cessna Aircraft Company

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
ITEM CODE
NUMBER

TASK

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
- 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
operation.

230

243001

Main Battery - Examine the general condition and
security. Complete a check of the level of electrolyte.
Refer to Chapter 12, Battery - Servicing.

310

243002

Main Battery Box and Cables - Clean and remove
any corrosion. Examine the cables for routing,
support, and security of the connections.

310

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,
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.
Check for proper inflation.

720, 721,
722

321003

Main Landing Gear Attachment Structure - Check
for damage, cracks, loose rivets, bolts and nuts and
security of attachment.

721, 722

ZONE

MECH INSP

REMARKS

224,230

720

5-12-02
© Cessna Aircraft Company

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
ZONE

ITEM CODE
NUMBER

TASK

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,
Markings and Identification Plates - Inspect for
security of installation and legibility. Refer to Chapter
11, Placards and Markings - Inspection/Check.

MECH INSP

REMARKS

ALL

***End of Operation 2 Inspection Items ***

5-12-02
© Cessna Aircraft Company

Page 6
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INSPECTION OPERATION 3
Date:
Registration Number:
Serial Number:
Total Time:
1.

2.

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.

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

TASK

ZONE

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
installation.

- Check for security of

110

611007

Propeller Heat Slip Rings, Brushes, and Boots
- Inspect for condition, and security.
Perform
operational check.

110

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
Connections - Check condition and security. Check
alternator belts for condition and proper adjustment.
Check belt tension.

MECH INSP

REMARKS

120

5-12-03
© Cessna Aircraft Company

Page 1
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
ZONE

ITEM CODE
NUMBER

TASK

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,
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.

120

716001

Alternate Induction Air System - Check for
obstructions, operation, and security.

120

716002

Induction System - Check security of clamps, tubes,
and ducting. Inspect for evidence of leakage.

120

722001

Engine - Inspect for evidence of oil and fuel leaks.
Wash engine and check for security of accessories.

120

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.
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
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.

120

792001

Oil Cooler - Check for obstructions, leaks, and
security of attachment.

120

801002

Bendix Drive Starter Assembly - Clean and lubricate
starter drive assembly.

120

MECH INSP REMARKS

120

5-12-03
© Cessna Aircraft Company

Page 2
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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
ITEM CODE
NUMBER

TASK

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.

ZONE

MECH INSP

REMARKS

5-12-03
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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
ZONE

ITEM CODE
NUMBER

TASK

311001

Instruments - Check general condition and markings 220
for legibility.

331001

Instrument and Cabin Lights - Check operation, 220, 211,
221
condition of lens, and security of attachment.

246002

Power Junction Box - Check operation and
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
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,
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,
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.

MECH INSP

REMARKS

222

222, 223

224

310

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
ITEM CODE
NUMBER

TASK

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.
Horizontal Stabilizer and Tips - Inspect externally for 320, 330
skin damage and condition of paint.

551002

ZONE

272001

Rudder - Check internal surfaces for corrosion,
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
Attachment - Check condition, security, and
operation.

340

272005

Rudder Control - Check freedom of movement and
proper operation through full travel. Check rudder
stops for damage and security.

340

553001

Vertical Stabilizer Fin - Inspect 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.

340

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.

MECH INSP

REMARKS

340

5-12-03
© Cessna Aircraft Company

Page 5
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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
ITEM CODE
NUMBER

TASK

ZONE

571001

Wing Surfaces and Tips - Inspect for skin damage,
loose rivets, and condition of paint.

510, 520,
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
stringers for cracks, wrinkles, loose rivets, corrosion,
or other damage.

510, 520,
610, 620

275001

Flaps - Check tracks, rollers, and control rods for
security of attachment. Check rod end bearings for
corrosion. Check operation.

510, 610

275003

Flap Structure, Linkage, Bellcranks, Pulleys, and
Pulley Brackets - Check for condition, operation and
security.

510, 610

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
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,
cracks, loose screws and rivets, and condition of
paint.

510, 610

271003

Aileron Structure, Control Rods, Hinges, Balance
Weights, Bellcranks, Linkage, Bolts, Pulleys, and
Pulley Brackets - Check condition, operation, and
security of attachment.

520, 620

271004

Ailerons and Hinges - Check condition, security, and
operation

520, 620

275005

Flap Motor, Actuator, and Limit Switches - Check 610
wiring and terminals for condition and security.
Check actuator for condition and security.

MECH INSP REMARKS

510, 610

5-12-03
© Cessna Aircraft Company

Page 6
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
ITEM CODE
NUMBER

TASK

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.

ZONE

MECH INSP

REMARKS

*** End of Operation 3 Inspection Items ***

5-12-03
© Cessna Aircraft Company

Page 7
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INSPECTION OPERATION 4
Date:

Registration Number:
Serial Number:
Total Time:
1.

Description
A.

B.

C.
2.

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.
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.
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.

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

TASK

ZONE

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
installation.

- Check for security of

110

611007

Propeller Heat Slip Rings, Brushes, and Boots
- Inspect for condition, and security.
Perform
operational check.

110

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,
and security.

MECH INSP

REMARKS

120

5-12-04
© Cessna Aircraft Company

Page 1
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
ITEM CODE
NUMBER

TASK

ZONE

242001

Alternator, Mounting Bracket, and Electrical
Connections - Check condition and security. Check
alternator belts for condition and proper adjustment.
Check belt tension.

120

282010

Auxiliary (Electric) Fuel Pump - Check pump and
fittings for condition, operation, security.

120

371001

Vacuum System - Inspect for condition and security.

120

371002

Vacuum Pumps - Check for condition and security.
Check vacuum system breather line for obstructions,
condition, and security.

120

371003

Vacuum System Hoses - Inspect for hardness,
deterioration, looseness, or collapsed hoses.

120

371004

Gyro Filter - Inspect for damage, deterioration and
contamination. Clean or replace if required.

120

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,
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.

120

716001

Alternate Induction Air System - Check for
obstructions, operation, and security.

120

716002

Induction System - Check security of clamps, tubes,
and ducting. Inspect for evidence of leakage.

120

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
damage and service.

120

722001

Engine - Inspect for evidence of oil and fuel leaks.
Wash engine and check for security of accessories.

120

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.

MECH INSP REMARKS

5-12-04
© Cessna Aircraft Company

Page 2
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
ITEM CODE
NUMBER

TASK

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
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
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
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.

120

742001

Ignition Harness and Insulators - Check for proper
routing, deterioration, and condition of terminals.

120

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
damage, condition, and security.

120

781001

Exhaust System - Inspect for cracks and security.
Special check in area of heat exchanger. Refer
to Chapter 78, Exhaust system - Maintenance
Practices.

120

ZONE

MECH INSP

REMARKS

120

120

5-12-04
© Cessna Aircraft Company

Page 3
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
ITEM CODE
NUMBER

TASK

ZONE

781002

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.

120

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
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
starter drive assembly.

120

761001

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.

120, 225

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
operation.

230

243001

Main Battery - Examine the general condition and
security. Complete a check of the level of electrolyte.
Refer to Chapter 12, Battery - Servicing.

310

243002

Main Battery Box and Cables - Clean and remove
any corrosion. Examine the cables for routing,
support, and security of the connections.

310

341103

Pitot Tube and Stall Warning Vane - Check for 510
condition and obstructions and verify operation of
anti-ice heat.

MECH INSP

REMARKS

120

5-12-04
© Cessna Aircraft Company

Page 4
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
ITEM CODE
NUMBER

TASK

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.
Check for proper inflation.

720, 721,
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,
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.

ZONE

MECH INSP

REMARKS

721, 722

*** End of Operation 4 Inspection Items ***

5-12-04
© Cessna Aircraft Company

Page 5
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INSPECTION OPERATION 5
Date:
Registration Number:
Serial Number:
Total Time:
1.

2.

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.

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

TASK

ZONE

212001

Ventilation System - Inspect clamps, hoses, and
valves for condition and security.

211

252201

Upholstery, Headliner, Trim, and Carpeting - Check
condition and security.

211

324003

Brake Lines, Wheel Cylinders, Hoses,
Fittings - Check for leaks, condition,
and hoses for bulges and deterioration.
lines and hoses for proper routing and

721, 722

Clamps, and
and security
Check brake
support.

MECH INSP REMARKS

*** End of Operation 5 Inspection Items **

5-12-05
© Cessna Aircraft Company

Page 1
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.

© Cessna Aircraft Company

5-12-06 Page 1
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INSPECTION OPERATION 7
Date:
Registration Number:
Serial Number:
Total Time:
1.

2.

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.

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

TASK

ZONE

282008

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.

220

221001

Autopilot Rigging - Refer to Autopilot - Maintenance
Practices.

610

MECH INSP

REMARKS

*** End of Operation 7 Inspection Items ***

5-12-07
© Cessna Aircraft Company

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 INTHIS SECTION.

5-12-08
© Cessna Aircraft Company

Page 1

April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INSPECTION OPERATION 9
Date:
Registration Number:
Serial Number:
Total Time:
1.

2.

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.

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

TASK

ZONE

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.

MECH INSP

REMARKS

***End of Operation 9 Inspection Items ***

5-12-09
© Cessna Aircraft Company

Page 1
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INSPECTION OPERATION 10
Date:
Registration Number:
Serial Number:
Total Time:
1.

2.

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.

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

TASK

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).

ZONE

MECH INSP

REMARKS

***End of Operation 10 Inspection Items ***

5-12-10
© Cessna Aircraft Company

Page 1
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INSPECTION OPERATION 11
Date:
Registration Number:
Serial Number:
Total Time:
1.

2.

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.

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

TASK

ZONE

341102

Pitot and Static System - Examine in accordance
with 14 CFR Part 91.411.

220

246003

Alternator Control Unit - Complete the Over-voltage 222
Protection Circuit Test.
Refer to Chapter 24,
Alternator Control Unit.

MECH INSP REMARKS

*** End of Operation 11 Inspection Items ***

5-12-11
0

Cessna Aircraft Company

Page 1
Jul 3/2006

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
© Cessna Aircraft Company

Page 1

April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INSPECTION OPERATION 14
Date:
Registration Number:
Serial Number:
Total Time:
1.

2.

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.

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

TASK

ZONE

342102

Magnetic Compass - Calibrate.

220

MECH INSP

REMARKS

***End of Operation 14 Inspection Items ***

5-12-14
© Cessna Aircraft Company

Page 1
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INSPECTION OPERATION 15
Date:
Registration Number:
Serial Number:
Total Time:
1.

2.

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.

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

TASK

ZONE

612003

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.

120,210

743002

Inspect and lubricate ACS brand ignition switch. 224
Refer to Chapter 74, Ignition System - Maintenance
Practices.

MECH INSP

REMARKS

***End of Operation 15 Inspection Items ***

5-12-15
© Cessna Aircraft Company

Page 1
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INSPECTION OPERATION 16
Date:
Registration Number:
Serial Number:
Total Time:
1.

2.

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.

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

TASK

221002

Autopilot Servo Capstan Assemblies.
Check 610
slip-clutch torque settings. Refer to Autopilot Maintenance Practices.

221003

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.

ZONE

MECH INSP

REMARKS

610

*** End of Operation 16 Inspection Items ***

5-12-16
© Cessna Aircraft Company

Page 1
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INSPECTION OPERATION 17
Date:
Registration Number:
Serial Number:
Total Time:
1.

2.

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.

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

TASK

ZONE

262002

Cockpit Mounted Halon Type Fire ExtinguisherWeigh bottle. Bottle must be reserviced by qualified
individual if more than 2 ounces is lost.

211

MECH INSP

REMARKS

***End of Operation 17 Inspection Items ***

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INSPECTION OPERATION 18
Date:
Registration Number:
Serial Number:
Total Time:
1.

Description
A.
B.

C.
2.

Operation 18 gives a list of item(s), which are completed every 6 years.
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.
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.

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

TASK

262004

Cockpit Mounted Halon Type Fire Extinguishers - 211
Empty, inspect for damage, and recharge.

ZONE

MECH INSP REMARKS

***End of Operation 18 Inspection Items ***

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INSPECTION OPERATION 19
Date:
Registration Number:
Serial Number:
Total Time:
1.

2.

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.

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.
ZONE

ITEM CODE
NUMBER

TASK

262003

Cockpit Mounted Halon Type Fire Extinguishers - 211
Perform hydrostatic test. The hydrostatic test shall
be at twelve-year intervals based on initial servicing
or date of last hydrostatic test.

MECH INSP REMARKS

*** End of Operation 19 Inspection Items ***

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INSPECTION OPERATION 20
Date:
Registration Number:
Serial Number:
Total Time:
1.

2.

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.

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

TASK

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.

ZONE

MECH INSP REMARKS

*** End of Operation 20 Inspection Items ***

5-12-20
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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INSPECTION OPERATION 21
Date:
Registration Number:
Serial Number:
Total Time:
1.

2.

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.

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

TASK

351002

Oxygen Cylinder (if applicable) - Inspect for 211
condition, check hydrostatic test date and perform
hydrostatic test, if due.

ZONE

MECH INSP REMARKS

*** End of Operation 21 Inspection Items ***

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INSPECTION OPERATION 22
Date:
Registration Number:
Serial Number:
Total Time:
1.

2.

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.

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

TASK

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.

ZONE

MECH INSP

REMARKS

*** End of Operation 22 Inspection Items ***

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INSPECTION OPERATION 23
Date:
Registration Number:
Serial Number:
Total Time:
1.

2.

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.

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

TASK

ZONE

212002

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.

220, 225

MECH INSP

REMARKS

***End of Operation 23 Inspection Items ***

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INSPECTION OPERATION 24
Date:
Registration Number:
Serial Number:
Total Time:
1.

2.

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.

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

TASK

ZONE

720000

Fuel line (Stainless steel tube assembly) and support
clamp inspection and installation. Refer to Lycoming
Service Bulletin Number 342E or later version.

120

MECH INSP

REMARKS

*** End of Operation 24 Inspection Items ***

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INSPECTION OPERATION 25
Date:
Registration Number:
Serial Number:
Total Time:
1.

2.

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.

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

TASK

ZONE

371007

Do an inspection of the wear indicator ports on the
vacuum pumps described in Tempest Service Letter
004.

120

MECH INSP

REMARKS

***End of Operation 25 Inspection Items ***

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INSPECTION OPERATION 26
Date:
Registration Number:
Serial Number:
Total Time:
1.

2.

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.

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

TASK

ZONE

273107

Elevator Trim Tab Actuator - Remove, clean,
examine, and lubricate the actuator.
Refer to
Chapter 27, Elevator Trim Control - Maintenance
Practices.

320

MECH INSP

REMARKS

***End of Operation 26 Inspection Items ***

5-12-26
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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
UNSCHEDULED MAINTENANCE CHECKS
1.

General
A.

B.
C.
D.
2.

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.
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.
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.
If foreign object damage (FOD) is found, complete a visual inspection of the airplane before the
airplane is returned to service.

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.
Main gear attachments and supporting structure - Examine for loose or unserviceable
2
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.
Nose gear attachments and supporting structure - Examine for loose or unserviceable
4
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.
Trailing edge - Examine for any deformation that stops the normal flap operation.
2
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.
All hinged doors - Examine the hinges, hinge attach points, latches and attachments,
2
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.

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MODEL 182/T182

MAINTENANCE MANUAL
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)

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.
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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.

F.

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.
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.

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B4224

1.

LIGHTNING STRIKE/STATIC DISCHARGE INCIDENT REPORTING FORM
Part 1

Flight Crew must complete Part 1.
NOTE:

A.

B.

C.

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.

Flight Information:
Flight Number_
ft
Altitude _

Strike Date_
Model
_
Unit/Serial Number
knots Geographical Location
Airspeed

Airplane Orientation:
Takeoff
Climb
Approach
Other
At time of Strike, aircraft was:

Within Clouds __

Above Clouds __

D.
E.

Precipitation at Strike:
Sleet
Rain

Below Ceiling

Hail

Snow

None

Lightning in Vicinity:
Before

F.

Descent

Cruise

After

None

Static in Comm/Nav
Before

After

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.
I
Engines
0
0
Navigation
0
Communication
Flight Instruments
0
Flight Control
0
0
AC Power System
I
DC Power System
I
0
I. Additional comments and descriptions:

Date

Part 1 completed by:

Phone

5-50-00
© Cessna Aircraft Company

Page 4

Jan 2/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

B4227

1.

LIGHTNING STRIKE/STATIC DISCHARGE INCIDENT REPORTING FORM
Part 2
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

Phone

5-50-00
© Cessna Aircraft Company

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

PAGE

DATE

6-00-00

Page 1

April 1/2002

6-1 0-00

Pages 1-5

April 1/2002

6-1 5-00

Pages 1-3

April 1/2002

6-20-00

Pages 1-4
Pages 1-11

Jul 1/2007

06-Title
06-List of Effective Pages
06-Record of Temporary Revisions
06-Table of Contents

6-20-02

06
©D
Cessna Aircraft Company

-

Jul 1/2007

LIST OF EFFECTIVE PAGES

Page 1of 1
Jul 1/2007

RECORD OF TEMPORARY REVISIONS
Temporary Revision
Number

Page Number

Issue Date

By

Date Removed

By

CESSNA AIRCRAFT COMPANY

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
DIMENSIONS AND AREAS - GENERAL
1.

Scope
A.

2.

This chapter includes statistical information and illustrations concerning the Model 182 airplane.

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.

© Cessna Aircraft Company

6-00-00 Page 1
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
AIRPLANE DIMENSIONS AND SPECIFICATIONS - DESCRIPTION AND OPERATION
1.

2.

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.

Dimensions and Specifications

AIRPLANE OVERALL
FUSELAGE DIMENSIONS
Length (Overall)

29.0 Feet

Height (Maximum)

9 Feet 3 Inches

Wing Span (Overall)

36.0 Feet

Tail Span

11 Feet 8 Inches

Landing Gear Track Width

9.0 Feet

Cabin Width (Maximum Sidewall to Sidewall)

42.0 Inches

Cabin Height (Floorboard to Headliner)

48.5 Inches

MAXIMUM WEIGHT
Ramp

3110 Pounds

Takeoff

3100 Pounds

Landing

2950 Pounds

FUEL CAPACITY
Total

92.0 Gallons

Usable

88.0 Gallons

ENGINE DATA
Type

Lycoming IO-540-AB1A5

Oil Capacity

9.0 Quarts

RPM (Maximum)

2400 RPM

Horsepower

230 HP

Type

Lycoming TIO-540-AK1A

Oil Capacity

9.0 Quarts

RPM (Maximum)

2400 RPM

Horsepower

235 HP

PROPELLER
Type

McCauley B2D34C235/90 DKB-08,
2-Blade

Diameter (Maximum to Minimum)

82.0 to 80.5 Inches

© Cessna Aircraft Company

6-1 0-00
Page 1
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

PROPELLER
Pitch Range (High to Low)

31.8 to 17.0 Degrees

Type

McCauley B3D36C431/80 VSA-01,
3-Blade

Diameter (Maximum to Minimum)

79.0 to 77.5 Inches

Pitch Range (High to Low)

31.7 to 14.9 Degrees

Pitch Range T182 (High to Low)

35.4 to 15.3

TIRE, STRUT AND WHEEL ALIGNMENT DATA
Main Tire Size

6.00 X 6, 6-Ply Rating

Main Tire Pressure

42.0 PSI

Nose Tire Size

5.00 X 5, 6-Ply Rating

Nose Tire Pressure

49.0 PSI

Nose Gear Strut Pressure (Strut Extended)

55 to 60 PSI

Camber (Measured With Airplane Empty)

5 to 7 Degrees

Toe-In (Measured With Airplane Empty)

0.00 to 0.06 Inch

CONTROL SURFACE TRAVELS/CABLE TENSION SETTINGS
AILERONS
Aileron Up Travel

20 Degrees, +2 or -2 Degrees

Aileron Down Travel

15 Degrees, +2 or -2 Degrees

Aileron Carry Through Cable Tension

40 Pounds, +10 or -10 Pounds

RUDDER
Rudder Travel (Measured Parallel to Water Line)
Right

24 Degrees, +0 or -1 Degree

Left

24 Degrees, +0 or -1 Degree

Rudder Travel (Measured Perpendicular to Hinge Line)
Right

27 Degrees 13 Minutes, +0 or -1
Degree

Left

27 Degrees 13 Minutes, +0 or -1
Degree

Rudder Cable Tension

30 Pounds, +10 or -10 Pounds

ELEVATOR
Up Travel (Relative to Stabilizer)

28 Degrees, +1 or -1 Degree

Down Travel (Relative to Stabilizer)

21 Degrees, +1 or-1 Degree

6-10-00
© Cessna Aircraft Company

Page 2

April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

TIRE, STRUT AND WHEEL ALIGNMENT DATA
30 Pounds, +10 or -10 Pounds

Cable Tension
ELEVATOR TRIM TAB
Up Travel

24 Degrees, +2 or -2 Degrees

Down Travel

15 Degrees, +1 or-1 Degree

Cable Tension

15 Pounds, +0 or -5 Pounds

FLAPS
Flap Setting:
0 Degree (Up)

0 Degree, +0 or -0 Degree

10 Degrees

10 Degrees, +2 or -2 Degrees

20 Degrees

20 Degrees, +2 or -2 Degrees

38 Degrees (Full)

38 Degrees, +0 or -1 Degree

6-10-00
© Cessna Aircraft Company

Page 3

April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

B1076

SPINNER
COWLING

WING

\

J

L
S

0

FLAP

Al LERON

[
AGE

HORIZONTAL STABI

TRIM TAB

ELEVATOR

1 FEET 8 INCHES

071 OT1002

Airplane Dimensions and Areas
Figure 1 (Sheet 1)

6-10-00
©Cessna Aircraft Company

Page 4

April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1077

36.0 FEET

4

Z I

I1

ino

pg

29.0 FEET
A

EET 3 INCHES

v

0710T1003
0710T1002

Airplane Dimensions and Areas
Figure 1 (Sheet 2)

6-10-00
© Cessna Aircraft Company

Page 5

April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
AIRPLANE STATIONS - DESCRIPTION AND OPERATION
1.

General
A.

B.

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).
For an illustration of Fuselage Stations, refer to Figure 1. For an illustration of Wing Stations, refer to
Figure 2.

© Cessna Aircraft Company

6-15-00 Page 1
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1078

FS 0.00

FS 156.00

FS

FS 17.00

FS 209.00

FS 185.50

FS 124.00

FS 230.18
FS 199.00
FS 140.00

FS8.12

FS56 .70

FS 110.00

FS 172.00

0710T1006

Fuselage Stations
Figure 1 (Sheet 1)

6-15-00
© Cessna Aircraft Company

Page 2

April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1079

WS 40.12

WS

.-

.'-

. AA

v

WS 136.00

WS 208.00

0710T1013

Wing Stations
Figure 2 (Sheet 1)

6-15-00
© Cessna Aircraft Company

Page 3

April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82
MAINTENANCE MANUAL
AIRPLANE ZONING

-

DESCRIPTION AND OPERATION

General
A. The Model 182fTi 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
Major Zone

310
I ISubdivision

Zone

Submajor Zone

B.

2.

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.

Description
A.

For a breakdown of airplane zones, refer to Figure 1.

6-20-00
© Cessna Aircraft Company

Page 1
Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti82

MAINTENANCE MANUAL

21081

110

51

611

310

11

T1 003
Ti 003
T1 003

(INTERIOR)
Airplane Zones
Figure 1 (Sheet 1)

6-20-00
0 Cessna Aircraft Company

Page 2
Jul 1/2007

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/Ti182
MAINTENANCE MANUAL

B2143

230

INTERIOR FLOOR

071 OT 1005

Airplane Zones
Figure 1 (Sheet 3)

6-20-00
© Cessna Aircraft Company

Page 4
Jul 1/2007

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:

B.
2.

3.

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.

This section can be used in conjunction with inspection practices (Chapter 5) or standard maintenance
practices to quickly find related components throughout the airplane.

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 threenumber 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).

Description
A.

Access/Inspection Panels.

6-20-02
© Cessna Aircraft Company

Page 1
Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182
MAINTENANCE MANUAL

61084

230AB

NOTE:

011nnn

CABIN FLOORBOARD PANELS
THE ACCESS PANEL IS APPLICABLE
ON AIRPLANES 18281225 AND ON
AND AIRPLANES Ti 8208203 AND ON.
Cabin Floorboard Panels
Figure 1 (Sheet 1)

071OT1009

6-20-02
C Cessna Aircraft Company

Page 2
Jul 1/2007

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
230DB

Brake Lines
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
231 FB

Rudder Cables, Elevator Cables, Elevator Trim Cables, Rudder Pulleys, Elevator Pulleys,
Elevator Trim Pulleys, Transponder Antenna
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
Q Cessna Aircraft Company

Page 3
Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti82

MAINTENANCE MANUAL

B1 083

31
31 OBB

)DB

310CB

BOTTOM VIEW

340BR
340AL
(34OAR)
31 OAR

LEFT VI EW

FUSELAGE PANELS
0710T1010
0710T1010

Fuselage Panels
Figure 2 (Sheet 1)

6-20-02
0 Cessna Aircraft Company

Page 4
Jul 1/2007

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
(34OAR)

Rudder Cables, Elevator Trim Cables, Rudder Pulleys, Elevator Trim Pulleys

340BR

Antenna T-Phasing Combiner

6-20-02
Q Cessna Aircraft Company

Page 5
Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182
MAINTENANCE MANUAL

B1085

BOTTOM VIEW

WING ACCESS PANELS

071OT1 01 1

Wing Access Panels
Figure 3 (Sheet 1)

6-20-02
© Cessna Aircraft Company

Page 6
Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82

MAINTENANCE MANUAL

B1 086

51 OCT

61 OCT

I 61 ODT

51

51 OBT

61 OBT

TOP VIEW

WING ACCESS PANELS

0710T1002

Wing Access Panels
Figure 3 (Sheet 2)

6-20-02
© Cessna Aircraft Company

Page 7
Jul 1/2007

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
6-20-02
0 Cessna Aircraft Company

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

6-20-02
©Cessna Aircraft Company

Page 9
Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182
MAINTENANCE MANUAL

B7580

511
(61
51 1BT
(61 1BT)

511CT
(61 1CT)
(61 1IDT)

FLAP PANELS

0725T1001

Flap Panels
Figure 4 (Sheet 1)

6-20-02
©Cessna Aircraft Company

Page 10
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

6-20-02
©Cessna Aircraft Company

Page 11
Jul 1/2007

CHAPTER

LIFTING AND
SHORING

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

LIST OF EFFECTIVE PAGES
PAGE

DATE

7-00-00

Page 1

April 1/2002

7-10-00

Pages 201-202

April 1/2002

7-11-00

Page 201

April 1/2002

CHAPTER-SECTION-SUBJECT
07-Title
07-List of Effective Pages
07-Record of Temporary Revisions
07-Table of Contents

07 - LIST OF EFFECTIVE PAGES
© Cessna Aircraft Company

Page 1of 1
Mar 1/2005

RECORD OF TEMPORARY REVISIONS
Temporary Revision
Number

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
7-00-00
7-00-00
7-00-00
7-10-00
7-10-00
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Page
Page
Page
Page

1
1
1
1

201
201
201
201

7-11-00 Page 201
7-11-00 Page 201

CONTENTS
© Cessna Aircraft Company

Page
Page
Page
Page

Page 1 of 1
Mar 1/2005

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
LIFTING AND SHORING - GENERAL

1.

Scope
A.

2.

This chapter describes both standard and emergency procedures used to lift the airplane off the
ground.

Tools, Equipment and Material
NOTE:

Equivalent substitutes may be used for the following listed items:
MANUFACTURER

USE

Jack

Obtain locally

To jack wing.

Leg Extension

Obtain locally

To extend legs on jack.

Slide Tube
Extension

Obtain locally

To extend jack height.

Universal Tail Stand

Obtain locally

To secure tail.

Padded Block

Fabricate locally

To provide cushion
between wing jack and
wing spar.

NAME

3.

NUMBER

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
© Cessna Aircraft Company

Page 1

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.
2.

Tools, Equipment and Materials
A.

3.

When the airplane needs to be raised off the ground at all points, the following procedure should be
used.

For a list of required tools, equipment and materials, refer to Lifting and Shoring - General.

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.

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MODEL 182/T182

MAINTENANCE MANUAL

B1087

PADDED

ING

BUILT-IN JACK PAD
(PART OF STEP BRACKET)

_
S

-TAIL
ASTAND

071 0T1008

Airplane Jacking
Figure 201 (Sheet 1)

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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.

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CHAPTER

LEVELING AND
WEIGHING

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

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MAINTENANCE MANUAL

CONTENTS
LEVELING AND WEIGHING - GENERAL ..........................................

Scope......................................................................
Tools, Equipment and Material ...............................................
Definition ...................................................................
LEVELING - MAINTENANCE PRACTICES.........................................

General ....................................................................
Tools, Equipment and Materials ..............................................
Leveling Points .............................................................

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MAINTENANCE MANUAL
LEVELING AND WEIGHING - GENERAL
1.

2.

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.

Tools, Equipment and Material
NOTE:

NAME

NUMBER

Spirit Level

3.

Equivalent substitutes may be used for the following items:
MANUFACTURER

USE

Commercially available

Bubble level used to level
airplane.

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.

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
LEVELING - MAINTENANCE PRACTICES

1.

2.

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.

Tools, Equipment and Materials
A.

3.

For a list of required tools, equipment and materials, refer to Leveling And Weighing - General.

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:

B.

Out of level tolerance for wing tips is 3 inches total.

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).

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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)

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CHAPTER

TOWING AND TAXIING

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

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MAINTENANCE MANUAL

CONTENTS
TOWING AND TAXIING - GENERAL ..............................................

S cope......................................................................
Definition ...................................................................
TOWING - MAINTENANCE PRACTICES ..........................................

G eneral ....................................................................

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MODEL 182/T182
MAINTENANCE MANUAL
TOWING AND TAXIING - GENERAL
1.

Scope
A.

2.

This chapter describes towing procedures for movement of the airplane on the ground.

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.

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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.

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MAINTENANCE MANUAL

TOW BAR
ASSEMBLY
0710T1001
A0714T1016

Tow Bar Installation
Figure 201 (Sheet 1)

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CHAPTER

PARKING AND
MOORING

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82
MAINTENANCE MANUAL

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CONTENTS
PARKING, MOORING, STORAGE AND RETURN TO SERVICE
Scope....................................
Tools, Equipment and Materials........................
Definition ..................................

- GENERAL.

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PARKING - MAINTENANCE PRACTICES......................
General...................................
Parking Instructions .............................

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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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MODEL 182/T182
MAINTENANCE MANUAL
PARKING, MOORING, STORAGE AND RETURN TO SERVICE - GENERAL
1.

Scope
A.

2.

This chapter provides maintenance instructions for parking, mooring, storage and return to service.

Tools, Equipment and Materials
NOTE:

Equivalent substitutes may be used for the following items:

NAME

NUMBER

MANUFACTURER

USE

Wheel Chocks

Available Commercially

To chock landing wheels.

Engine Air Inlet
Cover

Cessna Aircraft
Cessna Parts Distribution
Department 701, CPD
25800 East Pawnee Road
Wichita, KS 67218-5590

To prevent entry of
moisture and/or foreign
particles through cowling.

Pitot Tube Cover

Cessna Aircraft

To prevent entry of
moisture and/or foreign
particles in pitot tubes.

Static Ground
Cable

Available Commercially

To static ground airplane.

Rope (0.375
inch diameter
minimum) or
equivalent

Available Commercially

To tie down wing and tail.

Dehydrator Plugs

MS27215-1 or
-2

Available Commercially

To prevent moisture in
cylinders during indefinite
storage.

Corrosion
Preventive Oil

One part
MIL-L-6529,
Type 1, with
one part Royal
"D"

Royal Lubricants Co. Inc.
72 Eagle Rock Ave.
East Hanover, NJ 07936

Preserve engine during
long term storage.

Preservative Oil

MIL-C-6529

Available Commercially

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.

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MAINTENANCE MANUAL
PARKING - MAINTENANCE PRACTICES

1.

2.

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.

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.

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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

3.

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.

C.

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.
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.

Temporary Storage
NOTE:

A.

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.

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.

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(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.
(10) Disconnect the spark plug leads.
(11) 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.
(19) If the airplane is to be stored outside, tie it down using the procedures outlined in Chapter 10,
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.

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.
(2)

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.

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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.
(10) Allow the engine to stand for ten minutes, then turn the propeller back and forth through 90
degrees for twelve cycles.
(11) 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 (93.330 C)
and 2200 F (104.44 0 C).
(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:

5.

Inspection During Flyable Storage
A.

6.

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.

There are no inspection requirements for airplanes in flyable storage.

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.

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MAINTENANCE MANUAL
(4) Every 30 days do a minimum of one cylinder inspection for interior corrosion.
NOTE:
7.

Do not move the crankshaft during an inspection of the interior of cylinder.

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.

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MODEL 182/T182
MAINTENANCE MANUAL
MOORING - MAINTENANCE PRACTICES

1.

General
A.

2.

This section provides instructions for mooring the airplane.

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.

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MODEL 182/T182
MAINTENANCE MANUAL
RETURN TO SERVICE - MAINTENANCE PRACTICES
1.

General
A.

2.

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.

Flyable Storage Return to Service
A.

Accomplish the following:
(1) Perform a thorough preflight inspection.
NOTE:

3.

Temporary Storage Return to Service
A.

4.

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.

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.

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:
(6)
(7)
(8)
(9)
(10)
(11)
(12)
(13)
(14)

Preservative oil which remains in sump will mix with engine oil. Flushing of the oil
system is not required.

Remove old oil filter. Install new oil filter.
Reinstall drain plug and service engine with correct quantity and grade of engine oil.
Service and install induction air filter.
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.
Clean, gap and install spark plugs.
Rotate propeller by hand through compression stroke of each cylinders to check for possible
liquid lock. Torque plugs to 330 inch-pounds.
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.
Perform a thorough preflight inspection, then start and warm up engine.
Thoroughly clean and test fly airplane.

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© Cessna Aircraft Company

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CHAPTER

PLACARDS
AND
MARKINGS

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

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General ....................................................................

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PLACARDS AND MARKINGS - INSPECTION/CHECK ..............................
S cope......................................................................
Interior and Exterior Placard and Decal Inspection .............................

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PLACARDS AND MARKINGS - GENERAL.........................................

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
PLACARDS AND MARKINGS - GENERAL
1.

I

General
A.

Placards and markings on the exterior surfaces of the airplane are found in the Model 182 Illustrated
Parts Catalog, Chapter 11.

© Cessna Aircraft Company

11-00-00
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Mar 1/2004

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
PLACARDS AND MARKINGS - INSPECTION/CHECK
1.

Scope
A.

2.

This section gives information about the inspection of interior and exterior placards.

Interior and Exterior Placard and Decal Inspection
NOTE:
A.

This inspection is intended to be an overall inspection of all placards, decals, and markings on
the airplane.
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.

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CHAPTER

SERVICING

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

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MODEL 182/T182
MAINTENANCE MANUAL

CONTENTS
SERVICING - GENERAL .........

................................................

Scope.... ..................................................................
Definition ...................................................................
REPLENISHING - DESCRIPTION AND OPERATION ...............................
Genera l. ..... ....... . ... ...... ............ ....... .................... .....
Description ................................................................
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 .........
............................
.....................
Oil 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......................................................

© Cessna Aircraft Company

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
SCHEDULED SERVICING - DESCRIPTION AND OPERATION.....................
General ....................................................................
Description .................................................................

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LUBRICANTS - DESCRIPTION AND OPERATION .................................
General ....................................................................
Lubrication Service Notes....................................................
Definition of "As Needed" ...................................................
Recommended Lubricants Table .............................................

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BATTERY TERMINALS - SERVICING ............................................

General ....................................................................
Battery Terminal Lubrication..................................................

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1
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1
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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.......................................

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FLIGHT CONTROLS - SERVICING..............................................

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Page
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Page
Page

General ....................................................................
Aileron System Lubrication...................................................
Flap System Lubrication .....................................................
Elevator System Lubrication .................................................
Rudder System Lubrication ..................................................
ENGINE CONTROL CABLES - SERVICING .......................................

301
301
301
301
301
301

General ...................................................................
Engine Control Cables Lubrication ...........................................

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HEATING AND VENTILATION CONTROL CABLES - SERVICING ...................
General ....................................................................
Heating And Ventilation Control Cables Lubrication.............................

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AIRPLANE EXTERIOR - CLEANING/PAINTING ....................................
General ....................................................................
Precautio 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 ....................................................

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703
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705
705
705

INTERIOR - CLEANING/PAINTING................................................

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701
701
701
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General ....................................................................
Interior Cleaning Materials ...................................................
Cleaning Interior Panels .....................................................
Cleaning Carpet ............................................................
Cleaning Seats .........
....................................................
Cleaning the GDU 1040 Display Lens .........................................

© Cessna Aircraft Company

CONTENTS

Page 2 of 3
Jul 3/2006

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
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CONTENTS
© Cessna Aircraft Company

Page
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1
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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
SERVICING - GENERAL
1.

Scope
A.

2.

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.

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
© Cessna Aircraft Company

Page 1

April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
REPLENISHING - DESCRIPTION AND OPERATION
1.

General
A.

2.

3.

This section provides maintenance personnel with servicing information for replenishing fuel and oil.

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
(1)
(2)
(3)

following tables are provided to establish replenishment capacities of various systems:
Fuel Capacity (Table 1)
Approved Fuels (Table 2)
Engine Oil Capacity (Table 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

4.

U.S.

Fuel Capacity

92.0 Gallons

Usable Fuel

88.0 Gallons

Approved Fuel Table
A.

The following table lists approved fuels for use in the airplane.

Table 2. Approved Fuels

TYPE OF FUEL

SPECIFICATION

COLOR

100 LL

ASTM-D910

Blue

100

ASTM-D910

Green

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
© Cessna Aircraft Company

Page 1
Jan 2/2006

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
hoses)

13.0 quarts

12-10-00
© Cessna Aircraft Company

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
© Cessna Aircraft Company

Page3

Jan 2/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
NOSE LANDING GEAR SHOCK STRUT - SERVICING
1.

General
A.

2.

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.

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:
(5)
(6)
(7)

Fluid used must agree with specification MIL-PRF-5606.

(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 MILPRF-5606 or kerosene to clean the machined surfaces of dirt and dust.

12-11-00
© Cessna Aircraft Company

Page 301
Aug 4/2003

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
NOSE LANDING GEAR SHIMMY DAMPER - SERVICING
1.

2.

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.

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:

(7)
(8)

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.
Make sure that the floating piston is at the bottom.
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
© Cessna Aircraft Company

Page 301
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
0710T1001
A0741R 1010

Shimmy Damper Servicing
Figure 301 (Sheet 1)

12-12-00
© Cessna Aircraft Company

Page 302
Jul 3/2006

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, bottomedout 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
© Cessna Aircraft Company

Page 301
Aug 4/2003

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
FUEL AND ENGINE OIL - DESCRIPTION AND OPERATION
1.

General
A.

2.

3.

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.

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.

Oil Precautions
A.

Maintenance Precautions.
(1) Use proper servicing procedures; do not overfill, do not mix manufacturers brands of oil.

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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:

2.

For detailed description and maintenance practices related to the fuel system, refer
to Chapter 28, Fuel - General.

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.

3.

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.

Fuel Servicing
A.

Fuel Fill Procedures.

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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.

B.

4.

(1)
(2)
(3)
(4)
(5)
(6)

Electrically ground airplane and vehicle. Refer to the Safety and Maintenance Precautions.
Make sure that the battery switch is turned to OFF.
Put a protective mat around the fuel filler area and remove the fuel filler caps.
Fuel the airplane with the correct grade of aviation fuel.
Install the filler caps. Wipe up the excess fuel from the wing area.
Remove the equipment that you used to ground the airplane.

Fuel
(1)
(2)
(3)
(4)
(5)
(6)
(7)

Removal Procedures.
Electrically ground the airplane and the vehicle.
Make sure that the battery switch is turned to OFF.
Remove the fuel filler caps.
Put the defueling nozzle into the fuel bay and begin to defuel.
Remove as much fuel as possible with the defuel nozzle.
Remove the drain valves from the bottom of the fuel tank and drain the remaining fuel.
Remove grounding equipment.

Fuel Additive (DiEGME) Precautions

WARNING: 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.
WARNING: 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.
CAUTION: 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.
CAUTION: 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

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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.

5.

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.

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.

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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.

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ENGINE OIL - SERVICING
1.

General
A.

2.

This section provides instructions to examine and change the engine oil.

Oil Change Intervals
NOTE:
A.

An inspection of the filter can aid in the detection of premature engine wear. Refer to Lycoming
Service Bulletin 480D or latest revision.

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:
(2)

3.

For other engine change intervals, refer to Chapter 5, Inspection Time Limits.

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:

(7)
(8)
4.

The turbocharged engines use only ashless dispersant oil conforming to SAE J1899,
even during the engine break-in period.

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.

Insert the dipstick in the filler tube and do a check for correct seating.
Close the engine oil door.

Changing Engine Oil
A.

Oil Changing Procedures. Refer to Chapter 71, Figure 1 Engine - Description And Operation.
NOTE:
(1)

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.

Operate engine until oil temperature is at a normal operating temperature.
NOTE:

(2)

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.

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.

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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.

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B1091

SPECIFIED AVIATION GRADE OIL:
AVERAGE AMBIENT TEMPERATURE/OIL GRADE
0OF 10OF 20OF 30OF 40OF 50OF 60OF 70OF 80OF 90°F
-18°C -12 0 C -70C -1°C 4 0 C 10°C 15°C 21°C 270C 32°C
|

MAXIMUM OIL
TEMPERATURE

SAE 60
245°F (118°C)

SAE 40 or SAE 50

SAE 40
SAE 30, SAE 40 or SAE 20W-40
SAE 30 or
SAE 20W-30

'I

SAE 20
SAE

15W-50 or SAE 20W-50

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)

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INDUCTION AIR FILTER - SERVICING

1.

General
A.

2.

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.

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:
(f)

The filtering panels of the filter may become distorted when wet, but they will
return to their original shape when dry.

Be sure airbox is clean, and inspect filter. If filter is damaged, a new filter must be installed.
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(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.

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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:

2.

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.

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) Locate air filter forward of instrument panel.
(2)
(3)
(4)
3.

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.

Vacuum System Relief Valve Filter
A.

The relief valve filter should be serviced using time intervals set forth in Chapter 5, Inspection Time
Limits.

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SUCTION RELIEF

BRACKET

COVER
AIR
FILTER

NASHER

DETAIL

A

A07183001
07nTfins:

Vacuum System Air Filter - Servicing
Figure 301 (Sheet 1)

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BATTERY - SERVICING
1.

General
A.

2.

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.

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.

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TIRES - SERVICING
1.

General
A.

2.

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.

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.

3.

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.

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)

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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.

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SCHEDULED SERVICING - DESCRIPTION AND OPERATION
1.

General
A.

2.

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.

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.

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LUBRICANTS - DESCRIPTION AND OPERATION
1.

2.

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.

Lubrication Service Notes
A.

3.

4.

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.

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.

Recommended Lubricants Table
NOTE:

Equivalent substitutes may be used for the following items:

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MAINTENANCE MANUAL

Table 1. Recommended Lubricants
SYMBOL

PROCUREMENT SPECIFICATION

LUBRICANT
DESCRIPTION

PRODUCT
PART
NUMBER

SUPPLIER

GR

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
grease 22

Shell Oil Co.
One Shell Plaza
Houston, TX 77001

Southwest
Grease
16215

Southwest Petro- Chem, Inc.
Division - Witco
1400 S. Harrison
Olathe, KS 66061

Aeroshell
grease 7

Shell Oil Co.

Royco 27A

Royal Lubricants Co., Inc.

Supermil
grease No.
A72832

Amoco Oil Co.
200 East Randolph Dr.
Chicago, IL 60601

Braycote
6275

Burmah-Castrol, Inc.
Bray Products Div.
16815 Von Karman Ave.
Irving, CA 92714

Castrolease
A1

Burmah-Castrol, Inc.

TG-11900
low temp
grease EP

Southwest Petro-Chem,lnc.

Brayco 885

Brumah-Castrol, Inc.

Royco 363

Royal Lubricants Co., Inc.

Petrotect
7870A

Penreco
106 South Main Street
Butler, PA 16001

Windsor lube
L-1018

Anderson Oil & Chemical Co.,
Inc.
Portland, CT 06480

Octoil 70

Octagon Process, Inc.
596 River Road
Edgewater, NJ 07020

GH

OG

MIL-G-23827

MIL-L-7870

Grease, aircraft
and instrument,
gear and
actuator screw.

Oil, general
purpose

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MAINTENANCE MANUAL
Table 1. Recommended Lubricants (continued)

I

SYMBOL

PROCUREMENT SPECIFICATION

LUBRICANT
DESCRIPTION

PL

VV-P-236

Petrolatum
technical

Available Commercially

PG

SS-G-659

Powdered
Graphite

Available Commercially

GL

MIL-G-21164

High and Low
Temperature
Grease

PRODUCT
PART
NUMBER

SUPPLIER

Everlube
211-G Moly
Grease

E/M Corporation
Box 2200
Highway 52 N.W.
West Lafayette, IN 47906

Royco 64

Royal Lubricants Co., Inc.

GP

NONE

Number
10 weight,
nondetergent
oil

Available Commercially

OL

VV-L-800

Light Oil

Available Commercially

Grease,
general
purpose

U000992

Cessna Aircraft Co.
1 Cessna Blvd.
Wichita, Ks
67277-7704

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MAINTENANCE MANUAL
BATTERY TERMINALS - SERVICING
1.

General
A.

2.

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.

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.

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MAINTENANCE MANUAL

0

E

A

Ir

1

DETAIL

A

ITEM
NUMBER

ITEM
DESCRIPTION

LUBE
TYPE

APPLICATION

1

BATTERY TERMINALS

PL

HAND

PL - GREASE, PETROLATUM - VV-P-236
0710T1001
0718T3002

Battery Terminals Lubrication
Figure 301 (Sheet 1)

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MAINTENANCE MANUAL
LANDING GEAR AND PARKING BRAKE - SERVICING
1.

General
A.

2.

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.

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.
3.

4.

5.

6.

7.

Refer to Figure 301 for lubrication requirements of the wheel bearings.

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.

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.

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.

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.

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.

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MAINTENANCE MANUAL

B1094
r

L
3

l

5

DETAIL A

NOSE GEAR

1
MAIN GEAR
ITEM
NUMBER

ITEM
DESCRIPTION

LUBE
TYPE

APPLICATION

1
2
3

WHEEL BEARINGS
TORQUE LINKS
SHIMMY DAMPER
PIVOTS
STEERING SYSTEM
NEEDLE BEARINGS
NOSE GEAR STEERING
PUSHRODS

GR
GR
GR

HAND
GUN
OIL CAN

GR

HAND

OG

OIL CAN

4
5

GR - GREASE, GENERAL PURPOSE - (MIL-G-81322)
OG - OIL, GENERAL PURPOSE - (MIL-L-7870)

0742T1001
A0742T1002
0741T1001

Landing Gear Lubrication
Figure 301 (Sheet 1)

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MAINTENANCE MANUAL

B1095

ITEM
NUMBER

ITEM
DESCRIPTION

LUBE
TYPE

APPLICATION

1

PARKING BRAKE
HANDLE SHAFT

OG

OIL CAN

OG - OIL, GENERAL PURPOSE - (MIL-L-7870)

0741T1002

Parking Brake Handle Shaft Lubrication
Figure 302 (Sheet 1)

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MAINTENANCE MANUAL
FLIGHT CONTROLS - SERVICING
1.

General
A.

2.

3.

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.

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.

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.

B.

It is not necessary to remove actuator from airplane to clean or lubricate threads.
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.

NOTE:

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.
Trim tab piano hinges should be lubricated on an "as needed" basis and when assembled or installed.

C.

5.

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.

Rudder System Lubrication
A.
B.
C.

The rudder bar bearing block halves should be lubricated on an "as needed" basis and when
assembled or installed.
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.
Refer to Figure 304 for lubrication requirements of the rudder system.

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MAINTENANCE MANUAL

B1096

ITEM
NUMBER

ITEM
DESCRIPTION

LUBE
TYPE

APPLICATION

1

NEEDLE BEARINGS
NEEDLE BEARING
ROLLERS
NEEDLE BEARING
THRUST BEARING

GR
GR

HAND
HAND

GR
GR

HAND
HAND

2
3
4

GR - GREASE, GENERAL PURPOSE - (MIL-G-81322)

0724T1001

Aileron System Lubrication
Figure 301 (Sheet 1)

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MAINTENANCE MANUAL

B1097

2

3
AILERON BELLCRANK

1

AILERON HINGES

IT EM

NUWMBER
1
2
3

ITEM
DESCRIPTION

LUBE
TYPE

APPLICATION

AILERON PIANO HINGES
BELLCRANK NEEDLE
BEARINGS
ROD END BEARINGS

PG
GR

SYRINGE
HAND

OG

OIL CAN

(SS-G-659)
PG - POWDERED GRAPHITE
GR - GREASE, GENERAL PURPOSE - (MIL-G-81322)
OG - OIL, GENERAL PURPOSE - (MIL-L-7870)

0724T1002
0724T1003

Aileron System Lubrication
Figure 301 (Sheet 2)

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MAINTENANCE MANUAL

DETAIL

A

ELECTRIC FLAP DRIVE MECHANISM
IT'EM

NUNABER
1
2

ITEM
DESCRIPTION

LUBE
TYPE

APPLICATION

FLAP MOTOR SCREW
JACK THREADS
NEEDLE BEARINGS

GP

OIL CAN

GR

HAND

GP - OIL NO. 1 -WEIGHT, NON-DETERGENT
GR - GREASE, GENERAL PURPOSE - (MIL-G-81322)
0718T1005

Flap System Lubrication
Figure 302 (Sheet 1)

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MAINTENANCE MANUAL

RB10n

TRIM WHEEL

5

3
4

II I
I .I

ELEVATOR RUB STRIP
ACTUATOR AND TRIM TAB

ITEM
NUMBER

ITEM
DESCRIPTION

LUBE
TYPE

1

NEEDLE BEARINGS
OILITE BEARINGS
TRIM TAB PIANO
HINGES
TRIM TAB ACTUATOR
ELEVATOR DOWN
SPRING LINK RUB STRIP

GR
OG

2
3
4
5

APPLICATION

PG

HAND
OIL CAN
SYRINGE

GL

HAND

GR

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)

0718T4001
0734T1001
0734T1002

Elevator System Lubrication
Figure 303 (Sheet 1)

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MAINTENANCE MANUAL

B1100

ITEM
NUMBER

~1

ITEM
DESCRIPTION

LUBE
TYPE

APPLICATION

OILITE BEARING
(RUDDER BAR ENDS)

OG

OIL CAN

ALL LINKAGE
PIVOT POINTS

OG

OIL CAN

OG

OIL CAN

BEARING BLOCK
HALVES

OG - OIL, GENERAL PURPOSE - (MIL-L-7870)

0562T2002

Rudder Pedals Lubrication
Figure 304 (Sheet 1)

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MAINTENANCE MANUAL
ENGINE CONTROL CABLES - SERVICING

1.

General
A.

2.

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.

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.

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MAINTENANCE MANUAL
HEATING AND VENTILATION CONTROL CABLES - SERVICING
1.

General
A.

2.

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.

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.

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AIRPLANE EXTERIOR - CLEANING/PAINTING
1.

2.

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.

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.
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.

C.

3.

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.

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
NAME

NUMBER

MANUFACTURER

USE

Spray

MIL-C-6799,
Type 1, Class

Commercially Available

Gives surfaces protection
from solvents.

II

Masking Paper

WPL-3

Champion Intl. Corp.
Forest Product Division
7785 Bay Meadows Way
Jacksonville, FL 32256

Gives surfaces protection
from solvents.

Poly-Spotstick

SXN

Champion Intl. Corp.

Gives surfaces protection
from solvents.

Mask Off Company
345 Marie Avenue
Monrovia, CA

Gives surfaces protection
from solvents.

Protex 40

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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

NUMBER

Mild soap
or detergent
(household type
without abrasives)
Aliphatic Naphtha
Type II

Federal
Specification
TT-N-95

Turtle Wax (paste)

Permatex Plastic
Cleaner No. 403D
Soft cloth (cotton
flannel or cotton
terry cloth)
NOTE:
5.

Federal
Specification
P-P-560

MANUFACTURER

USE

Commercially Available

Cleans windshields and
windows.

Commercially Available

Removes deposits which
cannot be removed with
mild soap solution on
acrylic windshields and
windows.

Commercially Available

Gives protection to
acrylic windshields and
windows.

Permatex Company, Inc.
Kansas City, KS 66115

Gives protection to
acrylic windshields and
windows.

Commercially Available

Applies and removes
wax and cleaning agents.

Equivalent substitutes can be used for the items given in Table 702.

Cleaning Windshield and Windows

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.
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.
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.

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(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:

7.

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.

Aluminum Surfaces
A.

8.

Windshields and windows must be cleaned before you apply wax. When you apply and remove
wax and cleaning agents, use a soft, clean cloth.

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.

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:

B.

9.

For more information on the external paint finish, refer to Chapter 20, Exterior Finish Cleaning/Painting.

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.

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.

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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.
WARNING: 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:
(2)
B.

If you use compressed air to apply solvent or to dry components, adjust the pressure
to the lowest possible setting.

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.

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: Do not use gasoline or other flammable materials to clean the
engine compartment. If used, these materials can cause a fire.
WARNING: 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.
CAUTION: 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.

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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.

11.

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.

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
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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

MANUFACTURER

USE

Protectant

Son-Of-A-Gun

Commercially available

To protect and shine interior
components (excluding
fabric materials).

All-Purpose
Cleaner

Fantastik

Commercially available

For general purpose
cleaning of interior
components.

Aliphatic Naphtha

TT-N-94

Commercially available

To remove tar, asphalt,
and similar materials from
interior components.

Rug Shampoo

Commercially available

To clean carpet.

Perchloroethylene
Cleaning Solvent

Commercially available

To spot clean carpet and
seats.

Household
Ammonia

Commercially available

To clean seat fabric.

Household Vinegar

Commercially available

To clean seat fabric.

Rubbing Alcohol

Commercially available

To clean seat fabric.

Ivory Liquid (white
or colorless)

Commercially available

To clean seat fabric.

Commercially available

To clean seat fabric.

Cheer

Detergent
3.

Cleaning Interior Panels
A.

4.

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.

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.

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CESSNA AIRCRAFT COMPANY

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MAINTENANCE MANUAL

5.

Cleaning Seats
A.

B.

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.
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
PROCESS AND
SEQUENCE

STAIN

STAIN

PROCESS AND
SEQUENCE

Antacid (Maalox)

1

Infant Formula

2,1

Betadine (Iodine)

2,3,4,6

Ink (ball point)

8
1,2,3,4

Blood *

2,3,5

Motor Oil

Catsup

2,3,5

Mud

2,1

Chewing Gum

7,1,2

Petroleum Jelly

1,2

Pepto Bismol

6,1

Chocolate Syrup

5,1
2,4,5,1

Coffee/Tea

2,3,4

Cola

2

Cough Syrup

Urine
Suntan Lotion
Shoe Polish

2,3,4
1,2
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
Wine
2,3,4,5,1
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.

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CESSNA AIRCRAFT COMPANY

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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.

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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:

2.

Extreme Weather Maintenance
A.

3.

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.

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:

4.

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.

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.

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:

(2)

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.

Make sure that the temperature of the warm air is no more than 120 °C (248 °F).

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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) Do not use a heater with open flames to supply the warm air to preheat the engine.
(4) Preheat the engine before an engine start if the engine temperature is less then -6 °C (20 °F).
(5) 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:

C.

D.

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.

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.
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.

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MAINTENANCE MANUAL

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CHAPTER-SECTION-SUBJECT

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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

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CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182

MAINTENANCE MANUAL
FUEL, WEATHER AND HIGH-TEMPERATURE
PRACTICES ...................................
General...................................
Tools and Equipment.............................
Definition of Sealing Terms ..........................
Materials ..................................
General Requirements............................
Sealant Curing................................
Mixing of Sealants..............................
Cleaning ..................................
Sealing Application..............................
Sealant Repair................................

SEALING

-

CONVERSION DATA - DESCRIPTION AND OPERATION ..............
General...................................
Formulas for Conversion Computations ....................

MAINTENANCE
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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
STANDARD PRACTICES AIRFRAME - GENERAL
1.

2.

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.

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
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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.

3.

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.

Asbestos

WARNING: Do not let asbestos fibers make entry into the body of personnel.
Asbestos fibers can cause injury or death.

4.

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.

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.
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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.

B.

C.

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
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.
The human body can filter small amounts of solvents out of itself. This filtration
1
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.
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

D.

FLASH POINT

Methyl n-Propyl
Ketone

45F (7.2'C)

Toluene

39F (3.9;C)

Isopropyl Alcohol

53.6F (12cC)

Acetone

1.4F (-17cC)

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.
The yellow symbol on the label shows that the contents are oxidizers.
2

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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.

(4)

8.

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.

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.

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.

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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.

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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 inchpounds, 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.
(10) 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.

(DCessna Aircraft Company

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MODEL 182/T1182
MAINTENANCE MANUAL

B1 101

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.
TORQUE
WRENCH

SHORT OPEN-END
ADAPTER

JO)

6

WRENCH
ATTACHMENT FITTING
CENTERLINE
ADAPTER
CENTERLINE

SETSCREW
ADAPTER

FORMULA

Tx L
L+E

- Y

EXAMPLE (WITH "E" AS PLUS DIMENSION)
T
Y
E
L

HOSE CLAMP
ADAPTER

=
=
=
=

T
Y
L
E
OPEN-END WRENCH
ADAPTER

%AIDE:MrLJ

Y = 135 x 10 = 117.39
10 + 1.5
Y = 117 IN-LB

135 IN-LB
UNKNOWN
1.5 IN
10.0 IN
=
=
=
=

TORQUE
TORQUE
LENGTH
LENGTH

LEGEND
TO BE FOUND
SHOWN ON TORQUE WRENCH
OF LEVER
OF EXTENSION

ADAPTER
CENTERILINE

HANDLE
CENTERLINE

ATTACHM
CENTERLI

FLARE NUT WRENCH
ADAPTER
FORMULA Tx L

TORQUE
WRENCH

y

=

L -E

EXAMPLE (WITH "E" AS MINUS DIMENSION)

SPANNER WRENCH
ADAPTER

T
Y
L
E

=
=
=
=

135 IN-LB
UNKNOWN
10.0 IN
1.5 IN

Y = 135 x 10

10
Y

=

-

1.5

=

1350

=

158.82

8.5

159 IN-LB
5598T2005

Torque Wrench and Adapter Formulas
Figure 201 (Sheet 1)

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CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182

MAINTENANCE MANUAL

Bi 102

EXTERNAL WRENCHING HEAD

CORRECT INSTALLATION
INSTALL WASHER WITH COUNTERSUNK
FACE NEXT TO BOLT HEAD RADIUS

INTERNAL WRENCHING HEAD

STANDAR[
WASHER

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

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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

MS1 7826 NUTS

FINE THREADED SERIES
(SHEAR TYPE NUTS
EXCEPT IVI17826)

FINE THREADED SERIES
(TENSION TYPE NUTS)
Alternate
Torque

Standard
Torque

Alternate
Torque

Standard
Torque

Alternate
Torque

~~7 to 9

8-36

12 tolS5

10-32

20 to 25

20 to 28

12 to 15

12 to 19

12 to 15

12 to 20

1/4-28

50 to 70

50 to 75

30 to 40

30 to 48

30 to 40

30 to 45

5/16-24

100 to 140

100 tolSO0

60 to 85

60Oto 100

60 to 80

60 to 90

3/8- 24

160 to 190

160 to 260

95 to 110

95 to 170

95 to 110

95 to 125

7/16-20

450 to 500

450 to 560

270 to 300

270 to 390

180 to 210

180 to 225

1/2-20

480 to 690

480 to 730

290 to41 0

290 to 500

240 to 280

240 to 300

9/16-18

800 to 1000

800 to 1070

480 to 600

480 to 750

320 to 370

320 to 400

5/8-18

llO to1300

llO
00tol1600

660 to 780

660 to 1060

480 to 550

480 to 600

3/4-16

2300 to 2500

2300 to 3350

1300 to 1500

1300 to 2200

880 to 1010

880 to 1100

7/8-14

2500 to 3000

2500 to 4650

1500 to 1800

1500 to 2900

1-14

3700 to 4500

3700 to 6650

2200 to 3300

2200 to 4400

1-1/8-12 5000 to 7000

5000 to
10000

3000 to 4200

3000 to 6300

1-1/4-12 9000 to
11000

9000 to
16700

5400 to 6600

5400 to
10000

1500
1750
2200
2700
3200
4200
5900
6400

1500
1900
2200
3000
3200
5000
5900
7000

--

to
to
to
to

Fine Thread Tension application nuts include: AN310, AN315, AN345, MS17825,
NASM21 044 through MVS21 048, MVS21 078, NAS679, NASi 291
Fine Thread Shear application nuts include:
MVS21083, MVS21245, NAS1022, S1117

AN316, AN320,

Coarse Thread application nuts include: AN340, MVS20341,

MVS21025,

to
to
to
to

MVS20365,

MVS21042, IVS21043,

MVS20365, MS35649

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MAINTENANCE MANUAL
(Newton Meters)
SIZE
OF
BOLT,
NUT
OR
SCREW

FINE THREADED SERIES
(TENSION TYPE NUTS)

FINE THREADED SERIES
(SHEAR TYPE NUTS
EXCEPT MS1 7826)

Standard

Standard

Alternate

Alternate

MS17826 NUTS

Standard

Alternate

1.4-2.1

1.4-1.7

1.4-2.3

3.4-4.5

3.4-5.4

3.4-4.5

3.4-5.1

11.3-16.9

6.8-9.6

6.8-11.3

6.8-9.0

6.8-10.2

18.1-21.5

18.1-29.4

10.7-12.4

10.7-19.2

10.7-12.4

10.7-14. 1

7/16-20

50.8-56-5

50.8-63.3

30.5-33.9

30.5-44.1

20.3-23.7

20.3-25.4

1/2-20

54.2-78.0

54.2-82.5

32.8-46.3

32.8-56.5

27.1-31.6

27.1-33.9

9/16-18

90.4-113.0

90.4-120.9

54.2-67.8

54.2-84.7

36.2-41.8

36.2-45.2

5/8-18

124.3-146.9

124.3-180.8

74.6-88.1

74.6-119.8

54.2-62.1

54.2-67.8

3/4-16

259.9-282.5

259.9-378.5

146.9-169.5

146.9-248.6

99.4-114.1

99.4-124.3

7/8-14

282.5-339.0

282.5-525.4

169.5-203.4

169.5-327.7

169.5-197.7

169.5-214.7

1-14

418.0-508.4

418.0-751.3

248.6-372.9

248.6-497.1

248.6-305.1

248.6-339.0

1-1/8-12

564.9-790.9

564.9-1129.9

339.0- 474.5

339.0-711.8

361.6-474.5

361.6-564.9

1-1/4-12

1016.91242.8

1016.91886.9

610.1-745.7

61 0.1-1129.9

666.6-723.1

666.6-790.9

8-36

1.4- 1.7

.10-32

2.3-2.8

2.3-3.2

1.4-1.7

1/4-28

5.6-7.9

5.6-8.5

5/16-24

11.3-15.8

3/8- 24

3.

-

-

~~0.8-1 .0

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

ALLOY STEEL 180 - 200
KSI (INCH-POUNDS)

6-32

8-10

8-32

12-15

10-32

20-25

1/4-28

50-70

5/16-24

100-1 40

3/8-24

160-1 90

7/16-20

450-500

1/2-20

480-690

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CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182
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.
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.
Use Table 204 to determine torque requirements for threaded fasteners used as airframe electrical
ground terminals.
NOTE:

B.

Table 203. Torque Values Electrical Current Carrying Fasteners
FASTENER
DIAMETER

TORQUE VALUE
(INCH-POUNDS)

6-32

8-12

8-32

13-17

10-32

20-30

3/16

20-30

1/4

40-60

5/16

80-100

3/8

105-125

11/2

130-150

Table 204. Torque Values Airframe Electrical Ground Terminals

5.

FASTENER
DIAMETER

TORQUE VALUE
(INCH-POUNDS)

5/16

130-1 50

3/8

160-19go

Torque Requirements for Rigid Tubing and Hoses
A.

Use Table 205 to determine torque requirements for tubes and hoses.

20-11-00
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MODEL 1821T182

MAINTENANCE MANUAL

Table 205. Tubing/HoseTorque Limits (Inch-Pounds)
Hose Tubing
Size
O.D.

Flared or Flareless fitting with
Aluminum or Annealed Stainless
Steel Tubing, and Hose with
Aluminum Inserts
Min

Flared or Flareless fitting with Steel
Tubing, and Hose with Steel Inserts

Max

Min

Max

-2

1/8

20

30

75

85

-3

3/16

25

35

95

105

-4

1/4

50

65

135

150

-5

5/16

70

90

170

200

-6

3/8

110

130

270

300

-8

1/2

230

260

450

500

-10

5/8

330

360

650

700

-12

3/4

460

500

900

1000

-16

1

500

700

1200

1400

-20

1 1/4

800

900

1520

1680

-24

1 1/2

800

900

1900

2100

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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.

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.
(4)

B.

2.

Cotter Pin.
(1) The selection of material shall be in accordance with temperature, atmosphere and service
limitations.

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
SIZE AND NUMBER (NASM20995-XXX)

MATERIAL

.051

.091

NC40

NC51

NC91

N40

N51

N91

.020

.032

.040

NC20

NC32

Ni-Cr-Fe Alloy
(Inconel)

N20

N32

Carbon Steel

F20

F32

.015
Ni-Cu Alloy
(Monel)

.041

F41

.047

F47

F91

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
Table 201. Safety Wire (continued)
MATERIAL

Corrosion
Resistant Steel

.015

.020

.032

C15

C20
AB20

Aluminum Alloy
(Blue)
Copper (Yellow)
3.

SIZE AND NUMBER (NASM20995-XXX)

CY15

.040

.041

.047

.051

.091

C32

C41

C47

C91

AB32

AB41

AB47

AB91

CY20

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
© Cessna Aircraft Company

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

STEP 1.

!OLT A

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.

1l TI

U-VLL

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.

L

DOUBLE-WIRE SAFETYING

-

-COUNTER-

CLOCKWISE

MULTIPLE FASTENER
APPLICATION DOUBLE

DOUBLE-TWIST SAFETYING
SINGLE HOLE METHOD

TWIST- MULTIPLE

HOLE METHOD.

5598T2001
5599T2001
6598T1029

Lockwire Safetying
Figure 201 (Sheet 1)

20-12-00
© Cessna Aircraft Company

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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

5598T1003
5598T1024
5598T1024
5598T1024

Lockwire Safetying
Figure 201 (Sheet 2)

20-12-00
© Cessna Aircraft Company

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1105

hllllllllllll
1111111111111
II1illlllllll

AN500A

5598T1001
5598T1001

Lockwire Safetying
Figure 201 (Sheet 3)

20-12-00
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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:
(2)

D.

4.

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.

Care shall be exercised when installing safety wire to ensure that it is tight but not over stressed.

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.

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.

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B1106

TO PROVIDE CLEARANCE
PRONG MAY BE CUT HERE

CASTELLATED NUT ON BOLT
ALTERNATE METHOD

CASTELLATED NUT ON BOLT
PREFERRED METHOD

THREAD SIZE

MINIMUM
PIN SIZE
(INCH)

6

0.028

8

0.044

10

0.044

1/4

0.044

5/16

0.044

3/8

0.072

7/16

0.072

1/2

0.072

9/16

0.086

5/8

0.086

3/4

0.086

7/8

0.086

1

0.086

1 1/8

0.116

1 1/4

0.116

1 3/8

0.116

1 1/2

0.116

TANGENT
TO PIN
MAXIMUM
COTTER PIN
LENGTH

MINIMUM
COTTER PIN
LENGTH

PIN APPLICATION
5598T1025
5598T1025
5598T1025
5598T1025

Cotter Pin Safetying
Figure 202 (Sheet 1)

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(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 4313.1B, Safety Methods For Turnbuckles.

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B1107

(NOTE)
CABLE
TERMINAL

BARREL
II

- .

/

(NOTE)

NOTE:

PULL WITH YOUR FINGERS FOR AN
INSPECTION TO MAKE SURE THE CLIP
WILL NOT COME OUT.

STRAIGHT END

HOOK SHOULDER

B
HOOK LIP

END LOOP

HOOK LOOP

SAFETY CLIP INSTALLATION
SAFETY CLIP INSTALLATION
0798T1005
0798T1003
0798T1004

Safetying Turnbuckle Assemblies with Safety Clips
Figure 203 (Sheet 1)

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LOCKING CLIP
MS21256

Bto108

TURNBUCKLE
CLEVIS

0

TURNBUCKLE EYE

] [

II

CARI F

I

THIMBLE
TURNBUCKLE BARREL
MS21251

LOCKING CLIP
MS21256

TYPICAL TURNBUCKLE ASSEMBLY
"\

X
L1n I

\

\

\

'

\

\

\

\

I 'A

EID

'\
\

'

['

'

'

\

-

SWAGED
TERMINAL
METHOD OF ASSEMBLING LOCKING CLIPS, TURNBUCKLE BARREL AND TERMINAL

NOMINAL
CABLE DIA

THREAD
UNF-3

LOCKING
CLIP
MS21256
(NOTE)

1/16

No. 6-40

-1

3/32

No. 10-32

1/8
5/32

1/4-28

TURNBUCKLE
BODY
MS21251
-2S
-3S

-2

-3L

-1

-4S

-2

-4L

-1

-5S

-2

-5L
-6S

3/16

5/16-24

-1

7/32

-7L

1/4

3/8-24

9/32

7/16-20

5/16

1/2-20

NOTE:

-6L

-2

-8L
-9L

-3

-10L

TWO LOCKING CLIPS REQUIRED FOR EACH
TURNBUCKLE.

5598T1023
5598T1023

Safetying Turnbuckle Assemblies with Safety Clips
Figure 203 (Sheet 2)

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B2495

SINGLE WRAP SPIRAL

ED

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)

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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.

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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)

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SOLVENTS, SEALANTS, AND ADHESIVES - DESCRIPTION AND OPERATION
1.

General
A.

B.

C.
2.

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.
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.
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.

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.

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ACCEPTABLE REPLACEMENTS FOR CHEMICALS AND SOLVENTS - DESCRIPTION AND OPERATION
1.

2.

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-FRL5636-1), RIN 2060-AG65.

C.

Compliance with the standard is mandatory by September 1, 1998.

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
SURFACE

APPROVED PRODUCT/NUMBER

SUPPLIER ADDRESS

All Metals and
Painted Surfaces

Methyl n-propyl ketone
(CAS No. 107-87-9)

Eastman Chemical
Products
Wilcox Dr. and Lincoln St
Kingsport, TN

Desoclean 110
(020K19)

Courtaulds Aerospace
Glendale, CA 91203

DS108

Dynamold Solvents,
Incorporated
2905 Shamrock Ave
Fort Worth, TX 76107

All Plastics (Except
Windows and
Windshields)

Isopropyl Alcohol
(TT-I-735)

Available Commercially

All Rubber (Natural
or Synthetic) and
Silicone

Isopropyl Alcohol

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.

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Table 2. Replacement Products for Priming Operations
PRIMER APPLICATION

APPROVED PRODUCT/NUMBER

SUPPLIER ADDRESS

Corrosion Primer
(Notes 1,4)

Corrosion Primer
(513 X 419)(910 X 942)

Courtaulds Aerospace
1608 Fourth St.
Berkeley, CA 94710

Corrosion Primer
(02-Y-40)(02-4-40 CATA)

DEFT, Inc.
17451 Von Karman Ave.
Irvine, CA 92714

Corrosion Primer
(U-1201 F/U-1202F)

Sterling Lacquer Mfg.
3150 Brannon Ave.
St. Louis, MO 63139

Corrosion Primer
R4001-K14
MAX COR

U.S. Paint Corp.
831 S. 21st St.
St. Louis, MO 63103

Fuel Bay Primer
(Notes 2, 4)

Fuel Bay Primer
(10P30-5)

Dexter Crown Metro
Aerospace
East Water St.
Waukegan, IL 60085

Pretreatment Primer
(Notes 3, 4)

Pretreatment Primer
(728- 013/702-701)

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.

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Table 3. Replacement Products for Topcoat Painting Operations
TOPCOAT APPLICATION

APPROVED PRODUCT/NUMBER

SUPPLIER ADDRESS

Basecoat
(Note 4)

830 Series High Solids Acry Glo

Pratt & Lambert

Low VOC Enamel

Sterling Lacquer Mfg.

24-F 20 Series

Dexter Crown Metro
Aerospace

Low VOC Acrylic 830 Series

Pratt & Lambert

Paint Stripes
(Note 4)
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

APPROVED PRODUCT/NUMBER

SUPPLIER ADDRESS

Chemical Stripping

Turco T-6776 LO

Turco Products, Inc.
Westminster, CA 92684

Mechanical Stripping
(Note 5)

180 Grit or finer

Available Commercially

NOTE 5: Mechanical and hand- sanding operations are exempt from these requirements.

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MAINTENANCE MANUAL
GENERAL SOLVENTS/CLEANERS - MAINTENANCE PRACTICES
1.

General
A.

2.

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.

Tools, Equipment and Materials
NOTE:

Equivalent substitutes may be used for the following items.

NAME

NUMBER

Detergent

MANUFACTURER

USE

Commercially available

General cleaning.

ScotchBrite Pads

Type A

Minnesota Mining and Mfg. Co.
3M Center
St. Paul, MN 55101

Light abrasion of metal
surfaces.

Sandpaper

320 Grit

Commercially available

Light abrasion of metal
surfaces.

Rymple Cloth

Commercially available

Wiping and applying
cleaning agents.

Wiping cloth white,
oil free, absorbent

Commercially available

Wiping and applying
cleaning agents.

3.

4.

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 wellventilated 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.

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.

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(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
CLEANER/
SOLVENT

FEDERAL
SPECIFICATION

TYPE
CLASSIFICATION

USE/ DESCRIPTION
FUNCTION

CAUTION/ WARNING

Dry

MILPRF-680

Type I -100F
Type II -140'F

General cleaning solvent.
Dry cleaning of textile
materials. Grease
removal.

FLAMMABLE.

1,1,1
Inhibited

O-T-620

Type I Regular Type

Spot removing from
fabrics. General cleaning
solvent. Cleaning of
assembled equipment.

USE WITH ADEQUATE
VENTILATION.
AVOID PROLONGED
BREATHING OF VAPOR.
AVOID PROLONGED
CONTACT WITH SKIN.

Technical

II - with

Trichloroethane

dauber Type
III - Aerosol

Turco Seal
Solvent Turco
Products

Cleaning/Degreasing
metal parts.

Penwalt 2331

Preparing metal plate for
painting.

ACID ACTIVATED
SOLVENT, DO NOT
USE ON PLASTICS.

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.

REMOVES PAINT. AVOID
CONTACT WITH SKIN.

Carbon
Removing
Compound

P-C-

Cleaning
Compound

P- C-535

111A

Heavy duty electro
cleaner used for removal
of soils from ferrous
metal surfaces prior to
electroplating or other
treatments.

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Table 201. General Solvents (continued)
CLEANER/
FEDTYPE
SOLVENT
ERAL
CLASSIFISPECIFI- CATION
CATION

USE/ DESCRIPTION
FUNCTION

CAUTION/ WARNING

Cleaning
Compound,
Unfinished
Aluminum

MIL-C5410

Type I Viscous
Emulsion
Type II - Clear
Liquid

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.

Trichloroethylene

O-T634B

Type I Regular Type
II - Vapor
Degreasing

Cleaning of metal parts.
Degreasing of metal parts.
Special purpose solvent.

REMOVES PAINT
AND DAMAGES
PLASTICS. USE ONLY
WITH ADEQUATE
VENTILATION. HIGH
CONCENTRATIONS
OF VAPOR ARE
ANESTHETIC AND
DANGEROUS TO LIFE.
VERY TOXIC.

Polish, Metal
Aluminum

MIL-P6888C

Type I -Liquid
Type II Paste

Metal polish for use
on airplane aluminum
surfaces.

FLAMMABLE.

Naphtha,
Aliphatic

TT-N958

Type I Type II

For use with organic
coatings only. Cleaner for
acrylic plastics and may
be used in place of Type I
General cleaning agent.

FLAMMABLE. VAPOR
HARMFUL. AVOID
PROLONGED OR
REPEATED BREATHING
OR CONTACT WITH
SKIN.

Paint and adhesive
thinner, cleaning agent.

FLAMMABLE.

For use with organic
coatings and as an
anti-icing fluid. General
Solvent for synthetic
rubbers.

DO NOT USE WITH
ACRYLIC PLASTICS.

Methyl Propyl
Ketone
Isopropyl
Alcohol

TT-1-735

Grade B
-0.4% water

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Table 201. General Solvents (continued)
TYPE
CLEANER/
FEDCLASSIFISOLVENT
ERAL
SPECIFI- CATION
CATION
Wax,

Airplane,
Waterproof
Solvent Type
Cleaning
Compound,
Aluminum

MIL-C-

Type I - Vis-

5410B

cous EmulsionType II -

A-A-

59107

CAUTION/ WARNING

A waterproof wax that can DO NOT USE SOLVENTS
be dissolved or dispersed THAT MAY DAMAGE
PAINT OR FINISH FOR
with an organic solvent.
REMOVAL OF WAX.

MIL- W18723C

Clear Liquid

Toluene

USE/ DESCRIPTION
FUNCTION

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.

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.

Use as a solvent or thinner
for organic layers, various
resins, and chlorinated
rubber. Also used to
dilute cellulose lacquers
and dopes.

FLAMMABLE VAPOR.
VAPOR HARMFUL.

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MAINTENANCE MANUAL
INTERIOR AND EXTERIOR FINISH - CLEANING/PAINTING
1.

General
A.

2.

Interior and exterior finish cleaning/painting consists of general information and instructions for
applying chemical film treatments, primer and topcoats to the airplane.

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.

4.

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.

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.
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(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
Do not sand into the fabric layers of composite
accomplished.
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.

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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.
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.
Mask all rubber and other non metals.
Composites if possible, shall be removed from airplane prior to stripping.
Mask all honeycomb panels and all fasteners which penetrate honeycomb panels.
Mask all pivots, bearings and landing gear.
Titanium, if used on airplane, must be protected from strippers.
Mask all skin laps, inspection holes, drain holes, or any opening that would allow stripper
to enter airplane structure.
1

(b)
(c)
(d)
(e)
(f)
(g)

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.

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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)

(5)
(6)
(7)
(8)
(9)
(10)
(11)
(12)
(13)
C.

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.
Allow stripper coating to lay on the surface until paint lifts.
After paint begins to lift, use a propylene bristle brush to agitate stripper to allow deeper
penetration of stripper.
Remove lifted paint with a plastic squeegee. Dispose of residue in accordance with local
regulations.
Inspect all surfaces for incomplete paint removal.
(a) Repeat previous procedural steps as necessary until all paint is removed.
After stripping airplane, thoroughly rinse to remove any stripping residue.
Remove tape applied to protect joints and other masked areas.
Carefully remove remaining paint at skin joints and masked areas by sanding with a hand or
jitterbug type sander.
If necessary to remove paint from inside skin joints, refer to Cleanout of Skin Joints.
If corrosion is encountered, refer to Structural Repair Manual, Chapter 51, Corrosion/Repair, for
corrosion treatment.

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:
6.

Surface conditioning disc will wear rapidly, it will be necessary to resharpen (retaper)
disc frequently.

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.

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(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.

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FUEL, WEATHER AND HIGH-TEMPERATURE SEALING - MAINTENANCE PRACTICES
1.

General
A.

2.

Procedures for application of sealants are provided for various types of sealing required for the
airplane.

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
NAME

NUMBER

MANUFACTURER

USE

Sealants

GC-408

Goal Chemical Sealant Corp.
3137 East 26th Street
Los Angeles, CA 90023

Fuel, pressure and weather
sealant brush application.

Pro-Seal 890

PRC-DeSoto International
5454 San Fernando Rd.
Glendale, CA 91209

PR-1440

PRC-DeSoto International

SEALANTS TYPE I, CLASS B-1/4, QUICK REPAIR - MIL-S-83318
Sealant

GC-435

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
NAME

NUMBER

MANUFACTURER

USE

Sealants

PR-1440

PRC-DeSoto International

Fuel pressure and
weather sealant,
suitable for application
by extrusion gun and
spatula.

AC-236

Advanced Chemistry And
Technology

CS 3204

Flamemaster Corporation

Pro Seal 890

PRC-DeSoto International

SEALANTS TYPE I, CLASS C-20, C-48 OR C-80
Sealant

Pro-Seal 890

PRC-DeSoto International

Fuel, pressure and
weather sealant. Suitable
for faying surface sealing.

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SEALANTS TYPE IV
Dapco 2100

D. Aircraft Inc.
Anaheim, CA 92807

Firewall and wire bundle
sealing.

Pro Seal 700

PRC-DeSoto International

Firewall sealing (except
wire bundles).

Q3-6077

Dow Corning

Wire bundle firewall
sealing.

Sealant

FA-0606 125

HB Fuller
St. Paul, MN 55116

Water and weather-tight
acrylic latex sealant for
windows and metal lap
joints.

Sealant

SM8500

Schnee-Moorehead
Irving, TX 75017

Water and weather-tight
acrylic latex sealant for
windows and metal lap
joints.

Sealant

SEALANTS TYPE VI

SEALANT TYPE VIII, CLASS B-1/2 ORB2 - MIL-S-8784
Sealant

Low adhesion access
door, fuel, pressure and
weather sealing.

PR-1428 Class

PRC-DeSoto International

PR-1081 Class

PRC-DeSoto International

U000927S

Available from
Cessna Parts Distribution
Cessna Aircraft Company
Department 701
5800 E. Pawnee Rd.
Wichita, KS 67218-5590

Permanently pliable
extruded tape for fixed
windows.

SEALANT TYPE XI
Sealant

CLEANING SOLVENTS
NAME

NUMBER

MANUFACTURER

USE

1, 1, 1 Trichloroethane
Technical
Inhibited (Methyl
Chloroform)

Federal
Specification
ASTM D4126

Commercially Available

Before sealing cleaning.

Commercially Available

Cleaning organic coating.

Methyl Propyl
Ketone

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CLEANING SOLVENTS
NAME

NUMBER

MANUFACTURER

USE

Naphtha Type II

Federal
Specification
TT-N-95

Commercially Available

Before sealing cleaning.

Cleaning
compound

A-A-59281

Commercially Available

Before sealing cleaning.

Isopropyl alcohol

Federal
Specification
TT-I-735

Commercially Available

Cleaning plastic. (Except
plastic transparencies)

NAME

NUMBER

MANUFACTURER

USE

Silicone compound

AS 8660

Commercially available

Prevent sealant sticking.

Petrolatum
technical

Federal
Specification
VV-P-236

Commercially available

Prevent sealant sticking.

Pneumatic sealing
gun.

Semco
Number
250 with
accessories
(or equivalent)

PRC-DeSoto International

Injection sealing.

Hand-operated
sealing gun

Semco
Number 850

PRC-DeSoto International

Injection sealing.

PRC-DeSoto International

Application of sealant.

Polyethylene
cartridges with
plungers and caps
for sealant gun.

Commercially available

Application of sealant.

Metal spatulas with
either stainless
steel or glass
plates.

Commercially available

Mixing sealant.

PARTING AGENTS

EQUIPMENT

Nozzles,
Round 1/16 orifice

Semco
Number 420

Round 1/8 orifice

Semco
Number 440

Duckbill

Semco
Number 8615

Duckbill

Semco
Number 8648

Comb

Semco
Number 8646

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EQUIPMENT
Plastic lined cups,
wax-free with caps

Commercially available

Mixing sealant.

Sealant fairing
tools

Commercially available

To fair-in sealant.

Cheesecloth,
lint-free

Commercially available

Cleaning.

Plastic scraper,
45- degree cutting
edge.

Commercially available

Removing old sealant.

Rex Gauge Company, Inc.
3230 West Lake Avenue
P.O. Box 46
Glenview, IL 60025

Testing cure of sealant.

Gloves, lightweight
lint-free white
cotton

Commercially available

Removing old sealant.

Nylon bristle
brushes

Commercially available

Removing old sealant.

Pipe cleaners

Commercially available

Cleaning.

Funnel brushes

Commercially available

Cleaning.

Durometer

3.

Rex Model
1500 (or
equivalent)

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.)

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(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.

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Table 201. Curing Properties of Type I Sealant

5.

TACK-FREE
TIME (HOURS,
MAXIMUM)

CURING RATE
(HOURS,
MAXIMUM)

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)

CLASS

APPLICATION
TIME (HOURS,
MINIMUM)

A-1/2

WORK LIFE
(HOURS,
MINIMUM)

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.

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(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.

7.

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.

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.
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(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)
(2)

Pull dasher rod to the FULL OUT position so that the dasher is at the nozzle end of the cartridge.
Insert ramrod in the center of the dasher rod against the piston and push the piston in
approximately one inch (25 mm).
NOTE:

(3)

Extra force will be needed on the ramrod at the beginning of accelerator injection into
the base material.

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.
A minimum of five full clockwise revolutions must be made for each full out stroke and
1
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).

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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)

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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.
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.

C.

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.
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.
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.

F.

G.

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.
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J.

9.

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.

Sealing Application
A.

B.

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.
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.

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B1111

INSPECTION
PANEL
(TYPICAL)

RAILING
SKIN

TO
SK

NG EDGE
STIFFENER

BO

05261010
05261009
05261011

Integral Fuel Compartment Sealing
Figure 202 (Sheet 1)

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81112

FAYING SURFACE SEAL

TYPICAL RIB
SECTION

FAY SEAL
(SEALANT
EXTRUDED
CONTINUOUSLY)

SEALANT EXTRUDED
CONTINUOUSLY

5598T2007
5598T2007

Integral Fuel Compartment Sealing
Figure 202 (Sheet 2)

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B1377

I

I

I

I

I
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)

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B1113

PNEUMATIC
SEAL TOOL

55981009

Integral Fuel Compartment Sealing
Figure 202 (Sheet 4)

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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.
2

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.

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10.

Sealant Repair
A.

B.

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.

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.

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(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) Mix PR-1826 Class B sealant according to instructions supplied with the material.
(5) 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.

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CONVERSION DATA - DESCRIPTION AND OPERATION
1.

2.

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.

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:
(2)

(3)

Reference conversion factors in Figure 1.

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).
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.

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MAINTENANCE MANUAL

MULTIPLY

TO OBTAIN

BY

CENTIMETERS

0.3937
0.03281

INCHES
FEET

CUBIC
CENTIMETERS

0.001
0.06102
0.0002642

LITERS
CUBIC INCHES
U.S. GALLONS

CUBIC FEET

28,320
1,728
7.481
28.32

CUBIC INCHES

CUBIC
METERS

16.39
0.01639
0.004329
0.01732
1,000,000
35.31
61,023
264.2
999.97

FEET

0.3048
12,000
304.8
0.3333

FOOT-POUNDS

FLUID OUNCE

CUBIC CENTIMETERS
CUBIC INCHES
U.S. GALLONS
LITERS

0.1383
0.001285
0.000000376
8
29.6

CUBIC CENTIMETERS
LITERS
U.S. GALLONS
QUARTS
CUBIC CENTIMETERS
CUBIC FEET
CUBIC INCHES
GALLON
LITERS
METERS
MILS
MILLIMETERS
YARDS
METER-KILOGRAMS
BRITISH THERMO UNIT
KILOWATTS PER HOUR
DRAM
CUBIC CENTIMETERS

GALLON,
IMPERIAL

277.4
1.201
4.546

CUBIC INCHES
U.S. GALLON
LITERS

GALLON,
U.S. DRY

268.8
0.1556
1.164
4.405

CUBIC INCHES
CUBIC FEET
U.S. GALLON, LIQUID
LITERS

GALLON,
U.S. LIQUID

231.0
0.1337
3.785
0.8327
128

CUBIC INCHES
CUBIC FEET
LITERS
IMPERIAL GALLON
FLUID OUNCES

INCHES

2.540
.08333

CENTIMETERS
FEET

Conversion Factors
Figure 1 (Sheet 1)

20-50-00
©Cessna Aircraft Company

Page 2

April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

MULTIPLY

BY
0.000948
0.7376

JOULES

2.205
35.27

KILOGRAMS

1000
LITERS

1000

61.03
0.03532
0.2642
0.22
1.057
39.37
3.281

METERS

1000
METER-KILOGRAM
OUNCES,
AVOIRDUPOIS
OUNCES, FLUID
POUND,
AVOIRDUPOIS

7.233
9.807
0.0625
28.35
437.5
29.57
1.805
453.6
7000
16.0

TO OBTAIN
BRITISH THERMO UNIT
FOOT-POUNDS
POUNDS
OUNCES
GRAMS
CUBIC CENTIMETERS
CUBIC INCHES
CUBIC FEET
U.S. GALLON
IMPERIAL GALLON
QUARTS
INCHES
FEET
MILLIMETERS
FOOT-POUNDS
JOULES
POUND, AVOIRDUPOIS
GRAMS
GRAINS
CUBIC CENTIMETERS
CUBIC INCHES
GRAMS
GRAINS
OUNCES

SQUARE INCH

6.4516

SQUARE CENTIMETERS

POUND PER
SQUARE INCH
(PSI)

0.0703

KILOGRAM-CENTIMETER
SQUARED

STATUTE MILE

1.609
0.0684

KILOMETER
NAUTICAL MILE

NAUTICAL MILE

1.151

STATUTE MILE

QUART

0.9463

LITER

MILLIMETER
MICRON

1000
0.001

0.00003937

MICRON
MILLIMETER
INCH

INCH POUNDS

11.521

METER GRAMS

INCH OUNCES

0.72

METER GRAMS

Conversion Factors
Figure 1 (Sheet 2)

20-50-00
© Cessna Aircraft Company

Page 3

April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

INCH-POUNDS TO CENTIMETER-KILOGRAMS
INCHPOUNDS
5
10
15
20
25
30
35
40

CENTIMETER- INCHKILOGRAMS POUNDS
5.76
45
11.52
50
17.28
55
23.04
60
28.80
65
34.56
70
40.32
75
46.08
80

CENTIMETERINCHKILOGRAMS POUNDS
51.84
85
57.60
90
63.36
95
69.12
100
74.88
105
110
80.64
86.40
115
92.16
120

CENTIMETERKILOGRAMS
97.82
103.68
109.44
115.20
120.96
126.72
132.48
138.24

CENTIMETER-KILOGRAMS TO INCH-POUNDS
INCHCENTIMETERINCHCENTIMETERINCHCENTIMETERKILOGRAMS POUNDS KILOGRAMS POUNDS KILOGRAMS POUNDS
477.4
50
43.4
300
260.4
550
520.8
100
86.8
350
303.8
600
564.2
150
130.2
400
347.2
650
607.6
390.6
700
173.6
450
200
250
217.0
500
434.0

FOOTPOUNDS
2.5
5.0
7.5
10.0

FOOT-POUNDS TO METER-KILOGRAMS
FOOTMETERFOOTMETERKILOGRAMS POUNDS KILOGRAMS POUNDS
165
.346
67.5
9.332
170
.691
70.0
9.678
1.037
10.024
175
72.5
1.383
10.369
180
75.0

METERKILOGRAMS
22.813
23.504
24.195
24.887

12.5
15.0
17.5
20.0

1.728
2.074
2.419
2.765

77.5
80.0
82.5
85.0

10.715
11.060
11.406
11.752

185
190
195
200

25.578
26.269
26.960
27.652

22.5
25.0
27.5
30.0

3.111
3.456
3.802
4.148

87.5
90.0
92.5
95.0

12.097
12.443
12.789
13.134

205
210
215
220

28.343
29.034
29.726
30.417

32.5
35.0
37.5
40.0

4.493
4.839
5.185
5.530

97.5
100.0
102.5
105.0

13.480
13.826
14.517
15.208

225
230
235
240

31.108
31.800
32.491
33.182

42.5
45.0
47.5
50.0

5.876
6.222
6.567
6.913

110.0
120.0
125.0
130.0

15.900
16.591
17.282
17.974

245
250
255
260

33.873
34.565
35.256
35.947

52.5
55.0
57.5
60.0

7.258
7.604
7.950
8.285

135.0
140.0
145.0
150.0

18.665
19.356
20.047
20.739

265
270
275
280

36.639
37.330
38.021
38.713

62.5
65.0

8.641
8.987

155.0
160.0

21.430
22.121

285
290
295
300

39.404
40.095
40.786
41.478

Torque Conversion Chart
Figure 2 (Sheet 1)

20-50-00
© Cessna Aircraft Company

Page 4
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

METER-KILOGRAMS TO FOOT-POUNDS
METERMETERFOOTMETERFOOTKILOGRAMS POUNDS KILOGRAMS POUNDS KILOGRAMS
15
57.86
8
1
7.23
2
16
9
65.89
14.46
72.32
17
10
3
21.69
28.93
11
79.56
18
4
19
86.79
5
36.16
12
6
43.39
13
94.02
20
21
101.26
14
7
50.63
22

FOOTPOUNDS
108.49
115.72
122.95
130.19
137.42
144.65
151.89
159.12

Torque Conversion Chart
Figure 2 (Sheet 2)

20-50-00
©Cessna Aircraft Company

Page 5

April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

B1898

INCHES-

0.0000

0.0001

0.0002

0.0003

0.0004

0.0005

0.0006

0.0007

0.0008 0.0009

0.0203
0.0457
0.0711
0.0965
0.1219

0.0228
0.0482
0.0736
0.0990
0.1244

MILLIMETER
0.0254
0.0508
0.0762
0.1016

0.0025
0.0279
0.0533
0.0787
0.1041

0.0050
0.0304
0.0558
0.0812
0.1066

0.0076
0.0330
0.0584
0.0838
0.1092

0.0101
0.0355
0.0609
0.0863
0.1117

0.0127
0.0381
0.0635
0.0889
0.1143

0.0152
0.0406

0.1168

0.0177
0.0431
0.0685
0.0939
0.1193

0.009

0.1270
0.1524
0.1778
0.2032
0.2286

0.1295
0.1549
0.1803
0.2057
0.2311

0.1320
0.1574
0.1828
0.2082
0.2336

0.1346
0.1600
0.1854
0.2108
0.2362

0.1371
0.1625
0.1879
0.2133
0.2387

0.1397
0.1651
0.1905
0.2159
0.2413

0.1422
0.1676
0.1930
0.2184
0.2438

0.1447
0.1701
0.1955
0.2209
0.2463

0.1473
0.1727
0.1981
0.2235
0.2489

0.1498
0.1752
0.2006
0.2260
0.2514

INCHES-

0.000

0.001

0.002

0.003

0.004

0.005

0.006

0.007

0.008

0.009

0.000
0.001
0.002

0.003
0.004
0.005
0.006
0.007

0.008

0.0660
0.0914

MILLIMETER
0.00
0.01
0.02
0.03
0.04
0.05
0.06
0.07

0.08
0.09

0.254
0.508
0.762
1.016

0.025
0.279
0.533
0.787
1.041

0.050
0.304
0.558
0.812
1.066

0.076
0.330
0.584
0.838
1.092

0.101
0.355
0.609
0.863
1.117

0.127
0.381
0.635
0.889
1.143

0.152
0.406
0.660
0.914
1.168

0.177
0.431
0.685
0.939
1.193

0.203
0.457
0.711
0.965
1.219

0.228
0.482
0.736
0.990
1.244

1.270
1.524
1.778
2.032
2.286

1.295
1.549
1.803
2.057
2.311

1.320
1.574
1.828
2.082
2.336

1.346
1.600
1.854
2.108
2.362

1.371
1.625
1.879
2.133
2.387

1.397
1.651
1.905
2.159
2.413

1.422
1.676
1.930
2.184
2.438

1.447
1.701
1.955
2.209
2.463

1.473
1.727
1.981
2.235
2.489

1.498
1.752
2.006
2.260
2.514

Inches to Millimeter (0.0001 to 10 inches)
Figure 3 (Sheet 1)

20-50-00
© Cessna Aircraft Company

Page 6
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1899

INCHES-

0.00

0.01

0.02

0.03

0.04

0.05

0.06

0.07

0.08

0.09

MILLIMETER

0.0
0.1
0.2
0.3
0.4
0.5
0.6
0.7

0.8
0.9
INCHES-

2.540
5.080
7.620
10.160

0.254
2.794
5.334
7.874
10.414

0.508
3.048
5.588
8.128
10.668

0.762
3.302
5.842
8.382
10.922

0.016
3.556
6.096
8.636
11.176

1.270
3.810
6.350
8.890
11.430

1.524
4.064
6.604
9.144
11.684

1.778
4.318
6.858
9.398
11.938

2.032
4.572
7.112
9.652
12.192

2.286
4.826
7.366
9.906
12.446

12.700
15.240
17.780
20.320
22.860

12.954
5.494
18.034
20.574
23.114

13.208
15.748
18.288
20.828
23.368

13.462
16.002
18.542
21.082
23.622

13.716
16.256
18.796
21.336
23.876

13.970
16.510
19.050
21.590
24.130

14.224
16.764
19.304
21.844
24.384

14.478
17.018
19.558
22.098
24.638

14.732
17.272
19.812
22.352
24.892

14.986
17.526
20.066
22.606
25.146

0.5

0.6

0.7

0.00

0.1

0.2

0.3

0.4

0.8

0.9

MILLIMETER

0
1
2
3
4

25.40
50.80
76.20
101.60

2.54
27.94
53.34
78.74
104.14

5.08
30.48
55.88
81.28
106.68

7.62
33.02
58.42
83.82
109.22

10.16
35.56
60.96
86.36
111.76

12.70
38.10
63.50
88.90
114.30

15.24
40.64
66.04
91.44
116.84

17.78
43.18
68.58
93.98
119.38

20.32
45.72
71.12
96.52
121.92

22.86
48.26
73.66
99.06
124.46

5
6
7
8
9

127.00
152.40
177.80
203.20
228.60

129.54
154.94
180.34
205.74
231.14

132.08
157.48
182.88
208.28
233.68

134.62
160.02
185.42
210.82
236.22

137.16
162.56
187.96
213.36
238.76

139.70
165.10
190.50
215.90
241.30

142.24
167.64
193.04
218.44
243.84

144.78
170.18
195.58
220.98
246.38

147.32
172.72
198.12
223.52
248.92

149.86
175.26
200.66
226.06
251.46

Inches to Millimeter (0.0001 to 10 inches)
Figure 3 (Sheet 2)

20-50-00
© Cessna Aircraft Company

Page 7

April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

B1900

FRACTION
1/64

DECIMAL
EQUIV.

MILLIMETER

FRACTION

DECIMAL
EQUIV.

MILLIMETER

0.396

33/64

0.515

13.096

0.793
1.190
1.587

35/64
9/16

0.531
0.546
0.562

13.493
13.890

1/16

0.031
0.046
0.062

17/32

5/64

0.078

1.984

37/64

0.578

14.684

3/32

0.093

0.593

15.081

0.109

2.381
2.778

19/32

7/64
1/8

0.609

0.125

3.175

39/64
5/8

0.625

15.478
15.875

9/64

0.140

3.571

41/64

0.640

16.271

5/32
11/64

0.156
0.171

3.968
4.365

21/32
43/64

0.656
0.671

16.668
17.065

3/16

0.187

4.752

11/16

0.687

17.462

13/64

0.203

5.159

45/64

0.703

7/32
15/64

0.218
0.234

5.556
5.953

23/32
47/64

0.718
0.734

17.859
18.256

1/4

0.250

6.350

3/4

0.750

19.050

17/64

6.746
7.143
7.540

49/64

0.765
0.781
0.796

5/16

0.265
0.281
0.296
0.312

0.812

19.446
19.843
20.240
20.637

21/64

0.328

21.034

0.343

53/64
27/32
55/64
7/8

0.828

11/32

8.334
8.731

0.843

21.431

0.859
0.875

21.828
22.225

57/64
29/32
59/64
15/16

0.890
0.906
0.921

22.621

0.937

23.812

0.953

24.209

0.968

24.606

0.984
1.000

25.003

1/32
3/64

9/32
19/64

23/64

0.015

7.937

25/32
51/64
13/16

0.359
0.375

9.128

9.921

13/32
27/64

0.390
0.406
0.421

10.318
10.715

7/16

0.437

11.112

29/64

0.453

11.509

15/32

0.468

11.906

31/64

0.484

12.303

61/64
31/32
63/64

1/2

0.500

12.700

1

3/8
25/64

9.525

14.287

18.653

23.018
23.415

25.400

Fraction to Decimal to Millimeter Conversion
Figure 4 (Sheet 1)

20-50-00
© Cessna Aircraft Company

Page 8

April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1901

READ LEFT COLUMN
TO CONVERT TO
CELSIUS

READ KNOWN
TEMPERATURE IN THIS
COLUMN (FAHRENHEIT
OR CELSIUS)

I

C

READ RIGHT COLUMN
TO CONVERT TO
FAHRENHEIT

I

I

F

I

I

C

F

C

F

-73.3
-72.8
-72.2
-71.7
-71.1

-100
-99
-98
-97
-96

-148.0
-146.2
-144.4
-142.6
-140.8

-51.1
-50.6
-50.0
-49.4
-48.9

-60
-59
-58
-57
-56

-76.0
-74.2
-72.4
-70.6
-68.8

-28.9
-28.3
-27.8
-27.2
-26.7

-20

-70.6
-70.0
-69.4
-68.9
-68.3

-95
-94
-93
-92
-91

-139.0
-137.2
-135.4
-133.6
-131.8

-48.3
-47.8
-47.2
-46.7
-46.1

-55
-54
-53
-52
-51

-67.0
-65.2
-63.4
-61.6
-59.8

-26.1
-25.6
-25.0
-24.4
-23.9

-15
-14

-67.8
-67.2
-66.7
-66.1
-65.6

-90
-89
-88
-87
-86

-130.0
-128.2
-126.2
-124.6
-122.8

-45.6
-45.0
-44.4
-43.9
-43.5

-50
-49
-48
-47
-46

-58.0
-56.2
-54.4
-52.6
-50.8

-23.3
-22.8
-22.2
-21.7
-21.1

-65.0
-64.4
-63.9
-63.3
-62.8

-85
-84
-83
-82
-81

-121.0
-119.2
-117.4
-115.6
-113.8

-42.8
-42.2
-41.7
-41.1
-40.6

-45
-44
-43
-42
-41

-49.0
-47.2
-45.4
-43.6
-41.8

-62.2
-61.7
-61.1
-60.6
-60.0

-80
-79
-78
-77
-76

-112.0
-110.2
-108.4
-106.6
-104.8

-40.0
-39.4
-38.9
-38.3
-37.8

-40
-39
-38
-37
-36

-59.4
-58.9
-58.3
-57.8
-57.2

-75
-74
-73
-72
-71

-103.0
-101.2
-99.4
-97.6
-95.8

-37.2
-36.7
-36.1
-35.6
-35.0

56.7
-56.1
-55.6
-55.0
-54.4

-70
-69
-68
-67
-66

-94.0
-92.2
-90.4
-88.6
-86.8

-53.9
-53.3
-52.8
-52.2
-51.7

-65
-64
-63
-62
-61

-85.0
-83.2
-81.4
-79.6
-77.8

F

C

-4.0
-2.2
-0.4
1.4
3.2

-6.7
-6.1
-5.6
-5.0
-4.4

20
21
22
23
24

68.0
69.8
71.6
73.4
75.2

5.0
6.8
8.6
10.4
12.2

-3.9
-3.3
-2.8
-2.2
-1.7

25
26
27
28
29

77.0
78.8
80.6
82.4
84.2

-10
-9
-8
-7
-6

14.0
15.8
17.6
21.2

-1.1
-0.6
0.0
0.6
1.1

30
31
32
33
34

86.0
87.8
89.6
91.4
93.2

-20.6
-20.0
-19.4
-18.9
-18.3

-5
-4
-3
-2
-1

23.0
24.8
26.6
28.4
30.2

1.7
2.2
2.8
3.3
3.9

35
36
37
38
39

95.0
96.8
98.6
100.4
102.2

-40.0
-38.2
-36.4
-34.6
-32.8

-17.8
-17.2
-16.7
-16.1
-15.6

0
1
2
3
4

32.0
33.8
35.6
37.4
39.2

4.4
5.0
5.6
6.1
6.7

40
41
42
43
44

104.0
105.8
107.6
109.4
111.2

-35
-34
-33
-32
-31

-31.0
-29.0
-27.4
-25.6
-23.8

-15.0
-14.4
-13.9
-13.3
-12.8

5
6
7
8
9

41.0
42.8
44.6
46.4
48.2

7.2
7.8
8.3
8.9
9.4

45
46
47
48
49

113.0
114.8
116.6
118.4
120.2

-34.4
-33.9
-33.3
-32.8
-32.2

-30
-29
-28
-27
-26

-22.0
-20.2
-18.4
-16.6
-14.8

-12.2
-11.7
-11.1
-10.6
-10.0

10

50.0
51.8
53.6
55.4
57.2

10.0
10.6
11.1
11.7
12.2

50
51
52
53
54

122.0
123.8
125.6
127.4
129.2

-31.7
-31.1
-30.6
-30.0
-29.4

-25
-24
-23
-22
-21

-13.0
-11.2
-9.4
-7.6
-5.8

-9.4
-8.9
-8.3
-7.8
-7.2

15
16
17

59.0
60.8
62.6
64.4
66.2

12.8
13.3
13.9
14.4
15.0

55
56
57
58
59

131.0
132.8
134.6
136.4
138.2

-19
-18
-17

-16

-13
-12
-11

11
12
13

14

18

19

19.4

Fahrenheit and Celsius (Centigrade) Temperature Conversion
Figure 5 (Sheet 1)

20-50-00
© Cessna Aircraft Company

Page 9

April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

B1902

C

F

C

F

C

F

C

F

15.6
16.1
16.7
17.2
17.8

60
61
62
63
64

140.0
141.8
143.6
145.4
147.2

37.8
38.3
38.9
39.4
40.0

100
101
102
103
104

212.0
213.8
215.6
217.4
219.2

60.0
60.6
61.1
61.7
62.2

140
141
142
143
144

284.0
285.8
287.6
289.4
291.2

82.2
82.8
83.3
83.9
84.4

180
181
182
183
184

356.0
357.8
359.6
361.4
363.2

18.3
18.9
19.4
20.0
20.6

65
66
67
68
69

149.0
150.8
152.6
154.4
156.2

40.6
41.1
41.7
42.2
42.8

105
106
107
108
109

221.0
222.8
224.6
226.4
228.2

62.8
63.3
63.9
64.4
65.0

145
146
147
148
149

293.0
294.8
296.6
298.4
300.2

85.0
85.6
86.1
86.7
87.2

185
186
187
188
189

365.0
366.8
368.6
370.4
372.2

21.1
21.7
22.2
22.8
23.3

70
71
72
73
74

158.0
159.8
161.6
163.4
165.2

43.3
43.9
44.4
45.0
45.6

110
111
112
113
114

230.0
231.8
233.6
235.4
237.2

65.6
66.1
66.7
67.2
67.8

150
151
152
153
154

302.0
303.8
305.6
307.4
309.2

87.8
88.3
88.9
89.4
90.0

190
191
192
193
194

374.0
375.8
377.6
379.4
381.2

23.9
24.4
25.0
25.6
26.1

75
76
77
78
79

167.0
168.8
170.6
172.4
174.2

46.1
46.7
47.2
47.8
48.3

115
116
117
118
119

239.0
240.8
242.6
244.4
246.2

68.3
68.9
69.4
70.0
70.6

155
156
157
158
159

311.0
312.8
314.6
316.4
318.2

90.6
91.1
91.7
92.2
92.8

195
196
197
198
199

383.0
384.8
386.6
388.4
390.2

26.7
27.2
27.8
28.3
28.9

80
81
82
83
84

176.0
177.8
179.6
181.4
183.2

48.9
49.4
50.0
50.6
51.1

120
121
122
123
124

248.0
249.8
251.6
253.4
255.2

71.1
71.7
72.2
72.8
73.3

160
161
162
163
164

320.0
321.8
323.6
325.3
327.2

93.3
93.9
94.4
95.0
95.6

200
201
202
203
204

392.0
393.8
395.6
397.4
399.2

29.4
30.0
30.6
31.1
31.7

85
86
87
88
89

185.0
186.8
188.6
190.4
192.2

51.7
52.2
52.8
53.3
53.9

125
126
127
128
129

257.0
258.8
260.6
262.4
264.2

73.9
74.4
75.0
75.6
76.1

165
166
167
168
169

329.0
330.8
332.6
334.4
336.2

96.1
96.7
97.2
97.8
98.3

205
206
207
208
209

401.0
402.8
404.6
406.4
408.2

32.2
32.8
33.3
33.9
34.4

90
91
92
93
94

194.0
195.8
197.6
199.4
201.2

54.4
55.0
55.6
56.1
56.7

130
131
132
133
134

266.0
267.8
269.6
271.4
273.2

76.7
77.2
77.8
78.3
78.9

170
171
172
173
174

338.0
339.8
341.6
343.4
345.2

98.9
99.4
100.0
100.6
101.1

210
211
212
213
214

410.0
411.8
413.6
415.4
417.2

35.0
35.6
36.1
36.7
37.2

95
96
97
98
99

203.0
204.8
206.6
208.4
210.2

57.2
57.8
58.3
58.9
59.4

135
136
137
138
139

275.0
276.8
278.6
280.4
282.2

79.4
80.0
80.6
81.1
81.7

175
176
177
178
179

347.0
348.8
350.6
352.4
354.2

101.7
102.2
102.8
103.3
103.9

215
216
217
218
219

419.0
420.8
422.6
424.4
426.2

Fahrenheit and Celsius (Centigrade) Temperature Conversion
Figure 5 (Sheet 2)

©Cessna Aircraft Company

20-50-00 Page 10
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1903

C

F

C

C

F

F

C

F

104.4
105.0
105.6
106.1
106.7

220
221
222
223
224

428.0
429.8
431.6
433.4
435.2

148.9
151.7
154.4
157.2
160.0

300
305
310
315
320

572.0
581.0
590.0
599.0
608.0

260.0
262.8
265.6
268.3
271.1

500
505
510
515
520

932.0
941.0
950.0
959.0
968.0

371.1
373.9
376.7
379.4
382.2

700
705
710
715
720

1292.0
1301.0
1310.0
1319.0
1328.0

107.2
107.8
108.3
108.9
109.4

225
226
227
228
229

437.0
438.8
440.6
442.4
444.2

162.8
165.6
168.3
171.1
173.9

325
330
335
340
345

617.0
626.0
635.0
644.0
653.0

273.9
276.7
279.4
282.2
285.0

525
530
535
540
545

977.0
986.0
995.0
1004.0
1013.0

385.0
387.8
390.6
393.3
396.1

725
730
735
740
745

1337.0
1346.0
1355.0
1364.0
1373.0

110.0
110.6
111.1
111.7
112.2

230
231
232
233
234

446.0
447.8
449.6
451.4
453.2

176.7
179.4
182.2
185.0
187.8

350
355
360
365
370

662.0
671.0
680.0
689.0
698.0

287.8
290.6
293.3
296.1
298.9

550
555
560
565
570

1022.0
1031.0
1040.0
1049.0
1058.0

398.9
401.7
404.4
407.2
410.0

750
755
760
765
770

1382.0
1391.0
1400.0
1409.0
1418.0

112.8
113.3
113.9
114.4
115.0

235
236
237
238
239

455.0
456.8
458.6
460.4
462.2

190.6
193.3
196.1
198.9
201.7

375
380
385
390
395

707.0
716.0
725.0
734.0
743.0

301.7
304.4
307.2
310.0
312.8

575
580
585
590
595

1067.0
1076.0
1085.0
1094.0
1103.0

412.8
415.6
418.3
421.1
423.9

775
780
785
790
795

1427.0
1436.0
1445.0
1454.0
1463.0

115.6
116.1
116.7
117.2
117.8

240
241
242
243
244

464.0
465.8
467.6
469.4
471.2

204.4
207.2
210.0
212.8
215.6

400
405
410
415
420

752.0
761.0
770.0
779.0
788.0

315.6
318.3
321.1
323.9
326.7

600
605
610
615
620

1112.0
1121.0
1130.0
1139.0
1148.0

426.7
429.4
432.2
435.0
437.8

800
805
810
815
820

1472.0
1481.0
1490.0
1499.0
1508.0

118.3
118.9
119.4
120.0
120.6

245
246
247
248
249

473.0
474.8
476.6
478.4
480.2

218.3
221.1

425
430

223.9

435

226.7

440

229.4

445

797.0
806.0
815.0
824.0
833.0

329.4
332.2
335.0
337.8
340.6

625
630
635
640
645

1157.0
1166.0
1175.0
1184.0
1193.0

440.6
443.3
446.1
448.9
451.7

825
830
835
840
845

1517.0
1526.0
1535.0
1544.0
1553.0

121.1
123.9
126.7
129.4
132.2

250
255
260
265
270

482.0
491.0
500.0
509.0
518.0

232.2
235.0
237.8
240.6
243.3

450
455
460
465
470

842.0
851.0
860.0
869.0
878.0

343.3
346.1
348.9
351.7
354.4

650
655
660
665
670

1202.0
1211.0
1220.0
1229.0
1238.0

454.4
457.2
460.0
462.8
465.6

850
855
860
865
870

1562.0
1571.0
1580.0
1589.0
1598.0

135.0
137.8
140.6
143.3
146.1

275
280
285
290
295

527.0
536.0
545.0
554.0
563.0

246.1
248.9
251.7
254.4
257.2

475
480
485
490
495

887.0
896.0
905.0
914.0
923.0

357.2
360.0
362.8
365.6
368.3

675
680
685
690
695

1247.0
1256.0
1265.0
1274.0
1283.0

468.3
471.1
473.9
476.7
479.4

875
880
885
890
895

1607.0
1616.0
1625.0
1634.0
1643.0

Fahrenheit and Celsius (Centigrade) Temperature Conversion
Figure 5 (Sheet 3)

20-50-00
© Cessna Aircraft Company

Page 11
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1904

F

C

F

C

F

C

F

C

482.2
485.0
487.8
490.6
493.3

900
905
910
915
920

1652.0
1661.0
1670.0
1679.0
1688.0

593.3
596.1
598.9
601.7
604.4

1100
1105
1110
1115
1120

2012.0
2021.0
2030.0
2039.0
2048.0

704.4
707.2
710.0
712.8
715.6

1300
1305
1310
1315
1320

2372.0
2381.0
2390.0
2399.0
2408.0

815.6
818.3
821.1
823.9
826.7

1500
1505
1510
1515
1520

2732.0
2741.0
2750.0
2759.0
2768.0

496.1
498.9
501.7
504.4
507.2

925
930
935
940
945

1697.0
1706.0
1715.0
1724.0
1733.0

607.2
610.0
612.8
615.6
618.3

1125
1130
1135
1140
1145

2057.0
2066.0
2075.0
2084.0
2093.0

718.3
721.1
723.9
726.7
729.4

1325
1330
1335
1340
1345

2417.0
2426.0
2435.0
2444.0
2453.0

829.4
832.2
835.0
837.8
840.6

1525
1530
1535
1540
1545

2777.0
2786.0
2795.0
2804.0
2813.0

510.0
512.8
515.6
518.3
521.1

950
955
960
965
970

1742.0
1751.0
1760.0
1769.0
1778.0

621.1
623.9
626.7
629.4
632.2

1150
1155
1160
1165
1170

2102.0
2111.0
2120.0
2129.0
2138.0

732.2
735.0
737.8
740.6
743.3

1350
1355
1360
1365
1370

2462.0
2471.0
2480.0
2489.0
2498.0

843.3
846.1
848.9
851.7
854.4

1550
1555
1560
1565
1570

2822.0
2831.0
2840.0
2849.0
2858.0

523.9
526.7
529.4
532.2
535.0

975
980
985
990
995

1787.0
1796.0
1805.0
1814.0
1823.0

635.0
637.8
640.6
643.3
646.1

1175
1180
1185
1190
1195

2147.0
2156.0
2165.0
2174.0
2183.0

746.1
748.9
751.7
754.4
757.2

1375
1380
1385
1390
1395

2507.0
2516.0
2525.0
2534.0
2543.0

857.2
860.0
862.8
865.6
868.3

1575
1580
1585
1590
1595

2867.0
2876.0
2885.0
2894.0
2903.0

537.8
540.6
543.3
546.1
548.9

1000
1005
1010
1015
1020

1832.0
1841.0
1850.0
1859.0
1868.0

648.9
651.7
654.4
657.2
660.0

1200
1205
1210
1215
1220

2192.0
2201.0
2210.0
2219.0
2228.0

760.0
762.8
765.6
768.3
771.1

1400
1405
1410
1415
1420

2552.0
2561.0
2570.0
2579.0
2588.0

871.1
873.9
876.7
879.4
882.2

1600
1605
1610
1615
1620

2912.0
2921.0
2930.0
2939.0
2948.0

551.7
554.4
557.2
560.0
562.8

1025
1030
1035
1040
1045

1877.0
1886.0
1895.0
1904.0
1913.0

662.8
665.6
668.3
671.1
673.9

1225
1230
1235
1240
1245

2237.0
2246.0
2255.0
2264.0
2273.0

773.9
776.7
779.4
782.2
785.0

1425
1430
1435
1440
1445

2597.0
2606.0
2615.0
2624.0
2633.0

885.0
887.8
890.6
893.3
896.1

1625
1630
1635
1640
1645

2957.0
2966.0
2975.0
2984.0
2993.0

565.6
568.3
571.1
573.9
576.7

1050
1055
1060
1065
1070

1922.0
1931.0
1940.0
1949.0
1958.0

676.7
679.4
682.2
695.0
687.8

1250
1255
1260
1265
1270

2282.0
2291.0
2300.0
2309.0
2318.0

787.8
790.0
793.3
796.1
798.9

1450
1455
1460
1465
1470

2642.0
2651.0
2660.0
2669.0
2678.0

898.9
901.7
904.4
907.2
910.0

1650
1655
1660
1665
1670

3002.0
3011.0
3020.0
3029.0
3038.0

579.4
582.2
585.0
587.8
590.6

1075
1080
1085
1090
1095

1967.0
1976.0
1985.0
1994.0
2003.0

690.6
693.3
696.1
698.9
701.7

1275
1280
1285
1290
1295

2327.0
2336.0
2345.0
2354.0
2363.0

801.7
804.4
807.2
810.0
812.8

1375
1480
1485
1490
1495

2687.0
2696.0
2705.0
2714.0
2723.0

912.8
915.6
918.3
921.1
923.9

1675
1680
1685
1690
1695

3047.0
3056.0
3065.0
3074.0
3083.0

Fahrenheit and Celsius (Centigrade) Temperature Conversion
Figure 5 (Sheet 4)

20-50-00
© Cessna Aircraft Company

Page 12
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1905

F

C

F

C

F

C

C

F

926.7
929.4
932.2
935.0
937.8

1700
1705
1710
1715
1720

3092.0
3101.0
3110.0
3119.0
3128.0

1037.8
1040.6
1043.3
1046.0
1048.9

1900
1905
1910
1915
1920

3452.0
3461.0
3470.0
3479.0
3488.0

1148.9
1151.7
1154.4
1157.2
1160.0

2100
2105
2110
2115
2120

3812.0
3821.0
3830.0
3839.0
3848.0

1260.0
1262.8
1265.6
1268.3
1271.1

2300
2305
2310
2315
2320

4172.0
4181.0
4190.0
4199.0
4208.0

940.6
943.3
946.1
948.9
951.7

1725
1730
1735
1740
1745

3137.0
3146.0
3155.0
3164.0
3173.0

1051.7
1054.4
1057.2
1060.0
1062.8

1925
1930
1935
1940
1945

3497.0
3506.0
3515.0
3524.0
3533.0

1162.8
1165.6
1168.3
1171.1
1173.9

2125
2130
2135
2140
2145

3857.0
3866.0
3875.0
3884.0
3893.0

1273.9
1276.7
1279.4
1282.2
1285.0

2325
2330
2335
2340
2345

4217.0
4226.0
4235.0
4244.0
4255.0

954.4
957.2
960.0
962.8
965.6

1750
1755
1760
1765
1770

3182.0
3191.0
3200.0
3209.0
3218.0

1065.6
1068.3
1071.1
1073.9
1076.7

1950
1955
1960
1965
1970

3542.0
3551.0
3560.0
3569.0
3578.0

1176.7
1179.4
1182.2
1185.0
1187.8

2150
2155
2160
2165
2170

3902.0
3911.0
3920.0
3929.0
3938.0

1287.8
1290.6
1293.3
1296.1
1298.9

2350
2355
2360
2365
2370

4262.0
4271.0
4280.0
4289.0
4298.0

968.3
971.1
973.9
976.7
979.4

1775
1780
1785
1790
1795

3227.0
3236.0
3245.0
3254.0
3263.0

1079.4
1082.2
1085.0
1087.8
1090.6

1975
1980
1985
1990
1995

3587.0
3596.0
3605.0
3614.0
3623.0

1190.6
1193.3
1196.1
1198.9
1201.7

2175
2180
2185
2190
2195

3947.0
3956.0
3965.0
3974.0
3983.0

1301.7
1304.4
1307.2
1310.0
1312.8

2375
2380
2385
2390
2395

4307.0
4316.0
4325.0
4334.0
4343.0

982.2
985.0
987.8
990.6
993.3

1800
1805
1810
1815
1820

3272.0
3281.0
3290.0
3299.0
3308.0

1093.6
1096.1
1098.9
1101.7
1104.4

2000
2005
2010
2015
2020

3632.0
3641.0
3650.0
3659.0
3668.0

1204.4
1207.2
1210.0
1212.8
1215.6

2200
2205
2210
2215
2220

3992.0
4001.0
4010.0
4019.0
4028.0

1315.6
1318.3
1321.1
1323.9
1326.7

2400
2405
2410
2415
2420

4352.0
4361.0
4370.0
4379.0
4388.0

996.1
998.9
1001.7
1004.4
1007.2

1825
1830
1835
1840
1845

3317.0
3326.0
3335.0
3344.0
3353.0

1107.2
1110.0
1112.8
1115.6
1118.3

2025
2030
2035
2040
2045

3677.0
3686.0
3695.0
3704.0
3713.0

1218.3
1221.1
1223.9
1226.7
1229.4

2225
2230
2235
2240
2245

4037.0
4046.0
4055.0
4064.0
4073.0

1329.4
1332.2
1335.0
1337.8
1340.6

2425
2430
2435
2440
2445

4397.0
4406.0
4415.0
4424.0
4433.0

1010.0
1012.8
1015.6
1018.3
1021.1

1850
1855
1860
1865
1870

3362.0
3371.0
3380.0
3389.0
3398.0

1121.1
1123.9
1126.7
1129.4
1132.2

2050
2055
2060
2065
2070

3722.0
3731.0
3740.0
3749.0
3758.0

1232.2
1235.0
1237.8
1240.6
1243.3

2250
2255
2260
2265
2270

4082.0
4091.0
4100.0
4109.0
4118.0

1343.3
1346.1
1348.9
1351.7
1354.4

2450
2455
2460
2465
2470

4442.0
4451.0
4460.0
4469.0
4478.0

1023.9
1026.9
1029.4
1032.2
1035.0

1875
1880
1885
1890
1895

3407.0
3416.0
3425.0
3434.0
3443.0

1135.0
1137.8
1140.6
1143.3
1146.1

2075
2080
2085
2090
2095

3767.0
3776.0
3785.0
3794.0
3803.0

1246.1
1248.9
1251.7
1254.4
1257.2

2275
2280
2285
2290
2295

4127.0
4136.0
4145.0
4154.0
4163.0

1357.2
1360.0
1362.8
1365.6
1368.3

2475
2480
2485
2490
2495

4487.0
4496.0
4505.0
4514.0
4523.0

Fahrenheit and Celsius (Centigrade) Temperature Conversion
Figure 5 (Sheet 5)

20-50-00
© Cessna Aircraft Company

Page 13
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1906

F

C

F

C

F

C

1371.1
1373.9
1376.7
1379.4
1382.2

2500
2505
2510
2515
2520

4532.0
4541.0
4550.0
4559.0
4568.0

1398.9
1401.7
1404.4
1407.2
1410.0

2550
2555
2560
2565
2470

4622.0
4631.0
4640.0
4649.0
4658.0

1426.7
1429.4
1432.2
1435.0
1437.8

2600
2605
2610
2615
2620

4712.0
4721.0
4730.0
4739.0
4748.0

1385.0
1387.8
1390.6
1393.3
1396.1

2525
2530
2535
2540
2545

4577.0
4586.0
4595.0
4604.0
4613.0

1412.8
1415.6
1418.3
1421.1
1423.9

2575
2580
2585
2590
2595

4667.0
4676.0
4685.0
4694.0
4703.0

1440.6
1443.3
1446.1
1448.9
1451.7

2625
2630
2635
2640
2645

4757.0
4766.0
4775.0
4784.0
4793.0

Fahrenheit and Celsius (Centigrade) Temperature Conversion
Figure 5 (Sheet 6)

20-50-00
©Cessna Aircraft Company

Page 14
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

STANDARD DRILL SIZES
DRILL DECIMAL DRILL DECIMAL DRILL DECIMAL DRILL DECIMAL DRILL DECIMAL
80
79
1/64
78
77

0.0135
0.0145
0.0156
0.0160
0.0180

45
44
43
42
3/32

0.0820
0.0860
0.0890
0.0935
0.0937

12
11
10
9
8

0.1890
0.1910
0.1935
0.1960
0.1990

S
T
23/64
U
3/8

0.3480
0.3580
0.3594
0.3680
0.3750

55/64
7/8
57/64
29/32
29/64

0.8594
0.8750
0.8906
0.9062
0.9219

76
75
74
73
72

0.0200
0.0210
0.0225
0.0240
0.0250

41
40
39
38
37

0.0960
0.0980
0.0995
0.1015
0.1040

7
13/64
6
5
4

0.2010
0.2031
0.2040
0.2055
0.2090

V
W
25/64
X
Y

0.3770
0.3860
0.3906
0.3970
0.4040

15/16
61/64
31/32
63/64
1

0.9375
0.9531
0.9687
0.9844
1.0000

71
70
69
68
1/32

0.0260
0.0280
0.0292
0.0310
0.0313

36
7/64
35
34
33

0.1065
0.1093
0.1100
0.1110
0.1130

3
7/32
2
1
A

0.2130
0.2187
0.2210
0.2280
0.2340

13/32
Z
27/64
7/16
29/64

0.4062
0.4130
0.4219
0.4375
0.4531

67
66
65
64
63

0.0320
0.0330
0.0350
0.0360
0.0370

32
31
1/8
30
29

0.1160
0.1200
0.1250
0.1285
0.1360

15/64
B
C
D
E

0.2344
0.2380
0.2420
0.2460
0.2500

15/32
31/64
1/2
33/64
17/32

0.4687
0.4843
0.5000
0.5156
0.5312

62
61
60
59
58

0.0380
0.0390
0.0400
0.0410
0.0420

28
9/64
27
26
25

0.1405
0.1406
0.1440
0.1470
0.1495

1/4
F
G
17/64
H

0.2500
0.2750
0.2610
0.2656
0.2660

35/64
9/16
37/64
19/32
39/64

0.5469
0.5625
0.5781
0.5937
0.6094

57
56
3/64
55
54

0.0430
0.0465
0.0469
0.0520
0.0550

24
23
5/32
22
21

0.1520
0.1540
0.1562
0.1570
0.1590

I
J
K
9/32
L

0.2720
0.2770
0.2811
0.2812
0.2900

5/8
41/64
21/32
43/64
11/16

0.6250
0.6406
0.6562
0.6719
0.6875

53
1/16
52
51
50

0.0595
0.0625
0.0635
0.0670
0.0700

20
19
18
11/64
17

0.1610
0.1660
0.1695
0.1719
0.1730

M
19/64
N
5/16
O

0.2950
0.2968
0.3020
0.3135
0.3160

45/64
23/32
47/64
3/4
49/64

0.7031
0.7187
0.7344
0.7500
0.7656

49
48
5/64
47
46

0.0730
0.0760
0.0781
0.0785
0.0810

16
15
14
13
3/16

0.1770
0.1800
0.1820
0.1850
0.1875

P
21/64
Q
R
11/32

0.3230
0.3281
0.3320
0.3390
0.3437

25/32
51/64
13/16
53/64
27/32

0.7812
0.7969
0.8125
0.8281
0.8437

Drill and Tap Decimal Conversion
Figure 6 (Sheet 1)

20-50-00
© Cessna Aircraft Company

Page 15

April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

MILLIMETER DRILL SIZES
mm DECIMAL mm DECIMAL mm DECIMAL mm DECIMAL mm DECIMAL
.35
.40
.45
.50
.55

0.0138
0.0157
0.0177
0.0197
0.0217

2.10
2.15
2.20
2.25
2.30

0.0827
0.0846
0.0866
0.0886
0.0905

4.60
4.70
4.75
4.80
4.90

0.1811
0.1850
0.1870
0.1890
0.1929

7.50
7.60
7.70
7.75
7.80

0.2953
0.2992
0.3031
0.3051
0.3071

12.50
13.00
13.50
14.00
14.50

.60
.65
.70
.75
.80

0.0236
0.0256
0.0276
0.0295
0.0315

2.35
2.40
2.45
2.50
2.55

0.0925
0.0945
0.0965
0.0984
0.1004

5.00
5.10
5.20
5.25
5.30

0.1968
0.2008
0.2047
0.2067
0.2087

7.90
8.00
8.10
8.20
8.25

0.3110
0.3150
0.3189
0.3228
0.3248

15.00 0.5906
15.50 0.6102
16.00 0.6299
16.50 0.6496
17.00 0.6693

.85

1.05

0.0335
0.0354
0.0374
0.0394
0.0413

2.60
2.65
2.70
2.75
2.80

0.1024
0.1043
0.1063
0.1083
0.1102

5.40
5.50
5.60
5.70
5.75

0.2126
0.2165
0.2205
0.2244
0.2264

8.30
8.40
8.50
8.60
8.70

0.3268
0.3307
0.3346
0.3386
0.3425

17.50
18.00
18.50
19.00
19.50

0.6890
0.7087
0.7283
0.7480
0.7677

1.10
1.15
1.20
1.25
1.30

0.0433
0.0453
0.0472
0.0492
0.0512

2.90
3.00
3.10
3.20
3.25

0.1142
0.1181
0.1220
0.1260
0.1280

5.80
5.90
6.00
6.10
6.20

0.2283
0.2323
0.2362
0.2401
0.2441

8.75
8.80
8.90
9.00
9.10

0.3445
0.3465
0.3504
0.3543
0.3583

20.00
20.50
21.00
21.50
22.00

0.7874
0.8071
0.8268
0.8465
0.8661

1.35
1.40
1.45
1.50
1.55

0.0531
0.0551
0.0571
0.0591
0.0610

3.30
3.40
3.50
3.60
3.70

0.1299
0.1339
0.1378
0.1417
0.1457

6.25
6.30
6.40
6.50
6.60

0.2461
0.2480
0.2520
0.2559
0.2598

9.20
9.25
9.30
9.40
9.50

0.3622
0.3642
0.3661
0.3701
0.3740

22.50
23.00
23.50
24.00
24.50

0.8858
0.9055
0.9252
0.9449
0.9646

1.60
1.65
1.70
1.75
1.80

0.0629
0.0650
0.0669
0.0689
0.0709

3.75
3.80
3.90
4.00
4.10

0.1477
0.1496
0.1535
0.1575
0.1614

6.70
6.75
6.80
6.90
7.00

0.2638
0.2658
0.2677
0.2716
0.2756

9.60
9.70
9.75
9.80
9.90

0.3780
0.3819
0.3839
0.3858
0.3898

25.00

0.9843

1.85

0.0728
0.0748
0.0768
0.0787
0.0807

4.20
4.25
4.30
4.40
4.50

0.1654
0.1674
0.1693
0.1732
0.1771

7.10
7.20
7.25
7.30
7.40

0.2795
0.2835
0.2855
0.2874
0.2913

10.00
10.50
11.00
11.50
12.00

0.3937
0.4134
0.4330
0.4528
0.4724

.90

.95
1.00

1.90

1.95
2.00
2.05

0.4921
0.5118
0.5315
0.5512
0.5709

Drill and Tap Decimal Conversion
Figure 6 (Sheet 2)

20-50-00
© Cessna Aircraft Company

Page 16
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

TAP HOLE SIZES
HOLE ID
TAP
SIZE

MINIMUM

MAXIMUM

0-80
1-64
1-72
2-56
2-64

0.0616
0.0746
0.0746
0.0876
0.0876

0.0619
0.0749
0.0749
0.0879
0.0879

3-48
3-56
4-40
4-48
5-40

0.1011
0.1006
0.1146
0.1141
0.1276

0.1014
0.1009
0.1149
0.1144
0.1279

5-44
6-32
6-40
8-32
8-36

0.1271
0.1411
0.1406
0.1671
0.1666

0.1274
0.1414
0.1409
0.1674
0.1669

10-24
10-32
12-24
12-28
1/4-20

0.1941
0.1931
0.2201
0.2196
0.2551

0.1944
0.1934
0.2204
0.2199
0.2555

1/4-28
5/16-18
5/16-24
3/8-16
3/8-24

0.2536
0.3181
0.3166
0.3811
0.3791

0.2540
0.3185
0.3170
0.3815
0.3795

7/16-14
7/16-20
1/2-13
1/2-20
9/16-12

0.4446
0.4426
0.5076
0.5051
0.5701

0.4450
0.4430
0.5080
0.5055
0.5705

9/16-18
5/8-11
5/8-18
3/4-10
3/4-16

0.5681
0.6331
0.6306
0.7592
0.7562

0.5685
0.6335
0.6310
0.7596
0.7566

7/8-9
7/8-14
1-8
1-14

0.8852
0.8822
1.0112
1.0072

0.8856
0.8826
1.0116
1.0076

Drill and Tap Decimal Conversion
Figure 6 (Sheet 3)

20-50-00
©Cessna Aircraft Company

Page 17

April 1/2002

CHAPTER

aI

CODIIOIN

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

LIST OF EFFECTIVE PAGES
CHAPTER-SECTION-SUBJECT

PAGE

DATE

21 -Table of Contents
21-00-00

Page 1

21-20-00

Page 1

April 1/2002
April 1/2002

21-20-00

April 1/2002

21-20-00

Pages 101 -102
Pages 201 -203

21-21-00

Pages 201-206

Jan 2/2006

21-40-00

Pages 101 -102

April 1/2002

21-40-00

Pages 201-206

Janl1/2007

21 -Title
21 -List of Effective Pages
21 -Record of Temporary Revisions

©Cessna Aircraft Company

21

-

Mar 1/2005

LIST OF EFFECTIVE PAGES

Page 1 of 1
Janl1/2007

RECORD OF TEMPORARY REVISIONS
Temporary Revision
Number

Page Number

Issue Date

By

Date Removed

By

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82

MAINTENANCE MANUAL

CONTENTS
AIR CONDITIONING - GENERAL .........................
Scope....................................
Tools, Equipment and Materials........................
Definition.
FRESH AIR DISTRIBUTION - DESCRIPTION AND OPERATION...........
General...................................
Description .................................
System Operation ..............................
FRESH AIR DISTRIBUTION - TROUBLESHOOTING ................
General...................................
FRESH AIR DISTRIBUTION - MAINTENANCE PRACTICES.............
General...................................
Air Outlet Valve Removal/Installation......................
Cabin Air Control Cable Removal/Installation..................
Distribution Duct Removal/installation .....................
AVIONICS COOLING - MAINTENANCE PRACTICES ................
General ..................................
Firewall Avionics Cooling Fan Removal/installation (Airplanes without Garmin
G 100o) .................................
Primary Flight Display (PFD) Fan Removal/Installation (Airplanes with Garmin
GlOQO) .................................
Multi-Function Display (MFD) Fan Removal/Installation (Airplanes with Garmin
G 1000)..................................
Deck Skin Fan Removal/Installation (Airplanes with Garmin G1000) .......
Remote Avionics Cooling Fan Removal/Installation (Airplanes with Garmin G1 000)
Primary Flight Display (PFD) and Multi-Function Display (MFD) Fan Operational
Check (Airplanes with Garmin G1000)....................
HEATING AND DEFROSTING - TROUBLESHOOTING ...............
General...................................
HEATING AND DEFROSTING - MAINTENANCE PRACTICES............
General...................................
System Operation ..............................
Heat Shroud Removal/installation.......................
Shutoff Valve Removal/Installation.......................
Cabin Heat Control Cable Removal/Installation.................
Defrost Control Cable Removal/Installation...................
Distribution System Components Removal/Installation..............

©Cessna Aircraft Company

21 -00-00
21-00-00
21 -00-00
21-00-00

Page
Page
Page
Page

1
1
1
1

21-20-00
21-20-00
21-20-00
21-20-00

Page
Page
Page
Page

1
1
1
1

21 -20-00 Page 101
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21 -CONTENTS

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
AIR CONDITIONING - GENERAL
1.

Scope
A.

2.

This chapter describes those units and components which furnish a means of heating and ventilating
the cockpit/cabin area.

Tools, Equipment and Materials
NOTE:

Equivalent substitutes may be used for the following items:

NAME

NUMBER

MANUFACTURER

USE

Type II Sealant

PR1488

Courtaulds Aerospace
5426 San Fernando Rd.
Glendale, CA 91209

To secure cabin duct to
various air outlets.

Type IV Sealant

Pro-Seal 700

Courtaulds Aerospace

To seal shutoff valve to
firewall.

Type IV Sealant

GC- 1900

Courtaulds Aerospace

To seal shutoff valve to
firewall.

3.

Definition
A.

This chapter is divided into sections to aid maintenance technicians in locating information. Consulting
the table of contents will further assist in locating a particular subject. A brief description of the sections
follows:
(1) The section on distribution describes that portion of the system used to distribute fresh and
heated air throughout the cockpit/cabin area.
(2) The section on heating describes those components used to generate (but not distribute) heat
for the cockpit/cabin area.
(3) The section on temperature control describes components used to control heat in the cockpit/
cabin area.

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
FRESH AIR DISTRIBUTION - DESCRIPTION AND OPERATION
1.

General
A.

2.

Description
A.

3.

The cockpit/cabin area is ventilated with fresh air by means of external wing root openings, an
adjustable air scoop, and internal ducting.

Fresh air enters the cabin from one of three sources. Two of those sources are located on the leading
edge of the wing (one left and one right) and the other source is located on the right and left sides of
the fuselage, between the firewall and the forward door post.
(1) Fresh air from the leading edge inlets is distributed through a series of ducts to adjustable air
outlet valves (Wemacs). Each wing feeds three Wemacs, with a total of six Wemacs located
throughout the cabin. Wemacs are located at the upper corner of the windshield, between the
instrument panel and forward doorpost, and overhead in the rear passenger area.
(2) Fresh air entering from the right side of the fuselage is controlled by an infinitely positionable
scoop (door). This air is ducted directly into the heated air plenum and is distributed throughout
the cabin.

System Operation
A.
B.

The amount of fresh air entering the cabin can be controlled by any of the six Wemacs. Rotating the
Wemac valve will vary the airflow from fully closed to fully open.
Airflow into the cabin can also be adjusted by the CABIN AIR control cable. Pulling the control fully aft
allows the maximum amount of fresh air to flow through the distribution system. Pushing the control
fully forward closes the scoop (door) and allows no fresh air to flow through the distribution system.
NOTE:

Air temperature in the distribution system can be altered by use of the CABIN HT control.
As the CABIN HT control is gradually pulled out, more and more heated air will blend with
the fresh air from the scoop, and is distributed into the cabin. Either one or both of the
controls may be set at any position from full open to full closed.

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
FRESH AIR DISTRIBUTION - TROUBLESHOOTING
1.

General
A.

A troubleshooting chart has been developed to aid the maintenance technician in system
understanding. Refer to Figure 101.

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April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1114

NO AIRFLOW OR REDUCED
AIRFLOW FROM OUTLETS.

CHECK FOR DISCONNECTED
OR CRUSHED DUCT. IF -

I
OK, CHECK FOR DEFECTIVE
WEMAC VALVE, REPAIR OR
REPLACE WEMAC VALVE.

NOT OK, CONNECT DUCT OR
REPLACE DAMAGED DUCT.

PRECIPITATION ENTERING
CABIN THROUGH AIR VENTS.

REPLACE AIR VENT
ASSEMBLIES.

Fresh Air System Troubleshooting Chart
Figure 101 (Sheet 1)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
FRESH AIR DISTRIBUTION - MAINTENANCE PRACTICES
1.

General
A.

2.

3.

4.

Fresh air is distributed through ducts from two inlet openings, one in each wing leading edge, to air
outlet valves located in the cockpit/cabin area at the wing roots by the upper corners of the windshield,
in the side walls just aft of the instrument panel, and above the passenger seat. Air outlet valve
removal/installation is typical at each location. A door assembly, located on the right side of the
fuselage between the firewall and door post, also allows fresh air to be routed into the heat ducts.
The door is operated by a control on the instrument panel labeled CABIN AIR.

Air Outlet Valve Removal/Installation
A.

Remove Air Outlet Valve (Refer to Figure 201).
(1) Remove retaining ring from air outlet valve.
(2) Remove upholstery panel or headliner. Refer to chapter 25, Interior Upholstery - Maintenance
Practices.
(3) Remove clamp securing ducting hose to air outlet valve adapter.
(4) Remove air outlet valve and adapter.

B.

Install Wing Root Air Outlet Valve (Refer to Figure 201).
(1) Install air outlet valve and valve adapter to ducting. Secure with clamp.
(2) Install upholstery panel or headliner. Refer to Chapter 25, Interior Upholstery - Maintenance
Practices.
(3) Install retaining ring to air outlet valve.

Cabin Air Control Cable Removal/Installation
A.

Remove Cabin Air Control Cable (Refer to Figure 201).
(1) Carefully straighten end of CABIN AIR control cable.
(2) Loosen clamp bolt on control arm and withdraw cable from control arm.
(3) Remove screws securing clamp.
(4) Gain access to the backside of the CABIN AIR control cable.
(5) Loosen nut on backside of control cable.
(6) Carefully withdraw cable from instrument panel.

B.

Install Cabin Air Control Cable (Refer to Figure 201).
(1) Thread end of control cable through hole in instrument panel.
(2) Secure CABIN AIR control cable to backside of instrument panel using existing jamnut.
(3) Thread end of control cable through the clamp bolt.
(4) Clamp control housing.
(5) Test control cable to ensure full range of travel. Travel may be adjusted by positioning control
housing in clamps.
(6) When full range of travel has been established, bend end of control cable around clamp bolt.

Distribution Duct Removal/Installation
A.

The majority of the fresh air distribution system components are riveted to the airframe and do not
require replacement during normal maintenance. Ducts are secured to these components using
clamps. If ducts become damages or worn, they should be replaced.

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

DOOR ASSEMBLY
CLAMP BOLT

HOUSING

CONTROL/

DETAIL

A

0710T1001
A0714T1006

Fresh Air System Installation
Figure 201 (Sheet 1)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1116

PLENUM
CLAMP
DUCT

JR INLET ASSEMBLY
CLAMP

CLAMP
DUCT
AIR OUTLET VALVE

CLAMP

AIR OUTLET VALVE
ESCUTCHEON
DUCT

PLENUM

CLAMP
AlI UU I LE I

VMLVr

B

DETAIL
RIGHT SIDE SHOWN
LEFT SIDE OPPOSITE
A0714T1001

Fresh Air System Installation
Figure 201 (Sheet 2)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
AVIONICS COOLING - MAINTENANCE PRACTICES
1.

2.

General
A.

The maintenance procedures that follow are for the removal and installation of the avionics cooling
fan(s).

B.

Airplanes with the standard avionics system have one cooling fan for the instrument panel installed
on the forward top right side of the firewall. The fan is used to cool the different components in the
radio stack.

C.

Airplanes with the Garmin G1000 avionics system have four avionics fans. Two of the fans are
installed behind the instrument panel to help cool each Control Display Unit (CDU). The third fan
is installed in the deck skin to pull hot air out from the forward side of the instrument panel. The fourth
fan is installed in the tailcone next to the avionics.

Firewall Avionics Cooling Fan Removal/Installation (Airplanes without Garmin G1000)
A.
Remove the Firewall Avionics Cooling Fan (Refer to Figure 201).
(1) Make sure that the airplane MASTER and AVIONICS switches are in the off position.
(2) Remove the screws that attach the fan to the firewall.
(3) Disconnect the electrical connector (PC901) from the wire bundle.
(4) Cut the tie straps and disconnect the flexible ducts from the fan.
(5) Remove the fan from the airplane.
B.

Install the Firewall Avionics Cooling Fan (Refer to Figure 201).
(1) Connect the flexible ducts to the fan.
(2) Install the tie straps on the ducts.
(3) Connect the electrical connector (PC901) to the wire bundle.
(4) Install the fan to the firewall with screws.
(5) Do a test of the fan.
(a) Put the MASTER switch in the BATT position.
(b) Put the MASTER switch in the ON position and listen for the fan operation.
(6) Put the MASTER switch and the AVIONICS switch in the off position.

3.

Primary Flight Display (PFD) Fan Removal/Installation (Airplanes with Garmin G1000)
A.
Remove the PFD Fan (Refer to Figure 202).
(1) Make sure that the MASTER switch and the AVIONICS switch are in the off position.
(2) Remove the PFD. Refer to Chapter 34, Control Display Unit - Maintenance Practices.
(3) Record the fan airflow direction.
(4) Remove the screws and nuts that attach the fan to the fan bracket.
(5) Disconnect the electrical connector (PI316) from the wire bundle.
(6) Remove the fan from the airplane.
B. Install the PFD Fan (Refer to Figure 202).
(1) Connect the electrical connector (PI316) to the wire bundle.
(2) Install the screws and nuts that attach the fan to the fan bracket.
(3) Do a test of the fan.
(a) Put the MASTER switch in the BATT position.
(b) Put the AVIONICS switch in the ON position and listen for the fan operation.
(c) Make sure that the direction of the airflow is toward the PFD.
(4) Put the AVIONICS switch and the MASTER switch in the off position.
(5) Install the PFD. Refer to Chapter 34, Control Display Unit - Maintenance Practices.

4.

Multi-Function Display (MFD) Fan Removal/Installation (Airplanes with Garmin G1000)
A. Remove the MFD Fan (Refer to Figure 202).
(1) Make sure that the MASTER switch and the AVIONICS switch are in the off position.
(2) Remove the MFD. Refer to Chapter 34, Control Display Unit - Maintenance Practices.

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

A

EXIBLE DUCT
O AVIONICS
TACK)

ELECTRICAL
CONNECTOR
(PC901)

FIREWALL

0

0

AVIONICS
FAN

DETAIL A

071T1T001
A051T1026

Firewall Avionics Fan Installation (Airplanes without Garmin G 1000)
Figure 201 (Sheet 1)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

PRIMARY Fl I(1-IT

D

0710T1001
A0718T1063

Avionics Cooling Installation (Garmin G1000)
Figure 202 (Sheet 1)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
(3) Remove the turn coordinator. Refer to Chapter 34, Attitude and Direction - Maintenance
Practices.
(4) Record the fan airflow direction.
(5) Remove the screws and nuts that attach the fan to the fan bracket.
(6) Disconnect the electrical connector (PI315) from the wire bundle.
(7) Remove the fan from the airplane.
B.

5.

6.

Install the MFD Fan (Refer to Figure 202).
(1) Connect the electrical connector (PI315) to the wire bundle.
(2) Make sure that the airflow direction is towards the MFD.
(3) Install the screws and nuts that attach the fan to the fan bracket.
(4) Do a test of the fan.
(a) Put the MASTER switch in the BATT position.
(b) Put the AVIONICS switch to the ON position and listen for the fan operation.
(5) Put the AVIONICS switch and the MASTER switch in the off position.
(6) Install the turn coordinator. Refer to Chapter 34, Attitude and Direction - Maintenance Practices.
(7) Install the MFD. Refer to Chapter 34, Control Display Unit - Maintenance Practices.

Deck Skin Fan Removal/nstallation (Airplanes with Garmin G1000)
A.

Remove the Deck Skin Fan (Refer to Figure 202).
(1) Make sure that the MASTER switch and the AVIONICS switch are in the off position.
(2) Remove the PFD. Refer to Chapter 34, Control Display Unit - Maintenance Practices.
(3) Record the airflow direction.
(4) Remove the screws and nuts that attach the fan to the deck skin.
(5) Disconnect the electrical connector (PI314) from the wire bundle.
(6) Remove the fan from the airplane.

B.

Install the Deck Skin Fan (Refer to Figure 202).
(1) Connect the electrical connector (PI314) to the wire bundle.
(2) Make sure that the direction of the airflow is away from the deck skin and toward the windshield.
(3) Install the screws and nuts that attach the fan to the deck skin.
(4) Do a test of the fan.
(a) Put the MASTER switch in the BATT position.
(b) Put the AVIONICS switch to the ON position and listen for the fan operation.
(5) Put the AVIONICS switch and the MASTER switch in the off position.
(6) Install the PFD. Refer to Chapter 34, Control Display Unit - Maintenance Practices.

Remote Avionics Cooling Fan Removal/nstallation (Airplanes with Garmin G1000)
A.

Remove the Remote Avionics Cooling Fan (Refer to Figure 203).
(1) Make sure that the MASTER switch and the AVIONICS switch are in the off position.
(2) Remove the upholstery. Refer to Chapter 25, Interior Upholstery - Maintenance Practices.
(3) Remove the screws that attach the fan to the structure.
(4) If necessary, remove the caps from the unused ports.
(5) Disconnect the electrical connector (PT901) from the wire bundle.
(6) Remove the clamps from the flexible ducts of the fan.
(7) Disconnect the flexible ducts from the fan.
(8) Remove the fan from the airplane.

B.

Install the Remote Avionics Cooling Fan (Refer to Figure 203).
(1) Connect the flexible ducts to the fan.
(2) Put the clamps on the flexible ducts.
(3) Connect the electrical connector (PT901) to the wire bundle.
(4) Install the screws that attach the fan to the structure.
(5) If necessary, install the caps on the unused ports.
(6) Do a test of the fan.
(a) Put the MASTER switch in the BATT position.
(b) Put the AVIONICS switch to the ON position and listen for the fan operation.
(7) Put the AVIONICS switch and the MASTER switch in the off position.

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

INTEGRATED
A

II

CAPS

REMOTE AVIONICS
COOLING FAN

DETAIL A

0710T1001
A0718T1081

Remote Avionics Cooling Fan Installation (Garmin G1000)
Figure 203 (Sheet 1)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
(8) Install the upholstery. Refer to Chapter 25, Interior Upholstery - Maintenance Practices.
7.

Primary Flight Display (PFD) and Multi-Function Display (MFD) Fan Operational Check (Airplanes
with Garmin G1000)
A.

PFD
(1)
(2)
(3)
(4)

and MFD Fan Operational Check (Refer to Figure 202).
Remove the PFD and the MFD. Refer to Control Display Unit - Maintenance Practices.
Put the MASTER switch and AVIONICS switch in the ON position.
Listen and look for the correct operation of both fans.
Install the PFD and the MFD. Refer to Control Display Unit - Maintenance Practices.

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
HEATING AND DEFROSTING - TROUBLESHOOTING
1.

General
A.

A troubleshooting chart has been developed to aid the maintenance technician in system
understanding. Refer to Figure 101.

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Page 101
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1118

NO AIRFLOW OR REDUCED
AIRFLOW FROM OUTLETS.

CHECK FOR STICKING

I OR BINDING VALVE. IF - I

I
OK, CHECK FOR BINDING
CONTROL. IF-

NOT OK, REPAIR VALVE.

OK, CHECK FOR DISCONNECTED
OR CRUSHED DUCT. CONNECT
OR REPLACE DAMAGED DUCT.

NOT OK, LUBRICATE
CONTROL OR REPLACE.

I

Heating and Defrosting System Troubleshooting Chart
Figure 101 (Sheet 1)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T1 82

MAINTENANCE MANUAL
HEATING AND DEFROSTING

-

MAINTENANCE PRACTICES

1.General
A. The heating and defrosting system is comprised of the heat exchange section of the exhaust mufflers,
a shutoff valve mounted on the firewall, defrosting valve outlet located under the deck just aft of the
windshield, push-pull controls on the instrument panel, outlets, and flexible ducting connecting the
system.
2.

System Operation
A.
Ram air enters the engine compartment through cowling inlets located aft of the propeller. A portion of
this air is directed toward an exit point in the rear engine baffle. This air is directed, via ducting, to the
heat exchange section around the left exhaust muffler. As air passes into the heat shroud and around
the exhaust muffler, it picks up heat from the engine exhaust. The heated air is then directed to the
right exhaust heat shroud. This heated air exits the right heat shroud and isdirected, via ducting, to a
firewall shutoff valve. The shutoff valve is cable controlled from the cockpit, and controls the amount
of heated air entering the cockpit area distribution plenum. From the plenum, various ducts distribute
the heated air to floorboard and defroster outlets.
NOTE:

The cockpit area distribution plenum is also plumbed to receive outside fresh air from the
right external air scoop (door). This arrangement allows a combination of fresh air and
heated air to be mixed and distributed throughout the system.

3.

Heat Shroud Removal/installation
A.
Remove Heat Shroud (Refer to Figure 201 and Figure 202).
(1) Remove engine cowling. Refer to Chapter 71, Cowling - Maintenance Practices.
(2) Remove clamps securing flexible ducts to left heat shroud.
(3) Remove sheet metal screws securing heat shroud to itself.
(4) Carefully remove shroud from around left muffler.
(5) Remove clamps securing flexible ducts to right heat shroud.
(6) Remove sheet metal screws securing heat shroud to itself.
(7) Carefully remove heat shroud from around right muffler.
(8) Muffler must be carefully examined and inspected for leaks or cracks. Refer to Chapter 5,
Inspection Time Limits for normal inspection time frame. Refer to Chapter 78, Exhaust System
- Maintenance Practices for inspection criteria of the muffler.
B. Install Heat Shroud (Refer to Figure 201 and Figure 202).
(1) Carefully wrap heat shroud around right muffler.
(2) Secure heat shroud to itself using sheet metal screws.
(3) Carefully wrap heat shroud around left muffler.
(4) Secure heat shroud to itself using sheet metal screws.
(5) Secure flexible ducts to heat shrouds using clamps.
(6) Install engine cowling. Refer to Chapter 71, Cowling - Maintenance Practices.

4.

Shutoff Valve Removal/installation
A. The shutoff valve is riveted to the firewall and is not removed from the airplane during normal
maintenance. If valve is replaced, firewall must be sealed using Type IV sealant upon reattachment of
shutoff valve to firewall. For a list of Type IV sealants refer to Chapter 21, Air Conditioning - General.

5.

Cabin Heat Control Cable Removal/installation
A. Remove Control Cable (Refer to Figure 201 and Figure 202).
(1) Remove engine cowling. Refer to Chapter 71, Cowling - Maintenance Practices.
(2) Carefully straighten end of cabin heat control cable.
(3) Loosen clamp bolt on control arm and withdraw cable from control arm.
(4) Remove screws securing clamps to firewall.
(5) From inside the cabin, gain access to the backside of the CABIN HT control cable.

©Cessna Aircraft Company

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CESSNA AIRCRAFT COMPANY

MODEL 182/T1182

MAINTENANCE MANUAL

CLAMP BOLT
SPRING

CONTRC
ARM

SEAT
VALVE
DOOR

CABIN HEAT
CONTROL
CABLE

VALVE
BODY

DETAIL B

IINTAKE
ICT

MUFFLER AND
HEAT SHROUD

DETAIL A

0710T100 1
A071 4T1 009
B0714R1030

AIRPLANES 18280001 AND ON
Cabin Heating and Defrosting Installation
Figure 201 (Sheet 1)

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CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182

MAINTENANCE MANUAL

833409

DEFROST NOZZLE

PIN

w

CONTR

NUT

DETAIL

C

AlIRPLAN ES 18280001 THRU 18280944

-FROST NOZZLE
LAMP
,VALVE
ASSEMBLY

LEVER
ASSEMBLY

DETAIL

C

AIRPLANES 18280945 AND ON
C0714R1032
C0714R1031

Cabin Heating and Defrosting Installation
Figure 201 (Sheet 2)
0 Cessna Aircraft Company

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CESSNA AIRCRAFT COMPANY

MODEL 182/T1182
MAINTENANCE MANUAL

E

ITLET
CT

INLET DUCT

DETAIL

A

AIRPLANES Ti 8208001 AND ON
0710T1001
A0724T 1024

Cabin Heating and Defrosting Installation
Figure 202 (Sheet 1)

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S

CESSNA AIRCRAFT COMPANY

MODEL 1821182

MAINTENANCE MANUAL

B34o8

CLAMP BOLT

VALVE SEAT
COI
AR1

CABIN HEAT
CONTROL
CABLE

VALVE DOOR
VALVE BODY
CLAMP

iDutn I
DETAIL

B

-FROST NOZZLE

~LAMP
.VALVE
ASSEMBLY

LEVER
ASSEMBLY

DETAIL

C
B0714R1030
C0714F11031

Cabin Heating and Defrosting Installation
Figure 202 (Sheet 2)

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CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182

MAINTENANCE MANUAL
(6) Loosen nut on backside of control cable.
(7) Carefully withdraw cable from instrument panel and firewall.
B.

6.

7.

Install Control Cable (Refer to Figure 201 and Figure 202).
(1) Thread end of control cable through hole in instrument panel and through hole in firewall.
(2) Secure CABIN HT control cable to backside of instrument panel using existing jamnut.
(3) Thread end of control cable through the clamp bolt and tighten clamp bolt.
(4) Clamp control to firewall.
(5) Test control cable to ensure full range of travel. Travel may be adjusted by positioning control
housing in clamp on firewall.
(6) When full range of travel has been established, bend end of control cable around clamp bolt.
(7) Install engine cowling. Refer to Chapter 71, Cowling - Maintenance Practices.

Defrost Control Cable Removall/Installation
A.

Remove Defrost Control Cable (Refer to Figure 201 and Figure 202).
(1) Carefully straighten end of defrost control cable.
(2) Loosen clamp bolt on control arm and withdraw cable from control arm.
(3) Remove screws securing clamps.
(4) From inside the cabin, gain access to the backside of the DEFROST control cable.
(5) Loosen nut on backside of control cable.
(6) Carefully withdraw cable from instrument panel.

B.

Install Defrost Control Cable (Refer to Figure 201 and Figure 202).
(1) Thread end of control cable through hole in instrument panel.
(2) Secure DEFROST control cable to backside of instrument panel using existing jamnut.
(3) Thread end of control cable through the clamp bolt.
(4) Clamp control housing.
(5) Test control cable to ensure full range of travel. Travel may be adjusted by positioning control
housing in clamps.
(6) When full range of travel has been established, bend end of control cable around clamp bolt.

Distribution System Components Removal/Installation
A.

The majority of heated air distribution system components are riveted to the airframe and do not
require replacement during normal maintenance. Ducts are secured to these components using
clamps. If ducts become damaged or worn, they should be replaced with new ducts.

B.

Ducts are typically attached to various outlets using tie straps.

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CHAPTER

AUTO FLIGHT

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

LIST OF EFFECTIVE PAGES
CHAPTER-SECTION-SUBJECT

PAGE

DATE

22-00-00

Page 1

Janl1/2007

22-10-00

Pages 201 -212

Jul 1/2007

22-11-00

Pages 201-207

Janl1/2007

22-Title
22-List of Effective Pages
22-Record of Temporary Revisions
22-Table of Contents

22
©Cessna Aircraft Company

-

LIST OF EFFECTIVE PAGES

Page 1 of 1
Jul 1/2007

RECORD OF TEMPORARY REVISIONS
Temporary Revision
Number

Page Number

Issue Date

By

Date Removed

By

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82
MAINTENANCE MANUAL

CONTENTS
AUTO FLIGHT - GENERAL ............................
Scope and Definition.............................
Tools, Equipment and Materials........................
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...........................

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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.......................

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MAINTENANCE MANUAL
AUTO FLIGHT

-

GENERAL

1.Scope and Definition

I

A.

The GFC-700 flight control system is a two-axis (pitch and roll) autopilot system. The GFC-700 flight
control system has the GIA-63W Integrated Avionics Unit, Primary Flight Display (PFD), Multi-Function
Display (MFD), roll axis servo, pitch axis servo, pitch trim servo, and servo mounts.

B.

I

C.

The KAP-1 40 flight control system can be one of two autopilot systems: single-axis (roll) or two-axis
(pitch and roll).
(1) The KAP-140 single-axis configuration has the flight computer, configuration module, roll axis
servo actuator, rate gyro, directional gyro and servo mount.
(2) The KAP-1 40 two-axis configuration has the flight computer, configuration module, roll axis servo
actuator, pitch axis servo actuator, pitch trim servo actuator, rate gyro, directional gyro and servo
mounts.
This chapter gives the removal and installation procedures for the KAP-1 40 (single and two-axis) and
GFC-700 autopilot flight computers and servo actuators.

2.

Tools, Equipment and Materials
NOTE:

Equivalent alternatives can be used for the items that follow.

NAME

NUMBER

MANUFACTURER

Test Stand

071-06028-0000

Adapter Tool

071-06021-0003

Adapter Pin

071-06021-0002

Honeywell International, To hold the servo mount
Inc.
in position while the
1 Technology Center
servo clutch torque
Olathe, KS 66061
setting is adjusted.
Honeywell International, To adjust the servo
Inc.
clutch torque setting.
Honeywell International, To adjust the servo
Inc.
clutch torque setting.

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MAINTENANCE MANUAL
AUTOPILOT

-

MAINTENANCE PRACTICES

1.General
A. A single-axis autopilot with heading hold is installed as standard equipment on the airplane. Heading
hold is used on the directional gyro input and can have VOR or Localizer input as required.
B.

A dual-axis autopilot is available as an option. The dual-axis system gives both vertical speed and
altitude hold selection.

KC- 140 (Single-Axis) Autopilot Flight Computer Removal/installation

2.

A.

Remove the Autopilot (Single-Axis) Flight Computer (Refer to Figure 201).
(1) Make sure the MASTER and AVIONICS switches are in the off position.
(2) Loosen the screw on the face of the autopilot flight computer.
(3) Remove the autopilot flight computer from the mounting tray.

B.

Install the Autopilot Flight Computer (Refer to Figure 201).
(1) Put the autopilot flight computer in position in the mounting tray.
(2) Tighten the screw on the face of the autopilot flight computer.
(3) Put the MASTER and AVIONICS switches in the ON position.
(4) Do a test of the autopilot. Refer to Introduction, the List of Manufacturers Technical Publications
for the manufacturer's installation manual.

KC-140 (Dual-Axis) Autopilot Flight Computer Remova~l/nstallation

3.

Autopilot (Dual-Axis) Flight Computer Removal/Installation is typical for airplanes with and
without the Garmin G1000 installation.

NOTE:

4.

A.

Remove the Autopilot (Dual-Axis) Flight Computer (Refer to Figure 201).
(1) Make sure the MASTER and AVIONICS switches are in the off position.
(2) Loosen the screw on the face of the autopilot flight computer.
(3) Remove the autopilot flight computer from the mounting tray.

B.

Install the Autopilot Flight Computer (Refer to Figure 201).
(1) Put the autopilot flight computer in position in the mounting tray.
(2) Tighten the screw on the face of the autopilot flight computer.
(3) Put the MASTER and AVIONICS switches in the ON position.
(4) Do a test of the autopilot. Refer to Introduction, the List of Manufacturers Technical Publications
for the manufacturer's installation manual.

Roll Servo Removal/installation
The autopilot roll servo removal/installation is typical for single-axis and dual-axis autopilot
installations.

NOTE:
A.

I

Remove the Roll Servo (Refer to Figure 202).
(1) Make sure the MASTER and AVIONICS switches are in the off position.
(2) Remove the access panel (620GB). Refer to Chapter 6, Access/inspection Plates - Description

~

B.

~~and
Operation.

(3) Disconnect the electrical connector (PR301) from the roll servo.
(4) Release the control cable tension and loosen the roll servo control cable at the turnbuckle.
(5) Remove the bolts and washers that attach the roll servo to the bracket assembly.
(6) Remove the roll servo from the airplane.
(7) Do an inspection of the roll servo. Refer to Roll Servo Inspection.
Install the Roll Servo (Refer to Figure 202).
(1) Put the roll servo in position on the bracket assembly and attach with the bolts and washers.
(2) Connect the electrical connector (PR301) to the roll servo.
(3) Install the roll servo control cable on the roll servo.
(4) Make sure the aileron and bell crank are in the neutral position.

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DETAIL

A

AUTOPILOT CONTROLLER

DETAIL

0710T1001
AO718T1002
B0718T1X01

B
KAP-140 Autopilot Installation
Figure 201 (Sheet 1)

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B3488

DETAIL A

DETAIL B

B

AUTOPILOT
CONTROLLER

AIRPLANES WITH GARMIN G1000

9T1 0ss
ALJ71
B071 8T1 063

KAP-140 Autopilot Installation
Figure 201 (Sheet 2)

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t

C

CONTROL
CABLE

ROLL SERVO
CONTROL CABLE
GUARD
(NOTE)

CONTROL
viewv

P%-P%

AILERON
BELL CRANK

GUARD LEG
(TYPICAL)

TU RNBUCKLE

ROLL SERVO

NOTE:

THE CONTROL CABLES MUST
NOT TOUCH THE CONTROL
CABLE GUARD LEGS

DETAIL

A

0710T1001
A076OT 1013
AA076OT10019

Autopilot Servo Installation
Figure 202 (Sheet 1)

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MAINTENANCE MANUAL

21 123
I

PITCH SERVO

ELEVATOR
BELL CRANK
TU RN BUCKLE

B*NS~
DETAIL

B

PITCH SERVO
CONTROL CABLE GUARD (NOTE)

VIEw

B-B

B076OT 1003
BB076OT 1010

Autopilot Servo Installation
Figure 202 (Sheet 2)

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81 124

TRIM TAB
ACTUATOR

0

TU RN BUCKLE

C

DETAIL

C

PITCH TRIM SERVO
CON.TROL

PITCH TRIM SERVO
CONTROL CABLE GUARD (NOTE)
CONTROL CABLE
GUARD LEG
.(TYPICAL)

CABLE

VIEW G-LU
C076OT 1004
CCO76OT 1011

Autopilot Servo Installation
Figure 202 (Sheet 3)

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(5) Wind the control cable around the servo drum approximately 1.25 turns in each direction from
the swaged ball (drum ball detent inboard).
(6) Make sure the flanges of the control cable guard do not touch the control cable.
(7) Make sure the flanges of the control cable guard are on each side of the notches around the
outer edge of the mount.
(8) Use the turnbuckle to adjust the roll servo control cable tension to 15 pounds, +3 or -3 pounds.
(9) Install the access panel (520GB). Refer to Chapter 6, Access/Inspection Plates - Description
and Operation.
(10) Put the MASTER and AVIONICS switches in the ON position.
(11) Do a test of the autopilot to make sure it operates correctly. Refer to Introduction, the List of
Manufacturers Technical Publications for the manufacturer's installation manual.
5.

6.

Pitch Servo Removal/Installation
A.

Remove Pitch Servo (Refer to Figure 202).
(1) Make sure the MASTER and AVIONICS switches are in the off position.
(2) Remove the access panels (31OAR, 340AL and 340AR). Refer to Chapter 6, Access/Inspection
Plates - Description and Operation.
(3) Disconnect the electrical connector (PT300) from the pitch servo.
(4) Release the control cable tension and loosen the pitch servo control cable at the turnbuckle.
(5) Remove the bolts and washers that attach the pitch servo to the bracket assembly.
(6) Remove the pitch servo from the airplane.
(7) Do an inspection of the pitch servo. Refer to Pitch Servo Inspection.

B.

Install the Pitch Servo (Refer to Figure 202).
(1) Put the pitch servo in position on the bracket assembly and attach with the bolts and washers.
(2) Connect the electrical connector (PT300) to the pitch servo.
(3) Install the pitch servo control cable on the pitch servo actuator.
(4) Make sure the aileron and bellcrank are in the neutral position.
(5) Wind the control cable around the servo drum approximately 1.25 turns in each direction from
the swaged ball (drum ball detent inboard).
(6) Make sure the flanges of the control cable guard do not touch the control cable.
(7) Make sure the flanges of the control cable guard are on each side of the notches around the
outer edge of the mount.
(8) Use the turnbuckle to adjust the pitch servo cable tension to 15 pounds, +3 or -3 pounds.
(9) Install the access panels (310AR, 340AL and 340AR). Refer to Chapter 6, Access/Inspection
Plates - Description and Operation.
(10) Put the MASTER and AVIONICS switches in the ON position.
(11) Do a test of the autopilot to make sure it operates correctly. Refer to Introduction, the List of
Manufacturers Technical Publications for the manufacturer's installation manual.

Pitch Trim Servo Removal/Installation
A.

Remove the Pitch Trim Servo (Refer to Figure 202).
(1) Make sure the MASTER and AVIONICS switches are in the off position.
(2) Remove the access panels (31 OAR, 340AL and 340AR). Refer to Chapter 6, Access/Inspection
Plates - Description and Operation.
(3) Disconnect the electrical connector (PT301) from the pitch trim servo.
(4) Release the control cable tension and loosen the pitch trim servo control cable at the turnbuckle.
(5) Remove the bolts and washers that attach the pitch trim servo to the bracket assembly.
(6) Remove the pitch trim servo from the airplane.
(7) Do an inspection of the pitch trim servo. Refer to Pitch Trim Servo Inspection.

B.

Install the Pitch Trim Servo (Refer to Figure 202).
(1) Put the pitch trim servo in position on the bracket assembly and attach with the bolts and
washers.
(2) Connect the electrical connector (PT301) to the pitch trim servo.

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(3) Do the pitch trim servo control cable rigging.
(a) The servo trim chain must be on the aft sprocket of the actuator before the manual trim
system rigging can be done.
(b) You must do the manual trim system rigging before the servo trim system rigging. Refer to
Chapter 27, Elevator Trim Control - Maintenance Practices, Trim Tab Control Adjustment!
Test.
(c) Put the elevator in the neutral position.
(d) Use an inclinometer to put the trim tab to 5 degrees up in relation to the elevator.
NOTE:

The chain sprocket on the actuator will be at approximately the halfway point in
its rotation from the mechanical stops.

(e) Move the servo trim chain on the aft sprocket of the actuator so that equal lengths of the
chain are on either side of the sprocket.
(f) Wind the control cable around the pitch trim servo drum approximately 1.25 turns each
direction from the swaged ball.
(g) Make sure the flanges of the control cable guard do not touch the control cable.
(h) Make sure the flanges of the control cable guard are on either side of the notches around
the outer edge of the mount.
(i) Use the turnbuckle to adjust the pitch trim servo control cable tension to 15 pounds, +3 or
-3 pounds.
(4) Install the access panels (310AR, 340AL and 340AR). Refer to Chapter 6, Access/inspection
Plates - Description and Operation.
(5) Put the MASTER and AVIONICS switches in the ON position.
(6) Do a test of the autopilot to make sure it operates correctly. Refer to Introduction, the List of
Manufacturers Technical Publications, for the manufacturer's installation manual.
7.

Roll Servo Inspection
A.

Do Inspection the Roll Servo (Refer to Figure 202).
(1) Remove the servo cover.

CAUTION: Make sure the maintenance personnel and the table are electrically
grounded.
Do disassembly or assembly of the servo at an
electrostatic-safe area.

(2)

(3)
(4)
(5)

(a) Put an electrical ground on the maintenance personnel and table.
(b) Remove the two screws that attach the cover to the unit.
(c) Carefully remove the cover over the wiring harness.
(d) Put the servo on the table so the inner parts of the unit will not be damaged.
Do inspection of the solenoid and clutch.
(a) Make sure the solenoid shaft moves freely in and out of the solenoid body.
(b) Make sure there is no dirt, contamination or corrosion around the solenoid shaft.
(c) Make sure the release spring freely pulls the shaft out of the solenoid and against the stop
fitting.
(d) Make sure the pinion gear turns and does not touch the clutch gears.
Do a general inspection of the roll servo.
(a) Examine the electrical wiring for indication of wear or damage of the insulation.
(b) Examine the servo for any loose hardware or other defects.
Install the cover.
(a) Carefully put the cover in position.
(b) Install the screws with Loctite 222 or Loctite 242.
Remove the servo capstan assembly and do a check of the slip-clutch torque setting (Refer to
Servo Capstan Clutch Adjustment).

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8.

Pitch Servo Inspection
A. Do Inspection of the Pitch Servo (Refer to Figure 202).
(1) Remove the servo cover.

CAUTION: Make sure the maintenance personnel and the table are electrically
grounded. Do disassembly or assembly of the servo at an
electrostatic-safe area.
(a) Put an electrical ground on the maintenance personnel and table.
(b) Remove the two screws that attach the cover to the unit.
(c) Carefully remove the cover from the wiring harness.

CAUTION: Do not move any wires, tie wraps or the spring clamp. The
position of each is set by the manufacturer and is necessary
for correct operation.
(d) Put the servo on the table so the inner parts of the unit will not be damaged.
(2) Do inspection of the solenoid and clutch.
(a) Make sure the solenoid shaft moves freely in and out of the solenoid body.
(b) Make sure there is no dirt, contamination or corrosion around the solenoid shaft.
(c) Make sure the release spring freely pulls the shaft out of the solenoid and against the stop
fitting.
(d) Make sure the pinion gear turns and does not touch the clutch gears.
(3) Do a general inspection.
(a) Examine the electrical wiring for indication of wear or damage of the insulation.
(b) Examine the servo for any loose hardware or other defects.
(4) Do an inspection of the pitch servo motor.
(a) Put the servo in position so the baseplate is on the bottom side of the unit.
(b) Hold the top section of the motor and carefully turn the motor shaft.
(c) The motor shaft must turn freely from side to side a small quantity.
(5) Install the cover.
(a) Carefully put the cover in position.
(b) Install the screws with Loctite 222 or Loctite 242.
(6) Remove the servo capstan assembly and do a check of the slip-clutch torque setting (Refer to
Servo Capstan Clutch Adjustment).
9.

Pitch Trim Servo Inspection
A.
Do Inspection of the Pitch Trim Servo (Refer to Figure 202).
(1) Remove the servo cover.

CAUTION: Make sure the maintenance personnel and the table are electrically

grounded. Do disassembly or assembly of the servo at an
electrostatic-safe area.

(a) Put an electrical ground on the maintenance personnel and table.
(b) Remove the two screws that attach the cover to the unit.
(c) Carefully remove the cover over the wiring harness.
(d) Put the servo on the table so the inner parts of the unit will not be damaged.
(2) Do inspection of the solenoid and clutch.
(a) Make sure the solenoid shaft moves freely in and out of the solenoid body.
(b) Make sure there is no dirt, contamination or corrosion around the solenoid shaft.
(c) Make sure the release spring freely pulls the shaft out of the solenoid and against the stop
fitting.
(d) Make sure the pinion gear turns and does not touch the clutch gears.

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Do a general inspection.
(a) Examine the electrical wiring for indication of wear or damage of the insulation.
(b) Examine the servo for any loose hardware or other defects.
(4) Install the cover.
(a) Carefully put the cover in position.
(b) Install the screws with Loctite 222 or Loctite 242.
(5) Remove the servo capstan assembly and check the slip-clutch torque setting (Refer to Servo
Capstan Clutch Adjustment).
(3)

10.

Pitch Trim Rigging Inspection
A.

Do a check of the pitch trim rigging.
(1) Attach an inclinometer to the trim tab.
(2) Put the trim tab in the 0 degree position.
(3) Manually operate the trim tab to the up and down limits.
(4) Record the limits of travel.
(5) Put an observer at the right-hand access opening of the tailcone.
(6) Put the electrical trim to the full nose-up position until the observer sees the clutch slip.
(7) Turn the manual trim wheel nose-up (test load condition) 1/4 turn more while the clutch slips.
(8) Make sure the swaged ball on the control cable assembly does not turn aft of the tangent point.
(9) Release the trim wheel and disengage the autopilot.
(10) Manually operate the trim to the full nose-up position.
(11) Do a check of the trim tab position with an inclinometer.
(12) Trim tab position that is greater than the limits of travel values recorded is an indication that the
stop blocks slipped.
(a) Do the trim system rigging again.
(b) Make sure the stop block bolts torque is correct.
(c) Repeat the check of the pitch trim rigging.
(13) If necessary, make adjustments to the swaged ball position.
(a) Put the control cable assembly chain in the applicable position on the gear teeth of the
actuator sprocket.
NOTE:

One chain link adjustment is related to approximately 17 degrees of travel on
the capstan.

(b) Apply the applicable tension to the control cable and repeat the check of the pitch trim
rigging.
(14) Do the procedure again for the full nose-down trim condition.
11.

Servo Capstan Clutch Adjustment
A. Do a check of the clutch torque setting.
(1) Remove the servo capstan.
(2) Remove the control cable guard from the servo capstan.
(3) Attach the servo capstan on the capstan test stand. Refer to Autopilot - General for a list of tools
and equipment.
(4) Place the adapter tool over the servo capstan.
(5) Insert the adapter pin from the straight up position to attach the adapter tool.
(6) Insert the torque wrench.
(7) Apply 28 VDC (1 amp maximum) electrical power to the test stand.
(8) Do a check of the torque reading with the test stand motor in the clockwise operation.
NOTE:

The check of the torque reading will be done three times.

(a) Put the capstan switch in the clockwise position.
(b) Record the torque reading of the torque wrench.
(c) Put the switch in the off position.

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(9) Do a check of the torque reading with the test stand motor in the counterclockwise operation.
NOTE:

The check of the torque reading will be done three times.

(a) Put the capstan switch in the counterclockwise position.
(b) Record the torque reading of the torque wrench.
(c) Put the switch in the off position.
(10) Average the six torque readings.
NOTE:
(11)

The torque reading to be used is the average of the six torque readings.

Refer to Table 201 for the correct torque reading of the servo capstan.

Table 201. KAP-140 Autopilot Servo Clutch Torque Setting

Roll Servo Capstan

182S

182T/T182T

55, +5 or -5 inch-pounds (6.2,
+0.56 or -0.56 N-in)

35, +3 or -3 inch-pounds (3.95,
+0.34 or -0.34 N-in)

Pitch Servo Capstan

26, +2 or -2 inch-pounds (2.9,
38, +3 or -3 inch-pounds (4.3,
+0.23 or -0.23 N-in)
+0.34 or -0.34 N-i)
Pitch Trim Servo Capstan
45, +5 or -5 inch-pounds (5.1,
45, +5 or -5 inch-pounds (5.1,
+0.56 or -0.56 N-in)
+0.56 or -0.56 N-in)
(a) If the torque indication is below the value given in Table 201, rotate the clutch adjust nut
clockwise and do the check of the torque readings again.
(b) If the torque indication is above the value given in Table 201, rotate the clutch adjust nut
counterclockwise and do the check of the torque readings again.
(12) Record the slip clutch torque indication, airplane type, axis, and date on the decal attached to
the servo mount body.
(13) Install the control cable guard on the servo capstan.
(14) Install the servo capstan.
12.

Set the Autopilot Roll Null
A.

Set
(1)
(2)
(3)
(4)

the Autopilot Roll Null (If the Autopilot is Installed).
Make sure the autopilot flight computer completes the pre-flight test.
Disconnect the roll servo connector from the airplane harness.
Apply a ground to pin K of the harness connector.
Connect a digital multimeter across the harness connector at pins D and L to monitor the servo
drive voltage.
(5) Push the autopilot AP button on the autopilot flight computer to engage it.
(a) Make sure the default ROL mode is set.
NOTE:

For example, the HDG, NAV or APR modes are not engaged.

(b)

Use a DMVM to measure the DC voltage across pins D and L of the roll servo harness
connector.
(c) Adjust the pot until a value of 0 volts, +0.020 or -0.020 volts are measured.
1
If the end of the pot movement is reached before the servo drive is nulled, disengage
the autopilot, turn the pot fully to the opposite stop and then engage the autopilot.
(d) The roll null adjustment range emulates a four turn pot that lets the method of the pot
adjustment range to be set.
NOTE:

This adjustment lets offsets be in the roll axes.
coordinator.

This includes the turn

(e) Continue to turn the pot to null the voltage.

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(6) Connect the airplane roll servo harness connector to the servo connector.

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AUTOPILOT

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MAINTENANCE PRACTICES

1.General
A. The GFC-700 is a dual-axis autopilot with heading, altitude, and vertical speed hold.
2.

GFC-700 Autopilot Flight Computer Remova~l/nstallation
A. Remove the Autopilot Flight Computer.
(1) Refer to Chapter 23, Communications - Maintenance Practices
B. Install the Autopilot Flight Computer.
(1) Refer to Chapter 23, Communications - Maintenance Practices

3.

Roll Servo Actuator Removal/installation
A.
Remove the Roll Servo (Refer to Figure 201).
(1) Make sure the MASTER and AVIONICS switches are in the OFF position.
(2) Remove the 620GB access panel. Refer to Chapter 6, Access/inspection Plates - Description
and Operation.
(3) Disconnect the electrical connector from the roll servo actuator.
(4) Remove the bolts and washers that attach the roll servo actuator to the torque mount.
(5) Remove the roll servo actuator from the airplane.
B. Install the Roll Servo (Refer to Figure 201).
(1) Put the roll servo actuator in position on the torque mount and attach with bolts and washers.
(2) Connect the electrical connector to the roll servo actuator.
(3) Do a check to make sure the servo operates correctly. Refer to the Garmin G1 000 Maintenance
Manual, Revision G or later.
(4) Install the 620GB access panel. Refer to Chapter 6, Access/Inspection Plates - Description and
Operation.

4.

Roll Servo And Cable Removal/installation
A. Remove the Roll Servo and Cable (Refer to Figure 201).
(1) Make sure the MASTER and AVIONICS switches are in the OFF position.
(2) Remove the 620GB access panel to get access to the roll servo and the cable. Refer to Chapter
6, Access Plates and Panels Identification - Description and Operation.
(3) Disconnect the electrical connector.
(4) Release the servo cable tension at the turnbuckle.
(5) Remove the cable guard.
(6) Record how the cable is installed on the capstan.
(7) Disconnect the cable from the turnbuckle.
(8) Remove the cable from the capstan.
(9) Remove the bolts that attach the servo assembly to the bracket.
(10) Remove the servo from the airplane.
B. Install the Roll Servo and Cable (Refer to Figure 201).
(1) Put the servo and the cable in position at the servo mount and install the bolts.
(2) Put the servo cable in position on the capstan.
(3) Wind the cable approximately 1.25 turns each direction around the capstan.
(4) Install the cable guard.
(5) Connect the cable to the turnbuckle.
(6) Use the turnbuckle to adjust the roll servo cable tension to 15 pounds, +3 or -3 pounds.
(7) Connect the electrical connector.
(8) Do acheck to make sure the servo operates correctly. Refer to the Garmin G1000Maintenance
Manual, Revision G or later.
(9) Install the 620GB access panel. Refer to Chapter 6, Access Plates and Panels Identification Description and Operation.

©Cessna Aircraft Company

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MAINTENANCE MANUAL

C

ROLL SERVO
CONTROL CABLE
GUARD

CONTROL
CABLE

(NOTE)

AILERON
*BELL CRANK

CABLE
G

viEw A-A
TURN BUCKLE

NOTI
0710T1001
A076OT 10 15
AA076OT101 5

CABLE GUARDS LEGS.
Autopilot Servo Installation
Figure 201 (Sheet 1)

22-11-00
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B7361

NJK

;~~~~~~~~~~~~~~~~~~

-

-A--

i
PIT
SEF

IROL
CONTROL
MOUNT

B4~

DETAIL B

GUARD LEG
(TYPICAL)
VIEW B-B

B076OT1016
BB076OT1016

Autopilot Servo Installation
Figure 201 (Sheet 2)

22-1 1-00
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MAINTENANCE MANUAL

873'

TRIM TAB
ACTUATOR

h
PITCH
TRIM
I

PITCH TRIM SERVO
CONTROL CABLE
GUARD
(NOTE)

C

-

t

MOUNT

CONTROL CABLE
GUARD LEG
(TYPICAL)

C076OT1 014
0CC76OT1 014

VIEW C-C
Autopilot Servo Installation
Figure 201 (Sheet 3)

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5.

Pitch Servo Motor Removalllnstallation
A. Remove Pitch Servo (Refer to Figure 201).
(1) Make sure the MASTER and AVIONICS switches are in the OFF position.
(2) Remove the 31 OAR, 340AL and 340AR access panels. Refer to Chapter 6, Access/Inspection
Plates - Description and Operation.
(3) Disconnect the electrical connector from the pitch servo.
(4) Remove the bolts and washers that attach the pitch servo to the torque mount.
(5) Remove the pitch servo actuator from the airplane.
B. Install the Pitch Servo (Refer to Figure 201).
(1) Put the pitch servo in position on the torque mount and attach with the bolts.
(2) Connect the electrical connector to the pitch servo.
(3) Do a check to make sure the servo operates correctly. Refer to the Garmin G1 000 Maintenance
Manual, Revision G or later.
(4) Install the 31 OAR, 340AL and 340AR access panels. Refer to Chapter 6, Access/Inspection
Plates - Description and Operation.

6.

Pitch Servo And Cable Remova~installation
A. Remove the Pitch Servo and Cable (Refer to Figure 201).
(1) Make sure the MASTER and AVIONICS switches are in the OFF position.
(2) Remove the 31 OAR, 340AL and 340AR access panels to get access to the pitch servo and the
cable. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation.
(3) Disconnect the electrical connector .
(4) Release the servo cable tension at the turnbuckle.
(5) Remove the cable guard.
(6) Record how the cable is installed on the capstan.
(7) Disconnect the cable from the turnbuckle.
(8) Remove the cable from the capstan.
(9) Remove the bolts that attach the servo assembly to the bracket.
(10) Remove the servo from the airpiane.
B. Install the Pitch Servo and Cable (Refer to Figure 201).
(1) Put the servo and the cable in position at the servo mount and install the bolts.
(2) Put the servo cable in position on the capstan.
(3) Wind the cable approximately 1.25 turns each direction around the capstan.
(4) Install the cable guard.
(5) Connect the cable to the turnbuckle.
(6) Use the turnbuckle to adjust the roll servo cable tension to 15 pounds, +3 or -3 pounds.
(7) Connect the electrical connector.
(8) Do a check to make sure the servo operates correctly. Refer to the Garmin G1 000 Maintenance
Manual, Revision G or later.
(9) Install the 31 OAR, 340AL and 340AR access panel. Refer to Chapter 6, Access Plates and
Panels Identification - Description and Operation.

7.

Pitch Trim Servo Actuator RemovaVlnstallation
A. Remove the Pitch Trim Servo (Refer to Figure 201).
(1) Make sure the MASTER and AVIONICS switches are in the OFF position.
(2) Remove the 31 OAR, 340AL and 340AR access panels. Refer to Chapter 6, Access/Inspection
Plates - Description and Operation.
(3) Disconnect the electrical connector from the pitch trim servo.
(4) Remove the bolts and washers that attach the pitch trim servo to the torque mount.
(5) Remove the pitch trim servo from the airplane.
B. Install the Pitch Trim Servo (Refer to Figure 201).
(1) Put the pitch trim servo in position on the torque mount and attach with the bolts and washers.
(2) Connect the electrical connector to the pitch trim servo.

0

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(3) Do a check to make sure the servo operates correctly. Refer to the Garmin G1 000 Maintenance
Manual, Revision G or later.
(4) Install the 31 OAR, 340AL and 340AR access panels. Refer to Chapter 6, Access/inspection
Plates - Description and Operation.
8.

Pitch Trim Servo and Cable Removallinstallation
A. Remove the Pitch Trim Servo (Refer to Figure 201).
(1) Make sure the MASTER and AVIONICS switches are in the OFF position.
(2) Remove the 31 OAR, 340AL and 340AR access panels. Refer to Chapter 6, Access/inspection
Plates - Description and Operation.
(3) Disconnect the electrical connector from the pitch trim servo.
(4) Release the control cable tension and loosen the pitch trim servo control cable at the turnbuckle.
(5) Remove the bolts and washers that attach the pitch trim servo to the bracket.
(6) Remove the pitch trim servo from the airplane.
B.

Install the Pitch Trim Servo (Refer to Figure 201).
(1) Put the pitch trim servo in position on the bracket and attach with the bolts and washers.
(2) Connect the electrical connector to the pitch trim servo.
(3) Do the pitch trim servo control cable rigging.
(a) The servo trim chain must be on the aft sprocket of the actuator before the manual trim
system rigging can be done.
(b) You must do the manual trim system rigging before the servo trim system rigging. Refer to
Chapter 27, Elevator Trim Control - Maintenance Practices, Trim Tab Control Adjustment]
Test.
(c) Put the elevator in the neutral position.
(d) Use an inclinometer to put the trim tab to 5 degrees up in relation to the elevator.
NOTE:

The chain sprocket on the actuator will be at approximately the halfway point in
its rotation from the mechanical stops.

(e) Move the servo trim chain on the aft sprocket of the actuator so that equal lengths of the
chain are on either side of the sprocket.
(f) Wind the control cable around the pitch trim servo drum approximately 1.25 turns each
direction from the swaged ball.
(g) Make sure the flanges of the control cable guard do not touch the control cable.
(h) Make sure the flanges of the control cable guard are on either side of the notches around
the outer edge of the mount.
(i) Use the turnbuckle to adjust the pitch trim servo control cable tension to 15 pounds, +3 or
-3 pounds.
(4) Do a check to make sure the servo operates correctly. Refer to the Garmin G1 000 Maintenance
Manual, Revision G or later.
(5) Install the 31 OAR, 340AL and 340AR access panels. Refer to Chapter 6, Access/Inspection
Plates - Description and Operation.
9.

Pitch Trim Rigging Inspection
A. Do a check of the pitch trim rigging.
(1) Attach an inclinometer to the trim tab.
(2) Put the trim tab in the 0 degree position.
(3) Manually operate the trim tab to the up and down limits.
(4) Record the limits of travel.
(5) Put an observer at the right-hand access opening of the tailcone.
(6) Put the electrical trim to the full nose-up position until the observer sees the clutch slip.
(7) Turn the manual trim wheel nose-up (test load condition) 1/4 turn more while the clutch slips.
(8) Make sure the swaged ball on the control cable assembly does not turn aft of the tangent point.
(9) Release the trim wheel and disengage the autopilot.
(10) Manually operate the trim to the full nose-up position.
(11) Do a check of the trim tab position with an inclinometer.

22-1 100
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(12) Trim tab position that is greater than the limits of travel values recorded is an indication that the
stop blocks slipped.
(a) Do the trim system rigging again.
(b) Make sure the stop block bolts torque is correct.
(c) Do the check of the pitch trim rigging again.
(13) If necessary, make adjustments to the swaged ball position.
(a) Put the control cable assembly chain in the applicable position on the gear teeth of the
actuator sprocket.
NOTE:

One chain link adjustment is related to approximately 17 degrees of travel on
the capstan.

(b) Apply the applicable tension to the control cable and do the check of the pitch trim rigging
again.
(14) Do the procedure again for the full nose-down trim condition.
10.

Servo Capstan Clutch Adjustment
A.
Adjust the servo capstan clutch in accordance with the manufactures installation manual. Refer
to Introduction, the List of Manufacturers Technical Publications for the manufacturer's installation
manual.

IPitch Servo Clutch Plate

55, +7 or -7 inch-pounds (6.2, +0.79 or -0.79 N-in)
35, +5 or -5 inch-pounds (3.95, +0.56 or -0.56 N-in)

IPitch Trim Servo Clutch Plate

45, +6 or -6 inch-pounds (5.1, +0.68 or -0.68 N-in)

IRoll Servo Clutch Plate

22-1100
©Cessna Aircraft Company

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CHAPTER

COMMUNICATIONS

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82

MAINTENANCE MANUAL

LIST OF EFFECTIVE PAGES
CHAPTER-SECTION-SUBJECT

PAGE

DATE

23-00-00

Page 1

April 1/2002

23-10-00

Pages 201-209

Janl1/2007

23-50-00

Pages 201 -204

Mar 1/2004

23-60-00

Pages 201 -202

April 1/2002

23-Title
23-List of Effective Pages
23-Record of Temporary Revisions
23-Table of Contents

©Cessna Aircraft Company

23

-

LIST OF EFFECTIVE PAGES

Page 1 of 1
Janl1/2007

RECORD OF TEMPORARY REVISIONS
Temporary Revision
Number

Page Number

Issue Date

By

Date Removed

By

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82

MAINTENANCE MANUAL

CONTENTS
COMMUNICATIONS - GENERAL .........................
Scope....................................
Definition ..................................
COMMUNICATIONS - MAINTENANCE PRACTICES ................
General...................................
Troubleshooting ...............................
NAV/COM Radio Removal/Installation.....................
GIA 63 Integrated Avionics Unit (Garmin G1000) Removal/installation ......
VHF Antenna Removal/installation.......................
NAV Antenna Removal/Installation.......................
Microphone Switch Removal/Installation....................
Microphone Switch Button Cleaning......................
AUDIO PANEL - MAINTENANCE PRACTICES ...................
General...................................
Audio Panel Removal/Installation .......................
Pilot/Front Intercom Jacks Removal/Installation.................
Rear Passenger Intercom Jacks Removal/installation..............
STATIC WICKS - MAINTENANCE PRACTICES...................
General...................................
Tools and Equipment.............................
Static Wicks Removal/Installation .......................
Bonding Straps Removal/Installation......................

© Cessna Aircraft Company

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
COMMUNICATIONS - GENERAL
1.

2.

Scope
A.

This chapter describes and provides maintenance instructions for equipment which furnishes a
means of communicating from one part of the airplane to another, and between the airplane and
other airplanes or ground stations

B.

Additional information on communications equipment can be found in the Wiring Diagram Manual
supplied with the airplane.

C.

Technical publications available from the manufacturer of the various components and systems which
are not covered in this manual must be utilized as required for maintenance of those components and
systems.

Definition
A.

Information contained in this chapter provides the basic procedures which can be accomplished at
the flight line level; such as, removal and installation of components and system operation.

B.

This chapter is divided into sections to aid maintenance personnel in locating information. A brief
description of each section is as follows:
(1) The speech communication section describes radio equipment used for reception and
transmission of voice communication.
(2) The audio integrating system section describes that portion of the system which controls
the output of the communications and navigation receivers into the pilot and passengers
headphones and speakers, and the output of the pilot's microphone into the communications
transmitters.
(3) The static discharging section describes the static discharge wicks used to dissipate static
electricity.

23-00-00
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MAINTENANCE MANUAL
COMMUNICATIONS

-

MAINTENANCE PRACTICES

1.General
A. This section gives maintenance practices for the NAV/COM component removal and installation.
B. The dual navigation/communications (NAV/GOM/) radio is in the instrument panel.
C.

For airplanes with the Garmin G1000, the center of the Garmin G1000 is the GIA 63 Integrated
Avionics Unit (IAUJ), which is in the tailcone. The GIA 63 operates as a primary communications
center that connects all of the Line Replaceable Units (LRUs) with the Primary Function Display (PFD)
and Multi-Function Display (MFD). The GIA 63 has the GPS receiver, VHF NAV/COM receivers, and
system integration microprocessors. The GIA 63W has the Wide Area Augmentation System (WAAS)
installed. The GIA 63 transmits directly to the PFD and MFD by a High-Speed Data Bus (HSDB)
Ethernet connection. Software and configurations are sent from the displays through the GIA 63 to
the LRU's in the system.

2.

Troubleshooting
A. For troubleshooting procedures of the GIA 63 Integrated Avionics Units in airplanes with Garmin
G1000, refer to the Garmin G1000 Line Maintenance Manual.

3.

NAVICOM Radio Removal/installation

CAUTION: Do not interchange the KX-155A and the KX-165A NAV/COM radios. The

wiring is not the same for the two different radios. If these radios are
interchanged and used with the same wiring, damage can occur to the
KX-1 55A and/or the KX-1 65A NAV/COM radios.

NOTE:
A.

B.

4.

The airplane has dual NAV/COM units installed. One NAV/COM unit contains the glideslope
function. The removal and installation are typical.
Remove the NAV/COM Unit (Refer to Figure 201).
(1) Put the MASTER switch in the OFF position.
(2) Put the NAV/COM switch in the OFF position.
(3) Disengage the NAV/COM 1 and/or NAV/COM 2 circuit breaker.
(4) Turn the recessed mounting screw on the face of the NAV/COM unit counterclockwise until the
locking paw releases from the mounting tray.
(5) Move the NAV/COM unit aft out of the mounting tray to disconnect the electrical connectors
(PI1004, P11000, and P11 002).
(6) Remove the NAV/COM unit from the mounting tray.
Install the NAV/COM Unit (Refer to Figure 201).
(1) Put the NAV/COM unit in the mounting tray and move the unit forward.
(2) Connect the electrical connectors (PI1004, P11000, and P11002).
(3) Turn the recessed mounting screw on the face of the NAV/COM unit clockwise until the NAV/
COM unit is attached to the mounting tray.
(4) Engage the NAV/COM 1 and/or NAV/COM 2 circuit breaker.
(5) Put the MASTER switch in the ON position.
(6) Put the NAV/COM switch in the ON position and make sure that the electronic display comes on.
(7) Put the MASTER and NAV/COM switches in the OFF position.

GIA 63 Integrated Avionics Unit (Garmin G1000) Remova~linstallation
NOTE:
A.

The airplane has dual integrated avionics units installed. The removal and installation are typical.
Remove the Integrated Avionics Unit (Refer to Figure 202).
(1) Put the MASTER switch in the OFF position.
(2) Disengage the NAV/COM 1 and/or NAV/COM 2 circuit breaker.

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B
A

CinTc

A-a it--

O

*oOn.
000000

00

- -7 I01
DIETAIL

LIZZ
2.I1-N
0

0

0

0

0

A

.NAV/COM WITH GLIDESLOPE

.NAV/COM

DETAIL

B

0710T1001
A0718T 1002
B0718BT1O01

NAV/COM Installation
Figure 201 (Sheet 1)

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I..-

VIEW A-A
LOOKING FORWARD AT ES 140
AIRPLANES THAT HAVE
THE GARMIN G1000
071OT1 001
A07 14TIO04

Tailcone Avionics Installation
Figure 202 (Sheet 1)
Q Cessna Aircraft Company

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(3) Remove the tailcone access/inspection plate (31 OAR) to get access to the integrated avionics
units. Refer to Chapter 6, Access/inspection Plates - Description and Operation.
(4) Push on the screw and turn it 90 degrees counterclockwise to release the lever.
(5) Move the lever up to disengage the locking stud with the dogleg slot in the mounting rack.
(6) Remove the unit from the mounting rack.
B.

Install the Integrated Avionics Unit (Refer to Figure 202).

CAUTION: Make sure that the unit goes into position without resistance. Damage
to the connectors, unit, or mounting rack will occur if the unit is pushed
into position with force.
NOTE:

The unit must be in position in the mounting rack to let the locking stud engage the channel.

(1) Carefully put the unit in position in the mounting rack.
(2) Push the lever down toward the bottom of the unit to engage the locking stud with the dogleg
slot in the mounting rack.
(3) Push on the screw and turn it 90 degrees clockwise to attach the lever.
(4) Install the tailcone access/inspection plate (31 OAR). Refer to Chapter 6, Access/Inspection
Plates - Description and Operation.
(5) Engage the NAV/COM 1 and/or NAV/COM 2 circuit breaker.
(6) Put the MASTER switch in the ON position.
(7) Do a check for correct operation. Refer to the Garmin G1lOQO Line Maintenance Manual.
(8) Put the MASTER and NAV/COM switches in the OFF position.
5.

VHF Antenna Removal/installation
NOTE:

The removal and installation procedures are typical for all VHF antennas.

NOTE:

The left VHF antenna is also the GDL-69A antenna and a GPS antenna.

A.

Remove the VHF Antenna (Refer to Figure 203).
(1) Put the MASTER switch in the OFF position.
(2) Remove the four screws that attach the VHF antenna to the upper surface of the fuselage.
(3) Pull the antenna away from the fuselage to disconnect the coax connector from the antenna.
NOTE:

Coax connector reference designators for airplanes without the Garmin G1000 are
PC1 001 for VHF1 and PC1 002 for VHF2.

NOTE:

Coax connector reference designators for airplanes with the Garmin G1000 are
PF1 002 for VHF1 and PC1 007 for VHF2.

(4) Attach the coax cable to the airplane structure so it will not fall into the headliner area.
B.

Install the VHF Antenna (Refer to Figure 203).
(1) Connect the coaxial connector to the antenna.
NOTE:

Coax connector reference designators for airplanes without the Garmin G1000 are
PC1 001 for VHF1 and PC1 002 for VHF2.

NOTE:

Coax connector reference designators for airplanes with the Garmin G1000 are
PF1 002 for VHF1 and PC1 007 for VHF2.

(2) Attach the antenna to the upper surface of the fuselage with the four screws.
6.

NAV Antenna Removal/installation
A.

Remove the NAV Antenna (Refer to Figure 204).
(1) Put the MASTER switch in the OFF position.

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MAINTENANCE MANUAL

t

NTENNA CAN BE
IFEERENT THAN
LUSTRATION.
SCREW~

VHF
(NOI
LAGE SKIN
NUTPLAN

I

COAXIj
(PC1 00
PC1 001

DETAIL

A

AIRPLANES WITH VHF ANTENNA

071OT1 001
A0518T 1025

VHF Communication Antenna Installation
Figure 203 (Sheet 1)
Q Cessna Aircraft Company

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MAINTENANCE MANUAL

B2496

VHF

SCREW

WASHER

C

FUSELAGE
SKIN
NUT[

VIBRATION
DAMPENER
COAXIAL
CON NEC'
GDL-69A

-

LEF]

COMM 1 - RIGHT ANTENNA
COMM 2 - LEFT ANTENNA

DETAIL

A

COAXIAL
CONNECTOR

AIRPLANES WITH
GARMIN G1000
VHF Communication Antenna Installation
Figure 203 (Sheet 2)

A0518T1 107

23-1 0-00
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MAINTENANCE MANUAL

I

B,
CABLE
,ASSEMBLY
T-PHASING

DETAIL

A

PANEL
(340BR)

DETAIL

B

0710T1001
A0718T1061
B0718T 1062

NAV Antenna Installation
Figure 204 (Sheet 1)
Q Cessna Aircraft Company

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MAINTENANCE MANUAL
(2) Remove the screws that attach the NAV antenna to the tail.
(3) Carefully remove the fillet seal from the junction of the NAV antenna and the skin of the airplane.
(4) Pull the antenna away from the fuselage to disconnect the coax connector from the antenna.
B.

7.

Microphone Switch Remova~llnstallation
A.

B.

8.

Install the NAV Antenna (Refer to Figure 204).
(1) Connect the coaxial connector to the antenna.
(2) Attach the antenna to the tail with the screws.
(3) Clean and fillet seal the interface area of the antenna base and fuselage with Type VI sealant.
Refer to Chapter 20, Fuel, Weather and High Temperature Sealing for a list of Type VI sealants.

Remove the Microphone Switch (Refer to Figure 205).
(1) Remove the nut that attaches the microphone switch (Si) to the escutcheon.
(2) Remove the screw that attaches the escutcheon to the control wheel.
(3) Lift up the escutcheon to get access to the microphone switch and disconnect the microphone
switch from the control wheel connection.
Install the Microphone Switch (Refer to Figure 205).
(1) Connect the microphone switch (Si1) to the connection in the control wheel.
(2) Attach the microphone switch to the escutcheon with the nut.
(3) Set the escutcheon in position and install the screw in the escutcheon.

Microphone Switch Button Cleaning
A. Clean the Switch Button (Refer to Figure 205).

CAUTION: Make sure that you clean the switch. Oil and dirt can collect on the
internal electrical contacts of the switch and cause the button to operate
incorrectly.
(1) Apply a sufficient quantity of electrical contact cleaning spray around the full edge of the button
so it will soak down into the switch.
NOTE:

The electrical cleaner will help to remove oil and dirt from the internal electrical
contacts of the switch. The recommended contact cleaner is Electro Contact Cleaner
03116 or equivalent, which can be supplied by LPS Laboratories, Inc. The phone
number is 1-800-241-8334.

(2) Press the button many times to make sure the cleaner gets into the internal electrical contacts
of the switch.
(3) Complete an operational check of the switch.
NOTE:

The transmit light on the comn radio will come on when the power is turned on.

(4) If the button does not operate after the first application of the electric cleaner, apply more cleaner.
(5) If the button continues to operate incorrectly, replace the microphone switch. Refer to
Microphone Switch Removal/installation.

23-1 0-00
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MAINTENANCE MANUAL

R

A
UUN I HUL WHEEL

A

DETAIL

5qflRFW

KNOB

NUT

TRIM
SWITCH
(S3 AND S4)
'T

NUT

DETAIL

B
S.,..

ESCUTCHEON

-

. %Sj
S.II

0710T1001
A07608R1007
8071 5T 1004

Microphone Switch
Figure 205 (Sheet 1)

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MAINTENANCE MANUAL
AUDIO PANEL - MAINTENANCE PRACTICES
1.

2.

General
A.

The audio panel is in the center of the instrument panel. It has audio function, intercom function, and
marker beacon indicators in a single unit.

B.

Maintenance practices for the audio panel have procedures for the removal/installation of the audio
panel and the intercom jacks.

C.

For removal/installation of the overhead speaker, refer to Chapter 25, Interior Upholstery Maintenance Practices.

D.

For removal/installation of the marker beacon antenna, refer to Chapter 34, Marker Beacon Maintenance Practices.

Audio Panel Removal/Installation
NOTE:

3.

4.

Audio panel removal and installation is typical for all avionics packages.

A.

Remove the Audio Panel (Refer to Figure 201).
(1) Make sure the AVIONICS and MASTER switches are in the off position.
(2) Turn the recessed screw on the face of the audio panel counterclockwise until the locking paw
releases from the mounting tray.
(3) Carefully pull the audio panel out of the mounting tray.

B.

Install the Audio Panel (Refer to Figure 201).
(1) Put the audio panel in position and move it forward into the mounting tray.
(2) Turn the recessed screw on the face of the audio panel clockwise until the audio panel is attached
to the mounting tray.

Pilot/Front Intercom Jacks Removal/Installation
A.

Remove the Pilot/Front Passenger Intercom Jacks (Refer to Figure 201).
(1) Make sure the AVIONICS and MASTER switches are in the off position.
(2) To get access to the jacks, remove the interior sidewall panel between the instrument panel and
the forward doorpost. Refer to Chapter 25, Interior Upholstery - Maintenance Practices.
(3) Remove the jamnut that attaches the jack to the interior panel.
(4) Put a label on the applicable wires of the microphone jack (small plug) or the headphone jack
(large plug).
(5) Cut the wires near the soldered joint of the applicable jack.

B.

Install the Pilot/Front Passenger Intercom Jacks (Refer to Figure 201).
(1) If applicable, remove unwanted solder from the jack.
(2) Solder the applicable wires to the jack. Refer to Model 182 Wiring Diagram Manual, Chapter
20, Soldering - Maintenance Practices.
(3) Attach the jack to the sidewall panel with the jamnut.
(4) Install the sidewall panel. Refer to the Chapter 25, Interior Upholstery - Maintenance Practices.

Rear Passenger Intercom Jacks Removal/Installation
A.

Remove the Rear Passenger Intercom Jacks (Refer to Figure 201).
(1) Make sure the AVIONICS and MASTER switches are in the off position.
(2) Remove the rear seat. Refer to Chapter 25, Rear Seats - Maintenance Practices.
(3) Remove the rear sidewall panel. Refer to Chapter 25, Interior Upholstery - Maintenance
Practices.
(4) Put a label on the applicable wires of the microphone jack (small plug) or the headphone jack
(large plug).
(5) Cut the wires near the soldered joint of the applicable jack.
(6) Remove the jamnut that attaches the jack to the interior panel.

23-50-00
© Cessna Aircraft Company

Page 201
Mar 1/2004

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

B

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Audio Panel Installation
Figure 201 (Sheet 1)

23-50-00
© Cessna Aircraft Company

Page 202
Mar 1/2004

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B3475

D

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AUDIO PANEL
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Audio Panel Installation
Figure 201 (Sheet 2)

23-50-00
© Cessna Aircraft Company

Page 203
Mar 1/2004

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
B.

Install the Rear Passenger Intercom Jacks (Refer to Figure 201).
(1) If applicable, remove unwanted solder from the jack.
(2) Solder the applicable wires to the jack. Refer to Model 182 Wiring Diagram Manual, Chapter
20, Soldering - Maintenance Practices.
(3) Attach the jack to the sidewall panel with the jamnut.
(4) Install the rear sidewall panel. Refer to Chapter 25, Interior Upholstery - Maintenance Practices.
(5) Install the rear seat. Refer to Chapter 25, Rear Seats - Maintenance Practices.

23-50-00
© Cessna Aircraft Company

Page 204
Mar 1/2004

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
STATIC WICKS - MAINTENANCE PRACTICES
1.

2.

General
A.

Maintenance of the static (discharger) wicks consists of removal/replacement of the wick assembly
and ensuring that bonding straps are properly connected between control surfaces and primary
structure.

B.

Static wicks are mounted on the trailing edges of the ailerons, rudder and the elevators. Bonding
straps are secured to flight control surfaces and electrically connect those surfaces to the primary
structure.

Tools and Equipment
A.

3.

4.

For a list of applicable tools and equipment, refer to Communications - General.

Static Wicks Removal/Installation
A.

Remove Static Wick (Refer to Figure 201).
(1) Carefully drill out mounting rivets which attach static wick to structure. Ensure holes are not
drilled oversize.
(2) Remove static wick from the airplane skin.

B.

Install Static Wick (Refer to Figure 201).
(1) Clean surface of airplane skin where static wick will attach to skin. Remove all traces of
contaminants (including paint/primer) using scotchbrite and P-D-680 solvent.
(2) Secure static wick to airplane skin using rivets.
(3) Repaint base of new wick (if required).

Bonding Straps Removal/Installation
A.

B.
C.

Bonding straps are provided to ensure that electrical potential between primary and secondary
structure remains nearly equal. If bonding straps are removed, they should be reinstalled using
hardware called out in the Model 182 Illustrated Parts Catalog.
The maximum allowable resistance (in ohms) for bonding straps is 0.0025 ohms.
Primary and secondary structure should be cleaned using scotchbrite pad and P-D- 680 solvent
before installing bonding hardware. Aluminum surfaces should be chemically protected (alodine or
equivalent) before attaching bonding hardware to surface.

23-60-00
© Cessna Aircraft Company

Page 201
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

A
A

STATIC WICK

DETAIL A
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0710T1001
A0518T1024
B0518T2002
C0518T2002
D0518T2002

Static Discharger Installation
Figure 201 (Sheet 1)

23-60-00
© Cessna Aircraft Company

Page 202
April 1/2002

CHAPTER

ELECTRICAL POWER

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

LIST OF EFFECTIVE PAGES
CHAPTER-SECTION-SUBJECT

PAGE

DATE

24-00-00

Pages 1-2

Jul 3/2006

24-20-00

Pages 101-105

Jul 3/2006

24-20-00

Pages 201-202

Aug 4/2003

24-30-00

Pages 101-107

April 1/2002

24-30-00

Pages 201-206

Aug 4/2003

24-30-10

Pages 201-205

Jan 2/2006

24-60-00

Pages 101-104

Jan 2/2006

24-60-00

Pages 201-204

Jul 3/2006

24-60-01

Pages 201-206

Jul 3/2006

24-61-00

Pages 201-203

Mar 1/2005

24-61-01

Pages 201-206

Jul 3/2006

24-70-00

Pages 1-4

Jul 3/2006

24-Title
24-List of Effective Pages
24-Record of Temporary Revisions
24-Table of Contents

24 - LIST OF EFFECTIVE PAGES
© Cessna Aircraft Company

Page 1of 1
Jul 3/2006

RECORD OF TEMPORARY REVISIONS
Temporary Revision
Number

Page Number

Issue Date

By

Date Removed

By

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

CONTENTS
ELECTRICAL POWER - GENERAL ..............................................

Scope......................................................................
Tools, Equipment, and Materials..............................................

24-00-00 Page 1
24-00-00 Page 1
24-00-00 Page 1

ALTERNATOR SYSTEM - TROUBLESHOOTING...................................
General ....................................................................

24-20-00 Page 101
24-20-00 Page 101

ALTERNATOR - MAINTENANCE PRACTICES .....................................
General ....................................................................
Alternator Removal/Installation ...............................................

24-20-00 Page 201
24-20-00 Page 201
24-20-00 Page 201

BATTERY - TROUBLESHOOTING ...............................................

24-30-00 Page 101
24-30-00 Page 101

General ....................................................................

24-30-00
24-30-00
24-30-00
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24-30-00
24-30-00
24-30-00

Page
Page
Page
Page
Page
Page
Page

201
201
201
201
203
203
205

STANDBY BATTERY - MAINTENANCE PRACTICES Airplanes with Garmin G1000 ...
General ....................................................................
Standby Battery Removal/Installation .........................................
Standby Battery Printed Circuit Board Removal/Installation .....................
Standby Battery Charging....................................................
Standby Battery Storage.....................................................
Standby Battery Capacity Test ...............................................
12-VOLT CABIN POWER SYSTEM - TROUBLESHOOTING.........................
General ...................................................................
Cabin Power Interface ......................................................
Power Converter............................................................

24-30-10
24-30-10
24-30-10
24-30-10
24-30-10
24-30-10
24-30-10

Page
Page
Page
Page
Page
Page
Page

201
201
201
201
204
204
205

24-60-00
24-60-00
24-60-00
24-60-00

Page
Page
Page
Page

101
101
101
101

POWER JUNCTION BOX - MAINTENANCE PRACTICES...........................
General ...................................................................
Power Junction Box Removal/Installation......................................
Component Removal/Installation .............................................
Power Junction Box Troubleshooting .........................................

24-60-00
24-60-00
24-60-00
24-60-00
24-60-00

Page
Page
Page
Page
Page

201
201
201
201
201

ALTERNATOR CONTROL UNIT - MAINTENANCE PRACTICES.....................
General ....................................................................
Alternator Control Unit Removal/Installation ..................................
Over-voltage Protection Circuit Test...........................................
Alternator Control Unit Troubleshooting .......................................

24-60-01
24-60-01
24-60-01
24-60-01
24-60-01

Page
Page
Page
Page
Page

201
201
201
201
206

CIRCUIT BREAKER - MAINTENANCE PRACTICES ...............................
General ....................................................................
Circuit Breaker Removal/Installation ..........................................

24-61-00 Page 201
24-61-00 Page 201
24-61-00 Page 201

ESSENTIAL AND CROSSFEED BUS DIODES - MAINTENANCE PRACTICES .......
General ...................................................................
Essential and Crossfeed Bus Diode Removal/Installation .......................
Essential and Crossfeed Bus Diode Inspection ................................
Essential and Crossfeed Bus Diode Multimeter Test ............................

24-61-01
24-61-01
24-61-01
24-61-01
24-61-01

BATTERY - MAINTENANCE PRACTICES ........................................

General ....................................................................
Battery Removal/Installation .........
......... ...............................
Battery Cleaning ............................................................
New Battery Activation ......................................................
Battery Charging............................................................
Battery Test ................................................................

ELECTRICAL LOAD ANALYSIS - DESCRIPTION AND OPERATION .................
General ....................................................................

201
201
201
201
206

24-70-00 Page 1
24-70-00 Page 1

CONTENTS
© Cessna Aircraft Company

Page
Page
Page
Page
Page

Page 1 of 1
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
ELECTRICAL POWER - GENERAL
1.

2.

Scope
A.

This chapter gives the electrical units and components which control and supply electrical power for
the airplane systems. This includes the alternator, batteries, and relays.

B.

Electrical energy for the airplanes is supplied by a 28-volt, direct current, single primary bus, negative
ground electrical system. A single 24-volt main battery supplies power to the starting system and gives
a reserve source of power if an alternator failure were to occur. Airplanes that have the Garmin G1000
system also have a standby battery. The standby battery is controlled and monitored by the standby
battery controller and supplies power to the G1000 essential bus if there is a failure of the main battery
and the alternator. A power junction box, also referred to as a Master Control Unit (MCU), is attached
to the forward left side of the firewall and includes electrical relays, an alternator control unit (ACU),
an ammeter sensor, an external power receptacle, fuses and/or circuit breakers, in a single box. An
engine-driven alternator is the normal source of power during flight and maintains a battery charge
controlled by the ACU. The external power receptacle is used for ground operation of the electrical
equipment and helps the main battery during ground starts.

C.

Electrical power is supplied to the two primary electrical busses through two 30A fuses, two 30A circuit
breakers, or two 40A circuit breakers in the junction box. These electrical busses supply power to two
avionics busses through 15A circuit breakers. The two avionics busses are controlled by an avionics
master switch. Airplanes that have propeller heat have three electrical busses that supply power
through three 30A fuses, three 30A circuit breakers, or three 40A circuit breakers.

D.

The operation of the main battery and alternator system is controlled by the MASTER ALT BAT switch.
The switch is an interlocking split rocker and is found on the left side of the switch panel. The right
half of the rocker controls the main battery and the left half controls the alternator. It is possible
in this configuration for the main battery to be on-line without the alternator. However, operation of
the alternator without the main battery is not possible. The BAT MASTER switch, when operated,
connects the main battery contactor coil to ground so that the contacts close and supply power to the
system from the main battery only. The ALT MASTER switch, when ON, applies positive voltage to
the ACU and to the alternator contactor coil at the same time, which then applies field voltage to the
alternator field and supplies power to the electrical system from the alternator.

E.

The operation of the standby battery, if installed, is controlled by a three-position STDBY BATT switch.
Normal flight operation is with the switch in the ARM position that lets the standby battery charge from
the G1000 essential bus. If there is an alternator failure, the standby battery controller will not let the
standby battery discharge to the G1000 essential bus until the depletion or failure of the main battery.
It is necessary during preflight to do an energy level acceptance test. Refer to the Pilot's Operating
Handbook, Chapter 4, Starting Engine, for details of the "energy level" acceptance test.

F.

The main battery ammeter is controlled by a sensor found in the power junction box. In flight, without
the use of external power, the meter shows the quantity of current that flows to or from the battery.
With a low battery and the engine at cruise speed, the ammeter will show a large positive output and a
charge of the main battery. When the main battery is fully charged, the ammeter will show a minimum
charge rate.

G.

The standard main battery is a 24-volt, 12.75 Amp-hour (5-hour rate), flooded lead-acid type. The
battery is installed in the tailcone. A heavy-duty main battery is installed in airplanes with propeller
heat systems. The heavy-duty battery is a 24-volt, 15.5 Amp-hour (5-hour rate), flooded lead-acid
type.

Tools, Equipment, and Materials
NOTE:

Equivalent substitutes can be used for the following items:

24-00-00
© Cessna Aircraft Company

Page 1
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
NAME

NUMBER

MANUFACTURER

USE

Adhesive

41-30

Mid-West Industrial Chemical
Company
1509 Sublette
St. Louis, MO 63110

Used to bond the battery
vent drain tubes to the
battery case elbows.

Battery Charger

TDMC-81

Cessna Aircraft Company

Charges the battery.

Available Commercially

Cleans the battery.

John Fluke Mfg. Co.
6920 Seaway Blvd.
Everett, WA 98206

General electrical use.

Available Commercially

Measures the specific
gravity of electrolytes.

Lamar Technology Inc.
14900 40th Avenue North East
Marysville, WA 98271

To do the tests and
troubleshooting for
the J-box, (MCU) and
alternator systems.

Nonmetallic Brush
(Acid-Resistant)

Available Commercially

Cleans battery cells.

Rubber Gloves,
Rubber Apron, and
Protective Goggles.

Available Commercially

Give protection when you
clean the battery.

Small syringe

Available Commercially

Service of the battery.

Variable Power
Supply

Available Commercially

Supplies external power for
ground maintenance.

Cleaning Cloth
Digital Voltmeter

Model 87

Hydrometer (1.100
to 1.310 specific
gravity range)

I

MCU Test Set
(With instructions,
LI-0021)

TE04

12 Volt DC Power
Adapter

D02-0042

Cessna Aircraft Company
Cessna Parts Distribution
Department 701, CPD 2
5800 East Pawnee Road
Wichita, KS 67218-5590

Cabin Power System.
Commercial Airline
Connector adapts to
Automotive Power Port
Connector.

24-Volt Battery
Charger

TSC-01 V

Teledyne Continental Motors Battery
Products
840 West Brockton Avenue
Redlands, CA 92374
Phone: 1-800-456-0070

Charges the battery.

24-00-OCI
© Cessna Aircraft Company

Page 2
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
ALTERNATOR SYSTEM - TROUBLESHOOTING
1.

General
A.

I

A troubleshooting chart has been developed to aid the maintenance technician in system
understanding. Refer to Figure 101.
NOTE:

Refer to the Lamar TE04 MCU Test Set and the LI-0021 instructions for additional testing
procedures of the alternator system. Refer to Electrical Power- General, Tools, Equipment,
and Materials.

24-20-00
O Cessna Aircraft Company

Page 101
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1130

ALTERNATOR FIELD CIRCUIT BREAKER
OPENS, BATTERY SWITCH ON, ALTERNATOR
SWITCH ON, ENGINE NOT RUNNING.

I
TURN OFF BATTERY AND ALTERNATOR SWITCH AND RESET
BREAKER. REMOVE "B" LEAD FROM ALTERNATOR. TURN BATTERY
AND ALTERNATOR SWITCH ON. IFALTERNATOR FIELD CIRCUIT
BREAKERS OPENS -

I
THEN TURN OFF BATT AND ALT SWITCH AND RESET
BREAKER. DISCONNECT ALTERNATOR POWER WIRE FROM
ACU. TURN ON BATTAND ALT SWITCHES. IF ALTERNATOR
FIELD CIRCUIT BREAKER OPENS.

IF NOT, REPAIR OR
REPLACE ALTERNATOR.

THEN TURN OFF BATT AND ALT SWITCH AND RESET
BREAKER. DISCONNECT FIELD WIRE FROM FIELD TERMINAL
OF ALTERNATOR. TURN BATT AND ALT SWITCH ON. IF
ALTERNATOR FIELD CIRCUIT BREAKER OPENS.

IF NOT, CHECK FOR
SHORT IN ALTERNATOR
POWER WIRE BETWEEN
ACU AND ALTERNATOR.
REPAIR OR REPLACE
WIRE AS NECESSARY.

THEN CHECK FOR SHORT IN FIELD
WIRE BETWEEN ACU AND
ALTERNATOR. IF SHORT IS FOUND.

IF NOT, FIELD IS SHORTED INSIDE
ALTERNATOR. REPAIR OR REPLACE
ALTERNATOR.

THEN REPAIR OR REPLACE FIELD
WIRE AS NECESSARY.

IF NOT, THEN TURN OFF BATT AND ALT
SWITCH AND RESET CIRCUIT BREAKER.
DISCONNECT CONNECTOR FROM ACU.
TURN ON BATT AND ALT SWITCH. IF
ALT FIELD CIRCUIT BREAKER OPENS.

THEN CHECK FOR SHORT IN WIRE
BETWEEN CIRCUIT BREAKER AND ACU.
REPAIR OR REPLACE WIRE.

I

IF NOT, THEN REPLACE ACU.

I

Alternator System Troubleshooting Chart
Figure 101 (Sheet 1)

24-20-00
© Cessna Aircraft Company

Page 102
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1131

ALTERNATOR FIELD CIRCUIT BREAKER OPENS ONLY WHEN
ENGINE IS RUNNING. ALTERNATOR AND BATTERY SWITCH ON.

CHECK FOR SHORT BETWEEN ALTERNATOR FIELD WIRE AND

ALTERNATOR POWER WIRE.

IF SHORT IS FOUND, REPAIR
OR REPLACE DAMAGED WIRE.

IF NO SHORT IS FOUND,
REPLACE ACU.

WITH ENGINE RUNNING, LOW VOLTAGE LIGHT DOES NOT GO OUT WHEN
ALTERNATOR AND BATTERY SWITCHES ARE TURNED ON, ALL OTHER SWITCHES OFF.

CHECK BUS VOLTAGE. WITH ENGINE RUNNING, IF 25V OR HIGHER,

I

I
THEN DISCONNECT CONNECTOR
FROM ACU AND OBSERVE
LOW VOLTAGE INDICATOR WITH
ENGINE NOT RUNNING.

I
IF NOT, THEN CHECK FIELD VOLTAGE
AT ALTERNATOR FIELD TERMINAL
AND BATTERY VOLTAGE WITH ENGINE
NOT RUNNING. IF THERE IS LESS
THAN 3V DIFFERENCE.

* I
IF LOW VOLTAGE LIGHT COMES
ON, CHECK LOW VOLTAGE WARNING
WIRE BETWEEN ACU AND ANNUNCIATOR
PANEL FOR SHORT TO GROUND. IF SHORT
IS FOUND,

OTHERWISE,
REPLACE ACU.

REPAIR OR REPLACE DAMAGED WIRING.

OTHERWISE,
REPLACE ANNUNCIATOR.

A
Alternator System Troubleshooting Chart
Figure 101 (Sheet 2)

24-20-00
© Cessna Aircraft Company

Page 103
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1132

A

OTHERWISE, CHECK VOLTAGE AT
COIL TERMINAL OF ALTERNATOR
CONTACTOR. IF IT IS WITHIN 2V OF
BATTERY VOLTAGE,

THEN REPLACE
ALTERNATOR.

THEN CHECK VOLTAGE BETWEEN
GROUND AND ACU SIDE OF
ALTERNATOR CONTACTOR AND
COMPARE TO VOLTAGE BETWEEN
GROUND AND BUS SIDE OF
CONTACTOR. THE TWO READINGS
SHOULD BE THE SAME (WITHIN LESS
THAN 1 VOLT DIFFERENCE).
IF THEY ARE,

THEN REPLACE ACU.

OTHERWISE CHECK ALTERNATOR
FIELD CIRCUIT BREAKER, ALTERNATOR
SWITCH AND ANY CONNECTORS, BETWEEN
BUS AND COIL TERMINAL OF ALTERNATOR
CONTACTOR, AND REPLACE AS NECESSARY
UNTIL VOLTAGE DIFFERENCE IS LESS
THAN 2V.

I

OTHERWISE REPLACE ALTERNATOR
CONTRACTOR.

Alternator System Troubleshooting Chart
Figure 101 (Sheet 3)

24-20-00
© Cessna Aircraft Company

Page 104
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1133

WITH ENGINE RUNNING ALTERNATOR MAKES ABNORMAL WHINING NOISE.

CHECK FOR SHORTED DIODE IN ALTERNATOR. TURN OFF BATTERY SWITCH AND REMOVE
CABLE FROM "BAT" TERMINAL OF ALTERNATOR. USING A DIGITAL MULTIMETER WITH THE
DIODE FUNCTION SELECTED, PLACE NEGATIVE LEAD ON "BAT" TERMINAL OF ALTERNATOR
AND POSITIVE LEAD ON CASE OR "GND" TERMINAL AND A READING OF APPROXIMATELY 0.8
TO 1.0 SHOULD BE SEEN. REVERSE THE TEST LEADS AND THE METER SHOULD INDICATE AN
OPEN CIRCUIT. IF THE RESISTANCE FUNCTION OF THE METER IS SELECTED OR IF USING
OLDER ANALOG METERS THE READINGS WILL BE DIFFERENT BUT ONE DIRECTION
SHOULD YIELD AN OPEN CIRCUITAND THE OTHER A NUMERICAL VALUE OF VERY HIGH
RESISTANCE (USUALLY GREATER THAN 1 MEGA OHM). SINCE THE ALTERNATOR HAS AN
INTERNAL CAPACITOR, READINGS TAKEN WITH METERS SELECTED ON RESISTANCE MAY BE
UNSTABLE. IF READINGS ARE OBTAINED THAT DIFFER FROM PREVIOUSLY STATED,

I
THEN REPAIR OR REPLACE ALTERNATOR.

Alternator System Troubleshooting Chart
Figure 101 (Sheet 4)

24-20-00
© Cessna Aircraft Company

Page 105
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
ALTERNATOR - MAINTENANCE PRACTICES

1.

General
A.

2.

The alternator is installed on the forward side of the engine, below and to the right of the crankshaft.
(1) A 60-amp alternator is standard for all airplanes. A 95-amp alternator is optional for some model
182T's and for all T182T's.

Alternator Removal/Installation
A.

Remove Alternator (Refer to Figure 201).
(1) Remove the cowls. Refer to Chapter 71, Cowl - Maintenance Practices.
(2) Disconnect battery cables.
(3) Disconnect the connector terminals (UC001) from the alternator (MN001).
(4) Remove safety wire from adjusting bolt. Loosen bolt.
(5) Loosen alternator mounting bolt.
(6) Rotate alternator and remove drive belt from alternator pulley.
(7) Remove adjusting bolt and mounting bolt, then remove alternator from airplane.

B.

Install Alternator (Refer to Figure 201).
(1) Set the alternator (MN001) on the mounting bracket and install the mounting bolt and nut. Do
not tighten at this time.
(2) Place drive belt on alternator pulley.
(3) Install adjusting bolt.

CAUTION: Any airplane with a new alternator belt installed, including new
airplanes, belt tension must be checked within the first 10 to 25
hours of operation.
(4) Apply a torque wrench to the nut on alternator pulley and adjust the belt tension so the belt slips
at 7 foot-pounds to 9 foot-pounds (9.49 N.m to 12.20 N.m) of torque with a used belt, or 11
foot-pounds to 13 foot-pounds (14.91 N.m to 17.62 N.m) of torque with new belt.
(5) Tighten and safety wire adjusting bolt.
(6) Tighten alternator mounting bolt.
(7) Connect electrical connectors to alternator.
(8) Install the cowls. Refer to Chapter 71, Cowl - Maintenance Practices.

24-20-00
© Cessna Aircraft Company

Page 201
Aug 4/2003

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

ndd~J

WASHER

1001)

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DETAIL A
0710T1001
A0750T1004

Alternator Installation
Figure 201 (Sheet 1)

24-20-00
© Cessna Aircraft Company

Page 202
Aug 4/2003

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
BATTERY - TROUBLESHOOTING
1.

General
A.

A troubleshooting chart is included to aid in maintenance of the battery system. Refer to Figure 101.

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April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

B1135

BATTERY WILL NOT HOLD ITS CHARGE
OR WILL NOT COME UP TO CHARGE.

CHECK TO ENSURE ALTERNATOR CONTROL UNIT
IS WORKING PROPERLY. IF -

OK, CHECK TO ENSURE EQUIPMENT
NOT LEFT ON ACCIDENTALLY. IF -

NOT OK, ADJUST/REPLACE
ALTERNATOR CONTROL UNIT.

OK, CHECK FOR SHORT CIRCUIT OR
SHORT TO GROUND IN WIRING. IF -

NOT OK, TURN OFF EQUIPMENT,
REMOVE BATTERY AND RECHARGE.

OK, CHECK FOR BROKEN CELL
PARTITION. IF-

NOT OK, REPAIR WIRING
AND REMOVE BATTERY.

OK, CHECK TOP OF BATTERY FOR
CONTAMINATED ELECTROLYTE. IF -

NOT OK, REPLACE
BATTERY.

OK, CHECK FOR SULFATED PLATES.
IF-

NOT OK, CLEAN AND DRY
TOP SURFACE OF BATTERY.

OK, CHECK FOR INTERNAL
SHORT UNDER LOAD. IF -

NOT OK, REMOVE BATTERY AND CHARGE USING
NORMAL PROCEDURES AND THEN GIVE A 60 HOUR
OVER CHARGE AT 10 PERCENT NORMAL CHARGING
RATE. IF SPECIFIC GRAVITY IS STILL LOW (BELOW
1.260) BATTERY IS UNFIT FOR SERVICE. IF ABOVE
1.260, PERFORM CAPACITY CHECK,

, A
Battery Troubleshooting Chart
Figure 101 (Sheet 1)

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MODEL 182/T182
MAINTENANCE MANUAL

B1136

I

I
OK, CHECK FOR BATTERY
DISCHARGING DUE TO
SULFATION TRACE BUILDUP.
REMOVE BATTERY, FULLY
CHARGE. CLEAN AND
NEUTRALIZE OUTSIDE OF
BATTERY. STORE IN DRY
COOLAREA FOR 10 DAYS.
IF SPECIFIC GRAVITY DROPS
MORE THAN 15 POINTS,
REPLACE BATTERY.

NOT OK, REMOVE BATTERY.
AFTER A FULL CHARGE, APPLY
30 AMP LOAD FOR 10 MINUTES.
REPLACE BATTERY IF SPECIFIC
GRAVITY DROPS 80 OR MORE
POINTS BELOWAVERAGE.

A -Battery Troubleshooting Chart
Figure 101 (Sheet 2)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

B1137

BATTERY LIFE IS SHORT.

I

I
CHECK ALTERNATOR CONTROL UNIT
FOR VOLTAGE OUTPUT. IF -

OK, ENSURE ELECTROLYTE LEVEL
IS NOT BELOW TOP OF PLATES. IF -

NOT OK, ADJUST OR
REPLACE AS REQUIRED.

OK, CHECK FOR FREQUENT DISCHARGES.
THIS IS DUE TO EXCESSIVE USE OF STARTER
AND OTHER ELECTRICAL EQUIPMENT WHILE
ON GROUND AND RECHARGING IN AIR,
WHICH USES BATTERY EXCESSIVELY. IF -

NOT OK, ADD
WATER.

OK, CHECK FOR IMPROPER STORAGE.
DRY BATTERIES STORED IN A DAMP
LOCATION, OR WET BATTERIES STORED
TOO LONG A PERIOD WITHOUT
CHARGING, WILL CONTRIBUTE TO SHORT
BATTERY LIFE.

NOT OK, REDUCE UNNECESSARY
USE OF STARTER AND OTHER
ELECTRICAL EQUIPMENT WHILE
ON THE GROUND.

Battery Troubleshooting Chart
Figure 101 (Sheet 3)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

B1138

I

CASE OR CELL DAMAGED.

CHECK TO ENSURE HOLD-DOWN IS NOT
TOO LOOSE OR TIGHT. IF -

I
OK, CHECK FOR FROZEN BATTERY.
THIS MAY BE DUE TO ADDING
WATER IN COLD WEATHER WITHOUT
SUFFICIENT CHARGING AFTERWARD,
OR A LOW SPECIFIC GRAVITY OF
ELECTROLYTE DUE TO IMPROPER
FILLING PROCEDURES. REPLACE WITH
FULLY CHARGED BATTERY.

NOT OK, REMOVE BATTERY AND
INSPECT. IF NO VISUAL DAMAGE,
CHARGE AND TEST. IF DAMAGED,
REPLACE WITH FULLY CHARGED
BATTERY.

Battery Troubleshooting Chart
Figure 101 (Sheet 4)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1139

POLARITY REVERSED.

I
CHECK TO ENSURE BATTERY WAS NOT CONNECTED
BACKWARDS ON AIRPLANE. IF -

I

I
OK, ENSURE BATTERY WAS NOT
CONNECTED BACKWARD ON
CHARGER. SLOWLY DISCHARGE
COMPLETELY AND THEN CHARGE
CORRECTLY AND TEST.

NOT OK, SLOWLY DISCHARGE
COMPLETELY AND THEN
CHARGE CORRECTLY AND
TEST.

Battery Troubleshooting Chart
Figure 101 (Sheet 5)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1140

BATTERY CONSUMES
EXCESSIVE WATER.

CHECK ALTERNATOR CONTROL UNIT FOR PROPER VOLTAGE
OUTPUTAT GIVEN TEMPERATURE RANGES. IF -

I
I

I
NOT OK, ADJUST OR REPLACE
ALTERNATOR CONTROL UNIT
AS REQUIRED.

OK, CHECK FOR PROPER
ELECTROLYTE LEVELAND
ADJUSTAS REQUIRED.

Battery Troubleshooting Chart
Figure 101 (Sheet 6)

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April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
BATTERY - MAINTENANCE PRACTICES
1.

General
A.

The battery is a 24-Volt, 12.75 Amp-hour or an optional heavy-duty 15.5 Amp-hour flooded lead acid
type. Either of these batteries can be installed. The battery is installed in the tailcone, aft of the
baggage compartment on the left side.
NOTE:

2.

The Amp-hour rate is based on a five hour discharge rate.

Battery Removal/Installation
A.

Remove the Battery (Refer to Figure 201).
(1) Remove the access plate (31 OAR). Refer to Chapter 6, Access/Inspection Plates - Description
and Operation.
(2) Cut the tie straps to the positive terminal cover.
(3) Remove the positive terminal cover.

CAUTION: Disconnect the negative battery cable first, then the positive cable.
This will prevent an accidental short of the battery from hand tools.
(4)
(5)
(6)
(7)
(8)
(9)
B.

Disconnect the negative cable from the battery.
Disconnect the positive cable from the battery.
Disconnect the drain tube from the battery.
Remove the battery hold-down bolts and washers.
Remove the battery cover.
Remove the battery from the airplane.

Install the Battery (Refer to Figure 201).
(1) Set the battery in position and install the battery hold-down bolts.

CAUTION: Do not tighten the hold-down bolts too much or you will damage the
hold-down strap.
|* ~

(2) Tighten the hold-down bolts until the bolt head touches the batter cover and add one turn.
(3) Connect the battery drain tubes with the hose clamps.

CAUTION: Connect the positive battery cable first, then the negative cable.
This will prevent an accidental short of the battery from hand tools.
(4) Connect the positive battery cable.
(5) Install the positive battery terminal cover.
(6) Attach tie-straps to the terminal cover.
(7) Connect the negative battery cable.
(8) Install the access plate (31 OAR). Refer to Chapter 6, Access/Inspection Plates - Description and
Operation.
3.

Battery Cleaning
A.

Clean the Battery (Refer to Figure 201).
NOTE:

For correct operation, the battery and connections must be clean at all times.

(1) Remove the battery. Refer to Battery Removal/Installation.
(2) Tighten the battery cell filler caps to prevent the cleaning solution from entering the cells.
(3) Use a clean cloth moistened with a solution of bicarbonate (baking soda) and water to clean the
battery cable ends, battery terminals and the surfaces of the battery.
(4) Rinse with clear water.
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Aug 4/2003

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

B1141

BOLT
BATTERY
COVER

EGATIVE

ABLE

BATTERY

DRAIN
TUBE

-

ANUntif

NUT

0718T1016

Battery Installation
Figure 201 (Sheet 1)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
(5)
(6)
(7)
(8)
4.

New Battery Activation
A.

5.

Use a dry cloth to clean off the water and let the battery dry.
Polish the cable ends and battery terminals with an emery cloth or a wire brush.
Install the battery. Refer to Battery Removal/Installation.
Apply petroleum jelly or an ignition spray product to the battery terminals to decrease corrosion.

Activate the New Battery.
(1) Do a specific gravity check to make sure the correct strength of electrolyte is used. The
electrolyte must be 1.285 +0.005 or -0.005 specific gravity when it is measured between 75TF
to 85'F (24%i

0710T1001
A0718T1053A
B0718T1060

Standby Battery Installation
Figure 201 (Sheet 1)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
A
Am
B

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B

A

DETAIL

_r66.
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A

SCREW
STANDBY BATI
TEST OVERHE/
SWITCH (S1022)

STANDBY BATTERY
TEST RESISTOR
(RI01 0)

DETAIL

B
0710T1001
A1218T1001A
B1218T1047

Standby Battery Printed Circuit Board Installation
Figure 202 (Sheet 1)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
(3) Install the screws that attach the board to the extrusion.
(4) Connect the board to the electrical connector (PI036).
(5) Install the switch panel. Refer to Chapter 31, Instrument and Control Panels - Maintenance
Practices.
4.

Standby Battery Charging
A.

Charge the Battery.
(1) Remove the battery from the airplane and put it in a well-ventilated area to charge. Refer to
Chapter 24, Standby Battery - Removal/Installation.
(2) Connect the battery to the charger with the black, round Standby Battery Connector (P1). A
mating connector (JC032) is available from Cessna Aircraft Company. Refer to the Model 182S/
182T/T182T Wiring Diagram Manual, Chapter 24 Electrical Power - Battery System.
NOTE:

|I

To charge the standby battery, a constant voltage charger, constant current charger,
or a modification of both is used. Use only chargers that are made to charge lead
acid batteries. A constant voltage "fast" charge can be done with a charger that has a
DC voltage between 28.3 and 30.0 volts. A "float" charge can be done with a charger
that has a DC voltage between 27.2 and 28.2 volts.

CAUTION: Never set the charger to a level higher than 30.0 volts or you can
damage the battery.
(3) For a constant current charger, charge the battery per the charger's instructions.
NOTE:

There is no limit on the initial charge current as long as the voltage is not more than
30.0 volts. If it is necessary to set the charger to the battery capacity, use 8 amp-hour
as the standby battery capacity.

(4) For a constant voltage charger, charge the battery for up to 16 hours with a "fast" charge voltage
between 28.3 and 30.0 volts.
NOTE:

Charge times of less than 16 hours can be done, depending on the state of charge
of the battery. The battery can be thought to be completely charged if the charge
current stays stable (approximately .1 to .2 amps) for a minimum of one hour. You can
charge the battery for more than 16 hours if you keep the charge voltages between
the recommended float charge range (between 27.2 and 28.2 volts).

(5) Install the battery. Refer to Chapter 24, Standby Battery - Removal/Installation.
(6) Do the Standby Battery Energy Level Test in the Pilot's Operating Handbook, Chapter 4 - Starting
Engine Procedures. Make sure that the green test light for the standby battery comes on and
stays on for the specified time period.
5.

Standby Battery Storage
A.

For the best battery life, keep the standby battery in a fully charged state when not in use. This is true
when installed on the aircraft and when in long-term storage. To leave the battery in an uncharged
state for a given period of time will decrease the life of the battery. It is recommended to charge the
battery at a minimum of once every three months of inactivity. In warm climates, a more frequent
charge will be necessary.

B.

Do not keep the battery in storage for long periods of time in an environment where the temperature
is more than approximately 77 °F (25 °C). Sun shades that cover the aircraft deck skin that decrease
the temperature of the battery are recommended when the aircraft is parked in direct sunlight.

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MODEL 182/T182
MAINTENANCE MANUAL

6.

Standby Battery Capacity Test
A.

The battery capacity must be tested. Refer to Chapter 5, Inspection Time Limits. This test is also
necessary to give the battery condition if the battery voltage decreases to less than 20.0 volts, such
as in unintentional deep discharge.

B.

Battery Capacity Test
(1) Make sure that the battery is fully charged before the capacity test is started. If charge condition
is unknown, charge the battery. Refer to Chapter 24 Standby Battery - Maintenance Practices.
(2) Put the airplane in an area where there are high cabin light levels. Use sunlight or a well-lit
hangar facility.
NOTE:

The photocell on the PFD must cause the PFD light level to be full bright. The
AVIONICS rheostat cannot operate with the primary alternator and battery off.

(3) Turn the STDBY IND rheostat to the full clockwise position.
NOTE:

A stopwatch will be necessary in the following steps to time the battery discharge.

(4) With the BAT/ALT MASTER switch in the OFF position, set the STDBY BATT switch to the ARM
position and immediately start the stopwatch.
(5) Make sure that all of the equipment on the essential bus operates correctly.
NOTE:

After initialization, the PFD operates in full bright mode with only red X's over the NAV
2, COM 2, and XPDR functions.

(6) Make sure that all the standby indicator lights come on.
(7) Make sure that the MFD and all the other electrical and avionic equipment on the primary busses
are not on.
(a) If the conditions in steps 6 through 8 are not met, stop the test and correct these conditions.
(b) Start at Step 1 when the condition has been corrected.
NOTE:

The standby battery initial current discharge is between 2.1 and 3.1 amps as
shown on the PFD standby battery ammeter. The essential bus initial voltage is
approximately 24.2 volts as shown on the PFD essential bus voltmeter.

(8) Continuously monitor the essential bus voltage as shown on the PFD essential bus voltmeter.
The battery capacity is satisfactory if the bus voltage stays above 20.0 volts for a minimum of
55 minutes.
(9) Set the STDBY BATT switch to OFF if the essential bus decreases to 20.0 volts or after 55
minutes.
CAUTION: Do not let the essential bus voltage decrease below 20.0 volts or
you can cause damage to the standby battery. Set the STDBY
BATT switch to the OFF position before the voltage drops below
20.0 volts. Voltage values less than 22.5 volts can decrease quickly
so monitor the voltage closely. If the voltage drops below 20.0 volts,
charge the battery immediately and do the test again.
NOTE:

If the standby battery does not stay above 20.0 volts for 55 minutes during the capacity
test, the battery is not acceptable for return to service.

(10) Charge the battery. Refer to Chapter 24, Battery - Maintenance Practices, Battery Charging.

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
12-VOLT CABIN POWER SYSTEM - TROUBLESHOOTING
1.

2.

General
A.

The 12-volt cabin power outlet on the pedestal uses a power converter to convert 28-volt DC input
power to 13.8-volt DC output power. In airplanes with the Garmin G1000 the power converter is in the
cockpit on the aft, right side of the firewall. The power converter in all other airplanes is in the tailcone.

B.

The 12-volt cabin power outlet behind the copilot's seat and near the headset jacks on airplanes
with Garmin G 1000 uses a power converter to convert 28-volt DC input power to 13.8-volt DC output
power. The 20 amps of 12-volt power are split evenly between the forward and the aft power outlets.
In airplanes with the Garmin G1000 installed, a CABIN PWR 12V switch is located on the switch panel.

C.

The converter output is used to power electrical devices that require a 12-volt power input. The
electrical connections are made with the use of a terminal block that is on the side of the converter.
The converter's output can be turned on and off by the use of the ON/OFF signal terminal on the
converter's terminal block. When 28 VDC is applied to this terminal, the converter will turn the output
on. When the 28 VDC is removed from the terminal, the output is turned off.

Cabin Power Interface
A.

3.

Complete a Test of the Cabin Power Interface (Refer to Figure 101).
(1) Make sure the ALT/BAT Master switch is in the ON position.
(2) For airplanes with serials 18280001 thru 18281197 and airplanes T18208001 thru T18208185,
use a 12-Volt DC power adapter to do the test. Refer to Tools, Equipment and Materials.
(a) Attach the adapter to the cabin power system.
(3) Use a voltmeter to make sure the output shows 13.4 volts, +0.9 or -0.9 volts at the cabin power
interface.
(4) If the correct voltage is not indicated, refer to the Power Converter troubleshooting procedures.

Power Converter
A.

Test the Power Converter (Refer to Figure 102 and to the Model 182 Wire Diagram Manual, Chapter
24, Power Interface).
(1) Disconnect the connector (JI).
(2) Test for approximately 24-Volts between VI+ and VI- at the connector (JI).
(3) Test for approximately 24-Volts between the ON/OFF and VI- at the connector (JI).
(4) If there is no voltage, examine the wiring from the power convertor to the connector (JI) for
damage or bad connections.
(a) Repair or replace the connector (JI) or the wiring as necessary.
1
Attach the connector (JI).
2
Test the cabin power interface for correct operation. Refer to Cabin Power Interface.
3
Proceed to step 3.A.(5) if the cabin power interface does not operate correctly.
(5) Test the pins VO+ and VO- for an output of 13.4 volts, +0.9 or -0.9 volts.
(a) If the correct voltage is supplied, test the continuity from the connector (JI) to the cabin
power interface in Figure 101.
1
If the wire continuity is not correct or the wire is damaged, replace the wiring as
necessary.
2
If the wire continuity is correct, replace the power converter.

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

A

TRIM
WHEEL

(
0o

CABIN
POWER
INTERFACE

PEDESTAL
COVER

AUDIO
IN
0

AUDIO IN

CABIN
POWER
INTERFACE

--

-

DETAIL A

DETAIL A
AIRPLANES 18280001 THRU 18280944,
AIRPLANES 18280945 THRU 18281197 AND
AIRPLANES T18208001 THRU T18208185

AIRPLANES 18281198 AND ON AND
AIRPLANES T18208186 AND ON

0710T1001
A071 9T1031
A0719T1032

Cabin Power Interface
Figure 101 (Sheet 1)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

B4145

CABIN
nf^'\Airc

AFT SIDEWALL
UPHOLSTERY

A

*A
DETAIL B
VIEW LOOKING OUTBOARD
ON RIGHT SIDE

VIEW A-A
VIEW WITH CAP REMOVED
B0719T1094
AA0719T094

Cabin Power Interface
Figure 101 (Sheet 2)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

neon

c

NOTE:

THE POWER CONVERTER
CAN BE IN DIFFERENT
LOCATIONS. IN AIRPLANES
WITH THE GARMIN G1000
IT IS IN THE COCKPIT ON THE
AFT, RIGHT SIDE OF THE
FIREWALL. IN AIRPLANES
WITH STANDARD AVIONICS
IT IS IN THE TAILCONE.

CONNECTOR
(J1)
JVERTER

DETAIL

A

0710T1001
A1260T1012

Power Converter
Figure 102 (Sheet 1)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
POWER JUNCTION BOX - MAINTENANCE PRACTICES
1.

General
A.

2.

3.

The power junction box, also referred to as a Master Control Unit (MCU), is installed on the forward,
left side of the firewall. The power junction box has a battery relay, starter relay, alternator relay,
current sensor, external power relay, alternator control unit, power distribution bus, and bus fuses (or
circuit breakers as applicable).

Power Junction Box Removal/Installation
A.

Remove the Power Junction Box (Refer to Figure 201).
(1) Remove the access plate (31 OAR) and disconnect the battery cables (UC001). Refer to Chapter
6, Access/Inspection Plates - Description and Operation.
(2) Remove the cover from the power junction box.
(3) Disconnect the electrical connectors, cables, and ground strap from the power junction box.
(4) Remove the screws that attach the power junction box to the firewall.
(5) Remove the power junction box.

B.

Install the Power Junction Box (Refer to Figure 201).
(1) Position the power junction box on the firewall and attach it with the screws.
(2) Connect the electrical connectors, cables, and ground strap to the power junction box.
(3) Install the cover on the power junction box.
(4) Connect the battery cables (UC001), and install the access plate (31 OAR). Refer to Chapter 6,
Access/Inspection Plates - Description and Operation.

Component Removal/Installation
A.

General Precautions and Notes.

CAUTION: Make sure that all electrical power is removed from the airplane and
that the battery is disconnected before you work on components of
the junction box.
Individual components such as relays, transducers, and the alternator control unit can
be replaced on an as-needed basis. Refer to the Model 182 Illustrated Parts Catalog for
replacement part numbers.
(2) Before you disconnect the wires, identify and put a label on the wires for later installation.
(3) Torque values for ground and current-carrying studs can be found in Chapter 20, Torque Data Maintenance Practices.
(1)

4.

Power Junction Box Troubleshooting
A.

Complete the Power Junction Box Troubleshooting.
(1) The power junction box troubleshooting is done with the Lamar TE04 MCU Test Set. Use the
LI-0021 instructions. Refer to Electrical Power - General, Tools, Equipment, and Materials.

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

E

BOLT

POWER
JUNCTION
BOX

A
EXTERNAL
ELECTRICAL
POWER

A

DETAIL A
0710T1001
A0558T1001

Power Junction Box Installation
Figure 201 (Sheet 1)

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MODEL 182/T182
MAINTENANCE MANUAL

ALTERNATOR

ALTERNATOR
CONTROL

PROPELLER DE-ICE
FUSE (F3)

CABLE

POIN
CLOCK
FUSE

CURREN
SENSOR

I

D
D
FUSE
(F1)

STARTER
RELAY (K

EXTERNAL
OWER
ELAY (K4)

STARTER CABLE
ATTACH POINT

RELAY

(K3)

POSITIVE BATTERY
CABLE ATTACH
POINT

ELECTRICAL
CONNECTORS
(J1 AND J2)

VIEWA-A
AIRPLANES 18280001 THRU 18280944

AA0558R1002

Power Junction Box Installation
Figure 201 (Sheet 2)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B4005

CIRCUIT
BREAKER

ALTERNATOR

CIRCUIT
D

IT

ALTERNATOR
CONTACTOR
(K1)

CK

D

[

ST
C
(K

TERNAL
WER
NTACTOR

CONNECTORS
(J1 AND J2)

VIEW A-A
AIRPLANES 18280945 AND ON AND
AIRPLANES T18208001 AND ON AND
AIRPLANES 18280001 THRU 18280944
INCORPORATING SB00-24-01

NOTE:

CS3100 CURRENT SENSOR SHOWN
CS3200 CURRENT SENSOR SIMILAR
FOR J-BOXES MC01-3A(IC10) AND ON.
AA0558T1007

Power Junction Box Installation
Figure 201 (Sheet 3)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
ALTERNATOR CONTROL UNIT - MAINTENANCE PRACTICES
1.

General
A.

2.

Alternator Control Unit Removal/Installation
A.
B.

3.

The Alternator Control Unit (ACU) is found inside the power junction box, also referred to as a Master
Control Unit (MCU) or J-Box. The alternator system includes the ACU, Alternator Contactor, and
alternator field circuit. The ACU functions are as follows:
(1) Alternator Voltage Regulation - The ACU controls the alternator field circuit to supply a main bus
voltage of approximately 28.5 volts.
(2) Low Voltage Annunciation - The ACU monitors the main bus voltage in the power junction box
and supplies an output for low voltage (less than 24.5 +0.35 or -0.35 volts) for the annunciation.
(3) Over-voltage Protection - The ACU monitors the main bus voltage in the power junction box and
disengages the aircraft ALT FIELD circuit breaker. This removes the power from the alternator
system if there is an over-voltage condition greater than 31.75 +0.5 or -0.5 volts.
(4) Reverse Alternator Current Protection - The ACU monitors the alternator output current and
disengages the aircraft ALT FIELD circuit breaker. This removes the power from the alternator
system if there is a reverse alternator current.
(5) Excess Field Current Protection - The ACU monitors the alternator field current and disengages
the aircraft ALT FIELD circuit breaker. This removes the power from the alternator system if
there is an excessive field current.

Remove the Alternator Control Unit. Refer to Power Junction Box - Maintenance Practices,
Component Removal/Installation.
Install the Alternator Control Unit. Refer to Power Junction Box - Maintenance Practices, Component
Removal/Installation.

Over-voltage Protection Circuit Test
A.

General.
(1) The ACU Over-voltage Protection Circuit must be tested in accordance with the time limits in
Chapter 5, Inspection Time Limits. Use one of the two procedures that follow to do the test of
the Over-voltage Protection Circuit. The recommended procedure uses the Lamar TE04 MCU
Test Set. The external battery procedure can be used if a TE04 test set is not available.

B.

Over-voltage Protection Circuit Test with the Lamar TE04 MCU Test Set
(1) Use a Lamar TE04 MCU Test Set and do steps 4.2, 4.3.A, 4.3.B, and 4.3.1 in the Lamar's TE04
MCU Test Set instructions LI-0021 (refer to Electrical Power - General, Tools, Equipment, and
Materials).
(2) If the ACU TRIP indicator on the TE04 MCU Test Set does not illuminate in step 4.3.1, the Overvoltage Protection Circuit is not operational.
(a) Replace the ACU.
(b) Do this test again.
(3) If the ACU TRIP indicator does illuminate in step 4.3.1, the Over-voltage Protection Circuit is
operational.
(a) Complete the Lamar procedure 4.3.1.
(b) Remove the TE04 MCU Test Set.
(c) Continue with step D in this section.

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C.

Over-voltage Protection Circuit Test with External Batteries
NOTE:

It is necessary to use two general non-rechargeable 9 volt batteries in new condition to
apply a temporary over-voltage condition on the ACU Sense wire. A locally fabricated
battery test harness is also necessary. The test harness uses two 9-volt snap connectors
and two insulated alligator clips. (Refer to Figure 201.) These components are available
at most battery supply stores. For ground safety reasons, only general household 9 volt
batteries which have a relatively low ampere rating are used.

(1) Make sure the BAT MASTER, ALT MASTER, AVIONICS master, and all electrical system
switches are in the OFF position.
(2) Remove the upper cowl. Refer to Chapter 71, Cowls - Maintenance Practices.
(3) Disconnect the airplane 24 volt battery cables from the battery. Refer to Battery - Maintenance
Practices.
(4) Remove the cover from the power junction box.
(5) Find the orange ACU sense wire attached to the upper Battery Contactor terminal inside the
power junction box. Refer to Figure 201.
(a) Remove the nut, washer, and orange ACU sense wire ring terminal from the upper Battery
Contactor terminal.
NOTE:
(6)

The ACU sense wire is connected to Pin B in the ACU connector.

Connect the battery test harness in series with the orange ACU Sense wire and the upper Battery
Contactor terminal as shown in Figure 201.
(a) Use tape or an equivalent as electrical insulation on the bare sense wire ring terminal.
NOTE:

This will help prevent accidental electrical shorts.

(7) Connect two new 9-volt batteries to the harness.
(a) Put the 9 volt batteries in position below the power junction box as shown in Figure 201.
(8) Connect the airplane 24 volt battery cables to the battery. Refer to Battery - Maintenance
Practices.
(9) Make sure the ALT FIELD circuit breaker on the pilot's circuit breaker panel is engaged.
(10) Put the BAT and ALT MASTER switches to the ON position for 5 seconds and then return to the
OFF position.
(a) Make sure the ALT Field circuit breaker opens or the cap pops out.
(b) If the circuit breaker opens, the Over-voltage Protection circuit is operational. Continue
with step 11.
(c) If the circuit breaker does not open, do step 10 a second time.
1
Use a digital voltmeter and measure the voltage between the orange ACU sense wire
ring terminal and the power junction box ground stud.
(d) If the circuit breaker does not open the second time and the ACU sense voltage is greater
than 34 volts, the Over-voltage Protection Circuit is not operational.
1
Replace the ACU.
(e) Do step 10 again after a new ACU is installed.
(11) Engage the ALT Field circuit breaker.
(12) Disconnect the airplane 24 volt battery cables from the battery. Refer to Battery - Maintenance
Practices.
(13) Disconnect the two 9-volt batteries from the harness.
(14) Disconnect the battery test harness.
(15) Install the nut, washer, and orange ACU sense wire ring terminal to the upper Battery Contactor
terminal.
(a) Torque the terminal nut from 35 to 45 inch-pounds.
(16) Install the cover on the power junction box.
(17) Connect the airplane 24 volt battery cables to the battery. Refer to Battery - Maintenance
Practices.
(18) Install the upper cowl. Refer to Chapter 71, Cowls - Maintenance Practices.
(19) Continue with step D in this section.

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MAINTENANCE MANUAL

B

BOLT
WASHER

POWER
JUNCTION
BOX

A
EXTERNAL

A

DETAIL A
0710T1001
A0558T1001

Over-Voltage Protection Circuit Test with External Batteries
Figure 201 (Sheet 1)

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MAINTENANCE MANUAL

B6230

ALTERNATOR
CONTROL
UNIT

CIRCUIT
BREAKERS

D

D

BATTERY
CONTACT

SENSE WIRE
ROM UPPER
NTACTOR

VIEW A-A

AA0558T1007

Over-Voltage Protection Circuit Test with External Batteries
Figure 201 (Sheet 2)

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MAINTENANCE MANUAL

B6231

INSULATED
ALLIGATOR

INSULATED
ALLIGATER

BLACK LEAD WIRE
RED LEAD WIRE

LEAD WIRE (POS)
WIRE (NEG)

9 VOLT BATTERY
SNAP CONNECTOR

9 VOLT BATTERY
SNAP CONNECTOR

DETAIL B

B0558T1007

Over-Voltage Protection Circuit Test with External Batteries
Figure 201 (Sheet 3)

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MAINTENANCE MANUAL
D.

Make sure of the correct ACU functions immediately after the next engine start.
(1) Start the engine in accordance with the Pilot's Operating Handbook, Starting Engine (Using
Battery) procedure but make sure the ALT MASTER switch is in the OFF position.
(2) After the engine start and oil pressure check, set the engine RPM to idle.
(3) Make sure the Low Voltage annunciator is On.
(4) While you monitor the aircraft voltmeter, set the ALT MASTER switch to the ON position.
(a) If the voltmeter shows more than 29 volts, immediately set the ALT MASTER switch to the
OFF position and stop the engine.
NOTE:

The ACU regulation circuit is non operational. The ALT FLD circuit breaker
should open if the voltage is more than 32 volts.

1
Replace the ACU and do the Over-voltage Protection Test again.
If the voltmeter shows less than 29 volts, slowly increase the throttle to an engine speed
of 1300 RPM.
(5) If the voltmeter shows approximately 28 volts at an engine speed of 1300 RPM the ACU
regulation circuit is operational.
(6) Make sure the battery charge is shown on the aircraft battery ammeter.
(7) Make sure the LOW VOLTS annunciator is off.
(b)

4.

Alternator Control Unit Troubleshooting
A.

Complete the Alternator Control Unit Troubleshooting.
(1) The Alternator Control Unit troubleshooting is done with the Lamar TE04 MCU Test Set. The
instructions are contained in the test set. Refer to Electrical Power - General, Tools, Equipment,
and Materials.

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MAINTENANCE MANUAL
CIRCUIT BREAKER - MAINTENANCE PRACTICES
1.

General
A.

2.

The circuit breaker panel is on the left lower instrument panel, below the pilot's control wheel. The
circuit breaker panel has electrical circuit breakers, the ignition/magneto switches, the master switch,
the avionics master switch, and the light switches.

Circuit Breaker RemovaVlnstallation
A.

Remove the Circuit Breaker (Refer to Figure 201 or Figure 202).
(1) Remove the access/inspection plate (31 OAR) and disconnect the battery (UC001) cables. Refer
to Chapter 6, Access/Inspection Plates - Description and Operation.
(2) In the cockpit, remove the screws that attach the circuit breaker panel to the lower instrument
panel.
(3) Remove the screws that attach the circuit breaker cover to the circuit breaker panel.
(4) Remove the circuit breaker cover.
(5) Put a label on the applicable circuit breaker wires.
(6) Disconnect the applicable circuit breaker wires.
(7) Remove the screws and the washers that attach the bus bar to the circuit breakers.
(8) Remove the bus bar.
(9) Remove the nut that attaches the circuit breaker to the circuit breaker panel.
(10) Remove the circuit breaker.

B.

Install the Circuit Breaker (Refer to Figure 201 or Figure 202).
(1) Put the circuit breaker in the circuit breaker panel and attach the circuit breaker with the nut.
(2) Attach the bus bar to the circuit breakers with the screws and washers.
(3) Remove the labels and connect the wires to the circuit breakers.
(4) Install the circuit breaker cover assembly.
(a) Put three tie straps between the circuit breakers and the panel.
(b) Put the circuit breaker cover assembly over the circuit breakers.
(c) The flanges on the cover fit between the circuit breakers and the panel.
(d) The recessed areas in the cover must align with the screw holes in the panel.
(e) Put the main power bus wires and the circuit breaker panel assembly wire bundle out of
the left side of the cover.
(f) Attach the cover with three tie straps.
(5) Attach the circuit breaker cover to the circuit breaker panel with the screws.
(6) Put the circuit breaker panel on the lower instrument panel and attach with the screws.
(7) Connect the battery cables (UC001) and install the access/inspection plate (310AR). Refer to
Chapter 6, Access/Inspection Plates - Description and Operation.

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MAINTENANCE MANUAL

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B1218T1003
C1218T1003

PROPELLER DE-ICE
CIRCUIT BREAKER/
SWITCH (T182 ONLY)
Circuit Breaker Panel Installation
Figure 201 (Sheet 1)

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MAINTENANCE MANUAL

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AIRPLANES WITH GARMIN G1000
0710T1001
A0718T1053
B0718T1054

Circuit Breaker Panel Installation
Figure 202 (Sheet 1)

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MODEL 182/T182
MAINTENANCE MANUAL
ESSENTIAL AND CROSSFEED BUS DIODES - MAINTENANCE PRACTICES
1.

2.

3.

General
A.

Airplanes that have the Garmin G1000 avionics system have an essential bus and a crossfeed bus.
Airplanes without the Garmin G1000 avionics have only a crossfeed bus.

B.

The essential and crossfeed bus diodes are found on the circuit breaker panel. The diodes give power
to the essential and crossfeed busses from the two primary busses, and at the same time isolate the
two primary buses.

Essential and Crossfeed Bus Diode Removal/Installation
A.

Remove the essential or crossfeed bus diode. Refer to Figure 201.
(1) Remove the circuit breaker panel. Refer to Chapter 24, Circuit Breaker - Maintenance Practices.
(2) Carefully remove the heat shrinkable tubing from the diode.
(3) Remove the solder from the wire and from the diode. Refer to Model 182 Wiring Diagram Manual,
Chapter 20, Soldering - Maintenance Practices.
(4) Remove the nut and the washer from the diode.
(5) Remove the diode.

B.

Install the essential or crossfeed bus diode. Refer to Figure 201.
(1) Put the diode in position on the circuit breaker panel.
(2) Attach the diode with the nut and the washer to the circuit breaker panel.
(3) Install the heat shrinkable tubing over the wire. Refer to Model 182 Wiring Diagram Manual,
Chapter 20, Heat Shrinkable Tubing - Maintenance Practices.
(4) Add solder to attach the wire to the diode. Refer to Model 182 Wiring Diagram Manual, Chapter
20, Soldering - Maintenance Practices.
(5) Apply heat to the heat shrinkable tubing with a heat gun until the tubing fits tightly around the wire
and diode. Refer to Model 182 Wiring Diagram Manual, Chapter 20, Heat Shrinkable Tubing Maintenance Practices.
(6) Install the circuit breaker panel. Refer to Chapter 24, Circuit Breaker - Maintenance Practices.

Essential and Crossfeed Bus Diode Inspection
NOTE:

Do inspections of the essential and crossfeed bus diodes in accordance with the time limits given
in Chapter 5, Inspection Time Limits.

NOTE:

When the diodes are replaced, the inspections that follow (3A, 3B, or 3C) must be done to make
sure that all of the diodes operate correctly.

NOTE:
A.

The Lamar TE04 MCU Test Set is used as an alternative to inspections 3A, 3B, or 3C. Refer to
the Lamar TE04 MCU Test Set, instructions LI-0021 steps 4.3.A through 4.3.E.
Do an inspection of the crossfeed bus diodes. Refer to Figure 201. The inspection procedure that
follows is for power junction boxes that have primary bus fuses.
NOTE:

Airplanes 18280945 and ON, Airplanes T18208001 and ON, and Airplanes 18280001 thru
18280944 incorporating SB00-24-01 do not use fuses in the power junction box.

CAUTION: Do not remove any fuses with the MASTER BAT switch in the ON
position.
(1)
(2)
(3)
(4)
(5)
(6)
(7)

Set the MASTER BAT, TAXI LIGHT, and LAND LIGHT switches to the ON position.
Make sure that the landing light, taxi light, and oil pressure annunciator come on.
Set the MASTER BAT, TAXI LIGHT, and LAND LIGHT switches to the OFF position.
Remove the screws that attach the power junction box cover.
Remove the junction box cover.
Remove the fuse (F1). Refer to Power Junction Box - Maintenance Practices, Figure 201.
Set the MASTER BAT, TAXI LIGHT, and LAND LIGHT switches to the ON position.

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MAINTENANCE MANUAL

OO

B

DETAIL

A

C

BUS BAR

DETAIL

B

NUT
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LOCK WA

DETAIL

C

0710T1001
A0714T1041
B0718T1057
C0718T1058

Essential Bus Diode Installation
Figure 201 (Sheet 1)

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MODEL 182/T182
MAINTENANCE MANUAL

B2245

IB

DETAIL

A

AIRPLANES WITH THE
GARMIN G1000

C
(NOTE 1)

C
(NOTE 2)

DETAIL

W

B

BUS

NOTE 1: ESSENTIAL BUS DIODES
NOTE 2: CROSSFEED BUS DIODES

DETAIL C

A0718T1053A
B0718T1056
C0718T1055

Essential Bus Diode Installation
Figure 201 (Sheet 2)

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MAINTENANCE MANUAL
(8) Make sure that the landing light and oil pressure annunciator come on. If the taxi light comes
on or the oil pressure annunciator does not come on, do a test of the crossfeed bus diodes with
the diode test function of a digital multimeter to find which diodes must be replaced. Refer to
Essential and Crossfeed Bus Diode Multimeter Test.
(9) Set the MASTER BAT, TAXI LIGHT, and LAND LIGHT switches to the OFF position.
(10) Install the fuse (F1) into the power junction box.
NOTE:

If the fuse is pitted, arced, or does not fit tightly into the fuse receptacle, replace the
fuse with one of the same type. Do not replace the fuse with a fuse with thinner
blades.

(11) Remove the fuse (F2). Refer to Power Junction Box - Maintenance Practices, Figure 201.
(12) Set the MASTER BAT, TAXI LIGHT, and LAND LIGHT switches to the ON position.
(13) Make sure that the taxi light and oil pressure annunciator come on. If the landing light comes
on, or the oil pressure annunciator does not come on, do a test of the crossfeed bus diodes with
the diode test function of a digital multimeter to find which diodes must be replaced. Refer to
Essential and Crossfeed Bus Diode Multimeter Test.
(14) Set the MASTER BAT, TAXI LIGHT, and LAND LIGHT switches to the OFF position.
(15) Install the fuse (F2) into the power junction box.
NOTE:

If the fuse is pitted, arced, or does not fit tightly into the fuse receptacle, replace the
fuse with one of the same type. Do not replace the fuse with a fuse with thinner
blades.

NOTE:

If the diodes are replaced, do this test again to make sure that all the diodes operate
correctly.

(16) Install the junction box cover with the screws.
B.

Do an inspection of the crossfeed bus diodes. Refer to Figure 201. The inspection procedure that
follows is for power junction boxes that have primary bus circuit breakers.
NOTE:

The inspection procedure that follows is for airplanes without the Garmin G1000 avionics
system.

CAUTION: Do not remove bus wires from the circuit breakers with the MASTER
BAT switch in the ON position.
(1) Set the MASTER BAT, TAXI LIGHT, and LAND LIGHT switches to the ON position.
(2) Make sure that the landing light, taxi light, and oil pressure annunciator come on.
(3) Set the MASTER BAT, TAXI LIGHT, and LAND LIGHT switches to the OFF position.
(4) Remove the screws that attach the power junction box cover.
(5) Remove the power junction box cover.
(6) Remove the hex nut and the lock washer that connect the bus wire to the circuit breaker (F1).
Refer to Power Junction Box - Maintenance Practices, Figure 201.
(7) Remove the wire terminal from the F1 circuit breaker stud that has a label of AUX and isolate
the end of the bus wire.
(8) Set the MASTER BAT, TAXI LIGHT, and LAND LIGHT switches to the ON position.
(9) Make sure that the landing light and oil pressure annunciator come on. If the taxi light comes
on or the oil pressure annunciator does not come on, do a test of the crossfeed bus diodes with
the diode test function of a digital multimeter to find which diodes must be replaced. Refer to
Essential and Crossfeed Bus Diode Multimeter Test.
(10) Set the MASTER BAT, TAXI LIGHT, and LAND LIGHT switches to the OFF position.
(11) Install the bus wire to the F1 circuit breaker terminal. Use the same hex nut and the washer that
were removed.
(12) Torque the nut to between 20 and 25 inch-pounds (between 2.3 and 2.8 N-m).
(13) Remove the hex nut and the lock washer that connect the bus wire to the circuit breaker (F2).
Refer to Power Junction Box - Maintenance Practices, Figure 201.

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MAINTENANCE MANUAL
(14) Remove the wire terminal from the F2 circuit breaker stud with the label of AUX and isolate the
end of the bus wire.
(15) Set the MASTER BAT, TAXI LIGHT, and LAND LIGHT switches to the ON position.
(16) Make sure that the taxi light and the oil pressure annunciator come on. If the landing light comes
on or the oil pressure annunciator does not come on, do a test of the crossfeed bus diodes with

the diode test function of a digital multimeter to find which diodes must be replaced. Refer to
Essential and Crossfeed Bus Diode Multimeter Test.
(17) Set the MASTER BAT, TAXI LIGHT, and LAND LIGHT switches to the OFF position.
(18) Install the bus wire to the F2 circuit breaker terminal with the hex nut and the washer that were
removed. Refer to Power Junction Box - Maintenance Practices, Figure 201.
(19) Torque the nut to between 20 and 25 inch-pounds (between 2.3 and 2.8 N-m).
NOTE:

If the diodes are replaced, do this test again to make sure that all the diodes operate
correctly.

(20) Install the junction box cover with the screws.
C.

Do an inspection of the essential and crossfeed bus diodes. Refer to Figure 201. The inspection
procedure that follows is for airplanes that have the Garmin G1000 avionics system.

CAUTION: Do not remove bus wires from the circuit breakers with the MASTER
BAT switch in the ON position.
(1) Set the battery MASTER BAT, TAXI LIGHT, and LAND LIGHT switches to the ON position.
(2) Make sure that the STDBY BATT switch and the AVIONICS master switch are in the OFF
position.
(3) Make sure that the landing and taxi lights come on.
(4) Make sure that a minimum of 20 volts shows on the primary flight display (PFD) for the main
and essential bus voltmeters.
NOTE:

(5)
(6)
(7)
(8)
(9)
(10)
(11)

(12)
(13)
(14)
(15)
(16)
(17)

A minimum of 20 volts shows that there is power to the crossfeed and essential
busses. The GEA-71 must be on to show the voltage of the crossfeed bus. If there
are no red X's on the engine indicators, the GEA-71 is on.

Set the MASTER BAT, TAXI LIGHT, and LAND LIGHT switches to the OFF position.
Remove the screws that attach the power junction box cover to the power junction box.
Remove the power junction box cover.
Remove the hex nut and lock washer that connect the bus wire to the circuit breaker (F1). Refer
to Power Junction Box - Maintenance Practices, Figure 201.
Remove the wire terminal from the F1 circuit breaker stud that has a label of AUX and isolate
the end of the bus wire.
Set the battery MASTER BAT, TAXI LIGHT, and LAND LIGHT switches to the ON position.
Make sure that the landing light comes on and the main and essential bus voltages show a
minimum of 20 volts on the PFD. If the taxi light comes on, the main and essential bus voltages
do not show a minimum of 20 volts, or the PFD does not come on, do a test of the essential
and crossfeed bus diodes with the diode test function of a digital multimeter to find which diodes
must be replaced. Refer to Essential and Crossfeed Bus Diode Multimeter Test.
Set the MASTER BAT, TAXI LIGHT, and LAND LIGHT switches to the OFF position.
Install the bus wire to the circuit breaker (F1) terminal. Use the same hex nut and washer that
was removed.
Torque the nut to between 20 and 25 inch-pounds (between 2.26 and 2.82 N-m).
Remove the hex nut and lock washer that connects the bus wire to circuit breaker (F2). Refer
to Power Junction Box - Maintenance Practices, Figure 201.
Remove the wire terminal from the F2 circuit breaker stud with the label of AUX and isolate the
end of the bus wire.
Set the battery MASTER BAT, TAXI LIGHT, and LAND LIGHT switches to the ON position.

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MAINTENANCE MANUAL
(18) Make sure that the taxi light comes on and the main and essential bus voltages show a minimum
of 20 volts on the PFD. If the landing light comes on, or the main and essential bus voltages do
not show a minimum of 20 volts, or if the PFD does not come on, do a test of the essential and
crossfeed bus diodes with the diode test function of a digital multimeter to find which diodes
must be replaced. Refer to Essential and Crossfeed Bus Diode Multimeter Test.
(19) Set the MASTER BAT, TAXI LIGHT, and LAND LIGHT switches to the OFF position.
(20) Install the bus wire to the circuit breaker (F2) terminal. Use the same hex nut and washer that
was removed. Refer to Power Junction Box - Maintenance Practices, Figure 201.
(21) Torque the nut to between 20 and 25 inch-pounds (between 2.26 and 2.82 N-m).
NOTE:

If the diodes are replaced, do this test again to make sure that all the new diodes
operate correctly.

(22) Install the power junction box cover with the screws.
4.

Essential and Crossfeed Bus Diode Multimeter Test
NOTE:

Do the essential or crossfeed bus diode inspection procedure applicable to your airplane before
the test that follows is done. Refer to Essential and Crossfeed Bus Diode Inspection.

NOTE:

The test that follows must be done only if required by the essential or crossfeed bus diode
inspections. The replacement of all the essential and crossfeed diodes can be done as an
alternative to the test procedure that follows.

A.

Do a test of the essential and crossfeed bus diodes.
(1) Remove the circuit breaker panel to get access to the essential and crossfeed bus diodes. Refer
to Circuit Breaker - Maintenance Practices.
(2) Remove the nut and washer from each diode. Refer to Figure 201.
(3) Isolate the diode from the bus bar on the circuit breaker panel. Do not remove the heat shrinkable
tubing or the wire from the diode.
(4) Do a test of each diode with the diode test function of a Fluke 75, 77, or 87 digital multimeter (or
equivalent digital multimeter with a diode test function).
(a) Connect the negative (-), or common lead of the meter to the threaded part of the diode
and the positive (+) lead of the meter to the opposite end of the wire to which the diode is
soldered. If the diode operates correctly, it will be conductive of an electric current and the
meter will show the forward voltage drop of the diode (approximately 0.2 to 0.8 volts).
(b) Interchange the meter leads. Connect the positive (+) lead of the meter to the threaded
part of the diode and the negative (-), or common lead of the meter to the opposite end
of the wire to which the diode is soldered. If the diode operates correctly, it will not be
conductive of an electric current and the meter will give an open circuit indication. This
indication on the meter will be the same as if the leads are not connected.
(c) Replace each diode that does not give a satisfactory indication during the multimeter test.
Refer to Essential and Crossfeed Bus Diode Removal/Installation.
(5) Install the diodes that give a satisfactory indication during the multimeter test. Refer to Essential
and Crossfeed Bus Diode Removal/Installation.
NOTE:
(6)

When the diodes are replaced, do the applicable essential and crossfeed diode
inspection (3A, 3B, or 3C) again to make sure that all the diodes operate correctly.

Install the circuit breaker panel. Refer to Circuit Breaker - Maintenance Practices.

24-61-01
© Cessna Aircraft Company

Page 206
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
ELECTRICAL LOAD ANALYSIS - DESCRIPTION AND OPERATION
1.

General
A.

The tables give an electrical load analysis of some of the components used on the airplane.

Table 1. Components on all airplanes
Component

Draw at 24.0 VDC
(Amperes)

Draw at 28.0 VDC
(Amperes)

Landing Light (4596 Lamp)

7.65

8.93

Landing Light (4591 Lamp)

3.06

3.57

Landing Light (35 Watt HID)

1.65

1.41

Taxi Light (4587 Lamp)

7.65

8.93

Taxi Light (4626 Lamp)

4.59

5.36

Taxi Light (35 Watt HID)

1.65

1.41

Navigation Lights

2.65

3.1

Wing Anti-collision Lights (average
value) (Qty. 2)

1.98

1.7

Beacon Light (peak value)

1.07

1.25

Under Wing Courtesy Lights (Qty. 2)

0.98

1.14

Pilot Overhead Light (1864 Lamp)

0.14

0.16

Pilot Overhead Light (LED Lamp)

0.02

0.02

Copilot Overhead Light (1864 Lamp)

0.14

0.16

Copilot Overhead Light (LED Lamp)

0.02

0.02

Passenger Overhead Light (1864
Lamp)

0.14

0.16

Passenger Overhead Light (LED
Lamp)

0.02

0.02

Map Light

0.08

0.09

Instrument Light (2 and 3 inch round)
(Each)

0.02

0.02

Oxygen Control/Gauge Light

0.02

0.02

Pedestal Lights (Qty. 2)

0.08

0.10

Flap Motor

2.06

2.4

Fuel Pump

2.74

3.2

Pitot Heat

3.33

3.89

Stall Warning Heat

1.46

1.7

Stall Warning Horn

0.4

0.35

Prop Heat

13.3

15.5

12V Cabin Power Converter (Peak
10A out)

6.33

5.42

24-70-00
©Cessna Aircraft Company

Page 1
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
Table 1. Components on all airplanes (continued)
Draw at 24.0 VDC
(Amperes)

Draw at 28.0 VDC
(Amperes)

Hourmeter

0.01

0.02

Battery Relay Coil

0.29

0.33

Start Relay Coil

0.85

N/A

Alternator Relay Coil

0.29

0.33

Alternator Field and ACU Power
(Maximum)

1.63

1.9

ACU Bus Sense

0.02

0.02

Start Motor

100

N/A

Autopilot Computer (KAP 140)

0.58

0.5

Pitch Servo & Clutch

0.58

0.5

Pitch Trim Servo & Clutch

0.58

0.5

Roll Servo & Clutch

0.53

0.45

Turn Coordinator

0.27

0.33

Stormscope (WX-500)

0.93

0.8

ADF Receiver (KR 87)

0.6

0.52

Component

Table 2. Components used only on airplanes that do not have Garmin G1000 installation.
Draw at
24 VDC
(Amperes)

Component

Draw at 28 VDC
(Amperes)

Glareshield Light (Fluorescent)

0.86

1

Glareshield Light (LED)

0.17

0.2

Radio Lights

0.17

0.2

Annunciator Panel (All annunciations on)

0.35

0.3

Avionics Fan

0.43

0.5

Engine and Fuel Gauges

0.38

0.45

Audio Panel (KMA-26) (Maximum)

1.5

1.29

Audio Panel (KMA-28) (Maximum)

1.5

1.29

MFD (KMD-550)

0.93

0.8

GPS (KLN 89/89B)

1.45

1.25

GPS (KLN 94)

1.4

1.2

Transponder (KT 73) (Maximum)

1.07

1.25

Transponder (KT 76) (Maximum)

0.6

0.7

Altitude Encoder (SSD120)

0.2

0.23

HSI (KCS 55A) (Maximum)

1.46

1.25

24-70-00
© Cessna Aircraft Company

Page 2
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
Table 2. Components used only on airplanes that do not have Garmin G1000 installation. (continued)
Component

Draw at
24 VDC
(Amperes)

#1 Nav/Comm (KX 155A) (Receive)

0.8

0.69

6

6

0.8

0.69

6

6

#1 Nav/Comm (KX 155A) (Transmit) (Maximum)
#2 Nav/Comm (KX 165A) (Receive)

Draw at 28 VDC
(Amperes)

#2 Nav/Comm (KX 165A) (Transmit) (Maximum)
Table 3. Components used only on airplanes that have Garmin G1000 installation.
Component

Draw at
24 VDC
(Amperes)

Draw at 28 VDC
(Amperes)

Circuit Breaker Panel Light (LED)

0.06

0.07

Switch Panel Light (LED)

0.07

0.08

Avionics Panel Lights (MFD, PFD, A/P)

0.17

0.2

Throttle/Flap Panel Light (LED)

0.07

0.08

Standby Battery Main Volt Sense

0.001

0.001

Standby Battery Controller

0.007

0.008

2

N/A

Main Bus Voltage Sense

0.001

0.001

Essential Bus Voltage Sense

0.001

0.001

Deck Skin Fan

0.28

0.33

PFD Fan

0.08

0.09

MFD Fan

0.08

0.09

#1 Comm (GIA 63) (Receive)

0.22

0.19

#1 Comm (GIA 63) (Transmit) (VSWR 3)

4.96

4.16

#2 Comm (GIA 63) (Receive)

0.22

0.19

#2 Comm (GIA 63) (Transmit) (VSWR 3)

4.96

4.16

#1 Nav (GIA 63)

0.94

0.8

#2 Nav (GIA 63)

0.94

0.8

PFD (GDU 1040)

1.46

1.25

MFD (GDU 1040)

1.46

1.25

AHRS (GRS 77)

0.29

0.25

Air Data Computer (GDC 74)

0.25

0.21

Engine/Airframe Unit (GEA 71)

0.2

0.17

Transponder (GTX 33)

1.17

1

Standby Battery Test

24-70-00
© Cessna Aircraft Company

Page 3
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
Table 3. Components used only on airplanes that have Garmin G1000 installation. (continued)
Component

Draw at
24 VDC
(Amperes)

Draw at 28 VDC
(/ Amperes)

Audio Panel (GMA 1347)

1.58

1.36

FIS (GDL 69A)

0.42

0.36

TAS (KTA 870)

1.34

1.15

24-70-00
© Cessna Aircraft Company

Page 4
Jul 3/2006

CHAPTER

EQUIPMENT/
FURNISHINGS

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82

MAINTENANCE MANUAL

LIST OF EFFECTIVE PAGES
CHAPTER-SECTION-SUBJECT

PAGE

DATE

Page 1
Pages 201 -204

Janl1/2007

25-10-00
25-10-04

Pages 201 -202

April 1/2002

25-11-00

Pages 201-203

Jul 3/2006

25-11-10

Pages 201 -208

Jan 1/2007

25-2 1-00

Pages 201-202

Jul 3/2006

25-22-00

April 1/2002

25-50-00

Pages 201 -205
Pages 201-202

April 1/2002

25-60-00

Pages 201 -207

Janl1/2007

25-60-01

Pages 201-205
Pages 601 -602

Janl1/2007
Jan 1/2007

Page 1
Page 101

Janl1/2007

25-60-02

Janl1/2007

25-60-02

Pages 201 -205

Janl1/2007

25-60-02

Pages 601 -606
Pages 201 -202

Jan-1/2007

25-60-10
25-80-00

Pages 201-203

April 1/2002

25-Title
25-List of Effective Pages
25-Record of Temporary Revisions
25-Table of Contents
25-00-00

25-60-01
25-60-02

©Cessna Aircraft Company

Janl1/2007

Janl1/2007

25 - LIST OF EFFECTIVE PAGES

Page 1 of 1
Janl1/2007

RECORD OF TEMPORARY REVISIONS
Temporary Revision
Number

Page Number

Issue Date

By

Date Removed

By

CESSNA AIRCRAFT COMPANY

MODEL 182/T1 82
MAINTENANCE MANUAL

CONTENTS
EQUIPMENT/FURNISHING - GENERAL ......................
Scope....................................
Tools, Equipment and Materials........................
Definition ..................................

25-00-00
25-00-00
25-00-00
25-00-00

Page
Page
Page
Page

1
1
1
1

FRONT SEATS AND RAILS - MAINTENANCE PRACTICES .............
General...................................
Seat Removal/installation...........................
Seat Rail Removal/Installation.........................

25-1 0-00
25-1 0-00
25-10-00
25-10-00

MAP COMPARTMENT - MAINTENANCE PRACTICES................
General...................................
Map Compartment Removal/installation ....................

25-10-04 Page 201
25-10-04 Page 201
25-10-04 Page 201

SEAT BELTS/RESTRAINTS - MAINTENANCE PRACTICES .............
General...................................
Seat Belt/Restraints Removal and Installation..................
Restraint Testing...............................

25-11 -00
25-11 -00
25-11 -00
25-1 1-00

Page
Page
Page
Page

INFLATABLE RESTRAINTS - MAINTENANCE PRACTICES Airplanes with AMSAFE
Inflatable Restraint System.............................
General ...................................
Inflatable Restraint Component Cleaning....................
Inflatable Restraint - Inspection ........................
Storage of Spares ..............................
AMVSAFE 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 ....................
General...................................
Rear Seat Removal/Installation ........................

25-11 -10
25-11 -10
25-11 -10
25-11 -10
25-1 1-1 0
25-1 1-1 0
25-11 -10
25-11 -10
25-11 -10
25-21 -00
25-21 -00
25-21 -00

Page 201
Page 201
Page 201
Page 202
Page 202
Page 202
Page 203
Page 207
Page 208
Page 201
Page 201
Page 201

25-22-00
25-22-00
25-22-00
25-22-00

Page 201
Page 201
Page 201
Page 201

INTERIOR UPHOLSTERY - MAINTENANCE PRACTICES..............
General...................................
Cabin Panels Removal/installation.......................
Door Panels and Carpet Removal/Installation..................
CARGO TIE-DOWNS - MAINTENANCE PRACTICES ................
General...................................
POINTER EMERGENCY LOCATOR TRANSMITTER - MAINTENANCE PRACTICES..
General...................................
Pointer ELT Removal/installation .......................
Pointer ELT Remote Switch Removal/Installation ................
ELT Antenna Removal/Installation (integral Base with Coax Cable)........
ELT Whip Antenna Removal/installation ....................
Pointer ELT Battery Pack Removal/Installation .................
Pointer ELT Operational Test .........................
ARTEX C406-N EMERGENCY LOCATOR TRANSMITTER - MAINTENANCE
PRACTICES ...................................
General...................................
Artex C406-N ELT Removal/installation ....................
Artex C406-N ELT Remote Switch Removal/Installation.............
Artex C406-N ELT Rod Antenna Removal/installation..............
Artex C406-N Buzzer Removal/Installation...................

© Cessna Aircraft Company

Page
Page
Page
Page

201
201
201
201

201
201
201
201

25-50-00 Page 201
25-50-00 Page 201
25-60-00
25-60-00
25-60-00
25-60-00
25-60-00
25-60-00
25-60-00
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Page
Page
Page
Page
Page
Page
Page
Page

201
201
201
204
204
205
205
206

25-60-01 Page 201
25-60-01 Page 201
25-60-01 Page 201
25-60-0 1 Page 201
25-60-01 Page 204
25-60-01 Page 204

25 - CONTENTS

Page 1of 2
Janl1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
ARTEX C406-N EMERGENCY LOCATOR TRANSMITTER
General...................................
Artex C406-N ELT Functional Test.......................

-

INSPECTION/CHECK

ARTEX ME406 EMERGENCY LOCATOR TRANSMITTER SYSTEM
AND OPERATION ................................
General...................................
Description .................................
Operation..................................

-

25-60-01 Page 601
25-60-01 Page 601
25-60-01 Page 601

...

DESCRIPTION
25-60-02
25-60-02
25-60-02
25-60-02

LOCATOR
TRANSMITTER
SYSTEM
ME406
EMERGENCY
ARTEX
TROUBLESHOOTING ..............................
General...................................
Tools and Equipment.............................
ME406 Emergency Locator Transmitter Self Test Preparation ..........

1
1
1
1

-

ARTEX ME406 EMERGENCY LOCATOR TRANSMITTER SYSTEM - MAINTENANCE
PRACTICES ...................................
General...................................
Emergency Locator Transmitter (ELT) Removal/Installation ...........
ELT Buzzer Removal/installation .......................
Remote Switch Removal/Installation......................
ELT Antenna Removal/Installation.......................
ARTEX ME406 EMERGENCY LOCATOR TRANSMITTER (ELT) SYSTEM
INSPECTION/CHECK...............................
General...................................
Tools and Equipment.............................
Artex ME406 Emergency Locator Transmitter (ELT) Inspection..........
Artex ME406 Emergency Locator Functional Test................

Page
Page
Page
Page

25-60-02
25-60-02
25-60-02
25-60-02

Page
Page
Page
Page

101
101
101
101

25-60-02
25-60-02
25-60-02
25-60-02
25-60-02
25-60-02

Page
Page
Page
Page
Page
Page

201
201
201
201
204
204

25-60-02
25-60-02
25-60-02
25-60-02
25-60-02

Page
Page
Page
Page
Page

601
601
601
601
602

-

CARBON MONOXIDE DETECTOR - MAINTENANCE PRACTICES..........
General...................................
Carbon Monoxide Detector Removal/Installation ................

25-60-1 0 Page 201
25-60-1 0 Page 201
25-60-1 0 Page 201

SOUNDPROOFING AND INSULATION
General...................................

25-80-00 Page 201
25-80-00 Page 201

-

MAINTENANCE PRACTICES........

25 - CONTENTS
© Cessna Aircraft Company

Page 2 of 2
Janl1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182

MAINTENANCE MANUAL
EQUIPMENT/FURNISHING

-

GENERAL

1.Scope
A. This chapter describes the interior equipment and furnishings used throughout the airplane. Also
included in this chapter is information on the emergency locator transmitter (PT900) and the carbon
monoxide detector.
2.

Tools, Equipment and Materials
NOTE:

I

Equivalent substitutes may be used for the following listed items:

NAME

NUMBER

MANUFACTURER

USE

Aeroflex
Communications
Test Set

IFR 4000

Aeroflex, Wichita Division
10200 West York Street
Wichita, KS 67215-8935

To complete the
functional test of the Artex
ELT ME406 Emergency
Locator Transmitter.

Spray Adhesive

Airtac 2

Advanced Materials Group
2542 East Del Amo Blvd.
Box 6207
Carson, CA 90745

To adhere soundproofing
and insulation to fuselage
structure.

V23 System
Diagnostic Tool

508668-201

Cessna Aircraft Co.
Cessna Parts Distribution
Department 701, CPD 2,
5800 East Pawnee Road
Wichita, KS 67218-5590

Test of the inflatable
restraint system.

SARSAT Beacon
Test Set

453-0131

Artex
P0 Box 1270
Canby, OR 97013

To complete the
functional test of the
Artex ELT.

30-dB Attenuator
3.

To test the ELT.

Definition
A. The 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 Flight Compartment covers those items installed in the cabin area, including
seats, seat belts, carpets and interior panels.
(2) The section on emergency equipment covers the emergency locator transmitter (PT900)
installed behind the aft baggage compartment. It also covers the carbon monoxide detector
installed forward of the instrument panel on airplanes that are equipped with Garmin G 1000.
(3) The section on soundproofing and insulation covers the material used to deaden sound
throughout the airplane.

©D
Cessna Aircraft Company

25-00-04J

Pagel1
Janl1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/T1 82
MAINTENANCE MANUAL
FRONT SEATS AND RAILS

-

MAINTENANCE PRACTICES

1.General
A. This maintenance practices section covers removal and installation for the front seats and seat rails.
For removal/installation of seat belts and harnesses, refer to Seat Belts/Restraints - Maintenance
Practices. For removal/installation of the rear seats, refer to Rear Seat - Maintenance Practices.

WARNING: If the airplane has AMSAFE inflatable restraints, do not do
maintenance on the crew seats, seat rails, seat belts, or shoulder
harnesses until you first look at and obey all applicable precautions
and instructions supplied in AMSAFE publications and this
maintenance manual. If you do not obey these instructions and
safety precautions, damage to equipment and harm to personnel
can occur.
B.

2.

If your airplane has the AMVSAFE inflatable restraint system, do not do maintenance on the seats
or the seat restraint system unless you first obey all applicable precautions and instructions in
the E508804 Supplemental Amsafe Maintenance Manual and this Maintenance Manual. Refer to
Inflatable Restraint System - Maintenance Practices.

Seat Removal/installation
A. Seat Removal (Refer to Figure 201).

WARNING: If the airplane has AMSAFE inflatable restraints, do not remove
seats with the seat belts buckled or the EMA connected. Damage
can occur to the system and an accidental deployment of the
system can cause injury.

B.

(1) Disarm the AMVSAFE Inflatable Restraints. Refer to AMVSAFE Inflatable Restraint Disarm/Arm.
(2) Remove the seat stops from the front and aft of the two seat tracks.
(3) Unlatch the seat from the seat track and move the seat forward on the seat track until the forward
roller clears the seat track.
(4) Move the seat aft on the seat track until the aft rollers clear the seat track.
(5) Remove the seat from the airplane.
Seat Installation (Refer to Figure 201).
(1) Put the aft roller of the seat in position on the seat track.
(2) Move the seat forward on the seat track until you can install the front roller on the seat track.

WARNING: Make sure the seat stops are set correctly. Incorrectly installed
seat stops can let the seat move during flight, with the result
of serious injury or death.
(3)
(4)
(5)
(6)
3.

Install the seat stops to the front and the rear of the seat track.
Make sure that the seat stops are installed correctly.
Do a test of the seat through the full range of motion to make sure of the correct operation.
Arm the AMVSAFE Inflatable Restraints. Refer to AMVSAFE Inflatable Restraint Disarm/Arm.

Seat Rail Removal/installation
A. Seat Rail Removal (Refer to Figure 202).
(1) Remove the bolts that attach the seat rails to the fuselage.
B. Seat Rails Installation (Refer to Figure 202).
(1) Install the seat rails to the fuselage with the bolts.

© Cessna Aircraft Company

25-1 0-00

Page 201
Janl1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182ffT182
MAINTENANCE MANUAL

0

LOCK
ASSEMBLY

BASE

DETAIL A

0710T1001
A0519T1O36

Seat Installation
Figure 201 (Sheet 1)

25-1 0-00
©Cessna Aircraft Company

Page 202
Janl1/2007

CESSNA AIRCRAFT COMPANY

MODEL 1821T182

MAINTENANCE MANUAL

CYLINDER
LOCK

BOLT

DETAIL

E
WASHERS

WASHERS

BUSHING

kRD
-IALVES

BUSHING

BUSHING

DETAIL

D

DETAIL

AFT FOOT ASSEMBLY

C

FORWARD FOOT ASSEMBLY

0710T1001
A0519T 1036
B0519T 1037
C0519T1038
DOS519T1039
E051 1T1001

Seat Installation
Figure 201 (Sheet 2)

25-1 0-00
©Cessna Aircraft Company

Page 203
Janl1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182
MAINTENANCE MANUAL

S

81 148

FLOORBOARD

RAIL

BOLT
SPACER

WARNING: IT IS EXTREMELY IMPORTANT THAT PILOT'S SEAT STOPS ARE INSTALLED,
SINCE ACCELERATION AND DECELERATION COULD POSSIBLY PERMIT SEAT
TO BECOME DISENGAGED FROM SEAT RAILS AND CREATE A HAZARDOUS
SITUATION, ESPECIALLY DURING TAKEOFF AND LANDING.

051 1TIO01

Seat Stop Installation
Figure 202 (Sheet 1)

25-1 0-00
C Cessna Aircraft Company

Page 204
Janl1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
MAP COMPARTMENT - MAINTENANCE PRACTICES
1.

General
A.

2.

This maintenance practices section consists of removal and installation of the map compartment.

Map Compartment Removal/Installation
A.

Remove Map Compartment (Refer to Figure 201).
(1) Remove interior screws securing map compartment to instrument panel structure.

B.

Install Map Compartment (Refer to Figure 201).
(1) Place map compartment in position and secure to instrument panel structure using screws.

25-10-04
©Cessna Aircraft Company

Page 201
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

D

::

4

A

SCREW
-F
I

1*

0_

*

VIEW

A-A

LATCH
I

I~

DOOR

HINGE
ASSEMBLY
I--

LA

1+

+

+

+

~ I

r-<

=-

DETAIL

J

A

VIEW LOOKING FWD
0710T1001
A0519T3003

Map Compartment Installation
Figure 201 (Sheet 1)

25-10-04
© Cessna Aircraft Company

Page 202
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
SEAT BELTS/RESTRAINTS - MAINTENANCE PRACTICES
1.

General
A.

The airplane has inertia style reels which let the user lean forward, but will lock in position with sudden
movement. The seat belts retract and stow in position when not in use. This maintenance practices
section covers removal and installation for restraints used in both the front and rear positions.

B.

The restraint system components are non-repairable field items. If any component in the restraint
system is not operating correctly, the system must be replaced.

WARNING: If the airplane has AMSAFE inflatable restraints, do not do
maintenance on the seat belts until you look at and obey all
applicable precautions and instructions supplied in AMSAFE
publications and this Maintenance Manual. If you do not obey
and follow these instructions and safety precautions, damage to
equipment and harm to personnel can occur.
C.

2.

If your airplane has the AMSAFE inflatable restraint system, do not do maintenance on the seats
or the seat restraint system unless you first obey all applicable precautions and instructions in
the E508804 Supplemental Amsafe Maintenance Manual and this Maintenance Manual. Refer to
Inflatable Restraint System - Maintenance Practices.

Seat Belt/Restraints Removal and Installation
NOTE:

3.

The seat belt/restraint assembly removal/installation is typical for restraints in all locations.

A.

Pilot's and Copilot's Seat Belt/Restraint Removal (Refer to Figure 201).
(1) Remove the access cover on the overhead console to get access to the restraint inertia reel
assemblies.
(2) Remove the nuts, bolts, and washers that attach the inertia reel assemblies to the bracket
assembly.
(3) Remove the nuts, washers, bolts, and spacers that attach the restraint assemblies to the seats.

B.

Pilot's and Copilot's Seat Belt/Restraint Installation (Refer to Figure 201).
(1) Attach the restraint inertia reel assemblies to the bracket assembly above the overhead console
with the bolts, washers, and nuts.
(2) Install the access cover on the overhead console.
(3) Attach the restraint assemblies to the seats with the bolts, washers, spacers, and nuts.
(4) Do a check of the system for correct installation and operation.

C.

Bench Seat Restraint Removal (Refer to Figure 201).
(1) Remove the bolt and the washer that attach the seat restraint inertia reel to the aft cabin structure.
(2) Remove the bolts, washers, and spacers that attach the restraint inertia reels to the seat frame.

D.

Bench Seat Restraint Installation (Refer to Figure 201).
(1) Attach the restraint inertia reels to the seat frame with the spacers, washers, and bolts.
(2) Attach the restraint inertia reels to the aft cabin structure with the washers and the bolts.

Restraint Testing
A.

Inspect the restraint system in accordance with the time intervals set forth in Chapter 5, Inspection
Time Limits. In addition to these scheduled inspections, the restraint assemblies have life limits. Refer
to Chapter 5, Component Time Limits.

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MAINTENANCE MANUAL

B

RESTRAINT
ASSEMBLY

ANTICHAFE
PLATE

BRACKET
ASSEMBLY
WASHER

D

ER

BOLT
BOLT
NUT

DETAIL

B

WASHER

DETAIL C
Y
NUT

DETAIL A
5
8

WASHERS

DETAIL U

C0519T1047
D05 19T1047

Seat Belts and Restraints Installation
Figure 201 (Sheet 1)

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MAINTENANCE MANUAL
B1151

BOLT
WASHER
BUSHING
ASHERS

SEA
FRA

F

DETAIL H

G

H
DETAIL

E

INTERTIA
REEL
ASSEMBLY

SPACER

FLAT
WASHER

INTERTIA
REEL
ASSEMBLY

BOLT
BOLT

DETAIL

BOLT
WASH

WASHER

G

DETAIL F

E0719T1009
F0519T1049
G0519T1049
H0519T1049

Seat Belts and Restraints Installation
Figure 201 (Sheet 2)

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MAINTENANCE MANUAL
INFLATABLE RESTRAINTS - MAINTENANCE PRACTICES
Airplanes with AMSAFE Inflatable Restraint System
1.General
A. This section gives maintenance information for the AMVSAFE Aviation Inflatable Restraint (AAIR). The
AAIR is a self-contained, modular, three-point restraint system that protects occupants from headimpact injury during an accident. The AAIR system has four core components: the air bag assembly,
the inflator assembly, the electronics module assembly (EMVA), and the cable interface assembly.

WARNING: Do not try to open the inflator assembly. Do not apply an electric
current to the electronics connection. The inflator assembly is
a stored, gas/energetic material device and can cause injury if
accidentally deployed.
2.

Inflatable Restraint Component Cleaning
A. AMVSAFE recommends that the AAIR components be cleaned on a regular (annual) basis. Buildup of
dirt and unwanted material can cause problems with system operation, decrease the life of the system,
and cause corrosion of the metal parts in the system. Clean the belt assembly, hoses, cables, inflation
device/cap assembly, and the EMA.

CAUTION: Use care to keep contamination and cleaning agents away from the
hardware assemblies.
CAUTION: Do not let any part of the AAIR soak in any solution. This can cause
damage to the AAIR system. Do not use too much water when you
clean the AAIR parts. Too much water can cause damage to the internal
components and cause them to be unserviceable.
CAUTION: Only use sufficient cleaning agent to make minimal suds. Excess soap
must be removed before the part is installed in the system.
CAUTION: Do not dry the belt assembly in sunlight or near any source of heat. Do
not dry clean the belt assembly. Do not put the belt assembly fully into
water.
CAUTION: Keep the isopropyl alcohol away from the webbing, air bag cover, and
the gas hose material.
CAUTION: Do not use soap or water on metal parts.
(1) Clean non-metallic parts with warm water and a household soap/laundry detergent and a moist
cloth.
(2) Flush the parts with clear water on a clean cloth.
(3) Use a soft brush, and cold soapy solution to clean the webbing, air bag cover, and gas hose by
hand. Use a household liquid soap or detergent
(4) Let the belt assembly dry by air.
(5) Clean all spacers, washers, nuts, and bolts with a lint-free cloth and isopropyl alcohol.
(6) Cover the cable opening into the EMVA with pieces of cloth. Clean the inflator and cables by hand
with a lint-free cloth and a cold water and mild soap solution.

© Cessna Aircraft Company

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MODEL 182/T182
MAINTENANCE MANUAL

3.

Inflatable Restraint
A.

4.

-

Inspection

Do an inspection of the AAIR system parts.
(1) Air bag assembly.
(a) Make sure that the attachments are tightly connected.
(b) Do a visual inspection for dirt, oil, grease, or other unwanted material.
(c) Do a check for wear on the edges of the belt.
(d) Do a check for damage of the stitching or fabric threads.
(e). Do a check for holes or wear on the air bag cover.
(f) Do a check of the end fittings, buckle, and connector for cracks, dents, or corrosion.
(2) Inflator hose.
(a) Do a check for frayed edges, wear, or tears.
(3) Cable interface assembly.
(a) Make sure that all attachments are tightly connected.
(4) Inflator assembly.
(a) Do a check for loose mounting hardware.
(b) Do a check of the hose connection.
(c) Do a check of the electrical connection.
(5) Electronics module assembly (EMA).
(a) Do a check for loose connections and mounting hardware.

Storage of Spares
A.

Inflator Assembly.
NOTE:

The maximum continuous storage time for the inflator assembly is seven years from the
date of manufacture. After seven years, send the inflator assembly to AMSAFE Aviation
for inspection and repair.

(1) Keep the inflator assembly in a cool and dry area. The inflator assembly must be kept at a
temperature between -220 F and 131 OF (-30 0 C and 550 C).
(2) Keep the inflator assembly away from sunlight, dust, moisture, and other contamination.
(3) Keep the inflator assembly away from high electromagnetic, radio frequency, and electrostatic
environments.
(4) Obey all local storage regulations.
B.

Electronics Module Assembly (EMA).
NOTE:

The maximum continuous storage time for the EMA is seven years from the date of
manufacture. After seven years, send the EMA to AMSAFE Aviation for inspection and
repair.

(1) Keep the EMA assembly in a cool and dry area. The EMA assembly must be kept at a
temperature between -220 F and 131 OF (-30OC and 550C).
(2) Keep the EMA away from sunlight, dust, moisture, and other contamination.
(3) Keep the EMA away from high electromagnetic, radio frequency, and electrostatic environments.
(4) Obey all local storage regulations.
C.

I5.
*
*

Air Bag Assembly.
(1) Keep the air bag assembly in a cool and dry area. The air bag assembly must be kept at a
temperature between -220 F and 131 OF (-30 0C and 550C).
(2) Keep the air bag assembly away from sunlight, dust, moisture, and other contamination.

AMVSAFE Inflatable Restraint Disarm/Arm
A.Disarm the AMSAFE Inflatable Restraints.
A.(1) Make sure all seat belts are unbuckled.
~~(2) Find the end-release connector at the seat base.
~~(3) Remove the tie straps that attach the cable and end-release connector.

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I

B.

6.

(4) Disconnect the end-release connector to disable the inflatable restraint.
Arm the AMSAFE Inflatable Restraints.

~~(1)Connect the end-release connector.

(2) Attach the cable and end-release connector to the seat frame with tie wraps.
Inflatable Restraint

-

Removalllnstallation

WARNING: Keep all magnetic fields away from the EMA during the removal and
installation procedure. Accidental deployment of the system can cause
injury.
A.

Restraint System Removal (Refer to Figure 201).

WARNING: Do not remove seats from the airplane with the seat belts buckled
or the electronic module assembly (EMVA) connected. Damage can
occur to the system, and accidental deployment of the system can
cause injury.
WARNING: Do not connect the EMA to the cable interface assembly unless the
EMA is mounted to the airplane structure.
*

~~(1)

Disarm the AMSAFE inflatable restraints. Refer to AMSAFE Inflatable Restraint Disarm/Arm.
(2) Disconnect the squib connector from the inflator assembly.
(3) Disconnect the gas hose from the inflator assembly.
NOTE:

The gas hose barb has a layer of Loctite and is tightly attached to the fitting. Use
soft-grip channel-lock type pliers to hold the barb while you disconnect the hose

(4) Loosen the clamps on the inflator assembly mounting bracket.
(5) Remove the inflator assembly from the mounting bracket.
(6) Put shipping caps on the inflator hose connector fitting (Refer to Table 201).
Table 201. Torque Values and Tool Sizes
PART DESCRIPTION
Inflator Shipping Cap
Hose Connection to
the Inflator

RELATED
SUBASSEMBLY
Inflator Assembly
SAA/Inflator Assembly

TOOL AND SIZE
Torque Wrench (in.
Lb. type)
Torque Wrench (In.
Lb. type)

TORQUE (IN. LBS.)
5

-10

110

-

130

(7) Remove the inertia reel (three-point air bag belt) from the airplane. Refer to Chapter 25, Seat
Belts/Restraints- Maintenance Practices.
(8) Remove the end-release buckle assembly from the airplane. Refer to Chapter 25, Seat Belts/
Restraints - Maintenance Practices.
(9) Disconnect the cable interface assembly from the EMA.
(a) Push down on the locking clip on the EMA connector and pull on the connector.
(10) Remove the cable interface assembly from the airplane.
(11) Remove the EMA from the aircraft.
(a) Remove the nuts, washers and bolts that attach the EMA to the floorboard.
(b) Carefully remove the EMA from the aircraft.

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MODEL 182ffT182
MAINTENANCE MANUAL

t8

A
SEAT BACK

rC

BUSHING
BOLT

DETAIL
WASHER

WA~c

A

SEAT BACK

G
IOLT

TIE S
MOUNTIN
BRACKET
INFLATOR
HOSE (TO AIR
BAG BELT)

INFLATOF
ASSEIVBL

DETAIL

B

ND-RELEASE
;ONN ECTOR
-ECTRONICS MODULE
MBLY (EMVA)
!BOARD

DETAIL

0710T1 001
A051 9T10014
B071 9T1056
G051ST1 074

C

AMVSAFE Aviation Inflatable Restraint System
Figure 201 (Sheet 1)

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MODEL 182/Ti 82
MAINTENANCE MANUAL

B3949

INFLA
HOSE

H

HER
4JUT

BOLT

E

WASHER

DIETAIL
FO CREW SEATS

E

CABLE INTERFACE
I

I-RONICS
JLE

G

TIE STRAP

(EM

DETAIL

D
DIAGNOSTIC
CONNECTOR
END

5qfll lip

CONNEC

INFLATOR
HOSE

-

RELEASE

TO INFLATOR
ASSEMBLY

UL

INFLATOR
ASSEMBLY

F

TO
CABLE INTERFACE
ASSEMBLY
INFLATOR
ASSEMBLY
END

-

INFLATOR HOSE
(TO AIR BAG BELT)

F

CONNE'
I
UUNNEW IH

STRAP

DETAILIG

SQUIB CONNECTOR

D071 9T1 009
E051 4T1049
F0719T1039
G0514T1 050

AMVSAFE Aviation Inflatable Restraint System
Figure 201 (Sheet 2)

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MODEL 1821T182

MAINTENANCE MANUAL

B6062

CHILD SEAT ADAPTER

DETAIL

H

A07 19T1057

AMVSAFE Aviation Inflatable Restraint System
Figure 201 (Sheet 3)

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MAINTENANCE MANUAL
B.

Restraint System Installation (Refer to Figure 201).
NOTE:
(1)

Keep the protective plastic bag on the air bag belt during installation to keep it clean.

Remove and keep the shipping caps from the inflator-hose connector fitting.
NOTE:

The shipping caps can be used again.

(2) Put the inflator assembly into the mounting bracket. Do not tighten the clamps on the mounting
bracket.
(3) Remove and discard the end cap plug (if new) from the three-point air bag belt hose. Do not
remove the safety cable tie for the air bag connector tongue.
NOTE:

(4)

If the three-point air bag belt is not new, and the inflator is new, apply a thin layer of
Loctite 242 thread-locking compound on the hose barb threads before you attach the
inflator assembly.

Make sure that the three-point seat belt air bag belt is aligned correctly.
NOTE:

If aligned correctly, the gas hose will be on top of the seat belt attachment hardware.
The label will be on the aft side of the belt.

(5) Connect the gas hose from the three-point air bag belt to the inflator assembly with the correct
torque (Refer to Table 201).
NOTE:
(6)
(7)
(8)
(9)
(10)
(11)
*

~~(12)
(13)
(14)

(15)
7.

The inflator hose connector fitting is a pressure fitting which must be fully extended
onto the gas hose barb to make an airtight connection.

Attach the squib connector to the inflator assembly.
Tighten the clamps on the mounting bracket to between 21 and 25 inch-pounds of torque.
Attach the EMA to the floorboard with the washers, nuts, and bolts.
Connect the cable interface assembly to the EMVA.
Make sure that the cables and hoses of the AAIR are clear of the height-adjustment crank, the
seat lock handle, and the seat-back adjustment lever.
Install the inertia reel (three-point air bag belt) in the airplane. Refer to Chapter 25, Seat Belt!
Restraints - Maintenance Practices.
Arm the AMSAFE inflatable restraints. Refer to AMVSAFE Inflatable Restraint Disarm/Arm.
Remove the safety cable tie from the air bag buckle tongue.
Do a seat operation test on the pilot's seat and copilot's seat.
(a) Move the seat-back aft and forward to its maximum travel.
(b) Move the seat-base up an down to its maximum travel.
(c) Move the seat-base aft and forward to its maximum travel.
Do a functional test on the system. Refer to the AMSAFE Aviation AAIR Supplemental
Maintenance Manual, V23 System Diagnostic Tool - Operation and Maintenance Manual.

AMVSAFE Aviation Inflatable Restraint (AAIR) System Adjustment/Test
A. The AAIR diagnostic check gives a system functional test of the AAIR circuits. To find problems in
system components, use a replace-and-test procedure. There are two seats to each AAIR system.
The 1 LED light will show an indication for the first seat on the AAIR system circuit. The 2 LED light will
show an indication for the second seat on the AAIR system circuit. Once the V23 system diagnostic
tool (SDT) is connected to the airplane, a check of the system is done one seat at a time.
B. The V23 system diagnostic tool uses a 9-volt battery that can be replaced. A check of the diagnostic
tool must be done yearly. The label on the back of the diagnostic tool will show when a check of the
tool needs to be done. The diagnostic tool must only be sent to AMVSAFE to be calibrated.

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MAINTENANCE MANUAL

CAUTION: Calibrate the V23 system diagnostic tool again before use if it is hit,
shaken, or if it falls to the floor.
C.

Before the V23 system diagnostic tool is connected to the airplane, do the steps that follow.
(1) Set the SDT ON/OFF Switch to the ON position.
(2) Look at the Tool Battery Indicator LED light.
(a) If the LED light is green, the battery condition is satisfactory.
(b) If the LED light is red, replace the 9-volt battery on the back of the SDT.

D.

Do the System Functional Test.
NOTE:
(1)
(2)
(3)
(4)
(5)
(6)

There are two seats in each AAIR system. This functional test must be completed for each
AAIR system on the airplane.

Make sure that the seat belt safety buckles are not connected.
Remove the protective cap from the cable interface assembly.
Connect the V23 system diagnostic tool to the diagnostic connector.
Set the SDT ON/OFF Switch to the ON position.
Look at the Seat Position PASS/FAIL LED light.
If the 1 and 2 LED lights are amber, do the steps that follow. If the 1 and 2 LED lights do not give
an amber indication, troubleshoot the system. Refer to AMSAFE Aviation Inflatable Restraint
(AAIR) System Troubleshooting.
(a) Connect the air bag safety buckle on the first seat location.
(b) If the 1 LED light is green, the AAIR system for that seat is satisfactory.
(c) If there is an amber LED light indication, a red indication, or no indication, troubleshoot the
system. Refer to AMSAFE Aviation Inflatable Restraint (AAIR) System Troubleshooting.
(d) Disconnect the air bag safety buckle.
(e) Do steps (a) thru (d) again for the second seat location.
NOTE:

For the second seat location, the 2 LED light will be used to give an indication.

(7) Set the SDT ON/OFF Switch to the OFF position.
(8) Disconnect the V23 system diagnostic tool from the diagnostic connector.
(9) Put the protective cap on the cable interface assembly.
8.

AMVSAFE Aviation Inflatable Restraint (AAIR) System Troubleshooting
A.

The procedures in this section must be done if the V23 system diagnostic tool gives an unsatisfactory
indication for the seats in the AAIR System Adjustment/Test. An unsatisfactory indication by the seat
LED light isan amber indication, red indication, or no indication. If the V23 system diagnostic tool gives
a satisfactory indication after the replacement of the individual components, stop the troubleshooting
procedure.
(1) If an unsatisfactory indication is given before the safety buckle is connected, do the steps that
follow.
(a) Do a check of all connections and tighten loose connections that are found. Do the
Adjustment/Test procedure again if there are loose connections found.
(b) Replace the cable interface assembly. Do the Adjustment/Test procedure again.
(c) Replace the EMVA. Do the Adjustment/Test procedure again.
(d) Replace the inflator. Do the Adjustment/Test procedure again.
(2) If an unsatisfactory indication is given after the safety buckle is connected, do the steps that
follow.
(a) Replace the cable interface assembly. Do the Adjustment/Test procedure again.
(b) Replace the air bag safety buckle. Do the Adjustment/Test procedure again.
(c) Replace the EMVA. Do the Adjustment/Test procedure again.
(d) Replace the inflator. Do the Adjustment/Test procedure again.

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MODEL 182/T182
MAINTENANCE MANUAL
REAR SEAT - MAINTENANCE PRACTICES
1.

General
A.

This section provides instruction for removal and installation of the rear seat.

WARNING: If the airplane has AMSAFE inflatable restraints, do not do
maintenance on the seats until you look at and obey all applicable
precautions and instructions supplied in the AMSAFE publications
and this maintenance manual. If you do not obey and follow these
instructions and safety precautions, damage to equipment and
harm to personnel can occur.
B.

2.

If your airplane has the AMSAFE inflatable restraint system, do not do maintenance on the seats
or the seat restraint system unless you first obey all applicable precautions and instructions in
the E508804 Supplemental Amsafe Maintenance Manual and this maintenance manual. Refer to
Inflatable Restraint System - Maintenance Practices.

Rear Seat Removal/Installation
A.

Rear Seat Removal (Refer to Figure 201).

WARNING: If the airplane has AMSAFE inflatable restraints, do not remove the
seats with the seat belts buckled or the EMA connected. Damage
can occur to the system and an accidental deployment of the
system can cause injury.
(1) Remove the restraints before you remove the seats. Refer to Seat Belts/Restraints Maintenance Practices.
(2) Remove the bolts and the washers that attach the seat frame to the fuselage.
(3) Remove the seat from the airplane.
B.

Rear Seat Installation (Refer to Figure 201).
(1) Install the seat to the fuselage with the bolts and the washers.
(2) Install the restraints. Refer to Seat Belts/Restraints - Maintenance Practices.

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MODEL 182/T182

MAINTENANCE MANUAL
B1152

ST

SEAT
BASE
SEAT BACK

DETAIL

A

B
BOLT

CONTROKL

CAL

CONTROL

DETAIL B

DETAIL C

0710T1001
A0719T1003
B0719T1004
C0719T1005

Aft Bench Seat Installation
Figure 201 (Sheet 1)

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MODEL 182/T182

MAINTENANCE MANUAL
INTERIOR UPHOLSTERY - MAINTENANCE PRACTICES
1.

General
A.

2.

Cabin Panels Removal/Installation
A.

3.

This section provides general instructions for removal and installation of the interior panels and carpet.

Interior panels are typically attached to fuselage structure using screws. Refer to Figure 201 for an
exploded view of the interior panels, headliner and overhead console.

Door Panels and Carpet Removal/Installation
A.

Cabin door panels are typically attached to the fuselage and door structure using small screws. Carpet
is attached to the floorboard using velcro. Refer to Figure 202 for a view of the side panels and carpet.

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April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

4X
DE

b

REAR WINDOW TRIM

WINDL- VINDOW
Ci

-r

\I

TRIM

WINDLACE

DETAIL A

LOWER
FIREWALL
UPHOLSTERY

SIDE PANEL

Cabin Top and Interior Installation
Figure 201 (Sheet 1)

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MODEL 182/T182
MAINTENANCE MANUAL

81154

ELECTRICAL CONNECTOR

OVERHEAD CONSOLE

DETAIL C

C0519T1050

Cabin Top and Interior Installation
Figure 201 (Sheet 2)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

REAR PANEL

FORWARD SIDE PANEL

DOOR PANEL

/

/

/
f
./I

*'

. .

ACCENT
TRIM

VIEW A-A

ACCENT TRIM
DOOR PANEL

FORWARD SIDE PANEL

/

/
CD

0

REAR PANEL

*

/

0

0

0

/

0710T1001
AA0719T1001
BB0719T1001

VIEW B-B
Cabin Side Panel and Floorboard Upholstery Installation
Figure 202 (Sheet 1)

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MODEL 182/T182

MAINTENANCE MANUAL

B1156

AFT CARPET

FORW/

FF PLATE

AREA CARPET

I
zCONSOLE
U
CONSOLE
CARPET

FOOTWELL CARPET

DETAIL A

A0519T1040

Cabin Side Panel and Floorboard Upholstery Installation
Figure 202 (Sheet 2)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
CARGO TIE-DOWNS - MAINTENANCE PRACTICES
1.

General
A.

Cargo tie-downs are provided for the airplane to accommodate a variety of loading positions. These
tie-downs are secured directly through nutplates. Refer to Figure 201 for an illustration of tie-downs.

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1157

TIE-DOWN RING

05141010

Cargo Tie-Downs Installation
Figure 201 (Sheet 1)

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MODEL 182/Ti 82

MAINTENANCE MANUAL
POINTER EMERGENCY LOCATOR TRANSMITTER

-

MAINTENANCE PRACTICES

1.General
A. This section gives maintenance practices for the Emergency Locator Transmitter (ELT). The ELT is
activated automatically by an internal G-switch or manually by a remote switch on the instrument
panel, or by the ELT master switch. The ELT transmits an emergency distress signal on 121.5/243.0
MHz.
2.

Pointer ELT Removal/installation
A. ELT Removal (Refer to Figure 201).
(1) Put a support stand under the tail tiedown ring to support the tailcone. Refer to Chapter 7,
Jacking - Maintenance Practices.
(2) Remove the rear seat. Refer to Rear Seat - Maintenance Practices.
(3) Remove the baggage curtain to get access to the transmitter. Refer to Interior Upholstery Maintenance Practices.
(4) Put the ELT master switch in the OFF/RESET (center) position.

CAUTION: Do not disconnect the ELT remote connector before you put the ELT
master switch in the OFF/RESET (center) position. ELT internal
fuse failure can occur if the ELT remote connector is disconnected
before the ELT master switch is put in the OFF/RESET (center)
position.

B.

(5) Disconnect the ELT antenna coaxial cable from the ELT.
(6) Disconnect the ELT remote connector from the ELT.
(7) Disengage the attach strap from around the ELT and remove the ELT from the airplane.
ELT Installation (Refer to Figure 201).
(1) Complete an ELT G-Switch Operation Check. Refer to ELT Operational Test, ELT G-Switch
Operation Check

CAUTION: Make sure that the direction of flight arrow on the ELT points to the
nose of the airplane.
CAUTION: Make sure that the ELT master switch is inthe OFF/RESET position.
ELT internal fuse failure can occur if the ELT remote connector is
installed with the ELT master switch in the ON or AUTO position.
(2)
(3)
(4)
(5)
(6)

Put the ELT into the ELT bracket and tighten the ELT attach strap.
Connect the ELT remote connector to the ELT.
Connect the ELT antenna coaxial cable to the ELT.
Put the ELT master switch in the AUTO position.
Complete the Control Tower Monitored or Locally Monitored ELT Operational Test. Refer to the
ELT Operational Test, Control Tower Monitored ELT Operational Test or Locally Monitored ELT
Operational Test.
(7) Install the baggage curtain. Refer to Interior Upholstery - Maintenance Practices.
(8) Install the rear seat. Refer to Rear Seat - Maintenance Practices.
(9) Remove the support stand. Refer to Chapter 7, Jacking - Maintenance Practices.

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MODEL 1821T182

MAINTENANCE MANUAL

U

INTERNAL
LOCKING
,rl¶vv

:IN
ENNA
JBILER
NNA

'CH)

GASKET
NEOPRENE WASI,BASE PLATE
ATTACH STRA
MOUNTING BRACKET

DETAIL A

0710T1001
Afl51 1 014

Pointer Emergency Locator Transmitter Installation
Figure 201 (Sheet 1)

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MAINTENANCE MANUAL

B1 159

viEw A-A

MOUNTED SWITCH

DETAIL B
AA071 STI002
B0585T1 040

Pointer Emergency Locator Transmitter Installation
Figure 201 (Sheet 2)
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*3.

Pointer ELT Remote Switch RemovaVlnstallation

CAUTION: Do not disconnect the ELT remote connector before you put the ELT
master switch in the OFF/RESET (center) position. ELT internal fuse
failure can occur if the ELT remote connector is disconnected before the
ELT master switch is put in the OFF/RESET (center) position.
CAUTION: Disconnect the ELT remote connector from the ELT before you remove
the ELT remote switch or disconnect the ELT remote switch connector.
ELT internal fuse failure can occur if the ELT remote switch or disconnect
is removed before the ELT remote connector is disconnected.

*4.

A.

ELT
(1)
(2)
(3)
(4)
(5)
(6)

Remote Switch Removal (Refer to Figure 201 ).
Put the aircraft master switch (ALT/BAT) in the OFF position.
Get access to the back of the remote mounted switch.
Put the ELT master switch in OFF/RESET (center) position.
Disconnect the electrical connector (PT905) from the ELT.
Get access to the back of the ELT remote switch (Zone 221).
Disconnect the ELT remote switch connector.

B.

ELT
(1)
(2)
(3)
(4)
(5)
(6)
(7)

Remote Switch Installation (Refer to Figure 201).
Hold the edges of the ELT remote switch and put it into the instrument panel cutout.
Make sure that the locking tabs engage and that the switch is correctly installed.
Connect the ELT remote switch connector.
Put the ELT remote switch in the AUTO position.
Connect the electrical connector (PT905) to the ELT.
Make sure that the ELT master switch is set to the OFF position.
Complete the Control Tower Monitored or Locally Monitored ELT Operational Test. Refer to
ELT Operational Test, Control Tower Monitored ELT Operational Test, or Locally Monitored ELT
Operational Test.

ELT Antenna RemovaVlnstallation (integral Base with Coax Cable)
A.

ELT Antenna Removal (Refer to Figure 201).
(1) Remove the panel (31 OAR) from the right side of the tailcone to get access to the ELT. Refer to
Chapter 6, Access/Inspection Plates - Description and Operation.
(2) Disconnect the ELT antenna coaxial cable from the ELT.
(3) Remove all of the tie straps that attach the ELT antenna coaxial cable to the fuselage.
(4) On the external skin of the airplane, remove the six internal locking screws that attach the ELT
antenna to the fuselage.
NOTE:

The ELT antenna has an integral base and coaxial cable.

(5) Remove the ELT antenna from the inside of the airplane.
B.

ELT Antenna Installation (Refer to Figure 201).
(1) From inside the airplane, put the ELT antenna in position on the fuselage with the ELT antenna
pointing aft.
(2) On the external skin of the airplane, use the internal locking screws to attach the ELT antenna
base to the fuselage.
(3) Connect the ELT antenna coaxial cable to the ELT.
(4) Use tie straps to attach the ELT antenna coaxial cable to the fuselage.
(5) Complete the Control Tower Monitored or Locally Monitored ELT Operational Test. Refer to
ELT Operational Test - Control Tower Monitored ELT Operational Test or Locally Monitored ELT
Operational Test.
(6) Install the panel (31 OAR) on the right side of the tailcone. Refer to Chapter 6, Access/Inspection
Plates - Description and Operation.

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.

1
~5.

ELT Whip Antenna Removal/installation
A.

B.

*6.

ELT Whip Antenna Removal (Refer to Figure 201).
(1) Get access to the ELT and ELT whip antenna through the panel (31 OAR) on the right side of the
tailcone.
(2) Disconnect the ELT whip antenna coaxial cable from the ELT whip antenna.
(3) From inside the airplane, remove the nut and washer that attach the ELT whip antenna to the
fuselage.
(4) Remove the ELT whip antenna from the external skin of the airplane.
ELT Whip Antenna Installation (Refer to Figure 201).
(1) Put the ELT whip antenna in position on the external skin of the fuselage with the ELT whip
antenna pointing aft.
(2) From inside the airplane, use the nut and washer to connect the ELT whip antenna to the
fuselage.
(3) Connect the ELT antenna coaxial cable to the ELT whip antenna.
(4) Complete the Control Tower Monitored or Locally Monitored ELT Operational Test. Refer to
ELT Operational Test, Control Tower Monitored ELT Operational Test, or Locally Monitored ELT
Operational Test.
(5) Install the panel (31 OAR) on the right side of the tailcone. Refer to Chapter 6, Access/inspection
Plates - Description and Operation.

Pointer ELT Battery Pack Removal/Installation
A. ELT Battery Pack Removal (Refer to Figure 201).

WARNING: Obey the correct procedures to discard the unserviceable
ELT battery packs to prevent damage to the environment and
personal injury.

B.

(1)
(2)
(3)
(4)
ELT

Remove the ELT from the airplane. Refer to ELT Removal/Installation.
Remove the screws that attach the ELT base plate to the ELT.
Disconnect the battery pack connector for the ELT.
Remove the ELT battery pack from the ELT.
Battery Pack Installation (Refer to Figure 201).

CAUTION: Use only the recommended battery pack for the ELT. If you use other
types of battery packs, the operating life and/or signal strength of the
ELT will decrease. The incorrect battery pack can also change the
mechanical configuration, which will cause too much vibration and
corrosion.
(1) Put the ELT battery pack in the ELT.
(2) Connect the ELT battery pack connector.

CAUTION: Do not tighten the ELT gasket and screws too much.
(3) Use screws to attach the ELT base plate and gasket to the ELT.
NOTE:

(4)

When the new battery pack expiration date is put in the airplane records, it is also
recommended that you record the expiration date in the ELT owner's manual for quick
reference.

Put the new replacement date on the outside of ELT transmitter with a stamp. Put the date on
the ELT switch nameplate, on the side of the ELT transmitter, and in instruction nameplate on
top of the ELT transmitter.

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(5) Install the ELT in the airplane. Refer to ELT Removal/Installation.
*7.

Pointer ELT Operational Test
A.

Control Tower Monitored ELT Operational Test.

CAUTION: Operate the Emergency Locator Transmitter (ELT) system only
during the first five minutes of each hour. Refer to the FAA Advisory
Circular AC-91 -44A.
(1) Get permission from the control tower and/or flight service station to do a test of the ELT system.

CAUTION: Do not operate the ELT system for more than three pulses of the
audio signal. Longer operation can decrease the ELT battery power
supply.
NOTE:

Do not use the airplane's VHF receiver or ADF to measure the power of the ELT audio
signal.

(2) Put the ELT remote switch in the ON position.
(3) Contact the control tower and/or flight service station to make sure that the ELT system operates
correctly.
(4) Momentarily put the ELT remote switch to the RESET position.
(5) Put the ELT remote switch in the AUTO position.
(6) Contact the control tower and/or flight service station to make sure that the ELT stopped
transmission.
B.

Locally Monitored ELT Operational Test.

CAUTION: Operate the Emergency Locator Transmitter (ELT) system only
during the first five minutes of each hour. Refer to the FAA Advisory
.Circular AC-91 -44A.
(1) (1) Put a small, hand held AM radio tuned to any frequency, within six inches of the ELT antenna.

CAUTION: Do not operate the ELT system for more than three pulses of the
audio signal. Longer operation can decrease the ELT battery power
supply.
NOTE:

Do not use the airplane's VHF receiver or ADIF to measure the power of the ELT audio
signal.

(2) Put the ELT remote switch in the ON position.
(3) Make sure that the ELT signal is heard on the AM radio.
(4) Momentarily put the ELT remote switch to the RESET position.
(5) Put the ELT remote switch in the AUTO position.
C.

ELT Master Switch Operational Test.

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CAUTION: Operate the Emergency Locator Transmitter (ELT) system only

during the first five minutes of each hour. Refer to the FAA Advisory
Circular AC-91 -44A.

CAUTION: Do not operate the ELT system for more than three pulses of the
audio signal. Longer operation can decrease the ELT battery power
supply.

D.

Put the ELT master switch in the ON position.
Make sure that the signal is heard by the Control Tower, Flight Service Station, or AM radio.
Put the ELT master switch in the OFF/RESET position.
Put the ELI master switch in the AUTO position.
G-Switch Operational Check.
Remove the ELT from the airplane. Refer to ELI Removal/Installation.
Put the ELI master switch in the AUTO position.
Hold the ELI tightly in one hand, and move the ELT fast in one direction, followed by a sudden
reversal of direction.
(4) Make sure that the ELI G-switch has been activated.
(5) Put the ELI master switch in the OFF/RESET position to reset the ELI G-switch.
(6) Install the ELI in the airplane. Refer to ELI Removal/installation.
(1)
(2)
(3)
(4)
ELI
(1)
(2)
(3)

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ARTEX C406-N EMERGENCY LOCATOR TRANSMITTER

-

MAINTENANCE PRACTICES

1.

General
A. This section gives maintenance practices for the emergency locator transmitter (ELT) system.
Components in the ELT system include the ELT, antenna, remote switch, and buzzer.

2.

Artex C406-N ELT Remova~l/nstallation
A. ELT Removal (Refer to Figure 201).
(1) Put a support stand under the tail tie-down ring to support the tailcone. Refer to Chapter 7,
Jacking - Maintenance Practices.
(2) Remove the rear seat. Refer to Rear Seat - Maintenance Practices.
(3) Remove the baggage curtain to get access to the transmitter. Refer to Interior Upholstery Maintenance Practices.
(4) Put the ELT master switch in the OFF position.
(5) Disconnect the electrical connector (PT905) and the coaxial connector (PT1 029) from the ELT.
(6) Loosen the knurl nuts on the end cap of the transmitter and the mounting tray.
(7) Pull the front cover away from the transmitter and the mounting tray.
(8) Carefully pull the mounting tray end and the tray away from the ELT.
(9) Remove the ELT from the mounting tray.
(10) Remove the screws that attach the mounting tray to the shelf assembly.
B. ELT Installation (Refer to Figure 201).
(1) Attach the mounting tray to the shelf assembly with the screws.

CAUTION: Make sure that the direction-of-flight arrow on the ELT points to the
nose of the airplane.
(2)
(3)
(4)
(5)
(6)
(7)
(8)
(9)
(10)
(11)
(12)
(13)
(14)
(15)
3.

Put the ELT transmitter in position in the tray at an angle. Move the locking ears at the end
opposite to the direction-of-flight arrow into the mounting tray locking slots.
Make sure that the ELT switch on the ELT is in the OFF position.
Put the ELT in the mounting tray at an angle to engage the locking mechanism at the opposite
end of the ELT.
Push the ELT down into the mounting tray until it is fully installed in the tray.
Put the top cover on the top of the transmitter.
Make sure that the top cover locks into the aft end of the transmitter.
Put the end cap on the transmitter and mounting tray.
Tighten the knurl nuts.
Connect the electrical connectors (PT905) and (PT1 029) to the ELT transmitter.
Connect the electrical power to the airplane.
Do a functional test of the ELT. Refer to Artex C406-N ELT Functional Test.
Install the baggage curtain. Refer to Interior Upholstery - Maintenance Practices.
Install the rear seat. Refer to Rear Seat - Maintenance Practices.
Remove the support stand. Refer to Chapter 7, Jacking - Maintenance Practices.

Artex C406-N ELT Remote Switch Removal/installation
A. ELT Remote Switch Removal (Refer to Figure 201 ).
(1) Put the aircraft master switch (ALT/BAT) in the OFF position.
(2) Get access to the ELT.
(3) Put the ELT master switch in the OFF position.
(4) Disconnect the ELT remote connector from the ELT.
(5) Get access to the back of the ELT remote switch (Zone 221).
(6) Disconnect the ELT remote switch connector.
(7) Remove the screws that attach the ELT remote switch to the instrument panel.
(8) Remove the ELT remote switch from the airplane.
B. ELT Remote Switch Installation (Refer to Figure 201).
(1) Put the ELT remote switch in position in the instrument panel.

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ROD
ANTENNA
SKIN
DOUBLER
ELECTRICAL
CONNECTOR
(PT1 030)

MOUNTING
TRAY

EMERGENCY
LOCATOR
TRANSM ITTER

1-

1AY
Z;KET
ELECT
CONN
(PT90t

ER
CABLE
(PT1 029)

BUZZER

DETAIL

A

0710T1 001
A0718T1 105

Artex C406-N ELT Installation
Figure 201 (Sheet 1)

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B6004

R

REMOTE MVOUNSCREW

AA3940T445
B3940T445

Artex C406-N ELT Installation
Figure 201 (Sheet 2)
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(2)
(3)
(4)
(5)
(6)
(7)
4.

Attach the ELT remote switch to the instrument panel with the screws.
Connect the ELT remote switch connector.
Put the ELT remote switch to the AUTO position.
Connect the ELT remote connector to the ELT.
Make sure that the ELT master switch is set to the OFF position.
Do a functional test of the ELT. Refer to Artex C406-N ELT Functional Test.

Artex C406-N ELT Rod Antenna Removal/installation
A.

B.

ELT Antenna Removal (Refer toFigure 201).
(1) Put a support stand under the tail tie-down ring to support the tailcone. Refer to Chapter 7,
Jacking - Maintenance Practices.
(2) Remove the rear seat. Refer to Rear Seat - Maintenance Practices.
(3) Remove the baggage curtain to get access to the transmitter. Refer to Interior Upholstery Maintenance Practices.
(4) Disconnect the coaxial cable connector (PT1 029) for the antenna.
(5) Remove the tie strap that attaches the ELT antenna coaxial cable to the fuselage.
(6) Remove the four screws that attach the ELT antenna to the fuselage.
(7) Remove the ELT antenna from the airplane.
ELT Antenna Installation (Refer to Figure 201).
(1) Remove all of the old sealant from the ELT rod antenna and from the airplane skin. Refer to
Chapter 20, General Solvents/Cleaners - Maintenance Practices.
(2) Put the ELT antenna in position on the fuselage with the ELT antenna pointing aft.
(3) Install the four screws that attach the ELT antenna to the fuselage.
(4) Connect the ELT antenna coaxial cable to the ELT.
(5) With the tie strap, attach the ELT antenna coaxial cable to the mount on the fuselage.
(6) Make sure that there is a correct electrical bond between the antenna and the airplane structure.
(a) Remove one screw.
(b) With an ohmmeter, measure the electrical resistance from the antenna base metal insert
to the structure at the screw position.
NOTE:

The maximum allowable resistance (in ohms) at each of the four measured
positions is 0.0025.

Install the screw and remove and install each of the remaining screws in turn as you
measure the electrical resistance at each screw hole.
Apply a fillet seal around the antenna with Type I Class B Sealant. Do not cover the screw
head with the sealant. Refer to Chapter 20, Fuel, Weather and High-Temperature Sealing Maintenance Practices.
Do a functional test of the ELT. Refer to Artex C406-N ELT Functional Test.
Install the baggage curtain. Refer to Interior Upholstery - Maintenance Practices.
Install the rear seat. Refer to Rear Seat - Maintenance Practices.
Remove the support stand. Refer to Chapter 7, Jacking - Maintenance Practices.
(c)

(7)
(8)
(9)
(10)
(11)
5.

Artex C406-N Buzzer Removal/installation
A.

Buzzer Removal (Refer to Figure 201).
(1) Put a support stand under the tail tie-down ring to support the tailcone. Refer to Chapter 7,
Jacking - Maintenance Practices.
(2) Remove the rear seat. Refer to Rear Seat - Maintenance Practices.
(3) Remove the baggage curtain to get access to the transmitter. Refer to Interior Upholstery Maintenance Practices.
(4) Make sure that the ELT master switch on the ELT transmitter is in the OFF position.
(5) Tag the wires and terminals for identification.
(6) Remove the screws that attach the electrical terminals to the buzzer.
(7) Loosen the black retainer ring on the outboard side of the buzzer.
(8) Remove the buzzer from the bracket.

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B.

Buzzer Installation (Refer to Figure 201)
(1) Put the buzzer in the bracket.
(2) Install the black retainer ring on the outboard face of the buzzer.
(3) Connect the electrical wires to the buzzer with the screws.
(4) Do a functional test of the ELT. Refer to Artex C406-N ELT Functional Test.
(5) Install the baggage curtain. Refer to Interior Upholstery - Maintenance Practices.
(6) Install the rear seat. Refer to Rear Seat - Maintenance Practices.
(7) Remove the support stand. Refer to Chapter 7, Jacking - Maintenance Practices.

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ARTEX C406-N EMERGENCY LOCATOR TRANSMITTER

-

INSPECTION/CHECK

1.General
A. This section gives the procedures that are necessary to do the inspection and operational checks are
necessary to comply with 14 CFR 91 .207, for the Artex 0406-N Emergency Locator Transmitter (ELT)
System.
2.

Artex C406-N ELT Functional Test

CAUTION: Operate the Emergency Locator Transmitter system only during the first
five minutes of each hour. If you must complete the functional test at a
time other than the first five minutes of the hour, you must do the test
with a direct connection to the ELT and a 30 dB attenuator. Refer to the
FAA Advisory Circular AC-91-44A.
CAUTION: Do not operate the emergency locator transmitter for more than five
seconds at a time. Do not operate the ELT again for 15 seconds.
The ELT will transmit a 406.028 MHz signal after the ELT is active for
approximately 50 seconds. This signal is identified as a distress signal
A.

B.

C.

Prepare for the Artex 0406-N ELT Functional Test.
(1) You must replace the ELT battery with a new ELT battery if one or more of the conditions that
follow occur:
*
Use of the ELT battery in an emergency
*
Operation for an unknown amount of time
*
Use for more than one hour of cumulative time
•
On or before the replacement date shown on the battery label.
(2) Examine the ELT battery to make sure that it is not due for replacement.
(3) If the battery must be replaced, follow the manufacturer's instructions to replace it.
(4) Supply +28 v, +0.25 or -0.25 v, external electrical power to the airplane.
(5) Initialize the global positioning system (GPS) on the multi-function display (MFD).
Do the ELT Transmitter Test.
(1) Adjust the volume to make sure that the transmissions from the radio are heard in the cockpit.
(2) Adjust the COM 1 frequency to 121.50 MHz. Make sure that the audio is heard through the
cockpit speakers.
(3) Put the cockpit ELT switch in the ON position for approximately one second.
(4) Make sure that the ELT audio signal and the cockpit ELT switch light adjacent to the ELT remote
switch come on.
(5) Immediately put the cockpit ELT switch in the ARM position.
(6) Make sure that the LED stays on for approximately one second before it goes off.
(7) If the ELT system has sensed a fault in the system, the LED will flash a fault code at this time.
Refer to the Installation and Operation Manual for the Artex ELT system for information on the
possible codes.
Do the NAV Interface Test.
(1) Hold the SARSAT tester no more than fifteen feet from the antenna.
NOTE:

The SARSAT tester is used as an example to gather test information. However, other
equivalent test equipment such as the Aeroflex IFR 4000 Communications Test Set
is acceptable.

(2) Turn on the SARSAT tester.
(3) Engage the receive function of the SARSAT tester.
(4) Make sure that the display on the tester shows that it is searching for a signal.
(5) Put the ELT remote switch in the ON position.
(6) Within 15 seconds, put the ELT remote switch in the ARM position.

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(7) Monitor the SARSAT tester to see if it received a signal from the ELT system.
(a) If no signal was received, do the test again after the 15-second off cycle.
(8) Make sure that the tail number on the SARSAT tester is correct.
(9) Make sure that the Mode S code shown on the SARSAT tester is the same as the number that
is on the back of the transmitter.
(10) Make sure that the latitude and longitude information is the same as that shown on the MFD
display.
(11) Turn the SARSAT tester off.
(12) Disconnect external electrical power from the aircraft.
D.

Do the G-Switch Operational Test.

CAUTION: Operate the Emergency Locator Transmitter system only during the

first five minutes of each hour. If you must complete the functional
test at a time other than the first five minutes of the hour, you must do
the test with a direct connection to the ELT and a 30 dB attenuator.
Refer to the FAA Advisory Circular AC-91 -44A.

CAUTION: Do not operate the emergency locator transmitter for more than five
seconds at a time. Do not operate the ELT again for 15 seconds.
The ELT will transmit a 406.028 MHz signal after the ELT is active
for approximately 50 seconds. This signal is identified as a distress
signal.
(1) Remove the ELT from the airplane. Refer to ELT Removal/Installation (On airplanes with the
Artex C406-N.
(2) Install a jumper wire between pins 12 and 13 on the electrical connector of the ELT.
NOTE:

The ELT will not activate with the G-switch unless electrical pins 12 and 13 have
a jumper wire installed between them (this happens automatically when the ELT is
locked into the mount tray with the electrical connector in position). Because of the
potential physical damage that can occur if the jumper wire is not installed correctly,
it is recommended that an experienced technician do this procedure.

(3) Put the ELT switch in the OFF position.
(4) Use a receiver, and set it to 121 .5 MHz to listen for the aural warning sweep tone.
(5) Hold the ELT transmitter tightly in one hand and make a throwing movement followed by an
opposite movement of the ELT transmitter.
(6) Make sure that the G-switch operates and that the aural warning sweep tone is heard on the
receiver set to 121 .5 MHz.
(7) Set the ELT switch to the ON position and then back to the OFF position to reset the G-switch.
(8) Remove the jumper wire from electrical pins 12 and 13 on the electrical connector of the ELT.
(9) Install the emergency locator transmitter in the airplane. Refer to ELT Removal/Installation (On
airplanes with the Artex C406-N.

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ARTEX ME406 EMERGENCY LOCATOR TRANSMITTER SYSTEM

-

DESCRIPTION AND OPERATION

1.General
A. An Artex ME406 Emergency Locator Transmitter (ELT) System is installed to help rescue teams find
the airplane in the event of a crash. It is made to operate in a wide range of environmental conditions
and is resistant to the forces caused by many types of accidents.
2.

Description
A.

Artex ME406 ELT.
(1) The Artex ME406 Emergency Locator Transmitter (ELT) system includes an ELT unit, an integral
battery pack, warning buzzer, internal G-switch, antenna, remote switch, cable assembly, and
antenna coaxial cable. The ELT unit transmits on 121.5 MHz and 406.028 MHz.
(2) The battery pack has two D-size lithium cells mounted under a battery cover. The battery pack
is replaced as necessary in the field.
(3) The ELT activates a buzzer that is installed near the ELT assembly. The buzzer makes a loud
noise to let people know that the ELT is on.
(4) The G-switch is internally installed in the ELT transmitter and is activated with a sudden reduction
in forward speed.

B.

Artex ELT Antenna.
(1) The ELT system uses an antenna to transmit the emergency locator signal. The ELT antenna
is installed on top of the tailcone skin, forward of the vertical stabilizer. The ELT antenna is
connected with a coaxial cable to the ELT unit inside the dorsal.
ELT Remote Switch.
(1) The ELT remote switch is installed on the right panel. The ELT remote switch is a two-position
rocker switch that can be set in the ARM or the ON positions.

C.

3.

Operation

CAUTION: Operate the emergency locator transmitter (ELT) system only during the first
five minutes of each hour. If you must complete the functional test at a time
other than the first five minutes of the hour, you must do the test with a direct
connection to the ELT and a 30 dB attenuator. Refer to the FAA Advisory
Circular AC-91-44A.
CAUTION: Do not operate the emergency locator transmitter (ELT) for more than five
seconds at a time. Do not operate the ELT again for 15 seconds. The ELT
will transmit a 406.028 MHz signal after the ELT is active for approximately
50 seconds. This signal is identified as a distress signal.
A.

B.

Artex ME406 ELT.
(1) During an accident, the ELT will activate automatically and transmit a standard swept tone on
121.5 MHz (emergency frequency). The 121.5 MHz signal will continue until the ELT battery has
expired. Every 50 seconds for 440 milliseconds, the 406.028 MHz transmitter will activate and
send a message to the satellite. The 406.028 MHz transmission will continue for 24 hours and
then stop. During operation, the ELT will receive electrical power from the ELT battery pack only.
ELT Remote Switch.
(1) The ELT can also be activated manually in the cockpit with the ELT remote switch. To manually
activate the ELT, put the ELT remote switch in the ON position. The red LED will come on when
the remote switch is set in the ON position. The ELT remote switch can also be used to do a
test of the ELT system (refer to Artex ME406 Emergency Locator Transmitter - Troubleshooting).
During typical operation, the ELT remote switch will be in the ARM position.

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ARTEX ME406 EMERGENCY LOCATOR TRANSMITTER SYSTEM

-

TROUBLESHOOTING

1.General
A. This section contains the information that is needed to complete the self test for the ARTEX ME406
Emergency Locator Transmitter system. The system transmits on two frequencies at the same time.
2.

Tools and Equipment
A. For information on tools and equipment, refer to Equipment and Furnishings - General.

3.

ME406 Emergency Locator Transmitter Self Test Preparation

CAUTION: Operate the Emergency Locator Transmitter system only during the first
five minutes of each hour. If you must complete the functional test at a
time other than the first five minutes of the hour, you must do the test
with a direct connection to the ELT and a 30 dB attenuator. Refer to the
FAA Advisory Circular AC-91-44A.
CAUTION: Do not operate the emergency locator transmitter for more than five
seconds at a time. Do not operate the ELT again for 15 seconds.
The ELT will transmit a 406.028 MHz signal after the ELT is active for
approximately 50 seconds. This signal is identified as a distress signal.
A.

B.

C.

Prepare the Airplane for the ME406 Emergency Locator Transmitter Troubleshooting.
(1) Put the BATTERY switch in the ON position.
(2) Examine the ELT battery to make sure that it is serviceable.
(a) If the battery must be replaced, follow the manufacturers instructions to replace it.
ELT 121.5 MHz Test.
(1) Tune the receiver (usually the aircraft radio) to 121.5 MHz.
(2) Set the ELT instrument panel remote switch to the ON position and wait for 3 sweeps on the
receiver which takes about 1 second.
(3) Set the remote switch back to the ARM (OFF) position immediately and the switch LED and
buzzer will give 1 pulse. If more pulses are displayed, find the problem from the list below.
(a) One flash - Shows that the system is operational and that no error conditions were found.
(b) Three flashes - Shows an open or short condition on the antenna output or cable. Use the
list below to isolate and repair the problem:
1
Examine that the coaxial cable is connected and in good condition. Do a continuity
check of the center conductor and shield. Examine for a shorted cable.
2
Examine for a intermittent connection in the coaxial cable.
3 Examine the antenna installation if this error code persists. This can be examined
with a VSWR meter. Examine the antenna for opens, shorts, and a resistive ground
plane connection.
(c) Four flashes - This shows a low power condition. This occurs if the output power is below
approximately 33 dBm (2 watts) for the 406.028 MHz signal, or 17 dBm (50mW) for the
121.5 MHz signal. Also this can show that the 406.028 MHz signal is off frequency. For
this error code the ELT must be sent back for repair or replacement.
(d) Five flashes - This shows that the ELT has not been programmed, however this does not
show erroneous or corrupted programmed data.
(e) Six flashes - This shows that the G-switch loop between pins 5 and 12 at the D-sub
connector is not installed. The ELT will not activate during a crash.
1
Do a resistance test to make sure the harness D-sub jumper is installed. There must
be less than 1 ohm of resistance between pins 5 and 12.
(f) Seven flashes -This shows that the ELT battery has too much accumulated operation time
and must be replaced to meet FAA specifications.
Put the BATTERY switch in the OFF position.

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MAINTENANCE MANUAL
ARTEX ME406 EMERGENCY LOCATOR TRANSMITTER SYSTEM

-

MAINTENANCE PRACTICES

1.General
A. This section gives maintenance practices for the emergency locator transmitter (ELT) system.
Components in the ELT system include the ELT, antenna, remote switch, and buzzer.
2.

Emergency Locator Transmitter (ELT) Remova~l/nstallation
A. Rlemove the Emergency Locator Transmitter (ELT) (Refer to Figure 201).
(1) Make sure the MASTER switch is in the OFF position.
(2) Get access to the ELT.
(a) Put a support stand under the tail tiedown ring to support the tailcone. Refer to Chapter 7,
Jacking - Maintenance Practices.
(b) Remove access panel (31 OAR) on the right side of the tailcone. Refer to Access/inspection
Plates - Description and Operation
(3) Keep the ON/ARM switch on the ELT in the ARM position.

CAUTION: Although the ELT is off with the electrical connector removed, the
ELT can be activated if the switch on the front is moved to the ON
position. Be careful not to move the switch to the ON position.
(4) Disconnect the BNC connector (PT1 029) and the electrical connector (PT907) from the ELT.
NOTE:

B.

The ELT is off when the electrical connector is removed from the ELT.

(5) Open the Velcro strap that holds the ELT to the mounting tray.
(6) Remove the ELT from the airplane.
Install the Emergency Locator Transmitter (ELT) (Refer to Figure 201).
NOTE:

The ELT is off when the electrical connector is removed from the ELT.

CAUTION: Although the ELT is off with the electrical connector removed, the ELT
can be activated if the switch on the front is moved to the ON position.
Be careful not to move the switch to the ON position.
(1) Put the ELT in the mounting tray at an angle to engage the lock mechanism at the opposite end
of the ELT.
(2) Push the ELT down into the mounting tray until it is fully installed in the tray.
(3) Connect the Velcro strap that holds the ELT firmly to the mounting tray.
(4) Connect the BNC connector and the electrical connector to the ELT.
(5) Make sure the ONARM switch is in the ARM position.
(6) Complete a functional test of the ELT system to make sure the installation is correct. Refer to
Artex ME406 Emergency Locator Transmitter - Adjustment/Test.
(7) Install access panel (31 OAR) on the right side of the tailcone. Refer to Access/inspection Plates
- Description and Operation
(8) Remove the support stand. Refer to Chapter 7, Jacking - Maintenance Practices.
3.

ELT Buzzer Removal/installation
A.
Remove the ELT Buzzer (Refer to Figure 201).
(1) Get access to the ELT.
(a) Put a support stand under the tail tiedown ring to support the tailcone. Refer to Chapter 7,
Jacking - Maintenance Practices.
(b) Remove access panel (31 OAR) on the right side of the tailcone. Refer to Access/inspection
Plates - Description and Operation
(2) Make sure that the ELT master switch on the ELT transmitter is in the ARM position.

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CESSNA AIRCRAFT COMPANY

MODEL 1821T182
MAINTENANCE MANUAL

SCREW
ROD
ANTENNA
SKIN
~~~
DOUBLER
ASSEMBLY

BNC
CONNECTOR
(PT1 030)

EMERGENCY
LOCATOR
TRANSMITTER

BNC
CONN
(PT1 O'

MOUNTING TRAY

-BRACKET
CABLE

ELECTRICAL
CONNECTOR
(PT907)
BUZZER

DETAIL A

0710T1 001
A0718T 1109

Artex ME406 Emergency Locator Transmitter System Installation
Figure 201 (Sheet 1)

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MAINTENANCE MANUAL

B6583

B

LED

REMC
SWIT(

DETAIL

B

B3940T445
C0718T1 106

Artex ME406 Emergency Locator Transmitter System Installation
Figure 201 (Sheet 2)

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MAINTENANCE MANUAL
(3)
(4)
(5)
(6)
B.

4.

5.

Tag the wires and terminals for identification.
Remove the screws that attach the electrical terminals to the buzzer.
Loosen the black retainer ring on the outboard side of the buzzer.
Remove the buzzer from the bracket.

Install the ELT Buzzer (Refer to Figure 201).
(1) Put the buzzer in the bracket.
(2) Install the black retainer ring on the outboard face of the buzzer.
(3) Remove the tags from the wires and terminals.
(4) Connect the electrical wires to the buzzer with the screws.
(5) Do a check of the ELT system. Refer to Refer to Artex ME406 ELT Functional Test.
(6) Install access panel (31 OAR) on the right side of the tailcone. Refer to Access/Inspection Plates
- Description and Operation
(7) Remove the support stand. Refer to Chapter 7, Jacking - Maintenance Practices.

Remote Switch Removal/Installation
A.

Remove the Remote Switch. Refer to Figure 201.
(1) Remove electrical power from the aircraft.
(2) Get access to the ELT.
(a) Put a support stand under the tail tiedown ring to support the tailcone. Refer to Chapter 7,
Jacking - Maintenance Practices.
(b) Remove the access panel (31 OAR) on the right side of the tailcone. Refer to Access/
Inspection Plates - Description and Operation
(3) Disconnect the electrical connector (PT907) from the ELT.
(4) Remove the screws from the front of the remote switch.
(5) Pull the remote switch from the panel to get to the electrical connector.
(a) Disconnect the connector from the back of the switch.

B.

Install the Remote Switch. Refer to Figure 201.
(1) Connect the electrical connector to the back of the switch.
(2) Put the remote switch into the panel.
(a) Install the screws that attach the switch to the panel.
(3) Connect the electrical connector to the ELT.
(4) Complete a functional test of the ELT system to make sure the installation is correct. Refer to
Artex ME406 Emergency Locator Transmitter - Adjustment/Test.
(5) Install access panel (31 OAR) on the right side of the tailcone. Refer to Access/Inspection Plates
- Description and Operation
(6) Remove the support stand. Refer to Chapter 7, Jacking - Maintenance Practices.

ELT Antenna Removal/Installation
A.

Remove the ELT Antenna (Refer to Figure 201).
(1) Remove the screws that attach the antenna to the fuselage.
(2) Pull the antenna upward from fuselage and disconnect the BNC connector (PT1030) from
antenna.
(3) Remove the antenna from the airplane.
(4) Remove sealant from antenna and airplane.

B.

Install the ELT Antenna (Refer to Figure 201).
(1) Put the antenna near the mounting position and connect the BNC connector (PT1 030) to the
antenna.
(2) Install the screws that attach the antenna to the fuselage.
(3) Make sure that there is a correct electrical bond between the antenna and the airplane structure.
(a) Remove one screw.
(b) With an ohmmeter, measure the electrical resistance from the antenna base metal insert
to the structure at the screw position.
NOTE:

The maximum allowable resistance (in ohms) at each of the four measured
positions is 0.0025.

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MAINTENANCE MANUAL

0

(c)

Install the screw and remove and install each of the remaining screws in turn as you
measure the electrical resistance at each screw hole.
(4) Apply a fillet seal around the antenna with Type I Class B Sealant. Do not cover the screw
head with the sealant. Refer to Chapter 20, Fuel, Weather and High-Temperature Sealing Maintenance Practices.
(5) Do a functional test of the ELT system. Refer to Artex ME406 Emergency Locator Transmitter
- Adjustment/Test.

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MODEL 182/Ti82

MAINTENANCE MANUAL
ARTEX ME406 EMERGENCY LOCATOR TRANSMITTER (ELT) SYSTEM

-

INSPECTION/CHECK

1.

General
A. This section gives the procedures that are necessary to do the inspection and operational checks
necessary to comply with 14 CFR 91.207, for the Artex ME406 Emergency Locator Transmitter (ELT)
System. The system transmits on two frequencies. The 121.5 MHz frequency has the standard swept
tone that rescue personnel can follow to the source. The other frequency is 406.028 MHz and is used
to activate a satellite tracking system. The 406.028 MHz frequency includes other information such as
the country code of the airplane, the aircraft identification beacon serial number, the 24-bit address,
the tail number, or other identification.

2.

Tools and Equipment
A.
For information on tools and equipment, refer to Equipment and Furnishings

3.

-

General.

Artex ME406 Emergency Locator Transmitter (ELT) Inspection
A. Get access to the ELT.
(1) Put a support stand under the tail tiedown ring to support the tailcone. Refer to Chapter 7,
Jacking - Maintenance Practices.
(2) Remove the rear seat. Refer to Rear Seat - Maintenance Practices.
(3) Remove the baggage curtain to get access to the transmitter. Refer to Interior Upholstery Maintenance Practices.
B. Do an inspection of the ELT, mounting tray, antenna, and the ELT battery for condition and correct
installation.
(1) Make sure that the ELT switch, found on the forward end of the ELT. is set to the ARM position.
(2) Remove the ELT from the mounting tray. Refer to Artex ELT ME406 Emergency Locator
Transmitter System - Maintenance Practices.

CAUTION: Do not use solvents to clean the ELT, mounting tray, or electrical
contacts. Solvents used in these areas can cause damage to the
ELT housing.

(3)

Examine the ELT and the mounting tray for correct installation, cleanliness, cracks, or other
damage.
(4) Examine the ELT battery for corrosion.
(5) Look at the battery expiration date.
(a) Make sure that the battery life limit is not expired.
(b) Make sure that the battery expiration date is shown correctly in the Maintenance Records.
NOTE:

The battery manufacturer puts a mark on the battery to show the battery life limit.
When you install a new battery in an ELT, make sure a record of the expiration
date is put in the space given on the ELT name and data plate.

(c) If you have to replace the ELT battery, refer to Artex Maintenance Manual 570-1600.
(d) You must replace the ELT battery with a new battery if one or more of the conditions that
follow occur:
* Use of the ELT battery in an emergency
* Operation for an unknown amount of time
* Use for more than one hour of cumulative time
* Replacement date shown on the battery label has expired.
(e) Record the new battery expiration date in the maintenance log if you replaced it.
(6) Examine the ELT antenna for correct installation and cracks or other damage.
(7) Install the ELT into the mounting tray. Refer to Artex ELT ME406 Emergency Locator Transmitter
System - Maintenance Practices.

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MAINTENANCE MANUAL
(8) Closeout to the lower baggage area (Zone 240). Refer to Airplane Zoning - Description and
Operation.
(a) Install the baggage curtain. Refer to Interior Upholstery - Maintenance Practices.
(b) Install the rear seat. Refer to Rear Seat - Maintenance Practices.
(c) Remove the support stand. Refer to Chapter 7, Jacking - Maintenance Practices.
4.

Artex ME406 Emergency Locator Functional Test
NOTE:
A.

If possible, do the test procedure for the emergency locator transmitter inside a metal hangar
with the doors closed to decrease the signal transmission from the ELT unit during the test.

Do a G-Switch Operational Test:

CAUTION: Operate the Emergency Locator Transmitter (ELT) system only during
the first five minutes of each hour. If you must complete the functional
test at a time other than the first five minutes of the hour, you must do the
test with a direct connection to the ELT and a 30 dB attenuator. Refer to
the FAA Advisory Circular AC-91-44A.
CAUTION: Do not operate the Emergency Locator Transmitter (ELT) for more than
five seconds at a time. Do not operate the ELT again for 15 seconds.
The ELT will transmit a 406.028 MHz distress signal after it is activated
for approximately 50 seconds.
(1) Remove the ELT from the airplane. Refer to Artex ELT ME406 Emergency Locator Transmitter
System - Maintenance Practices.
(2) Install a jumper wire between pins 5 and 12 on the electrical connector of the ELT.

CAUTION: It is recommended that an experienced technician do this procedure
because of the potential physical damage that can occur if the
jumper wire is not installed correctly.
NOTE:

The ELT will not activate with the G-switch unless electrical pins 5 and 12 have a
jumper wire installed between them (this happens automatically when the ELT is
locked into the mount tray with the electrical connector in position).

(3) Make sure the ELT switch is in the ARM position.
(4) Use a receiver set to 121.5 MHz to listen for the aural warning sweep tone.
(5) Hold the ELT transmitter tightly in one hand and make a throwing movement followed by an
opposite movement of the ELT transmitter.
(6) Make sure that the G-switch operates and that the aural warning sweep tone is heard on the
receiver set to 121.5 MHz.
(7) Set the ELT switch to the ON position and then back to the ARM position to reset the G-switch.
(8) Remove the jumper wire from electrical pins 5 and 12 on the electrical connector of the ELT.
(9) Install the emergency locator transmitter in the airplane. Refer to Artex ELT ME406 Emergency
Locator Transmitter System - Maintenance Practices.
B.

Do a Transmitter Test of the Artex ME406 Emergency Locator Transmitter (ELT) System:

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MAINTENANCE MANUAL
CAUTION: Operate the Emergency Locator Transmitter (ELT) system only
during the first five minutes of each hour. If you must complete the
functional test at a time other than the first five minutes of the hour,
you must do the test with a direct connection to the ELT and a 30
dB attenuator. Refer to the FAA Advisory Circular AC-91 -44A.

CAUTION: Do not operate the Emergency Locator Transmitter (ELT) for more

than five seconds at a time. Do not operate the ELT again for 15
seconds. The ELT will transmit a 406.028 MHz distress signal after
it is activated for approximately 50 seconds.

(1) Make sure the BATTERY switch and the AVIONICS switches are in the OFF position.
(2) Connect external electrical power to the airplane.
(3) Make sure that the COM/NAV 1 and AUD/MKR circuit breakers on the circuit breaker panel are
engaged.
(4) Set the BATTERY switch to the ON position.
(5) Set the AVIONICS switches to the ON position.
(6) Remove the ELT from the airplane. Refer to Artex ELT ME406 Emergency Locator Transmitter
System - Maintenance Practices.
(7) Make sure that the ELT remote switch on the right panel is in the ARM position.
(8) Set one of the communication units to receive a frequency of 121.5 MHz.
(9) Set the communication unit to the airplane speakers at an audio level loud enough to be heard.
NOTE:

The SARSAT tester is used as an example to gather test information. However, other
equivalent test equipment such as the Aeroflex IFR 4000 Communications Test Set
is acceptable.

(110) Have another person use the SARSAT tester set to the RECV function. Refer to Figure 601.
NOTE:

The SARSAT tester must be less than 15 feet from the ELT antenna and must have
a line-of-sight between the ELT antenna and SARSAT tester.

NOTE:

The person with the SARSAT tester must make sure that the ELT buzzer is heard
during the test.

NOTE:

If it is necessary to do the transmitter test after the first five minutes of the hour, the
SARSAT tester is connected directly to the ELT with a coaxial cable and a 30 dB
attenuator. You will not hear the sweep tone from the ELT on the airplane speakers
with the attenuator installed.

(11)

Install the 30 dB attenuator between the ELT and SARSAT tester if necessary (Refer to Figure
601).
(12) Set the ELT remote switch on the right panel to the ON position.
(13) Let the ELT make three sweeps on the airplane speakers.
NOTE:

This will take one second. The ELT remote switch will start to flash.

(14) Set the ELT remote switch back to the ARM position and monitor the LED.
NOTE:

The ELT will do a self-test. The LED will stay on for one second and the ELT sweeps
are not audible on the airplane speakers if the ELT operation is normal.

NOTE:

The ELT does not transmit a 406.028 MHz test signal to the SARSAT tester until the
ELT remote switch is set back to the ARM position.

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MAINTENANCE MANUAL
(15) If the LED continues to flash, refer to Artex ME406 Emergency Locator Transmitter System Troubleshooting.
(16) If the SARSAT tester did not receive a 406.028 MHz signal and the ELT remote switch LED does
not show a transmitter problem, do the test again.
(17) When the SARSAT tester receives a 406.028 MHz signal, scroll the pages on the tester and
make sure of the information that follows:
(a) Make sure the information shown by the SARSAT tester agrees with the placard on the
ELT.
NOTE:

The information that follows must match the data on the ELT placard:

* COUNTRY code
* 15-dligit Hex code ID
* Aircraft identification number.
(b) Mlake sure that the SARSAT tester shows the messages that follow:
* S TEST OK
* Frequency - PASS
* Homing frequency
* Message format (short).
NOTE:

When ownership of an aircraft is transferred within the same country, the ME406 ELT
should be reregistered with the applicable authority. When an aircraft with a ME406
ELT changes tail number or country registration, the ELT will need to have the new
identification data entered. The ELT will also need to be registered with the applicable
authority.

(18) Install the bolts, tiedowns, and plastic closeout to the lower baggage area (Zone 240). Refer to
Airplane Zoning - Description and Operation.

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MAINTENANCE MANUAL

.1-

ELT

BNC
CONNECTION
TO ANTENNA

DETAIL

A

LIFT THE DOOR TO GET
ACCESS TO THE CONTRA!3T
KNOB ADJUSTMENT
CLEAR

CAP

NRUM

a

+

0~~11-

E~JDL
WW

FPA1E

COVER
0710T1001
A2618T1 109
6618T1 379

Artex ME406 Emergency Locator Transmitter (ELT) SARSAT Test Set-up
Figure 601 (Sheet 1)

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MODEL 1821T 182

MAINTENANCE MANUAL

A64137

COAXIAL
SARSAT

COAXIAL CABLE
TO ELT

ATTACHES TO ELT

661 8T1380

Artex ME406 Emergency Locator Transmitter (ELT) SARSAT Test Set-up
Figure 601 (Sheet 2)

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MODEL 182/Ti82

MAINTENANCE MANUAL
CARBON MONOXIDE DETECTOR

-

MAINTENANCE PRACTICES

1.

General
A. The carbon monoxide (CO) detector is installed on Airplanes 182081742 and On and Airplanes
Ti 82008481 and On that have the Garmin G 1000.
B. The CO detector detects, measures, and gives an alert to the crew before the cockpit level of CO
reaches a critical level. The CO data is displayed and controlled through the CO detector RS232
interface with the multi-function display (MFD).

2.

Carbon Monoxide Detector Removal/installation
A.
Carbon Monoxide Detector Removal (Refer to Figure 201).
(1) Put the AVIONICS MASTER switch in the off position.
(2) Remove the MED from the copilot side of the instrument panel. Refer to Chapter 34, Control
Display Unit - Maintenance Practices.
(3) Disconnect the electrical connector (P1903) from the CO detector.
(4) Remove and keep the three screws and three washers that connect the CO detector to the
avionics support structure.
(5) Remove the CO detector from the airplane.
B. Carbon Monoxide Detector Installation (Refer to Figure 201).
(1) Put the CO detector in position on the avionics support structure.
(2) Attach the CO detector to the structure with the three kept screws and three kept washers.
(3) Connect the electrical connector (P1 903) to the CO detector.
(4) Install the MED on the copilot side of the instrument panel. Refer to Chapter 34, Control Display
Unit - Maintenance Practices.
(5) Put the AVIONICS MASTER switch in the ON position.
(6) On the primary flight display (PFD), do a check to make sure that the CO detector operates
correctly.

I

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MAINTENANCE MANUAL

BATTERY
TRAY
ASSEMBLY
R
CARBON
MONOXIDE
DETECTOR

AVIONICS
SUPPORT
STRUCTURE

DETAIL

A

LOOKING FORWARD AT ES 17.00
AIRPLANES THAT HAVE GARMIN G1 000
071 OT1001
A071ST1 095

Carbon Monoxide Detector Installation
Figure 201 (Sheet 1)

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CESSNA AIRCRAFT COMPANY

MODEL 182fT182
MAINTENANCE MANUAL
SOUNDPROOFING AND INSULATION - MAINTENANCE PRACTICES
1.

General
A.

The airplane utilizes soundproofing and insulation throughout the fuselage area. This material is glued
into place using spray adhesive. Any time old material is being replaced, care should be taken to
ensure all traces are removed from fuselage skin before reapplication. For a list of spray adhesives,
refer to Equipment/Furnishing - General.

B.

For an illustration of soundproofing and insulation locations, refer to Figure 201 and Figure 202.

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MAINTENANCE MANUAL

SOUNDPROOFING

DETAIL A

0710T1001
A0719T2001

Soundproofing Installation
Figure 201 (Sheet 1)

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MAINTENANCE MANUAL

DETAIL

A

0710T1001
A0719T3003

Insulation Installation
Figure 202 (Sheet 1)

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CHAPTER

FIRE PROTECTION

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

LIST OF EFFECTIVE PAGES
CHAPTER-SECTION-SUBJECT

PAGE

DATE

26-Title
26-List of Effective Pages
26-Record of Temporary Revisions
26-Table of Contents
26-00-00

Page 1

April 1/2002

26-20-00

Pages 1-2

April 1/2002

26 - LIST OF EFFECTIVE PAGES
© Cessna Aircraft Company

Page 1 of 1
Mar 1/2005

RECORD OF TEMPORARY REVISIONS
Temporary Revision
Number

Page Number

Issue Date

By

Date Removed

By

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

CONTENTS
FIRE PROTECTION - GENERAL..................................................

Scope and Definition ........................................................
HAND FIRE EXTINGUISHER - DESCRIPTION AND OPERATION ...................
Description and Operation ...................................................

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26-00-00 Page 1
26-20-00 Page 1
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CONTENTS
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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
FIRE PROTECTION - GENERAL
1.

Scope and Definition
A.

This chapter contains a single section which describes the portable fire extinguisher used in the cabin.

26-00-00
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MAINTENANCE MANUAL
HAND FIRE EXTINGUISHER - DESCRIPTION AND OPERATION
1.

Description and Operation
A.

A portable, hand operated fire extinguisher is mounted on the floor between the pilot and copilot
seats for use in the event of a fire. The extinguishing agent is Halon 1211 and may be used on
solid combustible, electrical or liquid fires. Servicing of the extinguisher can be handled by most
fire equipment dealers. The fire extinguisher is mounted within a quick release, clamp type bracket
assembly. (Refer to Figure 1).

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MODEL 182/T182

MAINTENANCE MANUAL

FIRE

LOT SEAT

'MOUNTING BRACKET
DETAIL

B

0710T1001
A0514T1004
B0578T1001

Fire Extinguisher Installation
Figure 1 (Sheet 1)

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CHAPTER

FLIGHT CONTROLS

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82
MAINTENANCE MANUAL

LIST OF EFFECTIVE PAGES
CHAPTER-SECTION-SUBJECT

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27
© Cessna Aircraft Company

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LIST OF EFFECTIVE PAGES

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CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82
MAINTENANCE MANUAL

CONTENTS
27-00-00
27-00-00
27-00-00
27-00-00

FLIGHT CONTROLS - GENERAL .........................
General...................................
Tools, Equipment and Materials........................
Definition ..................................

Page
Page
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Page

1
1
1
1

AILERON CONTROL SYSTEM - TROUBLESHOOTING...............
General...................................
AILERON CONTROL SYSTEM - MAINTENANCE PRACTICES............
General.......
Control Wheel Removal/Installation ......................
Pilot Control Column Removal/Installation ...................
Copilot's Control Column Removal/Installation .................
Aileron Removal/installation..........................
Aileron Bell Crank Removal/installation ....................
Adjustment/Test ...............................
RUDDER CONTROL SYSTEM - TROUBLESHOOTING ...............
General...................................

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RUDDER CONTROL SYSTEM - MAINTENANCE PRACTICES............
General...................................
Rudder Pedal Assembly Removal/Installation..................
Rudder Removal/installation .........................
Rudder Control Cables Removal/installation ..................
Rudder Control Adjustment/Test........................

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RUDDER TRIM - TROUBLESHOOTING ......................
General...................................
RUDDER TRIM CONTROL SYSTEM - MAINTENANCE PRACTICES.........
General...................................
Rudder Trim System Removal/Installation ...................
Rudder Trim Adjustment/Test.........................

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ELEVATOR SYSTEM - TROUBLESHOOTING....................
General...................................

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ELEVATOR CONTROL SYSTEM - MAINTENANCE PRACTICES...........
General ..................................
Forward Elevator Bell Crank Removal/Installation................
Aft Elevator Arm Assembly Removal/Installation ................
Elevator Control Adjustment/Test .......................

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ELEVATOR TRIM CONTROL - TROUBLESHOOTING................
General...................................

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ELEVATOR TRIM CONTROL - MAINTENANCE PRACTICES.............
General...................................
Trim Tab Actuator Removal/Installation.....................
Trim Tab Actuator Disassembly/Assembly ...................
Trim Tab Actuator Cleaning and Inspection ........
..........
Trim Tab Free Play Inspection.........................
Trim Tab Control Cables and Pulleys Removal/installation............
Trim Tab Control Wheel Removal/installation..................
Trim Tab Control Adjustment/Test .......................

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CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82

MAINTENANCE MANUAL
STALL WARNING SYSTEM - MAINTENANCE PRACTICES .............
General .....................
.............
Stall Warning Horn Assembly Removal and Installation .............
Stall Detector Removal and Installation ....................
Stall Detector Adjustment...........................

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FLAP CONTROL SYSTEM - TROUBLESHOOTING.................
General...................................

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FLAP CONTROL SYSTEM - MAINTENANCE PRACTICES..............
General...................................
Flap Motor and Transmission Assembly Removal/installation ..........
Flap Removal/Installation...........................
Flap Drive Pulley Removal/Installation.....................
Flap Control System Adjustment/Test .....................

27-50-00
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206
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FLAP FOLLOW-UP AND INDICATING SYSTEM - MAINTENANCE PRACTICES.
General...................................
Flap Follow-Up and Indicating System Removal/Installation ...........
Flap Follow-Up and Indicating System Adjustment/Test .............

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27 - CONTENTS
© Cessna Aircraft Company

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

FLIGHT CONTROLS - GENERAL
1.

General
A.

2.

This chapter provides maintenance of components which furnish a means of manually controlling the
flight attitude characteristics of the airplane, including flaps.

Tools, Equipment and Materials
NOTE:

Equivalent substitutes may be used for the following items:

NAME

NUMBER

MANUFACTURER

USE

Tensiometer

T52002101

Pacific Scientific
Electro Kinetics Div.
402 E. Guitierrez St.
Santa Barbara, CA
93102

To measure and obtain
cable tension.

Inclinometer

SE716

Cessna
Aircraft
Company
Cessna
Parts
Distribution
Department 701, CPD
25800 East Pawnee
Road
Wichita, KS
67218-5590

To measure control
surface travel.

Polyurethane Tape

Y8761

3M
3M Center
Minneapolis, MN 55144

To prevent flap chafing.

3.

Definition
A.

This chapter is divided into sections and subsections to assist maintenance personnel in locating
specific systems and information. The following is a brief description of each section. For locating
information within the chapter, refer to the Table of Contents at the beginning of the chapter.
(1) The aileron section provides information on control wheels, cables, linkage and aileron
assemblies.
(2) The rudder section provides information on rudder pedals, cables, linkage and rudder assembly.
(3) The elevator section provides information on control column, cables, linkage and elevator
assemblies.
(4) The flap section provides information on the flap actuator, cables, linkage, and the flap
assemblies.

27-00-C10
© Cessna Aircraft Company

Page 1
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
AILERON CONTROL SYSTEM - TROUBLESHOOTING
1.

General
A.

A troubleshooting chart has been developed to aid the maintenance technician in system
understanding. Refer to Figure 101.

27-1 0-00
© Cessna Aircraft Company

Page 101
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

B1163

LOST MOTION IN
CONTROL ARM

CONTROL WHEELS
NOT LEVEL WITH
AILERONS NEUTRAL.

CHECK FOR LOOSE CABLES
IN HIGH OR LOW
TENSION LOOPS. IF -

IMPROPER ADJUSTMENT
OF CONTROL CABLES. IF -

I

I

OK, CHECK FOR
BROKEN PULLEYS,
PULLEY BRACKETS
OR PUSHROD
BEARINGS. IF-

NOT OK, CHECK
CABLE TENSION.
ADJUST AS
NECESSARY.

OK, CHECK FOR
ANY CABLES OFF
OF PULLEYS
AND REINSTALL
AS NECESSARY.
CHECK CABLE
TENSION.

NOT OK, REPLACE
WORN OR BROKEN
PARTS AS
NECESSARY.

OK, IMPROPER
ADJUSTMENT
OF PUSH-PULL
ROD, ADJUST.

NOT OK, CHECK
FOR PROPER
CABLE
ADJUSTMENT.

Aileron System Troubleshooting Chart
Figure 101 (Sheet 1)

27-10-00
© Cessna Aircraft Company

Page 102
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1164

RESISTANCE TO CONTROL
WHEEL MOVEMENT

CHECK FOR EXCESSIVE CABLE
TENSION. IF-

I

I
OK, CHECK FOR PULLEY
BINDING OR CABLE OFF
OF PULLEY. IF-

NOT OK, ADJUST CABLE
TO PROPER TENSION.

OK, CHECK CLEVIS BOLTS IN
SYSTEM FOR EXCESSIVE
TENSION. IF-

NOT OK, REPLACE DEFECTIVE
PULLEY OR INSTALL CABLE ON
PULLEY. CHECK CABLE TENSION.

OK, CHECK FOR BINDING OR
DAMAGED BELLCRANK. IF -

NOT OK, LOOSEN CLEVIS BOLTS
AND TIGHTEN PROPERLY.

OK, CHECK QUADRANT
ASSEMBLY. CHECK
VISUALLY. REPLACE
DEFECTIVE QUADRANT.

NOT OK, REPLACE BELLCRANK
OR LUBRICATE BELLCRANK
BEARINGS.

Aileron System Troubleshooting Chart
Figure 101 (Sheet 2)

27-10-00
© Cessna Aircraft Company

Page 103
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
AILERON CONTROL SYSTEM - MAINTENANCE PRACTICES
1.

General
A.
B.

C.

2.

The ailerons receive the input from the pilot or copilot control wheel. The torque tubes, bearings,
cable quadrants, pulleys, cables, bell cranks, and pushrods help to supply the input to the ailerons.
When you turn the control wheel, the four bearing roller assemblies on the end of the control wheel
tube turn. This turns a square control tube assembly inside of and extending from the control wheel
tube. Attached to the square tube is a quadrant that operates the aileron system. The aileron system
is controlled by the two control wheels. The interconnect cables, turnbuckle, and adjustment terminals
give synchronized control to the two control wheels. The forward end of the square control tube is
installed in a bearing block on the firewall. It rotates with the control wheel and does not move in a
fore-and-aft direction.
As the control wheel moves in a fore-and-aft direction, the four bearing roller assemblies on the end
of the control wheel tube decrease the friction. Bearings in the sleeve assembly let the control wheel
tube turn. The sleeve assembly is attached to the control wheel tube by a sleeve and a retaining
ring. The sleeve moves in a fore-and-aft direction with the control wheel tube. The movement lets
the push-pull tube attached to the sleeve assembly operate an elevator arm assembly. One elevator
cable is attached to the elevator arm assembly. A torque tube connects one arm assembly to the other
arm assembly on the opposite end of the torque tube, where the other elevator cable is attached. The
pilot and copilot control wheels are both linked to the aileron and elevator control systems when dual
controls are installed.

Control Wheel Removal/Installation
NOTE:

3.

The pilot and copilot control wheel removal/installation is typical.

A.

Control Wheel Removal (Refer to Figure 201).
(1) Disconnect the electrical connector from the control wheel.
(2) Remove the screws that attach the control wheel to the control tube.
(3) Remove the control wheel.

B.

Control Wheel Installation (Refer to Figure 201).
(1) Attach the control wheel to the control tube with the screws.
(2) Connect the electrical connector to the control wheel.

Pilot Control Column Removal/Installation
A.

Control Column Removal (Refer to Figure 201).
(1) Remove the control wheel. Refer to Control Wheel Removal/Installation.
(2) Remove the glide plug.
(3) Disconnect the push-pull tube at the sleeve assembly.
(4) Remove the screws from the collar at the instrument panel.
(5) Remove the pilot's center instrument panel. Refer to Chapter 31, Instrument And Control Panels
- Maintenance Practices.
(6) To help remove the control wheel tube, remove the snap ring from its locking groove to permit
more movement of the sleeve assembly.
(7) Carefully pull the control wheel tube aft and work it out through the instrument panel.
(a) If removal of control tube assembly is necessary, go to step 3.A.(8).
(8) Remove the access plates 520AB and 620AB. Refer to Chapter 6, Access/Inspection Plates Description and Operation.
(9) Remove the safety clips from the turnbuckles at the direct cable, and loosen the tension.
(10) Remove and discard the safety wire from the turnbuckle at the interconnect cable, and loosen
the tension.
(11) Remove and discard the safety wire from the roll pin in the quadrant and the control tube
assembly.
(12) Remove the roll pin installed in the quadrant and the control tube assembly.

27-10-00
© Cessna Aircraft Company

Page 201
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

CABLE GUARD
'ULLEY

DETAIL B

CABLE
GUARD
.

H
TURNBUCKLE

C

D
E

CARRY-THRU
CABLE

F
G

B

F

D

COTTER PIN

DETAIL

A

TURNBUCKLE
DIRECT CABLE

PULLEY

CABLE
GUARD
DETAIL

CABLE
GUARD

F

PULLEY

DETAIL D

E

DETAIL
Aileron Control System Installation
Figure 201 (Sheet 1)

27-10-00
©Cessna Aircraft Company

0710T1001
A0763R1014
B0763R1019
C0763R1018
D0763R1015
E0763R1016

Page 202
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

CONTROL TUBE
ASSEMBLY

B1166

0.002 INCH

RETAINER
BEARING

SLEEVE
ASSEMBLY
WHEEL TUBE

VIEW A-A
A'

CABLE
GUARD

BE

BEARING
BLOCK

CABLE
GUARD

DIFFERENT
E USED
N
-A.

FIREWALL
I

UM
IITTED
BEARING
BLOCK
ASSEMBLY

QUADRANT

DETAIL

GER

AFTER

G

G0763R1021

Aileron Control System Installation
Figure 201 (Sheet 2)

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© Cessna Aircraft Company

Page 203
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1167

RUBBER GROMM

CABLE ASSEMBLY
DETAIL
BOLT

H

BOLT

BUSHING
CARRY-THRU
CABLE

BUSHING

B

BRASS

BRASS WASHER
DIRECT CABLE

DETAIL J

H0760R 1001
J0763R1012

Aileron Control System Installation
Figure 201 (Sheet 3)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1422

AILERON

A

0

DETAIL

A

AILERON HINGE

05611014
A05611015

Aileron Control System Installation
Figure 201 (Sheet 4)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
(13) Remove the cotter pin, nut, and washer from the center of the bearing block assembly.
NOTE:

The control tube goes through the center of the bearing block assembly.

(14) Carefully pull the control tube assembly in the aft direction.
(15) Remove the quadrant.
B.

Control Column Installation (Refer to Figure 201).
NOTE:
(1)
(2)
(3)
(4)
(5)
(6)
(7)
(8)
(9)
(10)

If the control tube assembly was not removed, go to step 3.B.(4).

Install the control tube assembly through the instrument panel.
Install the control tube assembly through the quadrant and the firewall.
Install the roll pin through the quadrant and the control tube assembly.
Safety the roll pin with wire. Refer to Chapter 20, Safetying - Maintenance Practices.
Install the washer, locknut, and cotter pin to the control tube assembly that goes through the
bearing block on the forward side of the firewall. There must be 0.03- inch minimum clearance
between the bearing block and the nut after they are tightened.
Install the snap ring to the sleeve assembly.
Attach the push-pull tube to the sleeve assembly.
Install the center instrument panel. Refer to Chapter 31, Instrument and Control Panels Maintenance Practices.
Install the collar, plug, and glide.
Adjust the control column for free play.
(a) Tighten the screw to remove lateral free play in the control column. Do not tighten the
screw too much.
NOTE:

If the screw is too tight, friction in the fore and aft direction in the full range of
the elevator control travel will result.

(b) Do not leave the screw loose when you adjust the drag. The adjustment is equal to a typical
wheel bearing adjustment. For example, tighten the screw until all free play is removed
and you feel drag. Loosen the adjustment screw about 1/8th of a turn for each step until
there is minimum free play and no drag is felt.
(11) Install the control wheel.
(12) Install the access plates 520AB and 620AB. Refer to Chapter 6, Access/Inspection Plates Description and Operation.
(13) Rig the aileron control system. Refer to the Adjustment/Test.
4.

Copilot's Control Column Removal/Installation
A.

Control Column Removal (Refer to Figure 201).
(1) Remove the control wheel. Refer to Control Wheel Removal/Installation.
(2) Remove the glide plug.
(3) Disconnect the push-pull tube at the sleeve assembly.
(4) Remove the screws from the attach plate at the instrument panel.
(5) Remove the copilot instrument panel. Refer to Chapter 31, Instrument and Control Panels Maintenance Practices.
(6) To help remove the control wheel tube, remove the snap ring from its locking groove for more
movement of the sleeve assembly.
(7) Carefully pull the control wheel tube aft and work it out through the instrument panel.
(a) If removal of control tube assembly is necessary, go to step 4.A.(8).
(8) Remove the access plates 520AB and 620AB. Refer to Chapter 6, Access/Inspection Plates Description and Operation.
(9) Remove the safety clips from the turnbuckles at the direct cable, and loosen the tension.
(10) Remove and discard the safety wire from the turnbuckle at the interconnect cable, and loosen
the tension.
(11) Remove and discard the safety wire from the roll pin in the quadrant and the control tube
assembly.

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
(12) Remove the cotter pin, nut, and washer from the control tube assembly that is attached to the
forward side of the firewall.
NOTE:

B.

The control tube assembly goes through the bearing block assembly on the forward
side of the firewall.

(13) Carefully pull the control tube assembly aft and remove the quadrant.
(14) Remove the radios and related equipment as necessary to work the control wheel tube assembly
out from under the instrument panel.
Control Column Installation (Refer to Figure 201).
(1) Install the control tube assembly through the instrument panel.
(2) Install the control tube assembly through the quadrant and the firewall.
(3) Install the roll pin through the quadrant and the control tube assembly.
(4) Safety the roll pin with wire. Refer to Chapter 20, Safetying - Maintenance Practices.
(5) Install the washer, locknut, and cotter pin to the control tube assembly that comes through the
bearing block on the forward side of the firewall. There must be 0.03-inch minimum clearance
between the bearing block and the nut after they are tightened.
(6) Install the snap ring to the sleeve assembly.
(7) Connect the push-pull tube to the sleeve assembly.
(8) Install the instrument panel. Refer to Chapter 31, Instrument and Control Panels - Maintenance
Practices.
(9) Install the collar and the glide plug.
(10) Adjust the control column for free play.
(a) Tighten the screw to eliminate lateral free play in the control column. Do not tighten the
screw too much.
NOTE:

(11)
(12)
(13)
(14)
5.

If the screw is too tight, friction in the fore and aft direction in the entire elevator
control travel will result.

(b) Do not leave the screw loose when you adjust the drag. The adjustment is equal to a typical
wheel bearing adjustment. For example, tighten the screw until all free play is removed
and you feel drag. Loosen the adjustment screw about 1/8th of a turn for each step until
there is minimum free play and no drag is felt.
Install the control wheel.
Install the radios and related equipment that you removed.
Install the access plates 520AB and 620AB. Refer to Chapter 6, Access/Inspection Plates Description and Operation.
Rig the aileron control system. Refer to the Adjustment/Test.

Aileron Removal/Installation
A.

Aileron Removal (Refer to Figure 201).
(1) Disconnect the aileron pushrod at the aileron.
(2) Disconnect the electrical bonding straps.
(3) Remove the screws and the nuts that attach the aileron hinges to the trailing edge of the wing.
(4) Carefully pull the aileron out and down to slide the hinges from under the wing skin and the
auxiliary spar reinforcements.

B.

Aileron Installation (Refer to Figure 201).
(1) Put the aileron hinges between the skin and the auxiliary spar reinforcements.
(2) Install the screws and the nuts that attach the hinges to the trailing edge of the wing.
(3) Connect the electrical bonding straps.
(4) Attach the aileron pushrod to the aileron.
(5) Check the aileron travel. Refer to the Adjustment/Test.

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

6.

Aileron Bell Crank Removal/Installation
NOTE:
A.

The left and the right aileron bell crank removal/installation is typical.

Aileron Bell Crank Removal (Refer to Figure 201).
(1) Remove the access plates 520AB, 520BB, 620AB, and 620BB located inboard of the bell crank
on the bottom of each wing. Refer to Chapter 6, Access/Inspection Plates - Description and
Operation.
(2) Remove the safety clip from the turnbuckle at the carry-thru cable.
(3) Loosen the control cable tension at the turnbuckle.
(4) Disconnect the control cables from the bell crank.
(5) Remove the safety clip from the turnbuckle at the direct cable.
(6) Loosen the control cable tension at the turnbuckle.
(7) Disconnect the control cables from the bell crank.
(8) Disconnect the aileron pushrod at the bell crank.
(9) Remove the nuts, washers, and bolts from the bell crank stop bushing and from the bell crankto-wing structure.
(10) Remove the bell crank through the access opening. Make sure that the bearing bushing is not
dropped from the bell crank.
CAUTION: Use tape on the open ends of the bell crank to prevent dust and dirt
from going into the bell crank needle bearings.
(11) Use brass washers as shims between the lower end of the bell crank and the wing structure.
Keep the shims.

B.

7.

Aileron Bell Crank Installation (Refer to Figure 201).
(1) Install the bell crank to the structure. Make sure that the bushings are in the correct position.
(2) Install the brass washers between the lower end of the bell crank and the wing channel to remove
unwanted clearance.
(3) Install the bell crank pivot bolt.
(4) Put the bell crank stop-bushing in position and install the bolt.
(5) Attach the aileron pushrod to the bell crank.
(6) Attach the control cables to the bell crank. Make sure that the spacers and the bushings are
correctly installed.
(7) Rig the aileron system. Refer to the Adjustment/Test.
(8) Install the safety clips on the turnbuckles. Refer to Chapter 20, Safetying - Maintenance
Practices.
(9) Install the access plates 520AB, 520BB, 620AB, and 620BB. Refer to Chapter 6,
Access/Inspection Plates - Description and Operation.

Adjustment/Test
WARNING: After the rigging is completed, make sure that the ailerons move in
the correct direction when operated by the control wheel.
A.

Rig the Aileron Cables (Refer to Figure 201, Figure 202, and Figure 203).
(1) Remove the safety clips and loosen the tension from the turnbuckles at the direct and the carrythru cables at the bell cranks in the wings.
(2) Disconnect the push-pull rods at the bell cranks.
(3) Remove the safety clip from the turnbuckle at the interconnect cable.
(4) Adjust tension on the interconnect cable to 40 pounds, +10 or -10 pounds (177.93 N, +44.48 or
-44.48 N) at 70 °F (21 °C). Refer to the Charts in Figure 203 for the correct tensions at other
temperatures.
(5) Put the control wheels in a level position and tape a bar across both control wheels to hold them
in position.

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© Cessna Aircraft Company

Page 208
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1168

TOOL NUMBER SE716

0780T1001

Inclinometer for Measuring Control Surface Travel
Figure 202 (Sheet 1)

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© Cessna Aircraft Company

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

7A

TE
AIU

z

30

20
10
0

II11

I" 0

-40 -30 -20 -10

10

20 30 40 50 60
DEGREES FAHRENHEIT

70

BO

80.

0

100 110

--ir

YYW

77

300

I I

II

tI
Al
250
00.
z
i

150

9

100
{

50 -

0-

TMl
-40

35 -30 .25 -20 -15 .10 -5
0
5
10
DEGREES CELSIUS

15

20

25

30

35

40

Aileron Cable Tension
Figure 203 (Sheet 1)

,

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MAINTENANCE MANUAL
(6) Adjust the direct and carry-thru cable turnbuckles to center the position of the bell crank stop
bushings in the slots. The tension on the carry-thru cable must be 40 pounds, +10 or -10 pounds
(177.93 N, +44.48 or -44.48 N) at 70 °F (21 °C). Refer to the Charts in Figure 203 for the correct
tensions at other temperatures. Disregard the tension on the direct cables.
(7) Adjust the push-pull rods at each aileron until the ailerons are neutral with reference to trailing
edge of wing flaps. Make sure that the wing flaps are in the full UP position when you make this
adjustment.
(8) With the ailerons in the neutral position (streamlined), mount an inclinometer on the trailing edge
of one aileron and set it to 0 degrees.
(9) Remove the bar from the control wheels. If travel is not within limits, readjust push-pull rods and
cables as necessary.
(10) Check the aileron travel which must be 20 degrees +2 or -2 degrees up and 15 degrees, +2 or
-2 degrees down.
(11) Make sure that the safety clips are correctly installed in all turnbuckles. Refer to Chapter 20,
Safetying - Maintenance Practices.
(12) Make sure that the cables and the cable guards are correctly installed, all jam nuts are tight, and
all items removed for access are installed.

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MAINTENANCE MANUAL
RUDDER CONTROL SYSTEM - TROUBLESHOOTING
1.

General
A.

A troubleshooting chart has been developed to aid the maintenance technician in system
understanding. Refer to Figure 101.

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MODEL 182/T182

MAINTENANCE MANUAL

B1169

BINDING OR JUMPY MOVEMENT
OF RUDDER PEDALS.

CHECK FOR EXCESSIVE CABLE TENSION.
IF-

OK, CHECK FOR CABLES NOT RIDING
PROPERLY ON PULLEYS. IF -

NOT OK, ADJUST CABLE
TENSION AS NECESSARY.

OK, CHECK FOR BINDING OR
DEFECTIVE PULLEYS. IF -

NOT OK, PROPERLY ROUTE
CABLES OVER PULLEYS.

OK, CHECK RUDDER BARS
FOR LUBRICATION. IF -

NOT OK, LUBRICATE OR REPLACE
DEFECTIVE PULLEYS.

I
OK, CHECK FOR DEFECTIVE TENSION
RUDDER BAR BEARINGS. IF -

NOT OK, LUBRICATE
RUDDER BARS.

OK, CHECK FOR OVER TIGHT
CLEVIS BOLTS. IF-

NOT OK, LUBRICATE BEARINGS
OR REPLACE BEARING BLOCKS.

OK, CHECK FOR IMPROPER NOSE
WHEEL STEERING ADJUSTMENT.
RE-RIG AS NECESSARY.

NOT OK, ADJUST CLEVIS
BOLTS AS NECESSARY.

Rudder System Troubleshooting Chart
Figure 101 (Sheet 1)

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MAINTENANCE MANUAL

B1170

RUDDER DOES NOT
RESPOND TO
PEDAL MOVEMENT.

LOST MOTION BETWEEN
RUDDER PEDALS AND
RUDDER.

CHECK FOR BROKEN OR
DISCONNECTED CABLE,
REPLACE OR CONNECT
CABLE.

CHECK FOR INSUFFICIENT
CABLE TENSION. ADJUST
CABLE TENSION AS NECESSARY.

Rudder System Troubleshooting Chart
Figure 101 (Sheet 2)

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MODEL 182/T182
MAINTENANCE MANUAL
RUDDER CONTROL SYSTEM - MAINTENANCE PRACTICES
1.

General
A.

2.

Conventional rudder pedals control the rudder and the nose wheel steering. The rudder control system
has rudder pedals, torque tubes, bearings, a centering bungee, bell crank, cables, and pulleys, all of
which link the pedals to the rudder and the nose wheel steering.

Rudder Pedal Assembly Removal/Installation
A.

Rudder Pedal Assembly Removal (Refer to Figure 201).
(1) Remove the crew seats. Refer to Chapter 25, Front Seats and Rails - Maintenance Practices.
(2) Remove the pedestal cover, carpet, and rudder shield assemblies. Refer to Chapter 25,
Equipment/Furnishings - General.

(3)
(4)
(5)
(6)
(7)
(8)
(9)
(10)
(11)

Disconnect the master cylinders at the pilot rudder pedals.
Disconnect the parking brake cables at the master cylinders.
Remove the rudder pedals and the brake links.
Remove the fairings (340AL and 340AR) for access to the rudder cable turnbuckles. Refer to
Chapter 6, Access/Inspection Plates - Description and Operation.
Remove the safety clips from the turnbuckles and relieve cable tension.
Disconnect the right forward and the left forward cables from the rudder bar arms.
Disconnect the nose gear steering pushrods from the rudder bar arms.
Remove the bolts that attach the bearing blocks and the rudder bars that are found under the
instrument panel.
Remove the bearing blocks and the rudder bars.
NOTE:

B.

The two inboard bearing blocks have clearance holes for the rudder bars at one end
and a bearing hole at the other. Label these bearing blocks for reference when you
install them.

Rudder Pedal Assembly Installation (Refer to Figure 201).
(1) Lubricate the rudder bar assemblies. Refer to Chapter 12, Flight Controls - Lubrication.
(2) Position the rudder bars in the area below the instrument panel and attach the bearing blocks
with the bolts.
(3) Connect the nose gear steering pushrods to the rudder bar arms.
(4) Connect the left forward and the right forward cables to the rudder bar arms.
(5) Install the rudder pedals and the brake links.
(6) Connect the parking brake cables at the master cylinders.
(7) Connect the master cylinders at the pilot rudder pedals.
(8) Rig the rudder system. Refer to Rudder Control Adjustment/Test.
(9) Install the safety clips.
(10) Install the crew seats. Refer to Chapter 25, Front Seats and Rails - Maintenance Practices.
(11) Install the pedestal cover, carpet, and rudder shield assemblies. Refer to Chapter 25,
Equipment/Furnishings - General.

(12) Install the fairings (340AL and 340AR). Refer to Chapter 6, Access/Inspection Plates Description and Operation.
3.

Rudder Removal/Installation
A.

Rudder Removal (Refer to Figure 201).
(1) Remove the stinger.
(2) Disconnect the tail navigation light quick-disconnect (JV001) at the bottom of the rudder.
(3) Remove the fairing from the two sides of the vertical fin.
(4) Remove the safety wire from the turnbuckles.
(5) Loosen the turnbuckles to remove cable tension.
(6) Disconnect the cables from the rudder bell crank.
(7) With the rudder supported, remove the hinge bolts.
(8) Remove the electrical bonding strap.
(9) Carefully lift the rudder away from the vertical fin.
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MODEL 182/T182

MAINTENANCE MANUAL

GUARD

CABLE

PULLEY

B

DETAIL

TURNBUCKLE

C

PULLEY

TURNBUCKLE
DETAIL

E

M
E

CABLE
GUARD

DETAIL

A
BELL CRANK

RIGHT
CABLE

STOP BOLT

DETAIL C

LEFT AFT
CABLE

0710T1001

A0763T2004
B0763T1022
C0763T1023
D0763T2006
E0763T1025

Rudder Control System Installation
Figure 201 (Sheet 1)

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MAINTENANCE MANUAL

B1172

BRAKE LINK

G

RIGHT
FORWARD

E

BEAR
BLOC
RUDDER
BAR

ARM

BRAKE
TORQUE
TUBE
BEARING

BELL CRANK

MASTER
CYLINDER
DETAIL

H

F
F0763T1026
G0763T1027
H0763T1028

DETAIL H
Rudder Control System Installation
Figure 201 (Sheet 2)

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MAINTENANCE MANUAL

B1173

STEERING
BUNGEE
SPROCKET

IDLER SPROCKET
DETAIL

L

DETAIL K

CABLE
GUARD

FORWARD TRIM
SHAFT SPROCKE

CHAIN

L

K
TAIL

J

DETAIL

M

BUNGEE

J0763T1029
K0763T1030
L0763T1031
M0763T1005

Rudder Control System Installation
Figure 201 (Sheet 3)

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MAINTENANCE MANUAL
B.

4.

Rudder Installation (Refer to Figure 201).
(1) With the rudder supported, install the hinge bolts to attach the rudder to the vertical fin.
(2) Install the electrical bonding strap.
(3) Torque the nuts to 50 to 70 inch pounds plus free running torque.
(4) Connect the cables to the rudder bell crank. Do not tighten too much. Make sure that the terminal
(clevis) pivots freely.
(5) Rig the rudder system.
(6) Safety the turnbuckles with wire.
(7) Lubricate the system. Refer to Chapter 12, Flight Controls - Lubrication.
(8) Connect the tail navigation light quick-disconnect (JV001) at the bottom of the rudder.
(9) Install the stinger.

Rudder Control Cables RemovaVlnstallation
A.

Rudder Cables Removal (Refer to Figure 201).
(1) Remove the seats, carpet, and baggage wall. Refer to Chapter 25, Equipment/Furnishings General.
(2) Remove the rudder shield assemblies and the plates (231 AB, 231 BB, 231 DB, 231 EB, 231 HB,
231JB, and 310AR). Refer to Chapter 6, Access/Inspection Plates - Description and Operation.
(3) Remove the fairings (340AL and 340AR). Refer to Chapter 6, Access/Inspection Plates Description and Operation.
(4) Remove the safety clips from the turnbuckles and relieve cable tension.
(5) Disconnect the left and the right rudder cables from the rudder bell crank.
(6) Disconnect the left and the right rudder cables from the rudder bar arms.
(7) Remove the pulleys and the cable guards as necessary to remove the cables.
NOTE:

B.

5.

To ease the routing of the cables, you can attach a length of wire to the end of the
cable before you remove it from the airplane. Leave the wire in place, routed through
the structure. Then attach the cable the wire to install and pull the cable into position.

(8) Remove the rudder cables.
Rudder Cables Installation (Refer to Figure 201).
(1) If installed, attach the cables to the wires and pull the cables through the airplane structure.
(2) Attach the left and the right rudder cables to the rudder bell crank.
(3) Attach the left and the right rudder cables to the rudder bar arms.
(4) Install the pulleys and the pulley guards. Make sure that the cables are in the pulley grooves
before you install the cable guards.
(5) Rig the rudder system. Refer to Rudder Control Adjustment/Test.
(6) Install the rudder shield assemblies and the plates (231AB, 231BB, 231DB, 231EB, 231HB,
231 JB, and 31 OAR), that you removed for access. Refer to Chapter 6, Access/Inspection Plates
- Description and Operation.
(7) Install the seats, carpet, and baggage wall. Refer to Chapter 25, Equipment/Furnishings General.
(8) Install the fairings (340AL and 340AR). Refer to Chapter 6, Access/Inspection Plates Description and Operation.

Rudder Control Adjustment/Test
A.

Rig Rudder Controls (Refer to Figure 201, Figure 202, and Figure 203).
(1) Remove the stinger (310DB) for access to the rudder stop bolts. Refer to Chapter 6, Access/
Inspection Plates - Description and Operation.
(2) Adjust the rudder stop bolts to get 24 degrees, +0 or -1 degree, measured parallel to the water
line, and 27 degrees 13 minutes, +0 or -1 degree, measured perpendicular to the hinge line.
(3) Tighten the jam nuts.
(4) Remove the crew seats. Refer to Chapter 25, Front Seats and Rails- Maintenance Practices.
(5) Remove the pedestal cover, carpet, and rudder shield assemblies. Refer to Chapter 25,
Equipment/Furnishings - General.

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MODEL 182/T182
MAINTENANCE MANUAL

B1174

STEP 1:

STRAIGHTEDGES

ESTABLISH NEUTRAL
POSITION OF RUDDER.

STEP 2:

MEASURE
RUDDER TRAVEL.

VERT

R
BLOCK
8.12 TO 8.72 INCH
(206.25 to 221.49 mm)

WIRE POINTER

0562T1009
0562T1009

Rudder Travel Adjustment
Figure 202 (Sheet 1)

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MODEL 182/T182
MAINTENANCE MANUAL

60

50
40

]

UPPERI

UPPER
E
RUDDER CABLES (0.125-INCH DIAMETER)

I

-

I
-

TENSION 30 POUNDS AT 71

30

NOM

NOMII

20
10
LOWER LIMIT

l
-30

-40

1
-20

1
-10

0

10

20

30

40

50

60

70

80

90

100

110

DEGREES FAHRENHEIT

300
250

z

RUDDER
RUDDER

t

3. 8-mm DIAMETER)

CABLES

(3.18-MM DIAMETER)

200

z
150
100

LOWER LIMIT

50

0
40 -35 -30 -25 -20

-15 -10

5
0
5
10 15
DEGREES CELSIUS

20

25

30

35

40

45

Rudder Cable Tension
Figure 203 (Sheet 1)

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MAINTENANCE MANUAL
(6)
(7)
(8)
(9)
(10)

Loosen the idler sprocket and disengage the chain from the forward trim shaft sprocket and the
steering bungee sprocket.
Disconnect the steering bungee adjustable rod end from the bell crank.
Remove the fairings (340AL and 340AR). Refer to Chapter 6, Access/Inspection Plates Description and Operation.
Remove the safety clips from the left and the right rudder cable turnbuckles and relieve cable
tension.
Clamp the rudder pedals in the neutral position and adjust the push-pull rods to center the bell
crank.
NOTE:

The bell crank is centered when the bolts in each end are the same distance from the
bulkhead just forward of the bell crank.

(11) Tighten the jam nuts.
(12) Keep the rudder pedals in the neutral position and adjust the turnbuckles on the left and the
right rudder cables. The correct tension adjustment is 30 pounds, +10 or -10 pounds (133.45
N, +44.48 or -44.48 N) at 70 °F (21 °C) with the rudder offset one degree to the right. Refer to
Figure 203 for the correct tensions at other temperatures.
NOTE:

When the rudder is offset one degree to the right, this is 5/16 inch at the lower trailing
edge from the neutral position of the rudder.

(13) Install the safety clips on the rudder cable turnbuckles.
(14) Check the rudder travel. (Refer to Figure 202).
(a) Find the neutral position of the rudder.
1
Clamp a straightedge on each side of the fin and the rudder.
Block the trailing edge of the rudder at half of the distance between the straightedges.
2
Tape a length of soft wire to the stinger to let it bend to index at the lower corner of
3
the rudder trailing edge.
4
With a soft lead pencil, mark the rudder at the at the soft wire indexing point (neutral).
(b) Remove the straightedges and the blocks.
(c) Hold the rudder against the right and then the left rudder stop.
(d) In the two directions of travel, measure the distance from the pointer to the pencil mark on
the rudder. The distance should be between 8.12 inches and 8.72 inches (206.25 mm and
221.49 mm).
(15) Rig rudder trim system. Refer to Rudder Trim Adjustment/Test.
NOTE:

The rudder control system, rudder trim control system, and nosewheel steering
system are connected. Adjustments to one of these systems have an effect on the
others. The rudder control system must be correctly rigged before you rig the rudder
trim and the nosewheel steering system.

(16) Install stinger (310DB), fairings (340AL and 340AR), pedestal cover, carpet, rudder shield
assemblies, and seats. Refer to Chapter 6, Access/Inspection Plates - Description and
Operation, Chapter 25, Front Seats and Rails - Maintenance Practices, and Chapter 25, Rear
Seat - Maintenance Practices.

WARNING: Make sure that the rudder moves in the correct direction when
you operate the rudder pedals.
(17) Operate the rudder system to check for ease of movement, full travel, and correct operation.

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MAINTENANCE MANUAL
RUDDER TRIM - TROUBLESHOOTING
1.

General
A.

A troubleshooting chart has been developed to aid the maintenance technician in system
understanding. Refer to Figure 101.

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MODEL 182/T182
MAINTENANCE MANUAL

B1175

FALSE READING
ON TRIM
INDICATOR
POINTER.

HARD ON
SLUGGISH
OPERATION.

I
CHECK FOR
BENT POINTER.

CHECK FOR WORN
COMPONENTS OR
DIRTY THREADS ON

IF-

COMPONENTS. IF-

I
OK, CHECK
FOR LOOSE
POINTER
ACTUATING
SCREW.
POSITION
INDEX
POINTER
AND TIGHTEN
SCREW.

I
NOT OK,
STRAIGHTEN
POINTER.
REFORM TO
PREVENT
HANGING
UP ON AFT
PEDESTAL
COVER.

OK, CHECK
FOR
INCORRECT
RUDDER
CABLE
TENSION.
ADJUST AS
NECESSARY.

NOT OK,
REPLACE
WORN PART
AND CLEAN
THREAD.

CANNOT
ESTABLISH
FULL TRAVEL.

I
CHECK FOR
IMPROPERLY
RIGGED TRIM
SYSTEM.
RE-RIG AS
NECESSARY.

Rudder Trim System Troubleshooting Chart
Figure 101 (Sheet 1)

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MODEL 182/T182
MAINTENANCE MANUAL
RUDDER TRIM CONTROL SYSTEM - MAINTENANCE PRACTICES
1.

General
A.

2.

Rudder Trim System Removal/Installation
A.

B.

3.

Rudder trim system maintenance practices consists of rudder trim system removal/installation and
rudder trim system rigging.

Remove Rudder Trim System (Refer to Figure 201).
(1) Remove pilots and copilots seats, pedestal cover, carpet and shield assemblies, Refer to
Chapter 25, Front Seats - Maintenance Practices, and Rear Seat - Maintenance Practices.
(2) Loosen bolt securing idler sprocket and relieve tension on chain.
(3) Remove chain guard from steering bungee sprocket.
(4) Disconnect steering bungee from bellcrank.
(5) Remove chain from steering bungee sprocket and forward trim shaft sprocket.
Install Rudder Trim System (Refer to Figure 201).
(1) Install chain on steering bungee sprocket and forward trim shaft sprocket.
(2) Connect steering bungee to bellcrank.
(3) Position chain on idler sprocket
(4) Rig trim system. Refer to Rudder Trim Adjustment/Test.
(5) Install chain guard on steering bungee sprocket.
(6) Install pedestal cover, carpet and shield assemblies, pilots and copilots seats. Refer to Chapter
25, Front Seats - Maintenance Practices, and Rear Seat - Maintenance Practices.

Rudder Trim Adjustment/Test
NOTE:

A.

The rudder control system, rudder trim control system and nosewheel steering system are
interconnected. Adjustments to any one of these systems will affect the others. The rudder
control system must be correctly rigged prior to rigging the rudder trim and nosewheel steering
system.

Rig Rudder Trim System (Refer to Figure 201).
NOTE:
(1)
(2)
(3)
(4)
(5)
(6)
(7)
(8)
(9)
(10)
(11)

Rudder control system must be rigged prior to rigging rudder trim system.

Ensure rudder control system is properly rigged.
Weight or tie down tail of airplane to raise nose wheel from floor.
Extend nose gear strut and ensure nose gear is centered against external centering stop.
Clamp rudder pedals in neutral position.
Adjust nose wheel steering bungee rod end to 0.81 inch +0.00 or -0.06 inches from sprocket to
center of rod end bearing.
Rotate sprocket in or out as required to align rod end with attaching hole in bellcrank and install
bolt, washer, and nut.
Rotate rudder trim wheel until indicator is centered in pedestal slot (neutral).
Without moving sprocket, engage chain on steering bungee sprocket, forward trim shaft sprocket
and idler sprocket.
Adjust idler sprocket to allow approximately one-half inch deflection at chain midpoint and tighten
sprocket.
Install cable guard over sprocket.
Lower nose wheel to ground and remove clamps from rudder pedals.

WARNING: Ensure rudder moves in the correct direction when operated by the
rudder pedals and trim control wheel.

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MAINTENANCE MANUAL

C

DETAIL A

B

0710T1001
A0763T2004

Rudder Trim Control System Installation
Figure 201 (Sheet 1)

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MODEL 182fT182
MAINTENANCE MANUAL

B1177

FORWARD TRIM
SHAFT SPROCKE

E
CHAIN

BE BELL CRANK

DETAIL C

D

STEERING
BUNGEE
SPROCKET

DETAIL B

CABLE
GUARD
RSPROCKET

DETAIL D
DETAIL E

80763R1029
C0763R1005
D0763R1030
E0763R1031

Rudder Trim Control System Installation
Figure 201 (Sheet 2)

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MODEL 182/T182

MAINTENANCE MANUAL
ELEVATOR SYSTEM - TROUBLESHOOTING
1.

General
A.

A troubleshooting chart has been developed to aid maintenance technician in system understanding.
Refer to Figure 101.

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MODEL 182/T182
MAINTENANCE MANUAL

B1178

BINDING OR JUMPY MOTION IN
MOVEMENT OF ELEVATORS.

CHECK FOR DEFECTIVE CONTROL COLUMN
SUPPORTARM BEARING. IF-

I
OK, CHECK FOR OVERTIGHT
CLEVIS BOLTS. IF-

NOT OK, REPLACE SUPPORT
ARM BEARINGS.

OK, CHECK FOR DEFECTIVE
OR BROKEN PULLEYS. IF-

NOT OK, ADJUST CLEVIS
BOLTS AS NECESSARY.

OK, CHECK FOR INSUFFICIENT
CABLE TENSION. IF -

NOT OK, REPLACE PULLEYS
AS NECESSARY.

OK, CHECK FOR DEFECTIVE
ELEVATOR HINGES. LUBRICATE
OR REPLACE HINGES AS
NECESSARY.

NOT OK, ADJUST CABLE
TENSION AS NECESSARY.

Elevator System Troubleshooting Chart
Figure 101 (Sheet 1)

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MAINTENANCE MANUAL

B1179

ELEVATORS FAIL TO ATTAIN
PRESCRIBED TRAVEL.

I
CHECK THAT STOPS
ARE CORRECTLY SET. IF -

I
OK, CHECK THAT CABLE
TENSION IS SET EVENLY.

NOT OK, CHECK TRAVEL.
RE-RIG AS NECESSARY.

Elevator System Troubleshooting Chart
Figure 101 (Sheet 2)

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MODEL 182/Ti182

MAINTENANCE MANUAL
ELEVATOR CONTROL SYSTEM

-

MAINTENANCE PRACTICES

1.General
A. Elevators are operated by forward and aft movement of the control wheels. Movement of the control
wheels goes to the elevators through the control yoke and a series of cables, bell cranks, and
push rods.
2.

3.

Forward Elevator Bell Crank Removal/installation
A.

Forward Elevator Bell Crank Removal (Refer to Figure 201).
(1) Remove the seats and the carpet. Refer to Chapter 25, Front Seats and Rails - Maintenance
Practices and Rear Seat - Maintenance Practices.
(2) Remove the access plate (31 OBB). Refer to Chapter 6, Access/Inspection Plates - Description
and Operation.
(3) Relieve cable tension at the turnbuckles and disconnect the cables from the forward bell crank.
(4) Disconnect the push-pull tube from the forward bell crank.
(5) Remove the pivot bolt and remove the forward bell crank.

B.

Forward Elevator Bell Crank Installation (Refer to Figure 201).
(1) Place the forward bell crank in position and install the pivot bolt.
(2) Connect the push-pull tube to the forward bell crank.
(3) Install the cables.
(4) Adjust the cable tension and safety the turnbuckles. Refer to Elevator Control Adjustment/Test.
(5) Install the access plate (310OBB). Refer to Chapter 6, Access/Inspection Plates - Description and
Operation.
(6) Install the seats and the carpet. Refer to Chapter 25, Front Seats and Rails - Maintenance
Practices and Rear Seat - Maintenance Practices.

Aft Elevator Arm Assembly Removal/installation
A.

Aft Elevator Arm Assembly Removal (Refer to Figure 201).
(1) Remove the stinger (310DB). Refer to Chapter 6, Access/inspection Plates - Description and
Operation.
(2) Relieve cable tension at the turnbuckles and disconnect the cables from the arm assembly.
(3) Remove the bolt and the washer that attach the push-pull tube to the arm assembly.
(4) Remove the bolts that attach the elevators to the arm assembly.
(5) Remove the arm assembly pivot bolt and slide the arm assembly out between the tube
assemblies.
NOTE:

B.

4.

If necessary, you can remove one of the stabilizer attach bolts for clearance when
you remove the bell crank pivot bolt.
Aft Elevator Arm Assembly Installation (Refer to Figure 201).
(1) Place the bell crank in position and install the pivot bolt.
(2) If necessary, install the components that you removed for clearance when you removed the arm
assembly.
(3) Install the bolts that attach the elevators to the arm assembly.
(4) Attach the push-pull tube to the arm assembly with the bolt and the washer.
(5) Install the cables.
(6) Adjust the cable tension and safety the turnbuckles. Refer to Elevator Control Adjustment/Test.
(7) Install the stinger (310DB). Refer to Chapter 6, Access/Inspection Plates - Description and
Operation.

Elevator Control Adjustment/Test
A.

Rig Elevator (Refer to Figure 202, Figure 203, and Figure 204).
(1) Remove the stinger (310ODB), fairings (340AL and 340AR), and access plate (31 OBB). Refer to
Chapter 6, Access/Inspection Plates - Description and Operation.

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Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182
MAINTENANCE MANUAL

lF=ThII

R

PULLEY

UP CABLE

C
DETAIL

E
DOWN CABLE

DETAIL

A

PULLEY

DETAIL %.p PULLEY

DETAIL

D

A0763T2003
B0763T1 032
C0763T 1033
D0763T 1034
E0763T1 035

Elevator Control System
Figure 201 (Sheet 1)

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Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 1821T182

MAINTENANCE MANUAL

B1 181

LIINK

UP

PUSH-PULL
TUBE
SPRING

DOWN CABLE
DETAIL

t~rLL UrIMI'%Ir

F
TORQUE
TUBE

ARM
ASSEMBLY

PUSH-PULL XI

DETAIL

IM
---- ---

H

--

ASSE-MBLY

F0763T2 002
G0763T1 036
H0763T1 037

Elevator Control System
Figure 201 (Sheet 2)

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Cessna Aircratt Company

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CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182
MAINTENANCE MANUAL

B
NEUTRAL
RIGGING TOOL

A

DETAIL
BELL CRANK
-a-- El
U

DONSO

UP STOP
:-VATOR
SH-PULL
BE

PRESS FIT
INCH
(16,2
Imm)
1

0.46 INCH
(12 mm)

DETAIL

C
0.19 INCH
(5 mm)
RADI US

-~.<(1

(TYPICAL)

F

! 30.4

jz4

0.30 INCH -4(9
(7.6 mm)
NOTE:

MAKE FROM 0.125-INCH (3.18 mm)
STEEL PLATE, 0.209-INCH DIAMETER
DRILL ROD FOR SHORT PIN, AND 0.250-IN CH07T10
DIAMETER DRILL ROD FOR LONG PIN.
REFER TO DIMENSIONS SHOWN.
Elevator Control System Rigging
Figure 202 (Sheet 1)

0.60 INCH
5.24 mm)

DETAIL

B

0.35 INCH
mm)
RADIUS
(TYPICAL)
A076OT1 007
B0760T1 006
C076OT1 005

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CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82

MAINTENANCE MANUAL

OW130

An
UPPER UMIT

lI.

I I

1,

I

iI

I

I

ELEVATOR CABLES .(0.125-INCH DIAMETERI)
I

A

I

TENSIONi 30 POUNDS AT 70 -F

zI

[

II.I

0-

I

I .

I
I

I

~ ~~~I
I

.

Aw- --I
1111 11111111 II II III III II IITj ITUTIT]
D -30.-213

-10

0

10

20

30

DEGREES FAHRENHEIT

co
z

z
0,
U,

I
DMGREES CELSIUS

Elevator Cable Tension (without the GFC-700 Autopilot)
Figure 203 (Sheet 1)

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Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti82

MAINTENANCE MANUAL

VI

z
0
02

z

9f

z

t2

C-

DIEGREJES FAHRENHEIT

z
0,

z

I

DEGREES CELSIUS'

0

Elevator Cable Tension (with the GFC-700 Autopilot)
Figure 204 (Sheet 1)

27-30-00
©Cessna Aircraft Company

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Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82
MAINTENANCE MANUAL

CAUTION: Position a support stand under the tail tiedown to prevent the
tailcone from falling while you work inside.
(2)

Lock the elevator control column in the neutral position with the neutral rigging tool (Refer to
Figure 202).
(3) Streamline the elevators to the neutral position with the horizontal stabilizer.
Ignore
counterweight areas of the elevators when you streamline the elevators.
NOTE:

Neutral position for the elevators is when they are streamlined with the horizontal
stabilizer.

NOTE:

The counterweight areas have a contour of approximately 3 degrees DOWN at
cruising speed.

(4) While you hold the elevators in the neutral position, adjust the turnbuckles equally to cable
tension at 70 OF (21 'C). Refer to Figure 203 for the correct tensions at other temperatures.
*
Without the GFC-700 Autopilot system, 30 pounds, +10 or -10 pounds (133.45 N, +44.48
or -44.48 N)
*
With the GFC-700 Autopilot system, 35 pounds, +5 or -5 pounds (155.69 N, +22.24 or
-22.24 N)
(5) Mount an inclinometer on one elevator.
(6) While you keep the elevator streamlined with the horizontal stabilizer, set the inclinometer to 0
degrees. Ignore counterweight areas of the elevators when you streamline the elevators.
NOTE:

Neutral position for the elevators is when they are streamlined with the horizontal
stabilizer.

NOTE:

The counterweight areas have a contour of approximately 3 degrees DOWN at
cruising speed.

(7) Remove the neutral rigging tool.
(8) Adjust the bell crank up stop to get 28 degrees, +1 or -1 degree, up travel.
(9) Adjust the bell crank down stop to get 21 degrees, +1 or -1 degree, down travel.

NOTE:

The bell crank stop blocks (7) are four-sided bushings, drilled off center. They can
be turned to four different positions for correct elevator travel. Each 90-dlegree turn
of the stop changes the elevator travel approximately one degree.

(10) Check the sponge at the control column in both up and down positions and, if necessary, adjust
the turnbuckles until the control column cannot touch the instrument panel or the firewall.
(11) Safety the turnbuckles.
(a) Use the single-wrap preferred procedure with the 0.040 inch (1.0 mm) stainless steel or
monel safety wire. Refer to Chapter 20, Safetying - Maintenance Practices.
(12) Install the stinger (31 0DB), fairings (340AL and 340AR), and access plate (31 OBB). Refer to
Chapter 6, Access/Inspection Plates - Description and Operation.
(13) Remove the support stand.

WARNING: Make sure that the elevators move in the correct direction
when you move the control column.
(14) Do a check for the correct operation of the elevators.

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
ELEVATOR TRIM CONTROL - TROUBLESHOOTING
1.

General
A.

A troubleshooting chart has been developed to aid the maintenance technician in system
understanding. Refer to Figure 101.

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© Cessna Aircraft Company

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April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

B1183

TRIM CONTROL WHEEL MOVES
WITH EXCESSIVE RESISTANCE.

CHECK FOR EXCESSIVE CABLE TENSION. IF -

I
OK, CHECK FOR RUBBING OR
BINDING PULLEYS. IF-

NOT OK, ADJUST CABLE
TENSION AS NECESSARY.

OK, CHECK FOR TRIM TAB
HINGE BINDING. IF -

NOT OK, REPAIR OR REPLACE
PULLEYS AS NECESSARY.

OK, CHECK FOR DEFECTIVE
TRIM TAB ACTUATOR. IF -

NOT OK, LUBRICATE OR REPLACE
HINGE AS NECESSARY.

I
OK, CHECK FOR DAMAGED
SPROCKET. IF-

NOT OK, REPLACE
IF DEFECTIVE.

OK, CHECK FOR BENT
SPROCKET SHAFT.
REPLACE IF BENT

NOT OK, REPLACE
IF DAMAGED.

Elevator Trim System Troubleshooting Chart
Figure 101 (Sheet 1)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1184

LOST MOTION BETWEEN CONTROL
WHEEL AND TRIM TAB.

CHECK FOR INSUFFICIENT CABLE TENSION. IF -

OK, CHECK FOR BROKEN
PULLEYS. IF-

NOT OK, ADJUST CABLE
TENSION AS REQUIRED.

OK, CHECK FOR CABLES
OFF OF PULLEYS. IF -

NOT OK, REPLACE
PULLEY.

OK, CHECK FOR WORN
TRIM TAB ACTUATOR. IF -

NOT OK, REPLACE
ACTUATOR.

OK, CHECK FOR LOOSE ACTUATOR
ATTACHMENT. TIGHTEN AS NECESSARY.

NOT OK, REPLACE TRIM
TAB ACTUATOR.

Elevator Trim System Troubleshooting Chart
Figure 101 (Sheet 2)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

B1185

TRIM INDICATOR FAILS TO
INDICATE CORRECT TRIM POSITION.

I
INDICATOR INCORRECTLY ENGAGED
ON TRIM WHEEL TRACK. IF -

I

I
OK, CHECK CABLE TENSION.
ADJUST TENSION.

NOT OK, RESET
INDICATOR.

Elevator Trim System Troubleshooting Chart
Figure 101 (Sheet 3)

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April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
ELEVATOR TRIM CONTROL - MAINTENANCE PRACTICES
1.

General
A.

2.

The elevator trim tab is on the right elevator. It is controlled by a trim wheel installed in the pedestal.
The power to operate the elevator trim tab comes from the trim control wheel through chains, cables,
and an actuator. A mechanical pointer adjacent to the trim wheel shows elevator trim tab position. A
nose up setting causes an elevator trim tab down position.

Trim Tab Actuator Removal/Installation
A.

Trim Tab Actuator Removal (Refer to Figure 201).

CAUTION: Put a support stand in position under the tail tiedown ring. The
support stand will help to prevent the tailcone from falling while a
person works inside.

B.

3.

(1) Remove the panel 31OAR to get access to the stop blocks.
Refer to Chapter 6,
Access/Inspection Plates - Description and Operation (Refer to Figure 201).
(2) Remove the safety clip and loosen the tension on the cable at the turnbuckle.
(3) Remove the lock nut, bolt, and washers from the push-pull tube and disconnect it from the
actuator.
(4) Remove the access plate 310CB to get access to the actuator. Refer to Chapter 6, Access/
Inspection Plates - Description and Operation.
(5) Remove the chain guard and the chain from the actuator sprocket.
(6) Remove the screws that attach the actuator clamps to the bracket.
(7) Carefully remove the actuator from the access opening.
Trim Tab Actuator Installation (Refer to Figure 201).
(1) Carefully install the actuator through the access opening.
(2) Use the screws to attach the actuator clamps to the bracket.
(3) Install the chain on the actuator sprocket.
(4) Install the chain guard.
(5) Install the access plate 310CB. Refer to Chapter 6, Access/Inspection Plates - Description and
Operation.
(6) Use the washers, bolt, and lock nut to connect the push-pull tube to the actuator.
(7) Set the cable tension at the turnbuckle. Refer to the Trim Tab Control Adjustment/Test.
(8) Install the safety clip. Refer to Chapter 20, Safetying - Maintenance Practices.
(9) Install the panel 310AR. Refer to Chapter 6, Access/Inspection Plates - Description and
Operation.
(10) Remove the support stand.

Trim Tab Actuator Disassembly/Assembly
A.

Trim Tab Actuator Disassembly (Refer to Figure 202).
(1) Remove the trim tab actuator. Refer to Tim Tab Actuator Removal/Installation.
(2) Turn the screw assembly to loosen and remove it from the actuator.

B.

Trim Tab Actuator Assembly (Refer to Figure 202).
(1) If a new bearing is necessary, press it into the boss on the screw assembly. Make sure that the
force pushes against the outer race of the bearing.
(2) Install the screw assembly into the actuator as follows:
(a) Pack the internal housing with MIL-G-21164C grease.
NOTE:

This supplies the lubrication for the screw assembly.

(b) Install the screw assembly in the housing.
(c) If necessary, clean the unwanted grease from the housing.

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© Cessna Aircraft Company

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Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

ACTUATOR ASSEMBLY

J
STOP

H
G

TURNBUCKLE
B

E

D
C

DETAIL

A

0710T1001
A0763R1033

Elevator Trim Tab Control System
Figure 201 (Sheet 1)

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Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

B3410

TRIM IN

SCREW

DETAIL

B

FS 17.00

RD

BOLT
CABLE

DETAIL C

B0763R1005
C0763R1038

Elevator Trim Tab Control System
Figure 201 (Sheet 2)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

B3411

CABLE

rag

FS 45.00

MA rmrs

PULLEYS

CABLE GUARD

DETAIL

D

CABLE GUARD

iUARDS

PULLEYS

PULLEYS

BOLTS

DETAIL

E
D0763R1034
E0763R1033

Elevator Trim Tab Control System
Figure 201 (Sheet 3)

27-31-00
© Cessna Aircraft Company

Page 204
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1246

CABLE GUARD
BOL

SHER
NUT

FS

DETAIL

F

BOL

PULLLY

DETAIL

G
F0763R1039
G0763R2006

Elevator Trim Tab Control System
Figure 201 (Sheet 4)

27-31-00
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Page 205
Jul 3/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B3412

FS 230.18
UARDS

PULLEY

DETAIL

H

ACTUATOR
31.50
ASSEMBLY
(Right Side Only)

SS 31.50

uARD
OR
ET

NUT

WASHER

WASHER
BOLT

PUSH-PULL TUBE

DETAIL

J

H0763T1041
J0763R1040

Elevator Trim Tab Control System
Figure 201 (Sheet 5)

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Page 206
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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
B1247

ACTUATOR

DETAIL A

SCREW
ASSEMBLY

HOUSING

BEARING

SPROCKET

DETAIL B
0710T1007
A0563T1010
B0563T1010

Elevator Trim Tab Actuator Assembly
Figure 202 (Sheet 1)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
(3) Hold the screw assembly and turn the sprocket by hand to do a test of the actuator assembly.
NOTE:
4.

The screw assembly must move smoothly in the actuator.

Trim Tab Actuator Cleaning and Inspection
A.

Complete a Trim Tab Actuator Cleaning and Inspection (Refer to Figure 202).
(1) Remove the screw assembly from the housing. Refer to Trim Tab Actuator Disassembly/
Assembly.
(a) Do not remove the sealed bearing from the screw assembly unless the bearing replacement
is necessary.
(2) Wash the screw assembly, except the sealed bearing, in Stoddard solvent or equivalent. Do not
clean the sealed bearing.
(3) Do a check of the sealed bearing and screw assembly for wear and for parts that have scores.
Refer to Table 201 for dimensions.

Table 201. Wear Dimensions
COMPONENT

MAXIMUM DIMENSION

MINIMUM DIMENSION

Aft End Bearing Inside
Diameter

0.249 Inch

0.248 Inch

0.245 Inch (Shank)
0.246 Inch (Shank)
Threaded Rod End
Outside Diameter
(4) Examine the screw assembly and the screw for threads that have damage or dirt particles that
can cause the assembly to operate incorrectly.
(5) Examine the screw assembly sealed bearing for smoothness of operation.
(6) Examine the housing components for stripped threads, cracks, deep nicks, dents, and other
signs of damage.
(7) Examine the sprocket for broken, chipped, and/or worn teeth.
(8) Examine the linear free play at the sprocket end of the housing.
NOTE:

The linear free play at the sprocket end must not be more than 0.010 inch maximum.

(a) If the free play is more than the permitted limits, replace the actuator.
(9) Do not try to repair the actuator assembly parts that have damage or wear.
(10) Install the screw assembly into the housing. Refer to Trim Tab Actuator Disassembly/Assembly.
5.

Trim Tab Free Play Inspection
A.

Tab Free Play Inspection (Figure 203).
Put the elevator and the trim tab in the neutral position.
With the elevator gust lock, make sure that the elevator cannot move.
Find the maximum amount of permitted free play.
(a) Measure the chord length at the extreme inboard end of the trim tab.
(b) Multiply the chord length by 0.025 to get the maximum permitted free play.
(c) Measure the free play at the same point on the trim tab where the chord length was
measured.
(d) The total free play must not be more than the maximum permitted free play.
(4) With moderate hand pressure (up and down), measure the free play at the trailing edge of the
trim tab.
(5) If the trim tab free play is less than the maximum permitted free play, the system is in the approved
limits.
(6) If the trim tab free play is more than the maximum permitted free play, check the items that follow
for looseness while you move the trim tab up and down.
(a) The push-pull tube/trim tab horn assembly attachment.
(b) The push-pull tube/actuator assembly threaded rod-end attachment.
(c) The actuator assembly threaded rod end in the actuator assembly.
Trim
(1)
(2)
(3)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1248

CHORD LENGTH
HINGE POINT

TRAILING EDGE
TAB

HINGE POINT

TRAILING
EDGE
TRAILING

t

A

O FREE-PLAY UP
N

FREE-PLAY DOWN
TOTAL FREE-PLAY

C0563TC1012

Trim Tab Free Play Inspection
Figure 203 (Sheet 1)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
(7)
(8)
(9)
6.

If looseness is apparent while you check the push-pull tube/tab horn assembly, install new parts
to repair.
If looseness is apparent while you check the push-pull tube/actuator assembly threaded rod-end
assembly, install new parts to repair.
If looseness is apparent while you check the push-pull tube threaded rod end in the actuator
assembly, the threaded rod end is out of tolerance and you must replace it.

Trim Tab Control Cables and Pulleys Removal/Installation
A.

Cables and Pulleys Removal (Refer to Figure 201).

CAUTION: Position a support stand under the tail tiedown ring to prevent the
tailcone from falling while a person works inside.
(1)
(2)
(3)
(4)
(5)
(6)
(7)

Remove the crew seats and the rear seat. Refer to Chapter 25, Front Seats and Rails Maintenance Practices and Rear Seat - Maintenance Practices.
Remove the pedestal cover.
Remove the access panel (31 OAR), access plates (230DB, 230LB, 231 LB, 31 OBB, and 310CB),
and fairings (340AL and 340AR) for access. Refer to Chapter 6, Access/Inspection Plates Description and Operation.
Remove the stop blocks from the control cables.
Remove the cable guard from the actuator.
Remove the safety clip from the turnbuckle and disconnect the cable.
Disconnect the cables at the cable ends.
NOTE:

(8)
(9)
B.

7.

To ease the routing of the cables, a length of wire can be attached to the end of the
cable before you remove it from the airplane. You can leave the wire in place, routed
through the structure. Then you can attach the new cable and pull it into position.

Remove the cable guards and the pulleys.
Disengage the chains from the sprockets and remove the cables from the airplane structure.

Cables and Pulleys Installation (Refer to Figure 201).
(1) Attach the cables to the wires that are routed through the airplane structure and pull the cables
into position.
(2) Engage the chains on the sprockets and install the chain guard on the actuator.
(3) Install the pulleys and the pulley guards.
(4) Connect the cable ends and install the turnbuckle.
(5) Rig the system. Refer to Trim Tab Control Adjustment/Test.
(6) Install the access panel (310AR), access plates (230DB, 230LB, 231LB, 310BB, and 310CB),
and fairings (340AL and 340AR) removed to get access. Refer to Chapter 6, Access/Inspection
Plates - Description and Operation.
(7) Install the pedestal cover.
(8) Install the crew seats and the rear seat. Refer to Chapter 25, Front Seats - Maintenance
Practices and Rear Seat - Maintenance Practices.
(9) Remove the support stand.

Trim Tab Control Wheel RemovaVlnstallation
A.

Trim
(1)
(2)
(3)
(4)

Tab Control Wheel Removal (Refer to Figure 201).
Relieve cable tension at the turnbuckle.
Remove the pedestal cover.
Remove the screws that attach the control wheel retainer.
Remove the retainer and the pointer. Do not drop the trim control wheel.

B.

Trim
(1)
(2)
(3)

Tab Control Wheel Installation (Refer to Figure 201).
Install the retainer and the pointer with the screws.
Install the pedestal cover.
Set the cable tension at the turnbuckle. Refer to Trim Tab Control Adjustment/Test.
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MODEL 182/T182
MAINTENANCE MANUAL

8.

Trim Tab Control Adjustment/Test
A.

Set Trim Tab Control Cable Tension (Refer to Figure 204 and Figure 205).
CAUTION:
(1)
(2)
(3)
(4)
(5)
(6)
(7)

Position a support stand under the tail tiedown ring to prevent the
tailcone from falling while a person works inside.

Remove the access panel (310AR) and the access plates as necessary. Refer to Access/
Inspection Plates - Description and Operation.
Loosen the travel stop blocks on the cables.
Disconnect the actuator from the trim tab push-pull tube.
Adjust the turnbuckle as necessary to get 15 to 20 pounds (66.72 to 88.96 N) of cable tension at
70 °F (21 °C). Refer to the Charts in Figure 205 for the correct tensions at other temperatures.
If this trim tab adjustment/test is done as part of a chain and/or cable installation, let the actuator
screw turn freely, because the chains and the cables are connected.
Adjust the cable tension and safety the turnbuckle.
Turn the trim wheel full forward (nose down). Make sure that the pointer does not decrease the
trim wheel movement. If necessary, move the pointer to a new position. To move the pointer to
a new position, you can pry the trailing leg of the pointer out of the groove with a thin screwdriver
if necessary.
NOTE:

At the full forward (nose down) position of the trim wheel, more forward movement is
prevented because the chain or the cable ends contact the sprockets or the pulleys.

(8) With the elevator and the trim tab both in neutral (streamlined), mount an inclinometer on the tab
and set it at 0 degrees. Ignore the counterweight areas of the elevators when you streamline.
These areas are contoured so they will be approximately 3 degrees down at cruising speed.
NOTE:

Neutral positions for the elevators are streamlined with the horizontal stabilizer.
Ignore the counterweight areas of the elevators when you streamline. These areas
are contoured so they will be approximately 3 degrees DOWN at cruising speed.

NOTE:

An inclinometer for measuring control surface travel is available from the Cessna
Parts Distribution.

(9) Turn the trim tab actuator screw in or out as required to place the trim tab up with a maximum
of 2 degrees overtravel, with the actuator screw connected to the push-pull tube.
(10) Turn the trim wheel to position the trim tab up and down, and adjust the actuator screws as
required to get correct travel in both directions.
(11) Put the stop blocks in position. Refer to Figure 204.
(a) With the elevators in neutral, set the trim tab to neutral.
(b) Position the stop block (2) approximately 0.25 inch (6.35 mm) forward of the turnbuckle.
(c) Position the stop block (3) approximately 0.25 inch (6.35 mm) aft of the turnbuckle.
(d) Attach the stop blocks (2) and (3) to cable A.
(e) Put the inclinometer on the trim tab and lower it to 15 degrees, +1 or -1 degree.
(f) Put the stop block (4) against the stop block (3) and attach it to cable B.
(g) Run the trim tab up to 24 degrees, +2 or -2 degrees.
(h) Place stop block (1) against stop block (2) and attach to cable B.
(12) Make sure that the trim wheel pointer travels the same distance from the ends of the slot in the
cover. Move the trailing leg of the pointer to a new position if necessary.
WARNING: Make sure that the elevators travel in the correct direction
when you operate the control column.
(13) Move the control column to make sure that the elevators travel in the correct direction.

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

STOP BLOCK 3

STOP BLOCK 2
CABLE END

CABLE END

CABLE A

CABLE B

STOP BLOCK 1

DETAIL A

STOP BLOCK 4

FWD

0710T1001
A0763TC1011

Elevator Trim Tab Travel Stop Adjustment
Figure 204 (Sheet 1)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

ft4140

35
30

-

-

ELEVATOR TRIM

-

TENSION 175 PO

25
20

z

5
10 -

5

0

-40

-30

-20

-1

0

10

20

30

40

50

60

70

80

90

100

10

DEGREES FAHRENHEIT
160

140
ELEVATOR TRIM C
120.
TENSION 78 N AT
100

60

40

20
0

-40

35 -30

-25 -20 -15 -1

-5

0

5

10

15

20

25

30

35

40

45

DEGREES CELSIUS
Elevator Trim Cable Tension
Figure 205 (Sheet 1)

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MAINTENANCE MANUAL
(14) Make sure that the trim tab moves in the correct direction when it is operated by the trim wheel.
NOTE:

Nose down trim corresponds to the tab UP position.

(15) Safety the turnbuckle (Refer to Chapter 20, Safetying - Maintenance Practices).
(16) Install all of the items that you removed to get access to the components.
(17) Remove the support stand.

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MAINTENANCE MANUAL
STALL WARNING SYSTEM - MAINTENANCE PRACTICES
1.

2.

3.

General
A.

The stall warning system includes a stall warning horn and stall detector. The stall warning horn is
located inside the cabin behind the headliner, overhead and to the outboard side of the pilot, on the
fuselage rib. The (heated) stall detector is mounted on the leading edge of the left wing at WS 91.25.
The PITOT HEAT/OFF switch on the circuit panel assembly provides power to the heating element
of the stall detector.

B.

The stall detector is actuated by airflow over the surface of the wing. The stall detector internal switch
will close as a stall condition is approached, actuating the stall warning horn. The stall detector should
actuate the stall warning horn approximately 4.5 to 9.0 knots above airplane stall speed.

Stall Warning Horn Assembly Removal and Installation
A.

Remove Stall Warning Horn Assembly (Refer to Figure 201).
(1) Remove electrical power from airplane. Disengage WARN circuit breaker on circuit panel
assembly.
(2) Remove headliner to access stall warning horn assembly. Refer to Chapter 25, Interior
Upholstery - Maintenance Practices.
(3) Identify, tag, and disconnect stall warning horn wiring at stall warning horn connector (P1/JC030).
(4) Remove nuts and washers securing stall warning horn assembly to adapter plate.
(5) Remove stall warning horn assembly from airplane.

B.

Install Stall Warning Horn Assembly (Refer to Figure 201).
(1) Position stall warning horn on adapter plate and secure with nuts and washers.
(2) Connect stall warning horn wiring at stall warning horn connector (P1/JC030).
(3) Install headliner. Refer to Chapter 25, Interior Upholstery - Maintenance Practices.
(4) Restore electrical power to airplane. Engage WARN circuit breaker on circuit panel assembly.

Stall Detector Removal and Installation
A.

Remove Stall Detector (Refer to Figure 201).
(1) Remove electrical power from airplane. Disengage WARN circuit breaker on circuit panel
assembly and place PITOT HEAT/OFF switch to OFF.
(2) Remove access plate 610JB to access stall detector. Refer to Chapter 6, Access/Inspection
Plates - Description and Operation.
(3) Identify, tag, and disconnect electrical wiring from stall detector and disconnect stall warning
connector (JL021/PL021).
(4) Remove screws and nuts securing stall detector to wing leading edge.
(5) Remove stall detector from airplane.

B.

Install Stall Detector (Refer to Figure 201).
(1) Place stall detector at access plate opening and connect electrical wiring to stall detector and
connect stall warning connector (JL021/PL021).
(2) Position stall detector at wing leading edge and secure with screws and nuts.
NOTE:

The lip of the stall detector needs to be approximately 0.06 of an inch (1.52 mm)
below the centerline of the wing skin cutout.

(3) Install access plate 610JB. Refer to Chapter 6, Access/Inspection Plates - Description and
Operation.
(4) Restore electrical power to airplane. Engage WARN circuit breaker on circuit panel assembly.
(5) Adjust stall detector. Refer to Stall Detector Adjustment.

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MAINTENANCE MANUAL

A

STALL WARNING
HORN

WING LEADING
EDGE

)ETAIL A

DETAIL

B

0710T1001
A0718T1022
B0718T1021

Stall Warning Horn and Detector Installation
Figure 201 (Sheet 1)

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MAINTENANCE MANUAL

4.

Stall Detector Adjustment
A.

Adjust Stall Detector.
(1) It is necessary to test fly the airplane to determine if the stall detector actuates the stall warning
horn at the desired speed. Make the following adjustments to stall detector based on results of
test flight.
(a) If stall warning horn sounds at speeds in excess of 9.0 knots above stall speed, then loosen
stall detector mounting screws and move stall detector slightly down. Refer to Stall Detector
Removal and Installation.

WARNING: Do not allow airspeed to drop below airplane stall speed.
If stall warning horn does not sound before reaching stall speed plus 4.5 knots (4.5 knots
above stall speed), then loosen stall detector mounting screws and move stall detector
slightly up. Refer to Stall Warning System - Maintenance Practices, Stall Detector Removal
and Installation.
A successful test of the stall warning system will cause the stall warning horn to sound at 4.5 to
9.0 knots above airplane stall speed.
(b)

(2)

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MAINTENANCE MANUAL
FLAP CONTROL SYSTEM - TROUBLESHOOTING
1.

General
A.

A troubleshooting chart has been developed to aid the maintenance technician in system
understanding. Refer to Figure 101.

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MAINTENANCE MANUAL

B1251

FLAPS FAIL TO MOVE UP OR DOWN
WITH FLAP CONTROL LEVER, BUT
MOVE NORMALLY WITH STANDBY
UP/DOWN SWITCH.

I
CHECK FOR OPEN OR DEFECTIVE
FLAP MOTOR CIRCUIT BREAKER.
IF-

OK, CHECK
SWITCH. IF-

NOT OK, ENGAGE OR
REPLACE CIRCUIT
BREAKER.

OK, CHECK FOR MOTOR
FAILURE. IF-

NOT OK, REPLACE
SWITCH IF NECESSARY.

OK, CHECK FOR BROKEN OR
DISCONNECTED WIRES.
REPAIR AS NECESSARY.

NOT OK, REPLACE
AS NECESSARY.

Flap System Troubleshooting Chart
Figure 101 (Sheet 1)

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MAINTENANCE MANUAL

B1252

FLAPS FAIL TO MOVE UP OR DOWN
WITH FLAPS CONTROL LEVER.

FLAPS MOVE ONLY ONE DIRECTION.

I
CHECK FOR DEFECTIVE LINKAGE,
DEFECTIVE FLAP TRACKS, DEFECTIVE
BELLCRANKS OR CABLE SNAGGING.
IF-

I
OK, CHECK
TRANSMISSION
OR DRIVE
SCREW.
REPLACE
COMPONENTS
AS NECESSARY.

CHECK FOR DEFECTIVE UP OR
DOWN OPERATING SWITCH. IF -

NOT OK, REPLACE
SWITCH.

I
NOT OK, REPLACE
COMPONENTS
AS NECESSARY.

Flap System Troubleshooting Chart
Figure 101 (Sheet 2)

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MAINTENANCE MANUAL

B1253

BINDING IN SYSTEM AS FLAPS
ARE RAISED AND LOWERED.

I
CHECK FOR CABLES NOT
RIDING ON PULLEYS. IF -

I
OK, CHECK FOR BIND
IN DRIVE PULLEYS.

NOT OK, ROUTE CABLES
CORRECTLY OVER PULLEYS.

I
OK, CHECK FOR

NOT OK, REPLACE

FRAYED CABLE.

DEFECTIVE PULLEYS. I

OK, CHECK FOR FLAPS
BINDING ON TRACKS
OBSERVE FLAP TRACKS
AND ROLLERS. REPLACE
DEFECTIVE PARTS.

NOT OK, REPLACE
DEFECTIVE CABLE.

Flap System Troubleshooting Chart
Figure 101 (Sheet 3)

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MAINTENANCE MANUAL
FLAP CONTROL SYSTEM

-

MAINTENANCE PRACTICES

1.General
A. The wing flap control system contains an electric flap motor, transmission assembly, drive pulleys,
push-pull rods, cables, and a follow-up control. Power from the motor and the transmission assembly
is transmitted to the flaps by a system of drive pulleys, cables, and push-pull rods. Electric power to
the motor is controlled by two microswitches mounted on a floating arm assembly, a cam lever, and a
follow-up control. As the flap control lever is moved to the desired flap setting, the attached cam trips
one of the microswitches, activating the flap motor. As the flaps move to the position selected, the
floating arm is rotated by the follow-up control until the active microswitch clears the cam, breaking
the circuit and stopping the motor. To reverse flap direction, the control lever is moved in the opposite
direction, causing the cam to trip the second microswitch, which reverses the flap motor. The follow-up
control moves the cam until it is clear of the second switch, shutting off the flap motor. Limit switches
at the flap actuator assembly control flap travel as the flaps reach the full UP or DOWN positions.
*
2.
*

*

3.
*

B.

For a schematic of the flap system, refer to Figure 201.

Flap Motor and Transmission Assembly Removal/Installation
A. Flap Motor (MR001) and Transmission Assembly Removal (Refer to Figure 202).
(1) Lower the flaps fully.
(2) Set the ALT/BAT MASTER switch to the off position.
(3) Remove the access panels 61 OBB and 61 OCB. Refer to Chapter 6, Access/inspection Plates Description and Operation.
(4) Remove the bolt that attaches the actuating tube to the drive pulley.
(5) Turn the actuating tube in toward the transmission as far as possible by hand.
(6) Remove the bolt that attaches the flap motor hinge to the wing. Keep the brass washer between
the hinge and the wing structure.
(7) Disconnect the electrical connectors from the flap motor (MR001).
(8) Disconnect the electrical connectors from the up limit switch (SR001) and the down limit switch
(SR002).
(9) Carefully remove the flap motor and the transmission assembly from the wing through the access
opening.
B. Flap Motor and Transmission Assembly Installation (Refer to Figure 202).
(1) Carefully install the flap motor and the transmission assembly into the wing through the access
opening. If the hinge assembly was removed from the transmission, make sure that the short
end of the hinge is installed toward the top.
(2) Connect the electrical connectors to the flap motor (MR001).
(3) Connect the electrical connectors to the up limit switch (SR001) and the down limit switch
(SR002).
(4) Attach the flap motor hinge to the wing with the bolt and the brass washer.
(5) Turn the actuating tube out toward the bell crank.
(6) Install the bolt that attaches the actuating tube to the drive pulley.
(7) Install the access panels 61OBB and 610CB. Refer to Chapter 6, Access/inspection Plates Description and Operation.
(8) Set the ALT/BAT MASTER switch to the ON position.
(9) Make sure that the flaps operate correctly. Refer to Flap System Adjustment/Test for rigging
instructions.
Flap Removal/Installation
A. Flaps Removal (Refer to Figure 202).
(1) Lower the flaps fully with the flap selector switch.
(2) Set the ALT/BAT MASTER switch to the off position.
(3) Remove access panels 511AT (611AT), 511BT (6111BT), 511CT (611CT), and 511DT (611DT)
from the leading edge of the flap. Refer to Chapter 6, Access/Inspection Plates - Description
(4 aisondOecatitepshplordanhefa.bakt
a4isondOeration.shpl rda hefabakt

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MODEL 1821T182
MAINTENANCE MANUAL

B1 724

FLAP MOTOR AND

FWD
DRIVE PULLEY

DRIVE PULLEY

SETSCREW

)R
I;I

TURNBUCKLES
PUSH-PU LL
ROD

PUSH-PULL
ROD
TO LEFT
WING FLAP

TO RIGHT
WING FLAP

VIEW LOOKING DOWN

0525T1 007

Flap System Schematic
Figure 201 (Sheet 1)

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MODEL 182/Ti 82
MAINTENANCE MANUAL

I

C2

3LE
kRD

DETAIL

DETAIL

D

A

SPACER
PUL

BUSHING

BUSHING

DETAIL

GUARD

C
DETAIL

B

0710T1001
A076AR 1001
607638R1019
C0764R1 003
D076481002

Wing Flap Control System Installation
Figure 202 (Sheet 1)

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MODEL 182/1182

MAINTENANCE MANUAL

81255

NOTE:

A

FLAP
MOTOR
HINGE

USE LOCTITE GRADE CV ADHESIVE
ON THREADS OF SETSCREW AND
TORQUE TO 40 INCH POUNDS (4.5 N~m).

TRANSMISSION
BOLT

S ElrsCREW
(NCITE)

II

PUSH-PULL

ROD

UP LIMIT
SWITCH
(SR001)
SWITCH
ACTUATING
COLLAR

MOTOR
(MR001)

DOWN LIMIT
SWITCH (SR002)
0

DRIVE
PULLEY

RETRACT
CABLE

0
C

0

0

DETAIL

E

AU IUA IINU

COLLAR
\PS IN THE FULL UP POSITION

TRANSMISSION
VIEw

A-A

E0725R 1004
AA0725R 1005

Wing Flap Control System Installation
Figure 202 (Sheet 2)

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MAINTENANCE MANUAL

B7803

WASHER

:) 0 Ar'V
It CT

i

J
H
DETAIL

PLUG
N

F

G

P'LUU IIU I I UN

ACCESS PLATE

DETAIL U

NUT

G0525T1 006

OUTBOARD

J5510

Wing Flap Control System Installation
Figure 202 (Sheet 3)

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MAINTENANCE MANUAL
(5) Remove the bolts at each flap track.
NOTE:
*

B.

The washers, rollers, and bushings will fall as the flap is removed from the wing. Keep
the hardware for installation.

Flaps Installation (Refer to Figure 202).

CAUTION: Make sure that the width of the flap track slot is 0.5735 inch +0.03
or -0.03 inches. The flap track must be replaced if the width is not
in the limits.
(1)

Install the flap to the flap tracks.
NOTE:

It is permitted to apply 3M Y8671 (or equivalent) polyurethane tape on the upper flap
skins as required to prevent chafing against the wing trailing edge.

(2) Connect the push-pull rod to the flap bracket.
NOTE:

I
4.
*

*

Flap rigging may not be necessary if the push-pull rod adjustment was not disturbed.

(3) Install access panels 511 AT (61 1AT), 511 BT (611 BT), 51liCT (611 CT), and 511 DT (611 DT) to
the leading edge of the flap. Refer to Chapter 6, Access/Inspection Plates - Description and

~

~~~Operation.

(4) Set the inboard side of the MASTER switch to BAT.
(5) Raise the flaps to the full position with the flap selector switch.
(6) Set the BAT side of the MASTER switch to the off position.
Flap Drive Pulley RemovaVlnstallation
A. Flap Drive Pulley Removal (Refer to Figure 202).
(1) Remove the overhead console. Refer to Chapter 25, Interior Upholstery - Maintenance
Practices.
(2) Remove the safety clips and loosen the flap adjustment at the turnbuckles.
(3) Remove the access plates~l OBB and 51 OCB. Refer to Chapter 6, Access/inspection Plates Description and Operation.
(4) Remove the bolt that attaches the flap push-pull rod to the drive pulley.
(5) Carefully lower the right flap.
(6) Remove the bolt that attaches the actuating tube to the drive pulley.
(7) Carefully lower the left flap.
(8) Remove the cable locks that attach the control cables to the drive pulley. Tag the cables for
identification.
(9) Remove the bolt that attaches the drive pulley to the wing.
(10) Carefully remove the drive pulley through the access opening without dropping the bushing.
(11) Keep the brass washer from between the drive pulley and the wing structure for installation.
B.

Flap
(1)
(2)
(3)
(4)
(5)
(6)
(7)
(8)

Drive Pulley Installation (Refer to Figure 202).
Install the drive pulley and the bushing through the access opening.
Install the brass washer and attach the drive pulley to the wing structure with the bolt.
Remove the identification tags and install the cable locks that attach the control cables to the
drive pulley.
Raise the left flap fully and install the bolt that attaches the actuating tube to the drive pulley.
Raise the right flap fully and install the bolt that attaches the flap push-pull rod to the drive pulley.
Install the access plates 51 OBB and 51 OCB. Refer to Chapter 6, Access/Inspection Plates Description and Operation.
Adjust the flap drive cables as necessary. Refer to Flap Control Adjustment/Test.
Install the overhead console. Refer to Chapter 25, Interior Upholstery - Maintenance Practices.

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MAINTENANCE MANUAL

5.

Flap Control System Adjustment/Test
A.

Rig the Flap Control System (Refer to Figure 202 and Figure 203).
(1) Remove the overhead console. Refer to Chapter 25, Interior Upholstery - Maintenance
Practices.
(2) Remove the access plates 510OBB, 510OCB and 61 OBB. Refer to Chapter 6, Access/Inspection
Plates - Description and Operation.
(3) Remove the safety clips, loosen the cable tension, disconnect the turnbuckles, and carefully
lower the left flap.
(4) Disconnect the push-pull rods at the drive pulleys in both wings and carefully lower the right flap.
(5) Disconnect the actuating tube from the drive pulley.
(6) Adjust both push-pull rods to 8.83 inches +0.12 inch -0.12 inch between the centers of the rod
end bearings, and tighten the locknuts on both ends.
(7) Attach the push-pull rods to the flaps and the drive pulleys.
(a) If the control cables are not connected to the left and the right drive pulleys, the actuating
tube and the push-pull rods must be disconnected before you install the cables.
(b) If the drive pulleys are not installed, attach the control cables before you install the drive
pulleys in the wings.
(8) Turn the actuating tube in toward the transmission by hand 0.12 inch +0.05 or -0.05 inches
between the switch actuating collar and the transmission.
(9) Temporarily connect the cables at the turnbuckles.
(10) Test the flaps by hand to make sure that both flaps extend and retract together. If they do not,
the cables are incorrectly attached to the drive pulleys. Make sure that the right drive pulley
rotates clockwise when viewed from below as the flaps are extended.
(11) Place identification tag on the cables, and disconnect the turnbuckles.
(12) Loosen the setscrew that attaches the actuating tube to the switch actuating collar and hold the
collar to maintain 0.1 2 inch +0.05 or -0.05 inches. Hold the right flap up, and adjust the actuating
tube in or out as necessary to align with the attachment hole in the drive pulley.
(13) Apply Loctite grade CV sealant to the threads of the setscrew and torque to 40 inch pounds.
(14) Disconnect the push-pull rod at the drive pulley.
(15) Manually hold the right flap in a full up position and readjust the push-pull rod to align with the
attachment hole in the drive pulley.
(16) Connect the push-pull rod and tighten the locknuts.
(17) Set the flaps in the full up position.
(18) Shut off the electrical power to the flap motor (MR001) by loosening the setscrew and the idle
up limit switch adjustment block on the support to activate the switch.
(19) Tighten the setscrew.
(20) Manually hold the left flap full up and connect the control cables at the turnbuckles. Remove the
identification tags that are installed on the control cables.
(21) Adjust the retract cable first. With the flaps up, adjust the turnbuckles to 30 pounds, +10 or -10
pounds (133.45 N, +44.48 or -44.48 N) of tension on the cables at 70 0F (21 'C). Refer to the
Charts in Figure 202 for the correct tensions at other temperatures.
(22) Disconnect the push-pull rod at the left drive pulley.
(23) Turn on the motor (MR001) to extend the flaps approximately 20 degrees.
(24) Check the tension on each flap cable.
(25) Adjust the turnbuckles as necessary to maintain 30 pounds, +10 or -lO pounds (133.45 N, +44.48
or -44.48 N) of tension on the cables at 70 OF (21 0 C). Refer to the Charts in Figure 202 for the
correct tensions at other temperatures.
(26) Install safety clips on the turnbuckles. Refer to Chapter 20, Safetying - Maintenance Practices.
(27) Fully retract the right flap.
(28) Manually hold the left flap in the up position and adjust the push-pull rod to align with the attaching
hole in the drive pulley.
(29) Attach the push-pull rod and tighten the locknuts.
(30) Set an inclinometer on the right flap and adjust to zero degrees.
(31) Operate the flaps to the full down position. Repeat the check on the left flap.
(32) Adjust the down limit switch (SR002) to stop the flap motor (MR001) and flap at the degree of
travel.

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MODEL 182/Ti82

MAINTENANCE MANUAL

5ai4

El
UK

I

II

I

I

I

I

IUPPER

II

UMIT
I -li\L \

FLAP CABLES (0,094 AND 0.1251-lNCH DLAMMTR)
I

I

I

II

I

I

TENSION 30 POUNDS AT 70 IF
.
~~~~II
II

NW

I
-40

=30

-20

-

=1 0

0

.10

20 30
DEGRIEES FAHRENHEIT

0

300
U)250
9 200
z

z
0 150
50

0
I

DEGREES CELSIUS

Flap Cable Tension
Figure 203 (Sheet 1)

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MODEL 182/Ti 82
MAINTENANCE MANUAL
(33) Check the down limit switch (SR002) through some flap cycles.
(34) Connect and rig the flap follow-up system. Refer to Flap Follow-Up and Indicating System Maintenance Practices.
(35) Complete an operational check.
(36) Check all items for correct safetying. Refer to Chapter 20, Safetying - Maintenance Practices.
(37) Install the access plates 51OBB, 510CB and 611OBB1. Refer to Chapter 6, Access/Inspection
Plates - Description and Operation.
(38) Install the overhead console. Refer to Chapter 25, Interior Upholstery - Maintenance Practices.

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MODEL 182/T182
MAINTENANCE MANUAL
FLAP FOLLOW-UP AND INDICATING SYSTEM - MAINTENANCE PRACTICES
1.

General
A.

2.

The flap follow-up and indicating system consists of a sheathed cable assembly, pointers and
microswitches. One end of the cable is attached to the flap operating switch operating arm. The
other end is clamped to the flap direct cable, above the headliner in the rear cabin area. Motion of the
flap cable is transmitted through the follow-up control to the pointer, attached to the switch mounting
arm. Pointer moves along a scale as the flaps are extended or retracted. When the motion of the
switch mounting arm with the attached operating switches positions the "active" operating switch to
clear the cam on flap lever, flap motor circuit is broken and flaps stop at selected position.

Flap Follow-Up and Indicating System Removal/Installation
A.

Remove Flap Control Lever. (Refer to Figure 201).
(1) Remove follow-up control torque tube from switch mounting arm.
(2) Remove flap UP S1007 and DOWN SI008 operating switches from switch mounting arm. Do not
disconnect electrical wiring at switches.
NOTE:

Insulators are installed between switches and switch mounting arm.

(3) Remove knob from control lever.
(4) Remove remaining washers, bushings, switch mounting arm, and control lever by removing
mounting bolt. Use care not to drop parts into tunnel area.
B.

Install Flap Control Lever. (Refer to Figure 201).
(1) Install mounting bolt, assembling washers, bushings, switch mounting arm, and control lever.
NOTE:

Before installing knob on control lever, clean threads on control lever with methyl
propyl ketone or equivalent. After threads have thoroughly dried, prime with grade T
primer. Allow primer to flash off or dry for three to five minutes. Apply grade CU Loctite
(MIL-S-22473), Loctite 271, STA-LOK Catalog No. 800, or equivalent to threads of
control lever.

(2) Install knob and allow Loctite to cure for five to twenty minutes before service.
(3) Install flap UP S1007 and DOWN SI008 operating switches on switch mounting arm, making sure
to install insulators.
(4) Install follow-up control torque tube to switch mounting arm.
(5) Rig system. Refer to Flap Follow-Up and Indicating System Adjustment/Test.
3.

Flap Follow-Up and Indicating System Adjustment/Test
A.

Rig
(1)
(2)
(3)
(4)

Flap Follow-Up and Indicating System. Refer to Figure 201.
Run flaps to full up position.
Remove overhead center console.
Secure follow- up cable to retract cable with clamp assembly.
Torque clamp nut to 40 inch-pounds to 50 inch-pounds (4.52 N.m to 5.65 N.m) and lock with a
second nut.
(5) Pull all slack from follow-up cable, and with position indicator in full UP position connect
turnbuckle to follow-up cable.
(6) Connect spring to arm assembly.
(7) Make minor cable length adjustments using turnbuckle to position indicator at "0" degrees.
(8) With control lever in the full UP position adjust Up S1007 operating and Down S1008 operating
switch in slotted holes until cam is centered between switch rollers. Ensure control lever is in
full UP position during this adjustment.
(9) Mount inclinometer on trailing edge of one flap and set to "0" Degrees.
(10) Turn master switch S1009 ON and move control lever to "10" degree position.
(11) If flaps travel is more than 10 Degrees, +2 or -2 degrees, adjust flap DOWN operating switch
away from cam and recycle flaps.
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MODEL 182/T182
MAINTENANCE MANUAL

PULLEY
CABLE
GUARD

I/
DETAIL

Ut I AIL /^

D

BUSHING
PUL

BUSHING

SPACER

DETAIL B

DETAIL C

0710T1001
A0764T1001
B0763T1020
C0764T1003
D0764T1002

Flap Control Lever and Follow-up Installation
Figure 201 (Sheet 1)

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MODEL 182/T182
MAINTENANCE MANUAL

RETRA(

FOLLOW-UI

DETAIL
NOTE:

D

TORQUE CLAMP NUTTO
40 TO 50 INCH POUNDS (4.5 TO 5.6 N.m)

CABLE
GUARD

PULLEY

I/

CABLE
GUARD
PULLEY

CABLE
GUARD
DETAIL

F

DETAIL

E
D07641006
E07641007
F07641007

Flap Control Lever and Follow-up Installation
Figure 201 (Sheet 2)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
(12) If flaps travel is less than 10 Degrees, +2 or -2 degrees, adjust flap DOWN operating switch
closer to cam and recycle flaps.
(13) Move control lever to "20" degree position.
(14) If flaps travel is more than 20 Degrees, +2 or -2 degrees, adjust flap DOWN operating switch
away from cam and recycle flaps.
(15) If flaps travel is less than 20 Degrees, +2 or -2 degrees, adjust flap DOWN operating switch
closer to cam and recycle flaps.
(16) Adjust flaps UP SI007 operating switch in slotted holes for 0.062 inch (1.51 mm) clearance
between switch roller and cam when the flaps DOWN S1008 operating switch has just opened
in the "10" degree and "20" degree position.
NOTE:

Flap travel on UP cycle may deviate a maximum of 4 degrees from indicated position.

(17) Turn master switch S1009 ON and run flaps through several cycles, stopping at various mid-range
settings and checking that cable tension is within limits. Retract cable tension may increase to
90 pounds (400 N) when flaps are fully retracted.
(18) Check all rod ends and clevis ends for sufficient thread engagement, and all jamnuts are tight.
(19) Install overhead center console.

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CHAPTER

FUEL

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82
MAINTENANCE MANUAL

LIST OF EFFECTIVE PAGES
PAGE

DATE

28-00-00

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CHAPTER-SECTION-SUBJECT
28-Title
28-List of Effective Pages
28-Record of Temporary Revisions
28-Table of Contents

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Jul 1/2007

Pages 501-506

Jul 1/2007

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April 1/2002

28 - LIST OF EFFECTIVE PAGES
©Cessna Aircraft Company

Page 1 of 1
Jul 1/2007

RECORD OF TEMPORARY REVISIONS
Temporary Revision
Number

Page Number

Issue Date

By

Date Removed

By

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82
MAINTENANCE MANUAL

CONTENTS
FUEL - GENERAL ................................
Scope....................................
Tools, Equipment and Materials........................
Definition ..................................

28-00-00
28-00-00
28-00-00
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FUEL STORAGE AND DISTRIBUTION - DESCRIPTION AND OPERATION......
General ...................................
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 Ti 8208001 and On) .......................
Auxiliary Fuel Pump Serviceability Test (Airplanes 18280001 thru 18280944) ...

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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 ................
General...................................
Tools and Equipment.............................
Classification of Fuel Leaks..........................
Sealing Fuel Leaks..............................
Testing Integral Fuel Bay...........................

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201
201
201
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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

FUEL - GENERAL
1.

Scope
A.

2.

This chapter provides information on systems and components associated with fuel storage, fuel
distribution, refueling and fuel quantity indicating.

Tools, Equipment and Materials
NOTE:

Equivalent substitutes may be used for the following items:

NAME

NUMBER

MANUFACTURER

USE

Fuel Quantity Test
Box

0580001-1

Cessna Aircraft Company
Cessna Parts Distribution
Department 701, CPD
25800 East Pawnee Road
Wichita, KS 67218-5590

To calibrate fuel quantity
system.

Pressure Regulator

Commercially Available

To regulate input pressure.

Thermometer

Commercially Available

To monitor test area
temperature.

Eldorado Chemical Co. Inc.
14350 Lookout Road
P. 0. Drawer 34837
San Antonio, TX 78265-4837

To locate source of leak.

Commercially Available

To clean surfaces prior to
sealing.

Commercially Available

To remove loose primer.

Leak Detector

Eldorado LD-4

Methyl Propyl
Ketone
ScotchBrite Pad
3.

N/A

Definition
A.

This chapter is divided into sections and subsections to assist maintenance personnel in locating
specific systems and information. For locating information within the chapter, refer to the Table of
Contents at the beginning of the chapter.

28-00-00
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Page 1

April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
FUEL STORAGE AND DISTRIBUTION - DESCRIPTION AND OPERATION
1.

General
A.

B.

C.

The airplane is equipped with a wet wing fuel storage system. The system consists of two integral
fuel tanks (one each wing), a four position selector valve, an electrically driven auxiliary fuel pump,
fuel strainer, and a fuel quantity indicating system.
Components beyond the fuel strainer include the engine driven fuel pump, the fuel/air control unit and
the fuel distribution valve. These components are considered part of the power plant and are covered
in Chapter 73, Fuel Injection System - Description and Operation.
A schematic of the entire fuel system is shown to aid in system understanding. Refer to Figure 1.

©Cessna Aircraft Company

28-20-00
Page 1
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

B1258

FUEL QUANTITY INDICATORS
ITITY
-ER

LEFT I

TANK

VENT
(WITH
VALVE

DRAIN VALVE

AUXILIARY
FUEL PUMP
SWITCH
FUEL STRAINER

AUXILIARY DRAI

I-

DRAIN VALVE

UNIT

LEGEND
I

I

FUEL SUPPLY

I

I

VENT

-..

FUEL FLOW
INDICATOR

. ~ELECTRICAL
CONNECTION

4*4w.,
0791CT1001

Fuel System Schematic
Figure 1 (Sheet 1)

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Page 2

April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

B2056

FUEL QUANTITY INDICATORS

VAPnR

LEFT

VALVL

=r----

AUXILIARY FUEL PUMP

AUXILIARY
FUEL PUMP
SWITCH

FL

IVEN

DRAIN VALVE
IL UNIT

UTION UNIT

LEG!

I
I

I
I

FU

FUEL FLOW
INDICATOR

VEI
ELI
CO

ltt

(182T AND T182T)
0791C1001

Fuel System Schematic
Figure 1 (Sheet 2)

28-20-0 10
© Cessna Aircraft Company

Page 3

April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182
MAINTENANCE MANUAL
FUEL STORAGE AND DISTRIBUTION

-

MAINTENANCE PRACTICES

General
A.
2.

Precautions
A.

3.

This section gives fuel storage and distribution maintenance practices for the fuel tank component
removal and installation, and adjustment/test (Refer to Figure 201 and 202).

Obey these general precautions and rules when you refuel, defuel, clean the fuel tank, repair,
assemble or disassemble system components, and do electrical system tests and repairs on the
airplane fuel system.
(1) Put covers or caps on all disconnected hoses, lines, and fittings to prevent residual fuel drainage,
thread damage, or entry of dirt or unwanted material into the fuel system.
(2) When the fuel system is opened, use the fuel boost pump to flush the system with 1/2 gallon of
fuel at the inlet of the servo and flow divider.
(3) When you work on the fuel injection system, keep all parts clean and free from contamination.

Fuel Drain Valve Removal/installation
NOTE:

4.

The left and right fuel drain valve removal and installation are typical. Five fuel drains are installed
in each wing.

A.

Remove the Fuel Drain Valve (Refer to Figure 203).
(1) Defuel the airplane. Refer to Chapter 12, Fuel - Servicing.
(2) With a fuel sampler cup, push each fuel drain valve up to make sure that the fuel tank is fully
drained.
(3) Remove the safety wire and remove each fuel drain valve from the fuel tank. Chapter 20,
Safetying - Maintenance Practices.

B.

Install the Fuel Drain Valve (Refer to Figure 203).
(1) Install a new 0-ring on the fuel drain valve.
(2) Install the fuel drain valve in the fuel tank and safety the valve with wire to the clip. Refer to
Chapter 20, Safetying - Maintenance Practices.
(3) Add a small quantity of fuel to the fuel tank and examine the fuel drain valve for leaks.

Fuel Quantity Sender Removal/installation
NOTE:

The fuel quantity sender removal/installation is typical for left and right fuel tanks.

NOTE:

A.

Examine the fuel level sender for correct operation before you replace the fuel quantity indicator.
The resistance must be 6 ohms +5 or -5 ohms when empty, and 90 ohms +5 or -5 ohms when
full.
Remove the Left and Right Fuel Quantity Senders (Refer to Figure 204).
(1) Defuel the airplane. Refer to Chapter 12, Fuel Servicing.
(2) Remove the headliner to get access to the wing root. Refer to Chapter 25, Cabin Panels Removal/Installation.
(3) Disconnect the wire ring terminals from the fuel level sender.

CAUTION: Do not bend the float arm of the fuel level sender.
(4) Remove and keep the screws that attach the fuel level sender to the nut ring. Carefully remove
the fuel level sender and the gasket from the fuel tank. Keep the gasket for an inspection and
for installation.

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CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182

MAINTENANCE MANUAL

CFl
MN
F uK

MiI 1

=D

C'Afl

FUEL TANK

SMTTER

FILLER CAP

ELE
FUE

JT
)ELS)

FUEL STRAINER
DETAIL A
(182S)

071OT1 001
A0716T2001

Fuel System
Figure 201 (Sheet 1)

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Page 202
Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182
MAINTENANCE MANUAL

1--

VAPOR RETURN LINE

FUEL
STRAINER

rUI-L OILILU I Uri

DETAIL

VMLVI-

A

(182T AND T1 82T)
07lOTi1001
A0716T 1015

Fuel System
Figure 202 (Sheet 1)

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CESSNA AIRCRAFT COMPANY

MODEL 182/Ti82
MAINTENANCE MANUAL

0
X IP
DRAIN VALVE BOSS

)-RING

ICIUIM~
F_
ILA

-I'+

A

A

VIEW

A-A

LOOKING UP
071 OT1
001
A0726T1 001
AA0726T1 002

Fuel Drain Valve
Figure 203 (Sheet 1)

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CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82
MAINTENANCE MANUAL

E

RIB
NUT RING
SCI

FUEL QUANTITY
TRANSMITTER

DETAIL

A

LEFT SIDE SHOWN
(RIGHT SIDE TYPICAL)
NLIBRATION ACCESS HOLES
EACH SIDE OF INDICATOR)

FUEL QUANTITY INDICATOR

DETAIL

071OT1 001
A0714T1027
BS32777-2

B
Fuel Quantity System
Figure 204 (Sheet 1)

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CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182
MAINTENANCE MANUAL
B.

Install the Left and Right Fuel Quantity Senders (Refer to Figure 204).
NOTE:

Do the fuel quantity calibration only after installation of the fuel level sender.

(1) Examine the gaskets for cracks or other damage that can prevent the gasket from making a
good seal. If the gaskets have damage, or if there are signs of fuel leaks, install new gaskets.
Always install new gaskets when you install a new fuel level sender./

CAUTION: Do not bend the float arm of the fuel level sender.
(2) Carefully install the fuel quantity sender into the fuel tank and attach the nut ring with screws.
(3) Connect the wire ring terminals to the fuel level sender.
(4) Install the headliner. Refer to Chapter 25, Cabin Panels - Removal/Installation.
5.

Fuel Tank Vents Adjustment/Test
A.
B.

DESCRIPTION - A vent line is installed in the outboard end of each fuel tank and extends overboard
through the lower wing skin near the point where lift struts attach to the underside of the wings.
TEST - Fuel vents may become clogged as shown by field experience, and can cause fuel starvation
of the engine. If the bleed hole in the vent valve becomes clogged, over- pressurization can occur due
to normal temperature variation. This would usually occur when the airplane engine is not operating.
The procedure that follows must be used to make sure that the fuel vent and bleed system operate
correctly.
(1) Attach a rubber tube to the end of the vent line below the wing.

WARNING: Clogged vent lines and bleed holes can cause either fuel
starvation or the pressurization of the fuel tanks by fuel
expansion. You must clean any fuel vent found clogged or not
operating correctly before the airplane is returned to service.
(2) As you do the test, put a cap on the vent in the opposite wing.
(3) Blow air into the tube to pressurize the tank. If air can enter the tank, the vent line is open.
(4) After the tank is pressurized with a small quantity of air, insert the end of the rubber tube into a
container of water and look for a continuous stream of bubbles. This shows that the bleed hole
in the valve assembly is open, and that the valve assembly releases tank pressure.
(5) After completing step B.(3), blow air into the tube again to pressurize the tank. Crimp the rubber
tube to keep pressure in the tank. Loosen, but do not remove, the filler cap on the opposite wing.
If pressure is released through the filler cap, the cell crossover line is open. Remove the rubber
tube from the end of the vent line below the wing.
(6) Do steps B.(1) thru B.(5) again on the opposite wing.
NOTE:

A serviceable wing fuel vent check valve will release positive pressure through the
bypass port from the fuel tank. An unserviceable wing fuel vent check valve will not
release positive pressure through the bypass port from the fuel tank.

(7) If the fuel vent check valve is unserviceable, do the procedures that follow (Refer to Figure 205).
(a) Defuel the airplane. Refer to Chapter 12, Fuel - Servicing.
(b) Remove the wing access panels (510KB and 610KB) to get access to the wing fuel vent
check valve. Refer to Chapter 6, Inspection/Access Plates - Description and Operation.
(c) Remove the unserviceable wing fuel vent check valve and replace it with a new fuel vent
check valve. Make sure that the bypass hole on the valve flap is set at the top of the fuel
tank.
(d) Install and seal the wing fuel tank access plate. Make sure that the access plate is fully
sealed. Refer to Chapter 28, Fuel Bay Sealing - Maintenance Practices.
(e) Do steps B(1) thru B(7) again to make sure that the new fuel vent check valve operates
correctly.

28-20-00
© Cessna Aircraft Company

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Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182
MAINTENANCE MANUAL

E6

LEFT FUEL
VENT LINE

DETAIL

A

BYPASS PORT
(NOTE)

C

FUEL VENT
CHECK VALVE

DETAIL

NOTE:

C

IF THE PRESSURE TEST SHOWSc
THE BYPASS PORT IS CLOGGEE
THE CHECK VALVE MUST BE RE
INSTALL THE NEW VALVE WITH
HINGE/BYPASS PORT ON THE
TOP OF THE FUEL TANK.

FUEL VENT LINE

DETAIL

B

071OT1 001
A12261001
8 1226100-4

CSB99T2806

Fuel Vent Location
Figure 205 (Sheet 1)

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Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 1821T182
MAINTENANCE MANUAL
(f)

Fill the fuel tanks with fuel and examine the tanks for leaks. If leaks are apparent, defuel,
disassemble, and seal the tanks again until no leaks are found. Refer to Chapter 28, Fuel
Bay Sealing - Maintenance Practices.
(8) Make sure that the vent line is in the correct position in relationship to the wing struts. Refer to
Figure 206 and to Adjustment Procedures below.
(a) Put a six-inch scale perpendicular to the wing skin and measure the distance from the wing
skin to the end of the fuel vent line.

WARNING: One of the fuel vent lines must stay set behind the lift strut
with the dimensions given in Figure 204. This position will
give protection against ice formation in at least one vent
tube.
NOTE:

It may be necessary to remove the strut cuff to get an accurate measurement
using the six-inch scale.

1

The distance from the wing skin to the bottom of the fuel vent line must be 3.46 inches,
+0.03 or -0.03 inch.
(b) Using a six-inch scale, measure the straight line distance from the back of the wing strut
to the end of the fuel vent line.
1
The distance from the strut to the end of the fuel vent line must be 1.12 inches, +0.03
or -0.03 inch.
(9) If adjustments are necessary for the fuel vent line, do the procedure that follows.
(a) Remove and keep the access panels (510KB1 from the left wing and 610KB from the right
~ ~~~~wing).
Refer to Chapter 6, Access/inspection Plates - Description and Operation.
(b) Loosen the clamp on the fuel vent line.
(c) Adjust the fuel vent line with your hand to the proper dimensions.
(d) Tighten the clamp on the fuel vent line.
(e) Install the access/inspection plates.

I
C.

ADJUSTMENT - In some cases, fuel may flow in different quantities through each nozzle when the
fuel selector valve is in the BOTH position. This is caused by different quantities of pressure applied
to each of the individual fuel tank vents. Correct this condition with the procedure that follows.
NOTE:
(1)
(2)
(3)
(4)
(5)
(6)

This procedure must be done during a sequence of routine flight operations. Special flights
to measure and adjust the fuel tank feed rates are not recommended.

Examine the venting system to make sure that the lines are open, all connections are tight, and
that the system operates correctly.
Park the airplane on level ground and set fuel selector switch in the BOTH position. Keep the
airplane parked until the tank levels are equal, or until the two tanks are full.
After takeoff, with the fuel selector in the BOTH position, climb to an altitude where there is no
turbulence.
Adjust the airplane for straight and level flight. Make sure that the airplane is free of yaw by
adjusting the rudder to align the ball to the center of the turn coordinator. Fly at maximum cruise
power for a minimum of one hour.
At the end of the hour, and while still in straight and level flight, record the fuel tank levels as
shown on the fuel gage.
If the fuel tank levels are different by more than 5.0 gallons, do the applicable steps that follow
after the airplane is on the ground.
(a) Find the fuel tank with the most remaining fuel. With your hand, move the fuel vent on the
bottom of the wing outboard 0.25 inch.
(b) Find the fuel tank with the least remaining fuel. With your hand, move the fuel vent on the
bottom of the wing inboard 0.25 inch.
NOTE:

One of the vents must remain positioned behind the strut as illustrated in Figure
206 for icing protection.

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Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82

MAINTENANCE MANUAL

NOTE:

YOU CAN MOVE THE LEIFT OR RIGHT
VENT OUTBOARD FROM THE POSITION
SHOWN TO BALANCE THE PRESSURE
RELEASE FROM EACH TANK. ONE OF
THE VENTS MUST STAY IN THE
POSITION SHOWN TO PREVENT THE
FORMATION OF ICE.

WING

4 OUT

I

VIEW
LOOKING
FORWARD

WING

Di

STRUT

4 FWD

4ES
DETAIL A
LEFT SIDE SHOWN
(RIGHT SIDE OPPOSITE)
Fuel Vent Location
Figure 206 (Sheet 1)

0526TC1008

28-2000
©Cessna Aircraft Company

Page 209
Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182ffT182

MAINTENANCE MANUAL
(c)

6.

Do steps 5.C.(1) thru 5.C.(6) again and make sure that the fuel flow rates for the tanks are
equal, ±5.0 gallons/hour.

Fuel Filler Cap Vent Cleaning/Seal Replacement
A.

Examine, Clean, and Repair the Vented Fuel Filler Cap (Refer to Figure 207).
(1) Remove the vented fuel filler cap from the adapter assembly, disconnect the safety chain (if
installed), and put a cover or cap on the tank opening to keep unwanted material out.
(2) Examine the condition of the gasket and frictionless washer, and replace if necessary.
(3) Use cotton swabs and solvent to carefully lift the edges of the rubber umbrella inside the fuel
cap and clean the inside of the umbrella to remove all contaminants. Use a second cotton swab
to clean the umbrella , and remove all cotton fibers. Repeat these steps until the cotton swabs
show no discoloration.
(4) Replace the umbrella if the vent shows that there is a leak or shows deterioration.
NOTE:

It can be faster to buy and replace the fuel filler cap assembly, which is an alternative
to the removal of the umbrella.

CAUTION: Be careful when you remove the umbrella stem. If the umbrella
stem breaks when you remove it, make sure you remove all the
stem parts from the vent before you install the new umbrella.
If the stem parts are left in the vent, the vent will not operate
correctly.
(a) To remove the umbrella, apply lubricant to the umbrella stem with MIL-PRF-5606 hydraulic
fluid to prevent damage to the stem.
(b) When you install the new umbrella, apply lubricant to the stem with MIL-PRF-5606
hydraulic fluid. Use a small blunt tool to install the knob on the umbrella into the check
valve body.
(5) Connect the fuel cap to the safety chain (if installed) and install the cap in the adapter assembly.
7.

Fuel Selector Valve Removal/Installation
A. Remove the Fuel Selector Valve (Refer to Figure 208 and Figure 209).
(1) Drain all of the fuel from the wing fuel tanks. Refer to Chapter 12, Fuel - Servicing.
(2) Drain all of the fuel from the fuel selector valve and the door post fuel lines by draining the fuel
through the fuel selector valve drain.
(3) Remove the carpet as necessary to get access to the access plate (230DB) and remove the
access plate. Refer to Chapter 6, Access/Inspection Plates - Description and Operation.
(4) Remove the cotter pin and pin from the fitting assembly and disconnect the fitting from the valve.
(5) Disconnect the inlet and outlet fuel lines from the valve. Put a cover on the valve fittings and
seal the lines.
(6) Remove the safety wire and remove the screws and washers that attach the valve. Remove the
valve.
B. Install the Fuel Selector Valve (Refer to Figure 208 and Figure 209).
(1) Put the fuel selector valve on the bracket and install the washers and screws. Safety the screws
with wire.
(2) Remove the caps from the fuel selector valve fittings and remove the seals from the fuel lines.
Connect the fuel lines to the fuel selector valve.
(3) Put the fitting on the fuel selector valve and install the pin and cotter pin.
(4) Refuel the airplane and examine the fuel lines for leaks. Refer to Chapter 12, Fuel - Servicing.
(5) Install the access plate (230DB). Refer to Chapter 6, Access/Inspection Plates - Description and
Operation.
(6) Install the carpet.

28-20-00
rC Cessna Aircraft Company

Page 21 0
Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 1821T182
MAINTENANCE MANUAL

SCREW

r

f%^%

~~~,If

%-I/'Jv ~r-I,

=EL
CAP BODY

1ICTION LESS WASHER
kSKET

K VALVE

DETAIL

A

LEFT SIDE SHOWN
(RIGHT SIDE TYPICAL)

071 OT1 001
A05261 006

Vented Fuel Filler Cap
Figure 207 (Sheet 1)

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CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182

MAINTENANCE MANUAL

0

PLUG BUTTON
I

SCREW
WASH ER

I---

A

W1-Ainfi

r:

,CKET

)CK

GUIDE

IEW

SCREW
WASHER
PIN
'HER
TTER
PIN
TTER
SELECTOR VALVE

BELLY SKIN

rE MTrAI
I
IE
Lo 9--1 V%116

OT1 001.

At
N-S

I --AIU

AU/1011VV4

~

Fuel Selector Valve
Figure 208 (Sheet 1)

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Page 212
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CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82

MAINTENANCE MANUAL

L

Clfl

RETAINER

M r-1 AI

ISPRING

SEAL'
BUSHII
O-RING-

INSERT
0-RIN(
WASHER

BALL

WASHER
BODY

0-RING
SPRING

VALVE

DETAIL

A

(182T AND T1 82T)
0710T1001
A0985T1116

Fuel Selector Valve
Figure 209 (Sheet 1)

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Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182
MAINTENANCE MANUAL

8.

Fuel Strainer Disassembly/CleaninglAssembly0
A.

Disassemble and Clean the Fuel Strainer (Refer to Figure 210).
(1) Turn the fuel selector valve to the OFF position.
(2) Disconnect the strainer drain tube, remove the safety wire, nut, and washer at the bottom of the
filter bowl, and remove the bowl.
(3) Carefully remove the standpipe.
(4) Remove the filter screen and gasket.
(5) Clean the filter screen and the bowl in solvent and dry with compressed air.

B.

Assemble the Fuel Strainer (Refer to Figure 210).
(1) Install the screen and standpipe with a new gasket between the filter screen and the top
assembly. Tighten the standpipe with your fingers.
(2) Install the bowl with all new 0-rings. Torque the nut to between 25 and 30 inch-pounds.
NOTE:

The step-washer at the bottom of the bowl is installed so that the step is against the
0-ring.

(3) Connect the strainer to the drain tube.
(4) Turn the fuel selector valve to the ON position, close the strainer drain, and examine the system
for leaks. Make sure that the system operates correctly.
(5) Loosen the fuel supply hose at the fuel injection servo inlet.
(6) Set the mixture control to the OFF position.
(7) Set the throttle control to the IDLE STOP position.
(8) Set the FUEL PUMP switch to the ON position.
(9) Operate the electric auxiliary fuel pump until the air is removed from the fuel lines and the pump
is full of fuel.
(110) Set the FUEL PUMP switch to the OFF position.
(11) Tighten the fuel supply hose at the fuel injection servo inlet. Refer to Chapter 20, Torque Data Maintenance Practices.
(12) Install the safety wire from the bottom nut to the top of the assembly. Refer to Chapter 20,
Safetying - Maintenance Practices.
9.

Electric Auxiliary Fuel Pump Removal/Installation (Airplanes 18280001 thru 18280944)
A.

B.

Remove the Electric Auxiliary Fuel Pump (Refer to Figure 211).
(1) Set the MASTER ALT BAT switch to the OFF position.
(2) Turn the fuel selector handle to the OFF position.
(3) Disconnect the battery ground cable from the battery.
(4) Disconnect the electrical connector (P1) from the electric auxiliary fuel pump (UFO05).
(5) Disconnect the fuel lines and drain the line from the electric auxiliary fuel pump.
(6) Loosen the mounting clamps that attach the electric auxiliary fuel pump and remove the pump
from the airplane.
(7) Remove all the fuel fittings from the electric auxiliary fuel pump and discard the used 0-rings
from the inlet and outlet fuel fittings.
Install the Electric Auxiliary Fuel Pump (Refer to Figure 21 1).
(1) Put the new 0-rings on the inlet and outlet fuel fittings.
(2) Install the inlet and outlet fuel fittings into the electric auxiliary fuel pump and tighten the fittings.
Refer to Chapter 20, Torque Data -Maintenance Practices.
(3) Install the fuel drain fitting into the electric auxiliary fuel pump and tighten the fitting. Refer to
Chapter 20, Torque Data - Maintenance Practices.
(4) Put the electric auxiliary fuel pump into mounting clamps.
(5) Loosely install the mounting clamps.
(6) Connect the fuel drain line to the fuel drain fitting.
(7) Connect and tighten the fuel lines to the inlet and outlet fittings.
(8) Tighten the mounting clamps. Refer to Chapter 20, Torque Data - Maintenance Practices.
(9) Tighten the fuel lines onto the fittings. Refer to Chapter 20,Torque Data -Maintenance Practices.
(10) Connect the electrical connectors to the electric auxiliary fuel pump.

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MAINTENANCE MANUAL

Tfl D

SET
SCR E"A

FILTER
ASSEMBLY

STAN DPIF

BOWL

0-RI
WASHE

DETAIL A
071OTi1001
A0716T1003

Fuel Strainer Assembly
Figure 210 (Sheet 1)

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MAINTENANCE MANUAL

H

ELECTRIC

(182S)

0710T1001
A0716T1001

Electric Auxiliary Fuel Pump
Figure 211 (Sheet 1)

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MODEL 182/Ti 82
MAINTENANCE MANUAL
(11)
(12)
(13)
(14)
(15)
(16)
(17)
(18)
(19)
(20)
(21)
(22)
(23)
(24)
10.

Electric Auxiliary Fuel Pump Removal/installation (Airplanes 18280945 and On and Airplanes
T18208001 and On)
A. Remove the Electric Auxiliary Fuel Pump (Refer to Figure 212).
(1) Make sure that the master switch is in the OFF position.
(2) Disconnect the battery ground cable.
(3) Set the fuel selector to the OFF position.
(4) Remove the copilot's seat and carpet. Refer to Chapter 25, Front Seats and Rails - Maintenance
Practices and Chapter 25, Interior Upholstery-Maintenance Practices.
(5) Remove the access plate (230AB) to get access to the pump. Refer to Chapter 6, Access/
Inspection Plates-Description and Operation.
(6) Disconnect the fuel lines, drain line, and electrical connectors from the pump.
(7) Loosen the mounting clamps that attach the pump and remove the pump from the airplane.
B.

11.

Turn the fuel selector handle to the ON position.
Examine the electric auxiliary fuel pump and fuel fittings for fuel leaks.
Connect the battery ground cable to the battery.
Loosen the fuel supply hose at the fuel injection servo inlet.
Set the mixture control to the OFF position.
Set the throttle control to the IDLE STOP position.
Set the MASTER ALT BAT switch to the ON position.
Set the FUEL PUMP switch to the ON position.
Operate the electric auxiliary fuel pump until the air is removed from the fuel lines and the pump
is full of fuel.
Set the FUEL PUMP switch to the OFF position.
Tighten the fuel supply hose at the fuel injection servo inlet. Refer to Chapter 20, Torque Data Maintenance Practices.
Set the FUEL PUMP switch to the ON position.
Operate the electric auxiliary fuel pump and examine all fuel fittings for leaks.
Set the FUEL PUMP switch to the OFF position.

Install the Electric Auxiliary Fuel Pump (Refer to Figure 212).
(1) Put the pump in the mounting clamps and tighten the clamps. Refer to Chapter 20, Torque Data
- Maintenance Practices.
(2) Connect all the fuel lines, drain line, and electrical connectors to the pump.
(3) Set the master switch to the ON position and connect the battery ground cable.
(4) Turn fuel selector to the ON position.'
(5) Operate the electric auxiliary fuel pump and examine all the fuel fittings for leaks.
(6) Install the access plate (230AB). Refer to Chapter 6, Access/Inspection Plates-Description and
Operation.
(7) Install the carpet and copilot's seat. Refer to Chapter 25, Front Seats and Rails - Maintenance
Practices.and Chapter 25, Interior Upholstery-Maintenance Practices.

Auxiliary Fuel Pump Serviceability Test (Airplanes 18280001 thru 18280944)
A.

Auxiliary Fuel Pump Test (Refer to Table 201).

WARNING: Obey all fuel system fire and safety procedures. Remove all
flammable materials from the airplane and from all areas where
the fumes are dangerous.
(1) Remove the fuel supply hose from the inlet fitting of the engine-driven fuel pump.
(2) Install a tee fitting on the fuel supply hose.
(3) Connect a calibrated fuel pressure test gage and locally-purchased fuel shutoff valve to the tee
fitting.
(4) Set the fuel shutoff valve so that the fuel drains into a container.

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MODEL 182/Ti182
MAINTENANCE MANUAL

A

AUXILIARY
FI IR Pi MP

DRAIN LINE

FUEL SELECTOR

FUEL STRAINER

DETAIL

A

(182T AND T1 82T)

07 lT10I0 1
A0716T 158

Electric Auxiliary Fuel Pump
Figure 212 (Sheet 1)

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MODEL 182/T182
MAINTENANCE MANUAL
(5)

Use a controlled electric power source to supply the 24 VDC electric power to the airplane and
a multimeter to measure the electric current.
(a) Operate the auxiliary fuel pump and adjust the fuel shutoff valve to get a pressure value
as shown in Table 201. Make sure that the test is for the applicable part number.
(b) Monitor the current draw of the auxiliary fuel pump electric motor.
(c) Measure the fuel pump current draw and output. The output will be 1 gallon in 2.5 minutes.
NOTE:

The Dukes Model 51 00-00-1 auxiliary fuel pumps that are capable of giving a
minimum flow rate of 23.5 GPH at 23 PSI and have a maximum current of 3.0
amps at 24 volts DC are considered serviceable. Dukes Models 5100-00-3 and
51 00-00-4 auxiliary fuel pumps that are capable of giving a minimum flow rate
of 23.5 GPH at 14 PSI and have a maximum current draw of 3.0 amps at 24
volts DC are considered serviceable.

(6) If the fuel pump does not meet the requirements, replace it with a pump that does meet the
requirements.
(7) If the fuel pump meets the requirements, it must be considered serviceable.
Table 201. Dukes Model 51 00 Serviceability Requirements
FUEL FLOW
VOLUME

PUMP PART
NUMBER
________

____

FUEL FLOW
PRESSURE

SUPPLIED
VOLTAGE

(M INIM UM )

MAXIMUM FUEL
PUMP CURRENT
_

_

_

_

51 00-00-1 (or -1RX)

23.5 GPH

23 PSI

24 Volts DC

3.0 Amps

51 00-00-3 (or -3RX)

23.5 GPH

14 PSI

24 Volts DC

3.0 Amps

51 00-00-4 (or -4RX)

23.5 GPH

14 PSI

24 Volts DC

3.0 Amps

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MAINTENANCE MANUAL
(20) Set the FUEL PUMP switch to the OFF position.
(21) Tighten the fuel supply hose at the fuel injection servo inlet. Refer to Chapter 20, Torque Data
Maintenance Practices.
(22) Set the FUEL PUMP switch to the ON position.
(23) Operate the electric auxiliary fuel pump and examine all fuel fittings for leaks.
(24) Set the FUEL PUMP switch to the OFF position.
12.

13.

-

Electric Auxiliary Fuel Pump RemovaVinstallation (Airplanes 18280945 and On and Airplanes
T18208001 and On)
A.

Remove the Electric Auxiliary Fuel Pump (Refer to Figure 212).
(1) Make sure that the master switch is in the OFF position.
(2) Disconnect the battery ground cable.
(3) Set the fuel selector to the OFF position.
(4) Remove the copilot's seat and carpet. Refer to Chapter 25, Front Seats and Rails - Maintenance
Practices and Chapter 25, Interior Upholstery-Maintenance Practices.
(5) Remove the access plate (230AB) to get access to the pump. Refer to Chapter 6, Access/
Inspection Plates-Description and Operation.
(6) Disconnect the fuel lines, drain line, and electrical connectors from the pump.
(7) Loosen the mounting clamps that attach the pump and remove the pump from the airplane.

B.

Install the Electric Auxiliary Fuel Pump (Refer to Figure 212).
(1) Put the pump in the mounting clamps and tighten the clamps. Refer to Chapter 20, Torque Data
- Maintenance Practices.
(2) Connect all the fuel lines, drain line, and electrical connectors to the pump.
(3) Set the master switch to the ON position and connect the battery ground cable.
(4) Turn fuel selector to the ON position.
(5) Operate the electric auxiliary fuel pump and examine all the fuel fittings for leaks.
(6) Install the access plate. Refer to Chapter 6, Access/inspection Plates-Description and
Operation.
(7) Install the carpet and copilot's seat. Refer to Chapter 25, Front Seats and Rails - Maintenance
Practices.and Chapter 25, Interior Upholstery-Maintenance Practices.

Auxiliary Fuel Pump Serviceability Test (Airplanes 18280001 thru 18280944)
A.

Auxiliary Fuel Pump Test (Refer to Table 201).

WARNING: Obey all fuel system fire and safety procedures. Remove all
flammable materials from the airplane and from all areas where
the fumes are dangerous.
(1) Remove the fuel supply hose from the inlet fitting of the engine-driven fuel pump.
(2) Install a tee fitting on the fuel supply hose.
(3) Connect a calibrated fuel pressure test gage and locally-purchased fuel shutoff valve to the tee
fitting.
(4) Set the fuel shutoff valve so that the fuel drains into a container.
(5) Use a controlled electric power source to supply the 24 VDC electric power to the airplane and
a multimeter to measure the electric current.
(a) Operate the auxiliary fuel pump and adjust the fuel shutoff valve to get a pressure value
as shown in Table 201. Make sure that the test is for the applicable part number.
(b) Monitor the current draw of the auxiliary fuel pump electric motor.

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MODEL 182/Ti182
MAINTENANCE MANUAL
P1 ...

A

AUXILIARY
FUEL PUMP

FUEL STRAINER

DETAIL

A

(182T AND T1 82T)

0710T1001
A0716T158

Electric Auxiliary Fuel Pump
Figure 212 (Sheet 1)

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MODEL 182/Ti182
MAINTENANCE MANUAL
(c)

Measure the fuel pump current draw and output. The output will be 1 gallon in 2.5 minutes.
NOTE:

The Dukes Model 5100-00-1 auxiliary fuel pumps that are capable of giving a
minimum flow rate of 23.5 GPH at 23 PSI and have a maximum current of 3.0
amps at 24 volts DC are considered serviceable. Dukes Models 5100-00-3 and
51 00-00-4 auxiliary fuel pumps that are capable of giving a minimum flow rate
of 23.5 GPH at 14 PSI and have a maximum current draw of 3.0 amps at 24
volts DC are considered serviceable.

(6) If the fuel pump does not meet the requirements, replace it with a pump that does meet the
requirements.
(7) If the fuel pump meets the requirements, it must be considered serviceable.
Table 201. Dukes Model 51 00 Serviceability Requirements
FUEL FLOW
VOLUME

PUMP PART
NUMBER
________

____

(M IN IM U M )__

SUPPLIED
VOLTAGE

FUEL FLOW
PRESSURE
_

_

_

_

MAXIMUM FUEL
PUMP CURRENT
_

___

_

5100-00-1 (or -1RX)

23.5 GPH

23 PSI

24 Volts DC

3.0 Amps

5100-00-3 (or -3RX)

23.5 GPH

14 PSI

24 Volts DC

3.0 Amps

5100-00-4 (or -4RX) 123.5 GPH

14 PSI

24 Volts DC

3.0 Amps

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MODEL 182/Ti 82
MAINTENANCE MANUAL
FUEL STORAGE AND DISTRIBUTION

-

ADJUSTMVENT/TEST

1.General
A. This section gives the adjustment/test procedures for the fuel storage and distribution system.
2.

Fuel Quantity Calibration And Check (Airplanes without Garmin G1000)
A.

Fuel Indicator Calibration
(1) Put the fuel selector valve in the BOTH position.
(2) Defuel the airplane. Refer to Chapter 12, Fuel - Servicing.
(a) Open all the wing drain valves and drain the fuel bays until both are empty.
(b) Drain the fuel selector valve until empty.
(3) Put the fuel selector valve in the OF~position.
(4) Remove the fuel quantity indicator from the instrument panel.
(5) Install a 0580001 -1 test box between the wire harness connector and the fuel quantity indicator
connector.
NOTE:

The internal light for the fuel quantity indicator will not work when the test box is
connected.

(6) Make the airplane level.
(a) Make the wings level to 0.00 degree, +0.25 degree or -0.25 degree. Use blocks under the
wheels or adjust the tire pressure to make the wings level. Refer to Chapter 8, Leveling Maintenance Practices.
(b) Make the airplane level to 2.00 degrees, +0.25 or -0.25 degrees nose up position. Refer
to Chapter 8, Leveling - Maintenance Practices.
(7) Use an external power source to apply 28 VDC, +0.5 or -0.5 VDC, to the airplane, and put the
master switch in the ON position. Put both switches on the test box to the NORM position.
(8) Add unusable fuel to each fuel bay. Refer to Pilots'Operating Handbook for the amount of usable
fuel unusable fuel.
(9) Move the wing tips approximately 5 inches up and down for approximately 10 seconds.
(10) Let the airplane become stable for approximately 30 seconds.
(11) Make sure that the airplane is still at 2 degrees nose up and the wings are still level.
(12) Adjust the "EMPTY" potentiometer, on the fuel quantity indicator, for the left and right gages until
the indicator pointer is in the middle of the red radial line.
NOTE:

A nonmagnetic screwdriver must be used when you adjust the potentiometers on the
fuel quantity indicator.

(13) Make sure that the low-fuel warning-lamps come on.
(14) Fill both fuel bays.
(15) Adjust the "FULL" potentiometer for the left and right gages until the pointer is in the middle of
the white radial line at the full indication.
(16) Make sure the low-fuel warning-lamps go off.
(17) Proceed to the Fuel Warning System Check.
B.

Fuel Warning System Check.
(1) Configure the airplane for the Fuel Warning System Check.
(a) Apply 28 VDC to the airplane.
(b) Set the master switch to ON.
(c) Move the test box switches to NORM.
(d) Make sure the fuel gages read FULL.
(e) Make sure the low-fuel annunciator is OFF.

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MAINTENANCE MANUAL
(2) Turn the NORM/OPEN switch on the text box to the OPEN position and start the timer.
NOTE:

The airplane's digital clock can be used in the timer mode to measure the time of the
annunciators. The interval for this test is from switch operation until the annunciator
begins to flash. The annunciators will flash for approximately 10 seconds before they
come continuously on without a flash.

(3) Monitor the fuel quantity indicator.
(a) Make sure the pointer goes to the power off position below the first graduation.
(b) The annunciators must come on within 75 seconds.
(4) Put the NORM/OPEN switch to the NORM position.
(a) The indicators must read full and the annunciators must go off.
(b) Set the timer again.
(5) Turn the SHORT/NORM/i 00+ OHM switch to the 100+ OHM position. Start the timer.
(6) Monitor the fuel quantity indicator.
(a) Make sure the pointer goes to the power off position below the first graduation.
(b) The annunciators must come on within 75 seconds.
(7) Turn the SHORT/NORM/i100+ OHM switch to the NORM position.
(a) The indicators must read full and the annunciators must go off.
(b) Set the timer again.
(8) Turn the SHORT/NORM/i100+ OHM switch to the SHORT position. Start the timer.
(9) Monitor the fuel quantity indicator.
(a) Make sure the pointer goes to the power off position below the first graduation.
(b) The annunciators must come on within 75 seconds.
(10) Turn the SHORT/NORM/i 00+ OHM switch to the NORM position.
(a) The indicators must read full and the annunciators must go off.
(ii1) Set the airplane digital clock back to the clock mode.
(12) Set the master switch to OFF.

(13) Remove the test box.0
(14)
(15)
(16)
(17)
3.

Install the fuel quantity indicator in the instrument panel.
Set the master switch to ON.
Make sure the fuel quantity indicators show FULL and the annunciators are off.
Set the master switch to OFF.

Fuel Quantity Calibration and Fuel Flow Test (Airplanes with Garmin G1000 with software version
563.01 or earlier)
NOTE:

The software version is shown on the upper right corner of the MED on the first page displayed
after power is applied the MED in normal operation.

NOTE:

If the fuel quantity indicator on the Garmin G1000 system has a red X on it during normal
operation, examine the sender and wiring and refer to the Garmin G1000 Line Maintenance
Manual for more Garmin system troubleshooting. If the values given on the Primary Flight
Display (PFD) are not the same as the values given in the calibration procedure, refer to the
Garmin G1lOQO Line Maintenance Manual for troubleshooting.

A.

Do a Fuel Quantity Calibration and Fuel Flow Test.
(1) Put the selector valve in the BOTH position.
(2) Defuel the airplane. Refer to Chapter 12, Fuel - Servicing.
(a) Drain the fuel tanks with all wing drain valves until the two tanks are empty.
(b) Drain the fuel-selector drain valve until it is empty.
(3) Put the fuel selector valve in the OFF position.
(4) Make the airplane level.
(a) Make the wings level to 0.0 degrees, +0.25 or -0.25 degree. Use blocks under the wheels or
adjust the tire pressure to make the wings level. Refer to Chapter8, Leveling -Maintenance
Practices.
(b) Make the airplane level to 2.00 degrees, +0.25 or -0.25 degree, in the nose up position.
Refer to Chapter 8, Leveling - Maintenance Practices.

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MAINTENANCE MANUAL
(5) Add unusable fuel to each fuel tank. Refer to the Pilot's Operating Handbook for the amount of
usable fuel.
(6) Move the wing tips approximately 5 inches up and down for approximately 10 seconds.
(7) Let the airplane become stable for approximately 30 seconds.
(8) Put the BAT MASTER switch to the ON position while you push the ENT button on the PFD.
(9) Release the ENT button after the words INITIALIZING SYSTEM show on the FED.
NOTE:

The FED is now in the configuration mode.

(10) Use the Flight Management System (EMS) outer knob to go to the CAL page group.
(11) Use the EMS inner knob to go to the FUEL CALIBRATION page.
(12) Put the AVIONICS master switch in the ON position while you hold down the ENT button on the
MED.
(13) Release the ENT button after the words INITIALIZING SYSTEM show on the MED.

CAUTION: Before you do the calibration procedure, you must turn on the
G1000 system and let it become stable for a minimum of three
minutes.
NOTE:

The MED is now in the configuration mode.

(14) Push the softkeys on the EUEL CALIBRATION page of the FED, in the sequence that follows,
to enter the password.
(a) Push Softkey 12 (far right softkey).
(b) Push Softkey 11.
(c) Push Softkey 10.
(d) Push Softkey 9.
(15) Make sure that the EUEL FLOW ENG 1 SCALE value is 1.00000.
(a) If the FUEL ELOW ENG 1 SCALE value is not 1.00000, use the EMS knobs to make it
1.00000. Push in the inner EMS knob to activate the cursor. Use the outer EMS knob to
select EUEL FLOW ENG 1 SCALE. Use the inner EMS knob to change the value.
(16) Push the L RESET softkey to set the left calibration parameters to the default values.
NOTE:

When L RESET is pushed, the system shows the warning message "WARNING!
Pressing 'OK' will cause the calibration to revert to the default settings."

(17) Push ENT to make the OK selection.
(18) Make sure that the airplane is level at 2.0 degrees nose up position and 0.0 degrees wings level
attitude.
(19) Make sure that the CAL VAL value shown for the LEFT 1 SUB-TANK is stable.
(20) Push the L EMPTY softkey.
(21) Push the R RESET softkey to set the right calibration parameters to the default values.
NOTE:
(22)
(23)
(24)
(25)
(26)
(27)
(28)
(29)
(30)

When R RESET is pushed, the system shows the warning message "WARNING!
Pressing 'OK' will cause calibration to revert to default settings."

Push ENT to make the OK selection.
Make sure that the CAL VAL value shown for the RIGHT 1 SUB-TANK is stable.
Push the R EMPTY softkey.
Make su re that the CAL VAL values are between -0. 10 and +0. 10 gallon ( -0.38 and +0.381) for
the LEFT 1 SUB-TANK.
Make sure that the CAL VAL values are between -0.10 and +0.10 gallon ( -0.38 and +0.381) for
the RIGHT 1 SUB-TANK.
Put the AVIONICS master switch in the OFF position.
Put the BAT MASTER switch in the OFF position.
After a minimum of 10 seconds, put the BAT MASTER switch in the ON position.
Make sure that the left, L, and right, R, fuel quantity pointers are on the red line.

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MAINTENANCE MANUAL
(31)
(32)
(33)
(34)
(35)
(36)

Put the BAT MASTER switch in the OFF position.
Put the BAT MASTER switch to the ON position while the ENT button on the PFD is held down.
Release the ENT button after the words INITIALIZING SYSTEM show on the PFD.
Use the EMS outer knob to go to the CAL page group.
Use the EMS inner knob to go to the FUEL CALIBRATION page.
Put the AVIONICS master switch to the ON position while the ENT button on the MED is held
down.
(37) Release the ENT button after the words INITIALIZING SYSTEM show on the MED.

CAUTION: Before you do the calibration procedure, you must turn on the
G1000 system and let it become stable for a minimum of three
minutes.
(38)
(39)
(40)
(41)
(42)
(43)
(44)
(45)
(46)
(47)
(48)
(49)

(50)
(51)
(52)
4.

Add 5 gallons of fuel (low fuel level) to the left fuel tank. Refer to Chapter 12, Fuel - Servicing.
Make sure the fuel is sensed in the LEFT 1 SUB-TANK.
Add 5 gallons of fuel (low fuel level) to the right fuel tank. Refer to Chapter 12, Fuel - Servicing.
Make sure the fuel is sensed in the RIGHT 1 SUB-TANK.
Move the wing tips approximately 5 inches up and down for approximately 10 seconds.
Let the airplane become stable for approximately 30 seconds.
Make sure that the airplane is level at 2.0 degrees nose up position and 0.0 degrees wings level
attitude.
Make sure the CAL VAL values are stable for the LEFT 1 SUB-TANK and RIGHT 1 SUB-TANK
on the PFD.
Make sure the CAL VAL value for the LEFT 1 SUB-TANK is between 6.5 to 9 gallons.
Make sure the CAL VAL value for the RIGHT 1 SUB-TANK is between 6.5 to 9 gallons.
If the values are in the tolerance range, the procedure is complete.
If the CAL VAL values are not in tolerance:
(a) Move the wing tips approximately 5 inches up and down for approximately 10 seconds.
(b) Let the airplane become stable for approximately 30 seconds.
(c) Make sure that the airplane is level at 2.0 degrees nose up position and 0.0 degrees wings
level attitude.
(d) Make sure the CAL VAL values are stable for the LEFT 1 SUB-TANK and RIGHT 1 SUBTANK on the PFD.
(e) Make sure the CAL VAL value for the LEFT 1 SUB-TANK is between 6.5 to 9 gallons.
1
If the CAL VAL is still not in the tolerance range, drain the fuel from the tanks and do
the fuel calibration procedure again.
(f) Make sure the CAL VAL value for the RIGHT 1 SUB-TANK is between 6.5 to 9 gallons.
1
If the CAL VAL is still not in the tolerance range, drain the fuel from the tanks and do
the fuel calibration procedure again.
Inflate the tire to the correct pressure.
Put the AVIONICS switch to the OFF position.
Put the BAT MASTER switch to the OFF position.

Fuel Quantity Calibration and Fuel Flow Test (Airplanes with Garmin G1000 with software version
563.02 or later)
NOTE:

The software version is shown on the upper right corner of the MED on the first page displayed
after the MED is powered on in normal operation.

NOTE:

If the fuel quantity indicator on the Garmin G1000 system has a red X on it during normal
operation, examine the fuel quantity sender and wiring and refer to the Garmin G1000 Line
Maintenance Manual for more Garmin system troubleshooting. If the values given on the PFD
are not the same as the values given in the calibration procedure, refer to the Garmin G1000
Line Maintenance Manual for troubleshooting.

A.

Do a Fuel Quantity Calibration and Fuel Flow Test.
(1) Put the selector valve in the BOTH position

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MAINTENANCE MANUAL
(2) Defuel the airplane. Refer to Chapter 12, Fuel - Servicing.
(a) Drain the fuel tanks with all wing drain valves until the two tanks are empty.
(b) Drain the fuel-selector drain valve until it is empty.
(3) Put the fuel selector valve in the OFF position.
(4) Make the airplane level.
(a) Make the wings level to 0.0 degrees, +0.25 or -0.25 degree. Use blocks under the wheels
or adjust tire pressure to make the wings level. Refer to Chapter 8, Leveling - Maintenance
Practices.
(b) Make the airplane level to 2.00 degrees, +0.25 or -0.25 degrees nose up position. Refer
to Chapter 8, Leveling - Maintenance Practices.
(5) Add unusable fuel to each fuel tank. Refer to the Pilot's Operating Handbook for the unusable
fuel quantity.
(6) Move the wing tips approximately 5 inches up and down for approximately 10 seconds.
(7) Let the airplane become stable for approximately 30 seconds.
(8) Put the BAT MASTER switch to the ON position while you push the ENT button on the PFD.
(9) Release the ENT button after the words INITIALIZING SYSTEM show on the PFD.
NOTE:

The PFD is now in the configuration mode.

(10) Use the Flight Management System (FMS) outer knob to go to the CAL page group.
(11) Use the FMS inner knob to go to the FUEL CALIBRATION page.
(12) Put the AVIONICS master switch in the ON position while you hold down the ENT button on the
Multi-Function Display (MFD).
(13) Release the ENT button after the words INITIALIZING SYSTEM show on the MFD.

CAUTION: Before you do the calibration procedure, you must turn on the
G1000 system and let it become stable for a minimum of three
minutes.
NOTE:

The MFD is now in the configuration mode.

(14) Use the FMS outer knob to go to the GRS page group on the MFD.
(15) Use the FMS inner knob to go to the GRS/GMU CALIBRATION page on the MFD.
(16) Push the softkeys on the FUEL CALIBRATION page of the PFD, in the sequence that follows,
to enter the password.
(a) Push Softkey 12 (far right softkey).
(b) Push Softkey 11.
(c) Push Softkey 10.
(d) Push Softkey 9.
(17) Make sure that the FUEL FLOW ENG 1 SCALE value is 1.00000.
(a) If the FUEL FLOW ENG 1 SCALE value is not 1.00000, use the FMS knobs to make it
1.00000. Push in the inner FMS knob to activate the cursor. Use the outer FMS knob to
select FUEL FLOW ENG 1 SCALE. Use the inner FMS knob to change the value.
(18) Push the TNK SEL softkey to highlight the CURRENT TANK field.
(19) Turn the inner FMS knob to select LEFT.
(20) Make sure that the airplane is level at 2.0 degrees nose up and 0.0 degrees wings level attitude.
(21) Make sure that the CALIBRATED TOTAL value shown for the LEFT TANK is stable.
(22) Push the EMPTY softkey and press the enter (ENT) button to add the calibration point to the
CALIBRATION TABLE.
(23) Make sure that the CALIBRATED TOTAL values are between -0.1 0 and +0.1 0 gallon ( -0.38 and
+0.381) for the LEFT TANK.
(24) Push the TNK SEL softkey to highlight the CURRENT TANK field.
(25) Turn the inner FMS knob to select RIGHT.
(26) Make sure that the CALIBRATED TOTAL value shown for the RIGHT TANK is stable.
(27) Push the EMPTY softkey and press the ENT button to add the calibration point to the

CALIBRATION TABLE.

28-20-00
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CESSNA AIRCRAFT COMPANY

MODEL 182/Ti82
MAINTENANCE MANUAL
(28) Make sure that the CALIBRATED TOTAL vaiues are between -0.10 and +0.10 gallon (-0.38 and
+0.381) for the RIGHT TANK.
(29) Make sure there is only one calibration point in the CALIBRATION TABLE. Under ACTUAL
QUANTITY you must have '0.00 GL" and you must have one number under CALIBRATED
VALUE. If you have more points in the CALIBRATION TABLE highlight them and push the
DELETE softkey.
(30) Make sure that the left, L, and right, R, fuel quantity pointers are on the red line on the MED on
the GRS group GRS/GMU CALIBRATION page.
(31) Add 5 gallons of fuel (low fuel level) to the left fuel tank. Refer to Chapter 12, Fuel - Servicing.
(32) Make sure fuel is sensed in the LEFT TANK.
(33) Add 5 gallons of fuel (low fuel level) to the right fuel tank. Refer to Chapter 12, Fuel - Servicing.
(34) Make sure fuel is sensed in the RIGHT TANK.
(35) Move the wing tips approximately 5 inches up and down for approximately 10 seconds.
(36) Let the airplane become stable for approximately 30 seconds.
(37) Make sure that the airplane is level at 2.0 degrees nose up and 0.0 degrees wings level attitude..
(38) Make sure the CALIBRATED TOTAL value for the LEFT TANK is stable and between 6.5 to 9
gallons.
(39) Make sure the CALIBRATED TOTAL value for the RIGHT TANK is stable and between 6.5 to 9
gallons.
(40) If the values are in tolerance, the procedure is complete.
(41) If the CALIBRATED TOTAL values are not in the range:
(a) Move the wing tips approximately 5 inches up and down for approximately 10 seconds.
(b) Let the airplane become stable for approximately 30 seconds.
(c) Make sure that the airplane is level at 2.0 degrees nose up and 0.0 degrees wings level
attitude.
(d) Make sure the CALIBRATED TOTAL value for the LEFT TANK is stable and between 6.5
to 9 gallons.
1
If the CALIBRATED TOTAL is still not in the tolerance range, drain the fuel from the
tanks and do the fuel calibration procedure again.
(e) Make sure the CALIBRATED TOTAL value for the RIGHT TANK is stable and between 6.5
to 9 gallons.
1
If the CALIBRATED TOTAL is still not in the tolerance range, drain the fuel from the
tanks and do the fuel calibration procedure again.
(42) Inflate the tire to the correct pressure.
(43) Put the AVIONICS switch to the OFF position.
(44) Put the BAT MASTER switch to the OFF position.

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© Cessna Aircraft Company

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Jul 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
FUEL BAY SEALING - MAINTENANCE PRACTICES
1.

General
A.

The fuel bays may need to be resealed if a leak has developed or if the wing has been repaired. This
procedures provides instructions for sealing fuel bays, classifying fuel leaks and testing fuel bays after
repair.

2.

Tools and Equipment
A.

3.

Refer to Fuel - General, for Tools and Equipment.

Classification of Fuel Leaks
A.

B.

Fuel leaks are classified in to one of four categories based on the observed size of the leaks.
Dependent on where the leak is located, immediate corrective action may be required prior to flight.
Leaks may be classified as follows and are illustrated in Figure 201:
(1) Stains - An area of 0.75 inch (19.05 mm) or less in diameter.
(2) Seep - An area from 0.75 inch to 1.50 inch (19.05 mm to 38.1 mm) in diameter.
(3) Heavy Seep - An area from 1.50 inch to 4.00 inch (38.1 mm to 101.6 mm) in diameter.
(4) Running Leak - Size varies with location and intensity of leak.
The following leaks require corrective action before further flight:
(1) Running leaks in any area.
(2) Stains, seeps or heavy seeps in an enclosed area.
NOTE:

C.
4.

5.

An enclosed area is defined as the wing leading edge and the section of wing inboard
or outboard of the fuel bays.

The following leaks require correction when the airplane is grounded for other maintenance:
(1) Stains, seeps or heavy seeps not in an enclosed area.

Sealing Fuel Leaks
A.

Determine Source of Leak.
(1) Fuel can flow along a seam or structure of the wing for several inches, making the leak source
difficult to find. A stained area is an indication of the leak source.
(2) Fuel leaks can be found by testing the complete bay as described in Testing Integral Fuel Bay.
(3) Another method of detecting the source of a fuel leak is to remove access doors and blow with
an air nozzle from the inside of the bay in the area of the leak while soap bubble solution is
applied to the outside wing skin.

B.

Repair Leak.
(1) Remove existing sealant in the area of the leak.
(2) Clean the area and apply a filet seal. Press sealant into leaking area with a small paddle, working
out all air bubbles.
(3) If leakage occurs around a rivet or bolt, replace the rivet or loosen bolt, retorque and reseal
around nutplate.
(4) Apply Type VIII sealant to access doors, fuel quantity transmitter, etc., as required and reinstall
to structure. Refer to Chapter 20, Fuel, Weather and High-Temperature Sealing - Maintenance
Practices.
(5) Allow sealant to cure completely.
(6) Test fuel bay for leakage. Refer to Testing Integral Fuel Bay.

Testing Integral Fuel Bay
A.

The fuel system consists of two vented, integral fuel tanks (one in each wing). The following procedure
should be used only after sealant has fully cured.
(1) Remove vent line from vent fitting and cap fitting.
(2) Disconnect fuel lines from bay.

28-21-00
© Cessna Aircraft Company

Page 201
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

B1265

HEAVY
SEEP

SEEP

t

0.75 TO
1.50 INCH
(19 TO 38 mm)

1.50 TO
4.00 INCHES
(38 TO 100 mm)

1

\'

4 0
STAIN
0.75 INCH (19 mm)
MAXIMUM

RUNNING
LEAK
A

SIZE WILL VARY
WITH LOCATION
AND INTENSITY
OF LEAK.
UEL WILL USUALLY
LOW IN THIS AREA
LONG SKIN CONTOUR
FTER IT IS WIPED DRY.
FUEL USUALLY DRIPS
AT THIS POINT.
V

0516T1006

Classification of Fuel Leaks
Figure 201 (Sheet 1)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
(3) To one of the bay fittings, attach a water manometer capable of measuring 20 inches (.508 m)
of water.
(4) To the other bay fitting, connect a well regulated supply of air (0.5 PSI (415 Pa) maximum, or
13.8 (0.351 m) inches of water). Nitrogen may be used where the bay might be exposed to
temperature changes while testing.
(5) Make sure filler cap is installed and sealed.
(6) Apply pressure slowly until 0.5 PSI (415 Pa) is obtained.
(7) Apply a soap solution as required.
(8) Allow 15 to 30 minutes for pressure to stabilize.
(9) If bay holds for 15 minutes without pressure loss, seal is acceptable.
(10) Reseal and retest if any leaks are found.

28-21-00
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Page 203
April 1/2002

CHAPTER

ICE AND RAIN
PROTECTION

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

LIST OF EFFECTIVE PAGES
CHAPTER-SECTION-SUBJECT

PAGE

DATE

30-00-00

Page 1

April 1/2002

30-20-00

Pages 201 -202

April 1/2002

30-60-00

Page 1

Jan 2/2006

30-60-00

Pages 101 -110
Pages 201 -203

Janl1/2007

30-Title
30-List of Effective Pages
30-Record of Temporary Revisions
30-Table of Contents

30-60-00

©Cessna Aircraft Company

30

-

April 1/2002

LIST OF EFFECTIVE PAGES

Page 1of 1
Janl1/2007

RECORD OF TEMPORARY REVISIONS
Temporary Revision
Number

Page Number

Issue Date

By

Date Removed

By

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182

MAINTENANCE MANUAL

CONTENTS
ICE AND RAIN PROTECTION - GENERAL.....................
Scope....................................
Definition ..................................
WINTERIZATION KIT - MAINTENANCE PRACTICES ................
General...................................
Winterization Kit Installation..........................
PROPELLER HEAT (T182 ONLY) - DESCRIPTION AND OPERATION ........
General...................................
Description and Operation ..........................
PROPELLER HEAT - TROUBLESHOOTING ....................
General...................................

30-60-00 Page 101
30-60-00 Page 101

PROPELLER HEAT - MAINTENANCE PRACTICES.................
General...................................
Propeller Heat Timer/Monitor Removal/Installation ...............
Propeller Heat Annunciator Removal/Installation ................
Deice Boots Removal/installation .......................

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30-00-00 Page 1
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30-20-00 Page 201
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30 - CONTENTS

Page
Page
Page
Page
Page

201
201
201
201
201

Page 1of 1
Janl1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
ICE AND RAIN PROTECTION - GENERAL
1.

Scope
A.

2.

This chapter describes the procedures and components used to prevent or dispose of the formation
of ice and rain on various parts of the aircraft.

Definition
A.

This chapter is divided into sections and subsections 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 winterization provides procedures and techniques for the installation of the
winterization kit.
(2) The section on propeller heat provides procedures and techniques for the maintenance of the
propeller heat system.

© Cessna Aircraft Company

30-00-00
Page 1
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
WINTERIZATION KIT - MAINTENANCE PRACTICES
1.

2.

General
A.

The winterization kit consists of two coverplates (with placards) which attach to the air intakes in
the cowling nosecap and a placard silk-screened on the instrument panel, and insulation for the
engine crankcase breather line. This equipment should be installed for operations in temperatures
consistently below 20 degrees F (-7 degrees C). Once installed, the engine crankcase breather
insulation is approved for permanent use in both hot and cold weather.

B.

The winterization kit may be installed on 182S and 182T airplanes when temperatures are consistently
below 20 degrees F (-7 degrees C). This procedure provides instructions for the installation and
removal of the winterization kit and installation of the breather line insulation.

Winterization Kit Installation
A.

Winterization Cover Installation (Refer to Figure 201).
(1) Position Nose Covers in the air intake openings of the nosecap and mark the positions of the
holes.
NOTE:
(2)
(3)
(4)
(5)
(6)

B.

Be sure existing holes on nose covers align with existing holes in nosecap.

Using the newly made marks, drill holes through the nosecap.
Remove engine cowling and upper and lower nosecaps from the aircraft.
Using the nutplates as a template, mark and drill holes. Countersink holes on the forward side
of the nosecap.
Install and secure nutplates on the aft side of the nosecap with rivets.
Install covers, secure with screws.

Breather Line Insulation Installation. (Refer to Figure 201).
(1) Remove clamps from the breather line.
(2) Slip insulation tubes over breather line.
(3) Secure tube with a small amount of EC1300 cement (3M Corporation) or equivalent in
accordance to dimensions shown.
NOTE:
(4)

Ensure vent holes are not covered. If necessary, it is acceptable to trim the insulation.

Reconnect clamps.

30-20-00
CCessna Aircraft Company

Page 201
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

NOSE
COVE
(RH)

TUBE
EXISTING HC
4UTPLATES

rrr

oitwVV (t)
0710T1001
A0714T1017

Winterization Equipment
Figure 201 (Sheet 1)

30-20-00
© Cessna Aircraft Company

Page 202
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
PROPELLER HEAT (T182 ONLY) - DESCRIPTION AND OPERATION
1.

General
A.

2.

A propeller electrical heated boot system is standard equipment.

Description and Operation
A.

The system is of an electrothermal type. It has electrically heated boots bonded to each propeller
blade. There is a slip ring assembly for power distribution to the propeller boots and a brush block
assembly to transfer electrical power to the rotating slip ring. A propeller heat timer/monitor cycles
electrical power to the boots in the correct sequence and monitors the boot's heater current. There is
propeller heat indication for either correct or failed system operation. A toggle switch labeled PROP
HEAT controls the engine propeller heat system.
The propeller heat system also includes a larger alternator for additional current capacity. It has a
higher Amp/Hour Battery to support the additional current load required by the propeller heat system.
The propeller heat system applies heat to the surfaces of the propeller blades where ice would
normally adhere. This heat, plus centrifugal force and the blast from the airstream, removes
accumulated ice.
When the PROP HEAT switch is placed in the ON position, the timer controls electrical power through
the brush block and slip ring to the three propeller heat boots in intervals of 90 seconds on and 90
seconds off. The propeller heat system is off when the switch is placed in the OFF position. Operation
of the propeller heat system can be checked through the propeller heat annunciation. If the correct
amount of current does not flow to all three elements, the timer/monitor recognizes the condition,
removes current flow to all heating boots, and turns on the amber PROP HEAT annunciation. The
green PROP HEAT annunciation is on during the correct operation of the propeller heat system.

30-60-00
C Cessna Aircraft Company

Page 1

Jan 2/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82

MAINTENANCE MANUAL
PROPELLER HEAT

I

-

TROUBLESHOOTING

General
A. A troubleshooting chart has been developed to aid the maintenance technician in system
understanding. Referto Figure 101 for airplanes without Garmin GlOQO and Figure 102 for airplanes
with Garmin G1000.
B. The propeller heat timer has a 90-second ON cycle and a 90-second OFF cycle. The timer measures
the 90-second cycle interval of the de-icing boots and the correct electrical current (12.5 to 19 amps)
delivered to the de-icing boots. If the 90-second cycle interval or the electrical current delivered to the
de-icing boots is not in permitted limits, the timer causes these to show as faults.
The timer also monitors pin 6 and pin 8 for electrical grounds. If a ground is not applied to pin 6, the
timer causes this to show as a fault. If a ground is applied to pin 8, as occurs when one of the crew
sets the PROP HEAT switch to TEST, the timer causes this to show as a fault and also resets.
When there are faults, the timer disconnects the power that is supplied to the de-icing boots on pin
1, supplies a ground on pin 3 to start the amber alert, and removes a ground from pin 2 to stop the
green alert.
NOTE:

Operation of the propeller heat system for longer than 60 seconds without the propeller
rotation can cause damage to the de-icing boots.

NOTE:

Operation of the propeller heat system at below 24 volts can result in less than sufficient
power for normal operation.

© Cessna Aircraft Company

30-60-00

Page 101
Janl1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/T1182

MAINTENANCE MANUAL

B1978

INo green or amber PROP HEAT annunciation.
IMake sure the PROP HEAT switch/breaker is in the ON position (HI01 1). If-I

lut the switch/breaker in the O
)sition. If the breaker disengages,
.ok for a short circuit in the wiring
tween the Drop heat timer and the
switch/breaker.

Make sure the anti-ice
boots are warm. If-

3ke sure the voltage is between
-.0 and 30.0 VDC at the input of
-cuit breaker or fuse (F73) found in
E?electrical power control unit. If-

I
Examine the electrical power
-ontrol unit and the related wiring.
I

Make sure the same voltage
is supplied at the output of the
circuit breaker or fuse (F3). IfEngage circuit breaker i
sengaged. Replace circuit
breaker if engaged or
replace fuse.

I
I

Make sure the same voltage
is supplied to the PROP HEAT
switch/breaker (H101 1). If-

I

_

I
I

Examine the wiring from
he circuit breaker or fuse
(F73) to the PROP HEAT
switch/breaker (HI01 1).

Make sure the same voltage
is found at the output of the
PROP HEAT switch/breaker
(Hi01ll). If-

Propeller Heat Troubleshooting for Airplanes without Garmin G1 0000
Figure 101 (Sheet 1)

30-60-00
0 Cessna Aircraft Company

Page 102
Janl1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182

MAINTENANCE MANUAL

B1979

Make sure the same voltage
is found at the input pin on th
prop heat timer (pin 5 on PCI
If-

Zeplace the PROP HEAT
switch/breaker (HI11l 1).

I
I

Make sure ground voltage is
found at pin 4 and pin 6 on P
If-

Examine the wiring betwen
the timer and PROP HEAT
switch/breaker.

I
I

iine for a ground on pin
and pin 6 of PCO1 3.

I

I
Get access to the PROP HEAT annunciator
assembly. Disengage the electrical connector.
Make sure the voltage supplied to pins 2 & 3 (J1022) is
between 24.0 and 30.0 VDC. If-

I

sure the
oneter pin 1 or 4 (J1022).
Ifthere is; a ground, repla ce the
PH
RE
OP
AT ann ncia or sse mnb
ly
or
a repw re in the as embly.

troubleshooting

/Make

JIILi IV

Ir

1,~
%-'UN1 I L-2J I IJIJIVI

switch wiring, and the wires
connected to the circuit breaker.

Propeller Heat Troubleshooting for Airplanes without Garmin G1000
Figure 101 (Sheet 2)

30-60-00
© Cessna Aircraft Company

Page 103
Janl1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182

MAINTENANCE MANUAL

B1980

No amber PROP HEAT annunciation
with ANNUNCIATOR TEST/DIM
switch in the TEST position and
PROP HEAT switch/breaker in the
ON position. Get access to the PROP
HEAT annunciator disconnect (JI022)
and do a check for voltage between
24.0 and 30.0 VDC at pin 2. IfMake sure there is a ground
pin 1 (JI022) with the
ANNUNCIATOR TEST/DIM
switch in the TEST position.

Examine the ANNUNCIATOR
EST/DIM switch wiring for open
or short circuits.

H the PROP
ep ace
annunciator assembly or repairswthiteTETp
~sure
Iassembly.
wires in the
wires in the assembly.

Make sure the ANNUNCIATOR
TEST/DIM switch in the TEST position
and the PROP HEAT switch/circuit
breaker in the ON position. Make sure
there is a ground on pin 4 (PCO1 3) and
voltage between 24.0 to 30.0 VDC
on pin 5 of the electrical connector. If-

~~Put the ANNUNCIATI OR TEST/DIM

)sition. Make
I
is a groun( on pin 8 and pin 4
3) of the electri ical connector. If~~(PCO1there

Examine ANNUNCIATOR
TEST/DIM switch wiring on
pin 8 (PCO13) for open
or short circuits.

I

at pins 4 and 5 of PCO1 3, and
ine the wiring of the power and
und circuits for open circuits.
ie for correct operation of H10l1
/breaker and circuit breaker (or
aside the electrical power control

\\L
~~~unit.

Propeller Heat Troubleshooting for Airplanes without Garmin G1lOQO
Figure 101 (Sheet 3)

30-60-00
©Cessna Aircraft Company

Page 104
Jan 1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82

MAINTENANCE MANUAL

B4208

IAmber PROP HEAT annunciation with ANNUNCIATOR TEST/DIM switch not in the TEST position.

Get access to the prop heat timer electrical connector (PCO1 3) and make sure there is bus voltage
between 27 and 29 VDC at pin 5 with the PROP HEAT switch/breaker in the ON position and external
power supplied. IfI

Examine the wiring from the boots to the slip
ring for open wires or short circuits. Make
sure the resistance of all three boots wired
in parallel is 1.6 ohms, +0.2 or -0.2 ohms.
Stretch or bend the deicing boot leads a small
amount and look for intermittent open circuits
and measure the resistance. Push lightly on
the entire deicing boot heating element surface
near the leads. The resistance must not
change. This will help find an intermittent open
circuit that will not show up until the propeller
turns. Does the resistance change? If-

Make sure the connection between the
brushes and the slip ring is clean and
smooth. Make sure that the distance
between the brush holder and the face
of the slip rings is 0.064 inch, +0.01 5
or -0.01 5 inch, through the full rotation
of the slip ring. Make sure the brushes
are aligned with the slip rings so that
the entire face of each brush is in
contact with the slip ring through the full
circumference of the slip ring. Make
sure there is good electrical contact
through the wiring from the brushes to
the timer. If-

nine the power
ution system for
z~ct voltage and
operation.

andomeasur
therescistnce Pus ligtlo
thee tiredeiing bootkheatngdlmn
l
ufc
nerthelashe resistance
muste
notvid

change. Repair the wiring or replace the
defective boots if the resistance is nott
4.8 ohms, +0.3 or -0.3 ohms.

YES

NO

Propeller Heat Troubleshooting for Airplanes without Garmin G1000
Figure 101 (Sheet 4)

©Cessna Aircraft Company

30-60-00

Page 105
Janl1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti182

MAINTENANCE MANUAL

B6563

A

Get access to the prop heat timer
connector (PCO1 3) and look for a
jumper between pins 4 and 6.
Measure and make sure jumper
has continuit. If--

Align again or replace
brushes. Repair wiring
from brushes to timer.
I
I

Make sure there is no ground
pin 8 on the timer electrical
connector. Does pin 8 have a
ground? If-

I

I
Connect a jumper between pin
1 and pin 5 on the timer electrical
connector. (Make the jumper
from 14 AWG wire and two S2353-6
pins.) Put the PROP HEAT
switch/breaker in the ON position.
Does the switch/breaker disengage
or go back to the OFF position?
If-

sure there is a ground only or
*)I* I

U

¼ L J1 1.

-

L
I -Y I tI

AVlt
-Y

,

is in the TEST position.
I

After approximately 20 seconds
with the PROP HEAT switch/
breaker set to ON, make sure
all three boots are warm. If-

Examine fr a short circuit to groun
on the boot and brush block wiring

I
I

ce

epair the boot wiring or
place the unserviceable
boots.

the time

Propeller Heat Troubleshooting for Airplanes without Garmin G1 000
Figure 101 (Sheet 5)

30-60-00
©Cessna Aircraft Company

Page 106
Janl1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82

MAINTENANCE MANUAL

8B4209

No- green or amber PROP HEAT annunciation.I
IMake sure the PROP HEAT switch (HI01 1) is in the ON position. IfPut the switch in the ON
)n. If the breaker disengages,
2kfor a short circuit in the
1between the prop heat timer
and the circuit breaker.

Make sure the deicing
boots are warm. IfI

Make sure there is continuity
across the circuit breaker,
found in the electrical
power control unit. IfIf the circuit breaker is disengaged
*eset the circuit breaker. Look for a
hort circuit in the wiring between the
circuit breaker and PROP HEAT
switch.

Make sure the voltage
is between 24.0 and 30.0
VDC at the circuit
breaker. IfI
I

Make sure the same
voltage is supplied frc
the PROP HEAT swi
(HI1101). If-

Examine the electrical powe
control unit and wiring
connected to it.

I

mine the wiring from te circui
ker found in the electrical powe
)I unit to the PROP HEAT swth
!place the PROP HEAT switc
)20) or circuit breaker (HI1)
if
tound bad.

Make sure the
is found at the
on the prop hE
(pin 5 on PCO

Exainethewirng etween the
timerand
POP HAT switch.

Make sure the wiring from the timer pins 2 and 3 (PCO13) to the G1000 engine/airfra me
monitor is good. A ground should produce an annunciation if the G1000
system is operating correctly. Replace the timer if the wires are
satisfactory and grounding them produces an annunciation.
Propeller Heat Troubleshooting for Airplanes with Garmin G1000
Figure 102 (Sheet 1)

0 Cessna Aircraft Company

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CESSNA AIRCRAFT COMPANY

MODEL 182/Ti82

MAINTENANCE MANUAL

54210

INo Amber PROP HEAT annunciation with PROP HEAT switch in the TEST position.I

Get access to the prop heat timer connector and make sure there is a ground on pin 8 and pin 4
(PCO1 3) and voltage of 24.0 to 30.0 VDC on pin 5 of the electrical connector with PROP HEAT
switch set to the TEST position. If-

I

Make sure the wiring from timer pins 2 and 3
to the GlOQO0 engine/airframe monitor is
good. A ground should produce an
annunciation if the G1000 system is
operating correctly. Replace timer if the
wires are satisfactory, and grounding them
produces an annunciation.

Examine the wiring from the timer conector
tothe PROP HEAT switch for power. Examine
the wiring from pin 8 (PCO1 3) through the PROP
HEAT switch to ground. Make sure there is a
grudonly on pin 8 (PCO1 3) when the switch is
in the TEST position.

Propeller Heat Troubleshooting for Airplanes with Garmin G1000
Figure 102 (Sheet 2)

30-60-00
©Cessna Aircraft Company

Page 108
Janl1/2007

CESSNA AIRCRAFT COMPANY

MODEL 1821T182

MAINTENANCE MANUAL

B4211

Amber PROP HEAT annunciation with PROP HEAT switch not in the TEST position.
Get access to the prop heal timer electrical connector (PC01 3) and make sure there is bus
voltage between 27 and 29 VIDC at pin 5 with the PROP HEAT switch in the ON position and
external power supplied. IfI

Examine thepoe
istribution system for
correct voltage and
operation.

Examine the wiring from the boots to the slip
ring for open wires or short circuits. Make
sure the resistance of all three boots wired in
parallel is 1.6 ohms, +0.2 or -0.2 ohms.
Stretch or bend the deicing boot leads a small
amount and look for intermittent open circuits
and measure the resistance. Push lightly on
the entire deicing boot heating element surface
near the leads. The resistance must not
change. This will help find an intermittent
open circuit that will not show up until
the propeller turns. If-

I

Make sure the connection between the
brushes and the slip ring is clean and smooth.
Make sure that the distance between the
brush holder and the face of the slip rings
is 0.064 inch, +0.01 5 or -0.01 5 inch, through
the full rotation of the slip ring. Make sure
the brushes are aligned with the slip rings so
that the entire face of each brush is in contact
with the slip ring through the full circumference
of the slip ring. Make sure there is good
electrical contact through the wiring from the
brushes to the timer. If-

I

Disconnect the deicing boot wie
from the terminal blocks and measure the
resistance of the individual boots. Stretchi or bend
the deicing boot leads a small amount and look for
intermittent open circuits and measure the
resistance. Push lightly on the entire deicing boot

Get access to the PROP HEAT timer
connector (PCO1 3) and look for a
jumper between pins 4 and 6. Measure
and make sure jumper has continuity. If-I

Align again or replace brushes.
Repair wiring from brushes to timer.

Propeller Heat Troubleshooting for Airplanes with Garmin G1000
Figure 102 (Sheet 3)

@Cessna Aircraft

Company

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CESSNA AIRCRAFT COMPANY

MODEL 182/Ti 82

MAINTENANCE MANUAL

B4212

A

Make sure there is no ground at pin 8
on the timer electrical connector
(PCO13). Does pin 8 have a ground?
IfI

Connect a jumper between pin 1
and pin 5 on the timer electrical
connector. (Make the jumper from
a 14 AWG wire and two S2353-6 pins.)
Put the PROP HEAT switch in the ON
position. Does the PROP HEAT

<

I

Examine the wiring from
/electrical connector o~in 8 (PCO1 3)1

circuit breaker disengage? If-

(through

the PROP HEAT switch to

around. Make sure there is a around
onyon pin 8 when the switch si
the TEST position.
1~~

1
z-1--

4
--- 1

Examine to find and
repair short circuit to
ground on the boot and
brush block wiring.

§che

After approximately 20 seconds
with the PROP HEAT switch set
to ON, make sure all three boots
are warm. If-

I
Repair the boot wiring or replac'
the unserviceable boots.

time

0

Propeller Heat Troubleshooting for Airplanes with Garmin G1000
Figure 102 (Sheet 4)

30-60-00
© Cessna

Aircraft Company

Page 11 0
Janl1/2007

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
PROPELLER HEAT - MAINTENANCE PRACTICES
1.

General
A.

2.

3.

4.

The following procedures contain the propeller de-ice timer removal/installation and the propeller heat
annunciator removal/installation.

Propeller Heat Timer/Monitor Removal/Installation
A.

Propeller Heat Timer Removal (Refer to Figure 201).
(1) Set the ALT/BAT MASTER switch to the off position.
(2) Disconnect the electrical plug (PC013) from the propeller heat timer/monitor.
(3) Remove the screws attaching the propeller heat timer/monitor to the Pedestal.

B.

Propeller Heat Timer Installation (Refer to Figure 201).
(1) Set the ALT/BAT MASTER switch to the off position.
(2) Install the propeller heat timer/monitor to the pedestal.
(3) Connect the electrical plug (PC013) to the propeller heat timer/monitor.
(4) Set the ALT/BAT MASTER switch to the ON position.

Propeller Heat Annunciator Removal/Installation
A.

Propeller Heat Annunciator Removal (Refer to Figure 202).
(1) Set the ALT/BAT MASTER switch to the off position.
(2) Remove the screws attaching the annunciator panel to the glareshield.
(3) Carefully pull the annunciator panel forward.
(4) Disconnect the electrical plug from the propeller heat annunciator.
(5) Remove the screws from the attach clip to propeller heat annunciator.
(6) Remove the clip from the heat annunciator.
(7) Pull the propeller heat annunciator from the annunciator panel.

B.

Propeller Heat Annunciator Installation
(1) Press the ALT/BAT MASTER switch to the off position.
(2) Slide the propeller heat annunciator into annunciator panel.
(3) Install mounting clip to the propeller heat annunciator using screws.
(4) Connect electrical plug to the propeller heat annunciator.
(5) Install the annunciator panel to glareshield using screws.
(6) Press the ALT/BAT MASTER switch to the ON position.

Deice Boots Removal/Installation
A.

Refer to the List of Manufacturers Technical Publications, McCauley Electrothermal De-Ice Systems,
Service, Parts and Installation Manual.

30-60-00
© Cessna Aircraft Company

Page 201
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

rag

LE

X
4

-OR TRIM WHEEL
PROPELLER HE
TIMER/MONITO

(UC001)
SCREWS

ELECTRICAL
CONNECTOF
(PC013)

PEDESTAL

DETAIL

A
0710T1001
A0718T1039

Propeller Heat Timer/Monitor
Figure 201 (Sheet 1)

30-60-00
© Cessna Aircraft Company

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April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B

.

.

GLARESHIELD

SCREW

SCREW
PROPELLER HEAT
ANNUNCIATOR

SCREW

DETAIL

A

AIRPLANES 18280945 AND ON AND
AIRPLANES T18208001 AND ON

0710T1001
A0718T1040

Propeller Heat Annunciator
Figure 202 (Sheet 1)

30-60-00
© Cessna Aircraft Company

Page 203
April 1/2002

CHAPTER

INDICATING/
RECORDING
SYSTEMS

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

LIST OF EFFECTIVE PAGES
CHAPTER-SECTION-SUBJECT

PAGE

DATE

31-00-00

Page 1

April 1/2002

31-10-00

Pages 201-203

Mar 1/2004

31-10-10

Pages 201-203

Jan 2/2006

31-20-00

Pages 201-202

April 1/2002

31-30-00

Pages 201-202

April 1/2002

31-50-00

Pages 201-203

Jan 2/2006

31-Title
31-List of Effective Pages
31-Record of Temporary Revisions
31-Table of Contents

31 - LIST OF EFFECTIVE PAGES
© Cessna Aircraft Company

Page 1of 1
Jan 2/2006

RECORD OF TEMPORARY REVISIONS
Temporary Revision
Number

Page Number

Issue Date

By

Date Removed

By

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

CONTENTS
INDICATING/RECORDING SYSTEMS - GENERAL .................................
Scope......................................................................
Definition ...................................................................

31-00-00 Page 1
31-00-00 Page 1
31-00-00 Page 1

INSTRUMENT AND CONTROL PANELS - MAINTENANCE PRACTICES.............
General ....................................................................
Pilot's Center Panel Removal/Installation ..........
.......................
Pilot's Inboard/Outboard Panel Removal/Installation............................
Copilot's Panel Removal/Installation ..........................................

31-10-00
31-10-00
31-10-00
31-10-00
31-10-00

Page
Page
Page
Page
Page

201
201
201
201
201

INSTRUMENT AND CONTROL PANELS - MAINTENANCE PRACTICES Airplanes with
Garmin G1000.............................................
......................
G eneral ....................................................................
Center Panel Removal/Installation ............................................
Switch Panel Removal/Installation ............................................
Throttle/Flap Panel............................
...........
...................
Instrument Panel Removal/Installation ......................................

31-10-10
31-10-10
31-10-10
31-10-10
31-10-10
31-10-10

Page
Page
Page
Page
Page
Page

201
201
201
201
201
201

DIGITAL CLOCK - MAINTENANCE PRACTICES ...................................
Description and Operation ...................................................
Digital Clock Removal/Installation ............................................

31-20-00 Page 201
31-20-00 Page 201
31-20-00 Page 201

HOUR METER - MAINTENANCE PRACTICES.....................................
Description and Operation ...................................................
Hour Meter Removal/Installation ..........
..............................

31-30-00 Page 201
31-30-00 Page 201
31-30-00 Page 201

ANNUNCIATOR PANEL - MAINTENANCE PRACTICES ............................

31-50-00 Page 201
31-50-00 Page 201
31-50-00 Page 202

Description and Operation .............................
......................
Annunciator Panel Removal/Installation .......................................

31 - CONTENTS
© Cessna Aircraft Company

Page 1of 1
Jan 2/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INDICATING/RECORDING
1.

Scope
A.

2.

SYSTEMS - GENERAL

This chapter contains information on those systems and components used to indicate and/or record
various parameters of the engine, airframe or related flight operations. Also included in this chapter
is information on the instrument panels that house the indicating/recording systems.

Definition
A.

This chapter is divided into sections to aid maintenance personnel in locating information. Consulting
the Table of Contents will assist in locating a particular subject. A brief definition of the sections
incorporated in this chapter is as follows:
(1) The section on instrument and control panels provides general removal and installation
instructions for the various panels used in the cockpit.
(2) The section on indicating provides information on the digital clock.
(3) The section on recording provides information on the hour meter.
(4) The section on annunciation provides information on the multi-system panel annunciator.

31-00-00
© Cessna Aircraft Company

Page 1

April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
INSTRUMENT AND CONTROL PANELS - MAINTENANCE PRACTICES
1.

General
A.

2.

3.

4.

This section gives the removal and installation of different panels of the instrument panel

Pilot's Center Panel Removal/Installation
A.

Remove the Pilot's Center Panel (Refer to Figure 201).
(1) Disconnect the negative cable from airplane battery. Refer to Chapter 24, Battery - Maintenance
Practices.
(2) Remove the screws that attach the control column collar.
(3) Remove the screws that attach the center panel to the pilot's outboard and inboard panels.
(4) Put labels on all applicable electrical connections.
(5) Disconnect the electrical connections from the applicable instruments.
(6) Disconnect all of the pneumatic lines from the instruments.
(7) Install caps and plugs on all open pneumatic lines to prevent foreign object debris.
(8) Put caps and plugs on all open instrument ports to prevent foreign object debris.
(9) Remove pilot's center panel assembly.

B.

Install the Pilot's Center Panel (Refer to Figure 201).
(1) Remove the caps and plugs from the pneumatic lines and the instrument ports.
(2) Connect the applicable pneumatic lines to the instruments.
(3) Connect all electrical connections.
(4) Remove the labels from the electrical connections.
(5) Install the center panel with screws.
(6) Install the screws that attach the control column collar.
(7) Connect the negative battery cable. Refer to Chapter 24, Battery - Maintenance Practices.

Pilot's Inboard/Outboard Panel Removal/Installation
A.

Remove the Pilot's Inboard/Outboard Panel (Refer to Figure 201).
(1) Disconnect the negative cable from the airplane battery. Refer to Chapter 24, Battery Maintenance Practices.
(2) Remove the screws that attach the control column collar.
(3) Remove the screws that attach the inboard/outboard panel to the pilot's inboard and outboard
panels.
(4) Put labels on all applicable electrical connections.
(5) Disconnect the applicable electrical connections.
(6) Remove the panel assembly.

B.

Install the Pilot's Inboard/Outboard Panel (Refer to Figure 201 ).
(1) Connect all electrical connections.
(2) Remove the labels from the electrical connections.
(3) Install the inboard/outboard panel with screws.
(4) Install the screws that attach the control column collar.
(5) Connect the negative battery cable. Refer to Chapter 24, Battery - Maintenance Practices.

Copilot's Panel Removal/Installation
A.

B.

Remove the Copilot's Panel (Refer to Figure 201).
(1) Disconnect the negative cable from the airplane battery.
Maintenance Practices.
(2) Remove the screws that attach the control column collar.
(3) Remove the screws that attach the panel.
(4) Put labels on all applicable electrical connections.
(5) Disconnect the electrical connections.
(6) Remove the panel assembly.

Refer to Chapter 24, Battery -

Install the Copilot's Panel (Refer to Figure 201).
(1) Connect all electrical connections.

31-10-00
© Cessna Aircraft Company

Page 201
Mar 1/2004

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

I0

neon

DII
IIL/

PILOT'S INBOARD PANEL

-T'C rl ITDR-fADrn DAhAII
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J3-LIl IJ'MJtLJ rFt1dL/L

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999

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-

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RADIO PANEL

CIRCUIT BREAKER PANEL

ENGINE
CONTROLS

DETAIL

HEAT AND
VENTILATION
rCONTRLI
._v S
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vv, ....

A

AIRPLANES WITH STANDARD AVIONICS

0710T1001
A0718T1001

Instrument Panels
Figure 201 (Sheet 1)

31-10-00
© Cessna Aircraft Company

Page 202
Mar 1/2004

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

I

(2)
(3)
(4)
(5)

Remove the labels from the electrical connections.
Install the copilot's panel with screws.
Install the screws that attach the control column collar.
Connect the negative battery cable. Refer to Chapter 24, Battery - Maintenance Practices.

31-10-00
© Cessna Aircraft Company

Page 203
Mar 1/2004

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
INSTRUMENT AND CONTROL PANELS - MAINTENANCE PRACTICES
Airplanes with Garmin G1000
1.

General
A.

2.

3.

Center Panel Removal/Installation
A.

Remove the Center Panel (Refer to Figure 201).
(1) Make sure the MASTER ALT/BAT and AVIONICS switches are in the off position.
(2) Disengage the STDBY IND-LTS circuit breaker.
(3) Remove the screws that attach the center panel to the instrument panel.
(4) Carefully pull out the center panel as necessary to get access behind the panel.
(5) Install tags for identification on the electrical connectors and hoses and disconnect them from
the instruments.

B.

Install the Center Panel (Refer to Figure 201).
(1) Connect the electrical connectors and hoses to the applicable instruments.
(2) Remove the tags from the electrical connectors and hoses.
(3) Carefully put the center panel in the instrument panel.
(4) Install the screws that attach the center panel.
(5) Engage the STDBY IND LTS circuit breaker.

Switch Panel Removal/Installation
A.

B.

4.

5.

This section covers the removal and installation for the center panel, switch panel, throttle/flap panel,
and instrument panel.

Remove the Switch Panel (Refer to Figure 201).
(1) Make sure the MASTER ALT/BAT and AVIONICS switches are in the off position.
(2) Remove the screws that attach the switch panel to the instrument panel.
(3) Carefully pull the switch panel out from the instrument panel to get access behind the panel.
(4) Disconnect the switches from the electrical connections.
Install the Switch Panel (Refer to Figure 201).
(1) Connect the electrical connections to the switches.
(2) Put the switch panel in the instrument panel.
(3) Attach the switch panel with the screws.

Throttle/Flap Panel
A.

Throttle/Flap Panel Removal (Refer to Figure 201).
(1) Disconnect the negative cable from airplane battery. Refer to Chapter 24, Battery - Maintenance
Practices.
(2) Make sure the MASTER ALT/BAT and AVIONICS switches are in the off position.
(3) Remove the screws that attach the throttle/flap panel to the instrument panel.
(4) Carefully pull the throttle/flap panel out from the instrument panel to get access behind the panel.
(5) Disconnect the switches from the electrical connections.

B.

Throttle/Flap Panel Installation (Refer to Figure 201).
(1) Connect the electrical connections to the switches.
(2) Put the throttle/flap panel in the instrument panel.
(3) Attach the throttle/flap panel with the screws.
(4) Connect the negative battery cable. Refer to Chapter 24, Battery - Maintenance Practices.

Instrument Panel Removal/Installation
A.

Remove the Instrument Panel (Refer to Figure 201).
(1) Disconnect electrical power to the airplane.
(a) Make sure the AVIONICS switch is in the off position.
(b) Disengage the two PFD circuit breakers, the MFD, STDBY BATT, STDBY IND-LTS AUDIO
circuit breakers.

31-10-10
© Cessna Aircraft Company

Page 201
Jan 2/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

E

A

SWITCH
PANEL

INSTRUMENT
PANEL

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PANEL

THROTTLE/FLAP
PANEL

DETAIL A
AIRPLANES WITH GARMIN G1000

071 T1 001
A12181044A

Instrument and Control Panel Installation
Figure 201 (Sheet 1)

31-10-10
0 Cessna Aircraft Company

Page 202
Jan 2/2006

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

|* ~

(2)
(3)
(4)
(5)
(6)
(7)

Remove the center panel. Refer to Center Panel - Removal/Installation.
Remove the switch panel. Refer to Switch Panel - Removal/Installation.
Remove the throttle/flap panel. Refer to Throttle/Flap Panel - Removal/Installation.
Remove the Audio Panel. Refer to Audio Panel - Maintenance Practices.
Remove the screws that attach the control column collars to the instrument panel.
Remove the hourmeter to the instrument panel.
(a) Remove the screws for the hourmeter.
(b) Pull the hourmeter out and disconnect the connector.
(8) Remove the Control Display Units (CDU).
(a) Disengage the quick release fasteners.
(b) Carefully pull the CDU away from the instrument panel and disconnect the electrical
connector.
(9) Remove the screws from the instrument panel.
NOTE:

The ELT switch can only be removed from the back of the instrument panel.

(10) Disconnect and remove the ELT switch from the instrument panel.
(11) Remove the instrument panel.
B.

Install the Instrument Panel (Refer to Figure 201).
(1) Set the instrument panel in position.
(2) Install the ELT switch and connect the electrical connector.
(3) Install the instrument panel screws.
(a) Make sure to put the electrical connector for the hourmeter through the panel hole for the
hourmeter installation.
(4) Connect the electrical connector to the hourmeter.
(5) Install the hourmeter.
(6) Attach the collar for the control column to the instrument panel.
(7) Set the throttle/flap panel in position and connect the electrical connections to the switches.
(8) Install the throttle/flap panel to the instrument panel with the screws.
(9) Set the switch panel in position and connect the electrical connections to the switches.
(10) Install the switch panel to the instrument panel with the screws.
(11) Set the center panel in position and connect the electrical connectors and vacuum hoses to the
instruments.
(12) Install the center panel to the instrument panel with the screws.
(13) Set the Control Unit Displays (CDU's) in position and connect the electrical connector.
(14) Install the CDU's with the quick release fasteners to the instrument panel.
(15) Engage the two PFD circuit breakers, the MFD, STDBY BATT, STDBY IND-LTS AUDIO circuit
breakers.

31-10-10
© Cessna Aircraft Company

Page 203
Jan 2/2006

CESSNA AIRCRAFT COMPANY

MODEL 1821T182
MAINTENANCE MANUAL
DIGITAL CLOCK - MAINTENANCE PRACTICES
1.

Description and Operation
A.

2.

The digital clock is located in the upper left side of the instrument panel. The unit also gives an
indication of the temperature and voltage.

Digital Clock Removal/Installation
A.

Remove the Digital Clock (Refer to Figure 201).
(1) Press the ALT/BAT MASTER switch to the off position.
(2) Remove the screws that attach the digital clock to the instrument panel.
(3) Carefully pull the digital clock out from the instrument panel and disconnect the electrical
connector.

B.

Install Digital Clock (Refer to Figure 201).
(1) Connect the electrical connector to the digital clock.
(2) Set in position the digital clock in the instrument panel and attach with the screws.
(3) Press the ALT/BAT MASTER switch to the ON position.

31-20-00
© Cessna Aircraft Company

Page 201
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

Con.

E

HEX
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A

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INSTRUMENT
PANEL

DETAIL A
SCREW
U-11

0710T1001
A0714R1029

Digital Clock Installation
Figure 201 (Sheet 1)

31-20-00
©Cessna Aircraft Company

Page 202
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
HOUR METER - MAINTENANCE PRACTICES

1.

Description and Operation
A.
B.

2.

The hour (Hobbs) meter is located in the upper right corner of the instrument panel and provides
indication of flight hours based on engine operation.
The hour meter (E1003) receives power through the WARN circuit breaker (HI022) located on the
lower instrument panel. The hour meter is grounded through the Oil Pressure Switch (SN001), and
anytime oil pressure exceeds 20 PSI a ground is sent from the switch to the hour meter, completing
a circuit and activating the hour meter.

Hour Meter RemovaVlnstallation
A.

B.

Remove Hour Meter (Refer to Figure 201).
(1) Gain access to backside of instrument panel and hold nuts while loosening screws.
(2) Disconnect electrical connectors leading into hour meter.
Install Hour Meter (Refer to Figure 201).
(1) Connect electrical connectors to hour meter.
(2) Install hour meter to panel and secure using screws and nuts.

31-30-00
© Cessna Aircraft Company

Page 201
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B720

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HOUR
METER

PANEL

SCREW

DETAIL

A

0718T1002
A0518T1020

Hour Meter Installation
Figure 201 (Sheet 1)

31-30-00
© Cessna Aircraft Company

Page 202
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
ANNUNCIATOR PANEL - MAINTENANCE PRACTICES
1.

Description and Operation
A.

The annunciator panel is a multi-system display that gives visual warning and caution information
for some systems and fuel levels for the airplane. The annunciator shows this visual information in
amber (caution) or red (warning) messages. Refer to Table 201 for a breakdown of the messages
and sources.

B.

Table 201 gives a general description of the annunciator system and its inputs. Use this table with the
Wiring Diagram Manual to help with system troubleshooting.

Table 201. Annunciator Panel Messages and Inputs
MESSAGE

COLOR

MEANING

SOURCE OF SIGNAL

L LOW FUEL

Amber

Low fuel condition found
in the left tank.

Left fuel quantity system.

LOW FUEL R

Amber

Low fuel condition found
in the right tank.

Right fuel quantity
system.

L LOW FUEL R

Amber

Low fuel condition found
in the left and the right
fuel tanks.

Left and right fuel quantity
systems.

L LOW FUEL and left
fuel gauge needle stays
below 0

Amber

Short, open or increasing
resistance over time.

Left fuel transmitter or
electrical line between
transmitter and fuel
gauge.

LOW FUEL R and right
fuel gauge needle stays
below 0

Amber

Short, open or increasing
resistance over time.

Right fuel transmitter or
electrical line between
transmitter and fuel
gauge.

L LOW FUEL R and both
fuel gauge needles stay
below 0

Amber

Short, open or increasing
resistance over time.

Left and right transmitters
or electrical lines between
transmitters and fuel
gauge.

OIL PRESS

Red

Oil pressure less than 20
PSI.

Oil pressure switch
supplies ground to
annunciator.

L VAC

Amber

Vacuum less than 3.0 In.
Hg.

Left vacuum switch
supplies ground to
annunciator.

VAC R

Amber

Vacuum less than 3.0 In.
Hg.

Right vacuum switch
supplies ground to
annunciator.

L VAC R

Amber

Vacuum less than 3.0 In.
Hg.

Right vacuum switch and
left vacuum switch supply
ground to annunciator.

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MODEL 182/T182

MAINTENANCE MANUAL
Table 201. Annunciator Panel Messages and Inputs (continued)
MESSAGE

COLOR

MEANING

SOURCE OF SIGNAL

VOLTS

Red

Voltage less than 24.5
VDC, ±0.35 VDC.

Ground from the
alternator control unit
to the annunciator panel.

PITCH TRIM

Red

Autopilot pitch trim failure.

Autopilot flight computer.

TERR N/A

Amber

Ground proximity
warning.

KAC 502 EGPWS
module installed in the
KMD-540 multi-function
display.

2.

Annunciator Panel Removal/Installation
A.

Annunciator Panel Removal (Refer to Figure 201).
(1) Remove electrical power from the airplane.
(2) Get access to back side of annunciator panel and disconnect electrical connectors.
(3) Remove screws that attach annunciator panel to instrument panel.
(4) Carefully remove the annunciator panel from the airplane.

B.

Annunciator Panel Installation (Refer to Figure 201).
(1) Connect electrical connectors to annunciator panel.
(2) Put the annunciator panel in position on the instrument panel and attach it with the screws.
(3) Connect electrical power to the airplane.
(4) Do a check of the annunciator panel for correct operation.

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MODEL 182/T182
MAINTENANCE MANUAL
EA
E

B

\

DETAIL A

INSTRUMENT PANEL
ULAHRE

3EZEL

SWITCH

ANNUNCIATOR
UNIT

ETAIL B

BEZEL

BEZEL
SCREW

DETAIL D
NOTE 1: ANNUNCIATOR PANEL CONFIGURATION
CAN BE DIFFERENT THAN SHOWN.

BEZEL
SCREW

DETAIL C

071T1 001
A1218T1001
B1218T1068
C1218T1068
D1218T1068

Annunciator Panel Installation
Figure 201 (Sheet 1)

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CHAPTER

LANDING GEAR

CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

LIST OF EFFECTIVE PAGES
PAGE

DATE

32-00-00

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Aug 4/2003

32-10-00

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Aug 4/2003

CHAPTER-SECTION-SUBJECT
32-Title
32-List of Effective Pages
32-Record of Temporary Revisions
32-Table of Contents

32 - LIST OF EFFECTIVE PAGES
© Cessna Aircraft Company

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RECORD OF TEMPORARY REVISIONS
Temporary Revision
Number

Page Number

Issue Date

By

Date Removed

By

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

CONTENTS
LANDING GEAR - GENERAL

..................................................

S cope......................................................................
D efinition ...................................................................
Tools, Equipment and Materials ............................................
MAIN LANDING GEAR - TROUBLESHOOTING ....................................

Troubleshooting ............................................................
MAIN LANDING GEAR - MAINTENANCE PRACTICES .............................
General ....................................................................
Main Landing Gear Fairings Removal/Installation ..............................
Main Landing Gear Removal/Installation ......................................
Step Support Removal/Installation .........................................
Main Wheel Alignment Check ....................
............................
NOSE LANDING GEAR - TROUBLESHOOTING ...................................

General ....................................................................
NOSE LANDING GEAR - MAINTENANCE PRACTICES.............................
General ....................................................................
Nosewheel Speed Fairing Removal/Installation ................................
Nose Landing Gear Removal/nstallation ......................................
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 ..........
General...................................................................
Main Wheel Removal/Installation .............................................
Main Wheel Axle Removal/Installation ....................
....................
Main Wheel Disassembly/Assembly ..........................................

Main Wheel Inspection/Check ....................
.........................
Wheel Balancing ............ ........... ...................................
NOSE LANDING GEAR WHEEL - MAINTENANCE PRACTICES.....................
General ....................................................................
Nose Landing Gear Wheel Removal/Installation ...............................
Nose Landing Gear Wheel Disassembly/Assembly ...........................
Nose Landing Gear Wheel Inspection/Check ..................................
BRAKE SYSTEM - TROUBLESHOOTING .........................................

Troubleshooting ............................................................
BRAKE SYSTEM - MAINTENANCE PRACTICES...................................
General ....................................................................
Brake Master Cylinders Removal/Installation ..................................
Brake Master Cylinder Disassembly/Assembly ................................
Brake Master Cylinders Inspection/Repair ...................................
Brake Lining Wear Check....................................................
Brake Lining Replacement ..................................................
Brake System Bleeding ......................................................
Brake Lining Conditioning...................................................
Parking Brake System.......................................................

© Cessna Aircraft Company

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL
LANDING GEAR - GENERAL
1.

Scope
A.

2.

Definition
A.

3.

This chapter contains maintenance information concerning the landing gear and associated
components which provide means of supporting, braking, and steering the airplane.

This chapter is divided into sections to aid maintenance personnel in locating information. Consulting
the Table of Contents will assist in locating a particular subject. A brief definition of the sections
incorporated in this chapter is as follows:
(1) The section on main landing gear provides troubleshooting, maintenance practices and
adjustment instructions for the main landing gear.
(2) The section on nose landing gear provides troubleshooting, maintenance practices and
inspection/checks for the nose landing gear.
(3) The section on wheels and brakes provides troubleshooting, maintenance practices and
adjustment/test instructions for the main gear brake system.
(4) The section on main landing gear wheel and axle provides maintenance practices and
inspection/checks.
(5) The section on nose landing gear wheel provides maintenance practices and inspection/checks.
(6) The section on the brake system provides troubleshooting, maintenance practices and
inspection/checks.

Tools, Equipment and Materials
NOTE:

Equivalent substitutes may be used for the following items:

NAME

NUMBER

MANUFACTURER

USE

Adhesive

EA9309.3NA

Hysol Div. Dexter Corp.
15051 E. Don Julian Rd.
Industry, CA

To bond main landing gear
step bracket.

P840306

Commercially Available

To cover main gear strut
at upper end where strut
fairing could cause chafing.

Lubricant

Universal
Dynaplex 21C
Regular

Commercially Available

To apply to upper unpainted
end of main gear strut
before installation.

Rivet Setting Kit

199-1

Cessna Aircraft Company
Cessna Parts Distribution
Department 701, CPD2
5800 East Pawnee Road
Wichita, Kansas 67218-5590

To rivet brake linings to
back plate.

I Tape

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Page 1
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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
MAIN LANDING GEAR - TROUBLESHOOTING
1.

Troubleshooting
A.

A troubleshooting chart has been developed to aid the maintenance technicians in system
understanding. Refer to Figure 101.

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Page 101
April 1/2002

CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1268

AIRPLANE LEANS TO ONE SIDE.

I

I
CHECK FOR INCORRECT
TIRE PRESSURE. IF-

OK, CHECK FOR LANDING
GEAR ATTACHING PARTS
NOTTIGHT. IF-

NOT OK, INFLATE TO
CORRECT PRESSURE.

OK, CHECK FOR LANDING
GEAR TUBULAR STRUT
EXCESSIVELY SPRUNG. IF -

NOT OK, TIGHTEN LOOSE
PARTS OR REPLACE DEFECTIVE
PARTS WITH NEW PARTS.

OK, CHECK FOR BENT AXLE.
REPLACE AXLE.

NOT OK, REPLACE TUBULAR
STRUT.

Main Landing Gear Troubleshooting Chart
Figure 101 (Sheet 1)

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Page 102
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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

B1269

I

I

TIRE WEARS EXCESSIVELY.

CHECK FOR INCORRECT
TIRE PRESSURE. IF -

I

I

OK, CHECK FOR MAIN WHEELS
OUT OF ALIGNMENT. IF -

NOT OK, INFLATE TO
CORRECT PRESSURE.

OK, CHECK FOR LANDING
GEAR TUBULAR STRUT
EXCESSIVELY SPRUNG. IF -

NOT OK, CHECK MAIN WHEEL
ALIGNMENT. CORRECT
ALIGNMENT.

OK, CHECK FOR BENTAXLE. IF -

I

NOT OK, REPLACE TUBULAR
STRUT.

OK, CHECK FOR DRAGGING
BRAKES. IF-

I

NOT OK, REPLACE AXLE.
I

I

I

OK, CHECK FOR WHEEL
BEARING EXCESSIVELY
TIGHT. PROPERLY INSTALL
BEARINGS.

NOT OK, ADJUST BRAKES.

I

TIRE BOUNCE EVIDENT ON
SMOOTH SURFACE.
I
TIRE OUT OF BALANCE
BALANCE TIRE.

Main Landing Gear Troubleshooting Chart
Figure 101 (Sheet 2)

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Page 103
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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL
MAIN LANDING GEAR - MAINTENANCE PRACTICES
1.

2.

General
A.

The main landing gear maintenance practices give removal/installation instructions for the left main
landing gear. Removal/installation for the right main landing gear is typical unless noted.

B.

The tubular, spring-steel main landing gear struts are attached to the aircraft at inboard and outboard
forgings in the belly of the aircraft. A bracket is bonded to each strut for attachment of a step. Hydraulic
brake lines go down the main gear struts. The axles, main wheels, and brake assemblies are installed
at the lower end of each strut.

C.

The aircraft has fuselage fairings, attached to the fuselage and the tubular strut fairings with screws.
The tubular strut fairings cover the tubular landing gear struts, and attach to the fuselage fairings at
the upper end and to cover plates at the lower end. The cover plates attach to the tubular strut fairings
at the upper end and are clamped to the tubular struts at the lower end. Brake fairings are installed
at the lower end of the tubular strut fairings and are attached to the wheel speed fairings by screws
around their outer perimeters. The speed fairings are installed over the wheels and are attached to
mounting plates attached to the axles. The wheel fairings have adjustable scrapers installed in the
lower aft part of the fairings directly behind the wheels.

Main Landing Gear Fairings Removal/Installation
A.

Brake Fairing Removal (Refer to Figure 201).
(1) Remove the screws from the lower side of the brake fairing.
(2) Remove the brake fairing from the landing gear.

B.

Brake Fairing Installation (Refer to Figure 201).
(1) Put the brake fairing over the landing gear.
(2) Install the screws to the lower side of the brake fairing.

C.

Main
(1)
(2)
(3)
(4)

D.

Main
(1)
(2)
(3)

Wheel Speed Fairing Removal (Refer to Figure 201).
Remove and keep the screws that attach the brake fairing to the main wheel speed fairing.
Remove the screws that attach the main wheel speed fairing to the mounting plate.
Remove the bolt that attaches the outboard side of the main wheel speed fairing to the axle nut.
Loosen the scraper, if necessary, and remove the main wheel speed fairing from the wheel.

Wheel Speed Fairing Installation (Refer to Figure 201).
Put the speed fairing over the wheel. Adjust the scraper if necessary.
Install the bolt that attaches the outboard side of the main wheel speed fairing to the axle nut.
Install the screws that attach the main wheel speed fairing to the attach plate, which is bolted to
the axle.
(4) Install the screws that attach the brake fairing to the main-wheel speed fairing.

CAUTION: You must keep the scraper clean for the tire to turn correctly. Make
sure you complete a check of the clearance every time the scraper
has been disturbed, the tire changed, and when you install the
speed fairings. You can cause damage to the equipment if the
correct clearance is not set between the tire and the scraper. If
any mud, snow or ice collects on the scraper, it will prevent the tire
from correct movement.
(5) Do a check of the clearance between the tire and the scraper.
(a) Clean off any dirt or ice that has collected on the scraper.
(b) Adjust the clearance as necessary to have a minimum of 0.55 inch (14 mm) to a maximum
of 0.80 inch (20 mm).
(6) Remove any fuel and oil from the speed fairings to prevent stains and deterioration.

32-10-00
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CESSNA AIRCRAFT COMPANY

MODEL 182/T182

MAINTENANCE MANUAL

B1270

SNAP
RING
A TTACHING
P IN

A

STEP
PLUG
BUTTON

BRAKE
LINE
STEP
SUPPORT

FITTING
SHIMAXLE

AXLE

TORQUE
PLATE

NOTE: HUBCAP NOT
USED WITH
WHEEL FAIRINGS.

HUBCAP

DETAIL

A

Main Landing Gear Installation
Figure 201 (Sheet 1)

32-10-00
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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B1271

MOUNTING
PLATE

SPEED
FAIRING

DETAIL D

PER

AXLE
NUT

DETAIL C

C0741T1005
D0741T1007

Main Landing Gear Installation
Figure 201 (Sheet 2)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

DETAIL

A

(182T AND T182T)
0710T1001
A0741T1016

Main Landing Gear Installation
Figure 201 (Sheet 3)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

CAUTION: Make sure the tire pressure is correct. Incorrect tire pressure can
cause damage to the fairing.
(7) Do a check of the tire pressure and adjust the pressure as necessary. Refer to Chapter 12, Tires
- Servicing.
E.

F.

G.

H.

I.

J.

3.

Cover Plate Removal (Refer to Figure 201).
(1) Remove the screws and clamp that attach the cover plate to the tubular strut fairing.
(2) Remove the cap fairing.
Cover Plate Installation (Refer to Figure 201).
(1) Put the cover plate and the clamp over the tubular strut. Attach them with the screws.
(2) Install the cap fairing.
Main Gear Strut Fairing Removal (Refer to Figure 201).
(1) Remove the screws that attach the step-to-the step support.
(2) Remove the screws from the lower side of the strut fairing.
(3) Remove the cover plate.
(4) Carefully separate the main gear strut fairing along the aft edge and remove it over the step
support.
(5) Pull the strut fairing out of the fuselage fairing and remove it from the tubular strut.
Main Gear Strut Fairing Installation (Refer to Figure 201).
(1) Put the main gear strut fairing over the strut and put the fairing in position over the step support
and into the fuselage fairing. Attach it with screws.
(2) Install the step-on-the step support.
(3) Install the cover plate.
Fuselage Fairing Removal (Refer to Figure 201).
(1) Remove the main landing gear wheel. Refer to Main Landing Gear Wheel and Axle Maintenance Practices.
(2) Remove the mounting plate for the main-wheel speed fairing.
(3) Remove the brake torque plate.
(4) Remove the screws that attach the fuselage fairing to the fuselage.
(5) Slide the fuselage fairing down the tubular strut and over the main landing gear axle.
Fuselage Fairing Installation (Refer to Figure 201).
(1) Move the fuselage fairing over the main landing gear axle and slide it up to the fuselage. Attach
it with the screws.
(2) Install the brake torque plate.
(3) Install the mounting plate for the main-wheel speed fairing.
(4) Install the main landing gear wheel. Refer to Main Landing Gear Wheel and Axle - Maintenance
Practices.

Main Landing Gear Removal/Installation
A.

Main Landing Gear Removal (Refer to Figure 201).
NOTE:
(1)
(2)
(3)
(4)
(5)
(6)
(7)

This procedure removes the landing gear as a complete assembly.

Remove the pilot's and the copilot's seats. Refer to Chapter 25, Front Seats - Maintenance
Practices.
Remove the access plate 230NB or 230QB. Refer to Chapter 6, Access/Inspection Plates Description and Operation.
Jack the airplane. Refer to Chapter 7, Jacking - Maintenance Practices.
Remove the screws that attach the fuselage fairing to the fuselage. Remove the screws at the
splice in the fuselage fairing and remove from the strut fairing.
Remove the brake bleeder screw and drain the hydraulic fluid from the brake line on the strut.
Disconnect the hydraulic brake line at the fitting where the brake line emerges from the fuselage
skin. Cap or plug the disconnected fittings.
Remove the snap ring from strut attaching pin.
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MODEL 182/T182
MAINTENANCE MANUAL
(8) Remove the plug button from the belly of the airplane below the gear forging.
(9) With a punch, push the attaching pin upward out of the inboard forging.

WARNING: Use caution when the forging and pin are removed.
(10) Pull the tubular strut from the forgings. Use care when you remove the strut to prevent damage
to the hydraulic brake line.
NOTE:
B.

4.

To replace the bushing from the outboard forging, remove the retaining ring at the
inboard end and slide the bushing outboard from the forging.

Main Landing Gear Installation (Refer to Figure 201).
(1) Install all parts removed from the strut.
(2) Clean the inboard end of the strut. Refer to Chapter 20, General Solvents/Cleaners Maintenance Practices.
(3) Apply A840014 aluminum foil tape to the inboard end of each strut to seal the strut end.
(4) Apply U000992 grease to the unpainted area on the upper end of the strut. For the grease
supplier, refer to Chapter 12, Lubricants.
(5) Slide the strut through the bushing into the inboard forging and align the attaching pin holes.
(6) Install the attaching pin and the snap ring.
(7) Install the access plate 230NB or 230QB and the plug button. Refer to Chapter 6, Access/
Inspection Plates - Description and Operation.
(8) Remove the caps and connect the hydraulic brake line to the fitting. Fill and bleed the brake
system. Refer to Brake System - Maintenance Practices.
(9) Install the fuselage fairing.
(10) Remove the airplane from the jacks.
(11) Install the pilot's and copilot's seats. Refer to Chapter 25, Front Seats - Maintenance Practices.
(12) Do a check of the wheel alignment. Refer to Main Wheel Alignment.

Step Support Removal/Installation
A.

Step Support Removal (Refer to Figure 202).
(1) Remove the main landing gear fairings. Refer to Main Landing Gear Fairings Removal/
Installation.
(2) Remove the step support.
(a) With long-handled pliers or a similar tool, apply upward force to the step support.

CAUTION: Do not continue to heat the tubular strut to the point where the
paint or the epoxy blisters.
(b) Apply heat to the epoxy with a heat gun, until the epoxy softens and an upward force of
pliers breaks the step support away from the landing gear strut. Quickly remove heat.
B.

Step Support Installation (Refer to Figure 202).
NOTE:

The step support is attached to the tubular gear strut with EA9309.3NA, EC2216, EC2214,
EC3445 or an equivalent epoxy base adhesive.

(1) Mark the position of the step support to make sure that the new step support will be installed in
the same position on the strut.
(2) Remove all traces of the original step support adhesive, as well as rust, paint, or scale, with a
wire brush and coarse sandpaper.
(3) Leave surfaces slightly roughened or abraded, but remove deep scratches or nicks.
(4) Thoroughly clean the surfaces to be bonded together. If a solvent is used, remove all traces of
the solvent with a clean, dry cloth. It is important that the bonding surfaces be clean and dry.
(5) Check the fit of the step support on the tubular strut. A small gap is permitted between the
support and the tubular strut.
(6) Mix the adhesive in accordance with the manufacturer's directions.

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

AIRPLANES 18280945 THRU 18281297 AND
AIRPLANES T18208001 THRU T18208224
0710T1001
0720R1008

RIGHT SIDE SHOWN, LEFT SIDE OPPOSITE
Step Installation
Figure 202 (Sheet 1)

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CESSNA AIRCRAFT COMPANY

MODEL 182/T182
MAINTENANCE MANUAL

B2052

STEP TREAD

EP

DETAIL

A

AIRPLANES 18281298 AND ON AND
AIRPLANES T18208225 AND ON
RIGHT SIDE SHOWN, LEFT SIDE OPPOSITE

0714T1045

Step Installation
Figure 202 (Sheet 2)

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MODEL 182/T182
MAINTENANCE MANUAL
(7) Spread a coat of adhesive on both bonding surfaces, and put the step support in position on the
tubular strut. Clamp the step support to the strut to make sure that there is a good, tight fit.
(8) Make a small fillet of the adhesive at all edges of the bonded surfaces. Remove excess adhesive
with lacquer thinner. Do not dilute the adhesive in the step/gear interface.
(9) Allow adhesive to cure thoroughly in accordance with the manufacturer's recommendations
before the tubular gear strut is flexed or loads are applied to the strut.
(10) Paint the tubular strut and the step support after the adhesive is fully cured.
(11) Install the main landing gear fairings. Refer to Main Landing Gear Fairings Removal/Installation.
5.

Main Wheel Alignment Check

A.

Use tapered shims between the flange of the axle and the main axle fitting to align the main wheels.
Refer to Table 201, Table 202, and Figure 203.

Table 201. Camber Adjustment
SHIM PART
NUMBER

POSITION OF
THICKEST CORNER
OR EDGE OF SHIM

TOE-IN

0541157-1

Aft

0.063 Inch

TOE-OUT

Forward
0541157-2

---

Up

0.008 Inch

Up and Forward
Up and Aft

--0.028 Inch

Down and Forward
Down and Aft
0441139-5

--0.006 Inch

Up and Forward
0.117 Inch

Up and Aft
Down and Forward
Down and Aft
0441139-6

0.125 Inch

Up and Forward
Up and Aft

--0.235 Inch

Down and Forward
0541157-3

NEGATIVE
CAMBER

004'
0.063 Inch

Down
1241061-1

POSITIVE
CAMBER

---

0.008 Inch

0o4'
0°28'

---

0°28'

0.006 Inch

2°44'

---

2°46'

0.028 Inch

2°46'

---

2044'

0.125 Inch

0°10'

-

0°25'

0.117 Inch

0°25'

---

0010'

0.253 Inch

0°21'

---

0°51'

0.235 Inch

0°51'

Down and Aft

0.253 Inch

---

0°21'

Aft

0.12 Inch

---

007'

Forward

0.12 Inch

007'

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MAINTENANCE MANUAL

Table 202. Shim Chart
SHIM PART
NUMBER

CORRESPONDING AND TOTAL ALLOWABLE SHIM

1241061-1

0441139-6

0441139-5

0541157-2

0541157-1

0541157-3

1241061-1

0

0

0

0

0

0

0441139-6

0

0

0

1

1

0

0441139-5

0

0

1

1

2

0

0541157-2

0

1

1

2

2

0

0541157-1

0

1

1

2

2

0

0541157-3

0

0

1

2

1

0

NOTE:

The best alignment setting is zero toe-in and zero camber at normal operating weight.
Standard empty weight is 1910 pounds. Maximum useful load is 1200 pounds. Maximum
gross weight is 3110 pounds.

(1) Make sure that the floor is level where you do the work on the airplane.
(2) Ballast the aircraft to the normal operating weight. Put the ballast as close to the aft door frame
fuselage station as possible.
(3) Use tapered shims between the flange of the axle and main axle fitting to do the main wheel
alignment. Always use the minimum number of shims possible to get the necessary result.
Follow the illustration for the alignment procedure.
NOTE:

If you remove or loosen a self-locking nut beyond the locking area of the nut, you can
use it again unless the nut can be run up finger tight. When fiber-type self locking
nuts are used again, check the fiber carefully to make sure that it has not lost locking
function or become brittle.

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MODEL 182/T182
MAINTENANCE MANUAL

B1273

PUT AIRPLANE MAIN WHEELS ON GREASE
PLATES AND ROCK WINGS BEFORE THE
WHEEL ALI
BLOCK STRAIGHTEDGE
AGAINST TIRES JUST
BELOW AXLE HEIGHT

ALUMINUM PLATES
APPROXIMATELY
18 INCHES SQUARE
(4 REQUIRED)
BLOCK STRAIGHTEDGE
AGAINST TIRES JUST
BELOW AXLE HEIGHT
MEASURE TOE-IN AT EDGES OF
WHEEL FLANGE. DIFFERENCE
IN MEASUREMENTS IS TOE-IN
FOR ONE WHEEL
(HALF OF TOTAL TOE-IN

GREASE BETWEEN
PLATES
(AS REQUIRED)
POSITIVE
CAMBER

NEGATIVE
CAMBER

PROTRACTOR

FWD

CARPENTER'S
SQUARE
LOOKING DOWN
TOW-IN CHECK
(SHOWN WITH TOE-IN)

UP
FRONT VIEW OF
CAMBER CHECK

SB9832T03

Main Wheel Alignment Check
Figure 203 (Sheet 1)

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MAINTENANCE MANUAL

B1274

0.195

0.084

05411 11-2

0441139-6

0441139-5

.040
0.040

0.040
0.057

0.040

0.065

0.040
0.063

0.028

0.065

0

0
0.040

0.040

0.057
0.210

0.205

0.100

0.040

0.028

0.063

1241061-2

0

NOTE:

00

0.100

1241061-1

0.105

0541157-3

0541157-2

0541157-1

0.110

0

0.100

.1
0.100

Maximum shim thickness is 0.375 inches (with fairing support plate, if installed
between gear and axle). Maximum difference in shim thickness in camber plane
is 0.108 inches. Maximum difference in shim thickness in toe plane is 0.100 inches.
All dimensions taken at shim corners.
SB9832R03

Main Wheel Alignment Check
Figure 203 (Sheet 2)

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MODEL 182/T182
MAINTENANCE MANUAL
NOSE LANDING GEAR - TROUBLESHOOTING
1.

General
A.

A troubleshooting chart has been provided to aid maintenance technician in system troubleshooting.
Refer to Figure 101.

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April 1/2002

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MODEL 182/T182
MAINTENANCE MANUAL

B1276

TIRES WEARS
EXCESSIVELY.

CHECK FOR DEFECTIVE TORQUE LINKS.
IF-

OK, CHECK FOR DEFECTIVE
SHIMMY DAMPER.
IF-

NOT OK, REPLACE
PARTS AS REQUIRED.

OK, CHECK FOR MAIN GEAR
ALIGNMENT. IF-

NOT OK, REPAIR OR
REPLACE DAMPER.

OK, CHECK FOR LOOSE OR
WORN STEERING LINKAGE.
IF-

NOT OK, ALIGN
MAIN GEAR.

OK, CHECK NOSE WHEEL FOR
OUT OF BALANCE CONDITION
AND CORRECT AS REQUIRED.

NOT OK, TIGHTEN OR
REPLACE PARTS AS
REQUIRED.

Nose Landing Gear Troubleshooting Chart
Figure 101 (Sheet 1)

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MODEL 182/T182
MAINTENANCE MANUAL

B1277

NOSE WHEEL
SHIMMY.

CHECK SHIMMY DAMPER FOR LACK OF
FLUID OR DEFECTIVE OPERATION. IF -

I

I
OK, CHECK FOR LOOSE SHIMMY
DAMPER ATTACHMENTS. IF -

NOT OK, REPLACE
PARTS AS REQUIRED.

OK, CHECK NOSE WHEEL FOR OUT
OF BALANCE CONDITION. IF -

NOT OK, TIGHTEN OR REPLACE
ATTACHMENTS AS REQUIRED.

OK, CHECK TORQUE LINK BOLTS
AND BUSHINGS FOR WEAR AND
REPLACE AS REQUIRED.

NOT OK, REBALANCE
NOSE WHEEL.

Nose Landing Gear Troubleshooting Chart
Figure 101 (Sheet 2)

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MODEL 182/T182
MAINTENANCE MANUAL

B1278

NOSE GEAR STRUT
LEAKING HYDRAULIC
FLUID.

CHECK FOR DEFECTIVE STRUT SEALS.
IF-

I
OK, DETERMINE PATH OF
LEAK AND CORRECT
CONDITION.

NOT OK, REPLACE
SEALS.

Nose Landing Gear Troubleshooting Chart
Figure 101 (Sheet 3)

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MODEL 182/T182
MAINTENANCE MANUAL
NOSE LANDING GEAR - MAINTENANCE PRACTICES
1.

General
A.

The nose gear has a steering nosewheel, mounted in a fork, attached to an air/oil oleo shock strut.
The shock strut is attached to the firewall with upper and lower strut fittings.

B.

Nose wheel steering is accomplished through the use of the rudder pedals. A steering bungee links
the nose gear to a whiffletree (bell crank) which is operated by push-pull rods connected to the rudder
bars. Steering is afforded up to approximately 10 degrees each side of center, after which brakes may
be used to gain a maximum deflection of 30 degrees right or left of center. A flexible boot is used to
seal the fuselage entrance of the steering bungee. A sprocket operated screw mechanism to provide
rudder trim is incorporated at the aft end of the bungee. The trim system is operated by a trim control
wheel mounted in the pedestal.

C.

The steering bungee assembly is spring loaded, and should not be disassembled internally. The
steering bungee assembly is connected to the steering torque arm on the nose gear strut by a bearing
end assembly, and to the whiffletree (bell crank) by a rod assembly.
Torque links keep the lower strut aligned with the nose gear steering system, but permit shock strut
action.

D.

2.

E.

Shimmy Damper (For airplanes that do not have the Lord Shimmy Damper) - The shimmy damper
gives resistance to shimmy when it moves hydraulic fluid through small orifices in a piston. The
damper piston shaft is attached to a stationary part, and 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.

F.

Shimmy Damper (For airplanes with the Lord Shimmy Damper) - The shimmy damper uses rubber
with a lubricant to absorb nosewheel vibration. The damper piston shaft is attached to a stationary
part, and housing is attached to the nosewheel steering torque arm assembly, which moves as the
nosewheel turns. This movement causes relative motion between the damper shaft and the housing.

Nosewheel Speed Fairing Removal/Installation
A.

Nosewheel Speed Fairing Removal (Refer to Figure 201).
(1) Deflate nose gear strut.
(2) Weight or tie down tail of airplane to raise nose wheel from floor.
(3) Remove nose wheel axle stud.
(4) Remove bolt securing speed fairing, cover plate and tow bar spacers at top of strut.
(5) Slide speed fairing up and remove nose wheel. Loosen scraper as necessary.
(6) Rotate speed fairing 90 degrees to centerline of airplane and work fairing down over the nose
gear fork to remove.

B.

Install Nose Wheel Speed Fairing (Refer to Figure 201).
(1) With speed fairing 90 degrees to center line of airplane, work fairing up over nose gear fork.
(2) Slide fairing up and install nose wheel in fork. Install axle stud.
(3) Position speed fairing over nose wheel and tighten axle stud nut until a slight bearing drag is
obvious when the wheel is rotated. Back off nut to the nearest castellated and install cotter pin.
(4) Install bolt, tow bar spacers, washers and nut attaching fairing and cover plate to strut.

CAUTION: You must clean the scraper for the tire to turn correctly. Make sure
you complete a check of the clearance every time the scraper has
been disturbed, the tire changed and when you install the speed
fairings. Damage will result if the correct clearance is not set
between the tire and the scraper. If any mud, snow or ice collects
on the scraper, it will prevent the tire from correct movement.
(5) Do a check of the clearance between the tire and the scraper.
(a) Clean off any dirt or ice that has collected on the scraper.

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MODEL 182/T182
MAINTENANCE MANUAL

C

SURE ASSEMBLY
NO1TE: UNSHADED PARTS OF
THE NOSE GEAR TURN
AS THE NOSE GEAR
STEERING SYSTEM IS
OPERATED ON THE
UPPER
FORGING
U
GROUND, BUT DO NOT
TURN WHILE AIRBORNE.
AS THE LOWER STRUT
EXTENDS, A CENTERING
BLOCK ON THE UPPER
TORQUE LINK CONTACTS
NOTE: PREFLIGHT INSPECTION
A FLAT SPOT ON THE
OF NOSE GEAR STRUT
BOTTOM END OF THE
SHOULD REVEAL 1.75
UPPER STRUT, THUS
SHIMMY
INCH TO 3.50 INCH OF
KEEPING THE LOWER
NOSE STRUT BARREL
STRUT AND WHEEL FROM
(BETWEEN TORQUE LINK
TURNING
ATTACHMENT FITTINGS)
SHOWING (OR APPROXIMATEL
-OWER FORGING
2.30 INCH AFTER BOUNCING).
DEVIATION FROM THESE
EERING BUNGEE
DIMENSIONS ARE CAUSE
PPER TORQUE LINK
TO CHECK AND SERVICE
THE STRUT.
WER TORQUE LINK
2.30 INCHES, +1.20 OR -0.55 INCHES

A

WASHER
)RK
MAXIMUM EXTENSION
85 INCH
0.15 INCH OR
1.15 INCH.

DETAIL
DETAIL C

DETAILC

A
7100T1001
A0742T1001
B0742T1003
C0742T1007

LOWER STRUT FORGING
Nose Landing Gear Installation
Figure 201 (Sheet 1)

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MODEL 182/T182
MAINTENANCE MANUAL

B1280

PER TORQUE LINK

GREASE FITTIN

OWER TORQUE LINK

GREASE

DETAIL

D

SPEED FAIRING
TOW-BAR S

DRAPER
STUD

DETAIL

E

D07421006
E07421008

Nose Landing Gear Installation
Figure 201 (Sheet 2)

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MODEL 182/T182
MAINTENANCE MANUAL

COVER
PLATE

A

SPACER

PER

DETAIL

A

(182T AND T182T)

0710T1001
A0741T1007

Nose Landing Gear Installation
Figure 201 (Sheet 3)

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MODEL 182/T182
MAINTENANCE MANUAL
(b) Adjust the clearance as necessary to have a minimum of 0.55 inch (14 mm) to a maximum
of 0.80 inch (20 mm).
(6) Lower nose of airplane to floor.
(7) Inflate nose gear strut. Refer to Chapter 12, Nose Landing Gear Shock Strut - Servicing.
CAUTION: Make sure the tire pressure is correct. Damage to the fairing can
result if the tire pressure is incorrect.
(8) Do a check of the tire pressure and adjust the pressure as necessary. Refer to Chapter 12, Tires
- Servicing.

3.

Nose Landing Gear Removal/Installation
A.

Remove Nose Landing Gear (Refer to Figure 201).
(1) Remove cowling. Refer to Chapter 71, Cowling - Removal/Installation.
(2) Weight or tie down tail of airplane to raise nose wheel from floor.
(3) Disconnect nose wheel steering bungee and shimmy dampener from nose gear.
CAUTION: Ensure strut is completely deflated prior to removing bolt or roll pin
at top of strut.
(4)
(5)
(6)
(7)
(8)

B.

4.

Deflate strut completely and telescope strut to its shortest length.
Remove bolt from upper forging and strut.
Remove the screws securing the steering torque arm and closure assembly to the steering collar.
Remove lower forging attach bolt.
Pull the strut assembly down from upper attach forging through the steering torque arm and
lower forging.

Install Nose Landing Gear (Refer to Figure 201).
(1) Insert strut up through lower forging and install steering torque arm over strut.
(2) Position upper end of strut in upper forging, align bolt hole in forging and strut and install bolt.
(3) Install lower forging mount bolt and washer. Torque bolt 100 to 140 inch pounds.
(4) Install screws securing steering torque arm and closure assembly to steering collar.
(5) Connect steering bungee to steering torque arm.
(6) Connect shimmy dampener.
(7) Inflate and service shock strut. Refer to Chapter 12, Nose Landing Gear Shock Strut - Servicing.
(8) Rig nose wheel steering tubes. Refer to Chapter 27, Rudder Control System - Maintenance
Practices.
(9) Remove weights or tie down from tail, and lower nose wheel to floor.
(10) Install cowling. Refer to Chapter 71, Cowling - Removal/Installation.

Nose Gear Shock Strut Disassembly/Assembly
A.

Disassemble Nose Gear Shock Strut (Refer to Figure 202).
(1) Remove speed fairing and nose gear. Refer to Nose Wheel Speed Fairing Removal/Installation,
and Nose Landing Gear Removal/Installation.
(2) Ensure strut is completely deflated.
(3) Remove torque links. (Note position of washers, shims, and spacers).
(4) Remove lock ring from groove inside lower end of upper strut. A small hole is provided at the
lock ring grove to facilitate removal of the lock ring.
NOTE:

Hydraulic fluid will drain from strut as lower strut is pulled from upper strut.

(5) Use a straight, sharp pull to separate upper and lower struts. Invert lower strut and drain
remaining hydraulic fluid.
(6) Remove lock ring and bearing at top of lower strut.
(7) Slide packing support ring, scraper ring, retaining ring, and lock ring from lower strut, noting
relative position and top side of each ring, wire together if desired.
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MODEL 182/T182
MAINTENANCE MANUAL

O-RING

BACK-UP RING

LOWER

O-RING
BACK-UP RING

VALVE

RETAINING RING
O-RI

ORIFICE
PISTON
SUPPORT

PACKING

\

O-RING

PACKING
SUPPORT
RING

RETAINING
RING
I

LOCK

BEARING
O-RING

SUPPORT RING
SCRAPER RING

A

LOCK RING

I

VIEW A-A

RETAI NING
RING

LOWER STRUT

I
I

B
LINK

UPPER
STRUT

DETAIL

CO

L

A

L

B
PIN
G

R

DETAIL

_

A

001
T1009
A-A07421011
B07421012

Nose Gear Shock Strut Breakdown
Figure 202 (Sheet 1)

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MODEL 182/T182
MAINTENANCE MANUAL
(8)
(9)

Remove O-rings and backup rings from packing support ring.
Remove bolt securing torque link fitting and remove torque link fitting from lower strut.
NOTE:

Bolt attaching torque link fitting also holds metering pin base plug in place.

(10) Push metering pin and base plug assembly from lower strut. Remove O-rings and metering pin
from base plug.
NOTE:

B.

Lower strut and fork are press fit, drilled on assembly. Separation of these parts is
not recommended, except for installation of new parts.

(11) Remove retaining ring securing steering arm assembly on upper strut. Remove steering arm,
shims, and washers.
(12) Push orifice support from upper strut and remove O-ring.
Assemble Nose Gear Shock Strut (Refer to Figure 202).
(1) Make sure all parts are clean and examined for damage before you assemble the nose gear
shock strut. Refer to Nose Gear Shock Strut Inspection/Repair.
(2) Apply lubricant and assemble the parts that follow with a film of Petrolatum VV-P-236, hydraulic
fluid MIL-PRF-5606 or Dow Corning DC-7.
(3) Install washer and shim(s) under steering collar if installed.
(4) Lubricate needle bearings in steering collar. Refer to Chapter 12, Landing Gear and Parking
Brake - Lubrication.

(5) Install steering collar and retaining ring.
(6) Check steering collar for snug fit against washer. Shims of variable thickness are available
from Cessna Aircraft Company, Cessna Parts Distribution, Department 701, CPD 2 5800 East
Pawnee Road Wichita KS 67218-5590.
(7) If shims are required, remove retaining ring and steering collar and add shims as necessary to
provide a snug fit with steering collar retaining ring in place. Table 201 lists part number and
thickness of available shims:
PART NUMBER

THICKNESS

1243030-5

0.006 INCH

1243030-6

0.012 INCH

1243030-7
0.020 INCH
(8) Install O-ring and filler valve in orifice piston support, and install orifice piston support in upper
strut.
(9) Install O-ring and metering pin O-ring in base plug. Secure with nut.
NOTE:

If base plug is to be replaced, new part will need to be line drilled to accept NAS5 bolt.

(10) Install base plug assembly in lower strut fork assembly.
(11) Install bolt through upper hole in lower strut, through base plug and secure with nut.
(12) Install lock ring, retaining ring and scraper ring, making sure they are installed in the same
positions as they were removed.
(13) Install O-rings and backup rings in packing support ring; slide packing support ring over lower
strut.
(14) Install bearing and lock ring at upper end of lower strut assembly. Note top side of bearing.
(15) Install upper strut assembly over lower strut assembly.
(16) Install lock ring in groove in lower end of upper strut. Position lock ring so that one end covers
the small access hole in the lock ring groove.
(17) Install closure assembly over upper strut.
(18) Install steering torque arm over upper strut.
(19) Line up holes in steering torque arm and closure assembly with holes in steering collar and
screws, washers, and nuts.
(20) Install torque links, positioning washers, shims, and spacers exactly in positions as removed.
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MAINTENANCE MANUAL
(21) Install strut. Refer to Nose Landing Gear Removal/Installation and Nose Wheel Speed Fairing
Removal/Installation.
5.

Nose Gear Shock Strut Inspection/Repair
A.

6.

7.

Inspect and Repair Nose Gear Shock Strut. (Refer to Figure 202).
(1) Thoroughly clean all parts in cleaning solvent and inspect carefully.
(2) All worn or defective parts and all 0-rings and backup rings must be replaced with new parts.
(3) Sharp metal edges should be smoothed with No. 40 emery paper, then cleaned with solvent.

Shimmy Damper Removal/Installation
A.

Shimmy Damper Removal (Refer to Figure 201).
(1) Remove the cotter pin and remove the nut, bolt, and washers from the damper piston rod end.
(2) Remove the bolts and the washers that attach the barrel to the nosewheel steering torque arm.
(3) Remove the shimmy damper. For airplanes with the Lord Shimmy Damper installed, discard the
Lord Shimmy Damper.

B.

Shimmy Damper Installation (Refer to Figure 201).
(1) Before you install the shimmy damper, do the maintenance that follows.
(a) If a Lord Shimmy Damper has been in storage for a long period, make sure that the shaft
moves freely before you install it. Refer to Chapter 12, Nose Landing Gear Shimmy
Damper - Servicing.
(b) Make sure that the tire is in good condition, is balanced, and has no tears or foreign objects
in it.
(c) Examine the interface between the bottom of the steering collar and the top of the nose
gear fork. If there is looseness here, replace or add more shims under the collar.
(d) Examine the assembly hardware for wear and replace as necessary.
(e) Examine the shimmy damper arm attach points on the landing gear and the structure for
wear and replace as necessary.
(2) Install the shimmy damper on the steering torque arm with the washers and the bolts.
(3) Connect the shimmy damper rod with the bolt, washers, and nut.
(4) Install the cotter pin through the nut and the bolt.
(5) For cleaning and servicing of the shimmy damper, refer to Chapter 12, Nose Landing Gear
Shimmy Damper - Servicing.

Shimmy Damper Disassembly/Assembly (For airplanes that do not have the Lord Shimmy Damper)
A.

Disassemble Shimmy Damper (Refer to Figure 203).
NOTE:
(1)
(2)
(3)
(4)
(5)
(6)
(7)
(8)
(9)

B.

There are no inspection or overhaul requirements for the Lord Shimmy Damper.

Remove the filler plug and drain the hydraulic fluid from the shimmy damper.
Remove the setscrew, spring, and floating piston from the rod assembly.
Remove the snap ring, head, and second snap ring from the barrel.
Pull the rod assembly from the barrel.
Examine all of the 0-rings and the packing ring for serviceability.
Examine the piston, rod, and floating piston for serviceability.
Examine the inside surface of the barrel.
Examine the backup ring and the retainer ring for serviceability.
Replace all damaged parts.

Assemble Shimmy Damper (Refer to Figure 203).
(1) Before you assemble the shimmy damper, make sure there are no sharp edges on the parts
that can result in damage of the 0-rings or packing ring when assembled. Put lubricant on all
internal parts with MIL-PRF-5606 hydraulic fluid before you assemble them.
(2) If removed, install the 0-ring in the end of the barrel.
(3) If removed, install the 0-ring and the retainer ring on the piston.
(4) Install the 0-ring on the floating piston. Then install the floating piston, spring, and setscrew in
the rod.

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MODEL 182/T182
MAINTENANCE MANUAL

A

FILLER PLUG
STAT- O-SEAL

BARREL

SNAP
BACKUP RIN
PACKING RING
BACKUP RING
RETAINER
RING
PISTON
ROLL PIN

'RING

DETAIL A
0710T1001
A0741R1010

Shimmy Damper
Figure 203 (Sheet 1)

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MODEL 182/T182
MAINTENANCE MANUAL
Install the rod assembly in the barrel.
If removed, install the packing and the backup ring in the head.
If removed, install the O-ring on the head.
Install the snap ring in the barrel.
Install the head assembly and the outer snap ring.
Service the shimmy damper. Refer to Chapter 12, Nose Landing Gear Shimmy Damper Servicing.
(11) Install the shimmy damper on the nose landing gear. Refer to Shimmy Damper Removal/
Installation.
(5)
(6)
(7)
(8)
(9)
(10)

8.

9.

Nose Wheel Steering Removal/Installation
A.

Remove Nose Wheel Steering (Refer to Figure 204).
(1) Remove cowling. Refer to Chapter 71, Cowling - Removal/Installation.
(2) Remove pilot's and copilot's seats. Refer to Chapter 25, Front Seats - Maintenance Practices.
(3) Remove carpet and shield assemblies.
(4) Remove pedestal cover.
(5) Loosen rudde