182SMM14 182/T182 SERIES (1997 AND ON) Cessna_182S_1997on_MM_182SMM Cessna 182S 1997on MM 182SMM
User Manual: Cessna_182S_1997on_MM_182SMM
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A .awCamepn.
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
Page 3
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
Page 4
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
Page 4
i an 1/2007
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
Page
Page
Page
Page
Page
Page
1
1
1
1
1
2
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05 - CONTENTS
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Jul 1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
INSPECTION OPERATION 9 ...........................
Description ............
General Inspection Criteria ..........................
5-12-09 Page 1
5-12-09 Page 1
5-12-09 Page 1
INSPECTION OPERATION 10...........................
Description .................................
General Inspection Criteria ..........................
INSPECTION OPERATION 11...........................
Description .................................
General Inspection Criteria ..........................
5-12-10 Page 1
5-12-10 Page 1
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PROGRESSIVE CARE ..............................
Operation 13 ................................
INSPECTION OPERATION 14...........................
Description .................................
General Inspection Criteria ..........................
INSPECTION OPERATION 15...........................
Description .................................
General Inspection Criteria ..........................
5-12-13 Page 1
5-12-13 Page 1
INSPECTION OPERATION 16...........................
Description .................................
General Inspection Criteria ..........................
5-12-16 Page 1
5-12-16 Page 1
5-12-16 Page 1
INSPECTION OPERATION 17...........................
Description .................................
General Inspection Criteria ..........................
5-12-17 Page 1
5-12-17 Page 1
5-12-17 Page 1
INSPECTION OPERATION 18...........................
Description .................................
General Inspection Criteria ..........................
INSPECTION OPERATION 19...........................
Description .................................
General Inspection Criteria ..........................
5-12-18 Page 1
5-12-18 Page 1
5-12-18 Page 1
INSPECTION OPERATION 20...........................
Description .................................
General Inspection Criteria ..........................
5-12-20 Page 1
5-12-20 Page 1
5-12-20 Page 1
INSPECTION OPERATION 21...........................
Description .................................
General Inspection Criteria ..........................
INSPECTION OPERATION 22 ...........................
Description .................................
General Inspection Criteria ..........................
5-12-21 Page 1
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INSPECTION OPERATION 23...........................
Description .................................
General Inspection Criteria ..........................
5-12-23 Page 1
5-12-23 Page 1
5-12-23 Page 1
INSPECTION OPERATION 24...........................
Description .................................
General Inspection Criteria ..........................
5-12-24 Page 1
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5-12-24 Page 1
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
Page 4
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
5-10-01
© Cessna Aircraft Company
Page 5
Jul 3/2006
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
5-10-01
C Cessna Aircraft Comoanv
Page 6
Jul 3/2006
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.
5-10-01
© 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.
5-10-01
© 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
5-10-01
© Cessna Aircraft Company
Page 17
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti 82
MAINTENANCE MANUAL
COMPONENT TIME LIMITS
1.General
A. Most components given in Chapter 5 must be examined as shown elsewhere in this chapter and
repaired, overhauled, or replaced as necessary. Some components have a time or life limit and must
be overhauled or replaced on or before the specified limit.
B. The terms overhaul and replacement as used within this section are defined as follows:
(1) Overhaul - Overhaul the item as given in 14 CFR 43.2 or replace it.
(2) Replacement - Replace the item with a new item or a serviceable item that is within its service
life and time limits or has been rebuilt as given in 14 CFR 43.2.
C. This section (5-11 -00) gives a list of items which must be overhauled or replaced at specific time limits.
Cessna-Supplied Replacement Time Limits shows those items which Cessna has found necessary
to overhaul or replace at specific time limits. Supplier-Supplied Replacement Time Limits shows
component time limits which have been given by an outside supplier for their products. In addition to
these time limits, the components shown in this section are also examined at regular time intervals
given in the Inspection Time Intervals section. If necessary, based on service use and inspection
results, these components can be overhauled or replaced before their time limit is reached.
2.
Cessna-Supplied Replacement Time Limits
A.
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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MODEL 182/Ti82
MAINTENANCE MANUAL
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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CESSNA AIRCRAFT COMPANY
MODEL 182/Ti 82
MAINTENANCE MANUAL
PROGRESSIVE CARE PROGRAM
General
NOTE:
The inspection charts contained within the Progressive Care Program are not intended to be
all-inclusive, for no such charts can replace the good judgment of a certified airframe and
powerplant mechanic in performance of his or her duties. As the one primarily responsible for
the airworthiness of the airplane, the owner or operator must select only qualified personnel
to maintain the airplane.
A.
The program is divided into four primary operations (operations 1 thru 4) which cover all 50-hour,
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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MODEL 182/Ti182
MAINTENANCE MANUAL
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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MODEL 182/T182
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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MODEL 182/T182
MAINTENANCE MANUAL
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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MODEL 182/T182
MAINTENANCE MANUAL
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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MODEL 182/T182
MAINTENANCE MANUAL
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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MODEL 182/T182
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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MODEL 182/T182
MAINTENANCE MANUAL
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
5-12-01
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MODEL 182/T182
MAINTENANCE MANUAL
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
© Cessna Aircraft Company
Page 7
Jul 3/2006
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
5-12-02
Cessna Aircraft Company
Page 1
Jul 3/2006
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
5-12-02
© Cessna Aircraft Company
Page 2
Jul 3/2006
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
5-12-02
© Cessna Aircraft Company
Page 3
Jul 3/2006
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
Page 4
Jul 3/2006
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
Page 5
Jul 3/2006
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
Jul 3/2006
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
© Cessna Aircraft Company
Page 3
Jul 3/2006
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
5-12-03
© Cessna Aircraft Company
Page 4
Jul 3/2006
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
Jul 3/2006
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 ***
5-12-17
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Page 1
Jul 3/2006
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 ***
5-12-18
© Cessna Aircraft Company
Page 1
Jul 3/2006
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 ***
5-12-19
© Cessna Aircraft Company
Page 1
Jul 3/2006
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
© Cessna Aircraft Company
Page 1
Jul 3/2006
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 ***
5-12-21
© Cessna Aircraft Company
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Jul 3/2006
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 ***
5-12-22
© Cessna Aircraft Company
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Jul 3/2006
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 ***
5-12-23
© Cessna Aircraft Company
Page 1
Jul 3/2006
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 ***
5-12-24
© Cessna Aircraft Company
Page 1
Jul 3/2006
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 ***
5-12-25
© Cessna Aircraft Company
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Jul 3/2006
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
© Cessna Aircraft Company
Page 1
Jul 3/2006
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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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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© Cessna Aircraft Company
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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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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
7-10-00
7-10-00
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
LIST OF EFFECTIVE PAGES
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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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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
LIST OF EFFECTIVE PAGES
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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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MODEL 182/T182
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
LIST OF EFFECTIVE PAGES
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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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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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MAINTENANCE MANUAL
(5) Apply a tire preservative to the tires.
(6) Cover the tires to protect against grease and oil.
(7) Block up the fuselage to relieve the pressure on the tires or rotate the wheels every 30 days.
NOTE:
This aids to change supporting points and prevent flat spotting on the tires.
(8) Lubricate all airframe items and cover all openings which allow moisture and/or dust to enter.
(9) Turn battery and store in a cool, dry place. Service the battery periodically and charge as
required.
(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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(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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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.........................................
CONTENTS
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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
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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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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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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 ...........................................
12-21-04 Page 301
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HEATING AND VENTILATION CONTROL CABLES - SERVICING ...................
General ....................................................................
Heating And Ventilation Control Cables Lubrication.............................
12-21-05 Page 301
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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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INTERIOR - CLEANING/PAINTING................................................
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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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© Cessna Aircraft Company
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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.
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© 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:
12-21-00
© Cessna Aircraft Company
Page 1
Jan 2/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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
12-21-01O
© Cessna Aircraft Company
Page 2
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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
12-21-00
© Cessna Aircraft Company
Page 3
Jan 2/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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.
12-21-01
© Cessna Aircraft Company
Page 301
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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)
12-21-01
© Cessna Aircraft Company
Page 302
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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.
12-21-02
© Cessna Aircraft Company
Page 301
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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)
12-21-02
© Cessna Aircraft Company
Page 302
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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)
12-21-02
© Cessna Aircraft Company
Page 303
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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.
12-21-03
© Cessna Aircraft Company
Page 301
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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)
12-21-03
© Cessna Aircraft Company
Page 302
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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)
12-21-03
© Cessna Aircraft Company
Page 303
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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)
12-21-03
© Cessna Aircraft Company
Page 304
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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)
12-21-03
© Cessna Aircraft Company
Page 305
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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)
12-21-03
© Cessna Aircraft Company
Page 306
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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.
12-21-04
© Cessna Aircraft Company
Page 301
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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.
12-21-05
© Cessna Aircraft Company
Page 301
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
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
12-22-00
©Cessna Aircraft Company
Page 701
Mar 1/2005
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
4.
Windshield and Window Cleaners
CAUTION: Do not use methanol, gasoline, denatured alcohol, benzene, xylene,
acetone, carbon tetrachloride, fire extinguisher fluid, deicer fluid, lacquer
thinner, or commercial or household glass window cleaner when you clean
the windshield and windows of the airplane. These solvents will cause
damage to the plastic.
Table 702. Windshield and Window Cleaners/Polishers
NAME
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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© Cessna Aircraft Company
Page 702
Mar 1/2005
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
(3) Use a mild soap or detergent (such as dishwashing liquid) in water to clean the surface of the
windshield. Use bare hands to rub the solution over the surface. A clean cloth can be used to
apply the soap solution to the surface, but you must be very careful to prevent scratches.
(4) On acrylic windshields and windows only, if the windshield and windows are still dirty after they
are cleaned with a mild detergent, use Type II aliphatic naphtha as a cleaning agent. Apply
the agent only with a soft, clean cloth. Make sure that the cloth is frequently folded to avoid
scratching the windshield with any abrasive particles.
(5) Flush the surface with clean water and dry with a clean cloth.
6.
Waxing and Polishing Windshield and Windows
CAUTION: Do not use rain repellent on acrylic surfaces because it can cause damage.
NOTE:
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.
12-22-00
©Cessna Aircraft Company
Page 703
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
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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© Cessna Aircraft Company
Page 704
Mar 1/2005
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
(10) If necessary, the engine cowl can be cleaned with the same cleaning agents, then flushed with
water and dried with a soft, clean cloth. After you clean the engine, lubricate all the control arms
and moving parts, as necessary.
(11) Install the engine cowl.
WARNING: Make sure that the magneto switches are off, the throttle is
closed, the mixture control is in the idle cutoff position, and
the airplane is stable before you turn the propeller by hand. Do
not stay within the arc of the propeller blades while you turn
the propeller. If the engine accidentally starts, the propeller
blades can cause serious injury or death.
(12) Before you start the engine, turn the propeller by hand a minimum of four full revolutions.
10.
Propeller
A.
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
© Cessna Aircraft Company
Page 705
Mar 1/2005
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
INTERIOR - CLEANING/PAINTING
1.
General
A.
This section recommends different types of cleaning materials and cleaning procedures for the interior
of the airplane.
WARNING: Do these cleaning operations in an area with good airflow. Use the
applicable safety precautions for each cleaning material that you
use.
2.
Interior Cleaning Materials
NOTE:
Equivalent substitutes can be used for the following items:
NAME
NUMBER
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.
12-23-00
© Cessna Aircraft Company
Page 701
Jan 2/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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
Page 702
Jan 2/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
6.
Cleaning the GDU 1040 Display Lens
NOTE:
The Primary Flight Display (PFD) and Multi-Function Display (MFD) are the GDU 1040 displays
in airplanes with Garmin G1000.
CAUTION: If possible, do not touch the GDU 1040 display lens. The lens has a layer
of anti-reflective material which is very sensitive to skin oils, waxes, and
abrasive cleaners.
CAUTION: Do not use cleaners that contain ammonia. Ammonia will cause damage to
the anti-reflective material.
A.
Clean the GDU 1040 Display Lens.
(1) To clean the lens, use a clean, lint-free cloth and an eyeglass lens cleaner that is specified as
safe for anti-reflective material.
12-23-00
C Cessna Aircraft Company
Page 703
Jan 2/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
UNSCHEDULED SERVICING - DESCRIPTION AND OPERATION
1.
General
A.
This section gives procedures and recommendations for normally unscheduled servicing.
B.
Instructions are given in the Cold Soak procedures for operation of the airplane during very cold
temperatures.
NOTE:
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
Page 1
Jan 2/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
WARNING: Never bring open flames near the airplane. Use of a heater with
an open flame to preheat the engine can cause damage to the
airplane and injury to personnel.
(3) 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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© Cessna Aircraft Company
Page 2
Jan 2/2006
CHAPTER
STAMDAR
PRACICE
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
LIST OF EFFECTIVE PAGES
CHAPTER-SECTION-SUBJECT
PAGE
DATE
Page 1
Pages 1-4
April 1/2002
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©Cessna Aircraft Company
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RECORD OF TEMPORARY REVISIONS
Temporary Revision
Number
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By
CESSNA AIRCRAFT COMPANY
MODEL 182/T1 82
MAINTENANCE MANUAL
CONTENTS
STANDARD PRACTICES AIRFRAME - GENERAL .................
Scope....................................
Definition ..................................
MATERIAL AND TOOL CAUTIONS - DESCRIPTION AND OPERATION........
Titanium...................................
Mercury...................................
Asbestos ..................................
Cadmium Plated Fasteners..........................
Maintenance Precautions...........................
General Usage Solvents ...........................
National Emissions Standards for Hazardous Air Pollutants ...........
Facilities and Equipment ...........................
TORQUE DATA - MAINTENANCE PRACTICES...................
General...................................
Torque Requirements for Bolts, Screws and Nuts................
Torque Requirements for Hi-Lok Fasteners...................
Torque Requirements for Electrical Current Carrying And Airframe Ground
Fasteners.................................
Torque Requirements for Rigid Tubing and Hoses................
SAFETYING - MAINTENANCE PRACTICES ....................
General...................................
Safety Wire .................................
Safety Wire Installation............................
Cotter Pin Installation.............................
Safetying Turnbuckles ............................
CONTROL CABLE WIRE BREAKAGE AND CORROSION LIMITATIONS MAINTENANCE PRACTICES ...........................
Examination of Control Cables ........................
SOLVENTS, SEALANTS, AND ADHESIVES - DESCRIPTION AND OPERATION ...
General...................................
Description .................................
ACCEPTABLE REPLACEMENTS FOR CHEMICALS AND SOLVENTS - DESCRIPTION
AND OPERATION ................................
General...................................
Hand-Wipe Cleaning Operations .......................
Priming Operations..............................
Topcoat Operations .............................
Paint Stripping Operations ..........................
GENERAL SOLVENTS/CLEANERS - MAINTENANCE PRACTICES .........
General...................................
Tools, Equipment and Materials........................
Safety Precautions..............................
D escription
......
. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
INTERIOR AND EXTERIOR FINISH - CLEANING/PAINTING.............
General...................................
Interior and Exterior Finishes .........................
Paint Facility.................................
Sanding Surfacer ..............................
Paint Stripping................................
Hand Solvent Cleaning............................
Maintenance of the Interior and Exterior Primary Coatings and Topcoat......
©Cessna Aircraft Company
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20 - CONTENTS
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Janl1/2007
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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©D Cessna Aircraft Company
Page 2of 2
Janl1/2007
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
© Cessna Aircraft Company
Page 1
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
MATERIAL AND TOOL CAUTIONS - DESCRIPTION AND OPERATION
1.
Titanium
CAUTION: Do not use cadmium-plated tools on titanium parts. Cadmium particles can
stay on such parts. The cadmium particles will cause an unwanted condition
with the titanium when heated. The titanium part will become brittle in the
area of the unwanted condition and make cracks.
CAUTION: Do not let cadmium-plated fasteners touch titanium parts.
2.
Mercury
CAUTION: Do not use thermometers and other mercury-based test equipment on the
airplane.
A.
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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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
(3) Do not breathe the fumes of dangerous chemicals.
(4) Make sure the work area has good airflow and the applicable breathing equipment is used when
composites or metals are sanded or work is done in an area where small particles can be made.
6.
General Usage Solvents
A.
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
Page 2
Mar 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
7.
National Emissions Standards for Hazardous Air Pollutants
A.
National Emissions Standards for Hazardous Air Pollutants (NESHAP).
(1) The NESHAP standards have put a limit on the use of certain chemicals and solvents.
(2) For complete details of the regulatory standards, see the Federal Register, 40 CFR Part 63,
[Ad-FRL-5636-1], RIN 2060-AG65.
B.
NESHAP Requirements.
(1) Hand-Wipe Cleaning.
(a) All hazardous air pollutants or organic compounds that release dangerous fumes that are
used as hand wipe cleaning solvents must meet a composition requirement and have a
vapor pressure less than or equal to 1.75 Hg at 69°(45 mm Hg at 2 O'C.)
(b) The requirements specified may be met by an alternative compliance plan used by the
permitting authority and approved under Section 112(1) of the Clean Air Act.
(2) Primer Application.
(a) The organic hazardous air pollutant content is limited to 350 g/l (2.9 pounds-per-gallon),
less water, as applied.
(b) The volatile organic compound limit is 350 g/l (2.9 pounds per gallon), less water, as
applied.
(c) Use coatings below the content limit or use monthly volume-weighted averaging to get the
content limits to meet content limits.
(3) Topcoat Application.
(a) The base coat organic hazardous air pollutant content must be less than 420 g/l (3.5
pounds-per-gallon), less water, as applied.
(b) The volatile organic compound limit is 420 g/l (3.5 pounds per gallon), less water, as
applied.
(c) The topcoats must meet the requirements of MIL-C-85285.
(d) Stripe paint requirements are the same as the base coat requirements. If the recommended
supplier cannot be used, then use base coat materials to paint stripes.
(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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Page 3
Mar 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B.
Equipment
(1) Applied spray of cleaning solvents, paint removers or color chemical film treatment solutions is
to be prevented unless all requirements of NESHAP are met.
(2) Spraying equipment to wash the airplane with alkaline cleaner can be used. This equipment is
sufficient to spray deoxidizer, chemical film solutions and rinse water.
(3) A high pressure washer is recommended, with or without hot water.
(4) Respirators and/or dust masks must be used.
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Page 4
Mar 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti 82
MAINTENANCE MANUAL
TORQUE DATA
-
MAINTENANCE PRACTICES
General
A. To ensure security of installation and prevent over stressing of components during installation, the
torque values outlined in this section and other applicable chapters of this manual should be used
during installation and repair of components.
B. The torque value tables, listed in this section, are standard torque values for the nut and bolt
combinations shown. If a component requires special torque values, those values will be listed in the
applicable maintenance practices section.
C. Torque is typically applied and measured using a torque wrench. Different adapters, used in
conjunction with the torque wrench, may produce an actual torque to the nut or bolt which is different
from the torque reading. Figure 201 is provided to help calculate actual torque in relation to specific
adaptors used with the torque wrench.
D. Running Torque Value.
(1) Running torque value is the torque value required to rotate a nut on a threaded shaft, without
tightening. Running torque value does not represent the torque values listed in the tables of this
section. Torque values listed in the tables represent the torque values above running torque.
For example, if final torque required is to be 150 inch-pounds and the running torque is 25 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
20-1 1-00
Page 201
Jan11/2007
CESSNA AIRCRAFT COMPANY
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)
20-1 1-00
©Cessna Aircraft Company
Page 202
Janl1/2007
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
20-1 1-00
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Janl1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti182
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
20-1 1-00
©Cessna Aircraft Company
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Janl1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti182
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
20-1 1-00
©Cessna Aircraft Company
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Janl1/2007
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
©Cessna Aircraft Company
Page 206
Janl1/2007
CESSNA AIRCRAFT COMPANY
MODEL 1821T182
MAINTENANCE MANUAL
Table 205. Tubing/HoseTorque Limits (Inch-Pounds)
Hose Tubing
Size
O.D.
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
Q Cessna Aircraft Company
20-11 -00
Page 207
Janl1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
SAFETYING - MAINTENANCE PRACTICES
1.
General
A.
Safety Wire.
(1) Inconel (Uncoated), Monel (Uncoated).
(a) Used for general safety wiring purposes. Safety wiring is the application of wire to prevent
relative movement of structural or other critical components subjected to vibration, tension,
torque, etc. Monel to be used at temperatures up to 700'F (370 'C) and inconel to be
used at temperatures up to 1500F (8151C). Identi fled by the color of the finish, monel and
inconel color is natural wire color.
(2) Copper, Cadmium Plated and Dyed Yellow in accordance with FED-STD 595.
(a) This wire will be used for shear and seal wiring applications. Shear applications are those
where it is necessary to purposely break or shear the wire to permit operation or actuation
of emergency devices. Seal applications are those where the wire is used with a lead seal
to prevent tampering or use of a device without indication. Identified by the color of the
finish, copper wire is dyed yellow.
(3) Aluminum Alloy (Alclad 5056), Anodized and Dyed Blue in accordance with FED-STD 595.
(a) This wire will be used exclusively for safety wiring magnesium parts.
NOTE:
Surface treatments which obscure visual identification of safety wire are
prohibited.
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
20-12-00
© Cessna Aircraft Company
Page 201
Mar 1/2004
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
Page 202
Mar 1/2004
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
Page 203
Mar 1/2004
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
Page 204
Mar 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1105
hllllllllllll
1111111111111
II1illlllllll
AN500A
5598T1001
5598T1001
Lockwire Safetying
Figure 201 (Sheet 3)
20-12-00
© Cessna Aircraft Company
Page 205
Mar 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
C.
Tension.
(1) Parts shall be safety wired in such a manner that the safety wire shall be put in tension when
the part tends to loosen. The safety wire should always be installed and twisted so that the loop
around the head stays down and does not tend to come up over the bolt head and leave a slack
loop.
NOTE:
(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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MAINTENANCE MANUAL
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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MAINTENANCE MANUAL
(5) In the event of more than 50 percent of the cotter pin diameter is above the nut castellation, a
washer should be used under the nut or a shorter fastener should be used. A maximum of two
washers may be permitted under a nut.
(6) The largest nominal diameter cotter pin listed in MS24665, which the hole and slots will
accommodate, shall be used; but in no application to a nut, bolt or screw shall the pin size be
less than the sizes described in Figure 202.
(7) Install the cotter pin with the head firmly in the slot of the nut with the axis of the eye at right
angles to the bolt shank, and bend prongs so that the head and upper prong are firmly seated
against the bolt.
(8) In the pin applications, install the cotter pin with the axis of the eye parallel to the shank of the
clevis pin or rod end. Bend the prongs around the shank of the pin or rod end.
(9) Cadmium plated cotter pins shall not be used in applications bringing them in contact with fuel,
hydraulic fluid or synthetic lubricants.
5.
Safetying Turnbuckles
A.
Use of Locking Clips (Refer to Figure 203).
(1) Prior to safetying, both threaded terminals should be screwed an equal distance into the
turnbuckle barrel, and should be screwed in, at a minimum, so no more than three threads of
any terminal are exposed outside the body.
(2) After the turnbuckle has been adjusted to its locking position, with the groove on terminals and
slot indicator notch on barrel aligned, insert the end of the locking clip into the terminal and barrel
until the "U" curved end of the locking clip is over the hole in the center of the barrel.
(a) Press the locking clip into the hole to its full extent.
(b) The curved end of the locking clip will latch in the hole in the barrel.
(c) To check proper seating of locking clip, attempt to remove pressed "U" end from barrel hole
with fingers only.
NOTE:
Do not use a tool as the locking clip could be distorted.
(3) Locking clips are for one time use only and should not be reused.
(4) Both locking clips may be inserted in the same hole of the turnbuckle barrel or in opposite holes
of the turnbuckle barrel.
B.
Use of Safety Wire (Refer to Figure 204).
(1) Some turnbuckles use safety wire. For more information, refer to Federal Publication AC 4313.1B, Safety Methods For Turnbuckles.
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MAINTENANCE MANUAL
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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MODEL 182/T182
MAINTENANCE MANUAL
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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MAINTENANCE MANUAL
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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MAINTENANCE MANUAL
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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MAINTENANCE MANUAL
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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MAINTENANCE MANUAL
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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MAINTENANCE MANUAL
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)
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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
21-20-00 Page 101
21-20-00 Page 201
21 -20-00 Page 201
21-20-00 Page 201
21 -20-00 Page 201
21-20-00 Page 201
21-21 -00 Page 201
21 -21 -00 Page 201
21-21 -00 Page 201
21-21 -00 Page 201
21-21 -00 Page 201
21 -21 -00 Page 204
21-21-00 Page 204
21 -21 -00 Page 206
21 -40-00 Page 101
21 -40-00 Page 101
21 -40-00
21-40-00
21-40-00
21 -40-00
21-40-00
21-40-00
21-40-00
21-40-00
21 -CONTENTS
Page 201
Page 201
Page 201
Page 201
Page 201
Page 201
Page 206
Page 206
Pagel1of 1
Janl1/2007
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.
21-00-00
© Cessna Aircraft Company
Page 1
April 1/2002
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.
21-20-00
©Cessna Aircraft Company
Page 1
April 1/2002
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.
21-20-00
©Cessna Aircraft Company
Page 101
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)
21-20-00
© Cessna Aircraft Company
Page 102
April 1/2002
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.
21-20-00
© Cessna Aircraft Company
Page 201
Mar 1/2005
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)
21-20-00
© Cessna Aircraft Company
Page 202
Mar 1/2005
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)
21-20-00
© Cessna Aircraft Company
Page 203
Mar 1/2005
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.
21-21-00
©Cessna Aircraft Company
Page 201
Jan 2/2006
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)
21-21-00
© Cessna Aircraft Company
Page 202
Jan 2/2006
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)
21-21-00
© Cessna Aircraft Company
Page 203
Jan 2/2006
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
Page 204
Jan 2/2006
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)
21-21-00
© Cessna Aircraft Company
Page 205
Jan 2/2006
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.
21-21-00
Cessna Aircraft Company
c
Page 206
Jan 2/2006
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.
21-40-00
© Cessna Aircraft Company
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)
21-40-00
© Cessna Aircraft Company
Page 102
April 1/2002
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
21-40-00
Page 201
Janl1/2007
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)
21-40-00
©Cessna Aircraft Company
Page 202
Janl1/2007
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
21-40-00
Page 203
Janl1/2007
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)
21-40-00
©Cessna Aircraft Company
Page 204
Janl1/2007
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)
21-40-00
© Cessna Aircraft Company
Page 205
Janl1/2007
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.
21-40-00
© Cessna Aircraft Company
Page 206
Janl1/2007
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...........................
22-1 0-00
22-1 0-00
22-10-00
22-10-00
22-10-00
22-1 0-00
22-1 0-00
22-10-00
22-10-00
22-1 0-00
22-1 0-00
22-1 0-00
22-10-00
Page 201
Page 201
Page 201
Page 201
Page 201
Page 207
Page 207
Page 208
Page 209
Page 209
Page 21 0
Page 21 0
Page 211
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.......................
22-11 -00
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22 - CONTENTS
© Cessna Aircraft Company
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201
201
201
201
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Jul 1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti182
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.
0 Cessna Aircraft Company
USE
22-00-00
Page 1
Janl1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti182
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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CESSNA AIRCRAFT COMPANY
MODEL 182/Ti82
MAINTENANCE MANUAL
DETAIL
A
AUTOPILOT CONTROLLER
DETAIL
0710T1001
AO718T1002
B0718T1X01
B
KAP-140 Autopilot Installation
Figure 201 (Sheet 1)
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CESSNA AIRCRAFT COMPANY
MODEL 182/Ti 82
MAINTENANCE MANUAL
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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CESSNA AIRCRAFT COMPANY
MODEL 1821T182
MAINTENANCE MANUAL
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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Page 204
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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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MODEL 182/Ti182
MAINTENANCE MANUAL
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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MAINTENANCE MANUAL
(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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MODEL 182/Ti 82
MAINTENANCE MANUAL
(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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CESSNA AIRCRAFT COMPANY
MODEL 182/Ti 82
MAINTENANCE MANUAL
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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MAINTENANCE MANUAL
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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MODEL 182/Ti 82
MAINTENANCE MANUAL
(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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MAINTENANCE MANUAL
(6) Connect the airplane roll servo harness connector to the servo connector.
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MAINTENANCE MANUAL
AUTOPILOT
-
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)
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MODEL 182/Ti 82
MAINTENANCE MANUAL
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
©Cessna Aircraft Company
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CESSNA AIRCRAFT COMPANY
MODEL 1821T182
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)
22-11-00
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0
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MAINTENANCE MANUAL
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
22-1 1-00
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MAINTENANCE MANUAL
(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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MAINTENANCE MANUAL
(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
Page 207
Janl1/2007
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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23 - CONTENTS
Page 1 of 1
Janl1/2007
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
© Cessna Aircraft Company
Page 1
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti182
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.
23-1 0-00
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MAINTENANCE MANUAL
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)
23-10-00
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CESSNA AIRCRAFT COMPANY
MODEL 182/Ti182
MAINTENANCE MANUAL
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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Page 203
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MODEL 182/Ti182
MAINTENANCE MANUAL
(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.
23-1 0-00
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MODEL 182/Ti 82
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
23-1 0-00
Page 205
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CESSNA AIRCRAFT COMPANY
MODEL 182/1182
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
©Cessna Aircraft Company
Page 206
Janl1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti182
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
© Cessna Aircraft Company
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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)
23-1 0-00
©Cessna Aircraft Company
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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
GMA 1347
AUDIO PANEL
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00F[
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DETAIL
C
D
A0718T1053A
C0518T1041
D0718T1053A
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
;AL
IER
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DING
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SCREW
DETAIL
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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
24-30-00
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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MICRO-V-BELT
TER
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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.
24-30-00
© Cessna Aircraft Company
Page 101
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)
24-30-00
O Cessna Aircraft Company
Page 102
April 1/2002
CESSNA AIRCRAFT COMPANY
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)
24-30-00
© Cessna Aircraft Company
Page 103
April 1/2002
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)
24-30-00
© Cessna Aircraft Company
Page 104
April 1/2002
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)
24-30-00
© Cessna Aircraft Company
Page 105
April 1/2002
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)
24-30-00
© Cessna Aircraft Company
Page 106
April 1/2002
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)
24-30-00
© Cessna Aircraft Company
Page 107
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.
24-30-00
© Cessna Aircraft Company
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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)
24-30-00
© Cessna Aircraft Company
Page 202
Aug 4/2003
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)
24-30-10
© Cessna Aircraft Company
Page 202
Jan 2/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
A
Am
B
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DETAIL
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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)
24-30-10
© Cessna Aircraft Company
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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.
24-30-10
© Cessna Aircraft Company
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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.
24-30-10
© Cessna Aircraft Company
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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.
24-60-00
© Cessna Aircraft Company
Page 101
Jan 2/2006
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)
24-60-00
© Cessna Aircraft Company
Page 102
Jan 2/2006
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)
24-60-00
© Cessna Aircraft Company
Page 103
Jan 2/2006
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)
24-60-00
0 Cessna Aircraft Company
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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.
24-60-00
Q Cessna Aircraft Company
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Jul 3/2006
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)
24-60-00
© Cessna Aircraft Company
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Jul 3/2006
CESSNA AIRCRAFT COMPANY
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)
24-60-00
© Cessna Aircraft Company
Page 203
Jul 3/2006
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)
24-60-00
Cessna Aircraft Company
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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.
24-60-01
© Cessna Aircraft Company
Page 201
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
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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MODEL 182/T182
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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MODEL 182/T182
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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MODEL 182/T182
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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MODEL 182/T182
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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MODEL 182/T182
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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MODEL 182/T182
MAINTENANCE MANUAL
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Circuit Breaker Panel Installation
Figure 201 (Sheet 1)
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
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AIRPLANES WITH GARMIN G1000
0710T1001
A0718T1053
B0718T1054
Circuit Breaker Panel Installation
Figure 202 (Sheet 1)
24-61-00
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CESSNA AIRCRAFT COMPANY
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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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
OO
B
DETAIL
A
C
BUS BAR
DETAIL
B
NUT
ODE
LOCK WA
DETAIL
C
0710T1001
A0714T1041
B0718T1057
C0718T1058
Essential Bus Diode Installation
Figure 201 (Sheet 1)
24-61-01
© Cessna Aircraft Company
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CESSNA AIRCRAFT COMPANY
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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MODEL 182/T182
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.
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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
25-60-00
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.
25-11-00
© Cessna Aircraft Company
Page 201
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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)
25-11-00
© Cessna Aircraft Company
Page 202
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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)
25-11-00
© Cessna Aircraft Company
Page 203
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti182
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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Janl1/2007
CESSNA AIRCRAFT COMPANY
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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MAINTENANCE MANUAL
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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CESSNA AIRCRAFT COMPANY
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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Page 204
Janl1/2007
CESSNA AIRCRAFT COMPANY
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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©Cessna Aircraft Company
Page 205
Janl1/2007
CESSNA AIRCRAFT COMPANY
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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MODEL 182/Ti82
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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MODEL 1821T182
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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Janl1/2007
CESSNA AIRCRAFT COMPANY
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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© Cessna Aircraft Company
Page 201
Jul 3/2006
CESSNA AIRCRAFT COMPANY
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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© Cessna Aircraft Company
Page 202
Jul 3/2006
CESSNA AIRCRAFT COMPANY
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.
25-22-00
©Cessna Aircraft Company
Page 201
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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© Cessna Aircraft Company
Page 202
April 1/2002
CESSNA AIRCRAFT COMPANY
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
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April 1/2002
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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© Cessna Aircraft Company
Page 204
April 1/2002
CESSNA AIRCRAFT COMPANY
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)
25-22-00
© Cessna Aircraft Company
Page 205
April 1/2002
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.
25-50-00
©Cessna Aircraft Company
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April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1157
TIE-DOWN RING
05141010
Cargo Tie-Downs Installation
Figure 201 (Sheet 1)
25-50-00
© Cessna Aircraft Company
Page 202
April 1/2002
CESSNA AIRCRAFT COMPANY
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.
25-60-00
© Cessna Aircraft Company
Page 201
Janl1/2007
CESSNA AIRCRAFT COMPANY
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)
25-60-00
CCessna Aircraft Company
Page 202
Janl1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/T1182
MAINTENANCE MANUAL
B1 159
viEw A-A
MOUNTED SWITCH
DETAIL B
AA071 STI002
B0585T1 040
Pointer Emergency Locator Transmitter Installation
Figure 201 (Sheet 2)
©Cessna Aircraft Company
25-60-00
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Janl1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182ffT182
MAINTENANCE MANUAL
*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.
© Cessna Aircraft Company
25-60-02
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Janl1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti182
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.
25-60-02
© Cessna Aircraft Company
Page 201
Janl1/2007
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)
25-60-02
C Cessna Aircraft Company
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CESSNA AIRCRAFT COMPANY
MODEL 1821T182
MAINTENANCE MANUAL
B6583
B
LED
REMC
SWIT(
DETAIL
B
B3940T445
C0718T1 106
Artex ME406 Emergency Locator Transmitter System Installation
Figure 201 (Sheet 2)
25-60-02
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MODEL 182/Ti82
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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©Cessna Aircraft Company
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MODEL 182/Ti182
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.
© Cessna Aircraft Company
25-60-02
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Janl1/2007
CESSNA AIRCRAFT COMPANY
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.
© Cessna Aircratl Company
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CESSNA AIRCRAFT COMPANY
MODEL 182/Ti182
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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MODEL 182/Ti 82
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.
Q Cessna Aircratt Company
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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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Q Cessna Aircraft Company
Page 604
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MODEL 182/Ti 82
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)
25-60-02
©Cessna Aircraft Company
Page 605
Janl1/2007
CESSNA AIRCRAFT COMPANY
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)
25-60-02
©Cessna Aircraft Company
Page 606
Janl1/2007
CESSNA AIRCRAFT COMPANY
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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MODEL 182/Ti182
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)
25-60-1 0
©Cessna Aircraft Company
Page 202
Janl1/2007
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.
25-80-00
© Cessna Aircraft Company
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April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
SOUNDPROOFING
DETAIL A
0710T1001
A0719T2001
Soundproofing Installation
Figure 201 (Sheet 1)
25-80-00
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April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
DETAIL
A
0710T1001
A0719T3003
Insulation Installation
Figure 202 (Sheet 1)
25-80-00
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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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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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MODEL 182/T182
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).
26-20-00
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
FIRE
LOT SEAT
'MOUNTING BRACKET
DETAIL
B
0710T1001
A0514T1004
B0578T1001
Fire Extinguisher Installation
Figure 1 (Sheet 1)
26-20-00
© Cessna Aircraft Company
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CHAPTER
FLIGHT CONTROLS
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti 82
MAINTENANCE MANUAL
LIST OF EFFECTIVE PAGES
CHAPTER-SECTION-SUBJECT
PAGE
DATE
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April 1/2002
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April 1/2002
27-1 0-00
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Jul 3/2006
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April 1/2002
27-20-00
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Jul 3/2006
27-2 1-00
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April 1/2002
27-2 1-00
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April 1/2002
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April 1/2002
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Jul 3/2006
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April 1/2002
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27-Title
27-List of Effective Pages
27-Record of Temporary Revisions
27-Table of Contents
27
© 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
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CONTENTS
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FLIGHT CONTROLS - GENERAL .........................
General...................................
Tools, Equipment and Materials........................
Definition ..................................
Page
Page
Page
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...................................
27-10-00 Page 101
27-10-00 Page 101
RUDDER CONTROL SYSTEM - MAINTENANCE PRACTICES............
General...................................
Rudder Pedal Assembly Removal/Installation..................
Rudder Removal/installation .........................
Rudder Control Cables Removal/installation ..................
Rudder Control Adjustment/Test........................
27-20-00
27-20-00
27-20-00
27-20-00
27-20-00
27-20-00
RUDDER TRIM - TROUBLESHOOTING ......................
General...................................
RUDDER TRIM CONTROL SYSTEM - MAINTENANCE PRACTICES.........
General...................................
Rudder Trim System Removal/Installation ...................
Rudder Trim Adjustment/Test.........................
27-21 -00 Page 101
27-21-00 Page 101
ELEVATOR SYSTEM - TROUBLESHOOTING....................
General...................................
27-30-00 Page 101
27-30-00 Page 101
ELEVATOR CONTROL SYSTEM - MAINTENANCE PRACTICES...........
General ..................................
Forward Elevator Bell Crank Removal/Installation................
Aft Elevator Arm Assembly Removal/Installation ................
Elevator Control Adjustment/Test .......................
27-30-00
27-30-00
27-30-00
27-30-00
27-30-00
ELEVATOR TRIM CONTROL - TROUBLESHOOTING................
General...................................
27-31 -00 Page 101
27-31 -00 Page 101
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 .......................
27-31 -00
27-31 -00
27-31 -00
27-31 -00
27-3 1-00
27-31 -00
27-31 -00
27-31 -00
27-31 -00
27
© Cessna Aircraft Company
-
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CONTENTS
Page
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205
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Page 1 of 2
Jul 1/2007
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...........................
27-32-00
27-32-00
27-32-00
27-32-00
27-32-00
FLAP CONTROL SYSTEM - TROUBLESHOOTING.................
General...................................
27-50-00 Page 101
27-50-00 Page 101
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
27-50-00
27-50-00
27-50-00
27-50-00
27-50-00
Page
Page
Page
Page
Page
Page
201
201
201
201
206
207
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 .............
27-5 1-00
27-51 -00
27-5 1-00
27-51 -00
Page
Page
Page
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201
201
201
27 - CONTENTS
© Cessna Aircraft Company
Page
Page
Page
Page
Page
201
201
201
201
203
Page 2of 2
Jul 1/2007
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)
27-10-00
© 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)
27-10-00
© Cessna Aircraft Company
Page 204
Jul 3/2006
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)
27-10-00
© Cessna Aircraft Company
Page 205
Jul 3/2006
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.
27-10-00
© Cessna Aircraft Company
Page 206
Jul 3/2006
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.
27-10-00
© Cessna Aircraft Company
Page 207
Jul 3/2006
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.
27-10-00
© 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)
27-10-00
© Cessna Aircraft Company
Page 209
Jul 3/2006
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)
,
© Cessna Aircraft Company
27-10-00
Page 210
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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.
27-10-00
© Cessna Aircraft Company
Page 211
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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.
27-20-00
© Cessna Aircraft Company
Page 101
April 1/2002
CESSNA AIRCRAFT COMPANY
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)
27-20-00
© Cessna Aircraft Company
Page 102
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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)
27-20-00
© Cessna Aircraft Company
Page 103
April 1/2002
CESSNA AIRCRAFT COMPANY
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.
27-20-00
© Cessna Aircraft Company
Page 201
Jul 3/2006
CESSNA AIRCRAFT COMPANY
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)
27-20-00
© Cessna Aircraft Company
Page 202
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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)
27-20-00
© Cessna Aircraft Company
Page 203
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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)
27-20-00
© Cessna Aircraft Company
Page 204
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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.
27-20-00
©Cessna Aircraft Company
Page 205
Jul 3/2006
CESSNA AIRCRAFT COMPANY
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)
27-20-00
© Cessna Aircraft Company
Page 206
Jul 3/2006
CESSNA AIRCRAFT COMPANY
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)
27-20-00
© Cessna Aircraft Company
Page 207
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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.
27-20-00
© Cessna Aircraft Company
Page 208
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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.
27-21-00
© Cessna Aircraft Company
Page 101
April 1/2002
CESSNA AIRCRAFT COMPANY
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)
27-21-00
© Cessna Aircraft Company
Page 102
April 1/2002
CESSNA AIRCRAFT COMPANY
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.
27-21-00
© Cessna Aircraft Company
Page 201
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
C
DETAIL A
B
0710T1001
A0763T2004
Rudder Trim Control System Installation
Figure 201 (Sheet 1)
27-21-00
© Cessna Aircraft Company
Page 202
Jul 3/2006
CESSNA AIRCRAFT COMPANY
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)
27-21-00
© Cessna Aircraft Company
Page 203
Jul 3/2006
CESSNA AIRCRAFT COMPANY
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.
27-30-00
© Cessna Aircraft Company
Page 101
April 1/2002
CESSNA AIRCRAFT COMPANY
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)
27-30-00
© Cessna Aircraft Company
Page 102
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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)
27-30-00
© Cessna Aircraft Company
Page 103
April 1/2002
CESSNA AIRCRAFT COMPANY
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.
27-30-00
© Cessna Aircraft Company
Page 201
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)
27-30-00
©Cessna Aircraft Company
Page 202
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)
27-30-00
©D
Cessna Aircratt Company
Page 203
Jul 1/2007
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
27-30-00
©Cessna Aircraft Company
Page 204
Jul 1/2007
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)
27-30-00
©Cessna Aircraft Company
Page 205
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
Page 206
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.
27-30-00
© Cessna Aircraft Company
Page 207
Jul 1/2007
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.
27-31-00
© Cessna Aircraft Company
Page 101
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)
27-31-00
© Cessna Aircraft Company
Page 102
April 1/2002
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)
27-31-00
© Cessna Aircraft Company
Page 103
April 1/2002
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)
27-31-00
© Cessna Aircraft Company
Page 104
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.
27-31-00
© Cessna Aircraft Company
Page 201
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)
27-31-00
©Cessna Aircraft Company
Page 202
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)
27-31-00
© Cessna Aircraft Company
Page 203
Jul 3/2006
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
© Cessna Aircraft Company
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)
27-31-00
© Cessna Aircraft Company
Page 206
Jul 3/2006
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)
27-31-00
© Cessna Aircraft Company
Page 207
Jul 3/2006
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)
27-31-00
© Cessna Aircraft Company
Page 208
Jul 3/2006
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)
27-31-00
© Cessna Aircraft Company
Page 209
Jul 3/2006
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.
27-31-00
©Cessna Aircraft Company
Page 210
Jul 3/2006
CESSNA AIRCRAFT COMPANY
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.
27-31-00
© Cessna Aircraft Company
Page 211
Jul 3/2006
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)
27-31-00
Cessna Aircraft Company
Page 212
Jul 3/2006
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)
27-31-00
© Cessna Aircraft Company
Page 213
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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.
27-31-00
© Cessna Aircraft Company
Page 214
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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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© Cessna Aircraft Company
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April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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.
27-50-00
© Cessna Aircraft Company
Page 101
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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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CESSNA AIRCRAFT COMPANY
MODEL 182/Ti182
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
© Cessna Aircraft Company
27-50-00
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Jul 1/2007
CESSNA AIRCRAFT COMPANY
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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Jul 1/2007
CESSNA AIRCRAFT COMPANY
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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CESSNA AIRCRAFT COMPANY
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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CESSNA AIRCRAFT COMPANY
MODEL 182/7182
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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CESSNA AIRCRAFT COMPANY
MODEL 182/Ti182
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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MODEL 182/Ti 82
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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CESSNA AIRCRAFT COMPANY
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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CESSNA AIRCRAFT COMPANY
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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©Cessna Aircraft Company
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April 1/2002
CESSNA AIRCRAFT COMPANY
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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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
Page 1
April 1/2002
28-20-00
Pages 1-3
April 1/2002
CHAPTER-SECTION-SUBJECT
28-Title
28-List of Effective Pages
28-Record of Temporary Revisions
28-Table of Contents
28-20-00
28-20-00
Pages 201 -219
Jul 1/2007
Pages 501-506
Jul 1/2007
28-2 1-00
Pages 201-203
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 ..................................
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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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28 - CONTENTS
© Cessna Aircraft Company
Page
Page
Page
Page
Page
Page
Page
Page
Page
Page
201
201
201
201
201
201
Page 1 of 1
Jul 1/2007
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
© Cessna Aircraft Company
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)
28-20-00
© Cessna Aircraft Company
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.
28-20-00
Q Cessna Aircraft Company
Page 201
Jul 1/2007
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)
28-20-00
©Cessna Aircraft Company
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)
28-20-00
© Cessna Aircraft Company
Page 203
Jul 1/2007
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)
28-20-00
0 Cessna Aircraft Company
Page 204
Jul 1/2007
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
Page 205
Jul 1/2007
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
Page 206
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)
28-20-00
© Cessna Aircraft Company
Page 207
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.
28-20-00
© Cessna Aircraft Company
Page 208
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)
28-20-00
©Cessna Aircraft Company
Page 211
Jul 1/2007
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)
28-20-00
©Cessna Aircraft Company
Page 212
Jul 1/2007
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)
28-20-00
©Cessna Aircraft Company
Page 213
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.
© Cessna Aircraft Company
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MODEL 182/Ti 82
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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MODEL 182/Ti182
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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CESSNA AIRCRAFT COMPANY
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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CESSNA AIRCRAFT COMPANY
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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(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
© Cessna Aircraft Company
Page 505
Jul 1/2007
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.
28-20-00
© Cessna Aircraft Company
Page 506
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)
28-21-00
© Cessna Aircraft Company
Page 202
April 1/2002
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
© Cessna Aircraft Company
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 .......................
30-60-00
30-60-00
30-60-00
30-60-00
30-60-00
©Cessna Aircraft Company
30-00-00 Page 1
30-00-00 Page 1
30-00-00 Page 1
30-20-00 Page 201
30-20-00 Page 201
30-20-00 Page 201
30-60-00 Page 1
30-60-00 Page 1
30-60-00 Page 1
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
30-60-00
Page 107
Janl1/2007
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
30-60-00
Page 109
Janl1/2007
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
Page 202
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
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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
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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.
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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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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.
31-50-00
© Cessna Aircraft Company
Page 201
Jan 2/2006
CESSNA AIRCRAFT COMPANY
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.
31-50-00
© Cessna Aircraft Company
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Jan 2/2006
CESSNA AIRCRAFT COMPANY
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)
31-50-00
©Cessna Aircraft Company
Page 203
Jan 2/2006
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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April 1/2002
32-10-00
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Jul 3/2006
32-20-00
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April 1/2002
32-20-00
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Jul 3/2006
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Mar 1/2004
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Mar 1/2004
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April 1/2002
32-42-00
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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
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
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
32-00-00
© Cessna Aircraft Company
Page 1
Aug 4/2003
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.
32-10-00
© Cessna Aircraft Company
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)
32-10-00
© Cessna Aircraft Company
Page 102
April 1/2002
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)
32-10-00
© Cessna Aircraft Company
Page 103
April 1/2002
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
© Cessna Aircraft Company
Page 201
Jul 3/2006
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
© Cessna Aircraft Company
Page 202
Jul 3/2006
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)
32-10-00
© Cessna Aircraft Company
Page 203
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
DETAIL
A
(182T AND T182T)
0710T1001
A0741T1016
Main Landing Gear Installation
Figure 201 (Sheet 3)
32-10-00
© Cessna Aircraft Company
Page 204
Jul 3/2006
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.
32-10-00
© Cessna Aircraft Company
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Jul 3/2006
CESSNA AIRCRAFT COMPANY
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.
32-10-00
© Cessna Aircraft Company
Page 206
Jul 3/2006
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)
32-10-00
Cessna Aircraft Company
Page 207
Jul 3/2006
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)
32-10-00
© Cessna Aircraft Company
Page 208
Jul 3/2006
CESSNA AIRCRAFT COMPANY
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'
32-10-00
© Cessna Aircraft Company
Page 209
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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.
32-10-00
© Cessna Aircraft Company
Page 210
Jul 3/2006
CESSNA AIRCRAFT COMPANY
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)
32-10-00
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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)
32-10-00
© Cessna Aircraft Company
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CESSNA AIRCRAFT COMPANY
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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©Cessna Aircraft Company
Page 101
April 1/2002
CESSNA AIRCRAFT COMPANY
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)
32-20-00
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April 1/2002
CESSNA AIRCRAFT COMPANY
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)
32-20-00
© Cessna Aircraft Company
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April 1/2002
CESSNA AIRCRAFT COMPANY
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)
32-20-00
© Cessna Aircraft Company
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April 1/2002
CESSNA AIRCRAFT COMPANY
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.
32-20-00
© Cessna Aircraft Company
Page 201
Jul 3/2006
CESSNA AIRCRAFT COMPANY
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)
32-20-00
© Cessna Aircraft Company
Page 202
Jul 3/2006
CESSNA AIRCRAFT COMPANY
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)
32-20-00
© Cessna Aircraft Company
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CESSNA AIRCRAFT COMPANY
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)
32-20-00
© Cessna Aircraft Company
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CESSNA AIRCRAFT COMPANY
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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CESSNA AIRCRAFT COMPANY
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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CESSNA AIRCRAFT COMPANY
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.
32-20-00
© Cessna Aircraft Company
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
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.
32-20-00
© Cessna Aircraft Company
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CESSNA AIRCRAFT COMPANY
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)
32-20-00
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Page 209
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CESSNA AIRCRAFT COMPANY
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 rudder trim chain idler sprocket on forward side of pedestal.
(6) Remove cable guard from steering bungee sprocket.
(7) Remove nut, washer, and bolt securing steering bungee to bell crank.
(8) Remove chain from steering bungee sprocket.
(9) Remove clamp securing boot to steering bungee.
(10) Remove nut, washer, and bolt securing bungee to nose gear steering torque arm and remove
bungee.
B.
Install Nose Gear Steering (Refer to Figure 204).
(1) Place steering bungee through boot on firewall.
(2) Connect steering bungee to nose gear steering torque arm with bolt, washer and nut.
(3) Place chain over steering bungee sprocket and connect steering bungee to bell crank with bolt,
do not install washer and nut at this time.
(4) Rig nose gear steering. Refer to Rigging Nose Wheel Steering.
(5) Install clamp on nose wheel steering bungee boot.
(6) Install cowling. Refer to Chapter 71, Cowling - Removal/Installation.
(7) Install carpet and shield assemblies.
(8) Install pedestal cover.
(9) Install pilots and copilots seats. Refer to Chapter 25, Front Seats - Maintenance Practices.
Rigging Nose Wheel Steering.
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
(1)
(2)
(3)
(4)
(5)
Nose Wheel Steering. (Refer to Figure 204).
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.
(6) Rotate sprocket in or out as required to align rod end with attaching hole in bell crank and install
bolt, washer, and nut.
(7) Rotate rudder trim wheel until indicator is centered in pedestal slot (neutral).
(8) Without moving sprocket, engage chain on steering bungee sprocket, forward trim shaft sprocket
and idler sprocket.
(9) Adjust idler sprocket to allow approximately one-half inch deflection at chain midpoint and tighten
sprocket.
(10) Install cable guard over sprocket.
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
FORWARD TRIM
SHAFT SPROCKET
A
VIEW A-A
ARD
DETAIL
D
IDLER SPROCKET
DETAIL C
STEERING TORQUE ARM
FORWARD SIDE OF PEDESTAL
DETAIL
B
071 0T1 001
A07631005
B07631029
C07631031
D07631 030
A-A07421010
Nose Wheel Steering Installation
Figure 204 (Sheet 1)
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
(11) 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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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
MAIN LANDING GEAR WHEEL AND AXLE - MAINTENANCE PRACTICES
1.
General
A.
2.
Main landing gear wheel maintenance practices provide removal/installation instructions for left main
wheel. Removal/installation for right main wheel is typical unless otherwise noted.
Main Wheel Removal/Installation
NOTE:
3.
Wheel removal is not necessary to reline brakes or to remove brake parts, other than the brake
disc on the torque plate.
A.
Remove Main Wheel (Refer to Figure 201).
(1) Jack airplane. Refer to Chapter 7, Jacking - Maintenance Practices.
(2) Remove speed fairing or hub cap, if installed. Refer to Main Landing Gear - Maintenance
Practices.
(3) Remove cotter pin and axle nut.
(4) Remove bolts securing brake back plate to brake cylinder. Remove back plate.
(5) Pull wheel from axle.
B.
Install Main Wheel (Refer to Figure 201).
(1) Place wheel assembly on axle.
(2) Install axle nut and tighten axle nut until a slight bearing drag is obvious when the wheel is
rotated. Back off nut to nearest castellated and install cotter pin.
(3) Place brake back plate in position and secure with bolts.
(4) Install speed fairing or hub cap. Refer to Main Landing Gear - Maintenance Practices.
(5) Remove airplane from jacks. Refer to Chapter 7, Jacking - Maintenance Practices.
Main Wheel Axle Removal/Installation
A.
Remove Main Wheel Axle (Refer to Figure 201).
(1) Jack airplane. Refer to Chapter 7, Jacking - Maintenance Practices.
(2) Remove main wheel brake fairing, speed fairing, and cap fairing cover plate. Refer to Main
Landing Gear - Maintenance Practices.
(3) Remove main landing gear wheel. Refer to Main Wheel Removal/Installation.
(4) Disconnect, drain and cap or plug hydraulic brake line at the wheel brake cylinder.
NOTE:
(5)
B.
Remove nuts, washers, and bolts securing shims, axle, brake components, and speed fairing
mounting plate from strut fitting.
Install Main Wheel Axle (Refer to Figure 201).
NOTE:
(1)
(2)
(3)
(4)
(5)
(6)
4.
When removing axle from strut fitting, note number and position of wheel alignment
shims between axle and fitting. Mark shims or tape together carefully so they can be
installed in exactly the same position to ensure wheel alignment is not disturbed.
Ensure wheel alignment shims are installed in the same order and position as when
removed.
Secure shims, axle, brake components, and speed fairing mounting plate to strut fitting.
Install wheel on axle. Refer to Main Wheel Removal/Installation.
Connect hydraulic brake line to wheel brake cylinder.
Fill and bleed hydraulic brake system. Refer to Brake System - Maintenance Practices.
Install main wheel speed fairing. Refer to Main Landing Gear - Maintenance Practices.
Remove airplane from jacks. Refer to Chapter 7, Jacking - Maintenance Practices.
Main Wheel Disassembly/Assembly
A.
Disassemble Main Wheel (Refer to Figure 202).
32-40-00
© Cessna Aircraft Company
Page 201
Mar 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1284
SHIM
STRUT
FITTING
BACK
PLATE
11,
I
HUB
CAP
0741T1006
Main Landing Gear Wheel and Axle Installation
Figure 201 (Sheet 1)
32-40-00
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
WARNING: Serious injury can result from attempting to separate wheel
halves with tire and tube inflated.
(1) Completely deflate tire and tube and break loose tire bead. Extreme care must be exercised to
prevent tire tool damage when removing tire from wheel halves.
(2) Remove thru-bolts holding wheel halves together.
(3) Separate and remove wheel halves from tire and tube. Mark tube and tire relationship.
(4) From each wheel half, remove retaining rings, grease seal retainers, grease seal felts, grease
seal ring and bearing cones.
NOTE:
Bearing cups (races) are a press fit in wheel halves, and should not be removed
unless a new part is to be installed.
(5) To remove bearing cups, heat wheel half in boiling water for 30 minutes, or in an oven, not to
exceed 250F. Using an arbor press, if available, press out b earing cup and press in a new
bearing cup while wheel half is still hot.
B.
Assemble Main Wheel (Refer to Figure 202).
(1) Apply a small quantity of SAE 10 oil for lubrication on the felt grease seal.
(2) Install bearing cone, grease seal ring, grease seal felt, grease seal retainer and retaining ring
into each wheel half.
(3) Insert tube in tire, aligning index marks on tire and tube.
(4) Place wheel half into tire and tube (side opposite valve stem). With washer under head of thrubolt, insert bolt through wheel half.
(5) Place other wheel half into other side of tire and tube, aligning valve stem in valve slot.
(a) Ensure tube is not pinched between wheel halves before torquing nuts.
CAUTION: Uneven or improper torque of the nuts can cause failure of the
bolts with resultant wheel failure.
CAUTION: Do not use impact wrenches on thru-bolts or nuts.
(6) Insert washers and nuts on thru-bolts, and dry torque alternately to 90 inch-pounds, +2 or -2
inch-pounds.
(7) Inflate tire to seat tire beads, deflate and inflate to 42 PSI air pressure.
5.
Main Wheel Inspection/Check
A.
Inspect Main Wheel (Refer to Figure 202).
(1) Clean all metal parts and grease seal felts in solvent, and dry thoroughly.
NOTE:
(2)
(3)
(4)
(5)
(6)
(7)
(8)
(9)
(10)
(11)
(12)
(13)
A soft bristle brush may be used to remove hardened grease, dust or dirt.
Inspect wheel halves for cracks or damage.
Inspect bearing cones, cups, retaining rings, grease seal retainers, grease seal felts and grease
seal rings for wear or damage.
Inspect thru-bolts for cracks in bolt head.
Replace cracked or damaged wheel half.
Replace damaged retainer rings and seals.
Replace worn or damaged bearing cups and cones.
Replace any worn or damaged thru-bolts.
Remove any corrosion or small nicks.
Repair reworked areas of wheel by cleaning thoroughly, then applying one coat of clear lacquer
paint.
Apply a small quantity of SAE 10 oil for lubrication on the grease seal felt
Pack the bearings with MIL-PRF-81322 wheel bearing grease.
Inspect Brakes. Refer to Chapter 5, Inspection Time Limits.
32-40-00
© Cessna Aircraft Company
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1285
RETAINING
rIQFA QF
BEARING
CONE
WHEEL
HALF
TIRE
SEAL
RING
BEARING
GREASE
SEAL
RING
REASE
EAL
ILT
WHEEL
HALF
,
I
SEAL
RING
RETAINING
RING
ATE
BACK PLA1
BRAKI
DISK
THRU
BOLT
0741T1013
Main Wheel Assembly
Figure 202 (Sheet 1)
32-40-00
© Cessna Aircraft Company
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Mar 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
6.
Wheel Balancing
A.
Since uneven tire wear is usually the cause of wheel unbalance, replacing the tire will probably correct
this condition. Tire and tube manufacturing tolerance permits a specified amount of static unbalance.
The light weight point of this tire is marked with a red dot on the tire sidewall and the heavy weight
point of the tube is marked with a contrasting color line (usually near the inflation valve stem). When
installing a new tire, place these marks adjacent to each other. If a wheel shows evidence of unbalance
during service, it may be statically balanced but not dynamically balanced.
32-40-00
© Cessna Aircraft Company
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Mar 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
NOSE LANDING GEAR WHEEL - MAINTENANCE PRACTICES
1.
General
A.
2.
3.
Nose landing gear wheel maintenance practices consist of nose wheel removal/installation, nose
wheel disassembly/assembly and nose landing gear wheel inspection/check.
Nose Landing Gear Wheel Removal/Installation
A.
Remove Nose Landing Gear Wheel (Refer to Figure 201).
(1) Weight or tie down tail of airplane to raise nose wheel from floor.
(2) Remove nose wheel axle stud.
(3) Pull nose wheel assembly from fork and remove axle tube from nose wheel. Airplanes equipped
with speed fairing, loosen wheel scraper as necessary.
B.
Install Nose Landing Gear Wheel (Refer to Figure 201).
(1) Install axle tube in nose wheel.
(2) Install nose wheel assembly in fork and install nose wheel axle stud.
(3) Tighten axle stud until a slight bearing drag is obvious when wheel is rotated. Back the nut off
to the nearest castellation and insert cotter pins.
(4) Airplanes equipped with speed fairings, check scraper clearance. Refer to Nose Landing Gear
- Maintenance Practices.
Nose Landing Gear Wheel Disassembly/Assembly
A.
Disassemble Nose Landing Gear Wheel (Refer to Figure 201).
(1) Completely deflate tire and tube and break loose tire beads. Extreme care must be exercised
to prevent tire tool damage when removing tire from wheel halves.
WARNING: Serious injury can result from attempting to separate wheel
halves with tire and tube inflated.
(2) Remove thru-bolts and washers.
(3) Separate and remove wheel halves from tire and tube.
(4) Remove retaining rings, grease seal retainer, felt grease seal, grease seal retainer and bearing
cone from each wheel half.
NOTE:
Bearing cups are a press fit in wheel half and should not be removed unless a new
part is to be installed.
(5) To remove bearing cups, heat wheel half in boiling water for 30 minutes, or in an oven, not to
exceed 250'F (120@C). Using an arbor press, press out bearin g cup and press in new bearing
cup while wheel half is still hot.
B.
Assemble Nose Landing Gear Wheel (Refer to Figure 201).
(1) Assemble bearing cone, grease seal retainer, felt grease seal, grease seal retainer and retaining
ring into both wheel halves.
(a) Apply a small quantity of SAE 10 oil for lubrication on the grease seal felt.
(2) Insert tube in tire, aligning index marks on tire and tube.
(3) Place wheel half into tire and tube. With washer under head of thru bolt, insert bolt through
wheel half.
(4) Place wheel half into other side of tire and tube, aligning valve stem in valve slot.
(a) Ensure tube is not pinched between wheel halves before torquing nuts.
32-41-00
© Cessna Aircraft Company
Page 201
Mar 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
t!
NOTE:
THE SPEED FAIRING IS
REMOVED TO HELP
CLEARLY IDENTIFY
COMPONENTS.
C
TIRE AND WHEEL ASSEMBLY
K
TUD
B
DETAIL
A
0710T1001
A07421001
Nose Landing Gear Wheel Installation
Figure 201 (Sheet 1)
32-41-00
C Cessna Aircraft Company
Page 202
Mar 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1287
RETAINER RING
TIRE
WHEEL HALF
DETAIL
B
RETAINER RING
EED FAIRING
(182S)
B05421002
C07421008
PLUG BUTTON
Nose Landing Gear Wheel Installation
Figure 201 (Sheet 2)
32-41-00
© Cessna Aircraft Company
Page 203
Mar 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B2054
DETAIL
C
(182T AND T182T)
Nose Landing Gear Wheel Installation
Figure 201 (Sheet 3)
32-41-00
© Cessna Aircraft Company
Page 204
Mar 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
CAUTION: Uneven or improper torque of the nuts can cause failure of the
bolts with resultant wheel failure.
CAUTION: Do not use impact wrenches on thru-bolts or nuts.
(5) Insert washers and nuts on thru-bolts, and dry torque alternately to 90 inch-pounds, +2 or -2
inch-pounds (10.2 N.m., +0.2 or -0.2 N.m.).
(6) Inflate tire to seat tire beads, deflate and inflate to 49 PSI (338 kPa) air pressure.
4.
Nose Landing Gear Wheel Inspection/Check
A.
I
Inspect Nose Landing Gear Wheel (Refer to Figure 201).
(1) Clean all metal parts and felt grease seals in Stoddard solvent or equivalent, and dry thoroughly.
(2) Inspect wheel halves for cracks or damage.
(3) Inspect bearing cones, cups, retaining rings, and seals for wear or damage.
(4) Apply a small quantity of SAE 10 oil for lubrication on the grease seal felt.
(5) Inspect thru-bolts and nuts for cracks in threads or radius of bolt heads.
(6) Replace cracked or damaged wheel half.
(7) Replace damaged retaining rings and seals.
(8) Replace any worn or cracked thru-bolts or nuts.
(9) Replace worn or damaged bearing cups or cones.
(10) Remove any corrosion or small nicks.
(11) Repair reworked areas of wheel by cleaning thoroughly, then apply one coat of clear lacquer
paint.
32-41-00
© Cessna Aircraft Company
Page 205
Mar 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
BRAKE SYSTEM - TROUBLESHOOTING
1.
Troubleshooting
A.
A troubleshooting chart has been provided to aid the maintenance technician in system
troubleshooting. Refer to Figure 101.
32-42-00
©Cessna Aircraft Company
Page 101
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1288
BRAKES DRAGGING.
CHECK FOR DAMAGE OR ACCUMULATED
DIRT RESTRICTING FREE MOVEMENT OF
WHEELS BRAKES. IF-
I
OK, CHECK FOR BINDING BRAKE
PEDAL. IF-
NOT OK, CLEAN OR REPLACE
BRAKE PARTS AS REQUIRED.
OK, CHECK FOR WEAK OR BROKEN
MASTER CYLINDER PISTON RETURN
SPRING. IF-
NOT OK, LUBRICATE PIVOT
POINTS AND REPLACE OR
REPAIR DEFECTIVE PARTS.
OK, CHECK FOR IMPROPER
RIGGING OF PARKING
BRAKE CONTROL. IF-
NOT OK, REPAIR OR
RECYCLE MASTER
CYLINDER.
OK, CHECK FOR RESTRICTION IN
HYDRAULIC LINES. IF -
NOT OK, RIG
CORRECTLY.
OK, CHECK FOR WARPED OR
BADLY SCORED BRAKE DISC.
IF-
NOT OK, REMOVE RESTRICTIONS
AND FLUSH BRAKE SYSTEM WITH
HYDRAULIC FLUID.
I
NOT OK, REPLACE
DISC AND LININGS.
Brake System Troubleshooting Chart
Figure 101 (Sheet 1)
32-42-00
© Cessna Aircraft Company
Page 102
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1289
BRAKES FAIL TO OPERATE.
I
CHECK FOR LOW FLUID IN MASTER
CYLINDER RESERVOIR. IF -
I
OK, CHECK FOR SYSTEM
LEAK. IF-
NOT OK, FILL RESERVOIR
AND BLEED BRAKES.
OK, CHECK FOR AIR IN
SYSTEM. IF-
NOT OK, ISOLATE LEAK AND
REPLACE FAULTY PARTS.
OK, CHECK FOR WORN
BRAKE LININGS. IF-
NOT OK, BLEED
SYSTEM.
I
OK, CHECK FOR FAULTY O-RING IN
MASTER CYLINDER OR BRAKE
CYLINDER. IF-
NOT OK, REPLACE
LININGS.
OK, CHECK FOR INTERNAL DAMAGE TO
HOSES AND O-RING DUE TO USE OF
WRONG TYPE OF HYDRAULIC FLUID.
IF-
NOT OK, REPLACE
O-RING.
OK, CHECK FOR DEFECTIVE MASTER
CYLINDER(S) AND REPLACE AS REQUIRED.
NOT OK, REPLACE DAMAGED PARTS.
FLUSH SYSTEM WITH DENATURED
ALCOHOL. FILLAND BLEED BRAKE
SYSTEM.
Brake System Troubleshooting Chart
Figure 101 (Sheet 2)
32-42-00
© Cessna Aircraft Company
Page 103
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1290
BRAKE PEDAL
SPONGY.
PARKING BRAKE WILL
NOT HOLD.
CHECK FOR PROPER
FLUID LEVEL OR AIR
IN SYSTEM. IF-
CHECK PARKING BRAKE CONTROL
FOR IMPROPER RIGGING. IF -
I
OK, CHECK FOR
SWOLLEN HOSES.
REPLACE IF
DEFECTIVE AND
CHECK FOR
PROPER HYDRAULIC
FLUID IN SYSTEM.
NO OK, FILL
AND BLEED
SYSTEM.
OK, CHECK FOR
DEFECTIVE
PARKING BRAKE
SYSTEM. REPAIR
OR REPLACE
PARTS.
NOT OK, RIG
SYSTEM.
Brake System Troubleshooting Chart
Figure 101 (Sheet 3)
32-42-00
© Cessna Aircraft Company
Page 104
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
BRAKE SYSTEM - MAINTENANCE PRACTICES
1.
2.
|*
3.
General
A.
Brake system maintenance practices provide removal/installation and inspection/repair of the brake
master cylinders; removal/installation, inspection/repair, and rigging of the parking brake system.
B.
The hydraulic brake system is comprised of two master brake cylinders, located immediately forward
of the rudder pedals, brake lines connecting each master cylinder to its wheel brake cylinder, and the
single-disc, floating cylinder-type brake assembly, located at each main landing gear wheel.
C.
The brake master cylinders, located immediately forward of the pilot's rudder pedals, are actuated by
applying pressure at the top of the rudder pedals. A small reservoir is incorporated into each master
cylinder for the fluid supply. Mechanical linkage permits the copilot pedals to operate the master
cylinders.
D.
The wheel brake assemblies employ a floating brake assembly and a disc which is attached to the
main wheel.
E.
The brake lines are of rigid tubing, except for flexible hose used at the brake master cylinders. A
separate line is used to connect each brake master cylinder to its corresponding wheel brake cylinder.
F.
The parking brake system consists of a handle and ratchet mechanism, connected by a cable to
linkage at the brake master cylinders. Pulling out on the handle depresses both brake master cylinder
piston rods and the handle ratchet locks the handle in this position until the handle is turned and
released.
Brake Master Cylinders Removal/Installation
A.
Remove Brake Master Cylinders (Refer to Figure 201).
(1) Remove brake fairings for access to brake bleeder screws.
(2) Drain hydraulic fluid from brake master cylinders.
(3) Remove pilots seat. Refer to Chapter 25, Front Seats - Maintenance Practices.
(4) Remove shield assembly from pilots rudder pedals.
(5) Disconnect hoses from master cylinders and cap or plug hoses.
(6) Disconnect master cylinders at pilot rudder pedals.
(7) Remove cotter pins and pins securing lower end of brake master cylinders and remove brake
master cylinders.
B.
Install Brake Master Cylinders (Refer to Figure 201).
(1) Secure lower end of brake master cylinders using pins and new cotter pins.
(2) Secure upper end of brake master cylinders to rudder pedals. Use new cotter pins.
(3) Remove plugs or caps from hoses and connect hoses to brake master cylinders.
(4) Remove filler plug and fill brake master cylinders with MIL-PRF-5606 hydraulic fluid.
(5) Bleed brake system. Refer to Brake System Bleeding.
(6) Install brake fairings.
(7) Install shield assembly on pilots rudder pedals.
(8) Install pilots seat. Refer to Chapter 25, Front Seats - Maintenance Practices.
~
Brake Master Cylinder Disassembly/Assembly
A.
Disassemble Brake Master Cylinder (Refer to Figure 202).
(1) Remove brake master cylinder. Refer to Brake Master Cylinder Removal/Installation.
(2) Remove clevis and jamnut from piston rod.
(3) Remove filler plug.
NOTE:
(4)
(5)
(6)
A special tool, brake master cylinder wrench Proto Stanley Par No. C418 to remove
brake master cylinder cover.
Unscrew cover and remove up over piston rod.
Remove piston rod and spring.
Remove packing and backup ring from piston.
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Aug 4/2003
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
I
PARKING
BRAKE CABLES
E
MASTER
HOSE
COTTER
PIN
DETAIL A
HOSE
I
PIN
0710T1001
A0714T2001
Brake Master Cylinder Installation
Figure 201 (Sheet 1)
32-42-00
© Cessna Aircraft Company
Page 202
Aug 4/2003
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
81292
I
PISTON
BACK-UP R
CLEVIS
PACKING
FILLER
PLUG
Jr
'
A
A
SPRING
/ '0 0
|
RING
PACKING
SPRING
CYLINDER
BODY
N
I
Ilv
Iv
--- - --
FILLEF
PLUG
e"',
ba ?
VIEW A-A
NOTE:
FILLER PLUG MUST BE
VENTED SO PRESSURE
CANNOT BUILD UP
IN THE RESERVOIR
DURING BRAKE
OPERATION.
12171001
12171003
A-A12171002
Brake Master Cylinder Assembly
Figure 202 (Sheet 1)
32-42-00
© Cessna Aircraft Company
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B.
|
4.
Brake Master Cylinders Inspection/Repair
A.
5.
Check all parts for damage or wear. Repair is limited to replacement of worn or damaged parts.
Brake Lining Wear Check
A.
6.
Assemble Brake Master Cylinder (Refer to Figure 202).
(1) Apply lubrication to all interal parts with MIL-PRF-5606 hydraulic fluid.
(2) Install spring in cylinder body.
(3) Install backup ring and packing in groove of piston.
(4) Install piston in cylinder body.
(5) Install cover over piston and screw cover into cylinder body.
(6) Install jamnut and clevis on piston rod.
(7) Install filler plug making sure vent hole is open.
(8) Install brake master cylinder. Refer to Brake Master Cylinder Removal/Installation.
Check Brake Lining.
(1) A new brake lining should be installed when existing lining has worn to a thickness of 3/32-inch.
A 3/32-inch thick strip of material, held adjacent to each lining, can be used to determine amount
of wear. The shank end of a drill bit, of the correct size, can also be used to determine wear of
the brake linings.
Brake Lining Replacement
A.
Remove Brake Lining.
(1) Remove brake fairing and speed fairing. Refer to Main Landing Gear - Maintenance Practices.
(2) Remove bolts securing back plate and remove back plate.
(3) Pull brake cylinder out of torque plate and slide pressure plate off anchor bolts.
(4) Place back plate on a table with lining side down flat.
(5) Center a 9/64-inch (or slightly smaller) punch in the rolled rivet and hit the punch sharply with
a hammer. Punch out all rivets securing the linings to the back plate and pressure plate in the
same manner.
B.
Install Brake Lining.
NOTE:
A rivet setting kit is available from Cessna Aircraft Company.
(1) Clamp the flat side of the anvil in a vise.
(2) Align new lining on back plate and place brake rivet in hole with rivet head in the lining. Place
the head against the anvil.
(3) Center rivet setting punch on lips of rivet. While holding back plate down firmly against lining, hit
punch with a hammer to set the rivet. Repeat blows on punch until lining is firmly against back
plate.
(4) Realign the lining on the back plate and install rivets in the remaining holes.
(5) Install a new lining on pressure plate in the same manner.
(6) Position pressure plate on anchor bolts and place cylinder in position so that anchor bolts slide
into torque plate.
(7) Install back plate with bolts and washers. Torque bolts to 90-inch pounds.
(8) Install brake fairing and speed fairing. Refer to Main Landing Gear - Maintenance Practices.
(9) Perform brake lining burn-in. Refer to Brake Lining Burn-In.
7.
Brake System Bleeding
A.
Bleed Brake System.
(1) Remove brake master cylinder filler plug and screw flexible hose with appropriate fitting into filler
hole.
(2) Immerse opposite end of flexible hose into a container with enough hydraulic fluid to cover end
of hose.
(3) Connect a clean hydraulic pressure source, such as a hydraulic hand pump or Hydro-Fill unit to
the bleeder valve on the wheel brake cylinder.
32-42-00
© Cessna Aircraft Company
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MODEL 182/T182
MAINTENANCE MANUAL
(4)
(5)
8.
Brake Lining Conditioning
A.
9.
As fluid is pumped into the system, observe the immersed end of the hose from the master
brake cylinder for evidence of air bubbles being forced from the brake system. When bubbling
has ceased, remove bleeder source from wheel brake cylinder and tighten bleeder valve.
Remove hose from master cylinder and install filler plug.
Condition new brake linings.
(1) Taxi aircraft for 1500 feet with engine at 1700 rpm applying brake pedal force as needed to
develop a 5-10 mph taxi speed.
(2) Allow the brakes to cool for 10 to 15 minutes.
(3) Apply brakes and check for restraint at full throttle. If brakes hold, conditioning is complete.
(4) If brakes cannot hold aircraft during static run up, allow brakes to completely cool, and repeat
steps (1) through (3).
Parking Brake System
A.
Remove parking Brake System. (Refer to Figure 203).
(1) Remove pilots seat. Refer to Chapter 25, Front Seats - Maintenance Practices.
(2) Remove shield assembly from pilots rudder pedals.
(3) Disconnect spring from bell crank.
(4) Remove cotter pin from positioning pin and remove pin and cable from rod.
(5) Remove nut, bolt, and pulley from lower end of bell crank.
(6) Remove nuts from both ends of tube and remove tube and cable assembly.
(7) Remove cotter pins and disconnect park brake cable from rudder pedals.
(8) Remove nut, washer, and bolt and remove pulley and brake cable from upper end of bell crank.
B.
Install parking Brake System. (Refer to Figure 203).
(1) Connect brake cable to rudder pedals using new cotter pins.
(2) Position brake cable around upper pulley and install pulley, bolt, washer, and nut.
(3) Install tube and cable assembly upper end.
(4) Connect upper end of cable to rod using positioning pin and new cotter pin.
(5) Position cable around lower pulley and install pulley, bolt, and nut.
(6) Connect Cable and tube to bracket.
(7) Install spring.
(8) Ensure that cables are in grooves of pulleys and all cable guards are installed.
(9) Install shield assembly on pilots rudder pedals.
(10) Install pilots seat. Refer to Chapter 25, Front Seats - Maintenance Practices.
(11) Check parking brake operation.
32-42-00
© Cessna Aircraft Company
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Aug 4/2003
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
E
A
PARKING BRAKE
UPPER
PULLEY
LOCKING
SPRING
POSITIONING
PIN
DETAIL B
C,
LOWER PULLEY
DETAIL
A
0741T1009
A0514T3001
A0514T3003
B0741T1011
Parking Brake Installation
Figure 203 (Sheet 1)
32-42-00
© Cessna Aircraft Company
Page 206
Aug 4/2003
0
CHAPTER
LIGHTS
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
LIST OF EFFECTIVE PAGES
CHAPTER-SECTION-SUBJECT
PAGE
DATE
33-00-00
Page 1
April 1/2002
33-10-00
Pages 201-206
Jul 3/2006
33-11-00
Pages 201-204
April 1/2002
33-12-00
Pages 201-202
April 1/2002
33-13-00
Pages 201-204
Aug 4/2003
33-14-00
Pages 201-202
Aug 4/2003
33-15-00
Pages 201-202
April 1/2002
33-40-00
Pages 201-205
April 1/2002
33-41-00
Pages 201-203
Jan 2/2006
33-42-00
Pages 101-102
Jan 2/2006
33-42-00
Pages 201-205
Jan 2/2006
33-43-00
Pages 201-202
Aug 4/2003
33-Title
33-List of Effective Pages
33-Record of Temporary Revisions
33-Table of Contents
33 - LIST OF EFFECTIVE PAGES
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Jul 3/2006
RECORD OF TEMPORARY REVISIONS
Temporary Revision
Number
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Issue Date
By
Date Removed
By
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
CONTENTS
LIGHTING - GENERAL
............................
...........................
Scope......................................................................
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FLOOD LIGHTING - MAINTENANCE PRACTICES .................................
General ...................................................................
Floodlight Bulb Removal/Installation ..........................................
Light Assembly Removal/Installation ..........................................
Light Assembly Switch Removal/Installation .. ...............................
Potentiometer Removal/Installation ...........................................
Oxygen Panel Light Bulb Removal/Installation (Airplanes with Garmin G1000)....
Oxygen Panel Light Assembly Removal/Installation (Airplanes with Garmin
G1000) .................................. ................................
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GLARESHIELD LIGHTING - MAINTENANCE PRACTICES .........................
General ....................................................................
Glareshield Lamp Removal/Installation (182S) .................................
Glareshield Light Removal/Installation (T182 and T182T) .......................
Lighting Inverter Removal/Installation .........................................
Glareshield Lighting and Dimming Control Removal/Installation .................
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PEDESTAL LIGHTING - MAINTENANCE PRACTICES..............................
General ......................................... .. ....... ..................
Pedestal Light Lamp Replacement............................................
Pedestal Lighting Dimming Control Removal and Installation....................
INSTRUMENT LIGHTING - MAINTENANCE PRACTICES...........................
General ....................................................................
Description and Operation ...................................................
Flight Instrument Light Bar Replacement ......................................
Engine Instrument Light Bulb Replacement....................................
Dimming Assembly Removal and Installation ..................................
Instrument Lighting Dimming Control Removal and Installation ..................
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RADIO LIGHTING - MAINTENANCE PRACTICES..................................
General ....................................................................
Description and Operation ...................................................
Dimming Assembly Removal and Installation ..................................
Radio Lighting Dimming Control Removal and Installation ......................
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PILOT CONTROL WHEEL LIGHTING - MAINTENANCE PRACTICES................
General ...................................................................
Map Light Assembly Removal and Installation .................................
Map Light Potentiometer Removal and Installation .............................
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NAVIGATION AND STROBE LIGHTS - MAINTENANCE PRACTICES ................
General ....................................................................
Navigation Light Lamp Removal and Installation ...............................
Strobe Tube Assembly Removal and Installation ...............................
Strobe Power Supply Removal and Installation ................................
VERTICAL FIN FLASHING BEACON - MAINTENANCE PRACTICES ................
General ....................................................................
Flashing Beacon Lamp Removal/Installation...................................
Flashing Beacon Light Assembly Removal/Installation ........................
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LANDING/TAXI LIGHTS - TROUBLESHOOTING .........
..........................
High-Intensity Discharge (HID) Landing and Taxi Lights Troubleshooting .........
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CONTENTS
Page 1 of 2
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
LANDING/TAXI LIGHTS - MAINTENANCE PRACTICES ............................
Gen eral ....................................................................
Troubleshooting .............................................................
.............................
Light Adjustm ent ............................
Light Removal/Installation................................................
High-Intensity Discharge (HID) Ballast Removal/Installation ....................
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COURTESY LIGHTS - MAINTENANCE PRACTICES ...............................
General ....................................................................
Courtesy Light Lamp Removal and Installation.................................
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CONTENTS
© Cessna Aircraft Company
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
LIGHTING - GENERAL
1.
Scope
A.
This chapter describes those units and components which provide for external and internal illumination
such as landing lights, taxi lights, position lights, dome lights, etc. This chapter does not include
warning lights for individual systems or self-illuminating signs.
B.
It is intended to use the information in this chapter in conjunction with wiring diagrams to provide data
required to maintain the lighting systems that illuminate the interior and exterior of the airplane. An
understanding of the function of the components, electrical circuits, electrical wiring, and switches is
necessary to perform effective troubleshooting beyond lamp replacement. See the Model 182 Wiring
Diagram Manual for electrical diagrams of specific systems.
C.
This chapter is divided into sections to aid maintenance personnel to find information. The sections
provide maintenance procedures for individual exterior and interior lighting systems of the airplane.
(1) Exterior lighting.
(a) Flashing beacon light assembly located on the vertical fin tip assembly.
(b) Tail navigation light.
(c) Underwing courtesy lights.
(d) Wing tip strobe lights.
(e) Landing and taxi lights located on the left wing.
(f) Left (red) and right (green) navigation lights.
(2) Interior lighting.
(a) Dome lights provide cabin flood lighting.
(b) Map light is located on the pilot control wheel.
(c) Pedestal (console) lighting is provided by an upper, and lower pedestal light.
(d) Instrument and a glareshield lights provide lighting for flight instruments. Control of light
brightness is provided through dimming circuitry.
(e) A center light is included in the 182T and T182T models.
© Cessna Aircraft Company
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
FLOOD LIGHTING - MAINTENANCE PRACTICES
1.
General
A.
Cabin floodlights are mounted in the aft and the forward parts of the overhead console. Each floodlight
has a switch. The forward and the aft lights are reading lights. On airplanes with Garmin G1000 that
are equipped with oxygen, there is a light mounted on the oxygen panel. Dimming of the oxygen panel
light is controlled by the STBY IND dimmer switch located on the switch panel on the pilot instrument
panel.
WARNING: Obey all oxygen safety precautions on airplanes that have the
oxygen panel installed in the overhead console. Refer to the oxygen
maintenance practices for correct procedures to use when you must
do maintenance on or near to the oxygen lines.
2.
Floodlight Bulb Removal/Installation
CAUTION: Be careful when you remove and install the floodlight bulb. The floodlight
bulb can break if too much pressure is applied when you remove and install
it.
NOTE:
A.
Removal/Installation is typical for all floodlight bulbs.
Floodlight Bulb Removal (Refer to Figure 201).
(1) Press the lens holder up and turn it counterclockwise.
(2) Remove the lens holder.
(3) Carefully push the bulb up and turn it counterclockwise.
(4) Remove the bulb.
B.
3.
Floodlight Bulb Installation (Refer to Figure 201).
(1) Put the bulb in position.
(2) Carefully push the bulb up and turn it clockwise.
(3) Put the lens in position.
(4) Push the lens holder up and turn it clockwise.
Light Assembly Removal/Installation
NOTE:
A.
Removal/installation is typical for the overhead dome light assemblies.
Light Assembly Removal (Refer to Figure 201).
(1) Put the ALT/BAT MASTER switch in the off position.
CAUTION: Support the overhead console when you remove the screws to
prevent damage to the electrical wiring in the overhead console.
B.
(2) Remove the screws that attach the overhead console to the attach brackets.
(3) Identify, tag, and disconnect the electrical wires from the light assembly.
(4) Remove the light assembly from the overhead console.
Light Assembly Installation (Refer to Figure 201).
(1) Put the light assembly in position.
(2) Attach the light assembly to the overhead console.
(3)
(4)
(5)
Connect the electrical wires to the light assembly.
Attach the overhead console to the attach brackets with the screws.
Put the ALT/BAT MASTER switch in the ON position.
33-10-00
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
LIGHT
BULB
LENS
HOLDER
DETAIL B
ATTACH BRACKET
B
DETAIL A
CONSOLE
0710T
182S AIRPLANES
A0519T105
B0519T1059
Floodlight Installation
Figure 201 (Sheet 1)
33-10-00
© Cessna Aircraft Company
Page 202
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B4199
LEI
HOLDER
DETAIL B
ATTACH
BRACKET
DOME LIGH
ASSEMBLY
OVERHEAD
B
SWITCH
SWITCH
LIGHT ASSEMBLY
DETAIL A
182T AND T182T AIRPLANES WITHOUT GARMIN G1000
Floodlight Installation
Figure 201 (Sheet 2)
33-10-00
© Cessna Aircraft Company
0710T1001
A0719T1025A
Page 203
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
BULB
LENS
HOLDER
POTENTIOMETER
~
POTENTIOMETER
B
B
JA
LIGHT
ASSEMBLY
LIGHT
LIGH I
DETAIL A
AIRPLANES WITH GARMIN G1000
FILTER
0710T1001
CAP
A0719T1054
B0519T1105
DETAIL DD
DETAIL
C2618T1153
D0719T1055
Floodlight Installation
Figure 201 (Sheet 3)
33-10-00
© Cessna Aircraft Company
Page 204
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
4.
Light Assembly Switch Removal/Installation
A.
Light Assembly Switch Removal (Refer to Figure 201).
(1) Put the ALT/BAT MASTER switch in the off position.
CAUTION: Support the overhead console when you remove the screws to
prevent damage to the electrical wiring in the overhead console.
(2) Remove the overhead console from the attach brackets.
(3) Identify, tag, and disconnect the wires from the switch.
(4) Remove the switch from the overhead console.
B.
5.
Light Assembly Switch Installation (Refer to Figure 201).
(1) Install the switch in the overhead console.
(2) Connect the electrical wires to the switch.
(3) Attach the overhead console to the attach brackets with the screws.
(4) Put the ALT/BAT MASTER switch in the ON position.
Potentiometer Removal/Installation
A.
Potentiometer Removal (Refer to Figure 201).
(1) Put the ALT/BAT MASTER switch in the off position.
CAUTION: Support the overhead console when you remove the screws to
prevent damage to the electrical wiring in the overhead console.
(2)
(3)
(4)
(5)
B.
6.
Remove the
Identify, tag,
Remove the
Remove the
overhead console from the attach brackets.
and disconnect the wires from the switch.
knob assembly and the jam nut from the potentiometer.
potentiometer from the overhead console.
Potentiometer Installation (Refer to Figure 201).
(1) Install the jam nut and the knob assembly.
(2) Connect the electrical wires to the potentiometer.
(3) Attach the overhead console to the attach brackets with the screws.
(4) Put the ALT/BAT MASTER switch in the ON position.
Oxygen Panel Light Bulb Removal/Installation (Airplanes with Garmin G1000)
CAUTION: Be careful when you remove and install the oxygen panel light bulb. The
oxygen panel light bulb can break if too much pressure is applied when
you remove and install it.
7.
A.
Oxygen Panel Light Bulb Removal (Refer to Figure 201).
(1) Put the ALT/BAT MASTER switch in the off position.
(2) Remove the oxygen panel light assembly.
(3) Carefully turn the bulb counterclockwise.
(4) Remove the bulb from the light assembly.
B.
Oxygen Panel Light Bulb Installation (Refer to Figure 201).
(1) Put the bulb in position.
(2) Carefully turn the bulb clockwise.
(3) Install the oxygen panel light assembly.
(4) Put the ALT/BAT MASTER switch in the ON position.
Oxygen Panel Light Assembly Removal/Installation (Airplanes with Garmin G1000)
A.
Oxygen Panel Light Assembly Removal (Refer to Figure 201).
(1) Put the ALT/BAT MASTER switch in the off position.
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Page 205
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B.
(2) Turn the cap on the oxygen panel light assembly counterclockwise.
(3) Remove the cap, washer, and light assembly from the oxygen panel.
Oxygen Panel Light Assembly Installation (Refer to Figure 201.)
(1) Put the washer and light assembly in position on the oxygen panel.
(2) Put the cap in position on the light assembly.
(3) Turn the cap clockwise to tighten.
(4) Put the ALT/BAT MASTER switch in the ON position.
33-10-00
© Cessna Aircraft Company
Page 206
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
GLARESHIELD LIGHTING - MAINTENANCE PRACTICES
1.
General
A.
2.
The glareshield light provides overall lighting for the instrument panel and is located under the
glareshield. Model 182S aircraft have a single neon tube light and is powered by a variable AC
current lighting inverter. The inverter is located behind the copilot instrument panel assembly. Model
182T and T182T aircraft have a light strip with multiple Light Emitting Diodes (LED) which are
powered by variable DC current. A glareshield lighting dimming control is mounted on the right side
of the circuit panel assembly.
Glareshield Lamp Removal/Installation (182S)
A.
Remove Glareshield Lamp (Refer to Figure 201).
(1) Remove electrical power from airplane and turn off the ALT/BAT Master Switch.
(2) Remove screws securing copilot instrument panel assembly to bulkhead to gain access to
glareshield light connector. Refer to Chapter 31, Instrument and Control Panels - Maintenance
Practices.
NOTE:
(3)
(4)
Disconnect glareshield light connector.
Remove screws securing lens to glareshield assembly.
NOTE:
(5)
B.
Velcro strips are located on the edge of the lens to prevent light leakage around lens.
Remove lamp from light clips.
Install Glareshield Lamp (Refer to Figure 201).
(1) Position lamp at glareshield assembly with electrical wire and connector toward the right side of
the airplane. Secure lamp in light clips.
(2) Secure glareshield light lens to glareshield assembly with screws.
NOTE:
(3)
(4)
(5)
Apply Velcro strips to the edge of the lens as required to prevent light leakage around
lens.
Connect glareshield light connector.
Secure copilot instrument panel assembly to bulkhead with screws.
Instrument and Control Panels - Maintenance Practices.
NOTE:
3.
Note location of two spacers installed between the panel and bulkhead for installation
of copilot instrument panel assembly.
Refer to Chapter 31,
Two spacers are installed between the panel and bulkhead using the two screws
securing the right side of the panel.
Restore electrical power to airplane as required and turn on the ALT/BAT Master Switch.
Glareshield Light Removal/Installation (T182 and T182T)
A.
Remove Glareshield Light Strip (Refer to Figure 202).
(1) Remove electrical power from airplane and turn off the ALT/BAT Master Switch.
(2) Remove screws securing the left and right glareshield light enclosure plates and remove
enclosure plate.
CAUTION: LED light strip is fragile when not supported in glareshield.
Overbending of strip could cause failure of strip.
(3)
(4)
Remove screws securing light strip and gently remove light strip.
Disconnect glareshield light connector.
33-11-00
© Cessna Aircraft Company
Page 201
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
tj
n
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.
I
0
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0____Io
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VIEW A-A
0710T1001
A3930T368
Forward Avionics Equipment Installation
Figure 201 (Sheet 1)
34-13-00
© Cessna Aircraft Company
Page 202
Mar 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
ATTITUDE AND DIRECTION - DESCRIPTION AND OPERATION
1.
General
A.
Attitude and direction navigation systems are systems which use magnetic or gyroscopic forces to
sense and display the direction or attitude of the airplane. This includes the magnetic compass,
horizon gyro, directional gyro, and turn coordinator (roll rate gyro) indicator.
B.
The magnetic compass is located on the airplane centerline of the upper forward windshield. The
compass is independent of other navigation systems and does not supply information to other airplane
systems.
C.
The three gyroscopic instruments that indicate attitude and direction are mounted in the center pilot
panel assembly. The directional gyro and turn coordinator provide information to the autopilot system.
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© Cessna Aircraft Company
Page 1
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
ATTITUDE AND DIRECTION - MAINTENANCE PRACTICES
1.
2.
3.
General
A.
This section gives maintenance information, removal and installation procedures, and operational
checks for the horizon attitude gyro, directional gyro, and turn coordinator.
B.
On airplanes without Garmin G1000, three gyroscopic instruments show the attitude and direction of
the airplane. The instruments are found in the center pilot panel. These instruments are the horizon
attitude gyro, directional gyro, and turn coordinator.
C.
On airplanes with Garmin G1000, two gyroscopic instruments give attitude and direction. The horizon
gyro is in the center instrument panel. The horizon gyro gives attitude and direction and is the middle
standby instrument. The turn coordinator gives roll rate data to the autopilot and is installed on the
left side of the center instrument panel. The turn coordinator cannot be seen in the cockpit.
Operation Notes
A.
The vacuum system supplies airflow necessary to move the gyro rotor in the horizon gyro. Incorrect
operation of the vacuum system will cause the horizon gyro to operate incorrectly.
B.
It is necessary for the horizon gyro to have 4.5 to 5.5 in.hg. of vacuum to operate correctly. The gyro
will reach rated performance with correct vacuum applied in a minimum of 3 minutes of rotor spin time.
C.
The gyro rotor can continue to spin for approximately 15 minutes after vacuum in the system is
removed. It can show a change in the roll and/or pitch indication while the rotor speed decreases.
The gyro rotor will remain in a roll and/or pitch indication when stopped until the system starts again.
D.
If a gyro has been shut down and started again before the rotor has been permitted to stop, more time
will be necessary to get the correct pitch and roll indication.
Precautions
A.
Gyroscopic instruments are very sensitive. They have precision bearings on the gyroscope rotor,
pivots, and yoke shaft. Be careful when you move or touch the instrument when it is out of the airplane.
If you are not careful when you move or touch the instrument, you can cause damage to the bearings.
Dirt and other contaminants can also cause damage to the bearings. Obey these special precautions
when you move, install, remove, or ship any gyroscopic instruments.
(1) To prevent damage to the gyro, do not move a gyro after the electrical power or vacuum
pressure is removed and before the gyro rotor has stopped. The gyro rotor will not fully stop for
approximately 15 minutes after the electrical power or vacuum pressure is removed.
(2) During the removal of instruments, put soft material between the instruments and the control
column.
(3) Do not shake or cause vibration of the panel or the instruments.
(4) Do not hit the gyroscope against any other object. Do not shake the gyroscope or put the
gyroscope on a hard surface. If you are not careful, you can cause damage to the instrument.
CAUTION: Always be very careful when you move or hold gyroscopic
instruments, because you can easily cause damage.
(5)
(6)
(7)
(8)
(9)
Do not remove any wires, labels, tie straps, or any other parts of the gyro that are installed by
the manufacturer.
Visually examine the gyro for any external damage. There must be no scratches, dents, or dings
on any part of the gyro. Do not install gyros that have scratches, dents, or dings.
If you must ship a gyroscopic instrument, make sure that all the female ports have plugs that
you can remove, and that all the male receptacles have plastic caps that you can remove.
Put connector caps on all the electrical pin connectors to make sure that they are not bent or
broken.
Put all gyros in Styrofoam or other soft material for storage and transportation. If possible, ship
the gyroscope in the box from the manufacturer in which it was received.
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© Cessna Aircraft Company
Page 201
Jan 2/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
(10) Keep the plugs in the ports unless the instrument is installed in an aircraft or maintenance
personnel are doing a test.
4.
Prepare the Gyroscopic Instruments for Shipping
A.
All gyros that are shipped must obey the instructions that follow.
(1) All ports and vents must have plugs installed in them.
(2) All initial seals from the manufacturer must be installed and not damaged.
(3) All gyros must be carefully put in the same type of container in which the replacement gyro was
received.
(4) Put connector caps or adhesive tape on all electrical pin connectors to make sure that they are
not bent or broken.
5.
Horizon Attitude Gyro Description and Operation
A. The vacuum system supplies the air flow necessary to move the gyro rotor in the horizon attitude gyro.
Incorrect operation of the vacuum system will cause the horizon attitude gyro to operate incorrectly.
Problems with the vacuum system can cause incorrect indication and decreased performance.
B. The horizon attitude gyro must have between 4.5 and 5.5 in.hg. of vacuum to operate correctly. With
the correct vacuum applied, the gyro will get rated performance in a minimum of 3 minutes of rotor
turn time.
C. The horizon attitude gyro rotor can continue to turn for approximately 15 minutes after the vacuum in
the system is removed. It can show a change in the roll and/or pitch indication while the rotor speed
decreases. When fully stopped, the gyro rotor will stay in a roll and/or pitch indication until the system
starts again.
D. If a gyro has been stopped and started again before the rotor fully stops, more time will be necessary
for the gyro to correctly indicate the pitch and roll of the airplane.
6.
Horizon Attitude Gyro Removal/Installation
A. Horizon Attitude Gyro Removal (Refer to Figure 201 or Figure 202).
CAUTION: Make sure that the gyro rotor has fully stopped before you move the
instrument. The gyro rotor will not stop for approximately 15 minutes
after the electrical power or vacuum source is removed. Damage to the
instrument will occur if the instrument is moved before the gyro rotor has
stopped.
CAUTION: Be careful with the gyroscopic instruments. Do not hit, shake, or put the
instruments on a hard surface. Put soft material between the gyroscopic
instruments and any hard surface. Damage to the instruments will occur
if the instruments are not carefully moved. The manufacturer's warranty
can become void if the gyro is not kept in its initial condition as received
from the manufacturer.
(1) Put the MASTER switch and the AVIONICS switch in the off position.
(2) Remove the screws from the center pilot panel to get access to the back of the horizon attitude
gyro.
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CESSNA AIRCRAFT COMPANY
MODEL 182/r182
MAINTENANCE MANUAL
Rl11t
D
CENTER PILOT PANEL
HORIZON ATTITUDE GYRO
I
/
GLAR
SCREW
DIRECTIONAL C
TURN COORDINA1
IO12
VIEW A-A
AIRPLANES WITHOUT GARMIN G1000
0710T1001
AA0718R1038
Attitude and Direction Instrument Installation (Airplanes without Garmin G1000)
Figure 201 (Sheet 1)
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© Cessna Aircraft Company
Page 203
Jan 2/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1309
CENTER PILOT PANEL
HORIZON ATTITUDE GYRO
\
ELBOW
COORDINATOR
CLAMP
HOSE
DIRECTIONAL GYRO
J
ELECTRICAL
CONNECTOR
(J1008)
A
DETAIL
AIRPLANES WITHOUT GARMIN G1000
B0714T1033
Attitude and Direction Instrument Installation (Airplanes without Garmin G1000)
Figure 201 (Sheet 2)
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Page 204
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MODEL 182/T182
MAINTENANCE MANUAL
ADA
U
A
A
VIEW A-A
ALTIMETER
VACL
TRAN
HORIZON
ATTITUDE
GYRO
F
AIRSPEED
INDICATOR
REGULATOR
VALVE
FILTER
CLAMF
GYRO
FILTER
DETAIL A
AIRPLANES WITH GARMIN G1000
0710T1001
A1218T1001A
B0718T10 66
Attitude and Direction Instrument (Airplanes with Garmin G1000)
Figure 202 (Sheet 1)
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
CAUTION: Make sure that you put soft material between the horizon attitude
gyro and the control column before you remove the gyro. If you
put the sub panel on the control column without any protection, you
can damage the horizon attitude gyro and/or the other instruments
in the sub panel. Be very careful when you remove the sub panel
so that you do not hit the gyro.
(3)
(4)
(5)
(6)
(7)
Put a label on the air inlet hose, vacuum outlet hose, and gage hose that are attached to the
horizon attitude gyro.
Loosen the clamps and remove the hoses from the horizon attitude gyro.
Disconnect the electrical connectors from the horizon attitude gyro.
Put female plugs over the ports and put a connector cap on the electrical connector.
Remove the screws that attach the horizon attitude gyro to the center pilot panel.
CAUTION: Put a cover on the applicable hose or port, or on the applicable
electrical connector when the gyroscopic instrument is out of the
airplane or is to be shipped. Damage to the instrument will occur
from contamination if a cover is not used.
(8)
B.
Remove the horizon attitude gyro from the airplane.
Horizon Attitude Gyro Installation (Refer to Figure 201 or Figure 202).
CAUTION: Do not remove the horizon attitude gyro from the box in which it was
shipped until it is ready to be installed into the airplane. This will minimize
the possibility of accidentally causing damage to the gyro.
CAUTION: Remove all plugs from the horizon attitude gyro before you install it in
the aircraft.
CAUTION: Be careful with the gyroscopic instruments. Do not hit, shake, or put the
instruments on a hard surface. Put soft material between the gyroscopic
instruments and any hard surface. Damage to the instruments will occur
if the instruments are not carefully moved. The manufacturer's warranty
can become void if the gyro is not kept in its initial condition as received
from the manufacturer.
(1) Attach the horizon attitude gyro to the center pilot panel with the screws.
Make sure that the horizon altitude gyro is installed level in the panel.
Remove the female plugs from the ports and remove the connector cap from the electrical
connector.
(4) Make sure that the vacuum lines and the static lines have no kinks in them.
(5) Attach the air inlet hose, vacuum outlet hose, and gage hose to the horizon attitude gyro and
tighten the clamps.
(6) Attach the horizon attitude gyro connector to the horizon attitude gyro.
(7) Attach the center pilot panel with the screws.
(8) Tighten the screws in an opposite sequence.
(9) Put the MASTER switch and the AVIONICS switch in the ON position.
(10) Do an operational check of the horizon attitude gyro to make sure that it operates correctly.
(2)
(3)
7.
Horizon Attitude Gyro Operational Check
A.
Horizon Attitude Gyro Operational Check.
(1) Start the airplane engine.
(2) Let the engine run for no less than 3 minutes.
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(3) Make sure that the vacuum gage shows between 4.5 and 5.5 in.hg.
(4) Make sure that the horizon bar becomes stable at the correct position for the attitude of the
airplane, or becomes stable at the correct position, begins to vibrate, and then slowly stops
vibration altogether.
(5) Taxi in a straight line. Make sure that the horizon bar stays in the horizontal position while you
taxi.
(6) Do a 360-degree turn. Do not turn sharply as you make the turn. Make sure that the horizon bar
does not tip more than 4 degrees from the horizontal during the turn.
(7) If the horizontal gyro precession is more than 4 degrees from a heading in either direction during
a 10-minute period, or does not operate within one or more of the limits given in steps 4 through
6 of this operational check, you must repair the system and/or replace the gyro.
8.
Directional Gyro Description and Operation
A.
The vacuum system supplies the air flow necessary to move the gyro rotor in the directional gyro.
Incorrect operation of the vacuum system will cause the horizon attitude gyro to operate incorrectly.
Problems with the vacuum system can cause incorrect indication and decreased performance.
B.
The directional gyro must have between 4.5 and 5.5 in.hg. of vacuum to operate correctly. With the
correct vacuum applied, the gyro will get rated performance in a minimum of 3 minutes of rotor turn
time.
The directional gyro rotor can continue to turn for approximately 15 minutes after the vacuum in the
system is removed. It can show a change in the directional indication while the rotor speed decreases,
or the directional gyro dial can start to turn. When fully stopped, the gyro rotor will not correctly indicate
changes in the airplane's direction until the system starts again.
If a gyro has been stopped and started again before the rotor fully stops, more time will be necessary
for the gyro to correctly indicate the directional changes of the airplane.
C.
D.
9.
E.
The permitted limits for directional gyro drift on the ground or in flight is 4 degrees from a fixed heading,
during a 10-minute period.
F.
Continuous turns around a point and/or banks of more than 55 degrees can cause the directional gyro
to turn. This is a limit of the gyro and not a cause for removal.
Directional Gyro Removal/Installation (Airplanes without Garmin G1000)
A.
Directional Gyro Removal (Refer to Figure 201).
CAUTION: Make sure that the gyro rotor has fully stopped before you move the
instrument. The gyro rotor will not stop for approximately 15 minutes
after the vacuum source is removed. Damage to the instrument will
occur if the instrument is moved before the gyro rotor has stopped.
CAUTION: Be careful with the gyroscopic instruments. Do not hit, shake, or put the
instruments on a hard surface. Put soft material between the gyroscopic
instruments and any hard surface. Damage to the instruments will occur
if the instruments are not carefully moved. The manufacturer's warranty
can become void if the gyro is not kept in its initial condition as received
from the manufacturer.
(1) Put the MASTER switch and the AVIONICS switch in the off position.
(2) Remove the screws from the center pilot panel to get access to the back of the directional gyro.
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CAUTION: Make sure that you put soft material between the directional gyro
and the control column before you remove the gyro. If you put the
sub panel on the control column without any protection, you can
damage the directional gyro and/or the other instruments in the sub
panel. Be very careful when you remove the sub panel so that you
do not to hit the gyro.
(3) Put a label on the air inlet hose and the vacuum outlet hose that are attached to the directional
gyro.
(4) Loosen the clamps and remove hoses from the directional gyro.
(5) Disconnect the directional gyro connector and the electrical connector from the directional gyro.
(6) Put female plugs over the ports and put a connector cap on the electrical connector.
(7) Remove the screws that attach the directional gyro to the center pilot panel.
CAUTION: Put a cover on the applicable hose or port, or on the applicable
electrical connector when the gyroscopic instrument is out of the
airplane or is to be shipped. Damage to the instrument will occur
from contamination if you do not use a cover.
B.
(8) Remove the directional gyro from the airplane.
Directional Gyro Installation (Refer to Figure 201).
CAUTION: Do not remove the directional gyro from the box in which it was shipped
until it is ready to be installed into the airplane. This will minimize the
possibility of accidentally causing damage to the gyro.
CAUTION: Remove all plugs from the directional gyro before you install it in the
aircraft.
CAUTION: Be careful with the gyroscopic instruments. Do not hit, shake, or put the
instruments on a hard surface. Use soft material between the gyroscopic
instruments and any hard surface. Damage to the instruments will occur
if the instruments are not carefully moved. The manufacturer's warranty
can become void if the gyro is not kept in its initial condition as received
from the manufacturer.
(1) Attach the directional gyro to the center pilot panel with the screws.
(2) Remove the female plugs from the ports and remove the connector cap from the electrical
connector.
(3) Attach the air intake hose and the vacuum outlet hose to the directional gyro and tighten the
clamps.
(4) Attach the directional gyro connector and the electrical connector to the directional gyro.
(5) Attach the center pilot panel with the screws.
(6) Put the MASTER switch and the AVIONICS switch in the ON position.
(7) Do an operational check of the directional gyro to make sure that it operates correctly. Refer to
Directional Gyro Operational Check.
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10.
Directional Gyro Operational Check
A.
Directional Gyro Operational Check (Refer to Figure 201).
NOTE:
The permitted limit for gyro drift on the ground or in flight is 4 degrees from a fixed heading,
during a 10-minute period.
(1) Start the airplane engine.
(2) Make sure that the vacuum system operates correctly.
(a) The vacuum gage must show between 4.5 and 5.5 in.hg.
(3) Let the directional gyro become stable for at least 3 minutes.
(4) Ifthe directional gyro dial starts to turn, let the gyro become stable and then push the gyro-caging
knob. If the gyro dial continues to turn, repair the system and/or replace the gyro.
NOTE:
It is usual for the directional gyro dial to turn when the gyro becomes stable. This is
a limit of the gyro and not a cause for removal.
(5)
(6)
(7)
(8)
Point the airplane's heading to the north.
Set the directional gyro to the north.
Make sure that the directional gyro dial drift is not more than 4 degrees in a 10-minute period.
Point the airplane's heading and set the directional gyro to each of the other three cardinal
headings in turn (West, South, and East).
(9) Make sure that the directional gyro dial drift is not more than 4 degrees in a 10-minute period at
each of these cardinal headings.
(10) If the directional gyro dial drift is not satisfactory at any heading, repair the system and/or replace
the gyro.
NOTE:
11.
After you stop operation of the airplane, it is usual for the directional gyro dial to
continue to turn. This is not a cause to remove the gyro.
Turn Coordinator Removal/Installation (Airplanes without Garmin G1000)
A. Turn Coordinator Removal (Refer to Figure 201).
CAUTION: Make sure that the gyro rotor has fully stopped before you move the
instrument. The gyro rotor will not stop for approximately 15 minutes
after the vacuum source is removed. Damage to the instrument will
occur if the instrument is moved before the gyro rotor has stopped.
CAUTION: Be careful with the gyroscopic instruments. Do not hit, shake, or put the
instruments on a hard surface. Put soft material between the gyroscopic
instruments and any hard surface. Damage to the instruments will occur
if the instruments are not carefully moved. The manufacturer's warranty
can become void if the gyro is not kept in its initial condition as received
from the manufacturer.
(1) Put the MASTER switch and the AVIONICS switch in the off position.
(2) Remove the screws from the center pilot panel to get access to the back of the turn coordinator.
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CAUTION: Make sure that you put soft material between the turn coordinator
and the control column before you remove the turn coordinator. If
you put the sub-panel on the control column without any protection,
you can damage the turn coordinator and/or the other instruments
in the sub-panel. Be very careful when you remove the sub-panel
so that you do not to hit the turn coordinator.
(3) Disconnect the turn coordinator avionics connector and electrical connector from the turn
coordinator.
CAUTION: Put a cover on the applicable electrical connector when the
gyroscopic instrument is out of the airplane or is to be shipped.
Damage to the instrument will occur from contamination if a cover
is not used.
(4) Put connector caps on the turn coordinator avionics connector and electrical connector.
(5) Remove the screws that attach the turn coordinator to the center pilot panel.
(6) Remove the turn coordinator from the airplane.
B.
Turn Coordinator Installation (Refer to Figure 201).
CAUTION: Do not remove the turn coordinator from the box in which it was shipped
until it is ready to be installed into the airplane. This will minimize the
possibility of accidentally causing damage to the gyro.
CAUTION: Remove all plugs from the turn coordinator before you install it in the
aircraft.
CAUTION: Be careful with the gyroscopic instruments. Do not hit, shake, or put the
instruments on a hard surface. Put soft material between the gyroscopic
instruments and any hard surface. Damage to the instruments will occur
if the instruments are not carefully moved. The manufacturer's warranty
can become void if the gyro is not kept in its initial condition as received
from the manufacturer.
(1) Attach the turn coordinator to the center pilot panel with the screws.
(2) Remove the connector caps from the turn coordinator avionics connector and the electrical
connector.
(3) Attach the turn coordinator avionics connector and electrical connector to the turn coordinator.
(4) Attach the center pilot panel with the screws.
(5) Put the MASTER switch and the AVIONICS switch in the ON position.
(6) Set the autopilot roll null (if autopilot is installed). Refer to Autopilot - Maintenance Practices.
(7) Do an operational check of the turn coordinator to make sure that it operates correctly.
12. Turn Coordinator Removal/nstallation (Airplanes with Garmin G1000)
A.
Turn Coordinator Removal (Refer to Figure 203).
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CAUTION: Make sure that the gyro rotor has fully stopped before you move the
instrument. The gyro rotor will not stop for approximately 15 minutes
after the vacuum source is removed. Damage to the instrument will
occur if the instrument is moved before the gyro rotor has stopped.
CAUTION: Be careful with the gyroscopic instruments. Do not hit, shake, or put the
instruments on a hard surface. Use soft material between the gyroscopic
instruments and any hard surface. Damage to the instruments will occur
if the instruments are not carefully moved. The manufacturer's warranty
can become void if the gyro is not kept in its initial condition as received
from the manufacturer.
(1) Put the MASTER switch and the AVIONICS switch in the off position.
Remove the multi-function display (MFD). Refer to Chapter 34, Control Display Unit Maintenance Practices.
(3) Remove the screws that attach the turn coordinator.
(4) Move the turn coordinator aft to get access to the turn coordinator avionics connector.
(2)
CAUTION: Put a cover on the applicable electrical connector when the
gyroscopic instrument is out of the airplane or is to be shipped.
Damage to the instrument will occur from contamination if a cover
is not used.
B.
(5)
(6)
(7)
Turn
Disconnect the turn coordinator avionics connector and the electrical connector.
Put connector caps on the avionics connector and the electrical connector.
Remove the turn coordinator from the airplane.
Coordinator Installation (Refer to Figure 203).
CAUTION: Do not remove the turn coordinator from the box in which it was shipped
until it is ready to be installed into the airplane. This will minimize the
possibility of accidentally causing damage to the gyro.
CAUTION: Remove all plugs from the turn coordinator before you install it in the
aircraft.
CAUTION: Be careful with the gyroscopic instruments. Do not hit, shake, or put the
instruments on a hard surface. Put soft material between the gyroscopic
instruments and any hard surface. Damage to the instruments will occur
if the instruments are not carefully moved. The manufacturer's warranty
can become void if the gyro is not kept in its initial condition as received
from the manufacturer.
(1) Remove the connector caps from the turn coordinator avionics connector and the electrical
connector.
(2) Attach the turn coordinator avionics connector and the electrical connector.
(3) Attach the turn coordinator with screws.
(4) Install the MFD. Refer to Chapter 34, Control Display Unit - Maintenance Practices.
(5) Put the MASTER switch and the AVIONICS switch in the ON position.
(6) Set the autopilot roll null (if autopilot is installed). Refer to Autopilot - Maintenance Practices.
(7) Do an operational check of the turn coordinator to make sure that it operates correctly.
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MAINTENANCE MANUAL
I
NOTE:
AIR DATA
COMPUTER
TURN COORDINATOR
o
0
|
C
o
!'
-
i
o
THE INSTRUMENT PANEL
IS SHOWN WITH THE
MILTI-FUNCTION DISPLAY
(MFD) SCREEN REMOVED.
ENGINE
INTERFACE
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eo e[o Foo ool
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VIEW A-A
AIRPLANES WITH GARMIN G1000
0710T1001
A3930T368
Turn Coordinator Installation (Airplanes with Garmin G1000)
Figure 203 (Sheet 1)
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MODEL 182/T182
MAINTENANCE MANUAL
COMPASS INSTALLATION - MAINTENANCE PRACTICES
1.
General
A.
2.
A lighted, magnetic compass is installed on the upper windshield at the airplane centerline.
Compass Removal and Installation
A.
Remove Compass (Refer to Figure 201).
(1) Remove electrical power from airplane and turn master switch to "OFF".
(2) Identify, tag, and disconnect electrical wires for compass lighting.
NOTE:
(3)
(4)
B.
Splices are located under upper windshield trim.
Remove screw, post, and washers securing compass to compass base.
Remove compass from airplane.
Install Compass (Refer to Figure 201).
(1) Secure compass to compass base with screw, post, and washers. Torque screw to 12.5 Inch
pounds, +2.5 or - 2.5 Inch pounds (1.41 N.m, +0.28 or -0.28 N.m).
(2) Connect electrical wires at splices.
(3) Restore electrical power to airplane as required and turn master switch to "ON".
(4) Check compass accuracy on compass rose.
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MODEL 182/T182
MAINTENANCE MANUAL
SCREW
COMPASS
ASSEMBLY
DETAIL A
0710T1001
A0714T1002
Compass Installation
Figure 201 (Sheet 1)
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MAINTENANCE MANUAL
MAGNETOMETER - MAINTENANCE PRACTICES
1.
2.
General
A.
The magnetometer maintenance practices give procedures for the magnetometer removal/
installation.
B.
The magnetometer senses magnetic direction. The magnetometer uses this information to digitally
interface with the integrated avionics system. The magnetometer is in the bottom of the left wing.
GMU-44 Magnetometer Removal/Installation
CAUTION: Do the magnetometer calibration if the GMU-44 magnetometer is removed
and replaced after post-installation calibration. The magnetometer can give
incorrect information if the calibration is not completed.
CAUTION: Do not move the mounting racks if the GMU-44 magnetometer is removed
and replaced. The magnetometer can give incorrect information.
CAUTION: Do not use magnetic tools and screws on the magnetometer. Magnetic tools
and screws will cause the magnetometer to malfunction.
A.
Remove the Magnetometer (Refer to Figure 201).
(1) Make sure the MASTER and AVIONICS switches are in the off position.
(2) Remove the access/inspection plate (520DB) to get access to the magnetometer. Refer to
Chapter 6, Access/Inspection Plates - Description and Operation.
(3) Remove the screws that attach the magnetometer to the flux detector bracket.
(4) Disconnect the electrical connector (PL302) from the magnetometer.
B.
Install the Magnetometer (Refer to Figure 201).
(1) Connect the electrical connector (PL302) to the magnetometer.
(2) Attach the magnetometer to the flux detector bracket with the screws.
(a) Put the magnetometer in position on the flux detector bracket, temporarily aligned parallel
to the longitudinal axis of the airplane.
(3) Do the magnetometer calibration and functional test. Refer to the Garmin G1000 Line
Maintenance Manual.
(4) Install the access/inspection plate (520DB). Refer to Chapter 6, Access/Inspection Plates Description and Operation.
34-22-10
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MAINTENANCE MANUAL
U
....
n
FLUX DETECTOR
BRACKET
BOTTOM LEFT
WING SKIN
ELECTRICAL
CABLE
(NOTE)
ETER
ON
COVER PLATE
(520JB)
NOTE:
ELECTRICAL CABLE
THAT EXTENDS TO THE
ELECTRICAL CONNECTOR.
(PL302)
DETAIL
A
0710T1001
A0714T1048
Magnetometer Installation
Figure 201 (Sheet 1)
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MAINTENANCE MANUAL
ATTITUDE HEADING REFERENCE SYSTEM (AHRS) - MAINTENANCE PRACTICES
1.
General
A.
2.
The Attitude Heading Reference System (AHRS) has the electronic sensors and hardware that
read the airplane's altitude and directional information and digitally interfaces this information in the
integrated system. The AHRS unit is in the tailcone.
GRS-77 AHRS Removal/Installation
CAUTION: Do not move the unit mounting racks if the GRS-77 AHRS is removed and
replaced after post-installation calibration has been completed. The AHRS
can give incorrect information.
A.
Remove the AHRS unit (Refer to Figure 201).
(1) Make sure the MASTER and AVIONICS switches are in the off position.
(2) Remove the tailcone access/inspection plate (310AR) to get access to the NAV/COM units.
Refer to Chapter 6, Access/Inspection Plates - Description and Operation.
(3) Disconnect the electrical connector (P771).
(4) Remove the screws that attach the AHRS unit to the mounting tray.
(5) Remove the AHRS unit from the airplane.
B.
Install the AHRS unit (Refer to Figure 201).
(1) Put the AHRS unit in position in the mounting tray and attach to the tray with screws.
(a) If the fasteners that attach the mounting racks are loosened for any reason, the
post-installation calibration must be completed. Refer to the Garmin GRS 77/GMU 44
Installation Manual (P/N 190-00207-10).
(2) Connect the electrical connector (P771).
(3) Install the tailcone access/inspection plate (310AR). Refer to Chapter 6, Access/Inspection
Plates - Description and Operation.
(4) Do a check to make sure the AHRS operates correctly. Refer to the Garmin G1000 Line
Maintenance Manual.
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MAINTENANCE MANUAL
A .
B
A
INTEGRATED
AVIONICS UNIT
(COMM 2)
INTEGRATED
AVIONICS UNIT
(COMM 1)
0
C--,
l
VIEW A-A
LOOKING FORWARD AT FS 140
AIRPLANES THAT HAVE
THE GARMIN G1000
0710T1001
A0714T1044
Tailcone Avionics Installation
Figure 201 (Sheet 1)
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MAINTENANCE MANUAL
MARKER BEACON - DESCRIPTION AND OPERATION
1.
General
A.
2.
Marker beacon functions are included in the integrated Bendix/King KMA-26/KMA-28 Audio Amplifier/
Intercom/Marker Beacon Receiver. This receiver is a solid state unit and contains a push-button audio
selector panel, speaker and headphone isolation amplifiers, a six station intercom, and a marker
beacon receiver.
Description and Operation
A.
As many as three transceivers and six receivers can be controlled by the KMA-26/KMA-28 Audio
Amplifier/Intercom/Marker Beacon Receiver. This receiver also has two unswitched and mutable
auxiliary inputs, four unswitched and unmutable inputs, and two entertainment inputs.
B.
Separate isolation amplifiers are provided for headphones and speaker to provide isolation even when
the same source is selected for both headphones and speaker. Except for the unswitched, unmuted
inputs, the speaker output is muted when the MIC key is pressed to transmit. In the PA MIC selector
mode, all the audio inputs are muted to the speaker while the microphone is keyed. When the EMG
position is chosen on the MIC selector, the pilot's headphones and microphone are connected directly
to COM 1, continuing to operate even when power is lost to the KMA-26/KMA28 receiver.
C.
The KMA-26/KMA28 marker beacon receiver presentation uses three colored lenses (blue, amber,
and white) with the letter designations O-M-I engraved on the lens for visual station passage indication.
The appropriate marker audio tone can also be selected. HI-LO sensitivity and lamp test is selected
with the HI SENS/LO SENS/TEST switch adjacent to the marker beacon lights. A marker mute
feature mutes the marker audio until after the beacon has been passed. The marker beacon lights
are automatically dimmed to compensate for ambient cockpit lighting conditions.
D.
For operating instructions of the KMA-26/KMA28 Audio Amplifier/lntercom/Marker Beacon Receiver,
refer to the manufacturer's manual listed in the Introduction, List of Manufacturers Technical
Publications.
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MAINTENANCE MANUAL
MARKER BEACON - MAINTENANCE PRACTICES
1.
2.
General
A.
Maintenance practices have procedures forthe removal/installation of the KMA-26/KMA-28 and GMA1347 Audio Amplifier/lntercom/Marker Beacon Receiver and marker beacon antenna.
B.
For a check of the KMA-26/KMA-28 and GMA-1347 receiver, refer to the manufacturer's manual in
the Introduction, List of Manufacturers Technical Publications.
KMA-26/KMA-28 and GMA-1347 Removal/Installation
A.
3.
For removal and installation of the KMA-26/KMA-28, GMA-1347 receiver, refer to Chapter 23, Audio
Panel - Maintenance Practices.
Marker Beacon Antenna Removal/Installation
A.
Remove the Marker Beacon Antenna (Refer to Figure 201).
(1) Make sure the MASTER and AVIONICS switches are in the off position.
(2) Remove the baggage compartment lower access panel. Refer to Chapter 25, Interior Upholstery
- Maintenance Practices.
(3) Remove the aft floorboard access/inspection plate to get access to the marker beacon antenna.
(4) Disconnect the coaxial cable (PF1001) from the antenna.
(5) Remove the screws that attach the antenna to the bottom of the fuselage.
B.
Install the Marker Beacon Antenna (Refer to Figure 201).
(1) Put the marker beacon antenna in position on the bottom of the fuselage.
(2) Attach the antenna with screws.
(3) Attach the coaxial cable (PF1001) to the antenna.
(4) Install the access/inspection plate to the floor of the airplane.
(5) Install the baggage compartment lower access panel. Refer to Chapter 25, Interior Upholstery
- Maintenance Practices.
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MAINTENANCE MANUAL
D07A 1
D
FUSELAGE
SKIN
EACON
UF1001)
DETAIL
A
0710T1001
A0518T1035
Marker Beacon Antenna
Figure 201 (Sheet 1)
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INDEPENDENT POSITION DETERMINING - DESCRIPTION AND OPERATION
1.
Description
A.
2.
The section that follows has the maintenance procedures for the airplane system that gives the
position of the airplane. The airplane components of this system are mainly independent of ground
installations or satellites such as weather radar.
Operation
A.
B.
C.
KMH-880 Multi-Hazard Awareness System
(1) The Bendix/King KMH-880 Multi-Hazard Awareness System (MHAS) has Enhanced Ground
Proximity Warning System (EGPWS), Terrain Awareness and Warning System (TAWS B), and
Traffic Advisory System (TAS) functions. A processor is installed in the aft avionics (tailcone)
area. The system also uses a TAS directional antenna that is installed on the top of the fuselage,
and an omnidirectional antenna that is installed on the bottom of the fuselage.
KTA-870 Traffic Advisory System
(1) The KTA-870 TAS is installed on airplanes with the Garmin G1000. The KTA-870 TAS interfaces
with the Garmin G1000 to track, analyze, and display to the flight crew the range and altitude
data of traffic. A processor is installed in the tailcone area. The system also uses a TAS
directional antenna that is installed on the top of the fuselage, and an omnidirectional antenna
that is installed on the bottom of the fuselage.
WX-500 Stormscope
(1) The WX- 500 Stormscope shows lightning information at ranges of 200 nautical miles. It is
designed to interface with Garmin's Control Display Unit (CDU) or Honeywell's Multi-Function
Display (MFD). The Stormscope does an analysis of the radiated signals of electrical discharges
from storm cells to find thunderstorms. The information is then processed to determine the
location and intensity of dangerous thunderstorms.
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KMH-880 MULTI-HAZARD AWARENESS SYSTEM - MAINTENANCE PRACTICES
1.
General
A.
B.
C.
2.
The Bendix/King KMH 880 Multi-Hazard Awareness System (MHAS) has Enhanced Ground Proximity
Waming System (EGPWS) and Traffic Advisory System (TAS) functions. The MHAS system has
these main components installed in the tailcone area: a KMH-820 multi-hazard awareness processor,
a terrain awareness warning system (TAWS B), a traffic advisory system (TAS), and a KCM-805
configuration module. Altitude information for the system comes from the blind-encoding altimeter
and is changed into a digital signal by the KCM-805 configuration module.
Two antennas are necessary for the operation of the MHAS system. An omnidirectional antenna is
installed on the bottom side of the fuselage and a TAS directional antenna is installed on the top side
of the fuselage.
The KMD-540 Mutli-Function Display controls and shows the TAS and EGPWS information. Aural
warnings are given through the current audio system in the airplane. Other warnings for terrain are
given by the annunciator unit with the TERR N/A lens kit installed.
KMH-820 Processor Removal and Installation
A.
KMH-820 Processor Removal (Refer to Figure 201).
(1) Set the MASTER and AVIONICS switches to the off position.
(2) Disengage the IHAS circuit breaker on the circuit breaker panel.
CAUTION:
B.
3.
Use a tailcone stand when you do work in the tailcone. If you do
not use a tailcone stand, the tail of the airplane can fall to the floor.
(3) Remove tailcone access/inspection plate (31OAR) to get access to the processor. Refer to
Chapter 6, Access/Inspection Plates - Description and Operation.
(4) Disconnect the electrical connectors (J5, J6, and J8) from the forward side of the processor.
(5) Remove the screws that attach the rack assembly to the support bracket assembly.
(6) Remove the processor with the rack assembly from the airplane.
(7) Remove the processor from the rack assembly.
KMH-820 Processor Installation (Refer to Figure 201).
(1) Put the processor in the rack assembly.
(2) Put the processor at the correct location, on the left side of the tailcone.
(3) Install the screws that attach the rack assembly to the support bracket assembly.
(4) Connect the electrical connectors (J5, J6, and J8) to the forward side of the processor.
(5) Install tailcone access/inspection plate (31 OAR). Refer to Chapter 6, Access/Inspection Plates Description and Operation.
(6) Engage the IHAS circuit breaker on the circuit breaker panel.
KMH-880 Interface Adapter Removal and Installation
A.
KMH-880 Interface Adapter Removal (Refer to Figure 202).
(1) Set the MASTER and AVIONICS switches to the off position.
(2) Disengage the IHAS circuit breaker on the circuit breaker panel.
CAUTION: Use a tailcone stand when you do work in the tailcone. If you do
not use a tailcone stand, the tail of the airplane can fall to the floor.
(3) Remove tailcone access/inspection plate (31OAR) to get access to the interface adapter. Refer
to Chapter 6, Access/Inspection Plates - Description and Operation.
(4) Disconnect the electrical connectors (PT703 and PT704) from the interface adapter.
(5) Disconnect the electrical connector (PT705) from the configuration module.
(6) Disconnect the electrical connectors from the (PT706 and PT707) from the support bracket
assembly.
(7) Remove the screws that attach the support bracket to the airplane structure.
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MAINTENANCE MANUAL
A
KMH-820 MULTI-HAZARD
AWARENESS SYSTEM PROCESSOR
DAT
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ELECTRICAL
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0710T1001
A1218T1071
KMH-820 Processor Installation
Figure 201 (Sheet 1)
34-40-01
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MODEL 182/T182
MAINTENANCE MANUAL
D"".I
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A071 8T1094
KMH-880 Interface Adapter Installation
Figure 202 (Sheet 1)
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MAINTENANCE MANUAL
(8) Remove the support bracket from the airplane.
(9) Remove the screws that attach the interface adapter to the support bracket.
(10) Remove the screws that attach the configuration module to the support bracket.
B.
4.
5.
KMH-880 Interface Adapter Installation (Refer to Figure 202).
(1) Install the screws that attach the configuration module to the support bracket.
(2) Install the screws that attach the interface adapter to the support bracket.
(3) Put the support bracket at the correct location on the airplane structure on the right side of the
tailcone.
(4) Install the screws that attach the support bracket to the airplane structure.
(5) Connect the electrical connectors (PT703 and PT704) to the interface adapter.
(6) Connect the electrical connector (PT705) to the configuration module.
(7) Connect the electrical connectors (PT706 and PT707) to the support bracket assembly.
(8) Install tailcone access/inspection plate (31 OAR). Refer to Chapter 6, Access/Inspection Plates Description and Operation.
(9) Engage the IHAS circuit breaker on the circuit breaker panel.
Omnidirectional Antenna Removal and Installation
A.
Omnidirectional Antenna Removal (Refer to Figure 203).
(1) Set the MASTER and AVIONICS switches to the off position.
(2) Disengage the IHAS circuit breaker on the circuit breaker panel.
(3) Pull the applicable interior upholstery back to get sufficient access to the rear access panel on
the floorboard.
(4) Remove the floor panel to get access to the omnidirectional antenna installation.
(5) Disconnect the adapter (coax cable) from the omnidirectional antenna.
(6) Remove the screws that attach the omnidirectional antenna to the bottom of the fuselage.
(7) Remove the doubler and omnidirectional antenna from the airplane.
B.
Omnidirectional Antenna Installation (Refer to Figure 203).
(1) Put the doubler at the correct location on the bottom of the fuselage.
(2) Put the omnidirectional antenna at the correct location on the bottom side of the fuselage so that
the screw holes align with the doubler.
(3) Install the screws that attach the omnidirectional antenna and doubler to the airplane skin.
(4) Connect the coax cable to the omnidirectional antenna.
(5) Verify correct electrical bonding of the antenna to the airplane structure.
(6) Install the floor panel to the floorboard.
(7) Install the interior upholstery.
(8) Engage the IHAS circuit breaker on the circuit breaker panel.
Traffic Awareness System (TAS) Directional Antenna Removal and Installation
Directional Antenna Removal (Refer to Figure 204).
Set the MASTER and AVIONICS switches to the off position.
Disengage the IHAS circuit breaker on the circuit breaker panel.
Remove the headliner to get access to the directional antenna.
Put a label on each of the four adapters and disconnect them from the directional antenna.
Remove the screws that attach the directional antenna to the top of the fuselage.
Remove the directional antenna and doubler from the airplane.
A.
TAS
(1)
(2)
(3)
(4)
(5)
(6)
B.
TAS Directional Antenna Installation (Refer to Figure 204).
(1) To make sure that the electrical bonding requirement for the antenna is within the acceptable
limit, make sure that all of the bonding surfaces of the doubler, antenna, and airplane structure
are clean.
(2) Put the doubler and directional antenna on the fuselage so that the screw holes align through
the airplane skin.
(3) Install the screws that attach the directional antenna and doubler to the airplane skin.
(4) Remove the labels and connect the four adapters to the correct receptacles on the directional
antenna.
(5) Verify correct electrical bonding of the antenna to the airplane structure.
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©Cessna Aircraft Company
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MODEL 182/T182
MAINTENANCE MANUAL
DA"4^
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0718T1075
Omnidirectional Antenna Installation
Figure 203 (Sheet 1)
34-40-01
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
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Figure 204 (Sheet 1)
34-40-01
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MAINTENANCE MANUAL
I
(6) Fillet seal around the antenna with Type I Class B Sealant. Refer to Chapter 20, Fuel, Weather
and High-Temperature Sealing - Maintenance Practices.
(7) Install the headliner.
(8) Engage the IHAS circuit breaker on the circuit breaker panel.
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MODEL 182/T182
MAINTENANCE MANUAL
KTA-870 TRAFFIC ADVISORY SYSTEM (TAS) - MAINTENANCE PRACTICES
1.
General
A.
2.
The KTA-870 Traffic Advisory System (TAS) is installed on airplanes with the Garmin G1000. The KTA870 TAS interfaces with the Garmin G1000. This section gives removal and installation procedures for
the KTA-810 processor. Two antennas are necessary for the operation of the KTA-870 TAS. Refer to
KMH-880 Multi-Hazard Awareness System - Maintenance Practices for the removal and installation
procedures for the TAS directional antenna and the omnidirectional antenna.
KTA-810 Processor Removal/Installation
A.
KTA-810 Processor Removal (Refer to Figure 201).
(1) Set the MASTER and AVIONICS switches to the off position.
(2) Disengage the TAS circuit breaker on the circuit breaker panel.
CAUTION: Use a tailcone stand when you get in the tailcone. If you do not use
a tailcone stand, the tail of the airplane can fall to the floor.
(3) Remove tailcone access/inspection plate (310AR) to get access to the processor. Refer to
Chapter 6, Access/Inspection Plates - Description and Operation.
(4) Disconnect the electrical connectors (J1, J2, J3, J4, J7, and J10) from the forward side of the
processor.
(5) Remove the 50-ohm terminations from J5, J6, and J8 electrical connections on the forward side
of the processor.
(6) Loosen the two lock nuts that attach the processor to the support bracket.
(7) Remove the processor from the support bracket.
(8) Remove the screws that attach the support bracket to the support bracket assembly.
(9) Remove the support bracket assembly from the airplane.
B.
3.
KTA-810 Processor Installation (Refer to Figure 201).
(1) Install the screws that attach the support bracket to the support bracket assembly.
(2) Put the processor in the support bracket and tighten the lock nuts that attach the processor to
the support bracket assembly.
(3) Connect the electrical connectors (J1, J2, J3, J4, J7, and J10) to the forward side of the
processor.
(4) Install the 50-ohm terminations in J5, J6, and J8 electrical connections on the forward side of
the processor.
(5) Install the baggage divider forward of the tailcone.
(6) Install the rear seat. Refer to Chapter 25, Rear Seat - Maintenance Practices.
(7) Engage the TAS circuit breaker on the circuit breaker panel.
KCM-805 Configuration Module Removal/Installation
A.
KCM-805 Configuration Module Removal (Refer to Figure 202).
(1) Set the MASTER and AVIONICS switches to the off position.
(2) Disengage the TAS circuit breaker on the circuit breaker panel.
(3) Remove the rear seat to get access to the aft baggage divider. Refer to Chapter 25, Rear Seat
- Maintenance Practices.
CAUTION: Use a tailcone stand when you get in the tailcone. If you do not use
a tailcone stand, the tail of the airplane can fall to the floor.
(4) Remove the aft baggage divider to get access to the tailcone.
(5) Disconnect the electrical connector (PT705) from the configuration module.
(6) Remove the screws that attach the configuration module to the gusset assembly.
B.
KCM-805 Configuration Module Installation (Refer to Figure 202).
(1) Put the configuration module in position on the support bracket.
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MODEL 182/T182
MAINTENANCE MANUAL
KTA-810 TRAFFIC ADVISORY
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3T1102
KTA-810 Processor Installation
Figure 201 (Sheet 1)
34-40-( 35
© Cessna Aircraft Company
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Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
A
KTA-810
GL
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A0718T1101
KCM-805 Configuration Module Installation
Figure 202 (Sheet 1)
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MODEL 182/T182
MAINTENANCE MANUAL
(2)
(3)
(4)
(5)
(6)
Install the screws that attach the configuration module to the gusset assembly.
Connect the electrical connector (PT705) to the configuration module.
Install the aft baggage divider.
Install the rear seat. Refer to Chapter 25, Rear Seat - Maintenance Practices.
Engage the TAS circuit breaker on the circuit breaker panel.
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MODEL 182/T182
MAINTENANCE MANUAL
WX-500 STORMSCOPE - MAINTENANCE PRACTICES
1.
2.
3.
General
A.
The maintenance practices give the removal and installation procedures for the stormscope, which is
installed in the tailcone, aft of the baggage divider.
B.
The WX- 500 Stormscope shows lightning information at ranges of 200 nmi. It is designed to
interface with Garmin's Control Display Unit (CDU) or Honeywell's multi-function display (MFD).
The stormscope does an analysis of the radiated signals of electrical discharges from storm cells
to find thunderstorms. The information is then used to give the location and intensity of dangerous
thunderstorms.
WX-500 Stormscope Removal/Installation
A.
Remove the Stormscope (Refer to Figure 201).
(1) Make sure the MASTER and AVIONICS switches are in the off position.
(2) Remove the tailcone access/inspection plate (310AR) to get access to the stormscope. Refer
to Chapter 6, Access/Inspection Plates - Description and Operation.
(3) Disconnect the electrical connection.
(4) Loosen the knurled nut that holds the stormscope in position.
(5) Remove the stormscope from the airplane.
B.
Install the Stormscope (Refer to Figure 201).
(1) Set the stormscope in position on the tray and tighten the knurled nut.
(2) Connect the electrical connection.
(3) Install the tailcone access/inspection plate (310AR). Refer to Chapter 6, Access/Inspection
Plates - Description and Operation.
Stormscope Antenna Removal/Installation
A.
Remove the Stormscope Antenna (Refer to Figure 202).
(1) Make sure the MASTER and AVIONICS switches are in the off position.
(2) Remove the baggage compartment lower access panel. Refer to Chapter 25, Interior Upholstery
- Maintenance Practices.
(3) Disconnect the coaxial cable (PF1004) from the antenna.
(4) Remove the screws that attach the antenna to the bottom of the fuselage.
B.
Install the Stormscope Antenna (Refer to Figure 202).
(1) Put the stormscope antenna in position on the bottom of the fuselage.
(2) Attach the antenna with screws.
(3) Attach the coaxial cable (PF1004) to the antenna.
(4) Install the baggage compartment lower access panel. Refer to Chapter 25, Interior Upholstery
- Maintenance Practices.
34-40-10
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Mar 1/2004
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MODEL 182/T182
MAINTENANCE MANUAL
DOOS:
U
SHELF
DETAIL
A
0710T1001
A0714T1046
WX-500 Stormscope
Figure 201 (Sheet 1)
34-40-10
©Cessna Aircraft Company
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MODEL 182/T182
MAINTENANCE MANUAL
B
CONNECTOR
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-
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A0714T1049
Stormscope Antenna Installation
Figure 202 (Sheet 1)
34-40-10
© Cessna Aircraft Company
Page 203
Mar 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
KX-155A COMM/NAV SYSTEM - MAINTENANCE PRACTICES
1.
General
A.
2.
This section gives maintenance practices for the KX-155A NAV/COM System component removal and
installation. For more system information and the post installation check, refer to the manufacturer's
manuals listed in the Introduction, List of Manufacturers Technical Publications.
KX-155A/165A VHF COMM Transceiver/NavigationNOR/LOC Glideslope Receiver Removal and
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-155A and/or the KX-165A NAV/COM radios.
A.
3.
For removal and installation of the KX-155A receiver, refer to Chapter 23, Communications Maintenance Practices.
Omni (NAV) Antenna Removal and Installation (182S)
A.
B.
Remove the Omni (NAV) Antenna (Refer to Figure 201).
(1) Remove the electrical power from the airplane and turn the master switch to the OFF position.
(2) Remove the boots from the antenna radiators.
(3) Remove the self-locking hex nuts, and then remove the antenna radiators from the antenna
base.
(4) Get access to the omni antenna by removing the fin tip.
(5) Remove the screws that attach the antenna base to the fin rib.
(6) Lift the antenna base to get access to the coax connector. Disconnect the coax connector from
the antenna base.
(7) Remove the omni antenna from the airplane.
Install the Omni (NAV) Antenna (Refer to Figure 201).
(1) Position the omni antenna on the fin and connect the coax connector to the antenna base.
(2) Attach the antenna base to the fin rib with screws.
(3) Install the fin tip.
CAUTION: When you use self-locking hex nuts to attach the antenna radiators,
do not tighten the nuts too much.
(4) Attach the antenna radiators to the antenna base with the self-locking hex nuts.
(5) Install the boots on the antenna radiators.
(6) Supply electrical power to the airplane as necessary, and turn the master switch to the ON
position.
4.
NAV Antenna Coupler Removal and Installation (182S)
A.
Remove the NAV Antenna Coupler (Refer to Figure 201).
NOTE:
The NAV antenna coupler is found at FS 8.00 and WL 11.77, between the firewall and
instrument panel on the left outboard stringer assembly.
(1) Remove the electrical power from the airplane and turn the master switch to the OFF position.
(2) Get access to the NAV antenna coupler.
(3) Identify, put a label on, and disconnect the antenna coax connectors from the NAV antenna
coupler.
(4) Remove the screws and washers that attach the NAV antenna coupler to the fuselage.
(5) Remove the NAV antenna coupler from the airplane.
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MODEL 182/T182
MAINTENANCE MANUAL
/
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RADIATOR
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Navigation Components Installation
Figure 201 (Sheet 1)
34-50-00
© Cessna Aircraft Company
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1312
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Figure 201 (Sheet 2)
34-50-00
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B.
5.
Install the NAV Antenna Coupler (Refer to Figure 201).
(1) Put the NAV antenna coupler on the fuselage and attach it with the screws and washers.
(2) Connect the antenna coax connectors to the NAV antenna coupler.
(3) Supply electrical power to the airplane as necessary, and turn the master switch to the ON
position.
KI-209A and KI-208 Navigation Indicators Removal and Installation
NOTE:
The KI-209A Navigation Indicator is the NAV 1 indicator and the KI-208 is the NAV 2 indicator.
Removal and Installation is typical for the NAV 1 and NAV 2 indicators.
A.
Remove the Navigation Indicator (Refer to Figure 201).
(1) Remove the electrical power from the airplane and turn the master switch to the OFF position.
(2) Remove the inboard pilot panel assembly to get access to the rear of the navigation indicator.
Refer to Chapter 31, Instrument and Control Panels - Maintenance Practices.
(3) Disconnect the electrical connector from the navigation indicator.
(4) Remove the screws that attach the navigation indicator to the inboard pilot panel assembly.
(5) Remove the navigation indicator from the airplane.
B.
Install the Navigation Indicator (Refer to Figure 201).
(1) Put the navigation indicator on the inboard pilot panel assembly and attach it with the screws.
(2) Install the electrical connector to the navigation indicator.
(3) Attach the inboard pilot panel assembly to the structure with the screws. Refer to Chapter 31,
Instrument and Control Panels - Maintenance Practices.
(4) Supply the electrical power to the airplane as necessary and turn the master switch to the ON
position.
34-50-00
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Mar 1/2005
CESSNA AIRCRAFT COMPANY
MODEL 182ffl182
MAINTENANCE MANUAL
GIA - 63 INTEGRATED AVIONICS INSTALLATION
I
-
MAINTENANCE PRACTICES
1.General
A. Two GIA-63 Integrated Avionics Units (IAUs) are on the avionics shelf in the tailcone.
B. The units have the communication and navigation receiver/transmitter components to operate the
GPS, NAy, COM, and Glideslope functions. The GIA 63W has the Wide Area Augmentation System
(WAAS) installed. The units are integrated components of the Garmin G1000 avionics system.
2.
GIA - 63 Integrated Avionics Unit Rernoval/installation
A. Remove the Integrated Avionics Unit.
(1) Refer to Chapter 23, Communications - Maintenance Practices
©Cessna Aircraft Company
34-50-1 0
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Janl1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
KLN-89/KLN-89B/KLN-94 GPS - MAINTENANCE PRACTICES
1.
2.
3.
General
A.
Airplanes without the KR-87 ADF System are configured with a KLN-89 GPS Receiver (GPS-VFR)
that includes a GPS database. The GPS receiver is located in the avionics radio panel rack. A MD41230 GPS-NAV selector is located on the annunciator and GPS panel assembly located above the
avionics radio panel.
B.
Airplanes with the KR-87 ADF System are configured with a KLN-89B GPS Receiver (GPS-IFR) that
includes a GPS data cartridge. The GPS receiver is located in the avionics radio panel rack. A MD41228 GPS-NAV selector is located on the annunciator and GPS panel assembly, located above the
avionics radio panel.
C.
The GPS uses a KA-92 GPS Antenna located above the cabin at FS 43.45, in the general proximity
of the COMM antennas.
GPS Receiver Removal and Installation
A.
Remove GPS Receiver (Refer to Figure 201).
(1) Remove electrical power from airplane and turn the master switch to "OFF".
(2) Loosen single hex screw, located in recessed hole on face of GPS receiver, counterclockwise.
Continue turning hex screw until unit is free to be removed from avionics radio panel rack.
(3) Pull GPS receiver from radio panel rack and remove from airplane.
B.
Install GPS Receiver (Refer to Figure 201).
(1) Place GPS receiver in radio panel rack and slide forward, engaging fixed electrical connectors
and coax connector.
(2) Secure unit to avionics radio panel rack by turning hex screw in a clockwise direction until tight.
(3) Restore electrical power to airplane as required and turn the master switch to "ON".
KA-92 GPS Antenna Removal and Installation
A.
Remove GPS Antenna (Refer to Figure 201).
(1) Remove electrical power from airplane and turn the master switch to "OFF".
(2) Remove screws securing GPS antenna to fuselage skin.
(3) Carefully lift GPS antenna and disconnect coax connector from GPS antenna.
NOTE:
Secure coax cable using a tie strap, tape, or other suitable material, to prevent
connector from slipping through the opening in the fuselage once disconnected from
GPS antenna.
(4) Remove GPS antenna and gasket from airplane.
B.
Install GPS Antenna (Refer to Figure 201).
(1) Place GPS antenna gasket in position on fuselage skin.
(2) Position GPS antenna at coax connector opening in fuselage and connect coax connector to
GPS antenna.
(3) Remove material used to secure coax cable.
(4) Secure GPS antenna to fuselage skin with screws.
(5) Restore electrical power to airplane as required and turn the master switch to "ON".
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April 1/2002
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MODEL 182/T182
MAINTENANCE MANUAL
GPS RECEIVER
LOCKING SCREW
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KLN-89/KLN-89B GPS Installation
Figure 201 (Sheet 1)
34-51-00
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April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
KR-87 ADF SYSTEM - MAINTENANCE PRACTICES
1.
2.
3.
General
A.
This section gives removal and installation procedures for the Kl-227 ADF indicator, KR-87 ADF
receiver, and KA-44B ADF antenna.
B.
On airplanes without Garmin G1000, the KR-87 ADF receiver is installed in the avionics panel radio
rack. The KA-44B ADF antenna is installed on the bottom fuselage below the cabin at FS 39.31 and
RBL 3.75. Use the KR-87 ADF receiver to tune the KR-87 system. Indications are shown on the
Kl-227 ADF indicator, located to the left of the receiver on the inboard pilot panel assembly below the
navigation indicators.
C.
On airplanes with Garmin G1000, the KR-87 ADF receiver is installed on the instrument panel to the
right of the multi-function display (MFD). The ADF antenna is installed on the bottom fuselage below
the cabin at FS 39.31 and RBL 3.75. To tune the KR-87 ADF system, use the KR-87 ADF receiver.
All indications are shown on the G1000 primary-flight display (PFD).
KR-87 ADF Receiver Removal/Installation (Airplanes without Garmin G1000)
A.
ADF Receiver Removal (Refer to Figure 201).
(1) Remove electrical power from airplane and turn the master switch to off. Disengage the ADF
circuit breaker on the avionics circuit breaker panel.
(2) Loosen the single locking screw located in the recessed hole on the face of the receiver.
(3) Pull the ADF receiver from the radio rack and remove from airplane.
B.
ADF
(1)
(2)
(3)
KR-87 ADF Receiver Removal/Installation (Airplanes with Garmin G1000)
A.
B.
4.
Receiver Installation (Refer to Figure 201).
Put the ADF receiver in the radio rack and slide it forward to engage the fixed electrical plug.
Tighten the single locking screw located in the recessed hole on the face of the receiver.
Connect electrical power to the airplane as needed and turn the master switch to ON. Engage
the ADF circuit breaker on the avionics circuit breaker panel.
(4) Do an operational test of the ADF receiver.
(5) Remove electrical power from the airplane and turn the master switch to off. Disengage the ADF
circuit breaker on the avionics circuit breaker panel.
ADF Receiver Removal (Refer to Figure 202).
(1) Remove electrical power from the airplane and turn the master switch to off. Disengage the ADF
circuit breaker on the avionics circuit breaker panel.
(2) Loosen the single locking screw located in the recessed hole on the face of the receiver.
(3) Carefully pull the ADF receiver and the bezel from the instrument panel to disengage the
electrical connector (P1602) from the ADF receiver.
(4) Remove the ADF receiver, with the bezel, from the airplane.
ADF Receiver Installation (Refer to Figure 202).
(1) Carefully put the bezel on the rear of the ADF receiver and pull it forward evenly until it is in
position directly behind the face of the ADF receiver.
(2) Put the ADF receiver in position in the instrument panel and slide it forward to engage the
electrical connector (P1602) with the ADF receiver.
(3) Tighten the single locking screw located in the recessed hole on the face of the receiver.
(4) Connect electrical power to the airplane as needed and turn the master switch to ON. Engage
the ADF circuit breaker on the avionics circuit breaker panel.
(5) Do an operational test of the ADF receiver.
(6) Remove electrical power from the airplane and turn the master switch to off. Disengage the ADF
circuit breaker on the avionics circuit breaker panel.
KA-44B ADF Antenna Removal/Installation
A.
ADF Antenna Removal (Refer to Figure 201).
(1) Remove electrical power from airplane and turn the master switch to off.
34-52-00
© Cessna Aircraft Company
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Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
I
.
A.
.
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0710T1001
A0718T1001
B0518T1043
KR-87 ADF Installation
Figure 201 (Sheet 1)
34-52-00
© Cessna Aircraft Company
Page 202
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
KR-87
ADF
RECEIVER
BEZEL
LOCKING
SCREW
r
0000
DETAIL A
AIRPLANES WITH THE
GARMIN G1000
0710T1001
A1218T1001A
KR-87 ADF Installation
Figure 202 (Sheet 1)
34-52-00
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Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
(2) Remove the screws that attach the ADF antenna to the fuselage skin.
(3) Disconnect the antenna connector (PC600) from the ADF antenna.
(4) Remove the ADF antenna from the airplane.
B.
5.
ADF Antenna Installation (Refer to Figure 201).
(1) Connect the electrical connector (PC600) to the ADF antenna.
(2) Attach the ADF antenna to the fuselage skin with the screws.
Kl-227 ADF Indicator Removal/Installation
A.
B.
ADF Indicator Removal (Refer to Figure 201).
(1) Remove electrical power from airplane and turn the master switch to off.
(2) Remove the inboard pilot panel assembly to gain access to the ADF indicator. Refer to Chapter
31, Instrument and Control Panels - Maintenance Practices.
(3) Disconnect the electrical connector (P1603) from the ADF indicator.
(4) Remove the screws that attach the ADF indicator to the inboard pilot panel assembly.
(5) Remove the ADF indicator from the airplane.
ADF Indicator Installation (Refer to Figure 201).
(1) Put the ADF indicator on the inboard pilot panel assembly and attach with the screws.
(2) Connect the electrical connector (P1603) to the ADF indicator.
(3) Attach the inboard pilot panel assembly to the structure with the screws. Refer to Chapter 31,
Instrument and Control Panels - Maintenance Practices.
34-52-00
© Cessna Aircraft Company
Page 204
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti 82
MAINTENANCE MANUAL
KT-76C TRANSPONDER
-
MAINTENANCE PRACTICES
1.General
A.
2.
The KT-76C (Mode C) Transponder is installed in the avionics panel radio rack. The CI-105
Transponder Antenna is installed on the bottom of the fuselage at FS 86.50 and RBL 2.50.
KT-76C Transponder Removal and Installation
A.
B.
3.
Remove Transponder (Refer to Figure 201).
(1) Remove electrical power from airplane and turn the master switch to "OFF".
(2) Loosen single hex screw, located in recessed hole on face of transponder, counterclockwise.
Continue turning hex screw until unit is free to be removed from avionics radio panel rack.
(3) Pull transponder from avionics radio panel rack and remove from airplane.
Install Transponder (Refer to Figure 201).
(1) Place transponder in avionics radio panel rack and slide forward, engaging fixed electrical
connector (PI800) and coax connector (PI1001).
(2) Secure unit to avionics radio panel rack by turning hex screw in a clockwise direction until tight.
(3) Restore electrical power to airplane as required and turn the master switch to "ON".
CI-105 Transponder Antenna Removal and Installation
A.
Remove Transponder Antenna (Refer to Figure 201).
(1) Remove electrical power from airplane and turn the master switch to "OFF".
(2) Remove antenna access plate (231 EB) to gain access to the antenna . Refer to Chapter 6,
Access/Inspection Plates - Description and Operation for plate identification.
(3) Remove nuts and washers securing transponder antenna to fuselage.
NOTE:
B.
I
Identify locations of washers for use during transponder antenna installation.
(4) From outside of airplane, support transponder antenna and remove coax connector (PC1006)
from transponder antenna.
(5) Remove transponder antenna from airplane.
Install Transponder Antenna (Refer to Figure 201 )
(1) Position transponder antenna at opening in fuselage for coax connector. Connect coax
connector (PCi1006) to transponder antenna.
(2) Place transponder antenna studs through fuselage and secure to fuselage with nuts and
washers.
(3) Verify proper electrical bonding of doubler surface and transponder antenna.
(4) Install the antenna access plate (231 EB). Refer to Chapter 6, Access/Inspection Plates -
~
~~~Description and Operation for plate identification.
(5) Restore electrical power to airplane as required and turn the master switch to "ON".
© Cessna Aircraft Company
34-5300
Page 201
Jul 1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti 82
MAINTENANCE MANUAL
DOUBL
LOCKING SCREW
DETAIL A
-ENNA
071 OT1 001
A071BT 1001
8051 8T1042
DETAIL B
KT-76C Transponder Installation
Figure 201 (Sheet 1)
34-53-00
©Cessna Aircraft Company
Page 202
Jul 1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
KT-73 MODE S TRANSPONDER - MAINTENANCE PRACTICES
1.
General
A.
2.
The KT-73 (Mode S) transponder is installed in the avionics-panel radio mounting rack. The
Cl-105 transponder antenna is installed on the bottom of the fuselage. For removal and installation
procedures on the Cl-105 transponder antenna, refer to Chapter 34, KT-76C Transponder Maintenance Practices.
KT-73 Mode S Transponder Removal and Installation
A.
KT-73 Transponder Removal (Refer to Figure 201).
(1) Disconnect the main battery. Refer to Chapter 24, Battery - Maintenance Practices.
(2) Turn the single hex-screw, found in the recessed hole on the face of the transponder,
counterclockwise.
(3) Remove the single hex-screw from the transponder.
(4) Pull the transponder from the radio mounting rack.
(5) Disconnect the coaxial cable and electrical connector from the transponder.
(6) Remove the transponder from the airplane.
B.
KT-73 Transponder Installation (Refer to Figure 201).
(1) Put the transponder in the avionics radio mounting rack.
(2) Connect the electrical connector and the coaxial cable.
(3) Put the single hex-screw in the recessed hole on the face of the transponder and turn it clockwise
until it is tight.
(4) Do a test of the KT-73 transponder.
34-53-01
© Cessna Aircraft Company
Page 201
Jan 2/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
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Figure 201 (Sheet 1)
34-53-01
© Cessna Aircraft Company
Page 202
Jan 2/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
GTX - 33 TRANSPONDER - MAINTENANCE PRACTICES
1.
General
A.
B.
2.
3.
The maintenance practices give the removal and installation procedures for the transponder, which is
installed on the avionics shelf in the tailcone.
The GTX-33 Transponder is an integrated component of the Garmin G1000 avionics system. The
transponder is operated and monitored through the use of the Control Display Units (CDU's).
GTX - 33 Transponder Removal/Installation
A.
Remove the Transponder (Refer to Figure 201).
(1) Set the MASTER switch and AVIONICS switch to the off position.
(2) Remove the tailcone access/inspection plate (310AR) to get access to the NAV/COM units.
Refer to Chapter 6, Access/Inspection Plates - Description and Operation.
(3) Turn the quarterturn fastener 90 degrees counterclockwise and lift the locking lever to disengage
the transponder.
(4) Move the transponder aft out of the mounting rack.
(5) Remove the transponder from the airplane.
B.
Install the Transponder (Refer to Figure 201).
(1) Put the transponder in position with the locking lever stud in the mounting rack slot.
(2) Push the locking lever down and turn the quarter turn fastener 90 degrees clockwise to attach
the transponder to the mounting rack.
(3) Install the tailcone access/inspection plate (310AR). Refer to Chapter 6, Access/Inspection
Plates - Description and Operation.
(4) Do a check of the transponder to make sure it operates correctly. Refer to the Garmin G1000
Line Maintenance Manual.
Transponder Antenna Removal/Installation
A.
Remove the Transponder Antenna (Refer to Figure 202).
(1) Set the MASTER switch and AVIONICS switch to the off position.
(2) Remove the screws that attach the antenna to the bottom of the fuselage.
(3) Disconnect the coaxial cable from the antenna (PC1006).
B.
Install the Transponder Antenna (Refer to Figure 202).
(1) Attach the coaxial cable to the antenna (P1006).
(2) Put the transponder antenna in position on the bottom of the fuselage.
(3) Attach the antenna with screws.
34-53-10
© Cessna Aircraft Company
Page 201
Mar 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
nose
I:
INTEGRATED
AVIONICS UNIT
(COMM 1)
INTEGRATED
AVIONICS UNIT
(COMM 2)
-1-
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VIEW A-A
LOOKING FORWARD AT FS 140
AIRPLANES THAT HAVE
THE GARMIN G1000
0710T1001
A0714T1044
Tailcone Avionics Installation
Figure 201 (Sheet 1)
34-53-10
© Cessna Aircraft Company
Page 202
Mar 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
oozer
t
A
COAX CONNECTOR
(PC1 006)
DOUBLER
*USELAGE
SKIN
NDER
DETAIL
A
0710T1001
A0718T1064
Transponder Antenna Installation
Figure 202 (Sheet 1)
34-53-10
© Cessna Aircraft Company
Page 203
Mar 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
GDL-69A FIS - DESCRIPTION AND OPERATION
1.
General
A.
The GDL-69A Flight Information System (FIS) is a remote-mounted component of the Garmin G 1000
avionics system. The GDL-69A gives weather and FIS information to the pilot. The information is
controlled and seen through the Multi-Function Display (MFD). Information is sent from the data link
receiver to the MFD through the high-speed data bus ethemet data path.
With a current subscription, XM satellite radio service is available with the GDL-69A. The signals that
the data link receives from satellites give better coverage than land-based transmissions. The XM
radio is tuned through the MFD. Analog audio is sent to the audio panel and shares the AUX music
input with the external audio entertainment input.
GDL-69A capabilities include:
·
Graphical NEXRAD Data (NEXRAD)
Graphical METAR Data (METAR)
·
Textual METAR Data
Textual Terminal Aerodrome Forecasts (TAF)
City Forecast Data
·
Graphical Wind Data (WIND)
Graphical Echo Tops (ECHO TOP)
·
Graphical Cloud Tops (CLD TOP)
Graphical Lightning Strikes (XM LTNG)
Graphical Storm Cell Movement (CELL MOV)
NEXRAD Radar Coverage (displayed with NEXRAD data)
SIGMETs/AIRMETs (SIG/AIR)
·
Surface Analysis with City Forecasts (SFC)
County Warnings (COUNTY)
Freezing Levels (FRX LVL)
Hurricane Track (CYCLONE)
Temporary Flight Restrictions (TFR).
B.
The GDL-69A XM Weather Data Link is the receiver for the FIS, and is installed behind the instrument
panel. It is a remote sensor.
C.
The CI-2480 antenna for the GDL-69A FIS is installed on the left upper surface of the fuselage at FS
65.33.
34-54-00
©Cessna Aircraft Company
Page 1
Jan 2/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
GDL-69A FIS - MAINTENANCE PRACTICES
1.
General
A.
2.
The maintenance practices give the removal and the installation procedures for the GDL-69A XM
Weather Data Link. For removal and installation of the CI-2480 antenna for the GDL-69A Flight
Information System (FIS), refer to Chapter 23, Communications - Maintenance Practices.
GDL-69A XM Weather Data Link Removal/Installation
A.
Data Link Removal (Refer to Figure 201).
(1) Set the MASTER switch and the AVIONICS switch to the off position.
(2) Remove the GDU 1040 Multi-Function Display (MFD) unit. Refer to Chapter 34, Control Display
Unit - Maintenance Practices.
(3) Turn the quarter-turn fastener 90 degrees counterclockwise and lift the locking lever to disengage
the data link.
(4) Move the data link aft out of the mounting rack.
(5) Remove the data link from the airplane.
B.
Data
(1)
(2)
(3)
(4)
Link installation (Refer to Figure 201).
Inspect the connector for damaged pins.
Carefully push the data link into the rack to engage the connector.
Put the data link in position with the locking lever stud in the mounting rack slot.
Push the locking lever down and turn the quarter-turn fastener 90 degrees clockwise to attach
the data link to the mounting rack.
(5) Install the GDU 1040 MFD unit. Refer to Chapter 34, Control Display Unit - Maintenance
Practices.
(6) Set the MASTER switch and the AVIONICS switch to the ON position.
(7) Do a check of the GDL-69A XM Weather Data Link FIS to make sure that it operates correctly.
Refer to the Garmin G1000 Line Maintenance Manual, Revision D or later.
34-54-00
O Cessna Aircraft Company
Page 201
Jan 2/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
NOTE:
THE INSTRUMENT PANEL
IS SHOWN WITH THE
MULTI-FUNCTION DISPLAY
(MFD) SCREEN REMOVED.
ENGINE
O
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0710T1001
A3930T368
GDL-69A XM Weather Data Link Installation
Figure 201 (Sheet 1)
34-54-00
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Page 202
Jan 2/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
DME - MAINTENANCE PRACTICES
1.
General
A.
2.
3.
On airplanes with Garmin G1000, the KN-63 distance measuring equipment (DME) gives range,
speed, and time-to-station information displayed through the G1000 display system. The KN-63 DME
has a remote-mounted receiver in the rear fuselage at FS 172.10. The DME antenna is on the bottom
fuselage below the cabin at FS 114.50.
KN-63 DME Receiver Removal/Installation
A.
KN-63 DME Receiver Removal (Refer to Figure 201).
(1) Set the MASTER and the AVIONICS switches to the off position.
(2) Disengage the DME/ADF circuit breaker on the avionics circuit breaker panel.
(3) Remove the right, aft cabin panel for access to the DME receiver unit.
(4) Disconnect the electrical connector (PT1031) from the receiver.
(5) Disconnect the electrical connector (PT801) from the receiver.
(6) Remove the screws that attach the receiver to the support bracket.
(7) Remove the receiver from the airplane.
B.
KN-63 DME Receiver Installation (Refer to Figure 201).
(1) Install the receiver with the connectors toward the front of the airplane.
(2) Put the DME receiver in position.
(3) Put the four screws through the receiver at the two holes in the front plate tab and the two slots
in the rear plate tab.
(4) Attach the receiver to the support bracket assembly with the screws.
(5) Make sure that there is a correct electrical bond between the unit and the airplane structure.
(6) Attach the electrical connector (PT801) to the DME receiver.
(7) Attach the electrical connector (PT1031) to the DME receiver.
(8) Install the right, aft cabin panel.
(9) Set the MASTER and the AVIONICS switches to the ON position.
(10) Engage the DME/ADF circuit breaker on the avionics circuit breaker panel.
DME Antenna Removal/Installation
A.
DME Antenna Removal (Refer to Figure 202).
(1) Set the MASTER and the AVIONICS switches to the off position.
(2) Disengage the DME/ADF circuit breaker on the avionics circuit breaker panel.
CAUTION: Be careful when you remove the nuts from the antenna.
antenna can fall to the ground and as a result, be damaged.
The
(3) Remove the nuts and the washers that attach the DME antenna to the airplane at FS 114.50.
(4) Disconnect the electrical connector (PF1011) from the antenna.
(5) Remove the antenna from the airplane.
B.
DME Antenna Installation (Refer to Figure 202).
(1) Solvent clean the surface of the airplane skin where you will install the antenna.
(2) Put the antenna in position on the airplane skin.
(3) Attach the antenna to the airplane skin with the nuts and the washers.
(4) Make sure that there is a correct electrical bond between the antenna connector and the skin.
(5) Connect the electrical connector (PF1011) to the antenna.
(6) Set the MASTER and the AVIONICS switches to the ON position.
(7) Engage the DME/ADF circuit breaker on the avionics circuit breaker panel.
34-55-00
© Cessna Aircraft Company
Page 201
Jan 2/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
A
I
O 4PX
63
EIVER
ELECTRICAL
CONNECTOR
(PT801)
DETAIL A
0710T1001
A0718T1104
KN-63 DME Receiver Installation
Figure 201 (Sheet 1)
34-55-00
© Cessna Aircraft Company
Page 202
Jan 2/2006
CESSNA AIRCRAFT COMPANY
MODEL 182fT182
MAINTENANCE MANUAL
nJ4^
l
COAX
CONNEC
(PF1011)
-IER
05-16
TENNA
DETAIL A
0710T1001
A0718T1103
DME Antenna Installation
Figure 202 (Sheet 1)
34-55-00
© Cessna Aircraft Company
Page 203
Jan 2/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
KMD-540 MULTI-FUNCTION DISPLAY - MAINTENANCE PRACTICES
1.
General
A.
2.
3.
The KMD-540 Multi-Function Display (MFD) can be installed to give the pilot more situational
awareness during flight. Enhanced Ground Proximity Warning System (EGPWS), and Traffic
Advisory System (TAS) data is given on the color MFD display. Other data, such as Global
Positioning System (GPS) data and weather data can be shown on the display. These displays can
give the pilot more data that is easy to read in a short period of time.
KMD-540 MFD Removal/Installation
A.
KMD-540 MFD Removal (Refer to Figure 201).
(1) Disconnect the main battery from the airplane. Refer to Chapter 24, Battery - Maintenance
Practices.
(2) Disengage the MFD circuit breaker on the circuit breaker panel.
(3) Remove the screw in the face of the MFD.
(4) Carefully, pull the unit out of the avionics rack.
(5) Disconnect the electrical connector from the MFD.
(6) Remove the MFD from the airplane.
B.
KMD-540 MFD Installation (Refer to Figure 201).
(1) Put the MFD in the avionics rack.
(2) Connect the electrical connector to the MFD.
(3) Install the screw in the face of the MFD.
(4) Engage the MFD circuit breaker on the circuit breaker panel.
(5) Connect the main battery to the airplane. Refer to Chapter 24, Battery - Maintenance Practices.
(6) Do an operational check of the MFD.
KMD-540 MFD Operational Check
A.
MFD
(1)
(2)
(3)
(4)
(5)
(6)
(7)
Operational Check.
Set the MASTER ALT/BAT switch to the ON position.
Set the AVIONICS master switch to the ON position.
Turn the ON/OFF knob on the KMD-540 MFD to the ON position.
Make sure that the KMD-540 title page comes on the screen.
Turn the ON/OFF knob on the KMD-540 MFD to the OFF position.
Set the AVIONICS master switch to the off position.
Set the MASTER ALT/BAT switch to the off position.
34-60-01
© Cessna Aircraft Company
Page 201
Jan 2/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
A ..NA
I
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A1218T1070
KMD-540 MFD Installation
Figure 201 (Sheet 1)
34-60-01
0 Cessna Aircraft Company
Page 202
Jan 2/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
CONTROL DISPLAY UNIT - MAINTENANCE PRACTICES
Airplanes with Garmin G1000
1.
General
A.
2.
The Control Display Unit (CDU) is a flat screen display which is removed and installed by quick
release fasteners and an electrical connector attached to the back. A Garmin Display Unit (GDU-1040)
operates as the CDU. The left display serves as the Primary Function Display (PFD). The right display
serves as the Multi-Function Display (MFD). Each display is able to give the same information as
the other if needed. The displays incorporate the processors that move data through the different
components of the integrated system.
Control Display Unit Removal/Installation
A.
Remove the Control Display Unit (CDU) (Refer to Figure 201).
(1) Disengage the applicable PFD or MFD circuit breaker for the CDU.
(2) Disconnect the quick release fasteners from the CDU.
(3) Carefully pull the CDU from the instrument panel and disconnect the electrical connector that is
attached to the back of the CDU.
B.
Install the CDU (Refer to Figure 201).
(1) Connect the electrical connector to the back of the CDU and put the CDU in the instrument panel.
(2) Attach the CDU to the instrument panel with the quick release fasteners.
(3) Engage the applicable PFD or MFD circuit breaker for the CDU.
(4) Make sure the applicable CDU operates correctly. Refer to the Garmin G1000 Line Maintenance
Manual.
34-60-10
© Cessna Aircraft Company
Page 201
Mar 1/2004
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
-- -
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(PFD)
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Figure 201 (Sheet 1)
34-60-10
© Cessna Aircraft Company
Page 202
Mar 1/2004
CHAPTER
OXYGEN
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
LIST OF EFFECTIVE PAGES
CHAPTER-SECTION-SUBJECT
PAGE
DATE
35-Title
35-List of Effective Pages
35-Record of Temporary Revisions
35-Table of Contents
35-00-00
Page 1
Jul 3/2006
35-01-00
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Mar 1/2005
35-01-00
Pages 201-208
Jul 3/2006
35 - 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
OXYGEN - GENERAL..........
.........
...........
............................
S cope......................................................................
Tools, Equipment and Materials ..............................................
Definition...................................................................
OXYGEN - DESCRIPTION AND OPERATION .........
..........................
Description and Operation ...................................................
OXYGEN - MAINTENANCE PRACTICES
.........
.........
.....................
General ....................................................................
Precautions ......... ...... .........
.........
...............................
Replacement of Components .........
.........
..............................
Oxygen Release Indicator Disc...............................................
Oxygen Cylinder Inspection Requirements ..........
..........................
Oxygen Mask Inspection.............................
.......................
Oxygen Mask Maintenance .........
.........................................
Oxygen System Functional Testing ...........................................
System Leak Test ............................
...............................
Oxygen System Charging....................................................
© Cessna Aircraft Company
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
OXYGEN - GENERAL
1.
Scope
A.
2.
This chapter provides information on components associated with storage and distribution of oxygen
to crew and passengers.
Tools, Equipment and Materials
NOTE:
I
Equivalent substitutes may be used for the following items:
NAME
NUMBER
MANUFACTURER
USE
Teflon
Lubricating
Tape
S1465
Commercially Available
To lubricate threads
and fittings.
Trichloroethylene
ASTM D4080
Commercially Available
To clean oxygen
lines.
Naphtha
TT-N-95
Commercially Available
Flush oxygen lines.
Anti-Icing
Fluid
TT-1-735
Commercially Available
Flush oxygen lines.
Sherlock
Leak Detector
Type CG (MIL-PRF-25567
Oxygen leak detector, Type 1)
Lub-O-Seal Co. Inc.
17519 Lewis Dr.
Cypress, TX 77433
To do a leak test of
the oxygen system.
Flow rater (0
to 10 Liters
per Minute
LPM)
Commercially Available
Check pressure flow
to passenger mask.
Pressure
Gage (0-100
PSIG)
Commercially Available
To check oxygen
flow.
Oxygen
Outlet
Adapter
Commercially Available
Used with pressure
gage.
Merthiolate
Commercially Available
To clean oxygen
mask's and hose.
3.
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.
35-00-C(
© Cessna Aircraft Company
Page 1
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
OXYGEN - DESCRIPTION AND OPERATION
1.
Description and Operation
A.
The system has an oxygen cylinder and regulator assembly, filler valve, pressure gage, pressure lines,
outlets, and mask assemblies. The oxygen cylinder is attached aft of the baggage compartment. The
pilot's mask supply line gives a larger flow of oxygen than the passenger mask supply lines. The
pilot's mask has a microphone, keyed by a switch button on the pilot's control wheel. The filler valve
is found on the left side of the tailcone.
WARNING: Do not let oil, grease, or other lubricants near high-pressure
oxygen because it can cause a fire. Do not smoke or have an open
flame in or near the airplane while you work on the oxygen system.
B.
Oxygen flow to the outlet ports starts when the oxygen control valve knob, located in the overhead
console, is put in the ON position and mask hoses are connected to the overhead oxygen ports.
Each oxygen port has a spring-loaded valve which prevents the flow of oxygen until a mask
hose is connected. Each mask hose has an oxygen flow indicator for visual proof of oxygen
flow.
The oxygen system has an emergency release indicator with a green disc installed. The green disc will
be pushed out if there is too much oxygen pressure in the system. When there is too much pressure
in the oxygen system, a safety disc inside the oxygen regulator will release oxygen from the oxygen
tank to the emergency release indicator. The oxygen pressure will then push out the green disc and
release oxygen outside the airplane. The indicator disc will release oxygen at a pressure of 80 psi
+30 or -30 psi (551 kPa +208 or -208 kPa).
(1) The emergency release indicator is installed inside the tailcone on the left side. The green
indicator disc can be seen when it is not removed, from the outside of the airplane on the left
side of the tailcone.
(2) A indicator disc that has been removed shows a possible problem. Refer to Oxygen Maintenance Practices.
NOTE:
C.
Airplanes T18208309 and on do not have an emergency release indicator disc installed.
These airplanes have a vent found in the tailcone for emergency oxygen release.
The information that follows is found on the shoulder, neck, or top head of the oxygen cylinder to help
in correct identification.
(1) Cylinder specification followed by service pressure. For example, ICC or DOT-E8162.
(2) Cylinder serial number. This is found below or directly after the cylinder specification. The
symbol of the purchaser, user, or maker, if registered with the Bureau of Explosives, can be
found directly below the serial number. The cylinder serial number can possibly be found in an
alternative location on the cylinder top head.
(3) Inspector's official mark. This is found near the serial number.
(4) Date of manufacture. This is the date of the first hydrostatic test. For example, 6-98 for June
1998. The dash between the month and the year figures can be replaced with the mark of the
inspection agency or agency doing the test. For example, 6L98.
(5) Hydrostatic test date. The dates of subsequent hydrostatic tests must be steel-stamped (month
and year) directly below the original manufacturer date. The dash between the month and year
figures can be replaced with the mark of the testing agency.
(6) A Cessna identification placard. This is found near the center of the cylinder body.
(7) Halogen test stamp (if applicable). The phrase "Halogen Tested," the date of the test (month,
day, and year), and the inspector's mark is found below the Cessna identification placard.
NOTE:
D.
35-01-00
© Cessna Aircraft Company
Page 1
Mar 1/2005
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
OXYGEN - MAINTENANCE PRACTICES
1.
General
A.
2.
Before you do maintenance on the oxygen system, you must read and understand these maintenance
practices.
Precautions
WARNING: Do not smoke or have an open flame near the airplane while you do
maintenance on the oxygen system. Make sure all electrical power is
disconnected and that the airplane is correctly grounded. Oils, grease,
and solvents can burn or explode when near to oxygen under pressure.
A.
B.
C.
Make sure every port on the system is always fully clean and free of water, oil, grease, and solvent
contamination.
Put a cap on all openings immediately after you remove a component. Do not use tape or caps which
will cause moisture to collect.
Lines and fittings must be clean and dry. One of the methods that follow can be used to clean lines.
CAUTION: Most air compressors are lubricated with oil, and a minimum amount
of oil can be carried by the airstream into the system. Use a waterlubricated compressor to blow tubing clean only when nitrogen or argon
is not available. The air must be clean, dry, and filtered.
(1) Wash with a vapor-degreasing solution of stabilized trichloroethylene that conforms to MIL-T7003. Then blow tubing clean with a jet of nitrogen gas (BB-N-411) Type 1, Class 1, Grade A or
Technical Argon (MIL-A-18455).
(2) Flush with naptha that conforms to Specification TT-N-95. Then blow clean and dry with clean,
dry filtered air.
(3) Flush with anti-icing fluid that conforms to MIL-F-5566 or anhydrous ethyl alcohol. Rinse
thoroughly with fresh water and dry with a jet of nitrogen gas (BB-N-411) Type 1, Class 1,
Grade A or Technical Argon (MIL-A-18455).
(4) Flush with hot inhibited alkaline cleaner until free from oil and grease. Rinse with fresh water
and dry with a jet of nitrogen gas (BB-N-411) Type 1, Class 1, Grade A or Technical Argon
(MIL-A-18455). Put a cap on all lines immediately after they are dry.
(5) Do not fabricate pressure lines. Replace lines with factory parts, by part number.
(6) Make sure that your hands are free of dirt and grease before you install the oxygen tubing or
fittings.
35-01-00
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Page 201
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
WARNING: Do not use tools that can cause sparks.
CAUTION: With oxygen bottle charged, do not put the control in the ON position
with outlet ports (low pressure) open to the atmosphere. Damage
to the regulator metering poppet can occur.
CAUTION: When a component of the oxygen system has been removed,
installed, replaced, or the system has been disassembled in any
way, the oxygen system must be purged and a check for leaks
must be done.
D.
Use only S1465 Teflon lubricating tape on threads of male fittings. Do not use lubricating tape on
coupling sleeves or outside of flares. Use care to prevent contamination of Teflon tape with oil, grease,
or other lubricants. The Teflon tape must be used in accordance with the instructions that follow.
(1) Lay the tape on the threads close to the end of the fitting; Apply the tape clockwise on standard
threads and counter-clockwise on the left-hand threads.
(2) Apply enough tension while you wind to make the tape form into thread grooves.
(3) After the installation of the tape is complete, keep tension on the tape and pull it apart in the
direction it was applied. The necessary result is a ragged edge, which makes the tape stay in
place. (If you shear or cut it, the tape can unwind.)
(4) Press the tape well into the threads.
(5) Make connections.
E.
Keep all of the tools used for the installation of the oxygen tubes or fittings free of dirt, grease, and
oils.
NOTE:
3.
An accurate record of the number of recharges must be kept by the owner or his agent if
the cylinder is recharged an average of once every other day or more.
Replacement of Components
A.
Use Figure 201 to help you as you remove and install components in the oxygen system.
NOTE:
Oxygen cylinder and regulator assemblies cannot always be installed in the field exactly
as illustrated in Figure 201, which shows factory installation.
CAUTION: The pressure regulator, pressure gage and line, and filler valve must
be removed and replaced only by personnel familiar with high-pressure
fittings. Obey all maintenance precautions.
B.
Before you remove the cylinder, open the cabin outlets to release the low-pressure line. Disconnect
the push-pull control cable, filler line, pressure gage line, and outlet line from the regulator.
WARNING: Cap all lines immediately.
C.
Filler Valve Removal (Refer to Figure 201).
(1) Remove the line from the quick-disconnect valve at the regulator.
(2) Disconnect the chain, but do not remove the cap from the filler valve.
(3) Remove the screws that attach the valve and disconnect the pressure line.
(4) Cap and seat the pressure line.
(5) Remove the filler valve.
D.
Filler Valve Installation (Refer to Figure 201).
(1) Install the filler valve.
(2) Uncap the pressure line and seat.
(3) Attach the valve with the screws and connect the pressure line.
(4) Connect the chain.
(5) Connect the line to the quick-disconnect valve at the regulator.
35-01-00
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Page 202
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
t
.r.
TEE
DETAIL
A
0710T1001
A0714T1018
B0714T1018
Oxygen System
Figure 201 (Sheet 1)
35-01-00
© Cessna Aircraft Company
Page 203
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1993
BRACKET
TUBE ASSEMBLY
CROSS
SCRI
OXYGEN
OUTLET
ASSEMBLY
DETAIL
B
0710T1001
A0714T1018
Oxygen System
Figure 201 (Sheet 2)
35-01-00
© Cessna Aircraft Company
Page 204
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1994
OXYGEN
BOTTLE
XYGEN
MERGENCY
ELEASE
IDICATOR
MOUr
BRAC
FILLER
VALVE
ASSEMBLY
DETAIL
C
0710T1001
A0714T1018
Oxygen System
Figure 201 (Sheet 3)
35-01-00
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Page 205
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
E.
4.
To remove all of the oxygen system, lower the headliner and remove the soundproofing to get access
to the lines. Refer to Chapter 25 Equipment/Furnishings - Maintenance Practices.
Oxygen Release Indicator Disc
NOTE:
A.
Airplanes T18208309 and On do not have an emergency release indicator disc installed. These
airplanes have a vent found in the tailcone for emergency oxygen release.
A release of the indicator disc can be the result of a malfunction. Do the steps that follow to make sure
the oxygen cylinder operates correctly before you install a new indicator disc. (Refer to Figure 201).
(1) Look at the indication on the oxygen gage in the overhead console. If the indication on the
gage shows the oxygen cylinder is less than full, then fill the cylinder. Refer to Oxygen System
Charging.
(a) Look at the oxygen gage to see if it fills with oxygen.
(b) If the cylinder will not fill with oxygen, then you must replace the oxygen cylinder or you
must do an overhaul. Refer to Replacement of Components.
NOTE:
(c)
The oxygen cylinder and regulator are removed and installed together as one
assembly.
A Scott Aviation approved service center must do the overhaul. Contact Scott Aviation at
(716) 686-1666 to find an approved service center.
NOTE:
The phone number for Scott Aviation after close of business hours is (716) 6835100.
(2) To install a new indicator disc, press the disc past the snap ring in the oxygen release indicator
fitting found in the left side of the tailcone.
(3) Do a functional test of the oxygen system. Refer to Oxygen Function Test.
5.
Oxygen Cylinder Inspection Requirements
A.
6.
Oxygen Mask Inspection
A.
7.
Oxygen Cylinder Inspection (Refer to Figure 201).
(1) Do an inspection of the full external surface of the cylinder for an indication of damage.
(a) Make sure to carefully examine the neck of the cylinder for cracks, distortion, or damaged
threads.
(2) Complete an inspection of the cylinder to see if markings are clear.
(3) Complete an inspection of the date of the last hydrostatic test. If the test date is expired, do not
let the cylinder go back to service until the test has been done.
(4) Complete an inspection of the cylinder mounting bracket, bracket hold-down bolts, and cylinder
holding straps for cracks, deformation, a clean surface, and correct attachment.
(5) Do a check for signs of interference, chafing, deformation, or deterioration in the area adjacent
to where the cylinder is stored and attached.
Oxygen Mask Inspection.
(1) Do a check of the oxygen masks for fabric cracks and rough face seals.
(2) Flex the mask hose gently all over and check for signs of deterioration or dirt.
(3) Do an examination of the mask and hose storage compartment for cleanliness and general
condition.
Oxygen Mask Maintenance
A.
Oxygen Mask Cleaning and Care.
(1) Clean and disinfect the mask assemblies after use, as applicable. Use care to avoid damage to
the microphone assembly while you clean and sterilize the mask assemblies.
(2) Wash the mask and the hose with a mild soap solution and rinse it with clean water.
35-01-00
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MODEL 182/T182
MAINTENANCE MANUAL
(3) To sterilize, rub the mask and hose with a gauze or sponge soaked in a water and merthiolate
solution. This solution must contain 1/5 teaspoon of merthiolate per one quart of water. Wipe
the mask and hose with a clean cloth and air dry.
(4) Make sure that each mask breathing tube end is free of nicks and that the tube end will fit into
the cabin oxygen receptacle easily and will not leak.
(5) If a mask assembly has leaks, you cannot breathe through it, or has a damaged microphone,
return the mask assembly to the manufacturer or a repair station.
(6) Replace the hose if it shows signs of deterioration.
8.
Oxygen System Functional Testing
A.
9.
After the regulator and the cylinder assembly have been replaced or overhauled, do the flow and
internal leakage tests that follow to make sure that the system operates correctly.
(1) Fully charge the oxygen system in accordance with the procedures outlined in this section.
(2) Disconnect the line and the fitting assembly from the pilot's mask and the line assembly. Put the
outlet end of the line and the fitting assembly into the cabin outlet and attach the opposite end
of the line to a pressure gage (the gage must be calibrated in one-pound increments from 0 to
100 PSI). Put the control lever in the ON position. The gage pressure should read 75 PSI, +10
or-10 PSI.
(3) Put the mask and the line assemblies into all remaining cabin outlets. With oxygen flowing from
all outlets, the test gage pressure must still be 75 PSI, +10 or -10 PSI.
(4) Put the oxygen control lever in the OFF position and let the test gage pressure fall to 0 PSI.
Remove all the adapter assemblies, but do not remove the one with the pressure gage. The
pressure must not rise above 0 PSI after one minute. Remove the pressure gage and the adapter
from the oxygen outlet.
(5) If you do not get the specified pressure readings when you do this test, remove and replace the
cylinder regulator assembly and do the test again.
(6) Connect the mask and the line assemblies to each cabin outlet and do a check of each mask
for correct operation.
(7) Do a check of the pilot's mask microphone and control wheel switch for correct operation. After
the check, return all of the masks to the mask case.
(8) Recharge the oxygen system in accordance with these procedures.
System Leak Test
A.
When there are leaks in the system, you must find the opening. Frequently you can find leakage if
you listen for the hissing of gas as it escapes. If you cannot hear the oxygen as it escapes, you must
soap test all of the lines and connections with a Castile soap and water solution or specified leak-test
material. Make the solution sufficiently thick to stay on the contours of the fittings. At the end of the
leakage test, remove all of the leak detector or soap and water solution.
CAUTION: Do not try to tighten the connections while the system is charged.
10. Oxygen System Charging
A.
Charge Oxygen System (Refer to Figure 201).
WARNING: Be sure to ground the aircraft and the equipment used to service
the system before you charge the oxygen system.
(1) Use only aviator's breathing oxygen per MIL-0-27210 to charge the oxygen system.
(2) Do not charge the oxygen cylinders if the equipment fittings used to service the system or the
filler valve is corroded or contaminated. If necessary, clean with stabilized trichloroethylene and
let air dry. Do not let the solvent enter the internal parts.
(3) If the cylinder is empty, do not charge, as the cylinder must then be removed, inspected, and
cleaned.
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MODEL 182/T182
MAINTENANCE MANUAL
CAUTION: A cylinder which is empty can be contaminated. The regulator
and cylinder assembly must then be disassembled, inspected, and
cleaned by an FAA approved facility before filling. Contamination,
as used here, means dirt, dust, or foreign material, or air in large
quantities. If a gage line or filler line is disconnected and you
put caps on all of the fittings immediately, no contamination of
the cylinder will occur unless temperature variation has caused
a suction in the cylinder. Air contains water vapor which can
condense and freeze. Since there are very small orifices in the
system, it is very important that this condition not occur.
(4) Connect the charging cylinder line from the oxygen service cart to the filler valve.
(5) Slowly open the valve on the oxygen service cart and charge the airplane oxygen bottle to correct
the pressure. Refer to Table 1 for charging pressures at different temperatures.
(6) Ambient temperature listed in the chart is the air temperature in the area where the system is to
be charged. Filling pressure refers to the pressure to which aircraft cylinders must be filled. This
table gives approximations only and assumes a rise in temperature of approximately 25° F,due
to heat of compression. This table also assumes the aircraft cylinders will be filled as quickly
as possible and that they will only be cooled by ambient air; no water bath, or other means of
cooling can be used.
Table 201. Oxygen Cylinder Filling Pressures
Ambient Temp.
(Degrees F)
Filling Pressure (psig)
Ambient Temp.
(Degrees F)
Filling Pressure (psig)
0
1650
50
1875
10
1700
1925
20
1725
60
70
30
1775
80
2000
40
1825
90
2050
1975
NOTE 1: Example: If ambient temperature is 70° F,fill the aircraft cylinders to approximately 1,975 psi or as
close to this pressure as the gage can read. When they cool, cylinders must have approximately
1,850 psi pressure.
35-01-00
© Cessna Aircraft Company
Page 208
Jul 3/2006
CHAPTER
VACUUM
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
LIST OF EFFECTIVE PAGES
CHAPTER-SECTION-SUBJECT
PAGE
DATE
37-00-00
Page 1
April 1/2002
37-10-00
Pages 101-103
April 1/2002
37-10-00
Pages 201-209
Jan 2/2006
37-Title
37-List of Effective Pages
37-Record of Temporary Revisions
37-Table of Contents
37 - 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
VACUUM SYSTEM - GENERAL...................................................
Sco p e ......................................................................
Definition ...................................................................
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VACUUM SYSTEM - TROUBLESHOOTING
.....................................
General ....................................................................
37-10-00 Page 101
37-10-00 Page 101
VACUUM SYSTEM - MAINTENANCE PRACTICES.................................
Description and Operation ...................................................
Vacuum Pump Removal/Installation ..........................................
Vacuum Manifold Removal/Installation ........................................
Vacuum Regulator Filter Removal/Installation..................................
Gyro Filter Removal/Installation .............................................
Vacuum Gage Removal/Installation...........................................
Vacuum Transducer Removal/Installation .....................................
Vacuum Manifold Test (For airplanes with the Parker Airborne manifold) .........
Vacuum Pressure Adjustment/Test (For airplanes with the Parker Airborne regulator
valve or the Aero Accessories regulator valve) .............................
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© Cessna Aircraft Company
Page
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
VACUUM SYSTEM - GENERAL
1.
Scope
A.
2.
This chapter describes those units and components used to provide vacuum necessary to operate
the artificial horizon and directional gyros.
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 distribution describes those components used in the distribution of vacuum air.
(2) The section on indicating describes those components used to indicate relative vacuum pressure
in the system.
© Cessna Aircraft Company
37-00-00
Page 1
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
VACUUM SYSTEM - TROUBLESHOOTING
1.
General
A.
A troubleshooting chart has been provided to aid the maintenance technician in system
troubleshooting. Refer to Figure 101.
37-10-00
© Cessna Aircraft Company
Page 101
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1316
OIL IN DISCHARGE.
CHECK FOR DAMAGED
ENGINE DRIVE SEAL.
REPLACE SEAL.
HIGH SUCTION GAGE READINGS.
GYROS FUNCTION NORMALLY.
I
CHECK FOR CLOGGED
RELIEF VALVE FILTER. IF -
DEFECTIVE GAGE.
OK, CHECK FOR DEFECTIVE GAGE.
REPLACE GAGE.
INOT
OK, REPLACE
NOT OK, REPLACE
FILTER.
FILTER.
Vacuum System Troubleshooting Chart
Figure 101 (Sheet 1)
37-10-00
© Cessna Aircraft Company
Page 102
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1317
I
LOW SUCTION GAGE READINGS. I
ACU
CHCKFR
CHECK FOR VACUUM
REGULATOR LEAKING. IF
-
I
OK, CHECK FOR VACUUM PUMP
FAILURE. REPLACE PUMP.
NC)T OK, REPLACE VACUUM
REGULATOR.
LOW PRESSURE.
I
CHECK FOR VACUUM
REGULATOR LEAKING. IF-
I
OK, CHECK FOR VACUUM PUMP
FAILURE. REPLACE PUMP.
NOT OK, REPLACE SAFETY
VALVE.
Vacuum System Troubleshooting Chart
Figure 101 (Sheet 2)
37-10-00
© Cessna Aircraft Company
Page 103
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
VACUUM SYSTEM - MAINTENANCE PRACTICES
1.
2.
Description and Operation
A.
The vacuum system has a filter, vacuum gage, vacuum instruments, regulator valve, vacuum manifold,
low vacuum annunciator switches, engine-driven vacuum pumps, and related plumbing.
B.
On airplanes without Garmin G1000, the source of vacuum air is in the cabin and is pulled through
the system by the engine-driven vacuum pumps. This air goes through the gyro filter at the cabin
inlet source before it goes through the vacuum gage and gyro instruments. The vacuum is controlled
by the regulator valve. The regulator valve is on the aft side of the firewall. The vacuum air is then
pulled through the vacuum manifold and past the low vacuum annunciator switches and then into the
vacuum pumps.
C.
On airplanes without Garmin G1000, vacuum pressure is measured by the low vacuum annunciator
switches in the engine compartment. The vacuum gage in the instrument panel shows the vacuum
pressure.
(1) The vacuum gage gives a direct indication of the system vacuum in inches of mercury (in.hg.).
(2) The low vacuum annunciator switches are part of the panel annunciator warning system.
(a) If the left vacuum switch (SN012) senses a vacuum below 3.0 in.hg., the VAC annunciator
will show L VAC.
(b) If the right vacuum switch (SN011) senses a vacuum below 3.0 in.hg., the VAC annunciator
will show VAC R.
(c) If both switches sense a vacuum below 3.0 in.hg., the VAC annunciators will show L VAC
R.
(3) For more information on the maintenance practices for the panel-mounted annunciator (UI005),
refer to Chapter 31, Annunciator Panel - Maintenance Practices.
D.
On airplanes with Garmin G1000, the source of vacuum air is in the cabin and is pulled through
the system by the engine-driven vacuum pump. The vacuum pressure is measured by a vacuum
transducer. The air goes through the gyro filter at the cabin inlet source before it is goes through the
horizon gyro indicator. The vacuum is controlled by the regulator valve. The regulator valve and the
vacuum transducer are on the aft side of the firewall.
Vacuum Pump Removal/Installation
NOTE:
Removal/installation is typical for the vacuum pumps.
A.
Vacuum Pump Removal (Refer to Figure 201).
(1) Remove the engine cowl. Refer to Chapter 71, Cowl - Removal/Installation.
(2) Remove the cooling shroud.
(3) Disconnect the hoses from the inlet and outlet ports of the vacuum pump.
(a) Put caps on the hoses and the vacuum pump ports to prevent entry of foreign object debris.
(4) Remove the nuts, lock washers, and flat washers that attach the vacuum pump to the engine.
(5) Remove the vacuum pump from the engine.
(6) Remove the elbow from the pump.
(7) Replace any damaged fittings or nuts.
B.
Vacuum Pump Installation (Refer to Figure 201).
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MODEL 182/T182
MAINTENANCE MANUAL
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Vacuum System Installation
Figure 201 (Sheet 1)
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1981
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Figure 201 (Sheet 2)
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B2176
C
VIEW A-A
AIRPLANES WITH GARMIN G1000
VACUUM
TRANSDUCER
REPLACEMENT
HORIZON GYRO
INDICATOR
REGULATOR
VALVE
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PUMP
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Figure 201 (Sheet 3)
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
CAUTION: Do not install a vacuum pump that has been dropped or shows that
it was incorrectly held in a vise.
CAUTION: Do not use any cork type gaskets when the vacuum pump is
installed.
CAUTION: Make sure all unwanted material is removed from the system.
Foreign object debris will cause damage to the vacuum system
components.
CAUTION: Hold the pump housing by the flange and protect the flange with
soft material such as aluminum, copper, or wood if a vise is used.
The pump housing must never be set in a vise with pressure applied
across the center of the housing. The pressure will cause damage
to the carbon rotor.
CAUTION: Do not use Teflon tape, pipe dope, or thread lubricants of any type.
Particles of contamination will cause damage to the vacuum system
components.
(1) Put the vacuum pump in a jaw protected vise, with the drive coupling downward.
(2) Tighten the elbow in the pump by hand.
(3) Use only a box end wrench to tighten the fittings to the necessary position. Do not make more
than 1.5 turns beyond the hand tight position
(4) Make sure the pump and engine surfaces are clean and free of any old gasket material.
(5) Set the new pad gasket on the studs of the engine.
(6) Put the vacuum pump on the studs.
(7) Attach the pump to the engine with the flat washers, new lock washers, and nuts.
(8) Torque and tighten the nuts in a cross pattern to 70 inch-pounds, +10 or -10 inch-pounds (7.9
Nm, +1.1 or- 1.1 Nm).
(9)
(10)
(11)
(12)
I
(13)
(14)
3.
I
(a) To torque the nuts, fabricate a torque wrench adapter (Refer to Figure 202).
1
Weld a 3/8 inch drive to a 7/16 inch wrench with a 12 point cut out in the box end of
the wrench.
2
The wrench length must be 2.25 inches (57.15 mm) from the center of box end to the
center of the drive.
Connect the hose to the inlet and the outlet ports of the vacuum pump.
Put the hose in position so that the exhaust from the vacuum pump is not pointed at the magnetos
or the electrical wiring.
Install the cooling shroud.
Operate the engine and examine the indication on the vacuum gage. Refer to the Pilot's
Operating Handbook and FAA Approved Airplane Flight Manual.
Adjust the indication on the vacuum gage, if necessary. Refer to the vacuum pressure
adjustment/test.
Install the upper engine cowl. Refer to Chapter 71, Cowl - Removal/Installation.
Vacuum Manifold Removal/Installation
NOTE:
Airplanes with Garmin G1000 do not have vacuum manifolds.
NOTE:
Removal/Installation is typical for the vacuum manifolds.
A.
Vacuum Manifold Removal (Refer to Figure 201).
(1) Remove the engine cowl. Refer to Chapter 71, Cowl - Removal/Installation.
(2) Remove the hoses from the vacuum manifold.
(3) Put a label on the applicable electrical connector (SN012 left, SN011 right).
(4) Disconnect the applicable electrical connector from the vacuum manifold.
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MODEL 1821T182
MAINTENANCE MANUAL
B814
A
FABRICATED TORQUE WRENCH
ADAPTOR
-
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END
Vacuum Pump Torque Wrench Adapter
Figure 202 (Sheet 1)
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
(5) Loosen the B-nut that attaches the vacuum manifold to the nipple in the firewall.
(6) Remove the vacuum manifold from the airplane.
B.
4.
5.
Vacuum Regulator Filter Removal/Installation
A.
Vacuum Regulator Filter Removal (Refer to Figure 201).
(1) Remove the pilot seat. Refer to Chapter 25, Front Seats - Maintenance Practices.
(2) Remove the vacuum regulator filter.
B.
Vacuum Regulator Filter Installation (Refer to Figure 201).
(1) Install the vacuum regulator filter.
(2) Install the pilot seat. Refer to Chapter 25, Front Seats - Maintenance Practices.
Gyro Filter Removal/Installation
A.
B.
6.
Vacuum Manifold Installation (Refer to Figure 201).
(1) Attach the vacuum manifold to the nipple in the firewall and tighten the B-nut.
(2) Connect the applicable electrical connector (SN012 left, SN011 right) to the vacuum manifold.
(3) Connect the hoses to the vacuum manifold and attach with the clamps.
(4) Install the upper engine cowl. Refer to Chapter 71, Cowl - Removal/Installation.
Gyro Filter Removal (Refer to Figure 201).
(1) Remove the bolt and the retainer from the mount and remove the gyro filter.
Gyro Filter Installation (Refer to Figure 201).
(1) Put the gyro filter and the retainer on the mount and attach with the bolt.
Vacuum Gage Removal/Installation
NOTE:
Airplanes with Garmin G1000 do not have a vacuum gage.
NOTE:
A.
B.
7.
The vacuum gage and ammeter operate together as a single instrument.
Vacuum Gage Removal (Refer to Figure 201).
(1) Disconnect the vacuum and air hoses from the vacuum gage.
(2) Disconnect the electrical connector (JI019) from the vacuum gage.
(3) Remove the screws that attach the vacuum gage to the instrument panel and remove the vacuum
gage.
Vacuum Gage Installation (Refer to Figure 201).
(1) Install the vacuum gage in the instrument panel.
(2) Attach with the screws.
(3) Connect the electrical connector (JI019) to the vacuum gage.
(4) Connect the vacuum and air hoses to the vacuum gage.
Vacuum Transducer Removal/Installation
NOTE:
A.
B.
Only airplanes with the Garmin G1000 have a vacuum transducer.
Vacuum Transducer Removal (Refer to Figure 201).
(1) Remove the center panel. Refer to Chapter 31, Instrument and Control Panels - Maintenance
Practices.
(2) Remove the screw and clamp that hold the vacuum transducer in position.
(3) Remove the vacuum transducer.
Vacuum Transducer Installation (Refer to Figure 201).
(1) Install the vacuum transducer.
(2) Install the screw and clamp that hold the vacuum transducer in position.
(3) Install the center panel. Refer to Chapter 31, Instrument and Control Panels - Maintenance
Practices.
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MODEL 182/T182
MAINTENANCE MANUAL
8.
Vacuum Manifold Test (For airplanes with the Parker Airborne manifold)
A.
9.
The vacuum manifold must be tested periodically to determine its condition and serviceability. Refer
to Chapter 5, Inspection Time Limits for inspection intervals. Refer to Parker Hannifin Corporation/
Airborne Division's Product Reference Memo #39 (or latest revision) for the procedures.
Vacuum Pressure Adjustment/Test (For airplanes with the Parker Airborne regulator valve or the
Aero Accessories regulator valve)
NOTE:
Before the adjustment procedure, the entire pneumatic system must be inspected and tested for
leaks, restrictions, and unserviceable components. Failure to correct all system anomalies will
lead to reduced dry air pump service life.
A.
Prepare the System for the Test (Refer to Figure 201).
(1) Remove the gyro (central air) filter.
B.
Do a Check of the Regulator Valve.
CAUTION: Make sure that the temperature of the engine does not go above the
maximum engine temperature during the adjustment/test of the regulator
valve.
NOTE:
At engine speeds between 1200 RPM and full throttle, suction must fall between 4.5 in.hg.
and 5.5 in.hg. (green range on gage).
(1) Start the engine, warm up to the normal operating temperature, and run at static RPM. Refer to
Pilot's Operating Handbook and FAA Approved Airplane Flight Manual.
(2) Make sure the suction gage indication does not go above 5.5 in.hg.
(3) Run the engine at 1200 RPM and make sure the gage indication does not go below 4.5 in.hg.
(4) If the suction indication falls outside of the range, shut down the engine and adjust the regulator
valve in the steps that follow.
(a) Bend the locking tab upward on the lower surface of the regulator valve.
CAUTION: Be careful when you turn the adjustment screw. Do not turn
it too much in either direction. When you turn it too much in
either direction, damage can occur to the equipment.
(b) Turn the adjustment screw on the lower surface of the regulator valve in the direction to
increase or decrease the pressure as necessary.
NOTE:
As you face the adjustment screw, when you turn it clockwise the pressure
increases. When you turn it counterclockwise, the pressure decreases.
(c) Tap the regulator after you adjust it to help reset the components.
(d) Bend the locking tab downward to keep the adjustment screw in place when the correct
pressure has been set.
(5) Run the engine at static RPM and make sure the gage indication does not go above 5.5 in.hg.
(6) Run the engine at 1200 RPM and make sure the gage indication does not go below 4.5 in.hg.
(7) Shut down the engine.
(a) For airplanes without the Garmin G1000, make sure that the L VAC R lights come on.
(b) For airplanes with the Garmin G1000, make sure that the low vacuum annunciator visual
and aural warnings come on.
(8) Attach the filter element to the gyro (central air) filter.
(9) Before you start the engine, make sure that the low vacuum annunciations are on.
(a) For airplanes without the Garmin G1000, make sure that the L VAC R lights are on.
(b) For airplanes with the Garmin G1000, make sure that the low vacuum annunciator visual
warning is on.
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MAINTENANCE MANUAL
(10) Run the engine for a final time at static RPM and observe the indication on the suction gage.
(a) If the indication falls noticeably after the filter is installed, replace the filter.
(11) Reduce the engine speed to 1200 RPM and make sure that the suction stays in the green range
(does not fall below 4.5 in.hg.). and that the low vacuum annunciations are off.
(a) For airplanes without the Garmin G1000, make sure that the L VAC R lights go off.
(b) For airplanes with the Garmin G1000, make sure that the low vacuum annunciator visual
and aural warnings go off.
(12) Shut down the engine.
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CHAPTER
STANDARD
PRACTICES STRUCTURES
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
LIST OF EFFECTIVE PAGES
CHAPTER-SECTION-SUBJECT
PAGE
DATE
51 -Title
51-List of Effective Pages
51-Record of Temporary Revisions
51-Table of Contents
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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
STRUCTURES - GENERAL ......................................................
S cope......................................................................
Definition ...................................................................
STRUCTURES - DESCRIPTION AND OPERATION ................................
Description .................................................................
CORROSION - DESCRIPTION AND OPERATION..................................
G eneral...................................................................
Characteristics of Corrosion..................................................
Types of Corrosion ..........................................................
Typical Corrosion Areas .....................................................
Corrosion Detection.........................................................
Corrosion Damage Limits ....................................................
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
STRUCTURES - GENERAL
1.
Scope
A.
2.
This chapter provides a description of general airplane structures and corrosion characteristics. For
repair of structural members and repair techniques used throughout the airplane, refer to the Single
Engine Models 172, 182, T182, 206, and T206 1996 and On Structural Repair Manual.
Definition
A.
This chapter is divided into two sections briefly described below.
(1) The section on structures provides an overall description of the airplane structure and methods
of construction used on the airplane.
(2) The section on corrosion provides a general description of corrosion characteristics, types of
corrosion and typical corrosion areas.
© Cessna Aircraft Company
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
STRUCTURES - DESCRIPTION AND OPERATION
1.
Description
A.
The fuselage is of semimonocoque construction and consists of three major sections: forward
section, center section, and tailcone section. Construction consists of formed bulkheads, longitudinal
stringers, reinforcing channels and skin. Frame members of the cabin section are constructed of
formed bulkhead channels. Bulkheads are formed "U" channel sections. Principal material is 20240 alclad aluminum alloy which, after forming, is heat treated to a 2024-T42 condition and painted
with epoxy primer. All bulkheads in the fuselage are constructed of formed sheet metal or reinforced
sheet metal.
B.
The wings are of all-metal, strut-braced, semi monocoque construction, utilizing two spars. Each wing
consists of an outer wing panel with an integral fuel bay, an aileron and a flap. Flanged upper and
lower edges of all ribs serve as cap- strips, in addition to providing rigidity to the rib. The skin, riveted
directly to each rib flange, provides the cellular strength for each successive rib bay. The nose, center,
and trailing edge rib segments are riveted together through the front and rear spars to form the basic
airfoil sections. Alclad stringers stiffen the skin between ribs. Spars are comprised of machine milled,
tapered extrusions riveted to sheet metal webs.
C.
The full cantilever, all-metal tail group consists of a vertical stabilizer and rudder, and a horizontal
stabilizer and elevators. The horizontal stabilizer is of one-piece construction, consisting of spars,
ribs and skins. Elevators are constructed of aluminum spars, ribs and skin panels. The skin panels
are riveted to ribs and spars. A balance weight is located in the outboard end of each elevator, forward
of the hinge line. An elevator trim tab, attached to the elevator, is constructed of a spar, ribs, and skin;
all riveted together. The vertical stabilizer is constructed of a forward spar, an aft spar, ribs and skin.
The rudder is constructed of spars, ribs and skin panels. The rudder trim tab is constructed of a spar,
ribs, and skin; all riveted together.
D.
The main landing gear is constructed of 6150 alloy spring steel tubing with attaching parts of high
strength 7075-T73 aluminum alloy forgings. Nose gear components are 4130, 6150 alloy steel and
7075-T73 aluminum alloy forgings.
E.
The engine mount is constructed of welded 4130 steel tubing.
F.
The engine cowling consists of upper and lower formed aluminum sections. The upper section
includes an oil inspection/filler door, and the lower section includes an air induction scoop with an
engine induction system air filter. Both sections are removable.
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MODEL 182/T182
MAINTENANCE MANUAL
CORROSION - DESCRIPTION AND OPERATION
1.
General
A.
2.
Characteristics of Corrosion
A.
3.
This section describes corrosion so the maintenance technician can identify the various types of
corrosion and apply preventative measures to minimize corrosion activity. For corrosion control and
corrosion damage, refer to the Single Engine Structural Repair Manual 1996 and On.
Corrosion is a natural phenomenon which destroys metal by chemical or electrochemical action and
converts it to a metallic compound, such as an oxide, hydroxide, or sulfate. All metals used in airplane
construction are subject to corrosion. Attack may take place over an entire metal surface, if exposed,
or it may be penetrating in nature, forming deep pits. It may follow grain boundaries or it may penetrate
a surface at random. Corrosion may be accentuated by stresses from external loads or from lack
of homogeneity in the metallic structure or from improper heat treatment. It is promoted by contact
between dissimilar metals or with materials which absorb moisture, such as wood, rubber, felt, dirt,
etc.
(1) The following conditions must exist for electrochemical corrosion to occur. Refer to Figure 1 for
an illustration of electrochemical corrosion.
(a) There must be a metal that corrodes and acts as the anode.
(b) There must be a less corrodible metal that acts as the cathode.
(c) There must be a continuous liquid path between the two metals which acts as the
electrolyte, usually condensation and salt or other contamination.
(d) There must be a conductor to carry the flow of electrons from the cathode to the anode.
This conductor is usually in the form of a metal-to-metal contact (rivets, bolts, welds, etc.)
(2) The elimination of any one of the four conditions described above will stop the corrosion reaction
process.
(3) One of the best ways to eliminate one of the four described conditions is to apply an organic
film (such as paint, grease, plastic, etc.) to the surface of the metal affected. This will prevent
the electrolyte from connecting the cathode to the anode, and current cannot flow, therefore,
preventing corrosion reaction. Refer to Figure 1 for a typical organic film application.
(4) At normal atmospheric temperatures, metals do not corrode appreciably without moisture, but
the moisture in the air is usually enough to start corrosive action.
(5) The initial rate of corrosion is usually much greater than the rate after a short period of time.
This slowing down occurs because of the oxide film that forms on the metal's surface. This film
tends to protect the metal underneath.
(6) When components and systems constructed of many different types of metals must perform
under various climatic conditions, corrosion becomes a complex problem. Salt on metal surfaces
(from sea coast operation) greatly increases the electrical conductivity of any moisture present
and accelerates corrosion.
(7) Other environmental conditions which contribute to corrosion are:
(a) Moisture collecting on dirt particles.
(b) Moisture collecting in crevices between lap joints, around rivets, bolts and screws.
Types of Corrosion
A.
Corrosion Types.
(1) Direct Surface Attack - The most common type of general surface corrosion results from direct
reaction of a metal surface with oxygen in the atmosphere. Unless properly protected, steel
will rust and aluminum and magnesium will form oxides. The attack may be accelerated by salt
spray or salt-bearing air, by industrial gases or by engine exhaust gases.
(2) Pitting - While pitting can occur in any metal, it is particularly characteristic of passive materials,
such as the alloys of aluminum, nickel and chromium. It is first noticeable as a white or gray
powdery deposit similar to dust, which blotches the surface. When the deposits are cleaned
away, tiny pits can be seen in the surface.
(3) Dissimilar Metal Corrosion - When two dissimilar metals are in contact and are connected by an
electrolyte (continuous liquid or gas path), accelerated corrosion of one of the metals occurs.
The most easily oxidized surface becomes the anode and corrodes. The less active member
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MODEL 182/T182
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B815
SIMPLIFIED CORROSION CELL
UNBROKEN PAINT FILM
NO CONTACT BETWEEN ELECTROLYTE AND ANODE AND ICATHODE
UNRKNPITFL
ELECTRON CONDUCTOR METAL
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CORROSION ELIMINATION BY APPLICATION OF ORGANIC FILM
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Corrosion Identification
Figure 1 (Sheet 1)
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(4)
(5)
(6)
4.
of the couple becomes the cathode of the galvanic cell. The degree of attack depends on the
relative activity of the two surfaces; the greater the difference in activity the more severe the
corrosion. Relative activity in descending order is as follows:
(a) Magnesium and its alloys.
(b) Aluminum alloys 1100, 3003, 5052, 6061, 220, 355, 356, cadmium and zinc.
(c) Aluminum alloys 2014, 2017, 2024, 7075 and 195.
(d) Iron, lead and their alloys (except stainless steel).
(e) Stainless steels, titanium, chromium, nickel, copper, and their alloys.
(f) Graphite (including dry film lubricants containing graphite).
Intergranular Corrosion - Selective attack along the grain boundaries in metal alloys is referred to
as intergranular corrosion. It results from lack of uniformity in the alloy structure. It is particularly
characteristic of precipitation hardened alloys of aluminum and some stainless steels. Aluminum
extrusions and forgings in general may contain nonuniform areas, which in turn may result in
galvanic attack along the grain boundaries. When attack is well advanced, the metal may blister
or delaminate, which is referred to as 'exfoliation'.
Stress Corrosion - This results from the combined effect of static tensile stresses applied
to a surface over a period of time. In general, cracking susceptibility increases with stress,
particularly at stresses approaching the yield point, and with increasing temperature, exposure
time and concentration of corrosive ingredients in the surrounding environment. Examples
of parts which are susceptible to stress corrosion cracking are aluminum alloy bell cranks
employing pressed-in taper pins, landing gear shock struts with pipe thread-type grease fittings,
clevis joints and shrink fits.
Corrosion Fatigue - This is a type of stress corrosion resulting from the cyclic stresses on a metal
in corrosive surroundings. Corrosion may start at the bottom of a shallow pit in the stressed area.
Once attack begins, the continuous flexing prevents repair of protective surface coating or oxide
films and additional corrosion takes place in the area of stress.
Typical Corrosion Areas
A.
This section lists typical areas of the airplane which are susceptible to corrosion. These areas should
be carefully inspected at periodic intervals to detect corrosion as early as possible.
(1) Engine Exhaust Trail Areas.
(a) Gaps, seams and fairings on the lower right side of the fuselage, aft of the engine exhaust
stack, are typical areas where deposits may be trapped and not reached by normal cleaning
methods.
(b) Around rivet heads, skin laps and inspection covers on the airplane lower fuselage, aft of
the engine secondary exhaust stack, should be carefully cleaned and inspected.
(2) Battery Box and Battery Vent Opening.
(a) The battery, battery cover, battery box and adjacent areas, especially areas below
the battery box where battery electrolyte may have seeped, are particularly subject to
corrosive action. If spilled battery electrolyte is neutralized and cleaned up at the same
time of spillage, corrosion can be held to a minimum by using a weak boric acid solution
to neutralize the battery electrolyte (ni-cad battery) or baking soda solution to neutralize
the lead acid-type battery electrolyte. If boric acid or baking soda is not available, flood
the area with water.
(3) Steel Control Cables (including Stainless Steel).
(a) Checking for corrosion on control cables is normally accomplished during the preventative
maintenance check. During preventative maintenance, broken wires and wear of the
control cables are also checked.
(b) If the surface of the cable is corroded, carefully force the cable open by reverse twisting
and visually inspect the interior. Corrosion on the interior strands of the cable constitutes
failure and the cable must be replaced. If no internal corrosion is detected, remove loose
external rust and corrosion with a clean, dry, coarse-weave rag or fiber brush.
NOTE:
Do not use metallic wools or solvents to clean installed cables. Use of metallic
wool will embed dissimilar metal particles in the cables and create further
corrosion. Solvents will remove internal cable lubricant, allowing cable strands
to abrade and further corrode.
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After thorough cleaning of the exterior cable surface, apply a light coat of lubricant (VV-L800) to the external cable surface.
(4) Internal Fuel Tanks.
(a) The presence of soil contamination (a brown slimy substance) and pitting-type corrosion
may occur in the lower areas of the integral fuel tanks of certain airplanes. This condition
can cause a general degradation of some top coating and some depolymerization and
loosening of sealant materials in lower areas.
(b) The contaminants resemble normal aluminum corrosion products, including a considerable
quantity of iron. The brown, slimy deposits are microbial in nature. Examination of the
corrosion pits by metallurgical techniques indicate the presence of intergranular attacks.
(c)
5.
Corrosion Detection
A.
6.
Corrosion Defoliation. The primary means of corrosion detection is visual, but in situations where
visual inspection is not feasible, other techniques must be used. The use of liquid dye penetrant,
magnetic particle, X-ray and ultra-sonic devices can be used, but most of these sophisticated
techniques are intended for the detection of physical flaws within metal objects, rather than the
detection of corrosion.
(1) Visual Inspection. A visual check of the metal surface can reveal the signs of corrosive attack,
the most obvious of which is a corrosive deposit. Corrosion deposits of aluminum or magnesium
are generally a white or grayish-white powder, while the color of ferrous compounds varies from
red to dark reddish-brown.
(a) The indications of corrosive attack are small, localized discolorations of the metal surface.
Surfaces protected by paint or plating may only exhibit indications of more advanced
corrosive attack by the presence of blisters or bulges in the protective film. Bulges in lap
joints are indications of corrosive build-up which is well advanced.
(b) In many cases the inspection area is obscured by structural members, equipment
installations or, for other reasons, are awkward to check visually. In such cases, mirrors,
borescope or similar devices can be used to inspect the obscured areas. Any means
which allows a thorough inspection can be used. Magnifying glasses are valuable aids
for determining whether or not all corrosive products have been removed during clean up
operations.
(2) Liquid Dye Penetrant Inspection. Inspection for large stress-corrosion or corrosion fatigue cracks
on nonporous or nonferrous metals may be accomplished using dye penetrant processes. The
dye applied to a clean metallic surface will enter small openings or cracks by capillary action.
After the dye has an opportunity to be absorbed by any surface discontinuity, the excess dye is
removed and a developer is applied to the surface. The developer acts like a blotter and draws
the dye from cracks or fissures back to the surface, giving visible indication of any fault that is
present on the surface. The magnitude of the fault is indicated by the quantity of dye brought
back to the surface by the developer.
Corrosion Damage Limits
A.
Following cleaning and inspection of the corroded area, the actual extent of the damage may
be evaluated using the following general guidelines and good, sound maintenance judgement.
Determine the degree of corrosion damage (light, moderate, or severe) with a dial-type depth gage,
if accessibility permits. If the area is inaccessible, clay impressions, or any other means which will
give accurate results, should be used. In the event the corrosion damage is severe, contact Cessna
Propeller Aircraft Product Support for assistance.
(1) Light Corrosion - Characterized by discoloration or pitting to a depth of approximately 0.001 inch
maximum. This type of damage is normally removed by light hand-sanding or a minimum of
chemical treatment.
(2) Moderate Corrosion - Appears similar to light corrosion except there may be blistering or some
evidence of scaling or faking. Pitting depths may be as deep as 0.010 inch. This type of damage
is normally removed by extensive hand-sanding or mechanical sanding.
(3) Severe Corrosion - General appearance may be similar to moderate corrosion with severe
blistering exfoliation and scaling or flaking. Pitting depths may be as deep as 0.10 inch. This
type of damage is normally removed by extensive mechanical sanding or grinding (if not
complete part replacement).
©Cessna Aircraft Company
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CHAPTER
DOORS
CESSNA AIRCRAIFT COMPANY
MODEL 182/Ti 82
MAINTENANCE MANUAL
LIST OF EFFECTIVE PAGES
CHAPTER-SECTION-SUBJECT
PAGE
DATE
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Jul 3/2006
52-30-00
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Jul 1/2007
52-Title
52-List of Effective Pages
52-Record of Temporary Revisions
52-Table of Contents
52 - 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
DOORS - GENERAL ...............................
Scope....................................
Definition ..................................
CABIN DOORS - DESCRIPTION AND OPERATION.................
Description .................................
Operation..................................
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CABIN DOORS - MAINTENANCE PRACTICES...................
General...................................
Cabin Door Removal/Installation .......................
Cabin Door Weatherstrip Removal/installation .................
Cabin Door Latch Lock Removal/installation ..................
Cabin Door Latch Assembly Removal/installation................
Cabin Door Latch Cable Assembly Installation .................
Cabin Door Lock Assembly Removal/Installation (On airplanes with standard
locks)...................................
Cabin Door Lock Assembly Removal/Installation (On airplanes with Medeco locks)
Cabin Door Lock Cam Assembly Removal/Installation (On airplanes with standard
locks)...................................
Cabin Door Lock Cam Assembly Removal/installation (On airplanes with Medeco
locks)...................................
Cabin Door Adjustment/Test .........................
Cabin Door Latch Cable Assembly Rigging...................
Cabin Door Inside Handle Rigging.......................
Latch Assembly Adjustment/Test .......................
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Page
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208
208
209
209
BAGGAGE DOOR - MAINTENANCE PRACTICES..................
General...................................
Baggage Door Removal/Installation ......................
Baggage Door Weatherstrip Removal/Installation................
Baggage Door Weatherstrip Inspection ....................
Baggage Door Lock Assembly Removal/Installation (On airplanes with Medeco
lock) ...................................
Baggage Door Lock Cam Assembly Removal/installation (On airplanes with
Medeco lock)...............................
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52 - CONTENTS
© Cessna Aircraft Company
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
DOORS - GENERAL
1.
Scope
A.
2.
This chapter provides maintenance information on doors.
instructions and rigging procedures.
Provided are removal/installation
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 cabin door section provides information on removal/installation and rigging of the doors.
(2) The baggage door section provides information on removal/installation.
52-00-00
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MODEL 182/T182
MAINTENANCE MANUAL
CABIN DOORS - DESCRIPTION AND OPERATION
1.
Description
A.
2.
A cabin door is installed on each side of the airplane. Each door has an outer sheet skin that is
chemically bonded to an inner pan assembly. Each door has a latch assembly, an inside handle, a
pair of external hinges, and a doorstop assembly.
Operation
A.
The cabin doors open by the inside or outside handle, that is connected to internal components.
(1) The cabin door latch is a two-part assembly latch base, external handle, spring-loaded latch bolt
and pull-bar assembly, and a spring-loaded catch pin assembly. The interior handle base plate
assembly is directly connected to the cabin door latch by an adjustable push rod assembly. This
push rod assembly has two clamps attached 180 degrees apart on the main rod. These clamps
operate a cable assembly that moves a cable pin from the top aft end of the cabin door into the
aft top door sill.
(2) The door latch exterior handle is extended when the cabin door is open. The handle is held in
position by the spring-loaded latch catch engaged with the latch bolt through the hole in the bolt.
The push rod assembly will move forward. The attached cable assembly will be retracted from
the top door sill with the cable pin in a recess in the pin guide. The interior handle will move
approximately 15 degrees aft of the vertical position.
B.
The cabin doors close and latch by the internal or external handle connected with internal components.
(1) The cabin door moves the catch pin over the actuator attached to the cover plate. The cover
plate is on the rear door post. The catch pin disengages the latch catch from the latch bolt as the
catch pin is moved forward. The latch handle extends and the pull-bar assembly compresses.
The latch handle is pulled in and the latch bolt is moved on the latch striker. The latch striker is
on the rear door post.
(2) The push rod assembly moves aft and moves the cable pin from the pin guide in the door into
the top aft door sill receptacle when the exterior handle is pushed flush with the fuselage skin.
The interior door handle has moved from approximately 15 degrees aft of the vertical position
to approximately 45 degrees forward of the vertical position. The interior handle pushed to the
horizontal position, flush with the armrest, will overcenter the door latch.
C.
The cabin doors have a key lock.
(1) The key lock turns and moves the pin into the exterior latch handle when the cabin door is closed
and the exterior latch handle is flush.
NOTE:
(2)
It is possible to lock the cabin door when the exterior handle is used and the push rod
assembly is not adjusted correctly. The rigging and adjustment procedures must be
used to correctly adjust the push rod.
An optional Medeco lock is installed on the cabin doors on some airplanes.
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Page 1
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
CABIN DOORS - MAINTENANCE PRACTICES
1.
2.
General
A.
The cabin door maintenance practices give procedures for the removal and installation of the cabin
doors, weatherstrip, locks, latches, handles, and cable assemblies.
B.
The cabin door maintenance practices also give procedures for the adjustment and the test of the
cabin door, latch cable, and inside handle.
Cabin Door Removal/Installation
NOTE:
3.
4.
The removal and installation procedures given are for the pilot's door. The procedures for the
copilot's door are typical.
A.
Cabin Door Removal (Refer to Figure 201).
(1) Open the cabin door.
(2) Remove the nut, screw, and spacers from the stop fitting.
(3) Remove the nuts and screws that attach the hinges to the fuselage structure.
(4) Remove the cabin door from the airplane.
B.
Cabin Door Installation (Refer to Figure 201).
(1) Put the cabin door in position and attach the door with the screws and nuts.
(2) Install the screw, spacers, and nut on the stop fitting.
(3) Close and latch the cabin door.
(4) Make sure the cabin door is correctly adjusted. Refer to Cabin Door Adjustment/Test.
Cabin Door Weatherstrip Removal/Installation
A.
Cabin Door Weatherstrip Removal (Refer to Figure 201).
(1) Use a nonmetallic scraper to remove the weatherstrip and adhesive from the door assembly.
(2) Use solvent to remove all remaining adhesive from the door surface.
B.
Cabin Door Weatherstrip Installation (Refer to Figure 201).
(1) Cut the new weatherstrip to the correct length with the used weatherstrip as a template.
(2) Cut a small notch in the butt ends of the new weatherstrip to let water drain.
(3) Put the weatherstrip in position with the notches at the door low point.
(4) Apply a thin, smooth layer of EC-1300L, or equivalent adhesive to the two surfaces.
(5) Let the adhesive dry until it is tacky.
(6) Push the weatherstrip in position.
(7) Do not stretch the weatherstrip around the door corners.
Cabin Door Latch Lock Removal/Installation
Lock Removal (Refer to Figure 201).
cam from the latching side of the locking arm.
washers between the cam and the locking arm.
locking arm pin from the locking arm and the catch base assembly.
A.
Cabin Door Latch
(1) Remove the
(2) Remove the
(3) Remove the
B.
Cabin Door Latch Lock Installation (Refer to Figure 201).
(1) Assemble the locking arm with the locking arm pin.
(a) Put one washer on each side of the locking arm.
(b) Swage the locking arm pin so there is minimum movement between the parts.
(c) Cut the unwanted material from the pin.
(2) Put the locking arm pin into the 0.125 inch (3.2 mm) diameter hole at the catch base assembly.
(3) Align the hole in the locking arm with the hole in the latch base assembly and install the pin.
(4) Put three washers between the cam and the locking arm.
(5) Attach the cam to the latch side of the locking arm.
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
U-
A'
A H
SPA
D
PIN GUIDE
PL
Bl
STOI
ANDLE
DETAIL D
DOOR
PAN
DOOR
SKIN
DETAIL
DETAIL
WEATHERSTRIP
B
CAM
E
LOCK
ASSEMBLY
NUT
071OT1001
t
AS NECESSARY
FOR GOOD SEAL
WASHER
VIEW A-A
^^_H/
~A0711T1023
DETAIL C
AIRPLANES WITH STANDARD LOCK
Cabin Door Installation
Figure 201 (Sheet 1)
52-10-00
© Cessna Aircraft Company
B0711T1025
C0511T1005
A0711T1023
D0711T1027
E0511T1002
Page 202
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1320
CABLE ASSEMBLY
DOOR
E
SHAFT
ASSEMBLY
CLAMP
BOLT
\
G
ATCH
;OVER
PUSHROD
ASSEMBLY
BASE
PLATE
1-1
DETAIL F
r
ARMREST
DOOR
HANDLE
PIN
-**Z"",j
e-11-
OUTSIDE DOOR HANDLE
Cabin Door Installation
Figure 201 (Sheet 2)
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1321
STRIKER
0o
IA
I
I
9
I
DOOR
LATCH
ACTUATOR
DETAIL
H
H0711T1031
Cabin Door Installation
Figure 201 (Sheet 3)
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B6018
BEND THESE TABS TO MAKE SURE
THAT THEY DO NOT TOUCH THE
LATCH HOUSING
C
C
VIEW B-B
AIRPLANES WITH MEDECO LOCK
MACHINE SCREW
LOCKING ARM
SERRATED WASHER
RETAINING WASHER
CAM/PIN
ASSEMBLY
ANTI-ROTATI(
WASHER
SPACER
SHELL
0.75-INCH HEX N
LOCK TUMBLER
ASSEMBLY
VIEW C-C
BB1211T1038
CC1211T1038
LOCK SHOWN IN UNLOCKED POSITION
Cabin Door Installation
Figure 201 (Sheet 4)
52-10-00
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Page 205
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
5.
Cabin Door Latch Assembly Removal/Installation
A.
Cabin Door Latch Assembly Removal (Refer to Figure 201).
(1) Remove the cabin door lock assembly. Refer to Cabin Door Lock Assembly Removal/
Installation.
(2) Remove the rivets that attach the latch base to the door skin.
(3) Remove the screws that attach the latch to the door pan.
(4) Remove the pushrod and bolt.
(5) Pull the latch handle through the cutout in the door skin.
(6) Remove the latch assembly from the airplane.
B.
Cabin Door Latch Assembly Installation (Refer to Figure 201).
(1) Put the latch assembly in the closed position between the door pan and the door skin.
(2) Make sure the cable assembly is forward of the latch base attach plate, and inboard of latch
base cup.
(3) Extend the latch handle through the cutout in the door skin.
(4) Push the latch assembly aft so the bolt and pushrod extend through their related holes.
(5) Release the pushrod so the bolt is fully extended and the handle is flush.
(6) Attach the latch to the door pan with the screws through the base assembly and through the aft
flange of the door pan.
(7) Make sure the door skin dimension around the latch assembly is correct.
CAUTION:
Do not make the holes oversize in the latch base.
(8) Drill eleven 0.128 inch (3.25 mm) diameter holes that align with the latch base.
(9) Make sure the cabin door latch cable assembly rigging and the cabin door inside handle rigging
is done before the latch base is attached to the skin. Refer to Cabin Door Latch Cable Assembly
Adjustment/Test and Cabin Door Inside Handle Rigging.
(10) Attach the latch base to the door skin with rivets.
(11) Install the cabin door lock assembly. Refer to Cabin Door Lock Assembly Removal/Installation.
6.
Cabin Door Latch Cable Assembly Installation
A.
Cabin Door Latch Cable Assembly Removal (Refer to Figure 201).
(1) Remove the screw and clamp that attach the cable assembly to the door.
(2) Remove the plug button.
(3) Remove the pin from the pin guide.
(4) Pull the pin end of the cable from the top of the door.
(5) Remove the nut and clamp from the opposite end of the cable casing.
(6) Remove the cable assembly from the door.
B.
Cabin Door Latch Cable Assembly Installation (Refer to Figure 201).
(1) Attach the clamp and nut one inch (25 mm) from the end of the cable casing on the pin end of
the cable assembly.
(2) Put the pin end of the cable between the door pan and the door skin at the aft end of the door.
(3) Push the pin end of the cable to the top of the door.
(4) Remove the plug button and align the pin of the cable with the pin guide.
(5) Put the pin through the pin guide.
(6) Align the clamp on the cable casing through the hole that is below the 0.875 inch (22.22 mm)
access hole.
(7) Install the screw.
(8) Make sure the cable operates freely.
(a) Add washers as necessary if the cable does not operate freely.
(9) Do the cabin door latch cable assembly rigging. Refer to Cabin Door Latch Cable Assembly
Rigging.
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MODEL 182/T182
MAINTENANCE MANUAL
7.
8.
Cabin Door Lock Assembly Removal/Installation (On airplanes with standard locks)
A.
Cabin Door Lock Assembly Removal (Refer to Figure 201).
(1) Remove the lower door accent panel and main door panel to get access to the cabin door lock
assembly. Refer to Chapter 25, Interior Upholstery - Maintenance Practices.
(2) Remove the armrest door plugs, door panel insert at the armrest, armrest, door handle and
cover plate from the door to get access to the cabin door lock assembly.
(3) Remove the nut and washer.
(4) Remove the cabin door lock assembly.
B.
Cabin Door Lock Assembly Installation (Refer to Figure 201).
(1) Put the cabin door lock assembly in position.
(2) Install the washer and nut.
(3) Install the armrest door plugs, door panel insert at the armrest, armrest, door handle and cover
plate.
(4) Install the lower door accent panel and main door panel. Refer to Chapter 25, Interior Upholstery
- Maintenance Practices.
Cabin Door Lock Assembly Removal/Installation (On airplanes with Medeco locks)
A.
Cabin Door Lock Assembly Removal (Refer to Figure 201).
(1) Remove the lower door accent panel and main door panel to get access to the cabin door lock
assembly. Refer to Chapter 25, Interior Upholstery - Maintenance Practices.
(2) Remove the armrest door plugs, door panel insert, armrest, door handle, and cover plate from
the door to get access to the cabin door lock assembly.
(3) Remove the cotter pin, washer, locking arm, and spacer from the lock assembly.
(4) Remove the hex nut and the anti-rotational washer that attach the lock tumbler assembly to the
door structure and the cam assembly.
(5) Remove the lock assembly from the door.
B.
Cabin Door Lock Assembly Installation (Refer to Figure 201).
(1) Put the cabin door lock assembly in position on the cabin door.
(2) Install the hex nut and the anti-rotational washer that attach the lock tumbler assembly to the
door structure and the cam assembly. Install the anti-rotational washer under the hex nut.
(3) Torque the nut.
(4) Bend the applicable tab on the anti-rotational washer against the flat part of the nut.
(5) Install the spacer, locking arm, washer, and cotter pin that connect the lock assembly to the door
handle.
(6) Bend the applicable tabs on the cam-pin assembly to make sure that they do not touch the latch
housing.
(7) Install the armrest door plugs, door panel insert, armrest, door handle, and cover plate.
(8) Install the lower door accent panel and main door panel. Refer to Chapter 25, Interior Upholstery
- Maintenance Practices.
9.
Cabin Door Lock Cam Assembly Removal/Installation (On airplanes with standard locks)
A.
Cabin Door Lock Cam Assembly Removal (Refer to Figure 201).
(1) Remove the lower door accent panel and main door panel to get access to the cabin door lock
cam assembly. Refer to Chapter 25, Interior Upholstery - Maintenance Practices.
(2) Remove the armrest door plugs, door panel insert at the armrest, armrest, door handle, and
cover plate from the door to get access to the cabin door lock cam assembly.
(3) Remove the cam stop screw from the cabin door lock cam assembly.
(4) Remove the cam assembly.
B.
Cabin Door Lock Cam Assembly Installation (Refer to Figure 201).
(1) Put the cam assembly in position.
(2) Install the cam stop screw with Loctite 242.
(3) Install the armrest door plugs, door panel insert at the armrest, armrest, door handle, and cover
plate.
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MODEL 182/T182
MAINTENANCE MANUAL
(4)
10.
11.
Install the lower door accent panel and main door panel. Refer to Chapter 25, Interior Upholstery
- Maintenance Practices.
Cabin Door Lock Cam Assembly Removal/nstallation (On airplanes with Medeco locks)
A.
Cabin Door Lock Cam Assembly Removal (Refer to Figure 201).
(1) Remove the lower door accent panel and main door panel to get access to the cabin door lock
cam assembly. Refer to Chapter 25, Interior Upholstery - Maintenance Practices.
(2) Remove the armrest door plugs, door panel insert, armrest, door handle, and cover plate from
the door to get access to the cabin door lock cam assembly.
(3) Remove the machine screws, serrated washers, and retaining washer from the cabin door lock
cam assembly.
(4) Remove the cam assembly.
B.
Cabin Door Lock Cam Assembly Installation (Refer to Figure 201).
(1) Put the cam assembly in position.
Install the machine screws, serrated washers, and retaining washer that attach the cam
(2)
assembly to the cabin door lock. Install the machine screws with Loctite 242.
(3) Install the armrest door plugs, door panel insert, armrest, door handle, and cover plate.
(4) Install the lower door accent panel and the main door panel. Refer to Chapter 25, Interior
Upholstery - Maintenance Practices.
Cabin Door Adjustment/Test
A.
Adjust the new cabin doors.
CAUTION: Do not adjust the bonded door flange or the airplane structure with
force. The bonded areas and the structural components can be
damaged.
(1)
B.
Trim the door flange as necessary to get a gap between the door skin and fuselage skin of 0.09
inch (2.3 mm) or less.
Adjust the cabin doors.
NOTE:
(1)
12.
The cabin doors must be smooth with the fuselage skin.
Use the slots at the door latch plate to adjust the latch assembly and the bolt engagement with
the rotary clutch on the door post.
Cabin Door Latch Cable Assembly Rigging
A.
Do the Cabin Door Latch Cable Assembly Rigging (Refer to Figure 201).
(1) Pull the cable tight.
(2) Attach the clamp and the nut to the cable so it aligns with the 0.193 inch (4.9 mm) diameter hole
in the door pan.
(3) Make sure the door latch is open.
(4) Cut the casing of the cable assembly approximately two inches (50 mm) from the clamp bolt on
the push rod assembly.
(5) Put the core of the cable through the clamp.
(6) Pull the core of the cable through the clamp bolt so the pin extends approximately 0.125 inch
(3.2 mm) from the door pan contour.
(7) Cut the core of the cable approximately one inch (25 mm) forward of the push rod clamp.
(8) Attach the two nuts to the push rod clamp bolt.
(9) Make sure the latch operates freely.
If the latch binds up and will not operate freely, remove the cable core from the clamp and
(a)
operate the latch.
(b) Do a check of the cable for possible adjustments that will make the latch operate correctly.
(10) Install the cover assembly.
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MODEL 182/T182
MAINTENANCE MANUAL
~ ~|(11)
13.
Cabin Door Inside Handle Rigging
A.
14.
Do another cable operational check.
Do the Cabin Door Inside Handle Rigging (Refer to Figure 201).
(1) Attach the pushrod assembly to the pull bar and attach it with the pin while the latch is attached
to the door pan.
(2) Do not install the cotter pin.
(3) Make sure the latch is in the closed position.
(4) Remove the pin that connects the push-pull rod to the latch base assembly.
(5) Adjust the rod so a load of 6 to 12 pounds (2.7 to 5.4 kilograms) is necessary at the end of the
inner handle to move it from the closed position to the over center position.
NOTE:
The rod can be turned in or out 180 degree to make the applicable adjustments.
NOTE:
The rod must be attached to the latch assembly before the cabin door inside handle
rigging can be done.
Latch Assembly Adjustment/Test
A.
Do the adjustment of the latch assembly. (Refer to Figure 201).
(1) Make sure the cabin door is installed and fitted to the fuselage before the adjustment/test can
be done.
(2) Make sure the cabin door latch is in the OPEN position before the adjustment/test can be done.
(3) Make sure the door latch operates smoothly and freely.
(4) Make sure the bolt or pull bar are not filed, ground, or sanded in any way.
NOTE:
A noise can be heard when the inside handle is pushed down. It is recommended
that the outside door handle be flush with the door skin, although the noise is heard.
(5) Install shims to adjust the striker plate forward to give a minimal clearance between the bolt and
the striker plate.
NOTE:
This adjustment will make sure that the pushrod will engage the latch catch. It will
also make sure the exterior handle will stay open until the door is closed again when
the door is opened from the outside.
(6) Install shims as necessary below the actuator on the cover assembly.
NOTE:
If the cabin door is too far forward, the door latch will not operate correctly because
the latch assembly pushrod will not cause the bolt to move.
(7) Close the cabin door from inside the airplane.
(8) Make sure the exterior handle is flush with the door skin when you close the door.
(a) If the exterior handle is not flush with the door skin when the door is closed, adjust the
push-pull rod out.
1
Remove the screws and the nuts that attach the base plate to the door.
2
Remove the smaller end of the push-pull rod and turn it 180 degrees.
3
Install the screws and nuts that attach the base plate.
(9) Do a check for slippage between the cable casing and the clamps that attach the cable.
(10) Install the cotter pin in the clevis pin.
52-10-00
© Cessna Aircraft Companv
Page 209
Jul 3/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti 82
MAINTENANCE MANUAL
BAGGAGE DOOR
-
MAINTENANCE PRACTICES
1.General
A. A baggage door is installed on the left side of the airplane, aft of the cabin door. The baggage door
allows access into the baggage area and into the tailcone.
3 B. A rubber weatherstrip is cemented around the edge of the doorsill.
C.
2.
Baggage Door Removal/installation
A. Baggage Door Removal (Refer to Figure 201).
(1) Open the baggage door.
(2) Disconnect the doorstop chain.
(3) Remove the upholstery panel from the door.
(4) Remove the bolts that attach the door to the hinges.
B.
3.
I
An optional Medeco lock is installed on the baggage door on some airplanes.
Baggage Door Installation (Refer to Figure 201).
(1) Put the baggage door in position on the hinges and attach it with the bolts.
(2) Install the upholstery panel to the door.
(3) Connect the door stop chain.
(4) Close the baggage door and do a check for smooth operation.
Baggage Door Weatherstrip Removal/installation
A. Baggage Door Weatherstrip Removal (Refer to Figure 201).
(1) Remove the baggage door.
(2) With a nonmetallic scraper, remove the seal and its adhesive from the doorsill.
~ ~(3)
Remove the adhesive residue and clean the doorsill area with DeSocleanl110Solvent.
B. Baggage Door Weatherstrip Installation (Refer to Figure 201).
(1) Use the old seal or the doorsill area as a guide to measure and cut the new seal to length.
(2) Apply a thin, even coat of EC1300L Adhesive around the circumference of the doorsill area.
(3) Make sure that you put the seam at the bottom center of the doorsill.
(4) Make sure that you do not stretch the seal around the corners of the doorsill.
(5) Press the new seal into the adhesive. Allow the adhesive to cure per the manufacturer's
instructions, and make sure that the seal completely adheres to the doorsill with no gaps
between the seal and the doorsill.
(6) Install the baggage door.
4.
Baggage Door Weatherstrip Inspection
A. Do an Inspection of the Baggage Door Weatherstrip.
(1) Put a 4-inch by 11-inch piece of paper between the baggage door frame and the baggage door.
Close the baggage door. Slowly pull on the paper to make sure there is seal tension. Move the
paper around the perimeter of the door to test the door seal tension.
(2) Remove the paper from the door frame. Make sure that the baggage door is closed. Pour a
gallon of water over the door and tailcone door frame. After the water no longer drips, open the
door and inspect for leaks.
(3) If you find a leak, towel dry the upholstery with a clean, dry towel. Install the weatherstrip again
as necessary to make sure that there are no leaks around the seal area of the baggage door.
5.
Baggage Door Lock Assembly Remnoval/Installation (On airplanes with Medeco lock)
A. Baggage Door Lock Assembly Removal (Refer to Figure 201).
(1) Remove the baggage door panel to get access to the lock assembly of the baggage door. Refer
to Chapter 25, Interior Upholstery - Maintenance Practices.
(2) Remove the 0.75-inch hex nut and the anti-rotational washer that attach the lock tumbler
assembly to the door structure and the cam assembly.
(3) Remove the lock assembly from the door.
52-30-00
© Cessna Aircraft Company
Page 201
Jul 1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti182
MAINTENANCE MANUAL
B13
E-:R
SKIN
bp
viEw A-A
WEATH ER
STRIP
C
n
9.r-INCH (A-9.
mm) ~NOlT(H-1l~
DOORSILL
II
DETAIL
PIN
B
LATCH ASSEMBLY
HIN
DETAIL
DETAIL
D
C
AIRPLANES WITH STANDARD LOCK
051 2T1 004
AA0711T1 007
B051 1T1 003
C0512T1 006
D0712T1 001
Baggage Door Installation
Figure 201 (Sheet 1)
52-30-00
©Cessna Aircraft Company
Page 202
Jul 1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti 82
MAINTENANCE MANUAL
66022
VIEW B-B
AIRPLANES WITH MEDECO LOCK
HEX NUT
LOCK TUMBLER ASSEMBLY
VIEW C-C
LOCK SHOWN IN LOCKED POSITION
B6B0711T1 048
G0071 1T1 048
Baggage Door Installation
Figure 201 (Sheet 2)
52-30-00
©Cessna Aircraft Company
Page 203
Jul 1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/182
MAINTENANCE MANUAL
B.
6.
Baggage Door Lock Assembly Installation (Refer to Figure 201).
(1) Put the baggage door lock assembly in position on the baggage door.
(2) Install the 0.75-inch hex nut and the anti-rotational washer that attach the lock tumbler assembly
to the door structure and the cam assembly. Make sure that the anti-rotational washer is installed
under the 0.75-inch hex nut.
(3) Torque the nut.
(4) Bend the applicable tab on the anti-rotational washer against the flat part of the nut.
(5) Install the baggage door panel to the baggage door. Refer to Chapter 25, Interior Upholstery Maintenance Practices.
Baggage Door Lock Cam Assembly Removal/installation (On airplanes with Medeco lock)
A.
Baggage Door Lock Cam Assembly Removal (Refer to Figure 201).
(1) Remove the baggage door panel to get access to the baggage door lock assembly. Refer to
Chapter 25, Interior Upholstery - Maintenance Practices.
(2) Remove the hex nut and the serrated washer that attach the cam assembly to the baggage door
lock.
(3) Remove the cam assembly.
B.
Baggage Door Lock Cam Assembly Installation (Refer to Figure 201).
(1) Put the cam assembly in position.
(2) Install the hex nut and the serrated washer that attach the cam assembly to the baggage door
lock. Install the hex nut with Loctite 242.
(3) Install the baggage door panel to the baggage door. Refer to Chapter 25, Interior Upholstery Maintenance Practices.
52-30-00
© Cessna Aircraft Company
Page 204
Jul 1/2007
CHAPTER
STABILIZERS
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
LIST OF EFFECTIVE PAGES
CHAPTER-SECTION-SUBJECT
PAGE
DATE
55-Title
55-List of Effective Pages
55-Record of Temporary Revisions
55-Table of Contents
55-00-00
Page 1
April 1/2002
55-10-00
Pages 201-202
April 1/2002
55-30-00
Pages 201-202
April 1/2002
55 - 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
STABILIZERS - GENERAL .......................................................
Scope......................................................................
Definition ...................................................................
55-00-00 Page 1
55-00-00 Page 1
55-00-00 Page 1
G eneral ....................................................................
Horizontal Stabilizer Removal/Installation .....................................
55-10-00 Page 201
55-10-00 Page 201
55-10-00 Page 201
VERTICAL FIN - MAINTENANCE PRACTICES.....................................
G eneral ....................................................................
Vertical Fin Removal/Installation ..........................................
55-30-00 Page 201
55-30-00 Page 201
55-30-00 Page 201
HORIZONTAL STABILIZER - MAINTENANCE PRACTICES .........
................
CONTENTS
© Cessna Aircraft Company
Page 1 of 1
Mar 1/2005
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
STABILIZERS - GENERAL
1.
Scope
A.
2.
This chapter provides maintenance information on the horizontal and vertical stabilizer.
Definition
A.
The section on horizontal stabilizer provides instructions for removal and installation of the horizontal
stabilizer.
B.
The section on vertical fin provides instructions for removal and installation on the vertical fin.
©Cessna Aircraft Company
55-00-00
Page 1
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
HORIZONTAL STABILIZER - MAINTENANCE PRACTICES
1.
2.
General
A.
The horizontal stabilizer is of metal construction, consisting of ribs and spars covered with skin. A
formed metal leading edge is riveted to the assembly to complete the structure. The elevator trim
tab actuator is contained within the horizontal stabilizer. The underside of the stabilizer contains a
covered opening which provides access to the actuator. Hinges are located on the rear spar assembly
to support the elevators.
B.
This section provides removal and installation instructions for the horizontal stabilizer.
Horizontal Stabilizer Removal/Installation
A.
Remove Horizontal Stabilizer (Refer to Figure 201).
(1) Remove elevators. Refer to Chapter 27, Elevator Control System - Maintenance Practices.
(2) Remove rudder. Refer to Chapter 27, Rudder Control System - Maintenance Practices.
(3) Remove vertical stabilizer. Refer to Vertical Stabilizer - Maintenance Practices.
(4) Disconnect elevator trim control cables at clevis and turnbuckle inside tailcone.
(5) Remove pulleys which route the aft cables into horizontal stabilizer, and pull cables out of
tailcone. Refer to Chapter 27, Elevator Trim Control - Maintenance Practices.
(6) Remove bolts securing horizontal stabilizer to fuselage.
(7) Remove horizontal stabilizer.
B.
Install Horizontal Stabilizer (Refer to Figure 201).
(1) Install horizontal stabilizer to fuselage using bolts.
(2) Reroute cables into tailcone and install pulleys.
(3) Reconnect elevator trim control cables at clevis and turnbuckle inside tailcone.
(4) Install vertical stabilizer. Refer to Vertical Stabilizer - Maintenance Practices.
(5) Install rudder. Refer to Chapter 27, Rudder Control System - Maintenance Practices.
(6) Install elevators. Refer to Chapter 27, Elevator Control System - Maintenance Practices.
(7) Rig elevator. Refer to Chapter 27, Elevator Control System - Maintenance Practices.
(8) Rig rudder. Refer to Chapter 27, Rudder Control System - Maintenance Practices.
(9) Rig elevator trim. Refer to Chapter 27, Elevator Trim Control - Maintenance Practices.
55-10-00
© Cessna Aircraft Company
Page 201
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
HINGE
DETAIL D
OT1001
12T1007
2T 1008
32T1009
32T1010
32T1011
Horizontal Stabilizer Installation
Figure 201 (Sheet 1)
55-10-00
© Cessna Aircraft Company
Page 202
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
VERTICAL FIN - MAINTENANCE PRACTICES
1.
2.
General
A.
The vertical fin is of metal construction, consisting of ribs and spars covered with aluminum skin. The
trailing edge of the fin contains three hinges used to attach the rudder.
B.
Maintenance practices consist of removal and installation of the vertical fin.
Vertical Fin Removal/Installation
A.
Remove Vertical Fin (Refer to Figure 201).
(1) Remove rudder. Refer to Chapter 27, Rudder Control System - Maintenance Practices.
(2) Remove upper fairing 340AL and 340AR. Refer to Chapter 6, Access/Inspection Plates Description and Operation.
(3) Disconnect all electrical and navigation leads from base of fin area.
(4) Remove screws attaching dorsal to fin.
(5) Disconnect elevator cable from elevator bell crank.
(6) Remove hardware attaching fin rear spar to fuselage fitting.
WARNING: Carefully note position of spacers and/or shims, if installed, for
reinstallation.
(7) Remove upper elevator stop bolts.
(8) Remove bolts attaching fin front spar to fuselage bulkhead and remove fin from fuselage.
B.
Install Vertical Fin (Refer to Figure 201).
(1) Place fin on fuselage and secure front spar of fin to fuselage. Torque bolts 50 inch-pounds to
70 inch pounds (6 to 8 N.m).
(2) Install upper elevator stop bolts.
(3) Attach fin rear spar to fuselage fitting using retained hardware. Torque bolts 100 inch-pounds to
140 inch-pounds (11 to 16 N.m).
WARNING: Spacers and/or shims must be reinstalled in the position from
which they were removed.
(4)
(5)
(6)
(7)
(8)
(9)
(10)
Connect elevator cable to elevator bell crank. Refer to Chapter 27, Elevator Control System Maintenance Practices.
Secure dorsal to fin using screws.
Reconnect all electrical and navigation leads.
Install rudder. Refer to Chapter 27, Rudder Control System - Maintenance Practices.
Rig rudder. Refer to Chapter 27, Rudder Control System - Maintenance Practices.
Rig Elevator. Refer to Chapter 27, Elevator Control System - Maintenance Practices.
Install upper fairing 340AL and 340AR. Refer to Chapter 6, Access/Inspection Plates Description and Operation.
55-30-00
© Cessna Aircraft Company
Page 201
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1
A
HINGE
B
VERTICAL FIN
DETAIL A
HINGE
C
D
DETAIL B
BOLT
NUT
B(
-I
rM/a1
DUL I
DETAIL
\vzz,
D
NUT
0731T1008
A0731T1006
B0731T1004
C0731T1003
D0731T1007
DETAIL C
Vertical Fin Installation
Figure 201 (Sheet 1)
55-30-00
© Cessna Aircraft Company
Page 202
April 1/2002
CHAPTER
WINDOWS
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
LIST OF EFFECTIVE PAGES
CHAPTER-SECTION-SUBJECT
PAGE
DATE
56-00-00
Pages 1-2
Jan 2/2006
56-00-01
Pages 1-2
April 1/2002
56-10-00
Pages 201-203
April 1/2002
56-20-00
Pages 201-202
Mar 1/2005
56-30-00
Pages 201-202
April 1/2002
56-Title
56-List of Effective Pages
56-Record of Temporary Revisions
56-Table of Contents
© Cessna Aircraft Company
56 - LIST OF EFFECTIVE PAGES
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
WINDOWS - GENERAL .........
............................
.....................
S cope......................................................................
Tools, Equipment and Materials ..............................................
Definition...................................................................
56-00-00
56-00-00
56-00-00
56-00-00
Page
Page
Page
Page
1
1
1
2
WINDSHIELDS AND WINDOWS - DESCRIPTION AND OPERATION ...............
General ....................................................................
Tools, Equipment and Materials ..............................................
Cleaning Instructions .....................................................
Windshield and Window Preventive Maintenance ..............................
Windshield and Window Installation Techniques ...............................
Windshield Rain Repellent
............................
......................
56-00-01
56-00-01
56-00-01
56-00-01
56-00-01
56-00-01
56-00-01
Page
Page
Page
Page
Page
Page
Page
1
1
1
1
1
2
2
WINDSHIELD - MAINTENANCE PRACTICES...................................
General ...................................................................
Windshield Removal/Installation
............................................
Temporary Repairs ..........................................................
56-10-00
56-10-00
56-10-00
56-10-00
Page
Page
Page
Page
201
201
201
201
CABIN WINDOWS - MAINTENANCE PRACTICES .................................
G eneral....................................................................
Rear Window Removal/Installation............................................
Side Window Removal/Installation ............................................
Optional Openable Side Window .............................................
56-20-00
56-20-00
56-20-00
56-20-00
56-20-00
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Page
Page
Page
Page
201
201
201
201
201
CABIN DOOR WINDOWS - MAINTENANCE PRACTICES ..........................
General ....................................................................
Cabin Door Window Removal/Installation .....................................
56-30-00 Page 201
56-30-00 Page 201
56-30-00 Page 201
56 - CONTENTS
© Cessna Aircraft Company
Page 1of 1
Jan 2/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
WINDOWS - GENERAL
1.
Scope
A.
2.
This chapter provides information on windows used throughout the airplane.
Tools, Equipment and Materials
NOTE:
Equivalent substitutes may be used for the following listed items:
NAME
NUMBER
Mild soap or
detergent (hand
dishwashing type
without abrasives)
USE
Commercially Available
To clean windshields and
windows.
Aliphatic Naphtha
Type II Federal
Specification
TT-N-95
Commercially Available
To remove deposits from
windshields and windows.
Novus
Number 1
Commercially Available
To clean acrylic
windshields and windows.
Novus
Number 2
Commercially Available
To remove minor surface
scratches in acrylic
windshields and windows.
Novus
Number 3
Commercially Available
To remove heavy scratches
and abrasions in acrylic
windshields and windows.
Mirror Glaze
MGH-7
Meguiars Mirror Bright Polish
210 N. First Ave.
Arcadia, CA 91006
To clean and polish acrylic
windshields and windows.
Commercially Available
To apply and remove wax
and polish.
Soft cloth, such as,
Cotton flannel or
cotton terry cloth
I
MANUFACTURER
Windshield sealant
tape
U000927S
Available from
Cessna Parts Distribution
Cessna Aircraft Company
Department 701
5800 E. Pawnee Rd.
Wichita, KS 67218-5590
To seal windshield and
fixed windows.
Repcon rain
repellent
6850-00-1395297
Unelko Corporation
7428 East Karen Drive
Scottsdale, Arizona 85260
To repel rain from
windshield.
Wax
Paste type hard
Commercially Available
To wax windshield and
windows.
Fuel, pressure and
weather sealant
Pro Seal 890
Courtaulds Aerospace
To seal cabin door windows
© Cessna Aircraft Company
56-00-00
Page 1
Jan 2/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
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 section on flight compartment windows provides maintenance instructions for repair and
replacement of the windshield.
(2) The section on cabin windows provides maintenance instructions for the cabin side and cabin
rear windows.
(3) The section on door windows provides maintenance instructions for openable windows located
in the cabin doors.
©Cessna Aircraft Company
56-00-00
Page 2
Jan 2/2006
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
WINDSHIELDS AND WINDOWS - DESCRIPTION AND OPERATION
1.
General
A.
2.
Tools, Equipment and Materials
A.
3.
This section provides instructions and tips for cleaning and installing windshields and windows used
in the airplane.
For a list of required tools, equipment and materials, refer to Windows - General.
Cleaning Instructions
CAUTION: Windshields and windows (acrylic-faced) are easily damaged by
improper handling and cleaning techniques.
CAUTION: Do not use methanol, denatured alcohol, gasoline, benzene, xylene,
methyl propyl ketone, acetone, carbon tetrachloride, lacquer thinner,
commercial or household window cleaning sprays on windshields or
windows.
A.
Instructions For Cleaning.
(1) Place airplane inside hangar or in shaded area and allow to cool from heat of sun's direct rays.
(2) Using clean (preferably running) water, flood the surface. Use bare hands with no jewelry to feel
and dislodge any dirt or abrasive materials.
(3) Using a mild soap or detergent (such as a dishwashing liquid) in water, wash the surface. Again
use only the bare hand to provide rubbing force. (A clean cloth may be used to transfer the soap
solution to the surface, but extreme care must be exercised to prevent scratching the surface.)
(4) When contaminants on acrylic windshields and windows cannot be removed by a mild detergent,
Type II aliphatic naphtha, applied with a soft clean cloth, may be used as a cleaning solvent. Be
sure to frequently refold cloth to avoid redepositing contaminants and/or scratching windshield
with any abrasive particles.
(5) Rinse surface thoroughly with clean fresh water and dry with a clean cloth.
(6) Hard polishing wax should be applied to acrylic surfaces. (The wax has an index of refraction
nearly the same as transparent acrylic and will tend to mask any shallow scratches on the
windshield surface.)
(7) Acrylic surfaces may be polished using a polish meeting Federal Specification P-P-560 applied
per the manufacturers instructions.
NOTE:
4.
When applying and removing wax and polish, use a clean, soft cloth, such as cotton
flannel.
Windshield and Window Preventive Maintenance
Utilization of the following techniques will help minimize windshield and window crazing.
General Notes and Techniques For Acrylic Windshields.
(1) Keep all surfaces of windshields and windows clean.
(2) If desired, wax acrylic surfaces.
(3) Carefully cover all surfaces during any painting, powerplant cleaning or other procedure that
calls for use of any type of solvents or chemicals.
(4) Do not park or store airplane where it might be subjected to direct contact with or vapors from:
methanol, denatured alcohol, gasoline, benzene, xylene, methyl propyl ketone, acetone, carbon
tetrachloride, lacquer thinner, commercial or household window cleaning sprays, paint strippers,
or other types of solvents.
(5) Do not leave sunvisors up against windshield when not in use. The reflected heat from these
items causes elevated temperatures on the windshield. If solar screens are installed on the
inside of the airplane, make sure they are the silver appearing, reflective type.
NOTE:
A.
56-00-01
© Cessna Aircraft Company
Page 1
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
(6)
5.
Do not use a power drill motor or other powered device to clean, polish, or wax surfaces.
Windshield and Window Installation Techniques
A.
Installation Techniques.
(1) Special drills must be used when drilling holes in acrylic. Standard drills will cause the hole to
be oversized, distorted, or excessively chipped.
(2) Whenever possible, a coolant, such as a plastic drilling wax, should be used to lubricate the drill
bit.
(3) Drilled holes should be smooth with a finish of 125 rms (root mean square).
(4) The feed and speed of the drill is critical. Refer to Table 1 for thickness versus drill speed
information.
Table 1. Material Thickness vs. Drill Speed
Thickness (inches)
Thickness (mm)
Drill Speed (RPM)
0.062 to 0.1875
1.57 to 4.76
1500 to 4500
0.250 to 0.375
6.35 to 9.52
1500 to 2000
0.4375
11.10
1000 to 1500
0.500
12.70
500 to 1000
0.750
19.05
500 to 800
1.00
25.4
500
(5) In addition to feed and speed of the drill bit, the tip configuration is of special importance when
drilling through acrylic windows and windshields. Tip configuration varies with hole depth, and
the following information applies when drilling through acrylic:
(a) Shallow Holes - When hole depth to hole diameter ratio is less than 1.5 to 1, the drill shall
have an included tip angle of 55 degrees to 60 degrees and a lip clearance angle of 15
degrees to 20 degrees.
(b) Medium Deep Holes - When hole depth to hole diameter ratio is from 1.5 to 1 up to 3 to 1,
the drill shall have an included tip angle of 60 degrees to 140 degrees and a lip clearance
angle of 15 degrees to 20 degrees.
(c) Deep Holes - when hole depth of hole diameter ratio is greater than 3 to 1, the drill shall
have an included tip angle of 140 degrees and a lip clearance of 12 degrees to 15 degrees.
(6) Parts which must have holes drilled shall be backed up with a drill fixture. Holes may be drilled
through the part from one side. However, less chipping around holes will occur if holes are drilled
by drilling the holes from both sides. This is accomplished by using a drill with an acrylic backup
piece on the opposite side. Remove the drill from the hole and switch the backup plate and finish
drilling from the opposite side.
6.
Windshield Rain Repellent
A.
Repcon is a rain repellent and surface conditioner that may be used to increase the natural cleaning
of the windshield during rain. Apply in accordance with manufacturers instructions.
56-00-01
© Cessna Aircraft Company
Page 2
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
WINDSHIELD - MAINTENANCE PRACTICES
1.
General
A.
2.
This section provides instructions for removal and installation of the window as well as repair
techniques applicable to acrylic windshields and windows.
Windshield Removal/Installation
A.
Remove Windshield (Refer to Figure 201).
(1) Remove wing fairings.
(2) Remove air vent tubes. Refer to Chapter 21, Fresh Air Distribution - Maintenance Practices.
(3) Drill out rivets securing front retainer strip.
(4) Remove and tape compass clear of work area. Do not disconnect electrical wiring.
CAUTION: If windshield is to be reinstalled, be sure to protect windshield during
removal.
B.
(5) Pull windshield straight forward, out of side and top retainers. Remove top retainer if necessary.
(6) Clean sealer from inner sidewalls and bottom of retainers.
Install Windshield (Refer to Figure 201).
(1) If windshield is to be reinstalled, clean off old sealer and felt, then install new felt around edges
of windshield.
(2) If new windshield is to be installed, remove protective cover and clean.
(3) Apply new felt to edges of windshield.
(4) Apply windshield sealant tape along the sides and bottom of felt. Refer to Windows - General,
for a list of sealant tape.
(5) Position bottom edge of windshield against deck skin.
(6) Starting at upper corner, gradually work windshield into position.
(7)
(8)
(9)
(10)
NOTE:
Use care not to crack windshield when installing. If not previously removed, top
retainer may be removed if necessary.
NOTE:
Screws and self-locking nuts may be used instead of rivets which fasten front retaining
strip to cowl deck. If at least No. 6 screws are used, no loss of strength will result.
Install compass
Tighten or install windshield retainers as required.
Install air vent tube. Refer to Chapter 21, Fresh Air Distribution - Maintenance Practices.
Install wing fairings.
NOTE:
3.
Tape gap between windshield and leading edge with cloth industrial tape 2.5 inches
wide on both sides.
Temporary Repairs
A.
Temporary repairs to windshields and windows can be accomplished using the following steps. Refer
to Figure 202 for an illustration of repair techniques.
(1) When a crack appears, drill a hole at end of crack to prevent further spreading. Hole should
be approximately 1/8 inch (3.2 mm) diameter, depending on length of crack and thickness of
material.
(2) Temporary repairs to flat surfaces can be accomplished by placing a thin strip of wood over each
side of the surface, and inserting small bolts through the wood and plastic. A cushion of sheet
rubber or airplane fabric should be placed between wood and plastic on both sides.
(3) A temporary repair can be made by drilling small holes along both sides of crack, 1/8 to 1/4 inch
(3.2 to 6.4 mm) apart, and lacing edges together with soft wire. This type of repair is used as a
temporary measure only, and as soon as facilities are available, panel should be replaced.
56-10-00
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
3UTER
RETAINER
3
DETAIL
A
jOUTER
RETAINER
FELT
SEAL
f~1 I-I
UU I l-l
R E TA IN E R
DETAIL D
INNER
RETAINER
INNER
RETAINER
0710T1001
A0511T3002
B0511T3002
C0511T3002
D0511T3002
DETAIL C
Windshield Installation
Figure 201 (Sheet 1)
56-10-00
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April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1326
CORRECT
INCORRECT
STOP
WIRE
G
RPER
IAL
DRILLED
CRAC
UU1HINJU UtMtN I INU, IMHtI-UHt
H AND HOLE
NEEEDS TO BE APPLIED ONLY
JLD BE TRIMMED
ON TOP SURFACE. TAPER ASSURES
TAPERED EDGES. EQI JAL PRESSURE ON ALL SIDES.
HEAT EDGES OF
PATCH UNTIL SOFT
AND FORCE IT INTO
HOLE. HOLD IT IN
PLACE UNTIL COOL
AND HARD TO ASSURE
SUF
PAT
CRA
EDGE
PATCH
D r-Dr -)r"rT
rnlrF AI
r-IT
-ri r-I
1ni. I rlCI
REMOVE PATCH FOR
CEMENTING BATH.
/
^
AFTER CEMENT HAS
HARDENED, SAND
OR FILE EDGES LEVEL
WITH SURFACE.
0511T1014
WindshieldNVindow Repair
Figure 202 (Sheet 1)
56-10-00
© Cessna Aircraft Company
Page 203
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
CABIN WINDOWS - MAINTENANCE PRACTICES
1.
General
A.
2.
3.
Rear Window Removal/Installation
A.
Remove the Rear Window (Refer to Figure 201).
(1) Remove the upholstery as necessary to get access to the retainer strips inside the cabin. Refer
to Chapter 25, Interior Upholstery - Maintenance Practices.
(2) Remove the rivets as necessary to remove the outer retainer strip from the aft edge of the
window.
(3) To remove the window, lift the aft edge and pull the window aft. If you cannot remove the window
easily, rivets that attach the retainer strips inside the cabin can also be removed and the retainer
strips loosened or removed.
B.
Install the Rear Window (Refer to Figure 201).
(1) If the same window is being installed again, remove all the remaining sealant from the window.
(2) Clean the channels and retainers to remove all the remaining sealant.
(3) Make sure that the window fits correctly, and carefully grind off unwanted plastic.
(4) Put a felt strip around all the edges of the window, and apply sealant to prevent leaks.
(5) Install the rear window in the airplane and attach the window with retainer strips and rivets.
(6) Install the upholstery. Refer to Chapter 25, Interior Upholstery - Maintenance Practices.
Side Window Removal/Installation
A.
B.
4.
The airplane has two side windows and a rear window, all found in the rear cabin area. Maintenance
procedures are limited to the removal and installation of the windows. For instructions on temporary
repair, refer to Windshield - Maintenance Practices.
Remove the Side Window (Refer to Figure 201).
(1) Remove the upholstery as necessary to get access to the retainer strips inside the cabin. Refer
to Chapter 25, Interior Upholstery - Maintenance Practices.
(2) Remove the rivets that attach the retainer strips to the airplane.
(3) Remove the window from the airplane.
Install the Side Window (Refer to Figure 201).
(1) If the same window is being installed again, remove all the remaining sealant from the window.
(2) Clean the channels and retainers to remove all the remaining sealant.
(3) Put a felt strip around all the edges of the window, and apply sealant to prevent leaks.
(4) Install the side window in the airplane and attach the window with retainer strips and rivets.
(5) Install the upholstery. Refer to Chapter 25, Interior Upholstery - Maintenance Practices.
Optional Openable Side Window
A.
Some airplanes have an optional openable side window found on the left side of the airplane aft of the
pilot's cabin door window. These windows have hinges and are a part of the side window. The window
opens to the inside, and has two latches at the top and three hinges at the bottom. The removal and
installation procedure for the openable window assembly is the same as the removal and installation
procedure for the standard side window. If the openable side window is damaged, all of the window
assembly must be replaced.
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1327
SKIN
SKIN
IER
RETAINER
FELT
SEAL
DETAIL A
WINDOW
DETAIL D
WINDOW
WINDOW
RETAINER
FELT
SEAL
/
J
SKIN
FELT
SEAL
..
_
.
DETAIL
SKIN
_
B
,
0711T1002
A0711T1003
E0711T1004
C0711T1005
D0711TC1006
DETAIL C
Cabin Windows Installation
Figure 201 (Sheet 1)
56-20-00
© Cessna Aircraft Company
Page 202
Mar 1/2005
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
CABIN DOOR WINDOWS - MAINTENANCE PRACTICES
1.
General
A.
2.
This maintenance practices section consists of removal and installation of the hinged windows located
in each door. For instructions on temporary repair to the cabin door windows, refer to Windshield Maintenance Practices.
Cabin Door Window Removal/Installation
A.
Remove Cabin Door Window (Refer to Figure 201).
(1) Disconnect arm from window assembly.
(2) Remove hinge pins from hinge.
(3) To remove frame from window, drill out blind rivets at frame splice.
B.
Install Cabin Door Window (Refer to Figure 201).
(1) Install window in frame using rivets. Ensure that sealing strip and an adequate coating of Pro
Seal 890 (Type I) sealing compound is used around all edges of panel.
(2) Position window assembly to door.
(3) Secure window assembly to hinge using hinge pin.
56-30-00
© Cessna Aircraft Company
Page 201
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
E
LATCH
BRACKET
PLATE
&'
DETAIL B
HINGE
ASSEMBLY
ARM
DETAIL
A
1001
T3001
T1002
Cabin Door Window Installation
Figure 201 (Sheet 1)
56-30-00
© Cessna Aircraft Company
Page 202
April 1/2002
CHAPTER
WINGS
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
LIST OF EFFECTIVE PAGES
PAGE
DATE
57-00-00
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Aug 4/2003
57-10-00
Pages 201-208
April 1/2002
CHAPTER-SECTION-SUBJECT
57-Title
57-List of Effective Pages
57-Record of Temporary Revisions
57-Table of Contents
57 - 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
W INGS - GENERAL..........
..................................................
S cope......................................................................
Tools, Equipment and Materials ..............................................
Definition...................................................................
WINGS AND WING STRUTS - MAINTENANCE PRACTICES........................
Description and Operation ...................................................
Wing and Strut Removal/Installation ..........................................
Adjustment (Correcting Wing Heavy Conditions) ...............................
Strut Damage and Repair Criteria ............................................
Wing Tip Removal/Installation ...............................................
57-00-00
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57-00-00
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57-10-00
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© Cessna Aircraft Company
Page
Page
Page
Page
Page
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Page
Page
Page
Page
1
1
1
1
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201
201
205
206
207
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
WINGS - GENERAL
1.
Scope
A.
2.
This chapter provides instructions on wing removal and installation. Information and repair procedures
beyond the scope of this chapter can be found in the Single Engine Models 172, 182, 206 and T206
1996 and On Structural Repair Manual.
Tools, Equipment and Materials
NOTE:
I
Equivalent substitutes may be used for the following listed items:
NAME
NUMBER
MANUFACTURER
USE
Grease
MIL-G-21164
E/M Corporation
Box 2200
Highway 52 N.W.
West Lafayette, IN 47906
To lubricate wing attach
fittings and bolts upon
reinstallation.
Polyurethane Tape
P840306
3M
3M Center
Minneapolis, MN 55144
To eliminate chafing of wing
struts from strut fairings.
3.
Definition
A.
This chapter contains a single section on wing removal, installation and adjustment.
57-00-00
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
WINGS AND WING STRUTS - MAINTENANCE PRACTICES
1.
Description and Operation
WARNING: Some right wings have a spar cap of 0.100 inches thick, and are
not to be used on increased weight STC's (such as float planes).
2.
A.
Each metal wing is a semicantilever, semimonocoque type, with two main spars and suitable ribs for
the attachment of the skin. Panels are riveted to ribs, spars and stringers to complete the structure.
An all metal, piano hinged aileron, flap and detachable wing tip are mounted on each wing assembly.
Each wing also incorporates an integral fuel bay located between the two spars at the inboard portion
of the wing. Each wing is supported in position by a single lift strut. It consists of a streamlined tube
riveted to two end fittings for attachment at the wing and at the fuselage.
B.
For a skeletal view of the wing assembly, refer to Chapter 6, Airplane Stations - Description and
Operation.
Wing and Strut Removal/Installation
A.
Remove the Wing and Strut (Refer to Figure 201).
CAUTION: The wing must be supported with a sling or a maintenance stand when
the fasteners are loosened. If a sling or stand is not available, a minimum
of four people must be used to handle the wing.
(1) Remove the fairings from the wing and fuselage intersection.
(2) Remove the inspection plates as required to allow for disconnection of all the electrical,
mechanical and fuel connections.
(3) Drain the fuel. Refer to Chapter 12, Fuel - Servicing.
(4) Disconnect the electrical wires at the wing root disconnects.
(5) Disconnect the fuel lines at the wing root.
(6) Disconnect the pitot tube on the left wing. Refer to Chapter 34, Pitot And Static Systems Maintenance Practices.
(7) Disconnect the fresh air distribution duct at the wing root.
(8) Disconnect the aileron cables at the aileron bell crank. Refer to Chapter 27, Aileron Control
System - Maintenance Practices.
NOTE:
For easier routing of cables, attach a guide wire to each cable before it is pulled free
from the wing. Disconnect the cable from the guide wire, leaving the guide wire routed
through the wing. The guide wire will be attached to the cable during installation and
used to pull the cable into position.
(9) Remove the cabin headliner to get access to the flap cables at the turnbuckle. Refer to Chapter
25, Interior Upholstery - Maintenance Practices.
(10) Disconnect the flap cables at the turnbuckle and pull cables into wing root area. Refer to Chapter
27, Flap Control System - Maintenance Practices.
NOTE:
(11)
(12)
(13)
(14)
(15)
(16)
For easier routing of cables, attach a guide wire to each cable before it is pulled free
from the wing. Disconnect the cable from the guide wire, leaving the guide wire routed
through the wing. The guide wire will be attached to the cable during installation and
used to pull the cable into position.
Remove the screws from the strut fairings.
Move the fairings toward the center of the strut.
Support the wing at the outboard end.
Remove the strut-to-wing attach bolt and the strut-to-fuselage attach bolt.
Remove the strut from the wing and fuselage.
Tape the flaps in a streamlined position to prevent flap movement during handling.
57-10-00
© Cessna Aircraft Company
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April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
AXAAA
B
FAIRING
'REW
B
FLAP
C
AILERON
WIl
DETAIL A
WING TIP
0710T1001
A0720R1009
Wing and Strut Installation
Figure 201 (Sheet 1)
57-10-00
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April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B3420
AFT WING
SPAR
ING
NASHER
EC(
BU<
NUT
I
DETAIL
B
NUT
'HER
WASHE
BOLT
FORW
WING
DETAIL C
B0520R1003
C0520R1002
Wing and Strut Installation
Figure 201 (Sheet 2)
57-10-00
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Page 203
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
E
F
STRUT
STRUT
DETAIL D
WASHE
BOLT
DETAIL
NOTE: WRAP WING STRUT USING
3M Y8671 POLYURETHANE
TAPE (1 INCH WIDE)
rxri-
tN
T
r-
r--
A
I-
I tI-IU A I r
-flllT
-T
I
TAll.
-f-
E
--
CUFF TERMINAT
FITTING
WASHER
DETAIL F
D0720R1004
E0720R1005
F0720R1006
Wing and Strut Installation
Figure 201 (Sheet 3)
57-10-00
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
(17) Mark position of the wing attachment eccentric bushings in relationship to the fittings. The
bushings are used to rig out wing heaviness.
NOTE:
Wings must be rigged at installation if bushings are not marked.
(18) Remove the nuts, washers, bushings and bolts attaching the wing spars to the fuselage.
NOTE:
It may be necessary to rock the wings slightly and/or to use a long drift punch to
remove attaching bolts.
(19) Remove the wing and lay it on a padded stand.
B.
Install the Wing and Strut (Refer to Figure 201).
CAUTION: Do not lubricate the threads of the bolts.
(1) Lightly lubricate the wing attach bolts and holes with MIL-G-21164 grease before installing bolts.
(2) Hold the wing in position and install the bolts, bushings, washers and nuts attaching the wing
spars to the fuselage fittings. Make sure eccentric bushings are positioned as marked.
(3) Torque the front wing spar bolts 290 to 410 inch-pounds.
(4) Torque the rear wing spar bolts 450 to 500 inch-pounds.
(5) Install the 0.38 inch seal around strut with 0.12 inch gap on lower surface.
(6) Install the bolts, spacers and nuts to attach the upper and lower ends of the wing strut to the
wing and fuselage fittings.
(7) Route the flap cables using the guide wires.
(8) Connect the flap cables at the turnbuckle above the headliner. Refer to Chapter 27, Flap Control
System - Maintenance Practices.
(9) Route the aileron cables using the guide wires.
(10) Connect the aileron cable at the aileron bell crank. Refer to Chapter 27, Aileron Control System
- Maintenance Practices.
(11) Connect the fresh air distribution at wing root.
(12) Connect the pitot tube. Refer to Chapter 34, Pitot And Static Systems - Maintenance Practices.
(13) Connect the fuel lines at the wing root.
(14) Connect the electrical wires at the wing root.
(15) Complete a leak check of the pitot tube. Refer to Chapter 34, Pitot And Static Systems Maintenance Practices.
(16) Remove the tape from the flaps.
(17) Rig the flap system. Refer to Chapter 27, Flap Control System - Maintenance Practices.
(18) Rig the aileron system. Refer to Chapter 27, Aileron Control System - Maintenance Practices.
(19) Fuel the wing bay. Refer to Chapter 12, Fuel Servicing.
(20) Check the operation of the fuel quantity system. Refer to Chapter 28, Fuel Storage and
Distribution - Maintenance Practices.
(21) Install the wing root fairings.
(22) Install the cabin headliner. Refer to Chapter 25, Interior Upholstery - Maintenance Practices.
3.
Adjustment (Correcting Wing Heavy Conditions)
NOTE:
A.
If considerable control wheel pressure is required to keep the wings level in normal flight, a "wing
heavy" condition exists and can be corrected by the following procedure.
Adjustment Procedures (Refer to Figure 201).
CAUTION: The eccentric cams must be adjusted after all flight control systems have
been adjusted and rigged.
(1) If necessary, rig the flight controls. Refer to Chapter 27, Flight Controls - General.
(2) Remove the wing fairing strip from the heavy side of the airplane.
57-10-00
© Cessna Aircraft Company
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MODEL 182/T182
MAINTENANCE MANUAL
CAUTION: Make sure you rotate the eccentric bushings together. If you rotate
just one, you will destroy the alignment between the off-center bolt
holes in the bushings. A nonalignment of a bolt will result in a force
on the bolt which will damage the hole in the wing spar.
(3) Loosen the aft wing spar nuts and rotate eccentric bushings simultaneously until the bushings
are positioned with the thick side of the eccentrics up.
NOTE:
This will lower the trailing edge of the wing, and decrease wing heaviness by
increasing angle of incidence of the wing.
(4) Torque the front wing spar bolts 290 to 410 inch-pounds.
(5) Torque the rear wing spar bolts 450 to 500 inch-pounds.
(6) Install the fairing strip.
(7) Test fly the airplane.
CAUTION: Make sure the eccentric bushings are rotated simultaneously.
Rotating them separately will destroy the alignment between
the off-center bolt holes in the bushings, thus exerting a
shearing force on the bolt, with possible damage to the hole
in the wing spar.
(a) If the wing heavy condition continues, remove the fairing strip on the lighter wing, loosen
the nut and rotate the eccentric bushings simultaneously until the bushings are positioned
with the thick side of the eccentrics down.
NOTE:
This will raise the trailing edge of the wing, thus increasing wing heaviness to
balance heaviness in the opposite wing.
(8) Torque the rear wing spar bolts 450 to 500 inch-pounds.
(9) Install fairing strip and repeat flight test.
4.
Strut Damage and Repair Criteria
CAUTION: If the strut is severely dented, cracked or deformed, it must be replaced.
A.
Damage Caused by the Strut Fairings.
NOTE:
The following procedures are applicable only to the specific areas of the strut.
(1) The strut must be replaced if a groove is more then 0.010 inch in depth and is less then 0.75
inch from a rivet center.
(2) The strut must be replaced if a groove is more than 0.75 inch from a rivet center and the groove
depth is more then 0.025 inch.
(3) If groove depth is less than 0.025 inch and is more than 0.75 inch from a rivet center, the strut
must be repaired. tapering gradually to the original surface and burnishing out to a smooth finish.
(a) Blend and smooth the surface area of the groove. Make sure not to remove any more
material from the groove.
(b) Check the area using a dye penetrant to make sure there are no cracks.
(c) Apply Alodine and repaint the area.
57-10-00
© Cessna Aircraft Company
Page 206
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B.
Damage Caused by the Cabin Door.
NOTE:
The following applies to the wing struts with grooves worn in the lower trailing edge. This
type of damage can occur with cabin door usage with a missing or incorrectly adjusted
door stop. A incorrectly adjusted door stop allows the door to hit against the aft edge of
the strut at the lower end.
(1) The strut must be replaced if a groove is deeper than 50 percent of the original material thickness.
(2) Repair the strut if a groove is less than 50 percent of the original material thickness.
(a) Blend and smooth the surrounding surface area of the groove. Make sure not to remove
any more material from the groove.
(b) Check the area using a dye penetrant to make sure there are no cracks.
(c) Apply Alodine and repaint the area.
(d) Rig the door to prevent door from rubbing the strut tube.
5.
Wing Tip Removal/Installation
A.
Remove the Wing Tip (Refer to Figure 202).
(1) Remove the wing tip.
(2) Remove the strobe light and the navigation light ground straps to power supply.
(3) Disconnect the navigation lights electrical connector.
(4) Disconnect the strobe lights electrical connector.
(5) Remove wing tip from wing.
B.
Install the Wing Tip (Refer to Figure 202).
(1) Connect the strobe lights electrical connector.
(2) Connect the navigation lights electrical connector.
(3) Move the wing tip into position over the wing tip rib. Make sure the existing holes in the wing tip
align with the attach holes in the wing skin/rib nutplates.
(4) Make a curved spacer from phenolic or aluminum which is 0.01 inch to 0.03 inch thick and is 1.0
inch to 2.0 inches in length. Make sure it matches the contour of the leading edge.
(5) Install the spacer at the leading edge of the wing between the skin and the inside contour of the
wing tip.
(6) Start at the aft of the tip and work forward, attach the wing tip to wing using screws.
(7) When all screws are installed, remove the spacer to leave a gap of 0.01 inch to 0.03 inch between
the skin and the inside contour of the wing tip.
57-10-00
© Cessna Aircraft Company
Page 207
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
A1424
IP
A
INCH
WING ROOT
VIEW A-A
WING TIP
SCREW
GAP BETWEEN WING TIP
AND FRONT OF WING
LEADING EDGE
0.01 INCH MINIMUM
0.03 INCH MAXIMUM
WING LEADING EDGE
DETAIL
A
1210T1001
A0510T1001
A-A0523T1001
Wing Tip Installation
Figure 202 (Sheet 1)
57-10-00
© Cessna Aircraft Company
Page 208
April 1/2002
CHAPTER
PROPELLERS
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti 82
MAINTENANCE MANUAL
LIST OF EFFECTIVE PAGES
PAGE
DATE
April 1/2002
61 -10-00
Page 1
Pages 201-203
61-20-00
Pages 201-205
Jul 1/2007
CHAPTER-SECTION-SUBJECT
61 -Title
61 -List of Effective Pages
61 -Record of Temporary Revisions
61 -Table of Contents
61-00-00
61
©Cessna Aircraft Company
-
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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/T182
MAINTENANCE MANUAL
CONTENTS
PROPELLER - GENERAL.............................
Scope....................................
61 -00-00 Page 1
61 -00-00 Page 1
PROPELLER - MAINTENANCE PRACTICES....................
General...................................
Propeller and Spinner Removal and Installation.................
61 -10-00 Page 201
61 -10-00 Page 201
61 -10-00 Page 201
PROPELLER GOVERNOR - MAINTENANCE PRACTICES..............
General...................................
Propeller Governor Removal/installation....................
High RPM Stop Screw Adjustment.......................
Propeller Control Cable............................
Governor Control Rigging...........................
61 -20-00
61 -20-00
61 -20-00
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201
201
201
204
204
205
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Jul 1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
PROPELLER - GENERAL
1.
Scope
A.
This chapter contains information for removal and installation of the propeller and propeller governor,
and adjustment and rigging procedures for the propeller governor.
©Cessna Aircraft Company
61-00-00
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April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
PROPELLER - MAINTENANCE PRACTICES
1.
General
A.
2.
The airplane is equipped with a two or three bladed, constant-speed, metal propeller. Maintenance
practices consist of removal and installation of the propeller and spinner. For additional information,
troubleshooting, adjustments, and maintenance procedures not addressed in this section, see
the applicable McCauley Service Manual. Refer to Introduction, List of Manufacturers Technical
Publications.
Propeller and Spinner Removal and Installation
A.
Remove Propeller and Spinner (Refer to Figure 201).
(1) Remove all power from airplane.
WARNING: Exercise care when working with the propeller. Always treat
the propeller as if the ignition switch were on. Do not stand,
nor allow anyone else to stand, within the arc of the propeller.
Ensure magneto switch is in the OFF position before turning
propeller.
WARNING: Ensure magneto is grounded before turning propeller.
(2) Remove twelve screws and washers securing spinner to spinner bulkhead assembly.
(3) Remove spinner, spinner support, and shims from prop cylinder.
NOTE:
(4)
Note number of shims for use during reinstallation of spinner.
Remove cowl assemblies as required to gain access to propeller mounting bolts.
NOTE:
If equipped with prop deice system, remove brush block assembly before removing
propeller, to prevent possible brush damage.
(5) Cut safety wire from mounting bolts.
(6) Remove mounting bolts as follows:
(a) Evenly back off mounting bolts approximately 0.25 of an inch (6.35 mm).
(b) Pull propeller assembly forward, taking up the 0.25 inch (6.35 mm) provided by backing off
mounting bolts.
NOTE:
As the propeller assembly is separated from the engine crankshaft, oil will drain
from the propeller and engine crankshaft cavities.
Continue evenly backing off the mounting bolts and pulling the propeller assembly forward,
0.25 inch (6.35 mm) at a time, until all bolts are completely removed.
Remove propeller assembly and O-Ring from engine prop shaft.
(c)
(7)
B.
Install Propeller and Spinner (Refer to Figure 201).
61-10-00
© Cessna Aircraft Company
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MODEL 182/T182
MAINTENANCE MANUAL
B
ENGINE MOUNT
ABLY
SPINNER
SPINNER SUPPORT
DETAIL A
0710T1001
A0750T1003
Propeller and Spinner Installation
Figure 201 (Sheet 1)
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MODEL 182/T182
MAINTENANCE MANUAL
WARNING: Exercise care when working with the propeller. Always treat
the propeller as if the ignition switch were on. Do not stand,
nor allow anyone else to stand, within the arc of the propeller.
Ensure magneto switch is in the OFF position before turning
propeller.
WARNING: Ensure magneto is grounded before turning propeller.
(1) Clean mating surfaces of propeller assembly, spinner bulkhead assembly, engine prop shaft and
mating surfaces.
(2) Apply film of MIL-L-7711 lubricant, or equivalent, to new O-Ring and engine prop shaft.
(3) Install new O-Ring.
(4) Carefully slide propeller assembly unto engine prop shaft and align propeller assembly to engine
and secure with mounting bolts.
(5) Torque mounting bolts incrementally in a crossing pattern to 60 foot-lbs, +5 or -5 foot-lbs (660780 in-lbs).
(6) Safety wire mounting bolts in sets of two or three bolts. Refer to Chapter 20, Safetying Maintenance Practices.
(7) Position shims, spinner support, and spinner on prop cylinder.
(8) Lightly press spinner snugly against spinner support and check alignment of mounting holes in
spinner with holes in spinner bulkhead assembly.
NOTE:
Without increasing pressure on spinner, the mounting holes in spinner need to be
positioned approximated 0.050 inch (1.27 mm) forward of the true center of holes in
spinner bulkhead assembly.
Add or remove shims as required to position spinner mounting holes 0.050 inch (1.27 mm)
forward of holes in spinner bulkhead assembly.
Push hard on spinner until spinner mounting holes are aligned with the spinner bulkhead
assembly holes and install four (4) screws and washers equally spaced around circumference
of spinner.
(a)
(9)
NOTE:
Use only the number of shims that will allow just enough alignment for screws to be
installed while pushing hard against spinner.
(10) Relax force against spinner and install remaining screws and washers. Tighten all screws
uniformly around spinner.
(11) Install cowl assemblies.
(12) Check engine oil and service as needed.
61-10-00
© Cessna Aircraft Company
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CESSNA AIRCRAFT COMPANY
MODEL 182/Ti 82
MAINTENANCE MANUAL
PROPELLER GOVERNOR
1.
2.
-
MAINTENANCE PRACTICES
General
A.
The propeller governor is a single-acting, centrifugal type, which boosts oil pressure from the engine
and directs it to the propeller where the oil is used to increase blade pitch. The governor is installed
on the forward, upper left side of the engine.
B.
Maintenance practices consist of removal and installation of the propeller governor, high RPM
stop adjustment, and rigging of the governor control. For additional information, troubleshooting,
adjustments, and maintenance procedures not addressed in this section, refer to the applicable
McCauley Service Manual.
Propeller Governor Remova~l/nstallation
A.
Remove the Propeller Governor (Refer to Figure 201).
(1) Remove all power from airplane.
WARNING: Treat the propeller as if the ignition switch were on. Do not
stand or allow anyone to stand in the arc of the propeller.
Make sure the magneto switch is set to the OFF position
before turning propeller.
(2) Remove cowling. Refer to Chapter 71, Cowling - Maintenance Practices.
(3) Remove the cotter pin, nut, washers, and bolt attaching the control cable to the control arm.
NOTE:
(4)
(5)
(6)
(7)
B.
Identify washers and position of washers for use when reconnecting control cable to
control arm.
Loosen the screws attaching the control cable to the control cable bracket.
Remove the control cable from the bracket restraint.
Remove the nuts and washers attaching the propeller governor to the engine.
Remove the propeller governor and gasket.
Install the Propeller Governor (Refer to Figure 201).
(1) Clean the smooth surfaces of propeller governor and engine mounting surface.
(2) Install a new mount gasket.
WARNING: Treat the propeller as if the ignition switch were on. Do not
stand or allow anyone to stand in the arc of the propeller.
Make sure the magneto switch is set to the OFF position
before turning propeller.
WARNING: Make sure you ground the magneto before you turn the
propeller.
CAUTION: Do not force the spline engagement. Rotate the crankshaft slightly
and the splines will mesh smoothly when properly aligned.
(3) Position the propeller governor and attach to the engine with the washers and nuts.
(a) If required, rotate the crankshaft to properly align the propeller governor and the engine
splines.
(4) Install the control cable in the bracket restraint and tighten the screws.
(5) Attach the control cable to the control arm with the bolt, washers, and nut.
(a) Torque the nut to 30 inch-pounds.
61 -20-00
© Cessna Aircraft Company
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Jul 1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti82
MAINTENANCE MANUAL
ts
THESE SCREWS MAY ONLY BE USED ONCE.
WHEN REMOVED, THESE SCREWS MUST
BE REPLACED WITH NEW SCREWS.
REFERENCE MCCAULEY SERVICE LETTER
2000-1 1, OR LATEST REVISION, FOR SCREW
AND TORQUE RECOMMENDATIONS.
A
CONTROL CABLE BRACKET RESTRAINT
WASHERS
1UTS
MOL
AND
ABLE
D END
PIN
WASHERS
DETAIL
WASHERS
A
0710T1001
A0755T1 003
Propeller Governor Installation
Figure 201 (Sheet 1)
61-20-00
©Cessna Aircraft Company
Page 202
Jul 1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti182
MAINTENANCE MANUAL
B3423
CONTROL ARM
TROL CABLE
CONTROL CABLE
ROD END
AA0755R1O1 1
Propeller Governor Installation
Figure 201 (Sheet 2)
61-20-00
©Cessna Aircraft Company
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Jul 1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti 82
MAINTENANCE MANUAL
CAUTION: Do not exceed 50 inch-pounds.
(b) Continue to torque the nut past 30 inch-pounds until the cotter pin hole lines up with
castellations in the nut.
(c) Install a new cotter pin.
(6) Rig the governor control. Refer to governor control rigging.
(7) Install cowling. Refer to Chapter 71, Cowling - Maintenance Practices.
3.
High RPM Stop Screw Adjustment
WARNING: Treat the propeller as if the ignition switch is set to on. Do not stand or
allow anyone to stand in the arc of the propeller. Make sure the magneto
switch is set to the OFF position before turning propeller.
WARNING: Make sure you ground the magneto before you turn the propeller.
A.
Adjust the High RPM Stop Screw (Refer to Figure 201).
(1) Remove the cowling. Refer to Chapter 71, Cowling - Maintenance Practices.
(2) Cut and discard the safety wire from high RPM stop screw.
~~(3) Loosen the high RPM stop screw lock nut.
(4) Turn the high RPM stop screw in (clockwise) for decrease in RPM or out (counterclockwise) to
increase maximum RPM. One complete turn will cause a change of approximately 25 RPM.
*
NOTE:
Due to climate conditions, field elevation, low pitch propeller blade angle, and other
factors, the engine may not reach rated RPM on the ground. It may be necessary to
readjust the governor high RPM stop screw after test flying to obtain maximum rated
RPM when airborne.
(5) Torque the lock nut to 8 to 12 inch-pounds.
(6) Adjust the propeller governor control as necessary to maintain full travel. Make sure the governor
control arm contacts the high RPM stop screw in both the maximum and minimum settings
(bottomed out against both high and low pitch stops). Make sure a cushion exists at both
positions of control arm travel. Refer to governor control rigging.
(7) Safety wire high RPM stop screw. Refer to Chapter 20, Safetying - Maintenance Practices.
(8) Install cowling. Refer to Chapter 71, Cowling - Maintenance Practices.
(9) Test and operate the governor and propeller combination.
4.
Propeller Control Cable
A.
Remove the Propeller Control Cable (Refer to Figure 201).
CAUTION: The control cable is not repairable and must be replaced at every
engine overhaul or when maximum linear movement exceeds 0.050
inch.
(1) Remove the upper cowling. Refer to Chapter 71, Cowling - Maintenance Practices.
(2) Remove the cotter pin, nut, washers, and bolt attaching the control cable to the control arm.
Discard the cotter pin.
(3) Remove the control cable rod end.
(4) Remove the nuts and bolts attaching the clamp bracket and pull control cable out of the grommet
on the engine baffle
(5) Remove the control cable nut and washer at the firewall.
(6) Pull control cable aft through firewall.
(7) Remove the nut and washer from the control cable.
(8) Remove the nut and washer on the forward side of the instrument panel from control cable while
pulling control cable from the instrument panel.
61-20-00
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MODEL 1821T182
MAINTENANCE MANUAL
B.
5.
Install the Propeller Control Cable (Refer to Figure 201).
(1) Route the control cable through the instrument panel.
(2) Route control cable through firewall and install the instrument panel washer nut.
(3) Install firewall washer and nut.
(4) Route cable through grommet in engine baffle.
(5) Attach the clamp bracket on the control cable.
(6) Rig governor control. Refer to Governor Control Rigging.
(7) Install cowling. Refer to Chapter 71, Cowling - Maintenance Practices.
Governor Control Rigging
WARNING: Treat the propeller as if the ignition switch is set to on. Do not stand or
allow anyone to stand in the arc of the propeller. Make sure the magneto
switch is set to the OFF position before turning propeller.
NOTE:
A.
The result of rigging of the governor control is full travel of the governor control arm (bottomed
out against both high and low pitch stops), with some cushion at both ends of the control travel.
Rig the Governor Control (Refer to Figure 201).
(1) Remove the cowling. Refer to Chapter 71, Cowling - Maintenance Practices.
(2) Remove the cotter pin, nut, washers, and bolt attaching the control cable to the control arm.
(a) Identify the washers and position of washers for attaching the control cable to the control
arm.
(3) Set the governor control in the cockpit to full forward. Pull the governor control back
approximately 0.125 inch and lock in this position.
NOTE:
This allows cushion which will make sure there is full contact with the governor high
RPM stop screw.
(4) Set the governor control arm against the high RPM stop screw.
(5) Loosen the jamnuts on the control cable rod end.
(6) Adjust rod end to align with control arm.
(a) Make sure the threads engage during adjustments. If necessary, adjust the position of
the control cable in the control cable bracket restraint to achieve proper alignment and for
threads to engage.
(7) Attach the control cable to the control arm with the bolt, washers, and nut.
(a) Torque the nut to 30 inch-pounds.
CAUTION: Do not exceed 50 inch-pounds.
(b) Continue to torque the nut past 30 inch-pounds until the cotter pin hole lines up with
castellations in the nut.
(c) Install a new cotter pin.
(8) Tighten the loose jamnuts on the control cable rod end.
(9) Operate the propeller control to make sure the governor control arm has full travel and contacts
stop in both directions with proper cushion.
(10) Install the cowling. Refer to Chapter 71, Cowling - Maintenance Practices.
61-20-00
© Cessna Aircraft Company
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CHAPTER
POWER PL~~~~ANT
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti 82
MAINTENANCE MANUAL
LIST OF EFFECTIVE PAGES
CHAPTER-SECTION-SUBJECT
PAGE
DATE
71 -Title
71 -List of Effective Pages
71 -Record of Temporary Revisions
71 -Table of Contents
©Cessna Aircraft Company
71
-
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
POWERPLANT - GENERAL............................
S cope..... . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Definition ..................................
ENGINE - DESCRIPTION AND OPERATION ....................
Description and Operation ..........................
ENGINE - TROUBLESHOOTING..........................
Troubleshooting Chart ............................
ENGINE - MAINTENANCE PRACTICES ......................
General...................................
Engine Removal/installation..........................
Engine Cleaning...............................
Engine Storage ...............................
COWL - MAINTENANCE PRACTICES .......................
Description and Operation ..........................
Side Cowl Removal/Installation ........................
Top Cowl Removal/Installation ........................
Nose-Cap Removal/Installation ........................
Bottom Cowl Removal/Installation.......................
Cowl Repair.................................
Cowl Flap Removal/Installation ........................
Cowl Flap Rigging ..............................
ENGINE MOUNT - MAINTENANCE PRACTICES ..................
Description and Operation ..........................
Engine Mount Procedures ..........................
Engine Mount Repairs ............................
AIR INDUCTION SYSTEM - MAINTENANCE PRACTICES..............
Description and Operation ..........................
Air Induction System Removal/Installation ...................
DRAIN LINES - MAINTENANCE PRACTICES....................
Description and Operation ..........................
Maintenance Practices............................
©Cessna Aircraft Company
71
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CONTENTS
Page 1 of 1
Janl1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
POWERPLANT - GENERAL
1.
Scope
A.
2.
This chapter contains maintenance information on the powerplant and associated components. For
engine related information not found in this chapter, refer to applicable Textron Lycoming maintenance
manuals, listed in Introduction - List of Manufacturers Technical Publications.
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 powerplant provides description, operation, troubleshooting and removal/
installation information for the engine.
(2) The section on engine cowlings provides removal and installation instructions for the engine
cowlings.
(3) The section on mounts provides removal and installation procedures for the engine mount.
(4) The section on air induction provides removal and installation procedures for the air induction
part of the fuel system.
(5) The section on drain lines provides removal and installation instructions on the various drain
lines used in the engine compartment.
71-00-00
C Cessna Aircraft Company
Page 1
April 1/2002
CESSNA AIRCRAFT COMPANY
MODEL 182/1 182
MAINTENANCE MANUAL
ENGINE
-
DESCRIPTION AND OPERATION
1.Description and Operation
A. Textron Lycomning's 10-540 ABlA5 and TIO-540-AKlA are direct drive, six cylinder, fuel injected,
horizontally opposed, air cooled engines. The cylinders, numbered from front to rear, are staggered
to permit a separate throw on the crankshaft for each connecting rod. The right front cylinder is number
1 and the other cylinders on the right side of the engine are identified by odd numbers 3 and 5. The
left front cylinder is number 2 and the other cylinders on the left side are identified as 4 and 6.
B. For a technical description of the engine, refer to Table 1. For an illustration of the engine, refer to
Figure 1 and Figure 2.
C. For information beyond the scope of this chapter, refer to applicable engine manuals listed in
Introduction - List of Manufacturers Technical Publications.
Table 1. 10-540-ABl A5 Technical Description
Rated Horsepower at 2400 RPM
Number of Cylinders
230
Displacement
Bore
541.5 Cubic Inches (8.875 1)
5.125
Stroke
4.375
6 Horizontally Opposed
Compression Ratio
Firing Order
8.5:1
1-4-5-2-3-6
Magnetos:
Right Magneto
Slick Model No. 6351 (fires at 230
BTDC)
Left Magneto
Slick Model No. 6351 (fires at 230
BTDC)
Spark Plugs
18MM
Torque:
420 Inch-pounds
Valve Rocker Clearance (hydraulic tappets
collapsed)
0.028 to 0.080 inch
Fuel Injector
RSA-5AD1
Tachometer
Mechanical Drive
Oil Capacity
9.0 Quarts (8.52 1)
Oil Pressure
Minimum Idling
20 PSI
Normal
50 to 90 PSI
Maximum
115 PSI
Oil Temperature
© Cessna Aircraft Company
71-00-01
Page 1
Janl1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti182
MAINTENANCE MANUAL
Table 1. 10-540-ABl A5 Technical Description (continued)
100 to 2450 F (38 to 1180C)
Normal
2450 F (118-C)
Maximum
382 Lbs
Dry Weight - with accessories
Table 2. TIO-540-AKl1A Technical Description
Rated Horsepower at 2400 RPM
235
Number of Cylinders
6 Horizontally Opposed
Displacement
541 .5 Cubic Inches (8.875 I)
Bore
5.125
Stroke
4.375
Compression Ratio
8.0:1
Firing Order
1-4-5-2-3-6
Magnetos:
Slick Model No. 6361 (fires at 200
BTDC)
Slick Model No. 6361 (fires at 200
BTDC)
Right Magneto
Left Magneto
18MM
Spark Plugs
420 Inch-pounds
Torque:
Valve Rocker Clearance (hydraulic tappets
collapsed)
0.028 to 0.080 inch
Fuel Injector
RSA-5AD1
Tachometer
Mechanical Drive
Oil Capacity
9.0 Quarts (8.52 I)
Oil Pressure
Minimum Idling
20 PSI
Normal
50 to 90 PSI
Maximum
115 PSI
Oil Temperature
Normal
100 to 2450 F (38 to 11 80 C)
Maximum
245-F (118 0C)
Dry Weight
-
with accessories
472 Lbs
71-00-01
© Cessna Aircraft Company
Page 2
Janl1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti 82
MAINTENANCE MANUAL
81333
OIL COOLER
IRE
LTER
'ASE
]ER
OIL FILLER/DIPSTICK
TOP VIEW
A075OT1 007
Engine Installation
Figure 1 (Sheet 1)
71-00-0 1
©Cessna Aircraft Company
Page 3
Janl1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti182
MAINTENANCE MANUAL
831334
DnDflA2
I
FUEL FLOW
TRANSDUCER
I 120
ENGINE
MOUNT
HEA T SHROUD)
-1 .-..
". -
LEFT SIDE VIEW
A075OT 1006
Engine Installation
Figure 1 (Sheet 2)
71 -00-01
©Cessna Aircraft Company
Page 4
Jan-1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti182
MAINTENANCE MANUAL
B1335
CABIN HEAT
MAGNETOS
I
ENGINE DRI 1
FUEL PUMP
CABIN
HEAT
DUCT
TAIL PIPE
UNIT
VIEW LOOKING FORWARD
A0750T 1005
Engine Installation
Figure 1 (Sheet 3)
©Cessna Aircraft Company
71-00-01
Page 5
Jan-1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti 82
MAINTENANCE MANUAL
OIL PRESSURE
TRANSDUCER
,ILFILTER
CRANKCASE
BREATHER
LI NE
EU
VA
L FILLER!
PSTICK
FUEL PRESSURE
TRANSDUCER
DETAIL
A
TOP VIEW (11
82T)
0710T1001
A0750T635D
Engine Installation
Figure 1 (Sheet 4)
71-00-01
Q Cessna Aircraft Company
Page 6
Jan 1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti82
MAINTENANCE MANUAL
----
PROPELLER
OIL PRESSURE
TRANSDUCER
kvv I I I I I it-/-
I
SHIELD)
FUEL PRESSURE
TRANSDUCER
ENGINE MOUNT
DETAIL A
LEFT SIDE SHOWN (11
82T)
071 OTi 001
A0750T635D
Engine Installation
Figure 1 (Sheet 5)
©Cessna Aircraft Company
71-00-0 I
Pagel7
Janl1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti182
MAINTENANCE MANUAL
-----
NBI N
DAT
JCT
ENGINE DRI\v
FUEL PUMP
CONTROL
UNIT
DETAIL A
VIEW LOOKING FORWARD (182T)
071OT1001
A0750T635D
Engine Installation
Figure 1 (Sheet 6)
71 -00-01
0 Cessna Aircraft Company
Page 8
Janl1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti182
MAINTENANCE MANUAL
B2069
OIL COOLER
OIL PRESSURE
TRANSDUCER
OIL FILLER/DIPSTICK
I-Uf-L UIZ 1HIIbU I ION VALVE
07501636
Engine Installation
Figure 1 (Sheet 7)
© Cessna Aircraft Company
71-00-01
Page 9
Jan-1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti182
MAINTENANCE MANUAL
B2067
FUEL FLOW
TRANSDUCER
PPC)PFI I FRP
EXHAUST
STACK
LEFT SI DE VIEW (Ti 82T)
0750T636
Engine Installation
Figure 1 (Sheet 8)
71 -00-01
©Cessna Aircraft Company
Page 10
Janl1/2007
CESSNA AIRCRAFT COMPANY
MODEL 1821T182
MAINTENANCE MANUAL
B2068
MAGNETOS
L COOLER
HEAT
DUCT
TAIL PIPE
VIEW LOOKING FORWARD (Ti 82T)
0750T636
Engine Installation
Figure 1 (Sheet 9)
©Cessna Aircraft Company
71 -00-01
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Janl1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/Ti182
MAINTENANCE MANUAL
61995
FUEL LINES
FUEL LINES
0750T636
Fuel Line Location
Figure 2 (Sheet 1)
71-00-01
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Janl1/2007
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
ENGINE - TROUBLESHOOTING
1.
Troubleshooting Chart
A.
Use the chart that follows and the information in Chapter 74, Ignition System - Troubleshooting to
help with engine and fuel system troubleshooting. For more information than that given in this chapter,
refer to the applicable engine manuals and publications listed in the Introduction, List of Manufacturers
Technical Publications.
B.
Static Run-up Procedures.
NOTE:
(1)
(2)
(3)
(4)
(5)
(6)
(7)
If the engine operates at a lower power than usual, use the troubleshooting chart and the
procedures that follow to find the cause of the low power condition.
Align the airplane 90 degrees to the right of the wind direction.
Operate the engine at full throttle in accordance with procedures given in the Pilot's Operating
Handbook and the approved Airplane Flight Manual.
Record the engine revolutions per minute (RPM).
Align the airplane 90 degrees to the left of the wind direction.
Operate the engine again at full throttle.
Record the RPM again.
Calculate the average RPM from the recorded RPM figures. The RPM must be between 2350
and 2400 RPM.
NOTE:
(8)
Differences in atmospheric pressure, temperature, and humidity can have an
important effect on run-up RPM. Low static run-up RPM information must be used
with other troubleshooting procedures to find if other maintenance is needed.
If the run-up shows low power, do a check of the items that follow.
(a) Make sure that the alternate air door operates correctly and that the door stays closed
while the airplane is in operation.
Measure the magneto timing, and examine the spark plugs and ignition harness. Make
(b)
sure that they are correctly set and are in good condition.
(c) Make sure that the fuel injection nozzles are clean and free from contamination. Make sure
that the un-metered fuel flow is correct.
(d) Make sure that the induction air filter is clean and in good condition. Clean or replace the
induction air filter, as necessary.
Do the engine compression check.
(e)
71-00-01
© Cessna Aircraft Company
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Mar 1/2005
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1336
The engine will not start and
no fuel flow is shown on the
fuel flow indicator.
Do a check of the fuel level in the
fuel tanks. Do the fuel tanks have a
sufficient quantity of fuel? If -
Is the mixture control in
the correct position? If -
(Fill
the fuel tanks.)
Is the fuel pump on and
operating correctly? If -
Put the mixture contro;
the correct position.
Are all the fuel valves open
and operating correctly? If-
Repair or replace the fuel
boost pump, as necessary.
Are the fuel filters clean and
free from blockages? If not,
clean or replace the fuel filters,
as necessary.
C Clean or replace the fuel>
valves, as necessary.
Engine Troubleshooting Chart
Figure 101 (Sheet 1)
71-00-01
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1337
The engine will not start and
sufficient fuel flow is shown
on the fuel flow indicator.
Do a check of the engine.
Is the engine flooded? If -
I
Lu
breaker points? If-
_
J
Refer to the applicable supplier
publication for information on
the correct timing procedures.
Do the magnetos have a weak
1I ,reervitrw
apaLci;tL
Are the magnetos correctly
timed to the engine? If -
/
__"
I
_I
Refer to the applicable
supplier pubiication Tor nme
\correct repair procedures
Are there air leaks in the
intake manifold? If-
Make sure that the hose connections
are tight, and the gaskets are in good
condition. Tighten the hose clamps
and flange attach bolts.
Do the troubleshooting procedures
for the ignition system. Refer to
Chapter 74, Ignition System Troubleshooting.
Engine Troubleshooting Chart
Figure 101 (Sheet 3)
71-00-01
© Cessna Aircraft Company
Page 104
Mar 1/2005
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1338
The engine does not
operate at idle speed.
Are the idle stop screw and/or the idle
mixture lever correctly adjusted? If -
Adjust the idle stop screw or
the idle mixture lever to the
correct position.
J
Is there an air leak in the
intake manifold? If -
I
Make sure that the hose connecti
are tight, and the gaskets are in gc
condition. Tighten the hose clam
and flange attaching bolts. ReplE
damaged parts, as necessary.
Is the magneto capacitor
serviceable? Refer to the
applicable supplier publication. If -
I
Damage to the spark plugs can be
caused by a leakage of oil from around
the piston rings. Are the spark plugs
free of oil? If -
Replace the magneto capacitor.
If the problem continues, do a
top overhaul of the engine. J
\
Refer to the applicable engine
overhaul manual in the Introduction
- List of Suppliers Publications for
more information.
Remove and clean the spark~
plugs. Replace unserviceable
spark plugs, as necessary. J
Engine Troubleshooting Chart
Figure 101 (Sheet 4)
71-00-01
© Cessna Aircraft Company
Page 105
Mar 1/2005
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1339
The engine does not idle smoothly.
I
Is thie idle mixture adjustment correct? If- I
YES
N
Is the manual mixture control
set for a lean mixture? If -
I
_
/Refer to Chapter 73, Fuel Injection
System - Maintenance Practices.J
_
et the manual mixture control to
a full rich mixture for all ground
\•
~operations.
Are the spark plugs in a
serviceable condition? Ifc
YES
NO
Remove and clean the spark plugs.
Make sure that the spark plugs have
the correct gaps and that the insulators are
in a serviceable condition. Install the spark
plugs with new gaskets. Do a test of the ignition
harness. Do an inspection of the magneto
\breaker points. If the problem persists, do /
a top overhaul of the engine.
Are the engine mounts
loose or damaged? If -
A
Make sure that the line does
not have any bends, kinks, or
/
blockages.
Is there sufficient flow to
the flow divider valve? If -
.
I
...,
..
MaKe sure tnat me mixture control is
in the correct position. Make sure
that the fuel filter is not clogged. /
Is there sufficient flow
from the fuel pump? If -
YES
I
.
NO
Is the magneto-to-engine
timing and the internal
magneto timing correct? If-
>
I
fExamine the fuel pump and\
shaft for wear. Install a new
\
fuel pump, if necessary.
/
' ~~~~~~~~~~~~~~~~~~~I
I
Adjust the magneto-to-engine timing
or refer to the applicable supplier
/
publication for the internal magneto )
'
timing procedures.
Do the magnetos have a weak
capacitor or incorrectly adjusted
breaker points? If-
I
Refer to the applicable
supplier publication for the
correct repair procedures.
I Are any valve springs broken? If YES
N
Are any ofthe valves
(nstall
Are any of the valves
burned or warped? If-
a new valve spring)
I
Examine the hydraulic tappets for
contamination and wear. Remove,
clean, or replace the hydraulic tappets,
~as necessary.
(Do a top overhaul of the engine)
lec<
Engine Troubleshooting Chart
Figure 101 (Sheet 6)
71-00-01
© Cessna Aircraft Company
Page 107
Mar 1/2005
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1341
The engine responds
slowly and has low power.
Examine the fuel injectors. Are the fuel injectors
clogged or have decreased flow? If -
Remove and clean the fuel injecto
Do a test of the fuel injectors to ma
sure that they operate correctly. Ins
the fuel injectors.
Are the valve seats worn? If -
o a top overhaul of the engine)
rno
Mn ovprhnidl
V - -,-I-
Are the piston rings worn? If -
Can the piston rings
move freely? If -
of thp.Pnninp")
-
",-
FOR TURBOCHARGED AIRPLANES
ONLY If there is a slow increase in manifold
pressure, do a check of the manifold
pressure reference orifice on the number
three cylinder. Is the orifice free from
particles and contamination? If-
I
(Do a top overhaul of the engine)
YES
N
efer to applicable engine overhaul
manual in the Introduction - List of
Suppliers Publications for more
information.
Remove any particles or
contamination from the orifice.
0
Engine Troubleshooting Chart
Figure 101 (Sheet 7)
71-00-01
© Cessna Aircraft Company
Page 108
Mar 1/2005
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1342
Low fuel flow is shown
on the fuel flow indicator.
Is the line to the flow transducer
clogged or have decreased flow? If-
YES
NO
Make sure that the line does
not have any bends, kinks, or
blockages.
Is there sufficient flow to
the flow divider valve? If -
I
ake sure that the mixture controlhas full travel and is in the correct
position. Make sure that the fuel
filter is not clogged.
Is there sufficient flow
from the fuel pump? If-
Examine the fuel pump andr
shaft for wear. Install new parts
or fuel pump, as necessary.
xamine the mixture control.
Make sure that the mixture
control can move freely. J
Engine Troubleshooting Chart
Figure 101 (Sheet 8)
71-00-01
© Cessna Aircraft Company
Page 109
Mar 1/2005
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1343
The fuel flow indicator shows
decreased fuel flow.
Is the line downstream of the flow divider
clogged or have decreased flow? If -
c
YES
NO
r/ake sure that the line does
I nat have an\
hanrkle
inlk
Is there sufficient flow to
r 1
the flow divider valve? If -
blockages.
I
I
ake sure that there are no clogged
zles and that there are no blockages
n the flow divider valve. Clean or
eplace the valves, as necessary.
Monitor the fuel flow indicator for
changes in flow that can indicate air
in the system or high fuel temperatur
Are there changes in flow? If -
I
I
Operate the boost pump to make
sure that the system is free of air.
If the condition continues, drain
the fuel line.
Examine the line between the flow
divider and the flow transducer for
eaks. Replace the line, as necessary/
i~ed~mn
h
iebtentefo''
Engine Troubleshooting Chart
Figure 101 (Sheet 9)
71-00-01
© Cessna Aircraft Company
Page 110
Mar 1/2005
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B3645
The engine does not stop when the mixture
control is put in the idle cutoff position.
I
Does the mixture control valve have a leak when the
mixture control is in the idle cutoff position? If I
I
ake sure that the fuel
Mboost
pump is off.
CRepair or replace the mixture>
control valve, as necessary. J
J
Engine Troubleshooting Chart
Figure 101 (Sheet 10)
71-00-01
© Cessna Aircraft Company
Page 111
Mar 1/2005
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1344
The engine has a high oil temperature.
Is the oil supply low? If -
I
I
( il the engine oil reservoir with oil
Is the viscosity of
the oil too high? IfYES
NO
CMake sure that the correct
Has the engine been operated
on the ground at a high speed
for a long period of time? If -
grade of oil is used.
I
void engine operation of more th
1500 rpm for a long period of tim
when the airplane is on the groun
Are the oil cooler
lines clogged? If-
I
Clean or replace the oil"
Are the oil passages in the
oil cooler clogged? If-
emove the oil cooler from theT
airplane. Clean and flush the
oil cooler.
J
Is the oil cooler bypass
valve damaged or caught
in the open position? If -
cooler lines, as necessary
I
I
airplane. Clean or replace the bypass
valve and valve seat, as necessary.
Make sure that the oil filter is
clean and free from blockages.
Replace the oil filter, as necessary.
Remove the oil cooler from the
Engine Troubleshooting Chart
Figure 101 (Sheet 11)
71-00-01
© Cessna Aircraft Company
Page 112
Mar 1/2005
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1345
The engine has low oil pressure.
I
Is the oil supply low? If -
YES
NO
ill the engine oil reservoir with oi
Is the viscosity of
the oil too low? If YES
NO
C
Make sure that the correct
grade of oil is used. J
Is the relief valve clean and
free from contamination? If -
I
r
Is the oil pressure gage
operating correctly? If -
( Remove and clean the relief valve. )
I
Is the oil transducer line
free from blockages? If-
( Replace the oil pressure gage. )
I
xamine the system for leaks, damaged
gaskets, or damaged bearings. Refer to the
applicable engine overhaul manual in the
Introduction - List of Suppliers Publications
for the correct repair procedures or for engine
overhaul instructions.
Clean or replace the oil transducer
line, as necessary. Make sure that
the line does not have any bends,
kinks, or blockages.
Engine Troubleshooting Chart
Figure 101 (Sheet 12)
71-00-01
©Cessna Aircraft Company
Page 113
Mar 1/2005
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1346
The engine has a high
cylinder head temperature.
I
Is the correct grade of fuel
being used? If-
YES
NO
Fully defuel the airplane. Fill the fue
anks with the correct grade of fuel.
Are the cylinder
fins clogged? IfYES
NO
I
I
Clean the cylinder fins.
Are the magnetos correctly
timed to the engine? If -
I
Adjust the magnetos so that
they are correctly timed to
the engine.
Is the internal timing of the
magnetos correct? If -
K,
Do the magnetos have a weak
capacitor or incorrectly
adjusted breaker points? If-
Refer to the applicable
supplier publication for the
correct timing procedures.
Refer to the applicablet
supplier publication for the
correct repair procedures.
Is there carbon buildup on
the cylinder head and on
the piston? If -
(Do a top overhaul of the engine)
Examine the exhaust valves for
leaks. If leaks are found, do a
top overhaul of the engine. J
Engine Troubleshooting Chart
Figure 101 (Sheet 13)
71-00-01
© Cessna Aircraft Company
Page 114
Mar 1/2005
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1347
The engine uses too much oil. I
I
Is the correct grade of oil
being used? If-
I
the oil from the engine and
with the correct grade of oil
Are the bearings worn
or damaged? If-
Are the piston rings
worn or damaged? If-
Do a check of the oil filter for met;
(particles. If metal particles are foun
do a full overhaul of the engine.
I
/Make sure that the piston rings
are installed correctly. Replace
the piston rings, as necessary.
(Replace the piston rings.
Engine Troubleshooting Chart
Figure 101 (Sheet 14)
71-00-01
© Cessna Aircraft Company
Page 115
Mar 1/2005
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1348
The engine has low
compression in the cylinders.
I
Are the cylinders and/or
cylinder rings worn? If I
ake sure that the valves do no
have a leak. If a leak is found,
\do a top overhaul of the engine.
fo a top overhaul of the engine,
or replace the worn cylinder. J
Engine Troubleshooting Chart
Figure 101 (Sheet 15)
71-00-01
© Cessna Aircraft Company
Page 116
Mar 1/2005
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
ENGINE - MAINTENANCE PRACTICES
1.
General
A.
2.
This section gives procedures for the removal and installation of the engine and the engine mount from
the firewall. For more maintenance information, refer to the applicable engine publications which are
listed in the Introduction - List of Manufacturers Technical Publications.
Engine Removal/Installation
A.
Remove the Engine and the Engine Mount.
NOTE:
This procedure shows how you remove the engine and engine mount from the firewall. If
the engine is removed from the engine mount and the engine mount stays attached to the
firewall, some of the steps will not be necessary. To disconnect the engine from the engine
mount, remove the (4) AN7 bolts that connect the (4) shock mounts to the engine mounting
flange and the engine mount tube.
(1) Set all cabin switches to the OFF position.
(2) Set the fuel shutoff valve to the OFF position.
(3) Remove the engine cowl. Refer to Chapter 71, Cowling - Maintenance Practices.
NOTE:
Do the subsequent steps from the right side of the airplane.
(4) Disconnect the positive and negative battery leads from the battery.
(5) Loosen the C-clamp that attaches the flexible duct to the firewall-mounted heater valve.
(6) Remove the flexible duct from the heater valve.
WARNING: If the P lead wire from the magnetos is disconnected, the
electrical ground is removed from the magneto circuit. This
will cause hot magnetos. Attach a ground wire to the magneto
or remove all the high tension wires from the spark plugs
before you turn the propeller.
(7)
(8)
(9)
(10)
(11)
(12)
(13)
Disconnect the P lead wires on the magnetos.
Remove the propeller governor. Refer to Chapter 61, Propeller Governor - Maintenance
Practices.
Disconnect the electrical connector from the Exhaust Gas Temperature (EGT) Probe.
Disconnect the fuel outlet line at the fuel strainer.
Disconnect the throttle cable at the fuel/air control unit and record the position of the washers
and spacers for later installation.
Disconnect the vacuum hoses at the firewall-mounted manifold/check valve.
Disconnect and put a label on the electrical wires on the low vacuum annunciator switches.
NOTE:
(14)
(15)
(16)
(17)
(18)
(19)
(20)
(21)
(22)
(23)
Do the subsequent steps from the left side of the airplane.
Loosen and remove the clamps from the tachometer drive cable in the engine area.
Disconnect the tachometer drive cable from the rear of the accessory case.
Cut the tie wraps (sta straps) that attach the different wire bundles to the engine mount.
On the bottom side of the engine, loosen and remove the clamps that attach the starter wires to
the sump area.
Remove the starter wires from the starter.
Disconnect the ground strap from the engine mount.
Disconnect the electrical connector from the fuel flow transducer.
Disconnect the electrical connector from the low oil pressure switch.
Disconnect the electrical connector from the oil pressure transducer.
Remove the two screws on the rear side of the upper right baffles. Remove the electrical
connector from the baffles and separate the baffles.
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
(24)
(25)
(26)
(27)
(28)
Loosen the clamps that attach the battery vent tube to the drain line cluster.
Remove the vent tube through the clamps.
Remove the bolt and spacer that attach the drain line cluster to the firewall.
Loosen and remove the ram air tubes on the rear side of the upper left baffle.
Put a stand under the tail tie-down to adjust for a tail heavy condition, which will occur when the
engine is removed from the airframe.
(29) Attach the hoist to the lifting strap on top of the engine.
CAUTION: Do not lift the engine higher than necessary. If you lift the engine
too high, it puts a strain on the attach bolts.
(30) Start to take up the engine weight using the hoist.
(31) Remove the bolts that attach the engine and engine mount to the firewall.
NOTE:
Record the sequence of nuts, washers, and flat washers.
NOTE:
You can get access to the bolt heads from inside the cockpit to keep them from turning.
(32) Slowly lift the engine using the hoist until the engine and engine mount move free of the bolts.
B.
3.
Install the Engine and Engine Mount.
(1) Attach the engine mount to the firewall. Refer to Engine Mount - Maintenance Practices.
(2) Lift the engine into position with the hoist.
(3) Torque the firewall bolts to between 160 and 190 inch-pounds.
(4) Remove the stand from under the tail tie-down.
(5) Attach the ram air tubes to the rear side of the upper left baffle.
(6) Attach the drain line cluster to the firewall with a bolt and spacer.
(7) Put the battery vent tube through the drain line clamps and tighten the clamps.
(8) Put the wires from the electrical connector through the baffle cutout area.
(9) Attach the baffle pieces together with screws.
(10) Connect the electrical connector to the oil pressure transducer.
(11) Connect the electrical connector to the low oil pressure switch.
(12) Connect the electrical connector to the fuel flow transducer.
(13) Connect the ground strap to the engine mount.
(14) Connect the starter wires to the starter.
(15) Connect the starter wires to the sump area with clamps.
(16) Connect the different wire bundles to the engine mount with tie wraps.
(17) Connect the tachometer drive cable to the rear of the accessory case.
(18) Connect the tagged wires to the low vacuum annunciator switches.
(19) Connect the vacuum lines to the firewall-mounted manifold/check valve.
(20) Connect the throttle and mixture control cables to the fuel air control unit.
(21) Connect the fuel outlet line to the fuel strainer.
(22) Connect the electrical connector to the EGT Probe.
(23) Install the propeller governor. Refer to Chapter 61, Propeller Governor - Maintenance Practices.
(24) Connect the P leads to the magnetos.
(25) If necessary, connect the high tension wires to the spark plugs.
(26) Connect the flexible duct to the firewall-mounted heater valve.
(27) Make sure that all the controls and lines are installed correctly and can move freely.
(28) Make sure that all fuel fittings are tight and that there are no leaks.
(29) Connect the positive and negative leads to the battery.
(30) Install the engine cowl. Refer to Chapter 71, Cowl - Maintenance Practices.
Engine Cleaning
A.
Clean the engine.
71-00-01
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
CAUTION: All openings must be covered with caps to prevent solvent entry into
the engine. Cover the electrical accessories (starters, alternators,
etc.) before the cleaning solvent is applied.
(1) Clean the engine using a Stoddard solvent or equivalent chemical.
4.
Engine Storage
A.
If the engine is removed for storage purposes, refer to the Lycoming Service Letter L180B (or latest
revision) for preservation procedures.
71-00-01
© Cessna Aircraft Company
Page 203
Mar 1/2005
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
COWL - MAINTENANCE PRACTICES
1.
2.
Description and Operation
A.
The engine has a top cowl, two side cowls and a bottom cowl. The front of the engine has a top and
bottom or a left and right nose-cap that is made of composite material. The cowls use quick-release
fasteners that lock into receptacles for easy removal and installation. The nose-caps attach to each
other with screws.
B.
There are two cowl flaps in the bottom cowl. They help control the engine temperature and operate
by a control lever in the cockpit.
Side Cowl Removal/Installation
NOTE:
The removal and installation is typical for the left and right side cowl.
A.
Remove the Side Cowl (Refer to Figure 201).
(1) Disconnect the quick-release fasteners around the edges of the side cowl and remove the cowl
from the airplane.
B.
Install the Side Cowl (Refer to Figure 201 for the same cowl you removed or Figure 202 for installation
of a new side cowl).
(1) Install the same cowl you removed.
(a) Attach the top edge of the cowl to the airplane.
(b) Attach the forward, aft and bottom edges of the cowl to the airplane.
(2) Install a new side cowl.
NOTE:
When a new side cowl is installed, it must be fitted to the airplane. The new cowl
must be cut and adjusted for the correct fit. The installation for the left and right side
of each new side cowl is typical.
CAUTION: You must examine the cowl after you complete each step and
install each quick-release fastener to make sure the cowl does
not wrinkle and the contour of the cowl will match the contour
of the airplane.
(a) Make sure the cowl matches the contour of the airplane correctly before you install it.
NOTE:
The cowl must fit the contour of the airplane without force used to make it fit.
Hold the cowl in position on the airplane to examine for the correct contour.
If the cowl does not fit the contour of the airplane, it is acceptable to make small form
adjustments by hand to help fit the contour.
3
If you cannot form the cowl by hand to the correct contour, then replace the cowl
before you try to fit it to the airplane.
(b) Set the cowl in position on the airplane with hole number (1) aligned with the receptacle.
1
2
NOTE:
(c)
The holes for the quick-release fasteners are numbered in Figure 202, Detail A.
If a new right side cowl is to be installed, material from the cowl must be removed to let the
cowl fit on the fuselage edge next to the fuel step handle.
CAUTION: Make sure you remove minimal cowl material as necessary.
1
2
Make a mark for the material to be removed from the cowl for clearance around the
fuel step handle.
Remove the cowl.
71-10-00
© Cessna Aircraft Company
Page 201
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
"1QAO
n
TOP
rCnAWI
(
LEFT
SIDE
COWL
AIF
HO
0710T1001
A0752T1002
A0752T1004
Engine Cowl Installation
Figure 201 (Sheet 1)
71-10-00
© Cessna Aircraft Company
Page 202
Aug 4/2003
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1350
RIGHT
NOSE-CAP
:)
BE-
BOTTOM
NOSECAP
DETAIL
B
AIRPLANES 18280001 THRU 18280667
DETAIL
B
AIRPLANES 18280668 AND ON AND
AIRPLANES T18208001 AND ON
IUICK-RELEASE
ASTENER
TOP
COWL
REWALL
n7 lTno1t n
A0752T 007
B0753T1007
C0752T1003A
Engine Cowl Installation
Figure 201 (Sheet 2)
71-10-00
© Cessna Aircraft Company
Page 203
Aug 4/2003
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
D.t10
D
4
9
A
B
5
10
1
1
2
12
3
-13
6
-
21
7
0
8
19
18
17
14
16
15
DETAIL
A
0710T1001
A0752T1002
New Side Cowl Installation
Figure 202 (Sheet 1)
71-10-00
© Cessna Aircraft Company
Page 204
Aug 4/2003
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
B1186
LUICK-RELEASE
ASTENER
TOP
COWL
REWALL
-
0.030 INCH TO
0.060 INCH
(0.762 mm TO 1.524 mm)
0
0
LEFT
SIDE
COWL
.FUSELAGE
0
(NOTE)
NOTE:
THE CLEARANCE SHOWN
IS TYPICAL FOR ALL FOUR
EDGES OF THE SIDE COWLS
VIEW
A-A
B0752T1007
AA0752T1007
New Side Cowl Installation
Figure 202 (Sheet 2)
71-10-00
© Cessna Aircraft Company
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Aug 4/2003
CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
3
Remove the marked material from the cowl.
NOTE:
A 0.75 inch (19 mm) drum sander will work good to remove the cowl
material.
(d) Align the cowl on the airplane and use duct tape to hold it in position.
CAUTION: Do not use a regular drill or damage to the receptacle can occur
if you drill too deep.
(e) Use a counterbore with an applicable size pilot to fit the pilot hole and spot-face the cowl
to 0.470 inch (12 mm) for the number (1) hole.
(f) Install a quick-release fastener with a grommet and lock it in position at hole number (1).
(g) Remove the duct tape so you can move the cowl as necessary to align the holes that
remain.
CAUTION: Make sure you spot-face and install the quick-release fasteners
and grommets in the sequence shown on Figure 202, Detail A.
(h) Use a counterbore to spot-face each pilot hole and install each quick-release fastener and
grommet in the sequence shown in Figure 202, Detail A.
1
If the pilot hole is not centered over the receptacle, use a small round file to move the
center of the pilot hole so it will be aligned over the receptacle.
If you increase the pilot hole diameter in the cowl with a round file, you must change
2
the counterbore pilot to fit the pilot hole.
3
If you do not have the correct size pilot for the counterbore, use a piece of steel
sheet-metal and drill a hole to the same diameter as the counterbore pilot which can
be used as a template to help guide the counterbore.
NOTE:
The template thickness must be sufficient to help keep the counterbore
aligned with the receptacle. Use a minimum thickness of 0.032 inch (0.81
mm) material for the template.
Clamp the template to the bottom side of the cowl hole. Make sure to align the
template pilot hole over the receptacle as you align it.
b
With the template as a guide, spot-face the pilot hole with the counterbore.
After all the cam-locks are installed, the cowl edges must be cut to the correct size.
a
(i)
CAUTION: Make sure you mark the cowl for the correct clearance. You
cannot have more than 0.060 inch (1.524 mm) clearance
between the edges of the cowl. If you cut too much off the
cowl, the cowl cannot be used.
1
2
Use an edge scribe to mark a line along all edges of the new cowl, which will give
0.030 to no more than 0.060 inch (0.762 to 1.524 mm) clearance between the edges
of the cowls. Loosen only the quick-release fasteners as necessary to let the scribe
move through that area of the cowl. Make sure you install the quick-release fastener
as soon as you move through the area.
Remove the cowl and cut just along the outside of the scribed line with sheet metal
snips.
(j)
Smooth the cowl edges with a file and sandpaper to the scribed line.
3
Install the cowl.
1
Attach the top edge of the cowl to the airplane.
2
Attach the forward, aft and bottom edges to the airplane.
71-10-00
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
(k)
Measure around all edges for the side cowl clearance to make sure there is a 0.030 to
0.060 inch (0.762 to 1.524 mm) between the cowls and that there is no overlap of the cowl
edges.
(I) Disconnect the quick-release fasteners around the new cowl and remove the cowl.
(m) Apply the finish paint. Refer to Chapter 12, Airplane Exterior - Cleaning/Painting.
(n) Install the cowl.
1
Attach the top edge of the cowl to the airplane.
2
Attach the forward, aft and bottom edges to the airplane.
C.
If Necessary, Install More Fasteners to the Left or Right Side Cowl (Refer to Figure 202).
NOTE:
As many as two more fasteners can be installed if the cowl does not tightly set on the
nose-cap. The illustration shows the left cowl, the right cowl is typical.
(1) Make a mark with approximate equal distance between position six and seven, and/or between
eight and fourteen for the new fasteners and receptacles. Make sure to keep the same edge
distance as the other fasteners.
NOTE:
The holes will be drilled with the nose-cap and side cowl attached to make sure the
holes are correctly aligned.
(2) Remove the side cowl and look to see if there is anything beneath the nose-cap that could be
damaged when you drill. Make sure the new recepticle will not touch components beneath the
nose-cap such as engine cooling baffles and seals.
CAUTION: Make sure before you install the cowl, that you will not drill into
anything on the engine side of the nose-cap.
(3) Install the side cowl.
CAUTION: Use a drill-stop to prevent the drill going to deep and cause damage
to something on the engine side of the nose-cap.
(4) Drill with a drill-stop to make a pilot hole in the cowl and nose-cap.
(5) Use a counterbore with an applicable size pilot to fit the pilot hole and spot-face the cowl and
nose-cap to 0.470 inch (12 mm).
(6) Remove the cowl.
(7) Increase the recepticle hole diameter in the nose-cap to 0.562 inch (14 mm).
(8) Install the new fastener in the cowl.
(9) Install the new receptacle in the nose-cap.
(10) Remove all metal shavings.
(11) Install the side cowl.
3.
Top Cowl Removal/nstallation
A.
Remove the Top Cowl (Refer to Figure 201).
(1) Disconnect the quick-release fasteners from the side cowls and remove the cowls.
(2) Remove the screws installed in the aft and forward edges of the top cowl. Keep the screws for
the top cowl installation.
(3) Remove the top cowl from the airplane.
B.
Install the Top Cowl (Refer to Figure 201).
(1) Put the top cowl in position on the airplane.
(2) Install the screws in the aft and forward edges of the top cowl.
(3) Install the side cowls with the quick-release fasteners.
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© Cessna Aircraft Company
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MODEL 182/T182
MAINTENANCE MANUAL
4.
5.
Nose-Cap Removal/Installation
A.
Remove the Nose-Cap (Refer to Figure 201).
(1) Disconnect the quick-release fasteners from the side cowls and remove the cowls.
(2) Remove the screws that attach the nose-cap to the bottom cowl. Keep the screws for the nosecap installation.
(3) Remove the screws that attach the two parts of the nose-cap together and remove the two nosecap pieces.
B.
Install the Nose-Cap (Refer to Figure 201).
(1) Put the two nose-cap parts in position on the airplane.
(2) Attach the two nose-cap parts together with the screws.
(3) Install the screws that attach the nose-cap to the bottom cowl.
Bottom Cowl Removal/Installation
A.
Remove the Bottom Cowl (Refer to Figure 201).
(1) Disconnect the quick-release fasteners from the side cowls and remove the cowls.
(2) Loosen the hose clamp installed on the air filter housing hose.
NOTE:
(3)
(4)
B.
6.
8.
Remove the nuts and bolts that attach the control cables to the cowl flaps.
Remove the screws that attach the aft edge of the bottom cowl to the firewall and remove the
cowl.
Install the Bottom Cowl (Refer to Figure 201).
(1) Install the screws that attach the aft edge of the bottom cowl to the firewall.
(2) Attach the control cables with the bolts and nuts to the cowl flaps.
(3) Connect the hose for air filter housing and tighten the hose clamp.
(4) Install the side cowls with the quick-release fasteners.
(5) Install the screws that attach the forward edge of the bottom cowl to the nose cap.
Cowl Repair
A.
7.
When the bottom cowl is removed, the air filter housing will remain attached to it.
For repair procedures to the cowl, refer to the Single Engine Models 172,182, 206, and T206 1996
and On Structural Repair Manual.
Cowl Flap Removal/Installation
A.
Remove the Cowl Flap (Refer to Figure 203).
(1) Set the cowl flap control lever in the OPEN position.
(2) Remove the nuts, bolts and washers that attach the control devises to the cowl flap shock
mounts. Keep the hardware for the control clevis installation.
(3) Remove the lock nuts, bolts, washers and bushing from the cowl flaps and remove the cowl
flaps from the airplane. Keep the hardware for cowl flap installation.
B.
Install the Cowl Flap (Refer to Figure 203).
(1) Install the cowl flaps with the bushings, washers, bolts and lock nuts.
(2) Attach the cowl flap control devises to the cowl flap shock mounts with the washers, bolts and
nuts.
(a) If the cowl flaps need rigged, the control clevis needs to remain disconnected.
(3) Rig the cowl flaps if necessary. Refer to Cowl Flap Rigging.
Cowl Flap Rigging
A.
Rig the Cowl Flap (Refer to Figure 203).
NOTE:
(1)
The cowl flap rigging is typical for each side.
Disconnect the cowl flap control devises from the cowl flap shock mounts.
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© Cessna Aircraft Company
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CESSNA AIRCRAFT COMPANY
MODEL 182/T182
MAINTENANCE MANUAL
a
>,
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Modify Date : 2007:12:06 14:53:21-05:00
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Title : 182SMM14 - MODEL 182/T182 SERIES (1997 AND ON)
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