BRAKE LINING CHANGE ICA Supplement - Cessna Support

CESSNA AIRCRAFT COMPANY

AIRCRAFT DIVISION

WICHITA, KANSAS 67277

BRAKE LINING CHANGE

ICA Supplement

MODEL NO: 208

SUPPLEMENT NO: ICA-208-32-00001

SUPPLEMENT DATE: 4/29/2014

© Cessna Aircraft Company

Form 2261 Rev 1


AIRCRAFT DIVISION


REVISIONS

ICA-208-32-00001 Rev: - Date: April/29/2014

ICA Summary Pages 1-6

Manuals Affected Description Title

Maintenance Manual page 1 thru 10 LIST OF PUBLICATIONS

• Added Cleveland Brake Lining Identification Guide

Maintenance Manual 32-40-00 pages201 thru 215

WHEELS AND BRAKES - MAINTENANCE PRACTICES

• In Tire Mounting Precautions Section, added a step as a procedure for how to remove stickers and stickerresidue from inside tire and from outside tube.

• In Brake Assembly Removal/Installation Section, added CAUTION and instruction not to intermix brakelinings with different part numbers on the airplane.

• In Brake Assembly Removal/Installation Section, added NOTE that it is not necessary to remove anchorbolts or anchor bolt nuts to remove the brake assembly.

• In Brake Assembly Removal/Installation Section and in Brake Backplate and Pressure Plate Removal/Installation, added a step to do the Operational Check of the Brakes as return to service.

• In Brake Backplate and Pressure Plate Removal/Installation, added a note concerning removal of brakeassembly.

• In Brake Assembly Disassembly/Reassembly Section, changed Hydraulic Fluid Specification from MIL-PRF-5606 to MIL-H-5606.

Appendix A: Illustrated PartsCatalog

32-40-00 Figure03

MAIN WHEEL BRAKE ASSEMBLY

Appendix B: Wiring DiagramManual

NOT USED

1. Export Compliance

A. This publication contains technical data and is subject to U.S. export regulations. This information hasbeen exported from the United States in accordance with export administration regulations. Diversioncontrary to U.S. law is prohibited.

ECCN: 9E991

2. Revision Bars

A. Revision bars in this ICA supplement identify new ICAs and/or changes to the current ICAs in thereleased maintenance manual.• New ICAs that are not in the current maintenance manual will have a revision bar from top to

bottom along the left margin.• ICAs that are in the current maintenance manual and have information added, deleted or revised

will have a revision bar(s) in the left margin adjacent to the added, deleted or revised information.• New or changed illustrations will have a change bar for the entire length of the page.

3. Page Numbering

A. The page number system for ICA included in this supplement have three-element numbers that areseparated by dashes. The three-element number is found at the bottom right corner of the page, leftof the page number. The date is found below the page number.

Page 1 of 6Apr 29/2014


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AIRCRAFT DIVISION


B. When the chapter/system element number is followed with zeros in the section/subsystem andsubject/unit element number (28-00-00), the information is applicable to the entire system.

C. When the section/subsystem element number is followed with zeros in the subject/unit elementnumber (28-21-00), the information is applicable to the subsystems in the system.

D. The subject/unit element number is used to identify information applicable to units in the subsystems.The subject/unit element number continues in sequence from the number -01- with the number ofsubsystem units in which maintenance information is necessary.

E. All system/subsystem/unit (chapter/section/subject) maintenance data is separated into specifiedtypes of information: Description and Operation, Troubleshooting, Maintenance Practices, etc.Blocks of page numbers that are in sequence are used to identify the type of information:(1) Description and Operation or Troubleshooting information may not be included if the procedure

is easy. When subtopics are short, they may be put together into the Maintenance Practicessection. Maintenance Practices can have a mix of subtopics that includes information to service,remove, install, adjust, test, clean, paint or do approved repairs.

(2) Longer procedures that are not as easy to do may be included in a specified section.Page 1 through 99 - Description and OperationPage 101 through 199 - TroubleshootingPage 201 through 299 - Maintenance PracticesPage 301 through 399 - ServicingPage 401 through 499 - Removal/InstallationPage 501 through 599 - Adjustment/TestPage 601 through 699 - Inspection/CheckPage 701 through 799 - Cleaning/PaintingPage 801 through 899 - Approved Repairs

F. A typical page number:

G. Illustrations use the same figure numbers as the page block in which they appear. For example, Figure202 would be the second figure in a Maintenance Practices section.



ICA-208-32-00001 Form 2261 Rev 1


AIRCRAFT DIVISION


4. Supplement Revisions

A. Revisions to this supplement may be accomplished if changes to this supplement are required afterrelease of the original issue and prior to incorporation into the manuals listed in the REVISIONS table.

B. All revisions to this supplement will have changes identified in detail in the revision block(s) above.

C. All pages in this ICA supplement will have the same date and are valid as of the date shown.

5. ICA Incorporation into Applicable Manuals

NOTE: Most ICA supplements will be incorporated in the next available revision to the manuals listedabove and should be used in conjunction with those manuals until the next available revision isreleased.

A. The ICA Supplement List located in the Introduction section of each manual listed in the REVISIONStable will indicate the incorporation status as of the release date of the published revision.

B. The manual revision level of the supplement incorporation will be listed in the "Manual IncorporationStatus" column in the ICA Supplement List, when those ICAs associated with that manual have beenincorporated. After ICAs are incorporated, the manual that they are incorporated in must now be usedfor those ICAs instead of the supplement.• Based on revision cycle times for the affected manuals, MM ICAs, WDM ICAs, etc. in this

supplement may be incorporated in the manuals at different times.• There will not be a revision to this supplement to indicate incorporation in the manuals. Users are

required to check the ICA Supplement List for each manual affected to determine incorporationstatus.

C. This supplement will be completely superseded by the manuals listed in the REVISIONS table whenit has been incorporated in all of the manuals.



ICA-208-32-00001 Form 2261 Rev 1


AIRCRAFT DIVISION


INTRODUCTION

1. Purpose

A. The purpose of this Supplement is to provide the maintenance technician with the informationnecessary to ensure the correct functionality and performance of the Brake Lining Change on theCessna Model 208 until this information gets incorporated into the next revision to the manuals listedin the "REVISIONS" section of this supplement.

B. This ICA supplement is designed to satisfy the requirements of 14 CFR 23.1529 "Instructions forContinued Airworthiness" associated with this installation. This document is a supplement to theModel 208 Maintenance Manual and will be incorporated in the next revision to the manual.

C. When this information is incorporated in the next revision to the manuals listed in the "REVISIONS"section, those manuals shall take precedence over this supplemental document. Refer to the "ICASupplement List" in the "Introduction" section of the respective manual for the status of all applicableICA Supplements.

D. Revisions to this supplement may occur if there is a change to any of the ICAs in this supplementprior to incorporation into all of the affected manuals.

NOTE: This document must be placed with the aircraft operator's Technical Library CD-ROMor Model 208 Maintenance Manual and incorporated into the operator's scheduledmaintenance program.

2. Effectivity

A. These Instructions for Continued Airworthiness (ICA) are effective for the following aircraft model andserialization.

Model Beginning Effectivity Ending Effectivity

208 20800567 and On

208B 208B5170 and On

3. Complete ICA Documents

A. The following document(s), in conjunction with this supplement, constitute the Instructions forContinued Airworthiness for the Brake Lining Change on the Cessna Model 208. All items must beavailable to the operator at initial delivery.(1) Model 208 Maintenance Manual

4. System Components

A. Refer to Appendix A: Illustrated Parts Catalog



ICA-208-32-00001 Form 2261 Rev 1


AIRCRAFT DIVISION


LIST OF INSTRUCTIONS FOR CONTINUED AIRWORTHINESS

1. Model 208 Maintenance Manual

A. Introduction(1) Refer to List of Publications

B. Chapter 32 Landing Gear(1) Refer to 32-40-00, Wheels and Brakes - Maintenance Practices.



ICA-208-32-00001 Form 2261 Rev 1


AIRCRAFT DIVISION


INSPECTION PROGRAM AND AIRWORTHINESS LIMITATIONS

1. Continuous Inspection Program

A. This ICA Supplement does not affect the current inspection program.

2. Airworthiness Limitations

A. Cessna Aircraft Company Model 208 Maintenance Manual, Chapter 4, Airworthiness Limitations,contains the system and airframe limitations for the Model 208.

NOTE: The Airworthiness Limitations section is FAA-approved and specifies maintenancerequired under Section 43.16 and 91.403 of Title 14 Code of Federal Regulations, unlessan alternative program has been FAA approved.

(1) There are no new (or additional) airworthiness limitations associated with this equipment and/orinstallation.



ICA-208-32-00001 Form 2261 Rev 1


MODEL 208MAINTENANCE MANUAL

LIST OF PUBLICATIONS

1. List of Manufacturers Technical Publications Available Through Cessna

A. The following listed publications are necessary for the support of your Model 208. Contact theappropriate manufacturer to order the publications that are necessary for the support of your Model208.

NOTE: The publications made by King Radio and Sigmatek Inc./ARC Avionics must be ordereddirectly from the manufacturer. The publication names, numbers and addresses are listedafter this section.

Table 1. Chapter 21 - Air Conditioning

Item CessnaPartNumber

Manufact-urers PartNumber

Publica-tion PartNumber

Publication Title Manufacturer

VentBlower

33E83-2 37E66-1-13

33E83 BlowerAssembly ComponentMaintenance Manual(Vent Blower) withIllustrated Parts List

FL Aerospace Corp.Janitrol Aero Div.4200 Surface Rd.Columbus, OH 43228

Flow Con-trol Valve,and Tem-peratureControlValve

1H101-4,1H102-2

CM-200-1 Airborne ComponentOverhaul Manual WithIllustrated Parts List

Parker-Hannifin Corp.Airborne Division711 Taylor St.P.O. Box 4032Elyria, OH 44036

Table 2. Chapter 22 - Auto Flight





GFC -700Autopilot

190-00869-00

G1000 Caravan LineMaintenance Manual

Garmin International,Inc.1200 E. 151st StreetOlathe, Kansas 66062

AutopilotServo

GSA8X/GSM 85

190-00303-72

Installation Manual Garmin International,Inc.

AutopilotServo Gearbox

GSM 86 190-00303-83

Installation Manual Garmin International,Inc.

Table 3. Chapter 23 - Communications





GarminGDL69/69A

011-00987-00

190-00355-02

Garmin GDL 69/69AInstallation Manual

Garmin International,Inc.1200 E. 151st StreetOlathe, Kansas 66062

LIST OF PUBLICATIONS Page 1© Cessna Aircraft Company Apr 29/2014

ICA-208-32-00001 Form 2261 Rev 1



Table 4. Chapter 24 - Electrical Power





DC to DCPowerConverter

RG40 83706C Removal/InstallationManual Model RG40Regulated DC toDC Converter (FAATSO-C71 Approved)

KGS Electronics, Inc.418A E. Live Oak Ave.Arcadia, CA 91006-5690

Battery G6381E GSM682-13

Gill Battery ServiceManual

Teledyne BatteryProducts840 W. Brockton Ave.P.O. Box 431Redlands, CA 92373

Battery 30994-001 BA89-9/92-13

Battery InstructionManual (NICAD)Marathon BatteryService Manual

Marathon PowerTechnologies Co.8301 Imperial Dr.Waco, TX 76712-6588

Table 5. Chapter 27 - Flight Controls





RudderGust LockKit

AT-RL-1001-ICA

Rudder Gust Lock KitMaintenance Manualwith Illustrations

Aero Twin Inc.2404 Merrill Field Dr.Anchorage, AK 99501


ICA-208-32-00001 Form 2261 Rev 1



Table 6. Chapter 30 - Deice





PropellerDe-IceBrushBlock

3E2090-1 68-04-714K13

Propeller Deice SystemBrush Block AssemblyOverhaul Manual andIllustrated Parts Catalog

BF GoodrichAerospace Div.Engineered PolymerProducts150 Division Dr.Wilmington, NC 28401

PropellerDe-Ice

3E2205-4 68-04-712D-13

Propeller Deice SystemMaintenance Manual

BF GoodrichAerospace Div.Engineered PolymerProducts150 Division Dr.Wilmington, NC 28401

PropellerAnti-icingBoot

18361-12-83

Propeller Anti-icing BootRemoval and InstallationManual

Hartzell Propeller Inc.One Propeller PlacePiqua, OHU.S.A 45356- 2634Web: http://www.hartzellprop.com/service_support.php

PropellerIceProtection

18030-61-80

Propeller Ice ProtectionSystem Manual


PropellerDe-Ice

9910587-202

P7036368-0154

830415-1-13

McCauleyElectrothermal DeiceSystems Service PartsManual

McCauley PropellerSystemsP.O. Box 7704Wichita, KS 67277-7704

PnuematicDe-IceBoots

BFG30-10-31

Pneumatic De-IcerInstallation, Maintenanceand Repair Manual

Goodrich CorporationAerospace Div.Ice Protection Systems1555 Corporate WoodsParkwayUniontown, OH 44685

PnuematicDe-IceBoots

BFG30-10-70

Fastboot PneumaticDe-Icer InstallationInstructions

Goodrich CorporationAerospace Div.Ice Protection Systems1555 Corporate WoodsParkwayUniontown, OH 44685


ICA-208-32-00001 Form 2261 Rev 1



Table 7. Chapter 31 - Indicating/Recording Systems





L-3 FA2100CVDR

165E1847-01

L-3 CommunicationsFA2100 CVDRInstallation andOperation Manual

L-3 CommunicationsAviation Recorders P.O.Box 3041 Sarasota, FL34230

L-3 FA2100CVDR

165E1630-00

Lao CommunicationsPortable Interface (PI)Operators Manual


L-3 FA2100CVDR

165E1696-002 (rev 3or higher)

L-3 CommunicationsROSE / PI SoftwareVersion 3.0 OperatorsManual


Table 8. Chapter 32 - Landing Gear





BrakeAssemblies

AWBCMM-0001-X

ComponentMaintenance Manualfor External DesignWheels & Brakes

Parker-Hannifin Corp.Aircraft Wheel and BrakeDivision1160 Center RoadAvon, OH 44011

BrakeLinings

Brake LiningIdentification Guide

Parker-Hannifin Corp.Aircraft Wheel and BrakeDivision1160 Center RoadAvon, OH 44011


ICA-208-32-00001 Form 2261 Rev 1



Table 9. Chapter 34 - Navigation





G1000 sys-tem com-ponents

190-00869-00

G1000 LineMaintenanceManual (CessnaCaravan)

Garmin International,Inc.

85 ServoMount

011-00878-00

190-00303-72

GSA 8X/GSM 85(A)Installation Manual

Garmin International,Inc.

GSM 86ServoMount

SupplierPN: GSM86

190-00303-83

GSM 86 Servo Gear BoxInstallation Manual

Garmin International,Inc.1200 E. 151st St.Olathe, KS 66062

NAV/COMMTestSet (IFR4000)

Supplier PNIFR 4000

AeroflexNAV/COMMTest SetIFR 4000OperationManual

AC0823CD

Aeroflex Wichita Division10200 West YorkWichita, KS 67215

Storm-scope Se-ries IIWeatherMappingSystems

WX-1000 78-8051-9150-0

Stormscope SeriesII Weather MappingSystems WX-1000Installation Manual

L-3 CommunicationsAvionics Systems5353 52ND Street, S.E.Grand Rapids, MI49512-9704

Table 10. Chapter 35 - Oxygen





PortableOxygenBottle

5500AGW-FF23A

AVOX ComponentMaintenace Manual

AVOX Systems Inc.225 Erie St.Lancaster, NY 14086

Table 11. Chapter 36 - Pneumatic





PressureRegulator

1H75-14 CM200-1 Airborne ComponentOverhaul Manual withIllustrated Parts List

Parker-Hannifin Corp.711 Taylor St.P.O. Box 4032Elyria, OH 44036


ICA-208-32-00001 Form 2261 Rev 1



Table 12. Chapter 61 - Propellers





Propeller HC-B3MN3/M10083

135C-13 Composite BladeInspection, Repair, andOverhaul Instructions

TRW Hartzell PropellerDivision of TRW Inc.1800 Covington Ave.Piqua, OH 45356

Propeller HC-B3N21100S

13961-00-39

Propeller Owner'sManual and Logbook(Steel Hub TurbinePropellers withAluminum Blades)


Propeller HC-B3N21050S

14661-00-46

Propeller Owner'sManual and LogbookModels: HC-B3MN-3HC-B4MN-5ALHC-B4MP-3A

Hartzell Propeller Inc.One Propeller PlacePiqua, OHU.S.A 45356- 2634

PropellerSpinner

D4898PD4899

127-13 Spinner AssemblyMaintenance InstructionGuide

TRW Hartzell PropellerDivision of TRW Inc.1800 Covington Ave.Piqua, OH 45356

Propeller 9910587-201

P7036368-01

8103012-13

McCauley C700Propeller ServiceManual

McCauley PropellerSystemsP.O. Box 7704Wichita, KS 67277-7704


ICA-208-32-00001 Form 2261 Rev 1



Table 13. Chapter 71 - Engine





Engine600SHP

9910579-1

PT6A-114 3043512 Pratt & WhitneyPT6A-114/116/135/135AMaintenance Manual

Pratt & Whitney CanadaInc.100 Marie-Victorin Blvd.Longueuil, QuebecCanada J4G 1A1

Engine600SHP

9910579-1

PT6A-114 3043514 Pratt & WhitneyPT6A-114/116/135/135AIllustrated Parts Catalog


Engine675SHP

9910589-1

PT6A-114A 3043512 Pratt & Whitney PT6A-114/114A/116/135/135AMaintenance Manual


Engine675SHP

9910589-1

PT6A-114A 3043514 Pratt & Whitney PT6A-114/114A/116/135/135AIllustrated Parts Catalog


Engine867SHP

2650001-2

PT6A-140 3075742 Pratt & WhitneyPT6A-140 MaintenanceManual


Table 14. Chapter 77 - Engine Indicating





FASTEngineTrendMonitor

2618507 FAST-A-010-4

3077188 Abbreviated ComponentMaintenance Manual(ACMM)



2618507 Monitor Transfer ModuleHelp Manual andReference Manual



2618507 FAST Configuration andTest

Pratt & Whitney EngineServices.249 Vanderbilt, Ave.Blvd.Norwood, MA 02062


ICA-208-32-00001 Form 2261 Rev 1



Table 15. Chapter 80 - Starter/Generator





200SGL119Q-2

200SGL119Q-2RX

200SGL153Q

Starter/Generator

200SGL153QRX

TM105A

Overhaul Instructionswith IllustratedParts Breakdown- Starter-GeneratorModels 200SGL-XXXX

Skurka Aerospace Inc.4600 Calle BoleroP.0. Box 2869Camarillo, CA 93011Web: www.skurka-aero.com

Starter/Generator

300SGL145Q

TM109 Overhaul Instructionswith IllustratedParts Breakdown- Starter-GeneratorModels 300SGL-XXXX

Skurka Aerospace Inc.

Starter/Generator

23081-22 23081-023-3-13

Lear Siegler 23081DC Starter/ GeneratorOverhaul Manual withIllustrated Parts List

Lucas AerospacePower Equipment Corp.777 Lena DriveAurora, OH 44202

Starter/Generator

23081-22 23700-6-13

Lucas AerospaceDC Generators andStarter-GeneratorsMaintenance Manual

Lucas AerospacePower Equipment Corp.777 Lena DriveAurora , OH 44202

GeneratorControl UnitAssembly

51539-012N

51539-012-13

Lear Siegler 51539-012DC Generator ControlUnit Overhaul Manualwith Illustrated Parts List

Lucas AerospacePower Equipment Corp.777 Lena DriveAurora, OH 44202

2. Radio Manufacturer Manuals

A. The following publications must be ordered directly from Honeywell. Refer to the following list foraddress and telephone numbers:

UNITED STATES OPERATIONS

Honeywell International, Inc.,Aerospace Electronics Systems1 Technology Center23500 W. 105th StreetOlathe, KS 66061

800-257-0726 - Direct line to the Product Support Operator for assistance from Customer Service,Product Specialists, Warranty, Field Engineering and Training.913-782-0600 - 24 hour emergency service during nonworking hours.Telex: WUD (0) 4-229Cable: KINGRAD


ICA-208-32-00001 Form 2261 Rev 1



EUROPEAN MARKETING OFFICE:

Telephone: Switzerland 22 98 58 80Telex: Switzerland 289445. Answer back: King CHGeneva, Switzerland

Telephone: France 4 422 1747Telex: France 150952. Answer back: KINGRADIvry-Le Temple

MANUALNUMBER

MANUAL TITLE

006-0180-01 Audio Panel/Marker Beacon Receiver Installation Manual (Type KMA-24)

006-5180-01 Audio Panel/Marker Beacon Receiver Overhaul/Maintenance Manual (TypeKMA-24)

006-0179-03 VHF NAV/COMM Transceiver Installation Manual (Type KX-155/KX-165)

006-5179-03 Weather Radar Installation Manual (Type KX-155/KX-165)

006-0191-01 Weather Radar Installation Manual (Type KWX-56, KI- 244, KA-126)

006-5193-01 Weather Radar Overhaul/Maintenance Manual (Type KWX-56, KI-244, KA-126)

006-0184-02 Automatic Direction Finder Installation Manual (Type KR-87, KI-227, KA-44B)

006-0534-01 Transponder Installation Manual (Type KT-79)

006-5534-00 Transponder Overhaul/Maintenance Manual (Type KT-79)

006-0176-03 DME/Master Indicator/Slave Indicator Installation Manual (TypeKN-63/KDI-572/KDI-573/KDI-574)

006-5176-01 DME Overhaul/Maintenance Manual (Type KN-63)

006-5178-00 DME Indicator Overhaul/Maintenance Manual (Type KDI-572/KDI-573/KDI-574)

006-0193-01 Radio Magnetic Indicator Installation Manual (Type KNI-582)

006-5193-00 Radio Magnetic Indicator Installation Manual (Type KNI-582)

006-0137-03 VOR/LOC/GS Indicator Installation Manual (Type KI-202, KI-203, KI-204, KI-206,KI-207)

006-5137-03 VOR/LOC/GS Indicator Overhaul/Maintenance Manual (Type KI-202, KI-203,KI-204, KI-206, KI-207)

006-0185-00 Digital Area Navigation System Installation Manual (Type KNS-81)

006-5185-00 Digital Area Navigation System Overhaul/Maintenance Manual (Type KNS-81)

006-0152-02 Radar Altimeter Installation Manual (Type KRA-10A) (KI-250 Included)

006-5152-02 Radar Altimeter Overhaul/Maintenance Manual (Type KRA-10A) (KI-250 Included)

006-10536-02 Radar Altimeter Installation Manual (Type KRA-405B) (KNI-415/416 Included)

006-10557-0006 Autopilot Installation Manual (Type KFC225)

006-00702-0000 Flight Control and Avionics System Installation Maintenance Manual

006-0169-03 VHF Comm Transceiver Installation Manual (Type KY-196)

006-5169-03 VHF Comm Transceiver Overhaul/Maintenance Manual (Type KY-196)

006-0192-02 Radio Magnetic Indicator Installation Manual (Type KI-229)

006-5192-00 Radio Magnetic Indicator Overhaul/Maintenance Manual Type KI-229)


ICA-208-32-00001 Form 2261 Rev 1



3. Sigmatek Inc./ARC Avionics Manufacturer Manuals

NOTE: Following listed Sigmatek Inc./ARC publications must be ordered directly from SigmatekInc./ARC Avionics, Attn: ARC Order Entry, 1001 Industrial Rd., Augusta, Kansas 67010, USA.Telephone No. 316-775-1178.

MANUAL NUMBER MANUAL TITLE

RP0070104-320 300/400 Series Navigation Indicators

RP0070104-310 400 Nav/Com (Type RT-485B) Service/Parts Manual

RP0070104-370 400 Marker Beacon (Type R-402) Service/Parts Manual

RP0070103-580 400 Glide Slope Receiver (Type R-443B) Service/Parts Manual

RP0070104-140 400 RMI (Type IN-404A) Service/Parts Manual

RP0070103-610 400 ADF (Type R-546E) Service/Parts Manual

RP0070103-780 400 ADF (Type R446A) Service/Parts Manual

RP0070104-280 400/1000 DME (Type RN-477A) Service/Parts Manual

RP0070104-290 400/1000 RNAV (Type RN-479A) Service/Parts Manual

RP0070104-341 400B Autopilot/IFCS Vol. I (Type AF-550A & IF-550A)

RP0070104-342 400B Autopilot/IFCS Vol. II (Type AF-550A & IF-550A)

RP0070104-343 400B Autopilot/IFCS Vol. III (Type AF-550A & IF-550A)

RP0070104-344 400B Autopilot/IFCS Vol. IV (Type AF-550A & IF-550A)

RP0070104-440 400 Audio Amplifier (Type SDM-490A) Service/Parts Manual

RP0070104-447 300 DME (Type SDM-77A) Service/Parts Manual

RP0070104-330 300/400/800 Transponder (Type RT-359A & RT-459A) Service/Parts Manual

7010429 400 RNAV (Type RN-479A) Service/Parts Manual

D4551-13 400 Encoding Altimeter (Type EA-401A) Service/Parts Manual

D4551-13 800 Encoding Altimeter (Type EA-801A) Service/Parts Manual

D4556-13 800 Alerter (Type AA-801A) Service/Parts Manual


ICA-208-32-00001 Form 2261 Rev 1



WHEELS AND BRAKES - MAINTENANCE PRACTICES

1. General

A. This section provides information on brake system bleeding, wheel removal/installation, tire mountingand dismounting, brake components removal/installation and brake inspection criteria.

2. Tire Mounting Precautions

A. Tire Mounting and Dismounting Criteria (Refer to Figure 201).(1) Prior to removing the wheel/tire assembly from the airplane, completely deflate the tire with a

deflation cap. It is good practice to deflate the tire before removing the axle nut. When allpressure has been relieved, remove the valve core. Valve cores under pressure can be ejectedlike a bullet. If wheel or tire damage is suspected, approach the tire from the front or rear, notfrom the side (facing the wheel).

CAUTION: A tire/wheel assembly that has been damaged in service should bedeflated by a remote means. If this is not possible, the tire/wheelassembly should be allowed to cool for a minimum of three hoursbefore the tire is deflated.

(2) Take special care when encountering difficulty in freeing tire beads from wheel flanges. Tryingto pry beads free incorrectly may cause an accident. Even with tire tools, care must be taken toprevent damage to beads or wheel flanges. On small tires, successive pressing with a two-footlength of wood close to the bead or tapping with a rubber mallet is generally sufficient.

(3) Ensure the mating tire and tube are specified and correct for the wheel/tire assembly.(4) Remove stickers from the inside of the tire and the outside of the tube. Remove sticker residue

with isopropyl alcohol or suitable solvent.(5) Clean inside of tire, then lubricate lightly with talcum powder.(6) Inflate tube to slightly round and insert in tire. This aids in mounting tire and tube to wheel half

and helps prevent pinching tube.(7) Align yellow stripe on tube with red balance dot on tire. Align red dot with valve if no stripe exists

on tube.

NOTE: After inserting valve stem in hole on wheel half, connect a valve stem puller deviceto the valve stem to prevent the valve stem from receding from hole in wheel half.

(8) When mounting tire and tube on wheel, ensure wheel bolts are torqued to wheel manufacturer'sinstructions before inflating.

(9) Inflate tire in a safety cage to rated pressure.(10) Deflate to equalize stretch.(11) Reinflate to rated pressure.(12) After a 12-hour stretch period, reinflate to rated inflation pressure.

3. Servicing Tires and Tubes

A. For servicing procedures related to tires and tubes, refer to Chapter 12, Tires - Servicing.

4. Brake System Replenishing

A. For replenishing of the Brake System, Hydraulic Fluid, refer to Chapter 12, Hydraulic Fluid - Servicing.

32-40-00 Page 201© Cessna Aircraft Company Apr 29/2014

ICA-208-32-00001 Form 2261 Rev 1



5. Brake System Bleeding

NOTE: Anytime a brake line is disconnected or a spongy feel to the brake pedal is detected, there islikelihood air has entered the system. To assure proper braking action, all trapped air must beremoved from the system by the following procedures.

A. Brake Bleeding Procedures(1) Ensure parking brake handle is off (fully in).(2) Connect hydraulic pressure source, such as a hand pump or Hydro Fill unit, to right brake wheel

cylinder bleeder valve.(a) It is necessary that you only use hydraulic fluid with MIL-H-5606 specifications.

(3) Open bleeder valve and begin pumping hydraulic fluid into the system while observing fluid levelin brake system reservoir, located on lower left corner of firewall in engine compartment.

(4) When the reservoir is full, close the wheel-brake bleeder valve and remove pressure source.(5) Using a test syringe or equivalent, remove 90% of fluid from the reservoir.

(a) Make sure that the remaining fluid covers the outlet fitting in the base of the reservoir.(6) Connect a hydraulic pressure source to the left wheel-brake bleeder valve.

(a) It is necessary that you only use hydraulic fluid with MIL-H-5606 specifications.(7) Open the left wheel-brake bleeder valve and pump hydraulic fluid into the system while you

observe the fluid level in the brake system reservoir.(8) When the reservoir is full, close the left wheel-brake bleeder valve and remove the pressure

source.(9) Make sure that the reservoir is filled to the full line.(10) Close both bleeder valves.

(a) Torque each of the valves to 35-45 In-Lbs.(11) Reinstall the brake fairings.

6. Main Wheel and Tire Removal/Installation

A. Remove Main Wheel and Tire (Refer to Figure 201).(1) Jack airplane. Refer to Chapter 7, Jacking - Maintenance Practices.

WARNING: Make sure that you deflate the tires before you remove thewheel/tire assemblies from the airplane. When all pressurehas been released, use an extraction tool to remove the valvecore from the valve stem. Valve cores under pressure canbe ejected from the valve stem and cause injury to personnelor damage to the airplane. If you think there is wheel or tiredamage, get access to the tire from the front or rear, not fromthe side (facing the wheel).

(2) Deflate tire completely.(3) Remove backplate bolts (12), washers and shims (3) attaching brake backplate to brake

assembly. Remove backplate.(4) Remove cotter pins and axle nut.

NOTE: Bearings and bearing seals will be removed during disassembly.

(5) Pull wheel from axle.(6) Examine the axle fittings for cracks, corrosion, pits, security, and any other damage.

(a) Make sure that the attach bolts have sufficient thread engagement in the self-locking nuts.(7) Examine the outer wheel axle surface and attachment bolts for condition, cracks, corrosion,

signs of damage, and wear.


ICA-208-32-00001 Form 2261 Rev 1



Main Wheel, Tire and Tube InstallationFigure 201 (Sheet 1)


ICA-208-32-00001 Form 2261 Rev 1



Main Wheel, Tire and Tube InstallationFigure 201 (Sheet 2)


ICA-208-32-00001 Form 2261 Rev 1



(8) Examine the inner main gear wheel axle surface for corrosion.

NOTE: The main gear axle is a time limited part. You should verify the current number oflandings, inspection status and replacement time before you install the main wheeland tire. Refer to Chapter 4, Replacement Time Limits and Typical Inspection TimeLimits for the applicable inspection criteria.

(9) Examine the main gear axle attachment to the axle fitting and the attachment bolts for corrosion,cracks, signs of damage, and security.

(10) Examine the main gear axle fitting where it is installed to the outer spring and the attachmentbolts for corrosion, cracks, signs of damage, and security.(a) Make sure that the axle fittings part number/serialization identification placards are

securely attached.(11) Examine the fillet seal around the main gear spring and at the axle fitting.

(a) If the seal is broken, loose, or deteriorated, replace it with a new fillet seal using Type 1,Class B ½ sealant. Refer to Chapter 20, Fuel, Weather and High-Temperature Sealing -Maintenance Practices.

(12) Examine the axle spacer for wear at the grease seals contact area. If the grooves will not let theseal seat correctly, replace the axle spacer.

NOTE: Cessna Propeller Aircraft Product Support, 316-517-5800 or Fax 316-942-9006, isthe source to get the information on damage criteria.

(13) Remove all wheel bearing cones.(a) Clean the bearing cones and cups and the wheel halves with stoddard solvent or an

equivalent approved cleaning solvent.

WARNING: Use low pressure shop air to dry bearings. Do not spinbearing cones with compressed air. Dry running bearingswithout lubrication can explode.

(14) Examine for, and replace the bearing cups if the cups are loose in the wheels, or there arescratches, pitting, corrosion, or signs of overheating.

(15) Examine for, and replace the bearing cones if there are nicks, scratches, water staining, spalling,heat discoloration, roller wear, cage damage, cracks, or distortion.

(16) Re-pack bearings with general purpose grease MIL-G-81322 or an equivalent grease.(17) Install the bearings in the wheels with new grease seals.

B. Install Main Wheel and Tire (Refer to Figure 201).(1) Place wheel assembly on axle.(2) Install axle nut and rotate wheel while torquing to 60 inch-pounds (6.8 N.m). Back off axle nut

and torque to 30 inch-pounds (3.4 N.m) while rotating wheel. Tighten axle nut to next castellationbut do not advance nut in excess of 15 degrees (one-half castellation). Install cotter pin.(a) If torque exceeds 40 inch-pounds (4.5 N.m) during final tightening, remove nut and install

washers as required to meet the torque requirements given above. Washers (Clevelandpart number 153-00100) can be ordered from Cessna Parts Distribution.

(3) Install brake backplate (1) and shim (3) using bolts (12) and washers. Torque bolts from 85 to90 inch-pounds (9.6 to 10.2 N.m).

NOTE: Bolts (12) incorporate a special self-locking feature and are typically good forapproximately four to six reuses. If bolt (12) can be fully engaged into the backplateby hand with no resistance, the self-locking feature of bolt (12) has been destroyedand the bolt should be rejected. Replacement bolts (part number 103-14300) can beordered from Cessna Parts Distribution.

(4) Inflate tire to proper pressure. Refer to Chapter 12, Tires - Servicing.(5) Remove airplane from jacks. Refer to Chapter 7, Jacking - Maintenance Practices.


ICA-208-32-00001 Form 2261 Rev 1



7. Main Wheel, Tire and Tube Disassembly/Reassembly

WARNING: Injury can result from attempting to separate wheel halves withtube inflated. Take care to avoid damaging wheel halves whenbreaking tire beads loose.

A. Disassemble Main Wheel, Tire and Tube (Refer to Figure 201).

NOTE: Refer to Tire Mounting Precautions before disassembly of main wheel, tire and tube.

(1) Ensure tube (11) is deflated completely then break beads of tire (10) loose.(2) Remove thru-bolts (14) and separate wheel halves (6) and (12). Retain spacer (8).(3) Remove tire (10), tube (11) and brake disk (13).(4) Remove snap rings (3), grease seals (4) and bearing cone (5) from inboard wheel half (12).(5) Remove snap ring (3), grease seal (4), bearing cone (5), from outboard wheel half (6).

NOTE: Bearing cups (7) are a press-fit in wheel halves (6) and (12) and should not beremoved unless replacement is necessary. To remove bearing cups (7), heat wheelhalf in boiling water for 15 minutes. Using an arbor press, press out bearing cup andpress in new bearing cup while wheel is still hot.

B. Assemble Main Wheel, Tire and Tube (Refer to Figure 201).

NOTE: Refer to Tire Mounting Precautions before reassembly of main wheel, tire and tube.

(1) Clean the inside of both wheel halves with mineral spirits.(2) Let it dry and apply Royco 103 or other MIL-C-16173 Type 1, Grade 1 protectant to all surfaces

except the bearing outer race and the flanges where the tire bead seats.

NOTE: A swab may be necessary to apply protectant to the wheel material inside the boltholes.

(3) If replacing the bearing outer races, remove outer race and clean race cup bore surfaces of thewheel and apply a thin coating of protectant to the mating surface of the wheel. Install outer racewhile protectant is still wet.

(4) Brush coat the wheel surfaces around outer race after race installation to replace any protectantremoved during the race installation.

NOTE: Some protectant in the snap ring (3) groove is permitted, but do not fill the groove.Too much protectant can be removed with mineral spirits.

(5) Insert thru-bolts (14) through brake disk (13) and position in inner wheel half (12), using bolts toguide disc. Ensure disc is bottomed in wheel half.

(6) Position tire (10) and tube (11) on outboard wheel half (6).

NOTE: Lightweight point of tire is marked with a red dot on tire sidewall and heavyweightpoint of tube is marked with a contrasting color line (usually near valve stem). Wheninstalling tire, place these marks adjacent to each other.

(7) Valve stem (9) must protrude through hole in wheel half (6).(8) With spacer (8) positioned into inboard wheel (12), place outboard wheel half (6) in position,

applying a light force to keep wheel halves together. Do not pinch tube (11) between wheelhalves.

(9) Assemble washers (2) and nuts (1) on thru-bolts (14).(10) Torque nuts (1) evenly to 150 inch-pounds (16.9 N.m).


ICA-208-32-00001 Form 2261 Rev 1



CAUTION: Uneven or improper torque of thru-bolt nuts (1) can cause boltfailure with resultant wheel failure.

(11) Inflate tube to set tire beads, then adjust tire pressure. Refer to Chapter 12, Tires - Servicing.(12) Clean bearing cones (5) and repack with clean wheel bearing grease. (Refer to Chapter 12.)(13) Assemble bearing cone (5) and grease seal (4) into inboard wheel half (12) and secure with

snap ring (3).(14) Assemble bearing cone (5) and grease seal (4) into outboard wheel half (6) and secure with

snap ring (3).

8. Brake Backplate and Pressure Plate Removal/Installation

NOTE: Brake linings can be removed without removing main wheels or disconnecting brake lines.

NOTE: It is not necessary to remove the anchor bolts or the anchor bolt nuts to remove the brakeassembly.

A. Remove Backplate and Pressure Plate (Refer to Figure 202).(1) Remove brake backplate bolts (12).(2) Remove backplates (1) and shim (3). Only one shim is allowed.(3) Slide brake cylinder (13) clear of anchor bolts (8).(4) Remove pressure plate (7) and linings (6) from anchor bolts (8).(5) Retain brake piston insulators (9).

B. Install Backplate and Pressure Plate (Refer to Figure 202).

CAUTION: Brake linings with different part numbers must not be intermixed on theairplane. Brake function can be altered and diminished as a result ofintermixed brake linings.

(1) Find and record the part numbers for all of the brake linings on the left and on the right sides.Make sure that all of the brake linings that are installed and all of the replacement brake liningsthat you will install have the same part numbers.

NOTE: Refer to the Cleveland Brake Lining Identification Guide if the part numbers on thebrake linings are not legible.

(2) Slide new brake lining (6) and pressure plate (7) over anchor bolts (8).(3) Insert piston insulators (9) opposite pistons (11) and slide brake cylinder (13) over anchor bolts

(8).(4) Position backplates (1) and shim (3) over brake disc (4) opposite backplate bolt holes in brake

cylinder (13).(5) Install backplate bolts (12) and torque from 85 to 90 inch-pounds.

NOTE: Backplate bolts (12) incorporate a special self-locking feature and are typically goodfor approximately four to six reuses. If backplate bolt (12) can be fully engaged intothe backplate by hand with no resistance, the self- locking feature of backplate bolt(12) has been destroyed and the backplate bolt should be rejected. Replacementbolts (part number 103-14300) can be ordered from Cessna Parts Distribution.

(6) Do the Operational Check of the Brakes. Refer to Chapter 32-40-00, Wheels and Brakes -Inspection/Check, Brakes Operational Check.

9. Brake Assembly Removal/Installation

A. Remove the Brake Assembly (Refer to Figure 202).(1) Without applying brakes, pull parking brake handle to the ON position (fully out).(2) Disconnect brake line at brake cylinder (13) and allow fluid to drain from brake line.


ICA-208-32-00001 Form 2261 Rev 1



Brake AssemblyFigure 202 (Sheet 1)


ICA-208-32-00001 Form 2261 Rev 1



(3) Remove backplate bolts (12) and backplates (1).(4) Slide brake cylinder assembly (13) off torque plate (5).

B. Install the Brake Assembly (Refer to Figure 202 ).(1) Install pressure plate (7) over anchor bolts (8).

CAUTION: Do not use a liquid lubricant on the anchor bolts or torque platebusings. Liquid lubricant can attract dirt and moisture that cancause the accelerated wear or corrosion of the components.

(2) Lubricate the anchor bolts and torque plate bushings with the following:(a) For non-amphibious environments, use Silicone Spray, Dri-Slide®Multi-Purpose Lubricant

or LPS Force 842® Dry Moly Lubricant (equivalent substitutes are permitted).(b) For amphibious environments, use Lubriplate X-357 Extreme Pressure Moly Lubricant

(equivalent substitutes are permitted).(3) Slide brake cylinder assembly (13) onto torque plate (5).(4) With shim (3) positioned against backplates (1), install backplate bolts (12) and torque from 85

to 90 inch-pounds (9.6 to 10.2 N.m).

NOTE: Backplate bolts (12) incorporate a special self- locking feature and are typically goodfor approximately four to six reuses. If backplate bolt (12) can be fully engaged intothe backplate by hand with no resistance, the self-locking feature of backplate bolt(12) has been destroyed and the backplate bolt should be rejected. Replacementbolts (part number 103- 14300) can be ordered from Cessna Parts Distribution.

(5) Connect brake line at wheel cylinder fitting.(6) Push parking brake handle to the off position (fully in).(7) Bleed brake system. Refer to Brake System Bleeding.(8) Do the Operational Check of the Brakes. Refer to Chapter 32-40-00, Wheels and Brakes -

Inspection/Check, Brakes Operational Check.

10. New Brake Burn-In

A. Airplanes 20800001 thru 20800135 and 208B0001 thru 208B0102.(1) Perform six consecutive light braking applications from 20 to 35 knots. Allow brake discs to cool

substantially between stops.

CAUTION: Do not set the parking brakes while they are hot. This will help toprevent irregular friction surface mix transfer that can result in brakeclatter, noise and vibration.

B. Airplanes 20800136 and On, 208B0103 and On, and All Spares.

NOTE: The brake pads are of a metallic composition and require the following break-in procedure.

(1) Perform two consecutive full stop braking applications from 30 to 35 knots.

CAUTION: Do not allow brake discs to cool substantially between stops.Use caution in performing this procedure, as higher speeds withsuccessive stops could cause the brakes to overheat, resulting inwarped discs and/or pressure plates.

11. Brake Assembly Disassembly/Reassembly

A. Disassemble the Brake Assembly (Refer to Figure 202).(1) Remove pistons (11) and insulators (9) from brake cylinder (13). Remove O-rings (10) from

piston (11) and discard.(2) Remove bleeder valve cap and bleeder valve (14).


ICA-208-32-00001 Form 2261 Rev 1



B. Assemble the Brake Assembly (Refer to Figure 202).(1) Install bleeder valve (14) in brake cylinder (13).(2) Using clean hydraulic fluid (MIL-H-5606) as a lubricant, install new O-rings (10) on pistons (11).(3) Install pistons (11) into cylinder (13).(4) Install insulators (9) in pistons (11).

12. Nose Wheel Removal/Installation

A. Remove Nose Wheel (Refer to Figure 203).(1) Jack airplane. Refer to Chapter 7, Jacking - Maintenance Practices.

WARNING: Make sure that you deflate the tire before you remove thewheel/tire assembly from the airplane. When all pressure hasbeen released, use an extraction tool to remove the valvecore from the valve stem. Valve cores under pressure canbe ejected from the valve stem and cause injury to personnelor damage to the airplane. If you think there is wheel or tiredamage, get access to the tire from the front or rear, not fromthe side (facing the wheel).

(2) Deflate tire completely.(3) Remove cotter pin (1), nut (2) and washer (3) from one side of fork (9), withdraw axle stud (8).(4) Using long punch through one axle bucket (4), tap out bucket at opposite side of fork (9).(5) Remove both buckets (4) and pull tire and wheel (6) from fork (9).(6) Remove spacers (5) or (10) and axle tube (7) before disassembling wheel.(7) Examine the wheel axle tube for condition, cracks, corrosion, and wear.

(a) Examine the axle spacer for wear at the grease seals contact area. If the grooves will notlet the seal seat correctly, replace the axle spacer.

(8) Examine the wheel spacers and the buckets for condition, cracks, and corrosion.(a) For airplanes 20800202 and On, 208B0256 and On, and airplanes that incorporate CAB91-

30, examine the seal for condition, cuts, and deterioration.(9) Examine the axle stud for condition, bends, damaged threads, cracks, and corrosion.(10) Remove all wheel bearing cones.

(a) Clean the bearing cones and cups and the wheel halves with stoddard solvent or anequivalent approved cleaning solvent.

WARNING: Use low pressure shop air to dry bearings. Do not spinbearing cones with compressed air. Dry running bearingswithout lubrication can explode.

(11) Examine for, and replace the bearing cups if the cups are loose in the wheels, or there arescratches, pitting, corrosion, or signs of overheating.

(12) Examine for, and replace the bearing cones if there are nicks, scratches, water staining, spalling,heat discoloration, roller wear, cage damage, cracks, or distortion.

(13) Re-pack the bearings with general purpose grease MIL-G-81322 or an equivalent grease.(14) Install the bearings in the wheels with new grease seals.

B. Install Nose Wheel Airplanes 20800001 thru 20800201 and 208B0001 thru 208B0255 notincorporating CAB 91-30 (Refer to Figure 203).(1) Insert axle tube (7) into wheel and place a spacer (5) on each side of wheel.(2) Position wheel into fork (9) and install buckets (4) into fork recesses. Tap buckets with

nonmetallic hammer until seated in fork.(3) Install axle stud (8), washer (3), and nut (2).(4) Tighten nut (2) until a slight drag can be felt when rotating the tire.(5) Rotate the tire, by hand, and measure the force at the outside diameter of tire. Force should be

between 3 and 5 pounds (13.4 to 22.2 N).


ICA-208-32-00001 Form 2261 Rev 1



Nose Wheel InstallationFigure 203 (Sheet 1)


ICA-208-32-00001 Form 2261 Rev 1



(6) Install new cotter pin (1) in nut (2). If cotter pin does not line up, back off nut to the nextcastellation.

(7) Again, verify the measured force at the outside diameter of the tire is between 3 and 5 pounds(13.4 to 22.2 N).

(8) Remove airplane from jacks. Refer to Chapter 7, Jacking - Maintenance Practices.

C. Install Nose Wheel Airplanes 20800202 and On and 208B0256 and On and Airplanes 20800001 thru20800201 and 208B0001 thru 208B0255 incorporating CAB 91-30 (Refer to Figure 203).

NOTE: Application of Permatex Anti-Seize Lubricant as indicated in this procedure will provideprotection for nose wheel bearings and, if followed carefully, will allow 200 hours betweenbearing inspections and wheel bearing repacking.

(1) Coat mating surfaces of seal (11) and spacer (10) with anti-seize lubricant, and then apply toseal surface which contacts wheel bearing seal.

(2) Insert axle tube (7) into wheel and place a seal (11) and spacer (10) on each side of wheel.(3) Coat inside surface of the spacer (10) and outside surface of axle (7) where axle will slide inside

the spacer (10) with anti-seize lubricant.(4) Coat outer surface of buckets (4) with anti-seize lubricant.(5) Position wheel into fork (9) and install buckets (4) into fork recesses. Tap buckets with

nonmetallic hammer until seated in fork.(6) Coat underside of axle stud (8) with anti-seize lubricant and install axle stud (8), washer (3), and

nut (2).(7) Tighten nut (2) until a slight drag can be felt when rotating the tire.(8) Rotate the tire, by hand, and measure the force at the outside diameter of tire. Force should be

between 3 and 5 pounds (13.4 to 22.2 N).(9) Install new cotter pin (1) in nut (2). If cotter pin does not line up, back off nut to the next

castellation.(10) Again, verify the measured force at the outside diameter of the tire is between 3 and 5 pounds

(13.4 to 22.2 N).(11) Apply a small amount of anti-seize lubricant to threaded end of axle stud (8).(12) Apply a small amount of anti-seize lubricant to both sides of wheel where seal (11) meets the

snap ring of wheel bearing.(13) Remove airplane from jacks. Refer to Chapter 7, Jacking - Maintenance Practices.

13. Nose Wheel Tire and Tube Disassembly/Reassembly

A. Disassemble Nose Wheel Tire and Tube (Refer to Figure 204).

WARNING: Injury can result from attempting to separate wheel halves withtube inflated. Take care to avoid damaging wheel halves whenbreaking tire beads loose.

NOTE: Refer to Tire Mounting Precautions before disassembly of nose wheel, tire and tube.

(1) Ensure tube (8) is completely deflated then break beads of tire (7) loose.(2) Remove thru-bolts (5) and separate wheel halves (6) and (9).(3) Remove tire (7) and tube (8).(4) Remove snap rings (1), grease seal (2) and bearing cones (3) from both wheel halves.

NOTE: Bearing cups (4) are a press fit in wheel halves (6) and (9) and should not be removedunless replacement is necessary. To remove bearing cups (4), heat each wheel halfin boiling water for 15 minutes. Using an arbor press, press out bearing cup andpress in new bearing cup while wheel is still hot.


ICA-208-32-00001 Form 2261 Rev 1



Nose Wheel, Tire and Tube InstallationFigure 204 (Sheet 1)


ICA-208-32-00001 Form 2261 Rev 1



B. Assemble Nose Wheel, Tire and Tube (Refer to Figure 204).

NOTE: Before reassembly of nose wheel, tire and tube, refer to Tire Mounting Precautions.

(1) Clean the inside of both wheel halves with mineral spirits.(2) Let it dry and apply Royco 103 or other MIL-C-16173 Type 1, Grade 1 protectant to all surfaces

except the bearing outer race and the flanges where the tire bead seats.

NOTE: A swab may be necessary to apply protectant to the wheel material inside the boltholes.

(3) If replacing the bearing outer races, remove outer race and clean race cup bore surfaces of thewheel and apply a thin coating of protectant to the mating surface of the wheel. Install outer racewhile protectant is still wet.

(4) Brush coat the wheel surfaces around outer race after race installation to replace any protectantremoved during the race installation.

NOTE: Some protectant in the snap ring (3) groove is permitted, but do not fill the groove.Too much protectant can be removed with mineral spirits.

(5) Place tire (7) and tube (8) on wheel half (9), aligning valve stem of tube with hole in wheel half.

NOTE: Lightweight point of tire is marked with a red dot on tire sidewall and heavyweightpoint of tube is marked with a contrasting color line (usually near valve stem). Wheninstalling tire, place these marks adjacent to each other.

(6) Position wheel half (6) into position opposite assembled tire and wheel half (9), applying lightforce to keep wheel halves together. Do not pinch tube (8) between wheel halves.

CAUTION: Uneven or improper torque of thru-bolt nuts (10) can cause boltfailure with resultant wheel failure.

(7) Insert thru-bolts (5) through wheel halves and torque nuts (10) evenly to 150 inch-pounds (16.9N.m).

(8) Inflate tube to set tire beads, then adjust tire pressure. Refer to Chapter 12, Tires - Servicing.(9) Clean bearing cones (3) and repack with clean wheel bearing grease.(10) Assemble bearing cones (3) and grease seals (2) into both wheel halves, and secure with snap

rings (1).

14. Inspection and Checks

A. Wheel Inspection.(1) Disassemble wheel. Refer to Main Wheel, Tire and Tube Disassembly/Reassembly or Nose

Wheel, Tire and Tube Disassembly/Reassembly.(2) Visually inspect the wheel halves for cracks, corrosion, or other damage. Make sure to dye

penetrant inspect any areas with suspected cracks. Cracked or badly corroded parts must bereplaced. Small nicks, pits, and scratches may be polished out with fine 400 grit wet or drysandpaper and refinished.

(3) Inspect bearing cups for looseness, scratches, pitting, corrosion or evidence of overheating.Replace cup if any defect exists.

(4) Visually inspect bearing cones for nicks, scratches, water staining, spalling, heat discoloration,roller wear, cage damage, cracks or distortion. Replace if defective or worn.


ICA-208-32-00001 Form 2261 Rev 1



(5) Install new wheel bolts or the removed wheel bolts that have passed a visual and magneticparticle inspection.

NOTE: If the wheel bolts are to be used again, they must pass an inspection for cracks,bending, thread damage, and excessive corrosion. A complete magnetic particleinspection must be done on each bolt, especially in the radius under the head and inthe threads adjacent to the bolt shank.

(6) Inspect thru-bolt nuts for self-locking feature. Replace nut if doubtful.(7) Reassemble wheel. Refer to Main Wheel, Tire and Tube Disassembly/Reassembly or Nose

Wheel, Tire and Tube Disassembly/Reassembly.

B. Service Brake Disc. (Refer to Figure 202).(1) Discs are plated for special applications only; therefore, rust in varying degrees can occur. If

a powder rust appears, one or two taxi/braking applications should wipe the disc clear. Rustallowed to progress beyond this point may require removal of the disc from the wheel assemblyto properly clean both faces.

(2) Wire brushing, followed by sanding with 220 grit sandpaper, can restore the braking surfacesfor continued use.

C. Inspect Brake Line For Chaffing (Airplanes 20800001 thru 20800039).(1) Inspect brake line for chaffing against lower main landing gear axle fitting and fairing. If chaffing

is evident, brake line shall be re routed in accordance with Service Bulletin CAB85-4.


ICA-208-32-00001 Form 2261 Rev 1


AIRCRAFT DIVISION



APPENDIX A: ILLUSTRATED PARTS CATALOG

Part Number Nomenclature Quantity

066-15300 Lining - Brake, Metallic 8 Individual Linings Per BrakeAssembly


Form 2261 Rev 1


AIRCRAFT DIVISION



APPENDIX B: WIRING DIAGRAM MANUAL

NOT APPLICABLE


Form 2261 Rev 1

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