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
CESSNA AIRCRAFTCOMPANY AIRCRAFT DIVISION WICHITA, KANSAS 67277
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 pages WHEELS AND BRAKES MAINTENANCE PRACTICES 201 thru 215 InTireMountingPrecautionsSection,addedastepasaprocedure for how to remove stickers and sticker residue from inside tire and from outside tube. In Brake Assembly Removal/Installation Section, added CAUTION and instruction not to intermix brake linings with different part numbers on the airplane. In Brake Assembly Removal/Installation Section, added NOTE that it is not necessary to remove anchor bolts 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 brake assembly. In Brake Assembly Disassembly/Reassembly Section, changed Hydraulic Fluid Specification from MIL PRF 5606 to MIL H 5606. Appendix A: Illustrated Parts 32 40 00 Figure MAIN WHEEL BRAKE ASSEMBLY Catalog 03 Appendix B: Wiring Diagram NOT USED Manual
1. Export Compliance A. This publication contains technical data and is subject to U.S. export regulations. This information has been exported from the United States in accordance with export administration regulations. Diversion contrary 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 the released 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. ICAsthatareinthecurrentmaintenancemanualandhaveinformation 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 are separated by dashes. The three element number is found at the bottom right corner of the page, left of the page number. The date is found below the page number.
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B. When the chapter/system element number is followed with zeros in the section/subsystem and subject/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 element number (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 of subsystem units in which maintenance information is necessary. E. All system/subsystem/unit (chapter/section/subject) maintenance data is separated into specified types 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 Practices section. 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 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 F. A typical page number:
G. Illustrations use the same figure numbers as the page block in which they appear. For example, Figure 202 would be the second figure in a Maintenance Practices section.
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4. Supplement Revisions A. Revisions to this supplement may be accomplished if changes to this supplement are required after release 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 listed above and should be used in conjunction with those manuals until the next available revision is released. A. The ICA Supplement List located in the Introduction section of each manual listed in the REVISIONS table 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 Incorporation Status" column in the ICA Supplement List, when those ICAs associated with that manual have been incorporated. After ICAs are incorporated, the manual that they are incorporated in must now be used for 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. Therewillnotbearevisiontothissupplementtoindicateincorporation in the manuals. Users are required to check the ICA Supplement List for each manual affected to determine incorporation status. C. This supplement will be completely superseded by the manuals listed in the REVISIONS table when it has been incorporated in all of the manuals.
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INTRODUCTION
1. Purpose A. The purpose of this Supplement is to provide the maintenance technician with the information necessary to ensure the correct functionality and performance of the Brake Lining Change on the Cessna Model 208 until this information gets incorporated into the next revision to the manuals listed in the "REVISIONS" section of this supplement. B. This ICA supplement is designed to satisfy the requirements of 14 CFR 23.1529 "Instructions for Continued Airworthiness" associated with this installation. This document is a supplement to the Model 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 "ICA Supplement List" in the "Introduction" section of the respective manual for the status of all applicable ICA Supplements. D. Revisions to this supplement may occur if there is a change to any of the ICAs in this supplement prior to incorporation into all of the affected manuals.
NOTE: This document must be placed with the aircraft operator's Technical Library CD ROM or Model 208 Maintenance Manual and incorporated into the operator's scheduled maintenance program.
2. Effectivity A. These Instructions for Continued Airworthiness (ICA) are effective for the following aircraft model and serialization.
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 for Continued Airworthiness for the Brake Lining Change on the Cessna Model 208. All items must be available to the operator at initial delivery. (1) Model 208 Maintenance Manual
4. System Components A. Refer to Appendix A: Illustrated Parts Catalog
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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 to32 40 00, Wheels and Brakes Maintenance Practices.
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INSPECTION PROGRAM AND AIRWORTHINESS LIMITATIONS
1. Continuous Inspection Program A. ThisICASupplement 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 maintenance required under Section 43.16 and 91.403 of Title 14 Code of Federal Regulations, unless an alternative program has been FAA approved.
(1) There are no new (or additional) airworthiness limitations associated with this equipment and/or installation.
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CESSNA AIRCRAFT COMPANY MODEL 208 MAINTENANCE MANUAL
LIST OF PUBLICATIONS
1. ListofManufacturers Technical Publications Available Through Cessna A. The following listed publications are necessary for the support of your Model 208. Contact the appropriate manufacturer to order the publications that are necessary for the support of your Model 208.
NOTE: The publications made by King Radio and Sigmatek Inc./ARC Avionics must be ordered directly from the manufacturer. The publication names, numbers and addresses are listed after this section.
Table 1. Chapter 21 Air Conditioning
Item Cessna Manufact- Publica- Publication Title Manufacturer Part urers Part tion Part Number Number Number Vent 33E83 2 37E66 33E83 Blower FL Aerospace Corp. Blower 1 13 Assembly Component Janitrol Aero Div. Maintenance Manual 4200 Surface Rd. (Vent Blower) with Columbus, OH 43228 Illustrated Parts List Flow Con 1H101 4, CM 200 1 Airborne Component Parker Hannifin Corp. trol Valve, 1H102 2 Overhaul Manual With Airborne Division and Tem Illustrated Parts List 711 Taylor St. perature P.O. Box 4032 Control Elyria, OH 44036 Valve
Table 2. Chapter 22 Auto Flight
Item Cessna Manufact- Publica- Publication Title Manufacturer Part urers Part tion Part Number Number Number GFC 700 190 G1000 Caravan Line Garmin International, Autopilot 00869 00 Maintenance Manual Inc. 1200 E. 151st Street Olathe, Kansas 66062 Autopilot GSA 190 Installation Manual Garmin International, Servo 8X/GSM 85 00303 72 Inc. Autopilot GSM 86 190 Installation Manual Garmin International, Servo Gear 00303 83 Inc. box
Table 3. Chapter 23 Communications
Item Cessna Manufact- Publica- Publication Title Manufacturer Part urers Part tion Part Number Number Number Garmin 011 190 Garmin GDL 69/69A Garmin International, GDL 00987 00 00355 02 Installation Manual Inc. 69/69A 1200 E. 151st Street Olathe, Kansas 66062
LIST OF PUBLICATIONS Page 1 © Cessna Aircraft Company Apr 29/2014 ICA 208 32 00001 Form 2261 Rev 1 CESSNA AIRCRAFT COMPANY MODEL 208 MAINTENANCE MANUAL
Table 4. Chapter 24 Electrical Power
Item Cessna Manufact- Publica- Publication Title Manufacturer Part urers Part tion Part Number Number Number DC to DC RG40 83706C Removal/Installation KGS Electronics, Inc. Power Manual Model RG40 418A E. Live Oak Ave. Converter Regulated DC to Arcadia, CA 91006 5690 DC Converter(FAA TSO C71 Approved) Battery G6381E GSM682 Gill Battery Service Teledyne Battery 13 Manual Products 840W.BrocktonAve. P.O . B ox 4 31 Redlands, CA 92373 Battery 30994 001 BA89 9/ Battery Instruction Marathon Power 92 13 Manual (NICAD) Technologies Co. Marathon Battery 8301 Imperial Dr. Service Manual Waco, TX 76712 6588
Table 5. Chapter 27 Flight Controls
Item Cessna Manufact- Publica- Publication Title Manufacturer Part urers Part tion Part Number Number Number Rudder AT RL Rudder Gust Lock Kit Aero Twin Inc. Gust Lock 1001 ICA Maintenance Manual 2404 Merrill Field Dr. Kit with Illustrations Anchorage, AK 99501
LIST OF PUBLICATIONS Page 2 © Cessna Aircraft Company Apr 29/2014 ICA 208 32 00001 Form 2261 Rev 1 CESSNA AIRCRAFT COMPANY MODEL 208 MAINTENANCE MANUAL
Table 6. Chapter 30 Deice
Item Cessna Manufact- Publica- Publication Title Manufacturer Part urers Part tion Part Number Number Number Propeller 3E2090 1 68 04 Propeller Deice System BF Goodrich De Ice 714K13 Brush Block Assembly Aerospace Div. Brush Overhaul Manual and Engineered Polymer Block Illustrated Parts Catalog Products 150 Division Dr. Wilmington, NC 28401 Propeller 3E2205 4 68 04 Propeller Deice System BF Goodrich De Ice 712D 13 Maintenance Manual Aerospace Div. Engineered Polymer Products 150 Division Dr. Wilmington, NC 28401 Propeller 183 Propeller Anti icing Boot Hartzell Propeller Inc. Anti icing 61 12 83 Removal and Installation One Propeller Place Boot Manual Piqua, OH U.S.A 45356 2634 Web: http:// www.hartzellprop.com/ service_support.php Propeller 180 Propeller Ice Protection Hartzell Propeller Inc. Ice 30 61 80 System Manual One Propeller Place Protection Piqua, OH U.S.A 45356 2634 Web: http:// www.hartzellprop.com/ service_support.php Propeller 9910587 P7036368 830415 McCauley McCauley Propeller De Ice 202 0154 1 13 Electrothermal Deice Systems Systems Service Parts P.O . Box 7704 Manual Wichita, KS 67277 7704 Pnuematic BFG Pneumatic De Icer Goodrich Corporation De Ice 30 10 31 Installation, Maintenance Aerospace Div. Boots and Repair Manual Ice Protection Systems 1555 Corporate Woods Parkway Uniontown, OH 44685 Pnuematic BFG Fastboot Pneumatic Goodrich Corporation De Ice 30 10 70 De Icer Installation Aerospace Div. Boots Instructions Ice Protection Systems 1555 Corporate Woods Parkway Uniontown, OH 44685
LIST OF PUBLICATIONS Page 3 © Cessna Aircraft Company Apr 29/2014 ICA 208 32 00001 Form 2261 Rev 1 CESSNA AIRCRAFT COMPANY MODEL 208 MAINTENANCE MANUAL
Table 7. Chapter 31 Indicating/Recording Systems
Item Cessna Manufact- Publica- Publication Title Manufacturer Part urers Part tion Part Number Number Number L 3 FA2100 165E184 L 3 Communications L 3 Communications CVDR 7 01 FA2100 CVDR Aviation Recorders P.O. Installation and Box 3041 Sarasota, FL Operation Manual 34230 L 3 FA2100 165E163 Lao Communications L 3 Communications CVDR 0 00 Portable Interface (PI) Aviation Recorders P.O. Operators Manual Box 3041 Sarasota, FL 34230 L 3 FA2100 165E1696 L 3 Communications L 3 Communications CVDR 002 (rev 3 ROSE / PI Software Aviation Recorders P.O. or higher) Version 3.0 Operators Box 3041 Sarasota, FL Manual 34230
Table 8. Chapter 32 Landing Gear
Item Cessna Manufact- Publica- Publication Title Manufacturer Part urers Part tion Part Number Number Number Brake AWBCMM Component Parker HannifinCorp. Assemblies 0001 X Maintenance Manual Aircraft Wheel and Brake for External Design Division Wheels & Brakes 1160 Center Road Avon, OH 44011 Brake BrakeLining Parker HannifinCorp. Linings Identification Guide Aircraft Wheel and Brake Division 1160 Center Road Avon, OH 44011
LIST OF PUBLICATIONS Page 4 © Cessna Aircraft Company Apr 29/2014 ICA 208 32 00001 Form 2261 Rev 1 CESSNA AIRCRAFT COMPANY MODEL 208 MAINTENANCE MANUAL
Table 9. Chapter 34 Navigation
Item Cessna Manufact- Publica- Publication Title Manufacturer Part urers Part tion Part Number Number Number G1000 sys 190 G1000LineMaintenance Garmin International, tem com 00869 00 Manual (Cessna Inc. ponents Caravan) 85 Servo 011 190 GSA 8X/GSM 85(A) Garmin International, Mount 00878 00 00303 72 Installation Manual Inc. GSM 86 Supplier 190 GSM 86 Servo Gear Box Garmin International, Servo PN: GSM 00303 83 Installation Manual Inc. Mount 86 1200 E. 151st St. Olathe, KS 66062 NAV/ Supplier PN Aeroflex AC0823 Aeroflex Wichita Division COMM Test IFR 4000 NAV/COMM CD 10200 West York Set (IFR Test Set Wichita, KS 67215 4000) IFR 4000 Operation Manual Storm WX 1000 78 8051 Stormscope Series L 3 Communications scope Se 9150 0 II Weather Mapping Avionics Systems ries II Systems WX 1000 5353 52ND Street, S.E. Weather Installation Manual Grand Rapids, MI Mapping 49512 9704 Systems
Table 10. Chapter 35 Oxygen
Item Cessna Manufact- Publica- Publication Title Manufacturer Part urers Part tion Part Number Number Number Portable 5500AGW AVOX Component AVOX Systems Inc. Oxygen FF23A Maintenace Manual 225ErieSt. Bottle Lancaster, NY 14086
Table 11. Chapter 36 Pneumatic
Item Cessna Manufact- Publica- Publication Title Manufacturer Part urers Part tion Part Number Number Number Pressure 1H75 14 CM200 1 Airborne Component Parker Hannifin Corp. Regulator Overhaul Manual with 711 Taylor St. Illustrated Parts List P.O. Box 4032 Elyria, OH 44036
LIST OF PUBLICATIONS Page 5 © Cessna Aircraft Company Apr 29/2014 ICA 208 32 00001 Form 2261 Rev 1 CESSNA AIRCRAFT COMPANY MODEL 208 MAINTENANCE MANUAL
Table 12. Chapter 61 Propellers
Item Cessna Manufact- Publica- Publication Title Manufacturer Part urers Part tion Part Number Number Number Propeller HC B3MN3/ 135C 13 Composite Blade TRW Hartzell Propeller M10083 Inspection, Repair, and Division of TRW Inc. Overhaul Instructions 1800 Covington Ave. Piqua, OH 45356 Propeller HC B3N211 139 Propeller Owner's Hartzell Propeller Inc. 00S 61 00 39 Manual and Logbook One Propeller Place (Steel Hub Turbine Piqua, OH Propellers with U.S.A 45356 2634 Aluminum Blades) Web: http:// www.hartzellprop.com/ service_support.php Propeller HC B3N210 146 Propeller Owner's Hartzell Propeller Inc. 50S 61 00 46 Manual and Logbook One Propeller Place Models: HC B3MN 3 Piqua, OH HC B4MN 5AL U.S.A 45356 2634 HC B4MP 3A Propeller D4898P 127 13 Spinner Assembly TRW Hartzell Propeller Spinner D4899 Maintenance Instruction Division of TRW Inc. Guide 1800 Covington Ave. Piqua, OH 45356 Propeller 9910587 P7036368 0 8103012 McCauley C700 McCauley Propeller 201 1 13 Propeller Service Manual Systems P.O. Box 7704 Wichita, KS 67277 7704
LIST OF PUBLICATIONS Page 6 © Cessna Aircraft Company Apr 29/2014 ICA 208 32 00001 Form 2261 Rev 1 CESSNA AIRCRAFT COMPANY MODEL 208 MAINTENANCE MANUAL
Table 13. Chapter 71 Engine
Item Cessna Manufact- Publica- Publication Title Manufacturer Part urers Part tion Part Number Number Number Engine 991057 PT6A 114 3043512 Pratt & Whitney Pratt & Whitney Canada 600SHP 9 1 PT6A 114/116/135/135A Inc. Maintenance Manual 100 Marie Victorin Blvd. Longueuil, Quebec Canada J4G 1A1 Engine 991057 PT6A 114 3043514 Pratt & Whitney Pratt & Whitney Canada 600SHP 9 1 PT6A 114/116/135/135A Inc. Illustrated Parts Catalog 100 Marie Victorin Blvd. Longueuil, Quebec Canada J4G 1A1 Engine 991058 PT6A 114A 3043512 Pratt & Whitney PT6A Pratt & Whitney Canada 675SHP 9 1 114/114A/116/135/135A Inc. Maintenance Manual 100 Marie Victorin Blvd. Longueuil, Quebec Canada J4G 1A1 Engine 991058 PT6A 114A 3043514 Pratt & Whitney PT6A Pratt & Whitney Canada 675SHP 9 1 114/114A/116/135/135A Inc. Illustrated Parts Catalog 100 Marie Victorin Blvd. Longueuil, Quebec Canada J4G 1A1 Engine 265000 PT6A 140 3075742 Pratt & Whitney Pratt & Whitney Canada 867SHP 1 2 PT6A 140 Maintenance Inc. Manual 100 Marie Victorin Blvd. Longueuil, Quebec Canada J4G 1A1
Table 14. Chapter 77 Engine Indicating
Item Cessna Manufact- Publica- Publication Title Manufacturer Part urers Part tionPart Number Number Number FAST 2618507 FAST A 3077188 Abbreviated Component Pratt & Whitney Canada Engine 010 4 Maintenance Manual Inc. Trend (ACMM) 100 Marie Victorin Blvd. Monitor Longueuil, Quebec Canada J4G 1A1 FAST 2618507 Monitor Transfer Module Pratt & Whitney Canada Engine Help Manual and Inc. Trend Reference Manual 100 Marie Victorin Blvd. Monitor Longueuil, Quebec Canada J4G 1A1 FAST 2618507 FAST Configuration and Pratt & Whitney Engine Engine Test Services. Trend 249 Vanderbilt, Ave. Monitor Blvd. Norwood, MA 02062
LIST OF PUBLICATIONS Page 7 © Cessna Aircraft Company Apr 29/2014 ICA 208 32 00001 Form 2261 Rev 1 CESSNA AIRCRAFT COMPANY MODEL 208 MAINTENANCE MANUAL
Table 15. Chapter 80 Starter/Generator
Item Cessna Manufact- Publica- Publication Title Manufacturer Part urers Part tion Part Number Number Number 200SGL119 Q 2 Skurka Aerospace Inc. Overhaul Instructions 200SGL119 4600 Calle Bolero with Illustrated Starter/ Q 2RX P.0. Box 2869 TM105A Parts Breakdown Generator Camarillo, CA 93011 200SGL153 Starter Generator Web: www.skurka Q Models 200SGL XXXX aero.com 200SGL153 QRX 300SGL145 TM109 Overhaul Instructions Skurka Aerospace Inc. Q with Illustrated Starter/ Parts Breakdown Generator Starter Generator Models 300SGL XXXX 23081 22 23081 Lear Siegler 23081 Lucas Aerospace Starter/ 023 3 13 DC Starter/ Generator Power Equipment Corp. Generator Overhaul Manual with 777 Lena Drive Illustrated Parts List Aurora, OH 44202 23081 22 23700 Lucas Aerospace Lucas Aerospace Starter/ 6 13 DC Generators and Power Equipment Corp. Generator Starter Generators 777 Lena Drive Maintenance Manual Aurora , OH 44202 51539 51539 Lear Siegler 51539 012 Lucas Aerospace Generator 012N 012 13 DC Generator Control Power Equipment Corp. Control Unit Unit Overhaul Manual 777 Lena Drive Assembly with Illustrated Parts List Aurora, OH 44202
2. Radio Manufacturer Manuals A. The following publications must be ordered directly from Honeywell. Refer to the following list for address and telephone numbers:
UNITED STATES OPERATIONS Honeywell International, Inc., Aerospace Electronics Systems 1 Technology Center 23500 W. 105th Street Olathe, 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) 4 229 Cable: KINGRAD
LIST OF PUBLICATIONS Page 8 © Cessna Aircraft Company Apr 29/2014 ICA 208 32 00001 Form 2261 Rev 1 CESSNA AIRCRAFT COMPANY MODEL 208 MAINTENANCE MANUAL
EUROPEAN MARKETING OFFICE: Telephone: Switzerland22985880 Telex: Switzerland 289445. Answer back: King CHGeneva, Switzerland Telephone: France 4 422 1747 Telex: France 150952. Answer back: KINGRAD Ivry Le Temple
MANUAL MANUAL TITLE NUMBER 006 0180 01 Audio Panel/Marker Beacon Receiver Installation Manual (Type KMA 24) 006 5180 01 Audio Panel/Marker Beacon Receiver Overhaul/Maintenance Manual (Type KMA 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 (Type KN 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)
LIST OF PUBLICATIONS Page 9 © Cessna Aircraft Company Apr 29/2014 ICA 208 32 00001 Form 2261 Rev 1 CESSNA AIRCRAFT COMPANY MODEL 208 MAINTENANCE MANUAL
3. Sigmatek Inc./ARC Avionics Manufacturer Manuals
NOTE: Following listed Sigmatek Inc./ARC publications must be ordered directly from Sigmatek Inc./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 400AudioAmplifier (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 800Alerter(TypeAA 801A)Service/PartsManual
LIST OF PUBLICATIONS Page 10 © Cessna Aircraft Company Apr 29/2014 ICA 208 32 00001 Form 2261 Rev 1
CESSNA AIRCRAFT COMPANY MODEL 208 MAINTENANCE MANUAL
WHEELS AND BRAKES - MAINTENANCE PRACTICES
1. General A. This section provides information on brake system bleeding, wheel removal/installation, tire mounting and dismounting, brake components removal/installation and brake inspection criteria.
2. Tire Mounting Precautions A. TireMountingandDismountingCriteria(RefertoFigure201). (1) Prior to removing the wheel/tire assembly from the airplane, completely deflate the tire with a deflationcap.Itisgoodpracticetodeflate the tire before removing the axle nut. When all pressure has been relieved, remove the valve core. Valve cores under pressure can be ejected like a bullet. If wheel or tire damage is suspected, approach the tire from the front or rear, not from the side (facing the wheel).
CAUTION: A tire/wheel assembly that has been damaged in service should be deflated by a remote means. If this is not possible, the tire/wheel assembly should be allowed to cool for a minimum of three hours beforethetireisdeflated.
(2) Take special care when encountering difficulty in freeing tire beads from wheel flanges. Trying to pry beads free incorrectly may cause an accident. Even with tire tools, care must be taken to prevent damage to beads or wheel flanges. On small tires, successive pressing with a two foot length 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 device to 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's instructions 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, reinflatetoratedinflation 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.
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5. Brake System Bleeding
NOTE: Anytime a brake line is disconnected or a spongy feel to the brake pedal is detected, there is likelihood air has entered the system. To assure proper braking action, all trapped air must be removed 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 fluidwithMIL H 5606specifications. (3) Open bleeder valve and begin pumping hydraulic fluid into the system while observing fluid level in 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 fluidwithMIL H 5606specifications. (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 the wheel/tire assemblies from the airplane. When all pressure has been released, use an extraction tool to remove the valve core from the valve stem. Valve cores under pressure can be ejected from the valve stem and cause injury to personnel or damage to the airplane. If you think there is wheel or tire damage, get access to the tire from the front or rear, not from the 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.
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Main Wheel, Tire and Tube Installation Figure 201 (Sheet 1)
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Main Wheel, Tire and Tube Installation Figure 201 (Sheet 2)
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(8) Examine the inner main gear wheel axle surface for corrosion.
NOTE: Themaingearaxle is a time limited part. You should verify the current number of landings, inspection status and replacement time before you install the main wheel and tire. Refer to Chapter 4, Replacement Time Limits and Typical Inspection Time Limits 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 attachment bolts 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 the seal seat correctly, replace the axle spacer.
NOTE: Cessna Propeller Aircraft Product Support, 316 517 5800 or Fax 316 942 9006, is the 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 spin bearing cones with compressed air. Dry running bearings without lubrication can explode.
(14) Examine for, and replace the bearing cups if the cups are loose in the wheels, or there are scratches, 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 castellation but 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 (Cleveland part 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 to 90 inch pounds (9.6 to 10.2 N.m).
NOTE: Bolts (12) incorporate a special self locking feature and are typically good for approximately four to six reuses. If bolt (12) can be fully engaged into the backplate by hand with no resistance, the self locking feature of bolt (12) has been destroyed and the bolt should be rejected. Replacement bolts (part number 103 14300) can be ordered 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.
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7. Main Wheel, Tire and Tube Disassembly/Reassembly
WARNING: Injury can result from attempting to separate wheel halves with tube inflated. Take care to avoid damaging wheel halves when breaking 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 be removed unless replacement is necessary. To remove bearing cups (7), heat wheel half in boiling water for 15 minutes. Using an arbor press, press out bearing cup and press 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 bolt holes.
(3) If replacing the bearing outer races, remove outer race and clean race cup bore surfaces of the wheel and apply a thin coating of protectant to the mating surface of the wheel. Install outer race while protectant is still wet. (4) Brush coat the wheel surfaces around outer race after race installation to replace any protectant removed 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 to guide 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 heavyweight point of tube is marked with a contrasting color line (usually near valve stem). When installing 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 wheel halves. (9) Assemble washers (2) and nuts (1) on thru bolts (14). (10) Torque nuts (1) evenly to 150 inch pounds (16.9 N.m).
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CAUTION: Uneven or improper torque of thru bolt nuts (1) can cause bolt failure 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 brake assembly. 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 the airplane. Brake function can be altered and diminished as a result of intermixed 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 linings that you will install have the same part numbers.
NOTE: Refer to the Cleveland Brake Lining Identification Guide if the part numbers on the brake 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 good for approximately four to six reuses. If backplate bolt (12) can be fully engaged into the backplate by hand with no resistance, the self locking feature of backplate bolt (12) has been destroyed and the backplate bolt should be rejected. Replacement bolts (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.
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Brake Assembly Figure 202 (Sheet 1)
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(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 plate busings. Liquid lubricant can attract dirt and moisture that can cause 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 good for approximately four to six reuses. If backplate bolt (12) can be fully engaged into the backplate by hand with no resistance, the self locking feature of backplate bolt (12) has been destroyed and the backplate bolt should be rejected. Replacement bolts (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 to prevent irregular friction surface mix transfer that can result in brake clatter, 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 with successive stops could cause the brakes to overheat, resulting in warped 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).
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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 the wheel/tire assembly from the airplane. When all pressure has been released, use an extraction tool to remove the valve core from the valve stem. Valve cores under pressure can be ejected from the valve stem and cause injury to personnel or damage to the airplane. If you think there is wheel or tire damage, get access to the tire from the front or rear, not from the 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) Usinglong 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 not let 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 an equivalent approved cleaning solvent.
WARNING: Use low pressure shop air to dry bearings. Do not spin bearing cones with compressed air. Dry running bearings without lubrication can explode.
(11) Examine for, and replace the bearing cups if the cups are loose in the wheels, or there are scratches, 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 not incorporating 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).
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Nose Wheel Installation Figure 203 (Sheet 1)
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(6) Install new cotter pin (1) in nut (2). If cotter pin does not line up, back off nut to the next castellation. (7) Again, verify the measured force at the outside diameter of the tire is between 3 and 5 pounds (13.4to22.2N). (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 thru 20800201 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 provide protection for nose wheel bearings and, if followed carefully, will allow 200 hours between bearing inspections and wheel bearing repacking.
(1) Coat mating surfaces of seal (11) and spacer (10) with anti seize lubricant, and then apply to seal 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) Coatunderside 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) Rotatethe 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 (13.4to22.2N). (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 with tube inflated. Take care to avoid damaging wheel halves when breaking 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: Bearingcups(4)areapressfit in wheel halves (6) and (9) and should not be removed unless replacement is necessary. To remove bearing cups (4), heat each wheel half in boiling water for 15 minutes. Using an arbor press, press out bearing cup and press in new bearing cup while wheel is still hot.
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Nose Wheel, Tire and Tube Installation Figure 204 (Sheet 1)
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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: Aswabmaybenecessary to apply protectant to the wheel material inside the bolt holes.
(3) If replacing the bearing outer races, remove outer race and clean race cup bore surfaces of the wheel and apply a thin coating of protectant to the mating surface of the wheel. Install outer race while protectant is still wet. (4) Brush coat the wheel surfaces around outer race after race installation to replace any protectant removed 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 heavyweight point of tube is marked with a contrasting color line (usually near valve stem). When installing tire, place these marks adjacent to each other.
(6) Position wheel half (6) into position opposite assembled tire and wheel half (9), applying light force 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 bolt failure with resultant wheel failure.
(7) Insert thru bolts (5) through wheel halves and torque nuts (10) evenly to 150 inch pounds (16.9 N.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 be replaced. Small nicks, pits, and scratches may be polished out with fine 400 grit wet or dry sandpaper 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.
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(5) Install new wheel bolts or the removed wheel bolts that have passed a visual and magnetic particle 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 particle inspection must be done on each bolt, especially in the radius under the head and in the 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. Rust allowed to progress beyond this point may require removal of the disc from the wheel assembly to properly clean both faces. (2) Wire brushing, followed by sanding with 220 grit sandpaper, can restore the braking surfaces for 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.
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CESSNA AIRCRAFT COMPANY AIRCRAFT DIVISION WICHITA, KANSAS 67277
SUPPLEMENT NO: ICA-208-32-00001 APPENDIX A: ILLUSTRATED PARTS CATALOG
Part Number Nomenclature Quantity 066 15300 Lining Brake, Metallic 8 Individual Linings Per Brake Assembly
© Cessna Aircraft Company Form 2261 Rev 1
CESSNA AIRCRAFT COMPANY AIRCRAFT DIVISION WICHITA, KANSAS 67277
SUPPLEMENT NO: ICA-208-32-00001 APPENDIX B: WIRING DIAGRAM MANUAL
NOT APPLICABLE
© Cessna Aircraft Company Form 2261 Rev 1