Cessna Model 182 and Skylane Series Service Manual

14-2 ............................. 0 14-3 thru 14-4........... 3 14-4A ..... ..................... 3 14-4B Blank ............. 3 14-5 thru 14-6 .......... 0 14-7 thru 14-10 ........... 3 14-10A........................3 14-10B Blank .............. 3 14-11 thru 14-13......... 0 14-14 Blank .............. 0 *15-1 thru 15-1B ........... 4 *15-1B Blank................. 4 15-2 thru 15-3............. 1 15-4 ............................. 2 15-5 thru 15-6 ........... 0 15-6A .......................... 2 15-6B Blank ................ 2 15-7 ............................. 0 15-8 ............................. 3 15-9 thru 15-10 ........... 0 15-11 .................. 1 15-12 ........................... 0 15-13 thru 15-15 ......... 1 15-16 ........................... 0 *15-17 thru 15-18 .......... 4 15-19 ........................... 1 *15-20 thru 15-20C ....... 4 *15-20D Blank............. 4 15-2 1...........................1 15-22 thru 15-23......... 0 15-24 thru 15-25......... 1 15-26 Blank ............... 1 16 -1 ............................. 3 16-2 thru 16-4 ........... 0 16 -5 ............................. 3 16 -6 ............................. 1 16-7 thru 16-11 .......... 0 16-12...........................3 16-13...........................1 16-14 thru 16-18..........3 16-18Athru 16-18B ..... 3 16-19...........................3 16-20 ........................... 0 16-21 thru 16-24.......... 1 16-25 thru 16-31..........0 16-32 thru 16-33..........2 16-34 ........................... 3 16-35 ........................... 0 16-36 thru 16-42..........3 *18-1 thru 18-2A............4 *18-2B Blank.................4 *18-3..............................4 *18-3A thru 18-3B ......... 4 *18-4..............................4 18-5 thru 18-6..............2 *18-7..............................4 18-8 thru 18-11 .......... 0 18-12.............. ...... 3 18-13 thru 18-31..........0 18-32..........................2 18-33 thru 18-35..........0 18-36 Blank.................0 19-1 thru 19-2 .............. 3 20-1 thru 20-2 ............ 3 20-2A ........................... 3 20-2B Blank ................. 3 20-3 thru 20-4 .............. 0 20-5 thru 20-7 ............. 3 2 0-8 ............................. 2 2 0-9 ............................. 3 20-10 ........................... 0 20 -11 ........................... 1 20-12...........................3 20-13...........................2 20-14...........................0 20-15...........................1 20-16...........................0 20-17 thru 20-19......... 1 20-20...........................2 20-20A ........................ 2 20-20B Blank.............. 2 20-21 ........................... 1 20-22...........................2 22-22A ........................ 1 20-22B Blank.............. 1 20-23...........................2 20-24...........................3 20-25...........................1 20-26 ......... .... ... 3 20-27 thru 20-28......... 0 20-29 thru 20-30......... 3 20-30A ......... ........... 3 20-30B Blank.............. 3 20-31 ........................... 2 20-32 thru 20-33......... 1 20-34...........................2 20-34A ........................ 1 20-34B Blank.............. 1 20-35 thru 20-37......... 0 20-38...........................1 20-38A thru 20-38B .... 2 20-39...........................1 20-40...........................2 20-40A .... .............. 20-40B Blank.............. 2 20-41 ........................... 3 20-42...........................2 20-43 thru 20-44......... 0 20-45...........................1 20-46...........................3 20-46A thru 20-46B .... 3 20-47...........................1 20-48...........................2 © Cessna Aircraft Company Revision No. B Revision 4 Mar 1/2004 TABLE OF CONTENTS SECTION 1 GENERAL DESCRIPTION . 2 GROUND HANDLING, SERVICING, CLEANING, L INSPECTION ........ 3 FUSELAGE ................. 4 WINGS AND EMPENNAGE ........... 5 LANDING GEAR AND BRAKES .... 6 AILERON CONTROL SYSTEM .... 7 WING FLAP CONTROL SYSTEM ....... 8 ELEVATOR CONTROL SYSTEM .... 9 ELEVATOR TRIM TAB CONTROL SYSTEM . . . .0 RUDDER AND RUDDER TRIM CONTROL SYSTEM 1 ENGINE .......... .2 FUEL SYSTEM ........ 13 PROPELLER AND GOVERNOR .... 14 UTILITY SYSTEMS ....... .5 INSTRUMENTS AND INSTRUMENT SYSTEMS . . UBRICATION AND 16 ELECTRICAL SYSTEMS ...... 17 18 19 20 ELECTRONIC SYSTEMS (DELETED) (See Page iii) STRUCTURAL REPAIR ............. PAINTING .......... WIRING DIAGRAMS............... Page . . . .. . .. . . . . . . . . . . . . . . ........ 1-1 2-1 1 1 1 1 1 1 3-1 4-1 5-1 6-1 7-1 8-1 9-1 10-1 11-1 12-1 13-1 14-1 15-1 16-1 18-1 19-1 20-1 i CESSNA AIRCRAFT COMPANY MODEL 182 AND SKYLANE SERIES SERVICE MANUAL INTRODUCTION 1. General. WARNING: ALL INSPECTION INTERVALS, REPLACEMENT TIME LIMITS, OVERHAUL TIME LIMITS, THE METHOD OF INSPECTION, LIFE LIMITS, CYCLE LIMITS, ETC., RECOMMENDED BY CESSNA ARE SOLELY BASED ON THE USE OF NEW REMANUFACTURED, OR OVERHAULED CESSNA APPROVED PARTS. IF PARTS ARE DESIGNED, MANUFACTURED, REMANUFACTURED, OVERHAULED, AND/OR APPROVED BY ENTITIES OTHER THAN CESSNA, THEN THE DATA IN CESSNA'S MAINTENANCE/SERVICE MANUALS AND PARTS CATALOGS ARE NO LONGER APPLICABLE AND THE PURCHASER IS WARNED NOT TO RELY ON SUCH DATA FOR NON CESSNA PARTS. ALL INSPECTION INTERVALS, REPLACEMENT TIME LIMITS, OVERHAUL TIME LIMITS, THE METHOD OF INSPECTION, LIFE LIMITS, CYCLE LIMITS, ETC., FOR SUCH NON-CESSNA PARTS MUST BE OBTAINED FROM THE MANUFACTURER AND/OR SELLER OF SUCH NON-CESSNA PARTS. A. The information in this publication is based on data available at the time of publication and is updated, supplemented, and automatically amended by all information issued in Service Newsletters, Service Bulletins, Supplier Service Notices, Publication Changes, Revisions, Reissues and Temporary Revisions. All such amendments become part of and are specifically incorporated within this publication. Users are urged to keep abreast of the latest amendments to this publication through information available at Cessna Authorized Service Stations or through the Cessna Propeller Aircraft Product Support subscription services. Cessna Service Stations have also been supplied with a group of supplier publications which provide disassembly, overhaul, and parts breakdowns for some of the various supplier equipment items. Suppliers publications are updated, supplemented, and specifically amended by supplier issued revisions and service information which may be reissued by Cessna thereby automatically amending this publication and are communicated to the field through Cessna's Authorized Service Stations and/or through Cessna's subscription services. B. Inspection, maintenance and parts requirements for STC installations are not included in this manual. When an STC installation is incorporated on the airplane, those portions of the airplane affected by the installation must be inspected in accordance with the inspection program published by the owner of the STC. Since STC installations may change systems interface, operating characteristics and component loads or stresses on adjacent structures, Cessna provided inspection criteria may not be valid for airplanes with STC installation. C. REVISIONS, REISSUES, and TEMPORARY REVISIONS can be purchased from your Cessna Service Station or directly from Cessna Propeller Aircraft Product Support, Department 751, Cessna Aircraft Company, P.O. Box 7706, Wichita, Kansas 67277-7706. D. This manual contains factory recommended procedures and instructions for ground handling, servicing and maintaining Cessna Model 182-Series and F182-Series aircraft. This includes the Model A182, which is manufactured by Fuerza Aerea Argentina, Area de Material, Cordoba. E. All supplemental service information concerning this manual is supplied to all appropriate Cessna Service Stations so they have the latest authoritative recommendations for servicing these Cessna airplanes. It is recommended that Cessna owners utilize the knowledge and experience of the Cessna Service Station. Revision 4 © Cessna Aircraft Company Mar 1/2004 CESSNA AIRCRAFT COMPANY MODEL 182 AND SKYLANE SERIES SERVICE MANUAL 2. CROSS REFERENCE LISTING OF POPULAR NAME VS. MODEL NUMBERS AND SERIALS A. All aircraft, regardless of manufacturer, are certified under model number designations. However, popular names are used for marketing purposes. To provide a consistent method of referring to the various aircraft, model numbers will be used in this publication unless names are required to differentiate between versions of the same basic model. The following table provides a cross-reference listing of popular name vs. model numbers. POPULAR NAME 182 or SKYLANE SKYLANE ONLY REIMS MODEL YEAR 1969 1970 1971 1972 1973 1974 1975 1976 1976 MODEL 182M 182N 182N 182P 182P 182P 182P 182P F182P BEGINNING SERIAL NUMBER 18259306 18260056 18260446 18260826 18261426 18262466 18263476 18264296 F1820001 ENDING SERIAL NUMBER 18260055 18260445 18260825 18261425 18262465 18263475 18264295 18265175 F18200025 ARGENTINE 182 AMC 182 1969 1970 1971 1972 1973 1974 1975 1976 A182M A182N A182N A182N A182N A182N A182N A182N NONE A182-0117 NONE NONE A182-0137 NONE NONE NONE A182-0136 A182-0146 3. Coverage and Format. A. The Cessna Model 182-Series Service Manual has been prepared to help maintenance personnel in servicing and maintaining the Model 182-Series. This manual provides the necessary information required to enable the mechanic to service, inspect, troubleshoot, remove and replace components or repair systems. B. Technical Publications are also available for the various components and systems which are not covered in this manual. These manuals must be utilized as required for maintenance of those components and systems, and may be purchased from the manufacturer. 4. Temporary Revisions. A. Additional information which becomes available may be provided by temporary revision. This service is used to provide, without delay, new information which will assist in maintaining safe flight/ground operations. Temporary revisions are numbered consecutively. Temporary revisions are normally incorporated into the maintenance manual at the next regularly scheduled revision. 5. Material Presentation. A. This Service Manual is available on paper, aerofische or Compact Disc (CD/ROM); The CD ROM contains the Service Manuals, Illustrated Parts Catalogs and Avionics Manuals. Revision 4 Mar 1/2004 iii/ (iv Blank) I © Cessna Aircraft Company I FOREWORD This manual contains factory recommended procedures and in- structions for ground handling, servicing and maintaining Cessna Model 182-Series aircraft. This includes the Model A182, which is manufactured by Fuerza Aerea Argentina, Area de Material, Cordoba. Besides serving as a reference for the experienced mechanic, this book also covers step-by-step procedures for the less experi- enced man. This manual should be kept in a handy place for ready reference. If properly used, it will better enable the mechanic to maintain Cessna Model 182-Series aircraft and thereby establish a reputation for reliable service. The information in this book is based on data available at the time of publication and is supplemented and kept current by service letters and service news letters published by Cessna Aircraft Com- pany. These are sent to all Cessna Dealers so that they have the latest authoritative recommendations for servicing Cessna aircraft. Therefore, it is recommended that Cessna owners utilize the know- ledge and experience of the factory-trained Dealer Service Organi- zation. In addition to the information in this Service Manual, a group of vendor publications is available from the Cessna Service Parts Center which describe complete disassembly, overhaul and parts breakdown of some of the various vendor equipment items. A list- ing of the available publications is issued periodically in service letters. Information for Nav-O-Matic Autopilots, Electronic Communi- cations and Navigation Equipment are not included in this manual. These manuals are available from the Cessna Service Parts Center. iii/(iv blank) SECTION 1 GENERAL DESCRIPTION TABLE OF CONTENTS Page GENERAL DESCRIPTION .......... 1-1 Aircraft Specifications ........ 1-1 Model 182-Series ............ 1-1 Stations ............... 1-1 Description ............. 1-1 Torque Values ........... 1-1 1-1. GENERAL DESCRIPTION. 1-4. AIRCRAFT SPECIFICATIONS. Leading par- ticulars of these aircraft, with dimensions based on 1-2. MODEL 182-SERIES. gross weight, are given in figure 1-1. If these di- mensions are used for constructing a hangar or com- 1-3. DESCRIPTION. Cessna Model 182-Series air- puting clearances, remember that such factors as craft, described in this manual, are high-wing, strut- nose gear strut inflation, tire pressures, tire sizes braced monoplanes of all-metal, semimonocoque con- and load distribution may result in some dimensions struction. These aircraft are equipped with a fixed that are considerably different from those listed. tricycle landing gear. Thru aircraft Serial 18260825, the aircraft employ flat spring-steel main landing 1-5. STATIONS. A station diagram is shown in gear struts. Beginning with aircraft Serial 18260826, figure 1-2 to assist in locating equipment where a the aircraft are equipped with tubular spring-steel written description is inadequate or impractical. main gear struts. The steerable nose gear is equip- ped with an air/hydraulic fluid shock strut. Four- 1-6. TORQUE VALUES. A chart of recommended place seating is standard, and a two-place child's nut torque values is shown in figure 1-3. These seat may be installed as optional equipment. Model torque values are recommended for all installation 182-Series aircraft are equipped with a six-cylinder procedures contained in this manual, except where horizontally opposed, air cooled 0-470-Series Con- other values are stipulated. They are not to be tinental engine, driving an all-metal, constant speed used for checking tightness of installed parts during propeller. These aircraft feature rear side windows, service. a "wrap around" rear window and a swept-back fin and rudder. 1-1 MODELS 182 and A182 GROSS WEIGHT (Thru 1969 Model 182N) ................. . 2800 lb Take-Off (Thru 1971 Model 182N) ............. . 2950 lb Landing (Thru 1971 Model 182N) ............... 2800 lb (Beginning with 1972 Model 182P) .............. 2950 lb FUEL CAPACITY Standard Wing (Total) .. .... . . . 65 gal. When not modified by Standard Wing (Usable) ......... 60 gal. Cessna Single-Engine Long-Range (Total) .................... 84 gal. Service Letter SE75-7 Long-Range (Usable) ................. 79 gal. and prior to 18262251. Standard Wing (Total) . ......... .61 gal.1 When modified by Cessna Standard Wing (Usable) ................... 56 gal. Single-Engine Service Long-Range (Total) ................ 80 gal. Letter 75-7 and begin- Long-Range (Usable) .. 75 gal. ning with 18262251. OIL CAPACITY (Without External Filter) .................. 12 qt (With External Filter) ................... 13 qt ENGINE MODEL ........................ CONTINENTAL 0-470 Series PROPELLER (Constant Speed) ................ . 82" McCAULEY MAIN WHEEL TIRES (Standard) .. . ........... . 6.00 x 6, 6-Ply rating Pressure (Thru 1971 Model 182N) .............. 32 psi Pressure (Beginning with 1972 Model 182P) .. ....... 42 psi Pressure (Model A182) ................... 32 psi MAIN WHEEL TIRES (Optional) ................. 8.00 x 6, 6-Ply rating Pressure .................... . 25 psi to 35 psi NOSE WHEEL TIRE (Standard) .. . ........... . 5. 00 x 5, 6-Ply rating Pressure (Thru 1971 Model 182N) ............. . 50 psi Pressure (Beginning with 1972 Model 182P) . ... .... 49 psi Pressure (Model A182) ................ . 50 psi NOSE WHEEL TIRE (Optional) .................. 6.00 x 6, 4-Ply rating Pressure ....................... 30 psi NOSE GEAR STRUT PRESSURE (Strut Extended) ......... 55 psi to 60 psi WHEEL ALIGNMENT Camber .. ................... 5° to 7° Toe-In . . . . . . . . . . . . . . . . . . . . . . . . . . 0" to .06" AILERON TRAVEL Up . ............... ... 20 ° ± 2 ° Down ...................... 15 ° ± 2 ° WING FLAP TRAVEL .. O............ . 0 ° to 40 ° , +1° -2 ° RUDDER TRAVEL (Measured parallel to water line) Right .................. .... 24 ° ± 1° Left ................. 24 ° ± 1° RUDDER TRAVEL (Measured perpendicular to hinge line) Right ........................... 27 ° 13' ± 1° Left . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 ° 13' ± 1° ELEVATOR TRAVEL (Relative to Stabilizer) Up . . . . . . . . . . . . . . . . . . . . . . . . . . .. 26 ° 1° Down ........................... 17° ± 1° ELEVATOR TRIM TAB TRAVEL Up . . . . . . . . . . . . . . . . . . . . . . .... . .25 ° ± 2 Down . ......................... . 15 ° ± 1° PRINCIPAL DIMENSIONS Wing Span (Conventional Wing Tip) ............. 36' 2" Wing Span (Conical-Camber Wing Tip) ........... 35' 10" Tail Span . . . . . . . . . . . . . . . . . . . . .. 11' 8" Length (Thru 1971 Model 182N) .............. . 28' 1/2" Length (Beginning with 1972 Model 182P) .. . ..... . 28' 2" (Add 2" for strobe lights) Fin Height (Maximum with Nose Gear Depressed and Flashing Beacon Installed on Fin) (Thru 1971 Model 182N) ............... . 8' 10-1 1/2" (Beginning with 1972 Model 182P) ....... . ... 9' 1-1/2" Track Width (Thru 1971 Model 182N) ............. 7' 11-1/2" Track Width (Beginning with 1972 Model 182P) .. ...... 9' 1" BATTERY LOCATION .. ................... Aft of Baggage Compartment Figure 1-1. Aircraft Specifications 1-2 Change 3 23.62 I 39.00 71.97 154.00 THRU 182N 0?0 172.00 Figure 1-2. Reference Stations Change 3 1-3 RECOMMENDED NUT TORQUES THE TORQUE VALUES STATED ARE POUND-INCHES, RELATED ONLY TO STEEL NUTS ON OIL-FREE CADMIUM PLATED THREADS. FINE THREAD SERIES TENSION SHEAR TAP SIZE TORTORQUE TORQUE STD ALT STD ALT (NOTE 1) (NOTE 2) (NOTE 3) (NOTE 2) 8-36 12-15 7-9 10-32 20-25 20-28 12-15 12-19 1/4-28 50-70 50-75 30-40 30-48 5/16-24 100-140 100-150 60-85 60-106 3/8-24 160-190 160-260 95-110 95-170 7/16-20 450-500 450-560 270-300 270-390 1/2-20 480-690 480-730 290-410 290-500 9/16-18 800-1000 800-1070 480-600 480-750 5/8-18 1100-1300 1100-1600 660-780 660-1060 3/4-16 2300-2500 2300-3350 1300-1500 1300-2200 7/8-14 2500-3000 2500-4650 1500-1800 1500-2900 1-14 3700-5500 3700-6650 2200-3300 2200-4400 1-1/8-12 5000-7000 5000-10000 3000-4200 3000-6300 1-1/4-12 9000-11000 9000-16700 5400-6600 5400-10000 COARSE THREAD SERIES (NOTE 4) (NOTE 5) 8-32 12-15 7-9 10-24 20-25 12-15 1/4-20 40-50 25-30 5/16-18 80-90 48-55 3/8-16 160-185 95-100 7/16-14 235-255 140-155 1/2-13 400-480 240-290 9/16-12 500-700 300-420 5/8-11 700-900 420-540 3/4-10 1150-1600 700-950 7/8-9 2200-3000 1300-1800 1-8 3700-5000 2200-3000 1-1/8-8 5500-6500 3300-4000 1-1/4-8 6500-8000 4000-5000 NOTES 1. Covers AN310, AN315, AN345, AN363, MS20365, MS21042, MS21044, MS21045 and MS21046. 2. When using AN310 or AN320 castellated nuts where alignment between the bolt and cotter pin slots is not reached using normal torque values, use alternate torque values or replace the nut. 3. Covers AN316, AN320, MS20364 and MS21245. 4. Covers AN363, MS20365, MS21042, MS21043, MS21044, MS21045 and MS21046. 5. Covers AN340. CAUTION DO NOT REUSE SELF-LOCKING NUTS. The above values are recommended for all installation procedures contained in this manual, except where other values are stipulated. They are not to be used for checking tightness of installed parts during service. Figure 1-3. Torque Values 1-4 Change 2 SECTION 2 GROUND HANDLING, SERVICING, CLEANING, LUBRICATION AND INSPECTION TABLE OF CONTENTS Page GROUND HANDLING, SERVICING, CLEANING, Battery .............. 2-7 LUBRICATION, AND INSPECTION ..... 2-1 Tires ............... 2-7 GROUND HANDLING . ......... 2-1 Nose Gear Shock Strut ........ 2-7 Towing ............... 2-1 Nose Gear Shimmy Dampener ..... 2-8 Hoisting .............. 2-3 Hydraulic Brake System ....... 2-8 Jacking . ........ ......... 2-3 CLEANING .............. 2-8 Leveling .............. 2-3 General Description ......... 2-8 Parking .............. 2-3 Windshield and Windows . ..... 2-8 Tie-Down .............. 2-3 Interior Trim ........... 2-9 Flyable Storage ........... 2-3 Painted Surfaces ........ . 2-9 Returning Aircraft to Service . ... 2-3 Aluminum Surfaces ..... . .. 2-9 Temporary Storage ....... .. 2-3 Engine Compartment ........ 2-9 Inspection During Storage ..... 2-4 Upholstery and Interior . .... . 2-9 Returning Aircraft to Service ..... 2-4 Propeller .............. 2-9 Indefinite Storage .......... 2-4 Wheels ............ . 2-9 Inspection During Storage ..... 2-5 LUBRICATION ............. 2-9 Returning Aircraft to Service ..... 2-5 General Description ....... . 2-9 SERVICING .............. 2-6 Tachometer Drive Shaft ....... 2-9 General Description . ........ 2-6 Wheel Bearings ........... 2-9 Fuel ................ 2-6 Nose Gear Torque Links ..... . 2-9 Carburetor Drain Plug Inspection · · . 2-6 Wing Flap Actuator ......... 2-9 Fuel Drains ............. 2-6 Rod End Bearings . ........ 2-10 Engine Oil ... . ....... . 2-6 INSPECTION ............. 2-17 Engine Induction Air Filter ...... 2-7 Vacuum System Filter . ....... 2-7 2-1. GROUND HANDLING, SERVICING, CLEANING, ground. With the nose wheel clear of the ground, the LUBRICATION AND INSPECTION. aircraft can be turned by pivoting it about the main wheels. 2-2. GROUND HANDLING. CAUTION 2-3. TOWING. Moving the aircraft by hand is ac- complished by using the wing struts and landing gear When towing the aircraft, never turn the nose struts as push points. A tow bar attached to the nose wheel more than 30 degrees either side of gear should be used for steering and maneuvering the center or the nose gear will be damaged. Do aircraft on the ground. When no tow bar is available, not push on control surfaces or outboard em- press down at the horizontal stabilizer front spar ad- pennage surfaces. When pushing on the tail- jacent to the fuselage to raise the nose wheel off the cone, always apply pressure at a bulkhead to avoid buckling the skin. Figure 2-1. Tow Bar Change 3 2-1 ITEM NUMBER TYPE AND PART NUMBER REMARKS Jack Any short jack of capable capacity Cessna #SE-767 Universal tail stand (SEE NOTE 1) Cessna #SE-576 (41-1/2" high) Universal jack stand (FOR USE WITH ITEM 2) Cessna #10004-98 Jack point (SEE NOTE 2) #2-170 Basic jack Closed height: 69-1/2 inches; extended #2-109 Leg Extension height: 92 inches (Insert slide tube #2-70 Slide tube extension extension into basic jack). 1. Weighted adjustable stand attaches to tie-down ring. 2. Cessna #10004-98 jack point may be used to raise only one wheel. Do not use brake casting as a jack point. 3. Items (3). (4), (5) and (6) are available from the Cessna Service Parts Center. JACKING PROCEDURE a. Lower aircraft tail so that wing jack can be placed under front spar just outboard of wing strut. b. Raise aircraft tail and attach tail stand to tie-down ring. BE SURE that tail stand weighs enough to keep tail down under all conditions and is strong enough to support aircraft weight. c. Raise jacks evenly until desired height is reached. When using the universal jack point, flexibility of the gear strut will cause the main wheel to slide in- board as the wheel is raised, tilting the jack. The jack must be lowered for a second operation. Jacking both main wheels simultaneously with universal jack points is not recommended. Figure 2-2. Jacking Details 2-2 Change 1 2-4. HOISTING. The aircraft may be lifted with a NOTE hoist of two-ton capacity by using hoisting rings, which are optional equipment, or by means of suit- The aircraft is delivered from Cessna with able slings. The front sling should be hooked to a Corrosion Preventive Aircraft Engine Oil each upper engine mount at the firewall, and the aft (Military Specification MIL-C-6529 Type II sling should be positioned around the fuselage at the Rust Ban). This engine oil is a blend of avi- first bulkhead forward of the leading edge of the ation grade straight mineral oil and a corro- stabilizer. If the optional hoisting rings are used, sion preventive compound. This engine oil a minimum cable length of 60 inches for each cable should be used for the first 25 hours of engine is required to prevent bending of the eyebolt-type operation. Refer to paragraph 2-21 for oil hoisting rings. If desired, a spreader jig may be changes during the first 50 hours of operation. fabricated to apply vertical force to the eyebolts. 2-5. JACKING. Refer to figure 2-2 for jacking During the 30 day non-operational storage or the first procedures. 25 hours of intermittent engine operation, the propel- ler shall be rotated through five revolutions every 2-6. LEVELING. Corresponding points on both seventh day, without running the engine. If the air- upper door sills may be used to level the aircraft craft is stored outside, tie it down in accordance laterally. Reference point for leveling the aircraft with paragraph 2-8. In addition, the pitot tube, static longitudinally is the top of the tailcone between the air vents, air vents, openings in the engine cowling, rear window and vertical fin. and other similar openings shall have protective cov- ers installed to prevent entry of foreign material. 2-7. PARKING. Parking precautions depend prin- After 30 days, aircraft should be flown for 30 minutes cipally on local conditions. As a general precaution, or ground run-up until oil has reached operating tem- set parking brake or chock the wheels and install the perature. Controls lock. In severe weather and high wind con- ditions, tie down the aircraft as outlined in paragraph 2-10. RETURNING AIRCRAFT TO SERVICE. After 2-8 if a hangar is not available, flyable storage, returning the aircraft to service is accomplished by performing a thorough pre-flight 2-8. TIE-DOWN. When mooring the aircraft in the inspection. At the end of the first 25 hours of engine open, head into the wind if possible. Secure control operation, drain engine oil, clean oil screens and surfaces with the internal control lock and set brakes. change external oil filter element. Service engine with correct grade and quantity of engine oil. Refer Do not set parking brakes during cold weather when accumulated moisture may freeze the 2-11. TEMPORARY STORAGE. Temporary storage brakes or when the brakes are overheated. is defined as aircraft in a non-operational status for a maximum of 90 days. The aircraft is constructed a. Tie ropes, cables, or chains to the wing tie- of corrosion resistant alclad aluminum, which will down fittings located at the upper end of each wing last indefinitely under normal conditions if kept clean, strut. Secure the opposite ends of ropes, cables, however, these alloys are subject to oxidation. The or chains to ground anchors. first indication of corrosion on unpainted surfaces is b. Secure a tie-down rope (no chains or cables) to in the form of white deposits or spots. On painted upper strut of the nose gear, and secure opposite end surfaces, the paint is discolored or blistered. Stor- of rope to a ground anchor. age in a dry hangar is essential to good preservation c. Secure the middle of a rope to the tail tie-down and should be procured, if possible. Varying con- ring. Pull each end of rope away at a 45 degree ditions will alter the measures of preservation, but angle and secure to ground anchors at each side of under normal conditions in a dry hangar, and for tail. storage periods not to exceed 90 days, the following d. Secure control lock on pilot control column. If methods of treatment are suggested. control lock is not available, tie pilot control wheel a. Fill fuel cells with correct grade of gasoline. back with front seat belt. b. Clean and wax aircraft thoroughly. e. These aircraft are equipped with a spring-loaded c. Clean any oil or grease from tires and coat tires steering bungee which affords protection against nor- with a tire preservative. Cover tires to protect mal wind gusts. However, if extremely high wind against grease and oil. gusts are anticipated, additional external locks may be d. Either block up fuselage to relieve pressure on installed. tires or rotate wheels every 30 days to prevent flat spotting the tires. 2-9. FLYABLE STORAGE. Flyable storage is de- e. Lubricate all airframe items and seal or cover fined as a maximum of 30 days non-operational stor- all openings which could allow moisture and/or dust age and/or the first 25 hours of intermittent engine to enter. operation. Change 2 2-3 NOTE effect that the propeller shall not be moved while the engine is in storage. The aircraft battery serial number is recorded in the aircraft equipment list. To assure ac- 2-12. INSPECTION DURING STORAGE. curate warranty records, the battery should be a. Inspect airframe for corrosion at least once a reinstalled in the same aircraft from which it month. Remove dust collections as frequently as was removed. If the battery is returned to possible. Clean and wax aircraft as required. service in a different aircraft, appropriate b. Inspect the interior of at least one cylinder record changes must be made and notification through the spark plug hole for corrosion at least sent to the Cessna Claims Department. once each month. f. Remove battery and store in a cool, dry place; NOTE service battery periodically and charge as required. Do not move crankshaft when inspecting in- NOTE terior of cylinder for corrosion. An engine treated in accordance with the fol- c. If at the end of the 90 day period, the aircraft is lowing may be considered being protected to be continued in non-operational storage, repeat the against normal atmospheric corrosion for a procedural steps "g" thru "o" of paragraph 2-11. period not to exceed 90 days. 2-13. RETURNING AIRCRAFT TO SERVICE. After g. Disconnect spark plug leads and remove upper temporary storage, use the following procedures to and lower spark plugs from each cylinder. return the aircraft to service. a. Remove aircraft from blocks. Check tires for NOTE proper inflation. b. Check and install battery. The preservative oil must be Lubricating Oil - c. Check that oil sump has proper grade and quantity Contact and Volatile, Corrosion Inhibited, of engine oil. MIL-L-46002, Grade 1, or equivalent. The d. Service induction air filter and remove warning following oils are approved for spraying by placard from propeller. Teledyne Continental Motors: Nude Oil 105- e. Remove materials used to cover openings. Daubert Chemicals Co., 4700 So. Central f. Remove, clean and gap spark plugs. Ave., Chicago, Illinois; Petratect VA-Penn- g. While spark plugs are removed, rotate propeller sylvania Refining Co., Butler, Pennsylvania, several revolutions to clear excess rust preventive and Ferro-Gard 1009G-Ranco Laboratories, oil from cylinders. Inc., 3617 Brownsville Road, Pittsburgh, h. Install spark plugs and torque to value specified i. Check fuel strainer. Remove and clean filter h. Using a portable pressure sprayer, spray pre- screen, if necessary. Check fuel cells and fuel lines servative oil through the upper spark plug hole of for moisture and sediment. Drain enough fuel to each cylinder with the piston in a down position. Ro- eliminate moisture and sediment. tate crankshaft as each pair of cylinders is sprayed. j. Perform a thorough pre-flight inspection, then start and warm-up engine. i. After completing step "h, " rotate crankshaft so that no piston is at a top position. If the aircraft is 2-14. INDEFINITE STORAGE. Indefinite storage to be stored outside, stop two-bladed propeller so is defined as aircraft in a non-operational status for that blades are as near horizontal as possible to pro- an indefinite period of time. Engines treated in ac- vide maximum clearance with passing aircraft. cordance with the following may be considered pro- j. Again, spray each cylinder without moving the tected against normal atmosphere corrosion, pro- crankshaft, to thoroughly cover all interior surfaces vided the procedures outlined in paragraph 2-15 are of the cylinder above the piston. performed at the intervals specified. k. Install spark plugs and connect spark plug leads. a. Operate engine until oil temperature reaches 1. Apply preservative oil to the engine interior by normal operating range. Drain engine oil sump in spraying approximately two ounces of the preservative accordance with procedures outlined in paragraph oil through the oil filler tube. 2-16. Close drain valve or install drain plug. m. Seal all engine openings exposed to the atmos- b. Fill oil sump to normal operating capacity with phere, using suitable plugs or non-hygroscopic tape. corrosion preventive mixture recommended in the Attach a red streamer at each point that a plug or following note. Thoroughly mix and preheat the pre- tape is installed. ventive to a minimum of 221°F at the time it is added n. If the aircraft is to be stored outside, perform to the engine. the procedures outlined in paragraph 2-8. In addi- tion, the pitot tube, static source vents, air vents, openings in the engine cowling, and other similar openings should have protective covers installed to prevent entry of foreign material. o. Attach a warning placard to the propeller to the 2-4 Change 3 NOTE o. Attach a warning placard on the throttle control knob to the effect that the engine contains no lubricat- Corrosion preventive mixture consists of one ing oil. Placard the propeller to the effect that it part compound MIL-C-6529C, Type I, mixed should not be moved while the engine is in storage. with three parts new lubricating oil of the p. Prepare airframe for storage as outlined in grade recommended for service. Continen- paragraph 2-11 thru step "f." tal Motors Corporation recommends Cosmo- line No. 1223, supplied by E. F. Houghton NOTE & Co., 305 W. LeHigh Avenue, Philadelphia, Pa. During all spraying operations, corro- As an alternate method of indefinite storage, sion preventive mixture is preheated to 221 ° the aircraft may be serviced in accordance to 250°F. with paragraph 2-11, providing the aircraft is run-up at maximum intervals of 90 days and c. Immediately after filling the oil sump with a then reserviced per paragraph 2-11. corrosion preventive mixture, fly the aircraft for a period of time not to exceed a maximum of 30 min- 2-15. INSPECTION DURING STORAGE. Aircraft utes. in indefinite storage shall be inspected as follows: d. After flight, with engine operating at 1200 to a. Inspect cylinder protex plugs each 7 days. 1500 rpm, and induction air filter removed, spray b. Change protex plugs if their color indicates an corrosion preventive mixture into induction airbox, unsafe condition. at the rate of one-half gallon per minute. Spray c. If the protex plugs have changed color in one half until heavy black smoke comes from exhaust stack. of the cylinders, all desiccant material in the engine Then increase the spray until engine is stopped. should be replaced with new material. d. Respray the cylinder interiors with corrosion CAUTION preventive mixture every 6 months. Spraying the mixture too fast can cause a NOTE hydrostatic lock. Before spraying, inspect the interior of one e. Do not rotate propeller after completing step cylinder for corrosion through the spark "d. " plug hole and remove at least one rocker f. Remove all spark plugs and spray corrosion box cover and inspect the valve mechanism. preventive mixture, which has been preheated to 221 ° to 240°F., into all spark plug holes to thorough- 2-16. RETURNING AIRCRAFT TO SERVICE. After ly cover interior surfaces of cylinders, indefinite storage, use the following procedure to g. Install spark plugs or solid plugs into the lower return the aircraft to service. spark plug holes and install dehydrator plugs in the a. Remove aircraft from blocks. Check tires for upper spark plug holes. Be sure that dehydrator correct inflation. plugs are blue in color when installed. b. Check and install battery. h. Cover spark plug lead terminals with shipping c. Remove all materials used to seal and cover plugs (AN4060-1), or other suitable covers. openings. i. With throttle in full open position, place a bag d. Remove warning placards posted at throttle and of desiccant in the induction air intake and seal open- propeller. ing with moisture resistant paper and tape. e. Remove and clean engine oil screen, then rein- j. Place a bag of desiccant in the exhaust tailpipe stall and safety. On aircraft equipped with an exter- and seal openings with moisture resistant tape. nal oil filter, install new filter element. k. Seal cold air inlet to the heater muff with mois- f. Remove oil sump drain plug or open drain valve ture resistant tape. and drain sump. Install or close drain valve and 1. Seal engine breather tube by inserting a protex safety. plug in the breather hose and clamping in place. g. Service and install the induction air filter. m. Seal all other engine openings exposed to atmos- phere, using suitable plugs or non-hygroscopic tape. NOTE NOTE The corrosion preventive mixture will mix with the engine lubricating oil, so flushing Attach a red streamer to each location where the oil system is not necessary. Draining plugs or tapes are installed. Either attach the oil sump will remove enough of the cor- red streamers outside the sealed area with rosion preventive mixture. tape or to the inside of the sealed area with safety wire to prevent wicking of moisture h. Remove protex plugs and spark plugs or plugs in- into the sealed area. stalled in spark plug holes. Rotate propeller several revolutions by hand to clear corrosion preventive mix- n. Drain corrosion preventive mixture from engine ture from cylinders. sump and reinstall drain plug or close drain valve. i. Clean, gap and install spark plugs. Torque spark The corrosion preventive mixture is harmful plugs to value specified in Section 11. Connect leads. to paint and should be wiped from painted sur- j. Check fuel strainer. Remove and clean filter faces immediately. screen. Check fuel cells and fuel lines for moisture Change 3 2-5 and sediment. Drain enough fuel to eliminate mois- should be drained while the engine is still hot, and the ture and sediment. nose of the aircraft should be raised slightly for more k. Perform a thorough pre-flight inspection, then positive draining of any sludge which may have col- start and warm-up engine. lected in the engine oil sump. Engine oil should be 1. Thoroughly clean and test-fly aircraft. changed every six months, even though less than the specified hours have accumulated. Reduce these in- 2-17. SERVICING. tervals for prolonged operations in dusty areas, in cold climates where sludging conditions exist, or 2-18. GENERAL DESCRIPTION. Servicing require- where short flights and long idle periods are en- ments are shown in figure 2-3. The following para- countered, which cause sludging conditions. Always graphs supplement this figure by adding details not change oil, clean oil screens and clean and/or change included in the figure. external filter element whenever oil on the dipstick appears dirty. Aviation grade ashless dispersant oil 2-19. FUEL. Fueltanks should be filled immediately conforming to Continental Motors Specification MHS- after flight to lessen condensation in the tanks and lines. 24 and all revisions or supplements thereto and con- Tank capacities are listed in figure 1-1. The recom- forming with current Continental Aircraft Engine mended fuel grade to be used is given in figure Service Bulletins shall be used in the Continental En- gines. 2-20. FUEL DRAINS are located at various places throughout the fuel system. Refer to Section 12 for NOTE location of the various drains in the system. The strainer drain valve is an integral part of the fuel New or newly overhauled engines should be strainer assembly. The strainer drain is equipped operated on aviation grade straight mineral with a control which is located adjacent to the oil dip- oil until the first oil change. The aircraft is stick. Access to the control is through the oil dip- delivered from Cessna with straight mineral stick access door. Remove drain plugs and open oil (MIL-C-6529, Type II, RUST BAN). If drain valves at the intervals specified in the inspec- oil must be added during the first 25 hours, tion charts in this Section. Also, during daily inspec- use only aviation grade straight mineral oil tion of the fuel strainer, if water is found in the strai- conforming to Specification MIL-6082. Af- ner, there is a possibility that the wing tank sumps ter the first 25 hours of operation, drain or fuel lines contain water. Therefore, all drain engine oil sump and clean both the oil suction plugs/valves should be removed and all water drained strainer and the oil pressure screen. If an from the system. To activate drain valve for fuel optional oil filter is installed, change filter sampling, place cup up to valve and depress valve elenent at this time. Refill sump with with rod protruding from cup. (Refer to figure 12-3.) straight mineral oil and use until a total of 50 hours have accumulated or oil consump- 2-21A. CARBURETOR DRAIN PLUG INSPECTION. tion has stabilized, then change to ashless In order to prevent the possibility of thread sealant dispersant oil. contamination in the carburetor float chamber, cleaning and inspection of the carburetor should be When changing engine oil, remove and clean oil accomplished at each 100-hour inspection and any- screens, or install a new filter element on aircraft time water in the fuel is suspected. equipped with an external oil filter. An oil quick- a. With the fuel valve OFF, remove carburetor drain valve may be installed. This valve provides drain plug and clean off any sealant present on the a quick and cleaner method of draining the engine oil. end of the plug or in the threads on the plug. This valve is installed in the oil drain port of the oil b. Inspect drain plug hole in the carburetor and re- sump. To drain the oil, proceed as follows: move any sealant remaining in the hole. a. Operate engine until oil temperature is at a c. Install drain plug as follows: normal operating temperature. 1. Install drain plug in carburetor 1-1/2 to 2 b. (With Quick-Drain Valve) Attach a hose to the turns, quick-drain valve in oil sump. Push upon quick- 2. Apply sealant to drain drain valve until it locks open, and allow oil to Never-Seez RAS-4 or equivalent). drain through hose into container. 3. Tighten and safety drain plug. c. (Without Quick-Drain Valve) Remove oil drain 3. Tighten and safety drain plug. f. Turn fuel valve ON and inspect for evidence of plug from engine sump and allow oil to dran into a fuel leakage. container. d. After engine oil has drained, close quick-drain 2-21. ENGINE OIL. Check engine lubricating oil valve, if installed, and remove hose. Install and 2-21. ENGINE OIL. Check engine lubricating oil with the dipstick five to ten minutes after the engine safety drain plug. has been stopped. The aircraft should be in as near e. Remove and clean oil screen. oil, so that a true reading is obtained. Engine oil engine oil. 2-6 Change 3 NOTE d. After washing, rinse filter with clear water un- til rinse water draining from filter is clear. Allow Refer to inspection charts for intervals for water to drain from filter and dry with compressed changing oil and filter elements. Refer to air (not over 100 psi). figure 2-3 for correct grade of engine oil, and refer to figure 1-1 for correct capacities. NOTE The filtering panels of the filter may become distorted when wet, but they will return to their original shape when dry. 2-22. ENGINE INDUCTION AIR FILTER. The in- e. Be sure air box is clean, inspect filter. If duction air filter keeps dust and dirt from entering filter is damaged, install a new filter. the induction system. The value of maintaining the f. Install filter at entrance to air box with gasket air filter in a good clean condition can never be over- on aft face of filter frame and with air flow arrows stressed. More engine wear is caused through the on filter frame pointed in the correct direction. use of a dirty or damaged air filter than is generally believed. The frequency with which the filter should 2-23. VACUUM SYSTEM FILTER. The vacuum sys- be removed, inspected, and cleaned will be deter- ter central air filter keeps dust and dirt fron entering mined primarily by aircraft operating conditions. A the vacuum operated instruments. Inspect the filter good general rule however, is to remove, Inspect, every 200 hours for damage and cleanliness. Change and clean the filter at least every 50 hours of engine central air filter element every 500 hours of operating operating time and more frequently if warranted by time and whenever suction reading drops below 4. 6 operating conditions. Some operators prefer to hold inches of mercury. Also, do not operate the vacuum spare induction air filters at their home base of system with the filter removed, or a vacuum line dis- operation so that a clean filter is always readily avail- connected as particles of dust or other foreign matter able for use. Under extremely dusty conditions, may enter the system and damage the vacuum operated daily servicing of the filter is recommended. To instruments. service the induction air filter, proceed as follows: 2-24. BATTERY. Battery servicing involves add- a. Remove filter from aircraft. ing distilled water to maintain the electrolyte even with the horizontal baffle plate at the bottom of the NOTE filler holes, checking the battery cable connections, and neutralizing and cleaning off and spilled electro- Use care to prevent damage to filter element lyte or corrosion. Use bicarbonate of soda (baking when cleaning filter with compressed air. soda) and water to neutralize electrolyte or corro- sion. Follow with a thorough flushing with water. b. Clean filter by blowing with compressed air Brighten cables and terminals with a wire brush, (not over 100 psi) from direction opposite of normal then coat with petroleum jelly before connecting. air flow. Arrows on filter case indicate direction of The battery box also should be checked and cleaned normal air flow. if any corrosion is noted. Distilled water, not acid or "rejuvenators", should be used to maintain elec- CAUTION trolyte level. Check the battery every 50 hours (or at least every 30 days) oftener in hot weather. See Do not use solvent or cleaning fluids to wash Section 16 for detailed battery removal, installation filter. Use only a water and household deter- and testing. gent solution when washing the filter. 2-25. TIRES. Maintain tire pressure at the pressure c. After cleaning as outlined in step "b", the filter specified in figure 1-1. When checking tire pressure, may be washed, if necessary, in a solution of warm examine tires for wear, cuts, bruises, and slippage. water and a mild household detergent. A cold water Remove oil, grease, and mud from tires with soap solution may be used. and water. NOTE NOTE The filter assembly may be cleaned with corn- Recommended tire pressures should be main- pressed air a maximum of 30 times or it may tained. Especially in cold weather, remember be washed a maximum of 20 times. A new that any drop in temperature of the air inside filter should be installed after using 500 hours a tire causes a corresponding drop in air pres- of engine operating time or one year, whichever sure. should occur first. However, a new filter should be installed at anytime the existing filter is 2-26. NOSE GEAR SHOCK STRUT. The nose gear damaged. A damaged filter may have sharp shock strut requires periodic checking to ensure that or broken edges in the filtering panels which the strut is filled with hydraulic fluid and is inflated would allow unfiltered air to enter the induc- to the correct air pressure. To service the nose gear tion system. Any filter that appears doubtful, shock strut, proceed as follows: shall have a new filter installed in its place. Change 2 2-7 a. Remove valve cap and release air pressure. NOTE b. Remove valve housing. c. Compress nose gear to its shortest length and Be sure that the shimmy dampener and fill strut with hydraulic fluid to the bottom of the hydraulic fluid are at 70 ° to 80°F while filler hole. filling the shimmy dampener. d. Raise nose of aircraft, extend and compress strut several times to expel any entrapped air, then g. Install filler plug, and wash dampener in clean- lower nose of aircraft and repeat step "c". ing solvent and wipe dry with a clean cloth. e. With strut compressed, install valve housing h. Install dampener on aircraft. assembly. f. With nose wheel off ground, inflate strut. Shock NOTE strut pressure is listed in figure 1-1. g. Check strut extension by measuring distance "A", Keep shimmy dampener, especially the as indicated in figure 5-5. exposed portions of the dampener piston shaft, clean to prevent collection of dust NOTE and grit which could cut the seals in the dampener barrel. Keep machined sur- The nose landing gear shock strut will faces wiped free of dirt and dust, using a normally require only a minimum amount clean lint-free cloth saturated with hy- of service. Maintain the strut extension draulic fluid (MIL-H-5606) or kerosene. pressure as shown in Section 1. Lubricate All surfaces should be wiped free of ex- landing gear as shown in figure 2-4. Check cessive hydraulic fluid. the landing gear daily for general cleanli- ness, security of mounting, and for hydrau- 2-28. HYDRAULIC BRAKE SYSTEMS. Check brake lic fluid leakage. Keep machined surfaces master cylinders and refill with hydraulic fluid as wiped free of dirt and dust, using a clean required every 200 hours. Bleed the brake system lint-free cloth saturated with hydraulic of entrapped air whenever there is a spongy response fluid (MIL-H-5606) or kerosene. All sur- to the brake pedals. Refer to Section 5 for filling faces should be wiped free of excessive and bleeding of the brake systems. hydraulic fluid. 2-29. CLEANING. 2-27. NOSE GEAR SHIMMY DAMPENER. The nose gear shimmy dampener contains a compensating 2-30. GENERAL DESCRIPTION. Keeping the air- mechanism within the hollow piston rod. This is for craft clean is important. Besides maintaining the thermal expansion and contraction of the hydraulic trim appearance of the aircraft, cleaning lessens the fluid in the dampener. The shimmy dampener must possibility of corrosion and makes inspection and be filled completely with hydraulic fluid, free of en- maintenance easier. trapped air with the compensating piston bottomed in the piston rod. Before servicing the shimmy dampen- 2-31. WINDSHIELD AND WINDOWS should be er, ascertain that the compensating piston is bottom- cleaned carefully with plenty of fresh water and a ed in the piston rod. Service the shimmy dampener mild detergent, using the palm of the hand to feel at least every 50 hours as follows: and dislodge any caked dirt or mud. A sponge, soft a. Remove shimmy dampener from the aircraft. cloth, or chamois may be used, but only as a means b. While holding the shimmy dampener in a verti- of carrying water to the plastic. Rinse thoroughly, cal position with the filler plug pointed upward, then dry with a clean moist chamois. Do not rub the loosen filler plug to allow excess fluid to escape. plastic with a dry cloth as this builds up an electro- c. Allow the spring to bottom out the floating pis- static charge which attracts dust. Oil and grease ton inside the shimmy dampener rod. may be removed by rubbing lightly with a soft cloth d. When the fluid stops flowing, insert a length of moistened with Stoddard solvent. stiff wire through the air bleed hole in the setscrew at the end of the piston rod until it touches the float- CAUTION ing piston. The depth of insertion should be 3-13/16 inches. Do not use gasoline, alcohol, benzene, acetone, carbon tetrachloride, fire extinguisher fluid, NOTE de-icer fluid, lacquer thinner, or glass window cleaning spray. These solvents will soften and If the wire insertion is less than 3-13/16 craze the plastic. inches, the floating piston is lodged in the shaft. If the wire cannot be used to free After washing, the plastic windshield and windows the piston, the rod assembly and piston should be cleaned with an aircraft windshield cleaner. should be replaced. Apply the cleaner with soft cloths and rub with mod- erate pressur e. Allow the cleaner to dry, then wipe e. After determining that floating piston is bottomed, it off with soft flannel cloths. A thin, even coat of move dampener rod to place piston to the end of the wax, polished out by hand with soft flannel cloths, barrel opposite the filler plug. will fill in minor scratches and help prevent further f. Remove filler plug and fill shimmy dampener scratching. Do not use a canvas cover on the wind- with hydraulic fluid, shield or windows unless freezing rain or sleet is 2-8 Change 3 anticipated since the cover may scratch the plastic longs upholstery fabrics and interior trim. To clean surface. the interior, proceed as follows: a. Empty all ash trays and refuse containers. 2-32. INTERIOR TRIM. The instrument panel, in- b. Brush or vacuum clean the upholstery and carpet terior plastic trim, and control knobs need only be to remove dust and dirt. wiped with a damp cloth. Oil and grease on the con- c. Wipe leather and plastic trim with a damp cloth. trol wheels and control knobs can be removed with a d. Soiled upholstery fabrics and carpet may be cloth moistened with Stoddard solvent. Volatile sol- cleaned with a foam-type detergent used according to vents, mentioned in the caution note of paragraph 2-31, the manufacturer's instructions. must never be used since they soften and craze the e. Oil spots and stains may be cleaned with house- plastic trim. hold spot removers, used sparingly. Before using any solvent, read the instructions on the container 2-33. PAINTED SURFACES. The painted exterior and test it on an obscure place in the fabric to be surfaces of the aircraft, under normal conditions, cleaned. Never saturate the fabric with volatile sol- require a minimum of polishing and buffing. Approxi- vent; it may damage the padding and backing material. mately 15 days are required for acrylic or lacquer f. Scrape sticky material from fabric with a dull paint to cure completely; in most cases, the curing knife, then spot clean the area. period will have been completed prior to delivery of the aircraft. In the event that polishing or buffing is 2-37. PROPELLER. The propeller should be wiped required within the curing period, it is recommended occasionally with an oily cloth to remove grass and that the work be done by an experienced painter. bug stains. In salt water areas this will assist in Generally, the painted surfaces can be kept bright by corrosion proofing the propeller. washing with water and mild soap, followed by a rinse with water and drying with cloths or chamois. 2-38. WHEELS should be washed periodically and Harsh or abrasive soaps or detergents which could examined for corrosion, chipped paint, and cracks cause corrosion or make scratches should never be or dents in the wheel castings. Sand smooth, prime, used. Remove stubborn oil and grease with a cloth and repaint or repair minor defects. moistened with Stoddard solvent. After the curing period, the aircraft may be waxed with a good auto- 2-39. LUBRICATION. motive wax. A heavier coating of wax on the leading edges of the wing and tail and on the engine nose cap 2-40. GENERAL DESCRIPTION. Lubrication re- will help reduce the abrasion encountered in these quirements are shown in figure 2-4. Before adding areas. lubricant to a fitting, wipe fitting free of dirt. Lubri- cate until grease appears around part being lubricat- 2-34. ALUMINUM SURFACES. The aluminum sur- ed, and wipe excess grease from parts. The follow- faces require a minimum of care, but should never ing paragraphs supplement figure 2-4 by adding de- be neglected. The aircraft may be washed with clean tails not shown in the figure. water to remove dirt and may be washed with non- alkaline grease solvents to remove oil and/or grease. 2-41. TACHOMETER DRIVE SHAFT. Refer to Sec- Household type detergent soap powders are effective tion 15 for details on lubrication of the drive shaft. cleaners, but should be used cautiously since some of them are strongly alkaline. Many good aluminum 2-42. WHEEL BEARINGS. Clean and repack the cleaners, polishes and waxes are available from com- wheel bearings at the first 100-hour inspection and mercial suppliers of aircraft products, at each 500-hour inspection thereafter. If more than the usual number of take-offs and landings are 2-35. ENGINE COMPARTMENT cleaning is essen- made, extensive taxiing is required, or the aircraft tial to minimize any danger of fire, and for proper is operated in dusty areas or under seacoast condi- inspection of components. The engine compartment tions, cleaning and lubrication of the wheel bearings may be washed down with a suitable solvent, such as shall be accomplished at each 100-hour inspection. Stoddard solvent or equivalent, then dried thoroughly. 2-43. NOSE GEAR TORQUE LINKS. Lubricate nose from a dirt strip or in extremely areas, more fre- Particular care should be given to electrical quent lubrication of the torque links is required. equipment before cleaning. Solvent should not be allowed to enter magnetos, starters, 2-44. WING FLAP ACTUATOR. alternators, voltage regulators, and the like. a. On aircraft prior to Serials 18260698 & A182- Hence, these components should be protected 0136 which have not been modified by Service Kit before saturating the engine with solvent. Any SK150-37, proceed as follows: fuel, oil, and air openings should be covered 1. At each 100 hour inspection, inspect wing before washing the engine with solvent. Caustic flap actuator jack screw and ball retainer assembly cleaning solutions should be used cautiously and for lubrication, and lubricate if required. Also, should always be properly neutralized after remove, clean and lubricate jack screw whenever their use. actuator slippage is experienced. If lubrication is required, proceed as follows: a. Gain access to actuator by removing 2-36. UPHOLSTERY AND INTERIOR cleaning pro- appropriate inspection plates on lower surface of Change 3 2-9 wing. threaded end of the nut. b. Expose jack screw by operating flaps to m. Repeat the process and work nut back full-down position. and forth several times. c. Wipe a small amount of lubricant from n. Remove excess grease. jack screw with a rag and examine for condition. o. Reinstall actuator in aircraft in accor- Lubricant should not be dirty, sticky, gummy or dance with instructions outlined in Section 7. frothy in appearance. b. On aircraft prior to Serials 18260698 & A182- d. Inspect wiped area on jack screw for 0136 which have been modified by Service Kit SK150- presence of hard scale deposit. Previous wiping 37, proceed as follows: action will have exposed bare metal if no deposit 1. At each 100 hour inspection, expose jack is present. screw by operating flaps to full-down position, and e. If any of the preceding conditions exist, inspect wing flap actuator jack screw for proper clean and relubricate jack screw as outlined in steps lubrication. If lubrication is required, proceed as "f" thru "r". follows: f. Remove actuator from aircraft in accor- a. Clean jack screw with solvent rag, if dance with procedures outlined in Section 7. necessary, and dry with compressed air. g. Remove all existing lubricant from jack b. Relubricate jack screw with MIL-G- screw and torque tube by running the nut assembly to 21164 (Molybdenum Disulfide Grease) as required. the end of the jack screw away from the gearbox, and c. On aircraft beginning with Serials 18260698 & soaking the nut assembly and jack screw in Stoddard A182-0136, clean and lubricate wing flap actuator solvent. jack screw each 100 hours as follows: 1. Expose jack screw by operating flaps to NOTE full-down position. 2. Clean jack screw threads with solvent rag Care must be taken to prevent solvent from and dry with compressed air. entering gearbox. The gearbox lubricant is not affected and should not be disturbed. NOTE h. After soaking, clean entire length of jack It is not necessary to remove actuator from screw with a wire brush, rinse with solvent and dry aircraft to clean or lubricate threads. with compressed air. 3. With oil can apply light coat of No. 10 weight, NOTE non-detergent oil to threads of jack screw. Do not disassemble nut and ball retainer 2-45. ROD END BEARINGS. Periodic inspection assembly. and lubrication is required to prevent corrosion of the bearing in the rod end. At each 100-hour inspec- i. Relubricate jack screw with MIL-G-21164 tion, disconnect the control rods at the aileron and (Molybdenum Disulfide Grease) as outlined in steps nose gear steering bungee, and inspect each rod end "j" thru "m". for corrosion. If no corrosion is found, wipe the j. Rotate nut down screw toward the motor. surface of the rod end balls with general purpose oil k. Coat screw and thread end of nut with and rotate ball freely to distribute the oil over its grease and run nut to full extension. entire surface and connect the control rods to their 1. Repeat the process and pack lubricant in respective units. If corrosion is detected during the the cavity between the nut and ball retainer at the inspection, install new rod ends. 2-10 HYDRAULIC FLUID: SPEC. NO. MIL-H-5606 OXYGEN: SPEC. NO. MIL-0-27210D RECOMMENDED FUEL: ENGINE MODEL 0-470-Series CONTINENTAL Compliance with conditions stated in Continental aircraft engine Service Bulletins M74-6 and M75-2 and supplements or revisions thereto, are recommended when using alternate fuel. FUEL: 1. MINIMUM: 80/87 Aviation grade 2. ALTERNATES: a. 100/130 Low Lead Avgas (with lead content limited to a maximum of 2 cc Tetraethyl lead per gallon). b. 100/130 Higher Lead Avgas (with lead content limited to a maximum of 4. 6 cc Tetra- ethyl lead per gallon). Figure 2-3. Servicing (Sheet 1 of 3) Change 3 2-11 RECOMMENDED ENGINE OIL: ENGINE MODEL 0-470-Series CONTINENTAL AVIATION GRADE: ABOVE: SAE 50 BELOW: SAE 30 Aviation Grade ashless dispersant oil, conforming to Continental Motors Specification MHS-24 and all revisions and supplements thereto, must be used except as noted in paragraph 2-21. Refer to Continental Aircraft Engine Service Bulletin M75-2 and any superseding bulletins, revisions or supplements thereto, for further recommendations. DAILY 3 FUEL CELLS: Service after each flight. Keep full to retard condensation. Refer to paragraph 2-19. 4 FUEL CELL SUMP DRAINS: Drain off any water and sediment before first flight of the day. 10 FUEL STRAINER: Drain off any water and sediment before first flight of the day. 16 OIL DIPSTICK: Check on preflight. Add oil as necessary. Refer to paragraph 2-21 for details. Check that filler cap is tight and oil filler is secure. 6 PITOT AND STATIC PORTS: Check for obstructions before first flight of the day. 21 OXYGEN CYLINDER: Check for anticipated requirements before each flight. Refer to Section 14. (FIRST 25 HOURS 15 ENGINE OIL SYSTEM: Refill with straight mineral oil and use until a total of 50 hours have accumulated or oil consump- tion has stabilized, then change to ashless dispersant oil. Refer to paragraph 2-21. 50 HOURS 13 INDUCTION AIR FILTER: Clean filter per paragraph 2-22. Replace as required. 14 BATTERY: Check electrolyte level and clean battery compartment each 50 hours or each 30 days. 15 ENGINE OIL SYSTEM: Change oil each 50 hours if engine is NOT equipped with external filter; if equipped with external filter, change filter element each 50 hours and oil at least at each 100 hours, or every 6 months. 12 SHIMMY DAMPENER: Check fluid level and refill as required in accordance with paragraph 2-27. Figure 2-3. Servicing (Sheet 2 of 3) 2-12 Change 3 50 HOURS (Cont.) TIRES: Maintain correct tire inflation as listed in figure 1-1. Refer to paragraph 2-25. 11 NOSE GEAR SHOCK STRUT: Keep strut filled and inflated to correct pressure. Refer to paragraph 2-26. 17 SPARK PLUGS: Remove, clean and re-gap all spark plugs. Refer to Section 11. 100 HOURS 22 VACUUM SYSTEM OIL SEPARATOR: Remove, flush with solvent, and dry with compressed air. 20 CARBURETOR DRAIN PLUG: Check for thread sealant residue in float chamber. Refer to paragraph 2-20. 10 FUEL STRAINER: Disassemble and clean strainer bowl and screen. 5 SELECTOR VALVE DRAIN: Remove plug and drain off any water or sediment. Refer to paragraph 2-20. 19 ALTERNATOR SUPPORT BRACKET: Check alternator support bracket for security and cracking. (Also refer to Service Letter SE71-42. ) 200 HOURS 18 VACUUM RELIEF VALVE FILTER: Change every 100 hours or to coincide with engine overhauls. 4 FUEL BAY SUMP DRAINS: Drain off any water or sediment. 9 BRAKE MASTER CYLINDERS: Check fluid level and fill as required with hydraulic fluid. 500 HOURS 2 VACUUM SYSTEM CENTRAL AIR FILTER: Replace every 500 hours. AS REQUIRED 8 GROUND SERVICE RECEPTACLE: Connect to 12-volt DC, negative-ground power unit. Refer to Section 16. Figure 2-3. Servicing (Sheet 3 of 3) Change 3 2-13 FREQUENCY (HOURS) METHOD OF APPLICATION GUN CAN (FOR POWDERED GRAPHITE) WHERE NO INTERVAL IS SPECIFIED, LUBRICATE AS REQUIRED AND WHEN ASSEMBLED OR INSTALLED. NOTE The military specifications listed are not mandatory, but are intended as guides in choosing satisfactory materials. Products of most reputable manufacturers meet or exceed these specifications. LUBRICANTS PG SS-G-659 ............ POWDERED GRAPHITE GR MIL-G-81322A. ......... GENERAL PURPOSE GREASE GH MIL-G-23827A ......... . AIRCRAFT AND INSTRUMENT GREASE GL MIL-G-21164C. ......... HIGH AND LOW TEMPERATURE GREASE 06 MIL-L-7870A .......... GENERAL PURPOSE OIL PL VV-P-236 ............ PETROLATUM 6S MIL-S-8660 ........... DC4 (DOW CORNING) P ................. NO. 10-WEIGHT, NON-DETERGENT OIL ALSO REFER TO PARAGRAPH 2-43 NOSE GEAR ALSO REFER TO SHIMMY PARAGRAPH 2-42 DAMPENER PIVOTS TORQUE LINKS WHEEL BEARINGS WHEEL BEARINGS Figure 2-4. Lubrication (Sheet 1 of 3) 2-14 Change 1 OILITE BEARINGS ELEVATOR DOWN SPRING LINK RUB STRIP CHART IN THIS SECTION AND RUDDER BARS AND PEDALS TO SECTION 9 OF THIS MANUAL. ELEVATOR TRIM TAB ACTUATOR PARKING BRAKE BATTERY TERMINALS WING STRUT-ATTACH HANDLE SHAFT (UPPER) BOLT & HOLE CABIN DOOR WINDOW INSERT GROOVES WING STRUT-ATTACH (LOWER) BOLT & HOLE* TRIM WHEEL OILITE AND NEEDLE BEARINGS * UPON INSTALLATION Figure 2-4. Lubrication (Sheet 2 of 3) Change 1 2-15 CONTROL COLUMN NEEDLE BEARINGS NEEDLE BEARING THRUST BEARING NEEDLE BEARING ELECTRIC FLAP NEEDLE BEARINGS ROD END BEARINGS NOTES Sealed bearings require no lubrication. Do not lubricate roller chains or cables except under seacoast conditions. Wipe with a clean, dry cloth. Lubricate unsealed pulley bearings, rod ends, Oilite bearings, pivot and hinge points, and any other friction point obviously needing lubrication, with general purpose oil every 1000 hours or oftener if required. Paraffin wax rubbed on seat rails will ease sliding the seats fore and aft. Lubricate door latching mechanism with MIL-G-81322A general purpose grease, applied sparingly to friction points, every 1000 hours or oftener, if binding occurs. No lubrication is recommended on the rotary clutch. Figure 2-4. Lubrication (Sheet 3 of 3) I INSPECTION REQUIREMENTS. As required by Federal Aviation Regulations, all civil aircraft of U.S. registry must undergo a COMPLETE INSPECTION (ANNUAL) each twelve calendar months. In addition to the required ANNUAL inspection, aircraft operated commercially (for hire) must also have a COMPLETE AIRCRAFT INSPECTION every 100 hours of operation. In lieu of the above requirements, an aircraft may be inspected in accordance with a progressive inspection schedule, which allows the work load to be divided into smaller operations that can be accomplished in shorter time periods. Therefore, the Cessna Aircraft Company recommends PROGRESSIVE CARE for aircraft that are being flown 200 hours or more per year, and the 100 HOUR inspection for all other aircraft. INSPECTION CHARTS. The following charts show the recommended intervals at which items are to be inspected. As shown in the charts, there are items to be checked each 50 hours, each 100 hours, each 200 hours, and also Special Inspection items which require servicing or inspection at intervals other than 50, 100 or 200 hours. a. When conducting an inspection at 50 hours, all items marked under EACH 50 HOURS would be inspected, serviced or otherwise accomplished as necessary to insure continuous airworthiness. b. At each 100 hours, the 50 hour items would be accomplished in addition to the items marked under EACH 100 HOURS as necessary to insure continuous airworthiness. c. An inspection conducted at 200 hour intervals would likewise include the 50 hour items and 100 hour items in addition to those at EACH 200 HOURS. d. The numbers appearing in the SPECIAL INSPECTION ITEMS column refer to data listed at the end of the inspection charts. These items should be checked at each inspection interval to insure that applicable servicing and inspection requirements are accomplished at the specified intervals. e. A COMPLETE AIRCRAFT INSPECTION includes all 50, 100 and 200 hour items plus those Special Inspection Items which are due at the time of the inspection. III INSPECTION PROGRAM SELECTION. AS A GUIDE FOR SELECTING THE INSPECTION PROGRAM THAT BEST SUITS THE OPERATION OF THE AIRCRAFT, THE FOLLOWING IS PROVIDED. 1. IF THE AIRCRAFT IS FLOWN LESS THAN 200 HOURS ANNUALLY. a. IF FLOWN FOR HIRE An aircraft operating in this category must have a COMPLETE AIRCRAFT INSPECTION each 100 hours and each 12 calendar months of operation. A COMPLETE AIRCRAFT INSPECTION consists of all 50, 100, 200 and Special Inspection Items shown in the in- spection charts as defined in paragraph I above. b. IF NOT FLOWN FOR HIRE An aircraft operating in this category must have a COMPLETE AIRCRAFT INSPECTION each 12 calendar months (ANNUAL). A COMPLETE AIRCRAFT INSPECTION consists of all 50, 100, 200 and Special Inspection Items shown in the inspection charts as defined in paragraph I above. In addition, it is recommended that between annual inspections, all items be inspected at the intervals specified in the inspection charts. Change 3 2-17 2. IF THE AIRCRAFT IS FLOWN MORE THAN 200 HOURS ANNUALLY. Whether flown for hire or not, it is recommended that aircraft operating in this category be placed on the CESSNA PROGRESSIVE CARE PROGRAM. However, if not placed on Progressive Care, the inspection requirements for aircraft in this category are the same as those defined under paragraph m 1. (a) and (b). Cessna Progressive Care may be utilized as a total concept program which insures that the inspection intervals in the inspection charts are not exceeded. Manuals and forms which are required for conducting Progressive Care in- spections are available from the Cessna Service Parts Center. IV INSPECTION GUIDE LINES. (a) MOVABLE PARTS for: lubrication, servicing, security of attachment, binding, excessive wear, safetying, proper operation, proper adjustment, correct travel, cracked fittings, security of hinges, defective bearings, cleanliness, corrosion, deformation, sealing and tension. (b) FLUID LINES AND HOSES for: leaks, cracks, dents, kinks, chafing, proper radius, security, corrosion, deterioration, obstruction and foreign matter. (c) METAL PARTS for: security of attachment, cracks, metal distortion, broken spotwelds, corrosion, condition of paint and any other apparent damage. (d) WIRING for: security, chafing, burning, defective insulation, loose or broken terminals, heat deterioration and corroded terminals. (e) BOLTS IN CRITICAL AREAS for: correct torque in accordance with torque values given in the chart in Section 1, when installed or when visual inspection indicates the need for a torque check. NOTE Torque values listed in Section 1 are derived from oil-free cadmium-plated threads, and are recommended for all installation procedures contained in this book except where other values are stipulated. They are not to be used for checking tightness of installed parts during service. (f) FILTERS, SCREENS & FLUIDS for: cleanliness, contamination and/or replacement at specified intervals. (g) AIRCRAFT FILE. Miscellaneous data, information and licenses are a part of the aircraft file. Check that the following documents are up-to-date and in accordance with current Federal Aviation Regulations. Most of the items listed are required by the United States Federal Aviation Regulations. Since the regulations of other nations may require other documents and data, owners of exported aircraft should check with their own aviation officials to determine their individual requirements. To be displayed in the aircraft at all times: 1. Aircraft Airworthiness Certificate (FAA Form 8100-2). 2. Aircraft Registration Certificate (FAA Form 8050-3). 3. Aircraft Radio Station License, if transmitter is installed (FCC Form 556). To be carried in the aircraft at all times: 1. Weight and Balance, and associated papers (Latest copy of the Repair and Alteration Form, FAA Form 337, if applicable). 2. Aircraft Equipment List. To be made available upon request: 1. Aircraft Log Book and Engine Log Book. 2-18 Change 1 (h) ENGINE RUN-UP. Before beginning the step-by-step inspection, start, run up and shut down the engine in accordance with instructions in the Owner's Manual. During the run-up, observe the following, making note of any discrepancies or abnormalities: 1. Engine temperatures and pressures. 2. Static rpm. (Also refer to Section 11 of this Manual). 3. Magneto drop. (Also refer to Section 11 of this Manual). 4. Engine response to changes in power. 5. Any unusual engine noises. 6. Fuel selector and/or shut-off valve; operate engine(s) on each tank (or cell) position and OFF position long enough to ensure shut-off and/or selector valve functions properly. 7. Idling speed and mixture; proper idle cut-off. 8. Alternator and ammeter. 9. Suction gage. 10. Fuel flow indicator. After the inspection has been completed, an engine run-up should again be performed to determine that any discrepancies or abnormalities have been corrected. SHOP NOTES: Change 1 2-19 SPECIAL INSPECTION ITEM IMPORTANT EACH 200 HOURS EACH 100 HOURS READ ALL INSPECTION REQUIRE- MENTS PARAGRAPHS PRIOR TO EACH 50 HOURS USING THESE CHARTS. PROPELLER 1. Spinner . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2. Spinner bulkhead . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3. Blades. . . . . . . .............................. 4. Bolts and nuts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5. Hub ........................ 6. Governor and control . . . . ... . . . . . . . . . . . .. . . . . . ..... ENGINE COMPARTMENT Check for evidence of oil and fuel leaks, then clean entire engine and compartment, if needed, prior to inspection. 1. Engine oil screen filler cap, dipstick, drain plug and external filter element ..... 1 2. Oil cooler ............................... ..... . 3. Induction air filter ......................................... 4. Induction airbox, air valves, doors and controls ....... . ..... . * 5. Cold and hot air hoses . ............... 6. Engine baffles . . . . . . . . . . . . . . . . . 7. Cylinders, rocker box covers and push rod housings ...... ..... . . 8. Crankcase, oil sump, accessory section and front crankshaft seal .......... 9. Hoses, metal lines and fittings .......................... 3 10. Intake and exhaust systems ........................... 4 11. Ignition harness ............................... . 12. Spark plugs .................................. 13. Compression check ................. 14. Crankcase and vacuum system breather lines ........... 15. Electrical wiring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16. Vacuum pump, oil separator and relief valve .................. . 17. Vacuum relief valve filter ........................ 5 18. Engine controls and linkage ........................... 6 19. Engine shock mounts, mount structure and ground straps ........ 2-20 Change 1 CESSNA AIRCRAFT COMPANY MODEL 182 AND SKYLANE SERIES SERVICE MANUAL SPECIAL INSPECTION ITEM EACH 200 HOURS EACH 100 HOURS EACH 50 HOURS 20. Cabin heat valves, doors and controls .................................................................................... 21. Starter, solenoid and electrical connections........................................................................... 22. Starter brushes, brush leads, commutator............................................................................. 23. Alternator and electrical connections ........................................ ..................................... 24. Alternator brushes, brush leads, commutator or slip ring. .................................... 7 25. Voltage regulator mounting and electrical leads .................................................................... 26. Magnetos (External) and electrical connections .................................................................... 27. M agneto timing....................................................................................................................... 8 28. Carburetor and drain plug (Refer to Service Letter (SE73-13.) ............................................. 29. Firew all................................................................................................................................... 30. Engine cowl flaps and controls............................................................................................... 31. E ng ine cow lin g ....................................................................................................................... 32. Cowl flap hinges and hinge pins (Refer to Service Letter SE71-27.).................. ............ 33. Carburetor throttle arm attachment (Refer to Service Letter SE71-17.) ................................ 34. Alternator support bracket for security (Refer to Service Letter SE71-42.)............................ FUEL SYSTEM 1. Fuel strainer, drain valve and control, fuel cell vents, caps and placards.............................. 2. Fuel strainer screen and bowl ................................................................................................ 3. Drain fuel and check cell interior, attachment and outlet screens.......................................... 5 4. Fuel cells and sump drains..................................................................................................... 5. Fuel selector valve and placards (Refer to Service Letter SE74-1.) ........................ ........... 6. E ng ine prim er ......................................................................................................................... 7. Fuel quantity indicators and transmitters................................................................................ 8. Perform a fuel quantity indicating system operational test. Refer to 16 Section 15 for detailed accomplishment instructions ............................................................ LANDING GEAR 1. Brake fluid, lines and hose, linings, discs, brake assemblies and master cylinders ............... 2. Main gear wheels ........................................ ..................................... 3. W heel bearings........................................................................................................................ 9 4. Main gear springs .................................................................................................................... Revision 4 2-21 Mar 1/2004 © Cessna Aircraft Company SPECIAL INSPECTION ITEM EACH 200 HOURS EACH 100 HOURS EACH 50 HOURS Tires . . . . . . . . . . . . . . Torque link lubrication ...................... Parking brake system .. . ................. Nose gear strut and shimmy dampener (service as required) .... Nose gear wheel . ... . . . . . ... ... .. .. .. . . Nose gear fork . . . . . . . . . . . . . . . . . . . . . . . . . Nose gear steering system .................... Park brake and toe brakes operational test ............ . . . . .. . 0 . . . . . . 0 0 . . . . . . 0 AIRFRAME 1. Aircraft exterior ............. 2. Aircraft structure (Refer to Service Letters SE72-3 and SE72-29.) . 3. Windows, windshield, doors and seals ....... 4. Seat stops, seat rails, upholstery, structure and mounting . 5. Seat belts and shoulder harnesses .. . . ......... 6. Control column bearings, pulleys, cables and turnbuckles . . . . 7. Control lock, control wheel and control column mechanism . .... . . . . . . 0 0 0 . . . . . . . . 0 0 0 Instruments and markings .................... Gyros central air filter ..................... Magnetic compass compensation ................. Instrument wiring and plumbing ..... .. ....... Instrument panel, shock mounts, ground straps, cover, decals and la Defrosting, heating and ventilating systems and controls ...... Cabin upholstery, trim, sunvisors and ash trays.......... Area beneath floor, lines, hose, wires and control cables .. Lights, switches, circuit breakers, fuses and spare fuses ..... . . . . . 10 5 beling ..... . . . . . . . . Exterior lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Pitot and static systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . Stall warning unit and pitot heater ... . .. . ........ ...... Radios, radio controls, avionics and flight instruments .............. 2-22 Change 3 5. 6. 7. 8. 9. 10. 11. 12. I 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18. 19. 20. SPECIAL INSPECTION ITEM EACH 200 HOURS EACH 100 HOURS EACH 50 HOURS 21. Antennas and cables ............................. . 22. Battery, battery box and battery cables .. . . .............. . . 23. Battery electrolyte ............................ 11 24. Emergency locator transmitter .................. .. 12 25. Oxygen system ......... ................ . 26. Oxygen supply, masks and hose ......................... 13 CONTROL SYSTEMS In addition to the items listed below, always check for correct direction of movement, correct travel and correct cable tension. 1. Cables, terminals, pulleys, pulley brackets, cable guards, turnbuckles and fairleads . 2. Chains, terminals, sprockets and chain guards .................. . 3. Trim control wheels, indicators, actuator and bungee ............... . 4. Travel stops .................................. . 5. Decals and labeling ... ............................ 0 6. Flap control switch, flap rollers and flap position indicator ............. . 7. Flap motor, transmission, limit switches, structure, linkage, bellcranks, etc. 8. Flap actuator jackscrew threads ......................... 14 9. Elevators, trim tab, hinges and push-pull tube ................. 10. Elevator trim tab actuator lubrication and tab free-play inspection ......... 15 11. Rudder pedal assemblies and linkage ....................... 12. External skins of control surfaces and tabs .................... 13. Internal structure of control surfaces .. .................... 14. Balance weight attachment ................... . Change 1 2-23 CESSNA AIRCRAFT COMPANY MODEL 182 AND SKYLANE SERIES SERVICE MANUAL SPECIAL INSPECTION ITEMS 1. First 25 hours; (refill with straight mineral oil and use until a total of 50 hours has accumulated or oil consumption has stabilized) then change to ashless dispersant oil. Change oil each 50 hours if engine is NOT equipped with external oil filter; if equipped with an external oil filter, change filter element at each 50 hours and oil at each 100 hours or every six months. 2. Clean filter per paragraph 2-22. Replace as required. 3. Replace engine compartment hoses (Cessna-installed only) every 5 years or at engine overhaul whichever occurs first. This does not include drain hoses. Hoses which are beyond these limits and are in a serviceable condition, must be placed on order immediately and then replaced within 120 days after receiving the new hose(s) from Cessna. Replace drain hoses on condition. Engine flexible hoses, (Continental Motors installed) refer to Continental Motors Maintenance Manual and Continental Motors Engine Service Bulletins. 4. General inspection every 50 hours. Refer to Section 11 for 100 hour inspection. 5. Each 1000 hours, or to coincide with engine overhaul. 6. Each 50 hours for general condition and freedom of movement. These controls are not repairable. Replace as required at each engine overhaul. 7. Each 500 hours. 8. Internal timing and magneto-to-engine timing limits are described in detail in Section 11. 9. First 100 hours and each 500 hours thereafter. More often if operated under prevailing wet or dusty conditions. 10. Replace each 500 hours. 11. Check electrolyte level and clean battery compartment each 50 hours or 30 days. 12. Refer to Section 16 of this Service Manual. 13. Inspect masks, hose fittings for condition, routing and support. Test, operate and check for leaks. 14. Refer to paragraph 2-44 for detailed instructions for various serial ranges. 15. Lubrication of the actuator is required each 1000 hours and/or 3 years, whichever comes first. Refer to Figure 2-4 for grease specification. NOTE: Refer to Section 9 of this manual for free-play limits, inspection, replacement and/or repair. 16. Fuel quantity indicating system operational test is required every 12 months. Refer to Section 15 for detailed accomplishment instructions. NOTE: A high time inspection is merely a 100-hour inspection with the addition of an engine overhaul. Refer to Teledyne Continental Service Information Letter SIL98-9, or latest revision, for recommended time between overhaul for 0-470 series engines. At the time of overhaul, engine accessories should be overhauled. Propeller overhaul should coincide with engine overhaul, but intervals between overhauls of the propeller shall not exceed 1200 hours, except as stipulated in current issues of the McCauley Accessory Division Service Information Summary and currently effective Service Manuals, Bulletins and Letters. 2-24 Revision 4 ©Cessna Aircraft Company Mar 1/2004 CESSNA AIRCRAFT COMPANY MODEL 182 AND SKYLANE SERIES SERVICE MANUAL 2-46. COMPONENT TIME LIMITS 1. General A. Most components listed throughout Section 2 should be inspected as detailed elsewhere in this section and repaired, overhauled or replaced as required. Some components, however, have a time or life limit, and must be overhauled or replaced on or before the specified time limit. NOTE: The terms overhaul and replacement as used within this section are defined as follows: Overhaul - Item may be overhauled as defined in CFR 43.2 or it can be replaced. Replacement - Item must be replaced with a new item or a serviceable item that is within its service life and time limits or has been rebuilt as defined in CFR 43.2. B. This section provides a list of items which must be overhauled or replaced at specific time limits. Table 1 lists those items which Cessna has mandated must be overhauled or replaced at specific time limits. Table 2 lists component time limits which have been established by a supplier to Cessna for the supplier's product. C. In addition to these limits, the components listed herein are also inspected at regular time intervals set forth in the Inspection Charts, and may require overhaul/replacement before the time limit is reached, based on service usage and inspection results. 2. Cessna established replacement Time Limits A. The following component time limits have been established by Cessna Aircraft Company. Table 1: Cessna-Established Replacement Time Limits COMPONENT REPLACEMENT OVERHAUL TIME Restraint Assembly Pilot Copilot 10 years NO And Passenger Seats Trim Tab Actuator 1,000 hours or 3 years, YES Whichever occurs first Vacuum System Filter 500 hours NO Vacuum System Hoses 10 years NO Pitot and Static System Hoses 10 years NO Vacuum Relief/Regulator Valve 500 hours NO Filter (If Installed) Engine Compartment Flexible Fluid- 10 years or engine overhaul, NO Carrying Teflon Hoses (Cessna- whichever occurs first Installed) Except Drain Hoses (Note 1) (Drain hoses are replaced on condition) Revision 4 2-25 Mar 1/2004 © Cessna Aircraft Company CESSNA AIRCRAFT COMPANY MODEL 182 AND SKYLANE SERIES SERVICE MANUAL COMPONENT REPLACEMENT TIME OVERHAUL Engine Compartment Flexible Fluid- Carrying Rubber Hoses (Cessna- Installed) Except Drain Hoses (Drain hoses are replaced on condition) Engine Air Filter Engine Mixture, Throttle, and Propeller Controls Oxygen Bottle - Lightweight Steel (ICC-3HT, DOT-3HT) Oxygen Bottle - Composite (DOT-E8162) Engine-Driven Dry Vacuum Pump Drive Coupling (Not lubricated with engine oil) Engine-Driven Dry Vacuum Pump (Not lubricated with engine oil) Standby Dry Vacuum Pump 5 years or engine overhaul, whichever occurs first (Note 1) 500 hours or 36 months, whichever occurs first (Note 9) At engine TBO Every 24 years or 4380 cycles, whichever occurs first Every 15 years 6 Years or at vacuum pump replacement, whichever occurs first 500 hours (Note 10) 500 hours or 10 Years, whichever occurs first (Note 10) 3. Supplier-Established Replacement Time Limits A. The following component time limits have been established by specific suppliers and are reproduced as follows: Table 2: Supplier-Established Replacement Time Limits COMPONENT REPLACEMENT TIME OVERHAUL ELT Battery Vacuum Manifold Magnetos Engine Engine Flexible Hoses (TCM-Installed) Auxiliary Electric Fuel Pump Propeller (Note 3) (Note 4) (Note 5) (Note 6) (Note 2) (Note 7) (Note 8) 2-26 © Cessna Aircraft Company NO NO NO NO NO NO NO NO NO NO YES YES NO YES YES Revision 4 Mar 1/2004 CESSNA AIRCRAFT COMPANY MODEL 182 AND SKYLANE SERIES SERVICE MANUAL NOTES: NOTE 1: This life limit is not intended to allow flexible fluid-carrying Teflon or rubber hoses in a deteriorated or damaged condition to remain in service. Replace engine compartment flexible Teflon (AE3663819BXXXX series hose) fluid-carrying hoses (Cessna-installed only) every ten years or at engine overhaul, whichever occurs first. Replace engine compartment flexible rubber fluid- carrying hoses (Cessna-installed only) every five years or at engine overhaul, whichever occurs first (this does not include drain hoses). Hoses which are beyond these limits and are in a serviceable condition must be placed on order immediately and then be replaced within 120 days after receiving the new hose from Cessna. NOTE 2: For TCM engines, refer to Teledyne Continental Service Bulletin SB97-6, or latest revision. NOTE 3: Refer to FAR 91.207 for battery replacement time limits. NOTE 4: Refer to Airborne Air & Fuel Product Reference Memo No. 39, or latest revision, for replacement time limits. NOTE 5: For airplanes equipped with Slick magnetos, refer to Slick Service Bulletin SB2-80C, or latest revision, for time limits. For airplanes equipped with TCM/Bendix magnetos, refer to Teledyne Continental Motors Service Bulletin No. 643, or latest revision, for time limits. NOTE 6: Refer to Teledyne Continental Service Information Letter SIL98-9, or latest revision, for time limits. NOTE 7: Refer to Cessna Service Bulletin SEB94-7 Revision 1/Dukes Inc. Service Bulletin No. 0003, or latest revision. NOTE 8: Refer to the applicable McCauley Service Bulletins and Overhaul Manual for replacement and overhaul information. NOTE 9: The Air Filter may be cleaned. Refer to Section 2 of this service manual and for ai