CENTURION SERIES SERVICE MANUAL

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0 17-38 thru 17-48.............. 4 18-1.................................. 2 18-2 thru 18-3 .................. 0 18-4.................................. 1 18-5.................................. 3 18-6.................................. 1 Revision 5 Jul 1/2004 Page No. Revision No. CESSNA AIRCRAFT COMPANY CENTURION SERIES SERVICE MANUAL LIST OF EFFECTIVITY PAGES (CONT.) Page Revision No. No. 18-7 ................................... 4 18-8 thru 18-10 ................. 0 18-11 .................................. 4 18-12 thru 18-28 ................ 0 19-1 thru 19-2 ................... 4 20-1 ................................... 4 20-2 thru 20-42 ................. 0 20-43................................. 1 20-44................................. 4 20-45................................. 3 20-46................................. 4 20-47................................. 1 20-48................................. 4 20-49................................. 1 20-50................................. 4 20-51 ................................. 1 20-52................................. 4 20-53 thru 20-56 ............... 1 20-56A thru 20-56B ........4 20-57................................. 3 20-58................................. 1 20-59 thru 20-62B Blank .. 4 20-63 ................................ 1 20-64................................. 4 20-65................................. 1 20-66................................. 3 20-66A thru 20-67............. 4 20-68................................. 1 20-69................................. 3 20-70................................. 1 20-71 thru 20-74.... ......... 4 20-74A thru 20-75............ 3 20-76................................. 4 20-77................................. 3 20-78................................. 1 20-79................................. 4 20-80 thru 20-81 ............... 1 20-82 thru 20-82B Blank.. 4 20-83................................. 1 20-84 thru 20-90 Blank..... 4 Revision 5 C /(D Blank) Jul 1/2004 © Cessna Aircraft Company TABLE OF CONTENTS SECTION 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 12A. 13. 14. 15. 16. 17. 18. 19. GENERAL DESCRIPTION .... .... .. .......... GROUND HANDLING. SERVICING. CLEANING. LUBRICATION AND INSPECTION ... FUSELAGE .......... WINGS AND EMPENNAGE ............. LANDING GEAR. BRAKES AND HYDRAULIC SYSTEM AILERON CONTROL SYSTEM ........... WING FLAP CONTROL SYSTEM .......... ELEVATOR CONTROL SYSTEM .......... ELEVATOR TRIM TAB CONTROL SYSTEM ..... RUDDER CONTROL SYSTEM ............ RUDDER TRIM CONTROL SYSTEM ......... ENGINE (NORMALLY ASPIRATED) ......... ENGINE (TURBOCHARGED) ............ FUEL SYSTEM . . . . . . . . . . . . . . . . . . PROPELLERS AND PROPELLER GOVERNORS . . UTILITY SYSYEMS . ... .... .. . . . . . . INSTRUMENTS AND INSTRUMENT SYSTEMS .... ELECTRICAL SYSTEMS .............. STRUCTURAL REPAIR .............. EXTERIOR PAINTING ............... 20. WIRING DIAGRAMS . Page 1-1 2-1 3-1 7-1 8-1 . . 9-1 10-i 11-1 . 12-1 .12A - . 13-1 . 14-1 15-1 . 16-1 . 17-1 18-1 . 19-1 20-1 Change 4 i CESSNA AIRCRAFT COMPANY CENTURION SERIES SERVICE MANUAL 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 210-Series aircraft. This includes the Models 210 and T210, which is identical to the Model 210 except that it is turbocharged. Besides serving as a reference for the experienced mechanic, this book also covers step-by-step procedures for the less experienced person. This manual should be kept in a handy place for ready reference. If properly used, it will better enable the mechanic to maintain Cessna 210-Series aircraft and thereby establish a reputation for reliable service. 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 ii Revision 5 © Cessna Aircraft Company Jul 1/2004 CESSNA AIRCRAFT COMPANY CENTURION 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 CENTURION TURBO CENTURION CENTURION CENTURION II TURBO CENTURION TURBO CENTURION II CENTURION CENTURION II TURBO CENTURION TURBO CENTURION II CENTURION CENTURION II TURBO CENTURION TURBO CENTURION II CENTURION CENTURION II TURBO CENTURION TURBO CENTURION II MODEL YEAR 1970 1970 1971 1971 1971 1971 1972 1972 1972 1972 1973 1973 1973 1973 1974 1974 1974 1974 MODEL 210K T210K 210K 210K T210K T210K 210L 210L T210L T210L 210L 210L T210L T210L 210L 210L T210L T210L BEGINNING SERIAL NUMBER 21059200 21059200 21059352 21059352 21059352 21059352 21059503 21059503 21059503 21059503 21059720 21059720 21059720 21059720 21060090 21060090 21060090 21060090 ENDING SERIAL NUMBER 21059351 21059351 21059502 21059502 21059502 21059502 21059719 21059719 21059719 21059719 21060089 21060089 21060089 21060089 21060539 21060539 21060539 21060539 CENTURION CENTURION II TURBO CENTURION TURBO CENTURION II CENTURION CENTURION II TURBO CENTURION TURBO CENTURION II 1975 1975 1975 1975 1976 1976 1976 1976 210L 210L T210L T210L 210L 210L T210L T210L 21060540 21060540 21060540 21060540 21061040 21061040 21061040 21061040 21061039 21061039 21061039 21061039 21061573 21061573 21061573 21061573 3. Coverage and Format. A. The Cessna Model 210-Series Service Manual has been prepared to help maintenance personnel in servicing and maintaining the Model 210-Series. This manual provides the necessary information required to enable the mechanic to service, inspect, troubleshoot, remove and replace components or repair systems. Revision 5 Jul 1/2004 © Cessna Aircraft Company iii I CESSNA AIRCRAFT COMPANY CENTURION SERIES SERVICE MANUAL 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, aerofiche or Compact Disc (CD/ROM). The CD ROM contains the Service Manuals, Illustrated Parts Catalogs and Avionics Manuals. iv Revision 5 © Cessna Aircraft Company Jul 1/2004 SECTION 1 GENERAL DESCRIPTION TABLE OF CONTENTS Page GENERAL DESCRIPTION ...... ..... 1-1 Aircraft Specifications ..... . ... 1-1 Model 210-Series .. . ........ 1-1 Stations ................. 1-1 Description .... . . . ..... 1-1 Torque Values ... .......... 1-1 1-1. GENERAL DESCRIPTION. 1-4. AIRCRAFT SPECIFICATIONS. Leading parti- culars of these aircraft, with dimensions based on 1-2. MODEL 210-SERIES. gross weight, are given in figure 1-1. If these dimen- sions are used for constructing a hangar or computing 1-3. DESCRIPTION. The Cessna Model 210-Series clearances, remember that such factors as nose gear aircraft, described in this manual, are single-engine, strut inflation, tire pressures, tire sizes, and load high-wing monoplanes of all-metal, semimonocoque distribution may result in some dimensions that are construction. Wings are full cantilever, with a considerably different from those listed. sealed section which forms an integral fuel bay area in each wing. The fully-retractable tricycle landing 1-5. STATIONS. A station diagram is shown in fig- gear consists of tubular spring-steel main gear struts ure 1-2 to assist in locating equipment when a written and a steerable nose gear with an air/hydraulic fluid description is inadequate or impractical. shock strut. Six-place seating is standard. The Model 210 is powered by a six-cylinder, horizontally 1-6. TORQUE VALUES. A chart of recommended opposed, air-cooled, fuel injection Continental engine, nut torque values is shown in figure 1-3. These tor- driving an all-metal, constant-speed propeller. The que values are recommended for all installation pro- Model T210 engine is turbocharged. cedures contained in this manual, except where other values are stipulated. They are not to be used for checking tightness of installed parts during service. 1-1 210 & T210 GROSS WEIGHT .. ...... ................ 3800 lb FUEL CAPACITY Total ....... .................... 90 gal Usable ........................... 89 gal OIL CAPACITY (Detergent Only) ................ . 10 qt With External Oil Filter and All Turbocharged Engines ................. 11 qt ENGINE MODEL 210 ........................... .CONTINENTAL 10-520 SERIES T210 .......................... . CONTINENTAL TSIO-520 SERIES PROPELLER (Constant-Speed) (Two Blades). . .................. . .82" McCAULEY (Three Blades) . .... .... . ......... ... . 80" McCAULEY LANDING GEAR (Retractable, Hydraulically-Actuated) .... .. . Tricycle MAIN WHEEL TIRES .............. .. . . . . 6.00 x 6, 8-Ply Rating Pressure .......................... 55 psi NOSE WHEEL TIRE. ................... . .. 5.00 x 5, 6-Ply Rating Pressure ...... 50 psi NOSE GEAR STRUT PRESSURE (Strut Extended) ... ... . 90 psi WHEEL ALIGNMENT Camber ................... ........ 4 ° 1 1 30' Toe-in. .................. .. . . 0" to .06" AILERON TRAVEL Up . . . . . . . . . . . . . . . . . . . . . . . . .... . 20 ° 2 Down ........................... . 15 ° 2° WING FLAP TRAVEL (Electrically-Actuated) ............ t0° to 30°, 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 Up ............................. 23° 1 Down . .............. 17° 1° ELEVATOR TRIM TAB TRAVEL Up . . . . . . . . . . . . . . . . . . . . . .... . .. 25 ° 1° Down . . . . . . . . . . . . . . . . . . . . . . . . . . .. 100 1° PRINCIPAL DIMENSIONS Wing Span ................... ....... 36'9" Tail Span ............ ...... ......... 13' Length ............. ............... 28'-1 3/4" Fin Height (Maximum with Nose Gear Depressed and Flashing Beacon Installed on Fin) .............. 9'5 Track Width . ............ ......... . 8'8" BATTERY LOCATION ................. . .. . .Left Side of Firewall Figure 1-1. Aircraft Specifications Change 4 25.25 I 40.00 54. 00 3 . 7 O ^-".8 124.0 3.8 70.1 112 0 152.2 20900 18 0 90.0 138.0 180.6 8.1 *67. 98.0 109.6* 166.4 194.8 230.8 0.0 44.0 55.6 * 106.C. *124.6 77.0 * INDICATES CANTED BULKHEAD Figure 1-2. Reference Stations Change 4 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 TORQUE 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 3 SECTION 2 GROUND HANDLING. SERVICING. CLEANING. LUBRICATION AND INSPECTION TABLE OF CONTENTS Page GROUND HANDLING ............ 2-1 Nose Gear Shimmy Dampener ...... 2-8 Towing ................ 2-1 Hydraulic Brake Systems ....... . 2-8 Hoisting ................ 2-1 Hydraulic Reservoir .......... 2-8 Jacking ................ 2-1 Hydraulic Filter . .......... . 2-8 Parking ................ 2-2 Hydraulic Fluid Sampling and Tie-Down ............... 2-2 Contamination ............ 2-8 Flyable Storage ............ 2-2 Oxygen System ............ . 2-9 Returning Aircraft to Service ..... . 2-2 Face Masks .............. 2-9 Temporary Storage ....... ....... 2-2 CLEANING .... ........... . 2-10 Inspection During Storage ........ 2-4A Upholstery and Interior .... ..... 2-10 Returning Aircraft to Service ..... . 2-4A Plastic Trim .......... ... . 2-10 Indefinite Storage .......... .. 2-4A Windshield and Windows ........ 2-10 Inspection During Storage ........ 2-5 Aluminum Surfaces .......... 2-10 Returning Aircraft to Service ...... 2-5 Painted Surfaces ............ 2-10 Leveling. ............... 2-6 Engine Compartment .......... 2-10 SERVICING ................ 2-6 Propellers ............. . 2-10 Fuel Tanks . ............. 2-6 Wheels ................ 2-11 Fuel Drains .............. 2-6 Landing Gear and Door Manifold Solenoids 2-11 Engine Oil .............. ... . 2-6 LUBRICATION .......... ... . 2-11 Engine Induction Air Filters ....... 2-7 Nose Gear Torque Links ........ 2-11 Vacuum System Air Filters ...... . 2-7 Tachometer Drive Shaft ........ 2-11 Battery ............. ......... 2-7 Wheel Bearing Lubrication ...... . 2-11 Tires ........ ........ . 2-7 Wing Flap Actuator ......... . 2-11 Nose Gear Strut ............ 2-7 Rod End Bearings .............. 2-11 INSPECTION ............... 2-20 2-1. GROUND HANDLING. 2-3. HOISTING. The aircraft may be hoisted with a hoist of two-ton capacity, either by using hoisting 2-2. TOWING. Moving the aircraft by hand is ac- rings (optional equipment) or by using suitable slings. complished by using the landing gear struts as push The front sling should be hooked to the engine lifting points. A tow bar attached to the nose gear should be eye, and the aft sling should be positioned around the used for steering and maneuvering the aircraft. fuselage at the first bulkhead forward of the leading When no tow bar is available, press down at the hori- edge of the stabilizer. If the optional hoisting rings zontal stabilizer front spar, adjacent to the fuselage, are used, a minimum cable length of 60 inches for to raise the nose wheel off the ground. With the nose each cable is required to prevent bending of the eye- wheel clear of the ground, the aircraft can be turned bolt type hoisting rings. If desired, a spreader jig by pivoting it about the main wheels. may be fabricated to apply vertical force to the eye- bolts. CAUTION---~ ~2-4. JACKING. Refer to figure 2-2 for jacking pro- When towing the aircraft, never turn the nose cedures. wheel more than 35 degrees either side of center or the nose gear will be damaged. Do not push on control surfaces or outboard em- pennage surfaces. When pushing on the tail- cone, always apply pressure at a bulkhead to avoid buckling the skin. Change 4 2-1 TOW BAR: PART NUMBER 0501019-1, IS AVAILABLE FROM THE CESSNA SERVICE PARTS CENTER. Figure 2-1. Tow Bar iCAUTION NOTE When using the landing gear strut jack pad, The aircraft is delivered from Cessna with flexibility of the gear strut will cause the rrsi reeive irraf n a Corrosion Preventive Aircraft Engine Oil main wheel to slide inboard as the wheel is main wheel to slide inboard as the wheel is (Military Specification MIL-C-6529, Type II raised, tilting the jack. The jack must then be lowered for a second jacking operation. T aviation grade straight mineral oil and a Jacking both wheels simultaneously with corrosion preventive compound. This engine corrosion preventive compound. This engine landing gear strut jack pad is not recom- c p n compound. Ti engine lamending gear strut jack pad is not reco- oil should be used for the first 25 hours of mended. engine operation. Refer to paragraph 2-20 for oil changes during the first 50 hours 2-5. PARKING. Parking precautions depend prin- of engine operation. cipally on local conditions. As a general precaution, cipaly on local conditions. As a general precaution, During the 30 day non-operational storage or the first it is wise to set the parking brake or chock the wheels, and install the control lock. In severe 25 hours of intermittent engine operation, the propel- weatheels, and high nst, te down the air- ler shall be rotated through five revolutions every weather, and high wind conditions, tie down the air- craft as outlined in paragraph 2-6 if a hangar is not seventh day, without running the engine. If the air- .^available. *craft is stored outside, tie it down in accordance with paragraph 2-6. In addition, the pitot tube, static 2-6. TIE-DOWN should be accomplished in antici- air vents, air vents, openings in the engine cowling, pation of high winds. Tie-down aircraft as follows: and other similar openings shall have protective a. Tie ropes or chains to the wing tie-down fittings covers installed to prevent entry of foreign material. located on the underside of each wing. Secure the After 30 days, aircraft should be flown for 30 minutes opposite ends of the ropes or chains to ground an- or ground run-up until oil has reached operating chors. temperature. b. Secure a rope (no chains) to the upper TRN A RAFT T Aft trunnion of the nose gear and secure opposite end of 28 U G AT TO S After rope to a ground anchor. flyable storage, returning the aircraft to service is rope to a ground anchor. c. Secure the middle of a rope to tail tie-down ring. accomplished by performing a thorough preflight Pull each end of rope away at 45-degree angle and inspection. At the end of the first 25 hours of engine secure to ground anchors at each side of tail operation, drain engine oil, clean oil screens and d. Install control lock on pilot's control column if change external oil filter element Service engine available; if control lock is not available, tie pilot's with correct grade and quantity of engine oil Refer control wheel back with front seat belt. to figure 2-4 and paragraph 2-20 for correct grade of engine oil. e. These aircraft are equipped with a spring-loaded steering bungee which affords protection against nor- 2-9. TEMPORARY STORAGE. Temporary storage mal wind gusts. However, if extremely high wind is defined as aircraft in a non-operational status for gusts are anticipated, additional external locks may a maximum of 90 days. The aircraft is constructed be installed, of corrosion-resistant alclad aluminum, which will last indefinitely under normal conditions if kept 2-7. FLYABLE STORAGE. Flyable storage is de- clean. However, these alloys are subject to oxida- fined as a maximum of 30 days non-operational stor- tion. The first indication of corrosion on unpainted age and/or the first 25 hours of intermittent engine surfaces is in the form of white deposits or spots. operation. On painted surfaces, the paint is discolored or blis- tered. Storage in a dry hangar is essential to good preservation and should be procured, if possible. 2-2 Change 3 Cessna #1200028-1 Jack point (SEE NOTE 1) Jackk Any short jack of capable capacity ~~~(E2~~~) ~(SEE NOTE 1) (O Cessna #SE-767 Universal tail stand (SEE NOTE 2) Cessna #SE-576 (41-1/2" high) Universal jack stand (FOR USE WITH ITEM 2) (i)\ Cessna #1200031-1 Jack point (Thru 1971 Models) (SEE NOTE 3) q2-170 Basic jack Closed height: 69-1/2 inches; extended (2-109 Leg Extension height: 92" (Insert slide tube -2-70 Slide tube extension extension into basic jack) 1. Provisions are furnished on the bottom of each wing for installation of optional 1200028-1 jack points. 2. Weighted adjustable stand attaches to tie-down ring. Wing jack points are aft of the aircraft center-of-gravity. This causes the aircraft to be nose heavy when on jacks. Place additional weights (shot bags or sand bags) on the weighted tail stand to hold the tail down. In addition, the base of adjustable tail stand (SE767) is to be filled with concrete for additional weight as a safety factor. 3. Optional 1200031-1 jack point may be used to raise only one wheel. Do not use brake casting as a jack point. Beginning with 1972 Models, use jack point on bottom of step. 4. Items (1), (3), (4), (5) and (6) are available from the Cessna Service Parts Center. Figure 2-2. Jacking Details (Sheet 1 of 2) Change 1 2-3 JACKING AIRCRAFT 1. Lower the aircraft tail so that wing jack and stands can be placed at wing jack points. 2. Raise aircraft tail and attach tail stand to tail tie-down ring. BE SURE the tail stand weighs enough to keep the tail down under all conditions and that it is strong enough to support any weight that may be placed upon it. 3. Raise jacks evenly until desired height is reached. When jacking the aircraft, the main landing gear wheels must be a minimum of 16" above shop floor for landing gear retraction. 4. The jack point assembly may be used to raise only one main wheel. Do not use brake casting as a jack point. 5. The nose may be raised by weighting down the tail. Place weight on each side of stabilizer, next to fuselage. 6. Whenever the landing gear is to be operated in the shop, use the wing jack and tail jack points to raise the aircraft. 7. The aircraft may be hoisted as outlined in paragraph 2-3. REMOVING AIRCRAFT FROM JACKS 1. Place landing gear control handle in gear down position. 2. Operate ground hydraulic power source or aircraft emergency hydraulic hand pump until landing gear is down and locked, the green (DOWN) light is illuminated and landing gear control handle has tripped to down neutral. 3. Disconnect ground hydraulic power source and/or stow emergency hydraulic hand pump handle. 4. Ascertain that green (DOWN) light is illuminated; then place master switch in OFF position. 5. Lower jacks evenly until aircraft rests on the landing gear and remove wing jacks and tail stand. 6. Compress nose landing gear shock strut to static position. SHOP NOTES: Figure 2-2. Jacking Details (Sheet 2 of 2) 2-4 Change 1 Varying conditions will alter the measures of preser- 1. Apply preservative oil to the engine interior by vation, but under normal conditions in a dry hangar, spraying approximately two ounces of the preserva- and for storage periods not to exceed 90 days, the tive oil through the oil filler tube. following methods of treatment are suggested. m. Seal all engine openings exposed to the atmos- a. Fill fuel bays with correct grade of gasoline. phere, using suitable plugs or non-hygroscopic tape. b. Clean and wax aircraft thoroughly. Attach a red streamer at each point that a plug or c. Clean any oil or grease from tires, and coat tape is installed. tires with a tire preservative. Cover tires to pro- n. If the aircraft is to be stored outside, perform tect against grease or oil. the procedures outlined in paragraph 2-6. In addi- d. Either block up fuselage to relieve pressure on tion, the pitot tube, static source vents, air vents, tires or rotate wheels every 30 days to prevent flat openings in the engine cowling, and other similar spotting the tires. openings should have protective covers installed to e. Lubricate all airframe items and seal or cover prevent entry of foreign material. all openings which could allow moisture and/or dust o. Attach a warning placard to the propeller to the to enter. effect that the propeller shall not be moved while the engine is in storage. NOTE 2-10. INSPECTION DURING STORAGE. The aircraft battery serial number is recorded a. Inspect airframe for corrosion at least once a in the aircraft equipment list. To assure ac- month. Remove dust collections as frequently as curate warranty records, the battery should possible. Clean and wax aircraft as required. be reinstalled in the same aircraft from which b. Inspect the interior of at least one cylinder it was removed. If the battery is returned to through the spark plug hole for corrosion at least service in a different aircraft, appropriate once each month. record changes must be made and notification sent to the Cessna Claims Department. NOTE f. Remove battery and store in a cool, dry place; Do not move crankshaft when inspecting service battery periodically and charge as required. interior of cylinder for corrosion. NOTE c. If at the end of the 90 day period, the aircraft is to be continued in non-operational storage, repeat An engine treated in accordance with the fol- the procedural steps "g" thru "o" of paragraph 2-9. lowing may be considered being protected against normal atmospheric corrosion for a 2-11. RETURNING AIRCRAFT TO SERVICE. After period not to exceed 90 days. temporary storage, use the following procedure to return the aircraft to service. g. Disconnect spark plug leads and remove upper a. Remove aircraft from blocks. Check tires for and lower spark plugs from each cylinder. proper inflation. b. Check and install battery. NOTE c. Check that oil sump has proper grade and quan- tity of engine oil. The preservative oil must be Lubricating d. Service induction air filter and remove warning Oil-Contact and Volatile, Corrosion In- placard from propeller. hibited, MIL-L-46002, Grade 1, or equiva- e. Remove materials used to cover openings. lent. The following oils are approved for f. Remove, clean and gap spark plugs. spraying by Teledyne Continental Motors: g. While spark plugs are removed, rotate propeller Nucle Oil 105 - Daubert Chemicals Co., several revolutions to clear excess rust preventive 4700 So. Central Ave., Chicago, Illinois; oil from cylinders. Petratect VA-Pennsylvania Refining Co., h. Clean, gap and install spark plugs. Torque Butler, Pennsylvania, and Ferro-Gard plugs to value listed in Section 12 or 12A. 1009G-Ranco Laboratories, Inc., 3617 i. Check fuel strainer. Remove and clean filter Brownsville Road, Pittsburgh, Pennsylvania. screen, if necessary. Check fuel bays and fuel lines for moisture and sediment. Drain enough fuel to h. Using a portable pressure sprayer, spray pre- eliminate moisture and sediment. servative oil through the upper spark plug hole of j. Perform a thorough pre-flight inspection, then each cylinder with the piston in a down position. Ro- start and warm-up engine. tate crankshaft as each pair of cylinders is sprayed. i. After completing step "h, " rotate crankshaft so 2-12. INDEFINITE STORAGE. Indefinite storage is that no piston is at a top position. If the aircraft is defined as aircraft in a non-operational status for an to be stored outside, stop two-bladed propeller so indefinite period of time. Engines treated in accor- that blades are as near horizontal as possible to pro- dance with the following may be considered protected vide maximum clearance with passing aircraft. against normal atmospheric corrosion, provided the j. Again, spray each cylinder without moving the procedures outlined in paragraph 2-13 are performed crankshaft, to thoroughly cover all interior surfaces at the intervals specified. of the cylinder above the piston. k. Install spark plugs and connect spark plug leads. Change 4 2-4A/(2-4B blank) a. Operate engine until oil temperature reaches NOTE normal operating range. Drain engine oil sump and reinstall drain plug. Attach a red streamer to each place plugs or b. Fill oil sump to normal operating capacity with tape is installed. Either attach red streamers corrosion preventive mixture which has been thor- outside of the sealed area with tape or to the oughly mixed and pre-heated to a minimum of 221°F inside of the sealed area with safety wire to at the time it is added to the engine. prevent wicking of moisture into the sealed area. NOTE n. Drain corrosion-preventive mixture from engine Corrosion preventive mixture consists of one sump and reinstall drain plug. part compound MIL-C-6529, Type I, mixed with three parts new lubricating oil of the NOTE grade recommended for service. Continental Motors Corporation recommends Cosmoline The corrosion-preventive mixture is harmful No. 1223, supplied by E. F. Houghton & Co., to paint and should be wiped from painted sur- 305 W. LeHigh Avenue, Philadelphia, Pa. faces immediately. During all spraying operation corrosion mix- ture is pre-heated to 221 ° to 250°F. o. Attach a warning placard on the throttle control knob. to the effect that the engine contains no lubri- c. Immediately after filling the oil sump with cor- eating oil. Placard the propeller to the effect that it rosion preventative mixture, fly the aircraft for a should not he moved while the engine is in storage. period of time not to exceed a maximum of 30 min- p. Prepare airframe for storage as outlined in utes. paragraph 2-9 thru step "f. d. With engine operating at 1200 to 1500 rpm and induction air filter removed, spray corrosion pre- NOTE ventive mixture into induction airbox, at the rate of one-half gallon per minute, until heavy smoke As an alternate method of indefinite storage. comes from exhaust stack, then increase the spray the aircraft may be serviced in accordance until the engine is stopped. with paragraph 2-9 providing the aircraft is run-up at maximum intervals of 60 days and then reserviced per paragraph 2-9. ICAUTION Injecting corrosion-preventive mixture too 2-13. INSPECTION DURING STORAGE. Aircraft in fast can cause a hydrostatic lock. an indefinite storage shall be inspected as follows: a. Inspect cylinder protex plugs each 7 days. e. Do not rotate propeller after completing step b. Change protex plugs if their color indicates an "d. " unsafe condition. f. Remove all spark plugs and spray corrosion- c. If the dehydrator plugs have changed color in one preventive mixture, which as been pre-heated to half of the cylinders, all desiccant material in the 221 ° to 250°F, into all spark plug holes to thorough- engine shall be replaced with new material. ly cover interior surfaces of cylinders. d. Every 6 months respray the cylinder interiors g. Install lower spark plugs or install solid plugs, with corrosion-preventive mixture. and install dehydrator plugs in upper spark plug holes. Be sure that dehydrator plugs are blue in NOTE color when installed. h. Cover spark plug lead terminals with shipping Before spraying, inspect the interior of one plugs (AN4060-1) or other suitable covers. cylinder for corrosion through the spark i. With throttle in full open position, place a bag plug hole and remove at least one rocker box of desiccant in the induction air intake and seal cover and inspect the valve mechanism. opening with moisture resistant paper and tape. j. Place a bag of desiccant in the exhaust tail- 2-14. RETURNING AIRCRAFT TO SERVICE. pipe(s) and seal openings with moisture resistant After indefinite storage, use the following procedure tape. to return the aircraft to service. k. Seal cold air inlet to the heater muff with mois- a. Remove aircraft from blocks and check tires for ture resistant tape. correct inflation. Check for correct nose gear strut 1. Seal engine breather by inserting a protex plug inflation. in the breather hose and clamping in place. b. Check battery and install. m. Seal all other engine openings exposed to atmos- c. Remove all materials used to seal and cover phere using suitable plugs or non-hygroscopic tape. openings. d. Remove warning placards posted at throttle and propeller. e. Remove and clean engine oil screen, then re- install and safety. On aircraft that are equipped with an external oil filter, install new filter element. f. Remove oil sump drain plug and drain sump. Install and safety drain plug. 2-5 NOTE a level position as possible when checking the engine oil, so that a true reading is obtained. Engine oil The corrosion-preventive mixture will mix should be drained while the engine is still hot, and the with the engine lubricating oil, so flushing nose of the aircraft should be raised slightly for more the oil system is not necessary. Draining positive draining of any sludge which may have col- the oil sump will remove enough of the cor- lected in the engine oil sump. Engine oil should be rosion-preventive mixture. changed every six months, even though less than the specific hours have accumulated. Reduce these inter- g. Service and install the induction air filter. vals for prolonged operations in dusty areas, in cold h. Remove dehydrator plugs and spark plugs or climates where sludging conditions exist, or where plugs installed in spark plug holes and rotate pro- short flights and long idle periods are encountered, peller by hand several revolutions to clear corrosion- which cause sludging conditions. Always change oil preventive mixture from cylinders, and clean oil screens whenever oil on the dipstick i. Clean, gap and install spark plugs. Torque appears dirty. Ashless dispersant oil, conforming plugs to value listed in Section 12 or 12A. to Continental Motors Specification No. MHS-24A, j. Check fuel strainer. Remove and clean filter shall be used in these engines. Multi-Viscosity oil screen. Check fuel tanks and fuel lines for moisture may be used to extend the operating temperature and sediment, and drain enough fuel to eliminate. range, improve cold engine starting and lubrication k. Perform a thorough pre-flight inspection, then of the engine during the critical warm-up period, start and warm-up engine. thus permitting flight through wider ranges of climate 1. Thoroughly clean aircraft and flight test air- change without the necessity of changing oiL The craft. inulti-viscosity grades are recommended for aircraft engines subjected to wide variations in ambient air 2-15. LEVELING. Longitudinally leveling of the air- temperatures when cold starting of the engine must craft is accomplished by backing out the two screws be accomplished at temperatures below 30°F. on the left side of the fuselage and then placing a level across the screws. Corresponding points on either NOTE the upper or lower main door sills may be used to level the aircraft laterally. New or newly-overhauled engines should be operated on aviation grade straight mineral 2-16. SERVICING. oil until the first oil change. The aircraft is delivered from Cessna with straight 2-17. Servicing requirements are shown in the mineral oil (MIL-C-6529, Type I RUST Servicing Chart (figure 2-4). The following para- BAN. ) If oil must be added during the first graphs supplement figure 2-4 by adding details not 25 hours, use only aviation grade straight included in the chart. mineral oil conforming to Specification MIL-6082. After the first 25 hours of 2-18. FUEL TANKS. An area of each wing is seal- operation, drain engine oil sump and clean ed to form an integral fuel tank. Recommended fuel both the oil suction strainer and the oil grade is listed in figure 2-4, and fuel capacities are pressure screen. If an optional oil filter given in figure 1-1. is installed, change filter element at this time. Refill sump with straight mineral 2-19. FUEL DRAINS are located at various points oil and use until a total of 50 hours have in the fuel system to provide drainage of water and accumulated or oil consumption has stabi- sediment. Refer to Section 13 for location of drain lized, then change to ashless dispersant oil. plugs and valves. The strainer drain control is ad- jacent to the engine oil dipstick. Access to the con- When changing engine oil, remove and clean oil trol is through the cowling door on the left side of the screens, or install a new filter element on aircraft upper cowl. Also, during daily inspection of the equipped with an external oil filter. To drain oil, fuel strainer, if water is found in the fuel strainer, proceed as follows: there is a possibility that the wing tank sumps, fuel a. Operate engine until oil temperature is at nor- lines, and fuel reservoir tanks contain water. There- mal operating temperature. fore, all drain plugs or valves should be removed and b. Remove oil drain plug from engine sump and al- all water drained from the fuel system. On aircraft low oil to drain into a container. equipped with drain valves, to activate the drain valves c. After engine oil has drained, install and safety for fuel sampling, place cup up to valve and depress drain plug. valve with rod protruding from cup. (Refer to figure d. Remove and clean oil screen. 13-2. ) e. Service engine with correct quantity and grade of engine oil. 2-20. ENGINE OIL. Check engine lubricating oil with the dipstick five to ten minutes after the engine has been stopped. The aircraft should be in as near 2-6 Change 4 NOTE filter may have sharp or broken edges in the filtering panels which would allow unfiltered Refer to inspection charts for intervals for air to enter the induction system. Any filter changing oil and filter elements. Refer to that appears doubtful should be replaced. figure 2-4 for correct grade of engine oil and refer to figure 1-1 for correct capacities. d. After washing, rinse filter with clear water un- til rinse water runs clear from filter. Allow water to drain from filter and dry with compressed air (not over 100 psi). 2-21. ENGINE INDUCTION AIR FILTERS keep dust NOTE and dirt from entering the induction system. Dust entering the intake system is probably the greatest The filtering panels of the filter may become single cause of early engine wear; therefore, the val- distorted when wet, but they will return to ue of maintaining the induction air filter in good clean their original shape when dry. condition can never be overstressed. The frequency with which the filter should be removed and cleaned e. Be sure induction air box and air inlet ducts to will be determined primarily by aircraft operating the engine are clean, inspect filter and install new conditions. Some operators prefer to hold a spare filter if old filter is damaged. filter(s) at their home base of operation so that a f. install filter as outlined in Section 12 and 12A. clean filter(s) is always readily available for use. Under extreme dusty conditions, daily maintenance 2-22. VACUUM SYSTEM AIR FILTER. The vacuum of the filter is recommended. A dry type filter is system central air filter keeps dust and dirt from used on the aircraft, entering the vacuum operated instrument. Inspect the filter element every 200 hours for damage. Change NOTE the central air filter element every 500 hours of operating time and whenever the suction gage reading Model T210 has one filter located at the up- drops below 4.6 inches of mercury. Also, do not per right aft baffle. Model 210 has two filters operate the vacuum system with the filter element located at the upper aft baffle on each side of removed or a vacuum line disconnected as particles the engine. of dust or other foreign matter may enter the system and damage the vacuum operated instruments. To service the dry type filter, proceed as follows: a. Remove the filter as outlined in Section 12 and 2-23. BATTERY. Battery servicing involves adding 12A. distilled water to maintain the electrolyte level even b. Clean filter by blowing with compressed air (not with the horizontal baffle plate or split ring at the bot- over 100 psi) from direction opposite of normal air tom of the filler holes, checking cable connections, and flow. Arrows on the filter frame indicate direction neutralizing and cleaning off any spilled electrolyte of normal air flow. or corrosion. Use bicarbonate of soda (baking soda) and clean water to neutralize electrolyte or corro- NOTE sion. Follow with a thorough flushing with clean wa- ter. Do not allow bicarbonate of soda to enter bat- Use care to prevent damage to filter element tery. Brighten cable and terminal connection with a when cleaning with compressed air. Never wire brush, then coat with petroleum jelly before use air pressure greater than 100 psi to clean connecting. Check the battery every 50 hours (or at filter. least every 30 days), oftener in hot weather. Add only distilled water, not acid or "rejuvenators, " to c. After cleaning as outlined in step "b, " filter may maintain electrolyte level in the battery. Inspect the be washed, if necessary, in a solution of warm water battery box and clean and remove any evidence of and a mild household detergent. A cold water solu- corrosion. tion may be used. 2-24. TIRES should be maintained at the air pres- CAUTION sure specified in figure 1-1. When checking tire pressure, examine tire for wear, cuts, bruises, and Do not use solvent or cleaning fluids to wash slippage. filter. Use only a water and household deter- gent solution when washing the filter. NOTE NOTE Recommended tire pressure should be main- tained. Especially in cold weather, remem- The dry type filter may be cleaned with com- ber that any drop in temperature of the air pressed air a maximum of 30 times or it may inside a tire causes a corresponding drop in be washed a maximum of 20 times. The filter pressure. should be replaced after 500 hours of engine operating time or one year, whichever should 2-25. NOSE GEAR STRUT. The nose gear strut re- occur first. However, the filter should be quires periodic checking to ascertain that the strut is replaced at anytime it is damaged. A damaged filled with hydraulic fluid and is inflated to the cor- Change 3 2-7 reelair pressure. To till the nose gear strut with pletely full. hydraulic fluid and air. proceed as follows: d. Reinstall filler plug and safety. a. Weitht tail to raise nose wheel off ground. e. Wash dampener in solvent and wipe dry with a b. Remove filler valve cap from filler valve, and cloth. depress valve core to completely deflate nose strut. f. Reinstall shimmy dampener in aircraft. Remove valve core from filler valve. di. Attach a rubber huse to the filler valve. NOTE e. With other end of rubber hose in a container of clean hydraulic fluid compress and extend strut sev- Keep shimmy dampener, especially the eral times. This will draw fluid from container into exposed portions of the dampener piston the strut. tilling strut with hydraulic fluid. shaft, clean to prevent collection of dust f. Alter strut has been cycled several times, allow and grit which could cut the seals in the strut to extend. Holding end of rubber hose above dampener barrel. Keep machined sur- fluid level in container. slowly compress strut. al- faces wiped free of dirt and dust, using a lowing excess fluids to be drained into container, clean lint-free cloth saturated with hy- g. While strut is compressed remove hose and in- draulic fluid (MIL-H-5606) or kerosene. stall valve core in filler valve. All surfaces should be wiped free of ex- h. Inflate strut to the pressure specified in figure cessive hydraulic fluid. I -1. 2-27. HYDRAULIC BRAKE SYSTEMS should be NOTE checked for the correct amount of fluid at least every 200 hours. Add hydraulic fluid at the brake master The nose landing gear shock strut will cylinders. Bleed the brake system of entrapped air normally require only a minimum amount whenever there is spongy response to the brake ped- of service. Maintain the strut extension als. Refer to Section 5 for the bleeding procedure. pressure as shown in figure 1-1. Lubricate landing gear as shown in figure 2-5. Check 2-28. HYDRAULIC RESERVOIR. (Thru 21059502) the landing gear daily for general cleanli- The hydraulic reservoir should be filled as necessary ness. security of mounting, and for hydrau- whenever the fluid level in the reservoir sight window lic fluid leakage. Keep machined surfaces shows low. Filling is accomplished by using a pres- wiped free of dirt and dust, using a clean sure brake bleeder or Hydro Fill unit attached to the lint-free cloth saturated with hydraulic filler fitting, located on the right firewall. Hydraulic fluid (MII,-H-5606) or kerosene. All sur- fluid should be pumped into the filler fitting until fluid faces should be wiped free of excessive flows from the reservoir vent line. Refer to figure hydraulic fluid. 2-3 for procedures for filling the hydraulic power pack beginning with 21059503. 2-26 NOSE GEAR SHIMMY DAMPENER. The shimmy dampener should be serviced at least every 2-29. HYDRAULIC FILTER. (Thru 21059502) The 100 hours. The dampener must be filled completely hydraulic filter, located on the right firewall in the with hydraulic fluid, free of entrapped air with the hydraulic in the hydraulic pump pressure line, uses compensating piston bottomed in the rod. Check that a fine-mesh screen to filter the hydraulic fluid. The piston is completely bottomed as follows: filter screen should be removed and cleaned at the a. Remove shimmy dampener from the aircraft. first 25, first 50 hours, or thereafter, at 100-hour b1. While holding the shimmy dampener in a verti- intervals or whenever improper fluid circulation is cal position with the tiller plug pointed upward, suspected. loosen the filler plug. c. Allow the spring to bottom out the floating piston 2-30. HYDRAULIC FLUID SAMPLING AND CON- inside the shimmy dampener rod. TAMINATION CHECK. At the first 50 and first 100 d. When the fluid stops tlowing, insert a length of hour-inspection, thereafter at each 500-hour inspec- stiff wire through the air bleed hole in the setscrew tion or one year, whichever should occur first, a at the end of the piston rod until it touches the float- sample of fluid should be taken and examined for ing piston. The depth of insertion should be 3-13/16 sediment and discoloration. This may be done as inche s. follows: a. Place aircraft master switch in OFF position. NOTE b. With landing gear control handle in down-neutral, actuate hydraulic hand pump to supply pressure to It the wire insertion is less than 3-13/16 open landing gear doors. inches. the floating piston is lodged in the c. Disconnect door open line from nose gear door shaft. If the wire cannot be used to free actuator cylinder. Using the hydraulic hand pump, the piston, the rod assembly and piston drain a small sample of hydraulic fluid into a non- should be replaced. metallic container. d. Connect nose gear door actuating cylinder line Service the shimmy dampener as follows: and analyze fluid sample. a. Remove filler plug from dampener. e. If the drain fluid is clear and is not appreciably b. Move piston completely to opposite end from darker in color than new fluid, continue to use the filler plug. present fluid. c. Fill dampener with clean hydraulic fluid conm- f. If the fluid color is doubtful, place fluid sample 2-8 Change 1 2-33. CLEANING. surface. After cleaning if any scratches, "bulls eyes" or other damage is detected, refer to Section 3 for 2-34. Keeping the aircraft clean is important. Be- repair or replacement of windows or windshield. sides maintaining the trim appearance of the aircraft, cleaning reduces the possibility of corrosion and 2-38. ALUMINUM SURFACES. The aluminum sur- makes inspection and maintenance easier, faces require a minimum of care, but should never be neglected. The aircraft may be washed with clean 2-35. UPHOLSTERY AND INTERIOR cleaning pro- water to remove dirt and may be washed with non- longs the life of upholstery fabrics and interior trim. alkaline grease solvents to remove oil and/or grease. To clean the interior, proceed as follows: Household-type detergent soap powders are effective a. Empty all the ash trays. cleaners, but should be used cautiously since some b. Brush out or vacuum clean the upholstery and of them are strongly alkaline. Many good aluminum carpeting to remove dirt. cleaners, polishes and waxes are available from com- c. Wipe leather and plastic surfaces with a damp mercial suppliers of aircraft products. cloth. d. Soiled upholstery fabrics and carpet may be 2-39. PAINTED SURFACES. The painted exterior cleaned with a foam-type detergent, used according surfaces of the aircraft, under normal conditions, to the manufacturer's instructions. require a minimum of polishing or buffing. Approx- e. Oily spots and stains may be cleaned with house- imately 15 days are required for acrylic or lacquer hold spot removers, used sparingly. Before using paint to cure completely and approximately 90 days any solvent, read the instructions on the container are required for vinyl paint to cure completely; in and test it on an obscure place in the fabric to be most cases, the curing period will have been com- cleaned. Never saturate the fabric with a volatile pleted prior to delivery of the aircraft. In the event solvent; it may damage the packing and backing ma- that polishing or buffing is required within the curing terial. period, it is recommended that the work be done by f. Scrape off sticky materials with a dull knife, an experienced painter. Generally, the painted sur- then spot clean the area. faces can be kept bright by washing with water and mild soap, followed by a rinse with water and drying 2-36. PLASTIC TRIM. The instrument panel, plas- with cloths or a chamois. Harsh or abrasive soaps tic trim and control knobs need only be wiped off with or detergents which cause corrosion or make scratch- a damp cloth. Oil and grease on the control wheel es should never be used. Remove stubborn oil and and control knobs can be removed with a cloth mois- grease with a cloth moistened with Stoddard solvent. tened with Stoddard solvent. After the curing period, the aircraft may be waxed with a good automotive wax. A heavier coating of CAUTION wax on the leading edges of the wings and tail and on the engine nose cap will help reduce the abrasion Do not use gasoline, alcohol, benzene, ace- encountered in these areas. tone, carbon tetrachloride, fire extinguisher fluid, deicer fluid, lacquer thinner or glass 2-40. ENGINE COMPARTMENT cleaning is essen- window cleaning spray. These solvents will tial to minimize any danger of fire, and for proper soften and craze the plastic. inspection of engine components. The engine and en- gine compartment may be washed down with a suit- 2-37. WINDSHIELD AND WINDOWS should be clean- able solvent, then dried thoroughly. ed carefully with plenty of fresh water and a mild de- CAUTION tergent, using the palm of the hand to feel and dis- lodge any caked dirt or mud. A sponge, soft cloth, or chamois may be used, but only as a means of Particular care should be given to electrical carrying water to the plastic. Rinse thoroughly, then equipment before cleaning. Solvent should dry with a clean moist chamois. Do not rub the plas- not be allowed to enter magnetos, starters, tic with a dry cloth since this builds up an electro- alternators, voltage regulators, and the like. static charge which attracts dust. Oil and grease Hence, these components should be protected may be removed by rubbing lightly with a soft cloth before saturating the engine with solvent. moistened with Stoddard solvent. Volatile solvents, Any oil, fuel, and air openings on the engine such as mentioned in paragraph 2-36, must never be and accessories should be covered before used since they soften and craze the plastic. After washing the engine with solvent. Caustic washing, the plastic windshield and windows should cleaning solutions should be used cautiously be cleaned with an aircraft windshield cleaner. Ap- and should always be properly neutralized ply the cleaner with soft cloths, and rub with moder- after their use. ate pressure. Allow the cleaner to dry, then wipe it off with soft flannel cloths. A thin, even coat of wax, 2-41. PROPELLERS should be wiped occasionally polished out by hand with clean soft flannel cloths, with an oily cloth to remove grass and bug stains will fill in minor scratches and help prevent further from the propeller blades. In salt water areas this scratching. Do not use a canvas cover on the wind- will assist in corrosion-proofing the propeller. shield or windows unless freezing rain or sleet is anticipated since the cover may scratch the plastic 2-10 Change 4 2-42. WHEELS should be washed periodically and dard solvent. Care must be taken to prevent solvent examined for corrosion, chipped paint, and cracks from entering gearbox. The gearbox lubricant is not or dents in the wheel castings. Sand smooth, prime, affected and should not be disturbed. and repaint minor defects. h. After soaking, clean entire length of jack screw with a wire brush, rinse with solvent 2-42A. LANDING GEAR AND DOOR MANIFOLD SO- and dry with compressed air. LENOIDS. Beginning with 21060961, disassemble, clean and reassemble every 1000 hours or 5 years. NOTE 2-43. LUBRICATION. Do not disassemble nut and ball retainer assembly. 2-44. Lubrication requirements are shown in fig- ure 2-5. Before adding grease to grease fittings, i. Relubricate jack screw with MIL-G- wipe off all dirt. Lubricate until new grease appears 21164 (Molybdenum Disulfide Grease) as outlined in around parts being lubricated, and wipe off excess steps "j" thru "m". grease. The following paragraphs supplement this j. Rotate nut down screw toward the motor. figure by adding details. k. Coat screw and thread end of nut with grease and run nut to full extension. 2-45. NOSE GEAR TORQUE LINKS. Lubricate 1 Repeat the process and pack lubricant nose gear torque links every 50 hours. When oper- i the cavity between the nut and ball retainer at the ating in dusty conditions, more frequent lubrication threaded end of the nut. is recommended. m. Repeat the process and work nut back and forth several times. 2-46. TACHOMETER DRIVE SHAFT. Refer to Sec- n. Remove excess grease. tion 16 for lubrication. o. Reinstall actuator in aircraft in accor- dance with instructions outlined in Section 7. 2-47. WHEEL BEARING LUBRICATION. Clean and b. On aircraft prior to 21059471 which have been repack wheel bearings at the first 100-hour inspec- modified by Service Kit SK210-68, proceed as follows: tion and at each 500-hour inspection thereafter. If 1. At each 100-hour inspection, expose jack more than the usual number of take-off and landings screw by operating flaps to full-down position, and are made, extensive taxiing is required, or the air- inspect wing flap actuator jack screw for proper ^craft is operated in dusty areas or under seacoast lubrication. If lubrication is required, proceed as conditions, clean and lubricate wheel bearings at follows: each 100-hour inspection. a. Clean jack screw with solvent rag, if necessary, and dry with compressed air. 2-48. WING FLAP ACTUATOR. b. Relubricate jack screw with MIL-G- a. On aircraft prior to 21059471 which have not 21164 (Molybdenum Disulfide Grease) as required. been modified by Service Kit SK210-68, proceed as c. On aircraft beginning with 21059471, clean and follows: lubricate wing flap actuator jack screw as follows each 1. At each 100 hour inspection, inspect wing 100 hours: flap actuator jack screw and ball retainer assembly 1. Expose jack screw by operating flaps to full- for lubrication, and lubricate if required. Also, down position. remove, clean and lubricate jack screw whenever 2. Clean jack screw threads with solvent rag actuator slippage is experienced. If lubrication is and dry with compressed air. required, proceed as follows: a. Gain access to actuator by removing NOTE appropriate inspection plates on lower surface of wing. It is not necessary to remove actuator from b. Expose jack screw by operating flaps to aircraft to clean or lubricate threads. full-down position. c. Wipe a small amount of lubricant from 3. With oil can, apply light coat of No. 10 jack screw with a rag and examine for condition. weight, non-detergent oil to threads of jack screw. Lubricant should not be dirty, sticky, gummy or frothy in appearance. 2-49. ROD END BEARINGS. Periodic inspection d. Inspect wiped area on jack screw for and lubrication is required to prevent corrosion of presence of hard scale deposit. Previous wiping the bearing in the rod end. At each 100-hour inspec- action, will have exposed bare metal if no deposit tion, disconnect the control rods at the aileron and is present. inspect each rod end for corrosion. If no corrosion e. If any of the preceding conditions exist, is found, wipe the surface of the rod end balls with clean and relubricate jack screw as outlined in steps general purpose oil and rotate ball freely to distribute "f" thru "n". the oil over its entire surface and connect the control f. Remove actuator from aircraft in accor- rods to the aileron. If corrosion is detected during dance with procedures outlined in Section 7. inspection, install new rod ends. g. Remove all existing lubricant from jack screw and torque tube by running the nut assembly to the end of the jack screw away from the gearbox, and soaking the nut assembly and jack screw in Stod- Change 4 2-11 25 ENGINE OFF, SYSTEM: Refill with straight mineral oil , non-detergent, and use until a total of 50 hours have accumu- lated or oil consumption has stabilized, then change to ashless dispersant oil. 23 HYDRAULIC FILTER: Check and clean screen at first 25 and 50 hours, thereafter at each 100 hours. 50 HOURS 4 INDUCTION AIR FILTER: Clean filter per paragraph 2-21. Replace as required. 13 BATTERY: Check electrolyte level and clean battery compartment each 50 hours or each 30 days. 25 ENGINE OIL SYSTEM: Change oil each 50 hours if engine is NOT equipped with external filter; if equipped with external oil filter, change filter element each 50 hours and oil at least at each 100 hours, or every 6 months. 18 SHIMMY DAMPENER: Check fluid level and refill as required in accordance with paragraph 2-26. 10 TIRES: Maintain correct tire inflation as listed in figure 1-1. Refer to paragraph 2-24 for details. 17 NOSE GEAR SHOCK STRUT: Keep strut filled and inflated to correct pressure. Refer to paragraph 2-25 for details. 20 SPARK PLUGS: Remove, clean and re-gap all spark plugs. Refer to Section 12 for details. 23 HYDRAULIC FILTER: Check and clean screen at first 25 and 50 hours, thereafter at each 100 hours. 22 HYDRAULIC FLUID RESERVOIR: At first 50 and first 100 hours, thereafter at each 500 hours or one year, whichever comes first, a sample of hydraulic fluid should be examined for sediment and discoloration as outlined in paragraph 2-30. 100 HOURS 2 VACUUM SYSTEM OIL SEPARATOR: Remove, flush with solvent, and dry with compressed air. 3 FUEL/AIR CONTROL UNIT SCREEN: Remove and clean screen. 23 HYDRAULIC FILTER: Check and clean screen at first 25 and 50 hours, thereafter at each 100 hours. 22 HYDRAULIC FLUID RESERVOIR: At first 50 and first 100 hours, thereafter at each 500 hours or one year, whichever comes first, a sample of hydraulic fluid should be examined for sediment and discoloration as outlined in paragraph 2-30. Figure 2-4. Servicing (Sheet 3 of 4) 2-14 Change 4 0 200 HOURS 21 VACUUM RELIEF VALVE FILTER: Change each 1000 hours or to coincide with engine overhauls. 6 FUEL BAY SUMP DRAINS: Drain off any water or sediment. 9 FUEL RESERVOIR TANK DRAIN: Remove plugs and drain off water and sediment. Some aircraft are equipped with drain valves. 12 BRAKE MASTER CYLINDERS: Check fluid level and fill as required with hydraulic fluid. *I 500 HOURS 11 VACUUM SYSTEM CENTRAL AIR FILTER: Replace every 500 hours. 22 HYDRAULIC FLUID RESERVOIR: At first 50 and first 100 hours, thereafter at each 500 hours or one year, whichever comes first, a sample of hydraulic fluid should be examined for sediment and discoloration as outlined in paragraph 2-30. AS REQUIRED 14 GROUND SERVICE RECEPTACLE Thru 1971 Models, connect to 12-volt, D. C. negative-ground power unit. Beginning with 1972 Models, connect to 24-volt, D. C. negative-ground power unit for cold weather starting and lengthy ground maintenance of the aircraft's electrical equipment with the exception of electronic equipment. Master switch should be turned on before connecting a generator-type or battery-type external power source. Refer to Section 17. NOTE The ground power receptacle circuit incorporates a polarity reversal protection. Power from the external power source will flow only if the ground service plug is connected correctly to the aircraft. Figure 2-4. Servicing (Sheet 4 of 4) Change 4 2-15 PG ALL PIANO HINGES BUNGEE SCREW & SPROCKET DRIVE NUT THREADS BEGINNING WITH 21060540 MAIN GEAR GL PIVOT ASSEMBLY TRIMWHEEL BEARINGS OG OILITE BEARINGS GL BATTERY TERMINALS PL NEEDLE BEARINGS Also refer to inspection chart inthissection andtosection Lubricate between inside face of 9 of this manual. washer on shaft and drum. Lubricate shaft and small gear NOTE with clutch in open position. Drum groove and cable must ELECTRIC TRIM be free of grease and oil. ASSEMBLY Figure 2-5. Lubrication (Sheet 3 of 4) 2-18 Change 4 ELECTROFILM LUBRI-BOND "A" WHICH IS AVAILABLE IN AEROSOL SPRAY CANS, OR GL AN EQUIVALENT LUBRICANT. TORQUE 4ATTACHING BOLT TO 10-20 LB-IN. GL DOWN LOCK MECHANISM WING ATTACH RETRACTABLE STEP GL NOTES Sealed bearings require no lubrication. McCauley propellers are lubricated at overhaul and require no other lubrication. Do not lubricate roller chains or cables except under seacoast conditions. Wipe with a clean, dry cloth. Lubricate unsealed pulley bearings, 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-S-8660 silicone compound or equivalent lubricant, applied sparingly to friction points, every 1000 hours or oftener if binding occurs. No lubrication is recommended for the rotary clutch. Figure 2-5. Lubrication (Sheet 4 of 4) Change 4 2-19 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 11 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 II above. In addition, it is recommended that between annual inspections, all items be inspected at the intervals specified in the inspection charts. 2-20 Change 4 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 III 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. Change 1 2-21 (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 12 or 12A of this Manual.) 3. Magneto drop. (Also refer to Section 12 or 12A 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: 2-22 Change 1 CESSNA AIRCRAFT COMPANY CENTURION SERIES SERVICE MANUAL SPECIAL INSPECTION ITEM EACH 200 HOURS EACH 100 HOURS EACH 50 HOURS PROPELLER 1. Spinner........................................................................ 2. Spinner bulkheads .............................................................. 3. Blades ......................................................................... 4. Bolts and nuts .................................................................. 5. Hub ........................................................................... 6. Governor and control ............................................................ 7. Anti-Ice electrical wiring .......................................................... · 8. Anti-Ice brushes, slip ring and boots ............................................... 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 .......... ...................................................... 2 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 ........................... ............ 17. Vacuum relief valve filter ......... ................................................ 5 18. Engine controls and linkage ...................... ............................ 6 19. Engine shock mounts, mount structure and ground straps ............................ 20. Cabin heat valves, doors and controls ......... . ............................ 21. Starter, solenoid and electrical connections .......... . ............................ Revision 5 2-23 Jul 1/2004 © Cessna Aircraft Company CESSNA AIRCRAFT COMPANY CENTURION SERIES SERVICE MANUAL SPECIAL INSPECTION ITEM EACH 200 HOURS EACH 100 HOURS EACH 50 HOURS 22. Starter brushes, brush leads and 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. Magneto timing ................................................................. 8 28. Fuel-air (metering) control unit .................................................... 29. Firewall ....................................................................... 30. Fuel injection system ............................................................ 31. Engine cowl flaps and controls .................................................... 32. Engine cowling ................................................................. 33. Turbocharger............................ ...................................... 9 34. All oil lines to turbocharger, waste gate and controller ................................ 35. Waste gate, actuator and controller ................................................ 36. Turbocharger pressurized vent lines to fuel pump, discharge nozzles and fuel flow gage . 37. Turbocharger mounting brackets and linkage ....................................... 38. Alternator support bracket for security ............................................. 39. Turbocharger oil line check valves ................................................ 23 40. Fuel injection nozzles............................................................ 26 FUEL SYSTEM 1. Fuel strainer, drain valve and control, bay vents, caps and placards ................... 2. Fuel strainer screen and bowl .................................................... 3. Fuel injection screen ............................................................ 4. Fuel reservoir(s) ................................................................ 5. Drain fuel and check bay interior, attachment and outlet screens ...................... 6. Fuel bays and sump drains ....................................................... 2-24 Revision 5 © Cessna Aircraft Company Jul 1/2004 CESSNA AIRCRAFT COMPANY CENTURION SERIES SERVICE MANUAL SPECIAL INSPECTION ITEM EACH 200 HOURS EACH 100 HOURS EACH 50 HOURS 7. Fuel selector valve and placards ...................................................................... 8. Auxiliary fuel pump............................................................................................................ 9. Engine-driven fuel pump ................................................................................................... 10. Fuel quantity indicators and sensing units........................................................................ 11. Fuel lines, check valve, and vapor return line................................................................... 22 12. Turbocharger vent system ................................................................................................ 13. Engine primer.................................................................................................................... 14. Perform a fuel quantity indicating system operational test. Refer to Section 16 for detailed accomplishment instructions ........................................................ 25 LANDING GEAR 1. Brake fluid, lines and hose, linings, discs, brake assemblies and master cylinders ........ 19 2. M ain gear wheels ............................................................................................................. 3. W heel bearings................................................................................................................. 10 4. Main gear springs............................................................................................................. 5 . Tires .................................................................................................................................. 6. Torque link lubrication ...................................................................................................... 7. Parking brake system ....................................................................................................... 8. Nose gear strut and shimmy dam pener (service as required) ......................................... 9. Nose gear wheel............................................................................................................... 10. Nose gear fork .................................................................................................................. 11. Nose gear steering system ............................................................................................... 12. Parking brake and toe brakes operational check............................................................. LANDING GEAR RETRACTION SYSTEM NOTE: When performing an inspection of the landing gear retraction system, the aircraft must be placed on jacks and an external power source of at least 60 Amps should be used to prevent drain on the aircraft battery when operating the system. 1. Operate the landing gear through five fault-free cycles, noting cycle time. (9 seconds down; 11 seconds up).................................................................................... 2. Check landing gear doors for positive clearance with any part of the landing gear during operation, and for proper fit when closed......................................................................... 3. Check all hydraulic system components for security, hydraulic leaks and any apparent damage to components or mounting structure................................................................. Revision 5 2-25 Jul 1/2004 © Cessna Aircraft Company SPECIAL INSPECTION ITEM EACH 200 HOURS EACH 100 HOURS EACH 50 HOURS 4. Check doors, hinges, hinge pins and linkage for evidence of wear, other damage and security of attachment ............................................. 5. Inspect internal wheel well structure for cracks, dents, loose rivets, bolts and nuts, corrosion or other damage. ............................................ 6. Check electrical wiring and switches for security of connections, switch operation and check gear position indicator lights for proper operation. Check wiring for proper routing and support ....................................... 7. Perform operational check and insure proper rigging of all systems and components including downlocks, uplocks, doors, snubbers, switches, actuators and power pack, observing cycle time noted in item 1..................... 8. Check main gear strut-to-pivot attachment ...................................... 9. Check condition of all springs.................................................... 10. Check hydraulic filter ........................................................... 11 11. Hydraulic fluid contamination check... .................................... 12 12. Power pack inlet check valve screen cleaned ...................................... 13. Check emergency check valve operation .......................................... 14. Landing gear and door manifold solenoids (mounted on power pack).................. 20 AIRFRAME 1. Aircraft exterior ................................................................ 2. Aircraft structure ............................................................... 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, sprockets, pulleys, cables, chains and turnbuckles .......... 7. Control lock, control wheel and control column mechanism .......................... 8. Instruments and markings....................................................... · 9. Gyro central air filter ........................................................... 13 10. Magnetic compass compensation ......................................... 5 11. Instrument wiring and plumbing ................................................. 12. Instrument panel, shock mounts, ground straps, cover, decals and labeling ............ 13. Defrosting, heating and ventilating systems and controls............................. 14. Cabin upholstery, trim, sunvisors and ash trays .................................... 15. Area beneath floor, lines, hoses, wires and control cables ........................... 2-26 Change 4 SPECIAL INSPECTION ITEM EACH 200 HOURS EACH 100 HOURS EACH 50 HOURS 16. Lights, switches, circuit breakers, fuses and spare fuses .............. 17. Exterior lights ........ ........ 18. Pitot and static systems ............... 19. Stall warningunit and pitot heater ............ 20. Radios, radio controls, avionics and flight instruments ......... 21. Antennas and cables .................. 22. Battry, battery box and batter cables .................... .. 23. Battery electrolyte ............................ . 14 24. Emergency locator transmitter ...................... . 15 25. Oxygen system ................. 26. Oxygen supply, masks and hose ............ ... ....... 16 27. De-Ice system plumbing ............... 28. De-Ice system components ................... 29. De-Ice system boots ............... CONTROL SYSTEMS . In addition to the items listed below, always check for correct direction of movement, correct travel and correct cable tension 1. Cables terminal , pulleys, pulley brackets, cable guards, turnbuckles and (airlead . . . . . . . . . . . . . . . . . . . 2. Chains, terminals, sprockets and chain guards ........ 3. Trim control wheels, indicators, actuator and bungee........... 4. Travel stops . . . . . . . . . . . . . . . . . 5. Decals and labeling . . .. . . .. . . . . . . ... 6. Flap control switch, flap rollers and flap position indicator ........ 7. Flap motor, transmission, limit switches, structure, linkage, bellcrarks etc ..... 8. Flap actuator jackscrew threads ......................... 9. Elevators