Reims Rocket 1968 Thru 1976 Service Manual

manual and supersede aerofiche information. AEROFICHE AEROFICHE SECTION PAGE FICHE/FRAME SECTION PAGE FICHE/FRAME 15 18 1 L10 15 19 1 L11 15 20 1 L12 15 20A added 15 20B added 15 21 1 L13 REASON FOR TEMPORARY REVISION 1. To revise procedure to incorporate both Stewart Warner and Rochester fuel gage transmitter calibration. 2. To revise procedures to incorporate both electrically and pressure controlled oil temperature gages. 3. To add tables to aid in trouble shooting the cylinder head and oil temperature gages. FILING INSTRUCTIONS FOR THIS TEMPORARY REVISION For Paper Publications: File this cover sheet behind the publication's title page to identify the inclusion of the Temporary Revision into the manual. Insert the new pages into the publication at the appropriate locations and remove and discard the superseded pages. For Aerofiche Publications: Draw a line through any aerofiche frame (page) affected by the Temporary Revision with a permanent red ink marker. This will be a visual identifier that the information on the frame (page) is no longer valid and the Temporary Revision should be referenced. For "added" pages in a Temporary Revision, draw a vertical line between the applicable frames which is wide enough to show on the edges of the pages. Temporary Revisions should be collected and maintained in a notebook or binder near the aerofiche library for quick reference. COPYRIGHT 1994 CESSNA AIRCRAFT COMPANY WICHITA, KANSAS, USA INSERT LATEST CHANGED PAGES. DESTROY SUPERSEDED PAGES. LISTOf EFFECTIVE PAGESline In the outer margin of the page. Changes to illuatratios are Indicated by minlture pointing hands. Dates of issue for original and changed pages are; Original ... 0 ... 15 August 1970 Change . . .. . . 1 November 1972 Change . . . 1 September 1971 Change . . . 3 ... 15 June 1973 Change ... 4 ... I September 1974 Change ... 5... 1 October 1975 TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 420, CONSITING OF THE FOLLOWING: Page Change Page Change Change Page C Pe Cn P ane No. No. No. No. No. No. No. No. . . ... 1 A ......... *5-18A ....... . 5 15-2B Blank ...... 5 17-1OB ...... * thru iii.. ...... 5 5-18B Blank .. .. . 5 *15-3 thru 15-6 ..... 17-11 thru 17-29 .. 0 iv Blank ........ 5-19 thru 5-22 ..... S '15-6A thru 15-5B . . 5 17-30 thru 17-32 .... 1-1 .......... 0 5-23 ......... 3 15-7 ......... 5 *1-1 thru 18-..... 5 '1-2 S '5-24 ......... 5 15-8 ......... 19-1 ....... 1-3 .. ........ 5-5 thru 5-27 . 3 15-9thru 15-10 . . . 4 19-2 ......... 4 1-4 .......... 4 5-28 Blank ...... 3 15-11 ......... 0 19-3 . ...... 5 -1 thru 2-2 ...... 1 thru 6-3 . 4 15-12 thru -13 . 1 -4 . ........ . 4 * 2A ......... 6-4 .......... I '15-14 ......... 5 19-5 . ........ 2-21B Blank ...... 6-5 .......... 5 *15-14A ........ 19-. . ..... 2-thru 2-10 ..... 6- .......... 2 15-14B *......19-7thru 19-8..... *2-10A tru 2-10 . ... 5 -7 .......... 0 15-15 thru 15-20 .... 4 19- ......... 1 *2-11 thru 2-17 ..... 5 -8 Blank ....... 0 15-21 ......... 3 19-10 . ...... 5 2-18. .......... 7-1 thru 7-7 ...... 2 15-22 thru 15-24 .... 4 19-11 . .2..... *2-19 thru 2-22 ..... 5 7-8 .......... 3 16-1 thru 16-2 ..... 1912 th 19-14 .... 5 2-23 ......... 7-9 .......... 4 '16-A ......... 5 19-14A thru 19-14B. . 5 2-24 ......... 5 7-10 thru 7-12 ..... 2 16-B Blank ...... 19-15thru 19-21 .... 5 -1 .......... 8-1 thru 8-...... 4 16-3 ......... 4 19-22 ......... 3 3-2 .0........ 9-1 thru 9-4 ...... 4 164 ......... 0 19-23 ......... 3-3 .......... 9-4A . ........ 4 *16-5 ......... 19-24 ......... 3-4 .......... 9-4B Blank .. 4 16- thru 16-12 .... 4 19-25 thru 19-27 .... 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'16-20 ......... 5 19-37 . ....... 3-17 ......... 4 12-4A ......... 5 1-20A ........ 4 19-38 . ........ 3 *3-18 ......... *12-4B Blank ...... 5 1-20B Blank ..... 4 19-39 . ...... 5 3-19 thu3thru-1 .....12- thr 12-65 1-21 ......... 2 19-40 ......... 3 3-22 Blank ...... 4 *I-A ......... 5 '168-22 ........ 5 '19-41. ........ 5 4-1 thru 4-2 ...... 4 12-6B Blank ...... 5 1-23 ......... 3 19-4 ......... 3 4-3 ......... 2 12-7 ......... 3 1-2 . ..... 4 *1-43 ......... 4-4 ... 4 11-8 thru 12-10 .... 18-24A ........ 5 19-44 ......... 3 4-5 .......... 2 12-10A thru 12-10C. .. 5 16-24B Blank ..... 5 19-45 ......... 4-6 thru 4-7 ...... 12-IOD Blank ..... 5 18-5 thru 16-27 .... 1-4 ......... 3 4-8 Blank ....... 4 12-11 ..... . '18-28 ......... 5 '19-47 thru 19-49 .... '5-1 thr 5-5 ...... 5 12-12 ......... 2 18-29 .2 1...9-50 (Bank) ...... 5 -6 .......... 3 *13-1 thru 133 ... .. 5 1-30 thru 1-34 .... 4 19-51 thru 19-56 .... *5-7 thru 5- ...... 13-4 ......... 2 *1835 thru 16-35 .... *19-5EA . . 5 '-8A ......... 13-5 ......... 3 17-1 ...... . 4 *19-58B Blank .... '5-8B Blank ...... 13-6 thru 13-7 ..... 5 17-2 ......... '19-57 thru 19-83 .. 5 5-9 thru 5-11 ..... *13- Blank .5..... 17-3 thru 17-4 ..... 1 19-U4 Blank . .... 5-12 ......... 14-1 thru 14-2..... 0 17-5 thru 17-6 ..... 4 '5-13 ......... *14-3 ......... 5 17-7 . ........ 5-14 thru 5-16 ..... 3 14-4. ........ 17-8 thru 17-9 ..... 3 '15-1 thru 15-2. .... 5 17-10 . ....... 1 Upon receipt of the second and subsequent changes to this book, personnel responsible for maintaining this publication in current status should ascertain that all previous changes have been received and incorporated. The asterirk indicates page* changed, added or deleted by the current change A Change 5 TABLE OF CONTENTS SECTION Page 1 GENERAL DESCRIPTION ........................ 2 GROUND HANDLING, SERVICING, CLEANING, LUBRICATION AND INSPECTION ............................ 2-1 3 FUSELAGE ................... ........... 3-1 4 WINGS AND EMPENNAGE ....................... 4-1 5 LANDING GEAR AND BRAKES. ....................... 5-1 6 AILERON CONTROL SYSTEM ...................... 6-1 7 WING FLAP CONTROL SYSTEM .............. ....... 7-1 8 ELEVATOR CONTROL SYSTEM ..................... 8-1 9 ELEVATOR TRIM TAB CONTROL SYSTEM ............ ........... 9-1 10 RUDDER CONTROL SYSTEM ................... ... 10-1 11 ENGINE ........................... ... 11-1 12 FUEL SYSTEM ........................... 12-1 13 PROPELLERS AND PROPELLER GOVERNORS .............. 13-1 14 UTILITY SYSTEMS .......................... 14-1 15 INSTRUMENTS AND INSTRUMENT SYSTEMS ............... 15-1 16 ELECTRICAL SYSTEMS ........................ 16-1 17 STRUCTURAL REPAIR .................... .... 17-1 18 PAINTING .............................. 18-1 19 WIRING DIAGRAMS ......................... . 19-1 Change 5 i CROSS REFERENCE LISTING OF POPULAR NAME VS. MODEL NUMBERS AND SERIALS All aircraft, regardless of manufacturer, are certificated under model number designations. However, popular names are often used for market- ing purposes. To provide a consistent method of referring to these air- craft, the model number will be used in this publication unless the popular name is necessary to differentiate between versions of the same basic model. The following table provides a listing of popular name, model -number, andserial number. MODEL SERIALS POPULAR NAME YEAR MODEL BEGINNING ENDING REIMS ROCKET 1968 FR172E FR172-0001 FR172-0060 1969 FR172F FR172-0061 FR172-0145 1970 FR172G FR17200146 FR17200225 1971 FR172H FR17200226 FR17200275 1972 FR172H FR17200276 FR17200350 1973 FR172J FR17200351 FR17200440 1974 FR172J FR17200441 FR17200530 1975 FR172J FR17200531 FR17200559 &FR17200561 1976 FR172J FR17200560 &FR17200562 ii Change 5 FOREWORD This manual contains factory recommended procedures and instructions for ground handling, servicing and main- taining Cessna Model FR172-Series aircraft. Besides serving as a reference for the experienced mechanic this book also covers step-by-step procedures for the less experienced 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 FR172-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 Company. These are sent to all Cessna Dealers so that they have the latest authoritative recommendations for servicing Cessna aircraft. Therefore, it is recommended that owners of Cessna aircraft utilize the knowledge and experi- ence of the factory-trained Dealer Service Organization. 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 disassem- bly, overhaul and parts breakdown of some of the various vendor equipment items. A listing of the available publi- cations i issued periodically by the Cessna Customers Service Department. Information for Nav-O-Matic Autopilots, Electronic Communications and Navigation Equipment is not in- cluded in this manual. These systems are described in separate manuals, available from the Cessna Service Parts Center. Change 5 iii/(iv blank) SECTION 1 GENERAL DESCRIPTION TABLE OF CONTENTS Page GENERAL DESCRIPTION ......... . 1-1 Aircraft Specifications ......... 1-1 Model FR172-Series .......... 1-1 Stations ................ 1-1 Description ............ 1-1 Torque Values ............ 1-1 1-1. GENERAL DESCRIPTION. windows, a "wrap-around" rear window and a swept- back fin and rudder. 1-2. MODEL FR172-SERIES. 1-4. AIRCRAFT SPECIFICATIONS. Leading partic-1-3. DESCRIPTION. Cessna Model FR172-Series ulars of these aircraft, with dimensions based onaircraft, described in this manual, are high-wing gross weight, are given in figure 1-1. If these di- monoplanes of all-metal, semimonocoque construc- mensions are used for constructing a hangar or com-tion. These aircraft are equipped with a fixed tri- puting clearances, remember that such factors as cycle landing gear. Through 1970 Models, they are nose gear strut inflation, tire pressures, tire sizes, equipped with flat spring-steel main landing gear and load distribution may result in some dimensions struts. Beginning with 1971 Models, these aircraft that are considerably different from those listed. are equipped with tubular spring-steel main landing gear struts. The steerable nose gear is equipped 1-5. STATIONS. A station diagram is shown in with an air/hydraulic fluid shock strut. Standard figure 1-2 to assist in locating equipment when a seating accommodations consist of individual, re- written description is inadequate or impractical. clining back, pilot and copilot seats and dual reclin- ing back, bench-type center seats. A fold-up aux- 1-6. TORQUE VALUES. A chart of recommended iliary rear seat may be installed as optional equip- nut torque values is shown in figure 1-3. These ment. A baggage area is provided aft of the center torque values are recommended for all installation seats when the auxiliary seat is folded up. These procedures contained in this manual, except where aircraft are powered by a Continental six-cylinder, other values are stipulated. They are not to be used horizontally opposed, air-cooled, fuel injection for checking tightness of installed parts during ser-engine, driving an all-metal, constant-speed pro- vice. peller. The Model FR172-Series features rear side 1-1 GROSS WEIGHT Normal Category (Thru 1969) ................ 2500 lb Normal Category (Beginning with 1970) . . ... 2550 lb Utility Category ..... 2200 lb FUEL CAPACITY Total 52gal. Total . . . . . . . . . . . . . . . . . . . . . . . . . . . 52 gal. Usable ........................... 46 gal. (THRU FR17200530) OIL CAPACITY 49 gal. (BEGINNING WITH (Without External Filter) ............... 8 qt FR17200531) (With External Filter) ................... 9 qt ENGINE MODEL (Refer to Section 11 for Engine Data) ....... CONTINENTAL 10-360 Series PROPELLER (Constant Speed) ................. 76" McCauley MAIN WHEEL TIRES ............. ........ 6.00 x 6, 6-Ply Rating Pressure (Thru 1969 Models) ............... 24 ps Pressure (1970-Models)- . .- - 30 psi Pressure (Beginning with 1971 Models) .. . .... 38 psi NOSE WHEEL TIRE (Standard) .. . ............ 5.00 x 5, 6-Ply Rating Pressure (Thru 1969 Models) . ........ .. 26 psi Pressure (1970 Models). ........... .. 30 psi Pressure (Beginning with 1971 Models) ........... 45 psi NOSE WHEEL TIRE (Optional) ................. 6.00 x 6, 4-Ply Rating Pressure (Thru 1969 Models) . . ...... 26 psi Pressure (Beginning with 1970 Models) . .......... 21 psi NOSE GEAR STRUT PRESSURE (Strut Extended) . ....... 45 psi WHEEL ALIGNMENT (Flat Spring Struts) Camber . ................... 3° to 5 ° Toe-In . . . . . . . . . ... . . . . . . . . . . ... 0 " to .06" WHEEL ALIGNMENT (Tubular Spring) Camber .. ........................ 2 to 4' Toe-In ........... .......... ...... . 0" to .18" No provisions are made for aligning wheels on tubular gear aircraft. The toler- ances provided here are to be used only for checking existing wheel alignment. AILERON TRAVEL Up .................................. . 20 1 Down .................................. 15 ° 1 WING FLAP TRAVEL ................... .. 0 to 40°(*2 * THRU FR17200350) RUDDER TRAVEL (Measured parallel to waterline) (+0° -2° BEGINNING WITH Right ........................... 16 ° 10' * 1" FR17200351) Left .................................. . 16 ° 10' 1 RUDDER TRAVEL (Measured perpendicular to hinge line) Right .......................... 17 ° 44' * 10 Left .................... ....... 17 ° 44' ± 1° ELEVATOR TRAVEL Up .................................. . 28, +10 -0 ° Down ...................... ..... 23 ° , +1 ° -0 ° ELEVATOR TRIM TAB TRAVEL Up ............. ............. 28 ° , +1° -0 ° Down . . . . . . . . . . . . . . . . . . . . . . . . . . . 13°, .+1° -0 ° PRINCIPAL DIMENSIONS Wing Span (Conventional Wing Tip) ................ 36' 2" Wing Span (Conical-Camber Wing Tip) ............ 35' 10" Wing Span (Conical-Camber With Strobe Lights) ....... 36' (Thru 1971) 36' 7" (Beginning with 1972) Tail Span .. . . . . . . . . . . . . . . . . . . . . . . . 11' 4" Length .. .. ...... . . . ............ 26' 9-1/2" (Thru 1973) 27' 2" (Beginning with 1974) Fin Height (Maximum With Nose Gear Depressed and Flashing Beacon Installed on Fin) ............. 8' 9-1/2" Track Width (Flat Spring Struts) . 7' 2" Track Width (Tubular Spring) .. . . . ....... 8' 3-1/2",. BATTERY LOCATION ...... ............. Aft of Baggage Area Figure 1-1. Aircraft Specifications 1-2 Change 5 23. 62 STATIONS RE MAIN THE SAME 0.00 -39.3.37 16.66 65.33 108.00 142.00 205.281 .8 .1 4 -- '9!. O0 124. 00 1'8.00 228.68 8.12 44. 57 80.00 -7 7~~~Change 3 1-3 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 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 2500-4630 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, E20365, 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 4 SECTION 2 GROUND HANDLING, SERVICING, CLEANING, LUBRICATION AND INSPECTION TABLE OF CONTENTS Page GROUND HANDLING ............ 2-1 Battery ............... 2-7 Towing . ..... . ...... ... 2-1 Tires ...... ... . ..... .. 2-7 Hoisting. .............. . 2-1 Nose Gear Shock Strut ......... 2-7 Jacking ............ . .. 2-3 Nose Gear Shimmy Dampener ...... 2-8 Leveling. ............. . 2-3 Hydraulic Brake Systems ........ 2-8 Parking ................ 2-3 CLEANING ............. . 2-9 Tie-Down .. ........... 2-3 Windshield and Windows. ........ 2-9 Flyable Storage . ........... 2-3 Plastic Trim. ............. 2-9 Returning Aircraft to Service ...... 2-3 Painted Surfaces ............ 2-9 Temporary Storage ........... 2-3 Aluminum Surfaces .......... 2-9 Inspection During Storage ........ 2-4 Engine and Engine Compartment ..... 2-9 Returning Aircraft to Service ...... 2-4 Upholstery and Interior ......... 2-9 Indefinite Storage. ........... 2-4 Propeller ............... 2-10 Inspection During Storage ........ 2-5 Wheels ................ 2-10 Returning Aircraft to Service ...... 2-5 LUBRICATION. .............. 2-10 SERVICING ................ 2-6 Tachometer Drive Shaft ........ 2-10 Fuel ................. 2-6 Wheel Bearings ............ 2-10 Fuel Drains .............. 2-6 Nose Gear Torque Links ........ 2-10 Engine Oil. .............. 2-6 Wing Flap Actuator .......... 2-10 Engine Induction Air Filter ....... 2-7 Fuel Selector Valve. .......... 2-10A Vacuum System Filter ......... 2-7 INSPECTION ............... 2-17 2-1. GROUND HANDLING. CAUTION 2-2. TOWING. Moving the aircraft by hand is ac- When towing the aircraft, never turn the nose complished by using the wing struts and landing gear wheel more than 30 degrees either side of struts as push points. A tow bar attached to the nose center or the nose gear will be damaged. Do gear should be used for steering and maneuvering the not push on control surfaces or outboard em- aircraft on the ground. When no tow bar is available, pennage surfaces. When pushing on the tail- press down at the horizontal stabilizer front spar ad- cone, always apply pressure at a bulkhead to jacent to the fuselage to raise the nose wheel off the avoid buckling the skin. ground. With the nose wheel clear of the ground, the aircraft can be turned by pivoting it about the main 2-3. HOISTING. The aircraft may be lifted with a wheels. hoist of two-ton capacity by using hoisting rings, TOW BAR: PART NUMBER 0501019.-1 IS AVAILABLE FROM THE CESSNA SERVICE PARTS CENTER. NOTE avoid scarring finish on speed fairing. Figure 2-1. Tow Bar Change 5 2-1 REFER TO SHEET 2 FOR JACKING INFORMATION ITEM NUMBER TYPE AND NUMBER REMARKS Block (Jack point not available) 1x4x4 padded with 1/4" rubber Jack Any short jack of capable capacity Universal tail stand Any tail stand of capable capacity Cessna #SE-576 (41-1/2" high) Universal jack stand (FOR USE WITH ITEM 2) Cessna #10004-98 Jack point * (SEE CAUTION) Cessna #0541208-1 Jack point # (SEE NOTE 5) Built-in jack pad Part of step bracket t #2-170 Basic jack (includes #2-71 Min. closed height: 34" (6 Slide tube: Liftstroke 22-1/2") Max. extension height: 56-1/2" #2-70 Slide tube: Liftstroke Min. closed height: 57-1/2" 22-1/2" Max. extension height: 80" #2-64 Extension cap Adds 4" #2-109 Leg extension Adds 12" * THRU FR17200225 # FR17200226 THRU FR17200341 t BEGINNING WITH FR17200342 Corresponding points on both upper door sills may be used to level the aircraft laterally. Prior to 1972 Models, reference points for leveling the aircraft longitudinally are the top of the tailcont between rear window and vertical fin. Beginning with 1972 Models, reference points for longitudinal leveling of aircraft are two screws on left side of tailcone at zero waterline. These are indicated in illustration byA (Also refer to paragraph 2-5) Figure 2-2. Jacking and Leveling (Sheet 1 of 2) 2-2 Change 5 JACKING INFORMATION 1. Wing jacks, which must be of adequate strength, are placed under front spar of wing just outboard of wing strut and must extend far enough to raise wheels off ground. 2. Attach a suitable 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 on it. NOTE Place additional weights (shot bags or sand bags) on the weighted tail stand to hold the tail down. In addition, the base of the adjustable tail stand is to be filled with concrete for additional weight as a safety factor. 3. Operate jacks evenly until desired height is reached. CAUTION When using universal jack point (10004-98), flexibility of the gear strut will cause the main wheel to slide inboard as the wheel is raised, tilting the jack. The jack must be lowered for a second operation. Jacking both wheels simultaneously with universal jack points is not recommended. Universal jack point may be used to raise only one main wheel. DO NOT USE brake casting as a jack point. 4. Items (4), (5) and (6) are available from the Cessna Service Parts Center. 5. On tubular gear aircraft, the only fairing requiring removal is the fuselage-to-tube gear fairing. Jack pad is inserted on tube In area between fuselage and upper end of tube fairing, then jack aircraft as required. SHOP NOTES: Figure 2-2. Jacking and Leveling (Sheet 2 of 2) Change 5 2-2A/(2-2B blank) which are optional equipment, or by means of suit- NOTE able slings. The front sling should be hooked to each upper engine mount at the firewall, and the aft The aircraft is delivered from Cessna with a sling should be positioned around the fuselage at the Corrosion Preventive Aircraft Engine Oil first bulkhead forward of the leading edge of the (MIL-C-6529, Type II, RUST BAN). This stabilizer. If the optional hoisting rings are used, engine oil is a blend of aviation grade straight a minimum cable length of 60 inches for each cable mineral oil and a corrosion preventive com- is required to prevent bending of the eyebolt-type pound. This engine oil should be used for the hoisting rings. If desired, a spreader jig may be first 50 hours of engine operation. Refer to fabricated to apply vertical force to the eyebolts. paragraph 2-20 for oil changes during the first 50 hours of operation. 2-4. JACKING. Refer to figure 2-2 for jacking procedures. During the 30 day non-operational storage or the first 25 hours of intermittent engine operation, 2-5. LEVELING. Corresponding points on both upper every seventh day, the propeller shall be rotated door sills may be used to level the aircraft laterally. through five revolutions, without running the engine. Prior to 1972 Models, the reference point for leveling If the aircraft is stored outside, tie down in accor- the aircraft longitudinally is the top of the tailcone, be- dance with paragraph 2-7. In addition, the pitot tube, tween the rear window and vertical fin. Beginning with static air vents, air vents, openings in the engine 1972 Models, the reference points for longitudinally cowling and other similar openings shall have protec- leveling, are the two screws located on the left side tive covers installed to prevent entry of foreign mate- of the tailcone. Refer to figure 2-2 for screw loca- rial. After 30 days, aircraft should be flown for 30 tion. minutes or ground run-up until oil has reached oper- ating temperature. 2-6. PARKING. Parking precautions depend prin- cipally on local conditions. As a general precaution, CAUTION set parking brake or chock the wheels and install the controls lock. In severe weather and high wind con- Excessive ground operation shall be avoided. ditions, tie down the aircraft as outlined in paragraph 2-7 if a hangar is not available. 2-9. RETURNING AIRCRAFT TO SERVICE. After flyable storage, returning the aircraft to service is 2-7. TIE-DOWN. When mooring the aircraft in the accomplished by performing a thorough preflight open, head into the wind if possible. Secure control inspection. At the end of the first 25 hours of engine surfaces with internal control lock and set brakes. operation, drain engine oil, clean oil screens and change external oil filter element, if installed. Ser- CAUTION vice engine with correct grade and quantity of engine oil. Refer to figure 2-3 and paragraph 2-20 for cor- Do not set parking brakes during cold weather rect grade of oil. when accumulated moisture may freeze the brakes or when the brakes are overheated. 2-10. TEMPORARY STORAGE. Temporary storage is defined as aircraft in a non-operational status for After setting control lock and brakes, moor the air- a maximum of 90 days. The aircraft is constructed craft as follows: of corrosion resistant alclad aluminum, which will a. Tie ropes, cables or chains to wing tie-down last indefinitely under normal conditions, if kept clean. fittings located at upper end of each wing strut. Se- However, these alloys are subject to oxidation. The cure opposite ends to ground anchors. first indication of corrosion on unpainted surfaces is b. Secure rope (no chains or cables) to forward in the form of white deposits or spots. On painted mooring ring and secure opposite end to ground an- surfaces, the paint is discolored or blistered. Stor- chor. age in a dry hangar is essential to good preservation c. Secure middle of a rope to tail tie-down ring. and should be procured if possible. Varying condi- Pull each end of rope away at a 45 degree angle and tions will alter the measures of preservation, but secure to ground anchors at each side of tail. under normal conditions in a dry hangar, and for stor- d. If internal control lock is not available, tie pilot age periods not to exceed 90 days, the following control wheel back with front seat belt. methods of treatment are suggested. e. These aircraft are equipped with spring-loaded a. Fill fuel tanks with correct grade of gasoline. steering arms which afford protection against normal b. Clean and wax aircraft thoroughly. wind gusts. However, if extremely high wind gusts c. Clean any oil or grease from tires and coat are anticipated, additional external locks may be in- tires with a tire preservative. Cover tires to protect stalled. against grease and oil. d. Either block up fuselage to relieve pressure on 2-8. FLYABLE STORAGE. Flyable storage is de- tires or rotate wheels every 30 days to prevent flat fined as a maximum of 30 days non-operational stor- spotting the tires. age and/or the first 25 hours of intermittent engine e. Lubricate all airframe items.and seal or cover operation. all openings which could allow moisture and/or dust to enter. Change 5 2-3 NOTE engine is in storage. The aircraft battery serial number is recorded 2-11. INSPECTION DURING STORAGE. in the aircraft equipment list. To assure ac- a. Inspect airframe for corrosion at least once a curate warrant records, the battery should be month and remove dust collections as frequently as reinstalled in the same aircraft from which it possible. Clean and wax as required. was removed. If the battery is returned to b. Inspect the interior of at least one cylinder service in a different aircraft, appropriate through the spark plug hole for corrosion at least record changes must be made and notification once a month. sent to the Cessna Claims Department. NOTE f. Remove battery and store in a cool dry place; service the battery periodically and charge as re- Do not move crankshaft when inspecting in- quired. terior of cylinder for corrosion. NOTE -c. If at the end of the90 day period, the aircraft-is to be continued in non-operational storage, again per- An engine treated in accordance with the fol- form the procedural steps "g" thru "o" of paragraph lowing may be considered protected against 2-10. normal atmospheric corrosion for a period not to exceed 90 days. 2-12. RETURNING AIRCRAFT TO SERVICE. After temporary storage, use the following procedures to g. Disconnect spark plug leads and remove upper return the aircraft to service. and lower spark plugs from each cylinder. a. Remove aircraft from blocks and check tires for proper inflation. Check for proper nose gear strut NOTE inflation. (Refer to Section 1.) b. Check and install battery. The preservative oil must be Lubricating Oil- c. Check oil sump for proper grade and quantity of Contact and Volatile, Corrosion Inhibited, engine oil. MIL-L-46002, Grade 1 or equivalent. The d. Service induction air filter and remove warning following oils are approved for spraying op- placard from propeller. erations by Teledyne Continental Motors: e. Remove materials used to cover openings. Nude Oil 105-Daubert Chemical Co., 4700 f. Remove, clean and gap spark plugs. So. Central Ave., Chicago, Illinois; Petra- g. While spark plugs are removed, rotate propeller tect VA - Pennsylvania Refining Co., Butler, several revolutions to clear excess rust preventive Pennsylvania; Ferro-Gard 1009G-Ranco oil from cylinders. Laboratories, Inc. 3617 Brownsville Rd., h. Install spark plugs. Torque spark plugs to value Pittsburgh, Pennsylvania. specified in Section 11 and connect spark plug leads. i. Check fuel strainer. Remove and clean filter h. Using a portable pressure sprayer, spray pre- screen if necessary. Check fuel tanks and fuel lines servative oil through the upper spark plug hole of each for moisture and sediment. Drain enough fuel to cylinder with the piston in a down position. Rotate eliminate moisture and sediment. Torque bottom nut crankshaft as each pair of cylinders is sprayed. of strainer to 25-30 lb-in and safety wire to top as- i. After completing step "h, " rotate crankshaft so sembly of strainer. Wire must have right-hand wrap, that no piston is at a top position. If the aircraft is at least 45 degrees. to be stored outside, stop propeller so that blades as J. Perform a thorough pre-flight inspection, then near horizontal as possible to provide maximum clear- start and warm-up engine. ance with passing aircraft. j. Again spray each cylinder without moving the 2-13. INDEFINITE STORAGE. Indefinite storage is crankshaft to thoroughly cover all interior surfaces defined as aircraft in a non-operational status for an of the cylinder above the piston. indefinite period of time. Engines treated in accor- k. Install spark plugs and connect spark plug leads. dance with the following may be considered protected 1. Apply preservative oil to the engine interior by against normal atmosphere corrosion, provided the spraying approximately two ounces of the preserva- procedures outlined in paragraph 2-14 are performed tive oil through the oil filler tube. at the intervals specified. m. Seal all engine openings exposed to the atmos- a. Operate engine until oil temperature reaches phere using suitable plugs or non-hygroscopic tape. normal operating range. Drain engine oil sump and Attach a red streamer at each point that a plug or reinstall drain plug. tape is installed. b. Fill oil sump to normal operating capacity with n. If the aircraft is to be stored outside, perform corrosion preventive mixture which has been thor- the procedures outlined in paragraph 2-7. In addi- oughly mixed and pre-heated to a minimum of 221°F tion, the pitot tube, static source vents, air vents, at the time it is added to the engine. 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 effect that the propeller shall not be moved while the 2-4 Change 5 NOTE NOTE Corrosion preventive mixture consists of one The corrosion-preventive mixture is harmful part compount MIL-C-6529, Type I, mixed to paint and should be wiped from painted sur- with three parts new lubricating oil of the faces immediately. grade recommended for service. Continental Motors Corporation recommends Cosmoline o. Attach a warning placard on the throttle control No. 1223, supplied by E. F. Houghton & Co., knob, to the effect that the engine contains no lubri- 305 W. LeHigh Avenue, Philadelphia, Pa. cating oil. Placard the propeller to the effect that it During all spraying operation corrosion mix- should not be moved while the engine is in storage. ture is pre-heated to 221 ° to 250°F. p. Prepare airframe for storage as outlined in paragraph 2-10 thru step "f." c. Immediately after filling the oil sump with cor- rosion preventative mixture, fly the aircraft for a NOTE period of time not to exceed a maximum of 30 min- utes. As an alternate method of indefinite storage, d. With engine operating at 1200 to 1500 RPM and the aircraft may be serviced in accordance induction air filter removed, spray corrosion pre- with paragraph 2-10 providing the aircraft is ventive mixture into induction airbox, at the rate of run-up at maximum intervals of 60 days and one-half gallon per minute, until heavy smoke then reserviced per paragraph 2-10. comes from exhaust stack, then increase the spray until the engine is stopped. 2-14. INSPECTION DURING STORAGE. Aircraft in indefinite storage shall be inspected as follows: CAUTION a. Inspect cylinder protex plugs each 7 days. b. Change protex plugs if their color indicates an Injecting corrosion-preventive mixture too unsafe condition. fast can cause a hydrostatic lock. c. If the dehydrator plugs have changed color in one half of the cylinders, all desiccant material in the e. Do not rotate propeller after completing step engine shall be replaced with new material. "d." d. Every 6 months respray the cylinder interiors f. Remove all spark plugs and spray corrosion- with corrosion-preventive mixture. preventive mixture, which has been pre-heated to 221 ° to 250°F, into all spark plug holes to thorough- NOTE ly cover interior surfaces of cylinders. g. Install lower spark plugs or install solid plugs, Before spraying, inspect the interior of one and install dehydrator plugs in upper spark plug cylinder for corrosion through the spark holes. Be sure that dehydrator plugs are blue in plug hole and remove at least one rocker box color when installed. cover and inspect the valve mechanism. h. Cover spark plug lead terminals with shipping plugs (AN4060-1) or other suitable covers. 2-15. RETURNING AIRCRAFT TO SERVICE. i. With throttle in full open position, place a bag After indefinite storage, use the following procedure of desiccant in the carburetor intake and seal open- to return the aircraft to service. ing with moisture resistant paper and tape. a. Remove aircraft from blocks and check tires for j. Place a bag of desiccant in the exhaust tail- correct inflation. Check for correct nose gear strut pipe(s) and seal openings with moisture resistant inflation. tape. b. Check battery and install. k. Seal cold air inlet to the heater muff with mois- c. Remove all materials used to seal and cover ture resistant tape. openings. 1. Seal engine breather by inserting a protex plug d. Remove warning placards posted at throttle and in the breather hose and clamping in place. propeller. m. Seal all other engine openings exposed to atmos- e. Remove and clean engine oil screen, then re- phere using suitable plugs or non-hygroscopic tape. install and safety. On aircraft that are equipped with an external oil filter, install new filter element. NOTE f. Remove oil sump drain plug and drain sump. Install and safety drain plug. Attach a red streamer to each place plugs or tape is installed. Either attach red streamers NOTE outside of the sealed area with tape or to the inside of the sealed area with safety wire to The corrosion-preventive mixture will mix prevent wicking of moisture into the sealed with the engine lubricating oil, so flushing area. the oil system is not necessary. Draining the oil sump will remove enough of the cor- n. Drain corrosion-preventive mixture from engine rosion-preventive mixture. sump and reinstall drain plug. g. Service and install the induction air filter. h. Remove dehydrator plugs and spark plugs or plugs installed in spark plug holes and rotate pro- Change 5 2-5 peller by hand several revolutions to clear corrosion- be accomplished at temperatures below 30 0 F. preventive mixture from cylinders. i. Clean, gap, and install spark plugs. Torque NOTE plugs to the value listed in Section 11. j. Check fuel strainer. Remove and clean filter The aircraft is delivered from Cessna with a screen. Check fuel tanks and fuel lines for moisture corrosion preventative aircraft engine oil and sediment, and drain enough fuel to eliminate. (MIL-C-6529, Type II RUST BAN). If oil k. Perform a thorough pre-flight inspection, then must be added during the first 25 hours, use start and warm-up engine. only aviation grade straight mineral oil con- 1. Thoroughly clean aircraft and flight test air- forming to Specification MIL-L-6082. After craft. the first 25 hours of operation, drain engine oil sump and clean both the oil suction strainer 2-16. SERVICING. and the oil pressure screen if an optional full- flow oil filter is not installed. If an optional 2-17- Requireients are-shown-in-figure-2-3,-The- full-flow_oll filteriinstalled, change the fil- following supplements this figure by adding details. ter element (or optional spin-on oil filter).- Refill sump with aviation grade straight min- 2-18. FUEL. Fill tanks immediately after flight to eral oil and use until a total of 50 hours has lessen condensation. Fuel capacities are listed in accumulated or oil consumption has stabilized, Section 1 and fuel grades are shown in figure 2-3. then change to ashless dispersant oiL 2-19. FUEL DRAINS. Fuel drains are located at Newly-overhauled engines should also be various places throughout the fuel system. Refer to operated on aviation grade straight mineral Section 12 for location of the various drains in the oil until a total of 50 hours has accumulated system. The strainer drain valve is an integral part or oil consumption has stabilized. of the fuel strainer assembly. The strainer drain is equipped with a control which is located adjacent to When changing engine oil, remove and clean oil the oil dipstick. Access to the control is through the screens if aircraft is not equipped with an optional oil dipstick access door in the upper engine cowl. external oil filter. If the aircraft is equipped with Remove drain plugs and open strainer drain at the an external oil filter, install a new spin-on filter intervals specified in figure 2-3. Also, during daily or oil filter element. Refer to Section 11 for filter inspection of the fuel strainer, if water is found in applications and removal and installation. An oil the fuel strainer, there is a possibility that the wing quick-drain valve may be installed in the oil drain tank sumps or fuel lines contain water. Therefore, port of the oil sump. This valve provides a quick all fuel drain plugs should be removed and all water and cleaner method of draining the engine oil. To drained from system. To activate drain valve for fuel drain the engine oil proceed as follows: sampling, place cup up to valve and depress valve a. Operate engine until oil temperature is at nor- I with rod protruding from cup. (Refer to Section 12.) mal operating temperature. b. (With Quick-Drain Valve.) Attach a hose to the 2-20. ENGINE OIL. Check engine lubricating oil quick-drain valve in oil sump. Push up on quick- with the dipstick five to ten minutes after the engine drain valve until it locks open, and allow oil to drain has been stopped. The aircraft should be in as near through hose into container. a level position as possible when checking the engine c. (Without Quick-Drain Valve.) Remove oil drain oil, so that a true reading is obtained. Engine oil plug from oil sump and allow oil to drain into a con- should be drained while the engine is still hot, and tainer. the nose of the aircraft should be raised slightly for d. After oil has drained, close quick-drain valve more positive draining of any sludge which may have as shown in figure 2-2A and remove hose or reinstall collected in the engine oil sump. Engine oil should and safety oil drain plug. be changed every six months, even though less than the specific hours have accumulated. Reduce these intervals for prolonged operations in dusty areas, in Valve shown open. To elose, twist ~J cold climates where sludging conditions exist, or screwdriver until valve unlocks and where short flights and long idle periods are en- snaps down to closed position. countered, which cause sludging conditions. Always change oil and clean oil screens (when no full-flow oil filter is installed) whenever oil on the dipstick appears dirty. Ashless dispersant oil, conforming to Continental Motors Specification No. shall be used in these engines. Multi-viscosity oil may be used to extend the operating temperature range, improve cold engine starting and lubrication of the engine during the critical warm-up period, thus permitting flight through wider ranges of climate change without the necessity of changing oil. The multi-viscosity grades are recommended for aircraft engines subjected to wide variations in ambient air temperatures when cold starting of the engine must Figure 2-2A. Quick-Drain Valve 2-6 Change 5 e. Remove and clean oil screen, or change external NOTE oil filter in accordance with Section 11. f. Service engine with correct quantity and grade of The filtering panels of the filter may become engine oil. Refer to figure 2-3 and Section 11. distorted when wet, but they will return to their original shape when dry. 2-21. ENGINE INDUCTION AIR FILTER The engine induction air filter keeps dust and dirt from entering e. Be sure induction air box and air inlet ducts to the induction system. The value of maintaining the the engine are clean, inspect and replace filter if it induction air filter in a good clean condition can never is damaged. be overstressed. More engine wear is caused through f. Install filter as outlined in Section 11. the use of dirty and/or damaged air filters than is generally believed. The frequency with which the fil- 2-22. VACUUM SYSTEM FILTER. The vacuum sys- ter should be removed and cleaned will be determined ter central air filter keeps dust and dirt from enter- primarily by the airplane operating conditions. A ing the vacuum operated instruments. Inspect filter good general rule, however, is to remove, clean, every 100 hours for damage. Change central air filter and inspect filters at least every 50 hours of engine element every 500 hours of operating time and when- operating time and more frequently if warranted by ever suction gage reading drops below 4. 6 inches of operating conditions. Under extremely dusty condi- mercury. Also, do not operate the vacuum system tions, daily servicing of the filters is recommended. with the filter removed, or a vacuum line disconnected a. Remove filter from airplane as outlined in Sec- as particles of dust or other foreign matter may enter tion 11. the system and damage the gyros. b. Clean filter by blowing with compressed air (not over 100 psi) from direction opposite of normal air 2-23. BATTERY. Battery servicing involves add- flow. Normal air flow for the cylindrical filter is ing distilled water to maintain the electrolyte even from outside to inside, with the horizontal baffle plate at the bottom of the filler holes, checking the battery cable connections, NOTE and neutralizing and cleaning off and spilled electro- lyte or corrosion. Use bicarbonate of soda (baking Use care to prevent damage to filter element soda) and water to neutralize electrolyte or corro- when cleaning with compressed air. Never sion. Follow with a thorough flushing with water. use air pressure greater than 100 psi to clean Brighten cables and terminals with a wire brush, filter. then coat with petroleum jelly before connecting. The battery box also should be checked and cleaned c. After cleaning as outlined in step "b, " filter may ff any corrosion is noted. Distilled water, not acid be washed, if necessary, with a mild household deter- or "rejuvenators," should be used to maintain elec- gent and warm water solution. A cold water solution trolyte level. Check the battery every 50 hours (or may be used. at least every 30 days) oftener in hot weather. See Section 16 for detailed battery removal, installation CAUTION and testing. Do not use solvent or cleaning fluids to wash 2-24. TIRES. Maintain tire pressure at the air filter. Use only a mild household detergent pressures specified in Section 1. When checking and water solution when washing the filter. tire pressure, examine tires for wear, cuts, bruises, and slippage. Remove oil, grease and mud from NOTE tires with soap and water. The filter assembly may be cleaned with com- pressed air a maximum of 30 times or it may NOTE be washed a maximum of 20 times. The fil- ter should be replaced after 500 hours of en- Recommended tire pressures should be main- gine operation or one year, whichever should tained. Expecially in cold weather, remember occur first. However, the filter should be that any drop in temperature of the air inside replaced anytime it is damaged. A damaged a tire causes a corresponding drop in air pres- filter may have the perforated band broken on sure. the inside or the outside of the filter, or the filtering media may have sharp or broken 2-25. NOSE GEAR SHOCK STRUT. The nose gear edges. However, any filter that appears shock strut requires periodic checking to ensure doubtful should be replaced. that the strut is filled with hydraulic fluid and is inflated to the correct air pressure. To service the d. After washing, rinse filter in clean water until nose gear shock strut, proceed as follows: rinse water runs clear from filter. Allow water to a. Remove valve cap and release air pressure. drain from filter and dry with compressed air (not b. Remove valve housing. over 100 psi). Change 5 2-7 c. Compress nose gear to its shortest length and a. Remove shimmy dampener from aircraft. fill strut with hydraulic fluid to the bottom of the b. While holding the dampener in a vertical posi- filler hole. tion with fitting end pointed downward, pull fitting d. Raise nose of aircraft, extend and compress end of the dampener shaft to its limit of travel. strut several times to expel any entrapped air, then c. While holding dampener in this position, fill lower nose of aircraft and repeat step "c. " dampener through open end of cylinder with hydraulic e. With strut compressed, install valve housing fluid. assembly. d. Push the shaft upward slowly to seal off the f. With nose wheel off ground, inflate strut. Shock filler hole. strut pressure is listed in Section 1. e. Clean dampener with solvent. Be sure to keep the shaft protruding through the filler hole until NOTE dampener is installed on the aircraft. f. Install dampener on aircraft. The nose landing gear shock strut will nor- -- mally require only a minimum amount of ser NOTE vice. Maintain the strut extension pressure as shown in Section 1. Lubricate landing gear Keep the shimmy dampener, especially the as shown in figure 2-4. Check the landing exposed portions of the dampener piston gear daily for general cleanliness, security shaft clean to prevent collection of dust and of mounting, and for hydraulic fluid leakage. grit which could cut the seals in the dampen- Keep machined surfaces wiped free of dirt er barrel. Keep machined surfaces wiped and dust, using a clean lint-free cloth satu- free of dirt and dust, using a clean lint-free rated with MIL-H-5606 hydraulic fluid or ker- cloth saturated with MIL-H-5606 hydraulic osene. All surfaces should be wiped free of fluid or kerosene. All surfaces should be excess hydraulic fluid. wiped free of excess hydraulic fluid. 2-26. NOSE GEAR SHIMMY DAMPENER. The 2-27. HYDRAULIC BRAKE SYSTEMS. Check brake shimmy dampener should be serviced at least every master cylinders and refill with hydraulic fluid as I 50 hours. The shimmy dampener must be filled specified in the inspection charts. Bleed the brake completely with fluid, free of entrapped air, to system of entrapped air whenever there is a spongy serve its purpose. To service the shimmy damp- response to the brake pedals. Refer to Section 5 for ener, proceed as follows: filling and bleeding of the brakes. SHOP NOTES: 2-8 Change 5 2-28. CLEANING. period, the aircraft may be waxed with a good auto- motive wax. A heavier coating of wax on the leading 2-29. Keeping the aircraft clean is important. Be- edges of the wing and tail and on the engine nose cap sides maintaining the trim appearance of the aircraft, will help reduce the abrasion encountered in these cleaning lessens the possibility of corrosion and areas. makes inspection and maintenance easier. 2-33. ALUMINUM SURFACES. The aluminum sur- 2-30. WINDSHIELD AND WINDOWS. Windshield and 2-33. ALUMINUM SURFACES. The aluminum sur- windows should be cleaned carefully with plenty of be neglected. The aircraft may be washed with clean fresh water and a mild detergent, using the palm of water to remove dirt and may be washed with non- the hand to feel and dislodge any caked dirt or mud. alkaline grease solvents to remove oil and/or grease. A sponge, soft cloth, or chamois may be used, but Household type detergent soap powders are effective only as a means of carrying water to the plastic. cleaners, but should be used cautiously since some Rinse thoroughly, then dry with a clean moist cham- of them are strongly alkaline. Many good aluminum ois. Do not rub the plastic with a dry cloth as this cleaners, polishes, and waxes are available from builds up an electrostatic charge which attracts dUst. commercial suppliers of aircraft products. Oil and grease may be removed by rubbing lightly with a soft cloth moistened with Stoddard solvent. 2-34. ENGINE AND ENGINE COMPARTMENT. The engine should be kept clean since dirty cooling fins CAUTION and baffle plates can cause overheating of the engine. Also, cleaning is essential to minimize any danger of Do not use gasoline, alcohol, benzene, acetone, fire and provide for easier inspection of components. carbon tetrachloride, fire extinguisher fluid, The entire engine cowling may be removed to facili- de-icer fluid, lacquer thinner, or glass window tate engine and interior cowl cleaning. Wash down cleaning spray. These solvents will soften and the engine and components with a suitable solvent, craze the plastic. such as Stoddard solvent or equivalent, then dry thor- oughly witH compressed air. After washing, the plastic windshield and windows should be cleaned with an aircraft windshield cleaner.CAUTION Apply the cleaner with soft cloths and rub with mod- erate pressure. Allow the cleaner to dry, then wipe Particular care should be given to electri- it off with soft flannel cloths. A thin, even coat of cal equipment before cleaning. Solvent wax, polished out by hand with soft flannel cloths, should not be allowed to enter magnetos, will fill in minor scratches and help prevent further starters, alternators, voltage regulators, scratching. Do not use a canvas cover on the wind- and the like. Hence, these components shield or windows unless freezing rain or sleet is should be protected before saturating the anticipated since the cover may scratch the plastic engine with solvent. Any fuel, oil, and air surface. openings should be covered before washing the engine with solvent. Caustic cleaning 2-31. PLASTIC TRIM. The instrument panel, PlaS- solutions should not be used. After clean- tic trim, and control knobs need only be wiped with \ a damp cloth. Oil and grease on the control wheel r and control knobs can be removed with a cloth moist- and moving parts. ened with Stoddard solvent. Volatile solvents, such 2-35 UPHOLSTERY AND INTERIOR Keeping the as mentioned in paragraph 2-30, must never be used upholstery and interior trim clean prolongs uphol- since they soften and craze the plastic. stery fabric and interior trim life. To clean the in- 2-32. PAINTED SURFACES. The painted exterior teor proceed as follows: surfaces of the aircraft, under normal conditions, a. Empty all ash trays and refuse containers. require a minimum of polishing and buffing. Approxi- b. Brush or vacuum clean the upholstery and carpet mately 15 days are required for acrylic or lacquer to remove dust and dirt paint to cure completely; in most cases, the curing c. Wipe leather and plastic trim with a damp cloth. period will have been completed prior to delivery of d. Soiled upholstery fabrics and carpet may be the aircraft. In the event that polishing or buffing is cleaned with a foam-type detergent used according to the manufacturer's instructions. required within the curing period, it is recommended the manufacturer's nstructions. that the work be done by an experienced painter. hold spot removers, used sparingly. Before using washing with water and mild soap, followed by a any solvent, read the instructions on the container rinse with water and test t on an obscure place ing withe fabric to be rinse with water and drying with cloths or chamois cleaned. Never saturate the fabric with volatile sol- Harsh or abrasive soaps or detergents which could cause corrosion or make scratches should never be vent; it may damage the padding and backing material. f. Scrape sticky material from fabric with a dull used. Remove stubborn oil and grease with a cloth cr material from fabric with a dull moistened with Stoddard solvent. After the curing then spot clean the area Change 5 2-9 2-36. PROPELLER. Wash hub and blade with a presence of hard scale deposit. Previous wiping soft cloth and Stoddard cleaning solvent or equivalent, action will have exposed bare metal f no deposit is then dry thoroughly with compressed air. The pro- present. peller should be wiped occasionally with an oily cloth, e. If any of the preceding conditions exist, then wiped with a dry cloth. In salt water areas this clean and relubricate jack screw as outlined in steps will assist in corrosion proofing the propeller. "f" thru "o". f. Remove actuator from aircraft in accor- 2-37. WHEELS. The wheels should be washed per- dance with procedures outlined in Section 7. lodically and examined for corrosion, chipped paint, g. Remove all existing lubricant from jack and cracks or dents in the wheel halves or in the screw and torque tube by running the nut assembly flanges or hubs. If defects are found remove and re- to the end of the jack screw away from the gear box, pair in accordance with Section 5. Discard cracked and soaking the nut assembly and jack screw in Stod- wheel halves, flanges or hubs and install new parts. dard solvent. 2-38. LUBRICATION. - - -. - -NOTE- - 2-39. Lubrication requirements are shown in figure Care must be taken to prevent solvent from 2-4. Before adding grease to grease fittings, wipe entering gear box. The gear box lubricant dirt from fitting. Lubricate until grease appears is not affected and should not be disturbed. around parts being lubricated, and wipe excess grease from parts. The following paragraphs supplement h. After soaking, clean entire length of jack Ifigure 2-4 by adding details. screw with a wire brush, rinse with solvent and dry with compressed air. 2-40. TACHOMETER DRIVE SHAFT. Refer to Section 15 for details on lubrication of shaft. NOTE 2-41. WHEEL BEARINGS. Clean and repack the Do not disassemble nut and ball retainer as- wheel bearings at the first 100-hour inspection and sembly. at each 500-hour inspection thereafter. If more than the usual number of take-offs and landings are i. Relubricate jack screw with MIL-G- made, extensive taxiing is required, or the aircraft 21164 (Molybdenum Disulfide Grease) as outlined in is operated in dusty areas or under seacoast condi- steps "j" thru "m". tions, cleaning and lubrication of the wheel bearings j. Rotate nut down screw toward the motor. shall be accomplished at each 100-hour inspection. k. Coat screw and thread end of nut with grease and run nut to full extension. 2-42. NOSE GEAR TORQUE LINES. Lubricate nose 1. Repeat the process and pack lubricant gear torque links every 50 hours. When operating in in the cavity between the nut and ball retainer at the dusty conditions, more frequent lubrication is re- threaded end of the nut. quired. m. Repeat the process and work nut back and forth several times. 2-43. WING FLAP ACTUATOR. n. Remove excess grease. o. Reinstall actuator in aircraft in accor- a. On aircraft prior to FR17200298, not modified dance with procedures outlined in Section 7. by Service Kit SK150-37B or SK150-41, proceed as b. On aircraft prior to Serial FR17200298, which follows: have been modified by Service Kit SK150-37B, pro- 1. At each 100 hour inspection, inspect wing flap ceed as follows: actuator jack screw and ball retainer assembly for 1. At each 100 hour inspection, expose jack lubrication, and lubricate if required. Also, remove, screw by operating flaps to full-down position, and clean and lubricate jack screw whenever actuator slip- inspect wing flap actuator jack screw for proper lubri- page is experienced. If lubrication is required, pro- cation. If lubrication is required, proceed as follows: ceed as follows: a. Clean jack screw with solvent rag, if a. Gain access to actuator by removing ap- necessary, and dry with compressed air. propriate inspection plates on lower surface of wing. b. Relubricate jack screw with MIL-G-21164 b. Expose jack screw by operating flaps to (Molybdenum Disulfide Grease) as required. full-down position. c. On aircraft beginning with FR17200298, clean c. Wipe a small amount of lubricant from and lubricate wing flap actuator jack screw each jack screw with a rag and examine for condition. 100 hours as follows: (Lubricant should not be dirty, sticky, gummy or 1. Expose jack screw by operating flaps to full- frothy in appearance.) down position. d. Inspect wiped area on jack screw for 2. Clean jack screw threads with solvent rag and dry with compressed air. 2-10 Change 5 NOTE shaft for the following: a. Valve control detent plate for cleanliness and ex- It is not necessary to remove actuator from cessive wear. Dirt accumulation on this plate can aircraft to clean or lubricate threads. cause binding, poor detent feel and rapid wear of the plate. 3. With oil can, apply light coat of No. 10-weight, b. All drive shaft attach points for security, binding, non-detergent oil to threads of jack screw. excessive wear and lubrication, if required. c. Operate valve handle through all positions and 2-44. FUEL SELECTOR VALVE. At each 100-hour check for proper operation, detent feel and freedom of inspection, check the fuel selector valve and drive movement. SHOP NOTES: Change 5 2-10A Figure 2-3. Servicing (Sheet 1 of 4) i.... HYDRAULIC FLUID: SPEC. NO. MIL-H-5606 RECOMMENDED FUEL: ENGINE MODEL I0-360 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. 1. MINIMUM: 100/130 Aviation Grade 2. ALTERNATE: a. 115/145 Aviation Grade (with lead content limited to a maximum of 4.6 cc Tetraethyl lead per gallon. RECOMMENDED ENGINE OIL: ENGINE MODEL 10-360 Series CONTINENTAL AVIATION GRADE: Below 40°F SAE 30 Above 40°F SAE 50 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 2-20 Refer to Continental Engine Service Bulletin M75-2 and any other superseding bulletins, revisions or supplements thereto for further recommendations. NOTE Oil capacities for the aircraft are given in the following chart. To minimize loss of oil through the breather, fill to specified oil level on dipstick for normal operation (flight of less than three hours duration). For extended flight, fill to FULL mark on dipstick. Do not operate with less than MINIMUM-FOR-FLIGHT quantities listed. If an external oil filter is installed, one additional quart of oil is required when filter element is changed. CAPACITY CAPACITY (TOTAL NORMAL MINIMUM (TOTAL) WITH FILTER) OPERATION FOR FLIGHT 8 9 7 6 Figure 2-3. Servicing (Sheet 2 of 4) Change 5 2-11 DAILY 3 FUEL TANK FILLER Service after each flight. Keep full to retard condensation. Refer to paragraph 2-18 for details. 4 FUEL TANK SUMP DRAINS If quick-drain valves are installed, drain off any water and sediment before first flight of the day. 6 PITOT AND STATIC PORTS -- - Check-for-obstructions before first flightof the day. 10 FUEL STRAINER Drain off any water and sediment before the first flight of the day. Refer to paragraph 2-19 for details. 13 INDUCTION AIR FILTER Inspect and service under dusty conditions. Refer to paragraph 2-21 for details. 16 OIL DIPSTICK Check oil on preflight. Add oil as necessary. Refer to paragraph 2-20 for details. 18 OIL FILLER CAP Whenever oil is added, check that filler cap is tight and oil filler door is secure. FIRST 25 HOURS 15 17 ENGINE OIL SYSTEM Refill with straight mineral oil, non-detergent, and use until a total of 50 hours has accumulated or oil consumption has stabilized, then change to ashless dispersant oil. 50 HOURS 13 INDUCTION AIR FILTER Clean filter per paragraph 2-21. Replace as required. 14 BATTERY Check electrolyte level and clean battery compartment each 50 hours or each 30 days. 15 17 ENGINE OIL SYSTEM Change oil each 50 hours if engine is NOT equipped with external oil filter; if equipped with external oil filter, change filter element each 50 hours and oil at each 100 hours, or every 6 months. 12 SHIMMY DAMPENER Check fluid level and refill as required with hydraulic fluid. Refer to paragraph 2-26. 7 TIRES Maintain correct tire pressure as listed in chart of Section 1. Also refer to paragraph 2-24 for details. Figure 2-3. Servicing (Sheet 3 of 4) 2-12 Change 5 50 HOURS (Cont) 11 NOSE GEAR SHOCK STRUT Keep strut filled and inflate to correct pressure. Refer to paragraph 2-25 for details. 100 HOURS 10 FUEL STRAINER Disassembly and clean strainer bowl and screen. . 200 HOURS 1 VACUUM RELIEF FILTER Change each 1000 hours, or to coincide with engine overhauls. 4 FUEL TANK SUMP DRAINS If quick-drain valves are not installed, remove plugs and drain off water or sediment. Reinstall plugs and safety. Also refer to paragraph 2-19. 5 SELECTOR VALVE DRAIN Remove plug and drain off any water or sediment. Also refer to paragraph 2-19. 9 BRAKE MASTER CYLINDERS Check fluid level and refill as required with hydraulic fluid. Refer to paragraph 2-27. 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 11 for details. Figure 2-3. Servicing (Sheet 4 of 4) Change 5 2-13 FREQUENCY (HOURS) METHOD OF APPLICATION HAND GREASE OIL SYRINGE GUN CAN (FOR POWDERED GRAPHITE) WHERE NO INTERVAL IS SPECIFIED, LUBRICATE AS REQUIRED AND WHEN ASSEMBLED OR INSTALLED. NOTE - - - The-military-specifications-Usted-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 ........... MOLYBDENUM DISLULFIDE GREASE OG- MIL-L-7870A ........... GENERAL PURPOSE OIL PL- W-P-236 ............. PETROLATUM GS- MIL-S-8660 ............ DC4 DOW CORNING cG-. ................. NO. 10-WEIGHT, NON-DETERGENT OIL STEERING SYSTEM - ALSO REFER TO NEEDLE PARAGRAPH 2-42-" BEARINGS ALSO REFER TO PARAGRAPH 2-41 SHIMMY DAMPENER PIVOTS TORQUE LINKS PARAGRAPH 2-41 STEERING ARM BEARING MAIN GEAR WHEEL BEARINGS WHEEL BEARINGS NOSE GEAR Figure 2-4. Lubrication (Sheet 1 of 3) 2-14 Change 5 - CONTROL WHEEL SHAFT BUSHINGS AND UNIVERSALS OILITE BEARINGS *BUSHINGS AND ELEVATOR TRIM TAB -ACTUATOR ALSO REFER TO INSPECTION CHART IN THIS SECTION AND TO SECTION 9 OF THIS MANUAL P BATTERY NEEDLE BEARINGS CONTROL "U" PG ALL PIANO HINGES FUEL SELECTOR AILERON BELLCRANK DRIVE SHAFT NEEDLE BEARINGS ATTACH POINTS GR REFER TO . REFER TO PARAGRAPH 2-44 CABIN DOOR WINDOW DOORSTOP INSERT GROOVES Figure 2-4. Lubrication (Sheet 2 of 3) Change 5 2-15 ALL LINKAGE OILITE BEARINGS POINT PIVOTS NEEDLE (RUDDER BAR ENDS) BEARINGS RUDDER BARS AND PEDALS - - STRUT-ATTACH BOLTS ELECTRIC FLAP DRIVE MECHANISM REFER TO SCREW JACK -SCREW JACK PARAGRAPH 2-43 THREADS - 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, Ollite 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) 2-16 Change 5 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. I 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 n 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. Change 5 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 III1. (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, securityof 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 3 (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 5 2-19 SPECIAL INSPECTION ITEM IMPORTANT EACH 200 HOURS READ ALL INSPECTION REQUIR- EACH 100 HOURS MENTS PARAGRAPHS PRIOR TO EACH 50 HOURS USING THESE CHARTS.EACH 50 HOUR PROPELLER. 1. Spinner ................................. 2. Spinner bulkhead ........... . ...... ... 3. Blades .. . . --.-.-. . -.- ....- - 4. Bolts and/or 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, filler cap, dipstick, drain plug and oil screen (or external full-flow oil filter) ..................... ... . 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 ...................... .... . 11. Ignition harness . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12. Spark plugs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 13. Compression check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14. Crankcase and vacuum system breather lines ... ... ............. 15. Electrical wiring .... . . . . . . . . . . . . . . . . . . . . . . . . . . . 16. Vacuum pump and oil separator ................. ........ 17. Vacuum relief valve filter (cabin area) ................ ....... . . . 18. Engine controls and linkage .. . ... .. ........ . . . .... .. 19. Engine shockmounts, mount structure and ground straps ....... 2-20 Change 5 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 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. Firewall ....................................................................... 29. Fuel-air (metering) control unit ................................................... 30. Fuel injection system ......... .................................................. 31. Auxiliary fuel pump ............................................................. · 32. Engine-driven fuel pump ........................................................ · 33. Engine cowling and cowl flaps ................................................... FUEL SYSTEM 1. Fuel strainer, drain valve and control ............................ .............. ... · 2. Fuel strainer screen and bowl .................................................... · 3. Fuel, tank vents, caps, and placards .............................................. · 4. Fuel bays, sump drains, and fuel line drains ................................. ..... 5. Drain fuel and check bay interior, attachment and outlet screens...................... 5 6. Fuel vent valves ............................................................... 7. Fuel vent line drain ............................................................. 8. Fuel shut-off valve and placard ................................................... 9. Fuel selector valve and placard ......................................... ......... 10. Engine primer .............................................................. · 11. Perform a fuel quantity indicating system operational test. Refer to Section 15 for detailed accomplishment instructions ................................ 15 12. Fuel injection nozzles ........................................................... 16 LANDING GEAR 1. Main gear wheels and fairings ................................................... 2. Nose gear wheel, torque links, steering tubes, boots and fairings ..................... 3. W heel bearings ................................................................ 9 D849-5-13 Temporary Revision Number 4 - Apr 5/2004 2-21 © Cessna Aircraft Company SPECIAL INSPECTION ITEM EACH 200 HOURS EACH 100 HOURS EACH 50 HOURS 4. Nose gear strut and shimmy dampener (service as required) ......................... 5. Tires ........................................ .............................. e 6. Brake fluid, lines and hoses, linings, discs, brake assemblies and master cylinders...... 7. Parking brake system .......................................................... 8. Main gear springs .............................................................. 9. Nose gear steering arm lubrication ............................................... 10. Torque link lubrication ............... ......... .......................... 11. Parking brake and toe brakes - operational test ......... ........................... AIRFRAME 1. Aircraft exterior ................................................................ 2. Aircraft structure ............................................................... 3. Windows, windshield, doors and seals ............................................ 4. Seat belt and shoulder harness .................................................. 5. Seat stops, seat rails, upholstery, structure and mounting ............................ 6. Control "U" bearings, sprockets, pulleys, cables, chains and turnbuckles ............... 7. Control lock, control wheel and control "U" mechanism .............................. 8. Instruments and markings ......... .............................................. 9. Gyros central air filter ........................................................... 10 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 system controls ................................. 14. Cabin upholstery, trim, sun visors and ashtrays .................................... 15. Area beneath floor, lines, hoses, wires and control cables ........................... 16. Lights, switches, circuit breakers, fuses, and spare fuses ............................ 17. Exterior lights ................................................................... 18. Pitot and static systems ......................................................... 19. Stall warning system ........................................................... 0 2-22 Change 5 SPECIAL INSPECTION ITEM EACH 200 HOURS EACH 100 HOURS EACH 50 HOURS 20. Radios, radio controls, avionics and flight instruments ............................... 21. Antennas and cables .................................................... 22. Battery, battery box and battery cables ............................................ 23. Battery electrolyte ......... ......... ................................... 11 24. Emergency locator transmitter ................................................... 12 25. Inspect all fluid-carrying lines and hoses in the cabin and wing areas for leaks, damage, abrasion, and corrosion ......................................... 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 ............................................................ 6. Flap control switch, flap rollers and tracks, and flap indicator ......................... 7. Flap motor, transmission, limit switches, structure, linkage, bell cranks, etc............. 8. Elevator and trim tab hinges and control rods ...................................... 9. Elevator trim tab actuator lubrication and tab free-play inspection ..................... 13 10. Rudder pedal assemblies and linkage ............................................. 11. Skins (external) of control surfaces and tabs ...................................... . 12. Internal structure of control surfaces ............................................. 13. Balance weight attachment ................. ................... .................. 14. Flap actuator jackscrew threads ................. .......................... 14 Change 3 2-23 SPECIAL INSPECTION ITEM 1. Deleted. 2. Clean filters per paragraph 2-21. Replace as required. 3. Replace hoses at engine overhaul or after 5 years, whichever comes first. 4. General inspection every 50 hours. Refer to Section 11 for 100-hour inspection. 5. Each 1000 hours, or to coincide with engine overhauls. 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 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 each 30 days. 12. Refer to Section 16 of this Manual. 13. Lubrication of the actuator is required each 1000 hours and/or 3 years, whichever comes first. Refer to figure 2-4 for grease specifications. Refer to Section 9 of this manual for free-play limits, inspection, replacement and/or repair. 14. Refer to paragraph 2-43 for detailed instructions for various serial ranges. 15. Fuel quantity indicating system operational test is required every 12 months. Refer to Section 15 for detailed accomplishment instructions. 16. At the first 100-hour inspection on new, rebuilt or overhauled engines, remove and clean the fuel injection nozzles. Thereafter, the fuel injection nozzles must be cleaned at 300-hour intervals or more frequently if fuel stains are found. 2-24 D849-5-13 Temporary Revision Number 4 - Apr 5/2004 © Cessna Aircraft Company