1985 Thru 1986 Model P210 Service Manual

2-22 Blank ........ ................... 0 13-228 Blank .. .................... 2 2-23 thru 2-26 .......... ........... 1 13-23 .............. 0.... 0 *2-27 thru 2-39 .... ............. ..... 2 13-24 .... . ..... .................. 2 2-40 thru 2-43 ......... ................ 1 13-25 thru 13-27 .............. ....... . 0 *2-44 thru 2-81 ................. ...... . 2 13-28 Blank . ............... .......... 0 2-82 Blank ............. ....... ........ 2 14-1 thru 14-7 ................ ........ 0 3-1 thru 3-5 ........ ... ................ 0 14-8 Blank .............. ............... 0 3-5A ...... . . .. . ........... 0 15-1 thru 15-7 .......... ..... ... . ... . 0 3-58B Blank ............. ......... ....... 0 15-8 .......................... ...... 2 3-6 thru 3-20 ............ ....... ........ 0 15-9 thru 15-14 ............... ......... 0 3 -2 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 1 15 -15 . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . 0 3-22 thru 3-28 .......................... 0 15-16 ................... .. ... .... 2 4-1 thru 4-6 . ........ .......... . ... 0 15-17 thru 15-27 .... ............. . .... 0 *5-1 thru 5-3 ............................ 2 15-28 ............................... 2 5-4 thru 5-6 . .. ..... .. .... . 0 15-29 thru 15-66 ........................ 0 *5-7 .......... ...... .................. 2 15-67 .......... .......... ..... 2 5-8 thru 5-10 ........................... 0 15-68 .................. .............. 0 *5-11 thru 5-16 .......................... 2 15-69 thru 15-70 ........................ 2 5-17 thru 5-22 . ... .. ..... .......... 0 15-71 thru 15-72 ........................ 0 *5-23 thru 5-26 .......................... 2 15-73 ......... 2... ............ 2 5-26A thru 5-26C .................... ... 2 15-74 thru 15-76 ........................ 0 *5-26D B lank ..... .. .... .. .. .. .. . .. .... .. 2 16-1 .... ... ...... .. ...... . . ..... . .... 2 5-27 thru 5-28 .... ..................... 0 16-2 thru 16-21 ......................... 0 *5-29 -. 2 51-8 ................ .......... *5 -29 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 2 16 -22 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 5 -30 . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . 0 16 -23 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0 *5-31 thru 5-36 .... ..................... 2 16-24 thru 16-26 ........................ 2 5-37 thru 5-51 ........................ 0 16-26A thru 16-26B ..................... 2 *5-52 ........... ........ .............. 2 16-27 thru 16-37 ........................ 0 5-53 thru 5-54 ..... ... ................ 0 16-38 Blank ............................ 0 5-55 ................................. 2 17-1 ................................. 0 5-56 . . . . . ... .. . .. . .. ... . . . .. . . . .. . . . . 0 17 -2 .. . . . . . . . .. . . . .. . . . . . . .. .. . . . .. . 2 *5-57 thru 5-58 .......................... 2 17-3 thru 17-45 ......................... 0 5-59 thru 5-60 ..... ..... ... ...... .. 0 *17-46 thru 17-49 ........................ 2 *61 - -. 2 17-50 thru 17-51 ..................... 0... *6-1 .. . .. .............. ........ ...... 2 17-50 thru 17-5 1 .. ........ ............. 0 6-2 thru 6-8 ............................ 0 17-52 Blank ............................ 0 *6-9 .. . ........ .... .. .. .. .... ... ..... . 2 18-1 thru 18 -39 ..... .. .... .. . ....... .... 0 6-10 .. . ....... ........ . ..... ....... .. 0 18-40 B lank . .. ... ....... .. .. ..... . ... . 0 7-1 thru 7-9 ................... ........ 0 19-1 thru 19-3 .......................... 0 7-10 Blank ............................. 0 19-4 Blank ............................. 0 8-1 thru 8-3 ........................... 0 20-1 thru 20-50 ......................... 0 *8-4 .... ............................. 2 20-50A thru 20-50B ................... ... 0 8-5 thru 8-7 ........................... 0 20-51 thru 20-56 ........................ 0 8-8 B lank .............................. 0 20-56A ............................... 0 9-1 thru 9-12 .......................... 0 20-56B Blank ........................... 0 10-1 thru 10-8 ............ ............... 0 20-57 thru 20-90 ........................ 0 A Revision 2 MODEL P210 SERIES SERVICE MANUAL SECTION Page No. Aerofiche/Manual 1. GENERAL DESCRIPTION ............ ..................................... 1A7/1-1 2. GROUND HANDLING, SERVICING, CLEANING, LUBRICATION, AND INSPECTION ............................................ 1B5/2-1 3. FUSELAGE .................................................................. 1E23/3-1 4. WINGS AND EMPENNAGE ................................................... 1G9/4-1 5. LANDING GEAR, BRAKES AND HYDRAULIC SYSTEM ............................ 1G19/5-1 6. AILERON CONTROL SYSTEM ................................................. 1J11/6-1 7. WING FLAP CONTROL SYSTEM ............................................... 1K1/7-1 8. ELEVATOR CONTROL SYSTEM ................................................ 1K15/8-1 9. ELEVATOR TRIM CONTROL SYSTEM ......................................... 1 L3/9-1 10. RUDDER CONTROL SYSTEM .................................................. 2A3/10-1 11. RUDDER TRIM CONTROL SYSTEM ........................................ .... 2A15/11-1 12. ENGINE NORMALLY ASPIRATED .............................................. 2A23/12-1 13. FUEL SYSTEM ................................................................ 2D5/13-1 14. PROPELLERS AND PROPELLER GOVERNORS ................................... 2F15/14-1 15. UTILITY SYSTEMS ........................................................... 2F3/15-1 16. INSTRUMENTS AND INSTRUMENT SYSTEMS ................................... 2111/16-1 17. ELECTRICAL SYSTEMS ....................................................... 3A3/17-1 18. STRUCTURAL REPAIR ........................................................ 3C11/18-1 19. EXTERIOR PAINTING ........................................................ 3E7/19-1 20. WIRING DIAGRAMS ......................................................... 3E15/20-1 WARNING When performing any inspection or maintenance that re- quires turning on the master switch, installing a battery, or pulling the propeller through by hand, treat the prop- eller as if the ignition switch were ON. Do not stand, nor allow anyone else to stand, within the arc of the propel- ler, since a loose or broken wire, or a component mal- function, could cause the propeller to rotate. Revision 2 i MODEL P210 SERIES SERVICE MANUAL CROSS REFERENCE LISTING OF POPULAR NAME VS. MODEL NUMBERS AND SERIALS All aircraft, regardless of manufacturer, are certified under model number designations. However, popular names are often used for marketing purposes. To provide a consistent method of referring to these aircraft, 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 and serial number. MODEL SERIAL POPULAR NAME YEAR MODEL BEGINNING ENDING PRESSURIZED CENTURION 1985 P210R P21000835 P21000866 PRESSURIZED CENTURION WITH VALUE GROUPS A & B 1986 P210R P21000867 P21000874 ii Revision 2 MODEL P210 SERIES SERVICE MANUAL INTRODUCTION This manual contains factory-recommended procedures and instructions for ground handling, servicing, and maintaining the airplane. Besides serving as a reference for the experienced mechanic, this book also covers step-by-step procedures for the less experienced. This service manual is designed for aerofiche presentation. To facilitate the use of the aerofiche, refer to the aerofiche header for basic information. IMPORTANT INFORMATION CONCERNING KEEPING CESSNA PUBLICATIONS CURRENT 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, 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 the Cessna 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. Supplier's 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 is communicated to the field through Cessna's Authorized Service Stations and/or through Cessna's subscription services. 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, RE- MANUFACTURED, 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 IN- SPECTION, LIFE LIMITS, CYCLE LIMITS, ETC., FOR SUCH NON-CESSNA PARTS MUST BE OBTAINED FROM THE MANUFACTURER AND/OR SELLER OF SUCH NON-CESSNA PARTS. REVISIONS. 1. Revisions/changes are issued as required and include only pages that require updating. REISSUE. 1. A reissued manual is a complete manual incorporating all the latest information and outstanding revisions and temporary revisions. It supersedes and replaces previous issue(s) of the manual. CHANGES / REVISIONS and REISSUES. 1. Individual copies can be purchased from your Cessna Service Station or directly from Cessna Parts Distribution, Dept. 701, Cessna Aircraft Company, P.O. Box 949, Wichita, KS. 67201 (walk-in address: 5800 East Pawnee, Wichita, Kansas 67218). 2. Subscriptions, service bulletin listings, revision status checkcards and temporary revisions may be purchased through Propeller Aircraft Product Support, P.O. Box 7706, Wichita, KS. 67277, phone (316) 941-7674 or fax (316) 942-9006. Revision 2 MODEL P210 SERIES SERVICE MANUAL TEMPORARY REVISIONS. 1. Additional information which becomes available may be provided by temporary revisions. This service is used to provide, without delay, new information which will assist in maintaining safe flight/ground operations. Temporary revisions are designed to replace or add to existing pages in the manual and are numbered to match pages in the manual. Temporary revisions are normally incorporated into this manual at the next scheduled change, revision or reissue. REVISION BARS. 1. Additions, or revisions to text in an existing section will be identified by a revision bar on the page adjacent to the change. 2. When technical changes cause unchanged text to appear on a different page/pages, a revision bar will be placed in the margin opposite the page number of all affected pages providing no other revision bar appears on the page. 3. When extensive technical changes are made to text in an existing section that requires a complete retype of copy, revision bars will appear the full length of the page. 4. When art in an existing illustration is revised, a pointing hand will appear in the illustration and will point to the area of the art revision. 5. New art added to an existing section will be identified by a single pointing hand adjacent to the figure title and figure number. 6. Revision bars are not shown for: a. Introductory material, indexes and tabular data. b. Blank spaces which are the result of text, illustration or table deletion. c. Correction of minor inaccuracies, such as punctuation, etc., unless such a correction changes the meaning of instructive information and procedures. CUSTOMER CARE SUPPLIES AND PUBLICATIONS CATALOG. A Customer Care Supplies and Publications Catalog is available from your Cessna Service Station or directly from Cessna Propeller Aircraft Product Support, P.O. Box 7706, Wichita, KS. 67277, phone (316) 941-7950 or fax (316) 942-9006. This catalog lists all publications and Customer Care Supplies available from Cessna for prior year models as well as new products. To maintain this catalog in a current status, it is revised yearly and issued in paper and Aerofiche format. SUPPLEMENTAL TYPE CERTIFICATE INSTALLATIONS. Inspection, maintenance and parts requirements for supplemental type certificate (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 installations. CUSTOMER COMMENTS ON MANUAL. Cessna Aircraft Company has endeavored to furnish you with an accurate, useful, up-to-date manual. This manual can be improved with your help. Please use the Customer Comment Card provided with your manual, to report any errors, discrepancies, and omissions in this manual as well as any general comments you wish to make. iv Revision 2 MODEL P210 SERIES SERVICE MANUAL SECTION 1 GENERAL DESCRIPTION Page No. TABLE OF CONTENTS Aerofiche/Manual GENERAL DESCRIPTION ......... 1A7/1-1 SAFETY WIRE PROCEDURES ..... 1A14/1-8 PRESSURIZED CENTURION ... 1A7/1-1 USE OF COTTER PINS .......... 1A18/1-12 Description 1A7/1-1 USE OF LOCKING CLIPS ..... 1A20/1- 14 Aircraft Specifications 1A7/1-1 USE OF LOCKWASHERS .......... 1A20/1-14 Stations .................... 1A7/1-1 USE OF SELF-LOCKING NUTS ..... 1A20/1-14 GENERAL AIRFRAME PRACTICES 1A10/1-4 CONTROL CABLE WIRE BREAKAGE TORQUEING PROCEDURES ....... 1A10/1-4 AND CORROSION Calculating Torque ............. 1A10/1-4 LIMITATIONS 1A22/1-16 Torque Values - Bolts ........... 1A10/1-4 ADHESIVES, CEMENTS AND Torque Values - Fittings ......... 1A13/1-7 SEALANTS-SHELF LIFE SAFETYING PROCEDURES ....... 1A14/1-8 AND STORAGE .............. 1A24/1-18 1-1. GENERAL DESCRIPTION. 1-4. AIRCRAFT SPECIFICATIONS. Leading parti- 1-2. MODEL 210 SERIES. culars of these airplanes, with dimensions based on gross weight, are given in figure 1-1. If these dimen- 1-3 DESCRIPTION. The Cessna Pressurized, sions are used in computing clearance for construction of Centurion and Centurion II (P210 Series) Airplanes a hanger or other shelter, it should be noted that strut described in this manual, are high-wing, single- engine, inflation, tire pressure, tire size, and load distribution monoplanes of all metal, semi-monocoque construction. will change some dimensions significantly. Wings are full cantilever with integral fuel bays (wet wing). The fully retractable landing gear consists of 1-5. STATIONS. A station diagram is shown in fig- tubular-spring steel main gear struts, and a steerable ure 1-2 to assist in locating equipment when a written air/hydraulic nose gear strut. Seating arrangement is description is inadequate or impractical. six place conventional. Powering the Pressurized Centurion Series is a Continental, air-cooled, horizontally-opposed, six-cylinder, fuel-injected, turbocharged engine, driving a constant speed, three blade propeller. The pressurization system is designed for maximum passenger comfort at altitudes up to airplane ceiling, by maintaining a 3.35 psi maximum cabin pressure, or the equivalent to a 10,000 ft cabin altitude at 20,000ft actual. Revision 1 1-1 MODEL P210 SERIES SERVICE MANUAL P210 SERIES 25.25 68. 00 accuracy; and recheck frequently. () Bolts, nuts, and screws used in control 2. When using a torque wrench adapter which systems and installations where required torque changes distance from torque wrench drive to adapter would cause binding or interfere with proper opera- drive, the indicated reading must be adjusted for tion of parts. desired torque reading. (See Figure 1-2.) (d) Screws used with dimpled washers should 3. Be sure that bolt and nut threads are clean not be drawn tight enough to elminate washer and dry unless otherwise specified. crown. 4. Determine friction drag torque and add to (e) Fasteners that hive a specified torque in a specified dry torque value to ensure proper bolt utili- specific installation. zation. 2. The values shown in Table 1-1 are based on (a) Hand-turn nut onto bolt until it stops. parts being clean and dry with no lubricants added. (b) Using a torque wrench, measure running 3. Castellated nuts requiring cotter pins should torque (torque required to turn nut on bolt). be tightened to low torque value. Torque can be in- (c) This running torque must be added to creased to install cotter pin, but should never exceed specified dry torque value to ensure proper bolt utili- maximum torque value. zation. NOTE EXAMPLE Self-locking castellated nuts, MS17825 and Average running torque for a nut = 15 in.-lbs. MS17826, require a separate torque range. y torque _ _ .= 125 5 in.-lbs. These values are shown separately in torque Final Torque wrench reading = 140 5 in.-lb. value tables. 1-4 MODEL P210 SERIES SERVICE MANUAL NOTE When using a torque wrench adapter which changes the distance from torque wrench drive to adapter drive, apply following formula to obtain corrected torque reading. SHORT OPEN END ADAPTER FORMULA LEGEND T = Desired Torque MODEL P210 SERIES SERVICE MANUAL c. Torque Value - Threaded Straight Fittings. (b) Turn nut down until packing is firmly NOTE against lower threaded section of fitting. (c) Install fitting into boss and tighten until Tables in this section are for general applica- there is a sudden increase in torque. tions. Refer to specific installations for special (d) Tighten fitting 1-l/2 turns. torque values and procedures. (e) Orientation is accomplished by tightening fitting, but not exceeding one turn. 1. Connectors installed in bosses with no re- (f) Tighten jam-nut to torque values in Table quired orientation should be installed using torque 1-2. values given in Table 1-2. 3. Bulkhead fittings are installed with jam-nuts and should be torqued to values in Table 1-2. 4. Torque values for hose end fittings (nipple or THREADED CONNECTOR nut) are given in Table 1-3. TUBE JAM-NUT CONNECTOR OUTSIDE THREAD w/ PACKING TORQUE VALUE - HOSE ASSEMBUES DIAMETER w/o JAM-NUT (Inches) Torqu-Limits Torque-Limits HOSE Nipple Nut (in.-Ibs.) (lbs.) INSIDE ALUMINUM STEEL MIN. I MAX. MIN. MAX. DAMETER Torque-limits Ti.-smit 1/8 5/16-24 35 50 50 55 MIN. MAX.MIN. MAX. 3/16 38-24 65 80 65 75 8 20 7 1/8 20 30 75 85 1/4 7/16-20 85 105 95 10516 25 35 95 105 5/16 1/2-20 105 125 125 135 1/ 5 65 15 105 3/1 9/16-18 120 150 155 165514 0 65 35 150 5/16 70 90 170 200 1/2 3/4-16 240 280 280 30516 110 10 270 200 5/8 7/7-14 320 380 380 4052 230 260 450 500 3/4 1/16-12 500 600 550 600 330 60 650 700 1 1-5/16.12 720 880 800 900 1 1-6/16-12 720 880 800 D3/4 460 500 900 1000 1-1/4 1-5/-12 960 1200 900 100 1 1200 1400 1-1/2 1-7/8-12 1200 1440 900 1000 1-14 900 1520 10 2 2-1/2-12 1400 1500 900 1000 112 8 9 19 2100 I 1 1-3/4 - - - - Table 1-2. Torque Values 2 1800 2000 2660 2940 Jam-Nuts and Threaded Connector 2. Connectors installed in bosses requiring a Table 1-3. Torque Values specifc orientation do not use a torque value, but Hose Assemblies use the following steps: (a) Place jam-nut on fitting along with re- 5. Torque values for straight threaded fittings tainer and packig. used with rigid lines are given in Table 1-4. 1-7 MODEL P210 SERIES SERVICE MANUAL THREADED STRAIGHT FITTING TORQUE VALUE (RIGID TUBE) FLARED END STRAIGHT END TUBE ALUMINUM ALUMINUM STEEL 6061- ALUMINUM STEEL 6061-T(XI ALUMINUM MODEL P210 SERIES SERVICE MANUAL ches; or. on parts with tie hole diameters between NOTE 0.045 and 0.062 when spacing between ports is less than two inches; or. when bolts and screws of 0.25- Widely spaced multiple groups shall mean those inch diameter or less are closely spaced. in which fasteners are from four to six inches (c) 0.032-inch minimum diameter wire is used apart. Lockwiring shall not be used to secure for general purpose lockwiring. fasteners or fittings which are spaced more NOTE than six inches apart, unless tie points are pro- vided on adjacent parts to shorten span of When using single-wire method of locking, the lockwre to less than six inches. largest wire that will fit tie holes should be 5. When lockwiring closely spaced multiple used. groups, the number of units that can be lockwired b. Lockwire Installation. There are two basic forms by a 24-inch length of wire shall be the maximum of lockwiring. The single-wire method has limited number in a series. application; the double-twist method is the common 6. Parts should be lockwired so that wire is method of lockwiring. placed in tension (pulled on) if a part attempts to 1. Use new wire for each application; do not try loosen. to re-use old wire. c. Required Lockwire Installation Applications. 2. Single-wire method is accomplished by pas- 1. Bolts and other fasteners securing critical sing a single wire through tie holes and back with parts that affect airplane safety and operation. ends then twisted together. (See Figure 1-4.) (a) In blind-tapped hole applications or bolts or (a) Single-wire method is used for shear and castellated nuts on studs, lockwiring is installed in seal wiring applications. same manner as described for bolt heads. (b) Single-wire method can be used in closely (b) ' Hollow head bolts are safetied in manner spaced, closed geometric patterns. Closely spaced is prescribed for regular bolts. defined as spacing two inche or less between cen- (c) Drain plugs and cocks may be safetied to a ter of parts. bolt, nut, or other part having a free tie hole in CAUTION accordance with instructions described. (d) External snap rings may be locked if nec- Screws in cloely spaced geometric patterns esary using general locking principles as de- which secure hydraulic or air seals, hold hy- scribed and illustrated. Internal snap rings should draulic pressure, or are used in critical areas not be lookwired. should use double-twist method of lockwiring. (e) When locking is required on electrical connectors which use threded coupling rings, or 3. Lockwiring by the double-twist method is on plugs which employ screw or rings to fasten really one wire twisted on itself several times and is individual parts of plug together, they shall be accomplished by the following steps (see Figure 1- lockwired with 0.020-inch diameter wire in accor- 4) dance with locking principles as described and (a) Insert one end of wire through tie holes of illustrated. It is preferable to lockwre all electrical bolt head and firmly loop around bolt head. connectors individually. Do not lockwire one con- nector to another unless it is necessary to do so. NOTE (f) Drilled head bolts and screws need not be lookwired if installed into self-locking nut or in- This does not necesarily apply to castellated stalled with lockwashers. Castellated nuts with nuts when slot i close to top of nut. The wire cotter pins or lockwire are preferred on bolts or will be more secure if t is made to pass along studs with drilled shanks, but self-lockig nuts are side of stud. permissible within limitations described in Para- graph 1-13. (b) While taut, twit strands to within 1/8 inch 2. For new design, lockwire shall not be used to of next part The twisting keeps wire taut without secure nor hall lockwire be dependent upon frac- overstressing and prevent wire from becomng ture as basis for operation of emergency devices nicked, kinked, or mutilated. such as handles, switches, and guard-covering (c) Lockwiring multiple groups by double- handles that operate emergency mechanism such twist method is accomplished in a similar manner emergency exits, fire extingushers, emergency except twistsbetween parts are alternated between cabin pressure release, emergency landing gear clockwise and counterclockwise. release, and the like. However, where existing (d) After last tie hole, wire is twisted three to structural equipment or safety of flight emergency five times to form a pigtail devices requires shear wire to secure equipment (e) Cut off any excess wire and bend pigtail while not in use, but which are dependent upon towards part shearing or breaking of lookwire for successful 4. When lockwiring widely spaced multiple emergency operation of equipment, particular care groups by double-twist method, three units shall be exercised to assure that wiring under these cir- the maximum number in a series. cumstancesshall not prevent emergency operations of these devices. 1-9 MODEL P210 SERIES SERVICE MANUAL MODEL P210 SERIES SERVICE MANUAL DOUBLE-TWIST METHOD STEP 1. Insert wire through bolt A and bend around bolt (if necessary, bend wire BOLT A across bolt head). Twist wires clockwise until they reach bolt B. STEP 2. Insert one end of wire through bolt B. Bend other end around bolt (if necessary, bend wire across head of bolt). Twist wires counterclockwise 1/2 inch or six twists. Clip ends. Bend pigtail back againt part. BOLT B CLOCKWISE DOUBLE-TWIST METHOD COUNTERCLOCKWISE CLOCKWISE COUNTERCLOCKWISE CLOCKWISE MULTIPLE FASTENER APPLICATION ELECTRICAL CONNECTION DOUBLE-TWIST METHOD Figure 1-4. Lockwire Safetying (Sheet 2 of 2) 1-11 MODEL P210 SERIES SERVICE MANUAL 1-10. USE OF COTTER PINS. (6) Install cotter pin with head firmly in slot of a. Cotter Pin Installation. Castellated nuts and pins nut with ais of eye at right angles to bolt shank. may be safetied with cotter pins or lockwire. The Bend prongs so that head and upper prong are firmly preferred method is to use cotter pins. seated against bolt (see figure 1-5). 1. Select cotter pin material in accordance with temperature. atmosphere, and service limitations (see Table 1-5). Table 1-S). COTTER PIN - MINIMUM SIZE THREAD SIZE MINIMUM PIN SIZE MODEL P210 SERIES SERVICE MANUAL 1-11. USE OF LOCKING CLIPS. 5. When loosening of threaded parts would not a. Safetying Turnbuckles. (See Figure 1-6.) endanger safety of airplane or people. 1. Prior to safetying, both threaded terminals 6. When corrosion encouraged by gouging shall be screwed an equal distnce into turnbuckle aluminum or magnesium alloys by edges of teeth on body and shall be screwed in at least so far that not tooth-locked washers would not cause malfunctioning more than three threads of any terminal are exposed of parts being fastened together. outside body. 2. After turnbuckle has been adjusted to its 1-13. USE OF SELF-LOCKING NUTS. locking position, with slot indicator groove on termi- a. Restrictions. nals and slot indicator notch on body aligned, insert 1. Self-locking nuts cannot be used under cer- end of looking clip into terminal and body (refer to tain conditions. Figure 1-6) until U-curved end of locking clip is over (a) Used, reworked, or reprocessed nuts hole in center of body. should not be installed for any application. (a) Pres locking clip into hold to its full ex- (b) Do not use if at joints in control systems tent. for singular attach points. (b) Curved end of locking clip will expand and (c) Do not use on externally threaded parts latch in body slot. that serve as an axle of rotation for another part (c) To check proper seating of locking clip, where tensional (torque) loads can cause nut to loosen attempt to remove pressed "U" end from body hole and/or become separated. Examples are pulleys, lev- with fingers only. ers, linkages, and cam followers. NOTE NOTE Do not use tool as locking clip could be dis- Self-locking nuts can be used when threaded torted. parts are held by a positive locking device that requires hearing or rupture before torsional 3. Locking clips are for one time use only and loads can act on threaded parts. shall not be re-used. 4. Both locking clips may be inserted in same (d) Do not use where a loose nut, bolt, or hole of turnbuckle body or in opposite holes of screw could fall or be drawn into an area that turnbuckle body. would impede or damage or otherise distort opera- tion. 1-12. USE OF LOCKWASHERS. (e) Do not use to attach accesspanels and a. Lockwahers can be used only under the follow- doors or to assemble components that are routinely ing conditions. disassembled or removed for access and servicing. 1. When self-locking feature cannot be provided In general, donot use self-locking nuts in externally or internally threaded part. where lossof bolt affects safety of flight. 2. When a cotter pin cannot be used to prevent 2. Bolts, studs, or screw, excluding Hi-Looks, rotation of internal threads with respect to external must extend through self-locking nut for a length threads. equivalent of two threaded pitches. This length 3. When lockwire cannot be used to prevent includes chamfer. loosening of threaded parts. 3. Self-locking nuts which are attached to struc- 4. When fastening is not used for fabrication of ture shall be attched in a positive manner to elimi- primary struture. nate possibilty of their rotation or misalignment when tightening is to be acomplished by rotating bolts to structure, and permit replacement of nuts. 1-14 MODEL P210 SERIES SERVICE MANUAL 1-14. CONTROL CABLE WIRE BREAKAGE (b) Wire breakage criteria for cables in AND CORROSION LIMITATIONS. flap, a. Inspection of Control Cables. aileron, rudder, and elevator systems are as follows: 1. Control cable assemblies are subject to a (1) Individual broken wires are variety of environmental conditions and forms of acceptable in primary and secondary control cables deterioration that ultimately may be easy to at random locations when there are no more than six recognize such as wire/strand breakage, or the not so broken wires in any given ten-inch cable length. readily visible types of deterioration including 3. Corrosion. corrosion and/or distortion. The following (a) Carefully examine any cable for information will aid in detecting these cable corrosion that has a broken wire in a section not in conditions. contact with wear-producing airframe components 2. Broken Wire. such as pulleys, fairleads, rub blocks, etc. It may be (a) Examine cables for broken wires by necessary to remove and bend cable to properly passing a cloth along length of cable. This will detect inspect it for internal strand corrosion as this broken wires, if cloth snags on cable. Critical areas condition is usually not evident on outer surface of for wire breakage are those sections of cable which cable. Replace cable if internal corrosion is found. If pass through fairleads, across rob blocks, and around a cable has been wiped clean of its corrosion- pulleys.If no snags are found, then no further preventive lubricant and metal-brightened, the inspection is required. If snags are found or broken cable shall be examined closely for corrosion. For wires are suspected, then a more detailed inspection description of control cable corrosion, refer to FAA is necessary which requires that the cables be bent Advisory Circular AC43-4. in a loop to confirm broken wires (refer to figure 1-7). Loosen or remove cable to allow it to be bent in a loop as shown. While rotating cable, inspect bent area for broken wires. 1-16 Revision 1 MODEL P210 SERIES SERVICE MANUAL BROKEN WIRE UNDETECTED BY WIPING CLOTH ALONG CABLE BROKEN WIRE DETECTED VISUALLY WHEN CABLE WAS REMOVED AND BENT NORMAL TECHNIQUE FOR BENDING CABLE AND CHECKING FOR BROKEN WIRES DO NOT BEND INTO LOOP SMALLER THAN 50 CABLE DIAMETERS Figure 1-7. Cable Broken Wire Inspection Revision 1 1-17 MODEL P210 SERIES SERVICE MANUAL (g) Class IX - These are polyurethane 1-15. ADHESIVES, CEMENTS AND products. Store in original container, between 70 and SEALANTS - SHELF LIFE AND 100°F. Urethanes are moisture sensitive and STORAGE. precautions should be taken to ensure complete a. General. protection from moisture contamination. Container 1. This section provides information which must be tightly closed at all times. defines the proper storage and usable life (shelf life) (h) Class X - These are acrylic base of adhesives, cements and sealents which are used materials. They require storage at 40°F or per for maintenance and/or repair of the airplane. Also instructions on product container. included in this section is the criteria used for c. Storage of Sealants. testing these materials after the normal shelf life 1. All sealants shall be stored under has expired, to determine if an extension to the shelf controlled temperature conditions. If open shop life is possible. storage becomes necessary, these products shall in 2. Shelf life refers to a specified period of time no case be stored in an area which will subject them usually from the date of manufacture (normally to temperatures in excess of 95°F or below 40°F. stamped or printed on the product container ) to the Containers shall be tightly closed prior to placing expiration date (which should be determined using them in the proper storage environment. For proper limits specified in Table 1-7 or if applicable, the storage environment, refer to Table 1-7 and the manufacturer's expiration date printed or stamped following paragraphs. on the product container). The specified shelf life is (a) Premixed and frozen sealants shall be dependent on proper storage in accordance with the stored at -40°F or colder and shall not be used more limits specified in this section and/or the than six weeks after the date of mixing even if all manufacturer's instructions, storage is at -40°F or colder. If storage temperatures b. Storage Criteria. rise above -40°F, but not warmer than -30°F, the 1.Storage of Adhesives and Cements. material may be stored for a maximum of two weeks All adhesives and cements shall be stored under warmer than -40°F plus time at -40°F or colder for a controlled temperature conditions.. If open shop combined total not to exceed five weeks beyond the storage becomes necessary, these products shall in date of mixing. If storage temperatures rise above no case be stored in an area which will subject them -40°F but are not warmer than -20°F, the materials to temperatures in excess of 95°F. Containers shall may be stored for a maximum of one week above - be tightly closed prior to being placing them into the 30°F plus time at -40°F or colder for a combined total proper storage environment. For proper storage not to exceed four weeks beyond the date of mixing. environment, refer to Table 1-7 and the following (b) Unmixed sealants shall be stored at a paragraphs. controlled temperature of between 40 and 80°F and (a) Class I - These adhesives are epoxy have a shelf life of approximately six months when base materials and have one year storage at room stored within this temperature range. Unmixed temperature. 0°F storage will extend the storage life. sealants stored at temperatures exceeding 80°F shall Refer to the product container instructions for be used within five weeks. storage temperature and life. 2. All materials should be used on a "first in- (b) Class II, II1 and IV - These adhesives first out" basis. The adhesives, cements and sealants are rubber and resin base and are good for six should be rotated so this requirement can be months at room temperature storage. 40°F storage accomplished. All material containers should be will extend the storage life. Refer to the product clearly marked with a "use by" date, consisting of container instructions for limits of each adhesive. the year and month. All materials not used by this (c) Class V - These are silicone rubber date must be tested prior to use. Refer to Testing adhesives. If stored in their original containers at a criteria and Table 1-7. temperature below 80°F, have a shelf life of one year d. Testing Criteria. or as indicated on the storage container. 1. Any material (adhesive, cement or (d) Class VI - These are solvent bonding sealant not used within its shelf life will be tested solvents. They should be stored in their original and the results reviewed to determine if the material containers and tightly closed, and stored at 40°F is usable. If there is doubt about the material being temperature. usable, it must be properly disposed of. Material that (e) ClassVII - Cyanoacrylate base has exceeded its original shelf life may be retested to materials must be stored in the original containers determine if the material meets its requirements. at 40°F or as specified on the container instructions. Materials meeting their requirements will have (f) Class VIII - These are pressure their shelf life extended as specified in Table 1-7. sensitive materials. The shelflife is two years when Materials with shelflife extensions must be retested stored at 75°F and 50 percent relative humidity. after a specified period of time. Refer to Table 1-7. 1-18 Revision 1 MODEL P210 SERIES SERVICE MANUAL 2. Testing of Overaged Adhesives and shelf life extension shall be properly mixed using the Cements. correct materials, procedures and equipment. 3. Overaged premixed frozen sealants, along NOTE with unmixed sealants should be visually inspected. Sealants whic show conclusive evidence of Overaged adhesives and cements are those separation, discoloration and/or gelling prior to the that have exceeded their original shelf life addition of a thinner or curing agent shall be and must be tested prior to use and/or given discarded. When in doubt of the sealant quality, the extended shelf life. overaged sealant should be compared with the same type of sealant, under six months old, which is (a) Class I Epoxy Adhesive - Examine known to be satisfactory. both components to ensure that they are still 4. The mixed sealants may be tested by workable. Check for gelling and/or contamination. placing a small amount of sealant (smaple buttons) Stir components and mix a small amount of on a sheet of paper. After the sample buttons have adhesive. Verify that adhesive sets up and hardens. cured, they should be cut in half and examined. The (b) Class II, III and IV Rubber and Resin sealant should show no signs of spots or streaks of Base Adhesives - Open containers and check for unmixed base compound or curing agent. However, gelling and/or contamination. Check for spreading sample buttons containing spots, streaks, and drying. discoloration and/or variations in uniformity of color (c)Class V Silicone Rubber Adhesives - are acceptable if these spots, streaks, etc., are tack Examine adhesive for hardness. If adhesive is still free upon inspection. All mixed sealant should be as soft and can be spread, it is acceptable. Verify that void free as possible. adhesive will harden. 5. Contaminated sealant, premixed sealant (d) Class VI Solvent Bonding Solvents - that have been thawed and refrozen shall be Check for signs of apparent contamination. Solvents discarded. should be clean and clear with no signs of cloudiness. 6. Type I, Class A sealants should be checked (e) Class VII Cyanoacrylic Base for appearance, application time, tack-free time, Adhesives - Verify that product is still liquid with no cure time and adhesion. visible signs of contamination. 7. Type i, Class B sealants should be checked (f) Class VIII Pressure Sensitive for appearance, applicatiion time, cure time, tack- Materials - Open containers and inspect for free time and adhesion. In addition, Class B-2 and B- hardening, gelling and contamination. Stir 4 sealants should be checked for initial flow. components and mix a small amount of adhesive. 8. Type 1, Class C sealants should be checked Verify that adhesive sets up properly. for appearance, application time, cure time and (g) Class X Acrylic Adhesives - Inspect adhesion. In addition, Class C sealants should be base material to ensure that it is still liquid. Mix a tested to determine that they ARE NOT at a tackfree small amount of the components and verify that it condition at the end of their rated work life (squeeze sets up properly. out life). 3. In general, if these materials exhibit 9. Type II sealants should be checked for normal physical properties, with no signs of appearance, application time, tack-free time and hardening, gelling or contamination and set up cure time. and/or harden properly as applicable, the shelf life 10. Type III sealants should be easily may be extended as specified in Table 1-7. thinned with MEK, when difficulty is encountered in e. Testing of Overaged Sealants. thinning the sealant, it should be discarded. 11. Type IV sealants should be checked for NOTE appearance, application time, tack-free time and cure time. Overaged sealants are those that have 12. Type V and VI sealants should be exceeded their original shelf life and checked for appearance, tack-free time and cure must be tested prior to use and/or given time. extended shelf life. 13. Type VII sealants should be checked for appearance, application time, tack-free time and 1. For identification of sealants cure time. Classification, refer to Fuel, Weather, Pressure and 14. Type VIII sealants should be checked for H igh-Temperature Sealing - Maintenance Practices. appearance, application time, tack-free time, cure 2. Overaged sealants to be tested for possible time and adhesion. Adhesion to aluminum should be (peel) less than two-pounds per inch of width. Revision 1 1-19 MODEL P210 SERIES SERVICE MANUAL STORAGE CONDITION EXTEND MODEL P210 SERIES SERVICE MANUAL STORAGE MODEL P210 SERIES SERVICE MANUAL SECTION 2 GROUND HANDLING, SERVICING, CLEANING, LUBRICATION AND INSPECTION WARNING When performing any inspection or maintenance that requires turning on the master switch, installing a battery, or pulling the propeller through by hand, treat the propeller as if the ignition switch were ON. Do not stand, nor allow anyone else to stand, within the arc of the propeller, since a loose or broken wire, or a component malfunction, could cause the propeller to rotate. Page No. TABLE OF CONTENTS Aerofiche/Manual GROUND HANDLING ....... 1B5/2-1 Landing Gear Hydraulic Retraction Towing ........... 1B5/2-1 System ........... 1B16/2-10 Hoisting ....... . . 1B5/2-1 Hydraulic Fluid Sampling and Jacking. .......... 1B5/2-1 Contamination Check ...... 1B16/2-10 Leveling ........... 1B6/2-2 Oxygen System ......... 1B17/2-10A Weighing . . . . .......... 1B6/2-2 Face Masks .......... 1B17/2-10A Parking .. . ..... . B6/2-2 CLEANING ......... . . 1B17/2-1 Tie-Down .... ... . .1B6/2-2 General Description ...... . 1B17/2-10A Flyable Storage ......... 1B6/2-2 Upholstery and Interior ..... . 1B17/2-10A Returning Aircraft to Service .... 1B6/2-2 Plastic Trim ....... .. 1B17/2-10A Temporary Storage ...... 1B9/2-5 Windshield and Windows ..... 1B18/2-10B Inspection During Storage .... 1B9/2-5 Materials Required ...... . 1B18/2-10B Returning Aircraft to Service . . 1B9/2-5 Waxing ........... 1B19/2-11 Indefinite .Storage.. . . . . 1B9/2-5 Preventive Maintenance ..... 1B19/2-11 Inspection During Storage .... 1B10/2-6 InterorTri m ......... 1B19/2-11 Returning Aircraft to Service . . 1B10/2-6 Aluminum Surfaces ....... 1B19/2-11 SERVICING . . ....... 1B11 /2-6A Painted Surface ........ 1B20/2-12 Description .......... 1B/2-6A Engine/Engine Compartment ... . 1B20/2-12 Fuel Tanks .......... . 1B11/2-6A Propeller . ........ . .1B21/2-13 Fuel Additives ... ..... . 1B11/2-6A Wheels . ........... 1B21/2-13 Fuel Drains .......... 1B14/2-8 LUBRICATION .......... 1B21/2-13 Engine Oil . . ......... 1B14/2-8 General Description. ..... . 1B21/2-13 Hydraulic Fluid ........ 1B15/2-9 Nose Gear Torque Links ..... 1B21/2-13 Engine Induction Air Filter .... 1B15/2-9 Tachometer Drive Shaft ...... 1B21/2-13 Vacuum System Filter ...... 1B15/2-9 Wheel Bearing Lubrication .... 1B21/2-13 Battery ............ 1B15/2-9 Wing Flap Actuator ....... 1B21/2-13 Tires. ............... 1B15/2-9 Rod End Bearings. ...... 1B21/2-13 Nose Gear Strut ........ 1B16/2-10 INSPECTION . ......... 1C7/2-23 Nose Gear Shimmy Dampener . . . 1B16/2-10 Hydraulic Brake Systems ..... 1B16/2-10 2-1. GROUND HANDLING. The front sling should be hooked to the engine lifting 2-2. TOWING. Moving the aircraft by hand is ac- eye, and the aft sling should be positioned around the complished by using the landing gear struts as push fuselage at the first bulkhead forward of the leading points. A tow bar attached to the nose gear should be edge of the stabilizer. used for steering and maneuvering the aircraft. 2-4. JACKING. Refer to figure 2-2 for jacking pro- CAUTION cedures. CAUTION When towing the aircraft, never turn the nose wheel more than 35 degrees either side of When using the landing gear strut jack pad, center or the nose gear will be damaged. Do flexibility of thegear strut will cause the not push on control surfaces or outboard em- mainwheel to slide inboard as the wheel is pennage surfaces. When pushing on the tail- raised, tilting the jack. The jack must then cone, always apply pressure at a bulkhead to be lowered for a second jacking operation. avoid buckling the skin. Jacking both wheels simultaneously with 2-3. HOISTING. The aircraft may be hoisted with landing gear strut jack pad is not recom- a hoist of two-ton capacity by using suitable slings. mended. 2-1 MODEL P210 SERIES SERVICE MANUAL TOW BAR: PART NUMBER 0501019-1 OR 0700315-4 (TELESCOPING) IS AVAILABLE FROM THE CESSNA SUPPLY DIVISION. Figure 2-1. Typical Tow Bar 2-4A. LEVELING. Longitudinally leveling of the 2-7. FLYABLE STORAGE. Flyable storage is de- aircraft is accomplished by backing out the two fined as a maximum of 30 days non-operational stor- screws on the left side of the fuselage and then age and/or the first 25 hours of intermittent engine placing a level across the screws. Corresponding operation. points on either the upper or lower main door sills may be used to level the aircraft laterally. NOTE 2-4B. WEIGHING AIRCRAFT. Refer to Pilot's The aircraft is delivered from Cessna with a Operating Handbook. Corrosion Preventive Aircraft Engine Oil (Military Specification MIL-C-6529, Type II). 2-5. PARKING. Parking precautions depend prin- This engine oil is a blend of aviation grade cipally on local conditions. As a general precaution, straight mineral oil and a corrosion preventive it is wise to set the parking brake or chock the compound. This engine oil should be used for wheels, and install the control lock. In severe the first 25 hours of operation use only aviation weather, and high wind conditions, tie down the air- grade straight mineral oil of the correct vis- craft as outlined in paragraph 2-6 if a hangar is not cosity. available. During the 30 day non-operational storage or the first 2-6. TIE-DOWN. When mooring the aircraft in the 25 hours of intermittent engine operation, every sev- open, head into the wind if possible. Secure control enth day the propeller shall be rotated by hand without surfaces with the internal control lock and set brakes. running the engine. After rotating the engine five rev- CAUTION olutions, stop the propeller 45° to 90° from the posi- tion it was in. If the aircraft is stored outside, tie- down in accordance with pargraph 2-6. In addition, Do not set parking brakes during cold weather the pitot tube, static air vents, air vents, openings when accumulated moisture may freeze the. in the engine cowling, and other similar openings brakes or when the brakes are overheated. shall have protective covers installed to prevent en- a. Tie ropes, cables or chains to the wing tie-down try of foreign material. If at the end of thirty (30) a. Tie ropes, cables or chains to the wing tie-down d a f1 o remved from . et fittings located midwing in line with the outboard edgne aircraft will not e removed fr storage, of the flaps. Secure the opposite ends of ropes, cables engne shall be toythe andi The preferred or chains to ground anchors. method would be to fly the aircraft for thirty (30) b. Secure a tie-down rope (no chains or cables) minutes, and up to, but not eceeding normal oil and to upper trunnion of the nose gear, and secure oppo- cylinder temperatures. site end of rope to ground anchor. lIcutlo c. Secure the middle of a rope to the tail tie-down CAMTo ring. Pull each end of rope away at a 45-degree g o l angle and secure to ground anchors at each side of Excessive ground operation shall be avoded. tail. d. Secure control lock on pilot control column. If 2-8. RETURNING AICRAFT TO SERVICE. After control lock is not available, tie pilot control wheel flyabl storage, returning the aircraft to service is back with front seat belt accomplished by performing a thorough pre-fllght in- e. These aircraft are equipped with a spring-loaded spection. At the end of the first 25 hours of engine steering bungee which affords protection against nor- operation, drain engine oil nd change external oil mal wind gusts. However, if extremely high wind filter element Service engine with correct grade gusts are anticipated, additional locks may be install- and quantityof oIL Refer to figure 2-4 and para- ed. graph 2-20 for correct grade of engine oiL 2-2 MODEL P210 SERIES SERVICE MANUAL 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 on the bottom of the step 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, and the green (DOWN) light is illuminated. 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. Figure 2-2. Jacking Details (Sheet 2 of 2) 2-4 MODEL P210 SERIES SERVICE MANUAL 2-9. TEMPORARY STORAGE. Temporary storage k. Install spark plugs and connect spark plug leads. is defined as aircraft in a non-operational status for 1. Apply preservative oil to the engine interior by a maximum of 90 days. The aircraft is constructed spraying approximately two ounces of the preserva- of corrosion-resistant alclad aluminum, which will tive oil through the oil filler tube. last indefinitely under normal conditions if kept m. Seal all engine openings exposed to the atmos- clean. However, these alloys are subject to oxida- phere, using suitable plugs or non-hygroscopic tape. tion. The first indication of corrosion on unpainted Attach a red streamer at each point that a plug or surfaces is in the form of white deposits or spots. tape is installed. On painted surfaces, the paint is discolored or blis- n. If the aircraft is to be stored outside, perform tered. Storage in a dry hangar is essential to good the procedures outlined in paragraph 2-6. In addi- preservation and should be procured, if possible. tion, the pitot tube, static source vents, air vents, Varying conditions will alter the measures of preser- openings in the engine cowling, and other similar vation, but under normal conditions in a dry hangar, openings should have protective covers installed to and for storage periods not to exceed 90 days, the prevent entry of foreign material. following methods of treatment are suggested. o. Attach a warning placard to the propeller to the a. Fill fuel bays with correct grade of gasoline. effect that the propeller shall not be moved while the b. Clean and wax aircraft thoroughly. engine is in storage. c. Clean any oil or grease from tires, and coat tires with a tire preservative. Cover tires to pro- 2-10. INSPECTION DURING STORAGE. tect against grease or oil. a. Inspect airframe for corrosion at least once a d. Either block up fuselage to relieve pressure on month. Remove dust collections as frequently as tires or rotate wheels every 30 days to prevent flat possible. Clean and wax aircraft as required. spotting the tires. b. Inspect the interior of at least one cylinder e. Lubricate all airframe items and seal or cover through the spark plug hole for corrosion at least all openings which could allow moisture and/or dust once each month. to enter. NOTE NOTE Do not move crankshaft when inspecting The aircraft battery serial number is recorded interior of cylinder for corrosion. in the aircraft equipment list. To assure ac- curate warranty records, the battery should c. If at the end of the 90 day period, the aircraft be reinstalled in the same aircraft from which is to be continued in non-operational storage, repeat it was removed. If the battery is returned to the procedural steps "g" thru "o" of paragraph 2-9. service in a different aircraft, appropriate record changes must be made and notification 2-11. RETURNINGAIRCRAFTTOSERVICE. After sent to the Cessna Claims Department. temporary storage, use the following procedure to return the aircraft to service. f. Remove battery and store in a cool, dry place; a. Remove aircraft from blocks. Check tires for service battery periodically and charge as required. proper inflation. b. Check and install battery. NOTE c. Check that oil sump has proper grade and quan- tity of engine oil. An engine treated in accordance with the fol- d. Service induction air filter and remove warning lowing may be considered being protected placard from propeller. against normal atmospheric corrosion for a e. Remove materials used to cover openings. period not to exceed 90 days. f. Remove, clean and gap spark plugs. g. While spark plugs are removed, rotate propeller g. Disconnect spark plug leads and remove upper several revolutions to clear excess rust preventive and lower spark plugs from each cylinder. oil from cylinders. h. Clean, gap and install spark plugs. Torque NOTE plugs to value listed in Section 12. i. Check fuel strainer. Remove and clean filter The preservative oil must be Lubricating screen, if necessary. Check fuel bays and fuel lines Oil-Contact and Volatile, Corrosion In- for moisture and sediment. Drain enough fuel to hibited, MIL-L-46002, Grade 1, or equiva- eliminate moisture and sediment. lent. j. Perform a thorough pre-flight inspection. then start and warm-up engine. h. Using a portable pressure sprayer, spray pre- servative oil through the upper spark plug hole of 2-12. INDEFINITE STORAGE. Indefinite storage is each cylinder with the piston in a down position. Ro- defined as aircraft in a non-operational status for an tate crankshaft as each pair of cylinders is sprayed. indefinite period of time. Engines treated in accor- i. After completing step "h, " rotate crankshaft so dance with the following may be considered protected that no piston is at a top position. 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. 2-5 MODEL P210 SERIES SERVICE MANUAL a. Operate engine until oil temperature reaches NOTE normal operating range. Drain engine oil sump and reinstall drain plug. 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. outside of the sealed area with tape or to the inside of the sealed area with safety wire to NOTE prevent wicking of moisture into the sealed area. Corrosion preventive mixture consists of one part compound MIL-C-6529, Type I, mixed n. Drain corrosion-preventive mixture from engine with three parts new lubricating oil of the sump and reinstall drain plug. grade recommended for service. NOTE c. Immediately after filling the oil sump with cor- rosion preventative mixture, fly the aircraft for a The corrosion-preventive mixture is harmful period of time not to exceed a maximum of 30 min- to paint and should be wiped from painted sur- utes. faces immediately. d. With engine operating at 1200 to 1500 rpm and induction air filter removed, spray corrosion pre- o. Attach a warning placard on the throttle control ventive mixture into induction airbox, at the rate of knob, to the effect that the engine contains no lubri- one-half gallon per minute, until heavy smoke cating oil. Placard the propeller to the effect that it comes from exhaust stack, then increase the spray should not be moved while the engine is in storage. until the engine is stopped. p. Prepare airframe for storage as outlined in paragraph 2-9 thru step "f." CAUTION NOTE Injecting corrosion-preventive mixture too fast can cause a hydrostatic lock. As an alternate method of indefinite storage, the aircraft may be serviced in accordance e. Do not rotate propeller after completing step with paragraph 2-9 providing the aircraft is "d." run up at maximum intervals of 90 days and f. Remove all spark plugs and spray corrosion- then reserviced per paragraph 2-9. preventive mixture, which has been pre-heated (221° to 250*F), into all spark plug holes. 2-13. INSPECTION DURING STORAGE. Aircraft in an indefinite storage shall be inspected as follows: NOTE a. Inspect cylinder protex plugs each 7 days. b. Change protex plugs if their color indicates an To throughly cover all surfaces of the cylin- unsafe condition. der interior, move the nozzle of the spray gun c. If the dehydrator plugs have changed color in one from the top to the bottom of the cylinder. If half of the cylinders, all desiccant material in the by accident the propeller is rotated following engine shall be replaced with new material. this spraying, respray the cylinders to insure d. Every 6 months respray the cylinder interiors an unbroken coverage on all surfaces. with corrosion-preventive mixture and replace all desicant and Protex plugs. g. Install lower spark plugs or install solid plugs, desicant and Protex plugs. and install dehydrator plugs in upper spark plug NOTE holes. Be sure that dehydrator plugs are blue in color when installed. Before spraying, inspect the interior of one h. Cover spark plug lead terminals with shipping cylinder for corrosion through the spark plugs (AN4060-1) or other suitable covers. plug hole and remove at least one rocker box i. With throttle in full open position, place a bag cover and inspect the valve mechanism. of desiccant in the induction air intake and seal opening with moisture resistant paper and tape. 2-14. RETURNING AIRCRAFT TO SERVICE. J. Place a bag of desiccant in the exhaust tailpipe After indefinite storage, use the following procedure and seal opening with moisture resistant 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. 2-6 MODEL P210 SERIES SERVICE MANUAL e. Remove oil sump drain plug and drain sump NOTE Install and safety drain plug. f. Remove existing filter, install new oil filter. Before refueling or when airplane is parked on a slope, place the fuel selector handle in the LEFT ON or RIGHT ON position, whichever corresponds to the low wing. This will minimize NOTE crossfeeding from the fuller bay and reduce fuel seepage from the wing vents. This note applies The corrosion-preventive mixture will mix only to 1985 models. the oil system is not necessary. Draining WARNING the oil sump will remove enough of the corrosion-preventive mixture. DURING ALL FUELING PROCEDURES, FIRE- FIGHTING EQUIPMENT MUST BE AVAIL- g. Service and install the induction air filter. ABLE. TWO GROUND WIRES FROM DIFFER- h. Remove dehydrator plugs and spark plugs or ENT POINTS ON THE AIRPLANE TO SEPA- plugs installed in spark plug holes and rotate RATE APPROVED GROUND STAKES SHALL propeller by hand several revolutions to clear BE USED TO PREVENT ACCIDENTAL DISCON- corrosion-preventive mixture from cylinders. NECTION OF ONE GROUND WIRE. ENSURE i. Clean. gap and install spark plugs. Torque THAT FUELING NOZZLE IS GROUNDED TO plugs to value listed in Section 12. THE AIRPLANE. j. Check fuel strainer. Remove and clean filter screen. Check fuel tanks and fuel lines for a. Tie-down rings should be used as grounding moisture and sediment and drain enough fuel to points for all grounding wires during re-fueling eliminate. procedures. k. Perform a thorough pre-flight inspection, then b. Plugs or caps should be placed on all discon- start and warm-up engine. nected hoses, lines, and fittings to prevent residual 1. Thoroughly clean aircraft and flight test fuel drainage, thread damage, or entry of dirt or aircraft. foreign material into fuel system. 2-15. SERVICING. 2-18. USE OF FUEL ADDITIVES FOR COLD 2-16. DESCRIPTION. Servicing requirements are WEATHER OPERATION. Strict adherence to recom- shown in figure 2-4. The following paragraphs mended preflight draining instructions will eliminate supplement this figure by adding details not any free water accumulations from the tank sumps. included in the figure. While small amounts of water may still remain in solution in the gasoline, it will normally be consumed 2-17. FUEL BAYS. An are of each wing is sealed to and go unnoticed in the operation of the engine. form an integral fuel tank. Recommended fuel grade is listed in figure 2-4, and fuel capacities are given in figure 1-1. Fuel bays should be filled immediately after flight to lessen condenation in the bays and line.2 2-6A(2-6B blank) MODEL P210 SERIES SERVICE MANUAL One exception to this can be encountered when oper- Any high quality isopropy alcohol may be used, such ating under the combined effect of: 1) use of certain as: Anti-icing fluid (MIL-F-5566) or sopropyl alco- fuels, with 2) high humidity conditions on the ground hol (Federal Specification TT-I-735a). 3) followed by flight at high altitude and low tempera- ture. Under these unusual conditions small amounts Ethylene glycol monomethyl ether (EGME) compound of water in solution can precipitate from the fuel in compliance with MIL-I-27686 or Phillips PFA- stream and freeze in sufficient quantities to induce 55MB, if used, must be carefully mixed with the fuel partial icing of the engine fuel system. in concentrations not to exceed 0.15% by volume. While these conditions are quite rare and will not CAUTION normally pose a problem to owners and operators, they do exist in certain areas of the world and con- Mixing of the EGME compound with the fuel sequently must be dealt with when encountered. extremely important because concentrate- tio in excess of that recommended (0. 15 Therefore, to alleviate the possibility of fuel icing percent by volume maximum) will result in occurring under these unusual conditions it is per- detrimental affects to the fuel tanks, such missible to add isopropyl alcohol or ethyelene glycol as deterioration of protective primer and monomethyl ether (EGME) compound to the fuel sup- sealant and damage to O-rings and seals ply. See figure 2-3 for fuel additive mixing ratio. in the fuel system and engine component Use only blending equipment that to is recom- mended by the manufacturer to obtain proper proportioning CAUTION ~Do not allow the concentrated EGME com- Diethylene glycod monomethyl ether pound to come in contact with the airplane (DIEGME) has NOT been approved by engine finish or fuel cell as damage can result manufacturer for use with propellersingle water buildup in the fuel which "leeches out" the additive. An indication of this is when excessive amount of water accumulates in the fuel tank sumps. The introduction of alcohol or EGME compound into The concentration can be checked using a differential the fuel provides two distinct effects: 1) it absorbs refractometer. It is imperative that the technical the dissolved water from the gasoline and 2) alcohol manual for the differential refractometer be followed has a freezing temperature depressant effect, explicitly when checking the additive concentration. Alcohol, if used, is to be blended with the fuel in a concentration of 1% by volume. Concentrations greater than 1% are not recommended since they can be detrimental to fuel tank materials. The manner in which the alcohol is added to the fuel is significant because alcohol is most effective when it is completely dissolved in the fuel. To insure proper mixing the following is recommended. 1. For best results the alcohol should be added during the fueling operation by pouring the alcohol directly on the fuel stream issuing from the fuel nozzle. 2. An alternate method that may be used is to premix the complete alcohol dosage with some fuel in a separate clean container (approximately 2-3 gallon capacity) and then transfer this mixture to the tank prior to the fuel operation. Revision 2 2-7 MODEL P210 SERIES SERVICE MANUAL MODEL P210 SERIES SERVICE MANUAL 2-20A. HYDRAULIC FLUID. Refer to figure 2-4. NOTE 2-21. ENGINE INDUCTION AIR FILTER. The The filtering panels of the filter may induction air filter keeps dust and dirt from entering become distorted when wet, but they will the induction system. The value of maintaining the return to their original shape when dry. air filter in a good clean condition can never be over- stressed. More engine wear is caused through the e. Be sure airbox is clean. and inspect filter. If use of a dirty or damaged air filter than is generally filter is damaged, a new filter should be installed. believed. The fequency with which the filter should f. Install filter at entrance to airbox with gasket be removed, inspected and cleaned will be deter- on aft face of filter frame and with flow arrows on mined primarily by aircraft operating conditions. filter frame pointed in the correct direction. A good general rul, however, is to remove, inspect and clean the filter at least every 100 hours of engine 2-22. VACUUM SYSTEM AIR FILTER. The disposa- operating time, and more frequently f warranted by ble type central air filter keeps dust and dirt from operating conditions. Under extremely dusty condi- entering the vacuum-operated instruments. Inspect tions, daily servicing of the filter is recommended. To filter every 100 hours for damage. The filter should service the induction filter, proceed as follows: be replaced every 500 hours of operation and a. Remove filter from aircraft. whenever it becomes sufficiently clogged to cause suction gage readings to drop below 4.6 in. Hg. The system should not be operated at anytime without a NOTE filter, nor are any lines to be left open when perform- ing maintenance on the system, as minute particles of Use care to prevent damage to filter dust or other foreign materials may enter the lines element when cleaning filter with com- and could severly damage the gyro instruments. pressed air. b. Clean filter by blowing with compressed air CAUTION (not over 100 psi) from direction opposite of normal air flow. Arrows on filter case indicate direction of Smoking will cause premature filter clogging. normal air flow. CAUTION Do not use solvent or cleaning fluids to wash filter. Use only a water and 2-23. BATTERY. Battery servicing involves household detergent solution when adding distilled water to maintain the electrolyte washing the filter. even with the horizontal baffle plate or split ring at the bottom of the filler holes, checking cable c. After cleaning as outlined in step "b" the connections, and neutralizing and cleaning off any filter may be washed, if necessary. in a solution of spilled electrolyte or corrosion. Use bicarbonate of warm water and a mild household detergent. A soda (baking soda) and clean water to neutralize cold water solution may be used. electrolyte or corrosion. Follow with a thorough flushing with clean water. Do not allow NOTE bicarbonate of soda to enter battery. Brighten cable and terminal connection with a wire brush. The filter assembly may be cleaned with then coat with petroleum jelly before connecting. compressed air a maximum of 30 times or Check the battery every 100 hours (or at least every it may be washed a maximum of 20 90 days), oftener in hot weather. Add only distilled times. A new filter should be installed water, not acid or "rejuvenator." to maintain electro- after using 500 hours of engine operating lyte level in the battery. Inspect the battery box and time or one year. whichever should occur clean and remove any evidence of corrosion. first. However. a new filter should be installed anytime the existing filter is damaged. A damaged filter may have 2-24. TIRES. Maintain tire pressure at the value sharp or broken edges in the filtering specified in Section 1. When checking pressure, panels which would allow unfiltered air examine tire for wear, cuts, bruises and slippage. to enter the induction system. Any filter NOTE that appears doubtful. shall have a new filter installed in its place. Recommended tire pressure should be d. After washing. rinse filter with clear water maintained. Especially in cold weather. until rinse water draining from filter is clear remember that any drop in temperature of Allow water to drain from filter and dry with the inside a tire uses a compressed air (not over 100 psi). ponding drop 2-9 MODEL P210 SERIES SERVICE MANUAL 2-25. NOSE GEAR STRUT. The nose gear strut re- c. Fill dampener with clean hydraulic fluid quires periodic checking to ascertain that the strut is completely full. filled with hydraulic fluid and is inflated to the cor- d. Reinstall plug and safety. rect air pressure. To fill the nose gear strut with e. Wash dampener in solvent and wipe dry with a hydraulic fluid and air, proceed as follows: cloth. a. Remove valve cap and release all air. f. Reinstall shimmy dampener in aircraft. b. Remove valve housing assembly. c. Compress strut completely (stops in contact NOTE with outer barrel hub). d. Oil leveL Keep shimmy dampener. especially the 1. Fluid used should comply with specification exposed portions of the dampener piston MIL-O-5606. shaft. clean to prevent collection of dust 2. Fill strut to bottom of valve installation hole. and grit which could cut the seals in the 3. Maintain oil level at bottom of valve installa- dampener barrel Keep machined tion hole. surfaces wiped free of dirt and dust. using e. Fully extend strut. a clean lint-free cloth saturated with f. Replace valve housing assembly. hydraulic fluid (MIL-H5406) or g. With strut fully extended and nose wheel clear kerosene. All surfaces should be wiped free of excessive hydraulic fluid. of ground, inflate strut to 80 PSL 2-27. HYDRAULIC BRAKE SYSTEMS. Check brake NOTE master cylinders and refill with hydraulic fluid as specified in the inspection charts. Bleed the brake The nose landing gear shock strut will nor- system of entrapped air whenever there is a spongy mally require only a minimum amount of response to the brake pedals. Refer to Section 5 service. Maintain the strut extension pres- for filling and bleeding the brake systems. sure as shown in Section 1. Lubricate landing gear as shown in figure 2-5. Check 2-28. LANDING GEAR HYDRAULIC RETRACTION the landing gear daily for general cleanliness, SYSTEM. Draining, filling and bleeding of the land- security of mounting, and for hydraulic fluid ing gear hydraulic system can be accomplished by leakage. Keep machined surfaces wiped free the following method. of dirt and dust, using a clean lint-free cloth a. Place aircraft master switch in OFF position saturated with hydraulic fluid (MIL-H-5606) and place aircraft on Jacks as shown in figure 2-2. or kerosene. All surfaces should be wiped Bleed pressure from system by moving landing gear free of excessive hydraulic fluid. selector valve to gear UP position. 2-26. NOSE GEAR SHIMMY DAMPENER. The shimmy dampener should be serviced at least CAUTION every 100 hours. The dampener must be filled completely with hydraulic fluid. free of entrapped Do not turn master switch ON while hydraulic air with the compensating piston bottomed in the system is open to atmosphere. The pump rod. Check that piston is completely bottomed as will automatically start, causing hydraulic follows: fluid to spray from any open line. a. Remove shimmy dampener from the aircraft. b. While holding the shimmy dampener in a b. Drain system by removing cap from elbow on vertical position with the filler plug pointed right side of power pack (behind access cover) and upward. loosen the filler plug. attaching a drain hose to the elbow. Place end of c. Allow the spring to bottom out the floating hose in a container of at least one gallon capacity piston inside the shimmy dampener rod. and using emergency hand pump, pump fluid into con- d. When the fluid stops flowing, insert a length of tainer. When power pack reservoir is empty, re- stiff wire through the air bleed hole in the setscrew place cap. at the end of the piston rod until it touches the c. Fill power pack reservoir with MIL-H-5606 hy- floating piston. The depth should be 3-13/16 draulic fluid by inserting a funnel or filler hose in inches. dipstick opening on top of power pack body. d. Bleed system by cycling lading gear through NOTE several cycles. Refill power pack reservoir with MIL-H-5606 hydraulic fluid and remove aircraft from If the wire insertion is less than 3-13/16 jacks. inches. the floating piston is lodged in the shaft. If the wire cannot be used to free 2-29. HYDRAULIC FLUID SAMPLING AND CON- the piston. the rod assembly and piston TAMINATION CHECK. At the first 50 and first 100 should be replaced. hour inspection and thereafter at each 500 hour in- spection or one year, whichever should occur first, Service the snlmmy dampener as follows: 1asample of fluid should be taken and examined for a. Remove filler plug from dampener. sediment and discoloration. This may be done as b. Move piston completely to opposite end from follows: filler plug. 2-10 MODEL P210 SERIES SERVICE MANUAL a. Place aircraft master switch in OFF position b. Brush out or vacuum clean the upholstery and and replace aircraft on jacks as shown in figure 2-2. carpeting to remove dirt. Bleed pressure from system by moving landing gear selector valve to gear UP position. damp cloth. selector valve to gear UP position. c. Wipe leather and plastic surfaces with a damp cloth. d. Soiled upholstery fabrics and carpet may CAUTION be cleaned with a foam-type detergent. used Do not turn master switch ON while hydraulic according to the manufacturers instructions. e. Oily spots and stains may be cleaned system is open to atmosphere. The pump will automatically start, causing hydraulic sparingly. Before using any solvent. read the fluid to spray from any open line. instructions on the container and test it on an b. Remove cap from elbow on right side of power obscure place in the fabric to be cleaned. pack (behind access cover) and place a nonmetal con- Never saturate the fabric with a volatile tainer below opening, solvent: it may damage the packing and c. Place landing gear selector valve in DOWN posi- backing material. tion and operate emergency hand pump to pump fluid f. Scrape off sticky materials with a dull into container. knife, then spot clean the area. d. If the drain fluid is clear and not appreciably darker in color than new fluid, continue to use the present fluid. NOTE e. If the fluid color is doubtful, place a fluid sam- ple in a nonmetallic container and insert a strip of Repair kits are available for the repair of cracks polished copper in the fluid, in ABS. PBC, PVCP, graphite and fiberglass f. Keep copper in the fluid for six hours at a ten- material. (Cessna Supply Division, P.O. Box perature of 70ºF or more. A slight darkening of the 949, Wichita, KS 67201, 316/685-9111, Telex copper is permissible, but there should be no pitting 417-489.) or etching is evident, drain fluid from power pack 2-35. PLASTIC TRIM. The instrument reservoir. Fill power pack with MIL-H-5606 hy- pel plastic trim and control knobs need draulic fluid and bleed air from system. only be wiped off with a damp cloth. Oil and 2-30. OXYGEN SYSTEM Refer to Section 15. grease on the control wheel and control knobs can be removed with a cloth moistened with 2-31. FACE MASKS. Refer to Section 15. Stoddard solvent. 2-32. CLEANING. CAUTION Do not use gasoline, alcohol, benzene, 2-33. GENERAL DESCRIPTION. Keeping the aircraft acetone. carbon tetrachloride, fire ex- clean is important. Besides maintaining the trim tinguisher fluid, de-icer fluid, lacquer appearance of the aircraft, cleaning lessens the thinner or glass window cleaning spray. possibility of corrosion and makes inspection and These solvents will soften and craze the maintenance easier. plastic. 2-34. UPHOLSTERY AND INTERIOR. Cleaning prolongs the life of upholstery fabrics and interior trim. To clean the Interior, proceed as follows; a. Empty all the ash trays. 2-10A MODEL P210 SERIES SERVICE MANUAL 2-36. CLEANING WINDSHIELD AND WINDOWS. 2-36A. MATERIALS REQUIRED. NAME MANUFACTURER USE Mild soap or detergent Commercially available. Cleaning windshields and (hand dishwashing type windows. without abrasives). Aliphatic Naphtha Type II Commercially available. Removing deposits which conforming to Federal cannot be removed with mild Specification TT-N-95. soap solution on acrylic windshields and windows. Polishing wax. Waxing acrylic windshields and windows Turtle Wax (paste). Turtle Wax, Inc. Chicago, IL. 80038 Great Reflections E.I. duPont de Nemours Paste Wax and Co. (Inc.) Wilmington, DE 19898 *Slip-Stream Wax Classic Chemical (paste) Grand Prairie, TX 75050 *Acrylic polish conforming to Cleaning and polishing acrylic Federal Speciication windshields and windows. PP-P560 such as: Permatex plastic cleaner Permatex Company, Inc. No. 403D Kansas City, KS 66115 Cotton flannel or cotton Commercially available. terry cloth material. *These are the only polishing waxes tested and approved for use by Cessna Aircraft Company. CAUTION d. On acrylic windshields and windows only, if soils which cannot be removed by a mild detergent Windshields and windows are easily damaged remain, Type II aliphatic naphtha applied with a by improper handling and cleaning techniques. soft clean cloth may be used as a cleaning solvent. Be sure to frequently retold cloth to avoid redeposit- a. Place airplane insid hangar or in shaded area ing soil and/or scratching windshield with any and allow to cool from heat of sun's direct rays. abrasive particles. b. Using clean (preferably running) water, flood . Rinse surface thoroughly with clean fresh water surface. Use bare hand with no Jewelry to feel and and dry with a clean cloth. dislodge any dirt or abrasive materials. c. Using a mild soap or detergent (such as d- CAUTION hwashing liquid) in water, wash surface. Again use only bare hands to provide rubbing force. (A clean DO NOT use any of the following on or for cloth may be used to tranfer soap solution to sur- cleaning windshields and windows: methanol, face, but extreme care must be exercised to prevent denatured aloohol gasolne, bensee, xylene, scratching surface.) MEK, acetone, carbon tetrachloride, lacquer thinner, commercial or household window cleaning sprays. 2-1OB MODEL P210 SERIES SERVICE MANUAL 2-36B. WAXING. 5. Protex 10VS - Mask Off Company, Monrovia, a. Hand polishing wax should be applied to acrylic CA, and Southwest Paper Co., Wichita, KS. surfaces. (The wax has an index of refraction nearly 6. Scotch 344 Black Tape - 3M Company. the same as transparent acrylic and tend to mask any d. Do not park or store airplane where it might be shallow scratches on windshield surface). subjected to direct contact with or vapors from: b. Acrylic surfaces may be polished using a polish methanol, denatured alcohol, gasoline, benzene, meeting Federal Specification P-P-560 applied per xylene, MEK, acetone, carbon tetrachloride, lacquer manufacturer's instructions. thinners, commercial or household window cleaning sprays, paint strippers, or other types of solvents. CAUTION e. Do not use solar screens or shields installed on inside of airplane or leave sun visors up against DO NOT use rain repellent on acrylic surfaces. windshield. The reflected heat from these items causes elevated temperatures which accelerate crazing NOTE and may cause formation of bubbles in the inner ply of multiple ply windshields. When applying and removing wax and polish, f. Do not use a power drill motor or other powered use a clean soft cloth. device to clean, polish, or wax surfaces. 2-36C. PREVENTIVE MAINTENANCE 22-36D. INTERIOR TRIM. The instrument panel, interior plastic trim, and control knobs need only be wiped with a damp cloth. Oil and grease on the con- NOTE trol wheels and control knobs can be removed with a cloth moistened with Stoddard solvent. Volatile sol- Utilization of the following techniques will vents, mentioned in the caution note of paragraph 2- help minimize windshield and window crazing. 36, must never be used since they soften and craze the plastic trim. a. Keep all surfaces of windshields and windows clean. 2-37. ALUMINUM SURFACES. The aluminum b. If desired, wax acrylic surfaces. surfaces require a minimum of care. but should c. Carefully cover all surfaces during any painting, never be neglected. The aircraft may be washed powerplant cleaning or other procedure that calls for with clean water to remove dirt and may be washed use of any type of solvents or chemicals. The follow- with non-alkaline grease solvents to remove oil ing coatings are approved for use in protecting sur- and/or grease. Household-type detergent soap faces from solvent attack. powders are effective cleaners, but should be used 1. White Spary Lab, MIL-C-6799, Type I, Class cautiously since some of them are strongly m. alkaline. Many good aluminum cleaners. polishes 2. WPL-3 Masking Paper - St. Regis, Newton, and waxes are available from commercial MA. suppliers of aircraft products. 3. 5 X N - Poly-Spotstick - St. Regis, Newton, MA. 4. Protex 40 - Mask Off Company, Monrovia, CA, and Southwest Paper Co., Wichita, KS. 2-11 MODEL P210 SERIES SERVICE MANUAL 2-38. PAINTED SURFACES. The painted exterior pressure. Use of a stiff bristle brush rather than a surfaces of your new Cessna have a durable, long steel brush is recommended if cleaning agents do not lasting finish. Approximately 10 days are required remove excess grease and grime during spraying. for the paint to cure completely; in most cases, the curing period will have been completed prior to de- A recommended procedures for cleaning an engine and livery of the airplane. In the event that polishing or accessories is as follows: buffing is required within the curing period, it is recommended that the work be done by someone ex- CAUTION perienced in handling uncured paint. Any Cessna Dealer can accomplish this work Do not attempt to wash an engine which is still hot or running. Allow the engine to cool before Generally, the painted surfaces can be kept bright by cleaning. washing with water and mild soap, followed by a rinse with water and drying with cloths or a chamois. a. Remove engine cowling. Harsh or abrasive soaps or detergents which cause b. Carefully cover the coupling area between the corrosion or scratches should never be used. Remove vacuum pump and the engine drive shaft so that no stubborn oil and grease with a cloth moistened with cleaning solvent can reach the coupling or seal. Stoddard solvent. c. Cover the open end of the vacuum discharge tube. d. Cover the vacuum relief valve filter, if installed To seal any minor surface chips or scratches and pro- in the engine compartment. tect against corrosion, the airplane should be waxed e. Use fresh water for wash down when the engine is regularly with a good automotive wax applied in accor- contaminated with salt or corrosive chemicals. A dance with the manufactrer's instructions. If the cleaning agent such as described previously may then airplane is operated in a seacoast or other salt water be used to remove oil and grime. environment, it must be washed and waxed more fre- quently to assure adequate protection. Special care CAUTION should be taken to seal around rivet heads and skin laps, which are the areas most susceptible to corro- Care should be exercised to not direct cleaning sion. A heavier coating of wax on the leading edges agents or water streams at openings on the of the wings, and tail and on the cowl nose cap and starter, magnetos, alternator, vacuum pump propeller spinner will help reduce the abrasion en- or turbocharger relief valve. countered in these areas. Reapplication of wax will generally be necessary after cleaning with soap solu- f. Thoroughly rinse with clean warm water to re- tions or after chemical de-icing operations. move all traces of cleaning agents. 2-39. ENGINE AND ENGINE COMPARTMENT. An CAUTION engine and accessories wash down should be accom- plished during each 100-hour inspection to remove Cleaning agents should never be left on engine oil, grease, salt corrosion or other residue that components for an extended period of time. might conceal component defects during Inspection. Failure to remove them may cause damage to Also, periodic cleaning can be very effective in pre- components such as neoprene seals and silicone ventive maintenance. fire sleeves, and could cause additional corro- sion. Precautions should be taken when working with clean- ing agents such as wearing of rubber gloves, an apron g. Completely dry engine and accessories using or coveralls and a face shield or goggles. Use the clean, dry compressed air. least toxic of available cleaning agents that will satis- h. Remove the cover over the coupling area. factorily accomplish the work. These cleaning agents i. Remove the cover from the vacuum discharge include: (1) Stoddard Solvent (Specification P-D-680 tube. type 1), (2) A water alkaline detergent cleaner (MI- j. Remove the cover from the vacuum relief valve C-25769J) mixed, 1 part cleaner, 2 or 3 parts water filter, if installed. and 8 to 12 parts Stoddard solvent or (3) A solvent k. If desired, engine cowling my be washed with base emulsion cleaner (MIL-C-4361B) mixed 1 part the same cleaning agents, then rinsed thoroughly and cleaner and 3 parts Stoddard solvent, wiped dry. After cleaning engine, relubricate all *_______ , control arms and moving parts as required. CAUTION L Reinstall engine cowling. Do not use gasoline or other highly flammable WARNING substances for wash down. For maximum safety, check that the magneto Perform all cleaning operations in well ventilated switches are OFF, the throttle is cloed, the work areas and ensure that adequate firefighting and mixture control is in the idle cut-off position, safety equipment is available. Do not smoke or ex- and the airplane is secured before rotating the pose a flame, within 100 feet of the cleaning area. propeller by hand. Do not stand within the arc Compressed air, used for cleaning agent, application of the propeller blades while turning the pro- or drying, should be regulated to the lowest practical peller. 2-12 MODEL P210 SERIES SERVICE MANUAL m. Before starting engine rotate the propeller by 2-46. WHEEL BEARING LUBRICATION. Clean hand no less than four complete revolutions. and repack wheel bearings at the first 100-hour inspection and at each 500-hour inspection 2-40. PROPELLER. The propeller should be thereafter. If more than the usual number of take- wiped occasionally with an oily cloth to remove off and landings are made. extensive taxiing is grass and bug stains. In salt water areas. this will required or the aircraft is operated in dusty areas assist in corrosion-proofing the propeller. or under seacoast conditions, clean and lubricate wheel bearings at each 100-hour inspection. 2-41. WHEELS. The wheels should be washed periodically and examined for corrosion. chipped paint, and cracks or dents in the wheel halves or in 2-47. WING FLAP ACTUATOR. Clean and the flanges or hubs. If defects are found remove lubricate wing flap actuator jack screw each 100 and repair in accordance with Section 5. Discard hours as follows: cracked wheel halves flanges or hubs and install a. Expose jack screw by operating flaps to full- ~~~new parts.~ ~ ~down position. *~~~~new parts. "b. Clean jack screw threads with solvent rag and dry with compressed air. 2-42. LUBRICATION. NOTE WARNING It is not necessary to remove actuator The U.S. Environmental Protection Agency ad- from aircraft to clean or lubricate threads. vises that mechanics and other workers who handle engine oil are advised to minimize skin c. With oil can. apply light coat of No. 10 weight. contact with used oil and promptly remove used non-detergent oil to threads of jack screw. oil from the skin. In a laboratory study, mice developed skin cancer after skin was exposed to 2-48. ROD END BEARINGS. Periodic inspection used engine oil twice a week without being and lubrication is required to prevent corrosion of waahed off, for most of their life span. Sub- the bearing in the rod end. At each 100-hour stanes found to cause canoer ii laboratory ani- inspection. disconnect the control rods at the mals may also cause cancer in humans,. aileron and inspect each rod end for corrosion. If no corrosion is found. wipe the surface of the rod end balls with general purpose oil and rotate ball 2-43. GENERAL DESCRIPTION. Lubrication freely to distribute the oil over its entire surface requirements are outlined in figure 2-5. Before and connect the control rods to the aileron. If adding lubricant to a fitting. wipe the fitting free of corrosion is detected during inspection. install new dirt. Lubricate until grease appears around part rod ends. being lubr