D2058-2-13 - MODEL P210 SERIES (1978 THRU 1983) - AeroElectric

This Temporary Revision consists of the following pages, which affect and replace existing pages in the paper copy manual and supersede aerofiche information. CHAPTER/ CHAPTER/ SECTION/ AEROFICHE SECTION/ AEROFICHE SUBJECT PAGE FICHE/FRAME SUBJECT PAGE FICHE/FRAME 2 27 1 B-23 2 29 1 C-01 REASON FOR TEMPORARY REVISION To add Parker Hannifin Vacuum Manifold Check Valve inspection/replacement times to inspection section. FILING INSTRUCTIONS FOR THIS TEMPORARY REVISION For Paper Publications: File this cover sheet behind the publication's title page to identify inclusion of the temporary revision in the manual. Insert the new pages in the publication at the appropriate locations and remove and discard the superseded pages. For Aerofiche Publications: Draw a line, with a permanent red ink marker, through any aerofiche frame (page) affected by the temporary revision. This will be a visual identifier that the information on the frame (page) is no longer valid and the temporary revision should be referenced.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. Line should be 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 © 1998 CESSNA AIRCRAFT COMPANY WICHITA, KANSAS, USA MODEL P210 SERIES SERVICE MANUAL INSERT ATEST CHANGED PAGES, DESTROY SUPERSEDED.PAGES LIST OF EFFECTIVE PAGES NOTE: The portion of the text affected by the Revision is indicated by a vertical line in the outer margine of the page. Revised to illustrations are indicated by miniture pointing hands. Dates of issue for original and revised pages are: Original .... 0 .. 24 September 1982 Revision ... .1... 6 June 1983 Revision ... .2 ... 3 June 1996 TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 696, CONSISTING OF THE FOLLOWING: Page Revision Page Revision Page Revision No. No. No. No. No. No. *Title ..... ....... 2 *5A-30 ... ........ 2 15-18D ............... 1 *A ....... .............. 2 5A-31 thru 5A-38 . ...... 0 15-19 ................. 0 i ....................... 1 6-1 thru 6-12 ...... .... 0 15-20thru 15-22 ........ 1 *ii thru iv ............... 2 7-1 thru 7-9 ............ 0 15-22A thru 15-22B ... . 0 1-1 thru 1-5 ............. 0 7-10 Blank .......... 0 15-22C thru 15-22F ...... 1 1-6 Blank ............... 0 8-1 thru 8-7 .... ......... 0 15-23 .................. 1 2-1 thru 2-6 ............ 0 8-8 Blank .......... 0 15-24 thru 15-25 ........ 0 *2-7 ................. 2 9-1 ..................... 1 15-26 thru 15-27 ........ 1 2-8 .......... ..... 0 9-2 thru 9-15 ............ 0 15-28 thru 15-29 ........ 0 *2-9 thru 2-10 ......... 2 9-16 Blank ........... 0 15-29A thru 15-29B ..... 0 *2-10A .................. 2 10-1 . ............. 1 15-30 thru 15-32 ........ 0 *2-10B blank ............ 2 10-2 thru 10-8 .......... 0 15-33 thru 15-36 ........ 1 2-11 ................. 0 11-1 ......... ......... 1 16-1 ................... 1 2-12 ................... 1 11-2 thru 11-4 ........... 0 16-2thru 16-14 ......... 0 2-13 thru 2-14 ....... ... 0 12-1 thru 12-2 ........... 1 16-14A thru 16-14B ..... 1 2-15 ....... .. ... 1 12-3 thru 12-4 ......... 0 16-15 .................. 0 2-16 thru 2-22 .......... 0 *12-5 ............... ... 2 *16-16 ........ .. . 2 *2-23 thru 2-29 .......... 2 12-6 thru 12-29 ....... 0 16-17 .................. 0 *2-30 Blank .......... 2 *12-30thru 12-31 ...... 2 *16-18 .................. 2 3-1 thru 3-5 ............. 0 12-32thru 12-57 ... ... 0 16-19 .................. 0 *3-6 ......... ..... .. 2 *12-58 .............. ... 2 *16-20 .................. 2 3-7 thru 3-31 ........ 0 12-59 thru 12-60 0 *16-20A thru 16-20B ..... 2 3-32 Blank ......... 0 13-1 ............. 1 16-21 thru 16-30 ........ 0 4-1 thru 4-6 . .... ...... 0 13-2 thru 13-5 . ... ... . 0 17-1 thru 17-2 ........... 1 5-1 thru 5-20 ........... 0 *13-6 thru 13-7 ....... 2 17-3 thru 17-7 ........... 0 *5-20A ................ 2 13-8 thru 13-15 ......... 0 *17-8 ................... 2 *5-20B Blank ........... 2 *13-16 ............ ... 2 17-9thru 17-40 ........ 0 5-21 thru 5-37 ........... 0 13-17 thru 13-33 .. . .. 0 *17-41 .................. 2 *5-38 ................. 2 13-34 Blank .......... 0 17-42 thru17-51 ........ 0 *5-38A ...... ....... .. 2 14-1 .................. 1 *17-52 .................. 2 *5-38B blank ......... 2 14-2 thru 14-6 . ......... 0 17-53 thru 17-67 ........ 0 5-39 thru 5-49 ........... 0 15-1 thru 15-2 ........... 1 *17-68 .................. 2 *5-50 ................ 2 15-2A thru 15-2B ........ 0 17-69 thru 17-70 ........ 0 5-51 thru 5-87 ........... 0 15-3 thru 15-8 . ......... . 0 18-1 ...... ........ .. 1 5-88 Blank ............. 0 15-8A thru 15-8D ...... 0 18-2 thru 18-5 ........... 0 *5A-1 thru 5A-2 ......... 2 15-9 thru 15-12 ...... 0 18-5A Blank ............ 0 5A3 thru 5A-11 ......... 0 15-13 thru 15-16 ....... 1 18-5B thru 18-5D ....... 0 5A-11A thru 5-11B ... 0 15-16A ............ 1 18-6thru18-24 ......... 0 5A-12thru 5A-18 ....... 0 15-16B Blank ......... 1 19-1 ................... 1 5A18A thru 5A-18B ..... 0 15-17 thru 15-18 ..... 0 19-2 thru 19-3 ........... 0 5A-19thru 5A-26 ....... 0 15-18A thru 15-18B ... 1 19-4 Blank ............. 0 *5A-27 .................. 2 *15-18C ............ 2 20-1 thru 20-2 ........... 1 5A-28 thru 5A-29 ....... 0 20-3 thru 20-130 ....... 0 Upon receipt of the second and subsequent revisions to this book. personnel responsible for maintaining this publication in current status should ascertain that all previous revisions have been received and incorporated. *The asteric indicates pages revised, added or deleted by the current revision A Revision 2 MODEL P210 SERIES SERVICE MANUAL 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 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 MODEL YEAR BEGINNING ENDING PRESSURIZED CENTURION 1978 P210N P21000001 P21000150 PRESSURIZED CENTURION II PRESSURIZED CENTURION 1979 P210N P21000151 P21000385 PRESSURIZED CENTURION II PRESSURIZED CENTURION 1980 P210N P21000386 P21000590 PRESSURIZED CENTURION II PRESSURIZED CENTURION 1981 P210N P21000591 P21000760 PRESSURIZED CENTURION II PRESSURIZED CENTURION 1982 P210N P21000761 P21000811 PRESSURIZED CENTURION II PRESSURIZED CENTURION 1983 P210N P21000812 P21000834 PRESSURIZED CENTURION 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 news letters, service bulletins, supplier service notices, publication changes, revisions, reissues and temporary revisions. All such amendments become part of and are specifically incorporated within this publication. Users are urged to keep abreast of the latest amendments to this publication through information available at Cessna Authorized Service Stations or through the Cessna Product Support subscription which provide disassembly, overhaul, and parts breakdowns for some of the various suppliers equipment items. Suppliers publications are updated, supplemented, and specifically amended by supplier issued revisions and service information which may be reissued by Cessna; thereby automatically amending this publication and is communicated to the field through Cessna Authorized Service Stations and/or Cessna subscription service. WARNING ALL INSPECTION INTERVALS, REPLACEMENT TIME LIMITS, OVERHAUL TIME LIMITS, THE METHOD OF INSPECTION, LIFE LIMITS, CYCLE LIMITS, ETC., RECOMMENDED BY CESSNA ARE SOLELY BASED ON THE USE OF NEW, REMANUFACTURED, OR OVERHAULED CESSNA APPROVED PARTS. IF PARTS ARE DESIGNED, MANUFACTURED, REMANUFACTURED, OVERHAULED, AND/OR APPROVED BY ENTITIES OTHER THAN CESSNA, THEN THE DATA IN CESSNAS MAINTENANCE/SERVICE MANUALS NO LONGER APPLICABLE AND THE PURCHASER IS WARNED NOT TO RELY ON SUCH DATA FOR NON-CESSNA PARTS. ALL INSPECTION INTERVALS REPLACEMENT TIME LIMITS, OVERHAUL TIME LIMITS, THE METHOD OF INSPECTION, LIFE LIMITS, CYCLE LIMITS, ETC., FOR SUCH NON-CESSNA PARTS MUST BE OBTAINED FROM THE MANUFACTURER AND/OR SELLER OF SUCH NON-CESSNA PARTS. 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. 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 listing, revision status checkcards, and temporary revisions may be purchased through Propeller Aircraft Production Support, P.O. Box 7706, Wichita, KS. 67277, phone (316) 941-7674 or fax (316) 942-9006. Revision 2 iii 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 the 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 on Aerofiche. SUPPLEMENTAL TYPE CERTIFICATE INSTALLATIONS Inspection, maintenance and parts required for (STC) installations are not included in this manual. When an STC installation is incorporated on the aircraft, those portions of the aircraft 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 stress on adjacent structures. Cessna provided inspection criteria may not be valid for aircraft 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 return 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. Revision 2 MODEL P210 SERIES SERVICE MANUAL SECTION I GENERAL DESCRIPTION GENERAL DESCRIPTION ....... A8/1-1 Aircraft. . . . . .1A8/1-1 PRESSURIZED CENTURION ... . 1A8/1-1 Stations ....... ...... .1A8/1-1 Description . ....... . 1A8/ 1-1 Bolt Torques. .. ........ . A11/1-4 1-1. GENERAL DESCRIPTION. 1-2. MODEL PRESSURIZED CENTURION SERIES. 1-4. AIRCRAFT SPECIFICATIONS. Leading part- 1-3. DESCRIPTION. The Cessna Pressurized, iculars of these aircraft. with dimensions based on Centurion and Centurion II (P210 Series) Aircraft gross weight, are given in figure 1-1. If these dim- described in this manual, are high-wing, single- ensions are to be used in computing clearance for engine, monoplanes of all metal, semi-monocoque construction of a hangar or other shelter. it should construction. Wings are full cantilever with integral be noted that strut inflation, tire pressure, tire size. fuel bays (wet wing). The fully retractable landing and load distribution will change some dimensions gear consists of tubular-spring steel main gear struts, significantly. and a steerable air/hydraulic nose gear strut. Seat- ing arrangement is six place conventional Powering 1-5. STATIONS. A station diagram is shown in fig- the Pressurized Centurion Series is a Continental, ure 1-2 to assist in locating equipment, when a writ- air-cooled, horizontally-opposed. six-cylinder, fuel- ten description is inadequate or impractical. injected, turbocharged engine, driving a constant speed. three blade propeller. The pressurization system is designed for maximum passenger comfort at altitudes up to aircraft ceiling. by maintaining a 3.35 psi maximum cabin pressure. or the equivalent to a 10,000 ft cabin altitude at 20.000 ft actual. 1-1 MODEL P210 SERIES SERVICE MANUAL P210 SERIES 25.25 MODEL P210 SERIES SERVICE MANUAL 1-6. BOLT TORQUES. The importance of correct d. Add friction drag torque to desired torque application cannot be over emphasized. Under-torque recommended or obtain desired torque as shown in can result in unnecessary wear of nuts and bolts as figure 1-3. This is referred to as final torque well as parts they are holding together. When insuf- which should register on indicator or setting for a ficient pressures are applied, uneven loads will be snapover type wrench. transmitted throughout assembly. which may result e Apply a smooth even pull when applying torque in excessive wear or premature failure due to fatigue. pressure. Lf chattering or a jerking motion occurs Over-torque can be equally damaging because of fail- during final torque, back off and re-torque. ure of a bolt or nut from overstressing threaded areas. f. When installing a castle nut, start alignment There are a few simple, but very important, proce- with cotter pin hole at minimum recommended dures that should be followed to assure that correct torque, plus friction drag torque, and do not exceed torque is applied: maximum plus friction drag. If hole and nut castel- a. Calibrate torque wrench periodically to assure lation do not align change washers or nut and try accuracy; and recheck frequently. again. Exceeding maximum recommended torque is b. Be sure that bolt and nut threads are clean and not recommended unless specifically allowed or dry unless otherwise specified. recommended for that particular installation. c. Run nut down to near contact with washer or bearing surface and check "friction drag torque" required to turn nut. 1-4 MODEL P210 SERIES SERVICE MANUAL BOLTS BOLTS Steel Tension Steel Tension AN 3 thru AN 20 MS 20004 thru MS 20024 AN 42 thru AN 49 NAS 144 thru NAS 158 AN 73 thru AN 81 NAS 333 thru NAS 340 AN 173 thru AN 186 NAS 583 thru NAS 590 MS 20033 thru MS 20046 NAS 624 thru NAS 644 MS 20073 NAS 1303 thru NAS 1320 MS 20074 NAS 172 AN 509 NK9 NAS 174 MS 24694 NAS 517 Steel shear bolt AN 525 NK525 MS 27039 NAS 464 NUTS NUTS Steel Tension Steel Shear Steel Tension Steel Shear AN 310 AN 320 AN 310 AN 320 AN 315 AN 364 AN 315 AN 363 NAS 1022 AN 363 NAS 1022 AN 365 MS 17826 AN 365 MS 17826 NAS 1021 MS 20364 MS 17825 MS 20364 MS 17825 MS 20365 MS 21045 MS 21045 MS 20365 NAS 1021 MS 20500 NAS 679 NAS 679 NAS 1291 FINE THREAD SERIES Nut-bolt Torque Limits Torque Limits Torque Limits Torque Limits size in-lb*. in.-lbs in-lb. n -lbs Min. Max Min Max Min. Max. Min Max 8-36 12 15 7 9 25 30 15 20 10-32 20 25 12 15 80 100 50 60 1/4-28 50 70 30 40 120 145 70 90 5/16-24 100 140 60 85 200 250 120 150 3/8-24 160 190 95 110 520 630 300 400 7/16-20 450 500 270 300 770 950 450 550 1/2-20 480 690 290 410 1100 1300 650 800 9/16-18 800 1000 480 600 1250 1550 750 950 5/8-18 1100 1300 660 780 2650 3200 1600 1900 3/4-16 2300 2500 1300 1500 3550 4350 2100 2600 7/8-14 2500 3000 1500 1800 4500 5500 2700 3300 1-14 3700 4500 2200 3300 6000 7300 3600 4400 1-1/8-12 5000 7000 3000 4200 11000 13400 6600 8000 1-1/4.12 9000 11000 5400 6600 COARSE THREAD SERIES Torque Limits Torque Limits n-lbs. in -lbs Min Max Min Max 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 95 110 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 Figure 1-3. Bolt Torques. 1-5/(1-6 blank MODEL P210 SERIES SERVICE MANUAL SECTION 2 GROUND HANDLING, SERVICING, CLEANING, LUBRICATION AND INSPECTION When performing any inspection or maintenance that - requires turning on the master switch, installing a bat- tery, 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 compo- nent malfunction, could cause the propeller to rotate. Page No. TABLE OF CONTENTS Aerofiche/Manual GROUND HANDLING ................. 1A17/2-1 Hydraulic Brake Systems ............. 1B2/2-8 Towing ............................. 1A17/2-1 Landing Gear Hydraulic Retraction Hoisting ............................ 1A17/2-1 System ........................... 1B2/2-8 Jacking ............................ 1A17/2-1 Hydraulic Fluid Sampling and Leveling .......................... 1A18/2-2 Contamination .................... 1B2/2-8 Weighing ........................... 1A18/2-2 Oxygen System ...................... 1B3/2-9 Parking ............................ 1A18/2-2 Face Masks .......................... 1B3/2-9 Tie-Down ........................... 1A18/2-2 CLEANING ............................ 1B3/2-9 Flyable Storage ..................... 1A18/2-2 General Description .................. 1B3/2-9 Returning Aircraft to Service ......... 1A18/2-2 Upholstery and Interior ............... 1B3/2-9 Temporary Storage .................. 1A21/2-4 Plastic Trim ......................... 1B3/2-9 Inspection During Storage ............ 1A21/2-5 Windshield and Windows .............. 1B3 2-9 ReturningAircraft to Service ......... 1A21/2-5 Required Materials ................ 1B3i2-9 Indefinite Storage ................... 1A21/2-5 Cleaning Instructions ............. 1B4/2-10 Inspection During Storage ............ 1A22/2-6 Windshield and Window Returning Aircraft to Service ......... 1A22/2-6 Preventive Maintenance ........ 1B4/2-10 SERVICING ........................ 1A23/2-6A Aluminum Surfaces ................ 1B5/2-10A Description ........................ 1A23/2-6A Painted Surfaces .................. 1B5/2-10A Fuel Tanks ...................... 1A23/2-6A Engine and Engine Compartment .... 1B5/2-10A Fuel Additives ..................... 1A23/2-6A Propeller ........................... 1B7/2-11 Fuel Drains ....................... 1A24/2-6B Wheels ............................. 1B7/2-11 Engine Oil ........................ 1A24/2-6B LUBRICATION ....................... 1B7/2-11 Hydraulic Fluid ...................... 1B1/2-7 General Description ................. 1B7/2-11 Engine Induction Air Filter ............ 1B1/2-7 Nose Gear Torque Links .............. 1B7/2-11 Vacuum System Air Filter ............. 1B1/2-7 Tachometer Drive Shaft .............. 1B7/2-11 Battery .............................. 1B1/2-7 WingFlapActuator ................. 1B7/2-11 Tires ............................... 1B1/2-7 RodEndBearings ................... 1B7/2-11 Nose Gear Strut ...................... 1B2/2-8 INSPECTION ........................ 1B16/2-20 Nose Gear Shimmy Dampener ......... 1B2/2-8 2-1. GROUND HANDLING. The front sling should be hooked to the engine lifting eye, and the aft sling should be positioned around the 2-2. TOWING. Moving the aircraft by hand is ac- fuselage at the first bulkhead forward of the leading complished by using the landing gear struts as push edge of the stabilizer. points. A tow bar attached to the nose gear should be used for steering and maneuvering the aircraft. 2-4. JACKING. Refer to figure 2-2 forjacking pro- cedures. 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 the gear strut will cause the not push on control surfaces or outboard em- main wheel 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 landing gear strut jack pad is not recom- 2-3. HOISTING. The aircraft may be hoisted with mended. a hoist of two-ton capacity by using suitable slings. Revision 2 2-1 MODEL P210 SERIES SERVICE MANUAL TOW BAR: PART NUMBER 0501019-1 OR 0700315-4 (TELESCOPING) IS AVAILABLE FROM THE CESSNA SERVICE PARTS CENTER. 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 U 2-5. PARKING. Parking precautions depend prin- Ths 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 costty. 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- CAUTION 1 tion it was in. If the aircraft is stored outside, tie- down in accordance with paragraph 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- try of foreign material. If at the end of thirty (30) a. Tie ropes. cables or chains to the wing tie-down days aircraft will not be removed from storage, the fittings located midwing in line with the outboard edge engine shall be started and run. The preferred of the flaps. Secure the opposite ends of ropes, cables method would be to fly the airraft for thirty (0) borchains to ground anchorse minutes, and up to, but not exceeding normal oil and b. Secure a tie-down rope (no chains or cables) cylinder temperatures. to upper trunnion of the nose gear, and secure oppo- site end of rope to ground anchor. |CAUTIOI c. Secure the middle of a rope to the tail tie-down ring. Pull each end of rope away at a 45-degree Excessive ground operation shall be avoided. angle and secure to ground anchors at each side of tail. 2-8. RETURNING AIRCRAFT TO SERVICE. After d. Secure control lock on pilot control column. If flyable storage, returning the aircraft to service is control lock is not available, tie pilot control wheel accomplished by performing a thorough preflight in- back with front seat belt.*back with front seat belt. ...... spection. At the end of the first 25 hours of engine e. These aircraft are equipped with a spring-loaded opration, drain engine oil and change external oil steering bungee which affords protection against nor- filter element. Service engine with correct grade mal wind gusts. However. if extremely high wind a quantity of oil Refer to figure 2-4 and para- gusts are anticipated, additional locks may be install- graph 2-20 for correct grade of engine oil ed. 2-2 MODEL P210 SERIES SERVICE MANUAL 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. SHOP NOTES: 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. RETURNING AIRCRAFT TO SERVICE. 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 spraved. 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. 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 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, 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 Therefore, to alleviate the possibility of fuel icing Install and safety drain plug. occurring under these unusual conditions it is per- f. Remove and clean engine oil screen, then reinst missible to add isopropyl alcohol or ethyelene glycol reinstall and safety. Install new oil filter. monomethyl ether (EGME) compound to the fuel sup- ply. See figure 2-3 for fuel additive mixing ratio. NOTE The introduction of alcohol or EGME compound into the fuel provides two distinct effects: 1) it absorbs The corrosion-preventive mixture will mix the dissolved water from the gasoline and 2) alcohol with the engine lubricating oil, so flushing has a freezing temperature depressant effect. the oil system is not necessary. Draining the oil sump will remove enough of the Alcohol, if used, is to be blended with the fuel in a corrosion-preventive mixture. concentration of 1% by volume. Concentrations greater than 1% are not recommended since they can g Service and install the induction air filter. be detrimental to fuel tank materials. h. Remove dehydrator plugs and spark plugs or plugs installed in spark plug holes and rotate The manner in which the alcohol is added to the fuel propeller by hand several revolutions to clear is significant because alcohol is most effective when corrosion-preventive mixture from cylinders. it is completely dissolved in the fuel. To insure . Clean. gap and install spark plugs. Torque proper mixing the following is recommended. plugs to value listed in Section 12. j. Check fuel strainer. Remove and clean filter 1. For best results the alcohol should be added screen. Check fuel tanks and fuel lines for during the fueling operation by pouring the alcohol moisture and sediment. and drain enough fuel to directly on the fuel stream issuing from the fuel eliminate. nozzle. k. Perform a thorough pre-flight inspection. then 2. An alternate method that may be used is to start and warm-up engine. premix the complete alcohol dosage with some fuel 1. Thoroughly clean aircraft and flight test in a separate clean container (approximately 2-3 aircraft. gallon capacity) and then transfer this mixture to the 2-15. SERVICING tank prior to the fuel operation. 2-16 DESCRIPTION. Servicing requirements are Any high quality isopropyl alcohol may be used, such 2-16 DESCRIPTION. Servicing requirements are shown in figure 2-4. The following paragraphs as: Anti-icing fluid (MIL-F-5566) or Isopropyl alco- supplement this figure by adding details not hol (Federal Specification TT-I-735a). included in the figure. Ethylene glycol monomethyl ether (EGME) compound in compliance with MIL-I-27686 or Phillips PFA- 2-17 FUEL TANKS. An area of each wing is 55MB, if used, must be carefully mixed with the fuel sealed to form an integral fuel tank. in concentrations not to exceed 0. 15% by volume. Recommended fuel grade is listed in figure 2-4. and fuel capacities are given in figure 1-1. Fuel bays CAUTION should be filled immediately after flight to lessen condensation in the bays and lines. Mixing of the EGME compound with the fuel is extremely important because concentra- 2-18. USE OF FUEL ADDITIVES FOR COLD tion in excess of that recommended (0.15 WEATHER OPERATION. Strict adherence to recom- percent by volume maximum) will result in mended preflight draining instructions will eliminate detrimental affects to the fuel tanks, such any free water accumulations from the tank sumps. as deterioration of protective primer and While small amounts of water may still remain in sealants and damage to O-rings and seals solution in the gasoline, it will normally be consumed in the fuel system and engine components. and go unnoticed in the operation of the engine. Use only blending equipment that is recom- mended by the manufacturer to obtain proper One exception to this can be encountered when oper- proportioning. ating under the combined effect of: 1) use of certain fuels, with 2) high humidity conditions on the ground Do not allow the concentrated EGME com- 3) followed by flight at high altitude and low tempera- pound to come in contact with the airplane ture. Under these unusual conditions small amounts finish or fuel cell as damage can result. of water in solution can precipitate from the fuel stream and freeze in sufficient quantities to induce Prolonged storage of the airplane will result in a partial icing of the engine fuel system. water buildup in the fuel which "leeches out" the additive. An indication of this is when an excessive While these conditions are quite rare and will not amount of water accumulates in the fuel tank sumps. normally pose a problem to owners and operators, The concentration can be checked using a differential they do exist in certain areas of the world and con- refractometer. It is imperative that the technical sequently must be dealt with when encountered. manual for the differential refractometer be followed explicitly when checking the additive concentration. 2-6A MODEL P210 SERIES SERVICE MANUAL 140- 18 4.5 16 14 3.5 100 3.0 12 80 10 2.5 60 4 1.0 0 0 0.0 0 10 20 30 40 50 60 70 80 90 100 110 GALLONS OF GASOLINE Figure 2-3. Fuel Additive Mixing Ratio Chart 2-19. FUEL DRAINS. Drains are located at various NOTE Places throughout the fuel system. Refer to Section 13 for locations of the various drains in the system. The aircraft is delivered from Cessna with Remove drain plugs, actuate strainer drain and open a corrosion preventive aircraft engine oil all drain valves at the intervals specified In figure (MIL-C-6259, Type II). If oil must be 2-4. Drain valves are installed in the fuel bays and added during the first 25 hours of opera- in the reservoirs, and a fuel sampler cup is furnished. tion, use only aviation grade straight min- To activate the drain for sampling, place cup to valve eral oil conforming to Specification MIL-L- and depress valve with rod protruding from cup. If 6082. After the first 25 hours of operation, water is found during daily inspection of the fuel drain engine oil sump and change filter ele- strainer and fuel bay sump drains, open all drain ment. Refill sump with correct quantity and valves and remove all fuel drain plugs to drain all grade of ashless dispersant oil conforming water from the fuel system. to Continental Motors Specification MHS-24 and with current Continental Aircraft Engine Service Bulletins. Newly overhauled engines 2.20 ENGINE OIL. Check engine lubricating oil should also be operated on aviation grade with the dipstick five to ten minutes after the straight mineral oil conforming to Specifica- engine has been stopped The aircraft should be in tion MIL-L-6082 until a total of 25 hours as near a level position as possible when checking have accumulated. the engine oil so that a true reading is obtained. Engine oil should be drained while the engine Is When changing engine oil, install a new filter element. still hot. and the nose of the aircraft should be To drain oil, proceed as follows: raised slightly for more positive draining of any a. Operate engine until oil temperature is at nor- sludge which may have collected in the engine oil mal operating temperature. sump. Engine oil should be changed every six months, b. Remove oil drain plug from engine sump and even though less than the specified hours have accu- allow oil to drain into a container. mulated. Reduce these intervals for prolonged opera- c. After engine oil has drained, install and safety tions in dusty areas and in cold climates where sludg- drain plug. ing conditions exist. or where short flights and long d. Change external oil filter element. idle periods are encountered, which cause sludging e. Service engine with correct quantity and vis- conditions. Always change oil and change external cosity of aviation grade engine oil. filter element whenever oil on the dipstick appears dirtv. Aviation grade ashless dispersant oil conform- NOTE ing to Continental Motors Specification MHS-24. and all revisions or supplements thereto. and conforming Refer to inspection charts for intervals with current Continental Aircraft Engine Service Bul- for changing engine oil and external filter letins shall be used. elements. Refer to figure 2-4 for correct viscosities and capacities of aviation grade engine oil. 2-6B MODEL P210 SERIES SERVICE MANUAL 2-20A. HYDRAULIC FLUID. Refer to figure 2-4. rinse water draining from filter is clear. Allow water to drain from filter and dry with compressed air (not over 2-21. ENGINE INDUCTION AIR FILTER. The 100 psi). induction air filter keeps dust and dirt from entering the induction system. The value of maintaining the air NOTE filter in a good clean condition can never be over stressed. More engine wear is caused through the use of a dirty The filtering panels of the filter may become or damaged air filter than is generally believed. The distorted when wet, but they will return to frequency with which the filter should be removed, their original shape when dry. inspected, and cleaned will be determined primarily by aircraft operating conditions. A good general rule, f. Be sure airbox is clean, and inspect filter. If filter however, is to remove, inspect, and clean filter at least is damaged, a new filter should be installed. every 50 hours of engine operating time, and more g. Install filter at entrance to airbox with gasket on frequently if warranted by operating conditions. Under aft face of filter frame and with flow arrows on filter extremely dusty conditions, daily service of the filter, frame pointed in the same direction. is recommended. To service the induction air filter proceed as follows: 2-22. VACUUM SYSTEM CENTRAL AIR FILTER. a. Remove filter from aircraft. The disposable type central air filter keeps dust and dirt from entering the vacuum operated flight instruments. NOTE Inspect the filter every 200 hours for damage. The filter should be replaced every 500 hours of operation and Use care to prevent damage to filter element whenever it becomes sufficiently clogged to cause suction when cleaning filter with compressed air. gage readings to drop below 4.6 in hg. The system should not be operated at any time without a filter, nor are any b. Clean filter by blowing with compressed air (not lines to be left open when performing maintenance on the over 100 psi) from direction opposite of normal air flow. system, as minute particles of dust or other foreign mater- Arrows on filter case indicate direction of normal air ials may enter the lines and could severely damage the flow. gyro instruments. c. Check bonding of the paper pleats to the face screen. The bonding holds the paper pleats in place CAUTION and if broken, the pleats are free to shift which can impair filtration. A face screen that is loose or gap- Excessive smoking will cause premature ping away from the paper pleats is indicative of filter clogging. broken bonding and is cause to replace the filter element. 2-23. BATTERY. Battery servicing involves adding distilled water to maintain the electrolyte even with 1.... the horizontal baffle plate or split ring at the bottom Do not use solvent or cleaning fluids to wash of the filler holes checking cable connections, and neu- filter. Use only a water and household deter- tralizing and cleaning off any spilled electrolyte or gent solution when washing the filter. corrosion. Use bicarbonate of soda (baking soda) and clean water to neutralize electrolyte or corrosion. d. After cleaning as outlined in step "b.", the filter may Follow with a thorough flushing with clean water. Do be washed, if necessary, in a solution of warm water and a not allow bicarbonate of soda to enter battery. Brighten mild household detergent. A cold water solution may be cable and terminal connection with a wire brush, then used. coat with petroleum jelly before connecting. Check the battery every 50 hours (or at least every 30 days), more NOTE often in hot weather. Add only distilled water, not acid or rejuvenators, to maintain electrolyte level in the The filter assembly may be cleaned with com- battery. Inspect the battery box and clean and remove pressed air a maximum of 30 times or it may be any evidence of corrosion. washed a maximum of 20 times. A new filter should be installed after using 500 hours of en- 2-24. TIRES. Maintain tire pressure at the value gine operating time or one year, whichever specified in Section 1. When checking pressure, examine occurs first. However, a new filter should be tire for wear, cuts, bruises and slippage. installed anytime the existing filter is damag- ed. A damaged filter may have sharp or broken NOTE edges in the filtering panels which would allow unfiltered air to enter the induction system. Recommended tire pressure should be main- Any filter that appears doubtful, shall have a tained. Especially in cold weather. Remember new filter installed in its place. that any drop in temperature of the air inside a tire causes a corresponding drop in pressure. e After washing, rinse filter with clear water until Revision 2 2-7 MODEL P210 SERIES SERVICE MANUAL 2-25. NOSE GEAR STRUT. The nose gear strut re- 3. 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- 4. Reinstall filler plug and safety. rect air pressure. To fill the nose gear strut with 5. 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. 6. 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 portion of the dampener piston MIL-0-5606. 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 surfaces tion hole. wiped free of dirt and dust, using a clean e. Fully extend strut. lint-free cloth saturated with hydraulic f. Replace valve housing assembly. fluid (MIL-H-5606) or kerosene. All g. With strut fully extended and nose wheel clear surfaces should be wiped free of excess- of ground, inflate strut to 80 PSI. ive hydraulic fluid. NOTE 2-27. HYDRAULIC BRAKE SYSTEMS. Check brake master cylinders and refill with hydraulic fluid as The nose landing gear shock strut will nor- specified in the inspection charts. Bleed the brake mally require only minimum amount of system of entrapped air whenever there is a spongy service. Maintain the strut extension pres- response to the brake pedals. Refer to Section 5 sure as shown in Section 1. Lubricate for filling and bleeding the brake systems. landing gear as shown in figure 2-5. Check the landing gear daily for general cleanliness, 2-28. LANDING GEAR HYDRAULIC RETRACTION security of mounting, and for hydraulic fluid SYSTEM. Draining, filling, and bleeding of the land- leakage. Keep machined surfaces wiped free ing gear hydraulic system can be accomplished by of dirt and dust, using a clean lint-free cloth the following method. saturated with hydraulic fluid (MIL-H-5606) a. Place aircraft master switch in OFF position or kerosene. All surfaces should be wiped and place aircraft on jacks as shown in figure 2-2. free of excessive hydraulic fluid. Bleed pressure from system by moving landing gear selector valve to gear UP position. 2-26. NOSE GEAR SHIMMY DAMPENER. The shimmy dampener should be serviced at least 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 lines. 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 landing gear through NOTE several cycles. Refill power pack reservoir with MIL-H-5606 hydraulic fluid and remove aircraft If the wire insertion is less than 3-13/16 from 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, e. Service the shimmy dampener as Follows: a sample of fluid should be taken and examined for 1. Remove filler plug from dampener sediment and discoloration. This may be done as 2. Move piston completely to opposite end from follows: filler plug. 2-8 Revision 2 MODEL P210 SERIES SERVICE MANUAL a. Place aircraft master switch in OFF position appearance of the aircraft, cleaning lessens the and place aircraft on jacks as shown in figure 2-2. possibility of corrosion and makes inspection and Bleed pressure from system by moving landing gear maintenance easier. selector valve to gear UP position. 2-34. UPHOLSTERY AND INTERIOR. Cleaning CAUTION prolongs the life of upholstery fabrics and interior trim. To clean the interior, proceed as follows; Do not turn master switch ON while hydraulic a. Empty all the ash trays. system is open to atmosphere. The pump will b. Brush out or vacuum clean the upholstery and automatically start, causing hydraulic fluid carpeting to remove dirt. to spray from open line. c. Wipe leather and plastic surfaces with a damp cloth. b. Remove cap from elbow on right side of power d. Soiled upholstery fabrics and carpet may be pack (behind access cover) and place a nonmetal con- cleaned with a foam-type detergent, used tainer below opening. according to the manufacturers instructions. c. Place landing gear selector valve in DOWN posi- e. Oily spots and stains may be cleaned with house- tion and operate emergency hand pump to pump fluid hold spot removers, used sparingly. Before using any into container. solvent, read the instructions on the container, and test d. If the drained fluid is clear and not appreciably it on an obscure place in the fabric to be cleaned. Never darker in color than new fluid, continue to use the saturate the fabric with a volatile solvent, it may present fluid. damage the packing and backing material. e. If the fluid color is doubtful, place a fluid sam- f. Scrape off sticky materials with a dull knife. pie in a nonmetallic container and insert a strip of then spot clean the area. polished copper in the fluid. f. Keep copper in the fluid for six hours at a tem- 2-35. PLASTIC TRIM. The instrument panel, perature of 70°F or more. A slight darkening of the plastic trim and control knobs need only be wiped copper is permissible, but there should be no pitting off with a damp cloth. Oil and grease on the control or etching evident, if so drain fluid from power pack wheel and control knobs can be removed with a reservoir. Fill power pack with MIL-H-5606 hy- cloth moistened with Stoddard solvent. draulic fluid and bleed air from system. * CAUTION 2-30. OXYGEN SYSTEM. Refer to Section 15. - Do not use gasoline, alcohol, benzene, 2-31. FACE MASKS Refer to Section 15. acetone, carbon tetrachloride, fire ex- tinguisher fluid, de-icer fluid, lacquer 2-32. CLEANING. thinner, or glass window cleaning spray. These solvents will soften and craze the 2-33. GENERAL DESCRIPTION. Keeping the aircraft plastic. clean is important. Besides maintaining the trim 2-36. WINDSHIELD AND WINDOWS. 2-36A REQUIRED MATERIALS. NAME MANUFACTURER USE Mild soap or detergent (hand dish- Commercially available Cleaning windshields and windows. washing type without abrasives) Aliphatic naphtha Type II Commercially available Removing deposits which cannot conforming to Federal be removed with mild soap solution Specification TT-N-95 on acrylic windshields and windows. Polishing Wax: Waxing acrylic windshields and (Refer to Note 1) windows. Turtle Wax (paste) Turtle Wax, Inc. 5655 W 73 RD St. Chicago, IL 60638 Great Reflections Paste Wax E. I. Du-Pont De Nemours and Co. (Inc ) Wilmington, DE 19Y98 Slip-stream Wax (paste) Classic Chemical 3131 Turtle Creek Suit 1010 Dallas, TX 75050 Revision 2 2-9 MODEL P210 SERIES SERVICE MANUAL 2-36A. REQUIRED MATERIALS. (Cont NAME MANUFACTURER USE Acrylic Polish conforming Cleaning and polishing to Federal Specification acrylic windshields and P-P-560 such as: windows. Permatex plastic Loctite Corp,'North America Group cleaner Number 403D 1001 Trout Brook Crossing Rocky Hill, CT 06067 Mirror Glaze MGH-7 Meguiars Mirror Bright Polish 210 N Firt Ave. Arcadia, CA 91006 Soft cloth, such as: Commercially available Applying and removing wax Cotton flannel or cotton terry and polish. cloth material NOTE 1 These are the only polishing waxes tested and approved for use by Cessna Aircraft Company. 2-36B. CLEANING INSTRUCTIONS. NOTE CAUTION When applying and removing wax and polish, use a clean soft cloth. Windshields and windows (Acrylic Faced) are easily damaged by improper handling and h. Do not use rain repellent on acrylic surfaces. cleaning techniques. 2-36C. WINDSHIELD AND WINDOW PREVENTIVE a. Place aircraft inside hanger or in shaded area and MAINTENANCE. allow to cool from heat of suns direct rays. b. Using clean (preferably running) water, flood the NOTE surface. Use bare hands, with no jewelry, to feel and dislodge any dirt or abrasive materials. Utilization of the following techniques will c. Using mild soap or detergent(such as a dishwashing help minimize windshield and window crazing. liquid) in water, wash the surface. Again use only the bare hand to provide rubbing force. A clean cloth may be used a. Keep all surfaces of windshields and windows clean. to transfer the soap solution to the surface, but extreme b. If desired, wax acrylic surfaces. care must be exercised to prevent scratching the surface. c. Carefully cover all surfaces during any painting, d. On acrylic windshields and windows only, if soils powerplant cleaning or other procedure that calls for the which cannot be removed by a mild detergent remain, use of any type of solvents or chemicals. The following Type II aliphatic naphtha applied with a soft cloth may coatings are approved for use in protecting surfaces be used as a cleaning solvent. Be sure to frequently re- from solvent attack. fold the cloth to avoid redepositing soil and/or scratching 1. White Spray Lab, MIL-C-6799, Type I, Class II windshield with any abrasive particles 2. WPL-3 Masking Paper - St. Regis, 156 Oak St. e. Rinse surface thoroughly with clean fresh water and Newton Upperfalls, MA, 02164-1440 dry with a clean cloth. 3. 5x N - Poly-Spotstick - St. Regis, 156 Oak St. Newton Upperfalls, MA, 02164-1440 CAUTION 4. Protex 40 - Mask OffCompany, 345 Maple Av. Monrovia, CA, 91016-3331 and Southwest Paper Do not use any of the following on or for clean- Co., 3930 N. Bridgeport Cir.Wichita, KS 67219 ing windshields and windows: Methanol, 5. Protex 10VS - Mask Off Company, 345 Maple Av. Denatured Alcohol, Gasoline. Benzene, Xylene, Monrovia, CA,91016-3331 and Southwest Paper MEK, Acetone, Carbon Tetrachloride, Lacquer Co., 3930 N. Bridgeport Cir. Wichita, KS 67219 Thinners, commercial or household window 6. Scotch 344 Black Tape - 3M Company cleaning sprays. Additionally, strong acids or d. Do not park or store aircraft where it might be bases may destroy antistatic coatings on glass subjected to direct contact with or vapors from: windshields. When in doubt, DO NOT USE IT methanol, denatured alcohol, gasoline, benzene, xylene, MEK, acetone, carbon tetrachloride, lacquer f. Hard polishing wax should be applied to acrylic thinners, commercial or household window cleaning surfaces (The wax has an index of refraction nearly sprays, paint strippers, or other types of solvents. the same as transparent acrylic and will tend to mask e. Do not use solar screens or shields installed inside any shallow scratches on the windshield surface. of aircraft, or leave sun visors up against windshield. The g. Acrylic surfaces may be polished using a polish reflected heat from these items cause elevated temper- meeting Federal Specification P-P-560, applied per atures which accelerate crazing and may cause forma- the manufacturers instructions tion of bubbles in the inner ply of multiple ply windshields. 2-10 Revision 2 MODEL P210 SERIES SERVICE MANUAL f. Do not use a power drill motor or other powered Perform all cleaning operations in well ventilated work device to clean, polish, or wax surfaces. areas and ensure that adequate fire fighting and safety equipment is available. Do not smoke or expose a flame, 2-37. ALUMINUM SURFACES. The aluminum surfaces within 100 feet of cleaning area. Compressed air, used require a minimum of care, but should never be neglected. for cleaning agent, application or drying, should be The aircraft may be washed with clean water to remove regulated to the lowest practical pressure. Use of a stiff dirt and may be washed with nonalkaline grease solvents bristle brush rather than a steel brush is recommended if to remove oil and/or grease. Household type detergent cleaning agents do not remove excess grease and grime soap powders are effective cleaners, but should be used during spraying. A recommended procedure for cautiously since some of them are strongly alkaline. cleaning an engine and accessories is as follows: Many good aluminum cleaners, polishes, and waxes are available from-commercial suppliers or aircraft products. CAUTION 2-38. PAINTED SURFACES. The painted exterior Do not attempt to wash an engine which is surfaces of your new Cessna have a durable, long hot or running. Allow engine to cool before lasting finish. Approximately 10 days are required cleaning. for the paint to cure completely; in most cases, the curing period will have been completed prior to delivery of the a. Remove engine cowling. aircraft. In the event that polishing or buffing is required b. Carefully cover the coupling area between the within the curing period, it is recommended that work be vacuum pump and engine drive shaft so that cleaning done by someone experienced in handling uncured paint. solvent cannot reach the coupling or seal. Any Cessna Service Station can accomplish this work. c. Cover the open end of the vacuum discharge tube. d. Cover the vacuum relief valve filter, if installed Generally, painted surfaces can be kept bright by washing in the engine compartment. with water and mild soap, followed by a rinse with water e. Use fresh water for wash down when the engine is and drying with cloths or a chamois. Harsh or abrasive contaminated with salt or corrosive chemicals. A soaps or detergents which could cause corrosion or cleaning agent such as described previously may then scratches should never be used. Remove stubborn oil and be used to remove oil and grime. grease with a cloth moistened with Stoddard solvent. CAUTION To seal any minor surface chips or scratches and protect against corrosion, the aircraft should be waxed regularly Care should be exercised to not direct with a good automotive wax applied in accordance with cleaning agents or water streams at the manufacturers instructions. If the aircraft is operated openings on the starter, magnetos, in a seacoast or other salt water environment, it must be alternator, vacuum pump or turbocharger washed and waxed more frequently to assure adequate relief valve. protection. Special care should be taken to seal around rivet heads and skin laps, which are the areas most suscep- f. Thoroughly rinse with clean warm water to re- tible to corrosion. A heavier coating of wax on the lead- move all traces of cleaning agents. ing edges of the wings and tail and on the cowl nose cap and propeller spinner will help reduce the abra- CAUTION sion encountered in these areas. Reapplication of wax will generally be necessary after cleaning with Cleaning agents should never be left on engine soap solutions or after chemical deicing operations. components for an extended period of time. failure to remove them may cause damage to 2-43. ENGINE AND ENGINE COMPARTMENT. An fire sleeves, and could cause additional corrosion. engine and accessories washdown should be accomplished during each 100-hour inspection to remove oil, grease, salt g. Completely dry engine and accessories using corrosion or other residue that might conceal component clean, dry compressedair. defects during inspection. Also, periodic cleaning can be h. Remove the cover over the coupling area. very effective in preventive maintenance. i. Remove the cover from the vacuum discharge tube. j. Remove the cover from the vacuum relief valve Precautions should be taken when working with clean- filter, if installed. ing agents such as wearing of rubber gloves, an apron or k. If desired, engine cowling may be washed with the coveralls and a face shield or goggles. Use the least toxic same cleaning agents, then rinsed thoroughly and wiped of available cleaning agents that will satisfactorily accom- dry. After cleaning engine, relubricate all control arms plish the work. These cleaning agents include: (1) Stoddard and moving parts required. Solvent (Specification P-D-680 type II), (2) A water alka- 1. Reinstall engine cowling. line detergent cleaner (MIL-C-25769J) mixed, 1 part cleaner, 2 to 3 parts water and 8 to 12 parts Stoddard Sol- WARNING vent or 13. A solvent base emulsion cleaner (MIL-C-4361B) mixed 1 part cleaner and 3 parts Stoddard Solvent. For maximum safety, check that the magneto switches are OFF, the throttle is closed, the mix- CAUTION ture control is in the idle cut-off position, and the airplane is secured before rotating the propeller Do not use gasoline or other highly flammable by hand. Do not stand within the arc of the pro- substances for washdown peller blades while turning the propeller. Revision 2 2-10A"(2-10B blank 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 2-47. WING FLAP ACTUATOR. Clean and paint, and cracks or dents in the wheel halves or in lubricate wing flap actuator jack screweach 100 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 hurs as follows cracked wheel halves. flanges or hubs and install a. Expose jack screw by operating flaps to full- b. Clean jack screw threads with solvent rag and ~~~2-42. LUBRICATION.~dry with compressed air. 2-42. LUBRICATION. 2-43. GENERAL DESCRIPTION. Lubrication NOTE requirements are outlined in figure 2-5. Before It is not necessary to remove actuator adding lubricant to a fitting, wipe the fitting free of from aircraft to clean or lubricate threads. dirt. Lubricate until grease appears around part being lubricated and wipe excess grease from parts. The following paragraphs supplement c. With oil can. apply light coat of No. 10 weight. parts. The following paragraphs supplement non-detergent oil to threads of jack screw. figure 2.5 by adding details not shown in the figure. non-detergent oil to threads of jack screw. 2-44. NOSE GEAR TORQUE LINKS. Lubricate 2-48. ROD END BEARINGS. Periodic inspection torque links every 50 hours. When operating in and lubrication is required to prevent corrosion of torque links every 50 hours. When operating in the rod end. At each 100-hour dusty conditions, more frequent lubrication is the bearing in the rod end. At each 100-hour recommended frequent inspection. disconnect the control rods at the aileron and inspect each rod end for corrosion. If 2-45. TACHOMETER DRIVE SHAFT. Refer to no corrosion is found, wipe the surface of the rod Section 16 for lubrication instructions. end balls with general purpose oil and rotate ball freely to distribute the oil over its entire surface and connect the control rods to the aileron. If corrosion is detected during inspection. install new rod ends. 2-11 MODEL P210 SERIES SERVICE MANUAL HYDRAULIC FLUID: SPEC. NO. MIL-H-5606 SPECIFIED AVIATION GRADE FUELS: WARNING ONLY AVIATION GRADE FUELS ARE APPROVED FOR USE. ENGINE MODEL APPROVED FUEL GRADES NOTE Continental TSIO-520-P 100LL (blue) 1 100 (green) (formerly 100/130) 1 NOTE 1. Compliance with Continental Aircraft Engine Service Bulletin M81-11, and all supplements or revisions thereto, must be accomplished. SPECIFIED AVIATION GRADE OIL: AVERAGE AMBIENT TEMPERATURE (OF) / OIL GRADE 0 10° 200 300 400 500 60° 700 80c 90o - SAE25W60 -- SAE 30 -- SAE 50 SSAE20W-501 Aviation grade ashless dispersant oil, conforming to Continental Motors Specification MHS-24, and all revisions or supplements thereto, must be used except as noted in paragraph 2-20, herein. Refer to Continental Aircraft Engine Service Bulletin M81-11, and any superseding bulletins, revisions or supplements thereto, for further recom- mendations. 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. U an external oil filter is installed, one additional quart of oil is required when filter is changed. CAPACITY CAPACITY (TOTAL NORMAL MINIMUM (TOTAL) WITH FILTER) OPERATION FOR FLIGHT 10 11 8 7 Figure 2-4. Servicing (Sheet 2 of 4) 2-13 MODEL P210 SERIES SERVICE MANUAL DAILY 1 FUEL BAYS: Service after each flight. Keep full to retard condensation. Refer to paragraph 2-18 for details. 5 FUEL BAY SUMP DRAINS: Drain off any water and sediment before first flight of the day. 18 FUEL STRAINER: Drain off any water and sediment before first flight of the day. 14 OIL DIPSTICK Check on preflight. Add oil as necessary. Refer to paragraph 2-20 for details. Check that filler cap is tight and oil filler is secure. 8 PITOT AND STATIC PORTS: Check for obstructions before first flight of the day. 16 NOSE GEAR SHOCK STRUT: Check on preflight. Check inner barrel showing below outer barrel to be 1.00-2. 00 (approxi- mately 1.20) inches after bouncing. Deviation from these dimensions is cause to check and service strut per paragraph 2-25. 25 HOURS 20 ENGINE OIL SYSTEM: FIRST 25 HOURS Refill with ashless dispersant oil. 19 HYDRAULIC POWER PACK: Check every 25 hours and after a gear extension which uses the hydraulic hand pump. 50 HOURS 21 INDUCTION AIR FILTER: Clean filter per paragraph 2-21. Replace as required. 12 BATTERY: Check electrolyte level and clean battery compartment each 50 hours or each 30 days. 17 SHIMMY DAMPENER: Check fluid level and refill as required in accordance with paragraph 2-26. 10 TIRES: Maintain correct tire inflation as listed in Section 1. Refer to paragraph 2-24 for details. 16 NOSE GEAR SHOCK STRUT: Keep strut filled and inflated to correct pressure. Refer to paragraph 2-25 for details. 2 HYDRAULIC FLUID RESERVOIR: At first 50 and first 100 hours, thereafter at each 500 hours or one year, whichever comes first, a sample of hydraulic fluid should be examined for sediment and discoloration as outlined in paragraph 2-29. Figure 2-4. Servicing (Sheet 3 of 4) 2-14 MODEL P210 SERIES SERVICE MANUAL -- 100 HOURS 2 HYDRAULIC FLUID RESERVOIR: At first 50 and first 100 hours, thereafter at each 500 hours or one year, whichever comes first, a sample of hydraulic fluid should be examined for sediment and discoloration as outlined in paragraph 2-29. 3 FUEL/AIR CONTROL UNIT SCREEN: Remove and clean screen. 18 FUEL STRAINER: Disassemble and clean strainer bowl and screen. 20 ENGINE OIL SYSTEM: Change oil and filter each 100 hours or every 6 months, whichever comes first. 4 VACUUM SYSTEM RELIEF VALVE URETHANE FILTER: Replace every 100 hours. 200 HOURS 7 VACUUM SYSTEM CENTRAL AIR FILTER: Inspect every 200 hours for damage. Refer to paragraph 2-22. 5 FUEL BAY SUMPDRAINS: Drain off any water or sediment. 9 FUEL RESERVOIR TANK DRAIN: Open drain valves and drain off water and sediment. 11 BRAKE MASTER CYLINDERS: Check fluid level and fill as required with hydraulic fluid. > 500 HOURS 7 VACUUM SYSTEM CENTRAL AIR FILTER: Replace every 500 hours. Refer to paragraph 2-22. 2 HYDRAULIC FLUID RESERVOIR: At first 50 and first 100 hours, thereafter at each 500 hours or one year, whichever comes first, a sample of hydraulic fluid should be examined for sediment and discoloration as outlined in paragraph 2-29. AS REQUIRED 13 GROUND SERVICE RECEPTACLE Connect to 24-volt, D.C. negative-ground power unit for cold weather starting and lengthy ground maintenance of the aircraft's electrical equipment with the exception of electronic equipment. Master switch should be turned on before connecting a generator-type or battery-type external power source. Refer to Section 17. Figure 2-4. Servicing (Sheet 4 of 4) Revision 1 2-15 MODEL P210 SERIES SERVICE MANUAL FREQUENCY (HOURS) FREQUENCY(HOURS)~METHOD OF APPLICATION 0) 1i00 <> D00 HA HAND GREASE OIL SYRINGE .______ ~GUN CAN (FOR POWDERED WHERE NO INTERVAL IS SPECIFIED, GRAPHITE) LUBRICATE AS REQUIRED AND WHEN ASSEMBLED OR INSTALLED. NOTE The military specifications lited below 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 GM MIL-G-23827A . ........... AIRCRAFT AND INSTRUMENT GREASE GL MIL-G-21164C .... ...... HIGH AND LOW TEMPERATURE GREASE OG MIL-L-7870A . ............ GENERAL PURPOSE OIL Pt VV-P-236 . ....... ... . PETROLATUM GT ......... ........... NO. 10WT NON-DETERGENT OIL VV-L-800A .. ........ LIGHT OIL _ NEEDLE BEARINGS SHIMMY ^G DAMPENER ALSO REFER TO PIVOTS PARAGRAPH 2-44 o. NEEDLE BEARING cm(STEERING COLLAR) REFER TO PARA- GRAPH 2-46 ^ / \ N -REFER MAIN WHEEL PARAGRAPH 2-46 NOSE GEAR NOSE WHEEL BEARINGS BEARINGS igure 2-5. Lubrication (Sheet 1 of 4) 2-16 MODEL P210 SERIES SERVICE MANUAL MODEL P210 SERIES SERVICE MANUAL SPRAY BOTH SIDES OF SHADED AREAS WITH ELECTROFILM LUBRI-BOND "A" WHICH IS AVAILABLE IN AEROSOL SPRAY CANS, OR AN EQUIVALENT LUBRICANT. TORQUE ATTACHING BOLT TO 10-20 LB-IN. NOTES Sealed bearings require no lubrication. McCauley propellers are lubricated at overhaul and require no other lubrication. Do not lubricate roller chains or cables except under seacoast conditions. Wipe with a clean. dry cloth. Lubricate unsealed pulley bearings, Oilite bearings, pivot and hinge points, and any other friction point obviously needing lubrication, with general purpose oil every 1000 hours or oftener, if required. Paraffin wax rubbed on seat rails will ease sliding the seats fore and aft. Lubricate door latching mechanism with MIL-S-8660 silicone compound or equivalent lubricant. applied sparingly to friction points. every 1000 hours or oftener if binding occurs. No lubrication is recommended for the rotary clutch. Apply DOOR - EZE - lubricant to latch bolt. Figure 2-5. Lubrication (Sheet 4 of 4) 2-19 MODEL P210 SERIES SERVICE MANUAL 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. II 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 II above. b IF NOT FLOWN FOR HIRE An aircraft operating in this category must have a COMPLETE AIRCRAFT INSPECTION each 12 calendar months (ANNUAL). A COMPLETE AIRCRAFT INSPECTION consists of all 50, 100. 200 and Special Inspection Items shown in the inspection charts as defined in paragraph II above In addition, it is recommended that between annual inspections, all items be inspected at the intervals specified in the inspection charts. 2 -20 MODEL P210 SERIES SERVICE MANUAL 2 IF THE AIRCRAFT IS FLOWN MORE THAN 200 HOURS ANNUALLY. Whether fown for hire or not, it is recommended that aircraft operating in this category be placed on the CESSNA PROGRESSIVE CARE PROGRAM. However, if not placed on Progressive Care, the inspection requirements for aircraft in this category are the same as those defined under paragraph m 1. (a) and (b). Cessna Progressive Care may be utilized as a total concept program which insures that the inspection intervals in the inspection charts are not exceeded. Manuals and forms which are required for conducting Progressive Care in- spections are available from the Cessna Service Parts Center. IV INSPECTION GUIDE LINES. (a) MOVABLE PARTS for: lubrication, servicing, security of attachment, binding, excessive wear, safetying, proper operation, proper adjustment, correct travel, cracked fittings, security of hinges, defective bearings, cleanliness, corrosion, deformation, sealing and tension. (b) FLUID LINES AND HOSES for: leaks, cracks, dents, kinks, chafing, proper radius, security, corrosion, deterioration, obstruction and foreign matter. (c) METAL PARTS for: security of attachment, cracks, metal distortion, broken spotwelds, corrosion, condition of paint and any other apparent damage. (d) WIRING for: security, chafing, burning, defective insulation, loose or broken terminals, heat deterioration and corroded terminals. (e) BOLTS IN CRITICAL AREAS for: correct torque in accordance with torque values given in the chart in Section 1, when installed or when visual inspection indicates the need for a torque check. NOTE Torque values Listed in Section I 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. 3. Pilot's Operating Handbook To be made available upon request: 1. Aircraft Log Book and Engine Log Book. 2-21 MODEL P210 SERIES SERVICE MANUAL (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 Pilot's Operating Handbook. During the run-up observe the following, making note of any discrepancies or abnormalities: 1. Engine temperatures and pressures. 2. Static rpm. (Also refer to Section 12 of this Manual.) 3. Magneto drop. (Also refer to Section 12 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 on each tank (or cell) position and OFF position long enough to insure 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. IMPORTANT READ ALL INSPECTION REQUIRE- MENTS PARAGRAPHS PRIOR TO USING THESE CHARTS. SPECIAL INSPECTION ITEM EACH 200 HOURS EACH 100 HOURS PROPELLER BEACH 50 HOURS 1. S pinner . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2. Spinner bulkhead .. . . . . . . . . . .. . .... .. . . . . .... . . . 3. Blades ... ................................ . 4. Bolts and nuts . . . . . . . . . . . . . . . . . 5. H ub . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6. Governor and control ... . *... ............ 7. Anti-ice electrical wiring . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8. Anti-ice brushes, slip ring and boots . . . . . . . . . . . . . . . . . . . . . . . ENGINE COMPARTMENT Check for evidence of oil and fuel leaks, then clean entire engine and compartment, if needed, prior to inspection. 1. Engine oil screen filler cap, dipstick, drain plug and external filter element . . .. . . .. .. . . . . . . . . ..... . .... 2. O il coo le r . . . . . . . . . . . . . . . . . . . . . . . . . . .. 3. Induction air filter . .. . . . . . .. . . . . . . .. . 2 4. Induction airbox, air valves, doors and controls . .. . .. . . . . . . . .... 5. Cold and hot air hoses ....... ..................... 2-22 MODEL P210 SERIES SERVICE MANUAL SPECIAL INSPECTION ITEM EACH 200 HOURS EACH 100 HOURS EACH 50 HOURS 6. Engine baffles ................................................................. 7. Cylinders, rocker box covers and push rod housings ................................ · 8. Crankcase, oil sump, accessory section and front crankshaft seal ..................... 9. Engine hoses ................................................................. 3 10. Intake and exhaust systems ..................................................... · 4 11. Ignition harness ................................................................ 12. Spark plugs .............................................................. 13. Compression check ............................................................ 14. Crankcase and vacuum system breather lines ..................................... 15. Electrical wiring ............ ................................................ 16. Vacuum pum p ................................................................. 17. Deleted ...................................................................... 18. Engine controls and linkage ..................................................... 6 19. Engine shock mounts, mount structure and ground straps ........................... 20. Cabin heat valves, doors and controls ............................................. 21. Starter, solenoid and electrical connections ........................................ 22. Starter brushes, brush leads and commutator ............................... 23. Alternator and electrical connections ............................... .. ........... 21 24. Alternator brushes, brush leads, and commutator or slip ring ......................... 7 25. Voltage regulator mounting and electrical leads .................................... 0 26. Magnetos (external) and electrical connections ..................................... 27. Magneto timing ................................................................ 8 28. Fuel-air (metering) control unit ....................................... ........... 29. Firewall ...................................................................... * 30. Firewall pulley brackets .................... .................................... 27 31. Fuel injection system ........................................................... · 32. Engine cowl flaps and controls ................................................... · 33. Engine cowling ................................................................ 34. Turbocharger .................................................................. · 9 35. Turbocharger oil reservoir and oil lines to turbocharger, waste gate and controller ....... * 20 Revision 2 2-23 36. 37. 38. 39. 40. 41. 42. MODEL P210 SERIES SERVICE MANUAL SPECIAL INSPECTION ITEM EACH 200 HOURS EACH 100 HOURS EACH 50 HOURS W aste gate, actuator and controller ............................................... Turbocharger pressurized vent lines to fuel pump, discharge nozzles and fuel flow gage . Turbocharger mounting brackets and linkage ...................................... Alternator support bracket for security ............................................. Turbocharger oil line check valve ................................................. 42 Fuel manifold valve, valve cover, and fuel system .................................. * 43 Fuel injection nozzles .......................................................... 46 FUEL SYSTEM 1. Fuel strainer, drain valve and control, bay vents, caps and placards ................... 2. Fuel strainer screen and bowl.................................................... 3. Fuel injector screen ............................................................ 4. Fuel reservoirs ................................................................ 5. Drain fuel and check bay interior, attachment and outlet screens...................... 6. Fuel bays and sump drains ..................................................... 7. Fuel selector valve and placards ................................................. 8. Auxiliary fuel pump and throttle switches .......................................... 9. Engine-driven fuel pump ........................................................ 10. Fuel quantity indicators and sensing units ......................................... 11. Fuel lines, check valve and vapor return line ....................................... 12. Turbocharger vent system ...................................................... 13. Engine primer ................................................................. 14. Perform a fuel quantity indicating system operational test. Refer to Section 16 for detailed accomplishment instru