MODELS 210 & T210 SERIES (1985 THRU 1986) - AeroElectric

Cessna ATextron Company Service Manual 1985 Thru 1986 MODEL 210 & T210 SERIES Member of GAMA FAA APPROVAL HAS BEEN OBTAINED ON TECHNICAL DATA IN THIS PUBLICATION THAT AFFECTS AIRPLANE TYPE DESIGN. REVISION 2 TO THE BASIC MANUAL IS BEING SUPPLIED TO PROVIDE ADDITIONAL INFORMATION NECESSARY TO MAINTAIN THE AIRPLANE AND INCORPORATES TEMPORARY REVISIONS NUMBER 1, DATED 1 DECEMBER 1992, AND NUMBER 2, DATED 3 OCTOBER 1994. COPYRIGHT © 1985 CESSNA AIRCRAFT COMPANY 26 NOVEMBER 1985WICHITA, KANSAS, USA D2073-2-13 REVISION 2 3 JUNE 1996 (RGI-50-8/00) CessnaA Textron Company TEMPORARY REVISION NUMBER 6 DATE 5 April 2004 MANUAL TITLE 1985 thru 1986 Model 210 & T210 Series Service Manual MANUAL NUMBER - PAPER COPY MANUAL NUMBER - AEROFICHE TEMPORARY REVISION NUMBER D2073-2-13 D2073-2-13AF D2073-2TR6 MANUAL DATE 26 November 1985 REVISION NUMBER 2 DATE 3 June 1996 This Temporary Revision consists of the following pages, which affect and replace existing pages in the paper copy manual and supersede aerofiche information. AEROFICHE SECTION PAGE FICHE/FRAME 2 2 2 2 2 35 36 39 39A 39B 1/C17 1/C18 1/C21 Added Added REASON FOR TEMPORARY REVISION 1. To revise the cleaning interval of the engine fuel injection nozzles. FILING INSTRUCTIONS FOR THIS TEMPORARY REVISION 1. For Paper Publications, file this cover sheet behind the publication's title page to identify the inclusion of the Temporary Revision into the manual. Insert the new pages into the publication at the appropriate locations and remove and discard the superseded pages. 2. For Aerofiche Publications, draw a line with 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 This will be a visual identifier that the information on the frame (page) is no longer valid and the Temporary Revision should be referenced.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. © Cessna Aircraft Company AEROFICHE SECTION PAGE FICHE/FRAME A Textron Company TEMPORARY REVISION NUMBER 5 DATE 7 October 2002 MANUAL TITLE 1985 Thru 1986 Model 210 & T210 Service Manual MANUAL NUMBER - PAPER COPY D2073-2-13 MANUAL NUMBER - AEROFICHE D2073-2-13AF TEMPORARY REVISION NUMBER D2073-2TR5 MANUAL DATE 26 November 1985 REVISION NUMBER 2 DATE 3 June 1996 This Temporary Revision consists of the following pages, which affect and replace existing pages in the paper copy manual and supersede aerofiche information. AEROFICHE AEROFICHE SECTION PAGE FICHE/FRAME SECTION PAGE FICHE/FRAME 2 40 1/C22 2 40A Added 2 40B Added 2 41 1/C23 16 24C Added 16 24D Added REASON FOR TEMPORARY REVISION 1. To add a Component Time Limits section and a fuel quantity indicating system operational test. FILING INSTRUCTIONS FOR THIS TEMPORARY REVISION 1. For Paper Publications, file this cover sheet behind the publication's title page to identify the inclusion of the Temporary Revision into the manual. Insert the new pages into the publication at the appropriate locations and remove and discard the superseded pages. 2. For Aerofiche Publications, draw a line with 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 0 2002 CESSNA AIRCRAFT COMPANY WICHITA, KANSAS, USA TEMPORARY REVISION NUMBER 4 DATED 2 February 1998 MANUAL TITLE MODEL 210/T210 1985 THRU 1986 SERVICE MANUAL MANUAL NUMBER - PAPER COPY D2073-2-13 AEROFICHE D2073-2-13AF TEMPORARY REVISION NUMBER - PAPER COPY D2073-2TR4-13 AEROFICHE N/A MANUAL DATE 26 November, 1985 REVISION NUMBER 2 DATE 3 June, 1996 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 37 1 C-19 2 61 1 D-19 2 39 1 C-21 2 68 1 E-02 2 51 1 D-09 2 70 1 E-04 2 53 1 D-11 2 77 1 E-11 2 59 1 D-17 2 78 1 E-12 2 79 1 E-13 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 TEMPORARY REVISION NUMBER 3 DATED October 1, 1997 MANUAL TITLE Model 210, And T210 Series 1985 Thru 1986 Service Manual MANUAL NUMBER - PAPER COPY D2073-2-13 AEROFICHE D2073-2-13AF TEMPORARY REVISION NUMBER - PAPER COPY D2073-2TR3-13 AEROFICHE N/A MANUAL DATE 26 November 1985 REVISION NUMBER 2 DATE 3 June 1996 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 14 3 2F17 14 4 2F18 REASON FOR TEMPORARY REVISION 1. To add wet torque values for McCauley propeller hub bolts. 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 ° 1997 CESSNA AIRCRAFT COMPANY WICHITA, KANSAS, USA MODEL 210 & T210 SERIES SERVICE MANUAL LIST OF EFFECTIVE PAGES INSERT LATEST REVISED PAGES. DESTORY SUPERSEDED PAGES. NOTE The porton of the text affected by the revision is indicated by a vertical line in the outer margins of the page. Changes to illustrations are indicated by miniature pointing hands. The asteric indicates pages revised. added or deleted by the current revision. Original ..... 0 ......... 20 Nov 1985 Revision .... 1 .... 1 April 1992 Revision ..... 2 ...... . 3 June 1996 TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 670 Page Revision Page Revision No. No. No. No. *Title ... . . . ............... . 2 10-1 thru 10-8 ...................... 0 * A 2 11-1 thru 11-4 ...................... 0 * i thru iv .. ................... . 2 12-1 thru 12-2 ...................... 0 1-1 . . . . . . . . . . . . . . . . . . . .1 12-2A . . . . . . . . . . . . . . . . . . . . . . . . . . . .0 1-2 thru 1-15 .................... 0 12-2B Blank 0 1-16 thru 1-21 .1 12-3thru 12-13.......... 0 1-22 Blank ...................... . 1 12-14 Blank ........................ 0 2-1 thru 2-8 . 1 12-15 thru 12-35 .................... 0 2-9 .......................... 2 12-36 Blank ........................ 0 2-10 thru 2-16 . ............ . 0 12A-1 thru 12A-24 ......... 0 2-16A ................. 0 12A-25 2 2-16B Blank . ............. 0 12A-26 thru 12A-50 O:: ........... 0 *2-17 thru 2-28 .................. 0 13-1 thru 13-5 ...................... 0 2-29 thru 2-39 2 13-6.. ......... 1 *2-40 thru 2-46 .. 13-7 thru 13-10 . ....... 0 2-47 thru 2-79 .2 13-11 thru 13-12. ............. 2 2-80 Blank . .1 *13-13 thru 13-21 . ............. 0 3-1 .... 1 *13-22 ............................ 2 3-2 Blank ........... 0 13-23 ............................. 3-16A thru 3-28 ......... 0 .13-24 ... ......... 3-3 thru 3-22 . 0 *13-24A ............. 2 3-23 .. 1 13-24B Blank ...................... 2 3-24 thru 3-25 . 0 13-25 thru 13-26 .................... 0 3-26 Blank .................. 13-27 thru 13-28 2 3-27 thru 3-34 0 13-29 thru 13-31 ......... 0 4-1 thru 4-6 ....................... 13-32 Blank . ............ 0 5-1 thru 5-3 ................. 2 14-1 thru 14-9 0 .5-4 thru 5-6 .. . ............... 14-10 Blank ........................ 0 5-7 .. ........ 2 15-1 thru 15-32 ..................... 0 5-8 thru 5- 0 .............. 0 15-33 thru 15-34 .................... 2 5-11 thru 5-16 2 ... . 215-35........................... 0 _5- 17 Ihru 5-22 .. . ................. 0 *15-36 ............................ 2 .5-17 thru 5-22 ............ 5-36........................... 2 t5^23 thru 5-26 2215-36A ... 2 5-26A thru 5-26C .......... 2 15-36B Blank . 2 5-26D Blank ...... 2 15-37 thru 45 ....................... 0 .5-27 thru 5-28. 0 15-46 Blank . ................ 0 5-29 2 16-i thru 16-20 . ............... ... 0 ,5-30 . .... 0 16-21 ....... ............... 2 5-31 thru 5-32'2 .216-22 . .. 0 *5-31 thru 5-32 .. ......... .. ·. 2 *16-22 ............................ 0 *5-33 .. 5-3.... 0016-23 thru 16-24 ................... 2 5-34 thru 5-36 .. 2 *16-24A.. 2 *5-37 thru 5-51 . .......... 0 16-24B Blank. 2 5-52 .. . .. .. . . .16-25 thru 16-34 . ................... 0 .5-53 thru 5-54 1 .................. 17-1 thru 17-48.. 0 5-55S .................. 2 *17-49 thru 17-50 . . ................ 2 5-56 0 17-50A ........................... 2 5-57 thru 5-58 .......... . 2 17-50B Blank. 2 5-59 thru 5-60 ............ 0 17-51 thru 17-52. . ......... 2 6-1 thru 6-6 . ................. 0 17-53 thru 17-55 . . .................. 0 6-7 thru 6-8 ...... 2 17-56 Blank ......... .............. 0 6-9 0.. .. 0 18-1 thru 18-30 ..................... 0 6-10 Blank . ..... 0 18-31. .. . .... 2 7-1 thru 7-9 .. 0 18-32 ............................. 0 7-10 Blank 019-1 thru 19-3 . ..................... 0 -- 8-1-thru 8-7 . 0 19-4 Blank. 0 8-8 Blank ........ - -20-1thru 20-8 .-.. .. :....-........ -0 9-1 thru 9-13 ............... 020-9 thru 20-13 . . ...... 1 9-14 Blank 0 20-14thru 20-94 .................. 0 A Revision 2 MODEL 210 & T210 SERIES SERVICE MANUAL SECTION Page No. Aerofiche/Manual 1. GENERAL DESCRIPTION ................... ..................... 1A8/1-1 2. GROUND HANDLING, SERVICING, CLEANING, LUBRICATION, AND INSPECTION ............................................ 1B5/2-1 3. FUSELAGE .................................................................. 1E23/3-1 4. WINGS AND EMPENNAGE ................................................... 1G13/4-1 5. LANDING GEAR, BRAKES AND HYDRAULIC SYSTEM ............................ 1G21/5-1 6. AILERON CONTROL SYSTEM .............................................. 1J12/6-1 7. WING FLAP CONTROL SYSTEM ..................................... .......... J21/7-1 8. ELEVATOR CONTROL SYSTEM ................................................ 1K9/8-1 9. ELEVATOR TRIM CONTROL SYSTEM .......................................... 1K19/9-1 10. RUDDER CONTROL SYSTEM ......................................... ......... 1L11/10-1 11. RUDDER TRIM CONTROL SYSTEM ................................. ........... 2A3/11-1 12. ENGINE NORMALLY ASPIRATED .............................................. 2A9/12-1 12A. ENGINE TURBOCHARGED .................................................... 2C1/12A-1 13. FUEL SYSTEM ...................................... ............ ......... 2E5/13-1 14. PROPELLERS AND PROPELLER GOVERNORS ................................. 2F15/14-1 15. UTILITY SYSTEMS ........................................................... 2G3/15-1 16. INSTRUMENTS AND INSTRUMENT SYSTEMS ................................... 213/16-1 17. ELECTRICAL SYSTEMS . ....................................... 2J15/17-1 18. STRUCTURAL REPAIR ........................................................ 3A3/18-1 19. EXTERIOR PAINTING ........................................................ 3B15/19-1 20. W IRING DIAGRAMS ................... ...................................... 3B23/20-1 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 210 & T210 SERIES SERVICE MANUAL CROSS REFERENCE LISTING OF POPULAR NAME VS. MODEL NUMBERS AND SERIALS Allaircraft, regardless of manufacturer,are certified under model number de- signations. However, popular names are often used for marketing purposes. To provide a consistent method of referring to the aircraft, the model number will be used in this publication unless the popular name is necessary to dif- ferentiate between versions of the same basic model. The following table pro- vides a listing of popular name, modelnumber and serial number. MODEL SERIAL POPULAR NAME YEAR MODEL BEGINNING ENDING CENTURION 1985 210R 21064898 21064949 TURBO CENTURION 1985 T210R 21064898 2106949 CENTURION WITH 1985 210R 21094898 21064949 VALUE GROUP A (& B) TURBO CENTURION WITH 1985 T21OR 21064898 21064949 VALUE GROUP A (& B) CENTURION 1986 210R 2106495021065009 TURBO CENTURION 1986 T210R 2106 4950 21065009 CENTURION WITH 1986 210R 21064950 21065009 VALUE GROUP A (& B) TURBO CENTURION WITH 1986 T210R 21064950 21065009 VALUE GROUP A (& B) ii Revision 2 MODEL 210 & T210 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, 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. 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'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. It supersedes and replaces previous issue(s) of the manual. CHANGES / REVISIONS and REISSUES. 1. Can be purchased from your Cessna Service Station or directly from Cessna Parts Distribution (CPD 2), Dept. 701, Cessna Airplane Company, P.O. Box 949, Wichita, Kansas 67201 (walk-in address: 5800 East Pawnee, Wichita, Kansas 67218). 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 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 2 MODEL 210 & T210 SERIES SERVICE MANUAL 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 complete retype of copy, revision bars will appear 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 Parts Distribution (CPD 2), Dept. 701, Cessna Airplane Company, P.O. Box 949, Wichita, Kansas 67201 (walk-in address: 5800 East Pawnee, Wichita, Kansas 67218. 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 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 Airplane 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. iv Revision 2 MODEL 210 & T210 SERIES SERVICE MANUAL SECTION 1 GENERAL DESCRIPTION Page No. TABLE OF CONTENTS Aerofiche/Manual GENERAL DESCRIPTION . ........ 1A8/1-1 SAFETY WIRE PROCEDURES ..... 1A15/1-8 Model 210 Series ............ 1A8/1-1 USE OF COTTER PINS ............. 1A19/1-12 Description . ... 1A8/1-1 USE OF LOCKING CLIPS .......... 1A21/1-14 Aircraft Specifications.. 1A8/1-1 USE OF LOCKWASHERS .......... 1A22/1-14 Stations lA8/1-1 USE OF SELF-LOCKING NUTS ..... 1A21/1-14 GENERAL AIRFRAME PRACTICES 1A11/1-4 CONTROL CABLE WIRE BREAKAGE TORQUEING PROCEDURES ....... 1A11/1-4 AND CORROSION Calculating Torque . 1A/1-4 LIMITATIONS .............. 1A23/1-16 Torque Values - Bolts ...... . 1A11/1-4 ADHESIVES, CEMENTS AND Torque Values - Fittings ......... 1A14/1-7 SEALANTS-SHELF LIFE SAFETYING PROCEDURES ....... 1A15/1-8 AND STORAGE .............. 1B1/1-18 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 Centurion, sions are used for constructing a hangar or computing Centurion - With Value Group A (&B), Turbo clearances, remember that such factors as nose gear Centurion, and Turbo Centurion - With Value Group A strut inflation, tire pressure, tire sizes and load (&B) (Model 210 Series) airplanes, described in this distribution may result in some dimensions that are manual, are single-engine, high-wing monoplanes of all considerably different from those listed. metal, semimonocoque construction.. Wings are full cantilever, with sealed sections forming fuel bays. The 1-5. STATIONS. A station diagram is shown in fig- fully-retractable tricycle landing gear consists of tublar ure 1-2 to assist in locating equipment when a written spring-steel main gear struts and a steerable nose gear description is inadequate or impractical. with an air-hydraulic fluid shock strut. The six place seating arrangement is of conventional, forward facing type. Powering the Model 210 Series is a Continental, horizontally-opposed, air-cooled, six-cylinder, fuel- injected engine driving an all-metal, constant-speed propeller. A more desirable higher performance airplane, is offered in the turbocharged version of the Model 210 Series. Revision 1 1-1 MODEL 210 & T210 SERIES SERVICE MANUAL MAXIMUM WEIGHT - 210 Ramp ......................... 3812 lbs Takeoff or Landing .. . .. .. . . . .. . . . . . . . 3800 lbs STANDARD EMPTY WEIGHT - 210 Centurion . . . . . . . . . . . . . . . . . . . . . . . 2220 lbs Centurion - With Value Group A (& B) ............ 2269 lbs MAXIMUM USEFUL LOAD - 210 Centurion . . . . . . . . . . . . . . . . . . . . 1592 lbs Centurion - With Value Group A (& B) ............ . 1543 lbs MAXIMUM WEIGHT - T210 Ramp . . . . . . . . . . . . . . . . . . . . . 4118 1bs Takeoff .......... .............. 4100 lbs Landling. ........................ 3900 lbs STANDARD EMPTY WEIGHT - T210 Turbo Centurion .. ................. . 2320 lbs Turbo Centurion - With Value Group A (& B) .......... 2369 bs MAXIMUM USEFUL LOAD - T210 Turbo Centurion . . . . . . . . . . . . . . . . . . . . 1798 lbs Turbo Centurion - With Value Group A (& B) ....... . .1749 lbs FUEL CAPACITY Total . . . . . . . . . . . . . . . . . . . . . . . . .90 gal. Usable . . . . . . . . . . ... . . . . . . . . . . . 87 gal. OIL CAPACITY 10 qt. With External Oil Filter and All Turbocharged Engines ...... 11 qt. ENGINE MODEL 210 (Refer to Section 12 for Engine Data) .. . . .. .. .CONTINENTAL 10-520 T210 (Refer to Section 12A for Engine Data) .. . .... .. CONTINENTAL TSIO-520-CE PROPELLER (Constant-Speed) (Three Blades) ... . . . . . . . . . . . . . .. .. .80" McCauley LANDING GEAR (Retractable. Hydraulically-Actuated ........ Tricycle MAIN WHEEL TIRES ............. .... .. .. 00 x 6 Pressure ........................ 55 psi NOSE W1EEL TIRE 210 .................. ....... 5.00 x 5. 6 Ply Pressure. . ................... . 50 psi T210 . .. . . . . . . . . . . . . . . . . . . . . . . 5.00 x 5, 10 Ply Pressure . . . . . . . . . . . . . . . . . . . . . . 88 psi NOSE GEAR STRUT PRESSURE (Strut Extended) .......... 90 psi WHEEL ALIGNMENT. Camber . . . . . . . . . . . . . . . . . . . . . . . . 4° ± 1° 30' Toe-In. . ..................... ." to .06" AILERON TRAVEL .......... Up . . . . . . . . . . . . . . . . . . . . . . . . 20° ± 2° Down . . . . . . . . . . . . . . . . . . . . . . . . . 15 ° ± 2 ° WING FLAP TRAVEL (Electrically-Actuated) . .. . .. . 0° ± 0° to 30 ° , + 1° -2° RUDDER TRAVEL (Measured parallel to water line) .... Right . . . . . . . . . . . . . . . . . . . . . . . . . 24 ° ± 1° Left . . . . . . . . . . . . . . . . . . . . . . . . .24 ° ± 1° RUDDER TRAVEL (Measured perpendicular to hinge line) .. Right . . . . . . . . . . . . . . . . . . . . . . . . . 27 ° 13' ± 1° Left . . . . . . . . . . . . . . . . . . . . . . . . . 27 ° 13' ± 1 ° ELEVATOR TRAVEL Up . . . . . . . . . . . . . . . . . . . . . . . . .25° ± 1° Down . ... . . . . . . . . . . . . . . . . . . . ..20 ° - 1° ELEVATOR TRIM TAB TRAVEL Up . . . . . . . . . . . . . . . . . . . . . . . .20° ± 1° Down . . . . . . . . . . . . . . . . . . . . . . . . . 15 ° ± 1° PRINCIPAL DIMENSIONS Wing Span . . . ... . . . . . . . . . . . . . . . . . 441.75" Tail Span . . . . . . . . . . . . . . . . . . . . . . . 156.32" Length ... . . . . . . . . . . . . . . . .337.96" Fin Height (Maxium with Nose Gears Depressed-and - - Flashing Beacon installed on Fin) .. . . . .. .... .112.92" Track Width . . .. .. . ...... . . . . . . . .104.20" BATTERY LOCATION ................ .. . Left Side of Firewall Figure 1-1. Aircraft Specifications 1-2 MODEL 210 AND T210 SERIES SERVICE MANUAL 1-6. GENERAL. This chapter deals with general tor- (d) Since running torque will become less due que and safetying practices used to ensure security of to nutbolt re-use (in accepted applications), this pro- installation and prevent overstressing of components. cedure must be repeated each time. Special torque values, when required, are specified (e) When necessary to tighten from bolt head, with the specific component maintenance and installa- increase torque value by an amount equal to shank tion instructions. torque (torque required to turn bolt when installed). Measure with a torque wrench. 1-7. TORQUEING PROCEDURES. The importance of correct application cannot be overemphasized. Under- Average running torque for torque can result in unnecessary wear-of nuts andAverage running shank torque for bolts as well as parts they are holding together. When Average bolt bolt 10 int-lbs. insufficient pressures are applied, uneven loads will torque required = 1 in.-lbs. be transmitted throughout assembly, which may Final torque wrench reading = 120 5 in.-lbs result in excessive wear or premature failure due to fatigue. Overtorque can be equally damaging because b. Torque Values - Bolts and Nuts. (See Table 1-1.) of failure of a bolt or nut from overstressing threaded 1. Tables included in this section do not apply to areas. the following exceptions: a. Calculating Torque. There are a few simple, but (a) Sheet metal screws should be tightened very important, procedures that should be followed to firmly, but with no specific torque value. assure that correct torque is applied: (b) Screws attached to nutplates should be 1. Calibrate torque wrench periodically to assure tightened firmly, but with no specific torque value. accuracy; and recheck frequently. (c) 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 eliminate washer and dry unless otherwise specified. crown. 4. Determine friction drag torque and add to (e) Fasteners that have 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. Dry torque required = 125 5 in.-lbs. These values are shown separately in torque Final torque wrench reading = 140 5 in.-lbs. value tables. 1-4 MODEL 210 AND T210 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 T x L _ y Y = Indicated Torque L = Effective Length Lever E = Effective Length of Extension SETSCREW WRENCH HANDGRIP ADAPTER DRIVE CENTERLINE CENTERLINE (PREDETERMINED) ADAPTER TORQUE DRIVE WRENCH CENTERLINE HOSE CLAMP ADAPTER EXAMPLE T = 135 In.-Lbs y = 135 x 10= 1350 117.39 Y = Unknown Y= Unknown 10 + 1.5 11.5 L = 10.0 In.-Lbs E = 1.5 In. Y = 117 In.-Lbs OPEN-END WRENCH ADAPTER ADAPTER HANDGRIP DRIVE CENTERLINE CENTERLINE (PREDETERMINED) WRENCH TORQUE DRIVE WRENCH CENTERLINE FLARE NUT WRENCH ADAPTER EXAMPLE SPANNER WRENCH ADAPTER T = 135 In.-Lbs y 135 x 10 _ 1350 158.82 Y = Unknown L = 10.0 In.-Lbs 10 -1.5 8.5 E = -1.5 In. Y = 159 In.-Lbs Figure 1-3. Torque Wrench Adapter Adjustment 1-5 MODEL 210 AND T210 SERIES SERVICE MANUAL BOLT TORQUE VALUES Tension Shear Tension Shear BOLTS BOLTS AN3 thru AN20 MS20004 thru MS20024 NAS464 AN42 thru AN49 NOTE: Bolts in tension NAS144 thru NAS148 AN73thru AN81 column may be used NAS172 AN173 thru AN186 with shear nuts. Bolts NAS174 AN509NK9 in shear column NAS333 thru NAS340 AN525NK525 should not be used un- NAS585 thru NAS590 MS20033 thru MS20046 less a minimum of two NAS624 thru NAS644 MS20073 threads extend beyondNAS1303 thru NAS1320 MS20074 nut after installation. NAS517 MS24694 MS27039 NUTS NUTS AN310 AN320 AN310 AN320 AN315 AN364 AN315 AN364 AN363 MS20364 NA363 NAS1022 AN365 NAS1022 AN365 MS20364 MS20365 MS20365 MS20500 MS21045 MS21045 NAS679 NAS679 NAS1021 NAS1021 NAS1291 FINE THREAD SERIES FINE THREAD SERIES Nut-bolt Nut-bolt Nut-bolt Torque Limits Torque Limits Nut-bolt Torque Limits Torque Limits size in.-lbs in.-lbs. in.-lbs. in.-lbs. MIN. MAX. MIN. MAX. MIN. I MAX. MIN. MAX. 8-36 12 15 7 9 10-32 25 30 15 20 10-32 20 25 12 15 1/4-28 80 100 50 60 1.4-28 50 70 30 40 5/16-24 120 145 70 90 5 16-24 100 140 60 85 3/8-24 200 250 120 150 3.8-24 160 190 95 110 716-20 520 630 300 400 7 16-20 450 500 270 300 1 2-20 770 950 450 550 12-20 480 690 290 410 9/16-18 1100 1300 650 800 9/16-18 800 1000 480 600 5.8-18 1250 1550 750 950 5/8-18 1100 1300 660 780 3/4-16 2650 3200 1600 1900 34-16 2300 2500 1300 1500 7/8-14 3550 4350 2100 2600 7-8-14 2500 3000 1500 1800 1-14 4500 5500 2700 3300 1-14 3700 4500 2200 3300 1-1/8-12 6000 7300 3600 4400 1-1.8-12 5000 7000 3000 4200 1-1/4-12 11000 13400 6600 8000 1-14-12 9000 11000 5400 6600 Nut-bolt COURSE THREAD SERIES MS17825 MS17826 Nut-bolt Torque Limits Torque Limits Torque Limits Torque Limits in.-lbs. in.-lbs. size in.-lbs. in.-lbs. MIN. I MAX. MIN. I MAX. MIN. I MAX. MIN. I MAX. 8-32 12 15 7 9 10-32 28 35 16 20 10-24 20 25 12 15 14-28 65 80 35 45 14-20 40 50 25 30 5/16-24 180 225 70 90 5/16-18 80 90 48 55 3/8-24 260 325 100 125 38-16 160 185 95 110 7/16-20 460 575 180 225 7/16-14 235 255 140 155 1/2-20 720 900 240 300 1/2-13 400 480 240 290 9/16-18 880 1100 320 400 9/16-12 500 700 300 420 5/8-18 1300 1600 480 600 58-11 700 900 420 540 3/4-16 2200 2800 880 1100 3/4-10 1150 1600 700 950 7/8-14 3700 4600 1500 1900 7/8-9 2200 3000 1300 1800 1-14 5400 6800 2400 3000 1-8 3700 5000 2200 3000 1-1 8-12 8000 10000 4000 5000 1-1/8-8 -5500 - 6500 -- 3300- 4000 -- 1-1-4-12 11000 14000-- 5600 - 7000- - -- 1-1 4-8 6500 8000 4000 5000 Table 1-1. Torque Values - Bolts and Nuts 1-6 MODEL 210 AND T210 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 1-1/2 turns. torque values and procedures. installationsforspec(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 1. Connectors installed in bosses with no re- 1-2 1-2. quired orientation should be installed using torque 3. Bulkhead fittings are installed with jam-nuts values given in Table 1-2. 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 ASSEMBLIES DIAMETER w/o JAM-NUT Nipple or Nut (Inches) Torque-Limits Torque-Limits HOSE ALUMINUM STEEL (in.-Ibs.) (in.-Ibs.) INSIDE _________ ___ DIAMETER orque-Limits Torque-Limits MIN. I MAX. MIN. I MAX. DIAMETER in.-bs. in.-lbs 1/8 5/16-24 35 50 50 55 MIN. MAX. MIN. MAX. 3/16 3/8-24 65 80 65 758 20 30 75 85 1/4 7/16-20 85 105 95 1053/16 25 35 95 105 5/16 1/2-20 105 125 125 135 1/4 50 65 135 150 3/8 9/16-18 120 150 155 165 5/16 70 90 170 200 1/2 3/4-16 240 280 280 3053/8 110 130 270 300 5/8 7/7-14 320 380 380 405 1 230 260 450 500 3/4 1/16-12 500 600 550 600 330 360 650 700 1 1-5/16-12 720 880 800 9003/4 460 500 900 00 1-1/4 1-5/8-12 960 1200 900 1000 500 700 1200 100 1-1/2 1-7/8-12 1200 1440 900 1000 100 00 120 1680 2 2-1/2-12 1400 1500 900 1000 1-1/ 800 900 1900 2100 1-1/2 800 900 1900 2100 ,---- - ---- ----- . -1-3/4 - - - - 2 1800 2000 2660 2940 Table 1-2. Torque Values Jam-Nuts and Threaded Connector 2. Connectors installed in bosses requiring a Table 1-3. Torque Values specific 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 packing. used with rigid lines are given in Table 1-4. 1-7 MODEL 210 AND T210 SERIES SERVICE MANUAL THREADED STRAIGHT FITTING TORQUE VALUE (RIGID TUBE) FLARED END STRAIGHT END TUBE ALUMINUM ALUMINUM STEEL 6061-0 ALUMINUM STEEL 6061-T(X) ALUMINUM OUTSIDE On Oxygen Lines 5052-0 ALUMINUM w/ steel sleeve DIAMETER Torque-Limits Torque-Limits Torque-Limits Torque-Limits Torque-Limits Torque-Limits in-lbs. in-lbs. in-lbs. in-lbs. in-lbs. in-lbs. MIN. MAX. MIN. MAX. MIN. MAX. MIN. MAX. MIN. MAX.TUBEWALL MIN. MAX. 1 8 20 30 45 55 3 16 90 100 30 40 90 100 0.028 45 55 14 40 65 135 150 40 65 135 150 0.022 80 105 0.028 80 105 0.035 80 105 0.049 90 115 516 60 80 100 125 180 200 60 80 180 200 0.028 80 105 0.035 80 105 0.042 125 175 38 75 125 270 300 75 125 270 300 0.028 125 175 0.035 125 175 0.049 125 175 1/2 150 250 450 500 150 250 450 500 0.028 135 180 0.035 200 300 0.049 400 500 0.058 400 500 0.065 400 500 5/8 200 350 700 800 200 350 700 800 All 500 600 3/4 300 500 1100 1150 300 500 1100 1150 All 600 700 1 500 700 1200 1400 500 700 1200 1400 All 1000 1300 1-1/ 4 600 900 1300 1450 600 900 1300 1450 All 1300 1500 1-1 2 600 900 1350 1500 600 900 1350 1500 All 1400 1700 2 600 900 1500 1700 Table 1-4. Torque Values - Straight Threaded Fittings (Line) 1-8. SAFETYING PROCEDURES. The use of safety 2. Copper that is cadium-plated and dyed yellow wire, cotter pins, lockwashers, and self-locking nuts is used for shear and seal wiring applications. is to prevent relative movement of critical components (a) Shear applications are those where it is subject to vibration, torque, tension, etc., which could necessary to break or shear wire to permit operation cause attaching parts to be broken, loosened, and/or or actuation of emergency devices. detached. (b) Seal applications are where wire is used with a lead seal to prevent tampering or use of a 1-9. SAFETY WIRE PROCEDURES. device without indication. a. Identification. Lockwire comes in three types 3. Aluminum Alloy (Alclad 5056) is dyed blue which are identified by size and color. The three types and is used exclusively for safety-wiring magnesium are classified by use. parts. 1. Inconel and Monelwire-is used for-general 4. Size of-wire is-dependent on materialand lockwiring and is identified by a natural wire color. purpose of installation. (a) Inconel can withstand temperatures up to (a) 0.020-inch diameter copper wire should be 1500°F. used for shear and seal application. (b) Monel can withstand temperatures up to (b) 0.020-inch diameter wire may be used to 800°F. lockwire parts with tie holes smaller than 0.045 in- 1-8 MODEL 210 AND T210 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 lockwire 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 inches or less between cen- (c) Drain plugs and cocks may be safetied to a ters 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 closely spaced geometric patterns essary 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 lockwired. should use double-twist method of lockwiring. (e) When locking is required on electrical connectors which use threaded coupling rings, or 3. Lockwiring by the double-twist method is on plugs which employ screws 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 lockwire 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 lockwired if installed into self-locking nuts or in- This does not necessarily apply to castellated stalled with lockwashers. Castellated nuts with nuts when slot is close to top of nut. The wire cotter pins or lockwire are preferred on bolts or will be more secure if it is made to pass along studs with drilled shanks, but self-locking nuts are side of stud. permissible within limitations described in Para- graph 1-13. (b) While taut, twist 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 shall lockwire be dependent upon frac- overstressing and prevents wire from becoming 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 mechanisms such twist method is accomplished in a similar manner as emergency exits, fire extingushers, emergency except twists between 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 lockwire 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. cumstances shall not prevent emergency operations of these devices. 1-9 MODEL 210 AND T210 SERIES SERVICE MANUAL EXTERNAL SNAP RING SINGLE-WIRE METHOD NOTE BOLTS IN CLOSELY SPACED, CLOSED RIGHT-HAND THREADED PARTS GEOMETRICAL PATTERN. SINGLE- WIRE METHOD. SHOWN. REVERSE DIRECTION FOR LEFT-HAND THREADS. SINGLE FASTENER APPLICATION CASTELLATED NUTS ON DRILLED STUDS DOUBLE-TWIST METHOD DOUBLE-TWIST METHOD Figure 1-4. Lockwire Safetying (Sheet 1 of 2) 1-10 MODEL 210 AND T210 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 ELECTRICAL CONNECTION DOUBLE-TWIST METHOD Figure 1-4. Lockwire Safetying (Sheet 2 of 2) 1-11 MODEL 210 AND T210 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 axis 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). COTTER PIN - MINIMUM SIZE THREAD SIZE MINIMUM PIN SIZE COTTER PINS (MS24665) 0.028 MATERIAL TEMP USE 8 0.044 Carbon Steel Up to 450°F Pins that contact cadmium- 10 0.044 plated surfaces. 1/4 0.044 5/16 0.044 General Applications 3/8 0.072 7/16 0.072 Normal Atmospheres 1/2 0.072 9/16 0.086 Corrosion- Up to 800°F Pins that contact cor- 5/8 0.086 Resistant rosion-resistant steel. 3/4 0.086 7/8 0.086 Corrosive atmospheres 1 0.086 1-1/8 0.116 1-1/4 0.116 Table 1-5. Cotter Pin 1-3/8 0.116 Temperature and Use 1-1/2 0.116 2. Cotter pins shall be new upon each applica- tion. 3. When nuts are to be secured to fastener with Table 1-6. Cotter Pin cotter pins, tighten nut to low side (minimum) of Minimum Size applicable specified or selected torque range, unless otherwise specified, and if necessary, continue tight- (7) In pin applications, install cotter pin with ening until slot aligns with hole. In no case shall you axis of eye parallel to shank of clevis pin or rod end. exceed high side (maximum) torque range. Bend prongs around shank of pin or rod end (see 4. If more than 50 percent of cotter pin diameter Figure 1-5). is above nut castellation, a washer should be used CAUTION under nut or a shorter fastener should be used. A maximum of two washers may be permitted under a Cadium-plated cotter pins should not be used in nut. applications bringing them in contact with fuel, 5. The largest diameter cotter pin which hole hydraulic fluid, or synthetic lubricants. and slots will accommodate should be used, but in no application to a nut, bolt, or screw shall pin size be less than sizes described in Table 1-6. 1-12 MODEL 210 AND T210 SERIES SERVICE MANUAL TO PROVIDE CLEARANCE PRONG MAY BE CUT HERE I u PREFERRED METHOD ALTERNATE METHOD CASTELLATED NUT ON BOLT TANGENT TO PIN MAXIMUM MINIMUM COTTER PIN COTTER PIN LENGTH LENGTH PIN APPLICATION Figure 1-5. Installation of Cotter Pins Revision 1 1-13 MODEL 210 AND T210 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 safetyfing, both threaded terminals 6. When corrosion encouraged by gouging shall be screwed an equal distance 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 locking 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) Press 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 shearing 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 otherwise distort opera- tion. 1-12. USE OF LOCKWASHERS. (e) Do not use to attach access panels and a. Lockwashers 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 (f) In general, do not use self-locking nuts in externally or internally threaded part. where loss of bolt affects safety of flight. 2. When a cotter pin cannot be used to prevent 2. Bolts, studs, or screws, excluding Hi-Locks, 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 attached in a positive manner to elimi- primary structure. nate possibility of their rotation or misalignment when tightening is to be accomplished by rotating bolts to structure, and permit replacement of nuts. 1-14 MODEL 210 AND T210 SERIES SERVICE MANUAL LOCKING CLIP BARREL BARREL LOCKING CLIP LOCKING CLIP CABLE TERMINAL Detail A Figure 1-6. Safetying Turnbuckle Assemblies Revision 1 1-15 MODEL 210 & T210 SERIES SERVICE MANUAL 1-14. CONTROL CABLE WIRE BREAKAGE AND While rotating cable, inspect bent area for broken CORROSION LIMITATIONS. wires. a. Inspection of Control Cables. (b) Wire breakage criteria for cables in flap, 1. Control cable assemblies are subject to a aileron, rudder, and elevator systems are as follows: variety of environmental conditions and forms of (1) Individual broken wires are acceptable deterioration that ultimately may be easy to recognize in primary and secondary control cables such as wire/strand breakage, or the not so readily at random locations when there are no visible types ofdeterioration including corrosion and/or more than six broken wires in any given distortion. Thefollowing information will aid in ten-inch cable length. detecting these cable conditions. 3. Corrosion. 2. Broken Wire. (a) Carefully examine any cable for (a) Examine cables for broken wires by corrosion that has a broken wire in a section not in passing a cloth along length of cable. This will detect contact with wear-producing airframe components such broken wires, if cloth snags on cable. Critical areas for as pulleys, fairleads, rub blocks, etc. It may be wire breakage are those sections of cable which pass necessary to remove and bend cable to properly inspect through fairleads, across rob blocks, and around it for internal strand corrosion as this condition is pulleys.If no snags are found, then no further inspection usually not evident on outer surface of cable. Replace is required. If snags are found or broken wires are cable if internal corrosion is found. If a cable has been suspected, then a more detailed inspection is necessary wiped clean of its corrosion-preventive lubricant and which requires that the cables be bent in a loop to metal-brightened, the cable shall be examined closely confirm broken wires (refer to figure 1-7). Loosen or for corrosion. For description of control cable corrosion, remove cable to allow it to be bent in a loop as shown. refer to Chapter 51, Corrosion and Corrosion Control. 1-16 Revision 1 MODEL 210 & T210 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 210 & T210 SERIES SERVICE MANUAL (g) Class IX - These are polyurethane 1-15. ADHESIVES, CEMENTS AND SEALANTS - products. Store in original container, between 70 and SHELF LIFE AND STORAGE. 100°F. Urethanes are moisture sensitive and a. General. precautions should be taken to ensure complete 1. This section provides information which protection from moisture contamination. Container defines the proper storage and usable life (shelf life) of must be tightly closed at all times. adhesives, cements and sealents which are used for (h) Class X - These are acrylic base maintenance and/or repair of the airplane. Also materials. They require storage at 40°F or per included in this section is the criteria used for testing instructions on product container. these materials after the normal shelf life has expired, c. Storage of Sealants. to determine if an extension to the shelf life is possible. 1. All sealants shall be stored under controlled 2. Shelf life refers to a specified period of time temperature conditions. If open shop storage becomes usually from the date of manufacture (normally necessary, these products shall in no case be stored in stamped or printed on the product container) to the an area which will subject them to temperatures in expiration date (which should be determined using excess of 95°F or below 40°F. Containers shall be tightly limits specified in Table 1-7 or if applicable, the closed prior to placing them in the proper storage manufacturer's expiration date printed or stamped on environment. For proper storage environment, refer to the product container). The specified shelf life is Table 1-7 and the following paragraphs. dependent on proper storage in accordance with the (a) Premixed and frozen sealants shall be limits specified in this section and/or the stored at -40°F or colder and shall not be used more than manufacturer's instructions. six weeks after the date of mixing even if all storage is b. Storage Criteria. at -40°F or colder. If storage temperatures rise above .Storage of Adhesives and Cements. 40°F, but not warmer than -30°F, the material may be All adhesives and cements shall be stored under stored for a maximum of two weeks warmer than -40°F controlled temperature conditions.. If open shop plus time at -40°F or colder for a combined total not to storage becomes necessary, these products shall in no exceed five weeks beyond the date of mixing. If storage case be stored in an area which will subject them to temperatures rise above -40°F but are not warmer than temperatures in excess of 95°F. Containers shall be -20°F, the materials may be stored for a maximum of tightly closed prior to being placing them into the one week above -30°F plus time at -40°F or colder for a proper storage environment. For proper storage combined total not to exceed four weeks beyond the date environment, refer to Table 1-7 and the following of mixing. paragraphs. (b) Unmixed sealants shall be stored at a (a) Class I - These adhesives are epoxy base controlled temperature of between 40 and 80°F and materials and have one year storage at room have a shelf life of approximately six months when temperature. 0°F storage will extend the storage life. stored within this temperature range. Unmixed Refer to the product container instructions for storage sealants stored at temperatures exceeding 80°F shall be temperature and life. used within five weeks. (b) Class II, III and IV - These adhesives are 2. All materials should be used on a "first in-first rubber and resin base and are good for six months at out" basis. The adhesives, cements and sealants should room temperature storage. 40° F storage will extend the be rotated so this requirement can be accomplished. All storage life. Refer to the product container instructions material containers should be clearly marked with a for limits of each adhesive. "use by" date, consisting of the year and month. All (c)Class V - These are silicone rubber materials not used by this date must be tested prior to adhesives. If stored in their original containers at a use. Refer to Testing criteria and Table 1-7. temperature below 80°F, have a shelf life of one year or d. Testing Criteria. as indicated on the storage container. 1. Any material (adhesive, cement or sealant) (d) Class VI -These are solvent bonding not used within its shelf life will be tested and the solvents. They should be stored in their original results reviewed to determine if the material is usable. containers and tightly closed, and stored at 40°F If there is doubt about the material being usable, it temperature. must be properly disposed of. Material that has (e)ClassVII - Cyanoacrylate base materials exceeded its original shelf life may be retested to must be stored in the original containers at 40°F or as determine if the material meets its requirements. specified on the container instructions. Materials meeting their requirements will have their (f) Class VIII - These are pressure sensitive shelf life extended as specified in Table 1-7. Materials materials. The shelf life is two years when stored at with shelf life extensions must be retested after a 75°F and 50 percent relative humidity. specified period of time. Refer to Table 1-7. 1-18 Revision 1 MODEL 210 & T210 SERIES SERVICE MANUAL 2. Testing of Overaged Adhesives and 2. Overaged sealants to be tested for possible Cements. shelf life extension shall be properly mixed using the correct materials, procedures and equipment. NOTE 3. Overaged premixed frozen sealants, along with unmixed sealants should be visually inspected. Overaged adhesives and cements are those Sealants whic show conclusive evidence of separation, that have exceeded their original shelf life discoloration and/or gelling prior to the addition of a and must be tested prior to use and/or given thinner or curing agent shall be discarded. When in extended shelf life. doubt of the sealant quality, the overaged sealant should be compared with the same type of sealant, (a) Class I Epoxy Adhesive - Examine both under six months old, which is known to be satisfactory. components to ensure that they are still workable. 4. The mixed sealants may be tested by placing a Check for gelling and/or contamination. Stir small amount of sealant (smaple buttons) on a sheet of components and mix a small amount of adhesive. Verify paper. After the sample buttons have cured, they should that adhesive sets up and hardens. be cut in half and examined. The sealant should show (b) Class 11, III and IV Rubber and Resin no signs of spots or streaks of unmixed base compound Base Adhesives - Open containers and check for gelling or curing agent. However, sample buttons containing and/or contamination. Check for spreading and drying. spots, streaks, discoloration and/or variations in (c)Class V Silicone Rubber Adhesives - uniformity of color are acceptable if these spots, streaks Examine adhesive for hardness. If adhesive is still soft etc., are tack free upon inspection. All mixed sealant and can be spread, it is acceptable. Verify that adhesive should be as void free as possible. will harden. 5. Contaminated sealant, premized sealant that (d) Class VI Solvent Bonding Solvents - have been thawed and refrozen shall be discarded. Check for signs of apparent contamination. Solvents 6. Type I, Class A sealants should be checked for should be clean and clear with no signs of cloudiness. appearance, application time, tack-free time, cure time (e)Class VII Cyanoacrylic Base Adhesives - and adhesion. Verify that product is still liquid with no visible signs of 7. Type I, Class B sealants should be checked for contamination. appearance, applicatiion time, cure time, tack-free time (f) Class VIII Pressure Sensitive Materials - and adhesion. In addition, Class B-2 and B-4 sealants Open containers and inspect for hardening, gelling and should be checked for initial flow. contamination. Stir components and mix a small 8. Type I, Class C sealants should be checked for amount of adhesive. Verify that adhesive sets up appearance, application time, cure time and adhesion. properly. In addition, Class C sealants should be tested to (g) Class X Acrylic Adhesives - Inspect base determine that they ARE NOT at a tackfree condition material to ensure that it is still liquid. Mix a small at the end of their rated work life (squeeze out life). amount of the components and verify that it sets up 9. Type II sealants should be checked for properly. appearance, application time, tack-free time and cure 3. In general, if these materials exhibit normal time. physical properties, with no signs of hardening, gelling 10. Type III sealants should be easily thinned or contamination and set up and/or harden properly as with MEK, when difficulty is encountered in thinning applicable, the shelf life may be extended as specified in the sealant, it should be discarded. Table 1-7. 11. Type IV sealants should be checked for e. Testing of Overaged Sealants. appearance, application time, tack-free time and cure time. NOTE 12. Type V and VI sealants should be checked for appearance, tack-free time and cure time. Overaged sealants are those that have 13. Type VII sealants should be checked for exceeded their original shelf life and appearance, application time, tack-free time and cure must be tested prior to use and/or given time. extended shelf life. 14. Type VIII sealants should be checked for appearance, application time, tack-free time, cure tim 1. For identification of sealants Classification, and adhesion. Adhesion to aluminum should be (peel) refer to Fuel, Weather, Pressure and High- less than two-pounds per inch of width. Temperature Sealing - Maintenance Practices. Revision 1 1-19 MODEL 210 & T210 SERIES SERVICE MANUAL STORAGE CONDITION EXTEND CONDITION SHELF LIFE EXTEND RETEST IN PRODUCT (TEMPERATURE INMONTHS SHELF LIFE MONTHS IN DEGREES IN MONTHS FAHENHEIT) ADHESIVES AND CEMENTS EA9309.3NA 40 TO 80°F 12 Months 6 Months 6 Months EA9339 40 TO 80°F 12 Months 6 Months 6 Months EA9314 40 TO 80°F 12 Months 6 Months 6 Months EA9330 40 TO 80°F 12 Months 6 Months 6 Months EA907 40 TO 80°F 12 Months 6 Months 6 Months Devcon F 40 TO 80°F 12 Months 6 Months 6 Months EA934NA 40 TO 80°F 12 Months 6 Months 6 Months 380/6 40 TO 80°F 12 Months 6 Months 6 Months A1186B 40 TO 80°F 12 Months 6 Months 6 Months EC2216 40 TO 80°F 12 Months 6 Months 6 Months #10 Fastset 40 TO 80°F 12 Months 6 Months 6 Months 608 Quickset 40 TO 80°F 12 Months 6 Months 6 Months EC880 40 TO 80°F 8 Months 3 Months 3 Months EC847 40 TO 80°F 8 Months 3 Months 3 Months EC1300L 40 TO 80°F *6 Months *3 Months *3 Months 5452 40 TO 80°F 12 Months 6 Months 6 Months 56431 40 TO 80°F 12 Months 6 Months 6 Months 1636 40 TO 80°F 12 Months 6 Months 6 Months RTV - 157 40 TO 80°F 12 Months 6 Months 6 Months RTV - 158 40 TO 80°F 12 Months 6 Months 6 Months RTV - 159 40 TO 80°F 12 Months 6 Months 6 Months RTV732 40 TO 80°F 12 Months 6 Months 6 Months RTV 102 40 TO 80°F 12 Months 6 Months 6 Months RTV 103 40 TO 80°F 12 Months 6 Months 6 Months RTV 106 40 TO 80°F 12 Months 6 Months 6 Months RTV108 40 TO 80°F 12 Months 6 Months 6 Months RTV109 40 TO 80°F 12 Months 6 Months 6 Months RTV94034 40 TO 80°F 12 Months 6 Months 6 Months Loctite 222 40 TO 80°F 12 Months 6 Months 6 Months Loctite 242 40 TO 80°F 12 Months 6 Months 6 Months Loctite 271 40 TO 80°F 12 Months 6 Months 6 Months Loctite 277 40 TO 80°F 12 Months 6 Months 6 Months Loctite 290 40 TO 80°F 12 Months 6 Months 6 Months Loctite 416 40 TO 80°F 12 Months 6 Months 6 Months Loctite 495 40 TO 80°F 12 Months 6 Months 6 Months Loctite 515 40 TO 80°F 12 Months 6 Months 6 Months Loctite 569 40 TO 80°F 12 Months 6 Months 6 Months Loctite 592 40 TO 80°F 12 Months 6 Months 6 Months Loctite 595 40 TO 80°F 12 Months 6 Months 6 Months * Do not use after three months of storage in the 81 ° F to 90°F range Do not use after five days of storage above 90°F. Table 1-7. (Sheet 1 of 2) 1-20 Revision 1 MODEL 210 & T210 SERIES SERVICE MANUAL STORAGE CONDITION EXTEND CONDITION SHELF LIFE EXTEND RETEST IN PRODUCT (TEMPERATURE IN MONTHS SHELF LIFE MONTHS IN DEGREES IN MONTHSMONTHS FAHENHEIT) ADHESIVES AND CEMENTS (CONTINUED) Loctite 40 TO 80°F 12 Months 6 Months 6 Months Loctite 40 TO 80°F 12 Months 6 Months 6 Months Loctite 40 TO 80°F 12 Months 6 Months 6 Months Loctite 40 TO 80°F 12 Months 6 Months 6 Months Loctite 40 TO 80°F 12 Months 6 Months 6 Months DA-5521 40 TO 80°F 12 Months 6 Months 6 Months PS-18 40 TO 80°F 12 Months 6 Months 6 Months PS-30 40 TO 80°F 12 Months 6 Months 6 Months XA-3678 40 TO 80°F 12 Months 6 Months 6 Months XF-3585 40 TO 80°F 12 Months 6 Months 6 Months LR-100-226 40 TO 80°F 12 Months 6 Months 6 Months EC776 40 TO 80°F * 8 Months * 3 Months *3 Months SB and P2 40 TO 80°F 12 Months 6 Months 6 Months SEALANTS Pro-Seal 890 40 TO 80°F 6 Months 2 Months 2 Months GC-408 40 TO 80°F 6 Months 2 Months 2 Months PR1422 40 TO 80°F 6 Months 2 Months 2 Months PR1440 40 TO 80°F 6 Months 2 Months 2 Months GC435 40 TO 80°F 6 Months 2 Months 2 Months Pro-Seal 567 40 TO 80°F 6 Months 2 Months 2 Months PR810 40 TO 80°F 6 Months 2 Months 2 Months Pro-Seal 700 40 TO 80°F 6 Months 2 Months 2 Months GC 1900 40 TO 80°F 6 Months 2 Months 2 Months PR366 40 TO 80°F 6 Months 2 Months 2 Months Pro-Seal 735 40 TO 80°F 6 Months 2 Months 2 Months Pro-Seal 895 40 TO 80°F 6 Months 2 Months 2 Months Pro-Seal 706B 40 TO 80°F 6 Months 2 Months 2 Months PR1321 40 TO 80°F 6 Months 2 Months 2 Months GC200 40 TO 80°F 6 Months 2 Months 2 Months RTV-730 40 TO 80°F 6 Months 2 Months 2 Months Pro-Seal 815 40 TO 80°F 6 Months 2 Months 2 Months GC402 40 TO 80°F 6 Months 2 Months 2 Months PR-1005L 40 TO 80°F *8 Months *3 Months *3 Months GC-3001 40 TO 80°F *8 Months *3 Months *3 Months 444R 40 TO 80°F *8 Months *3Months *3 Months * Do not use after three months of storage in the 81°F to 90°F range Do not use after five days of storage above 90° F. Table 1-7. (Sheet 2 of 2) Revision 1 1-21/(1-22 blank) MODEL 210 & T210 SERIES SERVICE MANUAL SECTION 2 GROUND HANDLING, SERVICING, CLEANING, LUBRICATION AND INSPECTION WARNING When performing any inspection or mainte- nance that requires turning on the master switch, installing a battery, or pulling the propeller through by hand, treat the propel- ler 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 mal- function, could cause the propeller to rotate. Page No. TABLE OF CONTENTS Aerofiche/Manual GROUND HANDLING ....... 1B6/2-2 Hydraulic Brake Systems .... . 1B16/2-12 Towing ............ 1B6/2-2 Landing Gear Hydraulic Retraction Hoisting . . .. . 1B6/2-2 System ........... 1B16/2-12 Jacking. ....... .... 1B6/2-2 Hydraulic Fluid Sampling and Leveling .. .......... 1B6/2-2 Contamination Check ...... 1B17/2-13 Weighing ........... 1B6/2-2 Oxygen System ......... B17/2-13 Parking ......... . 1B7/2-3 Face Masks .......... 1B17/2-13 Tie-Down . ....... ... 1B7/2-3 CLEANING ........... 1B17/2-13 Flyable Storage ......... 1B7/2-3 General Description ...... . 1B17/2-13 Returning Aircraft to Service ... 1B10/2-6 Upholstery and Interior ...... 1B17/2-13 Temporary Storage ....... 1B10/2-6 Plastic Trim. .......... B17/2-13 Inspection During Storage . . . . 1B10/2-6 Windshield and Windows ..... 1B18/2-14 Returning Aircraft to Service .. 1B11/2-7 Materials Required ....... 1B18/2-14 Indefinite Storage ........ 1B11/2-7 Waxing ........... 1B18/2-14 Inspection During Storage .. .. 1B11/2-7 Preventive Maintenance ..... 1B19/2-15 Returning Aircraft to Service . . . 1B12/2-8 Aluminum Surfaces ....... 1B19/2-15 SERVICING ........... 1B12/2-8 Painted Surfaces ........ 1B19/2-15 Description ......... . 1B12/2-8 Engine/Engine Compartment . .. . 1B20/2-16 Fuel Bays ........... 1B12/2-8 Propeller ........... 1B21/2-16A Fuel Additives ......... B12/2-8 Wheels . ........... 1B21/2-16A Fuel Drains . ......... 1B14/2-10 LUBRICATION ........ . 1B21/2-16A Engine Oil ........... 1B14/2-10 General Description ....... 1B21/2-16A Engine Induction Air Filter . . . 1B15/2-11 Nose Gear Torque Links . ... 1B21/2-16A Vacuum System Filter .. .. . 1B15/2-11 Tachometer Drive Shaft ...... 1B21.2-16A Battery ........ ... 1B15/2-11 Wheel Bearing Lubrication . ... 1B21/2-16A Tires ............. 1B16/2-12 Wing Flap Actuator. . ..... 1B21'2-16A Nose Gear Strut ...... 1B16/2-12 Rod End Bearings ........ 1B21/2-16A Nose Gear Shimmy Dampener . . . 1B16/2-12 INSPECTION . ......... 2C7/2-25 2-1 MODEL 210 & T210 SERIES SERVICE MANUAL 2-1. GROUND HANDLING. fuselage at the first bulkhead forward of the leading edge of the stabilizer. If the optional hoisting rings 2-2. TOWING. Moving the aircraft by hand is ac- are used, a minimum cable length of 60 inches for complished by using the landing gear struts as push each cable is required to prevent bending of the eye- points. A tow bar attached to the nose gear should be bolt type hoisting rings. If desired, a spreader jig used for steering and maneuvering the aircraft. may be fabricated to apply vertical force to the eye- When no tow bar is available, press down at the hori- bolts. zontal stabilizer front spar, adjacent to the fuselage, to raise the nose wheel off the ground. With the nose 2-4. JACKING. Refer to figure 2-2 for jacking pro- wheel clear of the ground, the aircraft can be turned cedures. by pivoting it about the main wheels. CAUTION CAUTION When using the landing gear strut jack pad, flexibility of the gear strut will cause the When towing the aircraft, never turn the nose main wheel to slide inboard as the wheel is wheel more than 35 degrees either side of raised, tilting thejack. The jack must then center or the nose gear will be damaged. Do be lowered for a second jacking operation. not push on control surfaces or outboard em- Jacking both wheels simultaneously with pennage surfaces. When pushing on the tail- landing gear strut jack pad is not recom- cone, always apply pressure at a bulkhead to mended. avoid buckling the skin. 2-4A. LEVELING. Longitudinally leveling of the 2-3. HOISTING. The aircraft may be hoisted with a aircraft is accomplished by backing out the two hoist of two-ton capacity, either by using hoisting screws on the left side of the fuselage and then rings (optional equipment) or by using suitable slings. placing a level across the screws. Corresponding The front sling should be hooked to the engine lifting points on either the upper or lower main door sills eye, and the aft sling should be positioned around the may be used to level the aircraft laterally. 2-4B. WEIGHING AIRCRAFT. Refer to Pilot's Operating Handbook. SHOP NOTES: 2-2 MODEL 210 & T210 SERIES SERVICE MANUAL TOW BAR: PART NUMBER 0501019-1, IS AVAIL- ABLE FROM THE CESSNA SUPPLY DIVISION. Figure 2-1. Typical Tow Bar 2-5. PARKING. Parking precautions depend prin- vation of the engine cylinders can be cipally on local conditions. As a general precaution, documented and confirmed at a later date it is wise to set the parking brake or chock the if necessary. wheels, and install the control lock. In severe weather, and high wind conditions, tie down the air- The airplane is delivered from Cessna with a craft as outlined in paragraph 2-6 if a hangar is not Corrosion Preventive Aircraft Engine Oil mix- available. ture. This engine oil is a blend of aviation grade straight mineral oil and corrosion pre- 2-6. TIE-DOWN. When mooring the aircraft in the ventive compound. This oil should be used for open, head into the wind if possible. Secure control the first 25 hours of engine operation. In the surfaces with the internal control lock and set brakes. event it is necessary to add oil during the first 25 hours of operation, use MIL-L-6082 CAUTION aviation grade straight mineral oil of the cor- rect viscosity. Do not set parking brakes when they are Flyable storage is defined as a maximum of 30 days overheated or during cold weather when non-operational storage and can be broken down into accumulated moisture may freeze them. the following two programs. a. Program 1 - engines or cylinders with less than a. Tie ropes cables or chains to the wing tie-down 50 operating hours. fittings located mid-wing in line with the outboard 1. Propeller pull-thru every five days. (See edge of the flaps. Secure the opposite ends of ropes step c.) cables or chains to ground anchors. 2. Fly airplane every 30 days. (See step d.) b. Secure a tie-down rope (no chains or cables) b. Program 2 - engines or cylinders with more than to upper trunnion of the nose gear, and secure oppo- 50 operating hours to TBO if not flown weekly. site end of rope to ground anchor. 1. Propeller pull-thru every seven days. (See c. Secure the middle of a rope to the tail tie-down step c.) ring. Pull each end of rope away at a 45-degree 2. Fly airplane every 30 days. (See step d.) angle and secure to ground anchors at each side of c. The propeller should be rotated by hand without tail. running the engine. For four and six cylinder d. Secure control lock on pilot control column. If straight drive engines, rotate engine six revolutions, control lock is not available, tie pilot control wheel stop propeller 45°to 90 ° from original position. For back with front seat belt. six cylinder geared engines, rotate propeller four rev- e. These aircraft are equipped with a spring-loaded olutions and stop propeller 30° to 60 ° from original steering bungee which affords protection against nor- position. mal wind gusts. However, if extremely high wind gusts are anticipated, additional locks may be install- CAUTION ed. For maximum safety, accomplish engine rota- 2-7. FLYABLE STORAGE. tion as follows: NOTES 1. Verify magneto switches are OFF. 2. Place throttle in CLOSED position. Preservation date should be written on pro- 3. Place mixture control in IDLE CUT-OFF peller tag. position. 4. Set brakes and block airplane wheels. Maintain complete and accurate engine pre- 5. Leave airplane tie-downs installed and servation records to ensure proper preser- verify that cabin door latch is open. 2-3 MODEL 210 & T210 SERIES SERVICE MANUAL 16" minimum A E ITEM NUMBER TYPE AND PART NUMBER REMARKS #2-170 Basic jack Closed height: 69-1/2 inches; extended MODEL 210 & T210 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 indicator light is observed. 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) 2-5 MODEL 210 & T210 SERIES SERVICE MANUAL 6. DO NOT stand within arc of propeller it was removed. If the battery is returned to blades while turning propeller. service in a different aircraft, appropriate d. The airplane should be flown for thirty (30) record changes must be made and notification minutes, reaching, but not exceeding, normal oil sent to the Cessna Claims Department. and cylinder temperatures. If the aircraft cannot be flown it should be represerved in accordance f. Remove battery and store in a cool, dry place; with paragraph 2-11. (Temporary Storage) or service battery periodically and charge as required. paragraph 2-14. (Idefinite Storage). Ground run- ning is not an acceptable substitute for flying. NOTE NOTE An engine treated in accordance with the fol- lowing may be considered being protected If step 2 in each program cannot be accom- against normal atmospheric corrosion for a plished on schedule due to weather, mainte- period not to exceed 90 days. nance, etc., pull the propeller through daily and accomplish as soon as possible. g. Disconnect spark plug leads and remove upper and lower spark plugs from each cylinder. e. If airplane is stored outside, tie it down in accor- dance with paragraph 2-6. In addition, the pitot tube, NOTE static air vents, air vents, openings in the engine cowling, and other similar openings shall have pro- The preservative oil must be MIL-L46002, tective covers installed to prevent entry of foreign grade 1, at room temperature. Two preserva- material. tive oils recommended for use in Teledyne Continental engines for temporary and indefi- 2-8. RETURNING AIRCRAFT TO SERVICE. After nite storage are NOX RUST VCI-105 (Daubert flyable storage, returning the aircraft to service is Chemical Co., 4700 S. Central Avenue accomplished by performing a thorough pre-flight in- Chicago, IL.) and PETROTECT, VA (Pennsyl- spection. At the end of the first 25 hours of engine vania Refining Company, Butler, PA). operation, drain engine oil and clean oil pressure h. Using a portable pressure sprayer, spray pre- screen (or change external oil filter element). Ser- servative oil through the upper spark plug hole of vice engine with correct grade and quantity of oil. Refer to figure 2-4 and paragraph 2-20 for correct crankshaft as each pair of cylinder s i s sprayed. tate crankshaft as each pair of cylinders is sprayed. grade of engine oil. i. After completing step "h," rotate crankshaft so that no piston is at a top position. 2-9. TEMPORARY STORAGE. Temporary storage that no piston is at a top position. is defined as aircraft in a non-operational status for j. Again, spray each cylinder without moving the a maximum of 90 days. The aircraft is constructed crankshaft, to thoroughly cover all interior surfaces of corrosion-resistant alclad aluminum, which will of the cylinder above the piston. clean. However, these alloys are subject to oxida- 1. Apply preservative oil to the engine interior by tion. The first indication of corrosion on unpainted spraying approximately two ounces of the preserva- surfaces is in the form of white deposits or spots. tive oil through the oil filler tube. On painted surfaces, the paint is discolored or blis- m. Seal all engine openings exposed to the atmos- tered. Storage in a dry hangar is essential to good phere, using suitable plugs or non-hygroscopic tape. preservation and should be procured, if possible. Attach a red streamer at each point that a plug or Varying conditions will alter the measures of preser- tape is installed. vation, but under normal conditions in a dry hangar, n. If the aircraft is to be stored outside, perform the procedures outlined in paragraph 2-6. In addi- and for storage periods not to exceed 90 days, the the procedures outlined in paragraph 2-6. In addi- following methods of treatment are suggested. tion, the pitot tube, static source vents, air vents, a. Fill fuel bays with correct grade of gasoline. openings in the engine cowling, and other similar b. Clean and wax aircraft thoroughly. openings should have protective covers installed to c. Clean any oil or grease from tires, and coat prevent entry of foreign material. tires with a tire preservative. Cover tires to pro- . Attach a warning placard to the propeller to the tect against grease or oil. effect that the propeller shall not be moved while the tect against grease or oil. d. Either block up fuselage to relieve pressure on engine is in storage. tires or rotate wheels every 30 days to prevent flat 2-10. INSPECTION DURING STORAGE. spotting the tires. a. Inspect airframe for corrosion at least once a e. Lubricate all airframe items and seal or cover mnth, collection as frequently a month. Remove dust collections as frequently as all openings which could allow moisture and/or dust possible. Clean and wax aircraft as required. to enter. b. Inspect the interior of at least one cylinder through the spark plug hole for corrosion at least once each month. The aircraft battery serial number is recorded NOTE in the aircraft equipment list. To assure ac- curate warranty records, the battery should Do not move crankshaft when inspecting be reinstalled in the same aircraft from which interior of cylinder for corrosion. 2-6 MODEL 210 & T210 SERIES SERVICE MANUAL c. If at the end of the 90 day period, the aircraft d. Apply preservative to engine interior by spray- is to be continued in non-operational storage, repeat ing M3L-L-46002, Grade 1 oil (approximately two the procedural steps "g" thru "o" of paragraph 2-9. ounces) through oil filler tube. e. Install dehydrator plugs MS27215-1 or-2, in 2-11. RETURNING AIRCRAFT TO SERVICE. After each of the top spark plug holes, making sure that temporary storage, use the following procedure to each plug is blue in color when installed. Protect and return the aircraft to service. support spark plug leads with AN-4080 protectors. a. Remove aircraft from blocks. Check tires for f. DO NOT rotate propeller after completing proper inflation. step'e". b. Check and install battery. g. If engine is equipped with a pressure type car- c. Check that oil sump has proper grade and quan- buretor, preserve this component by the following tity of engine oil. method. Drain carburetor by removing the drain and d. Service induction air filter and remove warning vapor vent plugs from regulator and fuel control placard from propeller. unit. With mixture control in "Rich" position, inject e. Remove materials used to cover openings, lubricating oil, grade 1010, into fuel inlet at a pres- f. Remove, clean and gap spark plugs. sure not to exceed 10 psi until oil flows from vapor g. While spark plugs are removed, rotate propeller vent opening. Allow excess oil to drain, plug inlet and several revolutions to clear excess rust preventive tighten and safety the drain and vapor vent plugs. oil from cylinders. Wire throttle in open position, place bags of desiccant h. Install spark plugs and torque to values listed in the intake and seal opening with moisture reis- in Section 12 or 12A of this manual. tent paper and tape or a cover plate. i. Check fuel strainer. Remove and clean filter h. If carburetor is removed from engine, place a screen, if necessary. Check fuel bays and fuel lines bag of desiccant in throat of carburetor air adapter. for moisture and sediment. Drain enough fuel to Seal adapter with moisture-resistant paper and tape eliminate moisture and sediment. or a cover plate. j. Perform a thorough pre-flight inspection, then i. The TCM fuel-injection system does not require start and warm-up engine. any special preservation preparation. For preserv- ation of the Bendix RSA-7DA1 fuel-injection system, 2-12. DEFINTE STORAGE. Indefinite s refer to the Bendix Operation and Service Mnual. defined as aircraft in a non-operational status for an J. Pae openings with moisture-resistant tape. .and seal the o with opening with moisture-rsistanttape. indefinite period of time. Engines treated in accor- k. Seal cold air inlet to heater muff with moisture- dance with the following may be considered protected resistant tape to exclude moisture and foreign objects. against normal atmosphere corrosion, provided proce- . engine breather by inserting a dehydrator dures outlined in paragraph 2-13 are performed at in- 1 S715-2 plug in breather hose andclaming in tervl Roptatfed.~ cakaMS2f7215-2 plug in breather hose and clamping in tervals specified. p. a. Drain engine oil and refill with MI -6529 Type II. The aircraft should be flown for thirty (30) min- atmosphere using suitable plugs or non-hyro atmosphere, using suitable plugs or non-hypro- utes, reaching, but not exceeding normal oil and cyl- scopie tape inder temperatures. Allow engine to cool to ambient n. Attach a red streamer to each place on the en- temperature. spark plug gine where ags of desiccant are placed. Either attach b. Remove top spark plug and spray preservative red streamers outside of sealed area with tape or to oil (Lubrication Oil - Contact and Volatile Corrosion - inside of sealed are with safety-wire to prevent wick- Inhibited, MIL--46002, Grade 1) at room tempera- ng of moisture into sealed area ture, through upper spark plug hole of each cylinder o. Drain corrosion-preventive mixture from engine with piston in approxmately bottom dead center posi- sump and reinstall drain plug or close drain valve. tion. Rotate crankshaft as each pair of opposite cylin- ders is sprayed. Stop crankshrft with no piston at top NOTE dead center. A pressure pot or pump-up type garden pressure sprayer may be used. The spray head should The corrosion-preventive mixture is harmful have ports around circumference to allow complete to paint and should be wiped from painted coverage of cylinder walls. surfaces immediately. c. Respray each cylinder without rotating crank. To thoroughly cover all surfaces of cylinder interior, p. Attach a warning placard on the throttle control move nozzle or spray gun from top to bottom of cyl- knob to the effect that the engine contains no lubri- inder. cating oil. Placard the propeller to the effect that it should not be moved while the engine is in storage. NOTE q. Prepare airframe for storage as outlined in para- graph 2-11 thru step "e. MIL-C-6529 Type II may be formulated by thoroughly mixing one part compound MIL- 2-13. INSPECTION DURING STORAGE. Aircraft C-6529 Type I (Esso Rust-Ban 628, Cos- in indefinite storage shall be inspected as follows: moline No. 1223 or equivalent) with three a. Aircraft prepared for indefinite storage should parts new lubricating oil of the grade recom- have cylinder dehydrator plugs visually inspected mended for service (all at room temperature). every 15 days. The plugs should be changed as soon Single grade oil is recommended. as their color indicates unsafe conditions of storage. 2-7 MODEL 210 & T210 SERIES SERVICE MANUAL If the dehydrator plugs have changed color in one- 1. Perform a thorough preflight inspection, then half or more of the cylinders, all desiccant material start and warm up engine. on the engine should be replaced. m. Thoroughly clean and test-fly airplane. b. The cylinder bOres of all engines prepared for in- definite storage should be resprayed with corrosion- 2-15. SERVICING. preventive mixture every six months, or more fre- quently if bore inspection indicates corrosion has 2-16. DESCRIPTION. Servicing requirements are started earlier than six months. Replace all desiccant shown in figure 2-4. The following paragraphs and dehydrator plugs. Before spraying, engine supplement this figure by adding details not should be inspected for corrosion as follows: Inspect included in the figure. interior of at least one cylinder on each engine through the spark plug hole. If cylinder shows start 2-17. FUEL BAYS. An area of each wing is sealed of rust, spray cylinder corrosion-preventive oil and to form an integral fuel bay. Recommended fuel turn prop over six times, then respray all cylinders. grades are listed in figure 2-4. Fuel bays should be Remove at least one rocker box cover from each en- filled immediately after flight to lessen condensation gine and inspect valve mechanism. in bays and lines. 2-14. RETURNING AIRPLANE TO SERVICE. NOTE After indefinite storage, use the following procedure to return the airplane to service. Before refueling or when airplane is parked on a. Remove aircraft from blocks and check tires for a slope, place the fuel selector handle in the correct inflation. Check for correct nose gear strut LEFT ON or RIGHT ON position, whichever cor- inflation. responds to the low wing. This will minimize cross- b. Check battery and install. feeding from the fuller bay and reduce fuel c. Remove all materials used to seal and cover seepage from the wing vents. This note applies openings. only to 1985 models. d. Remove warning placards posted at throttle and propeller. e. Remove and clean engine oil screen, then re- WARNING install and safety. on airplanes that are equipped with an external oil filter, install new filter elements.DURING ALL FUELING PROCEDURES f. Remove oil sump drain plug and drain sump. FIREFIGHTING EQUIPMENT MUST BE Install and safety drain plug and fill engine with oil. AVAILABLE. TWO GROUND WIRES FROM DIFFERENT POINTS ON THE AIRPLANE NOTE TO SEPARATE APPROVED GROUND STAKES SHALL BE USED TO PREVENT The corrosion-preventive mixture will mix ACCIDENTAL DISCONNECTION OF ONE with the engine lubrication oil, so flushing GROUND WIRE. ENSURE THAT FUELING the oil system is not necessary. Draining NOZZLE IS GROUNDED TO THE AIR- the oil sump will remove enough of the PLANE corrosion-preventive mixture. NOTE WARNING Tie-down rings should be used as grounding When returning the airplane to service do not points for all grounding wires during re- use the corrosion-preventive oil referenced in fueling procedures. paragraph 2 -12, step "a". 2-18. USE OF FUEL ADDITIVES FOR COLD g. Service and install the induction air filter. WEATHER OPERATION. Strict adherence to recom- h. Remove dehydrator plugs and spark plugs or mended preflight draining instructions will eliminate plugs installed in spark plug holes and rotate any free water accumulations from the tank sumps. propeller by hand several revolutions to clear While small amounts of water may still remain in corrosion-preventive mixture from cylinders. solution in the gasoline, it will normally be consumed i. Clean, gap, and install spark plugs. Torque and go unnoticed in the operation of the engine. plugs to value listed in Section 12 or 12A. j. Check fuel strainer. Remove and clean filter One exception to this can be encountered when oper- screen. Check fuel tanks and fuel lines for ating under the combined effect of: 1) use of certain moisture and sediment, and drain enough fuel to fuels, with 2) high humidity conditions on the ground eliminate moisture and sediment. 3) followed by flight at high altitude and low tempera- k. If the carburetor has been preserved with oil, ture. Under these unusual conditions small amounts drain it by removing the drain and vapor vent plugs of water in solution can precipitate from the fuel from the regulator and fuel control unit. With mix- stream and freeze in sufficient quantities to induce ture control in "Rich" position, inject service-type partial icing of the engine fuel system. gasoline into fuel inlet at a pressure not to exceed 10 psi until all of the oil is flushed from the carburetor. While these conditions are quite rare and will not Reinstall carburetor plugs and attach fuel line. normally pose a problem to owners and operators, 2-8 MODEL 210 & T210 SERIES SERVICE MANUAL they do exist in certain areas of the world and con- Any high quality isopropyl alcohol may be used, such sequently must be dealt with when encountered. as: Anti-icing fluid (MIL-F-5566) or Isopropyl alco- hol (Federal Specification TT-I-735a). Therefore, to alleviate the possibility of fuel icing occurring under these unusual conditions it is per- Ethylene glycolmonomethyl ether (EGME) compound missible to add isopropyl alcohol or ethyelene glycol in compliance with MIL-I-27686 or Phillps PFA- monomethyl ether (EGME) compound to the fuel sup- 55MB, if used, must be carefully mixed with the fuel ply. See Figure 2-3 for fuel additive mixing ratio. in concentrations not to exceed 0.15% by volume. CAUTION CAUTION Diethylene glycol monomethyl ether (DiEGME) has NOTbeen approved by engine Mixing of the EGME compound with the fuel manufacturer for use with propeller single is extremely important because concentra- engine aircraft tion in excessof that recommended (0.15 percent by volume max imum) will result in detrimental affects to the fuel tanks, such The introduction of alcohol or EGME compound into as deterioration protective primer and the fuel provides two distinct effects: 1) it absorbs sealants and damage to O-rings and seals the dissolved water from the gasoline and 2) alcohol in the fuel system and engine components. has a freezing temperature depressant effect. Use only blending quipment that is recom- mended bythe manufacturer to obtain proper Alcohol, if used, is to be blended with the fuel in a proportioning concentration of 1% by volume. Concentrations greater than 1% are not recommended since they can Do not allow the concentrated EGME com- be detrimental to fuel tank materials. pound to come in contact with the airplane finish or fuel cell as damage can result. 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. SHOP NOTES: Revision 2 2-9 MODEL 210 & T210 SERIES SERVICE MANUAL rod protruding from cup. If water is found during corrosion preventive aircraft engine oil daily inspection, open all drain valves and remove (MIL-C-6250, Type I). If oil must be added all fuel drain plugs to drain all water from the fuel during the first 25 hours of operation, use system. only aviation grade straight mineral oil con- 2-20. ENGINE OIL. Check engine lubricating oil forming to Specification MIL-L-6082. After with the dipstick five to ten minutes after the the first 25 hours of operation. drain engine engine has been stopped. The aircraft should be in oil sump and clean the oil pressure screen. as near a level position as possible when checking If an optional oil filter is installed, change the engine oil so that a true reading is obtained. filter element at this time. Refill sump Engine oil should be drained while the engine is with correct quantity and grade of dispersant still hot. and the nose of the aircraft should be oil conforming to Continental Motors Specifi- raised slightly for more positive draining of any cation MHS-24 and with current Continental sludge which may have collected in the engine oil Aircraft Engine Service Bulletins. Newly sump. Engine oil should be changed every six overhauled engines should also be operated months, even though less than the specified hours on aviation grade straight mineral oil con- have accumulated. Reduce these intervals for forming to Specification MIL-L-6082 until a prolonged operations in dusty