MODEL 210 & T210 SERIES SERVICE MANUAL

CessnaATextron Company SERVICE MANUAL 1977 thru 1984 MODEL 210 & T210 SERIES Member of GAMA FAA APPROVAL HAS BEEN OBTAINED ON TECHNICAL DATA IN THIS PUBLICATION THAT AFFECTS AIRPLANE DESIGN. REVISION 3 INCORPORATES TEMPORARY REVISIONS 1,2, AND 3, DATED 1 DECEMBER 1992, 1 APRIL 1993, AND 3 OCTOBER 1994. COPYRIGHT©1996 10 SEPTEMBER 1982 CESSNA AIRCRAFT COMPANY WICHITA. KANSAS. USA REVISION 3 1 MARCH 1996 D2057-3-13 (RGI-50-7/02) Cessna A Toxtro CompJny TEMPORARY REVISION NUMBER 8 DATE 5 April 2004 Model 210 & T210 Series 1977 Thru 1984 Service Manual MANUAL NUMBER - PAPER COPY MANUAL NUMBER - AEROFICHE TEMPORARY REVISION NUMBER MANUAL DATE 10 September 1982 D2057-3-13 D2057-3-13AF D2057-3TR8 REVISION NUMBER 3 DATE 1 March 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 FICHE/FRAME 1/B22 1/C03 AEROFICHE SECTION PAGE FICHE/FRAME REASON FOR TEMPORARY REVISION 1. To add 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 Insert the new pages into the publication at the appropriate locations and remove and discard the superseded pages. 2.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 This will be a visual identifier that the information on the frame (page) is no longer valid and the Temporary Revision should be referenced.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 MANUAL TITLE SECTION 2 2 PAGE 27 32 cessnaA Textron Company TEMPORARY REVISION NUMBER 7 DATE 7 October 2002 MANUAL TITLE Model 210 & T210 Series 1977 Thru 1984 Service Manual MANUAL NUMBER - PAPER COPY D2057-3-13 MANUAL NUMBER - AEROFICHE D2057-3-13AF TEMPORARY REVISION NUMBER D2057-3TR7 MANUAL DATE 10 September 1982 REVISION NUMBER 3 DATE 1 March 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 28 1/B23 2 28A/Deleted NA 2 29 1/B24 2 30 1/C01 2 31 1/C02 2 32 1/C03 2 32A/Deleted NA 2 33 Added 2 34 Added 2 35 Added 2 36 Added 16 22C Added 16 22D Added REASON FOR TEMPORARY REVISION 1. To include the requirement to inspect all fluid carrying lines and hoses in the cabin and wing areas. Revise the Special Inspection Items section and 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 @ 2002 CESSNA AIRCRAFT COMPANY WICHITA, KANSAS, USA TEMPORARY REVISION NUMBER 6 DATED 7 January 2000 MANUAL TITLE MODEL 210 & T210 SERIES 1977 THRU 1984 SERVICE MANUAL MANUAL NUMBER - PAPER COPY D2057-3-13 AEROFICHE D2057-3-13AF TEMPORARY REVISION NUMBER PAPER COPY D2057-3TR6 AEROFICHE N/A MANUAL DATE 10 SEPTEMBER 1982 REVISION NUMBER 3 DATE 1 MARCH 1996 This Temporary Revision consists of the following pages, which affect existing pages in the paper copy manual and supersede aerofiche information. AEROFICHE AEROFICHE SECTION PAGE FICHE/FRAME SECTION PAGE FICHE/FRAME 2 28A Added 2 32A Added REASON FOR TEMPORARY REVISION To include the inspection requirements of Cessna Service Bulletin SEB99-18. FILING INSTRUCTIONS FOR THIS TEMPORARY REVISION For Paper Publications: File this cover sheet behind the publication's title page to identify the inclusion of the Temporary Revision into the manual. Insert the new pages into the publication at the appropriate locations. Draw a line, with a permanent red ink marker, through any superceded information. For Aerofiche Publications: Draw a line through any aerofiche frame (page) affected by the Temporary Revision with a permanent red ink marker. This will be a visual identifier that the information on the frame (page) is no longer valid and the Temporary Revision should be referenced. For "added" pages in a Temporary Revision, draw a vertical line between the applicable frames which is wide enough to show on the edges of the pages. Temporary Revisions should be collected and maintained in a notebook or binder near the aerofiche library for quick reference. COPYRIGHT a 2000 CESSNA AIRCRAFT COMPANY WICHITA, KANSAS, USA TEMPORARY REVISION NUMBER 5 DATED 2 March, 1998 MANUAL TITLE MODEL 210 SERIES 1977 THRU 1984 SERVICE MANUAL MANUAL NUMBER - PAPER COPY D2057-3-13 AEROFICHE D2057-3-13AF TEMPORARY REVISION NUMBER - PAPER COPY D2057-3TR5-13 AEROFICHE N/A MANUAL DATE 10 September, 1982 REVISION NUMBER 3 DATE 1 March, 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 30 1 C-01 2 31 1 C-02 2 32 1 C-03 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 4 DATED October 1, 1997 MANUAL TITLE Model 210, And T210 Series 1977 Thru 1984 Service Manual MANUAL NUMBER - PAPER COPY D2057-3-13 AEROFICHE D2057-3-13AF TEMPORARY REVISION NUMBER - PAPER COPY D2057-3TR4-13 AEROFICHE N/A MANUAL DATE 10 September 1982 REVISION NUMBER 3 DATE 1 March 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 1 5 1A14 1 6 1A15 1 7 Added 1 8 Added 1 9 Added 1 10 Added 1 11 Added 1 12 Added 1 13 Added 1 14 Added 1 15 Added 1 16 Added 1 17 Added 1 18 Added 1 19 Added 1 20 Added 1 21 Added 1 22 Added 14 3 2H10 REASON FOR TEMPORARY REVISION 1. To add wet torque values for McCauley propeller hub bolts and add standard torque value tables. 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 LIST OF EFFECTIVE PAGE1 INSERT LATEST REVISED PAGES, DESTROY SUPERSEDED PAGES. NOTE: The portion of the text affected by the changes is indicated by a vertical line in the outer margins of the page. Changes to illustrations are indicated by miniature pointing hands. Dates of issue for original and revised pages are: 2Original ...... 0....... 10 September 1982 Revision ...... 1....... 3 October 1983 Revision ...... 2 ....... 29 November 1983 Revision ...... 3 ....... 1 March 1996 TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 802, CONSISTING OF THE FOLLOWING: Page Revision Page Revision Page Revision No. No. No. No. No. No. *Title ...................... 3 5-11 ....................... 2 *5A-11Athru5A-11D ....... 3 *AthruB .................. 3 5-12 ....................... 0 *5A-12 Blank ............... 3 C Blank ................... 2 *5-13 thru 5-14 ............. 3 *5A-13 thru 5A-16 .......... 3 * i thru iv ................... 3 5-15 thru 5-20 .............. 0 5A-17 thru 5A-18 .......... 0 1-1 thru 1-6 ................ 2 *5-20A ..................... 3 5A-18A ................... 0 *2-1 ........................ 3 5-20B Blank ............... 0 *5A-18B ................... 3 2.2 ........................ 0 5-21 thru 5-22 .............. 0 5A-19 thru 5A-21 .......... 0 2-3 thru 2-4 ................ 2 *5-22A ..................... 3 *5A-22 thru 5A-27 .......... 3 2-5 thru 2-7 ................ 0 5-22B ..................... 0 5A-28 thru 5A-29 .......... 2 *2-8 ........................ 3 5-23 thru 5-25 .............. 0 *5A-30 ..................... 3 2-9 ........................ 0 *5-26 ...................... 3 5A-31 thru 5A 34 .......... 0 2-10 ....................... 2 5-26A thru 5-26B ........... 0 5A-35 ..................... 2 2-11 thru 2-12 .............. 0 *5-27 ...................... 3 *5A-36 ..................... 3 2-13 ....................... 2 5-28 ....................... 0 5A-37 thru 5A-38 .......... 0 2-14 ....................... 0 *5-29 ...................... 3 *6-1 thru 6-2 ................ 3 2-15 ....................... 1 5-30 thru 5-31 .............. 2 6-3 ........................ 0 2-16 ....................... 2 5-32 ....................... 0 *6-4 ........................ 3 2-17 ....................... 0 *5-33 thru 5-34 ............. 3 6-5 ........................ 0 2-18 ....................... 2 *5-34A ..................... 3 *6-6 ........................ 3 2-19 ....................... 0 5-34B Blank ............... 2 6-7 thru 6-8 ................ 0 2-20 ....................... 2 5-35 thru 5-37 .............. 0 *6-9 thru 6-11 ............... 3 2-21 thru 2-23 .............. 0 *5-38 ...................... 3 6-12 Blank ................ 2 *2-24 ...................... 3 5-39 thru 5-43 .............. 0 *7-1 thru 7-2 ................ 3 2-25 ....................... 0 5-44 ....................... 2 7-3 thru 7-5 ................ 0 2-26 ....................... 1 *5-45 ...................... 3 *7-6 thru 7-7 ................ 3 *2-27 ...................... 3 5-46 ....................... 2 7-8 ........................ 0 2-28 ....................... 0 5-47 thru 5-49 .............. 0 *7-9 ........................ 3 *2-29 ...................... 3 *5-50 thru 5-52 ............. 3 7-10 Blank ................ 2 2-30 ....................... 1 *5-52A ..................... 3 *8-1 thru 8-3 ................ 3 *2-31 thru 2-32 ............. 3 *5-52B Blank ............... 3 8-4 thru 8-6 ................ 0 *3-1 ........................ 3 5-53 ....................... 0 *8-7 ........................ 3 3-2 thru 3-7 ................ 0 5-54 ....................... 2 8-8 Blank .................. 2 3-8 ........................ 2 *5-55 thru 5-60 ............. 3 *9-1 thru 9-2 ................ 3 *3-9 thru 3-10 ............... 3 *5-60A ..................... 3 9-3 ........................ 0 3-11 thru3-15 .............. 0 *5-60B Blank ............... 3 *9-4 ........................ 3 3-16 ....................... 2 5-61 thru 5-65 .............. 2 9-5 thru 9-9 ................ 0 3-17 thru 3-31 .............. 0 *5-66thru5-68 ............. 3 *9-10 ...................... 3 3-32 Blank ................ 0 5-69 thru 5-72 .............. 2 9-11 thru 9-16 .............. 0 4-1 thru 4-2 ................ 0 *5-73 ...................... 3 *10-1 ...................... 3 *4-3 ........................ 3 5-74 thru 5-94 .............. 2 10-2 thru 10-8 ............. 0 4-4 thru 4-6 ................ 0 *5A-1 thru 5A-2 ............. 3 *11-1 ...................... 3 *5-lthru5-3 ................ 3 5A-3 thru 5A-7 ............. 0 11-2 thru 11-3 .............. 0 5-4 thru 5-10 ............... 0 *5A-8thru5A-11 ........... 3 11-4 ....................... 2 Upon receipt of the second and subsequent revisions to this book, personnel responsible for maintaining this publication in current status should ascertain that all previous revisions have been received and incorporated. * The asterisk indicates pages revised, added, or deleted by the current revision. A Revision 3 LIST OF EFFECTIVE PAGES, Cont. - Page Revision Page Revision Page Revision No. No. No. No. No. No. *12-1 ...................... 3 14-2A Blank ............... 0 *17-66 thru 17-68 ........... 3 12-2 .............. ........ 0 14-2B ..................... 0 *17-68A .................... 3 12-2A .................... 2 14-3 thru 14-5 .............. 2 *17-68B Blank .............. 3 12-2B Blank ............... 2 14-6 thru 14-7 .............. 0 *17-69 thru 17-71 ........... 3 12-3 thru 12-8 .............. 0 *14-8 ...................... 3 17-72 thru 17-73 ........... 0 *12-9 ..................... 3 *15-1 thru 15-2 ............. 3 17-74 thru 17-75 ........... 3 12-10 ..................... 0 15-2A ..................... 0 17-76 thru 17-77 ........... 0 12-11 ..................... 2 15-2BBlank ............... 0 17-78thru17-80 ........... 2 12-12 thru 12-13 ........... 0 15-3thru 15-10 ............ 0 18-1 ...................... 3 12-14 Blank ............... 0 15-11thru15-15...........1 18-2 ................. ...... 0 12-15 .................. 2 *15-16 ..... ............. 3 18-3 thru 18-4 .............. 2 *12-16 .................... 3 15-17 ..................... 1 18-5. ...................... 0 12-17thru12-18 ........... 2 15-18 ..................... 0 18-6 Blank ................ 0 *12-18A .................... 3 15-19 thru 15-21 ....... .. 1 18-6A thru 18-6C ........... 2 12-18B Blank ............. 2 15-22 ..................... 2 18-6D ..................... 3 12-19 ..................... 0 15-23 thru 15-30 ........... 1 18-7 thru 18-12 ............ 2 12-20 ..................... 2 15-31 thru 15-32 ........... 3 18-12A .................... 2 12-21 thru 12-27 ........... 0 15-33thru 15-34 ........... 2 18-12B Blank .............. 2 12-28 Blank ............ ... 0 1534A .................... 2 18-13 thru 18-17 ........... 0 12-29 thru 12-30 ........... 2 15-34B Blank .............. 2 18-18 ..................... 2 12-31 thru 12-38 ........... 0 15-35 thru 15-40 ........... 1 18-19 thru 18-26 ........... 0 *12A-1 thru 12A-2 .......... 3 15-40A thru 15-40E ........ 1 18-27 ..................... 3 12A-3 ..................... 2 15-40F .................... 2 18-28thru 18-29 ........... 0 12A-4 ..................... 0 15-41 ..................... 3 18-30 Blank ............... 0 12A-4A ................... 0 15-42thru15-46 ........... 0 19-1 ...................... 3 12A-4B Blank ............. 0 *1547 thru 15-49 ........... 3 19-2 thru 19-4 ............. 0 12A-5 thru 12A-9 .......... 0 15-50 Blank ............... 0 19-5 thru 19-6 ............. 3 *12A-10 .................... 3 *16-1 ...................... 3 20-1 thru 20-2 ............. 3 12A-11 thru 12A-13 ........ 0 16-2 ....................... 0 20-2A ..................... 2 12A-14 Blank ............. 0 *16-3 ...................... 3 20-2B Blank ............... 2 12A-15 thru 12A-16 ........ 0 16-4 thru 16-9 .............. 0 20-3 ....................... 0 12A-16A thru 12A-16B ..... 2 16-10 ..................... 1 20-4 ...................... 2 12A-17thrul2A-18 ........ 2 16-11 ..................... 0 20-5 thru20-29 ............ 0 12A-18A .................. 2 16-12 thru 16-13 ........... 2 20-30 thru 20-32 ........... 2 12A-18B Blank ............ 2 16-14 ..................... 0 20-32A ................... 2 12A-19 thru 12A-30 ........ 0 16-15 thru 16-16 ........... 2 20-32B Blank .............. 2 12A-31 .................... 2 16-17 ..................... 0 20-33 thru 20-34 ........... 0 12A-32 thru 12A-33 ........ 0 *16-18 ..................... 3 20-35 thru 20-38 ........... 2 12A-34 Blank .............. 0 16-19 ..................... 0 20-38A thru 20-38B ........ 2 13-1 thru 13-4 ............ . 0 16-20 thru 16-22 ........... 3 20-39 ..................... 2 *13-5 thru 13-6 ............. 3 *16-22A .................... 3 20-40 thru 20-102 .......... 0 13-7 thru 13-8 .............. 0 *16-22B Blank .............. 3 20-103 .................... 2 13-9 ...................... 2 16-23 thru 16-29 ........... 0 20-104 ................... 0 13-10 thru 13-14 ........... 0 16-30 thru 16-32 ........... 2 20-105 thru 20-106 ......... 2 13-15 thru 13-16 ........... 2 *17-1 thru 17-2 ............. 3 20-107 thru 20-129 ......... 0 13-17 thru 13-23 .......... 0 17-3 thru 17-8 .............. 0 20-130 thru 20-132 ......... 2 13-24 ..................... 2 *17-9 thru 17-10 ............ 3 20-132A ................... 2 13-25 thru 13-30 ........... 0 17-11 thru 17-28 ........... 0 20-132B Blank ............. 2 13-31 ..................... *17.29 thru 17-30 ........... 3 20-133 thru 20-147 ......... 0 13-32 thru 13-33 ........... 0 17-31 thru 17-49 ........... 0 20-148 .................... 2 13-34 Blank . ..... ......... 0 17-50 ..................... 2 20-149thru 20-157 ......... 0 *14-1 ..................... 3 17-51 thru 17-65 ......... 0 20-158Blank .............. 0 14-2 ................. 0.... 0 * The asterisk indicates pages revised, added, or deleted by the current revision. Revision3 B/(C blank) MODEL 210 & T210 SERIES SERVICE MANUAL TABLE OF CONTENTS SECTION PAGE NO. AEROFICHE/MANUAL 1. GENERAL DESCRIPTION .......... ..... ............ .... 1A10 1-1 2. GROUND HANDLING, SERVICING. CLEANING, LUBRICATION AND INSPECTION .......................... 1A20/2-1 3. FUSELAGE ......................................... ... 1C9/3-1 4. WINGS AND EMPENNAGE ............................. 1... D20/4-1 5. LANDING GEAR, BRAKES AND HYDRAULIC SYSTEM (THRU 1978 MODELS) .................................. 1E5/-1 5A. LANDING GEAR, BRAKES AND HYDRAULIC SYSTEM (BEGINNING WITH 1979 MODELS) ......... 1......1115/5A-1 6. AILERON CONTROL SYSTEM ............................. 1K16/6-1 | 7. WING FLAP CONTROL SYSTEM ........................... 1L3/7-1 8. ELEVATOR CONTROL SYSTEM . .......................... 2A2/8-1 9. ELEVATOR TRIM TAB CONTROL SYSTEM ..................... 2A17/9-1 10. RUDDER CONTROL SYSTEM ............................... 2B13/10-1 11. RUDDER TRIM CONTROL SYSTEM .......................... 2C1/11-1 12. ENGINE (NORMALLY ASPIRATED) .......................... 2C13/12-1 12A. ENGINE (TURBOCHARGED) ............................ 2E6/12A-1 13. FUEL SYSTEM ........................ .... 2F19/13-1 14. PROPELLERS AND PROPELLER GOVERNORS ................. 2H6/14-1 15. UTILITY SYSTEMS ................................... 2H16/15-1 16. INSTRUMENTS AND INSTRUMENT SYSTEMS .................. 2K1/16-1 17. ELECTRICAL SYSTEMS ................................... 3A2/17-1 18. STRUCTURAL REPAIR .................................... 3D11/18-1 19. EXTERIOR PAINTING .................................... 3E21/19-1 20. WIRING DIAGRAMS .................. ........... 3F5/20-1 WARNING When performing any inspection or maintenance that requires turning on the master switch, installing a battery, or pulling the propeller through by hand, treat the propeller as if the ignition switch were ON. Do not stand nor allow anyone else to stand, within the arc of the propeller, since a loose or broken wire or a component malfunction could cause the propeller to rotate. Revision 3 i MODEL 210 & T210 SERIES SERVICE MANUAL CROSS REFERENCE LISTING OF POPULAR NAME VS. MODEL NUMBERS AND SERIALS All aircraft, regardless of manufacturer, are certified under model number designations. However, popular names are often used for marketing purposes. To provide a consistent method of referring to these aircraft, the model number will be used in this publication unless the popular name is necessary to differentiate between ver- sions of the same basic model. The following table provides a list- ing of popular name, model number and serial number. MODEL SERIAL POPULAR NAME YEAR MODEL BEGINNING ENDING CENTURION 1977 210M 21061574 21062273 TURBO CENTURION 1977 T210M 21061574 21062273 CENTURION II 1977 210M 21061574 21062273 TURBO CENTURION II 1977 T210M 21061574 21062273 CENTURION 1978 210M 21062274 21062954 TURBO CENTURION 1978 T210M 21062274 21062954 CENTURION II 1978 210M 21062274 21062954 TURBO CENTURION 1978 T210M 21062274 21062954 CENTURION 1979 210M 21062955 21063640 TURBO CENTURION 1979 T210M 21062955 21063640 CENTURION II 1979 210M 21062955 21063640 TURBO CENTURION I 1979 T210M 21062955 21063640 CENTURION 1980 210M 21063641 21064135 TURBO CENTURION 1980 T210M 21063641 21064135 CENTURION II 1980 210M 21063641 21064135 TURBO CENTURION II 1980 T210M 21063641 21064135 CENTURION 1981 210N 21064136 21064535 TURBO CENTURION 1981 T210N 21064136 21064535 CENTURION II 1981 210N 21064136 21064535 TURBO CENTURION I 1981 T210N 21064136 21064535 CENTURION 1982 210N 21064536 21064772 TURBO CENTURION 1982 T210N 21064536 21064772 CENTURION I 1982 210N 21064536 21064772 TURBO CENTURION II 1982 T210N 21064536 21064772 CENTURION 1983 210N 21064773 21064822 TURBO CENTURION 1983 T210N 21064773 21064822 CENTURION II 1983 210N 21064773 21064822 TURBO CENTURION II 1983 T210N 21064773 21064822 CENTURION 1984 210N 21064823 21064897 TURBO CENTURION 1984 T210N 21064823 21064897 CENTURION II 1984 210N 21064823 21064897 TURBO CENTURION II 1984 T210N 21064823 21064897 ii Revision 3 MODEL 210 &T210 SERIES SERVICE MANUAL INTRODUCTION This manual contains factory-recommended procedures and instructions for ground handling, servicing, and maintaining Cessna 210 Series Models. The 210 and T210 Series Models covered in this manual are identical, except the Model T210 is turbocharged. Besides serving as a reference for the experienced mechanic, this book also covers step-by-step procedures for the less experienced. This service manual is designed for aerofiche presentation. To facilitate the use of the aerofiche, refer to the aerofiche header for basic information. IMPORTANT INFORMATION CONCERNING KEEPING CESSNA PUBLICATIONS CURRENT The information in this publication is based on data available at the time of publication and is updated, supplemented, and automatically amended by all information issued in Service News Letters, Service Bulletins, Supplier Service Notices, Publication Changes, Revisions, Reissues and Temporary Revisions. All such amendments become part of and are specifically incorporated within this publication. Users are urged to keep abreast of the latest amendments to this publication through 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. IWARNING ALL INSPECTION INTERVALS, REPLACEMENT TIME LIMITS, OVERHAUL TIME LIMITS, THE METHOD OF INSPECTION, LIFE LIMITS, CYCLE LIMITS, ETC., RECOMMENDED BY CESSNA ARE SOLELY BASED ON THE USE OF NEW, REMANUFACTURED, OR OVERHAULED CESSNA APPROVED PARTS. IF PARTS ARE DESIGNED, MANUFACTURED, REMANUFACTURED, OVERHAULED, PURCHASED, AND/OR APPROVED BY ENTITIES OTHER THAN CESSNA, THEN THE DATA IN CESSNA'S MAINTENANCE/SERVICE MANUALS AND PARTS CATALOGS ARE NO LONGER APPLICABLE AND THE PURCHASER IS WARNED NOT TO RELY ON SUCH DATA FOR NON-CESSNA PARTS. ALL INSPECTION INTERVALS, REPLACEMENT TIME LIMITS, OVERHAUL TIME LIMITS, THE METHOD OF INSPECTION, LIFE LIMITS, CYCLE LIMITS, ETC., FOR SUCH NON-CESSNA PARTS MUST BE OBTAINED FROM THE MANUFACTURER AND/OR SELLER OF SUCH NON-CESSNA PARTS. 1. REVISIONS/CHANGES. Revisions/changes are issued for this publication as required and include only pages that require updating. 2. REISSUE. A reissue is issued as required, and is a complete manual incorporating all the latest | information and outstanding revisions/changes. It supersedes and replaces previous issue(s). REVISIONS/CHANGES and REISSUES can be purchased from a Cessna Service Station or directly from Cessna Parts Distribution (CPD 2), Dept. 701, Cessna Aircraft Company, P. O. Box 949, Wichita, Kansas 67201 (walk-in address: 5800 East Pawnee, Wichita, Kansas 67218). All supplemental service information concerning this manual is supplied to all appropriate Cessna Service Stations so that they have the latest authoritative recommendations for servicing these Cessna airplanes. Therefore, it is recommended that Cessna owners utilize the knowledge and experience of the factory-trained Service Station Organization. Revision 3 iii MODEL 210 & T210 SERIES SERVICE MANUAL CUSTOMER CARE SUPPLIES AND PUBLICATIONS CATALOG A Customer Care Supplies and Publications Catalog is available from a Cessna Service Station or directly from Cessna Parts Distribution (CPD 2), Dept. 701, Cessna Aircraft Company, P. 0. 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 quarterly and issued on Aerofiche with the quarterly Service Information Summaries. A listing of all available publications is issued periodically by the Cessna Propeller Product Support Department. SUPPLEMENTAL TYPE CERTIFICATE INSTALLATIONS Inspection, maintenance, and parts requirements for supplemental type certificate (STC) installations are not included in this manual. When an STC installation is incorporated on the airplane, those portions of the airplane affected by the installation must be inspected in accordance with the inspection program published by the owner of the STC. Since STC installations may change systems interface, operating characteristics, and component loads or stresses on adjacent structures, Cessna provided inspection criteria may not be valid for airplanes with STC installations. CUSTOMER COMMENTS ON MANUAL Cessna Aircraft Company has endeavored to furnish you with an accurate, useful, up-to-date manual. This manual can be improved with your help. Please use the 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 3 MODEL 210 & T210 SERIES SERVICE MANUAL SECTION 1 GENERAL DESCRIPTION Page No. Aerofiche/Manual GENERAL DESCRIPTION ....... 1A10/1-1 Aircraft Specifications .. A10/1-1 Model 210 Series . ....... 1A10/1-1 Stations .......... 1A10/1-1 Description ......... 1A10/1-1 Bolt Torques. ....... 1A14/1-5 1-3. GENERAL DESCRIPTION. 1-2. MODEL 210-SERIES. 1-4. AIRCRAFT SPECIFICATIONS. Leading parti- culars of these aircraft, with dimensions based on 1-3. DESCRIPTION. The Cessna Centurion, gross weight, are given in figure 1-1. If these dimen- Centurion II, Turbo Centurion, and Turbo sions are used for constructing a hangar on computing Centurion II (Model 210 Series) aircraft, described clearances, remember that such factors as nose gear in this manual, are single-engine, high-wing strut inflation, tire pressures, tire sizes, and load monoplanes of all metal, semimonocoque construc- distribution may result in some dimensions that are tion. Wings are full cantilever, with sealed sections considerably different from those listed. forming fuel bays. The fully-retractable tricycle landing gear consists of tublar spring-steel main 1-5. STATIONS. A station diagram is shown in fig- gear struts and a steerable nose gear with an air- ure 1-2 to assist in locating equipment when a written hydraulic fluid shock strut. The six place seating description is inadequate or impractical arrangement is of conventional, forward facing type. Powering the Model 210 Series is a Continental, hor- izontally-opposed, air-cooled, six-cylinder, fuel- injected engine driving an all-metal, constant-speed propeller. A more desirable higher performance aircraft, is offered in the turbocharged version of the Model 210 Series. Revision 2 1-1 MODEL 210 & T210 SERIES SERVICE MANUAL MODEL 210 AND T210 SERIES MAXIMUM WEIGHT - 210 Ramp ............................ 3812 lbs. Takeoff or Landing ...................... 3800 Ibs. STANDARD EMPTY WEIGHT - 210 Centurion .......................... . 2173 lbs. Centurion II ..................... .. 2223 lbs. MAXIMUM USEFUL LOAD - 210 Centurion ......................... 1639 lbs. Centurion II . . . . . . . . . . . . . . . . . . . . . . . . . 1589 bs. MAXIMUM WEIGHT - T210 Ramp ........... .......... 4016 lbs. Takeoff .......................... . 4000 lbs. Landing .................. ........ 3800 lbs. STANDARD EMPTY WEIGHT - T210 Turbo Centurion ...................... . 2263 lbs. Turbo Centurion II ...................... 2311 lbs. MAXIMUM USEFUL LOAD - T210 Turbo Centurion ....................... 1753 lbs. Turbo Centurion II ...................... 1705 lbs. FUEL CAPACITY Total ................. ........ ... 90 gal. Usable - Thru Serial 21064535 . . .............. .89 gal. Usable - Beginning with Serial 21064536 ........... 87 gal OIL CAPACITY ................ ......... 10 qt. With External Oil Filter and All Turbocharged Engines ................ 11 qt. ENGINE MODEL 210 (Refer to Section 121for Engine Data) .......... . CONTINENTAL 10-520 T210 (Refer to Section 12A for Engine Data) ........... CONTINENTAL TSIO-520 PROPELLER (Constant-Speed) (Three Blades) ................... .... 80" McCAULEY LANDING GEAR (Retractable, Hydraulically-Actuated) ........ Tricycle MAIN WHEEL TIRES ....................... 6.00 x 6 Pressure .. .... . . . ....... . .. . .... . 55 psi NOSE WHEEL TIRE 210 ........ .............. 5.00 x 5, 6ply Pressure .............. ........ 50 psi T210 (THRU T21062954) ................... 5.00 x 5, 6 ply Pressure ......... . ............. 50 psi T210 (BEGINNING WITH T21062955) ............. 5.00 x 5, 10 ply Pressure . . . . ........ . .... 88 psi Figure 1-1. Aircraft Specifications (Sheet 1 of 2) 1-2 Revision 2 MODEL 210 & T210 SERIES SERVICE MANUAL MODEL 210 AND T210 SERIES NOSE GEAR STRUT PRESSURE (Strut Extended) .......... 90 psi WHEEL ALIGNMENT Camber . ......... ........... ..... 4 ° 1° 30' Toe-in .................. ... ..... 0" 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 ............................. 23 ° ± 1° Down . . .. . . . . . . . . . .. . . . . . .. . . . . . . 17° ± 1° ELEVATOR TRIM TAB TRAVEL Up . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 25 ° ± 1° Down . . . . . . . . . . . . . .. . . . . . . . . . . . . . 10 °± 1° PRINCIPAL DIMENSIONS Wing Span ....................... . . . 441.75" Tail Span .. .. . . . .. ..... .. . .... . . . . . 156.32" Length .................. ........ 337.96" Fin Height (Maximum with Nose Gear Depressed and Flashing Beacon Installed on Fin) .............. 112.92" Track Width ................. . ...... 104.20" BATTERY LOCATION .................... Left Side of Firewall Figure 1-1. Aircraft Specifications (Sheet 2 of 2) Revision 2 1-3 MODEL 210 & T210 SERIES SERVICE MANUAL MODEL 210 SERIES 25.25 54.00 3.8 70.8 112.0 152.2 209.0 7 68.00 0.0 44.0 55.6 *106.0 *124.6 7796.00 * INDICATES CANTED BULKHEAD ~~°°11. 00 138. 00 Fure 1-2. Reference Stations0 ~~~1-4 Revis~~i~~on 2~~189.00 206.00 3.8 70.8 112,0 152.2 209.0 18.0I _90o.o / 138.0 180. 6 8.1 67.2 98.0 109.6* 166.4 194.8 23o. 8 0.0 44 0 55.6 3 106.0 '124.6 77.0 *INDICATES CANTED BULKHEAD Figure 1-2. Reference Stations 1-4 Revision 2 MODEL 210 & T210 SERIES SERVICE MANUAL 1-6. MATERIALAND TOOL CAUTIONS- GENERAL Solvents are hazardous to work with because of their flammability, rate of evaporation and reaction to A. Mercury oxidizers. Solvents can also be an irritant to the skin CAUTION and eyes. THERMOMETERS AND OTHER TEST A single spark, a smoldering cigarette, or even EQUIPMENT CONTAINING MERCURY, MUST atmospheric conditions can ignite solvent vapors. The NOT BE USED ON THE AIRPLANE. lower the flash point of the chemical, the more likely it is to become flammable. Generally, flash points of less Mercury, by the amalgamation process, can penetrate than 100°F (37.8°C) are considered flammables. any break in the finish, paint or sealing coating of a Examples of solvent flash points are shown below: metal structural element. An oxide coating on a dry metallic surface will tend to inhibit an immediate SOLVENT FLASH-POINT action while a bright, polished, shining or scratched surface will hasten the process. Moisture will also Methyl Propyl Ketone 45°F (7.2° C) promote the amalgamation process. Soils, greases or other inert contaminants, present on the metal Touluene 39°F (3.9° C) surfaces, will prevent the start of the action. The corrosion and embrittlement which results from an Isopropyl Alcohol 53.6°F (12° C) initial penetration, can be extremely rapid in structural members under load. Once it has begun, Acetone 1.4° (-17°C) there is no known method of stopping it. Complete destruction of the load carrying capacity of the metal The rate of evaporation is closely tied to flammability, will result. because normally the vapors must be present to ignite the liquid. Vaporization also allows solvents, even those that b. Maintenance Precautions are not flammable, to get into the air and into the body's blood stream through the lungs. WARNING Solvents can also react explosively with oxidizers (chemicals which release oxygen). A very violent and uncontrollable reaction takes place which generates heat DURING MAINTENANCE, REPAIR AND rapidly. For this reason, it is very important for each SERVICING OF THE AIRPLANE, MANY person to be aware of specific chemicals in use in the work SUBSTANCES AND ENVIRONMENTS area, and to adhere to the labeling of containers. Chemical ENCOUNTERED MAY CAUSE INJURY IF manufacturers are required to label each container with a PROPER PRECAUTIONS ARE NOT diamond shaped symbol: red forflammable and yellow for OBSERVED. oxidizers. Carefully read and follow all instructions, and Solvents can also damage the hands and skin. Solvents especially adhere to all cautions and warnings dry out skin and dissolve the natural oils. The condition provided by the manufacturer of the product being can develop into an irritation, or if left untreated with used. Use appropriate safety equipment as required continuous exposure, it may progress to a dermatitis. including goggles, face shields, breathing apparatus, Damaged skin allows other contaminants to worsen the protective clothing and gloves. Fuel, engine oil, condition, because the contaminants have easier access to solvents, volatile chemicals, adhesives, paints and the deeper levels of the skin. In serious cases, blood strong cleaning agents may cause injury when poisoning is also possible. contacting the skin or eyes, or when vapors are breathed. When sanding composites or metals or The best defense against skin irritation is not to be otherwise working in an area where dust particles exposed. If exposure is unavoidable, steps should betaken may be produced, the area should be ventilated and to limit exposure times. Prolonged exposure to these the appropriate respirator must be used. irritants can lead to long term liver damage. c. General Usage Solvents General usage solvents include the following: Methyl Propyl Ketone Toluene Isopropyl Alcohol Acetone Methylene Chloride 1,1,1-Trichloroethane Naptha Trichloroethylene These chemicals/solvents are generally colorless, evaporate quicker than water, and tend to give off vapors in higher quantities as their temperature increases. The vapors are generally heavier than air, which causes them to collect in low lying areas or push normal oxygen and air out of a confined area. This situation can lead to Temporary Revision Number 4 1-5 October 1,1997 MODEL 210 & T210 SERIES SERVICE MANUAL 1-7. TORQUE DATA- MAINTENANCE PRACTICES f. Countersunk washers used with close tolerance bolts must be installed correctly to ensure proper To ensure security of installation and prevent over torquing (refer to Figure 1-5). stressing of components during installation, thetorque values outlined in this section and other applicable Tighten accessible nuts torque values Table chapters of this manual should be used~ during g. Tighten accessible nutsto torque values per Table installation and repair of components 1-1. Screws attached to nutplates, or screws with installation andrepair of components. threads not listed in Table 201 should be tightened The torque value tables, listed in this section, are firmly, but not to a specific torque value. Screws standard torque values for the nut and bolt used with dimpled washers should not be drawn combinations shown. If a component requires special tight enough to eliminate the washer crown. torque values, those values will be listed in the applicable maintenance practices section h. Table 1-1 is not applicable to bolts, nuts and screws . used in control systems or installations where the Torque is typically applied and measured using a required torque would cause binding or would torquewrench. Differentadapters, used inconjunction interfere with proper operation of parts. On these with the torque wrench, may produce an actual torque to the nut or bolt which is different from the torque installations, the assembly should be firm but not reading. Figure 1-4 is provided to help calculate actual binding. torque in relation to specific adaptors used with the torquewrench i. Castellated Nuts. Free Running Torque Value Self-locking and non self-locking castellated nuts, Free running torque value is the torque vale tightened to the minimum torque value shown in required to rotate a nut on a threaded shaft, h 11 The torque may increased nallth without tightening. Free running torque value does Table 1-1. The torque may be increased to install the not represent the torque values listed in the tables cotter pin, but this increase must not exceed the of this section. Torque values listed in the tables alternatetorque values. represent the torque values above free running torque. MS17826 self-locking, castellated nuts shall be torqued per Table 1-1. EXAMPLE The end of the bolt or screw should extend through If finaltorque required isto be 150 inch-pounds and the nut at least two full threads including the the free running torque is 25 inch-pounds, then the chamfer. free running torque must be added to the required torque to achieve final torque of 150 +25 = 175 inch-pounds. Breakaway torque value is the value of torque required to start a nut rotating on a thread shaft, and does not represent free running torque value. It should be noted that on some installations the breakaway torque value cannot be measured. General Torquing Notes: a. These requirements do not apply to threaded parts used for adjustment, such as turnbuckles and rod ends. b. Torque values shown are for clean, nonlubricated parts. Threads should be free of dust, metal filings, etc. Lubricants, other than that on the nut as purchased, should not be used on any bolt installation unless specified. c. Assembly of threaded fasteners, such as bolts, screws and nuts, should conform to torque values shown in Table 1-1. d. When necessary to tighten from the bolt head, increase maximum torque value by an amount equal to shank friction. Measure shank friction with a torque wrench. e. Sheet metal screws should be tightened firmly, but notto a specifictorquevalue. Temporary Revision Number 4 1-6 October 1, 1997 MODEL 210 & T210 SERIES SERVICE MANUAL NOTE: WHEN USING A TORQUE WRENCH ADAPTER WHICH CHANGES THE DISTANCE FROM THE TORQUE WRENCH DRIVE TO THE ADAPTER DRIVE, APPLY THE FOLLOW- ING FORMULAS TO OBTAIN THE CORRECTED TORQUE READING. SHORT OPEN END ADAPTER WRENCH TORQUE HANDGRIP DRIVE WRENCH CENTERLINE ADAPTER CENTERLINE (PREDETERMINED) DRIVE CENTERLINE -- SETSCREW- ADAPTER FORMULA TL y L+E EXAMPLE (WITH "E" AS PLUS DIMENSION) T = 135IN-LB y- 135x10 =117.39 Y = UNKNOWN 10+1.5 HOSE CLAMP E = 1.5 IN Y = 117 IN-LB ADAPTER L = 10.0 IN LEGEND T = ACTUAL (DESIRED) TORQUE < )\~Qk) ~Y = APPARENT(INDICATED) TORQUE L = EFFECTIVE LENGTH LEVER <~~~--~~ ~E = EFFECTIVE LENGTH OF EXTENSION ADAPTER OPEN-END WRENCH DRIVE HANDGRIP ADAPTER WRENCH CENTERLINE CENTERLINE DRIVE (PREDETERMINED) CENTERLINE- FLARE NUT WRENCH ADAPTER TORQUE FORMULA WRENCH __ ^ ~~~EXAMPLE (WITH "E" AS MINUS DIMENSION) T = 135 IN-LB y 135 x 10 = 1350 = 158.82 Y = UNKNOWN 10 - .5 SPANNER WRENCH L = 10.0 IN ADAPTER E = 1.5IN Y = 159 IN-LB 4^^.~~~~~h~~~~~~ ssss~5598C200 Torque Wrench and Adapter Formulas Figure 1-4 Sheet 1 Temporary Revision Number 4 1-7 October 1,1997 MODEL 210 & T210 SERIES SERVICE MANUAL EXTERNAL WRENCHING HEAD CORRECT INSTALLATION INSTALL WASHER WITH COUNTERSUNK FACE NEXT TO BOLT HEAD RADIUS INTERNAL WRENCHING HEAD I STANDARD COUNTERSUNK WASHER WASHER INCORRECT INSTALLATION CAUTION: NEVER INSTALL STANDARD WASHER OR COUNTERSUNK WASHER IN REVERSE WHEN USING BOLTS WITH RADIUS UNDER THE HEAD 5598C1004 5598C1004A Washer Installation Close Tolerance Bolts Figure 1-5 Sheet 1 Temporary Revision Number 4 1-8 October 1, 1997 MODEL 210 & T210 SERIES SERVICE MANUAL Table 1-1: Torque Requirements For Steel Bolts, Screws and Nuts (Inch-Pounds) *~~~~~~ ~~~FINE THREADED SERIES FINE THREADED SERIES (SHEAR TYPE NUTS SIZE (TENSION TYPE NUTS) EXCEPT MS17826) MS17826 NUTS Standard Alternate Standard Alternate Standard Alternate Torque Torque Torque Torque Torque Torque 8-36 12to 15 -- 7to9 -- 10-32 20to25 20to28 12to15 12to19 12to15 12to20 1/4-28 50 to 70 50 to 75 30 to 40 30 to 48 30 to 40 30 to 45 5/16-24 100to 140 100to 150 60to85 60to 100 60to80 60to 90 3/8-24 160to 190 160to 260 95to 110 95to 170 95to 110 95to 125 7/16-20 450to500 450to560 270to300 270to390 180to210 180to 225 1/2-20 480 to 690 480 to 730 290 to 410 290 to 500 240 to 280 240 to 300 9/16-18 800to 1000 800to 1070 480to600 480to750 320to370 320to400 5/8-18 1100to 1300 1100to 1600 660to 780 660to 1060 480to 550 480to 600 3/4-16 2300to2500 2300to3350 1300to 1500 1300to2200 880to1010 880to 1100 7/8-14 2500to3000 2500to4650 1500to 1800 1500to2900 1500to 1750 1500to 1900 1-14 3700 to 4500 3700 to 6650 2200 to 3300 2200 to 4400 2200 to 2700 2200 to 3000 1-1/8-12 5000to 7000 5000 to 10000 3000 to 4200 3000 to 6300 3200 to 4200 3200to 5000 1-1/4-12 9000to 11000 9000to 16700 5400to6600 5400to 10000 5900to6400 5900to7000 Fine Thread Tension application nuts include: AN310, AN315, AN345, MS17825, MS20365, MS21044 through MS21048, MS21078, NAS679, NAS1291. FineThread Shearapplication nuts include: AN316, AN320, MS21025, MS21042, MS21043, MS21083, MS21245, NAS1022, S1117. Coarse Thread application nuts include: AN340, MS20341, MS20365, MS35649 Table 1-1: Torque Values (Newton Meters) Nuts, Bolts and Screws (Steel) SIZE OF BOLT, FINE THREADED SERIES NUTOR FINE THREADED SERIES (SHEAR TYPE NUTS SCREW (TENSION TYPE NUTS) EXCEPT MS17826) MS17826 NUTS Standard Alternate Standard Alternate Standard Alternate Torque Torque Torque Torque Torque Torque 8-36 1.4to 1.7 -- 0.8 to 1.0- 10-32 2.3to 2.8 2.3to 3.2 1.4to 1.7 1.4to 2.1 1.4to 1.7 1.4to 2.3 1/4-28 5.6 to 7.9 5.6to8.5 3.4 to4.5 3.4to 5.4 3.4 to4.5 3.4to 5.1 5/16-24 11.3to 15.8 11.3to 16.9 6.8to 9.6 6.8to 11.3 6.8 to 9.0 6.8to 10.2 3/8-24 18.1 to 21.5 18.1 to 29.4 10.7 to 12.4 10.7 to 19.2 10.7 to 12.4 10.7 to 14.1 7/16-20 50.8 to 56-5 50.8 to 63.3 30.5 to 33.9 30.5 to 44.1 20.3 to 23.7 20.3 to 25.4 1/2-20 54.2 to 78.0 54.2 to 82.5 32.8 to 46.3 32.8 to 56.5 27.1 to 31.6 27.1 to 33.9 9/16-18 90.4to 113.0 90.4to 120.9 54.2 to 67.8 54.2 to 84.7 36.2 to 41.8 36.2 to 45.2 5/8-18 124.3 to 146.9 124.3 to 180.8 74.6 to 88.1 74.6to 119.8 54.2 to 62.1 54.2 to 67.8 3/4-16 259.9to 282.5 259.9to 378.5 146.9 to 169.5 146.9 to 248.6 99.4to 114.1 99.4to 124.3 7/8-14 282.5to 339.0 282.5 to 525.4 169.5 to 203.4 169.5to 327.7 169.5to 197.7 169.5to 214.7 1-14 418.0 to 508.4 418.0 to 751.3 248.6 to 372.9 248.6 to 497.1 248.6 to 305.1 248.6 to 339.0 1-1/8-12 564.9 to 790.9 564.9 to 1129.9 339.0 to 474.5 339.0 to 711.8 361.6to 474.5 361.6 to 564.9 1-1/4-12 1016.9to 1242.8 1016.9to 1886.9 610.1 to745.7 610.1 to 1129.9 666.6to723.1 666.6to790.9 Temporary Revision Number 4 1-9 October 1,1997 MODEL 210 & T210 SERIES SERVICE MANUAL Torque Requirements for Hi-Lok Fasteners Use Table 1-2 to determine torque requirements for Hi-Lok fasteners. NOTE: Thistable is used in conjunction with MS21042 self-locking nuts. Table 1-2. Torque Values Hi-Lok Fasteners (Used with MS21042 Self-Locking Nuts) NOMINAL ALLOY STEEL ALLOY STEEL FASTENER 180- 200 KSI 180- 200 KSI DIAMETER (INCH POUNDS) (NEWTON METERS) 6-32 8to 10 0.9to 1.1 8-32 12to 15 1.4to 1.7 10-32 20to 25 2.3to 2.8 1/4-28 50 to 70 5.6 to 7.9 5/16-24 100 to 140 11.3 to 15.8 3/8-24 160to 190 18.1 to 21.5 7/16-20 450 to 500 50.8 to 56.5 1/2-20 480 to 690 54.2 to 78.0 Torque Requirements for Electrical Current Carrying And Airframe Ground Fasteners Use Table 1-3 to determine torque requirements for threaded electrical current carrying fasteners. Torque values shown are clean, nonlubricated parts. Threads shall be free of dust and metal filings. Lubricants, other than on the nut as purchased, shall not be used on any bolt installations unless specified in the applicable chapters of this manual. All threaded electrical current carrying fasteners for relay terminals, shunt terminals, fuse limiter mount block terminals and bus bar attaching hardware shall be torqued per Table 1-3. NOTE: There isno satisfactory method of determining the torque previously applied to a threaded fastener. When retorquing, always back off approximately 1/4 turn or more before reapplying torque. Use Table 1-4to determine torque requirements for threaded fasteners used as airframe electrical ground terminals. Table 1-3. Torque Values Electrical Current Carrying Fasteners FASTENER TORQUE VALUE TORQUE VALUE DIAMETER (INCH POUNDS) (NEWTON METERS) 6-32 8to 12 0.9to 1.4 8-32 13to 17 1.5to 1.9 10-32 20 to 30 2.3 to 3.4 3/16 20 to30 2.3 to3.4 1/4 40 to 60 4.5to 6.8 5/16 80to 100 9.0 to 11.3 3/8 105to 125 11.9to 14.1 1/2 130to 150 14.7 to 16.9 Temporary Revision Number 4 1-10 October 1, 1997 MODEL 210 & T210 SERIES SERVICE MANUAL Table 1-4. Torque Values Airframe Electrical Ground Terminals FASTENER TORQUE VALUE TORQUE VALUE DIAMETER (INCH POUNDS) (NEWTON METERS) 5/16 130 to 150 14.7 to 16.9 3/8 160 to 190 18.1 to 21.5 Torque Requirements for Rigid Tubing and Hoses Use Table 1-5 to determine torque requirements fortubes and hoses. Table 1-5. Tubing/HoseTorque Limits (Inch-Pounds) Flared or Flareless Fitting with Hose Tubing Aluminum or Annealed Stainless Steel Flared or Flareless Fitting with Steel Size O.D. Tubing, and Hose with Aluminum Inserts Tubing, and Hose with Steel Inserts Min Max Min Max -2 1/8 45 55 65 75 -3 3/16 75 85 95 105 -4 1/4 105 115 135 150 -5 5/16 135 145 180 200 -6 3/8 160 175 260 285 -8 1/2 265 290 475 525 -10 5/8 340 375 665 735 -12 3/4 425 470 855 945 -16 1 710 785 1140 1260 Table 1-5. Tubing/HoseTorque Limits (Newton Meters) Flared or Flareless Fitting with Hose Tubing Aluminum or Annealed Stainless Steel Flared or Flareless Fitting with Steel Size O.D. Tubing, and Hose with Aluminum Inserts Tubing, and Hose with Steel Inserts Min Max Min Max -2 1/8 5.1 6.2 7.3 8.5 -3 3/16 8.5 9.6 10.7 11.9 -4 1/4 11.5 13.0 15.3 16.9 -5 5/16 15.3 16.4 20.3 22.6 -6 3/8 18.1 19.8 29.4 32.2 -8 1/2 29.9 32.8 53.7 59.3 -10 5/8 38.4 42.4 75.1 83.0 -12 3/4 48.0 53.1 96.6 106.8 -16 1 80.2 88.7 128.8 142.4 Temporary Revision Number4 1-11 October 1, 1997 MODEL 210 &T210 SERIES SERVICE MANUAL 1-8. SAFETYING - MAINTENANCE PRACTICES Safety Wire Installation (Refer to Figure 1-6). Safety Wire Inconel (Uncoated), Monel (Uncoated). CAUTION Used for general safety wiring purposes. Safety wiring CAUTION is the application of wireto prevent relative movement of structural or other critical components subjected to SCREWS IN CLOSELY SPACED GEOMETRIC vibration, tension, torque, etc. Monel to be used at PATTERNS WHICH SECURE HYDRAULIC OR temperatures up to 700°F (370ºC) and inconel to be AIR SEALS, HOLD HYDRAULIC PRESSURE, OR used at temperatures up to 1500 F (815°C). Identified USED IN CRITICAL AREAS SHOULD USE THE by the color of the finish, monel and inconel color is USED CRITICAL OF SAFETY WIRING natural wire color. DOUBLE TWIST METHOD OF SAFETY WIRING. Copper, is cadmium plated and dyed yellow in accordance Single wire method of safety wiring shall use the largest with FED-STD 595. nominal size wire listed in Table 1-6, which will fit the This wire will be used for shear and seal wiring hole. applications. Shear applications are those where it is The double twist method of safety wiring shall be used as necessary to purposely break or shear the wire to The double twist method of safety wiring shall be used as necessary to purposely break or shear the wire to permit operation or actuation of emergency devices. the common method of safety wiring. It is really one wire Seal applications are those where the wire is used with twisted on itself several times. The single wire method of a lead seal to prevent tampering or use of a device safety wiring may be used in a closely spaced, closed without indication. Identified bythe color of the finish, geometrical pattern (triangle, square, circle, etc.), on copper wire is dyed yellow, parts in electrical systems, and in places that would make Aluminum Alloy (Alclad 5056), is anodized and dyed blue the single wire method more advisable. Closely spaced in accordance with FED-STD 595. shall be considered a maximum of two inches between centers. This wire will be used exclusively for safety wiring magnesium parts. Use single wire method for shear and seal wiring NOTE application. Make sure the wire is installed so that it can be easily broken when required in an emergency Surface treatments which obscure visual identification situation. For securing emergency devices where it is of safety wire is prohibited. necessary to break the wire quickly, use copper only. Inconel or monel, wire can be substituted for same Safety wiring by the double twist method shall be done as diameter and length of carbon steel or corrosion resistant follows: wire. Wires are visually identifiable by their colors: natural for One end of the safety wire shall be inserted through inconel and monel, yellow for copper, and blue for one set of safety wire holes in the bolt head. The other aluminum. end of the safety wire shall preferably be looped firmly around the head to the next set of safety wire holes in Cotter Pin. the same unit and inserted through this set of safety The selection of material shall be in accordance with wire holes. The "otherend" may go overthe head when temperature, atmosphere and service limitations, the clearances around the head are obstructed by Safety Wire adjacent parts. The size of the safety wire shall be in accordance with The strands, while taut, shall be twisted until the the requirements of Table 1-6. twisted part is just short of the nearest safety wire hole in the next unit. The twisted portion shall be within 1/8 0.032 inch diameter safety wire is for general inch of the holes in each unit. The actual number of purpose use; however, 0.020 inch diameter safety twists will depend upon the wire diameter, with wire may be used on arts having a nominal hole smaller diameters being able to have more twists than nominal te of less than between 0.045 parts having a larger diameters. The twisting shall keep the wire taut nominal hole diameter between 0.045 and 0.062 inch with spacing between parts of less than two without over stressing or allowing it to become nicked, inches, or on closely spaced screws and bolts of 0.25 kinked or mutilated. Abrasions from commercially inch diameter and smaller. available twist pliers shall be acceptable. 0.020 inch diameter copper wire shall be used for shear and seal wire applications. When employing the single wire method of locking, the largest nominal size wire for the applicable material or part in which the hole will accommodateshallbe used. Temporary Revision Number 4 1-12 October 1, 1997 MODEL 210 & T210 SERIES SERVICE MANUAL STEP 1. INSERT WIRE THROUGH BOLT A AND _BEND AROUND BOLT (IF NECESSARY, BEND WIRE 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 AGAINST PART. NOTE: RIGHT THREADED PARTS SHOWN: REVERSE DIRECTIONS FOR LEFT PARTS. BOLT B CLOCKWISE DOUBLE-WIRE SAFETYING COUNTER- CLOCKWISE ^ ^^CLOCKWISE COUNTER- ^ CLOCKWISE ~ ^-CLOCKWISE MULTIPLE FASTENER APPLICATION DOUBLE TWIST - MULTIPLE DOUBLE-TWIST SAFETYING HOLE METHOD. SINGLE HOLE METHOD 5598C2001 5599C2001 6598C1029 Lockwire Safetying Figure 1-6, Sheet 1 Temporary Revision Number 4 1-13 October 1,1997 MODEL 210 & T210 SERIES SERVICE MANUAL EXTERNAL SNAP RING SINGLE-WIRE METHOD BOLTS IN CLOSELY SPACED, CLOSED GEOMETRICAL PATTERN, SINGLE WIRE METHOD SINGLE FASTENER APPLICATION DOUBLE-TWIST METHOD SMALL SCREWS IN CLOSELY SPACED, CLOSED GEOMETRICAL PATTERN, SINGLE WIRE METHOD NOTE: RIGHT THREADED PARTS SHOWN. REVERSE DIRECTION FOR LEFT THREADS 5598C1 003 5598C1024 5598C1024 _^^~~~~~~~~~~~ ~~5598C1024 Lockwire Safetying Figure 1-6, Sheet 2 Temporary Revision Number 4 1-14 October 1, 1997 MODEL 210 & T210 SERIES SERVICE MANUAL Lockwire Safetying Figure 1-6, Sheet 3 Temporary Revision Number 4 1-15 October 1, 1997 October 1, 1997 MODEL 210 & T210 SERIES SERVICE MANUAL Table 1-6. Safety Wire MATERIAL SIZE AND NUMBER (MS20995-XXX) 0.015 0.020 0.032 0.040 0.041 0.047 0.051 0.091 Ni-Cu Alloy _ NC20 NC32 NC40 _ NC51 NC91 (Monel) Ni-Cr-Fe Alloy _ N20 N32 N40 N51 N91 (Inconel) Carbon Steel _ F20 F32 _ F41 F47 F91 Corrosion Resistant C15 C20 C32 _C41 C47 C91 Steel Aluminum Alloy _ AB20 AB32 _ AB41 AB47 _AB91 (Blue) Copper (Yellow) CY15 CY20 The wire shall be twisted to form a pigtail of 3 to 5 Usage twists after wiring the last unit. The excess wire shall A pigtail of 0.25 to 0.50 inch (3 to 5 twists) shall be be cut off. The pigtail shall be bent toward the part to made at the end of the wiring. This pigtail shall be bent prevent it from becoming a snag. Safety wiring back or under to prevent it from becoming a snag. multiple groups by the double twist double hole method shall be the same as the previous double twist Safety wire shall be new upon each application. single hole method except the twist direction between When castellated nuts are to be secured with safety subsequent fasteners may be clockwise or wire, tighten the nut to the low side of the selected counterclockwise. torque range, unless otherwise specified, and if Spacing necessary, continue tightening until a slot aligns with the hole. When safety wiring widely spaced multiple groups by the double twist method, three units shall be the In blind tapped hole applications of bolts or castellated maximum number in a series. nuts on studs, the safety wiring shall be as described in these instructions. When safety wiring closely spaced multiple groups, the number of units that can be safety wired by a Hollow head bolts are safetied in the manner twenty four inch length of wire shall be the maximum prescribed for regular bolts. number in a series. Drain plugs and pet cocks may be safetied to a bolt, nut Widely spaced multiple groups shall mean those in or other part having a free lock hole in accordance with which the fastenings are from four to six inches apart. the instructions described in this text. Safety wiring shall not be used to secure fasteners or External snap rings may be locked, if necessary, in fittings which are spaced more than six inches apart, accordance with the general locking principles as unless the points are provided on adjacent parts to described and illustrated. Internal snap rings shall not shorten the span of the safety wire to less than six be safety wired. inches. When safety wiring is required on electrical connectors Tension which use threaded coupling rings, or on plugs which Parts shall be safety wired in such a manner that the employ screws or rings to fasten the individualparts of safety wire shall be put in tension when the part tends the plug together, they shall be safety wired with 0.020 to loosen. The safety wire should always be installed inch diameter wire in accordance with the safety and twisted so that the loop around the head stays wiring principles as described and illustrated. It is down and does not tend to come up over the bolt head preferable to safety wire all electrical connectors and leave a slack loop. individually. Do not safety wire one connector to another unless it is necessary to do so. NOTE ~~~~~~NOTE ~Drilled head bolts and screws need not be safety wired This does not necessarily apply to castellated nuts if installed into self-locking nuts or installed with lock when the slot is close to the top of the nut, the wire washers. Castellated nuts with cotter pins or safety will be more secure if it is made to pass along the wire are preferred on bolts or studs with drilled shanks side ofthe stud. but self-locking nuts are permissible within the limitations of MS33588. Care shall be exercised when installing safety wire to ensure that it is tight but not over stressed. Temporary Revision Number 4 1-16 October 1, 1997 MODEL 210 & T210 SERIES SERVICE MANUAL Safetying Turnbuckles Larger assemblies, such as hydraulic cylinder heads Safetying Turnbuckles for which safety wiring is required but not specified, Use of Safety Wire. shall be safety wired as described in these instructions. Some turnbuckles are secured using safety wire. These Safety wire shall not be used to secure nor shall safety safetying procedures are detailed and illustrated in wire be dependent upon fracture as the basis for Federal Publication AC 43-13.1A, Safety Methods For operation of emergency devices such as handles, switches, guards covering handles, etc., that operate turnbuckles. emergency mechanism such as emergency exits, fire Use of Locking Clips extinguishers, emergency cabin pressure release, emergency landing gear release and the like. General instruction for the selection and application of However, where existing structural equipment or locking clips(RefertoFigures 1-8and 1-9). safety of flight emergency devices require shear wire to secure equipment while not in use, but which are Prior to safetying, both threaded terminals should be dependent upon shearing or breaking of the safety screwed an equal distance into the turnbuckle barrel, wireforsuccessful emergency operation of equipment, and should be screwed in, at a minimum, so no more particular care shall be exercised to that wiring under than three threads of any terminal are exposed outside these circumstances shall not prevent emergency the body operations of these devices. Cotter Pin Installation After the turnbuckle has been adjusted to its locking position, with the groove on terminals and slot General instruction for the selection and application of indicator notch on barrel aligned, insert the end of the cotter pins (Referto Figure 1-7). locking clip into the terminal and barrel until the "U" Select cotter pin material in accordance with curved end of the locking clip is over the hole in the temperature, atmosphere and service limitations. center of the barrel. Cotter pins shall be new upon each application. a. Press the locking clip into the hole to its full extent. When nuts areto be secured to thefastenerwith cotter b. The curved end of the locking clip will latch in the pins, tighten the nut to the low side (minimum) of the hole in the barrel. applicable specified or selected torque range, unless otherwise specified, and if necessary, continue c. To check proper seating of locking clip, attempt to tightening until the slot aligns with the hole. In no remove pressed "U" end from barrel hole with case shall the high side (maximum) torque range be fingers only. exceeded. NOTE Castellated nuts mounted on bolts may be safetied withcotterpinsorsafetywire.Thepreferredmethodis Do not use a tool as the locking clip could be with the cotter pin. An alternate method where the distorted. cotter pin is mounted normal to the axis of the bolt may be used where the cotter pin in the preferred Locking clips are for one time use only and should not method is apt to become a snag. be reused. In the event of more than 50 percent of the cotter pin Both locking clips may be inserted in the same hole of diameter is above the nut castellation, a washer the turnbuckle barrel or in opposite holes of the should be used under the nut or a shorter fastener turnbuckle barrel. should be used. A maximum of two washers may be permitted under a nut. The largest nominal diameter cotter pin listed in MS24665, which the hole and slots will accommodate, shall be used; but in no application to a nut, bolt or screw shall the pin size be less than the sizes described in Figure 1-7. Install the cotter pin with the head firmly in the slot of the nut with the axis of the eye at right angles to the bolt shank, and bend prongs so that the head and upper prong are firmly seated against the bolt. In the pin applications, install the cotter pin with the axis of the eye parallel to the shank of the clevis pin or rod end. Bend the prongs around the shank of the pin or rod end. Cadmium plated cotter pins shall not be used in applications bringing them in contact with fuel, hydraulic fluid or synthetic lubricants. Temporary Revision Number 4 1-17 October 1, 1997 MODEL 210 & T210 SERIES SERVICE MANUAL TO PROVIDE CLEARANCE PRONG MAY BE CUT HERE CASTELLATED NUT ON BOLT CASTELLATED NUT ON BOLT ALTERNATE METHOD PREFERRED METHOD TANGENT MINIMUM TO PIN PIN SIZE MAXIMUM THREAD SIZE (INCH) COTTER PIN 6 0.028 LENGTH 8 0.044 \ ~ 60 DEGREES 10 0.044 1/4 0.044 5/16 0.044 60 DEGREES 3/8 0.072 7/16 0.072 1/2 0.072 MINIMUM COTTER PIN 9/16 0/086 9/16 0.086 LENGTH 5/8 0.086 3/4 0.086 7/8 0.086 1 0.086 11/8 0.116 1 1/4 0.116 1 3/8 0.116 1 1/2 0.116 PIN APPLICATION 5598C1025 5598C1025 5598C1025 _~~~~~~~~~~~ ~5598C1025 Cotter Pin Safetying Figure 1-7, Sheet 1 Temporary Revision Number 4 1-18 October 1,1997 MODEL 210 &T210 SERIES SERVICE MANUAL STRAIGHT END * ~HOOK SHOULDER END LOOP HOOK LIP HOOK LOOP n PULL FOR INSPECTION PULL FOR INSPECTION 55982002 Safetying Tumbuckle Assemblies Figure 1-8, Sheet 1 Temporary Revision Number 4 1-19 October 1, 1997 MODEL 210 & T210 SERIES SERVICE MANUAL TURNBUCKLE LOCKING CLIP TURNBUCKLE EYE CLEVIS MS21256 CABLE THIMBLE TURNBUCKLE BARREL LOCKING CLIP MS21251 MS21 256 TYPICAL TURNBUCKLE ASSEMBLY SWAGED TERMINAL METHOD OF ASSEMBLING LOCKING CLIPS, TURNBUCKLE BARREL AND TERMINALS LOCKING CLIP TURNBUCKLE NOMINAL THREAD MS21256 BODY CABLE DIA. UNF-3 (NOTE 1) MS21251 1/16 No. 6-40 -1 -2S 3/32 No. 10-32 -1 -3s -2 -3L -1 -4S 1/8 -2 -4L 5/32 1/4-28 -1 -5S -2 -5L -1 -6S 3/16 5/16-24 -2 -6L 7/32 -2 -7L 1/4 3/8-24 -2 -8L 9/32 7/16-20 -3 -9L 5/16 1/2-20 -3 -10L NOTE 1: TWO LOCKING CLIPS REQUIRED FOR EACH TURNBUCKLE. 5598C1023 5598C1023 Safetying Turnbuckle Assemblies Figure 1-9, Sheet 1 Temporary Revision Number 4 1-20 October 1,1997 MODEL 210 & T210 SERIES SERVICE MANUAL 1-9. CONTROL CABLE WIRE BREAKAGE AND Wire breakage criteria for cables in flap, aileron, 1-9. CONTROL CABLE WIRE BREAKAGE AND CORROSION LIMITATIONS rudder, and elevator systems are as follows: . of. Control^ Cables.~ ~Individual broken wires at random locations are Examination of Control Cables. acceptable in primary and secondary control cables Control cable assemblies are subject to a variety of when there are no more than six broken wires in environmental conditions and forms of deterioration. any given ten-inch cable length. Some deterioration, such as wire or strand breakage, is Corrosion easy to recognize. Other deterioration, such as internal corrosion or cable distortion, is harder to identify. The Carefully examine any cable for corrosion that has a following information will aid in detecting these cable broken wire in a section not in contact with wear- conditions. producing airframe components, such as pulleys, Broken Wire Examination (Referto Figure 1-9). remove and bend cable to properly inspect it for Examine cables for broken wires by passing a cloth internal strand corrosion, as this condition is usually along length of cable. This will detect broken wires, if not evident on outer surface of cable. Replace cable if cloth snags on cable. Critical areas for wire breakage internal corrosion is found. If a cable has been wiped are those sections of cable which pass through clean of its corrosion-preventive lubricant and metal- fairleads, across rub blocks, and around pulleys. If no brightened, the cable shall be examined closely for snags are found, then no further inspection is required. corrosion. If snags are found or broken wires are suspected, then a more detailed inspection is necessary, which requires that the cable be bent in a loop to confirm broken wires. Loosen or remove cable to allow itto be bent in a loop as shown. While rotating cable, inspect bent area for broken wires. Temporary Revision Number 4 1-21 October 1, 1997 MODEL 210 & T210 SERIES SERVICE MANUAL BROKEN WIRE UNDETECTED BY WIPING CLOTH ALONG CABLE BROKEN WIRE DETECTED VISUALLY WHEN CABLE WAS REMOVED AND BENT DO NOT BEND INTO LOOP SMALLER THAN 50 CABLE DIAMETERS NORMAL TECHNIQUE FOR BENDING CABLE AND CHECKING FOR BROKEN WIRES Cable Broken Wire Examination Figure 1-9 Sheet 1 Temporary Revision Number 4 1-22 October 1, 1997 MODEL 210 & T210 SERIES SERVICE MANUAL SECTION 2 GROUND HANDLING, SERVICING, CLEANING, LUBRICATION AND INSPECTION WARNING When performing any inspection or maintenance that requires turning on the master switch, installing a battery, or pulling the propeller through by hand, treat the propeller as if the ignition switch were ON. Do not stand nor allow anyone else to stand, within the arc of the propeller, since a loose or broken wire or a component malfunction could cause the propeller to rotate. Page No. TABLE OF CONTENTS Aerofiche/Manual GROUND HANDLING ........ 1A21/2-2 Nose Gear Shimmy Dampener . . . 1B6/2-11 Towing ........... . 1A21/2-2 Hydraulic Brake Systems ... .1B6/2-11 Hoisting ...... ..... 1A21/2-2 Landing Gear Hydraulic Retraction Jacking ............ 1A21/2-2 System ....... 1B6/2-11 Leveling ........ . .. 1A21/2-2 Hydraulic Fluid Sampling and Weighing .......... A21/2-2 Contamination Check ...... 1B7/2-12 Parking .... . .. . 1A22/2-3 Oxygen System. . . . . ..... 1B7/2-12 Tie-Down .......... 1A22/2-3 Face Masks ......... 1. . B7/2-12 Flyable Storage .... . . 1A22/2-3 CLEANING .. . . . . . . . . 1B7/2-12 Returning Aircraft to Service . .. 1A22/2-3 General Description .. . .... 1B7/2-12 Temporary Storage . . . .1A22/2-3 Upholstery and Interior ... .. .1B7/2-12 Inspection During Storage .... . 1B1/2-6 Plastic Trim ....... ...1B7/2-12 Returning Aircraft to Service . . . B1/2-6 Windshield and Windows. .. . .1B7/2-12 Indefinite Storage ... . .. 1B1/2-6 Aluminum Surfaces . .. . .1B7/2-12 Inspection During Storage ..... 1B2/2-7 Painted Surfaces ......... 1B7/2-12 Returning Aircraft to Service .. . 1B2/2-7 Engine and Engine Compartment . . 1B8/2-13 SERVICING . ....... 1B3/2-8 Propeller ........ 1B9/2-14 Description ..... 1B3/2-8 Wheels ............ 1B9/2-14 Fuel Bays ... .... 1B3/2-8 LUBRICATION . ...... 1B9/2-14. Fuel Additives for Cold Weather General Description ..... .1B9/2-14 Operation . ..................... 1B3/2-8 Nose Gear Torque Links ..... 1B9/2-14 Fuel Drains . ............. 1B4/2-9 Tachometer Drive Shaft .. .. .1B9/2-14 Engine Oil .... ................. 1B4/2-9 Wheel Bearing Lubrication- . · . 1B9/2-14 Engine Induction Air Filter ....... 1B4/2-9 Wing Flap Actuator........ 1B9/2-14 Vacuum System Air Filter ........ 1B5/2-10 Rod End Bearings .. .. .. 1B9/2-14 Battery ......... ............... 1B5/2-10 INSPECTION ........... 1B18/2-23 Tires . ................. 1B6/2.11 Nose Gear Strut ............. 1B6/2-11 Revision 3 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. CAUTION I 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 the jack. 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 thetwo 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- Oil (Military Specification MIL-C-6529, cipally on local conditions. As a general precaution, Type II). This engine oil is a blend of avi- it is wise to set the parking brake or chock the ation grade straight mineral oil and a corro- wheels, and install the control lock. In severe sion preventive compound. This engine oil weather, and high wind conditions, tie down the air- should be used for the first 25 hours of engine craft as outlined in paragraph 2-6 if a hangar is not operation. In the event it is necessary to add available. oil during the first 25 hours of operation use only aviation grade straight mineral oil of the 2-6. TIE-DOWN. When mooring the aircraft in the correct viscosity. open, head into the wind if possible. Secure control surfaces with the internal control lock and set brakes. During the 30 day non-operational storage or the first 25 hours of intermittent engine operation, every sev- CAUTION enth day the propeller shall be rotated by hand without running the engine. After rotating the engine five revo- Do not set parking brakes when they are lutions, stop the propeller 45º to 90* from the position overheated or during cold weather when it was in. If the aircraft is stored outside, tie-down accumulated moisture may freeze them. in accordance with paragraph 2-8. In addition, the pitot tube, static air vents, air vents, openings in the a. Tie ropes, cables or chains to the wing tie-down engine cowling, and other similar openings shall have fittings located mid-wing in line with the outboard protective covers installed to prevent entry of foreign edge of the flaps. Secure the opposite ends of ropes material. If at the end of thirty (30) days aircraft cables or chains to ground anchors. will not be removed from storage, the engine shall b. Secure a tie-down rope (no chains or cables) be started and run. The preferred method would be to upper trunnion of the nose gear, and secure oppo- to fly the aircraft for thirty (30) minutes, and up to, site end of rope to ground anchor. but not exceeding normal oil and cylinder tempera- c. Secure the middle of a rope to the tail tie-down tures. ring. Pull each end of rope away at a 45-degree angle and secure to ground anchors at each side of CAUTION tail. d. Secure control lock on pilot control column. If Excessive ground operation shall be avoided. control lock is not available, tie pilot control wheel back with front seat belt. 2-8. RETURNING AIRCRAFT TO SERVICE. After e. These aircraft are equipped with a spring-loaded flyable storage, returning the aircraft to service is steering bungee which affords protection against nor- accomplished by performing a thorough pre-flight in- mal wind gusts. However, if extremely high wind spection. At the end of the first 25 hours of engine gusts are anticipated, additional locks may be install- operation, drain engine oil and clean oil pressure ed. screen (or change external oil filter element). Ser- vice engine with correct grade and quantity of oil. 2-7. FLYABLE STORAGE. Flyable storage is de- Refer to figure 2-4 and paragraph 2-20 for correct fined as a maximum of 30 days non-operational stor- grade of engine oil. age and/or the first 25 hours of intermittent engine operation. 2-9. TEMPORARY STORAGE. Temporary storage is defined as aircraft in a non-operational status for NOTE a maximum of 90 days. The aircraft is constructed The aircraft is delivered from Cessna with a Corrosion preventive Aircraft Engine Revision 2 2-3 MODEL 210 & T210 SERIES SERVICE MANUAL 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 landin 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 of corrosion-resistant alclad aluminum, which will 1. Apply preservative oil to the engin interior by last indefinitely under normal conditions if kept spraying approximately two ounces of the preserva- clean. However, these alloys are subject to oxida- tive oil through the oil filler tube. tion. The first indication of corrosion on unpainted m. Seal all engine openings exposed to the atmos- surfaces is in the form of white deposits or spots. phere, using suitable plugs or non-hygroscopic tape. On painted surfaces, the paint is discolored or blis- Attach a red streamer at each point that a plug or tered. Storage in a dry hangar is essential to good tape is installed. preservation and should be procured, if possible. n. If the aircraft is to be stored outside, perform Varying conditions will alter the measures of preser- the procedures outlined in paragraph 2-6. In addi- vation, but under normal conditions in a dry hangar, tion, the pitot tube, static source vents, air vents, and for storage periods not to exceed 90 days, the openings in the engine cowling, and other similar following methods of treatment are suggested. openings should have protective covers installed to a. Fill fuel bays with correct grade of gasoline. prevent entry of foreign material. b. Clean and wax aircraft thoroughly. o. Attach a warning placard to the propeller to the c. Clean any oil or grease from tires, and coat effect that the propeller shall not be moved while the tires with a tire preservative. Cover tires to pro- engine is in storage. tect against grease or oil. d. Either block up fuselage to relieve pressure on 2-10. INSPECTION DURING STORAGE. tires or rotate wheels every 30 days to prevent flat a. Inspect airframe for corrosion at least once a spotting the tires, month. Remove dust collections as frequently as e. Lubricate all airframe items and seal or cover possible. Clean and wax aircraft as required. all openings which could allow moisture and/or dust b. Inspect the interior of at least one cylinder to enter. through the spark plug hole for corrosion at least once each month. NOTE NOTE The aircraft battery serial number is recorded in the aircraft equipment list. To assure ac- Do not move crankshaft when inspecting curate warranty records, the battery should interior of cylinder for corrosion. be reinstalled in the same aircraft from which it was removed. If the battery is returned to c. If at the end of the 90 day period, the aircraft service in a different aircraft, appropriate is to be continued in non-operational storage, repeat record changes must be made and notification the procedural steps "g" thru "o" of paragraph 2-9. sent to the Cessna Claims Department. RETURNING AIRCRAFT SERVICE. After 2-11. RETURNING AIRCRAFT TO SERVICE. After f. Remove battery and store in a cool, dry place; temporary storage, use the following procedure to service battery periodically and charge as required. return the aircraft to service. a. Remove aircraft from blocks. Check tires for NOTE proper inflation. b. Check and install battery. An engine treated in accordance with the fol- c. Check that oil sump has proper grade and quan- lowing may be considered being protected tity of engine oil. against normal atmospheric corrosion for a d. Service induction air filter and remove warning period not to exceed 90 days. placard from propeller. e. Remove- materials used to-cover openings. g. Disconnect spark plug leads and remove upper f. Remove, clean and gap spark plugs. and lower spark plugs from each cylinder. g. While spark plugs are removed, rotate propeller several revolutions to clear excess rust preventive NOTE oil from cylinders. h. Install spark plugs and torque to values listed The preservative oil must be Lubricating in Section 12 or 12A of this manual. Oil-Contact and Volatile, Corrosion In- i. Check fuel strainer. Remove and clean filter hibited, MIL-L-46002, Grade 1, or equiva- screen, if necessary. Check fuel bays and fuel lines lent. for moisture and sediment. Drain enough fuel to eliminate moisture and sediment. j. Perform a thorough pre-flight inspection, then h. Using a portable pressure sprayer, spray pre- start and warm-up engine. servative oil through the upper spark plug hole of each cylinder with the piston in a down position. Ro- 2-12. INDEFINITE STORAGE. Indefinite storage is tate crankshaft as each pair of cylinders is sprayed. defined as aircraft in a non-operational status for an i. After completing step "h, " rotate crankshaft so indefinite period of time. Engines treated in accor- that no piston is at a top position. dance with the following may be considered protected j. Again, spray each cylinder without moving the against normal atmospheric corrosion, provided the crankshaft, to thoroughly cover all interior surfaces procedures outlined in paragraph 2-13 are performed of the cylinder above the piston. at the intervals specified. k. Install spark plugs and connect spark plug leads. 2-6 MODEL 210 & T210 SERIES SERVICE MANUAL a. Operate engine until oil temperature reaches NOTE normal operating range. Drain engine oil sump and reinstall & safety drain plug. Attach a red streamer to each place plugs or b. Fill oil sump to normal operating capacity with tape is installed. Either attach red streamers corrosion preventive mixture which has been thor- outside of the sealed area with tape or to the oughly mixed. inside of the sealed area with safety wire to prevent wicking of moisture into the sealed NOTE area. Corrosion preventive mixture consists of one n. Drain corrosion-preventive mixture from engine part compound MIL-C-6529, Type I. mixed sump and reinstall drain plug. with three parts new lubricating oil of the grade recommended for service. NOTE c. Immediately after filling the oil sump with cor- The corrosion-preventive mixture is harmful rosion preventive mixture. fly the aircraft for a to paint and should be wiped from painted sur- period of time not to exceed a maximum of 30 min- faces immediately. utes. d. With engine operating at 1200 to 1500 rpm and o. Attach a warning placard on the throttle control induction air filter removed, spray corrosion pre- knob, to the effect that the engine contains no lubri- ventive mixt-re into induction airbox, at the rate of cating oil. Placard the propeller to the effect that it one-half gallon per minute, until heavy smoke comes should not be moved while the engine is in storage. from exhaust stack, then increase the spray until the p. Prepare airframe for storage as outlined in engine is stopped. paragraph 2-9 thru step "f." CAUTION NOTE Injecting corrosion-preventive mixture too As an altermate method of indefinite storage, fast can cause a hydrostatic lock. the aircraft may be serviced in accordance with paragraph 2-9 providing the aircraft is e. Do not rotate propeller after completing step run up at maximun intervals of 90 days and "d. " then reserviced per paragraph 2-9. f. Remove all spark plugs and spray corrosion- preventive mixture, which has been pre-heated 2-13. INSPECTION DURING STORAGE. Aircraft in (221 ° to 2500F,) into all spark plug holes to thor- an indefinite storage shall be inspected as follows: oughly cover interior surfaces of cylinders. a. Inspect cylinder protex plugs each 7 days. b. Change protex plugs if their color indicates an NOTE unsafe condition. c. If the dehydrator plugs have changed color in one To thoroughly cover all surfaces of the cylin- half of the cylinders, all desiccant material in the der interior, move the nozzle of the spray gun engine shall be replaced with new material. from the top to the bottom of the cylinder. If d. Every 6 months respray the cylinder interiors by accident the propeller is rotated following with corrosion-preventive mixture and replace all this spraying, respray the cylinders to insure desiccant and protex plugs. an unbroken coverage on all surfaces. NOTE g. Install lower spark plugs or install solid plugs, Before spraying, inspect the interior of one and install dehydrator plugs in upper spark plug cylinder for corrosion through the spark holes. Be sure that dehydrator plugs are blue in plug hole and remove at least one rocker box color when installed. cover and inspect the valve mechanism. h. Cover spark plug lead terminals with shipping plugs (AN4060-1) or other suitable covers. 2-14. RETURNING AIRCRAFT TO SERVICE. i. With throttle in full open position, place a bag After indefinite storage, use the following procedure of desiccant in the induction air intake and seal to return the aircraft to service. opening with moisture resistant paper and tape. a. Remove aircraft from blocks and check tires for j. Place a bag of desiccant in the exhaust tail- correct inflation. Check for correct nose gear strut pipe(s) and seal openings with moisture resistant inflation tape. b. Check battery and install. k. Seal cold air inlet to the heater muff with mois- c. Remove all materials used o seal and cover ture resistant tape. openings 1. Seal engine breather by inserting a protex plug d. Remove warning placards posted at throttle and in the breather hose and clamping in place. propeller m. Seal all other engine openings exposed to atmos- Remove and clean engine oil screen. then re- phere using suitable plugs or non-hygroscopic tape. install and safety. On aircraft that are equipped with an external oil filter. install new filter element. 2-7 MODEL 210 & T210 SERIES SERVICE MANUAL f. Remove oil sump drain plug and drain sump. While these conditions are quite rare and will not Install and safety drain plug and fill engine with oil. normally pose a problem to owners and operators, they do exist in certain areas of the world and con- NOTE sequently must be dealt with when encountered. The corrosion-preventive mixture will mix Therefore, to alleviate the possibility of fuel icing with the engine lubrication oil, so flushing occurring under these unusual conditions it is per- the oil system is not necessary. Draining missible to add isopropyl alcohol or ethyelene glycol the oil sump will remove enough of the monomethyl ether (EGME) compound to the fuel sup- corrosion-preventive mixture. ply. See Figure 2-3 for fuel additive mixing ratio. g. Service and install the induction air filter. CAUTION h. Remove dehydrator plugs and spark plugs or plugs installed in spark plug holes and rotate Diethylene glycol monomethyl ether propeller by hand several revolutions to clear (DiEGME) has NOT been approved by engine corrosion-preventive mixture from cylinders. manufacturer for use with propeller single i. Clean. gap and install spark plugs. Torque engine aircraft plugs to value listed in Section 12 or 12A. j. Check fuel strainer. Remove and clean filter The introduction of alcohol or EGME compound into screen. Check fuel tanks and fuel lines for the fuel provides two distinct effects: 1) it absorbs moisture and sediment, and drain enough fuel to the dissolved water from the gasoline and 2) alcohol eliminate. has a freezing temperature depressant effect. k. Perform a thorough pre-flight inspection. then start and warm-up engine. Alcohol, if used, is to be blended with the fuel in a 1. Thoroughly clean aircraft and flight test concentration of 1% by volume. Concentrations aircraft. greater than 1% are not recommended since they can be detrimental to fuel tank materials. 2-15. DELETED. The manner in which the alcohol is added to the fuel 2-16. SERVICING. is significant because alcohol is most effective when it is completely dissolved in the fuel. To insure 2-17. DESCRIPTION. Servicing requirements are proper mixing the following is recommended. shown in figure 2-4. The following paragraphs supplement this figure by adding details not 1. For best results the alcohol should be added included in the figure. during the fueling operation by pouring the alcohol directly on the fuel stream issuing from the fuel 2-18. FUEL BAYS. An area of each wing is sealed nozzle. to form an integral fuel bay. Recommended fuel 2. An alternate method that may be used is to premix the complete alcohol dosage with some fuel grades are listed in figure 2-4. Fuel bays should be in a separate clean containerl dosage with some fuel in a separate clean container (approximately 2-3 filled immediately after flight to lessen condensation gallon capacity) and then transfer this mixture to the in bays and lines. -~~~in bays and lines. ^tank prior to the fuel operation. NOTE Any high quality isopropyl alcohol may be used, such Beginning with Serial 21064536, before re- as: Anti-icing fluid (MIL-F-5566) or Isopropyl alco- fueling or when the aircraft is parked on a hol (Federal Specification TT-I-735a). slope, place the fuel selector handle in the LEFT ON or RIGHT ON position, whichever Ethylene glycol monomethyl ether (EGME) compound corresponds to the low wing. This will mini- in compliance with MIL-1-27686 or Phillips PFA- mize crossfeeding from the fuller bay and . 55MB, if used, must be carefully mixed with the fuel reduce fuel seepage from the wing vents. in concentrations not to exceed 0.15o by volume. 2-18A. USE OF FUEL ADDITIVES FOR COLD ICAUTION1 WEATHER OPERATION. Strict adherence to recom- mended preflight draining instructions will eliminate Mixing of the EGiME compound with the fuel any free water accumulations from the tank sumps. is extremely important because concentra- While small amounts of water may still remain in tion in excess of that recommended (0.15 solution in the gasoine, it will normally be consumed percent by volume maximum) will result in and go unnoticed in the operation of the engine. detrimental affects to the fuel tanks, such as deterioration of protective primer and One exception co this can be encountered when oper- sealants and damage to O-rings and seals acing under the combined effect of: 1) use of certain in the fuel system and engine components. fuels, with 2) high humidity conditions on the ground Use only blending equipment that is recom- 3; followed by flight at high altitude and low tempera- mended by the manufacturer to obtain proper ture. Under these unusual conditions small amounts proportioning. of water in solution can precipitate from the fuel stream and freeze in sufficient quantities to induce Do not allow the concentrated EGIME com- partial icing of the engine fuel system. pound to come in contact with the airplane finish or fuel cell as damage can result. 2-8 Revision 3 MODEL 210 & T210 SERIES SERVICE MANUAL MODEL 210 & T210 SERIES SERVICE MANUAL times. A new filter should be installed When changing engine oil, remove and clean oil pressure screen or install a new filter element on after using 500 hours of engine operating aircraft equipped with an external oil filter. To time or oneyear, whichever should occur drain oil, proceed as follows: first. However, a new filter should be installed anytime the existing filter is a. Operate engine until oil temperature is at normal operating temperature. damaged. A damaged filter may have b. Remove oil drain plug from engine sump and sharp or broken edges in the filtering allow oil to drain into a container. panels which would allow unfiltered air c. After engine oil has drained, install and safety to enter the induction, system. Any filter drain plug. that appears doubtful, shall have a new d. Remove and clean oil pressure screen or filter installed in its place. change external oil filter element. e. Service engine with correct quantity and d. After washing, rinse filter with clear water viscosity of aviation grade engine oil. until rinse water draining from filter is clear. Allow water to drain from filter and dry with NOTE compressed air (not over 100 psi). Refer to inspection charts for intervals NOTE for changing engine oil and external filter elements. Refer to figure 2-4 for correct The filtering panels of the filter may viscosities and capacities of aviation become distorted when wet, but they will grade engine oil. return to their original shape when dry. 2-21. ENGINE INDUCTION AIR FILTER. The e. Be sure airbox is clean, and inspect filter. If induction air filter keeps dust and dirt from filter is damaged, a new filter should be installed. entering the induction system. The value of f. Install filter at entrance to airbox with gasket maintaining the air filter in a good clean condition on aft face of filter frame and with flow arrows on can never be over-stressed. More engine wear is filter frame pointed in the correct direction. caused through the use of a dirty or damaged air filter than is generally believed. The frequency with which the filter should be removed, inspected 2-22. VACUUM SYSTEM AIR FILTER. The vacuum and cleaned will be determined primarily by system central air filter keeps dust and dirt from aircraft operating conditions. A good general rule, entering the vacuum operated instruments. Inspect however. is to remove, inspect and clean the filter filter every 200 hours for damage. Replace filter at least every 50 hours of engine operating time, when damaged, every 500 hours of operation or when- and more frequently if warranted by operating ever it becomes sufficiently clogged to cause suction conditions. Under extremely dusty conditions, daily gage readings to drop below 4. 6 in Hg. Do not oper- servicing of the filter is recommended. To service ate the vacuum system with the filter removed or a the induction filter, proceed as follows: a. Remove filter from aircraft. vacuum line disconnected as particles of dust or other foreign matter may enter the system and damage the vacuum-operated instruments. NOTE Use care to prevent damage to filter element when cleaning filter with Excessive smoking will cause premature compressed air. filter clogging. b. Clean filter by blowing with compressed air (not over 100 psi) from direction opposite of normal air flow. Arrows on filter case indicate direction of normal air flow. 2-23. BATTERY. Battery servicing involves CAUTION adding distilled water to maintain the electrolyte even with the horizontal baffle plate or split ring at Do not use solvent or cleaning fluids to the bottom of the filler holes, checking cable wash filter. Use only a water and connections, and neutralizing and cleaning off any household detergent solutio