1977 Thru 1986 Model 182 & T182 Series Service Manual

2-21 thru 2-23 ................. 0 5-26 ........................ 1 2-24 thru2-27 . ................ 2 5-27 thru 5-33 ................. 0 *2-28 ....................... 3 5-34 ........................ 1 2-29 thru 2-31 ................. 2 *5-35 ....................... 3 *2-32 ...................... 3 5-36 ........................ 1 2-33 thru 2-36 ................. 2 *5-37 ....................... 3 *2-37 thru 2-39 . ..... ......... 3 *5-38 Blank ................... 3 2-40 thru 2-43 ................. 2 6-1 ......................... 1 *2-44 thru 2-71 . ............... 3 6-2 thru 6-6 .................. 0 *2-72 Blank ...... ............ 3 6-7 ........................ 1 3-1 thru 3-2 . ................. 1 6-8 ..... .................. 0 3-3 ... ..................... 0 7-1 ......................... 1 3-4 thru 3-6 ............... 1 7-2 thru 7-6 .................. 0 3-7 thru 3-15 . ....... 0 *7-7 ...................... 3 3-16 .... ............... ... 2 7-8 thru 7-10 .................. 0 3.17 ... ................. .. 0 8-1 . ................ ........ 1 3-18 ................... 1 8-2 thru 8-6 ................ 0 3-19 thru 3-20 ...... ......... 9-1 ....................... 1 3-20A ....................... 0 9-2 thru 9-5 . ...... . ... ... 0 A Revision 3 MODEL 182 & T182 SERIES SERVICE MANUAL LIST OF EFFECTIVE PAGES Page Revision Page Revision No. No. No. No. *9 -6 . . . . . . . . . . . . . . . . . . . . . . . 3 13-1 . . . . . .. . . . . . . . . . . . . . . . . 1 9-7 thru 9-12 ................. 0 13-2 thru 13-9 ................ 0 10-1 ....................... 1 13-10 Blank ............... 0 10-2 thru 10-12 ............... 0 14-1 ................... 1 11-1 thru 11-2 ................ 1 14-2 ........ 0... 11-3 . 14-3 thru 14-5 . ...... .1 *11-4 . ... 3 14-6 thru 14-8 ................ 0 11-5 .. .. .. .. .. .. ..-. . - 14-9 thru 14-10 ............ 1 11-thru 11 .......................11-7 thru 11-11. .14-11 thru 14-17......... 11-14 thru 11-22 . . . 0............................0 11-23 ....................... 14-20 thru 14-21 . ............. 1 11-24thru 11-25 thru 11-26 .............. 1 14-23 ...................... 1 11-27 thru 11-30 .............. 0 14-24 thru 14-25. ............. 0 11-30A ...................... 14-26 thru 14-28 .............. 1 11-30B Blank ................. 0 14-29 thru 14-31 .......... 0 11-3 1 ...... ....... . . ..... .. 1 14-32 . .. ..... ... . .. ..... . 1 11-32 thru 11-33 .............. 1 14- 3 0 11-34 Blank .................. 0... 14-34 Blank . 0 11A-1 thru 11A-2 ........ .. . 1 * 15-1 ........ ........ ...... 3 11A-3thru 11A-0 ............. 0 15-2 thru 5-14 .............. 0 11A-11 .. ................... 15-14Athru...............0 11A-12thru 11A-15 ............ 15-14B Blank ................ 0 11A-16 ..................... . . 15-15 thru 15-17 ......... 0... 11A-1thru A-................. 1518 11A-19 ..................... 1 15-18A thru 15-18C . ........ 0.... 11A-20 .15-18D 11A-21 ..................... 15-19 thru 15-19...... .............. 0 11A-22 thru 11A-25 ............ 0 *15-20 thru 15-21 ............. 3 11A-26 Blank ................. 15-02 *12-1 .. . . ........ 12-2 thru 12-6 ............. 0 12-7 thru 12-82 ................. 2.. *15-24A thru 15-24 ....... *12-9 thru 12-10 ............... 12-11 ...................... . 15-28 . ............. 0 12-12....... . 15-28 thru 12-13 thru 12-19 thru 12-20 .............. 16-48A 16-18 ..................... 1 12-21 thru 12-24 ................ 16-48B Blank 1 12-25 12-26 ..................... ....... 3 12-27 thru 12-32 .............. 1 16-64 hru 16-68 ......... Upon receipt of a revision to this book, personnel responsible for maintaining this publication in current status should ascertain that all previous revisions have been received and incorporated. Revision 3 B Revision 3 B MODEL 182 & T182 SERIES SERVICE MANUAL *16-69 .................. ... 3 20-83 thru 20-92 ............... 0 16-70 thru 16-71 .............. 0 20-92A thru 20-92C ............ 0 16-72 ...................... 1 20-92D Blank ................ 0 18-1 ....................... 0 20-93 thru 20-94 .............. 0 18-2 thru 18-6 ................ 0 20-94A ..................... 0 18-6A thru 18-6D ........ .... 0 20-94B Blank ................ 0 18-7 thru 18-12 ............... 0 20-95 thru 20-98 .............. 0 18-12A ..................... 0 20-98A ..................... 0 18-12B Blank ................ 0 20-98B Blank ................ 0 18- 13 thru 18-35 ............. 0 20-99 thru 20-128 ............. 0 18-36 Blank ................. 0 20-128A ................... 0 19-1 ....................... 1 20-128B Blank ............... 0 19-2 thru 19-6 ................ 0 20-129 thru 20-140 ............ 0 *20-1 thru 20-2 ............... 3 20-140A thru 20-140C .......... 0 20-3 thru 20-82 ............... 0 20-140D Blank ............... 0 20 82A ..................... 0 20-141 thru 20-143 ............ 0 20-82B Blank ................ 0 20-144 ..................... 0 C Revision 3 MODEL 182 & T182 SERIES SERVICE MANUAL TABLE OF CONTENTS SECTION PAGE NO. AEROFICHE/MANUAL 1. GENERAL DESCRIPTION .................................. 1A7/1-1 2. GROUND HANDLING, SERVICING. CLEANING. LUBRICATION AND INSPECTION .......................... 1Bb/2-1 3. FUSELAGE ............................................ 19/3-1 4. WINGS AND EMPENNAGE ................................. 1G7/4-1 5. LANDING GEAR AND BRAKES 1G21/5-1 6. AILERON CONTROL SYSTEM .............................. 1I17/6-1 7. WING FLAP CONTROL SYSTEM ............................. 1J9/7-1 8. ELEVATOR CONTROL SYSTEM ............................. 1K1/8-1 9. ELEVATOR TRIM TAB CONTROL SYSTEM ..................... 1K13/9-1 10. RUDDER CONTROL SYSTEM ............................... 1L7/10-1 11. ENGINE (NORMALLY-ASPIRATED) .......................... 2A3/11-1 11A. ENGINE (TURBOCHARGED) ............................... 2B19/11A-1 12. FUEL SYSTEM .......................................... 2D1/12-1 13. PROPELLERS AND PROPELLER GOVERNORS ................. 2E13/13-1 14. UTILITY SYSTEMS ....................................... 2F3/14-1 15. INSTRUMENTS AND INSTRUMENT SYSTEMS .................. 2G19/15-1 16. ELECTRICAL SYSTEMS ................................... 2I9/16-1 17. ELECTRONIC SYSTEMS (DELETED) 18. STRUCTURAL REPAIR .................................. 3A3/18-1 19. PAINTING ........................ ......... ......... 3C3/19-1 20. WIRING DIAGRAMS .................................... 3C15/20-1 WARNING When performing any inspection or maintenance that re- quires turning on the master switch, installing a battery, or pulling the propeller through by hand, treat the prop- eller as if the ignition switch were ON. Do not stand, nor allow anyone else to stand, within the arc of the propel- ler. since a loose or broken wire, or a component mal- function, could cause the propeller to rotate. Revision 1 i MODEL 182 & T182 SERIES SERVICE MANUAL CROSS REFERENCE LISTING OF POPULAR NAME VS. MODEL NUMBERS AND SERIALS All aircraft, regardless of manufacturer, are certified un- der model number designations. However, popular names are often used for marketing purposes. To provide a consis- tent method of referring to these aircraft, the model num- ber will be used in this publication unless the popular name is necessary to differentiate between versions of the same basic model. The following table provides a listing of popular name, model number and serial number. MODEL SERIAL POPULAR NAME YEAR MODEL BEGINNING ENDING SKYLANE 1977 182Q 18265176 18265965 SKYLANE II 1978 182Q 18263479, 18265966 18266590 1979 182Q 18266591 18267300 1980 182Q 18267301 18267715 REIMS/CESSNA 1977 F182P F18200026 F18200064 SKYLANE REIMS/CESSNA SKYLANE II FSKYLANE 1978 F182Q F18200065 F18200094 F SKYLANE II 1979 F182Q F18200095 F18200129 1980 F182Q F18200130 F18200169 SKYLANE 1981 182R 18267302, 18267716 18268055 TURBO SKYLANE 1982 182R 18268056 18268293 SKYLANE II 1983 182R 18268294 18268368 TURBO SKYLANE II 1984 182R 18268369 18268434 SKYLANE 1985 182R 18268435 18268541 TURBO SKYLANE 1986 182R 18268542 18268586 SKYLANE-WITH VALUE GROUP A TURBO SKYLANE-WITH VALUE GROUP A ii Revision 3 MODEL 182 &T182 SERIES SERVICE MANUAL This manual contains factory-recommended procedures and instructions for ground handling, servicing, and maintaining Cessna 182 Series Models. The 182 and T182 Series Models covered in this manual are identical, except the Model T182 is turbocharged. Besides serving as a reference for the experienced mechanic, this man- ual also covers step-by-step procedures for the less experienced. If properly used, it will better enable the me- chanic to maintain Cessna 182 Series airplanes and thereby establish a reputation for reliable service. This service manual is designed for aerofiche presentation. To facilitate the use of the aerofiche, refer to the aerofiche header for basic information. KEEPING CESSNA PUBLICATIONS CURRENT The information in this publication is based on data available at the time of publication and is updated, supple- mented, and automatically amended by all information issued in Service News Letters, Service Bulletins, Sup- plier Service Notices, Publication Changes, Revisions, Reissues and Temporary Revisions. All such amendments become part of and are specifically incorporated within this publication. Users are urged to keep abreast of the latest amendments to this publication through information available at Cessna Authorized Service Stations or through the Cessna Product Support subscription 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 var- ious supplier equipment items. Suppliers publications are updated, supplemented, and specifically amended by supplier issued revisions and service information which may be reissued by Cessna; thereby automatically amending this publication and is communicated to the field through Cessna's Authorized Service Stations and/or through Cessna's subscription services. WARNING: ALL INSPECTION INTERVALS, REPLACEMENT TIME LIMITS, OVERHAUL TIME OMMENDED BY CESSNA ARE SOLELY BASED ON THE USE OF NEW, REMANU- FACTURED, OR OVERHAULED CESSNA APPROVED PARTS. IF PARTS ARE DE- SIGNED, 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, RE- PLACEMENT TIME LIMITS, OVERHAUL TIME LIMITS, THE METHOD OF INSPEC- TION, 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. These are issued to the Service Stations by Cessna Aircraft Company for this publication as required, and include only pages that require updating. 2. REISSUE. Manual is reissued to Service Stations as required, and is a complete manual incorporating all the latest information and outstanding revisions/changes. It supersedes and replaces previous is- sue(s). REVISIONS/CHANGES and REISSUES can be purchased from your Cessna Service Station or directly from the Cessna Parts Distribution, (CPD 2) Dept. 701, Cessna Aircraft Company, 5800 East Pawnee, Wichita, Kansas 67201. All supplemental service information concerning this manual is supplied to all appropriate Cessna Service Sta- tions so that they have the latest authoritative recommendations for servicing these Cessna aircraft. Therefore, it is recommended that Cessna owners utilize the knowledge and experience of the Cessna Service Station Or- ganization. Revision 3 iii MODEL 182 & T182 SERIES SERVICE MANUAL CUSTOMER CARE SUPPLIES AND PUBLICATIONS CATALOG A Customer Care Supplies and Publications Catalog is available from your Cessna Service Station or directly from the Cessna Parts Distribution, (CPD 2) Dept. 701, Cessna Aircraft Company, 5800 East Pawnee, Wichita, Kansas 67201. The Supplies and Publications catalog lists all publications and Customer Care Supplies avail- able from Cessna for prior year models as well as new products. SUPPLEMENTAL TYPE CERTIFICATE INSTALLATIONS Inspection, maintenance and parts requirements for supplemental type certificate (STC) installations are not in- cluded 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 man- ual 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 comments you wish to make. iv Revision 3 MODEL 182 & T182 SERIES SERVICE MANUAL SECTION 1 GENERAL DESCRIPTION Page No. Page No. TABLE OF CONTENTS Aerofiche/Manual TABLE OF CONTENTS Aerofiche Manual GENERAL DESCRIPTION . . ... 1A7/1-1 Torque Values - Bolts ...... 1A10/1-4 Model 182, F182, and T182 Series . 1A7/1-1 Torque Values - Fittings ... . 1A131-7 Description. ...... .. 1A7/1-1 SAFETYING PROCEDURES .... 1A14 1-8 Aircraft Specifications ... . 1A7/1-1 SAFETY WIRE PROCEDURES .... . 1A14 1-8 Stations ... ..... .. 1A7/1-1 USE OF COTTER PINS ....... 1A18 1-12 GENERAL AIRFRAME PRACTICES . . 1A10/1-4 USE OF LOCKING CLIPS . . . . 1A20,1-14 TORQUEING PROCEDURES . .... 1A10/1-4 USE OF LOCKWASHERS ...... 1A20/1-14 Calculating Torque ....... 1A10/1-4 USE OF SELF-LOCKING NUTS . .. 1A20/1-14 1-1. GENERAL DESCRIPTION. series aircraft consists of a single air-cooled, six cylinder horizontally-opposed 0-470 Series Con- 1-2. MODEL 182, F182, and T182 SERIES. tinental engine. The power plant for the T182 series aircraft is a turbocharged, air-cooled, 1-3. DESCRIPTION. The Cessna Model 182, F182 horizontally-opposed, six-cylinder, 0-540 Lycoming and T182 series aircraft, described in this manual, engine. Both engines are coupled directly to a two- are high wing, strut-braced monoplanes of all-metal, bladed all-metal, constant speed McCauley propeller. semimonocoque construction. The aircraft are of conventional design consisting of five basic units, 1-4. AIRCRAFT SPECIFICATIONS. Leading par- i. e. fuselage, wing, stabilizers, flight control sur- ticulars of these aircraft, with dimensions based on faces and landing gear. The landing gear is of con- gross weight, are given in figure 1-1. If these di- temporary fixed tricycle layout for increased ground mensions are used for constructing a hangar or com- stability and is equipped with steerable nose gear, puting clearances, remember that such factors as tubular spring-steel main gear struts and ABS speed nose gear strut inflation, tire pressures, tire sizes fairings for all wheels. In addition, the nose gear and load distribution may result in some dimensions utilizes an air/hydraulic fluid type shock strut, that are considerably different from those listed. Standard cabin seating is four place with an optional child's seat installation available. A carpeted bag- 1-5. STATIONS. A station diagram is shown in gage compartment area is provided aft of the pass- figure 1-2 to assist in locating equipment where a enger seats. The power plant for the 182 and F182 written description is inadequate or impractical. Revision 1 1-1 MODEL 182 & T182 SERIES SERVICE MANUAL MODELS 182, F182 AND T182 GROSS WEIGHT (Takeoff and Landing) (182 & F182 thru 1980) .. . . .... ... ...... 2950 lb. (T182 & 182 1981 & ON) ................... 3100 lb. FUEL CAPACITY Standard Wing (Total) ............... .... 61 gal. THRU 1978 Standard Wing (Usable). .................... 56 gal. THRU 1978 Long-Range (Total) ...................... 80 gal. THRU 1978 Long-Range (Usable). .................. . 75 gal. THRU 1978 Wet Wing (Total). ....................... 92 gal. 1979 & ON Wet Wing (Usable) ....................... 88 gal. 1979 & ON OIL CAPACITY Without External Oil Filter (182 & F182). ............ 12 qts. With External Oil Filter (182 & F182) .............. 13 qts. Without External Oil Filter (T182). ............... 8 qts. With External Oil Filter (T182) ................. 9 qts. ENGINE MODEL (182 & F182) ................. CONTINENTAL 0-470 Series ENGINE MODEL (T182) ...................... LYCOMING 0-540 Series PROPELLER (Constant Speed) ................... 82" McCAULEY MAIN WHEEL TIRES ....................... 6.00 x 6, 6-Ply rating Pressure ................... ....... 42 psi NOSE WHEEL TIRE....................... 5.00 x 5, 6-Ply rating Pressure ........................... 49 psi NOSE GEAR STRUT PRESSURE (Strut Extended) ........... 55 psi to 60 psi WHEEL ALIGNMENT Camber .. ..... .. . . . ... . . . . . .... ... 5° to 7° Toe-In ........................... . 0" to. 06" AILERON TRAVEL Up ..... .... . .. . . . ... . . . . . 20 ° ± 2° Down . . . . . . . . . . . . . . . . . . . . . . .. 15 ° ± 2 ° WING FLAP TRAVEL ........... ......... . 0° to 40 ° +1°-2° THRU 1981 0° ± 0 ° t o 3 8 ° + 0 ° - 1 ° 1982 & ON RUDDER TRAVEL (Measured Parallel to Water Line) Right . . . . . . . . . . . . . . . . . . . . . . . . . .. . 24 ° +0 -1 Left . . . . . . . . . . . . . . . . . . . . . . . . . . ... 24 +0 -1 RUDDER TRAVEL (Measured Perpendicular to Hinge Line) Right ........................... . 27° 13' +0 -1 Left ............................. 27° 13' +0 -1 ELEVATOR TRAVEL (Relative to Stabilizer) Up (182 & F182). ....................... 26 ° ± 1° THRU 1980 Up (182 & T182). ....................... 28 ° ± 1° 1981 & ON Down (182 & F182). ...................... 17° ± 1° THRU 1980 Down (182& T182). ...................... 21 ° ± 1° 1981 & ON ELEVATOR TRIM TAB TRAVEL Up (182 & F182). ....................... 25 ° ± 2° THRU 1980 Up (182& T182) ......................... 24 ° ± 2 ° 1981 & ON Down (182, F182 & T182) . ................. 15 ° ± 1° PRINCIPAL DIMINSIONS Wing Span ........... ... . ........... 432.00" Tail Span. ................... ........ 140. 00" Lenght (182 & F182) ...................... 337.47" Length (T182) ..... ... . . ... . .. .. ....... 338. 97" Fin Height ......... .. ... ....... ... . 109.68" Track Width ............. . ........... 109.25" BATTERY LOCATION ...................... Aft of Baggage Compartment Measured with strobe lights installed. Measured with aircraft empty. (Maximum with nose gear depressed and flashing beacon installed on fin. ) Figure 1-1. Aircraft Specifications 1-2 MODEL 182 & T182 SERIES SERVICE MANUAL MODEL 18Z, F82, and T82 SERIES 23. 62 WET WING 39.00 9785.87 1 ~85-96 ,Il T9796-5r .100 56.7850 |17~".00 7 40 23. 62 56.5371.9785.87 100. s50 . 8. ~12 56. 118.70 - Figure 1-2.Refere s- -136 00 154. 00 STANDARI) WI 172. 0 190. 00 19N7--"' - - 8 208. 00 0..00 124; 00 156: 00 185.50 209. 00 45. A~ 1 I92.00 8.12 0 79. 00 56.70 Figure 1-2. Reference Stations 1-3 MODEL 182 & T182 SERIES SERVICE MANUAL 1-6. GENERAL. This chapter deals with general tor- (d) Since running torque will become less due que and safetying practices used to ensure security of to nutbolt re-use (in accepted applications), this pro- installation and prevent overstressing of components. cedure must be repeated each time. Special torque values, when required, are specified (e) When necessary to tighten from bolt head, with the specific component maintenance and installa- increase torque value by an amount equal to shank tion instructions. torque (torque required to turn bolt when installed). Measure with a torque wrench. 1-7. TORQUEING PROCEDURES. The importance of correct application cannot be overemphasized. Under- torque can result in unnecessary wear of nuts and bolts as well as parts they are holding together. When Average insufficient pressures are applied, uneven loads will be transmitted throughout assembly, which may Dry torque required result in excessive wear or premature failure due to fatigue. Overtorque can be equally damaging because b. Torque Values - Bolts and Nuts. (See Table 1-1.) of failure of a bolt or nut from overstressing threaded 1. Tables included in this section do not apply to areas. the following exceptions: a. Calculating Torque. There are a few simple, but (a) Sheet metal screws should be tightened very important, procedures that should be followed to firmly, but with no specific torque value. assure that correct torque is applied: (b) Screws attached to nutplates should be 1. Calibrate torque wrench periodically to assure tightened firmly, but with no specific torque value. accuracy; and recheck frequently. (c) Bolts, nuts, and screws used in control 2. When using a torque wrench adapter which systems and installations where required torque changes distance from torque wrench drive to adapter would cause binding or interfere with proper opera- drive. the indicated reading must be adjusted for tion of parts. desired torque reading. (See Figure 1-2.) (d) Screws used with dimpled washers should 3. Be sure that bolt and nut threads are clean not be drawn tight enough to eliminate washer and dry unless otherwise specified. crown. 4. Determine friction drag torque and add to (e) Fasteners that have a specified torque in a specified dry torque value to ensure proper bolt utili- specific nstallation. zation. 2. The values shown in Table 1-1 are based on (a) Hand-turn nut onto bolt until it stops. parts being clean and dry with no lubricants added. (b) Using a torque wrench, measure runnin 3. Castellated nuts requiring cotter pins should torque (torque required to turn nut on bolt). be tightened to low torque value. Torque can be in- (c) This running torque must be added to creased to install cotter pin, but should never exceed specified dry torque value to ensure proper bolt utili- maximum torque value. zation. NOTE EXAMPLE Self-looking castellated nuts, MS17825 and Average running torque for a nut = 15 in.-lbs. MS17826, require a separate torque range. Dry torque required = 125 5 in.-lbs. These values are shown separately in torque Final torque wrench reading = 140 ± 5 in.-lbs. value tables. 1-4 Revision 1 MODEL 182 & T182 SERIES SERVICE MANUAL NOTE When using a torque wrench adapter which changes the distance from torque wrench drive to adapter drive, apply following formula to obtain corrected torque reading. SHORT OPEN END ADAPTER FORMULA LEGEND T = Desired Torque L + SETSCREW WRENCH HANDGRIP ADAPTER DRIVE CENTERLINE CENTERLINE (PREDETERMINED) ADAPTER TORQUE CENTERLINE HOSE CLAMP ADAPTER EXAMPLE Y = Unknown 10 + 1.5 11.5 E = 1.5 In. Y = 117 In.-Lbs OPEN-END WRENCH ADAPTER DRIVE CENTERLINE CENTERLINE (PREDETERMINED) WRENCH TORQUE DRIVE WRENCH CENTERLINE FLARE NUT WRENCH ADAPTER EXAMPLE SPANNER WRENCH ADAPTER T = 135 In.-Lbs y = 135 x 10 _ 1350 15882 Y = Unknown L = 10.0 In.-Lbs 10 1.5 8.5 E = -1.5 In. Y = 159 In.-Lbs Figure 1-3. Torque Wrench Adapter Adjustment Revision 1 1-5 MODEL 182 & T182 SERIES SERVICE MANUAL BOLT TORQUE VALUES Tension Shear Tension Shear BOLTS BOLTS AN3 thru AN20 MS20004 thru MS20024 NAS464 AN42 thru AN49 NOTE: Bolts in tension NAS144 thru NAS148 AN73 thru AN81 column may be used NAS172 AN173 thru AN186 with shear nuts. Bolts NAS174 AN509NK9 in shear column NAS333 thru NAS340 AN525NK525 should not be used un- NAS585 thru NAS590 MS20033 thru MS20046 less a minimum of two NAS624 thru NAS644 MS20073 threads extend beyondNAS1303 thru NAS1320 MS20074 nut after installation. NAS517 MS24694 MS27039 NUTS NUTS AN310 AN320 AN310 AN320 AN315 AN364 AN315 AN364 AN363 MS20364 NA363 NAS1022 AN365 NAS1022 AN365 MS20364 MS20365 MS20365 MS20500 MS21045 MS21045 NAS679 NAS679 NAS1021 NAS1021 NAS1291 Nut-bolt FINE THREAD SERIES size Torque Limits Torque Limits in.-lbs. in.-lbs. size in.-lbs. in.-lbs. MIN. MAX. MIN. MAX. MIN. I MAX. MIN. MAX. 8-36 12 15 7 9 10-32 25 30 15 20 10-32 20 25 12 15 1.4-28 80 100 50 60 1 4-28 50 70 30 40 5/16-24 120 145 70 90 5 16-24 100 140 60 85 3,8-24 200 250 120 150 38-24 160 190 95 110 7/16-20 520 630 300 400 7 16-20 450 500 270 300 1/2-20 770 950 450 550 12-20 480 690 290 410 9/16-18 1100 1300 650 800 916-18 800 1000 480 600 5,8-18 1250 1550 750 950 58-18 1100 1300 660 780 3/4-16 2650 3200 1600 1900 34-16 2300 2500 1300 1500 7/8-14 3550 4350 2100 2600 7 8-14 2500 3000 1500 1800 1-14 4500 5500 2700 3300 1-14 3700 4500 2200 3300 1-1/8-12 6000 7300 3600 4400 1-1 8-12 5000 7000 3000 4200 1-1,4-12 11000 13400 6600 8000 1-1 4-12 9000 11000 5400 6600 Nut-bolt Nut-bolt size Torque Limits Torque Limits size Torque Limits Torque Limits in.-lbs. in.-lbs.size in.-lbs. in.-lbs. MIN. I MAX. MIN. I MAX. MIN. I MAX. MIN. MAX. 8-32 12 15 7 9 10-32 28 35 16 20 10-24 20 25 12 15 1/4-28 65 80 35 45 1/4-20 40 50 25 30 5i16-24 180 225 70 90 5,16-18 80 90 48 55 3/8-24 260 325 100 125 38-16 160 185 95 110 7,16-20 460 575 180 225 7.16-14 235 255 140 155 1/2-20 720 900 240 300 12-13 400 480 240 290 9/16-18 880 1100 320 400 9 16-12 500 700 300 420 5,8-18 1300 1600 480 600 5/8-11 700 900 420 540 3/4-16 2200 2800 880 1100 34-10 1150 1600 700 950 7 8-14 3700 4600 1500 1900 78-9 2200 3000 1300 1800 1-14 5400 6800 2400 3000 1-8 3700 5000 2200 3000 1-1/8-12 8000 10000 4000 5000 1-1 8-8 5500 6500 3300 4000 1-1/4-12 11000 14000 5600 7000 1-1 4-8 6500 8000 4000 5000 Table 1-1. Torque Values - Bolts and Nuts 1-6 Revision 1 MODEL 182 & T182 SERIES SERVICE MANUAL c. Torque Value - Threaded Straight Fittings. (b) Turn nut down until packing is firmly NOTE against lower threaded section of fitting. (c) Install fitting into boss and tighten until Tables in this section are for general applica- there is a sudden increase in torque. tions. Refer to specific installations for special (d) Tighten fitting 1-1/2 turns. torque values ad pro ure. (e) Orientation is accomplished by tightening fitting, but not exceeding one turn. (f) Tighten jam-nut to torque values in Table 1. Connectors installed in bosses with no re- quired orientation should be installed using torque 3. Bulkhead fittings are installed with jam-nuts values given in Table 1-2. and should be torqued to values in Table 1-2. 4. Torque values for hose end fittings (nipple or THREADED CONNECTOR nut) are given in Table 1-3. TUBE JAM-NUT CONNECTOR OUTSIDE THREAD DIAMETER w/o JAM-NUT (Inches) Torque-Limits Torque-Limits HOSE ALUMINUM STEEL 1/8 5/16-24 35 50 50 55 MIN. MAX. MIN. MAX. 3/16 3/8-24 65 80 65 20 30 75 85 1/4 7/16-20 85 105 95 1053/16 25 35 95 105 5/16 1/2-20 105 125 125 135 1/4 50 65 135 150 3/8 9/16-18 120 150 155 165 5/16 7 90 170 200 1/2 3/4-16 240 280 280 3053/8 110 130 270 300 5/8 7,7-14 320 380 380 405 230 260 450 500 3/4 1/16-12 500 600 550 600 1 1-5/16-12 720 880 800 900 1-1/4 1-5/8-12 960 1200 900 1000 1-1/2 1-7/8-12 1200 1440 900 1000 2 2-1/2-12 1400 1500 900 1000 1-3/4 . - - 2 1800 2000 2660 2940 Table 1-2. Torque Values Jam-Nuts and Threaded Connector 2. Connectors installed in bosses requiring a Table 1-3. Torque Values specific orientation do not use a torque value, but Hose Assemblies use the following steps: (a) Place jam-nut on fitting along with re- 5. Torque values for straight threaded fittings tainer and packing. used with rigid lines are given in Table 1-4. Revision 1 1-7 MODEL 182 & T182 SERIES SERVICE MANUAL THREADED STRAIGHT FITTING TORQUE VALUE (RIGID TUBE) FLARED END STRAIGHT END TUBE ALUMINUM ALUMINUM STEEL 6061-0 ALUMINUM STEEL 6061-T(X) ALUMINUM OUTSIDE On Oxygen Lines 5052-0 ALUMINUM w/ steel sleeve DIAMETER Torque-Limits Torque-Limits Torque-Limits Torque-Limits Torque-Limits Torque-Limits in-lbs. in-bs. inlbs. in-lbs. in-lbs. in-bs. MIN. MAX. MIN. MAX. MIN. MAX. MIN. MAX. MIN. I MAX. TUBE WALL MIN. MAX. 18 20 30 45 55 316 90 100 30 40 90 100 0.028 45 55 14 40 65 135 150 40 65 135 150 0.022 80 105 0.028 80 105 0.035 80 105 0.049 90 115 516 60 80 100 125 180 200 60 80 180 200 0.028 80 105 0.035 80 105 0.042 125 175 38 75 125 270 300 75 125 270 300 0.028 125 175 0.035 125 175 0.049 125 175 12 150 250 450 500 150 250 450 500 0.028 135 180 0.035 200 300 0.049 400 500 0.058 400 500 0.065 400 500 58 200 350 700 800 200 350 700 800 All 500 600 34 300 500 1100 1150 300 500 1100 1150 All 600 700 1 500 700 1200 1400 500 700 1200 1400 All 1000 1300 1-1 4 600 900 1300 1450 600 900 1300 1450 All 1300 1500 1-1 2 600 900 1350 1500 600 900 1350 1500 All 1400 1700 2 600 900 1500 1700 Table 1-4. Torque Values - Straight Threaded Fittings (Line) 1-8. SAFETYING PROCEDURES. The use of safety 2. Copper that is cadium-plated and dyed yellow wire, cotter pins, lockwashers, and self-locking nuts is used for shear and seal wiring applications. is to prevent relative movement of critical components (a) Shear applications are those where it is subject to vibration, torque, tension, etc., which could necessary to break or shear wire to permit operation cause attaching parts to be broken, loosened, and/or or actuation of emergency devices. detached. (b) Seal applications are where wire is used with a lead seal to prevent tampering or use of a 1-9. SAFETY WIRE PROCEDURES. device without indication. a. Identification. Lockwire comes in three types 3. Aluminum Alloy (Alclad 5056) is dyed blue which are identified by size and color. The three types and is used exclusively for safety-wiring magnesium are classified by use. parts. 1. Inconel and Monel wire is used for general 4. Size of wire is dependent on material and lockwiring and is identified by a natural wire color. purpose of installation. (a) Inconel can withstand temperatures up to (a) 0.020-inch diameter copper wire should be 1500°F. used for shear and seal application. (b) Monel can withstand temperatures up to (b) 0.020-inch diameter wire may be used to 800°F. lockwire parts with tie holes smaller than 0.045 in- 1-8 Revision 1 MODEL 182 & T182 SERIES SERVICE MANUAL ches; or, on parts with tie hole diameters between NOTE 0.045 and 0.062 when spacing between ports is less than two inches; or, when bolts and screws of 0.25- Widely spaced multiple groups shall mean those inch diameter or less are closely spaced. in which fasteners are from four to six inches (c) 0.032-inch minimum diameter wire is used apart. Lockwiring shall not be used to secure for general purpose lockwiring. fasteners or fittings which are spaced more NOTE than six inches apart, unless tie points are pro- vided on adjacent parts to shorten span of When using single-wire method of locking, thelockwire to less than six inches. largest wire that will fit tie holes should be 5. When lockwiring closely spaced multiple used. groups, the number of units that can be lockwired b. Lockwire Installation. There are two basic forms by a 24-inch length of wire shall be the maximum of lockwiring. The single-wire method has limited number in a series. application; the double-twist method is the common 6. Parts should be lockwired so that wire is method of lockwiring. placed in tension (pulled on) if a part attempts to 1. Use new wire for each application; do not try loosen. to re-use old wire. c. Required Lockwire Installation Applications. 2. Single-wire method is accomplished by pas- 1. Bolts and other fasteners securing critical sing a single wire through tie holes and back with parts that affect airplane safety and operation. ends then twisted together. (See Figure 1-4.) (a) In blind-tapped hole applications or bolts or (a) Single-wire method is used for shear and castellated nuts on studs, lockwiring is installed in seal wiring applications. same manner as described for bolt heads. (b) Single-wire method can be used in closely (b) Hollow head bolts are safetied in manner spaced, closed geometric patterns. Closely spaced is prescribed for regular bolts. defined as spacing two inches or less between cen- (c) Drain plugs and cocks may be safetied to a ters of parts. bolt, nut, or other part having a free tie hole in (d) External snap rings may be locked if nec- Screws in closely spaced geometric patterns essary using general locking principles as de- which secure hydraulic or air seals, hold hy- scribed and illustrated. Internal snap rings should draulic pressure, or are used in critical areas not be lockwired. should use double-twist method of lockwiring. (e) When locking is required on electrical connectors which use threaded coupling rings, or 3. Lockwiring by the double-twist method is on plugs which employ screws or rings to fasten really one wire twisted on itself several times and is individual parts of plug together, they shall be accomplished by the following steps (see Figure 1- lockwired with 0.020-inch diameter wire in accor- 4) dance with locking principles as described and (a) Insert one end of wire through tie holes of illustrated. It is preferable to lockwire all electrical bolt head and firmly loop around bolt head. connectors individually. Do not lockwire one con- nector to another unless it is necessary to do so. NOTE (f) Drilled head bolts and screws need not be lockwired if installed into self-locking nuts or in- This does not necessarily apply to castellated stalled with lockwashers. Castellated nuts with nuts when slot is close to top of nut. The wire cotter pins or lockwire are preferred on bolts or will be more secure if it is made to pass along studs with drilled shanks, but self-locking nuts are side of stud. permissible within limitations described in Para- graph 1-13. (b) While taut, twist strands to within 1/8 inch 2. For new design, lockwire shall not be used to of next part. The twisting keeps wire taut without secure nor shall lockwire be dependent upon frac- overstressing and prevents wire from becoming ture as basis for operation of emergency devices nicked, kinked, or mutilated. such as handles, switches, and guard-covering (c) Lockwiring multiple groups by double- handles that operate emergency mechanisms such twist method is accomplished in a similar manner as emergency exits, fire extingushers, emergency except twists between parts are alternated between cabin pressure release, emergency landing gear clockwise and counterclockwise. release, and the like. However, where existing (d) After last tie hole, wire is twisted three to structural equipment or safety of flight emergency five times to form a pigtail. devices requires shear wire to secure equipment (e) Cut off any excess wire and bend pigtail while not in use, but which are dependent upon towards part. shearing or breaking of lockwire for successful 4. When lockwiring widely spaced multiple emergency operation of equipment, particular care groups by double-twist method, three units shall be exercised to assure that wiring under these cir- the maximum number in a series. cumstances shall not prevent emergency operations of these devices. Revision 1 1-9 MODEL 182 & T182 SERIES SERVICE MANUAL r rl( I ''I EXTERNAL SNAP RING SINGLE-WIRE METHOD NOTE BOLTS IN CLOSELY SPACED, CLOSED RIGHT-HAND THREADED PARTS GEOMETRICAL PATTERN. SINGLE- WIRE METHOD. SHOWN. REVERSE DIRECTION FOR LEFT-HAND THREADS. SINGLE FASTENER APPLICATION CASTELLATED NUTS ON DRILLED STUDS DOUBLE-TWIST METHOD DOUBLE-TWIST METHOD Figure 1-4. Lockwire Safetying (Sheet 1 of 2) 1-10 Revision 1 MODEL 182 & T182 SERIES SERVICE MANUAL DOUBLE-TWIST METHOD STEP 1. Insert wire through bolt A and bend around bolt (if necessary, bend wire across bolt head). Twist wires clockwise STEP 2. Insert one end of wire through bolt B. Bend other end around bolt (if necessary, bend wire across head of bolt). Twist wires counterclockwise 1/2 inch or six twists. Clip ends. Bend pigtail back againt part. BOLT B CLOCKWISE DOUBLE-TWIST METHOD COUNTERCLOCKWISE CLOCKWISE COUNTERCLOCKWISE < "CLOCKWISE MULTIPLE FASTENER APPLICATION DOUBLE-TWIST METHOD bELECTRICAL CONNECTION DOUBLE-TWIST METHOD Figure 1-4. Lockwire Safetying (Sheet 2 of 2) Revision 1 1- MODEL 182 & T182 SERIES SERVICE MANUAL 1-10. USE OF COTTER PINS. (6) Install cotter pin with head firmly in slot of a. Cotter Pin Installation. Castellated nuts and pins nut with axis of eye at right angles to bolt shank. may be safetied with cotter pins or lockwire. The Bend prongs so that head and upper prong are firmly preferred method is to use cotter pins. seated against bolt (see figure 1-5). 1. Select cotter pin material in accordance with temperature, atmosphere, and service limitations (see Table 1-5). COTTER PIN - MINIMUM SIZE THREAD SIZE MINIMUM PIN SIZE COTTER PINS (MS24665) 0028 MATERIAL TEMP USE 8 0.044 Carbon Steel Up to 450°F Pins that contact cadmium- 10 0.044 plated surfaces. 1/4 0.044 5/16 0.044 General Applications 3/8 0.072 7/16 0.072 Normal Atmospheres 1/2 0.072 9/16 0.086 Corrosion- Up to 800°F Pins that contact cor- 5/8 0.086 Resistant rosion-resistant steel. 3/4 0.086 7/8 0.086 Corrosive atmospheres 1 0.086 1-1/8 0.116 1-1/4 0.116 Table 1-5. Cotter Pin 1-3/8 0.116 Temperature and Use 1-1/2 0.116 2. Cotter pins shall be new upon each applica- tion. 3. When nuts are to be secured to fastener with Table 1-6. Cotter Pin cotter pins, tighten nut to low side (minimum) of Minimum Size applicable specified or selected torque range, unless otherwise specified, and if necessary, continue tight- (7) In pin applications, install cotter pin with ening until slot aligns with hole. In no case shall you axis of eye parallel to shank of clevis pin or rod end. exceed high side (maximum) torque range. Bend prongs around shank of pin or rod end (see 4. If more than 50 percent of cotter pin diameter Figure 1-5). is above nut castellation. a washer should be used under nut or a shorter fastener should be used. A maximum of two washers may be permitted under a Cadium-plated cotter pins should not be used in nut. applications bringing them in contact with fuel, 5. The largest diameter cotter pin which hole hydraulic fluid, or synthetic lubricants. and slots will accommodate should be used, but in no application to a nut, bolt, or screw shall pin size be less than sizes described in Table 1-6. 1-12 Revision 1 MODEL 182 & T182 SERIES SERVICE MANUAL TO PROVIDE CLEARANCE PRONG MAY BE CUT HERE PREFERRED METHOD ALTERNATE METHOD CASTELLATED NUT ON BOLT TANGENT TO PIN MAXIMUM MINIMUM COTTER PIN COTTER PIN LENGTH LENGTH PIN APPLICATION Figure 1-5. Installation of Cotter Pins Revision 1 1-13 MODEL 182 & T182 SERIES SERVICE MANUAL 1-11. USE OF LOCKING CLIPS. 5. When loosening of threaded parts would not a. Safetying Turnbuckles. (See Figure 1-6.) endanger safety of airplane or people. 1. Prior to safetying, both threaded terminals 6. When corrosion encouraged by gouging shall be screwed an equal distance into turnbuckle aluminum or magnesium alloys by edges of teeth on body and shall be screwed in at least so far that not tooth-locked washers would not cause malfunctioning more than three threads of any terminal are exposed of parts being fastened together. outside body. 2. After turnbuckle has been adjusted to its 1-13. USE OF SELF-LOCKING NUTS. locking position, with slot indicator groove on termi- a. Restrictions. nals and slot indicator notch on body aligned, insert 1. Self-locking nuts cannot be used under cer- end of locking clip into terminal and body (refer to tain conditions. Figure 1-6) until U-curved end of locking clip is over (a) Used, reworked, or reprocessed nuts hole in center of body. should not be installed for any application. (a) Press locking clip into hold to its full ex- (b) Do not use if at joints in control systems tent. for singular attach points. (b) Curved end of locking clip will expand and (c) Do not use on externally threaded parts latch in body slot. that serve as an axle of rotation for another part (c) To check proper seating of locking clip, where tensional (torque) loads can cause nut to loosen attempt to remove pressed "U" end from body hole and/or become separated. Examples are pulleys, lev- with fingers only. ers, linkages, and cam followers. NOTE NOTE Do not use tool as locking clip could be dis- Self-locking nuts can be used when threaded torted. parts are held by a positive locking device that requires shearing or rupture before torsional 3. Locking clips are for one time use only and loads can act on threaded parts. shall not be re-used. 4. Both locking clips may be inserted in same (d) Do not use where a loose nut, bolt, or hole of turnbuckle body or in opposite holes of screw could fall or be drawn into an area that turnbuckle body. would impede or damage or otherwise distort opera- tion. 1-12. USE OF LOCKWASHERS. (e) Do not use to attach access panels and a. Lockwashers can be used only under the follow- doors or to assemble components that are routinely ing conditions. disassembled or removed for access and servicing. 1. When self-locking feature cannot be provided (f) In general, do not use self-locking nuts in externally or internally threaded part. where loss of bolt affects safety of flight. 2. When a cotter pin cannot be used to prevent 2. Bolts, studs, or screws, excluding Hi-Locks, rotation of internal threads with respect to external must extend through self-locking nut for a length threads, equivalent of two threaded pitches. This length 3. When lockwire cannot be used to prevent includes chamfer. loosening of threaded parts. 3. Self-locking nuts which are attached to struc- 4. When fastening is not used for fabrication of ture shall be attached in a positive manner to elimi- primary structure. nate possibility of their rotation or misalignment when tightening is to be accomplished by rotating bolts to structure, and permit replacement of nuts. 1-14 Revision 1 MODEL 182 & T182 SERIES SERVICE MANUAL LOCKING CUP BARREL BARREL LOCKING CLIP LOCKING CLIP CABLE TERMINAL Detail A Figure 1-6. Safetying Turnbuckle Assemblies Revision 2 1-15 MODEL 182 & T182 SERIES SERVICE MANUAL 1-14. CONTROL CABLE WIRE BREAKAGE as shown. While rotating cable, inspect bent area for AND CORROSION LIMITATIONS. broken wires. a. Inspection of Control Cables. (b) Wire breakage criteria for cables in 1. Control cable assemblies are subject to a flap, aileron, rudder, and elevator systems are as variety of environmental conditions and forms of follows: deterioration that ultimately may be easy to recognize (1) Individual broken wires are acceptable such as wire/strand breakage, or the not so readily in primary and secondary control visible types of deterioration including corrosion cables at random locations when there and/or distortion. The following information will aid are no more than six broken wires in in detecting these cable conditions. any given ten-inch cable length. 2. Broken Wire. 3. Corrosion. (a) Examine cables for broken wires by (a) Carefully examine any cable for passing a cloth along length of cable. This will detect corrosion that has a broken wire in a section not in broken wires, if cloth snags on cable. Critical areas for contact with wear-producing airframe components wire breakage are those sections of cable which pass such as pulleys, fairleads, rub blocks, etc. It may be through fairleads, across rub blocks, and around necessary to remove and bend cable to properly inspect pulleys. If no snags are found, then no further it for internal strand corrosion as this condition is inspection is required. If snags are found or broken usually not evident on outer surface of cable. Replace wires are suspected, then a more detailed inspection is cable if internal corrosion is found. If a cable has been necessary which requires that the cables be bent in a wiped clean of its corrosion-preventive lubricant and loop to confirm broken wires (refer to figure 1-7). metal-brightened, the cable shall be examined closely Loosen or remove cable to allow it to be bent in a loop for corrosion. 1-16 Revision 3 MODEL 182 & T182 SERIES SERVICE MANUAL -ROKEN WIRE UNDETECTED BY WIPING CLOTH ALONG CABLE BROKEN WIRE DETECTED VISUALLY WHEN CABLE WAS REMOVED AND BENT NORMAL TECHNIQUE FOR BENDING CABLE AND CHECKING FOR BROKEN WIRES DONOT BEND INTO LOOP SMALLER THAN 50 CABLE DIAMETERS Figure 1-7 Cable Broken Wire Inspection Revision 2 1-17 MODEL 182 & T182 SERIES SERVICE MANUAL (g) Class IX - These are polyurethane 1-15. ADHESIVES, CEMENTS AND SEALANTS products Store in original container, between 70°F - SHELF LIFE AND STORAGE and 100°F. Urethanes are moisture sensitive and a. General precautions should be taken to ensure complete 1 This section provides information which protection from moisture contamination. Container defines the proper storage and usable life (shelf life) of must be tightly closed at all times. adhesives, cements and sealents which are used for (h) Class X - These are acrylic base maintenance and/or repair of the airplane. Also, materials. They require storage at 40°F or per included in this section is the criteria used for testing instructions on product container. these materials after the normal shelf life has expired, c Storage of Sealants. to determine if an extension to the shelf life is possible. 1. All sealants shall be stored under controlled 2. Shelf life refers to a specified period of time temperature conditions. If open shop storage becomes usually from the date of manufacture (normally necessary, these products shall in no case be stored in stamped or printed on the product container) to the an area which will subject them to temperatures in expiration date (which should be determined using excess of 95°F or below 40°F. Containers shall be limits specified in Table 1-7 or if applicable, the tightly closed prior to placing them in the proper manufacturer's expiration date printed or stamped on storage environment. For proper storage environment, the product container). The specified shelf life is refer to Table 1-7 and the following paragraphs. dependent on proper storage in accordance with the (a) Premixed and frozen sealants shall be limits specified in this section and/or the stored at -40°F or colder and shall not be used more manufacturer's instructions. than six weeks after the date of mixing even if all b Storage Criteria storage is at -40°F or colder. If storage temperatures 1 Storage of Adhesives and Cements. rise above -40°F, but not warmer than -30F, the All adhesives and cements shall be stored under material may be stored for a maximum of two weeks controlled temperature conditions. If open shop warmer than -40°F plus time at -40°F or colder for a storage becomes necessary, these products shall in no combined total not to exceed five weeks beyond the case be stored in an area which will subject them to date of mixing. If storage temperatures rise above temperatures in excess of 95°F Containers shall be -40F but are not warmer than -20°F, the materials tightly closed prior to being placing them into the may be stored for a maximum of one week above -30°F proper storage environment. For proper storage plus time at -40°F or colder for a combined total not to environment, refer to Table 1-7 and the following exceed four weeks beyond the date of mixing. paragraphs. (b) Unmixed sealants shall be stored at a (a) Class I - These adhesives are epoxy base controlled temperature of between 40°F and 80°F and materials and have one year storage at room have a shelf life of approximately six months when temperature. 0°F storage will extend the storage life. stored within this temperature range. Unmixed Refer to the product container instructions for storage sealants stored at temperatures exceeding 80°F shall temperature and life. be used within five weeks. (b) Class II, III and IV - These adhesives 2. All materials should be used on a "first in- are rubber and resin base and are good for six months first out" basis The adhesives, cements and sealants at room temperature storage. 40°F storage will extend should be rotated so this requirement can be the storage life Refer to the product container accomplished. All material containers should be instructions for limits of each adhesive. clearly marked with a "use by" date, consisting of the (c) Class V. These are silicone rubber year and month All materials not used by this date adhesives. If stored in their original containers at a must be tested prior to use. Refer to Testing criteria temperature below 80°F, have a shelf life of one year and Table 1-7. or as indicated on the storage container d. Testing Criteria (d) Class VI These are solvent bonding I Any material (adhesive, cement or sealant) solvents They should be stored in their original not used within its shelf life will be tested and the containers and tightly closed, and stored at 40°F results reviewed to determine if the material is usable temperature If there is doubt about the material being usable, it (e) ClassVII - Cyanoacrylate base must be properly disposed of. Material that has materials must he stored in the original containers at exceeded its original shelf life may be retested to 40°F or as specified on the container instructions determine if the material meets its requirements sensitive materials The shelf life is two years when shelf life extended as specified in Table 1-7. Materials stored at 75°F and 50 percent relative humidity with shelf life extensions must be retested after a specified period of time Refer toTable 1-7 1-18 Revision 2 MODEL 182 & T182 SERIES SERVICE MANUAL 2 Testing of Overaged Adhesives and shelf life extension shall be properly mixed using the Cements correct materials, procedures and equipment. 3. Overaged premixed frozen sealants, along Sealants which show conclusive evidence of Overaged adhesives and cements are those separation, discoloration and/or gelling prior to the that have exceeded their original shelf life addition of a thinner or curing agent shall be and must be tested prior to use and/or given discarded. When in doubt of the sealant quality, the extended shelf life. overaged sealant should be compared with the same type of sealant, under six months old, which is known (a) Class I Epoxy Adhesive - Examine both to be satisfactory. components to ensure that they are still workable. 4. The mixed sealants may be tested by placing Check for gelling and/or contamination Stir a small amount of sealant (smaple buttons) on a sheet components and mix a small amount of adhesive. of paper. After the sample buttons have cured, they Verify that adhesive sets up and hardens should be cut in half and examined. The sealant (b) Class II, IIIand IV Rubber and Resin should show no signs of spots or streaks of unmixed Base Adhesives - Open containers and check for base compound or curing agent. However, sample gelling and/or contamination. Check for spreading and buttons containing spots, streaks, discoloration and/or drying. variations in uniformity of color are acceptable if these (c) Class V Silicone Rubber Adhesives - spots, streaks, etc., are tack free upon inspection. All Examine adhesive for hardness. If adhesive is still soft mixed sealant should be as void free as possible. and can be spread, it is acceptable. Verify that 5. Contaminated sealant, premixed sealant adhesive will harden. that have been thawed and refrozen shall be (d) Class VI Solvent Bonding Solvents- discarded. Check for signs of apparent contamination. Solvents 6. Type 1, Class A sealants should be checked should be clean and clear with no signs of cloudiness. for appearance, application time, tack-free time, cure (e) Class VII Cyanoacrylic Base Adhesives time, and adhesion. - Verify that product is still liquid with no visible signs 7. Type I, Class B sealants should be checked of contamination. for appearance, applicatiion time, cure time, tack-free ( Class VIII Pressure Sensitive Materials time, and adhesion. In addition, Class B-2 and B-4 - Open containers and inspect for hardening, gelling sealants should be checked for initial flow. amount of adhesive. Verify that adhesive sets up for appearance, application time, cure time and properly adhesion. In addition, Class C sealants should be (g) Class X Acrylic Adhesives- Inspect base tested to determine that they ARE NOT at a tackfree material to ensure that it is still liquid. Mix a small condition at the end of their rated work life (squeeze amount of the components and verify that it sets up out life). properly. 9. Type II sealants should be checked for 3. In general, if these materials exhibit normal appearance, application time, tack-free time and cure physical properties, with no signs of hardening, time. gelling or contamination and set up and/or harden 10. Type IIIsealants should be easily thinned properly as applicable, the shelf life may be extended with MEK, when difficulty is encountered in thinning as specified in Table 1-7. the sealant, it should be discarded e. Testing of Overaged Sealants 11. Type IV sealants should be checked for appearance, application time, tack-free time and cure NOTE time. 12. Type V and VI sealants should be checked Overaged sealants are those that have for appearance, tack-free time and cure time. exceeded their original shelflife and 13 Type VII sealants should be checked for must be tested prior to use and/or given appearance, application time, tack-free time and cure extended shelf life time 14 Type VIII sealants should be checked for 1. For identification ofsealants Classification, appearance, application time, tack-free time, cure refer to Fuel, Weather, Pressure and High- time and adhesion Adhesion to aluminum should be Temperature Sealing - Maintenance Practices. (peel) less than two-pounds per inch of width. 2 Overaged sealants to be tested for possible Revision 2 1-19 STORAGE CONDITION EXTEND CONDITION SHELF LIFE EXTEND RETESTIN PRODUCT (TEMPERATURE IN MONTHS SHELF LIFE MONTHS IN DEGREES IN MONTHS FAHENHEIT) ADHESIVES AND CEMENTS EA9309.3NA 40 TO 80°F 12 Months 6 Months 6 Months EA9339 40 TO 80°F 12 Months 6 Months 6 Months EA9314 40 TO 80°F 12 Months 6 Months 6 Months EA9330 40 TO 80°F 12 Months 6 Months 6 Months EA907 40 TO 80°F 12 Months 6 Months 6 Months Devcon F 40 TO 80°F 12 Months 6 Months 6 Months EA934NA 40 TO 80F 12 Months 6 Months 6 Months 380/6 40 TO 80°F 12 Months 6 Months 6 Months A1186B 40 TO 80°F 12 Months 6 Months 6 Months EC2216 40 TO 80°F 12 Months 6 Months 6 Months #10 Fastset 40 TO 80°F 12 Months 6 Months 6 Months 608 Quickset 40 TO 80°F 12 Months 6 Months 6 Months EC880 40 TO 80°F 8 Months 3 Months 3 Months EC847 40 TO 80°F 8 Months 3 Months 3 Months EC1300L 40 TO80F *6 Months 3 Months 3 Months 5452 40 TO 80°F 12 Months 6 Months 6 Months 56431 40 TO 80°F 12 Months 6 Months 6 Months 1636 40 TO 80°F 12 Months 6 Months 6 Months RTV- 157 40 TO 80F 12 Months 6 Months 6 Months RTV 158 40 TO 80°F 12 Months 6 Months 6 Months RTV - 159 40 TO 80°F 12 Months 6 Months 6 Months RTV732 40 TO 80°F 12 Months 6 Months 6 Months RTV 102 40 TO 80°F 12 Months 6 Months 6 Months RTV 103 40 TO 80°F 12 Months 6 Months 6 Months RTV 106 40 TO 80°F 12 Months 6 Months 6 Months RTV 108 40 TO 80°F 12 Months 6 Months 6 Months RTV 109 40 TO 80°F 12 Months 6 Months 6 Months RTV94034 40 TO 80°F 12 Months 6 Months 6 Months Loctite 222 40 TO 80°F 12 Months 6 Months 6 Months Loctite 242 40 TO 80°F 12 Months 6 Months 6 Months Loctite 271 40 TO 80°F 12 Months 6 Months 6 Months Loctite 277 40 TO 80°F 12 Months 6 Months 6 Months Loctite 290 40 TO 80°F 12 Months 6 Months 6 Months Loctite 416 40 TO 80F 12 Months 6 Months 6 Months Loctite 495 40 TO 80°F 12 Months 6 Months 6 Months Loctite 515 40 TO 80°F 12 Months 6 Months 6 Months Loctite 569 40 TO 80°F 12 Months 6 Months 6 Months Loctite 592 40 TO 80°F 12 Months 6 Months 6 Months Loctite 595 40TO 80°F 12 Months 6 Months 6 Months Do not use after three months of storage in the 81°F to 90°F range Do not use after five days of storage above 90°F Table 1-7 (Sheet 1 of 2) 1-20 Revision 2 STORAGE CONDITION EXTEND PRODUCT (TEMPERATURE SN MONTHS SHELF LIFE MONTE S IN DEGREES IN MONTHS FAHENHEIT) ADHESIVES AND CEMENTS (CONTINUED) Loctite 601 40 TO 80°F 12 Months 6 Months 6 Months Loctite 620 40 TO 80°F 12 Months 6 Months 6 Months Loctite 680 40 TO 80°F 12 Months 6 Months 6 Months Loctite 1282 40 TO 80°F 12 Months 6 Months 6 Months Loctite 1283 40 TO 80°F 12 Months 6 Months 6 Months DA-5521 40 TO 80F 12 Months 6 Months 6 Months PS 18 40 TO 80°F 12 Months 6 Months 6 Months PS-30 40 TO 80°F 12 Months 6 Months 6 Months XA-3678 40 TO 80°F 12 Months 6 Months 6 Months XF-3585 40 TO 80F 12 Months 6 Months 6 Months IR- 100-226 40 TO 80°F 12 Months 6 Months 6 Months EC776 40 TO 80°F * 8 Months * 3 Months *3 Months SB and P2 40 TO 801' 12 Months 6 Months 6 Months SEALANTS Pro-Seal 890 40 TO 80°F 6 Months 2 Months 2 Months GC-408 40 TO 80°F 6 Months 2 Months 2 Months PR1422 40 TO 80F 6 Months 2 Months 2 Months PR1440 40 TO 80F 6 Months 2 Months 2 Months GC435 40 TO 80F 6 Months 2 Months 2 Months Pro-Seal 567 40 TO 80°F 6 Months 2 Months 2 Months PR810 40 TO 80°F 6 Months 2 Months 2 Months Pro-Seal 700 40 TO 80°F 6 Months 2 Months 2 Months GC 1900 40 TO 80°F 6 Months 2 Months 2 Months PR366 40 TO 80OF 6 Months 2 Months 2 Months Pro-Seal 735 40 TO 80F 6 Months 2 Months 2 Months Pro-Seal 895 40 TO 80F 6 Months 2 Months 2 Months Pro-Seal 706B 40 TO 80°F 6 Months 2 Months 2 Months PR1321 40 TO 80F 6 Months 2 Months 2 Months GC200 40 TO 80OF 6 Months 2 Months 2 Months RTV-730 40 TO 80°F 6 Months 2 Months 2 Months Pro-Seal 815 40TO 80°F 6 Months 2 Months 2 Months GC402 40 TO 80OF 6 Months 2 Months 2 Months PR- 1005L 40 TO 80F *8 Months *3 Months *3 Months GC-3001 40 TO 80°F *8 Months *3 Months *3 Months 444R 40 TO 80'F *8 Months *3Months *3 Months * Do not use after three months of storage in the 81°F to 90F' range Do not use after five days of storage above 90°F Table I 7 (Sheet 2 of 2) Revision 2 1-21/(1-22 blank) MODEL 182 & T182 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, install- ing 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. Page No. TABLE OF CONTENTS Aerofiche/Manual TABLE OF CONTENTS Aerofiche/Manual GROUND HANDLING ......... . 1B12/2-2 Carburetor Drain Plug Towing ...................... 1B12/2-2 Inspection .................. B20/2-10 Hoisting ....................... 1B14/2-4 Engine Oil ...................... 1B20/2-10 Jacking ....................... B14/2-4 Engine Induction Air Filter ...... 1B21/2-11 Leveling..... .... 1B14/2-4 Vacuum System Filter .......... 1B21/2-11 Weighing ....................... 1B14/2-4 Battery . ....................... 1B22/2-12 Parking ....................... 1B14/2-4 Tires ........................... 1B22/2-12 Tie-Down .................... 1B14/2-4 Nose Gear Shock Strut ........... 1B22/2-12 Flyable Storage Nose Gear Shimmy Dampener .... B22/2-12 (Lycoming Engines) ......... B14/2-4 Hydraulic Brake System ........ 1B22/2-12 Flyable Storage CLEANING ....................... 1B22/2-12 (Continental Engines) ....... B14/2-4 General Description ............. 1B22/2-12 Returning Aircraft to Service .... 1B15/2-5 Windshields and Windows ....... 1B23/2-13 Temporary Storage .............. 1B15/2-5 Materials Required ......... 1B23/2-13 Inspection During Storage ....... 1B16/2-6 Waxing . ................... B23/2-13 Returning Aircraft to Service ..... 1B16/2-6 Preventive Maintenance ..... 1B23/2-13 Indefinite Storage Interior Trim ................ 1B24/2-14 (Lycoming Engines) ......... B16/2-6 Painted Surfaces ............... 1B24/2-14 Indefinite Storage Aluminum Surfaces ............. 1B24/2-14 (Continental Engines) ..... 1B17/2-7 Engine/Engine Compartment .... 1B24/2-14 Inspection During Storage Upholstery and Interior .......... 1C1/2-15 (Lycoming Engines) ......... 1B18/2-8 Propeller ....................... 1C1/2-15 Inspection During Storage Wheels ......................... 1C1/2-15 (Continental Engines) ...... 1B18/2-8 LUBRICATION .................... 1C1/2-15 Returning Aircraft toService ..... 1B18/2-8 General Description ............ 1C112-15 SERVICING ....................... 1B19/2-9 TachometerDrive Shaft ......... C1/2-15 General Description .......... 1B192-9 Wheel Bearings ................. 1C1/2-15 Fuel .... ................... 1B19/2-9 NoseGearTorqueLinks ......... 1C12-15 Use of Fuel Additives For WingFlap Actuator ............ 1C1/2-15 Cold Weather Operation .... 1B19/2-9 Rod End Bearings ............... 1C1/2-15 Fuel Drains ................... 1B19/2-9 GENERAL INSPECTION ........... 1C10/2-24 Revision 3 2-1 MODEL 182 & T1 82 SERIES SERVICE MANUAL 2-1. GROUND HANDLING. 2-2. TOWING. Moving the aircraft by hand is ac- When towing the aircraft, never turn the nose complished by using the wing struts and landing gear wheel more than 29° (degrees) either side of struts as push points. A tow bar attached to the nose center or the nose gear will be damaged. Do gear should be used for steering and maneuvering the not push on control surfaces or outboard em- aircraft on the ground. Beginning with 1982 the tow pennage surfaces. When pushing on the tail- bar is stowed under the rear seat using two clips, cone, always apply pressure at a bulkhead to one attached to the center leg of the seat and one avoid buckling the skin. secured to the floorboard under the left side of the seat. When no tow bar is available, press down at the horizontal stabilizer front spar adjacent to the fuselage to raise the nose wheel off the ground. With the nose wheel clear of the ground, the aircraft can be turned by pivoting it about the main wheels. Figure 2-1. Typical Tow Bar SHOP NOTES: 2-2 MODEL 182 & T182 SERIES SERVICE MANUAL F18200065 & ON ITEM NUMBER TYPE AND PART NUMBER REMARKS A2-170 Basic jack Closed height: 69-1 '2 inches: extended 0QJ #2-109 Leg Extension height: 92 inches (Insert slide tube <2-70 Slide tube extension extension into basic jack). (T) Cessna #2-168 Universal tail stand (See Note 1) Q (3) Built-in jack pad Part of step bracket (See Caution) G) Block 1x4x4 padded with 1/4" rubber 1. Weighted adjustable stand attaches to tie-down ring. 2. Items (1) and (2) are available from the Cessna Supply Division. JACKING PROCEDURE a. Lower aircraft tail so that wing jack can be placed under front spar just outboard of wing strut. b. Raise aircraft tail and attach tail stand to tie-down ring. BE SURE that tail stand weighs enough to keep tail down under all conditions and is strong enough to support aircraft weight. c. Raise jacks evenly until desired height is reached. ICAUTIONi When using the universal jack point. flexibility of the gear strut will cause the main wheel to slide in- board as the wheel is raised, tilting the jack. The jack must be lowered for a second operation. Jacking both main wheels simultaneously with universal jack points is not recommended. NOTE Corresponding points on both upper door sills may be used to level the aircraft laterally. Reference points for longitudinal leveling of the aircraft are two screws on the left side of the tailcone. These are indicated in the above illustration by A · (Also refer to paragraph 2-5) Figure 2-2. Jacking Details 2-3 MODEL 182 & T182 SERIES SERVICE MANUAL 2-3. HOISTING. The aircraft may be lifted with a 2-9. FLYABLE STORAGE. (Airplanes with a hoist of two-ton capacity by using hoisting rings, Lycoming engine). Flyable storage is defined which are optional equipment, or by means of suit- as a maxmum of 30 days non-operational storage able slings. The front sling should be hooked to and/or the first 25 hours of intermittent engine each upper engine mount at the firewall, and the aft operation. sling should be positioned around the fuselage at the first bulkhead forward of the leading edge of the NOTE stabilizer. If the optional hoisting rings are used, a minimum cable length of 60 inches for each cable Lycoming 0-540 Series aircraft engines is required to prevent bending of the eyebolt-type used in the T182 series aircraft are de- hoisting rings. If desired, a spreader jig may be livered from Cessna with MIL-L-6082 fabricated to apply vertical force to the eyebolts. Aviation Grade Mineral Oil. This engine oil should be used to replenish the oil 2-4. JACKING. See figure 2-2 for jacking proced- supply during the first 25 hours of engine ures. operation at the first 25 hour oil change and until a total of 50 hours have accumu- 2-5. LEVELING. Corresponding points on both lated or oil consumption has stabilized. upper door sills may be used to level the aircraft Then use Ashless Dispersant Oil conform- laterally. Reference point for leveling the aircraft ing to MIL-L-22851 in accordance with the longitudinally is the top of the tailcone between the oil chart in figure 2-4. rear window and the vertical fin. Beginning with Serials 18266076 & ON, F18200065 & ON, and T182- During the 30 day non-operational storage or the first 67717 ON, leveling points have been added to the left 25 hours of intermittent engine operation, every sev- side of tailcone at Sta. 139.65 and 171. 65. Remove enth day the propeller shall be rotated by hand without NAS221-7 screws and install suitable studs to support running the engine. After rotating the engine five rev- a level. olutions, stop the propeller 45 to 90 from the posi- tion it was in. If the aircraft is stored outside, tie- 2-6. WEIGHING AIRCRAFT. Refer to Pilot's down in accordance with paragraph 2-8. In addition, Operating Handbook. the pitot tube, static air vents, air vents, openings in the engine cowling, and other similar openings 2-7. PARKING. Parking precautions depend prin- shall have protective covers installed to prevent entry cipally on local conditions. As a general precaution, of foreign material. If at the end of thirty (30) days set parking brake or chock the wheels and install the aircraft will not be removed from storage, the engine controls lock. In sever weather conditions and high shall be started and run. The preferred method would wind, tie down the aircraft as outlined in paragraph be to fly the aircraft for thirty (30) minutes, and up to 2-8 i a hangar is not available. but not exceeding normal oil and cylinder temperatures. 2-8. TIE-DOWN. When mooring the aircraft in the open. head into the wind if possible. Secure control surfaces with the internal control lock and set brakes. Excessive ground operation shall be avoided. Do not set parking brakes when they are NOTES overheated or during cold weather when accumulated moisture may freeze them. Preservation date should be written on pro- a. Tie ropes, cables, or chains to the wing tie- peller tag. down fittings located at the upper end of each wing strut. Secure the opposite ends of ropes, cables, Maintain complete and accurate engine pre- or chains b. Secure a tie-down rope (no chains or cables) to vationof the engine cylinders can be docu- upper strut of the nose gear, and secure opposite end of rope to a ground anchor.necessary. c. Secure the middle of a rope to the tail tie-down ring. Pull each end of rope away at a 45 degreeThe airplane is delivered from Cessna with a angle and secure to ground anchors at each side of Corrosion Preventive Aircraft Engine Oil mix tail. ture. This engine oil is a blend of aviation d. Secure control lock on pilot control column. If grade straight mineral oil and corrosion pre- control lock is not available, tie pilot control wheel ventive compound. This oil should be used for back with front seat belt. the first 25 hours of engine operation. In the e. These aircraft are equipped with a spring-loaded event it necessary to add oil during the steering bungee which affords protection against nor- aviation grade straight mineral oil of the cor- mal wind gusts. However, if extremely high wind gusts are anticipated, additional external locks may be installed. Flyable storage is defined as a maximum of 30 days 2-4 Revision 1 MODEL 182 & T182 SERIES SERVICE MANUAL non-operational storage and can be broken down into a maximum of 90 days. The aircraft is constructed the following two programs. of corrosion resistant alclad aluminum, which will a. Program 1 - engines or cylinders with less than last indefinitely under normal conditions if kept clean, 50 operating hours. however, these alloys are subject to oxidation. The 1. Propeller pull-thru every five days. (See first indication of corrosion on unpainted surfaces is step c.) in the form of white deposits or spots. On painted 2. Fly airplane every 30 days. (See step d.) surfaces, the paint is discolored or blistered. Stor- b. Program 2 - engines or cylinders with more than age in a dry hangar is essential to good preservation 50 operating hours to TBO if not flown weekly. and should be procured, if possible. Varying con- 1. Propeller pull-thru every seven days. (See ditions will alter the measures of preservation. but step c.) under normal conditions in a dry hangar. and for 2. Fly airplane every 30 days. (See step d.) storage periods not to exceed 90 days. the following c. The propeller should be rotated by hand without methods of treatment are suggested. running the engine. For four and six cylinder a. Fill fuel tanks or bays with correct grade of gas- straight drive engines, rotate engine six revolutions, oline. stop propeller 45°to 90 ° from original position. For b. Clean and wax aircraft throughly. six cylinder geared engines, rotate propeller four rev- c. Clean any oil or grease from tires and coat tires olutions and stop propeller 30° to 60 ° from original with a tire preservative. Cover tires to protect position. against grease and oil. d. Either block up fuselage to relieve pressure on spotting the tires. For maximum safety, accomplish engine rota- e. Lubricate all airframe items and seal or cover tion as follows: all openings which could allow moisture and/or dust to enter. 1. Verify magneto switches are OFF. 2. Place throttle in CLOSED position. NOTE 3. Place mixture control in IDLE CUT-OFF position. The aircraft battery serial number is recorded 4. Set brakes and block airplane wheels. in the aircraft equipment list. To assure ac- 5. Leave airplane tie-downs installed and curate warranty records, the battery should be verify that cabin door latch is open. reinstalled in the same aircraft from which it 6. DO NOT stand within arc of propeller was removed. If the battery is returned to blades while turning propeller. service in a different aircraft, appropriate d. The airplane should be flown for thirty (30) record changes must be made and notification minutes, reaching, but not exceeding, normal oil sent to the Cessna Claims Department. and cylinder temperatures. If the aircraft cannot be flown it should be represerved in accordance f. Remove battery and store in a cool, dry place; with paragraph 2-11. (Temporary Storage) or service battery periodically and charge as required. paragraph 2-14. (Idefinite Storage). Ground run- ning is not an acceptable substitute for flying. NOTE NOTE An engine treated in accordance with the fol- If step 2 in each program cannot be accom- lowing may be considered being protected plished on schedule due to weather, mainte- against normal atmospheric corrosion for a nance, etc., pull the propeller through daily period not to exceed 90 days. and accomplish as soon as possible. g. Disconnect spark plug leads and remove upper e. If airplane is stored outside, tie it down in accor- and lower spark plugs from each cylinder. dance with paragraph 2-8. In addition, the pitot tube, static air vents, air vents, openings in the engine NOTES cowling, and other similar openings shall have pro- tective covers installed to prevent entry of foreign On 182 and F182 Series aircraft equipped material. with Continental O-470 Series aircraft engine the preservative oil must be 2-10. RETURNING AIRCRAFT TO SERVICE. After Lubricating Oil - Contact and Volatile, flyable storage, returning the aircraft to service is Corrosion Inhibited. MIL-L-46002, accomplished by performing a thorough pre-flight Grade 1, or equivalent. inspection. At the end of the first 25 hours of engine operation, drain engine oil, clean oil pressure screen On T182 Series aircraft equipped with (or change external oil filter) and service engine with Lycoming 0-540 Series aircraft engine. correct grade and quantity of engine oil. See figure MIL-C-6529, Type I, preservative oil 2-4 and paragraph 2-23 for correct grade of engine must be used. oil. For airplanes with a Continental engine, 2-11. TEMPORARY STORAGE. Temporary storage the preservative oil must be MIL-L-46002, is defined as aircraft in a non-operational status for grade 1, at room temperature. Two preserva- Revision 1 2-5 MODEL 182 & T182 SERIES SERVICE MANUAL tive oils recommended for use in Teledyne h. Install spark plugs and torque to values specified Continental engines for temporary and indefi- in Section 11 & 11A. Connect spark plug leads. nite storage are NOX RUST VCI-105 (Danbert i. Check fuel strainer. Remove and clean filter Chemical Co., 4700 S. Central Avenue, screen if necessary. Check fuel tanks or bays and Chicago, IL.) and PETROTECT VA (Pennsyl- fuel lines for moisture and sediment. Drain enough vania Refining Company. Butler, PA). fuel to eliminate moisture and sediment. h. Using a portable pressure sprayer, spray pre- j. Perform a thorough preflight inspection, then servative oil through the upper spark plug hole of start and warm-up engine. each cylinder with the piston in a down position. Ro- tate crankshaft as each pair of cylinders is sprayed. 2-14. INDEFINITE STORAGE. (Airplanes with a i. After completing step "h, " rotate crankshaft so Lycoming engine.) Indefinite storage is defined as that no piston is at a top position. If the aircraft is aircraft in a non-operational status for an indef- to be stored outside, stop two-bladed propeller so inite period of time. Engines treated in accordance that blades are as near horizontal as possible to pro- with the following may be considered protected vide maximum clearance with passing aircraft. against normal atmosphere corrosion, provided pro- j. Again, spray each cylinder without moving the cedures outlined in paragraph 2-15 are performed at crankshaft, to thoroughly cover all interior surfaces intervals specified. of the cylinder above the piston. a. Operate engine until oil temperature reaches k. Install spark plugs and connect spark plug leads. normal operating range. Drain engine oil sump in 1. Apply preservative oil to the engine interior by accordance with procedures outlined in paragraph spraying approximately two ounces of the preservative 2-23. Close drain valve or install drain plug. oil through the oil filler tube. b. Fill oil sump to normal operating capacity with m. Seal all engine openings exposed to the atmos- corrosion preventative mixture which has been thor- phere, using suitable plugs or non-hygroscopic tape. oughly mixed. Attach a red streamer at each point that a plug or tape is installed. NOTE n. If the aircraft is to be stored outside, perform the procedures outlined in paragraph 2-8. In addi- Corrosion preventative mixture consists of tion, the pitot tube, static source vents, air vents, one part compound MIL-C-6529C, Type I, openings in the engine cowling, and other similar mixed with three parts new lubricating oil openings should have protective covers installed to of the grade recommended for service. prevent entry of foreign material. o. Attach a warning placard to the propeller to the effect that the propeller shall not be moved while the c. Immediately after filling the oil sump with a engine is in storage. corrosion preventative mixture, fly the aircraft for a period of time not to exceed a maximum of 2-12. INSPECTION DURING STORAGE. 30 minutes. a. Inspect airframe for corrosion at least once a d. After flight, with engine operating at 1200 to month. Remove dust collections as frequently as 1500 RPM, and induction air filter removed, spray possible. Clean and wax aircraft as required, corrosion preventative mixture into induction airbox, b. Inspect the interior of at least one cylinder at the rate of one-half gallon per minute. Spray through the spark plug hole for corrosion at least until heavy black smoke comes from exhaust stack. once each month. Then increase the spray until engine is stopped. NOTE Do not move crankshaft when inspecting in- Spraying the mixture too fast can cause a terior of cylinder for corrosion, hydrostatic lock. c. If at the end of the 90 day period, the aircraft is e. Do not rotate propeller after completing step to be continued in non-operational storage, repeat the "d. " procedural steps "g" thru "o" of paragraph 2-11. f. Remove all spark plugs and spray corrosion preventative mixture, which has been preheated 2-13. RETURNING AIRCRAFT TOSERVICE. After (221° to 250°F,) into all spark plug holes to thor- temporary storage, use the following procedures to oughly cover interior surfaces of cylinders. return the aircraft to service. a. Remove aircraft from blocks. Check tires for NOTE proper inflation. b. Check and install battery. To thoroughly cover all surfaces of the c. Check that oil sump has proper grade and quantity cylinder interior, move the nozzle of the of engine oil. spray gun from the top to the bottom of d. Service induction air filter and remove warning the cylinder. If by accident the propeller placard from propeller. is rotated following this spraying, re-spray e. Remove materials used to cover openings. the cylinders to insure an unbroken coverage f. Remove, clean and gap spark plugs. on all surfaces. g. While spark plugs are removed, rotate propeller several revolutions to clear excess rust preventive oil from cylinders. 2-6 Revision 1 MODEL 182 & T182 SERIES SERVICE MANUAL g. Install spark plugs or solid plugs into the lower a. Drain engine oil and refill with MIL-C-6529 Type spark plug holes and install dehydrator plugs in the II. The aircraft should be flown for thirty (30) min- upper spark plug holes. Be sure that dehydrator utes, reaching, but not exceeding normal oil and cyl- plugs are blue in color when installed. inder temperatures. Allow engine to cool to ambient h. Cover spark plug lead terminals with shipping temperature. plugs (AN4060-1). or other suitable covers. b. Remove top spark plug and spray preservative i. With throttle in full open position, place a bag oil (Lubrication Oil - Contact and Volatile Corrosion - of desiccant in the induction air intake and seal Inhibited, MIL-L-46002. Grade 1) at room tempera- opening with moisture resistant paper and tape. ture. through upper spark plug hole of each cylinder j. Place a bag of desiccant in the exhaust tailpipe with piston in approximately bottom dead center posi- and seal openings with moisture resistant tape. tion. Rotate crankshaft as each pair of opposite cylin- k. Seal cold air inlet to the heater muff with mois- ders is sprayed. Stop crankshaft with no piston at top ture resistant tape. dead center. A pressure pot or pump-up type garden 1. Seal engine breather tube by inserting a protex pressure sprayer may be used. The spray head should plug in the breather hose and clamping in place. have ports around circumference to allow complete m. Seal all other engine openings exposed to at- coverage of cylinder walls. mosphere using suitable plugs or non-hygrosoopic tape. NOTE NOTE NOTE The preservative oil must be MIL-L-46002. Attach a red streamer to each location where grade 1, at room temperature. Two preserva- plugs or tapes are installed. Either attach tive oils recommended for use in Teledyne red streamers outside th sealed area with Continental engines for temporary and tape or to the inside of the sealed area with safety wire to prevent wicking of moisture vania Refining Company, Butler. PA). n. Drain corrosion-prventive mixture from en- gine sump and reinstall drain plug or close drain To. Respray each cylinder without rotating crank. move nozzle or spray gun from top to bottom of cyl- inder. The corrosion-preventive mixture is harm- NOTE ful to paint and should be wiped from Type II may be painted surfaces immediately. thoroughly mixin one part compound MIL- C-6529 Type I (Esso RustBan 628, Cos- o. Attach a warning placard on the throttle control moline No. 1223 or equivalent) with three knob to the effect that the engine contains no lubricat- parts new lubricating oil of the grade recom- ing oil. Placard the propeller to the effect that it mended for service (all at room temperature). should not be moved while the engine is in storage. Single grade oil is recommended. p. Prepare airframe for storage as outlined in paragraph 2-11 thru step "f". d. Apply preservative to engine interior by spray- ing MIL-L-46002, Grade 1 oil (approximately two NOTE ounces) through oil filler tube. e. Install dehydrator plugs MS27215-1 or-2, in As an alternate method of indefinite storage, each of the top spark plug holes, making sure that the aircraft may be serviced in accordance each plug is blue in color when installed. Protect and with paragraph 2-11, providing the aircraft support spark plug leads with AN-4060 protectors. is run up at maximum intervals of 90 days f. DO NOT rotate propeller after completing and then reserviced per paragraph 2-11. step e". g. If engine is equipped with a pressure type car- 2-14A. INDEFINITE STORAGE. (Airplanes with a buretor, preserve this component by the following Continental engine.) Indefinite storage is defined as method. Drain carburetor by removing the drain and aircraft in a non-operational status for an indef- vapor vent plugs from regulator and fuel control inite period of time. Engines treated in accordance unit. With mixture control in "Rich" position, inject with the following may be considered protected lubricating oil, grade 1010. into fuel inlet at a pres- against normal atmosphere corrosion, provided pro- sure not to exceed 10 psi until oil flows from vapor cedures outlined in paragraph 2-15 are performed at vent opening. Allow excess oil to drain, plug inlet and intervals specified. tighten and safety the drain and vapor vent plugs. Wire throttle in open position, place bags of desiccant in the intake and seal opening with moisture resis- tant paper and tape or a cover plate. Revision 1 2-7 MODEL 182 & T182 SERIES SERVICE MANUAL h. If carburetor is removed from engine, place a bag engine should be replaced. of desiccant in throat of carburetor air adapter. Seal b. The cylinder bores of all engines prepared for adapter with moisture resistant paper and tape or a indefinite storage should be resprayed with corrosion- cover plate. preventive mixture every six months, or more fre- i Place a bag of desiccant in the exhaust pipes and quently if bore inspection indicates corrosion has start- seal the openings with moisture resistant tape. ed earlier than six months. Replace all desiccant and j. Seal cold air inlet to heater muff with moisture dehydrator plugs. Before spraying, engine should be resistant tape to exclude moisture and foreign objects inspected for corrosion as follows: Inspect interior of at k. Seal engine breather by inserting a dehydrator least one cylinder on engine through the spark plug MS27215-2 plug in breather hose and clamping in hole. If cylinder shows start of rust, spray cylinder place corrosion-preventive oil and turn prop over six times, 1 Seal all other engine openings exposed to atmo- then respray all cylinders. Remove at least one rocker sphere. using suitable plugs or non-hygroscopic tape. box cover from engine and inspect valve mechanism. m. Attach a red streamer to each place on the en- gine where bags of desiccant are placed. Either attach 2-16. RETURNING AIRCRAFTTO SERVICE. After red streamers outside of sealed area with tape or to in- indefinite storage, use the following procedure to re- side of sealed area with safety wire to prevent wicking turn the aircraft to service. of moisture into sealed area. a. Remove aircraft from blocks. Check tires for n. Drain corrosion-preventive mixture from engine correct inflation. sump and reinstall drain plug or close drain valve. b. Check and install battery. c. Remove all materials used to seal and cover NOTE openings. d. Remove warning placards posted at throttle The corrosion-preventive mixture is and propeller. harmful to paint and should be wiped e. Remove and clean engine oil screen, then re- from painted surfaces immediately, install and safety. On aircraft equipped with an exter- nal oil filter, install new filter. o. Attach a warning placard on the throttle control f. Remove oil sump drain plug or open drain knob to the effect that the engine contains no lubricat- valve and drain sump. Install or close drain valve and ing oil. Placard the propeller to the effect that it safety. Service engine with oil per figure 24. should not be moved while the engine is in storage. g. Service and install the induction air filter. p. Prepare airframe for storage as outlined in para- graph 2-11., steps "a." through "f.". NOTE 2-15. INSPECTION DURING STORAGE. (Air- The corrosion-preventive mixture will planes with a Lycoming engine.) Aircraft in indefinite mix with the engine lubricating oil, so storage shall be inspected as follows: flushing the oil system is not necessary. a. Inspect cylinder protex plugs each seven days. Draining the oil sump will remove enough b. Change protex plugs if their color indicates an of the corrosion-preventive mixture. unsafe condition. c. If the protex plugs have changed color in one half WARNING of the cylinders, all desiccant material in the engine should be replaced with new material. d. Respray the cylinder interiors with corrosion On aircraft with a Continental engine, preventive mixture every six months and replace des- upon returning the aircraft to service do iccant and protex plugs. not use the corrosion-preventive oil refer- enced in paragraph 2-14. NOTE h. Remove dehydrator plugs and spark plugs or Before spraying, inspect the interior of plugs installed in spark plug holes. Rotate propeller one cylinder for corrosion through the several revolutions by hand to clear corrosion- spark plug hole and remove at least one preventive mixture from cylinders. rocker box cover and inspect the valve i. Clean, gap and install spark plugs and rotate mechanism. propeller by hand though the compression strokes of all the cylinders to check for possible liquid lock. 215A. INSPECTION DURING STORAGE. (Air- Torque plugs the value specified in Section 11 or 11A. planes with a Continental engine.) Aircraft in indefi- j. Check fuel strainer. Remove and clean filter nite storage shall be inspected as follows: screen. Check fuel cells and fuel lines for moisture and a. Aircraft prepared for indefinite storage should sediment. Drain enough fuel to eliminate moisture have cylinder dehydrator plugs visually inspected ev- and sediment. ery 15 days. The plugs should be changed as soon as k. If the carburetor has been preserved with oil, their color indicates unsafe conditions of storage. If the drain it by removing the drain and vapor vent plugs dehydrator plugs have changed color in one-half or from the regulator and fuel control unit. With mix- more of the cylinders, all desiccant material on the ture control in "Rich" position, inject service type 2-8 Revision 3 MODEL 182 & T182 SERIES SERVICE MANUAL gasoline into fuel inlet at a pressure not to exceed 10 The introduction of alcohol or EGME compound into psi until all of the oil is flushed from the carburetor. the fuel provides two distinct effects: 1) it absorbs Reinstall carburetor plugs and attach fuel line. the dissolved water from the gasoline and 2) alcohol l. Perform a thorough preflight inspection, then has a freezing temperature depressant effect. start and warm up engine. m. Thoroughly clean and test fly aircraft. Alcohol, if used, is to be blended with the fuel in a concentration of 1% by volume. Concentrations 2-17. SERVICING. greater than 1% are not recommended since they can be detrimental to fuel tank materials. 2-18. GENERAL DESCRIPTION. Servicing require- The manner in which the alcohol is added to the fuel ments are shown in figure 2-4. The following para- is significant because alcohol is most effective when graphs supplement this figure by adding details not it is completely dossolved in the fuel. To insure included in the figure. proper mixing the following is recommended: 1. For best results the alcohol should be added 2-19. FUEL. Fuel tanks should be filled immediately during the fueling operation by pouring the alcohol after flight to lessen condensation in the tanks and lines. directly on the fuel stream issuing from the fueling Tank capacities are listed in figure 1-1. The recom- nozzle. mended fuel grade to be used is given in figure 2-4. 2. An alternate method that may be used is to gallon capacity) and then transfer this mixture to the DURING ALL FUELING PROCEDURES, FIRE tank prior to the fuel operation. FIGHTING EQUIPMENT MUST BE AVAI- Any high quality isopropyl alcohol may be used, LABLE. TWO GROUND WIRES FROM DIF- such as: FERENT POINTS ON THE AIRPLANE TO Anti-icing fluid (MIL-F-5566) or SEPARATE APPROVED GROUND STAKES Isopropyl alcohol.(Federal Spec. TT-I-735a). SHALL BE USED TO PREVENT ACCIDEN- Ethylene glycol monomethyl ether (EGME) com- TAL DISCONNECTION OF ONE GROUND pound in compliance with MIL-I-27686 or Phillips WIRE. ENSURE THAT FUELING NOZZLE PFA-55MB, if used, must be carefully mixed with IS GROUNDED TO THE AIRPLANE. fuel in concentrations not to exceed 0.15% by volume. Tie-down rings should be used as grounding points for all grounding wires during refuel- Mixing of the EGME compound with the fuel ing procedures. is extremely important because concentra- tion in excess of that recommended (0.15 2-20. USE OF FUEL ADDITIVES FOR COLD percent by volume maximum) will result in WEATHER OPERATION. Strict adherence to recom- detrimental affects to the fuel tanks, such mended preflight draining instructions will eliminate as deterioration of protective primer and any free water accumulations from the tank sumps. sealants and damage to O-rings and seals While small amounts of water may still remain in in the fuel system and engine components. solution in the gasoline, it will normally be consumed Use only blending equipment that is recom