100 - SERIES SERVICE MANUAL

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Al-l CROSS REFERENCE LISTING OF POPULAR NAME VS. MODEL NUMBERS AND SERIALS All aircraft, regardless of manufacturer, are certificated under model number designations. However, popular names are often used for marketing purposes. To provide a consistent method of referring to the various aircraft, model numbers will be used in this publication unless names are required to differentiate between versions of the same basic model. The following table provides a cross reference listing of popular name vs. model numbers. MODEL SERIALS POPULAR NAME YEAR MODEL BEGINNING ENDING 150 STANDARD 1963 150C 15059701 15060087 150 TRAINER, or 1964 150D 15060088 15060772 150 COMMUTER 1965 150E 15060773 15061532 1966 150F 15061533 15064532 1967 150G 15064533 15067198 1968 150H 15067199 -FRENCH-150 .1966. F150F F150-0001 F150-0067 1967 F 50G F 150-0068 F150-0219 1968 F150H F150-0220 172 or SKYHAWK 1963 172D 17249545 17250572 1964 172E 17250573 17251822 1965 172F 17251823 17253392 1966 172G 17253393 17254892 1967 172H 17254893 17256512 1968 1721 17256513 FRENCH 172 1963 F172D F172-0001 F172-0018 1964 F172E F172-0019 F172-0085 1965 F172F F172-0086 F172-0179 1966 F172G F172-0180 F172-0319 1967 F172H F172-0320 F172-0446 1968 F172H F172-0447 172 POWERMATIC r 1963 P172D P17257120 P17257188 SKYHAWK POWERMATIC FRENCH POWERMATIC 1963 FP172D FP172-0001 FP172-0003 180 1963 180F 18051184 18051312 1964 180G 18051313 18051445 1965 180H 18051446 18051607 1966 180H 18051608 18051774 1967 180H 18051775 18051875 1968 180H 18051876 182 or SKYLANE 1963 182F 18254424 18255058 1964 182G 18255059 18255844 1965 182H 18255845 18256684 1966 182J 18256685 18257625 1967 182K 18257626 18258505 1968 182L 18258506 ARGENTINE 182 1966 A182J A182-0001 A182-0056 1967 A182K A182-0057 A182-0096 1968 A182L A182-0097 185 SKYWAGON 1963 185B 185-0513 185-0653 (260 H. P. Engine) 1964 185C 185-0654 185-0776 1965 185D 185-0777 185-0967 1966 185E 185-0968 185-1149 185 SKYWAGON 1966 A185E 185-0968 185-1149 (300 H. P. Engine) 1967 A185E 185-1150 185-1300 1968 A185E 185-1301 ii FOREWORD This manual contains factory recommended procedures and in- structions for ground handling, servicing and maintaining Cessna 100-Series aircraft. These include the Models 150, 172, P172, 180, 182, 185, and A185. The Model F172, which is manufactured by Reims Aviation S.A., Reims (Marne) France, is identical to the 172 except that it is powered by an 0-300-D engine, manufactured under license by Rolls Royce, Crewe, England. All 172 information in this manual pertains to the F172 as well. Likewise, the Model FP172 is identical to the P172 except that it is powered by a GO-300-E Rolls Royce engine, and the Model F150 is identical to the 150 except that it is powered by an 0-200-A Rolls Royce engine. The Model A182, which is manufactured by Directorate National of Fabrication and Investigation Aeronautical, Cordoba, Argentina, is identical to the Model 182. All 182 information in this manual pertains to the A182 as well. Besides serving as a reference for the experienced mechanic, this book also covers step-by-step procedures for the less exper- ienced man. This manual should be kept in a handy place for ready reference. If properly used, it will better enable the mechanic to maintain Cessna 100-Series aircraft and thereby establish a repu- tation for reliable service. The information in this book is based on data available at the time of publication, and is supplemented and kept current by service letters and service news letters published by Cessna Aircraft Com- pany. These are sent to all Cessna Dealers so that they have the latest authoritative recommendations for servicing Cessna airplanes. Therefore, it is recommended that Cessna owners utilize the know- ledge and experience of the factory-trained Dealer Service Organi- zation. In addition to the information in this Service Manual, a group of vendor publications are available from the Cessna Service Parts Center which describe complete disassembly, overhaul, and parts breakdown of some of the various vendor equipment items. A list- ing of the available publications is issued periodically in service letters. iii SECTION 1 GENERAL DESCRIPTION 1-1. GENERAL DESCRIPTION. Cessna single- tional equipment. Beginning with the Model 180G, engine aircraft described in this manual are similar the pilot's seat only is standard, while optional seat- in that all models are high-wing monoplanes, em- ing arrangements include two front seats only, two ploying patented spring-steel main landing gear front seats with one, two-place rear seat, and two struts, horizontally opposed air-cooled engines, front seats with two, two-place rear seats of stowable and all-metal semi-monocoque airframe construc- design. Beginning with 1967, the center stowable tion. seat is replaced with two individual stowable seats. The four-place version may be furnished with either 1-2. MODEL 150 SERIES. The Model 150 is utility or deluxe fabrics, and the rearmost stowable equipped with a tricycle landing gear, a four-cylinder seat may also be used with the four-place version as Continental engine, and a fixed-pitch propeller. Two- a child's seat. place seating is standard, and a two-place child's seat may be installed as optional equipment. The Model 1-6. MODEL 182 SERIES. The Model 182 is equip- 150D and on features a "wrap around" rear window, ped with a tricycle landing gear, a six-cylinder which replaces the rear side windows used on the Continental engine, and a constant-speed propeller. Model 150C. Beginning with the Model 150F, a Four-place seating is standard, and a two-place swept-back fin and rudder is used. child's seat may be installed as optional equipment. The Model 182 features rear side windows, a "wrap 1-3. MODEL 172 SERIES. The Model 172 is around" rear window, and a swept-back fin and rud- equipped with a tricycle landing gear. Four-place der. seating is standard, and a two-place child's seat may be installed as optional equipment. The Model 1-7. MODEL 185 SERIES. The Model 185 is equip- 172 features rear side windows, a "wrap around" ped with a tailwheel-type landing gear, a fuel-injected rear window, and a swept-back fin and rudder. six-cylinder Continental engine, and a constant-speed Prior to 1968, the Model 172 is powered by a six- propeller. The pilot's seat only is standard, while cylinder Continental engine, and a fixed-pitch pro- optional seating arrangements include two front seats peller. Beginning with 1968, the aircraft is powered only, two front seats with one, two-place rear seat, by a four-cylinder "Blue-Streak" (Lycoming) engine, and two front seats with two, two-place rear seats of and a fixed-pitch propeller. stowable design. Beginning with 1967, the center stowable seat is replaced with two individual stow- 1-4. MODEL P172. The Model P172 is equipped able seats. The four-place version may be furnished with a tricycle landing gear, a six-cylinder geared with either utility or deluxe fabrics, and the rear- Continental engine, and a constant-speed propeller. most stowable seat may also be used with the four- Four-place seating is standard, and a two-place place version as a child's seat. child's seat may be installed as optional equipment. The Model P172 features rear side windows, a 1-8. Leading particulars of each model, with di- "wrap-around" rear window, and a swept-back fin mensions based on gross weight, are given in the and rudder. following charts. If these dimensions are used for constructing a hangar or computing clearances, re- 1-5. MODEL 180 SERIES. The Model 180 is equip- member that such factors as nose strut inflation, ped with a tailwheel-type landing gear, a six-cylinder tire pressures, tire sizes, and load distribution Continental engine, and a constant-speed propeller. may result in some dimensions that are considerably On the Model 180F, four-place seating is standard, different from those listed. and a two-place child's seat may be installed as op- 1-1 MODEL 150 DESIGN GROSS WEIGHT (150C) .................. 1500 lb DESIGN GROSS WEIGHT (150D & on) ................ 1600 lb FUEL CAPACITY (Total) ..................... 26 gal Optional . . . . . .. . . . . . . . . . . . . . . . . ... 38 gal OIL CAPACITY ......................... 6 qt ENGINE MODEL (Refer to Section 12 for Engine Data) ........ CONTINENTAL 0-200 Series PROPELLER (Fixed Pitch). .......... 69" McCAULEY MAIN WHEEL TIRES (Standard thru 150E) .......... ... 5.00 x 5, 4-Ply Rating Pressure ........................ 30 psi MAIN WHEEL TIRES (Standard 150F & on) ............. 6.00 x 6, 4-Ply Rating Pressure . ......................... 21 psi MAIN-WHEEL_TIRES (Optional thru 150E) ........... . 6.00 x 6, 4-Ply Rating Pressure ............. .............. 21-psi NOSE WHEEL TIRE (Standard) ................. . 5.00 x 5, 4-Ply Rating Pressure .......................... 30 psi NOSE WHEEL TIRE (Optional) . ................ .15 x 6.00 x 6, 4-Ply Rating Pressure .. ............ . ..... ...... 35 ps NOSE GEAR STRUT PRESSURE (Strut Extended) ........... 20 psi WHEEL ALIGNMENT Camber . .. . ... . .. . .. .. . ..... .. ... . 4 ° to 6 ° Toe-In .......................... . 0" to .06" AILERON TRAVEL Up .... ......................... 20 ° , +2°-0° Down . ........... ............ ... . 14°, +2°-0 ° WING FLAP TRAVEL (Thru 150E) ......................... 0, 10-, 20°, 30, 40°, 2° (150F & on) ....................... . 0 ° to 40 ° ± 2° RUDDER TRAVEL (Measured perpendicular to hinge line) Right (Thru 150E) . .............. ..... .16 ° 1° Left (Thru 150E) ..... ......... ......... 16 ° * 1° Right (150F & on) ................... .. .. 23 ° , +0-2 Left (150F & on) ...................... 23 ° , +0-2 ELEVATOR TRAVEL Up ............................. 25 ° 1° Down ............................ 15 ° 1° ELEVATOR TRIM TAB TRAVEL Up ............................. 10° 1° Down ............................ 20 ° 1 ° PRINCIPAL DIMENSIONS Wing Span (Thru 150E) ... ....... ........ ...... 33'6" (150F & on) ....................... 32' 8-1/2" Length With Large Spinner (Thru 150E) .............. 22'0" With Small Spinner (Thru 150E) .......... .... 21'7" With Large Spinner (150F & on) . ............. 23'9" With Small Spinner (150F & on) ........ ..... 23'0" Fin Height (Maximum with Nose Gear Depressed) (Rotating Beacon Installed on Fin, thru 150E) ...... . 7'10" (Rotating Beacon Installed on Fin, 150F) ......... 8'9" (Flashing Beacon Installed on Fin, 150G & on) ....... 8' 7-1/2" Track Width (Thru 150E) ................... 6'5" Track Width (150F & on) ................... 6' 6-1/2" BATTERY LOCATION (150C) .......... ............. ..... Aft of Baggage Compartment (150D & on) ...... ... .... .... .... .... Firewall MODEL 172 DESIGN GROSS WEIGHT ..................... 2300 lb FUEL CAPACITY (Total) (1963 thru 1968 - Except P172) ................ 42 gal. (P172) . . . . . . . . . . . . . . . . . . . . . . . . . . . 52 gal. USABLE FUEL (1963 tbru 1967 - Except P172) ................ 39 gal. (P172) Refer to Owner's Manual. ............... 41-1/2 gal. (1968 Model 1721) ...................... 38 gal. PROPELLER (Fixed Pitch) ................ . 76" McCAULEY MAIN WHEELTIRES ....................... 6.00 x 6, 4-ply rating Pressure .................. .... . . 24 psi NOSE WHEEL TIRE (Standard) .................. 5.00 x 5, 4-ply rating Pressure . ... ... .. ... . .... . . . .. ... . 26 psi NOSE WHEEL TIRE (Optional) .. ................ 6.00 x 6, 4 -ply rating Pressure .......... .... ....... . 26 psi NOSE GEAR STRUT PRESSURE (Strut Extended) Pressure (Thru 172G) ................... 35 psi Pressure (172H & on) ............... .45 psi WHEEL ALIGNMENT Camber . . . . . . . . . . . . . . . . . . . . . . . . . . 3 to 5 Toe-in . . . .. . . . . . . .. . . .. . . . . . . . . . .0" to .06" AILERON TRAVEL Up . ... . . . . . . . . . . . . .. . .... . . . . . . 20*01 ° Down............ ................ 150*10 WING FLAP TRAVEL Manual .......................... 0, 10° , 20 ° , 30 ° , 40 ° , ± 2 Electric .......................... 0° to 40 ° ± 2 RUDDER TRAVEL (Measured perpendicular to Hinge Line) Right ................... ......... 17°44'±1 *Left ............................ 17°44'.10 ELEVATOR TRAVEL Up . .......... . ............ ..... 28 ° , +1° -0 Down. ............................ 23 ° , +1° -0O ELEVATOR TRIM TAB TRAVEL Up . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 ° , +1° -00 Down .............. . ............. 13", +10 -0 0 PRINCIPAL DIMENSIONS Wing Span .... .................... 36'2" Tail Span ......................... . 11'4" Length (Thru 172F) ..................... 26'6" Length (172G & on) ..................... 26'11" Fin Height (Maximum with Nose Gear Depressed) (Rotating Beacon Installed on Fin) ....... .... 8'11" (Flashing Beacon Installed on Fin) ............. 8'9-1/2" Track Width. ................. ..... . 7'2" BATTERY LOCATION ...................... Firewall 1-3 MODEL P172 (1963) DESIGN GROSS WEIGHT ................... 2500 lb FUEL CAPACITY (Total) .................... 52 gal OIL CAPACITY ........... ........... . 10 qt ENGINE MODEL (Refer to Section 12 for Engine Data) ....... CONTINENTAL GO-300 Series PROPELLER (Constant Speed) .................. 84" McCAULEY MAIN WHEEL TIRES .................. ... 6.00x 6, 4-ply rating Pressure ......................... 24 psi NOSE WHEEL TIRE (Standard) ................ 5.00 x 5, 4 -ply rating Pressure ......................... 26 psi NOSE WHEEL TIRE (Optional) ................. 6.00 x 6, 4-ply rating Pressure ...................... . . 26 psi NOSE GEAR STRUT PRESSURE (Strut Extended). ......... 35 psi WHEEL ALIGNMENT Camber .......................... 3 to 5- Toe-in .......................... ' to. 06" AILERON TRAVEL Up ........................... 20*l1' Down ..... ...................... 15'%l1 WING FLAP TRAVEL .................... i 0, 10', 20', 30', 40', *2 RUDDER TRAVEL (Measured perpendicular to Hinge Line) Right ............. . 17.44'±1' Left. . . . . . . . . . . . .. .. . . . . .. .. . . .. 17-44 1' ELEVATOR TRAVEL Up. .. .................. 26', +1'-o' Don.23-, +1 -0Down .. ... .... . .. . ..... ..... .. .. 23 , +1'-0' ELEVATOR TRIM TAB TRAVEL Up . . . . . . . . . . . . . . . . . . . . . . 2 ', +1 - Down ................ . . 13', +1'-0- PRINCIPAL DIMENSIONS Wing Span .. ...... . '. . . . . . .... .. .... 31 2" Tail Span 0.. . " Length. . . . .... 26' 6" Fin Height (Maximum with Nose Gear Depressed and Rotating Beacon Installed on Fin) ........... . 8' 11" Track Width . ....................... BATTERY LOCATION .......................... Aft of Baggage Comprtment 1-4 MODEL 180 DESIGN GROSS WEIGHT (180F) ... .............. 2150 lb DESIGN GROSS WEIGHT (180G & on) ................ 26001lb FUEL CAPACITY (Total) ..................... 6.5 gal Optional ... ........... .......... . 84 gal OIL CAPACITY ....... . .. ........... .. 12 qt ENGINE MODEL (Refer to Section 12 for Engine Data) ........ CONTINENTAL 0-470 Series PROPELLER (Constant Speed) ............... . 82" McCAULEY MAIN WHEEL TIRES (Standard) ................. 6.00 x 6, 6-Ply rating Pressure . . . . . . . . . . . . . . . . . . .. . . ..... 30 psi MAIN WHEEL TIRES (Optional, Prior to 180G) ......... . . 00 x 6, 4-Ply rating Pressure . .. ... . . ... .. .... .... . .. . .23 psi MAIN WHEEL TIRES (Optional) .................. 8.00 x 6, 6-Ply rating Pressure ................... .... .. .23 psi TAILWHEEL TIRE (Thru Serial No. 18051262) .......... .8.00 S.C., 6-Ply rating Pressure ... ... . . ....... .. . .... .. . .35 psi TAILWHEEL TIRE (Serial No. 18051263 & on) ..... ..... 8.00 x 2. 80, 4-Ply rating Pressure ......................... .*55 psi to 65 psi maximum WHEEL ALIGNMENT Camber ........................... 4° to 6° Toe-In ........................... 0 to . 12" AILERON TRAVEL Up ........ .... ............. 20 ° ± 2 ° Down ............. .............. 14° ± 2 ° WING FLAP TRAVEL ..................... 0 ° , 10 ° , 20 ° , 32 ° , 38 ° , +2 ° -1° RUDDER TRAVEL (Measured perpendicular to hinge line) Right ........................... 24 ° , +0 ° -1 ° Left ...................... 24 ° , +0 ° -1° ELEVATOR TRAVEL (With stabilizer full down) Up ............................ 25 ° + 1 ° Down . . . . . . . . . . . . . . . . . . . . . . . . . . 23 ° ± 1 STABILIZER TRAVEL Up ........................ .... 45' ± 15 Down .......... ........... 8°45 ' ± 15' PRINCIPAL DIMENSIONS Wing Span .......................... 36'2" Tail Span .................. ........ 0'10" Length (Thru 1966). ............ ...... . 25'6" (1967 and on) ...................... 25'9" Fin Height (Rotating Beacon Installed on Fin) ............. .7'10-1/2" (Flashing Beacon Installed on Fin) ............ 7'9" Track Width ............... ....... . 7'8" BATTERY LOCATION ...................... ft of Baggage Compartment *55 psi to 65 psi maximum (2300 lb to 2800 lb normal operating loads). 1-5 MODEL 182 DESIGN GROSS WEIGHT .................... 2800 lb FUEL CAPACITY (Total) ..................... 65 gal Optional .............. ............ 84 gal OIL CAPACITY ......... ... . . ......... 12 qt ENGINE MODEL (Refer to Section 12 for Engine Data) ........ CONTINENTAL 0-470 Series PROPELLER (Constant Speed) .................. 82" McCAULEY MAIN WHEEL TIRES (Standard) ................. 6.00 x 6, 6-Ply rating Pressure ........................... 32 psi MAIN WHEEL TIRES (Optional) ................. .. 8.00 x 6, 6-Ply rating Pressure ........................... 25 psi to 35 psi NOSE WHEEL TIRE (Standard). ................. 5.00 x 5, 6-Play rating Pressure (Thru 182J) ................... .. 32 psi Pressure-(182K & on)...... ........ .... . . 50 psi NOSE WHEEL TIRE (Optional) ................... . 6 00-x 6,-4-P-lyrating Pressure (Thru 182J) ................... 20 psi to 29 psi Pressure (182K & on) ..................... 30 psi NOSE GEAR STRUT PRESSURE (Strut Extended) (Thru 182J) ......................... 50 psi (182K & on) ................. ...... 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 (Electrically Operated) ............ 0 ° to 40 ° , +1 ° -2 ° RUDDER TRAVEL (Measured perpendicular to hinge line) Right ............................ 27013 ' * 1 Left . . .. . . .. .. . . .. . . .... .. . ..... 27°13 ' * 1° ELEVATOR TRAVEL Up . ........................... 26 ° * 1 Down ............................ 17 1° ELEVATOR TRIM TAB TRAVEL Up . ........................... 25 ° 2° Down ............................ 15° * 1° PRINCIPAL DIMENSIONS Wing Span .......................... 36'2" Tail Span (Thru 182G) ....................... 10'10" (182H & on) ....................... 11'8" Length (Thru 182G) ....................... 27'4" (182H thru 182J) ................... .. 27'10" (182K & on) ................. ..... 28'-1/2" Fin Height (Maximum with Nose Gear Depressed) (Rotating Beacon Installed on Fin) ............. 9'0" (Flashing Beacon Installed on Fin) ............. 8'10-1/2" Track Width ......................... 7'11-1/2" BATTERY LOCATION ...................... Aft of Baggage Compartment 1-6 MODELS 185 & A185 DESIGN GROSS WEIGHT (Thru 1965 Model 185D) .............. .............. 3200 lb (1966 and 1967 Models 185E & A185E). ............. 3300 lb (1968 Model A185E) ...................... 3350 lb FUEL CAPACITY (Total) ..................... 65 gal Optional .......................... . 84 gal OIL CAPACITY .............. ....... . 12 qt ENGINE MODEL (Refer to Section 12 for Engine Data) 260 HP (Thru 185E) ...................... CONTINENTAL IO-470 Series 300 HP (A185E and on) .................. . CONTINENTAL IO-520 Series PROPELLER (Constant Speed) 260 HP (Thru 185E) ...................... 88" McCAULEY 300 HP (A85E and on) .................... 82" McCAULEY MAIN WHEEL TIRES (Standard) .... ............. 6.00 x 6, 6-Ply rating Pressure ...................... 35 psi MAIN WHEEL TIRES (Optional) .................. 8.00 x 6, 6 -Ply rating Pressure ................. .... 25 psi TAILWHEEL TIRE (185B) . . .............. ... 10.00 x 3.50, 4-Ply rating Pressure .................. 45 psi TAILWHEEL TIRE (185C and on) ................ 8.00 x 2. 80, 4-Ply rating Pressure ......................... *55 psi to 70 psi (max) WHEEL ALIGNMENT Camber ........................ 4° to 6 ° Toe-In ........................... 0" to. 12" AILERON TRAVEL Up ...... ............... .20° +2° Down ....................... .... 14 ° + 2° WING FLAP TRAVEL ...................... 0, 10, 20 ° , 32 ° , 38 ° , +2 ° -1 ° RUDDER TRAVEL (Measured perpendicular to hinge line) Right .......................... 24 ° , +0 -1 ° Left . 24 ° , +0 -1 ° ELEVATOR TRAVEL (With stabilizer full down) Up ......... .................. . 25 ° 1° Down . .... .. . . ..... .... . . .. ... .. 23 ° 1° STABILIZER TRAVEL Up (Thru 185E) ...................... .0°45 ' + 15' (A185E and on) ................ . .. 0°45', +45'-15' Down ............................ 8°30' 15' PRINCIPAL DIMENSIONS Wing Span ....... ............ .36'2" Tail Span ................... ....... 0'10" Length (Thru 1966) ..................... 25'6" (1967 and on) ...................... 25'9" Fin Height (Rotating Beacon Installed on Fin) ............. 7'10-1/2" (Flashing Beacon Installed on Fin) ............. 7'9" Track Width ....................... 7'8" BATTERY LOCATION .................... Aft of Baggage Compartment *55 psi to 70 psi maximum (2300 lb to 3200 lb normal operating loads). If the 10-inch tire has been replaced with the 8-inch tire, these pressures also apply to the Model 185B. 1-7 22.12 31. 75 192.0 44.12 0.00 1.3 56.8769 MODE 5 OD THRU 150E 173.41 200.37 11.00 36.00 49.69 0.00 18.35 56.69 95.00 133.31 Fig .Rer-en \ MODEL150 - AND.150E V " \/r 173.41 200.37 / \ 71.44 76.44 11.00 38.00 49.69 [_-----------------------I 173.41 200. 37 11.00 36.00 49.69 Figure 1-1. Reference Stations - Model 150 (Sheet 1 of 2) 1-8 18.50 56.69 0.00 70.69 200 37 8.37 36.00 76.44 150F & ON 49.69 71.44 SHOP NOTES: Figure 1-1. Reference Stations - Model 150 (Sheet 2 of 2) 1-9 1-10 23.62 0.00 17.00 65.33 124.00 156.00 185.50 209.00 92.00 8.12 45.00 79.00 56. 70 MODEL 182H & ON Figure 1-3. Reference Stations - Model 182 1-11 23.62 39.00 REAR SIDE WINDOW NOT IN- STALLED ON MODEL 180F 8.12 44.00 90.00 Figure 1-4. Reference Stations - Models 180 and 185 1-12 1-12 TORQUE VALUES IN POUND-INCHES FINE THREAD SERIES STANDARD TYPE NUTS SHEAR TYPE NUTS BOLT SIZE Alternate Alternate (See Note 1) (See Note 2) Values MS20364, AN320 Values AN310 AN316, AN7502 AN320 (See Note 4) (See Note 4) 10-32 20-25 20-28 12-15 12-19 1/4-28 50-70 50-75 30-40 30-48 5/16-24 100-140 100-150 60-85 60-106 3/8-24 160-190 160-260 95-110 95-170 7/16-20 450-500 450-560 270-300 270-390 1/2-20 480-690 480-730 290-410 290-500 9/16-18 800-1000 800-1070 480-600 480-750 5/8-18 1100-1300 1100-1600 660-780 660-1060 3/4-16 2300-2500 2300-3350 1300-1500 1300-2200 7/8-14 2500-3000 2500-4650 1500-1800 1500-2900 1-14 3700-5500 3700-6650 2200-3300 2200-4400 1-1/8-12 5000-7000 5000-10000 3000-4200 3000-6300 1-1/4-12 9000-11000 9000-16700 5400-6600 5400-10000 COARSE THREAD SERIES BOLT SIZE STANDARD TYPE NUTS SHEAR TYPE NUTS (See Note 1) (See Note 3) MS20364, AN320, AN316 8-32 12-15 7-9 10-24 20-25 12-15 1/4-20 40-50 25-30 5/16-18 80-90 48-55 3/8-16 160-185 95-100 7/16-14 235-255 140-155 1/2-13 400-480 240-290 9/16-12 500-700 300-420 5/8-11 700-900 420-540 3/4-10 1150-1600 700-950 7/8-9 2200-3000 1300-1800 1-8 3700-5000 2200-3000 1-1/8-8 5500-6500 3300-4000 1-1/4-8 6500-8000 4000-5000 NOTES: (1) AN3, AN23, AN42, AN173, MS20004, NAS334, NAS464 Series Bolts; AN502, AN503, NAS220 and NAS517 Series Screws. (2) AN310, AN315, AN345, AN362, AN363, MS20365, AN366, NAS679, "EB," "1452," "Z1200, " "UWN" and other self-locking nuts. (3) AN310, AN340, MS20365, AN366 and other self-locking anchor nuts. (4) When using AN310 and AN320 castellated nuts where alignment between bolt and cotter pin holes is not reached using normal torque values, use alternate torque values or replace nut. These torque values are derived from oil-free cadmium-plated threads, and are recommended for all installation procedures contained in this book except where other values are stipulated. They are not to be used for checking tightness of installed parts during service. 1-13 SECTION 2 GROUND HANDLING, SERVICING, LUBRICATION, AND INSPECTION TABLE OF CONTENTS GROUND HANDLING ........................................... Towing .............................................................. Hoisting............................................................. Jacking ............................................................. Parking ............................................................. Tie-Down .......................................................... Hangar Storage................................................ Outside Storage ............................................... Extended Storage............................................. Returning Airplane to Service .......................... Leveling ............................................................ SERVIC ING ........................................................... Fuel................................................................... Fuel Drains....................................................... Engine Oil......................................................... Engine Induction Air Filters .............................. Vacuum System Filters .................................... Battery .............................................................. Tires.................................................................. Nose Gear Shock Strut .................................... Nose Gear Shimmy Dampener (Models 150 and 172) ........................................................... Nose Gear Shimmy Dampener (Model 182 Prior to 1967).................................................... Shimmy Dampener (1967 Model 182 and On).................................................................. Hydraulic Brake System s............................... Castering Axle................................................ Oxygen Cylinder............................................. Face M asks.................................................... CLEANING .......................................................... W indshields and Windows ............................. Plastic Trim ..................................................... Aluminum Surfaces........................................ Painted Surfaces............................................ Engine Com partment ..................................... Upholstery and Interior................................... Propellers ....................................................... W heels............................................................ Page 2-2 2-2 2-3 2-3 2-3 2-3 2-3 2-3 2-3 2-5 2-5 2-5 2-5 2-5 2-5 2-7 2-8 2-8 2-8 2-8 2-9 2-9 2-9 2-10 2-10 2-10 2-10 2-10 2-10 2-10 2-10 2-10 2-1 0A 2-10A 2-10A 2-10A Page LUBRICATION.................................................. 2-10A Nose Gear Torque Links.............................. 2-10A Rudder Trim Wheel Threads (Model 185 2-1 0A Series).......................................................... 2-10A Tachometer Drive Shaft ............................... 2-10A Wheel Bearing Lubrication ........................... 2-10A Castering Axle.............................................. 2-10A INSPECTION.................................................... 2-19 Airplane File ........................................ 2-19 Engine Runup ........................................ 2-19 Scope and Preparation (Continental Engine)......................................................... 2-20 Scope and Preparation ("Blue Streak Lycoming") ........................................ 2-20 Propeller....................................................... 2-20 Engine Compartment ................................... 2-20 Fuel System ........................................ 2-22 Landing Gear ........................................ 2-22 Airframe........................................................ 2-23 Control Systems........................................... 2-23 COMPONENT TIME LIMITS............................. 2-25 G eneral........................................................ 2-25 Cessna-Established Replacement Time Limits ............................................................ 2-25 Supplier-Established Replacement Time Lim its ............................................................ 2-26 © Cessna Aircraft Company Revision 1 2-1 Aug 4/2003 2-1. GROUND HANDLING. 2-2. TOWING. Moving the airplane by hand is accomplished by using the wing struts and landing gear struts as push points. A tow bar attached to the nose gear should be used for steering and maneuvering the airplane. 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 airplane can be turned by pivoting it about the main wheels. CAUTION: WHEN TOWING THE AIRPLANE, NEVER TURN THE NOSE WHEEL MORE THAN 30 DEGREES EITHER SIDE OF CENTER OR THE NOSE GEAR WILL BE DAMAGED. DO NOT PUSH ON CONTROL SURFACES OR OUTBOARD EMPENNAGE SURFACES. WHEN PUSHING ON THE TAILCONE, ALWAYS APPLY PRESSURE AT A BULKHEAD TO AVOID BUCKLING THE SKIN. B1838 USE TOW BAR CAREFULLY TO AVOID SCARRING FNISH ON SPEED FAIRING Figure 2-1. Typical Tow Bars © Cessna Aircraft Company 2-2 Revision 1 Aug 4/2003 MASONITE BLOCK 4" SQUARE AND 1" THICK WITH DEPRESSION FOR JACK IN UNDER- SIDE. PAD TOP SIDE WITH 1/4" RUBBER. ADJUSTABLE STAND ATTACHED TO TIE-DOWN RING (PART NO. 10004-98) AVAILABLE FROM THE CESSNA SERVICE PARTS CENTER 1. Wing jacks must be short enough to slide under front spar of wing just outboard of wing strut, must extend far enough to raise wheels off ground, and must be of adequate strength. 2. Jacks short enough to slide under Model 150 wings, with leg extensions or adapter stands for other models with higher wings, are recommended. 3. 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 on it. 4. Jacking one wing is not recommended due to landing gear flexibility. However, if adequate precautions against slipping are taken, it is permissible. 5. Lowering the tail on tricycle gear aircraft and pushing up at the front spar of the wing will gain additional height for initially positioning jacks. 6. Operate jacks evenly until desired height is reached. 7. The universal jack point may be used to jack one wheel. Do not use the brake casting as a jack point. Flex brake line away from gear spring when using the universal jack point. 8. The nose may be raised by weighting down the tail. Place weight on each side of stabilizer, next to fuselage. 9. On conventional gear aircraft, place a suitable stand under the tailwheel to raise the tail until the aircraft is approximately level before jacking the wings. Figure 2-2. Jacking Details Revision 1 2-2A/2-2B © Cessna Aircraft Company Aug 4/2003 B1840 2-3. HOISTING. The airplane may be lifted with a a. Rotate the propeller by hand at least four rev- hoist of two-ton capacity by using hoisting rings, olutions every few days to maintain an oil film on which are optional equipment on all airplanes ex- the internal parts of the engine. cept the Model 150, or by means of suitable slings. The front sling should be hooked to each upper engine mount at the firewall, and the aft sling should be positioned around the fuselage at the first bulkhead Ignition switch must be OFF when rotating forward of the leading edge of the stabilizer. If the propeller by hand. optional hoisting rings are used, a minimum cable length of 60 inches for each cable is required to pre- b. Keep fuel tanks full to retard moisture condensa- vent bending of the eyebolt-type hoisting rings. If tion in the tanks. desired, a spreader jig may be fabricated to apply c. Keep battery fully charged to prevent the electro- vertical force to the eyebolts. lyte from freezing in an unheated hangar. 2-4. JACKING. Refer to figure 2-2 for jacking pro- 2-8. OUTSIDE STORAGE. Short-term storage of an cedures. aircraft requires secure tie-down procedures in CAUTION accordance with paragraph 2-6, as well as the pre- cautions listed in paragraph 2-7. In addition, the When using the universal jack point, flexibility pitot tube, air vents, openings in the engine cowling, of the gear strut will cause the main wheel to and other similar openings should have protective slide inboard as the wheel is raised, tilting covers installed if rain, sleet, snow, or blowing dust the jack. The jack must then be lowered for are anticipated. a second jacking operation. Jacking both wheels simultaneously with universal jack 2-9. EXTENDED STORAGE. Although the aircraft points is not recommended. is constructed of corrosion resistant Alclad alumi- num which will last indefinitely under normal con- 2-5. PARKING. Parking precautions depend prin- ditions if kept clean, these alloys are subject to cipally on local conditions. As a general precaution, oxidation. The first indication of corrosion on un- it is wise to set the parking brake or chock the painted surfaces is the form of white deposits or wheels, and install the control lock. In severe spots. On painted surfaces, the paint is discolored weather and high wind conditions, tie down the air- or blistered. Storage in a dry hangar is essential to plane as outlined in paragraph 2-6 if a hangar is good preservation and should be procured if possible. not available. varying conditions will alter the measures of preser- vation, but under normal conditions in a dry hangar 2-6. TIE-DOWN should be accomplished in antici- and for storage periods not to exceed three months, pation of high winds. Tie down airplane as follows: the following methods of treatment are suggested: a. Tie ropes or chains to the wing tie-down fittings a. Fill fuel tanks with gasoline. located at the upper end of each wing strut. Secure b. Clean and wax aircraft thoroughly. the opposite ends of the ropes or chains to ground c. Clean any oil or grease from tires and coat anchors. tires with a tire preservative. Cover tires to pro- b. Secure a tie-down line through the nose gear tie- tect against grease and oil. down ring. On tricycle gear aircraft without a nose d. Block up fuselage to remove weight from tires. gear tie-down ring, use a rope (no chains or cables) to secure the upper strut (exposed portion of engine NOTE mount on the Model 150) to ground anchors. c. On tricycle gear aircraft, secure the middle of Tires will take a set, causing them to become a length of rope to tail tie-down ring. Pull each end out-of-round, if an aircraft is left parked for of rope away at a 45° angle and secure to ground more than a few days. For this reason, a anchors at each side of tail. On aircraft with con- stored aircraft should not have its weight on ventional tailgear, tie down the tailwheel. Some the tires. Model 180 and 185 aircraft are equipped with a tie- down ring at the tailgear. e. Lubricate all airframe items and seal or cover d. Install surface control locks between wing tip all openings. and aileron, and over fin and rudder. f. Remove battery and store in a cool dry place; e. Install control lock on pilot's control column if service battery periodically and charge as required. available; if control lock is not available, tie pilot's g. Inspect for corrosion at least once a month and control wheel back with front seat belt. remove dust collections as frequently as possible. Clean and wax as required. 2-7. HANGAR STORAGE. An aircraft stored in a hangar will require little attention. The following If the engine has been in temporary storage and will operations will maintain it in a serviceable condition. be stored and not operated for a period of from 30 to 60 days, the engine should be treated for extended NOTE storage. The engine is treated for storage prior to airframe treatment. If the aircraft is to be stored for a period of more than 30 days, see paragraph 2-9. a. Operate engine until oil temperature reaches 2-3 normal operating range. Drain engine oil sump e. Remove, clean, and install oil filter screens. completely, and install sump drain plug. Install new filter element on aircraft equipped with b. (LYCOMING ENGINE). Fill oil sump to normal external filter. capacity with corrosion-preventive mixture meeting specification MIL-C-6529C (Esso "Rust Bane 628" or NOTE equivalent) which has been preheated to 220°F (104°C). Preheat the preservative mixture to 200-220°F (CONTINENTAL ENGINE). Fill oil sump to (93-104°C) for all spraying operations described normal capacity with corrosion-preventive oil in the following. (Continental Motors Corporation recommends Cosmoline No. 1223, supplied by E. F. Houghton & f. Disconnect ignition harness and remove all spark Co., 305 W. Lehigh Ave., Philadelphia, Pa.), which plugs. Spray each cylinder through the spark plug has been pre-heated to 225°F (107. 2°C). holes with two ounces of preservative mxiture while c. Start and operate engine at 1200-1500 rpm for the engine is turned five full revolutions for each cyl- four to five minutes. inder. Store spark plugs. g. Remove and store the exhaust pipes and spray CAUTIONi the exhaust port and exhaust valve of each cylinder with piston 1/4 turn before top dead center on the Do not exceed maximum allowable engine -cylinder-exhaust-stroke temperatures. h. Spray each cylinder through spark plug holes without engine rotation. Install spark plugs or solid d. Stop engine and drain preservative mixture from plugs in lower spark plug holes; install cylinder oil sump. The preservative mixture may be saved dehydrator plugs in upper spark plug holes, and in- and re-used. stall metal covers over cylinder exhaust ports. i. Cover spark plug cable terminals with tape, and NOTE cover all other engine and accessory vents, and other openings with a vapor-proof covering material. The corrosive-preventive mixture is harmful j. Attach a warning placard on the throttle control to paint and should be wiped from painted to the effect that the engine contains no lubricating surfaces immediately. oil. Placard the propeller to the effect that it should -i + - . , :.^^^ - WIH CONTROL SURFACE LOCKS TAIL ELASTIC WHEEL WHEEL STRAP WIN Figure 2-3. Tie- DOWN !. . - WITH CONTROL LOCK OR SAFET Figure 2-3. Tie-Down 2-4 not be rotated while the engine is in storage. 2-11. LEVELING. Corresponding points on both k. Perform steps "a" thru "g" after the engine is upper door sills may be used to level all models prepared for storage. laterally. References for longitudinal leveling are: 1. The preceding is applicable only for storage Model 150C (1963) - Top edge of fuselage splice periods not exceeding 60 days. Should it become plate. necessary to extend the storage period beyond the Models 150D & on, 172, P172, and 182 - Top 60 day limit, the storage procedure shall be repeated. of tailcone between rear window and vertical fin. 2-10. RETURNING AIRCRAFT TO SERVICE. After Models 180 and 185 - Lower surface of upper short-term storage, returning the aircraft to service door sill is accomplished by completing a thorough pre-flight inspection. After an extended storage, use the fol- 2-12. SERVICING. lowing procedure to return the aircraft to service. a. Remove aircraft from blocks and check tires 2-13. Servicing requirements are shown in the Ser- for proper inflation. Check for proper nose gear vicing Chart (figure 2-4). The following paragraphs strut inflation. supplement this figure by adding details not included b. Check and install battery. in the chart. c. Remove all materials used to seal and cover openings. 2-14. FUEL. Fuel tanks should be filled immediate- d. Remove warning placards posted at throttle ly after flight to lessen moisture condensation. Tank control and on propeller. capacities are listed in Section 1. The recommended e. Remove and clean engine oil screens, then in- fuel is 80/87 minimum, aviation grade gasoline, for stall and safety screens. If an external filter is all except the Model 185 and A185 Series airplanes, installed, install new element, which require 100/130 aviation grade gasoline. f. Drain engine oil sump. Install and safety drain plug, then service engine with correct grade and 2-15. FUEL DRAINS are located at various points in quantity of engine oil. the fuel systems to provide for drainage of water and sediment. Each aircraft is equiped with a fuel NOTE strainer drain valve, fuel line or selector valve drain plugs or drain valves, and fuel tank sump drain plugs The corrosive-preventive mixture will mix or drain valves. In many airplanes, the fuel strainer with engine lubricating oil, so flushing the drain valve may be operated by a control located at oil system is not necessary. Draining the the instrument panel. During the 1967 model year oil sump will remove enough of the corrosive- the strainer drain control was removed from the preventive mixture. However, after 25 hours instrument panel and relocated adjacent to the engine of operation the engine oil should be drained oil dipstick. Access to the strainer drain control is while the engine is hot. This will remove any through the engine oil dipstick access door. Remove residual corrosive-preventive mixture that drain plugs and open strainer drain at the intervals may be present in the oil system. specified in figure 2-4 to drain water and sediment from the fuel system. Also, during daily inspection g. Remove dehydrator plugs installed in upper of the fuel strainer, if any water is found in the fuel spark plug holes, and remove spark plug or solid strainer, there is a possibility that wing tank sumps, plugs installed in lower spark plug holes. Rotate lines, and accumulator tank contain water. There- propeller several revolutions to clear corrosion- fore, all fuel drain plugs should be removed and preventive mxiture from the cylinders and to saturate all water drained from the fuel system. the interior of the engine with clean lubricating oil. 2-16. ENGINE OIL. Check engine lubricating oil NOTE with the oil dipstick five to ten minutes after the engine has been stopped. The aircraft should be in The corrosion-preventive mixture is harmful as near a level position as possible when checking to paint and should be wiped from painted engine oil, so that a true reading is obtained. Engine surfaces immediately. oil should be drained while the engine is still hot and the nose of the aircraft should be raised slightly for h. Remove cover plates and install exhaust pipes. more positive draining of any sludge which may have i. Clean, gap, and install spark plugs and connect collected in the engine oil sump. spark plug leads. j. Check fuel strainer and drain carburetor. Re- Engine oil should be changed every four months even move and clean fuel strainer filter screen if neces- though less than the specified hours have accumulated. sary. Check fuel tanks and fuel lines for moisture Reduce these intervals for prolonged operation in condensation and sediment and drain enough fuel to dusty areas, in cold climates where sludging conditions eliminate any moisture. exist, or where short flights and long idle periods k. Service induction air filter, are encountered, which cause sludging conditions. 1. Perform a thorough pre-flight inspection, then Always change oil, clean oil screens, and/or change start and warm-up engine. external filter element whenever oil on the dipstick appears dirty. 2-5 Detergent or ashless dispersant oil conforming to craft equipped with an external oil filter, the engine Lycoming Specification No. 301E for the "Blue oil change intervals may be extended to 100-hour Streak" (Lycoming) engine or conforming to Contin- intervals providing the external filter element is ental Motors Specification MHS-24A for the Contin- changed AT 50-HOUR INTERVALS. ental engine shall be used in these engines. Multi- viscosity oil may be used to extend the operating CONTINENTAL ENGINE. On aircraft equipped with temperature range, improve cold engine starting and an external oil filter, change engine oil and filter lubrication of the engine during the critical warm-up element at 50-hour intervals. On aircraft NOT period, thus permitting flight through wider ranges of equipped with an external oil filter, change engine climate change without the necessity of changing oil. oil and clean the oil screen EVERY 25 HOURS. The multi-viscosity grades are recommended for air- craft engines subjected to wide variations in ambient NOTE air temperatures when cold starting of the engine must be accomplished at temperatures below 30 ° F. Detergent or ashless dispersant oil conforming to Continental Motors Specification MHS-24A NOTE MUST be used in all Model A185 series air- craft and in the 1966 and 1967 Model 172 series New or newly overhauled engines should be aircraft. However straight-mineral-oil-may- operated on aviation grade straight mineral be used in all other models equipped with Con- oil until the first oil change, or until oil con- tinental engines, detergent or ashless disper- sumption has stabilized. If a detergent or sant oil conforming to Continental Motors ashless dispersant oil is used in a new engine, Specification MHS-24A is recommended. On or a newly overhauled engine, high oil con- models where a straight mineral oil has been sumption might possibly be experienced. The used continuously, converting to detergent or anti-friction additives of some detergent and ashless dispersant oil is not recommended ashless dispersant oil will retard the "break- except at engine overhaul or replacement. in" of the piston rings and cylinder walls. This condition can be avoided by the use of Oil capacities for the different models are given in straight mineral oil until normal oil con- the following chart. To minimize loss of oil through sumption is obtained, then change to detergent the breather, fill to specified oil level on dipstick for or ashless dispersant oil. The aircraft is normal operation (flight of less than three hours). delivered from Cessna with straight mineral For extended flight, fill to full mark on dipstick. Do oil of the correct viscosity. not operate with less than minimum-for-flight quan- tities listed. If an external oil filter is installed, one "BLUE STREAK" (Lycoming) ENGINE. On aircraft additional quart of oil is required when filter element NOT equipped with an external oil filter, change oil is changed. and clean oil screens at 50-hour intervals. On air- ALL ENGINES MODEL CAPACITY CAPACITY (TOTAL NORMAL MINIMUM (TOTAL) WITH FILTER) OPERATION FOR FLIGHT 150 6 7 5 4 172 8 9 7 6 P172 10 11 8 6 180 12 13 10 9 182 12 13 10 9 185 12 13 10 9 SHOP NOTES: 2-6 When adding or changing oil, use aviation grade oil in accordance with the following chart. CONTINENTAL ENGINES ABOVE 40 ° F BELOW 40 ° F MODEL GRADE MODEL *GRADE 150 SAE 40 150 SAE 10W30 or SAE 20 172 (Prior to 172G) SAE 40 172 (Prior to 172G) SAE 10W30 or SAE 20 P172 SAE 40 P172 SAE 10W30 or SAE 20 172G and on SAE 50 172G and on SAE 10W30 or SAE 30 180 SAE 50 180 SAE 10W30 or SAE 30 182 SAE 50 182 SAE 10W30 or SAE 30 185 SAE 50 185 SAE 10W30 or SAE 30 A185 SAE 50 A185 SAE 10W30 or SAE 30 *Multi-viscosity oil with a range of SAE 10W30 is recommended for improved cold weather starting. However, since this oil is also a detergent oil, it should not be used in those models where a straight mineral oil is being used, except as noted in the preceding text. "BLUE STREAK" (Lycoming) ENGINE MODEL GRADE AMBIENT TEMPERATURE 1721 and on SAE 50 ABOVE 60°F SAE 30 0° to 70°F SAE 20 BELOW 10°F *SAE 10W30 *Multi-viscosity oil with a range of SAE 10W30 is recommended for improved cold weather starting and lubrication of the engine during the critical warm-up period. Detergent or ashless dispersant oil, conforming to Lycoming Specification No. 301E MUST BE USED. 2-17. ENGINE INDUCTION AIR FILTER. The induc- However, when spares stocks are exhausted. tion air filter keeps dust and dirt from entering the new filters ordered from Cessna Service Parts induction system. The value of maintaining the air Center will be the dry type with an improved filter in a good clean condition can never be over- element. The 1968 Model 1721 is equipped stressed. More engine wear is caused through the with the dry type filter. use of a dirty or damaged air filter than is generally believed. The frequency with which the filter should To service the flock-coated, oiled filter, proceed as be removed, inspected, and cleaned will be deter- follows: mined primarily by aircraft operating conditions. A a. Remove filter from aircraft. good general rule however, is to remove, inspect, b. Wash filter thoroughly, soiled face down in and clean the filter at least every 50 hours of engine solvent (Federal Specification P-S-661 or equiv- operating time and more frequently if warranted by alent). operating conditions. Some operators prefer to hold c. Drain and dry filter, then dip flock-coated spare induction air filters at their home base of screen filter in the same grade of oil used in the operation so that a clean filter is always readily engine and allow excess oil to drain off. available for use. Under extremely dusty conditions, d. Be sure air box is clean, inspect filter and re- daily servicing of the filter is recommended. Two place if damaged. types of filters are used. One is a flock-coated, oiled filter and the other is a dry, paper-media NOTE filter. A damaged filter may have broken filtering NOTE panels or the flock coating may be missing from the filtering panels, which will allow The Model 172-series prior to 1968, and all unfiltered air to enter the induction system. Model 150 aircraft are equipped with a flock- Any filter that appears doubtful shall be re- coated, oiled filter when it leaves the factory. placed. 2-7 e. Install filter in air box with gasket on aft face of e. Be sure induction air box and air inlet ducts to filter frame and with air flow arrow on filter pointed the engine are clean, inspect and install new filter in the correct direction. if filter is damaged. f. Install filter. Be sure gasket on aft face of NOTE filter is in good condition. Keeping a supply of clean, serviced filters NOTE on hand will speed up air filter servicing. Refer to figure 2-5. An optional air filter installation for the alter- nate air source (SK 172-21) is available for To service the dry type filter, proceed as follows: Model 172 Series aircraft through the 1966 a. Remove filter by releasing the quick-release Model year. Refer to paragraph 12-24A. fasteners. 2-17A. VACUUM SYSTEM FILTERS keep dust and NOTE dirt from entering the vacuum operated flight instru- ments. On airplanes NOT equipped with the central Use care to-prev-ent-damage-to-filter-element air_filter system (see Section 16), the filters in the when cleaning filter with compressed air. instruments should be replaced every 100-lours-of- operation and whenever erratic or sluggish responses b. Clean filter by blowing with compressed air are noted with normal suction gage readings. On air- (not over 100 psi) from direction opposite of normal planes equipped with vacuum systems containing a air flow. Arrows on filter case indicate direction of central air filter, change the filter every 500 hours normal air flow. of operation and whenever suction gage reading drops below 4.6 inches of mercury. Change the gyro in- CAUTION| strument air filters, when equipped with central air filter, whenever the gyro instruments are overhauled. Do not use solvent or cleaning fluids to wash Beginning with the 1967 models and on, different gyro filter. Use only a water and household deter- instruments are used in the vacuum system. These gent solution when washing the filter. instruments are not equipped with internal filters. The new instruments are smaller with a beveled box- c. After cleaning as outlined in step "b" filter may type case. Also, these instruments and related be washed, if necessary, in a solution of warm water plumbing are used as service parts. and a mild household detergent. A cold water solu- tion may be used. 2-18. BATTERY servicing Involves adding dis- tilled water to maintain the electrolyte even with the NOTE horizontal baffle plate at the bottom of filler holes, checking the battery cable connections, and neutral- The filter assembly may be cleaned with cor- izing and cleaning off any spilled electrolyte or pressed air a maximum of 30 times or it may corrosion. Use bicarbonate of soda (baking soda) be washed a maximum of 20 times. The fil- and water to neutralize electrolyte or corrosion. ter should be replaced after 500 hours of en- Follow with a thorough flushing with water. Brighten gine operating time or one year, whichever cables and terminals with a wire brush, then coot should occur first. An exception to this is with petroleum jelly before connecting. The battery the dry filter formerly used on Models 180, box also should be checked and cleaned if any 182, and 185 (Cessna Part No. 0750038, with- corrosion is noticed. Distilled water, not acid or out a dash number), which should be replaced "rejuvenators," should be used to maintain after 300 hours or one year. Cessna Part electrolyte level. Check the battery every 50 hours No. 0750038-4 contains an improved element; (or at least every 30 days), oftener in hot weather. this filter should be replaced after 500 hours See Section 17 for detailed battery replacement and or one year. However, the filter should be re- testing. placed at any time it is damaged. A damaged filter, may have sharp or broken edges in the 2-19. TIRES should be maintained at the air pres- filtering panels which would allow unfiltered sures specified in the charts in Section 1. When air to enter the induction system. Any filter checking tire pressure, examine tire for wear, cuts, that appears doubtful shall be replaced. bruises, and slippage. Remove oil and grease with soap and water. d. After washing, rinse filter with clear water until rinse water draining from filter is clear. Allow NOTE water to drain from filter and dry with compressed air (not over 100 psi). Recommended tire pressures should be main- tained. Especially in cold weather, remember NOTE that any drop in temperature of the air inside a tire causes a corresponding drop in pressure. The filtering panels of the filter may become distorted when wet, but they will return to 2-20. NOSE GEAR SHOCK STRUT. The nose gear their original shape when dry. strut requires periodic checking to ensure that the strut is filled with hydraulic fluid and is inflated to 2-8 the correct air pressure. When servicing the nose If the dampener has a filler plug, refill as follows: gear strut, proceed as follows: a. Remove dampener from airplane. a. Remove valve cap and release air pressure. b. Remove filler plug and drain all hydraulic fluid b. Remove valve housing assembly. from the dampener, then fill with the amount of c. Telescope strut to its shortest length and fill to hydraulic fluid specified on the placard. bottom of filler hole with hydraulic fluid. d. Lift nose of airplane, extend and compress strut NOTE several times to expel any entrapped air, then lower nose of airplane and repeat step "c." Fill the smaller dampener with 52cc of fluid e. Install valve housing assembly and inflate strut and the larger one with 74cc of fluid. with nose wheel off ground (strut extended). Shock strut pressures are listed in Section 1. c. Install and safety filler plug and reinstall damp- ener on airplane. NOTE If the dampener does not have a filler plug, refill as Keep the nose gear shock strut, especially the follows: exposed portion of the strut piston, wiped off a. Remove dampener and pull the fitting end of the with a clean dry cloth to remove dust and dampener shaft to its travel limit. Drain all fluid grit which may cut the seals in the strut barrel. from the dampener. Do not wipe the strut with hydraulic fluid, since b. Fill through the opposite end with the amount of this tends to collect even more dust and grit. hydraulic fluid specified on the placard, while holding the dampener vertical. 2-21. NOSE GEAR SHIMMY DAMPENER (MODELS 150 AND 172). The shimmy dampener should be NOTE serviced at least every 100 hours. The shimmy dampener must be filled completely with fluid, free Fill the smaller dampener with 52cc of fluid of entrapped air, to serve its purpose. Two types and the larger one with 74cc of fluid. of shimmy dampeners are used, one of which must be removed to check fluid level and refill. If the c. Push the shaft upward slowly to seal off the dampener has a filler plug, refill as follows: filler hole, and reinstall the dampener on the air- a. Remove filler plug, and turn nose gear in the plane. Be sure to keep shaft protruding through the O direction that places the dampener piston at the end filler hole until dampener is installed. opposite the filler plug. d. Observe "note" in preceding paragraph. b. While holding in this position, fill dampener with hydraulic fluid and install and safety filler plug. 2-21B. NOSE GEAR SHIMMY DAMPENER (1967 MODEL 182 AND ON). The Model 182 is equipped If the dampener does not have a filler plug, refill as with a different shimmy dampener which contains a follows: compensating meahcnism within the hollow piston a. Remove dampener and pull the fitting end of the rod for thermal expansion and contraction of the dampener shaft to its travel limit. hydraulic fluid. The shimmy dampener must be b. Fill through the opposite end with hydraulic fluid, filled completely with hydraulic fluid, free of en- while holding the dampener vertical. trapped air with the compensating piston bottomed. c. Push the shaft upward slowly to seal off the filler Beginning with serial number 18258404 and on, the hole, and reinstall the dampener on the airplane. Be filling procedure is changed. It is recommended sure to keep the shaft protruding through the filler that aircraft prior to serial number 18258404 have hole until the dampener is installed, the excessive fluid removed from the compensating mechanism as follows: NOTE a. Remove shimmy dampener from the aircraft. b. While holding the shimmy dampener in a verti- Keep shimmy dampener, especially the ex- cal position with the filler plug pointed upward, posed portions of the dampener piston shaft, loosen the filler plug. clean to prevent collection of dust and grit c. Allow the spring to bottom out the floating which could cut the seals in the dampener piston inside the shimmy dampener rod. barrel. Wipe dampener and shaft with a d. When the fluid stops flowing, insert a length of clean cloth. Do not use a cloth saturated stiff wire through the air bleed hole in the setscrew with hydraulic fluid, since this tends to at the end of the piston rod until it touches the float- collect even more dust and grit. ing piston. The depth of insertion should be 3-13/16 inches. 2-21A. NOSE GEAR SHIMMY DAMPENER (MODEL 182 PRIOR TO 1967). The shimmy dampener should NOTE be serviced at least every 100 hours. Two sizes of shimmy dampeners are used. The shimmy dampener If the wire insertion is less than 3-13/16 inches, on the Model 182 is subjected to more heat than other the floating piston is lodged in the shaft. If the models, and a small airspace is needed for fluid ex- wire cannot be used to free the piston, the rod pansion. Both shimmy dampeners must be removed assembly and piston should be replaced. for filling, since each must be filled with a specific amount of hydraulic fluid. 2-9 e. Tighten filler plug and install shimmy dampener electrostatic charge which attracts dust. Oil and in aircraft. grease may be removed by rubbing lightly with a soft cloth moistened with Stoddard solvent. After To service the shimmy dampener proceed as follows: washing, the plastic windshield and windows should a. Remove shimmy dampener from aircraft. be cleaned with an aircraft windshield cleaner. Ap- b. Remove filler plug from dampener. ply the cleaner with soft cloths, and rub with moder- c. Submerge dampener in clean hydraulic fluid and ate pressure. Allow the cleaner to dry, then wipe it work dampener shaft in and out to remove any en- off with soft flannel cloths. A thin, even coat of wax, trapped air and ascertain complete filling. polished out by hand with clean soft flannel cloths, will fill in minor scratches and help prevent further NOTE scratching. Do not use a canvas cover on the wind- shield or windows unless freezing rain or sleet is Be sure that the shimmy dampener and hydrau- anticipated since the cover may scratch the plastic lic fluid at 70 ° to 80 ° while filling the shimmy surface. dampener. d.Install-filler-plug-before-removing-dampener- from hydraulic fluid. Do not use gasoline, alcohol, benzene,-acetone, carbon tetrachloride, fire extinguisher fluid, NOTE de-icer fluid, lacquer thinner or glass window cleaning spray. These solvents will soften Be sure to keep the shaft protruding through and craze the plastic. barrel at filler end, until the dampener is installed. 2-28. PLASTIC TRIM. The instrument panel, plastic trim, plastic control wheels, and control e. Wash dampener in cleaning fluid and wipe dry knobs need only be wiped off with a damp cloth. Oil with a cloth. and grease on the control wheel and control knobs f. Install shimmy dampener on aircraft. can be removed with a cloth moistened with Stoddard solvent. Volatile solvents, such as mentioned in NOTE paragraph 2-27, must never be used since they soften and craze the plastic. Keep shimmy dampener, especially the exposed portion of the dampener shaft, wiped clean with 2-29. ALUMINUM SURFACES require a minimum of a clean, dry cloth to remove dust and grit which care, but should never be neglected. The airplane may cut the seals in the dampener barrel. Do may be washed with clean water to remove dirt, and not wipe the shaft with hydraulic fluid, since with carbon tetrachloride or other non-alkaline this tends to collect even more dirt and grit. grease solvents to remove oil and/or grease. Household type detergent soap powders are effective 2-22. HYDRAULIC BRAKE SYSTEMS should be cleaners, but should be used cautiously since some checked and the brake master cylinder refilled as of them are strongly alkaline. Many good aluminum required at least every 100 hours with hydraulic fluid, cleaners, polishes, and waxes are available from Bleed the brake system of entrapped air whenever commercial suppliers of aircraft products. there is a spongy response to the brake pedals. 2-30. PAINTED SURFACES. The painted exterior 2-22A. CASTERING AXLE. Check and refill if re- surfaces of the airplane, under normal conditions, quired per paragraph 5-22H, at each 100-hour in- require a minimum of polishing or buffing. Approx- spection. imately 15 days are required for acrylic or lacquer paint to cure completely and approximately 90 days 2-23. OXYGEN CYLINDER. Refer to Section 15. are required for vinyl paint to cure completely; in most cases, the curing period will have been com- 2-24. FACE MASKS. Refer to Section 15. pleted prior to delivery of the airplane. In the event that polishing or buffing is required within the curing 2-25. CLEANING. period, it is recommended that the work be done by an experienced painter. Generally, the painted sur- 2-26. Keeping the aircraft clean is important. Be- faces can be kept bright by washing with water and sides maintaining the trim appearance of the airplane, mild soap, followed by a rinse with water and drying cleaning lessens the possibility of corrosion and with cloths or a chamois. Harsh or abrasive soaps makes inspection and maintenance easier. or detergents which cause corrosion or make scratch- es should never be used. Remove stubborn oil and 2-27. WINDSHIELD AND WINDOWS should be clean- grease with a cloth moistened with Stoddard solvent. ed carefully with plenty of fresh water and a mild After the curing period, the airplane may be waxed detergent, using the palm of the hand to feel and dis- with a good automotive wax. A heavier coating of lodge any caked dirt or mud. A sponge, soft cloth, wax on the leading edges of the wings and tail and or chamois may be used, but only as a means of on the engine nose cap will help reduce the abrasion carrying water to the plastic. Rinse thoroughly, encountered in these areas. then dry with a clean moist chamois. Do not rub the plastic with a dry cloth since this builds up an 2-10 2-31. ENGINE COMPARTMENT cleaning is essen- 2-34. WHEELS should be washed off periodically tial to minimize any danger of fire, and for proper and examined for corrosion, chipped paint, and inspection of components. The engine and engine cracks or dents in the wheel castings. Sand smooth, compartment may be washed down with a suitable prime, and repaint minor defects. solvent, then dried thoroughly. 2-35. LUBRICATION. CAUTION 2-36. Lubrication requirements are shown on the Particular care should be given to electrical Lubrication Chart (figure 2-4). Before adding grease equipment before cleaning. Solvent should to grease fittings, wipe off all dirt. Lubricate until not be allowed to enter magnetos, starters, new grease appears around parts being lubricated, alternators, voltage regulators, and the like. and wipe off excess grease. The following para- Hence, these components should be protected graphs supplement this figure by adding details. before saturating the engine with solvent. Any oil, fuel, and air openings on the engine 2-37. NOSE GEAR TORQUE LINKS. The nose gear and accessories should be covered before torque links should be lubricated at least every 50 washing the engine with solvent. Caustic hours, or oftener when operating in dusty areas. cleaning solutions should be used cautiously Under extremely dusty conditions, daily lubrication and should always be properly neutralized is recommended. after their use. 2-38. RUDDER TRIM WHEEL THREADS (MODEL 2-32. UPHOLSTERY AND INTERIOR cleaning pro- 185 SERIES). Spray the rudder trim wheel threads longs the life of upholstery fabrics and interior trim. with Electrofilm Lubri-Bond "A" which is available To clean the interior: in aerosol spray cans. a. Empty the ash trays. b. Brush out or vacuum clean the carpeting and 2-39. TACHOMETER DRIVE SHAFT. Refer to Sec- upholstery to remove dirt. tion 16 for lubrication. c. Wipe off leather, Royalite, and plastic sur- faces with a damp cloth. 2-40. WHEEL BEARING LUBRICATION. It is now d. Soiled upholstery fabrics and carpeting may be recommended that nose and main wheel bearings be cleaned with a foam-type detergent, used accord- cleaned and repacked at the first 100-hour inspection ing to the manufacturer's instructions, and at each 500-hour inspection thereafter. If more e. Oily spots and stains may be cleaned with than the usual number of take-off and landings are household spot removers, used sparingly. Before made, extensive taxiing is required, or the airplane using any solvent, read the instructions on the con- is operated in dusty areas or under seacoast condi- tainer and test it on an obscure place in the fabric tions, it is recommended that cleaning and lubrica- to be cleaned. Never saturate the fabric with a tion of wheel bearings be accomplished at each 100- volatile solvent; it may damage the padding and hour inspection. backing materials. f. Scrape off sticky materials with a dull knife, 2-41. CASTERING AXLE. Lubricate pivot pin dur- then spot clean the area. ing assembly. Also lubricate the pivot pin through the grease fittings after assembly and at each 100- 2-33. PROPELLERS should be wiped off occasion- hour inspection. ally with an oily cloth to clean off grass and bug stains. In salt water areas this will assist in corrosion-proofing the propeller. SHOP NOTES: 2-10A/2-10B * 5 22 1O DAILY 3 FUEL TANK FILLERS Fill after each flight. Keep full to retard condensation. Refer to paragraph 2-14 for details. 5 FUEL TANK SUMP DRAINS If quick-drain valves are installed, drain off any water and sediment before the first flight of the day. 6 OXYGEN CYLINDER Check for anticipated requirements before each oxygen flight. Refer to Section 15 for details. 8 PITOT AND STATIC PORTS Check for obstructions before first flight of the day. 13 OIL DIPSTICK Check on preflight. Add oil as necessary. Refer to paragraph 2-16 for details. 18 FUEL STRAINER Drain off any water and sediment before the first flight of the day. SERVICING Figure 2-4. Servicing and Lubrication (Sheet 1 of 7) 2-11 (O 50 HOURS 7 BATTERY Check level of electrolyte. Check at least every 30 days, oftener in hot weather. Refer to paragraph 2-18 for details. 14 19 ENGINE OIL SYSTEM Change engine oil and external filter element. Without external filter, change oil and clean oil screen EVERY 25 HOURS. Reduce these intervals under severe operating conditions. Refer to paragraph 2-16 for details. 17 INDUCTION AIR FILTER Service oftener under dusty conditions. Refer to paragraph 2-17 for details. -15-SHIMMY-DAMPENER_(1_9_67 MODEL 182) Check shimmy dampener compensating mechanism. Refer to-paragraph-2-21B-for-details. DO 100 HOURS FUEL/AIR CONTROL UNIT SCREEN Remove and clean screen in bottom of fuel/air control unit on fuel injection engines, then reinstall and safety the screen. 2 GYRO INSTRUMENT AIR FILTERS If not equipped with central air filter, replace every 100 hours and when erratic or sluggish responses are noted with normal suction gage readings. Refer to paragraph 2-17A for details. 4 FUEL LINE DRAIN PLUGS OR VALVES Remove plugs and drain off any water and sediment. Reinstall and resafety plugs. Some aircraft use drain valves instead of drain plugs. 5 FUEL TANK SUMP DRAINS If quick-drain valves are not installed, remove plugs and drain off any water and sediment. Reinstall and resafety plugs. 11 BRAKE MASTER CYLINDERS Check fluid level and refill as required with hydraulic fluid. 15 SHIMMY DAMPENER Check fluid level and refill as required with hydraulic fluid. Refer to paragraphs 2-21 and 2-21A for details. 18 FUEL STRAINER Disassemble and clean strainer bowl and screen. 9 CASTERING AXLE Check and refill if required. Refer to paragraph 2-22A for details. 21 VACUUM SYSTEM OIL SEPARATOR Remove, flush with solvent, and dry with compressed air. 22 SUCTION RELIEF VALVE SCREEN OR FILTER Check inlet screen or filter for cleanliness. Remove, flush with solvent, and dry with compressed air to clean. On Garwin valves, remove retaining ring to remove screen. On filter-equipped valves, replace garter filter at engine overhaul periods. SERVICING Figure 2-4. Servicing and Lubrication (Sheet 2 of 7) 2-12 < >o 500 HOURS 20 VACUUM SYSTEM CENTRAL AIR FILTER Replace central air filter every 500 hours and when suction gage reading drops below 4.6 inches of mercury. Refer to paragraph 2-17A for details. AS REQUIRED 10 TIRES Maintain proper tire inflation as listed in the charts in Section 1. Also refer to paragraph 2-19. 12 GROUND SERVICE RECEPTACLE (PRIOR TO 1967 MODELS) Connect to 12-volt, DC, negative-ground power unit for cold weather starting and lengthy ground maintenance of the electrical system. Master switch should be turned on before connecting a generator type external power source; it should be turned off before connecting a battery type external power source. Refer to paragraph 12-14. CAUTION Be certain that the polarity of any external power source or batteries is correct (positive to positive and negative to negative). A polarity reversal will result in immediate damage to semiconductors in the airplane's electronic equipment. 12 GROUND SERVICE RECEPTACLE (1967 MODELS AND ON) Connect to 12-volt, DC, negative-ground power unit for cold weather starting and lengthy ground maintenance of the airplane's electrical equipment with the exception of electronic equipment. Master switch should be turned on before connecting a generator type or battery type external power source. Refer to paragraph 12-14A. NOTE The ground power receptacle circuit incorporates a polarity reversal protection. Power from the external power source will flow only if the ground service plug is connected correctly to the airplane. 16 NOSE GEAR SHOCK STRUT Keep strut filled and inflate to correct pressure. Refer to paragraph 2-20 for details. SERVICING Figure 2-4. Servicing and Lubrication (Sheet 3 of 7) 2-13 FREQUENCY (HOURS) METHOD OF APPLICATION GUN CAN (FOR POWDERED WHERE NO INTERVAL IS SPECIFIED, GRAPHITE) LUBRICATE AS REQUIRED AND WHEN ASSEMBLED OR INSTALLED. NOTE The military specifications listed are not mandatory, but are intended as guides in choosing satisfactory materials. Products of most reputable manufacturers meet or exceed these specifications. LUBRIC-ANTS PG - MIL-G-6711 POWDERED GRAPHITE GG - MIL-G-7711 GENERAL PURPOSE GREASE GA - MIL-G-25760 AIRCRAFT WHEEL BEARING GREASE GH - MIL-G-23827 AIRCRAFT AND INSTRUMENT GREASE GL - MIL-G-21164 HIGH AND LOW TEMPERATURE GREASE OG - MIL-L-7870 GENERAL PURPOSE OIL P L - W- P- 236 PETROLATUM GS SIL-GLYDE (OR EQUIVALENT) .-- ALSO REFER TO SHIMMY DAMPENER PIVOTS -- -- REFER TO. PARA- GRAPH 2-40X STEERING SYS- TEM NEEDLE BEARINGS GGA NOSE GEAR MAIN GEAR WHEEL BEARINGS WHEEL BEARINGS TAIL GEAR FLAP BELLCRANK NEEDLE BEARINGS LUBRICATION Figure 2-4. Servicing and Lubrication (Sheet 4 of 7) 2-14 OILITE BEARINGS CONTEEDLE COLUMEARN CONTROL T ROLLERS CONTROL / W KWHEEL SHAFT cG UNIVERSALS NEEDLE BEARINGS NEEDLE BEARINGS NEEDLE BEARING CONTROL COLUMN CONTROL "T" CONTROL WHEEL SHAFT INIVERSALS USHINGS AND OILITE BEARINGS CONTROL "Y" CONTROL "Y" NEEDLE BEARINGS BATTERY PARKING BRAKE LUBRICATION Figure 2-4. Servicing and Lubricatio (Sheet 5 of 7) 2-15 OILITE BEARINGS (RUDDER BAR ENDS) NEEDLE ALL LINKAGE POINT PIVOTS | SCREW JACK THREADS ELECTRIC F7AP- DRIVE MECHANISM r0 BEARING BLOCK HALVES RUDDER BARS AND PEDALS RELEASE BUTTON & RATCHET LATCH O06 ALL PIANO HINGES NEEDLE BEARINGS FLAP LEVER GL ELEVATOR TRIM TAB ACTUATOR HARTZELL PROPELLER GL STABILIZER ACTUATORS * REFER TO FIGURE 14-5 FOR A LIST OF APPROVED GREASES. LUBRICATION Figure 2-4. Servicing and Lubrication (Sheet 6 of 7) 2-16 SPRING-LOADED FRICTION STOPS ALL TRIM WHEEL . OILITE BEARINGS ALL TRIM WHEEL NEEDLE BEARINGS GH CABIN DOOR WINDOW INSERT GROOVES REFER TO PARAGF. PH 2-38 FOR DETAILS ALSO REFER TO PARAGRAPH 2-41 MODEL 185 RUDDER TRIM WHEEL THREADS CASTERING AXLE PIVOT PIN WING FLAP INDICATOR NOTES Sealed bearings require no lubrication. McCauley propellers are lubricated at overhaul and require no other lubrication. Do not lubricate roller chains or cables except under seacoast conditions. Wipe with a clean, dry cloth. Lubricate unsealed pulley bearings, rod ends, Oilite bearings, pivot and hinge points, and any other friction point obviously needing lubrication, with general purpose oil every 1000 hours or oftener if required. Paraffin wax rubbed on seat rails will ease sliding the seats fore and aft. Lubricate door latching mechanism with MIL-G-7711 general purpose grease, applied sparingly to friction points, every 1000 hours or oftener if binding occurs. No lubrication is recommended on the rotary clutch. LUBRICATION Figure 2-4. Servicing and Lubrication (Sheet 7 of 7) 2-17 HOLDER BRACKET 2 REQD MATERIAL: (. 040) HANDLE -- ~ /,/ 2024-T4 CLAD .50 FLANGE j^^ '~'(j BBEND RADI .09 tA~~ D^^~~ ^~ ~.75. 1.62 BEND EDGES OF BOTTOM AND LID .50 FLANGE \ Ft / ^ \ ^^c ^/-^'c /~g gWELD 1. IBOTTOM ENDS A8 REQD 1.62 48 00 LI D 1 ^ N ^**?; : ^^ ^ANGLE 1.25 1. 00 x . 00 xI /8(ORBQUIVx 2-^ >1 8^ / /DRILL 1/4 (.250) DRAIN HOLES \/4 INCH CENTER ..... . \----BOX ASSEMBLY ''v 3. 0 ^^^^^ IMATERIAL FOB BOTTOM AND ENDS MS20470AD4 RIVET - AS REQD ON HINGE 154.0 I \ . ^< ^ MS20470AD3 RIVET - AS REQD 15.D 12.0 Figure 2-5. Construction of Induction Air Filter Servicing Box 2-18 INSPECTION To avoid repetition throughout the inspection, general points to be checked are given below. In the inspection, only the items to be checked are listed; details as to how to check, or what to check for, are excluded. The- inspection covers several different models. Some items apply only to specific models, and some items are optional equipment that may not be found on a particular airplane. Check FAA Airworthines Directive and Cessna Service Letters for compliance at the time specified by them. Federal Aviation Regulations require that all civil aircraft have a periodic (annual) inspection as prescribed by the administrator, and performed by a person designated by the administrator. The Cessna Aircraft Company recommends a 100-hour periodic inspec- tion for the airplane. CHECK AS APPLICABLE: MOVABLE PARTS for: lubrication, servicing, security of attachment, binding, excessive wear, safetying, proper operation, proper adjustment, correct travel, cracked fittings, security of hinges, defective bearings, cleanliness, corrosion, deformation, sealing, and tensions. FLUID LINES AND HOSES for: leaks, cracks, dents, kinks, chafing, proper radius, security, corrosion, deterioration, obstructions, and foreign matter. METAL PARTS for: security of attachment, cracks, metal distortion, broken spotwelds, corrosion, condition of paint, and any other apparent damage. WIRING for: security, chafing, burning, defective insulation, loose or broken terminals, heat de- terioration, and corroded terminals. BOLTS IN CRITICAL AREAS for: correct torque in accordance with the torque values given in the chart in Section 1, when installed or when visual inspection indicates the need for a torque check. FILTERS, SCREENS, AND FLUIDS for: cleanliness, contamination and/or replacement at specified intervals. AIRPLANE FILE. Miscellaneous data, information, and licenses are a part of the airplane file. Check that the following docu- ments are up-to-date and in accordance with current Federal Aviation Regulations. Most of the items listed are required by the United States Federal Aviation Regulations. Since the regulations of other nations may require other documents and data, owners of exported aircraft should check with their own aviation officials to determine their individual requirements. To be displayed in the airplane at all times: 1. Aircraft Airworthiness Certificate (Form FAA 1362B). 2. Aircraft Registration Certificate (Form FAA 500A). 3. Aircraft Radio Station License, if transmitter installed (Form FCC 404-2). To be carried in the airplane at all times: 1. Weight and Balance, and associated papers (Latest copy of the Repair and Alteration Form, Form FAA 337, if applicable). 2. Aircraft Equipment List. To be made available upon request: 1. Aircraft Log Book and Engine Log Book. ENGINE RUN-UP. Before beginning the step-by-step inspection, start, run up, and shut down the engine in accordance with instructions in the Owner's Manual. During the run-up, observe the following, making note of any discrep- ancies or abnormalities: 1. Engine temperatures and pressures. 2. Static rpm. 3. Magneto drop (See Owner's Manual). 4. Engine response to changes in power. 5. Any unusual engine noises. 6. Propeller response (See Owner's Manual). 7. Fuel tank selector and/or shut-off valve; operate engine on each tank position and off position long enough to make sure the valve functions properly. 8. Idling speed and mixture; proper idle cut-off. 9. Alternator and ammeter. 10. Suction Gage. 11. Fuel flow indicator. After the inspection has been completed, an engine run-up should again be performed to ascertain that any discrepancies or abnormalities have been corrected. 2-19 SCOPE AND PREPARATION. CONTINENTAL ENGINE: If the engine is equipped with an external oil filter, change engine oil and filter element at 50-hour intervals. If the engine is NOT equipped with an external oil filter, change engine oil and clean the oil screen EVERY 25 HOURS. "BLUE-STREAK" (Lycoming) ENGINE: If the engine is NOT equipped with an external oil filter, change engine oil and clean oil screens at 50-hour intervals. If the engine is equipped with an external oil filter, the engine oil change intervals may be extended to 100-HOUR intervals providing the external filter element is changed at 50-HOUR intervals. The 50-hour inspection includes a visual check of the engine, propeller, and aircraft exterior for any apparent damage or defects; an engine oil change as required above; and accomplishment of lubrication and servicing requirements. Remove propeller spinner and engine cowling, and replace after the inspection has been com- pleted. The 100-hour (or annual) inspection includes everything in the 50-hour inspection, and oil change as required above. Also loosen or remove the fuselage, wing, empennage, and upholstery inspection doors, plates, and fairings only as necessary-to-perform-a-thorough,-searchinginspection of the aircraft. Replace after the inspection has been completed. NOTE Numbers appearing in the "AS SPECIFIED" column refer to the data listed at the end of the inspection chart. AS SPECIFIED EACH 100 HOURS PROPELLER. EACH 50 HOURS 1. Spinner and spinner bulkhead-------------------------------------- ---- 2. Blades------- --------------------------- . 3. Hub -------------------------------------------- - 4. Lubrication (Hartzell)-------------------------------------------------------- 5. Bolts and/or nuts---------------------------------------- ------------------------ 6. Governor and control--------------------------------- -------------------- ENGINE COMPARTMENT. Check for evidence of oil and fuel leaks, then clean entire engine and compartment, if needed, prior to inspection. 1. Engine oil, screen, filler cap, dipstick, drain plug and external filter element----------- 2. Oil cooler----- -- ------------------------------ ----------------------- 3. Induction air filter (Also see paragraph 2-17. ) ---------------------- ------------ - 2 2-20 AS SPECIFIED EACH 100 HOURS EACH 50 HOURS 4. Induction airbox, air valves, doors, and controls ........................................ 5. Cold and hot air hoses .............................................................. 6. Engine baffles ..................................................................... 7. Cylinders, rocker box covers, and push rod housings .................................... 8. Crankcase, oil pan, reduction gear housing, accessory section and front crankshaft seal ..... · 9. All lines and hoses ................................................................. 10. Intake and exhaust systems (Also see paragraph 12-101) ............................... 11. Ignition harness ................................................................... 12. Spark plugs and compression check .................................................. 13. Crankcase and vacuum system breather lines ......................................... 14. Electrical wiring .................................................................... 15. Vacuum pump and oil separator, and relief valve ....................................... · 16. Vacuum relief valve screen or filter .................................................. 3 17. Engine controls and linkage ........................................................ · 18. Engine shock mounts, engine mount structure, and ground straps ........................ · 19. Cabin heater valves, doors and controls ............................................... 20. Starter, solenoid and electrical connections, and engagement lever ....................... · 21. Starter brushes, brush leads and commutator .......................................... 4 22. Generator or Alternator, drive belt, pulley, and electrical connections ...................... 23. Generator or Alternator brushes, brush leads, commutator or slip ring ..................... 4 24. Voltage regulator mounting and electrical leads .................... ..................... 25. Magnetos (externally) and electrical connections ....................................... 26. Bendix magneto breaker compartment and timing (Also see paragraph 12-77) .............. * 5 27. Slick magneto timing ............................................................... 6 28. Slick magneto breaker compartment (Also see paragraphs 12-71 and 12-71 E) ..... ........ 6 29. Fuel injection fuel-air control unit, fuel pump, fuel manifold valve, fuel lines, and nozzles...... 30. Fuel-air control unit screen .......................................................... Revision 1 2-21 © Cessna Aircraft Company Aug 4/2003 31. Carburetor ........................................................................ 32. Firewall ......................................................................... 33. Engine cowling .................................................................... 34. Cowl flaps and control .............................................................. FUEL SYSTEM 1. Fuel strainer, drain valve, and control ................................................. 2. Fuel strainer screen and bowl ........................................................ 3. Electric fuel pump, throttle switch, and electric connections .............................. 4. Fuel tanks, fuel accumulator tank, fuel lines, drains, filler caps, and placards ............... 5. Drain fuel and check tank interior, attachment and outlet screens ......................... 6. Fuel vents and vent valves ......................................................... 7. Fuel selector and/or shut-off valve and placards ........................................ 8. Fuel quantity gages and transmitter units .............................................. 9. Engine primer ..................................................................... 10. Vapor return line and check valve .................................................... 11. Perform a fuel quantity indicating system operational test. Refer to Section 16 for detailed accomplishment instructions. ............................................. 12. For airplanes equipped with an engine that uses a carburetor, drain fuel from carburetor bowl and check for fuel contaminants. Refer to Cessna Service Bulletin SEB99-19, Engine Carburetor Fuel Inspection (or latest revision) for detailed accomplishment instructions ........................................................ 13. Fuel injection nozzles ............................................................... LANDING GEAR 1. Brake fluid, lines and hoses, linings, disc and clips, brake assemblies and master cylinders .. 2. Main gear wheels, wheel bearings, step and spring strut, tires, and fairings ................ 3. Main and nose gear wheel bearing lubrication (Refer to paragraph 2-40) ................... 4. Torque link lubrication (Refer to paragraph 2-36) ....................................... 5. Tailgear lubrication and nose gear strut servicing ....................................... 6. Nose gear shimmy dampener servicing ............................................... 7. Tailwheel friction check (Refer to paragraph 5-60) ...................................... 8. Nose gear wheels, wheel bearings, strut, steering system, shimmy dampener, tire, fairing, and torque links ........................................ 9. Tailwheel, tire, wheel bearings, steering system, anti-swivel mechanism, tailwheel locking system, cables, and spring tube ....................................... 10. Parking brake system .............................................................. 2-22 D637-1-13 TemDorarv Revision Number i © Ce