Piper Comanche Service Manual

Revised: 11/1. • Figure PIPER COMANCHE SERVICE MANt'AL LIST OF ILLlJSTRATIO~S(cont.) Aerofiche Grid xo. Revised: 11/1/82 • • 4-1 4-4. 4-5. 4-6. 4-7. 4_7a. 4-"b. 4-"c. 4-X. 4-9. 4-10. 4-11. 4·12. 4-1 :. 4-14. 5-1. 5-la. 5-2. 5-3. 5-4. 5-5. 5-6. 5-1 . 5-~. 5-9. 5·10. 5-11. 5-12. 5-13. 0-1. 6-2. 6-3. 6-4. 6-5. 6-6. 6-7. 6-8. 6-8a. 6-8b. 6-8c. Flap Roller Installation (Electrically Operated) . Aileron Bearing Installation . Door Installation . Door l.ockins Mechanism PA-24-250. Serial 'os. 24-2844 to 24-3284 . Door Locking Mechanism PA-24-250. Serial 'os. 24-3285 and up. PA-24-200 and PA-24-400 . Stabilator Balance Weight . Checking Stabilator Free Play . Checking and Balancing Rudder . Fuselage Skin Diagram PA-24-IXO. PA-24-250 and PA-24-260. Serial '0". 24-4000 to 24-4246. 24424X to 24-4299 . Wing and Empennage Skin Diagram PA-24-180. PA-24-250 and PA-24-260. Serial '0.,. 24-4000 to 24-4246. 24-424~ to 24-4299 . Fuselage Skin Diagram PA-24-260. Serial ~os. 24-4247. 24-4300 and up . Wing. and Empennage Skin Diagram PA-24-260. Serial Nos. 24-4247.24.4300 and ur . Fuselage Skin Diagram PA-::~4-400 . \\ ing and r mpennage Skill Diagram PA-24400 . Typical Acce Holes . Control Column Installation . Correct Method of Installing Rod End Bearings . Aileron Control Installation . Installation of Bellcrank Checking Tool . Aileron Adjusting Points . Flap Control Installation . Determining ~eutral Rudder Position . Checking Rudder Travel . Rudder and Rudder Trim Controls . Clamping Rudder Pedals in Neutral Position . Stabilaror and Stabilator Trim Controls . Checking Stabilator Travel in Up Position . Stabilator Adjustment Points . Special Fabricated Tools . ~ose Gear Oleo Strut. Serial 'os. 24-1 to 24-214 incl. . Xose Gear Oleo Strut Assembly PA-24-180. PA-24-250. Serial 'os. 24-215 and up. PA-24-260 and P A-24-400 . ~ose Landing Gear Installation . Clamping Rudder Pedals in ~eutral Position . Rudder Pedals at 'eutral Angle . Installations of Plumb Bob Attachment Tool and Alignment Jig . Nose Gear Installation PA-24-260 and PA-24-400 ..........•................... Main Gear Oleo Strut Assembly : . Main Gear Side Brace Link Travel . Main Gear Side Brace Bearing Tolerance " . Main Gear Side Brace Link Tolerance . lA6 IEI4 IE 14 IE 17 If IX I EI9 IE::;4 IF2 IF5 IFfl I Fi IF!' IF9 IFIO IFII I FI2 IFI9 IF::!) IG2 IG4 IG4 IG6 IGI5 IGI5 IG If' IGI~ IG21 IHI IH4 IHI6 IH24 115 1110 1113 1113 1114 1116 1120 1122 1121 \123 PIPER COMANCHE SERVICE MANl~AL LIST OF IlLUSTRATlO~S(com.) •Figure Aerofiche Grid \0. 1./2 Uti Ir 1.1 I() 1.11 ~ 1.1('7 1.l1!' IJ 19 1.114 IKI IK1 IK3 IK5 IKti IKX IK9 I K 10 IKI~. IKI4 I KI5 IKI6 IKli IA7 \lain Landing Gear Installation (left) . Adjustment of Main Landing Gear Drag Link . Aligning Main Gear . Landing Gear Retraction System . Landing Gear Retraction Transmission Assembly . Landing Gear Retraction System Installation . 'ose Gear Drag Link Clevis . Landing Gear L'p limit Switch. , . Torque Wrench and Adapter Installation. Serial Xos. 24-1 to 24.4781 incl. 14-471'4 to 24-480J incl. . Torque Wrench and Adapter Installation. Serial Nos, 24-478J. 244804 and up . Landing Gear Down Safety Lock Installation . Landing Gear Warning Switch Installation . Landing Gear Warning Indicator . \osc "'heel Assernblv " . Main Wheel Assernblv (Cleveland] PA-24-180 and PA-24-250 . Main Wheel Assembl;' (Cleveland) PA-24-260 and PA·24-400 . Main Wheel Assemblv (Goodrich) PA-24400 . Brake Assembly (Cleveland) PA-24-180 and PA-24-250. Serial ~os. 14-\ to 14-3295 . Brake Assemble (Cleveland] PA-24-180 and PA-24-250. Serial ~os. 14-3196 and up. PA-14-260 and PA-24400 . Brake Assembly (Goodrich) PA-24-400 . Replacing Brake Disc . Bleeding Brakes . Bra ke System Insta lIation P A-24-180 and PA-24-250. Serial"!'; as. 24-1 to 14·2174 incl.. 24-2176 to 24.:2298 incl. I K IH Brake System Installation PA-24-180 and PA-24-250. Serial '0S. 24-2175. 24-2298 and up. PA-24-260 and PA-24-400 IKI9 Brake Cvlinderlnstallation ; . . . . . .. . . . . . . .. . . . . . . . . . . . . . . . . I K21 Brake Master Cylinder PA-24-180 and PA-24-250. Serial 1\05. 24-1 to 14-2174 incl.. 24-2176 to 24-2298 inc.......................................... IK23 Parking Brake Valve. . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . III Brake Master Cylinder PA-24-180 and PA-24-250. Serial Nos. 24-2175 14-1299 and up:PA-24-260 and PA-24-400.................................... I U Brake Cylinder Installation I L4 Fabricated Plumb Bob Tool 11.7 Fabricated \ose Wheel Alignment Jig. . . . . . . .. . . . .. .. . . . .. . .. . . . . .. . . . . . . . I1.X Fabricated Spanner Wrench......................................... .... . ... 11.9 Inspection of Rod End Bearing....... . . . . . . . . . .. .. ... . .. . .. .. . . .. . .. . . . . . . . . I 1 II Main Gear Wear Limits.................................................... I L14 \ose Gear Wear Limits :. . . . .. . . . . . . . . I Lito Propeller Installation (McCauley) . . . . . . . . . . . . . . . . . . .. . .. . . . . . . . . . . . . 2A 14 Typical Nicks and Removal Method 2A 15 Propeller Installation (Hanlell).............................................. 2AI~ Revised: 1111. 6-9. 6-10. 6-11. 6-11. 6-L~. 6-14. 6-15. 6-16. 6-19. 6-10. 6-11. 6-11. 6-13. 6-14. 6-15. 6-10. 6-27. 6-1~. 6-~7a. o-JX. 6-:~9 . 6-40. 6-41. ti-41. ti-43. 7-1. 7·1. 7-J. 6-:~0. 6-J I. h-:~1. to-JJ. PIPER COMANCHE SERVICE MASt"AL LIST OF ILLl1STRA TlO'S (cont.) Aerofichc Grid '0, Revised: It /1/82 • figure 7-~. 7-5. 7-fl. 7-fla. 7-7. 7-H. 7-9. 7-10. 7-11, 7-1 ~. 7-13. 7-14, 7-15. 7-1 ft. 7-17. 7A-I, 7A-~. • 7A-4. 7A-5. 7/,\-(,. 7A- -:. 7A-~. 7A-9, 7A-IO. 7A-II. 7A-I~. 7A-I~. 7.'\-14. 7A-15. 7A-lh. 7A-li. 7A-IX, 7A-19 1A-20. 7A-~ I. 7A-~2. 7A-~). 7B-1. 7B-1. 7B-J. 78-4. 7B-5. • Woodward Propeller Governor Adjustment Points . Hartzell Propeller Governor Adjustment Points . Engine Installation (PA-24-IXO) . Cockpit Control Spring Back . Carburetor . Magneto Inspection . Lead Positioning . Impulse Coupling . Magneto Timing Marks . Timing Pointer . Timing Plate Installed on Breaker Compartment . Breaker Compartment With Cast Timing Marks . Engine Timing Marks . Ignition System Retard Breaker Magneto Installation . Removing Seized Spark Plug . Propeller Installation (McCauley) PA-24-250 . Typical 'ick~ and Removal Method . Propeller Installation (Hartzell] PA-24-250 . Propeller Installation (Hartzell] PA-24-260 . Woodward Propeller Governor Adjustment Points . Hartzell Propeller Governor Adjustment Points . Engine Installation PA-24-250 . Engine Installation PA-14-160. Serial 'as. 24-4000 to 244782 inel. and 2~-~7x~ to 24-~I<OJ incl. . Engine Installation PA-24-2flO. Serial 'os. 24-4783 and 24-4804 and up . Carburetor . Schematic Diagram of RSA Fuel Injector System (PA-24-250 & PA-24-260) . Idle and Mixture Adjustment (Fuel Injector) . Fuel Air Bleed 'OllIe . Magneto Inspection _ . Lead Positioning . Impulse Coupling . Magneto Timing Marks . Timing Pointer . Timing Plate Installed on Breaker Compartment ' . Breaker Compartment with Cast Timing Marks . Engine Timing Marks , Ignition System Retard Breaker Magneto Installation . Removing Seized Spark Plugs . Propeller Installation . Typical 'icks and Removal Methods . Propeller Governor Adjustment Points . Engine Installation (PAp:24-400l . Schematic Diagram of RSA Fuel Injector System (PA-14-400l . lAS :2A~' 2A2~ 2BI 2B5 ~Bf, :2 Bl' 2B9 ~B9 28 In 2810 2811 2B \I 2B 12 2B 15 281'" 2C7 2el< 2CIO 2('12 2C If, :2CI7 2C21 ~DI 20 7 2DII 2014 2016 2DI7 1DI9 2020 2020 ~011 2D21 2D2~ ~D22 2D24 2E2 2E4 1E22 1E2J 2F1 1FJ '~FX Figure PIPER COMANCHE SERVICE MANUAL LIST OF ILLUSTRATIONS (eont.) •Aerofiche Grid ;'1;0. 7B·6. 7B-7. 7B-8. 7B·9. 7B-IO. 7B-11. 7B-12. 78·13- 7B-14. 7B-15. 7C- t. 7C-2. 7C-l 7C-4. 7C·5. 7C-6. 7C-7. 7C-8. 7C-9. 7C-10. 7C-11. 7C·12. 7C·13. 7C-14. 7C·15. 7C·16. 7C-17. 8-1. 8-2. 8-1 8·4. 8-5. 8-6. 8-7. 8-8. 8-9. 8-10. 8-11. 8-12. 8-13. 8-14. 8-15. 8-16. 8-17. Idle Speed and Mixture Adjustment (Fuel Injector) , 2F 10 Fuel Air Bleed Nozzle. . . . . . . . . . . . . . • . . . . . • . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2F 12 Magneto Timing Marks.................................................... 2FI4 Reworked Plain Washer. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . • . . . . . . . . . . 2F 14 Filed Notch on Cam . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . • . . . . . . . . . . . . . . . . . . 2F I5 Installation of Rotor Holding Tool and Timing Pointer. • . . . . . . . . . . . . . . . . . . . . . . . 2F I 5 Alignment of Cam in Inspection Hole........................................ 2FI6 Engine Timing Marks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 2F 17 Ignition System Retard Breaker Magneto Installation 2F20 Removal of Seized Spark Plug . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2F22 Propeller Installation. .. .. . . .. . . .. .. . . . .. . .. . .. .. . .. .. 2G 12 Typical Nicks and Removal Methods. . .. . . ... .. ... . . .. . .. . . . ... 2G 13 Propeller Governor .................•.•...... . . . . . . . . . . • . . . . . . . . . . . . . . . . . . . 2G IS Engine Installation (PA-24-260 Turbocharged)....... .. . .. . .. .. 2G22 Schematic Diagram of Turbocharger System.. . .. . .. . .. 2G23 Schematic Diagram of RSA Fuel Injector System (PA·24-260 Turbocharged)...... 2H7 Fuel Injector. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . • . . . . . . . . . . . . . . . . .. 2H9 Fuel Air Bleed Nozzle " . . . . . . . . . . . . . . . . . . . 2H 10 Contact Points... . . . . . . . . . . . . . . . . . . 2H 12 Rotor Holding Tool Installed ,. 2H 14 Timing Kit Installed....................................................... 2HI.Aligning Timing Marks Single Contact Assembly Magneto ,. 2H 1 Forming Leads in Breaker Compartment 2H IS Engine Timing. Marks. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 2H 16 Magneto Timing Marks '.' . .. . .. . .. . . . . 2H 16 Removing Frozen Spark Plug '" '" . . . . .. .. 2H 19 Turbo Oil Flow Check ..•..•. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2H22 Fuel Cell Installation (Main Installation) ..•.................................. 2114 Fuel System Schematic PA-24-l80 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . • . . . . . . . 2115 Fuel System Schematic PA-24-2S0. Serial Nos. 24-105 to 24-2298 .. .. 2116 Fuel Svstem Schematic PA-24-2S0. Serial Nos. 24-2299 and up and PA-24-260 2117 Fuel System Schematic PA-24-260 (Turbo)... . . . . . . 2118 Fuel System Schematic PA·24·400 " . . .. . 2120 Bayonent Fasteners. . . . . . . . . . . . .. . . . .. . . . . . . . . . . .. . .. . . . . . . . . . . . . . . . . . .. 2121 Button Fasteners 2121 Checking Sender Unit. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2124 Checking Fuel Gauge , .....................•••.•.... , , 2124 Three Position Fuel Valve PA·24·180 and P A·24-2S0. . . . . . . . . . . . . . . . . . . . . . . . . . . 2J3 Five Position Fuel Valve PA-24-2S0 and PA-24-260... . .. . .. .. . 2J5 Fuel Va lve and Filter PA-24-400. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2J 5 Fuel Strainer Disassembled PA·24-400 2J7 Bendix Plunger Fuel Pump (Early). . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2J9 Bendix Plunger Fuel Pump (Late) 2J9 Exploded View Bendix Rotary Fuel Pump '. 2J 12 lA9 REVISED: 4/1. • PIPER COMA~CHE SERVICE MANl'Al LIST OF ILLliSTRATIO,S (cont.) Aerofiche Grid 'no • Figure ~-,~. ~-'9. 9-1. 9-:!. 9-). 9-4. 9-5. 9-ft. 9- ~, 9-~. 9-9. 9-10. 9-11. 9-12. 9-D. 9- J.t. 9-15. 9-1 ft. 9-17, 9-IX, 9-19. 9-20. 9-21. 9-22. 9-:!~ , 9-24. 9-25. 9-:!6, 9-2'1. 9-:!7a. 9-2":'b. 9-:!'7c. 9-:!7d. 9-:!7e, 9-2:1. 9-:!7g. 9-27h, Primer Pump (Carburetor Induction System) , . Fabricated Fuel Quantity Transmitter Checking Jig . Generator and Starter Wiring System . Sectional View of Generator , , , . Wiring Circuit of Three Unit Regulator . L'se of Rimer File to Clean Contact Points, . Voltage Regulator Air Gap Check and Adjustment , . Adjusting Voltage Regulator Settings . Checking Voltage Setting. Fix-ed Resistance Method . Checking Voltage Setting. Variable Resistance Method , . Cutout Relay Air Gap Check and Adjustment , . , Cutout Relay Point Opening Check and Adjustment . Checking Cutout Relay Closing Voltage , Adjustment of Cutout Relay Closing Voltage . Checking Current Regulator Load Method . Checking Current Lead Method. Jumper Lead Method , .. Alternator and Starter Wiring System , , . Cross Sectional View of Alternator . Checking Rotor ." . Slip Ring End Frame. , . Checking Stator , , . Checking Diodes . Brush Holder Assembly . Exploded View of Heat Sink Assembly , . Checking Alternator Output . Volt-Ohmmeter Test . Jumper Connection . Regulator Checks . Relay Test . Exploded View of Alternator " . Alternator and Starter Wiring System Schematic (Prestolite) . Removal of Rectifier . Removal of Slip Ring End Bearing . Removal of Drive End Head . Removal of End Head Bearing . Testing Rotor for Grounds , . , . Testing Rotor for Shorts . 2.115 :!Jll' 3AI3 ~Alo ~A:!:! ~.-\:!4 ~A:!4 3BI ~BI ~BI ~B~ ~B~ 3B.t ~B4 385 385 ~B!\ ~810 ~BII ~BII 3BI I ~B12 3BI4 ~B14 ~B15 ~B17 3817 381X ~819 3820 3822 3823 38D ~814 3824 3el ~CI • lAtO Revised: 11/ 1 /82 Figure PIPER COMANCHE SERVICE MA!'il'AL LIST OF ILLl;STRATlO,S (cont.) •Aerofiche Grid ,\(). 9-~7i, 9~ :!7j. 9-27k. 9·271. 9-27m. 9-27n, 9-270. 9·~7p. 9-171.1. 9-:nr. 9-:!7s. 9·21<. 9-19. 9-19a. 9-19b. 9-29c. 9-29d. 9-19t.:. 9-19i. 10·1, 10-~. 10-3. 10-4. 10-f,. to·7. II-I. 12-1. Installation of Bearing . Installation of Rectifier . Terminal Assembly . Slip Ring End Bearing Assembly . Testing Alternator . Brush Installation . Internal Wiring Diagram . Regulator Diagram . Testing Regulator . Application of Overvoltage Control . Test ing 0\ ervoltage Control . 'o-l.oad Test . Lock-Torque Test . Exploded View of Gear Reduction Starting Motor . Turning Starting Motor Commutator . Tcosting Motor Armature for Shorts . Testing Motor Fields for Grounds . 'o-Load Test Hookup . Stall-Torque Hookup . Cabin Heater. Defroster and Fresh Air System PA-24-180 and PA-24·:!50. Serial' os. 14-1 to 24- I251 . Cabin Heater. Defroster and Fresh Air Svstem PA-24-180 and PA·24-150. Serial' os. 14-1152 to 24-219M : . Cabin Heater. Defroster and Fresh Air System PA-24-180 and PA-24-250. Serial 'os. 24-2299 and up . Cabin Heater. Defroster and Fresh Air System PA-24-260. Serial 'os. 24-4000 to 24-4146. 24-4248 to 24-4299 . Cabin Heater. Defroster and Fresh Air System PA-24-260. Serial 'os. 14-4247. 24-4300 to 24-4782 inclusive: 14-4784 to 24-4803 inclusive . Cabin Heater. Defroster and Fresh Air System PA-24-400 . Cabin Heater. Defroster and Fresh Air System PA-24-260. Serial 'os. 24-471:0. 24·4804 and up . Instrument Panel , . Avionics Antenna Locations . NOTE Refer to Electrical System Schematics Index at 3D7 ~C2 ~C2 ~C3 3C3 ~C3 ~C4 .~C 4 .~C· .1Cl'o 3CQ ~C9 .~CII 3C 12 3CI4 3C17 3CJf .1(1-:' 3(lloi ~C II' 3F9. 3FIO ~FII 3FI:! 3FI5 3F24 3H5 IAII Revised: ttl. • Table LIST OF TABLES Acrotichc Gnd \~l. • • II-I II-II II-IIA II-Ill 11-1\' II-v II- v I 11-\'11 11-\111 111-1 \'-1 \'·11 \'1-1 v I-II \'1-111 \'1-1\' \'11-1 \'II-II \'II-111 \'IIA-l \'IIA-II \'IIA-lIl v11 B-1 \' 11 B-lI \'11C-\ \'IIC-IA \'lIC-lI \'111-1 \'111-11 \'111-\II \'11 I-I\' IX-I IX-II \X·lIA I\:-\II ix-tv I\:-v 1\.-\'1 1\.-\'11 x1-I XI-\I \:1-111 XI-I\' x 1-v X\-\'\ \:\-\'11 Lead ing Particulars and Principal Dimensions , . , . , Recommended 'ut Torques (Inch Pounds) , . Flare Fitting Torques , , . Indicated Oxygen Cylinder Pressures for Given Ambient Temperatures , . Inspection Report - Overhaul Time Limits (Oxygen System Components) . Trouble hooting Chart (Oxygen System) , . Recommended Lubricating Oils . Decimal Equivalents Millimeters , , , . Lubrication (Special \nstructions) " " .,., Inspection Report .. ,., , ,., .. " Control Surface Travel And Tension , , . Troubleshooting Chart (Surface Controls) , , , , . Torque For Effective Wrench Length , , .. Troubleshooting Chart (Landing Gear and Brake System) " . Main Gear Wear Limits , , . 'ose Gear Wear Limits , .. , ,. Propeller Specifications (PA-24-180) , . Timing Data , .. , . , , , , , , . Troubleshooting Chart (Engine) (PA-24-180) , , , . Propeller Specifications (PA-24-250 2(0) , , . Timing Data " , ,. , . Troubleshooting Chart (Engine) (PA-24-250 2(0) , , . ' . Propeller Specifications (PA-24-40m . Troubleshooting Chart (Engine) (PA-24-400) .. , , ,.,., ",. Propeller Specifications (PA-24-160 Turbocharged) ,., . Troubleshooting Chart (M ixture Control Indicator) , , . Troubleshooting Chart (Engine - Turbocharged) , , .. , . Specifications. Duke ModeI414Q..00-218 Electric Fuel Pump .. , ,. Flow Versus Pressure Chart at 14 V,D.C. , , . Pump Pressures (Fuel Injection) , , , .. , , . , . Fuel System Troubleshooting , , . Alternator Checks , , . Circuit Load Chart (Models Prior To 1970) . Circuit Load Chart (Models 1970 And Later) , . Lamp Replacement Guide , . , . Index Electrical Svstern Schematics , . Electrical Wire Coding , . Electrical Svrnbols , , . Troubleshooting . Vacuum Svsrern , , . Directional Gyro Indicator , , , .. Gyro Horizon Indicator , . Rate Of Climb Indicator ,.,. Altimeter . Airspeed Tubes And Indicator , _ , . Magnetic Compass , , , , . IRI' IRI9 IB~~ JCI~ ICI5 ICIX 1("19 IC~~ IC~~ ID20 lFI5 IH5 IJ~':\ 115 I\. 1,:\ 1L15 2\ 19 :8 \I :R~I :CI~ 2D2~ 2EH :r-:l :G2 2GII' :H2 211 2.1 1~ 2.1 I.; 2.1 15 2.117 ~B16 ~D~ ~D5 ~D6 ,:\07 ~DII ~D12 ~E22 ~F2~ ~G6 ~G7 ~GX ~G9 ~GIO ~GII REVISED: 11/1/82 IAl2 PIPER COMANCHE SERVICE MANUAL LIST OF TABLES (eont.) •Table Aerofiche Grid 1'0. XI-VIlI Xl-IX XI-X XI-XI XI-XII Xl-XIII XI-IV XI-V XlI-I Manifold Pressure Indicator . Tachometer . Engine Oil Pressure Gauge . Fuel Pressure Gauge . Turn And Bank Indicator .............•.................................. Oil Temperature Indicators . Fuel Quantity Indicators ..........•........••.•.......................... Fuel Quantity Indicator . Index - Electronic Installation Schematics ...............•.................. 3GI2 3GI3 3G13 3GI4 3GI5 3G17 3GI8 3GI9 3D7 • REVISED: 4/10/81 tAt3 • • • • lA14 INTENTIONALLY LEFT BLANK • SECTION I INTRODUCTION Paragraph Aeroficbe Grid \0. I-I. General......... A 16 1-3. Scope Of Manual Alb 1-7. Description............................................................... A 16 1-9. Wing.................... A 16 1-10. Empennage...................................................... AI6 I-I I. Fuselage.................................................... A 16 I-I~. Landing Gear AI6 1-13. Hydraulic Systems.... . A16 1-14. Engine And Propellers............................................. AI6 1-15. Fuel System ~ · All 1-16. Flight Controls................................................... A 17 1-17. Radio........................................................... AI7 I-IS. Cabin Heater. Defroster. And Fresh Air System. .... . .. . . . . . . .. . . . . . . A 1'7 1-19. Instrument And Autopilot Systems.................................. A 1'7 • •ISSl'ED: 8/18/72 tAl5 • • • PIPER COMANCHE SERVICE MANUAL SECTION I INTRODUCTION 1-1. Gala. 1·2. This manual conains sct'Iice and maintenance irlsuue:t:ions for the Piper PA·24 Comanche (Figure 1-1). dcsiped and manufaCtUred u a venatile aircnft in the penonal and businas aviation field. by the PiperAimVt Cotporation. Lock Haven. PClUllYIVUlia. 1-3. Scope Of Maaual. 14. Sections II and 111 comprise the service pan:of this manual. wbereas Seet:ions IV throuah XII comprise the maintenance instructions. The service iDscructions include p'0llDd handlint. servicm,. and inspection. The maintenance instrUctions for each system include troublahooan" ranoval and iDsullation of com ponents. and COlTC'Ctive mamteMJlce and tcstinl; each major system of the aircn.ft is covered in I separate section 1·5. Only qualified personnel should perform the operations described in this manual. 1~. The description of the airc:rait included in this section is limited to ICDera1 infomation: however. FiBures 1·2 throulh 1-10 lives specific extcma1 dUnCftlions. Table IHI lisa the IClldm, particulan and principal dimensions. 1·7. Dacription. 1-8. The Piper PA-24 Comanche is I four place. (optional 5th and 6th seats arc available in the P.'o·2....260. Serial Sos. 24-4300 and up) sinllC'"CDIine. loW"Wi"l monoplane of all metal construction. Paragraphs 1-9 through 1-19 provide descriptions of the major components and systems. 1·9. Wm,. The laminar flow win, is of all·meta1 stresICd1k.in. tilU-eantilcvcr. low·wing desip. consisting of two willi panels bolted tOiether at the ccntCf of the fusclqe. The winJ tip are removable. The ailerons an: cable and push rod controlled and are statically and dynamically balaaccd. The trailin, edp wing flaps are manually or electrically operated. HO. Empamap. The CtnpeftDqe consists of the f1l1. stabilators. and stabilator trim tabs. The rudder and stabilators ate dynamically and statically balanced. 1·11. Fuselap. The tilse1ate consists of three baic units: the eftlinc section. the cabin section. Uld the sheet-metal tail cone. 1-12. Landini Gar. The landinggcu is an electrically operated tricycle IQI'. consiRinr of a nose wheel and two main wheels. 1·13. Hydraulic Systems. The brake system is operated by a hand lever or by toe brakes. 1·14. EnJinc And Propellers. INTRODUCTION ISSUED: 8118n2 lA16 PIPER COMANCHE SERVICE MANUAL I EqiDa PropcUm Honepower Ocaae I I i PA·24-180 O·3600A Huaell HC·92ZX-8D 180 91196 McCaulry ZD36C14 PA·2...Z50 0·540-A HaraeU HC-8ZXX·ID 250 91/96 [Q.54O-C or HC·AZXX-l McCauley 2DJ6C28 I PA·24-260 0-540-E HC-c2YX·IA or 260 91/96 1Q.540-D. N HC-cZYX-lB I I PA-Z4-400 1Q.72o-A HC·A3VX-4 400 100/130 I PA·Z4-Z60 "C" 1<r5040-N He·EZVR-lB 260 91/96 [Q.S40-R HC·E2YR·1BF 260 100/130 • 1·15. Puel System. The fuel system on the PA-Z4-11O consilb of nro rubber cells in the winp. one engine driven pump. and one electrical auxiliary pump. On the PA-2....Z$O the fuel system is similar. with the exception that there are two electrical auxiliary PwbPS in addition to the CJIIiDc driven pump and two auxiliary fuel ceUs as optional equipment. The fuel system on the PA-24-260 has two fuel cd1s u standard • equipment. twO fuel cells as optional equipment. one eDJine dtiYCft pump and two eleetric auxiliary fuel pumps with carburetor equipped e.a or one electric auxiliary plUllp with fuel injection enpnes. The PA.Z"-400 syRem consistS of four fuel cells. one CftpC dri¥cn pump and one elecaic auxiliary pump. 1·16. PU....t Conaoll. The fllsht controls arc conventional equipment. consisrinl of a control wheel which operates the ailerons and stabiJatOl'S. and pcdais which operate the rudder. Duplicate contrOls are provided for the copilot. 1-11. Radio. Provisions for radio installations consist of microphone and headset jacks and mounting bracken. I loudspeaker. necessary winn" and panel space for It last four radios. 1-18. tabiD Heater. Detro'Uf. ADd Frail Air SyRnl. Heater air for the cabin and defrostct is obtained directly from the exhauSt system muffler shroud. On the PA-Z4-180 and PA·Z4-250 fresh air is obtained through intakes It the ~e cowl, and an air intake at the top of the fuxJace providinl air to the individual scats through the air line type overhead vena. On the PA·24-Z60 and PA-204-400 fresh air is taken from the lcacling edge of each wing to the forwud portion of the cabin and throulh 1ft intake located on the dorsal fin directing air throuth overhead ventS. 1-19. InstrUment .-\bd AutoPilot Systeml. Provisions for inltnUnent installation include panels for engine instruments and ldvance flight instrUments. :u wdl u for 1ft AutoPilot system .which consists of four principal pam: a modified directional gyro. a modified JYfO horizon. Ii motor-driven actuator, and an amplifier. INTRODUCTION ISSUED: 8/18n2 tAl7 • • • • THIS PAGE INTENTIONALLY LEFT BLANK tAt8 THIS PAGE INTENTIONALLY LEFT BLANK lA19 • • • • SECTION II HANDLING AND SERVICING Paragraph Acrofiche Grid '0. • • ~-1. ~':!. 1-). 1-4. 1-5. 2-6. 1-7. :>7a. 1-l<. 1-9. 1-11. 2-30. 2-40. 1-41. 1-44. Introduction . Dimensions . Weight and Balance Data . Serial 'umber Plate . Access and Inspection Provisions . Tools and Test Equipment . Torque Requirements . Torque Wrenches . Handhold and Walkwavs . Ground Handling : . 1-10. Introduction to Ground Handling . 1-IOa. Torque Wrenches . 2-11. Jackinz . 1-11. \\"eightng . 2-1). Leveling . 2-14. Mooring . 2-15. Parking: . 1-16. Locking Airplane . 2-17. Towing . 1-Il<. Taxiing . External Power Receptacle . 2-10. Operation of External Power Receptacle . Cleaning . 1-21. Cleaning Engine Compartment . 1-1~. Cleaning Landing Gear . 2-14. Cleaning Exterior Surfaces . 1-15. Cleaning Windshield and Windows . 1-16. Cleaning Headliner. Side Panels and Seats . 2-17. Cleaning Carpets . Servicing ' . 1-29. Introduction to Servicing . Landing Gear Svstern "...............•.. 1-~ I. Servicing Landing Gear . Oleo Struts .............................................•................. 1-n. Servicing. Oleo Struts . 1-34. Filling Oleo Struts . 1-J5. Inflating Oleo Struts . Brake System . 1-:P. Servicing Brake System . 2-3l<. Filling Brake System Reservoir . 2-39. Draining Brake System . Tires . 1-41. Servicing Tires . Power Plant . 1-4~. Sen icing Power Plant . Propeller . IA12 IA12 1.-\22 IA21 IA11 1.-\11 IA13 IA1~ 1.-\13 1.-\13 1.-\23 tBIX 1823 1813 1824 IC1 IC1 IC3 IC3 IC3 K3 IC3 IC4 lC4 IC4 IC4 IC5 IC5 IC5 lC5 1C5 ICo lCo ICo IC6 lCi res ICt\ ICt\ IC~ IC~ IC9 tC9 1(9 'IC9 ICIO REVISED: 11/1/82 lA20 2..0. 2~8. 2-52. 2-54. 2·13. 2-14. PIPER COMANCHE SERVICE MANUAl 2-45. Savic:inc Ptopeller • . . . . • . • • • . . . . . . . . . . • . . . . . . . . • . . . . .. ICIO Induction Air Filter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ICIO 2-47. Scrvic:i.allnduetioa Air Filea' .•....••.....••............•. ICIO Fuel System .....•....................................... ICIO 2-49. FiDiDt Fud TIDks • . . . . . . . . . • . . • • . . • . • • . • . • . . . . • . • . • . • ICIO 2·50. DIIiJUDI Fuel Valve aDd SU'lincrs . . . . . . . . . . . . . . . . . . . . . . . . . . . ICn 2·St. DraiDiD, Fuel Sysccm . . . . . . . • . . . . . . . • . . . . . . . . . . . . . . . . .. Ie12 Elec:trica1 Systan ...•.....................................• ICl2 2·53. Scmcial E1ecuica1 Sysmn . . . . . . . . . . . . . . . . . . . . . . • . • . . . . .. ICl2 OzyJco Systelll ..............•.•..•...•.................... ICl2 2·55. DscripaoD of Oxyp Syscem • • • • • • • . • • • . • • . • • . • • • • • . • • . . . ICU 2-56. Troublesbooq. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ICl2 2-57. Oxypn System Safety PrecaatioDS ••••••••••.••••••••••••••• ICU 2-58. Fillina Oxypn CyliDder . . • . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. IC13 2-59. IlIIpcetion aDdOverhaul Time Limits . . . . . . . • • • . . • • . . . . . . . . . .. ICl4 2-60. TCItiq for Leaks ............•...•................... IC15 2-61. . Maintenance................... . . . . . . . . . . . . . . . . . . . . ICl5 2-62. ClaDiD, Operations . . . . . . . • . . . . . • . . . . . . . . . . . . . . . • . . . . . IC15 2-63. Ranewa1 of 0XYFn Cytinder and Repa1tor .. . . . . . . . . . • • • • • . . . . . ICl6 2-64. IDlU1lationofOxypn Cyuder &Dei Rcp1ator ICl6 2-65. Reaum! of Filler Valve . . . . • . . . . . . . . . . . . . . . . . . . . . . . . . . . . ICl7 2-66. l-.llatioa of filler Valve . . . . . . . . . . . . . . • . • . . . . . . . . . . . . . . . ICI7 2-67. Rcmewal of PraIUte GIIlF ..............•.•.............. ICl7 2-68. InsuUaaoa of Prasure GIUF ICl7 2-69. Ranovl1 of Oudets .....................••............ ICl7 2-70. IDSUllation of Ouam . . . . . . . . . . . . . . • . . . . . . . . . . . . . • . . . . . ICl7 2·71. Purging Oxypn system ..•••.•..•.••.....•.............. ICl8 2-72. CleaoinlofFaccMasks tCl8 Lubrication ICl9 Oil Systems <ElJIine) •.....•.•...••••....•..•.........•.•.... ICl9 2·15. Savicins Oil System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. lCl9 2·76. Dramn. Oil Swnp . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . icrs 2-77. Fillint Oil Sump ...........•....•....•............... ICl9 2-78. Oil Screen (SllCtion) . . • . . . • . . . . . . • . . . . . • . . . . . . . . . . . . . . . IC20 2·79. Oil ScreeD (Pra:sure) ..•.......••..••.••••••..•.••..... IC20 2·80. Oil Filta' (FuU Flow) .....•............................ tClI 2-81. Rceommadadons for CbuaFnI Oil IClI 2·82. Lubrication IDIUllctions IClI 2·83. Application of Oil . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IC2l 2-84. Application of Grcuc .•..............•................. IC2l 2·85. Lubrication Chart .....•••...•.........•..•........... ICll tA21 • • • • • • PIPER COMANCHE SERVICE MANrAL SECTIO!' II HA~DLl!'G Al'4D SERVICI~G 2-I. Introduction. This section contains routine handling and servicing procedures that are most frequently encountered. Frequent reference to this section will aid the individual by providing information such as the location of various components. ground handling procedures. routine service procedures and lubrication. When any system or component requires service other than the procedures outlined in this section. refer to the appropriate section for that component. 2-2. Dimensions. The principal airplane dimensions are shown in Figures 2-1 thru 2-5 and are listed in Table II-I. 2·3. Weight and Balance Data. When figuring various weight and balance computations. the weight and empty weight center of gravity of the airplane may be found in the Weight and Balance Form of the Airplane Flight Manual. 2-4. Serial !':umber Plate. (Refer to Figure 2-6.) Theserial number plate on the various PA-24 model aircraft can be found at one of the following locations: On the inside of the baggage compartment door. on the upper right side of the firewall (engine side). on the fuselage adjacent to the left side of the tail skid. 2-5. Access and Inspedion Provisions. The access and inspection provisions for the airplane are show n in Figures 2-6 thru 2-8. The component to be serviced or inspected through each opening is identified in the illustration. All access plates and panels are secured by either metal fasteners or screws. The floor panels may be removed by first removing the desired seats. then sliding the carpet edges from under its retainer strips. lifting the edges and removing the carpet attaching screws. Remove the carpet. thus exposing the floor panel attaching screws. To enter the aft section of the fuselage. remove the lower rear baggage compartment upholstery panel by removing the attaching screws. CAUTIO!' Before entering the aft section of the fuselage. be sure the airplane is supported at the tail skid. 2-6. Tools and Test Equipment. Because of the simplicity and easy accessibility of components. few special tools outside normal shop tools will be required. Tools that are required may be fabricated from dimensions given in the back of the section that pertains to a particular component. REVISED: 4/3/78 tA22 HANDLING AND SER\'ICI~G PIPER COMANCHE SERVICE MANUAL 2-7. Torque Requirements. The torque values given in Table II-II are derived from oil-free cadmium-Pie threads and are recommended for all airframe installation procedures where torquing is required. unk otherwise noted in sections where other values are stipulated. Engine torque values are found in the latest revision of Avec-Lycoming Service Bulletin No. 268. Propellertorquevaluesarefound in Sections VIl. VilA. VIlB and VIlC of this manual. Table 1I-IlA lists the torque values for flared fittings of various sizes and materials. 2-7a. Torque Wrenches. Torque wrenches should be checked daily and calibrated by means of weights and a measured lever arm to make sure that inaccuracies are not present. Checking one torque wrench against another is not sufficient and is not recommended. Some wrenches are quite sensitive as to the way they are supported during a tightening operation. Any instructions furnished by the manufacturer must be followed explicitly. CAUTION Do not overtorque fittings. NOTE When flared fittings are being installed, ascertain that the male threads are properly lubricated. Torque fittings in accordance with Table 1l-11A. When it is necessary to use a special extension or adapter wrench together with a torque wrench a simple mathematical equation must be worked out to arrive at the correct torque reading. Following is the formula to be used: (Refer to Figure 2-8a.) • 2-8 Handhold and Walkways. A fixed handhold is located on the right side ofthe fuselage. above the re... window. Walkways of four parts Devoe non-skid compound and one part black enamel are painted on the right wing and flap. CAUTION Avoid damage to the wings by stepping only on the walkway. 2-9. Ground Handling. 2-10. Introduction to Ground Handling. Ground handling covers all essential information governing and handling of the airplane while on the ground. This includes jacking, weighing. leveling. mooring. parking. towing and taxiing. When the airplane is handled in the manner described in the following paragraphs. damage to the airplane and its equipment will be prevented. • HANDLING AND SERVICING REVISED: 4/10/81 tAl3 • ooaa 2113 PIPER COMANCHE SERVICE MANUAL .....---150·'---.;.;.;.., 5· OIH!IltAL \t--_llO..r--'!"""""-~*J ~1I~ M.14.dO I 14.' '"' " ·u•• 1~.1 t--------Z9. l/4..·-------~ .... 24.110 114·1 ,",14. UtI I/1lC1..1 ......-------Z9. l/Z·----------4..·14 .110 .I~ 114 • In- &NO ....., --------Z9. ~/1.·--- --4 ,......----- 4311-. ------------------. • • FIGURE 2.1. THREE·VIEW Of CCMANQ4E PA••,80 .... PA·.ZSO HANDLING AND SERVICING REVISED: 413/78 lA24 • • • PIPER COMANCHE SERVICE MANUAL _---150-;","--_ STA.IS.'" ~-----43Ii:-'---------------- I ,. OIHEDRAL ' ':t! ll'l SI -I~ ~; 1- W1>- I~ ~ :*'5: 15 • I~ Z99 il w I~ a ..., III FIOURE 2-2. THREE VIEW OF COMANCHE PA.24-2IO S.i.1 NOI. 24-4000 to 24-4~, 24-4~8 to 24-4219 HANDUNG AND SERVICING REVISED: 413/78 181 PIPER COMANCHE SERVICE MANUAL 11" ----,....---- • -115/f'- i .....r -----4313/4"----....;;;.----------__ . nr--- I ~ • ~~-=3!L=-"'----II. I II...-------3131/1,..'--------1 I FIGURE 2·3. THREE·V1EW OF COMANCHE PA·24e2lO Seri.. Nos. 24-4247, 24-4300 to 24-4782, 24-471& • 24 .103 incl. HANDLING AND SERVICING REVISED: 413178 IB2 .." • • '·OIHEDRAl. •.. " 150"--_ ~-----.3'-i-"---~~----------..., uu PIPER COMANCHE SERVICE MANUAL. • • • FIGURE 24. THREE·VIEW OF COMAN04E PA.:M0400 HANDLING AND SERVICING REViSED: 413/7& IB3 • PIPER COMANCHE SERVICE MANUAL ----12· ... --- -----3S·I1.1S..,---------------_ -----..... _- I T l ...· c=~=-------- -1'1.12"- -------25'1.22" ------- FIGURE 2·5. THREE·VIEW OF COMANCHE PA-~ao Serilll NQL 24-0'783. ae 'SOl ..d up HANDLING AND SERVICING REViSED: 4/3178 IB4 • • • • PIPER COMANCHE SERVICE MANUAL • '"ll 1'''''11 IUUllC' All Sl(IIOI IWII '1111------ LICCACI ("'U'.'I' ,"t" "1" LICUCI (1llI'1I1.,., 000. ... '!ilL U •• 'lllll'UTI ISlILI "---AU" HUeu•• • Wler.PUIl III! '''AID Itm~ 'III(L In.-alit 'lfU SII.., • Figure 2-6. Access Panels and Plates PA-24-l80. PA-24-2S0 and PA-24-260, Serial Nos. 24-4000 to 24-4246. 24-4248 to 24-4299 lR5 HANDLING AND SERVICING REVISED: 4/3/71 PIPER COMANCHE SERVICE MANUAL TABLE II-I. LEADING PARTICULARS AND PRINCIPLE DIMENSIONS • MODEL ENGIl"E PA-24-180 PA-24-250 Carburetor Induction Manufacturer Model FAA type certificate Rated horsepower. RPM: Full throttle Oi\, SAE number Oil sump capacity Fuel. aviation grade. minimum octane Carburetor. Marvel-Schebler Fuel injector. Bendix Magnetos (2). Scintilla: left Right Left Right Magneto timing Magneto point clearance Spark plugs (shielded): Spark plug gap setting Firing Order Tachometer drive. ratio to crankshaft Starter: Delco-Remy, 12 volt Prestolite, 12 volt Generator. Delco-Remy: 12 Volt (35 Amp) 12 Volt (50 Amp) Generator voltage regulator. Delco-Remy 12 volt (35 amp) 12 volt (50 amp) Fuel pump drive A vee-Lycoming Avec-Lycoming 0-360·A IA or 0-360-A ID 0-540-A 1AS-: 0-540-A I B5. 0-54D-AIC5 or 0-540-AID5 286 295 180 HP @ 2700 RPM 250 HP @ 2575 RPM See Table II-VI See Table II-VI 8 qts, 12 qts, 91/96 91'96 MA-4-5 MA-4-5 S4LN-21 I S6LN2P. S6LJ\-21 4 S4LN-20' S6LN-203• S6LN-21 4 S4LN-2oo 2 S6LN-2oo~ S4LN-204 2 S6LN-204 s 25 degrees BTC 25 degrees BTC 0.018 j: 0.006 in. 0.018 :t. 0.006 in. •(6) (6) (6) (6) 1-3-2-4 1-4-5-2-3-6 0.5:1 0.5:1 1109689 11095 II 1101900 1101900 1101915 1101915 1118704 11 18704 1119224 1119224 Plunger Plunger I. D-360·A 1A 2 0-360-AID 3. D-S40-AIA5 4. O-SAO-A 185. 0-540-,4, 10 5. O.~AID5 6. Refer 10 laleSI revision of lycoming Service Instruction So. 1042. HANDLING AND SERVICING REVISED: 4/10/81 IB6 • • PIPER COMANCHE SERVICE MANUAL TABLE II-I. LEADI?'G PARTICULARS AND PRINCIPAL DIMENSIO?,S (cont.) MODEL PA-24-250 Fuel Injected PA-24-260 Carburetor Induction ENGI?'E Manufacturer Avec-Lycoming Avec-Lycoming Model IO-540-C IB5 0-54Q-E4A5 FAA type certificate IE4 295 Rated horsepower. RPM: Full throttle 250 HP @ 2575 RPM 260 HP @ 2700 RPM Oil. SAE number See Table II-IV See Table II-IV Oil sump capacity 12 qts. 12 qts. Fuel. aviation grade. min octane 91 ;96 91;96 Carburetor. Marvel-Schebler MA-4-5 Fuel injector. Bendix RSA-5ADI Magnetos (2). Scintilla: Left S6LN-200 S6LN-200 Right S6LN-204 S6LN-204 Magneto timing 25 degrees BTC 25 degrees BTC Magneto point clearance 0.018.± 0.006 in. 0.018 J:. 0.006 in. Spark plugs (shielded): (6) (6) • Spark plug gap setting (6) (6) Firing Order 1-4-5-2-3-6 1-4-5-2-3-6 Tachometer drive. ratio to crankshaft 0.5:1 0.5: I Starter: Delco-Rerny 12 volt 11095II 11095II Presto lite. 12 volt MZ-4206 Generator. Delco-Remy: 12 volt (35 amp) 1101900 12 volt (50 amp) 1101915 Generator voltage regulator. Delco-Remy . 12 volt (35 amp) 1118704 12 volt (50 amp) 1119224 Alternator. Delco-Rerny 12 volt (70 amp) 1100660 or 1100717 Alternator voltage regulator. Delco-Rerny 9000590 Alternator overvoltage relay. Delco-Remy 1115831 Alternator. Prestolite 12 volt (70 amp) Alternator voltage regulator. Prestolite Alternator overvoltage relay. Prestolite Fuel pump drive Plunger Plunger 6. Refer 10 latest revision of Lycoming Service lnstruction So. 1042 • IB7 HANDLING AND SERVICING REVISED: 4/10/81 PIPER COMANCHE SERVICE MANUAL TABLE II-I. LEADING PARTICULARS AND PRINCIPLE DIMENSIONS (cont.) • MODEL PA-24-260 Fuel Injected - Serial Nos. 24-4783, 24-4804 and up PA-24-260 Fuel Injected - Serial Nos. 24-4000 to 24-4782. 24-4784 to 24--4803 inclusive ENGINE Manufacturer Avec-Lycoming Avec-Lycoming Model IQ-S40-N lAS IQ-S4D-D4AS FAA type certificate IE4 IE4 Rated horsepower. RPM: Full throttle 260 HP @ 2700 RPM 260 HP @ 2700 RPM Oil, SAE number See Table II-IV See Table II-IV Oil sump capacity 12 qts 12 qts. Fuel aviation grade: Minimum octane 91/96 91/96 Carburetor. Marvel-Schebler Fuel injector. Bendix RSA-SADI RSA-SADI Magnetos (2). Scintilla: Left S6LN-200 S6LN-200 Right S6LN-204 S6LN·204 Magneto timing 25 degrees BTC 25 degrees BTC •Magneto point clearance 0.018 ± 0.006 in. 0.018 ±. 0.006 in. Spark plug (shielded): (6) (6) Spark plug gap setting: (6) (6) Firing Order 1-4-S-2-3-6 1·4-5-2-3-6 Tachometer drive. ratio to crankshaft O.S: I 0.5:1 Starter: Delco-Remy, 12 volt 1109511 Prestolite. 12 volt MZ-4206 MZ·4206 Generator. Delco-Rerny: 12 volt (35 amp) 12 volt (SO amp) Generator voltage regulator. Delco-Remy: 12 volt (3S amp) 12 volt (50 amp) Alternator. Delco-Remy 12 volt (70 amp) 1100660 or 1100717 Alternator voltage regulator. Delco-Remy 9000590 Alternator overvoltage relay. Delco-Remy 1115831 Alternator. Prestolite 12 volt (70 amp) ALX8421 Alternator voltage regulator. Prestolite VSF7203 Alternator overvoltage relay. Prestolite XI7621 Fuel pump drive Plunger Plunger 6. Refer 10 late'l rev is.on of Lycoming Service Instructions ~o. 1042. lR8 HANDLING AND SERVICI' REVISED: 4/10/81 • PIPER COMANCHE SERVICE MANUAL TABLE II-I. LEADING PARTICULARS AND PRINCIPLE DIMENSIONS (cont.) MODEL PA-24-26O Turbo PA-24-400 ENGINE Manufacturer Avec-Lycoming Avec-Lycoming Model 10-54()"RIA5 IO-72Q..AIA FAA type certificate IE4 IEI5 Rated horsepower. RPM: Full throttle 260 HP @ 2700 RPM 400 HP @ 2650 RPM Oil, SAE number See Table II-VI See Table II-VI Oil sump capacity 12 qts 17 qts Fuel aviation grade: Minimum octane 100; 130 100; 130 Carburetor. Marvel-Schebler Fuel injector. Bendix RSA-5ADI RSA-IOADI Magnetos (2). Scintilla: left S6lN-1209 S8LN-701 Right S6LN-1208 S8LN-705 Magneto timing 25 degrees BTC 20 degrees BTe Magneto point clearance 0.016 .1 006 in. 0.019 i 0.001 in. Spark plugs (shielded): (6) (6) Spark plug gap setting (6) (6) • Firing Order 1-4-5-2-3-6 1-5-8-J.2-6-7-4 Tachometer drive, ratio to crankshaft 0.5: 1 0.5: 1 Starter: Delco-Remy, 12 volts 1113471 Prestolite, 12 volt MZ~4206 Generator. Delco-Rerny: 12 volt (35 amp) 12 volt (50 amp) Generator voltage regulator, Delco-Rerny 12 volt (35 amp) 12 volt (50 amp) Alternator. Delco-Remy 12 volt (70 amp) 1100660 or 1100717 Alternator voltage regulator, Delco-Rerny 9000590 Alternator overvoltage relay, Delco-Remy 1115831 Alternator. Prestolite 12 volt (70 amp) ALX8421 Alternator voltage regulator, Prestolite VSF 7203 Alternator overvoltage relay, Prestolite XI7621 Fuel pump drive Lear Seigler RG·17980 lear Seigler RG-17980 6. Rc:fcr to latest reVISIOn of lycominl Service Instruction ~o. 1041. • IB9 HANDLING AND SERVICING REVISED: 4/10/81 PIPER COMANCHE SERVICE MANUAL TABLE 11·1. LEADING PARTICULARS AND PRINCIPAL DIMENSIONS (cont.) • MODEL PA-24-180 PA-24-250 FUEL SYSTEM Inboard (main) fuel cells Capacity (each) Unusable fuel (each) Outboard (auxiliary) fuel cells Capacity (each) LANDING GEAR Type Shock strut type Fluid required (struts and brakes) Strut exposure (exposure under static load) Wheel tread Wheel base Nose wheel travel Wheel. Nose Wheel. Main Brake type Tire. Nose Tires. Main Tire pressure. Nose Tire pressure. Main OVERALL Gross weight Gross landing weight Two 30 U.S. gal 2 U.S. gal Electrically operated Combination air and oil MIL-H-5606 2.75 in. 9 ft. 8 in. 6 ft. 6.62 in. Left 20°. Right 20° Cleveland 38501 Cleveland 30-70, Serial Nos. 24-1 to 24-3306 Cleveland 40-58, Serial Nos. 24·3307 and up Cleveland 3000·250. Serial Nos. 24-1 to 24-3295 Cleveland 30-41, Serial Nos. 24-3296 and up 6:00 x 6, 4 ply rating 6:00 x 6,4 ply rating 27 psi 27 psi 25501bs. 25501bs Two 30 U.S. gal 2 U.S. gal Two IS U.S. gal Electrically operated Combination air and oil MIL·H-5606 2.75 in. 9 ft. 8 in. 6 ft. 6.62 in. Left 20°. Right 20° Cleveland 38501 Cleveland 30-70, Serial Xos. 24-1 to 24·3306 Cleveland 40-58. Serial ~. 24-3307 and up Cleveland 3000-250. Serial Nos. 24·1 to 24-3295 Cleveland 30-41, Serial Nos. 24·3296 and up 6:00 x 6, 4 ply rating 6:00 x 6. 6 ply rating 27 psi 42 psi 2800 lbs 9 or 2900 lbs 10 2800 lbs 9 or 2900 Ibs 10 9. Serial Sos. 24-1. 2~ 103 10 24-2002 incl. 2~2004 to 2"2298 incl. 10. Serial :\OS. 24-2003. 24-2299 and up. IBI0 HANDLING AND SERVIC. REVISED: 4/10/81 • PIPER COMASCHE SERVICE MANrAL TABLE II-I. PARTICL'lARS A'O PRI~CIPAl 01 ME\SIO~S (cont.) • \10DEL Fl'El SYSTE\1 Inboard (ma in) fuel cells Capacitv (each) L'nusable fuel (each) Outboard (auxiliary) fuel cells Capacity (each) Inusable fuel leach) Typ~ Shock strut type Fluid required (struts and brakes) Strut exposure (exposure under static load) \\' hee 1 tread Wheel base \ose \\ heel trav el Wheel. \ose Wheel. Main Brake ty pe Tire. \oslo: Tires. \1ain Tire pressure. \ose Tire pressure. \Iain O\'ERAll Gross weight Gross landing weight PA-24-260 Serial Nos. 24-2400 to 24·4782, 24·4784 to 24·4803 inclusive Two 30 L'.S. gal 2 L'.S, gal T\\o 15 L,S. gal Electrically operated Combination air and oil 2.75 in. 9 ft. Min, 6 ft. 6.62 in, left 20 c . Righ t 20 c Cleveland 3850 J Cleveland 40-84 Cleveland 30-41 6:00 x 6. 4 ply rating 6:00 x 6. 6 ply rating 27 psi 42 psi 2900 Ibs II or 3100 Ibs ,~ 2900 Ibs 11 or 2945 Ibs Ie PA-24':!60 Serial 'os. 24-47~3. 24·4~04 and up Two 30 L'.S. gal '1 L". S. gal Two 15 LS. gal Electrically operated Combination air and oil MIl-H·5606 2.75 in. \ose. 2.50 in. \tain 9 ft. 8 in. 6 ft. 6.62 in. left 20". Right 20 c Clevela nd 3~50 I Cleveland 40·~4 6:00 x 6. 4 ply rating 6:00 x 6. 6 ply rating 27 psi 42 psi 32001bs. 3040lbs • II "([1.1: ,." : ..I-.~I> ..C_ ~J·~l1l\1 1<' :J..J:JI> me! :J.J:J~ to :J.J:qq met I:, ~,,·rl.1 't h ~J··C"'''. ~J·J.~IJ(I III ~"".J-,..,: mel. ~~-.J"'l\-l h.l :-l--I.l\O':\ incl. IBll HANDLll\G A~D SER\'ICI'G RE\"ISED: 4/10/81 PIPER COMANCHE SERVICE MANl:AL TABLE II-I. LEADI\G PARTlCtLARS A;\D PRI~CIPAl DIME\SIO\S tcont.) • \10DEL Fl'EL SYSTE\1 Inboard (maim fuel cells Capacity reacht l.nusable fuel (each) Outboard (auxiliary) iuel cells Capacity (each) Lnusable fuel (each) L.-\ xD I:'\G GEAR Type Shock strut type Fluid required tstrust and brakes) Strut exposure (exposure under static load) Wheel tread Wheel base \ose \\ heel tr avel Wheel. \ose Wheel. Main Brake type Tire. :'\ose Tires. Main Tire pressure. Xose Tire pressure. Main O\'ERALL Gross weight Gros.. landing "eight PA-24-400 Two 30 L'.S. gal 3 U.S. gal Two 35 U.S. gal Electrically operated Combination air and oil MIL-H-5606 2.50 in. 9 ft. 8.375 in. 6 ft. 6.62 in. Left 20°. Right 20° Cleveland 38501 Goodrich 3-1038-1 Cleveland 40-90 Goodrich 2-8521 Serial Xos. 26-2 to 26-129 incI. Cleveland 30-23 Serial Xos. 26-130 and up 6:00 x 6. 6 ply rating 6:00 x 6. 6 ply rating 42 psi 42 psi 36001bs. 36001bs. • HAN"OLING A'O SER\'ICI. REVISED: 4/10/81 IB12 • PIPER COMANCHE SERVICE MANl'Al TABLE 11-1. LEADI:\G PARTlCL:lARS Al\D PRI~CIPlE D1MEl'SIO~S (cont.) • • \10DEL PROPELLER Manufacturer Type Hub model. McCauley Hartzell Blade model. McCauley Hartzell Diameter. McCaule\ Hartzell . Diameter. min .. Mcf'aulev Hartzell . Blade Angle (low pitch)". \1cCauley Hartzell Blade Angle (high pitch)". McCauley Hartzell Control governor Governor model. Woodward Hartzell McCauley or Hartzell Constant speed (two blades) :!D 36C 14 HC-92ZK8D D-2101 78KM-4 8447A-12A 74 in. 72 in. 72 in. 70.5 in. 12.7° .± 0.2° 13° 27.5° 17° Woodward or Hartzell 210305 D 1-5 IB13 PA-24-250 Carburetor Induction McCaul(\' or Hartzell Constant' speed (tWO blade" I 2D 36C28 HC-82XK I D or HC-A2\K-1 D-2286 80M M-6 V8433:\-7 74 in. 'n in. 73 in. 76 in. 15.7° Z 0.2° 14.5° .10.15'" 32° .1 0.5° 31° to 33° Woodward or Hart/ell A210305 8-4-2 HANDLING A!'iD SER\'JCJ~G REVISED: 4/10/81 PIPER COMANCHE SERVICE MANt:AL TABLE II-I. LEADI~G PARTICl:LARS A:\D PRI~CIPLE DIME~SIO~S tconr.) • HC-A2VK-l HC-C2YK-1 A or HC-C2YK-IB \'8433~-7 8467-7R 77 in. 77 in. s 76 in. 75 in. 14.5° .: 0.15° 15° 31° to 33° 32° to 34° •Hartzell Hartzell A2J030S B-4-2 F-4-4 or F-4-4A MODEL PROPELLER Manufacturer Type Hub model. McCauley Hartzell Blade model. McCaule\' Hartzell . Diameter. '\1cCauley Hartzell Diameter. min .. McCaule\' Hartzell . Blade Angle (low pitch!". Mcf'auley Hartzell Blade Angle (high pitch)", McCauley Hartzell Control governor Governor model. Woodward Hartzell PA-24-250 Fuel Injected Hartzell Constant speed (two blades) PA-24-260 Carburetor Induction and Fuel Injected - Serial ~O~. 24-4000 to 24-4782. 24-4784 to 24-4803 incl. Hartzell Constant speed (two blades) ~, Rlad~ angk at ~u In ,,,diU', II, If It become- n~ce"ar) t" reduce the propeller diameter below "" Inches. IN maintenance rebalancing purposes. a placard stalin!! -'A\ Oldconunuous operation between ~5t10 and ~/lO(J rpm above ~5 inche-, manifold pressure" must be displayed ncar the manifold pressure gaU!!~ HANDLING AND SER\"Icl REVISED: 4/10/81 IB14 PIPER COMANCHE SERVICE MANUAL • TABLE II-I. LEADING PARTICULARS AND PRINCIPLE DIMENSIONS (cont) MODEL PA-24-260 P A-24-260 Turbo PA-24-400 Fuel Injected - Serial Nos. 24-4783. 24-4804 and up PROPELLER Manufacturer Hartzell Hartzell Hartzell Type Constant speed Constant speed Constant speed (two blades) (two blades) (three blades) Hub model. McCauley Hartzell HC-E2YR-IB HC-E2YR·IB or HC-A3VK-4 HC-E2YR-IBF Blade model. McCauley Hartzell 8467-7R 8467-7R V8433-7 Diameter. McCauley Hartzell 77 in. 77 in. 77.25 in. Diameter. min .. McCauley Hartzell 75 in. 75 in. 75.25 in. Blade angle (low pitch)? McCauley Hartzell 15° 13.5° + .3°1-.0° 14° • Blade angle (high pitch)' McCauley Hartzell 32° to 34° 32° to 34° 36° Control governor Hartzell Hartzell Hartzell Governor model. Woodward Hartzell F-4-4A F-4-4A F-4-J CONTROL SURFACE TRAVELS Refer to Section V. CONTROL SURFACE CABLE TENSIONS 7. Blade angle al 30 in. radius • HANDLING AND SERVICING REVISED: 4/10/11 IBIS 2110 PIPER COMANCHE SERVICE MANUAL • fllS(LAI( AfT SfCTIIIl ACtUS PLAn / " ..fill. 'AlIl accESS PUTt ISEAL I ..AIEL ,.fIJI. pun ISEAl, ..-IEW:llAlIl BU. pun - Willi ACClSS 1I0U cow. PlAn Figure 2-7. Access Panels and Plates PA-24-260. Serial Nos. 24-4247, 24-4300 and up HANDLING AND SERVICI. REVISED: 4/3 IB16 • 21.1 PIPER COMANCHE SERVICE MANUAL • UR sl""n fUSUA51 1fT 51tllOI ICCISS '1111---- CUI 1111151155101 ICCISS ""Il--~ Sill IUIUIIt fUll III1A ,cms ,UII SUl "---Ill'" IIHCIlIII _SPIt I'" 'UTI 1111' accln lOll ca'" PUll IKIlI lifT ICCISS '1111( _ - lifT fOllII. ICCUS '1II1l .• II..,t" "lC~ s.", OIl fllil ICtUS 'UII • Figure 2-8. Access Panels and Plates PA-24-400 HANDLING AND SERVICING REVISED; 4/3/78 IB17 PIPER COMANCHE SERVICE MANrAL 2-IOa. TORQl'[ WR[~CHES. Torque wrenches should be checked dailv and calibrated bv mean!'. weights and a measured lever arm to make sure that inaccuracies are not present, Checking one torque wren against another is not sufficient and is not recommended. Somewrenchesarequitesensitiveastothewa\thev are supported during a tightening operation. Any instructions furnished by the manufacturer must be folio\\cd explicitly. When it is necessary to use a special extension or adapter wrench together with a torque \\ rench. a simple mathematical equation must be worked out to arrive at the correct torque reading. Following is the formula to be used: (Refer to Figure 2-8a.) T ;:; Torque desired at the part. A ;:; Basic lever length from center of wrench shank to center of handle or stamped on \\ rench or listed for that model wrench. B ;:; Length of adapter extension, center of bolt to center of shank. C ;:; Scale reading needed to obtain desired torque (T). The formula: C;:; A x T EXAMPLE A bolt requires 30 foot-pounds and a 3 inch adapter (one-quarter of a foot or .25') is needed to get at it. You want to know what scale reading it will take on a one-foot lever arm wrench to obtain the 30 foot-pounds at the bolt. C ;:; I x 30 or C = 30 ;:; 24 ft.-Ibs. Remember. the 3 inch adapter must be projecting 3 inches straight along the wrench axis. In general. avoid all complex assemblages or adapters and extensions of flex joints. T • IB18 REVISED: 11/1/82 Figure 2~8a. Torque Wrench Formula HANDLl1\'G AJ'llID SERVin. • PIPER COMANCHE SERVICE MANt:AL TABLE II-II. RECOM~1E~DED xur TORQUES (I~CH-POl:'DS) Torque (self-locking fasteners) - Add thefriction torquefrom Chart A for sizes 8through 7 I{ito the recommended torque from Chart B to get the final torque. This would be the actual reading on the torque wrench. Torque (castellated and non-self-locking nuts) - Use only the torque given in Chart B. Unless other- \\ ise specified. \\ hen castellated nuts are used with a cotter pin on moving joints. do not torque the nut. Turn the nut onto the bolt until proper grip is established and alignment with the cotter pin hole is achieved. Then install the cotter pin. b. TORQl'E REQURE~E~TS: The torque values given in the following tables are recommended for all airframe installation procedures where torquing is required. unless otherwise noted in sections where other values are stipulated. The importance of correct application cannot be overemphasized. Undertorque can result in unnecessary wear of nub and bolts as well as the parts they are holding together. When insufficient pressures are applied, uneven loads will be transmitted throughout the assembly which may result in excessive wear or premature failure due to fatigue. Overtorque can be equally damaging because of failure of a bolt or nut from over- stressing the threaded areas. The following procedures should be followed to assure that the correct torque is applied: a. GE~ERAl REQl'IRE~ESTS: a. b. c. • d. e. f. g. Calibrate the torque wrench periodically to assure accuracy; recheck frequently. Ascertain that the bolt and nut threads are clean and dry (unless otherwise specified by the manu- facturer). If the bolt or nut is specified to be lubricated prior to tightening. the torque range should be reduced 50 percent. lse a bolt length long enough to prevent bearing loads on the threads. The complete chamfer orend radius of the bolt or screw must extend through the nut. Inique torques specified in the text of this manual supersede the torques given in Charts A and B. Refer to the latest revision of Lycoming SSP 1776 for torques on parts used on Lycoming engines. A maximum of two A'960 washers rnav be added under the bolt heads or nuts to correct for variations in material thickness within th~ tolerances permitted. Limitations of the use of self-locking nuts. bolts and screws including fasteners with non-metallic inserts are as follows: I. Fasteners incorporating self-locking devices shall not be reused if they can be run up using only fingers. They may be reused if hand tools are required to run them up. providing there is no obvious damage to the self-locking device prior to installation. Bolts 5 16 inch diameter and over with cotter pin holes may be used with self-locking nuts. ;\uts with non-metallic locking devices may be used in this application only if the bolts are free from burrs around the cotter pin hole. J Do not use self-locking nuts at joints which subject either the nut or the bolt to rotation. 4. 'ever tap or rethread self-locking: fasteners. Do not use nuts. bolts or screws with damaged threads or rough ends. • RE\'ISED: 11/1/82 IB19 HANDLING AND SERVICISG PIPER COMANCHE SERVICE MANt'AL TABLE II-II. RECOMMP'OEO ~CT TORQl'ES (I~CH-POL1~OS)(cont.) CHART A CHART B BOLT FRICTION DRAG SIZE TORQUE flNLBS ) S" 15 10 18 1/4 30 5/16 60 3/8 80 7/16 100 "APPLICABLE TO COARSE THREADS ONLY REVISED: 11/1/82 IB20 COARSE THREAD SERIES BOLTS St.1 T.nsion AN 3 thru AN 20 AN 42 thru AN 49 AN 73 thru AN Bl AN 173 thru AN 186 MS 20033 thru MS 20046 MS 20073 MS 20074 AN 509 NK9 MS24694 AN S25 NK525 MS 27039 NUTS SteelT.nlion Steel Sh..r AN 310 AN 320 AN 315 AN 364 P.N 363 NAS 1022 AN 365 MS 17826 NAS 1021 MS20364. MS 17825 MS 21045 MS 2036S MS 20500 NAS 679 Nut-bolt Torqu. Limits TorQu.Limits lil' in-lb. in-Ibs Min. M.ll. Min. Mill. 8 -32 12 lS 7 9 10 -24 20 25 12 15 114-20 40 SO 25 30 5116-18 80 90 48 5S 3/8-16 160 185 95 110 7/16-14 23S 255 140 155 112-13 400 480 240 290 9/16-12 500 700 300 420 5'8-11 700 900 420 540 3'4-10 1.150 1,GOO 700 950 7/8- 9 2,200 3,000 1,300 1.800 1 -8 3.700 5.000 2,200 3.000 1-118-8 5.500 6.500 3,300 4,000 1-114-8 6,500 8.000 4.000 5,000 HANDLING AND SERVIn. • PIPER COMANCHE SERVICE MA~UAL TABLE It-II. RECOMME:\DED xtr TORQl'ES (I~CH-POL':\DS)(cont.) FINE THREAD SERIES BOLTS BOLTS BOLTS S, ... Tension St ..1T."lion Aluminum AN 3 ,hru AN 20 MS 20004 ,hru MS 20024 AN 30D thru AN 2000 AN 42 ,hru AN 49 NAS 144 thru NAS 158 AN 17300 ,hru AN 18600 AN 73 ,hru AN 81 NAS 333 'hru NAS 340 AN 50900 AN 173 thru AN 186 NAS 583 thru NAS 590 AN 5250 MS 20033 'hru MS 20046 NAS 824 thru NAS 644 MS 270390 MS 20073 NAS 1303 thru NAS 1320 MS 2469400 MS 20074 NAS 172 AN 509 NK9 NAS 174 MS 24694 NAS 517 Steel stlRr bolt AN 525 NK525 MS 27039 NAS 464 NUTS NUTS NUTS Steel Tension S1ft1 Sheer S.'T,nliOn S.ISh. Alum. TenliQn Alum.She. AN 310 AN 320 AN 310 AN 320 AN 3650 AN 3200 AN 315 AN 364 AN 315 AN 364 AN 3100 AN 3640 AN 363 NAS 1022 AN 363 NAS 1022 NAS 10210 NAS 10220 AN 365 MS 17826 AN 365 MS 17826 NAS 1021 MS 20364 MS 17825 MS 20364 MS 17825 MS 20385 MS 21045 MS 210lIl5 MS 20365 NAS 1021 MS 20500 NAS 679 NAS 679 NAS 1291 Nut·bol, Torque Limits Torque Limits Torque LimitS Torque Limit. Torque Limits Torque L iml11 lize in.lbl in·lbl in·lbl in-Ibl in-lbl in·lbl Min. Max. Min. Mu. Min. Mex. Min. Mex. Min. Mex. Min. Mex. 8 -36 12 15 7 9 5 10 3 6 10 -32 20 25 12 15 25 30 15 20 10 15 5 10 1/4-28 50 70 30 40 80 100 50 60 30 45 15 30 5116-24 100 140 60 85 120 145 70 90 40 65 25 40 3/8-24 160 190 95 110 200 250 120 150 75 110 45 70 7116-20 450 500 270 300 520 630 300 400 180 280 110 170 1/Z-2O 480 690 290 410 770 950 450 550 280 410 160 260 9116-1S 800 1,000 480 600 1.100 1.300 850 800 380 !i8O 230 360 5/8-18 1,'00. 1,300 660 780 1.250 '.550 750 950 550 870 270 420 3/4-'6 2.300 2.500 1.300 1.500 2.860 3.200 1.600 1,900 950 1.250 560 880 7/8-14 2.500 3.000 1,500 1 ,BOO 3.550 4,350 2.100 2.&90 1.250 1,100 750 1,200 1 -14 3,700 4,500 2,200 3.300 4.500 5.500 2,700 3.300 1.600 2,400 950 1.500 " 1·1/8-12 5.000 7,000 3.000 4.200 6.000 7.300 3.600 4.400 2.100 3,200 1,250 2.000 1·1/4-12 9,000 11,000 5,400 8.800 11.000 13.400 6,800 B,ooo 3,900 5,IDO 2.300 3,650 • • ..~ ~ RE\'ISED: 11/1/82 IB21 HANDLING AND SER\'ICI~G PIPER COMANCHE SERVICE MANUAL •TABLE 1l~IlA. FLAR E FITTI~G TORQL' ES TORQL'E r\CH-POl: xD Il'HI\,(j AU \lI\l'\1 • ALLOY STEEl. TUBI\G HOSE E\D FITTI\(j OD rtar«: I-TARE -·\\n FLARE A\,D I\CHES IOO(i1 OR "\D /O()1x A\D IOOtd HOSE ASSEMBliES ; I \1 1\,/\1 l' \1 \1AXI\1l'\1 MI\I\1LJM MAXIMl'\1 MI~I\1l'M MAXI\11 \1 i -I ~ I ~ 16 90 100 7(1 I ! I I III I I 4 ~II (is I.l5 ISO 711 1.'11 i 5 16 hi} XII I xn :WO x5 1;>;(1 I J 8 ~5 125 270 Joo 100 ~~(I , I ., 1511 250 ~50 500 210 ~211 I 5 8 200 .lSO flSO 700 JOO ~xO ! iJ 4 I Joo 500 'lUll I(KIll SOO ~50 i I i 50(1 7(111 I I:!OIl 141111 7110 I J 50 , I-I 4 (i00 9110 i I I-I ., (ion 'lOO I I<~ 4 I i 2 I .. ADDED: 4/10/81 HANDLING AND SERVICI. IB22 • • • PIPER COMANCHE SERViCE MANUAL FIGURE ~•• JACKING ARRANGEMENiS HI. j-.=Idn.. nu: airplane is provided with a jack pad OD each n.in spar just outboard of the nWn landing gClt and support position by makinl use of me WI skid. (Refer to FiprI: 2·9.) To jack the airplane. proceed as follows: a. PLac:e the jacks under the jack pads. b. AtUA:h the tail support to the rail skid. PIKe approximately 400 pouDds of ballast on the suppOrt to hold the taU down. CAUTJON Be sure to apply sufficiau WI support ba1lut: otherwise the airplane will tip forward and faU 011. the iuIC. DOse scctio~. c. Raise the jacks C'lealy until aU three wheelscleu the floor. 2·12. Weitbial. (Refer to Fipre 2·10.) a. Block the main ,car oleo saua in there fully exteDdcd posicion abd the nose gear It 2.50 inches extcnsion. Indatc all tires to the required preuura. (Refer to Table II-I.) b. PLac:c the aircarft on three iDdividua.l scales by posiQoaint a ramp of the samc hqht as the sales being used in front of each landinl gearwheel. Position the s.::a1. in front of the ramps and tow the aircra...:r: ontO the scales. (Refer to Paragnph 2·17 for towin. procedures.> Remave the runp so they will not interfere with the swcs. Levd the aircraft per insauetions pYe1\ in Puqraph 2·13. Co Proceed to wCl,h the aircmft in accordance with insuuct:ions Biven in maniaiJ AC 43.13-1A. HANDLING AND SERVICING REVISED: 413na IB23 PIPER COMANCHE SERVICE MANUAL FIGURE 2-10. WEIGHING 2·13. LcvcIiDI. (Refer to Fipre 2-11 and 2,12.) The aircraft may be leveled wbile on jacks or durinl the 'ftichinB procedure. (Ilefer to Panp'apb 2·12 for wGihiDl-) L To lonpaadinally level the aitc:rUt. putiaUy withdraw the twO l~ Krewl on tbc side of the fuacJate. R.cfe to Filum 2-11 or 2-12 for the lneUrlllocuion on lIle pamcular aitc:nft bani serviced. Usc a level lon, eDOulJb to cncnd accrou the twO ICI'e'W badL b. To pUt the aircraft on ja.cks. refer to hnpapb 2-11. c. To put the aircraft in a lonpaadinally level pOliaoD for ..iDa or riainI. first block the mairl JUI' oleo sauD to their full extension and the DOle sear to 2.S0 inches. Non All tires should be at normal idatiOD prasure. Deflate the ROle wbeel tift uti! the lCV'el poaitioll is obtained. d. To lucra.lly lCV'd the airaaft. pl&ce & level over cbc bulkhead to which the bllPF door lUDIC brackets an: attached or on the hat lCClion c1wlDd of me (1NW1ll bulkhead. (Refer to Fipres 2-11 or 2·12 for the panicu1at location of the airaaft bciq serviced.) Should cquipmem or ocher obades binder pl&cint the level directly on the channel. UK two spacers of equalleDp bccwem the Icvelilld the channel to brinl the level above any abRac1es. e. To put the aircraft into a laceral1y level position, raise or Iowa' aile wiJlI by adjulti,. the jacks or if the aircraft is on the Ifound or on scales by deflatiD, the appropriate tire IUnil an lCcun.te level readinc is obtained. HANDLING AND SERVICING REVISED: 4/3/78 1824 • • • eo Al79 PIP£R COMANCHE SERVICE MANUAL A111 ~e;JJW~ _ .. L.at.,.lly e AU9 FIGURE 2-11. LEVELING AIRPLANE PA-24-180. 250. 210. 51,. Noa. 24-4000 1D ZI 4241.24-42"" a-aztIlftd P"2~ \ e FIGURE 2·12. LEVELING AIRPlANE PA.24-2IO. s.n. Nos. 24042'7. 2404300 and u" HANDLING AND SERVICING ADDED:413ns lCl PIPER COMANCHE SERVICE MANUAL •z.t4. MooriDJ. The airplaDe sbowd be moored to insure its immovability. protection &.tid security under various wa.ther conditions. The foUowiDa procedure Jives the iDscructions for proper moonn, of the ~lane. L Had the airplane into the wind. if p-"lc. b. Lock the ailetOll &.tid. Rabilator coacrols \lIiJlI the troDt scu belt or contrOl surflcc blocks. e, Block the wbeels. d. Secure tieo-dOWft ropa to die triDt tie-dowD riap &ad die tail skid at approximately 45~earee antics to the pound. Lewe suffic:icDt sladr. to avoid dam. to the aircraft wbca the ropes contraCt due to moirture. CAUTION Uscsquare or bowlineknoa. Do not II. slip knots. NOTE Additioaai prepantioDS for bitb winds include _. tie-dOWD ropes from the laDdin••ar forks, &.tid sccurin. the nuidcr. e. lftltall pitot tube cover. if pOllible. 2-15. hridIl,. Whca parltinB the &irp1&.tle. insure that it is sufficiendy proteaed apinst advme weather • conditions &Ild pracnG no dUlp!' to other aircnft. Wbea parlUnc the airplane for &Dy lcacm of time or ovcmiIht. it is recommended that it be mo~d u in Puapapb 2-14. a. To park the airplane. bead it into cDe wiDd. if potIiblc. b. Set the parki,. brake by applyin, tow pralllfC apiast the top of the brake pedals or pWl back on the brake lever IDd at the same time pl&1l Ollt on the brake "Too handle. located at the left of the conaol panel. To relcue the paritiDI brake, apply toe prasure on the pedals IIld push in on the parkina brake bandle. NOTE To prewnt dun.lce to brake c:lrum, CU'C should be taken wben sea:int btakcs that are overheated or duriDI cold wacher wben aCCllmulated moisane mayfrene the brake. HANDLING AND SERVICING REVISED: 413/78 lC2 • • • • PIPER COMANCHE SERVice MANUAL 2-16. LodciD, AirpIuJe. The cabin and b••doon are provided 1rith a key lock. The same key can be U$ed to opcnte both door locks. 2-17. Towill.. The airplane may be moved by uUl the nose ....beel tOWiaclsnaq bit pnwided, or power equipment that will not damaF or c:aue ceca n:rai.a to the DOte JCII' IIICIDbly. On PA·24-UO. 250 and 260 alr:n.ft with SaiI1 Numbers 24-4000 to 24-4246. 24004241 to 24-4299 uad PA·24-400 the stCcriDi b. is stoWed OD the uadcrside of the haabdf in dle b•• comparunmt:_ On PA·24-260 Serial Sumbcn 24-4247, 2404299 and up it is anached to the forwvd secUon of the maiD spv CO¥er. CAUTtON Wbm towing with power equipmGlt. do Dot tum the DOse tar beyond ia 20 dqrecs ill either direc1::ion from ccDter. u this will result in ciamaseto the DOIC par uu1StccriDc mcchlDilm. 2-18. TaxDa,. Before mcmpQnI to taXi the airpiaDe, FOUnd pcnoancl should be checked out by a qualified pilot or other responsible person. Enpne sun::iftJ and shut-down procedures should be covered IS wdl. WbeD it is ucertained that the propeller back blut and taXi ueu U'C clear, apply power to start tbe wei roU and perform the foUowinl checks: L Taxi forward a few feft and apply bnkes to dftftmiDc their cffcc:tiwncss. b. Taxi with propeller set in low pitch. biIb RPM seu:iDI. c. While taxiiq. make slisbt tums to ucenain the effeetiWDCII of steerinI. ci. Observe win, clearances when taXiin, ncar buildiDp or ocher atiorwy objccu. If possible. nation a guide outside the airplane to obKr'Yc. e. When taxiinI on uneven ground. look for holes and nns. f. Do not operate the ellline at hilb RPM .heD I"IUlning up or wtiinI over around cODtainiDg loose stones. gravel or any loolC material that may cauJC damq'e to propeller blades. 2-19. Examal Power Rccepadc. 2-20. OpaatiOD of Exmmal Power beepable. The extcmal POWCl' reccpude on PA·2..180. 250 and 260 airpla.nc:s with Serial Numbers 24-2299 to 24-4246 iDduliYe. 24-4248 to 24-4299 inclusive aDd PA·24-400 Serial Numbers 26--2 and up. is located 011 the l'iIht side of dle fulellle aft of 1lUi0D 151. On PA-24-260 airplane with Serial Numbers 24-4247, 24-4300 to 24-4104 aDd up. it is located OD the right side of the engine naceUe JUSt forward of the firewall. Wbeft IlliDI the eXDmW power receptacle for starting or opcntion of a.ny airplane equipment. place the muter switch in die OFF poIitiOD before iDscrting or rcmO'ling the power plug. The power connectOr plUI UlC'mbly isltorcd in the b.....e companmCftt. HANDLING AND SERVICING REVISED: 4/3178 lea PIPER COMANCHE SERVICE MANUAL 1·21. Oeeoi,., 2·22. CaDiaI ED.... CoatpllnlD.~ BeforeclaDinc the eJIIiDe computmalt, place & strip of cape on the D'IIpetO vans to pft'Valt my solWDt from enama, thae llDia. L Place a la.rp pill under the cqiDe to c:ateb WUlC. b. With the CllliDe cowtiJll relDOftd. spray Of' bru" the capae with IOlftJIC or & mixture of solvent aDd d~. IS daimi. It may be nccaary to bftllb aras dw were sprayed wliae heavy paR aDd dirt depOlia havecollected iD order to c1C:&1l than. CAtmON Do Dot spny solftbt iDeo the puaator or altml&ZOr. arter, or lit iDukcs. Co Allow the solve:nt to remain on the c:qjDe hum five to tal IIlUlU_ then rime the cugine clean with additional solVCllt and allow to dry. CAutJON Do not operate cnlJiDe uDtil ezcea solvat hIS evaporued or othcnrilc been removed. d. Remove the protl:c1ivc cowen &om the mapnDl. Co Lubricarc controls. bt:IriDt surfaces, ftc .• pet l.ubricaUOll Cb.c. FilUre 2·20 thru 2·22. 2·23. aaaiDs l,andiDI Gar. Before c1euUD1 the landinl par. place & plutic cover or similar malerial over the wheeland blUe usembly. a. Place a pan under the acu to catch wate. b. Spray or brush the par area with sotveDt or & mixmrc of solvent and d~. IS daiNd. 1t may be necesury to brush areu mal were sprayed wheft heavy sreuc aDd din: deposia have collected in order to clean them. c. Allow the solvent to remain 00 the aar fonn me to ten miDutcs. then rinse me gear with additional solvent and aUow to dry. d. Remove the cover from the wheel and remove the catCh pUl. e. Lubricate me 'eu' per lubrication Cb8't., Fipre 1·21. 2·24. CaD.. Exlaior 5..... ne airplane sbouid be wIShed with & mild soap and warcr. harsh abruive or alkaline soaps or detaplCC5 uKd OD paiDted or pluac surfaces could make scratches or calise cOn'osion of meal S1Irfac:CS. C""cr areas whece daN", solutioo could C&1lIC damatc. to WISh the air?lanc. the foUowin, procedure may be used: CAunON When hosing down aircraft avoid directinl water in the fuel tank vents. drain tubes and around the sealed cover plates and filler ,cap access openinp. HANDLING AND SERVICING Revised: 9 10 79 lC4 • • • • • • PIPER COMANCHE SERVICE MANUAL a. Flush away loose dirt with water. b. Apply cleaning solution with a rag. sponge or soft bristle brush. c. To remove stubborn oil and grease. use a cloth dampened with naptha. d. Where exhaust stains exist. allow solution to remain on the surface longer. e. Any good automotive wax may be used to preserve the painted surfaces. Soft cleaning cloths or chamois should be used to prevent scratches when cleaning or polishing. A heavier coating of wax on the leading surfaces will reduce the abrasion problems in these areas. 2-25. Cleanine Windshield and Windows. a. Remove dirt. mud. etc.. from exterior surface with clean water. b. Wash with mild soap and warm water or an aircraft plastic cleaner. Used a soft cloth or sponge using a straight rubbing motion. Do not harshly rub surfaces. c. Remove oil and grease with a cloth moistened with kerosene. NOTE Do not use gasoline. alcohol. benezene, carbon tetrachloride. thinner. acetone. or window cleaning sprays. d. After cleaning plastic surfaces. apply a thin coat of hard polishing wax. Rub lightly with a soft cloth. Do not use a circular motion. e. A servere scratch or mar in plastic can be removed by using jeweler's rouge to rub out the scratch. Smooth both sides and apply wax. f. Ta improve visibility through windshield and windows during flight through rain. a rain repellent such as REPCON should be applied to the windshield and windows. The surfaces of the windshield and windows treated becomes so smooth that water beads up and readily flows off the surface. Apply this product in accordance with the manufacturer's instructions. 2-26. Cleaning Headliner. Side Panels and Seats. a. Clean headliner. side panels and seats with a stiff bristle brush and vacuum where necessary. b. Soiled upholstery, except leather. may be cleaned by using an approved air type cleaner or foam upholstery cleaner. Carefully follow the manufacturer's instructions. Avoid soaking or harsh rubbing. CAUTION Solvent cleaners require adequate ventilation. c. Leather material should be cleaned with saddle soap or a mild soap and water. 2-27. Cleaninl Carpets. Use a small whisk broom or vacuum to remove dirt. For soiled spots. use a non-inflammable dry-cleaning fluid. 2-28. Servicing. 2-29. Introduction to Servicinl. Servicing the airplane includes the replenishment of fuel. oil, hydraulic fluid. tire pressures, lubrication requirements and other items required to completely service the airplane. HANDLING AND SERVICING REVISED: 4/10/81 lC5 }·)O. Landing Gear System, PIPER COMANCHE SERVICE MANl'AL •2-) I. Senicinx Landing Gear. The landing gear consisting of tires. brakes. oleo strut assembly. drag links. do" n loeb and gear doors should be visually inspected to determine proper strut extension. possible hydraulic tluid leakage, security and condition of all related components. Minor service is described in the following paragraphs. and detailed service and overhaul instructions are listed in Section VI. MAIN FIGl'RE 2·13. LASDING GEAR STRl'T (EXPOSl'RE) ::!-:~::!. Oleo Struts. 2-~~. Servicing Oleo Struts. The air-oil type oleo strut should be maintained at proper strut tube exposures for best oleo action. (Refer to Figure 2-13.) These measurements are taken with the airplane sitting on level surface under normal static load. (Empty weight of airplane plus full fuel and oil.) If the strut has less tube exposure than prescribed. determine whether it needs air or oil by rocking the airplane. If the oleo strut oscillates with short strokes (approximately one inch) and the airplane settles to its normal position within one or two cycles after the rocking force is removed. the oleo strut requires inflating, Check the valve core and filler plug for air leaks. correct if required. and add air as described in Paragraph 2-35. If the oleo strut oscillates with long strokes (approximately three inches) and the airplane continues to oscillate after the rocking force is removed. the oleo struts require fluid. Check the oleo for indications of oil leaks. correct if required. and add fluid as described in Paragraph 2-34. For repair procedures of the landing gear and or oleo struts. refer to Section VI. WAR~I~G Deflate strut air pressure before disassembly. REVISED: 4/3/78 lC6 HA!'iDLISG A!'iD SER\'ICl. • • • PIPER COMANCHE SERVICE MANUAL 2·34. FiI1iDI Oleo Strua. To 6U the nose or main ,ar oleo saut with fluid (MIL·fH606), whether it be only the additiol1 of I small amount or if the unit has been completely emptied and will require I largc amount, it should be filled as follows: WAANING Do not release air by removint the mgt valve core or filler plq. Depras thc valve core pin wu:il stnlt chAmber plelalre bu diminished. CAUrtON Dirt Uld foreip partida form around the filler piup of me landirc ,eu struts. therefore. before attemptillJ to mnove mae piup. me tops of the struts should be cleaned with compraRCI air a.adJor 'Nidi a dry type solvent. a, Place the airplane on jacks. (Refcno Jackinl. Parapapb 2·11.) b. Placc a pan under tbe acar to catch spillqe. c. At the filler plUJ. relievc air prellUrc from the saut housin, chamber by ranovinJ the cap from the air valve and depraaiq the valve core. d. There are twO methods by which the stNt chuabcr may be fUled and these ate u follows: First Method: 1. Remove the valve core from the filler plua at the top of the DOR Jar strut housirc or at the tOP inboard side of the main ,car housing. Allow thc filler pllll to razap insaJJed. 2. Amc:b one end of a clean plutic hose to the valve seem of the 6Uer pluS and submCl'Jc the other cnd in a cOllwncr of hydraulic fluid. NOTE An air-alht COftllectioll is nccaury bccwccn the plutic Nbc aDd the valve sum. Without such a connection, a small aDlOUllt of air will be sucked into the oleo strut durinl aeh sequacc, rclUltinl in an inordi.D..ue uaount of air bubbles Uld .. proloapd flllinJ operation. 3. Fully compress and exrcnd the saue thus drawifta fluid from the fluid coallUncr and expdlil'll air from the smn chamber. By watchilll the fluid pus throup the plutic hose. it can be determined when the strut is full and no air is present in the chamber. 4-. When air bubbles cease to flow throqh the hose. compress the strut fully and remove the hose from the valve stem. 5. With the strut compreslCd. remove the rl1lcr plUJ to determine that the fluid level is visible up to the bottom of the filler holc. HANDLING AND SERVICING REViSED: 413/78 lC7 PIPER COMANCHE SERVlCE MANt:AL 6. With the oleo strut fully compressed. reinstall the core in the filler plug and the plug in the s. housing and tighten. - Second Method: I. Remove the filler plug from the top of the nose gear strut housing or at the top inboard side of the main gear housing. 2. Raise the strut piston tube until it is fully compressed. J Pour fluid from a clean container through the filler opening until it reaches the bottom of t he filler plug hole. (Air pressure type oil container may be helpful.) 4. Install the filler plug finger tight. and extend and compress the strut two or three times to remove air from the housing. 5. Remove the filler plug. raise the strut to full compression and fill with fluid if needed. 6. With the oleo strut fully compressed. reinstall filler plug and tighten. e. With the airplane raised. retract and extend the gear strut several times to ascertain that the strut actuates freely. The weight of the gear fork and wheel should extend the strut. f. Clean off overflow of fluid and inflate the strut as described in Paragraph 2-35. g. Check that fluid is not leaking around the strut piston at the bottom of the housing. 2-35. Innating Oleo Struts. After making certain that an oleo strut has sufficient fluid. attach a strut pump to the air valve and inflate the oleo strut. The gear struts should be inflated to provide correct extension with normal static load. (Empty weight plus full fuel and oil.) (Refer to Figure 2·13.) Rock the airplane several times to ascertain that the gear settles back to the correct strut position. (If a strut pump is not available. the airplane may be raised and line pressure from a high pressure air system used. Lower the airplane and while rocking it. let air out from the valve to bring t he strut down to t he proper extension.) Before capping the valv e. check for valve core leakage. 2-36. Brake System. •2-37. Servicing Brake System. The brake system incorporates a hydraulic fluid reservoir through which the brake system is periodically serviced. Fluid is drawn from the reservoir by the brake cylinders to maintain the volume of fluid required for maximum braking efficiency. Spongy brake pedal action is often an indication that the brake fluid reservoir is running low on fluid or air in the system. Instructions for filling the reservoir are given in Paragraph 2-38. When necessary to repair any of the brake system components. or to bleed system. refer to Section VI. 2-38. filling Brake System Reservoir. (Refer to Figures 2-14 and 2·15.) The brake system reservoir should be filled to the level marked on the reservoir. with the fluid specified in Table II-I. 2-39. Draining Brake System. To drain the brake system. connect a hose to the bleeder fitting on the bottom of each main gear brake assembly and place the ends of the hoses in suitable containers. Open the bleeders and slowly pump the brake lever or brake pedals until fluid ceases to flow. To clean the brake system. flush with denatured alcohol. REVISED: 4/3/78 lC8 HANDLING A~D SERVICI. ... r.. l,.... -- -- _ j (·1 -- ---;,.- - - -- - --~---- - - --~- - 7 - ---- PIPER COMASCHE SERVICE MANl"Al • • FIGt'RE 2·14. BRAKE RESERVOIR PA·24-180 and PA-24·2S0. Serial !'ios. 24·1 to 24-2298 inclusive FIGt:RE 2~IS. BRAKE RESERVOIR PA·2....180 and PA·24-2S0. Serial Nos. 2....2299 and up. PA·2....260 and PA~24-400 2-40. Tires. 2·41. Servicing Tires. The tires should be maintained at the pressure specified in Table Il-l. When checking tire pressure. examine the tire for "ear. cuts. bruises and slippage. 2-42. Power Plant, • 2-4~. Servicing Power Plant. Regularly check the engine compartment for oil and fuel leaks. chafing of lines. loose wires and tightness of all parts. For cleaning of the engine compartment. refer to Paragraph 2-22. Maintenance instructions for the Power Plant may be found in Section VII thru vile of this manual and in the appropriate manufacturer's manuals. REVISED: 4/3/78 lC9 HASDLlNG ASD SER\'ICI:"OG PIPER COMANCHE SERVICE MANUAL 2-44. Propell&r. 2-4'. SerYiciaI Propeller. The propeller blades. spillner IIId viIibIc bub surfaca should be claDed and iDspecteci frequelldy for dunaF. c:ncks and oilleabp. Nicki mould be rcmOftd from the ladiaJ edae of the blada ill accordUlce with applicable 'AA rep1adoaa or illlUUcacn. foulld ill 5cc1:ioas VII dlm VUe. The face of each blade should be pUnted wbal nec-.ry tricb • flat pline: to reard Jl&re. To prevent corrosion. wipe sudaces with • liFe: oil orwu; The bIada sboult becbedred tbat they turn freely on the bub pilot tube by rockin, die bladea back aDd form dlroap. die stiPt freedom allowed by me pitch chanp mechaailm. Lubrieue the propeller at 100 bout iD..... ill accordIIIcz with the L1abricadon Chut. 'ilures Z·20 thN 2·22. AIcenain propeUcr is chilled to die proper c:.baanbc:r pressure. AdditionaJ. service information for die propci1cr may be found in SecDons vn thra vne. Z-46. lDducDoQ Air Fater. Z-47. ScmcialladuClioD Air FU•. Due to the 'lViftY of power plana ued on the various PA·Z4 model U'planes. refer to the Power Plant Section (VII dmI VIIO for the puticular iDdue:tion airfiltcr heine serviced. • 2-48. Fuel Synems. 2-49. FiDinI FuII!:l Taub. Observe all requited precautions for baacllinl pIOline. Fill the fud tanks with • fuel specified in Table 11-1. On the PA·Z4-1'0. to obtain the saadanl fuel quuacity of,O ,allons total, or 2' pUOQl per tank. the cells are filled only to me bottom of the filler neck. which cxc:ends into the fuel cell about 1 inch. To obtain the SWldard plus mcrvc quam:ity of 60 pIloas. the cd1s are filled to the tOP of the filler neck. On the PA-Z,..Z50and PA·Z4-Z6O, to obtain the ftIDdud fuel quantity of 60 gaUons total. or 30 pllODS per tank, the fuel cells arc complerdy 6lled. if auxiliary fad cells are insu11ed (15 pl. ea.) the fuel quantity is incrcued to 90 pUons. On the PA'24-400, to obtain stilldard fuel quantity of approximately 100 pUons, 6I1 both inboud cells completely and the outboard cells I.IDtiJ fuel appears at the bottom of each fuel cell when 'ppcarinI throup me fsUer neck. To obuin standard plus reserve. 130 gallons. fill the outboard cells completely. CAUTION Accumalation of water in the fuel tanks could cause rouah engine operation or complete power loss if the water freezes during cold weather operation. Therefore. to keep condensation in fuel tanks at a minimum. refuel the aircraft after each flight. HANDUNG AND SERVICING Revised: 9 10 79 lelO • • PIPER COMASCHE SERVICE MANl"AL • FIGt'RE 2·16. rttt, STRAINER AND DRAIN PA-2+180 and PA-2+250. Serial Nos, 2+2299 and up. and PA·2+260 FIGt:RE 2·17. FrEL SELECTOR AND DRAIN PA·2+400 • 2-50. Draining Fuel Vain and Strainers. a, On PA-:!4-180 and PA-24'::!50 aircraft bearing Serial ~os. 24-1 to 24-2298 inclusive. the fud strainer. equipped \\ ith an easy drain valve is mounted under the right forward section of the fuselage, The fuel strainer drain (Figure 2·16) on PA-24·180 and PA-24-250 aircraft bearing Serial ;\os, 24-2299 and up and PA'::!4-260 aircraft is located in the cabin floor just aft of the fuel selector valve and is drained by opening the access door and moving the easy drain valve handle to the aft position, Draining is accomplished within the cockpit. A transparent plastic tube is attached to the drain valve and extends through a hole in the bottom of the fuselage, Flow of the fuel is observed by means of the transparent tube and should cease as observed through tube when the handle is released. On the PA-24-400 (Figure 2-17). the fuel is drained from the cockpit by lifting up the red knob located in t he center of the fuel selector. Thefuel strainer should be drained regularly to check for water or dirt accumulations. b. The procedure for draining the right and left tanks and lines is to open the easy drain valve for a few seconds with the fuel tank selector valve on one tank. Then change the fuel selector to the opposite tank and repeat the process. allowing enough fuel to flow out to clear water from the fuel line as well as the fuel strainer. The same procedure will apply when auxiliary fuel cells are installed by simply selecting the right and left auxiliary fuel tank, ~OTE During cold weather operation. if the sediment bowls drain slower than normal or not at all. it could be an indication of ice at the drain and the aircraft should be hangered to thaw out. and drained thoroughly. REVISED: 9/10/79 ten HANDLI!'lG AND SERVICING PIPER COMANCHE SERVICE MANt:AL 1·51. Draining Fuel System. Drain the fuel from the system by opening the drain valve at the bottom of.fuel strainer bowI. or removing the bowl. 1-52. Electrical System. 2-53. Servicing Electrical System. Servicing the electrical system involves adding distilled water to the battery to maintain correct electrolyte level. checking cable connections and checking for any spilled electrolvte that would lead to corrosion. The securitv of all electrical connections should be checked a- well as the operation of all lights. general condition of 'generator or alternator and starter. All electrical wires should be inspected for chafing and bare wires. For detailed information on this system. refer to Section IX of this manual. 1-54. Ox~'gen System. • 1-55. Description of Oxygen System. The oxygen system for the PA-24 consists of an oxygen c~ linder and regulator. filler vain. pressure gauge. outlets and masks and an 0]'\ OFF control mounted on the instrument panel. The stationary cylinder is located aft of the baggage area on the left side ofthe fuselage. The cylinder used is an ICC or DOT 3AA 1800 classification with a 63 cubic foot capacity at a working pressure of 11'00 psi. High pressure oxygen is routed from the cylinder and regulator to the pressure gauge mounted in t he upper ponion of I he aft cabin bulkhead. Low pressure oxygen is routed from the cylinder and regulator to the OUI Jets and masks whenever the control knob is pulled to the O~ position. Each outlet has a spring loaded valve which prev ents the now of oxygen until a mask hose is engaged into the outlet. 2-5tl. Troubleshooting. Troubles peculiar to the oxygen system are listed in Table II-V along \\ ith probable causes and suggested remedies. 2-57. Ox~'gen System Safety Precautions. The utmost care must be exercised in servicing. handling and inspection of the oxygen system. Comply with the following precautions: a. Keep all oxygen system components free from oil. grease. gasoline and all other readily combustible substances. b. Do not allow foreign matter to enter the oxygen lines. WAR~I~G The presence offoreign matter in the high pressure lines can cause an explosion. When coming in contact with oxygen equipment keep hands. tools and clothing clean - hospital clean. HANDLI!I\G ASD SERVIn. icuREVISED: 11 /1/82 c. "ner attempt to repair or repaint oxygen equipment. d. Keep fire and heat away from oxygen equipment. Do not smoke while working with or near oxygen equipment. and take care not to generate sparks with carelessly handled tools when working on the oxygen system. e. Never allow electrical equipment to come in contact with the oxygen cylinder. f. Lse Ribbon Dope Thread Sealant (Perrnacel 412) on male ends of fittings only. Wrap thread in direction of thread spiral. beginning with the second thread on the fitting. Avoid getting any sealant mto the lines. • • • PIPER COMANCHE SERVICE MA~l'AL TABLE 1I~1I1. I\OICATEO OXYGE\ CYU\OER PRESSl"RES FOR GIVE' AMBIE~T TEMPERATURES I\OICATED CYU\OER PRESS. TE~IPERATl'RE OF PSI 110 19~O 100 19].5 90 1890 SO IK45 70 \tWO 60 1155 50 1710 40 1665 2-5R. Filling Oxygen Cvllnder, The filler valve for the oxygen system is accessible through a door located on the left side of the fuselage just aft of the rear window. a. To fill th, oxygen cylinder. open the access door. remove the cap from the filler valve and attach the filler ho .... e from the oxygen recharge unit to the filler valve. Ascertain that all fittings are free from oil. grease. dirt. etc. \OTE If the airplane's oxygen cylinder pressure is below 50 psi. the system should be purged as descri bed in Paragraph 2~ 71. b. To obtain the correct filling pressure for the oxygen cylinder at various ambient temperatures a chart ha .. been included for your convenience. The pressures given are not exact. but sufficiently accurate for pract ical purposes of \\ orking pressure between 1800 and 2400 psig cylinders. The cylinder should be a 110\\ ed to cool to a .... tabilized temperature after filling before checking against the figures given in Table It-III. c. When using a recharge unit consisting of one supply cylinder. slowly open the valve of the supply unit and allow the oxygen to transfer. d. When using a recharge unit consisting of two or more supply cylinders (cascade storage systerm, it i.. recommended that the following procedure be used: REVISED: 4/3/78 icu HA~DLI~G A~D SERVICI~G PIPER COMANCHE SERVICE MANt"AL I. Before opening any valves, check the pressure remaining in the airplane's oxygen cylinder.• i" st ill pa nlv cha rged. note the pressure indicated on the cylinder gauge. Then open and close each \ alve on th, ca ... cadc storage ... ~ ... tern and determine which cylinder has the lowest pressure. When found. if this cylinder has a pressure lower than the oxygen cylinder in the airplane. do not attempt using it forfilling. Lse the storage cylinder that has a pres!>urc higher than the airplane's cylinder but lower than the others. "'l Open the valve on only the one storage cylinder with the lowest pressure. When the pre-sure indicated on the airplane's oxygen gauge and charging gauge has become equal. close the valve of the ... torage cylinder. then go In the storage cylinder with the next higher pressure and repeat the procedure. J. If. after using the last storage cylinder. the airplane's oxygen system is still not fully charged. a full storage cylinder should be put in place of a cylinder with the lowest pressure and used in the same manner. 4. A good deal of oxygen will remain in the large cylinders used in the cascade system after filling only one of the c~ linders, but such remaining oxygen will be at a pressure something less t han the 1l<00 pound "I. which i"l not sufficient pressure to completely refill another aircraft cylinder. although it will refill ..evcral smaller cylinder... 5. It is not economical, even on a three or four-cylinder cascade system. to begin recharging w ith oxygen at b ... than .'\00 psi pressure in the 300 cubic foot bank of cylinders. So. use JOO cubic foot cylinder... dow n In approximately JOO psi. then return for refilling. In two-cylinder systems. use to approximately 600 pvi, then return for filling. C'. When the pressure gauge on the recharge unit or in the airplane reaches 1800 psi. close the pressure regulator valve on the recharge unit. Disconnect the filler hose from the filler valve. replace the protective cap on the filler valve and close the access cover. Check cylinder pressure against chart after cylinder temperature ... tabilize .... 2-59. Inspection and Overhaul Time Limits. It is recommended that inspection and overhaul be conducted b~ an FA.-\ Approved Station of the manufacturer. Scott Aviation. The following checks and chart gi.recommended inspection and overhaul time for the various parts of the oxygen system. a. ThC' oxygen c~ tinder can be identified by the ICC or DOT identification stamped on the cylinder. The standard wciuht cvlinder lice or DOT :lAA 1800) must be hvdrostatic tested at the end of each 5 vear period. The tight\~eigh't cylinder (ICC or DOT :lHT 1850) must be tested every 3 years. The month and vear of the la... t test is stamped on the cylinder beneath the lec or DOT identification. h. The outlets should be checked for leakage both in the non-use condition. and for leakage around an inserted connector. c. The high pressure gauge may be checked for accuracy by comparing its indicated pressure with that of a uauue of known accuracv. d. ~I nspection of the regulator may be effected by introducing into an outlet a mask connector to which is attached a 100 psi gauge. With one other outlet flowing through a plugged in mask. the indicated regulator output pn:"... urc ... hall he not less than 45 psig at sea level with 200 psig supply cylinder pressure. It should be noted that the permissible leakage through the I 16 diameter vent hole in the side of the upper regulator hou ... ing i... 10 I;C min. maximum. when the regulator is turned on. There shall be no external leakage any where on the regulator when il is turned off. All fittings shall be leak free. ADDED: 4/3/78 lC14 •HA:'\DLlNG A~D SER\'ICT\G • • PIPER COMAl\CHE SER\lCE MAJi'l"AL TABLE lI-I\'. I:'\SPECT)O~ - OVERHAl'L TIME LIMITS PARTS I"SPECTIO" O\'ERHAl'L Regulator 300 Flight Hrs. 5 Yrs, Pressure Gauge 300 Flight H rs. 5 Yrs, High Pressure Lines 300 Flight Hrs. Low Pressure Lines 300 Flight H rs. Outlets (Cabin) 300 Flight Hrs. 5 Yrs. External Recharge Valve Each Use Replace Every 5 Yrs, Masks Each Use Replace as 'ecessary 2-60. Testing for Leaks. Apply detector fluid type CD-l solution or its equivalent. The solution should he shaken to obtain suds or foam. The suds or foam should be applied sparingly to the joints of a closed system. Look for traces of bubbles. '0 visible